B737 Flight Controls

How many flight spoilers are located on the upper surface of each wing?. Two. Three. Four. Six.

In the event of a control column jam, an override mechanism allows: the control columns to be physically separated. either crew member to apply force against the jam to breakout the Captain's control column only. the elevator feel and centering unit to transfer proper aerodynamic forces to the control columns. for lighter than normal forces to be used on the control column for takeoff or landing.

Autopilot trim and manual stabilizer trim use separate motors. True. False.

Main electric trim authority limit is: with flaps retracted 3.95 to 14.5 units. with flaps retracted 3.95 to 12.5 units. with flaps extended 0.20 to 16.9 units. with flaps extended 0.50 to 14.5 units.

Conditions for speed trim operation include. the autopilot not engaged. ten seconds after release of trim switches. 100 KIAS - Mach 0.50. Both A and C are correct.

With the loss of hydraulic system B, (system A operating normally): main yaw damper functions are available as long as hydraulic system A is providing normal pressure and the yaw damper switch is ON. standby yaw damper functions are available as long as hydraulic system A is providing normal pressure and the yaw damper switch is ON. main and standby yaw damper functions are inoperative. standby yaw damper functions are available if the FLT CONTROL B switch is placed to STBY RUD and the YAW DAMPER switch is reset to ON.

When the standby yaw damper is active, rudder movements are indicated on the yaw damper indicator. True. False.

Yaw damper inputs (main or standby) can be overriden. only when the yaw damper switch is OFF. by trim inputs but not rudder pedal inputs. by rudder pedal inputs but not trim inputs. by either trim or rudder pedal inputs.

The number of ground spoilers on each wing is. Two. Three. Four. Six.

If wheel spin up is not detected on landing with the speed brake armed, the night spoilers will deploy automatically: Only when the right main landing gear strut is compressed. When the air/ground system senses the ground mode (when any strut compresses). When the ground spoilers deploy. Flight spoilers do not deploy on landing, only ground spoilers deploy.

The number of slats located on each wing is: 2. 4. 3. 6.

The trailing edge devices consist of double slotted flaps inboard and outboard of each engine. True. False.

The flap load relief system is operational at: all flap settings. flaps 15,30 and 40. flaps 30 and 40. flaps 40 only.

The flap/slat electronics unit (FSEU) provides. LE skew detection for slats 2 through 7 except during autoslat operation.B. TE asymmetry protection. uncommanded motion protection for LE devices or TE flaps. All of the above are correct.

The trailing edge flaps are at 15 units. The correct indication on the aft overhead panel for the leading edge devices is: all amber TRANSIT lights illuminated. all LE devices FULL EXT lights illuminated. all LE devices EXT lights illuminated. LE slats EXT lights and LE flaps FULL EXT lights illuminated.

During descent from altitude, you need to decrease your airspeed by using your speed brakes. What is the correct position for the SPEED BRAKE LEVER?. ARMED. FLIGHT DETENT. UP. Any intermediate position.

What is the maximum flap extension altitude?. 10,000 feet. 17,000 feet. 20,000 feet. 23,000 feet.

The ALTERNATE FLAPS master switch: Fully extends the LE devices using standby hydraulic pressure, and electrically extends the TE flaps. Closes the flight spoiler shutoff valve. Activates the standby hydraulic pump and pressurizes the standby rudder power control unit. Arms the ALTERNATE FLAPS position switch, activates the standby hydraulic pump, and closes the trailing edge flaps bypass valve.

An alternate retraction system is provided for the LE devices. True. False.

The amber LE FLAPS TRANSIT light. Indicates all LE devices are fully extended. Indicates LE slats are fully extended. Is inhibited during autoslat operation in flight. Provides TE flaps asymmetry protection.

The autoslat system: Provides for slap deployment above Vmo/Mmo. Drives the slats to the full extended position when the TE flaps are at positions 1,2 or 5 and the airplane approaches a stall. Is normally powered by hydraulic system A. Is normally powered by the Power Transfer Unit (PTU.

The Power Transfer Unit (PTU) provides an alternate source of power for the autoslat system if. a loss of hydraulic system A pressure is sensed. the hydraulic system A engine-driven pump is inoperative. the alternate flaps position switch is momentarily held down. pressure from the hydraulic system B engine-driven pump drops below limits.

In addition to hydraulic system A and B, the rudder can also be powered the standby hydraulic system through the. System A standby rudder power control unit. System B standby rudder power control unit. Standby rudder power control unit. Main rudder power control unit.

Elevator system feel is provided by the elevator feel computer. This computer receives inputs of. altitude and elevator position. elevator balance tabs position. only system A hydraulic pressure. airspeed and stabilizer position.

The amber FEEL DIFF PRESS light illuminates when the: TE flaps are up or down and an excessive differential pressure exists in the elevator feel computer. flaps are not up and a hydraulic pressure imbalance is detected or one of the elevators feel pitot systems fails. flaps are up or down and a hydraulic pressure imbalance is detected or if one of the elevator pitot systems fails. There are no correct answers.

Select the correct statement. The primary flight controls are powered by hydraulic systems A and B, with backup form the standby hydraulic system for the rudder and manual reversion for the ailerons and elevator. Flight spoilers are used both for roll control, descent and deceleration. The trailing edge flaps can be both extended and retracted using the alternate flap drive system. All statements are correct.

Loss of hydraulic system B pressure does not disengage the yaw damper switch. True. False.