Inspection of the Engine after a Bowed Rotor Protection Fault [PW11]

TASK 72-00-00-200-824-A
Inspection of the Engine after a Bowed Rotor Protection Fault

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: 210
ZONE: 400

1. Reason for the Job
Use this procedure to do an inspection of the engine after a bowed rotor protection fault.
2. Job Set-up Information
A. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
210	CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD
400	POWER PLANT, NACELLES AND PYLONS

B. Referenced Information

REFERENCE	DESIGNATION
TASK 31-32-00-860-012-A	Procedure to Get Access to the SYSTEM REPORT/TEST/ENG Page
TASK 72-35-00-290-803-A	Bowed Rotor Special Borescope Inspection of the High Pressure Compressor (HPC) Assembly
TSM 71-00-00-810-888	Motor to Start Aborted due to Bowed Rotor Overspeed
Maximum Shutdown Time (min) - Table 2
Alternate Minimum Shutdown Time (min) - Table 3
System-Report Test-Engine Page
EEC Channel Page
Other Maintenance-Reports Page
Exceedance Reports

3. Job Set-up
Subtask 72-00-00-860-132-A ** ON A/C NOT FOR ALL

A. Not Applicable

4. Procedure
Subtask 72-00-00-280-093-A ** ON A/C NOT FOR ALL

A. Inspection of the Engine after a Bowed-Rotor Protection Fault

CAUTION: DO NOT TRY TO START THE ENGINE AFTER A BOWED ROTOR PROTECTION FAULT. YOU MUST FIRST COMPLETE THIS PROCEDURE AND THE FINAL ENGINE ANALYSIS. IF YOU DO NOT OBEY THESE INSTRUCTIONS, TOO MUCH HIGH-PRESSURE COMPRESSOR RUB WILL CAUSE DAMAGE TO THE ENGINE.

(1) A bowed rotor protection fault (ENG1D-0546-ENGINE BORESCOPE or ENG2D-0546-ENGINE BORESCOPE) occurs when the Electronic Engine Control (EEC) channel A or channel B has sensed that a specified N2 speed limit was outside the permitted limits after the engine motoring to start (slow motor) sequence was started.
(2) If the engine is pre−Service Bulletin (SB) PW1000G−C−73−00−0037A (EEC software FCS 5.0), continue to step 4.A.(4). Otherwise, obtain the closedown value from the EXCEEDANCE REPORT on page 2 of 2 using the Multipurpose Control & Display Unit (MCDU) as follows. This will be used to determine if an engine borescope inspection and a secondary analysis is required:

NOTE: If the maintenance message ENG1D−0546−ENGINE BORESCOPE or ENG2D−0546−ENGINE BORESCOPE occurred during a manual start, you can transition the master lever OFF to ON and then to OFF before starting the MCDU exceedance report closedown calculation function. If this is not done, then the exceedance report may not be reported or updated.

(a) Get access to the SYSTEM REPORT/TEST/ENG page within the MCDU (Ref. AMM TASK 31-32-00-860-012).
(b)

System-Report Test-Engine Page ** ON A/C NOT FOR ALL

(c)

EEC Channel Page ** ON A/C NOT FOR ALL

(d)

Other Maintenance-Reports Page ** ON A/C NOT FOR ALL

(e)

Exceedance Reports ** ON A/C NOT FOR ALL

1 No closedown value was calculated ("XX.X" displayed). Continue to step 4.A.(4).
2 The software was unable to calculate a value ("ERROR" displayed). Continue to step 4.A.(4).
3 The DATE displayed on the EXCEEDANCE REPORT screen 2 of 2 does not match the date of the bowed rotor protection fault. Continue to step 4.A.(4).
(3) Determine if an engine boroscope inspection is required and if a secondary analysis is required using Table 1.

Closedown (mils.)	Disposition
Less than 25.5 mils	Borescope inspection and secondary analysis not required. Engine is serviceable. Continue to step 4.A.(8).
Between 25.5 and 29.5 mils	Borescope inspection required. Secondary analysis not required. Continue to step 4.A.(7).
Greater than 29.5 mils	Borescope inspection and secondary analysis required. Continue to step 4.A.(7).

Table - Bowed Rotor Protection Fault Closedown and Disposition

(a) If a secondary analysis is required, provide the following data to Pratt & Whitney:

Engine oil monitoring 2 report <27>
Engine start report <10>
Post Flight Report (PFR)
Ground scanning report
Borescope images of High Pressure Compressor (HPC) stage 7 stators and stage 7 and 8 rotors to estimate coating loss
DSU data dump.

CAUTION: IF THE ENGINE WAS NOT OPERATED AT OR NEAR IDLE POWER FOR A MINIMUM OF THREE MINUTES BEFORE THE LAST ENGINE SHUTDOWN, DO NOT USE THE DATA IN TABLES 2 AND 3 FOR THE ENGINE-COMPRESSOR HEALTH ANALYSIS. THE DATA WILL NOT BE APPLICABLE AND THE ANALYSIS WILL NOT BE ACCURATE, WHICH CAN CAUSE DAMAGE TO THE ENGINE HIGH-PRESSURE COMPRESSOR AT THE SUBSEQUENT ENGINE START.

(4) Get the subsequent information for analysis. The analysis will find if an engine borescope inspection is necessary and if more data is required. Use this step only if required due to closedown not available through MCDU.
(a) If the engine was not operated at or near idle power for a minimum of three minutes prior to the last engine shutdown, go to step 4.A.(7).

NOTE: If the last engine shutdown was after flight, the time at idle starts after main and nose gear touchdown.

(b) Engine shutdown time between the last flight shutdown and the failed start attempt shall be accurate within plus or minus five minutes. Use data from the engine oil monitoring 2 report <27> from the last flight shutdown and the maintenance PFR from the failed start to calculate engine shutdown time as follows:
1 Subtract the engine shutdown time recorded on the engine oil monitoring 2 report <27>, parameter set 16, line O1 (identified as UTC) from the ENGxD-0546-ENGINE BORESCOPE fault time recorded on the PFR (shown under the failure messages header and identified as GMT) or the time shown in troubleshooting data/fault cell information (identified as UTC) for the ENGxD-0546-ENGINE BORESCOPE fault.
2 If the ECAM alert and associated message are not available in the PFR, the fault time can also be obtained from the ground scanning report.
(c) Event ambient temperature:
1 Use temperature data available from airline operations or the temperature shown in the troubleshooting data/fault cell information for the ENGxD-0546-ENGINE BORESCOPE fault, if available, to find the event temperature.
(d) Event location altitude:
1 Use data available from airline operations or the altitude shown in the troubleshooting data/fault cell information for the ENGxD-0546-ENGINE BORESCOPE fault, if available, to find event location altitude.
(5) Use event ambient temperature and location altitude to complete Table 2:

Maximum Shutdown Time (min) - Table 2 ** ON A/C NOT FOR ALL

(a) Find the engine maximum shutdown time as follows:
1 If the engine shutdown time found in step 4.A.(4)(b)1_ is less than the maximum engine shutdown time, continue to step 4.A.(8). If the engine shutdown time found in step 4.A.(4)(b)1_ was more than the engine maximum shutdown time, continue to step 4.A.(6).
(6) Use event ambient temperature and location altitude to complete Table 3:

Alternate Minimum Shutdown Time (min) - Table 3 ** ON A/C NOT FOR ALL

(a) Find the engine alternate minimum shutdown time as follows:
1 If the engine shutdown time found in step 4.A.(4)(b)1_ is less than the engine alternate minimum shutdown time, continue to step 4.A.(7). If the engine shutdown time found in step 4.A.(4)(b)1_ is more than the engine alternate minimum shutdown time, continue to step 4.A.(8).
(7) Do a bowed rotor special borescope inspection of the HPC assembly (Ref. AMM TASK 72-35-00-290-803):
(a) Determine engine serviceability as follows:
1 If the borescope inspection is more than the permitted limits, provide findings to Pratt & Whitney and remove the engine from service.
2 If a secondary review was required in step 4.A.(3), provide the required data and request results from Pratt & Whitney.
3 If the borescope inspection is in the permitted limits and the results of any secondary analysis required in step 4.A.(3) are acceptable, continue to step 4.A.(8).
(8) If the engine is serviceable, do the applicable troubleshooting procedure TSM 71-00-00-810-888 to clear the fault message.

[Rev.10 from 2021] 2026.04.01 02:47:33 UTC