81_FR_26761 81 FR 26675 - Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

81 FR 26675 - Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 86 (May 4, 2016)

Page Range26675-26677
FR Document2016-10279

We are adopting a new airworthiness directive (AD) for certain Turbomeca S.A. Astazou XIV B and H turboshaft engines. This AD requires a one-time inspection of the front surface of the 3rd stage turbine for a groove. This AD was prompted by a report of a crack on the 3rd stage turbine wheel. We are issuing this AD to prevent cracks in the 3rd stage turbine wheel, failure of the engine, in-flight shutdown, and loss of control of the helicopter.

Federal Register, Volume 81 Issue 86 (Wednesday, May 4, 2016) 
[Federal Register Volume 81, Number 86 (Wednesday, May 4, 2016)]
[Rules and Regulations]
[Pages 26675-26677]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-10279]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-7490; Directorate Identifier 2015-NE-40-AD; 
Amendment 39-18500; AD 2016-09-02]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Turboshaft 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 
Turbomeca S.A. Astazou XIV B and H turboshaft engines. This AD requires 
a one-time inspection of the front surface of the 3rd stage turbine for 
a groove. This AD was prompted by a report of a crack on the 3rd stage 
turbine wheel. We are issuing this AD to prevent cracks in the 3rd 
stage turbine wheel, failure of the engine, in-flight shutdown, and 
loss of control of the helicopter.

DATES: This AD becomes effective June 8, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 8, 
2016.

ADDRESSES: For service information identified in this final rule, 
contact Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 
00; fax: 33 (0)5 59 74 45 15. 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-2015-7490.

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-
7490; 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 mandatory continuing airworthiness information 
(MCAI), 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: Wego Wang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7134; 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 the specified products. The

[[Page 26676]]

NPRM was published in the Federal Register on February 2, 2016 (81 FR 
5395). The NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    During the overhaul of an ASTAZOU XIV engine, a crack was 
detected on the front face of the third stage turbine wheel between 
two balancing lugs. The cause of the crack is probably linked to a 
geometric singularity, likely caused by the transformation operation 
aimed at introducing expansion slots between the blades during 
embodiment of Turbomeca mod AB 173. Although there is only one known 
case of this type of crack, and although it was detected, the 
possibility exists that additional parts have the same geometric 
singularity.
    This condition, if not detected and corrected, may lead to 
failure of a turbine blade and its associated piece of rim, possibly 
resulting in an uncommanded in-flight shut-down and/or release of 
high energy debris.

    You may obtain further information by examining the MCAI in the AD 
docket on the Internet at http://www.regulations.gov by searching for 
and locating Docket No. FAA-2015-7490.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (81 FR 5395, February 2, 
2016).

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed.

Related Service Information Under 1 CFR Part 51

    Turbomeca S.A. has issued Service Bulletin (SB) No. 283 72 0811, 
Version A, dated August 25, 2015. The SB describes procedures for 
inspection of the 3rd stage turbine wheel. 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.

Costs of Compliance

    We estimate that this AD affects 9 engines installed on helicopters 
of U.S. registry. We also estimate that it will take about 5 hours per 
engine to comply with this AD. 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 $3,825.

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 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the 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 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 (AD):

2016-09-02 Turbomeca S.A.: Amendment 39-18500; Docket No. FAA-2015-
7490; Directorate Identifier 2015-NE-40-AD.

(a) Effective Date

    This AD becomes effective June 8, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Astazou XIV B and XIV H turboshaft 
engines with 3rd stage turbine wheel, part number (P/N) 0 265 25 700 
0 or P/N 0 265 25 706 0, installed, if the engine incorporates 
Turbomeca modification AB-173 or AB-208.

(d) Reason

    This AD was prompted by a report of a crack on the 3rd stage 
turbine wheel. We are issuing this AD to prevent cracks in the 3rd 
stage turbine wheel, failure of the engine, in-flight shutdown, and 
loss of control of the helicopter.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) At the next piece part exposure of the 3rd stage turbine 
wheel or within 1,000 engine hours after the effective date of this 
AD whichever comes first, perform a one-time inspection for a groove 
on the front surface of the 3rd stage turbine wheel. Use 
Accomplishment Instructions, paragraph 4.4.2, of Turbomeca S.A. 
Service Bulletin (SB) No. 283 72 0811, Version A, dated August 25, 
2015 to perform the inspection.
    (2) If the 3rd stage turbine wheel passes inspection required by 
paragraph (e)(1) of this AD, no further action is required.
    (3) If the 3rd stage turbine wheel fails inspection required by 
paragraph (e)(1) of this AD, remove the part and replace with a part 
eligible for installation.

(f) Installation Prohibition

    After the effective date of this AD, do not install any 3rd 
stage turbine wheel, P/N 0 265 25 700 0 or P/N 0 265 25 706 0, 
unless it was inspected per the Accomplishment Instructions, 
paragraph 4.4.2, of Turbomeca S.A. SB No. 283 72 0811, Version A, 
dated August 25, 2015.

(g) 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].

(h) Related Information

    (1) For more information about this AD, contact Wego Wang, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7134; fax: 781-238-7199; email: [email protected].
    (2) Refer to MCAI European Aviation Safety Agency AD 2015-0223, 
dated November 16, 2015, for more information. You may examine the 
MCAI in the AD

[[Page 26677]]

docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-7490-0001.

(i) 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.
    (i) Turbomeca S.A. Service Bulletin No. 283 72 0811, Version A, 
dated August 25, 2015.
    (ii) Reserved.
    (3) For Turbomeca S.A. service information identified in this 
AD, contact Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 
74 40 00; fax: 33 (0)5 59 74 45 15.
    (4) You may view this service information at FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.
    (5) 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 202-741-6030, or go to: 
http://www.archives.gov/federal-register/cfr/ibr-locations.html.


    Issued in Burlington, Massachusetts, on April 21, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-10279 Filed 5-3-16; 8:45 am]
 BILLING CODE 4910-13-P

Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations 26675 717–55A0012, dated June 12, 2015, except as ACO, to make those findings. To be We are adopting a new SUMMARY: required by paragraph (i)(2) of this AD. Do all approved, the repair method, modification airworthiness directive (AD) for certain applicable related investigative and deviation, or alteration deviation must meet Turbomeca S.A. Astazou XIV B and H corrective actions before further flight. the certification basis of the airplane, and the Repeat the applicable inspection thereafter at approval must specifically refer to this AD. turboshaft engines. This AD requires a the intervals specified in paragraph 1.E., one-time inspection of the front surface ‘‘Compliance,’’ of Boeing Alert Service (l) Related Information of the 3rd stage turbine for a groove. Bulletin 717–55A0012, dated June 12, 2015. For more information about this AD, This AD was prompted by a report of a (1) Do detailed inspections for any loose contact Eric Schrieber, Aerospace Engineer, crack on the 3rd stage turbine wheel. and missing fasteners of the vertical stabilizer Airframe Branch, ANM–120L, FAA, Los We are issuing this AD to prevent cracks leading edge as specified in ‘‘Part 4’’ of Angeles ACO, 3960 Paramount Boulevard, in the 3rd stage turbine wheel, failure of Boeing Alert Service Bulletin 717–55A0012, Lakewood, CA 90712–4137; phone: 562–627– the engine, in-flight shutdown, and loss dated June 12, 2015. 5348; fax: 562–627–5210; email: (2) Do eddy current testing high frequency Eric.Schrieber@faa.gov. of control of the helicopter. (ETHF) and radiographic testing (RT) DATES: This AD becomes effective June (m) Material Incorporated by Reference inspections for any crack of the vertical 8, 2016. stabilizer spar cap as specified in ‘‘Part 2’’ of (1) The Director of the Federal Register The Director of the Federal Register Boeing Alert Service Bulletin 717–55A0012, approved the incorporation by reference approved the incorporation by reference dated June 12, 2015; or do ETHF inspections (IBR) of the service information listed in this of a certain publication listed in this AD for any crack of the vertical stabilizer spar paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. as of June 8, 2016. cap as specified in ‘‘Part 3’’ of Boeing Alert Service Bulletin 717–55A0012, dated June (2) You must use this service information ADDRESSES: For service information 12, 2015. as applicable to do the actions required by identified in this final rule, contact this AD, unless the AD specifies otherwise. Turbomeca S.A., 40220 Tarnos, France; (i) Exceptions to the Service Information (i) Boeing Alert Service Bulletin 717– phone: 33 (0)5 59 74 40 00; fax: 33 (0)5 (1) Where Boeing Alert Service Bulletin 55A0012, dated June 12, 2015. 59 74 45 15. You may view this service 717–55A0012, dated June 12, 2015 specifies (ii) Reserved. information at the FAA, Engine & a compliance time ‘‘after the original issue (3) For Boeing service information date of this service bulletin,’’ this AD identified in this AD, contact Boeing Propeller Directorate, 1200 District requires compliance within the specified Commercial Airplanes, Attention: Data & Avenue, Burlington, MA. For compliance time after the effective date of Services Management, 3855 Lakewood information on the availability of this this AD. Boulevard, MC D800–0019, Long Beach, CA material at the FAA, call 781–238–7125. (2) If any crack is found during any 90846–0001; telephone: 206–544–5000, It is also available on the Internet at inspection required by this AD, and Boeing extension 2; fax: 206–766–5683; Internet: http://www.regulations.gov by searching Alert Service Bulletin 717–55A0012, dated https://www.myboeingfleet.com. for and locating Docket No. FAA–2015– June 12, 2015, specifies to contact Boeing for (4) You may view this service information 7490. appropriate action: Before further flight, at the FAA, Transport Airplane Directorate, repair using a method approved in 1601 Lind Avenue SW., Renton, WA. For Examining the AD Docket accordance with the procedures specified in information on the availability of this paragraph (k) of this AD. material at the FAA, call 425–227–1221. You may examine the AD docket on (5) You may view this service information the Internet at http:// (j) Credit for Previous Actions that is incorporated by reference at the www.regulations.gov by searching for This paragraph provides credit for the National Archives and Records and locating Docket No. FAA–2015– initial inspection specified in paragraph (g) Administration (NARA). For information on 7490; or in person at the Docket of this AD, if that inspection was performed the availability of this material at NARA, call Management Facility between 9 a.m. before the effective date of this AD using 202–741–6030, or go to: http:// and 5 p.m., Monday through Friday, Boeing MOM–MOM–14–0437–01B(R1), www.archives.gov/federal-register/cfr/ibr- dated July 3, 2014, which is not incorporated locations.html. except Federal holidays. The AD docket by reference in this AD. contains this AD, the mandatory Issued in Renton, Washington, on April 20, continuing airworthiness information (k) Alternative Methods of Compliance 2016. (MCAI), the regulatory evaluation, any (AMOCs) John P. Piccola, Jr., comments received, and other (1) The Manager, Los Angeles Aircraft Acting Manager, Transport Airplane information. The address for the Docket Certification Office (ACO), FAA, has the Directorate, Aircraft Certification Service. Office (phone: 800–647–5527) is authority to approve AMOCs for this AD, if [FR Doc. 2016–10160 Filed 5–3–16; 8:45 am] requested using the procedures found in 14 Document Management Facility, U.S. CFR 39.19. In accordance with 14 CFR 39.19, BILLING CODE 4910–13–P Department of Transportation, Docket send your request to your principal inspector Operations, M–30, West Building or local Flight Standards District Office, as Ground Floor, Room W12–140, 1200 appropriate. If sending information directly DEPARTMENT OF TRANSPORTATION New Jersey Avenue SE., Washington, to the manager of the ACO, send it to the DC 20590. attention of the person identified in Federal Aviation Administration FOR FURTHER INFORMATION CONTACT: paragraph (l) of this AD. Information may be emailed to: 9-ANM-LAACO-AMOC- 14 CFR Part 39 Wego Wang, Aerospace Engineer, Requests@faa.gov. Engine Certification Office, FAA, Engine (2) Before using any approved AMOC, [Docket No. FAA–2015–7490; Directorate & Propeller Directorate, 1200 District notify your appropriate principal inspector, Identifier 2015–NE–40–AD; Amendment 39– Avenue, Burlington, MA 01803; phone: or lacking a principal inspector, the manager 18500; AD 2016–09–02] 781–238–7134; fax: 781–238–7199; asabaliauskas on DSK3SPTVN1PROD with RULES of the local flight standards district office/ RIN 2120–AA64 email: wego.wang@faa.gov. certificate holding district office. SUPPLEMENTARY INFORMATION: (3) An AMOC that provides an acceptable Airworthiness Directives; Turbomeca level of safety may be used for any repair, S.A. Turboshaft Engines Discussion modification, or alteration required by this AD if it is approved by the Boeing AGENCY: Federal Aviation We issued a notice of proposed Commercial Airplanes Organization Administration (FAA), DOT. rulemaking (NPRM) to amend 14 CFR Designation Authorization (ODA) that has part 39 by adding an AD that would ACTION: Final rule. been authorized by the Manager, Los Angeles apply to the specified products. The VerDate Sep<11>2014 17:12 May 03, 2016 Jkt 238001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\04MYR1.SGM 04MYR1

26676 Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations NPRM was published in the Federal section 106, describes the authority of 2016–09–02 Turbomeca S.A.: Amendment Register on February 2, 2016 (81 FR the FAA Administrator. ‘‘Subtitle VII: 39–18500; Docket No. FAA–2015–7490; 5395). The NPRM proposed to correct Aviation Programs,’’ describes in more Directorate Identifier 2015–NE–40–AD. an unsafe condition for the specified detail the scope of the Agency’s (a) Effective Date products. The MCAI states: authority. This AD becomes effective June 8, 2016. During the overhaul of an ASTAZOU XIV We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, (b) Affected ADs engine, a crack was detected on the front face of the third stage turbine wheel between two Part A, Subpart III, Section 44701: None. balancing lugs. The cause of the crack is General requirements.’’ Under that (c) Applicability probably linked to a geometric singularity, section, Congress charges the FAA with This AD applies to all Astazou XIV B and likely caused by the transformation operation promoting safe flight of civil aircraft in aimed at introducing expansion slots XIV H turboshaft engines with 3rd stage air commerce by prescribing regulations turbine wheel, part number (P/N) 0 265 25 between the blades during embodiment of for practices, methods, and procedures 700 0 or P/N 0 265 25 706 0, installed, if the Turbomeca mod AB 173. Although there is the Administrator finds necessary for engine incorporates Turbomeca modification only one known case of this type of crack, safety in air commerce. This regulation AB–173 or AB–208. and although it was detected, the possibility exists that additional parts have the same is within the scope of that authority (d) Reason geometric singularity. because it addresses an unsafe condition that is likely to exist or develop on This AD was prompted by a report of a This condition, if not detected and crack on the 3rd stage turbine wheel. We are corrected, may lead to failure of a turbine products identified in this rulemaking issuing this AD to prevent cracks in the 3rd blade and its associated piece of rim, action. stage turbine wheel, failure of the engine, in- possibly resulting in an uncommanded in- flight shutdown, and loss of control of the flight shut-down and/or release of high Regulatory Findings helicopter. energy debris. We determined that this AD will not have federalism implications under (e) Actions and Compliance You may obtain further information by examining the MCAI in the AD Executive Order 13132. This AD will Comply with this AD within the not have a substantial direct effect on compliance times specified, unless already docket on the Internet at http:// done. www.regulations.gov by searching for the States, on the relationship between the national Government and the States, (1) At the next piece part exposure of the and locating Docket No. FAA–2015– 3rd stage turbine wheel or within 1,000 7490. or on the distribution of power and engine hours after the effective date of this responsibilities among the various AD whichever comes first, perform a one- Comments levels of government. time inspection for a groove on the front We gave the public the opportunity to For the reasons discussed above, I surface of the 3rd stage turbine wheel. Use participate in developing this AD. We certify this AD: Accomplishment Instructions, paragraph received no comments on the NPRM (81 (1) Is not a ‘‘significant regulatory 4.4.2, of Turbomeca S.A. Service Bulletin FR 5395, February 2, 2016). action’’ under Executive Order 12866, (SB) No. 283 72 0811, Version A, dated (2) Is not a ‘‘significant rule’’ under August 25, 2015 to perform the inspection. Conclusion the DOT Regulatory Policies and (2) If the 3rd stage turbine wheel passes Procedures (44 FR 11034, February 26, inspection required by paragraph (e)(1) of We reviewed the available data and this AD, no further action is required. determined that air safety and the 1979), (3) Will not affect intrastate aviation (3) If the 3rd stage turbine wheel fails public interest require adopting this AD inspection required by paragraph (e)(1) of in Alaska to the extent that it justifies as proposed. this AD, remove the part and replace with a making a regulatory distinction, and part eligible for installation. Related Service Information Under 1 (4) Will not have a significant CFR Part 51 economic impact, positive or negative, (f) Installation Prohibition on a substantial number of small entities After the effective date of this AD, do not Turbomeca S.A. has issued Service under the criteria of the Regulatory install any 3rd stage turbine wheel, P/N 0 265 Bulletin (SB) No. 283 72 0811, Version Flexibility Act. 25 700 0 or P/N 0 265 25 706 0, unless it was A, dated August 25, 2015. The SB inspected per the Accomplishment describes procedures for inspection of List of Subjects in 14 CFR Part 39 Instructions, paragraph 4.4.2, of Turbomeca the 3rd stage turbine wheel. This service Air transportation, Aircraft, Aviation S.A. SB No. 283 72 0811, Version A, dated information is reasonably available safety, Incorporation by reference, August 25, 2015. because the interested parties have Safety. (g) Alternative Methods of Compliance access to it through their normal course (AMOCs) of business or by the means identified Adoption of the Amendment The Manager, Engine Certification Office, in the ADDRESSES section. Accordingly, under the authority FAA, may approve AMOCs for this AD. Use Costs of Compliance delegated to me by the Administrator, the procedures found in 14 CFR 39.19 to the FAA amends 14 CFR part 39 as make your request. You may email your We estimate that this AD affects 9 follows: request to: ANE-AD-AMOC@faa.gov. engines installed on helicopters of U.S. registry. We also estimate that it will PART 39—AIRWORTHINESS (h) Related Information take about 5 hours per engine to comply DIRECTIVES (1) For more information about this AD, with this AD. The average labor rate is contact Wego Wang, Aerospace Engineer, asabaliauskas on DSK3SPTVN1PROD with RULES $85 per hour. Based on these figures, we ■ 1. The authority citation for part 39 Engine Certification Office, FAA, Engine & continues to read as follows: Propeller Directorate, 1200 District Avenue, estimate the cost of this AD on U.S. Burlington, MA 01803; phone: 781–238– operators to be $3,825. Authority: 49 U.S.C. 106(g), 40113, 44701. 7134; fax: 781–238–7199; email: Authority for This Rulemaking § 39.13 [Amended] wego.wang@faa.gov. (2) Refer to MCAI European Aviation Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by adding Safety Agency AD 2015–0223, dated specifies the FAA’s authority to issue the following new airworthiness November 16, 2015, for more information. rules on aviation safety. Subtitle I, directive (AD): You may examine the MCAI in the AD VerDate Sep<11>2014 17:12 May 03, 2016 Jkt 238001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\04MYR1.SGM 04MYR1

Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations 26677 docket on the Internet at http:// and corrective action if necessary. AD except Federal holidays. The AD docket www.regulations.gov/ 2004–19–11 also provided optional contains this AD, the regulatory #!documentDetail;D=FAA-2015-7490-0001. terminating action for the repetitive evaluation, any comments received, and (i) Material Incorporated by Reference inspections. This new AD retains the other information. The address for the (1) The Director of the Federal Register requirements of AD 2004–19–11, and Docket Office (telephone 800–647–5527) approved the incorporation by reference requires the previously optional is Docket Management Facility, U.S. (IBR) of the service information listed in this terminating action. This AD was Department of Transportation, Docket paragraph under 5 U.S.C. 552(a) and 1 CFR prompted by a determination that the Operations, M–30, West Building part 51. previously optional terminating action Ground Floor, Room W12–140, 1200 (2) You must use this service information is necessary to address the unsafe New Jersey Avenue SE., Washington, as applicable to do the actions required by condition. We are issuing this AD to DC 20590. this AD, unless the AD specifies otherwise. prevent fatigue cracking of the inner FOR FURTHER INFORMATION CONTACT: (i) Turbomeca S.A. Service Bulletin No. 283 72 0811, Version A, dated August 25, rear spar, which may lead to reduced Sanjay Ralhan, Aerospace Engineer, 2015. structural integrity of the wing and the International Branch, ANM–116, (ii) Reserved. MLG. Transport Airplane Directorate, FAA, (3) For Turbomeca S.A. service information DATES: This AD becomes effective June 1601 Lind Avenue SW., Renton, WA identified in this AD, contact Turbomeca 8, 2016. 98057–3356; telephone 425–227–1405; S.A., 40220 Tarnos, France; phone: 33 (0)5 59 The Director of the Federal Register fax 425–227–1149. 74 40 00; fax: 33 (0)5 59 74 45 15. approved the incorporation by reference SUPPLEMENTARY INFORMATION: (4) You may view this service information at FAA, Engine & Propeller Directorate, 1200 of a certain publication listed in this AD Discussion District Avenue, Burlington, MA. For as of June 8, 2016. The Director of the Federal Register We issued a notice of proposed information on the availability of this material at the FAA, call 781–238–7125. approved the incorporation by reference rulemaking (NPRM) to amend 14 CFR (5) You may view this service information of a certain publication listed in this AD part 39 to supersede AD 2004–19–11, at the National Archives and Records as of November 5, 2004 (69 FR 58828, Amendment 39–13805 (69 FR 58828, Administration (NARA). For information on October 1, 2004). October 1, 2004) (‘‘AD 2004–19–11’’). the availability of this material at NARA, call The Director of the Federal Register AD 2004–19–11 applied to certain 202–741–6030, or go to: http:// approved the incorporation by reference Airbus Model 320 series airplanes. The www.archives.gov/federal-register/cfr/ibr- NPRM published in the Federal of certain other publications listed in locations.html. Register on November 27, 2015 (80 FR this AD as of June 30, 2000 (65 FR Issued in Burlington, Massachusetts, on 34069, May 26, 2000). 74058) (‘‘the NPRM’’). The NPRM was April 21, 2016. The Director of the Federal Register prompted by a determination that the Colleen M. D’Alessandro, approved the incorporation by reference previously optional terminating action of a certain publication listed in this AD is necessary to address the unsafe Manager, Engine & Propeller Directorate, Aircraft Certification Service. as of February 14, 1994 (59 FR 1903, condition. The NPRM proposed to January 13, 1994). retain the requirements of AD 2004–19– [FR Doc. 2016–10279 Filed 5–3–16; 8:45 am] The Director of the Federal Register 11, and requires the previously optional BILLING CODE 4910–13–P approved the incorporation by reference terminating action. We are issuing this of a certain other publication listed in AD to prevent fatigue cracking of the DEPARTMENT OF TRANSPORTATION this AD as of June 11, 1993 (58 FR inner rear spar, which may lead to 27923, May 12, 1993). reduced structural integrity of the wing Federal Aviation Administration ADDRESSES: For service information and the MLG. The European Aviation Safety Agency identified in this final rule, contact 14 CFR Part 39 (EASA), which is the Technical Agent Airbus, Airworthiness Office—EIAS, 1 for the Member States of the European [Docket No. FAA–2015–5811; Directorate Rond Point Maurice Bellonte, 31707 Union, has issued EASA Airworthiness Identifier 2014–NM–158–AD; Amendment Blagnac Cedex, France; telephone +33 5 Directive 2014–0169, dated July 17, 39–18489; AD 2016–08–13] 61 93 36 96; fax +33 5 61 93 44 51; email 2014, corrected July 22, 2014 (referred account.airworth-eas@airbus.com; RIN 2120–AA64 to after this as the Mandatory Internet http://www.airbus.com. You Continuing Airworthiness Information, Airworthiness Directives; Airbus may view this referenced service or ‘‘the MCAI’’), to correct an unsafe Airplanes information at the FAA, Transport condition on certain Airbus Model 320 Airplane Directorate, 1601 Lind Avenue AGENCY: Federal Aviation series airplanes. The MCAI states: SW., Renton, WA. For information on Administration (FAA), Department of the availability of this material at the During centre fuselage certification full Transportation (DOT). FAA, call 425–227–1221. It is also scale fatigue test, cracks were found on the inner rear spar at holes position 52 on the ACTION: Final rule. available on the Internet at http:// right hand wing due to fatigue aspects. www.regulations.gov by searching for This condition, if not detected and SUMMARY: We are superseding and locating Docket No. FAA–2015– corrected, could affect the structural integrity Airworthiness Directive (AD) 2004–19– 5811. of the aeroplane. 11 for certain Airbus Model A320 series To prevent such cracks, Airbus developed Examining the AD Docket asabaliauskas on DSK3SPTVN1PROD with RULES airplanes. AD 2004–19–11 required modifications, which were introduced in modification of the inner rear spar web You may examine the AD docket on production and in service through several of the wing, cold expansion of the the Internet at http:// Airbus Service Bulletins (SB). attachment holes of the forward pintle www.regulations.gov by searching for DGAC France issued * * * [an earlier AD], which was subsequently superseded by fitting and the actuating cylinder and locating Docket No. FAA–2015– [DGAC] AD 2001–249 [which corresponds anchorage of the main landing gear 5811; or in person at the Docket with FAA AD 2004–19–11, Amendment 39– (MLG), repetitive ultrasonic inspections Management Facility between 9 a.m. 13805 (69 FR 58828, October 1, 2004)], to for cracking of the rear spar of the wing, and 5 p.m., Monday through Friday, require modification of the rear spar on some VerDate Sep<11>2014 17:12 May 03, 2016 Jkt 238001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\04MYR1.SGM 04MYR1


Document Created: 2016-05-04 01:23:07
Document Modified: 2016-05-04 01:23:07
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal rule.
DatesThis AD becomes effective June 8, 2016.
ContactWego Wang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7134; fax: 781- 238-7199; email: [email protected]
FR Citation81 FR 26675 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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