G25982
Flap Alternate Drive Unit Installation 505
27-51-241 Figure 401 Nov 15/77
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
FLAP ALTERNATE DRIVE UNIT - ADJUSTMENT/TEST
1. Flap Alternate Drive Unit Test
A. Prepare Alternate Drive Unit for Test
(1)
Connect electrical power to airplane.
(2)
Check that the following circuit breakers on panel P6-2 are closed:
(a)
TE ALT FLAP DRIVE MOTOR
(b)
FLAP VALVES
B. Test Alternate Drive Unit
(1)
Position alternate flap switch at ARM.
NOTE: Actuation of alternate flap switch to ARM energizes standby hydraulic pump motor.
(2)
Move flap control lever to FLAP DOWN (40-unit) detent.
CAUTION: DURING GROUND OPERATION, DO NOT OPERATE FLAP ALTERNATE DRIVE UNIT MORE THAN 4 MINUTES OPERATION AND 25 MINUTES OFF.
NOTE: Flap control lever is moved to FLAP DOWN position as a standard procedure to minimize load on flap hydraulic motors when hydraulic system A is pressurized.
(3) Actuate alternate flap drive switch to DOWN position. Hold switch in this position until trailing edge flap motion stops.
CAUTION: LEADING EDGE DEVICES WILL EXTEND. ENSURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR.
NOTE: Extension of trailing edge flaps is controlled by limit switches.
(4)
Check that time for flaps to extend is 146 (+10/-20) seconds.
(5)
Actuate alternate flap drive switch to UP position. Hold switch in this position until trailing edge flap motion stops.
(6)
Check that time for flaps to retract is 146 (+10/-20) seconds.
C. Restore Airplane to Normal Configuration
(1)
Position flap control lever in FLAP UP detent.
(2)
Position alternate flap switches to OFF.
(3)
Determine whether there is any further need for electrical power, if not, disconnect power.
500
Aug 01/96 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-241 Page 501
FLAP TORQUE TUBES - REMOVAL/INSTALLATION
1. General
A. Flap torque tubes connect the components of the flap drive system with spline coupling sleeves at both ends of the torque tubes.
B. The torque tube between the outboard flap transmissions has two segments with the flap position transmitter acting as a support bearing near its midpoint.
C. The torque tube between the inboard flap outboard transmission and the flap angle gearbox has two segments with a three bolt flange connection.
2. Equipment and Materials
A. Grease - MIL-G-23827 (Ref 20-30-21)
B. Flap Drive Adapter - F70300-1
C. Sealant - BMS 5-95 (Ref 20-30-11)
3. Prepare Flap Torque Tubes for Removal
A. Remove inboard flap track fairing, if required, to gain access to torque tube (Ref 27-51-141 R/I).
B. Provide system A hydraulic power (Ref 27-51-0 MP).
C. Position flap control lever to FLAP DOWN detent.
D. Remove system A hydraulic power (Ref 27-51-0).
E. Secure flaps to prevent motion when torque tubes are disconnected.
4. Remove Flap Torque Tubes
A. If removing torque tube in wing, remove torque tube guard.
B. Remove three screws attaching spline coupling sleeves to spline coupling. Slide coupling sleeves off splines to disconnect torque tubes (Fig. 401).
567
Oct 20/91 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-251 Page 401
C. If torque tube between inboard flap outboard transmission and angle gearbox is being removed, disconnect torque tube segments by removing three bolts at flange connection.
D. Remove torque tube from airplane.
5. Install Flap Torque Tubes
A. Position torque tube in airplane.
CAUTION: IF INSTALLING FLAP TORQUE TUBE THROUGH ENGINE NACELLE OUTBOARD BULKHEAD ENSURE THAT ABRASION RESISTANT TEFLON COATING ON TORQUE TUBE IS LOCATED AT BULKHEAD SEAL.
B. If torque tube between inboard flap outboard transmission and angle gearbox is being installed:
(1)
Locate torque tube segments so that flange connection is located 5 inches outboard of inboard ground spoiler outboard actuation fitting.
(2)
Apply a layer of sealant to the two flanges.
(3)
Install three bolts to connect flange connection.
(4)
Apply sealant to the bolts, washers and nuts.
中國航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 3(67)
