a. Apply nose up force on control
wheel Note nose down trim
b. Apply nose down force on control
wheel Note nose up trim motion
after approximately 3 seconds.
Press right rudder Note left
approximately 3 seconds.
d. Press left rudder Note right
approximately 3 seconds.
5. Select HDG mode Observe FD
commands and control wheel motion
heading selector knob.
6. AP DISC & TRIM INTRPT Press
annunciation, and aural disconnect
7. Manual electric trim Check.
a. Pilot and copilot control wheel trim
Operation of the electric trim switch
system should occur only by movement of
pairs of switches. Any movement of the
elevator trim wheel while pressing only one
switch element denotes a trim system
malfunction. The AP / TRIM POWER switch
must be turned OFF and flight conducted
only by manual operation of the trim wheel.
Do not use autopilot
b. Pilot and copilot trim switches
Check individual element for no
movement of trim, then check
proper operation of both elements.
Pilot trim switches Check pilot
switches override copilot switches
directions, and trim moves in
direction commanded by pilot.
d. Pilot and copilot trim switches
activating pilot or copilot trim
8. AP XFER Switch Select copilot's
side and repeat steps 2 through 7.
3A-15. ATTITUDE AND HEADING REFERENCE
The attitude and heading reference system
consists of the vertical gyros, directional gyros, dual
remote compensator, and flux valves.
The vertical gyros provide the digital flight control
system, electronic flight instrument system, and
weather radar antenna with pitch and roll information.
The directional gyros, with the flux valve and
referenced heading information for use by the digital
flight control computer and electronic flight instrument
3A-16. AIR DATA SYSTEM.
microprocessor-based digital computers that accept
both analog and digital inputs, perform digital
computations, and supply both digital and analog
outputs. They receive both pitot and static pressure
for computing standard air data functions. They
control autopilot gains as a function of altitude and
airspeed. They contain sensors for the flight director
airspeed/altitude pre-select, and true airspeed for the
flight management system. They also include the
sensor function for the altitude portion of the altitude
and vertical speed indicator. The altitude encoder for
the mode C function of the transponder is also in the
air data computer.
a. Description. The electronic flight instrument
system consists of the pilot's and copilot's EADI and
EHSI display units, symbol generators, and EFIS
The EFIS electronic displays present pitch and
roll attitude, heading, course orientation, flight path
commands, radio altitude, weather radar and lightning
sensor system presentations, and mode and source
annunciations. The displays are color coded as shown
in Table 3A-2 for easier interpretation of information.