737 AMM 飞机维护手册 起落架 LANDING GEAR(32)

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M.  Install special washer (18A) and trunnion link pin nut (19). Tighten nut to run-on torque plus 1000-1200 pound-inches. Loosen the nut and tighten to 250-750 pound-inches.
CAUTION:  MAKE SURE YOU USE THE SPECIAL UNDERSIZE NUT ON TRUNNION PINS WITH UNDERSIZE THREADS. CHECK FOR BLACK MARKING WITH A YELLOW BACKGROUND ON THE TRUNNION PIN. THIS IS AN INDICATION THAT THE THREADS HAVE BEEN REWORKED (UNDERSIZE). IF YOU USE A STANDARD NUT ON UNDERSIZE THREADS, THE NUT COULD COME OFF AND CAUSE STRUCTURAL DAMAGE TO THE LANDING GEAR.
N.  Add washer and nut to trunnion pin lockbolt (16). Tighten nut 100 to 150 pound-inches torque.
O.  Install locking key (2).
NOTE: Locking key may be installed in either of two positions to align tabs with slots.
P.  Position retainer washer (18) to align serrations of trunnion link pin nut (19) and lockbolt (17) on trunnion link (20).
Q.  Add washer and nut to lockbolt (17) and tighten nut 100 to 150 pound-inches lube torque.
R.  Insert actuator beam arm antirotation bolt (12) through beam arm (13) and trunnion pin (22). Add washer and nut.
S.  Tighten nut 30 to 40 pound-inches torque.
T.  Install main gear actuator and actuator walking beam (Ref 32-32-11 R/I).
NOTE: If the main landing gear stabilizing beam was reinstalled, it may be removed to facilitate the installation of the main landing gear actuator assembly.
U.  Release and line up end of reaction link (29) with lug on trunnion pin (22).
V.  Install thread protector on spring support shaft (26).
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W.  Insert shaft from aft side. Tap shaft hard down.
CAUTION:  DO NOT TAP ON THREAD END OF HEAD. USE THICK WALL TUBE OVER THREADS FOR DRIFT.
X.  Add spring support cap (27) on shaft (26).
Y.  Tighten spring support cap (27) 100 to 150 pound-inches torque.
Z. If necessary, slack cap back to align nearest slot with cotter pin hole. Lock cap with cotter pin. AA. Connect lock strut (28) to reaction link (29).
(1)  
Line up lock strut (28) with reaction link (29).

(2)  
Insert bolt (30) from forward side of gear.

(3)  
Add washer and nut.

(4)  
Install keeper (31) with washer and bolt.

(5)  
Tighten nut on bolt (30) 100 to 150 pound-inches dry torque.

(6)  
If necessary, slack off nut to align nearest castellation slot with cotter pin hole. Lock nut

with cotter pin. AB. Install downlock springs (25) (Ref 32-32-91 R/I). AC. Deleted. AD. Align upper end of drag strut (4) with lug on trunnion link (20). AE. Insert attachment bolt from inboard side. Add washer and nut.
CAUTION:  ENSURE THAT DRAG STRUT UPPER ATTACHMENT BOLT (5) IS SAME BOLT OR REPLACEMENT BOLT IS SAME PART NUMBER AS THAT WHICH WAS REMOVED IN STEP 4.F. DRAG STRUT UPPER ATTACHMENT BOLT (5) IS A STRUCTURAL FUSE AND MUST BE INSTALLED IN SAME LOCATION FROM WHICH REMOVED TO MAINTAIN STRUCTURAL INTEGRITY OF THE REAR SPAR.
AF.  Tighten nut as tightly as possible by hand. If necessary, back off nut to line up nearest slot with cotter pin hole. Lock nut with cotter pin.
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AG.  Remove caps and plugs. Connect hydraulic lines.
AH. On right gear, connect ground spoiler interlock valve cable clamps to trunnion link.
AI.  Pressurize hydraulic systems A and B and bleed brakes by operating brake pedals four to six times (Ref 29-11-0 and 29-12-0 MP).
(1) Check hydraulic brake line connections for leaks and lines are not cross connected. AJ. Pressurize B hydraulic system. AK. Depressurize brake pedals and verify that only outboard brakes are actuated.
NOTE:  Actuation of one of the inboard brakes is an indication that hydraulic tubes are cross connected.
AL.  Install hydraulic access panels.
AM. Service shock strut and lubricate points of disassembly (Ref Chapter 12, Gaseous System Servicing and Landing Gear Component Lubrication).
AN. Jack airplane for retraction of main landing gear only (Ref Chapter 7, Jacking Airplane).
AO.  Remove ground lock assemblies (Ref 32-00-01) and perform retraction test on gear (Ref 32-32-0 A/T).
AP. Extend gear and install gear ground lockpins.
AQ.  Lower airplane and remove jacks (Ref Chapter 7, Jacking Airplane).
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MAIN GEAR TRUNNION LINK ASSEMBLY - INSPECTION/CHECK
1.  General
A.  These data consist of illustrations and wear limit charts. No procedure is given in this section for access to permit inspection. Refer to Main Gear Trunnion Link Assembly - R/I.
　
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