(c)
AIRPLANES WITH CONTROL WHEEL STEERING the captain's and first officer's control column/wheels provide the manual control cable input for pitch and roll control. They also drive autopilot force transducers and spoiler system transducers located under the flight compartment floor. The autopilot force transducers enable control wheel steering (CWS) through the autopilot. The CWS inputs allow manual control of airplane pitch and roll with the autopilot engaged. The spoiler system transducers assist in roll control of the airplane.
(d)
The outboard horn of each control wheel has an autopilot disengage switch, stabilizer trim switch, and switch for communication systems. An aileron trim indicator is on the top of each control wheel hub.
(e)
The captain's and first officer's rudder pedals provide the manual cable input for yaw control. The autopilot and yaw damper systems also provide yaw control inputs.
(f)
The aft section of the control stand (P8) contains aileron and rudder trim switches, and a rudder trim position indicator.
(2) Secondary Flight Control Inputs
(a)
The stabilizer trim switches (thumb operated) on each control wheel provide an electrical input to drive the stabilizer up and down.
(b)
The center section of the control stand (quadrant stand - P10) incorporates the following items: 1) Stabilizer trim manual trim levers (or alternate stab trim
switches) on the left side for manual trimming of the
stabilizer. 2) Stabilizer trim position indicators on each side. 3) Stabilizer trim hydraulic power CUTOUT switches (right and
center hydraulic systems) on the left side. 4) Speedbrake control lever on the left side for manually extending the speedbrakes. 5) Flap/slat control lever on the right side for manually extending the flaps and slats.
M. Flight Deck Control Panels (Fig. 12)
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MAINTENANCE MANUAL
ALTERNATE FLAP CONTROL (P3-1)
AFDS MODE CONTROL PANEL - M90 (P55) (EXAMPLE)
Flight Deck Control Panels
Figure 12
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C98112
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MAINTENANCE MANUAL
(1)
Annunciator Lights Panel
(a) Six amber annunciators indicate faulty operation of various flight control systems. The annunciator lights panel is on P5.
(2)
Yaw Damper Panel
(a) The two independent yaw damper systems are controlled by individual push-on/push-off switch/lights. The yaw damper is engaged when the switch translucent ON legend illuminates white. The lower part of the switch/light illuminates amber INOP for a yaw damper failure. A YAW DMPR test switch on the test panel on P61 enables ground testing for the yaw damper system.
(3)
Alternate Flaps Control Panel
(a) Two push-on/push-off switch/lights arm individual electrical control of leading edge slats and trailing edge flaps. The degree of extension of the flaps/slats is controlled with an 8-position rotary switch. The switch is left in NORM for normal hydraulic control of the flaps and slats.
(4)
Autopilot Mode Control Panel
(a) The autopilot mode control panel enables autopilot control of the primary flight control surfaces in various selected modes. Thrust management system arming and mode selection switches are on the left side of the panel. Captain's and first officer's flight director on-off switches at each end of the panel cause flight director commands to be displayed on the electronic attitude director indicators (EADIs).
N. Flight Deck Flight Control Indicators (Fig. 13)
(1) Trim Indicators
(a) Two stabilizer trim indicators are installed, one on each side of the quadrant section of the control stand (P10). The indicators have a green band and units of stabilizer position. The green band indicates the safe takeoff stabilizer position range. The units indicate relative stabilizer position for airplane nose-up and nose-down. The indicators are driven by position transmitters at the stabilizer.
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