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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.
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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.
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(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.
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