AD 2016-02-04

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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: <a href="/cdn-cgi/l/email-protection#2544534c44514c4a4b0b4349404051565055554a57516542400b464a48"><span class="__cf_email__" data-cfemail="b5d4c3dcd4c1dcdadb9bd3d9d0d0c1c6c0c5c5dac7c1f5d2d09bd6dad8">[email&#160;protected]</span></a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating 
Docket No. FAA-2015-2983.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#d0bba9bcb5feb7a5a3a4b1b6a3bfbe90b6b1b1feb7bfa6"><span class="__cf_email__" data-cfemail="7e1507121b50190b0d0a1f180d11103e181f1f50191108">[email&#160;protected]</span></a>.

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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (80 FR 59672, October 2, 2015) for correcting the unsafe 
condition; and
    <bullet> 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//<a href="http://www.continentalsanantonio.com">www.continentalsanantonio.com</a> 
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: <a href="/cdn-cgi/l/email-protection#c2838c87ef8386ef838f8d8182a4a3a3eca5adb4"><span class="__cf_email__" data-cfemail="62232c274f23264f232f2d21220403034c050d14">[email&#160;protected]</span></a>.

(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: 
<a href="/cdn-cgi/l/email-protection#3c57455059125b494f485d5a4f53527c5a5d5d125b534a"><span class="__cf_email__" data-cfemail="2e4557424b00495b5d5a4f485d41406e484f4f00494158">[email&#160;protected]</span></a>.
    (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: <a href="/cdn-cgi/l/email-protection#8cedfae5edf8e5e3e2a2eae0e9e9f8fff9fcfce3fef8ccebe9a2efe3e1"><span class="__cf_email__" data-cfemail="7415021d15001d1b1a5a1218111100070104041b06003413115a171b19">[email&#160;protected]</span></a>.
    (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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    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]
 BILLING CODE 4910-13-P