83 FR 25590 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 107 (June 4, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 107 (June 4, 2018)
| Page Range | 25590-25595 | |
| FR Document | 2018-11822 |
[Federal Register Volume 83, Number 107 (Monday, June 4, 2018)] [Proposed Rules] [Pages 25590-25595] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-11822] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0497; Product Identifier 2017-NM-140-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 A300 B4-603, B4-620, and B4-622 airplanes; Model A300 F4-605R airplanes; Model A300 C4-605R Variant F airplanes; and Model A300 B4-600R series airplanes. This proposed AD was prompted by reports of cracking on the frame (FR) 47 angle fitting. This proposed AD would require, depending on airplane configuration, a modification of certain angle fitting attachment holes, repetitive inspections for cracking of certain holes of the internal lower angle fitting web, certain holes of the internal lower angle fitting horizontal splicing, the aft bottom panel, and the FR47/Rib 1 junction area, and related investigative and corrective actions 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 July 19, 2018. 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. 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 SAS, Airworthiness Office--EAW, 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 Standards Branch, 2200 [[Page 25591]] South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. 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-2018- 0497; 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 NPRM, 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: Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3225. 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-2018-0497; Product Identifier 2017-NM-140-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM 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 NPRM. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017-0210, dated October 24, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A300 B4-603, B4- 620, and B4-622 airplanes; Model A300 F4-605R airplanes; Model A300 C4- 605R Variant F airplanes; and Model A300 B4-600R series airplanes. The MCAI states: Prompted by cracks found on the Frame (FR) 47 angle fitting, Airbus issued SB [Service Bulletin] A300-57-6049, SB A300-57-6050, and SB A300-57-6086. These cracks, if not detected and corrected, could affect the structural integrity of the centre wing box (CWB) of the aeroplane. Consequently, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France published AD 94-241-170, AD 1999-147-279, AD 2000-533-328 and AD F-2004-159 (EASA approval 2004-9779), each AD superseding the previous one, to require repetitive high frequency eddy current (HFEC) rotating probe inspections of the FR47 internal lower angle fitting. After DGAC France AD F-2004-159 was issued, cracks were reportedly found on the horizontal flange of FR47 internal corner angle fitting during accomplishment of routine maintenance structural inspection and modification in accordance with the instructions of Airbus SB A300-57-6050. Prompted by these findings, Airbus reviewed and amended the inspection programme for the internal lower angle fitting flange (horizontal face). Consequently, EASA issued AD 2012-0092 [which corresponds to FAA AD 2014-20-18, Amendment 39-17991 (79 FR 65879, November 6, 2014) (``AD 2014-20-18'')], retaining the requirements of DGAC France AD F-2004-159, which was superseded, and requiring additional repetitive inspections of the CWB lower panel through the ultrasonic method and, depending on findings, re-installation of removed fasteners in transition fit instead of interface. In addition, DGAC France had previously issued AD F-2005-124 (EASA approval 2005-6071) to require the same inspections for A300 F4-608ST aeroplanes, in accordance with Airbus SB A300-57-9001 and SB A300-57-9002. Following the discovery of numerous cracks during the accomplishment of SB A300-57-6049 and SB A300-57-6089 inspections, Airbus developed in a first step a new (recommended) modification (Airbus SB A300-57-6113) and defined, for post-mod aeroplanes, new inspections, and published SB A300-57-6119, which included new inspection methods (ultrasonic/radiographic) with new inspection thresholds and intervals. Consequently, EASA issued AD 2016-0198, retaining the requirements of EASA AD 2012-0092, which was superseded, to require repetitive inspections for post-SB A300-57-6113 aeroplanes. Since EASA AD 2016-0198 was issued, Airbus revised in a second step the inspection programme for A300-600 pre-SB 57-6113 and A300- 600ST aeroplanes, reducing inspection thresholds and intervals. At this opportunity, the existing ultrasonic inspection for A300-600 aeroplanes has been added for A300-600ST aeroplanes. For the reasons described above, this new [EASA] AD retains the requirements of EASA AD 2016-0198 for A300-600 aeroplanes and of DGAC France AD F-2005-124 for A300-600ST aeroplanes, which are both superseded, and requires [modification through cold expansion of certain angle fitting attachment holes and] repetitive inspections [for cracking of certain holes of the internal lower angle fitting web, certain holes of the internal lower angle fitting horizontal splicing, the aft bottom panel, and the FR47/Rib 1 junction area, and applicable related investigative and corrective actions] with new compliance times and intervals. This [EASA] AD is applicable to both A300-600 and A300-600ST aeroplanes * * *. Related investigative actions include a rotating probe inspection for cracking. Corrective actions include replacing damaged fasteners, reaming and drilling holes, installing the next nominal fastener for oversized bore holes, and repairing cracks. 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-2018-0497. Relationship Between Proposed AD and AD 2014-20-18 This NPRM would not supersede AD 2014-20-18. Rather, we have determined that a stand-alone AD would be more appropriate to address the changes in the MCAI. This NPRM would require depending on airplane configuration, a modification of certain angle fitting attachment holes, inspections for cracking of certain holes of the internal lower angle fitting web, certain holes of the internal lower angle fitting horizontal splicing, the aft bottom panel, and the FR47/Rib 1 junction area. Accomplishment of the proposed modification and initial inspections would then terminate all of the requirements of AD 2014-20- 18. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. Service Bulletin A300-57-6049, Revision 8, dated July 4, 2017. This service information describes procedures for HFEC rotating probe inspections for cracking of certain holes of the internal lower angle fitting web. Service Bulletin A300-57-6086, Revision 6, dated July 4, 2017. This service information describes procedures for HFEC rotating probe inspections for cracking of certain holes in the internal lower angle fitting horizontal splicing (left-hand and right-hand sides) and for ultrasonic inspections for cracking of the aft bottom panel. Service Bulletin A300-57-6119, Revision 00, dated April 25, 2016. This service information describes procedures for ultrasonic and radiographic inspections for cracking of the FR47/Rib 1 junction area. This service information is reasonably available because the interested parties have access to it through their normal [[Page 25592]] 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. Costs of Compliance We estimate that this proposed AD affects 65 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs for Required Actions ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Up to 727 work-hours x $85 per Up to $3,370............... Up to $65,165.............. Up to $4,235,725 hour = Up to $61,795. per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate that it would take about 1 work-hour per product to comply with the proposed reporting requirement in this proposed AD. The average labor rate is $85 per hour. Based on these figures, we estimate the cost of reporting the inspection results on U.S. operators to be $5,525, or $85 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this NPRM is 2120- 0056. The paperwork cost associated with this NPRM has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this NPRM is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES-200. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this 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-2018-0497; Product Identifier 2017-NM-140-AD. (a) Comments Due Date We must receive comments by July 19, 2018. (b) Affected ADs This AD affects AD 2014-20-18, Amendment 39-17991 (79 FR 65879, November 6, 2014) (``AD 2014-20-18''). (c) Applicability This AD applies to Airbus Model A300 B4-603, A300 B4-620, A300 B4-622, A300 B4-605R, A300 B4-622R, A300 C4-605R Variant F, and A300 F4-605R airplanes, certificated in any category, all manufacturer serial numbers, except airplanes on which Airbus Modification 12171 or 12249 has been embodied in production, or on which Airbus Service Bulletin A300-57-6069 has been embodied in service. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by reports of cracking on the frame (FR) 47 angle fitting. We are issuing this AD to detect and correct cracking of FR47 angle fitting, which could [[Page 25593]] result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definitions For the purposes of this AD, the definitions in paragraphs (g)(1) through (g)(6) apply. (1) Group 1 airplanes are those airplanes on which Airbus Service Bulletin A300-57-6113, Revision 00, dated April 25, 2016, has not been incorporated as of the effective date of this AD. (2) Group 2 airplanes are those airplanes on which Airbus Service Bulletin A300-57-6113, Revision 00, dated April 25, 2016, has been incorporated as of the effective date of this AD. (3) The average flight time (AFT) for the inspection threshold is defined as the flight hours (FH) divided by the flight cycles (FC), counted from the first flight of the airplane. (4) The AFT for the inspection interval is defined as the FH divided by the FC, counted from the date of the last inspection required by paragraph (i), (j), (k), or (l) of this AD, as applicable. (5) For airplanes on which Airbus modification 10155 has been embodied, the thresholds for the inspections required by paragraphs (i), (j), and (k) of this AD are counted from the first flight of the airplane. (6) For airplanes on which Airbus modification 10155 has not been embodied, the thresholds for the inspections required by paragraphs (i), (j), and (k) of this AD are counted since the date on which Airbus Service Bulletin A300-57-6050 was embodied on the airplane. (h) Modification For all airplanes on which Airbus modification 10155 has not been embodied: Before exceeding 15,100 FC or 38,900 FH, whichever occurs first after first flight of the airplane; or within the ``grace periods'' defined in paragraph 1.B.(4), ``Accomplishment Timescale,'' of Airbus Service Bulletin A300-57-6050, Revision 3, dated May 31, 2001; whichever occurs later, modify the angle fitting attachment holes of the wing center box by cold expansion, including doing a rotating probe inspection for cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57- 6050, Revision 3, dated May 31, 2001. Where paragraph 1.B.(4), ``Accomplishment Timescale,'' of Airbus Service Bulletin A300-57- 6050, Revision 3, dated May 31, 2001, specifies ``grace periods'' relative to the receipt of the service bulletin, count the ``grace periods'' from December 19, 2005 (the effective date of AD 2005-23- 08). If any crack is found during any inspection: Before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA- authorized signature. (i) Internal Lower Angle Fitting (Vertical Face) Web Inspections For Group 1 airplanes: Before exceeding the applicable threshold specified in figure 1 to paragraph (i) of this AD, or within 12 months after the effective date of this AD, whichever occurs later, do a high frequency eddy current (HFEC) rotating probe inspection for cracking of holes H, I, K, L, M, N, U, V, W, X, and Y of the internal lower angle fitting web (left-hand and right-hand sides), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6049, Revision 8, dated July 4, 2017. Repeat the inspection thereafter at intervals not to exceed those specified in figure 1 to paragraph (i) of this AD. [GRAPHIC] [TIFF OMITTED] TP04JN18.002 (j) Internal Lower Angle Fitting (Horizontal Face) Inspections For Group 1 airplanes: Before exceeding the applicable threshold specified in figure 2 to paragraph (j) of this AD, or within 12 months after the effective date of this AD, whichever occurs later, do an HFEC rotating probe inspection for cracking of holes A, B, C, D, E, F, G, P, Q, S, and T (adjacent to hole G) of the internal lower angle fitting horizontal splicing (left-hand and right-hand sides), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, Revision 6, dated July 4, 2017. Repeat the inspection thereafter at intervals not to exceed those specified in figure 2 to paragraph (j) of this AD. [GRAPHIC] [TIFF OMITTED] TP04JN18.003 [[Page 25594]] (k) Aft Bottom Panel Inspections For Group 1 airplanes: Before exceeding the applicable thresholds specified in figure 3 to paragraph (k) of this AD, or within 12 months after the effective date of this AD, whichever occurs later, do an ultrasonic inspection for cracking of the aft bottom panel, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, Revision 6, dated July 4, 2017. Repeat the inspection thereafter at intervals not to exceed those specified in figure 3 to paragraph (k) of this AD. [GRAPHIC] [TIFF OMITTED] TP04JN18.004 (l) FR47/Rib 1 Junction Area Inspections For Group 2 airplanes: Before exceeding the applicable thresholds specified in figure 4 to paragraph (l) of this AD, do ultrasonic and radiographic inspections for cracking of the FR47/Rib 1 junction area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6119, Revision 00, dated April 25, 2016. Repeat the inspections thereafter at intervals not to exceed those specified in figure 4 to paragraph (l) of this AD. Count the threshold compliance times from the date on which Airbus Service Bulletin A300-57-6113, Revision 00, dated April 25, 2016, was embodied on the airplane. [GRAPHIC] [TIFF OMITTED] TP04JN18.005 (m) Related Investigative and Corrective Actions If, during any inspection required by paragraph (i), (j), (k), or (l) of this AD, any crack is found: Before further flight, accomplish all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of the service information specified in paragraphs (m)(1) through (m)(3) of this AD, as applicable. Where the service information specified in paragraphs (m)(1) through (m)(3) of this AD specifies to contact Airbus for instructions, before further flight, obtain instructions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA and accomplish those instructions accordingly. If approved by the DOA, the approval must include the DOA-authorized signature. (1) If the inspection was done as specified in paragraph (i) of this AD: Airbus Service Bulletin A300-57-6049, Revision 8, dated July 4, 2017. (2) If the inspection was done as specified in paragraph (j) or (k) of this AD: Airbus Service Bulletin A300-57-6086, Revision 6, dated July 4, 2017. (3) If the inspection was done as specified in paragraph (l) of this AD: Airbus Service Bulletin A300-57-6119, Revision 00, dated April 25, 2016. (n) Reporting At the applicable time specified in paragraph (n)(1) or (n)(2) of this AD: Report the results of the inspections required by paragraphs (i), (j), (k), and (l) of this AD to Airbus Service Bulletin Reporting Online Application on Airbus World (https://w3.airbus.com/), or submit the results to Airbus in accordance with the instructions of the applicable service information specified in paragraphs (i), (j), (k), or (l) of this AD. The report must include the inspection results, a description of any discrepancies found, the [[Page 25595]] airplane serial number, and the number of flight cycles and flight hours on the airplane. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (o) Terminating Action for AD 2014-20-18 Accomplishment of the action required by paragraph (h) of this AD and the initial inspections required by paragraphs (i) and (j), and (k) of this AD terminates all requirements of AD 2014-20-18. (p) Credit for Previous Actions This paragraph provides credit for actions specified in paragraph (h) of this AD, if those actions were performed before December 19, 2005 (the effective date of AD 2005-23-08), using Airbus Service Bulletin A300-57-6050, Revision 02, dated February 10, 2000. (q) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, 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 Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA- authorized signature. (3) Paperwork Reduction Act Burden Statement: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 1 work-hour per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. (4) Required for Compliance (RC): Except as required by paragraph (m) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (r) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017-0210, dated October 24, 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-2018-0497. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3225. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 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 Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. Issued in Des Moines, Washington, on May 23, 2018. James Cashdollar, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-11822 Filed 6-1-18; 8:45 am] BILLING CODE 4910-13-P
![25590 Federal Register / Vol. 83, No. 107 / Monday, June 4, 2018 / Proposed Rules
(3) During any detailed or rototest (o) Other FAA AD Provisions DEPARTMENT OF TRANSPORTATION
inspection required by paragraph (h)(2) of The following provisions also apply to this
this AD, if any crack is found, before further Federal Aviation Administration
AD:
flight, replace the NLG door mechanism
(1) Alternative Methods of Compliance
actuator shaft with a serviceable part, in 14 CFR Part 39
accordance with the instructions of Airbus (AMOCs): The Manager, International
Defence and Space AOT AOT–CN235–32– Section, Transport Standards Branch, FAA, [Docket No. FAA–2018–0497; Product
0001, Revision 2, dated October 26, 2016; or has the authority to approve AMOCs for this Identifier 2017–NM–140–AD]
AOT AOT–C295–32–0001, Revision 2, dated AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR RIN 2120–AA64
October 26, 2016; as applicable.
39.19, send your request to your principal
(j) Replacement not Terminating Action Airworthiness Directives; Airbus
inspector or local Flight Standards District
Accomplishment of any corrective action Airplanes
Office, as appropriate. If sending information
on an airplane, as required by paragraph directly to the International Section, send it AGENCY: Federal Aviation
(i)(1), (i)(2), or (i)(3) of this AD, as applicable,
to the attention of the person identified in Administration (FAA), DOT.
is not terminating action for the repetitive
paragraph (p)(2) of this AD. Information may ACTION: Notice of proposed rulemaking
detailed or rototest inspections required by
paragraphs (h)(1) and (h)(2) of this AD, for be emailed to: 9-ANM-116-AMOC- (NPRM).
that airplane. REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate SUMMARY: We propose to adopt a new
(k) Optional Terminating Action principal inspector, or lacking a principal airworthiness directive (AD) for certain
For Model CN–235, CN–235–100, CN–235– inspector, the manager of the local flight Airbus Model A300 B4–603, B4–620,
200, and CN–235–300 airplanes: standards district office/certificate holding and B4–622 airplanes; Model A300 F4–
Modification of the NLG door latching district office. 605R airplanes; Model A300 C4–605R
mechanism, in accordance with the (2) Contacting the Manufacturer: For any Variant F airplanes; and Model A300
Accomplishment Instructions of Airbus requirement in this AD to obtain corrective
Defence and Space Service Bulletin SB–235– B4–600R series airplanes. This proposed
actions from a manufacturer, the action must AD was prompted by reports of cracking
32–0031C, dated September 22, 2016, is
be accomplished using a method approved on the frame (FR) 47 angle fitting. This
terminating action for the repetitive
inspections required by paragraphs (h)(1) and by the Manager, International Section, proposed AD would require, depending
(h)(2) of this AD, for that airplane. Transport Standards Branch, FAA; or the on airplane configuration, a
European Aviation Safety Agency (EASA); or modification of certain angle fitting
(l) Parts Installation Limitation Airbus Space and Defense’s EASA Design attachment holes, repetitive inspections
As of the effective date of this AD, Organization Approval (DOA). If approved by for cracking of certain holes of the
installation of an NLG door mechanism the DOA, the approval must include the
actuator shaft assembly having P/N 35–
internal lower angle fitting web, certain
DOA-authorized signature. holes of the internal lower angle fitting
42311–00 or P/N 95–42315–00, or any of its
components, is allowed, provided that the (p) Related Information horizontal splicing, the aft bottom
part is new; or provided that the assembly or (1) Refer to Mandatory Continuing panel, and the FR47/Rib 1 junction area,
the components, as applicable, has passed an Airworthiness Information (MCAI) EASA AD and related investigative and corrective
inspection; in accordance with the 2017–0181, dated September 18, 2017, for actions if necessary. We are proposing
instructions of Airbus Space and Defence this AD to address the unsafe condition
related information. This MCAI may be
AOT AOT–CN235–32–0001, Revision 2, on these products.
dated October 26, 2016; or AOT AOT–C295– found in the AD docket on the internet at
32–0001, Revision 2, dated October 26, 2016; http://www.regulations.gov by searching for DATES: We must receive comments on
as applicable. and locating Docket No. FAA–2018–0493. this proposed AD by July 19, 2018.
(2) For more information about this AD, ADDRESSES: You may send comments,
(m) Reporting Not Required contact Shahram Daneshmandi, Aerospace using the procedures found in 14 CFR
Although Airbus Space and Defence AOT Engineer, International Section, Transport 11.43 and 11.45, by any of the following
AOT–CN235–32–0001, Revision 2, dated Standards Branch, FAA, 2200 South 216th methods:
October 26, 2016; and AOT AOT–C295–32–
0001, Revision 2, dated October 26, 2016;
St., Des Moines, WA 98198; telephone and • Federal eRulemaking Portal: Go to
fax 206–231–3220. http://www.regulations.gov. Follow the
both specify to submit certain information to
(3) For service information identified in instructions for submitting comments.
the manufacturer, this AD does not include
that requirement. this AD, contact Airbus Defense and Space • Fax: 202–493–2251.
Services/Engineering Support, Avenida de • Mail: U.S. Department of
(n) Credit for Previous Actions Aragón 404, 28022 Madrid, Spain; telephone Transportation, Docket Operations, M–
This paragraph provides credit for the +34 91 585 55 84; fax +34 91 585 31 27; email 30, West Building Ground Floor, Room
initial inspection required by paragraph MTA.TechnicalService@airbus.com. You W12–140, 1200 New Jersey Avenue SE,
(h)(1) and (h)(2) of this AD, and the may view this service information at the
corrective actions required by paragraphs
Washington, DC 20590.
(i)(1), (i)(2), and (i)(3) of this AD, if those
FAA, Transport Standards Branch, 2200 • Hand Delivery: Deliver to Mail
South 216th St., Des Moines, WA. For address above between 9 a.m. and 5
actions were performed before the effective information on the availability of this
date of this AD using the applicable service p.m., Monday through Friday, except
material at the FAA, call 206–231–3195. Federal holidays.
information identified in paragraphs (n)(1)
through (n)(4) of this AD. Issued in Des Moines, Washington, on May For service information identified in
(1) Airbus Space and Defence AOT AOT– 23, 2018. this NPRM, contact Airbus SAS,
sradovich on DSK3GMQ082PROD with PROPOSALS
CN235–32–0001, dated September 29, 2015. Airworthiness Office—EAW, 1 Rond
James Cashdollar,
(2) Airbus Space and Defence AOT AOT– Point Maurice Bellonte, 31707 Blagnac
CN235–32–0001, Revision 1, dated February Acting Director, System Oversight Division,
Aircraft Certification Service. Cedex, France; telephone +33 5 61 93 36
19, 2016.
(3) Airbus Space and Defence AOT AOT– [FR Doc. 2018–11699 Filed 6–1–18; 8:45 am]
96; fax +33 5 61 93 44 51; email
C295–32–0001, dated September 29, 2015. account.airworth-eas@airbus.com;
BILLING CODE 4910–13–P
(4) Airbus Space and Defence AOT AOT– internet http://www.airbus.com. You
C295–32–0001, Revision 1, dated February may view this service information at the
19, 2016. FAA, Transport Standards Branch, 2200
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![Federal Register / Vol. 83, No. 107 / Monday, June 4, 2018 / Proposed Rules 25591
South 216th St., Des Moines, WA. For [Service Bulletin] A300–57–6049, SB A300– holes of the internal lower angle fitting
information on the availability of this 57–6050, and SB A300–57–6086. horizontal splicing, the aft bottom panel, and
material at the FAA, call 206–231–3195. These cracks, if not detected and corrected, the FR47/Rib 1 junction area, and applicable
could affect the structural integrity of the related investigative and corrective actions]
Examining the AD Docket centre wing box (CWB) of the aeroplane. with new compliance times and intervals.
Consequently, DGAC [Direction Générale This [EASA] AD is applicable to both A300–
You may examine the AD docket on de l’Aviation Civile] France published AD 600 and A300–600ST aeroplanes * * *.
the internet at http:// 94–241–170, AD 1999–147–279, AD 2000–
www.regulations.gov by searching for 533–328 and AD F–2004–159 (EASA Related investigative actions include a
and locating Docket No. FAA–2018– approval 2004–9779), each AD superseding rotating probe inspection for cracking.
0497; or in person at the Docket the previous one, to require repetitive high Corrective actions include replacing
Management Facility between 9 a.m. frequency eddy current (HFEC) rotating damaged fasteners, reaming and drilling
and 5 p.m., Monday through Friday, probe inspections of the FR47 internal lower holes, installing the next nominal
angle fitting. fastener for oversized bore holes, and
except Federal holidays. The AD docket
After DGAC France AD F–2004–159 was
contains this NPRM, the regulatory issued, cracks were reportedly found on the
repairing cracks. You may examine the
evaluation, any comments received, and horizontal flange of FR47 internal corner MCAI in the AD docket on the internet
other information. The street address for angle fitting during accomplishment of at http://www.regulations.gov by
the Docket Operations office (telephone routine maintenance structural inspection searching for and locating Docket No.
800–647–5527) is in the ADDRESSES and modification in accordance with the FAA–2018–0497.
section. Comments will be available in instructions of Airbus SB A300–57–6050.
Prompted by these findings, Airbus reviewed Relationship Between Proposed AD and
the AD docket shortly after receipt. AD 2014–20–18
and amended the inspection programme for
FOR FURTHER INFORMATION CONTACT: Dan the internal lower angle fitting flange
Rodina, Aerospace Engineer, This NPRM would not supersede AD
(horizontal face).
International Section, Transport Consequently, EASA issued AD 2012–0092 2014–20–18. Rather, we have
Standards Branch, FAA, 2200 South [which corresponds to FAA AD 2014–20–18, determined that a stand-alone AD
216th St., Des Moines, WA 98198; Amendment 39–17991 (79 FR 65879, would be more appropriate to address
telephone and fax 206–231–3225. November 6, 2014) (‘‘AD 2014–20–18’’)], the changes in the MCAI. This NPRM
SUPPLEMENTARY INFORMATION:
retaining the requirements of DGAC France would require depending on airplane
AD F–2004–159, which was superseded, and configuration, a modification of certain
Comments Invited requiring additional repetitive inspections of angle fitting attachment holes,
the CWB lower panel through the ultrasonic inspections for cracking of certain holes
We invite you to send any written method and, depending on findings, re-
relevant data, views, or arguments about of the internal lower angle fitting web,
installation of removed fasteners in transition
this proposal. Send your comments to fit instead of interface. certain holes of the internal lower angle
an address listed under the ADDRESSES In addition, DGAC France had previously fitting horizontal splicing, the aft bottom
section. Include ‘‘Docket No. FAA– issued AD F–2005–124 (EASA approval panel, and the FR47/Rib 1 junction area.
2018–0497; Product Identifier 2017– 2005–6071) to require the same inspections Accomplishment of the proposed
NM–140–AD’’ at the beginning of your for A300 F4–608ST aeroplanes, in modification and initial inspections
accordance with Airbus SB A300–57–9001 would then terminate all of the
comments. We specifically invite
and SB A300–57–9002. requirements of AD 2014–20–18.
comments on the overall regulatory, Following the discovery of numerous
economic, environmental, and energy cracks during the accomplishment of SB Related Service Information Under 1
aspects of this NPRM. We will consider A300–57–6049 and SB A300–57–6089 CFR Part 51
all comments received by the closing inspections, Airbus developed in a first step
date and may amend this NPRM based a new (recommended) modification (Airbus Airbus has issued the following
on those comments. SB A300–57–6113) and defined, for post-mod service information.
We will post all comments we aeroplanes, new inspections, and published • Service Bulletin A300–57–6049,
receive, without change, to http:// SB A300–57–6119, which included new Revision 8, dated July 4, 2017. This
inspection methods (ultrasonic/radiographic) service information describes
www.regulations.gov, including any
with new inspection thresholds and procedures for HFEC rotating probe
personal information you provide. We intervals.
will also post a report summarizing each inspections for cracking of certain holes
Consequently, EASA issued AD 2016–
substantive verbal contact we receive 0198, retaining the requirements of EASA AD of the internal lower angle fitting web.
about this NPRM. 2012–0092, which was superseded, to require • Service Bulletin A300–57–6086,
repetitive inspections for post-SB A300–57– Revision 6, dated July 4, 2017. This
Discussion 6113 aeroplanes. service information describes
The European Aviation Safety Agency Since EASA AD 2016–0198 was issued, procedures for HFEC rotating probe
(EASA), which is the Technical Agent Airbus revised in a second step the inspections for cracking of certain holes
for the Member States of the European inspection programme for A300–600 pre-SB in the internal lower angle fitting
57–6113 and A300–600ST aeroplanes,
Union, has issued EASA AD 2017–0210, horizontal splicing (left-hand and right-
reducing inspection thresholds and intervals.
dated October 24, 2017 (referred to after At this opportunity, the existing ultrasonic hand sides) and for ultrasonic
this as the Mandatory Continuing inspection for A300–600 aeroplanes has been inspections for cracking of the aft
Airworthiness Information, or ‘‘the added for A300–600ST aeroplanes. bottom panel.
MCAI’’), to correct an unsafe condition For the reasons described above, this new • Service Bulletin A300–57–6119,
sradovich on DSK3GMQ082PROD with PROPOSALS
for certain Airbus Model A300 B4–603, [EASA] AD retains the requirements of EASA Revision 00, dated April 25, 2016. This
B4–620, and B4–622 airplanes; Model AD 2016–0198 for A300–600 aeroplanes and service information describes
A300 F4–605R airplanes; Model A300 of DGAC France AD F–2005–124 for A300– procedures for ultrasonic and
C4–605R Variant F airplanes; and Model 600ST aeroplanes, which are both
radiographic inspections for cracking of
superseded, and requires [modification
A300 B4–600R series airplanes. The the FR47/Rib 1 junction area.
through cold expansion of certain angle
MCAI states: fitting attachment holes and] repetitive This service information is reasonably
Prompted by cracks found on the Frame inspections [for cracking of certain holes of available because the interested parties
(FR) 47 angle fitting, Airbus issued SB the internal lower angle fitting web, certain have access to it through their normal
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![25592 Federal Register / Vol. 83, No. 107 / Monday, June 4, 2018 / Proposed Rules
course of business or by the means bilateral agreement with the State of develop on other products of the same
identified in the ADDRESSES section. Design Authority, we have been notified type design.
FAA’s Determination and Requirements of the unsafe condition described in the
Costs of Compliance
of This Proposed AD MCAI and service information
referenced above. We are proposing this We estimate that this proposed AD
This product has been approved by AD because we evaluated all pertinent
the aviation authority of another affects 65 airplanes of U.S. registry.
information and determined an unsafe
country, and is approved for operation We estimate the following costs to
condition exists and is likely to exist or
in the United States. Pursuant to our comply with this proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost Parts cost Cost per product Cost on U.S. operators
Up to 727 work-hours × $85 per hour = Up to $61,795 ....... Up to $3,370 ......... Up to $65,165 ....... Up to $4,235,725 per inspection cycle.
We estimate that it would take about General requirements.’’ Under that List of Subjects in 14 CFR Part 39
1 work-hour per product to comply with section, Congress charges the FAA with Air transportation, Aircraft, Aviation
the proposed reporting requirement in promoting safe flight of civil aircraft in safety, Incorporation by reference,
this proposed AD. The average labor air commerce by prescribing regulations Safety.
rate is $85 per hour. Based on these for practices, methods, and procedures
figures, we estimate the cost of reporting the Administrator finds necessary for The Proposed Amendment
the inspection results on U.S. operators safety in air commerce. This regulation Accordingly, under the authority
to be $5,525, or $85 per product. is within the scope of that authority delegated to me by the Administrator,
We have received no definitive data because it addresses an unsafe condition the FAA proposes to amend 14 CFR part
that would enable us to provide cost that is likely to exist or develop on 39 as follows:
estimates for the on-condition actions products identified in this rulemaking
specified in this AD. action. PART 39—AIRWORTHINESS
Paperwork Reduction Act This proposed AD is issued in DIRECTIVES
accordance with authority delegated by
A federal agency may not conduct or the Executive Director, Aircraft ■ 1. The authority citation for part 39
sponsor, and a person is not required to Certification Service, as authorized by continues to read as follows:
respond to, nor shall a person be subject FAA Order 8000.51C. In accordance Authority: 49 U.S.C. 106(g), 40113, 44701.
to penalty for failure to comply with a with that order, issuance of ADs is
collection of information subject to the normally a function of the Compliance § 39.13 [Amended]
requirements of the Paperwork and Airworthiness Division, but during ■ 2. The FAA amends § 39.13 by adding
Reduction Act unless that collection of this transition period, the Executive the following new airworthiness
information displays a current valid Director has delegated the authority to directive (AD):
OMB control number. The control issue ADs applicable to transport Airbus: Docket No. FAA–2018–0497; Product
number for the collection of information category airplanes to the Director of the Identifier 2017–NM–140–AD.
required by this NPRM is 2120–0056. System Oversight Division.
The paperwork cost associated with this (a) Comments Due Date
NPRM has been detailed in the Costs of Regulatory Findings We must receive comments by July 19,
Compliance section of this document We determined that this proposed AD 2018.
and includes time for reviewing would not have federalism implications (b) Affected ADs
instructions, as well as completing and under Executive Order 13132. This This AD affects AD 2014–20–18,
reviewing the collection of information. proposed AD would not have a Amendment 39–17991 (79 FR 65879,
Therefore, all reporting associated with substantial direct effect on the States, on November 6, 2014) (‘‘AD 2014–20–18’’).
this NPRM is mandatory. Comments the relationship between the national
concerning the accuracy of this burden (c) Applicability
Government and the States, or on the
and suggestions for reducing the burden distribution of power and This AD applies to Airbus Model A300 B4–
should be directed to the FAA at 800 603, A300 B4–620, A300 B4–622, A300 B4–
responsibilities among the various 605R, A300 B4–622R, A300 C4–605R Variant
Independence Ave. SW, Washington, levels of government.
DC 20591, ATTN: Information F, and A300 F4–605R airplanes, certificated
For the reasons discussed above, I in any category, all manufacturer serial
Collection Clearance Officer, AES–200. certify this proposed regulation: numbers, except airplanes on which Airbus
Authority for This Rulemaking 1. Is not a ‘‘significant regulatory Modification 12171 or 12249 has been
action’’ under Executive Order 12866; embodied in production, or on which Airbus
Title 49 of the United States Code Service Bulletin A300–57–6069 has been
specifies the FAA’s authority to issue 2. Is not a ‘‘significant rule’’ under the embodied in service.
rules on aviation safety. Subtitle I, DOT Regulatory Policies and Procedures
sradovich on DSK3GMQ082PROD with PROPOSALS
(44 FR 11034, February 26, 1979); (d) Subject
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII: 3. Will not affect intrastate aviation in Air Transport Association (ATA) of
Aviation Programs,’’ describes in more Alaska; and America Code 57, Wings.
detail the scope of the Agency’s 4. Will not have a significant (e) Reason
authority. economic impact, positive or negative, This AD was prompted by reports of
We are issuing this rulemaking under on a substantial number of small entities cracking on the frame (FR) 47 angle fitting.
the authority described in ‘‘Subtitle VII, under the criteria of the Regulatory We are issuing this AD to detect and correct
Part A, Subpart III, Section 44701: Flexibility Act. cracking of FR47 angle fitting, which could
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![Federal Register / Vol. 83, No. 107 / Monday, June 4, 2018 / Proposed Rules 25595
airplane serial number, and the number of Washington, DC 20591, Attn: Information Airbus Model A330–200 Freighter series
flight cycles and flight hours on the airplane. Collection Clearance Officer, AES–200. airplanes; Airbus Model A330–200
(1) If the inspection was done on or after (4) Required for Compliance (RC): Except series airplanes; and Airbus Model
the effective date of this AD: Submit the as required by paragraph (m) of this AD: If
any service information contains procedures
A330–300 series airplanes. This
report within 30 days after the inspection.
(2) If the inspection was done before the or tests that are identified as RC, those proposed AD was prompted by reports
effective date of this AD: Submit the report procedures and tests must be done to comply of Angle of Attack (AOA) blockages not
within 30 days after the effective date of this with this AD; any procedures or tests that are detected by upgraded flight control
AD. not identified as RC are recommended. Those primary computer (FCPC) software
procedures and tests that are not identified standards. This proposed AD would
(o) Terminating Action for AD 2014–20–18 as RC may be deviated from using accepted require upgrading certain FCPCs, which
Accomplishment of the action required by methods in accordance with the operator’s would terminate a certain airplane flight
paragraph (h) of this AD and the initial maintenance or inspection program without
inspections required by paragraphs (i) and (j), obtaining approval of an AMOC, provided
manual revision for certain airplanes.
and (k) of this AD terminates all the procedures and tests identified as RC can We are proposing this AD to address the
requirements of AD 2014–20–18. be done and the airplane can be put back in unsafe condition on these products.
an airworthy condition. Any substitutions or DATES: We must receive comments on
(p) Credit for Previous Actions changes to procedures or tests identified as this proposed AD by July 19, 2018.
This paragraph provides credit for actions RC require approval of an AMOC. ADDRESSES: You may send comments,
specified in paragraph (h) of this AD, if those
actions were performed before December 19, (r) Related Information using the procedures found in 14 CFR
2005 (the effective date of AD 2005–23–08), (1) Refer to Mandatory Continuing 11.43 and 11.45, by any of the following
using Airbus Service Bulletin A300–57–6050, Airworthiness Information (MCAI) EASA AD methods:
Revision 02, dated February 10, 2000. 2017–0210, dated October 24, 2017, for • Federal eRulemaking Portal: Go to
related information. This MCAI may be http://www.regulations.gov. Follow the
(q) Other FAA AD Provisions found in the AD docket on the internet at instructions for submitting comments.
The following provisions also apply to this http://www.regulations.gov by searching for • Fax: 202–493–2251.
AD: and locating Docket No. FAA–2018–0497. • Mail: U.S. Department of
(1) Alternative Methods of Compliance (2) For more information about this AD, Transportation, Docket Operations, M–
(AMOCs): The Manager, International contact Dan Rodina, Aerospace Engineer,
International Section, Transport Standards
30, West Building Ground Floor, Room
Section, Transport Standards Branch, FAA,
has the authority to approve AMOCs for this Branch, FAA, 2200 South 216th St., Des W12–140, 1200 New Jersey Avenue SE,
AD, if requested using the procedures found Moines, WA 98198; telephone and fax 206– Washington, DC 20590.
in 14 CFR 39.19. In accordance with 14 CFR 231–3225. • Hand Delivery: Deliver to Mail
39.19, send your request to your principal (3) For service information identified in address above between 9 a.m. and 5
inspector or local Flight Standards District this AD, contact Airbus SAS, Airworthiness p.m., Monday through Friday, except
Office, as appropriate. If sending information Office—EAW, 1 Rond Point Maurice Federal holidays.
directly to the International Section, send it Bellonte, 31707 Blagnac Cedex, France; For service information identified in
to the attention of the person identified in telephone +33 5 61 93 36 96; fax +33 5 61 this NPRM, contact Airbus SAS,
paragraph (r)(2) of this AD. Information may 93 44 51; email account.airworth-eas@
airbus.com; internet http://www.airbus.com.
Airworthiness Office—EAL, 1 Rond
be emailed to: 9-ANM-116-AMOC-
You may view this service information at the Point Maurice Bellonte, 31707 Blagnac
REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate FAA, Transport Standards Branch, 2200 Cedex, France; telephone +33 5 61 93 36
principal inspector, or lacking a principal South 216th St., Des Moines, WA. For 96; fax +33 5 61 93 45 80; email
inspector, the manager of the local flight information on the availability of this airworthiness.A330-A340@airbus.com;
standards district office/certificate holding material at the FAA, call 206–231–3195. internet http://www.airbus.com. You
district office. Issued in Des Moines, Washington, on May may view this service information at the
(2) Contacting the Manufacturer: For any 23, 2018. FAA, Transport Standards Branch, 2200
requirement in this AD to obtain corrective James Cashdollar, South 216th St., Des Moines, WA. For
actions from a manufacturer, the action must information on the availability of this
be accomplished using a method approved Acting Director, System Oversight Division,
Aircraft Certification Service. material at the FAA, call 206–231–3195.
by the Manager, International Section,
Transport Standards Branch, FAA; or EASA; [FR Doc. 2018–11822 Filed 6–1–18; 8:45 am] Examining the AD Docket
or Airbus’s EASA DOA. If approved by the BILLING CODE 4910–13–P
DOA, the approval must include the DOA- You may examine the AD docket on
authorized signature. the Internet at http://
(3) Paperwork Reduction Act Burden DEPARTMENT OF TRANSPORTATION www.regulations.gov by searching for
Statement: A federal agency may not conduct and locating Docket No. FAA–2018–
or sponsor, and a person is not required to Federal Aviation Administration 0498; or in person at the Docket
respond to, nor shall a person be subject to Management Facility between 9 a.m.
a penalty for failure to comply with a and 5 p.m., Monday through Friday,
collection of information subject to the
14 CFR Part 39
except Federal holidays. The AD docket
requirements of the Paperwork Reduction [Docket No. FAA–2018–0498; Product
Act unless that collection of information
contains this NPRM, the regulatory
Identifier 2018–NM–013–AD]
displays a current valid OMB Control evaluation, any comments received, and
Number. The OMB Control Number for this RIN 2120–AA64 other information. The street address for
information collection is 2120–0056. Public the Docket Operations office (telephone
reporting for this collection of information is Airworthiness Directives; Airbus 800–647–5527) is in the ADDRESSES
sradovich on DSK3GMQ082PROD with PROPOSALS
estimated to be approximately 1 work-hour Airplanes section. Comments will be available in
per response, including the time for the AD docket shortly after receipt.
reviewing instructions, completing and AGENCY: Federal Aviation
Administration (FAA), DOT. FOR FURTHER INFORMATION CONTACT:
reviewing the collection of information. All
responses to this collection of information ACTION: Notice of proposed rulemaking Vladimir Ulyanov, Aerospace Engineer,
are mandatory. Comments concerning the (NPRM). International Section, Transport
accuracy of this burden and suggestions for Standards Branch, FAA, 2200 South
reducing the burden should be directed to SUMMARY: We propose to adopt a new 216th St., Des Moines, WA 98198;
the FAA at: 800 Independence Ave. SW, airworthiness directive (AD) for certain telephone and fax 206–231–3229.
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Document Created: 2018-06-02 00:47:50
Document Modified: 2018-06-02 00:47:50
| 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 July 19, 2018. | |
| Contact | Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3225. | |
| FR Citation | 83 FR 25590 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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