81 FR 44232 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 130 (July 7, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 130 (July 7, 2016)
| Page Range | 44232-44235 | |
| FR Document | 2016-15910 |
[Federal Register Volume 81, Number 130 (Thursday, July 7, 2016)] [Proposed Rules] [Pages 44232-44235] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-15910] ======================================================================== 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. 130 / Thursday, July 7, 2016 / Proposed Rules [[Page 44232]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-7425; Directorate Identifier 2014-NM-244-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) 2011-17- 05, for certain Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C airplanes. AD 2011-17-05 currently requires repetitive inspections in sections 13 through 18 of the fuselage between rivets of the longitudinal lap joints between frames (FR) 18 and 80 for cracking, and repair or modification if necessary. Since we issued AD 2011-17-05, we have determined that a revised inspection program is necessary. This proposed AD would include a revised repetitive inspection program of all longitudinal lap joints and repairs between frames 18 and 80 to address this widespread fatigue damage (WFD). We are proposing this AD to detect and correct fatigue cracking of the longitudinal lap joints of the fuselage, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by August 22, 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- 7425; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425- 227-1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-7425; Directorate Identifier 2014-NM-244-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 September 23, 2011, we issued AD 2011-17-05, Amendment 39-16769 (76 FR 63177, October 12, 2011) (``AD 2011-17-05''). AD 2011-17-05 requires actions intended to address an unsafe condition on certain Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C airplanes. Since we issued AD 2011-17-05, we have determined it is necessary to require a revised inspection program for the longitudinal lap joints and repairs between FR 18 and FR 80 because additional cracking was found in an expanded area. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0265, dated December 9, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states: Cracks were found on in-service aeroplanes in sections 13 to 18 of the fuselage between rivets of longitudinal lap joints between frames (FR) 18 and FR80. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To address this unsafe condition, Airbus developed an inspection programme for the longitudinal lap joints and repairs between FR18 and FR80, and EASA issued AD 2007-0091 [which corresponds to FAA AD 2011-17-05] to require the implementation of that programme. Since EASA AD 2007-0091 was issued, [a] new Widespread Fatigue Damage regulation has been issued. This new regulation led to the revision of the maintenance programme for the longitudinal lap joints and repairs between FR18 and FR80. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2007-0091, which is superseded, and requires implementation of the revised inspection programme. Required actions include repetitive inspections of the bonded inner [[Page 44233]] doublers of the longitudinal lap joints in sections 13 through 18 for disbonding or corrosion, and repairing any disbonding and corrosion; a follow-on rototest or ultrasonic inspection to verify cracking, and repair of any cracking. The repetitive inspection interval ranges from 3,000 flight cycles up to 8,000 flight cycles, depending on airplane configuration. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-2016-7425. Widespread Fatigue Damage Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread 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. This condition is known as widespread fatigue damage. It is associated with general degradation of large areas of structure with similar structural details and stress levels. 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 of these 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. We are issuing this AD to detect and correct fatigue cracking of the longitudinal lap joints of the fuselage, which could result in reduced structural integrity of the airplane. 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. Differences Between This Proposed AD and the MCAI or Service Information Unlike the procedures described in the service information, this proposed AD would not permit further flight if cracks are detected. We have determined that, because of the safety implications and consequences associated with that cracking, any cracked upper shell structure must be repaired before further flight. The MCAI refers to Airbus Service Bulletin A300-53-0211, Revision 08, dated November 26, 2013, for compliance times and for the new inspections. However, paragraph (l) of this proposed AD would require operators to do the initial inspections within 180 days after the effective date of this AD, in 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); and thereafter at intervals approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. We find that 180 days is an appropriate amount of time to accomplish the initial inspections and address the unsafe condition. These differences have been coordinated with the EASA and Airbus. Costs of Compliance We estimate that this proposed AD affects 4 airplanes of U.S. registry. Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost product operators ---------------------------------------------------------------------------------------------------------------- Retained actions from AD 2011-17-05 (5 3,735 work-hours x $85 per hour $317,475 $1,587,375 airplanes). = $317,475. New proposed inspections (4 airplanes)........ 140 work-hours x $85 per hour = 11,900 47,600 $11,900. ---------------------------------------------------------------------------------------------------------------- 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. [[Page 44234]] 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, 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) 2011-17-05, Amendment 39-16769 (76 FR 63177, October 12, 2011), and adding the following new AD: Airbus: Docket No. FAA-2016-7425; Directorate Identifier 2014-NM- 244-AD. (a) Comments Due Date We must receive comments by August 22, 2016. (b) Affected ADs This AD replaces AD 2011-17-05, Amendment 39-16769 (76 FR 63177, October 12, 2011) (``AD 2011-17-05''). (c) Applicability This AD applies to Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C airplanes; certificated in any category; all manufacturer serial numbers, except those on which Airbus Modification 2611 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by an evaluation done by the design approval holder indicating that certain sections of the longitudinal lap joints are subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking of the longitudinal lap joints of the fuselage, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Fuselage Inner Doubler Inspections and Repair, With Revised Formatting This paragraph restates the requirements of paragraph (l) of AD 2011-17-05, with revised formatting. For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking have not been done as of November 16, 2011 (the effective date of AD 2011-17-05), as specified by Airbus Service Bulletin A300-53-229: Prior to the accumulation of 24,000 total flight cycles or within 15 years since new, whichever occurs first; or within 60 days after November 16, 2011; whichever occurs later; do a detailed inspection of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no cracking are found, repeat the inspection thereafter at the applicable intervals specified in paragraph (h) of this AD. (1) If no cracking is found, and ``minor'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. (2) If no cracking is found, and ``major'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (h) Retained Repetitive Intervals for Inspections for Disbonding and Cracking This paragraph restates the repetitive intervals specified in table 1 of AD 2011-17-05. At the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, repeat the inspection required by paragraph (g) of this AD. (1) For Sections 13 and 14 as specified in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997: Repeat the inspection at intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first. (2) For Sections 15 through 18 as specified in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997: Repeat the inspection within 8.5 years or 12,000 flight cycles, whichever occurs first. (i) Retained Fuselage Inner Doubler Inspections and Repair This paragraph restates the requirements of paragraph (m) of AD 2011-17-05. For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking have been done as of November 16, 2011 (the effective date of AD 2011-17-05), as specified in Airbus Service Bulletin A300-53-229; except for airplanes on which a repair of that area has been done as specified in Airbus Service Bulletin A300-53-229: Within 7 years or 12,000 flight cycles (for Sections 13 and 14), or within 8.5 years or 12,000 flight cycles (for Sections 15 and 18), after doing the inspection, whichever occurs first; or within 60 days after November 16, 2011, whichever occurs later, do a detailed inspection of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no cracking are found, repeat the inspection at the applicable time specified in paragraph (h) of this AD. (1) If no cracking is found, and ``minor'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. (2) If no cracking is found, and ``major'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (j) Retained Fuselage Inner Doubler Inspections and Repair, With No Changes This paragraph restates the requirements of paragraph (n) of AD 2011-17-05, with no changes. For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand [[Page 44235]] and right-hand for disbonding and cracking have not been done as of November 16, 2011 (the effective date of AD 2011-17-05), as specified in Airbus Service Bulletin A300-53-229: Prior to the accumulation of 24,000 total flight cycles or within 12 years since new, whichever occurs first; or within 60 days after November 16, 2011, whichever occurs later, do a detailed inspection of the fuselage bonded inner doubles of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no cracking are found, repeat the inspection thereafter at intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first. (1) If no cracking is found, and ``minor'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. Doing a repair in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, terminates the repetitive inspections required by this paragraph for that area. (2) If no cracking is found, and ``major'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (k) Retained Fuselage Inner Doubler Inspections and Repair, With No Changes This paragraph restates the requirements of paragraph (o) of AD 2011-17-05, with no changes. For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking have been done as of November 16, 2011, as specified in Airbus Service Bulletin A300-53-229; except airplanes on which a repair of that area has been done as specified in Airbus Service Bulletin A300-53-229: Within 7 years or 12,000 flight cycles after doing the inspection, whichever occurs first; or within 60 days after November 16, 2011; whichever occurs later; do a detailed inspection of the fuselage bonded inner doubles of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right- hand for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no corrosion are found, repeat the inspection thereafter at intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first. (1) If no cracking is found, and ``minor'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. Doing a repair, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, terminates the repetitive inspections required by this paragraph for that area. (2) If no cracking is found, and ``major'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (l) New Repetitive Inspections and Repair Within 180 days after the effective date of this AD, do rototest and ultrasonic inspections, as applicable, for cracking of all longitudinal lap joints and repairs between frames 18 and 80; and repair any cracking before further flight; 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). Repeat the applicable inspection, including post-repair inspections, thereafter at intervals approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. Accomplishing the initial inspection and applicable repairs required by this paragraph terminates the actions required by paragraphs (g) through (k) of this AD. (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-2125; fax 425-227-1149. Information may be emailed to: [email protected]. 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: 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 the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0265, dated December 9, 2014, 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-2016-7425. (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 June 23, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-15910 Filed 7-6-16; 8:45 am] BILLING CODE 4910-13-P
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Proposed Rules Federal Register
Vol. 81, No. 130
Thursday, July 7, 2016
This section of the FEDERAL REGISTER • Hand Delivery: U.S. Department of closing date and may amend this
contains notices to the public of the proposed Transportation, Docket Operations, M– proposed AD based on those comments.
issuance of rules and regulations. The 30, West Building Ground Floor, Room We will post all comments we
purpose of these notices is to give interested W12–140, 1200 New Jersey Avenue SE., receive, without change, to http://
persons an opportunity to participate in the Washington, DC, between 9 a.m. and 5 www.regulations.gov, including any
rule making prior to the adoption of the final
rules.
p.m., Monday through Friday, except personal information you provide. We
Federal holidays. will also post a report summarizing each
For service information identified in substantive verbal contact we receive
DEPARTMENT OF TRANSPORTATION this NPRM, contact Airbus SAS, about this proposed AD.
Airworthiness Office—EAW, 1 Rond Discussion
Federal Aviation Administration Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36 On September 23, 2011, we issued AD
14 CFR Part 39 96; fax +33 5 61 93 44 51; email 2011–17–05, Amendment 39–16769 (76
account.airworth-eas@airbus.com; FR 63177, October 12, 2011) (‘‘AD
[Docket No. FAA–2016–7425; Directorate 2011–17–05’’). AD 2011–17–05 requires
Identifier 2014–NM–244–AD] Internet http://www.airbus.com. You
may view this referenced service actions intended to address an unsafe
RIN 2120–AA64 information at the FAA, Transport condition on certain Airbus Model A300
Airplane Directorate, 1601 Lind Avenue B2–1C, A300 B2–203, A300 B2K–3C,
Airworthiness Directives; Airbus A300–B4–103, A300 B4–203, and A300
Airplanes SW., Renton, WA. For information on
the availability of this material at the B4–2C airplanes.
AGENCY: Federal Aviation FAA, call 425–227–1221. Since we issued AD 2011–17–05, we
Administration (FAA), DOT. have determined it is necessary to
Examining the AD Docket require a revised inspection program for
ACTION: Notice of proposed rulemaking
You may examine the AD docket on the longitudinal lap joints and repairs
(NPRM).
the Internet at http:// between FR 18 and FR 80 because
SUMMARY: We propose to supersede www.regulations.gov by searching for additional cracking was found in an
Airworthiness Directive (AD) 2011–17– and locating Docket No. FAA–2016– expanded area.
05, for certain Airbus Model A300 B2– The European Aviation Safety Agency
7425; or in person at the Docket
1C, A300 B2–203, A300 B2K–3C, A300– (EASA), which is the Technical Agent
Management Facility between 9 a.m.
B4–103, A300 B4–203, and A300 B4–2C for the Member States of the European
and 5 p.m., Monday through Friday,
airplanes. AD 2011–17–05 currently Union, has issued EASA Airworthiness
except Federal holidays. The AD docket
requires repetitive inspections in Directive 2014–0265, dated December 9,
contains this proposed AD, the
sections 13 through 18 of the fuselage 2014 (referred to after this as the
regulatory evaluation, any comments
between rivets of the longitudinal lap Mandatory Continuing Airworthiness
received, and other information. The
joints between frames (FR) 18 and 80 for Information, or ‘‘the MCAI’’), to correct
street address for the Docket Operations
cracking, and repair or modification if an unsafe condition for the specified
office (telephone (800) 647–5527) is in
necessary. Since we issued AD 2011– products. The MCAI states:
the ADDRESSES section. Comments will
17–05, we have determined that a be available in the AD docket shortly Cracks were found on in-service aeroplanes
revised inspection program is necessary. after receipt. in sections 13 to 18 of the fuselage between
This proposed AD would include a rivets of longitudinal lap joints between
revised repetitive inspection program of FOR FURTHER INFORMATION CONTACT: Dan frames (FR) 18 and FR80.
all longitudinal lap joints and repairs Rodina, Aerospace Engineer, This condition, if not detected and
between frames 18 and 80 to address International Branch, ANM–116, corrected, could affect the structural integrity
Transport Airplane Directorate, FAA, of the aeroplane.
this widespread fatigue damage (WFD). To address this unsafe condition, Airbus
We are proposing this AD to detect and 1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–2125; developed an inspection programme for the
correct fatigue cracking of the longitudinal lap joints and repairs between
longitudinal lap joints of the fuselage, fax 425- 227–1149.
FR18 and FR80, and EASA issued AD 2007–
which could result in reduced structural SUPPLEMENTARY INFORMATION: 0091 [which corresponds to FAA AD 2011–
integrity of the airplane. 17–05] to require the implementation of that
Comments Invited programme.
DATES: We must receive comments on
this proposed AD by August 22, 2016. We invite you to send any written Since EASA AD 2007–0091 was issued, [a]
new Widespread Fatigue Damage regulation
ADDRESSES: You may send comments by relevant data, views, or arguments about has been issued. This new regulation led to
any of the following methods: this proposed AD. Send your comments the revision of the maintenance programme
• Federal eRulemaking Portal: Go to to an address listed under the for the longitudinal lap joints and repairs
ADDRESSES section. Include ‘‘Docket No.
Lhorne on DSK30JT082PROD with PROPOSALS
http://www.regulations.gov. Follow the between FR18 and FR80.
instructions for submitting comments. FAA–2016–7425; Directorate Identifier For the reasons described above, this
• Fax: (202) 493–2251. 2014–NM–244–AD’’ at the beginning of [EASA] AD retains the requirements of EASA
• Mail: U.S. Department of your comments. We specifically invite AD 2007–0091, which is superseded, and
Transportation, Docket Operations, M– comments on the overall regulatory, requires implementation of the revised
30, West Building Ground Floor, Room economic, environmental, and energy inspection programme.
W12–140, 1200 New Jersey Avenue SE., aspects of this proposed AD. We will Required actions include repetitive
Washington, DC 20590. consider all comments received by the inspections of the bonded inner
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![44234 Federal Register / Vol. 81, No. 130 / Thursday, July 7, 2016 / Proposed Rules
Regulatory Findings (d) Subject paragraph (h)(1) or (h)(2) of this AD, repeat
Air Transport Association (ATA) of the inspection required by paragraph (g) of
We determined that this proposed AD this AD.
America Code 53, Fuselage.
would not have federalism implications (1) For Sections 13 and 14 as specified in
under Executive Order 13132. This (e) Reason Airbus Service Bulletin A300–53–229,
proposed AD would not have a This AD was prompted by an evaluation Revision 5, dated April 8, 1997: Repeat the
substantial direct effect on the States, on done by the design approval holder inspection at intervals not to exceed 7 years
the relationship between the national indicating that certain sections of the or 12,000 flight cycles, whichever occurs
Government and the States, or on the longitudinal lap joints are subject to first.
widespread fatigue damage. We are issuing (2) For Sections 15 through 18 as specified
distribution of power and
this AD to detect and correct fatigue cracking in Airbus Service Bulletin A300–53–229,
responsibilities among the various Revision 5, dated April 8, 1997: Repeat the
of the longitudinal lap joints of the fuselage,
levels of government. which could result in reduced structural inspection within 8.5 years or 12,000 flight
For the reasons discussed above, I integrity of the airplane. cycles, whichever occurs first.
certify this proposed regulation:
(f) Compliance (i) Retained Fuselage Inner Doubler
1. Is not a ‘‘significant regulatory Inspections and Repair
action’’ under Executive Order 12866; Comply with this AD within the
2. Is not a ‘‘significant rule’’ under the compliance times specified, unless already This paragraph restates the requirements of
done. paragraph (m) of AD 2011–17–05. For
DOT Regulatory Policies and Procedures airplanes on which any inspections of the
(44 FR 11034, February 26, 1979); (g) Retained Fuselage Inner Doubler fuselage bonded inner doublers of the
3. Will not affect intrastate aviation in Inspections and Repair, With Revised longitudinal lap joints in Sections 13 through
Alaska; and Formatting 18 (except Sections 16 and 17 at Stringer 31
4. Will not have a significant This paragraph restates the requirements of left-hand and right-hand) for disbonding and
economic impact, positive or negative, paragraph (l) of AD 2011–17–05, with revised cracking have been done as of November 16,
on a substantial number of small entities formatting. For airplanes on which any 2011 (the effective date of AD 2011–17–05),
under the criteria of the Regulatory inspections of the fuselage bonded inner as specified in Airbus Service Bulletin A300–
doublers of the longitudinal lap joints in 53–229; except for airplanes on which a
Flexibility Act.
Sections 13 through 18 (except Sections 16 repair of that area has been done as specified
List of Subjects in 14 CFR Part 39 and 17 at Stringer 31 left-hand and right- in Airbus Service Bulletin A300–53–229:
hand) for disbonding and cracking have not Within 7 years or 12,000 flight cycles (for
Air transportation, Aircraft, Aviation been done as of November 16, 2011 (the Sections 13 and 14), or within 8.5 years or
safety, Incorporation by reference, effective date of AD 2011–17–05), as 12,000 flight cycles (for Sections 15 and 18),
Safety. specified by Airbus Service Bulletin A300– after doing the inspection, whichever occurs
53–229: Prior to the accumulation of 24,000 first; or within 60 days after November 16,
The Proposed Amendment total flight cycles or within 15 years since 2011, whichever occurs later, do a detailed
Accordingly, under the authority new, whichever occurs first; or within 60 inspection of the fuselage bonded inner
delegated to me by the Administrator, days after November 16, 2011; whichever doublers of the longitudinal lap joints in
the FAA proposes to amend 14 CFR part occurs later; do a detailed inspection of the Sections 13 through 18 (except Sections 16
fuselage bonded inner doublers of the and 17 at Stringer 31 left-hand and right-
39 as follows: longitudinal lap joints in Sections 13 through hand) for disbonding and cracking, in
18 (except Sections 16 and 17 at Stringer 31 accordance with the Accomplishment
PART 39—AIRWORTHINESS left-hand and right-hand) for disbonding and Instructions of Airbus Service Bulletin A300–
DIRECTIVES cracking, in accordance with the 53–229, Revision 5, dated April 8, 1997. If no
Accomplishment Instructions of Airbus disbonding and no cracking are found, repeat
■ 1. The authority citation for part 39 Service Bulletin A300–53–229, Revision 5, the inspection at the applicable time
continues to read as follows: dated April 8, 1997. If no disbonding and no specified in paragraph (h) of this AD.
Authority: 49 U.S.C. 106(g), 40113, 44701. cracking are found, repeat the inspection (1) If no cracking is found, and ‘‘minor’’
thereafter at the applicable intervals specified disbonding, as defined in Airbus Service
§ 39.13 [Amended] in paragraph (h) of this AD. Bulletin A300–53–229, Revision 5, dated
■ 2. The FAA amends § 39.13 by (1) If no cracking is found, and ‘‘minor’’ April 8, 1997, is found: Repeat the inspection
disbonding, as defined in Airbus Service thereafter at intervals not to exceed 1 year for
removing Airworthiness Directive (AD)
Bulletin A300–53–229, Revision 5, dated areas below stringer 22, and at intervals not
2011–17–05, Amendment 39–16769 (76 April 8, 1997, is found: Repeat the inspection to exceed 2 years for areas above and
FR 63177, October 12, 2011), and thereafter at intervals not to exceed 1 year for including stringer 22.
adding the following new AD: areas below stringer 22, and at intervals not (2) If no cracking is found, and ‘‘major’’
Airbus: Docket No. FAA–2016–7425; to exceed 2 years for areas above and disbonding, as defined in Airbus Service
Directorate Identifier 2014–NM–244–AD. including stringer 22. Bulletin A300–53–229, Revision 5, dated
(2) If no cracking is found, and ‘‘major’’ April 8, 1997, is found: Within 1,000 flight
(a) Comments Due Date disbonding, as defined in Airbus Service cycles after doing the inspection, repair, in
We must receive comments by August 22, Bulletin A300–53–229, Revision 5, dated accordance with the Accomplishment
2016. April 8, 1997, is found: Within 1,000 flight Instructions of Airbus Service Bulletin A300–
cycles after doing the inspection, repair, in 53–229, Revision 5, dated April 8, 1997.
(b) Affected ADs accordance with the Accomplishment (3) If any cracking is found, repair prior to
This AD replaces AD 2011–17–05, Instructions of Airbus Service Bulletin A300– further flight, in accordance with Airbus
Amendment 39–16769 (76 FR 63177, October 53–229, Revision 5, dated April 8, 1997. Service Bulletin A300–53–229, Revision 5,
12, 2011) (‘‘AD 2011–17–05’’). (3) If any cracking is found, repair prior to dated April 8, 1997.
further flight, in accordance with Airbus
Lhorne on DSK30JT082PROD with PROPOSALS
(c) Applicability Service Bulletin A300–53–229, Revision 5, (j) Retained Fuselage Inner Doubler
This AD applies to Airbus Model A300 B2– dated April 8, 1997. Inspections and Repair, With No Changes
1C, A300 B2–203, A300 B2K–3C, A300–B4– This paragraph restates the requirements of
103, A300 B4–203, and A300 B4–2C (h) Retained Repetitive Intervals for paragraph (n) of AD 2011–17–05, with no
airplanes; certificated in any category; all Inspections for Disbonding and Cracking changes. For airplanes on which any
manufacturer serial numbers, except those on This paragraph restates the repetitive inspections of the fuselage bonded inner
which Airbus Modification 2611 has been intervals specified in table 1 of AD 2011–17– doublers of the longitudinal lap joints in
embodied in production. 05. At the applicable time specified in Sections 16 and 17 at Stringer 31 left-hand
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![Federal Register / Vol. 81, No. 130 / Thursday, July 7, 2016 / Proposed Rules 44235
and right-hand for disbonding and cracking Bulletin A300–53–229, Revision 5, dated accomplished using a method approved by
have not been done as of November 16, 2011 April 8, 1997, is found: Repeat the inspection the Manager, International Branch, ANM–
(the effective date of AD 2011–17–05), as thereafter at intervals not to exceed 1 year for 116, Transport Airplane Directorate, FAA; or
specified in Airbus Service Bulletin A300– areas below stringer 22, and at intervals not the EASA; or Airbus’s EASA DOA. If
53–229: Prior to the accumulation of 24,000 to exceed 2 years for areas above and approved by the DOA, the approval must
total flight cycles or within 12 years since including stringer 22. Doing a repair, in include the DOA-authorized signature.
new, whichever occurs first; or within 60 accordance with Airbus Service Bulletin
days after November 16, 2011, whichever A300–53–229, Revision 5, dated April 8, (n) Related Information
occurs later, do a detailed inspection of the 1997, terminates the repetitive inspections (1) Refer to Mandatory Continuing
fuselage bonded inner doubles of the required by this paragraph for that area. Airworthiness Information (MCAI) EASA
longitudinal lap joints in Sections 16 and 17 (2) If no cracking is found, and ‘‘major’’ Airworthiness Directive 2014–0265, dated
at Stringer 31 left-hand and right-hand for disbonding, as defined in Airbus Service December 9, 2014, for related information.
disbonding and cracking, in accordance with Bulletin A300–53–229, Revision 5, dated This MCAI may be found in the AD docket
the Accomplishment Instructions of Airbus April 8, 1997, is found: Within 1,000 flight on the Internet at http://www.regulations.gov
Service Bulletin A300–53–229, Revision 5, cycles after doing the inspection, repair, in by searching for and locating Docket No.
dated April 8, 1997. If no disbonding and no accordance with the Accomplishment FAA–2016–7425.
cracking are found, repeat the inspection Instructions of Airbus Service Bulletin A300– (2) For service information identified in
thereafter at intervals not to exceed 7 years 53–229, Revision 5, dated April 8, 1997. this AD, contact Airbus SAS, Airworthiness
or 12,000 flight cycles, whichever occurs (3) If any cracking is found, repair prior to Office—EAW, 1 Rond Point Maurice
first. further flight, in accordance with Airbus Bellonte, 31707 Blagnac Cedex, France;
(1) If no cracking is found, and ‘‘minor’’ Service Bulletin A300–53–229, Revision 5, telephone +33 5 61 93 36 96; fax +33 5 61
disbonding, as defined in Airbus Service dated April 8, 1997. 93 44 51; email account.airworth-eas@
Bulletin A300–53–229, Revision 5, dated airbus.com; Internet http://www.airbus.com.
April 8, 1997, is found: Repeat the inspection (l) New Repetitive Inspections and Repair You may view this service information at the
thereafter at intervals not to exceed 1 year for Within 180 days after the effective date of FAA, Transport Airplane Directorate, 1601
areas below stringer 22, and at intervals not this AD, do rototest and ultrasonic Lind Avenue SW., Renton, WA. For
to exceed 2 years for areas above and inspections, as applicable, for cracking of all information on the availability of this
including stringer 22. Doing a repair in longitudinal lap joints and repairs between material at the FAA, call 425–227–1221.
accordance with Airbus Service Bulletin frames 18 and 80; and repair any cracking
Issued in Renton, Washington, on June 23,
A300–53–229, Revision 5, dated April 8, before further flight; using a method
2016.
1997, terminates the repetitive inspections approved by the Manager, International
required by this paragraph for that area. Branch, ANM–116, Transport Airplane Dorr M. Anderson,
(2) If no cracking is found, and ‘‘major’’ Directorate, FAA; or the European Aviation Acting Manager, Transport Airplane
disbonding, as defined in Airbus Service Safety Agency (EASA); or Airbus’s EASA Directorate, Aircraft Certification Service.
Bulletin A300–53–229, Revision 5, dated Design Organization Approval (DOA). Repeat [FR Doc. 2016–15910 Filed 7–6–16; 8:45 am]
April 8, 1997, is found: Within 1,000 flight the applicable inspection, including post- BILLING CODE 4910–13–P
cycles after doing the inspection, repair, in repair inspections, thereafter at intervals
accordance with the Accomplishment approved by the Manager, International
Instructions of Airbus Service Bulletin A300– Branch, ANM–116, Transport Airplane
DEPARTMENT OF TRANSPORTATION
53–229, Revision 5, dated April 8, 1997. Directorate, FAA; or EASA; or Airbus’s EASA
(3) If any cracking is found, repair prior to DOA. Accomplishing the initial inspection
Federal Aviation Administration
further flight, in accordance with Airbus and applicable repairs required by this
Service Bulletin A300–53–229, Revision 5, paragraph terminates the actions required by
dated April 8, 1997. paragraphs (g) through (k) of this AD. 14 CFR Part 39
(k) Retained Fuselage Inner Doubler (m) Other FAA AD Provisions [Docket No. FAA–2016–7424; Directorate
Inspections and Repair, With No Changes Identifier 2015–NM–173–AD]
The following provisions also apply to this
This paragraph restates the requirements of AD: RIN 2120–AA64
paragraph (o) of AD 2011–17–05, with no (1) Alternative Methods of Compliance
changes. For airplanes on which any (AMOCs): The Manager, International Airworthiness Directives; Airbus
inspections of the fuselage bonded inner Branch, ANM–116, Transport Airplane Airplanes
doublers of the longitudinal lap joints in Directorate, FAA, has the authority to
Sections 16 and 17 at Stringer 31 left-hand approve AMOCs for this AD, if requested AGENCY: Federal Aviation
and right-hand for disbonding and cracking using the procedures found in 14 CFR 39.19. Administration (FAA), DOT.
have been done as of November 16, 2011, as In accordance with 14 CFR 39.19, send your ACTION: Notice of proposed rulemaking
specified in Airbus Service Bulletin A300– request to your principal inspector or local (NPRM).
53–229; except airplanes on which a repair Flight Standards District Office, as
of that area has been done as specified in appropriate. If sending information directly SUMMARY: We propose to adopt a new
Airbus Service Bulletin A300–53–229: to the International Branch, send it to ATTN: airworthiness directive (AD) for all
Within 7 years or 12,000 flight cycles after Dan Rodina, Aerospace Engineer,
Airbus Model A330–200, –200
doing the inspection, whichever occurs first; International Branch, ANM–116, Transport
or within 60 days after November 16, 2011; Airplane Directorate, FAA, 1601 Lind Freighter, and –300 series airplanes; and
whichever occurs later; do a detailed Avenue SW., Renton, WA 98057–3356; Model A340–200, –300, –500, and –600
inspection of the fuselage bonded inner telephone 425–227–2125; fax 425–227–1149. series airplanes. This proposed AD was
doubles of the longitudinal lap joints in Information may be emailed to: 9-ANM-116- prompted by a determination that, due
Sections 16 and 17 at Stringer 31 left-hand AMOC-REQUESTS@faa.gov. Before using to significant differences among all
and right-hand for disbonding and cracking, any approved AMOC, notify your appropriate airspeed sources, the flight controls will
in accordance with the Accomplishment principal inspector, or lacking a principal revert to alternate law, the autopilot
Lhorne on DSK30JT082PROD with PROPOSALS
Instructions of Airbus Service Bulletin A300– inspector, the manager of the local flight (AP) and the auto-thrust (A/THR) will
53–229, Revision 5, dated April 8, 1997. If no standards district office/certificate holding
automatically disconnect, and the flight
disbonding and no corrosion are found, district office. The AMOC approval letter
repeat the inspection thereafter at intervals must specifically reference this AD. director (FD) bars will be automatically
not to exceed 7 years or 12,000 flight cycles, (2) Contacting the Manufacturer: As of the removed. Then, if two airspeed sources
whichever occurs first. effective date of this AD, for any requirement become similar while still erroneous,
(1) If no cracking is found, and ‘‘minor’’ in this AD to obtain corrective actions from the flight guidance computers will
disbonding, as defined in Airbus Service a manufacturer, the action must be display the FD bars again, and enable
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Document Created: 2018-02-08 07:54:27
Document Modified: 2018-02-08 07:54:27
| 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 August 22, 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 44232 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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