the determination of operational and support

NASA-CR-140626

THE DETERMINATION OF OPERATIONAL ANDSUPPORT REQUIREMENTS AND COSTS

DURING THE CONCEPTUAL DESIGNOF SPACE SYSTEMS / ^v<r ^ £ /

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Prepared for

National Aeronautics and Space Administration

Langley Research Center

under

Grant No. NAG-1-1327

V

Prepared by

Charles EbelingKenneth Beasley

University of Dayton

Engineering Management and Systems Department

300 College Park

Dayton, Ohio 45469-0236

https://ntrs.nasa.gov/search.jsp?R=19920022016 2018-02-13T14:13:05+00:00Z

Table of Contents

List of Figures iv

List of Tables v

List of Attachments vi

Chapter I - Introduction 1Background 1Related Efforts 1Scope of Research 4

Chapter II - Data Sources 5Reliability and Maintainability Data 5Military R&M Data Systems 6Commercial Aircraft R&M Data 9Aircraft Performance and Design Specifications . . . 10Initial Data Base 11

Chapter III - Methodology 16Parametric Analysis 16Computation of MTBM 17Maintainability Estimates . 21Spare Parts Requirements 22Vehicle Turn Times 23

Chapter IV - Analysis and Results 24Preliminaries 24Regression Analysis 26Analysis of Weights and Secondary Variables 27MTBM Equations 31MHMA Equations 36Scheduled Maintenance 39Removal Rates 39Crew Sizes 41Repair Distribution 43

PRECEDING PAGE BLANK NOT FILMED

Chapter V - Implementation 47Introduction 47Modes of Operation 47Additional Input Parameters 50Computations 55Output Report 58Validation 61User Options 63

Chapter VI - Conclusions 64

Bibliography 65

APPENDIXA. AFALDP 800-4 Format A-lB. MODAS Report Format B-lC. Navy 3-M Report Format C-lD. R&M Data Sources D-lE. Data Generation Programs (BASIC) E-lF. Variable Definitions F-lG. Design/Performance/Weight Values G-lH. Dependent Variable Values H-lI. Subsystem Weight Percentage 1-1J. MTBM Regression Analysis J-lK. MHMA Regression Analysis K-lL. POFF Regression Analysis L-lM. Removal Rate Data & Regression M-lN. Abort Rate Data & Regression N-lO. Crew Size Data & Regression O-lP. Scheduled Maintenance Data P-lQ. Learning Curve Data & Regression Q-lR. Technology Growth Data R-lS. R & M Model - BASIC Program Listing S-l

in

List of Figures

1. AF R&M Summary Format 142. Navy R&M Summary Format 153. Mission Profile 484. Driver & System Variables 485. Weight Menu 496. Secondary Variable Menu 507. Calibration Menu - MTBM 518. Calibration Menu - MH/MA 529. Mission Profile Menu 53

10. Subsystem Operating Times 5411. Technology Factor Display Menu 5512. Reliability Report 5813. Maintainability Report 5914. Subsystem Spares Report 6015. Vehicle Turn Time Report 60

IV

List of Tables

1. Aircraft Design/Performance Variables 112. AF/NAVY Aircraft 123. Aircraft Subsystems 2-Digit Work Unit Codes (WUC) 134. WUC to WBS Conversions 255. WUC 11XXX Maintenance Actions 266. Subsystem Weight Equations 287. Secondary Variable Equations 298. Weight Distribution 309. MTBM Equations 32

10. Learning Curve Results 3311. Technology Growth Rates 3412. Critical Failure Rate Equations 3513. MHMA Equations 3714. Percent Off Equipment Equations 3815. Scheduled Maintenance Manhours 3916. Removal Rate Equations 4017. Crew Size Data 4118. Crew Size Regression Equations 4219. Crew Size Probability Distribution 4220. Repair Time Data 4421. Goodness of Fit Tests 4522. Model Validation - F16 6223. Model Validation - C141B 62

List of Attachments

1. USAF APR 66-1 Data

2. Navy 3-M Data

3. AF/Navy Regression Models

4. WUC 11XXX Breakdown Data

5. Removal Rate Data

6. Scheduled Maintenance Data

7. Commercial Data Systems

VI

Chapter I

Introduction

A. Background

This report documents the first year of research conducted by the University of Dayton forthe National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC)under NASA research grant NAG-1-1327. The purpose of the grant is to provide support toNASA in predicting operational and support parameters and costs of proposed space systems.Specific research objectives include: (1) the development of a methodology for derivingreliability and maintainability parameters and based upon their estimates determine operationalcapability and support costs, and (2) the identification of data sources and the establishment ofan initial data base to implement the methodology. Implementation of the methodology isaccomplished through the development of a comprehensive computer model. A third objective,not documented in this report, is to assist NASA in the development of a simulation modelwhich will provide an integrated view of the operations and support of proposed spacetransportation systems.

B. Related Efforts

Several previous studies provide insight and motivation for this research. These studies arediscussed briefly below.

The Supportability Assessment Model (SAM) developed by Rockwell International [21]provided much of the motivation for the development of the parametric equations as part of thisresearch. SAM projects maintenance action rates as a function of the dry (empty) weight of avehicle. Dry weight is considered a surrogate for complexity. This projection is then modifiedby factors which consider the environment (e.g. space vs. ground), technology (developmentyear) and reliability procurement policies (high or low reliability specifications). Using AirForce Maintenance Data Collection (MDC) data (AFM 66-1) pertaining to the C-9A, C-141Aand the C-5A, Rockwell derived a regression equation with maintenance actions per flying houras a dependent variable and empty weight as an independent variable. Predictions from thisequation for estimating spacecraft reliability are then adjusted by an environmental factor derivedfrom MIL-HDBK-217, Reliability Prediction of Electronic Equipment and a technology factorrelated to the development year.

An enhancement to the original Rockwell SAM model is the Reliability/Maintainability(R/M) Analysis Methodology used by Rockwell in assessing the R&M of the Personnel LaunchSystem, Advanced Manned Launch System (PLS/AMLS). [19] This analysis establishedregression equations between unscheduled maintenance actions and vehicle dry weight for severalaircraft subsystems such as avionics, powerplants, electrical, hydraulic, structural and landinggear. Eight different aircraft including a bomber, fighters and airlift (cargo) are used to generateexamples of the correlations obtained between subsystem weight and maintenance actions per

flying hour or per landings. Component removals are computed as a percent of the componentmaintenance actions in order to determine requirements for spares. Both a bottom-up and atop-down analysis is performed using Air Force, airline and orbiter data.

In a discussion on life cycle costing, Earles [7] presents one of the first successfulparametric models for estimating maintenance manhours per flying hour (MH/FH). An estimateof the MH/FH for on-aircraft propulsion is obtained from a regression equation with thethrust/engine and number of engines as independent variables. Five tactical aircraft and the T-38provided the source of data.

Another early study by Harmon, Pates, and Gregor [9] developed maintenance manhoursper flying hour (MH/FH) estimates for tactical aircraft for use during conceptual anddevelopment design phases. Again, using AFM 66-1 data, MH/FH estimating relationships werederived using aircraft design and performance parameters. Using ten tactical aircraft, a database covering maintenance manhours over a 6 month period was developed at the two-digit workunit code (WUC). Different independent variables were selected for each subsystem. Forexample, landing gear maintenance manhours was assumed to be related to kinetic energy andaircraft weight while the fuel system maintenance manhours was related to weight, number ofengines and fuel quantity. Correlations above .90 were reported for each of the examples,however, only 5 to 7 data points (aircraft) were used in the analysis. Technology improvementfactors are given for each WUC but details on their derivations are not provided.

Norris and Timmins [16] present another early study which focused on spacecraftperformance during its orbital life. Component failure rates over time of 57 unmannedspacecraft were analyzed. Both a Duane reliability growth curve and a Weibull hazard ratefunction provided an adequate fit to the data. A decreasing failure rate over time and a four-foldincrease in failures during the first day following launch were observed from the data.

Decreasing failure rates were also reported in a study by Hecht and Florentine [10] andHecht and Hecht [11] which focused on electronic systems of over 300 spacecraft. The studyconcluded that design and environmental causes of failures contributed the most to a decreasingfailure rate. They computed Weibull shape and scale parameters for each of several failureclassifications. Causes of spacecraft failures, their distribution by subsystem and criticality andmission type are also presented. A reliability prediction method is developed for electronicequipment operating in a space environment which is consistent with MIL-HDBK-217.

Peacore [18] discusses some reliability results pertaining to the Air Force's AW ACS (E-3A)system. In flight failure rates were found to be decreasing with flight time which he believesto be characteristic of large multi-engine transport type aircraft. A model, developed by BoeingAerospace Corporation and based upon B-52 data, has high early failure rates which decreaseto a relatively constant rate after 10 hours of flight. The high early failures are attributed toenvironmental stresses during takeoff, failures occurring when initiating (e.g. turning on) andstabilizing equipment, failures undetected during testing, andmaintenance induced failures.

One of the few papers addressing failure time and repair time probability distributions ispresented by Ostrofsky [17]. However, only graphical examples of these distributions areprovided with no results on fitted theoretical distributions reported.

A comprehensive report prepared for the Goddard Space Flight Center (NASA) byBloomquist and Graham [5] describes the study of 44 unmanned orbital spacecraft. In fact, thisstudy is an update of earlier studies conducted by the Planning Research Corporation (PRC)which addressed 350 spacecraft. In addition to providing an extensive data base of the 44spacecraft, the report classified anomalies by satellite mission, subsystem, effect, and incidenttype (e.g. electrical or mechanical). Subsystem survival times were also computed in units ofthe spacecraft design life.

A report prepared by Hughes Aircraft for the Rome Air Development Center [14] addressesdifferences between predicted and demonstrated reliability and the observed field values(primarily MTBF). Prediction models for estimating the field MTBF were derived. The studycontains a detailed description of the Air Force's MDC (AFM 66-1) and D056 data systems.The relationship between predicted and observed MTBF was established using multipleregression techniques. Of interest in this report is the derivation of a "K" factor (equipment usefactor) to account for the differences between equipment flying hours and equipment operatinghours. Equipment operating hours varied from 1.2 to 2.4 times the flying hours depending uponthe aircraft.

Maintenance policies may have a significant effect on the maintenance manhours expendedin supporting a space vehicle. Barnard and Matteson [4] describe a test conducted by the Navyto perform aircraft maintenance similar to that of the commercial airlines. Both scheduledmaintenance manhours and aircraft downtime were significantly reduced while the quality ofmaintenance increased. Similar changes in maintenance policies may be contemplated as NASAtransitions from the Shuttle to the next generation of space transportation vehicles.

C. Scope of Research

This initial effort is limited to the prediction of reliability and maintainability (R&M)parameters and their effect on the operations and support of space transportation vehicles. Thefocus is on the failure and repair of major subsystems and their impact on vehicle turn times,maintenance manpower, and repairable spares requirements. Other system components such asbooster rockets, expendables (e.g. fuels and oxygen), ground support facilities, softwaredevelopment and maintenance, and overhead staff would be subjects for future researchactivities.

Chapter II discusses various sources of R&M data and documents the data utilized in thisstudy. Chapter III develops the general methodology for estimating R&M parameters and forrelating these parameters to the logistics support requirements of the proposed vehicle. ChapterIV presents the analysis and results of applying the methodology to the initial data base whileChapter V describes the implementation of the methodology through the use of a computermodel and provides some validation of the model. The report concludes with a summary of theresearch findings and results.

Chapter II.

Data Sources

The principle approach to be used in establishing R&M estimates of new space systems isbased upon comparability with existing systems. In this regard, many of the subsystems definedfor manned space vehicles may be favorably compared to corresponding aircraft systems.Therefore, a primary source of data to support this analysis are commercial and military aircraftfailure and repair data.

A. Reliability and Maintainability Data

Data requirements consist of the following R&M data pertaining to all relevant aircraftsubsystems.

The primary R&M data are:

(1) Mean time between maintenance (MTBM). This is defined to be the length oftime in flying hours between maintenance actions on a particular subsystem or component. Onlyunscheduled maintenance actions are included. A distinction is made between maintenanceactions and failures. Maintenance actions include inherent failures (internal subsystem failures),induced failures (external failure causes) and no defect.

(2) Maintenance manhours per maintenance action (MH/MA). This is the primarymeasure of maintainability used in this study. Along with the number of maintenance actionsper mission (obtained from the MTBM), it becomes the basis of the maintenance cost estimates.

(3) Maintenance Task Times. The length of time (usually in hours) to perform aparticular task such as troubleshoot, remove and replace, perform minor maintenance, etc. Thismaintainability parameter is usually summarized at the subsystem or component level as theMean Time to Repair (MTTR). In this study, task times are obtained by dividing the MH/MAby an average crew size. Task Times include both on and off vehicle times.

(4) Maintenance crew sizes. The number of maintenance personnel required toperform a particular task. This number may vary depending upon the task, the particularcomponent involved and the skill level of the personnel. An average crew size was determinedby subsystem.

(5) Removal rates (RR). This is the percent of maintenance actions which resultsin a removal and replacement of a component from the aircraft. It is the basis for establishingdemand rates for spare components.

(6) Abort rates (AB). This is the percent of maintenance actions as a result of aground or air abort. This rate is used to establish a critical failure rate which in turn is used tocompute a mission reliability.

(7) Percent off equipment (POFF). This is the percent of the total unscheduledmaintenance manhours performed on components removed from the aircraft. These hours donot delay processing the vehicle. Therefore 1-POFF, or the percent of on-aircraft work, is usedin determining the vehicle turnaround time.

Secondary R&M data which were collected and documentedinclude:

(1) Maintenance manhours per flying hours (MH/FH). This is sometimes referredto as the maintenance index (MI) and may be broken down into off-equipment (aircraft) andon-equipment (aircraft) manhours. When it differs from flying hours, subsystem operating hoursshould be used.

(2) Mean sorties between maintenance actions (MSBMA). This is the averagenumber of sorties flown between unscheduled maintenance actions.

B. Military R&M Data Systems

(1) US Air Force data systems

Reliability and maintainability data for USAF aircraft originates with the MaintenanceData Collection (MDC) system as described in AFM 66-1. This data is collected at the base(squadron/wing) level (AFTO Form 349) and transmitted periodically to AF Logistics Command(AFLC). AFR 65-110 data (aircraft status reporting) reports flying hours and sorties for thesame bases monthly. The D056 Product Performance System processes this data producingseveral R&M reports. D056 also provides data to the Maintenance and Operational Data AccessSystem (MODAS) for on-line viewing and retrieval. AFALD Pamphlet 800-4, AircraftHistorical Reliability and Maintainability Data summarizes the worldwide R&M data at thetwo-digit work unit code (WUC) in 6-month intervals (see Appendix A for an example ofAFALDP 800-4 data). Currently Volumes I through VI covering the years 1972 through 1989have been published.

The current Office of Primary Responsibility (OPR) for AFALDP 800-4 isALD(AFLC)/LSR, Wright-Patterson AFB, Ohio. However, with the consolidation of AFLCand the Air Force Systems Command (AFSC) scheduled for July 1992, this office may no longerexist. With the eventual implementation of REMIS (Reliability and Maintainability InformationSystem), the D056 system along with MODAS will also be eliminated. It is not certain at thistime what the final configuration and capabilities of REMIS will be.

The MOD AS system (G063) is currently sponsored by AFLC/MMES, Wright-PattersonAFB, Ohio 45433. MOD AS provides the user with access to various data bases through aninteractive menu driven system. It is a Data Base Management System (DBMS) with someautomated analytical capability. R&M information may be displayed by aircraft (MDS), WUC,level of WUC, base and by month. Examples of MODAS reports may be found in AppendixB.

In addition, to the above systems, a unique representation of aircraft R&M data exist inthe form of Logistics Composite Model (LCOM) data bases. LCOM is a computer simulationmodel which simulates the operation of a squadron or wing of aircraft with random failurestimes and repair times of aircraft subsystems and components. LCOM data bases exist for mostof the aircraft in the Air Force inventory although many of these data bases are several yearsold. This data is unique in that the failure times may be based upon several years of (AFM66-1) data and repair times and crew sizes are often based upon field audits conducted at theunit's themselves. This data, which is usually collected at the 3 or 4 digit WUC level, is arefinement of the MDC data. LCOM data bases may be obtained from ASD/ENSSC,Wright-Patterson AFB, Ohio. LCOM data bases were not used in developing the parametricequations because of the more readily available and more relevant MODAS and AFALDP 800-4data.

(2) US Navy

The primary source of R&M data pertaining to Navy aircraft is the Aviation 3-MInformation reports. The Navy Maintenance Support Office (NAMSO), is the central data bankfor Aviation 3-M data (Maintenance and Material Management system). NAMSO is part of theNaval Sea Logistics Center. Although preformatted reports are published monthly, quarterlyand annually, and are available on request, a potential user may also request the developmentof a new report. Most reports can be obtained on either hard copy or microfiche. Magnetictape may be obtained under a special request.

The following R&M reports have been identified as relevant to this research. Examplesof each report may be found in Appendix C.

Report Title Report Number

Reliability and Maintainability Summary NAMSO 4790.A7142-01WUC System R&M Summary NAMSO 4790.A7142-02R&M Summary for selected WUCs NAMSO 4790.A7142-03R&M Trend Analysis Summary NAMSO 4790.A7142-045-Digit WUC R&M Trend Analysis Summary NAMSO 4790.A7142-05R&M Summary for Selected Equipments NAMSO 4790.A7298-01

The R&M Summary Report provides data similar to that available from the MODASsystem. Summary statistics are reported by aircraft type at the 5-digit WUC and include meanflying hours between maintenance actions, maintenance manhours per flying hour, maintenancemanhours per maintenance action, and elapsed maintenance time per maintenance action.

Of particular interest in this research is the WUC System R&M Summary. This reportprovides mean flying hours between maintenance actions, maintenance manhours per flyinghour, maintenance manhours per maintenance action, and elapsed maintenance time permaintenance action by system level WUC (2-digit) for all appropriate aircraft. Similar R&Minformation is provided in the R&M Summary for selected WUCs. However, this report is atthe 4-digit WUC and pertains only to engines and avionic components.

The two trend analysis reports provide MTBF and MH/FH information at the 4-digit and5-digit WUC respectively. Multiple time periods may be displayed to produce trend data, anda comparative failure ranking of the WUC relative to all WUCs for the aircraft is computed.

The final report, R&M Summary for Selected Equipments, allows for R&M data to bepresented at the 2nd and 4th level WUC by activity. This report would not add any newinformation not already available on the other reports other than the activity breakdown.

(3) Reliability Analysis Center

The Reliability Analysis Center (RAC) is one of 21 DOD Information Analysis Centers(IAC). It is operated by IIT Research Institute in Rome, New York. As an IAC, RACmaintains data bases and studies concerning component reliability particularly that of electronicsystems. The Center also conducts special studies, publishes newsletters, and offers trainingcourses. In general, the items contained in RAC's data bases are individual parts rather thanan entire component. Therefore, this data was not used in this research.

C. Commercial Aircraft R&M Data

Commercial data sources were investigated but not used in developing the initial database for reasons discussed below. However, examples of the reports and types of data availablefrom these sources is documented in Attachment 8.

(1) Federal Aviation Agency (FAA)

Commercial sources of R&M data include both the airlines and the aerospacecontractors. In addition, the Federal Aviation Agency (FAA) in Oklahoma City maintains a database consisting of component failures by Airline Transport Association (ATA) code whichcorresponds to the military's WUC. The data base is very detailed with significant variabilityin reporting by the individual airlines. A narrative on each incident is included, but there is noquantitative data for estimating MTBF or MTTR. This data is of limited use since there is nopractical way to obtain failure rates or times of failure without additional information.

(2) Commercial Airlines

Each airline maintains R&M data in a form useful to them. However, they onlymeasure reliability in terms of failures which cause schedule delays (usually of 15 minutes ormore) or aborts. Therefore total maintenance activities are generally not captured in their datasystems. R&M reports from three different carriers were obtained and analyzed for theirrelevance to this research. Because of major differences in reporting compared to the militarydata systems, it was concluded that this data would be of very limited use. For example, USAirproduces a monthly reliability assurance program report [22] which focus schedule departuredelays and cancellations. Flying hours between events and maintenance hours are not reported.

(3) Aerospace Contractors

Examples of the type of data maintained by the major aerospace corporations may befound in Attachment 7. These contractors are dependent upon the airlines for reporting failuresand, as a result, their reports focus on those events which significantly affect scheduled flightsresulting in delays (again exceeding 15 minutes), cancellations, diversions, and air turn backs.While this information is very useful in identifying problem areas, failure times cannot becomputed from this report. For example, scheduled interruptions are Boeing's major measureof reliability. They maintain very little data on MTBF, MTTR or maintenance MH/FH.McDonnell Douglas maintains a Data Exchange Program which reports various reliabilityinformation which is then provided to commercial aircraft customers. Information contained inthis report is obtained from participating airlines. Like the Boeing report, it focuses on eventswhich result in excessive delays and cancellations. However, a component removal summarycontains some MTBF information.

(4) Other Sources

A secondary source of reliability data consists of subcontractors involved in themanufacture of particular aircraft subsystems and components. For example, HughesCorporation which, among other things, makes radar systems for various aircraft. We were ableto obtain the system specifications and reliability test results on four of their radar systems. Asadditional information like this on other radar sets is obtained, a parametric estimation of MTBFis possible. We have requested similar input from other subcontractors including HarrisCorporation (digital map generators, global positioning system) and E-Systems (electronicsystems). This level of detail may be beneficial during the follow-on effort when componentlevel R&M analysis is anticipated.

Other sources which had been pursued include Airbus Industries (Europe), The Society ofAutomotive Engineers (SAE) which has published a guidebook on rocket booster reliability, theAeronautical Systems Division (Air Force Systems Command) concerning a comparative studyon competing radar systems, and the Air Force Logistics Command's Reliability andMaintainability Information System (REMIS). Some of the information gathered is beyond thescope of this task and has not been incorporated into this report.

Various points of contact for the data sources identified above are summarized in AppendixD.

D. Aircraft Performance and Design Specifications.

In addition to R&M data, aircraft performance and design specifications (Table 1) werenecessary to support the parametric analysis. A primary source of this data for military aircraftwas a technical report titled "Modular Life Cycle Cost Model for Advanced Aircraft SystemsPhase HI," prepared by the Grumman Aerospace Corporation [15] for the Flight DynamicsLaboratory, Wright-Patterson AFB, Ohio. This report documents the data base used indeveloping a life cycle cost model for the proposed aircraft.

10

Table 1Aircraft Design/Performance Variables1

(Potential Drivers)

VEHICLE DRY WEIGHTVEHICLE LENGTHWETTED AREAVEHICLE WING SPANFUSELAGE VOLUMESUBSYSTEM WEIGHTSFUSELAGE SURFACE AREALANDING DISTANCECREW SIZENUMBER PASSENGERSNUMBER ENGINES

NUMBER INTERNAL FUEL TANKSMISSION LENGTHOPERATING CEILINGNUMBER OF WHEELSNUMBER ACTUATORSNUMBER CONTROL SURFACESMAXIMUM ELECTRICAL OUTPUTNUMBER HYDRAULICS SYSTEMSNUMBER AVIONICS SYSTEMSBTU COOLING CAPACITYAVIONICS INSTALL WEIGHT

The primary source for subsystem weights used in this study was Design Branch of the Plansand Programs Directorate of the Wright Laboratories at Wright-Patterson AFB (WL/XPAD).Secondary data sources included all volumes of Jane's All The World's Aircraft [13], "AviationWeek & Space Technology" [3], and Observer's Directory of Military Aircraft [8].

E. Initial Data Base

The primary source of military R&M data is the Air Force AFM 66-1 Maintenance DataCollection (MDC) system and the Navy 3-M data system. The initial data base consisted of AFMDC data as reported in Volume V (October 1985 to September 1987) of AFALDP 800-4 andNavy data reported in the July 1990 - June 1991 R&M Summary Report. Volume VI ofAFALDP 800-4 (October 1987-September 1989) and the MOD AS on-line system (January1990-December 1991) were secondary sources. AFALDP 800-4 summarizes R&M data at6-month intervals. Four 6-month periods were averaged together in order to provide moreaccurate measures. The Navy data is presented by quarters. Four quarters were averagedtogether also to provide for more accurate MTBM's and manhours. Table 2 lists the 37 AirForce and Navy aircraft used in the study and Table 3 identifies the 26 major aircraft subsystemswhich were included. These subsystems are identified by two-digit work unit codes (WUC).

1 Variable definitions of those used in the models are found in Appendix F.

11

Table 2AF/NAVY Aircraft

TACTICAL BOMBER

A-7D/E B-1B

A-10A B-52G

F-4C/D/E FB-111A

F-5E

F-14A

F-15A/C

F-16A/B

F-18A

F-106

F-111A/D/F

CARGO/TANKER

C-2A

C-5A

C-9A

KC-10A

C130B/E/H

KC-135A

C-140A

C-141B

COMMAND/CONTROL/TRAINER

E-2C

E-3A

EA-6B

T-38

12

Table 3Aircraft Subsystems

2-Digit Work Unit Codes (WUC)

WUCSYSTEM

11

12

13

14

23

24

41

42

44

45

47

49

51

52

55

61

62

63

64

66

71

72

91

93

96

97

SYSTEM NOUN

STRUCTURES/AIRFRAME

EQUIP/FURNGS/CREW COMPARTMENT

LANDING GEAR

FLIGHT CONTROLS

POWER PLANT SYSTEM

AIRBORNE AUXY PWR (APU)

AIR CONDITIONING/ENVIRONMENTAL CONTROL

ELECTRICAL POWER

LIGHTING SYSTEM

HYDRAULIC POWER

OXYGEN

FIRE PROTECTION/MISC UTILITIES

INSTRUMENTS

AUTO FLIGHT

MAL ANLY RECORDING

COMMUNICATIONS

VHP COMMUNICATIONS

UHF SYSTEM

PASS ADDRESS SYS

EMERG LOCT XMTR

NAVIGATION

RADAR NAVIGATION

EMERG EQUIP

DRAG CHUTE EQUIP

PERSONNEL EQUIP

EXP DEV & COMP

13

Figure 1AF R&M Summary Format

OUTPUT RESULTS FOR F-15

TOT FLYING-HRS 172258TOT SORTIES 130501TOT LANDINGS 146896AVG MISSION LENGTH 1.319975

WUC 13

TOTAL MAINTENANCE EVENTS 13223.61TOTAL MAINTENANCE MANHOURS 125632

TOTAL ON-EQUIP MAINT 89678TOTALOFF-EQUIPMAIHT 35954PERCENT OFF EQUIPMENT HRS .2861851

MEAN FLYING HR BTWN MAINT 13.02655MEAN SORTIES BTWN MAINT 9.868786MEAN LANDINGS BTWN MAINT 11.10861MAN-HOURS PER FLY-HR .7293246MAN-HOURS PER SORTIE .9626899

MAN-HOURS PER MAINT ACTION 9.500581ON-EQUIP MAN-HRS/MAINT ACTION 6.781657OFF-EQUIP MAN-HRS/MAINT ACTION 2.718924

ECHO CHECK OF INPUT DATA

PERIOD MTBM ON-EQUIP MH OFF-EQUIP MH

131 9.276 30658 115482 13.707 28229 117073 14.368 16776 69764 16.831 14015 5723

VALIDATION CHECK

PERIOD ON-EQUIP MH/FH OFF-EQUIP MH/FH

131 .7647485 .28805912 .6180946 .25633343 .3967458 .16497974 .3169811 .1294386

14

Two computer programs, written in interactive Microsoft0 BASIC, were utilized for processingthe data. The data was aggregated into two years (AF) or one year (Navy) and various R&Mparameters computed as illustrated in Figures 1 and 2. These programs are listed in AppendixE; the AF processed data is in Attachment 1; and the Navy processed data is in Attachment 2.These data provided the MTBM and MH/MA dependent variable values used in the subsequentregression analysis.

Values for the independent variables (Table 1) and subsystem weights used in the analysisare found in Appendix G. R&M (Dependent) variable values are summarized in Appendix H.

Figure 2Navy R&M Summary Format

OUTPUT RESULTS FOR F-14AWUC 45XXX

TOT FLYING-HRS 92011TOT MAINT ACTIONS 8943TOT MAN-HRS 56868TOT ELAPSED TIME 32224.9

MEAN FLYING HR BTWN MAINT 10.28861MAN-HOURS PER FLY-HR .6180566AVG ELAPSED MAIN TIME 3.603366AVE CREW SIZE 1.764722MAN-HOURS PER MAINT ACTION 6.35894

SUMMARY STATS FOR 45XXX HYDRAULICS/PNEUMATIC PWR

AVG TASK TIME 3.38761AVG CREW SIZE 1.747144

15

Chapter III

Methodology

A. Parametric Analysis

The primary objective is to develop a methodology for estimating reliability andmaintainability parameters for use in life cycle costing, supportability requirements determinationand the assessment of operational capabilities and constraints of proposed space vehicles. Thismethodology utilizes the available data sources identified in the previous chapter. The approachis based upon a comparability analysis with similar aircraft subsystems. By estimating aircraftequipment failure and repair parameters as a function of performance and design specifications,then, with suitable adjustments to account for the differences in operating environment, theR&M parameters of a conceptual space vehicle may be estimated based upon its design andoperating specifications. Adjustments are also necessary to account for technological innovationover time. This chapter presents the mathematical foundation for the analysis performed on thedata base and described in the following chapter.

Parametric R&M equations are derived using regression analysis. In general, let

Y = B0 + Bt Xi + B2 X2 + ... + Bk Xk (1)

where Y = R&M parameter of interest (e.g. MTBF or MH/MA)

and Xj = jth design or performance specification(e.g. vehicle dry weight), j = 1, 2, ... k,

thenB0, BI, ... , Bfc. are the regression coefficients.

These are estimated by performing a least-squares fit of the equation against known paired valuesfor Y and the corresponding X1? X2, ... , Xk obtained from the data base.

The following R&M parameters have been estimated using this approach:

MTBM - Mean Flying Hours between Maintenance Actions

MH/MA - Maintenance Manhours per Maintenance Actions

RR - Subsystem removal rate

POFF - Percent off-equipment (vehicle) manhours

CREW - Average crew size per maintenance task

AB - Abort Rates (Critical Failure Rate)

16

In addition to the above R&M parameters, regression equations were derived to estimatesubsystem weights and design/performance variables (see Table 1) as functions of the vehicledry weight (DRY WT) and length + wing span (LEN+WING). These variables are classifiedas secondary variables while the dry weight and length + wing span are classified as primaryvariables. Using these equations, it is possible to estimate all of the necessary R&M parametersusing only a small number of primary (driver) variables. First subsystem weights aredetermined from the regression equations, then the secondary variables are computed from theirequations, and finally the MTBM, MH/MA and other R&M parameters are estimated from theirregression equations. The latter equations will include subsystem weights and those secondaryvariables which were found to significantly improve upon their prediction capability.

B. Computation of MTBM

An initial MTBM is obtained by subsystem from the derived parametric estimatingequations. The MTBM is in units of operating (flying) hours between maintenance actions andreflects a subsystem operating in an aircraft (air/ground) environment.

(1) Technology Growth Factor

In order to account for increased reliability as a result of technological change over time,a growth factor was computed. First, the learning curve effect on the reliability of a subsystemover time was estimated. The learning curve accounts for engineering changes, modifications,and other reliability burn-in phenomena associated with a system maturing over time. This wasaccomplished by fitting an equation of the form:

MTBM = a T" (2)

where: T = cumulative calendar time or cumulative operating (flying) hours and "a" and "b"are parameters estimated using least-squares.

Next, a technology adjustment factor was found by averaging several pairwise comparisonsbetween aircraft developed during different technology periods but having similar missions andrequirements. An MTBM for both aircraft was obtained from the data set (generally a two-yearaverage value). The MTBM of the newer aircraft was modified using the learning curve growthrate (b) to account for the differences in age between the two systems. That is,

Mod MTBM = a x (1986 - Dev YR Old ACFT)b (3)

where solving Equation (2) for "a" provides:

a = NEW ACFT MTBM/(1986-DEV YR NEW ACFT)b (4)

17

The baseline year of the data is 1986 and the MTBM reflects the baseline year. The "a"parameter defines the units (e.g. operating hours or years) while the "b" parameter describesthe rate of growth.

The adjustment factor was then found by solving the compound growth rate curve:

MOD MTBM = OLD ACFT MTBM x (1+ADJ FAC)AGEDIFF (5)

That is,

ADJ FAC = [MOD MTBM/OLD ACFT MTBM](1/AGEDIFF) -1 (6)

This factor was then used in adjusting the initial MTBM to account for technological growth inreliability between the baseline year of the data and the expected development year of theproposed system. That is

ADJ MTBM = MTBM x (1+ADJ FAC)(yr'1986) (7)

(2) Environmental Adjustment

A further adjustment to the MTBM was then made to account for the change in failure rates(from those of the aircraft air/ground environment) during launch and orbit. During the air(non-booster launch and re-entry phase) and ground phase, failure rates are assumed to beconstant (exponential) with a MTBM based upon the ADJ MTBM defined above. However,during launch under booster rockets, the failure rate may increase dramatically as a result of theincreased vibration and stresses. On the other hand, while in orbit, the failure rate is assumedto decrease over time based upon results found in related work cited in Chapter 1. A Weibullfailure rate function was assumed for this portion of the mission. Previous studies have showna decrease in component failure rates occurring in the somewhat more benign spaceenvironment. Two approaches have been identified to quantify this change. The first is toinclude an environmental factor in the regression model. This would require obtaining historicaldata on comparable components operating in space. This data is quite limited and may beexplored during the follow-on effort. An alternate approach is to make use of the earlierresearch which concluded failure rates in space were decreasing with the Weibull failuredistribution providing a reasonable model. This study utilizes the latter approach.

18

For each subsystem, a mission profile curve was assumed having the following form:

Figure 3Mission Profile

Mission ProfileFailure Rate

Ground Launch OrbitProcessing Booster Time

Recovery

19

This failure rate curve may be expressed mathematically as:

A. ( t) =

A, for 0 <. t < t0for t0 £ t< tj_

A. for ; t< t^(-\ for t, s t< t,a \ a l 2 3

X for t3 ^ t< t4

(8)

where:

K=LAUNCH FACTOR

and a, and b are the Weibull scale and shapeparameters respectively

Since, in general, a reliability function is given by

R ( t)= e - ^ M £ ) d £ (9)

the reliability function may be obtained from (8) using (9):

R(t) = * t -Jb / *•» \ b

-T - -T -^t-^)

forforfor

for

for

(10)

Since the mission profile is repetitive over time, a steady-state MTBM may be computed fromequation (11).

SS MTBM = (11)

20

The use of the Weibull failure distribution in defining R(t) requires a numerical integration tocompute the MTBM from Equation (11). In the implementation of the model discussed inChapter V, Simpson's rule was used to perform the integration.

(3) Critical MTBM

Using aircraft air and ground abort rates (AB), subsystem regression equations were derivedto provide estimates of critical failure rates. A critical MTBM was then obtained from

CRIT MTBM = SS MTBM/AB (12)

A vehicle MTBM is calculated from the subsystem MTBM's using:

VEH MTBM = 1/[1/MTBM! + 1/MTBM2 + ... + 1/MTBMJ (13)

where 1/MTBM; is the failure rate of the ith subsystem.

With critical failure rates replacing 1/(ADJ MTBM), approximate mission reliabilities are foundusing Equation (10) for each subsystem. A Vehicle reliability is computed by multiplyingsubsystem reliabilities (Rj)

Rv* = R ! x R 2 x ... xRk (14)

Equation (14) assumes no explicit redundancy at the subsystem level. Some componentredundancy may be implicitly taken into account by the critical MTBM.

C. Maintainability Estimates

The primary maintainability parameter used in this study is the maintenance manhours permaintenance action (MH/MA). This parameter is estimated from the parametric regressionequations for each subsystem. Then using

TOT MA = 1/(SS MTBM) x OPER HRS (15)

total maintenance actions per mission is obtained and from

TOT MANHRS = MH/MA x TOT MA (16)

total maintenance manhours per mission is found. Manhours are then split into on-vehicle andoff-vehicle manhours using the percent off-equipment hours (POFF) obtained from regressionequations:

TOT ON-VEH MH = (1-POFF) x TOT MANHRS (17)TOT OFF-VEH MH = POFF x TOT MANHRS (18)

21

Maintenance manpower requirements are determined by computing the total manhours of workper month and dividing this total by the number of hours per month available per technician todo direct maintenance work.

Let N = number of mission per month,

AV = available hours per month per individual

IND = percent of indirect work (work not included in the MH/MA)

then,

PER ~

Scheduled maintenance manhours per mission are found by multiplying the unscheduledmanhours by a percentage estimated from a regression equation giving scheduled maintenanceas a percent of the unscheduled maintenance.

C. Spare Parts Requirements

In order to estimate spare parts requirements, it is necessary to distinguish between a failureresulting in a remove and (if a spare is available) replace action versus other maintenance actionssuch as on-aircraft troubleshoot and repair. The MODAS system identifies maintenance actionsby an action taken code one of which is a removal code.

Using regression equations or an estimated mean value, a removal rate (RR) per maintenanceaction was determined and used to obtain the mean number of demands (failures) for spares(MFAIL) per mission as follows:

MFAIL = RR x (TOT MA) (20)

Under the common assumption that the number of failures in a given time period follows aPoisson process, a spare parts level can now be found which will satisfy demands a specifiedpercent of the time. This is the frequently used fill rate criterion which represents the percentof time a demand (failure) can be immediately satisfied from the on-hand stock.

Let S = spare parts level to support a given mission andp = desired percent of time demands are satisfied (fill rate), then find the smallest value for Ssuch that F(S) > = p where

SF(S) = % Exp(-MFAIL) x MFAILj/i! (21)

i=0F(S) is the cumulative probability of demands not exceeding the spares level (S).

22

D. Vehicle Turn Times

In order to determine the time required to perform maintenance on the vehicle, estimates ofaverage repair crew sizes for typical on- vehicle tasks by subsystem must first be obtained. Oncethe average crew size has been determined from regression equations or averages from the database, an average repair time can be obtained by

REPAIR TIME = (1-POFF) X (MH/MA)/AVG CREW (22)

Average on-vehicle subsystem repair time per mission may be found from

MSN REPAIR TIME = TOT ON-VFH MH _ (23)AVG CREW

Assuming all tasks are performed sequentially (a worst case), then total vehicle mission repairtime is the sum of the subsystem repair times:

VEH REPAIR TIME = ^ SUBSYSMSN REPAIR TIME (24)

Scheduled maintenance time may then be added to obtain a total vehicle maintenance time:

TOT VEH TASK TIME = VEH REPAIR TIME + srw MHPS (25)AVG CREW SIZE

Mission time must be included in order to obtain a vehicle turn-around time. Therefore, vehicleturn-around time in working days is:

VEH TURNAROUND = MSN TIME/24 + TOT VEH TASK TIME/8 (26)

Equation (26) assumes a single 8-hour maintenance shift per day. Dividing the vehicleturnaround time into the number of working days per month gives an estimate of the number ofmissions per month per vehicle:

MSN/MO/VEH = wnpinNO HA/MO (27)VEH TURNAROUND

Dividing the required number of mission per month by the number of missions per month pervehicle provides an estimate of the required fleet size:

23

Chapter IV

Analysis and Results

A. Preliminaries

Both Navy and Air Force aircraft were initially selected for deriving the parametricequations. However, Air Force subsystem data was utilized primarily in the current modelbecause it was more comprehensive and consistent. In many cases, there was a significantdifference in failure times between Navy and Air Force systems due, in part, to the morestressful environment found on carrier based aircraft. The first set of R&M equations alsocontained variables such as mission length and maximum ceiling which could not accurately beextrapolated to values representative of space vehicles. Finally, these equation were not weightbased making them difficult to use in those cases where vehicle design had not progressed muchbeyond the determination of subsystem weights. Nevertheless, many of these equations resultedin a good fit to the data (e.g. high R-squared values) and are presented in Attachment 3. Theremainder of this chapter is based primarily upon the Air Force data base presented in ChapterII.

Table 4 identifies the subsystems by military aircraft work unit code (WUC) and shows themapping of WUC's to NASA's Work Breakdown Structure (WBS) for space vehicle subsystems.The mapping in some cases is only approximate. For example, WUC 14XXX, flight controls,includes control surfaces whereas WBS 1.12, actuators, does not. Miscellaneous utilities (WUC49XXX) and Personal Equipment (WUC 96XXX) may include oxygen masks, communications,goggles, maintenance crane, fire protection and warning devices, water systems, flashlights,ladder, cooler, toilets, etc., while WBS 1.15 personnel provisions includes food, water, wastemanagement and seats.

Similarly, WBS 1.16, recovery and auxiliary systems, includes parachutes, escapesystems, separation systems, docking system and manipulator system, which, in turn, is mappedto emergency equipment (survival kit, emergency oxygen system, emergency lights, search andrescue systems, parachute system, life raft, life vest, evacuation system, escape slide), dragchute, explosive devices (ejection seats devices, escape initiating systems, and canopy removalsystem). During implementation of the equations, adjustments can be made to the parametersto account for the approximate nature of the match between the WBS and WUC structure. Todevelop a complete match would involve developing equations at a much lower level of both theWBS and WUC structures.

24

Table 4WUC to WBS Conversions

WBS

1.1

1.2

1.3

1.4

1.5

1.6

1.7

1.8

1.9

1.10

1.11

1.12

1.13

1.14

1.15

1.16

Wing Group

Tail Group

Body Group

Thermal Protection System

Landing Gear

Propulsion

Propulsion, RCS

Propulsion, OMS

Prime Power

Electrical

Hydraulics/Pneumatics

Actuators

Avionics

Environmental Control

Personnel Provisions

Recovery & Auxiliary Sys

WUC

11XXX

12XXX

13XXX

23XXX

24XXX

42XXX

44XXX

45XXX

14XXX

51XXX

52XXX

55XXX

61XXX

62XXX

63XXX

64XXX

66XXX

71XXX

72XXX

41XXX

47XXX

49XXX

96XXX

91XXX

93XXX

97XXX

Airframe

Crew Compartment

Landing Gear

Propulsion System

Aux Power Units-APU

Electrical

Lighting System

Hydr/Pneumatics

Flight Controls

Instruments

Autopilot

Malfunc Anal Rec

HF Comm

VHFComm

UHF Comm

Interphone

Emergency Comm

Radio Navigation

Radar Navigation

Environ Control

Oxygen System

Misc Utilities

Personnel Equipment

Emerg Equipment

Drag Chute Eqpt

Explosive Devices

25

WUC 11XXX (airframe) was mapped into WBS's 1.1 (wing group), 1.2 (tail group), 1.3(body group), and 1.4 (TPS). The distribution of failures was based, in part, upon thebreakdown of aircraft maintenance actions of WUC 11XXX to the wing, tail, and body usingthe data in Table 5. WUC 12XXX (crew compartment) was also mapped into the body group.The allocation of failures and manhours to the thermal protection system (TPS) was proportionalto its weight to the total weight of WBS 1.1, 1.2, 1.3 and 1.4.

Table 5WUC 11XXX Maintenance Actions

AIRCRAFT

B-52

KC-10A

F-15E

F-4E

F-16C

F-16A

TOTAL

PERCENT

TAIL

417

37

-

32

787

272

945

.014

WING

7417

212

203

1225

2430

2109

13,393

.202

BODY

22,501

1,427

2,388

5,575

8,809

13,116

52,028

.784

TOTAL

30,335

1676

2591

6832

12,026

15,497

66,366

1.000

In many cases, work unit codes were combined into a single WBS using Table 4 before derivinga regression equation. WUC's 42XXX (electrical) and 44XXX (lighting) were combined underWBS 1.10 (electrical distribution). WUC's 41XXX (environmental) and WUC's 47XXX(oxygen systems) were combined under WBS 1.14 (environmental control system). All avionicsWUC's were combined under WBS 1.13 (avionics). WUC 23XXX (propulsion system) wascomputed separately for WBS 1.6 (propulsion), 1.7 (RCS), and 1.8 (QMS) using theircorresponding weights.

B. Regression Analysis

Multiple linear regression procedures were used to develop each of the parametric equations.A "best fit" was defined as the simplest mathematical model having a significant Rvalue, a largeR-squared value, and a small standard error. Generally, only independent variables which weresignificant (based upon a t-test) were included in the final model. Several models weremarginally significant but retained nevertheless. A secondary criterion for model selection was

26

the practical test that the model would provide reasonable results over the anticipated range ofindependent variable values. Because of the difference between aircraft and space vehicleparameters, extrapolations outside the domain of the input data were expected. Nonlineartransformations of the independent variables were also included in the model if they significantlycontributed to the prediction power of the equation. Generally these transformations consistedof squaring, taking logarithms or square roots of the variables.

An investigation of the residuals would, on occasion, identify one or more data points asoutliers (two or more standard deviations from the mean). At times these outliers were deletedfrom the data base. This was based upon the strong possibility that the AFALDP 800-4 datawas incomplete. This is particularly true for the Vol VI data which contains a warning to thiseffect. In processing AFM 66-1, the monthly tapes from the bases may not contain all of thefailures logged for that month. On the other hand, the monthly flying hours and sorties reportedthrough a different data system is almost always complete. The net result is an overstatementof the MTBF. This was normally the case when outliers were observed.

C. Analysis of Weights and Secondary Variables

Several variables were identified as primary or "driver" variables. These include (1)vehicle dry weight in pounds, (2) the sum of the vehicle length and wing span in feet, (3) crewsize, and (4) number of passengers. Values for these independent variables were based uponreferences [8] and [13] and are found in Appendix G. Using these four driver variables,regression equations were derived to estimate subsystem weights and secondary variables. Table6 displays the weight equations and Table 7 displays the secondary variable equations. As aconceptual vehicle becomes better defined, it is expected values for these variables will beobtained from the design specifications and will need not be estimated from the "driver"variables. With the exception of Prime Power (WBS 1.9) and Avionics (1.13), there areexcellent least-squares fits to the data. The number of aircraft in the data base having an APUweight is quite small and its weight is not as dependent with vehicle size as are othersubsystems. The engine weight equation was not used since aircraft engines are not comparableto spacecraft engines. Instead, a percentage of dry weight was allocated to each propulsionsystem and the TPS. Avionics weight is not as highly correlated with vehicle size as are theremaining subsystems. Observe that the secondary variable equations must be evaluated in aparticular order since several of these equations require values derived from the previoussecondary variable equations. Correlation of these equations vary from under 60 percent to over99 percent.

27

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Table 8Weight Distribution

WBS

1.1

1.2

1.3

1.4

1.5

1.6

1.7

1.8

1.9

1.10

1.11

1.12

1.13

1.14

1.15

1.16

SUBSYSTEM

WING

TAIL

BODY

TPS

LANDING GEAR

PROPULSION

PROPULSION, RCS

PROPULSION, QMS

APU (PRIME POWER)

ELECTRICAL

HYDRAULICS/PNEU

ACTUATORS

AVIONICS

ECS

PERSONNEL PROV

RECOVERY & AUX

AVE VEHICLE

AVERAGE

.091

.003

.140

.099

.053

.019

.029

.017

.151

.059

.021

.007

.061

.083

.070

.097

1.00

30

D. MTBM Equations

Based upon the "driver" variables, subsystem weights, and the secondary variables,regression equations were derived to estimate MTBM. These equations are summarized in thefollowing table with the regression analysis provided in Appendix J. The estimated MTBMrepresents an unadjusted number and reflects aircraft reliability as captured in the data base.With the exception of Propulsion (WBS 1.6-1.8), acceptable correlations were obtained with theregression models. Aircraft engine failures were estimated exclusively from engine weight inorder to utilize the equation for each Propulsion WBS and to provide a reasonable approach forextrapolating aircraft engine results to space vehicle propulsion systems. It is expected that thisequation will be replaced as data on space propulsion systems becomes available.

31

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The estimated MTBM is adjusted for technological change. In deriving the adjustmentfactor, a learning curve of the form given by Equation (2) is determined by using least-squares.These curves are summarized by subsystem in Table 10. Three separate equations were derivedusing historical data from the F-16B, B-l, and F-15A. Appendix Q summarizes the results ofthe regression analysis and Table 10 depicts the average growth rate (b parameter) for eachsubsystem. Only statistically significant growth rates from among the three aircraft wereaveraged. A separate analysis was performed for the overall aircraft.

Table 10.Learning Curve Results

WBS

1.1

1.2

1.3

1.4

1.5

1.6-1.8

1.9

1.10

1.11

1.12

1.13

1.14

1.15

1.16

SUBSYSTEM

WING

TAIL

BODY

TPS

LANDING GEAR

PROPULSION

APU (PRIME POWER)

ELECTRICAL

HYDRAULICS/PNEU

ACTUATORS

AVIONICS

ECS

PERSONNEL PROV

RECOVERY & AUX

VEHICLE

AVE GROWTHRATE (b)

.1534

.1534

.1534

—.1480

.2305

.1927

.1333

.1703

.1608

.2427

.1555

.0683

.3592

.1370

Using the methodology discussed in the previous chapter, technology adjustment factors werethen derived. These factors, displayed in Table 11, represent an average annual growth ratebased upon a compound growth curve derived from the pairwise comparisons shown inAppendix R. One subsystem, electrical, resulted in a negative growth rate which was set equalto zero. A combined avionics growth rate of .42 appeared to be excessive and was replacedwith an adjusted rate obtained by deleting the F-4E - F-16A comparison which had a 0.978

33

annual growth rate. The rates shown in Table 11 represent the default values used in theimplementation phase. In implementation, the TPS subsystem defaulted to the structuralsubsystems (WBS 1.1, 1.2, 1.3) growth rates. The APU growth rate was not computed becauseof insufficient data. The aircraft rate was used as a default value.

Table 11Technology Growth Rates

WBS

1.1

1.2

1.3

1.4

1.5

1.6-1.8

1.9

1.10

1.11

1.12

1.13

1.14

1.15

1.16

SUBSYSTEM

WING

TAIL

BODY

TPS

LANDING GEAR

PROPULSION

APU (PRIME POWER)

ELECTRICAL

HYDRAULICS/PNEU

ACTUATORS

AVIONICS

ECS

PERSONNEL PROV

RECOVERY & AUX

AVE TOTAL

AVERAGE

.08184

.08184

.08184

—.03352

.01116

.0557

-0.02090

.09222

.05622

.41915 (.22)

.00617

.03571

.08358

.0557

Regression equations for subsystem critical failure rates were derived from MODASobtained aircraft air/ground abort rates found in Appendix N and displayed in Table 12. ForWUC's 24XXX, 49/96XXX, and 91/93/97XXX, averages were used since the number of datapoints were insufficient to properly fit a regression curve. Regression results may also be foundin Appendix N. Because of the processing time required to obtain the abort rates, theseequations are based upon a smaller sample size consisting of 13 aircraft. Each subsystem andeach aircraft data point had to be retrieved separately from the MODAS ABORT SUMMARYREPORT. In general, there is a high correlation between vehicle size as measured by DRYWEIGHT or LENGTH plus WING SPAN and abort rates.

34

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Predicted maintenance manhours per maintenance action were obtained from regressionequations using primary, secondary and subsystem weight variables. These equations arepresented in Table 13. Appendix K contains the regression analysis.

Marginal correlations were obtained for several subsystems including electrical, andoxygen subsystems. For those subsystems average manhours per maintenance action remainssomewhat constant across aircraft. However, except for landing gear and oxygen, the fittedequations were significant at the 10 percent level and therefore partly explain the variation foundin this parameter. In order to separate the on and off vehicle work being performed, the percentof off-equipment (POFF) manhours was also estimated from regression equations. Theseequations are identified in Table 14.

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Limited data is maintained on military aircraft pertaining to scheduled maintenance.These tasks fall into two categories: preflight/postflight inspections and periodic maintenance.For AF aircraft, total maintenance manhours expended in both areas are recorded in AFALDP800-4. Using this data pertaining to 27 different data points, a regression analysis wasperformed with the results summarized in Table 15. Scheduled maintenance manhours ispredicted as a percent of the unscheduled maintenance manhours. Once total unscheduledmaintenance is computed, then the predicted percentage is applied to obtain the total scheduledmaintenance.

Table 15.Scheduled Maintenance Manhours

As a percentage of UNSCHEDULED Maintenance Manhours:

%UNSCH = 0.844224 + .002638 X (LENGTH + WING)+ .00003379 X (WETTED AREA) - .005231 SQRT (DRY WT)

(R = 0.922)

SCH MANHOURS = % UNSCH x UNSCH MANHOURS

G. Removal Rates

Removal rates were based on data pertaining to six aircraft: C-5A, C-130E, C-141B, F-15D, F-111A, and T-38A. Since it was not possible to obtain adequate least-square fits forWBS's 1.11 and 1.15, mean values were used. Results are depicted in Table 16 with the dataand regression analysis found in Appendix M.

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H. Crew Sizes

Average (mean) crew sizes for performing unscheduled maintenance are predicted fromderived regression equations. The input data for this analysis was obtained from the MODASmaintenance summary reports which provided by aircraft and by subsystem total maintenancemanhours and total elapsed time. The crew size analysis may be found in Appendix O and issummarized in Table 17. By dividing the maintenance manhours by elapsed time, an averagecrew size was obtained. For this analysis, crew sizes were estimated at the one digit (or higher)level. Because of the difficulty and time in extracting this data from MODAS, the data wasobtained at the higher level. The resulting equations are in Table 18. No significant fit couldbe obtained for WUC's 2XXXX and avionics (5XXXX, 6XXXX and 7XXXX). Therefore themean value was used. Neither propulsion repair crew size nor avionics repair crew size seemto be related to aircraft size.

Table 17Repair Crew Size Data

(by WUC)

AIRCRAFT

A7DF111E

F4E

F15C

F16A

C130E

KC135

C141B

C5B

1XXXX

1.66

2.66

1.80

2.03

1.90

2.12

1.90

2.30

2.09

2XXXX

2.44

2.85

2.37

2.26

2.37

2.00

2.53

2.99

2.11

4XXXX

1.58

2.73

2.04

2.18

2.02

2.21

2.39

2.26

2.22

AVIONICS

2.01

2.42

2.28

2.21

2.21

1.98

2.42

1.98

2.10

9XXXX

1.762.87

1.88

2.00

2.17

2.02

2.03

2.12

2.42

41

Table 18Crew Size Regression Equations

wuc1XXXX

2XXXX

4XXXX

AVIONICS

9XXXX

WBS

1.1-1.5, 1.12

1.6-1.9

1.10, 1.11, 1.14

1.13

1.15, 1.16

EQUATION

1.5 -3.m*E-5(WET AREA)+ 9. 1722£-3 JWET AREA

AVE = 2.44

-1.48 -2S33E-3(LEN + WING)+ M466LOG(LEN + WING)

AVE = 2.18

1. 78933 +9.8722£-4v/D/?r WT

R

.737

™

.774

—.759

An empirical crew size distribution was obtained from the MODAS Detail Maintenance Datareport which identifies the start and stop time of each maintenance activity along with theassigned crew size. The crew size distribution and average (mean) crew size were found (Table19). Since this distribution was based on over 130 individual maintenance tasks, it is assumedto be representative of the crew size requirements for this particular component (AC powersystem) on B-1B.

Table 19Crew Size Probability Distribution

AIRCRAFT ISWORK UNIT CODE ISNOMENCLATURE IS

CREW SIZE PROB CUM PROB

B-1B42B**AC POWER SYSTEM

1.002.003.004.005.006.007.008.00

0.110.520.330.030.010.010.000.00

0.110.630.960.990.991.001.001.00

AVERAGE CREW SIZE IS 2.326485

42

I. Repair Distribution

Using August 1990 data from the Bl-B bomber, MOD AS provided start and stopmaintenance times for each failure record in the system (see Table 20). Using the repair timescomputed from these values, a Chi-square goodness of fit test was conducted to determine asuitable distribution. Because of the tendency to report times in whole hours (or 30 minuteperiods), the data had to be aggregated into four intervals. A significant fit was obtained usingeither the Weibull or lognormal distributions (see Tables 21). Follow-on research will attemptto analyze repair distributions more fully.

43

Table 20Repair Time5 Data

Repair Time Observations

NASA Bl-B WUC 42B TIHE-TO-RKPAIR

UBIBiBII ARIIAT OP OBSERVATIONS

5 5 5 $ 55 5 10 10 IS20 20 20 20 2025 25 30 10 JOSO 30 30 30 3030 30 30 30 3030 30 30 30 3030 30 30 30 3030 30 30 30 3040 58 (0 10 1010 10 10 10 fO(0 «0 CO «0 fO(0 (0 (0 (0 10<0 SO SO 60 SOso to so so soSO SO SO SO SOso so so so so•0 SO SO 00 •••0 00 SO 00 SO00 00 »0 00 (0•o to to to to•o to to in tn118 1*0 120 ISO ISO1X0 110 1X0 1X0 1X01X0 120 120 1X0 1X01X0 1X0 120 1X0 1X01X0 1X0 1X0 1X0 1X0ISO 1X0 120 120 ISO1«0 110 ISO ITS ITSISO 110 110 ISO ISOISO 110 100 ISO 240240 240 240 240 240240 240 240 240 240240 240 2TO 2TO JSI300 300 300 300 300300 330 300 301 420420 410 410 400 410

DUUUIMITE STATISTICS

SAMPLE SIZE 1SSMEAN 1124432Amttnt so* COIF INTERVAL IOOLSOST i2S.srrtMEDIAN , SOVARIANCE 1 OSTO.STSTARDAU DETIATIOM 10X4131VARIANCE/MEAN RATIO 1344)400cuifFitmrr or VARIATION .totooxs

4TSM) 1.000341

10* CRITICAL VALUES FOR 81-0 -.1003412 .2002412HimiUSIS-fB2> S.2SST1310* cxrr VALUES FOR B2-J <NORMAU 2.iorso4 3.103407

'Time is in minutes.

44

Table 21Goodness of Fit Tests

Repair Time Distributions

CBI-SQVARE COMPUTATION

WBBOLL WITH SCALE PARAMETER* 120 AND SHAPE PARAMETER* 1.17

CELL LOVER UPPER OBS ED? <O-EJ»2/E1.00 0.00 41.37 48.00 4ff«S8 0.002.00 41.37 37.T3 Si.OO 41.26 0.4*3.00 37.73 ! 31.04 46.00 48JS 0.004.00 158.84 9900.00 42.00 48.18 0.38

CHX-SQVABZ STATISTIC* .8810111 OEOREES OF FREEEDOM- 198* CRITICAL VALUE- 3.S4 90* CRITICAL VALUE- 2.71

CANNOT REJECT AT IDS LEVEL

MEAN OF LOONORMAL- 121.80tt WTTB STND OEV- .9832414

CELL LOWER UPPER OBS EXP (O-EV2/E1.00 -9900.00 3.08 48^0 48^8 0.032.00 3.88 4.32 52.00 48^8 0.713.0O 4^2 4.08 49.00 4U8 0^84^0 4.08 9900.00 4MO 48^8 0.00

CRI-SQUABE STATISTIC- 1.140*41 DECREES OF FHEEEDOM- 198* CRITICAL VALUE* 3.84 90* CRITICAL VALUE- 2.71

CANNOT REJECT AT 10* LEVEL

45

An attempt to derive a failure time distribution from the MODAS data was more difficult.MODAS provides the Julian date and time (although time does not appear to be very accurate)of each failure. However flying hours (and sorties) are reported monthly. Therefore it isimpossible to determine from this data set the actual flying hours between failures. However,it may be possible to show in some cases that the number of failures per flying hour is Poissonby taking failures per month and converting to failures per flying hour. Therefore the time(flying hours) between failures would be exponential. This approach will be investigated in thefollow-on effort.

46

CHAPTER V

Implementation

I. INTRODUCTION

This chapter describes the PC based model for evaluating the reliability and maintainabilityequations derived in the previous chapter. Because of the large number of equations to beevaluated and the large number of additional calculations, the only practical way to implementthe results of this research is on a computer. This PC based model is completely menu drivenwith all parameters computed at the subsystem (WBS) level and then rolled up to reflect overallvehicle performance.

Flying hours between maintenance actions, maintenance manhours per maintenance action,critical failure (abort) rates, percent on/off vehicle hours, removal rates, and crew sizes areestimated using the multiple regression models derived from aircraft data. Lower bounds (andin some cases upper bounds) are set if the equations predict values outside the limits of the inputdata. In addition to predicting failures and repair manhours, estimates of mission reliability,spares support, manpower requirements, and fleet size are also made.

The computer model is design to evaluate all 16 major subsystems as defined by the NASAwork breakdown structure (WBS). Upon execution of the model, the user may elect to deleteany number of these subsystems from the analysis.

II. Modes of Operation

A. The model operates in one of three modes: PRECONCEPTUAL, WEIGHTDRIVEN, & WEIGHT/VARIABLE DRIVEN. In mode 1, PRECONCEPTUAL, the user mustspecify 4 driver variables and 10 system parameters. The driver variables are used to estimatesubsystem weights and secondary variable values from the multiple regression models derivedfor this purpose. These 4 variables and the 10 system parameters are listed below as theyappear on the first menu. When operating in Mode 1, the user will bypass the weight andsecondary variable menus shown below. However, changes to the primary variables will resultin both weights and secondary variables being recomputed. The user has the option of havingweights computed by the regression (aircraft) equations or by the weight distribution presentedin Table 8. The user must specify the average crew size for scheduled maintenance activity.However, the model will compute crew sizes for unscheduled maintenance based upon theregression equations in Table 18. The default value for the technology growth factor is theestimated factor (see Table 11) for the overall vehicle. The user may elect to replace asubsystem growth factor with this value on a subsequent menu. The Weibull shape parameterdefault value is based upon a previous study [11] and is used in determining the MTBM adjustedfor the time in orbit. The launch factor applies to the booster phase of the mission. Availablehours per month is the average number of working hours a month, and the percent indirect work

47

refers to all work accomplished by the individual which is not accounted for in the maintenancemanhour equations.

Figure 4Driver & System Variables

INPUT MODULE - PRIMARY INDEP VARIABLESNBR

1234

567891011121314

VARIABLE

VEHICLE DRIVER VARIABLES

DRY WGT (LBS)LENGTH+WING SPAN (FT)CREW SIZENBR PASSENGERS

SYSTEM PARAMETER VALUES

TECHNOLOGY YRDEFAULT TECH GROWTH FACTOR"TEBUTfT- SHAPE PARAMETERLAUNCH FACTORAVAIL MANHRS /MONTHPERCENT INDIRECT WORKSPARE FILL RATE OBJAVG CREW SIZE-SCHD MAINTPLANNED MISSIONS /MONTHWGT IND O-PCT/1-EQS

CURRENT VALUE

900010028

1994.0557.2820144.15.951.811

48

B. In Mode 2, WEIGHT DRIVEN, the user may input/change subsystem weights.This should result in more accurate estimates. Secondary variables may be recomputed fromthese weights, however, the secondary menu will not be displayed and the user cannot updateit. As subsystem weights are updated, the total weight is recomputed. The overall vehicledry-weight is set equal to this new total weight regardless of the initialvalue on the first menu. The subsystem weight menu is shown below:

Figure 5Weight Menu

NBR

1 .2345678910111213141516

TOTAL

SUBSYSTEM WEIGHTSSUBSYSTEM

1.1 WING GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TPS1.5 LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-OMS1.9 PRIHE POWER1.10 ELECTRIC CONV/DISTR1.11 HYDRAULICS /PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 ENVIRONMENTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS

WGT

WEIGHT IN LBS

1846.976364.95962319.57849.7662347.247777.25148309.0059154.503114.4622263.2065253.3027429.6665501.S043348.434247.32994772.5147

9000

49

C. Mode 3, WEIGHT/VARIABLE DRIVEN, allows the user to specify and changeboth subsystem weights and 12 secondary variables. These secondary variables provide for moreaccurate regression equations as measured by the R value (MultipleCorrelation coefficient) and the standard error of the estimate (a measure of the variability ofthe estimated value. This mode, therefore, should result in the most accurate assessments.However, the vehicle must be sufficiently defined to enable theuser to assign values to these variables. Definitions of these variables may be found inAppendix F. Default values are computed values from the regression equations. These are thesame values which would be used in Modes 1 and 2. The user may run the model in Mode 3,and by not changing the weight or secondary variable values, generate the same results as Mode1.

Figure 6Secondary Variable Menu

SECONDARY INDEP VARIABLES

NBR

123456789101112

VARIABLE

FUSELAGE AREAFUSELAGE VOLUMEWETTED AREANBR m"UBT.sNBR ACTUATORSNBR CONTR SURFACESKVA MAXNBR HYDR SUBSYSNBR FUEL TANKS ( JJ»u:i5«ilAL)TOT NBR AVIONICS SUBSYSNBR DIFF AVIONICS SUBSYS3TU COOLING

CURRENT VALUE

4781185.1831996.13135724.1249184161686.46997

III. Additional Input Parameters

A. Subsystem Calibration

To provide sufficient flexibility to transition from the aircraft system to the space vehiclesystem, a calibration factor is included. This factor is used in modifying the aircraft computedMTBM AND MH/MA where CALIBRATED MTBM = CAL FACTOR x AIRCRAFT MTBMand CALIBRATED MH/MA = CAL FACTOR x MH/MA. The default value is one. Withthese two factors, the R&M parameters may be calibrated by subsystem based upon non-aircraft

50

data (e.g. Shuttle data) in order to account for those differences between aircraft and spacevehicles which are not accounted for by the variables in the aircraft generated equations.

Figure 7Calibration Menu - MTBM

SUBSYSTEM MTBM CALIBRATION

NBR

12345678910111213141516

SPACE VEH-MTBM = CAL FACSUBSYSTEM

1.1 WING GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TPS1.5 LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-OMS1.9 PRIME POWER1.10 ELECTRIC CONV/DISTR1.11 HYDRAULICS /PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 ENVIRONMENTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS

XFACTORACPT-MTBM

.CAL FACTOR

1111111111111111

51

Figure 8Calibration Menu - MH/MA

SUBSYSTEM MH/MA CALIBRATION FACTORCAL MH/MA - CAL FAC X COMPUTED-MH/MA

NBR

12345678910111213141516

SUBSYSTEM

1.1 WING GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TPS1.5 LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROFULSION-OMS1.9 PRIME POWER1.10 ELECTRIC CONV/DISTR1.11 HYDRAULICS /PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 ENVIRONMENTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS

CAL FACTOR

1111111111111111

B. Mission Profile and Subsystem Operating Hours

In order to adjust for the time spent in space and to account for ground operating times,the following mission profile menu is provided (see Figure 4):

52

Figure 9Mission Profile Menu

MISSION PROFILE

NBR TIME IN HOURS

1 GROUND TIME PRIOR TO LAUNCH 2

LAUNCH TIME AT T=0

2 BOOSTER COMPLETION TIME .143 ORBIT INSERTION TIME 14 ORBIT COMPLETION TIME 715 GROUND RECOVERY TIME 72

From the selected profile, subsystem operating times are determined and displayed in thefollowing manner:

53

Figure 10Subsystem Operating Times

SUBSYSTEM OPERATING TIMESTOTAL MISSION TIME " HRS MAX GROUND TIME;IBR

12345673910111213141516

SUBSYSTEM GROUNDTIME

1.1 WING GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TFS1.5 LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-OMS1.9 PRIME POWER1.10 ELECTRIC CONV/DISTR1.11 HYDRAULICS /PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 ENVIRONMENTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS

2222222222222222

BOOSTERTIME

.14

.14

.14

.14

.14

.14

.14

.14

.14

.14

.14

.14

.14

.14

.14

.14

2 HRSREM TIMETO -ORBIT

.86

.86

.86

.86

.86

.86

.86

.86

.86

.36

.86

.86

.86

.86

.86

.86

ORBITTIME

70707070707070707070707070707070

RECOVERYTIME

1111111111111111

The user may then uniquely adjust each subsystem based upon its mission profile. In computingspace adjusted MTBM's, the ground segment, non-booster time to orbit, and recovery segmentshave constant failure rates based upon the calibrated MTBM as adjusted for technology and thesteady-state ground/air/space environment. During the launch (booster) segment, the failure rateis increased by the launch factor (system parameter number 8). During the orbit segment, thefailure rate is assumed to be decreasing based upon the Weibull shape parameter (systemparameter number 7).

54

C. Technology Factor

The default technology factors used by the model are those presented in Table11. The user may replace any one of these with the system value displayed on the first menu.

Figure 11Technology Factor Display Menu

OPTION TO USE DEFAULT RATE

MBR

12345678910111213141516

FOR ANNUAL RELIABILITY

SUBSYSTEM

1.1 WING GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TPS1.5 LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-OHS1.9 PRIME POWER1.10 ELECTRIC CONV/DISTR1.11 HYDRAULICS /PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 ENVIRONMENTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS

GROWTH FACTOR

ANNUAL GROWTH RATE

.082

.082

.082

.082

.033

.011

.011

.011

.0540.092.056.22.0062.036.083

IV. Computations

A. MTBM (mean operating hours between maintenance actions)

An aircraft MTBM is first computed by evaluating the regression equations. Then thecalibration factor is applied to obtain the calibrated MTBM. A technology adjustment to accountfor increases in reliability in obtained by:

ADJ MTBM = (1+TECH GROWTH FAC)(tech ***> x CAL MTBM

where 86 reflects the baseline year of the input data.

55

The primary MTBM used in subsequent calculations is based upon the adjustment foroperating in the launch and space environment (SS MTBM). This adjustment uses the subsystemmission profiles as previously discussed. As a result of the decreasing failure rate, a numericalintegration must be performed for each subsystem. Therefore, this process may take severalseconds to a minute to complete.

A critical MTBM is based upon a critical failure or abort rate and is found from:

CRIT MTBM = SS MTBM / ABORT RATE

Corresponding to and computed from the subsystem critical MTBM is a subsystem missionreliability. This reliability may be interpreted as the probability the subsystem will complete themission without a critical failure. This reliability also depends upon the subsystem missionprofiles (operating times). A vehicle mission reliability is obtained by multiplying the subsystemreliabilities.

B. Maintainability Parameters

The initial calculation is the determination of the subsystem maintenance manhour permaintenance action (MH/MA) obtained by evaluating the corresponding regression equations.This value is then adjusted by the maintainability calibration factor. Total maintenance actionsper mission (TOT MA) is found by

TOT MA = TOT OPER HRS / SS MTBM

Then total manhours per mission (MH) is calculated by:

TOT MH = MH/MA x TOT MA

These manhours are then split into on-vehicle and off-vehicle manhours using the regressionestimated percent of off/on-vehicle manhours. Scheduled maintenance manhours per missionis based upon a regression estimated percent of unscheduled maintenance applied to the totalunscheduled maintenance manhours. Scheduled maintenance is also broken down into on andoff-vehicle work.

To convert total manhours into manpower requirements, the following calculations areperformed:

MANHRS/MO = TOT MH x MISSIONS/MO

Then

NBR PERSONNEL = MANHRS/MO / {AVAIL MANHRS/MO x (1-% INDIRECT)}

56

and NBR PERSONNEL is rounded up to the nearest integer if the fraction portion exceeds .001.This is done by subsystem.

C. Spares

Spares levels for each subsystem are determined using a single mission fill rate goalspecified on the first menu. Fill rate refers to the percent of time a spare will be available whena demand (failure) is generated. The average number of demands (MFAIL) are determined froman estimated removal rate (RR) as follows:

MFAIL = RR x TOT MA

This becomes the mean of a Poisson probability distribution. The spares level is iterativelyincreased by one unit until the probability of demands not exceeding the spares level reaches orexceeds the fill rate objective (system variable number 11). The achieved fill rate and computedspares level are then retained for display.

D. Vehicle Turn Time

For each subsystem, an average task time is found from:

AVG TASK TIME = MH/MA / AVG CREW SIZE

Average hours (clock time) on-vehicle time per mission becomes:

ON-VEH HRS/MSN = TOT ON-VEH MH /AVG CREW

The subsystem on-vehicle times are summed together in order to obtain a maximum vehicle turntime. This assumes each task must be accomplished sequentially. Since this is probably not thecase, it provides an upper bound on vehicle turn time. On-vehicle scheduled maintenance is alsoadded to this sum to obtain a total turn time. By adding the mission time (including groundprocessing time) to this total, a complete vehicle turnaround time is obtained. This is convertedto days under the assumption that the mission time will occur on a 24 hour/day basis but thescheduled and unscheduled work would occur on a 8 hour/day basis. For a given vehicle, thenumber of missions per month is found by

VEH MSN/MO = (WORKING DAYS/MO) /TURNAROUND TIME IN DAYS

The fleet size is computed from:

FLEET SIZE = (MSN/MO) / (MSN/MO/VEH)

rounded up to the nearest integer.

57

V. Output Reports

The following figures are examples of the output displays resulting from running the modelSeparate screen displays are found for the reliability calculations, maintainability calculations^spares levels, and vehicle turn time analysis.

VEHICLE IS TEST VEH

WBS

Figure 12Reliability Report

RELIABILITY REPORTDATE: 06-11-1992

CALIBRATED MTBM

1.1 WING GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TPS1.5 LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-OHS1.9 PRIME POWER1.10 ELECTRIC CONV/DISTR1.11 HYDRAULICS/PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 ENVIRONMENTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS

VEHICLE

34.72139500.98294.63618537.401936.25531831.4318228.9158730.37121121.27745.1546.9502622.5884627.1306228.538232S9.32253.802

1.140834

TECH ADJ

65.22554941.11138.70921270.260643.11057934.306731.5606333.14908184.7165.1594.9334134.92995133.149229.984784325.19480.311

1.558437

TIME: 16:25:32

SPACE ADJ

333.58875072.35730.29372360.785427.23173166.8098152.0331160.5794979.675412.77312494.1188170.1649700.7554143.558323383.492S78.978

5.248452

VEHICLE IS TEST VEHWBS

1.1 WING GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TPSI'.S LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-OMS1.9 PRIME POWER1.10 ELECTRIC CONV/DISTR1.11 HYDRAULICS/PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 ENVIRONMENTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS

VEHICLE

RELIABILITY REPORT - page 2DATE: 06-11-1992

CRITICAL CRITICALFAIL RATE MTBM

1.831055E-021.831055E-O21.895309E-021.831055E-024.266358E-02.035484.035484.035484.064.00248.000845.542377E-02.023764.817755E-02.0185.004678

18218.39277018.31598.35319703.69638.28984700.9884284.5544525.40415307.435150.451588236.63070.25129493.072979.7761263973551299.3

254.6037

TIKE: 16:25:43SUBSYSMSH RELIABILITY

.9992496

.9999506

.9914805

.9993061

.9788026

.9970951

.9968133

.9969826

.999107

.9973483

.9999768

.9955556

.9995364

.9954211

.9999891

.9999752

.9477038

58

Figure 13Maintainability Report


MAXHTAZHABZLT? REPORTDATE: 06-11-1992

MAHHR/MA TOT HA

1.1 WING GROUP1.2 TAIL CROUP1.3 BODY GROUP1.4 TPS1.5 LAUDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-QMS1.9 PRIME POWER1.10 ELECTRIC COHV/DISTR1.11 HYDRAULICS/PNEUMATICS1.12 ACTDATORS1.13 AVIOaiCS1.14 mv.nujhimre'AL CONTROL1.13 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTERS

SCHEDULEDTOTALS

TIME: 16:26:08TOT HANHRS

9.0976289.09762812.18929.0976284.37683249.3434145.9953647.880925.24.4990228.4466172.1S.4404916.1236596.89484.051671

14.35193 (AVG)

.22183011.4588B8E-022.442751.20510812.717419.443619.4867361.46083127.S53S23E-025.793417.1497616.4348724.1056003.51547013.164626B-032.869354E-02

14.0994

2.018128.132724229.775171.86599712.4371721.8453122.387622.06502.392783226.041541.264979.9132319.57491763.1S6S632.087008E-02.1162968

77.19669222.2046


1.1 HXRC GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TPSl.S LAUDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-QMS1.9 PRIME PUMUt1.10 ELECTRIC COHV/DISTR1.11 HYDRAULICS/PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 EMVIKONMEHTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY I AUX SYSTEMS

MAXBXAZKABZLTY REPORT - paqa 2DATE: 06-11-1992

OH-VEH MH

1.849614.121641727.221951.7101868.8058346.007466.1565896.06788.380999720.123331.212454.69*3355.42915392.9123911.7837S7E-027.680828E-02

TOTALS75.65276159.4392

! TIME: 16:26:35•VEH MH PERCENT ON-VEH

.16891361.108247E-022.553221.13581073.63133515.8378516.2310115.99714.01178355.9182075.232423E-02.2168965.1493637.24417223.032502E-033.944849E-02

1.54393462.76932

.9165

.9165

.91425

.9169

.7080296

.279

.279

.279

.97

. 7727397

. 9584781

. 7624958

.740019

.9226462

. 3946961

. 660678

.7399081

WBS

MAIHTAINABTLTY REPORT - pag» 3IS TEST VEH DATE: 06-11-1992

MMBBS/KSB MAKBRS/MO

1.1 N1N6 GROUP1.2 TAIL GROUP1.3 BODY uKuur1.4 TPS1.5 LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-QMS1.9 t'klRE PONER1.10 FTJU.TKIC COHV/DISTR1.11 HYDRAULICS /PNEUMATICS1.12 ACTUATORS1.13 AVIOHieS1.14 fcitv j KOHHEHTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS

77.19669TOTAL

77.19669145.0079

TUBS 16:27:26NBR PERSONNEL

2.018128.132724229.779171.86999712.4371721.8453122.387622.06502.393783226.041541.264979.9132319.57451763.1369632.087008E-02. 1162968

2.018128.132724229.775171.86999712.4371721.8493122.387622.06902.392783226.041541.264979.9132319.57431763.1963632.087008E-02.1162968

1111111111111100

115

59

w

Figure 14Subsystem Spares Report

VEHICLE IS TEST VEHwas

SUBSYSTEM SPARES REPORTDATE: 06-11-1992 TIME: 15:27-37

REM RATE AVG DEMAND SPARES RQMT FILL RATE

1.1 WING GROUP1.2 TAIL GROUP1.3 BODY GROUP1.4 TPS1.5 LANDING GEAR1.6 PROPULSION1.7 PROPULSION-RCS1.8 PROPULSION-OMS1.9 PRIME POWER1.10 ELECTRIC CONV/DISTR1.11 HYDRAULICS/PNEUMATICS1.12 ACTUATORS1.13 AVIONICS1.14 ENVIRONMENTAL CONTROL1.15 PERSONNEL PROVISIONS1.16 RECOVERY & AUX SYSTEMS

TOTALS

.1919366

.1919366

.2227305

.194

.22

.5992393

.5773786

.5901843

.5077349

.5007281

.368

.38593

.4140355

.5070317

.274

.747236

4.257731E-022.800139E-03.54407513.979097E-02.5978321.2658339.281031.27197543.835187E-022.9009275.511226E-02.16783034.372229E-02.26135968.671074E-O42.144084E-02

.4057564 (AVG) 5.535527

0020211106I10100

16

.9820489

.9820489

.9770984

.9703458

.9671848

.9690837

.9690837

.9712413

.9985361

.9873974

.9873974

.9712519

.9712519

.9712519

Figure 15Vehicle Turn Time Report

VEHICLE IS TEST VEH

WBS

VHHierr.f TURN TIME REPORTDAXE: 06-11-1992 TIKE: 16:28:03

AVG CREW SIZE AVG (ON) TASK TIME (HRS)AVG ON-VEH CLOCK HRS

1.1 WING GROUP 1.845915 4.5169871.2 TAIL GROUP 1.845915 4.5169871.3 BODY GROUP 1.845915 6.0370991.4 TPS 1.845915 4.5169871.5 LANDING GEAR 1.845915 1.7555051.6 PROPULSION 2.43 5.5728131.7 PROPULSION-RCS 2.43 5.2052351.8 PROPULSION-OMS 2.43 5.4186221.9 PRIME POWER 2.43 2.075721.10 ELECTRIC CONV/DISTR 1.98833 1.7469351.11 HYDRAULICS/PNEUMATICS 1.98833 4.0717081.12 ACTUATORS 1.845915 .86745091.13 AVIONICS 2.18 1.8468191.14 ENVIRONMENTAL CONTROL 1.98833 2.8415661.15 PERSONNEL PROVISIONS 1.935642 2.911981.16 RECOVERY & AUX SYSTEMS 1.882954 1.421622

1.0020046.589777E-O214.74713.92647054.7704432.4722062.5335762.49707.1567910.12072.6097854.3772304.19502471.4647429.215327E-034.079137E-02

60

VEHICLE TURN TIME REPORT - page 2VEHICLE IS TEST VEH DATE: 06-11-1992 " TIME: 16:28:36

MAX TURN TIMES

AVG VEH TASK TIME 3.457753 HRSSCHD MAINT MSN TASK TIME 42.02931 HRSMAX TURK TIME NO SCH MAINT 41.9891 HRSMAX TORS TIME WITH SCH MAINT 84.0184 HRSMISSION TIME -INC GROT TIME 74 HRSTOT VEHICLE TURNAROUND TIME 116.0293 HRSTOT vi-'HTPT-T? TURNAROUND TIME 8.336997 DAYSMISSIONS /MONTH/VEHICLE 2.518893FLEET SIZE 1

VI. Validation

Some model validation was accomplished by running the computer model for differentaircraft having known R&M parameters. The R&M parameters were obtained from AFALDP800-4 Volume VI, and therefore, were not part of the input data to the model. Since the averagedate of the data in Volume IV is 1988, this date was used for the technology year. The spaceadjusted feature of the model was not utilized since it obviously does not apply to aircraft.Mission profiles reflected the average mission of the aircraft.The model was run in all three modes. Table 22 and 23 compare the results of the computedMTBM values in each model with reported values from Volume VI for the F-16A and C-141Brespectively.

61

Table 22Model Validation - F16

SUBSYSTEM

STRUCTURAL

LANDING GEAR

PROPULSION

APU

ELECTRICAL

HYDRAULICS

ACTUATORS

AVIONICS

ECS

PERSON PROV

REC & AUX SYS

AIRCRAFT

MODE 1

6.2

14.0

20.7

22.8

19.9

96.8

17.4

19.9

29.7

784

88.5

1.8

MODE 2

7.8

14.2

19.2

37.0

17.3

84.9

14.1

16.1

29.7

1539

88.5

1.9

MODE 3

7.8

14.2

19.2

50.4

21.5

100.3

13.3

14.7

29.7

1539

88.5

1.9

OCT87MAR 88

7.4

11.4

20.2

23.4

16.6

58.7

13.7

16.4

36.0

493

117

1.8

APR 88SEP 88

7.5

10.1

17.8

21.5

14.4

64.8

15.2

15.6

33.5

476

224

1.7

Table 23Model Validation - C141B

SUBSYSTEM

STRUCTURAL

LANDING GEAR

PROPULSION

APU

ELECTRICAL

HYDRAULICS

ACTUATORS

AVIONICS

ECS

PERSON PROV

REC & AUX SYS

AIRCRAFT

MODE 1

3.6

1.5

9.6

147

37.3

5.6

11.1

1.7

16.6

210

120.7

.50

MODE 2

1.3

3.6

9.6

60.7

46.1

5.6

3.1

1.8

16.6

50.1

120.8

.43

MODES

1.7

7.8

9.6

54.1

39.1

5.6

5.0

1.7

16.6

50.1

120.8

.52

OCT87MAR 88

2.7

6.8

3.3

41.5

8.9

15.6

4.9

4.0

10.7

30.8

96.7

.57

APR 88SEP 88

2.3

6.3

2.6

32.0

7.6

14

4.5

3.2

9.9

23.3

87.0

.48

62

VII. User Options

At the conclusion of a run, the user has the option of repeating the analysis after changingone or more of the input parameters. Regardless of the mode, the primary variable screen willbe displayed for update. If in mode 2 or 3, the subsystem weight menu will be available forupdate, and if in mode 3, the secondary variable menu will also appear. The calibration andmission/subsystem profile menu and technology growth rates will also be available for update.

The user may also save all of the current input menus for use at a later time. The calculatedMTBMs (both space adjusted and critical operating hours between failures) may also be savedfor a more detailed reliability calculation.

63

Chapter VI

Conclusion

This report describes the data, methodology, and results of a one year research effort todevelop a model for predicting R&M parameters for conceptual space transportation systems foruse in determining operational capabilities and support costs. Whilethe model appears to work reasonable well when applied to aircraft systems, its accuracy whenused for space systems has not as yet been demonstrated.

The model is dynamic and should be updated as new data becomes available. It isparticularly important to integrate the current aircraft data base with data obtained from theShuttle and other space systems. Subsystems unique to a space vehicle such as the TPS,propulsion systems, and docking systems require data not available from aircraft. Although thisstudy has included these subsystems in a rationale way using comparabilitywith aircraft subsystems, their uniqueness requires the use of R&M parameters obtained fromsimilar subsystems in order to insure a higher degree of accuracy. As the model is used overtime, those features which seem to work should be retained while those which do not providereasonable results should be replaced. The model is modularized in the sense that any regressionequation may be easily replaced without affecting other areas of the model.

Finally, this research addressed only the major subsystems on the vehicle. The spacetransportation system includes booster rockets, launch and recovery facilities, software, andexpendable fuels, oxygen, etc. Therefore, follow-on research efforts should focus on theseaspects of the system. Much work remains as well in refining the subsystem analysis. Betteraccuracy may be achieved by analyzing component (rather than subsystem) failures and repair.Subsystems may then be defined in terms of their individual components. This would alsopermit a more explicit determination of redundancy and its effect on mission reliability.

64

BIBLIOGRAPHY

1. Aircraft Historical Reliability and Maintainability Data, Vols. V & VI, J. Osmanski, ed.Air Force Acquisition Logistics Center, Pamphlet 800-4. Dayton: Department of the"Air Force, 1988, 1990.

2. Aviation 3-M Information Reports, NAVSEALOGCEN INSTR 4790.1.Mechanicsburg: Department of the Navy, 1988.

3. Aviation Week and Space Technology, Vol. 134, No. 11. March 18, 1991.

4. Barnard, R. A. and T. D. Matteson. "Military Aircraft Maintenance - A NewConcept." Proceedings 1975 Annual Reliability and Maintainability Symposium pp. 596-600. New York: Institute of Electrical and Electronic Engineers, 1975.

5. Bloomquist, C. and W. Graham. Analysis of Spacecraft On-orbit Anomalies andLifetimes. For Goddard Space Flight Center Contract No. NAS 5-27279. Los Angeles:PRC Systems Service, 1983.

6. Brussell, E. R., K. R. Pope, and K. M. Tasugi. "Cost of Ownership - IndustryViewpoint: Parametric Analysis of Operating and Support Costs." Proceedings 1975Annual Reliability and Maintainability Symposium pp. 217-220. New York: Instituteof Electrical and Electronic Engineers, 1975.

7. Earles, D. R. "LCC - Commercial Application: Ten Years of Life Cycle Costing."Proceedings 1975 Annual Reliability and Maintainability Symposium pp. 74-85. NewYork: Institute of Electrical and Electronic Engineers, 1975.

8. Green, W. and G. Swanborough. Observer's Directory of Military Aircraft. New York:Arco Publishing, Inc., 1982.

9. Harmon, D. F., P. A. Pates, and D. Gregor. "Maintainability Estimating Relationships."Proceedings 1975 Annual Reliability and Maintainability Symposium, pp. 18-25. NewYork: Institute of Electrical and Electronic Engineers, 1975.

10. Hecht, H. and E. Florentino. "Reliability Assessment of Spacecraft Electronics." 1987Proceedings Annual Reliability and Maintainability Symposium pp. 341-345. New York:Institute of Electrical and Electronic Engineers, 1987.

11. Hecht, H. and M. Hecht. Reliability Prediction for Spacecraft. Rome Air DevelopmentCenter Final Technical Report No. 85-229, 1985.

65

12. Hintle, Jerry. "Number Cruncher Statistical System, Version 5.03." Kaysville, UT,September 1991.

13. Jane's All the World's Aircraft, J. W. R. Taylor, ed. New York: McGraw-Hill BookCompany, 1971-1990.

14. Kern, G. A. and T. M. Drnas. Operational Influences on Reliability. For Rome AirDevelopment Center Contract No. RADC-TR-76-366. Culver City: Hughes AircraftCompany, 1975.

15. "Modular Life Cycle Cost Model for Advanced Aircraft Systems, Phase III", GrummanAerospace Corp., Bethpage, NY. Contract No. AFF DC-DC-TR-78-40, Vol. IV, Rev.3, September 1986.

16. Norris, H. P. and A. R. Timmins. "Failure Rate Analysis of Goddard Space FlightCenter: Spacecraft Performance During Orbital Life." Proceedings 1976 AnnualReliability and Maintainability Symposium pp. 120-125. New York: Institute ofElectrical and Electronic Engineers, 1976.

17. Ostrofsy, B. "Development of I.L.S. Models from R and M Data." Proceedings 1975Annual Reliability and Maintainability Symposium pp. 130-138. New York: Instituteof Electrical and Electronic Engineers, 1975.

18. Peacore, E. J. "Reliability Developments - AWACS." Proceedings 1975 AnnualReliability and Maintainability Symposium pp. 383-389. New York: Institute ofElectrical and Electronic Engineers, 1975.

19. Personnel Launch System Advanced Manned Launch System (AMLS): PLSReliability I Maintainability Analysis, Ehrlich, Jr., C. F., ed. For Langley ResearchCenter Contract No. NAS1-18975. Los Angeles: Rockwell International Space SystemsDivision, 1990.

20. Personnel Launch System (PLS) Advanced Manned Launch System Study (PLS/AMLS):Final Oral Review. For Langley Research Center Contract No. NAS1-18975. LosAngeles: Rockwell International Space Systems Division, 1990.

21. Report on the Development of a Spacecraft Supportability Assessment Model. LosAngeles: Rockwell International Space Systems Division, n.d.

22. "USAir Reliability Assurance Program Monthly Report," prepared by The Reliability andMaintenance Programs Department, Pittsburgh, PA, May 1991.

66

APPENDIX A

AFALDP 800-4 Format

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APPENDIX B

MODAS Report Format

Operational SummaryDate Range = January, 1990 TO December, 1991 , Base Code = ****MDS/CMD = F004E /***

Date

123456789101112123456T89101112

909090909090909090909090919191919191919191919191

FlightHours

483246075185497449954932445954343392442939683003270227773374338126582096193016749821175816619

Poss. Avg.Hours Sorties Landings Inv.

164606179401139978186269194349167411249048246912237120243360234000241800241080217728238920227580229728221304226776211698198336196536180888181536

40393757415339273986395036174481292537373399258623652342256123842095172015071205739847607521

470443364483453443684255410547633121439835842710273225072696272522541802179813387921076724640

220266190258261232335332330325325325323324320316311307305284276264252244

Percnt PercntFMC PMC

646864696866798381828086888485869092919295969798

.76

.59

.92

.08

.83

.10

.18

.59

.05

.89

.04

.26

.23

.38

.97

.62

.80

.52

.91

.99

.98

.41

.24

.04

667679334453222100000000

.68

.97

.35

.88

.85

.97

.34

.57

.72

.19

.05

.17

.38

.41

.03

.40

.73

.33

.27

.38

.16

.29

.23

.25-

PercntNMC

28:5624.4527.7224.0423.3223.9417.4812.8414.2312.9214.9110.569.3913.2112.0011.978.477.157.826.633.863.302.531.71

78394 5056364 63450 70445

B-l

Summary Maintenance Data - ManhoursDate Range = January/ 1990 TO December, 1991 , Base Code = ****MDS/WUC = F004E /ll***

Flight Hours Maintenance ManhoursOn-Eq

Date Mo Cum On-Eq; Off-Eq Sup Total Events

1 902 903 904 905 906 907 908 909 9010 9011 9012 901 912 913 914 915 916 917 918 919 9110 9111 9112 91

483246075185497449954932445954343392442939683003270227773374338126582096193016749821175816619

78394

4832943914624195982459329525339843941842810472395120754210569125968963063664446910271198731287480275784769597777578394

On-Eq

89055358824880466444454853324323425554437135490659331961308229036641127252594410281154422550

Off-Eq

2592595097165502183401986662092291776317902417133181195517

Sup

00000.00000000000 -00-000000

Total

91645617875787626994476656724342434155097344513561102024309929936881144265896210391249427567

95236 4127 99363

2203.1216182716931521110311319389859711290838928319399633246212314247254342124141

19875

MMHTK

3.563.794.224.343.863.704.283.704.034.944.954.895.665.095.074.102.624.956.813.513.723.443.023.64

B-2

Abort Summary - ON EquipmentDate Range = January, 1990 TO December, 1991 , Base Code = ****MDS/WUC = F016A /ll***

1234567

90909090909090

8 909 9010 9011 9012 901 912 913 914 915 916 917 918 919 9110 9111 9112 91

Flight

Mo

11801109321232711936116811246610915127651003311958107619011969612238115041179611696978793001030298181093688697693

Hours

Cum J

1180122733350604699658677711438205894823104856116814127575136586146282158520170024181820193516203303212603222905232723243659252528260221

;

\ir GI

i00001412102110402411002

&ort Coui

round T<

83753817425571040523543358

it

3tal

937539215465911509259543510

Cum

9121924273657626672778697102102111113118127132136139144154

Sort

MO

861876848910895386189222787594867473872678856477681785908088780480127326718079797315808966795902

:ies

Cum

86181630225212341654278352005598806936676839855659345099927106744115334123422131226139238146564153744161723169038177127183806189708

260221 28 126 154 189708

B-3

Summary Maintenance Data - FailuresDate Range = January, 1990 TO December, 1991 , Base Code = ****MDS/WUC = F004E /ll***

Flight Hours On-Equipment Failures

1 902 90345

909090

6 907 908 909 9010 9011 9012 901 912 913 914 915 916 917 918 919 9110 9111 91.12 91

MO

483246075185497449954932445954343392442939683003270227773374338126582096193016749821175816619

78394

Cum

4832943914624195982459329525339843941842810472395120754210569125968963063664446910271198731287480275784769597777578394

Tl

61037549248929225517928119767538307416408018583504410258532141.

T2

113606845672434402021723156121121196151013314

T6

1671141281201321601879587124106794729666318182312191493

Total

89054968865449143940041630421271641751981157269120748212490703148

5255 766 1820 7841

Removals

558302414370183144771499030310128215114783

: '.': 483122502320

' 710

3322

B-4

System Summary - ReliabilityDate Range = July, 1991 TO July, 1991 , Base CodeMDS/WUC = F015A /****»

Failure Count

= *ts*

MTBM

System

2 = POWER PLAN33=LOOK PH SC34=SPECIAL IN11=AIRFRAME12=CKPT &. FUS13=LANDING GE14=FLIGHT CON32=NOT DEFINEU=AIR COND P42=ELECTRICAL43=NOT DEFINE44=LIGHTING Si5=HYD AN PNE16=FUEL SYSTE47=OXYGEN SYSi9=MISC UTILI51= INSTRUMENT52=AUTOPILOT53=NOT DEFINE54=NOT DEFINE55=MALF ANAL57=INTER GUID32=NOT DEFINE53=UHF COMMUN55=IFF?1=RADIO NAVI74=FIRE CONTR75=WPN DLVRY76=TAC ELEC W31=EMERG EQUI32=TOW TARGET37=EXPLOSIVE

Removal

86500

374630281038360

3166851319149390117180898911241591116190

123

MTBR

700

17113721780

1661760

2049674487333421620

63433733520

717156156954

3330

51

Tl

68200

21543306118053300

3888771411150390119661

16917411344790163103

T2

4500

203171003101131130000405815200.01

T6

131700

24796119120899605

25731479

361625910123109091120560373116200

124

Total

204400

4821424422488

155915

6416222724483159811

31101

12642732341012465279210

128

Tl

9002914720530

1192110

16672.82453576421620

634333396

6343373656147038

63430

2114

T2

14100

31721143736340

21146343

0634363432114634363432114

0000

15850

1268792

634312683171

000

6343

T6.

4 —0 •0^

2566-5352-

792 -64-1051268253864370417639-1076343

-. o .528204

o-7069,52:111754 -3170

51.

Total

3001344-1425-7924069

12689939272641322064

6343634320462

63432423276

1322302049

TOTAL 2897 3111 135 4120 7366

B-5

System Summary - MaintainabilityDate Range = August. 1989 TO July, 1991MDS/WUC = F015B /***** F015A /**«*«

Maintenance Manhours

, Base Code = ****

On Equip. Off Equip.^IM^»«»M

MHTCSystem

01=NOT DEFINE2 = POWER PLANOSsLOOK PH SC04sSPECIAL INOSsNOT DEFINE06sNOT DEFINE07sNOT DEFINEOSsNOT DEFINEOSsNOT DEFINElOsNOT DEFINE11=AIRFRAME12=CKPT i FUS13sLANDING GE14=FLIGHT CONISsNOT DEFINE16sNOT DEFINE17=NOT DEFINEISsNOT DEFINE31=NOT DEFINE32sNOT DEFINE33sNOT DEFINE34sNOT DEFINE36sNOT DEFINE39sNOT DEFINE40sNOT DEFINE41sAIR COND P42sELECTRICAL43sNOT DEFINE44sLIGHTING S45sHYD AN PNE46=FUEL SYSTE47=OXYGEN SYS48sNOT DEFINE49sMISC UTILISOsNOT DEFINESlsINSTRUMENT5 2s AUTOPILOT53sNOT DEFINE54sNOT DEFINESSsMALF ANAL56sNOT DEFINE57sINTER GUID59sNOT DEFINE61sNOT DEFINE62sNOT DEFINE63sUHF COMMUN64sNOT DEFINE65sIFF66sNOT DEFINE69=NOT DEFINETOsNOT DEFINE71sRADIO NAVI

On-eq

0599911

00000006

268809500577059331141

5325967619233335 -

213

4653731397335

33792535461385506246103313409528

43838196604334152

79082

9441126

2912677

2651913111

34342

Off-eq

0239764

00000040

64274522418319679

226021002418000

839125912

15519562773471316

07900

1474111820

221

50970

509101619

2520443

406023300

28190

Supp

549874173219721345544554

44777327444121034

1952250000000000000000000000000000000000000000000

Total

5498741062894721345544554

44777327444121034

1952296

2752365457911242490820

75853067619437515

213

5492857309336

39311591731458977562103314199528

58579314804356153

130052

135321

1825

54330120

6712146111

62532

MH/FH

3.4646.6974.5453.4310.0030.4870.2800.0071.2300.0001.7340.3440.7080.5720.0000.0010.0000.0000.0000.0010.0000.0000.0000.0000.0000.3460.3610.0020.2480.3730.9190.0480.0070.0890.0030.3690.1980.0270.0010.0820.0000.0850.0000.0000.0000.3420.0010.4230.0000.0000.0000.394

MMHTR

0.0009.3340.0000.0000.0000.0000.0000.0000.0000.6003.8465.7785.0946.6704.4171.3332.2502.0003.4553.1765.2004.8335.0002.0000.0005.9456.4652.6293.1265.96113.4173.73913.8008.2141.0004.6787.9986.4145.5004.2240.0003.4711.0000.0002.0003.3164.7143.1402.0000.0001.0004.096

MHTR

040376

00 .o •-o -~0^OT-02or

38173389192385387"11-600 •Or:o -Ox.0*83F0 =OtOJL

678722499

04080351016605280

3170

47117613

70

28680 -

31470

13 -12-

1697941

3220527"00

13382

0000000o .0004010000000000o00o;Oi000,00000000000001000000

B-6

Maroon IndustriesRecord Type: AMDS: B001B

*«* M 0 D A S II ***Detail Maintenance Data Report

TotalTime

Summary ReportAUG 90

Cum.CrewSize

TotalMan-hours

TotalUnits

Produced

214.8 247 520.8Hit <RETURN> to continue, or "$" to end output:MO DAS II *** Page: 1Record Type: A Detail Maintenance Data ReportMDS: BOOIB

101Marcon Industries

Summary ReportSEP $0

TotalTime

Cum.CrewSize

TotalMan-hours

TotalUnits

Produced

162.0 180 306.8Hit <RETURN> to continue, or "$" to end output:Marcon Industries **t MO DAS II ***Record Type: A Detail Maintenance Data ReportMDS: BOOIB

88

Summary ReportOCT 30

TotalTime

Cum.CrewSize

TotalMan-hours

295.9 349 757.6Hit <RETURN> to continue, or "$" to end output:

TotalUnits

Produced

141

B-7

Failures selected are All FailuresReliability - MTBM (by type)

Date Range = August, 1989 TO July, 1991 , Base Code = ****MDS/WUC = F015A /74F** F015B /74F**

Flight Hours Mean Time Between Maint.Failure

Date Mo Cum Count

8 899 8910 8911 8912 891234567

90909090909090

8 909 9010 9011 9012 901 912 913 914 915 916 917 91

TOTAL

Mo

778253277402606653946587610071337369690868615732742851277004682154496182613570436757776868957449

i -

Cum

77821310920511265773197138558446585179159160660687292978661860899121698220105041110490116672122807129850136607144375151270158719

' '158719

949615845750589111262591955389779411637419611092703726955792830936916691707

19861

Monthly

8.208.668.768.099.165.929.767.76

13.337.708.644.9310.025.346.419.707.516.477.758.497.228.489.9810.54

3mo avg

8.208.388.518.508.647.367.777.469.829.049.426.837.426.387.006.887.657.747.187.517.798.048.429.56

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C-12

APPENDIX D

R&M Data Sources

Government:

FAAOperations Systems Branch, AVN-120PO Box 25082Oklahoma City, Oklahoma 73125

US Air Force:

Rome Laboratory/ERSR (MIL HNDBK-217)Griffiss AFB, NY 13441-5700

Aeronautical Systems Division/ENACR (System Reliability)Wright-Patterson AFB, OH 45433

HQ Air Force Logistics Command/ENIS (MODAS & REMIS)WPAFB, OH 45433

Acquisition Logistics Division (ALD Pamphlet 800-4)WPAFB, OH 45433

Aeronautical Systems Divisiou/ENSSC (LCOM)WPAFB, OH 45433

Reliability Analysis Center (RAC)PO Box 4700Rome, NY 13440-8200

Naval Air Systems Command (AIR-4114)Washington, DC 20361

Naval Maintenance Support OfficeNaval Sea Logistics Center, Code 615450 Carlisle PikePO Box 2060Mechanicsburg, PA 17055-0795

Commerciah

Airbus Industrie of North America593 Herndon ParkwayHeradon, VA 22070

American Institute of Aeronautics and Astronautics (AIAA)37 UEnfant Promenade SWWashington, DC 20024

D-l

Commercial (continued)

Boeing Commercial Air PlanesPO Box 3707Seattle, WA 98124

Boeing Computer Services7990 Boeing CourtVienna, VA 22182-3999

Douglas Aircraft Company3855 Lakewood Blvd.Long Beach, CA 90846

E-SystemsPO Box 1056Greenville, TX 75401

Harris Corporation4141 CoL GlennDayton, OH 45431

Harris CorporationGovernment Aerospace Systems DivisionPO Box 9400Melbourne, FL 32902

Hughes Aircraft CompanyRadar Systems GroupPO Box 92426Los Angeles, CA 90009

Society of Automotive Engineers (SAE), Inc.400 Commonwealth Dr.Warrendale, PA 15096-0001

United AirlinesSan Francisco International Airport (MOC/SF Airport)San Francisco, CA 91428

US Air173 Industry Dr.Pittsburgh, PA 15275

D-2

APPENDIX E

Data Generation Programs (BASIC)

Basic Program for Data Analysis

AFALDP 800-4

'PROGRAM COMBINES 6 MONTH DATA FROM ALDP 800-4'COMPUTES RiM STATS FOR VARIOUS 2 -DIGIT WUC'SKEY OFF : CLS : COLOR 3PRINT TAB (20) "CALCULATION OF AIRCRAFT R4OOM PARAMETERS'PRINT: PRINTDIM MTBM(10,10) ,MMH( 10,10 ) ,WUC$( 10)FOR J=l TO 5READNEXT

AIRCRAFT" ; ACSNUMBER OF 6-MONTH INTERVALS "; MUM

FOR 1=1 TO NUMPRINT "ENTER FLYING HOURS FORINPUTPRINTINPUTPRINT

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INPUT "ENTER. INPUT "ENTER

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LANDINGS FOR

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; I; "6 -MONTH PERIOD"

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MMH(I.J)"ENTER OFF-EQUIP MMH FOR";WUC$(J)OMMH(I,J)

FH(I)"ENTERS(I)"ENTER

INPUT L(I)FOR J=l TO 5PRINT "ENTERINPUT MTBM (IPRINT "ENTERINPUTPRINTINPUTPRINTNEXT JNEXT ICLS: COLOR 2PRINT TAB (20)LPRINT TAB (20)PRINTLPRINTFOR 1=1 TO NUMTFH=TFH+FH(I)TS=TS+S(I)TL=TL+L(I)NEXT IPRINT TAB (10) "TOT FLYING-HBS" ; TAB (40) TFHLPHINT TAB (10) "TOT FLYING-HRS" J TAB (40 ) TFHPRINT TAB(IO) "TOT SORTIES" ; TAB (40) TSLPHINT TAB (10) "TOT SORTIES" ; TAB (40 ) TSPRINT TAB (10) "TOT LANDINGS" ; TAB (40) TLLPRINT TAB (10) "TOT LANDINGS" ; TAB (40) TLPRINT: LPRINTFOR J=l TO 5FOR 1=1 TO NUM

OUTPUT RESULTS FOR"OUTPUT RESULTS FOR

;ACS";ACS

E-l

TMAINT(J)=TMAINT(J)+<1/MTBM(I,J))*FH(I)TMMH(J)=TMMH(J)+MMH(I,J)TOMMH(J)=TOMMH(J)+OMMH(I,J)NEXT ITOTMH{J)=TMMH{J)+TOMMH{J)MFHBMC J)=TFH/TMAINT(J)MSBM(J)=TS/TMAINT(J)MLBM(J)=TL/TMAINT(J)MHFH{J)=TOTMH{J)/TFHMHS(J)=TOTMH(J)/TSPRINT:PRINTLPBINT:LPRINTPRINT TAB(10) "WUC ";WUCS(J):PRINTLPRINT TAB (10) "WUC " ; WUCS ( J ) : LPRINTPRINT TAB(15) "TOTAL MAINTENANCE EVENTS"; TAB(50) TMAINT(J)LPRINT TAB(15) "TOTAL MAINTENANCE EVENTS"; TAB(50) TMAINT(J)PRINT TAB(15) "TOTAL MAINTENANCE MANHOURS";TAB(50) TOTMH(J)LPRINT TABUS) "TOTAL MAINTENANCE MANHOURS"; TAB ( 5 0 ) TOTMH(J)PRINT TAB(20) "TOTAL ON-EQUIP MAINT";TAB(50) TMMH(J)LPRINT TAB(20) "TOTAL ON-EQUIP MAINT";TAB(50) TMMH(J)PRINT TAB(20) "TOTAL OFF-EQUIP MAINT";TAB(50) TOMMH(J)LPRINT TAB(20) "TOTAL OFF-EQUIP MAINT";TAB(50) TOMMH(J)PRINT:COLOR 12LPRINTPRINT TABU5) "MEAN FLYING HR BTWN MAINT" ; TAB(50) MFHBM(J)LPRINT TAB(15) "MEAN FLYING HR BTWN MAINT";TAB(50) MFHBM(J)PRINT TAB{15) "MEAN SORTIES BTWN MAINT";TAB(50) MSBM(J)LPRINT TABUS) "MEAN SORTIES BTWN MAINT" ;TAB< 50) MSBM(J)PRINT TABUS) "MEAN LANDINGS BTWN MA1NT";TAB{50) MLBM(J)LPBINT TABUS) "MEAN LANDINGS BTWN MAINT"; TAB (50) MLBM(J)PRINT TABUS) "MAN-HOURS PER FLY-HR" ;TAB( 50) MHFH(J)LPBINT TABUS) "MAN-HOURS PER FLY-HR" ; TAB ( 50 ) MHFH(J)PRINT TABUS) "MAN-HOURS PER SORTIE" ; TAB (50) MHS(J)LPBINT TABUS) "MAN-HOURS PER SORTIE" ; TAB ( 50 ) MHS(J)PRINT:LPRINTMHPF(J)=TOTMH(J)/TMAINT(J)MHPFON(J)=TMMH(J)/TMAINT(J)OMHPF(J)=TOMMH(J)/TMAINT(J)PRINT TABUS) "MAN-HOURS PER MAINT ACTION" ; TAB ( 50 ) MHPF(J)LPBINT TABUS) "MAN-HOURS PER MAINT ACTION" ; TAB ( 50 ) MHPF(J)PRINT TAB(20) "ON-EQUIP MAN-HRS/MAINT ACTION";TAB(50) MHPFON(J)LPBINT TAB (20) "ON-EQUIP MAN-HRS/MAINT ACTION" ; TAB ( 50 ) MHPFON (J)PRINT TAB(20) "OFF-EQUIP MAN-HRS/MAINT ACTION" ; TAB( 50 ) OMHPF(J).LEBINT TAB(20) "OFF-EQUIP MAN-HRS/MAINT ACTION" ; TAB ( 50 ) OMHPF(J)PRINTLPBINT: LPRINTNEXT JCOLOR 3GOSUB 1000END

E-2

10 'PROGRAM COMBINES 4 QUARTERS OF DATA FROM NAVY 3M SYSTEM20 "COMPUTES R&M STATS FOR A PARTICULAR 2-DIGIT WUC30 KEY OFF:CLS:COLOR 340 PRINT TAB(20) "CALCULATION OF AIRCRAFT R&M PARAMETERS"50 PRINT:PRINT !

60 DIM MTBM(IO),MMH(10),ACFT$(10)70 FOR 1=1 TO 980 READ ACFT$(I)90 NEXT I100 INPUT "ENTER WUC";WUC$105 LPRINT TAB(IO) "NAVY 3M DATA SYSTEM - R&M SUMMARY REPORT COMPOSITE"106 LPRINT:LPRINT110 LPRINT TAB(10) "WUC ";WUC$:LPRINT120 NUM=4130 FOR J=l TO 9135 TFH=0:TMA=0:TMMH=0:TET=0:TFAIL=0140 PRINT TAB(5) "FOR AIRCRAFT ";ACFT$(J)145 LPRINT:PRINT150 FOR 1=1 TO NUM160 PRINT "ENTER DATA FOR QTR";I170 READ FH(I)180 INPUT "ENTER MAINT ACTIONS FOR QTR";MA(I)190 INPUT "ENTER UNSCH MAINT MAN-HRS - QTR";MMH(I)210 INPUT "ENTER ELASPSED MAINT TIME":EMT(I)220 PRINT230 NEXT I240 CLS:COLOR 2250 PRINT TAB(20) "OUTPUT RESULTS FOR ";ACFT$(J)260 LPRINT TAB(20) "OUTPUT RESULTS FOR ";ACFT$(J)270 PRINT280 LPRINT290 FOR 1=1 TO NUM300 TFH=TFH+FH(I)310 TMA=TMA+MA(I)320 TMMH=TMMH+MMH(I)330 TET=TET+MA(I)*EMT(I)350 NEXT I360 PRINT TAB(IO) "TOT FLYING-HRS";TAB(40) TFH370 LPRINT TAB(10) "TOT FLYING-HRS";TAB(40) TFH380 PRINT TAB(IO) "TOT MAINT ACTIONS";TAB(40) TMA390 LPRINT TAB(IO) "TOT MAINT ACTIONS";TAB(40) TMA400 PRINT TAB(10) "TOT MAN-HRS";TAB(40) TMMH410 LPRINT TAB(IO) "TOT MAN-HRS";TAB(40) TMMH440 PRINT TAB(IO) "TOT ELAPSED TIME";TAB(40) TET450 LPRINT TAB(IO) "TOT ELAPSED TIME";TAB(40) TET460 PRINT:LPRINT470 MFHBMA=TFH/TMA480 MMHFH=TMMH/TFH490 AVEMT=TET/TMA500 AVCREW=TMMH/TET520 PRINT .'PRINT540 PRINT:COLOR 12550 LPRINT560 PRINT TABUS) "MEAN FLYING HR BTWN MAINT";TAB(50) MFHBMA570 LPRINT TAB(15) "MEAN FLYING HR BTWN MAINT";TAB(50) MFHBMA580 PRINT TAB(15) "MAN-HOURS PER FLY-HR";TAB(50) MMHFH590 LPRINT TABUS) "MAN-HOURS PER FLY-HR" ; TAB ( 50 ) MMHFH600 PRINT TABUS) "AVG ELAPSED MAIN TIME" ; TAB (50 ) AVEMT610 LPRINT TABUS) "AVG ELAPSED MAIN TIME" ;TAB( 50) AVEMT620 PRINT TABUS) "AVG CREW SIZE" ;TAB( 50) AVCREW630 LPRINT TABUS) "AVG CREW SIZE" ; TAB ( 50 ) AVCREW

E-3

PRINT TAB(15)LPRINT TAB (15)PRINTLPRINT: LPRINT

660670680690691695700710711712720 END1000 DATA10101020103010401050106010701080

NEXT JCOLOR 3LPRINT:LPRINTLPRINT:LPRINTLPRINT TAB(20;

MAN-HOURS PER MAINT ACTION";TAB(50) TMMH/TMA"MAN-HOURS PER MAINT ACTION";TAB(50) TMMH/TMA

= SUM2-1-TMMH:SUM3 =

TAB(IO) "SUMMARY STATS FOR ";WUC$TAB(20) "AVG TASK TIME";TAB(40) SUM1/SUM3"AVG CREW SIZE";TAB(40) SUM2/SUM1

1090

DATADATADATADATADATADATADATADATADATA

" A4-E" , "A-4F" , "EA-6B" , "A-6E" , "A--7E1

1579,1598,1770,13982335,2384,2625,25277444,6080,8517,598217022,14906,16840,153284624,5404,4989,5562751,3794,3871,17777341,9143,9738,603617856,15592,17214, 1518421649,19976,30652,19734

"C-2A","E-2C","F-18A","F-14A"

E-4

'PROGRAM COMBINES 6 MONTH DATA FROM ALDP 800-4'COMPUTES SCHEDULED MAINT AS A PERCENT OF TOTAL MAINTKEY OFF:CLS:COLOR 3PRINT TABJ20) "CALCULATION OF AIRCRAFT SCHEDULED MAINT"

PRINT"ENTER AIRCRAFT TYPE";AC$"ENTER TIME PERIOD";TIM$"ENTER NUMBER OF TIME PERIODS";NUMTO NUM

PRINT:INPUTINPUTINPUT

102030405060708090 FOR 1=1100 PRINT

PRINTINPUTINPUTINPUTINPUTINPUTINPUTINPUTINPUT

110112113120130140150160170180190200210220230231232240250260270280290300310320330340350360370380390400410420430440450460500

"FOR TIME PERIOD";!"ENTER TOT FLY HRS";FLY(I)"ENTER TOT SORTIES";SORT(I)"ENTER SCHED INSP-03 HRS";SCH3(I)"ENTER SCHED INSP-03 HRS OFF";OSCH3(I)"ENTER SCHED INSP-04 HRS ON";SCH4(I)"ENTER SCHED INSP-04 OFF HRS";OSCH4(I)"ENTER TOT ON EQ MHRS";TOTON(I)"ENTER TOT OFF EQ MHRS";TOTOFF(I)

SUM1=SUM1+SCH3{I)+OSCH3(I)+SCH4(I)+OSCH4(I)SUM2=SUM2+TOTON(I)+TOTOFF(I)SUM3=SUM3+SCH3(I)+SCH4(I)SUM4=SUM4+OSCH3(I)+OSCH4(I)SUM5=SUM5+TOTON(I)SUM6 =SUM6+TOTOFF(I)TFLY=TFLY+FLY(I)TSORT=TSORT+SORT(I)NEXT IPERSCH=SUM1/SUM2PERON=SUM3/SUM5PEROFF=SUM4/SUM6CLS:COLOR 3LOCATE 5,10:PRINT TAB(20) "AIRCRAFT TYPE";TAB(45)PRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTPRINTEND

TAB(20) "TIME PERIOD IS";TAB(45) TIM$AC$

TAB(10) "SCHEDULED MAINTENANCE PERCENTS"TAB(10) "OF TOTAL MAINTENANCE";TAB(40) PERSCHTAB(lO) "OF ON-EQ MAINTENANCE";TAB(40) PERONTAB(lO) "OF OFF-EQ MAINTENANCE";TAB(40) PEROFF

TAB(lO) "AS A PERCENT OF UNSCHEDULED MAINTENANCE"

TAB(10)TAB(10)TAB(lO)

TAB(IO)TAB(lO)TAB(10)TAB(IO)

"TOTAL";TAB(40) SUM1/(SUM2-SUM1)"ON-EQ";TAB(40) SUMS/(SUMS-SUMS)"OFF-EQ";TAB(40) SUM4/(SUM6-SUM4)

"SCH MAINT HRS PER FLY HR";TAB(40)"SCH MAINT HRS PER SORTIE";TAB(40)"% SCHED ON-EQUIP";TAB(40) SUMS/SUMl11 % SCHED OFF-EQUIP";TAB(40) SUM4/SUM1

SUM1/TFLYSUM1/TSORT

E-5

APPENDIX F

Variable Definitions

INDEPENDENT VARIABLE

Variable Name

ACT

ACTWT

AV INSTA

AVWT

AVS

BODYWT

BTU COOL

CONTS

CREW

DIP SUBS

DRYWT

ECS WT

ELECT WT

Definition

Total number of actuators to operate all vehicle movableflight surfaces.

Weight of the actuator subsystem in pounds.

Weight in pounds of brackets, shelves, wiring and plugsused on avionics equipment.

Weight in pounds of avionics equipment uninstalled (doesnot include wiring, shelves, ducts, fasteners, etc.).

Total number of avionics (AN nomenclature) subsystems.

Weight of the body (fuselage) in pounds.

Total cooling capacity of air conditioning equipment usedfor personnel and equipment cooling. Measured inBTU/HR/1000.

Total number of control surfaces - ailerons, rudders,elevator tabs, flaps, spoilers and slats.

Total number of crew members (repair or flyingdepending upon context).

Total number of different avionics subsystems (two ormore identical units count as one).

Empty weight (without fuel) of vehicle in pounds.

Total weight of the environmental control systemincluding heating, cooling and anti-icing equipment inpounds.

Weight of electrical subsystems in pounds.

F-l

ENG

ENG WT

FUEL TK

FUS AREA

FUS DENS

FUS VOL

HYD WT

KVAMAX

L.GEAR WT

LEN + WING

MSN LEN

PASS

SUB WT

SUBS

WET AREA

WHEELS

Number of primary engines.

Weight of the engine in pounds.

Number of separate internal fuel cells, bladders andtanks.

External area of fuselage including canopy in square feet.

Fuselage density (weight/volume).

Total volume of fuselage, excluding any engine inlet ductvolume, in cubic feet.

Weight of Hydraulic subsystems in pounds.

Total electrical power of engines, motors, and APUdriven generators/alternators in kVA (thousands of voltamps).

Landing gear weight in pounds.

Aircraft length plus wing span in feet.

Mission length in hours. May be adjusted by/forsubsystem utilization.

Maximum number of passengers.

Total subsystem weight in pounds.

Total number of aircraft subsystems requiring use ofhydraulic or pneumatic power.

Total external surface area of vehicle in square feet.

Total number of wheels.

WING LEN Length of the wing in feet.

F-2

APPENDIX G

Design/Performance/Weight Values

DRY WGT LEN WINGA-4EA-4FA-6EA-7DA-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT-38AE-3A

96241016925558177921854620822152293474802400043032443414434128545287022966394593903726768274251444714447230506710071990739629703021450140882313693200836179024061337498321626673

188000

69691088585

11134414410813713713797971017512610710780829423123123226711432813847121234713811272299

WETAREA10721094218017031703260017645316422303117311731011989198919899473105263226431385139820508899889988991095427341535037293371262482110131502295971

FUS VOL571581

1231813813793

12447188913211889188918891270127012706601822149517165965969649060906090601155017101967827128661076474130013461361806

G-l

A-4EA-4FA-6EA-7DA-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT-38AE-3A

FUS AREA4784988987497497114942958985961961961100010009615831647140514687355518903460346034604420105066831336166463221911510431017533

CREWS I ZE1121116212222221211121444445353454223

PASSENGR ENGINES

929292800

2092836040750

1.001.002.001.001.002.008.002.001.002.002.002.002.002.002.002.002.002.002.001.001.002.004.004.004.004.004.004.002.004.002.003.002.002.002.00

G-2

A-4EA-4FA-6EA-7DA-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT-38AE-3A 8.20

MSN LEN2.502.504. 101.504.001.706.703.201.502.202.302.401.201.301.200.903.701.301.301.301.302.402.402.402.803.001.903.30

3.901.204.405.103.101.20

WHEELS334443844444444343333466610610428610443

ACTUATOR14.0014.0023.0026.0026.0023.0042.0031.009.0031.0031.0031.0024.0027.0027.0019.0041.009.009.0014.0014.0012.0015.0015.0015.0029.00

29.0025.00115.0024.0039.0025.0024.000.00

CONT SUR13.0013.0019.0012.0012.0014.0032.0028.006.0028.0028.0028.0017.0017.0017.0012.0023.009.008.0011.0011.0011.0014.0014.0014.0024.0016.00

18.0043.0020.0052.0018.0019.00

G-3


ECSWT63.0063.00420.00263.00263.00210.00670.00631.00407.00631.00631.00631.00392.00397.00403.00143.001048.00669.00669.00230.0023.00

1526.001836.001836.001473.00608.002648.00656.003636.001538.002186.00510.00585.00325.00

KVA MAX11.0011.0065.0027.5027.5060.00160.00130.0028.30130.0062.4057.4063.0063.0063.0055.00126.5050.00130.0050.0050.0080.00190.00190.00190.00120.0028.00252.00123.00484.00112.00360.00123.0092.0016.00

SUBSYS17.0017.0034.0038.0038.0020.0076.0038.0025.0038.0022.0035.0039.0033.0033.0016.0045.0028.0030.0020.0020.0014.0020.0020.0020.0012.008.00

i 33.00! 31.0072.0012.0030.0027.0034.0014.00

FUEL TK2.002.006.007.007.00

4.007.004.006.004.009.009.009.003.00

5.005.007.004.008.006.006.006.0010.006.0012.002.0012.00

*

15.00

6.004.00

AV WGT

1178.00

1153.008823.00

2135.00

303.00

1910.001938.001103.001103.00

3249.003249.00

2323.004240.00

4015.002143.004181.00

493.002353.00

G-4

A-4EA-4FA-6EA-7DA-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BO130EC-130HKG- 135 AO140AC-141BC-2AC-5AO9AKC-10AE-2CEA-6BT-38AE-3A

TOTSUBS14.0015.0027.0031.0037.0016.0019.0026.0016.0026.0028.0025.0014.0027.0028.0010.0033.0025.0025.0018.0018.0016.0023.0027.0030.0022.0020.0025.0018.0033.0018.0036.0029.0026.00

9.00

AV INSTA203.00

70.00663.00523.00506.00203.00

2949.001080.00801.00874.00

1089.00992.00434.00496.00626.00207.00619.00393.00364.00250.00336.00329.00658.00851.00800.00654.00556.00

1241.00425.00

1377.00800.00

1389.00965.00

59.00

DIF SUBS14.0015.0021.0031.0037.0016.0019.0022.0014.0024.0023.0025.0014.0027.0028.0010.0031.0025.0025.0018.0018.0014.0022.0025.0025.0022.0020.0018.0017.0025.0015.0025.0027.0023.00

5.00

BTU COOL"' 25.00

25.00130.0075.0075.0015.80

180.00127.4095.0095.50

142.2095.5040.0040.0040.0035.00

174.00153.00155.0040.0040.00

106.0078.00

105.0078.00

130.0034.00

118.0050.00

318.00200.00145.00195.00130.00

G-5


WGT WING

3269

510737369

4688468846881349

339936421808

11626116261162625305295435092

1000121139259202

79532654

WGT TAIL

832

9676030

913913913328

10981104719

34103410341055658805907

12719279114636

3026310

WGT BODY

3302

474526731

4801480148012617

616062453118

14338143381433820732373636822

1212591182246987

214035193

G-6


WGT13

1267

148612992

196219621962768

130513439241067

48734873487311023108110850

38282429526211

52713330

WOT 14

1196.00

836.002591.00

ENG WGT

4497

428336554

WGT 2 4

157.00

1001.001001.001001.00422.00

800.00810.00718.00718.00

1693.001693.001693.002287.00939.003701.00

7263.001639.005773.00

9968996899682247

604960913671

166961669623386380425471

390911053543162

481.00482.00164.00170.40

451.00460.00460.00945.00

535.00367.001080.00832.001486.00

394.003214.00

176723321 500.00

G-7

A-4EA-4FA-6EA-7DA-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BO2AC-5AC-9AKC-10AE-2CEA-6BT-38AE-3A

WGT42

1094.00

732.006047.00

536.00536.00536.00310.00

583.00607.00441.00441.00

2299.002299.002299.004152.001937.002823.00

4046.001766.004862.00

327.00

WGT45

210.00

373.001915.00

601.00601.00159.00

431.00433.00309.00309.00

666.00666.00666.00880.00338.001605.00

4484.00756.004170.00

147.00

WGT51/72

1178.00

1153.008823.00

2135.00

303.00

1910.001938.001103.001103.00

3249.003249.00

2323.004240.00

4015.002143.004181.00

493.002353.00

G-8

APPENDIX H

Dependent Variable Values

FHBMA11 MH/MA11A-4EA-4FA-6EA-7D 10.00 5.80A-7EA-10A 11.30 5.20B-52G 3.00 6.90FB-111A 1.10 3.90F-106A 10.10 7.40F-111A 2.90 4.30F-111D 2.50 4.40F-111F 2.30 4.30F-4C 5.10 6.20F-4D 3.60 5.40F-4E 4.20 6.70F-5E 7.90 7.60F-14AF-15A 3.00 5.70F-15C 2.68 9.00F-16A 8.32 5.20F-16B 6.50 4.10F-18AC-130B 3.40 5.70C-130E 5.30 8.10C-130H 4.70 9.80KC-135A 4.00 6.00C-140A 9.40 9.20C-141B 3.63 6.30C-2AC-5A 1.37 5.40C-9A 10.30 4 .40KC-10A 41.90 5.10E-2CEA-6BT-38A 6 .20 7 .70E-3A 4.80 2.90

H-l

%OFF12 FHBMA12 MH/MA12A-4EA-4FA-6EA-7D 0.06 46.00 7.60A-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT-38A 0.16 29.40 4.60E-3A 8.90 7.90

0.070 .040.060.000.040.040.010.130.090.070.05

0. 100.050.100.11

0.180.300.090.270.440.39

0.180.290.05

22.8015.30

9.1041.3011.0018.4028.10

5.606.206.20

32.50

18.5026 .4028.8014.90

13.6014.7021.4024.9020.8010.00

1.908.90

4 .504 . 2 04 .003.205.005.306.005.405.204.703.80

8.5010.00

7.006.50

6 .408.80

11.9010.20

7.3010.40

7.705.007.70

H-2

FHBMA13 MH/MA13 %OFF EQPA-4EA-4FA-6EA-7D 14.40 9.90 0.34A-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10A 4.80E-2CEA-6BT-38A 12.70 6.60 0.33E-3A 7.90

18.50

11.208.70

10.70

11.308.40

12.0018.00

13.0015.3012.4010.30

12.8013.3012.30

6.2010.60

7.50

1.4015.70

3.506 .206 .406.80

10.1011.509.60

11.507.30

10.6011.90

9 .5013.606.004.30

10.909.40

11.709.10

10.906.60

5.905.90

0.390. 140.340 .260.340.300.270.540.310.410.50

0 .290.280.450.29

0.320.230.130.490.470.19

0.230.31

H-3


FHBMA143.932.764.2814.567.28

17. 147.084.3622.496.027.219.619.359.809.65

21.704.4812.9514.3515.5314.347.4714.3818.9418.326.6011.806.808.573.8021.98

6.704.2417.534.78

MH/MA14

10.60

6.005.706.009.709.909.309.6011.309.8011.9011.40

10.9015.107.305.80

6.607.309.406.307.706.50

6.303.906.10

8.902.10

%OFF EQP

0. 15

0. 130.18

0.080.160. 140.070.040.060. 130.22

0.080.080.200. 16

0.040.030.190.120.06

0.090.090.05

0.290.07

H-4

FHBMA23 MHMA23 %OFF EQPA-4EA-4FA-6EA-7D 21.70 22.60 0.54A-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT-38A 20 .20 25 .00 0.68E-3A 8.60 4.10 0.00

20.404 .606.20

13.205.705 .209.30

16.5020.5016.5022.10

11.2011.0022.0020.50

7.606.806.405.007.104 . 4 0

1.4026 .2028.40

29 .8013.7019.302 4 . 2 017.2013.7024 .7025.5031.5041.9058.80

36.0031.5032.9011.70

10.2012.8013.9014.1012.2014.20

11.406 .40

10.70

0.730 . 6 20.660.450 .430.360.630.450.520.630.82

0.620.560.690.21

0.240.420.200.580.340.55

0.64

H-5

FMA41/47 MHMA4147 %OFF EQP-41 %OFF EQP-47A-4EA-4FA-6EA-7D 29 .20 6.50 0 .22 0.12A-7E ,A-10A 17.50 4.50 0.17 0.08B-52G 18.30 6.20 0 .04FB-111A 5.90 5.20F-106A 22.10 7.20 0.12 0.05F-111A 8.80 6.50 0.26 0.33F-l l lD 9.90 10.40 0.31 0.23F-111F 10.00 10.80 0.24 0.32F-4C 16.60 6.90 0.03 0.10F-4D 19.90 9.20 0.03 0.17F-4E 19.40 9.20 0.04 0.20F-5E 35.80 6.70 0 .47F-14AF-15A 17.70 8.60 0.19 0.15F-15C 19.40 12.50 0.25F-16A 28.60 4.90 0.16F-16B 21.10 4.40 0.16 0.13F-18AC-130B 11.00 6.10 0.07 0.05C-130E 12.80 6.60 0.06 0.05C-130H 11.10 0.07 0.02KC-135A 28.50 8.20 0.15 0.070140A 19.80 7.00 0.19 0.06C-141B 9.30 5.30 0.14 0.11C-2AC-5A 4.20 5.90 0.10 0.02C-9A 5.00 0.04KC-10A 38.70 5.20E-2CEA-6BT-38A 41.60 7.30 0.34 0.12..

H-6

FMA42/44 MHMA4244 foOFF EQP - 42 %0FF EQP - 44A-4EA-4FA-6EA-7D 26.30 6.40 0.38 0.22A-7EA-10A 24.40 6.50 0.48 0.17B-52G 9.00 6.10 0.30 0.04FB-111A 9.00 7.30 0.31F-106A 18.80 4.60 0.20 0.12F-111A 7.90 6.80 0.15 0.26F-111D 9.40 9.90 0.16 0.31F-111F 17.90 5.20 0.30 0.24F-4C 16.00 9.40 0.33 0.03F-4D 15.70 6.70 0.35 0.03F-4E 16.30 8.20 0.31 0.04F-5E 36.30 7.90 0.47F-14AF-J5A 12.60 6.10 0.23 0.19F-15C 14.90 0.16 0.25F-16A 14.50 5.70 0.52 0.16F-16B 13.20 4.90 0.53 0.16F-18AC-130B 12.80 4.50 0.11 0.07C-130E 14.40 5.80 0.15 0.06C-130H 12.40 8.30 0.05 0.07KC-135A 10.00 7.30 0.36 0.15C-140A 20.20 5.70 0.25 0.19C-141B 39.80 0.28 0.14C-2AC-5A 2.50 4.10 0.29 0.10C-9A 20.70 4.40 0.19KC-10A 81.70 4.70E-2CEA-6BT-38A 31.20 6.60 0 .47 0.34E-3A 8.50 4.60

H-7

FHBMA45 MH/MA45 SOFFEQPA-4EA-4FA-6EA-7D 44.40 9.10 0.13A-7EA-10AB-52GFB-1 HAF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT_38A 91.60 5.90 0.18E_3A 17.60 2.40 0.17E-3A

95.809.60

12.3035.2020.5018.5028.2030.4026.3044.70

183.00

19.7025.4075.7062.70

17.0018.7019.4014.3027.3016.00

4.7073.8060.50

9.804.606.008.308.208.607.108.708.30

11.909.50

8.90

4.504.00

5.405.809.006.204.505.00

4.904.105.70

0.180.080.290. 120.110.130. 140.070.090.190.11

0.080.090.100.17

0.070.050.030.110.040.04

0.050.010.33

H-8

FMA49/96 MHMA4996 %OFF EQP-96 *0OFF EQP-49A-4EA-4FA-6EA-7D 234 .00 8.50 0.98 0.09A-7EA-10A 235.00 7.60 0.98 0.06B-52G 55.50 7.60 0.08FB-111A 40.10 3.60 0.47 0.01F-106A 60.30 13.80 0.08F-111A 95.00 5.30 0.05F-111D 108.40 10.50 0.00F-111F 121.80 5.70 0.05F-4C 236.60 5.00 0.02F-4D 236.80 4.90 0.00F-4E 262.10 . 0.00F-5E 610.80 6.40 0.00F-14AF-15A 83.60 7.20 0.03F-15C 131.10 13.20 0.02F-16A 561.10 7.70 0.96 0 15F-16B 492.70 4.00 0.24F-18AC-130B 34.70 4.00 0.23 0.05C-130E 48.80 7.10 0.57 o!o8C-130H 34.20 6.60 0.72 0.04KC-135A 46.70 3.40 0.31 0.13C-140A 70.50 4.10 0.05C-141B 34.60 8.70 0.45C-2AC-5A 10.00 6.40C-9A 201.40 5.70 0.03KC-10A 175.90 4.30E-2CEA-6BT-38A 331.50 4.50 0.69 0.00E-3A 45.30 2.20 0.14 0.13

H-9

AVIONICS

FHBMA MH/MA %OFF EQPA-4EA-4FA-6EA-7D 13.80 7.30 0.40A-7EA-10AB-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-14AF-15AF-15CF-16AF-16BF-18AC-130BC-130EC-130HKC-135AC-140AC-141BC-2AC-5AC-9AKC-10AE-2CEA-6BT-38A 14.40 4.60 0.23E-3A 4.80 8.50 0.29

11.703.603.205.305.704.506.504.603.002.30

13.40

7.206.80

17.1010.90

4.704.403.202.60

11.304.40

1.50

9.60

7.806.80

10.205.70

13.8013.0011.208.709.008.808.20

12.6013.604.704.90

8.709.60

11.008.00

11.807.00

8.005.005.30

0.310.290.520.280.360.410.480.380.430.360.35

0.400.460.290.19

0.410.440.230.350.530.31

0.29

H-10

NASA - WBS SUBSYSTEM ROLL-UP

FLY HRS ME42 MH42 ME44 MH44 FHBMA MH/MA ME41

A-7DA-10B-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-15AF-15CF-16AF-16BC-130BC-130EC-130HKC-135AC-140AC-141BC-5AC-9AKC-10AT-38E-3A

NAVY A/C

A4-EA-4FEA-6BA-6EA-7E

C-2AE-2CF-18AF-14A

150,924442,398136,04040,12721,83616,14940,11431,04830,998153,424204,99347,034172,258103,690350,10267,00288,133514,59542,802278,0125,783

572,817109,29040,07067,738460,85032,693

6,3459,87128,02364,09615,573

12,19332,25865,84692,011

2,49011,1158,3572,005519629

1,952607920

3,7174,795633

4,6062,157

13,6722,6273,73217,2161,70713,331

11913,38217,043

352829

6,7572,165

1,1419,8717,54828,5501,432

1,2464,3743,270

13,954

21,32892,78662,35212,6773,6164,22018,3904,50813,42739,74462,7725,89341,37637,844112,95718,90918,797118,82119,013128,443

930100,29991,0174,6323,86950,91713,129

5,6555,58246,800163,8018,481

8,31521,30126,99496,743

3,2527,0236,7882,474644

1,4132,3011,1271,0146,0677,789662

9,0784,78010,5012,4543,13818,6431,73114,335

1671,01427,2031,583

8,0031,672

1,040834

4,19513,4741,552

1,9975,4832,74214,216

15,30124,57330,30519,8371,7729,64123,8494,5534,67226,08340,9774,33642,65446,70525,7245,90012,05290,8009,47673,488

689157,42488,9383,804

46,2564,614

2,7222,63610,04236,8324,867

4,2779,24711,92940,522

26.324.49.09.018.87.99.417.916.015.716.336.312.614.914.513.212.814.412.410.020.239.82.520.781.731.28.5

2.90.92.41.55.2

3.83.311.03.3

6.46.56.17.34.66.89.95.29.46.78.27.96.112.25.74.94.55.88.37.35.717.94.14.44.76.64.6

3.80.84.84.84.5

3.93.16.54.9

4,21217,1565,0705,950536

1,5783,4872,6661,1444,7857,0091,0938,2394,6328,6142,1236,37932,2612,7112,711237

48,92319,9721,132983

8,0284,389

312123

2,2135,539769

1,0764,9564,5109,695

H-ll

MH41 ME47 MH47 FHBMA MH/MA ME49 MH49 ME96 MH96 FHBMA MH/MA

A-7DA-10B-52GFB-111AF-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-15AF-15CF-16AF-16BC-130BC-130EC-130HKC-135AC-140AC-141BC-5AC-9AKC-10AT-38E-3A

NAVY A/C

A4-EA— 4F"•AEA-6BA-6EA-7E

C-2AE-2CF-18AF-14A

2883343351038309536677661441038218112481

264125565916

,254,967,123,600,594,554,546,908,977,379,431,143,389,708,539,883,827,207,940,834,728,346,125,901,143,693,598

82

23

1

311817

126

3

1,772406

8,15618,8182,979

5,20,24,52,

429960310846

951,184,376876450266559440725,906,564219,480722,618,051,645,070,142,05155

,809,143453769,042569

460148

1,7202,478262

1,

2,

649484736108

5,26530,98212,1702,0801,4601,3953,5532,4972,93417,20430,8721,5947,1195,25515,5353,0809,833

46,1538,69931,158

30761,81229,3882,0852,93920,7741,507

1,006476

5,2638,2591,180

2,5285,6282,4397,914

291718522891016191935171928211112112819942538416

.2

.5

.3

.9

.1

.8

.9

.0

.6

.9

.4

.8

.7

.4

.6

.1

.0

.8

.1

.5

.8

.3

.2

.3

.7

.6

.6

8.236,7,8.15.

7.5.12.7.

.4

.1

.0,1

1068

6.54.56.25.27.26.510.410.86.99.29.26.78.612.54.94.46.16.631.68.27.05.35.95.05.27.33.7

3.63.33.43.44.0

4.64.15.15.1

6281,8412,45298716017035925513164878277

2,060791578115

2,53410,4271,2175,917

8216,57911,047

199385

1,377631

Tj

9183

31

36

14102

1073720

144711161

,940,675,576,611909839,838,373623,029,267482,870,422,642450,095,915,820,440339,805,029,129,637,199,492

1742

14202

11

46218

1283540

1,5494,631

404,078

63347730159

2,66110

2,154963971348770

1391

78118

,1,3

234.0234.955.540,60.95.0108.4121.8236.6236.8262.1610.883.6131.1561.1492.734.748.834.246.770.534.69.9

201.4175.9331.545.3

3.57.67.63.613.85.310.55.75.04.911.46.47.213.27.74.04.07.16.63.44.18.76.45.74.34.52.2

H-12

NASA - AVIONICS SUBSYSTEM ROLL-UP

FLY HRS ME51 MH51 OMH51 ME52 MH52 OMH52 MESS

A-7DA-10B-52G

150,924442,398136,040

FB-111A 40,127F-106AF-111AF-111DF-111FF-4CF-4DF-4EF-5EF-15AF-15CF-16AF-16BC-130BC-130EC-130H

21,83616,14940,11431,04830,998153,424204,99347,034172,258103,690350,10267,00288,133514,59542,802

KC-135A 278,012C-140AC-141BC-5AC-9AKC-10AT-38E-3A

MH55

16,0582,7872,9231,807920380678447

10,56625,765

88817,86715,8183,314407766

4,813854

17,950

5,783572,817109,29040,07067,738460,85032,693

2,901 14,23116,636 127,10016,062 89,0323,825 29,184329 3,264938 11,008

2,344 20,5481,372 13,6501,510 15,1107,629 71,91911,678 110,6671,544 11,4235,914 59,5432,619 33,1195,515 30,8941,652 9,3662,895 14,68913,375 77,1491,353 14,94439,657 230,067

84 42831,309 189,6319,869 68,871470 1,875858 3,014

19,736 75,4631,358 7,374

12,97,80,20,2,8,16,9,9,40,65,7,49,20,22,7,12,67,14,199,

155,52,1,3,62,7,

OHB55 ME61 MH61 OMH61

10,2152,551 11,5181,672857357 1508385

9,00414,259

72911,57011,9073,193391690 1

4,583 5825

2

17,672 9163,369 127,165 3

447753

388749

,027 12,026 8867 12,161 3

274 4,026 2,321 21,053 7641 8,769 3

,019,870

,035,794,367

130617309193771503062552224052896239310647630978071103113714393418376698000897255

2,7595,9762,506886779

2,8481,489604

3,1254,159404

1,3801,132

2,41214,7251,49418,767

7820,23512,900

3681,4972,576458

31434331652229

337542424

199917136

160116

39173

ME62 MH62

1,s,410 13,770 42,

928925

,026 20,136 29,979 16,110 5,999 9,300 27,900 10,176 6,218 25,104 50,925 3,959 12,917 13

,299 14,807 82,797 15,080 96406,470 113,122 98,823 3,520 9,710 11,903 3

OMH62

5,34927,071

,634,842,586,890,047,019,403,699,015,584,309,312,875

,000,100,390,870324,106

2,1088975563919888

1251,5604,087141

1,2381,76323112091885

4,800,948 25,744,805,520,636,903

ME63

1,9715,4423,8712,922505248

1,011634829

7,02310,645

,350 15,060 6,332 66,100 28777 9,274 4,811 33,875 1934 783

,362 116,661 51,097 32,479 2287 276171 937

590 6,445 4

,967,334,551,617276,049,939267937

,229

3,

2,1,

6,

17

622 16,998 4,441 4,378 18,533 4,382 1,22493 42,523 3,18710018102 1,

122

51901014171208341142173128561145256018

78

11,1572,9062,18511,0583,302762135

29,7172,57057635953633

6236,8154,2196,2861,080498

5,161243

5,45927

5,4121,060173399

3,158944

15486

MH63

15,13739,03930,58925,1202,0841,7529,0584,1575,71337,63173,9164,83363,64948,26228,9666,1603,96627,8851,97758,092

29328,1737,076434

2,06916,22911,673

OHH63

92114911613255423627193216126

174

2107

,277,329,837,943,584,329,236,990,487,045,727,945,555,053,238,559,428,507,454,523174,850,759434,069,167,174

H-13

NASA - AVIONICS SUBSYSTEM ROLL-UP

ME64 MH64 OMH64 ME66 MH66 OHH66 ME71 MH71 OMH71 ME72 MH72

7261,2575,7771,309

303710466

201

917477

2,21412,2591,4317,678

6218,6585,556384

1,3331,8941,337

OMH72

6,705262

7,947599

7158,61917,397

31,958277,55441,376152,334

44365,54146,8431,2532,197

2,567

5,645 4,2587,380 4,37241,505 25,6199,636 7,286

2,300 1,6265,479 5,0731,903 1,433

1,218 1,218

4,795 4,4642,457 2,36513,036 10,68,764 54,16,403 14,66,147 35,

65374,723 65,35,931 25,1,119 1,5,138 5,11,025 10,9,714 5,

TOT ME

10,97537,83637,44112,7244,0832,8418,8984,8006,75351,83089,3143,50123,92215,29620,4176,13318,869116,828 113,295106,825

511128,87171,8012,4277,02031,9446,803

363963716042370856396001133090804

TOT

8029425312923391155358467786283002089530163,1241468506

897576123714557

2881,317166

1,7291,99416527

101

3,

7,23,

1,

MH TOT

,266,534,684,763,459,332,666,946,536,703,741,774,929,781,188,286,253,261,546,505,052,663,062,017,321,463,861

47

953978697

024704674117

281

OMH

,826202,188180621625672836264503181791126724976341125542

623411103711141

,079,364,979,240,648,157,505,769,205,602,277,219,686,451,124,604,380,120,835,284,673,916,208,463,323

8673,723626

5,98414,227

556117

853

FHBMA

13.811.73.63.25.35.74.56.54.63.02.313.47.26.817.110.94.74.43.22.6

. 11.34.41.516.59.614.44.8

2,4153,7552,490617

1,472201576198

3,47030,71455,240

5719,8136,0882,3141,6952,77214,0511,9853,641110

20,0052,464347

2,1774,4081,377

MH/MA

7.37.86.810.25.713.813.011.28.79.08.88.212.613.64.74.98.79.611.08.011.87.08.05.05.34.68.5

18,20030,73019,8645,9298,1942,3276,8481,88922,413290,204468,8725,365

134,91186,66510,7007,88627,985253,85722,03944,4721,513

161,36629,0451,68013,87624,53312,192

%OFF EQ

0.4040.3140.2900.5190.2760.3580.4150.4780.3760.4340.3600.3540.4040.4630.2890.1930.4050.4360.2330.3480.5320.3060.2850.0920.0030.2340.286

10,20,10,2,5,1,5,

15,157,300,

3,69,38,7,7,15,88,16,23,

101,16,1,13,16,3,

107 1,552688 109955 1,341369 122062843107904995 215034 1,779342 3,505084530737004252595 5,879679 47,312027 4,228258 28,430720 94091 10,868450 8,594326 246876 458232156 450

13,125276

14,745831

5,67724,16532,417

63,358503,19658,478280,3611,55598,93496,1801,5252,198

3,508

MH/FH

001312211330120012331150001

.53

.67

.86

.23

.07

.44

.88

.74

.89

.05

.84

.61

.75

.01

.27

.45

.85

.18

.42

.06

.05

.57

.27

.30

.55

.32

.77

H-14

APPENDIX I

Subsystem Weight Percentage

WEIGHT DISTRIBUTION ANALYSIS

PLS AMLS AVG

WINGTAILBODYTPSLANDINGPROP 6,7,8PRIME PWRELECTRICACTUATORSAVIONICSECSPERS ACCOMRECOV & AUX

TOTAL

1,86969

2,2382,1241,1611,3662,8721,216

1731,3371,5991,4341,961

0.0960.0040.1150. 1090.0600.0700.1480.0630.0090.0690.0820.0740.101

1,73962

2,9071,555

8291,1382,720

999123956

1,4781,1951,634

0.1000.0040.1680.0900.0480.0660.1570.0580.0070.0550.0850.0690.094

0.0980.0040.1410.1000.0540.0680.1520.0600.0080.0620.0840.0710.098

19,419 1.000 17,335 1.00 1.00

1-1

APPENDIX J

MTBM Regression Analysis

Multiple RegressionDate/Time 04-01-1992 15:05:42Data Base Name C:\NASA\WUC11Description Backup of NASAMSTR created 12-18-1991

Multiple Regression Report

Dependent Variable: FHBMA11Independent Parameter Stndized StandardVariable Estimate Estimate ErrorIntercept 15.23085 0.0000 3.994154WGT TAIL .6057E-02 2.8217 .5551E-03SQR TW -.1375748 -1.7464 .5844E-01WETAREA -.723E-03 -0.7205 .6747E-03

t-value(b=0)

3.8110.91-2.35-1.07

Prob.Level0.00150.00000.03170.2997

Seq.R-Sqr

0.24390.88360.8914

SimpleR-Sqr

0.24390.04460.0343

Analysis of Variance Report

Dependent Variable: FHBMA11

Source df Sums of Squares(Sequential)

Constant 1 1114.525Model 3 1254.958Error 16 152.9258Total 19 1407.884

Root Mean Square ErrorMean of Dependent VariableCoefficient of Variation

R SquaredAdjusted R Squared

Mean Square

1114.525418.31959.55786174.09917

3.0915797.465.4141432

0.89140.8710

F-Ratio Prob. Level

43.77 0.000

J-l


Residual Analysis

Row

1234567891011121314151617IS1920212223242526272829303132333435

Durbin

ActualY..,

10.

11.331.110.12.92.52.35.13.64.27.9,

32.688.326.5•

3.45.34.749.43.63,

1 .3710.341.9,

,

6.2- Watson

PredictedValue,..

7.201859•

4.8981232.562452•

•

*

•

•

5.2914075.2914075.2914077.517668.

5.7760295.5835818.247961•

•

5.8715765.8715765.8715769.7660436.6141831.53145.

1.3440415.4327140.8043•

»

8.530637

Std Errof Fred*

.

•

.8609902•

.87151371.713773

t

•

•

•

t

1.0275271.0275271.0275271.150616

*

.836188

.86195951.022725•

•

.8064643

.8064643

.80646431.3919221.1036231.63013•

2.4764081.1493043.042678•

•

1.529309

Lower95%Mean•

.«

5.376893•

3.050851-1.070084

*

•

•

•

•

3.1134473.1134473.1134475.078806•

4.0036343.756566.08018•

•

4.1621834.1621834.1621836.8157054.27493-1.923795

*

-3.9049852.9966334.355•

•

5.289094

Upper95%Mean.•

.9.026825•

6.7453956.194987•

•

•

•

t

7.4693687.4693687.4693689.95653•

7.5484247.41060210.41574' «

•

7.5809687.5809687.58096812.716388.9534374.986695•

6.5930677.86879147.2536•

•

11.77218

Residual

•

•

•

2.798142•

6.401877.4375482•

•

•

t

•

-.1914072-1.691407-1.091407.3823323•

-2.776029-2.903581.7204E-01•

•

-2.471576-.5715756-1.171576-5.7660432.7858162.09855

t

.02595894.867291.095703•

•

-2.330637Statistic 1.213496

J-2

Multiple RegressionD.ate/T.ime 04-02-1992 14:43:23Data Base Name C:\NASA\WUC12ADescription Merge of WUC11 and WUC12 created 04-01-1992


Dependent Variable: FHBMA12IndependentVariableInterceptDRY WGTLN DRYWTSQR WOTCREWS I ZESQR CREWWGT BODYSQRWTBODCREW+TRP

ParameterEstimate3428.487-.142E-01-423.959411.05028111.5669-360.7212.1865E-01-4.835661-.2578509

StndizedEstimate0.0000

-99.4395-49.6111125.888548.0205

-28.120544.7105

-31.1615-2.1322

S tandardError889.042.4057E-02112.35143.05327229.2030491.78398. 5565E-021.462995.1338993

t-value(b=0)

3.86-3.50-3.773.623.82

-3.933.35

-3.31-1.93

Prob.Level0.00270.00500.00310.00400.00280.00240.00650.00700.0804

Seq.R-Sqr

0.26650.31940.33950.36890.5711,58527243

0,0,0.7938

SimpleR-Sqr

0.26650.31230.31780.11510.19750.21260.27110.1739



Source df Sums of Squares Mean Square(Sequential)


F-Ratio Prob. Level



6581.192234.176544.22873124.2067

6.65046818.14.366619

0.79380.6439

5.29 0.007

J-3

Multiple RegressionDate/Time 04-02-1992 14:43:48Data Base Name C:\NASA\WUC12ADescription Merge of WUC11 and WUC12 created 04-01-1992

Residual Analysis

Row

123456789101112131415161718192021222324252627282930313233343536

Durbin

ActualY...

46.

22.815.39.141.31118.428.15.66.26.232.5.

18.526.428.814.9•

13.614.721.424.920.810,

1.98.9•

.

.

29.48.9- Watson

PredictedValue,.,

35.40208•

18.0293414.40029.•

•

*

•

8.1983698.77435812.2691139.88201•

20.5776222.0104829.78044•

•

16.1278319.440720.3578120.1924810.508987.176239•

2.42415315.85721-282.9091•

•

31.9359.461346

Std Errof Pred•

.

•

4.578885•

3.3349616.470281

t

•

.

•

•

3.4281573.3624683.1766133.990315•

3.8283423.7858723.131097•

•

3.2145993.2214163.5564373.8471124.8397756.234165•

6.6419272.94807389.58411•

•

5.3706066.644016

Lower95%Meant

•

,

25.33262•

10.6954.1714525•

•

t

•

•

.65948491.3799315.28339731.10688•

12.1586913.6849422.89483•

•

9.05858412.3564612.5368311.73227-.1342001-6.533356.

-12.182169.374085-479.9141•

•

20.12446-5.149556

Upper95%Mean...

45.47154•

25.3632828.62913•

•

•

t

•

15.7372516.1687919.2548248.65714•

28.9965630.3360136.66606•

•

23.1970826.5249328.178828.6526921.1521620.88583,

17.0304622.34034-85.90405•

•

43.7455424.07225

Residual

•

•

*

10.59792•

4.77066.8997078•

•

•

•

•

-2.598369-2.574358-6.069109-7.382008•

-2.0776224.389523-.9804421•

•

-2.52783-4.7406971.0421894.7075210.291022.823762•

-.5241526-6.957213•

•

•

-2.535002-.5613461

Statistic .5828236

J-4

"Huitioie Kearessiori-Oate.' Time O4-12-1992 19:23:26Data Sase Name B:WUC13Description BacKuo of WUC13 created 03-27-1992


Dependent VariableIndependentVariableInterceptWHEELSLEN .WINGLN DRYWT3QRWHEELWGT13LOGWGT13

FHBMA13ParamererEstimate72.4115914.5682.9942E-01-12.41028-65.6-.568E-0218.59791

StndizedEstimate020oA*

_2-13-125

.0000

.6183

.6360

.9632

.8090

.0906

.0203

Standard t-valueError ( b=O )17.391414.177294-2670E-014.37050716.95416-1661E-026.412072

433-2-3—32

.16

.49

.72

.84

.87

.42

.90

Prob.Level0o00o00

.0013

.0045

.0029

.0149-OO22.0051.0133

Seq.R-Sqr

000000

-5762.5780.6106.6747.7200.8354

SimpleR-Sqr

O00OO0

.5762

.4303

.3896

.6015

.5508

.4365




Constant 1 269O.59Model 6 248.1326Error 12 48.88739Total 18 297.02


R SquaredAdiusted R Squared

2690.5941.355434.07394916.50111

2.01840311.9.1696137

0.83540.7531

F-Ratio Prob. Level

10.15 O.OOO

J-5

HuitiDle Rear ess i on-Date/Time 04-12-1992 1.9:23:27Data Base Name 8:WUC13Oescriotion Backuo of WUC13 created 03-27-1992

Residual Analysis

Row

1234567a91011121314151617181920212223242526272829303132333435

Durbi

ActualY,

.

..

14.4m

18.5.

..

11.28.710.7

„

11.3S.412.18

—

1315.312.410.3

m

12.813.312.36.210.67.5

„

1.415.7

„

.

.12.7

n - Watson

PredictedValue.

.

.

12.1383911.6232917.5O248-8.098694

„

m

„

.

.

11.6314111.5633411.6218915.52705

„

12.579712.596813.2817213.56009

„

14.37613.5030113.326715.2OO3710.494217.232115.1.53793414.52365-68.25033.

.

13.9O354

3td Errof Pred....8063493.78459611.1677026.455153

„

m

m

.

.

.9716528

.9720188

.89829581.127848,

1.2302381.223564.7411884.7361409.

.9899314

.8845586

.89131861.6429391.9O2811.476327.

2.O154741.04949522.92037.

.

1.488O36

Lower95?;Mean...

10.332189.91445614.95926-22.15785

m

m

m

a

.

9.5151759.4463079166542213.07O63•

9.900279.-93190811.6674311.95679

* ,

12.2199511.5764711.385441.6220916.3499354.016712.

-2.85171912.23788-118.1703.

m

10.66263

Uoper955Mean,

._

13.8945913.332122O. 045715.960466

„

—_

m

m

13.7476413.6803713.5783517.98348

—

15.2591215.2616914.8960115.16339

<•

16.5320415.4295615.267988.7786514.6384810.44752

—

5.92758716.80943-18.33034•

.17.14444

Residual

.„

.2.261614..9975166

m

w

.—

B

—

-.3314095-3.163341.37811182.472947

—

.42030332.7032-.8817177-3.26OO91•

-1.575998-.203O125-1.026712.9996295.105792.2678852

m

-.1379341.176345.

•

„

-1.203537Statistic 1.1842

J-6

Date/TJLnieData Base NameDescription

Sum of Functions Regression05-18-1992 15:20:40C:\NASA\WUC23Merge of WUC11 and WUC51 created 04-27-1992

Estimation Summary Report

Y: FHBMA23 X: ENG WGTModel: A+B*(X)+C*(SQR(X))

Term Coefficient EstimateA 34.10401387922342B 9.853047097031215D-04C -.3122318101760727

Std. Error10.237317.461445E-04.1872512

T-Value3.31.3

-1.7

SourceModelErrorTotal

df21719

Sum-Sqr338.017964.6731302.69

Mean Square169.008556.7454768.56263

SQR(M.S.13.000337.5329598.280255

Prob(!t!>TJ0.00400.20420.1137

F-Ratio3.0

R-Squared0.25947618

Prob(f>F)0.0778

J-7

Sura of Functions RegressionDate/Time 05-18-1992 1 5 : 2 0 : 4 9Data Base Name C : \ N A S A \ W U C 2 3Description Merge of WUC11 and WUC51 created 04-27-1992

Residual Analysis

Row123456789101112131415161718192021222324252627282930313233343536

ActualX,

,

t

4497,

428336554,

,

,

,

f

9968996899682247

*

604960913671,

,

t

166961669623386380425471

$

390911053543162

,

t

176723321

ActualY...

21.7.

20.44.66.213.25.75.29.316.520.516.522.1.

11.2112220.5.

7.66.86.457.14.4.

1.426.228.4..

20.28.6

PredicteY...

17.59677.

17.8901810.42493.....

12.7523512.7523512.7523521.51742.

15.7801915.7374218.80332...

10.2102510.210259.39835718.594729.369648.

10.8878212.4366811.76412..

22.720179.400715

Value Value Residual

17.59677 .9983463 34.19518 4.103235

17.89018 1.253127 34.52723 2.509822-7.081947 27.9318 -5.824929

-3.882895 29.38759-3.882895 29.38759-3.882895 29.387593.922633 39.1122

-.6974329 32.25782-.7396602 32.21452.009699 35.59695

-6.638539 27.05904-6.638539 27.05904-7.390118 26.186831.841787 35.34766-7.407126 26.14642

-7.082106 28.85775-4.230335 29.10369-7.23429 30.76253

4.610004 40.83033-7.388428 26.18986

3.7476537.7476533.747653.582585

-4.580194-4.7374173.196676

-3.410251-3.810252-4.398357-11.49472-4.969648

-9.48782313.7633216.63588

-2.520164-.8007144

J-8

Residual Plot

rMultiple Regression-Date/Time 04-02-1992 17:08:31Data Base Name A:WUC24Description Backup of WUC24 created 03-13-1992


Dependent VariableIndepenaentVariableInterceptKVA MAXSQR KVAWGT24SQR WT24LOG WT24

: FHBMA24ParameterEstimate4996.525-1.90606146.34963-2.735048284.5488-1642.986

StndizedEstimate0.0000-4.27203.7415

-18.411038.6879-20.2179

StandardError1764.139.596856717.272031.063313102.2125575.155

t-value(b=0)

2.83-3.192.68

-2.572.78-2.86

Prob.Level0.02530.01520.03140.03690.02710.0245

Seq.R-Sqr

0.01510.12010.5197'0.53380.7847

SimpleR-Sqr

0.01510.00410.13600.134O0.1154







Mean Square

54639.376415.0871256.9333406.164

35.4532564.83077.5468584

0.78470.6310

F-Ratio Prob. Level

5.10 0.027

J-9

MultiPle Regress i on-Date /T ime 04-02-1992 17:08:41Data Base Name A:WUC24Description Backup of WUC24 created 03-13-1992

Residual Analysis

3W

1234567a91011121314151617181920212223242526272829303132

ActualY.

,

.

100.

.

.

.

,

.

.

B

27.131.622.624

B

52.549.644. 12339853.2

f

14.599.790.9

333435

Durbin - Watson

Predicted Std ErrValue of Prea

69.82757

Lower95%Mean

22.92636 15.78379

Upper95%Mean

Resio.ua!

123.8713 30.17243

7.18551955.763145.4095735.43O1

41.5939344.5107444.51074181.7857

48.6821621.1045415.26921158.485594.35203

33.3694814.6383820.4951919.86587

17.0438516.7257316.7257326.3202

18.1014119.3458734.7541323.5097335.24929

-71.4755921.2564-2.903259-11.39926

1.4168555.0835725.083572119.7417

6.012123-24.49903-66.65589103.066611.25969

85.846639O. 2698193.7223982.25946

81.7710183.9379183.93791243.8297

91.3521966.7081197.19431213.9044177.4444

19.91448-24.1631-22.80956-11.4301

10.906075.089256-.410743751.21433

4.517845m

-.7692118-58.78552-3.452026

Statistic 1.276503

J-10

Date/Ti.me 04-07-1992 14Data Base Name A:WUC42Description Backup of WUC4;

••'-lultipie Reqression-T C- C "I

: createa 03-27-1992


Dependent VariableIndependentVariableInterceptWGT42SQR WT42LEN WINGLN DRYWTSQR WGTLOG KVAKVA SOD

FMA42/44ParameterEstimate1193.127-.755E-016.758773-.7155964-167.24012.230829.10236-.127E-02

StndizedEstimate0-77-5-10171

-4

.0000

.6982

.6694

.0081

.6606

.6804

.5538

.2703

StandardError117.0389.9180E-02.3034786.3059E-0116.50279.20853124.96025. 1504E-03

t-value(b=0)10-8a-a-10105-8

.19

.22

.41

.88

.13

.70

.87

.46

Prob.Level00000000

.0000

.0000

.0000

.0000

.0000

.0000

.0001

.0000

Sea.R-Sqr

0000000

.0233

.0363

.0384

.0391

.3664

.4321

.9126

SimpleR-Sqr

0000000

.0233

.0170

.0094

.0091

.0320

.0100

.0290


Dependent Variable: I-MA42/44


Constant 1 9425.524Model 7 5013.7J7Error 13 480.0486Total 20 5493.766



9425.524716.245336.92682274.6883

6.07674421.18571.2868321

0.91260.8656

F-Ratio Prob. Level

19.40 0.000

J-ll

Multiple Reg re ESI on-14:36:04Date/Time 04-07-1992

Data Base Name A:WUC42Description Sackuo of WUC42 created 03-27-1992

ROW ActualY

Predicted'.Value

Residual Analysis

3td Errof Pred

Lower95%Mean

Upper95%Mean

Residual

34567891011121314151617181920212223242526272829303132333435

Durbin

26.3.

24.49918.87.99 . 417.91615.716.336.3,

12.614.914.513.2

12.814.412.41020.239.8

2.520.781.7.

.

31.2- Watson

29.8017

14.950136.211584

3.488953

1.7404275.541101

22.26824

11.19215-5.752943

37.33516

18.7081218.17611

-3.501701

9.4498672.788416

16.7053116.8231414.2268633.83958

6.69112818.0953221.8323919.82873

4.7349313.6565916.1345919.8094817.4475339.02169

5.14978522.9655177.70444

2.3485492.8728242.9729564.143581

2.9379483.4580872.1832442.184684

3.2329782.7588872.6519552.9714534.4988684.757357

5.9562063.217155.775562

10.5546310.620047.80755524.89262

.347414510.628517.1182615.11149

-2.2458217.69951110.408413.393437.73343328.74945

-7.7110516.0189365.23366

22.8559923.0262320.6461642.78654

13.0348425.5621326.5465224.54597•

11.7156819.6136721 . 8607826.2255427.1616449.29393

18.0106229.912089O. 17522

-.705307-1.1231362.073142.460419

5.908873-3.195318-7.332394-6.628732

8.065071. 7434092-3.734589-9 . 8094852.752466. 7783089

-2.649785-2.2655053.99556

29.27219 4.585095Statistic .9728374

19.37191 39.17248 1.927809

J-12

—^Multiple Regression-Date/Time 04-03-1992 14:10:20Data Base Name A-.WUC45Description Backup of WUC45 created 03-13-1992


Dependent VariableIndependentVariableInterceptWETAREA3U8SYSSQR SUBSLOG SUBSSQR WT45LOG WT45

FHBMA45ParameterEstimate396.2586-.622E-0235.63519-779.8318975.56658.812898-105.7279

StndizedEstimate0.-1.14.

-27.12.3.-2.

0000253492055569848116243344

Standard t-valueError (b=O)158.0882.2952E-0213.60838293.7664372.15572.21449925.46246

O4.

-22-223-4

.51

.11

.62

.65

.62

.98

.15

Prob.Level0000000

.0263

.0552

.0212

.0198

.0211

.0016

.0011

Seq.R-Sqr

000000

.1895

.2126

.2190

.3287

.3724

.7302

SimpleR-Sqr.

0.0.0.0.0.0.

189516061578137716462943






R SauaredAd.justed R Squared

43300.824205.443717.05121818.648

26.7778146.53.5754956

0.73020.6057

F-Ratio Prob. Level

5.86 0.004

J-13

flu 1 tide Regression-Date/Time 04-03-1992 14:10:30Data Base Name A:WUC45Description Backup of WUC45 created 03-13-1992

Residual Analysis

Row

1234567891011121314151617181920212223242526272829303132333435

Durbin

ActualY.

.

.

44.4.

95.89.612.335.220.518.528.230.426 . 344.7183.

19.725.475.762.7.

1718.719.414.327.316

f

4.773.860.5,

m

91.6- Watson

Predicted Std ErrValueB

m

m

43.68098.

71.948197.946936

m

m

.

.

.

.

30.6770130.67701121.2529.

43.5881937.1987584.1158684.03505,

28.7947728.7198628.7198623.1532433.6419-19.23709,

8.60784249.3537368.67876

„

,

125.0493Statistic .

of Predm

.

.

18.99137.

9.O1718723.73618,

.

.

.

.

.

13.3297913.3297915.21319

B

8.8641459.7463299.8133089.798325•

11.8298411.8342911.8342914.2364224.3488816.0961

»

22.3944514.3985524.75348.

.

16.280757553009

Lower95?sMean.

.

. .

2.674194.

52.47798-43.30499.

.

.

.

m

.

1.8949031.89490388.404O7•

24.4484416.1541562.9266462.87819.

3:.2513913 . 1668823.166882-T: 586506-18.93301-53.99232•

-39.7469818.2639115.23025.

•

89.89542

Upper95%Mean,

.

.

84.68777.

91.418459.19886.

m

B_

.

.

59.4591259.45912154.1017•

62.7279458.24334105.3051105.1919

m

54.3381554.2728454.2728453.8929936.2168115.51813

m

56.96266SO. 44355122.1273

w

a

16O.2033

Residual

B

.7190208a

23.851811.653065...f

.•

-4.37701414.0229961.74712•

-23.88819-11.79875-8.415863-21.33505

m

-11. 79477-10.01986-9.319861-8.853242-6.341935.23709

9

-3.90784224.44627-8.178764,

m

-33.44935

J-14

--_ Multiple Regression-Dace/Time 04-02-1992 16:26:05Data Base Name A:WUC14Description Backup of WUC14 created 03-27-1992


Dependent VariableIndependentVariableIntercept3QR WT14ACTUATORCONT SURLEN WINGWETAREA

FHBMA14ParameterEstimate26.29027-1.11361.9516068-1.899484.3505284--357E-02

StndizedEstimate0.0000-3.12674.4096-3.21127.4989-5.6737

Standard t-valueError (b=0)5.516686.2823322.2070737.3542125.0697234.8842E-03

4.77-3.944.6O-5.365.03-4.04

Prob.Level0.00060.00230.00080.00020.00040.0019

Seq.R-Sqr

0.31190.36650.42570.58700.8338

SimpleR-Sqr

0.31190.36350.41770.19620.2781





F-Ratio Prob. Level



3124.49573.637196.6714227.59822

2.58290913.55706.1905213

0.83380.7583

11.04 0.001

J-15

Multiple Regression-Date./ Time 04-02-1992 15:26:14Data Base Name A:WUC14Description Backup of WUC14 created 03-27-1992

Residual Analysis

Row

12345678910111213141516171819202122232425262728293031323334

Durbin

ActualY

3.932.764.2814.567.2817.147.084.3622.496.027.219.619.359.89.6521.74.4812.9514.3515.5314.347.4714.3818.9418.326.611.86.88.573.821.98.

6.74.24- Watson

Predicted Std ErrValue.

m

m

13.36487.

18.932956.314134.

.

.

.

»

8.35759511.2124212.859921.57O82,

14.2221915.8861211.7961712.73119

»

17.1457817.1457817.706639.488832...

3.59049218.14413-73.75688.

•

Statistic 1

of Prea.m

B

1.540009.

1.2720042.212739•

.

.

.

•

1.3603071.1548891.1451792.105001.

1.2014211.2103351.1776661.058403•

1.2704081.2704081.299221.438714...

2.5524061.8166115.50723..

.453594

Lower95%Mean.

m

m

9.978226.

16.135681.448084•

m

B

.

m

5.3661368.67269210.3415316.9417.

11.5801413.224469.20635610.40365•

14.3520214.3520214.84956.324945•

.

.

-2.02252114.14921-107.8589.

.

Upper95?sMean..f

16.75151,

21.7302211.18018.

.

•

.

.

11.3490613.7521415.3782726.19994.

16.8642518.5477814.3859815.05873•

19.9395419.9395420.5637512.65272.

.

,

9.20350522.13905-39.65482.

•

Residual

1.19513.

-1.792948- 7658658

m

.

.

.9924049-1.412416-3.209903.129179.

-1.272195-1.5361193.7338311~. 608809

*

-2.7657791.794222.6133728-2.888832,

^

^

.20950823.835873•

•

^

J-16

rtultioie Rearession-1-4:10:02Oate/Time O4-O5-1992

Data Base Name B:AVIONIC3Oescrionon Sackuo of AVIONICS created 03-27-1992

Multiple Regression Report:

Dependent VariableI ndependentVariableInterceptTOTSUBSSQR TSUBAVG WT/3WQT51/72SQR51/72

FHBMAParameterEstimate-36.91729-4-496O1645.75636-.1230886.2360E-01-2.453409

StndizedEstimate0-73-210-9

.0000

.2132

.1287

.2612

.1898

.6786

Standard t-valueError (b=O )27.717371.79898518.14795.4387E-01. 7750E-02.7582701

-1-22-23-3

.33

.SO

.52

.81

.05

.24

Prob.Level000O00

.2124

.0315

.0303

.0186

.0124

.0089

3eq.R-Sqr

00000

.3061

.3499

.5039

.5524

.7813

SimpleR-Sqr

00000

.3061

. 3269

.1876

.4244

.5377


Dependent Variable: FHBMA

Source df 3ums of Squares Mean Square(Sequential }


F-Ratio Prob. Level



1161.10655.547937.7724723.69763

2.7879158.51875.3272681

0.78130.6720

7.15 O.OO4

J-17

nuitioie Recression-.14:10:02Oate/Time U4-O5-1992

Data Base Name B:AVIONICSDescription Backup of AVIONICS created O3-27-1992

Residual Analysis

Row Actual Predicted 3td Erry Value of Pred Mean

Upper95%Mean

Residual

34567a9

1011121314151617181920212223242526272829303132333435

Durbi

,13.8

„

11.73.63.25.35.74.56.54 .632.313.4.

7.26.817.110.9

_

4.74.43.22.611.34.4.

1.5

9.6„

14.4n - Watson

_

11.47413.

13.29583.321389

„

„

„

„

«

.,

3.347O25^

14.37355„

9.2150O68.96962113.6941812.69238.

„

4.354426.210011,

5.7701875.542498.

2.12689-.32241687.683124.

.

14.22974Statistic 1.

.2.163948.1.3918162.734361....-.1.895034.2.05159..9867181.96925661.4210321.256933..1.1187571.03621.1.5473291.320705.1.6367263.2934022.278235..2.211951

486O22

. -'6.654596.

10.19595-2.768568......

-.8735862.

9.804258.

7.0173926.81089710.529279.892949..1.8627313; 902168.

2.3239832.601031.

-1.51842-7.6574662.609049..9.303292

.

16.29367.

16.395649.411346......7.567636

m

18.94284.

11.4126211.1283416.859115.49182.

„

6.8461098.517853.

9.2163928.483965.

5.7721997.O1263212.7572•

m

19.15619

m

2.325869m

-1.595797.2786114

m

^

„

m

..

,

- . 3470249m

-.9735508m

-2.015006-2.1696213.4O5816-1.792384...4558E-01-3.010011

m

5.529813-1.142498.

- . 6268895m

1.916876.

m

.1702614

J-18

Multiple RegressionDate/Time 03-17-1992 15:46:03Data Base Name C:\NASA\PRECONDescription Merge of WUC12 and WUC11 created 03-17-1992


Dependent Variable: ECS FHMAIndependent Parameter StndizedVariableInterceptDRY_WGTLEN_WINGLN LENTH

Estimate454.3876-.547E-03.8210209-107.5185

Estimate Error0.0000 73.06644-2.7882 .1174E-036.3884 .1587219-4.3668 18.67703

t-value(b=0)

6.22-4.665.17-5.76

Prob.Level0.00000.00010.00000.0000

Seq.R-Sqr

0.22680.24120.7057

SimpleR-Sqr

0.22680.23990.3295


Dependent Variable: ECS FHMA

Source

ConstantModelErrorTotal

df Sums of Squares Mean Square F-Ratio Prob. Level(Sequential)

1 158763 2878.971 959.6572 16.78 0.000

21 1200.84924 4079.82



15876959.657257.18326169.9925

7.56196225.2.3000779

0.70570.6636

J-19


Residual Analysis

1 Std Errof Fred4.1182184.0854651.8288522.38572.369651.740723.8954842.9132071.7796172.6957682.8021192.8021192.115572.1239112.1004313.4870542.5337461.8862331.9164422.8438522.6477591.9964512.9614032.7142972.6823542.8266841.7491753.5578132.0402797.2512642.6218018.3792092.2909142.1521253.978719

564765

Lower95%Mean42.186141.9559921.8893531.8999531.5207324.1758817.408996.2004322.757278.7091017.7717127.77171222.2579722.1547520.4285539.38911.2141821.3262820.9039735.3652934.3502426.4742715.8312713.6693113.2265913.8963723.3564416.4876116.49411-11.19213.34383-38.7122712.6440416.9285341.95843

Upper95%Mean59.3124958.9461729.4949741.8213441.3753731.4149933.609118.3155630.1581519.9199619.4248619.4248631.0559730.9874329.1635953.8905821.7512429.1705428.8738647.1919945.3614534.7768928.1468324.9572324.3816725.6516730.6307231.2834524.9789918.9637524.24709-3.86573222.1712425.8785558.50468

Residual

(

.t

-1.060646•

-1.9954381.290951-5.55799314.24229-4.114533-2.098285-1.998284.44303515.528914.403929-3.639786

*

-4.34841-2.488913-.6786423-8.255842•

-8.189052-3.413271-3.00413214.32598-2.593578-12.18553•

1.61412416.60454•

•

•

7.168446

J-20

ResidMultiple Regression

Date/Time 03-18-1992 16:24:35Data Base Name C:\NASA\PRECONDescription Merge of WUC12 and WUC11 created 03-17-1992


Dependent Variable:IndependentVariableInterceptLEN_WINGLN DRYLDRY SQDWGT/LEN

FHBMA47Parameter StndizedEstimate Estimate6613.119 0.0000-1.484938 -3.7671-1358.298 -31.405573.58044 36.8273-.7258523 -2.5758

S tandardError2618.338.824043574.823432.95623

t-value(b=0)

2.53-1.80-2.362.23

Prob.Level0.01860.08410.02660.0352

Seq.R-Sqr

0.18440.38880.4523

SimpleR-Sqr

0.18440.31310.2908

.3997296 -1.82 0.0819 0.5185 0.2127







157445.36114.22946.46751684.718

30.7647173.68276.4175293

0.51850.4382

F-Ratio Prob. Level

6.46 0.001

J-21


Residual Analysis

Row

123456789101112131415161718192021222324252627282930313233343536

Durbin

ActualYt

,

,

•

59.45457.345.848.560.771.870.642.852.857.521543.6116.4143.696.863.889.553.663.837.539.410544.7,

17.888.588.1

t

•

15157.5- Watson

Predicted Std ErrValue141.1113135.105874.5027489.1327186.2055181.109750.205965.3828676.7792265.5499265.0115165.0115164.5768264.2231765.46734142.090165.1792372.5086471.52433103.5267103.856675.7008252.1328956.595157.4500257.7234179.3160152.8481667.6524726.0277956.8467961.1599467.1311366.90881183.777669.05804

Statistic 1

of Pred14.827813.739577.3882898.8569168.979489.00659913.074869.3737517.5358398.5896798.9946818.99468110.6924210.800149.71571515.253398.3947647.5620077.6797189.6274649.6126768.6973611.785611.0587711.0708511.895239.22261212.597338.16292727.4912910.5645919.69377.371018.1796824.3162519.9642

.776327

Lower95XMean110.5091106.749559.2544970.8534567.6732962.5215223.2214946.0369361.2264647.822246.4479246.4479242.5093741.9334145.41566110.609547.8537856.9018655.6746283.6571884.0176157.7508627.8092833.7715834.6015633.1735560.2820126.8492850.8055-30.7098435.0431720.5152851.9185550.02726133.592727.85511

Upper95%Mean171.7135163.462189.75098107.412104.737799.6978877.1903284.7287892.3319983.2776483.5750983.5750986.6442786.5129285.51902173.570682.5046888.1154187.37404123.3963123.695793.6507876.456579.4186380.2984882.2732698.3500178.8470384.4994582.7654178.65041101.804682.3437283.79037233.9624110.261

Residual

,(

•

•

-26.8055-27.10977.094097-19.58286-28.27922-4.8499186.7884985.588493-21.. 77682-11.42317-7.96733972.90994-21.5792343.8913772.07568-6.726723-40.0566413.799181.467117.204895-19.95002-18.3234125.68399-8.148155

t

-8.22778731.6532126.94006•

•

-32. .77757-11.55804

J-22

Multiple RegressionDate/Time 04-06-1992 11:25:48Data Base Name C:\NASA\WUC96Description Merge of WUC47 and WUC12 created 02-11-1992


Dependent VariableIndependentVariableInterceptDRY WGTCREWSIZELEN WINGPERSONSSQR PERWGT49/96SQRWT49/LOGWT49/

FMA49/96ParameterEstimate17952.73.5793E-02169.962-10.1356821.14998-461.3335-1.892708421.331-4O54.064

StndizedEstimate021

-610

-13-3771-29

.0000

.6703

.5299

.6007

.7670

.7798

.9819

.9834

.7305

Standard t-valueError (b=0)2610.109.1051E-0234.799771.4932223.98022986.43541.315461168.4356615.40O6

654-65-5-66-6

.88

.51

.88

.79

.31

.34

.00

.16

.59

Prob.Level000000000

.0000

.0002

.0005

.0000

.0002

.0002

.0001

.0001

.0000

Seq.R-Sqr

00000000

.2448

.4510

.5271

.5287

.5324

.5328

.6250.

.9242

SimpleRr-Sqr

00000000

.2448

.4508

.4064

.2572

.3662

.3246

.4239

.5188


Dependent Variable: FMA49/96


Constant 1 770752.3Model 8 534015.3Error 11 47919.77Total 19 631935



Mean Square

770752.373001.914356.34233259.74

66.00259196.31.3362162

0.92420.8690

F-Ratio Prob. Level

16.76 0.000

J-23


Residual Analysis

Row

1234567S9101112131415161718192O212223242526272829303132333435

Durbi

ActualY.

„

„

234B

23555.54O. 160.395108.4121.8236.6236.8262.1610.8.

83.6131.1561.1492.7.

34.748.834.246.770.534.6

m

10201.4175.9,

a

331.5n - Watson

Predicted Std ErrValue.

m

.

296.2767»

213.767647.42839.

.

.

.

„

258.4744259 . 3846217.3143454 . 2334.129.978132.4468630.444452.9334.

.367659226.3637521.5707873.3337878.9325984.06O72.

-7.931614•

179.8266.

.

376.9937Statistic .

of Pred*

m

.

23.31404•

36.6763165.27004.

.

.

.

B

36.7633236.8095934.7252228.79348•

36.8856236.6277446.6696440.21066

B

32.3759631.5515231.5928763.020853.7456649.07781•

64.03231.

65.26067.

.

33.911248255058

Lower95%Mean»

m

m

245.0067m

133.1125-96.10739

m

m

m

m

m

177.628178.4363140.9498390.9134

—

48.8625351.8985527.8124364.5058

• *

-70.83053-43.0214-47.90533-65.2557-39.25987-23.86664.

-148.7455m

36.31137m

•

302.4193

Upper95%Mean,

m

m

347.5468•

294.4228190.9642.

B

m

m

m

339.320934O . 3328293.6787517.5533

—

211.0934212.9951733.0755541.3609

m

71.5658595.7489191.0469211.9232197.125191.9881

—

132.8823a

323.3418.

•

451.5682

Residual

•

.

.-62 . 27673

m

21.232388.07161

m

.B

m

m

-21.87442-22.5845844.78574156.5666

m

-46.37795-1.346802-69.3439939 . 76666

m

34.3323422.4362512.62922-26.63378-8.432587-49.46072•

17.93161.

-3.926575.

.

-45.49371

J-24

—. Multiple Reqression-•Date/Time 04-20-1992 12:59:29Data Base Name B:WUC97Description Backup of WUC97 created 03-13-1992


Dependent Variable: FMA91397Independent Parameter Stndized StandardVariable Estimate Estimate ErrorIntercept 7549.095 0.0000 204O.461DRY_WGT -.165E-01 -4.8461 .7514E-02LEN_WING 4.00187 2.6090 1.085099LN DRYWT -999.7649 -6.7243 276.4O953QR WGT 16.8468 10.9600 6.396186PERSONS -4.224915 -2.1475 .862487

value=0)3.70-2.203.69-3.622.63-4.9O

Prob.Level0.00210.04420 . 00220.0025O.O1880.0002

Seq.R-Sqr

0.11830.29450.30540.62560.8560

SimpleR-Sqr

0.11830.18600 . 08310.12140.0506


Dependent Variable: FMA91397


Constant 1 6O3369.1Model 5 2055O8.5Error 15 34579.43Total 20 240087.9

F-Ratio Prob. Level



603369.141101.72305.295120O4.4

48.01349169.5048.2832575

0.85600.8080

17.83 O.OOO

J-25

Multiple Regression-Date /Time O4-20-1992 12:59:29Data Base Name B:WUC97Description Backup of WUC97 created 03-13-1992

Residual Analysis

ActualYw

„

.

104_

122.4m

249.241146.8175.219972.174.896.9125.4

i»

58109.5

-• i*

*

„189.9281.2140.8452.8128.596

„

385 . 3.

- Watson

Predicted Std ErrValue143.8382125.92597.2693653.5772846.76052134.22921031.059237.2138108.7047204.3625205.5599205.559945.6894545.4324562.84465174.4325159.903793.4960392.0333873.5501980.5303653.35607211.3269212.3031220.6398425.021893.45365104.506988.O2855-533.9526339.3272505.O987194.987895.26366289.9013

Statistic l.

of Pred25.8281724.4618216.0448418.0265217.8945526.72573205.203521.5065218.6879617.8731719.511219.511220.2745620.5197418.4420225.8818216.5136914.8038914.5377419.2375619.636716.5085529.4641226.6347525.4620135.3164225.0448246.2821222.05599436.025525.87459327.400915.9200515.4212841.4184

8O4476

Lower95%Mean88.805873.8039963.0824615.167988.63240177.28436593.8298191.389668.88611166.2799163.9872163.98722.49O2311.71081523.55004119.2859124.717861.9532261.0576732.5605238.6902318.18113148.5473155.5521166.3876349.77284O.09O395.89305941.03361-1462.997284.1959-192.498161.066862.40537201.6507

Upper95%Mean198.8705178.O461131.456391.9865884.88863191.1741468.288283.038148.5234242.4451247.1326247.132688.8886789.15409102.1393229.5792195.0896125.0388123.0091114.5399122.370588.53101274 . 1064269.054274 . 892500.2709146.8169203.1207135.0235395.0914394.45841202.695228.9089128.1219378.152

Residual

.

.50.42272.-11.82916.11.98621-67.70474-57.5625-30.35989-6.55989126.4105529.3675534.05535-49.03252

—

-35.4960317.46662

m

m

m

-21.4268668.89696-79.8397827.7781735.04635-8.506867

m

m

45.97281•

•

„

20.89865

J-26

APPENDIX K

MHMA Regression Analysis

Multiple RBgsedaaonDate/T,ime 04-01-1992 15:46:03Data Base Name C:\NASA\WUC11Description Backup of NASAMSTR created 12-18-1991


Dependent Variable: MH/MA11Independent Parameter Stndized StandardVariable Estimate Estimate ErrorIntercept 16.57323 0.0000 3.446548FUS DENS -.3511567 -0.7189 .8338E-01LN DRYWT -.7455627 -0.4292 .2965363

value:=0)4.81-4.21-2.51

Prob.Level0.00010.00030.0194

Seq.R-Sqr

0.29260.4451

SimpleR-Sqr

0.29260.0172


Dependent Variable: MH/MA11



F-Ratio Prob. Level



982.155415.205911.6483832.732985

1.2838946.146154.2088938

0.44510.3969

9.22 0.001

K-l


Row

1234567891011121314151617181920212223242526272829303132333435

Durbin

ActualY,

,

.

5.8,

5.26.93.97.44.34.44.36.25.46.77.6,

5.795.24.1

t

5.78.19.869.26.3,

5.44.45.1

f

t

7.7- Watson

PredictValue7.5689377.5651485.9721216.1180946.0871484.1100455.1510784.2515176.811384.6304664.6081254.6081256.0160826.0014865.9183147.374845.0970786.467176.7717155.7643465.7643465.8053037.1687767.1420277.1218796.4155677.3629026.254596.7449766.2516037.0082646.0111435.5941745.3583828.696106

Statistic :

Residual Analysis

of Pred.530663.5209367.2885803.339687.3332928.6046.4670056.5098779.3165508.4368744.4402585.4402585.2735671.2736548.2748418.5128313.3557626.280771.3012482.40291.40291.3146783.393468.3987096.3993941.3622405.397073.4301723.290952.6268806.3578876.5460897.2865999.3272913.7472628

.591353

Lower95%Mean6.4712856.4876155.3752075.4154675.3977482.8594584.1850993.1968596.156613.7268123.6974713.6974715.4502225.4354445.3498166.3140734.3611995.8864096.1485974.9309454.9309455.1544056.3549066.3173156.2957515.666296.5415755.3647996.1431564.9549296.267994.8815825.0013564.6813957.150428

Upper95%Mean8.6665888.6426816.5690366.820726.7765495.3606316.1170575.3061767.466155.534125.5187795.5187796.5819436.5675286.4868118.4356085.8329567.0479327.3948336.5977466.5977466.45627.9826467.966747.9480077.1648458.1842297.1443827.3467977.5482767.7485387.1407046.1869936.03536810.24178

Residual

•

•

9

-.3180933a

1.0899551.748922-.3515172.5886202-.3304658-.2081251-.308125.1839175-.6014857.7816863.2251596•

-.76717042.228285-.5643458-1.664346•

-1.468776.9579732.678121-.41556741.837098. 4541E-01*

-.8516026-2.608264-.9111433•

t

-.9961062

K-2

T Sum of Functions RegressionDate/Time 04-02-1992 15:39:30Data Base Name C:\NASA\WUC12ADescription Merge of WUC11 and WUC12 created 04-01-1992


Y: MH/MA12 X: LOG PERSModel: A+B*(1/SQR(X))+C*(X*X)

Term Coefficient EstimateA 7.085547889120501B -1.66660693023797C .0987784700042235

Std. Error2.5541922.2571517.185552E-02

T-Value Prob(!t!>T)2.8 0.0130-0.7 0.47041.4 0.1871


df21719

Sum-Sqr52.4533342.9846895.438

Mean Square26.226662.528515.023053

SQR(M.S.)5.1211981.5901292.241217

F-Ratio10.4

R-Squared0.54960626

Prob(f>F)0.0011

K-3

Sum of Functions RegressionDate/Time 04-02-1992 15:39:39Data Base Name C:\NASA\WUC12ADescription Merge of WUC11 and WUC12 created 04-01-1992

Residual Analysis

Row123456789101112131415161718192021222324252627282930313233343536

ActualX00.69314720001•

.79175969314720•

•

•

•

,

.

0•

000•

0444425353411•

3

693147269314726931472693147269314726931472

6931472

6931472

.564348

.564348

.564348

.430817

.397895

.365976

.433987

.899898

.7612

.369448

.609438

.3862946931472.135494

ActualY

7.6

4.4.43.55.65.5.4.3..

8.1076..

6.8.11107.10.

7.57.,.

4.7.

52

2

3

4278

5

5

48.9.23.4

7

7

69

Predicted Lower95%Y Value

5.131208 1.596899

65

555555

5

5

88886979786557

.

.157598

.131208

.

.131208

.131208

.131208

.131208

.131208

.131208

.

.131208

.

.

.

.131208

.

.363339

.363339

.363339

.233025

.577252

.210281

.351009

.837771

.62358

.174137

.027713

.859896

.131208

.115475

21

111111

1

1

44442535442213

,.453058.596899..596899.596899.596899.596899.596899.596899,.596899....596899,.840035.840035.840035.714607.839643.483817.732269.766802.054166.655851.355306.240462.596899.450584

Upper95%Value

8.665516

.9.8.,

8.8.8.8.8.8.

t

3.,,.

8.,

111111111012101311119.9.8.10

862137665516

665516665516665516665516665516665516

665516

665516

.88664

.88664

.88664

.75144

.31486

.93675

.96975

.90874

.19299

.692427001247933665516.78037

Residual

*

*

,

-1.957598-1.131207

*

-.1312074. 1687928.8687926.2687927.0687924-.4312076,,,,.

1.368793.

-1.963338.43666193.5366611.966975.72274821.189718

*

-2.137771-2.62358-.4741375

^9

-.5312075.7845255

K-4

Residual P--. • Sum of Functions Regression-Date/Time 04-02-1992 16:08:13Data Base Name C:\NASA\WUC13,-Description Backup of NASAMSTR created 12-20-1991


Y: MH/MA X: LOGWGT13Model : A+B*(X)+C*(X*X)-l-D*(X~3)

Term Coefficient EstimateA -156.94627814436718 55.98411332035852C -6.095157233287962D .2128174813014896

Std. Error175.319563.685287.631809.3017441

T-Value Prob(!t!>T)-0.9 0.38250.9 0.3909-0.8 0.43490.7 0.4897

R-Squared0.27491117


df Sum-Sqr3 39.0643818 103.033821 142.0982

Mean Square13.021465.72416.76658

SQR(M.S.3.6035262.. 3925092.601265

F-Ratio2.3

Prot>(f>F)0.1146

K-5

Sum of Functions Regression-Date / Time 04-02-1992 16:08:18Data base Name C : \ N A S A \ W U C 1 3Description Backup of NASAMSTR created 12-20-1991

ActualRow X

1234 7.1444075 .6 7.3038437 9.4720898 .9 .10 .1112 .13 7.5817214 7.5817215 7.5817216 6.6437917 .18 7.17395819 7.20266120 6.82871221 6.97260622 .23 8.49146524 8.49146525 8.49146526 9.30773927 6.98564228 9.29192129 .30 10.5527431 8.36520732 10.1739333 .34 .35 6.26720136 9.497772

ActualY,

«

.

9.9m

8.56.26.46.810.111.59.611.57.310.611.9

m

9.513.664.3•

10.99.411.79.110.96.6.

5.95.94.8.

.

6.67.9

Residual Analysis

Predicted Lower95% Upper95%Y Value Value Residual

9.522524 4.266597 14.77845 .3774756

9.720329 4.451412 14.989257.340721 1.897937 12.78351

9.8941269.8941269.8941268.370622

9.564929.6035648.8958049.221945

9.2529119.2529119.2529117.7002859.2480737.734547

5.1746969.430365.845793

6.9005557.284155

4.605783 15.132474.605783 15.182474.605783 15.182472.906784 13.83446

4.307173 14.822674.34368 14.863453.592491 14.199123.961608 14.48228

3.9501933.9501933.9501932.2692833.9893992.305128

14.5556314.5556314.5556313.1312914.5067513.16397

-1.452819 11.802214.138935 14.72179.1736933 11.51789

-1.220329-1.140721

.4045451.840164

13.3965612.72815

1.605874-2.594126.70587443.529378

-.649E-013.996436-2.895804-4.921945

1.647089.14708942.447091.3997151.651927-1.134547

.7253048-3.53036-1.045793

-.3005549.6158446

K-6

Sum of Functions RegressionDate/Time 05-18-1992 15:22:42•'Data "Base Name C:\NASA\WUC23Description Merge of WUC11 and WUC51 created 04-27-1992


Y: MHMA23 X: ENG WGTModel: A4-B*(X)+C*(SQR(X) )

Term Coefficient EstimateA 52.6323670458033B 9.122120994236714D-04C -.393600323202448

Std. Error14.947581.089452E-03.273407

T-Value Prob( !tJ >T)3.5 0.00260.8 0.4140-1.4 0.1681


df Sum-Sqr2 1509.60817 2056.60219 3566.21

Mean Square754.8038120.9766187.6953

SQR(M.S.27.4736910.9989413.70019

F-Ratio6.2

R-Squared0.42330867

Prob(f>F)0.0093

K-7

Sum of Functions RegressionDate/Time 05-18-1992 15:22:51Data Base Name C:\NASA\WUC23Description Merge of WUC11 and WUC51 created 04-27-1992

Residual Analysis

Row123456789101112131415161718192021222324252627282930313233343536

ActualX

•

•

4497,

428336554•

*

,

•

^

9968996899682247,

604960913671

»

,

t

166961669623386380425471,

390911053543162,

•

176723321

ActualY

•

•

.22.

2913192417132425314158. .36313211.

101213141214•

116.10•

•

254.

.6

.8

.7

.3

.2

.2

.7

.7

.5

.5

.9

.8

.5

.9

.7

.2

.8

.9

.1

.2

.2

.44.7

1

PredictedY

.30.

3010•

•

•

•

•

22222236•

272732•

•

t

1717133113•

102110•

*

3713

.33987

.78034

.72453

.42829

.42829

.42829

.02446

.53795

.47017

.13334

.00438

.00438

.7741

.8265

.05014

.47118

.84333

.23296

.69898

.79851

Lower95%Value

•

6

6

.•

•

•

104384

488446-14.83741

---1

337

e

•

.•

•

1110.•

•

•

•

•

•

-7-7

.860969

.860969

.860969

.33417

47882641185612824

.596682

.596682-10.738897•365395-11.44577

-•

1-25.76686.492323

-17.50677

1

•

•

1.25618-10.71545

Upper95%Value

*

.54.,

55.36.,

•

•

•

•

46.46.46.61..

51.51.56.

*

•

•

41.41.38.56.37..

36.46.37.•

•

64.38.

57537

0722428647

71755717557175571475

597075284965385

605446054428712876154605

70923178979727

1417831248

Residual

•

-7.739875•

-.98034352.975473•

.•

•

•

3.0717089.07170919.4717122.77554•

8.4620524.029831.7666664•

•

•

-4.204381-3.104381.325899-19.62651.14986•

.9288171-15.44333.4670366•

•

-12.69898-9.698515

K-8

Residual Plot

-Multiple Regression-Date/Time 04-02-1992 17:09:45Data Base Name A:WUC24Description Backup of WUC24 created 03-13-1992


Dependent Variable: MH/MA24IndependentVariableInterceptKVA MAXSQR KVAWGT24SQR WT24LOG WT24

ParameterEstimate-451.3954.9054E-01-2.965429.265695-26.09953150.5043

StndizedEstimate0.00003.4559-4.002730.0350-58.211929.6631

StandardError118.7124.4055E-011.175478.7173E-016.88959138.72723

t-value(b=0)-3.802.23-2.523.70

-3.793.89

Prob.Level0.00890.06700.04510.01000.00910.0081

Seq.R-Sqr

0.00720.01660.04120.07490.7370

SimpleR-Sqr

0.00720.01010.00250.00430.0098



Source


df Sums of Squares Mean Square F-Ratio Prob. Level(Sequential)

1 1164.275 95.682116 34.147911 129.83



1164.2719.136425.69131611.80273

2.3856489.85.2421977

0.73700.5178

3.36 0.086

K-9

Multiple Regression-Date/Time 04-02-1992 17:10:05Data Base Name A:WUC24Description Backup of WUC24 created 03-13-1992

Residual Analysis

Row

1234567891011121314151617181920212223242526272829303132333435

Durbin

ActualY.•

,

•

f

8.7,

•

•

,

,

.

,

•

•

,

,

17.213.87•

.

7.97.512.7rrt

129.

7.76.713•

•

,

- Watson

PredictedValue.t,.,

6.741755.......,...

17.0495311.434049.05177610.05459.10.2929410.1549710.154976.877838.

8.31726913.15047.6492337.56062812.91464...

Std Errof Pred.,,.,

1.770797,..........

2.276696.98696531.6565091.613951.

1.1469991.1254871.1254871.776137.

1.2217661.3222752.338621.5856652.372941...

Lower95%Meant

^9

t

,

2.411969,t

,,,,,,,«,

11.482779.0208075.0014386.108312,

7.4884117.4030357.4030352.534996,

5.3299249.91731.9310613.683517.112551...

Upper95%Mean9

9

.

t

t

11.07154t

§

9

t

f

t

t

t

9

9

t

22.6162913.8472713.1021114.00087

%

13.0974812.906912.906911.22068.

11.3046216.383513.367411.4377518.71673,9

t

Residual

.

.,

1.958245.

.

.t

.,.t

•

t

.15047262.365959-2.051776,"«-2.392944-2.6549692.545031,1221623

t

.6827307t

.5077E-01-.8606281.8536E-01.,9

Statistic 1.731521

K-10

Sum of Functions RegressionDate/Time 03-20-1992 16:11:05Data Base Name C:\NASA\PRECON2Description Merge of WUC12 and PRECON created 03-19-1992


Y: MH/MA42 X: LN DRYModel: A+B*(X)+C*(X*X)

Term Coefficient EstimateA -95.16097482423832B 20.31584606137617C -.983565860822489


df Sum-Sqr2 52.3716424 184.280226 236.6519

Std. Error57.2112910.63598.4916664

Mean Square26.185827.6783429.101995

T-Value Prob(ItJ>T)-1.7 0.10931.9 0.0681

-2.0 0.0569

SQR(M.S.5.1172082.7709823.016951

F-Ratio3.4

R-Squared0.22130247

Prob(f>F)0.0497

K-ll


Residual Analysis

Row123456789101112131415161718192021222324252627282930313233343536

ActualX9.1720159.227099109.9.9.1110101010101010109.1010109.9.1011111111

.1487178650482801943766.93356.76806.08581.6697.69967.69967.25924.26472.29766154722.57227.19496.21921578242578242.04542.11394.18428.21131.48278

9.9734811101211121010

.85568

.35358

.67634

.0315

.39095

.53204

.378548.80582512.1442

ActualY

.8..

8.7.6.76.9.7.1410139..

9178.7..

56.119.7.7..

5.134...

7.6.

6

353

744.6.7.13

.532

9.1685

3.27

51

Predicted Lower95%Y Value8.432947 2.1181088.555184 2.3042719.9.9.9.7.9.9.9.9.9.9.9.9.8.9.9.9.9.9.9.9.9.8.8.9.7.9.4.9.5.9.9.7.6.

714996458464500953601545209922555716688965631414610364610364741886742595745605393341687634729173734923194108194108668145138396024733978465434091623115449983745828320797259225559242705401743942468602500862

3.3.3.3.1.3.3.3.3.3.3.3.3.2.3.3.3.3.3.3.3.3.3.2.3.1.3.-23.*" •

3.3.

837769547251598363715425198005653239811125732719710418710418862651863181865008057032793509851511856787211594211594789035229833115607069075515919739674466471862843.4646393513537975169813326859775

.5409592

.3732426

Upper95%Value14.7477914.806115151515131515151515151515141515151515151514141415131511151115151412

.59222

.36968

.40354

.48767

.22184

.45819

.5668

.53011

.51031

.51031

.62112

.62201

.6262

.72965

.58176

.60683

.61306

.17662

.17662

.54726

.04696

.93386

.88786

.35226

.50656

.43349

.62881

.10623

.1671

.916

.59747

.62811

.39624

.62848

Residual

,-.8584635,

-1.301545.2900778-3.255715-2.688964-2.931413-.2103646-2.2103644.858114.95740553.354396.9066593

*

-.72917237.765077-.8941078-1.994108,

-4.138396-2.1247322.1215351.16591-1.823115. 5002E-01

m

.97920363.940775-.8592423

9

g

.3140E-01-.4008624

K-12

Multiple RegressionDate/Time 06-08-1992 12:05:32Data Base Name C:\NASA\PRECON2Description Merge of WUC1.2 and PRECON created 03-19-1992


Dependent Variable:IndependentVariableInterceptLN DRYLN LENTH

WGT/LENSQRLGDRY

SQRLGLEN

MH/MA44ParameterEstimate2300.043474.1092-452.2954

-.1462855-2769.85

1788.391

Stndized StandardEstimate Error0.0000 900.3793

231.8082 165.1477%-125.2645

148.6725-11.0183 .5235E-01%-206.6015

966.0448109.4917 593.9519

value= 0)2.552.87

-3.04-2.79

-2.873.01

Prob.Level0.01850.0091

0.00620.0109

0.00920.0067

Seq.R-Sqr

0.0274

0.05880.0979

0.09830.3702

SimpleR-Sqr

0.0274

0.04180.0312

0.02530.0393







Mean Square

630.757.7152573.1249394.007692

1.767754.833334.3657413

0.37020.2203

F-Ratio Prob. Level

2.47 0.066

K-13

Multiple RegressionDate/Time 06-08-1992 12:05:53Data Base Name C: \NfASA\PRECO.\'2Description Merge of WUC12 and PRECON created 03-19-1992

Row

123456789101112131415161718192021222324252627282930313233343536

Durbin

ActualYt

.

.4.7.

3.54.582.86.810.344.64.35.36.5

t

4.79.82.43.3•

3.84.95 . 55.14. 14.4.

3 .32.43.3

,

5.42.8- Watson

PredictValue4.4761424.2799735.1616384.3674974.3897143.6530585.0351936.9205124.8122596.6819516.7876646.7876645. 1065885.0992645.4466584.5054466.4760195.3922335.4749974.1343344.1503094.922563.3767574.4480464.6672455.1861513.4811115.1796414.215461.8614274.1576762.8497575.787185.9288246.1064574.827341

Statistic :

Residual Analysis

of Pred1.0335741.061601.4341575.7106825.749886.8042564.9830074.7419165.4654595.6717756.7033455.7033455.7295298.7355821.6352148.8628373.6235349.4540576.469175.7652015.6651328.6141115.8575392.656988.6337518.6777176.8803259.9178398.7478251.275647.71845621.251661.5418295.53776281.5192211.041613

458488

Lower 9 5%Mean2.3269842.0725384.2588752.8897432.8304421.9807312.9911825.3778123.8444085.2850975.3251665.3251663.5896443.5697354.1258272.7113095. 1794754.4480914;499422.5432162.7672693.645611.5936373.0819423.3494563.7769421.650613.2711352.660474-.79108232.663758.24712284.6605294.810632.9474732.661469

Upper 9 5%Mean6.62536.4874086.0644025.8452525.9489865.3253847.0792058.4632135.780118.0788048.2501618.2501616.6235326.6287936.7674896.2995837.7725646.3363756.4505735.7254525.533356.199515.1598775.8141515.9850346.595365.3116127.0881465.7704474.5139375.6515945.4523926.913837.0470199.2654416.993213

Residual

.t

t

.3325024(

-.1530578-.53519341.079488-2.012259. 11804963.512337-2.787664-.506588-.7992635-. 14665791.994554(

-.69223314.325004-1.734334-.8503091•

.4232426

.4519539

.8327551-.862E-01.6188891-.7796407,

1.438573-1.757676.4502428•

•

-.7064567-2.027341

K-14

. Multiple Regression—Date/Time 03-18-1992 20:48:06Data Base Name C:\NCSS\FILES\preconDescription Backup of PRECON created 03-18-1992


Dependent Variable: MH/MA45Independent Parameter StndizedVariable Estimate EstimateIntercept 0LN DRYLDRY SQD

2.412351 3.4617-.1630653 -2.5469

Standard t-valueError (b=0)

.4730937

.04346585.10-3.75

Prob.Level

0.00000.0009

Seq.R-Sqr

0.85570.9077

SimpleR-Sqr

0.85570.8116





02

2527

01365.137138.8831504.02



Mean Square

682.56855.55532155.70445

2.3569737.022222.3356449

0.90770.9040

F-Ratio Prob. Level

122.87 0.000

K-15

Multiple Regression—Date/Time 03-18-1992 20:48:06Data Base Name C:\NCSS\FILES\preconDescription Backup of PRECON created 03-18-1992

Residual Analysis

Row

123456789101112131415161718192021222324252627282930313233343536

Durbin

ActualY^.f

9.1t

9.84.668.38.28.67.18.78.311.99.5•

8.913.24.54•

5.45.896.24.55

f

4.94.15.7•

.5.92.4- Watson

PredictedValue8.4081128.3757297.6871177.9907987.9581687.8642065.5658367.0687477.7429297.1753027.1431557.1431557.5859347.5808237.5498248.4180767.2777367.6452787.6230488.146038.146037.7780876.6689536.5828856.5493646.1996377.8393825.6800657.4964124.3768776.7677774.8549767.3191527.4722548.5982425.246937

Std Errof Pred.7703225.7559537.5271578.6106086.6002989.5723715.7595165.4573211.5403237.4587896.4578761.4578761.5059632.5049864.4992655.7748201.4644312.5179666.5133272.6638971.6638971.5491371.4888824.5022931.5080413.5824589.5654381.7250962.49022121.14514.4761021.986229.4678913.4864747.8634986.8591117

Statistic 1.444019

Lower 95%Mean6.8217256.8189346.6014996.7333236.7219256.6854764.0017036.1269496.6301986.230486.2002146.2002146.5439636.5408656.5216476 8224276.3212966.5785886.5659126.7788136.7788136.6472055.6621595.5484735.5031155.0001336.6749314.1868176.4868612.0185995.7873032.8239566.3555876.4704196.8199713.477701

Upper95%Mean9.9944979.9325248.7727369.2482729.1944119.0429367.1299698.0105448.855668.1201238.0860958.0860958.6279048.6207828. -57800110.013728.2341768.7119688.6801839.5132469.5132468.9089687.6757487.6172977.5956147.3991419.0038347.1733138.5059636.7351557.7482526.8859958.2827188.47409110.376517.016174

Residual

.•

1.109203•

1.935794-.9658361-1.068747.55707121.0246981.456846-.432E-011.114066.71917734.3501761.081924•

1.2547225. 576952-3.64603-4.14603

*

-1.268953-.78288512.450636. 3629E-03-3.339382-.6800647

^

.5231233-2.667778.8450241

*

•

-2.698242-2.846937

K-16

Resiauai --lot

Multiple Regression-Date/Time 04-02-1992 16i:29:08Data Base Name A:WUC14Description Backup of WUC14 created 03-27-1992


Dependent VariableIndependentVariableInterceptACTUATORCONT SURWETAREADRY WOTLOG WG14SQR ACT

: MH/MA14ParameterEstimate26.23825-1.106748-1.66585-.328E-02.6018E-03-6.28269214.28908

StndizedEstimate0.0000-8.9169-6.7252-9.741217.3149-1.54988.4616

StandardError16.15215.5413623.6519315.1091E-02.2159E-033.4293736.916294

t-value(b=0)

1,-2,-2-32

-1,

620456017983

2.07

Prob.Level0.13260.06560.02670.01190.01770.09410.0632

Seq.R-Sqr

0.09250.21500.255545894688

0,0,0.6173

SimpleR-Sqr

0.09250.21210.21390.18550.25220.1272







Mean Square

1278.49415.270125.1632188.730359

2.2722728.427778.2696169

0.61730.4086

F-Ratio Prob. Level

2.96 0.057

K-17


Residual Analysis

Row

12345678910111213141516171819202122232425262728293031323334

Durbin

ActualY...

10.6.

65.769.79.99.39.611.39.811.911.4

*

10.915.17.35.8,

6.67.39.46.37.76.5,

6.33.96.1.

•

- Watson

PredictedValue...10.92807•

7.7142343.419895.....

8.604839.62538810.2037212.11051•

9.62702711.574128.7157748.673118

t

6.1286969.07150710.258264.962518.•.

6.7099266.5405986.831707•

•

Std Errof Pred•

•

•

1.527894•

.9371691.746283•.....9662351.0130471.0631921.982511•

1.3312171.2638721.002661.009739.

1.2229411.2369831.4748211.105857...

2.2635691.0021212.216654.•

Lower95%Mean•

•

,

7.568065•

5.653299-.420368•

*

•

•

•

6.4799767.3975897.8656467.750756•

6.6995388.7947296.5108186.452595•

3.4393186.3512497.0149712.53062

• -

•

•

1.7320964.3368261.957047•

•

Upper95%Mean•

t

•

14.28807*

9.7751687.260158•

•

•

•

•

10.7296811.8531912.5417916.47026•

12.5545214.3535110.9207310.89364•

8.81807511.7917613.501557.394416

*

,

%

11.687768.74437111.70637•

•

Residual

t

§

.-.3280668

t

-1.7142342.280105•

•

•

•

•

2.69517.1746121.69628-.7105103•

1.2729733.525882-1.415773-2.873117•

.4713035-1.771506-.85825921.337482•

,

•

-.4099255-2.640598-.7317071.

•

Statistic 1.432175

K-18

Huitipie Regression--1.4 : LA : 45Date/rime U4-O5-1992

Data Base Name B:AVIONICSDescription Backup of AVIONICS createa O3-27-1992

Multiple Repression Report

Dependent VariableI ndepenaentVariableInterceptDIP SUBSSQR T3UBWGT51/723QR51/72LOG5172

: MH/MAParameterEstimate131.39541.039403-9.035161-.154E-012.864137-26.19323

itndizedEstimate0.00002.3979-2.6722-10.994518.6286-7.6260

Error45.66148.26467632.627782-4954E-02-95541259.767553

value=0 )2.883.93-3.44-3.113.OO-2.68

Prob.Level0.01500 . 00240.00550 . 00990 . 01210.0213

Seq.R-Sqr

0 . 21560 . 30660 . 30660.4O870 . 6425

SimpleR-Sqr

0 . 21560.09180.0000O.OO790.0289


Dependent Variable: hH/MA

Source df 3ums of Squares Mean Square(Sequential)


F-Ratio Prob. Level


R SquaredAdiusted R Squared

1107.28516.8O6154-.2513238.174706

2.0618748.070588.25548

0.64250.4799

3.95 0.027

K-19

Multiple rtearession•14:1-4:45uate/Time O4-O5-1992

Data Base Name B:AVIONICSDescription Backup of AVIONICS created 03-27-1992

Residual Analysis

Row

1234567a91011121314151617181920212223242526272329303132333435

Ourbi

ActualY..

-,

7.3.

7.86.810.25.713.81311.23. 79

3.88.2

„

12.613.64.74.9

m

3.79.611811.8-7

„855.3.

„

4 . 6n - Watson

PredictedValue.

-.

8.218O63.

6.69O7496.7421

„

m

„

._

„

11.1196,

8.739O8„

10.0327710.133886.3776O36.377603..11.776419.236857.10.979O57.258468,7.6897097.2882745.474031..

3.O66015

3td Errof Pred.-.1.581274•

.92692022.056123

»......8945798.

1.94O782..7545902.7599139.8949887.8949887..1.044804.7690271.1.1040181.111545.

1.0303311.O848991.464335..1.443832

Lower95?>Mean„

-_

4.740672„

4.6523522.220465_

m

^

«

„

M

9.152324w

4.471093„

8.3733448.4627444.4O94274.409427.

•

9.4787727.545684

m

8.5511944.814O61

„

5.42394.9O24662.253802,

B

-.1091256

Upper 955Mean„

.

m

11.69545„

8.72914611.26373

^

„

„

M

-

^

13.08688w

13.00707-

11.6921911.805018.3457798.345779•

„

14.O74O410.92803

„

13.40699.7O2875

—

9.9555199.6740828.694262

m

—

6.241155

Residual

-.9180632m

1.109251.579OE-O1...m

[4

m

-2.1196.

- . 539O8O6—

2.5672323.466125-1.677603-1.477602•

.

-2.1764071.763144

„

.8209524-.2584677

„

. 3102908-2.288274-.174O313

m

„

1.533985Statistic 1.204315

K-20

Multiple RegressionDate/T.ime 03-20-1992 15:55:14Data Base Name C:\NASA\PRECON2Description Merge of WUC12 and PRECON created 03-19-1992


Dependent Variable: MH/MA41Independent Parameter Stndized Standard t-value Prob.Variable Estimate Estimate Error (b=0) LevelIntercept 0LN DRY .6886774 0.9419 .4914E-01 14.01 0.0000

Seq.R-Sqr

SimpleR-Sqr

0.8871 0.8871



Source


df

01

2526

Sums of Squares(Sequential)01409.219179.37091588.59



Mean Square

1409.2197.17483461.09961

2.6785887.442308.3599137

0.88710.8871

F-Ratio Prob. Level

196.41 0.000

K-21

Multiple RegressionDate/Time 03-20-1992 15:55:28Data Base Name C:\NASA\PRECON2Description Merge of WUC12 and PRECON created 03-19-1992

Row

123456789101112131415161718192021222324252627282930313233343536

Durbin

ActualY,•.

6.7.

4.56.75.610.46.71111.68.711.19.56.5•

9.313.35.25.1

t

6.16.7

*

7.27.35.4,

6.35.26.2,

,

7.43.8- Watson

PredictValue6.316566.3544966.9891856.7397456.7683296.8480478.2183747.4157236.9458697.3479827.3686187.3686187.0653057.0690837.0917646.3046517.2808817.0210417.037746.596326.596326.9180557.653927.7023637.7209747.9079296.8685118.1647387.1302748.7299067.5971438.5333657.2531817.1474676.0643748.363435

Statistic :

Residual Analysis

of Fred.4507101.4534169.4987044.4809059.4829455.4886337.5864117.5291395.4956136.5243059.5257784.5257784.5041359.5044054.5060238.4498603.519518.5009774.502169.470672.470672.493629.5461357.5495923.5509203.5642602.4900939.5825845.5087717.6229114.5420845.6088874.5175415.5099984.4327157.5967622

144088

Lower95%Mean5.3883775.4207385.9621635.7493775.7737615.8417657.010736.3260245.9252126.2682376.2858416.2858416.0270986.0303216.0496695.3782186.2109965.9893386.0035845.6270285r.6270285.9014856.5292196.5705446.586426.7459035.8592226.9649756.0825217.4470956.4807857.2794356.1873676.0971875.1732487.134475

Upper95%Mean7.2447437.2882538.0162077.7301137.7628977.854339.4260198.5054227.9665268.4277268.4513958.4513958.1035128.1078448.1338597.2310848.3507658.0527448.0718977.5656127.5656127.9346248.7786218.8341828.8555289.0699557.8778019.36458.17802810.012728.7135019.7872958.3189958.1977476.9554999.592395

Residual

•

t

•

-.397E-01•

-2.348047-1.518374-1.8157233.454131-.64798163.6313824.2313821.6346954.0309182.408237.1953492•

2.2789596.26226-1.39632-1.49632•

-1.55392-1.002363•

-.7079291.431489-2.764738•

-2.429906-2.397143-2.333365•

•

1.335627-4.563435

K-22



Y: MH/MA47 X: DRY_WGTModel: A+B*(LOG(X))+C*(SQR(X))

Term Coefficient EstimateA 5.743205009617056B 1.852806289238006D-02C -3.36575286114062D-03

Std. Error10.811721.2160179.676912E-03

T-Value0.50.0-0.3

Prob(


df2

2426

Sum-Sqr4.08758660.1190864.20667

Mean Square2.0437932.5049622.469487

SQR(M.S.1.4296131.5827071.57146

0.60020.98800.7310

F-Ratio0.8

R-Squared0.06366295

Prob(f>F)0.4541

K-23


Residual Analysis

Row123456789101112131415161718192021222324252627282930313233343536

ActualX96241016925558177921854620822152293474802400043032443414434128545287022966394593903726768274251444714447230506710071990739629703021450140882313693200836179024061337498321626673188000

ActualY

5

35235654587

4742

657454

443

62

.

.5

.

.8

.1

.4

.2

.2

.4

.7

.9

.7

.3,.8.3.3.9.

.7

.6

.4

.6

.8

.

.8

.6

.8

.

.

.8

.6

Predicted Lower95%Y Value5.582958 1.9953985.574758 2.0163225.5.5.5.4.5.5.5.5.5.5.5.5.5.5.5.5.5.5.5.5.5.5.4.5.4.5.4.5.4.5.5.5.4.

39316247558446693944177265083520932240865524269723271223271236463636317635431958548274093814337516251612251612241833107727204736503558907539435052699558338918073869110952321806286585331893631417508858

2.2.2.2.1.1.2.1.1.1.2.2.2.1.1.2.2.2.2.2.1.1.1.1.2.1.1.

04284209688109428208178522206583658805687875322863689863689014288012752003306988315912002031468025169093327093327064947689793658048645656513019077402283092986443

.8264E-011.726151.68052121.1.1.1.

926579978597792076019374

Upper95%Value9.1705179.1331938.8.8.8.8.8.8.8.8.8.8.8.8.9.8.8.8.8.8.8.8.8.8.8.8.8.8.8.8.7.8.8.9.7.

743483854286839595801758079604582056760441610072601735601735714984713670533118264563617973139172515593891793891777171546474943668242550430205879270311602369139406510249575296309646591685188470758998342

Residual

,

-,-

,2442E-01,

1.64177144916532.809322-2.208655

—1,-.31

—1

—-

,,2

—B,

.

—-

1-

.427E-01

.16728846728751.3646365368242.345681.71452.

.5814293

.9248381.2161222.6161224

92272876526353.56442.507538616494771004426.

7261315.5109522.5218055t

,

.1685831.908858

K-24

Mul tide RegressionOats/Time 04-06-1992 12:01:53(fata 6'ase Name C:\NASA\WUC96Description rtsrge of WUC47 and WUC12 r^reatea 02-11-1992


Dependent Variable: MHMA4996Independent Parametervariable EstimateIntercept 9.513174LEN WING .3508E-01WGT49/96 -.721E-03SQR CREW -4.520094

tndizedstimate01

— \_-0

.0000

.7971

.1406

.9904

Standard t-valueError (b=0)1.68657-1022E-01-2665E-031.519629

53-2-2

.64

.43

.70

.97

Prob.Level000o

.0000

.0037

.0163

.0095

Seq.R-Sqr

000

.0031

.2029

.4986

SimpleR-Sqr

000

.0031

. 0600

.1043


Dependent Variable: MHMA4996





773.123416.57323.3327985.539532

1.8255956.378947.2861907

0.49860.3984

F-Ratio Prob. Level

4.97 0.014

K-25

MultiDle RegressionD a t e / T i m s 04-06-1992 12:02:07Data Sase Name C:\NASA\WUC96Description Mercie of WUC47 and WUC12 created 02-11-1992

Residual Analysis

Row

1

34567891011121314151617181920212223242526272329303132333435

Durbin

ActualY

8.5

7.67.63.613.85.310.55.754.9

6.4,

7.213.27.74

B

47. 16.63.44. 13.7.

6.45.74.3

„

.

4.5- Watson

PredictedValue

7.669556

8.6436373.664033

3td Errof Pred

.6735326

.77303321.549436

Lower95%Mean

6.234453

6.9965275.362634

Upper95%Mean

9.104659

10.2907511.96543

Residual

8304439

-1.043637-1.064033

5.8436695.8436696.0085497.366797

8.4357598.4350387.577325.767948

5.0312775.0312775.0874073.1774093.3830246.748656

6.771239

6.378088

.5503315

.5503315

.5307801

.6628822

.7450752

.7449992

.667131

.604834

.5793074

.5793074

.57312911.1431381.089339.7755465

1.310955

.8124059

4.6710734-.6710734.877615.954387

6.8482196.847666^1558574. -479221

377969413:7969413.866234.74171191.0619585.096191

3.977974

4.647086

7.0162667.0162667. 1394888.779207

10.023310.022428.9987837.056674

6.2656146.2656146.3085795.6131055.7040898.401121

9.564504

3.10909

-.8436694-.9436693

-.9667969

-1.2357594.764962. 1226802-1.767948

-1.0312772.0687231.512593.2225916.71697641.951344

-.3712387

-2.078087

5.344202Statistic 1

.6632126490154

3.931088 6.757316 -.8442016

K-26

Residual P-urn or Functions Neoression-1.5:05: OSOate/ Time O4-2O-1992

Data Base Name B:WUC97Description Backup of WUC97 created 03-13-1992


Y: MHMA9137 X: DRY...WGTModel : A+B*(X )+C*(LOG(X ) )+D*(SQR(X ) )

Term Coefficient EstimateA -57.90084944513313 1. 4638806 795145O9D-04C 8.2373209437452080 -.1514356975659418

Std. Error20.626654.060194E-052.6343794.433468E-O2

T-Vaiue Prob(!t|>T )-2.8 0.01093.6 0.00183.1 O.O053

-3.4 0.0027

R-Squared0.41108948

SourceMode 1ErrorTotal

df Sum-Sqr3 18.6634620 26.7365423 '45.4

Mean Square6.2211541.3368271.973913

3QRCM.S. )2.4942241.1562121.4O496

F-Ratio4.7

Prob(f0.0126

K-27

Sum of Functions Regression-Date/Time 04-20-1992 13:05:06Data Base Name 6:WUC97Oescriotion GacKup of WUC97 created 03-13-1992

Residual Analysis

ROW

1

3456789101112131415161718192021222324252627282930313233343536

ActualX962410169255581779218546208221522934748024OOO43O324434144341285452S702296639459390372676827425144471444723050671007199073962970302145014O882313693200836179024061337498321626673188000

ActualY

6

5442354

654

55

554154

835

32

—

.4„

.8

.4

.7

.9

.1

.1m

.8

.7

—

.2

.2m

m

m

.6

.5

.7

.7

.3

.5,

.6

„

„

.3

.3

PredictedY4.204684.3233515555345444555445544544435357455533

.228855

.118762

.147458

.205316

.596225

.751958

.232194

.874202

.838446

.838446

.20O963

.198863

.184861

.165978

.980506

.220557

.214257

.911157

.911157

.229442

.243475

.134512

.O93051

.718819

.214932

.541364

.155697

.698452

.371178

.107493

.O19613

.140531

.241859

.994804

Lower95SValue1.479104I. 6318932222

.

,

.

„

7148O2587104619209683981

.963184122222222122222211112

„

»

„

.

•

._

„

.

.

.

.

•

.

.

.

.

.

.

.

254687162363755634O3663403666901316881946751774287684794117078570225435027435027471216733176616941572236153953694923

.9148228241222

.

.

.

.

.

.

647732475865867238418397517318633351

.16361221.35635

Upper95%Value6.9302567.014809T

77767777777767777776666767

.742908

.650419

.675707

.726651

.229265

.249236

.74815

.372845

.336525

.336525

.711795

.709533

.694546

.903187

.481602

.733264

.72626

.47204

.47204

.746725

.753775

.652083

.613867

.283685

.734942

.167904

.66366210.92104677766

.875117

.796589

.521908

.64771

.320105

.633258

Residual

.1.281238.

-.20531581.203776-.3519578-2.532193-.9742023.2615545-.7384455.

1.601137.5151388-.1659774.

- . 206E-0.1-.143E-01....

1.3565251.365488. 6O69483-2.018819.8507E-01. 9586363.. 30154855-.7711777-.107493...5814E-01-1.694804

K-28

APPENDIX L

POFF Regression Analysis

Date/Time 02-06-1992•-Descriptive Statistics-IBM?: 28

Data Base Name C:\NASA\WUC11Description Backup of NASAMSTR created 12-18-1991

Detail Report

Variable: %OFF EQUMean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Testfbl 1.00 Skew-Z

8.916666E-02.068566.10976735.475333E-024.879119E-022.38058E-03.54719091.0646711.1786170.113522.18 Pr 0.0291

No. observationsNo. missing valuesSum of frequenciesSum of observationsStd.error of meanT-value for mean=0T prob levelKurtosisReject if > 1.182(10%)Reject if > 0.162(10%)b2. 4.33 Kurt-Z

D'Agostino-Pearson Omnibus K} Normality Test100-%tile75-%tile50-%tile25-%tile0-%tile

r\ -I n __

1 1

( Maximum )

(Median )

( Minimum )

12 1111 1

.235

.1245

.0835

.052

.013

1 2 1

90-%tile10-%tileRange75th-25th %tileC.L. Median(95%;

Line Plot / Box Plot11 1 2 2 11

3511242.149.959459E-038.9529630.00001.9510671.289(5%)0.178(5%)

1.78 Pr 0.07517.9 Pr-0.0189

.14

.042

.222

.0725.053, .124

2351

Distribution & Histogram

Variable: %OFFBin Lower1 .0132 3.318E-023 5.336E-024 7.354E-025 9.372E-026 .11390917 .13409098 .15427279 .174454510 ,194636411 .2148182

EQUUpper3.318E-025.336E-027.354E-029.372E-02.1139091.1340909.1542727.1744545.1946364.2148182.235

Count16433330001

Prcnt4.2

25.016.712.512.512.512.50.00.00.04.2

Total-17

111417202323232324

Prcnt4.229.245.858.370.883.395.895.895.895.8100.0

Histogram* ' . • - ' •******-***** t * ;*********

j

*

L-l

Date/TimeData Base NameDescription

Descriptive Statistics02-06-1992 17:03:16C:\NASA\WUC12Data base created at 16:18:28 on 12-19-1991

Detail Report

Variable: %OFF EQPMean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality TestA>1 1.31 Skew-Z

.12876928.176091E-02. 1757775.3386806. 11639251.354722E-02.90388481.392012.0534020.217902.79 Pr 0.0052

No. observationsNo. missing valuesSum of frequenciesSum of observationsStd.error of meanT-value for mean=0T prob levelKurtosisReject if > 1.169(10%)Reject if > 0.156(10%)

359263.3482.282646E-025.6412270.00001.1751611.265(5%)0.171(5%)

D'Agostino-Pearson Omnibus K/ Normality Testb2 3.74 Kurt-Z

9.6100-%tile (Maximum) .43875-%tile .17850-%tile (Median) .08825-%tile .0490-%tile (Minimum) .002

90-%tile10-%tileRange75th-25th %tileC.L. Median(95%)

1.33 Pr 0.1835Pr- 0.0083.298.037.436

.05,. 129

. 16.002 Line Plot / Box Plot .4381 1 12212 11 11111 1 1 11- 111 1 1

Variable: %OFFBin Lower1 .0022 4.163E-023 8.127E-024 .12090915 .16054556 .20018187 .23981828 .27945459 .319090910 .358727311 .3983636


EQPUpper Count I4.163E-028.127E-02.1209091.1605455.2001818.2398182.2794545.3190909.3587273.3983636.438

39.5-220 •120 .11

^rcnt Total11.534.619.27.77.70.03.87.70.03.83.8

312171921212224242526

Prcnt Histogram.* 11.5; 46.2

- 65.4- 73.180.880.884.692.392.3

- 96.2100.0

*********************

***

**

Lr2

Multiple RegressionDate/Time 04-16-1992 12:01:35Data Base Name C:\NASA\WUC13Description Backup of IMASAMSTR created 12-20-1991


Dependent Variable: %OFF EQPIndependent ParameterVariable EstimateIntercept .2774E-O1DRY WGT -.407E-05LEN WING -.194E-02SQRWHEEL5QRW13

.1931569

.7156E-02

tndizedstimate0.0000-2.5518-1.85141..37712.5413

StandardError.1396931. 1497E-05.6558E-03.8535E-01.3463E-02

t-valuefb=0)

0.20-2.72-2.962.262.07

Prob.Level0.84530.01590.00970.03890.0565

Sep.R-Sqr

0.22630.32590 . 56790.6636

SimpleR-Sqr

0.22630.30370.10790.1937

Analysi:

Dependent Variable: %OFF EQP

of Variance Report


Constant 1 2.203816Model 4 .1751109Error 15 8.875405E-02Total 19 .263865



Mean Square

2.2038164.377772E-025.916937E-031.388763E-02

7.692163E-02.33195.2317265

0.66360.5739

F-Ratio

7.40

Prob. Level

0.002

L-3

oate/TimeData Base NameDescription

04-27-1992C:\NASA\WUC23Merae of WUC11 and

cf Functions Regression-42: 16

created 04-27-1992


Y: %OFF EQP X: ENG WGTModel: A+B*(X)+C*(SQR(X))

Term Coefficient EstimateA 1.146330127496948B 4.572100568624601D-05C -1.145581687278943D-O2


df Sum-Sqr2 .151861113 .201946615 .3538078

Std. Error.19059651.54087E-053.70415E-03

T-Value Prob(!t|>T)6.0 0.00003.0 0.0109

-3.1 0.0086

Mean Square7.593055E-021.553436E-022.358718E-02

3QR(M.S..275555.1246369.1535812

F-Ratio4.9

R-Sauared0.42921925

Prob(fO.0261

Date/Time 04-16-1992Data Base Name A:WUC24

Multiple Regression-12:38:01

Description Backup of WUC: :reated 03-13-1992


Dependent Variable:IndependentVariableInterceptLN DRYWTKVA MAXSQR KVA

LOG KVAWGT24SQR WT24

%OFF EQPParameterEstimate-109.8302-.1645163.1426994-6.151774

15.75077.6602E-01-5.683191

LOG WT24 29.07148

Estimate0.0000-1.0364 .80.9389 .%-159.2671

178.4592 3113.1754 .?i-247.6460

1133.8745 6

Standard t-valueError (b=0)4.7688 -4.434566E-01 -3.602812E-01 5.07

.26376

.3776481467E-01

..273395

.480136

-4.874.66

-4.464.49

Prob.Level0.04730.06910.0367

0.03970.04300.0460

0.04670.0463

3eq.R-Sqr

0.14030.4907

0.51060.51250.9286

0.94390.9949

SimpleR-Sqr

0.14030.3695

0.37290.36740.0362

0.02000.0089


Dependent Variable: %OFF EQP '. '.

Source


df Sums of Squares Mean Square(Sequential)

1 .26146897 .154171

F-Ratio Prob. Level

2 7.851048E-049 .1549561



.26146892.202443E-023.925524E-041.721735E-02

56.11 0.018

1.981294E-02.1617.122529

0.99490.9772

L-5



Dependent VariableIndependentVariableInterceptKVA MAXWGT42SQR WT42LOG WT42

%OFF EQPParameterEstimate-26.56543--271E-02.5143E-02-.74877886.621144

StndizedEstimate0

-236-6430

.0000

.1024

.0501

.7482

.6361

Standard t-valueError (b=0)5.705455. 1020E-02.8676E-03.13497851.325087

-4-25

-55

.66

.66

.93

.5S

.00

Prob.Level0.0.0.0.0.

00160288000400050011

Seq.R-Sqr

0.0.0.0.

1454203642318600

SimpleR-Sqr

0000

.1454

.1952

.2289

.2395

Analysis


of- Variance Report

Source


df- Sums of Squares(Sequential)

1 1.0553554 .24945588 4.060512E-0212 .2900609



Mean Square

1.0553556.236395E-025.07564E-032.417175E-02

7.124353E-02.2849231.2500448

0.86000.7900

F-Ratio

12.29

Prob. Level

0.002

Residual Plot

• Multiple Regress ion-Date/Time 04-16-1992 13:10:12Data Base Name A:WUC44Description Backup of WUC44 created 03-13-1992


Dependent Variable: %OFF EQPIndependentVariableInterceptDRY_WGTWETAREALN DRYWTSQR WING

ParameterEstimate3.061047.1178E-04-.127E-03-.4239174.1346839

StndizedEstimate0.00007.3057-8.7046-3.52604.4295

StandardError.6213115.3256E-05.3581E-04.0959754.3769E-01

t-value(b=0)

4.933.62

-3.56-4.423.57

Prob.Level0.00010.00200.00230.00030.0022

Seq.R-Sqr

0.11000.14600.33590.6115

SimpleR-Sqr

0.11000.12410.26550.1742




Constant 1 .6311348Model 4 .1681584Error 18 .1068569Total 22 .2750152

F-Ratio Prob. Level



.63113484.203959E-025.936492E-031.250069E-02

7.704864E-02.1656522.465123

0.61150.5251

7.08 0.001

L-7



Dependent Variable: %OFFEQPIndependent Parameter StndizedVariable Estimate EstimateInterceptLEN WING

.7614E-01 0.0000-.1S1E-02 -2.6037

Standard t-value Prob.Error (b=0) Level.0283886 2.68 0.0130.5151E-03 -3.52 0.0018

SQR WGT .1543E-02 2.5598 .4460E-03

Seq.R-Sqr

SimpleR-Sqr

0.0119 0.01193.46 0.0020 0.3406 0.0005


Dependent Variable: %OFFEQP


Constant 1 .3719467Model 2 4.866481E-02Error 24 9.420949E-02Total 26 .1428743



Mean Square

.3719467

.02433243.925395E-035.495166E-03

6.265298E-O2.1173704.5338057

0.34060.2857

F-Ratio Prob. Level

6.20 0.007

Lr8

Residual Plot



Dependent Variable: %OFF EQPIndependentVariableInterceptACTUATORWGT14LOG WG14SQR WT14

ParameterEstimate5.512466.2663E-02-.566E-03

StndizedEstimate0 . 00000.8745

-14.4189

StandardError1.372817.llllEr-02.1722E-03

t-value(b=0)

4.022.40-3.29

Prob.Level0.00130.03110.0054

Seq.R-Sqr

0.02930.1397

SimpleR-rSqr

0 .02930.1041

-1.193089 -13.1531..3157466.1055595 25.9373 .3051E-01

-3.78 0.0020 0.3424 0.23223.46 0.0038 0.6455 0.1545




Constant 1 .2719226Model 4 6.115096E-02Error 14 3.358546E-02Total 18 9.473642E-02

F-Ratio Prob. Level



.27192261.528774E-022.398961E-035.263134E-03

4.897919E-02.1196316.4094169

0.64550.5442

6.37 0.004

L-9

CLSOk

Multiple Reqression-11 :34:54Date/Time 04-16-1992

Data Base Name A:AVIONICSDescription Backup of AVIONICS created 03-27-1992

Multiple Regression Reoort

Dependent VariableIndependentVariableInterceptDIP SUBSWGT51/72SQR51/72LOG5172WGT/TSUB

%OFF EQPParameterEstimate7.166202.2090E-01-.128E-02.1773785-1.734067.6700E-02

StndizedEstimate0.1.

-28.35.-15.7.

000045990442200538262109

Standard t-valueError (b=0)1.777114.4766E-02.2910E-03.4246E-01.4300031.1521E-02

44-44-44

.03'

.39

.40

.18

.03

.40

Prob.Level000000

.0030

.0018

.0017

.0024

.0030

.0017

Seq.R-Sqr

00000

.1874

.2205

.2212

.2358

. 7578

SimpleR-Sqr

00000

..1874

.0064

.0000

.0091

.0131




Constant 1 1.782616Model 5 .1003Error 9 3.204889E-02.Total 14 .1323489

Root Mean Square ErrorMean of 'Dependent VariableCoefficient of Variation

R SauaredAd.justed R Squared

1.7826162.006001E-02-3.560988E-039.453496E-03

F-Ratio

5.63

Prob. Level

0.013

5.967401E-02.3447333.1731019

0.75780.6233

L-10

•Descript ive Stat is t ics-Date /TimeData 03.se NameDescription.

02-10-1992 i UC: \ .N 'ASA\WUC41Merge of WUC42

15:0"

and. WUC11 created 02-05-1992

Detail Report

Variable: %OFF EQPMean - AverageLower 95% c.i.limitUpper 95% c.i.limitAd.i sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Test(bl 1.01 Skew-ZD'Agostino-Pearson Omnibus

.09326.419662E-02.1222034.1184947.026557E-024.93725E-03.75392241.079831.1240250.19816

2.24 Pr 0.0249K;

No. observationsNo. missing valuesSum of frequenciesSum of observations

100-%tile75-%tile50-%tile25-%tile0-%tile

0 1 r _ _

1 11131 1

(Maximum)

(Median)

( Minimum)

1 4

.27

.13

.08

.03

.015

12 1

Std.error of meanT-value for mean=0T prob levelKurtosisReject if > 1.176(10%)Reject if > 0.159(10%)b2 3.15 Kurt-Z 0.74

Normality Test 5.690-%tile10-%tileRange75th-25th %tileC.L. Median<95%)

Plot / Box Plot2 1

035

3510252.331.405311E-026.6319820.0000.47104651.276(5%)0.174(5%)Pr 0.4604Pr 0.0615.2.026.2559.999999E-02. 11

1271

234567891011

.1772727

.2004546

.2236364

.2468182


Variable: %OFFBin Lower1 .015

3.818E-026.136E-028.454E-02.1077273.1309091.1540909

EQPUpper3.818E-026.136E-028.454E-02. 1077273.1309091.1540909.1772727.2004546.2236364.2468182.27

Count81533102011

Prcnt32.04.0

20.012.012.04.00.08.00.04.04.0

Total89141720212123232425

Prcnt32.036.056.068.080.084.084.092.092.096.0100.0

Histogram*********************

**

**

L-ll

Residual Plot

Multiple RegressionDate/Time 04-16-1992 12:59:43Data Base Name C:\NASA\WUC47BDescription Merge of WUC47 and WUC47 created 04-16-1992


Dependent Variable:IndependentVariableInterceptLEN WINGLN DRYWTLDWGTSQDWGT./LEN

%OFF EQPParameterEstimate Estimate Error23.85198 0.0000 6.959501-.902E-02 -10.1204-5.247019 -50.4282.3009554 62.2695-.212E-02 -2.7734

StandardError.959501.2212E-021.523853.8677E-01.S730E-03

value=0)3.43-4.08-3.443.47-2.42

Prob.Level0.00370.00100.00360.00340.0284

Seq.R-Sqr

0.17480.34740.60960..7196

SimpleR-Sqr

0.17480.05600.06370.0097




Constant 1 .2930621Model 4 .1118034Error 15 4.357554E-02Total 19 .155379

F-Ratio Prob. Level



.29306212.795085E-022.905036E-038.177839E-03

5.389838E-02.12105.4452572

0.71960.6448

9.62 0.000

L-12

Residual PlotMultiple Regression-- -——

Date/Time 04-16-1992 14:07:39Data Base Name C:\NASA\WUC49Description Merge of WUC24 and WUC13 created 02-12-1992


Dependent Variable: %OFF EQPIndependentVariableInterceptDRY WGTSQR WGTKVA MAX

ParameterEstimate.1988856.4938E-05-.205E-02.4877E-03

StndizedEstimate0.00002.0439-1.77430.3383

StandardError.114326-2131E-05. 1098E-02.4481E-03

t-value(b=0)

1.742.32-1.87L.09

Prob.Level0.09810.03180.07710.2900

Seq.R-Sqr

0.33040.40320.4382

SimpleR-Sqr

0.33040.26060.2504



Source


df Sums of Squares(Sequential)

1 .09365843 8.434577E-0219 .108127322 .1924731



Mean Square

.09365842.811526E-025.690911E-038.748776E-03-

7.543813E-02;.6.381305E-02..1.182174

0.43820.3495

F-Ratio Prob. Level

4.94 0.011

Resiaual •Multiple Regression

Date/Time 04-16-1992 14:11:10Data Base Name C:\NASA\WUC96Description Merge of WUC47 and WUC12 created 02-11-1992


Dependent VariableIndependentVariableInterceptLEN WINGWETAREAPERSONSSQR PERSQRWT49/

%OFF EQPParameterEstimate-5.46864. 1683579-.448E-02.3652105-4.152794.1779732

StndizedEstimate0.44.-59.56.-59.17'.'

000047558242949562249140

Standard t-valueError (b=0)1.728256.3631Er01.9387E-03.4935E-01.5515564.3293E-01

-34-47-75

.16

.64

.77

.40

.53

.40

Prob.Level000000

.0507

.0189

.0175

.0051

.0049-0124

Seq.R-Sqr

00000

.2583

.2815

.2901

.7208

.9740

SimpleR-Sqr

00000

.2583

.2633

.2636

.2901

.3109


Depenaent Variable: %OFF EQP

Source


df Sums of Squares Mean Square(Sequential)

1538

3.584711.76330672.038224E-02.7836889



3.584711.15266136.794081E-03-9.796111E-OZ:

8.242621E-02,.6311111.1306049

0.97400.9306

F-Ratio Prob. Level

22.47 0.014

L-14

Data Base Name C:\NASA\WUC91Description Backup of WUC49 created 02-13-1992


Dependent Variable: %OFF EQPIndependent Parameter Stndized StandardVariable Estimate Estimate ErrorIntercept 4.653976 0.0000 2.156753LN DRYWT -.4571863 -2.0304 .2379916SQR WGT .2421E-02 1.4973 .1709E-02

valuei=0)2.16

-1.921.42

Prob.Level0.04760.07390.1770

Seq.R-Sqr

0.31400.3950

SimpleR-Sqr

0.31400.2461




Constant 1 1.664096Model 2 .3243408Error 15 .4968562Total 17 .821197



Mean Square

1.664096.16217043.312375E-024.830571E-02

.1819993

.3040555

.5985725

0.39500.3143

F-Ratio Prob. Level

4.90 0.023

L-15

Descriptive StatisticsDate/Time 02-14-1992 14:38:09Data Ease Xame C:\NASA\WUC93Description Data base created, at lr: 14:42 en 02-13-1992

Detail Reoort

Variable: %OFF EQPMean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Test

0.44 Skew-Z

.2877375

. 1127736

.4627014

.3085063

.20993414.407232E-02.7296028.54452961.07360. 18167

0.73 Pr 0


D'Agostino-Pearson Omnibus100-%tile75-%tile50-%tile25-%tile0-%tile

O 1 R A -

1 1 1fY5

( Maximum)

(Median)

( Minimum)

:YYYYYYYYYY5

.644

. 44

.265

. 10075

.0464

1nnnrYYYYXj

4631 b2 1.98Normality Test

90-%tile10-%tileRange75th-25thC.L. Median

Line Plot / Box Plot1 1

8082.30197.422291E-023.8766670.0061-.74861942.421(5%)0.288(5%)

Kurt-Z0.7

tile

-0.41 Pr 0.6818Pr 0.7024.5625.0464.5976.33925

.0464, .644

1 1

Variable: %OFFBin Lower1 .04642 .13177143 .21714294 .30251435 .38788576 .47325727 .5586286

EQPUpper.1317714.2171429.3025143.3878857.4732572.5586286.644


Count Prcnt Total Prcnt Histogram3020111

37.50.0

25.00.012.512.512.5

3355678

37.37.62.62.75.87.

100.

5555050

**»

**

***

L-16

Descriptive Statistics-Date/Time 02-14-1992 15:16:51Data -2ase Name C:\NASA\WUC97Description Backup of -WUC91- created 02-14-1992

Detail Report

Variable: %OFF EQPMean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Testfbl 4.03 Skew-Z

1 .003704E-02-9.861112E-042.106019E-02.020-18922.786589E-027.765078E-042.7763064.268697192.59250.352385.70 Pr 0.0000

Mo. observationsNo. missing valuesSum of frequenciesSum of observationsStcUerror of meanT-value for mean=0T prob levelKurtosisReject if > 1.164(10%)Reject if > 0.153(10%)b2 19.00 Kurt-Z

D'Agostino-Pearson Omnibus K/ Normality Test 55.8100-%tile75-%tile50-%tile25-%tile0-%tile

0D422 11 1

(Maximum) .14 90-%tile.0048 10-%tile

(Median) .0013 Range0 75th-25th %tile

(Minimum) 0 C.L. Median(95%)Line Plot / Box Plot

36927.2715.362793E-031.8716060.072619.667711.254(5%)0.168(5%)

4.83 Pr 0.0000Pr 0.0000.0330.14.0048

0, .0047

1. 14

1


Variable: %OFFBin1234567891011

Lower01.272E-022.545E-023.818E-025.090E-026.363E-027.636E-028.909E-02. 1018182. 1145455. 1272727

EQPUpper1.272E-022.545E-023.818E-025.090E-026.363E-027.636E-028.909E-02. 1018182. 1145455.1272727.14

Count231110000001

Prcnt85.23.73.73.70.00.00.00.00.00.03.7

Total2324252626262626262627

Prcnt85.288.992.696.396,96,96,96,96,96,

,3,33333

Histogram***********************

**

100.0

APPENDIX M

Removal Rate Data & Regression

REMOVAL RATE

ANALYSIS SUMMARY

! WUC11121314

1234

24 541 6 .

1 42 7

IMEAN I C-5A0.194 0.1160.319 I 0.3980.4420.30403210385

02200.1310.1870.168

0.344 I 02301 44 8 0.716

C-130E0.168022503140247030603130305

C-141B0.177036203440263026903780332

0.767 0.530 0.69645 i 9 ! 0.368 I 0.234 0.257 0.30846 10 0572 ! 0.17847 i 1149 | 125152616263646566

1314151617181920

69 i 21

0.415 I 02370274 I 0.1500.5070.4580299024503680.4560.47203960.455

i 71* i 22: 1 0.44272 ; 23 0.475

0.45303750317027502990.518038203090.0000.3950.455

! 91 - i 24 0.461 I 0.179; 97 I 25 0.555 I 0.192

0.199037503130.4140.4830307032703060.4430.551055702950.411

0.1640.31303890.4450.5140.5390388027503210.44503220.4190.424

0.542 0.4270.1890.707

03920.128

F-15D0207

F-111A0.309

0235 0.0000.663 i 0.6200390 0.4290.521 0.0000345 0.6360.381 0.5390.694 0.8720.593 : 0.515-0.366 i 0.3890.514 0.53503680.5100.3450.0000.0000.4050.0000.3500.0000.000

0.1380.7260.70803300.0000.54603070.4220.0000.652

0.426 0.4330.000 0.0000.658 0.0000.911 0.421

T-38A0.18503770.49003630.0000.4680.2750.7340.3030.3590.51702880.49403220.0000235037502920.6800.0000.0000.5600.0000.8870.968

M-l

REMOVAL RATE

wuc

1112

13 .

, 14

24-

41

42

44

45

46

47

49

51

52-

61

62

63

64

65

66 -

69

71

72

91

97

MEAN

0.194

0319

0442

0304

0321

0385

0344

0.716

0368

0272

0.415

0274

0.507

0458

0299

0245

0366

0456

0.472

0396

0455

0442

0475

0.461

0355

MEDIAN

0.181

0362

0.417

0313

-02875

0.3615

0.3185

0.715

03055

0279

0.4445

03005

04735

0429

0317

0275

0.3405

0.507

0.4335

0322

0419

0425

0455

0392

0364

STDDEV

6.407E-2

.0826818

.1778206

.1107797

.1424603

.1573603

.1084576

.1120169

.1485499

.101439

.1231341

.10/3/73

.1127367

.1445094

.1925806

.1484907

.1003549

9.713E-2

.1230586

.1395815

.1812522

5.959E-2

5.997E-2

.3076337

.3612372

VARIANCE

4.105E-3

6.836E-3

3J62E-2

1227E-2

2J3E-2

2476E-2

1.176E-2

1.255E-2

2207E-2

1.029E-2

1.S66E-2

1.153E-2

1271E-2

2JBBE-2

3.7096-2

.02205-

.01007

9434E-3

1.514E-2.

1.948E-2

328SE-2-

3J51E-3

3.596E-3

9464E-2

.13049

VAR/MEAN II COEFF VARRATIO 9

2.119E-2

2.14E-2

7.1566E-2

4.0391E-2

63Z7E-2

6.4373E-2

3.4228E-2

1.7537E-2

5.991E-2

3.7784E-2

3.77163E-2

42029E-2

2.506BE-2

4.56126E-2

0.1242

8.999BE-2

2.73919E-2

iOB78E-2

32106E-2

4.91995E-2

7.215E-2

8.04246E-3

7.57649E-3

02062895

023533

03308

025887

0.40246

03646

0.44415

0.40908

0.31559

0.1566

0.4033

037248

03014

039141

022236

0315838

0.64495

0.60608

027295

02129

02609.

0.35248

0398

0.13497

0.12634

0.66732

0.66147

M-2

REMOVAL RATE ANALYSIS - WUC 23

REMOVALS MISSIONSACCOMPLISHED

PERCENT

F-4E

F-15C

F-16C

C-5A

C-130E

KC-135

1

8

16

6

12

1

,988

,653

,978

,845

,205

,787

5

16

39

43

36

10

,921

,891

,635

,508

,836

,354

0.3358

0.5123

0.4284

0.1573

0.3313

0.1726

TOTALS 48,456 153,145 0.3164

M-3


Sum of Functions Regression-06-04-1992 15:34:59C:\nasa\WUCllBackup of NASAMSTR created 12-18-1991

Y: REMRAT11Model: A+B*(X)


X: WGT BODY

Term Coefficient EstimateA .1934133385777032B -6.308858923946157D-07

Source df Sum-SqrModel 1 3.888923E-03Error 3 6.722772E-04Total 4 .0045612

Std. Error8.649185E-031.514432E-07

T-Value Prob(|t!>T)22.4 0.0002-4.2 0.0252

Mean Square3.888923E-032.240924E-04.0011403

SQR(M.S.)6.236123E-021.496972E-023.376833E-02

F-Ratio17.4

R-Squared0.85260957

Prob(f>F)0.0252

°l. I snotionsData Base Name C:\nasa\WUCllDescription Backup of NASAMSTR created 12-18-1991


Y: REMRAT13 X: LEN_WINGModel: A+B*(SQR(X))


Source df Sum-SqrModel 1 .1111809Error 4 4.691989E-02Total 5 .1581008

Std. Error.14404729.624203E-03

T-Value Prob(|t|>T)6.0 0.0039-3.1 0.0370

Mean Square.11118091.172997E-023.162017E-02

SQR(M.S..3334381.108305.1778206

F-Ratio9.5

R-Squared0.70322806

Prob(f>F)0.0370

M-4

Sum of Functions Regression-Date /Time 06-04-1992 15:17:11Data Base Name C:\nasa\WUCllDescription Backup of NASAMSTR created 12-18-1991

Y: REHEAT14Model: A+B*(X)


X: LEN_WING


Source df Sum-SqrModel 1 5.185439E-02Error 4 1.003094E-02Total 5 6.188534E-02

Std. Error3.872833E-021.468313E-04

T-Value Prob(!t!>T)11.7 0.0003-4.5 0.0104

Mean Square5.185439E-022.507735E-031.237707E-02

SQRM.S.).22771565.007729E-02.1112523

F-Ratio20.7

R-Squared0.8379108!

Prob(f>F)0.0104

Sum of Functions Regression-Date/Time 06-04-1992 15:23:55Data Base Name C:\nasa\WUCllDescription Backup of. NASAMSTR created 12-18-1991


Y: REMRAT24 X: DRY_WGTModel: A+B*(SQR(X))



Std. Error

2.547987E-04

T-Value Prob(!t!>T)6.1 0.0261-2.9 0.0984

Mean Square4.949569E-025.694529E-032.029492E-02

SQR(M.S..2224763.0754621.1424602

F-Ratio8.7

R-Squared0.81294072

Prob(f>F)0.0984

M-5

Sum of Functions RegressionDate/Time 04-27-1992 14:28:07Data Base Name C:\NASA\WUC23Description Merge of WUC11 and WUC51 created O4-27-1992


Y: REM RATE X: ENG WGTModel: A+B*(SQR(X))

Term Coefficient EstimateA .62110674490679298 -2.48722869S927137D-03


Std. Error7.217704E-025.62173E-04

T-Value Prob( j t',>T)8.6 0.0010-4.4 0.0115

Mean Square7.983025E-024.07827E-031.922867E-02

SQR(M.S.).28254256.386133E-02.1386675

F-Ratio19.6

R-Squared0.83032542

Prob(f>F)0.0115

Sum of Functions RegressionDate/Time 06-04-1992 16:03:23Data Base Name C:\nasa\WUC41Description Merge of WUC42 and, WUC11 created 02-05-1992

Estimation Summary*Report


X: BTU COOL

Term Coefficient EstimateA .2026788301027799B 5.880527005587363D-04

Source df Sum-SqrModel 1 .0100263Error 2 .0131717Total 3 .023198

Std. Error -9.232288E-024.765976E-04

T-Value Prob(!t!>T)2.2 0.15931.2 0.3426

Mean Square.01002636.585851E-037.732667E-03

SQR(M.S.).10013148;:il5325E-028V793558E-02

F-Ratio1.5

R-Squared0.43220529

Prob(f>F)0.3426

M-6

Sum of Functions RegressionDate/Time 06-04-1992 16:06:33Data Base Name C:\nasa\WUC41Description Merge of WUC42 and WUC11 created 02-05-1992



X: ECSWT


Source df Sum-SqrModel 1 6.933792E-02Error 4 5.447341E-02Total 5. .1238113

Std. Error7.991302E-023.950266E-05

T-Value Prob(!t!>T)6.6 0.0027-2.3 0.0870

Mean Square6.933792E-021.361835E-022.476227E-02

SQRfM.S.).263321.1166977.1573603

F-Ratio5.1

R-Squared0.56002885

Prob(f>F)0.0870

Sum of Functions RegressionDate/Time O5-O3-1992 11:11:02Data Base Name C:\NCSS\REMAVDescription Data base created at 10:48:48 on O5-O3-1992


Y: REM42 X: LEN+WINGModel: A+B*(X)+C*(LOG(X))Filter: REM42Term Coefficient EstimateA -.3853306486485544B -1.0061057835372460-03C .1771478107273882

Std. Error.55208916.318003E-04.1326407

T-Value Prob(|t{>T)-O.7 0.5574-1.6 0.25231.3 0.3134

R-Squared0.6231614

Source df Sum-SqrModel 2 8.119295E-O3Error 2 4.909905E-O3Total 4 .0130292

Mean Square4.059648E-032.454952E-03.0032573

SQR(M.S.)6.371536E-024.954748E-025.707276E-02

F-Ratio1.7

Prob(f>F0.3768

M-7

Sum of Functions RegressionDate/Time 05-O3-1992 11:12:43Data Base Name C:\NCSS\REMAVDescription Data base created at 10:48:48 on O5-O3-1992


Y: REM44 X: LEN+WINGModel: A+B*(X)+C*(LOG(X))Filter: REM42Term Coefficient EstimateA 2.365083753788492B 2.014026317131226D-03C -- 4115210829205226

Source df Sum-SqrModel 2 2.494925E-02Error 2 8.399552E-O3Total 4 .0333488

Std. Error.72210558.263639E-O4.1734875

T-Value Prob(|t|>T)3.3 0.08192.4 0:1351-2.4 0.1411

Mean Square1.247462E-O24.199776E-03.0083372

SQR(M.S.).11168996.48O568E-029.130827E-02

F-Ratio

R-Squared0.74813O3:

Prob(f>F0.2519

Sum of Functions RegressionDate/Time 06-04-1992 16:16:45Data Base Name C:\nasa\WUC47Description Merge, of WUC45 and WUC42 created 01-03-1992


Y: REMRAT47 X.: DRY_WOTModel: A+B*(SQR(X))

Term v Coefficient EstimateA .6026214260605686B -6.758594018545932D-04


Std. Error4.229213E-021.326294E-04

T-Value Prob(!t!>T)14.2 0.0001-5.1 0.0070

Mean Square6.784252E-022.612577E-031.565857E-02

SQR(M.S.).2604665.111338E-02.1251342

F-Ratio26.0

R-Squared0.86652279

Prob(f>F)0.0070

M-8

Sum of Functions RegressionB'ate/Time 06-04-1992 16:23:15Data Base Name C:\nasa\AVIONICSDescription Merge of WUC71 and WUC61 created 03-25-1992


Y: REMRAT91 X: LEN_WINGModel: A+B*(LOG(X))

Term Coefficient EstimateA 2.348927831791845B -.3585188334562223

Source df Sum-SqrModel 1 .3137073Error 3 6.484672E-02Total 4 .378554

Std. Error.49991449.410941E-02

T-Value Prob(!t!>T)4.7 0.0182-3.8 0.0318

Mean Square.31370732.161557E-02.0946385

SQR(M.S..5600958.1470224.3076337

R-Squared0.82869887

F-Ratio14.5

Prob(f>F)0.0318

Sum of Functions RegressionDate/Time 06-04-1992 16:31:52Data Base Name C:\nasa\WUC42Description Merge of WUC41 and WUC13 created 12-27-1991


Y: REMRAT97 X: WETAREAModel: A+B*(LOG(X))

Term Coefficient EstimateA 2.532197071458078B -.2283679845742844


df Sum-Sqr1 .43941214 .21304945 .6524615

Std. Error.69496387.950773E-02

T-Value Prob(!t|>T)3.6 0.0219-2.9 0.0454

Mean Square.43941215.326235E-02.1304923

SQR(M.S..6628817.2307864.3612372

F-Ratio8.2

R-Squared0.67346829

Prob(f>F)0.0454

M-9

Sum of Functions Regression •- '•<-Date/Time 05-O3-1992 11:00:51Data Base Name C:\NCSS\REMAVDescription Data base created at 10:48:48 on O5-03-1992


Y: REMAV X: DRY WGTModel: A+B*(X)+C*(SQR(X))Filter: REMAVTerm Coefficient Estimate Std. Error T-Value Prob(|t|>T) R-SquaredA .3973471291561014 .0219378 18.1 O.OO30 0.75776649B -4.265886102584761D-07 2.39473E-07 -1.8 0:2168C 2-163532620527512D-04 1.603619E-O4 1.3 0.3097

Source df Sum-Sqr Mean Square SQR(M.S.) F-Ratio Prob(f>F)Model 2 1.121494E-03 5.607472E-04 .02368O1 3~1 0.2422Error 2 3.585056E-O4 1.792528E-O4 1.338853E-O2Total 4 .00148 .00037 1.923538E-02

M-10

APPENDIX N

Abort Rate Data & Regression

ABORT RATES - ABORTS PER MAINTENANCE ACTION

F-4D-A F-4D-F F-4D B-52G-A B-52G-F B-62G B-52H-A B-52H-F

WUC11WUC12WUC13WUC14WUC41WUC42WUC44WUC45WUC47WUC51WUC52WUC61WUC62WUC63WUC64WUC71WUC72

1611172441662311012

13

60

7751,154758405207217218281102388144

2233

97154

0.020650.009530.022430.059260.019320.073730.027520.081850.009800.025770.08333•0.000000.05579

0.006180.00000

392248137

16-6184224-

01-400

3052520362

211

111

222

,437,850,000,649,284,620,248,306,719,280,681

22,428,024,251712

00000000000

00000

.00128

.00376

.00192

.00063

.00213

.00242

.00267

.00084

.00233

.00195

.00238

.00000

.00041

.00198

.00000

.00000

2341210783.2..0-23o,04-2;0.0

2031513261

10191

111

,234,933,326,144,734,023,507,481,324,941,054

3,787,991,720645

KC-10A-A KC-10A-F KC-10 C-130A-A C-130A-F C-130B-A C-130B-F C-130B C-130E-A

WUC11WUC12WUC13WUC14WUC41WUC42WUC44WUC45WUC47WUC51WUC52WUC61WUC62WUC63WUC64WUC71WUC72

5 -0191035 -7

17-363

0-0122

1,695 0.002952,041 0.000006,016 0.003162,056 0.004861,280 0.002341,011 0.004953,105 0.002251,707 0.00996884 0.00339956 0.00628

1,990 0.00151• •

196 0.00000473 0.00000

1,231 0.000812,509 0.00080529 0.00378

71176101403-0,11

00332

1,32916974642228237913234867262228

4330105226477

2755029305862821212

321025

11,395 0.002372,663 0.001885,087 0.009833,394 0.008541,718 0.017461,397 0.04152580 0.01034

2,380 0.01176382 0.00524

2,063 0.005821,802 0.00666

421 0.00713255 0.00784105 0.09524

1,130 0.001772,244 0.00223

77281546286101106094437

83241080

legend:

A - aborts

F - maintenance actions

N-l


C-130E-F C-130E C-130H-A C-130H-F C-130H F-4D-A F-4D-F F-4D F-4G-A F-4G-F

40,51512,25018,71112,00410,4456,1884,77710,7632,2159,2897,416

2,3992,1333,6116,63019,270

0.001900.002290.008230.005160.008230.016320.002090.005570.004060.004740.00499

0.003330.001410.006650.001510.00415

40138551418464561229

4262

25

14,5046,1679,3506,7344,0083,0551,8844,9901,2473,0163, .715

1,9381,3032,0322,6477,244

0.002760.002110.009090.007570.010230.027500.003180.009020.004810.003980.00781

0.002060.001530.002950.000760.00345

947819636356206484311850134

01060961

77542113

31

2

10

,841,917,115,727,127,164,176,570732,033,449

1,571

0,965787

00000000000

00

00

.01199

.00985

.03832

.07679

.02633

.17698

.04082

.12073

.02459

.01649

.09248

.00000

.04123

.00876

.00127

40691201422310031233144161

481

242

2,5633,3961,2391,776956492456

1,309292

1,514645

1,7300

5,681485

F-16A-A F-16A-F F-16A F-16C-A F-16C-F F-15A-A F-15A-F F-15A F-15B-A

154125737

1,200191884108375281730

2613430120

15,8449,85623,83117,6545,71911,6545, '1684,3001,9075,297

5

2 ,'3685,557896

2,3014

0.009720.012680.030930.067970.033400.075850.020900.087210.014680.032660.00000

0.010980.024110.033480.005220.00000

162153

1,0601,05148691914938651

2550

1417842221

11,8417,75426,31012,9307; 57210,5116,1433,1462,7126,996

9

2,0999,895891

3,56818

0.0.0.0.0.0.0.0.0.0.0.

0.0.0.0.0.

0136801973040290812806418087430242612270018810364500000

0066701799047140061705556

20352243236215289955606

196158

0510530

13,0884,1538,1376,6774,2712,6963,2364,293924

7,1082,239

26,489

86,451

0.0.0.0.0.0.0.0.0.0.0.

'0.0.0.0.

0155101252029860353505034107200293613044006490275707057

.•tt00000007860000000822

22316279414219

1153

3519

1.30110

N-2


F-15B-F F-15C-A F-15C-F F-15C F-15D-A F-15D-F F-15E-A F-15E-F F-111E-A

2,8101,3461,3311,271761361803641253

1,760419

1,516

1,359

142742702742102799652115

336150

40

63

15,3254,2387,2837,5186,3433,2514,9484,9501,4247,6612,594

8,506

7,636

00000000000

0

0

.00927

.01746

.03707

.03645

.03311

.08582

.01940

.10525

.01053

.04386

.05783

.00470

.00825

211656393136216723219

011

7

21111

1

1

1

,773,017,363,174,087558750851288,674385

,478

,217

322090115111641.2643

69162

21

.. 70

21211

22

2

1

,397,257,355,528,622795976421565,305,053

,072

,303185

29760147595915742

6298008100


F-111E-F F-111E KC-135A-A KC-135A-F KC-135A KC-135R-A KC-135R-F

5,5571,173752

3,4682,6411,3451,1361,822911

2,7912,2443089

1,120608411

0.005220.005970.079790.042390.022340.043870.013200.040610.002200.022210.043670.000000.000000.007140.016450.00000

415

413265713254 i374012r017

30,0654,65722,16021,4134,2388,4643,84911,3612,32617,0866,911911207

2,0132,3261,30110,650

0.001360.001070.001850.001490.001420.006730.003380.002200.001720.002170.000580.000000.004830.000990.003010.000000.00160

347"303315131493

51812431

15

22,6015,78033,01224,6944,8594,4383,8019,4902,54615,2635,606707405

1,8122,0681,15310,140

N-3

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N-6

Sum of Functions RegressionDate/Time O3-21-1992 13:18:31Data Base Name C:\NCSS\FILES\ABORTDescription Data base created at 12:22:06 on 03-21-1992


Y: AWUC11 X: DRY WTModel: A+B*(X)+C*(SQR(X))

Term Coefficient EstimateA 3.1212954054979310-02B 1.956O10750103666D-07C -1.5455S3903781419D-04

Source df Sum-SqrModel 2. 3.120985E-04Error 10 1.737278E-O4T Ota1 124.858263E-04

Std. Error7.319232E-039.48912E-O85.629948E-05

T-Value Prob(|t|>T)4.3 O.O0172.1 O.O662-2.7 0.0206

Mean Square1.560493E-O41.737278E-O54.O48552E-O5

SQR(M.S-)1.249197E-O24.168066E-O36.362824E-03

F-Ratio9.0

R-Squareo0.6424076

Prob(f>FO.OO58

Sum of Functions RegressionDate/Time O3-21-1992 13:23:44Data Base Name C:\NCSS\FILES\ABORTDescription Data base created at 12:22:06 on 03-21-1992


Y: AWUC12 X: DRY WTModel: A+B*(X)+C*(SQR(X))Filter: AWUC12Term Coefficient EstimateA .0423204OO2592303B 3.877491472986547D-07C -2.518829377924677D-O4

Source df Sum-SqrModel 2 3.7558O5E-04E rro r 9 7.379731E-O5Total 11 4.493778E-04

Std. Error7.036862E-031.259424E-O76.22464E-05

T-Value Prob(!tJ>T)6.0 O.OOO2311- 0.0132'-4.0 O.O029

Mean Square1.877903E-048.199701E-O64.085253E-05

SQR(M.S.)1.370366E-022.863512E-036.391598E-03

F-Ratio22.9

R-Squared0.8357789

Prob(f>FO.0003

N-7

Sum of Functions RegressionDate/Time 03-21-1992 13:31:13Data Base Name C:\NCSS\FILES\ABORTDescription Data base created at 12:22:06 on 03-21-1992


Y: AWUC13 X: LEN+WINGModel: A+B*(X)+C*(LOG(X))+D*(SQR(X))

Term Coefficient EstimateA -2.432076284094683B 5.911218731680826D-03C 1.145696021259627D -.3392548733540112


Std. Error1.3856853.564697E-03.6458694.1946242

Mean Square1.243831E-032.43479E-044.93567E-04

T-Value Prob(|t|>T)-1.8 0.11311.7 0.13161.8 071098-1.7 0.1153

SQR(M.S.)3.526799E-021.560381E-022.221637E-02

R-Squarec0.6300212

F-Ratio5.1

Prob(f>F0.0246

Sum of Functions RegressionDate/Time 05-O6-1992 15:15:57Data Base Name C:\NASA\WUC23Description Merge of WUC11 and WUC51 created 04-27-1992


Y: ABTRATE X:Model: A+B*(X)

LEN WING

Term Coefficient EstimateA 4.816425031610672D-02B -1.268146378348553D-04

Source df Sum-SqrModel 1 1.050443E-O3Error 2 6.902844E-O4Total 3 1.740727E-03

Std. Error1.836541E-027.~269126E-O5

T-Value Prob(! t |>T)2.6 0.1198

-1.7- 0.2232

Mean Square1.050443E-033.451422E-O45.802425E-04

SQR(M.S.)3.241054E-02.0185782.408822E-02

F-Ratio3;0

R-Squared0.60345060

Prob(f>F)0.2232

N-8

Sum of Functions Regression'Oate'/Time 03-22-1992 10:27:44Data Base Name C:\NCSS\FILES\ABORTDescription Data base created at 12:22:06 on 03-21-1992


Y: AWBS10 X: LN DRYModel: A+B*(X)+C*(X*X)+D*(X~3)

Term Coefficient EstimateA -39.95984549060828B 11.092141439OO919C -1.017822607855107D 3.0907587294699490-02

Source df Sum-SqrModel 3 1.531093E-O2Error 9 6.74579E-O3Total 12 2.205672E-02

Std. Error17.157764.735571.43417151.322297E-02

T-Value Prob(|t|>T)-2.3 0.04482.3 0.0439

-2.3 O.O4372.3 0.0442

Mean Square5.103644E-037;495322E-041.83806E-03

SQRCM-S.).07143982.737758E-02.0428726

R-Squared0.6941617

F-Ratio6.8

prob(f>FO.O1O8


Sum of Functions Regression ------03-21-1992 13:44:33C:\NCSS\FILES\ABORTData base created at 12:22:06 on 03-21-1992


Y: AWUC45 X: LN DRYModel: A+B*(1/SQR(X))+C*(X)+D*(X*X)+B*(X"3)Filter: AWUC45Term Coefficient Estimate Std. ErrorA 5000.25349948818B -7578.183026428647C -453.6120878012779D 24.60056275019885E. -.5276227079707911

Source df Sum-SqrModel 4 .0281919Error 7 1.759745E-03Total 11 2.995164E-02

2535.2523806.867234.465712.97183.2839331

Mean Square7.047974E-032.513922E-042.722876E-03

T-Value Prob({t J >T)2.0 0.0892

-2.0 0.0868-1.9 0;09431.9 0.0997

-1.9 0.1055

SQR(M.S.)8.395221E-021.585535E-025.218119E-02

R-Squared0.94124711

F-Ratio28.0

Prob(f>F)0.0002

N-9

Sum of Functions RegressionDate/Time 03-21-1992 13:37:30Data Base Name C:\NCSS\FILES\ABORTDescription Data base created at 12:22:06 on 03-21-1992


Y: AWUC14 X: LEN+WINGModel: A+B*(LOG(X))+C*(SQR(X))

Term Coefficient EstimateA .7119536461928977B -.1881388279494333C 2.098824012629048D-02

Source df Sum-SqrModel 2: 1.015222E-02Error 10 9.66868E-04Total 12 1.111908E-02

Std. Error.18466385.986314E-029.148882E-03

T-Value Prob(!t|>T)3.9 0.0032

-3.1 0.01052 3 0.0447

Mean Square5.076109E-039.66868E-059.265904E-04

SQR(M.S.)7.124681E-029.832945E-033.043995E-02

F-Ratio52.5

R-Squared0.9130442:

Prob(f>P0.0000

Sum of Functions RegressionDate/Time 03-22-1992 10:24:15Data Base Name C:\NCSS\FILES\ABORTDescription Data base created at 12:22:06 on O3-21-1992


Y: AWUCAV X: DRY WTModel: A+B*(X)+C*(SQR(X))

Term Coefficient EstimateA 5.027494869365O81D-02B 2.605132300912917D-07C -2.2881974939125510-04

Source df- Sum-SqrModel 2 9.871627E-O4Error 10 2.069475E-O4Total 12 1.19411E-03.

Std. Error7 . 988421Err031.03567E-076.144687E-05

T-Vaiue Prob(!t|>T)6.3 O.O0012.5 0.0306-3.7 O.O039

Mean Square4.935814E-042.O69475E-O59.95O918E-05

SQR(M.S.)2.221669E-024.549148E-O39.975429E-O3

F-Ratio23.9

R-Squared0.8266931L

Prob(f>F0.0002

N-10

Sum of Functions Regression* Date/Time 03-22-1992 10:45:38Data Base Name C:\NCSS\FILES\ABORTDescription Data base created at 12:22:06 oh 03-21-1992


Y: AWBS14 X: DRY WTModel: A+B*(X )+C*(SQR(X))

Term Coefficient Estimate Std. Error T-Value Prob(Jt!>T) R-SquaredA 8.2198986530845460-02 1.398155E-02 5.9 O.OO02 O.78927531B 5.0072044718141130-07 1.812657E-07 2.8 0.02OOC -4.0612509035796350-04 1.07546E-04 -3.8 O.O036

Source df Sum-Sqr Mean Square SQR(M.S.) F-Ratio prob(f>FModel 2 2.374444E-03 1.187222E-O3 3.4456O9E-O2 18.7 O.0004Error 10 6.339409E-O4 6.3394O9E-05 7.962041E-O3Total 12 3.008385E-03 2.506987E-O4 1.583347E-02

N-ll

APPENDIX O

Crew Size Data & Regression

Descriptive StatisticsDate/Time 05-O3-1992 08:56:17Data Base Name C:\NCSS\CREWDescription Data base created at 07:48:02 on O5-O3-1992

Detail Report

Variable: CREW1Mean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Test/bl 0.81 Skew-Z

2.0511111.8237042.278518.7O10889.2960348.763611E-02.1443286.9848181.1876070.185771.39 Pr 0.1653

No. observationsNo. missing valuesSum of frequenciesSum of observationsStd.error of meanT-value for mean=OT prob levelKurtosisReject if > 1.482(10%)Reject if > 0.252(10%)b2 3.11 Kurt-Z

D'Agostino-Pearson Omnibus KJ Normality Test-100-%tile (Maximum) 2.6675-%tile 2.1250-%tile (Median) 2.0325-%tile 1.90-%tile (Minimum) 1.66

1.661 1 2 - .

9O-%tile10-%tileRange75th-25th %tileC.L. Median(95%)

Line Plot / Box Plot ------i : i l 1

9o918.469.867799E-0220.7859O.OOOO1.3483142.151(5%)0.275(5%)

1.05 Pr 0.29483'.0 Pr 0.2207

2.481.661.2199999

1.8, 2.3•2.66

1

Detail Report

Variable: CREW2Mean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSKewnessNormality Test ValueK.S. Normality Test/bl 0.48 Skew-Z

2.4355562.1891362.681975.8232222.3207846.1029028.131709.58114421.0594250.1620O0 83 Pr 0.4077

No. observationsNo. missing valuesSum of frequenciesSum of observationsStd.error of meanT-value for mean=OT prob levelKurtosisReject if > 1.482(10%)Reject if > 0.252(10%)b2 2.29 Kurt-Z

D'Agostino-Pearson Omnibus K} Normality Test 0.7100-%tile (Maximum)75-%tile50-%tile (Median)25-%tile0-%tile (Minimum)

2-1

2.99 90-%tile2.53 • • * • - 10-%tile2.37 Range2.26 75th-25th %tile2 C.L. Median(95%)

Line Plot / Box PlotI" 2'- 1 1CXXXXXXXXmXXXXaXXXXXXX J

9O9"21.92.106928222.77748O.OOOO-.2131622.151(5%)0.275(5%)

0.02 Pr 0.9819Pr 0;70962.92

:' ' 2 :.99.27 •"

11, 2.85-2.99

1

0-1

Descriptive StatisticsDate/Time 05-03-1992 08:56:18Data Base Name C:\NCSS\CREWDescription Data base created at 07:48:02 on 05-03-1992

Detail Report

Variable: CREW4Mean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Test

-0.22 Skew-Z

2.1811111.9442352.417987.7606889.30836049.508611E-02.1413776-.26932981.2448260.17682

-O.39 Pr 0.6998

No. observationsNo. missing valuesSum of frequenciesSum of observationsStd.error of meanT-value for mean=OT prob levelKurtosisReject if > 1.482(10%)Reject if > 0.252(10%)b2 3.49 Kurt-Z.

D'Agostino-Pearson Omnibus KJ Normality Test 2.1100-%tile (Maximum) 2.7375-%tile 2.2650-%tile (Median) 2.2125-%tile 2.040-%tile (Minimum) 1.58

I CO - ___ .HIT Ull 1_

• ,30—"——•————•—i

90-%tile10-%tileRange75th-25th %tileC.L. Median(95%)

-Line Plot / Box Plot11 1_2 1,CXXXXXXXXXaXmXX]

Detail Report

90919.63.102786821.219760.00002.075O352.151(5%)0.275(5%)

1.41 Pr 0.1580Pr 0.34272.561.581.15.22 .

2.02, 2.39-2.7:

Variable: CREW567Mean - AverageLower 95% c.i.1imitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Test#>1 0.20 Skew-ZD'Agostino-Pearson Omnibus

2.422.282.212.011.98

2.1788892.0452032.312574.2422889.174O2913.O28611E-027.987055E-02.24651881.0710840.16743

No. observationsNo. missing valuesSum of frequenciesSum of observationsStd.error of meanT-value for mean=OT prob levelKurtosisReject if > 1.482(10%)Reject if > 0.252(10%)b2. 1.66 Kurt-Z

1.40.35 Pr 0.7241

7 Normality Test100-%tile (Maximum) 2.42 90-%tile75-%tile 2.28 10-%tile5O-%tile (Median) 2.21 Range25-%tile 2.01 75th-25th %tile0-%tile (Minimum) 1.98 C.L. Median(95%)

1.98 Line Plot / Box Plot21 1 2. 1.

CXXXXXXXXXXXXXXXXXXXXXXXXXXXXXaXXXXXmXXXXXXXXXXXD -

9O :-.=.,919.61,5.80O968E-0237.560780.0000-1.4037312.151(5%)0.2.75(5%)

-1.14 Pr 0.2528Pr O.48862.42-1.98 ..44OOOO1.27

1.98, 2.42

0-2

-—•* Descriptive StatisticsDate/Time 05-O3-1992 08:56:18Data Base Name C:\NCSS\CREWDescription Data base created at 07:48:02 on 05-03-1992

Detail Report

Variable: CREW9Mean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Test

1-22 Skew-Z

2.1411111.8876862.394536.87O6889.3299032.1088361.15408041.4763571.9679540.242892.04 Pr 0.0415

No. observationsNo. missing valuesSum of frequenciesSum of observationsStd.error of meanT-value for mean-OT prob levelKurtosisReject if > 1.482(10%)Reject if > 0.252(10%)b2 3.74 Kurt-Z

D'Agostino-Pearson Omnibus K.7 Normality Test 6.8100-%tile (Maximum) 2.87 90-%tile75-%tile 2.17 10-%tile50-%tile (Median) 2.O3 Range25-%tile 2 75th-25th ttile0-%tile (Minimum) 1.76 C.L. Median(95%)

1.76 Line Plot / Box Plot1 1 111 11 1

CXmXXXXXXXaX]

9o919.27.109967719.47036O.OOOO2.5475032.151(5%)0.275(5%)

1.62 Pr 0.1048Pr 0.03362.6451.761.11.1700001

88, 2.42-2.87

1

0-3

Sum of Functions RegressionDate/Time 05-03-1992 08:23:49Data Base Name C:\NCSS\CREWDescription Data base created at 07:48:02 on 05-03-1992


Y: CREW1 X: WET AREAModel: A+B*(X)+C*(SQR(X))Filter: CREW1Term Coefficient EstimateA 1.500658209569604B -3.198838553665343D-05C 9.172174012957018D-03


df; Sum-Sqr2 .15434995 .12965017" .284

Std. Error.24366762.614986E-055.589843E-03

T-Value Prob(!t|>T)6.2 0.0016

-1.2 0.27571.6 0.1617

Mean Square7.717495E-022.593002E-024.057143E-02

SQR(M.S.).2778038.161028.2014235

F-Ratio3.0

R-Squared0.5434855

Prob(f>F0.1408

ActualRow X

1 17032 .3 19894 26435 13856 88997 109548 153509 33712

ActualY.,1.66

2.031.92.121.92.32.09

Residual Analysis

Predicted Lower95% Upper95%Y Value Value Residual1.824694 1.359004 2.290384 -.164694

1.8460961.8876551.7977022.0812462.110232.1460242.106353

1.3875031.4379041.3205821.6088781.6324211.6664361.525632

2.3046892.3374062.2748222.5536142.5880382.6256122.687073

-.461E-01.1423445.1022978.3875E-01-.2102297.1539759-.164E-01

O-4

Sum of Functions Regression-Date/Time 05-03-1992 08:32:04Data Base Name C:\NCSS\CREWDescription Data base created at 07:48:02 on 05-03-1992


Y: CREW4 X: LEN+WINGModel: A+B*(X)+C*{LOG(X))Filter: CREW4Term Coefficient EstimateA -1.48042021491415B -2.832923203920881D-03C .8146558480412586


df Sum-Sqr2 .2526895 .1690617 .42175

Std. Error1.8986062.211458E-03.4565359

T-Value Prob( ,'t|>T)-0.8 0.4708-1.3 0.25641.8 0.1344

Mean Square.1263445.0338122.06025

SQRfM.S.).3554497.1838809.2454588

F-Ratio3.7

R-Squared0.599144K

Prob(f>F0.1017

ActualRow X

1 852 .3 1014 1075 806 2317 2678 3289 471

ActualY1.58

2,2,2,

.04,18.02

2.212.392.262.22

Residual Analysis

Predicted Lower95% Upper95%Y Value Value1.898013 1.. 358883 2.437143

Residual-.3180131

1.9931892.0232041.862792.2988722.3148742.3096932.199364

1.4748241.5065641.3099791.7453911.7690781.7762171.547251

2.5115552:. 5 3 984 52V41562.8523532.860672.8431692.851477

.0468105

.1567957

.1572104-.0888719.7513E-01-.0496934. 2064E-01

O-5

Sum of Functions RegressionDate/Time 05-03-1992 08:52:24Data Base Name C:\NCSS\CREWDescription Data base created at 07:48:02 on 05-03-1992


Y: CREW9 X: DRY WGTModel: A+B*(SQR(X))Filter: CREW9Term Coefficient EstimateA 1.789334628455685B 9.872173912348861D-04

Std. Error.10351513.452152E-04

T-Value Prob(|t|>T)17.3 0.00002.9 0.0288


df Sura-Sqr1 .15746876 .11553137 .273

Mean Square.1574687l;925522E-02.039

SQR(M.S..3968232.1387632.1974842

F-Ratio8.2

R-Squared0.5768083.

Prob(f>F0.0288

ActualRow X

1 177922 .3 296634 274255 144476 719907 970308 1408829 320083

ActualY1.76

lies2.27172.022.032.122.42

Residual Analysis

Predicted Lower95% Upper95%Y "• Value Value Residual1.921016 1.544625 2.297407 -.1610163

1.9593631.9528231.9079942.0542152.0968492.1598792.347862

1.5912411.5834831.5281911.6943241.7347551.7879461.90699

2.3274842.3221622.2877972.4141052.4589442.5318122.788734

-.794E-01.4718E-01.2620062-.342E-01-.668E-01-.0398794.7214E-01

0-6

APPENDIX P

Scheduled Maintenance Data

SCHEDULED MAINTENANCE DATA BASEREGRESSION FUNCTION & ANOVA FOR % OF UNSCH

% OF UNSCH = 0.844224 + 0.002638 LGTH+WING+ 3.379129E-05 WET AREA- 0.005231 SQR DRY WT

R-Squared = 0.849869Adjusted R-Squared = 0.830287Standard error of estimate = 0.048856Number of cases used = 27

Source

RegressionResidual

Total

Analysis of Variance

SS df MS : F Value

43.399860.31077 30.05490 23

0.36567 26

Ov103590.00239

Sig Prob

O..OOOOOO

Variable

ConstantLGTH+WINGWET AREASQR DRY WT

SCHEDULED MAINTENANCE DATA BASEREGRESSION COEFFICIENTS FOR % OF UNSCH

Coefficient,

0.84422.0.00264

3I37913E-05-0.00523

Std Error

0.047745.41478E-O44.82356E-065.44648E-04

t-Value

17.682674.871917~. 00547-9.60423

Two-SidedSig Prob

0.0000000.0000640.0000000.000000

Standard error of estimate = 0.048856Durbin-Watson statistic = 2.325117

P-l

SCHEDULED MAINTENANCE DATA BASESTANDARDIZED RESIDUALS TABLE FOR % OF UNSCH

CaseActual Predicted

% OF UNSCH % OF UNSCH

A-7DA-10AB-52GB-52G-2FB-111AF-106AF-111AF-111DF-111FF-4EF-5EF-15AF-15CF-16AC-130BC-130B-2C-130EC-130HC-130H-2KC-135AC-140A-2C-141BC-141B-2C-5AC05A-2C-9AT-38A

0.48400 . 46600.25900.33000.17000.48800.23600.25200.18100.2580O.63200.27900.34900.47200.38400.47000.32100.28800 . 4020O.29600.39100.25100.30300.25700.27200.27300.5850

0.42770.46960.30660.30660.19010.39490.22450.20820.20760.27770.56510 . 35850.34850 . 47200.39800.39800.34950.33460.33460.28930.47180.26560.26560.26510.26520.31510;6389

Residual

0.0563-3.562E-03-4.760E-02

0.0234-2.015E-02

0.09310.01150.0438

-2.661E-02-1.975E-02

0.0669-7.955E-025.1859E-04-1.384E-05-1.400E-02

0.0720-2.849E-02-4.662E-02

0.06746.6864E-03-8.076E-02-1.460E-02

0.0374-8.147E-036.8484E-03-4.212E-02-5.388E-02:

Std Dev

0.04620.04660.04590.04590.04420.0472O.04520.04460.04460.0452O . 04380.04680 . 04660.04580 . 04640 . O4640.04710.04710.04710.04650.04660.0455O.O455O.03560 . 03560.04610 . 0404

StdResidual

1.2168-7.641E-02

-1.0370.5097-0.4561.97080 ; 25360 . 9826-0.597-0.4371.5287-1.7010.0111

-3.020E-O4-O.3021.5514-O.605-0 . 9891 . 42950.1437-1.733-0.321_0.8221-0.2290.1926-0.914- 1 . 333

Durbin-Watson statisticPRESS statistic

= 2.325117= 0.07127

P-2

Descriptive Statistics •Date/Time 03-23-1992 13:50:42Data Base Name C:\NASA\MAINTDescription Merge of WUC51 and WUC11 created 02-21-1992

Detail Report

Variable: %UNSCHMean - AverageLower 95% c.i.limitUpper 95% c.i.limitAdj sum of squaresStandard deviationVarianceCoef. of variationSkewnessNormality Test ValueK.S. Normality Test

0.55 Skew-Z

.3731923

.3193155

.4270691

.444882

.1333991.779528E-02.3574537.58886641.0154850.123701.33 Pr 0.1846 b2


D'Agostino-Pearson Omnibus K/ Normality Test100-%tile (Maximum) .665 90-%tile75-%tile .472 10-%tile

2.49 Kurt-Z1.8

.3515 Range

.272 75th-25th %tile

.17 C.L. Median(95%).17 Line Plot / Box Plot11 1 12 21 11 1 11 11 1 1 1111 1

50-%tile (Median)25-%tile0-%tile (Minimum)

359269.7032.616169E-0214.264840.0000-.35604981.265(5%)0.171(5%)

-0.25 Pr 0.8000Pr 0.4016.585.236.495.2

.273, .4666651

Variable: %UNSCHBin Lower1 .172 .215

26305353954448553

34567891011

.5750001

.62

Upper.215.26.305.35.395.44.485.53.5750001.62.665


Count24523232012

Prcnt- 7.715.419.27.7

11.57.711.57.70.03.87.7

Total26111316182123232426

Prcnt. 7.723.142.350.061.569.280.888.588.592.3100.0

Histogram***********************

***

P-3

APPENDIX Q

Learning Curve Data & Regression

_ Multiple RegressionDate/Time 01-08-1992 16:07:40Data Base Name C:\NASA\learnDescription Data base created at 15:46:10 on 01-08-1992

Aircraf t : F-16BMultiple Regression Report

Dependent Variable: LOG MTBMIndependent Parameter Stndized Standard t-valueVariable Estimate Estimate Error (b=0)Intercept -1.826819 0.0000 .2906916 -6.28LOG CUM .1441237 0.7799 .2726E-01 5.29


Seq.R-Sqr

0.6082

SimpleR-Sqr

0.6081


Dependent Variable: LOG MTBM


Constant 1 1.973916Model 1 1.468497Error 18 .9458253Total 19 2.414322



Mean Square

1.9739161.4684975.254585E-02.1270696

.2292288-.3141589-.7296589

0.60820.5865

F-Ratio Prob. Level

27.95 0.000

Row MTBM FLY HRS LOG MTBM CUM

1234567891011121314151617181920

.315

.459

.587

.651

.801

.679

.953

.724

.48

.574

.63

.687

.633

.825

.779

.9391.1721.1121.411.076

106138729844735542861338907983193691004412787155311577516248159751642417726168771648112657

-1.155183-.7787051-.5327305-.4292457:-.2218943-.3871342-4.81E-02-.3229639-.7339692-.5551259-.4620355-.375421-.4572849-.1923719-.2497442-.0629398.1587117.1061602.34358977.325E-02

1061493447792121464020773296803951148880589247171187242103017119265135240151664169390186267202748215405

LOG CUM

4.6634397.3085438.4067099.1282639J5915139:94140910.2982310.5843310.7971210.98411.180411.3764411.5426511.689111.8148111.9294212.0399612.1349412.2197212.28028

Q-l

Multiole RegressionDate/Time 01-08-1992 16:14:52Data Base Name C:\NASA\learnDescription Data base created at 15:46:10 on 01-08-1992


Dependent Variable: LOG MTBMIndependent Parameter StndizedVariable Estimate EstimateIntercept -2.229546 0.0000LOG CUM .1271822

Standard t-valueError (b=0),2569398 -8.68

0.8949 .2836E-01 4.49

Aircraft: B-l


Seq.R-Sqr

SimpleR-Sqr

0.8009 0.800C




Constant 1 8.427293Model 1 .3213427Error 5 7.987001E-02Total 6 .4012127



Mean Square

8.427293.3213427.0159746.686879E-02

.1263883-1.097223-.1151892

0.80090.7611

F-Ratio Prob. Level

20.12 0.006

Row MTBM FLY MRS LOG MTBM CUM

12345678

.236

.266

.288

.396

.339

.238

.498

.382

36711672786651583O4110OO1242711676

-1.443923-1.324259-1.244795-.9263411.-1.081755

-.6971552-.9623347

367153443201083519139301394256654242

LOG CUM

5:9053627.3356348:3710119.2905379185948410.3135810.6588110.90121

Q-2

Multiple RegressionDate/Time 01-08-1992 16:25:06Data Base Name C:\NASA\learnDescription Data base created at 15:46:10 on 01-08-^1992 Aircraft: F-15A


Dependent Variable: LOG MTBMIndependent Parameter StndizedVariable Estimate EstimateIntercept -2.517107 0.0000LOG CUM .1403061 0.8265

StandardError.2322152.1912E-01

t-value<b=0)-10.847.34


Seq.R-Sqr

0.6830

SimpleR-Sqr

0.6830




Constant 1 18.84179Model 1 2.070925Error 25 .9610558Total 26 3.031981

Root Mean Square Error •Mean of Dependent VariableCoefficient of Variation


Row, MTBM FLY HRS

1 .23 4222 .186 15793 .242 36104 .343 89745 .217 83176 . 484 208867 .43 267628 .521 360229 .491 4028110 .482 4839611 .499 4599312 .5 4034913 .483 4210114 .449 4O42715 .424 3912616 .475 4196017 .423 4296018 .38 4169419 .438 4292520 .496 44157

21 .404 4077822 .492 4019823 .514 4008924 .687 4567125 .704 4228426 .74 4421427 1 3881728 .582 3736629 1.073 42941

Mean Square F-Ra

18.841792.070925 533.844223E-02.1166146

.1960669

.8353705

.2347065

0.68300.6703

LOG MT8M CUM

-1.469676 422-1.682009 2001-1.418818 5611-1.070025 14585-1.527858 22902-.7256704 43788-.8439701 70550-.6520053 106572-.7113112 146853-.7298112 195249-.6951492 241242-.6931472 281591-.7277386 323692-.8007324 364119-.8580218 403245-.7444405 445205-.8603831 488165-.967584 529859-.8255364 572784-.7011793 616941-.90634O4 657719-.7092766 697917-.665532 738006-.375421 783677-.3509769 825961-.3011051 870175

908992-: 5412849 946358

989299

Prob. Level

0.000

LOG CUM

6.045O057.6014023.6324849.58774910.0389810.6871111.1640811.5765811.8971912.1820312.3935612.5482112.6875512.8052412.907313.0O62913.0984113.1803713.2582613.3325313.3965313.4558613.5117113.5717513.624313.6764513.720O913.7603813.80475

Q-3

Learning Curve

SUMMARY OF REGRESSION ANALYSIS OF WUC FOR F15A

WUC R-SQUARED F-RATIO PROB(f>F)

11121314232441424445464749515255576365717475769197

.4986

.2419

.6682

.0051

.8615

.1733

.3939

.5006

.0571

.5544

.0484

.2858

.1241

.7441

.5637

.8064

.5747

.6388

.0588

.7474

.6896

.0001

.0347

.0043

.0849

26.88.654.40.1

168.05.7

17.527.11.6

32.21.3

10.43.7

75.633.6108.335.146.01.6

76.957.80.00.90.12.4

.0000

.0067

.0000

.7135

.0000

.0247

.0003

.0000

.2209

.0000

.2604

.0034

.0660

.0000

.0000

.0000

.0000

.0000

.2139

.0000

.0000

.9573

.3424

.7405

.1325

-1.915372.058404-.1265132.320406-1.157162.0835291.4757401.6287903.469018.71487622.0356953.1693163.582417.4074346.8766071.48106991.8363965.783D-22.294958-.280821-1.371032.0108363.7017416.5566561.856478

B

.2076786.85051D-2.1985811.35424D-2.2604547.37557D-2.111258.132691-3.5174D-2.1581114.59528D-2.1141946.83186D-2.217907.246037.304793.186201.2181413.60766D-2.227016.221936-2.5339-4.7932D-2-3.1327D-2.186038

Q-4

Learn ing Curve

SUMMARY OF REGRESSION ANALYSIS OF WUC FOR F16B

WUC R-SQUARED F-RATIO P R O B ( f > F )

111213142324414244454647495155626364657174757691939697

.1059

.36829

.32299

.52673

.60731

.61054

.51493

.142337

.000168

.596262

.383556

.006646

.003831

.006221

.152934

.295669

.391082

.694946

.009315

.380828

.733988

.705648

.249363

.167479

.861299

.012051

.007545

2.311.19.1

21.129.429.820.23.20.0

28.111.80.10.10.13.27.612.241.00.2

11.752.445.56.33.6

31.00.20.1

.15

.0035

.0072

.0002

.0000

.0000

.0003

.0918

.9555

.0000

.0028

.7254

.7955

.7340

.0882

.0132

.0024

.0000

.6773

.0029

.0000

.0000

.0212

.0732

.0026

.6450

.7081

1.06010.8958701.18406.68128.52739.1432431.0961762.3528413.3012241.9055431.1165094.0804916.4613573.4176077.7507617.0489222.1408831.1891824.4754612.109804-1.15588-.3489292.1966884.3369794.3793667.1128114.651410

B

6.46444D-02.165848

9.746065D-2.160767.200457.244629.205497

6.748413D-2-3.30773D-2

.182393

.1452481.689806D-2-2 .7 978 3D-21.448673D-2-.182029-.242943.1653402.3180727-2.87638D-2

.133664

.280784

.258164

.101590

.293534

.4249086.728099D-23.790276

Q-5

Learning Curve

SUMMARY OF REGRESSION ANALYSIS OF WUC FOR BIB

WUC R-SQUARED F-RATIO P R O B ( f > F )

11121314161923242739414243444546474849515255597375:7697

.3889

.5187

.0437

.0128

.5717

.2123

.2637

.7642

.0458

.1926

.2466

.3047

.1248

.6880

.0114

.1802

.4963

.2795

.6084

.5936

.3803

.6044

.2483

.6457

.1214

.2454

.3654

3.86.50.30.18.01.32.119.40.31.42.02.60.9

13.20.11.35.92.39.38.83.79.22.0

10.90.82.03.5

.0985

.0439

.6194

.7895

.0300

.2981

.1931

.0045

.6109

.2767

.2106

.1560

.3907

.0109

.8012

.2945

.0511

.1780

.0224

.0253

.1035

.0232

.2089

.0163

.3977

.2119

.1124

A

-.4813981.3397571.6275071.856759-1.288142.964628.514386.702416

3.8852552.4230091.040726.986220

3.072291.597645

1.8871972.8177221..8596262.6790965.9605211.0156084.465351,255066,752438

-.6095651.7397761.1279137.623481

11

B

.107564

.2182973.24288D-2-1.8648D-2.533732.1590607.03474D-2.259668-.07045.1585998.32289D-28.57397D-2.104326.199826.016278-.09968.191071.142582-.20272.415428-.10694.1771148.51324.169980.0822627.49415-.22974

Q-6

AVERAGE SLOPE FROM SUMMARY OF REGRESSION ANALYSIS OF WUC

PLANESF15AF16BBIB

USED:

WUCs11 &13142341 &42 &

12

4744

4549 & 9651 - 72*91, 93, & 97

AVERAGE.153578.148021.160767.230456.155505.133334.170252.068319.242701.359221

SLOPE NUMBER OF VALUES AVERAGED5212432182

51 - 72 IS COMPOSED OF 51, 52, 61, 62, 63, 64, 69, 71, & 72

Q-7

APPENDIX R

Technology Growth Data

TECHNOLOGY ADJUSTMENT FACTOR DATA

. 'i : LJ Mi -jM '- ALC w i_.-i i • 0 . • C

FLY HOURSMTBM/PERIOD

wucwucwucwucwucwucwucwucKUCVUCwucwucwucwucwucwucwucwucwucwucwucwucwuc

* ••%

± 1 '3L <J

14•> o_ o

41421445474931526162636469717291939697"

GROUPED11 i 1213

234142

4744

-rO4951 - 7291 & 97

WUCs

0/85-3/86

4,200

7.67338. £211.86711.03217.96229.75543.019

3634.721

1.36.2251.95.42939.265

83.S2455.019156.381

3,109.09151.42983.824152.679

4/86-9/86

10, 164

8.52540.43813.77412.93919.09829.25358.20348.56644.936168.050218.28352.571

89.45269.972193.096

2,868.85760.67196.317161.952

1C/86-3/37

3S.C27

12.33650.24715.30217.52327.35544.47873.37546.97146.188164.507259. 18760.754

133.92986.396251.S37'

1,896. 15365.743103.229232.432

4/37-9/87

40.533

12.58458.4031G. 18119.22724.79146.06078.70557.25054.774

167. 492311.79260.227

142.72289.280

258. 1722,533.313

75". 061107.230268.43

10/35-9/87

120,924

10.740448.154115.144315.811522.863837.740567.456249.996147.7059165.4609254.849956.5869

114.935280.1036226.1225

2.401.626766.0188101.2675207.9488

183.371 196.882 184.754 455:427 236.7149

8151522302847

25414

110

,78171443,81153638,73107142,70593499,55247007

WUCs 51, 62, 63, 64, 69 & 72

r~ < T PT*T \ TL.-.i-L >. i-.-ii

MTBM/PERIODwuc : iWUC 12WUC 13WUC 14WUC 23WUC 41WUC 42WUC 44WUC 45WUC 47WUC 49WUC 5 1WUC 52WUC 61WUC 52WUC v3WUC 6 IWUC 69WUC 71WUC 72WUC 91WUC 93WUC 96WUC 97

GROUPED11 & 12131423414245495191

4744

967297

10/85-3/86

106,021

3.47524.88220.33818.59425.02929. 16745.89765.083113.87958.285285.77128.960220.418

96.47091.793391.221

2,255. 7661.53.210

9,638.273302.054

4/86-9/86

113,267

6.95520. 11:216.35615.50118.49622.99437.90760.44194.46847.792230.68623.876143.014

64.83569.660337.104845.276106.354

3,146.306207.069

10/86-3/87

104, '537

6.48920.27515.82914.70917.74522.12433.30351.93177.723'43.179188.69524.054138.276

64.89070.112313.925

1,005. 16395.468

3,167.788244.245

4/87-9/87

118,573

3. 18527.46722.86020.80221.66130.63944.27778.681103.64875.332278.99530.521162.429

90.307101.344374.047513.303131.310

4,088.724334.008

10/85-9/87

442,293

7.451722.347818.491117.136520.363625.786939.802162.992595.778154.0563240.303026.5931160.3472

76.672281.2932351.9473857.3603117.8159

4,058.6975263.1751

WUCs

10,602.100 7,079.188 17,422.833 11,857.300 10,533.2860199.663 203.718 234.915 296.433 228.9848

5.619118.491117.136520.363617.458524.390795.7781234.943112.2062 WUCs 51, 52, 62, 63, 64, 69, 71, 72.

122.4462

R-2

10/85-3/36 4/36-3/86 10/86-3/87 4

FLY HOURSMTBM/PZRIODWUC :. 1VUC 12WUC 13

51,56" 54,718

WUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUC

140 Oi. U

4142444547495152SI62S38469717291939697

GROUPED11131422414245495191

& 12

&. 47& 44

- 72, 93,

WUCs

97

3.3166.96211.45910.33817.92433.79245.87825.29047.44059.069334.85118.56351.006

23.145

4.14462.963991.673170.188

2,242.043537. 156

2.094312.16019.942316.925619. 123616.813644.1927226.89652.577592.0627

2.6765.85911.6878.45715.59825.65339.91126.43442.91657.841279. 17316.84746.808

16.032

3.37446.371816.687144.757

2,379.043353.019

WUCs 51,

49 ,583

36121.01531412544512451749

,264021

, 578.102, 558,968.488, 585,629,703,460,086.533

/87-3/S7 1

491

3612101727432843622131750

,240

. 187

.208

.253

.083

. 140

.306

.357

.200

.979

.499

.583

.863

.229

.0/85-9/87

647

3.6 .12.9.16.27.43.27.44.60.226.17.49.

, ioa

1535215516019423925639230824575419278301896576399273

18.412 21.257 20.5800

3.338 4.190 4.025458.817 74.094 68.3182708.329 1,116.455 1,028.7890156.413 156.446 156.3819

MTBM NOT CALCULATED378.496 261.298 286.0779

52, 63, 71, & 72

R-3

10/85-3/86 4/86-9/86 10/86-3/87 4/37-9/87 10/85-9/87

FLY HOURSMTBM/PERIOD

40,089 45,571 2 0, .-00 - 44,214 179 ° ~ Qx I £ , «d w o

WUC*ucWUCwucWUCwucwucWUCwucwucwucwucWUCwucWUCwucwucwucwucwucwucwucwucwuc

:. 1•« n- w

13142341.'1 <~>-r t*

4445474951526162636469717291939697

GROUPED WUCs11 &.13142341 &42 &.454951 -91 &.

12

4744

7197

1 .9161 2 . 5 7 39.2769.8029.833

15.93429.91715. 16215.59399.47659.21625.024120.387

2.55920.26213.70714.04810.89720.22642.64320.12824.984135.92683.49431.849153.774

2.73622.69714.36814.17011.81823.76836.48319.45920.506

120.467107.04827.245126.599

3.09722.26216.83114.83212.28126.22442.67822.19619.350

113.369100.03233.34473.081

2.539518.540413.026512.945911.173120.907637.398518.975319.6957

116.390483.580129.1272109.7883.

20.633

41.934

2.233613.026512.945911.173117.723812.588219.695783.58017.1444

58.0187

28.349 25.094 28.055

84.420 127.746 56 i 180

WUCs 51, 52;: 63, 69, &. 71

25.2764

15.077 23.713 16.263 16.824 17.5541

331.314 496.424 671.175 566.846 486.6045

65.8729

R-4

'ISA

10/85-3/86 4/86-9/86 10/86-3/37 4/87-9/87 10/85-9/37

FLY HOURSMTBM/PERIODWUC 11

33,311 85, C2' 39.041 92,692 350, 102

WUCWUCWUCWUCwucwucWUCwucWUCwucwucwucWUCWUCwucwucwucwucwucwucwucwucwuc

121 *}1 sJ

14234142444547495 1- o*J &.

6162636469717291939697

625121421382230758064150

• O O *>

.699

.757

.362

.309

.637

.124

.833

.014

. 757

.085

.571

826,1115,25,35.22,34.74,90.488.64.

.350

.521

.210,756.008,019.943,410,324.551,661610

9341 OL 0

182351303779

10270676

.250.! - q• ~t *j j.489.010.432.469.619.085.359.938.675.627

3.29.12.14.19.40.28.31.74.118.626.66.

655690348470315O i QO i. J

166679333533304734

328121522402533759660563

30 r r:4. *J \J

.8032

.4037

.5285

.0051

.6432

.6072

.3399

.7139

.7670

.7130

.4818

85. 74252.219324.284

78.51151 .500397.322

38.42261.535418.033

73.44958.224397.324

80.967255.6955381.7905

150.707 140.773 170.250 146.203 151.2970

2,604.406 5,001.588 1,141.551 648.203 1,296.67427,576.455 28,342.333 22,260.250 92,693.000 18,426.421711,905.857 5,314.188 8,094.636 7,724.417 7,610.9133

2.13.695 228.567 57.483 50.159 84.1798

GROUPED WUCs11 & 1213

41 i 4742 St. 444549 & 9651 - 72 *91, 93, & 97

61215222814755611878

4587403752850051621848327139061008757103

WUCs 51, 62, 63, 64, fc 71

R-5

F4C MTBM CALCULATION'S

10/85-3/36 4/86-9/86 10/86-3/87 4/87-9/87 10/85-9/87

FLY HOURSMTBM/PERIODWUC 1 1WUC 12WUC 13WUC 14WUC 23WUC 41WUC 42WUC 44WUC 45WUC 47WUC 49WUC 51WUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUCWUC

526162S36469717291939697

18,421

39.959

8.536139.553877.190214.198708.500103.489

12,577 9.944

34.177

9.586151.530483.731196.516

44.995

12..864284.114904.000320.774

40 ,942

5.48205.613011.69609.783017.072025.656033.432029.616033.013046.2840224.646021.749051 . 4550

4.5575.48310.6958.77715.62429.52334.08432.08427.34138.462256.67318.97051.126

6.3959.48915.48912.47719.65238.99650.22243.61431.97454.339621.50028.99160.634

5.33436.181212.06689.954517.130529.265036.620832.964630.806645.0905278.516622.095253.3097

228.673 261.684

38.9925

9.6492163.7679705.8966226.1992

151.0777:

GROUPED WUCs11131423414245495191,

& 12

& 47&. 44

- 72 *, 93, & 97

2.12.9.17.17.17.30.278.

5.80.

8633066895451305746834838066516601492785

WUCs 51, 52, 63, 71, & 72

R-6

352G MTSM CALCULATIONS

10/85-3/86 4/86-9/86 1

FLY HOURSMTEM/PERIODWUCwucWUCwucwucWUCwucwucwucwucwucwucwucwufWUCwucwucwucwucwucwucwucwucwuc

111 O

13142341424445474951526162636459717291939697

GROUPED11 & 12

WUCs

131423414245495191

4 47& 44

- 72, 93,

*&

.32.742 34,536

97

3.32714. 1375.2437. 1743.588

2.3.96914.01619.6069.210

55.30759.6397.92019.443

134.741

39.40124.674

40.12583.739696.63884.170

85.712

2.54794.73647.08174.592518.30958.98249.621055.48103.7226

41.3999

2.37716.2605.0257.3224.851

25.35717.28521.5049.95656.99051.6238.61922.543124.679

36.08825.227

85.274101.279986.743100.104

54.994

WUCs 5 1 ,

0/86-3/87

33,363

2.87215.3924. 1076.6365.132

28.26617.24217 . 5558.968

- 50.54254.9728.51722.819132.277

30.72922.234

52.017109.235891.132103.874

;/87-3/87

34,899

3.07419.7954.7427.2315. 148

30.93916.94922.04610.44968.69956.4718.84627.350139. C40

35.57522.400

56.471116.719

1,125.774192.812

10/85-9/87

136,040

3.023816. 18934.73647.08174.5925

26.917216.278320.04129.6210

57.255955.48108.469622.7644L32.4636

35. 143623.5485

54.6346101.4466900.9271109.6212

159.731 51.933 71.8270

52, 61, 63, 64, 71, & 72

R-7

SIB MTBM CALCULATIONS

10/87-3/88 4/88-9/88 10/88-3/89 4/89-9/89 10/87-9/89

FLY HOURSMTBM/PERIODWUC 11WUC 12WUC 13WUC 14WUC 23WUC 41WUC 42WUC 44WUC 45WUC 17WUC 49WUC 51WUC 32WUC 61WUC 62WUC 63WUC 64WUC 69WUC 71WUC 72WUC 91WUC 93WUC 96WUC 97

8,304

1.90523.7946.4525.6073.0076.1015.08512.1947.152

35.03851.900159.69243.937

296.571

11,001

1.23521.5714.5843.4592.4734.0944.3678.8934.779

22.87128.42660.44522.314

139.253

12,427

2.42869.42511.C567.6104.6728.3129.37219.88311.31868.28046.894

225.94534.329

203.721

11,676

1.90051.8937.9655.8943.4296.8767.33017.4798.68169.08943.567

353.81819.299

93.408

43,408

1.769634.36936.91565.24543.27085.99456.138813.51847:349840.606140.1923134.807326.3237

148.1501

GROUPED WUCs11 & 1213142341 & 4742 & 44454951 & 5297

1.68296.91565.24543.27085.22344.22177.3498

40.192322.0232148.1501

R-8

Li!CD<ro:HI.

sr CN CN >o r% o CN ^ in CD INCD in CN <-" •rt &• CN N ^ in If}1-1M »O *-i »0 O CN in 0s K" M03 M in •-« O M 0- r-0 -H CD No o o o o o o o <t o ao o o o d o o o a o d

COf*

-iCDCNin04 :

iU

CD in CD CD to 0* 0s hO D* fN Q*Nt1 *"* 0s 0* 0s &* C''i M * " *™* ^o IIT o ~* •** o ^ o in o Hio o o o o o o o «$• •*• 13-O O O O O O O O O O •""•

! I I

(N o in CD t'~i •«-• fN in i-« tN ^in CN O «*" t-> OQ CD O KI •*•' K*t''J •** -O " N O in O 0- CN Ch^ O O O O O ~« <•« CN O CN

O O O O O O O O O O •""

s_o

oS_cs

C7)o

u(U

U.I

UJ

\n1-«li.

IUJ

u.

?1-*

I

i

Ch W N K) «O tN ^ ^ N »-«r i *^ o- >o m r-j CN h> ow o o o o o ^ CM o* oo o o o do o o o o

III CN CM O rt CD O

CM CM N in o <t o w ch inO O O O O O *-i M O

o o o d d d d d d c"I I ! I I I

r-s CD TI TH «j- c> in T-I jxn >o r>i ^ r-4 o to in N wCD vO K) -• O M IN ^H r-4 LOO O O O « O C-4 O O O

i i i i i

aUl-HUI

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1-4

SiT

R-9

TECHNOLOGY ADJUSTMENT FACTOR

Overall Aircraft

Perform pairwise comparison between similar aircraftdeveloped at different times (i.e. different technologies).

Determine the annual growth rate in reliability (FHBMA).

Average annual growth rate over several comparisons.

Model: Compound Growth Curve

ADJ FHBMA = FHBMA x {1+ADJ

ACFT

A-7DA-10A

F-4EF-15A

F-4EF-16A

F-4CF-16A

B-52GB-l

FHBMA

1.271.34

.507

.652

.5071.110

.6561.110

.406

.338

DEV YR

6872

6772

6774

6374

5885

DISCOUNTED FHBMA'

1.271.387

.507

.680

1.182

1.224

.534

AVERAGE =

ADJ FAC s

.0220

.0604

.128

.058

.0102

.0557

Notes:

1. 86 represents the baseline year of the data

2. Discounted FHBMAa = A x ( 86-yn+yrz )»

where B = .137 and A = FHBMA2 /(86-YR2)B

(based upon reliability growth curve)

3. ADJ FAC = (DISC FHBMAz/FHBMAi ) 1 / < r r « - y r i > -l

(by solving for the ADJ FAC in the compound growth curve)

R-10

APPENDIX S

R & M Model - BASIC Program Listing

10 'NASA, LANGLEY RESEARCH CENTER20 'MTBM COMPUTATIONAL MODEL - NASA RESEARCH GRANT -30 'DEVELOPED BY C. EBEUNG, UNIV OF DAYTON 2/10/9235 ' »******« COMBINED PRE/CONCEPTUAL MODEL **»*««**«*40'50 'SAVE AS "MTB3.BAS" Mean Time Between Maintenance - MODIFIED60'70 DIM WBS$(2S) 100),NAM$(100),THRS(20) IHMA(20) 1H(20) IP(20),ON1H(20) MH(20)72 DIM GOH(20)OX)H(20),TOH(20),OOH(20),ROH(20),R(20),TSKT(20)73 DIM V(15),SNAM$(15) JTV1AT(20)4'MACX20),FMAS(20),S(20)74 DIM MW(20),C(20),CM(20),OP$(20),TG(20),PWTS(20)75 DIM FMA(20)^F(20)^A(25)^(500),Y(SOO),RR(20),W(20)^IR(20)4'R(20)76RFLG=0 'REPEAT FLAG80'85 GOSUB 1000 'OPENING BANNER87 INPUT "DO YOU WISH TO INPUT FROM A FILE-(Y/N)";ANS$88 IF ANS$="Y" OR ANS$="y" THEN GOSUB ITOthGOTO 10090 GOSUB 500 INITIALIZATION95 GOSUB 12300 'OPTION TO DELETE SUBSYSTEMS100 GOSUB 1050 INPUT MODULE102 IF RFLG=0 OR MODE=0 THEN GOSUB 1500 ELSE GOSUB 1400 'SUBSYS WGTS103 IF RFLG=0 OR MODE-0 OR MODE=1 THEN GOSUB 11120 ELSE GOSUB 11000 'SECONDARY VARIABLES104 GOSUB 1200 'ESTABLISH SUBSYSTEM MTBM CALIBRATION FACTORS105 GOSUB 1600 'DETERMINE MISSION PROFILE110 GOSUB 1300 'DETERMINE SUBSYSTEM HRS111 GOSUB 12400 'ESTABLISH TECH GROWTH FACTORS112 CL&LOCATE 10,20:PRINT "COMPUTING MTBM'S ....."113P1 = .202:P2=.014:P3=.784 . . .114 'ADD=W(l)+W(2)+W(3):P1=W(1)/ADD:P2=W(2)/ADD:P3=W(3)/ADD115 GOSUB 3000 'EVALUATE REGRESSION EQS; DETERMINE UNADJUSTED MTBM & MH/MA120 GOSUB 2500 'PERFORM TECHNOLOGY ADJUSTMENT130 GOSUB 2000 'DETERMINE SPACE ADJUSTMENT140 GOSUB 2700 'DETERMINE CRITICAL FAILURES-MTBM145 GOSUB 2800 'DETERMINE CRTT FAIL RELIABILITY150 GOSUB 9000 'DISPLAY RELIABILITY PARAMETERS160 GOSUB 7000 'COMPUTE MANPOWER REQUIREMENTS170 GOSUB 7500 'DISPLAY MAINTAINABILrrY PARAMETERS175 CLS:LOCATE lO^ftPRINT "COMPUTING SPARES "180 GOSUB 8000 'COMPUTE SPARES REQUIREMENTS190 GOSUB 8500 'DISPLAY SPARES REQUIREMENTS200 GOSUB 9700 'DISPLAY VEHICLE TURN-TIME310TMA12=2257.4-687.44'LOG(W(3))+70.118»LOG(W(3))"2-2J8<LOG(W(3))"3400 CLS405 LOCATE 10^0:INPUT "DO YOU WISH ANOTHER ANALYSIS-<Y/N)";ANS$408 IF ANS$='V OR ANS$=y THEN RFLG=1:GOTO 100409CLS410 LOCATE 10,lfcINPUT "DO YOU WISH TO SAVE FHBMA'S FOR RELIABILITY ANALYSIS - (Y/N)";ANS$420 IF ANSS="Y" OR ANS$="y" THEN GOSUB 9500430 CLS435 LOCATE lO.lftlNPUT "DO YOU WISH TO SAVE INPUT FOR LATER USE - (Y/N)";ANS$440 IF ANS$="Y" OR ANS$=Y THEN GOSUB 9600470 LOCATE 15,25:PRINT "HAVE A NICE DAY"480 COLOR 3490 END500' INITIALIZATION MODULE520 FOR 1=1 TO 16525MW(I)=1526CM(I)=1527 OP$(i)="COMPUTE"

S-l

530 READ WBS$(I)540NEXTI580 FOR 1=1 TO 14590 READ NAM$(I)600NEXTI610 FOR 1=1 TO 12620 READ SNAM$(I)630 NEXT I640 FOR 1=1 TO 16:READ TG(1):NEXT I TECH GROWTH RATES650 FOR 1=1 TO 16:READ PWTS(I):NEXT I WGT DISTR PERCENTS690 ' •••• DEFAULT VALUES700 X(l)=9000! 'DRY WEIGHT - LBS710 X(2) = 100 'LENGTH + WING SPAN - FT720X(3)=2 'CREW SIZE730X(4)=8 'NBR PASSENGERS750 X(5)=1994 TECHNOLOGY YR760 X(6)=.0557 T>EFAULT TECH GROWTH FACTOR770X(7) = .28 -WEIBULL SHAPE PARAMETER780 X(8)=20 'LAUNCH FAILURE RATE FACTOR790 X(9)=144 ' AVAIL HRS PER MONTH800X(10) = .15 'PERCENT INDIRECT WORK810X(11) = .95 'SPARES FILL RATE GOAL815X(12)=1.8 'AVG CREW SIZE816X(13)=1 'PLANNED MSN PER MONTH817 X(14)= 1 "WGHT INDICATOR820T(0)=2:T(1)=.14:T(2) = 1:T(3)=71:T(4)=72830 'PI = J9:P2 = .01:P3=.6 'PRORATION FACTORS FOR WUC11 (WBS 1 A3)

900 'INrriALIZE SUBSYSTEM MSN PROFILES910 FOR 1=1 TO 16920 GOH(I)=T(0):LOH(I)=T(1):TOH(I)=T(2>T(1):OOH(I) =T(3>T(2):ROH(I) =T(4>T(3)921 NEXT I922 TOR 1=1 TO 3:OOH(I)=ftNEXT I923 'GOH(5)=0:OOH(5)=0924 'OOH(12)=0

999'1000 'INPUT MODULE1010 KEY OFRCL&COLOR 111015 IP RFLGS="YES" THEN GOTO 10501020 LOCATE 6,15:PRINT "VEHICLE REUABOJTY/MAINTAINABILrrY MODEL"1030 PRINT.PRINT TAB(20) "NASA - LANGLEY RESEARCH CENTER'1040 LOCATE 14,20:INPUT "ENTER VEHICLE NAME";VNAM$1042 PRINT:PRINT TAB(20) "ANALYSIS MODE"1043 PRINT:PRINTTAB(20) "PRECONCEPTUAI 1"1044 PRINT TAB(20) "SUBSYSTEM WEIGHT DRIVEN™2"1045 PRINT TAB(20) "WEIGHT/VARIABLE DRIVEN_-3"1046 PRINT:INPUT "ENTER CHOICE";MODE

1049 "PRIMARY MENU1050 CL&PRINT TAB(5) "INPUT MODULE - PRIMARY INDEP VARIABLES"1060 PRINT TAB(1) "NBR";TAB(10) "VARIABLE";TAB(35) "CURRENT VALUE"1065 PRINT:PRINTTAB(5) "VEHICLE DRIVER VARIABLES":PRINT1070 FOR 1=1 TO 141075 IF 1=5 THEN PRINT:PRINT TAB(5) "SYSTEM PARAMETER VALUES':PRINT1080 PRINT TAB(1) I;TAB(7) NAM$(I);TAB(35) X(I)1090 NEXT I1100 PRINT:INPUT "ENTER NBR OF VARIABLE TO BE CHANGED - 0 IF NONE";NBR1110 IF NBR=0 THEN GOTO 11351120 INPUT "ENTER NEW VALUE";X(NBR)1130 GOTO 10501135 YR=X(5):B=X(7):LF=X(8):X1=X(1):X2=X(2)

S-2

1137' -1200 'MODULE TO INPUT MOD FACTOR1205 CLS:PRINT TAB(20) "SUBSYSTEM MTBM CALIBRATION FACTOR"1206 PRINT TAB(20) "SPACE VEH-MTBM = CAL FAC x ACFT-MTBM"1210 PRINT TAB(3) "NBR SUBSYSTEM';TAB(45) "CAL FACTOR"1220 PRINT1230 FOR 1=1 TO 161235 IF OP$(I) = "DELETE" THEN GOTO 12501240 PRINT TAB(3) I;TAB(10) WBS$(I) TAB(45) MW(I)1250 NEXT I1260 PRINT:INPUT "ENTER NBR OF SUBSYSTEM TO BE CHANGED - 0 IF NONE";NBR1265 IF NBR> 16 THEN GOTO 12051270 IF NBR=0 THEN GOTO 12951280 INPUT "ENTER NEW FACTOR";MW(NBR)1290 GOTO 12051295 GOSUB 12200 'ESTABLISH CAL FACTOR FOR MAINT

1300 T>ISPLAY SUBSYSTEM OPERATING TIMES1301 CL&PRINT:PRINT TAB(5) "SUBSYSTEM OPERATING TIMES"1305 PRINT TAB(1) TOTAL MISSION TIME";TAB(20) T(4);" HRS";TAB(30) "MAX GROUND TIME";TAB(50) T(0);" HRS"1306 PRINT TAB(1) "NBR SUBSYSTEM";TAB(30) "GROUND",TAB(38) "BOOSTER";TAB(46) "REM TIME";TAB(S5)"ORBrT;TAB(65) "RECOVERY"1310 PRINT TAB(31) TIME";TAB(40) "nME";TAB(46) "TO-ORBn*;TAB(56) "nME";TAB(65) TIME"1320 PRINT1330 FOR 1=1 TO 161335 IF OP$(I)="DELETE" THEN GOTO 13501340 PRINT TAB(1) I;TAB(7) WBS$(I) TAB(35) GOH(I);TAB(42) LOH(I);TAB(50) TOH(I);TAB(58) OOH(I);TAB(65) ROH(I)1350 NEXT I1360 PRINTiINPUT "ENTER NBR OF SUBSYSTEM TO BE CHANGED - 0 IF NONE";NBR1365 IF NBR> 16 THEN GOTO 13011370 IF NBR=0 THEN GOTO 13951380 INPUT "ENTER NEW VALUES SEPARATED BY COMMAS";GOH(NBR)^OH(NBR),TOH(NBR),OOH(NBR),ROH(NBR)1390 GOTO 1300

1400 -WEIGHT MENU MODULE1402 IF MODE=1 THEN RETURN1405 CL&PRINT TAB(20) "SUBSYSTEM WEIGHTS"1410 PRINT TAB(3) "NBR SUBSYSTEM";TAB(45) "WEIGHT IN LBS"1420 PRINT1430 FOR 1=1 TO 161435 IF OP$(I)="DELETE" THEN GOTO 14501440 PRINT TAB(3) L-TAB(IO) WBS$(I) TAB(45) W(I)1450 NEXT I1455 PRINT:PRINTTAB(3) "TOTAL WGT";TAB(45) ADD:PRINT1460 PRINTINPUT "ENTER NBR OF SUBSYSTEM TO BE CHANGED - 0 IF NONE";NBR1465 IF NBR> 16 THEN GOTO 14051470 IF NBR=0 THEN GOTO 1495 C'.':1480 INPUT "ENTER NEW WEIGHT";W(NBR)1484ADD=01485 FOR 1=1 TO 16:ADD=ADD+W(I):NEXT I1486 X1=ADD:X(1)=ADD1490 GOTO 1405

1500 ' MODULE TO COMPUTE SUBSYSTEM WEIGHTS1505 IF X(14)=0 THEN GOTO 15671510W(l)=-«485026.7#+135102i5#*LOG(Xl)-135432!'(LOG(Xl))'>2+4522.4»(LOG(Xl))'>31511 IF W(l)< =0 THEN W(l)=7951515W(2)=-290909.9+91929.4*LOG(X1)-9709.901*(LOG(X1))'>2+343J*(LOG(X1))"31516 IF W(2)< =0 THEN W(2)=3021520W(3)=39713145^+1417950.4#'LOG(X1H04722(»#/SQR(IX>G(X1)>12993808^#»SQR{LOG(X1))1523 IF W(3)< =0 THEN W(3)=21401525 W(5)=^9535!+.282563'XH-6873.7*LOG(X1)-160.1'SQR(X1)

S-3

1526 IF W(5)< =0 THEN W(5)=5271530 W(12)=-9849.5 + .0459666*X1 + 1364.8'LOG(X1>26.248*SQR(X1)1531 IF W(12)< =0 THEN W(12)=1001535 W(9)=-910.4+100.22'LOG(X1)+ 13835*SQR(X1)1536 IF W(9)< =0 THEN W(9) = 1571540 W(14)=-719.15+5.56265*X2+56.882<SQR(X2)1541 IF W(14)< =0 THEN W(14)=631545 W(10)=-757.97+11.222'SQR(X1)1546 IF W(10)< =0 THEN W(10)=3101550 W(ll)=575.27+.022216*X1-5.0608*SQR(X1)1551 IF W(ll)< =0 THEN W(ll) = 1471555 W(15)=6625S.6-14720.4'LOG(X1)+818.19'(LOG(Xl)r21556 IF W(15)< =0 THEN W(15)=2841560 W(13)=-10901.5+ 1261.52'LOG(X1)1561 IF W(13)< =0 THEN W(13)=3031563 W(4)=.ll'Xl:W(6) = .01*X1:W(7)=.04*X1:W(8)=.02*X1:W(16)= .1*X11564 WENG=-7141.92+89.1053*SQR(X1)1565 -W(6)=WENG1567 FOR 1=1 TO 161568 IF OP$(I)=-DELETE" THEN W(I) = 11569 NEXTI1570 -WEIGHT RECONCILIATION1572 ADD=01575 FOR 1=1 TO 16:ADD=ADD+W(I):NEXT I1580 PCT=X1/ADD1586TX1=X11587 SMI=01588 FOR 1=1 TO 161589 IF OP$(I) = 'DELETE" THEN GOTO 15921590 IF X(14)=l THEN W(I)=PCT*W(I) ELSE W(I)=PWTS(I)*TX11591 SM1=SM1+W(I)1592NEXTI1593 DIF=X1-SM11594 IF DIF>1 AND X(14)=0 THEN TX1=TX1 + DIF:GOTO 15871595 ADD=SM11596 GOSUB 1400

1599'1600 -MODULE TO ESTABLISH MISSION PROFILE1615 CL&COLOR 10-.KEY OFF1630 NBR=01635 LOCATE 3,25:PRINT "MISSION PROFILE"1640 LOCATE 7,10:PRINT "NBR";TAB(50) TIME IN HOURS"1645 LOCATE 9,10:PRINT "I" ;TAB(25) "GROUND TIME PRIOR TO LAUNCH";TAB(55) T(0)1650 LOCATE 1L5:PRINT "LAUNCH TIME AT T=0"1655 LOCATE 13,10:PRINT "2" ;TAB(25) "BOOSTER COMPLETION TIME";TAB(55) T(l)1660 LOCATE 14,10:PRINT "3" ;TAB{25) 'ORBrT INSERTION TIME",TAB(55) T(2)1665 LOCATE 15,10: PRINT "4" ;TAB(25) "ORBir COMPLETION TTME-jTABCSS) T(3)1670 LOCATE 16,10:PRINT "5' ;TAB(25) "GROUND RECOVERY TIME";TAB(55) T(4)1675 PRINTiPRINT1680 INPUT -ENTER NUMBER TO BE CHANGED OR 0 IF NONE";NBR1685 IF NBR> 16 THEN GOTO 16151690 IF NBR>0 THEN NBR=NBR-1:INPUT "ENTER NEW TIME";T(NBR):GOTO 16151694 IF RFLG=O THEN GOSUB 900

1699'1700 'MODULE TO READ FROM A FILE1705 INPUT "ENTER FILE NAME";DNAM$1707 LOCATE 5,10:PRINT "INPUT DATA WILL BE READ FROM AN FILE"1708 PRINT1710 OPEN DNAMS FOR INPUT AS #31720 FOR 1=1 TO 16

1725 INPUT #3,WBS$(I),W(I),MW(I),CM(I)1730 INPUT #3,GOH(I),LOH(I),TOH(I),OOH(I),ROH(I)1731 INPUT #3,OP$(I)1735 NEXT I1740 FOR 1 = 1 TO 131745 INPUT #3,NAM$(I),X(I),SNAM$(I),V(I)1750 NEXT I1755 FOR 1=0 TO 41760 INPUT #3,T(I)1765 NEXT I1770 CLOSE #31780 LOCATE 15,10:PRINT "DATA SUCCESSFULLY READ"1785 RFLG=1

1999'2000 'MODULE TO DETERMINE SPACE ADJ MTBM2010YZ=fcYX=l2020 FOR J=l TO 162030 TO=GOH(J):T1=TO+LOH(J):T2=TH-TOH(J)2040 T3=T2+OOH(J):T4=T3+ROH(J)2050 IF OP$(J) = "DELETE" THEN GOTO 21002060 L1 = 1/FMAT(J):L2=LF'L12070 GOSUB 22002080 FMAS(J)= MEAN2090 YZ=YZ+ I/MEAN2095 YX=YX*RT42100 NEXT J2110 SVFMA=1/YZ:VR=YX

2200 'MODULE TO COMPUTE SPACE ADJUSTED MTBM2210 A= (BT(2r(B-l)/Lir(l/B)2220 Al = (1-EXP(-L1*TO))/L12230 A2=EXP(-L1TO)'(1-EXP(-L2*(T1-TO)))/L22240A3=EXP(-U'(Tl-TO))'(EXP(-L2nT))/L2-EXP(-L2'(T2+TO-Tl))/L2)2255 GOSUB 2320 TIND A4 USING SIMPSON'S RULE2260 A4=EXP(-Ll*(T2+TO-Tl>L2*(Tl-TO)+(T2/ArB)*AREA2270 AS = EXP(-L1*(T2 +TO-Tl>L2*(Tl-TOKI3/ArB + (T2/ArB)»(l-EXP(-Ll*(T4-T3)))/Ll2280 MEAN=A1+A2+A3+A4+A52290RT4=EXP(-Ll«(T2+TO-Tl)-L2'(Tl-TO)-(T3/ArB+(T2/ArB-Ll*Cr4-T3))2300 MEAN=MEAN/(1-RT4)

2320 N=INT((T3-T2)/^)2330 IF N=0 THEN AREA=0

2340DX=(T3-T2)/N2350 FX=42360Z(0)=T2:Y(0)=EXP(-(Z(0)/ArB):SUM=Y(0)2370 FOR 1=1 TON

2390 Y(I)=EXP(-(Z(I)/ArB)2400 IF I=N THEN FX=12410 SUM=SUM+FX'Y(I)2420 IF FX=4 THEN FX=2 ELSE FX=42430 NEXT I2440 AREA=DX'SUM/3

2500 TECHNOLOGY ADJUSTMENT MODULE2510 Y=02520 FOR 1=1 TO 162530 IF OP$(I) = "DELETE" THEN GOTO 25602540 FMAT(I) = FMA(I)*(l+TG(I)r(YR-1986)2550 Y=Y+1/FMAT(I)

S-5

2560NEXTI2S70TVFMA=1/Y

2700 'DETERMINE CRITICAL FMA2710 YY=02720 FOR 1 = 1 TO 162730 IF OP$(I) = "DELETE" THEN GOTO 27602740 FMAC(I) = FMAS(I)/PA(I)2750 YY=YY+1/FMAC(I)2760 NEXT I2770 CVFMA=1/YY

2800 'MODULE TO DETERMINE RELIABILITIES - CRITICAL FAILURES ONLY2810 VR=12820 FOR J=l TO 162830 TO=GOH(J):T1 =TO+LOH(J):T2 =T1 +TOH(J)2840 T3=T2+OOH(J):T4=T3+ROH(J)2850 IF OP$(J) = "DELETE" THEN R(J) = 1:GOTO 29002860L1 = 1/FMAC(J):L2=LF'L12870 A=(BT(2r(B-l)/Lir(l/B)2880 R(J)=EXP(-Ll'(T2+TO-Tl)-L2'Cn-TOKr3/ArB+(T2/ArB-Ll-(T4-T3))2890 VR=VR'R(J)2900 NEXT J

3000 'MTBM CALCULATIONS BY WUC3005 PROR=W(4)/(W(1) + W(2)+W(3)+W(4)):PP=1-PROR3010 *WBS 1,2 & 3 AIRFRAME "••3020 FMA11 = 15^3H-.006057»W(2>-.137575'SQR(W(1)+W(2)+W(3)+W(4)>.000723'V(3)3022 EPFMA11<1.4 THEN FMA11 = 1.4302SFMA(I) = FMAH/CPP*P1):FMA(2) = FMA11/(PP*P2) '="3030 MH11 = 16J732-3511567*W(3)/V(2>-.74556«LOG(X1)3031 IF MH1K 3.9 THEN MH=3.9 '- .3032MHMA(1)=MH11:MHMA(2)=MH11 ' C,.:.3040 ABU = .031213+1.956E-07*X1-1.54S6E-04*SQR(X1)3041 IF AB11<=0 THEN AB11=.00128 • . . . • -3042 IF AB11>.02065 THEN AB11=.02065 ; -•3045 PA(1)=AB11:PA(2)=AB11 -3050PF(l)=.0835:PF(2)=.0835:PF(3)=(.0835+.088)/23054 Rll = .1934-6309Bfl7»W(3)3055 R12=.20268+.000588'V(12)3060 RR(1)=R11:RR(2)=R11:RR(3)=(Rll+R12)/23100 -WUC12 AIRCREW COMPARTMENT .............3 1 1 0FMA12 = 3428.49-.0142*XW23.96*LOG(Xl) + 11.05'SQR(X1) + 111J67»X(3>360.72'SQR(X(3))+.01865*W(3>4-83566«SQR(W(3)>^5T85'(X(3)+X(4))3112 IF FMA12<5.6 THEN FMA12=5.6 ' 25TH PERCENTILE RANGE3115TP=P3'PP/FMA11+1/FMA12:FMA(3)=1/TP 'CHECK LINE 3715 FOR FMA(3)3120 MH12=7.0855-1.6667/SQR(X(3) + X(4)) + .098778*(X(2)+X(4))3121 IF MH12<3^ THEN MH12=3.23123 MHMA(3)=((1/FMA11)'MH11+(1/FMA12)*MH12)/(1/FMA11+1/FMA12) -3130AB12=.04232+33775EWX1-2^1883E-04*SQR(X1)3131 IF AB12>.02 THEN AB12=.023135 PA(3)=(AB11/FMA1H-AB12/FMA12)/(1/FMA11+1/FMA12)3200 WUC13/WBS5 LANDING GEAR SYSTEMS ••••••••••••••••3210 SMA13=22J723-.00313*V(3)+.19511'X2^S.47476'SQR(V(4))+.003161*W(5)- 171441*SQR(W(5))3211 TMA(5)=SMA13*(GOH(5)+LOH(5) +TOH(5)+OOH(5)+ROH(5))3212 IF SMA12<.4 THEN SMA12=.43213 FMA(5)=72.4+14J68*V(4)+.0994»X2-1Z41<LOG(X1>65.6»SQR(V(4)>.00568»W(5)+18J98'LOG(W(5))3214 IF FMA(5) < 1.4 THEN FMA(5)=1.43215 TMA(5)=SMA13'(GOH(5)+LOH(5) +TOH(5) + OOH(5)+ROH(5))3220 MHMA(5)=-156.95 -h55.984'LOG(W(5))-6.095'(LOG(W(5)))"2+^12817'(LOG(W(5)))'>33221 IF MHMA(5) < 1.9 THEN MHMA(5)=1.9

S-6

3230 AB13=-2.4321 + .0059112«X2+1.1457'LOG(X2)-33925*SQR(X2)3231 IF AB13<0 THEN PA(5) = .0018S ELSE PA(5)=AB133232 IF PA(5)>.08 THEN PA(5) = .083250 PF(5) = .02774-4.07E-06*X1-.00194'X2+.19316*SQR(V(4)) + .OOT156'SQR(W(13))3251 IF PF(5)<.134 THEN PF(5) = .1343252 IF PF(5) > .54 THEN PF(5) = 343260 RR(5) = .8639-.02963'X23261 IF RR(S)<.22 THEN RR(5) = .223300-WUCM WBS 12 FLIGHT CONTROLS ••••3310 FMA(12) = 26.29-1.1136*SQR(W(12)) + .9516»V(5)-1.9'V(6) + 3S05'X2-.00357*V(3)3312 IF FMA(12)<2.8 THEN FMA(12)=2.83320 MHMA(12)=26-238-1.1067*V(5>1.6658*V(6>.00328»V(3) + .0006018'X2-6J827*LOG(W(12)) + 14.289»SQR(V(5))3321 IF MHMA(12)<2.1 THEN MHMA(12)=2.13330 AB14=.7119S3-.1881388*LOG(X2) + .0209882*SQR(X2)3331 IF AB14<0 THEN PA(12)=6.000001E-04 ELSE PA(12)=AB143332 IF PA(12) > .08128 THEN PA(12) = .081283350 PF(12)=5.51246+.002663*V(5)-.000566'W(12)-1.193*LOG(W(12))+-105S6*SQR(W(12))3351 IF PF(12)<-04 THEN PF(12) = .043352 IF PF(12) > 39 THEN PF(12) = 293360 RR(12) = .4527-.0006677*X23361 IF RR(12)<0 THEN RR(12) = .073400 "ffVC2A APU3410 FMA(9) =4996-525-1.906'V(7)+4635'SQR(V(7)>2.735*W(9)+284^49'SQR(W(9))-1642.99'LOG(W(9))3411 IF FMA(9)<14.5 THEN FMA(9) = 1433420 MHMA(9)=^51.4+.09054*V(7>2.9654»SQR(V(7)) + -2657«W(9>26.1'SQR(W(9)) + 1503*LOG(W(9))3421 IF MHMA(9)<5.2THEN MHMA(9)=523440 PA(9) = .0643 4 5 0PF(9)=-109£3-.1645'LOG(Xl)+.1427*V(7)-6.1517*SQR(V(7)) + 15.751*LOG(V(7))+.066'W(9)-5.6832'SQR(W(9))+29.071 «LOG(W(9))3451 IF PF(9) < .03 THEN PF(9) = .033452 IF PF(9) > 39 THEN PF(9) = 393460 RR(9)=^79-.0007512*SQR(X1)3461 IF RR(9)<0 THEN RR(9)=.013500'WUC41/47 WBS14 ENVIRONMENTAL CONTROL •••••••3510'FMA(14)=34.08071-.42487*W(14r2 ;

3511 FH41=454J87-.000547*XH- 21'X2-1073185<LOG(X2)3512FH47=6613.12-1.485*X2-13583'LOG(X1)+73J8'(LOG(X1))'>2-.72S852*X1/X23513 Z=1/FH41-H/FH47:FMA(14) = 1/Z3515 IF FMA(14)<7.68 THEN FMA(14)=7.683520 MH41=.6886774'LOG(X1)3521 MH47=5.7432+.018525'LOG(X1>3J6575E-03'SQR(X1)3522 MHMA(14)=(MH41/FH4H-MH47/FH47)/(1/FH41-H/FH47)3523 IF MHMA(14)<1! THEN MHMA(14)=1!3530 PA(14)=.082199+5.0072E-07'XW.0612B04*SQR(X1)3531 IF PA(14) < 0 THEN PA(14)=.001523532 IF PA(14)>.05222 THEN PA(14) = .052223550 PF47=23.852-.00902*X2-5 J47*LOG(X1)+J01'LOG(X1)"2-.00212'X1/X23551 IF PF47< .02 THEN PF47=.023552 IF PF47>33 THEN PF47=333553 PF(14)=(.0932/FH41 + PF47/FH47)/(1/FH41+1/FH47)3555 R41 = J294-8.914E4)5*W(14)3556 IF R4KO THEN R41 = .1683557 R47=.6026-.0006758'SQR(X1)3560 RR(14)=(R41/FH41 + R47/FH47)/(1/FH41+1/FH47)3600 •WUC 42/44 WBS 10 ••• ELECTRICAL SYS ••••••3 6 1 0FMA(10)=1193.13-.0755»W(10)+6.758773*SQR(W(10))-.715596*X2-167.24'LOG(X1)+2^308*SQR(X1)+29.10236'LOG(V(7))-.00127'VC7T23611 FH44=13613FH42=13614 IF FMA(10)<5.15 THEN FMA(10)=5.153620'MHMA(10)=-183923+1694.6'LOG(Xl)-92Atl2'(LOG(Xl))"2+27629/SQR(LOG(Xl))+2*LOG(Xl)'v3

S-7

3621 MH42 = -95.161 + 20 J158'LOG(X1>.98356'(LOG(X1))"23622MH44=2m04+474.11'I^G(XlM52395'IX>G(X2>.146285*Xl/X2-2769^^3623 MHMA(10)=(MH42+MH44)/23624 IF MHMA(10)<1! THEN MHMA(10)=4.13630 PA(10) =-39.95984 + 11.09214'LOG(X1)-1.0178226#*LOG(X1)'S2 + .0309075«LOG(X1)"33631 IF PA(10)< =0 THEN PA(10)=. 002483632 IF PA(10)>.142 THEN PA(10) = .1423650PF42=-26^65-.00271'V(7)+.005143'W(10)-.74878*SQR(W(10))+6.62irLOG(W(10))3651 IF PF42<.054 THEN PF42=.0543652 IF PF42>.53 THEN PF42=.533653 PF44 = 3.061 + 1.178E-05'X1-.000127* V(3)-.42392*LOG(X1) + .13468*SQR(X2)3654 IF PF44<.03 THEN PF44=.033655 IF PF44>.47 THEN PF44 =.473656 PF(10)=(PF42/FH42+PF44/FH44)/(1/FH42-H/FH44)3660RR42=-38533-.001»X2 + .17715'LOG(X2) -3661 IF RR42<.23 THEN RR42=.23:IF RR42>.539 THEN RR42=.5393662RR44=2.3651+.00201»X2-.41152*LOG(X2)3663 IF RR44<.S3 THEN RR44=.53:IFRR44>.872 THEN RR44=.8723665RR(10)=(RR42/FH42+RR44/FH44)/(1/FH42-H/FH44)3700 ""'WBS4 THERMAL PROTECTION SYSTEM .........3710 FMAC4)=FMA11/PROR3720 MHMA(4) = MH113730 PA(4) =AB11:PF(4) = .0835:RR(4) = ,1943800 WUC45 WBS11 HYDRAULICS SYS ..................381<FMA(11) = 396.2S8-.00622*V(3) + 35.635'V(8>779.83'SQR(V(8)) +975 -56'LOG(V(8)) + 8.812899*SQR(W(11))-105.728'LOG(W(11))3812 IF FMA(11)<4.7 THEN FMA(11)=4.73820 MH45=2.41235'LOG(X1)-.16306'LOG(X1) 23821 MHMA(11)=MH453822 IF MHMA(11)<2.4 THEN MHMA(11)=2.43830 PA(ll)=5000J535#-7578.183/SQR(IX)G(Xl)H53.612*LOG(Xl)+24^005*LOG(Xl)A2- 276227'LOG(Xl)/<33831 IF PA(11) < =0 THEN PA(11) = .000843832 IF PA(11) > .1304 THEN PA(11) = .130438SOPF(11) = .07614-.00181*X2+.001543*SQR(X1) . . . . . .3851 IF PF(11)<. 014 THEN PF(11)=. 0143852 IF PF(11)>33 THEN PF(11)=333860 RR(11)= 3683900'WBS13 AVIONICS «•••••«•««•»«••••3910 FMA(13)=-36.917-4J*V(10)+45.756*SQR(V(10)>.123088*W(13)/V(10)-h.0236«W(13>2.4534'SQR(W(13))3912 IF FMA(13) < 15 THEN FMA(13) = 153920 MHMA(13) = 131395 + 1.0394*V(11)-9.035'SQR(V(10))-.01S4*W(13) + 2 64*SQR(W(13)>26.193'LOG(W(13))3921 IF MHMA(13)<4.6 THEN MHMA(13)=4.63930 PA(13) = .0502749+1605132E-07»X1-2J88197E-04'SQR(X1)3931 IF PA(13)<0 THEN PA(13)=. 001523932 IF PA(13) > .02376 THEN PA(13) = .023763950 PF(13) = 7. 1662 + .0209* V(l 1)-.00128*W(13) + .1774*SQR(W(13))-L734*LOG(W(13)) + .0067 V(13)/V(10)3951 IF PF(13)<. 193 THEN PF(13)=. 1933952 IF PF(13) > .532 THEN PF(13) = 5323960 RR(13) = 3973£4.2659E-07*X1+2.163S&O4*SQR(X1)3%1 IF RR(13)<0 THEN RR(13)= J353962 IF RR(13)>.726 THEN RR(13)=.7264000 WUC49 MISC UmJTIES .......................4010 ' WUC49/96 WBS15 PERSONNEL PROVISIONS ................4 0 2 0

054'LOG(W(15))

4023 IF FMA(15) <46.7 THEN FMA(15) =46.74030MHMA(15)=951317+.03508»X2-.000721*W(15H-52'SQR(X(3))4031 1MH49=.0831*LOG(X1)"2-.0116*X1/X24033 IF MHMA(15)<23 THEN MHMA(15)=2J4040 PA(15)=. 01854050PF49=.19888+4.938&fl6'Xl-.00205*SQR(Xl)+.0004877*V(7)

S-8

4051 IF PF49<.002 THEN PF49 = .0024052 IF PF49>.45 THEN PF49=.454053 PF96=-5.4686+ .1683S'X2-.00448*V(3) + .36521 •X(4>4-1528*SQR(X(4)) +• .178*SQR(W(15))4054 IF PF96<.23 THEN PF96=.234055 IF PF96>.98 THEN PF96=.984057 PF(15) = (PF49 + PF96)/24060 RR(15) = .2744100 •• ..... WUC23 PROPULSION SYSTEM *"* WBS 6, 7 & 8 ........4160 FOR 1=6 TO 84161 RR(I) = .6211-.0024872*SQR(W(I))4162 IF RR(I)<.157 THEN RR(I)=.1574163 'IF RR(D>.5120001 THEN RR(I) = .51200014165 PF(I) = 1.14633 +4.572E-05*W(I)-.0114S6*SQR(W(I))4166 IF PF(I)< 2 THEN PF(I) = .24167 IF PF(I)>.725 THEN PF(I)=.7254170 FMA(I)=34.H-9.853001E-04*W(I)-.312232'SQR(W(I))4171 IF FMA(I) < 1.4 THEN FMA(I) = 1.44175 MHMA(I)=52.6324+.0009122*W(I>3936'SQR(W(I))4176 IF MHMA(I)<4.1 THEN MHMA(I)=4.14178 PA(I)=.048164-.0001268'X24179 IF PA(I)<.0013 THEN PA(I)=.00134180 NEXT I4200 ' WUC91/93/97 WBS 16 ..... RECOVERY & AUX SYS ••••••••4210 FMA(16) = 7549.1-.0165«X1 +4*X2-999.76*LOG(X1) + 16.847*SQR(X1>4-225*(X(3) + X(4))4211 IF FMA(16)<17.9 THEN FMA(16) = 17.94220 MHMA(16) = -57.9 + 1.4639E-04*X1 + 8.23732*LOG(X1)-.151436*SQR(X1)4221 IF MHMA(16)<1.7 THEN MHMA(16) = 1.74230 PA( 16) = .0046784253 PF91=4.654-.45718*LOG(X1)+.00242'SQR(X1)4254 IF PF9K.011 THEN PF91=.0114255 IF PF91:>.84 THEN PF91=At4256 R97=2.532-.22837*LOG(V(3))4257 PF(16) = (PF91 + .287+ .01)/34258 IF R97<0 THEN R97=.1284260 R91=23489-35852»LOG(X(2))4261 IF R9KO THEN R91 = . 461 'SET EQUAL TO MEAN VALUE4262 IF R91>1 THEN R91 = .4614263 IF R97>1 THEN R97=.9684265 RR(16)=KR91 + R97)/24300 'APPLY MTBM & MHMA CALIBRATION FACTORS4310 FOR 1 = 1 TO 16

4325 MHMA(I) = CM(I)<MHMA(I)4330 NEXT I5500 'SCHEDULED MAINTENANCE MODULE5540 SCHP = -3.861213-.0449'X2 + 3^794'LOG(X1) + .02297*SQR(X1)-.0176»LOG(X1)'>3-7.289«LOG(X2) + 2J6973'SQR(X2)5550 IF SCHP<.17THEN SCHP=.175560 IF SCHP>.665 THEN SCHP=.6655569'5570 •VEHICLE ROLL-UP - UNADJUSTED MTBM5575 Y=05580 FOR 1=1 TO 165590 IF OP$(I)= "DELETE11 THEN GOTO 56105600Y=Y + 1/FMA(I)5610 NEXT I5620VFMA=1/Y

6999'7000 "MANPOWER COMPUTATION MODULE ......7005 TMA=ftVMH=fcAMHMA=ftIK=ftTOMH=0:TFMH=0-.APF=0:TMP=07010 MANF=(4.348'5'8)/(X(9)'(1-X(10))) 'HRLY AVAIL FACTOR7020 FOR 1=1 TO 16

S-9

7030 IF OP$(I) = -DELETE" THEN GOTO 71407035KK=KK+17040 THRS(I)=GOH(I)+LOH(I)+TOH(I)+OOH(I) + ROH(I)7045 MA=THRS(I)/FMAS(I)7046 TMA=TMA+MA7050 MH(I)=MA'MHMA(I)7055 AMHMA=AMHMA+MHMA(I)7060 VMH=VMH+MH(I)7070 MEN=(MH(I)'X(13))/(X(9)*(1-X(10)))7080 MP(I)=INT(MEN+.999)7085 TMP=TMP+MP(I)7090 OMH(I)=(1-PF(I))*MH(I)7100 FMH(I)=PF(I)'MH(I)7110 TOMH=TOMH+OMH(I)7120 TFMH=TFMH+FMH(I)7130APF=APF+1-PF(I)7135 VMOH=VMOH+MH(I)*X(13)7140 NEXT I7150 APF=APF/KK7160 AMHMA=AMHMA/KK7170 SMP=(SCHP*VMH*X(13))/(X(9)*(1-X(10)))7180 SMP=INT(SMP+.99)7190 TMP=TMP+SMP

7499'7500 ' DISPLAY MODULE FOR MAINTAINABILrrY REPORT7510 CLS:COLOR 147520 PRINT TAB(25) "MAINTAINABILTY REPORT"7530 PRINT TAB(1) "VEHICLE IS ";VNAM$;TAB(35) "DATE ";DATE$;TAB(60) TIME: ";TIME$7548 COLOR 77550 PRINT TAB(1) "WBS";TAB(32) "MANHR/MA";TAB(50) TOT MA";TAB(65) TOT MANHRS"7555 PRINT7570 FOR 1=1 TO 167580 IF OP$(I)="DELETE" THEN GOTO 75927590 PRINT TAB(1) WBS$(I);TAB(32) MHMA(I);TAB(50) THRS(I)/FMAS(I);TAB(65) MH(I)7592 NEXT I7593 PRINT:COLOR 117594 PRINT TAB(5) "SCHEDULED";TAB(65) SCHP'VMH7595 COLOR 157600 PRINT TAB(5) TOTALS";TAB(32) AMHMA;"(AVG)";TAB(50) TMA;TAB(65) VMH+SCHP'VMH7610 COLOR 147620 INPUT "ENTER RETURN TO CONTINUE_";RET7640 CL&COLOR 147650 PRINT TAB(25) "MAINTAINABILTY REPORT - page 2"7660 PRINT TAB(1) "VEHICLE IS ";VNAM$;TAB(35) "DATE: ";DATE$;TAB(60) TIME: ";TIME$7680 COLOR 77690 PRINT TAB(1) "WBS";TAB(32) "ON-VEH MH";TAB(47) "OFF-VEH MH";TAB(60) "PERCENT ON-VEH"7700 PRINT7710 FOR 1=1 TO 167720 IF OP$(I)='DELETE" THEN GOTO 77407730 PRINT TAB(1) WBS$(I);TAB(32) OMH(I);TAB(50) FMH(I);TAB(65) 1-PF(I)7740 NEXT I7750 PRINTiCOLOR 77755 PRINT TAB(5) "SCHEDULED";TAB(32) .98«SCHP*VMH;TAB(50) .02'SCHP*VMH7760 COLOR 157770 PRINT TAB(5) TOTALS";TAB(32) TOMH+.98»SCHP*VMH;TAB(50) TFMH+.02'SCHP*VMH;TAB(65) APF;"(AVG)"7780 COLOR 147790 INPUT "ENTER RETURN TO CONTINUE_",-RET7800 CL&COLOR 147810 PRINT TAB(25) "MAINTAINABILrV REPORT - page 3"7820 PRINT TAB(1) "VEHICLE IS ";VNAM$;TAB{35) "DATE: ";DATE$;TAB(60) TIME: ";TIME$7830 'PRINT TAB(1) "MNHR ADJ FAC";MANF

S-10

7840 COLOR 77850 PRINT TAB(1) "WBS";TAB(30) "MANHRS/MSN";TAB(45) "MANHRS/MO";TAB(60) "NBR PERSONNEL"7860 PRINT7870 FOR 1=1 TO 167880 IF OP$(I) = "DELETE" THEN GOTO 79007890 PRINT TAB(1) WBS$(I);TAB(30) MH(I);TAB(45) X(13)'MH(I);TAB(60) MP(I)7900NEXTI7910 PRINT:COLOR 117915 PRINT TAB(5) "SCHEDULED";TAB(30) SCHP*VMH;TAB(45) X(13)'SCHP*VMH;TAB(60) SMP7920 COLOR 157930 PRINT TAB(5) "TOTAL";TAB(45) VMOH;TAB(60) TMP:COLOR 147932 'PRINT TAB(5) "AVAIL HRS/MO = ";X(9);TAB(40) "INDIRECT WORK=";X(10)7940 COLOR 147950 INPUT "ENTER RETURN TO CONTINUE...";RET

7999'8000 'SPARES CALCULATIONS8010 ARR=0:TS=0:KK=0:TNR=08020 FOR 1=1 TO 168030 IF OP$(I)="DELETE" THEN GOTO 81808040NR(I) = RR(I)«(THRS(I)/FMAS(I)) ' MEAN NBR REMOVALS8045MN=NR(I)8050 GOSUB 8300 'COMPUTE FILL RATE RQMT - POISSON DISTR8055S(I)=STK:FR(I) = F8060 TNR=TNR+NR(I)8150 ARR=ARR+ RR(I)8160TS=TS+S(I)8170KK=KK+18180 NEXT I8190 ARR=ARR/KK

8300 ' COMPUTE SPARES USING POISSON DIST8310 P=EXP(-MN)8320 IF P> =X(11) THEN JD=1:GOTO 83708330JD = 1:F=P8340P=P'MN/JD8350JD=JD+1:F=F+P8360 IF F<X(11) THEN GOTO 83408370STK=JD-1

8499'8500 ' DISPLAY SPARES RESULTS8510 CL&COLOR 148520 PRINT TAB(25) "SUBSYSTEM SPARES REPORT"8530 PRINT TAB(1) "VEHICLE IS ";VNAM$;TAB(35) "DATE: ";DATE$;TAB(60) "TIME: ";TIME$8545 COLOR 78550 PRINT TAB(1) "WBS":TAB{25) "REM RATE";TAB(38) "AVG DEMAND";TAB(50) "SPARES RQMT";TAB(65) "FILL RATE"8555 PRINT8570 FOR 1=1 TO 168580 IF OP$(I)="DELETE" THEN GOTO 86008590 PRINT TAB(1) WBS$(I);TAB(30) RR(I);TAB(41) NR(I);TAB(56) S(I);TAB(65) FR(I)8600NEXTI8610 PRINT8620 COLOR 158630 PRINT TAB(5) TOTALS";TAB(27) ARR;"(AVG)";TAB(43) TNR;TAB(55) TS8640 INPUT "ENTER RETURN TO CONTINUE_.";RET

8999'9000 •••••• DISPLAY MODULE FOR RELIABILITY REPORT ••9010 CL&COLOR 149020 PRINT TAB(25) "RELIABILITY REPORT"9030 PRINT TAB(1) "VEHICLE IS ";VNAM$;TAB(35) "DATE: ";DATE$;TAB(60) TIME: ";TIMES

S-ll

9048 COLOR 79050 PRINT:PRINTTAB(1) "WBS*;TAB(2S) "CALIBRATED MTBM";TAB(48) TECH ADJ";TAB(61) "SPACE ADr9055 PRINT9070 FOR 1 = 1 TO 169080 IF OP$(I) = "DELETE' THEN GOTO 90929090 PRINT TAB(1) WBS$(I);TAB(35) FMA(I);TAB(48) FMAT(I);TAB(61) FMAS(I)9092NEXTI9093 PRINT9095 COLOR 159100 PRINT TAB(5) "VEfflCLE";TAB(35) VFMA;TAB(48) TVFMA;TAB(61) SVFMA9105 COLOR 149110 INPUT "ENTER RETURN TO CONTINUE_";RET9120 CL&COLOR 149130 PRINT TAB(20) "RELIABILrry REPORT - page 2"9140 PRINT TAB(1) "VEHICLE IS ";VNAM$;TAB(35) "DATE ";DATE$;TAB(60) "TIME: ";TIME$9160 COLOR 79170 PRINT TAB(1) "WBS";TAB(33) "CRrnCAL";TAB(48) "CRrnCAL";TAB(65) "SUBSYS"9171 PRINT TAB(33) "FAIL RATE";TAB(48) "MTBM";TAB(65) "MSN RELIABILITY"9180 PRINT9190 FOR 1 = 1 TO 169200 IF OP$(I)="DELETE" THEN GOTO 92209210 PRINT TAB(1) WBS$(I);TAB(33) PA(I);TAB(48) FMAC(I);TAB(65) R(I)9220NEXTI9230 PRINT9240 COLOR 159250 PRINT TAB(5) "VEfflCLE";TAB(48) CVFMA;TAB(6S) VR9260 COLOR 149270 INPUT "ENTER RETURN TO CONTINUE.»";RET

9500 "MODULE TO WRITE FHBMA TO A FILE9520 INPUT "ENTER FILE NAME";DNAM$9530 OPEN DNAMS FOR OUTPUT AS #19540 FOR 1=1 TO 169550 WRITE #1,FMAT(I),FMAS(I),FMAC(I)9560NEXTI9570 CLOSE #1

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9600'MODULE TO WRTTE INPUT DATA TO A FILE9605 INPUT "ENTER FILE NAME";DNAM$9610 OPEN DNAMS FOR OUTPUT AS #29615 FOR 1=1 TO 169620 WRITE #2,WBS$(I),Wa),MW(I),CM(I)9621WRTTE #2,GOH(I) JX)H(I),TOH(I)IOOH(I),ROH(I)9622 WRITE #2,OP$(I)9625 NEXT I9630 FOR 1 = 1 TO 139635 WRITE #2J<IAM$(I),X(I),SNAMS(I),V(I)9640NEXTI9645 FOR 1=0 TO 49650 WRITE #2,T(I)96S5NEXTI9690 CLOSE #2

9700 'MODULE TO DISPLAY VEHICLE TURN TIME9703 GOSUB 12000 'COMPUTE CREW SIZES9705 TT=09706 SUM=0:CT=09710 FOR 1=1 TO 169715 IF OP$(I) = "DELETE" THEN GOTO 97359716 CT=CT+19720TSKr(I)=(l-PF(I))'MHMA(I)/C(I) 'ON-EQUIP TASK TIME9730 TT=TT+(THRS(I)/FMAS(I))'TSKT(I)

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9733 SUM=SUM+TSKT(r)9735NEXTI9740 SCHT=.98*SCHP*VMH/X(12)9750 GTr=TT+SCHT:ATSK=SUM/CT9800 ' DISPLAY VEHICLE TURN TIME9810 CL&COLOR 149820 PRINT TAB(25) "VEHICLE TURN TIME REPORT"9830 PRINT TAB(1) "VEHICLE IS ";VNAM$;TAB(35) "DATE ";DATE$;TAB(60) "TIME: ";TIME$9840 PRINT9845 COLOR 79850 PRINTTAB(1) "WBS";TAB(22) "AVG CREWSEZE";TAB(40) "AVG (ON) TASK TIME (HRS)";TAB(57) "AVG ON-VEH CLOCKHRS"9855 PRINT9870 FOR 1=1 TO 169880 IF OP$(I)="DELETE" THEN GOTO 99009885 TEMP=(THRS(I)/FMAS(I))TSKT(I)9890 PRINT TAB(1) WBS$(I);TAB{30) C(I);TAB(45) TSKT(I);TAB(59) TEMP9900NEXTI9910 PRINTiINPUT "ENTER RETURN.....";RET9920 CL&COLOR 149921 PRINT TAB(25) "VEHICLE TURN TIME REPORT - page 2"9922 PRINT TAB(1) "VEHICLE IS ";VNAM$;TAB(35) "DATE: ";DATE$;TAB(60) "TIME: ";TIME$9923 PRINT9924 COLOR 15:PRINT:PRINT TAB(52) "MAX TURN TIMES":PRINT9925 PRINT TAB(5) "AVG VEH TASK TIME";TAB(55) ATSK;"HRS"9930 PRINT TAB(5) "SCHD MAINT MSN TASK TIME";TAB(55) SCHT.'HRS"9931 PRINT TAB(5) "MAX TURN TIME NO SCH MAim*;TAB(55) TT;"HRS"9932 PRINT TAB(5) "MAX TURN TIME WITH SCH MAINT";TAB{55) TT+SCHT;"HRS"9940 PRINT TAB(5) "MISSION TIME -INC GRND TIME";TAB(55) T(0)+T(4);"HRS"9945 VTT=T(0)+T(4)+OTT+SCHT9946 DVTT=(T(0)+T(4))/24+(OTr+SCHT)/89950 PRINT TAB(5) TOT VEHICLE TURNAROUND TIME";TAB(55) VTT;'HRS"9951 PRINT TAB(5) "TOT VEHICLE TURNAROUND TIME";TAB(55) DVTT;"DAYS"9955 PRINT TAB(5) "MISSIONS/MONTH/VEHICLE";TAB(55) 21/DVTT9960 PRINT TAB(5) "FLEET SIZE ";TAB(55) INT(X(13)/(21/DVTr)+.99)9985 LOCATE 21,10:INPUT "ENTER RETURN TO CONTINUE...";RET

10000 'INPUT DATA10005 DATA 1.1 WING GROUP.1.2 TAIL GROUP.13 BODY GROUP,1.4 TPS10010 DATA 1.5 LANDING GEAR.1.6 PROPULSION,1.7 PROPULSION-RCS10020 DATA 1.8 PROPULSION-OMS,1.9 PRIME POWER.1.10 ELECTRIC CONV/DISTR10030 DATA 1.11 HYDRAULICS/PNEUMATICS,1.12 ACTUATORS,1.13 AVIONICS10040 DATA 1.14 ENVIRONMENTAL CONTROL.1.15 PERSONNEL PROVISIONS10050 DATA 1.16 RECOVERY & AUX SYSTEMS10150 DATA DRY WOT (LBS),LENGTH+WING SPAN (FT),CREW SIZE^BR PASSENGERS10152 DATA TECHNOLOGY YR10155 DATA DEFAULT TECH GROWTH FACTOR, WffiBULL SHAPE PARAMETER10160 DATA LAUNCH FACTORAVAIL MANHRS/MONTILPERCENT INDIRECT WORK10170 DATA SPARE FILL RATE OBJAVG CREW SEE-SCHD MAINT,PLANNED MISSIONS/MONTH10180 DATA WGTIND O-PCT/1-EQS11000 CLS:PRINT:PRINT TAB(5) "SECONDARY INDEP VARIABLEy:PRINT11005 IF MODE=1 OR MODE=2 THEN RETURN11010 PRINT TAB(1) "NBR";TAB(10) "VARLABLE";TAB{35) "CURRENT VALUE'11020 PRINT11040 FOR 1=1 TO 1211050 PRINT TAB(1) I;TAB(7) SNAM$(I);TAB(35) V(I)11060 NEXT I11070 PRINT:INPUT "ENTER NBR OF VARIABLE TO BE CHANGED - 0 IF NONE";NBR11075 IF NBR>16 THEN GOTO 1100011080 IF NBR=0 THEN RETURN11090 INPUT "ENTER NEW VALUE";V(NBR)11100 GOTO 11000

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11110 '11120 'SUBROUTINE TO COMPUTE SECONDARY VARIABLES11122'WETTED AREA11123 V(3)=486.026+.1510165'X(2)*211130 'NBR WHEELS11140 V(4)=2.189572+6.66297E-OS*X(1)-138718E-10'X(1)*211150 V(4)=CINT(V(4))11160 IF V(4)<3 THEN V(4)=311170 'NBR CONTROL SURFACES11180 V(6)=3.588737+.0005281 *X(1) + .09493*X(2>.00517«V(3)11190 IF V(6)<6 THEN V(6)=611200 V(6)=INT(V(6))11210 "NBR ACTUATORS11220 V(5)= l-.001425'Xl+2.0752E 'Xrc+.007467*V(3H.0377*SQR(11230 IF V(5) <5 THEN V(5) =511240 V(5)=INT(V(5))11280 'KVA MAX11290 V(7)=-214.812-K001098*X(1)+25.1571'LOG(X(1))11300 IF V(7)<11 THEN V(7) = ll11340'NBR AVIONICS SYSTEMS (TOTSUBS)11350 V(10)= 0.4242-1.879E-05»X(1)+6.192823*U>G(X(1))11360 IF V(10)<9 THEN V(10)=911370 V(10) = ONT(V(10))11420 "NBR DIFFERENT AVIONICS SUBSYSTEMS11430 V(ll)=9.674-1.858»LOG(X(l)) + .87684* V(10)+1.4557*LOG(W(13))11440 IF V(ll)<5 THEN V(11)=5:IF V(ll)>V(10) THEN V(ll)=V(10)11450 V(ll) = ONT(V(11))11460 'BTU COOLING11470 V(12)=-1114.52-12.0178*X2+.0094G5'X2*2+230.872*SQR(X2)11480 IF V(12)<25 THEN V(12)=2511490 "MAX PERSONS = CREW + PASSENGERS11500 X(62)=X(7)+X(8) -11510 "NBR HYDRAULICS SUBSYSTEMS11520 V(8)=13.48-.56854'X2+.002409»V(3)+.433276>SQR(X1) ' ~' '11530 IF V(8)<8 THEN V(8)=811540 V(8)=ONT(V(8)) :11550'NBR INTERNAL FUEL TANKS11560 V(9)=-13.2236+1.851772*LOG(X(1))11570 IF V(9)<2 THEN V(9)=211580 IF V(9)>12 THEN V(9) = 1211590 V(9)=CINT(V(9))11620 "FUSELAGE AREA11630 V(l)=-«832.74+.082862'X(l) + 1274.76«LOG(X(l)).32.456'SQR(X(l))11640 IF V(l) <478 THEN V(l) =47811650 'FUSELAGE VOLUME11660 V(2)=-47618^+22143'LOG(X(2)>5743.09»SQR{X(2)) + .42623'X(2)"211670 IF V(2) <571 THEN V(2) =57111680 GOSUB 11000 'DISPLAY MENU

11700 DATA FUSELAGE AREA^FUSELAGE VOLUME,WETTED AREAlino DATA NBR WHEELSJJBR ACTUATORS,NBR CONTR SURFACESJCVA MAX11720 DATA NBR HYDR SUBSYSJMBR FUEL TANKS (INTERNAL) l"11730 DATA TOT NBR AVIONICS SUBSYS ;

11740 DATA NBR DIFF AVIONICS SUBSYS3TU COOLING ;

11750 TECH GROWTH RATES r

11760 DATA .082 082 082 082 033 011 011 011 054,0 092 05611770 DATA .2i.0062,036,.08311780 "WGT DISTRIBUTION PERCENTAGES11790 DATA .091,.003r140,.099,.053,.019,.029,.017,.151r.05911800 DATA .021,.007,.061,.083,.070,.09712000 'CREW SIZE CALCULATIONS12110 C(l)=1 -.000032'V(3)+.009172*SQR(V(3))

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12120 C(2)=C(1):C(3)=C(1):C(4)=C(1) ,12130 C(12)=C(1):C(5)=C(1)12140 C(6)=2.43:C(7)=2.43:C(8)=2.4312150 C(9)=2.4312160 C(10)=-1.48-.002833*X2-t-.814656*LOG(X2)12170 C(ll) = C(10):C(14) = C(10)12180 C(13)=2.1812190 C(16) = 1.7893+9.871999E-04'SQR(X1)12195 C(15)=(C(10)+C(16))/2

12199'12200 'MODULE TO INPUT MOD FACTOR FOR MAINTENANCE12202 COLOR 912205 CL&PRINT TAB(20) "SUBSYSTEM MH/MA CALIBRATION FACTOR"12206 PRINT TAB(20) "CAL MH/MA = CAL FAC x COMPUTED-MH/MA"12210 PRINT TAB(3) "NBR SUBSYSTEM";TAB(45) "CAL FACTOR"12220 PRINT12230 FOR 1 = 1 TO 1612235 IF OP$(I) = "DELETE' THEN GOTO 1225012240 PRINT TAB(3) I;TAB(10) WBS$(I) TAB(45) CM(I)12250 NEXT I12260 PRINT:INPUT "ENTER NBR OF SUBSYSTEM TO BE CHANGED - 0 IF NONE";NBR12270 IF NBR=0 THEN GOTO 1229512280 INPUT "ENTER NEW FACTOR";CM(NBR)12290 GOTO 12205

12300 ' MENU TO DELETE A SUBSYSTEM12305 CLS:PRINT TAB(20) "OPTION TO DELETE A SUBSYSTEM":PRINT12310 PRINT TAB(3) "NBR SUBSYSTEM";TAB(45) "OPTION"12320 PRINT12330 FOR 1=1 TO 1612335 IF OP$(I)="DELETE" THEN COLOR 4 ELSE COLOR 312340 PRINT TAB(3) I;TAB(10) WBS$(I) TAB(45) OP$(I)12350 NEXTI12360 PRINT:INPUT "ENTER NBR OF SUBSYSTEM TO BE DELETED - 0 IF NONE";NBR12365 IF NBR>16 THEN GOTO 1230512370 IF NBR=0 THEN GOTO 1239512380 OP$(NBR)="DELETE"12390 GOTO 12305

12400 ' MENU TO DEFAULT ON TECH GROWTH FACTOR12403 COLOR 1312405 CLS:PRINT TAB(25) "OPTION TO USE DEFAULT RATE"12406 PRINT TAB(20) "FOR ANNUAL REUABUJTY GROWTH FACTOR":PRINT12410 PRINT TAB(3) "NBR SUBSYSTEM";TAB(45) "ANNUAL GROWTH RATE"12420 PRINT12430 FOR 1=1 TO 1612435 IF OP$(I)="DELETE" THEN GOTO 1245012440 PRINT TAB(3) I;TAB(10) WBS$(I) TAB(45) TG(I)12450 NEXTI12460 PRINT:INPUT "ENTER NBR OF SUBSYSTEM TO BE CHANGED - 0 IF NONE";NBR12465 IF NBR>16 THEN GOTO 1240512470 IF NBR=0 THEN GOTO 1249512480 TG(NBR)=X(6)12490 GOTO 12405

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the determination of operational and support

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