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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
movement.
CITATION MUSTANG OPERATING MANUAL
DRAFT
15-10 510OM-00
CITATION MUSTANG OPERATING MANUAL
FLAP CONTROL
SWITCHES
FLAP MONITOR
SWITCHES
FLAP
DRIVE SHAFT
FLAP
ACTUATOR
(MECHANICAL)
MECHANICAL
INTERCONNECT
CABLE
FLAP POWER
DRIVE UNIT
(PDU)
FLAP
ACTUATOR
(MECHANICAL)
Figure 15-9. Flap System Schematic
LEGEND
ELECTRICAL
CONTROL
Figure 15-8. Flaps—LAND Position
510OM-00 15-11
CITATION MUSTANG OPERATING MANUAL
When the pilot moves the flap handle from one
position to another, the flap controller senses
the disagreement between the flap handle position
and the flap panel position, and energizes
the PDU to move the flap panels until the signals
are brought back into agreement. If the
flap controller detects a fault, it immediately
stops the PDU and goes into idle mode and the
amber FLAPS FAIL message appears.
Flap panel position is monitored by a flap
monitor circuit and is graphically depicted in
the cockpit on the EICAS display, usually on
the multifunction display (MFD) (Figure 15-
10). To generate the analog flap position indication,
the flap monitor evaluates:
• Command signals from the flap handle
• Position signals from the right interconnect
pulley
• A monopole signal from the PDU
If the flap monitor loses all flap-position inputs
(i.e., TO/APR and LAND positions), it replaces
the EICAS flap position display with
a red “X.”
In reversionary mode, only text appears on
the EICAS to indicate flap position (Figure 15-
11). Three positions are identified:
• UP (fully retracted)
• TO/APR (takeoff/approach)
• LAND (landing)
In emergency power mode, flap information
is not shown on the EICAS, because the flap
monitor circuit is not powered.
The flap system is DC-powered three ways:
• The flap drive motor is powered from the
left feed bus No. 2, through a current limiter
in the aft J-box, to the flap system
printed circuit board (PCB).
• The flap control is powered from the left
feed bus No. 2, through the FLAP CONTROL
circuit breaker in the aft J-box.
　
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