DOC AIRBUS | AMM A320FEngine Operation Limits and Guidelines [PW11]
TASK 71-00-00-910-803-A
Engine Operation Limits and Guidelines
Use this procedure to determine the engine operation limits and guidelines.
2. Job Set-up Information
A. Work Zones and Access Panels
B. Referenced Information
3. Job Set-up
Subtask 71-00-00-869-355-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 03:55:29 UTC
Engine Operation Limits and Guidelines
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:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
ZONE: 400
1. Reason for the JobUse this procedure to determine the engine operation limits and guidelines.
2. Job Set-up Information
A. Work Zones and Access Panels
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 400 | POWER PLANT, NACELLES AND PYLONS |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 71-00-00-780-802-A | Test No. 13 - Main Oil Pressure Test and Adjustment |
| TASK 72-00-00-210-809-A | Visual Examination (after an Exhaust Gas Temperature (EGT) Overtemperature) |
| TASK 72-00-00-210-810-A | Inspection of the Engine after N1/N2 Over Speed Operation |
| TASK 72-00-00-210-811-A | Inspection of the Engine after Engine Oil Overtemperature |
| TASK 79-00-00-210-810-A | Visual Inspection of the Engine Oil System |
| TASK 79-00-00-281-802-A | Inspection of the Magnetic Chip Collectors for Oil Contamination |
Engine Operation Limits and Guidelines - Engine Drain LocationSubtask 71-00-00-869-355-A ** ON A/C NOT FOR ALL
A. Not Applicable
4. ProcedureCAUTION:
WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE.
Subtask 71-00-00-910-056-A ** ON A/C NOT FOR ALL A. Engine Operation Limits and Guidelines
(1) Exhaust Gas Temperature (EGT) limits - fahrenheit (celsius)
(a) Starting: 1982 deg.F (1083.33 deg.C) ground start, 1982 deg.F (1083.33 deg.C) air start.
(b) Takeoff, for up to five minutes: 1982 deg.F (1083.33 deg.C).
(c) Maximum continuous: 1909 deg.F (1042.78 deg.C).
(d) If EGT over temperature occurs at start, idle and higher power, do this procedure (Ref. AMM TASK 72-00-00-210-809).
(2) Rotor operation speed limits (redline speed limit) - RPM
(a) Maximum N1: 100 percent (10047 RPM).
(b) Maximum N2: 100 percent (22300 RPM).
(c) If the engine has operated at more than N1 or N2 redline speed limit, do this procedure (Ref. AMM TASK 72-00-00-210-810).
(3) Vibration (VIB) guidelines - cockpit units
(b) N2 rotor: VIB advisory level- 5.0
(c) Fan rotor: VIB advisory level- 5.0.
(4) Oil specifications
(5) Oil pressure limits - psi (bar)
(a) The engine main oil pressure maximum limit is 270 psi (18.62 bar) when the engine is operating at or above idle speed.
(b) The engine main oil pressure minimum limit varies with the engine N2 speed. The limit ranges from 65 psi (4.48 bar) for idle speeds 13500 N2 RPM and below, linearly increasing with N2 from 65 psi (4.48 bar) at 13500 N2 RPM to 166 psi (11.45 bar) at redline N2 RPM.
(c) If the main oil pressure is out of the limits, refer to (Ref. AMM TASK 71-00-00-780-802).
(d) When an engine operates with the main oil pressure below the minimum limit, determine the cause and perform the corrective action before you continue operation, refer to (Ref. AMM TASK 79-00-00-281-802).
(e) The indicated oil pressure can vary between the engines by as much as 45 psi (3.10 bar). This can happen when you operate at the same oil temperature and N2 speed and will be acceptable and not be an indication of an oil system malfunction.
(6) Oil temperature limits
(a) The engine main oil temperature maximum limit varies with the engine power level. The limit decreases from 305 deg.F (151.67 deg.C) at idle power, to 295 deg.F (146.11 deg.C) at cruise power and to 285 deg.F (140.56 deg.C) at high power.
(b) The engine main oil temperature minimum limit at start is -40 deg.F (-40.00 deg.C) and at takeoff is 125 deg.F (51.67 deg.C) (Ref. AMM TASK 72-00-00-210-811).
(7) Oil consumption guidelines
(a) Maximum oil consumption is 0.2 quarts (0.19 liters) per hour.
(b) If engine increases its oil consumption, do a visual inspection of the engine oil system (Ref. AMM TASK 79-00-00-210-810).
(a) The maximum engine seal leakage limits for external oil system components during engine operation and after shutdown are shown in Table 201 given below. See the figure:
Table 201 - Engine External Component Oil Seal Leakage Limits
(9) Fuel specifications
(a) Refer to SB PW1000G-D-79-00-0002-00A-930A-D for a list of approved fuels and additives for use in PW1000G-JM engines.
(10) Engine fuel leakage limits
(a) The maximum engine seal leakage limits for external fuel system components during engine operation and after shutdown are shown in Table 202 given below. See the figure:
Table 202 - Engine External Component Fuel Seal Leakage Limits
(a) The starter duty cycle is as follows:
1 Three start attempts
2 35 seconds cooling period between each start attempt
3 15 minutes cumulative cranking
4 Followed by 15 minutes minimum period when N2 speed is zero (0) RPM.
1 15 minutes maximum continuous cranking
2 Followed by 15 minutes minimum period when N2 speed is zero (0) RPM.
Subtask 71-00-00-970-068-A ** ON A/C NOT FOR ALL (1) Exhaust Gas Temperature (EGT) limits - fahrenheit (celsius)
(a) Starting: 1982 deg.F (1083.33 deg.C) ground start, 1982 deg.F (1083.33 deg.C) air start.
(b) Takeoff, for up to five minutes: 1982 deg.F (1083.33 deg.C).
(c) Maximum continuous: 1909 deg.F (1042.78 deg.C).
(d) If EGT over temperature occurs at start, idle and higher power, do this procedure (Ref. AMM TASK 72-00-00-210-809).
(2) Rotor operation speed limits (redline speed limit) - RPM
(a) Maximum N1: 100 percent (10047 RPM).
(b) Maximum N2: 100 percent (22300 RPM).
(c) If the engine has operated at more than N1 or N2 redline speed limit, do this procedure (Ref. AMM TASK 72-00-00-210-810).
(3) Vibration (VIB) guidelines - cockpit units
NOTE: High VIB levels are usual during engine start operations. If high VIB levels return to normal as the engine becomes stable at idle speed, no troubleshooting is necessary.
(a) N1 rotor: VIB advisory level- 5.0 (b) N2 rotor: VIB advisory level- 5.0
(c) Fan rotor: VIB advisory level- 5.0.
(4) Oil specifications
CAUTION:
YOU MUST ONLY USE THE ENGINE OILS SPECIFIED IN SERVICE BULLETIN PW1000G-D-79-00-0002-00A-930A-D. IT IS NOT RECOMMENDED TO MIX DIFFERENT BRANDS OF APPROVED OILS, BUT IT IS PERMITTED IN THE LIMITS SPECIFIED IN THE SERVICE BULLETIN. THE USE OF UNAPPROVED TYPES OR BRANDS OF OILS IS NOT PERMITTED AND CAN CAUSE DAMAGE TO THE ENGINE.
(a) For a list of approved engine oil brands, types and specifications, refer to oil system Service Bulletin (SB) PW1000G-D-79-00-0002-00A-930A-D. (5) Oil pressure limits - psi (bar)
(a) The engine main oil pressure maximum limit is 270 psi (18.62 bar) when the engine is operating at or above idle speed.
(b) The engine main oil pressure minimum limit varies with the engine N2 speed. The limit ranges from 65 psi (4.48 bar) for idle speeds 13500 N2 RPM and below, linearly increasing with N2 from 65 psi (4.48 bar) at 13500 N2 RPM to 166 psi (11.45 bar) at redline N2 RPM.
(c) If the main oil pressure is out of the limits, refer to (Ref. AMM TASK 71-00-00-780-802).
(d) When an engine operates with the main oil pressure below the minimum limit, determine the cause and perform the corrective action before you continue operation, refer to (Ref. AMM TASK 79-00-00-281-802).
(e) The indicated oil pressure can vary between the engines by as much as 45 psi (3.10 bar). This can happen when you operate at the same oil temperature and N2 speed and will be acceptable and not be an indication of an oil system malfunction.
(6) Oil temperature limits
(a) The engine main oil temperature maximum limit varies with the engine power level. The limit decreases from 305 deg.F (151.67 deg.C) at idle power, to 295 deg.F (146.11 deg.C) at cruise power and to 285 deg.F (140.56 deg.C) at high power.
(b) The engine main oil temperature minimum limit at start is -40 deg.F (-40.00 deg.C) and at takeoff is 125 deg.F (51.67 deg.C) (Ref. AMM TASK 72-00-00-210-811).
(7) Oil consumption guidelines
(a) Maximum oil consumption is 0.2 quarts (0.19 liters) per hour.
(b) If engine increases its oil consumption, do a visual inspection of the engine oil system (Ref. AMM TASK 79-00-00-210-810).
NOTE: The oil quantity instrument in the cockpit only shows oil quantity in the oil tank. It does not show oil quantity in the engine. After engine shutdown, oil returns to the oil tank and cockpit oil indicator shows an increase in oil quantity.
NOTE: Oil consumption is typically quite low in this engine so timely and accurate updates to engine records are necessary to evaluate engine oil condition.
(8) Engine oil leakage limits (a) The maximum engine seal leakage limits for external oil system components during engine operation and after shutdown are shown in Table 201 given below. See the figure:
Table 201 - Engine External Component Oil Seal Leakage Limits
| Component Seal Drain | Fluid | Drain Location | Leakage Limit |
|---|---|---|---|
| Integrated fuel pump and control drive seal | Oil | Drain tube (DR41) | 10cc/hour (3.3 drops/minute) |
| Hydraulic pump drive seal | Oil (engine oil) | Drain tube (DR51) (HYDRAULIC) | 10cc/hour (3.3 drops/minute) |
| Integrated Drive Generator (IDG) drive seal | Oil | Drain tube (IDG) | 10cc/hour (3.3 drops/minute) |
| Low Pressure Compressor (LPC) 2.5 bleed cavity | Oil | Drain tube (DR11) | None permitted |
| No.4 bearing compartment | Oil | No.4 scupper | None permitted |
(a) Refer to SB PW1000G-D-79-00-0002-00A-930A-D for a list of approved fuels and additives for use in PW1000G-JM engines.
(10) Engine fuel leakage limits
(a) The maximum engine seal leakage limits for external fuel system components during engine operation and after shutdown are shown in Table 202 given below. See the figure:
Table 202 - Engine External Component Fuel Seal Leakage Limits
| Component Seal Drain | Fluid | Drain Location | Leakage Limit |
|---|---|---|---|
| LPC 2.5 bleed valve actuator | Fuel | Drain tube (DR11) 2.5 BLEED | 15cc/hour (5 drops/minute) |
| LPC Variable Stator Vane Actuator (VSVA) | Fuel | Drain tube (DR01) LPC-SVA | 15cc/hour (5 drops/minute) |
| High Pressure Compressor (HPC) variable stator vane primary actuator | Fuel | Drain tube (DR21) HPC-SVA1 | 15cc/hour (5 drops/minute) |
| HPC variable stator vane secondary actuator | Fuel | Drain tube (DR22) HPC-SVA2 | 15cc/hour (5 drops/minute) |
| Integrated fuel pump and control seal | Fuel | Drain tube (DR41) FOM-FUEL | 2cc/hour (1 drop/minute) |
| Fuel ecology tank | Fuel | Vent line (FB02) | None permitted* |
NOTE: *During engine motor-to-start:
- If a steady stream of fuel is observed coming from the overboard vent in the drain mast, the engine should be shut down and restart. If a steady stream of fuel is observed during the next motor-to-start, replace the ecology tank.
- If fuel leakage is less than or equal to ten drops/minute, proceed to idle.
*Engine at idle:
- If a steady stream of fuel is observed coming from the overboard vent in the drain mast after one minute at idle, the engine should be shut down and restart. If a steady stream of fuel is observed during the next run to idle, replace the ecology tank.
- A fuel leakage rate of five drops per minute at idle is acceptable and no maintenance action is required.
*After Shutdown:
- After engine shutdown, the ecology system may overfill and result in overboard leakage out the drain mast. A fuel leakage rate of five drops per minute is acceptable under these conditions and no maintenance action is required. If leakage exceeds five drops/min, draining the ecology tank is recommended.
*Required maintenance actions if any limits above are exceeded is to replace the ecology tank (or drain the ecology tank if aircraft is at an out station where no replacement ecology tank is available).
(11) Starter operational limits - If a steady stream of fuel is observed coming from the overboard vent in the drain mast, the engine should be shut down and restart. If a steady stream of fuel is observed during the next motor-to-start, replace the ecology tank.
- If fuel leakage is less than or equal to ten drops/minute, proceed to idle.
*Engine at idle:
- If a steady stream of fuel is observed coming from the overboard vent in the drain mast after one minute at idle, the engine should be shut down and restart. If a steady stream of fuel is observed during the next run to idle, replace the ecology tank.
- A fuel leakage rate of five drops per minute at idle is acceptable and no maintenance action is required.
*After Shutdown:
- After engine shutdown, the ecology system may overfill and result in overboard leakage out the drain mast. A fuel leakage rate of five drops per minute is acceptable under these conditions and no maintenance action is required. If leakage exceeds five drops/min, draining the ecology tank is recommended.
*Required maintenance actions if any limits above are exceeded is to replace the ecology tank (or drain the ecology tank if aircraft is at an out station where no replacement ecology tank is available).
(a) The starter duty cycle is as follows:
1 Three start attempts
2 35 seconds cooling period between each start attempt
3 15 minutes cumulative cranking
4 Followed by 15 minutes minimum period when N2 speed is zero (0) RPM.
NOTE: The Electronic Engine Control (EEC) will automatically command the Starter Air Valve (SAV) closed after 15 minutes to ensure the starter duty cycle is not exceed.
(b) The extended starter duty cycle is as follows: 1 15 minutes maximum continuous cranking
2 Followed by 15 minutes minimum period when N2 speed is zero (0) RPM.
NOTE: The EEC will automatically command the SAV closed after 15 minutes to ensure the starter duty cycle is not exceed.
B. Engine Condition Monitoring
(1) The margin adjustment is calculated relative to a "realistic worst case" takeoff flight condition (EGT margin calculation point).
(2) EGT margin calculation point
Subtask 71-00-00-970-069-A ** ON A/C NOT FOR ALL (1) The margin adjustment is calculated relative to a "realistic worst case" takeoff flight condition (EGT margin calculation point).
(2) EGT margin calculation point
NOTE: These points do not show the pinch points where EGT margin is a minimum. Engines with EGT margin more than zero at the pinch point will have positive EGT margin at all maximum continuous flight conditions.
Table 203 - EGT Margin Calculation Point | | PW1127G-JM PW1127GA-JM PW1127G1-JM PW1124G-JM PW1124G1-JM PW1122G-JM | PW1133G-JM PW1133GA-JM PW1130G-JM |
|---|---|---|
| N1K, N1/(Theta T2^0.490), ( packs OFF ) | 84.675 percent RPM | 90.897 percent RPM |
| Mach Number = | 0.30 | 0.30 |
| Altitude = | Sea level | Sea level |
| Total Air Temperature (TAT) = | 95.9 deg.F (35.50 deg.C) | 95.9 deg.F (35.50 deg.C) |
| Outside Air Temperature (OAT) = | 86.0 deg.F (30.00 deg.C) | 86.0 deg.F (30.00 deg.C) |
| Redline = | 1981.4 deg.F (1083.00 deg.C) | 1981.4 deg.F (1083.00 deg.C) |
C. Assessing EGT Margin at Other Takeoff Conditions for PW1100G-JM Engines Installed on A319/A320 Aircraft
(1) For a given takeoff condition (pressure altitude and OAT), obtain the DELTA EGT margin value from the figure:
Add this value to the realistic worst case EGT margin calculated in advanced diagnostics and engine management to obtain the margin at the desired condition (Contact Pratt & Whitney Engine Services for help in acquiring access to advanced diagnostics and engine management reporting.)
(2) PW1127G-JM example
(3) Takeoff condition
(a) OAT = 95.09 deg.F (35.0 deg.C)
(b) Pressure altitude = 2000 ft. (609.59 m)
(c) Obtain DELTA EGT margin from the figure:
(d) DELTA EGT = -70 deg.F (-57 deg.C)
(e) Calculate EGT margin at desired condition (assumed realistic worst case margin = 185 deg.F (85 deg.C))
(f) Margin = 185 deg.F (85 deg.C) + (-70 deg.F (-57 deg.C)) = 115 deg.F (46 deg.C)
(g) For PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G-JM, PW1124G1-JM and PW1122G-JM. See the figure:
Subtask 71-00-00-970-070-A ** ON A/C NOT FOR ALL (1) For a given takeoff condition (pressure altitude and OAT), obtain the DELTA EGT margin value from the figure:
Add this value to the realistic worst case EGT margin calculated in advanced diagnostics and engine management to obtain the margin at the desired condition (Contact Pratt & Whitney Engine Services for help in acquiring access to advanced diagnostics and engine management reporting.)
(2) PW1127G-JM example
(3) Takeoff condition
(a) OAT = 95.09 deg.F (35.0 deg.C)
(b) Pressure altitude = 2000 ft. (609.59 m)
(c) Obtain DELTA EGT margin from the figure:
(d) DELTA EGT = -70 deg.F (-57 deg.C)
(e) Calculate EGT margin at desired condition (assumed realistic worst case margin = 185 deg.F (85 deg.C))
(f) Margin = 185 deg.F (85 deg.C) + (-70 deg.F (-57 deg.C)) = 115 deg.F (46 deg.C)
(g) For PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G-JM, PW1124G1-JM and PW1122G-JM. See the figure:
D. Estimate the OAT Limit for PW1100G-JM Engines Installed on A319/A320 Aircraft
(1) This chart is intended to be used as a diagnostic tool for estimating the OAT limit at a selected takeoff pressure altitude, using the takeoff EGT margin at the realistic worst case calculated in advanced diagnostics and engine management.
(2) PW1127G-JM example
(a) Calculated realistic worst case takeoff EGT margin
(b) Margin = 122 deg.F (50 deg.C)
(c) Selected takeoff condition
(d) Pressure altitude = 2500 ft. (761.99 m)
(e) Determine OAT limit from the figure:
(f) OAT limit = 99 deg.F (37.2 deg.C)
(g) For PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G-JM, PW1124G1-JM and PW1122G-JM. See the figure:
Subtask 71-00-00-970-071-A ** ON A/C NOT FOR ALL (1) This chart is intended to be used as a diagnostic tool for estimating the OAT limit at a selected takeoff pressure altitude, using the takeoff EGT margin at the realistic worst case calculated in advanced diagnostics and engine management.
(2) PW1127G-JM example
(a) Calculated realistic worst case takeoff EGT margin
(b) Margin = 122 deg.F (50 deg.C)
(c) Selected takeoff condition
(d) Pressure altitude = 2500 ft. (761.99 m)
(e) Determine OAT limit from the figure:
(f) OAT limit = 99 deg.F (37.2 deg.C)
(g) For PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G-JM, PW1124G1-JM and PW1122G-JM. See the figure:
E. Assessing EGT Margin at Other Takeoff Conditions for PW1100G-JM Engines Installed on A321 Aircraft
(1) For a given takeoff condition (pressure altitude and OAT), obtain the DELTA EGT margin value from the figure:
(a) Add this value to the realistic worst case EGT margin calculated in advanced diagnostics and engine management to obtain the margin at the desired condition (Contact Pratt & Whitney Engine Services for help in acquiring access to advanced diagnostics and engine management reporting).
(2) PW1133G-JM example
(3) Takeoff condition
(a) OAT = 95.9 deg.F (35.5 deg.C)
(b) Pressure altitude = 2000 ft. (609.59 m)
(c) Obtain DELTA EGT margin from the figure:
(d) DELTA EGT = 3.6 deg.F (-15.8 deg.C)
(e) Calculate EGT margin at desired condition ((assumed realistic worst case margin = °F)(assumed realistic worst case margin = °C))
(f) Margin = 113.0 deg.F (45.0 deg.C) + 3.6 deg.F (-15.8 deg.C) = 116.6 deg.F (47.0 deg.C)
(g)
Subtask 71-00-00-970-072-A ** ON A/C NOT FOR ALL (1) For a given takeoff condition (pressure altitude and OAT), obtain the DELTA EGT margin value from the figure:
(a) Add this value to the realistic worst case EGT margin calculated in advanced diagnostics and engine management to obtain the margin at the desired condition (Contact Pratt & Whitney Engine Services for help in acquiring access to advanced diagnostics and engine management reporting).
(2) PW1133G-JM example
(3) Takeoff condition
(a) OAT = 95.9 deg.F (35.5 deg.C)
(b) Pressure altitude = 2000 ft. (609.59 m)
(c) Obtain DELTA EGT margin from the figure:
(d) DELTA EGT = 3.6 deg.F (-15.8 deg.C)
(e) Calculate EGT margin at desired condition ((assumed realistic worst case margin = °F)(assumed realistic worst case margin = °C))
(f) Margin = 113.0 deg.F (45.0 deg.C) + 3.6 deg.F (-15.8 deg.C) = 116.6 deg.F (47.0 deg.C)
(g)
F. Estimate the OAT Limit for PW1100G-JM Engines Installed on A319/A320/A321 Aircraft
(1) This chart is intended to be used as a diagnostic tool for estimating the OAT limit at a selected takeoff pressure altitude, using the takeoff EGT margin at the realistic worst case calculated in advanced diagnostics and engine management.
(2) PW1133G-JM example
(3) Calculated realistic worst case takeoff EGT margin
(4) Margin = 13 deg.F (-10.6 deg.C)
(5) Selected takeoff condition
(6) Pressure altitude = 2500 ft. (761.99 m)
(7) Determine OAT limit. See the figure:
(8) OAT limit = 75 deg.F (23.9 deg.C)
(9) For PW1133G-JM, PW1133GA-JM and PW1130G-JM. See the figure:
(10) Examine the assembly for foreign objects, damage and correct assembly.
(1) This chart is intended to be used as a diagnostic tool for estimating the OAT limit at a selected takeoff pressure altitude, using the takeoff EGT margin at the realistic worst case calculated in advanced diagnostics and engine management.
(2) PW1133G-JM example
(3) Calculated realistic worst case takeoff EGT margin
(4) Margin = 13 deg.F (-10.6 deg.C)
(5) Selected takeoff condition
(6) Pressure altitude = 2500 ft. (761.99 m)
(7) Determine OAT limit. See the figure:
(8) OAT limit = 75 deg.F (23.9 deg.C)
(9) For PW1133G-JM, PW1133GA-JM and PW1130G-JM. See the figure:
(10) Examine the assembly for foreign objects, damage and correct assembly.