service bulletin -...

SERVICE BULLETINEngines, Systems & Services – Phoenix, Arizona

of 3TFE731-76-3065Feb 20/03

Copying, use or disclosure of information on this page is subject to proprietary restrictions.

REVISION TRANSMITTAL SHEET

This sheet transmits Revision 9 to Service Bulletin No. TFE731-76-3065 titled ENGINE CONTROLS –POWER CONTROL – Install Digital Electronic Engine Control (N1 DEEC).

This is a COMPLETE reissue. This bulletin has been reprinted in its entirety. Please remove anddiscard all pages of prior issues and replace with pages of this revision.

Reason for Revision:

NOTE: This revision DOES NOT require further action if in compliance with a previousissue.

Revision 8 was limited in distribution due to validation and parts availability. Therevision contained the following primary changes.

Revision 8:

Added Engine Model TFE731-4R-2S.

Updated the production incorporation points and production incorporation information.

Added N1 DEEC, Part No. 2119010-7000.

Updated the special program and warranty information.

Added reference to Service Bulletin TFE731-76-3055.

Added Table 4. As a follow on, this will result in changes to references to table numbers forN1 DEEC Fault Codes in the maintenance text.

Changed the letter O, to the numerical 0, in the Fault Description for Fault Codes 30, 31, and32.

Changed the reference from SG:4 to SG:X, and Confirm 4 to Confirm setting, in examples forSteps 2.G.(1)(e) and 2.G.(3)(b).

Deleted reference to Kit, ECTMplus, Part No. 831702-6/-13/-20, for Engine ModelTFE731-5-1J. Engine Model TFE731-5-1J, has been combined with all other engine modelsfor Kit, ECTMplus, Part No. 831702-6/-13/-20.


of 3TFE731-76-3065Feb 20/03


This service bulletin revision is revised to:

Add STC ST01756CH-D, for Engine Model TFE731-4R-2S.

Add No. 27 as the special program number.

Add another method of locating a listing of Honeywell authorized service facilities.

Delete reference to the revision number for service bulletins no longer applicable after comply-ing with this service bulletin. Service bulletins, regardless of revision, are no longer applica-ble.

Add a NOTE to reference revision (Rev 9) when entering this service bulletin as completed inthe Engine Log Book.

Section 1

Title page is revised to reflect latest revision date.

Paragraph D is revised to add No. 27 as the special program number and to add STCST01756CH-D for Engine Model TFE731-4R-2S.

Paragraph G is revised to add another method of locating a listing of Honeywell authorizedservice facilities.

Paragraph K is revised to delete reference to the revision number for service bulletins no lon-ger applicable after complying with this service bulletin. Service bulletins, regardless of revi-sion, are no longer applicable.

Section 2

Accomplishment instructions are revised to add a NOTE to reference revision (Rev 9) whenentering this service bulletin as completed in the Engine Log Book.

Section 3

The order form, following Material Information, is revised to add STC ST01756CH-D, for En-gine Model TFE731-4R-2S.


of 3TFE731-76-3065Feb 20/03


List of Effective Pages:

Page No. Date Page No. Date

1 Feb 20/03 2 Oct 11/02 3 Oct 11/02 4 Feb 20/03 5 Feb 20/03 6 Oct 11/02 7 Feb 20/03 8 Oct 11/02 9 Aug 27/01 10 Apr 10/01 11 Apr 10/01 12 Apr 10/01 13 Apr 10/01 14 Apr 10/01 15 Oct 11/02 16 Oct 11/02

17 Oct 11/02 18 Oct 11/02 19 Oct 11/02 20 Oct 11/02 21 Oct 11/02 22 Oct 11/02 23 Oct 11/02 24 Oct 11/02 25 Oct 11/02 26 Oct 11/02 27 Oct 11/02 28 Oct 11/02 29 Oct 11/02 30 Feb 20/03 31 Oct 11/02 32 Feb 20/03

Previous Revisions:

Revision 1 dated Oct 3/97Revision 2 dated Apr 10/01Revision 3 dated Apr 10/01Revision 4 dated Apr 16/01

Revision 5 dated July 17/01Revision 6 dated Aug 27/01Revision 7 dated Oct 4/01Revision 8 dated Oct 11/02


Page 1 of 32TFE731-76-3065July 28/97

Revision 9, Feb 20/03Copyright 1997, 2003 Honeywell International Inc. All rights reserved.

Category 3: Durability, Maintainability, or Product Improvement

ENGINE CONTROLS – POWER CONTROL – INSTALL DIGITAL ELECTRONICENGINE CONTROL (N1 DEEC)

1. Planning Information

NOTE: (TFE731-5BR-1C/-2C, TFE731-5BR/-5R-1H) All engine N1 DEECsmust be the same part number and installed concurrently. When com-plying with this service bulletin, the Aircraft Supplemental Type Certifi-cate (STC) must also be complied with concurrently when installing theN1 DEEC, refer to Paragraph 1.D.

(TFE731-5-1J) An aircraft service bulletin, currently ConstruccionesAeronauticas S.A. (CASA) Service Bulletin SB-101-76-02, must becompleted on the aircraft in conjunction with this service bulletin for theaircraft and engine to be compatible.

A. Effectivity

This service bulletin is applicable to the following turbofan aircraft engines.

Part No. Model No.Prior toSerial No. Application

3073640-2/-3 TFE731-4R-2S ***102353 Cessna Citation VII

3074970-1/-2/-3 TFE731-5-1J ***93145 CASA 101

3075330-3/-4/-5 TFE731-5BR-1C ** Falcon 900B

3075160-3/-4 TFE731-5BR-1H *107734 Hawker 800XP

3075370-2/-3 TFE731-5BR-2C ** Falcon 20-5

3074600-1/-2/-3 TFE731-5R-1H ** Hawker 800

3074600-4/-5 TFE731-5R-1H ** Hawker 800

*Production Incorporation Point of N1 DEEC, Part No. 2119010-8000.

**Improvements provided by this service bulletin have been approved for new productionand existing units. Serial number effectivity will be provided when improvements areincorporated in production.

***Projected serial number for future production.

B. Reason

(1) Problem:

(a) Older controls that use N2 to control the engine thrust (N1), can cause N1 RPMovershoot, driving transients and the need for constant power lever adjustmentduring take-off and climb.


Page 2TFE731-76-3065July 28/97

Revision 8, Oct 11/02


1. B. (1) (b) The current engine controls are aging, they are expensive to repair and parts aredifficult to locate.

(c) The current engine controls do not have the capability of automatic monitoringand recording of data necessary for engine condition trending.

(2) Background: The N1 DEEC has been developed as a replacement for the originalanalog and digital controllers for the TFE731 engine. Using the latest circuit designand components and digital technology, this light-weight, reliable, directly interchange-able unit reduces the pilot’s workload and maintenance effort by controlling engine fanspeed directly and automatically recording engine and flight parameters. Direct controlon N1 allows automatic, stable thrust setting throughout takeoff, climb and cruise andeliminates “trimming” required with the previous N2 controls. Engine start logic hasbeen improved to provide automatic enrichment, eliminating the need to utilize thecockpit SPR/Fuel Enrich switch during engine start.

Increased fault detection has been added to aid in trouble shooting. The Engine Condi-tion Trend Monitoring (ECTM) software integrated into the controller automaticallyrecords all data needed to track component life, fault detection and reporting, trouble-shooting and parameter exceedance events.

(3) Action: Refer to Figure 1, Service Bulletin Incorporation Flow Chart, for a processoverview, and comply with the following.

NOTE: The fault monitoring capability of the N1 DEEC is morecapable than the older controllers. Therefore in somecases when the N1 DEEC is installed, LRU and wiring faultsthat were not detected by by older controllers will be de-tected by the N1 DEEC requiring the repair or replacementof LRUs or wiring.

(a) Install N1 DEEC(s) as applicable in the aircraft.

Engine Model Old Part No. New Part No.TFE731-4R-2S 2118002-41/-42 2119010-7000TFE731-5BR-1C/-2C 2118002-51/-52/-60 2119010-9000TFE731-5R/-5BR-1H 2118002-6/-62 2119010-8000TFE731-5-1J 2118002-6/-8/-9/

2119010-22119010-2001

(b) Complete N1 DEEC Installation Data Work Sheet.

(c) Install ECTM Software on personal computer (PC) and configure ECTM soft-ware.

(d) Perform N1 DEEC download operations and enter engine statistics.

(e) Perform N1 DEEC static adjustments.

(f) Perform N1 DEEC Built-In-Test (BIT) fault verification.

(g) Perform engine test run to verify proper overspeed solenoid operation.

(h) Conduct operational check and update installation documentation.


Page 3TFE731-76-3065July 28/97



READ ENTIRE SERVICEBULLETIN FOR FAMILIARITY

START

END

INSTALL N1 DEEC(PARAGRAPH 2.A.)

PERFORM ENGINE ACCELERATION TEST ANDTAKE-OFF N1 CHECK

(PARAGRAPH 2.H.)

PERFORM STATIC N1 DEEC ADJUSTMENT(PARAGRAPH 2.E.)

CONFIGURE ECTM, PERFORM ECTM DOWN-LOAD AND ENTER ENGINE STATISTICS

(PARAGRAPH 2.D.)

PERFORM ENGINE RUN TO VERIFY OVERSPEEDSOLENOID OPERATION

(PARAGRAPH 2.G.)

CHECK FOR N1 DEEC BIT FAULTS(PARAGRAPH 2.F.)

COMPLETE N1 DEEC DATA WORKSHEET(PARAGRAPH 2.B.)

INSTALL ECTM SOFTWARE(PARAGRAPH 2.C.)

COMPLETE THE ATTACHED COMPLIANCE CERTIFI-CATE AND RETURN TO ENGINES, SYSTEMS

& SERVICES(PARAGRAPH 2.H.)

Service Bulletin Incorporation Flow ChartFigure 1


Page 4TFE731-76-3065July 28/97

Revision 9, Feb 20/03


1. C. Description

This service bulletin provides instructions to install N1 DEEC, Part No. 2119010-2001/2119010-7000/2119010-8000/2119010-9000 (as applicable). Also provided are instructionsfor the use of TFE731 ECTMplus Kit. Part number information for the TFE731 ECTMplus Kitand other tooling necessary to support the installation of the N1 DEEC are provided in Para-graph 1.H.

D. Compliance

Compliance addresses durability, maintainability, or product improvement.

NOTE: The procedures outlined in this service bulletin may be accomplished atLine Maintenance level or greater.

+MSP Yes [X] or No [ ]

+Special Program No. 27 Yes [X] or No [ ]

#MSP Yes [ ] or No [X]

#Warranty Coverage Yes [X] or No [ ]

+TFE731-5B/-5BR-1H, TFE731-5BR-1C/-2C.

#TFE731-5-1J.

+TFE731-4R-2S.

This service bulletin may be accomplished at operator’s option.

However, when complying with this service bulletin, the aircraft Supplemental Type Certificate(STC) must be complied with concurrently when installing the N1 DEEC. Applicable STC isas follows.

Aircraft Model No. Engine Model No. STCCessna Citation VII TFE731-4R-2S ST01756CH-DFalcon 900B TFE731-5BR-1C ST01444CH-DFalcon 20-5 TFE731-5BR-2C ST01445CH-DHawker 800 TFE731-5R-1H ST01424CH-DHawker 800XP TFE731-5BR-1H ST01424CH-DCASA 101 TFE731-5-1J *NA*Must be in compliance with Construcciones Aeronauticas S.A. (CASA) Service BulletinSB-101-76-02.

E. Approval

The change to the engine type design authorized by this service bulletin complies withapplicable Federal Aviation Regulations and is FAA approved.


Page 5TFE731-76-3065July 28/97



1. F. Manhour Requirements

An estimated two manhours are required for completion of this service bulletin.

G. Material - Price and Availability

(TFE731-4R-2S, TFE731-5BR-1C/-2C, TFE731-5BR/-5R-1H) A special program may beavailable for this modification, under certain conditions, providing compliance recommenda-tions of Paragraph D are met. Information on special program and availability of parts maybe obtained from a Honeywell authorized service facility. (Refer to Service Information Letter(SIL) F731-3.) A listing of authorized service facilities is also available on e-engines (www.e-engines.honeywell.com).

(TFE731-5-1J) Warranty coverage may be available for this modification, under certainconditions, providing compliance recommendations of Paragraph D are met. Information onspecial program and availability of parts may be obtained from a Honeywell authorized ser-vice facility. (Refer to Service Information Letter (SIL) F731-3.) A listing of authorized servicefacilities is also available on e-engines (www.e-engines.honeywell.com).

H. Tooling - Price and Availability

Review the following ground support equipment for use in accomplishing the instructionsoutlined in this service bulletin in addition to tooling listed in publications referenced inParagraph J.

Part No. Nomenclature *Unit List Price +831702-19 Kit, ECTMplus

#831702-20 Kit, ECTMplus

%4243811-All J2 Extension Cable Customer Furnished Personal Computer

*Information regarding price and availability of ground support equipment may be obtainedfrom Honeywell Engines, Systems & Services, Customer Support Center, M/S26-06/2102-323, P.O. Box 29003, Phoenix, AZ 85038-9003, Telephone: (Domestic)1-800-421-2133 (International) 1-602-365-2180, FAX: 1-602-365-3343.

NOTE: Kit, ECTMplus, Part No. 831702-5/-6/-12/-13, may be reworked perService Bulletin 831702-SB NO. 2, refer to Paragraph 1.K.

+Kit, ECTMplus, Part No. 831702-5/-12/-19 (-5/-12 are obsolete and no longer available forordering), enables the ECTM data to be downloaded from the N1 DEEC. This kit is avail-able to the operator at no charge, one kit per aircraft, following the purchase of the N1DEEC. This kit consists of ECTM software (Users Manual 21-9505 information is now partof the software), and required cables for use with a PC (customer supplied) to comply withthis service bulletin.


Page 6TFE731-76-3065July 28/97



#Kit, ECTMplus, Part No. 831702-6/-13/-20 (-6/-13 are obsolete and no longer available forordering), provides the Service Center with the software and cables required to interfacewith all N1 DEEC TFE731 engine applications. This complete ECTMplus kit allows theService Centers to support the operator’s installation, downloading, maintenance, and trou-bleshooting needs. Only one Kit, Part No. 831702-6/-13/-20, per service center is required.

%J2 Extension Cable, Part No. 4243811-All. Refer to aircraft certification documents for spe-cific cable part number used and installation instructions. Its purpose is to extend the J2connector on the N1 DEEC to a point which is more convenient for communications with thePC and may be permanently installed per aircraft certification documents for ease of con-nection during future maintenance actions that involve the PC.

1. I. Weight and Balance

(TFE731-4R-2S) Replacing DEEC, Part No. 2118002-41/-42, weight difference from thischange is minus (-) 8.95 pounds per unit.

(TFE731-5-1J) Replacing DEEC, Part No. 2118002-6/-8/-9, weight difference from thischange is minus (-) 8.95 pounds.

(TFE731-5-1J) Replacing N1 DEEC, Part No. 2119010-2, no weight (change) difference.

(TFE731-5BR/-5R-1H) Replacing DEEC, Part No. 2118002-6/-62, weight difference from thischange is minus (-) 8.95 pounds per unit.

(TFE731-5BR-1C/-2C) Replacing DEEC, Part No. 2118002-51/-52/-60, weight differencefrom this change is minus (-) 8.95 pounds per unit.

J. Publications References

The sources of information used in the preparation of this service bulletin include Honeywellengineering documentation and the following.

Part/Model No.

HeavyMaintenanceManual

LightMaintenanceManual

IllustratedPartsCatalog

TFE731-4R-2S NA *72-02-33 *72-02-32

TFE731-5-1J NA *72-02-75 *72-02-29

TFE731-5R-1H NA *72-02-75 *72-02-51

TFE731-5BR-1C NA *72-02-96 *72-02-95

TFE731-5BR-1H NA *72-02-96 *72-02-95

TFE731-5BR-2C NA *72-02-96 *72-02-95

*Affected Chapter/Section/Subject 76-10-02, 76-10-03 (as applicable).


Page 7TFE731-76-3065July 28/97



1. K. Service Bulletin References

The following shall be accomplished prior to or concurrent with this service bulletin. Theaccomplishment instructions outlined in each service bulletin stand alone; therefore com-pliance with this service bulletin does not indicate compliance with any other service bulletin.

Service Bulletin No. Service Bulletin Title

831702-SB NO. 2 TFE – ECTM GROUND SUPPORT EQUIPMENT KIT -Install Version 5.1 Software

Incorporation of the following is recommended at the time this service bulletin isaccomplished.


TFE731-72-3397 (Rev 2or subsequent revisions)

ENGINE – Initiate Component Maintenance/ModificationRecord Card (Card-Log Book)

Accomplishment of the following will no longer be applicable when the equipment has beenmodified in accordance with the accomplishment instructions outlined in this service bulletin.


#TFE731-76-3041 ENGINE – CONTROLS – Install Electronic Engine Control(EEC), Part No. 2118002-6

+TFE731-76-3043 ENGINE – CONTROLS – Install Electronic Engine Control(EEC), Part No. 2118002-6

+TFE731-76-3047 ENGINE – CONTROLS – Install Digital Electronic EngineControl (DEEC), Part No. 2118002-9

+TFE731-76-3052 ENGINE – CONTROLS – Digital Electronic Engine Control(DEEC), Part No. 2118002-6 or 2118002-8 Installation

%TFE731-76-3053 ENGINE – CONTROLS – Install Digital Electronic EngineControl (DEEC), Part No. 2118002-52

**TFE731-76-3055 ENGINE – CONTROLS – Install Digital Electronic EngineControl (DEEC), Part No. 2118002-42

%TFE731-76-3057 ENGINE – CONTROLS – Install N1 Control Digital Elec-tronic Engine Control (DEEC), Part No. 2118002-60

**TFE731-4R-2S.

#TFE731-5R-1H.

+TFE731-5-1J.

%TFE731-5BR-1C/-2C.

L. Other Publications Affected

Same as those listed under Paragraph J, Publications References.


Page 8TFE731-76-3065July 28/97



2. Accomplishment Instructions

NOTE: Publications listed in Section 1 provide applicable disassembly, cleaning,inspection, reassembly, and testing instructions and shall be referred toduring the accomplishment of the following instructions.

Accomplishment instructions are divided into Paragraphs 2.A through 2.H.Paragraph 2.A provides instructions for installing the N1 DEEC, Paragraph2.B fills out the N1 DEEC Installation Data Worksheet. Paragraph 2.C pro-vides instructions to install and configure the ECTM software, and Para-graphs 2.D through 2.H provide instructions on fault code downloading,programing, fault code corrective action and operation of the installed N1DEEC. Refer to Paragraph 1.D for applicable aircraft certification docu-ments.

Paragraphs 2.C through 2.H require a PC to be connected.

All programs requiring port communication such as networking or fax modemprograms must not share the same COM port as the ECTM program. Shar-ing the COM port will result in communication errors with the N1 DEEC.

A. Install Digital Electronic Engine Control (N1 DEEC)

(1) Gain access to and remove DEEC in accordance with the Aircraft Maintenance Manualand the Engine Light Maintenance Manual.

(2) Install N1 DEEC, Part No. 2119010-2001, 2119010-7000, 2119010-8000, or2119010-9000 (as applicable) in accordance with the Aircraft Maintenance Manual, andthe following instructions. (See Figure 2.)

(a) Install N1 DEEC to the mount in accordance with the Aircraft MaintenanceManual. Refer to aircraft certification documents.

(b) Connect the Pt2 pneumatic tube to the N1 DEEC Pt2 port.

(c) Unplug the Ps0 port and leave open to ambient air as applicable per aircraftcertification documents.

(d) Connect DEEC wiring harness connector to the N1 DEEC J1 connector.

(e) (As applicable) If installed, connect J2 extension cable to J2 connector.

(3) Proceed to Paragraph 2.B.

J1

J2Pt2

Ps0

Part No. 2119010-X

N1 DEEC Front PanelFigure 2


Page 9TFE731-76-3065July 28/97

Revision 6, Aug 27/01


2. B. N1 DEEC Installation Data Worksheet

(1) Reproduce a copy of the following worksheet for use as an N1 DEEC Installation DataWorksheet.

(2) Fill out accordingly using previous control settings, N1 DEEC and engine nameplatesand logbook.

N1 DEEC Installation Data Worksheet

Date:______________Facility:_____________________Technician/Operator:_____________________Aircraft Tail #:___________________________Aircraft Flight Hours:_______________Comments/Reason forDown-load:_________________________________________________________

Engine Statistics:

DATA EXAMPLES

Engine Serial No.(Enter C designation ifconverted engine)

99999C = Conversion Engine

Engine Part No. 3074970-3

Engine Model No. TFE731-5-1J

N1 DEEC Part No.* 2119010-2001-01-00(2119010=base number, -2001=dash number,-01=series number and -00=mod record)

N1 DEEC Serial No.* 090-AG0001

*These numbers are provided for display example only.

Data Tag Info Engine #1 Engine #2 Engine #3

Engine Model

Engine P/N

Engine S/N

N1 DEEC P/N

N1 DEEC S/N


Page 10TFE731-76-3065July 28/97

Revision 3, Apr 10/01


NOTE: For instructions on using the ECTM software, please refer to the ECTM(Version 5.0 or subsequent revisions) manual included within the software.This electronic manual can be accessed by clicking on “Help” on the menubar.

2. C. Installing ECTM Software

(1) Close all other programs.

(2) Install the “ECTM” Installation Disk 1 in your A: or auxiliary drive.

(3) Click on the MS Windows start button, located in the lower left hand corner of the MSWindows desktop and select “Run” from the start menu.

(4) Type in the file location “A:\setup.exe” in the Run Dialog Box and click on “OK”.

(5) Click on “Continue” from the welcome screen.

(6) The next screen will set up the directory name (ECTM = Default) for the ECTM datadownload files and application software. Once you have determined the appropriatedrive destination of the application software (typically “C:” drive), click “Next”.

(7) When prompted, remove the ECTM Installation Disk 1 and insert Installation Disk 2,then click “OK” to continue the installation.

(8) Installation is automatic. When completed, a program listing will appear on the MSWindows programs menu under “ECTM”.

(9) Installation of the application software is now complete and you are ready to beginviewing TFE731 engine data.

(10) Click on finish.

(11) Go to the MS Windows desktop “Start” button, select “Programs”, the “ECTM” programgroup, then the “ECTM Version 5.X” program.

(12) This will open the ECTM application.


Page 11TFE731-76-3065July 28/97



2. D. DownLoading ECTM Data and Entering N1 DEEC/Engine Statistics

NOTE: Downloading the N1 DEEC using ECTM software will erase all theN1 DEEC STORED faults.

Engine condition trend monitoring is accomplished using the N1DEEC, GSE cabling, a customer furnished personal computer,ECTM software, and for additional features, contact the JETCARE DATA MANAGEMENT FACILITY.

The N1 DEEC automatically collects engine operational data andstores the information in the N1 DEEC memory. Downloading ofthe N1 DEEC allows customer access to raw data for typicalmaintenance action. Further data analysis may be provided byJET CARE.

Basic features include:

Recording control system faults.

N1, N2 rolldown times.

Exceedance peaks and duration.

Engine operating and flight hours.

Starts, landings, touch and go’s and landings withoutshutdowns for life cycle calculations.

Event recording for significant events.

Transfers to Manual Mode.

Uncommanded engine shutdowns.

Type 2 exceedances.

Pilot events recorded when the pilot presses the SPR/Fuel Enrich switch.

For more events, refer to the Help File within the ECTM(Version 5.0 or subsequent revisions) software.

Advanced features include:

JET-CARE performance trending.

Engine operational profile.


Page 12TFE731-76-3065July 28/97



2. D. (1) Downloading the N1 DEEC data with ECTM software.

(a) At first N1 DEEC installation and PRIOR to removal, swapping or reworking ofthe N1 DEEC, the N1 DEEC must be downloaded to assure data integrity.

NOTE: ECTM software in the PC automatically correlates data files backto the engine serial number and historically sequences them.ECTM software will store the data files in an engine directory thatis named per the serial number of the engine from which it wasjust removed from (in the case of an initial installation) or theengine on which it is currently located. The data file itself isnamed per the N1 DEEC serial number.

For example:

Engine SN: 91999

N1 DEEC SN: 090-AG0001

Download Count = 3

Upon ECTM data download, the following will be stored:

Within the C:drive:

Directory created: 91999.edr

Data file created: 090-AG0001.003

NOTE: This following procedure is required only when the data downloader is first installed on the computer or the communicationport settings have been changed.

(b) Verify the PC communication port is set up properly using the following proce-dure.

1 Start the ECTM software by clicking the MS Windows “Start” button, thenselect “Programs”, the “ECTM” program group, then the “ECTM Version 5.X”program.

2 Select “CONFIGURE” on the menu bar.


Page 13TFE731-76-3065July 28/97



2. D. (1) (b) 3 Select “HARDWARE” from the pulldown menu and validate the following typi-cal settings.

NOTE: The following settings are typical. These settings may varybased on the PC being used. Adjust as appropriate.

All programs requiring port communication such as net-working or fax modem programs must not share the sameCOM port as the ECTM program. Sharing the COM portwill result in communication errors with the N1 DEEC.

COM PORT COM1

Backup Media Drive Letter A:

4 Select the “OK” when entry is complete.

(c) Perform the ECTM data download with the following procedure.

1 Connect the applicable COM port of the PC to the J2 connector on the N1DEEC using the download/converter cable provided in the ECTMplus kit.

2 With the PC and appropriate cables installed and the ECTM data downloader software installed, turn the N1 DEEC power ON then OFF thenON.

3 Record the following information from the engine and N1 DEEC nameplatesprior to download, as per Paragraph 2.B, N1 DEEC Installation Data Work-sheet.

DATA EXAMPLES

Engine Serial No.(Enter C designation ifconverted engine)

99999C = Conversion Engine

Engine Part No. 3074970-3

Engine Model No. TFE731-5-1J

N1 DEEC Part No.* 2119010-2001-01-00(2119010=base number, -2001=dashnumber, -01=series number and-00=mod record)

N1 DEEC Serial No.* 090-AG0001

*These numbers are provided for display (example) only.


Page 14TFE731-76-3065July 28/97



NOTE: The default password when ECTM is first installed is“DOWNLOAD”. To change the password, go to the mainmenu, select “CONFIGURE” then “PASSWORD” and followthe screen prompts.

2. D. (1) (c) 4 When the main menu is displayed select the “DOWNLOAD AND CLEAR N1DEEC DATA” button.

5 Enter the current password and click on the “OK” button.

6 Enter the aircraft tail number, press “Tab”, then enter engine flight hours todate.

NOTE: The time and date can be changed by double clicking thetime in the lower right hand corner of the MS Windowsdesktop or via the “Date/Time” functions within the MSWindows control panel.

7 If the date and time are correct, select the “Yes” button from the “Is This TheCorrect Date And Time” section.

If the date and time are NOT CORRECT, exit the program and update the PCdate and time via the control panel. Re-enter the program at Step2.D.(1)(c)1.

NOTE: In the ECTM software version 5.0 or subsequent revi-sions, there is an option called “Enter Engine BuildData”. This button is for life cycle data growth opportuni-ties and should be ignored and not checked.

8 If previous step is complete, and the date and time is correct, install a diskettein the A:drive (or drive appropriate based on hardware configuration set-up)and select the “START” button to begin the download. This step will savedata currently stored in the N1 DEEC and clear the N1 DEEC for the installa-tion of new engine statistics.


Page 15TFE731-76-3065July 28/97



2. D. (1) (c) 9 When the “Download Comments” screen appears, type in comments. Exam-ples of typical comment information is as follows.

a Mechanic/Operator name.

b Aircraft tail number.

c Aircraft flight hours.

d Comments on observations/maintenance actions.

e Reason for download.

f (TFE731-5-1J) Click on the correct position (Engine/Other/Test Cell) forthe DEEC being downloaded.

g (TFE731-4R-2S, TFE731-5BR-1C/-2C, TFE731-5BR/-5R-1H) Click onthe correct engine position (Left, Right, Center/Other/Test Cell) for theDEEC being downloaded.

10 Click on “CONTINUE” when comments are completed.

NOTE: When first downloading a newly installed N1 DEEC,ECTM will save the data in c:\731ECTM\.EDR folder. Allsubsequent downloads will be saved in a folder accord-ing to the engine serial number.

11 ECTM will display an acknowledgement indicating the data has been suc-cessfully saved. Click “OK” and continue with Step 2.D.(2).

(2) Enter engine statistics into N1 DEEC.

(a) An “ENGINE STATISTICS” screen will be displayed. Enter/Verify the data intothe following fields.

NOTE: Ignore the fields marked N/A. No information is required in theseareas.

DATA EXAMPLESEngine Serial No.(Enter C designation ifconverted engine)

99999C

Engine Part No. 3074970-3Engine Model No. TFE731-5-1JN1 DEEC Part No.* 2119010-2001-01-00

(2119010=base number, -2001=dashnumber, -01=series number and-00=mod record)

N1 DEEC Serial No.* 090-AG0001*These numbers are provided for display (example) only.


Page 16TFE731-76-3065July 28/97



2. D. (2) (b) Select “STORE” and the new statistics data will be stored. If no data is changeda message that “no data has changed” will be displayed.

(c) Select the “CONTINUE” button at this time and the downloader will return to themain menu display.

(d) Proceed to Paragraph 2.E.

E. N1 DEEC Static Adjustment

NOTE: When the N1 DEEC is first installed, the engine configuration ID,SG setting, and N1 compensator value must be entered for properoperation.

A value of “1” must be entered to indicate no compensation onengines that do not have an N1 compensator.

(1) Set up.

(a) Apply power to the N1 DEEC.

(b) Start the ECTM software by clicking the MS Windows “Start” button, then select“Programs”, the “ECTM” program group, then the “ECTM Version 5.X” program.

(c) When the main menu is displayed, select the “DEEC HHT COMMUNICATION”button.

(d) At the prompt (>), type “ENG” and press “Enter”.

(e) The N1 DEEC will return with SETUP DEEC (Y/N)?.

1 Typing “Y” will allow N1 DEEC adjustment and press “Enter”.

2 Typing “N” will return user to the prompt.

(f) After a “Y” is entered, the N1 DEEC will respond with:

ENG_ID:X (where “X” is the current setting)

(g) Enter the appropriate engine ID value using Table 1, 2, 3, or 4 (as applicable).


Page 17TFE731-76-3065July 28/97



Table 1. N1 DEEC, Part No. 2119010-8000Engine Model to Engine ID Value

Engine Model Nozzle Engine ID Value Resulting PC Display

TFE731-5R-1H Grumman 1 TFE731-5R-1H H800G

TFE731-5R-1H *TR5000BA 2 TFE731-5R-1H H800 TR5000BA

TFE731-5BR-1H *TR5000BR 5 TFE731-5BR-1H H800XP TR5000BR

*TR50000XX is a Dee Howard thrust reverser.



TFE731-5-1J Standard 6 TFE731-5 C101CC



TFE731-5BR-1C Standard 1 TFE731-5BR-1C F900 STDSide Engine

TFE731-5BR-1C TR 2 TFE731-5BR-1C F900 TRCenter Engine

TFE731-5BR-2C TR 3 TFE731-5BR-2C F20 TR

TFE731-5BR-2C Standard 4 TFE731-5BR-2C F20 STD



TFE731-4R-2S Thrust Reverser 12 TFE731-4R-2S

2. E. (1) (h) Press “Enter” and the N1 DEEC will display the string corresponding to the En-gine ID Value selected. Confirm that the string displayed corresponds to the“Resulting PC Display” column in Table 1, Table 2, Table 3, or table 4 (as appli-cable), for the Engine ID Value selected.

(i) Press “Enter” and the N1 DEEC will respond as follows.

N1_COMP_ADJ:X (where “X” is the current setting)


Page 18TFE731-76-3065July 28/97



2. E. (1) (j) Enter the N1 compensator value and press “Enter”.

(k) Press “Enter” again and the N1 DEEC will respond as follows.

SG:X (where “X” is the current setting)

(l) Enter “5.0” for the SG setting and press “Enter”.

(m) Press “Enter” again and the N1 DEEC will respond with:

MMSW:(AM=0, MM=1)

0

(n) Pressing “Enter” will end the adjustment process and return user to the prompt.

(o) Cycle power to the N1 DEEC.

(p) Verify the adjustments entered are correct (see example below) by re-typing“ENG” and pressing “Enter”. The following displays/action required will be dis-played.

Displayed Action Required

Setup DEEC (Y/N)? Type “Y” and press “Enter”

Eng_ID: X Confirm proper ID and press “Enter”

N1_Comp_Adj: X Confirm proper N1 compensationnumber and press “Enter”

SG: X Confirm and press “Enter”

MMSW: (AM=0, MM=1) Confirm 0 and press “Enter”

(q) If proper values are not observed, return to Step 2.E.(1)(d).

NOTE: If this was the first ECTM download of a new N1 DEEC,there will be a configuration error, Fault 219. In order toclear this stored fault, the DEEC will have to be downloadedone more time.

(r) Exit the DEEC HHT Communication Screen by selecting the “Return to MainMenu” button.

(s) If this was the first ECTM download of an N1 DEEC just installed, perform asecond download by accomplishing Steps 2.D (1)(c) 1 through 11. Proceed toParagraph 2.F.


Page 19TFE731-76-3065July 28/97



2. F. Check for N1 DEEC Bit Faults

NOTE: The N1 DEEC records faults in “CURRENT” and “STORED”memory locations.

“CURRENT” faults indicate engine/control system anomalieswhich have occurred since last DEEC power cycle. Cycling DEECpower after a fault has occurred may remove a current fault fromthe “CURRENT” fault memory location.

“STORED” faults are a history of “CURRENT” faults which haveoccurred. Cycling DEEC power will not erase stored faults. Themost recent 50 faults are retained for display and ECTM download.

Downloading ECTM will erase “STORED” faults.

(1) Displaying “CURRENT” faults.


(b) Start the ECTM program and select “DEEC HHT Communication”.

(c) Type “ERR” and press enter to display CURRENT faults. Press “Enter” to dis-play each fault until prompted.

NOTE: If no codes are displayed, a “No Record” is displayed. Exitat any time using (esc) key.

(d) The faults are listed in the following format.

ERRXXX where: XXX is the fault code, refer to Table 5.

(e) Correct any engine control system fault using the appropriate troubleshootingprocedures listed in the Engine Light Maintenance Manual.


Page 20TFE731-76-3065July 28/97



2. F. (2) Displaying “STORED” Faults.

(a) Type “FLT” and press “Enter” to display the STORED faults.

(b) The faults are listed in the following format.

FLTXXX,Y,HHH:MM:SS.T where:

XXX=fault code, refer to Table 5.

Y= fault severity.

· 1 = Auto Mode normal operation (log only, no action required).

· 2 = Auto Mode Dispatch capable, only fault code 237 (ECTM MemoryFull or Event) will cause a slow (every 2 seconds) flash of themanual mode light after engine shutdown. All other level 2 severi-ty faults will be recorded in ECTM, but will not result in any flash-ing of the manual mode light (take correction action at earliestconvenience).

· 3 = Auto Mode Not Dispatch capable, fast (once per second) flash ofthe manual mode light after engine shutdown (download ECTM todetermine cause of fault. Take corrective action prior to nextflight).

· 4 = Manual Mode transfer, manual mode light on (download ECTM todetermine cause of fault. Take corrective action prior to nextflight).

· 5 = Pilot selected manual mode, Manual Mode light on (via cockpitswitch).

· HHH:MM:SS.T = Time stamp that shows the hours that the N1 DEEChas been powered since new (hours:minutes:seconds:tenths).

(c) The N1 DEEC categorizes the severity of N1, N2 and ITT limitations per theEngine Light Maintenance Manual limits and assigns the following types:

Type 1 exceedance requires download of ECTM data and logging of exceedancetype, peak and duration in the Engine Log Book.

Type 2 exceedance requires appropriate Engine Light Maintenance Manual orHeavy Maintenance Manual maintenance actions, a download of ECTM dataand logging of exceedance type, peak and duration in the Engine Log Book.


Page 21TFE731-76-3065July 28/97



NOTE: Fault codes displayed in the previous step have occurred since last erasureof DEEC faults but do not necessarily exist at this time. These faults mayhave been the result of intermittent problems that are not duplicated duringground runs and are a useful aid in trouble shooting to prevent re-occur-rence.

Some codes are not used for all applications. For fault severity explanation,refer to Step 2.F.(2)(b).

When a “Section” is referenced in the following table, it pertains to a Sectionand the maintenance instructions in the Engine Light Maintenance Manual.

The following fault code corrective action table is applicable only to N1DEECs, Part No. 2119010-2001/2119010-7000,2119010-8000/2119010-9000. Refer to applicable Engine Light MaintenanceManual for N1 DEEC fault code corrective actions for other N1 DEEC(s).

Table 5. N1 DEEC Fault Code Corrective Action

FaultCode Fault Description

FaultSeverity

Problem LRUand/or AssociatedHarness Corrective Action

2 N1 OPEN ORSHORT TOGROUND

4 N1 Monopoleand AssociatedHarnesses

Perform appropriate procedures specifiedin Section 72-00-00, Troubleshooting-Check Instructions, Paragraph 5 or 6.

4 N1 SIGNALCONDITIONER

4 DEEC Refer to Fault Code 2 for Corrective Action.Inspect DEEC harness for damage. If nodamage is evident, replace DEEC usinginstructions in this service bulletin.

5 N1 NOTREASONABLE


Refer to Fault Code 4 for Corrective Action.

6 N1 MAX LIMIT 4 N1 Monopoleand AssociatedHarnesses


8 N1 OUTPUT LOW 4 N1 Monopoleand AssociatedHarnesses


9 UNCOMMANDEDACCELERATION

4 Various ECTM Download Required. ContactHoneywell Representative for Trouble-shooting.

12 N2 OPEN ORSHORT TOGROUND




Page 22TFE731-76-3065July 28/97



Table 5. N1 DEEC Fault Code Corrective Action (Cont)

FaultCode Corrective Action

Problem LRUand/or AssociatedHarness

FaultSeverityFault Description

14 N2 SIGNALCONDITIONER

4 DEEC Refer to Fault Code 12 for Corrective Ac-tion. Inspect DEEC harness for damage. Ifno damage is evident, replace DEEC usinginstructions in this service bulletin.

15 N2 NOTREASONABLE


Refer to Fault Code 14 for Corrective Ac-tion.

16 N2 MAX LIMIT 4 N2 Monopoleand AssociatedHarnesses


23 ITT MAX LIMIT 2 ITT Harnessand AssociatedHarnesses


24 ITT MIN LIMIT 2 ITT Harnessand AssociatedHarnesses


25 ITT RATE LIMIT 2 ITT Harnessand AssociatedHarnesses


26 ITT SENSOR OPEN 2 ITT Harnessand AssociatedHarnesses


30 DEEC PS0 MAXLIMIT

2 DEEC Disconnect pneumatic line from DEEC inaccordance with Section 76-10-03. ClearDEEC faults by typing FER, then type ERRto verify that fault does not exist. If fault stillexists, replace DEEC using instructions inthis service bulletin.

31 DEEC PS0 MIN LIM-IT

2 DEEC Refer to Fault Code 30 for Corrective Ac-tion.

32 DEEC PS0 RATELIMIT


34 TT2 MAX LIMIT 4 DEEC Perform appropriate procedures specifiedin Section 72-00-00, Troubleshooting-Check Instructions, Paragraph 5 or 6.

35 TT2 MIN LIMIT 4 PT2 Sensorand AssociatedHarnesses


36 TT2 RATE LIMIT 4 PT2 Sensorand AssociatedHarnesses



Page 23TFE731-76-3065July 28/97







37 TT2 SENSOROPEN

4 PT2 Sensorand AssociatedHarnesses


38 TT2 SENSORSHORT

4 PT2 Sensorand AssociatedHarnesses


41 DEEC PT2 MAXLIMIT

4 DEEC Disconnect pneumatic line from DEEC inaccordance with Section 76-10-02. ClearDEEC faults by typing FER, then type ERRto verify that fault does not exist. If fault stillexists, replace DEEC using instructions inthis service bulletin.

42 DEEC PT2 MINLIMIT


43 DEEC PT2 RATELIMIT


61 FCU TM OPEN 4 FCU andAssociatedHarnesses


62 FCU TM SHORT TOGROUND

4 FCU andAssociatedHarnesses


64 FCU TM COIL 1SHORT



65 FCU TM COIL 1OPEN



66 FCU TM COIL 2SHORT



67 FCU TM COIL 2OPEN



70 FCU OVERSPEEDSOLENOID OPEN



71 FCU OVERSPEEDSOLENOID SHORT




Page 24TFE731-76-3065July 28/97







75 FCU TM SHORT 4 FCU andAssociatedHarnesses


78 DEEC OVERSPEEDSOLENOID DRIVERFAILED


80 SBV A SOLENOIDOPEN

4 SBV ASolenoid andAssociatedHarnesses


81 SBV A SOLENOIDSHORT

4 SBV ASolenoid andAssociatedHarnesses


85 SBV B SOLENOIDOPEN

4 SBV BSolenoid andAssociatedHarnesses


86 SBV B SOLENOIDSHORT

4 SBV BSolenoid andAssociatedHarnesses


89 BVA SOLENOIDDRIVER FAILED

4 DEEC Refer to Fault Code 80 for Corrective Ac-tIon.

90 FCU MMSOLENOID OPEN



91 FCU MMSOLENOID SHORT



92 DEEC MMSOLENOID DRIVEROPEN


93 DEEC MMSOLENOID DRIVERSHORT


94 FCU BVBSOLENOID DRIVERFAILED



Page 25TFE731-76-3065July 28/97







102 CLIMB INDICATORDRIVER OPEN ORSHORTED

2 DEEC Perform appropriate procedures specifiedin Section 72-00-00, Troubleshooting-Check Instructions, Paragraph 5 or 6.

105 DEEC COLDJUNCTIONCOMPENSATOREXCEEDS MAX

4 DEEC Perform ECTM data download per Step2.D.(1) then replace DEEC using instruc-tions in this service bulletin.

106 DEEC COLDJUNCTIONCOMPENSATORBELOW MIN LIMIT


153 DEEC POSITIVE 10VOLTS FAIL


155 DEEC EEPROMWRITE FAIL


156 DEEC TRIMVARIABLESDEFAULTED


157 DEEC GROUNDERROR


158 DEEC +/- 15 VOLT-AGE FAIL


183 DEEC WATCH DOGFREQUENCYERROR


184 DEEC (COP)TIMEOUT


185 COP TEST FAILED 4 DEEC Perform ECTM data download per Step2.D.(1) then replace DEEC using instruc-tions in this service bulletin.

188 DEEC ROMCHECKSUM


189 SERIAL EEPROMCHECKSUM



Page 26TFE731-76-3065July 28/97







190 DEEC BUFFER1BIT FAILED


210thru214

FCU PLA FAULT 4 PLA POT andAssociatedHarnesses


218 DEEC OVERSPEEDLOGIC FAILED


219 ENGINE HARNESSID MISMATCH

4 DEEC, Setup orHarness

Aircraft jumper pin(s) P1-u, v, w, x or CCfaulted. Repair faulted jumper pin(s) inaccordance with applicable aircraftmanufacturers’ instructions. Verify DEECsetup per Paragraph 2.E.

221 DEEC PT2TRANSDUCERFAULT


222 DEEC PT2TRANSDUCERFAULT


233 **ENGINE TYPE 2 N1EXCEEDANCE

3 ENG Type 2 N1 Exceedance has occurred. Re-fer to Section 72-00-00, Table 501 for cor-rective action.

234 **ENGINE TYPE 2 N2EXCEEDANCE


235 **ENGINE TYPE 2 ITTEXCEEDANCE

3 ENG Type 2 ITT Exceedance has occurred. Re-fer to Section 72-00-00, Table 501 for cor-rective action.

237 ECTM DATADOWN-LOADREQUIRED

2 ENG Down-load of ECTM data from DEEC isrequired. Download ECTM data fromDEEC in accordance with Step 2.D.(1).

240 OVERSPEEDSOLENOIDACTUATION

1 ENG An overspeed event has occurred in whichthe overspeed solenoid was energized. Refer to Section 72-00-00, Table 501 forcorrective action.

242 ECTM DATACHECKSUM FAIL

1 DEEC Indicates ECTM data may be suspect. Per-form ECTM download per Step 2.D.(1). Ifproblem persists, replace DEEC usinginstructions in this service bulletin.


Page 27TFE731-76-3065July 28/97







244 PS0 TRANSDUCERFAULT


245 PS0 TRANSDUCERFAULT


246 *ENGINE TYPE 1 N1EXCEEDANCE


247 *ENGINE TYPE 1 N2EXCEEDANCE


248 *ENGINE TYPE 1 ITTEXCEEDANCE

2 ENG Type 1 ITT Exceedance has occurred. Re-fer to Section 72-00-00, Table 501 for cor-rective action.

249 DEEC REAL TIMEFAILURE


250 DEEC REAL TIMEMONITOR


251 DEEC STACKOVERFLOW


255 OVERFLOW 4 DEEC Perform ECTM data download per Step2.D.(1) then replace DEEC using instruc-tions in this service bulletin.

*Type 1 exceedance requires download of ECTM data and logging of exceedance type, peak andduration in the Engine Log Book.

**Type 2 exceedance requires appropriate Engine Light Maintenance Manual or Heavy MaintenanceManual maintenance actions, a download of ECTM data and logging of exceedance type, peak andduration in the Engine Log Book.

2. F. (2) (d) Record any N1 DEEC faults for future maintenance actions.

(e) Correct any engine control system faults using the appropriate troubleshootingprocedures listed in the applicable Engine Light Maintenance Manual.

(f) N1 DEEC bit fault check is now complete.

(g) Proceed to Paragraph 2.G.


Page 28TFE731-76-3065July 28/97



2. G. Verify Overspeed Solenoid Operation

(1) To transfer the N1 DEEC to Powered Manual Mode:


(b) Start the ECTM software by clicking the MS Windows “Start” button, then select“Programs”, then “ECTM” program group, then the “ECTM Version 5.X” program.


(d) At the prompt (>), type ”ENG” and press “Enter”.

(e) Perform required action per the following example.





SG: X Confirm setting and press “Enter”

MMSW: (AM=0, MM=1) Type a “1” and press “Enter”

(2) Overspeed test.

CAUTION: MANUAL MODE BATTERY STARTS ARE NOT RECOM-MENDED, BATTERY STARTS COULD RESULT IN AN OVER-TEMPERATURE AND DAMAGE THE TURBINE SECTION.

NOTE: When the engine is started with powered manual modeselected, the N1 DEEC will actuate the overspeed solenoidat approximately 40-45% N2 speed momentarily. Theengine will noticeably “Droop” to about 30-40% speed andrecover to a normal start.

(a) Perform an engine start in accordance with Aircraft Flight Manual and/or ap-propriate aircraft documents to idle with the N1 DEEC in powered manual mode.

1 If the engine exhibits the “Droop” at about 40-45% N2 speed and recovers toa normal start, the overspeed test is successful.

2 If the engine does not respond properly, first verify that powered manualmode was selected and repeat the test.

3 If manual mode was selected, perform the appropriate troubleshooting perTable 5 and the Engine Light Maintenance Manual to identify the problemcomponent.


Page 29TFE731-76-3065July 28/97



2. G. (3) To transfer the N1 DEEC to Normal Mode:

(a) At the prompt (>), type ”ENG” and press “Enter”.

(b) Perform required action per the following example.




N1_Comp_Adj: 1 Confirm proper N1 compensationnumber and press “Enter”

SG: X Confirm setting and press “Enter”

MMSW: (AM=0, MM=1) Type a “0” and press “Enter”

(c) Proceed to Paragraph 2.H.

H. Operational Check

(1) Check engine(s) acceleration. If acceleration rate/time differs, and requiresadjustment, the SG setting may be moved up or down as follows.

NOTE: Raising SG will decrease (shorten) engine acceleration time.Lowering SG will increase (lengthen) engine acceleration time.Excessive upward adjustment is undesirable since it may result inengine compressor instability (surge) during rapid power leveradvance. Excessive adjustment in the downward direction is alsoundesirable in that it may reduce engine acceleration capability toan undesirable extent and may result in lean blowout.

To compensate for individual engine characteristics or installationeffects, a typical variation in acceleration adjustment setting (SG)may be to decrease by one value (setting number), or increase bytwo values (setting number), however, adjustments are not limitedto these values and may be increased or decreased as necessary.


(b) Start the ECTM software by clicking the MS Windows “Start” button, then select“Programs”, then “ECTM” program group, then the “ECTM Version 5.X” program.


(d) At the prompt (>), type ”ENG” and press “Enter”.


Page 30TFE731-76-3065July 28/97



2. H. (1) (e) Perform required action per the following example.





SG: X Enter revised value of SG per Step2.H.(1) and “NOTE” preceding Step

(a), press “Enter”

MMSW: (AM=0, MM=1) Confirm “0” and press “Enter”

(f) Cycle power to the N1 DEEC.

(g) Repeat the engine acceleration test.

(h) Repeat SG adjustment as necessary.

(2) Verify that N1 speed meets the required N1 of the day in the Aircraft Flight Manualtakeoff charts.

(a) Stabilize at idle for two minutes.

(b) Advance power lever to N1 of the day.

(c) Perform engine shutdown in accordance with the Aircraft Flight Manual and/orappropriate aircraft documents.

(3) Check for faults in accordance with Table 5 or the Engine Light Maintenance Manual.

(4) Update the Component Maintenance/Modification Record Card in accordance withService Bulletin TFE731-72-3397 (Rev 2 or subsequent revisions) on the removedDEEC and installed N1 DEEC.

NOTE: When complying with this service bulletin, revision (Rev 9), ensurethat the revision number is entered in the engine log book whencompleting the following step.

(5) Make entry in engine log book noting date of compliance, engine operating time, partnumber(s) and serial number(s) of installed component(s) (as applicable), andcompliance with this service bulletin (and service bulletin revision number, ifapplicable).

(6) Complete the attached Compliance Certificate form and send to Engines, Systems &Services.


Page 31TFE731-76-3065July 28/97



3. Material Information

NOTE: Applicable illustrated parts catalogs and spare parts bulletins, dated laterthan the original issue date of this service bulletin, may introduce differentparts for installation. Refer to these documents before ordering parts.

Expendable parts, discarded in gaining access to the affected area of theequipment, are not included.

The following parts are required to accomplish the instructions outlined in this service bulletin.

New PN QuantityUnit ExchangeList Price* Key Word Old PN

Instructions-Disposition

+2119010-2001 1 DEEC 2118002-6/-8/-9 or2119010-2

D, O

K

@2119010-7000 1 DEEC 2118002-41/-42 D, O

#2119010-8000 1 DEEC 2118002-6/-62 D, O

%2119010-9000 1 DEEC 2118002-51/-52/ -60

D, O

Disposition Code D. Return old part to Honeywell Engines, Systems & Services, Material Receiving,1944 East Sky Harbor Circle, Phoenix, AZ 85034, “Attn: Core Dept”. State onpacking list the shipper/invoice number. Identify (tag) part as removed in accor-dance with Service Bulletin TFE731-76-3065.

Disposition Code K. Old and new parts are interchangeable.

Disposition Code O. Replacement part is available on exchange basis or a special program may beavailable for this modification under certain conditions. Refer to Section 1,Paragraph G for program information.

*Refer to Section 1, Paragraph G for program information.

@TFE731-4R-2S.

+TFE731-5-1J.

#Used on both TFE731-5BR/-5R-1H engine models.

%Used on both TFE731-5BR-1C/-2C engine models.


Page 32TFE731-76-3065July 28/97



ATTN: Technical Data DistributionFAX (602) 365-5577 (Phone (602) 365-2493)(No Header Sheet Required)

SERVICE BULLETIN TFE731-76-3065SUPPLEMENTAL TYPE CERTIFICATE (STC)

ORDER FORM (NO CHARGE)

NOTE: This STC is also available at www.e-engine.honeywell.com.

Customer Name:

Address:

Shipping Address:(if different

from above orprovide emailaddress if you

prefer delivery viathe internet)

Aircraft Model and Serial No.: (Example Hawker 800-XXXX)

� STC ST01424CH-D, Engine ModelTFE731-5R/-5BR-1H (Hawker 800/800XP)

� STC ST01444CH-D, Engine ModelTFE731-5BR-1C (Falcon 900B)

� STC ST01445CH-D, Engine ModelTFE731-5BR-2C (Falcon 20-5)

� STC ST01756CH-D Engine ModelTFE731-4R-2S (Cessna Citation VII)

Comments:

,,,,,,,,,,

,,,,,,,,,,

,,,,,,,,,,

,,,,,,,,,,

Engines, Systems & Services – Phoenix, Arizona

CERTIFICATE OF COMPLIANCE

To: Operator or Service Center Performing Modification

Upon modification of equipment, please fill in the information requested below, then mailor fax the completed certificate to:

Honeywell Engines, Systems & ServicesP.O. Box 29003, Mail Stop 2102-127Phoenix, AZ 85038-9003FAX: 602-365-5638

Owner/Operator ____________________________________________________________

_________________________________________________________________________

Aircraft Model ____________________________Aircraft Serial No. ___________________

I certify that the following engine/equipment has been modified in accordance with the listedService Bulletins.

ENGINE/EQUIPMENT

NO. 1 NO. 2 NO. 3 NO. 4

PART NO. PART NO. PART NO. PART NO.

MODEL NO. MODEL NO. MODEL NO. MODEL NO.

SERIAL NO. SERIAL NO. SERIAL NO. SERIAL NO.

TSN/TSO TSN/TSO TSN/TSO TSN/TSO

CYCLES CYCLES CYCLES CYCLES

SERVICEBULLETIN

NO.REVISION

NO.

SERVICEBULLETIN

NO.REVISION

NO.

SERVICEBULLETIN

NO.REVISION

NO.

SERVICEBULLETIN

NO.REVISION

NO.

Signature _______________________Date_________________Repair Facility ________________________________________

service bulletin -...

Documents