Airworthiness Directives; International Aero Engines AG Turbofan Engines, 82202-82204 [2011-33536]

Download as PDF 82202 Federal Register / Vol. 76, No. 251 / Friday, December 30, 2011 / Proposed Rules construction permits, operating licenses, early site permits, limited work authorizations issued under 10 CFR 50.10 for which the NRC issued a final environmental impact statement (EIS) preceded by a draft EIS under 10 CFR 51.76 or 51.75, or combined licenses, any of which were issued by the NRC prior to issuance of the final regulatory guide. The NRC has already completed its siting determination for those construction permits, operating licenses, early site permits, limited work authorizations, and combined licenses. Therefore, no further NRC regulatory action on siting will occur for those licenses, permits, and authorizations, for which the guidance in the regulatory guide would be relevant. This regulatory guide may be applied to applications for early site permits, combined licenses, and limited work authorizations issued under 10 CFR 50.10, which includes information under 10 CFR 51.49(b) or (f), where the application is docketed by the NRC as of the date of issuance of the final regulatory guide, as well as future applications for construction permits, early site permits, combined licenses, and limited work authorizations, which includes information under 10 CFR 51.49(b) or (f), where the application is submitted after the issuance of the final regulatory guide. Such action does not constitute backfitting as defined in 10 CFR 50.109(a)(1) and is not otherwise inconsistent with the applicable issue finality provisions in 10 CFR part 52, inasmuch as such applicants or potential applicants are not within the scope of entities protected by the Backfit Rule or the relevant issue finality provisions in Part 52. Dated at Rockville, Maryland, this 21st day of December 2011. For the Nuclear Regulatory Commission. Harriet Karagiannis, Acting Chief, Regulatory Guide Development Branch, Division of Engineering, Office of Nuclear Regulatory Research. [FR Doc. 2011–33577 Filed 12–29–11; 8:45 am] tkelley on DSK3SPTVN1PROD with PROPOSALS BILLING CODE 7590–01–P VerDate Mar<15>2010 19:18 Dec 29, 2011 Jkt 226001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–1100; Directorate Identifier 2009–NE–37–AD] RIN 2120–AA64 Airworthiness Directives; International Aero Engines AG Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede an existing airworthiness directive (AD), for all International Aero Engines AG (IAE) V2500–A1, V2525–D5 and V2528– D5 turbofan engines, and certain serial numbers (S/Ns) of IAE V2522–A5, V2524–A5, V2527–A5, V2527E–A5, V2527M–A5, V2530–A5, and V2533–A5 turbofan engines. The existing AD currently requires initial and repetitive on-wing ultrasonic inspections (USIs) of certain high-pressure compressor (HPC) stage 3 to 8 drums, and replacement of drum attachment nuts. This proposed AD would expand the affected population for initial and repetitive onwing inspections of the HPC stage 3 to 8 drum, introduce an eddy current inspection (ECI) procedure, and require additional cleaning and repetitive onwing USI or ECI of some HPC stage 3 to 8 drums. We are proposing this AD to prevent failure of the HPC stage 3 to 8 drum, uncontained engine failure, and damage to the airplane. DATES: We must receive comments on this proposed AD by February 28, 2012. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact International Aero Engines AG, 628 Hebron Avenue, Suite 400, Glastonbury, CT 06033; phone: (860) 368–3700; fax: (860) 368–4600; e-mail: iaeinfo@iaev2500.com; Web site: https://www.iaeworld.com. You may SUMMARY: PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 review copies of the referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803. For information on the availability of this material at the FAA, call (781) 238– 7125. Examining the AD Docket You may examine the AD docket on the Internet at https://www.regulations. gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Carlos Fernandes, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: (781) 238–7189; fax: (781) 238– 7199; email: carlos.fernandes@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA-2009-1100; Directorate Identifier 2009–NE–37–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https://www. regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On September 15, 2010, we issued AD 2010–20–07, Amendment 39–16441 (75 FR 59067, September 27, 2010), for IAE V2500–A1, V2525–D5, and V2528–D5 turbofan engines and certain S/Ns of IAE V2522–A5, V2524–A5, V2527–A5, V2527E–A5, V2527M–A5, V2530–A5, and V2533–A5 turbofan engines. That AD requires initial and repetitive onwing USI of the HPC stage 3 to 8 drum for cracks for certain S/Ns of V2500–A1, V2522–A5, V2524–A5, V2527–A5, E:\FR\FM\30DEP1.SGM 30DEP1 Federal Register / Vol. 76, No. 251 / Friday, December 30, 2011 / Proposed Rules V2527E–A5, V2527M–A5, V2530–A5, and V2533–A5 series turbofan engines. As mandatory terminating action to the repetitive inspections, that AD requires removal from service of the fully silver plated nuts attaching the HPC stage 3 to 8 drum to the HPC stage 9 to 12 drum, removal of silver residue from the HPC stage 3 to 8 drum, and FPI of the stage 3 to 8 drum within a specified time. For all other engines, that AD requires removal from service of the fully silver plated nuts attaching the HPC stage 3 to 8 drum to the HPC stage 9 to 12 drum, removal of silver residue from the HPC stage 3 to 8 drum, and FPI of the HPC stage 3 to 8 drum at the next drum piece-part exposure. That AD resulted from reports of 39 HPC stage 3 to 8 drums found cracked since March 2009. We issued that AD to prevent failure of the HPC stage 3 to 8 drum, uncontained engine failure, and damage to the airplane. Actions Since Existing AD Was Issued Since we issued AD 2010–20–07 (75 FR 59067, September 27, 2010), inspections have found 50 additional HPC drums with cracks. Some reports have indicated that the FPI may miss small cracks. This has necessitated the expansion of the compliance requirements. Relevant Service Information tkelley on DSK3SPTVN1PROD with PROPOSALS We reviewed IAE Service Bulletin (SB) V2500–ENG–72–0615, Revision 3, dated September 20, 2011. That SB will replace IAE SB V2500–ENG–72–0594, Revision 6, dated April 12, 2010 and IAE SB V2500–ENG–72–0603, Revision 1, dated February 17, 2011. We have also reviewed IAE SB No. V2500–ENG– 72–0601, Revision 2, dated April 12, 2010. That SB describes procedures for removing the silver residue from the HPC stage 3 to 8 drum. We have also reviewed IAE SB V2500–ENG–72–0615, Revision 3, dated September 20, 2011 and IAE SB No. V2500–ENG–72–0608, Revision 3, dated September 20, 2011. Those SBs describe procedures for performing USIs of the HPC stage 3 to 8 drum. We have also reviewed IAE SB V2500–ENG–72–0625, dated September 20, 2011 which introduces an ECI procedure that will improve the ability to detect cracks of the HPC 3 to 8 drum. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. VerDate Mar<15>2010 19:18 Dec 29, 2011 Jkt 226001 Proposed AD Requirements This proposed AD would retain certain requirements of AD 2010–20–07. The proposed AD has the same applicability requirements as AD 2010– 20–07. This proposed AD, however, would expand the initial and repetitive on-wing USIs of the HPC stage 3 to 8 drum for cracks to a larger population of S/Ns of V2500–A1, V2522–A5, V2524–A5, V2527–A5, V2527E–A5, V2527M–A5, V2530–A5, and V2533–A5 turbofan engines and all V2525–D5 and V2528–D5 turbofan engines. This proposed AD would introduce an ECI procedure that will improve the ability to detect cracks of the HPC stage 3 to 8 drum. This proposed AD would require repetitive on-wing USI of the HPC stage 3 to 8 drum after removal from service of all of the fully silver plated nuts attaching the HPC stage 3 to 8 drum to the HPC stage 9 to 12 drum; removal of silver residue from the HPC stage 3 to 8 drum; and FPI or ECI of the stage 3 to 8 drum. This proposed AD would also remove the mandatory terminating action and replace it with an optional terminating action. Costs of Compliance We estimate that this proposed AD would affect about 906 IAE V2500–A1, V2522–A5, V2524–A5, V2525–D5, V2527–A5, V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, and V2533–A5 turbofan engines installed on airplanes of U.S. registry. We estimate that 906 of these engines would require USIs, and that it would take about 3 work-hours per engine to perform one USI. We estimate that it would take about 2 work-hours per engine to perform the FPI of the HPC stage 3 to 8 drum, and that the average labor rate is $85 per work-hour. We also estimate that removal of silver residue from the engine would cost about $2,600 per engine. Required parts would cost about $795 per engine. We also estimate the cost of replacing a drum if found cracked would be $189,000. We have no way of determining the number of aircraft that might need this replacement. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $4,385,040. 82203 We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Authority for This Rulemaking § 39.13 Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2010–20–07, Amendment 39–16441 (75 FR 59067, September 27, 2010), and adding the following new AD: PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 [Amended] International Aero Engines AG: Docket No. FAA–2009–1100; Directorate Identifier 2009–NE–37–AD. E:\FR\FM\30DEP1.SGM 30DEP1 82204 Federal Register / Vol. 76, No. 251 / Friday, December 30, 2011 / Proposed Rules (a) Comments Due Date The FAA must receive comments on this AD action by February 28, 2012. (b) Affected ADs This AD supersedes AD 2010–20–07, Amendment 39–16441 (75 FR 59067, September 27, 2010). (c) Applicability 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. (d) Unsafe Condition This AD results from reports of 50 additional high-pressure compressor (HPC) stage 3 to 8 drums found cracked since AD 2010–20–07 was issued. We are issuing this AD to prevent failure of the HPC stage 3 to 8 drum, uncontained engine failure, and damage to the airplane. (e) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. tkelley on DSK3SPTVN1PROD with PROPOSALS (f) Initial Ultrasonic Inspections (USIs) of the HPC Stage 3 to 8 Drum (1) Using IAE Service Bulletin (SB) No. V2500–ENG–72–0615, Revision 3, dated September 20, 2011, Accomplishment Instructions, paragraph 3, perform an initial USI of the HPC stage 3 to 8 drum: (i) For IAE V2500–A1, V2522–A5, V2524– A5, V2527–A5, V2527E–A5, V2527M–A5, V2530–A5, and V2533–A5 turbofan engines with S/Ns in ‘‘Group A’’ in Paragraph 1.A. in IAE SB No. V2500–ENG–72–0615, Revision 3, dated September 20, 2011, before accumulating 5,000 cycles-since-new (CSN) or within 500 cycles from the effective date of this AD, whichever occurs later. (ii) For IAE V2500–A1, V2522–A5, V2524– A5, V2527–A5, V2527E–A5, V2527M–A5, V2530–A5, and V2533–A5 turbofan engines with S/Ns in ‘‘Group B’’ in Paragraph 1.A. in IAE SB No. V2500–ENG–72–0615, Revision 3, dated September 20, 2011, before accumulating 12,500 CSN or within 500 cycles from the effective date of this AD, whichever occurs later, not to exceed 13,700 CSN. (2) For all IAE V2525–D5 and V2528–D5 turbofan engines, using IAE SB No. V2500– ENG–72–0608, Revision 3 dated September 20, 2011, Accomplishment Instructions, paragraph 3, perform an initial USI of the HPC stage 3 to 8 drum before accumulating 12,500 CSN or within 500 cycles from the effective date of this AD, whichever occurs later, not to exceed 13,700 CSN. (3) If cracks or crack indications are identified, remove the drum from service before further flight. VerDate Mar<15>2010 19:18 Dec 29, 2011 Jkt 226001 (g) Removal of All Fully Silver Plated Nuts (1) At the next piece part exposure of the HPC stage 3 to 8 drum after the effective date of this AD, but no later than 8 years from the effective date of this AD, do the following before returning any HPC stage 3 to 8 drum to service: (i) Remove from service all 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. (2) Perform an inspection using one of the following methods: (i) 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. (ii) Eddy Current Inspect (ECI) the HPC stage 3 to 8 drum for cracks, using IAE SB No. V2500–ENG–72–0625, dated September 20, 2011, and remove from service any drum found cracked. (3) If cracks or crack indications are identified, remove the drum from service before further flight. (h) Repetitive USIs of the HPC Stage 3 to 8 Drum Perform repetitive USIs of the HPC stage 3 to 8 drum for cracks in accordance with paragraphs (f)(1) or (f)(2) of this AD as follows: (1) Within every 750 cycles-since-last USI; or (2) Within 2,500 cycles-since-last FPI; or (3) Within 13,000 cycles-since-last ECI, whichever occurs latest. (i) Optional Terminating Action Accomplishment of paragraphs (h)(1) and (h)(2) of this AD, eliminate the cleaning and inspection requirements of this AD and no further actions are required. (1) Remove from service all 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) Install 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. (j) Definitions 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. effective date of this AD, meets the inspection requirements of paragraphs (f)(1) through (f)(3) of this AD. (2) Initial or repetitive USIs 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, or Revision 2, dated March 17, 2010, before the effective date of this AD, meets the inspection requirements of paragraphs (f)(1) through (f)(3) of this AD. (3) Initial or repetitive USIs of the HPC stage 3 to 8 drum using IAE SB No. V2500– ENG–72–0608, Revision 3, dated September 20, 2011, before the effective date of this AD, meets the inspection requirements of paragraphs (f)(1) through (f)(3) of this AD. (4) Initial or repetitive USIs of the HPC stage 3 to 8 drum using IAE SB No. V2500– ENG–72–615, Revision 3, dated September 20, 2011, before the effective date of this AD, meets the inspection requirements of paragraphs (f)(1) through (f)(3) of this AD. (l) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. (m) Related Information (1) For more information about this AD, contact Carlos Fernandes, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: (781) 238–7189; fax: (781) 238–7199; email: carlos.fernandes@faa.gov. (2) For service information identified in this AD, contact International Aero Engines AG, 628 Hebron Avenue, Suite 400, Glastonbury, CT 06033; phone: (860) 368– 3700; fax: (860) 368–4600; email: iaeinfo@iaev2500.com; Web site: https:// www.iaeworld.com. (3) You may review copies of the referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call (781) 238–7125. Issued in Burlington, Massachusetts, on December 23, 2011. Peter A. White, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2011–33536 Filed 12–29–11; 8:45 am] BILLING CODE 4910–13–P (k) Previous Credit (1) Initial or repetitive USIs 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, or Revision 6, dated April 12, 2010, before the PO 00000 Frm 00004 Fmt 4702 Sfmt 9990 E:\FR\FM\30DEP1.SGM 30DEP1

Agencies

[Federal Register Volume 76, Number 251 (Friday, December 30, 2011)]
[Proposed Rules]
[Pages 82202-82204]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-33536]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1100; Directorate Identifier 2009-NE-37-AD]
RIN 2120-AA64


Airworthiness Directives; International Aero Engines AG Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede an existing airworthiness directive 
(AD), for all International Aero Engines AG (IAE) V2500-A1, V2525-D5 
and V2528-D5 turbofan engines, and certain serial numbers (S/Ns) of IAE 
V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and 
V2533-A5 turbofan engines. The existing AD currently requires initial 
and repetitive on-wing ultrasonic inspections (USIs) of certain high-
pressure compressor (HPC) stage 3 to 8 drums, and replacement of drum 
attachment nuts. This proposed AD would expand the affected population 
for initial and repetitive on-wing inspections of the HPC stage 3 to 8 
drum, introduce an eddy current inspection (ECI) procedure, and require 
additional cleaning and repetitive on-wing USI or ECI of some HPC stage 
3 to 8 drums. We are proposing this AD to prevent failure of the HPC 
stage 3 to 8 drum, uncontained engine failure, and damage to the 
airplane.

DATES: We must receive comments on this proposed AD by February 28, 
2012.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact 
International Aero Engines AG, 628 Hebron Avenue, Suite 400, 
Glastonbury, CT 06033; phone: (860) 368-3700; fax: (860) 368-4600; e-
mail: iaeinfo@iaev2500.com; Web site: https://www.iaeworld.com. You may 
review copies of the referenced service information at the FAA, Engine 
& Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803. For information on the availability of this material at the FAA, 
call (781) 238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Carlos Fernandes, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: (781) 238-
7189; fax: (781) 238-7199; email: carlos.fernandes@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-1100; 
Directorate Identifier 2009-NE-37-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On September 15, 2010, we issued AD 2010-20-07, Amendment 39-16441 
(75 FR 59067, September 27, 2010), for IAE V2500-A1, V2525-D5, and 
V2528-D5 turbofan engines and certain S/Ns of IAE V2522-A5, V2524-A5, 
V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 turbofan 
engines. That AD requires initial and repetitive on-wing USI of the HPC 
stage 3 to 8 drum for cracks for certain S/Ns of V2500-A1, V2522-A5, 
V2524-A5, V2527-A5,

[[Page 82203]]

V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 series turbofan engines. 
As mandatory terminating action to the repetitive inspections, that AD 
requires removal from service of the fully silver plated nuts attaching 
the HPC stage 3 to 8 drum to the HPC stage 9 to 12 drum, removal of 
silver residue from the HPC stage 3 to 8 drum, and FPI of the stage 3 
to 8 drum within a specified time. For all other engines, that AD 
requires removal from service of the fully silver plated nuts attaching 
the HPC stage 3 to 8 drum to the HPC stage 9 to 12 drum, removal of 
silver residue from the HPC stage 3 to 8 drum, and FPI of the HPC stage 
3 to 8 drum at the next drum piece-part exposure. That AD resulted from 
reports of 39 HPC stage 3 to 8 drums found cracked since March 2009. We 
issued that AD to prevent failure of the HPC stage 3 to 8 drum, 
uncontained engine failure, and damage to the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2010-20-07 (75 FR 59067, September 27, 2010), 
inspections have found 50 additional HPC drums with cracks. Some 
reports have indicated that the FPI may miss small cracks. This has 
necessitated the expansion of the compliance requirements.

Relevant Service Information

    We reviewed IAE Service Bulletin (SB) V2500-ENG-72-0615, Revision 
3, dated September 20, 2011. That SB will replace IAE SB V2500-ENG-72-
0594, Revision 6, dated April 12, 2010 and IAE SB V2500-ENG-72-0603, 
Revision 1, dated February 17, 2011. We have also reviewed IAE SB No. 
V2500-ENG-72-0601, Revision 2, dated April 12, 2010. That SB describes 
procedures for removing the silver residue from the HPC stage 3 to 8 
drum. We have also reviewed IAE SB V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011 and IAE SB No. V2500-ENG-72-0608, Revision 3, dated 
September 20, 2011. Those SBs describe procedures for performing USIs 
of the HPC stage 3 to 8 drum. We have also reviewed IAE SB V2500-ENG-
72-0625, dated September 20, 2011 which introduces an ECI procedure 
that will improve the ability to detect cracks of the HPC 3 to 8 drum.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain certain requirements of AD 2010-20-
07. The proposed AD has the same applicability requirements as AD 2010-
20-07. This proposed AD, however, would expand the initial and 
repetitive on-wing USIs of the HPC stage 3 to 8 drum for cracks to a 
larger population of S/Ns of V2500-A1, V2522-A5, V2524-A5, V2527-A5, 
V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 turbofan engines and all 
V2525-D5 and V2528-D5 turbofan engines. This proposed AD would 
introduce an ECI procedure that will improve the ability to detect 
cracks of the HPC stage 3 to 8 drum. This proposed AD would require 
repetitive on-wing USI of the HPC stage 3 to 8 drum after removal from 
service of all of the fully silver plated nuts attaching the HPC stage 
3 to 8 drum to the HPC stage 9 to 12 drum; removal of silver residue 
from the HPC stage 3 to 8 drum; and FPI or ECI of the stage 3 to 8 
drum. This proposed AD would also remove the mandatory terminating 
action and replace it with an optional terminating action.

Costs of Compliance

    We estimate that this proposed AD would affect about 906 IAE V2500-
A1, V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, 
V2528-D5, V2530-A5, and V2533-A5 turbofan engines installed on 
airplanes of U.S. registry. We estimate that 906 of these engines would 
require USIs, and that it would take about 3 work-hours per engine to 
perform one USI. We estimate that it would take about 2 work-hours per 
engine to perform the FPI of the HPC stage 3 to 8 drum, and that the 
average labor rate is $85 per work-hour. We also estimate that removal 
of silver residue from the engine would cost about $2,600 per engine. 
Required parts would cost about $795 per engine. We also estimate the 
cost of replacing a drum if found cracked would be $189,000. We have no 
way of determining the number of aircraft that might need this 
replacement. Based on these figures, we estimate the total cost of the 
proposed AD to U.S. operators to be $4,385,040.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing airworthiness directive 
(AD) 2010-20-07, Amendment 39-16441 (75 FR 59067, September 27, 2010), 
and adding the following new AD:

International Aero Engines AG: Docket No. FAA-2009-1100; Directorate 
Identifier 2009-NE-37-AD.

[[Page 82204]]

(a) Comments Due Date

    The FAA must receive comments on this AD action by February 28, 
2012.

(b) Affected ADs

    This AD supersedes AD 2010-20-07, Amendment 39-16441 (75 FR 
59067, September 27, 2010).

(c) Applicability

    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.

(d) Unsafe Condition

    This AD results from reports of 50 additional high-pressure 
compressor (HPC) stage 3 to 8 drums found cracked since AD 2010-20-
07 was issued. We are issuing this AD to prevent failure of the HPC 
stage 3 to 8 drum, uncontained engine failure, and damage to the 
airplane.

(e) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified unless the actions 
have already been done.

(f) Initial Ultrasonic Inspections (USIs) of the HPC Stage 3 to 8 Drum

    (1) Using IAE Service Bulletin (SB) No. V2500-ENG-72-0615, 
Revision 3, dated September 20, 2011, Accomplishment Instructions, 
paragraph 3, perform an initial USI of the HPC stage 3 to 8 drum:
    (i) For IAE V2500-A1, V2522-A5, V2524-A5, V2527-A5, V2527E-A5, 
V2527M-A5, V2530-A5, and V2533-A5 turbofan engines with S/Ns in 
``Group A'' in Paragraph 1.A. in IAE SB No. V2500-ENG-72-0615, 
Revision 3, dated September 20, 2011, before accumulating 5,000 
cycles-since-new (CSN) or within 500 cycles from the effective date 
of this AD, whichever occurs later.
    (ii) For IAE V2500-A1, V2522-A5, V2524-A5, V2527-A5, V2527E-A5, 
V2527M-A5, V2530-A5, and V2533-A5 turbofan engines with S/Ns in 
``Group B'' in Paragraph 1.A. in IAE SB No. V2500-ENG-72-0615, 
Revision 3, dated September 20, 2011, before accumulating 12,500 CSN 
or within 500 cycles from the effective date of this AD, whichever 
occurs later, not to exceed 13,700 CSN.
    (2) For all IAE V2525-D5 and V2528-D5 turbofan engines, using 
IAE SB No. V2500-ENG-72-0608, Revision 3 dated September 20, 2011, 
Accomplishment Instructions, paragraph 3, perform an initial USI of 
the HPC stage 3 to 8 drum before accumulating 12,500 CSN or within 
500 cycles from the effective date of this AD, whichever occurs 
later, not to exceed 13,700 CSN.
    (3) If cracks or crack indications are identified, remove the 
drum from service before further flight.

(g) Removal of All Fully Silver Plated Nuts

    (1) At the next piece part exposure of the HPC stage 3 to 8 drum 
after the effective date of this AD, but no later than 8 years from 
the effective date of this AD, do the following before returning any 
HPC stage 3 to 8 drum to service:
    (i) Remove from service all 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.
    (2) Perform an inspection using one of the following methods:
    (i) 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.
    (ii) Eddy Current Inspect (ECI) the HPC stage 3 to 8 drum for 
cracks, using IAE SB No. V2500-ENG-72-0625, dated September 20, 
2011, and remove from service any drum found cracked.
    (3) If cracks or crack indications are identified, remove the 
drum from service before further flight.

(h) Repetitive USIs of the HPC Stage 3 to 8 Drum

    Perform repetitive USIs of the HPC stage 3 to 8 drum for cracks 
in accordance with paragraphs (f)(1) or (f)(2) of this AD as 
follows:
    (1) Within every 750 cycles-since-last USI; or
    (2) Within 2,500 cycles-since-last FPI; or
    (3) Within 13,000 cycles-since-last ECI, whichever occurs 
latest.

(i) Optional Terminating Action

    Accomplishment of paragraphs (h)(1) and (h)(2) of this AD, 
eliminate the cleaning and inspection requirements of this AD and no 
further actions are required.
    (1) Remove from service all 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) Install 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.

(j) Definitions

    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.

(k) Previous Credit

    (1) Initial or repetitive USIs 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, or Revision 6, dated April 12, 2010, before the 
effective date of this AD, meets the inspection requirements of 
paragraphs (f)(1) through (f)(3) of this AD.
    (2) Initial or repetitive USIs 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, or Revision 2, 
dated March 17, 2010, before the effective date of this AD, meets 
the inspection requirements of paragraphs (f)(1) through (f)(3) of 
this AD.
    (3) Initial or repetitive USIs of the HPC stage 3 to 8 drum 
using IAE SB No. V2500-ENG-72-0608, Revision 3, dated September 20, 
2011, before the effective date of this AD, meets the inspection 
requirements of paragraphs (f)(1) through (f)(3) of this AD.
    (4) Initial or repetitive USIs of the HPC stage 3 to 8 drum 
using IAE SB No. V2500-ENG-72-615, Revision 3, dated September 20, 
2011, before the effective date of this AD, meets the inspection 
requirements of paragraphs (f)(1) through (f)(3) of this AD.

(l) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, may approve AMOCs for 
this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(m) Related Information

    (1) For more information about this AD, contact Carlos 
Fernandes, Aerospace Engineer, Engine Certification Office, FAA, 
Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA 01803; phone: (781) 238-7189; fax: (781) 238-7199; 
email: carlos.fernandes@faa.gov.
    (2) For service information identified in this AD, contact 
International Aero Engines AG, 628 Hebron Avenue, Suite 400, 
Glastonbury, CT 06033; phone: (860) 368-3700; fax: (860) 368-4600; 
email: iaeinfo@iaev2500.com; Web site: https://www.iaeworld.com.
    (3) You may review copies of the referenced service information 
at the FAA, Engine & Propeller Directorate, 12 New England Executive 
Park, Burlington, MA. For information on the availability of this 
material at the FAA, call (781) 238-7125.

    Issued in Burlington, Massachusetts, on December 23, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-33536 Filed 12-29-11; 8:45 am]
BILLING CODE 4910-13-P

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