82 FR 56865 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 230 (December 1, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 230 (December 1, 2017)
| Page Range | 56865-56869 | |
| FR Document | 2017-25763 |
[Federal Register Volume 82, Number 230 (Friday, December 1, 2017)] [Rules and Regulations] [Pages 56865-56869] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-25763] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0708; Product Identifier 2017-NM-035-AD; Amendment 39-19113; AD 2017-24-09] 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) 2016-20-11, which 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 2016-20-11 required repetitive inspections of the external area of the aft cargo door sill beam for cracking, repetitive inspections for fatigue cracking of the cargo door sill beam, lock fitting, and torsion box plate, and repair if necessary. This new AD retains the inspections for cracking, and repair if necessary; and requires reinforcement of the aft cargo door sill beam area. This AD was prompted by the development of a reinforcement modification of the aft cargo door sill beam area, which constitutes terminating action for the repetitive inspections. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 5, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 2, 2014 (79 FR 34403, June 17, 2014). The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of January 3, 2017 (81 FR 85837, November 29, 2016). 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 Standards Branch, 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-2017- 0708. 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-2017- 0708; 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 Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; [[Page 56866]] 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 2016-20-11, Amendment 39-18677 (81 FR 85837, November 29, 2016) (``AD 2016-20-11''). AD 2016-20-11 applied to certain Airbus Model A300-600 series airplanes; and Airbus Model A310 series airplanes. The NPRM published in the Federal Register on July 27, 2017 (82 FR 34891). The NPRM was prompted by a determination that reinforcement of the aft cargo door sill beam area is necessary to address the unsafe condition, which constitutes terminating action for the repetitive inspections. The NPRM proposed to continue to require repetitive inspections of the external area of the aft cargo door sill beam for cracking, repetitive inspections for fatigue cracking of the cargo door sill beam, lock fitting, and torsion box plate, and repair if necessary. The NPRM also proposed to require reinforcement of the aft cargo door sill beam area. We are issuing this AD to prevent 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, loss of the cargo door in flight and rapid decompression. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017-0048, dated March 15, 2017; corrected April 20, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A300-600 series airplanes; and Airbus Model A310 series airplanes. The MCAI states: In the frame of the widespread fatigue damage (WFD) compliance study and after an in-service occurrence, the area of the aft cargo door sill beam and adjacent structure was identified as sensitive to the fatigue loads. 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 potential unsafe condition, Airbus issued Alert Operators Transmission (AOT) A53W005-14 providing inspection instructions and, consequently, EASA issued Emergency AD 2014-0097-E [which corresponded to FAA AD 2014-12-06, Amendment 39-17867, (79 FR 34403, June 17, 2014)] to require repetitive ultrasonic inspections (US) or detailed inspections (DET) of the aft cargo door sill beam area [and corrective actions if necessary]. After that [EASA] AD was issued, further analysis indicated that repetitive high frequency eddy current (HFEC) inspections needed to be introduced, and Airbus published Service Bulletin (SB) A310-53- 2139 and SB A300-53-6179 to provide instructions. Prompted by this determination, EASA issued AD 2015-0150 [which corresponded to FAA AD 2016-20-11], retaining the requirements of EASA Emergency AD 2014-0097-E, which was superseded, and required repetitive HFEC inspections of the concerned areas. The first HFEC inspection terminated the repetitive US/DET inspections. That [EASA] AD also required the inspection results to be reported. Since that [EASA] AD was issued, Airbus developed a reinforcement modification of the aft cargo door sill beam area, and published Airbus SB A310-53-2141 and SB A300-53-6181, which were revised lately, to make this available for in-service application. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2015-0150, which is superseded, and requires modification [reinforcement] of the aft cargo door sill beam, which constitutes terminating action for the repetitive inspections. This [EASA] AD is re-published to correct the compliance time description in Table 4. 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-2017- 0708. 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. Request To Make the Mandatory Terminating Modification Optional FedEx requested that the terminating modification in paragraph (n) of the proposed AD be made an optional action. FedEx stated that they have inspected their airplanes as required by AD 2016-20-11 and have not found any cracks during HFEC inspections. FedEx noted that they have inspected airplanes having accumulated anywhere from 12,000 total flight cycles to 40,000 total flight cycles. FedEx suggested that the modification would be necessary on less than 1 percent of inspected airplanes over the next 10 years. FedEx claimed that the modification is an unproven change that has not been subjected to full scale fatigue testing. For these reasons, FedEx argued that inspections alone will maintain safe airworthiness for the affected airplanes. We disagree with the commenter's request. EASA, as the State of Design Authority for Airbus products, has determined an unsafe conditions exists after conducting a risk analysis taking into consideration in-service data for the worldwide fleet. We agree with EASA's risk assessment and their decision to mitigate the risk by mandating the modification in this AD. FedEx has not provided sufficient data to support their request to allow inspections in lieu of the modification. We have not changed this AD in this regard. Request To Update the Costs for the Modification FedEx requested that we update the labor costs for the modification in the proposed AD. FedEx stated that their labor costs for the modification will be an additional $10,000 per airplane. FedEx further noted that the modification would extend their service checks, resulting in additional out-of-service time for their airplanes and additional expenses. We partially agree with the commenter's request. The number of work-hours to complete the modification depends on the airplane's configuration. In the NPRM, we used the 40 work-hours estimate for the configuration that requires less time to modify. We have updated this final rule to reflect work-hour costs of up to 68 hours (the estimated work-hours for the other configuration) for the required modification. Regarding the additional costs related to extended service checks, we do not consider it appropriate to attribute the costs associated with aircraft ``downtime'' to the AD. Normally, compliance with the AD will not necessitate any additional downtime beyond that of a regularly scheduled maintenance hold. Even if additional downtime is necessary for some airplanes in some cases, we do not have sufficient information to evaluate the number of airplanes that may be affected or the amount of additional downtime that may be required. Therefore, we are unable to provide an estimate for these variable costs. We have made no further change to this final rule regarding this issue. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor 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. [[Page 56867]] Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300-53-6181, Revision 01, dated July 2, 2015; and Service Bulletin A310-53-2141, Revision 01, dated July 2, 2015. This service information describes procedures for reinforcing the aft cargo door sill beam area. These documents are distinct since they apply to different airplane models. Airbus has also issued Service Bulletin A300-53-6179, dated December 12, 2014; and Service Bulletin A310-53-2139, dated December 12, 2014. This service information describes procedures for repetitive HFEC inspections of the cargo door sill beam, lock fitting, and torsion box plate. These documents are distinct since they apply to different airplane models. Airbus has also issued Alert Operators Transmission 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. 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 (retained action 12 work-hours x $85 per N/A $1,020 per $76,500 per from AD 2016[dash]20[dash]11). hour = $1,020 per inspection cycle. inspection cycle. inspection cycle. Modification (new action)...... Up to 68 work-hours x $96,890 Up to $102,670.... Up to $7,700,250. $85 per hour = $5,780. Reporting (retained action from 1 work hour x $85 per $0 $85 per inspection $6,375 per AD 2016[dash]20[dash]11). hour = $85 per cycle. inspection cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that will enable us to provide cost estimates for the on-condition actions specified in this AD. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120- 0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES-200. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. 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) 2016-20-11, Amendment 39-18677 (81 FR 85837, November 29, 2016), and adding the following new AD: 2017-24-09 Airbus: Amendment 39-19113; Docket No. FAA-2017-0708; Product Identifier 2017-NM-035-AD. (a) Effective Date This AD is effective January 5, 2018. [[Page 56868]] (b) Affected ADs This AD replaces AD 2016-20-11, Amendment 39-18677 (81 FR 85837, November 29, 2016) (``AD 2016-20-11''). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) through (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 prevent 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, loss of the cargo door in flight and rapid decompression. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2016-20-11, with no changes. 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 January 3, 2017 (the effective date of AD 2016-20-11), use only Airbus AOT A53W005-14, Revision 01, dated April 29, 2014, 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, Amendment 39-17867, (79 FR 34403, June 17, 2014) (``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 No Changes This paragraph restates the provisions of paragraph (h) of AD 2016-20-11, with no changes. Accomplishment of a high frequency eddy current (HFEC) inspection for cracking, in accordance with Airbus AOT A53W005-14, dated April 22, 2014; or 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 Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (i) Retained Reporting Requirement, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2016-20-11, with no changes. 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 January 3, 2017 (the effective date of AD 2016-20-11): Submit the report within 30 days after the inspection. (2) If the inspection was done before January 3, 2017 (the effective date of AD 2016-20-11): Submit the report within 30 days after January 3, 2017. (j) Retained Definition of Airplane Groups, With No Changes This paragraph restates the definitions specified in paragraph (j) of AD 2016-20-11, with no changes. 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, that have accumulated more than 18,000 total flight cycles as of January 3, 2017 (the effective date of AD 2016-20-11). (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 January 3, 2017 (the effective date of AD 2016-20-11). (k) Retained Repetitive HFEC Inspections, With No Changes This paragraph restates the requirements of paragraph (k) of AD 2016-20-11, with no changes. 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 January 3, 2017 (the effective date of AD 2016-20-11). (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 January 3, 2017 (the effective date of AD 2016-20-11), whichever occurs later. (l) Retained Corrective Action, With No Changes This paragraph restates the requirements of paragraph (l) of AD 2016-20-11, with no changes. 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 Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. (m) Retained Terminating Action for Repetitive Inspections in Paragraph (g) of This AD, With No Changes This paragraph restates the terminating action of paragraph (m)(1) of AD 2016-20-11, with no changes. 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. (n) New Cargo Door Reinforcement At the latest of the applicable times specified in paragraphs (n)(1), (n)(2), and (n)(3) of this AD: Reinforce the aft cargo door sill beam area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6181, Revision 01, dated July 2, 2015; or Airbus Service Bulletin A310-53-2141, Revision 01, dated July 2, 2015; as applicable. (1) Before exceeding 19,600 flight cycles since first flight of the airplane. (2) Within 2,300 flight cycles after the last HFEC or detailed inspection required by this AD that was accomplished before the effective date of this AD. (3) Within 12 months after the effective date of this AD. (o) New Terminating Action Modification of an airplane as required by paragraph (n) of this AD constitutes terminating action for the repetitive inspections required by paragraphs (g) and (k) of this AD for the modified airplane only. [[Page 56869]] (p) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (n) 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. (q) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, 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 Section, send it to the attention of the person identified in paragraph (r)(2) of this AD. Information may be emailed to: [email protected]. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (ii) AMOCs approved previously for AD 2016-20-11 are approved as AMOCs for the corresponding provisions of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or 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 1 hour 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. (r) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017-0048, dated March 15, 2017; corrected April 20, 2017, 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-2017-0708. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (s)(5) and (s)(6) of this AD. (s) 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 July 2, 2014 (79 FR 34403, June 17, 2014). (i) Airbus Alert Operators Transmission A53W005-14, dated April 22, 2014. (ii) Reserved. (4) The following service information was approved for IBR on January 3, 2017, (81 FR 85837, November 29, 2016). (i) Airbus Alert Operators Transmission A53W005-14, Revision 01, dated April 29, 2014. (ii) Airbus Service Bulletin A300-53-6179, dated December 12, 2014. (iii) Airbus Service Bulletin A300-53-6181, Revision 01, dated July 2, 2015. (iv) Airbus Service Bulletin A310-53-2139, dated December 12, 2014. (v) Airbus Service Bulletin A310-53-2141, Revision 01, dated July 2, 2015. (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. (6) You may view this service information at the FAA, Transport Standards Branch, 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 November 22, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017-25763 Filed 11-30-17; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / Rules and Regulations 56865
Section, Transport Standards Branch, FAA, (3) The following service information was beam, lock fitting, and torsion box plate,
has the authority to approve AMOCs for this approved for IBR on January 5, 2018. and repair if necessary. This new AD
AD, if requested using the procedures found (i) Airbus Service Bulletin A320–27–1206, retains the inspections for cracking, and
in 14 CFR 39.19. In accordance with 14 CFR Revision 02, dated November 2, 2015.
39.19, send your request to your principal
repair if necessary; and requires
(ii) Reserved.
inspector or local Flight Standards District (4) The following service information was reinforcement of the aft cargo door sill
Office, as appropriate. If sending information approved for IBR on March 26, 2014 (79 FR beam area. This AD was prompted by
directly to the International Section, send it 9398, February 19, 2014). the development of a reinforcement
to the attention of the person identified in (i) Airbus Service Bulletin A320–27–1206, modification of the aft cargo door sill
paragraph (o)(2) of this AD. Information may Revision 01, dated October 10, 2011. beam area, which constitutes
be emailed to: 9-ANM-116-AMOC- (ii) Reserved. terminating action for the repetitive
REQUESTS@faa.gov. (5) For service information identified in inspections. We are issuing this AD to
(i) Before using any approved AMOC, this AD, contact Airbus, Airworthiness
notify your appropriate principal inspector, address the unsafe condition on these
Office—EIAS, 1 Rond Point Maurice
or lacking a principal inspector, the manager products.
Bellonte, 31707 Blagnac Cedex, France;
of the local flight standards district office/ telephone +33 5 61 93 36 96; fax +33 5 61 DATES: This AD is effective January 5,
certificate holding district office. 93 44 51; email account.airworth-eas@ 2018.
(ii) AMOCs approved previously for AD airbus.com; Internet http://www.airbus.com. The Director of the Federal Register
2014–08–01 are approved as AMOCs for the (6) You may view this service information
corresponding provisions of paragraphs (g)
approved the incorporation by reference
at the FAA, Transport Standards Branch, of a certain publication listed in this AD
and (h) of this AD. 1601 Lind Avenue SW., Renton, WA. For
(2) Contacting the Manufacturer: As of the as of July 2, 2014 (79 FR 34403, June 17,
information on the availability of this
effective date of this AD, for any requirement material at the FAA, call 425–227–1221.
2014).
in this AD to obtain corrective actions from (7) You may view this service information
The Director of the Federal Register
a manufacturer, the action must be that is incorporated by reference at the approved the incorporation by reference
accomplished using a method approved by National Archives and Records of certain other publications listed in
the Manager, International Section, Transport this AD as of January 3, 2017 (81 FR
Administration (NARA). For information on
Standards Branch, FAA; or the European 85837, November 29, 2016).
the availability of this material at NARA, call
Aviation Safety Agency (EASA); or Airbus’s
202–741–6030, or go to: http:// ADDRESSES: For service information
EASA Design Organization Approval (DOA).
www.archives.gov/federal-register/cfr/ibr- identified in this final rule, contact
If approved by the DOA, the approval must
locations.html.
include the DOA-authorized signature. Airbus SAS, Airworthiness Office—
(3) Required for Compliance (RC): If any Issued in Renton, Washington, on EAW, 1 Rond Point Maurice Bellonte,
service information contains procedures or November 16, 2017. 31707 Blagnac Cedex, France; telephone
tests that are identified as RC, those Chris Spangenberg, +33 5 61 93 36 96; fax +33 5 61 93 44
procedures and tests must be done to comply Acting Director, System Oversight Division, 51; email account.airworth-eas@
with this AD; any procedures or tests that are
Aircraft Certification Service. airbus.com; Internet http://
not identified as RC are recommended. Those
procedures and tests that are not identified [FR Doc. 2017–25557 Filed 11–30–17; 8:45 am] www.airbus.com. You may view this
as RC may be deviated from using accepted BILLING CODE 4910–13–P referenced service information at the
methods in accordance with the operator’s FAA, Transport Standards Branch, 1601
maintenance or inspection program without Lind Avenue SW., Renton, WA. For
obtaining approval of an AMOC, provided DEPARTMENT OF TRANSPORTATION information on the availability of this
the procedures and tests identified as RC can material at the FAA, call 425–227–1221.
be done and the airplane can be put back in Federal Aviation Administration It is also available on the Internet at
an airworthy condition. Any substitutions or
changes to procedures or tests identified as http://www.regulations.gov by searching
14 CFR Part 39 for and locating Docket No. FAA–2017–
RC require approval of an AMOC.
[Docket No. FAA–2017–0708; Product 0708.
(o) Related Information
Identifier 2017–NM–035–AD; Amendment Examining the AD Docket
(1) Refer to Mandatory Continuing 39–19113; AD 2017–24–09]
Airworthiness Information (MCAI) EASA AD You may examine the AD docket on
2016–0113, dated June 15, 2016, for related RIN 2120–AA64 the Internet at http://
information. This MCAI may be found in the www.regulations.gov by searching for
AD docket on the Internet at http:// Airworthiness Directives; Airbus and locating Docket No. FAA–2017–
www.regulations.gov by searching for and Airplanes
locating Docket No. FAA–2017–0476. 0708; or in person at the Docket
(2) For more information about this AD, AGENCY: Federal Aviation Management Facility between 9 a.m.
contact Sanjay Ralhan, Aerospace Engineer, Administration (FAA), Department of and 5 p.m., Monday through Friday,
International Section, Transport Standards Transportation (DOT). except Federal holidays. The AD docket
Branch, FAA, 1601 Lind Avenue SW.,
ACTION: Final rule.
contains this AD, the regulatory
Renton, Washington 98057–3356; telephone evaluation, any comments received, and
425–227–1405; fax 425–227–1149. SUMMARY: We are superseding other information. The address for the
(3) Service information identified in this Docket Office (telephone 800–647–5527)
AD that is not incorporated by reference is Airworthiness Directive (AD) 2016–20–
available at the addresses specified in 11, which applied to certain Airbus is Docket Management Facility, U.S.
paragraphs (p)(5) and (p)(6) of this AD. Model A300 B4–600, B4–600R, and F4– Department of Transportation, Docket
600R series airplanes, and Model A300 Operations, M–30, West Building
(p) Material Incorporated by Reference Ground Floor, Room W12–140, 1200
C4–605R Variant F airplanes
jstallworth on DSKBBY8HB2PROD with RULES
(1) The Director of the Federal Register (collectively called Model A300–600 New Jersey Avenue SE., Washington,
approved the incorporation by reference series airplanes); and Airbus Model DC 20590.
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
A310 series airplanes. AD 2016–20–11 FOR FURTHER INFORMATION CONTACT: Dan
part 51. required repetitive inspections of the Rodina, Aerospace Engineer,
(2) You must use this service information external area of the aft cargo door sill International Section, Transport
as applicable to do the actions required by beam for cracking, repetitive inspections Standards Branch, FAA, 1601 Lind
this AD, unless this AD specifies otherwise. for fatigue cracking of the cargo door sill Avenue SW., Renton, WA 98057–3356;
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![56866 Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / Rules and Regulations
telephone 425–227–2125; fax 425–227– (DET) of the aft cargo door sill beam area after conducting a risk analysis taking
1149. [and corrective actions if necessary]. into consideration in-service data for the
After that [EASA] AD was issued, further worldwide fleet. We agree with EASA’s
SUPPLEMENTARY INFORMATION:
analysis indicated that repetitive high
risk assessment and their decision to
Discussion frequency eddy current (HFEC) inspections
needed to be introduced, and Airbus mitigate the risk by mandating the
We issued a notice of proposed published Service Bulletin (SB) A310–53– modification in this AD. FedEx has not
rulemaking (NPRM) to amend 14 CFR 2139 and SB A300–53–6179 to provide provided sufficient data to support their
part 39 to supersede AD 2016–20–11, instructions. Prompted by this determination, request to allow inspections in lieu of
Amendment 39–18677 (81 FR 85837, EASA issued AD 2015–0150 [which the modification. We have not changed
November 29, 2016) (‘‘AD 2016–20– corresponded to FAA AD 2016–20–11], this AD in this regard.
11’’). AD 2016–20–11 applied to certain retaining the requirements of EASA
Emergency AD 2014–0097–E, which was Request To Update the Costs for the
Airbus Model A300–600 series
superseded, and required repetitive HFEC Modification
airplanes; and Airbus Model A310 inspections of the concerned areas. The first
series airplanes. The NPRM published FedEx requested that we update the
HFEC inspection terminated the repetitive
in the Federal Register on July 27, 2017 US/DET inspections. That [EASA] AD also labor costs for the modification in the
(82 FR 34891). The NPRM was required the inspection results to be reported. proposed AD. FedEx stated that their
prompted by a determination that Since that [EASA] AD was issued, Airbus labor costs for the modification will be
reinforcement of the aft cargo door sill developed a reinforcement modification of an additional $10,000 per airplane.
beam area is necessary to address the the aft cargo door sill beam area, and FedEx further noted that the
unsafe condition, which constitutes published Airbus SB A310–53–2141 and SB modification would extend their service
A300–53–6181, which were revised lately, to checks, resulting in additional out-of-
terminating action for the repetitive make this available for in-service application.
inspections. The NPRM proposed to service time for their airplanes and
For the reasons described above, this
continue to require repetitive [EASA] AD retains the requirements of EASA additional expenses.
inspections of the external area of the aft AD 2015–0150, which is superseded, and We partially agree with the
cargo door sill beam for cracking, requires modification [reinforcement] of the commenter’s request. The number of
repetitive inspections for fatigue aft cargo door sill beam, which constitutes work-hours to complete the
cracking of the cargo door sill beam, terminating action for the repetitive modification depends on the airplane’s
lock fitting, and torsion box plate, and inspections. configuration. In the NPRM, we used
This [EASA] AD is re-published to correct the 40 work-hours estimate for the
repair if necessary. The NPRM also the compliance time description in Table 4.
proposed to require reinforcement of the configuration that requires less time to
aft cargo door sill beam area. We are You may examine the MCAI in the modify. We have updated this final rule
issuing this AD to prevent fatigue AD docket on the Internet at http:// to reflect work-hour costs of up to 68
cracking of the cargo door sill beam, www.regulations.gov by searching for hours (the estimated work-hours for the
lock fitting, and torsion box plate, and locating Docket No. FAA–2017– other configuration) for the required
which could result in the loss of the 0708. modification.
door locking function and subsequently, Regarding the additional costs related
Comments to extended service checks, we do not
loss of the cargo door in flight and rapid
We gave the public the opportunity to consider it appropriate to attribute the
decompression.
The European Aviation Safety Agency participate in developing this AD. The costs associated with aircraft
(EASA), which is the Technical Agent following presents the comments ‘‘downtime’’ to the AD. Normally,
for the Member States of the European received on the NPRM and the FAA’s compliance with the AD will not
Union, has issued EASA AD 2017–0048, response to each comment. necessitate any additional downtime
dated March 15, 2017; corrected April Request To Make the Mandatory beyond that of a regularly scheduled
20, 2017 (referred to after this as the Terminating Modification Optional maintenance hold. Even if additional
Mandatory Continuing Airworthiness downtime is necessary for some
FedEx requested that the terminating airplanes in some cases, we do not have
Information, or ‘‘the MCAI’’), to correct modification in paragraph (n) of the
an unsafe condition for certain Airbus sufficient information to evaluate the
proposed AD be made an optional number of airplanes that may be
Model A300–600 series airplanes; and action. FedEx stated that they have
Airbus Model A310 series airplanes. affected or the amount of additional
inspected their airplanes as required by downtime that may be required.
The MCAI states: AD 2016–20–11 and have not found any Therefore, we are unable to provide an
In the frame of the widespread fatigue cracks during HFEC inspections. FedEx estimate for these variable costs. We
damage (WFD) compliance study and after an noted that they have inspected airplanes
in-service occurrence, the area of the aft have made no further change to this
having accumulated anywhere from final rule regarding this issue.
cargo door sill beam and adjacent structure
was identified as sensitive to the fatigue
12,000 total flight cycles to 40,000 total
flight cycles. FedEx suggested that the Conclusion
loads.
This condition, if not detected and modification would be necessary on less We reviewed the available data,
corrected, could lead to failure of multiple than 1 percent of inspected airplanes including the comments received, and
lock fittings, possibly resulting in loss of the over the next 10 years. FedEx claimed determined that air safety and the
cargo door in flight and consequent explosive that the modification is an unproven public interest require adopting this AD
decompression of the aeroplane. change that has not been subjected to as proposed except for minor editorial
To address this potential unsafe condition, full scale fatigue testing. For these changes. We have determined that these
jstallworth on DSKBBY8HB2PROD with RULES
Airbus issued Alert Operators Transmission reasons, FedEx argued that inspections
(AOT) A53W005–14 providing inspection
minor changes:
instructions and, consequently, EASA issued
alone will maintain safe airworthiness • Are consistent with the intent that
Emergency AD 2014–0097–E [which for the affected airplanes. was proposed in the NPRM for
corresponded to FAA AD 2014–12–06, We disagree with the commenter’s correcting the unsafe condition; and
Amendment 39–17867, (79 FR 34403, June request. EASA, as the State of Design • Do not add any additional burden
17, 2014)] to require repetitive ultrasonic Authority for Airbus products, has upon the public than was already
inspections (US) or detailed inspections determined an unsafe conditions exists proposed in the NPRM.
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![Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / Rules and Regulations 56867
Related Service Information Under 1 December 12, 2014; and Service Bulletin inspection of the aft cargo door sill
CFR Part 51 A310–53–2139, dated December 12, beam external area for cracking.
Airbus has issued Service Bulletin 2014. This service information describes This service information is reasonably
A300–53–6181, Revision 01, dated July procedures for repetitive HFEC available because the interested parties
2, 2015; and Service Bulletin A310–53– inspections of the cargo door sill beam, have access to it through their normal
2141, Revision 01, dated July 2, 2015. lock fitting, and torsion box plate. These course of business or by the means
This service information describes documents are distinct since they apply identified in the ADDRESSES section.
procedures for reinforcing the aft cargo to different airplane models.
Costs of Compliance
door sill beam area. These documents Airbus has also issued Alert Operators
are distinct since they apply to different Transmission AOT A53W005–14, We estimate that this AD affects 75
airplane models. Revision 01, dated April 29, 2014, airplanes of U.S. registry.
Airbus has also issued Service which describes procedures for doing an We estimate the following costs to
Bulletin A300–53–6179, dated ultrasonic inspection or detailed comply with this AD:
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Inspection (retained action from AD 12 work-hours × $85 per hour = $1,020 N/A $1,020 per inspec- $76,500 per inspec-
2016-20-11). per inspection cycle. tion cycle. tion cycle.
Modification (new action) ....................... Up to 68 work-hours × $85 per hour = $96,890 Up to $102,670 ...... Up to $7,700,250.
$5,780.
Reporting (retained action from AD 1 work hour × $85 per hour = $85 per $0 $85 per inspection $6,375 per inspec-
2016-20-11). inspection cycle. cycle. tion cycle.
We have received no definitive data We are issuing this rulemaking under 1. Is not a ‘‘significant regulatory
that will enable us to provide cost the authority described in ‘‘Subtitle VII, action’’ under Executive Order 12866;
estimates for the on-condition actions Part A, Subpart III, Section 44701: 2. Is not a ‘‘significant rule’’ under the
specified in this AD. General requirements.’’ Under that DOT Regulatory Policies and Procedures
section, Congress charges the FAA with (44 FR 11034, February 26, 1979);
Paperwork Reduction Act promoting safe flight of civil aircraft in 3. Will not affect intrastate aviation in
air commerce by prescribing regulations Alaska; and
A federal agency may not conduct or 4. Will not have a significant
sponsor, and a person is not required to for practices, methods, and procedures
the Administrator finds necessary for economic impact, positive or negative,
respond to, nor shall a person be subject on a substantial number of small entities
to penalty for failure to comply with a safety in air commerce. This regulation
is within the scope of that authority under the criteria of the Regulatory
collection of information subject to the Flexibility Act.
requirements of the Paperwork because it addresses an unsafe condition
Reduction Act unless that collection of that is likely to exist or develop on List of Subjects in 14 CFR Part 39
information displays a current valid products identified in this rulemaking
action. Air transportation, Aircraft, Aviation
OMB control number. The control safety, Incorporation by reference,
number for the collection of information This AD is issued in accordance with Safety.
required by this AD is 2120–0056. The authority delegated by the Executive
paperwork cost associated with this AD Director, Aircraft Certification Service, Adoption of the Amendment
has been detailed in the Costs of as authorized by FAA Order 8000.51C. Accordingly, under the authority
Compliance section of this document In accordance with that order, issuance delegated to me by the Administrator,
and includes time for reviewing of ADs is normally a function of the the FAA amends 14 CFR part 39 as
instructions, as well as completing and Compliance and Airworthiness follows:
reviewing the collection of information. Division, but during this transition
Therefore, all reporting associated with period, the Executive Director has PART 39—AIRWORTHINESS
this AD is mandatory. Comments delegated the authority to issue ADs DIRECTIVES
concerning the accuracy of this burden applicable to transport category
airplanes to the Director of the System ■ 1. The authority citation for part 39
and suggestions for reducing the burden
Oversight Division. continues to read as follows:
should be directed to the FAA at 800
Independence Ave. SW., Washington, Authority: 49 U.S.C. 106(g), 40113, 44701.
Regulatory Findings
DC 20591, ATTN: Information § 39.13 [Amended]
Collection Clearance Officer, AES–200. We determined that this AD will not
have federalism implications under ■ 2. The FAA amends § 39.13 by
Authority for This Rulemaking removing Airworthiness Directive (AD)
Executive Order 13132. This AD will
not have a substantial direct effect on 2016–20–11, Amendment 39–18677 (81
Title 49 of the United States Code FR 85837, November 29, 2016), and
jstallworth on DSKBBY8HB2PROD with RULES
specifies the FAA’s authority to issue the States, on the relationship between
the national government and the States, adding the following new AD:
rules on aviation safety. Subtitle I,
section 106, describes the authority of or on the distribution of power and 2017–24–09 Airbus: Amendment 39–19113;
responsibilities among the various Docket No. FAA–2017–0708; Product
the FAA Administrator. ‘‘Subtitle VII: Identifier 2017–NM–035–AD.
Aviation Programs,’’ describes in more levels of government.
detail the scope of the Agency’s For the reasons discussed above, I (a) Effective Date
authority. certify that this AD: This AD is effective January 5, 2018.
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![Federal Register / Vol. 82, No. 230 / Friday, December 1, 2017 / Rules and Regulations 56869
(p) Credit for Previous Actions methods in accordance with the operator’s www.archives.gov/federal-register/cfr/ibr-
This paragraph provides credit for actions maintenance or inspection program without locations.html.
required by paragraph (n) of this AD, if those obtaining approval of an AMOC, provided
Issued in Renton, Washington, on
actions were performed before the effective the procedures and tests identified as RC can
November 22, 2017.
date of this AD using Airbus Service Bulletin be done and the airplane can be put back in
an airworthy condition. Any substitutions or Jeffrey E. Duven,
A300–53–6181, dated June 26, 2015; or
Airbus Service Bulletin A310–53–2141, changes to procedures or tests identified as Director, System Oversight Division, Aircraft
dated June 26, 2015; as applicable. RC require approval of an AMOC. Certification Service.
[FR Doc. 2017–25763 Filed 11–30–17; 8:45 am]
(q) Other FAA AD Provisions (r) Related Information
BILLING CODE 4910–13–P
The following provisions also apply to this (1) Refer to Mandatory Continuing
AD: Airworthiness Information (MCAI) EASA AD
(1) Alternative Methods of Compliance 2017–0048, dated March 15, 2017; corrected
(AMOCs): The Manager, International April 20, 2017, for related information. This DEPARTMENT OF LABOR
Section, Transport Standards Branch, FAA, MCAI may be found in the AD docket on the
has the authority to approve AMOCs for this Internet at http://www.regulations.gov by Employment and Training
AD, if requested using the procedures found searching for and locating Docket No. FAA– Administration
in 14 CFR 39.19. In accordance with 14 CFR 2017–0708.
39.19, send your request to your principal (2) For more information about this AD,
20 CFR Part 641
inspector or local Flight Standards District contact Dan Rodina, Aerospace Engineer,
Office, as appropriate. If sending information International Section, Transport Standards [Docket No. ETA–2017–0005]
directly to the International Section, send it Branch, FAA, 1601 Lind Avenue SW.,
to the attention of the person identified in Renton, WA 98057–3356; telephone 425– RIN 1205–AB79
paragraph (r)(2) of this AD. Information may 227–2125; fax 425–227–1149.
be emailed to: 9-ANM-116-AMOC- (3) Service information identified in this Senior Community Service
REQUESTS@faa.gov. AD that is not incorporated by reference is Employment Program; Performance
(i) Before using any approved AMOC, available at the addresses specified in Accountability
notify your appropriate principal inspector, paragraphs (s)(5) and (s)(6) of this AD.
or lacking a principal inspector, the manager
(s) Material Incorporated by Reference
AGENCY: Employment and Training
of the local flight standards district office/ Administration, Labor.
certificate holding district office. (1) The Director of the Federal Register
approved the incorporation by reference ACTION: Interim final rule; request for
(ii) AMOCs approved previously for AD
2016–20–11 are approved as AMOCs for the (IBR) of the service information listed in this comments.
corresponding provisions of this AD. paragraph under 5 U.S.C. 552(a) and 1 CFR
(2) Contacting the Manufacturer: As of the part 51. SUMMARY: The Employment and
effective date of this AD, for any requirement (2) You must use this service information Training Administration (ETA) of the
in this AD to obtain corrective actions from as applicable to do the actions required by Department of Labor (Department) is
a manufacturer, the action must be this AD, unless this AD specifies otherwise. issuing this Interim Final Rule (IFR)
accomplished using a method approved by (3) The following service information was revising performance accountability
the Manager, International Section, Transport approved for IBR on July 2, 2014 (79 FR measures for the Senior Community
Standards Branch, FAA; or EASA; or 34403, June 17, 2014). Service Employment Program (SCSEP).
Airbus’s EASA DOA. If approved by the (i) Airbus Alert Operators Transmission
Revised measures are necessary because
DOA, the approval must include the DOA- A53W005–14, dated April 22, 2014.
authorized signature. (ii) Reserved. the Older Americans Act
(3) Reporting Requirements: A federal (4) The following service information was Reauthorization Act of 2016 (OAA)
agency may not conduct or sponsor, and a approved for IBR on January 3, 2017, (81 FR amended the measures of performance
person is not required to respond to, nor 85837, November 29, 2016). for the SCSEP program in large part to
shall a person be subject to a penalty for (i) Airbus Alert Operators Transmission align them with the performance
failure to comply with a collection of A53W005–14, Revision 01, dated April 29, measures mandated for programs under
information subject to the requirements of 2014. the Workforce Innovation and
the Paperwork Reduction Act unless that (ii) Airbus Service Bulletin A300–53–6179, Opportunity Act (WIOA). This IFR
collection of information displays a current dated December 12, 2014.
revises the Performance Accountability
valid OMB Control Number. The OMB (iii) Airbus Service Bulletin A300–53–
Control Number for this information 6181, Revision 01, dated July 2, 2015. subpart of the SCSEP regulations to
collection is 2120–0056. Public reporting for (iv) Airbus Service Bulletin A310–53– reflect changes necessitated by the
this collection of information is estimated to 2139, dated December 12, 2014. passage of the 2016 OAA. In addition,
be approximately 1 hour per response, (v) Airbus Service Bulletin A310–53–2141, this rule makes minor, non-substantive
including the time for reviewing instructions, Revision 01, dated July 2, 2015. amendments to other subparts of the
completing and reviewing the collection of (5) For service information identified in SCSEP regulations to reflect the OAA
information. All responses to this collection this AD, contact Airbus SAS, Airworthiness amendments that aligned the SCSEP
of information are mandatory. Comments Office—EAW, 1 Rond Point Maurice program statutory language with WIOA,
concerning the accuracy of this burden and Bellonte, 31707 Blagnac Cedex, France;
such as updating outdated terminology
suggestions for reducing the burden should telephone +33 5 61 93 36 96; fax +33 5 61
be directed to the FAA at: 800 Independence 93 44 51; email account.airworth-eas@ and outdated references to the
Ave. SW., Washington, DC 20591, Attn: airbus.com; Internet http://www.airbus.com. Workforce Investment Act of 1998
Information Collection Clearance Officer, (6) You may view this service information (WIA), which WIOA superseded. This
AES–200. at the FAA, Transport Standards Branch, IFR solicits public comment on this IFR,
(4) Required for Compliance (RC): Except 1601 Lind Avenue SW., Renton, WA. For which the Department will consider
jstallworth on DSKBBY8HB2PROD with RULES
as required by paragraph (l) of this AD: If any information on the availability of this when it issues a Final Rule.
service information contains procedures or material at the FAA, call 425–227–1221.
DATES: Effective date: This IFR is
tests that are identified as RC, those (7) You may view this service information
procedures and tests must be done to comply that is incorporated by reference at the effective January 2, 2018.
with this AD; any procedures or tests that are National Archives and Records Compliance date: Performance
not identified as RC are recommended. Those Administration (NARA). For information on information under the measures
procedures and tests that are not identified the availability of this material at NARA, call implemented in this IFR are required to
as RC may be deviated from using accepted 202–741–6030, or go to: http:// be reported beginning July 1, 2018.
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Document Created: 2018-10-25 10:44:39
Document Modified: 2018-10-25 10:44:39
| 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 5, 2018. | |
| Contact | Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. | |
| FR Citation | 82 FR 56865 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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