82 FR 25940 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 107 (June 6, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 107 (June 6, 2017)
| Page Range | 25940-25943 | |
| FR Document | 2017-11290 |
[Federal Register Volume 82, Number 107 (Tuesday, June 6, 2017)] [Rules and Regulations] [Pages 25940-25943] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-11290] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-7262; Directorate Identifier 2015-NM-079-AD; Amendment 39-18912; AD 2017-11-13] 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) 98-13-14, for certain Airbus Model A320-211, -212, and -231 airplanes. AD 98-13-14 required repetitive inspections of certain fastener holes of the aft fuselage, and corrective action if necessary. This new AD continues to require the actions in AD 98-13-14, with revised inspection compliance times. This AD was prompted by identification of cracks in the fastener holes of the former junction of the aft fuselage, which occurred during a fatigue test; and a determination that certain compliance times specified in AD 98-13-14 must be reduced. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 11, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 11, 2017. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of July 30, 1998 (63 FR 34556, June 25, 1998). 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-2016- 7262. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 7262; 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 [[Page 25941]] part 39 to supersede AD 98-13-14, Amendment 39-10602 (63 FR 34556, June 25, 1998) (``AD 98-13-14''). AD 98-13-14 applied to certain Airbus Model A320 series airplanes (Model A320-211, -212, and -231 airplanes). Since we issued AD 98-13-14, an evaluation by the DAH indicates that the former junction of the aft fuselage is subject to fatigue damage. The NPRM published in the Federal Register on June 21, 2016 (81 FR 40210). The NPRM was prompted by the identification of four cracks in the fastener holes in the area of the former junction at frame (FR) 68 between stringers 4 and 5 (left- and right-hand sides), which occurred during a fatigue test, and a determination that certain compliance times specified in AD 98-13-14 must be reduced. The NPRM proposed to continue to require the actions in AD 98-13-14, with revised inspection compliance times. We are issuing this AD to prevent fatigue cracks from occurring or propagating in certain structures, which could adversely affect the structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2015-0084, dated May 13, 2015; corrected May 18, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''); to correct an unsafe condition for certain Airbus Model A320-211, -212, and -231 airplanes. The MCAI states: During a fatigue test campaign, four cracks were identified in the fastener holes of the former junction at frame (FR) 68 between stringers 4 and 5. This condition, if not detected and corrected, could lead to crack propagation, possibly resulting in reduced structural integrity of the fuselage. To address this unsafe condition, DGAC [Direction g[eacute]n[eacute]rale de l'aviation civile] France issued * * * [an AD, which corresponds to FAA AD 98-13-14] to require repetitive inspections and, depending on findings, the accomplishment of an applicable repair solution. That [DGAC] AD also provided modification of FR 68 [cold working of fastener and tooling holes] in accordance with Airbus Service Bulletin (SB) A320-53-1090 as optional terminating action. Following new analyses, the thresholds and inspection intervals have been reviewed and adjusted. For the reason described above, this [EASA] AD retains the requirements of DGAC France AD 96-298-093(B)R2 [http://ad.easa.europa.eu/ad/F-1996-298R2], which is superseded, and requires those actions within the new thresholds and intervals. This [EASA] AD was republished to correct a typographical error in the Reason. Repairs include doing applicable related investigative actions (i.e., rotating probe inspection of the hole to make sure the crack is removed and eddy current inspection of the cold expanded holes). You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 7262. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM and the FAA's response to the comment. Request To Update Service Information Airbus requested that Airbus Service Bulletin A320-53-1089, Revision 04, dated June 1, 2016, be referred to in the final rule. This service information replaces a certain nondestructive test manual (NTM) task, removes an eddy current inspection for a certain service bulletin task, and updates the service bulletin airplane effectivity. We agree with the request and have revised paragraphs (h) and (i) of this AD to refer to Airbus Service Bulletin A320-53-1089, Revision 04, dated June 1, 2016. We have also added paragraph (k)(1)(iii) to this AD to provide credit for Airbus Service Bulletin A320-53-1089, Revision 03, dated March 18, 2015. Additional Changes to the NPRM We have revised paragraphs (h)(2) and (h)(3) of this AD to remove references to the revision level and date of the service information that must be used for determining the compliance time, because operators might have used other versions for their most recent inspection. The number of affected U.S. registered airplanes has also been changed from 10 to 4. The total cost to operators has been changed accordingly. Conclusion We reviewed the available data, including the comment 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 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. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed the following Airbus service information: Service Bulletin A320-53-1089, Revision 04, dated June 1, 2016. This service information describes procedures for a special detailed rototest inspection for fatigue cracking of the frame junction holes and the adjacent tooling hole, as applicable, of the right- and left-hand former junctions at FR 68, and repair, including doing applicable related investigative actions. Service Bulletin A320-53-1090, Revision 02, dated December 22, 1998. This service information describes procedures for modifying the airplane (cold working of fastener and tooling holes). 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 4 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Initial and repetitive 8 work-hours x $85 $0 $680 per inspection $2,720 per inspections [retained from AD 98- per hour = $680 per cycle. inspection cycle. 13-14]. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that will be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these repairs: [[Page 25942]] On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product -------------------------------------------------------------------------------------------- Repair............................... 52 work-hours x $85 per $3,800 $8,220 hour = $4,420. ---------------------------------------------------------------------------------------------------------------- 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) 98-13-14, Amendment 39-10602 (63 FR 34556, June 25, 1998), and adding the following new AD: 2017-11-13 Airbus: Amendment 39-18912; Docket No. FAA-2016-7262; Directorate Identifier 2015-NM-079-AD. (a) Effective Date This AD is effective July 11, 2017. (b) Affected ADs This AD replaces AD 98-13-14, Amendment 39-10602 (63 FR 34556, June 25, 1998) (``AD 98-13-14''). (c) Applicability This AD applies to Airbus Model A320-211, -212, and -231 airplanes, certificated in any category, manufacturer serial numbers (S/Ns) 0001 through 0123 inclusive, except those that have embodied Airbus Modifications 21780 and 21781 in production. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by identification of four cracks in the fastener holes of the former junction at frame (FR) 68 between stringers 4 and 5, which occurred during a fatigue test, and a determination that certain compliance times specified in AD 98-13-14 must be reduced. We are issuing this AD to prevent fatigue cracks from occurring or propagating in certain structures, which could adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Repetitive Inspections and Repair, With Additional Methods of Approving Repairs This paragraph restates the requirements of paragraph (a) of AD 98-13-14, with additional methods of approving repairs. For Model A320 series airplanes, as listed in Airbus Service Bulletins A320- 53-1089 and A320-53-1090, both dated November 22, 1995: Prior to the accumulation of 20,000 total flight cycles, or within 500 flight cycles after July 30, 1998 (the effective date of AD 98-13-14), whichever occurs later, perform a rotating probe inspection for fatigue cracking of the fastener holes and/or the adjacent tooling hole, as applicable, of the right- and left-hand former junctions at FR 68, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089, dated November 22, 1995. Accomplishing an inspection required by paragraph (h) of this AD terminates the actions required by this paragraph. (1) If no crack is detected, accomplish either paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (i) Repeat the inspection thereafter at intervals not to exceed 20,000 flight cycles; or (ii) Prior to further flight following the accomplishment of the inspection required by paragraph (g) of this AD, cold work the fastener holes and/or the adjacent tooling hole of the right- and left-hand former junctions at FR 68, as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1090, dated November 22, 1995. Accomplishment of this cold working constitutes terminating action for the repetitive inspections required by paragraph (g)(1)(i) of this AD. (2) If any crack is detected, prior to further flight, repair in accordance with 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). (h) New Repetitive Inspection Requirement Within the compliance time specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, whichever occurs latest: Accomplish a special detailed rototest inspection for fatigue cracking of the frame junction holes and the adjacent tooling hole, as applicable, of the right- and left-hand former junctions at FR 68, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089, Revision 04, dated June 1, 2016. Repeat the inspection thereafter at intervals not to exceed 3,800 flight cycles or 7,600 flight hours, whichever occurs first, until a repair required by paragraph (i) of this AD is done or a modification specified in paragraph (j) of this AD is done. Accomplishing an inspection required by this paragraph terminates the inspections required by paragraph (g) of this AD. (1) Within 28,700 flight cycles or 57,400 flight hours since airplane first flight, whichever occurs first. (2) Within 3,800 flight cycles or 7,600 flight hours, whichever occurs first, since the most recent inspection done as specified in the Accomplishment Instructions of Airbus Service Bulletin A320-53- 1089. [[Page 25943]] (3) Within 3,800 flight cycles or 7,600 flight hours after the effective date of this AD, whichever occurs first, without exceeding 20,000 flight cycles since the most recent inspection done as specified in the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089. (i) New Repair Requirement If any crack is detected during any inspection required by paragraph (h) of this AD: Before further flight, repair, including doing all applicable related investigative actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089, Revision 04, dated June 1, 2016. Do all applicable related investigative actions before further flight. Repair of an airplane in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089, Revision 04, dated June 1, 2016, constitutes terminating action for the repetitive inspections required by paragraph (h) of this AD. (j) New Optional Modification Modification of an airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1090, Revision 02, dated December 22, 1998, constitutes terminating action for the repetitive inspections required by paragraphs (g) and (h) of this AD, provided the modification is accomplished before further flight after accomplishing an inspection required by paragraph (h) of this AD and no cracks were detected. (k) Credit for Previous Actions (1) This paragraph provides credit for the actions required by paragraphs (h) and (i) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraphs (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD. (i) Airbus Service Bulletin A320-53-1089, Revision 01, dated June 4, 1998. (ii) Airbus Service Bulletin A320-53-1089, Revision 02, dated February 3, 2003. (iii) Airbus Service Bulletin A320-53-1089, Revision 03, dated March 18, 2015. (2) This paragraph provides credit for the actions required by paragraph (j) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraphs (k)(2)(i) or (k)(2)(ii) of this AD. (i) Airbus Service Bulletin A320-53-1090, dated November 22, 1995, which was incorporated by reference in AD 98-13-14, Amendment 39-10602 (63 FR 34556, June 25, 1998). (ii) Airbus Service Bulletin A320-53-1090, Revision 1, dated June 10, 1998, which is not incorporated by reference in this AD. (l) 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 manager of the International Branch, send it to the attention of the person identified in paragraph (m)(2) of this AD. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015-0084, dated May 13, 2015; corrected May 18, 2015; for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-7262. (2) For more information about this AD, 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. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(5) and (n)(6) of this AD. (n) 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 the AD specifies otherwise. (3) The following service information was approved for IBR on July 11, 2017. (i) Airbus Service Bulletin A320-53-1089, Revision 04, dated June 1, 2016. (ii) Airbus Service Bulletin A320-53-1090, Revision 02, dated December 22, 1998. Pages 1, 2, 7, 8, 9, 10, and 11 of this document are identified as Revision 1, dated June 10, 1998; and pages 3, 4, 5, and 6 of this document are identified as Revision 02, dated December 22, 1998. (4) The following service information was approved for IBR on July 30, 1998, AD 98-13-14, Amendment 39-10602 (63 FR 34556, June 25, 1998). (i) Airbus Service Bulletin A320-53-1089, dated November 22, 1995. (ii) Airbus Service Bulletin A320-53-1090, dated November 22, 1995. (5) For service information identified in this AD, contact Airbus SAS, 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. (6) 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. (7) 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 May 23, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. 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(l) Other FAA AD Provisions (i) Airbus Service Bulletin A320–70–1003, junction of the aft fuselage, which
The following provisions also apply to this Revision 01, dated December 28, 2015. occurred during a fatigue test; and a
AD: (ii) Goodrich Aerostructures Service determination that certain compliance
(1) Alternative Methods of Compliance Bulletin RA32078–137, Rev. 3, dated March
14, 2016.
times specified in AD 98–13–14 must be
(AMOCs): The Manager, International reduced. We are issuing this AD to
Branch, ANM–116, Transport Airplane (3) For Airbus service information
identified in this AD, contact Airbus service address the unsafe condition on these
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested information identified in this AD, contact products.
using the procedures found in 14 CFR 39.19. Airbus, Airworthiness Office—EIAS, 1 Rond DATES: This AD is effective July 11,
In accordance with 14 CFR 39.19, send your Point Maurice Bellonte, 31707 Blagnac
2017.
request to your principal inspector or local Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email
The Director of the Federal Register
Flight Standards District Office, as approved the incorporation by reference
appropriate. If sending information directly account.airworth-eas@airbus.com; Internet
to the International Branch, send it to ATTN: http://www.airbus.com. of certain publications listed in this AD
Sanjay Ralhan, Aerospace Engineer, (4) For Goodrich Aerostructures service as of July 11, 2017.
International Branch, ANM–116, Transport information identified in this AD, contact The Director of the Federal Register
Airplane Directorate, FAA, 1601 Lind Goodrich Aerostructures, 850 Lagoon Drive, approved the incorporation by reference
Avenue SW., Renton, WA 98057–3356; Chula Vista, CA 91910–2098; telephone 619– of certain other publications listed in
telephone 425–227–1405; fax 425–227–1149. 691–2719; email jan.lewis@goodrich.com; this AD as of July 30, 1998 (63 FR
Information may be emailed to: 9-ANM-116- Internet https://techpubs.goodrich.com. 34556, June 25, 1998).
AMOC-REQUESTS@faa.gov. Before using (5) You may view this service information
at the FAA, Transport Airplane Directorate, ADDRESSES: For service information
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal 1601 Lind Avenue SW., Renton, WA. For identified in this final rule, contact
inspector, the manager of the local flight information on the availability of this Airbus, Airworthiness Office–EIAS, 1
standards district office/certificate holding material at the FAA, call 425–227–1221. Rond Point Maurice Bellonte, 31707
district office. (6) You may view this service information Blagnac Cedex, France; telephone +33 5
(2) Contacting the Manufacturer: For any that is incorporated by reference at the 61 93 36 96; fax +33 5 61 93 44 51; email
requirement in this AD to obtain corrective National Archives and Records account.airworth-eas@airbus.com;
actions from a manufacturer, the action must Administration (NARA). For information on
be accomplished using a method approved the availability of this material at NARA, call
Internet http://www.airbus.com. You
by the Manager, International Branch, ANM– 202–741–6030, or go to: http:// may view this referenced service
116, Transport Airplane Directorate, FAA; or www.archives.gov/federal-register/cfr/ibr- information at the FAA, Transport
EASA; or Airbus’s EASA DOA. If approved locations.html. Airplane Directorate, 1601 Lind Avenue
by the DOA, the approval must include the
Issued in Renton, Washington, on May 17, SW., Renton, WA. For information on
DOA-authorized signature. the availability of this material at the
2017.
(3) Required for Compliance (RC): Except FAA, call 425–227–1221. It is also
as required by paragraph (i) of this AD: If any Michael Kaszycki,
Acting Manager, Transport Airplane
available on the Internet at http://
service information contains procedures or
tests that are identified as RC, those Directorate, Aircraft Certification Service. www.regulations.gov by searching for
procedures and tests must be done to comply and locating Docket No. FAA–2016–
[FR Doc. 2017–11129 Filed 6–5–17; 8:45 am]
with this AD; any procedures or tests that are 7262.
BILLING CODE 4910–13–P
not identified as RC are recommended. Those
procedures and tests that are not identified Examining the AD Docket
as RC may be deviated from using accepted You may examine the AD docket on
methods in accordance with the operator’s DEPARTMENT OF TRANSPORTATION
the Internet at http://
maintenance or inspection program without www.regulations.gov by searching for
obtaining approval of an AMOC, provided Federal Aviation Administration
and locating Docket No. FAA–2016–
the procedures and tests identified as RC can
be done and the airplane can be put back in 14 CFR Part 39 7262; or in person at the Docket
an airworthy condition. Any substitutions or Management Facility between 9 a.m.
changes to procedures or tests identified as [Docket No. FAA–2016–7262; Directorate and 5 p.m., Monday through Friday,
RC require approval of an AMOC. Identifier 2015–NM–079–AD; Amendment except Federal holidays. The AD docket
39–18912; AD 2017–11–13]
(m) Related Information
contains this AD, the regulatory
RIN 2120–AA64 evaluation, any comments received, and
(1) Refer to Mandatory Continuing
other information. The address for the
Airworthiness Information (MCAI) EASA Airworthiness Directives; Airbus
Airworthiness Directive 2016–0076, dated Docket Office (telephone 800–647–5527)
Airplanes is Docket Management Facility, U.S.
April 18, 2016, for related information. This
MCAI may be found in the AD docket on the AGENCY: Federal Aviation Department of Transportation, Docket
Internet at http://www.regulations.gov by Administration (FAA), Department of Operations, M–30, West Building
searching for and locating Docket No. FAA– Transportation (DOT). Ground Floor, Room W12–140, 1200
2016–8182. New Jersey Avenue SE., Washington,
(2) Service information identified in this ACTION: Final rule.
DC 20590.
AD that is not incorporated by reference is
available at the addresses specified in
SUMMARY: We are superseding FOR FURTHER INFORMATION CONTACT:
paragraphs (n)(3), (n)(4), and (n)(5) of this Airworthiness Directive (AD) 98–13–14, Sanjay Ralhan, Aerospace Engineer,
AD. for certain Airbus Model A320–211, International Branch, ANM–116,
–212, and –231 airplanes. AD 98–13–14 Transport Airplane Directorate, FAA,
(n) Material Incorporated by Reference
required repetitive inspections of 1601 Lind Avenue SW., Renton, WA
sradovich on DSK3GMQ082PROD with RULES
(1) The Director of the Federal Register certain fastener holes of the aft fuselage, 98057–3356; telephone 425–227–1405;
approved the incorporation by reference and corrective action if necessary. This fax 425–227–1149.
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
new AD continues to require the actions SUPPLEMENTARY INFORMATION:
part 51. in AD 98–13–14, with revised
inspection compliance times. This AD Discussion
(2) You must use this service information
as applicable to do the actions required by was prompted by identification of We issued a notice of proposed
this AD, unless this AD specifies otherwise. cracks in the fastener holes of the former rulemaking (NPRM) to amend 14 CFR
VerDate Sep<11>2014 18:18 Jun 05, 2017 Jkt 241001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\06JNR1.SGM 06JNR1](https://thefederalregister.org/doc/82_FR_26047/page/1.svg)
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part 39 to supersede AD 98–13–14, with Airbus Service Bulletin (SB) A320–53– versions for their most recent
Amendment 39–10602 (63 FR 34556, 1090 as optional terminating action. inspection. The number of affected U.S.
June 25, 1998) (‘‘AD 98–13–14’’). AD Following new analyses, the thresholds registered airplanes has also been
98–13–14 applied to certain Airbus and inspection intervals have been reviewed changed from 10 to 4. The total cost to
and adjusted.
Model A320 series airplanes (Model For the reason described above, this
operators has been changed accordingly.
A320–211, –212, and –231 airplanes). [EASA] AD retains the requirements of DGAC Conclusion
Since we issued AD 98–13–14, an France AD 96–298–093(B)R2 [http://
evaluation by the DAH indicates that ad.easa.europa.eu/ad/F-1996-298R2], which We reviewed the available data,
the former junction of the aft fuselage is is superseded, and requires those actions including the comment received, and
subject to fatigue damage. within the new thresholds and intervals. determined that air safety and the
The NPRM published in the Federal This [EASA] AD was republished to correct public interest require adopting this AD
Register on June 21, 2016 (81 FR 40210). a typographical error in the Reason. with the changes described previously
The NPRM was prompted by the Repairs include doing applicable and minor editorial changes. We have
identification of four cracks in the related investigative actions (i.e., determined that these changes:
fastener holes in the area of the former rotating probe inspection of the hole to • Are consistent with the intent that
junction at frame (FR) 68 between make sure the crack is removed and was proposed in the NPRM for
stringers 4 and 5 (left- and right-hand eddy current inspection of the cold correcting the unsafe condition; and
sides), which occurred during a fatigue expanded holes). You may examine the • Do not add any additional burden
test, and a determination that certain MCAI in the AD docket on the Internet upon the public than was already
compliance times specified in AD 98– at http://www.regulations.gov by proposed in the NPRM.
13–14 must be reduced. The NPRM searching for and locating Docket No. We also determined that these
proposed to continue to require the FAA–2016–7262. changes will not increase the economic
actions in AD 98–13–14, with revised burden on any operator or increase the
Comments scope of this AD.
inspection compliance times. We are
issuing this AD to prevent fatigue cracks We gave the public the opportunity to Related Service Information Under 1
from occurring or propagating in certain participate in developing this AD. The CFR Part 51
structures, which could adversely affect following presents the comment
the structural integrity of the airplane. received on the NPRM and the FAA’s We reviewed the following Airbus
The European Aviation Safety Agency response to the comment. service information:
(EASA), which is the Technical Agent • Service Bulletin A320–53–1089,
Request To Update Service Information Revision 04, dated June 1, 2016. This
for the Member States of the European
Union, has issued EASA AD 2015–0084, Airbus requested that Airbus Service service information describes
dated May 13, 2015; corrected May 18, Bulletin A320–53–1089, Revision 04, procedures for a special detailed rototest
2015 (referred to after this as the dated June 1, 2016, be referred to in the inspection for fatigue cracking of the
Mandatory Continuing Airworthiness final rule. This service information frame junction holes and the adjacent
Information, or ‘‘the MCAI’’); to correct replaces a certain nondestructive test tooling hole, as applicable, of the right-
an unsafe condition for certain Airbus manual (NTM) task, removes an eddy and left-hand former junctions at FR 68,
Model A320–211, –212, and –231 current inspection for a certain service and repair, including doing applicable
airplanes. The MCAI states: bulletin task, and updates the service related investigative actions.
bulletin airplane effectivity. • Service Bulletin A320–53–1090,
During a fatigue test campaign, four cracks We agree with the request and have Revision 02, dated December 22, 1998.
were identified in the fastener holes of the
former junction at frame (FR) 68 between
revised paragraphs (h) and (i) of this AD This service information describes
stringers 4 and 5. to refer to Airbus Service Bulletin procedures for modifying the airplane
This condition, if not detected and A320–53–1089, Revision 04, dated June (cold working of fastener and tooling
corrected, could lead to crack propagation, 1, 2016. We have also added paragraph holes).
possibly resulting in reduced structural (k)(1)(iii) to this AD to provide credit for This service information is reasonably
integrity of the fuselage. Airbus Service Bulletin A320–53–1089, available because the interested parties
To address this unsafe condition, DGAC Revision 03, dated March 18, 2015. have access to it through their normal
[Direction générale de l’aviation civile] course of business or by the means
France issued * * * [an AD, which Additional Changes to the NPRM
identified in the ADDRESSES section.
corresponds to FAA AD 98–13–14] to require We have revised paragraphs (h)(2) and
repetitive inspections and, depending on Costs of Compliance
findings, the accomplishment of an
(h)(3) of this AD to remove references to
applicable repair solution. the revision level and date of the service We estimate that this AD affects 4
That [DGAC] AD also provided information that must be used for airplanes of U.S. registry.
modification of FR 68 [cold working of determining the compliance time, We estimate the following costs to
fastener and tooling holes] in accordance because operators might have used other comply with this AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Initial and repetitive inspec- 8 work-hours × $85 per hour = $0 $680 per inspection cycle ....... $2,720 per inspection cycle.
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tions [retained from AD 98– $680 per inspection cycle.
13–14].
We estimate the following costs to do required based on the results of the determining the number of aircraft that
any necessary repairs that will be inspection. We have no way of might need these repairs:
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![25942 Federal Register / Vol. 82, No. 107 / Tuesday, June 6, 2017 / Rules and Regulations
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Repair ............................................................................. 52 work-hours × $85 per hour = $4,420 ........................ $3,800 $8,220
Authority for This Rulemaking PART 39—AIRWORTHINESS after July 30, 1998 (the effective date of AD
DIRECTIVES 98–13–14), whichever occurs later, perform a
Title 49 of the United States Code rotating probe inspection for fatigue cracking
specifies the FAA’s authority to issue ■ 1. The authority citation for part 39 of the fastener holes and/or the adjacent
rules on aviation safety. Subtitle I, continues to read as follows: tooling hole, as applicable, of the right- and
section 106, describes the authority of left-hand former junctions at FR 68, in
Authority: 49 U.S.C. 106(g), 40113, 44701. accordance with the Accomplishment
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more Instructions of Airbus Service Bulletin A320–
§ 39.13 [Amended]
detail the scope of the Agency’s 53–1089, dated November 22, 1995.
■ 2. The FAA amends § 39.13 by Accomplishing an inspection required by
authority.
removing Airworthiness Directive (AD) paragraph (h) of this AD terminates the
We are issuing this rulemaking under 98–13–14, Amendment 39–10602 (63 actions required by this paragraph.
the authority described in ‘‘Subtitle VII, FR 34556, June 25, 1998), and adding (1) If no crack is detected, accomplish
Part A, Subpart III, Section 44701: the following new AD: either paragraph (g)(1)(i) or (g)(1)(ii) of this
General requirements.’’ Under that AD.
section, Congress charges the FAA with 2017–11–13 Airbus: Amendment 39–18912; (i) Repeat the inspection thereafter at
Docket No. FAA–2016–7262; Directorate intervals not to exceed 20,000 flight cycles;
promoting safe flight of civil aircraft in Identifier 2015–NM–079–AD.
air commerce by prescribing regulations or
(a) Effective Date (ii) Prior to further flight following the
for practices, methods, and procedures
accomplishment of the inspection required
the Administrator finds necessary for This AD is effective July 11, 2017. by paragraph (g) of this AD, cold work the
safety in air commerce. This regulation (b) Affected ADs fastener holes and/or the adjacent tooling
is within the scope of that authority hole of the right- and left-hand former
This AD replaces AD 98–13–14,
because it addresses an unsafe condition junctions at FR 68, as applicable, in
Amendment 39–10602 (63 FR 34556, June
that is likely to exist or develop on 25, 1998) (‘‘AD 98–13–14’’).
accordance with the Accomplishment
products identified in this rulemaking Instructions of Airbus Service Bulletin A320–
action. (c) Applicability 53–1090, dated November 22, 1995.
This AD applies to Airbus Model A320– Accomplishment of this cold working
Regulatory Findings 211, –212, and –231 airplanes, certificated in constitutes terminating action for the
any category, manufacturer serial numbers repetitive inspections required by paragraph
We determined that this AD will not (g)(1)(i) of this AD.
have federalism implications under (S/Ns) 0001 through 0123 inclusive, except
those that have embodied Airbus (2) If any crack is detected, prior to further
Executive Order 13132. This AD will Modifications 21780 and 21781 in flight, repair in accordance with a method
not have a substantial direct effect on production. approved by the Manager, International
the States, on the relationship between Branch, ANM–116, Transport Airplane
the national government and the States, (d) Subject Directorate, FAA; or the European Aviation
or on the distribution of power and Air Transport Association (ATA) of Safety Agency (EASA); or Airbus’s EASA
responsibilities among the various America Code 53, Fuselage. Design Organization Approval (DOA).
levels of government. For the reasons (e) Reason (h) New Repetitive Inspection Requirement
discussed above, I certify that this AD: This AD was prompted by identification of Within the compliance time specified in
1. Is not a ‘‘significant regulatory four cracks in the fastener holes of the former paragraph (h)(1), (h)(2), or (h)(3) of this AD,
action’’ under Executive Order 12866; junction at frame (FR) 68 between stringers whichever occurs latest: Accomplish a
2. Is not a ‘‘significant rule’’ under the 4 and 5, which occurred during a fatigue test, special detailed rototest inspection for fatigue
and a determination that certain compliance cracking of the frame junction holes and the
DOT Regulatory Policies and Procedures
times specified in AD 98–13–14 must be adjacent tooling hole, as applicable, of the
(44 FR 11034, February 26, 1979); right- and left-hand former junctions at FR
reduced. We are issuing this AD to prevent
3. Will not affect intrastate aviation in fatigue cracks from occurring or propagating 68, in accordance with the Accomplishment
Alaska; and in certain structures, which could adversely Instructions of Airbus Service Bulletin A320–
4. Will not have a significant affect the structural integrity of the airplane. 53–1089, Revision 04, dated June 1, 2016.
economic impact, positive or negative, Repeat the inspection thereafter at intervals
(f) Compliance not to exceed 3,800 flight cycles or 7,600
on a substantial number of small entities
Comply with this AD within the flight hours, whichever occurs first, until a
under the criteria of the Regulatory repair required by paragraph (i) of this AD is
compliance times specified, unless already
Flexibility Act. done. done or a modification specified in paragraph
List of Subjects in 14 CFR Part 39 (j) of this AD is done. Accomplishing an
(g) Retained Repetitive Inspections and inspection required by this paragraph
Air transportation, Aircraft, Aviation Repair, With Additional Methods of terminates the inspections required by
Approving Repairs paragraph (g) of this AD.
safety, Incorporation by reference,
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Safety. This paragraph restates the requirements of (1) Within 28,700 flight cycles or 57,400
paragraph (a) of AD 98–13–14, with flight hours since airplane first flight,
Adoption of the Amendment additional methods of approving repairs. For whichever occurs first.
Model A320 series airplanes, as listed in (2) Within 3,800 flight cycles or 7,600
Accordingly, under the authority Airbus Service Bulletins A320–53–1089 and flight hours, whichever occurs first, since the
delegated to me by the Administrator, A320–53–1090, both dated November 22, most recent inspection done as specified in
the FAA amends 14 CFR part 39 as 1995: Prior to the accumulation of 20,000 the Accomplishment Instructions of Airbus
follows: total flight cycles, or within 500 flight cycles Service Bulletin A320–53–1089.
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![Federal Register / Vol. 82, No. 107 / Tuesday, June 6, 2017 / Rules and Regulations 25943
(3) Within 3,800 flight cycles or 7,600 Flight Standards District Office, as identified as Revision 02, dated December 22,
flight hours after the effective date of this AD, appropriate. If sending information directly 1998.
whichever occurs first, without exceeding to the manager of the International Branch, (4) The following service information was
20,000 flight cycles since the most recent send it to the attention of the person approved for IBR on July 30, 1998, AD 98–
inspection done as specified in the identified in paragraph (m)(2) of this AD. 13–14, Amendment 39–10602 (63 FR 34556,
Accomplishment Instructions of Airbus Information may be emailed to: 9-ANM-116- June 25, 1998).
Service Bulletin A320–53–1089. AMOC-REQUESTS@faa.gov. Before using (i) Airbus Service Bulletin A320–53–1089,
any approved AMOC, notify your appropriate dated November 22, 1995.
(i) New Repair Requirement
principal inspector, or lacking a principal (ii) Airbus Service Bulletin A320–53–1090,
If any crack is detected during any inspector, the manager of the local flight dated November 22, 1995.
inspection required by paragraph (h) of this standards district office/certificate holding (5) For service information identified in
AD: Before further flight, repair, including district office. this AD, contact Airbus SAS, Airworthiness
doing all applicable related investigative (2) Contacting the Manufacturer: For any Office—EIAS, 1 Rond Point Maurice
actions, in accordance with the requirement in this AD to obtain corrective Bellonte, 31707 Blagnac Cedex, France;
Accomplishment Instructions of Airbus actions from a manufacturer, the action must telephone +33 5 61 93 36 96; fax +33 5 61
Service Bulletin A320–53–1089, Revision 04, be accomplished using a method approved 93 44 51; email account.airworth-eas@
dated June 1, 2016. Do all applicable related by the Manager, International Branch, ANM– airbus.com; Internet http://www.airbus.com.
investigative actions before further flight. 116, Transport Airplane Directorate, FAA; or (6) You may view this service information
Repair of an airplane in accordance with the the EASA; or Airbus’s EASA DOA. If at the FAA, Transport Airplane Directorate,
Accomplishment Instructions of Airbus approved by the DOA, the approval must 1601 Lind Avenue SW., Renton, WA. For
Service Bulletin A320–53–1089, Revision 04, include the DOA-authorized signature. information on the availability of this
dated June 1, 2016, constitutes terminating (3) Required for Compliance (RC): If any material at the FAA, call 425–227–1221.
action for the repetitive inspections required service information contains procedures or (7) You may view this service information
by paragraph (h) of this AD. tests that are identified as RC, those that is incorporated by reference at the
(j) New Optional Modification procedures and tests must be done to comply National Archives and Records
with this AD; any procedures or tests that are Administration (NARA). For information on
Modification of an airplane, in accordance
not identified as RC are recommended. Those the availability of this material at NARA, call
with the Accomplishment Instructions of
procedures and tests that are not identified 202–741–6030, or go to: http://
Airbus Service Bulletin A320–53–1090,
as RC may be deviated from using accepted www.archives.gov/federal-register/cfr/ibr-
Revision 02, dated December 22, 1998,
methods in accordance with the operator’s locations.html.
constitutes terminating action for the
maintenance or inspection program without
repetitive inspections required by paragraphs Issued in Renton, Washington, on May 23,
obtaining approval of an AMOC, provided
(g) and (h) of this AD, provided the 2017.
the procedures and tests identified as RC can
modification is accomplished before further Michael Kaszycki,
flight after accomplishing an inspection be done and the airplane can be put back in
an airworthy condition. Any substitutions or Acting Manager, Transport Airplane
required by paragraph (h) of this AD and no
changes to procedures or tests identified as Directorate, Aircraft Certification Service.
cracks were detected.
RC require approval of an AMOC. [FR Doc. 2017–11290 Filed 6–5–17; 8:45 am]
(k) Credit for Previous Actions BILLING CODE 4910–13–P
(m) Related Information
(1) This paragraph provides credit for the
actions required by paragraphs (h) and (i) of (1) Refer to Mandatory Continuing
this AD, if those actions were performed Airworthiness Information (MCAI) EASA AD
2015–0084, dated May 13, 2015; corrected DEPARTMENT OF TRANSPORTATION
before the effective date of this AD using the
service information identified in paragraphs May 18, 2015; for related information. This
MCAI may be found in the AD docket on the Federal Aviation Administration
(k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD.
(i) Airbus Service Bulletin A320–53–1089, Internet at http://www.regulations.gov by
Revision 01, dated June 4, 1998. searching for and locating Docket No. FAA– 14 CFR Part 39
(ii) Airbus Service Bulletin A320–53–1089, 2016–7262. [Docket No. FAA–2017–0124; Directorate
Revision 02, dated February 3, 2003. (2) For more information about this AD, Identifier 2016–NM–166–AD; Amendment
(iii) Airbus Service Bulletin A320–53– contact Sanjay Ralhan, Aerospace Engineer, 39–18911; AD 2017–11–12]
1089, Revision 03, dated March 18, 2015. International Branch, ANM 116, Transport
(2) This paragraph provides credit for the Airplane Directorate, FAA, 1601 Lind RIN 2120–AA64
actions required by paragraph (j) of this AD, Avenue SW., Renton, WA 98057–3356;
if those actions were performed before the telephone 425–227–1405; fax 425–227–1149. Airworthiness Directives; Bombardier,
effective date of this AD using the service (3) Service information identified in this Inc., Airplanes
information identified in paragraphs (k)(2)(i) AD that is not incorporated by reference is
or (k)(2)(ii) of this AD. available at the addresses specified in AGENCY: Federal Aviation
(i) Airbus Service Bulletin A320–53–1090, paragraphs (n)(5) and (n)(6) of this AD. Administration (FAA), Department of
dated November 22, 1995, which was (n) Material Incorporated by Reference Transportation (DOT).
incorporated by reference in AD 98–13–14, ACTION: Final rule.
Amendment 39–10602 (63 FR 34556, June (1) The Director of the Federal Register
25, 1998). approved the incorporation by reference SUMMARY: We are adopting a new
(ii) Airbus Service Bulletin A320–53–1090, (IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
airworthiness directive (AD) for certain
Revision 1, dated June 10, 1998, which is not Bombardier, Inc., Model BD–100–1A10
incorporated by reference in this AD. part 51.
(2) You must use this service information airplanes. This AD was prompted by
(l) Other FAA AD Provisions as applicable to do the actions required by several reports of nose wheel steering
The following provisions also apply to this this AD, unless the AD specifies otherwise. failures in service. This AD requires a
AD: (3) The following service information was part verification and replacement of
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(1) Alternative Methods of Compliance approved for IBR on July 11, 2017. certain steering manifolds. We are
(AMOCs): The Manager, International (i) Airbus Service Bulletin A320–53–1089, issuing this AD to address the unsafe
Branch, ANM–116, Transport Airplane Revision 04, dated June 1, 2016. condition on these products.
Directorate, FAA, has the authority to (ii) Airbus Service Bulletin A320–53–1090,
approve AMOCs for this AD, if requested Revision 02, dated December 22, 1998. Pages DATES: This AD is effective July 11,
using the procedures found in 14 CFR 39.19. 1, 2, 7, 8, 9, 10, and 11 of this document are 2017.
In accordance with 14 CFR 39.19, send your identified as Revision 1, dated June 10, 1998; The Director of the Federal Register
request to your principal inspector or local and pages 3, 4, 5, and 6 of this document are approved the incorporation by reference
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Document Created: 2017-06-06 06:20:53
Document Modified: 2017-06-06 06:20:53
| 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 is effective July 11, 2017. | |
| 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 | 82 FR 25940 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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