82 FR 34449 - 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 | 34449-34453 | |
| FR Document | 2017-15485 |
[Federal Register Volume 82, Number 141 (Tuesday, July 25, 2017)] [Proposed Rules] [Pages 34449-34453] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-15485] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0707; Directorate Identifier 2016-NM-014-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; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321 series airplanes. This proposed AD was prompted by reports of fatigue damage in the structure for the door stop fittings on certain fuselage frames (FR). This proposed AD would require repetitive rototest inspections for cracking of the fastener holes in certain door stop fittings, and repair if necessary. 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 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. [[Page 34450]] 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: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, 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- 0707; 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-2017-0707; Directorate Identifier 2016-NM-014-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 2016-0238, dated December 2, 2016, corrected January 4, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A318 series airplanes; Model A319 series airplanes; Model A320-211, - 212, -214, -231, -232, and -233; and Model A321 series airplanes. The MCAI states: During an A320 fatigue test campaign, it was determined that fatigue damage could appear at the door stop fitting holes of fuselage frame (FR) 66 and FR 68 on left hand (LH) and right hand (RH) sides. This condition, if not detected and corrected, could affect the structural integrity of the airframe. Two inspections, Airworthiness Limitations Item (ALI) tasks 534129 and 534130, were introduced in the Airworthiness Limitations Section (ALS) Part 2 with the April 2012 revision and with some compliance time changes with Revision 3 of ALS Part 2 of October 2014. Since these ALI tasks were implemented, a significant number of reports [were] received concerning non-critical damage and early crack findings. Prompted by these reports, Airbus published SB A320- 53-1288 and SB A320-53-1290, providing inspection instructions to improve damage management and modification instructions. Consequently, EASA issued AD 2016-0015, requiring repetitive rototest inspections of the affected door stop fitting holes and, depending on findings, repair of any cracked area(s). Since that [EASA] AD was issued, ALS Part 2 Revision 04 and later on Revision 05 were published, introducing updated thresholds and/or intervals for some tasks as specified in Airbus SB A320-53- 1288, introducing new configuration of aeroplane with RETRO WING having accomplished SB A320-57-1193 (mod 160080), and keeping the threshold or interval only in flight cycles (FC). For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2016-0015, which is superseded, but requires those actions within the updated thresholds and intervals. In addition, a corrected threshold for pre-mod 160021 A321 aeroplanes is introduced and the Applicability is reduced to exclude configurations that are not affected. This [EASA] AD is republished to clarify some requirements in Appendix 1 [in this EASA AD]. 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- 0707. Related Service Information Under 1 CFR Part 51 We have reviewed the following Airbus service information. Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016, provides procedures for rototest inspections for cracking of the fastener holes in the airframe structure for the door stop fittings installation in FR66 and FR68. Airbus Service Bulletin A320-53-1290, Revision 01, dated October 3, 2016, provides procedures for cold working the fastener holes in the airframe structure for the door stop fittings installation in FR66 and FR68. 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 the same type design. Difference Between This Proposed AD and the MCAI The MCAI includes an exception to the compliance times for ``post- mod 160080 aeroplanes for which a `corrected' threshold or interval can be defined in accordance with the instructions of Airbus SB A320-57- 1193.'' Airbus Service Bulletin A320-57-1193, Revision 04, dated September 30, 2016, and earlier revisions, do not contain corrected compliance times for doing the actions specified in this proposed AD. Therefore, this proposed AD does not include that exception. Operators may request approval of an alternative method of compliance (AMOC) for revised compliance times under the provisions of paragraph (q)(1) of this proposed AD. [[Page 34451]] Explanation of Compliance Time In most ADs, we adopt a compliance time allowing a specified amount of time after the AD's effective date. In this case, however, EASA has already issued regulations that require operators of airplanes in certain configurations to do a rototest inspection for cracking of the holes in certain door stop fittings to address an identified unsafe condition by certain dates. To provide for coordinated implementation of EASA's regulations and this proposed AD, we are using the same compliance dates in this proposed AD. Costs of Compliance We estimate that this proposed AD affects 1,084 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 ---------------------------------------------------------------------------------------------------------------- Inspections...................... 23 work-hours x $85 $0 $1,955 per $2,119,220 per per hour = $1,955 inspection cycle. inspection cycle. per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need this repair. On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Repair........................................ 27 work-hours x $85 per hour = $610 $2,905 $2,295. ---------------------------------------------------------------------------------------------------------------- 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-2017-0707; Directorate Identifier 2016-NM- 014-AD. (a) Comments Due Date We must receive comments by September 8, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and - 133 airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes; certificated in any category; all manufacturer serial numbers, except airplanes specified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD. (1) Airplanes on which Airbus Modification (Mod) 157039 has been embodied in production. (2) Model A319 series airplanes on which Mod 28238, Mod 28162, and Mod 28342 have been embodied in production. (3) Model A318 series airplanes on which Mod 39195 has been embodied in production or Airbus Service Bulletin A320-00-1219 has been embodied in service. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of fatigue damage in the structure for the door stop fittings on certain fuselage frames (FR). We are issuing this AD to detect and correct cracking at the door stop fitting holes of fuselage FR66 and FR68. Such cracking could result in reduced structural integrity of the airplane due to the failure of structural components. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Rototest Inspections Within the applicable compliance times specified in table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and [[Page 34452]] (j) of this AD: Do a rototest inspection of all holes below each door stop fitting at fuselage FR66 and FR68, both left-hand (LH) and right-hand (RH) sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016. Repeat the inspections thereafter at the applicable compliance times specified in table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD, until the modification specified in paragraph (i) of this AD is done. Where the ``Threshold'' column of table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD, specifies compliance times in ``FC'' (flight cycles), those compliance times are total flight cycles since the first flight of the airplane. Table 1 to Paragraphs (g) and (j) of This AD--Aft Passenger/Crew Door Cut-Out Door Stop Fittings Holes at FR66 WEB LH/RH ------------------------------------------------------------------------ Interval (not to Airplanes affected Threshold exceed) (FC) ------------------------------------------------------------------------ A318-PAX (A318-passenger)..... Before 33,800 FC..... 5,900. A319-PAX pre-mod 160001 and Before 42,700 FC..... 7,500. pre-mod 160080. A319-PAX post-mod 160001 OR Before 40,300 FC..... 7,200. A319-PAX post-mod 160080. A320 pre-mod 160001 and pre- Before 48,000 FC..... 9,700. mod 160080. A320 post-mod 160001 OR A320 Before 45,500 FC..... 7,800. post-mod 160080. A321 pre-mod 160021........... Before 34,500 FC or 17,000. before November 30, 2017, whichever is later, without exceeding the accumulation of 42,300 FC since first flight. A321 post-mod 160021.......... 39,400 FC............ 8,500. ------------------------------------------------------------------------ Table 2 to Paragraphs (g) and (j) of This AD--Aft Passenger/Crew Door Cut-Out Door Stop Fittings Holes at FR68 WEB LH/RH ------------------------------------------------------------------------ Interval (not to Airplanes affected Threshold exceed) (FC) ------------------------------------------------------------------------ A318-PAX...................... Before 30,800........ 5,900. A319-PAX pre-mod 160001 and Before 34,400........ 7,500. pre-mod 160080. A319-PAX post-mod 160001 OR Before 33,500........ 7,200. A319-PAX post-mod 160080. A320.......................... Before 40,900........ 9,700. A321 pre-mod 160021........... Before 24,400 FC or 13,600. before November 30, 2017, whichever is later, without exceeding the accumulation of 39,300 FC since first flight. A321 post-mod 160021.......... Before 39,300........ 8,500. ------------------------------------------------------------------------ (h) Airworthiness Limitations Item (ALI) Inspections Accomplished Before the Effective Date of This AD Inspections accomplished as specified in ALI task 534129 or ALI task 534130 before the effective date of this AD are acceptable for compliance with the inspection required by paragraph (g) of this AD. As of the effective date of this AD, repetitive inspections must be continued as required by paragraph (g) of this AD. (i) Optional Modification For airplanes on which no cracks were detected during any rototest inspection required by paragraph (g) of this AD: Modifying the affected area by cold working the fastener holes before further flight after no cracks were detected, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1290, Revision 01, dated October 3, 2016, terminates the repetitive inspections required by paragraph (g) of this AD for the modified area only. (j) Post-Modification Repetitive Inspections For airplanes on which the modification specified in paragraph (i) of this AD has been done: At the compliance time specified in paragraph (j)(1), (j)(2), or (j)(3) of this AD, as applicable, accomplish a rototest inspection of all holes at the door stop fitting locations at fuselage FR66 and FR68, both LH and RH sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016. Repeat the inspection thereafter at intervals not to exceed the applicable compliance times in table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD. (1) For airplanes with less than 1,800 flight cycles accumulated since first flight of the airplane at the time of accomplishing the modification specified in paragraph (i) of this AD: At the applicable initial compliance time specified in table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD. (2) For airplanes with 1,800 flight cycles or more and less than 13,800 flight cycles accumulated since first flight of the airplane at the time of accomplishing the modification specified in paragraph (i) of this AD: Before the accumulation of 48,000 flight cycles since first flight of the airplane. (3) For airplanes with 13,800 flight cycles or more accumulated since first flight of the airplane at the time of accomplishing the modification specified in paragraph (i) of this AD: Before the accumulation of 60,000 flight cycles since first flight of the airplane. (k) Repair If, during any inspection required by paragraph (g) or (j) of this AD, any crack is detected, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Repair of an airplane as required by this paragraph does not constitute terminating action for the repetitive inspections required by paragraph (g) or (j) of this AD for that airplane, unless specified otherwise in instructions approved using a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the EASA; or Airbus's EASA DOA. (l) Post-Repair Actions for Certain Airplanes For an airplane that has been inspected as specified in ALI task 534129 or task 534130 and repaired before the effective date of this AD as specified in the applicable structural repair manual or as specified in an Airbus repair design approval sheet (RDAS): Comply [[Page 34453]] with the requirements of paragraphs (l)(1) and (l)(2) of this AD. (1) For all fastener holes where no damage or cracks were detected (i.e., those not repaired), accomplish the actions required by paragraph (g) of this AD, unless the terminating action specified in paragraph (m) of this AD has been done. (2) For all repaired fastener holes: Within 30 days after the effective date of this AD, or within a compliance time approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the EASA; or Airbus's EASA DOA, whichever occurs later, contact the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the EASA; or Airbus's EASA DOA; for inspection instructions and applicable corrective actions, and do the inspections and applicable corrective actions accordingly. (m) Terminating Action for Certain Airplanes For airplanes that have been inspected, as specified in ALI task 534129 or task 534130, and repaired before the effective date of this AD, as specified in the applicable structural repair manual, or as specified in an Airbus RDAS: Modification of the four fastener holes at door stop locations where no damage or crack was detected (i.e., door stop locations not repaired) by cold working holes before further flight after no cracks were detected, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1290, Revision 01, dated October 3, 2016, constitutes terminating action for the repetitive inspections of those four fastener holes at those door stop locations as required by paragraph (g) or (l)(1) of this AD for that airplane. (n) Actions for Airplanes With Certain Repairs For an airplane that has been repaired before the effective date of this AD in the areas described in this AD using an Airbus RDAS unrelated to ALI task 534129 or task 534130: Before exceeding the compliance times specified in paragraph (g) of this AD, contact the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the EASA; or Airbus's EASA DOA; for corrective action instructions and accomplish those instructions accordingly. Accomplishment of corrective action(s) on an airplane, as required by this paragraph, does not constitute terminating action for the repetitive inspections as required by paragraph (g) or (j) of this AD for that airplane, as applicable, unless specified otherwise in the instructions. (o) Terminating Action for ALI Tasks (1) Accomplishment of inspections on an airplane, as required by paragraph (g), (j), or (l) of this AD, as applicable, constitutes terminating action for the inspection requirements of ALI task 534129 or task 534130, as applicable, for that airplane. (2) Modification of the four fastener holes at a door stop location of an airplane as specified in paragraph (i) or (m) of this AD, as applicable, and subsequent initial inspection required by paragraph (j) of this AD, constitutes terminating action for the inspection requirements of ALI task 534129 or task 534130, as applicable, for those holes for that airplane. Subsequent repetitive inspections are required by paragraph (j) of this AD. (p) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraphs (g) and (j) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-53-1288, including Appendixes 01 and 02, dated October 10, 2014. (2) This paragraph provides credit for actions required by paragraphs (i) and (m) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-53-1290, dated October 10, 2014. (q) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Branch, send it to the attention of the person identified in paragraph (r)(2) of this AD. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): 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. (r) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016-0238, dated December 2, 2016, corrected January 4, 2017, 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- 2017-0707. (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 13, 2017. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-15485 Filed 7-24-17; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 82, No. 141 / Tuesday, July 25, 2017 / Proposed Rules 34449
technical difficulties and cannot contact Comments, data, and other actively encourages the participation
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Otherwise, persons viewing comments electronic signature of the author. Appliance and Equipment Standards
will see only first and last names, Campaign form letters. Please submit Program staff at (202) 586–6636 or via
organization names, correspondence campaign form letters by the originating email at
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comments. letter with a list of supporters’ names
Issued in Washington, DC, on July 11,
Do not submit to https:// compiled into one or more PDFs. This 2017.
www.regulations.gov information for reduces comment processing and
Kathleen B. Hogan,
which disclosure is restricted by statute, posting time.
such as trade secrets and commercial or Confidential Business Information. Deputy Assistant Secretary for Energy
According to 10 CFR 1004.11, any Efficiency, Energy Efficiency and Renewable
financial information (hereinafter
Energy.
referred to as Confidential Business person submitting information that he
[FR Doc. 2017–15580 Filed 7–24–17; 8:45 am]
Information (CBI)). Comments or she believes to be confidential and
submitted through https:// exempt by law from public disclosure BILLING CODE 6450–01–P
www.regulations.gov cannot be claimed should submit via email, postal mail, or
as CBI. Comments received through the hand delivery/courier two well-marked
Web site will waive any CBI claims for copies: One copy of the document DEPARTMENT OF TRANSPORTATION
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information on submitting CBI, see the information believed to be confidential, Federal Aviation Administration
Confidential Business Information and one copy of the document marked
section. ‘‘non-confidential’’ with the information 14 CFR Part 39
DOE processes submissions made believed to be confidential deleted. [Docket No. FAA–2017–0707; Directorate
through https://www.regulations.gov Submit these documents via email or on Identifier 2016–NM–014–AD]
before posting. Normally, comments a CD, if feasible. DOE will make its own
RIN 2120–AA64
will be posted within a few days of determination about the confidential
being submitted. However, if large status of the information and treat it Airworthiness Directives; Airbus
volumes of comments are being according to its determination. Airplanes
processed simultaneously, your Factors of interest to DOE when
comment may not be viewable for up to evaluating requests to treat submitted AGENCY: Federal Aviation
several weeks. Please keep the comment information as confidential include: (1) Administration (FAA), DOT.
tracking number that https:// A description of the items, (2) whether ACTION: Notice of proposed rulemaking
www.regulations.gov provides after you and why such items are customarily (NPRM).
have successfully uploaded your treated as confidential within the
comment. industry, (3) whether the information is SUMMARY: We propose to adopt a new
Submitting comments via email, hand generally known by or available from airworthiness directive (AD) for certain
delivery/courier, or postal mail. other sources, (4) whether the Airbus Model A318 series airplanes;
Comments and documents submitted information has previously been made Model A319 series airplanes; Model
via email, hand delivery/courier, or available to others without obligation A320–211, –212, –214, –231, –232, and
postal mail also will be posted to concerning its confidentiality, (5) an –233 airplanes; and Model A321 series
https://www.regulations.gov. If you do explanation of the competitive injury to airplanes. This proposed AD was
not want your personal contact the submitting person which would prompted by reports of fatigue damage
information to be publicly viewable, do result from public disclosure, (6) when in the structure for the door stop fittings
not include it in your comment or any such information might lose its on certain fuselage frames (FR). This
accompanying documents. Instead, confidential character due to the proposed AD would require repetitive
provide your contact information in a passage of time, and (7) why disclosure rototest inspections for cracking of the
cover letter. Include your first and last of the information would be contrary to fastener holes in certain door stop
names, email address, telephone the public interest. fittings, and repair if necessary. We are
number, and optional mailing address. It is DOE’s policy that all comments proposing this AD to address the unsafe
The cover letter will not be publicly may be included in the public docket, condition on these products.
asabaliauskas on DSKBBY8HB2PROD with PROPOSALS
viewable as long as it does not include without change and as received, DATES: We must receive comments on
any comments. including any personal information this proposed AD by September 8, 2017.
Include contact information each time provided in the comments (except ADDRESSES: You may send comments,
you submit comments, data, documents, information deemed to be exempt from using the procedures found in 14 CFR
and other information to DOE. If you public disclosure). 11.43 and 11.45, by any of the following
submit via mail or hand delivery/ DOE considers public participation to methods:
courier, please provide all items on a be a very important part of the process • Federal eRulemaking Portal: Go to
CD, if feasible, in which case it is not for developing test procedures and http://www.regulations.gov. Follow the
necessary to submit printed copies. energy conservation standards. DOE instructions for submitting comments.
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• Fax: 202–493–2251. We will post all comments we You may examine the MCAI in the
• Mail: U.S. Department of receive, without change, to http:// AD docket on the Internet at http://
Transportation, Docket Operations, M– www.regulations.gov, including any www.regulations.gov by searching for
30, West Building Ground Floor, Room personal information you provide. We and locating Docket No. FAA–2017–
W12–140, 1200 New Jersey Avenue SE., will also post a report summarizing each 0707.
Washington, DC 20590. substantive verbal contact we receive
• Hand Delivery: U.S. Department of Related Service Information Under 1
about this proposed AD.
Transportation, Docket Operations, M– CFR Part 51
30, West Building Ground Floor, Room Discussion
We have reviewed the following
W12–140, 1200 New Jersey Avenue SE., The European Aviation Safety Agency Airbus service information.
Washington, DC, between 9 a.m. and 5 (EASA), which is the Technical Agent
p.m., Monday through Friday, except for the Member States of the European • Airbus Service Bulletin A320–53–
Federal holidays. Union, has issued EASA AD 2016–0238, 1288, Revision 01, including
For service information identified in dated December 2, 2016, corrected Appendixes 01, 02, and 03, dated
this NPRM, contact Airbus, January 4, 2017 (referred to after this as October 3, 2016, provides procedures
Airworthiness Office–EIAS, 1 Rond the Mandatory Continuing for rototest inspections for cracking of
Point Maurice Bellonte, 31707 Blagnac Airworthiness Information, or ‘‘the the fastener holes in the airframe
Cedex, France; telephone +33 5 61 93 36 MCAI’’), to correct an unsafe condition structure for the door stop fittings
96; fax +33 5 61 93 44 51; email for certain Airbus Model A318 series installation in FR66 and FR68.
account.airworth-eas@airbus.com; airplanes; Model A319 series airplanes; • Airbus Service Bulletin A320–53–
Internet http://www.airbus.com. You Model A320–211, –212, –214, –231, 1290, Revision 01, dated October 3,
may view this referenced service –232, and –233; and Model A321 series 2016, provides procedures for cold
information at the FAA, Transport airplanes. The MCAI states: working the fastener holes in the
Airplane Directorate, 1601 Lind Avenue airframe structure for the door stop
During an A320 fatigue test campaign, it
SW., Renton, WA. For information on fittings installation in FR66 and FR68.
was determined that fatigue damage could
the availability of this material at the appear at the door stop fitting holes of This service information is reasonably
FAA, call 425 227–1221. fuselage frame (FR) 66 and FR 68 on left hand available because the interested parties
Examining the AD Docket (LH) and right hand (RH) sides. have access to it through their normal
This condition, if not detected and course of business or by the means
You may examine the AD docket on corrected, could affect the structural integrity
the Internet at http:// identified in the ADDRESSES section.
of the airframe.
www.regulations.gov by searching for Two inspections, Airworthiness FAA’s Determination and Requirements
and locating Docket No. FAA–2017– Limitations Item (ALI) tasks 534129 and of This Proposed AD
0707; or in person at the Docket 534130, were introduced in the
Management Facility between 9 a.m. Airworthiness Limitations Section (ALS) Part This product has been approved by
and 5 p.m., Monday through Friday, 2 with the April 2012 revision and with some the aviation authority of another
compliance time changes with Revision 3 of country, and is approved for operation
except Federal holidays. The AD docket ALS Part 2 of October 2014.
contains this proposed AD, the in the United States. Pursuant to our
Since these ALI tasks were implemented,
regulatory evaluation, any comments bilateral agreement with the State of
a significant number of reports [were]
received, and other information. The received concerning non-critical damage and Design Authority, we have been notified
street address for the Docket Operations early crack findings. Prompted by these of the unsafe condition described in the
office (telephone 800–647–5527) is in reports, Airbus published SB A320–53–1288 MCAI and service information
the ADDRESSES section. Comments will and SB A320–53–1290, providing inspection referenced above. We are proposing this
be available in the AD docket shortly instructions to improve damage management AD because we evaluated all pertinent
after receipt. and modification instructions. information and determined an unsafe
Consequently, EASA issued AD 2016– condition exists and is likely to exist or
FOR FURTHER INFORMATION CONTACT:
0015, requiring repetitive rototest inspections develop on other products of the same
Sanjay Ralhan, Aerospace Engineer, of the affected door stop fitting holes and,
International Branch, ANM–116, type design.
depending on findings, repair of any cracked
Transport Airplane Directorate, FAA, area(s). Difference Between This Proposed AD
1601 Lind Avenue SW., Renton, WA Since that [EASA] AD was issued, ALS and the MCAI
98057–3356; telephone 425–227–1405; Part 2 Revision 04 and later on Revision 05
fax 425–227–1149. were published, introducing updated The MCAI includes an exception to
thresholds and/or intervals for some tasks as the compliance times for ‘‘post-mod
SUPPLEMENTARY INFORMATION:
specified in Airbus SB A320–53–1288, 160080 aeroplanes for which a
Comments Invited introducing new configuration of aeroplane ‘corrected’ threshold or interval can be
with RETRO WING having accomplished SB
We invite you to send any written A320–57–1193 (mod 160080), and keeping
defined in accordance with the
relevant data, views, or arguments about the threshold or interval only in flight cycles instructions of Airbus SB A320–57–
this proposal. Send your comments to (FC). 1193.’’ Airbus Service Bulletin A320–
an address listed under the ADDRESSES For the reasons described above, this 57–1193, Revision 04, dated September
section. Include ‘‘Docket No. FAA– [EASA] AD retains the requirements of EASA 30, 2016, and earlier revisions, do not
asabaliauskas on DSKBBY8HB2PROD with PROPOSALS
2017–0707; Directorate Identifier 2016– AD 2016–0015, which is superseded, but contain corrected compliance times for
NM–014–AD’’ at the beginning of your requires those actions within the updated doing the actions specified in this
comments. We specifically invite thresholds and intervals. In addition, a proposed AD. Therefore, this proposed
comments on the overall regulatory, corrected threshold for pre-mod 160021 A321 AD does not include that exception.
aeroplanes is introduced and the
economic, environmental, and energy Applicability is reduced to exclude
Operators may request approval of an
aspects of this proposed AD. We will configurations that are not affected. alternative method of compliance
consider all comments received by the This [EASA] AD is republished to clarify (AMOC) for revised compliance times
closing date and may amend this some requirements in Appendix 1 [in this under the provisions of paragraph (q)(1)
proposed AD based on those comments. EASA AD]. of this proposed AD.
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![Federal Register / Vol. 82, No. 141 / Tuesday, July 25, 2017 / Proposed Rules 34451
Explanation of Compliance Time a rototest inspection for cracking of the Costs of Compliance
holes in certain door stop fittings to
In most ADs, we adopt a compliance address an identified unsafe condition We estimate that this proposed AD
time allowing a specified amount of by certain dates. To provide for affects 1,084 airplanes of U.S. registry.
time after the AD’s effective date. In this coordinated implementation of EASA’s We estimate the following costs to
case, however, EASA has already issued regulations and this proposed AD, we comply with this proposed AD:
regulations that require operators of are using the same compliance dates in
airplanes in certain configurations to do this proposed AD.
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspections ........................ 23 work-hours × $85 per hour = $1,955 $0 $1,955 per inspection $2,119,220 per inspection
per inspection cycle. cycle. cycle.
We estimate the following costs to do required based on the results of the determining the number of aircraft that
any necessary repairs that would be proposed inspection. We have no way of might need this repair.
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Repair .......................................................... 27 work-hours × $85 per hour = $2,295 ....................................... $610 $2,905
Authority for This Rulemaking 2. Is not a ‘‘significant rule’’ under the (c) Applicability
DOT Regulatory Policies and Procedures This AD applies to Airbus Model A318–
Title 49 of the United States Code (44 FR 11034, February 26, 1979); 111, –112, –121, and –122 airplanes; Model
specifies the FAA’s authority to issue A319–111, –112, –113, –114, –115, –131,
3. Will not affect intrastate aviation in
rules on aviation safety. Subtitle I, –132, and –133 airplanes; Model A320–211,
Alaska; and
section 106, describes the authority of –212, –214, –231, –232, and –233 airplanes;
4. Will not have a significant
the FAA Administrator. ‘‘Subtitle VII: and Model A321–111, –112, –131, –211,
economic impact, positive or negative, –212, –213, –231, and –232 airplanes;
Aviation Programs,’’ describes in more
on a substantial number of small entities certificated in any category; all manufacturer
detail the scope of the Agency’s
under the criteria of the Regulatory serial numbers, except airplanes specified in
authority.
Flexibility Act. paragraphs (c)(1), (c)(2), and (c)(3) of this AD.
We are issuing this rulemaking under (1) Airplanes on which Airbus
the authority described in ‘‘Subtitle VII, List of Subjects in 14 CFR Part 39 Modification (Mod) 157039 has been
Part A, Subpart III, Section 44701: Air transportation, Aircraft, Aviation embodied in production.
General requirements.’’ Under that safety, Incorporation by reference, (2) Model A319 series airplanes on which
section, Congress charges the FAA with Mod 28238, Mod 28162, and Mod 28342
Safety. have been embodied in production.
promoting safe flight of civil aircraft in
air commerce by prescribing regulations The Proposed Amendment (3) Model A318 series airplanes on which
Mod 39195 has been embodied in production
for practices, methods, and procedures Accordingly, under the authority or Airbus Service Bulletin A320–00–1219 has
the Administrator finds necessary for delegated to me by the Administrator, been embodied in service.
safety in air commerce. This regulation the FAA proposes to amend 14 CFR part
is within the scope of that authority (d) Subject
39 as follows:
because it addresses an unsafe condition Air Transport Association (ATA) of
that is likely to exist or develop on PART 39—AIRWORTHINESS America Code 53, Fuselage.
products identified in this rulemaking DIRECTIVES (e) Reason
action. This AD was prompted by reports of
■ 1. The authority citation for part 39 fatigue damage in the structure for the door
Regulatory Findings continues to read as follows: stop fittings on certain fuselage frames (FR).
We determined that this proposed AD Authority: 49 U.S.C. 106(g), 40113, 44701. We are issuing this AD to detect and correct
would not have federalism implications cracking at the door stop fitting holes of
under Executive Order 13132. This § 39.13 [Amended] fuselage FR66 and FR68. Such cracking could
proposed AD would not have a ■ 2. The FAA amends § 39.13 by adding result in reduced structural integrity of the
substantial direct effect on the States, on airplane due to the failure of structural
the following new Airworthiness
asabaliauskas on DSKBBY8HB2PROD with PROPOSALS
components.
the relationship between the national Directive (AD):
Government and the States, or on the (f) Compliance
Airbus: Docket No. FAA–2017–0707;
distribution of power and Directorate Identifier 2016–NM–014–AD. Comply with this AD within the
responsibilities among the various compliance times specified, unless already
levels of government. (a) Comments Due Date done.
For the reasons discussed above, I We must receive comments by September
(g) Repetitive Rototest Inspections
8, 2017.
certify this proposed regulation: Within the applicable compliance times
1. Is not a ‘‘significant regulatory (b) Affected ADs specified in table 1 to paragraphs (g) and (j)
action’’ under Executive Order 12866; None. of this AD and table 2 to paragraphs (g) and
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![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
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Document Created: 2018-10-24 11:22:43
Document Modified: 2018-10-24 11:22:43
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | 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 34449 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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