81 FR 5056 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 20 (February 1, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 20 (February 1, 2016)
| Page Range | 5056-5060 | |
| FR Document | 2016-01736 |
[Federal Register Volume 81, Number 20 (Monday, February 1, 2016)] [Proposed Rules] [Pages 5056-5060] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-01736] ======================================================================== Proposed Rules Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. ======================================================================== Federal Register / Vol. 81, No. 20 / Monday, February 1, 2016 / Proposed Rules [[Page 5056]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-0451; Directorate Identifier 2013-NM-253-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) 2004-23- 20 for certain Airbus Model A300 series airplanes and Model A300 B4- 601, A300 B4-603, A300 B4-620, A300 B4-622, A300 B4-605R, A300 B4-622R, A300 F4-605R, and C4-605R Variant F airplanes. AD 2004-23-20 currently requires, for certain airplanes, repetitive inspections for cracking around certain attachment holes, installation of new fasteners for certain airplanes, and follow-on corrective actions if necessary. AD 2004-23-20 also requires modifying certain fuselage frames, which terminates certain repetitive inspections. Since we issued AD 2004-23- 20, we received a report indicating that the material used to manufacture the upper frame feet was changed and negatively affected the fatigue life of the frame feet. This proposed AD would reduce the compliance times for the initial inspection and the inspection intervals. This proposed AD would also expand the applicability and require an additional repair on certain airplanes that have been modified. We are proposing this AD to prevent cracking of the center section of the fuselage, which could result in a ruptured frame foot and reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by March 17, 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 NPRM, 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-2016- 0451; 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, 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-2016-0451; Directorate Identifier 2013-NM-253-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 November 10, 2004, we issued AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004) for all Airbus Model A300 series airplanes and Model A300 B4-601, A300 B4-603, A300 B4-620, A300 B4-622, A300 B4-605R, A300 B4-622R, A300 F4-605R and A300 C4-605R Variant F airplanes. (That AD superseded AD 2001-06-10, Amendment 39-12157 (66 FR 17490, April 2, 2001)). AD 2004-23-20 requires actions intended to address an unsafe condition on the products listed above. Since we issued AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004) we received a report indicating that a change in material for manufacturing the frame feet for certain airplanes negatively impacted the fatigue life of the frame feet. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013-0295, dated December 11, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for Airbus Model A300 B4- 601, A300 B4-603, A300 B4-620, A300 B4-622, A300 B4-605R, A300 B4-622R, A300 F4-605R, and A300 C4-605R Variant F airplanes. The MCAI states: During a scheduled inspection of the fuselage frame feet of an in-service A300-600 aeroplane, cracks were observed in Frame (FR) 43, FR 44, FR 45 and FR 46 between stringer (STGR) 24 and STGR 30. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. [[Page 5057]] To address this unsafe condition, [Direction Generale de l'Aviation Civile] DGAC France issued [an] AD * * * to require repetitive inspections of the affected frames and stringers on both sides of the fuselage and, depending on findings, repairs, as specified in Airbus Service Bulletin (SB) A300-53-6122. Subsequently, DGAC France issued AD F-2004-002 [http://ad.easa.europa.eu/ad/F-2004-002] (EASA approval 2003-2108) [which corresponds to FAA AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004)], retaining the requirements of [an] AD * * * and required the embodiment of Airbus SB A300-53-6125 (Airbus modification 12168) in order to improve the life of the frame foot attachment. Since DGAC France AD F-2004-002 was issued, a fleet survey and updated Fatigue and Damage Tolerance analyses were performed in order to substantiate the second A300-600 Extended Service Goal (ESG2) exercise. It was highlighted that the frame feet material change from 2024T3511 (A300B4) to 7175T7351 (A300-600) had an impact on the frame feet fatigue life duration. Airbus SB A300-53-6122 was revised accordingly to decrease the inspection thresholds and intervals. Subsequent SB revision introduced a second structural modification point (SMP2) for aeroplanes that embody Airbus SB A300-53-6125 (modification 12168). For the reasons described above, this new [EASA] AD retains the requirements of DGAC France AD F-2004-002, which is superseded, but requires those actions within the new thresholds and intervals as specified in Revision 04 of Airbus SB A300-53-6122. The retained requirements include rototest inspections for cracking in the area surrounding the frame feet attachment holes between fuselage FR 41 and FR 46 from stringers 24 to 28 on the left and right sides, and related investigative and corrective action if necessary. The related investigative actions include additional rotating probe inspections of the adjacent holes. The corrective actions include reaming out cracks, cold working fastener holes, and installing oversized fasteners, or repair. This proposed AD also expands the applicability to include airplanes on which Airbus Modification 12168 was done. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-0451. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300-53-6122, Revision 04, dated February 27, 2012. The service information describes procedures for the repetitive inspections of certain frame feet attachment holes for cracks, installation of new fasteners, and repair of cracked areas. In addition, Airbus has issued Service Bulletin A300-53-6125, Revision 01, dated June 13, 2003. The service information provides compliance times for certain airplanes to do the proposed modification. Airbus has also issued Service Bulletin A300-53-6125, Revision 04, dated March 17, 2015. The service information describes procedures for the modification of certain upper frame feet fittings. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA's Determination and Requirements of This 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 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004) This proposed AD would retain all requirements of AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004). Since AD 2004-23- 20 was issued the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph designators have changed in this proposed AD, as listed in the following table: Revised Paragraph Designators ------------------------------------------------------------------------ Requirement in AD 2004-23-20, Amendment 39-13875 (69 FR 68779, Corresponding requirement in this November 26, 2004) proposed AD ------------------------------------------------------------------------ paragraph (f) paragraph (g). paragraph (g) paragraph (h). paragraph (h) paragraph (i). paragraph (i) paragraph (j). paragraph (j) paragraph (k). ------------------------------------------------------------------------ We have converted ``TABLE 1.--SERVICE INFORMATION'' in AD 2004-23- 20, Amendment 39-13875 (69 FR 68779, November 26, 2004) to text in paragraphs (j)(3)(i) and (j)(3)(ii) of this proposed AD for formatting purposes only. We have also moved the service information acceptable for compliance if previously done from ``TABLE 1.--SERVICE INFORMATION'' in AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004) to paragraph (r)(2) of this proposed AD. Costs of Compliance We estimate that this proposed AD affects 65 airplanes of U.S. registry. The actions that are required by AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004), and retained in this proposed AD take about 90 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost about $4,000 per product. Based on these figures, the estimated cost of the actions that were required by AD 2004-23-20 is $11,650 per product. We also estimate that it would take up to 109 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost up to $6,070 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $996,775, or $15,335 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. 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 [[Page 5058]] 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. 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) 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004), and adding the following new AD: Airbus: Docket No. FAA-2016-0451; Directorate Identifier 2013-NM- 253-AD. (a) Comments Due Date We must receive comments by March 17, 2016. (b) Affected ADs This AD replaces AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004). (c) Applicability This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2- 203, B4-2C, B4-103, and B4-203 airplanes; and Model A300 B4-601, A300 B4-603, A300 B4-620, A300 B4-622, A300 B4-605R, A300 B4-622R, A300 F4-605R and A300 C4-605R Variant F airplanes; certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a report indicating that the material used to manufacture the upper frame feet was changed and negatively affected the fatigue life of the frame feet. We are issuing this AD to prevent cracking of the center section of the fuselage, which could result in a ruptured frame foot and reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspections This paragraph restates the requirements of paragraph (f) of AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004), with revised service information. For Model A300 B4-600 and A300 B4- 600R series airplanes, and Model A300 C4-605R Variant F and A300 F4- 605R airplanes, except those airplanes modified by Airbus Modification 12168: Perform a high-frequency eddy-current or rototest inspection to detect cracking in the area surrounding the frame feet attachment holes between fuselage frames (FR) 41 and FR 46 from stringers 24 to 28, left-and right-hand sides, in accordance with Airbus Service Bulletin A300-53-6122, dated February 9, 2000; or the Accomplishment Instructions of Airbus Service Bulletin A300- 53-6122, Revision 04, dated February 27, 2012; at the applicable time specified in paragraph (g)(1) or (g)(2) of this AD. Accomplishing an inspection required by paragraph (m) of this AD terminates the inspections required by this paragraph. (1) For airplanes on which Task 53-15-54 in Maintenance Review Board Document (MRBD), Revision 3, dated April 1998, has not been accomplished as of May 7, 2001 (the effective date of AD 2001-06-10, Amendment 39-12157 (66 FR 17490, April 2, 2001)): Perform the inspection at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. (i) Prior to the accumulation of the total flight-cycle or flight-hour threshold, whichever occurs first, specified in paragraph 1.E. (``Compliance'') of Airbus Service Bulletin A300-53- 6122, dated February 9, 2000; or (ii) Within the applicable grace period specified in paragraph 1.E. (``Compliance'') of Airbus Service Bulletin A300-53-6122, dated February 9, 2000. (2) For airplanes on which Task 53-15-54 in the MRBD, Revision 3, dated April 1998, has been accomplished as of May 7, 2001 (the effective date of AD 2001-06-10, Amendment 39-12157 (66 FR 17490, April 2, 2001)): Perform the next repetitive inspection at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. (i) Within the flight-cycle or flight-hour interval, whichever occurs first, specified in paragraph 1.E. (``Compliance'') of Airbus Service Bulletin A300-53-6122, dated February 9, 2000, following the latest inspection accomplished as specified in MRBD, Revision 3, dated April 1998; or (ii) Within the grace period specified in paragraph 1.E. (``Compliance'') of Airbus Service Bulletin A300-53-6122, dated February 9, 2000. (h) Retained Installation of Fasteners and Repetitive Inspections This paragraph restates the requirements of paragraph (g) of AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004), with revised service information. For airplanes on which no cracking is detected during the inspection required by paragraph (g) of this AD, prior to further flight, install new fasteners as applicable, in accordance with Airbus Service Bulletin A300-53-6122, dated February 9, 2000; or the Accomplishment Instructions of Airbus Service Bulletin A300-53-6122, Revision 04, dated February 27, 2012; and repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed the applicable intervals specified in paragraph 1.E. (``Compliance'') of Airbus Service Bulletin A300-53-6122, dated February 9, 2000; until the actions required by paragraph (j) or (o) of this AD have been done or the initial inspection required by paragraph (m) of this AD is done. (i) Retained Corrective Actions This paragraph restates the requirements of paragraph (h) of AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004), with revised service information. For airplanes on which cracking is detected during any inspection required by paragraph (g) of this AD: Prior to further flight, except as required by paragraph (k) of this AD, accomplish corrective actions (e.g., performing rotating probe inspections, reaming out cracks, cold working fastener holes, and installing oversized fasteners) in accordance with Airbus Service Bulletin A300-53-6122, dated February 9, 2000; or the Accomplishment Instructions of Airbus Service Bulletin A300-53-6122, Revision 04, dated February 27, 2012. Repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed the applicable intervals specified in paragraph 1.E. (``Compliance'') of Airbus Service Bulletin A300-53-6122, dated February 9, 2000; until the actions required by paragraph (j) or (o) of this AD have been done, or the initial inspection required by paragraph (m) of this AD is done. (j) Retained Modification: Model A300 Series Airplanes This paragraph restates the requirements of paragraph (i) of AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004), for certain airplanes, with no changes. For Model A300 series airplanes: Within the compliance times specified in paragraph 1.E. (``Compliance'') of Airbus Service Bulletin A300-53-0271, Revision 03, dated June 13, 2003, modify the fuselage frames, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-0271, Revision 03, dated June 13, 2003. For airplanes that have exceeded their design service goal, as specified in NOTE (01) of paragraph 1.E. (``Compliance'') of Airbus Service Bulletin A300- 53-0271, Revision 03, dated June 13, 2003; this AD requires compliance within the earlier of the flight-cycle and flight-hour grace periods specified in Airbus Service Bulletin A300-53-0271, Revision 03, dated June 13, 2003. [[Page 5059]] (k) Retained Exceptions to Service Bulletin Procedures This paragraph restates the requirements of paragraph (j) of AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004), with specific delegation approval language. During any inspection required by paragraphs (g), (h), (i), or (j) of this AD, if the applicable service information specified in paragraphs (g), (h), (i), and (j) of this AD specifies to contact the manufacturer for appropriate instructions: Before further flight, perform all applicable corrective actions in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Generale de l'Aviation Civile (DGAC) (or its delegated agent); or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (l) New Definition for This AD: Average Flight Time (AFT) For the purpose of this AD, use the parameters specified in paragraphs (l)(1), (l)(2), and (l)(3) of this AD to determine the applicable AFT for the actions required by paragraph (m) and compliance times required by paragraph (n) of this AD. (1) The initial inspection compliance time, as the total accumulated flight hours counted from take-off to touch-down, divided by the total accumulated flight cycles as of the effective date of this AD. (2) The first repetitive inspection interval, as the total accumulated flight hours divided by the total accumulated flight cycles at the time of the inspection. (3) The second inspection interval and subsequent, as the flight hours divided by the flight cycles between the last two inspections. (m) New Requirements of This AD: Inspections and Corrective Actions (1) At the applicable time specified in paragraph (n)(1) of this AD, do a rotating probe inspection for discrepancies of the frame feet attachment holes from FR 41 through FR 46, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53- 6122, Revision 04, dated February 27, 2012. Repeat the inspections thereafter at intervals not to exceed those specified in paragraph (n)(2) of this AD. Accomplishment of this inspection terminates the inspections required by paragraph (g)(2) of this AD. (2) If any discrepancy (e.g., cracking or damage) is found during any inspection required by paragraph (m)(1) of this AD, before further flight, do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6122, Revision 04, dated February 27, 2012; except where Airbus Service Bulletin A300- 53-6122, Revision 04, dated February 27, 2012, specifies to contact Airbus, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (3) Corrective actions, as required by paragraph (m)(2) of this AD, do not constitute terminating action for the repetitive inspections required by paragraph (m)(1) of this AD. (n) Compliance Times for Initial and Repetitive Inspections (1) Do the initial rotating probe inspection required by paragraph (m)(1) of this AD at the applicable times specified in paragraphs (n)(1)(i), (n)(1)(ii), and (n)(1)(iii) of this AD; or within 1,000 flight cycles after the effective date of this AD; whichever occurs later. (i) For airplanes on which the modification specified in Airbus Service Bulletin A300-53-6125 has not been done as of the effective date of this AD: At the applicable times specified in paragraph (n)(1)(i)(A) or (n)(1)(i)(B) of this AD. (A) If the AFT is greater than 1.5 flight hours/flight cycles: Within 14,800 flight hours or 6,800 flight cycles, whichever occurs first, since the airplane's first flight. (B) If the AFT is less than or equal to 1.5 flight hours/flight cycles: Within 11,100 flight hours or 7,400 flight cycles, whichever occurs first, since the airplane's first flight. (ii) For airplanes on which the modification specified in Airbus Service Bulletin A300-53-6125 has been done as of the effective date of this AD, except as provided by paragraph (n)(1)(iii) of this AD: At the applicable times specified in paragraph (n)(1)(ii)(A) or (n)(1)(ii)(B) of this AD. (A) If the AFT is greater than 1.5 flight hours/flight cycles: Within 56,400 flight hours or 26,100 flight cycles, whichever occurs first, after doing the modification specified in Airbus Service Bulletin A300-53-6125. (B) If the AFT is less than or equal to 1.5 flight hours/flight cycles: Within 42,300 flight hours or 28,200 flight cycles, whichever occurs first, after doing the modification specified in Airbus Service Bulletin A300-53-6125. (iii) For airplanes on which the additional modification required by paragraph (p) of this AD has been done: At the applicable times in paragraph (n)(1)(iii)(A) or (n)(1)(iii)(B) of this AD. (A) If the AFT is greater than 1.5 flight hours/flight cycles: Within 69,400 flight hours or 32,100 flight cycles, whichever occurs first, after doing the modification specified in Airbus Service Bulletin A300-53-6125. (B) If the AFT is less than or equal to 1.5 flight hours/flight cycles: Within 52,000 flight hours or 34,700 flight cycles, whichever occurs first, after doing the modification specified in Airbus Service Bulletin A300-53-6125. (2) Do the repetitive rotating probe inspections required by paragraph (m)(1) of this AD at intervals not to exceed those specified in paragraph (n)(2)(i) or (n)(2)(ii) of this AD, as applicable. (i) If the AFT is greater than 1.5 flight hours/flight cycles: 7,800 flight hours or 3,600 flight cycles, whichever occurs first. (ii) If the AFT is less than or equal to 1.5 flight hours/flight cycles: 5,800 flight hours or 3,900 flight cycles, whichever occurs first. (o) New Requirement of This AD: Modification for Model A300 B4-601, A300 B4-603, A300 B4-620, A300 B4-622, A300 B4-605R, A300 B4-622R, A300 F4-605R and A300 C4-605R Variant F Airplanes (1) For Model A300 B4-601, A300 B4-603, A300 B4-620, A300 B4- 622, A300 B4-605R, A300 B4-622R, A300 F4-605R and A300 C4-605R Variant F airplanes, except those modified in production before the effective date of this AD by Airbus Modification 12168 or those on which the modification (i.e., reinforcement of the upper frame feet fittings) specified in the service information identified in paragraph (p)(1)(i), (p)(1)(ii), or (p)(1)(iii) of this AD has been done before the effective date of this AD: At the applicable time specified in paragraph (o)(1)(i) or (o)(1)(ii) of this AD: Reinforce the upper frame feet fittings, including doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6125, Revision 04, dated March 17, 2015, except where Airbus Service Bulletin A300-53-6125, Revision 04, dated March 17, 2015, specifies to contact Airbus, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. Do all applicable related investigative and corrective actions before further flight. (i) For airplanes with an AFT greater than 1.5 flight hours/ flight cycles as of the effective date of this AD: At the later of the times in paragraphs (o)(1)(i)(A) and (o)(1)(i)(B) of this AD: (A) Within 18,200 flight hours or 8,400 flight cycles, whichever occurs first, since the airplane's first flight; or (B) At the earlier of the times specified in paragraphs (o)(1)(i)(B)1 and (o)(1)(i)(B)2 of this AD. 1 Within 1,000 flight cycles after the effective date of this AD. 2 Within the compliance times specified in paragraph 1.E. (``Compliance'') of Airbus Service Bulletin A300-53-6125, Revision 01, dated June 13, 2003. For airplanes that have exceeded their design service goal, as specified in NOTE (01) of paragraph 1.E. (``Compliance'') of Airbus Service Bulletin A300-53-6125, Revision 01, dated June 13, 2003; within the earlier of the flight-cycle and flight-hour grace periods specified in Airbus Service Bulletin A300- 53-6125, Revision 01, dated June 13, 2003. (ii) For airplanes with an AFT less than or equal to 1.5 flight hours/flight cycles as of the effective date of this AD: At the later of the times in paragraphs (o)(1)(ii)(A) and (o)(1)(ii)(B) of this AD: (A) Within 13,700 flight hours or 9,100 flight cycles, whichever occurs first, since the airplane's first flight; or (B) At the earlier of the times specified in paragraphs (o)(1)(ii)(B)1 and (o)(1)(ii)(B)2 of this AD. 1 Within 1,000 flight cycles after the effective date of this AD 2 Within the compliance times specified in paragraph 1.E. (``Compliance'') of Airbus Service Bulletin A300-53-6125, Revision 01, dated June 13, 2003. For airplanes that have [[Page 5060]] exceeded their design service goal, as specified in NOTE (01) of paragraph 1.E. (``Compliance'') of Airbus Service Bulletin A300-53- 6125, Revision 01, dated June 13, 2003; within the earlier of the flight-cycle and flight-hour grace periods specified in Airbus Service Bulletin A300-53-6125, Revision 01, dated June 13, 2003. (2) For the affected Model A300 B4-600 series airplanes: Accomplishment of the modification specified in Airbus Service Bulletin A300-53-6125 before the effective date of this AD terminates the requirements of paragraphs (g), (h), and (i) of this AD. (3) For Model A300 B2 and A300 B4 series airplanes: Accomplishment of the modification specified in Airbus Service Bulletin A300-53-6125 terminates certain repetitive inspections required by AD 2007-04-11, Amendment 39-14943 (72 FR 8604, February 27, 2014), i.e., inspections of the frame feet holes for frames 41 to 46 (as specified in Airbus Service Bulletin A300-53-0345) and frames 48 to 54 (as specified in Airbus Service Bulletin A300-53- 238). However, the repetitive inspections of the frame foot angle radius (as specified in Service Bulletin A300-53-238), which are required by AD 2007-04-11, must continue. (p) New Requirement of This AD: Additional Modification for Certain Airplanes (1) For Model A300 B4-601, A300 B4-603, A300 B4-620, A300 B4- 622, A300 B4-605R, A300 B4-622R, A300 F4-605R and A300 C4-605R Variant F airplanes modified in production before the effective date of this AD by Airbus Modification 12168, or modified before the effective date of this AD by accomplishment of the reinforcement of the upper frame feet fittings specified in the service information identified in paragraph (p)(1)(i), (p)(1)(ii), or (p)(1)(iii) of this AD: Within 360 flight cycles prior to reaching the applicable compliance time specified in paragraph (p)(2)(i) or (p)(2)(ii) of this AD, contact the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA; for modification instructions and within the applicable compliance time specified in paragraph (p)(2) of this AD, do the modification using a method approved by the Manager, International Branch, ANM- 116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (i) Airbus Service Bulletin A300-53-6125, dated November 8, 2000. (ii) Airbus Service Bulletin A300-53-6125, Revision 01, dated June 13, 2003, (iii) Airbus Service Bulletin A300-53-6125, Revision 02, dated February 25, 2005. (2) Do the modification required by paragraph (p)(1) of this AD at the applicable time specified below. (i) For airplanes with an AFT greater than 1.5 flight hours/ flight cycles as of the effective date of this AD: Within 32,100 flight cycles after the modification was completed. (ii) For airplanes with an AFT less than or equal to 1.5 flight hours/flight cycles as of the effective date of this AD: Within 34,700 flight cycles after the modification was completed. (q) Modification Is Not Terminating Action Accomplishment of the modification specified in paragraph (o) or (p) of this AD does not constitute terminating action for the repetitive inspections required by paragraph (m)(1) of this AD. (r) Credit for Previous Actions (1) For Model A300 B4-600 and B4-600R series airplanes, and Model A300 C4-605R Variant F and A300 F4-605R airplanes: This paragraph provides credit for inspections and corrective actions required by paragraphs (g), (h), and (i) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraphs (r)(1)(i), (r)(1)(ii), and (r)(1)(iii) of this AD. (i) Airbus Service Bulletin A300-53-6122, Revision 01, dated September 5, 2001, which is not incorporated by reference in this AD. (ii) Airbus Service Bulletin A300-53-6122, Revision 02, dated June 17, 2002, which is not incorporated by reference in this AD. (iii) Airbus Service Bulletin A300-53-6122, Revision 03, dated August 25, 2011, which is not incorporated by reference in this AD. (2) This paragraph restates the credit for Airbus Model A300 series airplanes for previous actions as provided by Table 1 of AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004). For Airbus Model A300 series airplanes: This paragraph provides credit for actions required by paragraph (j) of this AD, if those actions were performed before January 3, 2005 (the effective date of AD 2004-23-20) using the service information specified in paragraph (r)(2)(i), (r)(2)(ii), or (r)(2)(iii) of this AD. (i) Airbus Service Bulletin A300-53-0271, dated September 10, 1991, which is not incorporated by reference in this AD. (ii) Airbus Service Bulletin A300-53-0271, Revision 01, dated February 16, 1993, which is not incorporated by reference in this AD. (iii) Airbus Service Bulletin A300-53-0271, Revision 02, dated July 13, 2000, which is not incorporated by reference in this AD. (s) 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, 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 96-13-11, Amendment 39- 9679 (61 FR 35122, July 5, 1996), and AD 2001-06-10, Amendment 39- 12157, April 2, 2001), are approved as AMOCs for the corresponding requirements 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' EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (t) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013-0295, dated December 11, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-0451. (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 January 21, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-01736 Filed 1-29-16; 8:45 am] BILLING CODE 4910-13-P
![5056
Proposed Rules Federal Register
Vol. 81, No. 20
Monday, February 1, 2016
This section of the FEDERAL REGISTER • Federal eRulemaking Portal: Go to ADDRESSES section. Include ‘‘Docket No.
contains notices to the public of the proposed http://www.regulations.gov. Follow the FAA–2016–0451; Directorate Identifier
issuance of rules and regulations. The instructions for submitting comments. 2013–NM–253–AD’’ at the beginning of
purpose of these notices is to give interested • Fax: 202–493–2251. your comments. We specifically invite
persons an opportunity to participate in the • Mail: U.S. Department of comments on the overall regulatory,
rule making prior to the adoption of the final
Transportation, Docket Operations, M– economic, environmental, and energy
rules.
30, West Building Ground Floor, Room aspects of this proposed AD. We will
W12–140, 1200 New Jersey Avenue SE., consider all comments received by the
DEPARTMENT OF TRANSPORTATION Washington, DC 20590. closing date and may amend this
• Hand Delivery: U.S. Department of proposed AD based on those comments.
Federal Aviation Administration Transportation, Docket Operations, M– We will post all comments we
30, West Building Ground Floor, Room receive, without change, to http://
14 CFR Part 39 W12–140, 1200 New Jersey Avenue SE., www.regulations.gov, including any
Washington, DC, between 9 a.m. and 5 personal information you provide. We
[Docket No. FAA–2016–0451; Directorate
Identifier 2013–NM–253–AD] p.m., Monday through Friday, except will also post a report summarizing each
Federal holidays. substantive verbal contact we receive
RIN 2120–AA64 For service information identified in about this proposed AD.
this NPRM, contact Airbus SAS,
Airworthiness Directives; Airbus Airworthiness Office—EAW, 1 Rond Discussion
Airplanes Point Maurice Bellonte, 31707 Blagnac On November 10, 2004, we issued AD
AGENCY: Federal Aviation Cedex, France; telephone +33 5 61 93 36 2004–23–20, Amendment 39–13875 (69
Administration (FAA), DOT. 96; fax +33 5 61 93 44 51; email FR 68779, November 26, 2004) for all
ACTION: Notice of proposed rulemaking account.airworth-eas@airbus.com; Airbus Model A300 series airplanes and
(NPRM). Internet http://www.airbus.com. You Model A300 B4–601, A300 B4–603,
may view this referenced service A300 B4–620, A300 B4–622, A300 B4–
SUMMARY: We propose to supersede information at the FAA, Transport 605R, A300 B4–622R, A300 F4–605R
Airworthiness Directive (AD) 2004–23– Airplane Directorate, 1601 Lind Avenue and A300 C4–605R Variant F airplanes.
20 for certain Airbus Model A300 series SW., Renton, WA. For information on (That AD superseded AD 2001–06–10,
airplanes and Model A300 B4–601, the availability of this material at the Amendment 39–12157 (66 FR 17490,
A300 B4–603, A300 B4–620, A300 B4– FAA, call 425–227–1221. April 2, 2001)). AD 2004–23–20 requires
622, A300 B4–605R, A300 B4–622R,
Examining the AD Docket actions intended to address an unsafe
A300 F4–605R, and C4–605R Variant F
condition on the products listed above.
airplanes. AD 2004–23–20 currently You may examine the AD docket on
requires, for certain airplanes, repetitive Since we issued AD 2004–23–20,
the Internet at http://
inspections for cracking around certain Amendment 39–13875 (69 FR 68779,
www.regulations.gov by searching for
attachment holes, installation of new November 26, 2004) we received a
and locating Docket No. FAA–2016–
fasteners for certain airplanes, and report indicating that a change in
0451; or in person at the Docket
follow-on corrective actions if material for manufacturing the frame
Management Facility between 9 a.m.
necessary. AD 2004–23–20 also requires feet for certain airplanes negatively
and 5 p.m., Monday through Friday,
modifying certain fuselage frames, impacted the fatigue life of the frame
except Federal holidays. The AD docket
which terminates certain repetitive feet.
contains this proposed AD, the
inspections. Since we issued AD 2004– regulatory evaluation, any comments The European Aviation Safety Agency
23–20, we received a report indicating received, and other information. The (EASA), which is the Technical Agent
that the material used to manufacture street address for the Docket Operations for the Member States of the European
the upper frame feet was changed and office (telephone 800–647–5527) is in Union, has issued EASA Airworthiness
negatively affected the fatigue life of the the ADDRESSES section. Comments will Directive 2013–0295, dated December
frame feet. This proposed AD would be available in the AD docket shortly 11, 2013 (referred to after this as the
reduce the compliance times for the after receipt. Mandatory Continuing Airworthiness
initial inspection and the inspection Information, or ‘‘the MCAI’’), to correct
FOR FURTHER INFORMATION CONTACT: Dan
intervals. This proposed AD would also an unsafe condition for Airbus Model
Rodina, Aerospace Engineer,
expand the applicability and require an A300 B4–601, A300 B4–603, A300 B4–
International Branch, ANM 116,
additional repair on certain airplanes 620, A300 B4–622, A300 B4–605R,
Transport Airplane Directorate, 1601
that have been modified. We are A300 B4–622R, A300 F4–605R, and
Lind Avenue SW., Renton, WA 98057–
proposing this AD to prevent cracking of A300 C4–605R Variant F airplanes. The
3356; telephone 425–227–2125; fax
the center section of the fuselage, which MCAI states:
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425–227–1149.
could result in a ruptured frame foot During a scheduled inspection of the
SUPPLEMENTARY INFORMATION:
and reduced structural integrity of the fuselage frame feet of an in-service A300–600
airplane. Comments Invited aeroplane, cracks were observed in Frame
(FR) 43, FR 44, FR 45 and FR 46 between
DATES: We must receive comments on We invite you to send any written stringer (STGR) 24 and STGR 30.
this proposed AD by March 17, 2016. relevant data, views, or arguments about This condition, if not detected and
ADDRESSES: You may send comments by this proposed AD. Send your comments corrected, could affect the structural integrity
any of the following methods: to an address listed under the of the aeroplane.
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![Federal Register / Vol. 81, No. 20 / Monday, February 1, 2016 / Proposed Rules 5057
To address this unsafe condition, In addition, Airbus has issued Service We have also moved the service
[Direction Generale de l’Aviation Civile] Bulletin A300–53–6125, Revision 01, information acceptable for compliance if
DGAC France issued [an] AD * * * to dated June 13, 2003. The service previously done from ‘‘TABLE 1.—
require repetitive inspections of the affected information provides compliance times SERVICE INFORMATION’’ in AD 2004–
frames and stringers on both sides of the
fuselage and, depending on findings, repairs,
for certain airplanes to do the proposed 23–20, Amendment 39–13875 (69 FR
as specified in Airbus Service Bulletin (SB) modification. 68779, November 26, 2004) to paragraph
A300–53–6122. Airbus has also issued Service (r)(2) of this proposed AD.
Subsequently, DGAC France issued AD F– Bulletin A300–53–6125, Revision 04,
dated March 17, 2015. The service Costs of Compliance
2004–002 [http://ad.easa.europa.eu/ad/F-
2004-002] (EASA approval 2003–2108) information describes procedures for the We estimate that this proposed AD
[which corresponds to FAA AD 2004–23–20, modification of certain upper frame feet affects 65 airplanes of U.S. registry.
Amendment 39–13875 (69 FR 68779, fittings. The actions that are required by AD
November 26, 2004)], retaining the This service information is reasonably 2004–23–20, Amendment 39–13875 (69
requirements of [an] AD * * * and required available because the interested parties FR 68779, November 26, 2004), and
the embodiment of Airbus SB A300–53–6125 have access to it through their normal retained in this proposed AD take about
(Airbus modification 12168) in order to
course of business or by the means 90 work-hours per product, at an
improve the life of the frame foot attachment.
Since DGAC France AD F–2004–002 was
identified in the ADDRESSES section. average labor rate of $85 per work-hour.
issued, a fleet survey and updated Fatigue FAA’s Determination and Requirements Required parts cost about $4,000 per
and Damage Tolerance analyses were of This Proposed AD product. Based on these figures, the
performed in order to substantiate the second estimated cost of the actions that were
A300–600 Extended Service Goal (ESG2) This product has been approved by required by AD 2004–23–20 is $11,650
exercise. the aviation authority of another per product.
It was highlighted that the frame feet country, and is approved for operation We also estimate that it would take up
material change from 2024T3511 (A300B4) to in the United States. Pursuant to our to 109 work-hours per product to
7175T7351 (A300–600) had an impact on the bilateral agreement with the State of comply with the basic requirements of
frame feet fatigue life duration. Airbus SB Design Authority, we have been notified
A300–53–6122 was revised accordingly to
this proposed AD. The average labor
of the unsafe condition described in the rate is $85 per work-hour. Required
decrease the inspection thresholds and
MCAI and service information parts would cost up to $6,070 per
intervals. Subsequent SB revision introduced
a second structural modification point referenced above. We are proposing this product. Based on these figures, we
(SMP2) for aeroplanes that embody Airbus AD because we evaluated all pertinent estimate the cost of this proposed AD on
SB A300–53–6125 (modification 12168). information and determined an unsafe U.S. operators to be $996,775, or
For the reasons described above, this new condition exists and is likely to exist or $15,335 per product.
[EASA] AD retains the requirements of DGAC develop on other products of the same We have received no definitive data
France AD F–2004–002, which is type design. that would enable us to provide cost
superseded, but requires those actions within
Changes to AD 2004–23–20, estimates for the on-condition actions
the new thresholds and intervals as specified
in Revision 04 of Airbus SB A300–53–6122. Amendment 39–13875 (69 FR 68779, specified in this proposed AD.
November 26, 2004) Authority for This Rulemaking
The retained requirements include
rototest inspections for cracking in the This proposed AD would retain all Title 49 of the United States Code
area surrounding the frame feet requirements of AD 2004–23–20, specifies the FAA’s authority to issue
attachment holes between fuselage FR Amendment 39–13875 (69 FR 68779, rules on aviation safety. Subtitle I,
41 and FR 46 from stringers 24 to 28 on November 26, 2004). Since AD 2004– section 106, describes the authority of
the left and right sides, and related 23–20 was issued the AD format has the FAA Administrator. ‘‘Subtitle VII:
investigative and corrective action if been revised, and certain paragraphs Aviation Programs,’’ describes in more
necessary. The related investigative have been rearranged. As a result, the detail the scope of the Agency’s
actions include additional rotating corresponding paragraph designators authority.
probe inspections of the adjacent holes. have changed in this proposed AD, as We are issuing this rulemaking under
The corrective actions include reaming listed in the following table: the authority described in ‘‘Subtitle VII,
out cracks, cold working fastener holes, Part A, Subpart III, Section 44701:
and installing oversized fasteners, or REVISED PARAGRAPH DESIGNATORS General requirements.’’ Under that
repair. This proposed AD also expands section, Congress charges the FAA with
the applicability to include airplanes on Requirement in promoting safe flight of civil aircraft in
AD 2004–23–20, Corresponding
which Airbus Modification 12168 was Amendment requirement in air commerce by prescribing regulations
done. You may examine the MCAI in 39–13875 this proposed for practices, methods, and procedures
the AD docket on the Internet at (69 FR 68779, AD the Administrator finds necessary for
http://www.regulations.gov by searching November 26, 2004) safety in air commerce. This regulation
for and locating Docket No. FAA–2016– paragraph (f) paragraph (g). is within the scope of that authority
0451. paragraph (g) paragraph (h). because it addresses an unsafe condition
paragraph (h) paragraph (i). that is likely to exist or develop on
Related Service Information Under 1
paragraph (i) paragraph (j). products identified in this rulemaking
CFR Part 51 paragraph (j) paragraph (k). action.
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Airbus has issued Service Bulletin
A300–53–6122, Revision 04, dated We have converted ‘‘TABLE 1.— Regulatory Findings
February 27, 2012. The service SERVICE INFORMATION’’ in AD 2004– We determined that this proposed AD
information describes procedures for the 23–20, Amendment 39–13875 (69 FR would not have federalism implications
repetitive inspections of certain frame 68779, November 26, 2004) to text in under Executive Order 13132. This
feet attachment holes for cracks, paragraphs (j)(3)(i) and (j)(3)(ii) of this proposed AD would not have a
installation of new fasteners, and repair proposed AD for formatting purposes substantial direct effect on the States, on
of cracked areas. only. the relationship between the national
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![5058 Federal Register / Vol. 81, No. 20 / Monday, February 1, 2016 / Proposed Rules
Government and the States, or on the manufacture the upper frame feet was (h) Retained Installation of Fasteners and
distribution of power and changed and negatively affected the fatigue Repetitive Inspections
responsibilities among the various life of the frame feet. We are issuing this AD This paragraph restates the requirements of
levels of government. to prevent cracking of the center section of paragraph (g) of AD 2004–23–20,
the fuselage, which could result in a ruptured Amendment 39–13875 (69 FR 68779,
For the reasons discussed above, I frame foot and reduced structural integrity of
certify this proposed regulation: November 26, 2004), with revised service
the airplane. information. For airplanes on which no
1. Is not a ‘‘significant regulatory
(f) Compliance cracking is detected during the inspection
action’’ under Executive Order 12866; required by paragraph (g) of this AD, prior to
2. Is not a ‘‘significant rule’’ under the Comply with this AD within the further flight, install new fasteners as
DOT Regulatory Policies and Procedures compliance times specified, unless already applicable, in accordance with Airbus
(44 FR 11034, February 26, 1979); done. Service Bulletin A300–53–6122, dated
3. Will not affect intrastate aviation in (g) Retained Inspections February 9, 2000; or the Accomplishment
Alaska; and Instructions of Airbus Service Bulletin A300–
This paragraph restates the requirements of 53–6122, Revision 04, dated February 27,
4. Will not have a significant paragraph (f) of AD 2004–23–20, Amendment 2012; and repeat the inspection required by
economic impact, positive or negative, 39–13875 (69 FR 68779, November 26, 2004), paragraph (g) of this AD thereafter at
on a substantial number of small entities with revised service information. For Model intervals not to exceed the applicable
under the criteria of the Regulatory A300 B4–600 and A300 B4–600R series intervals specified in paragraph 1.E.
Flexibility Act. airplanes, and Model A300 C4–605R Variant (‘‘Compliance’’) of Airbus Service Bulletin
F and A300 F4–605R airplanes, except those A300–53–6122, dated February 9, 2000; until
List of Subjects in 14 CFR Part 39 airplanes modified by Airbus Modification the actions required by paragraph (j) or (o) of
Air transportation, Aircraft, Aviation 12168: Perform a high-frequency eddy- this AD have been done or the initial
safety, Incorporation by reference, current or rototest inspection to detect inspection required by paragraph (m) of this
Safety. cracking in the area surrounding the frame AD is done.
feet attachment holes between fuselage
frames (FR) 41 and FR 46 from stringers 24 (i) Retained Corrective Actions
The Proposed Amendment
to 28, left-and right-hand sides, in This paragraph restates the requirements of
Accordingly, under the authority accordance with Airbus Service Bulletin paragraph (h) of AD 2004–23–20,
delegated to me by the Administrator, A300–53–6122, dated February 9, 2000; or Amendment 39–13875 (69 FR 68779,
the FAA proposes to amend 14 CFR part the Accomplishment Instructions of Airbus November 26, 2004), with revised service
39 as follows: Service Bulletin A300–53–6122, Revision 04, information. For airplanes on which cracking
dated February 27, 2012; at the applicable is detected during any inspection required by
PART 39—AIRWORTHINESS time specified in paragraph (g)(1) or (g)(2) of paragraph (g) of this AD: Prior to further
DIRECTIVES this AD. Accomplishing an inspection flight, except as required by paragraph (k) of
required by paragraph (m) of this AD this AD, accomplish corrective actions (e.g.,
■ 1. The authority citation for part 39 terminates the inspections required by this performing rotating probe inspections,
paragraph. reaming out cracks, cold working fastener
continues to read as follows:
(1) For airplanes on which Task 53–15–54 holes, and installing oversized fasteners) in
Authority: 49 U.S.C. 106(g), 40113, 44701. in Maintenance Review Board Document accordance with Airbus Service Bulletin
(MRBD), Revision 3, dated April 1998, has A300–53–6122, dated February 9, 2000; or
§ 39.13 [Amended] the Accomplishment Instructions of Airbus
not been accomplished as of May 7, 2001 (the
■ 2. The FAA amends § 39.13 by effective date of AD 2001–06–10, Service Bulletin A300–53–6122, Revision 04,
removing Airworthiness Directive (AD) dated February 27, 2012. Repeat the
Amendment 39–12157 (66 FR 17490, April 2,
2004–23–20, Amendment 39–13875 (69 inspection required by paragraph (g) of this
2001)): Perform the inspection at the later of
AD thereafter at intervals not to exceed the
FR 68779, November 26, 2004), and the times specified in paragraphs (g)(1)(i) and
applicable intervals specified in paragraph
adding the following new AD: (g)(1)(ii) of this AD.
1.E. (‘‘Compliance’’) of Airbus Service
(i) Prior to the accumulation of the total Bulletin A300–53–6122, dated February 9,
Airbus: Docket No. FAA–2016–0451;
flight-cycle or flight-hour threshold, 2000; until the actions required by paragraph
Directorate Identifier 2013–NM–253–AD.
whichever occurs first, specified in (j) or (o) of this AD have been done, or the
(a) Comments Due Date paragraph 1.E. (‘‘Compliance’’) of Airbus initial inspection required by paragraph (m)
Service Bulletin A300–53–6122, dated of this AD is done.
We must receive comments by March 17,
February 9, 2000; or
2016.
(ii) Within the applicable grace period (j) Retained Modification: Model A300 Series
(b) Affected ADs specified in paragraph 1.E. (‘‘Compliance’’) of Airplanes
This AD replaces AD 2004–23–20, Airbus Service Bulletin A300–53–6122, This paragraph restates the requirements of
Amendment 39–13875 (69 FR 68779, dated February 9, 2000. paragraph (i) of AD 2004–23–20, Amendment
November 26, 2004). (2) For airplanes on which Task 53–15–54 39–13875 (69 FR 68779, November 26, 2004),
in the MRBD, Revision 3, dated April 1998, for certain airplanes, with no changes. For
(c) Applicability has been accomplished as of May 7, 2001 (the Model A300 series airplanes: Within the
This AD applies to Airbus Model A300 B2– effective date of AD 2001–06–10, compliance times specified in paragraph 1.E.
1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, Amendment 39–12157 (66 FR 17490, April 2, (‘‘Compliance’’) of Airbus Service Bulletin
and B4–203 airplanes; and Model A300 B4– 2001)): Perform the next repetitive inspection A300–53–0271, Revision 03, dated June 13,
601, A300 B4–603, A300 B4–620, A300 B4– at the later of the times specified in 2003, modify the fuselage frames, in
622, A300 B4–605R, A300 B4–622R, A300 paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. accordance with the Accomplishment
F4–605R and A300 C4–605R Variant F (i) Within the flight-cycle or flight-hour Instructions of Airbus Service Bulletin A300–
airplanes; certificated in any category, all interval, whichever occurs first, specified in 53–0271, Revision 03, dated June 13, 2003.
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manufacturer serial numbers. paragraph 1.E. (‘‘Compliance’’) of Airbus For airplanes that have exceeded their design
Service Bulletin A300–53–6122, dated service goal, as specified in NOTE (01) of
(d) Subject February 9, 2000, following the latest paragraph 1.E. (‘‘Compliance’’) of Airbus
Air Transport Association (ATA) of inspection accomplished as specified in Service Bulletin A300–53–0271, Revision 03,
America Code 53, Fuselage. MRBD, Revision 3, dated April 1998; or dated June 13, 2003; this AD requires
(ii) Within the grace period specified in compliance within the earlier of the flight-
(e) Reason paragraph 1.E. (‘‘Compliance’’) of Airbus cycle and flight-hour grace periods specified
This AD was prompted by a report Service Bulletin A300–53–6122, dated in Airbus Service Bulletin A300–53–0271,
indicating that the material used to February 9, 2000. Revision 03, dated June 13, 2003.
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exceeded their design service goal, as does not constitute terminating action for the 35122, July 5, 1996), and AD 2001–06–10,
specified in NOTE (01) of paragraph 1.E. repetitive inspections required by paragraph Amendment 39–12157, April 2, 2001), are
(‘‘Compliance’’) of Airbus Service Bulletin (m)(1) of this AD. approved as AMOCs for the corresponding
A300–53–6125, Revision 01, dated June 13, requirements of this AD.
(r) Credit for Previous Actions (2) Contacting the Manufacturer: As of the
2003; within the earlier of the flight-cycle
and flight-hour grace periods specified in (1) For Model A300 B4–600 and B4–600R effective date of this AD, for any requirement
Airbus Service Bulletin A300–53–6125, series airplanes, and Model A300 C4–605R in this AD to obtain corrective actions from
Revision 01, dated June 13, 2003. Variant F and A300 F4–605R airplanes: This a manufacturer, the action must be
(2) For the affected Model A300 B4–600 paragraph provides credit for inspections and accomplished using a method approved by
series airplanes: Accomplishment of the corrective actions required by paragraphs (g), the Manager, International Branch, ANM–
modification specified in Airbus Service (h), and (i) of this AD, if those actions were 116, Transport Airplane Directorate, FAA; or
Bulletin A300–53–6125 before the effective performed before the effective date of this AD EASA; or Airbus’ EASA DOA. If approved by
date of this AD terminates the requirements using the applicable service information the DOA, the approval must include the
of paragraphs (g), (h), and (i) of this AD. specified in paragraphs (r)(1)(i), (r)(1)(ii), and DOA-authorized signature.
(3) For Model A300 B2 and A300 B4 series (r)(1)(iii) of this AD.
(i) Airbus Service Bulletin A300–53–6122, (t) Related Information
airplanes: Accomplishment of the
modification specified in Airbus Service Revision 01, dated September 5, 2001, which (1) Refer to Mandatory Continuing
Bulletin A300–53–6125 terminates certain is not incorporated by reference in this AD. Airworthiness Information (MCAI) EASA
repetitive inspections required by AD 2007– (ii) Airbus Service Bulletin A300–53–6122, Airworthiness Directive 2013–0295, dated
04–11, Amendment 39–14943 (72 FR 8604, Revision 02, dated June 17, 2002, which is December 11, 2013, for related information.
February 27, 2014), i.e., inspections of the not incorporated by reference in this AD. This MCAI may be found in the AD docket
frame feet holes for frames 41 to 46 (as (iii) Airbus Service Bulletin A300–53– on the Internet at http://www.regulations.gov
specified in Airbus Service Bulletin A300– 6122, Revision 03, dated August 25, 2011, by searching for and locating Docket No.
53–0345) and frames 48 to 54 (as specified which is not incorporated by reference in this FAA–2016–0451.
in Airbus Service Bulletin A300–53–238). AD. (2) For service information identified in
However, the repetitive inspections of the (2) This paragraph restates the credit for this AD, contact Airbus SAS, Airworthiness
frame foot angle radius (as specified in Airbus Model A300 series airplanes for Office—EAW, 1 Rond Point Maurice
Service Bulletin A300–53–238), which are previous actions as provided by Table 1 of Bellonte, 31707 Blagnac Cedex, France;
required by AD 2007–04–11, must continue. AD 2004–23–20, Amendment 39–13875 (69 telephone +33 5 61 93 36 96; fax +33 5 61
FR 68779, November 26, 2004). For Airbus 93 44 51; email account.airworth-eas@
(p) New Requirement of This AD: Additional Model A300 series airplanes: This paragraph airbus.com; Internet http://www.airbus.com.
Modification for Certain Airplanes provides credit for actions required by You may view this service information at the
(1) For Model A300 B4–601, A300 B4–603, paragraph (j) of this AD, if those actions were FAA, Transport Airplane Directorate, 1601
A300 B4–620, A300 B4–622, A300 B4–605R, performed before January 3, 2005 (the Lind Avenue SW., Renton, WA. For
A300 B4–622R, A300 F4–605R and A300 C4– effective date of AD 2004–23–20) using the information on the availability of this
605R Variant F airplanes modified in service information specified in paragraph material at the FAA, call 425–227–1221.
production before the effective date of this (r)(2)(i), (r)(2)(ii), or (r)(2)(iii) of this AD. Issued in Renton, Washington, on January
AD by Airbus Modification 12168, or (i) Airbus Service Bulletin A300–53–0271, 21, 2016.
modified before the effective date of this AD dated September 10, 1991, which is not
by accomplishment of the reinforcement of incorporated by reference in this AD. Michael Kaszycki,
the upper frame feet fittings specified in the (ii) Airbus Service Bulletin A300–53–0271, Acting Manager, Transport Airplane
service information identified in paragraph Revision 01, dated February 16, 1993, which Directorate, Aircraft Certification Service.
(p)(1)(i), (p)(1)(ii), or (p)(1)(iii) of this AD: is not incorporated by reference in this AD. [FR Doc. 2016–01736 Filed 1–29–16; 8:45 am]
Within 360 flight cycles prior to reaching the (iii) Airbus Service Bulletin A300–53– BILLING CODE 4910–13–P
applicable compliance time specified in 0271, Revision 02, dated July 13, 2000, which
paragraph (p)(2)(i) or (p)(2)(ii) of this AD, is not incorporated by reference in this AD.
contact the Manager, International Branch,
(s) Other FAA AD Provisions DEPARTMENT OF THE TREASURY
ANM–116, Transport Airplane Directorate,
FAA; or EASA; or Airbus’s EASA DOA; for The following provisions also apply to this
modification instructions and within the AD: Internal Revenue Service
applicable compliance time specified in (1) Alternative Methods of Compliance
paragraph (p)(2) of this AD, do the (AMOCs): The Manager, International 26 CFR Part 1
modification using a method approved by the Branch, ANM–116, Transport Airplane
Manager, International Branch, ANM–116, Directorate, FAA, has the authority to [REG–139483–13]
Transport Airplane Directorate, FAA; or approve AMOCs for this AD, if requested
RIN 1545–BL87
EASA; or Airbus’s EASA DOA. using the procedures found in 14 CFR 39.19.
(i) Airbus Service Bulletin A300–53–6125, In accordance with 14 CFR 39.19, send your
Treatment of Certain Transfers of
dated November 8, 2000. request to your principal inspector or local
Flight Standards District Office, as Property of Foreign Corporations;
(ii) Airbus Service Bulletin A300–53–6125,
Revision 01, dated June 13, 2003, appropriate. If sending information directly Hearing Correction
(iii) Airbus Service Bulletin A300–53– to the International Branch, send it to ATTN: AGENCY: Internal Revenue Service (IRS),
6125, Revision 02, dated February 25, 2005. Dan Rodina, Aerospace Engineer,
International Branch, ANM 116, Transport Treasury.
(2) Do the modification required by
paragraph (p)(1) of this AD at the applicable Airplane Directorate, 1601 Lind Avenue SW., ACTION: Correction to a notice of public
time specified below. Renton, WA 98057–3356; telephone 425– hearing on proposed rulemaking.
(i) For airplanes with an AFT greater than 227–2125; fax 425–227–1149. Information
1.5 flight hours/flight cycles as of the may be emailed to: 9-ANM-116-AMOC- SUMMARY: This document corrects a
effective date of this AD: Within 32,100 flight REQUESTS@faa.gov. notice of public hearing on proposed
rmajette on DSK2TPTVN1PROD with PROPOSALS
cycles after the modification was completed. (i) Before using any approved AMOC, regulations that published in the
(ii) For airplanes with an AFT less than or notify your appropriate principal inspector, Federal Register on January 20, 2016, at
equal to 1.5 flight hours/flight cycles as of the or lacking a principal inspector, the manager 81 FR 3069.
effective date of this AD: Within 34,700 flight of the local flight standards district office/
DATES: The public hearing is being held
cycles after the modification was completed. certificate holding district office. The AMOC
approval letter must specifically reference on Monday, February 8, 2016 at 10 a.m.
(q) Modification Is Not Terminating Action this AD. The IRS must now receive outlines of
Accomplishment of the modification (ii) AMOCs approved previously for AD the topics to be discussed at the public
specified in paragraph (o) or (p) of this AD 96–13–11, Amendment 39–9679 (61 FR hearing by Thursday, February 4, 2016.
VerDate Sep<11>2014 13:21 Jan 29, 2016 Jkt 238001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 E:\FR\FM\01FEP1.SGM 01FEP1](https://thefederalregister.org/doc/81_FR_5076/page/5.svg)
Document Created: 2016-01-30 01:17:13
Document Modified: 2016-01-30 01:17:13
| 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 March 17, 2016. | |
| Contact | Dan Rodina, Aerospace Engineer, International Branch, ANM 116, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. | |
| FR Citation | 81 FR 5056 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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