Engine Power Assurance Test
Use this procedure to make sure that the engine will make rated takeoff thrust within the EGT and N2 speed limits when you set power to an N1 target.
Safety Precautions
(1) Review the operation limits and safety data to prepare the aircraft and engine for ground operation.
(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.
(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.
Aircraft Maintenance Configuration
(1) It is recommended that the wing and nacelle anti-ice switch is set to OFF for the test engine. The 60 percent power assurance table is calculated with the anti-icing system OFF.
(a) On the ANTI-ICE section of panel 25VU, make sure that the ANTI ICE/ENG 1(2) pushbutton switch is off (the ON legend of the ANTI ICE/ENG 1(2) pushbutton switch is off).
(2) It may be necessary to operate the engine with the anti-icing system on in the weather conditions that follow:
(a) There is moisture in the air that is rain or snow.
(b) There is moisture in the air so that you cannot see more than one mile (1.6 kilometers) because of fog.
Procedure
Find and record the power assurance data and calculate the percent N1 target as follows:
(1) Get and record the airport pressure altitude at the location of the aircraft.
(2) Get and record the Total Air Temperature (TAT) as follows:
(a) Get and record the outside TAT value displayed on the ECAM (S/D PAGE).
(b) Record the TAT and refer to the performance table only when you are ready to start the test.
(3) Use the TAT that you recorded above to find and record the power assurance targets as follows:
(b) Percent N2 speed maximum target
(c) EGT C° maximum target
(d) Fuel flow (Wf) Kg/Hr maximum flow target.
(2) Let both engines become stable for five minutes at MINIMUM IDLE.
(3) If it is necessary (because of weather conditions described above) to operate the tested engine with the anti-icing system on, you must operate the test engine as follows:
(a) On the ANTI-ICE section of panel 25VU, push the ANTI ICE/ENG 1(2) pushbutton switch (the ON legend of the ANTI ICE/ENG 1 (2) pushbutton switch comes on).
(b) During the test, the anti-icing system must be off for the last 30 seconds (the engine operation must be stable) and then you must record the engine data.
1 Push the ANTI ICE/ENG 1(2) pushbutton switch (the ON legend of the ANTI ICE/ENG 1(2) pushbutton switch is off).
2 After you record the engine data, push the ANTI ICE/ENG 1(2) pushbutton switch (the ON legend of the ANTI ICE/ENG 1(2) pushbutton switch comes on).
(4) Operate the tested engine with the engine bleed off.
(5) Operate the tested engine with the GEN loads off.
1 Release the GEN 1(2) pushbutton switch (the OFF legend comes on).
(6) Acceleration of the tested engine.
(a) Slowly accelerate the engine to the percent N1 speed target value calculated previously from the 60 percent power assurance table .
(7) Operate the engine at the percent N1 speed target value calculated previously from the 60 percent power assurance table for two minutes to let the engine become stable.
(8) After the engine becomes stable, record the data that follows:
(a) Record The EGT (degrees C)
(b) Record The percent N1 speed
(c) record The percent N2 speed
(d) Record The fuel flow (Kg/Hr).
(9) Decrease the power of the tested engine to MIN IDLE.
(10) Operate the both engines for ten minutes at MIN IDLE to decrease the engine temperatures.
(11) Do the engine shutdown procedure for the both engines.
Use the record of the engine data to check for satisfactory engine performance to the 60 percent power assurance table.
(1) The tolerances in the 60 percent power assurance table allow for the differences that follow:
(a) The difference in performance between one engine and other engine
(b) The difference in engine performance caused by initially worn engine parts (initial performance deterioration)
(c) The difference caused by humidity in the air.
(2) The 60 percent power assurance table is satisfactory from 0 ft. (0.00 m) to 10000 ft. (3047.94 m).
(3) For the fuel flow (Wf), you must subtract 100 Kg/Hr for each 1000 ft. (304.79 m) increase of altitude above sea level from the values shown in the 60 percent power assurance table.
(4) For the EGT, you must add 5.0 °C EGT for each 1000 ft. (304.79 m) increase of altitude above sea level to the values shown in the 60 percent power assurance table.
(5) If the recorded percent N1 at Para. 4.C.(8) is above the target percent N1 calculated at Para. 4.B., increase the limits (for N2, Wf and EGT) for every one percent N1 above the percent N1 target by the increments which follow:
(a) 0.4 percent delta for N2
(b) 53 Kg/Hr delta for the fuel flow (Wf)
(c) 8.0 degrees C delta for the EGT.
(6) Decrease the limits for every one percent N1 below the percent N1 target by the increments that follow:
(a) 0.4 percent delta for N2
(b) 53 Kg/Hr delta for the fuel flow (Wf)
(c) 8.0 degrees C delta for the EGT.
(7) To make sure that the engine is in the limits at takeoff power, the engine data (EGT, N2 speed) at the target N1 speed must be less than the maximum values of the 60 percent power assurance table.
(8) If the EGT or N2 speed are greater than the maximum values of the 60 percent power assurance table at the target N1 speed, the engine can be EGT or N2 limited at takeoff power.
This is for only training purpose of PW11 Engine.
Credit : Rabindar Singh
Sharing is Caring
Safety Precautions
(1) Review the operation limits and safety data to prepare the aircraft and engine for ground operation.
(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.
(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.
Aircraft Maintenance Configuration
(1) It is recommended that the wing and nacelle anti-ice switch is set to OFF for the test engine. The 60 percent power assurance table is calculated with the anti-icing system OFF.
(a) On the ANTI-ICE section of panel 25VU, make sure that the ANTI ICE/ENG 1(2) pushbutton switch is off (the ON legend of the ANTI ICE/ENG 1(2) pushbutton switch is off).
(2) It may be necessary to operate the engine with the anti-icing system on in the weather conditions that follow:
(a) There is moisture in the air that is rain or snow.
(b) There is moisture in the air so that you cannot see more than one mile (1.6 kilometers) because of fog.
Procedure
Find and record the power assurance data and calculate the percent N1 target as follows:
(1) Get and record the airport pressure altitude at the location of the aircraft.
(2) Get and record the Total Air Temperature (TAT) as follows:
(a) Get and record the outside TAT value displayed on the ECAM (S/D PAGE).
(b) Record the TAT and refer to the performance table only when you are ready to start the test.
(3) Use the TAT that you recorded above to find and record the power assurance targets as follows:
NOTE: The 60 percent power assurance table in these figures are applicable from 0 ft. (0.00 m) to 10000 ft. (3047.94 m) altitude.
(a) Percent N1 speed target (b) Percent N2 speed maximum target
(c) EGT C° maximum target
(d) Fuel flow (Wf) Kg/Hr maximum flow target.
NOTE: It is necessary in this test that the engine on the opposite wing location be operated at the same time to give full hydraulic system redundancy.
The opposite wing engine is operated at IDLE.
(1) Start the engine to be tested and the opposite engine and set the power to IDLE in order to get full hydraulic system redundancy (Ref. AMM TASK 71-00-00-860-822) or (Ref. AMM TASK 71-00-00-860-823). The opposite wing engine is operated at IDLE.
(2) Let both engines become stable for five minutes at MINIMUM IDLE.
(3) If it is necessary (because of weather conditions described above) to operate the tested engine with the anti-icing system on, you must operate the test engine as follows:
(a) On the ANTI-ICE section of panel 25VU, push the ANTI ICE/ENG 1(2) pushbutton switch (the ON legend of the ANTI ICE/ENG 1 (2) pushbutton switch comes on).
(b) During the test, the anti-icing system must be off for the last 30 seconds (the engine operation must be stable) and then you must record the engine data.
1 Push the ANTI ICE/ENG 1(2) pushbutton switch (the ON legend of the ANTI ICE/ENG 1(2) pushbutton switch is off).
2 After you record the engine data, push the ANTI ICE/ENG 1(2) pushbutton switch (the ON legend of the ANTI ICE/ENG 1(2) pushbutton switch comes on).
(4) Operate the tested engine with the engine bleed off.
NOTE: The 60 percent power assurance table is calculated with the engine bleed off.
(a) On AIR COND panel 30VU, make sure that the ENG 1(2) BLEED pushbutton switch is off (the OFF legend of the ENG 1(2) BLEED pushbutton switch is on). (5) Operate the tested engine with the GEN loads off.
NOTE: The 60 percent power assurance table is calculated with the GEN loads off.
(a) On ELEC panel 35VU: 1 Release the GEN 1(2) pushbutton switch (the OFF legend comes on).
(6) Acceleration of the tested engine.
(a) Slowly accelerate the engine to the percent N1 speed target value calculated previously from the 60 percent power assurance table .
(7) Operate the engine at the percent N1 speed target value calculated previously from the 60 percent power assurance table for two minutes to let the engine become stable.
(8) After the engine becomes stable, record the data that follows:
(a) Record The EGT (degrees C)
(b) Record The percent N1 speed
(c) record The percent N2 speed
(d) Record The fuel flow (Kg/Hr).
(9) Decrease the power of the tested engine to MIN IDLE.
(10) Operate the both engines for ten minutes at MIN IDLE to decrease the engine temperatures.
(11) Do the engine shutdown procedure for the both engines.
Use the record of the engine data to check for satisfactory engine performance to the 60 percent power assurance table.
(1) The tolerances in the 60 percent power assurance table allow for the differences that follow:
(a) The difference in performance between one engine and other engine
(b) The difference in engine performance caused by initially worn engine parts (initial performance deterioration)
(c) The difference caused by humidity in the air.
(2) The 60 percent power assurance table is satisfactory from 0 ft. (0.00 m) to 10000 ft. (3047.94 m).
(3) For the fuel flow (Wf), you must subtract 100 Kg/Hr for each 1000 ft. (304.79 m) increase of altitude above sea level from the values shown in the 60 percent power assurance table.
(4) For the EGT, you must add 5.0 °C EGT for each 1000 ft. (304.79 m) increase of altitude above sea level to the values shown in the 60 percent power assurance table.
(5) If the recorded percent N1 at Para. 4.C.(8) is above the target percent N1 calculated at Para. 4.B., increase the limits (for N2, Wf and EGT) for every one percent N1 above the percent N1 target by the increments which follow:
(a) 0.4 percent delta for N2
(b) 53 Kg/Hr delta for the fuel flow (Wf)
(c) 8.0 degrees C delta for the EGT.
(6) Decrease the limits for every one percent N1 below the percent N1 target by the increments that follow:
(a) 0.4 percent delta for N2
(b) 53 Kg/Hr delta for the fuel flow (Wf)
(c) 8.0 degrees C delta for the EGT.
(7) To make sure that the engine is in the limits at takeoff power, the engine data (EGT, N2 speed) at the target N1 speed must be less than the maximum values of the 60 percent power assurance table.
(8) If the EGT or N2 speed are greater than the maximum values of the 60 percent power assurance table at the target N1 speed, the engine can be EGT or N2 limited at takeoff power.
This is for only training purpose of PW11 Engine.
Credit : Rabindar Singh
Sharing is Caring
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