Airworthiness Directives; Airbus Airplanes, 34287-34290 [2016-12593]

Download as PDF Federal Register / Vol. 81, No. 104 / Tuesday, May 31, 2016 / Proposed Rules hooks and the eccentric bush at FR60 through FR64A. If any value outside tolerance is found, adjust the latching hook before further flight. (2) Do a one-time detailed inspection to detect signs of wear of the hooks, eccentric bushes, and x-stops. If any wear is found, do all applicable corrective actions before further flight. (3) Do a high frequency eddy current (HFEC) inspection to detect cracking at all frame fork stations of the aft LDCD. If any crack is found, replace the cracked frame fork before further flight. Repeat the HFEC inspection thereafter at intervals not to exceed 600 flight cycles. (h) Compliance Times At the later of the times specified in paragraphs (h)(1) and (h)(2) of this AD, do the actions required by paragraph (g) of this AD. (1) Before the accumulation of 4,500 total flight cycles. (2) At the applicable time specified by paragraph (h)(2)(i) or (h)(2)(ii) of this AD. (i) For airplanes that have accumulated 8,000 or more total flight cycles as of the effective date this AD: Within 100 flight cycles after the effective date of this AD. (ii) For airplanes that have accumulated fewer than 8,000 total flight cycles as of the effective date of this AD: Within 400 flight cycles after the effective date of this AD. asabaliauskas on DSK3SPTVN1PROD with PROPOSALS (i) Reporting At the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, report the findings (both positive and negative) of the clearance check and detailed inspection required by paragraphs (g)(1) and (g)(2) of this AD, and each HFEC inspection required by paragraph (g)(3) of this AD. Send the report to Airbus in accordance with paragraph 7 of Airbus AOT A52W011–15, Revision 00, dated July 23, 2015. The report must include the applicable information specified in Appendix 2 of Airbus AOT A52W011–15, Revision 00, dated July 23, 2015. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 60 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 60 days after the effective date of this AD. (j) Post-Repair Provisions (1) Accomplishment of corrective actions required by this AD does not terminate the repetitive HFEC inspections required by paragraph (g)(3) of this AD. (2) If all frame forks are replaced at the same time on the aft LDCD of an airplane, the next HFEC inspection required by paragraph (g)(3) of this AD can be deferred up to 4,500 flight cycles after the frame fork replacement. (k) 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. VerDate Sep<11>2014 18:42 May 27, 2016 Jkt 238001 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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 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. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Airworthiness Directive 2015–0152, dated July 24, 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– 2016–6894. (2) 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 account.airwortheas@airbus.com; Internet http:// www.airbus.com. 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. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 34287 Issued in Renton, Washington, on May 18, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–12522 Filed 5–27–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6896; Directorate Identifier 2016–NM–016–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A318–111, and –112 airplanes, Model A319–111, –112, –113, –114, and –115 airplanes, Model A320– 211, –212 and –214 airplanes, and Model A321–111, –112, –211, –212, and –213 airplanes. This proposed AD was prompted by a report of a production quality deficiency on the inner retainer installed on link assemblies of the engine mount, which could result in failure of the retainer. This proposed AD would require an inspection for, and replacement of, all non-conforming aft engine mount retainers. We are proposing this AD to detect and correct non-conforming retainers of the aft engine mount. This condition could result in the 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, possibly resulting in damage to the airplane and injury to persons on the ground. SUMMARY: We must receive comments on this proposed AD by July 15, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. DATES: E:\FR\FM\31MYP1.SGM 31MYP1 34288 Federal Register / Vol. 81, No. 104 / Tuesday, May 31, 2016 / Proposed Rules • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For Airbus service information identified in this NPRM, 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: account.airworth-eas@airbus.com; Internet: http://www.airbus.com. For Goodrich service information identified in this NPRM, contact Goodrich Corporation, Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910–2098; telephone: 619–691–2719; email: jan.lewis@goodrich.com; 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. asabaliauskas on DSK3SPTVN1PROD with PROPOSALS 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–2016– 6896; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–6896; Directorate Identifier 2016–NM–016–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// VerDate Sep<11>2014 18:42 May 27, 2016 Jkt 238001 www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2016–0010R1, dated February 16, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A318–111, and –112 airplanes, Model A319–111, –112, –113, –114, and –115 airplanes, Model A320–211, –212, and –214 airplanes, and Model A321– 111, –112, –211, –212, and –213 airplanes. The MCAI states: During in-service inspections, several aft engine mount inner 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/or injury to persons 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, Amendment 39–17901 (79 FR 42655, July 23, 2014)] to require a detailed inspection (DET) of the aft engine mount inner retainers and the replacement of all retainers with dull finish with retainers having a bright finish. Since that [EASA] AD was issued, inspection results showed that the main cause of crack initiation remains the vibration dynamic effect that affects both retainers, either with ‘‘dull’’ or ‘‘bright’’ surface finishes. The nonconforming ‘‘dull’’ surface’s pitting is an aggravating factor. Consequently, EASA issued AD 2015–0021 [http:// ad.easa.europa.eu/blob/EASA_AD_2015_ 0021_superseded.pdf/AD_2015–0021_1] [which corresponds to FAA NPRM Docket No. FAA–2015–3632; Directorate Identifier PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 2015–NM–023–AD (80 FR 55798, September 7, 2015)], retaining the requirements of EASA AD 2013–0050, which was superseded, and requiring repetitive DET of all aft engine mount inner retainers and, depending on findings, their replacement. Since that [EASA] AD was issued, a production quality deficiency was identified by Airbus and UTAS (formerly Goodrich Aerostructures, the engine mount retainer manufacturer) on the delivery of the inner retainer, Part Number (P/N) 238–0252–505, installed in the three Link assemblies of the engine mount fitted on CFM56–5A/5B engines. Airbus issued AOT A71N011–15 and SB A320–71–1070 providing a list of affected parts and applicable corrective actions. Consequently, EASA issued [a new] AD * * *, retaining the requirements of EASA AD 2015–0021, which was superseded, and in addition requiring the identification and replacement of all non-conforming aft engine mount inner retainers. Since that [new EASA] AD was issued, AOT A71N011–15 was revised, removing errors and reducing the list of affected parts. For the reason described above, this [EASA] AD is revised, adding reference to the revised AOT, and removing [EASA] AD appendixes, which content is included in the referenced Airbus documentation. This [EASA] AD is still considered to be an interim action, pending development and availability of a final solution. This proposed AD would require an inspection for, and replacement of, all non-conforming aft engine mount retainers. 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–2016– 6896. Related Service Information Under 1 CFR Part 51 We reviewed the following service information. This service information describes procedures for replacement of all non-conforming aft engine mount retainers. • Airbus Service Bulletin A320–71– 1070, dated November 23, 2015. This service information also describes procedures for an inspection for nonconforming aft engine mount retainers. • Airbus Alert Operators Transmission (AOT) A71N011–15, Revision 01, dated February 1, 2016. • Goodrich Service Bulletin RA32071–165, dated October 9, 2015. 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. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation E:\FR\FM\31MYP1.SGM 31MYP1 Federal Register / Vol. 81, No. 104 / Tuesday, May 31, 2016 / Proposed Rules in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. 34289 Costs of Compliance We estimate that this proposed AD affects 959 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspection ............................. 4 work-hours × $85 per hour = $340 .................................. We estimate the following costs to do any necessary replacements that would Cost per product Parts cost be required based on the results of the proposed inspection. We have no way of $0 $340 Cost on U.S. operators Up to $326,060. determining the number of airplanes that might need these replacements: ON-CONDITION COSTS Labor cost Replacement ................................... Up to 36 work-hours × $85 per hour = $3,060 ..................................... Authority for This Rulemaking 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. (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. List of Subjects in 14 CFR Part 39 (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. 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. asabaliauskas on DSK3SPTVN1PROD with PROPOSALS Regulatory Findings VerDate Sep<11>2014 18:42 May 27, 2016 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 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); Jkt 238001 Parts cost Cost per product Action [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2016–6896; Directorate Identifier 2016–NM–016–AD. (a) Comments Due Date We must receive comments by July 15, 2016. (b) Affected ADs None. (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. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 $10,000 Up to $13,060. (e) Reason This AD was prompted by a report of a production quality deficiency on the inner retainer installed on link assemblies of the engine mount, which could result in failure of the retainer. We are issuing this AD to detect and correct non-conforming retainers of the aft engine mount. This condition could result in 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, possibly resulting in damage to the airplane and injury to persons on the ground. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection and Replacement Within 2 months after the effective date of this AD, do an inspection to determine the part number of each engine mount inner retainer; and within 2 months after the effective date of this AD, replace each part that meets any of the criteria specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. Do the inspection in accordance with the service information specified in paragraph (h)(1) of this AD. Do the replacement in accordance with the service information specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD. A review of airplane maintenance records is acceptable in lieu of the inspection required by this paragraph, if the part E:\FR\FM\31MYP1.SGM 31MYP1 34290 Federal Register / Vol. 81, No. 104 / Tuesday, May 31, 2016 / Proposed Rules number of the engine mount inner retainer can be conclusively determined from that review. (1) An aft engine mount having a serial number listed in table 1 of Airbus Alert Operators Transmission (AOT) A71N011–15, Rev 01, dated February 1, 2016. (2) An engine mount inner retainer installed on an airplane between the first flight of the airplane or March 1, 2015 (whichever occurs later), and the effective date of this AD, and that can be identified by a purchase order (PO) listed in table 2 of Airbus AOT A71N011–15, Rev 01, dated February 1, 2016. (3) An engine mount inner retainer installed on an airplane between the first flight of the airplane or March 1, 2015 (whichever occurs later), and the effective date of this AD, and that cannot be identified by a PO. (h) Service Information for Actions Required by Paragraph (g) of This AD Accomplish the replacement required by paragraph (g) of this AD in accordance with the service information specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD. (1) The Accomplishment Instructions of Airbus Service Bulletin A320–71–1070, dated November 23, 2015. (2) Paragraph 4.2.2, ‘‘Requirements,’’ of Airbus AOT A71N011–15, Revision 01, dated February 1, 2016. (3) The Accomplishment Instructions of Goodrich Service Bulletin RA32071–165, dated October 9, 2015. (i) Credit for Previous Actions This paragraph provides credit for the applicable actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus AOT A71N011–15, Revision 01, dated February 1, 2016, which is not incorporated by reference in this AD. asabaliauskas on DSK3SPTVN1PROD with PROPOSALS (j) Parts Installation Prohibition As of the effective date of this AD, no person may install any part that meets any of the criteria specified in paragraph (j)(1), (j)(2), (j)(3) of this AD on any airplane. (1) An aft engine mount having a serial number listed in table 1 of Airbus AOT A71N011–15, Rev 01, dated February 1, 2016. (2) An engine mount inner retainer delivered through a PO listed in table 2 of Airbus AOT A71N011–15, Rev 01, dated February 1, 2016. (3) An engine mount inner retainer delivered through an unidentified PO. (m) Related Information (k) 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. (l) 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 VerDate Sep<11>2014 18:42 May 27, 2016 Jkt 238001 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: 9ANM-116-AMOC-REQUESTS@faa.gov. 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 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) Required for Compliance (RC): If any 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 an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016–0010R1, dated February 16, 2016, 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–2016–6896. (2) 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: account.airwortheas@airbus.com; Internet: http:// www.airbus.com. For Goodrich service information identified in this AD, contact Goodrich Corporation, Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910–2098; telephone: 619–691–2719; email: jan.lewis@ goodrich.com; Internet: http:// www.goodrich.com/TechPubs. 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. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Issued in Renton, Washington, on May 20, 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–12593 Filed 5–27–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOUSING AND URBAN DEVELOPMENT 24 CFR Part 1000 [Docket No. FR–5650–P–12] RIN 2577–AC90 Native American Housing Assistance and Self-Determination Act; Revisions to the Indian Housing Block Grant Program Formula Office of the Assistant Secretary for Public and Indian Housing, HUD. ACTION: Proposed rule. AGENCY: This proposed rule would revise the Indian Housing Block Grant (IHBG) Program allocation formula authorized by section 302 of the Native American Housing Assistance and SelfDetermination Act of 1996, as amended (NAHASDA). Through the IHBG Program, HUD provides federal housing assistance for Indian tribes in a manner that recognizes the right of Indian selfdetermination and tribal selfgovernment. HUD negotiated the proposed rule with active tribal participation and using the procedures of the Negotiated Rulemaking Act of 1990. The proposed regulatory changes reflect the consensus decisions reached by HUD and the tribal representatives on ways to improve and clarify the current regulations governing the IHBG Program formula. DATES: Comment Due Date: August 1, 2016. ADDRESSES: Interested persons are invited to submit comments regarding this proposed rule to the Regulations Division, Office of General Counsel, Department of Housing and Urban Development, 451 7th Street SW., Room 10276, Washington, DC 20410–0500. Communications must refer to the above docket number and title. There are two methods for submitting public comments. All submissions must refer to the above docket number and title. 1. Submission of Comments by Mail. Comments may be submitted by mail to the Regulations Division, Office of General Counsel, Department of Housing and Urban Development, 451 7th Street SW., Room 10276, Washington, DC 20410–0500. SUMMARY: E:\FR\FM\31MYP1.SGM 31MYP1

Agencies

[Federal Register Volume 81, Number 104 (Tuesday, May 31, 2016)]
[Proposed Rules]
[Pages 34287-34290]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-12593]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6896; Directorate Identifier 2016-NM-016-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A318-111, and -112 airplanes, Model A319-111, -112, -113, 
-114, and -115 airplanes, Model A320-211, -212 and -214 airplanes, and 
Model A321-111, -112, -211, -212, and -213 airplanes. This proposed AD 
was prompted by a report of a production quality deficiency on the 
inner retainer installed on link assemblies of the engine mount, which 
could result in failure of the retainer. This proposed AD would require 
an inspection for, and replacement of, all non-conforming aft engine 
mount retainers. We are proposing this AD to detect and correct non-
conforming retainers of the aft engine mount. This condition could 
result in the 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, possibly resulting in 
damage to the airplane and injury to persons on the ground.

DATES: We must receive comments on this proposed AD by July 15, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.

[[Page 34288]]

     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For Airbus service information identified in this NPRM, 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: account.airworth-eas@airbus.com; Internet: http://www.airbus.com.
    For Goodrich service information identified in this NPRM, contact 
Goodrich Corporation, Aerostructures, 850 Lagoon Drive, Chula Vista, CA 
91910-2098; telephone: 619-691-2719; email: jan.lewis@goodrich.com; 
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.

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-2016-
6896; 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-6896; 
Directorate Identifier 2016-NM-016-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0010R1, dated February 16, 2016 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A318-111, and -112 airplanes, Model A319-111, -112, -113, -114, and -
115 airplanes, Model A320-211, -212, and -214 airplanes, and Model 
A321-111, -112, -211, -212, and -213 airplanes. The MCAI states:

    During in-service inspections, several aft engine mount inner 
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/or injury to persons 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, Amendment 39-17901 (79 FR 42655, July 23, 
2014)] to require a detailed inspection (DET) of the aft engine 
mount inner retainers and the replacement of all retainers with dull 
finish with retainers having a bright finish. Since that [EASA] AD 
was issued, inspection results showed 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. 
Consequently, EASA issued AD 2015-0021 [http://ad.easa.europa.eu/blob/EASA_AD_2015_0021_superseded.pdf/AD_2015-0021_1] [which 
corresponds to FAA NPRM Docket No. FAA-2015-3632; Directorate 
Identifier 2015-NM-023-AD (80 FR 55798, September 7, 2015)], 
retaining the requirements of EASA AD 2013-0050, which was 
superseded, and requiring repetitive DET of all aft engine mount 
inner retainers and, depending on findings, their replacement.
    Since that [EASA] AD was issued, a production quality deficiency 
was identified by Airbus and UTAS (formerly Goodrich Aerostructures, 
the engine mount retainer manufacturer) on the delivery of the inner 
retainer, Part Number (P/N) 238-0252-505, installed in the three 
Link assemblies of the engine mount fitted on CFM56-5A/5B engines. 
Airbus issued AOT A71N011-15 and SB A320-71-1070 providing a list of 
affected parts and applicable corrective actions.
    Consequently, EASA issued [a new] AD * * *, retaining the 
requirements of EASA AD 2015-0021, which was superseded, and in 
addition requiring the identification and replacement of all non-
conforming aft engine mount inner retainers.
    Since that [new EASA] AD was issued, AOT A71N011-15 was revised, 
removing errors and reducing the list of affected parts.
    For the reason described above, this [EASA] AD is revised, 
adding reference to the revised AOT, and removing [EASA] AD 
appendixes, which content is included in the referenced Airbus 
documentation.
    This [EASA] AD is still considered to be an interim action, 
pending development and availability of a final solution.

    This proposed AD would require an inspection for, and replacement 
of, all non-conforming aft engine mount retainers. 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-2016-6896.

Related Service Information Under 1 CFR Part 51

    We reviewed the following service information. This service 
information describes procedures for replacement of all non-conforming 
aft engine mount retainers.
     Airbus Service Bulletin A320-71-1070, dated November 23, 
2015. This service information also describes procedures for an 
inspection for non-conforming aft engine mount retainers.
     Airbus Alert Operators Transmission (AOT) A71N011-15, 
Revision 01, dated February 1, 2016.
     Goodrich Service Bulletin RA32071-165, dated October 9, 
2015.
    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.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation

[[Page 34289]]

in the United States. Pursuant to our bilateral agreement with the 
State of Design Authority, we have been notified of the unsafe 
condition described in the MCAI and service information referenced 
above. We are proposing this AD because we evaluated all pertinent 
information and determined an unsafe condition exists and is likely to 
exist or develop on other products of these same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 959 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                            Cost per
             Action                    Labor cost          Parts cost        product     Cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
Inspection.....................  4 work-hours x $85 per              $0            $340  Up to $326,060.
                                  hour = $340.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of airplanes that might need 
these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
               Action                          Labor cost             Parts cost          Cost per  product
----------------------------------------------------------------------------------------------------------------
Replacement.........................  Up to 36 work-hours x $85            $10,000  Up to $13,060.
                                       per hour = $3,060.
----------------------------------------------------------------------------------------------------------------

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

Airbus: Docket No. FAA-2016-6896; Directorate Identifier 2016-NM-
016-AD.

(a) Comments Due Date

    We must receive comments by July 15, 2016.

(b) Affected ADs

    None.

(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 a report of a production quality 
deficiency on the inner retainer installed on link assemblies of the 
engine mount, which could result in failure of the retainer. We are 
issuing this AD to detect and correct non-conforming retainers of 
the aft engine mount. This condition could result in 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, possibly resulting in damage to the 
airplane and injury to persons on the ground.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspection and Replacement

    Within 2 months after the effective date of this AD, do an 
inspection to determine the part number of each engine mount inner 
retainer; and within 2 months after the effective date of this AD, 
replace each part that meets any of the criteria specified in 
paragraph (g)(1), (g)(2), or (g)(3) of this AD. Do the inspection in 
accordance with the service information specified in paragraph 
(h)(1) of this AD. Do the replacement in accordance with the service 
information specified in paragraph (h)(1), (h)(2), or (h)(3) of this 
AD. A review of airplane maintenance records is acceptable in lieu 
of the inspection required by this paragraph, if the part

[[Page 34290]]

number of the engine mount inner retainer can be conclusively 
determined from that review.
    (1) An aft engine mount having a serial number listed in table 1 
of Airbus Alert Operators Transmission (AOT) A71N011-15, Rev 01, 
dated February 1, 2016.
    (2) An engine mount inner retainer installed on an airplane 
between the first flight of the airplane or March 1, 2015 (whichever 
occurs later), and the effective date of this AD, and that can be 
identified by a purchase order (PO) listed in table 2 of Airbus AOT 
A71N011-15, Rev 01, dated February 1, 2016.
    (3) An engine mount inner retainer installed on an airplane 
between the first flight of the airplane or March 1, 2015 (whichever 
occurs later), and the effective date of this AD, and that cannot be 
identified by a PO.

(h) Service Information for Actions Required by Paragraph (g) of This 
AD

    Accomplish the replacement required by paragraph (g) of this AD 
in accordance with the service information specified in paragraph 
(h)(1), (h)(2), or (h)(3) of this AD.
    (1) The Accomplishment Instructions of Airbus Service Bulletin 
A320-71-1070, dated November 23, 2015.
    (2) Paragraph 4.2.2, ``Requirements,'' of Airbus AOT A71N011-15, 
Revision 01, dated February 1, 2016.
    (3) The Accomplishment Instructions of Goodrich Service Bulletin 
RA32071-165, dated October 9, 2015.

(i) Credit for Previous Actions

    This paragraph provides credit for the applicable actions 
required by paragraph (g) of this AD, if those actions were 
performed before the effective date of this AD using Airbus AOT 
A71N011-15, Revision 01, dated February 1, 2016, which is not 
incorporated by reference in this AD.

(j) Parts Installation Prohibition

    As of the effective date of this AD, no person may install any 
part that meets any of the criteria specified in paragraph (j)(1), 
(j)(2), (j)(3) of this AD on any airplane.
    (1) An aft engine mount having a serial number listed in table 1 
of Airbus AOT A71N011-15, Rev 01, dated February 1, 2016.
    (2) An engine mount inner retainer delivered through a PO listed 
in table 2 of Airbus AOT A71N011-15, Rev 01, dated February 1, 2016.
    (3) An engine mount inner retainer delivered through an 
unidentified PO.

(k) 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.

(l) 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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 
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) Required for Compliance (RC): If any 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 an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0010R1, dated February 16, 2016, 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-2016-6896.
    (2) 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: account.airworth-eas@airbus.com; 
Internet: http://www.airbus.com. For Goodrich service information 
identified in this AD, contact Goodrich Corporation, Aerostructures, 
850 Lagoon Drive, Chula Vista, CA 91910-2098; telephone: 619-691-
2719; email: jan.lewis@goodrich.com; Internet: http://www.goodrich.com/TechPubs. 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.

    Issued in Renton, Washington, on May 20, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-12593 Filed 5-27-16; 8:45 am]
 BILLING CODE 4910-13-P