737-300 400 500 AMM 飞机维护手册 自动飞行 AUTOFLIGHT 1(27)

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11. A/P ELEVATOR HYD PRESSURE SWITCH - PRESSURE WITHIN 3.5 SEC AFTER ELEV ACT DET SOL ENGAGED X 
12. FCC 115V AC (0.5 SEC)  X  X 
13. (DC) ENGAGE INTLK A  X  X 
14. FGN IN CMD AND APP PB AND LRRA >800 FT  X 
15. FCC DC AND FCC POWER SUPPLY  X  X 
16. 1800 Hz POWER SUPPLY  X  X 
17. POWER UP TEST VALID  X 
18. CONTINUOUS MONITOR  X  X 
19. A/P ONLY CONTINUOUS MONITOR VALID  X  X 
20. LESS THAN 3 LB FORCE ON CONTROL WHEEL  X 
21. LESS THAN 5 LB FORCE ON CONTROL COLUMN  X 
22. SELECTED IRU ROLL ANGLE VALID (NORM - OFF SIDE)  X  X 
23. SELECTED IRU ROLL RATE VALID (NORM - OFF SIDE)  X  X 
24. SELECTED IRU PITCH ANGLE VALID (NORM - ON SIDE)  X  X 
25. SELECTED IRU PITCH RATE VALID (NORM - ON SIDE)  X  X 
26. A/P TO CMD AND R/A <400 FT WITH LOC AND GS ENGAGED  X 
27. F/D IN TO OR GA, R/A ALT <400 FEET AND A/P TO CMD  X 
28. ADC CAS NOT VALID (EXCEPT WITH MONITORS ACTIVE)  X 
29. ATTITUDE XFR (SEE TEXT)  X 
30. A/P ENGAGE SWITCH SWAP (SEE TEXT)  X 
33. LCL AC BUS TRANSFER (SINGLE SHOT) 32. ADC UNCORRECTED BARO ALT VALID 31. ADC CORRECTED BARO ALT VALID  X X  X 1 1 

1 SEE PITCH MODE DISENGAGE TABLE
A/P Engage Interlock Table Figure 15
A737-300/400/500MAINTENANCE MANUAL
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A 
737-300/400/500MAINTENANCE MANUAL
 (d) (e) (f) (g) (h)  Item 4 - The aileron force limiter provides a variable stop for the control wheel during A/P operation. The mach trim switch and flap up switch provide control and interlock for each limit. A 3-second delay allows for transition without disengagement.Item 5 - Prior to engaging the A/P, the aileron force limiter clutch must be disengaged.Item 6 - In CWS or CMD the aileron force limiter clutch must be engaged.Item 7 - The A/P is normally disengaged by pressing the disengage switch of the control wheel.Item 8 - Prior to engaging the A/P, aileron pressure switch must not be closed.
 (i)  Item 9 - The A/P aileron actuator is synchronized to the surface prior to energizing the detent solenoid, when the A/P is raised to CWS or CMD. This action must be complete within 3.5 seconds from the time dc was applied to the actuator detent solenoid.
 (j) (k) (l)  Item 10 - Same as (8) except elevator.Item 11 - Same as (9) except elevator.Item 12 - The FCC uses 115 volts ac and reduces it to 26 volts ac for portion of the sensors. A delay allows an interrupt of 0.5 seconds.
 (m) (n)  Item 13 - The DC ENGAGE INTLK is the power source for several interlocks and therefore a requirement for unlock and hold logic.Item 14 - During an approach, if dual in CMD is desired, the second A/P must be in CMD prior to a radio altitude of 800 feet.
 (o) (p) (q)  Item 15 - FCC DC is the primary power source for the FCC. power input and power supply are monitored.Item 16 - The 1800 Hz power must be valid.Item 17 - The power UP test checks the CPU by inserting a signal to each of the two CPUs and comparing the outputs. After the CPUs are checked, autoland and GA circuits are The
 checked. Both CPUs are used to process the signals and the outputs compared. Likewise, a similar check is made of the dual-channel monitors. There are two sets of dual-channel
 monitors. These are exercised at power up by inserting BITE signals and the results compared.

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A 737-300/400/500MAINTENANCE MANUAL
 (r)  Item 18 - The continuous monitor checks the operation of the
 flight control computer, checks are made on ROM, program
 memory, RAM read/write operation, direct memory access (DMA)
 controller, D/A - A/D, program flow (TICKET) and heartbeat.
 The CPU 1 and 2 are also monitored by a continuous background
　
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