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2010-20-07 International Aero Engines AG: Amendment 39-16441. Docket No. FAA-2009-1100; Directorate Identifier 2009-NE-37-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective November 1, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to:
(1) All International Aero Engines AG (IAE) V2500-A1 turbofan engines; and
(2) All IAE V2525-D5 and V2528-D5 turbofan engines; and
(3) IAE V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 turbofan engines with serial numbers (S/Ns) up to and including V13181, and with S/Ns from V15000 up to and including V15245.
(4) These engines are installed on, but not limited to, Airbus A319, A320, and A321, and McDonnell Douglas MD-90 airplanes.
Unsafe Condition
(d) This AD results from reports of 39 high-pressure compressor (HPC) stage 3 to 8 drums found cracked since March 2009. We are issuing this AD to prevent uncontained failure of the HPC stage 3 to 8 drum, which could result in damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.
Engines Requiring Ultrasonic Inspections of the HPC Stage 3 to 8 Drum
(f) For IAE V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 turbofan engines with S/Ns in "Group A'' or "Group D'' in IAE Service Bulletin (SB) No. V2500-ENG-72-0594, Revision 6, dated April 12, 2010, and for V2500-A1 turbofan engines with S/Ns in "Group A'' in IAE SB No. V2500-ENG-72-0603, Revision 2, dated March 17, 2010, do the following:
(1) Perform an initial ultrasonic inspection of the HPC stage 3 to 8 drum using IAE SB No. V2500-ENG-72-0594, Revision 6, dated April 12, 2010, Accomplishment Instructions, paragraph 3, or IAE SB No. V2500-ENG-72-0603, Revision 2, dated March 17, 2010, Accomplishment Instructions, paragraph 3, before accumulating 5,200 cycles-since-new (CSN) or within 500 cycles from the effective date of this AD, whichever occurs later.
(2) Thereafter, perform repetitive ultrasonic inspections of the HPC stage 3 to 8 drum for cracks within every 500 cycles-since-last- inspection.
(3) If cracks or crack indications are identified, remove the drum from service before further flight.
Mandatory Terminating Action
(4) As mandatory terminating action to the repetitive inspections required by this AD, at the next engine shop visit, but no later than 27 months after the effective date of this AD, do the following before returning any HPC stage 3 to 8 drum to service:
(i) Remove from service fully silver plated nuts, part number (P/N) AS44862 or equivalent, that attach the HPC stage 3 to 8 drum to the HPC stage 9 to 12 drum.
(ii) Remove the silver residue from the HPC stage 3 to 8 drum using the IAE SB No. V2500-ENG-72-0601, Revision 2, dated April 12, 2010, Accomplishment Instructions, paragraph 3. Drums cleaned before the effective date of this AD using engine manual task 72-41-11-110- 001 satisfy this requirement.
(iii) Fluorescent penetrant inspect (FPI) the HPC stage 3 to 8 drum for cracks, and remove from service any drum found cracked. You can find guidance on performing an FPI of the HPC stage 3 to 8 drum in IAE engine manual task 72-41-11-200-001.
(iv) Installation of a zero-time HPC stage 3 to 8 drum or a drum that has never operated with fully silver plated nuts, P/N AS44862 or equivalent, that attach the HPC stage 3 to 8 drum to the HPC stage 9 to 12 drum eliminates the need for the cleaning and FPI required by paragraphs (f)(4)(ii) and (f)(4)(iii) of this AD.
All Other Engines
(g) For all other engines, at the next piece-part exposure of the HPC stage 3 to 8 drum after the effective date of this AD, do the following before returning the drum to service:
(1) Remove from service fully silver plated nuts, P/N AS44862 or equivalent, that attach the HPC stage 3 to 8 drum to the HPC stage 9 to 12 drum.
(2) Remove the silver residue from the HPC stage 3 to 8 drum using IAE SB No. V2500-ENG-72-0601, Revision 2, dated April 12, 2010, Accomplishment Instructions, paragraph 3. Drums cleaned before the effective date of this AD using engine manual task 72-41-11-110- 001 satisfy this requirement.
(3) FPI the HPC stage 3 to 8 drum for cracks, and remove from service any drum found cracked. You can find guidance on performing an FPI of the HPC stage 3 to 8 drum in IAE engine manual task 72-41- 11-200-001.
(4) Installation of a zero-time HPC stage 3 to 8 drum or a drum that has never operated with fully silver plated nuts, P/N AS44862 or equivalent, that attach the HPC stage 3 to 8 drum to the HPC stage 9 to 12 drum eliminates the need for the cleaning and FPI required by paragraphs (g)(2) and (g)(3) of this AD.
Definitions
(h) For the purpose of this AD, an engine shop visit is the induction ofan engine into the shop for maintenance involving the separation of a pair of major mating engine flanges, except that the separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance is not an engine shop visit.
(i) For the purpose of this AD, piece-part exposure is removal of the HPC stage 3 to 8 drum from the engine and removal of all blades from the drum.
Previous Credit
(j) Initial or repetitive ultrasonic inspections of the HPC stage 3 to 8 drum using IAE SB No. V2500-ENG-72-0594, Revision 3, dated August 7, 2009, or Revision 4, dated October 13, 2009, or Revision 5, dated November 23, 2009, before the effective date of this AD, meets the inspection requirements of paragraphs (f)(1) through (f)(3) of this AD.
(k) Initial or repetitive ultrasonic inspections of the HPC stage 3 to 8 drum using IAE SB No. V2500-ENG-72-0603, Original Issue, dated November 24 2009, or Revision 1, dated December 18, 2009, before the effective date of this AD, meets the inspection requirements of paragraphs (f)(1) through (f)(3) of this AD.
Alternative Methods of Compliance (AMOCS)
(l) The Manager, Engine Certification Office, has the authority to approve AMOCs for this AD if requested using the procedures found in 14 CFR 39.19.
Related Information
(m) Contact Mark Riley, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: mark.riley@faa.gov; telephone (781) 238-7758, fax (781) 238-7199, for more information about this AD.
(n) Contact International Aero Engines AG, 400 Main Street, East Hartford, CT 06108; telephone: (860) 565-5515; fax: (860) 565-5510, for a copy of the service information referenced in this AD.
Material Incorporated by Reference
(o) You must use the service information specified in the following Table 1 to perform the inspections and silver residue removal required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents listed in the following Table 1 in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact International Aero Engines AG, 400 Main Street, East Hartford, CT 06108; telephone: (860) 565-5515; fax: (860) 565-5510, for a copy of this service information. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Table 1--Incorporation by Reference
International Aero Engines Service Bulletin No.
Page
Revision
Date
V2500-ENG-72-0594
Total Pages: 61
ALL
6
April 12, 2010
V2500-ENG-72-0601
Total Pages: 9
ALL
2
April 12, 2010
V2500-ENG-72-0603
Total pages: 46
ALL
2
March 17, 2010
