CAE SimuFlite Citation Bravo, Pilot Training Manual

Page: 529 / 718

Flight Controls
Citation Bravo
Developed for Training Purposes
5E-7
September 2005
Electric Pitch Trim
System
An electric trim motor permits actu-
ation of the elevator trim tab through
the following:
n
a trim switch on the left grip of the
pilot’s control wheel (
Figure 5E-6
)
n
a copilot’s trim switch on the right
side of the copilot’s control wheel.
Trim override is provided by the
manual trim system or it can be
momentarily disabled by pressing
the AP/TRIM DISC switch on the
pilot’s or copilot’s yoke.
The electric motor on the trim
assembly engages whenever activa-
tion of one or more of the above
occurs.
The pilot’s trim switch interrupts and
overrides the copilot’s switch. Split
trim switches for both the pilot and
copilot provide electrical control of
the pitch trim motor (
Figure 5E-7
).
The motor drives the sector in the
appropriate direction with a chain
drive that moves the elevator trim
cables; this rotates the actuator
screws that adjust the trim tab. The
Left Main Extension bus supplies
electrical power for the motor.
A/P Trim Disconnect
The AP/TRIM DISC switch on the
pilot’s and copilot’s yoke electrically
disables the electric trim if a mal-
function in electric trim should
occur. Pulling the 5 amp PITCH
TRIM CB on the left circuit breaker
panel removes power from the elec-
tric trim motor.
Rudder
The rudder (
Figure 5E-8
) on the
trailing edge of the vertical stabilizer
provides effective yaw control of the
aircraft at all flight speeds. The rud-
der is actuated mechanically by
moving the rudder pedals or elec-
tronically by the autopilot servo. A
direct connect cable system from
both sets of rudder pedals to the tail
section drives the aircraft rudder.
Full range of motion is 22 ± 1° either
left or right of center. Torque tube
and bridge assemblies connect the
pilot’s and copilot’s rudder pedal
sets together. The connection pro-
vides corresponding rudder pedal
movement between the sets.
Depressing the rudder pedals trans-
mits directional information through
fuselage cable assemblies to the rud-
der bellcrank. The torque tube trans-
mits rudder bellcrank movement
information to deflect the rudder.
5E-6
5E-7
5E-8