80 FR 26492 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 89 (May 8, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 89 (May 8, 2015)
| Page Range | 26492-26496 | |
| FR Document | 2015-10949 |
[Federal Register Volume 80, Number 89 (Friday, May 8, 2015)] [Proposed Rules] [Pages 26492-26496] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-10949] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1275; Directorate Identifier 2014-NM-070-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) 2004-14- 09, for certain Airbus Model A320-211, -212, and -231 airplanes. AD 2004-14-09 currently requires repetitive inspections for fatigue cracking of the lower surface panel on the wing center box, and repair if necessary; and modification of the lower surface panel on the wing center box, which constitutes terminating action for the repetitive inspections. Since we issued AD 2004-14-09, we have determined that, based on the average flight duration, the average weight of fuel at landing is higher than that defined for the analysis of the fatigue- related tasks; and that shot peening might have been improperly done on the chromic acid anodizing (CAA) protection, which would adversely affect fatigue crack protection. This proposed AD would reduce the compliance times for the repetitive inspections, and would require a repair for certain airplanes. We are proposing this AD to detect and correct fatigue cracking of the lower surface panel on the wing center box, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by June 22, 2015. ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed 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 referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 1275; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-1275; Directorate Identifier 2014-NM-070-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On June 29, 2004, we issued AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004). AD 2004-14-09 requires actions intended to address an unsafe condition on the products listed above. AD 2004-14-09 superseded AD 98-22-05, Amendment 39-10851 (63 FR 56542, October 22, 1998). Since we issued AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), we have determined that, based on the average flight duration, the average weight of fuel at landing is higher than that defined for the analysis of the fatigue-related tasks; and that shot peening might have been improperly done on the CAA protection, which would adversely affect fatigue crack protection. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0065, dated March 14, [[Page 26493]] 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on certain Model A320-211, -212, and -231 airplanes. The MCAI states: During center fuselage certification full scale test, damage was found in the center wing box (CWB) lower surface panel. This condition, if not detected and corrected, could affect the structural integrity of the CWB. To prevent such damage, Airbus developed mod 22418 which consists in shot-peening of the lower panel in the related area. Mod 22418 has been embodied in production from aeroplane [manufacturer serial number] (MSN) 0359. For unmodified in-service aeroplanes, Airbus issued Service Bulletin (SB) A320-57-1082 to introduce repetitive High Frequency Eddy Current (HFEC) inspections on the external face of the center wing box lower panel between Frame (FR) 41 and FR42 to detect damage. DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 2002-342 [http://ad.easa.europa.eu/blob/20023420tb_superseded.pdf/AD_F-2002-342_1] to require these inspections and, depending on findings, applicable corrective action(s). Airbus also issued SB A320-57-1043 as an optional terminating action for the repetitive inspections required by DGAC France AD 2002-342. Since that [DGAC] AD was issued, the results of a survey, carried out on the A320 fleet, highlighted some differences between the mission parameters, mainly on the weight of fuel at landing and on the average flight duration, which are higher than those defined for the analysis of the fatigue related tasks. These findings have led to an adjustment of the A320 reference fatigue mission. Consequently, the threshold and intervals of these repetitive inspections have been revised and a new threshold figure expressed in flight hours (FH) has been established. In addition, it has been identified that, on aeroplanes that have been modified in accordance with Airbus SB A320-57-1043 (Airbus mod 22418) at Revision 05 or an earlier Revision, the shot peening may have been improperly done on the Chromic Acid Anodizing (CAA) protection, which has no fatigue benefit effect. Therefore, the inspections per Airbus SB A320-57-1082 are required again on these aeroplanes. Consequently, new shot-peening procedures with proper CAA protection removal instructions have been developed and their embodiment through Airbus SB A320-57-1043 Revision 06 cancels the repetitive inspections per Airbus SB A320-57-1082, as required by DGAC France AD 2002-342. For the reasons described above, this new [EASA] AD retains the requirements of DGAC France AD 2002-342, which is superseded, but requires these actions to be accomplished within reduced thresholds and intervals. In addition, the optional terminating action provision (SB A320-57-1043) is amended by including reference to the SB at Revision 06. The optional terminating action described in Airbus Service Bulletin A320-57-1043, Revision 06, dated December 5, 2013, is accomplishing shot peening in the radius of the milling step between stiffeners 13 and 14 near the fuel pump aperture. 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-2015- 1275. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320-57-1043, Revision 06, dated December 5, 2013. This service bulletin describes procedures for shot peening in the radius of the milling step between stiffeners 13 and 14 near the fuel pump aperture. Airbus has also issued Service Bulletin A320-57-1082, Revision 04, dated December 5, 2013. This service bulletin describes procedures for inspections for cracking of the lower surface panel on the wing center box. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. 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 of this NPRM. 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 46 airplanes of U.S. registry. The actions that are required by AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), and retained in this proposed AD take about 25 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that were required by AD 2004-14-09 is $2,125 per product. The new requirements of this proposed AD would add no additional economic burden. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. We have no way of determining the number of aircraft that might need these actions. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, [[Page 26494]] 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) 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), and adding the following new AD: Airbus: Docket No. FAA-2014-1275; Directorate Identifier 2014-NM- 070-AD. (a) Comments Due Date We must receive comments by June 22, 2015. (b) Affected ADs This AD replaces AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004). (c) Applicability This AD applies to Airbus Model A320-211, -212, and -231 airplanes, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification 22418 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a determination that, based on the average flight duration, the average weight of fuel at landing is higher than that defined for the analysis of the fatigue-related tasks; and that shot peening might have been improperly done on the chromic acid anodizing (CAA) protection, which would adversely affect fatigue crack protection. We are issuing this AD to detect and correct fatigue cracking of the lower surface panel on the wing center box (WCB), which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Repetitive Inspections, With No Changes This paragraph restates the requirements of paragraph (a) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no changes. Except as provided by paragraph (k) of this AD: Prior to the accumulation of 20,000 total flight cycles, or within 60 days after November 27, 1998 (the effective date of AD 98-22-05, Amendment 39-10851 (63 FR 56542, October 22, 1998)), whichever occurs later, perform a high frequency eddy current (HFEC) inspection to detect fatigue cracking of the lower surface panel on the WCB, in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997; or Revision 03, dated April 30, 2002. Repeat the HFEC inspection thereafter at intervals not to exceed 7,500 flight cycles until the actions required by paragraph (i) of this AD are accomplished. (h) Retained Repair, With No Changes This paragraph restates the requirements of paragraph (b) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no changes. Except as provided by paragraph (j) of this AD, if any cracking is detected during any inspection required by paragraph (g) of this AD: Prior to further flight, repair in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997; or Revision 03, dated April 30, 2002. Accomplishment of the repair constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD for the repaired area only. (i) Retained Inspection/Modification/Repair, With Terminating Action This paragraph restates the requirements of paragraph (c) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with terminating action provided. Prior to the accumulation of 25,000 total flight cycles, or within 60 days after November 27, 1998 (the effective date of AD 98-22-05, Amendment 39-10851 (63 FR 56542, October 22, 1998)), whichever occurs later: Perform an HFEC inspection to detect fatigue cracking of the lower surface panel on the WCB, in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997; or Revision 03, dated April 30, 2002. Accomplishment of the initial inspection required by paragraph (p) of this AD constitutes terminating action for the inspection requirements of this paragraph. (1) If no cracking is detected: Prior to further flight, modify the lower surface panel on the WCB, in accordance with Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997; or Revision 05, dated April 30, 2002. Accomplishment of the modification constitutes terminating action for the requirements of paragraph (g) of this AD. (2) Except as provided by paragraph (j) of this AD: If any cracking is detected, prior to further flight, repair in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997, or Revision 03, dated April 30, 2002; and modify any uncracked area, in accordance with Airbus Service Bulletin A320- 57-1043, Revision 02, dated May 14, 1997, or Revision 05, dated April 30, 2002. Accomplishment of the repair of cracked area(s) and modification of uncracked area(s) constitutes terminating action for the requirements of paragraph (g) of this AD. (j) Retained Service Bulletin Exception, With No Changes This paragraph restates the requirements of paragraph (d) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no changes. If any cracking is detected during any inspection required by paragraph (h) or (i)(2) of this AD, and the applicable service bulletin specifies to contact Airbus for an appropriate action: Prior to further flight, repair using a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated agent). (k) Retained Provision for Certain Inspection Exception, With No Changes This paragraph restates the provision of paragraph (e) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no changes. The actions required by paragraph (g) of this AD are not required to be accomplished if the requirements of paragraph (i) of this AD are accomplished at the time specified in paragraph (g) of this AD. (l) Retained Initial Inspection, With Terminating Action This paragraph restates the requirements of paragraph (f) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with terminating action provided. For airplanes on which neither the inspection required by paragraph (g) of this AD, nor the modification required by paragraph (i)(1) of this AD has been done before August 13, 2004 (the effective date of AD 2004-14-09): Perform an HFEC inspection to detect fatigue cracking of the lower surface panel on the WCB, in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997; or Revision 03, dated April 30, 2002; at the later of the times specified in paragraphs (l)(1) and (l)(2) of this AD. Accomplishment of the inspection required by this paragraph terminates the requirements of paragraph (g) of this AD. Accomplishment of the initial inspection required by paragraph (p) of this AD terminates the inspection requirements of this paragraph. (1) Prior to the accumulation of 13,200 total flight cycles or 39,700 total flight hours, whichever is first. (2) Prior to the accumulation of 20,000 total flight cycles, or within 3,500 flight cycles after August 13, 2004 (the effective date of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004)), whichever is later. (m) Retained Repetitive Inspections, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no changes. If no cracking is detected during the inspection required by paragraph (g) or (l) of this AD: Repeat the inspection required by paragraph (l) of this AD at the applicable time specified in paragraph (m)(1) or (m)(2) of this AD. Accomplishment of the modification required by paragraph (i)(1) of this AD terminates the requirements of this paragraph. (1) For airplanes on which the inspections required by paragraph (g) of this AD have been initiated before August 13, 2004 (the effective date of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004)): Do the next inspection within 5,700 flight cycles after accomplishment of the last inspection, or within 1,800 flight cycles after [[Page 26495]] August 13, 2004, whichever is later. Repeat the inspection thereafter at intervals not to exceed 5,700 flight cycles. (2) For airplanes on which no inspection required by paragraph (g) of this AD has been done before August 13, 2004 (the effective date of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004)): Do the next inspection within 5,700 flight cycles after accomplishment of the inspection required by paragraph (l) of this AD. Repeat the inspection thereafter at intervals not to exceed 5,700 flight cycles. (n) Retained Repair/Modification, With No Changes This paragraph restates the requirements of paragraph (h) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no changes. If any cracking is detected during any inspection required by paragraph (l) or (m) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997, or Revision 03, dated April 30, 2002; and modify any uncracked area, in accordance with Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997, or Revision 05, dated April 30, 2002. Where Airbus Service Bulletin A320-57-1082 specifies to contact Airbus for an appropriate repair action: Prior to further flight, repair using a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the DGAC (or its delegated agent). Accomplishment of the repair of cracked area(s) and modification of uncracked area(s) constitutes terminating action for the requirements of paragraphs (g) through (n) of this AD. (o) New Requirement of This AD: Repair of Certain Airplanes For airplanes on which the actions described in Airbus Service Bulletin A320-57-1043 have not been accomplished, and on which a repair has been accomplished, as described in Airbus Service Bulletin A320-57-1082, dated October 31, 1996; Revision 01, dated December 10, 1997; Revision 02, dated July 26, 1999; or Revision 03, dated April 30, 2002: Within 30 days after the effective date of this AD, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; the European Aviation Safety Agency (EASA); or Airbus's EASA design organization approval (DOA). (p) New Requirement of This AD: Repetitive WCB Inspections At the applicable time specified in paragraphs (p)(1) and (p)(2) of this AD: Do an HFEC inspection for cracking of the lower surface panel on the WCB, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1082, Revision 04, dated December 5, 2013. Repeat the inspection of the lower surface panel on the WCB thereafter at intervals not to exceed 7,200 flight cycles or 14,400 flight hours, whichever occurs first. Accomplishment of the initial inspection required by this paragraph terminates the inspections required by paragraphs (g), (i), and (l) of this AD. (1) For airplanes on which the actions described in Airbus Service Bulletin A320-57-1043 have not been done: At the later of the times specified in paragraphs (p)(1)(i) and (p)(1)(ii) of this AD. (i) Before the accumulation of 20,700 flight cycles or 41,400 flight hours, whichever occurs first since first flight of the airplane. (ii) Within 7,200 flight cycles or 14,400 flight hours, whichever occurs first after doing the most recent inspection as specified in Airbus Service Bulletin A320-57-1082, dated October 31, 1996; Revision 01, dated December 10, 1997; Revision 02, dated July 26, 1999; or Revision 03, dated April 30, 2002. (2) For airplanes on which the actions specified in Airbus Service Bulletin A320-57-1043, dated February 16, 1993; Revision 01, dated June 14, 1996; Revision 02, dated May 14, 1997; Revision 03, dated October 24, 1997; Revision 04, dated March 15, 1999; or Revision 05, dated April 30, 2002; have been done: At the latest of the times specified in paragraphs (p)(2)(i), (p)(2)(ii), and (p)(2)(iii) of this AD. (i) Within 7,200 flight cycles or 14,400 flight hours, whichever occurs first since doing the actions specified in Airbus Service Bulletin A320-57-1043. (ii) Within 3,750 flight cycles or 7,500 flight hours, whichever occurs first after July 31, 2012 (as described in Airbus Service Bulletin A320-57-1082, Revision 04, dated December 5, 2013). (iii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first after the effective date of this AD. (q) New Requirement of This AD: Repair of WCB If any crack is found during any inspection required by paragraph (p) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; the EASA; or Airbus's EASA DOA. (r) New Optional Terminating Action Modification of an airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1043, Revision 06, dated December 5, 2013, constitutes terminating action for the actions required by paragraph (p) of this AD. (s) Credit for Previous Actions This paragraph provides credit for applicable actions required by paragraphs (g) through (n) of this AD, if those actions were performed before the effective date of this AD using the applicable Airbus Service Information provided in paragraphs (s)(1) through (s)(8) of this AD. (1) Airbus Service Bulletin A320-57-1043, dated February 16, 1993, which is not incorporated by reference in this AD. (2) Airbus Service Bulletin A320-57-1043, Revision 01, dated June 14, 1996, which is not incorporated by reference in this AD. (3) Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997, which was incorporated by reference on November 27, 1998 (63 FR 56542, October 22, 1998). (4) Airbus Service Bulletin A320-57-1043, Revision 03, dated October 24, 1997, which is not incorporated by reference in this AD. (5) Airbus Service Bulletin A320-57-1043, Revision 04, dated May 15, 1999, which is not incorporated by reference in this AD. (6) Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997, which was incorporated by reference on November 27, 1998 (63 FR 56542, October 22, 1998). (7) Airbus Service Bulletin A320-57-1082, Revision 02, dated July 26, 1999, which is not incorporated by reference in this AD. (8) Airbus Service Bulletin A320-57-1082, Revision 03, dated April 30, 2002, which was incorporated by reference on August 13, 2004 (69 FR 41398, July 9, 2004). (t) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-1405; fax 425-227-1149. 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 Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (u) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0065, dated March 14, 2014, 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-2014-1275. (2) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. [[Page 26496]] Issued in Renton, Washington, on April 29, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-10949 Filed 5-7-15; 8:45 am] BILLING CODE 4910-13-P
![26492 Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules
Flight Standards District Office, as 09 currently requires repetitive and 5 p.m., Monday through Friday,
appropriate. If sending information directly inspections for fatigue cracking of the except Federal holidays. The AD docket
to the ACO, send it to ATTN: Program lower surface panel on the wing center contains this proposed AD, the
Manager, Continuing Operational Safety,
box, and repair if necessary; and regulatory evaluation, any comments
FAA, New York ACO, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone: modification of the lower surface panel received, and other information. The
516–228–7300; fax: 516–794–5531. Before on the wing center box, which street address for the Docket Operations
using any approved AMOC, notify your constitutes terminating action for the office (telephone 800–647–5527) is in
appropriate principal inspector, or lacking a repetitive inspections. Since we issued the ADDRESSES section. Comments will
principal inspector, the manager of the local AD 2004–14–09, we have determined be available in the AD docket shortly
flight standards district office/certificate that, based on the average flight after receipt.
holding district office. The AMOC approval duration, the average weight of fuel at FOR FURTHER INFORMATION CONTACT:
letter must specifically reference this AD.
landing is higher than that defined for Sanjay Ralhan, Aerospace Engineer,
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective the analysis of the fatigue-related tasks; International Branch, ANM–116,
actions from a manufacturer, the action must and that shot peening might have been Transport Airplane Directorate, FAA,
be accomplished using a method approved improperly done on the chromic acid 1601 Lind Avenue SW., Renton, WA
by the Manager, New York ACO, ANE–170, anodizing (CAA) protection, which 98057–3356; telephone 425–227–1405;
FAA; or TCCA; or Bombardier, Inc.’s TCCA would adversely affect fatigue crack fax 425–227–1149.
DAO. If approved by the DAO, the approval protection. This proposed AD would
must include the DAO-authorized signature. SUPPLEMENTARY INFORMATION:
reduce the compliance times for the
(j) Related Information repetitive inspections, and would Comments Invited
(1) Refer to Mandatory Continuing require a repair for certain airplanes. We We invite you to send any written
Airworthiness Information (MCAI) Canadian are proposing this AD to detect and relevant data, views, or arguments about
Airworthiness Directive CF–2014–32, dated correct fatigue cracking of the lower this proposed AD. Send your comments
September 8, 2014, for related information. surface panel on the wing center box, to an address listed under the
This MCAI may be found in the AD docket which could result in reduced structural ADDRESSES section. Include ‘‘Docket No.
on the Internet at http://www.regulations.gov integrity of the airplane.
by searching for and locating Docket No. FAA–2015–1275; Directorate Identifier
FAA–2015–0929. DATES: We must receive comments on 2014–NM–070–AD’’ at the beginning of
(2) For service information identified in this proposed AD by June 22, 2015. your comments. We specifically invite
this AD, contact Bombardier, Inc., 400 Côte- ADDRESSES: You may send comments by comments on the overall regulatory,
Vertu Road West, Dorval, Québec H4S 1Y9, any of the following methods: economic, environmental, and energy
Canada; telephone: 514–855–5000; fax: 514– • Federal eRulemaking Portal: Go to aspects of this proposed AD. We will
855–7401; email thd.crj@ consider all comments received by the
http://www.regulations.gov. Follow the
aero.bombardier.com; Internet http://
www.bombardier.com. You may view this instructions for submitting comments. closing date and may amend this
service information at the FAA, Transport • Fax: 202–493–2251. proposed AD based on those comments.
Airplane Directorate, 1601 Lind Avenue SW., • Mail: U.S. Department of We will post all comments we
Renton, WA. For information on the Transportation, Docket Operations, receive, without change, to http://
availability of this material at the FAA, call M–30, West Building Ground Floor, www.regulations.gov, including any
425–227–1221. Room W12–140, 1200 New Jersey personal information you provide. We
Issued in Renton, Washington, on April 13, Avenue SE., Washington, DC 20590. will also post a report summarizing each
2015. • Hand Delivery: U.S. Department of substantive verbal contact we receive
Michael Kaszycki, Transportation, Docket Operations, about this proposed AD.
Acting Manager, Transport Airplane M–30, West Building Ground Floor,
Discussion
Directorate, Aircraft Certification Service. Room W12–140, 1200 New Jersey
[FR Doc. 2015–10947 Filed 5–7–15; 8:45 am] Avenue SE., Washington, DC, between 9 On June 29, 2004, we issued AD
a.m. and 5 p.m., Monday through 2004–14–09, Amendment 39–13718 (69
BILLING CODE 4910–13–P
Friday, except Federal holidays. FR 41398, July 9, 2004). AD 2004–14–
For service information identified in 09 requires actions intended to address
DEPARTMENT OF TRANSPORTATION this proposed AD, contact Airbus, an unsafe condition on the products
Airworthiness Office—EIAS, 1 Rond listed above. AD 2004–14–09
Federal Aviation Administration Point Maurice Bellonte, 31707 Blagnac superseded AD 98–22–05, Amendment
Cedex, France; telephone +33 5 61 93 36 39–10851 (63 FR 56542, October 22,
14 CFR Part 39 96; fax +33 5 61 93 44 51; email 1998).
account.airworth-eas@airbus.com; Since we issued AD 2004–14–09,
[Docket No. FAA–2015–1275; Directorate
Internet http://www.airbus.com. You Amendment 39–13718 (69 FR 41398,
Identifier 2014–NM–070–AD]
may view this referenced service July 9, 2004), we have determined that,
RIN 2120–AA64 information at the FAA, Transport based on the average flight duration, the
Airplane Directorate, 1601 Lind Avenue average weight of fuel at landing is
Airworthiness Directives; Airbus SW., Renton, WA. For information on higher than that defined for the analysis
Airplanes the availability of this material at the of the fatigue-related tasks; and that shot
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
AGENCY: Federal Aviation FAA, call 425–227–1221. peening might have been improperly
Administration (FAA), DOT. done on the CAA protection, which
Examining the AD Docket would adversely affect fatigue crack
ACTION: Notice of proposed rulemaking
(NPRM). You may examine the AD docket on protection.
the Internet at http:// The European Aviation Safety Agency
SUMMARY: We propose to supersede www.regulations.gov by searching for (EASA), which is the Technical Agent
Airworthiness Directive (AD) 2004–14– and locating Docket No. FAA–2015– for the Member States of the European
09, for certain Airbus Model A320–211, 1275; or in person at the Docket Union, has issued EASA Airworthiness
–212, and –231 airplanes. AD 2004–14– Management Facility between 9 a.m. Directive 2014–0065, dated March 14,
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![Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules 26493
2014 (referred to after this as the The optional terminating action The new requirements of this
Mandatory Continuing Airworthiness described in Airbus Service Bulletin proposed AD would add no additional
Information, or ‘‘the MCAI’’), to correct A320–57–1043, Revision 06, dated economic burden.
an unsafe condition on certain Model December 5, 2013, is accomplishing We have received no definitive data
A320–211, –212, and –231 airplanes. shot peening in the radius of the milling that would enable us to provide cost
The MCAI states: step between stiffeners 13 and 14 near estimates for the on-condition actions
During center fuselage certification full the fuel pump aperture. specified in this proposed AD. We have
scale test, damage was found in the center You may examine the MCAI in the no way of determining the number of
wing box (CWB) lower surface panel. AD docket on the Internet at http:// aircraft that might need these actions.
This condition, if not detected and www.regulations.gov by searching for Authority for This Rulemaking
corrected, could affect the structural integrity and locating Docket No. FAA–2015–
of the CWB. 1275. Title 49 of the United States Code
To prevent such damage, Airbus developed specifies the FAA’s authority to issue
mod 22418 which consists in shot-peening of Related Service Information Under 1 rules on aviation safety. Subtitle I,
the lower panel in the related area. Mod CFR Part 51 section 106, describes the authority of
22418 has been embodied in production from the FAA Administrator. ‘‘Subtitle VII:
aeroplane [manufacturer serial number] Airbus has issued Service Bulletin
Aviation Programs,’’ describes in more
(MSN) 0359. For unmodified in-service A320–57–1043, Revision 06, dated
aeroplanes, Airbus issued Service Bulletin
detail the scope of the Agency’s
December 5, 2013. This service bulletin
(SB) A320–57–1082 to introduce repetitive authority.
describes procedures for shot peening in We are issuing this rulemaking under
High Frequency Eddy Current (HFEC) the radius of the milling step between
inspections on the external face of the center the authority described in ‘‘Subtitle VII,
stiffeners 13 and 14 near the fuel pump Part A, Subpart III, Section 44701:
wing box lower panel between Frame (FR) 41
and FR42 to detect damage.
aperture. General requirements.’’ Under that
DGAC [Direction Générale de l’Aviation Airbus has also issued Service section, Congress charges the FAA with
Civile] France issued AD 2002–342 [http:// Bulletin A320–57–1082, Revision 04, promoting safe flight of civil aircraft in
ad.easa.europa.eu/blob/20023420tb_ dated December 5, 2013. This service air commerce by prescribing regulations
superseded.pdf/AD_F-2002-342_1] to require bulletin describes procedures for for practices, methods, and procedures
these inspections and, depending on inspections for cracking of the lower the Administrator finds necessary for
findings, applicable corrective action(s). surface panel on the wing center box.
Airbus also issued SB A320–57–1043 as an safety in air commerce. This regulation
optional terminating action for the repetitive The actions described in this service is within the scope of that authority
inspections required by DGAC France AD information are intended to correct the because it addresses an unsafe condition
2002–342. unsafe condition identified in the that is likely to exist or develop on
Since that [DGAC] AD was issued, the MCAI. This service information is products identified in this rulemaking
results of a survey, carried out on the A320 reasonably available because the action.
fleet, highlighted some differences between interested parties have access to it
the mission parameters, mainly on the weight Regulatory Findings
through their normal course of business
of fuel at landing and on the average flight or by the means identified in the We determined that this proposed AD
duration, which are higher than those would not have federalism implications
ADDRESSES section of this NPRM.
defined for the analysis of the fatigue related under Executive Order 13132. This
tasks. FAA’s Determination and Requirements
These findings have led to an adjustment
proposed AD would not have a
of This Proposed AD substantial direct effect on the States, on
of the A320 reference fatigue mission.
Consequently, the threshold and intervals of This product has been approved by the relationship between the national
these repetitive inspections have been the aviation authority of another Government and the States, or on the
revised and a new threshold figure expressed country, and is approved for operation distribution of power and
in flight hours (FH) has been established. in the United States. Pursuant to our responsibilities among the various
In addition, it has been identified that, on bilateral agreement with the State of levels of government.
aeroplanes that have been modified in For the reasons discussed above, I
Design Authority, we have been notified
accordance with Airbus SB A320–57–1043 certify this proposed regulation:
(Airbus mod 22418) at Revision 05 or an of the unsafe condition described in the
MCAI and service information 1. Is not a ‘‘significant regulatory
earlier Revision, the shot peening may have
referenced above. We are proposing this action’’ under Executive Order 12866;
been improperly done on the Chromic Acid
AD because we evaluated all pertinent 2. Is not a ‘‘significant rule’’ under the
Anodizing (CAA) protection, which has no
fatigue benefit effect. Therefore, the information and determined an unsafe DOT Regulatory Policies and Procedures
inspections per Airbus SB A320–57–1082 are condition exists and is likely to exist or (44 FR 11034, February 26, 1979);
required again on these aeroplanes. develop on other products of the same 3. Will not affect intrastate aviation in
Consequently, new shot-peening type design. Alaska; and
procedures with proper CAA protection 4. Will not have a significant
removal instructions have been developed Costs of Compliance economic impact, positive or negative,
and their embodiment through Airbus SB on a substantial number of small entities
A320–57–1043 Revision 06 cancels the We estimate that this proposed AD
under the criteria of the Regulatory
repetitive inspections per Airbus SB A320– affects 46 airplanes of U.S. registry.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Flexibility Act.
57–1082, as required by DGAC France AD The actions that are required by AD
2002–342. 2004–14–09, Amendment 39–13718 (69 List of Subjects in 14 CFR Part 39
For the reasons described above, this new FR 41398, July 9, 2004), and retained in Air transportation, Aircraft, Aviation
[EASA] AD retains the requirements of DGAC
this proposed AD take about 25 work- safety, Incorporation by reference,
France AD 2002–342, which is superseded,
but requires these actions to be accomplished hours per product, at an average labor Safety.
within reduced thresholds and intervals. In rate of $85 per work-hour. Based on
these figures, the estimated cost of the The Proposed Amendment
addition, the optional terminating action
provision (SB A320–57–1043) is amended by actions that were required by AD 2004– Accordingly, under the authority
including reference to the SB at Revision 06. 14–09 is $2,125 per product. delegated to me by the Administrator,
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![26494 Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules
the FAA proposes to amend 14 CFR part Airbus Service Bulletin A320–57–1082, contact Airbus for an appropriate action:
39 as follows: Revision 01, dated December 10, 1997; or Prior to further flight, repair using a method
Revision 03, dated April 30, 2002. Repeat the approved by the Manager, International
PART 39—AIRWORTHINESS HFEC inspection thereafter at intervals not to Branch, ANM–116, FAA, Transport Airplane
DIRECTIVES exceed 7,500 flight cycles until the actions Directorate; or the Direction Générale de
required by paragraph (i) of this AD are l’Aviation Civile (DGAC) (or its delegated
■ 1. The authority citation for part 39 accomplished. agent).
continues to read as follows: (h) Retained Repair, With No Changes (k) Retained Provision for Certain Inspection
Authority: 49 U.S.C. 106(g), 40113, 44701. This paragraph restates the requirements of Exception, With No Changes
paragraph (b) of AD 2004–14–09, This paragraph restates the provision of
§ 39.13 [Amended] Amendment 39–13718 (69 FR 41398, July 9, paragraph (e) of AD 2004–14–09,
■ 2. The FAA amends § 39.13 by 2004), with no changes. Except as provided Amendment 39–13718 (69 FR 41398, July 9,
removing Airworthiness Directive (AD) by paragraph (j) of this AD, if any cracking 2004), with no changes. The actions required
2004–14–09, Amendment 39–13718 (69 is detected during any inspection required by by paragraph (g) of this AD are not required
paragraph (g) of this AD: Prior to further to be accomplished if the requirements of
FR 41398, July 9, 2004), and adding the flight, repair in accordance with Airbus paragraph (i) of this AD are accomplished at
following new AD: Service Bulletin A320–57–1082, Revision 01, the time specified in paragraph (g) of this AD.
Airbus: Docket No. FAA–2014–1275; dated December 10, 1997; or Revision 03,
(l) Retained Initial Inspection, With
Directorate Identifier 2014–NM–070–AD. dated April 30, 2002. Accomplishment of the
Terminating Action
repair constitutes terminating action for the
(a) Comments Due Date repetitive inspections required by paragraph This paragraph restates the requirements of
We must receive comments by June 22, (g) of this AD for the repaired area only. paragraph (f) of AD 2004–14–09, Amendment
2015. 39–13718 (69 FR 41398, July 9, 2004), with
(i) Retained Inspection/Modification/Repair, terminating action provided. For airplanes on
(b) Affected ADs With Terminating Action which neither the inspection required by
This AD replaces AD 2004–14–09, This paragraph restates the requirements of paragraph (g) of this AD, nor the modification
Amendment 39–13718 (69 FR 41398, July 9, paragraph (c) of AD 2004–14–09, required by paragraph (i)(1) of this AD has
2004). Amendment 39–13718 (69 FR 41398, July 9, been done before August 13, 2004 (the
2004), with terminating action provided. effective date of AD 2004–14–09): Perform an
(c) Applicability HFEC inspection to detect fatigue cracking of
Prior to the accumulation of 25,000 total
This AD applies to Airbus Model A320– flight cycles, or within 60 days after the lower surface panel on the WCB, in
211, –212, and –231 airplanes, certificated in November 27, 1998 (the effective date of AD accordance with Airbus Service Bulletin
any category, all manufacturer serial 98–22–05, Amendment 39–10851 (63 FR A320–57–1082, Revision 01, dated December
numbers, except those on which Airbus 56542, October 22, 1998)), whichever occurs 10, 1997; or Revision 03, dated April 30,
Modification 22418 has been embodied in later: Perform an HFEC inspection to detect 2002; at the later of the times specified in
production. fatigue cracking of the lower surface panel on paragraphs (l)(1) and (l)(2) of this AD.
the WCB, in accordance with Airbus Service Accomplishment of the inspection required
(d) Subject
Bulletin A320–57–1082, Revision 01, dated by this paragraph terminates the
Air Transport Association (ATA) of December 10, 1997; or Revision 03, dated requirements of paragraph (g) of this AD.
America Code 57, Wings. April 30, 2002. Accomplishment of the initial Accomplishment of the initial inspection
inspection required by paragraph (p) of this required by paragraph (p) of this AD
(e) Reason
AD constitutes terminating action for the terminates the inspection requirements of
This AD was prompted by a determination inspection requirements of this paragraph. this paragraph.
that, based on the average flight duration, the (1) If no cracking is detected: Prior to (1) Prior to the accumulation of 13,200
average weight of fuel at landing is higher further flight, modify the lower surface panel total flight cycles or 39,700 total flight hours,
than that defined for the analysis of the on the WCB, in accordance with Airbus whichever is first.
fatigue-related tasks; and that shot peening Service Bulletin A320–57–1043, Revision 02, (2) Prior to the accumulation of 20,000
might have been improperly done on the dated May 14, 1997; or Revision 05, dated total flight cycles, or within 3,500 flight
chromic acid anodizing (CAA) protection, April 30, 2002. Accomplishment of the cycles after August 13, 2004 (the effective
which would adversely affect fatigue crack modification constitutes terminating action date of AD 2004–14–09, Amendment 39–
protection. We are issuing this AD to detect for the requirements of paragraph (g) of this 13718 (69 FR 41398, July 9, 2004)),
and correct fatigue cracking of the lower AD. whichever is later.
surface panel on the wing center box (WCB), (2) Except as provided by paragraph (j) of
which could result in reduced structural (m) Retained Repetitive Inspections, With
this AD: If any cracking is detected, prior to
integrity of the airplane. No Changes
further flight, repair in accordance with
Airbus Service Bulletin A320–57–1082, This paragraph restates the requirements of
(f) Compliance paragraph (g) of AD 2004–14–09,
Revision 01, dated December 10, 1997, or
Comply with this AD within the Revision 03, dated April 30, 2002; and Amendment 39–13718 (69 FR 41398, July 9,
compliance times specified, unless already modify any uncracked area, in accordance 2004), with no changes. If no cracking is
done. with Airbus Service Bulletin A320–57–1043, detected during the inspection required by
Revision 02, dated May 14, 1997, or Revision paragraph (g) or (l) of this AD: Repeat the
(g) Retained Repetitive Inspections, With No inspection required by paragraph (l) of this
Changes 05, dated April 30, 2002. Accomplishment of
the repair of cracked area(s) and modification AD at the applicable time specified in
This paragraph restates the requirements of of uncracked area(s) constitutes terminating paragraph (m)(1) or (m)(2) of this AD.
paragraph (a) of AD 2004–14–09, action for the requirements of paragraph (g) Accomplishment of the modification
Amendment 39–13718 (69 FR 41398, July 9, required by paragraph (i)(1) of this AD
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
of this AD.
2004), with no changes. Except as provided terminates the requirements of this
by paragraph (k) of this AD: Prior to the (j) Retained Service Bulletin Exception, With paragraph.
accumulation of 20,000 total flight cycles, or No Changes (1) For airplanes on which the inspections
within 60 days after November 27, 1998 (the This paragraph restates the requirements of required by paragraph (g) of this AD have
effective date of AD 98–22–05, Amendment paragraph (d) of AD 2004–14–09, been initiated before August 13, 2004 (the
39–10851 (63 FR 56542, October 22, 1998)), Amendment 39–13718 (69 FR 41398, July 9, effective date of AD 2004–14–09,
whichever occurs later, perform a high 2004), with no changes. If any cracking is Amendment 39–13718 (69 FR 41398, July 9,
frequency eddy current (HFEC) inspection to detected during any inspection required by 2004)): Do the next inspection within 5,700
detect fatigue cracking of the lower surface paragraph (h) or (i)(2) of this AD, and the flight cycles after accomplishment of the last
panel on the WCB, in accordance with applicable service bulletin specifies to inspection, or within 1,800 flight cycles after
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![26496 Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules
Issued in Renton, Washington, on April 29, (NARA). For information on the Availability of SNPRMs
2015. availability of this proposed An electronic copy of this document
Jeffrey E. Duven, incorporation by reference material at may be downloaded through the
Manager, Transport Airplane Directorate, NARA, call 202–741–6030, or go to Internet at http://www.regulations.gov.
Aircraft Certification Service. http://www.archives.gov/federal_ Recently published rulemaking
[FR Doc. 2015–10949 Filed 5–7–15; 8:45 am] register/code_of_federal-regulations/ibr_
documents can also be accessed through
BILLING CODE 4910–13–P locations.html.
the FAA’s Web page at http://
FAA Order 7400.9, Airspace
Designations and Reporting Points, is www.faa.gov/airports_airtraffic/air_
published yearly and effective on traffic/publications/airspace_
DEPARTMENT OF TRANSPORTATION
September 15. For further information, amendments/.
Federal Aviation Administration you can contact the Airspace Policy and You may review the public docket
Regulations Group, Federal Aviation containing the proposal, any comments
14 CFR Part 71 Administration, 800 Independence received and any final disposition in
Avenue SW., Washington, DC 20591; person in the Dockets Office (see
[Docket No. FAA–2014–0565; Airspace ADDRESSES section for address and
Docket No. 14–ACE–7] telephone: 202–267–8783.
phone number) between 9:00 a.m. and
FOR FURTHER INFORMATION CONTACT: Raul
Proposed Revocation of Class D and E 5:00 p.m., Monday through Friday,
Garza, Jr., Central Service Center,
Airspace; Independence, KS except Federal holidays. An informal
Operations Support Group, Federal
docket may also be examined during
AGENCY: Federal Aviation Aviation Administration, Southwest
normal business hours at the office of
Administration (FAA), DOT. Region, 2601 Meacham Blvd., Fort
the Central Service Center, 2601
Worth, TX 76137; telephone: 817–321–
ACTION: Supplemental notice of Meacham Blvd., Fort Worth, TX 76137.
7654.
proposed rulemaking (SNPRM). Persons interested in being placed on
SUPPLEMENTARY INFORMATION:
a mailing list for future NPRMs should
SUMMARY: This supplemental notice of History contact the FAA’s Office of Rulemaking
proposed rulemaking proposes to (202) 267–9677, to request a copy of
remove Class D airspace and Class E On September 25, 2014, the FAA
published a NPRM to remove Class D Advisory Circular No. 11–2A, Notice of
surface area airspace at Independence Proposed Rulemaking Distribution
Municipal Airport, Independence, KS. airspace at Independence Municipal
Airport, Independence, KS, as the air System, which describes the application
In an NPRM published in the Federal procedure.
Register September 25, 2014, the FAA traffic control tower has closed (79 FR
proposed to remove Class D airspace at 57483). The comment period closed Availability and Summary of
Independence Municipal Airport, November 10, 2014. No comments were Documents Proposed for Incorporation
Independence, KS. The FAA has received. Subsequent to publication, the by Reference
reassessed the proposal to include the FAA reassessed the proposal to include
the removal of the associated Class E This document proposes to amend
removal of the associated Class E FAA Order 7400.9Y, Airspace
surface area airspace. The closure of the surface area airspace at Independence
Municipal Airport, Independence, KS. Designations and Reporting Points,
airport’s air traffic control tower has dated August 6, 2014, and effective
necessitated the need for this proposal. Also, the title section is amended to
include Class E airspace. The FAA seeks September 15, 2014. FAA Order
DATES: Comments must be received on 7400.9Y is publicly available as listed in
comments on this SNPRM.
or before June 22, 2015. the ADDRESSES section of this proposed
ADDRESSES: Send comments on this Comments Invited rule. FAA Order 7400.9Y lists Class A,
proposal to the U.S. Department of Interested parties are invited to B, C, D, and E airspace areas, air traffic
Transportation, Docket Operations, 1200 participate in this proposed rulemaking service routes, and reporting points.
New Jersey Avenue SE., West Building by submitting such written data, views, The Supplemental Proposal
Ground Floor, Room W12–140, or arguments, as they may desire.
Washington, DC 20590–0001. You must Comments that provide the factual basis This supplemental proposal proposes
identify the docket number FAA–2014– supporting the views and suggestions to amend Title 14, Code of Federal
0565/Airspace Docket No. 14–ACE–7, at presented are particularly helpful in Regulations (14 CFR), Part 71 by
the beginning of your comments. You developing reasoned regulatory removing Class D airspace and the
may also submit comments through the decisions on the proposal. Comments associated Class E surface area airspace
Internet at http://www.regulations.gov. are specifically invited on the overall at Independence Municipal Airport,
You may review the public docket regulatory, aeronautical, economic, Independence, KS. The closing of the
containing the proposal, any comments environmental, and energy-related airport’s air traffic control tower has
received, and any final disposition in aspects of the proposal. made this action necessary. Also, the
person in the Dockets Office between Communications should identify both Title section is amended to read
9:00 a.m. and 5:00 p.m., Monday docket numbers and be submitted in ‘‘Proposed Revocation of Class D and E
through Friday, except Federal holidays. triplicate to the address listed above. Airspace; Independence, KS’’.
The Docket Office (telephone 1–800– Commenters wishing the FAA to Class D and E airspace areas are
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
647–5527) is on the ground floor of the acknowledge receipt of their comments published in Paragraph 5000 and 6002,
building at the above address. on this notice must submit with those respectively, of FAA Order 7400.9Y,
FAA Order 7400.9Y, Airspace comments a self-addressed, stamped dated August 6, 2014, and effective
Designations and Reporting Points, and postcard on which the following September 15, 2014, which is
subsequent amendments can be viewed statement is made: ‘‘Comments to incorporated by reference in 14 CFR
online at http://www.faa.gov/air_traffic/ Docket No. FAA–2014–0565/Airspace 71.1. The Class D and E airspace
publications/. The Order is also Docket No. 14–ACE–7.’’ The postcard designations listed in this document
available for inspection at the National will be date/time stamped and returned will be published subsequently in the
Archives and Records Administration to the commenter. Order.
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Document Created: 2018-02-21 10:24:29
Document Modified: 2018-02-21 10:24:29
| 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 June 22, 2015. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. | |
| FR Citation | 80 FR 26492 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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