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, 43634-43636 [E9-20284]

Download as PDF 43634 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. DEPARTMENT OF TRANSPORTATION Related Information 14 CFR Part 39 (h) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2008–0118, dated June 27, 2008; and EADS CASA Service Bulletin SB–235– 30–16, dated January 21, 2005; for related information. [Docket No. FAA–2008–0174; Directorate Identifier 2008–NE–03–AD; Amendment 39– 15997; AD 2009–18–01] Material Incorporated by Reference (i) You must use EADS CASA Service Bulletin SB–235–30–16, dated January 21, 2005, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact EADS–CASA, Military Transport Aircraft Division (MTAD), Integrated Customer Services (ICS), ´ Technical Services, Avenida de Aragon 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; fax +34 91 585 55 05; e-mail MTA.TechnicalService@casa.eads.net; Internet http://www.eads.net. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on August 17, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–20581 Filed 8–26–09; 8:45 am] srobinson on DSKHWCL6B1PROD with RULES BILLING CODE 4910–13–P VerDate Nov<24>2008 16:19 Aug 26, 2009 Jkt 217001 Federal Aviation Administration 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), DOT. ACTION: Final rule. SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 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. This AD requires initial and repetitive eddy current inspections (ECIs) of certain part number (P/N) lowpressure (LP) turbine rear frames. 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. DATES: This AD becomes effective October 1, 2009. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of October 1, 2009. ADDRESSES: You can get the service information identified in this AD from CFM International, Technical Publications Department, 1 Neumann Way, Cincinnati, OH 45215; telephone (513) 552–2800; fax (513) 552–2816. The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: Stephen Sheely, Aerospace Engineer, Engine Certification Office, FAA, Engine PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 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. The FAA proposed to amend 14 CFR part 39 with a proposed AD and a supplemental proposed AD. The proposed AD applies 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, and the supplemental proposed AD applies 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; –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. We published the proposed AD in the Federal Register on May 7, 2008 (73 FR 25597). That action proposed to require initial and repetitive ECIs of certain P/N LP turbine rear frames. We published the supplemental proposed AD in the Federal Register on April 24, 2009 (74 FR 18662). That action proposed to require initial and repetitive ECIs of those same P/N LP turbine rear frames, to add two additional P/N LP turbine rear frames, to add 11 engine models to the applicability, and to clarify the commercial and corporate engines/LP turbine rear frames applicability. SUPPLEMENTARY INFORMATION: Examining the AD Docket You may examine the AD docket on the Internet at http:// 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment received. One commenter, CFM International, S.A. requests that we reference the latest European Aviation Safety Agency AD 2009–0110, dated May 7, 2009, as it is up-to-date on P/Ns and engine models affected. We agree and changed the AD to reference AD 2009–0110. E:\FR\FM\27AUR1.SGM 27AUR1 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations Conclusion We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. (3) 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. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. Costs of Compliance We estimate that this AD will affect 282 CFM56–5B series turbofan engines installed on airplanes of U.S. registry. We estimate that it will take about 3 work-hours to perform an eddy current inspection of an LP turbine rear frame. The average labor rate is $80 per workhour. A replacement LP turbine rear frame costs about $102,240. If all 282 LP turbine rear frames needed replacement, we estimate the total cost of the AD to U.S. operators to be $28,899,360. Our cost estimate is exclusive of possible warranty coverage. List of Subjects in 14 CFR Part 39 srobinson on DSKHWCL6B1PROD with RULES 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); and VerDate Nov<24>2008 16:19 Aug 26, 2009 Jkt 217001 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 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: ■ 2009–18–01 CFM International, S.A.: Amendment 39–15997. Docket No. FAA–2008–0174; Directorate Identifier 2008–NE–03–AD. Effective Date (a) This airworthiness directive (AD) becomes effective October 1, 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. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 43635 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 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. E:\FR\FM\27AUR1.SGM 27AUR1 43636 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations Related Information (k) European Aviation Safety Agency AD 2009–0110, dated May 7, 2009, 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. Material Incorporated by Reference (m) You must use CFM International, S.A. SB No. CFM56–5B S/B 72–0620, Revision 2, dated December 1, 2008 to perform the inspections required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact CFM International, Technical Publications Department, 1 Neumann Way, Cincinnati, OH 45215; telephone (513) 552–2800; fax (513) 552–2816, for a copy of this service information. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on August 17, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–20284 Filed 8–26–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0622; Directorate Identifier 2009–CE–034–AD; Amendment 39–15999; AD 2009–18–03] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Models PC–6, PC–6–H1, PC–6–H2, PC–6/350, PC–6/350–H1, PC– 6/350–H2, PC–6/A, PC–6/A–H1, PC–6/ A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/ B2–H2, PC–6/B2–H4, PC–6/C–H2, and PC–6/C1–H2 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. srobinson on DSKHWCL6B1PROD with RULES AGENCY: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) SUMMARY: VerDate Nov<24>2008 16:19 Aug 26, 2009 Jkt 217001 issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Findings of corrosion, wear and cracks in the upper wing strut fittings on some PC–6 aircraft have been reported in the past. It is possible that the spherical bearing of the wing strut fittings installed in the underwing can be loose in the fitting or cannot rotate because of corrosion. In this condition, the joint cannot function as designed and fatigue cracks may then develop. Undetected cracks, wear and/or corrosion in this area could cause failure of the upper attachment fitting, leading to failure of the wing structure and subsequent loss of control of the aircraft. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective October 1, 2009. On October 1, 2009, the Director of the Federal Register approved the incorporation by reference of Pilatus Aircraft Ltd. Pilatus PC–6 Service Bulletin No. 57–005, REV No. 2, dated May 19, 2008, and Chapter 57–00–02 of Pilatus Aircraft Ltd. Pilatus PC–6 Aircraft Maintenance Manual, dated November 30, 2008 (referenced as revision 9 in European Aviation Safety Agency (EASA) AD No.: 2007–0241R3), listed in this AD. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on July 8, 2009 (74 FR 32471), and proposed to supersede AD 2007– 19–14, Amendment 39–15205 (72 FR 53920, September 21, 2007). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Findings of corrosion, wear and cracks in the upper wing strut fittings on some PC–6 aircraft have been reported in the past. It is possible that the spherical bearing of the PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 wing strut fittings installed in the underwing can be loose in the fitting or cannot rotate because of corrosion. In this condition, the joint cannot function as designed and fatigue cracks may then develop. Undetected cracks, wear and/or corrosion in this area could cause failure of the upper attachment fitting, leading to failure of the wing structure and subsequent loss of control of the aircraft. To address this problem, FOCA published AD TM–L Nr. 80.627–6/Index 72–2 and HB– 2006–400 and EASA published AD 2007– 0114 to require specific inspections and to obtain a fleet status. Since the issuance of AD 2007–0114, the reported data proved that it was necessary to establish and require repetitive inspections. EASA published Emergency AD 2007– 0241–E to extend the applicability and to require repetitive eddy current and visual inspections of the upper wing strut fitting for evidence of cracks, wear and/or corrosion and examination of the spherical bearing and replacement of cracked fittings. Collected data received in response to Emergency AD 2007–0241–E resulted in the issuance of EASA AD 2007–0241R1 that permitted extending the intervals for the repetitive eddy current and visual inspections from 100 Flight Hours (FH) to 300 FH and from 150 Flight Cycles (FC) to 450 FC, respectively. In addition, oversize bolts were introduced by Pilatus PC–6 Service Bulletin (SB) 57–005 R1 and the fitting replacement procedure was adjusted accordingly. Based on fatigue test results, EASA AD 2007–0241R2 was issued to extend the repetitive inspection interval to 1 100 FH or 12 calendar months, whichever occurs first, and to delete the related flight cycle intervals and the requirement for the ‘‘Mild Corrosion Severity Zone’’. In addition, some editorial changes have been made for reasons of standardization and readability. Revision 3 of this AD refers to the latest revision of the PC–6 Aircraft Maintenance Manual (AMM) Chapter 5 limitations which includes the same repetitive inspection intervals and procedures already mandated in the revision 2 of AD 2007–0241. Besides the inspections, the latest revision of the PC– 6 AMM contains the replacement procedures for the fittings. Additionally, it is possible to replace the wing strut fitting with a new designed wing strut fitting. With this optional part replacement, in the repetitive inspection procedure the 1 100 FH interval is deleted so that only calendar defined intervals of inspections remain applicable. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. E:\FR\FM\27AUR1.SGM 27AUR1

Agencies

[Federal Register Volume 74, Number 165 (Thursday, August 27, 2009)]
[Rules and Regulations]
[Pages 43634-43636]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-20284]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0174; Directorate Identifier 2008-NE-03-AD; 
Amendment 39-15997; AD 2009-18-01]
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), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 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. This AD requires initial and repetitive eddy current 
inspections (ECIs) of certain part number (P/N) low-pressure (LP) 
turbine rear frames. 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.

DATES: This AD becomes effective October 1, 2009. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of October 1, 2009.

ADDRESSES: You can get the service information identified in this AD 
from CFM International, Technical Publications Department, 1 Neumann 
Way, Cincinnati, OH 45215; telephone (513) 552-2800; fax (513) 552-
2816.
    The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

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: The FAA proposed to amend 14 CFR part 39 
with a proposed AD and a supplemental proposed AD. The proposed AD 
applies 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, and the supplemental proposed AD applies 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; -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. We published the proposed AD in the Federal Register 
on May 7, 2008 (73 FR 25597). That action proposed to require initial 
and repetitive ECIs of certain P/N LP turbine rear frames. We published 
the supplemental proposed AD in the Federal Register on April 24, 2009 
(74 FR 18662). That action proposed to require initial and repetitive 
ECIs of those same P/N LP turbine rear frames, to add two additional P/
N LP turbine rear frames, to add 11 engine models to the applicability, 
and to clarify the commercial and corporate engines/LP turbine rear 
frames applicability.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://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 AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received.
    One commenter, CFM International, S.A. requests that we reference 
the latest European Aviation Safety Agency AD 2009-0110, dated May 7, 
2009, as it is up-to-date on P/Ns and engine models affected.
    We agree and changed the AD to reference AD 2009-0110.

[[Page 43635]]

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect 282 CFM56-5B series turbofan 
engines installed on airplanes of U.S. registry. We estimate that it 
will 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 $102,240. If all 282 LP 
turbine rear frames needed replacement, we estimate the total cost of 
the AD to U.S. operators to be $28,899,360. Our cost estimate is 
exclusive of possible warranty coverage.

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); and
    (3) 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.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. 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.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2009-18-01 CFM International, S.A.: Amendment 39-15997. Docket No. 
FAA-2008-0174; Directorate Identifier 2008-NE-03-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
1, 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.

[[Page 43636]]

Related Information

    (k) European Aviation Safety Agency AD 2009-0110, dated May 7, 
2009, 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.

Material Incorporated by Reference

    (m) You must use CFM International, S.A. SB No. CFM56-5B S/B 72-
0620, Revision 2, dated December 1, 2008 to perform the inspections 
required by this AD. The Director of the Federal Register approved 
the incorporation by reference of this service bulletin in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact CFM 
International, Technical Publications Department, 1 Neumann Way, 
Cincinnati, OH 45215; telephone (513) 552-2800; fax (513) 552-2816, 
for a copy of this service information. You may review copies at the 
FAA, New England Region, 12 New England Executive Park, Burlington, 
MA; or at the National Archives and Records Administration (NARA). 
For information on the availability of this material at NARA, call 
202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on August 17, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-20284 Filed 8-26-09; 8:45 am]
BILLING CODE 4910-13-P