V2500-ENG-72-A0615 

Page 1 of 2 

IAE PROPRIETARY INFORMATION

© IAE International Aero Engines AG (date as above). All right reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

ALERT SERVICE BULLETIN REVISION NOTICE

NON-MODIFICATION SERVICE BULLETIN — ENGINE — HIGH PRESSURE (HP)

COMPRESSOR — STAGE 3 TO 8 COMPRESSOR DRUM — ULTRASONIC INSPECTION

(USI) FOR STRESS CORROSION CRACKING

Turbojet Engine Alert Service Bulletin No. V2500-ENG-72-A0615

Revision No. 6 dated September 4, 2014.

Revision History

Original Issue July 19, 2010

Revision 1 dated August 2, 2010

Revision 2 dated November 24, 2010

Revision 3 dated September 20, 2011

Revision 4 dated May 2, 2013

Revision 5 dated August 5, 2014

Revision 6 dated September 4, 2014

Reason for the Revision

For Revision 5: 

 To revise the Engine Effectivity and Compliance in the Planning Information section.

To add Additional Instruction.

To add Accomplishment Proforma Table in the Accomplishment Instructions.

To add Material Data Table for A1/A5/D5 Engine models.

To delete FAA Airworthiness Directive Number in References.

For Revision 6:

 To correct the A319 Engine Effectivity Data

 To correct the group A Time Compliance Table.

 To update Group C Engine Serial Numbers.

 To correct the initial issue date of this Service Bulletin.

Effect of Revision on Prior Compliance

None.
V2500-ENG-72-A0615 

Page 2 of 2 

IAE PROPRIETARY INFORMATION

© IAE International Aero Engines AG (date as above). All right reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

This is a Complete Revision (Not Applicable to the SGML version)

The format of this Service Bulletin has been changed from previous versions. This revision shows

flow bars and the revision date on the bottom of every page. Technical changes incorporated in this

revision are marked with revision bars. The contents are in accordance with the list of effective

pages.

MODEL APPLICATION

V2500-A1, V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, V2533-A5, V2525-D5, V2528-D5

BULLETIN ISSUE SEQUENCE

V2500 Series 72-A0615

A copy of this Revision Notice and any future revision notices must be filed as a permanent

record with your copy of the subject bulletin.
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 1 of 23 

© IAE International Aero Engines AG (date as above). All rights reserved. 

ALERT SERVICE BULLETIN

NON-MODIFICATION SERVICE BULLETIN — ENGINE — HIGH PRESSURE (HP)

COMPRESSOR — STAGE 3 TO 8 COMPRESSOR DRUM — ULTRASONIC INSPECTION

(USI) FOR STRESS CORROSION CRACKING

MODEL APPLICATION

V2500-A1, V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5,

V2533-A5, V2525-D5, V2528-D5

BULLETIN ISSUE SEQUENCE

V2500 Series 72-A0615

 ATA NUMBER

 72-41-11

IAE PROPRIETARY INFORMATION

This document is the property of International Aero Engines (IAE). You may not possess, use, copy

or disclose this document or any information in it, for any purpose, including without limitation to

design, manufacture, or repair parts, or obtain FAA or other government approval to do so, without

IAE's express written permission. Neither receipt nor possession of this document alone, from any

source, constitutes such permission. Possession, use, copying or disclosure by anyone without IAE's

express written permission is not authorized and may result in criminal and/or civil liability.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Compliance Category

3
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 2 of 23 

© IAE International Aero Engines AG (date as above). All rights reserved. 

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Summary

The purpose of this Service Bulletin is to provide Ultrasonic Inspection (USI) thresholds of the HP compressor Stage 8

disk to be carried out "In-Service" and "At Overhaul". Cracks were highlighted during an Engine Manual crack inspection

of the Stage 7-8 disk internal cavity.

1. Planning Information

A. Effectivity Data

(1) Airbus A319 

(a) V2522-A5, V2524-A5, V2527M-A5 Engines from Serial No. V10001 to Serial No. 

 V13190.

(b) V2522-A5, V2524-A5, V2527M-A5 Engines from Serial No. V15001 to Serial No. 

V16728 except Serial No. V16707

 (2) Airbus A320 

(a) V2500-A1 Engine Serial No. V0001 to Serial No. V0361

(b) V2527-A5, V2527E-A5 Engines from Serial No. V10001 to Serial No. V13190.

(c) V2527-A5, V2527E-A5 Engines from Serial No. V15001 to Serial No. V16728 except Serial No. V16707.

(3) Airbus A321 

 (a) V2530-A5, V2533-A5 Engines from Serial No. V10001 to Serial No. V13190.

(b) V2530-A5, V2533-A5 Engines from Serial No. V15001 to Serial No. V16728 except Serial No. V16707.

(4) Boeing MD-90

 (a) V2525-D5, V2528-D5 Engines from Serial No. V20001 to Serial No.V20285

Note : For an engine not to require an Ultrasonic Inspection (USI) in accordance with this Non- 

 Modification Service Bulletin, the condition that follows must be achieved:

The engine must have installed a HP Compressor Stage 3-8 Drum Assembly (72-41-11-01-200)

that has never operated with Pre Service Bulletin V2500-ENG-72-0632

(72-41-12, 01-602) standard nuts.

B. Concurrent Requirements

The Non-Modification Service Bulletin that follows must be done at the same time as this one:

V2500-ENG-72-0638.

NON-MODIFICATION SERVICE BULLETIN - ENGINE - HIGH PRESSURE (HP) COMPRESSOR -

STAGE 3 TO 8 COMPRESSOR DRUM - ULTRASONIC INSPECTION PROCEDURE (USI)

 C Reason

 (1) Condition:

 Cracks have been found on the High Pressure (HP) compressor Stage 3-8 drum assembly during 

 overhaul.
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 3 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

(2) Background:

 Cracks were highlighted during an Engine Manual crack inspection of the Stage 7-8 disk internal cavity.

(3) Objective:

 To define Ultrasonic Inspection (USI) thresholds of the HP compressor Stage 8 disk to be carried out "In-

 Service" and "At Overhaul".

(4) Substantiation:

 Cracks have been found on the HP compressor Stage 3-8 drum assembly during overhaul. Inspections (Eddy

 Current, Fluorescent Penetrant and Ultrasonic) have been developed and have shown the capability of

 detecting cracks "In-Service" and "At Overhaul".

(5) Effects of Bulletin on:

(a) Removal/Installation:

 

Not affected.

(b) Disassembly/Assembly:

Not affected.

(c) Cleaning:

 

Not affected.

(d) Inspection/Check:

Not affected.

(e) Repair:

 

Not affected.

(f) Testing:

 

Not affected.

(6) Supplemental Information

None.

D. Description

This Non-Modification Service Bulletin identifies the thresholds and intervals for the USI inspection of the HP

compressor Stage 8 disk inner cavity for the engines listed under Effectivity to be accomplished in accordance with

Reference 6, Non-Modification Service Bulletin V2500-ENG-72-0638 initial issue or later approved revision.

 E. Compliance

Category 3
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 4 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Note: The compliance paragraph is divided into six groups (A to F). For individual applicability and the 

 resulting ultrasonic inspection start, threshold and inspection interval, refer to the group description.

Note: Additionally, IAE offers Grace Periods that can interrupt/delay the Ultrasonic Inspection (USI) for an

 applicable drum, if the drum is cleaned, Fluorescent Penetrant Inspected (FPI) and/or Eddy Current

 Inspected (ECI) at overhaul. Refer to the grace period table below the compliance time table for

 applicability.

 The Inspection interval remains as instructed in the applicable Compliance Time table, once the Grace

 Period is exhausted.
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 5 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Group A:

 V2500-A1 Engines V0008, V0013, V0026, V0050, V0052, V0064, V0068, V0070, V0073, V0077, V0080,

 V0087, V0094, V0105, V0109, V0114, V0116, V0125, V0145, V0149, V0150, V0151, V0158, V0160,

 V0180, V0197, V0200, V0220, V0221, V0222, V0228, V0233, V0236, V0243, V0244, V0252, V0281,

 V0296, V0297, V0298, V0299, V0303, V0306, V0309, V0312, V0329, V0338, V0342, V0350, V0352,

 V0354, V0355, V0356 and V0358.

HP Compressor Stage 3-8 Drum Assembly PNs: PN 6A8236, PN 6A8318, PN 6B1401, PN 6B1403 and

PN 6B1406 (Ti6246 Drum Material).

Compliance Time Table:

Inspection

location

HP compressor

3-8 Drum cycles

since new

Threshold From Regular Repeat

Inspection

Interval

Outer and Inner 

Diameters

>8000 Accomplish within

200 cycles.

Date of Revision 6 of

Non-Modification Service

Bulletin V2500-ENG-72-

A0615.

Not more than

750 cycles.

<=8000 Accomplish within 200

cycles of the drum

reaching 8000 cycles.
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 6 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Grace Periods Table:

 Compliance 

 Group

Nut/Drum Standard Required Drum Condition Permitted

Grace Period

(Cycles)

A

For drums that were fitted

with any standard of nut

Reference 1, Engine Manual, TASK 72-41-11-110-001

(Clean)

Reference 1, Engine Manual, TASK 72-41-11-200-001 (FPI)

4000

Reference 1, Engine Manual, TASK 72-41-11-110-001

(Clean)

Reference 1, Engine Manual, TASK 72-41-11-200-001 (FPI)

Reference 3, Non-Modification Service Bulletin V2500-ENG72-0625 (ECI)

5000

For drums that were

fitted with Reference 4,

V2500-ENG-72-0632

initial issue, dated 

December 20th 2012 or

later approved revision

Reference 1, Engine Manual, TASK 72-41-11-110-001

(Clean)

Reference 5, Non-Modification Service Bulletin

V2500-ENG-72-0637 (Enhanced FPI)

6000

Reference 1, Engine Manual, TASK 72-41-11-110-001

(Clean)

Reference 5, Non-Modification Service Bulletin

V2500-ENG-72-0637 (Enhanced FPI)

Reference 3, Non-Modification Service Bulletin

V2500-ENG-72-0625 (ECI)

8000
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 7 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Inspection

location

HP compressor

3-8 Drum cycles

since new

Threshold From Regular Repeat

Inspection

Interval

Outer and Inner

Diameters

>8000 Accomplish within 200

cycles.

Date of Revision 6 of

Non-Modification Service

Bulletin V2500-ENG-72-

A0615.

Not more than

750 cycles. <=8000 Accomplish within 200

cycles of the drum

reaching 8000 cycles.

Group B:

V2500-A1 Engines V0023, V0024, V0027, V0028, V0030, V0036, V0038, V0043, V0044, V0045, V0056,

V0057, V0059, V0062, V0063, V0071, V0072, V0074, V0079, V0082, V0092, V0095, V0097, V0098, V0100,

V0102, V0107, V0108, V0117, V0118, V0133, V0134, V0140, V0198, V0224, V0234, V0238, V0257, V0270,

V0271, V0272, V0273, V0278, V0279, V0280, V0282, V0290, V0304, V0307, V0308, V0330, V0341, V0345,

V0346, V0353, V0357, V0359 and V0360.

HP compressor stage 3-8 drum assembly P/Ns: 6A2030, 6A2355, 6A2455, 6A2645, 6A3508, 6A3648, 6A3934, 6A3936, 

6A4189, 6A5467, 6A5592, 6A5594, 6A5659, 6A6473, 6A7379, 6A7380, 6A7382, 6A7384, 6A7385, 6A7401, 6A8350, 

6B1379, 6B1380, 6B1381, 6B1382, 6B1383, 6B1384 and 6B1402 ( Ti5331 Drum Material).

Compliance Time Table:
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 8 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Grace Periods Table:

Compliance

Group

Nut/Drum Standard Required Drum Condition Permitted

Grace Period

(Cycles)

For drums that were

fitted with any

standard of nut.

Reference 1, Engine Manual, TASK 72-41-11-110-001

(Clean)

Reference 1, Engine Manual, TASK 72-41-11-200-001 (FPI)

2000

B

Reference 1, Engine Manual, TASK 72-41-11-110-001

(Clean)

Reference 1, Engine Manual, TASK 72-41-11-200-001 (FPI)

Reference 3, Non-Modification Service Bulletin V2500-ENG72-0625 (ECI)

5000

For drums that were

fitted with Reference

4,

V2500-ENG-72-0632

initial issue, dated

December 20th 2012

or later approved

revision

Reference 1, Engine Manual, TASK 72-41-11-110-001

(Clean)

Reference 5, Non-Modification Service Bulletin

V2500-ENG-72-0637 (Enhanced FPI)

5000

Reference 1, Engine Manual, TASK 72-41-11-110-001

(Clean)

Reference 5, Non-Modification Service Bulletin

V2500-ENG-72-0637 (Enhanced FPI)

Reference 3, Non-Modification Service Bulletin

V2500-ENG-72-0625 (ECI)

8000
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 9 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Group C:

V2500-A5 Engines V10001, V10005, V10096, V10101, V10102, V10103, V10195, V10196, V10204,

V10341, V10475, V10478, V10481, V10490, V10518, V10519, V10937, V11009, V11475, V11482,

V11516, V11521, V11788, V11848, V11849, V11871, V11879, V11884, V11899, V11904, V11917,

V11937, V11978, V11980, V11982, V11999, V12000, V12002, V12037, V12038, V12044, V12116,

V12120, V12122, V12129, V12131, V12140, V12142, V12148, V12150, V12166, V12168, V12171,

V12174, V12178, V12223, V12227, V12242, V12252, V12270, V12289, V12294, V12314, V12327,

V12330, V12331, V12333, V12340, V12342, V12345, V12346, V12354, V12377, V12379, V12389,

V12391, V12394, V12396, V12400, V12404, V12408, V12412, V12414, V12416, V12420, V12425,

V12427, V12432, V12443, V12445, V12447, V12449, V12451, V12477, V12479, V12480, V12488,

V12489, V12495, V12524, V12539, V12541, V12543, V12554, V12569, V12573, V12575, V12576,

V12586, V12601, V12603, V12622, V12646, V12654, V12668, V12703, V12705, V12721, V12723,

V12725, V12758, V12774, V12793, V12795, V12809, V12813, V12849, V12851, V12879, V12881,

V12884, V12888, V12921, V12930, V12968, V13071, V13124, V13137, V13170, V13184, V13186,

V13187, V15003, V15006, V15007, V15009, V15033, V15050, V15104, V15111, V15161, V15162,

V15168, V15191, V15207, V15216, V15226, V15253, V15300, V15304, V15347, V15349, V15453,

V15465, V15469, V15508, V15518, V15530, V15531, V15537, V15602, V15610, V15620, V15622,

V15633, V15635, V15652, V15653, V15676, V15678, V15680, V15702, V15726, V15728, V15731,

V15732, V15738, V15765, V15768, V15770, V15805, V15865, V15866, V15867, V15872, V15873,

V15918, V15920, V15924, V15926, V15949, V15951, V15976, V15985, V15986, V15996, V15998,

V16000, V16002, V16034, V16035, V16057, V16061, V16085, V16090, V16091, V16113, V16117,

V16129, V16130, V16171, V16173, V16177, V16179, V16185, V16187, V16190, V16191, V16193,

V16237, V16238, V16290, V16292, V16321, V16322, V16340, V16341, V16363, V16366, V16378,

V16379, V16400, V16401, V16418, V16419, V16430, V16431, V16478, V16493, V16515, V16516,

V16535, V16553, V16554, V16556, V16599, V16602, V16603, V16615, V16617, V16618, V16666,

V16667, V16684 and V16685.

HP Compressor Stage 3-8 Drum Assembly PNs: PN 6A7705, PN 6A8236, PN 6A8316, PN 6B1385, PN

6B1386, PN 6B1392, PN 6B1393, PN 6B1404 and PN 6B1405 (Ti6246 Drum Material).

Compliance Time Table:

Inspection

location

HP compressor

3-8 Drum cycles

since new

Threshold From Regular Repeat

Inspection

Interval

 Outer and Inner 

 Diameters

>6250 Accomplish 

within 200 cycles.

Date of Revision 6 of

Non-Modification Service

Bulletin V2500-ENG-72-

A0615.

Not more than

750 cycles.

<=6250 Accomplish within 200

cycles of the drum

reaching 6250 cycles.
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615

 IAE PROPRIETARY INFORMATION Page 10 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Grace Periods Table:

Compliance

Group

Nut/Drum Standard Required Drum Condition Permitted

Grace Period

(Cycles)

C

For drums that were

fitted with any

standard of nut.

Reference 1, or Reference 2, Engine Manual, TASK 72-41-

11-110-001 (Clean)

Reference 1, or Reference 2, Engine Manual, TASK 72-41-

11-200-001 (FPI)

4000

Reference 1, or Reference 2, Engine Manual, TASK 72-41-

11-110-001 (Clean)

Reference 1, or Reference 2, Engine Manual, TASK 72-41-

11-200-001 (FPI)

Reference 3, Non-Modification Service Bulletin V2500-ENG72-0625 (ECI)

5000

 For drums that were 

 fitted with Reference 4, 

 V2500-ENG-72-0632

 initial issue, dated

 December 20th 2012 or

 later approved revision

Reference 1, or Reference 2, Engine Manual, TASK 72-41-

11-110-001 (Clean)

Reference 5, Non-Modification Service Bulletin

V2500-ENG-72-0637 (Enhanced FPI)

6000

Reference 1, or Reference 2, Engine Manual, TASK 72-41-

11-110-001 (Clean)

Reference 5, Non-Modification Service Bulletin

V2500-ENG-72-0637 (Enhanced FPI)

Reference 3, Non-Modification Service Bulletin

V2500-ENG-72-0625 (ECI)

8000
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 11 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Inspection

location

HP compressor

3-8 Drum cycles

since new

Threshold From Regular Repeat

Inspection Interval

Outer and Inner

Diameters

>3750 Accomplish within 200

cycles.

Date of Revision 6 of

Non-Modification Service

Bulletin V2500-ENG-72-

A0615.

Not more than 500

cycles.

<=3750 Accomplish within 200

cycles of the drum

reaching 3750 cycles.

Group D:

V2500-A5 Engines V10310, V10408, V10503, V10531 and V10860.

 HP Compressor Stage 3-8 Drum Assembly PNs: PN 6A4900, PN 6A5467, PN 6A6473, PN 6A7383, PN 6A7384, 

 PN 6A7385, PN 6A7401, PN 6B1379, PN 6B1380, PN 6B1381, PN 6B1384, PN 6B1387 and PN 6B1391 (Ti5331 

 Drum Material).
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 12 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Grace Periods Table:

Compliance 

Group

Nut/Drum Standard Required Drum Condition Permitted

Grace Period

(Cycles)

D

For drums that

were fitted with any

standard of nut.

Reference 1, or Reference 2, Engine Manual, TASK 72-41-11-

110-001 (Clean)

Reference 1, or Reference 2, Engine Manual, TASK 72-41-11-

200-001 (FPI)

2000

Reference 1, or Reference 2, Engine Manual, TASK 72-41-11-

110-001 (Clean)

Reference 1, or Reference 2, Engine Manual, TASK 72-41-11-

200-001 (FPI)

Reference 3, Non-Modification Service Bulletin V2500-ENG-72-

0625 (ECI)

3000

For drums that

were fitted with

Reference 4,

V2500-ENG-72-

0632

initial issue, dated

December 20th

2012 or later

approved revision

Reference 1, or Reference 2, Engine Manual, TASK 72-41-11-

110-001 (Clean)

Reference 5, Non-Modification Service Bulletin V2500-

ENG-72-0637 (Enhanced FPI)

5000

Reference 1, or Reference 2, Engine Manual, TASK 72-41-11-

110-001 (Clean)

Reference 5, Non-Modification Service Bulletin V2500-

ENG-72-0637 (Enhanced FPI)

Reference 3, Non-Modification Service Bulletin V2500-

ENG-72-0625 (ECI)

5000
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 13 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Inspection

location

HP compressor

3-8 Drum cycles

since new

Threshold From Regular Repeat

Inspection

Interval

Outer and Inner

Diameters

>12500 Accomplish within 200

cycles.

Date of

Revision 6 of

Non-Modification

Service Bulletin

V2500-ENG-72-

A0615.

Not more than

750 cycles.

<=12500 Accomplish within 200

cycles of the drum

reaching 12500

cycles.

Group E:

 V2500-A1/A5/D5 Engines that are not listed specifically in Groups A, B, C or D.

HP Compressor Stage 3-8 Drum Assembly PNs: PN 6A7705, PN 6A8236, PN 6A8316, PN 6A8318, PN

6B1385, PN 6B1386, PN 6B1392, PN 6B1393, PN 6B1401, PN 6B1403, PN 6B1404, PN 6B1405 and PN

6B1406 (Ti6246 Drum Material).

Compliance Time Table:
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 14 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Grace Periods Table:

Compliance

Group

Nut/Drum Standard Required Drum Condition Permitted

Grace Period

(Cycles)

E

For drums that

were fitted with

any standard of

nut.

Reference 1, or Reference 2, Engine Manual, TASK 72-41-11-

110-001 (Clean)

Reference 1, or Reference 2, Engine Manual, TASK 72-41-11-

200-001 (FPI)

4000

Reference 1, or Reference 2, Engine Manual, TASK 72-41-11-

110-001 (Clean)

Reference 1, or Reference 2, Engine Manual, TASK 72-41-11-

200-001 (FPI)

Reference 3, Non-Modification Service Bulletin V2500-ENG-72-

0625 (ECI)

10000

For drums that were

fitted with Reference 4,

V2500-ENG-72-0632 

initial issue, dated

 December 20th 2012

or later approved

revision

Reference 1,or Reference 2, Engine Manual, TASK 72-41-11-

110-001 (Clean)

Reference 5, Non-Modification Service Bulletin V2500-

ENG-72-0637 (Enhanced FPI)

6000

Reference 1, or Reference 2, Engine Manual, TASK 72-41-11-

110-001 (Clean)

Reference 5, Non-Modification Service Bulletin V2500-

ENG-72-0637 (Enhanced FPI)

Reference 3, Non-Modification Service Bulletin V2500-

ENG-72-0625 (ECI)

13000
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 15 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Inspection

location

HP compressor

3-8 Drum cycles

since new

Threshold From Regular Repeat

Inspection Interval

Outer and Inner

Diameters

>9000 Accomplish within 200

cycles.

Date of Revision 6 of

Non-Modification Service

Bulletin V2500-ENG-72-

A0615.

Not more than 750

cycles.

<=9000 Accomplish within 200

cycles of the drum

reaching 9000 cycles.

Group F:

V2500-A1/A5/D5 Engines that are not listed specifically in Groups A, B, C or D.

HP Compressor Stage 3-8 Drum Assembly PNs: PN 6A2030, PN 6A2355, PN 6A2455, PN 6A6473, PN 6A8350,

PN 6A2645, PN 6A3508, PN 6A3648, PN 6A3934, PN 6A3936, PN 6A4900, PN 6A5467, PN 6A5592, PN 6A6973,

PN 6A7379, PN 6A7380, PN 6A7382, PN 6A7383, PN 6A7384, PN 6A7385, PN 6A7401, PN 6A8250, 

PN 6A5594, PN 6A5659, PN 6A4189, PN 6B1379, PN 6B1380, PN 6B1381, PN 6B1382, PN 6B1383, 

PN 6B1384, PN 6B1387, PN 6B1391 and PN 6B1402 (Ti5331 Drum Material).

Compliance Time Table:
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 16 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Grace Periods Table:

Compliance

Group

Nut/Drum Standard Required Drum Condition Permitted

Grace Period

(Cycles)

F

For drums that were

fitted with any

standard of nut.

Reference 1, or Reference 2, Engine Manual, TASK 72-41-

11-110-001 (Clean)

Reference 1, or Reference 2, Engine Manual, TASK 72-41-

11-200-001 (FPI)

2000

Reference 1, or Reference 2, Engine Manual, TASK 72-41-

11-110-001 (Clean)

Reference 1, or Reference 2, Engine Manual, TASK 72-41-

11-200-001 (FPI)

Reference 3, Non-Modification Service Bulletin V2500-ENG72-0625 (ECI)

5000

 For drums that were 

 fitted with Reference 4, 

 V2500-ENG-72-0632 

initial issue, dated

December 20th 2012

or later approved

revision

Reference 1, or Reference 2, Engine Manual, TASK 72-41-

11-110-001 (Clean)

Reference 5, Non-Modification Service Bulletin

V2500-ENG-72-0637 (Enhanced FPI)

5000

Reference 1, or Reference 2, Engine Manual, TASK 72-41-

11-110-001 (Clean)

Reference 5, Non-Modification Service Bulletin

V2500-ENG-72-0637 (Enhanced FPI)

Reference 3, Non-Modification Service Bulletin

V2500-ENG-72-0625 (ECI)

8000
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 17 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

 F. Additional Instruction

 Note: To comply with the IAE design policy, IAE recommends that engines in this effectivity must have 

installed a HP Compressor Stage 3-8 Drum Assembly (72-41-11-01-200) that has never operated with Pre

Service Bulletin V2500-ENG-72-0632 (72-41-12, 01-602) standard nuts by the 31st of December 2021.

If an engine that is not listed in the effectivity, has a HP compressor Stage 3-8 drum that has operated with

Pre Service Bulletin V2500-ENG-72-0632 (72-41-12,01-602) standard nuts, it must be inspected according to

the applicable requirements of Group A, B, C, D, E or F. The engine should be inspected according to the

applicable requirements of Group A, B, C or D, if that drum has stayed shutdown more than six hours in India

after engine shutdown, more than four times.

Engines which are not specifically listed in Groups A, B, C or D, should be inspected according to the

applicable requirements of Group A, B, C or D, if the engine has a HP Compressor Stage 3-8 Drum Assembly

(72-41-11-01-200) that has stayed shutdown more than six hours in India after engine shutdown, more than

four times.

If an engine that is not listed specifically in Group A, B, C or D stays shutdown more than six hours in India

after engine shut down, for the fourth time, do the procedure that follows:

1. Determine the new compliance threshold and grace period for the appropriate Group A, B, C, or D.

1. If the engine is beyond the new compliance threshold and grace period, perform the initial

 Ultrasonic Inspection within 200 cycles.

2. Notify IAE which Group A, B, C, or D, that the engine and drum belongs to.

G. Approval

The compliance statement and the procedures described in this Service Bulletin have been shown to comply

with the applicable Federal Aviation Regulations and are FAA-APPROVED for the engine model listed.

H. Manpower

Estimated man-hours to carry out this Non-Modification Service Bulletin in full:

(1) Refer to Reference 6, Non-Modification Service Bulletin V2500-ENG-72-0638.

Note: The ultrasonic inspection defined in Reference 6, Non-Modification Service Bulletin V2500-ENG-72-

 0638 must only be performed by personnel qualified to ultrasonic inspection level 2 or higher in

 accordance with EN4179 and/or NAS410 or alternative standards/ guidelines accepted by the

 applicable National Aviation Authority.

I. Weight and Balance

(1) Weight Change

None.
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 18 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

(2) Moment Arm

No Effect.

(3) Datum

Engine Front Mount Centerline (Power Plant Station (PPS) 100)

J. Electrical Load Data

This Service Bulletin has no effect on the aircraft electrical load.

K. Software Accomplishment Summary

Not Applicable.

L. References

Note: In 2014 IAE converted the V2500 Technical Publications to a new system. As a result of the conversion, some 

 manuals were consolidated. All manuals received new P&W part numbers. To facilitate the use of this Service 

 Bulletin, a Technical Publications conversion table is provided in the Appendix

(1) V2500 A1/A5 Series Engine Manual, P&W Ref. PN 2A4407, Chapter 72-41-11.

(2) V2500-D5 Series Engine Manual, P&W Ref. PN 2A4416 Chapter 72-41-11.

 (3) Non-Modification Service Bulletin V2500-ENG-72-0625

NON-MODIFICATION SERVICE BULLETIN - ENGINE - HIGH PRESSURE (HP) COMPRESSOR STAGE 3 TO 8 

 COMPRESSOR DRUM - EDDY CURRENT INSPECTION (ECI)

(4) Service Bulletin V2500-ENG-72-0632

ENGINE - HIGH PRESSURE (HP) COMPRESSOR DISCS - INTRODUCTION OF SILVER FREE NUTS

(5) Non-Modification Service Bulletin V2500-ENG-72-0637.

NON-MODIFICATION SERVICE BULLETIN - ENGINE - HIGH PRESSURE (HP) COMPRESSOR - ENHANCED 

 FLUORESCENT PENETRANT INSPECTION (FPI)

 

 (6) Non-Modification Service Bulletin V2500-ENG-72-0638

 NON-MODIFICATION SERVICE BULLETIN - ENGINE - HIGH PRESSURE (HP) COMPRESSOR - STAGE 3 TO 8 

 COMPRESSOR DRUM - ULTRASONIC INSPECTION PROCEDURE (USI)

 (7) SEN5088 Issue 1. "Significant shop findings on HPC 3-8 drum".

 (8) SEN5088 Issue 2. "Significant shop findings on HPC 3-8 drum".

 (9) SEN5088 Issue 2. "Significant shop findings on HPC 3-8 drum".

 (10) SIL 277 Issue 1. "HPC 3-8 Drum USI clarification".

 (11) Internal Reference No. EA 14VC146A

 (12) ATA Locator - 72-41-12.
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 19 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

M. Other Publications Affected

 None.

N. Interchangeability of Parts

 Not Applicable.

2. Material Information

 None

3. Accomplishment Instructions

A. Inspection Instructions

(1) Accomplish the Ultra Sonic Inspection (USI) instructed with Reference 6, Non-Modification Service Bulletin

V2500-ENG-72-0638 initial issue or later approved revision, in accordance with the applicable compliance

threshold and interval given in Compliance of this Non-Modification Service Bulletin.

(a) For V2500-A1/A5/D5 engines:

(i) Accept and reject criteria (Outer Diameter):

(1) Any ultrasonic response in the gated area above or at the amplitude of 40 percent FSH —

reject the engine.

(2) Any ultrasonic response in the gated area below the amplitude of 40 percent FSH —

 accept.

(ii) Accept and reject criteria (Inner Diameter):

(1) For HP compressor drums of Ti6 material: Ti6246

 A Any ultrasonic response in the gated area above or at the amplitude of 30 percent 

 FSH — reject the engine.

 B Any ultrasonic response in the gated area below the amplitude of 30 percent FSH

 — accept.

(2) For HP compressor drums of Ti5 material: Ti5331

 

 A Any ultrasonic response in the gated area above or at the amplitude of 55 percent

 FSH — reject the engine.

 B Any ultrasonic response in the gated area below the amplitude of 55 percent FSH —

 accept.

 B Recording Instructions

(1) Complete a separate Accomplishment Proforma for outer and inner diameter. See Table 1.

 Retain the proforma for record keeping.

(2) Record the incorporation of Non-Modification Service Bulletin V2500-ENG-72-A0615 in the applicable

engine record.
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615

 IAE PROPRIETARY INFORMATION Page 20 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Table 1 Accomplishment Proforma A1/A5/D5

General Information

Accomplishment Date

Aircraft Registration (Tail) Number

Engine Position

Engine Serial Number

Inspection Information

Position Inspected 

(Circle One — Complete 1 — Form for Inner and 1 — Form for outer) 

Outer Inner

Borescope Inspection Of Stage 7 Liner — Did you find Liner Loss Under Path of

Probe? (Circle One) (A1 only)

Yes No

Probe Serial Number

Working Standard Serial Number

Inspection Results (Circle One) PASS FAIL Not

Accomplished 1

1 Notes and/or Brief Description As To Why Inspection Not Accomplished). Is there anything else you would like Engineering to

be aware of concerning this Engine?1

2

Inspector Stamp or Printed Name

Ultrasonic Indication Summary Table Direction of drum rotation clockwise/anticlockwise. (looking forward)

#

%

F

S

H

Time

Base

Position

Drum

Position

Angle (DEG)

(If possible)

#

%

F

S

H

Time

Base

Position

Drum

Position

Angle (DEG)

(If possible)

#

%

F

S 

H

Time

Base

Position

Drum

Position 

 Angle (DEG)

(If possible)

1 1

1

21

2 1

2

22

3 1

3

23

4 1

4

24

5 1

5

25

6 1

6

26

7 1

7

27

8 1

8

28

9 1

9

29

10 2

0

30

Note: The borescope inspection for liner material loss is required to ensure clearance of the rotor path for the

ultrasonic probe. This is recorded for information only, and does not need to be stamped off as part of

the formal accomplishment records (A1 only).

Note: A separate Accomplishment Proforma is to be completed for each inner and outer diameter inspection.
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 21 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Appendix

Added Data

Internal Reference Information

Revision No. Reference Document Origination

 Original EC10VR775 RN/IEL

 1 EC10VR775A RN/IEL

 2 EC10VR775B RN/IEL

 3 EC10VR775C RN/IEL

 4 EC10VR775D RN/IEL

5 EA14VC146 RN/IEL

6 EA14VC146A ARO/AT
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 22 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

 NOTE: In 2014 IAE converted the V2500 Technical Publications to a new system. As a result of the 

 conversion, some manuals were consolidated. All manuals received new P&W part numbers. 

 To facilitate the use of this Service Bulletin, the following Technical Publications cross reference 

 table is provided.

Technical Publications Cross Reference Table

Publication Engine 

Model(s)

IAE IETM Pub Ref P&W Part

Number

ENGINE MANUAL — A1, A5 All E-V2500-1IA 2A4407

CMM-EHC — A1, A5 All EHC-V2500-1IA 2A4409

CMM-FN — A1, A5 All FN-V2500-1IA 2A4410

CMM-MMC — A1, A5 All MECH-V2500-1IA 2A4411

CMM-THD — A1, A5 All THD-V2500-1IA 2A4412

TLM — A1, A5 All T-V2500-1IA 2A4408

ENGINE MANUAL — D5 All E-V2500-3IA 2A4416

CMM-EHC — D5 All EHC-V2500-31A 2A4418

CMM-FN — D5 All FN-V2500-3IA 2A4419

CMM-MMC — D5 All MECH-V2500-3IA 2A4420

CMM-THD — D5 All THD-V2500-3IA 2A4423

TLM — D5 All T-V2500-3IA 2A4417
January 19/10

REVISION NO. 6 – September 04/14 V2500-ENG-72-A0615 

 IAE PROPRIETARY INFORMATION Page 23 of 23

© IAE International Aero Engines AG (date as above). All rights reserved.

Not Subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3).

Publication Engine Model(s) IAE IETM Pub 

Ref

P&W Part

Number

SPPM (SPM) — A1, A5, D5 All SPP-V2500-1IA 2A4414

EIPC — A1 V2500-A1102Q00 S-V2500-1IA 2A4427

EIPC — A5

V2522/V2524/V2527M-AQ02 S-V2500-6IA

2A4428

V2522/V2524/V2527M-AQ03 S-V2500-6IB

V2522/V2524/V2527M-SQ02 S-V2500-6SA

V2522/V2524/V2527M-SQ03 S-V2500-6SB

V2522/V2524/V2527M-SQ04 S-V2500-6NA

V2522/V2524/V2527M-SQ05 S-V2500-6NB

V2527/V2527E-AQ02 S-V2500-7IA

V2527/V2527E-AQ03 S-V2500-7IB

V2527/V2527E-SQ02 S-V2500-7SA

V2527/V2527E-SQ03 S-V2500-7SB

V2527/V2527E-SQ04 S-V2500-7NA

V2527/V2527E-SQ05 S-V2500-7NB

V2530-AQ02 S-V2500-2IA

V2530-AQ03 S-V2500-2IB

V2530-SQ02 S-V2500-2SA

V2530-SQ03 S-V2500-2SB

V2530-SQ04 S-V2500-2NA

V2530-SQ05 S-V2500-2NB

V2533-AQ02 S-V2500-5IA

V2533-AQ03 S-V2500-5IB

V2533-SQ02 S-V2500-5SA

V2533-SQ03 S-V2500-5SB

V2533-SQ04 S-V2500-5NA

V2533-SQ05All S-V2500-5NB

EIPC — D5

V2525/V2528-AQ02 S-V2500-3IA

V2525/V2528-AQ03 S-V2500-3IB 2A4426

V2525/V2528-AQ04 S-V2500-3IC