[Federal Register Volume 75, Number 109 (Tuesday, June 8, 2010)]
[Rules and Regulations]
[Pages 32262-32263]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-13432]



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DEPARTMENT OF TRANSPORTATION



Federal Aviation Administration



14 CFR Part 39



[Docket No. FAA-2009-0606; Directorate Identifier 2009-NE-11-AD; 

Amendment 39-16324; AD 2010-12-03]

RIN 2120-AA64




Airworthiness Directives; CFM International, S.A. Models CFM56-3 

and -3B Turbofan Engines



AGENCY: Federal Aviation Administration (FAA), DOT.



ACTION: Final rule.



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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 

certain CFM International, S.A. models CFM56-3 and -3B turbofan 

engines. This AD requires initial and repetitive inspections for damage 

to the fan blades. This AD results from a report of a failed fan blade 

with severe out-of-limit wear on the underside of the blade platform 

where it contacts the damper. We are issuing this AD to prevent failure 

of multiple fan blades, which could result in an uncontained failure of 

the engine and damage to the airplane.



DATES: This AD becomes effective July 13, 2010. The Director of the 

Federal Register approved the incorporation by reference of certain 

publications listed in the regulations as of July 13, 2010.



ADDRESSES: You can get the service information identified in this AD 

from CFM International, S. A., Technical Publication 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: Antonio Cancelliere, Aerospace 

Engineer, Engine Certification Office, FAA, Engine & Propeller 

Directorate, 12 New England Executive Park, Burlington, MA 01803; e-

mail: [email protected]; telephone (781) 238-7751; fax (781) 

238-7199.



SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 

with a proposed AD. The proposed AD applies to certain CFM 

International, S.A. models CFM56-3 and -3B turbofan engines. We 

published the proposed AD in the Federal Register on July 23, 2009 (74 

FR 36420), and published a supplemental proposed AD in the Federal 

Register on April 1, 2010 (75 16361). Those actions proposed to require 

initial and repetitive inspections for damage to the fan blades.



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 previously responded to the comments 

received on the original proposed AD in the supplemental proposed AD. 

We have considered the one comment received on the supplemental 

proposed AD. The commenter supports the proposal.



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 as proposed.



Costs of Compliance



    We estimate that this AD will affect 50 engines installed on 

airplanes of U.S. registry. We also estimate that it will take about 8 

work-hours per engine to perform the AD actions, and that the average 

labor rate is $80 per work-hour. Required parts will cost about $38,000 

per engine. Based on these figures, we estimate the total cost of the 

AD to U.S. operators to be $1,932,000.



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:





2010-12-03 CFM International, S.A.: Amendment 39-16324. Docket No. 

FAA-2009-0606; Directorate Identifier 2009-NE-11-AD.



[[Page 32263]]



Effective Date



    (a) This airworthiness directive (AD) becomes effective July 13, 

2010.



Affected ADs



    (b) None.



Applicability



    (c) This AD applies to CFM International, S.A. models CFM56-3 

and -3B turbofan engines with 25 degrees midspan shroud fan blades, 

part numbers (P/Ns) 9527M99P08, 9527M99P09, 9527M99P10, 9527M99P11, 

1285M39P01, or fan blade pairs, P/Ns 335-088-901-0, 335-088-902-0, 

335-088-903-0, and 335-088-904-0 installed. These engines are 

installed on, but not limited to, Boeing 737 series airplanes.

    (d) CFM International, S.A. has added to the basic engine model 

number on the engine nameplate to identify minor variations in 

engine configuration, installation components, or reduced ratings 

peculiar to aircraft installation requirements.

    (e) Those engines marked on the engine data plate as CFM56-3-B1 

are included in this AD as CFM56-3 turbofan engines.

    (f) Those engines marked on the engine data plate as CFM56-3B-2 

are included in this AD as CFM56-3B turbofan engines.



Unsafe Condition



    (g) This AD results from a report of a failed fan blade with 

severe out-of-limit wear on the underside of the blade platform 

where it contacts the damper. We are issuing this AD to prevent 

failure of multiple fan blades, which could result in an uncontained 

failure of the engine and damage to the airplane.



Compliance



    (h) You are responsible for having the actions required by this 

AD performed within the compliance times specified, unless the 

actions have already been done.



Inspection for Wear



    (i) Within 900 cycles-in-service after the effective date of 

this AD, perform an on-wing or in-shop inspection of the fan blade 

and damper for wear. Use paragraphs 3.A.(1) through 3.A.(5) or 

paragraphs 3.B.(1) through 3.B.(5) respectively, of the 

Accomplishment Instructions of CFM International Service Bulletin 

(SB) No. CFM56-3/3B/3C S/B 72-1067, dated February 15, 2007.

    (j) If you find out-of-limit wear on at least one fan blade 

platform underside, perform the additional inspections and 

disposition the parts, as specified in paragraphs 3.A.(3) and 

3.A.(5) or paragraphs 3.B.(3) and 3.B.(5) respectively, of the 

Accomplishment Instructions of CFM International SB No. CFM56-3/3B/

3C S/B 72-1067, dated February 15, 2007.

    (k) Thereafter, within intervals not to exceed 3,000 cycles-

since-last inspection, perform an on-wing or in-shop inspection for 

wear. Use paragraphs 3.A.(1) through 3.A.(5) or paragraphs 3.B.(1) 

through 3.B.(5) respectively, of the Accomplishment Instructions of 

CFM International SB No. CFM56-3/3B/3C S/B 72-1067, dated February 

15, 2007.

    (l) If you find wear on at least one fan blade platform 

underside, perform additional inspections and disposition the parts, 

as specified in paragraphs 3.A.(3) and 3.A.(5) or paragraphs 3.B.(3) 

and 3.B.(5) respectively, of the Accomplishment Instructions of CFM 

International SB No. CFM56-3/3B/3C S/B 72-1067, dated February 15, 

2007.



Installation Prohibition



    (m) After the effective date of this AD, don't install any 25 

degrees midspan shroud fan blades, P/Ns 9527M99P08, 9527M99P09, 

9527M99P10, 9527M99P11, 1285M39P01, or fan blade pairs, P/Ns 335-

088-901-0, 335-088-902-0, 335-088-903-0, and 335-088-904-0, unless 

they have passed an inspection specified in paragraph 3. of the 

Accomplishment Instructions of CFM International SB No. CFM56-3/3B/

3C S/B 72-1067, dated February 15, 2007.



Optional Terminating Action



    (n) Replacing the 25 degrees midspan shroud fan blade set with a 

37 degrees midspan shroud fan blade set terminates the repetitive 

inspection requirements specified in paragraph (k) of this AD.



Alternative Methods of Compliance



    (o) 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



    (p) Contact Antonio Cancelliere, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 01803; e-mail: 

[email protected]; telephone (781) 238-7751; fax (781) 

238-7199, for more information about this AD.

    (q) European Aviation Safety Agency AD 2009-0036, dated February 

20, 2009, also addresses the subject of this AD.



Material Incorporated by Reference



    (r) You must use CFM International Service Bulletin No. CFM56-3/

3B/3C S/B 72-1067, dated February 15, 2007, to perform the 

inspections and parts dispositions 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, S. A., Technical Publication 

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 May 25, 2010.

Peter A. White,

Assistant Manager, Engine and Propeller Directorate, Aircraft 

Certification Service.

[FR Doc. 2010-13432 Filed 6-7-10; 8:45 am]

BILLING CODE 4910-13-P