81 FR 74354 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 207 (October 26, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 207 (October 26, 2016)
| Page Range | 74354-74358 | |
| FR Document | 2016-25662 |
[Federal Register Volume 81, Number 207 (Wednesday, October 26, 2016)] [Proposed Rules] [Pages 74354-74358] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-25662] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9298; Directorate Identifier 2015-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 adopt a new airworthiness directive (AD) for all Airbus Model A300 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) that indicates a section of the wing and aft fuselage is subject to widespread fatigue damage (WFD). This proposed AD would require an inspection to determine if certain modifications have been done. For airplanes on which the specified modifications have not been done, this proposed AD would require accomplishing those modifications, including doing related investigative and corrective actions if necessary. We are proposing this AD to prevent reduced structural integrity of these airplanes due to the failure of certain structural components. DATES: We must receive comments on this proposed AD by December 12, 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 NRPM, 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. 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- 9298; 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: [[Page 74355]] 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-2016-9298; Directorate Identifier 2015-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 Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple- site-damage and multiple-element-damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane, in a condition known as WFD. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all transport category airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive AD 2015-0173, dated August 24, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A300 series airplanes. The MCAI states: A widespread fatigue damage (WFD) analysis conducted on A300 aeroplanes identified areas which are susceptible to crack development. This condition, if not corrected, could affect the structural integrity of the aeroplane. To address this issue, Airbus developed a modification (mod) to reinforce the structure of the aeroplane. Airbus issued Service Bulletin (SB) A300-53-0271 to provide instructions for a cold expansion of the foot attachment holes of certain fuselage frames, and DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD F-2004-001 to require this mod [which corresponds with certain requirements in FAA AD 2004-23- 20, Amendment 39-13875 (69 FR 68779, November 26, 2004)]. Since that [DGAC] AD was issued, Airbus released twelve other mods with corresponding SBs, to complete the set of inspections and repairs in the frame of the A300 WFD campaign. EASA issued AD 2015- 0115 to require ten of these mods through section 3 of ALS [Airworthiness Limitations Section] Part 2, and decision is made to delete section 3 from ALS Part 2. For the reasons described above, this [EASA] AD retains the requirements of DGAC France AD F-2004-001, which is superseded, and requires implementation of the additional inspection, modification and/or repair actions, as applicable to aeroplane model. Required actions include an inspection to determine if certain modifications have been done. For airplanes on which the specified modifications have not been done, this proposed AD would require accomplishing those modifications, including doing related investigative and corrective actions if necessary. Depending on airplane configuration, the compliance times for modifying the airplane structure range between 13,300 flight cycles and 48,000 flight cycles since first flight of the airplane,. 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-2016-9298. Related Service Information Under 1 CFR Part 51 Airbus issued the following service information: Airbus Service Bulletin A300-53-0239, Revision 02, dated March 6, 2000. This service information describes procedures to modify the longitudinal junction. The modification includes the addition of external doublers and installation of interference fit attachments and related investigative and corrective actions. The related investigative actions are rotary probe inspections for cracking of the fastener holes. The corrective action is repair. Airbus Service Bulletin A300-53-0247, Revision 02, dated July 20, 1990. This service information describes procedures to modify the fuselage upper door frame structure, which consists of eddy current inspections of certain structure for cracks, and structural modification or repair. Airbus Mandatory Service Bulletin A300-53-0271, Revision 05, dated June 21, 2013. This service information describes procedures to modify the fuselage frame (FR), which includes cold expansion of the fastener holes between FR 41 and FR 54, and related investigative and corrective actions. The related investigative actions including rotary probe inspections for cracking of the fastener holes. The corrective action is repair. Airbus Mandatory Service Bulletin A300-53-0366, dated April 7, 2005. This service information describes procedures to modify the fuselage [[Page 74356]] frame, which includes installing an additional external doubler on the fuselage lap joint at fuselage stringers (STGR) 22, left and right, between FR 26 and FR 40. Airbus Service Bulletin A300-53-0368, dated April 7, 2005. This service information describes procedures to modify the rear fuselage, which includes installing an additional external doubler on the fuselage lap joint at STGR 51, left and right, between FR 72 and FR 80. Airbus Mandatory Service Bulletin A300-53-0369, Revision 03, dated September 1, 2010. This service information describes procedures to modify the rear fuselage, which includes reinforcing the butt joint at FR 72 by installation of an additional external doubler at the butt joint of FR 72 at STGR 14, left and right. Airbus Mandatory Service Bulletin A300-53-0373, Revision 03, dated September 1, 2010. This service information describes procedures to modify the rear fuselage, which includes reinforcing the butt joint at FR 65 by installation of an additional external doubler at the butt joint of FR 65 between STGR 13 left and right. Airbus Mandatory Service Bulletin A300-53-0374, Revision 04, dated July 5, 2013. This service information describes procedures to modify the rear fuselage, which includes reinforcing the butt joints at FR 55 and FR 58 by installation of additional external doublers without cutout at certain butt joints. Airbus Mandatory Service Bulletin A300-53-0375, Revision 01, dated June 24, 2013. This service information describes procedures to modify the forward fuselage, which includes reinforcing the fuselage circumferential butt joint at FR 26 by installation of an additional external doubler at the butt joint of FR 26 between STGR 13 left and STGR 13 right. Airbus Mandatory Service Bulletin A300-53-0393, dated September 27, 2013. This service information describes procedures to modify the fuselage frame which includes reinforcing the longitudinal butt joints with additional butt straps at certain fuselage frames and stringers. Airbus Mandatory Service Bulletin A300-57-0203, Revision 04, dated February 18, 2015. This service information describes procedures to modify the outer wing, which includes removal of the wing stringer and run-out plate at STGR 19 on the bottom wing skin; replacement of the taper-lok bolts with interference fit parallel bolts; and related investigative and corrective actions. Related investigative actions include detailed visual and high frequency eddy current (HFEC) inspections for cracks and damage in the stringer run- outs; and eddy current inspections for cracks initiating from certain fastener holes. Corrective actions include repair. Airbus Mandatory Service Bulletin A300-57-0258, dated September 30, 2014. This service information describes procedures to modify the wing structure, which includes a first oversize of the critical holes on certain wing stringers, and related investigative and corrective actions. Related investigated actions include detailed visual inspections for damage of the top wing skin external surface and the stringer joint; and roto-probe inspections for damage of the fastener holes. Corrective actions include repair. Airbus Mandatory Service Bulletin A300-57-0259, dated September 30, 2014. This service information describes procedures to modify the wing structure, which includes a first oversize of the critical holes on certain wing stringers, and related investigative and corrective actions. Related investigated actions include detailed visual inspections for damage of the top wing skin external surface and the stringer joint; and roto-probe inspections for damage of the fastener holes. Corrective actions include 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. 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. Costs of Compliance We estimate that this proposed AD affects 8 airplanes of U.S. registry. We also estimate that it will take about 3,291 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 about $142,845 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $3,380,640, or $422,580 per product. In addition, we estimate that any necessary follow-on actions would take about 15 work-hours and require parts costing $10,000, for a cost of $11,275 per product. We have no way of determining the number of aircraft that might need this action. 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. 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, [[Page 74357]] 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 adding the following new Airworthiness Directive (AD): Airbus: Docket No. FAA-2016-9298; Directorate Identifier 2015-NM- 161-AD. (a) Comments Due Date We must receive comments by December 12, 2016. (b) Affected ADs This AD affects AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004) (``AD 2004-23-20''). (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, 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 an evaluation by the design approval holder (DAH) that indicates a section of the wing and aft fuselage is subject to widespread fatigue damage (WFD). We are issuing this AD to prevent reduced structural integrity of these airplanes due to the failure of certain structural components. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Verification of Embodied Modifications Within 4 months after the effective date of this AD, verify whether the Airbus modifications listed in table 1 to paragraphs (g), (h), and (i) of this AD, as applicable to airplane model, have been embodied on the airplane in accordance with the Accomplishment Instructions of the applicable Airbus service bulletin listed in table 1 to paragraphs (g), (h), and (i) of this AD. A review of the airplane maintenance records is acceptable to accomplish the verification required by this paragraph, provided those records can conclusively determine whether the modifications have been embodied. Table 1 to Paragraphs (g), (h), and (i) of This AD--Airbus Modification and Applicable Service Bulletin ------------------------------------------------------------------------ Airbus Applicable airbus Set modification service bulletin ------------------------------------------------------------------------ Set 1A........................ 751.............. A300-53-0247, Revision 02, dated July 20, 1990. 7301............. A300-53-0239, Revision 02, dated March 6, 2000. 10326............ A300-57-0203, Revision 04, dated February 18, 2015. 12735............ A300-53-0366, dated April 7, 2005. 12736............ A300-53-0368, dated April 7, 2005. 12737............ A300-53-0369, Revision 03, dated September 1, 2010. 12798............ A300-53-0375, Revision 01, dated June 24, 2013. 07757 and 12977.. A300-53-0271, Revision 05, dated June 21, 2013. 13611............ A300-57-0258, dated September 30, 2014. 13692............ A300-53-0393, dated September 27, 2013. 13716............ A300-57-0259, dated September 30, 2014. Set 1B........................ 12794............ A300-53-0374, Revision 04, dated July 5, 2013. 12796............ A300-53-0373, Revision 03, dated September 1, 2010. ------------------------------------------------------------------------ (h) Corrective Actions for Modifications Which Have Not Been Embodied If, during the verification required by paragraph (g) of this AD, it is determined that any modification has not been embodied, do the applicable actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD. (1) If it is determined that any Airbus modification, specified in the applicable Airbus Service Bulletin, identified in ``Set 1A'' of table 1 to paragraphs (g), (h), and (i) of this AD is not embodied: Within the applicable compliance time specified in the applicable Airbus Service Bulletin identified in ``Set 1A'' of table 1 to paragraphs (g), (h), and (i) of this AD, or within 4 months after the effective date of this AD, whichever occurs later, do the applicable actions specified in paragraphs (h)(1)(i) through (h)(1)(xi) of this AD, except as required by paragraph (i) of this AD. Do all applicable related investigative and corrective actions before further flight. (i) For airplanes on which Airbus Service Bulletin A300-53-0239, Revision 02, dated March 6, 2000, has not been embodied: Modify the longitudinal junction and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-0239, Revision 02, dated March 6, 2000. (ii) For airplanes on which Airbus Service Bulletin A300-53- 0247, Revision 02, dated July 20, 1990, has not been embodied: Modify the fuselage upper door frame structure by doing eddy current inspections for cracks of the structure specified in Airbus Service Bulletin A300-53-0247, Revision 02, dated July 20, 1990, and a structural modification or repair, as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53- 0247, Revision 02, dated July 20, 1990. (iii) For airplanes on which Airbus Mandatory Service Bulletin A300-53-0271, Revision 05, dated June 21, 2013, has not been embodied: Modify the fuselage frame, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0271, Revision 05, dated June 21, 2013. (iv) For airplanes on which Airbus Mandatory Service Bulletin A300-53-0366, dated April 7, 2005, has not been embodied: Modify the fuselage frame, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0366, dated April 7, 2005. (v) For airplanes on which Airbus Service Bulletin A300-53-0368, dated April 7, 2005, has not been embodied: Modify the rear fuselage, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0366, dated April 7, 2005. (vi) For airplanes on which Airbus Mandatory Service Bulletin A300-53-0369, Revision 03, dated September 1, 2010, has not been embodied: Modify the rear fuselage, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0369, Revision 03, dated September 1, 2010. (vii) For airplanes on which Airbus Mandatory Service Bulletin A300-53-0375, Revision 01, dated June 24, 2013, has not been embodied: Modify the forward fuselage, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0375, Revision 01, dated June 24, 2013. (viii) For airplanes on which Airbus Mandatory Service Bulletin A300-53-0393, dated September 27, 2013, has not been embodied: Modify the fuselage frame, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0393, dated September 27, 2013. (ix) For airplanes on which Airbus Mandatory Service Bulletin A300-57-0203, Revision 04, dated February 18, 2015, has not [[Page 74358]] been embodied: Modify the outer wing, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-57-0203, Revision 04, dated February 18, 2015. (x) For airplanes on which Airbus Mandatory Service Bulletin A300-57-0258, dated September 30, 2014, has not been embodied: Modify the wing structure and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-57-0258, dated September 30, 2014. (xi) For airplanes on which Airbus Mandatory Service Bulletin A300-57-0259, dated September 30, 2014, has not been embodied: Modify the wing structure, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-57-0259, dated September 30, 2014. (2) If it is determined that Airbus Service Bulletin A300-53- 0374, Revision 04, dated July 5, 2013 (mod 12794) has not been embodied: Within the compliance time specified in paragraphs (h)(2)(i), (h)(2)(ii), (h)(2)(iii), and (h)(2)(iv) of this AD, as applicable, modify the rear fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-0374, Revision 04, dated July 5, 2013, except as required by paragraph (i) of this AD. (i) For Model A300 B2 and A300 B4-100 airplanes, fuselage frame (FR) 55: Within 31,300 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (ii) For Model A300 B2 and A300 B4-100 airplanes, FR 58: Within 49,700 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (iii) For Model A300 B4-200 airplanes, FR 55: Within 33,600 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (iv) For Model A300 B4-200 airplanes, FR 58: Within 55,800 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (3) If it is determined that Airbus Service Bulletin A300-53- 0373, Revision 03, dated September 1, 2010 (mod 12796) has not been embodied: Within the compliance time specified in paragraphs (h)(3)(i), (h)(3)(ii), and (h)(3)(iii) of this AD, as applicable, modify the rear fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-0373, Revision 03, dated September 1, 2010, except as required by paragraph (i) of this AD. (i) For Model A300 B2 airplanes: Within 42,700 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (ii) For Model A300 B4-100 airplanes: Within 41,700 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (iii) For Model A300 B4-200 airplanes: Within 47,900 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (i) Service Information Exception Where any service information identified in table 1 to paragraphs (g), (h), and (i) of this AD specifies to contact the manufacturer for instructions or solutions, 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) Terminating Action for Certain Requirements in AD 2004-23-20 Accomplishing the modification required by paragraph (h)(1)(iii) of this AD terminates the modification required by paragraph (i) of AD 2004-23-20 for that airplane only. (k) 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 425-227-1405; fax 425-227-2125. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: 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. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015-0173, dated August 24, 2015, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA- 2016-9298. (2) For service information identified in this final rule, contact Airbus SAS, Airworthiness Office-EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: [email protected]; Internet http://www.airbus.com. You may view this 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 October 13, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-25662 Filed 10-25-16; 8:45 am] BILLING CODE 4910-13-P
![74354 Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules
(g) Repetitive Inspections requirement is removed from that step or accomplishing those modifications,
Except as specified in paragraph (i) of this substep. An AMOC is required for any including doing related investigative
AD: At the applicable time specified in deviations to RC steps, including substeps and corrective actions if necessary. We
paragraph 1.E., ‘‘Compliance,’’ of Boeing and identified figures.
are proposing this AD to prevent
Alert Service Bulletin DC6–57A001, dated (ii) Steps not labeled as RC may be
deviated from using accepted methods in reduced structural integrity of these
April 28, 2016 (‘‘ASB DC6–57A001, Revision airplanes due to the failure of certain
0’’), do radiographic, electromagnetic testing accordance with the operator’s maintenance
high frequency (ETHF), and electromagnetic or inspection program without obtaining structural components.
testing low frequency (ETLF) inspections for approval of an AMOC, provided the RC steps, DATES: We must receive comments on
cracking of the wing lower skin at station including substeps and identified figures, can
this proposed AD by December 12,
175, in accordance with the Accomplishment still be done as specified, and the airplane
can be put back in an airworthy condition. 2016.
Instructions of ASB DC6–57A001, Revision 0.
Repeat the radiographic, ETHF, and ETLF (k) Related Information ADDRESSES: You may send comments by
inspections of any unrepaired areas thereafter any of the following methods:
at the applicable intervals specified in (1) For more information about this AD,
contact Haytham Alaidy, Aerospace • Federal eRulemaking Portal: Go to
paragraph 1.E., ‘‘Compliance,’’ of ASB DC6–
57A001, Revision 0. Engineer, Airframe Branch, ANM–120L, http://www.regulations.gov. Follow the
FAA, Los Angeles ACO, 3960 Paramount instructions for submitting comments.
(h) Repairs Boulevard, Lakewood, CA 90712–4137; • Fax: 202–493–2251.
phone: 562–627–5224; fax: 562–627–5210;
If any cracking is found during any
email: haytham.alaidy@faa.gov. • Mail: U.S. Department of
inspection required by this AD: Before Transportation, Docket Operations, M–
further flight, repair the cracking using a (2) For service information identified in
method approved in accordance with the this AD, contact Boeing Commercial 30, West Building Ground Floor, Room
procedures specified in paragraph (j) of this Airplanes, Attention: Contractual & Data W12–140, 1200 New Jersey Avenue SE.,
AD. Services (C&DS), 2600 Westminster Blvd., Washington, DC 20590.
MC 110–SK57, Seal Beach, CA 90740–5600; • Hand Delivery: U.S. Department of
(i) Service information Exception telephone 562–797–1717; Internet https://
www.myboeingfleet.com. You may view this
Transportation, Docket Operations, M–
Where paragraph 1.E., ‘‘Compliance,’’ of 30, West Building Ground Floor, Room
ASB DC6–57A001, Revision 0, specifies a referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind W12–140, 1200 New Jersey Avenue SE.,
compliance time ‘‘after the original issue date
of this service bulletin,’’ this AD requires Avenue SW., Renton, WA. For information Washington, DC, between 9 a.m. and 5
compliance within the specified compliance on the availability of this material at the p.m., Monday through Friday, except
time after the effective date of this AD. FAA, call 425–227–1221. Federal holidays.
Issued in Renton, Washington, on October For service information identified in
(j) Alternative Methods of Compliance
(AMOCs)
13, 2016. this NRPM, contact Airbus SAS,
Michael Kaszycki, Airworthiness Office–EAW, 1 Rond
(1) The Manager, Los Angeles Aircraft
Acting Manager, Transport Airplane Point Maurice Bellonte, 31707 Blagnac
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if Directorate, Aircraft Certification Service. Cedex, France; telephone: +33 5 61 93
requested using the procedures found in 14 [FR Doc. 2016–25663 Filed 10–25–16; 8:45 am] 36 96; fax: +33 5 61 93 44 51; email:
CFR 39.19. In accordance with 14 CFR 39.19, BILLING CODE 4910–13–P continued.airworthiness-wb.external@
send your request to your principal inspector airbus.com; Internet http://
or local Flight Standards District Office, as www.airbus.com. You may view this
appropriate. If sending information directly DEPARTMENT OF TRANSPORTATION referenced service information at the
to the manager of the ACO, send it to the FAA, Transport Airplane Directorate,
attention of the person identified in Federal Aviation Administration 1601 Lind Avenue SW., Renton, WA.
paragraph (k)(1) of this AD. Information may
be emailed to: 9-ANM-LAACO-AMOC- 14 CFR Part 39 Examining the AD Docket
Requests@faa.gov.
(2) Before using any approved AMOC, [Docket No. FAA–2016–9298; Directorate You may examine the AD docket on
notify your appropriate principal inspector, Identifier 2015–NM–161–AD] the Internet at http://
or lacking a principal inspector, the manager www.regulations.gov by searching for
RIN 2120–AA64
of the local flight standards district office/ and locating Docket No. FAA–2016–
certificate holding district office. 9298; or in person at the Docket
(3) An AMOC that provides an acceptable Airworthiness Directives; Airbus
Airplanes Management Facility between 9 a.m.
level of safety may be used for any repair, and 5 p.m., Monday through Friday,
modification, or alteration required by this AGENCY: Federal Aviation except Federal holidays. The AD docket
AD if it is approved by the Boeing
Administration (FAA), DOT. contains this proposed AD, the
Commercial Airplanes Organization
Designation Authorization (ODA) that has ACTION: Notice of proposed rulemaking regulatory evaluation, any comments
been authorized by the Manager, Los Angeles (NPRM). received, and other information. The
ACO, to make those findings. To be street address for the Docket Operations
approved, the repair method, modification SUMMARY: We propose to adopt a new office (telephone 800–647–5527) is in
deviation, or alteration deviation must meet airworthiness directive (AD) for all the ADDRESSES section. Comments will
the certification basis of the airplane, and the Airbus Model A300 series airplanes. be available in the AD docket shortly
approval must specifically refer to this AD. This AD was prompted by an evaluation after receipt.
(4) For service information that contains by the design approval holder (DAH)
steps that are labeled as Required for that indicates a section of the wing and FOR FURTHER INFORMATION CONTACT: Dan
Lhorne on DSK30JT082PROD with PROPOSALS
Compliance (RC), the provisions of aft fuselage is subject to widespread Rodina, Aerospace Engineer,
paragraphs (j)(4)(i) and (j)(4)(ii) of this AD International Branch, ANM–116,
fatigue damage (WFD). This proposed
apply. Transport Airplane Directorate, FAA,
(i) The steps labeled as RC, including AD would require an inspection to
determine if certain modifications have 1601 Lind Avenue SW., Renton, WA
substeps under an RC step and any figures 98057–3356; telephone 425–227–2125;
identified in an RC step, must be done to been done. For airplanes on which the
comply with the AD. If a step or substep is specified modifications have not been fax 425–227–1149.
labeled ‘‘RC Exempt,’’ then the RC done, this proposed AD would require SUPPLEMENTARY INFORMATION:
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![Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules 74355
Comments Invited subject to the WFD rule, the rule Limitations Section] Part 2, and decision is
requires that DAHs establish a limit of made to delete section 3 from ALS Part 2.
We invite you to send any written For the reasons described above, this
relevant data, views, or arguments about validity (LOV) of the engineering data
[EASA] AD retains the requirements of DGAC
this proposed AD. Send your comments that support the structural maintenance
France AD F–2004–001, which is
to an address listed under the program. Operators affected by the WFD superseded, and requires implementation of
ADDRESSES section. Include ‘‘Docket No.
rule may not fly an airplane beyond its the additional inspection, modification and/
FAA–2016–9298; Directorate Identifier LOV, unless an extended LOV is or repair actions, as applicable to aeroplane
2015–NM–161–AD’’ at the beginning of approved. model.
The WFD rule (75 FR 69746,
your comments. We specifically invite Required actions include an
November 15, 2010) does not require
comments on the overall regulatory, inspection to determine if certain
identifying and developing maintenance
economic, environmental, and energy modifications have been done. For
actions if the DAHs can show that such
aspects of this proposed AD. We will airplanes on which the specified
actions are not necessary to prevent
consider all comments received by the modifications have not been done, this
WFD before the airplane reaches the
closing date and may amend this proposed AD would require
LOV. Many LOVs, however, do depend
proposed AD based on those comments. accomplishing those modifications,
We will post all comments we on accomplishment of future
including doing related investigative
receive, without change, to http:// maintenance actions. As stated in the
and corrective actions if necessary.
www.regulations.gov, including any WFD rule, any maintenance actions
Depending on airplane configuration,
personal information you provide. We necessary to reach the LOV will be
the compliance times for modifying the
will also post a report summarizing each mandated by airworthiness directives
airplane structure range between 13,300
substantive verbal contact we receive through separate rulemaking actions.
In the context of WFD, this action is flight cycles and 48,000 flight cycles
about this proposed AD. since first flight of the airplane,. You
necessary to enable DAHs to propose
Discussion LOVs that allow operators the longest may examine the MCAI in the AD
operational lives for their airplanes, and docket on the Internet at http://
Structural fatigue damage is www.regulations.gov by searching for
progressive. It begins as minute cracks, still ensure that WFD will not occur.
This approach allows for an and locating Docket No. FAA–2016–
and those cracks grow under the action 9298.
of repeated stresses. This can happen implementation strategy that provides
because of normal operational flexibility to DAHs in determining the Related Service Information Under 1
conditions and design attributes, or timing of service information CFR Part 51
because of isolated situations or development (with FAA approval),
Airbus issued the following service
incidents such as material defects, poor while providing operators with certainty
information:
regarding the LOV applicable to their
fabrication quality, or corrosion pits, • Airbus Service Bulletin A300–53–
dings, or scratches. Fatigue damage can airplanes.
0239, Revision 02, dated March 6, 2000.
The European Aviation Safety Agency
occur locally, in small areas or This service information describes
(EASA), which is the Technical Agent
structural design details, or globally. procedures to modify the longitudinal
for the Member States of the European
Global fatigue damage is general junction. The modification includes the
Union, has issued EASA Airworthiness
degradation of large areas of structure addition of external doublers and
Directive AD 2015–0173, dated August
with similar structural details and stress installation of interference fit
24, 2015 (referred to after this as the
levels. Multiple-site damage is global attachments and related investigative
Mandatory Continuing Airworthiness
damage that occurs in a large structural and corrective actions. The related
Information, or ‘‘the MCAI’’), to correct
element such as a single rivet line of a investigative actions are rotary probe
an unsafe condition for all Airbus
lap splice joining two large skin panels. inspections for cracking of the fastener
Model A300 series airplanes. The MCAI
Global damage can also occur in holes. The corrective action is repair.
states:
multiple elements such as adjacent • Airbus Service Bulletin A300–53–
frames or stringers. Multiple-site- A widespread fatigue damage (WFD) 0247, Revision 02, dated July 20, 1990.
damage and multiple-element-damage analysis conducted on A300 aeroplanes This service information describes
identified areas which are susceptible to
cracks are typically too small initially to procedures to modify the fuselage upper
crack development.
be reliably detected with normal This condition, if not corrected, could door frame structure, which consists of
inspection methods. Without affect the structural integrity of the eddy current inspections of certain
intervention, these cracks will grow, aeroplane. structure for cracks, and structural
and eventually compromise the To address this issue, Airbus developed a modification or repair.
structural integrity of the airplane, in a modification (mod) to reinforce the structure • Airbus Mandatory Service Bulletin
condition known as WFD. As an of the aeroplane. A300–53–0271, Revision 05, dated June
airplane ages, WFD will likely occur, Airbus issued Service Bulletin (SB) A300– 21, 2013. This service information
53–0271 to provide instructions for a cold
and will certainly occur if the airplane expansion of the foot attachment holes of
describes procedures to modify the
is operated long enough without any certain fuselage frames, and DGAC [Direction fuselage frame (FR), which includes
intervention. Générale de l’Aviation Civile] France issued cold expansion of the fastener holes
The FAA’s WFD final rule (75 FR AD F–2004–001 to require this mod [which between FR 41 and FR 54, and related
69746, November 15, 2010) became corresponds with certain requirements in investigative and corrective actions. The
effective on January 14, 2011. The WFD FAA AD 2004–23–20, Amendment 39–13875 related investigative actions including
Lhorne on DSK30JT082PROD with PROPOSALS
rule requires certain actions to prevent (69 FR 68779, November 26, 2004)]. rotary probe inspections for cracking of
structural failure due to WFD Since that [DGAC] AD was issued, Airbus the fastener holes. The corrective action
released twelve other mods with
throughout the operational life of corresponding SBs, to complete the set of
is repair.
certain existing transport category inspections and repairs in the frame of the • Airbus Mandatory Service Bulletin
airplanes and all transport category A300 WFD campaign. EASA issued AD A300–53–0366, dated April 7, 2005.
airplanes that will be certificated in the 2015–0115 to require ten of these mods This service information describes
future. For existing and future airplanes through section 3 of ALS [Airworthiness procedures to modify the fuselage
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![Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules 74357
the FAA proposes to amend 14 CFR part (b) Affected ADs (f) Compliance
39 as follows: This AD affects AD 2004–23–20, Comply with this AD within the
Amendment 39–13875 (69 FR 68779, compliance times specified, unless already
PART 39—AIRWORTHINESS November 26, 2004) (‘‘AD 2004–23–20’’). done.
DIRECTIVES (c) Applicability (g) Verification of Embodied Modifications
This AD applies to Airbus Model A300 B2–
■ 1. The authority citation for part 39 1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, Within 4 months after the effective date of
continues to read as follows: and B4–203 airplanes, certificated in any this AD, verify whether the Airbus
category, all manufacturer serial numbers. modifications listed in table 1 to paragraphs
Authority: 49 U.S.C. 106(g), 40113, 44701. (g), (h), and (i) of this AD, as applicable to
(d) Subject airplane model, have been embodied on the
§ 39.13 [Amended]
Air Transport Association (ATA) of airplane in accordance with the
■ 2. The FAA amends § 39.13 by adding America Code 53, Fuselage. Accomplishment Instructions of the
the following new Airworthiness (e) Reason applicable Airbus service bulletin listed in
Directive (AD): This AD was prompted by an evaluation by table 1 to paragraphs (g), (h), and (i) of this
the design approval holder (DAH) that AD. A review of the airplane maintenance
Airbus: Docket No. FAA–2016–9298;
indicates a section of the wing and aft records is acceptable to accomplish the
Directorate Identifier 2015–NM–161–AD.
fuselage is subject to widespread fatigue verification required by this paragraph,
(a) Comments Due Date damage (WFD). We are issuing this AD to provided those records can conclusively
prevent reduced structural integrity of these determine whether the modifications have
We must receive comments by December
airplanes due to the failure of certain been embodied.
12, 2016. structural components.
TABLE 1 TO PARAGRAPHS (g), (h), AND (i) OF THIS AD—AIRBUS MODIFICATION AND APPLICABLE SERVICE BULLETIN
Set Airbus modification Applicable airbus service bulletin
Set 1A ............................................. 751 ................................................. A300–53–0247, Revision 02, dated July 20, 1990.
7301 ............................................... A300–53–0239, Revision 02, dated March 6, 2000.
10326 ............................................. A300–57–0203, Revision 04, dated February 18, 2015.
12735 ............................................. A300–53–0366, dated April 7, 2005.
12736 ............................................. A300–53–0368, dated April 7, 2005.
12737 ............................................. A300–53–0369, Revision 03, dated September 1, 2010.
12798 ............................................. A300–53–0375, Revision 01, dated June 24, 2013.
07757 and 12977 .......................... A300–53–0271, Revision 05, dated June 21, 2013.
13611 ............................................. A300–57–0258, dated September 30, 2014.
13692 ............................................. A300–53–0393, dated September 27, 2013.
13716 ............................................. A300–57–0259, dated September 30, 2014.
Set 1B ............................................. 12794 ............................................. A300–53–0374, Revision 04, dated July 5, 2013.
12796 ............................................. A300–53–0373, Revision 03, dated September 1, 2010.
(h) Corrective Actions for Modifications Service Bulletin A300–53–0239, Revision 02, has not been embodied: Modify the rear
Which Have Not Been Embodied dated March 6, 2000. fuselage, in accordance with the
If, during the verification required by (ii) For airplanes on which Airbus Service Accomplishment Instructions of Airbus
Bulletin A300–53–0247, Revision 02, dated Mandatory Service Bulletin A300–53–0366,
paragraph (g) of this AD, it is determined that
July 20, 1990, has not been embodied: dated April 7, 2005.
any modification has not been embodied, do
Modify the fuselage upper door frame (vi) For airplanes on which Airbus
the applicable actions specified in
structure by doing eddy current inspections Mandatory Service Bulletin A300–53–0369,
paragraphs (h)(1), (h)(2), and (h)(3) of this
for cracks of the structure specified in Airbus Revision 03, dated September 1, 2010, has
AD. not been embodied: Modify the rear fuselage,
Service Bulletin A300–53–0247, Revision 02,
(1) If it is determined that any Airbus dated July 20, 1990, and a structural in accordance with the Accomplishment
modification, specified in the applicable modification or repair, as applicable, in Instructions of Airbus Mandatory Service
Airbus Service Bulletin, identified in ‘‘Set accordance with the Accomplishment Bulletin A300–53–0369, Revision 03, dated
1A’’ of table 1 to paragraphs (g), (h), and (i) Instructions of Airbus Service Bulletin A300– September 1, 2010.
of this AD is not embodied: Within the 53–0247, Revision 02, dated July 20, 1990. (vii) For airplanes on which Airbus
applicable compliance time specified in the (iii) For airplanes on which Airbus Mandatory Service Bulletin A300–53–0375,
applicable Airbus Service Bulletin identified Mandatory Service Bulletin A300–53–0271, Revision 01, dated June 24, 2013, has not
in ‘‘Set 1A’’ of table 1 to paragraphs (g), (h), Revision 05, dated June 21, 2013, has not been embodied: Modify the forward fuselage,
and (i) of this AD, or within 4 months after been embodied: Modify the fuselage frame, in accordance with the Accomplishment
the effective date of this AD, whichever and do all applicable related investigative Instructions of Airbus Mandatory Service
occurs later, do the applicable actions and corrective actions, in accordance with Bulletin A300–53–0375, Revision 01, dated
specified in paragraphs (h)(1)(i) through the Accomplishment Instructions of Airbus June 24, 2013.
(h)(1)(xi) of this AD, except as required by Mandatory Service Bulletin A300–53–0271, (viii) For airplanes on which Airbus
paragraph (i) of this AD. Do all applicable Revision 05, dated June 21, 2013. Mandatory Service Bulletin A300–53–0393,
related investigative and corrective actions (iv) For airplanes on which Airbus dated September 27, 2013, has not been
Lhorne on DSK30JT082PROD with PROPOSALS
before further flight. Mandatory Service Bulletin A300–53–0366, embodied: Modify the fuselage frame, in
(i) For airplanes on which Airbus Service dated April 7, 2005, has not been embodied: accordance with the Accomplishment
Bulletin A300–53–0239, Revision 02, dated Modify the fuselage frame, in accordance Instructions of Airbus Mandatory Service
March 6, 2000, has not been embodied: with the Accomplishment Instructions of Bulletin A300–53–0393, dated September 27,
Modify the longitudinal junction and do all Airbus Mandatory Service Bulletin A300–53– 2013.
applicable related investigative and 0366, dated April 7, 2005. (ix) For airplanes on which Airbus
corrective actions, in accordance with the (v) For airplanes on which Airbus Service Mandatory Service Bulletin A300–57–0203,
Accomplishment Instructions of Airbus Bulletin A300–53–0368, dated April 7, 2005, Revision 04, dated February 18, 2015, has not
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![74358 Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules
been embodied: Modify the outer wing, and effective date of this AD, whichever occurs changes to procedures or tests identified as
do all applicable related investigative and later. RC require approval of an AMOC.
corrective actions, in accordance with the (iii) For Model A300 B4–200 airplanes:
(l) Related Information
Accomplishment Instructions of Airbus Within 47,900 flight cycles since first flight
Mandatory Service Bulletin A300–57–0203, of the airplane, or within 4 months after the (1) Refer to Mandatory Continuing
Revision 04, dated February 18, 2015. effective date of this AD, whichever occurs Airworthiness Information (MCAI) EASA AD
(x) For airplanes on which Airbus later. 2015–0173, dated August 24, 2015, for
Mandatory Service Bulletin A300–57–0258, related information. You may examine the
(i) Service Information Exception MCAI on the Internet at http://
dated September 30, 2014, has not been
embodied: Modify the wing structure and do Where any service information identified www.regulations.gov by searching for and
all applicable related investigative and in table 1 to paragraphs (g), (h), and (i) of this locating Docket No. FAA–2016–9298.
corrective actions, in accordance with the AD specifies to contact the manufacturer for (2) For service information identified in
Accomplishment Instructions of Airbus instructions or solutions, before further this final rule, contact Airbus SAS,
Mandatory Service Bulletin A300–57–0258, flight, repair using a method approved by the Airworthiness Office–EAW, 1 Rond Point
dated September 30, 2014. Manager, International Branch, ANM–116, Maurice Bellonte, 31707 Blagnac Cedex,
(xi) For airplanes on which Airbus Transport Airplane Directorate, FAA; or the France; telephone: +33 5 61 93 36 96; fax:
Mandatory Service Bulletin A300–57–0259, European Aviation Safety Agency (EASA); or +33 5 61 93 44 51; email:
dated September 30, 2014, has not been Airbus’s EASA Design Organization continued.airworthiness-wb.external@
embodied: Modify the wing structure, and do Approval (DOA). airbus.com; Internet http://www.airbus.com.
all applicable related investigative and You may view this service information at the
(j) Terminating Action for Certain FAA, Transport Airplane Directorate, 1601
corrective actions, in accordance with the Requirements in AD 2004–23–20
Accomplishment Instructions of Airbus Lind Avenue SW., Renton, WA. For
Mandatory Service Bulletin A300–57–0259, Accomplishing the modification required information on the availability of this
dated September 30, 2014. by paragraph (h)(1)(iii) of this AD terminates material at the FAA, call 425–227–1221.
(2) If it is determined that Airbus Service the modification required by paragraph (i) of
Issued in Renton, Washington, on October
Bulletin A300–53–0374, Revision 04, dated AD 2004–23–20 for that airplane only.
13, 2016.
July 5, 2013 (mod 12794) has not been (k) Other FAA AD Provisions Michael Kaszycki,
embodied: Within the compliance time
The following provisions also apply to this Acting Manager, Transport Airplane
specified in paragraphs (h)(2)(i), (h)(2)(ii),
AD: Directorate, Aircraft Certification Service.
(h)(2)(iii), and (h)(2)(iv) of this AD, as
(1) Alternative Methods of Compliance [FR Doc. 2016–25662 Filed 10–25–16; 8:45 am]
applicable, modify the rear fuselage, in
(AMOCs): The Manager, International
accordance with the Accomplishment BILLING CODE 4910–13–P
Branch, ANM–116, Transport Airplane
Instructions of Airbus Service Bulletin A300–
Directorate, FAA, has the authority to
53–0374, Revision 04, dated July 5, 2013,
approve AMOCs for this AD, if requested
except as required by paragraph (i) of this DEPARTMENT OF TRANSPORTATION
using the procedures found in 14 CFR 39.19.
AD. In accordance with 14 CFR 39.19, send your
(i) For Model A300 B2 and A300 B4–100 request to your principal inspector or local Federal Aviation Administration
airplanes, fuselage frame (FR) 55: Within Flight Standards District Office, as
31,300 flight cycles since first flight of the appropriate. If sending information directly 14 CFR Part 39
airplane, or within 4 months after the to the International Branch, send it to ATTN:
effective date of this AD, whichever occurs Dan Rodina, Aerospace Engineer, [Docket No. FAA–2016–8836; Directorate
later. International Branch, ANM–116, Transport Identifier 2016–NE–17–AD]
(ii) For Model A300 B2 and A300 B4–100 Airplane Directorate, FAA, 1601 Lind
airplanes, FR 58: Within 49,700 flight cycles RIN 2120–AA64
Avenue SW., Renton, WA 98057–3356;
since first flight of the airplane, or within 4 telephone 425–227–1405; fax 425–227–2125.
months after the effective date of this AD, Airworthiness Directives; Pratt &
Information may be emailed to: 9-ANM-116- Whitney Division Turbofan Engines
whichever occurs later. AMOC-REQUESTS@faa.gov. Before using
(iii) For Model A300 B4–200 airplanes, FR any approved AMOC, notify your appropriate AGENCY: Federal Aviation
55: Within 33,600 flight cycles since first principal inspector, or lacking a principal Administration (FAA), DOT.
flight of the airplane, or within 4 months inspector, the manager of the local flight
after the effective date of this AD, whichever ACTION: Notice of proposed rulemaking
standards district office/certificate holding
occurs later. district office. The AMOC approval letter (NPRM).
(iv) For Model A300 B4–200 airplanes, FR must specifically reference this AD.
58: Within 55,800 flight cycles since first SUMMARY: We propose to adopt a new
(2) Contacting the Manufacturer: For any
flight of the airplane, or within 4 months requirement in this AD to obtain corrective
airworthiness directive (AD) for all Pratt
after the effective date of this AD, whichever actions from a manufacturer, the action must & Whitney Division (PW) PW4074,
occurs later. be accomplished using a method approved PW4074D, PW4077, PW4077D,
(3) If it is determined that Airbus Service by the Manager, International Branch, ANM– PW4084, PW4084D, PW4090, and
Bulletin A300–53–0373, Revision 03, dated 116, Transport Airplane Directorate, FAA; or PW4090–3 turbofan engines. This
September 1, 2010 (mod 12796) has not been EASA; or Airbus’s EASA DOA. If approved proposed AD was prompted by an
embodied: Within the compliance time by the DOA, the approval must include the uncontained failure of a high-pressure
specified in paragraphs (h)(3)(i), (h)(3)(ii), DOA-authorized signature.
and (h)(3)(iii) of this AD, as applicable,
turbine (HPT) hub during takeoff. This
(3) Required for Compliance (RC): If any
modify the rear fuselage, in accordance with service information contains procedures or
proposed AD would require an
the Accomplishment Instructions of Airbus tests that are identified as RC, those inspection to measure the surface
Service Bulletin A300–53–0373, Revision 03, procedures and tests must be done to comply condition of the aft side web/rim fillet
dated September 1, 2010, except as required with this AD; any procedures or tests that are of HPT 1st stage hubs and removal from
by paragraph (i) of this AD. not identified as RC are recommended. Those service of hubs that fail inspection. We
Lhorne on DSK30JT082PROD with PROPOSALS
(i) For Model A300 B2 airplanes: Within procedures and tests that are not identified are proposing this AD to prevent failure
42,700 flight cycles since first flight of the as RC may be deviated from using accepted of the HPT 1st stage hub, uncontained
airplane, or within 4 months after the methods in accordance with the operator’s hub release, damage to the engine, and
effective date of this AD, whichever occurs maintenance or inspection program without
later. obtaining approval of an AMOC, provided
damage to the airplane.
(ii) For Model A300 B4–100 airplanes: the procedures and tests identified as RC can DATES: We must receive comments on
Within 41,700 flight cycles since first flight be done and the airplane can be put back in this proposed AD by December 12,
of the airplane, or within 4 months after the an airworthy condition. Any substitutions or 2016.
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Document Created: 2016-10-26 02:17:46
Document Modified: 2016-10-26 02:17:46
| 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 December 12, 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 | 81 FR 74354 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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