82 FR 57340 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 232 (December 5, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 232 (December 5, 2017)
| Page Range | 57340-57343 | |
| FR Document | 2017-26037 |
[Federal Register Volume 82, Number 232 (Tuesday, December 5, 2017)] [Rules and Regulations] [Pages 57340-57343] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-26037] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0709; Product Identifier 2016-NM-200-AD; Amendment 39-19115; AD 2017-25-01] 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 series airplanes; Model A319 series airplanes; and Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes. This AD was prompted by a report indicating that the lower rib foot angle of the center wing box did not match with the bottom skin panel inner surface. This AD requires repetitive inspections for cracking of the external bottom skin in certain areas on the left and right wings, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 9, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 9, 2018. 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 Standards Branch, 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-2017- 0709. 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-2017- 0709; 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 Section, Transport Standards Branch, 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 and A319 series airplanes; and Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes. The NPRM published in the Federal Register on July 25, 2017 (82 FR 34453) (``the NPRM''). The NPRM was prompted by a report indicating that the lower rib foot angle of the center wing box did not match with the bottom skin panel inner surface. The NPRM proposed to require repetitive inspections for cracking of the external bottom skin in certain areas on the left and right wings, and corrective actions if necessary, and provided an optional terminating modification for the repetitive inspections. We are issuing this AD to detect and correct cracking of the external bottom skin in the area of the rib 2 attachment of the wings, which could result in reduced structural integrity of the wings. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016-0222, dated November 7, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A318 and A319 series airplanes; and Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes. The MCAI states: During installation in production of new wing box ribs on post- mod 39729 aeroplanes, it was discovered that the centre wing lower rib foot angle was not matching with the bottom skin panel inner surface. This condition, if not detected and corrected, could induce fatigue cracking of the skin panel at the rib foot attachment, with possible detrimental effect on wing structural integrity. This condition was initially addressed by Airbus on the production line through adaptation mod 152155, then through mod 152200. For affected aeroplanes in service, Airbus issued Service Bulletin (SB) A320-57-1205, providing instructions for repetitive detailed inspections (DET) or special detailed inspections (SDI), and SB A320-57-1207, providing modification instructions. For the reasons described above, this [EASA] AD requires repetitive inspections (DET or SDI) of the wing bottom skin lower surface for crack detection and, depending on findings, the accomplishment of applicable corrective action(s). This [EASA] AD also includes reference to an optional modification (Airbus SB A320- 57-1207), providing terminating action for the repetitive inspections required by this [EASA] AD. The corrective action for cracking is to repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; EASA; or Airbus's EASA Design Organization Approval. 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-2017- 0709. 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 Include Technical Adaptations Delta Airlines asked for another ``Contacting the Manufacturer'' subparagraph acknowledging Technical Adaptations from Airbus to be added under paragraph (j) of the proposed AD, ``Other FAA AD Provisions.'' Delta observed that the FAA provision for contacting the manufacturer in paragraph (j) of the proposed AD would provide allowances for corrective actions without alternative methods of compliance (AMOCs). Delta noted that operators often receive Technical Adaptations that include an EASA Design Organization Approval (DOA) [[Page 57341]] authorized signature for typographical, omitted instruction, and technical errors, and that they should be included in the proposed AD. We disagree with the commenter. The ``Contacting the Manufacturer'' paragraph in ADs only addresses the requirement to contact the manufacturer for corrective actions for the identified unsafe condition and does not cover deviations from other AD requirements. This paragraph states, in part, that for any requirement in an AD to obtain corrective actions from a manufacturer, the actions must be accomplished using a method approved by the FAA; or the EASA; or Airbus's EASA DOA. We do not agree to extend this allowance to other AD requirements. All deviations from the service information sections that are marked ``RC'' (Required for Compliance) require AMOC approval unless otherwise stated in 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 Airbus has issued Service Bulletin A320-57-1205, dated May 26, 2016. This service information describes procedures for inspecting the external bottom skin for cracking in the area of the rib 2 attachment between stringer 8 and stringer 11 on both wings, and repairing any cracks. Airbus has also issued Service Bulletin A320-57-1207, including Appendix 01 and Appendix 02, dated May 26, 2016. This service information describes procedures for inspecting the lower rib feet (rib 2) and the bottom skin upper surface on both wings for cracking, modifying the wings by installing shims between the lower rib foot (rib 2) and the bottom skin upper surface, and repairing any cracks. 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 10 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.................... 5 work-hours x $85 $0 $425 per inspection $4,250 per per hour = $425 per cycle. inspection cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- Estimated Costs for Optional Actions ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Modification............................... 32 work-hours x $85 per hour = $5,750 $8,470 $2,720. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. According to the manufacturer, some of the costs of the optional modification of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all available costs in our cost estimate. 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. 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. [[Page 57342]] 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): 2017-25-01 Airbus: Amendment 39-19115; Docket No. FAA-2017-0709; Product Identifier 2016-NM-200-AD. (a) Effective Date This AD is effective January 9, 2018. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers on which Airbus Modification 39729 was embodied in production, except those airplanes on which Airbus Modification 152155 or Modification 152200 was embodied in production. (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, -216, -231, -232, and - 233 airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a report indicating that the lower rib foot angle of the center wing box did not match with the bottom skin panel inner surface. Misalignment of the lower rib foot angle of the center wing box with the bottom skin panel inner surface could induce fatigue cracking of the skin panel at the rib foot attachment. We are issuing this AD to detect and correct cracking of the external bottom skin in the area of the rib 2 attachment of the wings, which could result in reduced structural integrity of the wings. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections Before exceeding the applicable compliance time specified in table 1 to paragraph (g) of this AD, or within 3 months after the effective date of this AD, whichever occurs later: Do a detailed inspection or a special detailed inspection for cracking of the external bottom skin in the area of the rib 2 attachment between stringer 8 and stringer 11 of the left and right wings, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1205, dated May 26, 2016. Do all applicable corrective actions before further flight. Repeat the inspection thereafter at the applicable intervals, based on the method used for the most recent inspection, as specified in table 2 to paragraph (g) of this AD. Table 1 to Paragraph (g) of This AD--Initial Inspection Times ------------------------------------------------------------------------ Compliance time-- whichever occurs first Airplane model and configuration since first flight of the airplane ------------------------------------------------------------------------ Model A318 series airplanes; Model A319 Before the accumulation series airplanes; and Model A320-211, -212, - of 14,500 total flight 214, -216, -231, -232, and -233 airplanes; cycles or 29,000 total pre-Airbus Modification 155374; not used as flight hours. VIP or Elite. Model A318 series airplanes; Model A319 Before the accumulation series airplanes; and Model A320-211, -212, - of 13,600 total flight 214, -216, -231, -232, and -233 airplanes; cycles or 27,300 total post-Airbus Modification 155374; not used as flight hours. VIP or Elite. Model A319 series airplanes; post-Airbus Before the accumulation Modifications 28162, 28238, and 28342; used of 7,400 total flight as VIP or CJ. cycles or 32,000 total flight hours. Model A318 series airplanes; post-Airbus Before the accumulation Modification 39195; used as VIP or Elite. of 14,500 total flight cycles or 43,500 total flight hours. ------------------------------------------------------------------------ Table 2 to Paragraph (g) of This AD--Repetitive Inspection Intervals ------------------------------------------------------------------------ Detailed Special detailed inspection-- inspection-- Airplane model and configuration whichever occurs whichever occurs first first ------------------------------------------------------------------------ Model A318 series airplanes; 4,000 flight 5,000 flight Model A319 series airplanes; cycles or 8,000 cycles or 10,000 and Model A320-211, -212, -214, flight hours. flight hours. -216, -231, -232, and -233 airplanes; not used as VIP or Elite. Model A319 series airplanes; 2,000 flight 2,500 flight post-Airbus Modifications cycles or 8,600 cycles or 11,000 28162, 28238 and 28342; used as flight hours. flight hours. VIP or CJ. Model A318 series airplanes; 4,000 flight 5,000 flight post-Airbus Modification 39195; cycles or 12,000 cycles or 15,000 used as VIP or Elite. flight hours. flight hours. ------------------------------------------------------------------------ Note 1 to paragraph (g) of this AD: Airbus Modification 155374 defines the minimum airplane configuration for operation on Commonwealth of Independent States runway profiles. (h) Terminating Action Limitation Repair of an airplane, as required by paragraph (g) of this AD, does not constitute terminating action for the repetitive inspections required by paragraph (g) of this AD unless otherwise specified in the instructions obtained using the procedures specified in paragraph (j)(2) of this AD. (i) Optional Terminating Action Modification of the wings including a detailed inspection of the lower rib feet (rib 2) and bottom skin upper surface of the wings for cracking and all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1207, including Appendix 01 and Appendix 02, dated May 26, 2016, constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD for that airplane. If, during modification of an airplane as specified in this paragraph, accomplishment of any modification instruction is not possible due to configuration difficulties, accomplish the modification using the procedures specified in paragraph (j)(1) of this AD. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this [[Page 57343]] AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Branch, send it to the attention of the person identified in paragraph (k)(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 Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (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. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016-0222, dated November 7, 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-2017-0709. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (l)(3) and (l)(4) of this AD. (l) 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 A320-57-1205, dated May 26, 2016. (ii) Airbus Service Bulletin A320-57-1207, including Appendix 01 and Appendix 02, dated May 26, 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 Standards Branch, 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 November 22, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017-26037 Filed 12-4-17; 8:45 am] BILLING CODE 4910-13-P
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(1) Applicability of the annual the availability of this material at the MCAI’’), to correct an unsafe condition
limitation. When grants are no longer FAA, call 425–227–1221. It is also for certain Airbus Model A318 and
available in a fiscal year, further available on the Internet at http:// A319 series airplanes; and Model A320–
decisions to grant such relief must be www.regulations.gov by searching for 211, –212, –214, –216, –231, –232, and
reserved until such time as a grant and locating Docket No. FAA–2017– –233 airplanes. The MCAI states:
becomes available under the annual 0709. During installation in production of new
limitation in a subsequent fiscal year. wing box ribs on post-mod 39729 aeroplanes,
Examining the AD Docket
* * * * * it was discovered that the centre wing lower
You may examine the AD docket on rib foot angle was not matching with the
Dated: November 21, 2017. the Internet at http:// bottom skin panel inner surface.
Jefferson B. Sessions III, www.regulations.gov by searching for This condition, if not detected and
Attorney General. and locating Docket No. FAA–2017– corrected, could induce fatigue cracking of
[FR Doc. 2017–26104 Filed 12–4–17; 8:45 am] 0709; or in person at the Docket the skin panel at the rib foot attachment, with
possible detrimental effect on wing structural
BILLING CODE 4410–30–P Management Facility between 9 a.m. integrity.
and 5 p.m., Monday through Friday, This condition was initially addressed by
except Federal holidays. The AD docket Airbus on the production line through
DEPARTMENT OF TRANSPORTATION contains this AD, the regulatory adaptation mod 152155, then through mod
evaluation, any comments received, and 152200. For affected aeroplanes in service,
Federal Aviation Administration other information. The street address for Airbus issued Service Bulletin (SB) A320–
the Docket Office (telephone 800–647– 57–1205, providing instructions for repetitive
14 CFR Part 39 5527) is Docket Management Facility, detailed inspections (DET) or special detailed
inspections (SDI), and SB A320–57–1207,
[Docket No. FAA–2017–0709; Product U.S. Department of Transportation, providing modification instructions.
Identifier 2016–NM–200–AD; Amendment Docket Operations, M–30, West For the reasons described above, this
39–19115; AD 2017–25–01] Building Ground Floor, Room W12–140, [EASA] AD requires repetitive inspections
1200 New Jersey Avenue SE., (DET or SDI) of the wing bottom skin lower
RIN 2120–AA64
Washington, DC 20590. surface for crack detection and, depending on
FOR FURTHER INFORMATION CONTACT: findings, the accomplishment of applicable
Airworthiness Directives; Airbus
Sanjay Ralhan, Aerospace Engineer, corrective action(s). This [EASA] AD also
Airplanes includes reference to an optional
International Section, Transport modification (Airbus SB A320–57–1207),
AGENCY: Federal Aviation Standards Branch, FAA, 1601 Lind providing terminating action for the
Administration (FAA), Department of Avenue SW., Renton, WA 98057–3356; repetitive inspections required by this
Transportation (DOT). telephone 425–227–1405; fax 425–227– [EASA] AD.
ACTION: Final rule. 1149.
The corrective action for cracking is to
SUPPLEMENTARY INFORMATION: repair using a method approved by the
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain Discussion Manager, International Section,
Airbus Model A318 series airplanes; Transport Standards Branch, FAA;
We issued a notice of proposed EASA; or Airbus’s EASA Design
Model A319 series airplanes; and Model rulemaking (NPRM) to amend 14 CFR
A320–211, –212, –214, –216, –231, Organization Approval. You may
part 39 by adding an AD that would examine the MCAI in the AD docket on
–232, and –233 airplanes. This AD was apply to certain Airbus Model A318 and
prompted by a report indicating that the the Internet at http://
A319 series airplanes; and Model A320– www.regulations.gov by searching for
lower rib foot angle of the center wing 211, –212, –214, –216, –231, –232, and
box did not match with the bottom skin and locating Docket No. FAA–2017–
–233 airplanes. The NPRM published in 0709.
panel inner surface. This AD requires the Federal Register on July 25, 2017
repetitive inspections for cracking of the (82 FR 34453) (‘‘the NPRM’’). The Comments
external bottom skin in certain areas on NPRM was prompted by a report
the left and right wings, and corrective We gave the public the opportunity to
indicating that the lower rib foot angle participate in developing this AD. The
actions if necessary. We are issuing this of the center wing box did not match
AD to address the unsafe condition on following presents the comment
with the bottom skin panel inner received on the NPRM and the FAA’s
these products. surface. The NPRM proposed to require response.
DATES: This AD is effective January 9, repetitive inspections for cracking of the
2018. external bottom skin in certain areas on Request To Include Technical
The Director of the Federal Register the left and right wings, and corrective Adaptations
approved the incorporation by reference actions if necessary, and provided an Delta Airlines asked for another
of certain publications listed in this AD optional terminating modification for ‘‘Contacting the Manufacturer’’
as of January 9, 2018. the repetitive inspections. We are subparagraph acknowledging Technical
ADDRESSES: For service information issuing this AD to detect and correct Adaptations from Airbus to be added
identified in this final rule, contact cracking of the external bottom skin in under paragraph (j) of the proposed AD,
Airbus, Airworthiness Office—EIAS, 1 the area of the rib 2 attachment of the ‘‘Other FAA AD Provisions.’’ Delta
Rond Point Maurice Bellonte, 31707 wings, which could result in reduced observed that the FAA provision for
Blagnac Cedex, France; telephone +33 5 structural integrity of the wings. contacting the manufacturer in
sradovich on DSK3GMQ082PROD with RULES
61 93 36 96; fax +33 5 61 93 44 51; email The European Aviation Safety Agency paragraph (j) of the proposed AD would
account.airworth-eas@airbus.com; (EASA), which is the Technical Agent provide allowances for corrective
Internet http://www.airbus.com. You for the Member States of the European actions without alternative methods of
may view this referenced service Union, has issued EASA AD 2016–0222, compliance (AMOCs). Delta noted that
information at the FAA, Transport dated November 7, 2016 (referred to operators often receive Technical
Standards Branch, 1601 Lind Avenue after this as the Mandatory Continuing Adaptations that include an EASA
SW., Renton, WA. For information on Airworthiness Information, or ‘‘the Design Organization Approval (DOA)
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Adoption of the Amendment (c) Applicability and correct cracking of the external bottom
This AD applies to the Airbus airplanes skin in the area of the rib 2 attachment of the
Accordingly, under the authority identified in paragraphs (c)(1), (c)(2), and wings, which could result in reduced
delegated to me by the Administrator, (c)(3) of this AD, certificated in any category, structural integrity of the wings.
the FAA amends 14 CFR part 39 as all manufacturer serial numbers on which (f) Compliance
follows: Airbus Modification 39729 was embodied in
production, except those airplanes on which Comply with this AD within the
Airbus Modification 152155 or Modification compliance times specified, unless already
PART 39—AIRWORTHINESS
152200 was embodied in production. done.
DIRECTIVES
(1) Airbus Model A318–111, –112, –121, (g) Repetitive Inspections
and –122 airplanes.
■ 1. The authority citation for part 39 (2) Airbus Model A319–111, –112, –113, Before exceeding the applicable
continues to read as follows: –114, –115, –131, –132, and –133 airplanes. compliance time specified in table 1 to
(3) Airbus Model A320–211, –212, –214, paragraph (g) of this AD, or within 3 months
Authority: 49 U.S.C. 106(g), 40113, 44701. after the effective date of this AD, whichever
–216, –231, –232, and –233 airplanes.
§ 39.13 [Amended] occurs later: Do a detailed inspection or a
(d) Subject special detailed inspection for cracking of the
■ 2. The FAA amends § 39.13 by adding Air Transport Association (ATA) of external bottom skin in the area of the rib 2
the following new airworthiness America Code 57, Wings. attachment between stringer 8 and stringer 11
of the left and right wings, and do all
directive (AD): (e) Reason applicable corrective actions, in accordance
2017–25–01 Airbus: Amendment 39–19115; This AD was prompted by a report with the Accomplishment Instructions of
Docket No. FAA–2017–0709; Product indicating that the lower rib foot angle of the Airbus Service Bulletin A320–57–1205,
Identifier 2016–NM–200–AD. center wing box did not match with the dated May 26, 2016. Do all applicable
bottom skin panel inner surface. corrective actions before further flight.
(a) Effective Date Misalignment of the lower rib foot angle of Repeat the inspection thereafter at the
This AD is effective January 9, 2018. the center wing box with the bottom skin applicable intervals, based on the method
panel inner surface could induce fatigue used for the most recent inspection, as
(b) Affected ADs cracking of the skin panel at the rib foot specified in table 2 to paragraph (g) of this
None. attachment. We are issuing this AD to detect AD.
TABLE 1 TO PARAGRAPH (g) OF THIS AD—INITIAL INSPECTION TIMES
Compliance time—whichever occurs first
Airplane model and configuration since first flight of the airplane
Model A318 series airplanes; Model A319 series airplanes; and Model A320–211, –212, –214, Before the accumulation of 14,500 total flight
–216, –231, –232, and –233 airplanes; pre-Airbus Modification 155374; not used as VIP or cycles or 29,000 total flight hours.
Elite.
Model A318 series airplanes; Model A319 series airplanes; and Model A320–211, –212, –214, Before the accumulation of 13,600 total flight
–216, –231, –232, and –233 airplanes; post-Airbus Modification 155374; not used as VIP or cycles or 27,300 total flight hours.
Elite.
Model A319 series airplanes; post-Airbus Modifications 28162, 28238, and 28342; used as VIP Before the accumulation of 7,400 total flight cy-
or CJ. cles or 32,000 total flight hours.
Model A318 series airplanes; post-Airbus Modification 39195; used as VIP or Elite .................... Before the accumulation of 14,500 total flight
cycles or 43,500 total flight hours.
TABLE 2 TO PARAGRAPH (g) OF THIS AD—REPETITIVE INSPECTION INTERVALS
Detailed inspection— Special detailed inspection—
Airplane model and configuration whichever occurs first whichever occurs first
Model A318 series airplanes; Model A319 series airplanes; and Model 4,000 flight cycles or 8,000 flight 5,000 flight cycles or 10,000 flight
A320–211, –212, –214, –216, –231, –232, and –233 airplanes; not hours. hours.
used as VIP or Elite.
Model A319 series airplanes; post-Airbus Modifications 28162, 28238 2,000 flight cycles or 8,600 flight 2,500 flight cycles or 11,000 flight
and 28342; used as VIP or CJ. hours. hours.
Model A318 series airplanes; post-Airbus Modification 39195; used as 4,000 flight cycles or 12,000 flight 5,000 flight cycles or 15,000 flight
VIP or Elite. hours. hours.
Note 1 to paragraph (g) of this AD: Airbus (i) Optional Terminating Action specified in this paragraph, accomplishment
Modification 155374 defines the minimum Modification of the wings including a of any modification instruction is not
airplane configuration for operation on possible due to configuration difficulties,
detailed inspection of the lower rib feet (rib
Commonwealth of Independent States accomplish the modification using the
2) and bottom skin upper surface of the
runway profiles. procedures specified in paragraph (j)(1) of
wings for cracking and all applicable this AD.
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(h) Terminating Action Limitation corrective actions, in accordance with the
Repair of an airplane, as required by Accomplishment Instructions of Airbus (j) Other FAA AD Provisions
paragraph (g) of this AD, does not constitute Service Bulletin A320–57–1207, including The following provisions also apply to this
terminating action for the repetitive Appendix 01 and Appendix 02, dated May AD:
inspections required by paragraph (g) of this 26, 2016, constitutes terminating action for (1) Alternative Methods of Compliance
AD unless otherwise specified in the the repetitive inspections required by (AMOCs): The Manager, International
instructions obtained using the procedures paragraph (g) of this AD for that airplane. If, Section, Transport Standards Branch, FAA,
specified in paragraph (j)(2) of this AD. during modification of an airplane as has the authority to approve AMOCs for this
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![Federal Register / Vol. 82, No. 232 / Tuesday, December 5, 2017 / Rules and Regulations 57343
AD, if requested using the procedures found (3) For service information identified in Attention: Contractual & Data Services
in 14 CFR 39.19. In accordance with 14 CFR this AD, contact Airbus, Airworthiness (C&DS), 2600 Westminster Blvd., MC
39.19, send your request to your principal Office—EIAS, 1 Rond Point Maurice 110–SK57, Seal Beach, CA 90740–5600;
inspector or local Flight Standards District Bellonte, 31707 Blagnac Cedex, France;
telephone 562–797–1717; Internet
Office, as appropriate. If sending information telephone +33 5 61 93 36 96; fax +33 5 61
directly to the manager of the International 93 44 51; email account.airworth-eas@ https://www.myboeingfleet.com. You
Branch, send it to the attention of the person airbus.com; Internet http://www.airbus.com. may view this service information at the
identified in paragraph (k)(2) of this AD. (4) You may view this service information FAA, Transport Standards Branch, 1601
Information may be emailed to: 9-ANM-116- at the FAA, Transport Standards Branch, Lind Avenue SW., Renton, WA. For
AMOC-REQUESTS@faa.gov. Before using 1601 Lind Avenue SW., Renton, WA. For information on the availability of this
any approved AMOC, notify your appropriate information on the availability of this material at the FAA, call 425–227–1221.
principal inspector, or lacking a principal material at the FAA, call 425–227–1221. It is also available on the Internet at
inspector, the manager of the local flight (5) You may view this service information http://www.regulations.gov by searching
standards district office/certificate holding that is incorporated by reference at the
National Archives and Records
for and locating Docket No. FAA–2017–
district office.
(2) Contacting the Manufacturer: For any Administration (NARA). For information on 0340.
requirement in this AD to obtain corrective the availability of this material at NARA, call Examining the AD Docket
actions from a manufacturer, the action must 202–741–6030, or go to: http://
be accomplished using a method approved www.archives.gov/federal-register/cfr/ibr- You may examine the AD docket on
by the Manager, International Section, locations.html. the Internet at http://
Transport Standards Branch, FAA; or the Issued in Renton, Washington, on www.regulations.gov by searching for
European Aviation Safety Agency (EASA); or November 22, 2017. and locating Docket No. FAA–2017–
Airbus’s EASA Design Organization
Jeffrey E. Duven, 0340; or in person at the Docket
Approval (DOA). If approved by the DOA,
the approval must include the DOA- Director, System Oversight Division, Aircraft Management Facility between 9 a.m.
authorized signature. Certification Service. and 5 p.m., Monday through Friday,
(3) Required for Compliance (RC): If any [FR Doc. 2017–26037 Filed 12–4–17; 8:45 am] except Federal holidays. The AD docket
service information contains procedures or BILLING CODE 4910–13–P contains this final rule, the regulatory
tests that are identified as RC, those evaluation, any comments received, and
procedures and tests must be done to comply other information. The address for the
with this AD; any procedures or tests that are DEPARTMENT OF TRANSPORTATION Docket Office (phone: 800–647–5527) is
not identified as RC are recommended. Those Docket Management Facility, U.S.
procedures and tests that are not identified Federal Aviation Administration Department of Transportation, Docket
as RC may be deviated from using accepted
methods in accordance with the operator’s Operations, M–30, West Building
maintenance or inspection program without 14 CFR Part 39 Ground Floor, Room W12–140, 1200
obtaining approval of an AMOC, provided [Docket No. FAA–2017–0340; Product New Jersey Avenue SE., Washington,
the procedures and tests identified as RC can Identifier 2017–NM–002–AD; Amendment DC 20590.
be done and the airplane can be put back in 39–19114; AD 2017–24–10] FOR FURTHER INFORMATION CONTACT:
an airworthy condition. Any substitutions or
changes to procedures or tests identified as RIN 2120–AA64 Muoi Vuong, Aerospace Engineer,
RC require approval of an AMOC. Airframe Section, FAA, Los Angeles
Airworthiness Directives; The Boeing ACO Branch, 3960 Paramount
(k) Related Information Company Airplanes Boulevard, Lakewood, CA 90712–4137;
(1) Refer to Mandatory Continuing phone: 562–627–5205; fax: 562–627–
Airworthiness Information (MCAI) EASA AD AGENCY: Federal Aviation
5210; email: Muoi.Vuong@faa.gov.
2016–0222, dated November 7, 2016, for Administration (FAA), DOT.
related information. This MCAI may be ACTION: Final rule. SUPPLEMENTARY INFORMATION:
found in the AD docket on the Internet at
http://www.regulations.gov by searching for SUMMARY: We are adopting a new Discussion
and locating Docket No. FAA–2017–0709. airworthiness directive (AD) for certain We issued a notice of proposed
(2) For more information about this AD, The Boeing Company Model 757–200,
contact Sanjay Ralhan, Aerospace Engineer,
rulemaking (NPRM) to amend 14 CFR
–200PF, and –300 series airplanes. This part 39 by adding an AD that would
International Section, Transport Standards AD was prompted by reports of cracking
Branch, FAA, 1601 Lind Avenue SW., apply to certain The Boeing Company
found at a certain fuselage frame inner Model 757–200, –200PF, and –300
Renton, WA 98057–3356; telephone 425–
227–1405; fax 425–227–1149. chord. This AD requires repetitive series airplanes. The NPRM published
(3) Service information identified in this inspections for any cracking of a certain in the Federal Register on May 19, 2017
AD that is not incorporated by reference is fuselage frame inner chord; (82 FR 22915). The NPRM was
available at the addresses specified in identification of the material of a certain prompted by reports of cracking found
paragraphs (l)(3) and (l)(4) of this AD. fuselage frame inner chord for certain at a certain fuselage frame inner chord.
(l) Material Incorporated by Reference airplanes; and applicable corrective The NPRM proposed to require
actions. We are issuing this AD to repetitive inspections for any cracking
(1) The Director of the Federal Register
address the unsafe condition on these of a certain fuselage frame inner chord,
approved the incorporation by reference
(IBR) of the service information listed in this products. identification of the material of a certain
paragraph under 5 U.S.C. 552(a) and 1 CFR DATES: This AD is effective January 9, fuselage frame inner chord for certain
part 51. 2018. airplanes, and applicable corrective
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(2) You must use this service information The Director of the Federal Register actions. We are issuing this AD to detect
as applicable to do the actions required by approved the incorporation by reference and correct such cracks, which could
this AD, unless this AD specifies otherwise. of certain publications listed in this AD
(i) Airbus Service Bulletin A320–57–1205,
result in the cargo door opening during
dated May 26, 2016.
as of January 9, 2018. flight, and result in rapid
(ii) Airbus Service Bulletin A320–57–1207, ADDRESSES: For service information decompression of the airplane and the
including Appendix 01 and Appendix 02, identified in this final rule, contact inability to sustain loads required for
dated May 26, 2016. Boeing Commercial Airplanes, continued safe flight and landing.
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Document Created: 2017-12-04 23:44:47
Document Modified: 2017-12-04 23:44:47
| 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 January 9, 2018. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227- 1149. | |
| FR Citation | 82 FR 57340 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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