(10)
Lubricate the landing gear (AMM 12-21-11/301).
(11)
Lift the airplane for gear retraction (AMM 07-11-11/201).
S 424-023
S 644-024
S 584-025
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737-300/400/500MAINTENANCE MANUAL
S 084-026
(12)
Remove the ground lockpins (AMM 32-00-01/201).
S 784-031
(13)
Pressurize the hydraulic system (AMM 29-15-00/201).
S 724-027
(14)
Retract and extend the gear.
S 494-028
(15)
Install the ground lockpins (AMM 32-00-01/201).
S 214-029
(16)
Examine the reaction link and other related parts, and make sure they operate correctly.
(17)
Lower the airplane and remove the jacks.
S 584-030
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737-300/400/500MAINTENANCE MANUAL
MAIN LANDING GEAR REACTION LINK - INSPECTION/CHECK
__________________________________________________
1. General
_______
A. This procedure only has illustration and a wear limits table which shows the data for wear limits. There are no procedures for the access, the removal, or the installation of the parts. Refer to the Main Landing Gear Reaction Link - Removal/Installation for procedures to do these tasks.
TASK 32-11-71-206-001
2. Wear Limits for the Reaction Link of the Main Landing Gear (Fig. 601)
__________________________________________________________
A. Wear Limits for the Reaction Link
S 226-002
(1) Refer to Fig. 601 for the inspection points and the wear limits table.
C
C D
D A B
FWD INBD REACTION LINK B A UPLOCK ASSEMBLY
Main Landing Gear Reaction Link Wear Limits Figure 601 (Sheet 1)
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A 737-300/400/500MAINTENANCE MANUAL
2. BUSHING/BOLT
UPPER DOWNLOCK UPPER DOWNLOCK
5. BUSHING/BOLT
LINK ASSEMBLY LINK ASSEMBLY
(2 LOCATIONS)
C-C D-D
Main Landing Gear Reaction Link Wear Limits
Figure 601 (Sheet 2)
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INDEX NO. PART NAME DIM. DESIGN LIMITS WEAR LIMITS REPLACE PART WORN REPAIR WORN PART REPAIR INSTR.
DIAMETER MAX WEAR DIM. MAX DIAM CLEAR-ANCE
MIN MAX
110 BUSHING ID 1.375 1.376 1.378 0.005 X
BOLT OD 1.373 1.374 1.372 X 1
1 11 BUSHING ID 1.250 1.251 1.253 0.005 X
BOLT OD 1.248 1.249 1.247 X 1
2 10 BUSHING ID 1.437 1.438 1.439 0.005 X
BOLT OD 1.435 1.436 1.434 X 1
2 11 BUSHING ID 1.375 1.376 1.377 0.005 X
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