Main n Nose Gear b.737

MAIN GEAR and NOSE GEAR OVERHAUL ASSY / DISASSY

BOEING 737 SERIES

PREPARED BY : SUKAMTO.M01

FOR TRAINING PURPOSE ONLY

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NOTICEThis handout is a part of the training material to get trainees familiar with the B737 landing gear system.

The imformation contained herein is for training purpose only and may not be copid, disclosed to third parties or

used for any purpose, without the express writen from……..

The values of pressure, temperature, speed, power, weight etc., are for the illustrative meaning only and are not

necessarily representative of the correct value.

It will not be reviced and does not amend or supersede applicable service bulletins, overhaul manuals and writen

instruction.

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MAIN AND NOSE LANDING GEAR


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TABLE OF CONTENT

No Subject Page

01 Introduction- History

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02 Main Gear Build-Up and Nose Gear Build-Up- General, Description, Interchangeability and Life-Limited Part

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03 Main Gear Assembly and Nose Gear Assembly- Description, Operation and Leading Particulars

16,68

04 Main Gear Shock Strut and Nose Gear Shock Strut- Description, Operation, Seal Replacement and Sleeve Installation

18,70

05 Corrosion Preventive Compound- Article on corrosion, Application of MIL-H-11796 and BMS 3-27- Tee bolt, Universal and Lower Drag Strut Installation

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06 Grease Application

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07 Main Gear Side Strut

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08 Main Gear Uplock Assembly

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09 Main Gear and Nose Gear Minor Components

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10 Nose Gear Locklink Assembly

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11 Main Gear and Nose Gear Oerhaul Process 60,77


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SAFETY PRECAUTION

OBEY ALL WARNINGS, CAUTIONS AND NOTES MENTIONED IN

APPLICABLE DOCUMENT(S).



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HYDRAULIC INSTALLATIONHARNESS INSTALLATION

MAIN GEAR BUILD-UP

CMM.32-16-11NO ASSIGNED PART NUMBER


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MAIN GEAR BUILD-UP

CMM.32-16-11NO ASSIGNED PART NUMBER

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CMM.32-16-01 CMM.32-11-11

CMM.32-16-31CMM.32-17-11 CMM.32-17-01

MINOR COMPONENT

Aft Trunion Nut Assembly

Actuator Beam Assembly

Support Link Assembly

Bearing Assembly fwd trunion

Bolt Assembly Lower Side StrutShaft Up-Lock Support

Bolt , Fwd Trunion Bearing


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Interchangeability and Life-limited Parts ( example )

-Service letter has been released to provide landing gear structural component interchangeability Imformation- Drawing 65C73761 outlines interchangeability which are FAA approved.- As drawing 65C73761 is reviced to add new part numbers, service letter will be reviced also.

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- Service letter has been released to provide landing gear structural component interchangeability Imformation- Drawing 65C73761 outlines interchangeability which are FAA approved.- As drawing 65C73761 is reviced to add new part numbers, service letter will be reviced also.

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- This drawing includes component life limit data

- Serialization of life limited components is needed to track life limited parts

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How to Use Interchangeability list

- This drawing includes component life limit data.

- Serialization of life limited components is needed to track life limited parts.

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How to Use Interchangeability list.

A. All part numbers listed within a block are fully interchangeable witheach other for listed gross weights. Only part/assembly numbers atthe interchangeable level are shown in this document. See CMM/OHM, D6-17370 for lower level components. If only one part is shown for an item, there is no alternate part available.

B. Some blocks are separated into groups of numbers is differentairplane gross weight limitations. All parts within the block may be interchanged provided the maximum gross weight limitation of each part is not exceeded. C. All part numbers listed within a block which is separated by a solidline from the previous or following block, are not generally interchangeable with part numbers listed in the block. Refer to flagnotes for imformation that will permit interchangeability across solid lines in some instances.

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MAIN GEAR ASSEMBLYCMM.32-16-01PN.65-737761-11 thru –16, thru –42, -65, -66, -81, -82, -87, -88, -97, -109,-110, -115, -116, -121, -122, -125 thru –128.

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SHOCK STRUT

CMM.32-11-11PN.65-46100-5, -6, -9 thru –31, -33, thru –79

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SUPPORT TUBE –ORIFICE

ORIFICE PLATE SHOCK- STRUT

MATERING PIN

INNER CYLINDER

OUTER CYLINDER

SEAL ADAPTER

BEARING LOWER

BEARING UPPER

DRAIN TUBE

GLAND NUT

SNUBBING VALVE


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FLUID AND NITORGEN SERVICINGMAIN GEAR SHOCK STRUT


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MAIN AND NOSE LANDING GEARFOR TRAINING PURPOSE ONLY

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SIDE STRUT

CMM.32-17-11 PN.65-73761-21 thru –26, -50, -55, -56, -77, -85, -86, -93 thru –96, -103, -105, -106, -111, -123, -124.



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UP-LOCK ASSEMBLY

CMM.32-17-01PN.65-46141-5 thru -12.PN.65-46141-15 thru -26



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MAIN GEAR MINOR COMPONENT CMM.32-16-31



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Overhaul Main Gear Process Special process (No cap) Common process (cap)

Diss Assembl

y

Hard Chrom Platting

Grinding &

machining

BakingShootpennin

g

HoningBoring

NDT MPI/FP

I

SandBlastin

g

Cadmium

Platting

Painting

Cleaning,

Stripping

Main Gear Assy

Main LG Shock Strut

Main LG Up Lock

Main LG Side Strut

Main LG Minor

Component

Major Part

Inner CylinderOuter Cylinder

Upper/Lower Torsion LinkTrunnion Link

Upper/Lower Drag StrutUniversal-Lower Side Strut

Trunion PinAttach Fitting-Tee Bolt

Universal Reaction LinkActuator Beam Arm

Reaction LinkUpper/Lower Side StrutLink Assembly Up Lock

Bellcrank Up LockHook Up Lock

Fuse Bolt-Fwd Trunnion BearingActuator Beam

Fuse Nut-Aft Trunion

Metering PinSupport Tube Oriffice

Orifice Plate-Shock StrutDrain TubeGland Nut

Pin Torsion LinksUpper/Lower Bolt Drag StrutBolt Tee Fitting Attechment

Nut – Trunion PinUpper/Lower Link Down Lock

Shaft Spring SupportBolt-Reaction Link Side Strut

Bolt-Upper Side StrutBolt Side Strut

Bolt Reaction Link UplockBolt-Downlock Link pivot

Shaft Uplock SupportBolt Reaction Link

Bolt Actuator Beam OitboardBolt Lower Side Strut

Support LinkTrunnion Bearing

Fwd Trunion Bearing



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SAFETY PRECAUTION

OBEY ALL WARNINGS, CAUTIONS AND NOTES MENTIONED IN

APPLICABLE DOCUMENT(S).



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B.737 NOSE GEAR INSTALLATION (BUILD UP 32-21-38).

General, Description and Operation.

The nose gear supports the forward end of the fuselage and provides directional control while the airplane is on the ground. The nose gear includes a drag brace, shock strut and torsion links, and hydraulically actuated to retract forward and up into wheel well recessed into the lower nose section of the airplane.

The nose gear buid up is an interchangeable module consisting of nose gear assembly, wheel and tire assemblies, taxi light and wiring harness, hydraulic tubing, nose wheel steering depressurization valve, steering cable and nose wheel steering control mechanism.

The unit provides rolling support with shock absorbing and steering capabilities. Steering inputs are transferred to the steering actuators throught a vontrol cable to the control mechanism and matering valve to provide steering control.

Electrical components consist of a taxi light and wiring harness

Weight………. 320 pounds.



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NOSE GEAR BUILD- UP



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CMM 32-26-01 ( B.737-200 )CMM 32-21-48 ( B.737-300/400/500 )

CMM 32-21-58. ( B.737-300/400/500 ) CMM 32-21-11 ( B.737-200 )

CMM 32-34-13

NOSE GEAR MINOR COMPONENTSOHM 32-01-03

PIN DRAG BRACE CENTER

PIN DRAG BRACE UPPER

LOWER DRAG BRACE UPPER DRAG BRACE

BOLT DRAG BRACE LOWER

AFT LOCK MECHANISM SHAFT


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Interchangeability and Life-limited Parts( example )

- Service leter has been released to provide landing gear structural component Interchangeability imformation.- Drawing 65C73762 outlines Interchangeability which are FAA approved.- As drawing 65C73762 is reviced to add new part number, service letter will be reviced also.



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- This drawing includes component life limit data

- Serialization of life limited components is needed to track life limited parts



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A. All part numbers listed within a block are fully interchangeable witheach other for listed gross weights. Only part/assembly numbers atthe interchangeable level are shown in this document. See CMM/OHM, D6-17370 for lower level components. If only one part is shown for an item, there is no alternate part available.

B. Some blocks are separated into groups of numbers is differentairplane gross weight limitations. All parts within the block may be interchanged provided the maximum gross weight limitation of each part is not exceeded. C. All part numbers listed within a block which is separated by a solidline from the previous or following block, are not generally interchangeable with part numbers listed in the block. Refer to flagnotes for imformation that will permit interchangeability across solid lines in some instances.

How to Use Interchangeability list.



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NOSE GEAR ASSEMBLY CMM 32-21-48.

PART NUMBER 65-73762-21 / -25 / -26 / -27 / -28

The nose gear assembly includes the shock strut, torsion links, steering collar, steering cylinders and steering metering valve.

The shock strut absorbs and impacts during take-off, landing and taxiing operations.The torsion links keep radial alignment of the shock strut inner and outer cylinders during compression and extension. The metering valve sends hydraulic fluid to the steering cylinders, which push their piston to turn the steering collar to turn the nose gear.

Length – Centerline of axle to mounting trunion holes.Compressed – 35.5 inches.Extended – 47.5 inches.Weight – 190 pounds.



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Nose Gear Assembly Ref CMM 32-26-01 ( B.737-200 ) Ref CMM 32-21-48 ( B.737-300/400/500 )



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NOSE GEAR SHOCK STRUT ASSEMBLY.CMM 32-21-58.

PART NUMBER 65-46200-60, -61, -62, -68, -74, -76, -77, -78, -80.-81, -82, -83.

The strut is the main supporting member of the nose gear. Its main structural components are the inner cylinder, which includes the axle, and the outer cylinder, which attaches to the airplane structure. Internal component s include a tapered metering pin, an orifice plate and support tube, and upper and lower centering cams. The inner and outer cylinders are made of high strength steel (270-300 ksi). All pinned joints are assembled with bushings or bearings.

The lower centering cam is keyed to outer cylinder and the upper centering cam is keyed to the inner cylinder. Cam action centers the gear when the shock strut extended. An air valve for inflating the strut is located at the top of outer cylinder. A check valve for servicing the strut with hydraulic fluid is located on the bottom of inner cylinder. A metering pin, connected to the inner cylinder , moves through an orifice plate supported by a tube assembly and varies the fluid flow as the strut is compressed or extended.

Length (extended) – 51 inchesLength (compressed) – 39 inchesAxle Length – 23 inchesWeight (wet) – 168 lbsWeight (dry) – 164 lbs

Hydraulic Fluid – (Prefered) BMS 3-32 Type 1 (with corrosion inhibitor) fluid, D50022 or Type 2 (without corrosion onhibitor) D00467 (Optional) MIL-H-6083 or MIL-H-5606 and Lubrizol 1395 antifriction additive hydraulic fluid, D50090.Fluid Capacity – 6 pints.

Description, Operation and Leading Particulars.



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NOSE GEAR SHOCK STRUT ASSEMBLY.



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NOSE GEAR SHOCK STRUT



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MAIN AND NOSE LANDING GEARNOSE GEAR SHOCK STRUT DISASSY

Outer CylinderInner CylinderSteering Plate Upp/LwrMatering PinSupport Tube OrificeStem Support OrificeGland NutPlate Upper Orifice


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NOSE GEAR SHOCK STRUT SEAL NOSE GEAR SHOCK STRUT SEAL REPLACEMENTREPLACEMENT



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NOSE GEAR SHOCK STRUT SEAL

REPLACEMENT Dinamic Seals.

Greene Tweed T-seals.

7339BFT972P3 Using two back-up rings.

Shamban Seals ( optional )

S34692-339GLF17 T-sealS33327 Hatseal ll



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FLUID AND NITORGEN SERVICINGNOSE GEAR SHOCK STRUT


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NOSE GEAR MINOR COMPONENT

CMM 32-21-38.


UPPER DRAG BRACE

LOWER DRAG BRACE

BOLT DRAG BRACE LOWER

AFT LOCK MECHANISM SHAFT

PIN DRAG BRACE UPPERPIN DRAG BRACE CENTER


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NOSE GEAR LOCK LINK ASSEMBLYCMM 32-34-13

P/N.65-46245-1 thru –14. DESCRIPTION AND OPERATION

• The nose gear lock link assembly is a two-segment linkage which attaches to the folding joint of the upper and lower drag strut and to airplane structure. Each segment has a shim adjusted stop.

• The assembly folds during nose gear extension or retraction. When the gear comes to the full up or full down position, external spring force pulls the lock link into an overcenter position, which locks the drag braces to hold the nose gear in the up or down position.



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NOSE GEAR LOCK LINK ASSEMBLY

LOCK LINK ASSY - FWD

SHAFT – CENTER LOCK

LOCK BRACE ASSY – AFT



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NOSE GEAR LOCKLINK MECHANISM OPERATION

Lock Brace

Lock Spring Bungee

Lock Link



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Nose Gear Overhaul Process Special process (No cap) Common process (cap)

Diss Assembl

y

Cleaning,

Stripping

Nose Gear Assy

Nose Gear Shock Strut

Nose Gear Minor

Component

Nose Gear Locklink

Hard Chrom Platting

Machining&

Grinding

BakingShoot

peenning

HoningBoring

Inner CylinderOuter CylinderTorsion Links

Collar steeringUpper Drag BraceLower Drag Brace

NDT MPI/FP

I

SandBlastin

g

Cadmium

Platting

Painting

Metering PinSupport Tube Matering Pin

Drain TubeGland Nut

Pin Torsion LinksOrifice Plate-Upper

Stem-orifice Support TubeShaft Spring Support

Support Tube Upper OrificeSteering Plate UpperSteering Plate LowerBolt Steering Collars

Bolt Torsion Link ApexPin Drag Brace CenterPin Uper Drag Braces

Shaft Aft Lock MechanismLock Brace Assy Aft

Bolt Lower Drag BraceLock Link Assy FwdShaft Center Lock

Pin Trunion LHPin Trunion RH

Major Part



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REFERENCES

The following references material has been used for the development of this handbook:Training Manual B737

Service Letter 737-SL-32-018-DAircraft Maintenance Manual ( AMM )

Component Maintenance Manual ( CMM )Overhaul Manual ( OHM )



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ADDITIONAL PAGE

B.737 Series Landing Gear System


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INNER DOOR

INNER DOOR

UNIVERSAL SISE STRUT ATTACHMENT

UNIVERSAL SISE STRUT ATTACHMENT

SHOCK STRUT

SHOCK STRUT

UPLOCK ROLLER

UPLOCK ROLLER

INNER DOOR PUSHROD

INNER DOOR PUSHROD

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locked position.



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Main n Nose Gear b.737

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