G25984
500 Typical Torque Tube Installation
Aug 15/67 Figure 401 27-51-251
Page 403
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
FLAP TORQUE TUBES - ADJUSTMENT/TEST
1. Flap Torque Tube Test
A. Test Flap Torque Tubes
(1)
Provide system A hydraulic power (Ref 27-51-0 MP).
(2)
Position flap control lever to extend and retract flaps. Check that at least 0.25-inch clearance exists between rotating parts of flap torque tubes and all surrounding structure and equipment.
(3)
Position flap control lever to FLAP DOWN detent to extend flaps.
(4)
Remove system A hydraulic power (Ref 27-51-0 MP).
(5)
Check that where torque tubes pass through wing to nacelle bulkhead seals, the seals are free floating and can be moved without restriction within the seal retainer and that a minimum radial clearance of 0.05 inch between seal and torque tube can be obtained.
NOTE: Inside diameter of seal is approximately 0.10 inch larger than outside diameter of torque tube.
(6)
Check torque tubes for straightness measured statically. Torque tubes must be straight within 0.01 inch total indicator reading per foot of torque tube length.
B. Restore Airplane to Normal Configuration
(1)
Provide system A hydraulic power (Ref 27-51-0 MP).
(2)
Position flap control lever in FLAP UP detent to retract flaps.
(3)
Remove system A hydraulic power (Ref 27-51-0 MP).
500
Oct 20/87 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-251 Page 501
FLAP TORQUE TUBE - APPROVED REPAIRS
1. Equipment and Materials
A. Alodine 1200 (Ref 20-30-02)
2. Repair Torque Tube
A. Remove torque tube from airplane (Ref 27-51-251, Removal/Installation).
B. Clean torque tube and check for wear and tube wall reduction (Fig. 801).
C. Repair defects using a minimum blend radius of 1.00 inch. Surface finish of repaired area must be 63 microinches or better. Reduction in wall thickness to be limited to dimensions shown in table.
D. Apply colored alodized surface treatment to repaired area.
E. Apply abrasion resistant finish to repaired area and to area each side of repaired area as shown per Fig. 801 (Ref 51-21-81, Abrasion Resistant Teflon Finish - Application).
F. Install torque tube in airplane (Ref 27-51-251).
500
Nov 15/76 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-251 Page 801
G25993
Torque Tube Approved Repairs 500
27-51-251 Figure 801 Nov 15/76
Page 802
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
FLAP RIGHT ANGLE GEARBOX - REMOVAL/INSTALLATION
Equipment and Materials
A. TE Wing Flap Drive Installation Alignment Checking Tool - F80186-10 (Preferred)or F80186-1 (Optional)
B. Grease - MIL-G-23827 (Ref 20-30-21)
2. Prepare for Removal
A. Remove inboard flap track fairing (Ref 27-51-141 R/I).
B. Provide System A hydraulic power (Ref 27-51-0 MP).
C. Position flap control lever to FLAPS UP detent.
NOTE: Flaps must be fully retracted to align boltholes.
D. Remove System A hydraulic power (Ref 27-51-0).
3. Remove Flap Right Angle Gearbox
A. Remove screws attaching torque tube coupling sleeves to gearbox spline couplings. Slide sleeves off couplings to disconnect torque tubes (Fig. 401).
NOTE: Restrain flaps to prevent motion when torque tubes are disconnected.
B. Remove the three mounting bolts which attach the support bracket to the structure.
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(jī)維護(hù)手冊 飛行操縱 FLIGHT CONTROLS 3(68)
