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A
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MAINTENANCE MANUAL
3) Make sure the dimension X on the midboard and the outboard flap linkage is not larger than the given values (Sections B-B and C-C).
NOTE: If the rigging tool is not available, measure the
____ dimension Y on the linkage. The dimension Y is equal to the dimension X minus 0.09 inch.
~....................................................... | | DIMENSION X | DIMENSION Y | ......................................................... | FLAP NO. | (| 0.03 Inch) | (| 0.03 Inch) | | 1E AND 26E | 30.89 | 30.80 | | (OUTBD LINKS) | | | ......................................................... | 1E AND 26E | 30.87 | 30.78 | | (INBD LINKS) | | | ......................................................... | 1 AND 26 | 30.87 | 30.78 | ......................................................... | 2, 3, 24, 25 | 30.88 | 30.79 | ......................................................... | 4, 5, 22, 23 | 30.89 | 30.80 | ......................................................... | 6 AND 21 | 35.71 | 35.62 | ......................................................... | 7 AND 20 | 35.71 | 35.62 | | (OUTBD LINKS) | | | ......................................................... | 7 AND 20 | 35.73 | 35.64 | | (INBD LINKS) | | | ......................................................... | 8 AND 19 | 35.73 | 35.64 | ......................................................... | 9 AND 18 | 35.76 | 35.67 | | (OUTBD LINKS) | | | ......................................................... | 9 AND 18 | 35.79 | 35.70 | | (INBD LINKS) | | | ......................................................... | 10 AND 17 | 35.82 | 35.73 | | (OUTBD LINKS) | | | ......................................................... | 10 AND 17 | 35.88 | 35.79 | | (INBD LINKS) | | | 2...............…...................…...................1
(c) If it is necessary to adjust the variable camber LE flaps, refer to paragraph E.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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MAINTENANCE MANUAL
(3)
The Krueger LE flaps are correctly adjusted if these conditions are satisfactory (Fig. 502):
(a)
Do these checks with the LE flaps retracted pneumatically:
1) Make sure the difference between adjacent flaps and between TE and LE flaps and wing structure are not out of tolerance (Details A and B and Sections B-B and C-C).
2) Make sure the distance between the adjacent flaps is not out tolerance (Section B-B).
3) Make sure the distance between the flap inboard edge and the wing structure is not out of tolerance (Section C-C).
4) Make sure the distances between the LE flap panels and the wing structure are not out tolerance (Detail A).
5) Make sure the distance between flaps No. 11 and 16 seal and nacelle structure is not out tolerance (Section A-A).
6) Make sure the distance between the retract stop on the actuator arm and the structure is not out tolerance (Section D-D).
7) Make sure the contour of the TE flap measured in line with the linkages is not out tolerance (Detail C).
(b)
If it is necessary to adjust the krueger LE flaps, refer to paragraph F.
B.
Special Tools and Equipment
(1)
6TE65B00114 Variable Camber Flap Rigging Bar
(2)
G27013-9 Inboard Krueger Flap No. 11 thru 16 Rigging Set
(Recommended)
(3)
12MIT65B04017 Krueger Flap Rigging Tool (Optional)
(4)
17MIT65B04017 Leading Edge Flap Drive Unit Lock
C. 中國航空網(wǎng) 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 7(63)
