Jun 20/92 27-31-101
Page 507
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(m)
Relevel the vertical gyro.
(n)
Disengage the pitch axis.
(o)
Add the displacements of steps (j) and (l). Check that total displacement is 3.51 +
0.56 inches.
(p)
Turn on hydraulic system A flight controls switch.
(q)
Repeat steps (h) thru (n) above.
(r)
Check that total displacement of steps (j) and (l) is 2.88 + 0.46 inches.
(s)
Set stabilizer jackscrew B dimension at 42.28 + 0.01 inches.
(t)
Reduce 3.5-psi (370 + 3 knots) pitot pressure to zero. Then increase pressure to 2.80
+ 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.
(x)
Check that total displacement of steps (j) and (l) is 2.43 + 0.39 inches.
(v)
Turn off hydraulic system A flight controls switch.
(z)
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.
545
27-31-101 Page 508 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/92
D. Restore Airplane to Normal
(1) Ensure that all tools used during testing are removed.
(2) Remove seals from drain holes in each vertical fin pitot tube.
CAUTION: MAKE SURE SEALS ARE REMOVED FROM PITOT TUBES.
(3) Remove pressure gage lines from systems A and B drain lines located below feel
computer.
(4) Install drain plugs on system A and B drain lines located below feel computer.
(5) Remove regulated air pressure lines from both vertical fin pitot tubes.
(6) Open the vertical gyro circuit breaker and wait 10 minutes before remounting gyro.
(7) Close all circuit breakers opened during testing.
(8) Restore airplane to normal hydraulic configuration (Ref 27-31-0).
(9) Remove electrical power if no longer required.
545
Feb 01/75 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-101 Page 509
G09713G09722
Elevator Power Control Unit Adjustment/Test 551
27-31-101 Figure 501 Oct 20/84
Page 510
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Stabilizer B Dimensions
Nov 01/74 Figure 502 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-101 Page 511
ELEVATOR POWER CONTROL UNIT - 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. Elevator Power Control Unit Wear Limits
G09761 W02025
551 Elevator Power Control Unit Wear Limits
May 01/75 Figure 601 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-101 Page 601
Elevator Power Control Unit Wear Limits 501
中國(guó)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(cè) 飛行操縱 FLIGHT CONTROLS 2(107)
