S 842-033
(7)
Do this task: "Removal of the Door Locks from the Body Landing Gear" (AMM 32-00-30/201).
TASK 32-13-14-222-022
4. Examine The Lower Torsion Link On The Body Landing Gear For Wear Limits
_______________________________________________________________________
A. References
(1)
AIPC 32-13-14 Fig. 1
B.
Access
(1)
Location Zone
755 Body Landing Gear, LH
765 Body Landing Gear, RH
C.
Procedure (Fig. 204)
S 022-023
(1)
Remove the lower torsion link on the body landing gear (Ref Remove Body Landing Gear Lower Torsion Link).
S 222-024
(2)
Do a check for limits of the wear of the lower attach bolt and the apex spindle.
(a)
Measure parts if it is necessary and compare measured dimensions to keep the dimensions to the limit.
(b)
If it is necessary, repair or replace the part that are out of tolerance.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
S 422-025
(3) Install the lower torsion link on the body landing gear (Ref Install Body Gear Landing Lower Torsion Link).
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
A-A
Body Gear Lower Torsion Link Wear Limits
Figure 204 (Sheet 1)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
TORSION LINK
4. BUSHING/SPINDLE
NO. INDEX PART NAME DIM. DESIGN LIMITS WEAR LIMITS PART WORN REPLACE PART WORN REPAIR INSTR REPAIR
DIAMETER DIM. PER-WEAR MITTED 3 ANCE CLEAR-MAX DIA
MIN MAX
1 BUSHING ID 3.2500 3.2510 3.2546 0.0076 X 2
BOLT OD 3.2470 3.2480 3.2434 X 1
2 BUSHINGS 12.0000 12.0040 12.0120 0.160 5 X 4 2
BUSHINGS 11.9960 11.9980 11.9880 X 4 2
3 BUSHING ID 3.2500 3.2520 3.2591 0.0121 X 2
BOLT OD 3.2470 3.2480 3.2434 X 1
4 BUSHING ID 2.7500 2.7520 2.7543 0.0063 X 2
SPINDLE OD 2.7480 2.7490 2.7447 X 1
5 HEAD/SHOULDER 5.0010 5.0140 5.330 0.0380 5 X 1
BUSHINGS 4.9950 5.0000 4.9760 X 2
PART IS REPAIRABLE. REFER TO OVERHAUL MANUAL FOR REPAIR INFORMATION.
PROCURE REPLACEMENT BUSHING. INSTALL BUSHING PER AMM 20-11-01/401 WITH INTERFERENCE FIT.
LIMITS SHOWN MAY BE EXCEEDED PROVIDED MAXIMUM CLEARANCE IS NOT EXCEEDED.
FOR IN-SERVICE REPAIR, INSTALL SPECIAL SHIM (AMM 32-00-01/801); PREFERRED
OVERHAUL REWORK IS TO RESTORE PART TO DESIGN LIMITS.
MAXIMUM AXIAL CLEARANCE
Body Landing Gear Lower Torsion Link Wear Limits
Figure 204 (Sheet 2)
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本文链接地址：747-400 AMM 飞机维护手册 起落架 LANDING GEAR 3(37)
