81 FR 44989 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 133 (July 12, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 133 (July 12, 2016)
| Page Range | 44989-44993 | |
| FR Document | 2016-16212 |
[Federal Register Volume 81, Number 133 (Tuesday, July 12, 2016)] [Rules and Regulations] [Pages 44989-44993] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-16212] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3632; Directorate Identifier 2015-NM-023-AD; Amendment 39-18590; AD 2016-14-09] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- [[Page 44990]] SUMMARY: We are superseding Airworthiness Directive (AD) 2014-14-06 for all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, - 113, -114, and -115 airplanes; Model A320-111, -211, -212, and -214 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. AD 2014-14-06 required inspecting the aft engine mount retainers for surface finish, cracks, and failure, and replacement if necessary. This new AD requires repetitive inspections for damaged, cracked, broken, and missing aft engine mount retainers, and replacement if necessary. This AD was prompted by inspection results that have shown that the main cause of crack initiation in the aft engine mount retainers is the vibration dynamic effect that affects both retainers, either with ``dull'' or ``bright'' surface finishes. We are issuing this AD to detect and correct failure of retainer brackets of the aft engine mount and consequent loss of the locking feature of the nuts of the inner and outer pins; loss of the pins will result in the aft mount engine link no longer being secured to the aft engine mount. DATES: This AD is effective August 16, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 16, 2016. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of August 27, 2014 (79 FR 42655, July 23, 2014). ADDRESSES: For Airbus service information identified in this AD, 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. For Goodrich Aerostructures service information identified in this AD, contact Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098; telephone 619-691-2719; email [email protected]; Internet http://www.goodrich.com/TechPubs. 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- 3632. 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- 3632; 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 (telephone 800- 647-5527) is 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 20590. 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. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2014-14-06, Amendment 39-17901 (79 FR 42655, July 23, 2014) (``AD 2014-14-06''). AD 2014-14-06 applied to all Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, and -115 airplanes; Model A320-111, -211, -212, and -214 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. The NPRM published in the Federal Register on September 17, 2015 (80 FR 55798) (``the NPRM''). The NPRM was prompted by inspection results that have shown that the main cause of crack initiation in the aft engine mount retainers is the vibration dynamic effect that affects both retainers, either with ``dull'' or ``bright'' surface finishes. The NPRM proposed to continue to require inspecting the aft engine mount retainers for surface finish, cracks, and failure, and replacement if necessary. The NPRM also proposed to require repetitive inspections for damaged, cracked broken, and missing aft engine mount retainers, and replacement if necessary. We are issuing this AD to detect and correct failure of retainer brackets of the aft engine mount and consequent loss of the locking feature of the nuts of the inner and outer pins; loss of the pins will result in the aft mount engine link no longer being secured to the aft engine mount. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0021, dated February 13, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition. The MCAI states: During in-service inspections, several aft engine mount retainers, fitted on aeroplanes equipped with CFM56-5A/5B engines, have been found broken. The results of the initial investigations highlighted that two different types of surface finish had been applied (respectively bright and dull material finishes), and that dull finish affects the strength of the retainer with regard to fatigue properties of the part. The pins which attach the engine link to the aft mount are secured by two nuts, which do not have a self-locking feature; this function is provided by the retainer brackets. In case of failure of the retainer bracket, the locking feature of the nuts of the inner and outer pins is lost; as a result, these nuts could subsequently become loose. In case of full loss of the nuts, there is the potential to also lose the pins, in which case the aft mount link will no longer be secured to the aft engine mount. The same locking feature is used for the three link assemblies of the aft mount. This condition, if not detected and corrected, could lead to in- flight loss of an aft mount link, possibly resulting in damage to the aeroplane and injury to person on the ground. To address this potential unsafe condition, EASA issued AD 2013- 0050 (http://ad.easa.europa.eu/blob/easa_ad_2013_0050_superseded.pdf/AD_2013-0050_1 [which corresponds to FAA AD 2014-14-06] to require detailed inspections (DET) of the aft engine mount retainers and the replacement of all retainers with dull finish with retainers having a bright finish. Since that [EASA] AD was issued, inspection results have shown that the main cause of crack initiation remains the vibration dynamic effect that affects both retainers, either with ``dull'' or ``bright'' surface finishes. The non-conforming ``dull'' surface's pitting is an aggravating factor. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2013-0050, which is superseded, and requires repetitive DET of all aft engine mount retainers and, depending on findings [damaged, cracked, broken, or missing retainers], their replacement. This [EASA] AD is considered to be an interim action, pending development and availability of a final solution. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 3632. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. [[Page 44991]] Request To Use Alternative Inspection Method Delta Airlines (DAL) requested that we revise paragraph (m) of the NPRM to approve use of a boroscope with 10X magnification when performing the inspection of the center aft engine mount inner retainer as an option to removing the center retainer. DAL stated that this procedure was allowed by the FAA in Alternative Method of Compliance (AMOC) ANM-116-14-423, dated September 16, 2014, for AD 2014-14-06. DAL stated that this procedure provides an equivalent level of safety since the detectability of the subject condition using this alternate inspection method is the same as a detailed visual inspection using 10X magnification, mirror, and light. We disagree with DAL's request. AMOC ANM-116-14-423, dated September 16, 2014, provides an AMOC for replacing 10X magnification, mirror, and light with a boroscope with 10X magnification but that AMOC is not an option to removing the center retainer. However, under the provisions of paragraph (q)(1) of this AD, we will consider requests for approval of alternative procedures, if sufficient data are submitted to substantiate that the change would provide an acceptable level of safety. We have not changed this AD in this regard. We have clarified in paragraph (q)(1)(ii) of this AD that AMOCs approved previously for AD 2014-14-06, are approved as AMOCs for the corresponding provisions of paragraphs (g) and (i) of this AD. Request To Use Later Revisions of Service Information DAL requested that we permit use of later approved revisions of the service information. DAL stated that Airbus has released Airbus Service Bulletin A320-71-1060, Revision 01, dated April 7, 2015. We partially agree with DAL's request. We do not agree to include an allowance for later approved revisions of the referenced service information. When referring to a specific service document in an AD, using the phrase, ``or later FAA-approved revisions,'' violates the Office of the Federal Register's regulations for approving materials that are incorporated by reference. See 1 CFR 51.1(f). However, affected operators may request approval to use a later revision of the referenced service document as an alternative method of compliance, under the provisions of paragraph (q)(1) of this AD. We have not changed this AD in this regard. We agree to reference to Airbus Service Bulletin A320-71-1060, Revision 01, dated April 7, 2015, in this final rule as the appropriate source of service information for accomplishing the actions required by paragraphs (l) and (m) of this AD (referred to as paragraphs (m) and (n) in the proposed AD). We have also redesignated paragraph (l) of the proposed AD to paragraph (p)(1) of this AD (the paragraph retains existing credit information) and added new paragraphs (p)(2) and (p)(3) of this AD to provide provisional credit for Airbus Service Bulletin A320-71-1060, dated October 9, 2014. For operators to obtain credit for Airbus Service Bulletin A320-71-1060, dated October 9, 2014, for the replacement, operators must use the torque value units applicable to nut item (14) specified in Airbus Service Bulletin A320-71-1060, Revision 01, dated April 7, 2015. Those torque value units were incorrectly stated in Airbus Service Bulletin A320-71-1060, dated October 9, 2014. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320-71-1060, Revision 01, dated April 7, 2015. This service information describes procedures for inspecting the aft engine mount retainers for surface finish (dull or bright), for damaged, cracked, broken, or missing retainers, and replacement. Goodrich Aerostructures has issued Service Bulletin RA32071-160, dated September 18, 2014. This service information describes procedures for inspecting the aft engine mount inner retainers for cracks or failure, and replacement. 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 922 airplanes of U.S. registry. The actions required by AD 2014-14-06, and retained in this AD, take about 3 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are were required by AD 2014-14-06 is $255 per inspection cycle per product (for two engines). We also estimate that it would take about 10 work-hours per product to comply with the basic requirements of this AD, and 1 work-hour per product to report inspection findings. 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 $862,070, or $935 per product. In addition, we estimate that any necessary follow-on actions would take about 2 work-hours and require parts costing $10,000, for a cost of $10,170 per product. We have no way of determining the number of airplanes that might need these actions. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120- 0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES-200. 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 [[Page 44992]] 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. 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 removing Airworthiness Directive (AD) 2014-14-06, Amendment 39-17901 (79 FR 42655, July 23, 2014), and adding the following new AD: 2016-14-09 Airbus: Amendment 39-18590. Docket No. FAA-2015-3632; Directorate Identifier 2015-NM-023-AD. (a) Effective Date This AD is effective August 16, 2016. (b) Affected ADs This AD replaces AD 2014-14-06, Amendment 39-17901 (79 FR 42655, July 23, 2014) (``AD 2014-14-06''). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A318-111 and -112 airplanes. (2) Airbus Model A319-111, -112, -113, -114, and -115 airplanes. (3) Airbus Model A320-211, -212, and -214 airplanes. (4) Airbus Model A321-111, -112, -211, -212, and -213 airplanes. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by inspection results that have shown that the main cause of crack initiation in the aft engine mount retainers is the vibration dynamic effect that affects both retainers, either with ``dull'' or ``bright'' surface finishes. We are issuing this AD to detect and correct failure of retainer brackets of the aft engine mount and consequent loss of the locking feature of the nuts of the inner and outer pins; loss of the pins will result in the aft mount engine link no longer being secured to the aft engine mount. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2014-14-06, with no changes. Within 3 months after August 27, 2014 (the effective date of AD 2014-14-06): Do a detailed inspection of the aft engine mount retainers for surface finish (dull or bright), and for cracks and failure, in accordance with Section 4.2.2, ``Inspection Requirements,'' of Airbus Alert Operators Transmission (AOT) A71N001-12, Rev. 2, dated February 27, 2013, except as specified in paragraph (h) of this AD. (h) Retained Exception to Paragraph (g) of This AD, With No Changes This paragraph restates the requirements of paragraph (h) of AD 2014-14-06, with no changes. The actions required by paragraph (g) of this AD are not required to be done on airplanes with manufacturer serial numbers 4942 and higher, provided a review of maintenance records verifies that no aft engine mount retainers have been replaced since first flight of the airplane. (i) Retained Repetitive Inspection and Retainer Replacement for Dull Finish Retainers, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2014-14-06, with no changes. If, during the detailed inspection required by paragraph (g) of this AD, any installed dull finish aft engine mount retainer is found without cracks and not failed: Do the actions specified in paragraphs (i)(1) and (i)(2) of this AD. (1) Within 25 flight cycles after doing the actions required by paragraph (g) of this AD: Repeat the detailed inspection specified in paragraph (g) of this AD. (2) Within 50 flight cycles after doing the first detailed inspection specified in paragraph (g) of this AD: Replace all dull finish retainers with new retainers, in accordance with Section 4.2.3.1, ``Replacement Procedure,'' of Airbus AOT A71N001-12, Rev. 2, dated February 27, 2013. (j) Retained Replacement of Cracked or Failed Retainers, With No Changes This paragraph restates the requirements of paragraph (j) of AD 2014-14-06, with no changes. If, during any detailed inspection specified in paragraph (g) of this AD, any installed aft engine mount retainer is found cracked or failed: Before further flight, replace all affected aft engine mount retainers with new retainers, in accordance with Section 4.2.3, ``Replacement Procedure,'' of Airbus AOT A71N001-12, Rev. 2, dated February 27, 2013. (k) Retained Parts Prohibition, With No Changes This paragraph restates the requirements of paragraph (k) of AD 2014-14-06, with no changes. As of August 27, 2014 (the effective date of AD 2014-14-06), no person may install any aft engine mount retainer with a dull finish on any airplane. The instructions of Airbus AOT A71N001-12, Rev. 2, dated February 27, 2013; or the Accomplishment Instructions of Goodrich Service Bulletin RA32071- 146, Rev. 2, dated July 26, 2012; may be used to verify the correct finish of the part. (l) New Requirement of This AD: Repetitive Inspections At the latest of the applicable times specified in paragraphs (l)(1), (l)(2), and (l)(3) of this AD: Do a detailed inspection for damaged, cracked, broken, or missing aft engine mount retainers, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-71-1060, Revision 01, dated April 7, 2015; or Goodrich Service Bulletin RA32071-160, dated September 18, 2014. Repeat the inspection of the aft engine mount retainers thereafter at intervals not to exceed 12 months. (1) Within 12 months since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness. (2) Within 12 months after installation of new retainers. (3) Within 9 months after the effective date of this AD. (m) New Requirement of This AD: Replacement of Retainers With Findings If, during any detailed inspection specified in paragraph (l) of this AD, any installed aft engine mount retainer is found damaged, cracked, broken, or missing: Before further flight, replace all affected aft engine mount retainers with new retainers, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-71-1060, Revision 01, dated April 7, 2015. [[Page 44993]] (n) New Requirement of This AD: No Terminating Action Replacement of retainers on an airplane, as required by paragraph (m) of this AD, does not constitute terminating action for the repetitive inspections required by paragraph (l) of this AD for that airplane. (o) New Requirement of This AD: Required Reporting Submit a report of positive findings of any inspection required by paragraph (l) of this AD to Airbus at the applicable time specified in paragraph (o)(1) or (o)(2) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (p) Credit for Previous Actions (1) This paragraph restates the provisions of paragraph (l) of AD 2014-14-06, with no changes. This paragraph provides credit for actions required by paragraphs (g), (i), and (j) of this AD, if those actions were performed before August 27, 2014 (the effective date of AD 2014-14-06) using Airbus AOT A71N001-12, Rev. 1, dated August 9, 2012. This service information is not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraph (l) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-71- 1060, dated October 9, 2014. Airbus Service Bulletin A320-71-1060, dated October 9, 2014, is not incorporated by reference in this AD. (3) This paragraph provides credit for actions required by paragraph (m) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-71- 1060, dated October 9, 2014, provided that it can be conclusively determined that the torque value units applicable to nut item (14) that are specified in Airbus Service Bulletin A320-71-1060, Revision 01, dated April 7, 2015, have been used. Airbus Service Bulletin A320-71-1060, dated October 9, 2014, is not incorporated by reference in this AD. (q) 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]. (i) 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. (ii) AMOCs approved previously for AD 2014-14-06, are approved as AMOCs for the corresponding provisions of paragraphs (g), (i), (j), and (k) of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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 European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. (4) Required for Compliance (RC): If any Airbus service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (r) Special Flight Permits Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed. (s) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015-0021, dated February 13, 2015, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-3632. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (t)(5), (t)(6), and (t)(7) of this AD. (t) 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. (3) The following service information was approved for IBR on August 16, 2016. (i) Airbus Service Bulletin A320-71-1060, Revision 01, dated April 7, 2015. (ii) Goodrich Service Bulletin RA32071-160, dated September 18, 2014. (4) The following service information was approved for IBR on August 27, 2014 (79 FR 42655, July 23, 2014). (i) Airbus Alert Operators Transmission A71N001-12, Rev. 2, dated February 27, 2013. The first page of this document contains the document number, revision, and date; no other page of this document contains this information. (ii) Goodrich Service Bulletin RA32071-146, Rev. 2, dated July 26, 2012. (5) For Airbus service information identified in this AD, 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. (6) For Goodrich Aerostructures service information identified in this AD, contact Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098; telephone 619-691-2719; email [email protected]; Internet http://www.goodrich.com/TechPubs. (7) 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. (8) 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 July 1, 2016. Phillip Forde, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-16212 Filed 7-11-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 133 / Tuesday, July 12, 2016 / Rules and Regulations 44989
Regulatory Findings and lower stiffener joints to the web at a by the Manager, International Branch, ANM–
certain frame. We are issuing this AD to 116, Transport Airplane Directorate, FAA; or
We determined that this AD will not detect and correct an unsatisfactory bore that EASA; or Dassault Aviation’s EASA DOA. If
have federalism implications under can adversely affect the structural integrity of approved by the DOA, the approval must
Executive Order 13132. This AD will the airplane. include the DOA-authorized signature.
not have a substantial direct effect on
(f) Compliance (k) Related Information
the States, on the relationship between
the national government and the States, Comply with this AD within the Refer to Mandatory Continuing
or on the distribution of power and compliance times specified, unless already Airworthiness Information (MCAI) EASA AD
done. 2015–0204, dated October 8, 2015, for related
responsibilities among the various
information. This MCAI may be found on the
levels of government. (g) Inspect Bores
Internet at http://www.regulations.gov by
For the reasons discussed above, I Within 4,000 flight cycles or 98 months, searching for and locating Docket No. FAA–
certify that this AD: whichever occurs first since date of issuance 2016–3987.
1. Is not a ‘‘significant regulatory of the original airworthiness certificate or
action’’ under Executive Order 12866; date of issuance of the original export (l) Material Incorporated by Reference
2. Is not a ‘‘significant rule’’ under the certificate of airworthiness, do a detailed (1) The Director of the Federal Register
DOT Regulatory Policies and Procedures visual and rototest inspection of the bores, approved the incorporation by reference
(44 FR 11034, February 26, 1979); located on upper and lower stiffener joints to (IBR) of the service information listed in this
3. Will not affect intrastate aviation in the web at pylon Frame 41, to determine if paragraph under 5 U.S.C. 552(a) and 1 CFR
the bores are not satisfactory, in accordance part 51.
Alaska; and with the Accomplishment Instructions of
4. Will not have a significant (2) You must use this service information
Dassault Service Bulletin 7X–346, dated as applicable to do the actions required by
economic impact, positive or negative, April 24, 2015. this AD, unless this AD specifies otherwise.
on a substantial number of small entities (i) Dassault Service Bulletin 7X–346, dated
under the criteria of the Regulatory (h) Repair
April 24, 2015.
Flexibility Act. If, during the inspection required by (ii) Reserved.
paragraph (g) of this AD, it is determined that (3) For service information identified in
List of Subjects in 14 CFR Part 39 any bore is not satisfactory: Before further this AD, contact Dassault Falcon Jet
Air transportation, Aircraft, Aviation flight, repair affected bores, in accordance Corporation, Teterboro Airport, P.O. Box
safety, Incorporation by reference, with the Accomplishment Instructions of 2000, South Hackensack, NJ 07606;
Dassault Service Bulletin 7X–346, dated telephone: 201–440–6700; Internet: http://
Safety. April 24, 2015, except as required by www.dassaultfalcon.com.
Adoption of the Amendment paragraph (i) of this AD. (4) You may view this service information
Accordingly, under the authority (i) Exceptions at the FAA, Transport Airplane Directorate,
delegated to me by the Administrator, Where the Dassault Service Bulletin 7X– 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
the FAA amends 14 CFR part 39 as 346, dated April 24, 2015, specifies to contact
Dassault Aviation: Before further flight, material at the FAA, call 425–227–1221.
follows: (5) You may view this service information
repair using a method approved by the
Manager, International Branch, ANM–116, that is incorporated by reference at the
PART 39—AIRWORTHINESS National Archives and Records
DIRECTIVES Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or Administration (NARA). For information on
Dassault Aviation’s EASA Design the availability of this material at NARA, call
■ 1. The authority citation for part 39 202–741–6030, or go to: http://
continues to read as follows: Organization Approval (DOA).
www.archives.gov/federal-register/cfr/ibr-
Authority: 49 U.S.C. 106(g), 40113, 44701. (j) Other FAA AD Provisions locations.html.
The following provisions also apply to this Issued in Renton, Washington, on June 23,
§ 39.13 [Amended] AD: 2016.
■ 2. The FAA amends § 39.13 by adding (1) Alternative Methods of Compliance
Dorr M. Anderson,
the following new airworthiness (AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane Acting Manager, Transport Airplane
directive (AD): Directorate, Aircraft Certification Service.
Directorate, FAA, has the authority to
2016–13–15 Dassault Aviation: approve AMOCs for this AD, if requested [FR Doc. 2016–15930 Filed 7–11–16; 8:45 am]
Amendment 39–18580. Docket No. using the procedures found in 14 CFR 39.19. BILLING CODE 4910–13–P
FAA–2016–3987; Directorate Identifier In accordance with 14 CFR 39.19, send your
2015–NM–165–AD. request to your principal inspector or local
(a) Effective Date Flight Standards District Office, as DEPARTMENT OF TRANSPORTATION
appropriate. If sending information directly
This AD is effective August 16, 2016. to the International Branch, send it to ATTN: Federal Aviation Administration
(b) Affected ADs Tom Rodriguez, Aerospace Engineer,
International Branch, ANM–116, Transport
None. Airplane Directorate, FAA, 1601 Lind 14 CFR Part 39
(c) Applicability Avenue SW., Renton, WA 98057–3356; [Docket No. FAA–2015–3632; Directorate
telephone 425–227–1137; fax 425–227–1149. Identifier 2015–NM–023–AD; Amendment
This AD applies to Dassault Aviation
Information may be emailed to: 9-ANM-116- 39–18590; AD 2016–14–09]
Model FALCON 7X airplanes, certificated in
any category, manufacturer serial numbers 1 AMOC-REQUESTS@faa.gov. Before using
through 221 inclusive, except serial numbers any approved AMOC, notify your appropriate RIN 2120–AA64
182 and 220. principal inspector, or lacking a principal
mstockstill on DSK3G9T082PROD with RULES
inspector, the manager of the local flight Airworthiness Directives; Airbus
(d) Subject standards district office/certificate holding Airplanes
Air Transport Association (ATA) of district office. The AMOC approval letter
America Code 53, Fuselage. must specifically reference this AD. AGENCY: Federal Aviation
(2) Contacting the Manufacturer: For any Administration (FAA), Department of
(e) Reason requirement in this AD to obtain corrective Transportation (DOT).
This AD was prompted by a report of actions from a manufacturer, the action must ACTION: Final rule.
improperly drilled bores, located on upper be accomplished using a method approved
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![44990 Federal Register / Vol. 81, No. 133 / Tuesday, July 12, 2016 / Rules and Regulations
SUMMARY: We are superseding Examining the AD Docket for the Member States of the European
Airworthiness Directive (AD) 2014–14– You may examine the AD docket on Union, has issued EASA Airworthiness
06 for all Airbus Model A318–111 and the Internet at http:// Directive 2015–0021, dated February 13,
–112 airplanes; Model A319–111, –112, www.regulations.gov by searching for 2015 (referred to after this as the
–113, –114, and –115 airplanes; Model and locating Docket No. FAA–2015– Mandatory Continuing Airworthiness
A320–111, –211, –212, and –214 3632; or in person at the Docket Information, or ‘‘the MCAI’’), to correct
airplanes; and Model A321–111, –112, Management Facility between 9 a.m. an unsafe condition. The MCAI states:
–211, –212, and –213 airplanes. AD and 5 p.m., Monday through Friday, During in-service inspections, several aft
2014–14–06 required inspecting the aft except Federal holidays. The AD docket engine mount retainers, fitted on aeroplanes
engine mount retainers for surface contains this AD, the regulatory equipped with CFM56–5A/5B engines, have
finish, cracks, and failure, and evaluation, any comments received, and been found broken. The results of the initial
replacement if necessary. This new AD investigations highlighted that two different
other information. The address for the types of surface finish had been applied
requires repetitive inspections for Docket Office (telephone 800–647–5527) (respectively bright and dull material
damaged, cracked, broken, and missing is Docket Management Facility, U.S. finishes), and that dull finish affects the
aft engine mount retainers, and Department of Transportation, Docket strength of the retainer with regard to fatigue
replacement if necessary. This AD was Operations, M–30, West Building properties of the part. The pins which attach
prompted by inspection results that Ground Floor, Room W12–140, 1200 the engine link to the aft mount are secured
have shown that the main cause of crack New Jersey Avenue SE., Washington, by two nuts, which do not have a self-locking
initiation in the aft engine mount DC 20590. feature; this function is provided by the
retainers is the vibration dynamic effect retainer brackets. In case of failure of the
FOR FURTHER INFORMATION CONTACT: retainer bracket, the locking feature of the
that affects both retainers, either with Sanjay Ralhan, Aerospace Engineer, nuts of the inner and outer pins is lost; as a
‘‘dull’’ or ‘‘bright’’ surface finishes. We International Branch, ANM–116, result, these nuts could subsequently become
are issuing this AD to detect and correct Transport Airplane Directorate, FAA, loose.
failure of retainer brackets of the aft 1601 Lind Avenue SW., Renton, WA In case of full loss of the nuts, there is the
engine mount and consequent loss of 98057–3356; telephone 425–227–1405; potential to also lose the pins, in which case
the locking feature of the nuts of the the aft mount link will no longer be secured
fax 425–227–1149. to the aft engine mount. The same locking
inner and outer pins; loss of the pins
SUPPLEMENTARY INFORMATION: feature is used for the three link assemblies
will result in the aft mount engine link
of the aft mount.
no longer being secured to the aft engine Discussion This condition, if not detected and
mount. We issued a notice of proposed corrected, could lead to in-flight loss of an aft
DATES: This AD is effective August 16, rulemaking (NPRM) to amend 14 CFR mount link, possibly resulting in damage to
2016. part 39 to supersede AD 2014–14–06, the aeroplane and injury to person on the
Amendment 39–17901 (79 FR 42655, ground.
The Director of the Federal Register To address this potential unsafe condition,
approved the incorporation by reference July 23, 2014) (‘‘AD 2014–14–06’’). AD EASA issued AD 2013–0050 (http://
of certain publications listed in this AD 2014–14–06 applied to all Model A318– ad.easa.europa.eu/blob/easa_ad_2013_0050_
as of August 16, 2016. 111 and –112 airplanes; Model A319– superseded.pdf/AD_2013-0050_1 [which
The Director of the Federal Register 111, –112, –113, –114, and –115 corresponds to FAA AD 2014–14–06] to
approved the incorporation by reference airplanes; Model A320–111, –211, –212, require detailed inspections (DET) of the aft
and –214 airplanes; and Model A321– engine mount retainers and the replacement
of certain other publications listed in of all retainers with dull finish with retainers
this AD as of August 27, 2014 (79 FR 111, –112, –211, –212, and –213
airplanes. The NPRM published in the having a bright finish.
42655, July 23, 2014). Since that [EASA] AD was issued,
Federal Register on September 17, 2015 inspection results have shown that the main
ADDRESSES: For Airbus service (80 FR 55798) (‘‘the NPRM’’). The
information identified in this AD, cause of crack initiation remains the
NPRM was prompted by inspection vibration dynamic effect that affects both
contact Airbus, Airworthiness Office— results that have shown that the main retainers, either with ‘‘dull’’ or ‘‘bright’’
EIAS, 1 Rond Point Maurice Bellonte, cause of crack initiation in the aft surface finishes. The non-conforming ‘‘dull’’
31707 Blagnac Cedex, France; telephone engine mount retainers is the vibration surface’s pitting is an aggravating factor.
+33 5 61 93 36 96; fax +33 5 61 93 44 dynamic effect that affects both For the reasons described above, this
51; email account.airworth-eas@ retainers, either with ‘‘dull’’ or ‘‘bright’’ [EASA] AD retains the requirements of EASA
airbus.com; Internet http:// AD 2013–0050, which is superseded, and
surface finishes. The NPRM proposed to requires repetitive DET of all aft engine
www.airbus.com. continue to require inspecting the aft mount retainers and, depending on findings
For Goodrich Aerostructures service engine mount retainers for surface [damaged, cracked, broken, or missing
information identified in this AD, finish, cracks, and failure, and retainers], their replacement.
contact Goodrich Aerostructures, 850 replacement if necessary. The NPRM This [EASA] AD is considered to be an
Lagoon Drive, Chula Vista, CA 91910– also proposed to require repetitive interim action, pending development and
2098; telephone 619–691–2719; email inspections for damaged, cracked availability of a final solution.
jan.lewis@goodrich.com; Internet http:// broken, and missing aft engine mount You may examine the MCAI in the
www.goodrich.com/TechPubs. retainers, and replacement if necessary. AD docket on the Internet at http://
You may view this referenced service We are issuing this AD to detect and www.regulations.gov by searching for
information at the FAA, Transport correct failure of retainer brackets of the and locating Docket No. FAA–2015–
Airplane Directorate, 1601 Lind Avenue aft engine mount and consequent loss of 3632.
mstockstill on DSK3G9T082PROD with RULES
SW., Renton, WA. For information on the locking feature of the nuts of the
the availability of this material at the inner and outer pins; loss of the pins Comments
FAA, call 425–227–1221. It is also will result in the aft mount engine link We gave the public the opportunity to
available on the Internet at http:// no longer being secured to the aft engine participate in developing this AD. The
www.regulations.gov by searching for mount. following presents the comments
and locating Docket No. FAA–2015– The European Aviation Safety Agency received on the NPRM and the FAA’s
3632. (EASA), which is the Technical Agent response to each comment.
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![44992 Federal Register / Vol. 81, No. 133 / Tuesday, July 12, 2016 / Rules and Regulations
the Administrator finds necessary for (c) Applicability Repeat the detailed inspection specified in
safety in air commerce. This regulation This AD applies to the Airbus airplanes paragraph (g) of this AD.
is within the scope of that authority identified in paragraphs (c)(1) through (c)(4) (2) Within 50 flight cycles after doing the
because it addresses an unsafe condition of this AD, certificated in any category, all first detailed inspection specified in
that is likely to exist or develop on manufacturer serial numbers. paragraph (g) of this AD: Replace all dull
(1) Airbus Model A318–111 and –112 finish retainers with new retainers, in
products identified in this rulemaking
airplanes. accordance with Section 4.2.3.1,
action. (2) Airbus Model A319–111, –112, –113, ‘‘Replacement Procedure,’’ of Airbus AOT
Regulatory Findings –114, and –115 airplanes. A71N001–12, Rev. 2, dated February 27,
(3) Airbus Model A320–211, –212, and 2013.
We determined that this AD will not –214 airplanes.
have federalism implications under (4) Airbus Model A321–111, –112, –211, (j) Retained Replacement of Cracked or
–212, and –213 airplanes. Failed Retainers, With No Changes
Executive Order 13132. This AD will
not have a substantial direct effect on (d) Subject This paragraph restates the requirements of
the States, on the relationship between paragraph (j) of AD 2014–14–06, with no
Air Transport Association (ATA) of changes. If, during any detailed inspection
the national government and the States, America Code 71, Powerplant.
or on the distribution of power and specified in paragraph (g) of this AD, any
(e) Reason installed aft engine mount retainer is found
responsibilities among the various
This AD was prompted by inspection cracked or failed: Before further flight,
levels of government. replace all affected aft engine mount retainers
results that have shown that the main cause
For the reasons discussed above, I of crack initiation in the aft engine mount with new retainers, in accordance with
certify that this AD: retainers is the vibration dynamic effect that Section 4.2.3, ‘‘Replacement Procedure,’’ of
1. Is not a ‘‘significant regulatory affects both retainers, either with ‘‘dull’’ or Airbus AOT A71N001–12, Rev. 2, dated
action’’ under Executive Order 12866; ‘‘bright’’ surface finishes. We are issuing this February 27, 2013.
2. Is not a ‘‘significant rule’’ under the AD to detect and correct failure of retainer
(k) Retained Parts Prohibition, With No
brackets of the aft engine mount and
DOT Regulatory Policies and Procedures consequent loss of the locking feature of the
Changes
(44 FR 11034, February 26, 1979); nuts of the inner and outer pins; loss of the This paragraph restates the requirements of
3. Will not affect intrastate aviation in pins will result in the aft mount engine link paragraph (k) of AD 2014–14–06, with no
Alaska; and no longer being secured to the aft engine changes. As of August 27, 2014 (the effective
4. Will not have a significant mount. date of AD 2014–14–06), no person may
economic impact, positive or negative, install any aft engine mount retainer with a
(f) Compliance
dull finish on any airplane. The instructions
on a substantial number of small entities Comply with this AD within the of Airbus AOT A71N001–12, Rev. 2, dated
under the criteria of the Regulatory compliance times specified, unless already February 27, 2013; or the Accomplishment
Flexibility Act. done. Instructions of Goodrich Service Bulletin
List of Subjects in 14 CFR Part 39 (g) Retained Inspection, With No Changes RA32071–146, Rev. 2, dated July 26, 2012;
This paragraph restates the requirements of may be used to verify the correct finish of the
Air transportation, Aircraft, Aviation part.
paragraph (g) of AD 2014–14–06, with no
safety, Incorporation by reference, changes. Within 3 months after August 27, (l) New Requirement of This AD: Repetitive
Safety. 2014 (the effective date of AD 2014–14–06): Inspections
Adoption of the Amendment Do a detailed inspection of the aft engine
mount retainers for surface finish (dull or At the latest of the applicable times
bright), and for cracks and failure, in specified in paragraphs (l)(1), (l)(2), and (l)(3)
Accordingly, under the authority
accordance with Section 4.2.2, ‘‘Inspection of this AD: Do a detailed inspection for
delegated to me by the Administrator, damaged, cracked, broken, or missing aft
the FAA amends 14 CFR part 39 as Requirements,’’ of Airbus Alert Operators
Transmission (AOT) A71N001–12, Rev. 2, engine mount retainers, in accordance with
follows: dated February 27, 2013, except as specified the Accomplishment Instructions of Airbus
in paragraph (h) of this AD. Service Bulletin A320–71–1060, Revision 01,
PART 39—AIRWORTHINESS dated April 7, 2015; or Goodrich Service
DIRECTIVES (h) Retained Exception to Paragraph (g) of Bulletin RA32071–160, dated September 18,
This AD, With No Changes
2014. Repeat the inspection of the aft engine
■ 1. The authority citation for part 39 This paragraph restates the requirements of mount retainers thereafter at intervals not to
continues to read as follows: paragraph (h) of AD 2014–14–06, with no exceed 12 months.
changes. The actions required by paragraph (1) Within 12 months since the date of
Authority: 49 U.S.C. 106(g), 40113, 44701. (g) of this AD are not required to be done on issuance of the original airworthiness
§ 39.13 [Amended] airplanes with manufacturer serial numbers certificate or the date of issuance of the
4942 and higher, provided a review of original export certificate of airworthiness.
■ 2. The FAA amends § 39.13 by maintenance records verifies that no aft (2) Within 12 months after installation of
removing Airworthiness Directive (AD) engine mount retainers have been replaced
new retainers.
2014–14–06, Amendment 39–17901 (79 since first flight of the airplane.
(3) Within 9 months after the effective date
FR 42655, July 23, 2014), and adding the (i) Retained Repetitive Inspection and of this AD.
following new AD: Retainer Replacement for Dull Finish
Retainers, With No Changes (m) New Requirement of This AD:
2016–14–09 Airbus: Amendment 39–18590. Replacement of Retainers With Findings
Docket No. FAA–2015–3632; Directorate This paragraph restates the requirements of
paragraph (i) of AD 2014–14–06, with no If, during any detailed inspection specified
Identifier 2015–NM–023–AD.
in paragraph (l) of this AD, any installed aft
mstockstill on DSK3G9T082PROD with RULES
changes. If, during the detailed inspection
(a) Effective Date required by paragraph (g) of this AD, any engine mount retainer is found damaged,
This AD is effective August 16, 2016. installed dull finish aft engine mount retainer cracked, broken, or missing: Before further
is found without cracks and not failed: Do flight, replace all affected aft engine mount
(b) Affected ADs the actions specified in paragraphs (i)(1) and retainers with new retainers, in accordance
This AD replaces AD 2014–14–06, (i)(2) of this AD. with the Accomplishment Instructions of
Amendment 39–17901 (79 FR 42655, July 23, (1) Within 25 flight cycles after doing the Airbus Service Bulletin A320–71–1060,
2014) (‘‘AD 2014–14–06’’). actions required by paragraph (g) of this AD: Revision 01, dated April 7, 2015.
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![Federal Register / Vol. 81, No. 133 / Tuesday, July 12, 2016 / Rules and Regulations 44993
(n) New Requirement of This AD: No Avenue SW., Renton, WA 98057–3356; Airworthiness Directive 2015–0021, dated
Terminating Action telephone 425–227–1405; fax 425–227–1149. February 13, 2015, for related information.
Replacement of retainers on an airplane, as Information may be emailed to: 9-ANM-116- This MCAI may be found in the AD docket
required by paragraph (m) of this AD, does AMOC-REQUESTS@faa.gov. on the Internet at http://www.regulations.gov
not constitute terminating action for the (i) Before using any approved AMOC, by searching for and locating Docket No.
repetitive inspections required by paragraph notify your appropriate principal inspector,
FAA–2015–3632.
(l) of this AD for that airplane. or lacking a principal inspector, the manager
of the local flight standards district office/ (2) Service information identified in this
(o) New Requirement of This AD: Required certificate holding district office. The AMOC AD that is not incorporated by reference is
Reporting approval letter must specifically reference available at the addresses specified in
this AD. paragraphs (t)(5), (t)(6), and (t)(7) of this AD.
Submit a report of positive findings of any
inspection required by paragraph (l) of this (ii) AMOCs approved previously for AD
2014–14–06, are approved as AMOCs for the (t) Material Incorporated by Reference
AD to Airbus at the applicable time specified
in paragraph (o)(1) or (o)(2) of this AD. The corresponding provisions of paragraphs (g), (1) The Director of the Federal Register
report must include the inspection results, a (i), (j), and (k) of this AD. approved the incorporation by reference
description of any discrepancies found, the (2) Contacting the Manufacturer: As of the (IBR) of the service information listed in this
airplane serial number, and the number of effective date of this AD, for any requirement paragraph under 5 U.S.C. 552(a) and 1 CFR
landings and flight hours on the airplane. in this AD to obtain corrective actions from part 51.
(1) If the inspection was done on or after a manufacturer, the action must be
(2) You must use this service information
the effective date of this AD: Submit the accomplished using a method approved by
as applicable to do the actions required by
report within 30 days after the inspection. the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or this AD, unless this AD specifies otherwise.
(2) If the inspection was done before the (3) The following service information was
effective date of this AD: Submit the report the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design approved for IBR on August 16, 2016.
within 30 days after the effective date of this (i) Airbus Service Bulletin A320–71–1060,
Organization Approval (DOA). If approved by
AD.
the DOA, the approval must include the Revision 01, dated April 7, 2015.
(p) Credit for Previous Actions DOA-authorized signature. (ii) Goodrich Service Bulletin RA32071–
(1) This paragraph restates the provisions (3) Reporting Requirements: A federal 160, dated September 18, 2014.
of paragraph (l) of AD 2014–14–06, with no agency may not conduct or sponsor, and a (4) The following service information was
changes. This paragraph provides credit for person is not required to respond to, nor approved for IBR on August 27, 2014 (79 FR
actions required by paragraphs (g), (i), and (j) shall a person be subject to a penalty for 42655, July 23, 2014).
of this AD, if those actions were performed failure to comply with a collection of (i) Airbus Alert Operators Transmission
before August 27, 2014 (the effective date of information subject to the requirements of
A71N001–12, Rev. 2, dated February 27,
AD 2014–14–06) using Airbus AOT the Paperwork Reduction Act unless that
collection of information displays a current 2013. The first page of this document
A71N001–12, Rev. 1, dated August 9, 2012. contains the document number, revision, and
valid OMB Control Number. The OMB
This service information is not incorporated date; no other page of this document contains
Control Number for this information
by reference in this AD. this information.
collection is 2120–0056. Public reporting for
(2) This paragraph provides credit for (ii) Goodrich Service Bulletin RA32071–
this collection of information is estimated to
actions required by paragraph (l) of this AD,
be approximately 5 minutes per response, 146, Rev. 2, dated July 26, 2012.
if those actions were performed before the
including the time for reviewing instructions, (5) For Airbus service information
effective date of this AD using Airbus Service
completing and reviewing the collection of identified in this AD, contact Airbus,
Bulletin A320–71–1060, dated October 9,
information. All responses to this collection Airworthiness Office—EIAS, 1 Rond Point
2014. Airbus Service Bulletin A320–71–1060, of information are mandatory. Comments
dated October 9, 2014, is not incorporated by Maurice Bellonte, 31707 Blagnac Cedex,
concerning the accuracy of this burden and France; telephone +33 5 61 93 36 96; fax +33
reference in this AD. suggestions for reducing the burden should
(3) This paragraph provides credit for 5 61 93 44 51; email account.airworth-eas@
be directed to the FAA at: 800 Independence
actions required by paragraph (m) of this AD, airbus.com; Internet http://www.airbus.com.
Ave. SW., Washington, DC 20591, Attn:
if those actions were performed before the Information Collection Clearance Officer, (6) For Goodrich Aerostructures service
effective date of this AD using Airbus Service AES–200. information identified in this AD, contact
Bulletin A320–71–1060, dated October 9, (4) Required for Compliance (RC): If any Goodrich Aerostructures, 850 Lagoon Drive,
2014, provided that it can be conclusively Airbus service information contains Chula Vista, CA 91910–2098; telephone 619–
determined that the torque value units procedures or tests that are identified as RC, 691–2719; email jan.lewis@goodrich.com;
applicable to nut item (14) that are specified those procedures and tests must be done to Internet http://www.goodrich.com/TechPubs.
in Airbus Service Bulletin A320–71–1060, comply with this AD; any procedures or tests (7) You may view this service information
Revision 01, dated April 7, 2015, have been that are not identified as RC are at the FAA, Transport Airplane Directorate,
used. Airbus Service Bulletin A320–71–1060, recommended. Those procedures and tests 1601 Lind Avenue SW., Renton, WA. For
dated October 9, 2014, is not incorporated by that are not identified as RC may be deviated
reference in this AD. information on the availability of this
from using accepted methods in accordance material at the FAA, call 425–227–1221.
(q) Other FAA AD Provisions with the operator’s maintenance or
(8) You may view this service information
inspection program without obtaining
The following provisions also apply to this that is incorporated by reference at the
approval of an AMOC, provided the
AD: procedures and tests identified as RC can be National Archives and Records
(1) Alternative Methods of Compliance done and the airplane can be put back in a Administration (NARA). For information on
(AMOCs): The Manager, International serviceable condition. Any substitutions or the availability of this material at NARA, call
Branch, ANM–116, Transport Airplane changes to procedures or tests identified as 202–741–6030, or go to: http://
Directorate, FAA, has the authority to RC require approval of an AMOC. www.archives.gov/federal-register/cfr/ibr-
approve AMOCs for this AD, if requested locations.html.
using the procedures found in 14 CFR 39.19. (r) Special Flight Permits
Issued in Renton, Washington, on July 1,
mstockstill on DSK3G9T082PROD with RULES
In accordance with 14 CFR 39.19, send your Special flight permits, as described in
request to your principal inspector or local Section 21.197 and Section 21.199 of the 2016.
Flight Standards District Office, as Federal Aviation Regulations (14 CFR 21.197 Phillip Forde,
appropriate. If sending information directly and 21.199), are not allowed. Acting Manager, Transport Airplane
to the International Branch, send it to ATTN:
(s) Related Information Directorate, Aircraft Certification Service.
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport (1) Refer to Mandatory Continuing [FR Doc. 2016–16212 Filed 7–11–16; 8:45 am]
Airplane Directorate, FAA, 1601 Lind Airworthiness Information (MCAI) EASA BILLING CODE 4910–13–P
VerDate Sep<11>2014 17:56 Jul 11, 2016 Jkt 238001 PO 00000 Frm 00013 Fmt 4700 Sfmt 9990 E:\FR\FM\12JYR1.SGM 12JYR1](https://thefederalregister.org/doc/81_FR_45122/page/5.svg)
Document Created: 2016-07-12 01:59:09
Document Modified: 2016-07-12 01:59:09
| 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 is effective August 16, 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 44989 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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