7-3-5
Trim
The aileron, horizontal stabilizer and rudder trim are electrically operated. Aileron and
horizontal stabilizer trim operation is controlled by a switch on the outboard yoke of each
control wheel, rudder trim operation is controlled by a switch on the Engine Power Control
Lever. Before selecting pitch or aileron trim, press and hold the trim engage switch located on
the forward side of each outboard control wheel yoke. A display for aileron, horizontal stabilizer
and rudder trim position is shown on the systems Multi-Function Display (MFD).
Pitch trim is accomplished by an electrically controlled actuator connected to the moveable
horizontal stabilizer. The actuator has two separate motors: a manual stabilizer trim motor
(controlled by the manual trim switches) and an alternate stabilizer trim motor (controlled by
the autopilot). The alternate stabilizer trim motor can also be used as a back-up system by the
pilot. To activate alternate Stabilizer trim, press the ALTERNATE STAB TRIM switch on the
center console to NOSE UP or NOSE DOWN as needed.
The leading edge of the horizontal stabilizer moves down for nose-up trim and moves up for
nose-down trim. At the root of the left horizontal stabilizer leading edge are trim range indicator
markings to show full travel in either direction and the takeoff trim range. As part of the pre-
flight inspection these trim indicator markings should be used to verify the cockpit trim position
indication.
If there is uncommanded trim operation, all trim operation (manual and auto trim) can be
stopped by lifting the switch guard and pressing the TRIM INTR switch located in front of the
Engine Control quadrant on the center console.
7-3-6
Flaps
Each wing trailing edge has a single piece Fowler type flap supported by three flap arms. The
flaps are controlled by a selector handle located to the right of the power controls on the center
console. The flaps may be set to one of the four preset positions 0°, 15°, 30° and 40° by
moving the handle to the appropriate position. If the flap lever is not at one of the four preset
positions, the Flap Control and Warning Unit (FCWU) will drive the flaps to the nearest preset
position.
The flaps are electrically actuated. There is a single flap Power Drive Unit (PDU) installed
below the cabin floor at the rear main frame. It drives screw actuators at the inboard and
middle stations through flexible shafts. The screw actuators are connected to the flap actuating
arms.
The flap control system incorporates a failure detection system. The system can detect a
failure of a flexible shaft by disconnection or jamming, potentially resulting in flap asymmetry or
failure of the system to achieve the selected flap position. The system can detect a failure of a
single actuator, potentially resulting in single flap panel twisting. If a failure is detected, the
FCWU disconnects the power to the PDU and the Crew Alerting System (CAS) window will
show
Flaps
. This condition cannot be reset by pilot action, a landing should be made, refer
to Section 3, Emergency Procedures,
Section 7 - Airplane and Systems Description
Trim
Pilot's Operating Handbook
Report No: 02406
Issue date: Mar 06, 2020
Page 7-3-2
12-C-A15-00-0703-00A-043A-A
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GENERAL
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