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27-51-20
ALL ú ú 02 Page 802 ú Oct 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
TUBE
12 BOLTS
A-A
INCHES (mm) TORQUE TUBE SIZE OD X WALL THICKNESS MATERIAL INCHES (mm) 2 WALL THICKNESS SPLICE TUBE BOLT
(31.8 x 3.0) 1.25 X 0.12 3 0.08 (2.0) MINIMUM NAS1104-20
(38.1 X 3.3) 1.5 X 0.13 0.08 (2.0) MINIMUM NAS1104-24
(44.5 X 1.9) 1.75 X 0.075 4 0.12 (3.0) MINIMUM NAS1104-28
(50.8 X 1.7) 2.00 X 0.065 0.14 (3.6) MINIMUM NAS1104-32
ADDITIONAL LENGTH AS NECESSARY TO OBTAIN THE AXIAL CLEARANCE SPECIFIED IN R/I MACHINE THE SPLICE TUBE OD TO THE AVERAGE TORQUE TUBE ID +0.000/-0.002 INCH (+0.00/-0.05mm) 4130 SEAMLESS STEEL TUBE OR BAR STOCK, HEAT-TREATED TO 150 KSI MINIMUM
2024-T3 OR -T4 ALUM ALLOY BAR STOCK OR SEAMLESS TUBE
Torque Tube Splicing Figure 801
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-51-20
ALL ú
ú 01 Page 803
ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
(3)
Washers - AN960PD416L (or equivalent) (24 necessary) (if necessary to prevent threads from bottoming)
(4)
Tubing or Bar Stock - 2024-T3 or 2024-T4 seamless aluminum (size and length per Fig. 801)
(5)
Tubing or Bar Stock - 4130 seamless steel, heat treated to 150 ksi minimum (size and length per Fig. 801)
B.
Consumable Materials
(1)
C00064 Surface Treatment, MIL-C-5541, Alodine 1200
(2)
C00259 Enamel - Primer, Green, BMS 10-11
C.
References
(1)
AMM 27-51-20/401, Flap Torque Tube
(2)
AMM 51-21-04/701, Alodized Surfaces
(3)
AMM 51-24-01/701, Chemical and Solvent Resistant Finish
D.
Access
(1)
Location Zone 135 Wing Landing Gear Wheel Well, LH 136 Wing Landing Gear Wheel Well, RH 572 Landing Gear Support Beam and Rear Spar to Trailing Edge,
LH 672 Landing Gear Support Beam and Rear Spar to Trailing Edge,
RH
581 Rear Spar to Trailing Edge, LH
681 Rear Spar to Trailing Edge, RH
E. Procedure
NOTE: Put the torque tube splice near the end of the shaft if it is
____ possible. Make sure that the clearance between the bolts and the adjacent structure is a minimum of 0.125 inch (3.18 mm).
S 028-006
(1)
Remove the torque tube (AMM 27-51-20/401).
S 328-007
(2)
Cut the torque tube shaft.
S 228-024
(3)
Measure the inner diameter of the torque tube.
S 328-008
(4)
Make the splice tube (Fig. 801):
(a)
Machine the splice tube outer diameter to the average inner diameter of the torque tube, +0.000 to -0.002 inch (+0.00 to -0.05 mm).
S 328-009
(5)
Drill the holes (Fig. 801):
(a)
Drill 0.254-0.250 inch (6.45-6.35 mm) holes through the rod and the torque tube.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-51-20
ALL ú ú 01 Page 804 ú Oct 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
(b) Put the bolts in the positions shown in section A-A.
S 378-010
(6)
Apply alodine to the inner diameter of the torque tube (AMM 51-21-04/701).
S 378-026
(7)
Apply alodine to the splice tube if the material is aluminum (AMM 51-21-04/701).
S 378-011
(8) 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：747-400 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 4(179)
