Flight Controls Flashcards
On the ground above 60kts groundspeed, the flight control system attempts to maintain a yaw rate near zero by applying rudder input. This function is only available in ____.
A. The NORMAL flight control mode.
B. The NORMAL and SECONDARY flight control modes.
C. The SECONDARY and DIRECT flight control modes
D. All modes.
A. The NORMAL flight control mode.
With a complete loss of flight control signaling, the ______ must be used to move the stabilizer.
A. Captains control wheel.
B. Autopilot.
C. Alternate pitch trim switches.
D. Vertical speed mode.
C. Alternate pitch trim switches.
The flaps and slats are both driven:
A. Hydraulically in all modes.
B. Electrically in all modes.
C. Electrically in the PRIMARY mode only.
D. Hydraulically in the PRIMARY mode only.
D. Hydraulically in the PRIMARY mode only.
With the flaps and slats in the SECONDARY mode, if airspeed exceeds 225 knots for the 787-8 or 240 knots for the 787-9/10 with the slats fully extended, they retract to the _____ position.
A. Retracted.
B. 5 degree.
C. Middle.
D. Slat load relief not available in secondary mode.
C. Middle.
When are all spoiler panels extend automatically?
A. When armed, upon landing, when the main gear trucks un-tilt and both thrust levers are not in the takeoff range.
B. When not armed, on the ground, with groundspeed above 85 knots, and either thrust lever was previously in the takeoff range, and both thrust levers are then moved to idle.
C. When not armed, on the ground, when both thrust levers are moved to the the reverse idle detent.
D. All of the above are correct.
D. All of the above are correct.
Which of the following is true when the flight control system is operating in secondary mode?
A. Autopilots and envelope protections are not available.
B. Envelope protection is available.
C. The ACE’s are not available.
D. The PFCs are not available.
A. Autopilots and envelope protections are not available.
With flight controls operating in the direct mode, which of the following components of the primary flight control system are inoperative?
A. Actuator control electronics (ACEs).
B. Electro hydraulic servos.
C. All components are operating.
D. Primary flight computer (PFCs).
D. Primary flight computer (PFCs).
The primary flight control system provides flight envelope protection in which mode(s)?
A. Normal Mode.
B. Secondary Mode.
C. Direct Mode.
D. All of the above are correct.
A. Normal Mode.
The autopilot sends signals:
A. Directly to the ACEs.
B. Directly to the PFCs.
C. To the backdrive actuators.
D. Answers B and C are correct.
D. Answers B and C are correct.
The autopilot is available in:
A. NORMAL and SECONDARY flight control modes.
B. ALTERNATE flight control mode.
C. Only if normal stab trim is available.
D. NORMAL flight control mode only.
D. NORMAL flight control mode only.
When the flaps and slats are in the PRIMARY mode, uncommanded motion will:
A. Cause the flaps or slats to transfer to the SECONDARY mode.
B. Cause the flap or slat system to transfer to the ALTERNATE mode.”
C. If the uncommanded motion continues in the Secondary mode, the respective system shuts down.
D. Both A and C are correct.
D. Both A and C are correct.
When operating B787-9/10 with the slats in the SECONDARY mode and positioned to the fully extended position, if the airspeed exceeds 240 knots:
A. The slats will transfer to the ALTERNATE mode.
B. LOAD RELIEF will be displayed on the EICAS.
C. The slats will retract to the middle position.
D. Both B and C.
D. Both B and C.
In the Normal mode, primary flight control computers (PFC’s) _______.
A. Monitors and provides envelope protection during manual flight.
B. When protecting the flight envelope, reduces pilot authority.
C. With the auto-pilot operating does not need to protect the flight envelope.
D. Both A and B are correct.
A. Monitors and provides envelope protection during manual flight.
The flaps and slats in the SECONDARY mode are _______.
A. Both controlled by the Flap handle.
B. Operated separately, either by hydraulic or electric motors, depending the failure.
C. Operated by the alternate flap switch.
D. Both A and B are correct.
D. Both A and B are correct.
How can the pilot place the aircraft into the SECONDARY flight control mode?
A. Disconnect the PFCs.
B. Disconnect the autopilt using the Autopilot Disengage Bar on the MCP.
C. You cannot, SECONDARY selection occurs automatically.
D. Both A and B are correct.
C. You cannot, SECONDARY selection occurs automatically.
In the NORMAL flight control mode, yaw control attempts to maintain zero yaw rate due to engine failure when above _______.
A. V1
B. 60kts groundspeed and aircraft on the ground.
C. 150kts IAS, with a thrust differential greater than 10%.
D. E/O acceleration height.
B. 60kts groundspeed and aircraft on the ground.
Disconnecting the primary flight control computers (PFC’s), places the aircraft _____.
A. In the SECONDARY mode.
B. In the ALTERNATE mode.
C. In the DIRECT mode.
D. Out of control.”
C. In the DIRECT mode.
Wheel to rudder cross-tie is available in which mode(s)?
A. Secondary.
B. All modes.
C. Direct.
D. A and C.
D. A and C.
The three modes of the Primary Flight Control System are:
A. NORMAL, SECONDARY, DIRECT.
B. PRIMARY, SECONDARY, ALTERNATE.
C. NORMAL, SECONDARY, STANDBY.
D. There are only two modes of operation for the Primary Flight Control System.
A. NORMAL, SECONDARY, DIRECT.
With a total hydraulic failure, Pitch and Roll control is still available:
A. Requires hydraulic accumulator pressure.
B. Cable connected trim tabs on the elevator and ailerons
C. Electrically using the control wheel and either primary or alternate pitch trim.
D. Hydraulic pressure is ALWAYS required.
C. Electrically using the control wheel and either primary or alternate pitch trim.
After landing, the flight control system automatically self tests:
A. When the center hydraulic system is pressurized.
B. During engine shutdown, before external power can be connected.
C. With flaps and speedbrakes retracted and groundspeed less than 30kts
D. When the PFCs are disconnected.
C. With flaps and speedbrakes retracted and groundspeed less than 30kts
Why is the B787 provided with an electrical flight control backup system?
A. In case of a dual engine failure.
B. In case of a complete hydraulic loss.
C. In case both FMC’s are lost.
D. A and C.
B. In case of a complete hydraulic loss.