82 FR 33002 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 137 (July 19, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 137 (July 19, 2017)
| Page Range | 33002-33004 | |
| FR Document | 2017-14588 |
[Federal Register Volume 82, Number 137 (Wednesday, July 19, 2017)] [Rules and Regulations] [Pages 33002-33004] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-14588] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9498; Directorate Identifier 2016-NM-105-AD; Amendment 39-18958; AD 2017-14-14] 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 all Airbus Model A321 series airplanes. This AD was prompted by a determination from fatigue testing that cracks could develop in the cabin floor beam junction at certain fuselage frame locations. This AD requires repetitive inspections for cracking in the cabin floor beam junction at certain fuselage frame locations, and repair if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 23, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 23, 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-2016-9498. 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- 9498; 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 all Airbus Model A321 series airplanes. The NPRM published in the Federal Register on December 16, 2016 (81 FR 91060). The NPRM was prompted by a determination from fatigue testing on the Model A321 airframe that cracks could develop in the cabin floor beam junction at certain fuselage frame locations. The NPRM proposed to require repetitive inspections for cracking in the cabin floor beam junction at certain fuselage frame locations, and repair if necessary. We are issuing this AD to detect and correct cracking in the cabin floor beam junction at certain fuselage frame locations, 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 AD 2016-0105, dated June 6, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on all Airbus Model A321 series airplanes. The MCAI states: Following the results of 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 in the cabin floor beam junctions at fuselage frame (FR) 35.1 and FR 35.2, on both left hand (LH) and right hand (RH) 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) A320-53-1317, SB A320- 53-1318, SB A320-53-1319, and SB A320-53-1320, each containing instructions for a different location. For the reasons described above, this [EASA] AD requires repetitive detailed inspections (DET) of the affected cabin floor beam junctions [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- 9498. 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 proposed AD 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. DAL added that they operate airplanes that are not listed in the service bulletin applicability, but are included in the proposed AD. DAL claimed that without a provision allowing later approved revisions, they might have to apply for multiple AMOCs as the service information is updated. We do not agree with DAL's request. We may not refer to any document that does not yet exist in an AD. In general terms, we are required by Office of the Federal Register (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 [[Page 33003]] 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. In addition, in accordance with 14 CFR part 39.27, if there is a conflict between an AD and service information, operators must follow the requirements of the 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 We reviewed the following service information, which describes procedures for inspections for cracking on the frame to cabin floor beam junction at certain fuselage frame locations, and repairs. This service information is distinct because it applies to different locations on the airplanes. Airbus Service Bulletin A320-53-1317, dated December 15, 2015 (FR 35.1 on the right-hand side). Airbus Service Bulletin A320-53-1318, dated October 9, 2015 (FR 35.1 on the left-hand side). Airbus Service Bulletin A320-53-1319, dated October 9, 2015 (FR 35.2 on the right-hand side). Airbus Service Bulletin A320-53-1320, dated October 9, 2015 (FR 35.2 on the left-hand side). 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............... 6 work-hours x $85 per $0 $510 per inspection $89,250 per hour = $510 per cycle. inspection cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2017-14-14 Airbus: Amendment 39-18958; Docket No. FAA-2016-9498; Directorate Identifier 2016-NM-105-AD. (a) Effective Date This AD is effective August 23, 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 in the cabin floor beam junction at certain fuselage frame locations. We are issuing this AD to detect and correct cracking in the cabin floor beam junction at certain fuselage frame locations, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. [[Page 33004]] (g) Repetitive Inspections Before exceeding 36,900 total flight cycles since first flight of the airplane, or within 2,100 flight cycles after the effective date of this AD, whichever occurs later: Do a detailed inspection for cracking of the frame to cabin floor beam junction on the aft and forward sides at frame (FR) 35.1 and FR 35.2 on the left-hand and right-hand sides, in accordance with the Accomplishment Instructions of the Airbus service information specified in paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD. Repeat the inspection of the frame to cabin floor beam junction on the aft and forward sides at FR 35.1 and FR 35.2 on the left-hand and right-hand sides thereafter at intervals not to exceed 15,300 flight cycles. (1) Airbus Service Bulletin A320-53-1317, dated December 15, 2015 (FR 35.1 right-hand side). (2) Airbus Service Bulletin A320-53-1318, dated October 9, 2015 (FR 35.1 left-hand side). (3) Airbus Service Bulletin A320-53-1319, dated October 9, 2015 (FR 35.2 right-hand side). (4) Airbus Service Bulletin A320-53-1320, dated October 9, 2015 (FR 35.2 left-hand side). (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 otherwise specified 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 the attention of the person identified in paragraph (j)(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 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 (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016-0105, 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-2016-9498. (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. Information may be emailed to: [email protected]. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (k)(3) and (k)(4) of this AD. (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 A320-53-1317, dated December 15, 2015. (ii) Airbus Service Bulletin A320-53-1318, dated October 9, 2015. (iii) Airbus Service Bulletin A320-53-1319, dated October 9, 2015. (iv) Airbus Service Bulletin A320-53-1320, dated October 9, 2015. (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 June 29, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-14588 Filed 7-18-17; 8:45 am] BILLING CODE 4910-13-P
![33002 Federal Register / Vol. 82, No. 137 / Wednesday, July 19, 2017 / Rules and Regulations
* * * * * Examining the AD Docket This condition, if not detected and
corrected, could reduce the structural
Dated at Rockville, Maryland, this 10th day You may examine the AD docket on integrity of the fuselage.
of July 2017. the Internet at http:// Prompted by these findings, Airbus
For the Nuclear Regulatory Commission. www.regulations.gov by searching for developed an inspection programme,
Cindy Bladey, and locating Docket No. FAA–2016– published in Service Bulletin (SB) A320–53–
Chief, Rules, Announcements and Directives 9498; or in person at the Docket 1317, SB A320–53–1318, SB A320–53–1319,
Branch, Division of Administrative Services, Management Facility between 9 a.m. and SB A320–53–1320, each containing
Office of Administration. and 5 p.m., Monday through Friday, instructions for a different location.
except Federal holidays. The AD docket For the reasons described above, this
[FR Doc. 2017–14717 Filed 7–18–17; 8:45 am]
[EASA] AD requires repetitive detailed
BILLING CODE 7590–01–P contains this AD, the regulatory inspections (DET) of the affected cabin floor
evaluation, any comments received, and beam junctions [for cracking] and, depending
other information. The street address for on findings, accomplishment of a repair.
the Docket Office (telephone: 800–647– This [EASA] AD is considered an interim
DEPARTMENT OF TRANSPORTATION
5527) is Docket Management Facility, action, pending development of a permanent
Federal Aviation Administration U.S. Department of Transportation, solution.
Docket Operations, M–30, West * * * * *
14 CFR Part 39 Building Ground Floor, Room W12–140,
You may examine the MCAI in the
1200 New Jersey Avenue SE.,
AD docket on the Internet at http://
[Docket No. FAA–2016–9498; Directorate Washington, DC 20590.
Identifier 2016–NM–105–AD; Amendment www.regulations.gov by searching for
FOR FURTHER INFORMATION CONTACT:
39–18958; AD 2017–14–14] and locating Docket No. FAA–2016–
Sanjay Ralhan, Aerospace Engineer, 9498.
RIN 2120–AA64 International Branch, ANM–116,
Transport Airplane Directorate, FAA, Comments
Airworthiness Directives; Airbus 1601 Lind Avenue SW., Renton, WA We gave the public the opportunity to
Airplanes 98057–3356; telephone: 425–227–1405; participate in developing this AD. The
fax: 425–227–1149. following presents the comment
AGENCY: Federal Aviation
SUPPLEMENTARY INFORMATION: received on the NPRM and the FAA’s
Administration (FAA), Department of
Transportation (DOT). Discussion response.
ACTION: Final rule. We issued a notice of proposed Request To Use Later Approved Service
rulemaking (NPRM) to amend 14 CFR Information Revisions
SUMMARY: We are adopting a new part 39 by adding an AD that would Delta Airlines (DAL) requested that
airworthiness directive (AD) for all apply to all Airbus Model A321 series we revise the proposed AD to permit
Airbus Model A321 series airplanes. airplanes. The NPRM published in the use of later approved revisions of
This AD was prompted by a Federal Register on December 16, 2016 service information as we have done in
determination from fatigue testing that (81 FR 91060). The NPRM was previous alternative methods of
cracks could develop in the cabin floor prompted by a determination from compliance (AMOCs). DAL stated that
beam junction at certain fuselage frame fatigue testing on the Model A321 Airbus service bulletins are EASA
locations. This AD requires repetitive airframe that cracks could develop in approved, and through the bi-lateral
inspections for cracking in the cabin the cabin floor beam junction at certain agreement with the European Union,
floor beam junction at certain fuselage fuselage frame locations. The NPRM these subsequent service bulletin
frame locations, and repair if necessary. proposed to require repetitive revisions should be allowed to be used
We are issuing this AD to address the inspections for cracking in the cabin by U.S. operators without seeking an
unsafe condition on these products. floor beam junction at certain fuselage AMOC. DAL also explained that having
DATES: This AD is effective August 23, frame locations, and repair if necessary. the ability to utilize future service
2017. We are issuing this AD to detect and bulletin revisions without seeking an
The Director of the Federal Register correct cracking in the cabin floor beam AMOC is more efficient and preserves
approved the incorporation by reference junction at certain fuselage frame the required level of safety. DAL added
of certain publications listed in this AD locations, which could result in reduced that they operate airplanes that are not
as of August 23, 2017. structural integrity of the airplane. listed in the service bulletin
ADDRESSES: For service information The European Aviation Safety Agency applicability, but are included in the
identified in this final rule, contact (EASA), which is the Technical Agent proposed AD. DAL claimed that without
Airbus, Airworthiness Office—EIAS, 1 for the Member States of the European a provision allowing later approved
Rond Point Maurice Bellonte, 31707 Union, has issued EASA AD 2016–0105, revisions, they might have to apply for
Blagnac Cedex, France; telephone: +33 5 dated June 6, 2016 (referred to after this multiple AMOCs as the service
61 93 36 96; fax: +33 5 61 93 44 51; as the Mandatory Continuing information is updated.
email: account.airworth-eas@ Airworthiness Information, or ‘‘the We do not agree with DAL’s request.
airbus.com; Internet: http:// MCAI’’), to correct an unsafe condition We may not refer to any document that
www.airbus.com. You may view this on all Airbus Model A321 series does not yet exist in an AD. In general
referenced service information at the airplanes. The MCAI states: terms, we are required by Office of the
FAA, Transport Airplane Directorate, Following the results of a new full scale Federal Register (OFR) regulations to
mstockstill on DSK30JT082PROD with RULES
1601 Lind Avenue SW., Renton, WA. fatigue test campaign on the A321 airframe either publish the service document
For information on the availability of in the context of the A321 extended service contents as part of the actual AD
this material at the FAA, call 425–227– goal, it was identified that cracks could language; or submit the service
develop in the cabin floor beam junctions at
1221. It is also available on the Internet fuselage frame (FR) 35.1 and FR 35.2, on both document to the OFR for approval as
at http://www.regulations.gov by left hand (LH) and right hand (RH) sides, also ‘‘referenced’’ material, in which case we
searching for and locating Docket No. on aeroplanes operated in the context of may only refer to such material in the
FAA–2016–9498. design service goal. text of an AD. The AD may refer to the
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service document only if the OFR as proposed except for minor editorial • Airbus Service Bulletin A320–53–
approved it for ‘‘incorporation by changes. We have determined that these 1317, dated December 15, 2015 (FR 35.1
reference.’’ See 1 CFR part 51. minor changes: on the right-hand side).
To allow operators to use later • Are consistent with the intent that • Airbus Service Bulletin A320–53–
revisions of the referenced document was proposed in the NPRM for 1318, dated October 9, 2015 (FR 35.1 on
(issued after publication of the AD), the left-hand side).
correcting the unsafe condition; and
either we must revise the AD to • Airbus Service Bulletin A320–53–
reference specific later revisions, or • Do not add any additional burden 1319, dated October 9, 2015 (FR 35.2 on
operators must request approval to use upon the public than was already the right-hand side).
later revisions as an AMOC under the proposed in the NPRM. • Airbus Service Bulletin A320–53–
provisions of paragraph (i)(1) of this AD. 1320, dated October 9, 2015 (FR 35.2 on
Related Service Information Under 1
In addition, in accordance with 14 the left-hand side).
CFR Part 51
CFR part 39.27, if there is a conflict This service information is reasonably
between an AD and service information, We reviewed the following service available because the interested parties
operators must follow the requirements information, which describes have access to it through their normal
of the AD. We have not changed this AD procedures for inspections for cracking course of business or by the means
in this regard. on the frame to cabin floor beam identified in the ADDRESSES section.
Conclusion junction at certain fuselage frame Costs of Compliance
locations, and repairs. This service
We reviewed the relevant data, We estimate that this AD affects 175
considered the comment received, and information is distinct because it airplanes of U.S. registry.
determined that air safety and the applies to different locations on the We estimate the following costs to
public interest require adopting this AD airplanes. comply with this AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspection ......... 6 work-hours × $85 per hour = $510 per inspection $0 $510 per inspection cycle $89,250 per inspection
cycle. cycle.
We have received no definitive data or on the distribution of power and § 39.13 [Amended]
that would enable us to provide cost responsibilities among the various
estimates for the on-condition actions levels of government. ■ 2. The FAA amends § 39.13 by adding
specified in this AD. the following new airworthiness
For the reasons discussed above, I directive (AD):
Authority for This Rulemaking certify that this AD:
2017–14–14 Airbus: Amendment 39–18958;
Title 49 of the United States Code 1. Is not a ‘‘significant regulatory Docket No. FAA–2016–9498; Directorate
specifies the FAA’s authority to issue action’’ under Executive Order 12866; Identifier 2016–NM–105–AD.
rules on aviation safety. Subtitle I, 2. Is not a ‘‘significant rule’’ under the
(a) Effective Date
section 106, describes the authority of DOT Regulatory Policies and Procedures
the FAA Administrator. ‘‘Subtitle VII: (44 FR 11034, February 26, 1979); This AD is effective August 23, 2017.
Aviation Programs,’’ describes in more 3. Will not affect intrastate aviation in (b) Affected ADs
detail the scope of the Agency’s Alaska; and None.
authority. 4. Will not have a significant
We are issuing this rulemaking under (c) Applicability
economic impact, positive or negative,
the authority described in ‘‘Subtitle VII, on a substantial number of small entities
This AD applies to Airbus Model A321–
Part A, Subpart III, Section 44701: 111, –112, –131, –211, –212, –213, –231, and
under the criteria of the Regulatory –232 airplanes, certificated in any category,
General requirements.’’ Under that Flexibility Act.
section, Congress charges the FAA with all manufacturer serial numbers.
promoting safe flight of civil aircraft in List of Subjects in 14 CFR Part 39 (d) Subject
air commerce by prescribing regulations Air Transport Association (ATA) of
for practices, methods, and procedures Air transportation, Aircraft, Aviation
safety, Incorporation by reference, America Code 53, Fuselage.
the Administrator finds necessary for
safety in air commerce. This regulation Safety. (e) Reason
is within the scope of that authority Adoption of the Amendment This AD was prompted by a determination
because it addresses an unsafe condition from fatigue testing on the Model A321
that is likely to exist or develop on Accordingly, under the authority airframe that cracks could develop in the
products identified in this rulemaking delegated to me by the Administrator, cabin floor beam junction at certain fuselage
action. the FAA amends 14 CFR part 39 as frame locations. We are issuing this AD to
follows: detect and correct cracking in the cabin floor
Regulatory Findings beam junction at certain fuselage frame
mstockstill on DSK30JT082PROD with RULES
We determined that this AD will not PART 39—AIRWORTHINESS locations, which could result in reduced
DIRECTIVES structural integrity of the airplane.
have federalism implications under
Executive Order 13132. This AD will (f) Compliance
not have a substantial direct effect on ■ 1. The authority citation for part 39
Comply with this AD within the
the States, on the relationship between continues to read as follows: compliance times specified, unless already
the national government and the States, Authority: 49 U.S.C. 106(g), 40113, 44701. done.
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(g) Repetitive Inspections standards district office/certificate holding 1601 Lind Avenue SW., Renton, WA. For
Before exceeding 36,900 total flight cycles district office. information on the availability of this
since first flight of the airplane, or within (2) Contacting the Manufacturer: For any material at the FAA, call 425–227–1221.
2,100 flight cycles after the effective date of requirement in this AD to obtain corrective (5) You may view this service information
this AD, whichever occurs later: Do a actions from a manufacturer, the action must that is incorporated by reference at the
detailed inspection for cracking of the frame be accomplished using a method approved National Archives and Records
to cabin floor beam junction on the aft and by the Manager, International Branch, ANM– Administration (NARA). For information on
forward sides at frame (FR) 35.1 and FR 35.2 116, Transport Airplane Directorate, FAA; or the availability of this material at NARA, call
on the left-hand and right-hand sides, in EASA; or Airbus’s EASA DOA. If approved 202–741–6030, or go to: http://
accordance with the Accomplishment by the DOA, the approval must include the www.archives.gov/federal-register/cfr/ibr-
DOA-authorized signature. locations.html.
Instructions of the Airbus service information
(3) Required for Compliance (RC): Except
specified in paragraphs (g)(1), (g)(2), (g)(3), Issued in Renton, Washington, on June 29,
as required by paragraph (h) of this AD: If
and (g)(4) of this AD. Repeat the inspection 2017.
any service information contains procedures
of the frame to cabin floor beam junction on
or tests that are identified as RC, those Michael Kaszycki,
the aft and forward sides at FR 35.1 and FR
procedures and tests must be done to comply Acting Manager, Transport Airplane
35.2 on the left-hand and right-hand sides
with this AD; any procedures or tests that are Directorate, Aircraft Certification Service.
thereafter at intervals not to exceed 15,300
not identified as RC are recommended. Those
flight cycles. [FR Doc. 2017–14588 Filed 7–18–17; 8:45 am]
procedures and tests that are not identified
(1) Airbus Service Bulletin A320–53–1317, BILLING CODE 4910–13–P
as RC may be deviated from using accepted
dated December 15, 2015 (FR 35.1 right-hand
methods in accordance with the operator’s
side).
maintenance or inspection program without
(2) Airbus Service Bulletin A320–53–1318, DEPARTMENT OF TRANSPORTATION
obtaining approval of an AMOC, provided
dated October 9, 2015 (FR 35.1 left-hand
the procedures and tests identified as RC can
side). Federal Aviation Administration
be done and the airplane can be put back in
(3) Airbus Service Bulletin A320–53–1319,
an airworthy condition. Any substitutions or
dated October 9, 2015 (FR 35.2 right-hand
changes to procedures or tests identified as 14 CFR Part 39
side).
RC require approval of an AMOC.
(4) Airbus Service Bulletin A320–53–1320, [Docket No. FAA–2016–9389; Directorate
dated October 9, 2015 (FR 35.2 left-hand (j) Related Information Identifier 2014–NM–153–AD; Amendment
side). (1) Refer to Mandatory Continuing 39–18953; AD 2017–14–09]
(h) Repair Airworthiness Information (MCAI) EASA AD
RIN 2120–AA64
2016–0105, dated June 6, 2016, for related
If any crack is found during any inspection
information. This MCAI may be found in the
required by paragraph (g) of this AD: Before
AD docket on the Internet at http:// Airworthiness Directives; Fokker
further flight, repair using a method www.regulations.gov by searching for and Services B.V. Airplanes
approved by the Manager, International locating Docket No. FAA–2016–9498.
Branch, ANM–116, Transport Airplane AGENCY: Federal Aviation
(2) For more information about this AD,
Directorate, FAA; or the European Aviation contact Sanjay Ralhan, Aerospace Engineer, Administration (FAA), Department of
Safety Agency (EASA); or Airbus’s EASA International Branch, ANM–116, Transport Transportation (DOT).
Design Organization Approval (DOA). Airplane Directorate, FAA, 1601 Lind ACTION: Final rule.
Although the service information specified in Avenue SW., Renton, WA 98057–3356;
paragraph (g) of this AD specifies to contact telephone: 425–227–1405; fax: 425–227– SUMMARY: We are adopting a new
Airbus for repair instructions, and specifies 1149. Information may be emailed to: 9- airworthiness directive (AD) for all
that action as ‘‘RC’’ (Required for ANM-116-AMOC-REQUESTS@faa.gov. Fokker Services B.V. Model F28 Mark
Compliance), this AD requires repair as (3) Service information identified in this
specified in this paragraph. Repair of an 0100 airplanes. This AD was prompted
AD that is not incorporated by reference is by an evaluation by the design approval
airplane as required by this paragraph does available at the addresses specified in
not constitute terminating action for the paragraphs (k)(3) and (k)(4) of this AD.
holder (DAH) indicating that certain
repetitive actions required by paragraph (g) of wing fuel tank access panels are subject
this AD, unless otherwise specified in the (k) Material Incorporated by Reference to widespread fatigue damage (WFD).
instructions provided by the Manager, (1) The Director of the Federal Register This AD requires replacement of
International Branch, ANM–116, Transport approved the incorporation by reference affected access panels and modification
Airplane Directorate, FAA; or EASA; or (IBR) of the service information listed in this of the coamings of the associated access
Airbus’s EASA DOA. paragraph under 5 U.S.C. 552(a) and 1 CFR holes. We are issuing this AD to address
part 51.
(i) Other FAA AD Provisions the unsafe condition on these products.
(2) You must use this service information
The following provisions also apply to this as applicable to do the actions required by DATES: This AD is effective August 23,
AD: this AD, unless this AD specifies otherwise. 2017.
(1) Alternative Methods of Compliance (i) Airbus Service Bulletin A320–53–1317, The Director of the Federal Register
(AMOCs): The Manager, International dated December 15, 2015. approved the incorporation by reference
Branch, ANM–116, Transport Airplane (ii) Airbus Service Bulletin A320–53–1318, of certain publications listed in this AD
Directorate, FAA, has the authority to dated October 9, 2015.
approve AMOCs for this AD, if requested
as of August 23, 2017.
(iii) Airbus Service Bulletin A320–53–
using the procedures found in 14 CFR 39.19. 1319, dated October 9, 2015. ADDRESSES: For service information
In accordance with 14 CFR 39.19, send your (iv) Airbus Service Bulletin A320–53– identified in this final rule, contact
request to your principal inspector or local 1320, dated October 9, 2015. Fokker Services B.V., Technical
Flight Standards District Office, as (3) For service information identified in Services Dept., P.O. Box 1357, 2130 EL
appropriate. If sending information directly this AD, contact Airbus, Airworthiness Hoofddorp, the Netherlands; telephone:
to the International Branch, send it to the
mstockstill on DSK30JT082PROD with RULES
Office—EIAS, 1 Rond Point Maurice +31 (0)88–6280–350; fax: +31 (0)88–
attention of the person identified in Bellonte, 31707 Blagnac Cedex, France; 6280–111; email: technicalservices@
paragraph (j)(2) of this AD. Information may telephone: +33 5 61 93 36 96; fax: +33 5 61
be emailed to: 9-ANM-116-AMOC- 93 44 51; email: account.airworth-
fokker.com; Internet: http://
REQUESTS@faa.gov. Before using any eas@airbus.com; Internet: http:// www.myfokkerfleet.com. You may view
approved AMOC, notify your appropriate www.airbus.com. this referenced service information at
principal inspector, or lacking a principal (4) You may view this service information the FAA, Transport Airplane
inspector, the manager of the local flight at the FAA, Transport Airplane Directorate, Directorate, 1601 Lind Avenue SW.,
VerDate Sep<11>2014 16:17 Jul 18, 2017 Jkt 241001 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 E:\FR\FM\19JYR1.SGM 19JYR1](https://thefederalregister.org/doc/82_FR_33139/page/3.svg)
Document Created: 2017-07-19 06:17:23
Document Modified: 2017-07-19 06:17:23
| 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 August 23, 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 33002 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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