Repair the Damage on the LP Compressor Stage 1.5 Blades - VRS1130 [IAE]

TASK 72-00-00-300-020-A
Repair the Damage on the LP Compressor Stage 1.5 Blades - VRS1130

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

CAUTION: PROTECT THE ENGINE TO PREVENT THE ENTRY OF UNWANTED MATERIAL.

CAUTION: BE CAREFUL NOT TO DAMAGE THE ADJACENT PARTS DURING THE REPAIR.

CAUTION: TITANIUM COMPONENT - YOU MUST USE SILICON CARBIDE TYPE ABRASIVE WHEELS, STONES AND PAPERS TO DRESS, BLEND AND POLISH THIS COMPONENT. IF MECHANICAL CUTTERS ARE USED, ONLY LIGHT CUTS MUST BE MADE TO AVOID OVERHEATING THE MATERIAL.

CAUTION: TITANIUM COMPONENT - AVOID BUILD UP OF HEAT BY APPLYING ONLY GENTLE PRESSURE AND KEEPING THE TOOL SPEED AS LOW AS POSSIBLE. USE TECHNIQUES WHICH ALLOW FOR PROGRESSIVE WEAR OF THE DRESSING MEDIA TO PRESENT A CONTINUALLY FRESH CUTTING SURFACE TO THE WORK PIECE.

CAUTION: DO NOT DWELL ON ONE AREA OF THE COMPONENT.

CAUTION: DRESS, WHERE POSSIBLE, IN A CIRCULAR MOTION, TAKING LIGHT CUTS TO AVOID OVERHEATING.

CAUTION: TITANIUM COMPONENT - YOU MUST MAKE SURE THAT WHEN YOU REMOVE MATERIAL, BLEND AND POLISH, TO MAKE SMOOTH, THAT NO SPARKS ARE PRODUCED AND THE ADJACENT AREA IS MASKED OFF.

CAUTION: TITANIUM COMPONENT- IF THE MATERIAL SHOWS A CHANGE IN COLOR TO DARKER THAN A LIGHT STRAW COLOR, THE COMPONENT IS TO BE REJECTED.

1. Reason for the Job
This task gives the repair procedure for the damage on the LP Compressor Stage 1.5 Blades.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	ABRASIVE STONE
No specific	1	ACCESS PLATFORM 1M(3 FT)
No specific	1	MAGNIFYING GLASS POWER 10X
No specific	AR	MAT - WORK
No specific	AR	PAPER - ABRASIVE, FINE
No specific	1	VIBRO ENGRAVER
No specific	AR	WARNING NOTICE(S)

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.V05-019)	Waterproof silicon carbide abrasive paper
(Material No.V05-020)	waterproof silicon carbide
(Material No.V05-021)	Waterproof silicon carbide abrasive paper
(Material No.V06-018)	fluorescent penetrant

C. Referenced Information

REFERENCE	DESIGNATION
TASK 70-23-05-230-010-A	Local Application of Fluorescent Penetrant Inspection
TASK 72-31-11-000-010-B	Removal of the LP Compressor Fan Blades
TASK 72-31-11-400-010-C	Installation of the LP Compressor Fan Blades
LP Compressor Stage 1.5 Blades Blend Limits

3. Job Set-up
Subtask 72-00-00-941-171-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) in position 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) in position to tell persons not to energize the FADEC 1(2).

Subtask 72-00-00-941-172-A ** ON A/C NOT FOR ALL

B. Installation of the Ground Support Equipment
(1) Put the ACCESS PLATFORM 1M(3 FT) in position to give access to the engine intake.
(2) Put the MAT - WORK in position in the intake cowl.

NOTE: Make sure that the red warning pennants on the workmat can be seen from the outside of the aircraft.

NOTE: Make sure that the workmat has sufficient dimensions to give full protection to the lower half of the intake cowl.

4. Procedure
Subtask 72-00-00-020-078-A ** ON A/C NOT FOR ALL

A. Removal of the Fan Blades (Ref. AMM TASK 72-31-11-000-010)

Subtask 72-00-00-320-050-A ** ON A/C NOT FOR ALL

B. Repair of the Damage on the LP Compressor Stage 1.5 Blades

LP Compressor Stage 1.5 Blades Blend Limits ** ON A/C NOT FOR ALL

NOTE: It is allowed to repair the tip corners up to 13 blades.

(1) Blend to remove the damages on the LP compressor stage 1.5 blades. Use ABRASIVE STONE or and/or PAPER - ABRASIVE, FINE. Apply only light pressure to prevent any risk of overheating material. Any polish marks must be made in a radial direction from root to tip of the blades.

NOTE: Remove the minimum quantity of material necessary to remove the damage.

(2) Make smooth and polish the repaired area. Use Waterproof silicon carbide abrasive paper (Material No.V05-019) , waterproof silicon carbide (Material No.V05-020) and Waterproof silicon carbide abrasive paper (Material No.V05-021) .
Surface finish on the repaired area must be same as that of the adjacent area.

Subtask 72-00-00-210-159-A ** ON A/C NOT FOR ALL

C. Visual Inspection of the Repaired Area
(1) Use MAGNIFYING GLASS POWER 10X. Galls, nicks, dents, pits, scratches, scores, burrs, crack indications, spatter or a change in color to a darker than light straw color are not permitted.

Subtask 72-00-00-230-050-A ** ON A/C NOT FOR ALL

D. Penetrant Crack Test on the Repaired Area (Ref. AMM TASK 70-23-05-230-010)

NOTE: This subtask is not required if the blend repair is done only at tip corners.

(1) Use fluorescent penetrant (Material No.V06-018) (Highpost-emulsified). No cracks are allowed.

Subtask 72-00-00-350-054-A ** ON A/C NOT FOR ALL

E. Identification of the Repair
(1) A log entry is necessary when you have completed this repair. Write VRS1130 in the engine log book.
(2) At the next shop visit make a mark VRS1130 adjacent to the part number of the repaired blades. Use VIBRO ENGRAVER equipment.
(3) Blades repaired to this scheme, must be inspected and glass bead peened at the next shop visit.

Subtask 72-00-00-420-075-A ** ON A/C NOT FOR ALL

F. Install the Fan Blades (Ref. AMM TASK 72-31-11-400-010)

5. Close-up
Subtask 72-00-00-942-070-A ** ON A/C NOT FOR ALL

A. Removal of the support equipment
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the workmat from the engine air intake.
(3) Remove the access platform(s).
(4) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 13:00:29 UTC