(b)
If the part is not in the tolerance, repair or replace it when it is necessary.
S 416-004
(3) Install the positioning actuator and the forward and the aft pin assemblies (Ref 32-11-20/401).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
32-11-20
ALL ú ú 01 Page 601 ú Oct 10/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
DRAG BRACE SHOCK STRUT
UPPER TORSION LINK
BRAKE EQUALIZER ROD
1. BEARING/PIN
OUTER
CYLINDER
2. BUSHING/ BEARING
10. BUSHING/PIN
3. BUSHING/PIN (4 PLACES)
A
747-400
MAINTENANCE MANUAL
LOWER SIDE STRUT
TRUCK POSITIONING ACTUATOR
A
POSITIONING MECHANISM (BELLCRANK)
A
FWD INBD
POSITIONING LINK
TRUCK LOWER
BEAM TORSION
LINK
POSITIONING 6. BEARING/PIN ACTUATOR
8.
BUSHING/PIN
9.
BUSHING/ END CAP
SHOCK STRUT
OUTER CYLINDER
4.
PIN/CAP 7. BUSHING/BEARING POSITIONING MECHANISM
5.
CAP/BOLT (BELLCRANK)
A-A
Wing Gear Truck Positioning Actuator Wear Limits
Figure 601 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
32-11-20
ALL ú ú 01 Page 602 ú Oct 10/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
INDEX NO. PART NAME DIM. DESIGN LIMITS WEAR LIMITS REPLACE PART WORN REPAIR WORN PART INSTR REPAIR
DIAMETER PER-MITTED WEAR DIM. 13 MAX CLEAR-ANCE DIA
MIN MAX
1 BEARING ID 1.4995 1.5000 1.5029 0.0049 X 2
PIN OD 1.4980 1.4990 1.4951 X 1
2 BUSHING 3 1.568 1.571 1.577 0.012 X
BEARING 4 1.565 1.567 1.559 2
3 BUSHING 5 3.160 3.180 0.050 X
PIN 6 3.150 3.155 3.140 X
4 PIN ID 1.0000 1.0050 1.0070 0.010 X
CAP OD 0.9940 0.9990 0.9950 X
5 CAP ID 0.4470 0.4530 0.4660 0.030 X
BOLT OD 0.4358 0.4367 0.4230 X 7
6 BEARING ID 1.4995 1.500 1.5024 0.0044 2
PIN OD 1.4980 1.4990 1.4956 1
7 BUSHING 8 1.568 1.571 1.580 0.018 X
BEARING 9 1.562 1.567 1.553 2
8 BUSHING ID 1.5000 1.5010 1.5034 0.0054 X
PIN OD 1.4980 1.4990 1.4956 X 1
9 END CAPS 10 3.3350 3.3500 3.3600 0.042 X
BUSHINGS 11 3.3180 3.3310 3.3080 12
10 BUSHING ID 1.5000 1.5010 1.5045 0.0055 X 8441
PIN OD 1.4980 1.4990 1.4955 X 14
Wing Gear Truck Positioning Actuator Wear Limits
Figure 601 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
32-11-20
ALL ú ú 01 Page 603 ú Oct 10/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
WORN PART REPAIRABLE. CHROME PLATE TO 0.010 THICKNESS AND GRIND TO DESIGN
DIMENSIONS TAKE REPAIR ACTION AS PRESCRIBED IN APPROPRIATE INSTRUCTIONS FOR THIS HYDRAULIC ASSEMBLY (REF ATA CHAPER 29)
GAP BETWEEN FLANGES OF BUSHINGS IN OUTER SHOCK STRUT CYLINDER
WIDTH OVER BEARING IN ACTUATOR HEAD END
WIDTH OVER OUTER FLANGES OF BUSHINGS IN SHOCK STRUT OUTER CYLINDER
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 起落架 LANDING GEAR 2(39)
