FLAP ANGLE GEARBOX - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Grease - MIL-G-23827 (Ref 20-30-21)
2. Prepare Flap Angle Gearbox for Removal
A. Provide system A hydraulic power (Ref 27-51-0, Maintenance Practices).
B. Position flap control lever to FLAP DOWN detent.
C. Remove system A hydraulic power (Ref 27-51-0).
D. Restrain flaps to prevent motion when torque tubes are disconnected.
3. Remove Flap Angle Gearbox
A. Remove screws attaching torque tube coupling sleeves to gearbox spline couplings. Slide sleeves off couplings to disconnect torque tube (Fig. 401).
B. Remove three mounting bolts attaching gearbox to landing gear beam and remove gearbox.
4. Install Flap Angle Gearbox
A. Align gearbox with landing gear beam and install mounting bolts (Fig. 401). Secure each bolt with two washers and locknut.
B. Lubricate spline couplings with grease, engage torque tube sleeves with spline couplings on gearbox and install retaining screws. Lockwire screw heads together.
C. Remove restraint from flaps.
D. Provide system A hydraulic power (Ref 27-51-0).
E. Position flap control lever to exercise flaps and check operation of gearbox.
5. Restore Airplane to Normal Configuration
A. Position flap control lever to FLAP UP detent.
B. Remove system A hydraulic power (Ref 27-51-0).
501
Nov 01/74 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-271 Page 401
G26020
Flap Angle Gearbox Installation 500
27-51-271 Figure 401 Aug 15/67
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
FLAP TRANSMISSION - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Flap Drive Adapter - F70300-1
B. Alemite Fitting - Z-737
C. Lubricating Oil - general purpose (low temperature), MIL-L-7870 (Ref 20-30-21)
D. Corrosion Preventive Compound - MIL-C-11796, Class 3 (Ref 20-30-21)
E. Hydraulic Fluid -MIL-H-5606 (Ref 20-30-21)
F. Grease - MIL-G-23827 (Ref 20-30-21)
G. Sealant - BMS 5-95 (Ref 20-30-11)
2. Prepare Flap Transmission for Removal
A. Provide system A hydraulic power (Ref 27-51-0 MP).
B. Retract flaps. Remove system A hydraulic power (Ref 27-51-0 MP).
C. Remove fairing to gain access to flap transmission.
(1)
For outboard flap transmission, remove forward fairing (Ref 27-51-121 R/I).
(2)
For inboard flap outboard transmission, remove engine-to-wing fairing tail cone, remove access panel from inboard side of fairing and access panel from aft of spring-loaded fairing door (Ref Chapter 54, Engine-to-Wing Fairing).
(3)
For inboard flap inboard transmission, remove fairing (Ref 27-51-141 R/I).
D. With flaps in full up position, check angular clearance (X1 between upstop on jackscrew ball nut and upstop on screw yoke. If this value is between 170 to 190 degrees (1/2 turn + 10 degrees) turn (1/4 to 5/6 turn if lateral trim correction has been made), record for use on installation.
CAUTION: MAXIMUM ALLOWABLE ANGULAR CLEARANCE IS 1/4 TO 5/6 TURNS. A VALUE FOR (X) OUTSIDE THIS RANGE MAY CAUSE DAMAGE DURING FLAP OPERATION. PREVIOUS LATERAL TRIM CORRECTIONS SHOULD BE RETAINED.
E. Provide system A hydraulic power (Ref 27-51-0 MP).
F. Extend trailing edge flaps.
G. Remove system A hydraulic power (Ref 27-51-0 MP).
H. Restrain flaps to prevent motion when transmissions are disconnected.
567
Jun 20/91 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-281 Page 401
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