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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
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DFCS - FUNCTIONAL DESCRIPTION - A/P ENGAGE INTERLOCK SCHEMATIC
DFCS - FUNCTIONAL DESCRIPTION - A/P ENGAGE INTERLOCK SCHEMATIC
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
General
The table shows some of the functions that the autopilot engage
interlock circuits monitor and the conditions that they cause.
These are the three conditions:
* Pre-engage - shows the functions necessary to engage the
autopilot
* Hold - shows the functions necessary to keep the autopilot
engaged
* Disengage - shows functions that disengage the autopilot.
Engage and Disengage Functions
1. The stabilizer trim cutout switch must be in the normal
position.
2. The crew must not push a main electric trim switch to
manually trim the stabilizer.
3. The A/P stabilizer trim system must not try to trim nose up
and nose down at the same time.
4. The stab trim motor is a two-speed motor and the speed
depends on the position of the flaps. The motor speed and flap
position must agree. A 10-second delay allows for flap
movement.
5. The captain and first officer must not push A/P disengage
switches.
6. Before the A/P engages, the A/P actuator hydraulic pressure
switches must show no hydraulic pressure.
7. After the A/P actuators synchronize, the FCC energizes the
detent solenoid. There must be hydraulic pressure in 3.5
seconds.
8. The FCC 115v ac must be valid. A delay allows an interrupt of
0.5 seconds.
9. The dc engage interlock is the power source for several
interlocks and is necessary for pre-engage and hold logic.
10. The FCC 28v dc and the internal power supplies must be
valid.
11. The power-up test monitors these components and functions
and they must pass the test:
* CPU 1 and 2
* Autoland
* Go-around (G/A).
The FCC also does these continuous checks:
* Read only memory (ROM)
* Random access memory (RAM)
* Direct memory access (DMA) controller
* Digital to analog and analog to digital converters
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* Program flow and master timer, also called heartbeat.
The FCC does these continuous autopilot checks:
* Actuator position transducers (LVDT) for an open circuit
* Neutral shift sensor for reasonable data
* Actuator commands to the actuator movement.
12. Any force on the control wheel must be less than 3 pounds.
Any force on the control column must be less than 5 pounds.
13. This inertial reference data from the ADIRU must be valid:
* Roll angle
* Roll rate
* Pitch angle
* Pitch rate.
14. This air data from the ADIRU must be valid except when the
autopilot is in the flare arm mode:
* Computed airspeed (CAS)
* Uncorrected baro altitude.
15. You can engage only one autopilot when in the cruise mode.
When you try to engage the second autopilot, the first autopilot
will disengage. The first autopilot will disengage after the
second autopilot actuators are fully pressurized.
16. The captain or the first officer can disengage the autopilots if
one pushes a disengage switch.
17. If the MCP bus is invalid, the autopilot will disengage in all
the modes except the approach mode after approach on course.
18. A local AC bus transfer disengages the local autopilot in
CMD. You may engage the autopilot again unless the foreign
autopilot is in the approach and CMD modes.
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D633A101-SHZ1 Jun 10/2003
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
22-11-00-056
DFCS - FUNCTIONAL DESCRIPTION - A/P ENGAGE LOGIC TABLE-1
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