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actuator control valve through push-pull rods, bellcranks and cables. The
control valve then shifts to direct pressure to the flight spoiler actuator. The
normally-extended actuator retracts and the flight spoiler panels follow
aileron movement to assist roll control. The flight spoiler panels on the
opposite wing remain retracted.
F. Roll Trim System:
(See Figure 14 and Figure 15.)
Trim control about the longitudinal axis is controlled by displacing a trim tab
attached to the trailing edge of the left aileron. This is accomplished
through the use of an aileron trim control wheel mounted on the upper aft
end of the center pedestal.
Rotation of the aileron trim control wheel left or right rotates a cable drum
through the use of a torque tube. As the drum rotates, cables transmit the
movement to the aileron trim actuator. Mechanical linkage attached to the
actuator causes the trailing edge of the aileron trim tab to be raised or
lowered.
Movement of the aileron trim control wheel also drives an incorporated
pointer that indicates the units of Left Wing Down (LWD) or Right Wing
Down (RWD) trim from neutral. Total trim wheel travel is approximately 4½
turns from stop to stop. This yields a maximum of 8 units (13 ±1°) of trim
tab deflection from either side of the neutral position.
OPERATING MANUAL
2A-27-00 PRODUCTION AIRCRAFT SYSTEMS
Page 44
October 11/02
Revision 8
If an attempt is made to force the aileron trim control wheel past its
mechanical stops, a shear pin breaks to disconnect the control wheel from
the torque tube, disabling roll trim.
G. Failure Detection System:
CAA Certified Aircraft Only: A flight control automatic failure detection
system monitors force applied to the aileron input / manual reversion rod,
providing detection of a jammed or malfunctioning aileron actuator. If the
system detects a failure, it automatically shuts off all hydraulic pressure to
that actuator (the opposite actuator remains unaffected) and triggers the
appropriate warning on the Crew Alerting System (CAS).
With the roll flight control system operating normally, forces on the aileron
input / manual reversion rod remain relatively low because there is no lag
between control wheel input and actuator output. If an actuator
malfunctions resulting in an aileron hardover action, force levels on the rod
increase significantly. When this force exceeds 150 pounds, a force-link
limit switch closes to energize an associated time delay relay.
Similarly, a jammed actuator results in increased control inputs being
applied by the flight crew. If these control inputs exceed approximately 20
pounds, the force-link limit switch closes to energize an associated time
delay relay.
If the time delay relay remains energized for more than ½ second, it
energizes a shutoff relay. The shutoff relay, in turn, powers the actuator’s
Combined and Flight hydraulic system shutoff valves to the closed position.
Closing of the shutoff valves also causes an amber L-R AIL HYD OFF
message to be displayed on CAS.
3. Controls and Indications:
(See Figure 14.)
A. Circuit Breakers (CBs):
Circuit Breaker Name: CB Panel: Location: Power Source:
L AIL HYD S/O (1) CPO A-14 Essential DC Bus
R AIL HYD S/O (1) CPO B-14 Essential DC Bus
NOTE(S):
(1) CAA certified aircraft only.
B. Caution (Amber) Messages and Annunciations:
CAS Message: Cause or Meaning:
L AIL HYD OFF (1) The flight control automatic failure detection system has
shut off Combined and Flight hydraulic system pressure to
the left aileron actuator.
R AIL HYD OFF (1) The flight control automatic failure detection system has
shut off Combined and Flight hydraulic system pressure to
the right aileron actuator.
RETRIM L-R WING
DOWN
Lateral axis out of trim.
NOTE(S):
(1) CAA certified aircraft only.
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-27-00
Page 45
October 11/02
Revision 8
4. Limitations:
There are no limitations established for the roll flight control system at the time of
this revision.
OPERATING MANUAL
2A-27-00 PRODUCTION AIRCRAFT SYSTEMS
Page 46
October 11/02
Revision 8
Roll Flight Control System
Simplified Block Diagram
Figure 15
OPERATING MANUAL
2A-27-00
Page 47 / 48
October 11/02
2A-27-50: Horizontal Stabilizer System
1. General Description:
A movable horizontal stabilizer provides automatic longitudinal trim assistance to
compensate for the nose pitchdown moment (tuck-in) associated with flap
extension. Stabilizer position (leading edge angle of incidence) is a direct function
　
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