737-300 400 500 AMM 飞机维护手册 自动飞行 AUTOFLIGHT 1(97)

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12. FCC 115V AC (0.5 SEC)  X  X 
13. (DC) ENGAGE INTLK A  X  X 
14. NOT (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. IRU TRANSFER (SEE TEXT) 2  2 
30. A/P ENGAGE SWITCH SWAP (SEE TEXT)  X 
31. ADC CORRECTED BARO ALT VALID  X  1 
32. ADC UNCORRECTED BARO ALT VALID  X  1 
33. LCL AC BUS TRANSFER (SINGLE SHOT)  2  2 
34. A/P DISENGAGE SWITCH PRESSED 
35. DISENGAGE BAR ON MCP PULLED DOWN 

A/P Engage Interlock Table
Figure 15

A737-300/400/500MAINTENANCE MANUAL
A 
737-300/400/500MAINTENANCE MANUAL
 (e)  Item 5 - INTENTIONAL BLANK
 (f)  Item 6 - INTENTIONAL BLANK
 (g)  Item 7 - The A/P is normally disengaged by pressing the
 disengage switch on the control wheel.
 (h)  Item 8 - Prior to engaging the A/P, the 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 engaged in CWS or CMD. This action must be complete within
 3.5 seconds from the time dc was applied to the actuator detent
 solenoid.
 (j)  Item 10 - Same as (8) except elevator.
 (k)  Item 11 - Same as (9) except elevator.
 (l)  Item 12 - The FCC 115 volts ac must be valid. A delay allows
 an interrupt of 0.5 seconds.
 (m)  Item 13 - The DC ENGAGE INTLK is the power source for several
 interlocks and therefore a requirement for unlock and hold
 logic.
 (n)  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)  Item 15 - FCC DC is the primary power source for the FCC. The
 power input and power supply are monitored.
 (p)  Item 16 - The 1800 Hz power must be valid.
 (q)  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
 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.
 (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
 BIT process. The power up stimilus test (STIM) is monitored to
 assure that test signals are not present during normal
 operation.
 (s)  Item 19 - The A/P continuous monitor only checks the actuator
 position transducer to assure that an open circuit does not
 exist. The neutral shift sensor is monitored for
 reasonableness. The NSS is deemed failed if the voltage
 changes greater than 10% of the full scale value per second.
 Actuator command is monitored by comparing command against
 response.
 (t)  Item 20 - A force applied on the control wheel inhibits A/P
 engagement. A 3-pound force is set as the threshold.
 (u)  Item 21 - A force applied on the control column inhibits A/P
 engagement. A 5-pound force is set as the threshold.

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