PITOT STATIC Flashcards
PITOT STATIC
The standby instruments use the ___ pitot static tube
input
The standby instruments use the ___ pitot static tube
input.
Co-pilot’s
PITOT STATIC
The standby instruments use their own static source
independent of the pilot’s and copilot’s static sources.
The standby instruments use their own static source
independent of the pilot’s and copilot’s static sources.
True
FLIGHT CONTROLS
How are the elevators and ailerons powered?
How are the elevators and ailerons powered?
Hydraulically
FLIGHT CONTROLS
If you press the yellow autopilot disconnect switch on
one of the control yokes, what will it disconnect?
If you press the yellow autopilot disconnect switch on
one of the control yokes, what will it disconnect?
Autopilot
Yaw damper, if the landing gear is down
FLIGHT CONTROLS
How do you disconnect the mechanical linkage between
the pilot and copilots yoke for pitch control?
How do you disconnect the mechanical linkage be-
tween the pilot and copilots yoke for pitch control?
By pulling the PITCH lever in the left side pedestal
FLIGHT CONTROLS
After the pitch lever has been pulled to disconnect the
mechanical linkage between each yoke, movement of
the pilot’s yoke will move the ___ elevator.
After the pitch lever has been pulled to disconnect the
mechanical linkage between each yoke, movement of
the pilot’s yoke will move the ___ elevator.
Left
FLIGHT CONTROLS
After you pull the Roll disconnect lever in the right side
pedesteal, the copilot’s yoke will control the ___ aileron.
After you pull the Roll disconnect lever in the right side
pedesteal, the copilot’s yoke will control the ___ aileron.
Right
FLIGHT CONTROLS
Can you disconnect the ailerons with a complete loss of
hydraulics?
Can you disconnect the ailerons with a complete loss of
hydraulics?
No
FLIGHT CONTROLS
How are the pilots rudder control inputs transferred to
the rudder?
How are the pilots rudder control inputs transferred to
the rudder?
Through bell cranks, push-pull rods, and torque
tubes
FLIGHT CONTROLS
The rudder bias system is actuated by the differential
bleed pressure during an asymmetric thrust condition.
The rudder bias system is actuated by the differential
bleed pressure during an asymmetric thrust condition.
True
FLIGHT CONTROLS
The yaw damper servo is mechanically connected to the
rudder system.
The yaw damper servo is mechanically connected to the
rudder system.
True
FLIGHT CONTROLS
The autopilot servo is mechanically connected to the
elevator control servo.
The autopilot servo is mechanically connected to the
elevator control servo.
True
