G06137
Balance Panels and Seals Installation 501
27-11-31Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 01/75
D. Place balance panel into position, and install forward and aft hinge pins.
E. Install hinge pin retaining bolts.
F. Install seals at inboard and outboard ends of balance panel and secure with bolts to structure. Check that gap between edge of seals and wing structure does not exceed 0.02 inch.
G. Ensure that correct number of aileron tab adjust weights are installed on balance panel.
NOTE: Data plate on aileron tab states required number of adjust weights.
H. Install access panel on lower wing surface and secure with screws.
I. Measure movement of ailerons to ensure that full travel is obtained without binding as shown in figure 402.
500
Aug 15/73 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-31 Page 403
T52452
Aileron Deflection Diagram 523
27-11-31 Figure 402 Aug 01/95
Page 404
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
BALANCE PANEL AND SEALS - INSPECTION CHECK
1. General
A. This data consists of illustrations and wear limits charts. There will be no procedure given in this section for gaining access to, or removing and replacing the component after inspection for wear. Refer to Component Removal/Installation for this information.
2. Balance Panel Wear Limits
G06149 G09239
500 Balance Panel and Seals Wear Limits
Nov 15/71 Figure 601 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-31 Page 601
Balance Panel and Seals Wear Limits 500
27-11-31 Page 602 Figure 501 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 15/73
AILERON CONTROL WHEEL - REMOVAL/INSTALLATION
1. General
A. This procedure does not allow the replacement of the wire bundle in the control column. The replacement control wheel is assumed to be equipped with stabilizer trim switch, terminal block in place, and cover on inboard horn.
NOTE: If wire bundle requires replacement, refer to overhaul manual for procedure and test.
2. Equipment and Materials
A. Control Wheel Straightedge - P/N SE27-0001
B. Rigging Pins Kit - F70207-84, or -98:
REF NO. F70207-( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
A/S-1 A/S-1A A/S-13 -13 -19 -8 0.309 - 0.311 0.309 - 0.311 0.309 - 0.311 2.35 + 0.06 8.25 + 0.25 3.7 + 0.25 AILERON TRANSFER MECHANISM AILERON TRANSFER MECHANISM AILERON TRIM GEARBOX
C. Dow Corning Compound No. 5 (Ref 20-30-21)
D. Insulation Tester - BIDDLE MODEL 656, MEGGER (500 VOLTS)
3. Remove Aileron Control Wheel
A. Set aileron trim control knob in zero trim position.
B. Insert rigging pins No. A/S-1 and A/S-1A in transfer mechanism, and rigging pin No. A/S-13 in aileron trim gearbox (Fig. 401).
NOTE: Rigging pin A/S-1 must be fully put into transfer mechanism and held to keep it from falling out.
C. Remove medallion from control wheel by removing three bolts.
D. Remove cotter pin, wheel retaining nut and special washer.
506
Aug 01/96 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-41 Page 401
G42335 G03210 G03213
Control Wheel Installation 500
27-11-41 Page 402 Figure 401 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 15/68
500 Control Wheel Installation
Aug 15/69 Figure 401 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-41 Page 403
Control wheel Installation 500
27-11-41 Page 404 Figure 401 (Sheet 3) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 15/67
E. Mark relative positions of control wheel and gear and sleeve assembly.
F. Carefully remove control wheel from control column, and support wheel until steps G. through
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