737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(75)

曝光台 注意防骗 网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者

NOTE:  Ensure that control columns are not disturbed from this position during the next step. 
7) 8)  Mark actual elevator trailing edge neutral position on masking tape. Using actual elevator trailing edge neutral position as a reference, mark elevator positions in steps 9) and 10) on masking tape. 
NOTE:  Pitot system check per step (b) must be satisfactory prior to proceeding. 
In the following column force checks, jiggle control column prior to each reading. 
In the following column force checks, elevator position refers to actual elevator travel as measured from a actual elevator neutral position. 
9)  Move captain's control column slowly aft and hold at indicated elevator position of 1.95 ±0.05 inches up on right elevator. The required column force shall be 37.5 ±4.0 pounds. 

500 
Jun 20/92  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-0 Page 533 

10)  Move captain's control column slowly forward and hold at indicated elevator position of 1.95 士0.05 inches down on right elevator. The required column force shall be 38.5 士4.0 pounds.
11)  Position flight controls hydraulic system B switch to OFF, leave system A switch ON.
12)  Move captain's control column slowly aft and hold at indicated elevator position of 1.95 士0.05 inches up on right elevator. The required column force shall be
37.5 士4.0 pounds.
13)  Move captain's control column slowly forward and hold at indicated elevator position of 1.95 士0.05 inches down on right elevator. The required column force shall be 38.5 士4.0 pounds.
14)  Position flight controls hydraulic system A switch to OFF and system B switch to ON. 15) Move captain's control column slowly aft and hold at indicated elevator position of 1.95 士0.05 inches up on right elevator. The required column force shall be
37.5 士4.0 pounds.
16)  Move captain's control column slowly forward and hold at indicated elevator position of 1.95 士0.05 inches down on right elevator. The required column force is 38.5 士4.0 pounds.
17)  Position flight controls hydraulic system A switch to ON.
18)  Reduce 3.50士0.05 psi (370士3 knots) dynamic pressure being applied to pitot tubes to zero pressure. Then increase pressure to 0.50士0.05 psi (145士7 knots).
CAUTION:  DO NOT RAISE TEST PRESSURE ABOVE 6.0 PSI (474 KNOTS) AT ANY TIME DURING TEST. OVERPRESSURE MAY DAMAGE COMPUTER.
500 
27-31-0 Page 534  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/92 

19) Move captain's control column slowly aft and hold at indicated elevator position. The following conditions shall be met:
CAPTAIN'S CONTROL COLUMN AFT 
RIGHT ELEVATOR POSITION COLUMN FORCE REQUIRED -POUNDS 
1.95 (士0.05) in. up 18.0 (士2.0) 
6.95 (士0.05) in. up 35.0 (士3.5) 

20) Move captain's control column slowly forward and hold at indicated elevator position. The following conditions shall be met.
CAPTAIN'S CONTROL COLUMN FORWARD 
RIGHT ELEVATOR POSITION COLUMN FORCE REQUIRED -POUNDS 
1.95 (士0.05) in. dn 19.0 (士2.0) 
6.15 (士0.05) in. dn 35.0 (士3.5) 

21)  Position flight controls hydraulic system B switch to OFF, leave system A switch ON.
22)  Perform test of step 19).
23)  Perform test of step 20).
24)  Position flight controls hydraulic system A switch to OFF and system B switch to ON.
25)  Perform test per step 19).
26)  Perform test per step 20).
27)  Position flight controls hydraulic system B switch to OFF.
500 
Feb 15/73  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-0 Page 535 

(d)  Test autopilot authority as follows:
NOTE:  Ensure that entire pitch channel of autopilot system is operational before proceeding.
Ensure that elevator and feel computer are properly adjusted before proceeding.
1)  Make sure that horizontal stabilizer B dimension is set at 41.57 士0.01 inches and mach trim actuator is in null position.
2)  Make sure that the following circuit breakers involved with autopilot pitch channel operation are engaged: a) Central Air Data Computer b) Vertical Gyro No. 1 c) Pitch Channel d) Autopilot Interlock
3) Open stabilizer trim circuit breakers.
4) Loosen vertical gyro No. 1 from mounting in electronics bay.
5) Using air pressure regulator, reduce pitot pressure to zero, then increase

pressure to 3.50 士0.05 psi (370 士3 knots).
CAUTION:  DO NOT EXCEED 6 PSI (474 KNOTS) TO PITOTS AT ANY TIME DURING THIS TEST. OVERPRESSURE MAY DAMAGE FEEL COMPUTER.
　
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(75)