Document ID: FAA-2009-0606-0005
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: CFM International, S.A Models CFM56-3 and -3B Turbofan Engines
Posted Date: 2010-06-08T04:00Z

[Federal Register: June 8, 2010 (Volume 75, Number 109)]
[Rules and Regulations]               
[Page 32262-32263]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08jn10-5]                         

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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: antonio.cancelliere@faa.gov; 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: 
antonio.cancelliere@faa.gov; 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