Systems 3 Flashcards
Where is the environmental control panel located?
A. Upper pilot’s instrument panel
B. Lower copilot’s instrument panel
C. Pilot’s side panel
D. Overhead panel
B
What system uses an electric motor to drive its compressor unit and draws a lot of power?
A. Vapor Cycle Cooling Subsystem (VCCS)
B. Air Conditioning Unit (ACU)
C. Forward Compressor Conditioning Unit (FCCU)
D. None of the above
A
What equipment provides ventilation and cooling air for the flight deck?
A. Flight Deck compressor fan
B. Cabin cooling fan
C. Avionics blower
D. Forward and aft evaporator blowers
D
Where is the compressor in the VCCS located?
A. Aft compartment
B. Left engine accessory gearbox
C. Avionics rack
D. Nose
D
T/F: The electric heat subsystem (EHS) can provide heating while airborne.
False
What is the primary means of cabin pressurization and temperature control in flight?
A. Air Cycle Unit (ACU)
B. Vapor Cycle Cooling Subsystem (VCCS)
C. Avionics Blowers
D. Electric Heat Subsystem
A
The ACU uses engine bleed air to provide:
A. Anti-ice to the horizontal stabilizer
B. Pressurization to the aft compartment
C. Heating, cooling and pressurization
D. Hot air to the coffee maker
C
With the BLEED AIR switch in NORM,
A. The temperature will be constant
B. Both engine bleed air valves are open
C. The ACU is not used
D. The right engine bleed air valve is closed
B
T/F: The ACU can operate completely on the air output from one engine.
True
With the MODE switch in AUTO FLDK, cooling will be controlled ________
A. By the crew using the TEMP switch to manually open/close the cabin temp valve
B. By sensors in both the cabin and the ducts
C. on the flight deck only, not in the cabin
D. By temperature sensors in the ducts only
B
The cabin pressurization controls are located ______
A. On the pilot’s instrument panel
B. On the copilot’s instrument panel
C. On the center console
D. On the overhead panel
B
T/F: The CABIN CLIMB gauge shows how rapidly cabin altitude is changing.
True
Wing leading edges are heated by _______
A. Engine bleed air
B. Electrical heaters inside the wings
C. The avionics blowers
D. Wing heating blankets
A
The ICING light will illuminate when _________
A. The ultrasonic prob detects 0.02 inches of ice
B. The AOA vane detects ice in it
C. The pitot heat system is turned off
D. The wing duct temperature falls below 140ºF
A
The WG ICE TEMP LO annunciator illuminates when the wing duct temperature falls below ________
A. 100ºF
B. 140ºF
C. 160ºF
D. 200ºF
B
The engine cowls are heated _________
A. By bleed air
B. By electrical heaters
C. By friction
D. By the horizontal stabilizer anti-ice
A
If the main avionics rack blower fails, flow pressure sensors cause the ______ annunciator to illuminate.
A. ICING
B. AV BLO FAIL
C. AV STBY BLO
D. STBY BLO FAIL
B
The electric heat subsystem (EHS) consists of how many heaters?
A. 1
B. 2
C. 3
D. 4
C
The ACU (Air Cycle Unit) distributes _____ and ____ air.
A. Warm; moist
B. Cool; conditioned
C. Hot; cold
D. Dry; hot
B
The VCCS and ACU are controlled by the crew using the ______
A. Heater select switches on the pilot’s instrument panel
B. Overhead panel
C. Environmental Control Panel
D. Air Conditioning Master Switch
C
The _____ provides preflight, inflight, and post flight air conditioning for the flight deck and avionics rack.
A. EHS
B. Pilot’s electric fan
C. VCCS
D. Swamp cooler
C
The electric heat subsystem needs external power to operate.
A. True
B. False
A
The ACU (Air Cycle Unit) uses _____ to provide heating, cooling and pressurization.
A. The VCCS
B. An electric powered compressor
C. A propane compressor
D. Engine bleed air
D
With the BLEED AIR switch in L ENG, the left valve is _____ and right valve is ______.
A. Closed; closed
B. Open; open
C. Open; closed
D. Closed; open
C
When the MODE switch on the Environmental Control Panel is in the AUTO DUCT position, the cabin air temperature valve is positioned based on temperature sensed in the _______.
A. Wing Piccolo Tube
B. Ram air intake
C. Duct system
D. Avionics rack compartment
C
T/F: The windshield has no ice or rain protection.
False
When the MODE switch on the Environmental Control Panel is in ______, the crew uses the TEMP switch to manually open/close the cabin temperature control valve.
A. ON
B. AUTO FLDK
C. MAN DUCT
D. AUTO DUCT
C
The _____ switch opens a valve to allow cool air to flow to the cabin aft ceiling air conditioning chamber, providing additional cooling to the aft cabin.
A. AFT CEILING COOL
B. VCCS
C. AFT CABIN COOL
D. CABIN OUTLET
D
When will the load shed controller automatically shut off the VCCS?
A. During Engine Start
B. When using windshield De-ice
C. When using horizontal stabilizer anti-ice/deice
D. All of the above
D
Which VCCS component removes heat from the refrigerant following compression?
A. Compressor
B. Cooling coils
C. Condenser/heat exchanger
D. Blower Units
C
Placing the AUX TEMP CONTROL rotary switch to the _______ position applies power to the VCCS.
AUX COOL
How is air temperature controlled with the AUX TEMP CONTROL switch in the ELEC HEAT 1 position?
Air temperature cannot be controlled by the crew when using the electric heat subsystem. The air temp is automatically maintained at 120ºF to 150ºF at the outlet.
T/F: When the BLEED AIR switch position(s) is in L ENG, R ENG, NORM, or HIGH, ACU cooling will be provided to the flight deck.
True
In which MODE switch position will sensors on the flight deck be used to help maintain a constant flight deck temperature?
A. AUTO FLDK
B. AUTO DUCT
C. MAN DUCT
A
For the ACU to function, the BLEED AIR switch must be in what position?
A. NORM
B. L ENG or R ENG
C. HIGH
D. Any of the above
D
For most training flights, the MODE switch will be in the _____ position.
A. CABIN OUTLET
B. AUTO FLDK
C. MAN DUCT
D. AUTO DUCT
B
A passenger seated in the rear of the aircraft complains that the aft cabin is too hot. How can you increase cool airflow into the aft portion of the cabin?
A. Select AUTO DUCT
B. Turn the TEMP knob toward cool
C. Press the CABIN OUTLET pushbutton
D. Switch to the MAN DUCT mode
C
Pressurization is provided by ______
A. Bleed air through the ACU
B. Bleed air through the pressurization unit
C. The oxygen cylinder
D. The vapor cycle unit
A
Cabin pressure is maintained by regulating the amount of _______
A. Bleed air exiting the engines
B. Air cycle air entering the cabin
C. Air leaving the cabin
D. Vapor cycle air entering the cabin
C
Prior to takeoff the cabin rate of climb knob should be set to the _____ O’clock position.
A. 2
B. 7
C. 10
D. 12
C
The CABIN PRESSURE LO annunciator illuminates when the cabin altitude reaches ________.
A. 18,000ft (+/- 500)
B. 13,000ft (+/- 1500)
C. 9,500ft (+/- 500)
D. 5,000ft (+/- 500)
C
When operating properly, the outflow valves will keep cabin pressure differential from exceeding _____ PSID.
A. 10.2
B. 9.2
C. 8.3
D. 3.5
B
Prolonged operation with bleed air in EMER can result in _______.
A. Over pressurization
B. Excessive rate of climb on the CABIN RATE OF CLIMB indicator
C. Extreme cold
D. Melted trim panels in the rear portion of the cabin
D
The VCCS provides ________.
A. The primary cooling prior to engine start and auxiliary cooling in the air
B. All aircraft cooling
C. Primary cooling on the ground
D. Primary cooling in the air
A
ELECT HEAT 1&2 activates _________
A. Inflight heating
B. One heater
C. Two heaters
D. Three heaters
D
Ground air provides fresh air to the cabin ___________.
A. In flight only
B. On the ground only
C. Any time below 10,000ft
D. Any time selected
B
What action should be taken in the event of the AV BLO FAIL annunciator illumination?
A. Turn on AUX COOL
B. Press the AV STBY BLO switch
C. Select GND AIR
D. Select BLOW 1&2
B
The T-1A is pressurized by _______.
A. The aft evaporator/blower unit
B. The vapor cycle unit
C. Engine bleed air
D. The oxygen bottle
C
The temperature in the cabin during normal inflight operations is controlled by ____________.
A. Mixing hot bleed air and bleed air that has been cooled
B. Selecting the amount of hot air entering the cabin
C. Selecting the amount of cold air entering the cabin
D. Turning the VCCS on and off
A
When planning to cruise at FL330 the cabin controller should be set to __________.
A. 35,000ft
B. 34,000ft
C. 33,000ft
D. 32,000ft
B
The use of the EMER position on the bleed air knob is _______.
A. Acceptable if flight does not continue for more than 1 hour
B. Acceptable until you can do an enroute descent below FL180
C. An emergency and should not be prolonged any longer than necessary
D. Unacceptable
C
The avionics standby blower _________.
A. Provides an alternate source for the avionics on the flight deck
B. Provides an additional source of cooling for the avionics rack in the back of the cabin
C. Uses fresh air from outside the aircraft
D. Uses the Air Cycle Unit system
B
Which of the following is capable of cooling the aircraft cabin prior to engine start?
A. ACU (Air Cycle Unit)
B. Avionics Standby Blower
C. Outflow valves
D. Vapor Cycle Cooling Subsystem (VCCS)
D
Selecting ELEC HEAT 1&2 on the AUX TEMP CONTROL switch ________
A. Activates 4 heaters
B. Activates 3 heaters
C. Activates 2 heaters
D. Adds a second heater to an already operating heater
B
For the ACU to function, the BLEED AIR switch must be in what to function?
A. NORM
B. L ENG or R ENG
C. HIGH
D. Any of the above
D
For most training flights, the MODE switch will be in the ______ position.
A. CABIN OUTLET
B. MAN DUCT
C. AUTO DUCT
D. AUTO FLDK
D
A passenger seated in the rear of the aircraft complains that the aft cabin is too hot. How can you increase the cool airflow into the aft portion of the cabin?
A. Select AUTO DUCT
B. Turn the TEMP knob toward cool
C. Press the CABIN OUTLET pushbutton
D. Switch to the MAN DUCT mode
C
The vapor cycle cooling system can be used ______.
A. On the ground or in the air
B. On the ground only
C. On the ground only with the ground power unit
D. In the air only
A
The electric heat subsystem ____________.
A. Can only be used on the ground with the aircraft’s battery or on external power
B. Can only be used on the ground when connected to external power
C. Is limited to one unit in the air due to load consideration
D. Can be used on the ground or as a back-up in the air
B
With the AUX TEMP CONTROL switch in ELECT HEAT 1&2, the electric subsystem uses ______.
A. Excess heat from the generators
B. Two electrical heating elements
C. Three electrical heating elements
D. One electrical heating element
C
The Ice Detector Probe ________.
A. Is continuously heated in flight
B. Must be tested during preflight to ensure proper operation
C. Receives power through its heater through the L AOA switch
D. Illuminates an annunciator when it accumulates 0.02 inches of ice.
D
Which of the following statements concerning the T-1A engine anti-ice system is correct?
A. The engine nacelles are warmed by electrical heater elements.
B. The T0 probe is continually heated when the engine is running.
C. The bleed air inlet valve closes when DC electrical power is applied and opens when power is removed.
D. The L or R ENG ICE TEMP LO annunciator extinguishes when the temperature of the air in the nacelle reaches 100ºF.
C
T/F: Do not operate the engine anti-ice while airborne if temperatures exceed 10ºC.
False
The red WING OV HT annunciator illuminates when ____.
A. Any one of the over temperature switches senses a temperature in excess of either 212ºF or 350ºF
B. The temperature switch closes as the temperature in the leading edge passes 140ºF
C. The three overtemperature switches sense temp in excess of 350ºF
D. The temperature switch senses a temperature in excess of 350ºF
A
Which of the following statements is true regarding wing anti-ice system operation?
A. Two wing anti-ice switches are located on the overhead panel
B. The wing anti-ice system uses a combination of engine bleed air and ram air.
C. The amber BL AIR DCT FAIL annunciator indicates high temperature in the wing leading edge
D. The wing leading edge deice system uses a combination of bleed air and electric heater elements
B
Should the horizontal stabilizer anti-ice system fail during flight, continue to your destination using the ________.
A. De-ice backup system
B. De-ice system
C. Either of the above
D. None of the above
A
Use the wing anti-ice and de-ice systems on the ground ________.
A. As necessary to clear ice from the horizontal stabilizer
B. Only on occasions where significant weather is present
C. When weather conditions are favorable for ice accumulation
D. For testing only
D
The backup de-ice system is operated by placing the switch in the ________.
A. MANUAL position for 30 seconds
B. TEST position for 20 seconds
C. MANUAL position momentarily
D. ON position for 30 seconds
C
Placing the H STAB ANTI ICE in the TEST position _______.
A. Simulates an overheat condition
B. Is necessary prior to switching the system OFF
C. Provides a continuity test of the ANTI ICE system
D. Creates a 10 second delay before the system switches to the ON position
A
The PLT STATIC rocker switch on the overhead control panel controls the power to heating elements in ______.
A. The two static ports on the pilot’s side of the aircraft
B. One static port on each side of the aircraft
C. All four static ports if the copilot’s system fails
D. Normally one port on each side, but all 4 if the copilot’s system fails
B
The PITOT HT OFF annunciator will illuminate when _________.
A. Either pitot heater fails
B. Both pitot heaters fail
C. Either pitot heater is turned OFF
D. Any of the above
D
What is the maximum airspeed for the windshield wipers?
200 KIAS