DOC AIRBUS | AMM A320FUltrasonic Inspection of the LP Compressor Fan Blade Roots [IAE]
TASK 72-00-00-200-024-B
Ultrasonic Inspection of the LP Compressor Fan Blade Roots
1. Reason for the Job
A. This TASK is for V2500-A5 engines.
B. This TASK gives the procedure for the ultrasonic inspection of the LP compressor fan blade roots.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Referenced Information
3. Job Set-up
Subtask 72-00-00-941-128-A ** ON A/C NOT FOR ALL
Subtask 72-00-00-730-055-A ** ON A/C NOT FOR ALL
Subtask 72-00-00-942-067-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 02:44:24 UTC
Ultrasonic Inspection of the LP Compressor Fan Blade Roots
1. Reason for the Job
A. This TASK is for V2500-A5 engines.
B. This TASK gives the procedure for the ultrasonic inspection of the LP compressor fan blade roots.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 1M(3 FT) |
| No specific | AR | MAT - WORK |
| No specific | AR | WARNING NOTICE(S) |
| IAE2R19315 | 1 | TEST BLOCK |
| IAE2R19316 | 1 | PROBE-ULTRASONIC |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.V05-126) | scotch brite |
| (Material No.V06-148) | Ultrasonic Couplant |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 72-31-11-000-010-B | Removal of the LP Compressor Fan Blades |
| TASK 72-31-11-200-010-B | Inspection of the Low Pressure (LP) Compressor Fan Blades |
| TASK 72-31-11-400-010-C | Installation of the LP Compressor Fan Blades |
| TASK 72-38-11-000-010-A | Removal of the Inlet Cone |
| TASK 72-38-11-400-010-A | Installation of the Inlet Cone |
Calibration of the Ultrasonic Flaw DetectorSubtask 72-00-00-941-128-A ** ON A/C NOT FOR ALL
A. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).
Subtask 72-00-00-941-129-A ** ON A/C NOT FOR ALL (1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).
B. Put the Ground Support Equipment in to Position
(1) Put the ACCESS PLATFORM 1M(3 FT) in position.
(2) Put the MAT - WORK in position.
4. Procedure(1) Put the ACCESS PLATFORM 1M(3 FT) in position.
(2) Put the MAT - WORK in position.
Subtask 72-00-00-730-055-A ** ON A/C NOT FOR ALL
A. Do a Calibration of the Ultrasonic Detector
(1) Set up the ultrasonic flaw detector for dual or through transmission operation with zero delay. Set the amplifier to 5-10 MHz.
(2) Apply Ultrasonic Couplant (Material No.V06-148) to the rear angled flank and position the IAE2R19316 PROBE-ULTRASONIC on the IAE2R19315 TEST BLOCK.
(3) Identify the signal produced by the large Slot-A. With the range control, position this signal at Division Line 5 on the time base and adjust the amplitude to approximately 50 percent screen height.
(4) Increase the gain by 20dB. Move the probe over Slot-B and identify the signal produced. Adjust the amplifier to bring the signal to 60 percent screen height.
(5) If a monitor gate is available, position it between the 4.5 and 5.5 Division Lines on the time base. Adjust any visual or audible alarms to trigger at 60 percent screen height. The calibration check is completed.
Subtask 72-00-00-010-167-A ** ON A/C NOT FOR ALL (1) Set up the ultrasonic flaw detector for dual or through transmission operation with zero delay. Set the amplifier to 5-10 MHz.
(2) Apply Ultrasonic Couplant (Material No.V06-148) to the rear angled flank and position the IAE2R19316 PROBE-ULTRASONIC on the IAE2R19315 TEST BLOCK.
(3) Identify the signal produced by the large Slot-A. With the range control, position this signal at Division Line 5 on the time base and adjust the amplitude to approximately 50 percent screen height.
(4) Increase the gain by 20dB. Move the probe over Slot-B and identify the signal produced. Adjust the amplifier to bring the signal to 60 percent screen height.
(5) If a monitor gate is available, position it between the 4.5 and 5.5 Division Lines on the time base. Adjust any visual or audible alarms to trigger at 60 percent screen height. The calibration check is completed.
B. Remove the Fairing, the Inlet Cone and the Fan Blades
(1) Remove the fairing and the inlet cone (Ref. AMM TASK 72-38-11-000-010)
(a) Write down the position of any trim balance weights that are installed.
(b) Remove the fairing and the inlet cone.
(2) Remove the fan blades (Ref. AMM TASK 72-31-11-000-010)
Subtask 72-00-00-270-051-A ** ON A/C NOT FOR ALL (1) Remove the fairing and the inlet cone (Ref. AMM TASK 72-38-11-000-010)
(a) Write down the position of any trim balance weights that are installed.
(b) Remove the fairing and the inlet cone.
(2) Remove the fan blades (Ref. AMM TASK 72-31-11-000-010)
C. Do an Ultrasonic Inspection
(1) Do a general inspection of the fan blades (Ref. AMM TASK 72-31-11-200-010).
(2) Do an ultrasonic inspection on each of the fan blades
(a) Apply the Ultrasonic Couplant (Material No.V06-148) to the concave face of the blade root flank. Position the probe on the blade root and move the probe along the full chordal width of the blade.
1 Monitor the signal very carefully as you move the probe, from the front of the leading edge for 2.4 in. (60.9599 mm) to the rear of the concave surface.
(c) Apply the Ultrasonic Couplant (Material No.V06-148) to the convex face of the blade root flank at the area to be inspected. Position the probe at 1.77 in. (45 mm) from the front face of the blade root (immediately behind the front chocking pad if still installed) and move the probe along the next 4.33 in. (110 mm) of the chordal width of the blade root terminating the inspection at 6.10 in. (155 mm) from the front face of the blade root (approximately 3.30 in. (84 mm) from the rear face of the root.
(d) Monitor the signal very carefully as you move the probe over this area.
(e) Reject the blade if a signal greater than 60 percent screen height is produced between 4.5 and 5.5 Division Lines on the time base.
(f) Subsequently to the above, if excess dry film lubricant is still present at the ultrasonic reject indication position on the blade root flank in the areas X and Y remove this by lightly rubbing with scotch brite (Material No.V05-126) .
Repeat the ultrasonic check as mentioned above (a), (c), (d) and (e). Reject the blade if a signal greater than 60 percent screen height is still present between 4.5 and 5.5 Division Lines on the time base.
(3) If any fan blades are rejected, contact IAE representative. Give the details of the signals detected (Position from the leading edge and signal amplitude), part number, serial number and the life of the rejected blade.
Subtask 72-00-00-410-170-A ** ON A/C NOT FOR ALL (1) Do a general inspection of the fan blades (Ref. AMM TASK 72-31-11-200-010).
(2) Do an ultrasonic inspection on each of the fan blades
(a) Apply the Ultrasonic Couplant (Material No.V06-148) to the concave face of the blade root flank. Position the probe on the blade root and move the probe along the full chordal width of the blade.
1 Monitor the signal very carefully as you move the probe, from the front of the leading edge for 2.4 in. (60.9599 mm) to the rear of the concave surface.
NOTE: It is possible that this area is the source of the cracks.
(b) Reject the blade if a signal greater than 60 percent screen height is produced between the 4.5 and 5.5 Division Lines on the time base. (c) Apply the Ultrasonic Couplant (Material No.V06-148) to the convex face of the blade root flank at the area to be inspected. Position the probe at 1.77 in. (45 mm) from the front face of the blade root (immediately behind the front chocking pad if still installed) and move the probe along the next 4.33 in. (110 mm) of the chordal width of the blade root terminating the inspection at 6.10 in. (155 mm) from the front face of the blade root (approximately 3.30 in. (84 mm) from the rear face of the root.
(d) Monitor the signal very carefully as you move the probe over this area.
(e) Reject the blade if a signal greater than 60 percent screen height is produced between 4.5 and 5.5 Division Lines on the time base.
(f) Subsequently to the above, if excess dry film lubricant is still present at the ultrasonic reject indication position on the blade root flank in the areas X and Y remove this by lightly rubbing with scotch brite (Material No.V05-126) .
Repeat the ultrasonic check as mentioned above (a), (c), (d) and (e). Reject the blade if a signal greater than 60 percent screen height is still present between 4.5 and 5.5 Division Lines on the time base.
(3) If any fan blades are rejected, contact IAE representative. Give the details of the signals detected (Position from the leading edge and signal amplitude), part number, serial number and the life of the rejected blade.
D. Install the Fan Blades, the Inlet Cone and the Fairing
(1) Install the fan blades (Ref. AMM TASK 72-31-11-400-010)
(2) Install the fairing and the inlet cone (Ref. AMM TASK 72-38-11-400-010)
(3) If all the removed parts are replaced in their original locations and no blade rework - apart from re-attachment of loose or detached fan blade chocking pads - has been carried out, a trim balance survey run is not required.
5. Close-up(1) Install the fan blades (Ref. AMM TASK 72-31-11-400-010)
(2) Install the fairing and the inlet cone (Ref. AMM TASK 72-38-11-400-010)
(3) If all the removed parts are replaced in their original locations and no blade rework - apart from re-attachment of loose or detached fan blade chocking pads - has been carried out, a trim balance survey run is not required.
Subtask 72-00-00-942-067-A ** ON A/C NOT FOR ALL
A. Remove the Ground Support Equipment
(1) Remove the workmat.
(2) Remove the access platform.
(3) Remove the warning notices.
(1) Remove the workmat.
(2) Remove the access platform.
(3) Remove the warning notices.