[Federal Register Volume 81, Number 16 (Tuesday, January 26, 2016)]
[Rules and Regulations]
[Pages 4172-4174]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-01266]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-2983; Directorate Identifier 2015-NE-20-AD;
Amendment 39-18383; AD 2016-02-04]
RIN 2120-AA64
Airworthiness Directives; CFM International S.A. Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for certain
CFM International S.A. (CFM) CFM56-5B series turbofan engines. This AD
was prompted by a corrected lifing analysis by the engine manufacturer
that shows the need to identify an initial and repetitive inspection
threshold for certain part number (P/N) turbine rear frames (TRFs).
This AD requires initial and repetitive inspections of certain P/N TRFs
on the low-pressure turbine (LPT) frame assembly. We are issuing this
AD to prevent failure of the TRF on the LPT frame assembly, which could
lead to engine separation, damage to the engine, and damage to the
airplane.
DATES: This AD is effective March 1, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 1,
2016.
ADDRESSES: For service information identified in this AD, contact CFM
International Inc., Aviation Operations Center, 1 Neumann Way, M/D Room
285, Cincinnati, OH 45125; phone: 877-432-3272; fax: 877-432-3329;
email: [email protected]. You may view this service
information at the FAA, Engine & Propeller Directorate, 1200 District
Avenue, Burlington, MA. For information on the availability of this
material at the FAA, call 781-238-7125. It is also available on the
Internet at http://www.regulations.gov by searching for and locating
Docket No. FAA-2015-2983.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2983; or in person at the Docket Management Facility 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 address for the Docket Office (phone: 800-647-
5527) is Document 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: Kyle Gustafson, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200
District Avenue, Burlington, MA 01803; phone: 781-238-7183; fax: 781-
238-7199; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain CFM CFM56-5B series
turbofan engines. The NPRM published in the Federal Register on October
2, 2015 (80 FR 59672). The NPRM was prompted by a corrected lifing
analysis by the engine manufacturer that shows the need to identify an
initial and repetitive inspection threshold for certain P/N TRFs. The
NPRM proposed to require initial and repetitive inspections of certain
P/N TRFs on the LPT frame assembly. We are issuing this AD to correct
the unsafe condition on these products.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (80 FR 59672, October 2,
2015) or on the determination of the cost to the public.
Clarification to the Repetitive Inspection Requirements
We have revised the Compliance, paragraph (e) of this AD, to
clarify the repetitive inspection requirements for when the initial
inspection is done prior to the initial inspection threshold.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting this AD as proposed except for the
changes described above. We have determined that the changes described
above are minor changes, as they:
Are consistent with the intent that was proposed in the
NPRM (80 FR 59672, October 2, 2015) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (80 FR 59672, October 2, 2015).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed CFM Service Bulletin (SB) No. CFM56-5B S/B 72-0850,
dated December 19, 2012, which describes procedures for inspecting the
TRF. This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section of this
final rule.
Other Related Service Information
We also reviewed CFM SB No. CFM56-5B S/B 72-0308. Operators subject
to this AD are required to follow different initial and repetitive
inspection intervals depending on whether CFM SB No. CFM56-5B S/B 72-
0308 has been applied.
Costs of Compliance
We estimate that this AD affects about 94 engines installed on
airplanes of U.S. registry. We also estimate that it will take about 3
hours per engine to do the inspection. The average labor rate is $85
per hour. Based on these figures, we estimate the cost of this AD on
U.S. operators to be $23,970.
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
[[Page 4173]]
because it addresses an unsafe condition that is likely to exist or
develop on products identified in this rulemaking action.
Regulatory Findings
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),
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for parthttp//www.continentalsanantonio.com
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 (AD):
2016-02-04 CFM International S.A.: Amendment 39-18383; Docket
No. FAA-2015-2893; Directorate Identifier 2015-NE-20-AD.
(a) Effective Date
This AD is effective March 1, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to CFM International S.A. (CFM) CFM56-5B engines
with turbine rear frame (TRF), part number (P/N) 338-102-907-0 or P/
N 338-102-908-0, installed.
(d) Unsafe Condition
This AD was prompted by a corrected lifing analysis by the
engine manufacturer that shows the need for an initial and
repetitive inspection of certain P/N TRFs on the low-pressure
turbine (LPT) frame assembly. We are issuing this AD to prevent
failure of the TRF on the LPT frame assembly, which could lead to
engine separation, damage to the engine, and damage to the airplane.
(e) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(1) For Engines that have Applied CFM Service Bulletin (SB) No.
CFM56-5B S/B 72-0308:
(i) Prior to accumulating 25,000 cycles since new (CSN) on the
TRF of the LPT frame assembly or within 150 cycles after the
effective date of this AD, whichever occurs later, perform an
initial eddy current inspection (ECI) or a fluorescent penetrant
inspection (FPI) of the TRF mount struts on the LPT assembly.
(ii) For engines with unknown CSN on the TRF of the LPT frame
assembly, perform the initial inspection required by this AD within
150 cycles-in-service (CIS) after the effective date of this AD.
(iii) Use paragraph 3.B. in the Accomplishment Instructions of
CFM SB No. CFM56-5B S/B 72-0850, dated December 19, 2012, to do the
ECI and paragraph 3.C. in the Accomplishment Instructions of CFM SB
No. CFM56-5B S/B 72-0850, to do the FPI. Do not include TRF mount
strut crack lengths towards the cumulative crack length after the
cracks are repaired.
(iv) If no cracks are found on any of the three TRF mount
struts, repeat the inspection within 1,670 cycles since last
inspection (CSLI) or prior to accumulating 25,000 CSN on the TRF of
the LPT assembly, whichever occurs later.
(v) If the cumulative length of all cracks found at any TRF
mount strut location is less than 0.20 inches, repeat the inspection
within 1,670 cycles CSLI.
(vi) If the cumulative length of cracks found at any TRF mount
strut location is greater than or equal to 0.20 inches, but less
than 0.25 inches, repeat the inspection within 280 CSLI.
(vii) If the cumulative length of cracks found at any TRF mount
strut location is 0.25 inches or greater, replace the TRF with a
part eligible for installation before further flight.
(2) For Engines that have Not Applied CFM SB No. CFM56-5B S/B
72-0308:
(i) Prior to accumulating 32,000 CSN on the TRF of the LPT frame
assembly or within 150 cycles after the effective date of this AD,
whichever occurs later, perform an initial ECI or FPI of the TRF
mount struts on the LPT frame assembly.
(ii) For engines with unknown CSN on the TRF of the LPT frame
assembly, perform the initial inspection required by this AD within
150 CIS after the effective date of this AD.
(iii) Use paragraph 3.B. in the Accomplishment Instructions of
CFM SB No. CFM56-5B S/B 72-0850, dated December 19, 2012, to do the
ECI and paragraph 3.C. in the Accomplishment Instructions of CFM SB
No. CFM56-5B S/B 72-0850, to do the FPI. Do not include TRF mount
strut crack lengths towards the cumulative crack length after the
cracks are repaired.
(iv) If no cracks are found on any of the three TRF mount
struts, repeat the inspection within 2,500 CSLI or prior to
accumulating 32,000 CSN on the TRF of the LPT assembly, whichever
occurs later.
(v) If the cumulative length of cracks found at any TRF mount
strut location is less than 0.20 inches, repeat the inspection
within 2,500 CSLI.
(vi) If the cumulative length of cracks found at any TRF mount
strut location is greater than or equal to 0.20 inches and less than
0.25 inches, repeat the inspection within 370 CSLI.
(vii) If the cumulative length of cracks found at any TRF mount
strut location is 0.25 inches or greater, replace the TRF with a
part eligible for installation before further flight.
(f) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, FAA, may approve AMOCs
for this AD. Use the procedures found in 14 CFR 39.19 to make your
request. You may email your request to: [email protected].
(g) Related Information
(1) For more information about this AD, contact Kyle Gustafson,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803;
phone: 781-238-7183; fax: 781-238-7199; email:
[email protected].
(2) CFM SB No. CFM56-5B S/B 72-0308, which is not incorporated
by reference in this AD, can be obtained from CFM, using the contact
information in paragraph (h)(4) of this AD.
(h) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
March 1, 2016.
(i) CFM International S. A. (CFM) Service Bulletin No. CFM56-5B
S/B 72-0850, dated December 19, 2012.
(ii) Reserved.
(4) For CFM service information identified in this AD, contact
CFM International Inc., Aviation Operations Center, 1 Neumann Way,
M/D Room 285, Cincinnati, OH 45125; phone: 877-432-3272; fax: 877-
432-3329; email: [email protected].
(5) You may view this service information at the FAA, Engine &
Propeller Directorate, 1200 District Avenue, Burlington, MA. For
information on the availability of this material at the FAA, call
781-238-7125.
(6) You may view this service information at the National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, call
[[Page 4174]]
202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on January 14, 2016.
Gaetano Sciortino,
Acting Directorate Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2016-01266 Filed 1-25-16; 8:45 am]
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