+ 0.05 psi (334 ± 3 knots).
CAUTION: DO NOT EXCEED 6 PSI (474 KNOTS) TO THE PITOTS AT ANY TIME DURING THIS TEST. OVERPRESSURE MAY DAMAGE FEEL COMPUTER.
(u)
Check that system B on the autopilot control panel is selected.
(v)
Repeat steps (h) thru (n) above.
(w)
Check that total displacement of steps (j) and (l) is 2.43 + 0.39 inches.
(x)
Turn off hydraulic system A flight controls switch.
(y)
Repeat steps (h) thru (n) above.
(aa) Check that total displacement of steps (j) and (l) is 3.07 + 0.49 inches.
(ab) Reduce 2.8 psi (334 knots) pitot pressure to zero.
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27-31-131 Page 412 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/92
S. Restore Airplane to Normal
(1)
Ensure that all tools used during testing are removed.
(2)
Remove all masking tape.
(3)
Remove seals from drain holes in each vertical fin pitot tube.
CAUTION: MAKE SURE SEALS ARE REMOVED FROM PITOT TUBES.
(4)
Remove pressure gage lines from systems A and B drain lines located below feel computer.
(5)
Install drain plugs on system A and B drain lines located below feel computer.
(6)
Remove regulated air pressure lines from both vertical fin pitot tubes.
(7)
Open the vertical gyro circuit breaker and wait 10 minutes before remounting gyro.
(8)
Close all circuit breakers opened during testing.
(9)
Install access panels.
(10)
Restore airplane to normal hydraulic configuration (Ref 27-31-0).
(11)
Service hydraulic reservoirs, if required (Ref Chapter 12 Hydraulic Servicing).
(12)
Remove electrical power if no longer required.
545
Aug 15/78 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-131 Page 413
ELEVATOR FEEL COMPUTER - 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 components after inspection for wear. Refer to Component Removal/Installation for this information.
2. Elevator Feel Computer Wear Limits
G10232 G10245G10254
500 Elevator Feel Computer Wear Limits
Aug 15/68 Figure 601 (Sheet 1) 27-31-131
Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Elevator Feel Computer Wear Limits 500
27-31-131 Figure 601 (Sheet 2) May 15/68
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Elevator Feel Computer Wear Limits
Aug 15/68 Figure 601 (Sheet 3) 27-31-131
Page 603
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
INDEX NO. PART NAME DIM DESIGN LIMITS WEAR LIMTS REPLACE WORN PART REPAIR WORN PART REPAIR INSTR.
DIAMETER MAX WEAR DIM. MAX DIAM CLEAR-ANCE
MIN MAX
1 ARM ID 0.2495 0.2505 0.2535 0.0040 X 1
BOLT OD 0.2485 0.2495 0.2481 X
2 BEARING ID 0.2497 0.2500 0.2530 0.0035 X
BOLT OD 0.2485 0.2495 0.2481 X
3 BEARING ID 0.2495 0.2500 0.2530 0.0035 X
BOLT OD 0.2485 0.2495 0.2481 X
4 BUSHING ID 0.2495 0.2505 0.2525 0.003530 X
BOLT OD 0.2485 0.2495 0.2481 X
5 ARM ID 0.3762 0.3767 0.3785 0.0040 X 2
BUSHING OD 0.3754 0.3761 0.3745 X
6 ARM ID 0.2495 0.2505 0.2535 0.0040 X
BOLT OD 0.2485 0.2495 0.2481 x
7 BEARING ID 0.1895 0.1900 0.1945 0.0050 X
BOLT OD 0.1870 0.1895 0.1866 X
8 CRANK ID 0.1895 0.1905 0.1950 0.0055 X
BOLT OD 0.1870 0.1895 0.1866 X
9 ARM ID 0.1895 0.1900 0.1945 0.0050 X 3
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