DMC:V2500-A5-72-41-1500-00A-627A-C|Issue No:005|Issue Date:2021-02-01

Export Control

EAR Export Classification: Not subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3), except for the following Service Bulletins which are currently published as EAR Export Classification 9E991: SBE70-0992, SBE72-0483, SBE72-0580, SBE72-0588, SBE72-0640, SBE73-0209, SBE80-0024 and SBE80-0025.

Copyright

© IAE International Aero Engines AG (2001, 2014 - 2021) The information contained in this document is the property of © IAE International Aero Engines AG and may not be copied or used for any purpose other than that for which it is supplied without the express written authority of © IAE International Aero Engines AG. (This does not preclude use by engine and aircraft operators for normal instructional, maintenance or overhaul purposes.).

Applicability

All

Common Information

TASK 72-41-15-300-055 HP Compressor Stage 3 To 12 Rotor Blades - Weld Repair The Airfoil Tip - Repair - 055 (VRS6534)

Effectivity

FIG/ITEM	PART NO.	SERVICE BULLETIN	ASSEMBLY
01-200	6A8688	72-0561	A
01-500	6A8738	72-0560	B
01-800	6B1346	72-0587	C
02-170	6A8797	72-0560	D
02-185	6A8798	72-0560	D
02-200	6A8732	72-0560	D
02-215	6A8732	72-0560	D
02-216	6B1494	70-1006	D
02-217	6A8733	72-0560	D
02-270	6A8743	72-0560	E
02-285	6A8744	72-0560	E
02-300	6A8741	72-0560	E
02-315	6A8741	72-0560	E
02-316	6B1495	70-1006	E
02-317	6A8742	72-0560	E
02-370	6A8747	72-0560	F
02-385	6A8748	72-0560	F
02-400	6A8745	72-0560	F
02-415	6A8745	72-0560	F
02-416	6B1496	70-1006	F
02-417	6A8746	72-0560	F
02-470	6A8751	72-0561	G
02-485	6A8752	72-0561	G
02-500	6A8749	72-0561	G
02-515	6A8749	72-0561	G
02-517	6A8750	72-0561	G
02-570	6A8755	72-0561	H
02-585	6A8756	72-0561	H
02-600	6A8753	72-0561	H
02-615	6A8753	72-0561	H
02-617	6A8754	72-0561	H
02-670	6A8759	72-0561	J
02-685	6A8760	72-0561	J
02-700	6A8757	72-0561	J
02-715	6A8757	72-0561	J
02-717	6A8758	72-0561	J
02-770	6A8763	72-0561	K
02-785	6A8764	72-0561	K
02-800	6A8761	72-0561	K
02-815	6A8761	72-0561	K
02-817	6A8762	72-0561	K

Material of Component

PART IDENT	RR SYMBOL	MATERIAL
HP Compressor Rotor Blade(s) - Assemblies A, B, C, D, E and F	TAF or TDY or TDX	Titanium Alloy
HP Compressor Rotor Blade(s) - Assemblies G, H, J and K	QMP	Nickel Alloy

General Data

This TASK gives the procedure to Repair the Airfoil Tip of the HP Compressor Stage 3 to 12 Rotor Blades by Welding.

This TASK must only be applied when the instruction to do so is given in the relevant inspection /check, refer to EM Section 72-41-15.

This repair cannot be applied to Assembly B and C components which have the rubber sealing strip attached.

Discard the blades if, during the weld procedure, arcing has occurred onto any part of the blade.

This repair can be reapplied to the HP Compressor Stage 3 to 12 Rotor Blades if;

The minimum airfoil chord width dimensions are within the limits given in the relevant inspection/check

The component is within the repairable limits as given in Repair Scheme, Repair, VRS6510 TASK 72-41-15-300-040 (REPAIR-040).

The component is within the repairable limits as given in the Repair Scheme, Repair, VRS6151 TASK 72-41-15-300-041 (REPAIR-041), for Assemblies A, B, C and D.

The component is within the repairable limits as given in the Repair Scheme, Repair, VRS6152 TASK 72-41-15-300-043 (REPAIR-043), for Assemblies E and F.

At least one sample blade per stage must be repaired at the same time as the HP Compressor Rotor Blade(s) being repaired. The sample blade(s) will be used for a metallurgical quality control assessment of the repair process. The sample blade(s) must go through the complete repair process, to the point where they are sectioned, for the results to reflect the process applied to the components which are to be returned to service.

Where reference is made to a SUBTASK within a TASK in the form "TASK, SUBTASK" the operator must read and apply the complete TASK. The SUBTASK is listed only when the TASK gives options for the processing of the component. The specified SUBTASK instructs what option must be used during application of the TASK for the successful completion of the Repair Scheme VRS6534.

TASKS identified by SPM TASK are in the Standard Practices Manual (SPM).

Where necessary refer to the following figures for the relevant assembly, unless otherwise specified;

For Assembly A refer to Figure, Figure, Figure, Figure and Figure.

For Assembly B refer to Figure, Figure, Figure, Figure and Figure.

For Assembly C refer to Figure, Figure, Figure, Figure and Figure.

For Assembly D refer to Figure, Figure, Figure and Figure.

For Assembly E refer to Figure, Figure, Figure and Figure.

For Assembly F refer to Figure, Figure, Figure and Figure.

For Assembly G refer to Figure, Figure, Figure and Figure.

For Assembly H refer to Figure, Figure, Figure and Figure.

For Assembly J refer to Figure, Figure, Figure and Figure.

For Assembly K refer to Figure, Figure, Figure and Figure.

Price and availability.

Refer to International Aero Engines (IAE).

NOTE

It is possible that some materials in the consumable materials chart cannot be used for some or all of the necessary applications. Before you use the materials, make sure the types, quantities and applications of the materials necessary are legally permitted in your location. All persons must obey all applicable federal, state, local and provincial laws and regulations when it is necessary to work with these materials.

NOTE

To identify the consumable materials refer to the Overhaul Processes and Consumables Index (PCI).

NOTE

Other necessary consumable materials are referred to in the SPM tasks in this TASK.

Preliminary Requirements

Pre-Conditions

Action/Condition	Data Module/Technical Publication
Make sure that all the necessary cleaning and inspection procedures are done before this repair.

Support Equipment

Name	Manufacturer	Part Number / Identification
Abrasive Blast Equipment	LOCAL	Abrasive Blast Equipment
Argonarc Welding Equipment	LOCAL	Argonarc Welding Equipment
Chemical cleaning equipment	LOCAL	Chemical cleaning equipment
Dimensional inspection equipment	LOCAL	Dimensional inspection equipment
Grinding Machine	LOCAL	Grinding machine
Hardness Tester	LOCAL	Hardness Tester
Heat Treatment Equipment	LOCAL	Heat Treatment Equipment
Penetrant Crack Test Equipment	LOCAL	Penetrant crack test equipment
Radiographic Equipment	LOCAL	Radiographic Equipment
Standard workshop tools	LOCAL	Standard workshop tools
Vibro-engraving equipment	LOCAL	Vibro-engraving equipment

Consumables, Materials and Expendables

Name	Manufacturer	Part Number / Identification
CoMat 01-103 FERRIC CHLORIDE HEXAHYDRATE	K6835	CoMat 01-103
CoMat 02-001 ADHESIVE TAPE (MASKING)	LOCAL	CoMat 02-001
CoMat 03-195 WELDING WIRE TITANIUM	LOCAL	CoMat 03-195
CoMat 03-284 WELDING FILLER WIRE, NiBASE	LOCAL	CoMat 03-284
CoMat 03-285 TITANIUM WELD WIRE	IE306	CoMat 03-285
CoMat 03-348 WELDING WIRE	LOCAL	CoMat 03-348
CoMat 05-003 ABRASIVE MEDIUM ALUMINUM OXIDE, 120/220 GRADE	X222X	CoMat 05-003
CoMat 05-140 ABRASIVE STONE SILICON CARBIDE	LOCAL	CoMat 05-140
CoMat 06-022 FLUORESCENT PENETRANT (POST-EMULSIFIED ULTRA HIGH SENSITIVITY)	X222X	CoMat 06-022

Spares

NONE

Safety Requirements

NONE

Procedure

1. The source demonstration requirements of this repair means that any facility not authorized to accomplish this repair either utilize the authorized repair vendors listed below or contact the IAE repair services group to determine if a qualification program can be initiated at their facility.
  IAE International Aero Engines AG
  400 Main Street
  Mail Stop 121-10
  East Hartford CT 06118
  ATTN: Manager, Tech Services
2. Authorized repair vendor for Repair VRS6534 is listed below:
  Turbine Overhaul Services Pte, Ltd. (TOS)
  5 Tuas Drive Two- Mail Stop 107-58
  Singapore 638639
  Tel: 65-6860-2260
  Fax: 65-6862-1068
3. The designation by IAE of an Authorised Repair Vendor indicated that the Repair Vendor has demonstrated the necessary capability to enable it to carry out the listed repair work. However, IAE makes no warranty or representation concerning the qualifications or quality standards of the Repair Vendors to carry out the repair work and accepts no responsibility for any work that may be carried out by a Repair Vendor other than when IAE is listed as the Repair Vendor.
1. 1. Refer to Repair, VRS6635 TASK 72-41-15-300-053 (REPAIR-053).
1. Refer to the relevant figures as listed in Paragraph
2. 1. Make sure that the HP Compressor Rotor Blade(s) can be repaired.
    Examine the HP Compressor Rotor Blade(s) (all Assemblies) for previous applications of the surface finish repair VRS6150.
    Inspect for the repair identification symbol from the repair scheme VRS6150 on the blade(s).
    If the component is beyond the repairable limit of VRS6150:
    Reject.
    If the component is within the repairable limits of VRS6150:
    Continue with the repair.
    Examine the Assembly A, B, C and D HP Compressor Rotor Blade(s) for previous applications of the shot peening repair VRS6151.
    Inspect for the repair identification symbol from the repair scheme VRS6151 on the blade(s).
    If the component is beyond the repairable limit of VRS6151:
    Reject.
    If the component is within the repairable limit of VRS6151:
    Continue with the repair.
    Examine the Assembly E and F HP Compressor Rotor Blade(s) for previous applications of the shot peening repair VRS6152:
    Inspect the repair identification symbol from the repair scheme VRS6152 on the blade(s).
    If the component is beyond the repairable limit of VRS6152:
    Reject.
    If the component is within the repairable limit of VRS6152:
    Continue with the repair.
1. Refer to the relevant figures as listed in Paragraph
2. 1. Refer to for the approved vendor in Step or use Standard workshop tools.
  2. Remove the minimum quantity of material necessary to remove the damage.
  3. Continue to remove material until all the damage is removed.
  4. Make sure that all the damage is removed and the area is made smooth into the adjacent material.
1. Refer to the relevant figures as listed in Paragraph.
2. 1. Make sure that the damage has been removed.
    If any of the damage has not been removed:
    Repeat the repair from Step.
    If all of the damage has been removed:
    Continue with the repair.
3. 1. Use Dimensional inspection equipment.
    If the HP Compressor Rotor Blade(s) cannot be restored to its original height with a weld buildup of maximum 0.060 in. (1.52 mm):
    Reject.
    If the HP Compressor Rotor Blade(s) can be restored to its original height with a weld buildup of 0.060 in. (1.52 mm) maximum:
    Record the dimensions of the component(s) and continue with the repair.
1. 1. Refer to SPM TASK 70-11-08-300-503.
1. 1. Refer to the SPM TASK 70-11-39-300-503, SUBTASK 70-11-39-300-001.
  2. Use CoMat 01-103 FERRIC CHLORIDE HEXAHYDRATE.
1. 1. Refer to the SPM TASK 70-23-04-230-501.
  2. Use CoMat 06-022 FLUORESCENT PENETRANT (POST-EMULSIFIED ULTRA HIGH SENSITIVITY).
  3. Use Penetrant Crack Test Equipment.
    If no cracking is detected:
    Continue with the repair.
    If cracking is detected:
    Reject.
1. Refer to the relevant figures as listed in Paragraph.
2. 1. Use CoMat 02-001 ADHESIVE TAPE (MASKING).
3. 1. Refer to the SPM TASK 70-12-01-120-501.
  2. Use CoMat 05-003 ABRASIVE MEDIUM ALUMINUM OXIDE, 120/220 GRADE.
  3. Use Abrasive Blast Equipment.
4. Remove and discard the masking tape.
1. 1. Refer to SPM TASK 70-11-03-300-503.
  2. Use Chemical cleaning equipment.
    NOTE
    The HP Compressor Rotor Blade(s) must be fully clean before you do Step.
1. Refer to the relevant figures as listed in Paragraph.
2. 1. Refer to for the approved vendor in Step or use Standard workshop tools.
  2. Refer to the SPM TASK 70-31-02-310-501-001.
  3. For Assemblies A, B and C:
    Use CoMat 03-195 WELDING WIRE TITANIUM.
  4. For Assemblies D and E:
    Use CoMat 03-348 WELDING WIRE.
  5. For Assembly F:
    Use CoMat 03-285 TITANIUM WELD WIRE.
  6. For Assemblies G, H, J and K:
    Use CoMat 03-284 WELDING FILLER WIRE, NiBASE.
  7. Ensure sufficient weld filler is built up to allow machining to the given dimensions.
  8. Make sure there is full gas coverage around the weld area.
  9. Use locally manufactured chills as necessary.
  10. Use Argonarc Welding Equipment.
    NOTE
    An increase in blade length of up to a maximum of 0.060 in. (1.52 mm) is permitted by this repair.
1. 1. Refer to the SPM TASK 70-31-02-310-501-001. Use Heat Treatment Equipment.
  2. Use heat treatment equipment.
    For Assemblies A, B and C:
    Heat treat at a temperature of 1283 deg F. to 1301 deg F. (695 deg C. to 705 deg C.) for 2 hours. Cool to room temperature in a reducing atmosphere
    For Assemblies D and E:
    Heat treat at a temperature of 1103 deg F (595 deg C.) for 4 hours in an vacuum or argon atmosphere. Cool to room temperature in a reducing atmosphere.
    For Assembly F:
    Heat-treat at 1157 deg F (625 deg C.) for 2 hours in a vacuum or reducing atmosphere. Cool to room temperature in a reducing atmosphere.
    For Assemblies G, H, J and K:
    Heat-treat at 1400 deg F. (760 deg C) for 2 hours in a vacuum or reducing atmosphere. Cool at a rate of 100 deg F (56 deg C.) per hour to 1150 deg F (621 deg. C.) and hold for 4 hours. Cool to room temperature in a reducing atmosphere.
1. Refer to the relevant figures as listed in Paragraph.
2. 1. Refer to Paragraph.
  2. Use the sample blade that was repaired with the HP Compressor Rotor Blade(s) that are to be returned to service.
  3. The hardness variation across the welded area, the heat affected zone and the base material must be less than 30 HV.
    If the sample blade has a hardness variation of more than 30 HV:
    Further samples must be tested for the variation in hardness. Use additional sample blades that were repaired with the components to be returned to service.
    If more than 10 percent of the additional sample blades have a hardness variation of more than 30 HV:
    Quarantine the repaired components. Contact IAE technical services for information how to proceed with the repaired components.
    Include the repair scheme number, the results of the hardness check and the number of sample blades tested in the initial communication.
    NOTE
    If more than 10 percent of the sample blades have a hardness variation of more than 30 HV then the cause of the hardness variation needs to be investigated and resolved before applying VRS6534 to any other components.
    If less than 10 percent of the additional sample blades have a hardness variation of more than 30 HV:
    Continue with the repair.
    If the sample blade has a hardness variation of less than 30 HV:
    Continue with the repair
3. 1. Use one of the sample blades repaired with the HP Compressor Stage 3 to 12 Rotor Blades to be returned to service. The hardness of the repaired area and heat affected zone must not be less than 361HV.
    If the hardness value of the sample blade is below 361 HV:
    Additional sample blades should be selected for metallurgical assessment.
    If the hardness of the additional sample blades are below 361 HV:
    Quarantine the repaired components. Contact IAE technical services for information how to proceed.
    Include the repair scheme number, the results of the hardness check and the number of sample blades tested in the initial communication.
    NOTE
    If the additional sample blade(s) have a hardness of less than 361 HV then the cause of the hardness variation needs to be investigated and resolved before applying VRS6534 to any other components.
    If the hardness of the additional sample blade(s) are above 361HV:
    Continue with the repair.
    If the hardness of the sample blade is above 361 HV:
    Continue with the repair.
1. Refer to the relevant figures as listed in Paragraph.
2. 1. Use a Grinding Machine.
3. 1. Refer to the approved vendors in Step for special tooling and machines required to restore the airfoil contour or use Standard workshop tools.
4. 1. Use CoMat 05-140 ABRASIVE STONE SILICON CARBIDE or Standard workshop tools.
1. Refer to the relevant figures as listed in Paragraph.
2. 1. Electrical arcing from the welding process is not acceptable anywhere on the blade.
    If there are signs of arcing anywhere on the component:
    Reject.
    If there are no signs of arcing anywhere on the component:
    Continue with the repair.
3. 1. Inspect the HP Compressor Rotor Blade(s) for evidence of scratching or scoring as a result of the repair.
    If there is any scratches or scores on the airfoil surface:
    Reject.
    If there is no scratches or scores on the airfoil surface:
    Continue with the repair.
4. 1. The tip contour must be smooth with the adjacent material and within the given limits.
    If the airfoil contour at the blade tip does not blend smoothly with the surrounding material:
    Repeat the repair from Step.
    If the airfoil contour at the blade tip is not within the given limits:
    Reject.
    If the airfoil contour at the blade tip is within the given limits and blends smoothly with the surrounding material:
    Continue with the repair.
5. 1. Compare the blade height dimensions from before and after the repair, refer to the record made during Step.
  2. The weld material must be contained within the given limits.
  3. Use Dimensional inspection equipment.
    NOTE
    An increase in blade height by welding up to a maximum of 0.060 in. (1.52 mm) is permitted by this repair.
    If the welded material is not contained within 0.060 in. (1.52 mm) of the blade tip:
    Reject.
    If the blade height is less than the given limits:
    Reject.
    If the blade height is greater than the given limits:
    Repeat the repair from Step.
    If the blade height is within the given limits and the weld is contained within 0.060 in. (1.52 mm) of the blade tip:
    Continue with the repair.
1. DELETED.
1. Refer to the relevant figures as listed in Paragraph.
2. 1. Make sure that HP Compressor Rotor Blade satisfies the minimum chord width requirements as given in the relevant inspection procedures (identified by the applicable part number) located in section 72-41-15.
  2. Use Dimensional inspection equipment.
    If the repaired HP Compressor Rotor Blade(s) is less than the minimum chord width:
    Reject.
    If the repaired HP Compressor Rotor Blade(s) is equal to or greater than the minimum chord width:
    Continue with the repair.
1. 1. Refer to SPM TASK 70-11-08-300-503, SUBTASK 70-11-08-300-001.
1. 1. Refer to SPM TASK 70-11-39-300-503, SUBTASK 70-11-39-300-001.
1. 1. Refer to SPM TASK 70-23-04-230-501.
  2. Use CoMat 06-022 FLUORESCENT PENETRANT (POST-EMULSIFIED ULTRA HIGH SENSITIVITY).
  3. Use Penetrant Crack Test Equipment.
    If no cracking is detected:
    Continue with the repair.
    If cracking is detected:
    Reject.
1. 1. Refer to SPM TASK 70-26-01-260-501 and to the approved vendors in Step for the appropriate data card and radiographic inspection parameters.
  2. Use Radiographic Equipment.
    If the component shows evidence of cracking:
    Reject.
    If there is a pore(s) with a diameter greater than 0.006 in. (0.15 mm) in the weld:
    Reject.
    If there are pores with a diameter less than 0.006 in. (0.15 mm) that are less than 0.200 in. (5.08 mm) apart:
    Reject.
    If there are pores with a diameter less than 0.006 in. (0.15 mm) and the pores break the surface of the component:
    Reject.
    If there are pores with a diameter less than 0.006 in. (0.15 mm) that are less than 0.04 in. (1.00 mm) from the leading or trailing edge:
    Reject.
    If there is no cracking and there are no pores with a diameter greater than 0.006 in. (0.1 5mm), there are no pores that are less than 0.200 in. (5.08 mm) apart, no pores that break the surface of the airfoil and no pores that are less than 0.04 in. (1.00 mm) from the leading and trailing edge(s):
    Continue with the repair.
1. 1. Repair VRS6150, TASK 72-41-15-300-040 (REPAIR-040).
1. 1. For Assemblies A, B, C, and D:
    Refer to the repair VRS6151, TASK 72-41-15-300-041 (REPAIR-041).
  2. For Assemblies E and F:
    Refer to the repair VRS6152, TASK 72-41-15-300-043 (REPAIR-043).
1. 1. Refer to Repair, VRS6236 TASK 72-41-15-300-035 (REPAIR-035) or Repair, VRS9297 TASK 72-41-15-300-058 (REPAIR-058).
1. 1. For Assembly B:
    Refer to Repair, VRS6214, TASK 72-41-15-300-031 (REPAIR-031).
  2. For Assembly C:
    Refer to Repair, VRS6215, TASK 72-41-15-300-032 (REPAIR-032).
1. 1. For Assemblies A, B and C:
    Refer to Repair, VRS6486, TASK 72-41-15-300-046 (REPAIR-046).
  2. For Assemblies D:
    Refer to Repair, VRS6495, TASK 72-41-15-300-049 (REPAIR-049).
  3. For Assemblies E:
    Refer to Repair, VRS6496, TASK 72-41-15-300-050 (REPAIR-050).
  4. For Assemblies F:
    Refer to Repair, VRS6497, TASK 72-41-15-300-051 (REPAIR-051).
1. 1. For Assembly D, E and F, refer to Figure.
    NOTE
    If the HP Compressor Rotor Blade(s) is already identified with the repair scheme identification symbol from a previous repair application, further identification is not necessary.
  2. For Assembly G, H, J and K, refer to Figure.
2. 1. Refer to SPM TASK 70-09-00-400-501.
  2. Mark the number 3 inside a triangle using the vibration peen method.
3. 1. Use CoMat 05-140 ABRASIVE STONE SILICON CARBIDE.

HP Compressor Stage 3 Rotor Blade (Assembly A) - Repair Details and Dimensions

HP Compressor Stage 4 Rotor Blade (Assembly B) - Repair Details and Dimensions

HP Compressor Stage 5 Rotor Blade (Assembly C) - Repair Details and Dimensions

HP Compressor Stage 6 Rotor Blade (Assembly D) - Repair Details and Dimensions

HP Compressor Stage 7 Rotor Blade (Assembly E) - Repair Details and Dimensions

HP Compressor Stage 8 Rotor Blade (Assembly F) - Repair Details and Dimensions

HP Compressor Stage 9 Rotor Blade (Assembly G) - Repair Details and Dimensions

HP Compressor Stage 10 Rotor Blade (Assembly H) - Repair Details and Dimensions

HP Compressor Stage 11 Rotor Blade (Assembly J) - Repair Details and Dimensions

HP Compressor Stage 12 Rotor Blade (Assembly K) - Repair Details and Dimensions

HP Compressor Stage 3 to 5 Rotor Blades (Assembly A to C) - Repair Details and Dimensions

HP Compressor Stage 6 To 8 Rotor Blades (Assembly D To F) - Repair Details And Dimensions

HP Compressor Stage 3 to 12 Rotor Blades (All Assemblies) - Repair Details and Dimensions

HP Compressor Stage 3 to 12 Rotor Blades (Assembly A to E and J) - Repair Details and Dimensions

HP Compressor Stage 3 to 12 Rotor Blades (Assembly F to H and K) - Repair Details and Dimensions

HP Compressor Stage 9 To 12 Rotor Blades (Assembly G To K) - Repair Marking Zones

Legend

HP Compressor Stage 9 To 12 Rotor Blades (Assembly G To K) - Repair Marking Zones

1. Dovetail Side Surface Marking Area. Both Sides Of Dovetail.

2. Platform Underside Surfaces Marking Areas. Do Not Mark On Outer Edges.

3. Dovetail Bottom Surfaces Marking Areas.

4. 0.0315 Inch (0.800 mm) Minimum.

5. Corner Radius Minimum. Both Sides Of Dovetail.

6. Fillet Radius Minimum.

7. Corner Radius Minimum.

8. Distance From Dovetail Fillet Radius To The Projected Dovetail Bottom Surface. Do Not Extend Marking Into The Fillet Radius.

Requirements After Job Completion

Follow-On Conditions

NONE

Manufacturer Code:	IE306
Enterprise Name:	DELETED. SEE CAGE CODE KB362
BU Name:	VBC LTD

Manufacturer Code:	K6835
Enterprise Name:	MED-LAB LTD
BU Name:	MED-LAB LTD
Street:	COPELAND ST
City:	DERBY
Zip Code:	DE1 2PU
Country:	GREAT BRITAIN
Phone Number:	44-1332-349094
Fax Number:	44-1332-371237
Email:	sales@med-lab.co.uk
Internet:	www.med-lab.co.uk

Manufacturer Code:	LOCAL
Enterprise Name:	LOCALLY SUPPLIED

Manufacturer Code:	X222X
Enterprise Name:	N/A – REFER TO APPLICABLE COMAT SUFFIX

Manufacturer Code:	LOCAL
Tool Number:	Abrasive Blast Equipment
Tool Name:	Abrasive Blast Equipment

TASK 72-41-15-300-055 HP Compressor Stage 3 To 12 Rotor Blades - Weld Repair The Airfoil Tip - Repair - 055 (VRS6534)

Export Control

Copyright

Applicability

Common Information

TASK 72-41-15-300-055 HP Compressor Stage 3 To 12 Rotor Blades - Weld Repair The Airfoil Tip - Repair - 055 (VRS6534)

Effectivity

Material of Component

General Data

NOTE

NOTE

NOTE

Preliminary Requirements

Pre-Conditions

Support Equipment

Consumables, Materials and Expendables

Spares

Safety Requirements

Procedure

Repair Facilities

SUBTASK 72-41-15-330-001 Remove the Clapper Coating - Assembly A

SUBTASK 72-41-15-220-001 Examine the Blades to be Repaired

SUBTASK 72-41-15-350-001 Remove the Damage from the HP Compressor Rotor Blade(s) Tip

CAUTION

CAUTION

CAUTION

CAUTION

SUBTASK 72-41-15-220-002 Visually and Dimensionally Inspect

SUBTASK 72-41-15-110-001 Swab Etch the Repair Area - Assemblies A, B, C, D, E and F

SUBTASK 72-41-15-110-002 Swab Etch the Repair Area - Assembly G, H, J and K

SUBTASK 72-41-15-230-001 Fluorescent Penetrant Inspect

SUBTASK 72-41-15-120-001 Vapour Blast the Repair Area

CAUTION

SUBTASK 72-41-15-110-003 Chemically Clean

NOTE

SUBTASK 72-41-15-310-001 Argonarc Weld Repair the HP Compressor Rotor Blade Tips

CAUTION

NOTE

SUBTASK 72-41-15-370-001 Heat-treat the HP Compressor Rotor Blades

SUBTASK 72-41-15-220-003 Do a Hardness Check

NOTE

NOTE

SUBTASK 72-41-15-350-002 Machine the Component to Height and Restore the Airfoil Contour

CAUTION

CAUTION

CAUTION

CAUTION

SUBTASK 72-41-15-220-004 Visually and Dimensionally Inspect the HP Compressor Rotor Blade(s)

NOTE

SUBTASK 72-41-15-350-003 Polish the HP Compressor Rotor Blade Airfoil Surface and Contour - Stages 3 to 12

SUBTASK 72-41-15-220-005 Dimensionally Inspect

SUBTASK 72-41-15-110-004 Swab Etch the Repair Area - Assemblies A, B, C, D, E and/or F

SUBTASK 72-41-15-110-005 Swab Etch the Repair Area - Assembly G, H, J and K

SUBTASK 72-41-15-230-002 Fluorescent Penetrant Inspect

SUBTASK 72-41-15-260-001 Radiographically Inspect the Repair Area

SUBTASK 72-41-15-380-001 Restore the Airfoil Surface Condition

SUBTASK 72-41-15-380-002 Shotpeen the Dovetail Root - Assemblies A, B, C, D, E and F

SUBTASK 72-41-15-340-001 Apply the Clapper Coating - Assembly A

SUBTASK 72-41-15-360-001 Apply the Rubber Sealing Strips - Assemblies B and C

SUBTASK 72-41-15-380-003 Apply the Dry Film Lubricant - Assemblies A, B, C, D, E and F

SUBTASK 72-41-15-350-004 Identify the Repair

CAUTION

NOTE

Figure: HP Compressor Stage 3 Rotor Blade (Assembly A) - Repair Details and Dimensions

HP Compressor Stage 3 Rotor Blade (Assembly A) - Repair Details and Dimensions

Figure: HP Compressor Stage 3 Rotor Blade (Assembly A) - Repair Details and Dimensions

HP Compressor Stage 3 Rotor Blade (Assembly A) - Repair Details and Dimensions

Figure: HP Compressor Stage 3 Rotor Blade (Assembly A) - Repair Details and Dimensions

HP Compressor Stage 3 Rotor Blade (Assembly A) - Repair Details and Dimensions

Figure: HP Compressor Stage 4 Rotor Blade (Assembly B) - Repair Details and Dimensions

HP Compressor Stage 4 Rotor Blade (Assembly B) - Repair Details and Dimensions

Figure: HP Compressor Stage 4 Rotor Blade (Assembly B) - Repair Details and Dimensions

HP Compressor Stage 4 Rotor Blade (Assembly B) - Repair Details and Dimensions

Figure: HP Compressor Stage 4 Rotor Blade (Assembly B) - Repair Details and Dimensions

HP Compressor Stage 4 Rotor Blade (Assembly B) - Repair Details and Dimensions

Figure: HP Compressor Stage 5 Rotor Blade (Assembly C) - Repair Details and Dimensions

HP Compressor Stage 5 Rotor Blade (Assembly C) - Repair Details and Dimensions

Figure: HP Compressor Stage 5 Rotor Blade (Assembly C) - Repair Details and Dimensions

HP Compressor Stage 5 Rotor Blade (Assembly C) - Repair Details and Dimensions

Figure: HP Compressor Stage 5 Rotor Blade (Assembly C) - Repair Details and Dimensions