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Each engine is equipped with two identical detection loops (A & B) each of which contain three heat sensing
elements and a computer (Fire Detection Unit). The sensing elements are located in the pylon nacelle, engine core,
and fan section. The FDU issues a fire warning when both loops detect an overheat in a particular area. If one loop
fails, the fire warning system remains operational with the other loop. A fire warning is also issued if both loops fail
within 5 seconds of each other.
The ECAM will issue appropriate messages if any component of the detection system fails. An engine fire is
indicated by an aural CRC, the illumination of the ENG FIRE pb, and MASTER WARN lights.
Each engine is equipped with two fire extinguishers which are discharged by pressing the associated AGENT DISCH
pb on the respective engine FIRE panel.
7. What external indications may be received in the event of an APU fire while on the ground?
The red APU FIRE light illuminates and an external warning horn sounds
The APU fire extinguisher discharges automatically 3 seconds after the appearance of the fire warning.
The light extinguishes when the fire has been extinguished.
8. In case of lavatory smoke, would you get a warning in the cockpit?
Lavatory smoke is indicated by:
Aural CRC
Illumination of MASTER WARN light
Red ECAM SMOKE LAVATORY SMOKE
9. How do you know when the engine fire extinguisher bottle has discharged?
2009 – 2010 TGS Study Guide
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AGENT DISCH illuminates amber when its fire extinguisher bottle has lost pressure.
APU
1. What are the altitude limits for APU generator and bleed air?
APU generator – 100% load up to 25,000 feet (Note: APU GEN is available up to 39,000 feet).
APU Bleed – Maximum altitude for APU bleed operation is 20,000 feet.
2. When would the APU MASTER SW pb FAULT light illuminate?
This amber light illuminates and a caution appears on the ECAM when an automatic APU shutdown occurs.
3. If an APU fire occurs in flight will the APU shut down automatically?
APU will automatically shut down due to fire on the ground only.
4. The APU START pb green AVAIL light signifies that what?
This light illuminates when N is above 99.5% or 2 seconds after N reaches 95%.
5. Will the APU bleed valve close automatically during climb? Will it reopen during descent?
No
6. With battery power only, what would an APU fire test look like?
APU FIRE pb illuminated
SQUIB and DISCH lights illuminated
7. Can the APU be shut down from outside the aircraft?
APU SHUT OFF pb on External Power Panel.
8. Can you name some of the possible reasons for an APU auto shutdown?
Fire (on ground only)
Air inlet flap not open
Overspeed
No acceleration
Slow start
EGT overtemperature
No flame
Reverse flow
Low oil pressure
High oil temperature
ECB failure
Loss off overspeed protection
Underspeed
DC power loss
Powerplant
1. How is autothrust disconnected to avoid thrust surges?
Autothrust instinctive disconnect pb.
2. How is the FADEC powered?
The system has its own alternator rendering it independent of the aircraft electrical system when N2 is above a set
value. If this alternator fails, the FADEC automatically switches over to aircraft electrical power.
3. Continuous ignition is provided automatically when:
2009 – 2010 TGS Study Guide
___________________________________________________________________________________________
____________________________________________________________________________________________
Unofficial Airbus Study Site www.airbusdriver.net
ENG ANTI ICE is selected ON
Engine flameout is detected in flight
The EIU fails
4. Name some reasons that a manual start may be required?
After aborting a start because of:
Stall
EGT overlimit
Low start air pressure
When expecting a start abort because of:
Degraded bleed performance due to a hot condition or at a high altitude airfield.
A mature engine in hot condition or at a high altitude airfield.
Marginal performance of external pneumatic power.
Tailwind greater than 10 knots.
5. What takes place when we push the MAN START button?
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