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757 MAINTENANCE MANUAL
e) GUN 051; provide interaction message to position MCP CMD bat handle switches up to CMD. This action automatically synchronizes the aileron and elevator servos to the present control surface position. Servos will not engage until servos synchronized.
f) GUN 001-050, 052-999; provide interaction message to push MCP CMD switches. This action automatically synchronizes the aileron and elevator servos to the present control surface position. Servos will not engage until servos synchronized.
g) Column centers, then moves aft (trailing edge up), then forward (trailing edge down) and back to center. Elevators are driven to a plus 20 degrees (trailing edge up) and a minus 9 degrees (trailing edge down) and the FCCs check that each position is within limits.
09 SERVO RUD
a) Displays any FCC self-test faults and FCC interface faults related to rudder servo.
b) Provides interaction message to verify hydraulic pressure on (VFY HYD ON).
c) Provides interaction message to verify rudder trim set to zero.
d) Rudder centers, then moves rudder trailing edge right, then left and back to center. Rudder driven to a plus and minus 20 degrees and FCCs check that each position is within limits.
10 SERVO A/T
a) Displays TMC self-test faults and TMC interface faults related to autothrottle.
b) Throttle is automatically initialized to aft position, then is driven at 10 degrees/second and checks for a Power Lever Angle (PLA) of 44 to 60 degrees. The test fails if a PLA of 55 degrees is not sensed within six seconds. The autothrottle is then driven forward for eight seconds at 10 degrees/second and checked for a PLA of 120 to 136 degrees, and a tachometer signal feedback of approximately 10 degrees/second. The autothrottle is driven aft for eight seconds at 10 degrees/second, and checked for a PLA of 44 to 60 degrees, and a tachometer feedback signal of approximately 10 degrees/second.
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10) 11 SW A/P DISC a) Displays any FCC self-test faults, and FCC interface faults related to A/P Disc switch. b) Instructs the operator to close the captain's and first officer's autopilot disconnect switches. The switch output is monitored for autopilot disconnect command response.
11) 12 SW A/T DISC a) Displays any TMC self-test faults and TMC interface faults related to A/T disconnect switch. b) Instructs operator to close the left and right autothrottle disconnect switches. Switch output is monitored for autothrottle disconnect command response.
12) 13 SW G/A a) Displays any FCC and TMC self-test faults, FCC and TMC interface faults related to G/A switch. b) Instructs the operator to close the captain's and first officer's Go-Around (G/A) switches. The G/A switch command response is monitored at each FCC and TMC.
13) AIRPLANES WITHOUT CONTROL WHEEL STEERING; 14 XDCR COL L a) This test does not apply to this aircraft configuration. If test selected, MCDP displays 14 NO TEST THIS A/C CONFIG.
14) AIRPLANES WITH CONTROL WHEEL STEERING; 14 XDCR COL L a) Displays any FCC self-test faults and FCC interface faults related to column transducer. b) Provides interaction message to verify hydraulic power on (VFY HYD ON). c) Instructs operator to move the left control column to the full aft position. The transducer output force is monitored for a plus 30 pounds. d) Instructs operator to move the left control column to the full forward position. The transducer output force is monitored for a minus 30 pounds.
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e) Instructs operator to release the left control column. The transducer output is monitored for a force of between plus and minus 4 pounds.
15) AIRPLANES WITHOUT CONTROL WHEEL STEERING; 15 XDCR COL R a) This test does not apply to this aircraft
configuration. If test selected, MCDP displays 15 NO TEST THIS A/C CONFIG.
16) AIRPLANES WITH CONTROL WHEEL STEERING; 15 XDCR COL R a) Functions the same as the XDCR COL L test.
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