Airworthiness Directives; CFM International, S.A. CFM56-7B Series Turbofan Engines, 21772-21774 [E9-10956]

Download as PDF 21772 Federal Register / Vol. 74, No. 89 / Monday, May 11, 2009 / Proposed Rules appointees and designees an opportunity to review and approve such rules. As noted above, when OPM reopened the public comment period, we received numerous substantive comments opposing the final rule, requesting amendments or clarifications, or stating concerns about implementation. OPM needs time to evaluate these comments, as well as the new comments in favor of the rule, as part of the review and evaluation process described in the White House memorandum on regulatory review. Accordingly, OPM proposes to revoke the November 7, 2008 final rule pending OPM’s review and consideration of the additional public comments that were solicited on March 9, 2009. OPM seeks additional public comments, with a 30day comment period, on the merits of revoking, retaining, or amending the November 7, 2008 final rule. When OPM issues a new final rule, or reissues the November 7, 2008 final rule, with or without amendments, OPM will account for the public comments received in response to the March 9, 2009 Federal Register notice, as well as any comments received in response to this notice of proposed rulemaking. these reasons, OPM proposes to extend the November 7, 2008 final rule’s effective date by an additional 90 days, until August 16, 2009. This will give OPM time to review public comments and complete the rulemaking proceeding. OPM is opening a 5-day public comment period on the proposed extension of the final rule’s effective date, separate from the 30-day public comment period on the notice of proposed rulemaking. OPM suggests that agencies delay preparations and financial commitments associated with the changes required by the final rule until a decision is made regarding whether and when, if at all, the regulation will go into effect. Proposal To Extend the Final Rule’s Effective Date The November 7, 2008 final rule is scheduled to take effect on May 18, 2009. However, in its February 6, 2008 notice of proposed rulemaking, OPM recognized that agencies need significant time to implement any new policy on time-in-grade requirements, and to communicate the policy to human resources staff and employees. This concern was validated by one agency’s comment, in response to OPM’s March 9, 2009 Federal Register notice, that implementing a time-ingrade policy required significant lead time, because of that agency’s need to modify merit promotion procedures, notify labor organizations, and amend hundreds of vacancy announcements for competitive service positions, all at a time when the agency had significant competing obligations. Unless the final rule’s effective date is further extended, agencies likely will undertake significant effort and expense to meet the changes required by the rule. If the decision is made to revoke or amend the final rule, these expenses will have been incurred unnecessarily. Furthermore, OPM will have to begin answering questions and providing compliance assistance about how the final rule is to be implemented, guidance that will only confuse agencies if new guidance about a revised rule has to be provided in the near future. For Freedom of information, Government employees, Reporting and recordkeeping requirements, Selective Service System. VerDate Nov<24>2008 12:49 May 08, 2009 Jkt 217001 Regulatory Flexibility Act I certify that this regulation will not have a significant economic impact on a substantial number of small entities because it affects only certain Federal employees. E.O. 12866, Regulatory Review This rule has been reviewed by the Office of Management and Budget in accordance with Executive Order 12866. List of Subjects in 5 CFR Part 300 U.S. Office of Personnel Management. John Berry, Director. [FR Doc. E9–11014 Filed 5–7–09; 12:00 pm BILLING CODE 6325–39–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0236; Directorate Identifier 2009–NE–06–AD] RIN 2120–AA64 Airworthiness Directives; CFM International, S.A. CFM56–7B Series Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for CFM International, S.A. CFM56–7B series turbofan engines. This proposed AD would require initial and repetitive eddy current inspections (ECIs) of certain part number (P/N) low-pressure PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 (LP) turbine rear frames. This proposed AD results from a refined life analysis by the engine manufacturer that shows the need to identify an initial and repetitive inspection threshold for inspecting certain LP turbine rear frames. We are proposing this AD to prevent failure of the LP turbine rear frame from low-cycle-fatigue cracks. Failure of the LP turbine rear frame could result in engine separation from the airplane, possibly leading to loss of control of the airplane. DATES: We must receive any comments on this proposed AD by July 10, 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. FOR FURTHER INFORMATION CONTACT: Antonio Cancelliere, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: antonio.cancelliere@faa.gov; (781) 238– 7199. Contact CFM International, Technical Publications Department, 1 Neumann Way, Cincinnati, OH 45215; telephone (513) 552–2800; fax (513) 552–2816, for a copy of the service information identified in this proposed AD. SUPPLEMENTARY INFORMATION: 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– 2009–0236; Directorate Identifier 2009– NE–06–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 E:\FR\FM\11MYP1.SGM 11MYP1 Federal Register / Vol. 74, No. 89 / Monday, May 11, 2009 / Proposed Rules 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 CFM International, S.A. performed a refined life analysis that identified the need for initial and repetitive inspection thresholds for LP turbine rear frames, P/Ns 340–166–254–0; 340–166–255–0; 340–166–256–0; 340–166–257–0; 340– 166–258–0; 340–166–259–0; P/N 340– 177–551–0; 340–177–552–0; 340–177– 553–0; 340–177–554–0; 340–177–555–0; and 340–177–556–0. These LP turbine rear frames are installed on CFM56–7B series turbofan engines. This proposed AD would require initial and repetitive ECIs of these LP turbine rear frames. This condition, if not corrected, could result in engine separation from the airplane, possibly leading to loss of control of the airplane. Relevant Service Information We have reviewed and approved the technical contents of CFM International, S.A. Service Bulletin (SB) No. CFM56– 7B S/B 72–0558, Revision 2, dated December 1, 2008, and SB No. CFM56– 7B S/B 72–0579, Revision 4, dated December 1, 2008, that describe procedures for performing initial and repetitive ECIs of the LP turbine rear frame. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or VerDate Nov<24>2008 12:49 May 08, 2009 Jkt 217001 21773 develop on other products of this same type design. We are proposing this AD, which would require initial and repetitive ECIs of the affected P/N LP turbine rear frames. The proposed AD would require you to use the service information described previously to perform these actions. 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. You may get a copy of this summary at the address listed under ADDRESSES. Costs of Compliance We estimate that this proposed AD would affect 1,228 CFM56–7B 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 about $275,000. If all 1,228 LP turbine rear frames needed replacement, we estimate the total cost of the proposed AD to U.S. operators to be $33,994,720. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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 AD: 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, PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: CFM International, S.A: Docket No. FAA– 2009–0236; Directorate Identifier 2009– NE–06–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by July 10, 2009. Affected ADs (b) None. Applicability (c) This AD applies to: (1) CFM International, S.A. CFM56–7B20; –7B22; –7B24; –7B26; –7B27; –7B22/B1; –7B24/B1; –7B27/B1; –7B26/B1; –7B26/B2; –7B20/3; –7B22/3; –7B24/3; –7B26/3; –7B27/ 3; –7B22/3B1; –7B24/3B1; –7B27/3B1; –7B26/3B1; –7B26/3B2; –7B26/3F; –7B27/3; –7B27/3F; –7B26/3B2F; –7B27/3B1F; –7B27/ 3B3; and –7B27A turbofan engines assembled with a low-pressure (LP) turbine rear frame, part number (P/N) 340–166–254–0; 340–166– 254–0; 340–166–255–0; 340–166–256–0; 340–166–257–0; 340–166–258–0; or 340– 166–259–0; and (2) CFM International, S.A. CFM56–7B20/ 2; –7B22/2; –7B24/2; –7B26/2; and –7B27/2 turbofan engines assembled with a dual annular combustor and an LP turbine rear frame, P/N 340–177–551–0; 340–177–552–0; 340–177–553–0; 340–177–554–0; 340–177– 555–0; or 340–177–556–0. (3) These engines are installed on, but not limited to, Boeing 737–600, 737–700, 737– 800, and 737–900 series airplanes. Unsafe Condition (d) This AD results from a refined life analysis by the engine manufacturer that shows the need to identify an initial and E:\FR\FM\11MYP1.SGM 11MYP1 21774 Federal Register / Vol. 74, No. 89 / Monday, May 11, 2009 / Proposed Rules repetitive inspection threshold for inspecting certain LP turbine rear frames. We are issuing this AD to prevent failure of the LP turbine rear frame from low-cycle-fatigue cracks. Failure of the LP turbine rear frame could result in engine separation from the airplane, 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. Inspections of LP Turbine Rear Frames (f) For CFM International, S.A. CFM56– 7B20; –7B22; –7B24; –7B26; –7B27; –7B22/ B1; –7B24/B1; –7B27/B1; –7B26/B2; –7B20/ 3; –7B22/3; –7B24/3; –7B26/3; –7B27/3; –7B22/3B1; –7B24/3B1; –7B27/3B1; –7B26/ 3B2; –7B26/3F; –7B27/3F; –7B26/3B2F; –7B27/3B1F; and –7B27A turbofan engines with an LP turbine rear frame, P/N 340–166– 254–0; 340–166–254–0; 340–166–255–0; 340–166–256–0; 340–166–257–0; 340–166– 258–0; or 340–166–259–0, do the following: (1) Perform an initial eddy current inspection (ECI) of the LP turbine rear frame within 25,000 cycles-since-new (CSN) on the LP turbine rear frame. (2) For engines with unknown LP turbine rear frame CSN, perform an initial ECI within 300 cycles from the effective date of this AD. (3) Perform repetitive ECIs of the LP turbine rear frame, using the inspection intervals in paragraph 3.A.(8) of the Accomplishment Instructions of CFM International, S.A. SB No. CFM56–7B S/B 72–0579, Revision 4, dated December 1, 2008. (4) Use paragraphs 3.A. through 3.A.(7)(d) of the Accomplishment Instructions of CFM International, S.A. Service Bulletin (SB) No. CFM56–7B S/B 72–0579, Revision 4, dated December 1, 2008, to do the ECIs. (5) Remove LP turbine rear frames from service that have a total cumulated crack VerDate Nov<24>2008 12:49 May 08, 2009 Jkt 217001 length at any location, of 0.79 inch (20 mm) or longer. (g) For CFM International, S.A. CFM56– 7B26/B1; –7B27/3; –7B26/3B1; and –7B27/ 3B3 turbofan engines with an LP turbine rear frame, P/N 340–166–254–0; 340–166–254–0; 340–166–255–0; 340–166–256–0; 340–166– 257–0; 340–166–258–0; or 340–166–259–0, do the following: (1) Perform an initial ECI of the LP turbine rear frame within 19,000 CSN on the LP turbine rear frame. (2) For engines with unknown LP turbine rear frame CSN, perform an initial ECI within 300 cycles from the effective date of this AD. (3) Perform repetitive ECIs of the LP turbine rear frame, using the inspection intervals in paragraph 3.A.(9) of the Accomplishment Instructions of CFM International, S.A. SB No. CFM56–7B S/B 72–0579, Revision 4, dated December 1, 2008. (4) Use paragraphs 3.A. through 3.A.(7)(d) of the Accomplishment Instructions of CFM International, S.A. Service Bulletin (SB) No. CFM56–7B S/B 72–0579, Revision 4, dated December 1, 2008, to do the ECIs. (5) Remove LP turbine rear frames from service that have a total cumulated crack length at any location, of 0.79 inch (20 mm) or longer. (h) For CFM International, S.A. CFM56– 7B20/2; –7B22/2; –7B24/2; –7B26/2; and –7B27/2 turbofan engines assembled with a dual annular combustor and an LP turbine rear frame, P/N 340–177–551–0; 340–177– 552–0; 340–177–553–0; 340–177–554–0; 340–177–555–0; or 340–177–556–0, do the following: (1) Perform an initial ECI of the LP turbine rear frame within 16,350 CSN on the LP turbine rear frame. (2) For engines with unknown LP turbine rear frame CSN, perform an initial ECI within 300 cycles from the effective date of this AD. (3) Perform repetitive ECIs of the LP turbine rear frame, using the inspection PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 intervals in paragraph 3.A.(8) of the Accomplishment Instructions of CFM International, S.A. SB No. CFM56–7B S/B 72–0558, Revision 2, dated December 1, 2008. (4) Use paragraphs 3.A. through 3.A.(7)(d) of the Accomplishment Instructions of CFM International, S.A. SB No. CFM56–7B S/B 72–0558, Revision 2, dated December 1, 2008, to do the ECIs. (5) Remove LP turbine rear frames from service that have a total cumulated crack length at any location, of 0.43 inch (11 mm) or longer. Alternative Methods of Compliance (i) 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 (j) European Aviation Safety Agency AD 2009–0009, dated January 15, 2009, also addresses the subject of this AD. (k) Contact CFM International, Technical Publications Department, 1 Neumann Way, Cincinnati, OH 45215; telephone (513) 552– 2800; fax (513) 552–2816, for a copy of the service information identified in this AD. (l) Contact Antonio Cancelliere, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: antonio.cancelliere@faa.gov; 238–7751; fax (781) 238–7199, for more information about this AD. Issued in Burlington, Massachusetts, on May 4, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–10956 Filed 5–8–09; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\11MYP1.SGM 11MYP1

Agencies

[Federal Register Volume 74, Number 89 (Monday, May 11, 2009)]
[Proposed Rules]
[Pages 21772-21774]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-10956]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0236; Directorate Identifier 2009-NE-06-AD]
RIN 2120-AA64


Airworthiness Directives; CFM International, S.A. CFM56-7B Series 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for CFM International, S.A. CFM56-7B series turbofan engines. This 
proposed AD would require initial and repetitive eddy current 
inspections (ECIs) of certain part number (P/N) low-pressure (LP) 
turbine rear frames. This proposed AD results from a refined life 
analysis by the engine manufacturer that shows the need to identify an 
initial and repetitive inspection threshold for inspecting certain LP 
turbine rear frames. We are proposing this AD to prevent failure of the 
LP turbine rear frame from low-cycle-fatigue cracks. Failure of the LP 
turbine rear frame could result in engine separation from the airplane, 
possibly leading to loss of control of the airplane.

DATES: We must receive any comments on this proposed AD by July 10, 
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.

FOR FURTHER INFORMATION CONTACT: Antonio Cancelliere, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803; e-
mail: antonio.cancelliere@faa.gov; (781) 238-7199.
    Contact CFM International, Technical Publications Department, 1 
Neumann Way, Cincinnati, OH 45215; telephone (513) 552-2800; fax (513) 
552-2816, for a copy of the service information identified in this 
proposed AD.

SUPPLEMENTARY INFORMATION: 

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-2009-0236; Directorate 
Identifier 2009-NE-06-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

[[Page 21773]]

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

    CFM International, S.A. performed a refined life analysis that 
identified the need for initial and repetitive inspection thresholds 
for LP turbine rear frames, P/Ns 340-166-254-0; 340-166-255-0; 340-166-
256-0; 340-166-257-0; 340-166-258-0; 340-166-259-0; P/N 340-177-551-0; 
340-177-552-0; 340-177-553-0; 340-177-554-0; 340-177-555-0; and 340-
177-556-0. These LP turbine rear frames are installed on CFM56-7B 
series turbofan engines. This proposed AD would require initial and 
repetitive ECIs of these LP turbine rear frames. This condition, if not 
corrected, could result in engine separation from the airplane, 
possibly leading to loss of control of the airplane.

Relevant Service Information

    We have reviewed and approved the technical contents of CFM 
International, S.A. Service Bulletin (SB) No. CFM56-7B S/B 72-0558, 
Revision 2, dated December 1, 2008, and SB No. CFM56-7B S/B 72-0579, 
Revision 4, dated December 1, 2008, that describe procedures for 
performing initial and repetitive ECIs of the LP turbine rear frame.

FAA's Determination and Requirements of the Proposed AD

    We have 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 would require 
initial and repetitive ECIs of the affected P/N LP turbine rear frames. 
The proposed AD would require you to use the service information 
described previously to perform these actions.

Costs of Compliance

    We estimate that this proposed AD would affect 1,228 CFM56-7B 
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 about 
$275,000. If all 1,228 LP turbine rear frames needed replacement, we 
estimate the total cost of the proposed AD to U.S. operators to be 
$33,994,720.

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 AD:
    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. You may get a copy of this summary at the 
address listed under ADDRESSES.

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-2009-0236; Directorate 
Identifier 2009-NE-06-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by July 10, 
2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to:
    (1) CFM International, S.A. CFM56-7B20; -7B22; -7B24; -7B26; -
7B27; -7B22/B1; -7B24/B1; -7B27/B1; -7B26/B1; -7B26/B2; -7B20/3; -
7B22/3; -7B24/3; -7B26/3; -7B27/3; -7B22/3B1; -7B24/3B1; -7B27/3B1; 
-7B26/3B1; -7B26/3B2; -7B26/3F; -7B27/3; -7B27/3F; -7B26/3B2F; -
7B27/3B1F; -7B27/3B3; and -7B27A turbofan engines assembled with a 
low-pressure (LP) turbine rear frame, part number (P/N) 340-166-254-
0; 340-166-254-0; 340-166-255-0; 340-166-256-0; 340-166-257-0; 340-
166-258-0; or 340-166-259-0; and
    (2) CFM International, S.A. CFM56-7B20/2; -7B22/2; -7B24/2; -
7B26/2; and -7B27/2 turbofan engines assembled with a dual annular 
combustor and an LP turbine rear frame, P/N 340-177-551-0; 340-177-
552-0; 340-177-553-0; 340-177-554-0; 340-177-555-0; or 340-177-556-
0.
    (3) These engines are installed on, but not limited to, Boeing 
737-600, 737-700, 737-800, and 737-900 series airplanes.

Unsafe Condition

    (d) This AD results from a refined life analysis by the engine 
manufacturer that shows the need to identify an initial and

[[Page 21774]]

repetitive inspection threshold for inspecting certain LP turbine 
rear frames. We are issuing this AD to prevent failure of the LP 
turbine rear frame from low-cycle-fatigue cracks. Failure of the LP 
turbine rear frame could result in engine separation from the 
airplane, 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.

Inspections of LP Turbine Rear Frames

    (f) For CFM International, S.A. CFM56-7B20; -7B22; -7B24; -7B26; 
-7B27; -7B22/B1; -7B24/B1; -7B27/B1; -7B26/B2; -7B20/3; -7B22/3; -
7B24/3; -7B26/3; -7B27/3; -7B22/3B1; -7B24/3B1; -7B27/3B1; -7B26/
3B2; -7B26/3F; -7B27/3F; -7B26/3B2F; -7B27/3B1F; and -7B27A turbofan 
engines with an LP turbine rear frame, P/N 340-166-254-0; 340-166-
254-0; 340-166-255-0; 340-166-256-0; 340-166-257-0; 340-166-258-0; 
or 340-166-259-0, do the following:
    (1) Perform an initial eddy current inspection (ECI) of the LP 
turbine rear frame within 25,000 cycles-since-new (CSN) on the LP 
turbine rear frame.
    (2) For engines with unknown LP turbine rear frame CSN, perform 
an initial ECI within 300 cycles from the effective date of this AD.
    (3) Perform repetitive ECIs of the LP turbine rear frame, using 
the inspection intervals in paragraph 3.A.(8) of the Accomplishment 
Instructions of CFM International, S.A. SB No. CFM56-7B S/B 72-0579, 
Revision 4, dated December 1, 2008.
    (4) Use paragraphs 3.A. through 3.A.(7)(d) of the Accomplishment 
Instructions of CFM International, S.A. Service Bulletin (SB) No. 
CFM56-7B S/B 72-0579, Revision 4, dated December 1, 2008, to do the 
ECIs.
    (5) Remove LP turbine rear frames from service that have a total 
cumulated crack length at any location, of 0.79 inch (20 mm) or 
longer.
    (g) For CFM International, S.A. CFM56-7B26/B1; -7B27/3; -7B26/
3B1; and -7B27/3B3 turbofan engines with an LP turbine rear frame, 
P/N 340-166-254-0; 340-166-254-0; 340-166-255-0; 340-166-256-0; 340-
166-257-0; 340-166-258-0; or 340-166-259-0, do the following:
    (1) Perform an initial ECI of the LP turbine rear frame within 
19,000 CSN on the LP turbine rear frame.
    (2) For engines with unknown LP turbine rear frame CSN, perform 
an initial ECI within 300 cycles from the effective date of this AD.
    (3) Perform repetitive ECIs of the LP turbine rear frame, using 
the inspection intervals in paragraph 3.A.(9) of the Accomplishment 
Instructions of CFM International, S.A. SB No. CFM56-7B S/B 72-0579, 
Revision 4, dated December 1, 2008.
    (4) Use paragraphs 3.A. through 3.A.(7)(d) of the Accomplishment 
Instructions of CFM International, S.A. Service Bulletin (SB) No. 
CFM56-7B S/B 72-0579, Revision 4, dated December 1, 2008, to do the 
ECIs.
    (5) Remove LP turbine rear frames from service that have a total 
cumulated crack length at any location, of 0.79 inch (20 mm) or 
longer.
    (h) For CFM International, S.A. CFM56-7B20/2; -7B22/2; -7B24/2; 
-7B26/2; and -7B27/2 turbofan engines assembled with a dual annular 
combustor and an LP turbine rear frame, P/N 340-177-551-0; 340-177-
552-0; 340-177-553-0; 340-177-554-0; 340-177-555-0; or 340-177-556-
0, do the following:
    (1) Perform an initial ECI of the LP turbine rear frame within 
16,350 CSN on the LP turbine rear frame.
    (2) For engines with unknown LP turbine rear frame CSN, perform 
an initial ECI within 300 cycles from the effective date of this AD.
    (3) Perform repetitive ECIs of the LP turbine rear frame, using 
the inspection intervals in paragraph 3.A.(8) of the Accomplishment 
Instructions of CFM International, S.A. SB No. CFM56-7B S/B 72-0558, 
Revision 2, dated December 1, 2008.
    (4) Use paragraphs 3.A. through 3.A.(7)(d) of the Accomplishment 
Instructions of CFM International, S.A. SB No. CFM56-7B S/B 72-0558, 
Revision 2, dated December 1, 2008, to do the ECIs.
    (5) Remove LP turbine rear frames from service that have a total 
cumulated crack length at any location, of 0.43 inch (11 mm) or 
longer.

Alternative Methods of Compliance

    (i) 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

    (j) European Aviation Safety Agency AD 2009-0009, dated January 
15, 2009, also addresses the subject of this AD.
    (k) Contact CFM International, Technical Publications 
Department, 1 Neumann Way, Cincinnati, OH 45215; telephone (513) 
552-2800; fax (513) 552-2816, for a copy of the service information 
identified in this AD.
    (l) Contact Antonio Cancelliere, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
antonio.cancelliere@faa.gov; 238-7751; fax (781) 238-7199, for more 
information about this AD.

    Issued in Burlington, Massachusetts, on May 4, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-10956 Filed 5-8-09; 8:45 am]
BILLING CODE 4910-13-P

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