DOC AIRBUS | AMM A320FInspection of the Low Pressure (LP) Compressor Fan Blades [IAE]
TASK 72-31-11-200-010-B
Inspection of the Low Pressure (LP) Compressor Fan Blades
This task gives the procedure for the inspection of the Low Pressure (LP) Compressor fan blades and annulus fillers.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Work Zones and Access Panels
C. Referenced Information
3. Job Set-up
Subtask 72-31-11-941-061-A ** ON A/C NOT FOR ALL
Subtask 72-31-11-210-058-A ** ON A/C NOT FOR ALL
Subtask 72-31-11-942-059-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 13:00:42 UTC
Inspection of the Low Pressure (LP) Compressor Fan Blades
CAUTION:
DETECTED REPAIRABLE DAMAGE ON THE LP COMPRESSOR FAN BLADES MUST BE REPAIRED AS SOON AS DAMAGE IS FOUND, TO GET BACK THE LP COMPRESSOR EFFICIENCY AND KEEP THE FAN BLADE DETERIORATION TO A MINIMUM.
ZONE: 400
1. Reason for the JobThis task gives the procedure for the inspection of the Low Pressure (LP) Compressor fan blades and annulus fillers.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | 1 | ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE |
| No specific | AR | MAT - WORK |
| No specific | AR | WARNING NOTICE(S) |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 400 | POWER PLANT, NACELLES AND PYLONS |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 72-31-11-000-010-B | Removal of the LP Compressor Fan Blades |
| TASK 72-31-11-200-013-B | Detailed Inspection of Fan Blades Leading Edge for Erosion |
| TASK 72-31-11-300-014-B | Repair of the LP Compressor Fan Blade Touch Up Coating - VRS1030 |
| TASK 72-31-11-300-016-A | Repair Damage on the Low Pressure Compressor (LPC) Fan Blades by Local Material Removal - VRS1506 |
| TASK 72-31-11-300-019-A | Repair of the LP Compressor Fan Blade Chocking Pads - VRS1063 |
| TASK 72-31-11-300-020-A | Repair of the LP Compressor Fan Re-apply Coating - VRS1973 |
| TASK 72-31-11-400-010-C | Installation of the LP Compressor Fan Blades |
| TASK 72-31-12-200-010-B | Inspection of the Stage 1 Fan Disk and the Rear Blade Retaining Ring |
| TASK 72-31-13-200-010-B | Inspection of the Front Blade Retaining Ring Assembly |
Stage 1 Fan BladesSubtask 72-31-11-941-061-A ** ON A/C NOT FOR ALL
A. Safety Precautions
(1) On the center pedestal, on ENG panel 115VU:
(a) Put the WARNING NOTICE(S) in position to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than five minutes before you do this procedure.
(3) On the overhead panel, on maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put the WARNING NOTICE(S) in position to tell persons not to energize FADEC 1(2).
(4) Put the support equipment in position:
(a) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position to give access to the engine.
(b) Put the MAT - WORK in position in the air inlet cowl.
4. Procedure(1) On the center pedestal, on ENG panel 115VU:
(a) Put the WARNING NOTICE(S) in position to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than five minutes before you do this procedure.
(3) On the overhead panel, on maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put the WARNING NOTICE(S) in position to tell persons not to energize FADEC 1(2).
(4) Put the support equipment in position:
(a) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position to give access to the engine.
(b) Put the MAT - WORK in position in the air inlet cowl.
NOTE: Make sure that the red warning pennants of the work mat can be seen external of the aircraft. Make sure that the work mat has sufficient dimensions to give full protection to the lower half of the fan case surface.
Subtask 72-31-11-210-058-A ** ON A/C NOT FOR ALL
A. Examine the LP Compressor fan blade airfoils.
(a) If they are cracked, reject them.
(b) If they have nicks, dents, scores or scratches up to 0.008 in. (0.20 mm) in depth, accept them.
(c) If they have nicks, dents, scores or scratches more than 0.008 in. (0.20 mm) in depth, reject them.
(d) If the leading edge of area Ar or the trailing edge of area Br has nicks, dents, scores or scratches more than 0.008 in. (0.20 mm) in depth, repair it (Ref. AMM TASK 72-31-11-300-016).
(2) Examine the areas At and Bt of the LP Compressor fan blades for cracks, nicks, dents, scores and scratches.
(a) If they are cracked, reject them.
(b) If they have nicks, dents, scores or scratches up to 0.025 in. (0.635 mm) in depth, accept them.
(c) If they have nicks, dents, scores or scratches more than 0.025 in. (0.635 mm) in depth, reject them.
(d) If the leading edge of area At or the trailing edge of area Bt has nicks, dents, scores and scratches more than 0.008in. (0.20 mm) in depth, repair it (Ref. AMM TASK 72-31-11-300-016).
(3) Examine the areas Ar and At of the stage 1 fan blades for erosion (Ref. AMM TASK 72-31-11-200-013).
(4) Examine the area Ct of the LP Compressor fan blades for cracks, nicks, dents, scores and scratches.
(a) If they are cracked, reject them.
(b) If they have nicks, dents, scores or scratches up to 0.008 in. (0.20 mm) in depth, accept them.
(c) If they have nicks, dents, scores or scratches more than 0.008 in. (0.20 mm) in depth, reject them.
(5) Examine the area F of the LP Compressor fan blades for cracks, nicks, dents, scores and scratches.
(a) If there are radial cracks extending from the tips :
1 Less than 0.394 in. (10.00 mm), accept them.
2 More than 0.394 in. (10.00 mm), replace them at the next A Check.
(b) If any other cracking (not radial) is present, reject them.
(c) If they have nicks, dents, scores or scratches up to 0.008 in. (0.20 mm) in depth, accept them.
(d) If they have nicks, dents, scores or scratches more than 0.008 in. (0.20 mm) in depth, reject them.
(6) Examine, when available, the area Cr of the LP Compressor fan blades for cracks, nicks, dents, scores and scratches.
(a) If they have cracks, nicks, dents, scores or scratches, reject them.
(7) Examine the areas Ar, At, Br, Bt, Cr and Ct of the LP Compressor fan blades for arc-burns.
(8) Examine the blade annulus line areas of the LP Compressor fan blades.
(a) If wear on the fan blade airfoil surfaces, caused by contact with the annulus filler sealing strip, is not more than 0.008 in. (0.20 mm), accept it.
(b) If wear on the fan blade airfoil surfaces, caused by contact with the annulus filler sealing strip, is more than 0.008 in. (0.20 mm), reject it.
(9) Examine the leading and trailing edges of the LP Compressor fan blades for bends
(a) Blade bends - general
1 The number of bent blades in one fan rotor assembly must not be more than three.
2 If there is more than one bend in a blade, reject it.
3 If the bend in the blade has kinks, creases, tears, cracks or nicks, reject it.
4 All blade untwist is not acceptable.
5 There must be a smooth transition between the undamaged airfoil and the bent area.
(b) Accept circumferential deviation (X) of not more than 0.2 in. (5.08 mm) if:
1 The axial length of bend (Y) is not less than 8 times circumferential deviation (X).
2 The radial length of bend (Z) is not less than 15 times circumferential deviation (X).
3 Bends do not go into the panel area by more than 2.0 in. (50.80 mm) from the leading edge.
(c) Accept circumferential deviation (X) of between 0.2 in. (5.08 mm) and 0.5 in. (12.70 mm) if:
1 The blade is replaced within 125 flight hours or 25 flight cycles, whichever occurs first.
2 The axial length of bend (Y) is not less than 8 times circumferential deviation (X).
3 The radial length of bend (Z) is not less than 15 times circumferential deviation (X).
(d) If the blade has bends that are more than the limits in (b) and (c), reject it.
(10) Examine the leading edge tips of the LP Compressor fan blades for bends.
(a) If they have leading edge tip bends, reject them.
(11) Examine the blade tips and the airfoil surfaces of the LP compressor fan blades for discoloration/blueing/scoring caused by heat/contact with the fan case attrition lining.
(a) If there is discoloration/blueing on the blade tips and on no more than 0.25 in. (6.35 mm) of the adjacent airfoil surfaces radially from the blade tip, accept them.
(b) If there is discoloration/blueing on the blade tips and on more than 0.25 in. (6.35 mm) of the adjacent airfoil surfaces radially from the blade tip, reject them.
(c) If there is scoring on the blade tips caused by contact with the fan case attrition lining, accept them.
Subtask 72-31-11-210-086-A ** ON A/C NOT FOR ALL CAUTION:
FOLLOWING LOSS OF ONE OR MORE ACOUSTIC LINER(S), CARRY OUT INSPECTION OF:
(1) Examine the areas Ar and Br of the LP Compressor fan blades for cracks, nicks, dents, scores and scratches. - LP COMPRESSOR FAN BLADES AS ACOUSTIC LINER RELEASE CAN INCREASE FAN BLADE ROOT STRESSES.
- FAN CASE ACOUSTIC LINER(S) TO ENSURE FURTHER DISBOND/DAMAGE IS PRESENT.
(a) If they are cracked, reject them.
(b) If they have nicks, dents, scores or scratches up to 0.008 in. (0.20 mm) in depth, accept them.
(c) If they have nicks, dents, scores or scratches more than 0.008 in. (0.20 mm) in depth, reject them.
(d) If the leading edge of area Ar or the trailing edge of area Br has nicks, dents, scores or scratches more than 0.008 in. (0.20 mm) in depth, repair it (Ref. AMM TASK 72-31-11-300-016).
(2) Examine the areas At and Bt of the LP Compressor fan blades for cracks, nicks, dents, scores and scratches.
(a) If they are cracked, reject them.
(b) If they have nicks, dents, scores or scratches up to 0.025 in. (0.635 mm) in depth, accept them.
(c) If they have nicks, dents, scores or scratches more than 0.025 in. (0.635 mm) in depth, reject them.
(d) If the leading edge of area At or the trailing edge of area Bt has nicks, dents, scores and scratches more than 0.008in. (0.20 mm) in depth, repair it (Ref. AMM TASK 72-31-11-300-016).
(3) Examine the areas Ar and At of the stage 1 fan blades for erosion (Ref. AMM TASK 72-31-11-200-013).
(4) Examine the area Ct of the LP Compressor fan blades for cracks, nicks, dents, scores and scratches.
(a) If they are cracked, reject them.
(b) If they have nicks, dents, scores or scratches up to 0.008 in. (0.20 mm) in depth, accept them.
(c) If they have nicks, dents, scores or scratches more than 0.008 in. (0.20 mm) in depth, reject them.
(5) Examine the area F of the LP Compressor fan blades for cracks, nicks, dents, scores and scratches.
(a) If there are radial cracks extending from the tips :
1 Less than 0.394 in. (10.00 mm), accept them.
2 More than 0.394 in. (10.00 mm), replace them at the next A Check.
(b) If any other cracking (not radial) is present, reject them.
(c) If they have nicks, dents, scores or scratches up to 0.008 in. (0.20 mm) in depth, accept them.
(d) If they have nicks, dents, scores or scratches more than 0.008 in. (0.20 mm) in depth, reject them.
(6) Examine, when available, the area Cr of the LP Compressor fan blades for cracks, nicks, dents, scores and scratches.
(a) If they have cracks, nicks, dents, scores or scratches, reject them.
(7) Examine the areas Ar, At, Br, Bt, Cr and Ct of the LP Compressor fan blades for arc-burns.
NOTE: An arc-burn is evident by a small circular or semi-circular heat-affected area on the blade surface that can contain pitting, melting or cracking. Visually a dark blue oxide discoloration can be associated with the heat-affected area.
(a) If they show signs of arc-burns, reject them and examine the fan disk, the rear blade retaining ring and the front blade retaining ring for arc-burns (Ref. AMM TASK 72-31-12-200-010) and (Ref. AMM TASK 72-31-13-200-010). (8) Examine the blade annulus line areas of the LP Compressor fan blades.
(a) If wear on the fan blade airfoil surfaces, caused by contact with the annulus filler sealing strip, is not more than 0.008 in. (0.20 mm), accept it.
(b) If wear on the fan blade airfoil surfaces, caused by contact with the annulus filler sealing strip, is more than 0.008 in. (0.20 mm), reject it.
(9) Examine the leading and trailing edges of the LP Compressor fan blades for bends
(a) Blade bends - general
1 The number of bent blades in one fan rotor assembly must not be more than three.
2 If there is more than one bend in a blade, reject it.
3 If the bend in the blade has kinks, creases, tears, cracks or nicks, reject it.
4 All blade untwist is not acceptable.
5 There must be a smooth transition between the undamaged airfoil and the bent area.
(b) Accept circumferential deviation (X) of not more than 0.2 in. (5.08 mm) if:
1 The axial length of bend (Y) is not less than 8 times circumferential deviation (X).
2 The radial length of bend (Z) is not less than 15 times circumferential deviation (X).
3 Bends do not go into the panel area by more than 2.0 in. (50.80 mm) from the leading edge.
(c) Accept circumferential deviation (X) of between 0.2 in. (5.08 mm) and 0.5 in. (12.70 mm) if:
1 The blade is replaced within 125 flight hours or 25 flight cycles, whichever occurs first.
2 The axial length of bend (Y) is not less than 8 times circumferential deviation (X).
3 The radial length of bend (Z) is not less than 15 times circumferential deviation (X).
(d) If the blade has bends that are more than the limits in (b) and (c), reject it.
(10) Examine the leading edge tips of the LP Compressor fan blades for bends.
(a) If they have leading edge tip bends, reject them.
(11) Examine the blade tips and the airfoil surfaces of the LP compressor fan blades for discoloration/blueing/scoring caused by heat/contact with the fan case attrition lining.
(a) If there is discoloration/blueing on the blade tips and on no more than 0.25 in. (6.35 mm) of the adjacent airfoil surfaces radially from the blade tip, accept them.
(b) If there is discoloration/blueing on the blade tips and on more than 0.25 in. (6.35 mm) of the adjacent airfoil surfaces radially from the blade tip, reject them.
(c) If there is scoring on the blade tips caused by contact with the fan case attrition lining, accept them.
B. Examine the LP Compressor fan blade roots.
(1) Remove the fan blade from the stage 1 fan disk (Ref. AMM TASK 72-31-11-000-010).
(2) Examine the stage 1 fan blade roots.
1 If they have any amount of peeling of dry film lubricant, repair them (Ref. AMM TASK 72-31-11-300-014) or (Ref. AMM TASK 72-31-11-300-020).
(b) For post SBE 72-0375 or post SBE 72-0384, examine the blade root of the stage 1 fan blades for the Metco 58 coating on the dovetail root flank.
1 If there are scores of root flank Metco 58 coating.
a Up to 0.004 in. (0.1 mm) deep, not more than 0.006 in. (0.15 mm) wide and no longer than 0.6 in. (15 mm) long, accept them if the underlying titanium is not visible and/or the location is not at the edge of bedding.
b More than a, reject them.
2 If there are localised gouges/chips in Metco 58 coating.
a Up to 0.015 in.2 (10 mm2) in total area, accept them if the underlying titanium is not visible and/or the location is not at the edge of bedding.
b More than a, reject them.
3 If there are flakings/debonds of Metco 58 coating from root flanks, reject them.
(c) Examine the chocking pads of the stage 1 fan blades for looseness or separation.
1 If they show signs of looseness or separation between chocking pad and fan blade root, repair them (Ref. AMM TASK 72-31-11-300-019).
Subtask 72-31-11-420-116-A ** ON A/C NOT FOR ALL (1) Remove the fan blade from the stage 1 fan disk (Ref. AMM TASK 72-31-11-000-010).
(2) Examine the stage 1 fan blade roots.
NOTE: Ensure that NMSB 72-0386 is complied with at appropriate intervals.
(a) Examine the blade root of fan blades for dry film lubricant peeling. 1 If they have any amount of peeling of dry film lubricant, repair them (Ref. AMM TASK 72-31-11-300-014) or (Ref. AMM TASK 72-31-11-300-020).
(b) For post SBE 72-0375 or post SBE 72-0384, examine the blade root of the stage 1 fan blades for the Metco 58 coating on the dovetail root flank.
1 If there are scores of root flank Metco 58 coating.
a Up to 0.004 in. (0.1 mm) deep, not more than 0.006 in. (0.15 mm) wide and no longer than 0.6 in. (15 mm) long, accept them if the underlying titanium is not visible and/or the location is not at the edge of bedding.
b More than a, reject them.
2 If there are localised gouges/chips in Metco 58 coating.
a Up to 0.015 in.2 (10 mm2) in total area, accept them if the underlying titanium is not visible and/or the location is not at the edge of bedding.
b More than a, reject them.
3 If there are flakings/debonds of Metco 58 coating from root flanks, reject them.
(c) Examine the chocking pads of the stage 1 fan blades for looseness or separation.
1 If they show signs of looseness or separation between chocking pad and fan blade root, repair them (Ref. AMM TASK 72-31-11-300-019).
C. Install the stage 1 fan blades.
(1) Install the stage 1 fan blade to the stage 1 fan disk (Ref. AMM TASK 72-31-11-400-010).
5. Close-up(1) Install the stage 1 fan blade to the stage 1 fan disk (Ref. AMM TASK 72-31-11-400-010).
Subtask 72-31-11-942-059-A ** ON A/C NOT FOR ALL
A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the workmat.
(3) Remove the access platform(s).
(4) Remove the WARNING NOTICE(S).
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the workmat.
(3) Remove the access platform(s).
(4) Remove the WARNING NOTICE(S).