81 FR 26677 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 86 (May 4, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 86 (May 4, 2016)
| Page Range | 26677-26680 | |
| FR Document | 2016-08956 |
[Federal Register Volume 81, Number 86 (Wednesday, May 4, 2016)] [Rules and Regulations] [Pages 26677-26680] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-08956] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-5811; Directorate Identifier 2014-NM-158-AD; Amendment 39-18489; AD 2016-08-13] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2004-19-11 for certain Airbus Model A320 series airplanes. AD 2004-19-11 required modification of the inner rear spar web of the wing, cold expansion of the attachment holes of the forward pintle fitting and the actuating cylinder anchorage of the main landing gear (MLG), repetitive ultrasonic inspections for cracking of the rear spar of the wing, and corrective action if necessary. AD 2004-19-11 also provided optional terminating action for the repetitive inspections. This new AD retains the requirements of AD 2004-19-11, and requires the previously optional terminating action. This AD was prompted by a determination that the previously optional terminating action is necessary to address the unsafe condition. We are issuing this AD to prevent fatigue cracking of the inner rear spar, which may lead to reduced structural integrity of the wing and the MLG. DATES: This AD becomes effective June 8, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 8, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 5, 2004 (69 FR 58828, October 1, 2004). The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of June 30, 2000 (65 FR 34069, May 26, 2000). The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 14, 1994 (59 FR 1903, January 13, 1994). The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of June 11, 1993 (58 FR 27923, May 12, 1993). ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office--EIAS, 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 5811. 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- 5811; 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800- 647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004) (``AD 2004-19-11''). AD 2004-19-11 applied to certain Airbus Model 320 series airplanes. The NPRM published in the Federal Register on November 27, 2015 (80 FR 74058) (``the NPRM''). The NPRM was prompted by a determination that the previously optional terminating action is necessary to address the unsafe condition. The NPRM proposed to retain the requirements of AD 2004-19-11, and requires the previously optional terminating action. We are issuing this AD to prevent fatigue cracking of the inner rear spar, which may lead to reduced structural integrity of the wing and the MLG. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0169, dated July 17, 2014, corrected July 22, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on certain Airbus Model 320 series airplanes. The MCAI states: During centre fuselage certification full scale fatigue test, cracks were found on the inner rear spar at holes position 52 on the right hand wing due to fatigue aspects. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To prevent such cracks, Airbus developed modifications, which were introduced in production and in service through several Airbus Service Bulletins (SB). DGAC France issued * * * [an earlier AD], which was subsequently superseded by [DGAC] AD 2001-249 [which corresponds with FAA AD 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004)], to require modification of the rear spar on some [[Page 26678]] aeroplanes, post-modification repetitive inspections and, depending on findings, accomplishment of a repair. DGAC France AD 2001-249 also specified that modification in accordance with Airbus SB A320- 57-1089 (in-service equivalent to Airbus mod 24591) constituted (optional) terminating action for the repetitive inspections. Since that [DGAC] AD [2001-249] was issued, in the framework of the A320 Extended Service Goal (ESG), it has been determined that Airbus mod 24591 is necessary to allow aeroplanes to operate up to the new ESG limit. For the reasons described above, this [EASA] AD retains the requirements of DGAC France AD 2001-249, which is superseded, and requires modification of all pre-mod 24591 aeroplanes. The modification includes modifying all specified fastener holes in the inner rear spar of the wing. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-5811. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. United Airlines provided its support for the content of the NPRM. Explanation of Changes Made to This AD We have added a new paragraph (l)(1) to this AD to provide credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-57-1060, Revision 1, dated April 26, 1993. We have redesignated paragraphs (l)(1) and (l)(2) of the proposed AD as paragraphs (l)(2) and (l)(3) of this AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued Airbus Service Bulletin A320-57-1089, Revision 03, dated February 9, 2001. This service information describes procedures for modification of the airplane by accomplishing cold re- expansion of the holes in the inner rear spar for the attachment of gear rib 5, forward pintle fitting, and actuating cylinder anchorage; and the installation of interference fit fasteners in the rear spar and gear rib 5. 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. Costs of Compliance We estimate that this AD affects 84 airplanes of U.S. registry. The actions required by AD 2004-19-11, and retained in this AD take about 684 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost about $13,644 per product. Based on these figures, the estimated cost of the actions that were required by AD 2004-19-11 is $71,784 per product. We also estimate that it takes about 980 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $32,727 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $9,746,268, or $116,027 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 that this AD: 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004), and adding the following new AD: 2016-08-13 Airbus: Amendment 39-18489. Docket No. FAA-2015-5811; Directorate Identifier 2014-NM-158-AD. (a) Effective Date This AD becomes effective June 8, 2016. (b) Affected ADs This AD replaces AD 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004) (``AD 2004-19-11''). (c) Applicability This AD applies to Airbus Model A320-211, -212, -214, -231, - 232, and -233 airplanes, certificated in any category, all manufacturer serial numbers, except those on which Airbus modification (mod) 24591 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by reports of fatigue cracking of the inner rear spar of the wing and also by a determination that the modification of the inner rear spar is necessary to address the unsafe condition. [[Page 26679]] We are issuing this AD to prevent fatigue cracking of the inner rear spar, which may lead to reduced structural integrity of the wing and the main landing gear (MLG). (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Modification of Inner Rear Spar Web of the Wing, With Change to Acceptable Service Information This paragraph restates the requirements of paragraph (a) of AD 2004-19-11, with a change to acceptable service information. For airplanes having manufacturer's serial numbers (MSNs) 003 through 008 inclusive, and 010 through 021 inclusive, except airplanes modified as specified in Airbus Service Bulletin A320-57-1089, dated December 22, 1996; Revision 01, dated April 17, 1997; Revision 02, dated November 6, 1998; or Revision 03, dated February 9, 2001: Prior to the accumulation of 12,000 total flight cycles, or within 500 flight cycles after June 11, 1993 (the effective date of AD 93- 08-15, Amendment 39-8563 (58 FR 27923, May 12, 1993)), whichever occurs later, modify the inner rear spar web of the wing in accordance with Airbus Service Bulletin A320-57-1004, Revision 1, dated September 24, 1992; or Revision 2, dated June 14, 1993. As of the effective date of this AD, only Airbus Service Bulletin A320-57- 1004, Revision 2, dated June 14, 1993, may be used for the actions required by this paragraph. (h) Retained Cold Expansion of Holes at Forward Pintle Fitting and Actuating Cylinder Anchorage of the Main Landing Gear, With Change to Acceptable Service Information This paragraph restates the requirements of paragraph (b) of AD 2004-19-11, with a change to acceptable service information. For airplanes having MSNs 002 through 051 inclusive, except airplanes modified as specified in Airbus Service Bulletin A320-57-1089, dated December 22, 1996; Revision 01, dated April 17, 1997; Revision 02, dated November 6, 1998; or Revision 03, dated February 9, 2001: Prior to the accumulation of 12,000 total flight cycles, or within 2,000 flight cycles after February 14, 1994 (the effective date of AD 93-25-13, Amendment 39-8777 (59 FR 1903, January 13, 1994)), whichever occurs later, accomplish the requirements of paragraphs (h)(1) and (h)(2) of this AD in accordance with Airbus Service Bulletin A320-57-1060, dated December 8, 1992; Revision 1, dated April 26, 1993; or Revision 2, dated December 16, 1994. As of the effective date of this AD, only Airbus Service Bulletin A320-57- 1060, Revision 2, dated December 16, 1994, may be used for the actions required by this paragraph. (1) Perform a cold expansion of all the attachment holes for the forward pintle fitting of the main landing gear (MLG), except for the holes that are for taper-lok bolts. (2) Perform a cold expansion of the holes at the actuating cylinder anchorage of the MLG. (i) Retained Repetitive Ultrasonic Inspections for Cracking of the Rear Spar of the Wing, With No Changes This paragraph restates the requirements of paragraphs (c), (d), and (e) of AD 2004-19-11, with no changes. Except for airplanes modified as specified in Airbus Service Bulletin A320-57-1089, dated December 22, 1996; Revision 01, dated April 17, 1997; Revision 02, dated November 6, 1998; or Revision 03, dated February 9, 2001: Do the actions specified in paragraphs (i)(1) and (i)(2) of this AD. (1) Do an ultrasonic inspection for cracking of the rear spar of the wing, in accordance with Airbus Service Bulletin A320-57-1088, Revision 04, dated August 6, 2001. Inspect at the applicable time specified in paragraph 1.E. of Airbus Service Bulletin A320-57-1088, Revision 04, dated August 6, 2001, except as required by paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. (i) For any airplane that has not been inspected but has exceeded the applicable specified compliance time in paragraph 1.E. of Airbus Service Bulletin A320-57-1088, Revision 04, dated August 6, 2001, as of November 5, 2004 (the effective date of AD 2004-19- 11): Inspect within 18 months after November 5, 2004. (ii) For any airplane that has been inspected before November 5, 2004 (the effective date of AD 2004-19-11): Repeat the inspection within 3,600 flight cycles after the most recent inspection. (2) Repeat the inspection required by paragraph (i)(1) of this AD at intervals not to exceed 3,600 flight cycles or 6,700 flight hours, whichever occurs first, until the requirements of paragraph (k) of this AD have been done. (j) Retained Corrective Action for Inspections Required by Paragraphs (i)(1) and (i)(2) of This AD, With Specific Delegation Approval Language This paragraph restates the requirements of paragraph (f) of AD 2004-19-11, with specific delegation approval language. If any crack is found during any inspection required by paragraph (i)(1) or (i)(2) of this AD: Before further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM- 116, FAA, Transport Airplane Directorate; or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (or its delegated agent); or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Accomplishment of a repair as required by this paragraph does not constitute terminating action for the repetitive inspections required by paragraph (i)(2) of this AD. (k) New Requirement of This AD: Modification of the Inner Rear Spar Before exceeding 48,000 flight cycles or 96,000 flight hours, whichever occurs first since first flight of the airplane: Modify all specified fastener holes in the inner rear spar of the wing, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1089, Revision 03, dated February 9, 2001; except, where Airbus Service Bulletin A320-57-1089, Revision 03, dated February 9, 2001, specifies to contact Airbus for certain conditions, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. Modification of all specified fastener holes in the rear spar of the wing terminates the initial and repetitive inspections required by paragraphs (i)(1) and (i)(2) of this AD. If the modification is done both before the airplane accumulates 12,000 total flight cycles and before the effective date of this AD, the modification also terminates the actions required by paragraphs (g) and (h) of this AD. (l) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-57- 1060, Revision 1, dated April 26, 1993. This service information is not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-57- 1088, Revision 02, dated July 29, 1999; or Revision 03, dated February 9, 2001. This service information is not incorporated by reference in this AD. (3) This paragraph provides credit for actions required by paragraph (k) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-57- 1089, Revision 02, dated November 6, 1998. This service information is not incorporated by reference in 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-1405; fax 425-227-1149. Information may be emailed to: [email protected]. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (ii) AMOCs approved previously in accordance with AD 2004-19-11 are approved as AMOCs for the corresponding provisions of paragraphs (g) through (j) of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement [[Page 26680]] 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. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0169, dated July 17, 2014, corrected July 22, 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-2015-5811. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(8) and (o)(9) of this AD. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on June 8, 2016. (i) Airbus Service Bulletin A320-57-1089, Revision 03, dated February 9, 2001. (ii) Reserved. (4) The following service information was approved for IBR on November 5, 2004 (69 FR 58828, October 1, 2004). (i) Airbus Service Bulletin A320-57-1088, Revision 04, dated August 6, 2001. (ii) Reserved. (5) The following service information was approved for IBR on June 30, 2000 (65 FR 34069, May 26, 2000). (i) Airbus Service Bulletin A320-57-1004, Revision 2, dated June 14, 1993. This service bulletin contains the following list of effective pages: Pages 1, 4, 12, 14, 17 through 20, 22, 23, 28, 29, Revision 2, dated June 14, 1993; page 15, Revision 1, dated September 24, 1992; and pages 2, 3, 5 through 11, 13, 16, 21, 24 through 27, 30, Original Issue, dated July 9, 1991. (ii) Airbus Service Bulletin A320-57-1060, Revision 2, dated December 16, 1994. (6) The following service information was approved for IBR on February 14, 1994 (59 FR 1903, January 13, 1994). (i) Airbus Service Bulletin A320-57-1060, dated December 8, 1992. (ii) Reserved. (7) The following service information was approved for IBR on June 11, 1993 (58 FR 27923, May 12, 1993). (i) Airbus Service Bulletin A320-57-1004, Revision 1, dated September 24, 1992. This service bulletin contains the following list of effective pages: Pages 1, 4, 12, 14 through 15, 17 through 18, 20, Revision 1, dated September 24, 1992; and pages 2 through 3, 5 through 11, 13, 16, 19, 21 through 30, Original Issue, dated July 9, 1991. (ii) Reserved. (8) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 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. (9) 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. (10) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on April 8, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-08956 Filed 5-3-16; 8:45 am] BILLING CODE 4910-13-P
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docket on the Internet at http:// and corrective action if necessary. AD except Federal holidays. The AD docket
www.regulations.gov/ 2004–19–11 also provided optional contains this AD, the regulatory
#!documentDetail;D=FAA-2015-7490-0001. terminating action for the repetitive evaluation, any comments received, and
(i) Material Incorporated by Reference inspections. This new AD retains the other information. The address for the
(1) The Director of the Federal Register requirements of AD 2004–19–11, and Docket Office (telephone 800–647–5527)
approved the incorporation by reference requires the previously optional is Docket Management Facility, U.S.
(IBR) of the service information listed in this terminating action. This AD was Department of Transportation, Docket
paragraph under 5 U.S.C. 552(a) and 1 CFR prompted by a determination that the Operations, M–30, West Building
part 51. previously optional terminating action Ground Floor, Room W12–140, 1200
(2) You must use this service information is necessary to address the unsafe New Jersey Avenue SE., Washington,
as applicable to do the actions required by condition. We are issuing this AD to DC 20590.
this AD, unless the AD specifies otherwise. prevent fatigue cracking of the inner FOR FURTHER INFORMATION CONTACT:
(i) Turbomeca S.A. Service Bulletin No.
283 72 0811, Version A, dated August 25,
rear spar, which may lead to reduced Sanjay Ralhan, Aerospace Engineer,
2015. structural integrity of the wing and the International Branch, ANM–116,
(ii) Reserved. MLG. Transport Airplane Directorate, FAA,
(3) For Turbomeca S.A. service information DATES: This AD becomes effective June 1601 Lind Avenue SW., Renton, WA
identified in this AD, contact Turbomeca 8, 2016. 98057–3356; telephone 425–227–1405;
S.A., 40220 Tarnos, France; phone: 33 (0)5 59 The Director of the Federal Register fax 425–227–1149.
74 40 00; fax: 33 (0)5 59 74 45 15. approved the incorporation by reference SUPPLEMENTARY INFORMATION:
(4) You may view this service information
at FAA, Engine & Propeller Directorate, 1200
of a certain publication listed in this AD Discussion
District Avenue, Burlington, MA. For as of June 8, 2016.
The Director of the Federal Register We issued a notice of proposed
information on the availability of this
material at the FAA, call 781–238–7125. approved the incorporation by reference rulemaking (NPRM) to amend 14 CFR
(5) You may view this service information of a certain publication listed in this AD part 39 to supersede AD 2004–19–11,
at the National Archives and Records as of November 5, 2004 (69 FR 58828, Amendment 39–13805 (69 FR 58828,
Administration (NARA). For information on October 1, 2004). October 1, 2004) (‘‘AD 2004–19–11’’).
the availability of this material at NARA, call The Director of the Federal Register AD 2004–19–11 applied to certain
202–741–6030, or go to: http:// approved the incorporation by reference Airbus Model 320 series airplanes. The
www.archives.gov/federal-register/cfr/ibr- NPRM published in the Federal
of certain other publications listed in
locations.html. Register on November 27, 2015 (80 FR
this AD as of June 30, 2000 (65 FR
Issued in Burlington, Massachusetts, on 34069, May 26, 2000). 74058) (‘‘the NPRM’’). The NPRM was
April 21, 2016. The Director of the Federal Register prompted by a determination that the
Colleen M. D’Alessandro, approved the incorporation by reference previously optional terminating action
of a certain publication listed in this AD is necessary to address the unsafe
Manager, Engine & Propeller Directorate,
Aircraft Certification Service. as of February 14, 1994 (59 FR 1903, condition. The NPRM proposed to
January 13, 1994). retain the requirements of AD 2004–19–
[FR Doc. 2016–10279 Filed 5–3–16; 8:45 am]
The Director of the Federal Register 11, and requires the previously optional
BILLING CODE 4910–13–P
approved the incorporation by reference terminating action. We are issuing this
of a certain other publication listed in AD to prevent fatigue cracking of the
DEPARTMENT OF TRANSPORTATION this AD as of June 11, 1993 (58 FR inner rear spar, which may lead to
27923, May 12, 1993). reduced structural integrity of the wing
Federal Aviation Administration ADDRESSES: For service information
and the MLG.
The European Aviation Safety Agency
identified in this final rule, contact
14 CFR Part 39 (EASA), which is the Technical Agent
Airbus, Airworthiness Office—EIAS, 1
for the Member States of the European
[Docket No. FAA–2015–5811; Directorate Rond Point Maurice Bellonte, 31707
Union, has issued EASA Airworthiness
Identifier 2014–NM–158–AD; Amendment Blagnac Cedex, France; telephone +33 5
Directive 2014–0169, dated July 17,
39–18489; AD 2016–08–13] 61 93 36 96; fax +33 5 61 93 44 51; email
2014, corrected July 22, 2014 (referred
account.airworth-eas@airbus.com;
RIN 2120–AA64 to after this as the Mandatory
Internet http://www.airbus.com. You
Continuing Airworthiness Information,
Airworthiness Directives; Airbus may view this referenced service
or ‘‘the MCAI’’), to correct an unsafe
Airplanes information at the FAA, Transport
condition on certain Airbus Model 320
Airplane Directorate, 1601 Lind Avenue
AGENCY: Federal Aviation series airplanes. The MCAI states:
SW., Renton, WA. For information on
Administration (FAA), Department of the availability of this material at the During centre fuselage certification full
Transportation (DOT). FAA, call 425–227–1221. It is also scale fatigue test, cracks were found on the
inner rear spar at holes position 52 on the
ACTION: Final rule. available on the Internet at http://
right hand wing due to fatigue aspects.
www.regulations.gov by searching for This condition, if not detected and
SUMMARY: We are superseding and locating Docket No. FAA–2015– corrected, could affect the structural integrity
Airworthiness Directive (AD) 2004–19– 5811. of the aeroplane.
11 for certain Airbus Model A320 series To prevent such cracks, Airbus developed
Examining the AD Docket
asabaliauskas on DSK3SPTVN1PROD with RULES
airplanes. AD 2004–19–11 required modifications, which were introduced in
modification of the inner rear spar web You may examine the AD docket on production and in service through several
of the wing, cold expansion of the the Internet at http:// Airbus Service Bulletins (SB).
attachment holes of the forward pintle www.regulations.gov by searching for DGAC France issued * * * [an earlier AD],
which was subsequently superseded by
fitting and the actuating cylinder and locating Docket No. FAA–2015– [DGAC] AD 2001–249 [which corresponds
anchorage of the main landing gear 5811; or in person at the Docket with FAA AD 2004–19–11, Amendment 39–
(MLG), repetitive ultrasonic inspections Management Facility between 9 a.m. 13805 (69 FR 58828, October 1, 2004)], to
for cracking of the rear spar of the wing, and 5 p.m., Monday through Friday, require modification of the rear spar on some
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aeroplanes, post-modification repetitive attachment of gear rib 5, forward pintle or on the distribution of power and
inspections and, depending on findings, fitting, and actuating cylinder responsibilities among the various
accomplishment of a repair. DGAC France anchorage; and the installation of levels of government.
AD 2001–249 also specified that modification
interference fit fasteners in the rear spar For the reasons discussed above, I
in accordance with Airbus SB A320–57–1089
(in-service equivalent to Airbus mod 24591) and gear rib 5. This service information certify that this AD:
constituted (optional) terminating action for is reasonably available because the 1. Is not a ‘‘significant regulatory
the repetitive inspections. interested parties have access to it action’’ under Executive Order 12866;
Since that [DGAC] AD [2001–249] was through their normal course of business 2. Is not a ‘‘significant rule’’ under the
issued, in the framework of the A320 or by the means identified in the DOT Regulatory Policies and Procedures
Extended Service Goal (ESG), it has been ADDRESSES section. (44 FR 11034, February 26, 1979);
determined that Airbus mod 24591 is 3. Will not affect intrastate aviation in
necessary to allow aeroplanes to operate up Costs of Compliance Alaska; and
to the new ESG limit.
We estimate that this AD affects 84 4. Will not have a significant
For the reasons described above, this
[EASA] AD retains the requirements of DGAC airplanes of U.S. registry. economic impact, positive or negative,
France AD 2001–249, which is superseded, The actions required by AD 2004–19– on a substantial number of small entities
and requires modification of all pre-mod 11, and retained in this AD take about under the criteria of the Regulatory
24591 aeroplanes. 684 work-hours per product, at an Flexibility Act.
The modification includes modifying average labor rate of $85 per work-hour.
List of Subjects in 14 CFR Part 39
all specified fastener holes in the inner Required parts cost about $13,644 per
product. Based on these figures, the Air transportation, Aircraft, Aviation
rear spar of the wing. You may examine
estimated cost of the actions that were safety, Incorporation by reference,
the MCAI in the AD docket on the
required by AD 2004–19–11 is $71,784 Safety.
Internet at http://www.regulations.gov
by searching for and locating Docket No. per product. Adoption of the Amendment
FAA–2015–5811. We also estimate that it takes about
980 work-hours per product to comply Accordingly, under the authority
Comments with the basic requirements of this AD. delegated to me by the Administrator,
The average labor rate is $85 per work- the FAA amends 14 CFR part 39 as
We gave the public the opportunity to
hour. Required parts will cost about follows:
participate in developing this AD. We
considered the comment received. $32,727 per product. Based on these
figures, we estimate the cost of this AD PART 39—AIRWORTHINESS
United Airlines provided its support for DIRECTIVES
the content of the NPRM. on U.S. operators to be $9,746,268, or
$116,027 per product. ■ 1. The authority citation for part 39
Explanation of Changes Made to This We have received no definitive data
AD continues to read as follows:
that would enable us to provide cost
estimates for the on-condition actions Authority: 49 U.S.C. 106(g), 40113, 44701.
We have added a new paragraph (l)(1)
to this AD to provide credit for actions specified in this AD. § 39.13 [Amended]
required by paragraph (h) of this AD, if Authority for This Rulemaking
those actions were performed before the ■ 2. The FAA amends § 39.13 by
effective date of this AD using Airbus Title 49 of the United States Code removing Airworthiness Directive (AD)
Service Bulletin A320–57–1060, specifies the FAA’s authority to issue 2004–19–11, Amendment 39–13805 (69
Revision 1, dated April 26, 1993. We rules on aviation safety. Subtitle I, FR 58828, October 1, 2004), and adding
have redesignated paragraphs (l)(1) and section 106, describes the authority of the following new AD:
(l)(2) of the proposed AD as paragraphs the FAA Administrator. ‘‘Subtitle VII: 2016–08–13 Airbus: Amendment 39–18489.
(l)(2) and (l)(3) of this AD. Aviation Programs,’’ describes in more Docket No. FAA–2015–5811; Directorate
detail the scope of the Agency’s Identifier 2014–NM–158–AD.
Conclusion authority. (a) Effective Date
We reviewed the relevant data, We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII, This AD becomes effective June 8, 2016.
considered the comments received, and
determined that air safety and the Part A, Subpart III, Section 44701: (b) Affected ADs
public interest require adopting this AD General requirements.’’ Under that This AD replaces AD 2004–19–11,
with the changes described previously section, Congress charges the FAA with Amendment 39–13805 (69 FR 58828, October
and minor editorial changes. We have promoting safe flight of civil aircraft in 1, 2004) (‘‘AD 2004–19–11’’).
determined that these minor changes: air commerce by prescribing regulations (c) Applicability
• Are consistent with the intent that for practices, methods, and procedures
the Administrator finds necessary for This AD applies to Airbus Model A320–
was proposed in the NPRM for 211, –212, –214, –231, –232, and –233
correcting the unsafe condition; and safety in air commerce. This regulation airplanes, certificated in any category, all
• Do not add any additional burden is within the scope of that authority manufacturer serial numbers, except those on
upon the public than was already because it addresses an unsafe condition which Airbus modification (mod) 24591 has
proposed in the NPRM. that is likely to exist or develop on been embodied in production.
products identified in this rulemaking
Related Service Information Under 1 (d) Subject
action.
asabaliauskas on DSK3SPTVN1PROD with RULES
CFR Part 51 Air Transport Association (ATA) of
Airbus has issued Airbus Service Regulatory Findings America Code 57, Wings.
Bulletin A320–57–1089, Revision 03, We determined that this AD will not (e) Reason
dated February 9, 2001. This service have federalism implications under This AD was prompted by reports of
information describes procedures for Executive Order 13132. This AD will fatigue cracking of the inner rear spar of the
modification of the airplane by not have a substantial direct effect on wing and also by a determination that the
accomplishing cold re-expansion of the the States, on the relationship between modification of the inner rear spar is
holes in the inner rear spar for the the national government and the States, necessary to address the unsafe condition.
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![26680 Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations
in this AD to obtain corrective actions from Office—EIAS, 1 Rond Point Maurice The Director of the Federal Register
a manufacturer, the action must be Bellonte, 31707 Blagnac Cedex, France; approved the incorporation by reference
accomplished using a method approved by telephone +33 5 61 93 36 96; fax +33 5 61 of certain publications listed in this AD
the Manager, International Branch, ANM– 93 44 51; email account.airworth-eas@
116, Transport Airplane Directorate, FAA; or
as of June 8, 2016.
airbus.com; Internet http://www.airbus.com.
EASA; or Airbus’s EASA DOA. If approved (9) You may view this service information ADDRESSES: You may examine the AD
by the DOA, the approval must include the at the FAA, Transport Airplane Directorate, docket on the Internet at http://
DOA-authorized signature. 1601 Lind Avenue SW., Renton, WA. For www.regulations.gov/
(n) Related Information information on the availability of this #!docketDetail;D=FAA-2015-3990; or in
material at the FAA, call 425–227–1221. person at the Docket Management
(1) Refer to Mandatory Continuing (10) You may view this service information
Airworthiness Information (MCAI) EASA Facility, U.S. Department of
that is incorporated by reference at the Transportation, Docket Operations, M–
Airworthiness Directive 2014–0169, dated National Archives and Records
July 17, 2014, corrected July 22, 2014, for Administration (NARA). For information on
30, West Building Ground Floor, Room
related information. This MCAI may be the availability of this material at NARA, call W12–140, 1200 New Jersey Avenue SE.,
found in the AD docket on the Internet at 202–741–6030, or go to: http:// Washington, DC.
http://www.regulations.gov by searching for www.archives.gov/federal-register/cfr/ibr- For Airbus service information
and locating Docket No. FAA–2015–5811. locations.html. identified in this final rule, contact
(2) Service information identified in this Airbus, Airworthiness Office—EIAS, 1
AD that is not incorporated by reference is Issued in Renton, Washington, on April 8,
available at the addresses specified in 2016. Rond Point Maurice Bellonte, 31707
paragraphs (o)(8) and (o)(9) of this AD. Michael Kaszycki,
Blagnac Cedex, France; telephone +33 5
61 93 36 96; fax +33 5 61 93 44 51; email
(o) Material Incorporated by Reference Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
account.airworth-eas@airbus.com;
(1) The Director of the Federal Register Internet http://www.airbus.com.
approved the incorporation by reference [FR Doc. 2016–08956 Filed 5–3–16; 8:45 am]
For Airbus Operations GmbH service
(IBR) of the service information listed in this BILLING CODE 4910–13–P information identified in this final rule,
paragraph under 5 U.S.C. 552(a) and 1 CFR
contact Airbus Operations GmbH, Cabin
part 51.
(2) You must use this service information Electronics, Lueneburger Schanze 30,
DEPARTMENT OF TRANSPORTATION
as applicable to do the actions required by 21614 Buxtehude, Germany; telephone
this AD, unless this AD specifies otherwise. Federal Aviation Administration +49 40 7437 46 32; telefax +49 40 7437
(3) The following service information was 16 80; email ruediger.jansen@
approved for IBR on June 8, 2016.
14 CFR Part 39 airbus.com.
(i) Airbus Service Bulletin A320–57–1089, You may view this referenced service
Revision 03, dated February 9, 2001. [Docket No. FAA–2015–3990; Directorate information at the FAA, Transport
(ii) Reserved. Airplane Directorate, 1601 Lind Avenue
Identifier 2014–NM–255–AD; Amendment
(4) The following service information was
approved for IBR on November 5, 2004 (69
39–18478; AD 2016–08–02] SW., Renton, WA. For information on
FR 58828, October 1, 2004). the availability of this material at the
RIN 2120–AA64 FAA, call 425–227–1221. It is also
(i) Airbus Service Bulletin A320–57–1088,
Revision 04, dated August 6, 2001. available on the Internet at http://
Airworthiness Directives; Airbus
(ii) Reserved. www.regulations.gov by searching for
(5) The following service information was Airplanes
and locating Docket No. FAA–2015–
approved for IBR on June 30, 2000 (65 FR AGENCY: Federal Aviation 3990.
34069, May 26, 2000).
(i) Airbus Service Bulletin A320–57–1004,
Administration (FAA), Department of FOR FURTHER INFORMATION CONTACT:
Revision 2, dated June 14, 1993. This service Transportation (DOT). Sanjay Ralhan, Aerospace Engineer,
bulletin contains the following list of ACTION: Final rule. International Branch, ANM–116,
effective pages: Pages 1, 4, 12, 14, 17 through Transport Airplane Directorate, FAA,
20, 22, 23, 28, 29, Revision 2, dated June 14, SUMMARY: We are adopting a new 1601 Lind Avenue SW., Renton, WA
1993; page 15, Revision 1, dated September airworthiness directive (AD) for certain 98057–3356; telephone 425–227–1405;
24, 1992; and pages 2, 3, 5 through 11, 13, Airbus Model A320–214, –232, and
16, 21, 24 through 27, 30, Original Issue,
fax 425–227–1149.
–233 airplanes; and Airbus Model SUPPLEMENTARY INFORMATION:
dated July 9, 1991. A321–211 and –231 airplanes. This AD
(ii) Airbus Service Bulletin A320–57–1060,
was prompted by reports of incorrect Discussion
Revision 2, dated December 16, 1994.
(6) The following service information was installation of jiffy joint connectors on We issued a notice of proposed
approved for IBR on February 14, 1994 (59 cables connected to certain passenger rulemaking (NPRM) to amend 14 CFR
FR 1903, January 13, 1994). service units (PSUs), which could cause part 39 by adding an AD that would
(i) Airbus Service Bulletin A320–57–1060, the passenger oxygen container to apply to certain Airbus Model A320–
dated December 8, 1992. malfunction if the connector becomes 214, –232, and –233 airplanes; and
(ii) Reserved. disengaged during flight due to
(7) The following service information was Airbus Model A321–211 and –231
vibration. This AD requires airplanes. The NPRM published in the
approved for IBR on June 11, 1993 (58 FR
27923, May 12, 1993). identification of the affected PSUs, and Federal Register on October 19, 2015
(i) Airbus Service Bulletin A320–57–1004, depending on findings, doing applicable (80 FR 63134) (‘‘the NPRM’’).
Revision 1, dated September 24, 1992. This related investigative and corrective The European Aviation Safety Agency
asabaliauskas on DSK3SPTVN1PROD with RULES
service bulletin contains the following list of actions. We are issuing this AD to (EASA), which is the Technical Agent
effective pages: Pages 1, 4, 12, 14 through 15, prevent failure of the door of the for the Member States of the European
17 through 18, 20, Revision 1, dated passenger oxygen container to open in Union, has issued EASA Airworthiness
September 24, 1992; and pages 2 through 3, the event of airplane decompression,
5 through 11, 13, 16, 19, 21 through 30,
Directive 2014–0256, dated November
resulting in lack of oxygen supply and 26, 2014 (referred to after this as the
Original Issue, dated July 9, 1991.
(ii) Reserved. consequent injury to occupants. Mandatory Continuing Airworthiness
(8) For service information identified in DATES: This AD becomes effective June Information, or ‘‘the MCAI’’), to correct
this AD, contact Airbus, Airworthiness 8, 2016. an unsafe condition for certain Airbus
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Document Created: 2016-05-04 01:23:03
Document Modified: 2016-05-04 01:23:03
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD becomes effective June 8, 2016. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. | |
| FR Citation | 81 FR 26677 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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