82 FR 24043 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 100 (May 25, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 100 (May 25, 2017)
| Page Range | 24043-24045 | |
| FR Document | 2017-10264 |
[Federal Register Volume 82, Number 100 (Thursday, May 25, 2017)] [Rules and Regulations] [Pages 24043-24045] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-10264] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9431; Directorate Identifier 2016-NM-104-AD; Amendment 39-18897; AD 2017-10-23] 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 A321 series airplanes. This AD was prompted by a determination that cracks could develop on holes at certain fuselage frame locations. This AD requires repetitive inspections for cracking on holes at certain fuselage frame locations, and repairs if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 29, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 29, 2017. 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- 9431. 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- 9431; 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 A321 series airplanes. The NPRM published in the Federal Register on December 2, 2016 (81 FR 86975). The NPRM was prompted by a determination from fatigue testing on the Model A321 airframe that cracks could develop on holes at certain fuselage frame locations. The NPRM proposed to require repetitive inspections for cracking on holes at certain fuselage frame locations, and repairs if necessary. We are issuing this AD to detect and correct cracking at certain hole locations in the fuselage frame, which could result in reduced 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 Airworthiness Directive 2016-0106, dated June 6, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on certain Airbus Model A321 series airplanes. The MCAI states: Following a new full scale fatigue test campaign on the A321 airframe, in the context of the A321 extended service goal, it was identified that cracks could develop on holes at frame (FR) 35.2A between stringers (STR) 22 and STR 23 on right hand (RH) and left hand (LH) sides, also on aeroplanes operated in the context of design service goal. This condition, if not detected and corrected, could reduce the structural integrity of the fuselage. Prompted by these findings, Airbus developed an inspection programme, published in Service Bulletin (SB) A320-53-1315 and SB A320-53-1316, each containing instructions for a different location. [[Page 24044]] For the reasons described above, this [EASA] AD requires repetitive special detailed (rototest) inspections (SDI) of the affected holes [for cracking] and, depending on findings, accomplishment of a repair. This [EASA] AD is considered an interim action, pending development of a permanent solution. 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- 9431. 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. Request To Use Later Approved Service Information Revisions Delta Airlines (DAL) requested that we revise the NPRM to permit use of later approved revisions of service information as we have done in previous alternative methods of compliance (AMOCs). DAL stated that Airbus service bulletins are EASA approved, and through the bi-lateral agreement with the European Union, these subsequent service bulletin revisions should be allowed to be used by U.S. operators without seeking an AMOC. DAL also explained that having the ability to utilize future service bulletin revisions without seeking an AMOC is more efficient and preserves the required level of safety. We do not agree with DAL's request. While we acknowledge that we allow the use of later approved revisions of service information in AMOCs, we may not allow use of ``later FAA-approved revisions'' in an AD when referring to the service document. Doing so violates Office of the Federal Register (OFR) regulations for approval of materials ``incorporated by reference,'' as specified in 1 CFR 51.1(f). In general terms, we are required by the OFR regulations to either publish the service document contents as part of the actual AD language; or submit the service document to the OFR for approval as ``referenced'' material, in which case we may only refer to such material in the text of an AD. The AD may refer to the service document only if the OFR approved it for ``incorporation by reference.'' See 1 CFR part 51. To allow operators to use later revisions of the referenced document (issued after publication of the AD), either we must revise the AD to reference specific later revisions, or operators must request approval to use later revisions as an AMOC under the provisions of paragraph (i)(1) of this AD. We have not changed this AD in this regard. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320-53-1315, dated January 13, 2016; and Service Bulletin A320-53-1316, dated January 13, 2016. This service information describes procedures for doing a special detailed inspection for cracking at the tooling holes on frame 35.2A between stringer 22 and stringer 23, and repairs. These documents are distinct since they apply to different sides of the airplane. 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 175 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 ---------------------------------------------------------------------------------------------------------------- Inspection............ 12 work-hours x $85 per $0 $1,020 per inspection $178,500 per hour = $1,020 per cycle. inspection cycle inspection cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that will enable us to provide cost estimates for the on-condition actions specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment 0 Accordingly, under the authority delegated to me by the Administrator, [[Page 24045]] 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): 2017-10-23 Airbus: Amendment 39-18897; Docket No. FAA-2016-9431; Directorate Identifier 2016-NM-104-AD. (a) Effective Date This AD is effective June 29, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A321-111, -112, -131, -211, - 212, -213, -231, and -232 airplanes, certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a determination from fatigue testing on the Model A321 airframe that cracks could develop on holes at certain fuselage frame locations. We are issuing this AD to detect and correct cracking at certain hole locations in the fuselage frame, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Do a special detailed (rototest) inspection for cracking of the affected holes at frame 35.2A on the left-hand side and right-hand side between stringer 22 and stringer 23, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1315, dated January 13, 2016 (right-hand side); and Airbus Service Bulletin A320-53-1316, dated January 13, 2016 (left- hand side). Repeat the inspection of the affected holes thereafter at intervals not to exceed 21,500 flight cycles or 43,100 flight hours, whichever occurs first. (1) Before exceeding 25,400 total flight cycles or 50,900 total flight hours since first flight of the airplane, whichever occurs first. (2) Within 3,300 flight cycles after the effective date of this AD. (h) Repair If any crack is found during any inspection required by paragraph (g) of this AD: 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). Although the service information specified in paragraph (g) of this AD specifies to contact Airbus for repair instructions, and specifies that action as ``RC'' (Required for Compliance), this AD requires repair as specified in this paragraph. Repair of an airplane as required by this paragraph does not constitute terminating action for the repetitive actions required by paragraph (g) of this AD, unless specified otherwise in the instructions provided by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (i) 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. (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 EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (h) of this AD: 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. (j) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016-0106, dated June 6, 2016, 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-2016-9431. (k) 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 A320-53-1315, dated January 13, 2016. (ii) Airbus Service Bulletin A320-53-1316, dated January 13, 2016. (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 May 10, 2017. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-10264 Filed 5-24-17; 8:45 am] BILLING CODE 4910-13-P
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the Manager, International Branch, ANM– Issued in Renton, Washington, on May 8, and locating Docket No. FAA–2016–
116, Transport Airplane Directorate, FAA; or 2017. 9431; or in person at the Docket
EASA; or Airbus’s EASA DOA. If approved Michael Kaszycki, Management Facility between 9 a.m.
by the DOA, the approval must include the Acting Manager, Transport Airplane and 5 p.m., Monday through Friday,
DOA-authorized signature. Directorate, Aircraft Certification Service. except Federal holidays. The AD docket
(3) Required for Compliance (RC): Except
[FR Doc. 2017–10282 Filed 5–24–17; 8:45 am] contains this AD, the regulatory
as required by paragraph (g)(2) of this AD: If
any service information contains procedures BILLING CODE 4910–13–P evaluation, any comments received, and
or tests that are identified as RC, those other information. The street address for
procedures and tests must be done to comply the Docket Office (telephone 800–647–
with this AD; any procedures or tests that are DEPARTMENT OF TRANSPORTATION 5527) is Docket Management Facility,
not identified as RC are recommended. Those U.S. Department of Transportation,
procedures and tests that are not identified Federal Aviation Administration Docket Operations, M–30, West
as RC may be deviated from using accepted Building Ground Floor, Room W12–140,
methods in accordance with the operator’s 14 CFR Part 39 1200 New Jersey Avenue SE.,
maintenance or inspection program without Washington, DC 20590.
obtaining approval of an AMOC, provided [Docket No. FAA–2016–9431; Directorate
Identifier 2016–NM–104–AD; Amendment FOR FURTHER INFORMATION CONTACT:
the procedures and tests identified as RC can
39–18897; AD 2017–10–23] Sanjay Ralhan, Aerospace Engineer,
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
International Branch, ANM–116,
RIN 2120–AA64 Transport Airplane Directorate, FAA,
changes to procedures or tests identified as
RC require approval of an AMOC. Airworthiness Directives; Airbus 1601 Lind Avenue SW., Renton, WA
Airplanes 98057–3356; telephone 425–227–1405;
(l) Related Information fax 425–227–1149.
(1) Refer to Mandatory Continuing AGENCY: Federal Aviation SUPPLEMENTARY INFORMATION:
Airworthiness Information (MCAI) EASA AD Administration (FAA), Department of
2015–0214, dated October 19, 2015, for Discussion
Transportation (DOT).
related information. This MCAI may be We issued a notice of proposed
found in the AD docket on the Internet at ACTION: Final rule.
rulemaking (NPRM) to amend 14 CFR
http://www.regulations.gov by searching for
and locating Docket No. FAA–2016–8849. SUMMARY: We are adopting a new part 39 by adding an AD that would
(2) For more information about this AD, airworthiness directive (AD) for certain apply to certain Airbus Model A321
contact Vladimir Ulyanov, Aerospace Airbus Model A321 series airplanes. series airplanes. The NPRM published
Engineer, International Branch, ANM–116, This AD was prompted by a in the Federal Register on December 2,
Transport Airplane Directorate, FAA, 1601 determination that cracks could develop 2016 (81 FR 86975). The NPRM was
Lind Avenue SW., Renton, WA 98057–3356; on holes at certain fuselage frame prompted by a determination from
telephone: 425–227–1138; fax: 425–227– locations. This AD requires repetitive fatigue testing on the Model A321
1149. inspections for cracking on holes at airframe that cracks could develop on
(3) Service information identified in this certain fuselage frame locations, and holes at certain fuselage frame locations.
AD that is not incorporated by reference is The NPRM proposed to require
repairs if necessary. We are issuing this
available at the addresses specified in
AD to address the unsafe condition on repetitive inspections for cracking on
paragraphs (m)(3) and (m)(4) of this AD.
these products. holes at certain fuselage frame locations,
(m) Material Incorporated by Reference and repairs if necessary. We are issuing
DATES: This AD is effective June 29,
(1) The Director of the Federal Register 2017. this AD to detect and correct cracking at
approved the incorporation by reference The Director of the Federal Register certain hole locations in the fuselage
(IBR) of the service information listed in this approved the incorporation by reference frame, which could result in reduced
paragraph under 5 U.S.C. 552(a) and 1 CFR structural integrity of the airplane.
part 51.
of certain publications listed in this AD
as of June 29, 2017. The European Aviation Safety Agency
(2) You must use this service information (EASA), which is the Technical Agent
as applicable to do the actions required by ADDRESSES: For service information
for the Member States of the European
this AD, unless this AD specifies otherwise. identified in this final rule, contact Union, has issued EASA Airworthiness
(i) Airbus Service Bulletin A330–71–3028, Airbus, Airworthiness Office—EIAS, 1
Revision 02, dated August 31, 2015. Directive 2016–0106, dated June 6, 2016
Rond Point Maurice Bellonte, 31707 (referred to after this as the Mandatory
(ii) Reserved. Blagnac Cedex, France; telephone +33 5 Continuing Airworthiness Information,
(3) For service information identified in
61 93 36 96; fax +33 5 61 93 44 51; email or ‘‘the MCAI’’), to correct an unsafe
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
account.airworth-eas@airbus.com; condition on certain Airbus Model A321
31707 Blagnac Cedex, France; telephone +33 Internet http://www.airbus.com. You series airplanes. The MCAI states:
5 61 93 36 96; fax +33 5 61 93 45 80; email may view this referenced service
information at the FAA, Transport Following a new full scale fatigue test
airworthiness.A330-A340@airbus.com;
Internet http://www.airbus.com. Airplane Directorate, 1601 Lind Avenue campaign on the A321 airframe, in the
context of the A321 extended service goal, it
(4) You may view this service information SW., Renton, WA. For information on was identified that cracks could develop on
at the FAA, Transport Airplane Directorate, the availability of this material at the holes at frame (FR) 35.2A between stringers
1601 Lind Avenue SW., Renton, WA. For FAA, call 425–227–1221. It is also (STR) 22 and STR 23 on right hand (RH) and
information on the availability of this available on the Internet at http:// left hand (LH) sides, also on aeroplanes
material at the FAA, call 425–227–1221. www.regulations.gov by searching for operated in the context of design service goal.
(5) You may view this service information This condition, if not detected and
that is incorporated by reference at the
and locating Docket No. FAA–2016–
9431. corrected, could reduce the structural
National Archives and Records integrity of the fuselage.
Administration (NARA). For information on Examining the AD Docket Prompted by these findings, Airbus
the availability of this material at NARA, call developed an inspection programme,
202–741–6030, or go to http:// You may examine the AD docket on published in Service Bulletin (SB) A320–53–
www.archives.gov/federal-register/cfr/ibr- the Internet at http:// 1315 and SB A320–53–1316, each containing
locations.html. www.regulations.gov by searching for instructions for a different location.
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For the reasons described above, this AMOC is more efficient and preserves determined that air safety and the
[EASA] AD requires repetitive special the required level of safety. public interest require adopting this AD
detailed (rototest) inspections (SDI) of the We do not agree with DAL’s request. as proposed except for minor editorial
affected holes [for cracking] and, depending While we acknowledge that we allow
on findings, accomplishment of a repair.
changes. We have determined that these
the use of later approved revisions of minor changes:
This [EASA] AD is considered an interim
service information in AMOCs, we may
action, pending development of a permanent
not allow use of ‘‘later FAA-approved • Are consistent with the intent that
solution. was proposed in the NPRM for
revisions’’ in an AD when referring to
You may examine the MCAI in the the service document. Doing so violates correcting the unsafe condition; and
AD docket on the Internet at http:// Office of the Federal Register (OFR) • Do not add any additional burden
www.regulations.gov by searching for regulations for approval of materials upon the public than was already
and locating Docket No. FAA–2016– ‘‘incorporated by reference,’’ as proposed in the NPRM.
9431. specified in 1 CFR 51.1(f).
In general terms, we are required by Related Service Information Under 1
Comments the OFR regulations to either publish CFR Part 51
We gave the public the opportunity to the service document contents as part of
Airbus has issued Service Bulletin
participate in developing this AD. The the actual AD language; or submit the
A320–53–1315, dated January 13, 2016;
following presents the comment service document to the OFR for
approval as ‘‘referenced’’ material, in and Service Bulletin A320–53–1316,
received on the NPRM and the FAA’s dated January 13, 2016. This service
response. which case we may only refer to such
material in the text of an AD. The AD information describes procedures for
Request To Use Later Approved Service may refer to the service document only doing a special detailed inspection for
Information Revisions if the OFR approved it for cracking at the tooling holes on frame
‘‘incorporation by reference.’’ See 1 CFR 35.2A between stringer 22 and stringer
Delta Airlines (DAL) requested that part 51. 23, and repairs. These documents are
we revise the NPRM to permit use of To allow operators to use later distinct since they apply to different
later approved revisions of service revisions of the referenced document sides of the airplane. This service
information as we have done in (issued after publication of the AD), information is reasonably available
previous alternative methods of either we must revise the AD to because the interested parties have
compliance (AMOCs). DAL stated that reference specific later revisions, or access to it through their normal course
Airbus service bulletins are EASA operators must request approval to use of business or by the means identified
approved, and through the bi-lateral later revisions as an AMOC under the in the ADDRESSES section.
agreement with the European Union, provisions of paragraph (i)(1) of this AD.
these subsequent service bulletin We have not changed this AD in this Costs of Compliance
revisions should be allowed to be used regard.
by U.S. operators without seeking an We estimate that this AD affects 175
AMOC. DAL also explained that having Conclusion airplanes of U.S. registry.
the ability to utilize future service We reviewed the relevant data, We estimate the following costs to
bulletin revisions without seeking an considered the comment received, and comply with this AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspection ...... 12 work-hours × $85 per hour = $1,020 per inspec- $0 $1,020 per inspection $178,500 per inspection
tion cycle. cycle. cycle
We have received no definitive data for practices, methods, and procedures 1. Is not a ‘‘significant regulatory
that will enable us to provide cost the Administrator finds necessary for action’’ under Executive Order 12866;
estimates for the on-condition actions safety in air commerce. This regulation 2. Is not a ‘‘significant rule’’ under the
specified in this AD. is within the scope of that authority DOT Regulatory Policies and Procedures
because it addresses an unsafe condition (44 FR 11034, February 26, 1979);
Authority for This Rulemaking
that is likely to exist or develop on 3. Will not affect intrastate aviation in
Title 49 of the United States Code products identified in this rulemaking Alaska; and
specifies the FAA’s authority to issue action. 4. Will not have a significant
rules on aviation safety. Subtitle I, Regulatory Findings economic impact, positive or negative,
section 106, describes the authority of on a substantial number of small entities
the FAA Administrator. ‘‘Subtitle VII: We determined that this AD will not under the criteria of the Regulatory
Aviation Programs,’’ describes in more have federalism implications under Flexibility Act.
detail the scope of the Agency’s Executive Order 13132. This AD will
authority. not have a substantial direct effect on List of Subjects in 14 CFR Part 39
We are issuing this rulemaking under the States, on the relationship between Air transportation, Aircraft, Aviation
the authority described in ‘‘Subtitle VII, the national government and the States, safety, Incorporation by reference,
Part A, Subpart III, Section 44701: or on the distribution of power and Safety.
General requirements.’’ Under that responsibilities among the various
Adoption of the Amendment
section, Congress charges the FAA with levels of government.
promoting safe flight of civil aircraft in For the reasons discussed above, I ■ Accordingly, under the authority
air commerce by prescribing regulations certify that this AD: delegated to me by the Administrator,
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the FAA amends 14 CFR part 39 as Branch, ANM–116, Transport Airplane June 6, 2016, for related information. This
follows: Directorate, FAA; or the European Aviation MCAI may be found in the AD docket on the
Safety Agency (EASA); or Airbus’s EASA Internet at http://www.regulations.gov by
PART 39—AIRWORTHINESS Design Organization Approval (DOA). searching for and locating Docket No. FAA–
DIRECTIVES Although the service information specified in 2016–9431.
paragraph (g) of this AD specifies to contact
(k) Material Incorporated by Reference
■ 1. The authority citation for part 39 Airbus for repair instructions, and specifies
continues to read as follows: that action as ‘‘RC’’ (Required for (1) The Director of the Federal Register
Compliance), this AD requires repair as approved the incorporation by reference
Authority: 49 U.S.C. 106(g), 40113, 44701. specified in this paragraph. Repair of an (IBR) of the service information listed in this
airplane as required by this paragraph does paragraph under 5 U.S.C. 552(a) and 1 CFR
§ 39.13 [Amended]
not constitute terminating action for the part 51.
■ 2. The FAA amends § 39.13 by adding repetitive actions required by paragraph (g) of (2) You must use this service information
the following new airworthiness this AD, unless specified otherwise in the as applicable to do the actions required by
directive (AD): instructions provided by the Manager, this AD, unless this AD specifies otherwise.
2017–10–23 Airbus: Amendment 39–18897; International Branch, ANM–116, Transport (i) Airbus Service Bulletin A320–53–1315,
Docket No. FAA–2016–9431; Directorate Airplane Directorate, FAA; or EASA; or dated January 13, 2016.
Identifier 2016–NM–104–AD. Airbus’s EASA DOA. (ii) Airbus Service Bulletin A320–53–1316,
dated January 13, 2016.
(a) Effective Date (i) Other FAA AD Provisions (3) For service information identified in
This AD is effective June 29, 2017. The following provisions also apply to this this AD, contact Airbus, Airworthiness
AD: Office—EIAS, 1 Rond Point Maurice
(b) Affected ADs (1) Alternative Methods of Compliance Bellonte, 31707 Blagnac Cedex, France;
None. (AMOCs): The Manager, International telephone +33 5 61 93 36 96; fax +33 5 61
Branch, ANM–116, Transport Airplane 93 44 51; email account.airworth-eas@
(c) Applicability Directorate, FAA, has the authority to airbus.com; Internet http://www.airbus.com.
This AD applies to Airbus Model A321– approve AMOCs for this AD, if requested (4) You may view this service information
111, –112, –131, –211, –212, –213, –231, and using the procedures found in 14 CFR 39.19. at the FAA, Transport Airplane Directorate,
–232 airplanes, certificated in any category, In accordance with 14 CFR 39.19, send your 1601 Lind Avenue SW., Renton, WA. For
all manufacturer serial numbers. request to your principal inspector or local information on the availability of this
(d) Subject Flight Standards District Office, as material at the FAA, call 425–227–1221.
appropriate. If sending information directly (5) You may view this service information
Air Transport Association (ATA) of to the International Branch, send it to ATTN: that is incorporated by reference at the
America Code 53, Fuselage. Sanjay Ralhan, Aerospace Engineer, National Archives and Records
(e) Reason International Branch, ANM–116, Transport Administration (NARA). For information on
Airplane Directorate, FAA, 1601 Lind the availability of this material at NARA, call
This AD was prompted by a determination Avenue SW., Renton, WA 98057–3356; 202–741–6030, or go to: http://
from fatigue testing on the Model A321 telephone 425–227–1405; fax 425–227–1149. www.archives.gov/federal-register/cfr/ibr-
airframe that cracks could develop on holes Information may be emailed to: 9-ANM-116- locations.html.
at certain fuselage frame locations. We are AMOC-REQUESTS@faa.gov. Before using
issuing this AD to detect and correct cracking Issued in Renton, Washington, on May 10,
any approved AMOC, notify your appropriate
at certain hole locations in the fuselage 2017.
principal inspector, or lacking a principal
frame, which could result in reduced Jeffrey E. Duven,
inspector, the manager of the local flight
structural integrity of the airplane. Manager, Transport Airplane Directorate,
standards district office/certificate holding
(f) Compliance district office. Aircraft Certification Service.
Comply with this AD within the (2) Contacting the Manufacturer: For any [FR Doc. 2017–10264 Filed 5–24–17; 8:45 am]
compliance times specified, unless already requirement in this AD to obtain corrective BILLING CODE 4910–13–P
done. actions from a manufacturer, the action must
be accomplished using a method approved
(g) Repetitive Inspections by the Manager, International Branch, ANM–
DEPARTMENT OF TRANSPORTATION
At the later of the times specified in 116, Transport Airplane Directorate, FAA; or
paragraphs (g)(1) and (g)(2) of this AD: Do a EASA; or Airbus’s EASA DOA. If approved
Federal Aviation Administration
special detailed (rototest) inspection for by the DOA, the approval must include the
cracking of the affected holes at frame 35.2A DOA-authorized signature.
on the left-hand side and right-hand side (3) Required for Compliance (RC): Except 14 CFR Part 39
between stringer 22 and stringer 23, in as required by paragraph (h) of this AD: If [Docket No. FAA–2017–0048; Directorate
accordance with the Accomplishment any service information contains procedures Identifier 2016–CE–035–AD; Amendment
Instructions of Airbus Service Bulletin A320– or tests that are identified as RC, those 39–18876; AD 2017–10–02]
53–1315, dated January 13, 2016 (right-hand procedures and tests must be done to comply
side); and Airbus Service Bulletin A320–53– with this AD; any procedures or tests that are RIN 2120–AA64
1316, dated January 13, 2016 (left-hand side). not identified as RC are recommended. Those
Repeat the inspection of the affected holes procedures and tests that are not identified Airworthiness Directives; Slingsby
thereafter at intervals not to exceed 21,500 as RC may be deviated from using accepted Aviation Ltd. Airplanes
flight cycles or 43,100 flight hours, methods in accordance with the operator’s
whichever occurs first. maintenance or inspection program without AGENCY: Federal Aviation
(1) Before exceeding 25,400 total flight obtaining approval of an AMOC, provided Administration (FAA), Department of
cycles or 50,900 total flight hours since first the procedures and tests identified as RC can Transportation (DOT).
flight of the airplane, whichever occurs first. be done and the airplane can be put back in ACTION: Final rule.
(2) Within 3,300 flight cycles after the an airworthy condition. Any substitutions or
effective date of this AD. changes to procedures or tests identified as SUMMARY: We are superseding
RC require approval of an AMOC.
(h) Repair airworthiness directive (AD) 2015–11–
If any crack is found during any inspection (j) Related Information 01 for Slingsby Aviation Ltd. Models
required by paragraph (g) of this AD: Before Refer to Mandatory Continuing T67M260 and T67M260–T3A airplanes.
further flight, repair using a method Airworthiness Information (MCAI) EASA This AD results from mandatory
approved by the Manager, International Airworthiness Directive 2016–0106, dated continuing airworthiness information
VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 PO 00000 Frm 00047 Fmt 4700 Sfmt 4700 E:\FR\FM\25MYR1.SGM 25MYR1](https://thefederalregister.org/doc/82_FR_24143/page/3.svg)
Document Created: 2018-11-08 08:52:28
Document Modified: 2018-11-08 08:52:28
| 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 June 29, 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 24043 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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