(12)
12 SW A/T DISC
(a) Displays any TMC self-test faults and TMC interface faults related to A/T disconnect switch.
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(b) Instructs operator to close the left and right autothrottle disconnect switches. Switch output is monitored for autothrottle disconnect command response.
(13)
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.
(14)
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.
(15)
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.
(e)
Instructs operator to release the left control column. The transducer output is monitored for a force of between plus and minus 4 pounds.
(16)
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.
(17)
AIRPLANES WITH CONTROL WHEEL STEERING; 15 XDCR COL R
(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 right control column to the full aft position. The transducer output force is monitored for a plus 30 pounds.
(d)
Instructs operator to move the right control column to the full forward position. The transducer output force is monitored for a minus 30 pounds.
(e)
Instructs operator to release the right control column. The transducer output is monitored for a force of between plus and minus 4 pounds.
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MAINTENANCE MANUAL
(18)
AIRPLANES WITHOUT CONTROL WHEEL STEERING; 16 XDCR WHL
(a) This test does not apply to this aircraft configuration. If test selected, MCDP displays 16 NO TEST THIS A/C CONFIG.
(19)
AIRPLANES WITH CONTROL WHEEL STEERING; 16 XDCR WHL
(a)
Displays any FCC self-test faults and FCC interface faults related to control wheel transducer.
(b)
Provides action message to verify hydraulic power on (VFY HYD ON).
(c)
Instructs operator to move the control wheel to the full clockwise position. The transducer output force is monitored for a plus 15 pounds.
(d)
Instructs operator to move the control wheel to the full counterclockwise position. The transducer output force is monitored for a minus 15 pounds.
(e)
Instructs operator to release the control wheel. The transducer output is monitored for a force of between plus and minus 2 pounds.
(20)
ON GUN 011-999; 17 PVDC
(21)
30 CURRENT FAULT REPORT
(a)
Displays all LRU and interface faults detected and stored in the FCCs and TMC while the MCDP operates in the ground test mode. Ground fault messages and diagnostic codes are the same as flight fault messages except the flight deck effect and intermittent bit status are not displayed. Diagnostic codes are displayed by pressing the GRD TEST mode switch.
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