82 FR 46729 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 193 (October 6, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 193 (October 6, 2017)
| Page Range | 46729-46738 | |
| FR Document | 2017-21221 |
[Federal Register Volume 82, Number 193 (Friday, October 6, 2017)] [Proposed Rules] [Pages 46729-46738] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-21221] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0902; Product Identifier 2016-NM-188-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2004-03- 07, which applies to certain Airbus Model A320-111, -211, -212, and - 231 series airplanes. AD 2004-03-07 requires repetitive inspections for fatigue cracking around the fasteners attaching the pressure panel to the flexible bracket at frame (FR) 36, adjacent to the longitudinal beams on the left and right sides of the airplane; and repair as necessary. Since we issued AD 2004-03-07, additional cracking has been found under the longitudinal beams in locations outside of the inspection areas required by AD 2004-03-07. This proposed AD would retain certain requirements of AD 2004-03-07, expand the applicability, and require an inspection of the fastener holes on the pressure panel between FR 35 and FR 36 under the longitudinal beam and modification or repair as applicable. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by November 20, 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. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 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- 0902; 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 Section, Transport Standards Branch, 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-2017-0902; Product Identifier 2016-NM-188-AD at the beginning of your comments. We specifically invite comments on the overall regulatory, [[Page 46730]] 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 On January 29, 2004, we issued AD 2004-03-07, Amendment 39-13451 (69 FR 5907, February 9, 2004) (``AD 2004-03-07''), for certain Airbus Model A320-111, -211, -212, and -231 series airplanes. AD 2004-03-07 was prompted by fatigue tests which revealed cracking around the fasteners attaching the pressure panel to the flexible bracket at FR 36, adjacent to the longitudinal beams on the left and right sides of the airplane. Investigation revealed that the damage was caused by high loads in this area. AD 2004-03-07 requires repetitive inspections for fatigue cracking around the fasteners attaching the pressure panel to the flexible bracket at FR 36, adjacent to the longitudinal beams on the left and right sides of the airplane; and repair as necessary. AD 2004-03-07 also provides an optional terminating action for the repetitive inspections. We issued AD 2004-03-07 to detect and correct fatigue cracking around the fasteners attaching the pressure panel to the flexible bracket at the FR 36 adjacent to the longitudinal beams, which could result in reduced structural integrity and possible rapid decompression of the airplane. Since we issued AD 2004-03-07, additional cracks have been found under the longitudinal beams at locations that are not included in the inspection area required by AD 2004-03-07. Fatigue and damage tolerance analyses were performed and the results indicated that all the holes in the pressure panel above the longitudinal beams have to be cold worked. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2016-0206, dated October 13, 2016; corrected October 14, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A318 and Model A319 series airplanes, Model A320-211, -212, -214, -231, -232, and -233 airplanes, and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The MCAI states: During fatigue tests, cracks were found around the fasteners connecting the pressure panel with the flexible bracket at fuselage frame (FR) 36, adjacent to the longitudinal beams on left-hand (LH) and right-hand (RH) sides. This condition, if not detected and corrected, could impair the structural integrity of the aeroplane. To address this unsafe condition, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued [French] AD 2000-531-155(B) [which corresponds with FAA AD 2004-03-07] to require repetitive inspections of the longitudinal beams of the FR 36 pressure panel and, depending on findings, the accomplishment of a repair. Since that [French] AD was issued, additional cracks have been found under the beams, but in locations not covered by the required inspections. Fatigue and damage tolerance analyses were performed, the results of which indicated that all the holes in the pressure panel above all the longitudinal beams have to be cold worked. For the reasons described above, this [EASA] AD retains the requirements of DGAC France AD 2000-531-155(B), which is superseded, extends the applicability to all A320 family aeroplanes and requires [a special detailed inspection of the fastener holes on the pressure panel between FR35 and FR36 under the longitudinal beam and] modification [or repair] of all the affected holes. This [EASA] AD is republished to correct the number of the superseded DGAC 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- 0902. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320-53-1264, Revision 01, dated July 4, 2016. The service information describes procedures for a special detailed inspection (rotating probe) for cracking of the fastener holes on the pressure panel between FR 35 and FR 36 under the longitudinal beam and repair of any crack. Airbus has also issued Service Bulletin A320-53-1240, Revision 01, dated April 4, 2016, which describes procedures for modifying the pressure panel above the left and right longitudinal beams, including related investigative action (e.g., high frequency eddy current (rototest) inspection of all the removed fastener holes) and corrective actions (e.g., repair), by cold working the attachment holes under the longitudinal beam at FR 36 for airplanes on which no cracking was found. In addition, Airbus issued Service Bulletin A320-53-1263, Revision 01, dated February 29, 2016, which describes procedures for modifying the pressure panel above the left and right longitudinal beams, including related investigative actions (e.g., eddy current rotating probe inspection of the fastener holes) and corrective actions (e.g., repair), by adding a doubler and a filler, and cold expansion of the holes under the longitudinal beam at FR 36 for airplanes on which cracking was found. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Differences Between This Proposed AD and the MCAI or Service Information The MCAI specifies that operators can calculate revised thresholds for Model A319 and A320 series airplanes with sharklets installed (Airbus Service Bulletin A320-57-1193). This proposed AD does not include those calculations because the calculations could result in different inspection thresholds for each individual airplane. However, under the provisions of paragraph (o)(1) of this AD, we will consider requests for approval of alternative compliance times. Costs of Compliance We estimate that this proposed AD affects 737 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: [[Page 46731]] Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection [Retained from AD Up to 2 work-hours x $0 Up to $170 per Up to $125,290 per 2004-03-07]. $85 per hour = $170 inspection cycle. inspection cycle. per inspection cycle. Inspection [new proposed 13 work-hours x $85 per 0 $1,105............ $814,385. requirement]. hour = $1,105. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary modifications 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 these modifications: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Modification....................... Up to 213 work-hours x $85 Up to $8,510.......... Up to $26,615. per hour = $18,105. Reporting.......................... 1 work-hour x $85 per hour $0.................... $85. = $85. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide a cost estimate for the on-condition repairs specified in the service information. 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 removing Airworthiness Directive (AD) 2004-03-07, Amendment 39-13451 (69 FR 5907, February 9, 2004), and adding the following new AD: Airbus: Docket No. FAA-2017-0902; Product Identifier 2016-NM-188-AD. (a) Comments Due Date We must receive comments by November 20, 2017. (b) Affected ADs This AD replaces AD 2004-03-07, Amendment 39-13451 (69 FR 5907, February 9, 2004) (``AD 2004-03-07''). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, except for airplanes on which Airbus Modification 151574 was embodied in production. (1) Model A318-111, -112, -121, and -122 airplanes. (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes. [[Page 46732]] (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by fatigue tests which revealed cracking around the fasteners attaching the pressure panel to the flexible bracket at frame (FR) 36, adjacent to the longitudinal beams on the left and right sides of the airplane. We are issuing this AD to detect and correct fatigue cracking around the fasteners attaching the pressure panel to the flexible bracket at the FR 36 adjacent to the longitudinal beams, which could result in reduced structural integrity of the airplane and possible rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection and Follow-On Actions, With No Changes This paragraph restates the requirements of paragraphs (a) and (b) of AD 2004-03-07, with no changes. (1) For Model A320-211, -212, and -231 series airplanes having serial numbers 0002 through 0107 inclusive, except those airplanes on which Airbus Modification 21202/K1432 has been incorporated in production, or on which Airbus Service Bulletin A320-53-1029, Revision 01, dated April 29, 2002, has been incorporated: Prior to the accumulation of 30,000 total flight cycles, do a rotating probe inspection on airplanes with a center fuel tank, or a detailed inspection on airplanes without a center fuel tank, to detect cracking around the fasteners that attach the pressure panel to the flexible bracket at FR 36, adjacent to the longitudinal beams on the left and right sides of the airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1030, Revision 01, dated May 21, 2002. (2) If no crack is detected by the inspection required by paragraph (g)(1) of this AD, repeat the applicable inspection thereafter at intervals not to exceed 6,000 flight cycles for airplanes without a center fuel tank, and at intervals not to exceed 18,000 flight cycles for airplanes with a center fuel tank. (h) Retained Corrective Actions, With Specific Delegation Approval Language This paragraph restates the requirements of paragraphs (c) and (d) of AD 2004-03-07, with specific delegation approval language. (1) If any crack is detected during any inspection required by paragraph (g)(1) of this AD, before further flight, repair the affected structure by accomplishing all applicable actions in accordance with paragraphs 3.B. through 3.E. of the Accomplishment Instructions of Airbus Service Bulletin A320-53-1030, Revision 01, dated May 21, 2002. Repeat the applicable inspection thereafter at intervals not to exceed 6,000 flight cycles for airplanes without a center fuel tank, and at intervals not to exceed 18,000 flight cycles for airplanes with a center fuel tank. For any area where cracking is repaired, the repair constitutes terminating action for the repetitive inspection of that area. Note 1 to paragraph (h)(1) of this AD: Airbus Service Bulletin A320-53-1030 references Airbus Service Bulletin A320-53-1029, Revision 01, dated April 29, 2002, as an additional source of service information for certain repairs. (2) If Airbus Service Bulletin A320-53-1030, Revision 01, dated May 21, 2002, specifies to contact the manufacturer for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o)(2) of this AD. (i) Retained Optional Terminating Action for Paragraphs (g) and (h) of This AD, With Revised Compliance Language This paragraph restates the requirements of paragraph (e) of AD 2004-03-07, with revised compliance language. For Model A320-211, - 212, and -231 series airplanes having serial numbers 0002 through 0107 inclusive, except those airplanes on which Airbus Modification 21202/K1432 has been incorporated in production, or Airbus Service Bulletin A320-53-1029, Revision 01, dated April 29, 2002: Modification, before the effective date of this AD, of the structure around the fasteners that attach the pressure panel to the flexible bracket at FR 36, adjacent to the longitudinal beams on the left and right sides of the airplane, by accomplishing all applicable actions in accordance with paragraphs 3.A. through 3.E. of the Accomplishment Instructions of Airbus Service Bulletin A320-53-1029, Revision 01, dated April 29, 2002, constitutes terminating action for the actions required by paragraphs (g) and (h) of this AD. (j) New Requirement of This AD: Inspection For all airplanes, except for airplanes identified in paragraph (l) of this AD: At the applicable time specified in table 1 to paragraph (j) of this AD, do a special detailed inspection for cracking of the fastener holes on the pressure panel between FR 35 and FR 36 under the longitudinal beam, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1264, Revision 01, dated July 4, 2016. BILLING CODE 4910-13-P [[Page 46733]] [GRAPHIC] [TIFF OMITTED] TP06OC17.000 [[Page 46734]] [GRAPHIC] [TIFF OMITTED] TP06OC17.001 [[Page 46735]] [GRAPHIC] [TIFF OMITTED] TP06OC17.002 [[Page 46736]] [GRAPHIC] [TIFF OMITTED] TP06OC17.003 BILLING CODE 4910-13-C [[Page 46737]] (k) On-Condition Actions (1) If, during any inspection required by paragraph (j) of this AD, no cracking is found, or cracking is found that is within the limits specified in Airbus Service Bulletin A320-53-1264, Revision 01, dated July 4, 2016: Before further flight, modify the pressure panel above the left and right longitudinal beams, including doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1240, Revision 01, dated April 4, 2016; or Service Bulletin A320-53-1263, Revision 01, dated February 29, 2016; as applicable. Do all related investigative and corrective actions before further flight. Where Airbus Service Bulletin A320-53-1240, Revision 01, dated April 4, 2016; and Service Bulletin A320-53-1263, Revision 01, dated February 29, 2016; specify to contact Airbus for appropriate action: Before further flight, accomplish the repair in accordance with the procedures specified in paragraph (o)(2) of this AD. (2) If, during any inspection required by paragraph (j) of this AD, any cracking is found that exceeds the limits specified in Airbus Service Bulletin A320-53-1264, Revision 01, dated July 4, 2016: Do the actions specified in, and at the compliance times specified in, paragraphs (k)(2)(i) and (k)(2)(ii) of this AD. (i) Before further flight, repair any cracking in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1264, Revision 01, dated July 4, 2016. Where Airbus Service Bulletin A320-53-1264, Revision 01, dated July 4, 2016, specifies to contact Airbus for appropriate action, and specifies that action as ``RC'' (Required for Compliance): Before further flight, request approval of repair instructions using a method approved in accordance with the procedures specified in paragraph (o)(2) of this AD, and accomplish the repair accordingly within the compliance time specified in those instructions. If no compliance time is defined in the repair instructions, accomplish the repair before further flight. (ii) At the times specified in paragraph (k)(2)(ii)(A) or (k)(2)(ii)(B) of this AD, as applicable: Report any findings of cracking that exceeds the limits specified in Airbus Service Bulletin A320-53-1264, Revision 01, dated July 4, 2016, to Airbus Customer Services through TechRequest on Airbus World (https://w3.airbus.com/) by selecting Engineering Domain and ATA 57-10. (A) If the inspection was done on or after the effective date of this AD: Report within 90 days after that inspection. (B) If the inspection was done before the effective date of this AD: Report within 90 days after the effective date of this AD. (l) Actions for Certain Airplanes For Model A319 and Model A320 series airplanes on which the actions specified in Airbus Service Bulletin A320-57-1193 have been embodied and the airplane has accumulated 33,000 flight cycles or 66,000 flight hours or more since the airplane's first flight on the effective date of this AD: Within 30 days after the effective date of this AD, contact the Manager, International Section, Transport Standards Branch FAA; or the EASA; or Airbus's EASA DOA for approved repair instructions and within the compliance time specified in those instructions, accomplish the repair accordingly. If no compliance time is defined in the repair instructions, accomplish the repair before the next flight. (m) Terminating Action for Repetitive Inspections Required by Paragraph (g)(2) of This AD (1) Modification of an airplane as specified in paragraph (m)(1)(i), (m)(1)(ii), or (m)(1)(iii) of this AD constitutes terminating action for the repetitive inspection required by paragraph (g)(2) of this AD for that airplane only. (i) Modification of an airplane as required by paragraph (k)(1) of this AD. (ii) Modification of an airplane prior to the effective date of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1240, dated March 19, 2015; or Airbus Service Bulletin A320-53-1263, dated March 19, 2015; as applicable. (iii) Modification of an airplane using instructions obtained in accordance with the procedures specified in paragraph (o)(2) of this AD. (2) Repair of an airplane as required by paragraph (k)(2) of this AD constitutes terminating action for the repetitive inspections required by paragraph (g)(2) of this AD for that airplane, unless specified otherwise in the repair instructions approved by the Manager, International Section, Transport Standards Branch, FAA; or the EASA; or Airbus's EASA DOA. (n) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraphs (g) and (h)(1) of this AD, if those actions were performed before March 15, 2004 (the effective date of AD 2004-03- 07) using Airbus Service Bulletin A320-53-1030, dated January 5, 2000; or Airbus Service Bulletin A320-53-1029, dated January 5, 2000. (2) This paragraph provides credit for actions required by paragraph (j) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-53- 1264, dated March 19, 2015. (3) This paragraph provides credit for actions required by paragraph (k)(1) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-53- 1240, dated March 19, 2015; or Airbus Service Bulletin A320-53-1263, dated March 19, 2015; for that airplane only. (o) 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 Branch, send it to the attention of the person identified paragraph (p)(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: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (k)(2)(i) 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. (4) Reporting Requirements: 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 5 minutes 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. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016-0206, dated October 13, 2016; corrected October 14, 2016; for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0902. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., [[Page 46738]] 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 Standards Branch, 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 September 21, 2017. Dionne Palermo, Acting Director, System Oversight Branch, Aircraft Certification Service. [FR Doc. 2017-21221 Filed 10-5-17; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 82, No. 193 / Friday, October 6, 2017 / Proposed Rules 46729
more effective method than Modification TU 2017, for more information. You may ADDRESSES: You may send comments,
147 to reduce the risk of uncoupling between examine the MCAI in the AD docket on the using the procedures found in 14 CFR
the low-pressure (LP) fuel pump impeller Internet at http://www.regulations.gov by 11.43 and 11.45, by any of the following
and the high-pressure (HP) fuel pump shaft searching for and locating it in Docket No.
methods:
of the HP/LP pump and hydro-mechanical FAA–2009–0889.
metering unit (HMU). We are issuing this AD (3) For service information identified in • Federal eRulemaking Portal: Go to
to prevent failure of the HMU. The unsafe this AD, contact Safran Helicopter Engines, http://www.regulations.gov. Follow the
condition, if not corrected, could result in S.A., 40220 Tarnos, France; phone: (33) 05 59 instructions for submitting comments.
failure of the engine, in-flight shutdown, and 74 40 00; fax: (33) 05 59 74 45 15. You may • Fax: 202–493–2251.
loss of the helicopter. view this referenced service information at • Mail: U.S. Department of
the FAA, Engine and Propeller Standards Transportation, Docket Operations, M–
(f) Compliance
Branch, 1200 District Avenue, Burlington, 30, West Building Ground Floor, Room
Comply with this AD within the MA 01803. For information on the
compliance times specified, unless already W12–140, 1200 New Jersey Avenue SE.,
availability of this material at the FAA, call
done. Washington, DC 20590.
781–238–7125.
(1) Check the transmissible torque between • Hand Delivery: Deliver to Mail
the LP fuel pump impeller and the HP fuel Issued in Burlington, Massachusetts, on address above between 9 a.m. and 5
pump shaft as follows: September 29, 2017. p.m., Monday through Friday, except
(i) For pre-Modification TU 147 HMUs, Robert J. Ganley, Federal holidays.
check the torque before accumulating 500 Manager, Engine and Propeller Standards For service information identified in
engine flight hours (FHs) since March 11, Branch, Aircraft Certification Service. this NPRM, contact Airbus,
2010 or before the next flight, whichever
occurs later. Use Paragraph 2 of Turbomeca
[FR Doc. 2017–21344 Filed 10–5–17; 8:45 am] Airworthiness Office—EIAS, 1 Rond
Alert Mandatory Service Bulletin (MSB) BILLING CODE 4910–13–P Point Maurice Bellonte, 31707 Blagnac
A292 73 2830, Version B, dated July 10, 2009 Cedex, France; telephone +33 5 61 93 36
to do the check. 96; fax +33 5 61 93 44 51; email
(ii) For HMUs that incorporated DEPARTMENT OF TRANSPORTATION account.airworth-eas@airbus.com;
Modification TU 147 on or before March 31, Internet http://www.airbus.com. You
2010, and those HMUs not listed in Figures Federal Aviation Administration may view this referenced service
2 or 3 of Turbomeca Alert MSB A292 73 information at the FAA, Transport
2836, Version A, dated August 17, 2010, 14 CFR Part 39
check the torque before the next flight. Use Standards Branch, 1601 Lind Avenue
Paragraph 2 of Turbomeca Alert MSB A292 [Docket No. FAA–2017–0902; Product SW., Renton, WA. For information on
73 2836, Version A, to do the check. Identifier 2016–NM–188–AD] the availability of this material at the
(2) If the HMU does not pass the torque FAA, call 425–227–1221.
check, replace the HMU with a post- RIN 2120–AA64
Modification TU 178 HMU before the next Examining the AD Docket
flight. Airworthiness Directives; Airbus You may examine the AD docket on
Airplanes the Internet at http://
(g) Mandatory Terminating Action
Within 2,200 engine FHs or 72 months AGENCY: Federal Aviation www.regulations.gov by searching for
after the effective date of this AD, whichever Administration (FAA), DOT. and locating Docket No. FAA–2017–
occurs first, replace any pre-Modification TU ACTION: Notice of proposed rulemaking
0902; or in person at the Docket
178 HMU with a post-Modification TU 178 (NPRM). Management Facility between 9 a.m.
configuration HMU. and 5 p.m., Monday through Friday,
(h) Installation Prohibition SUMMARY: We propose to supersede except Federal holidays. The AD docket
Airworthiness Directive (AD) 2004–03– contains this proposed AD, the
After the effective date of this AD, do not
install a pre-Modification TU 178 HMU on 07, which applies to certain Airbus regulatory evaluation, any comments
engines incorporating a post-Modification TU Model A320–111, –211, –212, and –231 received, and other information. The
178 HMU. series airplanes. AD 2004–03–07 street address for the Docket Operations
requires repetitive inspections for office (telephone 800–647–5527) is in
(i) Alternative Methods of Compliance the ADDRESSES section. Comments will
(AMOCs)
fatigue cracking around the fasteners
attaching the pressure panel to the be available in the AD docket shortly
(1) The Manager, ECO Branch, FAA, may after receipt.
flexible bracket at frame (FR) 36,
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. adjacent to the longitudinal beams on FOR FURTHER INFORMATION CONTACT:
In accordance with 14 CFR 39.19, send your the left and right sides of the airplane; Sanjay Ralhan, Aerospace Engineer,
request to your principal inspector or local and repair as necessary. Since we issued International Section, Transport
Flight Standards District Office, as AD 2004–03–07, additional cracking has Standards Branch, FAA, 1601 Lind
appropriate. You may email your request to: been found under the longitudinal Avenue SW., Renton, WA 98057–3356;
ANE-AD-AMOC@faa.gov. beams in locations outside of the telephone 425–227–1405; fax 425–227–
(2) Before using any approved AMOC, inspection areas required by AD 2004– 1149.
notify your appropriate principal inspector,
03–07. This proposed AD would retain SUPPLEMENTARY INFORMATION:
or lacking a principal inspector, the manager
of the local flight standards district office/ certain requirements of AD 2004–03–07,
expand the applicability, and require an Comments Invited
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
certificate holding district office.
inspection of the fastener holes on the We invite you to send any written
(j) Related Information pressure panel between FR 35 and FR relevant data, views, or arguments about
(1) For more information about this AD, 36 under the longitudinal beam and this proposal. Send your comments to
contact Robert Green, Aerospace Engineer, modification or repair as applicable. We an address listed under the ADDRESSES
ECO Branch, FAA, 1200 District Avenue, are proposing this AD to address the
Burlington, MA 01803; phone: 781–238– section. Include ‘‘Docket No. FAA–
unsafe condition on these products. 2017–0902; Product Identifier 2016–
7754; fax: 781–238–7199; email:
robert.green@faa.gov. DATES: We must receive comments on NM–188–AD at the beginning of your
(2) Refer to MCAI European Aviation this proposed AD by November 20, comments. We specifically invite
Safety Agency AD 2017–0102, dated June 13, 2017. comments on the overall regulatory,
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![46730 Federal Register / Vol. 82, No. 193 / Friday, October 6, 2017 / Proposed Rules
economic, environmental, and energy condition for certain Airbus Model investigative action (e.g., high frequency
aspects of this proposed AD. We will A318 and Model A319 series airplanes, eddy current (rototest) inspection of all
consider all comments received by the Model A320–211, –212, –214, –231, the removed fastener holes) and
closing date and may amend this –232, and –233 airplanes, and Model corrective actions (e.g., repair), by cold
proposed AD based on those comments. A321–111, –112, –131, –211, –212, working the attachment holes under the
We will post all comments we –213, –231, and –232 airplanes. The longitudinal beam at FR 36 for airplanes
receive, without change, to http:// MCAI states: on which no cracking was found.
www.regulations.gov, including any During fatigue tests, cracks were found In addition, Airbus issued Service
personal information you provide. We around the fasteners connecting the pressure Bulletin A320–53–1263, Revision 01,
will also post a report summarizing each panel with the flexible bracket at fuselage dated February 29, 2016, which
substantive verbal contact we receive frame (FR) 36, adjacent to the longitudinal describes procedures for modifying the
about this proposed AD. beams on left-hand (LH) and right-hand (RH) pressure panel above the left and right
sides. longitudinal beams, including related
Discussion This condition, if not detected and investigative actions (e.g., eddy current
On January 29, 2004, we issued AD corrected, could impair the structural
rotating probe inspection of the fastener
2004–03–07, Amendment 39–13451 (69 integrity of the aeroplane.
To address this unsafe condition, DGAC holes) and corrective actions (e.g.,
FR 5907, February 9, 2004) (‘‘AD 2004– [Direction Générale de l’Aviation Civile] repair), by adding a doubler and a filler,
03–07’’), for certain Airbus Model France issued [French] AD 2000–531–155(B) and cold expansion of the holes under
A320–111, –211, –212, and –231 series [which corresponds with FAA AD 2004–03– the longitudinal beam at FR 36 for
airplanes. AD 2004–03–07 was 07] to require repetitive inspections of the airplanes on which cracking was found.
prompted by fatigue tests which longitudinal beams of the FR 36 pressure This service information is reasonably
revealed cracking around the fasteners panel and, depending on findings, the available because the interested parties
attaching the pressure panel to the accomplishment of a repair. have access to it through their normal
flexible bracket at FR 36, adjacent to the Since that [French] AD was issued,
additional cracks have been found under the
course of business or by the means
longitudinal beams on the left and right identified in the ADDRESSES section.
beams, but in locations not covered by the
sides of the airplane. Investigation required inspections. Fatigue and damage
revealed that the damage was caused by FAA’s Determination and Requirements
tolerance analyses were performed, the of This Proposed AD
high loads in this area. AD 2004–03–07 results of which indicated that all the holes
requires repetitive inspections for in the pressure panel above all the This product has been approved by
fatigue cracking around the fasteners longitudinal beams have to be cold worked. the aviation authority of another
attaching the pressure panel to the For the reasons described above, this country, and is approved for operation
flexible bracket at FR 36, adjacent to the [EASA] AD retains the requirements of DGAC in the United States. Pursuant to our
longitudinal beams on the left and right France AD 2000–531–155(B), which is bilateral agreement with the State of
sides of the airplane; and repair as superseded, extends the applicability to all
A320 family aeroplanes and requires [a
Design Authority, we have been notified
necessary. AD 2004–03–07 also special detailed inspection of the fastener of the unsafe condition described in the
provides an optional terminating action holes on the pressure panel between FR35 MCAI and service information
for the repetitive inspections. We issued and FR36 under the longitudinal beam and] referenced above. We are proposing this
AD 2004–03–07 to detect and correct modification [or repair] of all the affected AD because we evaluated all pertinent
fatigue cracking around the fasteners holes. information and determined an unsafe
attaching the pressure panel to the This [EASA] AD is republished to correct condition exists and is likely to exist or
flexible bracket at the FR 36 adjacent to the number of the superseded DGAC AD. develop on other products of these same
the longitudinal beams, which could You may examine the MCAI in the type designs.
result in reduced structural integrity AD docket on the Internet at http://
and possible rapid decompression of the Differences Between This Proposed AD
www.regulations.gov by searching for and the MCAI or Service Information
airplane. and locating Docket No. FAA–2017–
Since we issued AD 2004–03–07, 0902. The MCAI specifies that operators can
additional cracks have been found calculate revised thresholds for Model
under the longitudinal beams at Related Service Information Under 1 A319 and A320 series airplanes with
locations that are not included in the CFR Part 51 sharklets installed (Airbus Service
inspection area required by AD 2004– Airbus has issued Service Bulletin Bulletin A320–57–1193). This proposed
03–07. Fatigue and damage tolerance A320–53–1264, Revision 01, dated July AD does not include those calculations
analyses were performed and the results 4, 2016. The service information because the calculations could result in
indicated that all the holes in the describes procedures for a special different inspection thresholds for each
pressure panel above the longitudinal detailed inspection (rotating probe) for individual airplane. However, under the
beams have to be cold worked. cracking of the fastener holes on the provisions of paragraph (o)(1) of this
The European Aviation Safety Agency pressure panel between FR 35 and FR AD, we will consider requests for
(EASA), which is the Technical Agent 36 under the longitudinal beam and approval of alternative compliance
for the Member States of the European repair of any crack. times.
Union, has issued EASA Airworthiness Airbus has also issued Service
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
Directive 2016–0206, dated October 13, Bulletin A320–53–1240, Revision 01, Costs of Compliance
2016; corrected October 14, 2016 dated April 4, 2016, which describes We estimate that this proposed AD
(referred to after this as the Mandatory procedures for modifying the pressure affects 737 airplanes of U.S. registry.
Continuing Airworthiness Information, panel above the left and right We estimate the following costs to
or ‘‘the MCAI’’), to correct an unsafe longitudinal beams, including related comply with this proposed AD:
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![Federal Register / Vol. 82, No. 193 / Friday, October 6, 2017 / Proposed Rules 46731
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Inspection [Retained Up to 2 work-hours × $85 per hour = $170 per $0 Up to $170 per inspec- Up to $125,290 per in-
from AD 2004–03–07]. inspection cycle. tion cycle. spection cycle.
Inspection [new pro- 13 work-hours × $85 per hour = $1,105 ............ 0 $1,105 .......................... $814,385.
posed requirement].
We estimate the following costs to do be required based on the results of the determining the number of aircraft that
any necessary modifications that would proposed inspection. We have no way of might need these modifications:
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Modification .......................... Up to 213 work-hours × $85 per hour = $18,105 ......... Up to $8,510 ...................... Up to $26,615.
Reporting ............................. 1 work-hour × $85 per hour = $85 ................................ $0 ....................................... $85.
We have received no definitive data air commerce by prescribing regulations List of Subjects in 14 CFR Part 39
that would enable us to provide a cost for practices, methods, and procedures
Air transportation, Aircraft, Aviation
estimate for the on-condition repairs the Administrator finds necessary for
safety, Incorporation by reference,
specified in the service information. safety in air commerce. This regulation
is within the scope of that authority Safety.
Paperwork Reduction Act because it addresses an unsafe condition The Proposed Amendment
A federal agency may not conduct or that is likely to exist or develop on
products identified in this rulemaking Accordingly, under the authority
sponsor, and a person is not required to
action. delegated to me by the Administrator,
respond to, nor shall a person be subject
This proposed AD is issued in the FAA proposes to amend 14 CFR part
to penalty for failure to comply with a
accordance with authority delegated by 39 as follows:
collection of information subject to the
requirements of the Paperwork the Executive Director, Aircraft
PART 39—AIRWORTHINESS
Reduction Act unless that collection of Certification Service, as authorized by
DIRECTIVES
information displays a current valid FAA Order 8000.51C. In accordance
OMB control number. The control with that order, issuance of ADs is
■ 1. The authority citation for part 39
number for the collection of information normally a function of the Compliance
continues to read as follows:
required by this NPRM is 2120–0056. and Airworthiness Division, but during
this transition period, the Executive Authority: 49 U.S.C. 106(g), 40113, 44701.
The paperwork cost associated with this
NPRM has been detailed in the Costs of Director has delegated the authority to § 39.13 [Amended]
Compliance section of this document issue ADs applicable to transport
category airplanes to the Director of the ■ 2. The FAA amends § 39.13 by
and includes time for reviewing
System Oversight Division. removing Airworthiness Directive (AD)
instructions, as well as completing and
2004–03–07, Amendment 39–13451 (69
reviewing the collection of information. Regulatory Findings FR 5907, February 9, 2004), and adding
Therefore, all reporting associated with
We determined that this proposed AD the following new AD:
this NPRM is mandatory. Comments
would not have federalism implications Airbus: Docket No. FAA–2017–0902; Product
concerning the accuracy of this burden
under Executive Order 13132. This Identifier 2016–NM–188–AD.
and suggestions for reducing the burden
proposed AD would not have a
should be directed to the FAA at 800 (a) Comments Due Date
substantial direct effect on the States, on
Independence Ave. SW., Washington, We must receive comments by November
the relationship between the national
DC 20591, ATTN: Information 20, 2017.
Government and the States, or on the
Collection Clearance Officer, AES–200.
distribution of power and (b) Affected ADs
Authority for This Rulemaking responsibilities among the various This AD replaces AD 2004–03–07,
levels of government. Amendment 39–13451 (69 FR 5907, February
Title 49 of the United States Code For the reasons discussed above, I 9, 2004) (‘‘AD 2004–03–07’’).
specifies the FAA’s authority to issue certify this proposed regulation:
rules on aviation safety. Subtitle I, 1. Is not a ‘‘significant regulatory (c) Applicability
section 106, describes the authority of action’’ under Executive Order 12866; This AD applies to the Airbus airplanes
the FAA Administrator. ‘‘Subtitle VII: identified in paragraphs (c)(1) through (c)(4)
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
2. Is not a ‘‘significant rule’’ under the
Aviation Programs,’’ describes in more DOT Regulatory Policies and Procedures of this AD, certificated in any category,
detail the scope of the Agency’s (44 FR 11034, February 26, 1979); except for airplanes on which Airbus
authority. 3. Will not affect intrastate aviation in Modification 151574 was embodied in
We are issuing this rulemaking under production.
Alaska; and (1) Model A318–111, –112, –121, and –122
the authority described in ‘‘Subtitle VII, 4. Will not have a significant airplanes.
Part A, Subpart III, Section 44701: economic impact, positive or negative, (2) Model A319–111, –112, –113, –114,
General requirements.’’ Under that on a substantial number of small entities –115, –131, –132, and –133 airplanes.
section, Congress charges the FAA with under the criteria of the Regulatory (3) Model A320–211, –212, –214, –231,
promoting safe flight of civil aircraft in Flexibility Act. –232, and –233 airplanes.
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![46738 Federal Register / Vol. 82, No. 193 / Friday, October 6, 2017 / Proposed Rules
Renton, WA 98057–3356; telephone 425– DATES: Comments must be received on Administrator promotes safe flight of
227–1405; fax 425–227–1149. or before November 6, 2017. civil aircraft in air commerce by
(3) For service information identified in prescribing regulations and minimum
this AD, contact Airbus, Airworthiness ADDRESSES: Send comments identified
by docket number FAA–2017–0879 standards for other practices, methods,
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; using any of the following methods: and procedures necessary for safety in
telephone +33 5 61 93 36 96; fax +33 5 61 • Federal eRulemaking Portal: Go to air commerce and national security.
93 44 51; email account.airworth-eas@ http://www.regulations.gov and follow This action is within the scope of that
airbus.com; Internet http://www.airbus.com. the online instructions for sending your authority.
You may view this service information at the comments electronically. IAPs are promulgated by rulemaking
FAA, Transport Standards Branch, 1601 Lind procedures and are incorporated by
• Mail: Send comments to Docket
Avenue SW., Renton, WA. For information reference pursuant to 5 U.S.C. 552(a)
on the availability of this material at the Operations, M–30; U.S. Department of
Transportation (DOT), 1200 New Jersey and 1 CFR part 51 into Title 14 of the
FAA, call 425–227–1221.
Avenue SE., Room W12–140, West Code of Federal Regulations; Part 97 (14
Issued in Renton, Washington, on CFR part 97), Subpart C—TERPS
September 21, 2017. Building Ground Floor, Washington, DC
20590–0001. Procedures.
Dionne Palermo,
• Hand Delivery or Courier: Take Background
Acting Director, System Oversight Branch,
comments to Docket Operations in
Aircraft Certification Service. The National Airspace System (NAS)
Room W12–140 of the West Building
[FR Doc. 2017–21221 Filed 10–5–17; 8:45 am] is currently in transition to a ‘‘NextGen
Ground Floor at 1200 New Jersey
BILLING CODE 4910–13–P NAS’’. During this transition, the FAA
Avenue SE., Washington, DC, between 9
is managing the technology and
and 5 p.m., Monday through Friday,
procedures to support both the Legacy
except Federal holidays.
DEPARTMENT OF TRANSPORTATION NAS as well as the NextGen NAS.
• Fax: Fax comments to Docket
Managing two versions of the NAS
Federal Aviation Administration Operations at 202–493–2251.
requires excess manpower,
Privacy: In accordance with 5 U.S.C.
infrastructure, and information
14 CFR Part 97 553(c), DOT solicits comments from the
management which is costly and
public to better inform its rulemaking
[Docket No.: FAA–2017–0879] unsupportable in the longterm. To
process. DOT posts these comments,
mitigate these costs, the FAA has a
RIN 2120–AA65 without edit, including any personal number of efforts underway to
information the commenter provides, to effectively transition from the legacy to
Criteria and Process for the www.regulations.gov, as described in the NextGen NAS. One area of focus for
Cancellation of Standard Instrument the system of records notice (DOT/ALL– this transition is instrument flight
Approach Procedures as Part of the 14 FDMS), which can be reviewed at procedures (IFPs). The FAA seeks to
National Procedures Assessment www.dot.gov/privacy. ensure an effective transition from
(NPA) Docket: Background documents or ground-based IFPs to greater availability
comments received may be read at and use of satellite-based IFPs while
AGENCY: Federal Aviation
http://www.regulations.gov at any time. maintaining NAS safety.
Administration (FAA), Department of
Follow the online instructions for In early 2015, the FAA requested the
Transportation (DOT).
accessing the docket or go to the Docket RTCA’s Tactical Operations Committee
ACTION: Proposed policy and request for
Operations in Room W12–140 of the (TOC) with providing feedback and
comment. West Building Ground Floor at 1200 recommendations on criteria and
SUMMARY: As new technology facilitates New Jersey Avenue SE., Washington, processes for cancelling instrument
the introduction of area navigation DC, between 9 a.m. and 5 p.m., Monday flight procedures. Among the many
(RNAV) instrument approach through Friday, except Federal holidays. recommendations provided by the TOC
procedures over the past decade, the FOR FURTHER INFORMATION CONTACT: For were criteria on how to identify circling
number of procedures available in the technical questions concerning this procedures that would qualify as
National Airspace System has nearly action, contact Lonnie Everhart, candidates for cancellation. As of the
doubled. The complexity and cost to the Aeronautical Information Services AJV– beginning of 2017, there are
Federal Aviation Administration (FAA) 5, Federal Aviation Administration, Air approximately 12,000 IAPs in
of maintaining the instrument flight Traffic Organization, 6500 S. MacArthur publication, and there were nearly
procedures inventory while expanding Blvd, Oklahoma City, OK 73169; 10,600 circling lines of minima. Circling
the new RNAV capability is not Telephone (405) 954–4576; Email AMC- procedures account for approximately
sustainable. The FAA is considering the ATO-IFP-Cancellations@faa.gov. one-third of all lines of minima in the
cancellation of certain circling SUPPLEMENTARY INFORMATION: NAS.
procedures (to include circling-only In its continued effort to right-size the
instrument approach procedures (IAPs) Authority for This Rulemaking NAS through optimization and
and circling minima charted on straight- Under 49 U.S.C. 40103(a), the elimination of redundant and
in IAPs). The FAA proposes specific Administrator has broad authority to unnecessary IAPs, the FAA proposes the
criteria to guide the identification and regulate the safe and efficient use of the following criteria to guide the
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
selection of appropriate circling navigable airspace. The Administrator is identification and selection of
procedures that can be considered for also authorized to issue air traffic rules appropriate circling procedures to be
cancellation. The circling procedures and regulations to govern the flight, considered for cancellation.
associated with this cancellation navigation, protection, and It should be noted that National
initiative would be selected from the identification of aircraft for the Procedures Assessment (NPA)
criteria outlined below. This document protections of persons and property on Instrument Flight Procedure (IFP)
is not a part of the FAA’s VOR the ground and for the efficient use of cancellation activities and associated
minimum operating network (MON) the navigable airspace. 49 U.S.C. criteria do not supersede similar
initiative. 40103(b). Under Section 44701(a)(5), the activities being performed under the
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Document Created: 2017-10-06 00:09:30
Document Modified: 2017-10-06 00:09:30
| 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 November 20, 2017. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227- 1149. | |
| FR Citation | 82 FR 46729 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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