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panel. It operates only if the AVN PWR switch
is set to the up position. The AVN PWR switch
is on the AVIONICS switch panel, below the
pilot PFD.
Manual Trim
By rotating the trim wheel forward toward the
nose-down position, the trim tabs rotate upward,
causing the elevator system to pitch the
nose of the aircraft down. By rotating the trim
wheel aft, the opposite is true.
TRIM
AILERON
RUDDER
Figure 15-6. Trim Display
Elevator trim position is indicated by a mechanical
pointer, which rides in a slot of the
LED-backlit panel of the throttle quadrant,
connected to the elevator trim cable loop.
Electric Trim
Electric elevator trim is controlled by a split-element
centering thumb switch on the outboard
side of each control yoke (see Figure 15-7).
When the pilot moves both elements of the
rocker switch, the electric elevator trim actuator
moves the cables to trim the aircraft in the
direction selected. Selecting forward trims nosedown.
The electric trim can be overridden by the
mechanical trim. Additionally, pilot pitch trim
inputs override the copilot trim inputs. As the
trim switch is moved to the UP or DOWN
DRAFT
15-8 510OM-00
CITATION MUSTANG OPERATING MANUAL
MANUAL TRIM
ELECTRIC TRIM
LEGEND
MECHANICAL
ELECTRICAL
Figure 15-7. Elevator Trim System
510OM-00 15-9
position, the elevator tabs are repositioned as
indicated by the elevator trim indicator.
Prior to flight, the electric pitch trim system
can be checked for proper operation by moving
both elements of the switch in both directions,
noting whether trim occurs in the
appropriate directions. Check for system malfunction
by attempting to trim with one element
of the switch. If trimming occurs, the
system is malfunctioning and must be restored
to normal operation prior to flight.
NOTE
If a pilot holds only one element of
the trim switch in either the UP or
DOWN position for more than 3 seconds,
the red PTRM message appears
on the upper left of the PFD.
Interrupt runaway or malfunctioning trim by
depressing the red AP/TRIM DISC switch on
the control yoke (see Figure 15-5) and pulling
the AFCS circuit breaker in the FLIGHT CONTROLS
section of the left CB panel.
NOTE
The autopilot will not engage if electric
trim is not operating properly.
FLAPS
Flaps on the wings provide control of lift and
drag. On the Citation Mustang, flaps increase
both lift and drag.
Components
The flap system consists of electrical and mechanical
components. The flap panels are on the
inboard trailing edge of each wing, one on either
side of the aircraft (Figure 15-8). They are
hinged for operation in three positions: UP (retracted),
TO/APR (takeoff/approach), and
LAND (landing).
Each flap panel is directly connected to a
mechanical actuator on the rear wing spar
(Figure 15-9). The two actuators are driven
through flexible drive shafts connected to a
common electric motor (electrically powered,
electronically controlled power drive unit).
The power drive unit (PDU) is behind the rear
wing spar at the aircraft centerline.
A mechanical interconnect system links the
two flap panels together at their inboard ends
via pushrods, pulleys, and cables (Figure 15-
9). This system ensures that even with linkage
failure, flap position remains synchronized,
preventing asymmetrical flap positions.
Controls and Indications
A flap handle is in the cockpit, to the right of
the throttle levers on the control pedestal (see
Figure 15-8).
The flap handle can be moved aft from the UP
detent and forward from the LAND detent.
The flap handle can be set in any of the three
detent positions:
• UP—On retraction, should not be selected
until TO/APR flap position is
achieved
• TO/APR
• LAND—On extension, may not be selected
until TO/APR flap position is
achieved
Three switches under the flap handle supply
command signals for the control and monitoring
circuits. The flap handle has a three-position
mechanical detent, which requires that the
handle be pushed down before it can be moved
forward or aft to a new position.
Flap panel movement is directly controlled
by a flap controller circuit that controls the flap
power drive unit (PDU). The flap controller
evaluates command signals from the flap handle
and position signals from the left interconnect
pulley to determine the appropriate
operation of the flap PDU to drive the flap
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Cessna塞斯纳公务机飞行手册(91)
