01-110hce-2-2 airframe and landing gear.pdf

8/18/2019 01-110HCE-2-2 Airframe and Landing Gear.pdf

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NAVAIR 01-110HCE-2-2

1 FEBRUARY 2006Change 1 - 1 September 2010

TECHNICAL MANUAL

ORGANIZATIONAL MAINTENANCE

AIRFRAMES AND LANDING GEAR

UTILITY HELICOPTERHH-1N/UH-1N

This change incorporates IRACs 5 thru 10.

DISTRIBUTION STATEMENT C. Di stribution authorized to U.S. Gove rnment age nciesonly and th eir contractors to protect publi cations requi red for offici al u se or fo radministrative or operational p urposes only, d etermined on 1 February 2006. Othe rrequests for this docum ent shall be re ferred to Commander, Naval Air Sys temsCommand (PMA-276), RADM William A Moffett Bldg, 471 23 Buse Rd, Bldg 22 72,Patuxent River, MD 20670-1547.

DESTRUCTION NOTICE - For un classified, limited doc uments, destroy by an y methodthat will prevent disclosure of contents or reconstruction of the document.

Published by Direction of Commander, Naval Air Systems Command


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A Change 1

LIST OF EFFECTIVE PAGES

Insert latest changed pages; dispose of superseded pages in accordance with applicable regulations.

NOTE: On a changed page, the portion of the text affected by the latest change is indicated by a vertical line, orother change symbol, i n t he outer margin of th e page. Chan ges to illu strations by miniature pointing hands.Changes to wiring diagrams are indicated by shaded areas.

IRACs 1 through 10 have been incorporated in this manual.IRAC 2 was never issued.

Dates of issue for original and changed pages are:

Original .....................0 .......................... 1 Feb 2006(Incl. IRACs 1 thru 4)

Change .....................1 .......................... 1 Sept 2010(Incl. IRACs 5 thru 6, and 10)

(IRACs 7 thru 9 cancelled)

Total number of pages in this manual is 106 consisting of the following:

Page *Chan geNo. No.



Title .......................................... 1 A............................................... 1i – iii.......................................... 1iv – ix........................................ 0x – xi ........................................ 1xii Blank ................................... 11-1 – 1-3 .................................. 01-4............................................ 11-5 ........................................... 0

1-6 Blank.................................. 02-1 – 2-7 .................................. 02-8 Blank.................................. 0

3-1 ........................................... 03-2 Blank ................................. 04-1 – 4-7 .................................. 04-8 ........................................... 14-9 – 4-14 ................................ 04-15 ......................................... 14-16 – 4-27 .............................. 04-28 ......................................... 14-29 – 4-35 .............................. 0

4-36 – 4-38 .............................. 14-38A – 4-38B ......................... 14-39 – 4-43 .............................. 0

4-44 – 4-46...............................14-46A – 4-46C ..........................14-46D Blank..............................14-47 – 4-61...............................04-62 Blank ................................0Index-1 .....................................0Index-2 .....................................1Index 3 – Index 4......................0Index 5......................................1

Index 6 – Index 7......................0Index-8 Blank ...........................0

*Zero in this column indicates an original page.


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TABLE OF CONTENTS

Section Page

I INTRODUCTION

1-1. General ..................................... 1-11-3. Scope and Arrangement of

Maintenance InstructionManual ................................ 1-1

1-4. Associated Aircraft Manuals..... 1-21-5. Lubrication and Servicing......... 1-31-7. Support Equipment .................. 1-31-9. Cons umable Materials ............. 1-31-11. Record of Applicable

Technical Directives ............. 1-31-13. Quality Assurance .................... 1-31-15. Special Abbreviations

and Symbols......................... 1-3

1-17. Warnings, Cautions,and Notes ............................. 1-3

II SYSTEM DESCRIPTION

2-1. Fus elage................................... 2-12-3. Windshields and Windows ....... 2-12-4. Winds hield Wipers ................... 2-12-5. Doors, Panels and Fairings...... 2-12-11. Tran smission and

Engine Cowling ................... 2-22-12. Crew Seats............................... 2-22-13. Nose Armor Panels .................. 2-22-14. Inertia Reel and

Shoulder Harness................. 2-22-15. Cargo Tie-Down

Fittings.................................. 2-22-16. Fire Extinguishers .................... 2-42-17. Air Distribution System............. 2-42-21. Ta ilboom................................... 2-42-22. Landi ng Gear............................ 2-4

III SUPPORT EQUIPMENTMAINTENANCE

3-1. General ..................................... 3-1

Section Page

IV ORGANIZATIONALMAINTENANCE

4-1. Windshields and Windows.... 4-14-27. Windshield Wipers ................ 4-8

4-34. Doors, Panels andFairings ............................

4-9

4-38. Nos e Access Doors .............. 4-114-43. Crew Doors ........................... 4-134-50. Passeng er – Cargo

Doors ............................... 4-214-57. Cabin (Hinged) Panels.......... 4-25

4-62. Miscellaneous AccessDoors, InspectionPanels and Fairings......... 4-26

4-67. Transmission and

Engine Cowling................ 4-294-72. Crew Seats............................ 4-304-77. Nose Armor Panels............... 4-364-80. Inertia Reel and

Shoulder Harness............ 4-364-88. Fire Extinguishers ................. 4-374-92. First Aid Kits.......................... 4-38A

4-95. Air Distribution System.......... 4-38B4-97. Emergency Air Distribution

System.............................4-38B4-100. Bleed Air Shutoff Valves ....... 4-394-103. Variable Control Mixing

Valve................................ 4-39

4-106. Nois e Suppressor ................. 4-414-109. Remote Sensor ..................... 4-414-112. Rotary Selector ..................... 4-414-115. Ventilation Blowers ............... 4-414-118. Duc ts..................................... 4-434-120. Tailboom ............................... 4-43

4-12 5. Driveshaft Covers,Tailboom Access

Doors, Panels andFairin gs ............................ 4-46

4-12 9. Tail Skid ................................ 4-46A4-13 4. Landing Gear ........................ 4-46B

ALPHABETICAL INDEX....................... Index-1


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LIST OF ILLUSTRATIONS

Number Title Page

2-1. Fuselage Station (Typical)........ 2-22-2. Transmission and Engine

Cowling ................................. 2-32-3. Cargo Deck Fittings .................. 2-54-1. Wind ow/Windshield

Damage Limits...................... 4-24-2. Winds hield Wiper...................... 4-124-3. Nos e Access Doors.................. 4-154-4. Installation of Conductive

Gasket (OBS AFT COMPWITH AFC 381) .................... 4-16

4-5. Installation of ConductiveGasket (USBL AFTCOMP WITH AFC 381)......... 4-16

4-6. Crew Door................................. 4-174-7. Crew Door Ejection

Mechanism and Cable.......... 4-194-8. Cargo Door Installation............. 4-224-9. Cabin (Hinged) Panel

Assembly .............................. 4-274-10. Crew Seat ................................. 4-324-11. Nose Armor Panel .................... 4-374-11A. Fire Extinguisher Removal

and Installation...................... 4-38

Number Title Page

4-12. Inertia Reel Installation............ 4-394-13. Air Distribution System

Schematic............................ 4-404-14. Air Distribution System............. 4-424-15. Tailboo m Attachment

Points ................................... 4-46A4-15A. Vertical Fin Driveshaft Cover

Hinge Pin Installation ........... 4-46C4-16. Landi ng Gear ........................... 4-474-17. Landing Gear Crosstube

Deflection ............................. 4-504-18. Crosstube Damage Limits........ 4-514-19. Skid Tube Repair Limits........... 4-534-20. Landing Gear Skid Tube

Repair................................... 4-544-21. Tow Fitting Hole Elongation

Repair – Method I................. 4-564-22. Tow Fitting Hole Elongation

Repair – Method II................ 4-584-23. Repair of Landing Gear

Skid Tube Shoes.................. 4-61

LIST OF TABLES

Number Title Page

1-1. Support EquipmentRequired ............................ 1-4

1-2. Materials Required................. 1-41-3. Record of Applicable

Technical Directives........... 1-5

Number Title Page

4-1. Wind shield WiperTroubleshooting ............... 4-13


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TECHNICAL PUBLICATION DEFICIENCY REPORTS (TPDR)

INCORPORATION LIST

The follo wing TPDR are i ncorporated as p art of thi s chan ge. T his p age shallremain with this chang e; next chan ge will provid e n ew listing p age with latestTPDR incorporation.

ORIGINATOR REPORT CONTROL NUMBER

HML/A-167 0989 8-2007-0018

HMLA/T-303 CTPL 55167 2009 0041


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iv

WARNINGS APPLICABLE TO HAZARDOUS MATERIALS

Warnings in this man ual alert pe rsonnel to h azards associated with th e use of ha zardous

materials. Ad ditional i nformation related to hazardous mate rials i s provided in OPNAVINST5100.23, Na vy Occup ational Safety and Health (NAVOSH) p rogram ma nual, OPNAVINST4110.2, Navy Ha zardous Material Cont rol a nd Management (HMC&M), and the DO D 6050.5,Hazardous Materials Inf ormation Sy stem (HMIS) se ries publications. F or ea ch ha zardousmaterial used within the Navy, a Mat erial Safety Data Sh eet (MSDS) m ust be p rovided andavailable for review by users. Consult your local safety and health staff concerning any questionsregarding h azardous materials, MSDS, person al prote ctive equipment requireme nts, andappropriate handling and emergency procedures and disposal guidance.

Under the heading “HAZ ARDOUS M ATERIALS WA RNINGS”, compl ete h azardous m aterialwarnings are listed by (1) warni ngs sequentially assign ed index numbers, (2) material,(nomenclature, spe cification, inclu ding relat ed i cons), a nd (3) compl ete warnin gs, in cludingappropriate personal protective equipment requirements.

In the text of the ma nual, the caption “WARNING” will not be used fo r h azardous mate rialswarnings. Ha zards are cit ed by nu meric ide ntifier t hat relate s t o the compl ete wa rnings, thenomenclature and applicable spe cification of the hazardous m aterial, a nd appropriate i con(s).Users of hazardous materials shall refer to the complete warnings.

EXPLANATION OF HAZARDOUS MATERIALS ICONS

Biological The a bstract symbol bug shows that a material may contain b acteria o r viruse s that

present a danger to your life or health.

Chemical The symbol of drops of a liquid onto a hand shows that the material will cause burns or

irritation to human skin or tissue.

Cryogenic The symbol of a hand in a block of ice sho ws that the material is extremely cold and

can injure human skin or tissue.

Explosion The rapidly expanding symbol shows that the material may explode if subjected to high

temperature, sources of ignition, or high pressure.

Eye

The symbol of a person wearing goggles shows that the material will injure the eyes.

Fire The symbol of a flame shows that the material may ignite and cause burns.


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EXPLANATION OF HAZARDOUS MATERIALS ICONS (Cont)

Poison The symbol of a skull and crossbones shows that a material is poisonous or is a danger

to life.

Radiation The symbol of three circular wedges shows that a material emits radioactive energy and

can injure human tissue or organs.

Vapor The symbol of a human figure in a cloud shows that vapors of a material present a

danger to life or health through inhalation.

HAZARDOUS MATERIALS WARNINGS

Index Material Warning

1. PLASTIC POLISHP-P-560

Plastic Polish, P-P-560, is combustible andmay cause slight skin and eye irritation.Wear safety glasses/goggles and nitrilegloves. Consult the applicable MaterialSafety Data Sheet (MSDS) and localOccupational Safety and Health (OSH)regulations for additional information.

2. ALIPHATIC NAPHTHATT-N-95

TT-N-95 Aliphatic naphtha is flammableand can irritate skin and eyes. Avoidcontact. Overexposure to vapors cancause dizziness, headache and other

central nervous system effects. Avoidbreathing vapors. Use with adequateventilation. Wear nitrile gloves and safetyglasses. Consult the applicable MaterialSafety Data Sheet (MSDS) and localOccupational Safety and Health (OSH)regulations for additional information.

3. ZINC CHROMATE PUTTYMIL-PRF-8116A

Zinc Chromate putty can irritate skin andeyes upon contact. This material containschromate compounds that arecarcinogenic. Keep material off clothingand skin. Wash hands thoroughly after use

and before breaks. Wear gloves and safetyglasses during use. Consult the applicableMaterial Safety Data Sheet (MSDS) andlocal Occupational Safety and Health(OSH) regulations for additionalinformation.


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HAZARDOUS MATERIALS WARNINGS (Cont)


4. SEALING COMPOUNDMIL-S-11030, TYPE I

MIL-S-11030 Non-curing sealingcompound, is relatively non hazardous.Concentrated dust may be an eye orrespiratory tract irritant. Avoid breathingdust. As with all chemicals, avoid contact.PPE: none normally required. Consult theapplicable Material Safety Data Sheet(MSDS) and local Occupational Safety andHealth (OSH) regulations for additionalinformation.

5. METHYL-ETHYL-KETONE ASTM D740

Methyl-ethyl-ketone (MEK) ASTM D740 isflammable. Vapors are irritating to eyesand respiratory tract. Overexposure tovapors can cause headache, dizziness or

nausea. Contact with eyes can causesevere, permanent injury. Keep away fromsparks and open flames. Use only withadequate ventilation. Wear chemicalsplash proof goggles, and butyl rubbergloves. Consult the applicable MaterialSafety Data Sheet (MSDS) and localOccupational Safety and Health (OSH)regulations for additional information.

6. ADHESIVEMMM-A-1617

MMM-A-1617 is flammable and a skin andeye irritant. Overexposure to vapors ancause damage to the nervous system, liver

or a developing fetus. Avoid contact withskin and eyes. Use in a well ventilatedarea and avoid inhaling curing vapors. Usebutyl rubber gloves, safety goggles, andadequate ventilation. Consult theapplicable Material Safety Data Sheet(MSDS) and local Occupational Safety andHealth (OSH) regulations for additionalinformation.

7. SILICONE RUBBER ADHESIVEDAPCOTAC 3300 (A-A-2985)

Dapcotac 3300 Silicone rubber adhesivemay cause eye and skin irritation. May beflammable. Use only in a well ventilated

area. Long term overexposure could harmliver or kidney. Wear protective gloves andsafety glasses. Consult the applicableMaterial Safety Data Sheet (MSDS) andlocal Occupational Safety and Health(OSH) regulations for additionalinformation.


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8. SEALING COMPOUNDMIL-PRF-81733

MIL-PRF-81733 Corrosion InhibitiveSealing and Coating Compound isflammable and may contain chromatecompounds that are suspectedcarcinogens. Avoid contact with skin andeyes. Avoid breathing vapors. Wear glovesand safety glasses. Consult the applicableMaterial Safety Data Sheet (MSDS) andlocal Occupational Safety and Health(OSH) regulations for additionalinformation.

9. ISOPROPYL ALCOHOLTT-I-735

TT-I-735 Isopropyl Alcohol is flammable.Do not use near open flame or othersources of ignition. May irritate skin and

eyes. Inhalation may cause dizziness,headaches and irritation to respiratorytract. Wear chemical splash proof gogglesand gloves. Consult the applicable MaterialSafety Data Sheet (MSDS) and localOccupational Safety and Health (OSH)regulations for additional information.

10. CHEMICAL CONVERSION COATING FOR ALUMINUM AND ALUMINUM ALLOYSMIL-DTL-81706

MIL-DTL-81706 Chemical ConversionCoating contains carcinogenic chromatesand contact may irritate or burn skin andeyes. Burns may not be immediatelyobvious. Avoid contact with eyes, skin, or

clothing. Keep away from oils, fuels, andother chemicals. Personnel shall wearbutyl gloves, splash proof goggles, andfaceshield. A respirator may be requiredwhen handling dry material. Consult theapplicable Material Safety Data Sheet(MSDS) and local Occupational Safety andHealth (OSH) regulations for additionalinformation.

11. SEALING COMPOUND AMS-S-8802

AMS-S-8802 Sealant can irritate skin andeyes. Repeated or prolonged contact cancause an allergic skin reaction. Do not

sand or grind on cured material. Usegloves, safety glasses and adequateventilation. Consult the applicable MaterialSafety Data Sheet (MSDS) and localOccupational Safety and Health (OSH)regulations for additional information.


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12. MOLYBDENUM DISULFIDE GREASEMIL-G-21164

Molybdenum disulfide grease, MIL-G-21164, may cause skin irritation. Avoidcontact with skin and eyes. Wear nitrilegloves and safety glasses. Consult theapplicable Material Safety Data Sheet(MSDS) and local Occupational Safety andHealth (OSH) regulations for additionalinformation.

13. PETROLATUMVV-P-236

Petrolatum can irritate skin and eyes. Avoid contact and wash hands after use.Consult the applicable Material SafetyData Sheet (MSDS) and localOccupational Safety and Health (OSH)regulations for more information.

14. EPOXY PRIMERMIL-PRF-23377

MIL-PRF-23377 Epoxy Primer isflammable. Contains carcinogenicchromate compounds. Avoid prolonged orrepeated breathing of vapors. Avoidcontact with skin and eyes. Personnel shallwear butyl rubber gloves, and goggles.Spray application requires an approved,ventilated paint booth and may require arespirator. Consult the applicable MaterialSafety Data Sheet (MSDS) and mostrecent industrial hygiene survey for moreinformation.

15. ACRYLIC LACQUERMIL-PRF-81352

MIL-PRF-81352 Acrylic Lacquer isflammable and may be irritating to eyes,skin, and respiratory system. Long-termoverexposure can damage the brain andnervous system. Use chemical splashproof goggles, gloves, and goodventilation. Consult the applicable MaterialSafety Data Sheet (MSDS) and localOccupational Safety and Health (OSH)regulations for additional information.

16. XYLENE

TT-X-916

Xylene, TT-X-916, is flammable. Keep

away from heat, sparks and flame. Contactwith liquid or vapor can cause skin and eyeirritation, dermatitis, and drowsiness. PPE:gloves, goggles. Consult the applicableMaterial Safety Data Sheet (MSDS) andlocal Occupational Safety and Health(OSH) regulations for additionalinformation.


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17. TOLUENETT-T-548

Toluene, TT-T-548, is flammable. Keepaway from heat, sparks and flames.Overexposure can cause headache,dizziness and damage the nervoussystem. This material can harm adeveloping child during pregnancy. Avoidprolonged breathing of vapor andprolonged or repeated skin contact. WearSilvershield gloves, chemical splashgoggles and use with plenty of ventilation.Consult the applicable Material SafetyData Sheet (MSDS) and localOccupational Safety and Health (OSH)regulations for additional information.

18. SILICONE ADHESIVERTV-106

RTV Adhesive may irritate skin and eyes. Avoid contact with skin and eyes. Do notbreathe vapors. Wear chemical gogglesand rubber gloves. Consult the applicableMaterial Safety Data Sheet (MSDS) andlocal Occupational Safety and Health(OSH) regulations for additionalinformation.

19. POLYURETHANE COATINGMIL-PRF-85285

MIL-PRF-85285 High Solids PolyurethaneCoatings are flammable. Vapors can causeirritation of the skin, eyes, and respiratorytract. Overexposure can cause headaches

or difficulty breathing. Repeated orprolonged exposure can cause allergicskin rash or asthma. Avoid breathing ofvapors or mist. Personnel shall use gloves,goggles and adequate ventilation. Sprayapplication may require air-suppliedrespirator. Consult the applicable MaterialSafety Data Sheet (MSDS) and mostrecent industrial hygiene survey for moreinformation.


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20. WELDI NG MATERIALS Short-term e xposure to weldi ng fum es,gases or d ust may re sult in discomf ortsuch as dizziness, nausea, fever, drynessand/or irritation of nose, throat, and e yes.Skin se nsitivity may also be noted. Lo ng-term expo sure to fume s/gases/dust maycause p ulmonary irritation orpneumoconiosis. En sure welding i s d onewith a pro perly functionin g exhau st hood.Welding creates ultraviolet radiation. Wearproper weldi ng h elmet with ult ravioletprotective le ns, wel der's gloves, lea therapron, long sleeve shirt, and he aringprotection. Consult the ap plicable MaterialSafety Data Sheet (M SDS) and l ocal

Occupational Safety and Health (O SH)regulations for additional information.

21. FLUORESCE NT PENETRANT INSPECTION ASTM E1417

ASTM E14 17 Flu orescent Pe netrantmaterials may c ause irritation to skin andeyes. Avoid inhaling powder or vapors, anduse i n well-ventilated are a. Avoidprolonged or repe ated co ntact with skin.Wear nitrile gloves and safety gla sses.Consult th e appli cable Materi al S afetyData She et (MSDS ) and localOccupational Safety and Health (O SH)regulations for additional information.

22. HALON ASTM D5632

Halon, ASTM D 563 2, is a fireextinquishing media. Co ntact with liq uidmay cau se freeze r bu rns to eye s orfrostbite to skin. Overexposure may causelightheadedness, gid diness, shortness o fbreath, irregular heartbeat. Do not breathevapors. Protection: chemical resistantgoggles an d gloves wh en workin g withliquid. If exposed to va pors, re spiratoryprotection m ay be re quired. Con sultMSDS and safety offic e for guidance inrespirator selection. Service in well

ventilated area o nly for acci dentalinhalation do not give Epineph rine orsimilar drugs; remove to fresh ai r and callphysician. Ensu re good personal hygieneprior to eating, drin king, or smo king.Manufacturers' hazards may vary. Alwaysconsult proper MSDS.


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23. LUBRICATING OIL, GENERAL PURPOSEMIL-PRF-32033

MIL-PRF-32033, Gen eral p urposelubricating oil may irritat e skin o r e yes.PPE: rubber gloves and safety glasses.Consult th e appli cable Materi al S afetyData She et (MSDS ) and localOccupational Safety and Health (O SH)regulations for additional information.

24. POLYSULFIDE RUBBER COMPOUNDCA 1000

CA 100 0 Po lysulfide Rub ber Compoundmay dry an d crack skin upon prolongedexposure. Can cause tearing and cornealdamage upo n conta ct wi th eyes. Avoidprolonged in halation of vapors. Weargloves or use tools to prevent skin contact.Wear safety gla sses. Co nsult l ocal

Occupational Safety and Healthregulations and Material Safety Data Sheetfor additional information.


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1-1

SECTION I

INTRODUCTION

1-1. GENERAL.

1-2. This manual is one of a set of 17 separatemanuals that compose the organizationalmaintenance instruction manual for model HH-1N/UH-1N helicopter manufactured by BellHelicopter Textron, Fort Worth, TX. The needs of themaintenance specialist have been the determiningfactor in preparing these manuals which are tailoredto the systems of the helicopter. Each component ofthe helicopter, therefore, is covered according to itsfunction or purpose in relation to a system,regardless of whether the component is hydraulic,electrical, electronic, or mechanical in nature.Components that are not a functional part of anysystem, or instructions not affecting a specificsystem or component, are covered under theappropriate manual title.

1-3. SCOPE AND ARRANGEMENT OFMAINTENANCE INSTRUCTION MANUAL. Themanuals which compose the organizationalmaintenance instruction manual and their generalcontents are as follows:

GENERAL INFORMATION ANDCONDITIONAL INSPECTIONS


Aircraft Description and Dimensions Access and Inspection ProvisionsSafety InformationStowage InformationGround HandlingServicing and Lubrication DataEmergency ProceduresTorque DataSupport EquipmentConsumable MaterialsConditional Inspections

AIRFRAME AND LANDING GEARNAVAIR 01-110HCE-2-2

Fuselage Air Distribution SystemTailboomLanding Gear

POWER PLANTS AND RELATED SYSTEMSNAVAIR 01-110HCE-2-3

Power Section Air Management SystemOil Cooler SystemFuel Supply System

Auxiliary Fuel System

POWER PLANT GROUND OPERATIONAND CONDITIONING MANUAL

NAVAIR 01-110HCE-2-3.1

Ground Operations Procedures and LimitsTroubleshooting

Engine Conditioning

POWER TRAIN SYSTEMNAVAIR 01-110HCE-2-4

Main DriveshaftTransmissionTransmission Oil SystemMain Rotor Mast AssemblyTransmission Drive QuillsTail Rotor Drive System

FLIGHT CONTROLS ANDHYDRAULIC SYSTEMS


Collective Pitch Control SystemCyclic Control SystemSynchronized Elevator SystemTail Rotor Control SystemFlight Control Hydraulic SystemRotor Brake System

MAIN AND TAIL ROTOR GROUPSNAVAIR 01-110HCE-2-6

Main Rotor InstallationTail Rotor Installation

Main and Tail Rotor Tracking and Balance

UTILITY SYSTEMSNAVAIR 01-110HCE-2-7

Litter Equipment All-Weather CoversCargo NetsRescue Hoist


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1-2

Troop SeatsFormation Lighting

Air TransportabilityWinterization Heating

ARMAMENT SYSTEMSNAVAIR 01-110HCE-2-8

External Stores Support Assembly (LH/RH)BRU-20/21 A/A Bomb Ejector RacksM-60D Gun Adapter AssemblyM-218 (GAU-16/A) Gun Adapter AssemblyCA-513E Optical Reflex SightGAU-17 Armament Subsystem

ELECTRONIC COUNTERMEASURE SYSTEMSNAVAIR 01-110HCE-2-9

Radar Warning System – AN/APR-39(V)1Countermeasures Dispensing System –

AN/ALE-39/AN/ALE-47Countermeasures Set System – AN/ALQ-144Missile Warning Set System – AN/AAR-47Radar Signal Detecting Set – AN/APR-39A(V)2Laser Warning System – AN/AVR-2

INSTRUMENTSNAVAIR 01-110HCE-2-10

Instrument PanelFlight InstrumentsNavigation InstrumentsEngine InstrumentsPitot-Static System

Miscellaneous Instruments

ELECTRICAL SYSTEMSNAVAIR 01-110HCE-2-11

DC System AC SystemLighting SystemCaution and Warning SystemEngine Controls and Accessories SystemMiscellaneous Electrical Systems

AVIONICS SYSTEMS

NAVAIR 01-110HCE-2-12 (UH-1N)

Communication SystemsNavigation SystemsIdentification System

Automatic Flight Control System – Electrical

AVIONICS SYSTEMSNAVAIR 01-110HCE-2-12-1 (HH-1N)

Communication SystemsNavigation SystemsIdentification System

Automatic Flight Control System – Electrical

WIRING DIAGRAMSNAVAIR 01-110HCE-2-13 (UH-1N)

Wiring Identification CodesWire Replacement DataWiring Diagrams

AC and DC Power SystemsCommunication SchematicsNavigation SchematicsComponent Wiring Diagrams

WIRING DIAGRAMSNAVAIR 01-110HCE-2-13-1 (HH-1N)

Wiring Identification CodesWire Replacement DataWiring Diagrams

AC and DC Power SystemsCommunications SchematicsNavigation SchematicsComponent Wiring Diagram

COMMUNICATIONS SECURITY SYSTEMSCERTIFICATION PROCEDURE


1-4. ASSOCIATED AIRCRAFT MANUALS.Manuals in the maintenance instruction manual donot contain instructions for overhaul of components.Such instructions are issued as separate manuals ofoverhaul instructions for the individual components.Intermediate level maintenance instructions arecontained in Intermediate Maintenance Manual,NAVAIR 01-110HCE-2-15. Instructions for repair ofthe helicopter structure are contained in StructuralRepair Manual, NAVAIR 01-110HCE-3. Datanecessary for obtaining replacement parts, and

complete identification of parts, is contained inIllustrated Parts Breakdown, NAVAIR 01-110HCE-4Series. To obtain these publications, refer toNAVSUP Publication 2002.


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1-3

1-5. LUBRICATION AND SERVICING.

1-6. Assembly a nd in stallation lu brication an dservicing requirements for systems and componentscovered in th is manual a re inclu ded as part of thenormal mai ntenance in structions. For pe riodic

lubrication re quirements, refer to th e approp riatemaintenance requi rements cards. For pe riodicservicing requirements, re fer to servici ng, Gen eralInformation, NAVAIR 01-110HCE-2-1.

1-7. SUPPORT EQUIPMENT.

1-8. Support equi pment req uired for maint enanceof systems and components covered in this man ualis listed in table 1-1. For a complete list of suppo rtequipment, refer to sup port eq uipment, Gene ralInformation, NAVAIR 01-110HCE-2-1. When an itemof support equipment i s not available, an approvedalternate identified in the activity’s Individual MaterialReadiness List (IMRL) may be substituted.

1-9. CONSUMABLE MATERIALS.

1-10. Consumable material s requi red formaintenance of systems and components covered inthis manual are listed in table 1-2. For a complete listof c onsumable ma terials, r efer to c onsumablematerials, General Information, NAVAIR 01-110HCE-2-1.

1-11. RECORD OF A PPLICABLE TECHN ICALDIRECTIVES.

1-12. Table 1 -3 i s a list of a pplicable te chnicaldirectives wh ich affect in structions in this manualwhere a pplicable. Instruct ions a re identified by thetechnical di rective numb er. Refe rence in text totechnical di rective num bers are fo r all Parts o r

Amendments, unless otherwise specifically noted. Ata specified time following incorporation of a technicaldirective, or whe n it i s known all appli cablehelicopters and e quipment have been m odified,obsolete information and referen ce to the techni caldirective will be deleted from text. For a complete listof technical directives, ref er to tech nical directives,General Information, NAVAIR 01-110HCE-2-1.

1-13. QUALITY ASSURANCE.

1-14. Quality assurance requirements are indicatedin this m anual by italicizing a procedural step an dthe legend (QA) will appear at the end of the step

when an inspection is required before proceeding tothe next ste p, or by summarizing at the end ofmaintenance pro cedure, i nspections th at are to beperformed after completion of the procedure.

1-15. SPECIAL ABBREVIATIONS AND

SYMBOLS.

1-16. The special abbreviations and symbols in thismanual are as follows:

AFC Airframe ChangeBL Butt LineCF3Br Monob romotrifluoromethaneFT-LB Foot PoundFS Fusel age StationID Inside DiameterIN Inc hLB Pound

LH Left HandMAX MaximumMIN MinimumOD Outsid e DiameterRH Right HandVDC Volts Direct Current

1-17. WARNINGS, CAUTIONS, AND NOTES.

1-18. Explanation of usag e of warnings, ca utions,and notes is as follows:

Refers to a procedure or practice that, if notcorrectly followed, could result in injury,death, or long-term health hazard.

Refers to a procedure or practice that, if notcorrectly ob served, could result in dam ageto or destruction of equipment.

NOTE

Refers to a pro cedure or condition thatrequires additional emphasis or explanation.


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1-4 Change 1

TABLE 1-1. SUPPORT EQUIPMENT REQUIRED

NomenclaturePart No./

Type Designation

Scale, 10 lbs capacity ---

Spanner Wrench (Special) XW20509

Special Tool BH120-1032M2

Torque Wrench, 60-300 inch-pounds ASME B107.14

TABLE 1-2. MATERIALS REQUIRED

NomenclatureSpecification No./

Part No.

Adhesive MMM-A-1617, Type lll

Adhesive, Silicone RTV-106

Adhesive, Silicone Rubber Dapcotac 3300 (A-A-2985)

Alcohol, Isopropyl TT-I-735

Chamois, Leather, Sheepskin, Oil Tanned KK-C-300

Cloth, Abrasive, Aluminum Oxide ANSI-B74.18, No. 180 Grit or No. 400 Grit

Cloth, Glass, Finished, for Resin Laminates, 120 or 127 Weave SAE AMS-C-9084

Cloths A-A-59323

Coating, Chemical Conversion for Aluminum and Aluminum Alloys

MIL-DTL-81706, Class 3

Coating, Polyurethane MIL-PRF-85285

Compound, Polysulfide Rubber CA 1000

Compound, Sealing MIL-PRF-81733,Type ll-1/2

Compound, Sealing AMS-S-8802, Class B2

Compound, Sealing MIL-S-11030, Type l

Grease, Molybdenum Disulfide MIL-G-21164

Lacquer, Acrylic MIL-PRF-81352

Mats, Abrasive A-A-58054

Methyl-Ethyl-Ketone ASTM D740

Naphtha, Aliphatic TT-N-95

Oil, Lubricating, Special Purpose MIL-PRF-32033

Penetrant, Fluorescent ASTM E1417

Petrolatum VV-P-236

Polish, Plastic P-P-560

Primer, Epoxy MIL-PRF-23377

Putty, Zinc Chromate MIL-PRF-8116A


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1-5/(1-6 Blank)

TABLE 1-2. MATERIALS REQUIRED (Cont)

NomenclatureSpecification No./

Part No.

Toluene TT-T-548

Wire, Safety or Lock, Copper, Cadmium Plated MS20995CY20

Xylene (Use until supply is exhausted) TT-X-916

TABLE 1-3. RECORD OF APPLICABLE TECHNICAL DIRECTIVES

Type/No. Date Title/ECP No. Date Inc.

AFC 112 8 May 1975 Replacement of the A-20 Fire Extinguisher withFR23-4-11848 Fire Extinguisher

–

AFC 251 30 Apr 1991 Improved Pilot/Copilot Seat Cushion Provisions(RAMEC PNCLA 20-89)

1 Jun 1993

AFC 263, Amend 3

14 Jul 1993 Single Engine Heat/Defrost Capability Modification(RAMEC PNCLA 19-90)

30 Jun 1994

AFC 381 8 Nov 2005 Conductive Gaskets on the Turrent FLIR Unit (TFU)Interface Plate and the Turrent Fairing Assembly,Installation of

1 Feb 2006

IAFC 366 28 Feb 2003 H-1N Tailboom Strake Kit, Installation of(WUC 113660)

1 Feb 2006


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2-1

SECTION II

SYSTEM DESCRIPTION

2-1. FUSELAGE.

2-2. The fuselage is of combinedsemimonocoque and reinforced-shell construction.(See figure 2-1.) Lower (1) and upper (2) hingednose compartment doors provide access to theelectrical compartment. A windshield wiper (3) islocated on each of the two acrylic plastic or glasswindshields (4). Crew doors (11), cabin panel doors(9) and passenger-cargo doors (8) on both sides ofthe helicopter permit entrance and exits. Acrylicplastic nose compartment window (12), roofwindows (5) and windows in doors permit a widerange of visibility. Transmission (6) and engine (7)cowling provide access to those components. Crewseats (10) are located in the forward cabin area. Thecargo-passenger area is equipped with cargo tie-down rings and studs, and is available for theinstallation of a cargo net, troop seats, litters orblackout curtains, when required to perform aparticular mission.

2-3. WINDSHIELDS AND WINDOWS.Transparent acrylic plastic or glass windshields andacrylic plastic windows are provided for occupantvisibility.

2-4. WINDSHIELD WIPERS. Windshield wipersare provided for both pilot and copilot. A five positionrotary switch on the overhead console permitsoperation of the wipers at low, medium or highspeed. Also included on the switch is an OFF andPARK position.

2-5. DOORS, PANELS AND FAIRINGS. Doors, panels and fairings are provided for accessto various compartments and components in thehelicopter airframe.

2-6. Nose Access Doors. Two hinged doors give

access to the nose compartment. The lower door (1,figure 2-1) is of aluminum alloy construction andswings down after removal of the attaching studs.The upper door (2) is of fiberglass-faced honeycombconstruction and swings up after release of sixmanually activated latches.

2-7. Crew Doors. The crew doors, located at pilotand copilot stations, are hinged at forward sides andprovided with windows, one of which opens bysliding vertically and can be adjusted to desiredpositions. The latch, near the aft edge of the door,has inner and outer handles and is also connectedto an auxiliary handle stowed flush into the innersurface of the door within reach from the crew seat.The auxiliary handle can be pulled outward formovement forward to locked or aft to unlockedposition, and is spring-loaded to return to flush,stowed position. Jettison or removal of door can beaccomplished by pulling an EMERGENCYRELEASE handle, causing hinge pins to bewithdrawn, and the latch striker, on the doorpost, to

be disengaged.

2-8. Passenger – Cargo Doors. A large slidingdoor on each side of the fuselage gives access tothe cargo passenger area of the cabin. The dooroperates on rollers and tracks and has a hook-typelatch for closed position. In open position, the aftedge of the door rests within two padded retainerstraps while a retainer on the forward edge fits overa plate stud on the cabin aft bulkhead, and can besecured by a lockpin. Two windows in each doorhave emergency handle latches for use as escapehatches.

2-9. Cabin (Hinged) Panels. A cabin (hinged)panel is attached to the doorpost, forward of eachsliding passenger – cargo door, to provide a widerpassenger cargo opening. Each panel is easilyremovable, has a latch with pins engaged instructural channels at top and bottom, and apositioning spring with a detent to hold panel openfor loading and unloading operations.

2-10. Miscellaneous Access Doors, InspectionPanels and Fairings. Doors and panels areprovided at various locations on the fuselage foraccess to interior areas. (Refer to NAVAIR 01-

110HCE-2-1.) Fairings cover joints and openings togive an aerodynamically clean contour. Two basictypes of construction are used; laminated glass fiberand sheet metal or glass fiber sheet bonded tohoneycomb core. Screws or twist type fasteners holdthe doors in place.


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2-2

Figure 2-1. Fuselage Station (Typical)

2-11. TRANSMISSION AND ENGINE COWLING.(See figure 2-2.) Major components of the aluminumalloy transmission and engine cowling are the

transmission fairing (1), the air inlet fairings (2),engine top cowl panels (3), engine upper cowls (4),reduction gearbox top cowls (5), reduction gearboxtop panel (6), oil cooler fairing (7), oil cooler airscoops (8), oil cooler support cowling (9), reductiongearbox side cowlings (10), an access door (11),engine lower cowls (12), pillar installation (13) andreduction gearbox oil filler door (14).

2-12. CREW SEATS. Pilot and copilot seats areadjustable fore-and-aft on floor tracks, and verticallyon tubular frames. Tilt latches are provided foremergency use to release the seat to be tilted back

for rapid removal of occupant. The seat bucket isceramic armor plate and is equipped with seat andback cushions, a lap safety belt and shoulderharness restrained by an inertia reel. When missionrequires, armor side panels are attached.

2-13. NOSE ARMOR PANELS. Two ceramic armorpanels are mounted, when mission requires, onsupports below and forward of tail rotor control

pedals.2-14. INERTIA REEL AND SHOULDERHARNESS. An inertia reel shoulder harness with amanually operated control handle is located on thecabin floor behind each crew seat. The inertia reel isa mechanical restraining device that is designed tohold crew members in a normal seated positionduring any maneuver which would tend to pitch themforward. Each reel is connected to a shoulderharness with a web strap. An automatic lockingmechanism, a webbing roller and a manual controlare incorporated in each unit.

2-15. CARGO TIE-DOWN FITTINGS. (See figure 2-3.) The cargo floor is designed to support amaximum load density of 100 pounds per squarefoot. Tie-down fittings are mounted on the floor forthe purpose of security of cargo.


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2-3

Figure 2-2. Transmission and Engine Cowling


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2-4

2-16. FIRE EXTINGUISHERS. On helicoptersmodified by AFC 112, two hand-operatedmonobromotrifluoromethane (CF3Br) fireextinguishers are provided in the forward cabin area.The pilot fire extinguisher is stowed in a bracketattached to the instrument pedestal. On helicopterBuNo. 159694 and subsequent, two hand-operatedcarbon dioxide type fire extinguishers are provided.One is stowed in a bracket attached to cabin floor

just aft of instrument pedestal, and the other isstowed in a bracket attached on the inboard side ofthe left hinged panel. The mounting brackets forboth types of extinguishers are of the quick openingtype for rapid removal.

2-17. AIR DISTRIBUTION SYSTEM.

NOTE

For winterization kit, refer to NAVAIR 01-

110HCE-2-7.

2-18. The cabin air distribution system includes twosubsystems and one emergency system providingoptional alternate use of heated or unheated air fromseparate sources. Functional separation of thesubsystems is located by the flow-actuated Y-valveslocated under the two windshield defrost-defognozzles. Use of the cabin heating-defrosting systemcan be restored in the event of a single enginefailure by using an Emergency Override Switch. Thisswitch is located directly below the AN/APX-72Control Panel on the pilot side of the centerpedestal.

2-19. The cabin heating-defrosting system usesbleed air from the engine compressors as a heatsource and to pump air to outlets on both doorposts,on sides of the control pedestal, in lower forward

window areas, and to nozzles at both windshields.The system is controlled by switches on theoverhead console, a temperature selecting dial onthe right-hand doorpost, and a control lever on theright-hand side of the instrument panel pedestal.

2-20. The ventilating-defogging system uses ram airfrom two intake grilles on the cabin nose, withoptional use of two blowers, for delivery to thewindshield nozzles and to outlets ahead of pilot andcopilot stations. Air intake is controlled by anactuating knob. The blowers are controlled by theoverhead panel switch.

2-21. TAILBOOM. The semimonocoque tailboom isattached to the fuselage at four points. Hinged tailrotor driveshaft covers on the top and two accessdoors, attached to the structure by screws, on thebottom to facilitate maintenance. The tailboom

supports the synchronized elevator, the tail skid, tailrotor driveshafts and gearboxes and the tail rotorassembly.

2-22. LANDING GEAR. The skid type landing gearused on the HH-1N/UH-1N helicopter consists of twoskid tubes which are attached to the ends of twoarched crosstubes. All tubes are constructed ofdrawn aluminum alloy tubing. The crosstubes aretaper chemical milled for proper energy absorption.

Aluminum alloy saddles attach the skid tubes to thecrosstubes. Each skid tube is equipped withmagnesium alloy step and a steel tow ring on theforward end. Two detachable steel abrasion shoesare affixed to the bottom of each skid tube. Eyeboltfittings, for mounting ground handling wheelassembly, and an aluminum end cap are also part ofeach skid tube.


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2-5

Figure 2-3. Cargo Deck Fittings (Sheet 1 of 3)


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2-6

Figure 2-3. Cargo Deck Fittings (Sheet 2)


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2-7/(2-8 Blank)

Figure 2-3. Cargo Deck Fittings (Sheet 3)


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3-1/(3-2 Blank)

SECTION III

SUPPORT EQUIPMENT MAINTENANCE

3-1. GENERAL.

3-2. Maintenance of support equipment used inthis manual is not applicable.


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4-1

SECTION IV

ORGANIZATIONAL MAINTENANCE

4-1. WINDSHIELDS AND WINDOWS.

PLASTIC POLISH 1P-P-560

4-2. CLEANING. Wash glass windshields withwater. Dry with a soft, clean cloth, A-A-59323, typeII. A chamois, KK-C-300, may be used to dry glasswindshields. Clean acrylic plastic windshields withplastic polish, P-P-560.

NOTE

Procedures for removal and installation ofwindshields are the same regardless ofmaterial.

4-3. REMOVAL – WINDSHIELD.

a. Cut Iockwire, loosen screw, remove bolt atwiper shaft and lift wiper assembly from shaft.

b. Remove free air temperature gage (pilotwindshield only) if installed.

c. Remove nuts, washers and screws attachingwindshield to fuselage.

d. Separate windshield from sealing compoundand remove windshield from helicopter.

4-4. INSPECTION AND REPAIR – WINDSHIELD.

a. Refer to figure 4-1 for damage and repairlimits for plastic windshield.

b. Inspect glass windshield for abrasions,scratches, cracks, holes and obstructions to visionas follows:

(1) Glass windshield for cracks, holes orsurface pits which exceed a maximum length of0.125 inch (3.175 millimeters) or form a patternobjectionable to the viewer are not permitted.

(2) Scratches which exceed a depth of 0.005inch (0.127 millimeters) and a length of 3.00 inches(76.2 millimeters) are not permitted on either

the inboard or outboard surface of the windshield. Ifany of these conditions exist, the windshield must bereplaced at the earliest opportunity.

4-5. INSTALLATION – WINDSHIELD.

NOTE

Whenever plexiglas windshield is replacedby a glass windshield and/or glasswindshield replaced by a plexiglaswindshield, a weight and balance checkshould be made to assure the C.G. positionis within the allowable range as perapplicable maintenance manual. Each glass

windshield increases the weight by 6 to 8pounds. Glass windshields areinterchangeable and do not have to beinstalled as a pair.

a. Remove all sealing compound from mountingflange.

ALIPHATIC NAPHTHA 2TT-N-95

b. Wipe and clean mounting flange with clothdampened with aliphatic naphtha, TT-N-95.

c. Position windshield against flange.

NOTE

Do not trim windshield to final size until all

mounting holes have been drilled.

d. Back drill two holes on each edge ofwindshield using holes in mounting flange as atemplate.

e. Temporarily secure windshield to mountingflange with four screws, washers and nuts. Back drillremaining holes in windshield using holes in flangeas a template.


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4-2

Figure 4-1. Window/Windshield Damage Limits (Sheet 1 of 2)


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4-3

Figure 4-1. Window/Windshield Damage Limits (Sheet 2)


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4-4

f. Determine proper edge distance, markwindshield and remove.

g. Trim windshield edge to proper size.

ZINC CHROMATE PUTTY 3MIL-PRF-8116A

SEALING COMPOUND 4MIL-S-11030, TYPE I

h. Remove all dust and foreign matter fromwindshield mating area and from windshieldmounting flange and apply a 0.12 inch diameterbead of zinc chromate putty, MIL-PRF-8116A orsealing compound, MIL-S-11030, type I.

i. Position windshield in mounting flange, alignholes and install screws, washers and nuts.

j. Remove excess sealing compound fromaround windshield and repaint as necessary.

k. Install windshield wiper assemblies andIockwire. Install free air temperature gage, ifremoved. (QA)

4-6. REMOVAL – CREW DOOR ADJUSTABLEWINDOWS.

a. Remove screws attaching plastic handle towindow.

b. Remove screws holding cover plate tobottom door channel in door frame below thewindow.

c. Guide window downward through slot inbottom of door assembly and remove from door.

4-7. INSPECTION AND REPAIR – CREW DOORADJUSTABLE WINDOWS. Refer to figure4-1 for damage and repair limits.

4-8. INSTALLATION – CREW DOORADJUSTABLE WINDOWS.

a. Guide window upward through slot in bottomof door channel and into side window channels.

NOTE

Check progress through opening in aft edgeof door.

b. Place window in partially closed position andattach window handle and bottom door channelcover plate with screws.

4-9. REMOVAL – CREW DOOR FORWARDWINDOWS.

a. Remove nuts, washers and screws attachingwindow to door.

b. Separate window from sealing compound,and remove window from helicopter.

4-10. INSPECTION AND REPAIR – CREW DOORFORWARD WINDOWS. Refer to figure 4-1 for

damage and repair limits.

4-11. INSTALLATION – CREW DOORFORWARD WINDOWS.

a. Remove all sealing compound from mountingflange.



c. Position window against mounting flange.

NOTE

Do not trim windshield to final size until all

mounting holes have been drilled.

d. Back drill two holes in each edge of windowusing holes in flange as a template.

e. Temporarily secure window to flange withscrews, washers and nuts.

f. Back drill remaining holes in window usingholes in template as a guide.


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4-5

g. Determine proper edge distance, markwindow and remove.

h. Trim window to proper size.



i. Remove all dust and foreign matter frommating area on window and flange and apply a 0.12

inch diameter bead of zinc chromate putty, MIL-PRF-8116A or sealing compound, MIL-S-11030,type I to window mating surface.

j. Position window in flange, align holes andsecure with screws, washers and nuts.

k. Remove excess sealing compound fromaround window and repaint as necessary.

4-12. REMOVAL – CREW DOOR UPPERWINDOWS.

a. Remove nuts, washers and screws

attaching window to doors.b. Separate window from sealing compound

and remove window from helicopter.

4-13. INSPECTION AND REPAIR – CREW DOORUPPER WINDOWS. Refer to figure 4-1 for damageand repair limits.

4-14. INSTALLATION – CREW DOOR UPPERWINDOWS.

a. Remove old sealing compound frommounting flange.


b. Clean mounting flange using cloth dampenedwith aliphatic naphtha, TT-N-95. Position windowover opening. Trim surplus edge to permit window tobe in mounting position against flange.

NOTE

Do not trim window to final size until allmounting holes have been drilled.

c. Position window against mounting flange.

d. Back drill two holes on each edge of windowusing holes in mounting flange as a template.

e. Temporarily secure window to mountingflange with four screws, washers and nuts. Drillremaining holes in window using holes in mountingflange as a template.

f. Determine proper edge distance, markwindow and remove. Trim window edge to propersize.

g. Remove all dust and foreign matter fromwindow mating area and from window mountingflange.

h. Apply a 0.12 inch diameter bead of zincchromate putty, MIL-PRF-8116A or sealingcompound, MIL-S-11030, type I to mating surface.

i. Position window in mounting flange, alignholes and install screws, washers and nuts.

j. Remove excess sealing compound fromaround window and repaint as necessary.

4-15. REMOVAL – CABIN ROOF WINDOWS.

a. Remove nuts, washers and screws attachingwindow to roof structure.

b. Separate window from sealing compoundand remove window from helicopter.

4-16. INSPECTION – CABIN ROOF WINDOWS. Refer to figure 4-1 for damage and repair limits.

4-17. INSTALLATION – CABIN ROOFWINDOWS.



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4-6



c. Position window over opening. Trim onlyenough surplus material from edge of window topermit proper alignment of window against mountingflange.

NOTE

Do not trim window to final size until allmounting holes have been drilled.

d. Position window against mounting flange.Back drill two holes on each edge of window usingholes in mounting flange as a template.

e. Temporarily secure window to mountingflange with screws, washers and nuts. Drillremaining holes in window using holes in mountingflange as a template.

f. Determine proper edge distance, markwindow and remove. Trim window edge to propersize.

g. Remove all dust and foreign matter fromwindow mating area and from window mountingflange.



h. Apply a 0.12 inch diameter bead of zincchromate putty, MIL-PRF-8116A or sealingcompound, MIL-S-11030, type I to mating surface.

i. Position window in mounting flange, alignholes and install screws, washers and nuts.

NOTE

All screws, nuts and washers shall be ofaluminum material to prevent interferencewith compass.

j. Remove excess sealing compound fromaround window and repaint as necessary.

4-18. REMOVAL – LOWER CABIN NOSEWINDOWS.

a. Remove nuts, washers and screws attachingwindows to frame.

b. Separate window from sealing compoundand remove window from helicopter.

4-19. INSPECTION – LOWER CABIN NOSEWINDOWS. Refer to figure 4-1 for damage and

repair limits.

4-20. INSTALLATION – LOWER CABIN NOSEWINDOWS.



c. Position window over opening. Trim surplusedge to permit window to be in mounting positionagainst flange.


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4-7

NOTE

Do n ot trim wind ow to final si ze un til allmounting holes have been drilled.

d. Position win dow agai nst mounting flange.Back drill two holes in each edge of window using

holes in mounting flange as a template.

e. Temporarily se cure window to m ountingflange with scre ws, wa shers and nuts. Drillremaining holes in window using holes in flange as atemplate.

f. Determine proper e dge distan ce, markwindow, a nd remove. Trim window e dge to propersize.

g. Remove all dust and foreign m atter fromwindow mati ng a rea a nd from win dow m ounting

flange.


SEALING COMPOUND 4

MIL-S-11030, TYPE I

h. Apply a 0.1 2 inch diam eter be ad of zin cchromate p utty, MIL-PRF-811 6A or sealin gcompound, MIL-S-11030, type I to wi ndow matingsurface.

i. Position window i n mou nting flang e, alignholes and install screws, washers and nuts.

j. Remove exce ss seali ng compound fromaround window and repaint as necessary.

4-21. REMOVAL – CARGO DOO R WIN DOWS.

(Refer to paragraph 4-52.)

4-22. INSPECTION – CARGO DOOR WI NDOWS. Refer to figure 4-1 for damage and repair limits.

4-23. INSTALLATION – CA RGO DOO RWINDOWS. (Refer to paragraph 4-53.)

4-24. REMOVAL – CABIN PANEL WINDOWS.

a. Remove riv ets and wa shers that attachwindow to cabin panel door.

b. Separate wi ndow from sealing compoundand remove window from helicopter.

c. Remove stiffener from top of windo w and

retain for installation.

4-25. INSPECTION – CABIN P ANEL WINDOWS. Refer to figure 4-1 for damage and repair limits.

4-26. INSTALLATION – CA BIN P ANELWINDOWS.

a. Remove old seali ng comp ound frommounting flange and stiffener.


b. Wipe and clean mounting flange and stiffenerwith cloth d ampened with aliphati c naphtha, TT -N-95.

c. Position window over o pening. Trim onlyenough surplus material f rom edge of win dow topermit proper alignment of window against mountingflange.

NOTE

Do not trim windows to final size u ntil allmounting holes have been drilled.

d. Position win dow agai nst mounting flange.Back drill two holes on each edge of windo w usingholes in mounting flange as a template.

e. Temporarily se cure window to m ountingflange with scre ws, wa shers and nuts. Drillremaining holes in win dow using hol es in mountingflange as a template.

f. Determine proper e dge distan ce, markwindow an d remove. Trim windo w edg e to prope rsize.

g. Remove all dust and foreign m atter fromwindow mati ng a rea a nd from win dow m ountingflange.


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4-8 Change 1



h. Apply a 0.1 2 inch diam eter be ad of zin cchromate p utty, MIL-PRF-811 6A or sealin gcompound, MIL-S-11030, type I to mating surface.

i. Position stiffener on in board side of do or atthe top of the window.

j. Position window i n mou nting flang e, alignholes and install rivets and washers.

k. Remove ex cess seali ng compound fromaround window and repaint as necessary.

4-27. WINDSHIEL D WIPERS.

Do not ope rate wipe rs o n dry wind shield;scratching will result.

4-28. OPERATIONAL CHE CK. Spray water o nwindshield. Rotate switch on overhead console to allpositions and observe operation of wipers.

4-29. TROUBLESHOOTING. Refer to table 4-1 fortroubleshooting the windshield wiper system.

4-30. REMOVAL – WINDSHIELD WIPER BLADE.

a. Remove nut attaching blade to wiper arm.

b. Remove blade from arm.

4-31. INSTALLATION – WI NDSHIELD WIPERBLADE.

a. Position wiper blade on arm.

b. Install attaching nut.

c. Use spe cial wre nch, XW20509 and adju stpressure of blade on windshield to 6 -3/4 pou nds,measured at the intersection of the wip er blade andwiper arm. (See figure 4-2.)

4-32. REMOVAL – MOTOR AND CONVERTER.

NOTE

Assure battery switch is in OFF position.

a. Lift arm up to insert pi n in a rm to relievespring pressure. Remove nut and washer attachingwiper arm a nd blad e to serrate d end of converte routput driveshaft and remove arm and blade.

b. Disconnect e lectrical rece ptacle fro m motorand converter assembly, and cover re ceptacle withinsulating tape.

c. Remove screws which attach h ead guardassembly to windshield wi per support bracket, andremove head guard assembly.

d. Remove four bolts, wa shers, and nuts whichattach moto r and converter asse mbly to sup portbracket, and remove motor and converter assembly.

4-33. INSTALLATION – MOTOR ANDCONVERTER. (See figure 4-2.)

a. Position mot or an d converter assembly onsupport bra cket, with co nverter outp ut driveshaft

projecting through mounting hole in cabin structure,and install four attaching nuts, washers and bolts.

b. Position head guard assembly over motorand conve rter assembly and supp ort bra cket andinstall two attaching screws.

c. Remove insulating tap e from el ectricalreceptacle a nd connect receptacle to motor a ndconverter assembly.

d. Prior to in stallation of arm asse mbly,straighten a rm in a vise and insert a 3/32 pin

between mo unting hea d and arm, to tempora rilyhold m ounting he ad straight with arm whileassembly is being inst alled on se rrated end ofconverter output driveshaft.

e. The m otor converter a ssembly should beactuated to PARK positio n prio r to att aching wiperarm.


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4-9

f. Position arm assembly on converter outputdriveshaft in such a manner that wiper blade isparallel to, and approximately 5.5 inches below,upper inboard edge of windshield.

g. Remove 3/32 temporary pin, and installattaching washer and nut.

h. Use special wrench XW20509 and adjustpressure of blade on windshield to 6-3/4 pounds,measured at intersection of wiper blade and wiperarm.

Cover windshield with paper when testing sothat blade does not operate on a drywindshield.

i. Check sweep of wiper on windshield by smallincrement movements of blade on the windshield.Momentarily rotate operating switch to accomplishthis check.

NOTE

If wiper arm and blade have been properlyinstalled, arm will move through a 64 degreearc, and with operating switch in PARKposition, wiper blade will come to restapproximately 5.5 inches below the upper

edge of windshield, where it will not obstructnormal vision.

4-34. DOORS, PANELS AND FAIRINGS.

4-35. SEAL REPLACEMENT – DOORS,COWLINGS AND FAIRINGS.

NOTE

Seals may be either rubber or siliconecomposition. Bonding procedure is differentfor each type. Seals subjected to fuel or oilcontamination (use in the pylon transmission

and engine compartment) should be ofpolysulfide or neoprene (rubber type).

a. Determine type of seal being replaced bycutting a small specimen from damaged seal andsubjecting it to flame. Silicone seals are more rapidlyaffected by flame and will leave a gray ash residue.Rubber type seals are much more fire resistant andwill leave a black ash residue.

b. Remove all paint and primer from metalsurface where seal is to be applied.

METHYL-ETHYL-KETONE 5 ASTM D740

c. Clean new seal and metal where new seal isto be applied with methyl-ethyl-ketone, ASTM D740or equivalent, and dry with clean cloth.

NOTE

It is necessary to thoroughly clean surfacesbefore sanding to preclude working anyforeign matter into pores of material.

d. Sand mating surfaces of seal and metal with180 grit sandpaper.

e. Clean sanded surfaces with methyl-ethyl-ketone, ASTM D740 or equivalent, and dry withclean cloth.

f. Bond rubber type (black ash) seals asfollows:

ADHESIVE 6MMM-A-1617

(1) Apply an even coat of rubber adhesive,MMM-A-1617, type III, to bond surfaces of seal andmetal.

NOTE

Type III adhesive shall be used for bonding.Type I and type II are not acceptable.

(2) Allow adhesive to air dry 10 – 15 minutesat 75°F (23.5°C) or above. Adhesive should beaggressively tacky and adhere, but not transfer, tofinger when touched.

(3) Repeat steps (1) and (2) above. Secondcoat is mandatory to obtain good adhesion.


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4-11

(c) Carefully remove strip and allow sealantto cure.

(2) Helicopter Structure and Gasket.

(a) Run a length of masking tape 0.03 to0.06 inch adjacent to gasket edge.

(b) Clamp a 0.030 inch thick strip ofaluminum sheet over gasket, even with the insideedge of gasket.

(c) Repeat application of sealant as in sub-steps a.(1)(b) and a.(1)(c).

4-37. INSTALLATION OF CONDUCTIVEGASKET. (Usable after Compliance with AFC 381.)

ISOPROPYL ALCOHOL 9TT-I-735

CHEMICAL CONVERSION COATING FOR ALUMINUM AND ALUMINUM ALLOYS 10MIL-DTL-81706

NOTE

Refer to Figure 4-5 for gasket application.

Surfaces that come in contact with thegasket shall be free of paint, dust, oil,grease, fingerprints and other contaminationprior to installation. Residue of previouslyapplied adhesives, sealants, or fillet sealingmaterials shall also be removed. Any primeror paint shall be removed to expose cleanbare metal. The surface shall be wiped witha clean cloth dampened with isopropylalcohol, TT-I-735 followed immediately bywiping with a clean dry cloth. MIL-DTL-81706, class 3 chemical conversion coatingmay be applied to the faying surface of the

fairing and the fairing interface plate andallowed to dry per manufacturer’sinstructions. Inspect surface areas forcorrosion and take corrective action IAWNAVAIR 01-1A-509.

Av-Dec HITAK polyurethane gaskets aresupplied with protective release film on bothsides of the gasket. Refer to Figure 4-5 forgasket installation.

a. Remove new Av-Dec conductive gasket, P/N AG354000-01, for fairing interface plate, P/N 42502-2, from the protective packaging, taking care not tofold or bend it.

b. Before removing the thin release film, verifythat the fastener holes in the gasket will align with

the fairing interface plate, P/N 42502-2. Theconductive gasket has come pre-stamped to matchthe shape and fastener hole locations of the plate.

c. Position gasket over the fairing interfaceplate and apply new gasket to the fairing interfaceplate, P/N 42502-2 by peeling away the thin releasefilm marked “AIRCRAFT SIDE”. Beginning at oneside or corner of the plate, place gasket intoposition, carefully aligning gasket fastener holes withthe fairing interface plate holes. Rub gently allaround the gasket area to make sure good adhesionis achieved. Leave the release film on the exposedside of the gasket until all gaskets are in place andready for final installation.

d. Remove new Av-Dec conductive gaskets,P/N PG838000-01A, -01B, -01C and -01D from theirprotective packaging, taking care not to fold or bendthem. These gaskets are for installation on the turretfairing assembly, P/N 42488-1.

e. Follow steps b. and c. above for installationof conductive gaskets for the turret fairing assembly,P/N 42488-1. The conductive gaskets have comepre-stamped to match the contour and fastener holelocations of the fairing. The slightly curvedconductive gasket, P/N PG838000-01A shall beinstalled on the forward flange of the turret fairing.Conductive gaskets, P/N PG838000-01B and -01Care identical and shall be installed on the right andleft flanges of the turret fairing. Conductive gasket,P/N PG838000-01D shall be installed on the aftflange of the turret fairing.

f. Remove release film on the exposed sides ofall the conductive gaskets on the turret fairing andthe fairing interface plate prior to installation of theturret fairing assembly, P/N 42488-1.

4-38. NOSE ACCESS DOORS.

4-39. REMOVAL.

a. Remove attaching stud from lower door (1,figure 4-3) and open door. Disconnect hingeassemblies from fitting on structure and remove doorassembly.

b. Remove upper door (2) by removing screwswhich attach top of door to hinges and releasinglatches.


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4-12

Figure 4-2. Windshield Wiper


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4-13

TABLE 4-1. WINDSHIELD WIPER TROUBLESHOOTING

Trouble Probable Cause Isolation Procedure Remedy

Wiper does notclean windshield.

Damaged or deterioratedwiper blade.

Inspect wiper blade. Replace wiper blade.

Improper tension. Check blade tension. Adjust blade tension.

Motor andconverterinoperative.

Tripped circuit breaker. Reset circuit breaker.If circuit breaker willnot reset, checkbreaker or associatedwiring.

Replace circuit breakeror make required circuitrepairs.

Damaged switch. Inspect for obviousdamage. Make continuitycheck of switch.

Replace switch.

Broken electrical wireor loose connections.

Check connections.Make continuitycheck of circuit.

Replace wire ifnecessary. Tightenconnections or replaceconnectors or terminalsas required.

Motor and converterdefective.

Substitute serviceableunit in place ofsuspected defectiveunit and makeoperational check.

Replace motor andconverter.

4-40. INSPECTION. Inspect doors for worn ordamaged hinges on latches.

4-41. REPAIR OR REPLACEMENT. Replaceunserviceable, worn or damaged hinges, latches orseals.

NOTE

Assure door seal properly aligns withfuselage seal. Assure seals are properlyinstalled.

4-42. INSTALLATION.

a. Position upper door (2, figure 4-3) tostructure and align attachment holes at top of doorwith holes in hinges. Install screws and engagelatches.

b. Install lower door (1) hinges to fittings onstructure. Close door and install attaching studs.

4-43. CREW DOORS.

4-44. OPERATIONAL CHECK.

a. Place door to closed and locked position,with latch handles fore-and-aft and auxiliary handleat forward position.

b. Check that door is securely held. Verticallatch rods should be extended to engage twostrikers at top of door opening, with a smallclearance (0.08 inch) above top of each roller. (Seefigure 4-6.)

c. Pull auxiliary handle inward and aft tounlocked position. Latch handles should moveclockwise, and rods should retract from upperstrikers, but latch should remain engaged withdoorpost striker.

d. Turn latch handles further clockwise to openposition. Latch should disengage from doorpoststriker, allowing door to open.


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e. To check ejection mechanism: Close andlock door. Station a man to catch door while pullingEMERGENCY RELEASE handle. Hinge pins shouldretract, and doorpost striker should pivot upward toclear latch, releasing door.

4-45. REMOVAL – CREW DOOR AND

COMPONENTS.

a. Open door. Support door while pullingEMERGENCY RELEASE handle to retract hingepins. Lift off door.

b. Remove latch installation parts, only to extentrequired for replacement or other maintenance, asfollows:

(1) Disconnect latch rod (26, figure 4-6) fromlatch assembly (13) arm by removing cotter pin andheaded pin.

(2) Remove inner access door (16) and plugbutton from inner face of door.

(3) Disconnect rod (30) from bellcrank (31) byremoving cotter pin and headed pin. Unscrew aftend of rod from rod end on latch assembly (13).Remove rod (30) through aft side of door.

(4) Remove nine screws to detach latchassembly (13) plate from inner face of door. Holdlatch shaft (27) while sliding latch assembly (13) offinboard end.

(5) Disconnect rod (28) from arms on latch

shaft (27) and shaft of auxiliary handle assembly(18) by removing cotter pins and headed pins.Remove rod (28) through aft side of door.

(6) Remove six screws to detach auxiliaryhandle assembly (18) from inner face of door.Remove auxiliary handle assembly (18).

(7) Remove outer handle (14) by removingtwo screws attaching escutcheon to door and pullinghandle off end of latch shaft (27). Remove latchshaft (27).

(8) Disconnect latch rod (34) from bellcrank

(31) by detaching spring (32) and removing headedpin. Assure spring (32) remains attached to headedpin inserted through hole in window frame. Removeplug button from inner face of door and removeshouldered bolt (33) with nut and washers to detachbellcrank from its support.

(9) To remove either latch rod (26 or 34),remove spring pin (25), unscrew latch rod roller (4),and remove rod downward through door.

(10) To remove latch striker from door post,disconnect ejection cable (12, figure 4-7) from latchstriker (21) by removing cotter pin and headed pin.Detach spring (22). Remove bolt with nut andwashers, and pull striker out through backing plates.

(11) Detach upper forward striker (1, figure 4-

6) and backing plates (2 and 3) from Iongeron byremoving three screws. On upper aft striker (9)remove two screws from slotted holes, and useaccess hole on upper side of Iongeron to remove nutand washer from countersunk screw to detachstriker and backing plates (7 and 8).

c. Remove sliding window (10), whennecessary, as follows:

(1) Remove lower access door (15), withattaching screws, from lower edge of door.

(2) Remove three screws to detach lift handle

(11) from window.

(3) Loosen adjustable stop (17). Move slidingwindow (10) downward and remove through accessdoor opening.

d. To remove upper window (5), removeattaching screws with nuts and washers and detachwindow assembly.

4-46. REMOVAL – CREW DOOR EJECTIONMECHANISM AND CABLE. With door removed,remove ejection mechanism and striker ejectioncable parts only to extent required for replacement

or other maintenance.

a. Remove cotter pin, washer and headed pin todetach ejection handle cable (5, figure 4-7) fromplate (6). When required, detach two clamps (2)which secure ejection handle tube (3) to supportangle and pull handle assembly up through grommet(4) to remove.

b. Detach ejection cable swivel (13) from plate(6) by removing nut and washer. Pull swivel fromend of cable (12). Keep nut and washer with swivel.

c. Remove two bolts and washers to detach

support (10) from structure. Pull hinge pins (8 and11) free of hinge bushings, and remove assembledejection mechanism from inboard side of nosestructure.

d. Disassemble ejection mechanism as follows:

(1) Remove cotter pin and headed pins todetach upper and lower hinge pins (8 and 11) fromplate (6) and link (9).


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Change 1 4-15

Figure 4-3. Nose Access Doors

(2) Remove bolt with nut, washers and spacer(7) to separate plate and link from support (10).

e. To remove ejection cable, disconnect aft endfork of cable (12) from latch striker (21) by removingcotter pin an d headed pin. Pull cable a ft out of flextube (14) leaving tube in place.

4-47. REPAIR O R REPLACEMENT – CRE WDOOR AND COMPONENTS.

a. Repair o r re place win dows i n acco rdance

with damage limits shown on figure 4-1.

SILICONE RUBBER ADHESIVE 7DAPCOTAC 3300 (A-A-2985)

b. Replace damaged or missing seals on innerface of doo r, using adh esive, Dap cotac 3300 o requivalent. Mating surfa ces of seal a nd doo r mustbe clean of dirt, grease or oil. Rub surfaces li ghtlywith sandpaper, and ap ply even coatin gs of mixed

adhesive on both su rfaces. Air dry at roomtemperature for one to eight hou rs, then pre ss,coating surf aces tog ether an d hol d with firmpressure until bonded.

NOTE

Improper shimming of the crew door hingescan cause m isalignment t hat may da magesurrounding structure.

c. If replacing a door, or hinge halves (19, figure4-6) on do or, peel shim s (2 0) un der hinge s a srequired to obtain ali gnment. Spring assem blies,attaching hardware, and bumpers can be replaced ifdamaged or missing.

d. Replace any damage d and un serviceableparts or assemblies in latch installation.

e. Replace any damage d and un serviceableparts or assemblies in door ejection mechanism andcable installation.

SEALING COMPOUND 11 AMS-S-8802


f. If hinge h alves (21) o n nose st ructure arereplaced, peel shims (22) as required for alignment,and in stall with long hin ge pin bu shings in sertedthrough nose ski n. Apply seali ng comp ound, AMS-S-8802, class B2 or MIL-S-11030, type I to fill gapsbetween bushings and skin.


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4-16

Figure 4-4. Installation of Conductive Gasket (OBS AFT COMP WITH AFC 381)

Figure 4-5. Installation of Conductive Gasket (USBL AFT COMP WITH AFC 381)


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4-17

Figure 4-6. Crew Door (Sheet 1 of 2)


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4-18

Figure 4-6. Crew Door (Sheet 2)


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4-19

Figure 4-7. Crew Door Ejection Mechanism and Cable


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4-21

door. Install a latch rod roller (4) into end of each rodwith not less than 0.30 inch thread engagement,leaving out spring pin (25) to allow later adjustment.

(2) Position bellcrank (31), with longest armdown, in support. Install shouldered bolt (33) frominboard side, with washers under head and nut,using access hole in inner face of door.

(3) Connect spring (32, figure 4-6) to end ofheaded pin inserted through hole in window frame, ifremoved. Connect latch rod (34) to short arm ofbellcrank (31) with a headed pin. Hook spring (32)into end of headed pin.

(4) Position outer handle (14) on latch shaft(27), and attach escutcheon to door with two screws.

(5) Position latch assembly (13) on inboardend of latch shaft (27). Attach plate of latch

assembly (13) to door with nine screws.

(6) Position auxiliary handle assembly (18) tomounting hole, and attach plate to door with sixscrews.

(7) Place auxiliary handle assembly (18)forward to locked position. With latch inner handlepointing forward and outer handle (14) aft, turnadjustment screw (29) of rod (28) as required, andconnect rod ends to arms on latch shaft (27) andauxiliary handle assembly (18) shaft with headedpins and cotter pins. Secure adjustment screw (29)with pin and cotter pin. (QA)

(8) Position rod (30) horizontally in door andscrew threaded end on mating rod end on latchassembly (13) until bottomed. Adjust by backing offrod and connect to lower arm of bellcrank (31) withheaded pin and cotter pin, with latch rod (34) fullyextended. Final adjustment will be made with doorinstalled.

(9) Connect latch rod (26) to arm on latchassembly (13) with headed pin and cotter pin. (QA)

(10) Position latch striker (21, figure 4-7) in

support bracket and insert bolt with washer undernut. Connect fork terminal of ejection cable (12) onaft end of striker with headed pin and cotter pin.Connect spring (22) between striker and bracket ondoor post structure.

(11) Position upper forward striker (1, figure 4-6) with backing plates (2 and 3) on Iongeron at topof door opening, and install three attaching screws

through slotted holes. Assemble upper aft striker (9)with one thick and three thin backing plates (8 and7) on countersunk screw. Place a thin aluminumalloy washer on screw. Insert screw throughmounting hole in Iongeron, and use access hole intop of Iongeron to install nut with another thinaluminum alloy washer. Install two screws throughslotted holes of striker assembly into plate nuts.

d. Lift door to position, pull ejection handle (1,figure 4-7) to retract hinge pins, align hinge halves,and release handle to engage hinge pins.

e. Close door slowly, observing action of latch.Slowly move handle to lock position, observingengagement of latch rods with upper strikers and forclearance above each rod when fully extended.

f. Adjust positions of strikers as required. If

necessary, also adjust latch rod roller (4, figure 4-6)to obtain clearance of 0.08 inch above each fullyextended latch rod roller. Maintain minimum threadengagement of 0.30 inch. When adjustment issatisfactory, install spring pins (25) through slots oflatch rods (26 and 34) and holes in latch rod rollers(4).

g. Install plug buttons and access doors. Securewith 0.020 copper Iockwire, MS20995CY20. (QA)

4-50. PASSENGER – CARGO DOORS.

4-51. OPERATIONAL CHECK ANDADJUSTMENT.

a. Place cargo door (3, figure 4-8) in closed andlatched position. Check upper edge of door for beingparallel to top of cabin door opening. If necessary,adjust positions of roller supports (4 and 8) onserrated plates (6 and 9) for alignment.

b. Operate door through full travel, checkingroller engagement to tracks at all positions.

c. With door closed, check that lower track (22)is engaged not less than 0.25 inch in channel oncabin. If necessary, loosen screws and adjust trackto provide specified engagement without restrictingdoor travel through full range.

d. Check for vertical play of door, not to exceed0.08 to 0.10 inch allowable. Readjust roller supportsas required.


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4-23

Figure 4-8. Cargo Door Installation (Sheet 2)


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4-25

(5) Insert a spacer (41) from inboard side ofwindow, into each of three mounting holes in loweredge of window frame. Insert bolt (37) from outboardthrough window and spacer, and place two steelwashers over inboard end of each spacer. Positionlatch assembly with pivot holes of handle and platesover ends of spacers, and install a thin aluminumalloy washer and a cap nut on each screw.

(6) Install window, checking for secureengagement of latch. (Refer to paragraph 4-53.)

c. Rollers (5 and 14, figure 4-8) and slider (17).With door removed, perform disassembly andassembly of rollers and slider to extent necessary toreplace unserviceable parts:

(1) Replace rollers and slider if wear exceedslimits:

(a) On outer diameters of upper rollers

(1.030 ± 0.010 inch) or rollers (0.800 ± 0.010 inch),wear exceeding 0.010 inch depth or 0.020 inch totalon diameter. (QA)

(b) On inner diameters of upper rollers(0.325/0.332 inch) or aft rollers (0.262/0.269 inch),wear exceeding 0.008 inch depth or 0.015 inch totalon diameter. (QA)

(c) Slider bearing strips must be at least0.025 inch thick on all surfaces.

(2) Remove cotter pin and washer to detachroller from support.

(3) Place new roller on support. Install washerand cotter pin. (QA)


d. Seals. Replace damaged or missing sealsusing adhesive Dapcotac 3300 or equivalent. Matingsurfaces of seal and door must be clean of dirt,grease or oil. Rub surfaces lightly with sandpaper,and apply even coating of mixed adhesive on bothsurfaces. Air dry at room temperature for 1 to 8hours, then press coated surfaces together and holdwith firm pressure until bonded.

4-56. INSTALLATION – PASSENGER – CARGODOOR.

a. Position passenger – cargo door (3, figure 4-8) to aft ends of tracks. Engage roller and slide in afttracks (12). Start lower track (22) on channel androllers on upper track (10). Slide door forward.

b. Install two retainer straps (11) with bolts andwashers in ends of aft tracks.

c. Install retainer (24) on forward edge of cargodoor with two screws, washers and spacers.

d. Assemble retainer plate (20) with twospacers on forward edge of door, and install twoscrews with washers. Attach outer end with bolt andwasher. Check fit of retainer to stud on plateattached on cabin aft bulkhead, adjusting position ofplate as necessary.

4-57. CABIN (HINGED) PANELS.

4-58. OPERATIONAL CHECK ANDADJUSTMENT.

a. With cabin (hinged) panel closed andlatched, check that upper and lower latch pins (13,figure 4-9) are securely engaged in holes instructural channels of door opening. Also check thatpin on lower inside of panel is engaged in door post.

b. Operate latch to open panel, checking thatupper and lower latch pins retract to clear top and

bottom of door opening.

c. Check action of positioning spring (2) onpivot (4) as panel is opened. Detent in spring slotshould catch and hold panel at approximately 90degrees to fuselage, and hook for spring shouldcatch when door is forced beyond detent.

d. If necessary to adjust either or both latchpins, remove screws (6 and 23) and covers (5 and22) for access. Adjust pins on threaded ends of latchtubes (11) to obtain secure engagement and properrelease. Install covers after adjustment.

e. Check condition of hinges, hinge pins andseals. Replace unserviceable parts.

f. With panel closed and latched, slowly closepassenger – cargo door to check for proper positionof catch (19). (Refer to paragraph 4-51.) Whennecessary, adjust catch by means of slotted holes orby peeling laminated shim (20) under catch.


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4-26

4-59. REMOVAL.

a. Unlatch and slide cargo door aft. Unlatch andopen cabin (hinged) panel.

b. Unhook positioning spring (2, figure 4-9) frompivot (4) at top of door opening.

c. Pull pins (1) from hinges (24) and removepanel.

4-60. REPAIR OR REPLACEMENT.


a. Seals. Replace damaged or missing sealsusing adhesive Dapcotac 3300 or equivalent. Matingsurfaces of seal and door must be clean of dirt,grease or oil. Rub surfaces lightly with sandpaper,and apply even coatings of mixed adhesive on bothsurfaces. Air dry at room temperature for 1 to 8hours, then press coated surfaces together and holdwith firm pressure until bonded.

b. Latch. (See figure 4

01-110hce-2-2 airframe and landing gear.pdf

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