Airworthiness Directives; CFM International, S.A. CFM56-5B1/P; -5B2/P; -5B3/P; -5B3/P1; -5B4/P; -5B4/P1; -5B5/P; -5B6/P; -5B7/P; -5B8/P; -5B9/P; -5B1/3; -5B2/3; -5B3/3; -5B4/3; -5B5/3; -5B6/3; -5B7/3; -5B8/3; -5B9/3; -5B3/3B1; and -5B4/3B1 Turbofan Engines, 18662-18664 [E9-9443]

Download as PDF 18662 Federal Register / Vol. 74, No. 78 / Friday, April 24, 2009 / Proposed Rules (excluding Saturday, Sundays, and holidays) after the date of receipt of the request, as described in paragraph (g) of this section, except as stated in paragraph (f)(3) of this section. * * * * * (3) * * * (iv) Tolling of time limits. (A) The OCC may toll the 20-day time period to: (1) Make one request for additional information from the requester; or (2) Clarify the applicability or amount of any fees, if necessary, with the requester. (B) The tolling period ends upon the OCC’s receipt of information from the requester or resolution of the fee issue. * * * * * 4. Amend § 4.17 by: a. Revising the section heading, and paragraph (a)(8); b. Adding paragraph (b)(6); and c. Removing, in the parenthetical in paragraph (d), the phrase ‘‘10 business days’’, and by adding in lieu thereof the phrase ‘‘20 business days’’. The revisions and addition are set forth below. tjames on PRODPC75 with PROPOSALS § 4.17 FOIA request fees. (a) * * * (8) Requester who is a representative of the news media means any person who, or entity that, gathers information of potential interest to a segment of the public, uses editorial skills to turn the raw materials into a distinct work, and distributes that work to an audience. A freelance journalist shall be regarded as working for a news media entity if the person can demonstrate a solid basis for expecting publication through that entity, whether or not the journalist is actually employed by that entity. A publication contract is one example of a basis for expecting publication that ordinarily would satisfy this standard. The OCC also may consider the past publication record of the requester in determining whether she or he qualifies as a ‘‘representative of the news media.’’ * * * * * (b) * * * (6) No fee if the time limit passes and the requester has not received a response. The OCC will not assess search and/or duplication fees, as applicable, if it fails to respond to a requester’s FOIA request within the time limits specified under 12 CFR 4.15, and no ‘‘unusual’’ circumstances (as defined in 5 U.S.C. 552(a)(6)(B) and § 4.15(f)(3)(i)) or ‘‘exceptional’’ circumstances (as defined in 5 U.S.C. 552(a)(6)(C)) apply to the processing of the request * * * * * 5. Add § 4.18 to read as follows: VerDate Nov<24>2008 14:02 Apr 23, 2009 Jkt 217001 § 4.18 How to track a FOIA request. (a) Tracking number. The OCC will issue a tracking number to all FOIA requesters within 5 days of the receipt of the request (as described in § 4.15(g)) in the OCC’s Communications Department. The tracking number will be sent via electronic mail if the requester has provided an electronic mail address. Otherwise, the OCC will mail the tracking number to the requester’s physical address, as provided in the FOIA request. (b) Web site. FOIA requesters may check the status of their FOIA request(s) at https://appsec.occ.gov/ publicaccesslink/. (c) If a requester does not have Internet access. Requesters without Internet access may continue to contact the Disclosure Officer, Communications Division, Office of the Comptroller of the Currency, at (202) 874–4700 to check the status of their FOIA request(s). Dated: April 17, 2009. John C. Dugan, Comptroller of the Currency. [FR Doc. E9–9375 Filed 4–23–09; 8:45 am] BILLING CODE 4810–33–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0174; Directorate Identifier 2008–NE–03–AD] RIN 2120–AA64 Airworthiness Directives; CFM International, S.A. CFM56–5B1/P; –5B2/ P; –5B3/P; –5B3/P1; –5B4/P; –5B4/P1; –5B5/P; –5B6/P; –5B7/P; –5B8/P; –5B9/ P; –5B1/3; –5B2/3; –5B3/3; –5B4/3; –5B5/3; –5B6/3; –5B7/3; –5B8/3; –5B9/ 3; –5B3/3B1; and –5B4/3B1 Turbofan Engines AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. SUMMARY: This supplemental NPRM revises an earlier proposed airworthiness directive (AD), applicable to CFM International, S.A. CFM56–5B1/ P; –5B2/P; –5B3/P; –5B3/P1; –5B4/P; –5B4/P1; –5B5/P; –5B6/P; –5B7/P; –5B8/P; and –5B9/P turbofan engines. That proposed AD would have required initial and repetitive eddy current inspections (ECIs) of certain part PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 number (P/N) low-pressure (LP) turbine rear frames. That proposed AD resulted from a refined lifing analysis by the engine manufacturer that shows the need to identify initial and repetitive inspection thresholds for inspecting certain LP turbine rear frames. This supplemental NPRM revises the proposed AD to add two LP turbine rear frame P/Ns to the applicability, to add 11 engine models to the applicability, and to clarify the commercial and corporate engines/LP turbine rear frames applicability. This supplemental NPRM results from CFM International, S.A. revising the service information to add LP turbine rear frame P/Ns and engine models, and from comments received on the proposed AD. This supplemental NPRM also results from a refined lifing analysis by the engine manufacturer that shows the need to identify initial and repetitive inspection thresholds for inspecting certain LP turbine rear frames. We are proposing this AD to detect low-cycle-fatigue cracks in the LP turbine rear frame, which could result in an engine separating from the airplane, causing damage to, and possibly leading to loss of control of, the airplane. DATES: We must receive any comments on this proposed AD by June 8, 2009. ADDRESSES: Use one of the following addresses to comment on this proposed AD. • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. You can get the service information identified in this proposed AD from CFM International, Technical Publications Department, 1 Neumann Way, Cincinnati, OH 45215; telephone (513) 552–2800; fax (513) 552–2816. FOR FURTHER INFORMATION CONTACT: Stephen Sheely, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: stephen.k.sheely@faa.gov; telephone (781) 238–7750; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: E:\FR\FM\24APP1.SGM 24APP1 Federal Register / Vol. 74, No. 78 / Friday, April 24, 2009 / Proposed Rules Comments Invited We invite you to send us any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2008–0174; Directorate Identifier 2008– NE–03–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light 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 with FAA personnel concerning this proposed AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office 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 Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. tjames on PRODPC75 with PROPOSALS Discussion On April 29, 2008, we issued a proposal to amend part 39 of the Code of Federal Regulations (14 CFR part 39) to add an AD, applicable to CFM International, S.A. CFM56–5B1/P; –5B2/ P; –5B3/P; –5B3/P1; –5B4/P; –5B4/P1; –5B5/P; –5B6/P; –5B7/P; –5B8/P; and –5B9/P turbofan engines. The proposed AD published as an NPRM in the Federal Register on May 7, 2008 (73 FR 25597). That NPRM proposed to require initial and repetitive ECIs of certain P/N LP turbine rear frames. Since we issued that NPRM, we became aware of two additional LP VerDate Nov<24>2008 14:02 Apr 23, 2009 Jkt 217001 turbine rear frame P/Ns affected, and 11 additional engine models affected that were not listed in the proposed AD applicability. CFM International, S.A. subsequently superseded Service Bulletin (SB) No. CFM56–5B S/B 72– 0620, Revision 1, dated December 20, 2007, to add those LP turbine rear frame P/Ns and engine models. We added LP turbine rear frame P/Ns 338–171–751–0; and 338–171–752–0, and CFM56–5B1/3; –5B2/3; –5B3/3; –5B4/3; –5B5/3; –5B6/ 3; –5B7/3; –5B8/3; –5B9/3; –5B3/3B1; and –5B4/3B1 engine models to the applicability of the supplemental NPRM. We also clarified the commercial and corporate engines/LP turbine rear frames applicability. Because we added those CFM56 engine models and added those LP turbine rear frame P/Ns, this supplemental NPRM reopens the comment period to include those added engine models and added P/Ns, and to reference the superseding service bulletin. As we stated in the original proposed AD, CFM International, S.A. performed a refined lifing analysis that shows the need to identify initial and repetitive inspection thresholds for inspecting LP turbine rear frames. This condition, if not corrected, could result in an engine separating from the airplane, causing damage to, and possibly leading to loss of control of the airplane. Comments We provided the public the opportunity to participate in the development of this proposed AD. We have considered the comments received. Consider Expanding the Engine Model Applicability One commenter, Virgin Airlines, requests that we consider expanding the applicability in the proposed AD by adding the CFM56–5B4/3 and CFM56– 5B6/3 turbofan engines. We agree that those engines are affected. We added them to this supplemental NPRM. Disagreement With Proposed AD Applicability One commenter, CFM International S.A., disagrees with the proposed AD applicability, specifically, the listing of all of the engines as certified for corporate application. They state that only the CFM56–5B6/P and CFM56– 5B7/P engine models certified for corporate application need to be covered by the proposed AD, because they were initially certified with a 22,500-cycle life. They now have a first inspection at 19,000 cycles. All of the other –5B/P engine models in the corporate application were certified PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 18663 with the first inspection at 19,000 cycles, and do not need to be covered by the proposed AD. We agree. We corrected and clarified the applicability in the supplemental NPRM. Request To Give Credit One commenter, Airbus, requests that we give credit for inspections previously done using CFM International, S.A. Service Bulletin No. CFM56–5B S/B 72–0620, dated May 3, 2007. We agree. We changed the supplemental NPRM to give credit for previous initial and repetitive inspections of turbine rear frames done before the effective date of the proposed AD using the original or Revision 1 of CFM International, S.A. Service Bulletin No. CFM56–5B S/B 72–0620. Correction to How Many Engines Affected Since we issued the original NPRM, we discovered that we incorrectly estimated how many engines are affected. We stated that about 426 engines are affected that are installed on airplanes of U.S. registry. That number actually reflects how many engines are installed on airplanes of U.S. registry, regardless of the LP turbine rear frame P/N. We corrected the estimated number of affected engines to 282, which reflects those engines with the affected LP turbine rear frames listed in this supplemental NPRM. FAA’s Determination and Requirements of the Proposed AD We evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. We are proposing this AD, which will require initial and repetitive ECIs of certain P/N LP turbine rear frames. This proposed AD results from a refined lifing analysis by the engine manufacturer that shows the need to identify initial and repetitive inspection thresholds for inspecting certain LP turbine rear frames. This proposed AD would require you to use the service information described previously to perform the inspections. Costs of Compliance We estimate that this proposed AD would affect 282 CFM56–5B series turbofan engines installed on airplanes of U.S. registry. We estimate that it would take about 3 work-hours to perform an eddy current inspection of an LP turbine rear frame. The average labor rate is $80 per work-hour. A replacement LP turbine rear frame costs E:\FR\FM\24APP1.SGM 24APP1 18664 Federal Register / Vol. 74, No. 78 / Friday, April 24, 2009 / Proposed Rules about $102,240. If all 282 LP turbine rear frames needed replacement, we estimate the total cost of the proposed AD to U.S. operators to be $28,899,360. 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation. tjames on PRODPC75 with PROPOSALS List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 as follows: VerDate Nov<24>2008 14:02 Apr 23, 2009 Jkt 217001 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: CFM International, S.A.: Docket No. FAA– 2008–0174; Directorate Identifier 2008– NE–03–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by June 8, 2009. Affected ADs (b) None. Applicability (c) This AD applies to: (1) CFM International, S.A. turbofan engines with a low-pressure (LP) turbine rear frame, part number (P/N) 338–171–703–0; 338–171–704–0; 338–171–705–0; or 338– 171–706–0 installed, as follows: (i) Commercial application CFM56–5B1/P; –5B2/P; –5B3/P; –5B3/P1; –5B4/P; –5B4/P1; –5B5/P; –5B6/P; –5B7/P; –5B8/P; –5B9/P turbofan engines. (ii) Corporate application CFM56–5B6/P and –5B7/P turbofan engines. (2) CFM International, S.A. turbofan engines with an LP turbine rear frame, P/N 338–171–751–0; or 338–171–752–0 installed, on corporate and commercial applications of CFM56–5B1/P; –5B2/P; –5B3/P; –5B3/P1; –5B4/P; –5B4/P1; –5B5/P; –5B6/P; –5B7/P; –5B8/P; –5B9/P; –5B1/3; –5B2/3; –5B3/3; –5B4/3; –5B5/3; –5B6/3; –5B7/3; –5B8/3; –5B9/3; –5B3/3B1; and –5B4/3B1 turbofan engines. (3) These engines are installed on, but not limited to, Airbus A318, A319, A320, and A321 series airplanes. Unsafe Condition (d) This AD results from a refined lifing analysis by the engine manufacturer that shows the need to identify initial and repetitive inspection thresholds for inspecting certain LP turbine rear frames. We are issuing this AD to detect low-cyclefatigue cracks in the LP turbine rear frame, which could result in an engine separating from the airplane, causing damage to, and possibly leading to loss of control of 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. Initial Inspection (f) Perform an initial eddy current inspection (ECI) of the LP turbine rear frame using paragraphs 3.A. through 3.A.(7)(d) of the Accomplishment Instructions of CFM PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 International, S.A. Service Bulletin (SB) No. CFM56–5B S/B 72–0620, Revision 2, dated December 1, 2008, at the following compliance times: (1) For commercial engine applications, within 25,000 cycles-since-new (CSN) on the LP turbine rear frame. (2) For corporate engine applications, within 19,000 CSN on the LP turbine rear frame. (3) For engines with unknown LP turbine rear frame CSN, within 300 cycles-in-service from the effective date of this AD. Repetitive Inspections (g) Perform repetitive ECIs of the LP turbine rear frame using paragraphs 3.A. through 3.A.(7)(d) of the Accomplishment Instructions of CFM International, S.A. SB No. CFM56–5B S/B 72–0620, Revision 2, dated December 1, 2008. Use the inspection intervals in paragraph 3.A.(8) of the Accomplishment Instructions of CFM International, S.A. SB No. CFM56–5B S/B 72–0620, Revision 2, dated December 1, 2008. LP Turbine Rear Frame Removal Criteria (h) Remove LP turbine rear frames from service that have a single crack length of 2.56 inches (65 mm) or longer, or multiple cracks with an accumulated crack length of 2.56 inches (65 mm) or longer. Previous Credit (i) Initial and repetitive inspections done before the effective date of this AD using CFM International, S.A. SB No. CFM56–5B S/B 72–0620, dated May 3, 2007, or SB No. CFM56–5B S/B 72–0620, Revision 1, dated December 20, 2007, comply with the initial and repetitive inspection requirements specified in this AD. Operators must continue performing the repetitive inspections required in paragraph (g) of this AD. Alternative Methods of Compliance (j) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (k) European Aviation Safety Agency AD 2007–0221, dated August 13, 2007, also addresses the subject of this AD. (l) Contact Stephen Sheely, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: stephen.k.sheely@faa.gov; telephone (781) 238–7750; fax (781) 238– 7199, for more information about this AD. Issued in Burlington, Massachusetts, on April 17, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–9443 Filed 4–23–09; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\24APP1.SGM 24APP1

Agencies

[Federal Register Volume 74, Number 78 (Friday, April 24, 2009)]
[Proposed Rules]
[Pages 18662-18664]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-9443]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0174; Directorate Identifier 2008-NE-03-AD]
RIN 2120-AA64


Airworthiness Directives; CFM International, S.A. CFM56-5B1/P; -
5B2/P; -5B3/P; -5B3/P1; -5B4/P; -5B4/P1; -5B5/P; -5B6/P; -5B7/P; -5B8/
P; -5B9/P; -5B1/3; -5B2/3; -5B3/3; -5B4/3; -5B5/3; -5B6/3; -5B7/3; -
5B8/3; -5B9/3; -5B3/3B1; and -5B4/3B1 Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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

SUMMARY: This supplemental NPRM revises an earlier proposed 
airworthiness directive (AD), applicable to CFM International, S.A. 
CFM56-5B1/P; -5B2/P; -5B3/P; -5B3/P1; -5B4/P; -5B4/P1; -5B5/P; -5B6/P; 
-5B7/P; -5B8/P; and -5B9/P turbofan engines. That proposed AD would 
have required initial and repetitive eddy current inspections (ECIs) of 
certain part number (P/N) low-pressure (LP) turbine rear frames. That 
proposed AD resulted from a refined lifing analysis by the engine 
manufacturer that shows the need to identify initial and repetitive 
inspection thresholds for inspecting certain LP turbine rear frames. 
This supplemental NPRM revises the proposed AD to add two LP turbine 
rear frame P/Ns to the applicability, to add 11 engine models to the 
applicability, and to clarify the commercial and corporate engines/LP 
turbine rear frames applicability. This supplemental NPRM results from 
CFM International, S.A. revising the service information to add LP 
turbine rear frame P/Ns and engine models, and from comments received 
on the proposed AD. This supplemental NPRM also results from a refined 
lifing analysis by the engine manufacturer that shows the need to 
identify initial and repetitive inspection thresholds for inspecting 
certain LP turbine rear frames. We are proposing this AD to detect low-
cycle-fatigue cracks in the LP turbine rear frame, which could result 
in an engine separating from the airplane, causing damage to, and 
possibly leading to loss of control of, the airplane.

DATES: We must receive any comments on this proposed AD by June 8, 
2009.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.
    You can get the service information identified in this proposed AD 
from CFM International, Technical Publications Department, 1 Neumann 
Way, Cincinnati, OH 45215; telephone (513) 552-2800; fax (513) 552-
2816.

FOR FURTHER INFORMATION CONTACT: Stephen Sheely, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
stephen.k.sheely@faa.gov; telephone (781) 238-7750; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

[[Page 18663]]

Comments Invited

    We invite you to send us any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2008-0174; Directorate 
Identifier 2008-NE-03-AD'' in the subject line of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of the proposed AD. We will consider 
all comments received by the closing date and may amend the proposed AD 
in light 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 
with FAA personnel concerning this proposed AD. Using the search 
function of the Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, the name of the individual who 
sent the comment (or signed the comment on behalf of an association, 
business, labor union, etc.). You may review the DOT's complete Privacy 
Act Statement in the Federal Register published on April 11, 2000 (65 
FR 19477-78).

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office 
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 Operations office (telephone (800) 647-5527) is 
the same as the Mail address provided in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

Discussion

    On April 29, 2008, we issued a proposal to amend part 39 of the 
Code of Federal Regulations (14 CFR part 39) to add an AD, applicable 
to CFM International, S.A. CFM56-5B1/P; -5B2/P; -5B3/P; -5B3/P1; -5B4/
P; -5B4/P1; -5B5/P; -5B6/P; -5B7/P; -5B8/P; and -5B9/P turbofan 
engines. The proposed AD published as an NPRM in the Federal Register 
on May 7, 2008 (73 FR 25597). That NPRM proposed to require initial and 
repetitive ECIs of certain P/N LP turbine rear frames.
    Since we issued that NPRM, we became aware of two additional LP 
turbine rear frame P/Ns affected, and 11 additional engine models 
affected that were not listed in the proposed AD applicability. CFM 
International, S.A. subsequently superseded Service Bulletin (SB) No. 
CFM56-5B S/B 72-0620, Revision 1, dated December 20, 2007, to add those 
LP turbine rear frame P/Ns and engine models. We added LP turbine rear 
frame P/Ns 338-171-751-0; and 338-171-752-0, and CFM56-5B1/3; -5B2/3; -
5B3/3; -5B4/3; -5B5/3; -5B6/3; -5B7/3; -5B8/3; -5B9/3; -5B3/3B1; and -
5B4/3B1 engine models to the applicability of the supplemental NPRM. We 
also clarified the commercial and corporate engines/LP turbine rear 
frames applicability. Because we added those CFM56 engine models and 
added those LP turbine rear frame P/Ns, this supplemental NPRM reopens 
the comment period to include those added engine models and added P/Ns, 
and to reference the superseding service bulletin.
    As we stated in the original proposed AD, CFM International, S.A. 
performed a refined lifing analysis that shows the need to identify 
initial and repetitive inspection thresholds for inspecting LP turbine 
rear frames. This condition, if not corrected, could result in an 
engine separating from the airplane, causing damage to, and possibly 
leading to loss of control of the airplane.

Comments

    We provided the public the opportunity to participate in the 
development of this proposed AD. We have considered the comments 
received.

Consider Expanding the Engine Model Applicability

    One commenter, Virgin Airlines, requests that we consider expanding 
the applicability in the proposed AD by adding the CFM56-5B4/3 and 
CFM56-5B6/3 turbofan engines.
    We agree that those engines are affected. We added them to this 
supplemental NPRM.

Disagreement With Proposed AD Applicability

    One commenter, CFM International S.A., disagrees with the proposed 
AD applicability, specifically, the listing of all of the engines as 
certified for corporate application. They state that only the CFM56-
5B6/P and CFM56-5B7/P engine models certified for corporate application 
need to be covered by the proposed AD, because they were initially 
certified with a 22,500-cycle life. They now have a first inspection at 
19,000 cycles. All of the other -5B/P engine models in the corporate 
application were certified with the first inspection at 19,000 cycles, 
and do not need to be covered by the proposed AD.
    We agree. We corrected and clarified the applicability in the 
supplemental NPRM.

Request To Give Credit

    One commenter, Airbus, requests that we give credit for inspections 
previously done using CFM International, S.A. Service Bulletin No. 
CFM56-5B S/B 72-0620, dated May 3, 2007.
    We agree. We changed the supplemental NPRM to give credit for 
previous initial and repetitive inspections of turbine rear frames done 
before the effective date of the proposed AD using the original or 
Revision 1 of CFM International, S.A. Service Bulletin No. CFM56-5B S/B 
72-0620.

Correction to How Many Engines Affected

    Since we issued the original NPRM, we discovered that we 
incorrectly estimated how many engines are affected. We stated that 
about 426 engines are affected that are installed on airplanes of U.S. 
registry. That number actually reflects how many engines are installed 
on airplanes of U.S. registry, regardless of the LP turbine rear frame 
P/N. We corrected the estimated number of affected engines to 282, 
which reflects those engines with the affected LP turbine rear frames 
listed in this supplemental NPRM.

FAA's Determination and Requirements of the Proposed AD

    We evaluated all pertinent information and identified an unsafe 
condition that is likely to exist or develop on other products of this 
same type design. We are proposing this AD, which will require initial 
and repetitive ECIs of certain P/N LP turbine rear frames. This 
proposed AD results from a refined lifing analysis by the engine 
manufacturer that shows the need to identify initial and repetitive 
inspection thresholds for inspecting certain LP turbine rear frames. 
This proposed AD would require you to use the service information 
described previously to perform the inspections.

Costs of Compliance

    We estimate that this proposed AD would affect 282 CFM56-5B series 
turbofan engines installed on airplanes of U.S. registry. We estimate 
that it would take about 3 work-hours to perform an eddy current 
inspection of an LP turbine rear frame. The average labor rate is $80 
per work-hour. A replacement LP turbine rear frame costs

[[Page 18664]]

about $102,240. If all 282 LP turbine rear frames needed replacement, 
we estimate the total cost of the proposed AD to U.S. operators to be 
$28,899,360.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Would not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration 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 adding the following new 
airworthiness directive:

CFM International, S.A.: Docket No. FAA-2008-0174; Directorate 
Identifier 2008-NE-03-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by June 8, 
2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to:
    (1) CFM International, S.A. turbofan engines with a low-pressure 
(LP) turbine rear frame, part number (P/N) 338-171-703-0; 338-171-
704-0; 338-171-705-0; or 338-171-706-0 installed, as follows:
    (i) Commercial application CFM56-5B1/P; -5B2/P; -5B3/P; -5B3/P1; 
-5B4/P; -5B4/P1; -5B5/P; -5B6/P; -5B7/P; -5B8/P; -5B9/P turbofan 
engines.
    (ii) Corporate application CFM56-5B6/P and -5B7/P turbofan 
engines.
    (2) CFM International, S.A. turbofan engines with an LP turbine 
rear frame, P/N 338-171-751-0; or 338-171-752-0 installed, on 
corporate and commercial applications of CFM56-5B1/P; -5B2/P; -5B3/
P; -5B3/P1; -5B4/P; -5B4/P1; -5B5/P; -5B6/P; -5B7/P; -5B8/P; -5B9/P; 
-5B1/3; -5B2/3; -5B3/3; -5B4/3; -5B5/3; -5B6/3; -5B7/3; -5B8/3; -
5B9/3; -5B3/3B1; and -5B4/3B1 turbofan engines.
    (3) These engines are installed on, but not limited to, Airbus 
A318, A319, A320, and A321 series airplanes.

Unsafe Condition

    (d) This AD results from a refined lifing analysis by the engine 
manufacturer that shows the need to identify initial and repetitive 
inspection thresholds for inspecting certain LP turbine rear frames. 
We are issuing this AD to detect low-cycle-fatigue cracks in the LP 
turbine rear frame, which could result in an engine separating from 
the airplane, causing damage to, and possibly leading to loss of 
control of 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.

Initial Inspection

    (f) Perform an initial eddy current inspection (ECI) of the LP 
turbine rear frame using paragraphs 3.A. through 3.A.(7)(d) of the 
Accomplishment Instructions of CFM International, S.A. Service 
Bulletin (SB) No. CFM56-5B S/B 72-0620, Revision 2, dated December 
1, 2008, at the following compliance times:
    (1) For commercial engine applications, within 25,000 cycles-
since-new (CSN) on the LP turbine rear frame.
    (2) For corporate engine applications, within 19,000 CSN on the 
LP turbine rear frame.
    (3) For engines with unknown LP turbine rear frame CSN, within 
300 cycles-in-service from the effective date of this AD.

Repetitive Inspections

    (g) Perform repetitive ECIs of the LP turbine rear frame using 
paragraphs 3.A. through 3.A.(7)(d) of the Accomplishment 
Instructions of CFM International, S.A. SB No. CFM56-5B S/B 72-0620, 
Revision 2, dated December 1, 2008. Use the inspection intervals in 
paragraph 3.A.(8) of the Accomplishment Instructions of CFM 
International, S.A. SB No. CFM56-5B S/B 72-0620, Revision 2, dated 
December 1, 2008.

LP Turbine Rear Frame Removal Criteria

    (h) Remove LP turbine rear frames from service that have a 
single crack length of 2.56 inches (65 mm) or longer, or multiple 
cracks with an accumulated crack length of 2.56 inches (65 mm) or 
longer.

Previous Credit

    (i) Initial and repetitive inspections done before the effective 
date of this AD using CFM International, S.A. SB No. CFM56-5B S/B 
72-0620, dated May 3, 2007, or SB No. CFM56-5B S/B 72-0620, Revision 
1, dated December 20, 2007, comply with the initial and repetitive 
inspection requirements specified in this AD. Operators must 
continue performing the repetitive inspections required in paragraph 
(g) of this AD.

Alternative Methods of Compliance

    (j) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Related Information

    (k) European Aviation Safety Agency AD 2007-0221, dated August 
13, 2007, also addresses the subject of this AD.
    (l) Contact Stephen Sheely, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
stephen.k.sheely@faa.gov; telephone (781) 238-7750; fax (781) 238-
7199, for more information about this AD.

    Issued in Burlington, Massachusetts, on April 17, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-9443 Filed 4-23-09; 8:45 am]
BILLING CODE 4910-13-P

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