80 FR 32058 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 108 (June 5, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 108 (June 5, 2015)
| Page Range | 32058-32061 | |
| FR Document | 2015-13335 |
[Federal Register Volume 80, Number 108 (Friday, June 5, 2015)] [Proposed Rules] [Pages 32058-32061] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-13335] [[Page 32058]] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1426; Directorate Identifier 2013-NM-200-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) 97-20-07, for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 97-20-07 requires repetitive inspections to detect fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar, and repair or modification of this area if necessary. Since we issued AD 97-20-07, we have determined that the inspection compliance time and repetitive inspection interval must be reduced to allow timely detection of cracking in the left and right wings in the area where the top skin attaches to the center spar. This proposed AD would reduce the inspection compliance time and repetitive inspection intervals. We are proposing this AD to detect and correct this cracking, which could reduce the residual strength of the top skin of the wings, and consequently affect the structural integrity of the airframe. DATES: We must receive comments on this proposed AD by July 20, 2015. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: (202) 493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 1426; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-1426; Directorate Identifier 2013-NM-200-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 17, 1997, we issued AD 97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997). AD 97-20-07 requires actions intended to address an unsafe condition on the products listed above. Since we issued AD 97-20-07, we have determined that the inspection compliance time and repetitive inspection interval must be reduced to allow timely detection of cracking in the left and right wings in the area where the top skin attaches to the center spar. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013-0221, dated September 19, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4- 605R Variant F airplanes (collectively called Model A300-600 series airplanes). The MCAI states: During fatigue tests conducted in the early 1990's, cracks were found on the top skin of the wing at the centre spar joint between ribs 1 and 7. Consequently, Airbus developed production mod. 10089 and issued Service Bulletin (SB) A300-57-6041, involving installation of a reinforcing plate on the affected area. Despite this improvement, subsequent cases of cracks were reported by operators. This condition, if not detected and corrected, could adversely affect the structural integrity of the aeroplane. To address this potential unsafe condition, Airbus issued SB A300-57-6044 and DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 95-086-180 (later revised twice) to require repetitive inspections of the affected area and, depending on findings, accomplishment of applicable corrective action(s). Since [DGAC] AD 1995-086-180(B)R2 [which corresponds to FAA AD 97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997)] was issued, a fleet survey and updated Fatigue and Damage Tolerance Analyses were performed in order to substantiate the second A300-600 Extended Service Goal (ESG2) exercise. The results of these analyses have shown that the inspection thresholds and intervals must be reduced to allow timely detection of these cracks and accomplishment of an applicable corrective action. Prompted by these findings, Airbus issued SB A300-57-6044 Revision 04 [dated August 19, 2011]. For the reasons described above, this [EASA] AD retains the requirements of DGAC France AD 1995-086-180(B)R2, which is superseded, but requires the repetitive inspections to be accomplished at reduced thresholds and intervals and, depending on findings, corrective actions. 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-2015-1426. [[Page 32059]] Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011. The service information describes procedures for inspections to detect fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar, and repair or modification of this area. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance We estimate that this proposed AD affects 47 airplanes of U.S. registry. The actions that are required by AD 97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997), and retained in this proposed AD take about 3 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that were required by AD 97-20-07 is $255 per product. We also estimate that it would take about 5 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $19,975, or $425 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national 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) 97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997), and adding the following new AD: Airbus: Docket No. FAA-2015-1426; Directorate Identifier 2013-NM- 200-AD. (a) Comments Due Date We must receive comments by July 20, 2015. (b) Affected ADs This AD replaces AD 97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers except those on which Airbus Modification 10160 has been done in production. (1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes. (2) Airbus Model A300 B4-605R and B4-622R airplanes. (3) Airbus Model A300 F4-605R and F4-622R airplanes. (4) Airbus Model A300 C4-605R Variant F airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a determination that the inspection compliance time and repetitive inspection interval must be reduced to allow timely detection of cracking in the left and right wings in the area where the top skin attaches to the center spar. We are issuing this AD to detect and correct this cracking, which could reduce the residual strength of the top skin of the wings, and consequently affect the structural integrity of the airframe. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Repetitive Inspections and Corrective Actions With Revised Service information This paragraph restates the requirements of paragraph (a) of AD 97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997), with revised service information. For airplanes on which Airbus Modification 10089 has not been installed: Prior to the accumulation of 18,000 total landings, or within 1,500 landings after October 30, 1997 (the effective date of AD 97-20-07), whichever occurs later, conduct either a detailed visual inspection or a high frequency eddy current (HFEC) inspection to detect fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar between ribs 1 and 7, in accordance with Airbus Service Bulletin A300-57-6044, Revision 02, dated September 6, 1995, including Appendix 1; or Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57- 6044, Revision 04, including Appendix 01, dated August 19, 2011. Accomplishment of the inspection required by paragraph (i) of this AD terminates the inspection requirements of this paragraph. [[Page 32060]] (1) If no cracking is detected, conduct repetitive inspections thereafter at the following intervals: (i) If the immediately preceding inspection was conducted using detailed visual techniques, conduct the next inspection within 5,000 landings. (ii) If the immediately preceding inspection was conducted using HFEC techniques, conduct the next inspection within 9,500 landings. (2) If any cracking is detected or suspected during any detailed visual inspection required by paragraph (g), (g)(1), or (g)(3)(i) of this AD, prior to further flight, confirm this finding and the length of this cracking by conducting an HFEC inspection, in accordance with Airbus Service Bulletin A300-57-6044, Revision 02, dated September 6, 1995, including Appendix 01; or Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011. If no cracking is confirmed during the HFEC inspection, accomplish the repetitive inspection required by paragraph (g)(1)(ii) of this AD at the time specified in that paragraph. (3) If any cracking is detected or confirmed during any HFEC inspection required by paragraph (g), (g)(1), or (g)(2) of this AD: (i) If the cracking is 75 millimeters (mm) or less per rib bay, prior to further flight, repair in accordance with Airbus Service Bulletin A300-57-6044, Revision 02, dated September 6, 1995, including Appendix 01; or Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57- 6044, Revision 04, including Appendix 01, dated August 19, 2011. Thereafter, conduct repetitive detailed visual inspections of the repaired area at intervals not to exceed 50 landings, in accordance with Airbus Service Bulletin A300-57-6044, Revision 02, dated September 6, 1995, including Appendix 01; or Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011. (ii) If the cracking exceeds 75 mm per rib bay, prior to further flight, install Airbus Modification 10089, in accordance with Airbus Service Bulletin A300-57-6044, Revision 02, dated September 6, 1995, including Appendix 01; or Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57- 6044, Revision 04, including Appendix 01, dated August 19, 2011. Thereafter, conduct a low frequency eddy current inspection in accordance with the requirements of paragraph (h) of this AD. Note 1 to paragraph (g) of this AD: Airbus Service Bulletin A300-57-6044, Revision 02, dated September 6, 1995, including Appendix 01 references Airbus Service Bulletin A300-57-6041, Revision 04, dated November 16, 1995, as an additional source of guidance for installing Airbus Modification 10089. (h) Retained Repetitive Inspections and Corrective Actions for Certain Airplanes with Revised Service Information and Repair Instructions This paragraph restates the requirements of paragraph (b) of AD 97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997), with revised service information and repair instructions. For airplanes on which Airbus Modification 10089 has been installed: Prior to the accumulation of 22,000 total landings after this modification has been installed, or within 1,500 landings after October 30, 1997 (the effective date of AD 97-20-07), whichever occurs later, conduct a low frequency eddy current (LFEC) inspection to detect fatigue cracking in the inboard and rear edges of the top skin reinforcing plates, in accordance with Airbus Service Bulletin A300-57-6044, Revision 02, dated September 6, 1995, including Appendix 01; or Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011. Accomplishment of the inspection required by paragraph (k) of this AD terminates the inspection requirements of this paragraph. (1) If no cracking is detected, repeat this inspection thereafter at intervals not to exceed 11,000 landings. (2) If any cracking is detected, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. As of the effective date of this AD, 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). Thereafter, repeat this inspection at intervals not to exceed 11,000 landings. (i) New Requirement of This AD: Initial Inspections For airplanes on which Airbus Modification 10089 has not been installed: At the applicable time specified in paragraphs (i)(1) and (i)(2) of this AD, do either a detailed visual inspection or an HFEC inspection to detect fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar between ribs 1 and 7, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011. Accomplishment of the inspection required by this paragraph terminates the inspection requirements of paragraph (g) of this AD. (1) For airplanes whose flight time average is equal to or more than 1.5 hours, at the later of the times specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. (i) Before the accumulation of 14,000 total flight cycles or 30,300 total flight hours, whichever occurs first. (ii) Within 1,500 flight cycles or 3,200 flight hours after the effective date of this AD, whichever occurs first. (2) For airplanes whose flight time average is less than 1.5 hours, at the later of the times specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD. (i) Before the accumulation of 15,100 total flight cycles or 22,700 total flight hours, whichever occurs first. (ii) Within 1,600 flight cycles or 2,500 flight hours after the effective date of this AD, whichever occurs first. (j) New Requirement of This AD: Repetitive Inspections Repeat the inspections specified in paragraph (i) of this AD thereafter at the applicable interval specified in paragraphs (j)(1) and (j)(2) of this AD. (1) For airplanes whose flight time average is equal to or more than 1.5 hours, at the applicable interval specified in paragraphs (j)(1)(i) and (j)(1)(ii) of this AD. (i) For a detailed inspection, at intervals not to exceed 3,900 flight cycles or 8,400 flight hours, whichever occurs first. (ii) For an HFEC inspection, at intervals not to exceed 7,400 flight cycles or 16,000 flight hours, whichever occurs first. (2) For airplanes whose flight time average is less than 1.5 hours at the applicable interval specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD. (i) For a detailed inspection, at intervals not to exceed 4,200 flight cycles or 6,300 flight hours, whichever occurs first. (ii) For an HFEC inspection, at intervals not to exceed 8,000 flight cycles or 11,900 flight hours, whichever occurs first. (k) New Requirement of This AD: Initial Inspection for Certain Airplanes For airplanes on which Airbus Modification 10089 has been installed: At the applicable time specified in paragraphs (k)(1) and (k)(2) of this AD, do an LFEC inspection to detect fatigue cracking in the inboard and rear edges of the top skin reinforcing plates, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011. Accomplishment of the inspection required by this paragraph terminates the inspection requirements of paragraph (h) of this AD. (1) For airplanes whose flight time average is equal to or more than 1.5 hours, at the later of the times specified in paragraphs (k)(1)(i) and (k)(1)(ii) of this AD. (i) Before the accumulation of 17,000 total flight cycles or 37,100 total flight hours, whichever occurs first. (ii) Within 1,500 flight cycles or 3,200 flight hours after the effective date of this AD, whichever occurs first. (2) For airplanes whose flight time average is less than 1.5 hours, at the later of the times specified in paragraphs (k)(2)(i) and (k)(2)(ii) of this AD. (i) Before the accumulation of 18,500 total flight cycles or 27,800 total flight hours, whichever occurs first. (ii) Within 1,600 flight cycles or 2,500 flight hours after the effective date of this AD, whichever occurs first. [[Page 32061]] (l) New Requirement of This AD: Repetitive Inspections for Certain Airplanes Repeat the inspection specified in paragraph (k) of this AD thereafter at the applicable interval specified in paragraphs (l)(1) and (l)(2) of this AD. (1) For airplanes whose flight time average is equal to or more than 1.5 hours, at intervals not to exceed 8,500 flight cycles or 18,500 flight hours, whichever occurs first. (2) For airplanes whose flight time average is less than 1.5 hours, at intervals not to exceed 9,200 flight cycles or 13,700 flight hours, whichever occurs first. (m) New Requirement of This AD: Corrective Actions (1) If any cracking is detected or suspected during any detailed visual inspection required by paragraph (i) or (j) of this AD: Before further flight, confirm this finding and the length of this cracking by conducting an HFEC inspection, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011, except as specified in paragraph (o) of this AD. If no cracking is confirmed during the HFEC inspection, accomplish the applicable repetitive inspections required by paragraphs (j) and (l) of this AD at the applicable time specified in those paragraphs. (2) If any cracking is found during any HFEC inspection required by paragraph (i), (j), (k) or (l) of this AD: Before further flight, do the applicable actions specified in paragraphs (m)(2)(i) and (m)(2)(ii) of this AD. (i) If the cracking is 75 mm or less per each rib bay: Before further flight, repair the cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011, except as specified in paragraph (o) of this AD. Do repetitive detailed visual inspections of the repaired area thereafter at intervals not to exceed 50 flight cycles or 110 flight hours, whichever occurs first, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011. Within 250 flight cycles or 550 flight hours, whichever occurs first after doing the temporary repair, do a permanent repair of the repaired area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011. (ii) If the cracking exceeds 75 mm per any rib bay: Before further flight, install Airbus Modification 10089, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011. Do an LFEC inspection thereafter at the intervals specified in paragraph (l) of this AD. (3) If any cracking is found during any inspection required by this AD at fastener holes 1A, 1, or 2: Before further flight, repair the cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011. (n) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (i) through (l) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300-57-6044, Revision 03, dated April 7, 1999, including Appendix 01, which is not incorporated by reference in this AD. (o) Exception to Service Information Specification Although Airbus Service Bulletin A300-57-6044, Revision 04, including Appendix 01, dated August 19, 2011, specifies to submit information to Airbus, this AD does not require that submission. (p) 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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 EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013-0221, dated September 19, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-1426. (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 account.airworth-eas@airbus.com; 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 May 19, 2015. Dionne Palmero, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-13335 Filed 6-4-15; 8:45 am] BILLING CODE 4910-13-P
![32058 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules
DEPARTMENT OF TRANSPORTATION Point Maurice Bellonte, 31707 Blagnac the inspection compliance time and
Cedex, France; telephone +33 5 61 93 36 repetitive inspection interval must be
Federal Aviation Administration 96; fax +33 5 61 93 44 51; email reduced to allow timely detection of
account.airworth-eas@airbus.com; cracking in the left and right wings in
14 CFR Part 39 Internet http://www.airbus.com. You the area where the top skin attaches to
[Docket No. FAA–2015–1426; Directorate may view this referenced service the center spar.
Identifier 2013–NM–200–AD] information at the FAA, Transport The European Aviation Safety Agency
Airplane Directorate, 1601 Lind Avenue (EASA), which is the Technical Agent
RIN 2120–AA64 SW., Renton, WA. For information on for the Member States of the European
the availability of this material at the Union, has issued EASA Airworthiness
Airworthiness Directives; Airbus FAA, call 425–227–1221.
Airplanes Directive 2013–0221, dated September
Examining the AD Docket 19, 2013 (referred to after this as the
AGENCY: Federal Aviation Mandatory Continuing Airworthiness
Administration (FAA), DOT. You may examine the AD docket on
the Internet at http:// Information, or ‘‘the MCAI’’), to correct
ACTION: Notice of proposed rulemaking an unsafe condition for certain Airbus
www.regulations.gov by searching for
(NPRM). and locating Docket No. FAA–2015– Model A300 B4–600, B4–600R, and F4–
1426; or in person at the Docket 600R series airplanes, and Model A300
SUMMARY: We propose to supersede C4–605R Variant F airplanes
Airworthiness Directive (AD) 97–20–07, Management Facility between 9 a.m.
and 5 p.m., Monday through Friday, (collectively called Model A300–600
for certain Airbus Model A300 B4–600, series airplanes). The MCAI states:
B4–600R, and F4–600R series airplanes, except Federal holidays. The AD docket
and Model A300 C4–605R Variant F contains this proposed AD, the During fatigue tests conducted in the early
airplanes (collectively called Model regulatory evaluation, any comments 1990’s, cracks were found on the top skin of
received, and other information. The the wing at the centre spar joint between ribs
A300–600 series airplanes). AD 97–20–
street address for the Docket Operations 1 and 7.
07 requires repetitive inspections to Consequently, Airbus developed
detect fatigue cracking in the left and office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will production mod. 10089 and issued Service
right wings in the area where the top Bulletin (SB) A300–57–6041, involving
skin attaches to the center spar, and be available in the AD docket shortly
after receipt. installation of a reinforcing plate on the
repair or modification of this area if affected area. Despite this improvement,
necessary. Since we issued AD 97–20– FOR FURTHER INFORMATION CONTACT: Dan subsequent cases of cracks were reported by
07, we have determined that the Rodina, Aerospace Engineer, operators.
inspection compliance time and International Branch, ANM–116, This condition, if not detected and
repetitive inspection interval must be Transport Airplane Directorate, FAA, corrected, could adversely affect the
reduced to allow timely detection of 1601 Lind Avenue SW., Renton, WA structural integrity of the aeroplane.
cracking in the left and right wings in 98057–3356; telephone 425–227–2125; To address this potential unsafe condition,
the area where the top skin attaches to fax 425–227–1149. Airbus issued SB A300–57–6044 and DGAC
SUPPLEMENTARY INFORMATION: [Direction Générale de l’Aviation Civile]
the center spar. This proposed AD
France issued AD 95–086–180 (later revised
would reduce the inspection Comments Invited twice) to require repetitive inspections of the
compliance time and repetitive affected area and, depending on findings,
inspection intervals. We are proposing We invite you to send any written
relevant data, views, or arguments about accomplishment of applicable corrective
this AD to detect and correct this action(s).
cracking, which could reduce the this proposed AD. Send your comments
to an address listed under the Since [DGAC] AD 1995–086–180(B)R2
residual strength of the top skin of the [which corresponds to FAA AD 97–20–07,
ADDRESSES section. Include ‘‘Docket No.
wings, and consequently affect the Amendment 39–10145 (62 FR 50251,
FAA–2015–1426; Directorate Identifier
structural integrity of the airframe. September 25, 1997)] was issued, a fleet
2013–NM–200–AD’’ at the beginning of survey and updated Fatigue and Damage
DATES: We must receive comments on your comments. We specifically invite
this proposed AD by July 20, 2015. Tolerance Analyses were performed in order
comments on the overall regulatory, to substantiate the second A300–600
ADDRESSES: You may send comments by economic, environmental, and energy Extended Service Goal (ESG2) exercise. The
any of the following methods: aspects of this proposed AD. We will results of these analyses have shown that the
• Federal eRulemaking Portal: Go to consider all comments received by the inspection thresholds and intervals must be
http://www.regulations.gov. Follow the closing date and may amend this reduced to allow timely detection of these
instructions for submitting comments. proposed AD based on those comments. cracks and accomplishment of an applicable
• Fax: (202) 493–2251. We will post all comments we corrective action.
• Mail: U.S. Department of receive, without change, to http:// Prompted by these findings, Airbus issued
Transportation, Docket Operations, www.regulations.gov, including any SB A300–57–6044 Revision 04 [dated August
M–30, West Building Ground Floor, personal information you provide. We 19, 2011].
Room W12–140, 1200 New Jersey For the reasons described above, this
will also post a report summarizing each
Avenue SE., Washington, DC 20590. [EASA] AD retains the requirements of DGAC
substantive verbal contact we receive France AD 1995–086–180(B)R2, which is
• Hand Delivery: U.S. Department of about this proposed AD.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
superseded, but requires the repetitive
Transportation, Docket Operations, inspections to be accomplished at reduced
M–30, West Building Ground Floor, Discussion
thresholds and intervals and, depending on
Room W12–140, 1200 New Jersey On September 17, 1997, we issued AD findings, corrective actions.
Avenue SE., Washington, DC, between 9 97–20–07, Amendment 39–10145 (62
a.m. and 5 p.m., Monday through FR 50251, September 25, 1997). AD 97– You may examine the MCAI in the
Friday, except Federal holidays. 20–07 requires actions intended to AD docket on the Internet at http://
For service information identified in address an unsafe condition on the www.regulations.gov by searching for
this proposed AD, contact Airbus SAS, products listed above. Since we issued and locating it in Docket No. FAA–
Airworthiness Office—EAW, 1 Rond AD 97–20–07, we have determined that 2015–1426.
VerDate Sep<11>2014 17:42 Jun 04, 2015 Jkt 235001 PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 E:\FR\FM\05JNP1.SGM 05JNP1](https://thefederalregister.org/doc/80_FR_32166/page/1.svg)
![Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 32059
Related Service Information Under 1 detail the scope of the Agency’s (a) Comments Due Date
CFR Part 51 authority. We must receive comments by July 20,
Airbus has issued Service Bulletin We are issuing this rulemaking under 2015.
A300–57–6044, Revision 04, including the authority described in ‘‘Subtitle VII, (b) Affected ADs
Appendix 01, dated August 19, 2011. Part A, Subpart III, Section 44701:
General requirements.’’ Under that This AD replaces AD 97–20–07,
The service information describes Amendment 39–10145 (62 FR 50251,
procedures for inspections to detect section, Congress charges the FAA with September 25, 1997).
fatigue cracking in the left and right promoting safe flight of civil aircraft in
air commerce by prescribing regulations (c) Applicability
wings in the area where the top skin
attaches to the center spar, and repair or for practices, methods, and procedures This AD applies to the Airbus airplanes
the Administrator finds necessary for identified in paragraphs (c)(1) through (c)(4)
modification of this area. The actions of this AD, certificated in any category, all
described in this service information are safety in air commerce. This regulation
is within the scope of that authority manufacturer serial numbers except those on
intended to correct the unsafe condition which Airbus Modification 10160 has been
identified in the MCAI. This service because it addresses an unsafe condition
done in production.
information is reasonably available that is likely to exist or develop on (1) Airbus Model A300 B4–601, B4–603,
because the interested parties have products identified in this rulemaking B4–620, and B4–622 airplanes.
access to it through their normal course action. (2) Airbus Model A300 B4–605R and B4–
of business or by the means identified 622R airplanes.
Regulatory Findings
(3) Airbus Model A300 F4–605R and F4–
in the ADDRESSES section of this NPRM. We determined that this proposed AD 622R airplanes.
FAA’s Determination and Requirements would not have federalism implications (4) Airbus Model A300 C4–605R Variant F
of This Proposed AD under Executive Order 13132. This airplanes.
This product has been approved by proposed AD would not have a (d) Subject
the aviation authority of another substantial direct effect on the States, on Air Transport Association (ATA) of
country, and is approved for operation the relationship between the national America Code 57, Wings.
in the United States. Pursuant to our Government and the States, or on the
distribution of power and (e) Reason
bilateral agreement with the State of
Design Authority, we have been notified responsibilities among the various This AD was prompted by a determination
levels of government. that the inspection compliance time and
of the unsafe condition described in the repetitive inspection interval must be
For the reasons discussed above, I
MCAI and service information reduced to allow timely detection of cracking
certify this proposed regulation:
referenced above. We are proposing this 1. Is not a ‘‘significant regulatory in the left and right wings in the area where
AD because we evaluated all pertinent action’’ under Executive Order 12866; the top skin attaches to the center spar. We
information and determined an unsafe are issuing this AD to detect and correct this
2. Is not a ‘‘significant rule’’ under the cracking, which could reduce the residual
condition exists and is likely to exist or DOT Regulatory Policies and Procedures
develop on other products of the same strength of the top skin of the wings, and
(44 FR 11034, February 26, 1979); consequently affect the structural integrity of
type design. 3. Will not affect intrastate aviation in the airframe.
Costs of Compliance Alaska; and
4. Will not have a significant (f) Compliance
We estimate that this proposed AD economic impact, positive or negative, Comply with this AD within the
affects 47 airplanes of U.S. registry. on a substantial number of small entities compliance times specified, unless already
The actions that are required by AD under the criteria of the Regulatory done.
97–20–07, Amendment 39–10145 (62 Flexibility Act. (g) Retained Repetitive Inspections and
FR 50251, September 25, 1997), and Corrective Actions With Revised Service
retained in this proposed AD take about List of Subjects in 14 CFR Part 39 information
3 work-hours per product, at an average Air transportation, Aircraft, Aviation This paragraph restates the requirements of
labor rate of $85 per work-hour. Based safety, Incorporation by reference, paragraph (a) of AD 97–20–07, Amendment
on these figures, the estimated cost of Safety. 39–10145 (62 FR 50251, September 25, 1997),
the actions that were required by AD with revised service information. For
97–20–07 is $255 per product. The Proposed Amendment airplanes on which Airbus Modification
We also estimate that it would take Accordingly, under the authority 10089 has not been installed: Prior to the
about 5 work-hours per product to delegated to me by the Administrator, accumulation of 18,000 total landings, or
comply with the basic requirements of the FAA proposes to amend 14 CFR part within 1,500 landings after October 30, 1997
this proposed AD. The average labor 39 as follows: (the effective date of AD 97–20–07),
whichever occurs later, conduct either a
rate is $85 per work-hour. Based on
PART 39—AIRWORTHINESS detailed visual inspection or a high
these figures, we estimate the cost of frequency eddy current (HFEC) inspection to
this proposed AD on U.S. operators to DIRECTIVES detect fatigue cracking in the left and right
be $19,975, or $425 per product. wings in the area where the top skin attaches
We have received no definitive data ■ 1. The authority citation for part 39 to the center spar between ribs 1 and 7, in
that would enable us to provide cost continues to read as follows: accordance with Airbus Service Bulletin
estimates for the on-condition actions Authority: 49 U.S.C. 106(g), 40113, 44701. A300–57–6044, Revision 02, dated
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
specified in this proposed AD. September 6, 1995, including Appendix 1; or
§ 39.13 [Amended] Airbus Service Bulletin A300–57–6044,
Authority for This Rulemaking ■ 2. The FAA amends § 39.13 by Revision 04, including Appendix 01, dated
Title 49 of the United States Code removing Airworthiness Directive (AD) August 19, 2011. As of the effective date of
97–20–07, Amendment 39–10145 (62 this AD, use only Airbus Service Bulletin
specifies the FAA’s authority to issue A300–57–6044, Revision 04, including
rules on aviation safety. Subtitle I, FR 50251, September 25, 1997), and
Appendix 01, dated August 19, 2011.
section 106, describes the authority of adding the following new AD: Accomplishment of the inspection required
the FAA Administrator. ‘‘Subtitle VII: Airbus: Docket No. FAA–2015–1426; by paragraph (i) of this AD terminates the
Aviation Programs,’’ describes in more Directorate Identifier 2013–NM–200–AD. inspection requirements of this paragraph.
VerDate Sep<11>2014 17:42 Jun 04, 2015 Jkt 235001 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 E:\FR\FM\05JNP1.SGM 05JNP1](https://thefederalregister.org/doc/80_FR_32166/page/2.svg)
![Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 32061
(l) New Requirement of This AD: Repetitive (n) Credit for Previous Actions Issued in Renton, Washington, on May 19,
Inspections for Certain Airplanes This paragraph provides credit for actions 2015.
Repeat the inspection specified in required by paragraphs (i) through (l) of this Dionne Palmero,
paragraph (k) of this AD thereafter at the AD, if those actions were performed before Acting Manager, Transport Airplane
applicable interval specified in paragraphs the effective date of this AD using Airbus Directorate, Aircraft Certification Service.
(l)(1) and (l)(2) of this AD. Service Bulletin A300–57–6044, Revision 03,
dated April 7, 1999, including Appendix 01, [FR Doc. 2015–13335 Filed 6–4–15; 8:45 am]
(1) For airplanes whose flight time average
is equal to or more than 1.5 hours, at which is not incorporated by reference in this BILLING CODE 4910–13–P
intervals not to exceed 8,500 flight cycles or AD.
18,500 flight hours, whichever occurs first.
(o) Exception to Service Information
(2) For airplanes whose flight time average DEPARTMENT OF TRANSPORTATION
is less than 1.5 hours, at intervals not to Specification
exceed 9,200 flight cycles or 13,700 flight Although Airbus Service Bulletin A300– Federal Aviation Administration
hours, whichever occurs first. 57–6044, Revision 04, including Appendix
01, dated August 19, 2011, specifies to 14 CFR Part 39
(m) New Requirement of This AD: Corrective submit information to Airbus, this AD does
Actions not require that submission. [Docket No. FAA–2015–1423; Directorate
(1) If any cracking is detected or suspected Identifier 2014–NM–173–AD]
(p) Other FAA AD Provisions
during any detailed visual inspection
required by paragraph (i) or (j) of this AD: The following provisions also apply to this RIN 2120–AA64
Before further flight, confirm this finding and AD:
the length of this cracking by conducting an (1) Alternative Methods of Compliance Airworthiness Directives; The Boeing
HFEC inspection, in accordance with the (AMOCs): The Manager, International Company Model 757–200 Series
Accomplishment Instructions of Airbus Branch, ANM–116, Transport Airplane Airplanes Modified by Supplemental
Service Bulletin A300–57–6044, Revision 04, Directorate, FAA, has the authority to Type Certificate (STC) ST01529SE or
including Appendix 01, dated August 19, approve AMOCs for this AD, if requested STC ST02278SE
2011, except as specified in paragraph (o) of using the procedures found in 14 CFR 39.19.
this AD. If no cracking is confirmed during In accordance with 14 CFR 39.19, send your AGENCY: Federal Aviation
the HFEC inspection, accomplish the request to your principal inspector or local Administration (FAA), DOT.
applicable repetitive inspections required by Flight Standards District Office, as ACTION: Notice of proposed rulemaking
paragraphs (j) and (l) of this AD at the appropriate. If sending information directly
to the International Branch, send it to ATTN:
(NPRM).
applicable time specified in those
paragraphs. Dan Rodina, Aerospace Engineer, SUMMARY: We propose to adopt a new
(2) If any cracking is found during any International Branch, ANM–116, Transport
airworthiness directive (AD) for certain
HFEC inspection required by paragraph (i), Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356; The Boeing Company Model 757–200
(j), (k) or (l) of this AD: Before further flight,
do the applicable actions specified in telephone 425–227–2125; fax 425–227–1149. series airplanes modified by particular
paragraphs (m)(2)(i) and (m)(2)(ii) of this AD. Information may be emailed to: 9-ANM-116- STCs. This proposed AD was prompted
(i) If the cracking is 75 mm or less per each AMOC-REQUESTS@faa.gov. Before using by reports of a main cargo door being
rib bay: Before further flight, repair the any approved AMOC, notify your appropriate blown past its full open position while
cracking, in accordance with the principal inspector, or lacking a principal on the ground during gusty wind
Accomplishment Instructions of Airbus inspector, the manager of the local flight conditions, which resulted in
Service Bulletin A300–57–6044, Revision 04, standards district office/certificate holding
uncontrolled fall down to its closed
including Appendix 01, dated August 19, district office. The AMOC approval letter
must specifically reference this AD. position. This proposed AD would
2011, except as specified in paragraph (o) of
this AD. Do repetitive detailed visual (2) Contacting the Manufacturer: As of the require installing a new placard and
inspections of the repaired area thereafter at effective date of this AD, for any requirement bracket, replacement of an existing
intervals not to exceed 50 flight cycles or 110 in this AD to obtain corrective actions from placard, and replacement of the main
flight hours, whichever occurs first, in a manufacturer, the action must be cargo door control panel. We are
accordance with the Accomplishment accomplished using a method approved by proposing this AD to prevent damage to
Instructions of Airbus Service Bulletin A300– the Manager, International Branch, ANM– the main cargo door, which could result
57–6044, Revision 04, including Appendix 116, Transport Airplane Directorate, FAA; or in rapid decompression, leading to in-
01, dated August 19, 2011. Within 250 flight EASA; or Airbus’s EASA DOA. If approved
cycles or 550 flight hours, whichever occurs by the DOA, the approval must include the
flight breakup.
first after doing the temporary repair, do a DOA-authorized signature. DATES: We must receive comments on
permanent repair of the repaired area, in this proposed AD by July 20, 2015.
accordance with the Accomplishment (q) Related Information
ADDRESSES: You may send comments,
Instructions of Airbus Service Bulletin A300– (1) Refer to Mandatory Continuing using the procedures found in 14 CFR
57–6044, Revision 04, including Appendix Airworthiness Information (MCAI) EASA
11.43 and 11.45, by any of the following
01, dated August 19, 2011. Airworthiness Directive 2013–0221, dated
(ii) If the cracking exceeds 75 mm per any September 19, 2013, for related information. methods:
rib bay: Before further flight, install Airbus This MCAI may be found in the AD docket • Federal eRulemaking Portal: Go to
Modification 10089, in accordance with the on the Internet at http://www.regulations.gov http://www.regulations.gov. Follow the
Accomplishment Instructions of Airbus by searching for and locating Docket No. instructions for submitting comments.
Service Bulletin A300–57–6044, Revision 04, FAA–2015–1426. • Fax: 202–493–2251.
including Appendix 01, dated August 19, (2) For service information identified in • Mail: U.S. Department of
2011. Do an LFEC inspection thereafter at the this AD, contact Airbus SAS, Airworthiness Transportation, Docket Operations, M–
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
intervals specified in paragraph (l) of this Office—EAW, 1 Rond Point Maurice 30, West Building Ground Floor, Room
AD. Bellonte, 31707 Blagnac Cedex, France; W12–140, 1200 New Jersey Avenue SE.,
(3) If any cracking is found during any telephone +33 5 61 93 36 96; fax +33 5 61
Washington, DC 20590.
inspection required by this AD at fastener 93 44 51; email account.airworth-eas@
• Hand Delivery: Deliver to Mail
holes 1A, 1, or 2: Before further flight, repair airbus.com; Internet http://www.airbus.com.
the cracking, in accordance with the You may view this service information at the address above between 9 a.m. and 5
Accomplishment Instructions of Airbus FAA, Transport Airplane Directorate, 1601 p.m., Monday through Friday, except
Service Bulletin A300–57–6044, Revision 04, Lind Avenue SW., Renton, WA. For Federal holidays.
including Appendix 01, dated August 19, information on the availability of this For service information identified in
2011. material at the FAA, call 425–227–1221. this proposed AD, contact Precision
VerDate Sep<11>2014 17:42 Jun 04, 2015 Jkt 235001 PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 E:\FR\FM\05JNP1.SGM 05JNP1](https://thefederalregister.org/doc/80_FR_32166/page/4.svg)
Document Created: 2015-12-15 15:20:48
Document Modified: 2015-12-15 15:20:48
| 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 July 20, 2015. | |
| Contact | Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. | |
| FR Citation | 80 FR 32058 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2024 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR