Normal Engine Automatic-Start Procedure [IAE]

TASK 71-00-00-710-043-A
Normal Engine Automatic-Start Procedure

WARNING: MAKE SURE THAT ALL ENGINE OPERATING AREAS ARE AS CLEAN AS POSSIBLE. ALL RAMPS, TAXIWAYS, RUNWAYS AND OTHER OPERATING AREAS MUST BE VERY CLEAN TO PREVENT BAD DAMAGE TO THE ENGINE, AIRCRAFT AND PERSONS IN THE AREA.

WARNING: DO NOT TRY TO STOP THE FAN FROM TURNING BY HAND. THIS CAN CAUSE INJURY TO THE PERSONS AND DAMAGE TO THE EQUIPMENT.

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

WARNING: - ENGINE OPERATION MUST NOT EXCEED MINIMUM IDLE WHEN PERSONNEL ARE IN ENTRY/EXIT CORRIDOR.

POSITIVE COMMUNICATION BETWEEN THE FLIGHT COMPARTMENT AND PERSONNEL IN ENTRY EXIT CORRIDOR IS NECESSARY.
INLET AND EXHAUST HAZARD AREAS MUST BE STRICTLY OBSERVED BY PERSONNEL IN ENTRY/EXIT CORRIDOR.

WARNING: MAKE SURE THAT:

THE PASSENGER DOORS ARE CLOSED AND THE PASSENGER LOADING STAIRS ARE REMOVED WHEN AT LEAST ONE ENGINE IS OPERATED ABOVE IDLE POWER.
THE CARGO DOORS ARE CLOSED AND CARGO LOADING EQUIPMENT IS REMOVED WHEN:

. ENGINE 2 IS OPERATED AT IDLE OR ABOVE . AT LEAST ONE ENGINE IS OPERATED ABOVE IDLE POWER IF YOU DO NOT OBEY THESE PRECAUTIONS INJURY TO THE PERSONNEL AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT CAN OCCUR.

WARNING: BEFORE YOU OPERATE THE ENGINES, MAKE SURE THAT THERE IS NO RISK OF PRE-PRESSURIZATION OR RESIDUAL PRESSURE IN THE AIRCRAFT AFTER SUBSEQUENT ENGINE SHUTDOWN. TO DO THIS, MAKE SURE THAT THE AIR CONDITIONING OUTFLOW-VALVE IS OPEN DURING ALL THE TEST. IF PERSONS TRY TO OPEN A DOOR WHEN THERE IS RESIDUAL PRESSURE IN THE AIRCRAFT:

THE DOOR CAN OPEN WITH DANGEROUS SUDDEN FORCE.
THERE IS A RISK OF INJURY OR DEATH.
DAMAGE TO THE AIRCRAFT CAN OCCUR.

WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

WARNING: DO NOT TOUCH THE PROBES DURING OR IMMEDIATELY AFTER THIS PROCEDURE. THE PROBES WILL BE HOT AND CAN BURN YOU.

WARNING: IF YOU DO MANY GROUND STARTS, MONITOR THE FUEL LEVEL IN THE WING TANK. IF YOU DO NOT OBEY THIS PRECAUTION, YOU CAN CAUSE FUEL SPILLS ON THE GROUND. FUEL SPILLS CAN CAUSE FIRE.

WARNING: MAKE SURE THAT THE LANDING GEAR GROUND SAFETIES AND THE WHEEL CHOCKS ARE IN POSITION. MOVEMENT OF THE AIRCRAFT CAN BE DANGEROUS.

CAUTION: MAKE SURE THAT FOR THE ENGINE GROUND-RUN TEST :

THE AIRCRAFT IS IN A CLEAR AREA SPECIFIED FOR ENGINE GROUND RUN AND WHICH AGREES WITH THE ENGINE DANGER AREAS GIVEN IN THE IAE ENGINE SAFETY PRECAUTIONS REF. AMM 71-00-00-860-012-A
THE AIRCRAFT IS STOPPED AND CANNOT MOVE DURING THE ENGINE GROUND RUN.

IF DURING THE ENGINE GROUND-RUN TEST THE AIRCRAFT STARTS TO MOVE FORWARD :

DECREASE THE ENGINE THRUST IMMEDIATELY
STOP THE AIRCRAFT WITH THE PARKING BRAKE.

CAUTION: MAKE SURE THAT THERE IS NO HYDRAULIC GROUND POWER SUPPLY CONNECTED TO THE AIRCRAFT WHEN YOU DO THIS PROCEDURE. IF A HYDRAULIC GROUND POWER SUPPLY IS CONNECTED, THERE IS A RISK OF DAMAGE TO THE ENGINE PUMPS.

ZONE: 210

1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	HOT AIR SOURCE
98F10103500000	2	CHOCK-MLG,ENGINE RUN-UP

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
210	CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

C. Referenced Information

REFERENCE	DESIGNATION
TASK 10-11-00-555-014-A	Removal of the Aircraft Protection Equipment
TASK 12-13-79-610-011-A	Check Oil Level and Replenish
TASK 24-41-00-861-002-A	Energize the Aircraft Electrical Circuits from the External Power
TASK 24-41-00-861-002-A-01	Energize the Aircraft Electrical Circuits from the APU
TASK 24-41-00-861-002-A-02	Energize the Aircraft Electrical Circuits from Engine 1(2)
TASK 24-41-00-862-002-A	De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01	De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02	De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 26-12-00-710-001-A	Operational Check of Loop/Squib
TASK 27-50-00-866-009-A-01	Retraction of the Flaps/Slats on the Ground
TASK 29-10-00-863-002-A	Pressurize the Yellow Hydraulic System with a Hydraulic Ground Power-Cart
TASK 29-30-00-200-002-A	Check of the Reservoir Quantity Indication on the ECAM Display Unit
TASK 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
TASK 36-12-00-860-001-A	Pressurization of the Bleed System with the APU
TASK 36-12-00-860-002-A	Pressurization of the Bleed System through the HP Ground Connector
TASK 71-00-00-700-014-B	Cold Weather Operation Procedure
TASK 71-00-00-700-016-A	Procedure for a Bowed Rotor Start Prevention
TASK 71-00-00-710-018-A	Discontinued Start, Restart and Shutdown Procedures
TASK 71-00-00-860-012-A	Engine Safety Precautions
TASK 71-00-00-860-013-A	Oil and Fuel Systems Priming Procedure
TSM 77-00-00-810-930	EGT Higher than the Limit on Engine 1 (Min Idle and below Including Start)
TSM 77-00-00-810-931	EGT Higher than the Limit on Engine 2 (Min Idle and below Including Start)
Tool Installation
Start Fault Diagnostics
Wind Direction and Velocity Operational Limits

3. Job Set-up
Subtask 71-00-00-210-060-B ** ON A/C NOT FOR ALL

A. Do these inspections before the procedure:

NOTE: If a Post Flight Report (PFR) is necessary after the ground run, you can enter a new flight number with the Multipurpose Control and Display Unit (MCDU) (a minimum of one dummy character is sufficient).

CAUTION: REMOVE THE PROTECTIVE COVERS FROM THE PROBES BEFORE YOU DO THIS PROCEDURE. IF YOU DO NOT REMOVE THEM, THE PROBES AND PROTECTIVE COVERS CAN BECOME DAMAGED OR BURNED.

(1) Make sure that all the protection covers are removed from the aircraft (Ref. AMM TASK 10-11-00-555-014).
(2) Make sure that the air-conditioning outflow valve is open during all the test:
(a) To open the valve:

Make sure that the ditching function is not on (the light must be off), and
Set the cabin pressure to the auto mode, or
Set the cabin pressure to the manual mode (the outflow valve will open automatically through the Residual Pressure Control Unit (RPCU)).

(3) Obey the safety precautions when you operate the engine on the ground (Ref. AMM TASK 71-00-00-860-012).
(4) Make sure that the engine areas are clear of any foreign objects.
(5) Do a visual check of the temperature sensors, the fan inlet and the exhaust areas:
(a) If snow or ice collected in the fan duct, make sure that the fan turns freely. Also, make sure that the engine inlet, the inlet lip, the fan spinner and the fan exhaust duct are clear of ice or snow.
(b) If the fan does not turn freely, remove the ice or snow from the engine with the HOT AIR SOURCE before you operate the engine.
(c) Do the cold-weather operation procedure (Ref. AMM TASK 71-00-00-700-014).
(6) Look at the general condition of the fan spinner and the fan blades, the core exhaust nozzle, the Low Pressure Turbine (LPT) and the external surfaces of the cowls.
(7) Do a check of the drain ports for fuel, oil and hydraulic leaks. Also, make sure that the fuel drained from the engine does not cause a fire.

Subtask 71-00-00-861-072-A ** ON A/C NOT FOR ALL

B. Energize the aircraft electrical circuits. (Ref. AMM TASK 24-41-00-861-002)

Subtask 71-00-00-865-081-A ** ON A/C NOT FOR ALL

C. Make sure that this(these) circuit breaker(s) is(are) closed:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	ENGINE/1 AND 2/IGN/SYS A	1JH	A03
FOR FIN: 1000EM1 (ENGINE1)
49VU	ENGINE/1/FADEC A/AND EIU 1	2KS1	A04
121VU	ENGINE/ENG1/OIL/PRESS/AND REV SNSR/CHAN A	2EN1	N40
121VU	ENGINE/ENG1/OIL/QTY	1EN1	N39
121VU	ENGINE/IGN/ENG1/SYS B	3JH1	P41
121VU	ENGINE/IGN/ENG1/SYS A BAT	2JH1	P39
121VU	ENGINE/ENG1/FADEC B/AND EIU 1	4KS1	R41
FOR FIN: 1000EM2 (ENGINE2)
49VU	ENGINE/2/FADEC A/AND EIU 2	2KS2	A05
121VU	ENGINE/ENG2/OIL/PRESS/AND REV SNSR/CHAN A	2EN2	N42
121VU	ENGINE/ENG2/OIL/QTY/AND REV SNSR/CHAN B	1EN2	N41
121VU	ENGINE/IGN/ENG2/SYS B	3JH2	P42
121VU	ENGINE/IGN/ENG2/SYS A BAT	2JH2	P40
121VU	ENGINE/ENG2/FADEC B	4KS2	Q40

Subtask 71-00-00-860-058-A ** ON A/C NOT FOR ALL

D. Do the EIS start procedure (ECAM display units only) (Ref. AMM TASK 31-60-00-860-001).

Subtask 71-00-00-869-182-A ** ON A/C NOT FOR ALL

E. Check of the Reservoir Quantity Indication:
(1) Make sure that fire-fighting personnel are present.
(2) On the lower ECAM display unit:

CAUTION: MAKE SURE THAT THE HYDRAULIC RESERVOIR PRESSURE IS IN THE CORRECT OPERATION RANGE BEFORE YOU START THE ENGINE. THE HYDRAULIC FLUID IS NECESSARY TO LUBRICATE THE HYDRAULIC PUMPS THAT THE ENGINE OPERATES.

(a) Get the HYDRAULIC page.
(b) Make sure that the pressure of the Green reservoir for the engine 1 (Yellow reservoir for the engine 2) is correct.
(c) Make sure that the reservoir fluid level is correct (Ref. AMM TASK 29-30-00-200-002).
(3) Make sure that the engine 1(2) pump is serviceable (on the HYD/FUEL PNL 40VU the OFF legend of the ENG1(2) PUMP pushbutton switch must be off).

Subtask 71-00-00-710-130-A ** ON A/C NOT FOR ALL

F. Do the operational test of the engine fire and overheat detection (loop/squib) (Ref. AMM TASK 26-12-00-710-001).

Subtask 71-00-00-869-183-A ** ON A/C NOT FOR ALL

G. Preparation
(1) Put chocks in position in front of each forward outboard MLG-wheel.
(a) If, after the engine start, you must operate the engine at high power, use the 98F10103500000 CHOCK-MLG,ENGINE RUN-UP.

Tool Installation ** ON A/C NOT FOR ALL

1 Put the 98F10103500000 CHOCK-MLG,ENGINE RUN-UP in position against the wheel.
2 Pull up the tow bar in the top position until it touches the weld stops.
(2) On RVD TRIM/PARKING BRK PNL:
(a) Make sure that the parking brake control-switch is set to ON.
(3) On ENG panel 115VU:
(a) Make sure that the ENG/MASTER 1(2) switch is set to OFF.
(4) Make sure that the thrust lever of engine 1(2) is in the idle stop position (zero on the graduated sector).
(5) On center instrument panel 400VU, make sure that:
(a) The brake pressure indication on the brake Yellow-pressure triple-indicator is correct. If necessary, pressurize the brake accumulator with the Yellow pump (Ref. AMM TASK 29-10-00-863-002).
(b) The landing-gear normal control-lever is in the DOWN position.
(6) Make sure that the interphone system operates correctly.
(7) Make sure there is a positive communication between the cockpit and the ground personnel in front of the aircraft to make sure that there are no persons in the dangerous areas.
(8) On the lower ECAM DU:
(a) Get the FUEL page.
(b) Make sure that the fuel tanks contain the correct quantity of fuel to operate the engine.
(9) On HYD/FUEL panel 40VU:
(a) Push all the FUEL/PUMPS pushbutton switches (the OFF legends go off).
(10) Supply the aircraft pneumatic system:

CAUTION: DO NOT RUN THE ENGINE IF THE FUEL INLET PRESSURE IS NOT POSITIVE (THE FUEL IS NECESSARY TO LUBRICATE THE ENGINE FUEL PUMPS AND THE FMU AND THUS PREVENT DAMAGE).

(a) Supply the aircraft pneumatic system from a HP Ground Power Unit (GPU) or the APU (Ref. AMM TASK 36-12-00-860-001) or (Ref. AMM TASK 36-12-00-860-002).
(11) On overhead control and indicating panel 25VU:

Set the EXT LT/BEACON switch to ON.

Subtask 71-00-00-860-225-A

H. Make Sure that the Flaps and Slats are in the 0 Position

CAUTION: MAKE SURE THAT THE FLAP AND SLAT CONTROL LEVER IS IN THE 0 POSITION. IF THE FLAP AND SLAT CONTROL LEVER IS NOT IN THE 0 POSITION, AND IF THE THROTTLE CONTROL LEVER(S) IS(ARE) SET TO THE MCT/FLX TO POSITION, THE COMMANDED THRUST WILL BE MAX TAKE-OFF AFTER 8 SECONDS.

(1) Make sure that the flaps and slats are in the 0 position (Ref. AMM TASK 27-50-00-866-009).

4. Procedure
Subtask 71-00-00-710-131-F ** ON A/C NOT FOR ALL

A. Do the Normal Engine Automatic Start Procedure as follows:
(1) General

WARNING: AFTER AN ABORT OF THE ENGINE STARTING SEQUENCE, A DRY CRANK, TO REMOVE FUEL VAPOURS, WILL OCCUR, ACCOMPANIED BY ECAM MESSAGE:

AUTO CRANK IN PROGRESS

ON COMPLETION OF THE DRY CRANK, ALWAYS PUT THE "ENG/MASTER" SWITCH BACK TO THE "OFF" POSITION WHEN INSTRUCTED BY ECAM MESSAGE:

ENG MASTER OFF.

IF YOU ONLY CHANGE THE POSITION OF THE ENGINE MODE SELECTOR SWITCH (FROM "IGN/START" TO "NORM"), THE FADEC SYSTEM WILL NOT COMPLETE THE ABORT. THERE IS THUS A RISK THAT THE ENGINE WILL START. THIS CAN CAUSE INJURIES TO PERSONS.

CAUTION: REVERSE WINDMILLING CAN OCCUR IF THE AIRCRAFT IS OPEN TO A STRONG TAIL WIND. CAREFULLY MONITOR THE START TO PREVENT A HOT START. REFER TO WIND DIRECTION AND VELOCITY OPERATIONAL LIMITATIONS DIAGRAM.

(a) Do each step of the procedure in sequence. If you abort the start, you must do each step of the sequence again.

Start Fault Diagnostics ** ON A/C NOT FOR ALL

(b) During the start, keep the service air bleed inputs and accessory load to a minimum.

Wind Direction and Velocity Operational Limits ** ON A/C NOT FOR ALL

1 If a tail wind prevents an easy start, position the aircraft toward the wind (Ref. AMM TASK 71-00-00-860-012).
(2) Do the engine start

ACTION	RESULT
1.On ENG panel 115VU: Set the ENG/MODE/CRANK/NORM/IGN/START selector switch to IGN/START.	On the lower ECAM display unit : The ENGINE page comes into view. Make sure that : The air pressure is between 20 psi (1.4 bar) and 39 psi (2.7 bar). The oil quantity is correct.
A.Fill the oil tank by the procedure that follows to avoid overfilling the system (1)If the engine was shut down for more than 10 hours, motor the engine with the starter for a minimum of two minutes. Check the oil level after the rotor stops. Fill the oil tank as necessary (Ref. AMM TASK 12-13-79-610-011). (2)If the engine was shut down for less than 10 hours, check the oil level. Fill the oil tank as necessary (Ref. AMM TASK 12-13-79-610-011). (3)Before the first start after an overhaul, or if you drained the fuel or the oil compartments to repair the engine, prime the oil and fuel systems (Ref. AMM TASK 71-00-00-860-013). CAUTION: THE HPC AND HPT ROTORS WILL HAVE IMPORTANT DAMAGE IF YOU DO NOT OBEY THE INSTRUCTION GIVEN IN THE TASK SPECIFIED BELOW. B.Before engine start refer to procedure for a bowed rotor start prevention (Ref. AMM TASK 71-00-00-700-016).
2.On ENG panel 115VU: Set the ENG/MASTER 1(2) control switch to ON.	On the lower ECAM display unit, on the ENGINE page: The symbol for the starter valve is in the open position. An automatic dry crank sequence of 30 seconds is performed.
3.On the upper ECAM display unit: Monitor the management parameters, EPR, N1, N2, EGT, FF.	30 seconds after MASTER switch ON, the A or B indication comes into view below IGN.
CAUTION: IF FUEL COMES ON AND NEITHER IGN A OR IGN B IS DISPLAYED OR NO EGT RISE WITHIN 20 SECONDS AFTER FUEL ON, INTERRUPT AUTOMATIC ENGINE START BY SELECTING ENG MASTER SWITCH TO OFF AND PROCEED WITH A MANUAL ENGINE START WITH 50 SECONDS DRY CRANK PROCEDURE. 4.Monitor the engine start:
5.On the lower ECAM display unit: Monitor the oil pressure.	At 43 percent N2 the symbol for the starter valve is in the closed position. The A or B indication goes out of view.

NOTE: During pack valves closing, the FAULT legends of the AIR COND/PACK pushbutton switches come on until the pack valves are fully closed.

CAUTION: AFTER A FAILED OR ABORTED START, IF YOU DO AN AUTOMATIC START WHEN N2 IS MORE THAN 10%, THERE IS A RISK OF EGT OVERTEMPERATURE.

CAUTION: IF YOU FAIL TO DO THE STEPS THAT FOLLOW, A HUNG START CAN BE THE RESULT.

(3) Monitor the engine start:

NOTE: If you abort a start, do a manual start for the next start.

(a) Monitor the N2 and the EGT carefully during the start for any unusual indications. Sluggish N2 acceleration is an indication of a possible hot or hung start. If this indication is accompanied by a fast increase in EGT when N2 is more than 50 percent, abort the start immediately. The EEC automatically aborts the start if there are unusual indications and N2 is less than 50 percent. The EEC also gives fault indication.
(b) If the EGT is more than the start temperature limit, shut the engine down immediately. Write down the length of the time and the highest temperature during overtemperature TSM 77-00-00-810-930 and TSM 77-00-00-810-931.
(c) Abort the start if the oil pressure does not increase.
(d) Abort the start if the fuel or ignition is accidently stopped.
(e) Monitor all the engine parameters to make a check of the automatic start procedure.
(f) Ignition automatically starts 30 seconds after the engine MASTER Switch is ON. The starter and the ignition automatically turn off at 43 percent N2.
(g) During the start sequence, if the igniter plug is defective, an automatic ground start abort occurs. The defective igniter plug is indicated by the ECAM system. During the subsequent start attempt the EEC selects the other igniter plug. If this is also defective, the ground start abort sequence again occurs and an ECAM message comes into view.
(h) Make sure that the APU rpm goes back to normal.

NOTE: Automatic dry cranking follows an aborted start.

(i) When the engine idle speed is stable , on ENG panel 115VU:
1 Set the ENG/MODE/CRANK/NORM/IGN/START selector switch to NORM.

NOTE: POST SB 31-1331 only: When the engine start sequence has ended and the engine is at or above idle (with TLA<8°): on the upper ECAM DU, "AVAIL" is displayed in green (10 seconds) on the middle of the EPR dial in order to indicate that the engine start is successful.

(4) Engine warm-up
(a) No minimum warm-up time is necessary after a usual engine shutdown if the engine is started again in less than two hours.
(b) If the engine was not operated for more than two hours, operate the engine at MIN IDLE for five minutes. This keeps thermal stresses to a minimum. The engine must be warmed-up until the oil temperature is a minimum of -10 deg.C (+14 deg.F) before you move the thrust lever forward.

5. Close-up
Subtask 71-00-00-869-184-A ** ON A/C NOT FOR ALL

A. Put the aircraft back to its initial configuration.
(1) Stop the engine (Ref. AMM TASK 71-00-00-710-018).
(2) Stop the pneumatic supply to the aircraft:
(a) Disconnect the HP ground-power unit or stop the APU.
(3) Do the Electronic Instrument System (EIS) stop procedure (Ref. AMM TASK 31-60-00-860-002).

Subtask 71-00-00-862-071-A ** ON A/C NOT FOR ALL

B. De-energize the aircraft electrical circuits. (Ref. AMM TASK 24-41-00-862-002)

[Rev.10 from 2021] 2026.04.01 04:22:00 UTC