81 FR 61993 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 174 (September 8, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 174 (September 8, 2016)
| Page Range | 61993-61996 | |
| FR Document | 2016-21144 |
[Federal Register Volume 81, Number 174 (Thursday, September 8, 2016)] [Rules and Regulations] [Pages 61993-61996] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-21144] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-5814; Directorate Identifier 2014-NM-247-AD; Amendment 39-18639; AD 2016-18-09] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, and A320 series airplanes. This AD was prompted by reports of chafing damage on the fuselage skin at the bottom of certain frames, underneath the fairing structure. This AD requires repetitive detailed inspections for damage on the fuselage skin at certain frames, and applicable related investigative and corrective actions. We are issuing this AD to detect and correct damage to the fuselage skin, which could lead to crack initiation and propagation, possibly resulting in reduced structural integrity of the fuselage. DATES: This AD is effective October 13, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 13, 2016. 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- 5814. 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- 5814; 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 street 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 by adding an AD that would apply to certain Airbus Model A318, A319, and A320 series airplanes. The NPRM published in the Federal Register on November 27, 2015 (80 FR 74045) (``the NPRM''). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2014-0259, dated December 5, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A318, A319, and A320 series airplanes. The MCAI states: An operator reported finding chafing damage on the fuselage skin at the bottom of frame (FR) 34 junction between stringer (STR) 43 left hand (LH) side and right hand (RH) side on several aeroplanes, underneath the fairing structure. After investigation, a contact between the fairing nut plate and the fuselage was identified, causing damage to the fuselage. This condition, if not detected and corrected, could lead to crack initiation and propagation, possibly resulting in reduced structural integrity of the fuselage. For the reason described above, this [EASA] AD requires repetitive detailed inspections (DET) of the fuselage [for chafing] at FR 34 and provides an optional terminating action [modification of the belly fairing] to the repetitive inspections required by this [EASA] AD. Related investigative actions include a special detailed inspection of external fuselage skin panel for any cracking, and measurement of crack length and remaining thickness. Corrective actions include repair or modification of the fuselage skin panel. 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-2015-5814. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Request To Use Latest Service Information Airbus requested that we revise paragraph (i) of the NPRM to add Airbus Service Bulletin A320-53-1281, Revision 02, including Appendix 01, dated October 9, 2015. United Airlines also requested that we revise paragraph (i) of the NPRM to add Airbus Service Bulletin A320-53-1281, Revision 02, including Appendix 01, dated October 9, 2015, and provide credit for Airbus Service Bulletin A320-53-1281, Revision 01, dated December 1, 2014. United Airlines explained that Airbus Service Bulletin A320-53- 1281, Revision 02, including Appendix 01, dated October 9, 2015, includes numerous configuration additions. For the reasons stated by the commenter, we agree to revise this AD to include Airbus Service Bulletin A320-53-1281, Revision 02, including Appendix 01, dated October 9, 2015. Airbus Service Bulletin A320-53- 1281, Revision 02, including Appendix 01, [[Page 61994]] dated October 9, 2015, includes, among other things, configuration changes, new configurations, and revision of the Manufacturer Serial Numbers (MSNs), but adds no new actions. We also included Airbus Service Bulletin A320-53-1281, Revision 01, dated December 1, 2014, in paragraph (j) of this AD, as credit for certain actions performed before the effective date of this AD. Request To Allow Use of Any Airbus-Approved Corrective Action Airbus requested that we revise the NPRM to add a paragraph that allows for any corrective action provided by Airbus. Airbus stated that in case of deviation during service information embodiment, the only solution to cover the deviation for the customer is to ask for an alternative method of compliance (AMOC). Airbus included the following example, which allows any corrective action provided by Airbus: If, during modification of an aeroplane as required by paragraph (1) of this AD, a difference (see Note) is detected which makes the accomplishment of a part of the modification instructions impossible, before next flight, contact Airbus for approved instructions and accomplish those instructions accordingly, including follow-on action(s), as applicable. Note: For the purpose of this AD, the detected difference can be either: (a) a necessary design deviation due to production related concessions that directly affect the sensitive area of the modification; (b) an obvious typographical error in the SB instructions; or (c) an aircraft configuration not (yet) included in/addressed by the SB instructions. We disagree to add a paragraph that allows for any corrective action provided by Airbus, because CFR 39.19 requires approval of an AMOC for an alternative method to mitigate the risk associated with the unsafe condition addressed in an AD. The FAA uses its discretion in determining actions within the provision of an AMOC. We have made no changes to this AD in this regard. Request To Clarify Steps Required for Compliance United Airlines requested that we revise the NPRM to clarify that the actions that are required for compliance (RC) are limited to the steps in paragraphs 3.C. and 3.D. of Airbus Service Bulletin A320-53- 1287, dated July 29, 2014; Airbus Service Bulletin A320-53-1281, Revision 02, including Appendix 01, dated October 9, 2015; and Airbus Service Bulletin A320-53-1281, Revision 01, dated December 1, 2014. The commenter noted that paragraph 3.D. contains no test requirements. We agree with the request, although, as the commenter noted, paragraph 3.D. of the referenced service information does not include any test requirements. We have therefore revised paragraphs (g) and (i) of this AD to limit the requirements to paragraph 3.C., ``Procedure,'' of the service information. Request for Clarification of Compliance Methods and Intervals United Airlines requested that we clarify whether the inspections specified in the NPRM and Airbus Service Bulletin A320-53-1287, dated July 29, 2014, override the inspection methods and intervals defined in structures repair manual (SRM) 53-21-11 PB 101, and whether the terminating action in paragraph (i) of the proposed AD terminates the inspections in SRM 53-21-11 PB 101 following rework. The commenter stated that SRM 53-21-11 PB 101 defines different inspection methods, threshold, and repetitive intervals. We agree that clarification is necessary. We recognize that there may be a conflict between the inspections specified in this AD and SRM 53-21-11 PB 101. The requirements of this AD were developed to address a known unsafe condition and prevail over the actions of previously developed service information provided by a manufacturer. We have made no changes to this AD in this regard. Request for Clarification of Limit United Airlines requested that we revise paragraph (g)(3) of the proposed AD to clarify the ``limits'' of detected damage. Paragraph (g)(3) of the proposed AD refers to damage that exceeds the limits defined in Airbus Service Bulletin A320-53-1287, dated July 29, 2014. United Airlines noted that this limit relates to the remaining skin thickness as defined by SRM 53-21-11 PB 101, but the meaning of ``remaining thickness out of limits'' is inconclusive. United Airlines stated that the remaining skin thickness following a blend out could become a Category `B' repair with subsequent inspections or a Category `C' repair, eventually requiring doubler repair. United Airlines stated that Airbus Service Bulletin A320-53-1287, dated July 29, 2014, does not give instructions to accomplish a doubler repair if the remaining thickness is within SRM 53-21-11 PB 101 limits. United Airlines stated that it would not be wise to install an external doubler (unless necessary) if the remaining skin thickness is ``within limits.'' The commenter therefore proposed that we clarify the ``limit'' as an allowable rework (blend out) that does not require repair (doubler installation). We agree that clarification is necessary. If Subtask 531287-832- 002-001 of Airbus Service Bulletin A320-53-1287, dated July 29, 2014, is performed, and no crack is found, and the measurement of the remaining thickness of fuselage skin exceeds certain limits, then Airbus Service Bulletin A320-53-1287, dated July 29, 2014, specifies contacting Airbus for repair instructions. The corresponding requirement in paragraph (g)(3) of this AD, requires that those repairs be done using a method approved by the FAA, EASA, or Airbus's EASA Design Organization Approval. Repair instructions are established based on the inspection results shared with Airbus, which may vary on a case- by-case basis. We have made no changes to this final rule in this regard. Request for Inclusion of Previously Repaired Area in Inspection United Airlines requested that we revise paragraph (g)(1) of the proposed AD to include damage on the ``fuselage skin or skin repair (if present)'' for the required detailed inspection. United Airlines explained that it experienced several issues of skin chafing prior to the release of Airbus Service Bulletin A320-53-1287, dated July 29, 2014; as a result, some airplanes have needed doubler repairs due to skin wear beyond remaining thickness allowed. The commenter stated that because repairs may be present, it will not be possible to inspect the skin in the chafing area. For the reasons stated by the commenter, we agree to include previously repaired areas for the inspection required by paragraph (g)(1) of this AD. We have revised paragraph (g)(1) of this AD accordingly. 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. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. [[Page 61995]] Related Service Information Under 1 CFR Part 51 We reviewed Airbus Service Bulletin A320-53-1281, Revision 02, including Appendix 01, dated October 9, 2015; and Airbus Service Bulletin A320-53-1287, dated July 29, 2014. The service information describes procedures for a detailed inspection for damage (including chafing marks) on the fuselage skin at FR 34 between STR 43 LH and RH sides, and applicable related investigative and corrective actions. 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 642 airplanes of U.S. registry. We also estimate that it would take about 12 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts would cost about $90 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $712,620, or $1,110 per product. In addition, we estimate that any necessary follow-on actions would take about 21 work-hours and require parts costing $3,550, for a cost of $5,335 per product. We have no way of determining the number of aircraft that might need this action. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this 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 adding the following new airworthiness directive (AD): AD 2016-18-09 Airbus: Amendment 39-18639; Docket No. FAA-2015-5814; Directorate Identifier 2014-NM-247-AD. (a) Effective Date This AD is effective October 13, 2016. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification 37878 has been embodied in production, or Airbus Service Bulletin A320-53-1281 has been done in service. (1) Airbus Model A318-111, -112, -121, and -122 airplanes. (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of chafing damage on the fuselage skin at the bottom of certain frames, underneath the fairing structure. We are issuing this AD to detect and correct damage to the fuselage skin, which could lead to crack initiation and propagation, possibly resulting in reduced structural integrity of the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspection and Corrective Action (1) Within the compliance times identified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD, whichever occurs later, do a detailed inspection for damage (including chafing marks) on the fuselage skin, including previously repaired areas, at frame (FR) 34 between stringer (STR) 43 on the left-hand and right-hand sides, in accordance with paragraph 3.C., ``Procedure,'' of Airbus Service Bulletin A320-53-1287, dated July 29, 2014. Repeat the inspection thereafter at intervals not to exceed 12,000 flight cycles or 24,000 flight hours, whichever occurs first. (i) Before exceeding 12,000 flight cycles or 24,000 flight hours, whichever occurs first since the airplane's first flight. (ii) Within 5,000 flight cycles or 10,000 flight hours, whichever occurs first after the effective date of this AD. (2) If any damage is detected during any inspection required by paragraph (g)(1) of this AD, before further flight, do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1287, dated July 29, 2014, except as required by paragraph (g)(3) of this AD. (3) If any cracking is found during any related investigative action required by paragraph (g)(2) of this AD, or if any damage detected during the inspection required by paragraph (g)(1) of this AD exceeds the limits defined in the Accomplishment Instructions of Airbus Service Bulletin A320-53-1287, dated July 29, 2014, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (h) Non-Terminating Repair Action Accomplishment of a repair on an airplane as required by paragraphs (g)(2) and (g)(3) of this AD, does not constitute terminating action for the repetitive detailed inspections required by paragraph (g)(1) of this AD, unless the approved repair indicates otherwise. (i) Terminating Action for the Repetitive Detailed Inspections Modification of the belly fairing on any airplane in accordance with paragraph 3.C., ``Procedure,'' of Airbus Service Bulletin A320- 53-1281, Revision 02, including Appendix 01, dated October 9, 2015, [[Page 61996]] constitutes terminating action for the repetitive detailed inspections required by paragraph (g)(1) of this AD for that airplane. (j) Credit for Previous Actions 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 A320-53-1281, dated July 29, 2014; or Airbus Service Bulletin A320-53-1281, Revision 01, dated December 1, 2014. This service information is not incorporated by reference in this AD. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: 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]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or 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. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0259, dated December 5, 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-2015-5814. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. (m) 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. (i) Airbus Service Bulletin A320-53-1281, Revision 02, including Appendix 01, dated October 9, 2015. (ii) Airbus Service Bulletin A320-53-1287, dated July 29, 2014. (3) 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. (4) 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. (5) 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 August 24, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-21144 Filed 9-7-16; 8:45 am] BILLING CODE 4910-13-P
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(ii) Airbus Service Bulletin A300–54–0081, DATES: This AD is effective October 13, Airworthiness Information, or ‘‘the
dated August 11, 1993. 2016. MCAI’’), to correct an unsafe condition
(3) For service information identified in The Director of the Federal Register for certain Airbus Model A318, A319,
this AD, contact Airbus SAS, Airworthiness approved the incorporation by reference and A320 series airplanes. The MCAI
Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
of certain publications listed in this AD states:
telephone +33 5 61 93 36 96; fax +33 5 61 as of October 13, 2016. An operator reported finding chafing
93 44 51; email account.airworth-eas@ ADDRESSES: For service information damage on the fuselage skin at the bottom of
airbus.com; Internet http://www.airbus.com. identified in this final rule, contact frame (FR) 34 junction between stringer
You may view this service information at the Airbus, Airworthiness Office—EIAS, 1 (STR) 43 left hand (LH) side and right hand
FAA, Transport Airplane Directorate, 1601 Rond Point Maurice Bellonte, 31707 (RH) side on several aeroplanes, underneath
Lind Avenue SW., Renton, WA. For Blagnac Cedex, France; telephone +33 5 the fairing structure.
information on the availability of this After investigation, a contact between the
61 93 36 96; fax +33 5 61 93 44 51; email
material at the FAA, call 425–227–1221. fairing nut plate and the fuselage was
(4) You may view this service information account.airworth-eas@airbus.com; identified, causing damage to the fuselage.
at the FAA, Transport Airplane Directorate, Internet http://www.airbus.com. You This condition, if not detected and
1601 Lind Avenue SW., Renton, WA. For may view this referenced service corrected, could lead to crack initiation and
information on the availability of this information at the FAA, Transport propagation, possibly resulting in reduced
material at the FAA, call 425–227–1221. Airplane Directorate, 1601 Lind Avenue structural integrity of the fuselage.
(5) You may view this service information SW., Renton, WA. For information on For the reason described above, this
that is incorporated by reference at the the availability of this material at the [EASA] AD requires repetitive detailed
National Archives and Records FAA, call 425–227–1221. It is also inspections (DET) of the fuselage [for chafing]
Administration (NARA). For information on at FR 34 and provides an optional
available on the Internet at http://
the availability of this material at NARA, call terminating action [modification of the belly
202–741–6030, or go to: http:// www.regulations.gov by searching for fairing] to the repetitive inspections required
www.archives.gov/federal-register/cfr/ibr- and locating Docket No. FAA–2015– by this [EASA] AD.
locations.html. 5814.
Related investigative actions include a
Issued in Renton, Washington, on August Examining the AD Docket special detailed inspection of external
25, 2016. fuselage skin panel for any cracking,
You may examine the AD docket on
John P. Piccola, Jr., and measurement of crack length and
the Internet at http://
Acting Manager, Transport Airplane www.regulations.gov by searching for remaining thickness. Corrective actions
Directorate, Aircraft Certification Service. include repair or modification of the
and locating Docket No. FAA–2015–
[FR Doc. 2016–21283 Filed 9–7–16; 8:45 am] 5814; or in person at the Docket fuselage skin panel. You may examine
BILLING CODE 4910–13–P Management Facility between 9 a.m. the MCAI in the AD docket on the
and 5 p.m., Monday through Friday, Internet at http://www.regulations.gov
except Federal holidays. The AD docket by searching for and locating Docket No.
DEPARTMENT OF TRANSPORTATION contains this AD, the regulatory FAA–2015–5814.
Federal Aviation Administration evaluation, any comments received, and Comments
other information. The street address for
We gave the public the opportunity to
14 CFR Part 39 the Docket Office (telephone 800–647–
participate in developing this AD. The
5527) is Docket Management Facility,
[Docket No. FAA–2015–5814; Directorate following presents the comments
U.S. Department of Transportation,
Identifier 2014–NM–247–AD; Amendment received on the NPRM and the FAA’s
Docket Operations, M–30, West
39–18639; AD 2016–18–09] response to each comment.
Building Ground Floor, Room W12–140,
RIN 2120–AA64 1200 New Jersey Avenue SE., Request To Use Latest Service
Washington, DC 20590. Information
Airworthiness Directives; Airbus FOR FURTHER INFORMATION CONTACT: Airbus requested that we revise
Airplanes Sanjay Ralhan, Aerospace Engineer, paragraph (i) of the NPRM to add Airbus
AGENCY: Federal Aviation International Branch, ANM–116, Service Bulletin A320–53–1281,
Administration (FAA), Department of Transport Airplane Directorate, FAA, Revision 02, including Appendix 01,
Transportation (DOT). 1601 Lind Avenue SW., Renton, WA dated October 9, 2015.
ACTION: Final rule. 98057–3356; telephone 425–227–1405; United Airlines also requested that we
fax 425–227–1149. revise paragraph (i) of the NPRM to add
SUMMARY: We are adopting a new SUPPLEMENTARY INFORMATION: Airbus Service Bulletin A320–53–1281,
airworthiness directive (AD) for certain Revision 02, including Appendix 01,
Airbus Model A318, A319, and A320 Discussion dated October 9, 2015, and provide
series airplanes. This AD was prompted We issued a notice of proposed credit for Airbus Service Bulletin A320–
by reports of chafing damage on the rulemaking (NPRM) to amend 14 CFR 53–1281, Revision 01, dated December
fuselage skin at the bottom of certain part 39 by adding an AD that would 1, 2014. United Airlines explained that
frames, underneath the fairing structure. apply to certain Airbus Model A318, Airbus Service Bulletin A320–53–1281,
This AD requires repetitive detailed A319, and A320 series airplanes. The Revision 02, including Appendix 01,
inspections for damage on the fuselage NPRM published in the Federal dated October 9, 2015, includes
skin at certain frames, and applicable Register on November 27, 2015 (80 FR numerous configuration additions.
related investigative and corrective 74045) (‘‘the NPRM’’). For the reasons stated by the
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actions. We are issuing this AD to detect The European Aviation Safety Agency commenter, we agree to revise this AD
and correct damage to the fuselage skin, (EASA), which is the Technical Agent to include Airbus Service Bulletin
which could lead to crack initiation and for the Member States of the European A320–53–1281, Revision 02, including
propagation, possibly resulting in Union, has issued EASA AD 2014–0259, Appendix 01, dated October 9, 2015.
reduced structural integrity of the dated December 5, 2014 (referred to Airbus Service Bulletin A320–53–1281,
fuselage. after this as the Mandatory Continuing Revision 02, including Appendix 01,
VerDate Sep<11>2014 15:15 Sep 07, 2016 Jkt 238001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\08SER1.SGM 08SER1](https://thefederalregister.org/doc/81_FR_62167/page/1.svg)
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Related Service Information Under 1 the States, on the relationship between (e) Reason
CFR Part 51 the national government and the States, This AD was prompted by reports of
We reviewed Airbus Service Bulletin or on the distribution of power and chafing damage on the fuselage skin at the
responsibilities among the various bottom of certain frames, underneath the
A320–53–1281, Revision 02, including
levels of government. fairing structure. We are issuing this AD to
Appendix 01, dated October 9, 2015; detect and correct damage to the fuselage
and Airbus Service Bulletin A320–53– For the reasons discussed above, I
skin, which could lead to crack initiation and
1287, dated July 29, 2014. The service certify that this AD: propagation, possibly resulting in reduced
information describes procedures for a 1. Is not a ‘‘significant regulatory structural integrity of the fuselage.
detailed inspection for damage action’’ under Executive Order 12866;
(f) Compliance
(including chafing marks) on the 2. Is not a ‘‘significant rule’’ under the
fuselage skin at FR 34 between STR 43 DOT Regulatory Policies and Procedures Comply with this AD within the
(44 FR 11034, February 26, 1979); compliance times specified, unless already
LH and RH sides, and applicable related
done.
investigative and corrective actions. 3. Will not affect intrastate aviation in
This service information is reasonably Alaska; and (g) Repetitive Inspection and Corrective
available because the interested parties 4. Will not have a significant Action
have access to it through their normal economic impact, positive or negative, (1) Within the compliance times identified
course of business or by the means on a substantial number of small entities in paragraphs (g)(1)(i) and (g)(1)(ii) of this
identified in the ADDRESSES section. under the criteria of the Regulatory AD, whichever occurs later, do a detailed
Flexibility Act. inspection for damage (including chafing
Costs of Compliance marks) on the fuselage skin, including
We estimate that this AD affects 642 List of Subjects in 14 CFR Part 39 previously repaired areas, at frame (FR) 34
airplanes of U.S. registry. between stringer (STR) 43 on the left-hand
Air transportation, Aircraft, Aviation and right-hand sides, in accordance with
We also estimate that it would take safety, Incorporation by reference, paragraph 3.C., ‘‘Procedure,’’ of Airbus
about 12 work-hours per product to Safety. Service Bulletin A320–53–1287, dated July
comply with the basic requirements of 29, 2014. Repeat the inspection thereafter at
this AD. The average labor rate is $85 Adoption of the Amendment intervals not to exceed 12,000 flight cycles or
per work-hour. Required parts would Accordingly, under the authority 24,000 flight hours, whichever occurs first.
cost about $90 per product. Based on delegated to me by the Administrator, (i) Before exceeding 12,000 flight cycles or
these figures, we estimate the cost of the FAA amends 14 CFR part 39 as 24,000 flight hours, whichever occurs first
this AD on U.S. operators to be since the airplane’s first flight.
follows:
$712,620, or $1,110 per product. (ii) Within 5,000 flight cycles or 10,000
In addition, we estimate that any flight hours, whichever occurs first after the
PART 39—AIRWORTHINESS
necessary follow-on actions would take effective date of this AD.
DIRECTIVES (2) If any damage is detected during any
about 21 work-hours and require parts
inspection required by paragraph (g)(1) of
costing $3,550, for a cost of $5,335 per ■ 1. The authority citation for part 39 this AD, before further flight, do all
product. We have no way of continues to read as follows: applicable related investigative and
determining the number of aircraft that Authority: 49 U.S.C. 106(g), 40113, 44701. corrective actions, in accordance with the
might need this action. Accomplishment Instructions of Airbus
§ 39.13 [Amended] Service Bulletin A320–53–1287, dated July
Authority for This Rulemaking 29, 2014, except as required by paragraph
Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by adding (g)(3) of this AD.
specifies the FAA’s authority to issue the following new airworthiness (3) If any cracking is found during any
rules on aviation safety. Subtitle I, directive (AD): related investigative action required by
section 106, describes the authority of AD 2016–18–09 Airbus: Amendment 39– paragraph (g)(2) of this AD, or if any damage
the FAA Administrator. ‘‘Subtitle VII: 18639; Docket No. FAA–2015–5814; detected during the inspection required by
Directorate Identifier 2014–NM–247–AD. paragraph (g)(1) of this AD exceeds the limits
Aviation Programs,’’ describes in more defined in the Accomplishment Instructions
detail the scope of the Agency’s (a) Effective Date of Airbus Service Bulletin A320–53–1287,
authority. This AD is effective October 13, 2016. dated July 29, 2014, before further flight,
We are issuing this rulemaking under repair using a method approved by the
the authority described in ‘‘Subtitle VII, (b) Affected ADs Manager, International Branch, ANM–116,
Part A, Subpart III, Section 44701: None. Transport Airplane Directorate, FAA; or the
General requirements.’’ Under that European Aviation Safety Agency (EASA); or
(c) Applicability Airbus’s EASA Design Organization
section, Congress charges the FAA with
promoting safe flight of civil aircraft in This AD applies to the airplanes identified Approval (DOA).
in paragraphs (c)(1), (c)(2), and (c)(3) of this
air commerce by prescribing regulations AD, certificated in any category, all (h) Non-Terminating Repair Action
for practices, methods, and procedures manufacturer serial numbers, except those on Accomplishment of a repair on an airplane
the Administrator finds necessary for which Airbus Modification 37878 has been as required by paragraphs (g)(2) and (g)(3) of
safety in air commerce. This regulation embodied in production, or Airbus Service this AD, does not constitute terminating
is within the scope of that authority Bulletin A320–53–1281 has been done in action for the repetitive detailed inspections
because it addresses an unsafe condition service. required by paragraph (g)(1) of this AD,
that is likely to exist or develop on (1) Airbus Model A318–111, –112, –121, unless the approved repair indicates
products identified in this rulemaking and –122 airplanes. otherwise.
action. (2) Airbus Model A319–111, –112, –113,
(i) Terminating Action for the Repetitive
Lhorne on DSK30JT082PROD with RULES
–114, –115, –131, –132, and –133 airplanes.
Detailed Inspections
Regulatory Findings (3) Airbus Model A320–211, –212, –214,
–231, –232, and –233 airplanes. Modification of the belly fairing on any
We determined that this AD will not airplane in accordance with paragraph 3.C.,
have federalism implications under (d) Subject ‘‘Procedure,’’ of Airbus Service Bulletin
Executive Order 13132. This AD will Air Transport Association (ATA) of A320–53–1281, Revision 02, including
not have a substantial direct effect on America Code 53, Fuselage. Appendix 01, dated October 9, 2015,
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![61996 Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Rules and Regulations
constitutes terminating action for the (2) Service information identified in this prompted by a report that on some
repetitive detailed inspections required by AD that is not incorporated by reference is airplanes, during the paint removal
paragraph (g)(1) of this AD for that airplane. available at the addresses specified in process for repainting the airplane, the
paragraphs (m)(3) and (m)(4) of this AD.
(j) Credit for Previous Actions basic corrosion protection (anodizing
This paragraph provides credit for actions (m) Material Incorporated by Reference and primer) coating was sanded down
required by paragraph (i) of this AD, if those (1) The Director of the Federal Register to bare metal on the aluminum skin
actions were performed before the effective approved the incorporation by reference panels, and the bare metal might not
date of this AD using Airbus Service Bulletin (IBR) of the service information listed in this have been treated correctly for corrosion
A320–53–1281, dated July 29, 2014; or paragraph under 5 U.S.C. 552(a) and 1 CFR prevention. This AD requires an
Airbus Service Bulletin A320–53–1281, part 51. inspection of structural components of
Revision 01, dated December 1, 2014. This (2) You must use this service information
service information is not incorporated by
the airplane for any damaged protective
as applicable to do the actions required by
reference in this AD. coating; inspections of those areas for
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320–53–1281, pitting corrosion, if necessary; a
(k) Other FAA AD Provisions thickness measurement to determine if
Revision 02, including Appendix 01, dated
The following provisions also apply to this October 9, 2015. there is reduced skin thickness, if
AD: (ii) Airbus Service Bulletin A320–53–1287, necessary; and repair, if necessary. We
(1) Alternative Methods of Compliance dated July 29, 2014. are issuing this AD to detect and correct
(AMOCs): The Manager, International (3) For service information identified in
Branch, ANM–116, Transport Airplane
damaged protective coatings. This
this AD, contact Airbus, Airworthiness condition could result in pitting
Directorate, FAA, has the authority to Office—EIAS, 1 Rond Point Maurice
approve AMOCs for this AD, if requested corrosion damage; and reduced metal
Bellonte, 31707 Blagnac Cedex, France;
using the procedures found in 14 CFR 39.19. thickness, which could result in
telephone +33 5 61 93 36 96; fax +33 5 61
In accordance with 14 CFR 39.19, send your 93 44 51; email account.airworth-eas@ reduced static and fatigue strength of
request to your principal inspector or local airbus.com; Internet http://www.airbus.com. the airplane’s structural parts.
Flight Standards District Office, as (4) You may view this service information DATES: This AD is effective October 13,
appropriate. If sending information directly
to the International Branch, send it to ATTN:
at the FAA, Transport Airplane Directorate, 2016.
1601 Lind Avenue SW., Renton, WA. For The Director of the Federal Register
Sanjay Ralhan, Aerospace Engineer,
information on the availability of this approved the incorporation by reference
International Branch, ANM–116, Transport
material at the FAA, call 425–227–1221. of a certain publication listed in this AD
Airplane Directorate, FAA, 1601 Lind
(5) You may view this service information
Avenue SW., Renton, WA 98057–3356; as of October 13, 2016.
that is incorporated by reference at the
telephone 425–227–1405; fax 425–227–1149. ADDRESSES: For service information
National Archives and Records
Information may be emailed to: 9-ANM-116- identified in this final rule, contact Saab
Administration (NARA). For information on
AMOC-REQUESTS@faa.gov. Before using
the availability of this material at NARA, call AB, Saab Aeronautics, SE–581 88,
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal 202–741–6030, or go to: http:// Linköping, Sweden; telephone +46 13
inspector, the manager of the local flight www.archives.gov/federal-register/cfr/ibr- 18 5591; fax +46 13 18 4874; email
standards district office/certificate holding locations.html. saab2000.techsupport@saabgroup.com;
district office. The AMOC approval letter Issued in Renton, Washington, on August Internet http://www.saabgroup.com.
must specifically reference this AD. 24, 2016. You may view this referenced service
(2) Contacting the Manufacturer: For any John P. Piccola, Jr., information at the FAA, Transport
requirement in this AD to obtain corrective Airplane Directorate, 1601 Lind Avenue
Acting Manager, Transport Airplane
actions from a manufacturer, the action must
Directorate, Aircraft Certification Service. SW., Renton, WA. For information on
be accomplished using a method approved
by the Manager, International Branch, ANM– [FR Doc. 2016–21144 Filed 9–7–16; 8:45 am] the availability of this material at the
116, Transport Airplane Directorate, FAA; or BILLING CODE 4910–13–P FAA, call 425–227–1221. It is also
the EASA; or Airbus’s EASA DOA. If available on the Internet at http://
approved by the DOA, the approval must www.regulations.gov by searching for
include the DOA-authorized signature. DEPARTMENT OF TRANSPORTATION and locating Docket No. FAA–2016–
(3) Required for Compliance (RC): If any 6668.
service information contains procedures or Federal Aviation Administration
tests that are identified as RC, those Examining the AD Docket
procedures and tests must be done to comply You may examine the AD docket on
14 CFR Part 39
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
the Internet at http://
[Docket No. FAA–2016–6668; Directorate
procedures and tests that are not identified Identifier 2014–NM–149–AD; Amendment
www.regulations.gov by searching for
as RC may be deviated from using accepted 39–18627; AD 2016–17–14] and locating Docket No. FAA–2016–
methods in accordance with the operator’s 6668; or in person at the Docket
maintenance or inspection program without RIN 2120–AA64 Management Facility between 9 a.m.
obtaining approval of an AMOC, provided and 5 p.m., Monday through Friday,
the procedures and tests identified as RC can Airworthiness Directives; Saab AB, except Federal holidays. The AD docket
be done and the airplane can be put back in Saab Aeronautics (Type Certificate contains this AD, the regulatory
an airworthy condition. Any substitutions or Previously Held by Saab AB, Saab
changes to procedures or tests identified as
evaluation, any comments received, and
Aerosystems) Airplanes other information. The street address for
RC require approval of an AMOC.
AGENCY: Federal Aviation the Docket Office (telephone 800–647–
(l) Related Information 5527) is Docket Management Facility,
Administration (FAA), Department of
(1) Refer to Mandatory Continuing Transportation (DOT). U.S. Department of Transportation,
Lhorne on DSK30JT082PROD with RULES
Airworthiness Information (MCAI) EASA Docket Operations, M–30, West
Airworthiness Directive 2014–0259, dated ACTION: Final rule.
Building Ground Floor, Room W12–140,
December 5, 2014, for related information.
This MCAI may be found in the AD docket SUMMARY: We are adopting a new 1200 New Jersey Avenue SE.,
on the Internet at http://www.regulations.gov airworthiness directive (AD) for certain Washington, DC 20590.
by searching for and locating Docket No. Saab AB, Saab Aeronautics Model FOR FURTHER INFORMATION CONTACT:
FAA–2015–5814. SAAB 2000 airplanes. This AD was Shahram Daneshmandi, Aerospace
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Document Created: 2018-02-09 13:12:43
Document Modified: 2018-02-09 13:12:43
| 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 October 13, 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 61993 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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