Inspection of the Engine after Bird Strike, Foreign Object or Slush Ingestion [IAE]

TASK 72-00-00-200-010-A
Inspection of the Engine after Bird Strike, Foreign Object or Slush Ingestion

WARNING: THERE IS A POSSIBLE HEALTH RISK TO PERSONNEL WHO DO MAINTENANCE TASKS AFTER A BIRD STRIKE. THE SAFETY MEASURES THAT FOLLOW ARE RECOMMENDED:

USE DISPOSABLE GLOVES.
USE CUT RESISTANT GLOVES OVER THE DISPOSABLE GLOVES.
USE A DISPOSABLE COVERALL IF THERE IS A RISK OF BODY CONTACT WITH THE BIRD REMAINS (ORGANIC MATTER) DURING FEATHER COLLECTION OR ENGINE CLEANING.
DO NOT USE PRESSURIZED AIR OR WATER TO CLEAN THE PARTS WHICH WERE IN CONTACT WITH THE BIRD.
REMOVE THE BIRD REMAINS AND PUT THEM IN A PLASTIC BAG.
DO NOT TOUCH YOUR FACE, EYES, NOSE, ETC. WITH YOUR GLOVES.
REMOVE THE GLOVES AND THE DISPOSABLE COVERALL AND PUT THEM IN THE SAME PLASTIC BAG AS THE REMAINS. SEAL THE BAG.
DISCARD THE BAG AS YOU DO FOR USUAL GARBAGE.
CAREFULLY WASH YOUR HANDS WITH SOAP AND WATER.

1. Reason for the Job
This TASK gives the procedure for a general check of the engine after the ingestion of birds, foreign objects or slush.

NOTE: If inspecting the engine following a bird strike, examine the pilots report for evidence of cabin odour. Cabin odour at the same time as a bird strike may indicate a core ingestion

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)

B. Referenced Information

REFERENCE	DESIGNATION
TASK 71-11-11-200-011-A	Visually Examine the Air Intake Cowl - Allowable Damage Data
TASK 72-00-00-100-010-A	Clean the Engine Gas Path for Performance Improvement (Water only)
TASK 72-00-00-100-010-A-01	Clean the Engine Gas Path for Performance Improvement (Cleaner only)
TASK 72-00-00-100-010-A-02	Clean the Engine Gas Path for Performance Improvement (Water only) Repair VRS7003
TASK 72-00-00-200-011-A	TAP Test of Engine Fan Blades
TASK 72-00-00-200-016-B	Inspection of the HP Compressor
TASK 72-00-00-200-016-B-01	Inspection of the HP Compressor
TASK 72-00-00-200-017-B	Inspection of the LP Compressor
TASK 72-00-00-200-022-B	Inspection of the LP Compressor Fan Blades and Fan Case Acoustic Linings
TASK 72-00-00-210-012-A	Inspection of the HP Compressor Stage 3 Rotor Clapper
TASK 72-31-11-100-010-A	Cleaning of the LP Compressor Blades
TASK 72-31-11-200-010-B	Inspection of the Low Pressure (LP) Compressor Fan Blades
TASK 72-31-11-200-012-B	Inspection of the LP Compressor Annulus Fillers
TASK 72-32-60-200-010-A	Inspection of the Screen
TASK 72-32-85-200-010-B	Inspection of the Fan Case Assembly
TASK 72-32-88-200-010-B	Inspection of the Fan Exit Vane Assembly
TASK 72-32-91-200-010-B	Inspection of the LP Compressor Inlet Guide Vane Assembly
TASK 72-38-11-200-010-B	Inspection of the Inlet Cone and the Inlet Cone Fairing
TASK 73-22-11-200-010-A	Inspection of the P2/T2 Sensor
Schematic View of Engine
Fan Blade Areas

3. Job Set-up
Subtask 72-00-00-941-097-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 72-00-00-941-098-A ** ON A/C NOT FOR ALL

B. Put the support equipment into position.
(1) Put the ACCESS PLATFORM 1M(3 FT) into position to give access to the engine for the inspection task.
(2) Put the MAT - WORK into position in the fan case.

NOTE: Make sure that the red warning pennants can be seen from the external side of the aircraft. Make sure the workmat has sufficient dimensions to give full protection to the lower half of the fan case.

4. Procedure
Subtask 72-00-00-210-094-B ** ON A/C NOT FOR ALL

A. If there is a bird strike, foreign object or slush on one or both engines, examine the following before the next flight.

Schematic View of Engine ** ON A/C NOT FOR ALL

(1) If possible, collect bird remains for later analysis.
(2) Examine the air inlet cowl (1) (Ref. AMM TASK 71-11-11-200-011).
(3) Examine the P2/T2 probe (Ref. AMM TASK 73-22-11-200-010).
(4) Examine the inlet cone (10) (Ref. AMM TASK 72-38-11-200-010).
(5) Examine the inlet cone fairing (9) (Ref. AMM TASK 72-38-11-200-010).
(6) If there is no damage or the damage is in the limits (items 2 to 5), continue with Step B.
(7) If there is damage more than the acceptable limits (items 2 to 5), repair per the applicable procedure and go to Step B.
(8) If the damage is more than the repairable limits, reject the damaged part and go to Step B.

Subtask 72-00-00-110-069-A ** ON A/C NOT FOR ALL

B. Clean the Low Pressure (LP) compressor fan blades (2) (Ref. AMM TASK 72-31-11-100-010).

Schematic View of Engine ** ON A/C NOT FOR ALL

(1) Remove sufficient deposits to allow assessment of fan blade damage.

Subtask 72-00-00-210-095-B ** ON A/C NOT FOR ALL

C. Examine the LP Compressor Fan Blades and Annulus Fillers

Schematic View of Engine ** ON A/C NOT FOR ALL

NOTE: We recommend that you use black light to do the following inspections if the maintenance base is available.

NOTE: It is not necessary to remove the annulus filler. Examine the outer surfaces for cracks, nicks, dents and scores.

(1) Inspect the outer surface of annulus fillers (Ref. AMM TASK 72-31-11-200-012).
(a) If there is a crack to the outer surface of annulus fillers, reject the cracked annulus filler.
(2) Inspect the LP compressor fan blades (2) airfoil (Ref. AMM TASK 72-31-11-200-010).

Fan Blade Areas ** ON A/C NOT FOR ALL

(a) If there is damage to the fan blades or an indication of a large rub on the fan track liner, do a transient acoustic propagation test on the full set of fan blades (Ref. AMM TASK 72-00-00-200-011) in less than ten flight hours or five flight cycles, the one that occurs first.

NOTE: If there is an indication of a bird strike but there is no damage to the fan blades, no transient acoustic propagation test is necessary.

(3) Turn the LP compressor rotor.

CAUTION: USE A GLOVED HAND AND NOT SHARP-ENDED TOOLS (A METAL BAR FOR EXAMPLE) TO TURN THE LP COMPRESSOR. SHARP-ENDED TOOLS CAN CAUSE DAMAGE TO THE LP COMPRESSOR FAN BLADES.

CAUTION: TURNING THE LP COMPRESSOR ROTOR IN THE CLOCKWISE DIRECTION, WHEN VIEWED FROM THE FRONT OF THE ENGINE, MAY CAUSE THE BRUSH SEALS AND/OR TURBINE BLADE SHROUDS TO BIND, PREVENTING FREE ROTATION OF THE LP COMPRESSOR ROTOR.

(a) Turn the LP compressor (2) in a counterclockwise direction (when viewed from the front) to make sure that the LP compressor rotor turns freely and that there are no unusual noises.
1 If the LP compressor rotor turns freely and there are no unusual noises, proceed with Steps D thru G.
2 If the LP compressor rotor does not turn freely and/or there are unusual noises, allow the engine to cool for a further 30 to 60 minutes and repeat Para. 3 (a).
a If the LP compressor rotor does not turn freely after the cooling period and/or there are unusual noises, reject the engine.

Subtask 72-00-00-210-096-B ** ON A/C NOT FOR ALL

D. Examine the LP Compressor Fan Case Assembly (8)
(1) Examine the attrition linings for rubs, gouges and scores (6) (Ref. AMM TASK 72-32-85-200-010).
(a) If there is no damage or the damage is in the limits, continue with Step D.(2).
(b) If the damage is within the repairable limits, repair per the applicable procedure.
(c) If there is a damage more than the repairable limits, reject the engine.
(2) Examine the acoustic linings (4) for debonding, cracks, dents and scores (Ref. AMM TASK 72-32-85-200-010).
(a) If the acoustic panels exhibit impact damage, do a tap test of the panels (Ref. AMM TASK 72-32-85-200-010).
(b) If an acoustic cover sheet is missing, do an inspection (Ref. AMM TASK 72-00-00-200-022).
(c) If there is no damage or the damage is in the limits, continue with Step D.(3).
(d) If the damage is within the repairable limits, repair per applicable procedure.
(e) If there is a damage more than the repairable limits, reject the engine.

NOTE: C-ducts do not need to be opened, unless it is suspected that panels behind the LP compressor fan blades are damaged.

(3) Examine the anti-ice impact panel (5) for damage and scores (Ref. AMM TASK 72-32-85-200-010).
(a) If the anti-ice impact panels exhibit impact damage, do a tap test of the panels (Ref. AMM TASK 72-32-85-200-010).
(b) If an anti-ice impact panel is missing, do an inspection (Ref. AMM TASK 72-00-00-200-022).
(c) If there are no loose or damaged panels, continue with Step E.
(d) If the damage is within the repairable limits, repair per the applicable procedure.
(e) If there is a damage more than the repairable limits, reject the engine.

NOTE: C-ducts do not need to be opened, unless it is suspected that panels behind the LP compressor fan blades are damaged.

Subtask 72-00-00-210-097-B ** ON A/C NOT FOR ALL

E. Examine the Fan Exit Guide Vanes (FEGVs)
(1) Examine the fan exit vane assembly vanes (Ref. AMM TASK 72-32-88-200-010).

NOTE: Visually examine the FEGV assembly from the front of the engine without opening the C-ducts. Open the C-ducts to examine the rear of the FEGV only when you find damage on the other engine parts during the inspection.

(a) If there is no damage, or the damage is in the limits, continue with Step F.
(b) If the damage is within the repairable limits, repair per the applicable procedure.
(c) If there is a damage more than the limits, reject the engine.

Subtask 72-00-00-210-134-A ** ON A/C NOT FOR ALL

F. V2500-A1 PRE SB 72-0595 and V2500-A5 PRE SB 70-0631 Engines Only.
(1) Examine the bleed valve outlet screen (Ref. AMM TASK 72-32-60-200-010).
(2) If a bird strike, foreign object or slush ingestion has been reported, inspect the BLEED VALVE OUTLET screen before the next flight.
(a) If there is metal debris present in any component, reject the engine.
(b) If no metal debris is found, continue with Step G.

END OF V2500-A1 PRE SB 72-0595 and V2500-A5 PRE SB 70-0631 engines

NOTE: A compressor wash is recommended to clean any bird remains from the engine gas path in less than 25 hours or 10 flight cycles from the time of the event (Ref. AMM TASK 72-00-00-100-010).

Subtask 72-00-00-210-099-B ** ON A/C NOT FOR ALL

G. Dual Engine Event Borescope Inspection Requirements

Schematic View of Engine ** ON A/C NOT FOR ALL

Area A for dual engine

(1) If there is an indication of bird strike, foreign object or slush ingestion in area A and/or the LPC inlet guide vane assembly on both engines, do the following before the next flight for one of the engines and do the same procedure again for the remaining engine in a maximum of 10 flight hours or 2 flight cycles, whichever occurs first.

NOTE: If the maintenance base is capable for performing the specified borescope inspections, it is highly recommended that these inspections are performed on both engines LPC and HPC before the next flight.

(a) Examine the LP compressor inlet guide vane assembly (Ref. AMM TASK 72-32-91-200-010), LP compressor stages 1.5 and 2.5 (Ref. AMM TASK 72-00-00-200-017) and HP compressor stages 3 and 6 (Ref. AMM TASK 72-00-00-200-016).
1 If there is an indication of damage on the LP compressor inlet guide vane assembly, LP compressor and/or the HP compressor stages 3 and 6, examine the remaining stages of the HP compressor (Ref. AMM TASK 72-00-00-200-016).
2 If the damage is within the repairable limits, repair per the applicable procedure.
3 If the damage is more than the repairable limits, reject the engine.
4 If evidence of a bird strike or foreign object ingestion is found in the LP or HP compressor, inspect stage 3 clappers (Ref. AMM TASK 72-00-00-210-012) at 750 flight cycle intervals thereafter for a total minimum of 2100 flight cycles beyond the ingestion event.

Area B for dual engine

(2) If there is an indication of damage or bending more than the limits in area B on both engines, do the following before the next flight for one of the engines and do the same procedure again for the remaining engine in a maximum of 10 flight hours or 2 flight cycles, whichever occurs first.

NOTE: If the maintenance base is capable for performing the specified borescope inspections, it is highly recommended that these inspections be performed on both engines LPC and HPC before the next flight.

(a) Examine the LP compressor inlet guide vane (11) assembly (Ref. AMM TASK 72-32-91-200-010), and LP compressor stages 1.5 and 2.5 (Ref. AMM TASK 72-00-00-200-017).

NOTE: If there is no evidence of damage or ingestion in the LP compressor, then the HPC stages 3 and 6 inspection is not required.

1 If there is an indication of a damage on the LP compressor inlet guide vane assembly, LP compressor stages 1.5 and 2.5 and:
a If the damage is within the repairable limits, examine HP compressor stages 3 and 6 (Ref. AMM TASK 72-00-00-200-016).
b If the damage is more than the repairable limits, reject the engine.
2 If there is an indication of damage on the HP compressor stages 3 and 6 and:
a If the damage is within the repairable limits, examine the remaining stages of the HP compressor (Ref. AMM TASK 72-00-00-200-016).
b Repair all damage within the repairable limits per the applicable procedure.
c If the damage is more than the repairable limits, reject the engine.
3 If evidence of a bird strike or foreign object ingestion is found in the LP or HP compressor, inspect the stage 3 clappers (Ref. AMM TASK 72-00-00-210-012) at 750 flight cycle intervals thereafter for a total minimum of 2100 flight cycles beyond the ingestion event.

Subtask 72-00-00-210-186-A ** ON A/C NOT FOR ALL

H. Single Engine Event Borescope Inspection Requirements

Area A for single engine

(1) If there is an indication of bird strike, foreign object or slush ingestion in area A on a single engine, do as follows:
(a) Examine the LP compressor inlet guide vane (11) assembly (Ref. AMM TASK 72-32-91-200-010), LP compressor stages 1.5 and 2.5 (Ref. AMM TASK 72-00-00-200-017) and HP compressor stages 3 and 6 (Ref. AMM TASK 72-00-00-200-016) before the next flight.

NOTE: If the maintenance base is not capable for performing the specified borescope inspections, it is possible to defer this borescope inspection requirement for a maximum of 10 flight hours or 2 flight cycles whichever occurs first.

1 If there is an indication of damage on the LP compressor inlet guide vane assembly, LP compressor and/or the HP compressor stages 3 and 6, and if the damage is within repairable limits, examine the remaining stages of the HP compressor (Ref. AMM TASK 72-00-00-200-016).
2 If the damage is within the repairable limits, repair per the applicable procedure.
3 If the damage is more than the repairable limits, reject the engine.
4 If evidence of a bird strike or foreign object ingestion is found in the LP or HP compressor, inspect the stage 3 clappers (Ref. AMM TASK 72-00-00-210-012) at 750 flight cycle intervals thereafter for a total minimum of 2100 flight cycles beyond ingestion event.

Area B for single engine

(2) If there is an indication of damage or bending more than the limits in area B on single engine, do as follows:

(a) Examine the compressor inlet guide vane (11) assembly (Ref. AMM TASK 72-32-91-200-010) and LP compressor stages 1.5 and 2.5 (Ref. AMM TASK 72-00-00-200-017) of the affected engine before the next flight.

NOTE: If there is no evidence of damage, or ingestion in the LP compressor, then the HPC stages 3 and 6 inspection is not required.

1 If there is an indication of a damage in the LP compressor inlet guide vane assembly, LP compressor stages 1.5 and 2.5 and:
a If the damage is within the repairable limits, examine HP compressor stages 3 and 6 (Ref. AMM TASK 72-00-00-200-016).
b If the damage is more than the repairable limits, reject the engine.
2 If there is an indication of damage on HP compressor stages 3 and 6, and:
a If the damage(s) is within the repairable limits, examine the remaining stages of the HP compressor (Ref. AMM TASK 72-00-00-200-016).
b Repair damage that is within the repairable limits per the applicable procedure.
c If the damage is more than the repairable limits, reject the engine.
(b) If evidence of a bird strike or foreign object ingestion is found in the LP or HP compressor, inspect the stage 3 clapper at 750 flight cycle intervals thereafter for a total minimum of 2100 flight cycles beyond the ingestion event.

5. Close-up
Subtask 72-00-00-410-121-A ** ON A/C NOT FOR ALL

A. Put the engine back to a serviceable condition.
(1) Remove the bright spotlight.
(2) Remove the protective mat.
(3) Remove the compressor wash rig.
(4) Remove the borescope.
(5) Remove the access platform(s).
(6) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 02:44:18 UTC