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CQ 2024 Limitations > Southwest Oral Exam Prep May 2022 > Flashcards

Southwest Oral Exam Prep May 2022 Flashcards

1
Q

What are the dimensions of the B737-700?

A

Width - 117’ 10”
W-gear - 18’ 8”
W- Elevator - 47’ 2”

Tail - Height - 41’ 2”
Wing - Height - 20’ 11”

Length - 110’ 4”

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2
Q

Exterior Lighting

A

Landing Runway, Turnoff and Taxi Lights.

ON or OFF

Retract - Retractable landing lights are retracted and extinguished
Extend - Retractable landing lights are extended and extinguished
ON - Retractable landing lights are extended and illuminated

Retractable landing light - lower fuselage, designed to extend and shine forward parallel to the waterline of the aircraft. V light - any speed
Fixed landing lights - two fixed landing lights are in the wing leading edge. Shine forward and down
Runway turnoff lights - wing root, illuminate area in front of main gear.
Taxi Light - Nose wheel strut, points same direction as nose wheel. Light extinguishes with nose wheel retraction
Logo Lights - Top of horizontal stabilizer, lights point at vertical stabilizer.
Position light - standard red (left forward), green (right forward)
Strobe Light - Three high intensity white strobe lights are installed on the left forward winglet, right forward winglet, and tail cone.
Anti-Collision Lights - two red-anti-collision strobe light located top and bottom of fuselage
Wing-Illumination Lights - illuminate leading edge of wing
Wheel Well Lights
Lights in the wheel well and nose gear of each main gear.

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3
Q

Miscellaneous Exterior Lighting

A

Logo, Position, Anti Collision, Wing, Wheel Well

ON or OFF

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4
Q

Emergency Lighting and Passenger Signs

A

Emergency Exit Lights Switch
OFF - Prevents emergency light operation during power failure, or is turned off.

Emergency Exit lights NOT in armed position.

No Smoking Switch
ON - low chime in cabin

Fasten Belts Switch
OFF - fasten belts, and return to seats sign NOT illuminated.
AUTO - respective signs are illuminated and extinguished automatically with reference to aircraft configuration.
ON - respective signs illuminated.

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5
Q

ELT

AFT overhead panel

A

ELT light
(amber) active transmitting tone on 121.5, 243.0, and 406.0

Emergency Locator Transmitter Switch
ARM - Guarded - transmits automatically when it reaches present G-Load limit.
ON - Manually activates the ELT.

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6
Q

Portable ELT

A

Forward Galley storage compartment.

  1. Transmitter
  2. Mounting bracket
  3. Float
  4. Auxiliary antenna
  5. Water Switch Sensor
  6. Visual Indicator (red)
  7. Three-Position Switch (ARM/OFF/ON)
  8. Tether ended by hook
  9. Velcro Strap.
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7
Q

Flight Deck Door and Flight Deck Emergency Access Panel

A

Flight Deck Door:
Dead bolt and dead bolt placard
Release Pins
Decompression panel

Flight Deck Emergency Access Panel
Illuminated (red) - Door locked or Flight Deck Access System Switch - OFF
Illuminated (amber) - Correct emergency access code entered
Illuminated (green) - Door Unlocked

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8
Q

Flight Deck Door Access System Switch

Flight Deck Door Lock Panel

A

Flight Deck Door Access System Switch -
OFF - Removes electric power from door lock.
NORM - configured for flight

Flight Deck Door Lock Panel
Lock/Fail Light
- Amber - Flight Deck Door selector in Auto and Door lock has failed or Flight Deck Access System switch is OFF.
Auto Unlock Light
- Amber Correct emergency access code entered in keypad. Auto UNLK Light flashes and continuous chime sounds before timer expires and door unlocks.
UNLKD - Door unlocked while selector in UNLKD
AUTO - Door locked - Allows door to unlock after entry of emergency access code, and timer expiration, unless crew action.
Deny - Rejects keypad entry request and prevents further emergency access code entry for a time period.

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9
Q

Oxygen Panel

Crew Oxygen / Passenger Oxygen

A

Crew Oxygen
O2 gauge,

Passenger Oxygen
Normal
ON

Pressure breathing at 27,000 ft. Single cylinder 1,850 psi

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10
Q

Bleed Air Controls - Forward overhead panel

A
  1. Dual Bleed Light - amber - APU bleed air valve open and engine No1 bleed air switch ON (OR) engine No2 bleed air switch ON APU bleed air valve and isolation valve open.
  2. Isolation valve switch
    close - closes isolation valve
    Auto -
    - closes isolation valve is both bleed air switches are on and both air conditioning pack switches are AUTO or HIGH.
    - Open isolation valve automatically if either engine Bleed air or air conditioning Pack switch positioned OFF.
    OPEN - Opens isolation valve.
  3. Wing-Body Overheat Light
    Amber
    - Left light overheat from bleed air duct in left engine strut, left inboard wing leading edge, left air conditioning bay, keel beam, or APU bleed air duct.
    - Right Light - indicated overheat from bleed air right engine strut, right inboard wing leading edge, right air conditioning bay.
  4. Engine Bleed Air Switches
    OFF - Closes engine bleed air valve
    ON - Opens engine bleed air valve when engines are operating.
  5. APU Bleed Air Switch
    OFF - Closes APU bleed air valve
    ON - Opens APU bleed air valve when APU is operating.
  6. Bleed Air duct pressure indicator
    Indicates pressure in L and R bleed air ducts
  7. Wing-Body Overheat Test (OVHT TEST) Switch.
    Push -
    Tests wing body overheat detector circuits
    Illuminates both wing-body overheat lights
  8. Bleed Trip OFF light.
    Amber - Excessive engine bleed air temperature or pressure
    Related engine bleed air valve closes automatically
    Requires reset.
  9. Pack Trip Off Light
    Pack temperature exceeded limits
    Related pack vale automatically closes and mix valves drive full cold
    Requires reset.
  10. Trip Reset Switch
    Push
    Resets Bleed Trip Off, Pack Trip Off, and Duct Overheat lights.
    Related engine bleed valve opens, related pack valve opens, or related air mix valve opens
    Lights remain illuminated until reset
  11. Gasped fan Switch
    Deactivated
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11
Q

Hydraulics Panel

A
  1. Electric Hydraulic Pump Overheat Lights
    Amber - Hydraulic fluid used to cool and to lubricate the corresponding electric motor driven pump has overheated or the pump itself has overheated
  2. Hydraulic Pump Low Pressure Lights
    Amber - Output pressure of associated pump is low.
    note: when an engine fire switch is pulled, the low pressure light is deactivated.
  3. Electric Hydraulic Pump Switches
    ON - Provides power to associated electric motor driven pump
    OFF - Electrical power removed from pump.
  4. Engine Hydraulic pumps switches
    ON - De-energizes blocking valve in pump to allow pump pressure to enter system.
    Note: Should remain ON at Shutdown to prolong solenoid life.
    OFF - energizes blocking valve to block pump output.
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12
Q

Hydraulic Indications

A
  1. MFD system switch
    Push SYS
    Displays hydraulic indications on lower DU; or the inboard DU if the main panel dusswitch is placed to the INBD MFD position.
    Second push removes indication from respective DU
  2. Hydraulic System Quantity indications (white)
    Indicates digital percentage (0 to 106%) of hydraulic quantity.
    Note: Quantity also displayed at each reservoir.
  3. Hydraulic System pressure indications (white)
    Indicates system pressure
    Normal pressure - 3000 psi
    Maximum pressure - 3000 psi
    Note: When both pumps for a system are OFF, the indication may read hydraulic system reservoir normally less than 100 psi.
  4. Refill (RF) indication (white)
    Illuminated (white) - below 76%
    Note: Valid only when aircraft is on ground with both engines shutdown or after landing with flaps up during taxi-in.
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13
Q

Flight Control Panel

A
  1. Flight Control Switches
    STBY RUD - Activates stand-by pump and opens standby rudder shutoff vale to pressurize standby rudder power control unit.
    OFF - Closes flight control shutoff valve isolating ailerons, elevators, and rudder from associated hydraulic system pressure.
    ON - guarded position - Normal operating position
  2. Flight Control low pressure lights
    Amber
    Indicates low hydraulic system (A or B) pressure to ailerons, elevator, and rudder
    Deactivated when associated flight control switch is positioned to STBY RUD and standby rudder shutoff valve opens
  3. Standby hydraulic low quantity Light
    Amber
    Indicates low quantity in standby hydraulic reservoir.
    Always armed
  4. Standby Hydraulic Low Pressure Light
    Amber
    Indicates output pressure of standby pump is low
    Armed only when standby pump operation has been selected or automatic standby function is activated.
  5. alternate Flaps Master Switch
    OFF (guarded position) Normal Operating position
    ARM Closes trailing edge flap bypass valve, activates standby pump, and arms alternate flaps position switch.
  6. STBY RUN ON Light
    Amber
    Indicates the stand by hydraulic system is commanded on to pressurize the standby rudder power control unit.
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14
Q

System indicators

A 
Three hydraulic systems, A, B and standby. The standby system is used if A, and or B pressure is lost. Hydraulic systems power the following aircraft systems.
Flight controls
Leading edge flaps and slats
Trailing edge flaps
Landing gear
Wheel brakes
Nose wheel steering 
Thrust Reversers 
Autopilots

A or B can power all flight controls with no decrease in aircraft controllability
Reservoir for each system in main wheel area, pressurized by bleed air.
Standby reservoir connected to B reservoir for pressurization and servicing.
Pressurization ensures positive fluid flow to all hydraulic pumps.

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15
Q

Hydraulic Power Distribution

A 
A
Ailerons
Rudder
Elevator and elevator feel
Flight spoilers (two on each wing)
Ground spoilers
Alternate Brakes
No 1 thrust reverser
Autopilot A
Normal nose wheel steering
Landing gear
PTU power transfer unit. 
B
Ailerons
Rudder
Elevator and elevator feel
Flight Spoilers (two on each wing)
Leading edge flaps and slats
Normal Brakes 
No 2 Thrust reverser
Autopilot B
Alternate nose wheel steering
Landing gear transfer unit
Auto slats
Yaw Damper
Trailing edge flaps.

A and B have engine driven pump and AC electric motor driven pump. A pump powered by NO 1 engine. B pump powered by NO 2 engine. Engine driven pump provides 6 times fluid volume of the electric motor driven pump.

Engine 1 Sys A or Engine 2 sys B ON/OFF switch controls the engine driven pump output pressure.
OFF - isolates fluid flow from components.
Pulling engine fire switch shuts off flow to engine driven pump and deactivates related low pressure light.

Elec 2 sys A or Elec 1 sys B ON/OFF switch controls the related electric motor driven pump. If overheat is detected overheat light illuminates, power is removed from the pump. And the - low pressure light illuminates. The related OVERHEAT illuminates.

Loss of engine driven pump and a high demand on the system may result in intermittent illumination of the low pressure light for the remaining electric motor driven pump.
Flight control low pressure light, master caution light and the flight cont and hg system annunciation light also illuminate.

Below 1,675 electric motor driven pump EMDP Overheat light may illuminate.

Pressure switches and signals to illuminate the related low pressure light if pump output pressure is low. Check valve in the output line isolates the related pump from the system. The related system send the combined pressure of the engine driven and electric motor driven pump to the related hydraulic stem pressure indication.

A leak
Standpipe in the reservoir prevents total loss of system fluid. 20% of full and A is maintained by electric motor driven pump.
If leak in lines servicing electric motor all system pressure is lost

B leak
Fluid in standpipe is sufficient for power transfer unit operation.

Leak in B does not affect operation of standby hydraulic system.

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16
Q

Power Transfer Unit

A

Purpose to supply addition volume of hydraulic fluid needed to operate auto slats and leading edge flaps and slates at the normal rate when system B engine driven pump volume is inoperative.

PTU uses A pressure to power hydraulic motor-driven pump, which pressurizes B hydraulic fluid. PTU operates automatically when all of the following conditions exist.
B engine driven pump hydraulic pressure drops below limits
Airborne
Flaps less than 15 but not up.
737-800
Flaps not up

17
Q

Landing Gear Transfer Unit

A

Purpose is to supply volume of hydraulic fluid needed to raise landing gear at normal rate when A engine driven pump volume is lost. B supplies the fluid needed to operate landing gear transfer unit.

Airborne
No 1 engine RPM drops below a limit value
Landing gear level is positioned up
Either main landing gear is not up and locked

18
Q

Standby hydraulic system

A

Backup if A and / or B pressure is lost.
Can be activated manually or automatically and uses a single electric motor driven pump to power.

Thrust reversers
rudder
Leading edge flaps and slats
Standby yaw damper

Manual operation
Position either Flt control switch to STBY RUD:
Activates standby electric motor driven pump
Shuts off related hydraulic system pressure to ailerons, elevators, and rudder by closing flight control shutoff valve
Opens standby rudder shutoff valve
Deactivates the related flight control low pressure light when the standby rudder shutoff valve opens
Illuminates the STBY RUD ON master caution and flight controls (FLT CONT) lights.
Alternate Flaps master to ARM refer to ch9 flight controls
Activates the standby electric motor driven pump
closes the trailing edge flap bypass valve
Arms the alternate flaps position switch.
Allows the standby system to power the leading edge flaps and slats and thrust reversers.

19
Q

Standby Hydraulic System (Automatic Operation)

A

Initiated when
Loss of System A or B and
Flaps extended, and
Airborne, or wheel speed greater than 60 kts, and
Flight CONTROL switch A or B hydraulic systems ON

OR

Main PCU force Flight Monitor (FFM) trips
Automatic operation:
Activates the the standby electric motor driven pump.
Opens the standby rudder shutoff valve
Allows the standby system to power the rudder and thrust reversers.
Illuminates the STBY RUD ON Master Caution and Flight Controls (FLT CONT) lights.

20
Q

Standby Hydraulic system Leak

A

Standby hydraulic reservoir quantity reduces to zero. Low quantity light illuminates when half empty. B operates normally but is at 70% full.

Variations in hydraulic quantity indications
System becomes pressurized after engine start .
Raising or lowering landing gear or leading edge devices
Cold soaking occurs during long periods of cruise.
Foaming might occur at higher altitudes, blinking low pressure lights. Master Caution and Hyd annunciator lights may illuminate momentarily.

CQ 2024 Limitations (3 decks)

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