Start the Engine (Normal Automatic Start) [PW11]

TASK 71-00-00-860-823-A
Start the Engine (Normal Automatic Start)

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE AFTER SHUTDOWN. THE ENGINE CAN STAY HOT FOR A LONG TIME. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY CAN OCCUR.

WARNING: MAKE SURE THAT ALL ENGINE-IN-OPERATION AREAS (RAMPS, TAXIWAYS, RUNWAYS, ETC.) ARE SUFFICIENTLY CLEAN TO PREVENT INJURY TO THE PERSONS IN THE AREA AND DAMAGE TO THE ENGINE OR AIRCRAFT.

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

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 AT POWER SETTINGS ABOVE IDLE, 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 VALVES ARE 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 BAD INJURY OR DEATH, AND - THERE CAN BE DAMAGE TO THE AIRCRAFT.

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: 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 PW GENERAL WARNINGS AND CAUTIONS AND RELATED SAFETY DATA REF. AMM 71-00-00-910-804-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.

ZONE: 210
ZONE: 400

1. Reason for the Job
Use this procedure to start the engine automatically.

NOTE: During a motoring sequence on the ground, the Electronic Engine Control (EEC) automatically determines if motoring to start is required for BOWED ROTOR PROTECTION. The EEC keeps the N2 speed at a low value (approximately 10% N2) for a calculated duration based on time since shutdown, Outside Air Temperature (OAT) and engine turbine temperature. During motoring to start, a "COOLING" indication is displayed on the upper ECAM display unit. When the motoring to start period is complete, the EEC will continue to normal engine start. If N2 exceeds the maximum speed for BOWED ROTOR PROTECTION during motoring to start, the EEC will abort the motoring and the warning ENG X START FAULT (BOWED ROTOR PROTECTION) will be displayed.

For more information about the power plant, refer to 71-00-00-00 CONF 21 - POWER PLANT - GENERAL - DESCRIPTION AND OPERATION.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	AR	COVER - PROTECTION
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
400	POWER PLANT, NACELLES AND PYLONS

C. Referenced Information

REFERENCE	DESIGNATION
TASK 10-11-00-555-014-A	Removal of the Aircraft Protection Equipment
TASK 12-13-79-612-803-A	Engine Oil Servicing
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 26-12-00-710-001-A	Operational Check of Loop/Squib
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 36-12-00-860-802-A	Pressurization of the Bleed System with the APU
TASK 36-12-00-860-803-A	Pressurization of the Bleed System through the HP Ground Connector
TASK 71-00-00-660-803-A	Prepare the Engine for Cold Weather after Shutdown
TASK 71-00-00-860-814-A	Shutdown of the Engine
TASK 71-00-00-860-817-A	Motor the Engine (Dry Method)
TASK 71-00-00-860-818-A	Operate the Engine after Exhaust Gas Temperature (EGT) Overtemperature (No Surge or Stall)
TASK 71-00-00-860-819-A	Operate the Engine after Engine Surge or Stall
TASK 71-00-00-860-820-A	Operate the Engine after Exhaust Gas Temperature (EGT) Overtemperature (with Surge or Stall)
TASK 71-00-00-910-803-A	Engine Operation Limits and Guidelines
TASK 71-00-00-910-804-A	General Warnings and Cautions and Related Safety Data
TASK 72-00-00-200-809-A	Inspection of the Engine (After Surge or Stall)
TASK 80-11-00-040-803-A	Starter Air Control Valve Manual Override
Tool Installation
Cockpit Controls and Panels

3. Job Set-up
Subtask 71-00-00-210-102-A ** ON A/C NOT FOR ALL

A. Examine the following:

CAUTION: WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE.

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).

CAUTION: REMOVE AND INSTALL PROTECTION COVERS AS NECESSARY TO PREVENT DAMAGE TO THE ENGINE AND ADJACENT COMPONENTS.

(2) Make sure that you remove and install the COVER - PROTECTION as necessary to prevent damage to the engine.
(3) Make sure that all parts, tools, equipment and loose objects are removed from the engine air intake and the area around the intake.
(4) In cold weather, do a visual check for damage or ice on the fan inlet, the fan blades, inlet cone (spinner), fan case rubstrip and acoustic panels, T2 probe and external cowl surfaces (Ref. AMM TASK 71-00-00-660-803).
(a) If you find ice on these parts, you must thaw the engine with hot air.
(b) Turn the fan clockwise as seen from the rear (normal operation). If the fan is accidentally turned counterclockwise, there can be some resistance. This condition is permitted, but do not continue to turn the fan in the counterclockwise (incorrect) direction.
(c) After the engine is thawed, make sure that the fan rotor turns freely.
(5) Do a visual check of the turbine exhaust system, exhaust nozzle assembly and the forward and aft centerbody assembly for damage and unwanted material.
(6) Do a check of the drain ports for fuel, oil and hydraulic leaks.
(7) Make sure that the aircraft is cleared and that there are no persons in the dangerous areas (Ref. AMM TASK 71-00-00-910-804).
(8) Do a check of the wind direction. A tail wind can prevent an easy start. If necessary, move the aircraft toward the wind. Obey the wind direction and velocity operational limits (Ref. AMM TASK 71-00-00-910-803) and (Ref. AMM TASK 71-00-00-910-804).

Subtask 71-00-00-861-108-A ** ON A/C NOT FOR ALL

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

Subtask 71-00-00-865-174-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: 4020KM1 (POWER PLANTDEMOUNTABLE, ENG 1)
49VU	FUEL/LP VALVE/MOT1/ENG1	1QG	A08
49VU	ENGINE/1/FADEC A/AND EIU 1	2KS1	A04
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG1/FADEC B/AND EIU 1	4KS1	R41
** ON A/C NOT FOR ALL
121VU	OIL/PRESS/ENG1	10KC1	N40
121VU	ENGINE/IGN/ENG1/SYS B	3JH1	P41
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG1/FADEC B/AND EIU 1	4KS1	R40
** ON A/C NOT FOR ALL
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENG 2)
49VU	FUEL/LP VALVE/MOT1/ENG2	2QG	A09
49VU	ENGINE/2/FADEC A/AND EIU 2	2KS2	A05
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG2/FADEC B/AND EIU2	4KS2	Q40
** ON A/C NOT FOR ALL
121VU	OIL/PRESS/ENG2	10KC2	N42
121VU	ENGINE/IGN/ENG2/SYS B	3JH2	P42
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG2/FADEC B/AND EIU2	4KS2	R41

Subtask 71-00-00-860-207-A ** ON A/C NOT FOR ALL

D. Aircraft Maintenance Configuration
(1) Do the Electronic Instrument System (EIS) start procedure (ECAM display units only) (Ref. AMM TASK 31-60-00-860-001).
(2) Make sure that the hydraulic system is serviceable:

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) On the lower ECAM display unit, get the HYD page:
1 Make sure that the pressure of the Green reservoir for the engine 1 (Yellow reservoir for the engine 2) is correct.
2 Make sure that the reservoir fluid level is correct (Ref. AMM TASK 29-30-00-200-002).
(b) On the HYD section of overhead panel 40VU:
1 Make sure that the engine 1(2) pump is serviceable (the OFF legend of the ENG 1(2) PUMP pushbutton switch must be off).
(3) Make sure that the fuel system is serviceable:
(a) On the lower ECAM display unit, get the FUEL page:
1 Make sure that there is the correct quantity of fuel in the fuel tanks to run the engine.
(4) On the ENG section of maintenance panel 50VU:
(a) Release the FADEC GND PWR/1(2) pushbutton switch (the ON legend comes on).
(5) Make sure that the engine oil system is serviceable:
(a) On the lower ECAM display unit, get the ENGINE page:
1 Make sure that there is the correct quantity of oil to run the engine.
(b) If necessary, do the servicing of the engine oil system (Ref. AMM TASK 12-13-79-612-803).
(6) On the ENG section of maintenance panel 50VU:
(a) Push the FADEC GND PWR/1(2) pushbutton switch (the ON legend goes off).
(7) On the FUEL section of overhead panel 40VU:
(a) Push all the PUMPS pushbutton switches.
(b) Make sure that the OFF legend of these pushbutton switches goes off.
(8) Supply the aircraft pneumatic system from a High Pressure (HP) ground power unit or the Auxiliary Power Unit (APU) (Ref. AMM TASK 36-12-00-860-802) or (Ref. AMM TASK 36-12-00-860-803).

NOTE: The minimum recommended starter air supply pressure is 25 psi (1.72 bar), when the start valve is open. Two external pneumatic power units may be used in parallel, if the pressure/flow relation is expected to be marginal.

(9) On the overhead control and indicating panel 25VU:
(a) Set the EXT LT/BEACON switch to ON position.
(10) Make sure that the TRHUST LEVERS are set to IDLE.
(11) On the center pedestal, on ENG panel 115VU:
(a) Make sure that the ENG/MASTER 1(2) control switch is in the OFF position.
(b) Make sure that the ENG/MODE selector switch is in the NORM position.
(12) On the ENG section of the overhead control and indicating panel 22VU:
(a) Make sure that the MAN START 1(2) switch is set to OFF.

WARNING: BEFORE YOU START THE ENGINE, MAKE SURE THAT THE DUAL COOLING PUSHBUTTON SWITCH IS IN THE OFF POSITION. IF YOU DO NOT OBEY THIS INSTRUCTION, THE OPPOSITE ENGINE WILL RUN AND THIS CAN CAUSE INJURIES TO PERSONS.

(13) Make sure that the DUAL COOLING pushbutton switch is in the OFF position.

Subtask 71-00-00-941-132-A ** ON A/C NOT FOR ALL

E. Safety Precautions
(1) Make sure that the interphone system is fully serviceable.
(2) Make sure that the wheel chocks are in position in front of each forward outboard Main Landing Gear (MLG) wheel.
(3) If engine start is followed by a power run above idle, use 98F10103500000 CHOCK-MLG,ENGINE RUN-UP.

Tool Installation ** ON A/C NOT FOR ALL

(4) On the center pedestal:
(a) On RUD TRIM/PARKING BRK panel 110VU, make sure that the parking-brake control switch is set to ON.
(b) Make sure that the engine thrust lever 1(2) is in the IDLE stop position (zero on the graduated sector).
(5) On right-center instrument panel 400VU:
(a) Make sure that the pressure indication on the Yellow brake-pressure triple-indicator is correct.
(b) If necessary, pressurize the brake accumulator with the Yellow pump (Ref. AMM TASK 29-10-00-863-002)
(6) Do the operational test of the engine fire and overheat detection (loop/squib) (Ref. AMM TASK 26-12-00-710-001).
(7) Make sure that you obey your local fire-fighting regulations.
(8) Make sure that all doors are closed and that aircraft is cleared of unnecessary ground support and/or loading equipment.
(9) Make sure that there are no persons in the dangerous areas (Ref. AMM TASK 71-00-00-910-804).

4. Procedure
Subtask 71-00-00-869-354-A ** ON A/C NOT FOR ALL

A. General
(1) Do each step of the procedure in the sequence shown. If you abort the start, you must do each step of the sequence again.
(2) During the start, keep the service air bleed inputs and the accessory loads to a minimum.

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.

(3) If a tail wind prevents an easy start, move the aircraft toward the wind. Obey the wind direction and velocity operational limits (Ref. AMM TASK 71-00-00-910-804).

Subtask 71-00-00-860-208-A ** ON A/C NOT FOR ALL

WARNING: ALWAYS PUT THE ENG/MASTER SWITCH BACK IN THE "OFF" POSITION AFTER AN ABORT OF THE START SEQUENCE. IF YOU ONLY CHANGE THE POSITION OF THE ENG/MODE SWITCH (FROM "IGN/START" TO "NORM"), THE FADEC SYSTEM WILL NOT COMPLETE THE ABORT. IF YOU DO NOT OBEY THIS INSTRUCTION, THE ENGINE CAN START AND THIS CAN CAUSE INJURIES TO PERSONS.

WARNING: SET THE THRUST LEVERS TO IDLE BEFORE YOU START THE ENGINE. IF YOU DO NOT DO THIS, THE THRUST LEVEL WILL RAPIDLY INCREASE AND CAN CAUSE DANGEROUS CONDITIONS.

CAUTION: ALWAYS PUT THE ENG/MASTER SWITCH BACK IN THE "OFF" POSITION BEFORE YOU START THE ENGINE. IF YOU DO NOT OBEY THIS INSTRUCTION, A HOT OR HUNG START CAN BE THE RESULT.

CAUTION: YOU MUST DO ALL OF THE STEPS IN THE START PROCEDURE THAT FOLLOWS IN THE CORRECT SEQUENCE. IF YOU DO NOT OBEY THIS INSTRUCTION, A HOT OR HUNG START CAN BE THE RESULT.

CAUTION: BEFORE YOU START THE ENGINE RUN OPERATIONS, MAKE SURE THAT ALL PYLON PANELS INCLUDED IN THE THRUST-REVERSER FIRE-SEAL LANDING ARE INSTALLED. IF ALL PYLON PANELS ARE NOT INSTALLED, THE THRUST-REVERSER FIRE SEAL WILL NOT OPERATE CORRECTLY.

B. Do the engine start as follows:

ACTION	RESULT
1.On the center pedestal, on ENG panel 115VU: Set the ENG/MODE selector switch to IGN/START.	On the lower ECAM display unit: The ENGINE page comes into view. . Make sure that the starter air supply pressure is available. NOTE: The engine alerts and the warnings should be cleared prior to starting.
2.On the center pedestal, on ENG panel 115VU: Set the ENG MASTER 1(2) control switch (for engine to be started) to ON.	Make sure that: The symbol for the starter valve opens. Do not set the ENG MASTER 1(2) control switch to ON before all the amber crosses and the messages have disappeared on the upper ECAM display unit.
3.Monitor the lower and the upper ECAM display units during the start for the usual engine parameters.	Make sure that N2 increases. Make sure the related start valve in line on the ECAM lower display valve (Ref. AMM TASK 80-11-00-040-803). . You can then continue the auto start procedure. Make sure that the bleed pressure indication is green on the ECAM lower display. Make sure that the engine oil pressure increases. At 18% N2, make sure the active igniter (A or B) indication comes into view adjacent to IGN on the ECAM lower display. NOTE: The activation speed varies with the ambient temperature and the start air supply pressure. The Fuel Flow (FF) increases. NOTE: The normal starting FF for the PW1100G-JM series engine is approximately 200 Pounds Per Hour (PPH) or 91 Kilograms Per Hour (KPH) at all field elevations. Once the normal idle is achieved, a FF of approximately 500 PPH (227 KPH) is acceptable. Within 20 seconds of the FF increase: . The Exhaust Gas Temperature (EGT) increases on the ECAM upper display. . N1 increases prior to 48% N2 on the ECAM upper display. At approximately 55% N2: . The start valve cross line indicates valve closed on the ECAM lower display. . The active igniter indication off on the ECAM lower display.
4.Set the ECAM displays to CHECK.	Make sure that the main and the secondary engine idle parameters are normal. NOTE: The gray background on N2 indication disappears. The usual parameters at International Standard Atmosphere (ISA) sea level are as follows: . The EGT is in the range between 914 deg.F (490.00 deg.C) and 1130 deg.F (610.00 deg.C) approximately. . FF is approximately 600 PPH (270 KPH). . N1 is approximately 19%. . N2 is approximately 59%.
5.On ENG panel 115VU: Set the ENG/MODE selector switch to NORM.	You must set the ENG/MODE selector switch to NORM after the two engines are started or after one engine is started if the second engine will not be started.

Subtask 71-00-00-860-216-A ** ON A/C NOT FOR ALL

C. Unusual Condition to Stop the Start Procedure:
(1) On the Upper ECAM display, monitor the engine start and engine parameters for any unusual conditions.
(a) Monitor the engine start for no light condition, no EGT increase or N2 and N1 acceleration beyond the N2 and N1 at the starter maximum speed. The EEC will automatically do an engine start abort.
(b) Monitor the engine for slow N2 acceleration which is an indication of a possible hot or hung start. If this slow N2 indication also has a fast increase in EGT, and is near the start EGT limit, the EEC will automatically do an engine start abort.
(c) If the EGT is near the start EGT limit, the EEC will automatically do an engine start abort (Ref. AMM TASK 71-00-00-860-814) and (Ref. AMM TASK 71-00-00-860-817).
(d) If the EGT limits were exceeded, (Ref. AMM TASK 72-00-00-200-809).

NOTE: Record how much time the EGT was more than the limit and the highest temperature for subsequent analysis.

(2) The EEC will automatically abort the start if the engine parameters are out of limits.
(3) During an aborted start, the EEC will automatically engage the starter at the necessary N2 rotor speed to dry-motor the engine for 30 seconds to decrease the EGT and to remove the remaining fuel from the engine that has not burned for the conditions that follow:
(a) If there is no EGT increase (no light or combustion).
(b) If there is no acceleration (hung start).
(c) If there is high EGT during the start (hot start).
(4) During an aborted start, the EEC will not automatically engage the starter if any of the events that follow occur:
(a) N1 locked rotor. No indication of sensed N1 after sensed N2 has increased beyond 30 percent.
(b) Loss of EGT indication.
(c) Inability to control fuel flow.
(d) EEC is unable to command the igniters in either EEC channel.
(e) Failure of automatic restart or unsuccessful restart.
(5) When the engine reaches idle speed and is stable, do a check the upper and lower ECAM display as follows.
(a) Make sure that N1, N2, EGT and fuel flow are at the usual idle values.
(b) Make sure the engine oil pressure is the usual idle value.
(c) Shutdown the engine if the oil pressure is below the amber line.

NOTE: The engine should be warmed up so that the oil temperature is at or above 18 deg.F (-7.78 deg.C) prior to any operation above idle. This is to ensure adequate engine oil scavenge capability.

(6) In case of EGT overtemperature, operate the engine after an EGT overtemperature (Ref. AMM TASK 71-00-00-860-818).
(7) In case of engine surge or stall, operate the engine after an engine surge or stall (Ref. AMM TASK 71-00-00-860-819).
(8) In case of EGT overtemperature with surge or stall, operate the engine after EGT overtemperature with surge or stall (Ref. AMM TASK 71-00-00-860-820).

5. Close-up
Subtask 71-00-00-860-209-A ** ON A/C NOT FOR ALL

A. Stop the pneumatic supply to the aircraft
(1) Disconnect and remove the HP ground power unit or stop the APU (Ref. AMM TASK 36-12-00-860-802) or (Ref. AMM TASK 36-12-00-860-803).

[Rev.10 from 2021] 2026.04.01 02:31:20 UTC