27-81-00
ALL ú ú 01 Page 529 ú Oct 10/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
S 225-051
(12)
Make sure flap seals are not out of tolerances (Fig. 502).
(a)
Adjust the flap seals to get the correct tolerances if it is necessary.
S 715-052
(13)
With the LE flaps retracted pneumatically, do a check on the retract stop clearance.
(a)
Move the flap control lever to the 5 unit detend to extend the LE flaps.
(b)
Put the instrument into the stop bolt hole to extend the clearance indicator pin 0.15-0.20 inch (Section E-E, Fig. 502).
(c)
Operate the LE flaps pneumatically.
(d)
Measure the height of the clearance indicator pin.
(e)
Make sure the clearance at the retract stop is not out of tolerance (Section E-E). 1) If the retract stop clearance is out of tolerance, do these
steps:
a) Move the washers to adjust the stop bolt.
b) Push the indicator pin in directly with the head of the
stop bolt when you get the correct clearance.
(f)
Install the coupling bolts and the lockwire.
I.
Put the Airplane Back to its Usual Condition
S 865-053
(1)
Remove No. 1 and 4 hydraulic system power (Ref 29-11-00/201).
S 865-054
(2)
Remove pneumatic power (Ref 36-00-00/201).
S 865-055
(3)
Remove electrical power (Ref 24-22-00/201).
TASK 27-81-00-705-056
5. Leading Edge Flaps System Test
______________________________
A. General
(1)
During the LE flap system test, the airplane can be on its landing gear or on the jacks. The airplane can have fuel or no fuel in its tanks during the system test.
(2)
Do this test at the same time as the Leading Edge Flap Indicating System - Operational Test (Ref 27-88-00/501).
B.
Special Tools and Equipment
(1)
G27009-19 Test Box - Leading Edge Flap Alternate Drive Motor
C.
Standard Tools and Equipment
(1)
DC Volt-Ohmmeter (Range 0-200 ohms)
(2)
AC Ammeter (Range 0-1 amp)
(3)
DC Ammeter (Range 0-1 amp)
D.
References
(1)
24-22-00/201, Manual Control
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27-81-00
ALL ú ú 01 Page 530 ú Oct 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
(2)
27-62-00/201, Speed Brake Control System
(3)
29-11-00/201, Main Hydraulic System
(4)
36-00-00/201, Pneumatic System
E.
Access
(1)
Location Zone 221 Control Cabin, LH 222 Control Cabin, RH 117 Electrical and Electronics Compartment - P414 Left Power
Distribution Center 118 Electrical and Electronics Compartment - P415 Right Power Distribution Center
F. Prepare for Test
S 865-057
(1)
Make sure the flap control lever is in full UP detent.
S 865-090
(2)
Make sure LE flaps and TE flaps are fully retracted.
S 865-058
(3)
Supply electrical power (Ref 24-22-00/201).
S 865-059
WARNING: MAKE SURE PERSONS AND EQUIPMENT ARE CLEAR OF THE LE FLAPS
_______ BEFORE YOU APPLY PNEUMATIC POWER. THE LE FLAPS CAN MOVE AUTOMATICALLY WHEN YOU APPLY PNEUMATIC POWER. THIS OCCUR IF YOU MOVED THE REVERSE THRUST LEVERS OR FLAP CONTROL LEVER WHEN PNEUMATIC POWER WAS OFF.
(4)
Supply pneumatic power (Ref 36-00-00/201).
S 865-096
(5)
Supply systems No. 1 and 4 hydraulic power (Ref 29-11-00/201).
G.
Test the Leading Edge Flap System
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27-81-00
ALL ú ú 01 Page 531 ú Oct 10/96
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本文链接地址：747-400 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 7(69)
