C.
Procedure
S 026-002
(1)
Do this task: "Aileron Tab Control Rod Removal" (Ref 27-11-34/401).
S 226-004
(2)
Do a check of the control rods (Fig. 601):
(a)
Remove the parts to be measured.
(b)
Measure the dimensions of these parts.
(c)
Compare the part dimensions to the limit dimensions.
(d)
If the part dimension is out of tolerance, replace the part.
(e)
Install all the parts removed to do the check.
S 426-003
(3) Do this task: "Aileron Tab Control Rod Installation" (Ref 27-11-34/401).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-11-34
ALL ú ú 01 Page 601 ú Mar 15/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
AILERON
SEE A
CONTROL RODS ADJUSTABLE TAB
(4 LOCATIONS) 1. ROD END/BOLT
FWD INBD A A A TAB BALANCE TAB MASTS AILERON
4. BUSHING/BOLT (2 LOCATIONS) 2. BUSHING/BUSHING
3. BUSHING/BOLT
A-A Aileron Tab Control Rods Wear Limits Figure 601 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-11-34
ALL ú ú 01 Page 602 ú Mar 15/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
NO. INDEX PART NAME DIM. DESIGN LIMITS WEAR LIMITS PARTWORN REPLACE PART WORN REPAIR INSTR REPAIR
DIAMETER PER-MITTED WEAR DIM. ANCE CLEAR-MAX DIA
MIN MAX
1 ROD END ID 1 0.0017 X
BOLT OD X
2 BUSHING ID 0.3761 0.3766 0.3780 0.0025 X
BUSHING OD 0.3756 0.3761 0.3740 X
3 BUSHING ID 0.2500 0.2515 0.2535 0.0040 X
BOLT OD 0.2485 0.2495 0.2475 X 2
4 BUSHING ID 0.2500 0.2515 0.2535 0.0040 X
BOLT OD 0.2485 0.2495 0.2475 X 2
REPLACE WHEN THE RADIAL PLAY OF THE BEARING IS MORE THAN 0.0020 INCH CHROME PLATE THICKNESS IS 0.0030 INCH
Aileron Tab Control Rods Wear Limits
Figure 601 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-11-34
ALL ú ú 01 Page 603 ú Mar 15/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
AILERON CONTROL WHEEL - REMOVAL/INSTALLATION
____________________________________________
1. General
_______
A. There are two tasks in this procedure. There is one task for the removal and one task for the installation of the aileron control wheel.
B. This procedure does not permit the replacement of the wire bundle in the control column. The replacement control wheel has the stabilizer trim switch, terminal block in its position, and a cover on the inboard horn. If it is necessary to replace the wire bundle, refer to the Overhaul Manual for the procedure and the test.
TASK 27-11-41-004-001
2. Aileron Control Wheel Removal
_____________________________
A. Special Tools and Equipment
(1)
SE27-0001 - Control Wheel Straithtedge
(2)
F70207-93 or -97 Rigging Pins Kit:
~.............................................................................. | | | DIAMETER | LENGTH | | | REF NO. | F70207-( ) | (INCHES) | (INCHES) | FUNCTION | ................................................................................ | A/S-1 | -13 | 0.309-0.311 | 2.35 |0.06 | AILERON TRANSFER | | | | | | MECHANISM | | A/S-1A | -19 | 0.309-0.311 | 8.25 +/- 0.25 | AILERON TRANSFER | | | | | | MECHANISM | | A/S-15 | -85 | 0.309-0.311 | 2.5 |0.25 | AILERON TRIM MECHANISM| 2.........…............…...............…...............….......................1
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 1(125)
