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MAINTENANCE MANUAL
(5)
Fault Data Storage
(a)
The FCC provides permanent storage for up to five internal faults which result in an FCC invalid, and temporary storage for five words of fault data per flight leg.
(b)
Fault data in temporary storage is formatted for transmission over a ARINC 429 data bus to the MCDP. The FCC clears temporary data at the start of each flight leg. Data provided to the MCDP includes: 1) Fault identity and location 2) Source of fault detection 3) Fault effect on flight deck 4) Fault intermittent or constant 5) Fault occured in-flight or on-ground
(6)
MCDP Fault Recording and Testing
(a)
The MCDP decodes and stores, in non-volatile memory, flight fault data from three flight control computers, one thrust management computer, and two flight management computers. The MCDP can store up to 350 independent flight faults. Ground faults during tests are annunciated but not stored for recall.
(b)
The MCDP outputs test discrete signals to the FCCs to initiate ground testing. The test discrete signals are inhibited when the airplane is not on the ground. The MCDP provides test control and test parameters for the FCC ground test.
(c)
The FCC tests the AFDS, including:
1) Central Processor Unit
2) Memories
3) Interfacing electronics
4) Power supplies
(d)
FCC tests include: 1) Automatic self-test - tests FCC hardware not tested during in-flight automatic self-test.
2) Automatic interface tests.
a) ILS Tune Inhibit
b) RA Test Inhibit
c) Bus Isolate
d) Autopilot Servos
e) Automatic Stabilizer Trim
3) Manual interface tests.
a) Servo Detents
b) Transducer Output
c) MCP
d) ASA
e) FCC-EFIS Display
f) Analog Data Comparison
(e) The MCDP displays flight faults, ground faults, or initiates ground testing (Ref 22-41-00, Maintenance Monitor).
C. Control
(1) The autopilot is ON when power is applied. Proper operation requires interfacing systems be ON and operational.
(a) Ensure the following systems are operational. 1) Thrust Management Power (22-31-00, Adjustment/Test)
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MAINTENANCE MANUAL
2) Maintenance Monitor (22-41-00, Adjustment/Test) 3) AC Generation (24-20-00, Adjustment/Test) 4) DC Generation (24-30-00, Adjustment/Test) 5) Aileron and Aileron Trim Control System (27-11-00,
Adjustment/Test) 6) Rudder and Rudder Trim Control System (27-21-00,
Adjustment/Test) 7) Elevator Control System (27-31-00, Adjustment/Test) 8) Horizontal Stabilizer Trim Control System (27-41-00,
Adjustment/Test) 9) Leading Edge Slat System (27-81-00, Adjustment/Test) 10) Main Hydraulic Systems (29-11-00, Adjustment/Test) 11) Engine Indication and Crew Alerting System (31-41-00,
Adjustment/Test) 12) Landing Gear Position Indicating and Warning System
(32-61-00, Adjustment/Test) 13) Integral Panel Lights (33-13-00, Maintenance Practices) 14) Master Dim and Test (33-16-00, Adjustment/Test) 15) Air Data Computing System (34-12-00, Adjustment/Test) 16) Inertial Reference System (34-21-00, Adjustment/Test) 17) Flight Instrument System (34-22-00, Adjustment/Test) 18) ILS Navigation System (34-31-00, Adjustment/Test) 19) Radio Altimeter System (34-33-00, Adjustment/Test) 20) DME System (34-55-00, Adjustment/Test) 21) Flight Management Computer System (34-61-00,
Adjustment/Test)
(b) Ensure the following circuit breakers on circuit breaker panel P11 are closed. 1) FLT CONT CMPTR SERVO L 2) MODE CONT PNL L 3) FLT CONT CMPTR PWR L 4) FLT CONT CMPTR SERVO R 5) MODE CONT PNL R 6) FLT CONT CMPTR PWR R 7) FLT CONT CMPTR SERVO C 8) FLT CONT CMPTR PWR C
The F/D is operational when the FD switches are positioned to ON. The F/D command bars are then in view on the EADIs.
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