Boeing 737-700 and 737-800 Systems and Limitations Review

Comprehensive question-and-answer practice flashcards based on Boeing 737-700/800 lecture notes covering general dimensions, limitations, APU, engines, flight controls, landing gear, brakes, hydraulics, and pressurization.

What are the wing span, length, and height dimensions of the Boeing 737-800?

Wing span: 35.79m, Length: 39.50m, Height: 12.50m.

What is the minimum width required to perform a 180-degree turn in a Boeing 737-800 versus a 737-700?

Boeing 737-800 requires 24.3m; Boeing 737-700 requires 20.4m.

How does the Fasten Seatbelts sign operate when set to AUTO?

It illuminates automatically when flaps or landing gear are extended, and extinguishes when they are retracted.

What is the required flight crew oxygen pressure indicator reading?

1850 psi.

At what cabin altitude do passenger oxygen masks drop automatically when set to NORM?

14000 ft cabin altitude.

On what frequencies does the ELT transmit its tone and position?

121.5 MHz, 243.0 MHz, and 406.0 MHz.

What are the takeoff and landing tailwind limitations for the 737-700 and 737-800?

737-700: 10 kts tailwind; 737-800: 15 kts tailwind.

What are the maximum operating altitude and maximum takeoff/landing altitude for the 737 aircraft?

Maximum operating altitude: 41000 ft; Maximum takeoff/landing altitude: 8400 ft.

What three conditions must be met for the overwing exits to unlock?

Aircraft is on the ground, at least one door is open, and thrust levers are not fully advanced.

Which component monitors, controls, protects, and handles shutdowns for the APU?

The Electronic Control Unit (ECU).

Where is APU fuel drawn from when AC fuel pumps are operating versus when they are not operating?

When operating: from the left side fuel manifold. When not operating: from the N°1 tank.

What four automatic actions take place when the APU is shut down?

The generator stops, the bleed air valve closes, the fuel valve closes, and the air inlet closes.

What specific fuel imbalance rate indicates a fuel leak?

A fuel imbalance of 230 kg in 30 minutes.

On the ground with engines OFF, when do the APU fire extinguishers automatically discharge after fire detection?

10 seconds after fire detection.

What procedure must be followed if the WHEEL WELL FIRE light illuminates?

Reduce speed and lower gears. If the gear must be retracted, wait a minimum of 20 minutes after the WHEEL WELL FIRE light has extinguished.

What engine model powers the 737NG, and what is its thrust rating?

CFM56-7, dual rotor, axial flow engine producing 27300 pounds of thrust.

What action is required if the oil filter bypass light illuminates?

Retard the thrust lever. If the light extinguishes, operate the engine at low power; if the light stays illuminated, shut down the engine.

How can primary flight controls be operated if both Hydraulic Systems A and B are lost?

Ailerons and elevator can be manually operated via control cables, and the rudder is powered by a standby hydraulic system.

What does the illumination of the 'FEEL DIFF PRESS' light signify?

Excessive differential hydraulic pressure in the Elevator Feel Computer.

Above what airspeed is full rudder authority limited, and by how much is hydraulic pressure reduced?

Above 135 kts, full rudder authority is limited by reducing hydraulic pressure by 25%.

What happens if the main Yaw Damper switch moves to OFF during normal operations versus when the standby hydraulic system takes over?

If moved to OFF normally, it cannot be reset to ON. If the standby hydraulic system takes over, the switch resets to ON and the standby hydraulic system powers the standby yaw damper.

What is the maximum altitude limit for extending flaps?

20000 ft.

What is the flap protection response on the Boeing 737-800 if speed exceeds 163 kts at Flaps 40?

Flaps will retract to Flaps 30, and re-extension to Flaps 40 will occur once speed drops below 158 kts.

How does selecting ENG ANTI ICE to ON affect the aircraft systems?

It changes the stick shaker logic for icing conditions and changes airspeed logic (switching it OFF returns logic back to normal).

How does selecting WINGS ANTI ICE to ON differ from ENG ANTI ICE regarding stick shaker logic?

Turning WINGS ANTI ICE ON changes stick shaker logic (without changing airspeed logic), but switching the button back OFF will NOT restore stick shaker logic to normal.

Which hydraulic systems power the normal brakes and alternate brakes?

Normal brakes are powered by Hydraulic System B; Alternate brakes are powered by Hydraulic System A.

What operational limitations apply when the Antiskid system is inoperative?

No reduced takeoff thrust (assumed temperature) can be used, Autobrake is unavailable, and speedbrakes must be manually deployed (cannot be armed).

Under what conditions will RTO (Rejected Takeoff) braking initiate?

RTO braking will start if the aircraft wheel speed is above 90 kts when the forward thrust levers are positioned to IDLE on the ground.

What primary systems are powered by Hydraulic System A?

Ailerons, Rudder, Elevator, Flight & Ground Spoilers, Alternate Brakes, N°1 Thrust Reverser, Autopilot A, Normal Nose Wheel Steering, and PTU.

What primary systems are powered by Hydraulic System B?

Ailerons, Rudder, Elevator, Flight Spoilers only, Leading Edge Flaps & Slats, Trailing Edge Flaps, Normal Brakes, N°2 Thrust Reverser, Autopilot B, Alternate Nose Wheel Steering, Landing Gear Transfer Unit, Autoslats, and Yaw Damper.

What occurs to the flight controls and system components if both Hydraulic Systems A and B lose pressure?

Thrust reversers and leading edge flaps/slats receive standby hydraulic pressure, trailing edge flaps operate electrically, inboard & outboard brakes have accumulator pressure only, and manual landing gear extension is required.

Under what conditions will the Standby Hydraulic System operate automatically?

When System A or B FLT CONTROL switch is ON, the aircraft is airborne or wheel speed exceeds 60 kts, flaps are extended, and there is a loss of System A or B, OR if the main PCU Force Flight Monitor (FFM) trips.

What position must Hydraulic System A pumps be in during pushback without a nose gear steering lockout pin?

Hydraulic System A pumps (ENG 1 and ELEC 2) must be OFF.

What cabin altitude is maintained when the aircraft is cruising at 41000 ft?

8000 ft.

What is the maximum differential pressure limit enforced by the positive pressure relief valves?

9.1 psi.