83 FR 49793 - Airworthiness Directives; Airbus SAS Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 192 (October 3, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 192 (October 3, 2018)
| Page Range | 49793-49799 | |
| FR Document | 2018-20348 |
[Federal Register Volume 83, Number 192 (Wednesday, October 3, 2018)] [Rules and Regulations] [Pages 49793-49799] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-20348] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0497; Product Identifier 2017-NM-140-AD; Amendment 39-19418; AD 2018-19-18] RIN 2120-AA64 Airworthiness Directives; Airbus SAS Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A300 B4-603, B4-620, and B4-622 airplanes; Model A300 B4-600R series airplanes; Model A300 C4-605R Variant F airplanes; and Model A300 F4-605R airplanes. This AD was prompted by reports of cracking on a certain frame (FR) angle fitting. This AD requires, depending on airplane configuration, a modification of certain angle fitting attachment holes; repetitive inspections for cracking of certain holes of the internal lower angle fitting web, certain holes of the internal lower angle fitting horizontal splicing, the aft bottom panel, and a certain junction area; and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective November 7, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 7, 2018. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of December 19, 2005 (70 FR 69056, November 14, 2005). ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EAW, Rond-Point Emile Dewoitine No: 2, 31700 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 Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018- 0497. 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-2018- 0497; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800-647- 5527) is 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, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3225. SUPPLEMENTARY INFORMATION: [[Page 49794]] Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus SAS Model A300 B4-603, B4-620, and B4-622 airplanes; Model A300 B4-600R series airplanes; Model A300 C4-605R Variant F airplanes; and Model A300 F4- 605R airplanes. The NPRM published in the Federal Register on June 4, 2018 (83 FR 25590). The NPRM was prompted by reports of cracking on the FR47 angle fitting. The NPRM proposed to require, depending on airplane configuration, a modification of certain angle fitting attachment holes; repetitive inspections for cracking of certain holes of the internal lower angle fitting web, certain holes of the internal lower angle fitting horizontal splicing, the aft bottom panel, and the FR47/ Rib 1 junction area; and related investigative and corrective actions if necessary. We are issuing this AD to address cracking of the FR47 angle fitting, which could result in reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017-0210, dated October 24, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus SAS Model A300 B4-603, B4-620, and B4-622 airplanes; Model A300 B4-600R series airplanes; Model A300 C4-605R Variant F airplanes; and Model A300 F4-605R airplanes. The MCAI states: Prompted by cracks found on the Frame (FR) 47 angle fitting, Airbus issued SB [Service Bulletin] A300-57-6049, SB A300-57-6050, and SB A300-57-6086. These cracks, if not detected and corrected, could affect the structural integrity of the centre wing box (CWB) of the aeroplane. Consequently, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France published AD 94-241-170, AD 1999-147-279, AD 2000-533-328 and AD F-2004-159 (EASA approval 2004-9779), each AD superseding the previous one, to require repetitive high frequency eddy current (HFEC) rotating probe inspections of the FR47 internal lower angle fitting. After DGAC France AD F-2004-159 was issued, cracks were reportedly found on the horizontal flange of FR47 internal corner angle fitting during accomplishment of routine maintenance structural inspection and modification in accordance with the instructions of Airbus SB A300-57-6050. Prompted by these findings, Airbus reviewed and amended the inspection programme for the internal lower angle fitting flange (horizontal face). Consequently, EASA issued AD 2012-0092 [which corresponds to FAA AD 2014-20-18, Amendment 39-17991 (79 FR 65879, November 6, 2014) (``AD 2014-20-18'')], retaining the requirements of DGAC France AD F-2004-159, which was superseded, and requiring additional repetitive inspections of the CWB lower panel through the ultrasonic method and, depending on findings, re-installation of removed fasteners in transition fit instead of interface. In addition, DGAC France had previously issued AD F-2005-124 (EASA approval 2005-6071) to require the same inspections for A300 F4-608ST aeroplanes, in accordance with Airbus SB A300-57-9001 and SB A300-57-9002. Following the discovery of numerous cracks during the accomplishment of SB A300-57-6049 and SB A300-57-6089 inspections, Airbus developed in a first step a new (recommended) modification (Airbus SB A300-57-6113) and defined, for post-mod aeroplanes, new inspections, and published SB A300-57-6119, which included new inspection methods (ultrasonic/radiographic) with new inspection thresholds and intervals. Consequently, EASA issued AD 2016-0198, retaining the requirements of EASA AD 2012-0092, which was superseded, to require repetitive inspections for post-SB A300-57-6113 aeroplanes. Since EASA AD 2016-0198 was issued, Airbus revised in a second step the inspection programme for A300-600 pre-SB 57-6113 and A300- 600ST aeroplanes, reducing inspection thresholds and intervals. At this opportunity, the existing ultrasonic inspection for A300-600 aeroplanes has been added for A300-600ST aeroplanes. For the reasons described above, this new [EASA] AD retains the requirements of EASA AD 2016-0198 for A300-600 aeroplanes and of DGAC France AD F-2005-124 for A300-600ST aeroplanes, which are both superseded, and requires [modification through cold expansion of certain angle fitting attachment holes and] repetitive inspections [for cracking of certain holes of the internal lower angle fitting web, certain holes of the internal lower angle fitting horizontal splicing, the aft bottom panel, and the FR47/Rib 1 junction area, and applicable related investigative and corrective actions] with new compliance times and intervals. This [EASA] AD is applicable to both A300-600 and A300-600ST aeroplanes * * *. Related investigative actions include a rotating probe inspection for cracking. Corrective actions include replacing damaged fasteners, reaming and drilling holes, installing the next nominal fastener for oversized bore holes, and repairing cracks. 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-2018-0497. Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA's response to each comment. Request To Refer to New Service Information FedEx Express requested that we revise paragraphs (j), (k), and (m)(2) of the proposed AD to refer to Airbus Service Bulletin A300-57- 6086, Revision 7, dated March 26, 2018, rather than Airbus Service Bulletin A300-57-6086, Revision 6, dated July 4, 2017. FedEx Express noted that the service information had been updated since the NPRM was released. We agree with the request. Airbus Service Bulletin A300-57-6086, Revision 7, dated March 26, 2018, removes one airplane from the effectivity and adds clarification on reporting related to ultrasonic inspections. All actions remain unchanged. We have revised paragraphs (j), (k), and (m)(2) of this AD to refer to Airbus Service Bulletin A300-57-6086, Revision 7, dated March 26, 2018. We have also revised paragraph (p) of this AD to provide credit for certain actions performed in accordance with Airbus Service Bulletin A300-57-6086, Revision 6, dated July 4, 2017. Request To Allow Previously Approved Alternative Methods of Compliance (AMOCs) FedEx Express requested that we revise the proposed AD to allow AMOCs previously approved for AD 2014-20-18 as AMOCs for the corresponding provisions of this AD. We agree with the commenter's request. We have revised paragraph (q)(1) of this AD to note that AMOCs previously approved for AD 2014- 20-18 are approved as AMOCs for the corresponding provisions of this AD. Request To Allow Reporting Through Alternative Method FedEx Express requested that paragraph (n) of the proposed AD be revised to allow operators to determine the method or form they use for reporting inspection results. FexEx Express noted that they believe reporting is needed, but do not currently have the capability to use the Airbus online reporting system. We acknowledge the commenter's request, but disagree that we need to change this AD regarding this issue. Paragraph (n) of this AD allows reporting in accordance with the instructions of the applicable service information. This allows operators to use alternative methods of reporting, including mail, fax, and email. Therefore, a change to this AD is unnecessary. [[Page 49795]] Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. Related Service Information Under 1 CFR Part 51 Airbus SAS has issued the following service information. Service Bulletin A300-57-6049, Revision 8, dated July 4, 2017. This service information describes procedures for HFEC rotating probe inspections for cracking of certain holes of the internal lower angle fitting web. Service Bulletin A300-57-6086, Revision 7, dated March 26, 2018. This service information describes procedures for HFEC rotating probe inspections for cracking of certain holes in the internal lower angle fitting horizontal splicing (left-hand and right-hand sides) and for ultrasonic inspections for cracking of the aft bottom panel. Service Bulletin A300-57-6119, Revision 00, dated April 25, 2016. This service information describes procedures for ultrasonic and radiographic inspections for cracking of the FR47/Rib 1 junction area. 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 65 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs for Required Actions ---------------------------------------------------------------------------------------------------------------- Labor cost Parts cost Cost per product Cost on U.S. operators ---------------------------------------------------------------------------------------------------------------- Up to 727 work-hours x $85 per hour Up to $3,370.......... Up to $65,165......... Up to $4,235,725 per = Up to $61,795. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate that it would take about 1 work-hour per product to comply with the reporting requirement in this AD. The average labor rate is $85 per hour. Based on these figures, we estimate the cost of reporting the inspection results on U.S. operators to be $5,525, or $85 per product. We have received no definitive data that would 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 and associated appliances to the Director of the System Oversight Division. Regulatory Findings 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: [[Page 49796]] PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2018-19-18 Airbus SAS: Amendment 39-19418; Docket No. FAA-2018-0497; Product Identifier 2017-NM-140-AD. (a) Effective Date This AD is effective November 7, 2018. (b) Affected ADs This AD affects AD 2014-20-18, Amendment 39-17991 (79 FR 65879, November 6, 2014) (``AD 2014-20-18''). (c) Applicability This AD applies to Airbus SAS Model A300 B4-603, A300 B4-620, A300 B4-622, A300 B4-605R, A300 B4-622R, A300 C4-605R Variant F, and A300 F4-605R airplanes, certificated in any category, all manufacturer serial numbers, except airplanes on which Airbus Modification 12171 or 12249 has been embodied in production, or on which Airbus Service Bulletin A300-57-6069 has been embodied in service. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by reports of cracking on the frame (FR) 47 angle fitting. We are issuing this AD to detect and correct cracking of the FR47 angle fitting, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definitions For the purposes of this AD, the definitions in paragraphs (g)(1) through (g)(6) apply. (1) Group 1 airplanes are those airplanes on which Airbus Service Bulletin A300-57-6113, Revision 00, dated April 25, 2016, has not been incorporated as of the effective date of this AD. (2) Group 2 airplanes are those airplanes on which Airbus Service Bulletin A300-57-6113, Revision 00, dated April 25, 2016, has been incorporated as of the effective date of this AD. (3) The average flight time (AFT) for the inspection threshold is defined as the flight hours (FH) divided by the flight cycles (FC), counted from the first flight of the airplane. (4) The AFT for the inspection interval is defined as the FH divided by the FC, counted from the date of the last inspection required by paragraph (i), (j), (k), or (l) of this AD, as applicable. (5) For airplanes on which Airbus modification 10155 has been embodied, the thresholds for the inspections required by paragraphs (i), (j), and (k) of this AD are counted from the first flight of the airplane. (6) For airplanes on which Airbus modification 10155 has not been embodied, the thresholds for the inspections required by paragraphs (i), (j), and (k) of this AD are counted since the date on which Airbus Service Bulletin A300-57-6050 was embodied on the airplane. (h) Modification For all airplanes on which Airbus modification 10155 has not been embodied: Before exceeding 15,100 FC or 38,900 FH, whichever occurs first after first flight of the airplane; or within the ``grace periods'' defined in paragraph 1.B.(4), ``Accomplishment Timescale,'' of Airbus Service Bulletin A300-57-6050, Revision 3, dated May 31, 2001; whichever occurs later, modify the angle fitting attachment holes of the wing center box by cold expansion, including doing a rotating probe inspection for cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57- 6050, Revision 3, dated May 31, 2001. Where paragraph 1.B.(4), ``Accomplishment Timescale,'' of Airbus Service Bulletin A300-57- 6050, Revision 3, dated May 31, 2001, specifies ``grace periods'' relative to the receipt of the service bulletin, count the ``grace periods'' from December 19, 2005 (the effective date of AD 2005-23- 08 (70 FR 69056, November 14, 2005)). If any crack is found during any 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 SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (i) Internal Lower Angle Fitting (Vertical Face) Web Inspections For Group 1 airplanes: Before exceeding the applicable threshold specified in figure 1 to paragraph (i) of this AD, or within 12 months after the effective date of this AD, whichever occurs later, do a high frequency eddy current (HFEC) rotating probe inspection for cracking of holes H, I, K, L M, N, U, V, W, X, and Y of the internal lower angle fitting web (left-hand and right-hand sides), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6049, Revision 8, dated July 4, 2017. Repeat the inspection thereafter at intervals not to exceed those specified in figure 1 to paragraph (i) of this AD. [GRAPHIC] [TIFF OMITTED] TR03OC18.000 (j) Internal Lower Angle Fitting (Horizontal Face) Inspections For Group 1 airplanes: Before exceeding the applicable threshold specified in figure 2 to paragraph (j) of this AD, or within 12 months after the effective date of this AD, whichever occurs later, do an HFEC rotating probe inspection for cracking of holes A, B, C, D, E, F, G, P, Q, S, and T (adjacent to hole G) of the internal lower angle fitting horizontal splicing (left-hand and right-hand sides), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, Revision 7, dated March 26, 2018. Repeat the inspection thereafter at intervals not to exceed those specified in figure 2 to paragraph (j) of this AD. [[Page 49797]] [GRAPHIC] [TIFF OMITTED] TR03OC18.001 (k) Aft Bottom Panel Inspections For Group 1 airplanes: Before exceeding the applicable thresholds specified in figure 3 to paragraph (k) of this AD, or within 12 months after the effective date of this AD, whichever occurs later, do an ultrasonic inspection for cracking of the aft bottom panel, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, Revision 7, dated March 26, 2018. Repeat the inspection thereafter at intervals not to exceed those specified in figure 3 to paragraph (k) of this AD. [GRAPHIC] [TIFF OMITTED] TR03OC18.002 (l) FR47/Rib 1 junction area inspections For Group 2 airplanes: Before exceeding the applicable thresholds specified in figure 4 to paragraph (l) of this AD, do ultrasonic and radiographic inspections for cracking of the FR47/Rib 1 junction area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6119, Revision 00, dated April 25, 2016. Repeat the inspections thereafter at intervals not to exceed those specified in figure 4 to paragraph (l) of this AD. Count the threshold compliance times from the date on which Airbus Service Bulletin A300-57-6113, Revision 00, dated April 25, 2016, was embodied on the airplane. [GRAPHIC] [TIFF OMITTED] TR03OC18.003 [[Page 49798]] (m) Related Investigative and Corrective Actions If, during any inspection required by paragraph (i), (j), (k), or (l) of this AD, any crack is found: Before further flight, accomplish all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of the service information specified in paragraphs (m)(1) through (m)(3) of this AD, as applicable. Where the service information specified in paragraphs (m)(1) through (m)(3) of this AD specifies to contact Airbus for instructions, before further flight, obtain instructions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA and accomplish those instructions accordingly. If approved by the DOA, the approval must include the DOA-authorized signature. (1) If the inspection was done as specified in paragraph (i) of this AD: Airbus Service Bulletin A300-57-6049, Revision 8, dated July 4, 2017. (2) If the inspection was done as specified in paragraph (j) or (k) of this AD: Airbus Service Bulletin A300-57-6086, Revision 7, dated March 26, 2018. (3) If the inspection was done as specified in paragraph (l) of this AD: Airbus Service Bulletin A300-57-6119, Revision 00, dated April 25, 2016. (n) Reporting At the applicable time specified in paragraph (n)(1) or (n)(2) of this AD: Report the results of the inspections required by paragraphs (i), (j), (k), and (l) of this AD to Airbus Service Bulletin Reporting Online Application on Airbus World (https://w3.airbus.com/), or submit the results to Airbus in accordance with the instructions of the applicable service information specified in paragraphs (i), (j), (k), or (l) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of flight cycles and flight hours on the airplane. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (o) Terminating Action for AD 2014-20-18 Accomplishment of the action required by paragraph (h) of this AD and the initial inspections required by paragraphs (i) and (j), and (k) of this AD terminates all requirements of AD 2014-20-18. (p) Credit for Previous Actions (1) This paragraph provides credit for actions specified in paragraph (h) of this AD, if those actions were performed before December 19, 2005 (the effective date of AD 2005-23-08 (70 FR 69056, November 14, 2005)), using Airbus Service Bulletin A300-57-6050, Revision 02, dated February 10, 2000. (2) This paragraph provides credit for actions specified in paragraphs (j), (k), and (m)(2) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300-57-6086, Revision 6, dated July 4, 2017. (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 previously approved for AD 2014-20-18 are approved as AMOCs for the corresponding provisions of this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA- authorized signature. (3) Paperwork Reduction Act Burden Statement: 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 work-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 (m) 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 2017-0210, dated October 24, 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-2018-0497. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3225. (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 November 7, 2018. (i) Airbus Service Bulletin A300-57-6049, Revision 8, dated July 4, 2017. (ii) Airbus Service Bulletin A300-57-6086, Revision 7, dated March 26, 2018. (iii) Airbus Service Bulletin A300-57-6119, Revision 00, dated April 25, 2016. (4) The following service information was approved for IBR on December 19, 2005 (70 FR 69056, November 14, 2005). (i) Airbus Service Bulletin A300-57-6050, Revision 03, dated May 31, 2001. This document contains the effective pages specified in paragraphs (s)(4)(i)(A), (s)(4)(i)(B), (s)(4)(i)(C), and (s)(4)(i)(D) of this AD. (A) Pages 1, 4, 10A through 11, 75, and 76 are identified as Revision 03, dated May 31, 2001. (B) Pages 2, 8, 9, 17 through 32, 41, 42, 57, 58, 61 through 63, and 77 are identified as Revision 02, dated February 10, 2000. (C) Pages 3, 5 through 7, 10, 12, 33, 34, 37, 38, 47, 59, and 60 are identified as Revision 01, dated May 31, 1999. (D) Pages 13 through 16, 35, 36, 39, 40, 43 through 46, 48 through 56, and 64 through 74 are identified as original, dated September 9, 1994. (ii) Reserved. (5) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, Rond-Point Emile Dewoitine No: 2, 31700 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, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. (7) You may view this service information that is incorporated by reference at the [[Page 49799]] 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 Des Moines, Washington, on September 10, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-20348 Filed 10-2-18; 8:45 am] BILLING CODE 4910-13-P
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(b) Unsafe Condition (i) Material Incorporated by Reference certain frame (FR) angle fitting. This AD
This AD defines the unsafe condition as (1) The Director of the Federal Register requires, depending on airplane
failure of an overhead panel shock mount approved the incorporation by reference of configuration, a modification of certain
assembly (shock mount). This condition the service information listed in this angle fitting attachment holes; repetitive
could result in detachment of the overhead paragraph under 5 U.S.C. 552(a) and 1 CFR inspections for cracking of certain holes
panel and injury to occupants during an part 51. of the internal lower angle fitting web,
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as applicable to do the actions required by
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This AD becomes effective November 7, (i) Airbus Helicopters Alert Service panel, and a certain junction area; and
2018. Bulletin (ASB) MBB–BK117 C–2–24A–015, related investigative and corrective
Revision 0, dated September 14, 2016. actions if necessary. We are issuing this
(d) Compliance (ii) Airbus Helicopters ASB MBB–BK117 AD to address the unsafe condition on
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action required by this AD within the 14, 2016.
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specified compliance time unless it has (3) For Airbus Helicopters service
information identified in this AD, contact 2018.
already been accomplished prior to that time. The Director of the Federal Register
Airbus Helicopters, 2701 N Forum Drive,
(e) Required Actions Grand Prairie, TX 75052; telephone (972) approved the incorporation by reference
(1) Within 300 hours time-in-service: 641–0000 or (800) 232–0323; fax (972) 641– of certain publications listed in this AD
(i) Install a retaining plate on each shock
3775; or at http:// as of November 7, 2018.
www.helicopters.airbus.com/website/en/ref/ The Director of the Federal Register
mount by following the Accomplishment
Technical-Support_73.html. approved the incorporation by reference
Instructions, paragraphs 3.B.2.1. through
(4) You may view this service information of a certain other publication listed in
3.B.2.4, of Airbus Helicopters Alert Service at FAA, Office of the Regional Counsel,
Bulletin (ASB) MBB–BK117 C–2–24A–015, this AD as of December 19, 2005 (70 FR
Southwest Region, 10101 Hillwood Pkwy.,
Revision 0, dated September 14, 2016 (ASB Room 6N–321, Fort Worth, TX 76177. For 69056, November 14, 2005).
MBB–BK117 C–2–24A–015), or ASB MBB– information on the availability of this ADDRESSES: For service information
BK117 D–2–24A–004, Revision 0, dated material at the FAA, call (817) 222–5110. identified in this final rule, contact
September 14, 2016 (ASB MBB–BK117 D–2– (5) You may view this service information Airbus SAS, Airworthiness Office—
24A–004), as applicable to your model that is incorporated by reference at the EAW, Rond-Point Emile Dewoitine No:
helicopter. National Archives and Records 2, 31700 Blagnac Cedex, France;
(ii) Re-identify shock mount P/N Administration (NARA). For information on telephone +33 5 61 93 36 96; fax +33 5
B246M2035102 as P/N B246M2035966 and the availability of this material at NARA, call
shock mount P/N B246M2036101 as P/N (202) 741–6030, or go to: http://
61 93 44 51; email account.airworth-
B246M2036966 using permanent ink. When www.archives.gov/federal-register/cfr/ibr- eas@airbus.com; internet http://
the ink is dry, apply varnish over the P/N. locations.html. www.airbus.com. You may view this
(iii) Re-install each shock mount. service information at the FAA,
Issued in Fort Worth, Texas, on September
(2) After the effective date of this AD, do 24, 2018.
Transport Standards Branch, 2200
not install a shock mount P/N South 216th St., Des Moines, WA. For
Lance T. Gant,
B246M2035102 or P/N B246M2036101 on information on the availability of this
any helicopter. Director, Compliance & Airworthiness material at the FAA, call 206–231–3195.
Division, Aircraft Certification Service.
(f) Alternative Methods of Compliance It is also available on the internet at
[FR Doc. 2018–21342 Filed 10–2–18; 8:45 am]
(AMOCs) http://www.regulations.gov by searching
BILLING CODE 4910–13–P
for and locating Docket No. FAA–2018–
(1) The Manager, Safety Management
Section, Rotorcraft Standards Branch, FAA,
0497.
may approve AMOCs for this AD. Send your DEPARTMENT OF TRANSPORTATION Examining the AD Docket
proposal to: Matt Fuller, Senior Aviation
Safety Engineer, Safety Management Section, You may examine the AD docket on
Federal Aviation Administration
Rotorcraft Standards Branch, FAA, 10101 the internet at http://
Hillwood Pkwy., Fort Worth, TX 76177; www.regulations.gov by searching for
14 CFR Part 39
telephone (817) 222–5110; email 9-ASW- and locating Docket No. FAA–2018–
FTW-AMOC-Requests@faa.gov. [Docket No. FAA–2018–0497; Product 0497; or in person at Docket Operations
(2) For operations conducted under a 14 Identifier 2017–NM–140–AD; Amendment between 9 a.m. and 5 p.m., Monday
CFR part 119 operating certificate or under 39–19418; AD 2018–19–18] through Friday, except Federal holidays.
14 CFR part 91, subpart K, we suggest that RIN 2120–AA64 The AD docket contains this final rule,
you notify your principal inspector, or the regulatory evaluation, any
lacking a principal inspector, the manager of Airworthiness Directives; Airbus SAS comments received, and other
the local flight standards district office or Airplanes information. The address for Docket
certificate holding district office, before Operations (phone: 800–647–5527) is
operating any aircraft complying with this AGENCY: Federal Aviation
U.S. Department of Transportation,
AD through an AMOC. Administration (FAA), Department of
Docket Operations, M–30, West
(g) Additional Information
Transportation (DOT).
Building Ground Floor, Room W12–140,
ACTION: Final rule.
The subject of this AD is addressed in 1200 New Jersey Avenue SE,
European Aviation Safety Agency (EASA) AD SUMMARY: We are adopting a new Washington, DC 20590.
No. 2017–0026, dated February 14, 2017. You airworthiness directive (AD) for certain FOR FURTHER INFORMATION CONTACT: Dan
daltland on DSKBBV9HB2PROD with RULES
may view the EASA AD on the internet at Airbus SAS Model A300 B4–603, B4– Rodina, Aerospace Engineer,
http://www.regulations.gov in Docket No. International Section, Transport
620, and B4–622 airplanes; Model A300
FAA–2018–0517.
B4–600R series airplanes; Model A300 Standards Branch, FAA, 2200 South
(h) Subject C4–605R Variant F airplanes; and Model 216th St., Des Moines, WA 98198;
Joint Aircraft Service Component (JASC) A300 F4–605R airplanes. This AD was telephone and fax 206–231–3225.
Code: 2400, Electrical Power System. prompted by reports of cracking on a SUPPLEMENTARY INFORMATION:
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![49794 Federal Register / Vol. 83, No. 192 / Wednesday, October 3, 2018 / Rules and Regulations
Discussion Amendment 39–17991 (79 FR 65879, Request To Refer to New Service
November 6, 2014) (‘‘AD 2014–20–18’’)], Information
We issued a notice of proposed retaining the requirements of DGAC France
rulemaking (NPRM) to amend 14 CFR AD F–2004–159, which was superseded, and FedEx Express requested that we
part 39 by adding an AD that would requiring additional repetitive inspections of revise paragraphs (j), (k), and (m)(2) of
apply to certain Airbus SAS Model the CWB lower panel through the ultrasonic the proposed AD to refer to Airbus
A300 B4–603, B4–620, and B4–622 method and, depending on findings, re-
installation of removed fasteners in transition
Service Bulletin A300–57–6086,
airplanes; Model A300 B4–600R series Revision 7, dated March 26, 2018, rather
airplanes; Model A300 C4–605R Variant fit instead of interface.
In addition, DGAC France had previously than Airbus Service Bulletin A300–57–
F airplanes; and Model A300 F4–605R 6086, Revision 6, dated July 4, 2017.
issued AD F–2005–124 (EASA approval
airplanes. The NPRM published in the 2005–6071) to require the same inspections FedEx Express noted that the service
Federal Register on June 4, 2018 (83 FR for A300 F4–608ST aeroplanes, in information had been updated since the
25590). The NPRM was prompted by accordance with Airbus SB A300–57–9001 NPRM was released.
reports of cracking on the FR47 angle and SB A300–57–9002.
fitting. The NPRM proposed to require, Following the discovery of numerous We agree with the request. Airbus
depending on airplane configuration, a cracks during the accomplishment of SB Service Bulletin A300–57–6086,
modification of certain angle fitting A300–57–6049 and SB A300–57–6089 Revision 7, dated March 26, 2018,
inspections, Airbus developed in a first step removes one airplane from the
attachment holes; repetitive inspections
a new (recommended) modification (Airbus effectivity and adds clarification on
for cracking of certain holes of the SB A300–57–6113) and defined, for post-mod
internal lower angle fitting web, certain reporting related to ultrasonic
aeroplanes, new inspections, and published
holes of the internal lower angle fitting SB A300–57–6119, which included new
inspections. All actions remain
horizontal splicing, the aft bottom inspection methods (ultrasonic/radiographic) unchanged. We have revised paragraphs
panel, and the FR47/Rib 1 junction area; with new inspection thresholds and (j), (k), and (m)(2) of this AD to refer to
and related investigative and corrective intervals. Airbus Service Bulletin A300–57–6086,
actions if necessary. Consequently, EASA issued AD 2016– Revision 7, dated March 26, 2018. We
We are issuing this AD to address 0198, retaining the requirements of EASA AD have also revised paragraph (p) of this
2012–0092, which was superseded, to require AD to provide credit for certain actions
cracking of the FR47 angle fitting, which
repetitive inspections for post-SB A300–57– performed in accordance with Airbus
could result in reduced structural 6113 aeroplanes.
integrity of the airplane. Since EASA AD 2016–0198 was issued,
Service Bulletin A300–57–6086,
The European Aviation Safety Agency Airbus revised in a second step the Revision 6, dated July 4, 2017.
(EASA), which is the Technical Agent inspection programme for A300–600 pre-SB Request To Allow Previously Approved
for the Member States of the European 57–6113 and A300–600ST aeroplanes,
Alternative Methods of Compliance
Union, has issued EASA AD 2017–0210, reducing inspection thresholds and intervals.
At this opportunity, the existing ultrasonic (AMOCs)
dated October 24, 2017 (referred to after
this as the Mandatory Continuing inspection for A300–600 aeroplanes has been
added for A300–600ST aeroplanes.
FedEx Express requested that we
Airworthiness Information, or ‘‘the revise the proposed AD to allow AMOCs
For the reasons described above, this new
MCAI’’), to correct an unsafe condition [EASA] AD retains the requirements of EASA previously approved for AD 2014–20–18
for certain Airbus SAS Model A300 B4– AD 2016–0198 for A300–600 aeroplanes and as AMOCs for the corresponding
603, B4–620, and B4–622 airplanes; of DGAC France AD F–2005–124 for A300– provisions of this AD.
Model A300 B4–600R series airplanes; 600ST aeroplanes, which are both We agree with the commenter’s
Model A300 C4–605R Variant F superseded, and requires [modification
through cold expansion of certain angle
request. We have revised paragraph
airplanes; and Model A300 F4–605R
fitting attachment holes and] repetitive (q)(1) of this AD to note that AMOCs
airplanes. The MCAI states:
inspections [for cracking of certain holes of previously approved for AD 2014–20–18
Prompted by cracks found on the Frame the internal lower angle fitting web, certain are approved as AMOCs for the
(FR) 47 angle fitting, Airbus issued SB holes of the internal lower angle fitting corresponding provisions of this AD.
[Service Bulletin] A300–57–6049, SB A300– horizontal splicing, the aft bottom panel, and
57–6050, and SB A300–57–6086. the FR47/Rib 1 junction area, and applicable Request To Allow Reporting Through
These cracks, if not detected and corrected, related investigative and corrective actions] Alternative Method
could affect the structural integrity of the
with new compliance times and intervals.
centre wing box (CWB) of the aeroplane. FedEx Express requested that
This [EASA] AD is applicable to both A300–
Consequently, DGAC [Direction Générale paragraph (n) of the proposed AD be
600 and A300–600ST aeroplanes * * *.
de l’Aviation Civile] France published AD revised to allow operators to determine
94–241–170, AD 1999–147–279, AD 2000– Related investigative actions include a
533–328 and AD F–2004–159 (EASA the method or form they use for
rotating probe inspection for cracking.
approval 2004–9779), each AD superseding reporting inspection results. FexEx
Corrective actions include replacing
the previous one, to require repetitive high Express noted that they believe
damaged fasteners, reaming and drilling
frequency eddy current (HFEC) rotating reporting is needed, but do not currently
probe inspections of the FR47 internal lower holes, installing the next nominal
have the capability to use the Airbus
angle fitting. fastener for oversized bore holes, and
online reporting system.
After DGAC France AD F–2004–159 was repairing cracks. You may examine the
issued, cracks were reportedly found on the MCAI in the AD docket on the internet We acknowledge the commenter’s
horizontal flange of FR47 internal corner at http://www.regulations.gov by request, but disagree that we need to
angle fitting during accomplishment of searching for and locating Docket No. change this AD regarding this issue.
routine maintenance structural inspection FAA–2018–0497. Paragraph (n) of this AD allows
and modification in accordance with the reporting in accordance with the
daltland on DSKBBV9HB2PROD with RULES
instructions of Airbus SB A300–57–6050. Comments instructions of the applicable service
Prompted by these findings, Airbus reviewed
and amended the inspection programme for
We gave the public the opportunity to information. This allows operators to
the internal lower angle fitting flange participate in developing this final rule. use alternative methods of reporting,
(horizontal face). The following presents the comments including mail, fax, and email.
Consequently, EASA issued AD 2012–0092 received on the NPRM and the FAA’s Therefore, a change to this AD is
[which corresponds to FAA AD 2014–20–18, response to each comment. unnecessary.
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![Federal Register / Vol. 83, No. 192 / Wednesday, October 3, 2018 / Rules and Regulations 49799
National Archives and Records Executive Summary participant who was a ‘‘substantial
Administration (NARA). For information on owner’’ at any time within the 60
the availability of this material at NARA, call Purpose of the Regulatory Action
months preceding the date on which the
202–741–6030, or go to: http:// This final rule is necessary to conform determination was made. Section
www.archives.gov/federal-register/cfr/ibr-
the regulations of PBGC to current law 4021(d) of ERISA defines a substantial
locations.html.
and practice. PBGC is incorporating owner as an individual who owns the
Issued in Des Moines, Washington, on statutory changes affecting guaranteed entire interest in an unincorporated
September 10, 2018. benefits and asset allocation when a trade or business, or a partner or
Michael Kaszycki, plan has one or more participants with shareholder who owns more than 10
Acting Director, System Oversight Division, certain ownership interests in the plan percent of the partnership or
Aircraft Certification Service. sponsor. PBGC’s legal authority for this corporation. PPA 2006 revised the
[FR Doc. 2018–20348 Filed 10–2–18; 8:45 am] action comes from sections 4002(b)(3), owner-participant provisions, in large
BILLING CODE 4910–13–P 4022, and 4044 of ERISA. Section part, by making them applicable to
4002(b)(3) authorizes PBGC to issue ‘‘majority owners’’ instead of substantial
regulations to carry out the purposes of owners. Section 4022(b)(5)(A) of ERISA
title IV of ERISA. Sections 4022 and defines a majority owner as an
PENSION BENEFIT GUARANTY 4044 authorize PBGC to prescribe individual who owns the entire interest
CORPORATION regulations regarding the determination in an unincorporated trade or business,
of guaranteed benefits and the allocation or a partner or shareholder who owns 50
29 CFR Parts 4001, 4022, 4043, and of assets within priority categories, percent or more of the entity.
4044 respectively. On March 7, 2018 (at 83 FR 9716),
PBGC published a proposed rule to
RIN 1212–AB24
Major Provisions amend parts 4001, 4022, 4041, 4043,
This final rule amends PBGC’s benefit and 4044 to incorporate statutory
Owner-Participant Changes to payment regulation by replacing the changes to the rules for participants
Guaranteed Benefits and Asset guarantee limitations applicable to with certain ownership interests in a
Allocation substantial owners with a new plan sponsor. PBGC received no
limitation applicable to majority comments on the proposed rule.
AGENCY: Pension Benefit Guaranty The final regulation is the same as the
owners.1 Additionally, this final rule
Corporation. proposed regulation with two
amends PBGC’s asset allocation
ACTION: Final rule. regulation by prioritizing funding of all exceptions discussed below: PBGC is
other benefits in priority category 4 adding clarifying language to § 4022.26
SUMMARY: The Pension Benefit Guaranty of the benefit payment regulation,
ahead of those benefits that would be
Corporation (PBGC) is amending its concerning PPA 2006 bankruptcy
guaranteed but for the new limitation.
regulations on guaranteed benefits and terminations; and PBGC is not making
The rulemaking also clarifies that plan
asset allocation. These amendments the proposed amendment to its
administrators may continue to use the
incorporate statutory changes to the regulation on Termination of Single-
simplified calculation in the existing
rules for participants with certain Employer Plans (29 CFR part 4041).
rule to estimate benefits funded by plan
ownership interests in a plan sponsor.
assets. Finally, it provides new Guaranteed Benefits Before and After
DATES: Effective Date: This rule is examples to aid in implementation. PPA 2006
effective November 2, 2018.
Applicability: Like the provisions of Background ERISA section 4022 imposes several
the Pension Protection Act of 2006 (PPA PBGC administers the pension limitations on PBGC’s guarantee of plan
2006) that this rule incorporates, the insurance program under title IV of benefits, including the ‘‘phase-in
amendments in this final rule are ERISA. ERISA sections 4022 and 4044 limitation.’’ As the name of this
applicable to plan terminations— cover PBGC’s guarantee of plan benefits limitation suggests, PBGC’s guarantee of
(A) under section 4041(c) of the and allocation of plan assets, a plan’s benefits is phased in over a
Employee Retirement Income Security respectively, under terminated single- specified time period. Before PPA 2006,
Act of 1974 (ERISA) with respect to employer plans. Special provisions this time period was drastically
which notices of intent to terminate are within these sections apply to ‘‘owner- different for owner-participants and for
provided under section 4041(a)(2) of participants,’’ who have certain all other participants; the benefits of
ERISA after December 31, 2005, and ownership interests in their plan owner-participants were phased in over
(B) under section 4042 of ERISA with sponsors. PPA 2006 made changes to 30 years, whereas the benefits of non-
respect to which notices of these provisions. PBGC has been owner-participants were phased in over
determination are provided under that operating in accordance with the five years. In addition, the extent to
section after December 31, 2005. amended provisions since they became which an owner-participant’s benefit
effective, but had not yet updated its was phased in was unique to each
FOR FURTHER INFORMATION CONTACT: owner-participant and based on the
Samantha M. Lowen (lowen.samantha@ regulations nor issued guidance on
implementation. With this rulemaking, number of years he or she was an active
pbgc.gov), Attorney, Regulatory Affairs participant in the plan; whereas the
Division, Office of the General Counsel, PBGC is increasing transparency into its
operations and is clarifying for plan extent to which all other participants’
Pension Benefit Guaranty Corporation, benefits were phased in was based on
1200 K Street NW, Washington, DC administrators the impact of the
daltland on DSKBBV9HB2PROD with RULES
statutory changes. the number of years a plan provision—
20005–4026; 202–326–4400, extension specifically, one that increased
3786. (TTY users may call the Federal Before PPA 2006, the owner-
participant provisions applied to any benefits—was in effect before the plan
relay service toll-free at 800–877–8339 terminated.
and ask to be connected to 202–326– 1 In this preamble, substantial owners and PPA 2006 greatly simplified the
4400, extension 3786.) majority owners are referred to interchangeably as method for determining PBGC’s
SUPPLEMENTARY INFORMATION: ‘‘owner-participants.’’ guarantee of owner-participants’
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Document Created: 2018-10-03 02:30:32
Document Modified: 2018-10-03 02:30:32
| 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 November 7, 2018. | |
| Contact | Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3225. | |
| FR Citation | 83 FR 49793 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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