11) Tilt the vertical gyro approximately 20 degrees front end up and hold.
12) Measure and record right elevator trailing edge displacement with respect to index mark.
13) Relevel the vertical gyro.
14) Disengage the pitch axis.
15) Add the displacements of steps 10) and 12). The total displacement shall be
3.51 士0.56 inches. 16) Turn on the hydraulic system A flight controls switch. 17) Repeat steps 8) thru 14) above. 18) The total displacement of steps 10) and 12) shall be 2.88 士0.46 inches. 19) Set stabilizer jackscrew B dimension at 42.28 士0.01 inches. 20) Reduce 3.50士0.05 psi (370士3 knots) pitot pressure to zero. Then increase
pressure to 2.80 士0.05 psi (334 士3 knots).
CAUTION: DO NOT EXCEED 6 PSI (474 KNOTS) TO THE PITOTS AT ANY TIME DURING THIS TEST. OVERPRESSURE MAY DAMAGE FEEL COMPUTER.
21) Check that system B on the autopilot control panel is selected.
22) Repeat steps 8) thru 14) above.
23) The total displacement of steps 10) and 12) shall be 2.43 士0.39 inches.
24) Turn off the hydraulic system A flight controls switch.
25) Repeat steps 8) thru 14) above.
26) The total displacement of steps 10) and 12) shall be 3.07 士0.49 inches.
27) Reduce pitot pressure to zero.
545
Jun 20/92 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-0 Page 537
C. 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
(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)
Restore airplane to normal hydraulic configuration (Ref 27-31-0).
(10)
Remove electrical power if no longer required.
545
27-31-0 Page 538 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 01/75
ELEVATORS - REMOVAL/INSTALLATION
EFFECTIVITY
Airplanes with Aluminum/Fiberglass Elevators
1. General
A. For interchangeability of graphite/epoxy elevator with aluminum/fiberglass elevator, refer to 27-09-800.
B. Balancing requirements are a function of elevator part number and elevator tab part number. Ensure that balancing requirements for elevator-elevator tab combination to be installed have been met per Chapter 51 of the Structural Repair Manual. Elevator rebalancing is required after structural repairs or after repainting.
C. If an elevator control tab is being installed on the elevator during elevator installation, it is necessary to check that the number of elevator control tab adjust weights installed on the elevator nose corresponds with the required number of adjust weights marked on the elevator tab data plate (Ref 27-31-31 MP).
2. Equipment and Materials
A. Elevator Hoisting Adapter - F80026-1
B. Hoist capable of lifting 200 pounds at a height of 20 feet
C. Rigging Pins Kit - F70207-3, -52, -61, or -84:
REF NO. F70207 - ( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
E-5 -11 0.309-0.311 6.7 ±0.25 Aft Control Quadrant
D. Trammel Bar - F80055-1
E. Corrosion Preventive Compound - MIL-C-11796, class 3 (Ref 20-30-21)
F. Loading block - 17 inches long, 2 x 4 wood block
G. Spring scale - 0- to 50-pound capability, graduated in 1-pound increments
H. Milliohmmeter - 0- to 0.1-ohm range.
3. Prepare for Removal
A. Remove elevator systems A and B hydraulic power (Ref 27-31-0 MP).
B. Remove or open the following access panels: Tail cone access panels 3801 and 3802, aft compartment access door 3701, stabilizer access panels 9105, 9107, 9108 and 9109 on left stabilizer or 9205, 9207, 9208 or 9209 on right stabilizer, elevator tab lock mechanism upper and lower access panels 9143 and 9142 on left elevator or 9243 and 9242 on right elevator (panels are located at elevator inboard leading edge, Fig. 401), tab pushrod access panel 9313 on left elevator or 9413 on right elevator, elevator hinge fitting upper and lower access panels 9128 thru 9141 on left elevator or 9228 thru 9241 on right elevator, and elevator control pushrod aft bolt access panel 3806 left or 3807 right (panel is located in tail cone adjacent to bolthead).
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(76)
