AIRBUS A330
Technical Ground School
July 1, 2004
(Updated 08/02/04)
*Note: The TGS test is a no jeopardy exercise. You may use what resources that have in the aircraft. It is a 50 Question open Book test from PART ONE TGS!! The questions with an asterisk* are the actual questions used on the test itself.
Chapter 6: Ice & Rain Protection
1.* Is it permitted to select WING ANTI-ICE pushbutton on the ground?
NO! Do Not USE!! But on the ground, the valves only open for 30 seconds for system testing. They close automatically:
· Upon touchdown,
· If a leak is detected, or
· If electrical power is lost.
Wing anti-ice is not permitted on the ground or in flight when the TAT exceeds 10°C.
2. *On approach, when should WING anti-ice be selected OFF?
Wing anti-ice operation:
· Select WING ANTI-ICE ON after thrust reduction altitude
· Normally, WING ANTI ICE should be selected OFF at the FAF
· If in severe icing conditions, WING ANTI-ICE may be left ON for landing
3. When will probe heat automatically come on?
· On the ground, low power is applied to the heaters when at least one engine is operating.
· In flight, the heating system automatically changes to high.
· The probe heaters can be activated manually prior to engine start by placing the PROBE/WINDOW HEAT pb ON.
Note: The TAT probes are not heated on the ground.
4. What part of each wing is anti-iced with pneumatic bleed air?
The four outboard slats on each wing are anti-iced by engine bleed air.
5. *What happens to the heat at the drain masts when the aircraft is on the ground?
On the ground, the heat is reduced to prevent injury to ground personnel.
6. What happens when Wing Anti-Ice is on and a bleed leak is detected?
Two pneumatic valves (one set on each wing) close if a leak is detected.
7. *What affect does Engine Anti-Ice have on engine performance?
The N1 limit for that engine is automatically reduced, and if necessary, the idle N1 is automatically increased for both engines in order to provide the required pressure. Additionally, continuous ignition is activated for that engine.
8. How will Engine Anti-Ice be affected if the aircraft is operating in an Emergency Electrical configuration?
If AC electrical power is lost, the engine anti-ice valve opens automatically.
Chapter 7: Electrical
1. If an IDG is disconnected, can it be reconnected in flight?
Pressing the IDG pb disconnects the IDG from its driveshaft. Only maintenance personnel can reconnect it.
2. *What does the EMER GEN red FAULT light indicate when illuminated?
AC power is lost and the Emergency Generator is not supplying power
3. Prior to the first flight of the day, what should the battery voltage be?
25.5 volts
4. How long must the IDG pushbutton be held to achieve a disconnect?
Press IDG pb until the GEN FAULT light comes on but for not more than 3 seconds to avoid damage to the disengage solenoid.
5. *What are the cautions regarding the disconnecting of an IDG?
Do not disconnect the IDG when the engine is not operating (or not windmilling) because starting the engine after having done so will damage the IDG.
Holding this pb in for more than approximately 3 seconds may damage the disconnection mechanism.
6. *What is the normal source of power for AC ESS BUS?
AC Bus 1
7. *What does the FAULT light indicate in the AC ESS FEED pushbutton?
The fault light illuminates amber with an ECAM when the AC Essential Bus is not electrically supplied.
8. Can the APU generator power all buses on the ground?
Yes. It can supply the entire electrical system.
9. How many batteries does the aircraft have?
Three. BAT 1 …. BAT 2…. APU BAT
10. *What busses will the emergency generator supply?
The Emergency generator will supply:
AC ESS, AC ESS Shed, AC Land recovery busses
DC ESS, DC ESS Shed, DC Land recovery, and Shed Land recovery busses.
NOTE: Land Recovery Busses are initially lost in an Emergency Electrical configuration, but are regained through activation of the Land Recovery Pb.
Chapter 8: Fire Protection
1. *What action arms the engine fire extinguishing squibs?
The ENG FIRE pb:
· Silences the aural fire warning
· Arms the fire extinguisher sqibs
· Closes the LP fuel valve
· Closes the hydraulic fire valve
· Closes the engine bleed valve
· Closes the pack flow control valve
· Disconnects the FADEC power supply
· Deactivates the IDG
2. If a failure in both engine fire loops occurs within 5 seconds of each other, what will occur?
A Fire Warning
3. *If there is an APU fire in flight will the APU automatically shutdown?
NO! Inflight there is no auto shutdown for a FIRE. The APU must be shutdown manually and the extinguisher must be discharged manually.
4. *How do you know when the engine fire extinguisher bottle has discharged?
The DISCH light illuminates amber when the bottle has lost its pressure.
5. What external indications may be received in the event of an APU fire while on the ground?
• An External warning Horn sounds
• A Red APU Fire light illuminates on the External Power Panel
• The APU itself might be heard shutting down.
6. How many cargo smoke detectors normally must sense smoke to issue a warning?
A smoke Detection Control Unit issues a smoke warning when two smoke detectors of one loop detect smoke. If one smoke detector fails, the system remains operational with the other detector.
7. *How many fire extinguisher bottles are provided for the cargo compartments?
2 Extinguisher Bottles….. can be discharged through either of the 2 nozzles in the FWD compartment…. OR through both of the nozzles (1 each) in the AFT and BULK compartments. The first bottle fires immediately, the second bottle is metered over a long period of time.
8. Which PB would be used to direct extinguishing agent if there is smoke detected in the bulk avionics section?
In this scenario, the AFT AGENT Squib Pb/ SMOKE (Red Light) covers both the AFT and BULK cargo compartments. The Red Smoke light will illuminate, the CRC sounds, and an ECAM Warning will be evident when smoke is detected.
Chapter 9: Aircraft Fuel
1. *What is the total fuel capacity of the Airbus 330?
172,000 lbs.
• Inner Tanks- 148,400 lbs.
• Outer Tanks- 12,800 lbs.
• Trim Tank - 10,800 lbs
2. How many fuel pumps are located in each wing tank collector box?
There are 2 main fuel pumps in each Wing Tank Collector Box. There is an additional Standby Pump in the Wing Inner Tank
3. *What events will trigger fuel in the trim tank to transfer forward into the wings?
Because CG shifts aft during normal fuel burn, automatic forward transfer of fuel typically occurs each time the CG shifts aft by 0.5%. The automatic forward transfer is initiated in the following situations:
• Actual CG reaches target CG (forward transfer stops when CG reaches 0.5% forward of target CG).
• Either inner tank quantity drops to 8800 lbs. (forward transfer stops when inner tank quantity increases to 11000 lbs.)
• Aircraft descends below FL 24500 or the FMGES time to destination is less than 35 minutes
4. When will fuel transfer from the outer tanks to the inner tanks?
The outer tanks’ transfer valves open allowing fuel to gravity feed transfer to the inner tanks when:
• The trim tank is empty
• Inner tank fuel quantity drops to 7700 lbs. and cycles closed to keep 8800 lbs in the inner tank
5. What is the caution when selecting the FEED switch to “Open”?
APU fuel supply is from the trim pipe, and operation is not possible when the trim pipe is drained. By moving the Trim Tank Feed Switch to “Open”… it opens all manual forward transfer valves and the trim tank inlet valve. This allows the transfer pipe to drain completely.
6. *Which fuel pumps can operate on emergency electrical power?
Emergency Power powered by RAT(L2, R2, Aft APU ). Only the main Left Pump 2 is powered. If the main Left Pump 2 fails or is selected OFF, then the main Right Pump 2 replaces it automatically. The Aft APU fuel pump operates in the emergency power configuration also. Fuel Crossfeed valve opens automatically.
Note: Emergency Electrical configuration- When speed decrease below 260 knots, or when the Land Recovery pb is selected ON(whichever is first) ALL FUEL PUMPS ARE LOST.
7. Can either wing tank feed either or both engines?
Yes. The Crossfeed Valve allows 1 engine fed by both sides, OR both engines fed by one side.
8. *What is the fuel source for the APU?
The trim pipe. There are 2 APU fuel pumps. The FWD APU fuel pump supplies fuel from the left main collector box via the trim pipe…and the AFT APU fuel pump supplies fuel from the trim pipe and /or the trim tank. They operate automatically to supply fuel to the APU, but not both at the same time
9. What events cause fuel to transfer AFT to the trim tank?
Because CG shifts aft during fuel burn, there is typically only one aft transfer per flight. The AFT transfer can only be done automatically, and it normally occurs as the aircraft climbs above FL 25500 and the CG is forward of target.
10. *What is the purpose of the inner tank split valves?
The Inner Tank Split valves control the Emergency Isolation valve. When selected ON, this valve closes and the inner tank is split into 2 parts in case of tank damage. Then the fuel from either inner tank can be used.
Chapter 10: Pneumatics, Air Conditioning, & Pressurization
1. *When would the LO selection on the PACK FLOW selector be used?
Captain’s discretion! Pack flow selection is made according to number of passengers or ambient conditions. Thus a light PAX load on a cool day would be a good time for a LO selection. LO position of the Pack Flow selector is 80% of NORM. Norm is 100%...HI is 125%.
2. If bleed air is being supplied by the APU or if one pack fails, what will the pack flow rate be?
HI is selected automatically…. regardless of the manual selection of the Pack Flow selector.
3. When does the pressurization system switch auto-controllers?
In the automatic mode, one cabin pressure controller is active and the other serves as a backup. If the active controller fails, the backup automatically resumes control. After each landing, the two controllers swap roles.
4. *With the LDG ELEV selector in AUTO, what altitude is used for landing field pressurization reference?
Destination elevation is supplied by the FMGEC. If the FMGEC is not available then the crew must manually select the landing elevation on the LND ELEV selector.
5. *What are the FOUR supply zones for conditioned air?
FWD, MID , AFT , and Flight Deck are the 4 Cabin Zones….
6. *In flight, what happens if HP bleed air pressure is insufficient?
Air is normally bled from the Intermediate Pressure stage of the high pressure compressor. When IP stage pressure and temperature are insufficient, a high pressure bleed valve opens to supply bleed air from the High Pressure stage. In flight, if the pressure is insufficient even with the HP stage valve open, the engine speed is automatically increased to provide adequate air pressure.
7. *When is the RAM AIR pushbutton used?
During flight, if both packs fail, or in case of smoke in the cabin, a ram air inlet may be opened allowing ambient air to enter the mixing unit.
8. *Can external air be used to supplement low APU bleed pressure?
NO.
9. *When operating pressurization in AUTO, if the pilot suspects the selected controller is malfunctioning, how can he swap controllers?
Attempt to select the other system by switching the MODE SEL pb to MAN for at least 3 seconds, then return it to AUTO.
10. Is cargo heat provided to the forward cargo compartment?
No. The Bulk cargo bin is ventilated and heated.
Chapter 13: Instruments/Navigation/Communication
1. If a TERR pb FAULT light illuminated, would that affect the basic GPWS modes?
This amber light illuminates, along with an ECAM caution, if the terrain detection function fails. The terrain is not shown on the ND. The basic EGPWS modes 1 to 5 are still operative.
2. With the RDCR GND CTL pushbutton in AUTO when does the CVR and Digital Flight Data Recorder (DFDR) energize?
The CVR and Digital Flight Data Recorder operate for 5 mins. after electrical power is supplied to the aircraft. They operate continuously with an engine running. They stop 5 mins. after the last engine is shut down.
3. *If ACP #1 (Captain's) should fail, how would the pilot restore communications?
Select CAPT 3 on the Audio Switching panel. The captain uses his acoustic equipment and the third occupant’s ACP.
4. Is the radar display available in all modes of the ND selector on the EFIS Control Panel?
No. When the “Terrain on ND “ function of the EGPWS is selected, then the weather display is inhibited. Weather can’t be seen on Plan or Eng either.
5. *Does the EGPWS use radar signals to “ground map” terrain?
The enhanced function is based on a worldwide terrain database. It provides Terrain Awareness Display (TAD) which predicts terrain conflict and displays the terrain on the ND, and Terrain Clearance Floor which triggers a warning. The TAD function computes a caution and warning envelope ahead of the aircraft and when the boundaries of this envelope conflict with the database terrain information, it generates alerts.