81 FR 4167 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 16 (January 26, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 16 (January 26, 2016)
| Page Range | 4167-4169 | |
| FR Document | 2016-01108 |
[Federal Register Volume 81, Number 16 (Tuesday, January 26, 2016)] [Rules and Regulations] [Pages 4167-4169] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-01108] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1429; Directorate Identifier 2014-NM-246-AD; Amendment 39-18382; AD 2016-02-03] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A319-113, A319-114, A320-211, and A320-212 airplanes. This AD was prompted by a report that the aft mount pylon bolts of the CFM56-5 engines may have been installed using the wrong torque values. This AD requires identification of engines that were installed using the wrong torque values and re-torque of the four aft mount pylon bolts of those engines. We are issuing this AD to detect and correct improper torque of the aft mount pylon bolts, which, if combined with any maintenance damage, could lead to aft engine mount failure, possibly resulting in engine detachment and consequent reduced control of the airplane. DATES: This AD becomes effective March 1, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 1, 2016. ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-1429; or in person at the Docket 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. For service information identified in this final rule, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 1429. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1405; fax: 425-227-1149. Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A319- 113, A319-114, A320-211, and A320-212 airplanes. The NPRM published in the Federal Register on June 15, 2015 (80 FR 34101). The NPRM was prompted by a report that the aft mount pylon bolts of the CFM56-5 engines may have been installed using the [[Page 4168]] wrong torque values. The NPRM proposed to require identification of engines that were installed using the wrong torque values and re-torque of the four aft mount pylon bolts of those engines. We are issuing this AD to detect and correct improper torque of the aft mount pylon bolts, which, if combined with any maintenance damage, could lead to aft engine mount failure, possibly resulting in engine detachment and consequent reduced control of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2014-0258, dated November 28, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A319-113, A319- 114, A320-211, and A320-212 airplanes. The MCAI states: In the Aircraft Maintenance Manual (AMM) revision dated May 2013, a wrong torque value was added in AMM task 71-00-00-400-040- A01 ``Installation of the power plant with Engine Positioner TWW75E''. Temporary Revisions (TR) dated March 2014 were published by Airbus to correct the information and with AMM revision dated May 2014, Task 71-00-00-400-040-A01 was corrected to include the correct values. Notwithstanding those actions, static and fatigue analyses have concluded that this undertorque scenario negatively impacts the assembly performance, reducing the aft mount capability. This condition, if not corrected and if combined with any maintenance damage, could lead to aft engine mount failure, possibly resulting in engine detachment and consequent reduced control of the aeroplane. For the reasons described above, this [EASA] AD requires identification of CFM56-5 engines (those listed in TCDS EASA.E.067 [http://easa.europa.eu/document-library/typecertificates/easae067]) that were installed by using the wrong torque data of AMM instructions mentioned above and re-torque of the four aft mount pylon bolts of those engines. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-1429-0002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM (80 FR 34101, June 15, 2015) and the FAA's response to each comment. Request to Revise Paragraph (h) of the Proposed AD (80 FR 34101, June 15, 2015) Delta Air Lines, Inc. (DAL) requested that we revise paragraph (h) of the proposed AD (80 FR 34101, June 15, 2015), by revising the wording to refer to the Aircraft Maintenance Manual (AMM), dated May 2013 instead of Airbus Service Bulletin A320-71-1063, including Appendix 01, dated August 13, 2014. DAL pointed out that paragraph (h) of the proposed AD required engine installation in accordance with Airbus Service Bulletin A320-71-1063, including Appendix 01, dated August 13, 2014. DAL also mentioned that Airbus Service Bulletin A320- 71-1063, including Appendix 01, dated August 13, 2014, only has requirements for inspection and re-torque of the aft engine mount pylon bolts. We agree to revise paragraph (h) of this AD because Airbus Service Bulletin A320-71-1063, including Appendix 01, dated August 13, 2014, does not contain installation instructions. We have revised paragraph (h) of this AD to specify that no person may install a CFM56-5 engine, on any airplane, unless accomplishing the actions specified in paragraph (g) of this AD. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD with the change described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM (80 FR 34101, June 15, 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 34101, June 15, 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 Airbus has issued Airbus Service Bulletin A320-71-1063, including Appendix 01, dated August 13, 2014. The service information describes procedures to detect and correct improper torque of the aft mount pylon bolts. 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 126 airplanes of U.S. registry. We also estimate that it will take about 2 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $21,420, or $170 per product. 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 that 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; 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. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-1429; 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 [[Page 4169]] information. The street address for the Docket Operations office (telephone: 800-647-5527) is in the ADDRESSES section. 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): 2016-02-03 Airbus: Amendment 39-18382. Docket No. FAA-2015-1429; Directorate Identifier 2014-NM-246-AD. (a) Effective Date This AD becomes effective March 1, 2016. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A319-113 and -114 airplanes. (2) Airbus Model A320-211 and -212 airplanes. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by a report that the aft mount pylon bolts of the CFM56-5 engines may have been installed using the wrong torque values. We are issuing this AD to detect and correct improper torque of the aft mount pylon bolts, which, if combined with any maintenance damage, could lead to aft engine mount failure, possibly resulting in engine detachment and consequent reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection for Incorrect Torque Values Within 6 months or 1,500 flight cycles, whichever occurs first after the effective date of this AD, inspect to determine the method used to install the engines, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-71-1063, including Appendix 01, dated August 13, 2014. A review of airplane maintenance records is acceptable in lieu of this inspection if the method used to install the engines can be conclusively determined from that review. For any engine replaced as specified in the Airbus A318/ A319/A320/A321 Aircraft Maintenance Manual (AMM), Task 71-00-00-400- 040-A01, ``Installation of the Power Plant with Engine Positioner TWW 75E,'' dated May 2013: Within 6 months or 1,500 flight cycles, whichever occurs first after the effective date of this AD, re- torque the 4 aft mount pylon bolts using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Note 1 to paragraph (g) of this AD: Additional guidance for the re-torque can be found in Airbus A318/A319/A320/A321 AMM Task 71-00- 00-400-040-A01, ``Installation of the Power Plant with Engine Positioner TWW 75E,'' dated May 2014. (h) Parts Installation Limitation As of the effective date of this AD, no person may install a CFM56-5 engine, on any airplane, unless the inspection, and, as applicable, the re-torque, is done as specified in paragraph (g) of this AD. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone: 425-227-1405; fax: 425-227-1149. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2014-0258, dated November 28, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-1429-0002. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (k)(3) and (k)(4) of this AD. (k) 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 this AD specifies otherwise. (i) Airbus Service Bulletin A320-71-1063, including Appendix 01, dated August 13, 2014. (ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: [email protected]; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference 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 Renton, Washington, on January 11, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-01108 Filed 1-25-16; 8:45 am] BILLING CODE 4910-13-P
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PART 39—AIRWORTHINESS your request. You may email your request to: This AD was prompted by a report that
DIRECTIVES ANE–AD–AMOC@faa.gov. the aft mount pylon bolts of the CFM56–
(h) Related Information 5 engines may have been installed using
■ 1. The authority citation for part 39 the wrong torque values. This AD
For more information about this AD,
continues to read as follows: contact Kyle Gustafson, Aerospace Engineer, requires identification of engines that
Authority: 49 U.S.C. 106(g), 40113, 44701. Engine & Propeller Directorate, FAA, 1200 were installed using the wrong torque
District Avenue, Burlington, MA 01803; values and re-torque of the four aft
§ 39.13 [Amended] phone: 781–238–7183; fax: 781–238–7199; mount pylon bolts of those engines. We
■ 2. The FAA amends § 39.13 by adding email: kyle.gustafson@faa.gov. are issuing this AD to detect and correct
the following new airworthiness (i) Material Incorporated by Reference improper torque of the aft mount pylon
directive (AD): bolts, which, if combined with any
(1) The Director of the Federal Register
2015–28–01 Engine Alliance: Amendment approved the incorporation by reference maintenance damage, could lead to aft
39–18384; Docket No. FAA–2015–3585; (IBR) of the service information listed in this engine mount failure, possibly resulting
Directorate Identifier 2015–NE–22–AD. paragraph under 5 U.S.C. 552(a) and 1 CFR in engine detachment and consequent
(a) Effective Date
part 51. reduced control of the airplane.
(2) You must use this service information DATES: This AD becomes effective
This AD is effective March 1, 2016. as applicable to do the actions required by March 1, 2016.
this AD, unless the AD specifies otherwise.
(b) Affected ADs The Director of the Federal Register
(i) Engine Alliance (EA) Service Bulletin
None. (SB) No. EAGP7–72–329, dated July 21, 2015. approved the incorporation by reference
(ii) EA SB No. EAGP7–72–330, dated July of a certain publication listed in this AD
(c) Applicability
21, 2015. as of March 1, 2016.
This AD applies to Engine Alliance (EA) (3) For EA service information identified in ADDRESSES: You may examine the AD
GP7270 turbofan engines with a high- this AD, contact Engine Alliance, 400 Main
pressure compressor (HPC) cone shaft, part
docket on the Internet at http://www.
St., East Hartford, CT 06108, M/S 169–10; regulations.gov/#!docketDetail;D=FAA–
number 382–100–907–0, installed. phone: 800–565–0140; email: help24@
2015–1429; or in person at the Docket
(d) Unsafe Condition pw.utc.com; Internet:
sp.engineallianceportal.com. Management Facility, U.S. Department
This AD was prompted by the (4) You may view this service information of Transportation, Docket Operations,
manufacturer informing us that the at FAA, Engine & Propeller Directorate, 1200 M–30, West Building Ground Floor,
inspection and repair criteria in the District Avenue, Burlington, MA. For Room W12–140, 1200 New Jersey
maintenance manual for aft bolt holes of the information on the availability of this Avenue SE., Washington, DC.
HPC cone shaft on the affected engines is material at the FAA, call 781–238–7125. For service information identified in
incorrect. We are issuing this AD to prevent (5) You may view this service information
failure of the HPC cone shaft, which could
this final rule, contact Airbus,
at the National Archives and Records Airworthiness Office—EIAS, 1 Rond
lead to uncontained engine failure and Administration (NARA). For information on
damage to the airplane. Point Maurice Bellonte, 31707 Blagnac
the availability of this material at NARA, call
202–741–6030, or go to: http://www.archives.
Cedex, France; telephone: +33 5 61 93
(e) Compliance 36 96; fax: +33 5 61 93 44 51; email:
gov/federal-register/cfr/ibr-locations.html.
Comply with this AD within the account.airworth-eas@airbus.com;
compliance times specified, unless already Issued in Burlington, Massachusetts, on Internet http://www.airbus.com. You
done. January 13, 2016.
may view this referenced service
(1) For HPC cone shafts with serial Gaetano Sciortino,
numbers listed in EA Service Bulletin (SB)
information at the FAA, Transport
Acting Directorate Manager, Engine & Airplane Directorate, 1601 Lind Avenue
No. EAGP7–72–330, dated July 21, 2015, Propeller Directorate, Aircraft Certification
inspect the inner diameter of the HPC cone SW., Renton, WA. For information on
Service.
shaft aft bolt holes for nicks, dents, pits, and the availability of this material at the
[FR Doc. 2016–01268 Filed 1–25–16; 8:45 am]
scratches before accumulating 9,000 cycles FAA, call 425–227–1221. It is also
since new (CSN). Do not reinstall the HPC BILLING CODE 4910–13–P available on the Internet at http://
cone shaft if the aft bolt hole has any nicks, www.regulations.gov by searching for
dents, pits, or scratches that are greater than and locating Docket No. FAA–2015–
0.002 inch in depth. DEPARTMENT OF TRANSPORTATION 1429.
(2) For HPC cone shafts with serial
numbers listed in EA SB No. EAGP7–72–329, Federal Aviation Administration FOR FURTHER INFORMATION CONTACT:
dated July 21, 2015, shot peen the HPC cone Sanjay Ralhan, Aerospace Engineer,
shaft aft bolt holes before accumulating 9,000 14 CFR Part 39 International Branch, ANM–116,
CSN. Use paragraph 1 of the Transport Airplane Directorate, FAA,
Accomplishment Instructions in EA SB No. [Docket No. FAA–2015–1429; Directorate
Identifier 2014–NM–246–AD; Amendment 1601 Lind Avenue SW., Renton, WA
EAGP7–72–329 to do the shot peening. 98057–3356; telephone: 425–227–1405;
39–18382; AD 2016–02–03]
(f) Installation Prohibition fax: 425–227–1149.
RIN 2120–AA64
After the effective date of this AD, do not Discussion
install an HPC cone shaft on any engine with
Airworthiness Directives; Airbus We issued a notice of proposed
the following:
(1) any nicks, dents, pits, or scratches in an Airplanes rulemaking (NPRM) to amend 14 CFR
HPC cone shaft aft bolt hole that is greater AGENCY: Federal Aviation part 39 by adding an AD that would
than 0.002 inch in depth; or Administration (FAA), Department of apply to certain Airbus Model A319–
mstockstill on DSK4VPTVN1PROD with RULES
(2) any repair of an HPC cone shaft aft bolt 113, A319–114, A320–211, and A320–
Transportation (DOT).
hole that did not include shot peening. 212 airplanes. The NPRM published in
ACTION: Final rule.
(g) Alternative Methods of Compliance the Federal Register on June 15, 2015
(AMOCs) SUMMARY: We are adopting a new (80 FR 34101). The NPRM was
The Manager, Engine Certification Office, airworthiness directive (AD) for certain prompted by a report that the aft mount
may approve AMOCs for this AD. Use the Airbus Model A319–113, A319–114, pylon bolts of the CFM56–5 engines
procedures found in 14 CFR 39.19 to make A320–211, and A320–212 airplanes. may have been installed using the
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![4168 Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Rules and Regulations
wrong torque values. The NPRM proposed AD (80 FR 34101, June 15, We also estimate that it will take
proposed to require identification of 2015), by revising the wording to refer about 2 work-hours per product to
engines that were installed using the to the Aircraft Maintenance Manual comply with the basic requirements of
wrong torque values and re-torque of the (AMM), dated May 2013 instead of this AD. The average labor rate is $85
four aft mount pylon bolts of those Airbus Service Bulletin A320–71–1063, per work-hour. Based on these figures,
engines. We are issuing this AD to including Appendix 01, dated August we estimate the cost of this AD on U.S.
detect and correct improper torque of 13, 2014. DAL pointed out that operators to be $21,420, or $170 per
the aft mount pylon bolts, which, if paragraph (h) of the proposed AD product.
combined with any maintenance required engine installation in
Authority for this Rulemaking
damage, could lead to aft engine mount accordance with Airbus Service Bulletin
failure, possibly resulting in engine A320–71–1063, including Appendix 01, Title 49 of the United States Code
detachment and consequent reduced dated August 13, 2014. DAL also specifies the FAA’s authority to issue
control of the airplane. mentioned that Airbus Service Bulletin rules on aviation safety. Subtitle I,
The European Aviation Safety Agency A320–71–1063, including Appendix 01, section 106, describes the authority of
(EASA), which is the Technical Agent dated August 13, 2014, only has the FAA Administrator. ‘‘Subtitle VII:
for the Member States of the European requirements for inspection and re- Aviation Programs,’’ describes in more
Union, has issued EASA AD 2014–0258, torque of the aft engine mount pylon detail the scope of the Agency’s
dated November 28, 2014 (referred to bolts. authority.
after this as the Mandatory Continuing We agree to revise paragraph (h) of We are issuing this rulemaking under
Airworthiness Information, or ‘‘the this AD because Airbus Service Bulletin the authority described in ‘‘Subtitle VII,
MCAI’’), to correct an unsafe condition A320–71–1063, including Appendix 01, Part A, Subpart III, Section 44701:
for certain Airbus Model A319–113, dated August 13, 2014, does not contain General requirements.’’ Under that
A319–114, A320–211, and A320–212 installation instructions. We have section, Congress charges the FAA with
airplanes. The MCAI states: revised paragraph (h) of this AD to promoting safe flight of civil aircraft in
In the Aircraft Maintenance Manual specify that no person may install a air commerce by prescribing regulations
(AMM) revision dated May 2013, a wrong CFM56–5 engine, on any airplane, for practices, methods, and procedures
torque value was added in AMM task 71–00– unless accomplishing the actions the Administrator finds necessary for
00–400–040–A01 ‘‘Installation of the power specified in paragraph (g) of this AD. safety in air commerce. This regulation
plant with Engine Positioner TWW75E’’. is within the scope of that authority
Temporary Revisions (TR) dated March 2014 Conclusion because it addresses an unsafe condition
were published by Airbus to correct the that is likely to exist or develop on
We reviewed the relevant data,
information and with AMM revision dated products identified in this rulemaking
May 2014, Task 71–00–00–400–040–A01 was considered the comment received, and
determined that air safety and the action.
corrected to include the correct values.
Notwithstanding those actions, static and public interest require adopting this AD Regulatory Findings
fatigue analyses have concluded that this with the change described previously
undertorque scenario negatively impacts the and minor editorial changes. We have We determined that this AD will not
assembly performance, reducing the aft determined that these minor changes: have federalism implications under
Executive Order 13132. This AD will
mount capability. • Are consistent with the intent that
This condition, if not corrected and if not have a substantial direct effect on
was proposed in the NPRM (80 FR
combined with any maintenance damage, the States, on the relationship between
could lead to aft engine mount failure,
34101, June 15, 2015) for correcting the
the national government and the States,
possibly resulting in engine detachment and unsafe condition; and
or on the distribution of power and
consequent reduced control of the aeroplane. • Do not add any additional burden responsibilities among the various
For the reasons described above, this upon the public than was already levels of government.
[EASA] AD requires identification of proposed in the NPRM (80 FR 34101, For the reasons discussed above, I
CFM56–5 engines (those listed in TCDS June 15, 2015).
EASA.E.067 [http://easa.europa.eu/ certify that this AD:
We also determined that these 1. Is not a ‘‘significant regulatory
document-library/typecertificates/easae067])
changes will not increase the economic action’’ under Executive Order 12866;
that were installed by using the wrong torque
data of AMM instructions mentioned above burden on any operator or increase the 2. Is not a ‘‘significant rule’’ under the
and re-torque of the four aft mount pylon scope of this AD. DOT Regulatory Policies and Procedures
bolts of those engines. Related Service Information under 1 (44 FR 11034, February 26, 1979);
You may examine the MCAI in the CFR part 51 3. Will not affect intrastate aviation in
AD docket on the Internet at http:// Alaska; and
www.regulations.gov/#!documentDetail; Airbus has issued Airbus Service 4. Will not have a significant
D=FAA–2015–1429–0002. Bulletin A320–71–1063, including economic impact, positive or negative,
Appendix 01, dated August 13, 2014. on a substantial number of small entities
Comments The service information describes under the criteria of the Regulatory
We gave the public the opportunity to procedures to detect and correct Flexibility Act.
participate in developing this AD. The improper torque of the aft mount pylon
bolts. This service information is Examining the AD Docket
following presents the comment
received on the NPRM (80 FR 34101, reasonably available because the You may examine the AD docket on
June 15, 2015) and the FAA’s response interested parties have access to it the Internet at http://www.regulations.
mstockstill on DSK4VPTVN1PROD with RULES
to each comment. through their normal course of business gov/#!docketDetail;D=FAA-2015-1429;
or by the means identified in the or in person at the Docket Management
Request to Revise Paragraph (h) of the ADDRESSES section. Facility between 9 a.m. and 5 p.m.,
Proposed AD (80 FR 34101, June 15, Monday through Friday, except Federal
2015) Costs of Compliance
holidays. The AD docket contains this
Delta Air Lines, Inc. (DAL) requested We estimate that this AD affects 126 AD, the regulatory evaluation, any
that we revise paragraph (h) of the airplanes of U.S. registry. comments received, and other
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information. The street address for the Airbus Service Bulletin A320–71–1063, found in the AD docket on the Internet at
Docket Operations office (telephone: including Appendix 01, dated August 13, http://www.regulations.gov/#!document
800–647–5527) is in the ADDRESSES 2014. A review of airplane maintenance Detail;D=FAA-2015-1429-0002.
records is acceptable in lieu of this (2) Service information identified in this
section.
inspection if the method used to install the AD that is not incorporated by reference is
List of Subjects in 14 CFR Part 39 engines can be conclusively determined from available at the addresses specified in
that review. For any engine replaced as paragraphs (k)(3) and (k)(4) of this AD.
Air transportation, Aircraft, Aviation specified in the Airbus A318/A319/A320/
safety, Incorporation by reference, A321 Aircraft Maintenance Manual (AMM), (k) Material Incorporated by Reference
Safety. Task 71–00–00–400–040–A01, ‘‘Installation (1) The Director of the Federal Register
of the Power Plant with Engine Positioner approved the incorporation by reference
Adoption of the Amendment TWW 75E,’’ dated May 2013: Within 6 (IBR) of the service information listed in this
Accordingly, under the authority months or 1,500 flight cycles, whichever paragraph under 5 U.S.C. 552(a) and 1 CFR
delegated to me by the Administrator, occurs first after the effective date of this AD, part 51.
the FAA amends 14 CFR part 39 as re-torque the 4 aft mount pylon bolts using (2) You must use this service information
follows: a method approved by the Manager, as applicable to do the actions required by
International Branch, ANM–116, Transport this AD, unless this AD specifies otherwise.
Airplane Directorate, FAA; or the European (i) Airbus Service Bulletin A320–71–1063,
PART 39—AIRWORTHINESS
Aviation Safety Agency (EASA); or Airbus’s including Appendix 01, dated August 13,
DIRECTIVES EASA Design Organization Approval (DOA). 2014.
■ 1. The authority citation for part 39 Note 1 to paragraph (g) of this AD: (ii) Reserved.
Additional guidance for the re-torque can be (3) For service information identified in
continues to read as follows: this AD, contact Airbus SAS, Airworthiness
found in Airbus A318/A319/A320/A321
Authority: 49 U.S.C. 106(g), 40113, 44701. AMM Task 71–00–00–400–040–A01, Office—EAW, 1 Rond Point Maurice
‘‘Installation of the Power Plant with Engine Bellonte, 31707 Blagnac Cedex, France;
§ 39.13 [Amended] Positioner TWW 75E,’’ dated May 2014. telephone: +33 5 61 93 36 96; fax: +33 5 61
■ 2. The FAA amends § 39.13 by adding 93 44 51; email: account.airworth-eas@
the following new airworthiness (h) Parts Installation Limitation airbus.com; Internet http://www.airbus.com.
directive (AD): As of the effective date of this AD, no (4) You may view this service information
person may install a CFM56–5 engine, on any at the FAA, Transport Airplane Directorate,
2016–02–03 Airbus: Amendment 39– airplane, unless the inspection, and, as 1601 Lind Avenue SW., Renton, WA. For
18382. Docket No. FAA–2015–1429; applicable, the re-torque, is done as specified information on the availability of this
Directorate Identifier 2014–NM–246–AD. in paragraph (g) of this AD. material at the FAA, call 425–227–1221.
(a) Effective Date (5) You may view this service information
(i) Other FAA AD Provisions that is incorporated by reference at the
This AD becomes effective March 1, 2016. The following provisions also apply to this National Archives and Records
(b) Affected ADs AD: Administration (NARA). For information on
(1) Alternative Methods of Compliance the availability of this material at NARA, call
None.
(AMOCs): The Manager, International 202–741–6030, or go to: http://www.archives.
(c) Applicability Branch, ANM–116, Transport Airplane gov/federal-register/cfr/ibr-locations.html.
This AD applies to the airplanes identified Directorate, FAA, has the authority to
Issued in Renton, Washington, on January
in paragraphs (c)(1) and (c)(2) of this AD, approve AMOCs for this AD, if requested
11, 2016.
certificated in any category, all manufacturer using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your Michael Kaszycki,
serial numbers.
request to your principal inspector or local Acting Manager, Transport Airplane
(1) Airbus Model A319–113 and –114
Flight Standards District Office, as Directorate, Aircraft Certification Service.
airplanes.
(2) Airbus Model A320–211 and –212 appropriate. If sending information directly [FR Doc. 2016–01108 Filed 1–25–16; 8:45 am]
airplanes. to the International Branch, send it to ATTN: BILLING CODE 4910–13–P
Sanjay Ralhan, Aerospace Engineer,
(d) Subject International Branch, ANM–116, Transport
Air Transport Association (ATA) of Airplane Directorate, FAA, 1601 Lind
DEPARTMENT OF TRANSPORTATION
America Code 71, Powerplant. Avenue SW., Renton, WA 98057–3356;
telephone: 425–227–1405; fax: 425–227–
(e) Reason Federal Aviation Administration
1149. Information may be emailed to: 9-116-
This AD was prompted by a report that the AMOC-REQUESTS@faa.gov. Before using
aft mount pylon bolts of the CFM56–5 any approved AMOC, notify your appropriate 14 CFR Part 39
engines may have been installed using the principal inspector, or lacking a principal [Docket No. FAA–2015–1991; Directorate
wrong torque values. We are issuing this AD inspector, the manager of the local flight Identifier 2014–NM–251–AD; Amendment
to detect and correct improper torque of the standards district office/certificate holding 39–18381; AD 2016–02–02]
aft mount pylon bolts, which, if combined district office. The AMOC approval letter
with any maintenance damage, could lead to must specifically reference this AD. RIN 2120–AA64
aft engine mount failure, possibly resulting in (2) Contacting the Manufacturer: For any
engine detachment and consequent reduced requirement in this AD to obtain corrective Airworthiness Directives; Airbus
control of the airplane. actions from a manufacturer, the action must Airplanes
be accomplished using a method approved
(f) Compliance by the Manager, International Branch, ANM– AGENCY: Federal Aviation
Comply with this AD within the 116, Transport Airplane Directorate, FAA; or Administration (FAA), Department of
compliance times specified, unless already the EASA; or Airbus’s EASA DOA. If Transportation (DOT).
mstockstill on DSK4VPTVN1PROD with RULES
done. approved by the DOA, the approval must
ACTION: Final rule.
include the DOA-authorized signature.
(g) Inspection for Incorrect Torque Values
Within 6 months or 1,500 flight cycles, (j) Related Information SUMMARY: We are adopting a new
whichever occurs first after the effective date (1) Refer to Mandatory Continuing airworthiness directive (AD) for all
of this AD, inspect to determine the method Airworthiness Information (MCAI) EASA AD Airbus Model A318–111 and –112
used to install the engines, in accordance 2014–0258, dated November 28, 2014, for airplanes; Model A319–111, –112, and
with the Accomplishment Instructions of related information. This MCAI may be –115 airplanes; Model A320–214
VerDate Sep<11>2014 16:44 Jan 25, 2016 Jkt 238001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\26JAR1.SGM 26JAR1](https://thefederalregister.org/doc/81_FR_4183/page/3.svg)
Document Created: 2018-02-02 12:38:06
Document Modified: 2018-02-02 12:38:06
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD becomes effective March 1, 2016. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1405; fax: 425-227-1149. | |
| FR Citation | 81 FR 4167 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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