82 FR 34453 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 141 (July 25, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 141 (July 25, 2017)
| Page Range | 34453-34456 | |
| FR Document | 2017-15481 |
[Federal Register Volume 82, Number 141 (Tuesday, July 25, 2017)] [Proposed Rules] [Pages 34453-34456] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-15481] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0709; Directorate Identifier 2016-NM-200-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt 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 proposed 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 proposed AD would require repetitive inspections for cracking of the external bottom skin in certain areas on the left and right wings, and corrective actions if necessary. This proposed AD also provides an optional terminating modification for the repetitive inspections. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by September 8, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR [[Page 34454]] 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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. 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0709; Directorate Identifier 2016-NM-200-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion 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 Branch, ANM-116, Transport Airplane Directorate, 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. 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. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Costs of Compliance We estimate that this proposed AD affects 10 airplanes of U.S. registry. We estimate the following costs to comply with this proposed 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 inspection per hour = $425 per cycle. cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- [[Page 34455]] 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 proposed AD. According to the manufacturer, some of the costs of the optional modification of this proposed 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. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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): Airbus: Docket No. FAA-2017-0709; Directorate Identifier 2016-NM- 200-AD. (a) Comments Due Date We must receive comments by September 8, 2017. (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 wing. (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 Airplane model and configuration occurs first since first flight of the airplane ------------------------------------------------------------------------ Model A318 series airplanes; Model A319 Before the accumulation of series airplanes; and Model A320-211, - 14,500 total flight cycles or 212, -214, -216, -231, -232, and -233 29,000 total flight hours. airplanes; pre-Airbus Modification 155374; not used as VIP or Elite. Model A318 series airplanes; Model A319 Before the accumulation of series airplanes; and Model A320-211, - 13,600 total flight cycles or 212, -214, -216, -231, -232, and -233 27,300 total flight hours. airplanes; post-Airbus Modification 155374; not used as VIP or Elite. [[Page 34456]] Model A319 series airplanes; post- Before the accumulation of Airbus Modifications 28162, 28238, and 7,400 total flight cycles or 28342; used as VIP or CJ. 32,000 total flight hours. Model A318 series airplanes; post- Before the accumulation of Airbus Modification 39195; used as VIP 14,500 total flight cycles or or Elite. 43,500 total flight hours. ------------------------------------------------------------------------ Table 2 to Paragraph (g) of This AD--Repetitive Inspection Intervals ---------------------------------------------------------------------------------------------------------------- Special detailed inspection-- Airplane model and configuration Detailed inspection--whichever whichever occurs first occurs first ---------------------------------------------------------------------------------------------------------------- Model A318 series airplanes; Model A319 4,000 flight cycles or 8,000 5,000 flight cycles or 10,000 series airplanes; and Model A320-211, - flight hours. flight hours. 212, -214, -216, -231, -232, and -233 airplanes; not used as VIP or Elite. Model A319 series airplanes; post-Airbus 2,000 flight cycles or 8,600 2,500 flight cycles or 11,000 Modifications 28162, 28238, and 28342; flight hours. flight hours. used as VIP or CJ. Model A318 series airplanes; post-Airbus 4,000 flight cycles or 12,000 5,000 flight cycles or 15,000 Modification 39195; 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 Branch, ANM-116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Branch, send it to the attention of the person identified in paragraph (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 Branch, ANM-116, Transport Airplane Directorate, 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 Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-1405; fax 425-227-1149. (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. 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. Issued in Renton, Washington, on July 14, 2017. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-15481 Filed 7-24-17; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 82, No. 141 / Tuesday, July 25, 2017 / Proposed Rules 34453
with the requirements of paragraphs (l)(1) inspection requirements of ALI task 534129 http://www.regulations.gov by searching for
and (l)(2) of this AD. or task 534130, as applicable, for those holes and locating Docket No. FAA–2017–0707.
(1) For all fastener holes where no damage for that airplane. Subsequent repetitive (2) For more information about this AD,
or cracks were detected (i.e., those not inspections are required by paragraph (j) of contact Sanjay Ralhan, Aerospace Engineer,
repaired), accomplish the actions required by this AD. International Branch, ANM–116, Transport
paragraph (g) of this AD, unless the Airplane Directorate, FAA, 1601 Lind
(p) Credit for Previous Actions
terminating action specified in paragraph (m) Avenue SW., Renton, WA 98057–3356;
of this AD has been done. (1) This paragraph provides credit for telephone 425–227–1405; fax 425–227–1149.
(2) For all repaired fastener holes: Within actions required by paragraphs (g) and (j) of (3) For service information identified in
30 days after the effective date of this AD, or this AD, if those actions were performed this AD, contact Airbus, Airworthiness
within a compliance time approved by the before the effective date of this AD using Office– EIAS, 1 Rond Point Maurice Bellonte,
Manager, International Branch, ANM–116, Airbus Service Bulletin A320–53–1288, 31707 Blagnac Cedex, France; telephone +33
FAA, Transport Airplane Directorate; or the including Appendixes 01 and 02, dated 5 61 93 36 96; fax +33 5 61 93 44 51; email
EASA; or Airbus’s EASA DOA, whichever October 10, 2014. account.airworth-eas@airbus.com; Internet
occurs later, contact the Manager, (2) This paragraph provides credit for http://www.airbus.com. You may view this
International Branch, ANM–116, FAA, actions required by paragraphs (i) and (m) of service information at the FAA, Transport
Transport Airplane Directorate; or the EASA; this AD, if those actions were performed Airplane Directorate, 1601 Lind Avenue SW.,
or Airbus’s EASA DOA; for inspection before the effective date of this AD using Renton, WA. For information on the
instructions and applicable corrective Airbus Service Bulletin A320–53–1290, availability of this material at the FAA, call
actions, and do the inspections and dated October 10, 2014. 425–227–1221.
applicable corrective actions accordingly.
(q) Other FAA AD Provisions Issued in Renton, Washington, on July 13,
(m) Terminating Action for Certain The following provisions also apply to this 2017.
Airplanes AD: Dionne Palermo,
For airplanes that have been inspected, as (1) Alternative Methods of Compliance Acting Manager, Transport Airplane
specified in ALI task 534129 or task 534130, (AMOCs): The Manager, International Directorate, Aircraft Certification Service.
and repaired before the effective date of this Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to [FR Doc. 2017–15485 Filed 7–24–17; 8:45 am]
AD, as specified in the applicable structural
repair manual, or as specified in an Airbus approve AMOCs for this AD, if requested BILLING CODE 4910–13–P
RDAS: Modification of the four fastener holes using the procedures found in 14 CFR 39.19.
at door stop locations where no damage or In accordance with 14 CFR 39.19, send your
crack was detected (i.e., door stop locations request to your principal inspector or local DEPARTMENT OF TRANSPORTATION
not repaired) by cold working holes before Flight Standards District Office, as
further flight after no cracks were detected, appropriate. If sending information directly Federal Aviation Administration
in accordance with the Accomplishment to the manager of the International Branch,
Instructions of Airbus Service Bulletin A320– send it to the attention of the person 14 CFR Part 39
53–1290, Revision 01, dated October 3, 2016, identified in paragraph (r)(2) of this AD.
constitutes terminating action for the Information may be emailed to: 9-ANM-116- [Docket No. FAA–2017–0709; Directorate
repetitive inspections of those four fastener AMOC-REQUESTS@faa.gov. Before using Identifier 2016–NM–200–AD]
holes at those door stop locations as required any approved AMOC, notify your appropriate
principal inspector, or lacking a principal RIN 2120–AA64
by paragraph (g) or (l)(1) of this AD for that
airplane. inspector, the manager of the local flight
standards district office/certificate holding Airworthiness Directives; Airbus
(n) Actions for Airplanes With Certain district office. Airplanes
Repairs (2) Contacting the Manufacturer: For any
AGENCY: Federal Aviation
For an airplane that has been repaired requirement in this AD to obtain corrective
before the effective date of this AD in the actions from a manufacturer, the action must Administration (FAA), DOT.
areas described in this AD using an Airbus be accomplished using a method approved ACTION: Notice of proposed rulemaking
RDAS unrelated to ALI task 534129 or task by the Manager, International Branch, ANM– (NPRM).
534130: Before exceeding the compliance 116, Transport Airplane Directorate, FAA; or
times specified in paragraph (g) of this AD, EASA; or Airbus’s EASA DOA. If approved SUMMARY: We propose to adopt a new
contact the Manager, International Branch, by the DOA, the approval must include the airworthiness directive (AD) for certain
ANM–116, FAA, Transport Airplane DOA-authorized signature. Airbus Model A318 series airplanes;
Directorate; or the EASA; or Airbus’s EASA (3) Required for Compliance (RC): If any Model A319 series airplanes; and Model
DOA; for corrective action instructions and service information contains procedures or A320–211, –212, –214, –216, –231,
accomplish those instructions accordingly. tests that are identified as RC, those
–232, and –233 airplanes. This proposed
Accomplishment of corrective action(s) on an procedures and tests must be done to comply
airplane, as required by this paragraph, does with this AD; any procedures or tests that are AD was prompted by a report indicating
not constitute terminating action for the not identified as RC are recommended. Those that the lower rib foot angle of the
repetitive inspections as required by procedures and tests that are not identified center wing box did not match with the
paragraph (g) or (j) of this AD for that as RC may be deviated from using accepted bottom skin panel inner surface. This
airplane, as applicable, unless specified methods in accordance with the operator’s proposed AD would require repetitive
otherwise in the instructions. maintenance or inspection program without inspections for cracking of the external
obtaining approval of an AMOC, provided bottom skin in certain areas on the left
(o) Terminating Action for ALI Tasks the procedures and tests identified as RC can
(1) Accomplishment of inspections on an
and right wings, and corrective actions
be done and the airplane can be put back in
airplane, as required by paragraph (g), (j), or if necessary. This proposed AD also
asabaliauskas on DSKBBY8HB2PROD with PROPOSALS
an airworthy condition. Any substitutions or
(l) of this AD, as applicable, constitutes changes to procedures or tests identified as provides an optional terminating
terminating action for the inspection RC require approval of an AMOC. modification for the repetitive
requirements of ALI task 534129 or task inspections. We are proposing this AD
534130, as applicable, for that airplane. (r) Related Information
to address the unsafe condition on these
(2) Modification of the four fastener holes (1) Refer to Mandatory Continuing products.
at a door stop location of an airplane as Airworthiness Information (MCAI) EASA
DATES: We must receive comments on
specified in paragraph (i) or (m) of this AD, Airworthiness Directive 2016–0238, dated
as applicable, and subsequent initial December 2, 2016, corrected January 4, 2017, this proposed AD by September 8, 2017.
inspection required by paragraph (j) of this for related information. This MCAI may be ADDRESSES: You may send comments,
AD, constitutes terminating action for the found in the AD docket on the Internet at using the procedures found in 14 CFR
VerDate Sep<11>2014 17:17 Jul 24, 2017 Jkt 241001 PO 00000 Frm 00027 Fmt 4702 Sfmt 4702 E:\FR\FM\25JYP1.SGM 25JYP1](https://thefederalregister.org/doc/82_FR_34594/page/1.svg)
![34454 Federal Register / Vol. 82, No. 141 / Tuesday, July 25, 2017 / Proposed Rules
11.43 and 11.45, by any of the following section. Include ‘‘Docket No. FAA– Manager, International Branch, ANM–
methods: 2017–0709; Directorate Identifier 2016– 116, Transport Airplane Directorate,
• Federal eRulemaking Portal: Go to NM–200–AD’’ at the beginning of your FAA; EASA; or Airbus’s EASA Design
http://www.regulations.gov. Follow the comments. We specifically invite Organization Approval. You may
instructions for submitting comments. comments on the overall regulatory, examine the MCAI in the AD docket on
• Fax: 202–493–2251. economic, environmental, and energy the Internet at http://
• Mail: U.S. Department of aspects of this proposed AD. We will www.regulations.gov by searching for
Transportation, Docket Operations, M– consider all comments received by the and locating Docket No. FAA–2017–
30, West Building Ground Floor, Room closing date and may amend this 0709.
W12–140, 1200 New Jersey Avenue SE., proposed AD based on those comments.
Washington, DC 20590. We will post all comments we Related Service Information Under 1
• Hand Delivery: Deliver to Mail receive, without change, to http:// CFR Part 51
address above between 9 a.m. and 5 www.regulations.gov, including any
p.m., Monday through Friday, except Airbus has issued Service Bulletin
personal information you provide. We A320–57–1205, dated May 26, 2016.
Federal holidays. will also post a report summarizing each
For service information identified in This service information describes
substantive verbal contact we receive procedures for inspecting the external
this NPRM, contact Airbus, about this proposed AD.
Airworthiness Office—EIAS, 1 Rond bottom skin for cracking in the area of
Point Maurice Bellonte, 31707 Blagnac Discussion the rib 2 attachment between stringer 8
Cedex, France; telephone +33 5 61 93 36 and stringer 11 on both wings, and
The European Aviation Safety Agency
96; fax +33 5 61 93 44 51; email repairing any cracks.
(EASA), which is the Technical Agent
account.airworth-eas@airbus.com; for the Member States of the European Airbus has also issued Service
Internet http://www.airbus.com. You Union, has issued EASA AD 2016–0222, Bulletin A320–57–1207, including
may view this referenced service dated November 7, 2016 (referred to Appendix 01 and Appendix 02, dated
information at the FAA, Transport after this as the Mandatory Continuing May 26, 2016. This service information
Airplane Directorate, 1601 Lind Avenue Airworthiness Information, or ‘‘the describes procedures for inspecting the
SW., Renton, WA. For information on MCAI’’), to correct an unsafe condition lower rib feet (rib 2) and the bottom skin
the availability of this material at the for certain Airbus Model A318 and upper surface on both wings for
FAA, call 425–227–1221. A319 series airplanes; and Model A320– cracking, modifying the wings by
Examining the AD Docket 211, –212, –214, –216, –231, –232, and installing shims between the lower rib
–233 airplanes. The MCAI states: foot (rib 2) and the bottom skin upper
You may examine the AD docket on surface, and repairing any cracks.
the Internet at http:// During installation in production of new
www.regulations.gov by searching for wing box ribs on post-mod 39729 aeroplanes, This service information is reasonably
and locating Docket No. FAA–2017–
it was discovered that the centre wing lower available because the interested parties
rib foot angle was not matching with the have access to it through their normal
0709; or in person at the Docket bottom skin panel inner surface.
Management Facility between 9 a.m. course of business or by the means
This condition, if not detected and identified in the ADDRESSES section.
and 5 p.m., Monday through Friday, corrected, could induce fatigue cracking of
except Federal holidays. The AD docket the skin panel at the rib foot attachment, with FAA’s Determination and Requirements
contains this proposed AD, the possible detrimental effect on wing structural of This Proposed AD
regulatory evaluation, any comments integrity.
received, and other information. The This condition was initially addressed by This product has been approved by
Airbus on the production line through the aviation authority of another
street address for the Docket Operations adaptation mod 152155, then through mod
office (telephone 800–647–5527) is in country, and is approved for operation
152200. For affected aeroplanes in service,
the ADDRESSES section. Comments will Airbus issued Service Bulletin (SB) A320– in the United States. Pursuant to our
be available in the AD docket shortly 57–1205, providing instructions for repetitive bilateral agreement with the State of
after receipt. detailed inspections (DET) or special detailed Design Authority, we have been notified
FOR FURTHER INFORMATION CONTACT: inspections (SDI), and SB A320–57–1207, of the unsafe condition described in the
Sanjay Ralhan, Aerospace Engineer, providing modification instructions. MCAI and service information
For the reasons described above, this referenced above. We are proposing this
International Branch, ANM–116,
[EASA] AD requires repetitive inspections AD because we evaluated all pertinent
Transport Airplane Directorate, FAA, (DET or SDI) of the wing bottom skin lower
1601 Lind Avenue SW., Renton, WA information and determined an unsafe
surface for crack detection and, depending on
98057–3356; telephone 425–227–1405; condition exists and is likely to exist or
findings, the accomplishment of applicable
fax 425–227–1149. corrective action(s). This [EASA] AD also develop on other products of these same
SUPPLEMENTARY INFORMATION: includes reference to an optional type designs.
modification (Airbus SB A320–57–1207), Costs of Compliance
Comments Invited providing terminating action for the
We invite you to send any written repetitive inspections required by this We estimate that this proposed AD
relevant data, views, or arguments about [EASA] AD. affects 10 airplanes of U.S. registry. We
this proposal. Send your comments to The corrective action for cracking is to estimate the following costs to comply
asabaliauskas on DSKBBY8HB2PROD with PROPOSALS
an address listed under the ADDRESSES repair using a method approved by the with this proposed AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspection .......... 5 work-hours × $85 per hour = $425 per in- $0 $425 per inspection cycle ..... $4,250 per inspection cycle.
spection cycle.
VerDate Sep<11>2014 17:17 Jul 24, 2017 Jkt 241001 PO 00000 Frm 00028 Fmt 4702 Sfmt 4702 E:\FR\FM\25JYP1.SGM 25JYP1](https://thefederalregister.org/doc/82_FR_34594/page/2.svg)
![Federal Register / Vol. 82, No. 141 / Tuesday, July 25, 2017 / Proposed Rules 34455
ESTIMATED COSTS FOR OPTIONAL ACTIONS
Cost per
Action Labor cost Parts cost product
Modification ................................................. 32 work-hours × $85 per hour = $2,720 ....................................... $5,750 $8,470
We have received no definitive data For the reasons discussed above, I Airbus Modification 39729 was embodied in
that would enable us to provide cost certify this proposed regulation: production, except those airplanes on which
estimates for the on-condition actions 1. Is not a ‘‘significant regulatory Airbus Modification 152155 or Modification
specified in this proposed AD. action’’ under Executive Order 12866; 152200 was embodied in production.
According to the manufacturer, some 2. Is not a ‘‘significant rule’’ under the (1) Airbus Model A318–111, –112, –121,
DOT Regulatory Policies and Procedures and –122 airplanes.
of the costs of the optional modification
(2) Airbus Model A319–111, –112, –113,
of this proposed AD may be covered (44 FR 11034, February 26, 1979);
–114, –115, –131, –132, and –133 airplanes.
under warranty, thereby reducing the 3. Will not affect intrastate aviation in (3) Airbus Model A320–211, –212, –214,
cost impact on affected individuals. We Alaska; and –216, –231, –232, and –233 airplanes.
do not control warranty coverage for 4. Will not have a significant
economic impact, positive or negative, (d) Subject
affected individuals. As a result, we
have included all available costs in our on a substantial number of small entities Air Transport Association (ATA) of
cost estimate. under the criteria of the Regulatory America Code 57, wings.
Flexibility Act. (e) Reason
Authority for This Rulemaking
List of Subjects in 14 CFR Part 39 This AD was prompted by a report
Title 49 of the United States Code indicating that the lower rib foot angle of the
specifies the FAA’s authority to issue Air transportation, Aircraft, Aviation
center wing box did not match with the
rules on aviation safety. Subtitle I, safety, Incorporation by reference, bottom skin panel inner surface.
section 106, describes the authority of Safety. Misalignment of the lower rib foot angle of
the FAA Administrator. ‘‘Subtitle VII: The Proposed Amendment the center wing box with the bottom skin
Aviation Programs,’’ describes in more panel inner surface could induce fatigue
detail the scope of the Agency’s Accordingly, under the authority cracking of the skin panel at the rib foot
authority. delegated to me by the Administrator, attachment. We are issuing this AD to detect
We are issuing this rulemaking under the FAA proposes to amend 14 CFR part and correct cracking of the external bottom
the authority described in ‘‘Subtitle VII, 39 as follows: skin in the area of the rib 2 attachment of the
wings, which could result in reduced
Part A, Subpart III, Section 44701:
PART 39—AIRWORTHINESS structural integrity of the wing.
General requirements.’’ Under that
DIRECTIVES (f) Compliance
section, Congress charges the FAA with
promoting safe flight of civil aircraft in ■ 1. The authority citation for part 39 Comply with this AD within the
air commerce by prescribing regulations continues to read as follows: compliance times specified, unless already
for practices, methods, and procedures done.
Authority: 49 U.S.C. 106(g), 40113, 44701.
the Administrator finds necessary for (g) Repetitive Inspections
safety in air commerce. This regulation § 39.13 [Amended] Before exceeding the applicable
is within the scope of that authority ■ 2. The FAA amends § 39.13 by adding compliance time specified in table 1 to
because it addresses an unsafe condition the following new airworthiness paragraph (g) of this AD, or within 3 months
that is likely to exist or develop on directive (AD): after the effective date of this AD, whichever
products identified in this rulemaking occurs later: Do a detailed inspection or a
Airbus: Docket No. FAA–2017–0709;
action. special detailed inspection for cracking of the
Directorate Identifier 2016–NM–200–AD.
external bottom skin in the area of the rib 2
Regulatory Findings (a) Comments Due Date attachment between stringer 8 and stringer 11
We determined that this proposed AD We must receive comments by September of the left and right wings, and do all
would not have federalism implications 8, 2017. applicable corrective actions, in accordance
under Executive Order 13132. This with the Accomplishment Instructions of
(b) Affected ADs Airbus Service Bulletin A320–57–1205,
proposed AD would not have a
None. dated May 26, 2016. Do all applicable
substantial direct effect on the States, on corrective actions before further flight.
the relationship between the national (c) Applicability Repeat the inspection thereafter at the
Government and the States, or on the This AD applies to the Airbus airplanes applicable intervals, based on the method
distribution of power and identified in paragraphs (c)(1), (c)(2), and used for the most recent inspection, as
responsibilities among the various (c)(3) of this AD, certificated in any category, specified in table 2 to paragraph (g) of this
levels of government. all manufacturer serial numbers on which AD.
TABLE 1 TO PARAGRAPH (g) OF THIS AD—INITIAL INSPECTION TIMES
asabaliauskas on DSKBBY8HB2PROD with PROPOSALS
Airplane model and configuration Compliance time—whichever occurs first since first flight of the airplane
Model A318 series airplanes; Model A319 series airplanes; and Model Before the accumulation of 14,500 total flight cycles or 29,000 total
A320–211, –212, –214, –216, –231, –232, and –233 airplanes; pre- flight hours.
Airbus Modification 155374; not used as VIP or Elite.
Model A318 series airplanes; Model A319 series airplanes; and Model Before the accumulation of 13,600 total flight cycles or 27,300 total
A320–211, –212, –214, –216, –231, –232, and –233 airplanes; post- flight hours.
Airbus Modification 155374; not used as VIP or Elite.
VerDate Sep<11>2014 17:17 Jul 24, 2017 Jkt 241001 PO 00000 Frm 00029 Fmt 4702 Sfmt 4702 E:\FR\FM\25JYP1.SGM 25JYP1](https://thefederalregister.org/doc/82_FR_34594/page/3.svg)
![34456 Federal Register / Vol. 82, No. 141 / Tuesday, July 25, 2017 / Proposed Rules
TABLE 1 TO PARAGRAPH (g) OF THIS AD—INITIAL INSPECTION TIMES—Continued
Airplane model and configuration Compliance time—whichever occurs first since first flight of the airplane
Model A319 series airplanes; post-Airbus Modifications 28162, 28238, Before the accumulation of 7,400 total flight cycles or 32,000 total flight
and 28342; used as VIP or CJ. hours.
Model A318 series airplanes; post-Airbus Modification 39195; used as Before the accumulation of 14,500 total flight cycles or 43,500 total
VIP or Elite. flight hours.
TABLE 2 TO PARAGRAPH (g) OF THIS AD—REPETITIVE INSPECTION INTERVALS
Detailed inspection—whichever occurs Special detailed inspection—whichever
Airplane model and configuration first occurs first
Model A318 series airplanes; Model A319 series air- 4,000 flight cycles or 8,000 flight hours ... 5,000 flight cycles or 10,000 flight hours.
planes; and Model A320–211, –212, –214, –216,
–231, –232, and –233 airplanes; not used as VIP or
Elite.
Model A319 series airplanes; post-Airbus Modifications 2,000 flight cycles or 8,600 flight hours ... 2,500 flight cycles or 11,000 flight hours.
28162, 28238, and 28342; used as VIP or CJ.
Model A318 series airplanes; post-Airbus Modification 4,000 flight cycles or 12,000 flight hours 5,000 flight cycles or 15,000 flight hours.
39195; used as VIP or Elite.
Note 1 to paragraph (g) of this AD: Airbus AMOC-REQUESTS@faa.gov. Before using Bellonte, 31707 Blagnac Cedex, France;
Modification 155374 defines the minimum any approved AMOC, notify your appropriate telephone +33 5 61 93 36 96; fax +33 5 61
airplane configuration for operation on principal inspector, or lacking a principal 93 44 51; email account.airworth-eas@
Commonwealth of Independent States inspector, the manager of the local flight airbus.com; Internet http://www.airbus.com.
runway profiles. standards district office/certificate holding You may view this service information at the
district office. FAA, Transport Airplane Directorate, 1601
(h) Terminating Action Limitation (2) Contacting the Manufacturer: For any Lind Avenue SW., Renton, WA. For
Repair of an airplane, as required by requirement in this AD to obtain corrective information on the availability of this
paragraph (g) of this AD, does not constitute actions from a manufacturer, the action must material at the FAA, call 425–227–1221.
terminating action for the repetitive be accomplished using a method approved
inspections required by paragraph (g) of this by the Manager, International Branch, ANM– Issued in Renton, Washington, on July 14,
AD unless otherwise specified in the 116, Transport Airplane Directorate, FAA; or 2017.
instructions obtained using the procedures the European Aviation Safety Agency Dionne Palermo,
specified in paragraph (j)(2) of this AD. (EASA); or Airbus’s EASA Design Acting Manager, Transport Airplane
Organization Approval (DOA). If approved by Directorate, Aircraft Certification Service.
(i) Optional Terminating Action the DOA, the approval must include the
[FR Doc. 2017–15481 Filed 7–24–17; 8:45 am]
Modification of the wings including a DOA-authorized signature.
detailed inspection of the lower rib feet (rib (3) Required for Compliance (RC): If any BILLING CODE 4910–13–P
2) and bottom skin upper surface of the service information contains procedures or
wings for cracking and all applicable tests that are identified as RC, those
corrective actions, in accordance with the procedures and tests must be done to comply DEPARTMENT OF THE TREASURY
Accomplishment Instructions of Airbus with this AD; any procedures or tests that are
Service Bulletin A320–57–1207, including not identified as RC are recommended. Those Internal Revenue Service
Appendix 01 and Appendix 02, dated May procedures and tests that are not identified
26, 2016, constitutes terminating action for as RC may be deviated from using accepted
the repetitive inspections required by methods in accordance with the operator’s
26 CFR Part 1
paragraph (g) of this AD for that airplane. If, maintenance or inspection program without [REG–112800–16]
during modification of an airplane as obtaining approval of an AMOC, provided
specified in this paragraph, accomplishment the procedures and tests identified as RC can RIN 1545–BN42
of any modification instruction is not be done and the airplane can be put back in
possible due to configuration difficulties, an airworthy condition. Any substitutions or Nuclear Decommissioning Funds;
accomplish the modification using the changes to procedures or tests identified as Hearing
procedures specified in paragraph (j)(1) of RC require approval of an AMOC.
this AD. AGENCY: Internal Revenue Service (IRS),
(k) Related Information
(j) Other FAA AD Provisions
Treasury.
(1) Refer to Mandatory Continuing
ACTION: Notice of a public hearing on
The following provisions also apply to this Airworthiness Information (MCAI) EASA AD
AD: 2016–0222, dated November 7, 2016, for notice of proposed rulemaking.
(1) Alternative Methods of Compliance related information. This MCAI may be
(AMOCs): The Manager, International found in the AD docket on the Internet at SUMMARY: This document provides a
Branch, ANM–116, FAA, has the authority to http://www.regulations.gov by searching for notice of public hearing on proposed
asabaliauskas on DSKBBY8HB2PROD with PROPOSALS
approve AMOCs for this AD, if requested and locating Docket No. FAA–2017–0709. changes to the regulations under section
using the procedures found in 14 CFR 39.19. (2) For more information about this AD, 468A of the Internal Revenue Code of
In accordance with 14 CFR 39.19, send your contact Sanjay Ralhan, Aerospace Engineer, 1986 (Code) relating to deductions for
request to your principal inspector or local International Branch, ANM–116, Transport contributions to trusts maintained for
Flight Standards District Office, as Airplane Directorate, FAA, 1601 Lind decommissioning nuclear power plants
appropriate. If sending information directly Avenue SW., Renton, WA 98057–3356; and the use of the amounts in those
to the manager of the International Branch, telephone 425–227–1405; fax 425–227–1149.
send it to the attention of the person (3) For service information identified in trusts to decommission nuclear plants.
identified in paragraph (k)(2) of this AD. this AD, contact Airbus, Airworthiness DATES: The public hearing is being held
Information may be emailed to: 9-ANM-116- Office—EIAS, 1 Rond Point Maurice on Wednesday, October 25, 2017 at
VerDate Sep<11>2014 17:17 Jul 24, 2017 Jkt 241001 PO 00000 Frm 00030 Fmt 4702 Sfmt 4702 E:\FR\FM\25JYP1.SGM 25JYP1](https://thefederalregister.org/doc/82_FR_34594/page/4.svg)
Document Created: 2018-10-24 11:22:19
Document Modified: 2018-10-24 11:22:19
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by September 8, 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 34453 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR