80 FR 71751 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 221 (November 17, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 221 (November 17, 2015)
| Page Range | 71751-71755 | |
| FR Document | 2015-28892 |
[Federal Register Volume 80, Number 221 (Tuesday, November 17, 2015)] [Proposed Rules] [Pages 71751-71755] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-28892] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-4813; Directorate Identifier 2013-NM-161-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 99-16-01, for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 99-16-01 currently requires repetitive inspections of certain bolt holes where parts of the main landing gear (MLG) are attached to the wing rear spar, and repair if necessary. Since we issued AD-99-16-01, we have determined that the risk of cracking in the rear spar is higher than initially determined. This proposed AD would add airplanes to the applicability, reduce the compliance times and repetitive intervals for the inspections, and change the inspection procedures. We are proposing this AD to detect and correct cracking of the rear spar of the wing, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by January 4, 2016. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 4813; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425-227-1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-4813; Directorate Identifier 2013-NM-161-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On July 21, 1999, we issued AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999). AD 99-16-01 requires actions intended to address an unsafe condition on 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). Since we issued AD 99-16-01, Amendment 39-11236 (64 FR 40743, [[Page 71752]] July 28, 1999), a fleet survey and updated fatigue and damage tolerance analyses have shown that the threshold for the initial inspections and the intervals for the repetitive inspections need to be reduced. The European Aviation Safety Agency (EASA), which is Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013-0180, dated August 9, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states: During full-scale fatigue testing, cracks were found on the rear spar from certain bolt holes at the attachment of the Main Landing gear (MLG) forward pick-up fitting and the MLG Rib 5 aft. This condition, if not detected and corrected, could reduce the structural integrity of the aeroplane. DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued * * * [an AD] (later revised) to require High Frequency Eddy Current (HFEC) or Ultrasonic (U/S) inspections of certain fastener holes where the MLG forward pick-up fitting and MLG Rib 5 aft are attached to the rear spar. Since DGAC France * * * [issued a revised AD, which corresponded to FAA AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999), which superseded FAA AD 95-20-02, Amendment 39-9380 (60 FR 52618, October 10, 1995)] * * *, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to substantiate the second A300-600 Extended Service Goal (ESG2) exercise. The results of these analyses have shown that the threshold and interval must be reduced to allow timely detection of these cracks and accomplishment of an applicable corrective action. For the reasons described above, this [EASA] AD retains the requirements of [the revised DGAC France AD], which is superseded, but reduces the related compliance times. The new, reduced threshold for the initial inspection ranges between 8,900 total flight cycles/20,000 total flight hours, and 34,600 total flight cycles/77,800 total flight hours, depending on the modification. The grace periods (750 or 1,500 landings) for airplanes that have exceeded the specified thresholds are unchanged from those provided in AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999). The new, reduced intervals for the repetitive inspections range between 4,000 flight cycles/9,000 flight hours (whichever occurs first), and 8,900 flight cycles/20,000 flight hours (whichever occurs first), depending on the modification. 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-2015-4813. Clarification of Terminating Action for Certain Paragraphs We have determined that if the inspection in paragraph (g)(4)(ii)(B)(2) of the proposed AD was done it would terminate the repetitive inspections specified in paragraph (g)(2) of this proposed AD. We have revised paragraph (g)(3)(i) of this proposed AD to include accomplishment of the inspection in paragraph (g)(4)(ii)(B)(2) as a terminating action. We have also determined that if the inspection in paragraph (g)(4)(ii)(B)(1) of the proposed AD was done it would terminate the repetitive inspections specified in paragraph (g)(2) of this proposed AD. We have revised paragraph (g)(3)(ii) of this proposed AD to include accomplishment of the inspection in paragraph (g)(4)(ii)(B)(1) of this AD as a terminating action. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 4, 2011. This service information describes procedures for repetitive inspections of certain bolt holes where parts of the MLG are attached to the wing rear spar, and repair. 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 of this NPRM. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Changes to AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999) This proposed AD would retain all the requirements of AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999). Since AD 99-16-01 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have been redesignated in this proposed AD, as listed in the following table: Revised Paragraph Identifiers ------------------------------------------------------------------------ Requirement in AD 99-16-01, Amendment 39-11236 (64 FR 40743, Corresponding requirement in this July 28, 1999) proposed AD ------------------------------------------------------------------------ paragraph (a) paragraph (g)(1) paragraph (b) paragraph (g)(2) paragraph (c) paragraph (g)(3) paragraph (d) paragraph (g)(4) paragraph (e) paragraph (g)(5) paragraph (f) paragraph (g)(6) ------------------------------------------------------------------------ Certain notes that appeared in AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999), were either removed due to the revised AD format or converted to regulatory text in this proposed AD. Notes 1, 6, and 7 of AD 99-16-01 have been removed from this proposed AD. Due to the revised AD format, certain information in these notes is now included in the AD template. The content of Note 2 of AD 99-16-01 is regulatory in nature; therefore, we have included that information in paragraph (k)(1) of this proposed AD. The content of Note 3 of AD 99-16-01 has been redesignated as Note 1 to paragraph (g) in this proposed AD. The content of Note 4 of AD 99-16-01 is regulatory in nature; therefore, we have included that information in paragraph (g)(2)(ii) of this proposed AD. The content of Note 5 of AD 99-16-01 is regulatory in nature; therefore, we have included that information in paragraph (k)(3) of this proposed AD. Costs of Compliance We estimate that this proposed AD affects 71 airplanes of U.S. registry. The actions required by AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999), and retained in this proposed AD, take about 226 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost about $0 per product. Based on these figures, the estimated cost of the actions that are required by AD 99-16-01 is $19,210 per product, per inspection cycle. We also estimate that it would take about 226 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $1,363,910, or $19,210 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. [[Page 71753]] Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999), and adding the following new AD: Airbus: Docket No. FAA-2015-4813; Directorate Identifier 2013-NM- 161-AD. (a) Comments Due Date We must receive comments by January 4, 2016. (b) Affected ADs This AD replaces AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999). (c) Applicability This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R airplanes; and Model A300 C4-605R Variant F airplanes; certificated in any category; all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by the results of a full-scale fatigue test when cracking was found on the rear spar of the wing, and the subsequent determination that the risk of such cracking is higher than initially determined. We are issuing this AD to detect and correct cracking of the rear spar of the wing, 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) Retained Inspections and Corrective Actions This paragraph restates the requirements of paragraphs (a), (b), (c), (d), (e), and (f) of AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999), with revised service information and reduced thresholds and repetitive intervals, for Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes; manufacturer serial numbers (MSNs) 252 through 553 inclusive; except those airplanes on which Airbus Modification 07601 has been accomplished prior to delivery. (1) Perform a high frequency eddy current (HFEC) rototest inspection to detect cracks in certain bolt holes where the main landing gear (MLG) forward pick-up fitting and MLG rib 5 aft are attached to the rear spar, in accordance with Airbus Service Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 25, 1994; or Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011, may be used for the actions required by this paragraph. (i) For airplanes that have accumulated 17,300 total landings or less as of November 9, 1995 (the effective date of AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999)): Inspect prior to the accumulation of 17,300 total landings, or within 1,500 landings after November 9, 1995, whichever occurs later. (ii) For airplanes that have accumulated 17,301 or more total landings, but less than 19,300 total landings as of November 9, 1995 (the effective date of AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999)): Inspect within 1,500 landings after November 9, 1995. (iii) For airplanes that have accumulated 19,300 or more total landings as of November 9, 1995 (the effective date of AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999)): Inspect within 750 landings after November 9, 1995 (the effective date of AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999)): (2) If no crack is found during the inspection required by paragraph (g)(1) of this AD, repeat that inspection thereafter at the time specified in either paragraph (g)(2)(i) or (g)(2)(ii) of this AD, as applicable. (i) For airplanes on which Airbus Modification 07716 (as specified in Airbus Service Bulletin A300-57-6020) has not been accomplished, inspect at the time specified in paragraph (g)(2)(i)(A) or (g)(2)(i)(B) of this AD, as applicable. (A) For airplanes having MSNs 465 through 553 inclusive: Repeat the inspection at intervals not to exceed 13,000 landings, until the inspection required by paragraph (g)(4)(ii)(A)(1) of this AD has been accomplished. (B) For airplanes having MSN 252 through 464 inclusive: Repeat the inspection at intervals not to exceed 8,400 landings, until the inspection required by paragraph (g)(4)(ii)(A)(2) of this AD has been accomplished. (ii) For airplanes on which Airbus Modification 07716 has been accomplished, inspect at the time specified in either paragraph (g)(2)(ii)(A) or (g)(2)(ii)(B) of this AD, as applicable. (A) For airplanes having MSNs 465 through 553 inclusive: Repeat the inspection at intervals not to exceed 11,800 landings, until the inspection required by paragraph (g)(4)(i)(B) of this AD has been accomplished. (B) For airplanes having MSNs 252 through 464 inclusive: Repeat the inspection within 10,700 landings following the initial inspection required by paragraph (g)(1) of this AD, and thereafter at intervals not to exceed 7,500 landings, until the inspection required by paragraph (g)(4)(ii)(B)(2) has been accomplished. (3) If any crack is found during the inspection required by either paragraph (g)(1) or (g)(2) of this AD, prior to further flight, [[Page 71754]] accomplish the requirements of either paragraph (g)(3)(i) or (g)(3)(ii) of this AD, as applicable. (i) For airplanes on which Airbus Modification 07716 has not been accomplished: Oversize the bolt hole by \1/32\ inch and repeat the HFEC inspection required by paragraph (g)(1) of this AD, in accordance with Airbus Service Bulletin 300-57-6017, Revision 01, including Appendix 1, dated July 25, 1994. After accomplishing the oversizing and HFEC inspection, repeat the inspection, as required by paragraph (g)(2) of this AD, at the applicable schedule specified in that paragraph, until the inspection required by paragraph (g)(4)(ii)(B)(1) or (g)(4)(ii)(B)(2) of this AD has been accomplished. (A) If no cracking is detected, install the second oversize bolt in accordance with Airbus Service Bulletin 300-57-6017, Revision 01, including Appendix 1, dated July 25, 1994. (B) If any cracking is detected, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. (ii) For airplanes on which Airbus Modification 07716 has been accomplished: Repair in accordance with a method approved by the Manager, International Branch, ANM-116. After repair, repeat the inspections as required by paragraph (g)(2) of this AD at the applicable schedule specified in that paragraph, until the inspection required by paragraph (g)(4)(ii)(B)(1) or (g)(4)(ii)(B)(2) of this AD has been accomplished. (4) Perform an ultrasonic inspection to detect cracks in certain bolt holes where the MLG forward pick-up fitting and MLG rib 5 aft are attached to the rear spar, in accordance with Airbus Service Bulletin A300-57-6017, Revision 03, dated November 19, 1997; or Revision 04, including Appendix 1, dated February 24, 2011; at the time specified in paragraph (g)(4)(i) or (g)(4)(ii) of this AD, as applicable. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011, may be used for the actions in this paragraph. (i) For airplanes not inspected prior to September 1, 1999 (the effective date of AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999)), as specified in Airbus Service Bulletin A300-57-6017, dated November 22, 1993; or Revision 01, including Appendix 1, dated July 25, 1994: Inspect at the time specified in paragraph (g)(4)(i)(A), (g)(4)(i)(B), or (g)(4)(i)(C) of this AD, as applicable. Accomplishment of this inspection terminates the requirements of paragraph (g)(1) of this AD. (A) For airplanes that have accumulated 17,300 total landings or fewer as of the effective date of this AD: Inspect prior to the accumulation of 17,300 total landings, or within 1,500 landings after September 1, 1999 (the effective date of AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999)), whichever occurs later. (B) For airplanes that have accumulated 17,301 total landings or more but fewer than 19,300 total landings as of September 1, 1999 (the effective date of AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999)): Inspect within 1,500 landings after September 1, 1999 (the effective date of AD 99-16-01). (C) For airplanes that have accumulated 19,300 total landings or more as of September 1, 1999 (the effective date of AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999)): Inspect within 750 landings after September 1, 1999 (the effective date of AD 99-16- 01). (ii) For airplanes on which an HFEC inspection was performed prior to September 1, 1999 (the effective date of AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999)), in accordance with the requirements of paragraph (g)(1) of this AD, or in accordance with Airbus Service Bulletin A300-57-6017, dated November 22, 1993: Inspect at the time specified in paragraph (g)(4)(ii)(A) or (g)(4)(ii)(B) of this AD, as applicable. (A) If no cracking was detected during any HFEC inspection accomplished prior to September 1, 1999 (the effective date of AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999)), and if Airbus Modification 07716 has not been accomplished: Inspect at the time specified in paragraph (g)(4)(ii)(A)(1) or (g)(4)(ii)(A)(2) of this AD, as applicable. (1) For airplanes having MSNs 465 through 553 inclusive: Inspect within 13,000 landings after the most recent HFEC inspection, and thereafter at intervals not to exceed 8,900 landings. Accomplishment of this inspection constitutes terminating action for the repetitive inspection requirement of paragraph (g)(2)(i)(A) of this AD. (2) For airplanes having MSNs 252 through 464 inclusive: Inspect within 8,400 landings after the most recent HFEC inspection, and thereafter at intervals not to exceed 5,500 landings. Accomplishment of this inspection constitutes terminating action for the repetitive inspection requirement of paragraph (g)(2)(i)(B) of this AD. (B) If any cracking was detected during any HFEC inspection performed prior to the effective date of this AD, regardless of the method of repair, or if Airbus Modification 07716 has been accomplished: Inspect at the time specified in paragraph (g)(4)(ii)(B)(1) or (g)(4)(ii)(B)(2) of this AD, as applicable. (1) For airplanes having MSNs 465 through 553 inclusive: Inspect within 11,800 landings after the most recent HFEC inspection, and thereafter at intervals not to exceed 8,200 landings. Accomplishment of this inspection constitutes terminating action for the repetitive inspection requirement of paragraph (g)(3)(i) or (g)(3)(ii) of this AD, as applicable. (2) For airplanes having MSNs 252 through 464 inclusive: Inspect within 10,700 landings after the initial inspection in accordance with paragraph (g)(1) of this AD, or within 7,500 landings after the most recent HFEC inspection, whichever occurs later, and thereafter at intervals not to exceed 4,900 landings. Accomplishment of this inspection constitutes terminating action for the repetitive inspection requirement of paragraph (g)(3)(i) or (g)(3)(ii) of this AD, as applicable. (5) If no cracking is detected during the ultrasonic inspection required by paragraph (g)(4)(i) of this AD, repeat that inspection thereafter at the time specified in paragraph (g)(5)(i) or (g)(5)(ii) of this AD, as applicable, until the initial ultrasonic inspection required by paragraph (h) of this AD is done. (i) For airplanes having MSNs 465 through 553 inclusive: Repeat the inspection at intervals not to exceed 8,900 landings. (ii) For airplanes having MSNs 232 through 464 inclusive: Repeat the inspection at intervals not to exceed 5,500 landings. (6) If any cracking is detected during any inspection performed in accordance with the requirements of paragraph (g)(4) or (g)(5) of this AD: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116; or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (or its delegated agent); or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Note 1 to paragraph (g) of this AD: Airbus Service Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 25, 1994; and Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011; also reference Airbus Service Bulletin A300-57-6020, dated November 22, 1993, as an additional source of service information for installation of oversize studs in the bolt holes. (h) New Repetitive Inspections At the applicable times specified in paragraph 1.B.(5), ``Accomplishment Timescale,'' of Airbus Service Bulletin A300-57- 6017, Revision 04, including Appendix 1, dated February 24, 2011: Do ultrasonic inspections to detect cracks in the MLG attachment fitting holes on the wing rear spar, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011. Repeat the inspections thereafter at the applicable intervals specified in paragraph 1.B.(5), ``Accomplishment Timescale,'' of Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011. For airplanes modified as specified in Airbus Service Bulletin A300-57-6073, the initial inspection threshold is counted from the completion date of the modification. Clarification of compliance time terminology used in table 1, ``Structural Inspection Program,'' of Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011, is provided in paragraphs (h)(1) through (h)(4) of this AD. Accomplishment of the initial inspection terminates the repetitive inspections required by paragraph (g)(5) of this AD. (1) For pre-Airbus Modification 07716 or pre-Airbus Modification 11440 airplanes: (i) The term ``flight cycles'' in the ``Inspection Threshold'' column is total flight cycles accumulated by the airplane. (ii) The term ``flight hours'' in the ``Inspection Threshold'' column is total flight hours accumulated by the airplane. (2) For post-Airbus Modification 07716 airplanes: (i) The term ``flight cycles'' in the ``Inspection Threshold'' column is total flight cycles accumulated by the airplane. [[Page 71755]] (ii) The term ``flight hours'' in the ``Inspection Threshold'' column is total flight hours accumulated by the airplane. (3) For post-Airbus Modification 11440 (Airbus Service Bulletin A300-57-6073) airplanes: (i) The term ``flight cycles'' in the ``Inspection Threshold'' column is flight cycles accumulated by the airplane after the modification was done. (ii) The term ``flight hours'' in the ``Inspection Threshold'' column is flight hours accumulated by the airplane after the modification was done. (4) For post-Airbus Modification 07601 airplanes: (i) The term ``flight cycles'' in the ``Inspection Threshold'' column is total flight cycles accumulated by the airplane. (ii) The term ``flight hours'' in the ``Inspection Threshold'' column is total flight hours accumulated by the airplane. (i) Repairs If any crack is found during any inspection required by paragraph (h) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (j) Repair Not Terminating Action Accomplishment of any repair as required by paragraph (i) of this AD is not terminating action for the repetitive inspections required by paragraph (g) or (h) of this AD. (k) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using any of the following service information: (1) Airbus Service Bulletin A300-57-6017, dated November 22, 1993, which is not incorporated by reference in this AD. (2) Airbus Service Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 25, 1994, which was incorporated by reference in AD 95-20-02, Amendment 39-9380 (60 FR 52618, October 10, 1995). (3) Airbus Service Bulletin A300-57-6017, Revision 02, dated January 14, 1997, including Appendix 1, dated July 25, 1994, which is not incorporated by reference in this AD. (4) Airbus Service Bulletin A300-57-6017, Revision 03, dated November 19, 1997, including Appendix 1, which was incorporated by reference in AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999). (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone: 425-227-2125; fax: 425-227-1149. Information may be emailed to: [email protected]. (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. The AMOC approval letter must specifically reference this AD. (ii) AMOCs approved previously for AD 99-16-01, Amendment 39- 11236 (64 FR 40743, July 28, 1999), 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 Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013-0180, dated August 9, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov searching for and locating Docket No. FAA-2015-4813. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on November 4, 2015. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-28892 Filed 11-16-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 221 / Tuesday, November 17, 2015 / Proposed Rules 71751
(1) Alternative Methods of Compliance DEPARTMENT OF TRANSPORTATION Internet http://www.airbus.com. You
(AMOCs): The Manager, New York Aircraft may view this referenced service
Certification Office (ACO), ANE–170, FAA, Federal Aviation Administration information at the FAA, Transport
has the authority to approve AMOCs for this Airplane Directorate, 1601 Lind Avenue
AD, if requested using the procedures found 14 CFR Part 39 SW., Renton, WA. For information on
in 14 CFR 39.19. In accordance with 14 CFR the availability of this material at the
[Docket No. FAA–2015–4813; Directorate
39.19, send your request to your principal FAA, call 425–227–1221.
Identifier 2013–NM–161–AD]
inspector or local Flight Standards District
Office, as appropriate. If sending information RIN 2120–AA64 Examining the AD Docket
directly to the ACO, send it to ATTN: You may examine the AD docket on
Program Manager, Continuing Operational Airworthiness Directives; Airbus the Internet at http://
Safety, FAA, New York ACO, 1600 Stewart Airplanes www.regulations.gov by searching for
Avenue, Suite 410, Westbury, NY 11590; AGENCY: Federal Aviation and locating Docket No. FAA–2015–
telephone 516–228–7300; fax 516–794–5531. Administration (FAA), DOT. 4813; or in person at the Docket
Before using any approved AMOC, notify Management Facility between 9 a.m.
ACTION: Notice of proposed rulemaking
your appropriate principal inspector, or and 5 p.m., Monday through Friday,
lacking a principal inspector, the manager of (NPRM).
except Federal holidays. The AD docket
the local flight standards district office/ SUMMARY: We propose to supersede contains this proposed AD, the
certificate holding district office. The AMOC Airworthiness Directive (AD) 99–16–01, regulatory evaluation, any comments
approval letter must specifically reference for certain Airbus Model A300 B4–600, received, and other information. The
this AD. B4–600R, and F4–600R series airplanes, street address for the Docket Operations
(2) Contacting the Manufacturer: For any and Model A300 C4–605R Variant F office (telephone 800–647–5527) is in
requirement in this AD to obtain corrective the ADDRESSES section. Comments will
airplanes (collectively called Model
actions from a manufacturer, the action must be available in the AD docket shortly
A300–600 series airplanes). AD 99–16–
be accomplished using a method approved after receipt.
01 currently requires repetitive
by the Manager, New York ACO, ANE–170, FOR FURTHER INFORMATION CONTACT: Dan
inspections of certain bolt holes where
Engine and Propeller Directorate, FAA; or Rodina, Aerospace Engineer,
parts of the main landing gear (MLG) are
Transport Canada Civil Aviation (TCCA); or International Branch, ANM–116,
attached to the wing rear spar, and
Bombardier, Inc.’s TCCA Design Approval Transport Airplane Directorate, FAA,
Organization (DAO). If approved by the DAO,
repair if necessary. Since we issued AD–
99–16–01, we have determined that the 1601 Lind Avenue SW., Renton, WA
the approval must include the DAO- 98057–3356; telephone: 425–227–2125;
authorized signature.
risk of cracking in the rear spar is higher
than initially determined. This fax: 425–227–1149.
(j) Related Information proposed AD would add airplanes to the SUPPLEMENTARY INFORMATION:
(1) Refer to Mandatory Continuing applicability, reduce the compliance Comments Invited
Airworthiness Information (MCAI) Canadian times and repetitive intervals for the
Airworthiness Directive CF–2015–17, dated inspections, and change the inspection We invite you to send any written
July 16, 2015, for related information. This procedures. We are proposing this AD to relevant data, views, or arguments about
MCAI may be found in the AD docket on the detect and correct cracking of the rear this proposed AD. Send your comments
Internet at http://www.regulations.gov by spar of the wing, which could result in to an address listed under the
searching for and locating Docket No. FAA– reduced structural integrity of the ADDRESSES section. Include ‘‘Docket No.
2015–4814. airplane. FAA–2015–4813; Directorate Identifier
(2) For service information identified in 2013–NM–161–AD’’ at the beginning of
DATES: We must receive comments on your comments. We specifically invite
this AD, contact Bombardier, Inc., 400 Côte- this proposed AD by January 4, 2016.
Vertu Road West, Dorval, Québec H4S 1Y9, comments on the overall regulatory,
ADDRESSES: You may send comments by economic, environmental, and energy
Canada; telephone 514–855–5000; fax 514–
855–7401; email thd.crj@
any of the following methods: aspects of this proposed AD. We will
aero.bombardier.com; Internet http://
• Federal eRulemaking Portal: Go to consider all comments received by the
www.bombardier.com. You may view this http://www.regulations.gov. Follow the closing date and may amend this
service information at the FAA, Transport instructions for submitting comments. proposed AD based on those comments.
Airplane Directorate, 1601 Lind Avenue SW., • Fax: 202–493–2251. We will post all comments we
Renton, WA. For information on the
• Mail: U.S. Department of receive, without change, to http://
availability of this material at the FAA, call Transportation, Docket Operations, M– www.regulations.gov, including any
425–227–1221. 30, West Building Ground Floor, Room personal information you provide. We
W12–140, 1200 New Jersey Avenue SE., will also post a report summarizing each
Issued in Renton, Washington, on Washington, DC 20590. substantive verbal contact we receive
November 5, 2015. • Hand Delivery: U.S. Department of about this proposed AD.
Dionne Palermo, Transportation, Docket Operations, M–
Acting Manager, Transport Airplane 30, West Building Ground Floor, Room Discussion
Directorate, Aircraft Certification Service. W12–140, 1200 New Jersey Avenue SE., On July 21, 1999, we issued AD 99–
[FR Doc. 2015–28885 Filed 11–16–15; 8:45 am] Washington, DC, between 9 a.m. and 5 16–01, Amendment 39–11236 (64 FR
BILLING CODE 4910–13–P
p.m., Monday through Friday, except 40743, July 28, 1999). AD 99–16–01
wgreen on DSK2VPTVN1PROD with PROPOSALS
Federal holidays. requires actions intended to address an
For service information identified in unsafe condition on Airbus Model A300
this proposed AD, contact Airbus SAS, B4–600, B4–600R, and F4–600R series
Airworthiness Office—EAW, 1 Rond airplanes, and Model A300 C4–605R
Point Maurice Bellonte, 31707 Blagnac Variant F airplanes (collectively called
Cedex, France; telephone +33 5 61 93 36 Model A300–600 series airplanes).
96; fax +33 5 61 93 44 51; email Since we issued AD 99–16–01,
account.airworth-eas@airbus.com; Amendment 39–11236 (64 FR 40743,
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![71752 Federal Register / Vol. 80, No. 221 / Tuesday, November 17, 2015 / Proposed Rules
July 28, 1999), a fleet survey and and locating Docket No. FAA–2015– have been redesignated in this proposed
updated fatigue and damage tolerance 4813. AD, as listed in the following table:
analyses have shown that the threshold
Clarification of Terminating Action for
for the initial inspections and the REVISED PARAGRAPH IDENTIFIERS
Certain Paragraphs
intervals for the repetitive inspections
need to be reduced. We have determined that if the Requirement in AD
The European Aviation Safety Agency inspection in paragraph (g)(4)(ii)(B)(2) of 99–16–01, Amend- Corresponding
the proposed AD was done it would ment 39–11236 requirement in this
(EASA), which is Technical Agent for (64 FR 40743, July proposed AD
the Member States of the European terminate the repetitive inspections 28, 1999)
Union, has issued EASA Airworthiness specified in paragraph (g)(2) of this
Directive 2013–0180, dated August 9, proposed AD. We have revised paragraph (a) paragraph (g)(1)
2013 (referred to after this as the paragraph (g)(3)(i) of this proposed AD paragraph (b) paragraph (g)(2)
to include accomplishment of the paragraph (c) paragraph (g)(3)
Mandatory Continuing Airworthiness paragraph (d) paragraph (g)(4)
Information, or ‘‘the MCAI’’), to correct inspection in paragraph (g)(4)(ii)(B)(2)
paragraph (e) paragraph (g)(5)
an unsafe condition for the specified as a terminating action. We have also paragraph (f) paragraph (g)(6)
products. The MCAI states: determined that if the inspection in
paragraph (g)(4)(ii)(B)(1) of the proposed Certain notes that appeared in AD 99–
During full-scale fatigue testing, cracks
were found on the rear spar from certain bolt AD was done it would terminate the 16–01, Amendment 39–11236 (64 FR
holes at the attachment of the Main Landing repetitive inspections specified in 40743, July 28, 1999), were either
gear (MLG) forward pick-up fitting and the paragraph (g)(2) of this proposed AD. removed due to the revised AD format
MLG Rib 5 aft. We have revised paragraph (g)(3)(ii) of or converted to regulatory text in this
This condition, if not detected and this proposed AD to include proposed AD.
corrected, could reduce the structural accomplishment of the inspection in • Notes 1, 6, and 7 of AD 99–16–01
integrity of the aeroplane. paragraph (g)(4)(ii)(B)(1) of this AD as a have been removed from this proposed
DGAC [Direction Générale de l’Aviation terminating action.
Civile] France issued * * * [an AD] (later
AD. Due to the revised AD format,
revised) to require High Frequency Eddy Related Service Information Under 1 certain information in these notes is
Current (HFEC) or Ultrasonic (U/S) CFR Part 51 now included in the AD template.
inspections of certain fastener holes where • The content of Note 2 of AD 99–16–
the MLG forward pick-up fitting and MLG Airbus has issued Service Bulletin 01 is regulatory in nature; therefore, we
Rib 5 aft are attached to the rear spar. A300–57–6017, Revision 04, including have included that information in
Since DGAC France * * * [issued a Appendix 1, dated February 4, 2011. paragraph (k)(1) of this proposed AD.
revised AD, which corresponded to FAA AD This service information describes • The content of Note 3 of AD 99–16–
99–16–01, Amendment 39–11236 (64 FR procedures for repetitive inspections of 01 has been redesignated as Note 1 to
40743, July 28, 1999), which superseded certain bolt holes where parts of the paragraph (g) in this proposed AD.
FAA AD 95–20–02, Amendment 39–9380 (60 MLG are attached to the wing rear spar, • The content of Note 4 of AD 99–16–
FR 52618, October 10, 1995)] * * *, a fleet and repair. This service information is 01 is regulatory in nature; therefore, we
survey and updated Fatigue and Damage
reasonably available because the have included that information in
Tolerance analyses have been performed in
order to substantiate the second A300–600 interested parties have access to it paragraph (g)(2)(ii) of this proposed AD.
Extended Service Goal (ESG2) exercise. The through their normal course of business • The content of Note 5 of AD 99–16–
results of these analyses have shown that the or by the means identified in the 01 is regulatory in nature; therefore, we
threshold and interval must be reduced to ADDRESSES section of this NPRM. have included that information in
allow timely detection of these cracks and paragraph (k)(3) of this proposed AD.
accomplishment of an applicable corrective FAA’s Determination and Requirements
action. of This Proposed AD Costs of Compliance
For the reasons described above, this This product has been approved by We estimate that this proposed AD
[EASA] AD retains the requirements of [the the aviation authority of another affects 71 airplanes of U.S. registry.
revised DGAC France AD], which is country, and is approved for operation The actions required by AD 99–16–01,
superseded, but reduces the related Amendment 39–11236 (64 FR 40743,
in the United States. Pursuant to our
compliance times.
bilateral agreement with the State of July 28, 1999), and retained in this
The new, reduced threshold for the Design Authority, we have been notified proposed AD, take about 226 work-
initial inspection ranges between 8,900 of the unsafe condition described in the hours per product, at an average labor
total flight cycles/20,000 total flight MCAI and service information rate of $85 per work-hour. Required
hours, and 34,600 total flight cycles/ referenced above. We are proposing this parts cost about $0 per product. Based
77,800 total flight hours, depending on AD because we evaluated all pertinent on these figures, the estimated cost of
the modification. The grace periods (750 information and determined an unsafe the actions that are required by AD 99–
or 1,500 landings) for airplanes that condition exists and is likely to exist or 16–01 is $19,210 per product, per
have exceeded the specified thresholds develop on other products of the same inspection cycle.
are unchanged from those provided in type design. We also estimate that it would take
AD 99–16–01, Amendment 39–11236 about 226 work-hours per product to
(64 FR 40743, July 28, 1999). The new, Changes to AD 99–16–01, Amendment comply with the basic requirements of
reduced intervals for the repetitive 39–11236 (64 FR 40743, July 28, 1999) this proposed AD. The average labor
wgreen on DSK2VPTVN1PROD with PROPOSALS
inspections range between 4,000 flight This proposed AD would retain all rate is $85 per work-hour. Based on
cycles/9,000 flight hours (whichever the requirements of AD 99–16–01, these figures, we estimate the cost of
occurs first), and 8,900 flight cycles/ Amendment 39–11236 (64 FR 40743, this proposed AD on U.S. operators to
20,000 flight hours (whichever occurs July 28, 1999). Since AD 99–16–01 was be $1,363,910, or $19,210 per product.
first), depending on the modification. issued, the AD format has been revised, We have received no definitive data
You may examine the MCAI in the AD and certain paragraphs have been that would enable us to provide cost
docket on the Internet at http:// rearranged. As a result, the estimates for the on-condition actions
www.regulations.gov by searching for corresponding paragraph identifiers specified in this proposed AD.
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![Federal Register / Vol. 80, No. 221 / Tuesday, November 17, 2015 / Proposed Rules 71753
Authority for This Rulemaking PART 39—AIRWORTHINESS A300–57–6017, Revision 01, including
DIRECTIVES Appendix 1, dated July 25, 1994; or Airbus
Title 49 of the United States Code Service Bulletin A300–57–6017, Revision 04,
specifies the FAA’s authority to issue ■ 1. The authority citation for part 39 including Appendix 1, dated February 24,
rules on aviation safety. Subtitle I, continues to read as follows: 2011. As of the effective date of this AD, only
section 106, describes the authority of Airbus Service Bulletin A300–57–6017,
Authority: 49 U.S.C. 106(g), 40113, 44701. Revision 04, including Appendix 1, dated
the FAA Administrator. ‘‘Subtitle VII: February 24, 2011, may be used for the
Aviation Programs,’’ describes in more § 39.13 [Amended] actions required by this paragraph.
detail the scope of the Agency’s ■ 2. The FAA amends § 39.13 by (i) For airplanes that have accumulated
authority. removing Airworthiness Directive (AD) 17,300 total landings or less as of November
We are issuing this rulemaking under 99–16–01, Amendment 39–11236 (64 9, 1995 (the effective date of AD 99–16–01,
FR 40743, July 28, 1999), and adding the Amendment 39–11236 (64 FR 40743, July 28,
the authority described in ‘‘Subtitle VII,
following new AD: 1999)): Inspect prior to the accumulation of
Part A, Subpart III, Section 44701: 17,300 total landings, or within 1,500
General requirements.’’ Under that Airbus: Docket No. FAA–2015–4813; landings after November 9, 1995, whichever
section, Congress charges the FAA with Directorate Identifier 2013–NM–161–AD. occurs later.
promoting safe flight of civil aircraft in (a) Comments Due Date (ii) For airplanes that have accumulated
air commerce by prescribing regulations 17,301 or more total landings, but less than
for practices, methods, and procedures We must receive comments by January 4, 19,300 total landings as of November 9, 1995
2016. (the effective date of AD 99–16–01,
the Administrator finds necessary for
safety in air commerce. This regulation (b) Affected ADs Amendment 39–11236 (64 FR 40743, July 28,
1999)): Inspect within 1,500 landings after
is within the scope of that authority This AD replaces AD 99–16–01, November 9, 1995.
because it addresses an unsafe condition Amendment 39–11236 (64 FR 40743, July 28, (iii) For airplanes that have accumulated
that is likely to exist or develop on 1999). 19,300 or more total landings as of November
products identified in this rulemaking (c) Applicability 9, 1995 (the effective date of AD 99–16–01,
action. This AD applies to Airbus Model A300 B4–
Amendment 39–11236 (64 FR 40743, July 28,
1999)): Inspect within 750 landings after
Regulatory Findings 601, B4–603, B4–620, and B4–622 airplanes;
November 9, 1995 (the effective date of AD
Model A300 B4–605R and B4–622R
99–16–01, Amendment 39–11236 (64 FR
We determined that this proposed AD airplanes; Model A300 F4–605R airplanes;
40743, July 28, 1999)):
would not have federalism implications and Model A300 C4–605R Variant F
(2) If no crack is found during the
under Executive Order 13132. This airplanes; certificated in any category; all
inspection required by paragraph (g)(1) of
proposed AD would not have a manufacturer serial numbers.
this AD, repeat that inspection thereafter at
substantial direct effect on the States, on (d) Subject the time specified in either paragraph (g)(2)(i)
the relationship between the national Air Transport Association (ATA) of or (g)(2)(ii) of this AD, as applicable.
Government and the States, or on the America Code 57, Wings. (i) For airplanes on which Airbus
distribution of power and Modification 07716 (as specified in Airbus
(e) Reason Service Bulletin A300–57–6020) has not been
responsibilities among the various
This AD was prompted by the results of a accomplished, inspect at the time specified
levels of government. in paragraph (g)(2)(i)(A) or (g)(2)(i)(B) of this
full-scale fatigue test when cracking was
For the reasons discussed above, I found on the rear spar of the wing, and the AD, as applicable.
certify this proposed regulation: subsequent determination that the risk of (A) For airplanes having MSNs 465
such cracking is higher than initially through 553 inclusive: Repeat the inspection
1. Is not a ‘‘significant regulatory
determined. We are issuing this AD to detect at intervals not to exceed 13,000 landings,
action’’ under Executive Order 12866; until the inspection required by paragraph
and correct cracking of the rear spar of the
2. Is not a ‘‘significant rule’’ under the wing, which could result in reduced (g)(4)(ii)(A)(1) of this AD has been
DOT Regulatory Policies and Procedures structural integrity of the airplane. accomplished.
(44 FR 11034, February 26, 1979); (B) For airplanes having MSN 252 through
(f) Compliance 464 inclusive: Repeat the inspection at
3. Will not affect intrastate aviation in Comply with this AD within the intervals not to exceed 8,400 landings, until
Alaska; and compliance times specified, unless already the inspection required by paragraph
4. Will not have a significant done. (g)(4)(ii)(A)(2) of this AD has been
economic impact, positive or negative, accomplished.
(g) Retained Inspections and Corrective (ii) For airplanes on which Airbus
on a substantial number of small entities Actions Modification 07716 has been accomplished,
under the criteria of the Regulatory This paragraph restates the requirements of inspect at the time specified in either
Flexibility Act. paragraphs (a), (b), (c), (d), (e), and (f) of AD paragraph (g)(2)(ii)(A) or (g)(2)(ii)(B) of this
We prepared a regulatory evaluation 99–16–01, Amendment 39–11236 (64 FR AD, as applicable.
of the estimated costs to comply with 40743, July 28, 1999), with revised service (A) For airplanes having MSNs 465
this proposed AD and placed it in the information and reduced thresholds and through 553 inclusive: Repeat the inspection
AD docket. repetitive intervals, for Airbus Model A300 at intervals not to exceed 11,800 landings,
B4–600, B4–600R, and F4–600R series until the inspection required by paragraph
List of Subjects in 14 CFR Part 39 airplanes, and Model A300 C4–605R Variant (g)(4)(i)(B) of this AD has been accomplished.
F airplanes; manufacturer serial numbers (B) For airplanes having MSNs 252 through
Air transportation, Aircraft, Aviation (MSNs) 252 through 553 inclusive; except 464 inclusive: Repeat the inspection within
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safety, Incorporation by reference, those airplanes on which Airbus 10,700 landings following the initial
Safety. Modification 07601 has been accomplished inspection required by paragraph (g)(1) of
prior to delivery. this AD, and thereafter at intervals not to
The Proposed Amendment (1) Perform a high frequency eddy current exceed 7,500 landings, until the inspection
(HFEC) rototest inspection to detect cracks in required by paragraph (g)(4)(ii)(B)(2) has been
Accordingly, under the authority certain bolt holes where the main landing accomplished.
delegated to me by the Administrator, gear (MLG) forward pick-up fitting and MLG (3) If any crack is found during the
the FAA proposes to amend 14 CFR part rib 5 aft are attached to the rear spar, in inspection required by either paragraph (g)(1)
39 as follows: accordance with Airbus Service Bulletin or (g)(2) of this AD, prior to further flight,
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(ii) The term ‘‘flight hours’’ in the appropriate. If sending information directly DEPARTMENT OF ENERGY
‘‘Inspection Threshold’’ column is total flight to the International Branch, send it to ATTN:
hours accumulated by the airplane. Dan Rodina, Aerospace Engineer, Federal Energy Regulatory
(3) For post-Airbus Modification 11440 International Branch, ANM–116, Transport Commission
(Airbus Service Bulletin A300–57–6073) Airplane Directorate, FAA, 1601 Lind
airplanes:
Avenue SW., Renton, WA 98057–3356; 18 CFR Part 35
(i) The term ‘‘flight cycles’’ in the
‘‘Inspection Threshold’’ column is flight telephone: 425–227–2125; fax: 425–227–
cycles accumulated by the airplane after the 1149. Information may be emailed to: 9-
[Docket No. RM15–23–000]
modification was done. ANM-116-AMOC-REQUESTS@faa.gov.
(ii) The term ‘‘flight hours’’ in the (i) Before using any approved AMOC, Collection of Connected Entity Data
‘‘Inspection Threshold’’ column is flight notify your appropriate principal inspector, from Regional Transmission
hours accumulated by the airplane after the or lacking a principal inspector, the manager
modification was done.
Organizations and Independent
of the local flight standards district office/ System Operators
(4) For post-Airbus Modification 07601 certificate holding district office. The AMOC
airplanes: approval letter must specifically reference
(i) The term ‘‘flight cycles’’ in the AGENCY:Federal Energy Regulatory
this AD. Commission. DOE.
‘‘Inspection Threshold’’ column is total flight
cycles accumulated by the airplane. (ii) AMOCs approved previously for AD
(ii) The term ‘‘flight hours’’ in the 99–16–01, Amendment 39–11236 (64 FR ACTION:Order Granting Motion for
‘‘Inspection Threshold’’ column is total flight 40743, July 28, 1999), are approved as Technical Conference and Request to
hours accumulated by the airplane. AMOCs for the corresponding provisions of Postpone Comment Deadline.
this AD.
(i) Repairs
(2) Contacting the Manufacturer: As of the SUMMARY: In this order, the Federal
If any crack is found during any inspection effective date of this AD, for any requirement Energy Regulatory Commission
required by paragraph (h) of this AD: Before in this AD to obtain corrective actions from
further flight, repair using a method
(Commission) grants a motion for a
a manufacturer, the action must be technical conference and request to
approved by the Manager, International
Branch, ANM–116, Transport Airplane accomplished using a method approved by postpone comment deadline that was
Directorate, FAA; or the European Aviation the Manager, International Branch, ANM– filed in response to the Notice of
Safety Agency (EASA); or Airbus’s EASA 116, Transport Airplane Directorate, FAA; or Proposed Rulemaking for the Collection
Design Organization Approval (DOA). EASA; or Airbus’s EASA DOA. If approved of Connected Entity Data from Regional
by the DOA, the approval must include the Transmission Organizations and
(j) Repair Not Terminating Action
DOA-authorized signature. Independent System Operators (NOPR)
Accomplishment of any repair as required
by paragraph (i) of this AD is not terminating (m) Related Information that Commission issued on September
action for the repetitive inspections required 17, 2015.1 The Commission directs staff
(1) Refer to Mandatory Continuing
by paragraph (g) or (h) of this AD. to convene a technical conference on
Airworthiness Information (MCAI) EASA
December 8, 2015 and postpones the
(k) Credit for Previous Actions Airworthiness Directive 2013–0180, dated
August 9, 2013, for related information. This
due date for comments on the NOPR
This paragraph provides credit for actions until January 22, 2016, 45 days after the
required by paragraphs (g) and (h) of this AD, MCAI may be found in the AD docket on the
Internet at http://www.regulations.gov technical conference.
if those actions were performed before the
effective date of this AD using any of the searching for and locating Docket No. FAA– DATES: The technical conference will be
following service information: 2015–4813. held on December 8, 2015 and NOPR
(1) Airbus Service Bulletin A300–57–6017, (2) For service information identified in comments will be due January 22, 2016.
dated November 22, 1993, which is not this AD, contact Airbus SAS, Airworthiness
incorporated by reference in this AD. Office—EAW, 1 Rond Point Maurice FOR FURTHER INFORMATION CONTACT:
(2) Airbus Service Bulletin A300–57–6017,
Bellonte, 31707 Blagnac Cedex, France; David Pierce (Technical Information),
Revision 01, including Appendix 1, dated
July 25, 1994, which was incorporated by telephone +33 5 61 93 36 96; fax +33 5 61 Office of Enforcement, Federal Energy
reference in AD 95–20–02, Amendment 39– 93 44 51; email account.airworth-eas@ Regulatory Commission, 888 First Street
9380 (60 FR 52618, October 10, 1995). airbus.com; Internet http://www.airbus.com. NE., Washington, DC 20426, (202) 502–
(3) Airbus Service Bulletin A300–57–6017, You may view this service information at the 6454 david.pierce@ferc.gov.
Revision 02, dated January 14, 1997, FAA, Transport Airplane Directorate, 1601
including Appendix 1, dated July 25, 1994, Kathryn Kuhlen (Legal Information),
Lind Avenue SW., Renton, WA. For
which is not incorporated by reference in this Office of Enforcement, Federal Energy
information on the availability of this
AD. material at the FAA, call 425–227–1221.
Regulatory Commission, 888 First Street
(4) Airbus Service Bulletin A300–57–6017, NE., Washington, DC 20426, (202) 502–
Revision 03, dated November 19, 1997, Issued in Renton, Washington, on 6855 kathryn.kuhlen@ferc.gov.
including Appendix 1, which was November 4, 2015.
incorporated by reference in AD 99–16–01, SUPPLEMENTARY INFORMATION:
Dionne Palermo,
Amendment 39–11236 (64 FR 40743, July 28, Before Commissioners: Norman C.
1999). Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service. Bay, Chairman; Cheryl A. LaFleur, Tony
(l) Other FAA AD Provisions [FR Doc. 2015–28892 Filed 11–16–15; 8:45 am]
Clark, and Colette D. Honorable.
The following provisions also apply to this BILLING CODE 4910–13–P Collection of Connected Entity Data
AD: from Regional Transmission
wgreen on DSK2VPTVN1PROD with PROPOSALS
(1) Alternative Methods of Compliance Organizations and Independent System
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Operators
Directorate, FAA, has the authority to Docket No. RM15–23–000
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. 1 Collection of Connected Entity Data from
In accordance with 14 CFR 39.19, send your Regional Transmission Organizations and
request to your principal inspector or local Independent System Operators, 152 FERC ¶ 61,219
Flight Standards District Office, as (2015).
VerDate Sep<11>2014 14:39 Nov 16, 2015 Jkt 238001 PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 E:\FR\FM\17NOP1.SGM 17NOP1](https://thefederalregister.org/doc/80_FR_71972/page/5.svg)
Document Created: 2015-12-14 14:00:10
Document Modified: 2015-12-14 14:00:10
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by January 4, 2016. | |
| Contact | Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425-227-1149. | |
| FR Citation | 80 FR 71751 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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