Test No. 4 - Power Acceleration/Deceleration Test [PW11]

TASK 71-00-00-710-805-A
Test No. 4 - Power Acceleration/Deceleration Test

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

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

ZONE: 400

1. Reason for the Job
Use this procedure to check for correct engine acceleration and deceleration operation within the permitted time limits.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

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

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
400	POWER PLANT, NACELLES AND PYLONS

C. Referenced Information

REFERENCE	DESIGNATION
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 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
TASK 71-00-00-710-806-A	Power Assurance Test
TASK 71-00-00-860-814-A	Shutdown of the Engine
TASK 71-00-00-860-822-A	Start the Engine (Normal Manual Start)
TASK 71-00-00-860-823-A	Start the Engine (Normal Automatic Start)
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
Tool Installation
Approach Idle Target Speed Table - PNs PW1124-JM, PW1127G-JM, PW1124G1-JM, PW1122G-JM, PW1127G1-JM and PW1127GA-JM
MTO Target N1 Speed Table - PNs PW1124-JM, PW1127G-JM, PW1124G1-JM, PW1122G-JM, PW1127G1-JM and PW1127GA-JM
Calculation of N1 Target Values for PNs PW1124-JM, PW1127G-JM, PW1124G1-JM, PW1122G-JM, PW1127G1-JM and PW1127GA-JM
Approach Idle Target Speed Table - PNs PW1130G-JM, PW1133G-JM and PW1133GA-JM
MTO Target N1 Speed Table - PNs PW1130G-JM, PW1133G-JM and PW1133GA-JM
Calculation of N1 Target Value for PNs PW1130G-JM, PW1133G-JM and PW1133GA-JM

3. Job Set-up
Subtask 71-00-00-941-130-A ** ON A/C NOT FOR ALL

A. Safety Precautions
(1) Review the operation limits and safety data to prepare the aircraft and engine for ground operation (Ref. AMM TASK 71-00-00-910-804) and (Ref. AMM TASK 71-00-00-910-803).

NOTE: This procedure can be performed at an ambient temperature range of -65 deg.F (-54 deg.C) to 127 deg.F (53 deg.C) and a test site altitude range of -2000 ft. (-610 m) to 15100 ft. (4602 m).

NOTE: Steady state high power engine operation greater than 60% N1 is not recommended without an inlet conditioning device such as a ramp, inlet grate or vortex destroyer. This procedure can be run without an inlet conditioning device as long as the engine does not dwell at over 60% N1.

(2) Make sure that the aircraft is pointed into the wind for the power acceleration/deceleration test:
(a) Do a check and monitor for cross winds during the acceleration/deceleration test.
(b) Obey the wind direction and velocity operational limits (Ref. AMM TASK 71-00-00-910-803).
(3) There must be two qualified persons in the cockpit when performing an engine run. One must monitor the outside and the aircraft behavior while the other performs the engine test.
(4) If the aircraft begins to move while performing an engine run, immediately set all the thrust levers to the IDLE position.

Subtask 71-00-00-865-192-A ** ON A/C NOT FOR ALL

CAUTION: DO NOT OPEN LGCIU CIRCUIT BREAKERS 1GA, 2GA AND 52GA. IF YOU DO THIS, AIRCRAFT BRAKING THROUGH BRAKE PEDALS DOES NOT OPERATE.

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	L/G/LGCIU/SYS1/NORM	1GA	C09
121VU	HYDRAULIC/LGCIU/SYS2	2GA	Q35
121VU	HYDRAULIC/LGCIU/SYS1/GRND SPLY	52GA	Q34

Subtask 71-00-00-860-201-A ** ON A/C NOT FOR ALL

C. Aircraft Maintenance Configuration
(1) Set the nacelle anti-ice switch to OFF for the engine test.
(2) Set the nacelle anti-ice switch to ON for the engine test when either of the following weather conditions exist, if necessary:
(a) Rain or snow is present.
(b) Fog is present that limits visibility to no more than one mile (1.6 kilometers).
(3) On AIR COND panel 30VU, push the ENG 1(2) BLEED pushbutton-switch:
(a) The OFF legend comes into view.
(4) On ELEC panel 35VU, push the GEN 1(2) pushbutton switch:
(a) The OFF legend comes into view.
(5) On the landing gear control and indicating panel 402VU:

Make sure that the A/SKID & N/WSTRG selector switch 5GG is ON.

(6) On RUD TRIM/PARKING BRK panel 110VU:

Make sure that the parking brake control-switch is set to ON.

(7) Put the wheel chock in position:

CAUTION: MAKE SURE THAT THE AIRCRAFT IS PARKED ON A CLEAN, DRY AND FLAT SURFACE. THERE MUST BE NO OIL, GREASE OR SIMILAR MATERIALS ON THE SURFACE. THE PAVEMENT MUST NOT BE BROKEN OR LOOSE, AND WE RECOMMEND CONCRETE MATERIAL BECAUSE ASPHALT CAN MELT AND CAUSE DAMAGE TO THE AIRCRAFT.

(a) If necessary, remove the ice and the snow from the surface.
(b) Put in position the wheel 98F10103500000 CHOCK-MLG,ENGINE RUN-UP at each forward outboard Main Landing Gear (MLG) wheel.

Tool Installation ** ON A/C NOT FOR ALL

(8) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(9) Do the Electronic Instrument System (EIS) start procedure (Ref. AMM TASK 31-60-00-860-001).
(10) 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.
(11) Make sure there is the necessary fuel quantity in the inner tanks.

NOTE: When the tested engine operates above N1=70 percent (not tested engine at N1=50%), make sure that a total of 6614 lb (3000.06 kg) (minimum) of fuel are in the inner tanks.

NOTE: This minimum fuel quantity does not include the fuel consumption of the engines necessary to do the test. This minimum quantity must stay in the inner tanks at the end of the test.

(12) Make sure that the hydraulic pump loads are minimal for the engine test.

4. Procedure
Subtask 71-00-00-720-080-A ** ON A/C NOT FOR ALL

A. Power Acceleration/Deceleration Test

WARNING: BEFORE YOU START THE ENGINE, MAKE SURE THAT:

YOU OBEY ALL THE ENGINE SAFETY PRECAUTIONS
YOU DO ALL THE OPERATIONS NECESSARY TO PREVENT MOVEMENT OF THE AIRCRAFT.

IF YOU DO NOT OBEY THESE PRECAUTIONS, INJURY TO THE PERSONNEL AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT CAN OCCUR.

CAUTION: IF AN ENGINE DOES A SURGE DURING THIS TEST, YOU MUST MOVE THE THRUST LEVER TO A MINIMUM IDLE IN ONE SECOND OR LESS OF THE SURGE. OPERATE THE ENGINE AT MINIMUM IDLE FOR FIVE MINUTES IF THERE IS NO EGT OVERTEMPERATURE. IF THERE IS AN EGT OVERTEMPERATURE, DO AN EMERGENCY SHUTDOWN AND DRY-MOTOR THE ENGINE UNTIL THE EGT IS LESS THAN 356 DEGREES FAHRENHEIT (180 DEGREES CELSIUS) OR FOR FOUR MINUTES, WHICHEVER COMES FIRST.

(1) Start the two engines by the automatic start procedure (Ref. AMM TASK 71-00-00-860-823).

NOTE: This is the recommended start method for normal conditions.

(2) As an alternate procedure, start the two engines by the manual start procedure (Ref. AMM TASK 71-00-00-860-822).

NOTE: This is the recommended start procedure with a low starter air pressure supply (external pneumatic power source).

(3) Let the two engines become stable for five minutes at MIN IDLE.
(4) Check that all the parameters of the two engines are within the permitted limits (Ref. AMM TASK 71-00-00-910-803).
(5) When the operation of the tested engine with the anti-icing system set to ON is necessary, proceed as follows:
(a) On the ANTI ICE section of panel 25VU:
1 Turn the anti-icing system off for the last 30 seconds before the acceleration and deceleration test.

NOTE: The engine operation must be stable.

2 Turn the anti-icing system on after the acceleration and deceleration tests.
(6) Perform the power assurance test (Ref. AMM TASK 71-00-00-710-806).

NOTE: The airport altitude (ft) and the outside air temperature (°C) must be recorded.

(7) Check that the engine operation is within the normal operational limits.
(8) Slowly move the thrust lever back to MIN IDLE.
(9) Find the approach idle N1 target, snap accel N1 target and 90 percent N1 decay target.

Calculation of N1 Target Values for PNs PW1124-JM, PW1127G-JM, PW1124G1-JM, PW1122G-JM, PW1127G1-JM and PW1127GA-JM ** ON A/C NOT FOR ALL

Calculation of N1 Target Value for PNs PW1130G-JM, PW1133G-JM and PW1133GA-JM ** ON A/C NOT FOR ALL

(10) Do an engine acceleration and deceleration test for the PW1124-JM, PW1127G-JM, PW1124G1-JM, PW1122G-JM, PW1127G1-JM and PW1127GA-JM as follows:

Approach Idle Target Speed Table - PNs PW1124-JM, PW1127G-JM, PW1124G1-JM, PW1122G-JM, PW1127G1-JM and PW1127GA-JM ** ON A/C NOT FOR ALL

MTO Target N1 Speed Table - PNs PW1124-JM, PW1127G-JM, PW1124G1-JM, PW1122G-JM, PW1127G1-JM and PW1127GA-JM ** ON A/C NOT FOR ALL

(a) For the tested engine, slowly increase the throttle until N1 is at the APPROACH IDLE target N1.
(b) Operate the tested engine at APPROACH IDLE for 15 minutes to make the engine thermally stable.
(c) For the NOT tested engine, slowly increase the throttle until N1 is at 50 percent.
(d) Before the performance of the snap acceleration test, get the STOPWATCH (or equivalent) and be aware of the timed acceleration N1 target calculation determined in step 4.A.(9).
(e) Push and hold the brake pedals at the full limit position.
(f) On RUD TRIM/PARKING BRK panel 110VU:
1 Make sure that the parking brake control switch is set to ON.
(g) Perform the snap acceleration test by a quick movement of the thrust lever (one second or less) from the APPROACH IDLE to TAKEOFF.

NOTE: Do not dwell at speeds over 60 percent N1.

(h) Record the snap acceleration time for the APPROACH IDLE target to Snap Accel N1 target speed with the STOPWATCH (or equivalent).
(i) Check the snap acceleration time limit:
1 For an altitude of less than 2000 ft. (610 m), the snap acceleration time must be less than 11.5 seconds.
2 For an altitude at or above 2000 ft. (610 m), the snap acceleration time (in seconds) must be less than this calculation: (11.5 + (altitude - 2000)/1250).
(j) After reaching the TAKEOFF power, perform the snap deceleration test by a quick movement of the thrust lever (one second or less) from TAKEOFF to MIN IDLE.
(k) Record the snap deceleration time from TAKEOFF speed to 90 percent N1 decay target speed with the STOPWATCH (or equivalent).
(l) Check the snap deceleration time limit:
1 For an altitude of less than 2000 ft. (610 m), the snap deceleration time must be less than 13.5 seconds.
2 For an altitude at or above 2000 ft. (610 m), the snap deceleration time (in seconds) must be less than this calculation: (13.5 + (altitude - 2000)/3200).
3 For an altitude at or above 10000 ft. (3048 m), the time must be less than 16 seconds.
(m) For an engine which does not require test, slowly move the thrust lever to MIN IDLE.
(n) Release the brake pedals.
(o) Let the two engines become stable for ten minutes at MIN IDLE.
(11) Do an engine acceleration and deceleration test for the PW1130G-JM, PW1133G-JM and PW1133GA-JM as follows:

Approach Idle Target Speed Table - PNs PW1130G-JM, PW1133G-JM and PW1133GA-JM ** ON A/C NOT FOR ALL

MTO Target N1 Speed Table - PNs PW1130G-JM, PW1133G-JM and PW1133GA-JM ** ON A/C NOT FOR ALL

(a) For the test engine, slowly increase the throttle until N1 is at the APPROACH IDLE target N1.
(b) Operate the tested engine at APPROACH IDLE for 15 minutes to make the engine thermally stable.
(c) For the NOT tested engine, slowly increase the throttle until N1 is at 50 percent.
(d) Before the performance of the snap acceleration test, get the STOPWATCH (or equivalent) and be aware of timed acceleration N1 target calculation determined in step 4.A.(9).
(e) Push and hold the brake pedals at the full limit position.
(f) On the RUD TRIM/PARKING BRK panel 110VU:
1 Make sure that the parking brake control switch is set to ON.
(g) Perform the snap acceleration test by a quick movement of the thrust lever (one second or less) from the APPROACH IDLE to TAKEOFF.

NOTE: Do not dwell at speeds over 60 percent N1.

(h) Record the snap acceleration time for the APPROACH IDLE target to Snap Accel N1 target speed with the STOPWATCH (or equivalent).
(i) Check the snap acceleration time limit:
1 For an altitude between -2000 ft. (-609.59 m) and 1999 ft. (609.28 m), the snap acceleration time must be less than 12 seconds.
2 For an altitude between 2000 ft. (609.59 m) and 9999 ft. (3047.64 m), the snap acceleration time (in seconds) must be less than this calculation: (9.75 + 1.125 (altitude/1000)).
3 For an altitude between 10000 ft. (3047.94 m) and 15100 ft. (4602.40 m), the snap acceleration time (in seconds) must be less than this calculation: (17 + (altitude/2500)).
(j) After reaching the TAKEOFF power, perform the snap deceleration test by a quick movement of the thrust lever (one second or less) from TAKEOFF to MIN IDLE.
(k) Record the snap deceleration time from TAKEOFF speed to 90 percent N1 Decay Target Speed with the STOPWATCH (or equivalent).
(l) Check the snap deceleration time limit:
1 For an altitude between -2000 ft. (-609.59 m) and 1999 ft. (609.28 m), the snap deceleration time must be less than 11.5 seconds.
2 For an altitude between 2000 ft. (609.59 m) and 15100 ft. (4602.40 m), the snap deceleration time (in seconds) must be less than this calculation: (11.5 + (altitude - 2000)/3250).
(m) For an engine which does not require test, slowly move the thrust lever to MIN IDLE.
(n) Release the brake pedals.
(o) Let the two engines become stable for ten minutes at MIN IDLE.
(12) Perform the shutdown of the two engines (Ref. AMM TASK 71-00-00-860-814).
(13) Record the acceleration and deceleration times in the engine final log.

5. Close-up
Subtask 71-00-00-860-202-A ** ON A/C NOT FOR ALL

A. Put the aircraft back to its initial configuration.
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002).
(3) If necessary, set nacelle anti-ice switch to OFF.
(4) On the AIR COND panel 30VU:

Release the ENG 1(2) BLEED pushbutton switch (the OFF legend goes off).

(5) On the ELEC panel 35VU:

Release the GEN 1(2) pushbutton switch (the OFF legend goes off).

(6) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(7) Remove the wheel 98F10103500000 CHOCK-MLG,ENGINE RUN-UP.

[Rev.10 from 2021] 2026.04.01 02:31:38 UTC