81 FR 38573 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 114 (June 14, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 114 (June 14, 2016)
| Page Range | 38573-38576 | |
| FR Document | 2016-13856 |
[Federal Register Volume 81, Number 114 (Tuesday, June 14, 2016)] [Rules and Regulations] [Pages 38573-38576] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-13856] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6899; Directorate Identifier 2016-NM-066-AD; Amendment 39-18558; AD 2016-12-09] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2016-09-11 for certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200 and -300 series airplanes. AD 2016-09-11 required removing fasteners, doing a rototest inspection of fastener holes, installing new fasteners, oversizing the holes and doing rototest inspections for cracks if necessary, and repairing any cracking that is found. This new AD requires the same actions as AD 2016-09-11, but includes Model A330-300 series airplanes in paragraph (g)(2) of this AD. This AD was prompted by the discovery of missing affected airplanes in paragraph (g)(2) of AD 2016-09-11 that resulted from converting a table in the proposed AD to text in AD 2016-09-11. We are issuing this AD to detect and correct cracking on certain holes of certain frames of the center wing box (CWB), which could affect the structural integrity of the airplane. DATES: This AD is effective June 29, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 13, 2016 (81 FR 27986, May 9, 2016). We must receive comments on this AD by July 29, 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. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: [email protected]; Internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 6899. 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- 6899; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion On April 21, 2016, we issued AD 2016-09-11, Amendment 39-18509 (81 FR 27986, May 9, 2016) (``AD 2016-09-11''), for certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200 and -300 series airplanes. AD 2016-09-11 was prompted by reports that cracks were found on an adjacent hole of certain frames of the CWB. AD 2016-09-11 required removing fasteners, doing a rototest inspection of fastener holes, installing new fasteners, oversizing the holes and doing rototest inspections for cracks if necessary, and repairing any cracking that was found. We issued AD 2016-09-11 to detect and correct cracking on certain holes of certain frames of the CWB that could affect the structural integrity of the airplane. Since we issued AD 2016-09-11, we discovered missing affected airplanes in paragraph (g)(2) of AD 2016-09-11 that resulted from converting a table to text in that AD. We stated in the preamble of AD 2016-09-11 that we revised the format of paragraph (g) of that AD, at the request of the Office of the Federal Register, by converting the table to text. We also stated this change to the format does not affect the requirements of that paragraph. However, in converting the table to text, we inadvertently omitted Model A330-300 series airplanes from paragraph (g)(2) of AD 2016-09-11. We have changed paragraph (g)(2) of this AD to include Model A330-300 series airplanes. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0149, dated June 13, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200 and -300 series airplanes. The MCAI states: During accomplishment of A330 Airworthiness Limitation Item (ALI) task 57-11-04 on the rear fitting of the Frame (FR) 40 between stringers 38 and 39 on both [left-hand] LH/[right-hand] RH sides, cracks were found on an adjacent hole. After reaming at second oversize of the subject hole, the crack was still present. Other crack findings on this adjacent hole have been reported on A330 and A340-200/-300 aeroplanes as a result of sampling inspections. [[Page 38574]] This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. For the reasons described above, this [EASA] AD requires removal of the fasteners and repetitive rototest inspections of fastener holes at FR40 vertical web located above Center Wing Box (CWB) lower panel reference and/or below CWB lower panel reference on both sides and, depending on findings, accomplishment of the applicable corrective actions. Note: These holes affected by this [EASA] AD are different from the ones affected by EASA AD 2009-0001 [http://ad.easa.europa.eu/blob/easa_ad_2009_0001.pdf/AD_2009-0001_1]. Required actions also include oversizing certain holes, installing new fasteners, and repairing any cracking that is found. The initial compliance times range from 13,500 to 30,900 flight cycles, or 57,000 to 162,000 flight hours, depending on airplane operation and utilization. The repetitive compliance times are 7,400 flight cycles/ 24,300 flight hours or 5,950 flight cycles/40,400 flight hours from ALI embodiment. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 6899. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. The service information describes procedures for removing the fasteners and doing a repetitive rototest inspection of fastener holes at FR40 vertical web on both sides, installing new fasteners in transition fit, and oversizing the holes. Airbus Service Bulletin A330-57-3114, dated March 12, 2013. Airbus Service Bulletin A330-57-3115, dated April 4, 2013. Airbus Service Bulletin A330-57-3116, dated March 12, 2013. Airbus Service Bulletin A340-57-4123, dated March 12, 2013. Airbus Service Bulletin A340-57-4124, Revision 01, dated August 22, 2013. Airbus Service Bulletin A340-57-4125, dated March 12, 2013. 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 AD This product has been approved by the aviation authority of another country, and is approved for operation 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 issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of these same type designs. FAA's Justification and Determination of the Effective Date We are superseding AD 2016-09-11 to correct an error in the regulatory text that we made when we converted a table to text in paragraph (g)(2) of AD 2016-09-11. No other changes have been made to AD 2016-09-11. Therefore, we determined that notice and opportunity for prior public comment are unnecessary. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-6899; Directorate Identifier 2016-NM-066-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of 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 AD. Costs of Compliance We estimate that this AD affects 35 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection................ 78 work-hours x $85 $0 $6,630 per inspection $232,050 per per hour = $6,630 cycle. inspection cycle. per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that will be required based on the results of the inspection. We have no way of determining the number of airplanes that might need this repair: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Oversize, installation, and inspection....... 98 work-hours x $85 per hour = $136,400 $144,730 $8,330. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that will enable us to provide cost estimates for the on-condition repair specified in this AD. 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 [[Page 38575]] promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. 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) 2016-09-11, Amendment 39-18509 (81 FR 27986, May 9, 2016), and adding the following new AD: 2016-12-09 Airbus: Amendment 39-18558. Docket No. FAA-2016-6899; Directorate Identifier 2016-NM-066-AD. (a) Effective Date This AD is effective June 29, 2016. (b) Affected ADs This AD replaces AD 2016-09-11, Amendment 39-18509 (81 FR 27986, May 9, 2016) (``AD 2016-09-11''). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification (Mod) 55792 or Mod 55306 has been embodied in production, and except those on which Airbus Repair Instruction R57115092 has been embodied in service on both right-hand (RH) and left-hand (LH) sides. (1) Airbus Model A330-201, -202, -203, -223, -223F, -243 -243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes. (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by reports that cracks were found on an adjacent hole of certain frames of the center wing box (CWB). We are issuing this AD to detect and correct cracking on certain holes of the CWB, which could affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection Do a rototest inspection of the fastener holes at the frame (FR) 40 vertical web, on both sides, as specified in paragraphs (g)(1) through (g)(6) of this AD, except as required by paragraph (k) of this AD. (1) For Model A330-300 series airplanes in pre-mod 44360 configuration: At the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD, inspect below the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3114, dated March 12, 2013. (i) At the applicable time specified in paragraph 1.E., ``Compliance'' of Airbus Service Bulletin A330-57-3114, dated March 12, 2013. (ii) Within 2,400 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (2) For Model A330-200 and -300 series airplanes in post-mod 44360 and pre-mod 49202 configuration: At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, inspect below the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3116, dated March 12, 2013. (i) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A330-57-3116, dated March 12, 2013. (ii) Within 2,400 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (3) For Model A330-200 and -300 series airplanes in pre-mod 55306 and pre-mod 55792 configuration: At the later of the times specified in paragraphs (g)(3)(i) and (g)(3)(ii) of this AD, inspect above the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3115, dated April 4, 2013. (i) At the applicable time specified in paragraph 1.E., ``Compliance'' of Airbus Service Bulletin A330-57-3115, dated April 4, 2013. (ii) Within 2,400 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (4) For Model A340-200 and -300 series airplanes in pre-mod 44360 configuration: At the later of the times specified in paragraphs (g)(4)(i) and (g)(4)(ii) of this AD, inspect below the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-57-4123, dated March 12, 2013. (i) At the applicable time specified in paragraph 1.E., ``Compliance'' of Airbus Service Bulletin A330-57-4123, dated March 12, 2013. (ii) Within 1,300 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (5) For Model A340-200 and -300 series airplanes in pre-mod 55306 and pre-mod 55792 configuration: At the later of the times specified in paragraphs (g)(5)(i) and (g)(5)(ii) of this AD, inspect above the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-57-4124, Revision 01, dated August 22, 2013. (i) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A340-57-4124, Revision 01, dated August 22, 2013. (ii) Within 1,300 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (6) For Model A340-200 and -300 series airplanes in post-mod 44360 and pre-mod 49202 configuration: At the later of the times specified in paragraphs (g)(6)(i) and (g)(6)(ii) of this AD, inspect below the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-57-4125, dated March 12, 2013. (i) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A340-57-4125, dated March 12, 2013. (ii) Within 1,300 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (h) Follow-On Actions: No Cracking If no crack is found during any inspection required by paragraph (g) of this AD, do the actions specified in paragraphs (h)(1) and (h)(2) of this AD. (1) Before further flight, install new fasteners in the transition fit, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. [[Page 38576]] (2) Repeat the inspection required by paragraph (g) of this AD thereafter at the applicable time identified in paragraph 1.E., ``Compliance,'' of the applicable service information identified in paragraph (g) of this AD. (i) Follow-On Actions: Crack Findings If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, oversize the holes to the first oversize in comparison with the current hole diameter, and do a rototest inspection for cracks, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. (1) If no cracking is found during the rototest inspection required by paragraph (i) of this AD, do the actions specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. (i) Before further flight: Install new fasteners in the transition fit, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. (ii) Repeat the inspection required by paragraph (g) of this AD thereafter at the applicable time identified in paragraph 1.E., ``Compliance,'' of the applicable service information identified in paragraph (g) of this AD. (2) If cracking is found during the rototest inspection required by paragraph (i) of this AD: Before further flight, repair 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). (j) Terminating Action Specifications Accomplishment of the initial and repetitive inspections required by this AD terminates accomplishment of Airworthiness Limitation Items Tasks 57-11-04 and 57-11-02 of the Airworthiness Limitation Section (ALS) Part 2, Damage Tolerant Airworthiness Limitation Items (DT ALI). (1) Installation of new fasteners, as specified in paragraph (h)(1) of this AD, does not terminate the repetitive inspections required by paragraph (g) of this AD. (2) Accomplishment of the corrective actions specified in the introductory text of paragraph (i) and paragraph (i)(1) of this AD does not terminate the repetitive inspections required by paragraph (g) of this AD. (3) Accomplishment of the repair specified in paragraph (i)(2) of this AD does not terminate repetitive inspections required by paragraph (g) of this AD, unless the approved repair method specifies otherwise. (k) Exceptions to Service Information (1) If the applicable service information identified in paragraph (g) of this AD specifies contacting Airbus for appropriate action: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. (2) Where paragraph 1.E., ``Compliance,'' of the applicable service information specified in paragraph (g) of this AD specifies a compliance time in terms of a ``Threshold'' and ``Grace Period,'' this AD requires compliance at the later of the applicable threshold and grace period. (3) Where paragraph 1.E., ``Compliance,'' of the applicable service information specified in paragraph (g) of this AD specifies a threshold as ``before next flight,'' this AD requires compliance before the next flight after the applicable finding. (l) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (i) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraph (l)(1), (l)(2), (l)(3), (l)(4), (l)(5), (l)(6), (l)(7), (l)(8), or (l)(9) of this AD. This service information is not incorporated by reference in this AD. (1) Airbus Technical Disposition LR57D11023270, Issue B, dated July 12, 2011. (2) Airbus Technical Disposition LR57D11029171, Issue B, dated September 6, 2011. (3) Airbus Technical Disposition LR57D11029173, Issue B, dated September 6, 2011. (4) Airbus Technical Disposition LR57D11030741, Issue B, dated September 22, 2011. (5) Airbus Technical Disposition LR57D11029170, Issue C, dated September 6, 2011. (6) Airbus Technical Disposition LR57D11023714, Issue B, dated July 12, 2011. (7) Airbus Technical Disposition LR57D11029172, Issue B, dated September 6, 2011. (8) Airbus Technical Disposition LR57D11030740, Issue C, dated September 22, 2011. (9) Airbus Service Bulletin A340-57-4124, dated April 4, 2013. (m) 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0149, dated June 13, 2014, 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-2016-6899. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(4) and (o)(5) of this AD. (o) 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 June 13, 2016, (81 FR 27986, May 9, 2016). (i) Airbus Service Bulletin A330-57-3114, dated March 12, 2013. (ii) Airbus Service Bulletin A330-57-3115, dated April 4, 2013. (iii) Airbus Service Bulletin A330-57-3116, dated March 12, 2013. (iv) Airbus Service Bulletin A340-57-4123, dated March 12, 2013. (v) Airbus Service Bulletin A340-57-4124, Revision 01, dated August 22, 2013. (vi) Airbus Service Bulletin A340-57-4125, dated March 12, 2013. (4) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: [email protected]; Internet: http://www.airbus.com. (5) 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. (6) 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 June 3, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-13856 Filed 6-13-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 114 / Tuesday, June 14, 2016 / Rules and Regulations 38573
Correction DATES: This AD is effective June 29, SUPPLEMENTARY INFORMATION:
In FR Doc. 2016–11908 beginning on 2016.
The Director of the Federal Register Discussion
page 33098 in the Federal Register of
approved the incorporation by reference On April 21, 2016, we issued AD
May 24, 2016, make the following
of certain publications listed in this AD 2016–09–11, Amendment 39–18509 (81
correction:
as of June 13, 2016 (81 FR 27986, May FR 27986, May 9, 2016) (‘‘AD 2016–09–
Correction 9, 2016). 11’’), for certain Airbus Model A330–
We must receive comments on this 200, –200 Freighter, and –300 series
1. On page 33098, in the first column,
AD by July 29, 2016. airplanes; and Model A340–200 and
in the document heading, revise
ADDRESSES: You may send comments, –300 series airplanes. AD 2016–09–11
‘‘[Docket No.: FAA–2014–0554; Amdt.
Nos. 1–69, 11–59, 121–374, 125–65, and using the procedures found in 14 CFR was prompted by reports that cracks
135–133]’’ to read ‘‘[Docket No.: FAA– 11.43 and 11.45, by any of the following were found on an adjacent hole of
2014–0554; Amdt. Nos. 1–69, 11–60, methods: certain frames of the CWB. AD 2016–
• Federal eRulemaking Portal: Go to 09–11 required removing fasteners,
121–374, 125–65, and 135–133]’’.
http://www.regulations.gov. Follow the doing a rototest inspection of fastener
Issued under authority provided by 49 instructions for submitting comments. holes, installing new fasteners,
U.S.C. 106(f) in Washington, DC, on June 1, • Fax: 202–493–2251.
2016. • Mail: U.S. Department of oversizing the holes and doing rototest
Dale A. Bouffiou, Transportation, Docket Operations, M– inspections for cracks if necessary, and
Acting Director, Office of Rulemaking. 30, West Building Ground Floor, Room repairing any cracking that was found.
W12–140, 1200 New Jersey Avenue SE., We issued AD 2016–09–11 to detect and
[FR Doc. 2016–13955 Filed 6–13–16; 8:45 am]
Washington, DC 20590. correct cracking on certain holes of
BILLING CODE 4910–13–P
• Hand Delivery: U.S. Department of certain frames of the CWB that could
Transportation, Docket Operations, M– affect the structural integrity of the
30, West Building Ground Floor, Room airplane.
DEPARTMENT OF TRANSPORTATION
W12–140, 1200 New Jersey Avenue SE., Since we issued AD 2016–09–11, we
Federal Aviation Administration Washington, DC, between 9 a.m. and 5 discovered missing affected airplanes in
p.m., Monday through Friday, except paragraph (g)(2) of AD 2016–09–11 that
14 CFR Part 39 Federal holidays. resulted from converting a table to text
For service information identified in in that AD. We stated in the preamble
[Docket No. FAA–2016–6899; Directorate this final rule, contact Airbus SAS, of AD 2016–09–11 that we revised the
Identifier 2016–NM–066–AD; Amendment Airworthiness Office—EAL, 1 Rond format of paragraph (g) of that AD, at the
39–18558; AD 2016–12–09] Point Maurice Bellonte, 31707 Blagnac request of the Office of the Federal
Cedex, France; telephone: +33 5 61 93 Register, by converting the table to text.
RIN 2120–AA64
36 96; fax: +33 5 61 93 45 80; email: We also stated this change to the format
Airworthiness Directives; Airbus airworthiness.A330-A340@airbus.com; does not affect the requirements of that
Airplanes Internet: http://www.airbus.com. You paragraph.
may view this referenced service However, in converting the table to
AGENCY: Federal Aviation information at the FAA, Transport text, we inadvertently omitted Model
Administration (FAA), Department of Airplane Directorate, 1601 Lind Avenue A330–300 series airplanes from
Transportation (DOT). SW., Renton, WA. For information on paragraph (g)(2) of AD 2016–09–11. We
ACTION: Final rule; request for the availability of this material at the have changed paragraph (g)(2) of this
comments. FAA, call 425–227–1221. It is also AD to include Model A330–300 series
available on the Internet at http:// airplanes.
SUMMARY: We are superseding www.regulations.gov by searching for
Airworthiness Directive (AD) 2016–09– and locating Docket No. FAA–2016– The European Aviation Safety Agency
11 for certain Airbus Model A330–200, 6899. (EASA), which is the Technical Agent
–200 Freighter, and –300 series for the Member States of the European
airplanes; and Model A340–200 and Examining the AD Docket Union, has issued EASA Airworthiness
–300 series airplanes. AD 2016–09–11 You may examine the AD docket on Directive 2014–0149, dated June 13,
required removing fasteners, doing a the Internet at http:// 2014 (referred to after this as the
rototest inspection of fastener holes, www.regulations.gov by searching for Mandatory Continuing Airworthiness
installing new fasteners, oversizing the and locating Docket No. FAA–2016– Information, or ‘‘the MCAI’’), to correct
holes and doing rototest inspections for 6899; or in person at the Docket an unsafe condition for certain Airbus
cracks if necessary, and repairing any Management Facility between 9 a.m. Model A330–200, –200 Freighter, and
cracking that is found. This new AD and 5 p.m., proposed AD, the regulatory –300 series airplanes; and Model A340–
requires the same actions as AD 2016– evaluation, any comments received, and 200 and –300 series airplanes. The
09–11, but includes Model A330–300 other information. The street address for MCAI states:
series airplanes in paragraph (g)(2) of the Docket Operations office (telephone: During accomplishment of A330
this AD. This AD was prompted by the 800–647–5527) is in the ADDRESSES Airworthiness Limitation Item (ALI) task 57–
discovery of missing affected airplanes section. Comments will be available in 11–04 on the rear fitting of the Frame (FR)
in paragraph (g)(2) of AD 2016–09–11 the AD docket shortly after receipt. 40 between stringers 38 and 39 on both [left-
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that resulted from converting a table in FOR FURTHER INFORMATION CONTACT: hand] LH/[right-hand] RH sides, cracks were
the proposed AD to text in AD 2016–09– Vladimir Ulyanov, Aerospace Engineer, found on an adjacent hole. After reaming at
second oversize of the subject hole, the crack
11. We are issuing this AD to detect and International Branch, ANM–116, was still present.
correct cracking on certain holes of Transport Airplane Directorate, FAA, Other crack findings on this adjacent hole
certain frames of the center wing box 1601 Lind Avenue SW., Renton, WA have been reported on A330 and A340–200/
(CWB), which could affect the structural 98057–3356; telephone: 425–227–1138; –300 aeroplanes as a result of sampling
integrity of the airplane. fax: 425–227–1149. inspections.
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This condition, if not detected and • Airbus Service Bulletin A330–57– table to text in paragraph (g)(2) of AD
corrected, could affect the structural integrity 3114, dated March 12, 2013. 2016–09–11. No other changes have
of the aeroplane. • Airbus Service Bulletin A330–57– been made to AD 2016–09–11.
For the reasons described above, this
[EASA] AD requires removal of the fasteners
3115, dated April 4, 2013. Therefore, we determined that notice
and repetitive rototest inspections of fastener • Airbus Service Bulletin A330–57– and opportunity for prior public
holes at FR40 vertical web located above 3116, dated March 12, 2013. comment are unnecessary.
Center Wing Box (CWB) lower panel • Airbus Service Bulletin A340–57–
reference and/or below CWB lower panel 4123, dated March 12, 2013. Comments Invited
reference on both sides and, depending on • Airbus Service Bulletin A340–57– This AD is a final rule that involves
findings, accomplishment of the applicable 4124, Revision 01, dated August 22,
corrective actions. requirements affecting flight safety, and
2013.
we did not precede it by notice and
Note: These holes affected by this [EASA] • Airbus Service Bulletin A340–57–
AD are different from the ones affected by opportunity for public comment. We
4125, dated March 12, 2013.
EASA AD 2009–0001 [http:// invite you to send any written relevant
ad.easa.europa.eu/blob/easa_ad_2009_ This service information is reasonably
data, views, or arguments about this AD.
0001.pdf/AD_2009–0001_1]. available because the interested parties
have access to it through their normal Send your comments to an address
Required actions also include listed under the ADDRESSES section.
oversizing certain holes, installing new course of business or by the means
identified in the ADDRESSES section. Include ‘‘Docket No. FAA–2016–6899;
fasteners, and repairing any cracking
Directorate Identifier 2016–NM–066–
that is found. The initial compliance FAA’s Determination and Requirements AD’’ at the beginning of your comments.
times range from 13,500 to 30,900 flight of This AD
cycles, or 57,000 to 162,000 flight hours, We specifically invite comments on the
depending on airplane operation and This product has been approved by overall regulatory, economic,
utilization. The repetitive compliance the aviation authority of another environmental, and energy aspects of
times are 7,400 flight cycles/24,300 country, and is approved for operation this AD. We will consider all comments
flight hours or 5,950 flight cycles/40,400 in the United States. Pursuant to our received by the closing date and may
flight hours from ALI embodiment. You bilateral agreement with the State of amend this AD because of those
may examine the MCAI on the Internet Design Authority, we have been notified comments.
at http://www.regulations.gov by of the unsafe condition described in the We will post all comments we
searching for and locating Docket No. MCAI and service information receive, without change, to http://
FAA–2016–6899. referenced above. We are issuing this www.regulations.gov, including any
AD because we evaluated all pertinent personal information you provide. We
Related Service Information Under 1 information and determined the unsafe
CFR Part 51 will also post a report summarizing each
condition exists and is likely to exist or substantive verbal contact we receive
Airbus has issued the following develop on other products of these same about this AD.
service information. The service type designs.
information describes procedures for Costs of Compliance
removing the fasteners and doing a FAA’s Justification and Determination
repetitive rototest inspection of fastener of the Effective Date We estimate that this AD affects 35
holes at FR40 vertical web on both We are superseding AD 2016–09–11 airplanes of U.S. registry.
sides, installing new fasteners in to correct an error in the regulatory text We estimate the following costs to
transition fit, and oversizing the holes. that we made when we converted a comply with this AD:
ESTIMATED COSTS
Cost on
Action Labor cost Parts cost Cost per product U.S. operators
Inspection ......... 78 work-hours × $85 per hour = $0 $6,630 per inspection cycle .......... $232,050 per inspection cycle.
$6,630 per inspection cycle.
We estimate the following costs to do required based on the results of the determining the number of airplanes
any necessary repairs that will be inspection. We have no way of that might need this repair:
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Oversize, installation, and inspection ........................... 98 work-hours × $85 per hour = $8,330 ...................... $136,400 $144,730
We have received no definitive data Authority for This Rulemaking detail the scope of the Agency’s
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that will enable us to provide cost authority.
Title 49 of the United States Code
estimates for the on-condition repair specifies the FAA’s authority to issue We are issuing this rulemaking under
specified in this AD. rules on aviation safety. Subtitle I, the authority described in ‘‘Subtitle VII,
section 106, describes the authority of Part A, Subpart III, Section 44701:
the FAA Administrator. ‘‘Subtitle VII: General requirements.’’ Under that
Aviation Programs,’’ describes in more section, Congress charges the FAA with
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![Federal Register / Vol. 81, No. 114 / Tuesday, June 14, 2016 / Rules and Regulations 38575
promoting safe flight of civil aircraft in (b) Affected ADs (ii) Within 2,400 flight cycles or 24 months
air commerce by prescribing regulations This AD replaces AD 2016–09–11, after the effective date of this AD, whichever
for practices, methods, and procedures Amendment 39–18509 (81 FR 27986, May 9, occurs first.
(3) For Model A330–200 and –300 series
the Administrator finds necessary for 2016) (‘‘AD 2016–09–11’’).
airplanes in pre-mod 55306 and pre-mod
safety in air commerce. This regulation (c) Applicability 55792 configuration: At the later of the times
is within the scope of that authority specified in paragraphs (g)(3)(i) and (g)(3)(ii)
because it addresses an unsafe condition This AD applies to the airplanes identified
of this AD, inspect above the CWB lower
in paragraphs (c)(1) and (c)(2) of this AD,
that is likely to exist or develop on panel reference, in accordance with the
certificated in any category, all manufacturer Accomplishment Instructions of Airbus
products identified in this rulemaking serial numbers, except those on which
action. Service Bulletin A330–57–3115, dated April
Airbus Modification (Mod) 55792 or Mod 4, 2013.
Regulatory Findings 55306 has been embodied in production, and (i) At the applicable time specified in
except those on which Airbus Repair paragraph 1.E., ‘‘Compliance’’ of Airbus
We determined that this AD will not Instruction R57115092 has been embodied in Service Bulletin A330–57–3115, dated April
have federalism implications under service on both right-hand (RH) and left-hand 4, 2013.
Executive Order 13132. This AD will (LH) sides. (ii) Within 2,400 flight cycles or 24 months
not have a substantial direct effect on (1) Airbus Model A330–201, –202, –203, after the effective date of this AD, whichever
–223, –223F, –243 –243F, –301, –302, –303, occurs first.
the States, on the relationship between (4) For Model A340–200 and –300 series
–321, –322, –323, –341, –342, and –343
the national government and the States, airplanes. airplanes in pre-mod 44360 configuration: At
or on the distribution of power and (2) Airbus Model A340–211, –212, –213, the later of the times specified in paragraphs
responsibilities among the various –311, –312, and –313 airplanes. (g)(4)(i) and (g)(4)(ii) of this AD, inspect
levels of government. below the CWB lower panel reference, in
(d) Subject accordance with the Accomplishment
For the reasons discussed above, I Instructions of Airbus Service Bulletin A340–
Air Transport Association (ATA) of
certify that this AD: 57–4123, dated March 12, 2013.
America Code 57, Wings.
1. Is not a ‘‘significant regulatory (i) At the applicable time specified in
(e) Reason paragraph 1.E., ‘‘Compliance’’ of Airbus
action’’ under Executive Order 12866;
This AD was prompted by reports that Service Bulletin A330–57–4123, dated March
2. Is not a ‘‘significant rule’’ under the cracks were found on an adjacent hole of 12, 2013.
DOT Regulatory Policies and Procedures certain frames of the center wing box (CWB). (ii) Within 1,300 flight cycles or 24 months
(44 FR 11034, February 26, 1979); We are issuing this AD to detect and correct after the effective date of this AD, whichever
3. Will not affect intrastate aviation in cracking on certain holes of the CWB, which occurs first.
could affect the structural integrity of the (5) For Model A340–200 and –300 series
Alaska; and airplanes in pre-mod 55306 and pre-mod
airplane.
4. Will not have a significant 55792 configuration: At the later of the times
economic impact, positive or negative, (f) Compliance specified in paragraphs (g)(5)(i) and (g)(5)(ii)
on a substantial number of small entities Comply with this AD within the of this AD, inspect above the CWB lower
under the criteria of the Regulatory compliance times specified, unless already panel reference, in accordance with the
done. Accomplishment Instructions of Airbus
Flexibility Act.
Service Bulletin A340–57–4124, Revision 01,
List of Subjects in 14 CFR Part 39 (g) Inspection dated August 22, 2013.
Do a rototest inspection of the fastener (i) At the applicable time specified in
Air transportation, Aircraft, Aviation holes at the frame (FR) 40 vertical web, on paragraph 1.E., ‘‘Compliance,’’ of Airbus
safety, Incorporation by reference, both sides, as specified in paragraphs (g)(1) Service Bulletin A340–57–4124, Revision 01,
Safety. through (g)(6) of this AD, except as required dated August 22, 2013.
by paragraph (k) of this AD. (ii) Within 1,300 flight cycles or 24 months
Adoption of the Amendment (1) For Model A330–300 series airplanes in after the effective date of this AD, whichever
pre-mod 44360 configuration: At the later of occurs first.
Accordingly, under the authority the times specified in paragraphs (g)(1)(i) and (6) For Model A340–200 and –300 series
delegated to me by the Administrator, (g)(1)(ii) of this AD, inspect below the CWB airplanes in post-mod 44360 and pre-mod
the FAA amends 14 CFR part 39 as lower panel reference, in accordance with the 49202 configuration: At the later of the times
follows: Accomplishment Instructions of Airbus specified in paragraphs (g)(6)(i) and (g)(6)(ii)
Service Bulletin A330–57–3114, dated March of this AD, inspect below the CWB lower
PART 39—AIRWORTHINESS panel reference, in accordance with the
12, 2013.
DIRECTIVES Accomplishment Instructions of Airbus
(i) At the applicable time specified in
Service Bulletin A340–57–4125, dated March
paragraph 1.E., ‘‘Compliance’’ of Airbus
12, 2013.
■ 1. The authority citation for part 39 Service Bulletin A330–57–3114, dated March
(i) At the applicable time specified in
continues to read as follows: 12, 2013. paragraph 1.E., ‘‘Compliance,’’ of Airbus
(ii) Within 2,400 flight cycles or 24 months Service Bulletin A340–57–4125, dated March
Authority: 49 U.S.C. 106(g), 40113, 44701. after the effective date of this AD, whichever 12, 2013.
occurs first. (ii) Within 1,300 flight cycles or 24 months
§ 39.13 [Amended]
(2) For Model A330–200 and –300 series after the effective date of this AD, whichever
■ 2. The FAA amends § 39.13 by airplanes in post-mod 44360 and pre-mod occurs first.
49202 configuration: At the later of the times
removing airworthiness directive (AD) (h) Follow-On Actions: No Cracking
specified in paragraphs (g)(2)(i) and (g)(2)(ii)
2016–09–11, Amendment 39–18509 (81 of this AD, inspect below the CWB lower If no crack is found during any inspection
FR 27986, May 9, 2016), and adding the panel reference, in accordance with the
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required by paragraph (g) of this AD, do the
following new AD: Accomplishment Instructions of Airbus actions specified in paragraphs (h)(1) and
2016–12–09 Airbus: Amendment 39–18558. Service Bulletin A330–57–3116, dated March (h)(2) of this AD.
Docket No. FAA–2016–6899; Directorate 12, 2013. (1) Before further flight, install new
Identifier 2016–NM–066–AD. (i) At the applicable time specified in fasteners in the transition fit, in accordance
paragraph 1.E., ‘‘Compliance,’’ of Airbus with the Accomplishment Instructions of the
(a) Effective Date Service Bulletin A330–57–3116, dated March applicable service information identified in
This AD is effective June 29, 2016. 12, 2013. paragraph (g) of this AD.
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![38576 Federal Register / Vol. 81, No. 114 / Tuesday, June 14, 2016 / Rules and Regulations
(2) Repeat the inspection required by and ‘‘Grace Period,’’ this AD requires actions from a manufacturer, the action must
paragraph (g) of this AD thereafter at the compliance at the later of the applicable be accomplished using a method approved
applicable time identified in paragraph 1.E., threshold and grace period. by the Manager, International Branch, ANM–
‘‘Compliance,’’ of the applicable service (3) Where paragraph 1.E., ‘‘Compliance,’’ of 116, Transport Airplane Directorate, FAA; or
information identified in paragraph (g) of this the applicable service information specified the EASA; or Airbus’s EASA DOA. If
AD. in paragraph (g) of this AD specifies a approved by the DOA, the approval must
threshold as ‘‘before next flight,’’ this AD include the DOA-authorized signature.
(i) Follow-On Actions: Crack Findings requires compliance before the next flight
If any crack is found during any inspection after the applicable finding. (n) Related Information
required by paragraph (g) of this AD: Before
(l) Credit for Previous Actions (1) Refer to Mandatory Continuing
further flight, oversize the holes to the first
This paragraph provides credit for actions Airworthiness Information (MCAI) EASA
oversize in comparison with the current hole
diameter, and do a rototest inspection for required by paragraphs (g) and (i) of this AD, Airworthiness Directive 2014–0149, dated
cracks, in accordance with the if those actions were performed before the June 13, 2014, for related information. This
Accomplishment Instructions of the effective date of this AD using the applicable MCAI may be found in the AD docket on the
applicable service information identified in service information specified in paragraph Internet at http://www.regulations.gov by
paragraph (g) of this AD. (l)(1), (l)(2), (l)(3), (l)(4), (l)(5), (l)(6), (l)(7), searching for and locating Docket No. FAA–
(1) If no cracking is found during the (l)(8), or (l)(9) of this AD. This service 2016–6899.
rototest inspection required by paragraph (i) information is not incorporated by reference (2) Service information identified in this
of this AD, do the actions specified in in this AD. AD that is not incorporated by reference is
paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. (1) Airbus Technical Disposition available at the addresses specified in
(i) Before further flight: Install new LR57D11023270, Issue B, dated July 12, paragraphs (o)(4) and (o)(5) of this AD.
fasteners in the transition fit, in accordance 2011.
with the Accomplishment Instructions of the (2) Airbus Technical Disposition (o) Material Incorporated by Reference
applicable service information identified in LR57D11029171, Issue B, dated September 6, (1) The Director of the Federal Register
paragraph (g) of this AD. 2011. approved the incorporation by reference
(ii) Repeat the inspection required by (3) Airbus Technical Disposition (IBR) of the service information listed in this
paragraph (g) of this AD thereafter at the LR57D11029173, Issue B, dated September 6, paragraph under 5 U.S.C. 552(a) and 1 CFR
applicable time identified in paragraph 1.E., 2011.
part 51.
‘‘Compliance,’’ of the applicable service (4) Airbus Technical Disposition
(2) You must use this service information
information identified in paragraph (g) of this LR57D11030741, Issue B, dated September
22, 2011. as applicable to do the actions required by
AD.
(5) Airbus Technical Disposition this AD, unless this AD specifies otherwise.
(2) If cracking is found during the rototest
inspection required by paragraph (i) of this LR57D11029170, Issue C, dated September 6, (3) The following service information was
AD: Before further flight, repair using a 2011. approved for IBR on June 13, 2016, (81 FR
method approved by the Manager, (6) Airbus Technical Disposition 27986, May 9, 2016).
International Branch, ANM–116, Transport LR57D11023714, Issue B, dated July 12, (i) Airbus Service Bulletin A330–57–3114,
Airplane Directorate, FAA; or the European 2011. dated March 12, 2013.
Aviation Safety Agency (EASA); or Airbus’s (7) Airbus Technical Disposition (ii) Airbus Service Bulletin A330–57–3115,
EASA Design Organization Approval (DOA). LR57D11029172, Issue B, dated September 6, dated April 4, 2013.
2011. (iii) Airbus Service Bulletin A330–57–
(j) Terminating Action Specifications (8) Airbus Technical Disposition 3116, dated March 12, 2013.
Accomplishment of the initial and LR57D11030740, Issue C, dated September (iv) Airbus Service Bulletin A340–57–
repetitive inspections required by this AD 22, 2011. 4123, dated March 12, 2013.
terminates accomplishment of Airworthiness (9) Airbus Service Bulletin A340–57–4124, (v) Airbus Service Bulletin A340–57–4124,
Limitation Items Tasks 57–11–04 and 57–11– dated April 4, 2013. Revision 01, dated August 22, 2013.
02 of the Airworthiness Limitation Section (vi) Airbus Service Bulletin A340–57–
(m) Other FAA AD Provisions
(ALS) Part 2, Damage Tolerant Airworthiness 4125, dated March 12, 2013.
Limitation Items (DT ALI). The following provisions also apply to this
AD: (4) For service information identified in
(1) Installation of new fasteners, as
(1) Alternative Methods of Compliance this AD, contact Airbus SAS, Airworthiness
specified in paragraph (h)(1) of this AD, does
(AMOCs): The Manager, International Office—EAL, 1 Rond Point Maurice Bellonte,
not terminate the repetitive inspections
required by paragraph (g) of this AD. Branch, ANM–116, Transport Airplane 31707 Blagnac Cedex, France; telephone: +33
(2) Accomplishment of the corrective Directorate, FAA, has the authority to 5 61 93 36 96; fax: +33 5 61 93 45 80; email:
actions specified in the introductory text of approve AMOCs for this AD, if requested airworthiness.A330-A340@airbus.com;
paragraph (i) and paragraph (i)(1) of this AD using the procedures found in 14 CFR 39.19. Internet: http://www.airbus.com.
does not terminate the repetitive inspections In accordance with 14 CFR 39.19, send your (5) You may view this service information
required by paragraph (g) of this AD. request to your principal inspector or local at the FAA, Transport Airplane Directorate,
(3) Accomplishment of the repair specified Flight Standards District Office, as 1601 Lind Avenue SW., Renton, WA. For
in paragraph (i)(2) of this AD does not appropriate. If sending information directly information on the availability of this
terminate repetitive inspections required by to the International Branch, send it to ATTN: material at the FAA, call 425–227–1221.
paragraph (g) of this AD, unless the approved Vladimir Ulyanov, Aerospace Engineer, (6) You may view this service information
repair method specifies otherwise. International Branch, ANM–116, Transport that is incorporated by reference at the
Airplane Directorate, FAA, 1601 Lind National Archives and Records
(k) Exceptions to Service Information Avenue SW., Renton, WA 98057–3356; Administration (NARA). For information on
(1) If the applicable service information telephone: 425–227–1138; fax: 425–227– the availability of this material at NARA, call
identified in paragraph (g) of this AD 1149. Information may be emailed to: 9- 202–741–6030, or go to: http://www.archives.
specifies contacting Airbus for appropriate ANM-116-AMOC-REQUESTS@faa.gov. gov/federal-register/cfr/ibr-locations.html.
action: Before further flight, repair using a Before using any approved AMOC, notify
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method approved by the Manager, your appropriate principal inspector, or Issued in Renton, Washington, on June 3,
International Branch, ANM–116, Transport lacking a principal inspector, the manager of 2016.
Airplane Directorate, FAA; or the EASA; or the local flight standards district office/ Michael Kaszycki,
Airbus’s EASA DOA. certificate holding district office. The AMOC
Acting Manager, Transport Airplane
(2) Where paragraph 1.E., ‘‘Compliance,’’ of approval letter must specifically reference
Directorate, Aircraft Certification Service.
the applicable service information specified this AD.
in paragraph (g) of this AD specifies a (2) Contacting the Manufacturer: For any [FR Doc. 2016–13856 Filed 6–13–16; 8:45 am]
compliance time in terms of a ‘‘Threshold’’ requirement in this AD to obtain corrective BILLING CODE 4910–13–P
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Document Created: 2016-06-14 02:58:58
Document Modified: 2016-06-14 02:58:58
| 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; request for comments. | |
| Dates | This AD is effective June 29, 2016. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149. | |
| FR Citation | 81 FR 38573 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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