81 FR 85837 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 229 (November 29, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 229 (November 29, 2016)
| Page Range | 85837-85840 | |
| FR Document | 2016-28335 |
[Federal Register Volume 81, Number 229 (Tuesday, November 29, 2016)] [Rules and Regulations] [Pages 85837-85840] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-28335] ======================================================================== Rules and Regulations Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. ======================================================================== Federal Register / Vol. 81, No. 229 / Tuesday, November 29, 2016 / Rules and Regulations [[Page 85837]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-5596; Directorate Identifier 2015-NM-121-AD; Amendment 39-18677; AD 2016-20-11] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2014-12-06 for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Airbus Model A310 series airplanes. AD 2014-12-06 required repetitive ultrasonic or detailed inspections of the external area of the aft cargo door sill beam for cracking, and repair if necessary, and provided an optional one-time high frequency eddy current (HFEC) inspection that would terminate the repetitive inspections. This new AD requires the previously optional terminating HFEC inspection, and requires that it be done repetitively. This AD was prompted by findings of multiple fatigue cracks in the aft cargo door that indicated the need for additional, repetitive, HFEC inspections. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 3, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 3, 2017. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of July 2, 2014 (79 FR 34403, June 17, 2014). ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. 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- 5596. 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- 5596, or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800- 647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: 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. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2014-12-06, Amendment 39-17867 (79 FR 34403, June 17, 2014) (``AD 2014-12-06''). AD 2014-12-06 applied to certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300- 600 series airplanes); and Airbus Model A310 series airplanes. AD 2014- 12-06 required repetitive ultrasonic or detailed inspections of the external area of the aft cargo door sill beam for cracking, and repair if necessary. AD 2014-12-16 also provided an optional one-time HFEC inspection that would terminate the repetitive inspections. The NPRM published in the Federal Register on April 27, 2016 (81 FR 24745). The NPRM was prompted by findings of multiple fatigue cracks in the aft cargo door that indicated the need for repetitive HFEC inspections. The NPRM proposed to continue to require repetitive ultrasonic or detailed inspections of the external area of the aft cargo door sill beam for cracking, and repair if necessary. The NPRM also proposed to require the previously optional terminating HFEC inspection, and to require that it be done repetitively. We are issuing this AD to detect and correct fatigue cracking of the cargo door sill beam, lock fitting, and torsion box plate. Failure of one or more of these components could result in the loss of the door locking function and, subsequently, complete loss of the cargo door in flight with the risk of rapid decompression. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0150, dated July 23, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4- 605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Airbus Model A310 series airplanes. The MCAI states: During accomplishment of Maintenance Review Board Report (MRBR) task 531625-01-1 on an A300-600 aeroplane having accumulated more than 25,000 flight cycles (FC) since aeroplane first flight, multiple fatigue cracks were found on the following parts: --Aft cargo door sill beam Part Number (P/N) A53973085210. --Lock fitting P/N A53978239002. --Torsion box plate P/N A53973318206. Prompted by these findings, a stress analysis was performed during which it was discovered that there is no dedicated [[Page 85838]] scheduled maintenance task to inspect the affected area for fatigue damage. This condition, if not detected and corrected, could lead to failure of multiple lock fittings, possibly resulting in loss of the cargo door in flight and consequent explosive decompression of the aeroplane. To address this unsafe condition, Airbus issued Alert Operators Transmission (AOT) A53W005-14 providing instructions for inspection of the affected area. Consequently, EASA issued Emergency AD 2014-0097-E [which corresponded to FAA AD 2014-12-06] to require repetitive ultrasonic (US) inspections or detailed inspections (DET) of the aft cargo door sill beam external area, and/or a one-time High Frequency Eddy Current (HFEC) inspection of the aft cargo door sill beam internal structure and, depending on findings, accomplishment of corrective action(s). Since that [EASA] AD was issued, the results of further analysis have indicated that repetitive HFEC inspections need to be introduced. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2014-0097-E, which is superseded, and requires repetitive HFEC inspections of the concerned areas. The first HFEC inspection terminates the repetitive US/DET inspections. 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- 5596. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Support for the NPRM The Air Line Pilots Association, International stated that it supports the NPRM. Request To Rewrite Reporting Requirements One commenter, Mark Hilborn, requested that we revise the structure of paragraph (i) of the proposed AD for clarity and to change the location where the reports should be sent. He stated that we could rewrite paragraph (i) of the proposed AD to remove the subparagraphs. We partially agree with the request. We have updated the contact information for submitting the reports. We do not find it necessary, however, to change the remainder of the paragraph since it is restated from AD 2014-12-06, and the compliance times are correct. Request To Clarify the Terminating Actions Mark Hilborn requested we revise paragraph (m) of the proposed AD for clarity and to add new subparagraphs to aid in that. We agree with the request and have changed paragraph (m) of this AD accordingly. Additional Changes Made in This Final Rule We have revised this AD to require the current version of the service information identified for the terminating action specified in this AD. This service information was revised to make a small tooling change; no additional work is necessary for airplanes on which the original version of this service information was accomplished. We have also added credit for airplanes on which the original version of this service information was accomplished, and made related changes accordingly. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information, which describes procedures for repetitive HFEC inspections of the cargo door sill beam, lock fitting, and torsion box plate. These service bulletins are distinct since they apply to different airplane models. Airbus Service Bulletin A300-53-6179, dated December 12, 2014. Airbus Service Bulletin A310-53-2139, dated December 12, 2014. Airbus has also issued AOT A53W005-14, Revision 01, dated April 29, 2014, which describes procedures for doing an ultrasonic inspection or detailed inspection of the aft cargo door sill beam external area for cracking. Additionally, Airbus has issued the following service information, which describes procedures for reinforcing the aft cargo door sill beam are between FR 60 and FR 63. These service bulletins are distinct since they apply to different airplane models. Airbus Service Bulletin A310-53-2141, Revision 01, dated July 2, 2015. Airbus Service Bulletin A300-53-6181, Revision 01, dated July 2, 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. Costs of Compliance We estimate that this AD affects 75 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..................... 12 work-hours x $85 N/A.............. $1,020 per $76,500 per per hour = $1,020 per inspection cycle. inspection inspection cycle. cycle. Reporting...................... 1 work-hour x $85 per N/A.............. $85.............. $6,375. hour = $85 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120- 0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 [[Page 85839]] Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES-200. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures 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 AD 2014-12-06, Amendment 39- 17867 (79 FR 34403, June 17, 2014), and adding the following new AD: 2016-20-11 Airbus: Amendment 39-18677; Docket No. FAA-2016-5596; Directorate Identifier 2015-NM-121-AD. (a) Effective Date This AD is effective January 3, 2017. (b) Affected ADs This AD replaces AD 2014-12-06, Amendment 39-17867 (79 FR 34403, June 17, 2014) (``AD 2014-12-06''). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), (c)(3), (c)(4), and (c)(5) of this AD, certificated in any category, all manufacturer serial numbers on which Airbus Modification 05438 has been embodied in production, except those on which Airbus Modification 12046 has been embodied in production. (1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes. (2) Airbus Model A300 B4-605R and B4-622R airplanes. (3) Airbus Model A300 F4-605R and F4-622R airplanes. (4) Airbus Model A300 C4-605R Variant F airplanes. (5) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of fatigue cracks on the cargo door sill beam, lock fitting, and torsion box plate. We are issuing this AD to detect and correct fatigue cracking of the cargo door sill beam, lock fitting, and torsion box plate, which could result in the loss of the door locking function and subsequently, complete loss of the cargo door in flight with the risk of rapid decompression. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection, With Revised Service Information This paragraph restates the requirements of paragraph (g)(1) of AD 2014-12-06, with revised service information. Within the compliance time identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable: Do an ultrasonic inspection or detailed inspection of the aft cargo door sill beam external area for cracking, in accordance with Airbus Alert Operators Transmission (AOT) A53W005-14, dated April 22, 2014; or Airbus AOT A53W005-14, Revision 01, dated April 29, 2014. Repeat the inspection thereafter at intervals not to exceed 275 flight cycles. As of the effective date of this AD, only Airbus AOT A53W005-14, Revision 01, dated April 29, 2014, may be used to comply with the requirements of this paragraph. (1) For airplanes that have accumulated 30,000 flight cycles or more since the airplane's first flight as of July 2, 2014 (the effective date of AD 2014-12-06): Within 50 flight cycles after July 2, 2014. (2) For airplanes that have accumulated 18,000 flight cycles or more, but fewer than 30,000 flight cycles since the airplane's first flight as of July 2, 2014 (the effective date of AD 2014-12-06): Within 275 flight cycles after July 2, 2014. (3) For airplanes that have accumulated fewer than 18,000 flight cycles since the airplane's first flight as of July 2, 2014 (the effective date of AD 2014-12-06): Before exceeding 18,275 flight cycles since the airplane's first flight. (h) Retained Optional Terminating Action, With Revised Service Information and Specific Delegation Approval Language This paragraph restates the provisions of paragraph (h) of AD 2014-12-06, with revised service information and specific delegation approval language. Accomplishment of a high frequency eddy current (HFEC) inspection for cracking, in accordance with Airbus AOT A53W005-14, dated April 22, 2014; or Airbus AOT A53W005-14, Revision 01, dated April 29, 2014; terminates the repetitive inspections required by paragraph (g) of this AD for that airplane. If any cracking is found during the HFEC inspection, 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). (i) Retained Reporting Requirement, With Revised Contact Information This paragraph restates the provisions of paragraph (i) of AD 2014-12-06, with revised contact information. Submit a report of the findings (both positive and negative) of the inspection required by paragraph (g) of this AD to ``Airbus Service Bulletin Reporting Online Application'' on Airbus World (https://w3.airbus.com/), at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD. The report must include the inspection results, including no findings. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (j) Definition of Airplane Groups Paragraphs (k)(1), (k)(2), and (k)(3) of this AD refer to airplane groups, as identified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD. (1) Airplanes on which an HFEC inspection was accomplished as specified in Airbus AOT A53W005-14. (2) Airplanes on which no HFEC inspection was accomplished as specified in Airbus AOT A53W005-14, and that have accumulated more than 18,000 total flight cycles as of the effective date of this AD. [[Page 85840]] (3) Airplanes on which no HFEC inspection was accomplished as specified in Airbus AOT A53W005-14, that have accumulated 18,000 total flight cycles or fewer as of the effective date of this AD. (k) New Repetitive HFEC Inspections and Repair At the applicable time specified in paragraph (k)(1), (k)(2), or (k)(3) of this AD: Do an HFEC inspection for fatigue cracking of the cargo door sill beam, lock fitting, and torsion box plate, in accordance with Airbus Service Bulletin A300-53-6179, dated December 12, 2014; or Airbus Service Bulletin A310-53-2139, dated December 12, 2014; as applicable. Repeat the HFEC inspection thereafter at intervals not to exceed 4,600 flight cycles. (1) For airplanes identified in paragraph (j)(1) of this AD: Inspect within 4,600 flight cycles after the most recent HFEC inspection specified in Airbus AOT A53W005-14. (2) For airplanes identified in paragraph (j)(2) of this AD: Inspect within 2,000 flight cycles after the effective date of this AD. (3) For airplanes identified in paragraph (j)(3) of this AD: Inspect before exceeding 13,000 total flight cycles since the airplane's first flight, or within 2,000 flight cycles after the effective date of this AD, whichever occurs later. (l) Corrective Action If any crack is found during any inspection required by paragraph (g) or (k) of this AD: 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. (m) Terminating Action for Repetitive Inspections This paragraph identifies the requirements to terminate repetitive inspections mandated by this AD. (1) For any airplane identified in paragraphs (j)(2) and (j)(3) of this AD, accomplishment of the initial inspection required by paragraph (k) of this AD terminates the repetitive inspections required by paragraph (g) of this AD. (2) For any airplane identified in paragraphs (c)(1) through (c)(5) of this AD, accomplishment of Airbus Service Bulletin A310- 53-2141, Revision 01, dated July 2, 2015; or Airbus Service Bulletin A300-53-6181, Revision 01, dated July 2, 2015; as applicable; terminates the repetitive inspections required by paragraph (k) of this AD. (n) Credit for Previous Actions This paragraph provides credit for actions provided in paragraph (m)(2) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300-53- 6181, dated June 26, 2015; or Airbus Service Bulletin A310-53-2141, dated June 26, 2015; as applicable. (o) 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: 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: [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: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. (4) Required for Compliance (RC): Except as required by paragraph (l) of this AD: 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. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015-0150, dated July 23, 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-2016-5596. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (q)(5) and (q)(6) of this AD. (q) 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 January 3, 2017. (i) Airbus Alert Operators Transmission (AOT) A53W005-14, Revision 01, dated April 29, 2014. (ii) Airbus Service Bulletin A310-53-2141, Revision 01, dated July 2, 2015. (iii) Airbus Service Bulletin A300-53-6179, dated December 12, 2014. (iv) Airbus Service Bulletin A300-53-6181, Revision 01, dated July 2, 2015. (v) Airbus Service Bulletin A310-53-2139, dated December 12, 2014. (4) The following service information was approved for IBR on July 2, 2014 (79 FR 34403, June 17, 2014). (i) Airbus AOT A53W005-14, dated April 22, 2014. (ii) Reserved. (5) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. 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 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. (7) 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 September 28, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-28335 Filed 11-28-16; 8:45 am] BILLING CODE 4910-13-P
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Rules and Regulations Federal Register
Vol. 81, No. 229
Tuesday, November 29, 2016
This section of the FEDERAL REGISTER The Director of the Federal Register (collectively called Model A300–600
contains regulatory documents having general approved the incorporation by reference series airplanes); and Airbus Model
applicability and legal effect, most of which of a certain other publication listed in A310 series airplanes. AD 2014–12–06
are keyed to and codified in the Code of this AD as of July 2, 2014 (79 FR 34403, required repetitive ultrasonic or detailed
Federal Regulations, which is published under June 17, 2014). inspections of the external area of the aft
50 titles pursuant to 44 U.S.C. 1510.
ADDRESSES: For service information cargo door sill beam for cracking, and
The Code of Federal Regulations is sold by identified in this final rule, contact repair if necessary. AD 2014–12–16 also
the Superintendent of Documents. Prices of Airbus SAS, Airworthiness Office— provided an optional one-time HFEC
new books are listed in the first FEDERAL EAW, 1 Rond Point Maurice Bellonte, inspection that would terminate the
REGISTER issue of each week. 31707 Blagnac Cedex, France; telephone repetitive inspections. The NPRM
+33 5 61 93 36 96; fax +33 5 61 93 44 published in the Federal Register on
51; email account.airworth-eas@ April 27, 2016 (81 FR 24745). The
DEPARTMENT OF TRANSPORTATION airbus.com; Internet http:// NPRM was prompted by findings of
www.airbus.com. You may view this multiple fatigue cracks in the aft cargo
Federal Aviation Administration door that indicated the need for
referenced service information at the
FAA, Transport Airplane Directorate, repetitive HFEC inspections. The NPRM
14 CFR Part 39 proposed to continue to require
1601 Lind Avenue SW., Renton, WA.
[Docket No. FAA–2016–5596; Directorate For information on the availability of repetitive ultrasonic or detailed
Identifier 2015–NM–121–AD; Amendment this material at the FAA, call 425–227– inspections of the external area of the aft
39–18677; AD 2016–20–11] 1221. It is also available on the Internet cargo door sill beam for cracking, and
RIN 2120–AA64 at http://www.regulations.gov by repair if necessary. The NPRM also
searching for and locating Docket No. proposed to require the previously
Airworthiness Directives; Airbus FAA–2016–5596. optional terminating HFEC inspection,
Airplanes and to require that it be done
Examining the AD Docket repetitively. We are issuing this AD to
AGENCY: Federal Aviation You may examine the AD docket on detect and correct fatigue cracking of the
Administration (FAA), Department of the Internet at http:// cargo door sill beam, lock fitting, and
Transportation (DOT). www.regulations.gov by searching for torsion box plate. Failure of one or more
ACTION: Final rule. and locating Docket No. FAA–2016– of these components could result in the
5596, or in person at the Docket loss of the door locking function and,
SUMMARY: We are superseding Management Facility between 9 a.m. subsequently, complete loss of the cargo
Airworthiness Directive (AD) 2014–12– and 5 p.m., Monday through Friday, door in flight with the risk of rapid
06 for certain Airbus Model A300 B4– except Federal holidays. The AD docket decompression.
600, B4–600R, and F4–600R series contains this AD, the regulatory
airplanes, and Model A300 C4–605R The European Aviation Safety Agency
evaluation, any comments received, and (EASA), which is the Technical Agent
Variant F airplanes (collectively called other information. The address for the
Model A300–600 series airplanes); and for the Member States of the European
Docket Office (telephone 800–647–5527) Union, has issued EASA Airworthiness
Airbus Model A310 series airplanes. AD is Docket Management Facility, U.S.
2014–12–06 required repetitive Directive 2015–0150, dated July 23,
Department of Transportation, Docket 2015 (referred to after this as the
ultrasonic or detailed inspections of the Operations, M–30, West Building
external area of the aft cargo door sill Mandatory Continuing Airworthiness
Ground Floor, Room W12–140, 1200 Information, or ‘‘the MCAI’’), to correct
beam for cracking, and repair if New Jersey Avenue SE., Washington,
necessary, and provided an optional an unsafe condition for certain Airbus
DC 20590. Model A300 B4–600, B4–600R, and F4–
one-time high frequency eddy current
FOR FURTHER INFORMATION CONTACT: Dan 600R series airplanes, and Model A300
(HFEC) inspection that would terminate
Rodina, Aerospace Engineer, C4–605R Variant F airplanes
the repetitive inspections. This new AD
International Branch, ANM–116, (collectively called Model A300–600
requires the previously optional
Transport Airplane Directorate, FAA, series airplanes); and Airbus Model
terminating HFEC inspection, and
1601 Lind Avenue SW., Renton, WA A310 series airplanes. The MCAI states:
requires that it be done repetitively.
98057–3356; telephone 425–227–2125;
This AD was prompted by findings of During accomplishment of Maintenance
fax 425–227–1149.
multiple fatigue cracks in the aft cargo Review Board Report (MRBR) task 531625–
SUPPLEMENTARY INFORMATION: 01–1 on an A300–600 aeroplane having
door that indicated the need for
additional, repetitive, HFEC Discussion accumulated more than 25,000 flight cycles
inspections. We are issuing this AD to (FC) since aeroplane first flight, multiple
We issued a notice of proposed fatigue cracks were found on the following
address the unsafe condition on these rulemaking (NPRM) to amend 14 CFR parts:
products.
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part 39 to supersede AD 2014–12–06, —Aft cargo door sill beam Part Number
DATES: This AD is effective January 3, Amendment 39–17867 (79 FR 34403, (P/N) A53973085210.
2017. June 17, 2014) (‘‘AD 2014–12–06’’). AD —Lock fitting P/N A53978239002.
The Director of the Federal Register 2014–12–06 applied to certain Airbus —Torsion box plate P/N A53973318206.
approved the incorporation by reference Model A300 B4–600, B4–600R, and F4– Prompted by these findings, a stress
of certain publications listed in this AD 600R series airplanes, and Model A300 analysis was performed during which it was
as of January 3, 2017. C4–605R Variant F airplanes discovered that there is no dedicated
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![85838 Federal Register / Vol. 81, No. 229 / Tuesday, November 29, 2016 / Rules and Regulations
scheduled maintenance task to inspect the paragraph (i) of the proposed AD for • Are consistent with the intent that
affected area for fatigue damage. clarity and to change the location where was proposed in the NPRM for
This condition, if not detected and the reports should be sent. He stated correcting the unsafe condition; and
corrected, could lead to failure of multiple
lock fittings, possibly resulting in loss of the
that we could rewrite paragraph (i) of • Do not add any additional burden
cargo door in flight and consequent explosive the proposed AD to remove the upon the public than was already
decompression of the aeroplane. subparagraphs. proposed in the NPRM.
To address this unsafe condition, Airbus We partially agree with the request.
issued Alert Operators Transmission (AOT) Related Service Information Under 1
We have updated the contact
A53W005–14 providing instructions for CFR Part 51
information for submitting the reports.
inspection of the affected area.
Consequently, EASA issued Emergency AD We do not find it necessary, however, to Airbus has issued the following
2014–0097–E [which corresponded to FAA change the remainder of the paragraph service information, which describes
AD 2014–12–06] to require repetitive since it is restated from AD 2014–12–06, procedures for repetitive HFEC
ultrasonic (US) inspections or detailed and the compliance times are correct. inspections of the cargo door sill beam,
inspections (DET) of the aft cargo door sill lock fitting, and torsion box plate. These
beam external area, and/or a one-time High Request To Clarify the Terminating
service bulletins are distinct since they
Frequency Eddy Current (HFEC) inspection Actions
apply to different airplane models.
of the aft cargo door sill beam internal
structure and, depending on findings, Mark Hilborn requested we revise • Airbus Service Bulletin A300–53–
accomplishment of corrective action(s). paragraph (m) of the proposed AD for 6179, dated December 12, 2014.
Since that [EASA] AD was issued, the clarity and to add new subparagraphs to • Airbus Service Bulletin A310–53–
results of further analysis have indicated that aid in that. 2139, dated December 12, 2014.
repetitive HFEC inspections need to be
introduced.
We agree with the request and have Airbus has also issued AOT
For the reasons described above, this changed paragraph (m) of this AD A53W005–14, Revision 01, dated April
[EASA] AD retains the requirements of EASA accordingly. 29, 2014, which describes procedures
AD 2014–0097–E, which is superseded, and for doing an ultrasonic inspection or
Additional Changes Made in This Final
requires repetitive HFEC inspections of the detailed inspection of the aft cargo door
concerned areas. The first HFEC inspection Rule
sill beam external area for cracking.
terminates the repetitive US/DET
We have revised this AD to require Additionally, Airbus has issued the
inspections.
the current version of the service following service information, which
You may examine the MCAI in the information identified for the describes procedures for reinforcing the
AD docket on the Internet at http:// terminating action specified in this AD. aft cargo door sill beam are between FR
www.regulations.gov by searching for This service information was revised to
and locating Docket No. FAA–2016– 60 and FR 63. These service bulletins
make a small tooling change; no are distinct since they apply to different
5596. additional work is necessary for airplane models.
Comments airplanes on which the original version
• Airbus Service Bulletin A310–53–
of this service information was
We gave the public the opportunity to 2141, Revision 01, dated July 2, 2015.
accomplished. We have also added
participate in developing this AD. The
credit for airplanes on which the • Airbus Service Bulletin A300–53–
following presents the comments 6181, Revision 01, dated July 2, 2015.
original version of this service
received on the NPRM and the FAA’s This service information is reasonably
information was accomplished, and
response to each comment. available because the interested parties
made related changes accordingly.
Support for the NPRM have access to it through their normal
Conclusion course of business or by the means
The Air Line Pilots Association,
We reviewed the available data, identified in the ADDRESSES section.
International stated that it supports the
NPRM. including the comments received, and Costs of Compliance
determined that air safety and the
Request To Rewrite Reporting public interest require adopting this AD We estimate that this AD affects 75
Requirements with the changes described previously airplanes of U.S. registry.
One commenter, Mark Hilborn, and minor editorial changes. We have We estimate the following costs to
requested that we revise the structure of determined that these changes: comply with this AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspection ....................... 12 work-hours × $85 per hour = $1,020 per in- N/A ............ $1,020 per inspection $76,500 per inspection
spection cycle. cycle. cycle.
Reporting ....................... 1 work-hour × $85 per hour = $85 per inspection N/A ............ $85 ................................ $6,375.
cycle.
Paperwork Reduction Act Reduction Act unless that collection of and includes time for reviewing
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information displays a current valid instructions, as well as completing and
A federal agency may not conduct or OMB control number. The control reviewing the collection of information.
sponsor, and a person is not required to number for the collection of information Therefore, all reporting associated with
respond to, nor shall a person be subject required by this AD is 2120–0056. The this AD is mandatory. Comments
to penalty for failure to comply with a paperwork cost associated with this AD concerning the accuracy of this burden
collection of information subject to the has been detailed in the Costs of and suggestions for reducing the burden
requirements of the Paperwork Compliance section of this document should be directed to the FAA at 800
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![Federal Register / Vol. 81, No. 229 / Tuesday, November 29, 2016 / Rules and Regulations 85839
Independence Ave. SW., Washington, Authority: 49 U.S.C. 106(g), 40113, 44701. date of this AD, only Airbus AOT A53W005–
DC 20591, ATTN: Information 14, Revision 01, dated April 29, 2014, may
§ 39.13 [Amended] be used to comply with the requirements of
Collection Clearance Officer, AES–200.
■ 2. The FAA amends § 39.13 by this paragraph.
Authority for This Rulemaking removing AD 2014–12–06, Amendment (1) For airplanes that have accumulated
30,000 flight cycles or more since the
Title 49 of the United States Code 39–17867 (79 FR 34403, June 17, 2014), airplane’s first flight as of July 2, 2014 (the
specifies the FAA’s authority to issue and adding the following new AD: effective date of AD 2014–12–06): Within 50
rules on aviation safety. Subtitle I, 2016–20–11 Airbus: Amendment 39–18677; flight cycles after July 2, 2014.
section 106, describes the authority of Docket No. FAA–2016–5596; Directorate (2) For airplanes that have accumulated
the FAA Administrator. ‘‘Subtitle VII: Identifier 2015–NM–121–AD. 18,000 flight cycles or more, but fewer than
Aviation Programs,’’ describes in more 30,000 flight cycles since the airplane’s first
(a) Effective Date flight as of July 2, 2014 (the effective date of
detail the scope of the Agency’s
This AD is effective January 3, 2017. AD 2014–12–06): Within 275 flight cycles
authority.
after July 2, 2014.
We are issuing this rulemaking under (b) Affected ADs (3) For airplanes that have accumulated
the authority described in ‘‘Subtitle VII, This AD replaces AD 2014–12–06, fewer than 18,000 flight cycles since the
Part A, Subpart III, Section 44701: Amendment 39–17867 (79 FR 34403, June airplane’s first flight as of July 2, 2014 (the
General requirements.’’ Under that 17, 2014) (‘‘AD 2014–12–06’’). effective date of AD 2014–12–06): Before
section, Congress charges the FAA with exceeding 18,275 flight cycles since the
(c) Applicability airplane’s first flight.
promoting safe flight of civil aircraft in
air commerce by prescribing regulations This AD applies to the airplanes identified
in paragraphs (c)(1), (c)(2), (c)(3), (c)(4), and (h) Retained Optional Terminating Action,
for practices, methods, and procedures With Revised Service Information and
(c)(5) of this AD, certificated in any category,
the Administrator finds necessary for all manufacturer serial numbers on which Specific Delegation Approval Language
safety in air commerce. This regulation Airbus Modification 05438 has been This paragraph restates the provisions of
is within the scope of that authority embodied in production, except those on paragraph (h) of AD 2014–12–06, with
because it addresses an unsafe condition which Airbus Modification 12046 has been revised service information and specific
that is likely to exist or develop on embodied in production. delegation approval language.
products identified in this rulemaking (1) Airbus Model A300 B4–601, B4–603, Accomplishment of a high frequency eddy
action. B4–620, and B4–622 airplanes. current (HFEC) inspection for cracking, in
(2) Airbus Model A300 B4–605R and B4– accordance with Airbus AOT A53W005–14,
Regulatory Findings 622R airplanes. dated April 22, 2014; or Airbus AOT
(3) Airbus Model A300 F4–605R and F4– A53W005–14, Revision 01, dated April 29,
We determined that this AD will not
622R airplanes. 2014; terminates the repetitive inspections
have federalism implications under (4) Airbus Model A300 C4–605R Variant F required by paragraph (g) of this AD for that
Executive Order 13132. This AD will airplanes. airplane. If any cracking is found during the
not have a substantial direct effect on (5) Airbus Model A310–203, –204, –221, HFEC inspection, before further flight, repair
the States, on the relationship between –222, –304, –322, –324, and –325 airplanes. using a method approved by the Manager,
the national government and the States, International Branch, ANM–116, Transport
(d) Subject Airplane Directorate, FAA; or the European
or on the distribution of power and
responsibilities among the various Air Transport Association (ATA) of Aviation Safety Agency (EASA); or Airbus’s
America Code 53, Fuselage. EASA Design Organization Approval (DOA).
levels of government.
For the reasons discussed above, I (e) Reason (i) Retained Reporting Requirement, With
certify that this AD: This AD was prompted by reports of Revised Contact Information
1. Is not a ‘‘significant regulatory fatigue cracks on the cargo door sill beam, This paragraph restates the provisions of
action’’ under Executive Order 12866; lock fitting, and torsion box plate. We are paragraph (i) of AD 2014–12–06, with revised
2. Is not a ‘‘significant rule’’ under the issuing this AD to detect and correct fatigue contact information. Submit a report of the
DOT Regulatory Policies and Procedures cracking of the cargo door sill beam, lock findings (both positive and negative) of the
(44 FR 11034, February 26, 1979); fitting, and torsion box plate, which could inspection required by paragraph (g) of this
3. Will not affect intrastate aviation in result in the loss of the door locking function AD to ‘‘Airbus Service Bulletin Reporting
Alaska; and and subsequently, complete loss of the cargo Online Application’’ on Airbus World
door in flight with the risk of rapid (https://w3.airbus.com/), at the applicable
4. Will not have a significant
decompression. time specified in paragraph (i)(1) or (i)(2) of
economic impact, positive or negative,
this AD. The report must include the
on a substantial number of small entities (f) Compliance
inspection results, including no findings.
under the criteria of the Regulatory Comply with this AD within the (1) If the inspection was done on or after
Flexibility Act. compliance times specified, unless already the effective date of this AD: Submit the
done. report within 30 days after the inspection.
List of Subjects in 14 CFR Part 39 (2) If the inspection was done before the
(g) Retained Inspection, With Revised
Air transportation, Aircraft, Aviation Service Information effective date of this AD: Submit the report
safety, Incorporation by reference, within 30 days after the effective date of this
This paragraph restates the requirements of AD.
Safety.
paragraph (g)(1) of AD 2014–12–06, with
Adoption of the Amendment revised service information. Within the (j) Definition of Airplane Groups
compliance time identified in paragraph Paragraphs (k)(1), (k)(2), and (k)(3) of this
Accordingly, under the authority (g)(1), (g)(2), or (g)(3) of this AD, as AD refer to airplane groups, as identified in
delegated to me by the Administrator, applicable: Do an ultrasonic inspection or paragraphs (j)(1), (j)(2), and (j)(3) of this AD.
the FAA amends 14 CFR part 39 as
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detailed inspection of the aft cargo door sill (1) Airplanes on which an HFEC
follows: beam external area for cracking, in inspection was accomplished as specified in
accordance with Airbus Alert Operators Airbus AOT A53W005–14.
PART 39—AIRWORTHINESS Transmission (AOT) A53W005–14, dated (2) Airplanes on which no HFEC
DIRECTIVES April 22, 2014; or Airbus AOT A53W005–14, inspection was accomplished as specified in
Revision 01, dated April 29, 2014. Repeat the Airbus AOT A53W005–14, and that have
■ 1. The authority citation for part 39 inspection thereafter at intervals not to accumulated more than 18,000 total flight
continues to read as follows: exceed 275 flight cycles. As of the effective cycles as of the effective date of this AD.
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![85840 Federal Register / Vol. 81, No. 229 / Tuesday, November 29, 2016 / Rules and Regulations
(3) Airplanes on which no HFEC Branch, ANM–116, Transport Airplane Airworthiness Directive 2015–0150, dated
inspection was accomplished as specified in Directorate, FAA, has the authority to July 23, 2015, for related information. This
Airbus AOT A53W005–14, that have approve AMOCs for this AD, if requested MCAI may be found in the AD docket on the
accumulated 18,000 total flight cycles or using the procedures found in 14 CFR 39.19. Internet at http://www.regulations.gov by
fewer as of the effective date of this AD. In accordance with 14 CFR 39.19, send your searching for and locating Docket No. FAA–
request to your principal inspector or local 2016–5596.
(k) New Repetitive HFEC Inspections and Flight Standards District Office, as
Repair (2) Service information identified in this
appropriate. If sending information directly
AD that is not incorporated by reference is
At the applicable time specified in to the International Branch, send it to ATTN:
paragraph (k)(1), (k)(2), or (k)(3) of this AD: available at the addresses specified in
Dan Rodina, Aerospace Engineer,
Do an HFEC inspection for fatigue cracking International Branch, ANM–116, Transport paragraphs (q)(5) and (q)(6) of this AD.
of the cargo door sill beam, lock fitting, and Airplane Directorate, FAA, 1601 Lind (q) Material Incorporated by Reference
torsion box plate, in accordance with Airbus Avenue SW., Renton, WA 98057–3356;
Service Bulletin A300–53–6179, dated telephone 425–227–2125; fax 425–227–1149. (1) The Director of the Federal Register
December 12, 2014; or Airbus Service Information may be emailed to: 9-ANM-116- approved the incorporation by reference
Bulletin A310–53–2139, dated December 12, AMOC-REQUESTS@faa.gov. Before using (IBR) of the service information listed in this
2014; as applicable. Repeat the HFEC any approved AMOC, notify your appropriate paragraph under 5 U.S.C. 552(a) and 1 CFR
inspection thereafter at intervals not to principal inspector, or lacking a principal part 51.
exceed 4,600 flight cycles. inspector, the manager of the local flight (2) You must use this service information
(1) For airplanes identified in paragraph standards district office/certificate holding as applicable to do the actions required by
(j)(1) of this AD: Inspect within 4,600 flight district office. The AMOC approval letter this AD, unless this AD specifies otherwise.
cycles after the most recent HFEC inspection must specifically reference this AD. (3) The following service information was
specified in Airbus AOT A53W005–14. (2) Contacting the Manufacturer: As of the approved for IBR on January 3, 2017.
(2) For airplanes identified in paragraph effective date of this AD, for any requirement (i) Airbus Alert Operators Transmission
(j)(2) of this AD: Inspect within 2,000 flight in this AD to obtain corrective actions from (AOT) A53W005–14, Revision 01, dated
cycles after the effective date of this AD. a manufacturer, the action must be April 29, 2014.
(3) For airplanes identified in paragraph accomplished using a method approved by
(j)(3) of this AD: Inspect before exceeding (ii) Airbus Service Bulletin A310–53–2141,
the Manager, International Branch, ANM– Revision 01, dated July 2, 2015.
13,000 total flight cycles since the airplane’s 116, Transport Airplane Directorate, FAA; or
first flight, or within 2,000 flight cycles after (iii) Airbus Service Bulletin A300–53–
the EASA; or Airbus’s EASA DOA. If
the effective date of this AD, whichever 6179, dated December 12, 2014.
approved by the DOA, the approval must
occurs later. (iv) Airbus Service Bulletin A300–53–
include the DOA-authorized signature.
(3) Reporting Requirements: A federal 6181, Revision 01, dated July 2, 2015.
(l) Corrective Action (v) Airbus Service Bulletin A310–53–2139,
agency may not conduct or sponsor, and a
If any crack is found during any inspection person is not required to respond to, nor dated December 12, 2014.
required by paragraph (g) or (k) of this AD: (4) The following service information was
shall a person be subject to a penalty for
Before further flight, repair using a method approved for IBR on July 2, 2014 (79 FR
failure to comply with a collection of
approved by the Manager, International 34403, June 17, 2014).
information subject to the requirements of
Branch, ANM–116, Transport Airplane (i) Airbus AOT A53W005–14, dated April
the Paperwork Reduction Act unless that
Directorate, FAA; or the EASA; or Airbus’s
collection of information displays a current 22, 2014.
EASA DOA.
valid OMB Control Number. The OMB (ii) Reserved.
(m) Terminating Action for Repetitive Control Number for this information (5) For service information identified in
Inspections collection is 2120–0056. Public reporting for this AD, contact Airbus SAS, Airworthiness
This paragraph identifies the requirements this collection of information is estimated to Office—EAW, 1 Rond Point Maurice
to terminate repetitive inspections mandated be approximately 5 minutes per response, Bellonte, 31707 Blagnac Cedex, France;
by this AD. including the time for reviewing instructions, telephone +33 5 61 93 36 96; fax +33 5 61
(1) For any airplane identified in completing and reviewing the collection of 93 44 51; email account.airworth-eas@
paragraphs (j)(2) and (j)(3) of this AD, information. All responses to this collection airbus.com; Internet http://www.airbus.com.
accomplishment of the initial inspection of information are mandatory. Comments
You may view this service information at the
required by paragraph (k) of this AD concerning the accuracy of this burden and
FAA, Transport Airplane Directorate, 1601
terminates the repetitive inspections required suggestions for reducing the burden should
be directed to the FAA at: 800 Independence Lind Avenue SW., Renton, WA. For
by paragraph (g) of this AD. information on the availability of this
(2) For any airplane identified in Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, material at the FAA, call 425–227–1221.
paragraphs (c)(1) through (c)(5) of this AD,
AES–200. (6) You may view this service information
accomplishment of Airbus Service Bulletin
A310–53–2141, Revision 01, dated July 2, (4) Required for Compliance (RC): Except at the FAA, Transport Airplane Directorate,
2015; or Airbus Service Bulletin A300–53– as required by paragraph (l) of this AD: If any 1601 Lind Avenue SW., Renton, WA. For
6181, Revision 01, dated July 2, 2015; as service information contains procedures or information on the availability of this
applicable; terminates the repetitive tests that are identified as RC, those material at the FAA, call 425–227–1221.
inspections required by paragraph (k) of this procedures and tests must be done to comply (7) You may view this service information
AD. with this AD; any procedures or tests that are that is incorporated by reference at the
not identified as RC are recommended. Those National Archives and Records
(n) Credit for Previous Actions procedures and tests that are not identified Administration (NARA). For information on
This paragraph provides credit for actions as RC may be deviated from using accepted the availability of this material at NARA, call
provided in paragraph (m)(2) of this AD, if methods in accordance with the operator’s 202–741–6030, or go to: http://
those actions were performed before the maintenance or inspection program without www.archives.gov/federal-register/cfr/ibr-
effective date of this AD using Airbus Service obtaining approval of an AMOC, provided locations.html.
Bulletin A300–53–6181, dated June 26, 2015; the procedures and tests identified as RC can
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or Airbus Service Bulletin A310–53–2141, be done and the airplane can be put back in Issued in Renton, Washington, on
dated June 26, 2015; as applicable. an airworthy condition. Any substitutions or September 28, 2016.
changes to procedures or tests identified as Dionne Palermo,
(o) Other FAA AD Provisions RC require approval of an AMOC. Acting Manager, Transport Airplane
The following provisions also apply to this
(p) Related Information Directorate, Aircraft Certification Service.
AD:
(1) Alternative Methods of Compliance (1) Refer to Mandatory Continuing [FR Doc. 2016–28335 Filed 11–28–16; 8:45 am]
(AMOCs): The Manager, International Airworthiness Information (MCAI) EASA BILLING CODE 4910–13–P
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Document Created: 2016-11-29 00:33:17
Document Modified: 2016-11-29 00:33:17
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective January 3, 2017. | |
| Contact | 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. | |
| FR Citation | 81 FR 85837 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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