Airworthiness Directives; Airbus Airplanes, 17007-17010 [2015-07281]

Download as PDF Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Amend § 39.13 by adding the following new airworthiness directive (AD): ■ Gulfstream Aerospace Corporation: Docket No. FAA–2015–0677; Directorate Identifier 2013–NM–244–AD. (a) Comments Due Date We must receive comments by May 15, 2015. (b) Affected ADs None. (c) Applicability This AD applies to all Gulfstream Aerospace Corporation Model GVI airplanes, certificated in any category. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (d) Subject Air Transport Association (ATA) of America Code 36, Pneumatic. (e) Unsafe Condition This AD was prompted by reports of corrosion on in-service air non-return valves. We are issuing this AD to ensure the flightcrew is provided with procedures to mitigate the risks associated with failure of the high pressure (HP) Stage 5 air non-return valve. Failure of the HP Stage 5 air nonreturn valve in the open position could result in engine instability and uncommanded inflight shutdown. VerDate Sep<11>2014 18:18 Mar 30, 2015 Jkt 235001 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Revision of the Airplane Flight Manual (AFM) Within 30 days after the effective date of this AD: Revise the Emergency Procedures section of the AFM by inserting Section 04– 08–20, Normal Airstart-Automatic; Section 04–08–30, Manual Airstart-Starter Assist; and Section 04–08–40, Manual AirstartWindmilling; of Chapter 04, Emergency Procedures; of the Gulfstream GVI (G650) AFM, Document Number GAC–AC–G650– OPS–0001, Revision 5, dated August 12, 2013. (h) Revision of Maintenance or Inspection Program Within 30 days after the effective date of this AD: Revise the airplane maintenance manual or inspection program, as applicable, by incorporating the requirement for the HP Stage 5 air non-return valve from Section 05– 10–10, Airworthiness Limitations, of Chapter 05, Time Limits/Maintenance Checks, of the Gulfstream GVI (G650) Maintenance Manual (MM), Revision 4, dated September 30, 2013. The initial compliance time for replacement of the HP Stage 5 air non-return valve is at the applicable time specified in Section 05– 10–10, Airworthiness Limitations, of Chapter 05, Time Limits/Maintenance Checks, of the Gulfstream GVI (G650) MM, Revision 4, dated September 30, 2013, or within 30 days after the effective date of this AD, whichever occurs later. (i) No Alternative Actions or Intervals After the maintenance or inspection program has been revised, as required by paragraph (h) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance in accordance with the procedures specified in paragraph (j) of this AD. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Atlanta Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (k)(1) of this AD. (2) 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. (k) Related Information (1) For more information about this AD, contact Eric Potter, Aerospace Engineer, Propulsion and Services Branch, ACE–118A, FAA, Atlanta ACO, 1701 Columbia Avenue, College Park, GA 30337; phone: 404–474– PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 17007 5583; fax: 404–474–5606; email: eric.potter@ faa.gov. (2) For service information identified in this AD, contact Gulfstream Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, GA 31402–2206; telephone 800–810–4853; fax 912–965–3520; email pubs@gulfstream.com; Internet http:// www.gulfstream.com/product_support/ technical_pubs/pubs/index.htm. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on March 19, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–07301 Filed 3–30–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0678; Directorate Identifier 2013–NM–207–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2013–13– 04, for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2013–13–04 currently requires installing a power interruption protection circuit for the landing gear control interface unit (LGCIU). Since we issued AD 2013–13–04, we have determined that additional work is necessary to adequately address the identified unsafe condition. This proposed AD would require a new modification of any previously modified LGCIU. This proposed AD would also require revising the maintenance or inspection program to reduce a certain functional check interval. This proposed AD also adds airplanes to the applicability. We are proposing this AD to prevent untimely unlocking and/or retraction of the nose landing gear (NLG), which, while on the ground, could result in injury to ground personnel and damage to the airplane. DATES: We must receive comments on this proposed AD by May 15, 2015. ADDRESSES: You may send comments by any of the following methods: SUMMARY: E:\FR\FM\31MRP1.SGM 31MRP1 17008 Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules • 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 AD, contact Airbus, Airworthiness Office—EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airwortheas@airbus.com; 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– 0678; 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: asabaliauskas on DSK5VPTVN1PROD with PROPOSALS 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–2015–0678; Directorate Identifier 2013–NM–207–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy VerDate Sep<11>2014 18:18 Mar 30, 2015 Jkt 235001 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 14, 2013, we issued AD 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013). AD 2013–13– 04 requires actions intended to address an unsafe condition on certain Airbus Model A318, A319, A320, and A321 series airplanes. Since we issued AD 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013), the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2013–0202, dated September 5, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for Airbus Model A318–111, –112, –121, and –122 airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. The MCAI states: After a push back from the gate, an A320 aeroplane was preparing to initiate taxi, when an uncommanded nose landing gear (NLG) retraction occurred, causing the nose of the aeroplane to hit the ground. Investigations revealed that the retraction was caused by a combination of a power interruption to Landing Gear Control and Interface Units (LGCIU) and an internal hydraulic leak through the landing gear (LG) selector valve 40GA. Deeper investigations have revealed that LGCIU power interruption appears during engine start at each flight. Even though no incident has been reported in service, it has been determined that a non-compliance to the safety objective exists when combined with a dormant single failure of the selector valve seal leaking. This condition, if not corrected, could lead to further incidents of untimely unlocking and/or retraction of the NLG which, while on the ground, could result in injury to ground personnel and damage to the aeroplane. To address the possible hydraulic leak of the LG selector valve, EASA issued AD 2007– 0065 [http://ad.easa.europa.eu/blob/easa_ ad_2007_0065.pdf/AD_2007-0065] currently at Revision 2. To address the risk of untimely unlocking and/or retraction of the NLG, EASA issued AD 2011–0202 [http://ad.easa.europa.eu/ blob/easa_ad_2011_0202.pdf/AD_2011-0202] to require installation of a power interruption PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 protection circuit to the LGCIU and accomplishment of associated modifications. Since that [EASA] AD was issued, it has been discovered that additional work is necessary to adequately correct this unsafe condition and consequently, Airbus issued Service Bulletin (SB) A320–32–1346 to Revision 05. An update of the maintenance programme is required as well, following the required modification. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2011–0202, which is superseded, and requires certain additional actions, as defined in the revised Airbus SB, as applicable to aeroplane model, and an update of the approved maintenance programme. The additional actions include a new modification of any previously modified LGCIU, and reducing a certain functional check interval. This proposed AD also adds airplanes on which Airbus modification 37866 has been embodied in production to the applicability. 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– 0678. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–32–1346, Revision 05, dated January 13, 2012. The service information describes procedures for modifying the LGCIU. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. This service information is reasonably available; see ADDRESSES for ways to access this service information. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Costs of Compliance We estimate that this proposed AD affects 851 airplanes of U.S. registry. The actions required by AD 2013–13– 04, Amendment 39–17492 (78 FR 41286, July 10, 2013), take about 48 work-hours per product, at an average labor rate of $85 per work-hour. Required parts will cost about $8,220 E:\FR\FM\31MRP1.SGM 31MRP1 Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules per product. Based on these figures, the estimated cost of the actions that are required by AD 2013–13–04 is $12,300 per product. We estimate that it would take about 46 work-hours per product to comply with the new modification in this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $9,650 per product. Based on these figures, we estimate the cost of the new modification on U.S. operators to be $11,539,560 or $13,560 per product. We estimate that it would take about 1 work-hour per product to revise the maintenance or inspection program in this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of revising the maintenance program on U.S. operators to be $72,335 or $85 per product. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS 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 VerDate Sep<11>2014 18:18 Mar 30, 2015 Jkt 235001 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013), and adding the following new AD: ■ Airbus: Docket No. FAA–2015–0678; Directorate Identifier 2013–NM–207–AD. (a) Comments Due Date We must receive comments by May 15, 2015. (b) Affected ADs This AD replaces AD 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013). (c) Applicability (1) This AD applies to Airbus Model A318– 111, –112, –121, and –122 airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes; certificated in any category; all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Reason This AD was prompted by a determination that additional work is necessary to adequately address the identified unsafe condition. We are issuing this AD to prevent untimely unlocking and/or retraction of the nose landing gear (NLG), which, while on the ground, could result in injury to ground personnel and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 17009 (g) Retained Modification This paragraph restates the requirements of paragraph (g) of AD 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013). For all airplanes except airplanes on which Airbus modification 37866 has been embodied in production: At the applicable compliance time specified in paragraph (g)(1) or (g)(2) of this AD: Install a power interruption protection circuit for the landing gear control interface unit (LGCIU), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 32–1346, Revision 04, including Appendices 01 and 02, dated April 22, 2011 (for Model A318, A319, A320, and A321 series airplanes other than the Model A319CJ (corporate jet) airplanes); or Airbus Service Bulletin A320– 32–1349, Revision 03, including Appendix 1, dated October 5, 2011 (for Model A319CJ (corporate jet) airplanes). (1) For airplanes that have embodied Airbus Modification 38947 specified in Airbus Service Bulletin A320–32–1348 during production or in service: Within 72 months after August 14, 2013 (the effective date of AD 2013–13–04, Amendment 39– 17492 (78 FR 41286, July 10, 2013)). (2) For all airplanes other than those identified in paragraph (g)(1) of this AD: Within 60 months after August 14, 2013 (the effective date of AD 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013)). (h) Retained Re-Identification of Identification Plates This paragraph restates the requirements of paragraph (h) of AD 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013). For airplanes on which the installation required by paragraph (g) of this AD has been done before August 14, 2013 (the effective date of AD 2013–13–04, Amendment 39– 17492 (78 FR 41286, July 10, 2013)) using Airbus Service Bulletin A320–32–1346, dated December 4, 2008 (for Model A318, A319, A320, and A321 series airplanes other than Model A319CJ (corporate jet) airplanes): Within the applicable times specified in paragraphs (g)(1) and (g)(2) of this AD, reidentify the identification plates, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 32–1346, Revision 04, including Appendices 01 and 02, dated April 22, 2011 (for Model A318, A319, A320, and A321 series airplanes other than Model A319CJ (corporate jet) airplanes). (i) New Modification For airplanes identified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD except airplanes on which Airbus modification 37866 has been embodied in production: Modify the LGCIU at the applicable time specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1346, Revision 05, dated January 13, 2012, or Airbus Service Bulletin A320–32–1349, Revision 03, including Appendix 1, dated October 5, 2011 (for Model A319CJ (corporate jet) airplanes). Accomplishing the modification in this paragraph terminates the actions required by paragraphs (g) and (h) of this AD. E:\FR\FM\31MRP1.SGM 31MRP1 17010 Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules (1) For airplanes on which any LG selector valve having part number (P/N) 114079019 is installed and that have embodied Airbus Modification 38947 specified in Airbus Service Bulletin A320–32–1348 during production or in service: Modify the LGCIU within 72 months after the effective date of this AD. (2) For airplanes on which any LG selector valve 40GA having a part number listed in paragraphs (i)(2)(i) through (i)(2)(xii) of this AD, provided the valve has the marking ‘‘DI’’ or ‘‘DI–BE’’ recorded on its amendment plates: Modify the LGCIU within 72 months after the effective date of this AD. (i) P/N 114079001. (ii) P/N 114079005. (iii) P/N 114079009. (iv) P/N 114079013. (v) P/N 114079001A. (vi) P/N 114079005A. (vii) P/N 114079009A. (viii) P/N114079015. (ix) P/N 114079001AB. (x) P/N 114079005AB. (xi) P/N 114079009AB. (xii) P/N 114079017. (3) For all airplanes other than those identified in paragraphs (i)(1) and (i)(2) of this AD: Modify the LGCIU within 60 months after the effective date of this AD. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (j) New Modification for Airplanes Previously Modified For airplanes that have been modified as of the effective date of this AD as specified in the applicable service information identified in paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this AD, except airplanes on which Airbus modification 37866 has been embodied in production: Within 72 months after the effective date of this AD, do the additional modification of the LGCIU, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1346, Revision 05, dated January 13, 2012. (1) Airbus Service Bulletin A320–32–1346, Revision 01, dated October 27, 2009, which is not incorporated by reference in this AD. (2) Airbus Service Bulletin A320–32–1346, Revision 02, dated November 4, 2009, which is not incorporated by reference in this AD. (3) Airbus Service Bulletin A320–32–1346, Revision 03, dated January 7, 2010, which is not incorporated by reference in this AD. (4) Airbus Service Bulletin A320–32–1346, including Appendices 01 and 02, Revision 04, dated April 22, 2011, which is incorporated by reference in AD 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013). (k) New Maintenance or Inspection Program Revision Before further flight after accomplishing the actions specified in paragraph (i) or (j) of this AD or within 7 days after the effective date of this AD, whichever occurs later: Revise the maintenance or inspection program, as applicable, to incorporate Task 32.30.00.17, ‘‘Functional Check of LGCIU Power Supply Relays,’’ of Section C–32 of Section C, Systems and Powerplant, of the Airbus A318/A319/A320/A321 Maintenance Review Board Report, Revision 18, dated March 2013. The initial compliance time is VerDate Sep<11>2014 18:18 Mar 30, 2015 Jkt 235001 within 4,000 flight hours after accomplishing the additional modification of the LGCIU. (l) Credit for Previous Actions This paragraph provides credit for A319 Corporate Jet airplanes for the modification required by paragraph (g) of this AD if that modification was performed before the effective date of this AD using Airbus Service Bulletin A320–32–1349, dated December 4, 2008; Airbus Service Bulletin A320–32–1349, Revision 01, dated August 31, 2009; or Airbus Service Bulletin A320–32–1349, Revision 02, dated June 16, 2010. (m) 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: 9-ANM-116AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter must specifically reference this AD. (2) AMOCs approved previously for AD 2013–13–04, Amendment 39–17492 (78 FR 41286, July 10, 2013) are approved as AMOCs for the corresponding provisions of this AD. (3) 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 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. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0202, dated September 5, 2013, 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–2015–0678. (2) For service information identified in this AD, contact Airbus, Airworthiness Office—EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, Transport PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on March 20, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–07281 Filed 3–30–15; 8:45 am] BILLING CODE 4910–13–P ENVIRONMENTAL PROTECTION AGENCY 40 CFR Part 52 [EPA–R09–OAR–2015–0165; FRL–9925–31– Region 9] Promulgation of Air Quality Implementation Plans; Arizona; Regional Haze Federal Implementation Plan; Reconsideration Environmental Protection Agency. ACTION: Proposed rule. AGENCY: The Environmental Protection Agency (EPA) is proposing to revise part of the Arizona Regional Haze (RH) Federal Implementation Plan (FIP) applicable to the Coronado Generating Station (Coronado). In response to a petition for reconsideration from the Salt River Project Agricultural Improvement and Power District (SRP), the owner/operator of Coronado, we are proposing to replace a plant-wide compliance method with a unit-specific compliance method for determining compliance with the best available retrofit technology (BART) emission limits for nitrogen oxides (NOX) from Units 1 and 2 at Coronado. While the plant-wide limit for the NOX emissions from Units 1 and 2 were established as 0.065 lb/MMBtu, we are proposing a unit-specific limit of 0.065 lb/MMBtu for Unit 1 and 0.080 lb/MMBtu for Unit 2. In addition, we are proposing to revise the work practice standard in the FIP for Coronado. Finally, we are proposing to remove the affirmative defense for malfunctions from the Arizona RH FIP, which applies to both Coronado and the Cholla Power Plant (Cholla). SUMMARY: Written comments must be submitted to the designated contact on or before May 15, 2015. Requests for a public hearing must be received on or before April 15, 2015. ADDRESSES: Submit your comments, identified by docket number EPA–R09– OAR–2015–0165, by one of the following methods: DATES: E:\FR\FM\31MRP1.SGM 31MRP1

Agencies

[Federal Register Volume 80, Number 61 (Tuesday, March 31, 2015)]
[Proposed Rules]
[Pages 17007-17010]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-07281]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0678; Directorate Identifier 2013-NM-207-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2013-13-
04, for certain Airbus Model A318, A319, A320, and A321 series 
airplanes. AD 2013-13-04 currently requires installing a power 
interruption protection circuit for the landing gear control interface 
unit (LGCIU). Since we issued AD 2013-13-04, we have determined that 
additional work is necessary to adequately address the identified 
unsafe condition. This proposed AD would require a new modification of 
any previously modified LGCIU. This proposed AD would also require 
revising the maintenance or inspection program to reduce a certain 
functional check interval. This proposed AD also adds airplanes to the 
applicability. We are proposing this AD to prevent untimely unlocking 
and/or retraction of the nose landing gear (NLG), which, while on the 
ground, could result in injury to ground personnel and damage to the 
airplane.

DATES: We must receive comments on this proposed AD by May 15, 2015.

ADDRESSES: You may send comments by any of the following methods:

[[Page 17008]]

     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 AD, contact Airbus, 
Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; 
email account.airworth-eas@airbus.com; 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-
0678; 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-2015-0678; 
Directorate Identifier 2013-NM-207-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 14, 2013, we issued AD 2013-13-04, Amendment 39-17492 (78 
FR 41286, July 10, 2013). AD 2013-13-04 requires actions intended to 
address an unsafe condition on certain Airbus Model A318, A319, A320, 
and A321 series airplanes. Since we issued AD 2013-13-04, Amendment 39-
17492 (78 FR 41286, July 10, 2013), the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, has issued EASA Airworthiness Directive 2013-0202, 
dated September 5, 2013 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for Airbus Model A318-111, -112, -121, and -122 
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; 
and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes. The MCAI states:

    After a push back from the gate, an A320 aeroplane was preparing 
to initiate taxi, when an uncommanded nose landing gear (NLG) 
retraction occurred, causing the nose of the aeroplane to hit the 
ground. Investigations revealed that the retraction was caused by a 
combination of a power interruption to Landing Gear Control and 
Interface Units (LGCIU) and an internal hydraulic leak through the 
landing gear (LG) selector valve 40GA.
    Deeper investigations have revealed that LGCIU power 
interruption appears during engine start at each flight. Even though 
no incident has been reported in service, it has been determined 
that a non-compliance to the safety objective exists when combined 
with a dormant single failure of the selector valve seal leaking.
    This condition, if not corrected, could lead to further 
incidents of untimely unlocking and/or retraction of the NLG which, 
while on the ground, could result in injury to ground personnel and 
damage to the aeroplane.
    To address the possible hydraulic leak of the LG selector valve, 
EASA issued AD 2007-0065 [http://ad.easa.europa.eu/blob/easa_ad_2007_0065.pdf/AD_2007-0065] currently at Revision 2.
    To address the risk of untimely unlocking and/or retraction of 
the NLG, EASA issued AD 2011-0202 [http://ad.easa.europa.eu/blob/easa_ad_2011_0202.pdf/AD_2011-0202] to require installation of a 
power interruption protection circuit to the LGCIU and 
accomplishment of associated modifications.
    Since that [EASA] AD was issued, it has been discovered that 
additional work is necessary to adequately correct this unsafe 
condition and consequently, Airbus issued Service Bulletin (SB) 
A320-32-1346 to Revision 05. An update of the maintenance programme 
is required as well, following the required modification.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2011-0202, which is superseded, and requires 
certain additional actions, as defined in the revised Airbus SB, as 
applicable to aeroplane model, and an update of the approved 
maintenance programme.

    The additional actions include a new modification of any previously 
modified LGCIU, and reducing a certain functional check interval. This 
proposed AD also adds airplanes on which Airbus modification 37866 has 
been embodied in production to the applicability. 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-2015-0678.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-32-1346, Revision 05, dated 
January 13, 2012. The service information describes procedures for 
modifying the LGCIU. The actions described in this service information 
are intended to correct the unsafe condition identified in the MCAI. 
This service information is reasonably available; see ADDRESSES for 
ways to access this service information.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 851 airplanes of U.S. 
registry.
    The actions required by AD 2013-13-04, Amendment 39-17492 (78 FR 
41286, July 10, 2013), take about 48 work-hours per product, at an 
average labor rate of $85 per work-hour. Required parts will cost about 
$8,220

[[Page 17009]]

per product. Based on these figures, the estimated cost of the actions 
that are required by AD 2013-13-04 is $12,300 per product.
    We estimate that it would take about 46 work-hours per product to 
comply with the new modification in this proposed AD. The average labor 
rate is $85 per work-hour. Required parts would cost about $9,650 per 
product. Based on these figures, we estimate the cost of the new 
modification on U.S. operators to be $11,539,560 or $13,560 per 
product.
    We estimate that it would take about 1 work-hour per product to 
revise the maintenance or inspection program in this proposed AD. The 
average labor rate is $85 per work-hour. Based on these figures, we 
estimate the cost of revising the maintenance program on U.S. operators 
to be $72,335 or $85 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2013-13-04, Amendment 39-17492 (78 FR 41286, July 10, 2013), and adding 
the following new AD:

Airbus: Docket No. FAA-2015-0678; Directorate Identifier 2013-NM-
207-AD.

(a) Comments Due Date

    We must receive comments by May 15, 2015.

(b) Affected ADs

    This AD replaces AD 2013-13-04, Amendment 39-17492 (78 FR 41286, 
July 10, 2013).

(c) Applicability

    (1) This AD applies to Airbus Model A318-111, -112, -121, and -
122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes; Model A320-211, -212, -214, -231, -232, and -233 
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes; certificated in any category; all manufacturer 
serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Reason

    This AD was prompted by a determination that additional work is 
necessary to adequately address the identified unsafe condition. We 
are issuing this AD to prevent untimely unlocking and/or retraction 
of the nose landing gear (NLG), which, while on the ground, could 
result in injury to ground personnel and damage to the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Modification

    This paragraph restates the requirements of paragraph (g) of AD 
2013-13-04, Amendment 39-17492 (78 FR 41286, July 10, 2013). For all 
airplanes except airplanes on which Airbus modification 37866 has 
been embodied in production: At the applicable compliance time 
specified in paragraph (g)(1) or (g)(2) of this AD: Install a power 
interruption protection circuit for the landing gear control 
interface unit (LGCIU), in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-32-1346, Revision 04, 
including Appendices 01 and 02, dated April 22, 2011 (for Model 
A318, A319, A320, and A321 series airplanes other than the Model 
A319CJ (corporate jet) airplanes); or Airbus Service Bulletin A320-
32-1349, Revision 03, including Appendix 1, dated October 5, 2011 
(for Model A319CJ (corporate jet) airplanes).
    (1) For airplanes that have embodied Airbus Modification 38947 
specified in Airbus Service Bulletin A320-32-1348 during production 
or in service: Within 72 months after August 14, 2013 (the effective 
date of AD 2013-13-04, Amendment 39-17492 (78 FR 41286, July 10, 
2013)).
    (2) For all airplanes other than those identified in paragraph 
(g)(1) of this AD: Within 60 months after August 14, 2013 (the 
effective date of AD 2013-13-04, Amendment 39-17492 (78 FR 41286, 
July 10, 2013)).

(h) Retained Re-Identification of Identification Plates

    This paragraph restates the requirements of paragraph (h) of AD 
2013-13-04, Amendment 39-17492 (78 FR 41286, July 10, 2013). For 
airplanes on which the installation required by paragraph (g) of 
this AD has been done before August 14, 2013 (the effective date of 
AD 2013-13-04, Amendment 39-17492 (78 FR 41286, July 10, 2013)) 
using Airbus Service Bulletin A320-32-1346, dated December 4, 2008 
(for Model A318, A319, A320, and A321 series airplanes other than 
Model A319CJ (corporate jet) airplanes): Within the applicable times 
specified in paragraphs (g)(1) and (g)(2) of this AD, re-identify 
the identification plates, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-32-1346, Revision 04, 
including Appendices 01 and 02, dated April 22, 2011 (for Model 
A318, A319, A320, and A321 series airplanes other than Model A319CJ 
(corporate jet) airplanes).

(i) New Modification

    For airplanes identified in paragraphs (i)(1), (i)(2), and 
(i)(3) of this AD except airplanes on which Airbus modification 
37866 has been embodied in production: Modify the LGCIU at the 
applicable time specified in paragraph (i)(1), (i)(2), or (i)(3) of 
this AD, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-32-1346, Revision 05, dated January 13, 
2012, or Airbus Service Bulletin A320-32-1349, Revision 03, 
including Appendix 1, dated October 5, 2011 (for Model A319CJ 
(corporate jet) airplanes). Accomplishing the modification in this 
paragraph terminates the actions required by paragraphs (g) and (h) 
of this AD.

[[Page 17010]]

    (1) For airplanes on which any LG selector valve having part 
number (P/N) 114079019 is installed and that have embodied Airbus 
Modification 38947 specified in Airbus Service Bulletin A320-32-1348 
during production or in service: Modify the LGCIU within 72 months 
after the effective date of this AD.
    (2) For airplanes on which any LG selector valve 40GA having a 
part number listed in paragraphs (i)(2)(i) through (i)(2)(xii) of 
this AD, provided the valve has the marking ``DI'' or ``DI-BE'' 
recorded on its amendment plates: Modify the LGCIU within 72 months 
after the effective date of this AD.
    (i) P/N 114079001.
    (ii) P/N 114079005.
    (iii) P/N 114079009.
    (iv) P/N 114079013.
    (v) P/N 114079001A.
    (vi) P/N 114079005A.
    (vii) P/N 114079009A.
    (viii) P/N114079015.
    (ix) P/N 114079001AB.
    (x) P/N 114079005AB.
    (xi) P/N 114079009AB.
    (xii) P/N 114079017.
    (3) For all airplanes other than those identified in paragraphs 
(i)(1) and (i)(2) of this AD: Modify the LGCIU within 60 months 
after the effective date of this AD.

(j) New Modification for Airplanes Previously Modified

    For airplanes that have been modified as of the effective date 
of this AD as specified in the applicable service information 
identified in paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this 
AD, except airplanes on which Airbus modification 37866 has been 
embodied in production: Within 72 months after the effective date of 
this AD, do the additional modification of the LGCIU, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-32-1346, Revision 05, dated January 13, 2012.
    (1) Airbus Service Bulletin A320-32-1346, Revision 01, dated 
October 27, 2009, which is not incorporated by reference in this AD.
    (2) Airbus Service Bulletin A320-32-1346, Revision 02, dated 
November 4, 2009, which is not incorporated by reference in this AD.
    (3) Airbus Service Bulletin A320-32-1346, Revision 03, dated 
January 7, 2010, which is not incorporated by reference in this AD.
    (4) Airbus Service Bulletin A320-32-1346, including Appendices 
01 and 02, Revision 04, dated April 22, 2011, which is incorporated 
by reference in AD 2013-13-04, Amendment 39-17492 (78 FR 41286, July 
10, 2013).

(k) New Maintenance or Inspection Program Revision

    Before further flight after accomplishing the actions specified 
in paragraph (i) or (j) of this AD or within 7 days after the 
effective date of this AD, whichever occurs later: Revise the 
maintenance or inspection program, as applicable, to incorporate 
Task 32.30.00.17, ``Functional Check of LGCIU Power Supply Relays,'' 
of Section C-32 of Section C, Systems and Powerplant, of the Airbus 
A318/A319/A320/A321 Maintenance Review Board Report, Revision 18, 
dated March 2013. The initial compliance time is within 4,000 flight 
hours after accomplishing the additional modification of the LGCIU.

(l) Credit for Previous Actions

    This paragraph provides credit for A319 Corporate Jet airplanes 
for the modification required by paragraph (g) of this AD if that 
modification was performed before the effective date of this AD 
using Airbus Service Bulletin A320-32-1349, dated December 4, 2008; 
Airbus Service Bulletin A320-32-1349, Revision 01, dated August 31, 
2009; or Airbus Service Bulletin A320-32-1349, Revision 02, dated 
June 16, 2010.

(m) 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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. The 
AMOC approval letter must specifically reference this AD.
    (2) AMOCs approved previously for AD 2013-13-04, Amendment 39-
17492 (78 FR 41286, July 10, 2013) are approved as AMOCs for the 
corresponding provisions of this AD.
    (3) 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 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.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0202, dated September 5, 
2013, 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-2015-0678.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on March 20, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-07281 Filed 3-30-15; 8:45 am]
 BILLING CODE 4910-13-P