80 FR 40942 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 134 (July 14, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 134 (July 14, 2015)
| Page Range | 40942-40947 | |
| FR Document | 2015-17201 |
[Federal Register Volume 80, Number 134 (Tuesday, July 14, 2015)] [Proposed Rules] [Pages 40942-40947] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-17201] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-2461; Directorate Identifier 2013-NM-202-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) 2009-18- 15 for all Airbus Model A300, A310, and A300 B4-600, B4-600R, and F4- 600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 2009-18-15 currently requires revising the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness (ICA) to require additional life limits and/or replacements for certain main landing gear and nose landing gear components. Since we issued AD 2009-18-15, we have determined that existing maintenance requirements and airworthiness limitations are inadequate to ensure the structural integrity of the airplane. This proposed AD would require revising the maintenance or inspection program to incorporate new maintenance requirements and airworthiness limitations. We are proposing this AD to prevent failure of certain system components, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by August 28, 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 SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this 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- 2461; 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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 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-2015-2461; Directorate Identifier 2013-NM-202-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 August 24, 2009, we issued AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). AD 2009-18-15 requires actions intended to address an unsafe condition for all Airbus Model A300, A310, and A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4- 605R Variant F airplanes (collectively called Model A300-600 series airplanes). Since we issued AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009), we have determined that more restrictive maintenance requirements and airworthiness limitations are necessary. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013-0248, dated October 14, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Model A300, A310, and A300-600 series airplanes. The MCAI states: The airworthiness limitations for Airbus aeroplanes are currently published in Airworthiness Limitations Section (ALS) documents. The mandatory instructions and airworthiness limitations applicable to the Aging Systems Maintenance (ASM) are specified in Airbus A310 or A300-600 ALS Part 4 documents, which are approved by the European Aviation Safety Agency (EASA). EASA AD 2007-0092 [http://ad.easa.europa.eu/blob/easa_ad_2007_0092.pdf/AD_2007-0092] [which corresponds to FAA AD 2009-06-06, Amendment 39-15842 (74 FR 12228, March 24, 2009)] was issued to require compliance to the requirements as specified in these documents. The revision 02 of Airbus A310 and Airbus A300-600 ALS Part 4 documents introduces more restrictive maintenance requirements and/ or airworthiness limitations. Failure to comply with the instructions of ALS Part 4 could result in an unsafe condition [reduced structural integrity of the airplane.] For the reasons described above, this new [EASA] AD retains the requirements of EASA AD 2007-0092, which is superseded, and requires the implementation of the new or more restrictive maintenance requirements and/or airworthiness limitations as specified in Airbus A310 ALS Part 4, Revision 02, or Airbus A300-600 ALS Part 4, Revision 02, as applicable to aeroplane type/model. 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- 2461. [[Page 40943]] Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information, which describes procedures for revising the maintenance or inspection program to incorporate new maintenance requirements and airworthiness limitations. For Model A300 series airplanes: ``Sub-part 1-2: Life Limits,'' and ``Sub-part 1-3: Demonstrated fatigue lives'' of Part 1, ``Safe Life Airworthiness Limitation Items,'' Revision 01, dated September 5, 2013, of the Airbus Model A300 Airworthiness Limitations Section. For Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes): ``Sub-part 1-2: Life Limits,'' and ``Sub-part 1-3: Demonstrated fatigue lives'' of Part 1, ``Safe Life Airworthiness Limitation Items,'' Revision 01, dated September 5, 2013, of the Airbus Model A300-600 Airworthiness Limitations Section. For Model A310 series airplanes: ``Sub-part 1-2: Life Limits,'' and ``Sub-part 1-3: Demonstrated fatigue lives'' of Part 1, ``Safe Life Airworthiness Limitation Items,'' Revision 01, dated September 5, 2013, of the Airbus Model A310 Airworthiness Limitations Section. 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 177 airplanes of U.S. registry. The ALS revision required by AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009), takes about 1 work-hour 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 2009-18-15 is $85 per product. We also estimate that it would take about 1 work-hour per product to comply with the new ALS revision of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $15,045, 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 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009), and adding the following new AD: Airbus: Docket No. FAA-2015-2461; Directorate Identifier 2013-NM- 202-AD. (a) Comments Due Date We must receive comments by August 28, 2015. (b) Affected ADs This AD replaces AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). (c) Applicability This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2- 203, B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R, and A300 C4-605R Variant F airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes; certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America 32, Landing Gear. (e) Reason This AD was prompted by a determination that existing maintenance requirements and airworthiness limitations are inadequate to ensure the structural integrity of the airplane. We are issuing this AD to prevent failure of certain system components, 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 Revision of Airworthiness Limitation Section (ALS) This paragraph restates the requirements of paragraph (h) of AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). For Model A300, A310, and A300-600 series airplanes: Within 3 months after October 27, 2009 (the effective date of AD 2009-18-15), revise the ALS of the instructions for continued airworthiness (ICA) to incorporate the applicable document [[Page 40944]] listed in paragraph (g)(1), (g)(2), or (g)(3) of this AD. Accomplishing the actions specified in the applicable document satisfies the requirements of paragraph A. of AD 84-02-04, Amendment 39-4795. (1) For Model A300 series airplanes: Incorporate the applicable document listed in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (i) Section 05-10-00, Revision 28, dated February 27, 1998, of Chapter 05, ``Service Life Limits and Maintenance Checks,'' of the Airbus A300 Aircraft Maintenance Manual, except that the parts listed in table 1 to paragraph (g) of this AD are subject to the life limits defined in the document listed in paragraph (g)(1)(ii) of this AD. (ii) ``Sub-part 1-2: Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives'' of Part 1, ``Safe Life Airworthiness Limitation Items,'' dated September 6, 2007, of the Airbus A300 ALS. Table 1 to Paragraph (g) of This AD--Parts Subject to the Life Limits Specified in the Document Identified in Paragraph (g)(1)(ii) of This AD ------------------------------------------------------------------------ Part No. (P/N) Part name ------------------------------------------------------------------------ P/N C61643-2, P/N C61643-4, P/N C61643-5.. Main landing gear (MLG) shock absorber end fitting. P/N A32210001205xx........................ Nose landing gear (NLG) pintle pin. P/N C62037-1.............................. NLG shock absorber bottom. P/N 196-0328-501.......................... Cross beam (Pratt & Whitney forward engine mount). ------------------------------------------------------------------------ (2) For Model A310 series airplanes: Incorporate ``Sub-part 1-2: Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives'' of Part 1, ``Safe Life Airworthiness Limitation Items,'' dated December 21, 2006, of the Airbus A310 ALS. (3) For Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes): Incorporate ``Sub-part 1-2: Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives'' of Part 1, ``Safe Life Airworthiness Limitation Items,'' dated December 21, 2006, of the Airbus A300-600 ALS. (h) Retained Initial Compliance Times and Repetitive Inspections This paragraph restates the requirements of paragraph (i) of AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). Do the replacement at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, except as provided by paragraph (i) of this AD. The replacement must be done thereafter within the interval specified in the applicable document identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. (1) For any life limitation/task that has been complied with before October 27, 2009 (the effective date of AD 2009-18-15, Amendment 39-16011), in accordance with the applicable document listed in paragraph (g)(1), (g)(2), or (g)(3) of this AD, or in accordance with paragraph (g) of AD 2009-18-15, use the last accomplishment of each limitation/task as a starting point for accomplishing each corresponding limitation/task required by this AD. (2) For any life limitation/task that has not been complied with before October 27, 2009 (the effective date of AD 2009-18-15, Amendment 39-16011), in accordance with the applicable document listed in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, or in accordance with paragraph (g) of AD 2009-18-15, the initial compliance time starts from the date of initial entry into service as defined in the applicable document. (i) Retained Special Compliance Times This paragraph restates the requirements of paragraph (j) of AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). For any airplane on which the history of accumulated landings is partial or unknown, or where the history of application details (airplane type, model, weight variant, etc.) is partial or unknown, with or without using the information in Airbus Service Information Letter 32-118, Revision 02, dated October 24, 2007: Parts listed in figure 1 to paragraph (i) of this AD must be replaced at the associated compliance time. The replacement must be done thereafter at the interval specified in the applicable document(s) specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. Note 1 to paragraph (i) of this AD: Airbus Service Information Letter 32-118, Revision 02, dated October 24, 2007, provides operators with guidance on the means to assign a conservative calculated life to parts whose history of accumulated landings is partial or unknown; and to select the limitations applicable to parts whose history of application details (aircraft type, aircraft model, weight variant, etc.) is partial or unknown. Figure 1 to Paragraph (i) of This AD--Special Compliance Times -------------------------------------------------------------------------------------------------------------------------------------------------------- Aircraft type applicability Compliance time (whichever occurs ---------------------------------------------------- first after the ``start date'') Designation A300 A310 A300-600 Start date --------------------------------------- ------------------------------------------ P/N X X X Landings Calendar time -------------------------------------------------------------------------------------------------------------------------------------------------------- MAIN LANDING GEAR -------------------------------------------------------------------------------------------------------------------------------------------------------- A32140032200xx X December 13, 2007.......... 13,500............ 9 years. A32140056200xx X December 13, 2007.......... 13,500............ 9 years. A32140056202xx X December 13, 2007.......... 13,500............ 9 years. Aft pintle pin................. A32140057200xx X December 13, 2007.......... 13,500............ 9 years. A32140057202xx X X December 13, 2007.......... 13,500............ 9 years. A32140062000xx X December 13, 2007.......... 13,500............ 9 years. A32140063000xx X X December 13, 2007.......... 13,500............ 9 years. A32140036200xx X December 13, 2007.......... 13,500............ 9 years. A32140036202xx X December 13, 2007.......... 13,500............ 9 years. A32140036204xx X December 13, 2007.......... 13,500............ 9 years. A32140036206xx X December 13, 2007.......... 13,500............ 9 years. Half ball housing (Fwd pintle A32140042200xx X X December 13, 2007.......... 13,500............ 9 years. bearing). A32140042202xx X X December 13, 2007.......... 13,500............ 9 years. A32140068002xx X December 13, 2007.......... 13,500............ 9 years. A32140068004xx X December 13, 2007.......... 13,500............ 9 years. A32140069002xx X X December 13, 2007.......... 13,500............ 9 years. A32140069004xx X X December 13, 2007.......... 13,500............ 9 years. Ball (Fwd pintle pin).......... A32140012202xx X December 13, 2007.......... 13,500............ 9 years. A32140043202xx X X December 13, 2007.......... 13,500............ 9 years. [[Page 40945]] Pin (Multiple link/Frame 50)... A53833451200xx X December 13, 2007.......... 13,500............ 9 years.. A53833451206xx X December 13, 2007.......... 13,500............ 9 years. A53834451200xx X December 13, 2007.......... 13,500............ 9 years. A53834451202xx X X April 25, 2007............. 13,500............ 9 years. Pin (Drop link/Frame 50)....... A53811122200xx X April 25, 2007............. 18,000............ 9 years. -------------------------------------------------------------------------------------------------------------------------------------------------------- MLG Barrel Assembly -------------------------------------------------------------------------------------------------------------------------------------------------------- Upper torque link pin nut...... 00-200-402 X December 13, 2007.......... N/A............... 30 months. SL40089 X December 13, 2007.......... N/A............... 30 months. SL40089P X December 13, 2007.......... N/A............... 30 months. SL40123 X December 13, 2007.......... N/A............... 30 months. SL40123P X X X April 25, 2007............. N/A............... 30 months. Torque link medium pin nut..... 00-200-358 X December 13, 2007.......... N/A............... 30 months. SL40114P X X April 25, 2007............. N/A............... 30 months. SL40132 X December 13, 2007.......... N/A............... 30 months. SL40132P X X April 25, 2007............. N/A............... 30 months. Attaching fitting pin.......... C62311-1 X December 13, 2007.......... 13,500............ 9 years. C62311-20 X X April 25, 2007............. 13,500............ 9 years. Pin (Connecting rod/Upper rod). C65815 X December 13, 2007.......... 13,500............ 9 years. C65815-1 X December 13, 2007.......... 13,500............ 9 years. C65815-20 X December 13, 2007.......... 13,500............ 9 years. C66472 X December 13, 2007.......... 13,500............ 9 years. C66472-1 X December 13, 2007.......... 13,500............ 9 years. C66472-20 X X April 25, 2007............. 13,500............ 9 years. D52751 X April 25, 2007............. 18,000............ 9 years. -------------------------------------------------------------------------------------------------------------------------------------------------------- MLG Shock Absorber Assembly -------------------------------------------------------------------------------------------------------------------------------------------------------- Lower torque link pin nut...... 00-200-402 X December 13, 2007.......... N/A............... 30 months. SL40089 X December 13, 2007.......... N/A............... 30 months. SL40089P X December 13, 2007.......... N/A............... 30 months. SL40123 X December 13, 2007.......... N/A............... 30 months. SL40123P X X X April 25, 2007............. N/A............... 30 months. -------------------------------------------------------------------------------------------------------------------------------------------------------- Bogie beam pivot pin nut....... SL40054 X December 13, 2007.......... at next removal/installation.1 2 SL40054P X X April 25, 2007............. at next removal/installation.1 2 SL40413P X April 25, 2007............. at next removal/installation.1 2 -------------------------------------------------------------------------------------------------------------------------------------------------------- MLG Lock Link Assembly -------------------------------------------------------------------------------------------------------------------------------------------------------- Lock link medium pin........... C61485-1 X December 13, 2007.......... N/A............... 30 months. C61485-20 X X April 25, 2007............. N/A............... 30 months. -------------------------------------------------------------------------------------------------------------------------------------------------------- NOSE LANDING GEAR -------------------------------------------------------------------------------------------------------------------------------------------------------- Pintle pin..................... A32210079200xx X X X April 25, 2007............. 13,500............ 9 years. -------------------------------------------------------------------------------------------------------------------------------------------------------- NLG Telescopic Strut Assembly -------------------------------------------------------------------------------------------------------------------------------------------------------- Nut (Cylinder/Locking cylinder) C61375 X X April 25, 2007............. 13,500............ 9 years. D55955 X X X April 25, 2007............. 13,500............ 9 years. Locking sleeve................. C61389 X X December 13, 2007.......... 13,200............ 9 years. C61389-1 X X X April 25, 2007............. 13,500............ 9 years. -------------------------------------------------------------------------------------------------------------------------------------------------------- NLG Barrel Assembly -------------------------------------------------------------------------------------------------------------------------------------------------------- Pin (Clevis/Telescopic strut).. C62231-1 X December 13, 2007.......... 13,200............ 9 years. C62231-2 X December 13, 2007.......... 13,200............ 9 years. [[Page 40946]] C62231-20 X X X April 25, 2007............. 13,500............ 9 years. D56530 X X X April 25, 2007............. 13,500............ 9 years. Lower pin (Link/Clevis)........ C62268-1 X December 13, 2007.......... 13,200............ 9 years. C62268-2 X December 13, 2007.......... 13,200............ 9 years. C62268-20 X X X April 25, 2007............. 13,500............ 9 years. Link (Clevis/Barrel)........... C62230-1 X X X April 25, 2007............. 13,500............ 9 years. D56526 X X X April 25, 2007............. 13,500............ 9 years. Upper pin (Link/Barrel)........ C62267-1 X December 13, 2007.......... 13,200............ 9 years. C62267-2 X December 13, 2007.......... 13,200............ 9 years. C62267-20 X X X April 25, 2007............. 13,500............ 9 years. -------------------------------------------------------------------------------------------------------------------------------------------------------- End fitting pin nut............ D68062 X X X December 13, 2007.......... at next removal/installation.\2\ MS17825-6 X X X December 13, 2007.......... at next removal/installation.\2\ End fitting pin................ AN6-17 X X X December 13, 2007.......... at next removal/installation.\2\ D61183 X X X December 13, 2007.......... at next removal/installation.\2\ D68063 X X X December 13, 2007.......... at next removal/installation.\2\ NAS1306-22D X X X December 13, 2007.......... at next removal/installation.\2\ -------------------------------------------------------------------------------------------------------------------------------------------------------- End fitting.................... C62032 X X X April 25, 2007............. 13,500............ 9 years. C62032-1 X X X April 25, 2007............. 13,500............ 9 years. Rack........................... C61453 X December 13, 2007.......... 13,200............ 9 years. C61453-1 X X X April 25, 2007............. 13,500............ 9 years. C61453-20 X X X April 25, 2007............. 13,500............ 9 years. C61453-40 X X X April 25, 2007............. 13,500............ 9 years. C61453-41 X X X April 25, 2007............. 13,500............ 9 years. Torque link pin (Upper & Lower) C62223-1 X December 13, 2007.......... 13,200............ 9 years. C62223-20 X X X April 25, 2007............. 13,500............ 9 years. Torque link medium pin nut..... SL40110P X X X April 25, 2007............. N/A............... 30 months. -------------------------------------------------------------------------------------------------------------------------------------------------------- NLG Shock Absorber Assembly -------------------------------------------------------------------------------------------------------------------------------------------------------- Wheel axle nut................. C62879 X X X April 25, 2007............. 4,000............. 24 months. -------------------------------------------------------------------------------------------------------------------------------------------------------- Upper cam dowel................ C62270 X X X December 13, 2007.......... at next removal/installation. -------------------------------------------------------------------------------------------------------------------------------------------------------- Upper cam...................... C62034-1 X X X April 25, 2007............. 13,500............ 9 years. Lower cam...................... C62035 X X X April 25, 2007............. 13,500............ 9 years. Restrictor..................... C62036 X December 13, 2007.......... 13,200............ 9 years. C62036-1 X December 13, 2007.......... 13,200............ 9 years. C62036-2 X December 13, 2007.......... 13,200............ 9 years. C67863 X December 13, 2007.......... 13,200............ 9 years. C67863-1 X X X April 25, 2007............. 13,500............ 9 years. C67863-2 X X X April 25, 2007............. 13,500............ 9 years. C67863-3 X December 13, 2007.......... 13,500............ 9 years. C67863-4 X X X April 25, 2007............. 13,500............ 9 years. -------------------------------------------------------------------------------------------------------------------------------------------------------- Lower cam dowel................ C62866 X X X December 13, 2007.......... at next removal/installation.\2\ Nut (S/A/Barrel)............... C64040 X December 13, 2007.......... at next removal/installation.1 2 C64040-1 X X X December 13, 2007.......... at next removal/installation.1 2 -------------------------------------------------------------------------------------------------------------------------------------------------------- \1\ When the nut is temporarily removed and reinstalled for the purpose of performing maintenance outside a workshop, no replacement is required provided the nut's removal and reinstallation are performed on the same assembly and neither the assembly nor the nut accumulates time in service during the period between the removal and reinstallation. \2\ If the removal/installation was done after the start date, but before the effective date of this AD, the compliance time is within 3 months. after October 27, 2009 (the effective date of AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009)). (j) New Requirements of This AD: Maintenance Program Revision Within 3 months after the effective date of this AD: Revise the maintenance or inspection program, as applicable, to incorporate the applicable limitation, replacement, or inspection specified in paragraph (j)(1), (j)(2), or (j)(3) of this AD, as applicable. Doing any task required by this paragraph terminates the corresponding task required by paragraph (g), (h), and (i) of this AD. (1) For Model A300 series airplanes: Incorporate ``Sub-part 1-2: Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives'' of Part 1, ``Safe Life Airworthiness Limitation Items,'' Revision 01, dated September 5, 2013, of the Airbus A300 ALS. (2) For Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4 605R Variant F airplanes (collectively [[Page 40947]] called Model A300-600 series airplanes): Incorporate ``Sub-part 1-2: Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives'' of Part 1, ``Safe Life Airworthiness Limitation Items,'' Revision 01, dated September 5, 2013, of the Airbus A300-600 ALS. (3) For Model A310 series airplanes: Incorporate ``Sub-part 1-2: Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives'' of Part 1, ``Safe Life Airworthiness Limitation Items,'' dated Revision 01, September 5, 2013, of the Airbus A310 ALS. (k) New Limitation: No Alternative Actions or Intervals After accomplishment of the revision required by paragraph (j) 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 (AMOC) in accordance with the procedures specified in paragraph (l) of this AD. (l) 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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-2125; 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. The AMOC approval letter must specifically reference this AD. (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 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. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013-0248, dated October 14, 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-2015-2461. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on June 25, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-17201 Filed 7-13-15; 8:45 am] BILLING CODE 4910-13-P
![40942 Federal Register / Vol. 80, No. 134 / Tuesday, July 14, 2015 / Proposed Rules
Issued in Washington, DC, on June 30, • Hand Delivery: U.S. Department of substantive verbal contact we receive
2015. Transportation, Docket Operations, about this proposed AD.
Kathleen B. Hogan, M–30, West Building Ground Floor,
Discussion
Deputy Assistant Secretary for Energy Room W12–140, 1200 New Jersey
Efficiency and Renewable Energy. Avenue SE., Washington, DC, between 9 On August 24, 2009, we issued AD
[FR Doc. 2015–17252 Filed 7–13–15; 8:45 am] a.m. and 5 p.m., Monday through 2009–18–15, Amendment 39–16011 (74
BILLING CODE 6450–01–P Friday, except Federal holidays. FR 48143, September 22, 2009). AD
For service information identified in 2009–18–15 requires actions intended to
this proposed AD, contact Airbus SAS, address an unsafe condition for all
DEPARTMENT OF TRANSPORTATION Airworthiness Office—EAW, 1 Rond Airbus Model A300, A310, and A300
Point Maurice Bellonte, 31707 Blagnac B4–600, B4–600R, and F4–600R series
Federal Aviation Administration Cedex, France; telephone +33 5 61 93 36 airplanes, and Model A300 C4–605R
96; fax +33 5 61 93 44 51; email Variant F airplanes (collectively called
14 CFR Part 39 account.airworth-eas@airbus.com; Model A300–600 series airplanes).
[Docket No. FAA–2015–2461; Directorate
Internet http://www.airbus.com. Since we issued AD 2009–18–15,
Identifier 2013–NM–202–AD] You may view this referenced service Amendment 39–16011 (74 FR 48143,
information at the FAA, Transport September 22, 2009), we have
RIN 2120–AA64 Airplane Directorate, 1601 Lind Avenue determined that more restrictive
SW., Renton, WA. For information on maintenance requirements and
Airworthiness Directives; Airbus the availability of this material at the
Airplanes airworthiness limitations are necessary.
FAA, call 425–227–1221.
The European Aviation Safety Agency
AGENCY: Federal Aviation Examining the AD Docket (EASA), which is the Technical Agent
Administration (FAA), DOT. for the Member States of the European
ACTION: Notice of proposed rulemaking
You may examine the AD docket on
the Internet at http:// Union, has issued EASA Airworthiness
(NPRM). Directive 2013–0248, dated October 14,
www.regulations.gov by searching for
SUMMARY: We propose to supersede and locating Docket No. FAA–2015– 2013 (referred to after this as the
Airworthiness Directive (AD) 2009–18– 2461; or in person at the Docket Mandatory Continuing Airworthiness
15 for all Airbus Model A300, A310, Management Facility between 9 a.m. Information, or ‘‘the MCAI’’), to correct
and A300 B4–600, B4–600R, and F4– and 5 p.m., Monday through Friday, an unsafe condition for all Model A300,
600R series airplanes, and Model A300 except Federal holidays. The AD docket A310, and A300–600 series airplanes.
C4–605R Variant F airplanes contains this proposed AD, the The MCAI states:
(collectively called Model A300–600 regulatory evaluation, any comments The airworthiness limitations for Airbus
series airplanes). AD 2009–18–15 received, and other information. The aeroplanes are currently published in
currently requires revising the street address for the Docket Operations Airworthiness Limitations Section (ALS)
Airworthiness Limitations section (ALS) office (telephone (800) 647–5527) is in documents.
The mandatory instructions and
of the Instructions for Continued the ADDRESSES section. Comments will
airworthiness limitations applicable to the
Airworthiness (ICA) to require be available in the AD docket shortly Aging Systems Maintenance (ASM) are
additional life limits and/or after receipt. specified in Airbus A310 or A300–600 ALS
replacements for certain main landing FOR FURTHER INFORMATION CONTACT: Dan Part 4 documents, which are approved by the
gear and nose landing gear components. Rodina, Aerospace Engineer, European Aviation Safety Agency (EASA).
Since we issued AD 2009–18–15, we International Branch, ANM–116, EASA AD 2007–0092 [http://
have determined that existing Transport Airplane Directorate, FAA, ad.easa.europa.eu/blob/easa_ad_2007_
maintenance requirements and 0092.pdf/AD_2007-0092] [which corresponds
1601 Lind Avenue SW., Renton, WA
airworthiness limitations are inadequate to FAA AD 2009–06–06, Amendment 39–
98057–3356; telephone 425–227–2125; 15842 (74 FR 12228, March 24, 2009)] was
to ensure the structural integrity of the fax 425–227–1149. issued to require compliance to the
airplane. This proposed AD would SUPPLEMENTARY INFORMATION: requirements as specified in these
require revising the maintenance or documents.
inspection program to incorporate new Comments Invited The revision 02 of Airbus A310 and Airbus
maintenance requirements and We invite you to send any written A300–600 ALS Part 4 documents introduces
airworthiness limitations. We are relevant data, views, or arguments about more restrictive maintenance requirements
proposing this AD to prevent failure of and/or airworthiness limitations. Failure to
this proposed AD. Send your comments
certain system components, which comply with the instructions of ALS Part 4
to an address listed under the could result in an unsafe condition [reduced
could result in reduced structural ADDRESSES section. Include ‘‘Docket No. structural integrity of the airplane.]
integrity of the airplane. FAA–2015–2461; Directorate Identifier For the reasons described above, this new
DATES: We must receive comments on 2013–NM–202–AD’’ at the beginning of [EASA] AD retains the requirements of EASA
this proposed AD by August 28, 2015. your comments. We specifically invite AD 2007–0092, which is superseded, and
ADDRESSES: You may send comments by comments on the overall regulatory, requires the implementation of the new or
any of the following methods: economic, environmental, and energy more restrictive maintenance requirements
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
• Federal eRulemaking Portal: Go to aspects of this proposed AD. We will and/or airworthiness limitations as specified
in Airbus A310 ALS Part 4, Revision 02, or
http://www.regulations.gov. Follow the consider all comments received by the
Airbus A300–600 ALS Part 4, Revision 02, as
instructions for submitting comments. closing date and may amend this applicable to aeroplane type/model.
• Fax: (202) 493–2251. proposed AD based on those comments.
• Mail: U.S. Department of We will post all comments we You may examine the MCAI in the AD
Transportation, Docket Operations, receive, without change, to http:// docket on the Internet at http://
M–30, West Building Ground Floor, www.regulations.gov, including any www.regulations.gov by searching for
Room W12–140, 1200 New Jersey personal information you provide. We and locating Docket No. FAA–2015–
Avenue SE., Washington, DC 20590. will also post a report summarizing each 2461.
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![Federal Register / Vol. 80, No. 134 / Tuesday, July 14, 2015 / Proposed Rules 40943
Related Service Information Under 1 estimated cost of the actions that were The Proposed Amendment
CFR Part 51 required by AD 2009–18–15 is $85 per Accordingly, under the authority
Airbus has issued the following product. delegated to me by the Administrator,
service information, which describes We also estimate that it would take the FAA proposes to amend 14 CFR part
procedures for revising the maintenance about 1 work-hour per product to 39 as follows:
or inspection program to incorporate comply with the new ALS revision of
new maintenance requirements and this proposed AD. The average labor PART 39—AIRWORTHINESS
airworthiness limitations. rate is $85 per work-hour. Based on DIRECTIVES
• For Model A300 series airplanes: these figures, we estimate the cost of
this proposed AD on U.S. operators to ■ 1. The authority citation for part 39
‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Sub-
be $15,045, or $85 per product. continues to read as follows:
part 1–3: Demonstrated fatigue lives’’ of
Part 1, ‘‘Safe Life Airworthiness Authority: 49 U.S.C. 106(g), 40113, 44701.
Authority for This Rulemaking
Limitation Items,’’ Revision 01, dated § 39.13 [Amended]
September 5, 2013, of the Airbus Model Title 49 of the United States Code
A300 Airworthiness Limitations specifies the FAA’s authority to issue ■ 2. The FAA amends § 39.13 by
Section. rules on aviation safety. Subtitle I, removing Airworthiness Directive AD
• For Model A300 B4–600, B4–600R, section 106, describes the authority of 2009–18–15, Amendment 39–16011
and F4–600R series airplanes, and the FAA Administrator. ‘‘Subtitle VII: (74 FR 48143, September 22, 2009), and
Model A300 C4–605R Variant F Aviation Programs,’’ describes in more adding the following new AD:
airplanes (collectively called Model detail the scope of the Agency’s Airbus: Docket No. FAA–2015–2461;
A300–600 series airplanes): ‘‘Sub-part authority. Directorate Identifier 2013–NM–202–AD.
1–2: Life Limits,’’ and ‘‘Sub-part 1–3: We are issuing this rulemaking under (a) Comments Due Date
Demonstrated fatigue lives’’ of Part 1, the authority described in ‘‘Subtitle VII,
We must receive comments by August 28,
‘‘Safe Life Airworthiness Limitation Part A, Subpart III, Section 44701: 2015.
Items,’’ Revision 01, dated September 5, General requirements.’’ Under that
2013, of the Airbus Model A300–600 section, Congress charges the FAA with (b) Affected ADs
Airworthiness Limitations Section. promoting safe flight of civil aircraft in This AD replaces AD 2009–18–15,
• For Model A310 series airplanes: air commerce by prescribing regulations Amendment 39–16011 (74 FR 48143,
‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Sub- for practices, methods, and procedures September 22, 2009).
part 1–3: Demonstrated fatigue lives’’ of the Administrator finds necessary for (c) Applicability
Part 1, ‘‘Safe Life Airworthiness safety in air commerce. This regulation This AD applies to Airbus Model A300 B2–
Limitation Items,’’ Revision 01, dated is within the scope of that authority 1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103,
September 5, 2013, of the Airbus Model because it addresses an unsafe condition and B4–203 airplanes; Model A300 B4–601,
A310 Airworthiness Limitations that is likely to exist or develop on B4–603, B4–620, and B4–622 airplanes;
Section. products identified in this rulemaking Model A300 B4–605R and B4–622R
This service information is reasonably action. airplanes; Model A300 F4–605R and F4–
available because the interested parties 622R, and A300 C4–605R Variant F
Regulatory Findings airplanes; and Model A310–203, –204, –221,
have access to it through their normal
–222, –304, –322, –324, and –325 airplanes;
course of business, or by the means We determined that this proposed AD certificated in any category, all manufacturer
identified in the ADDRESSES section of would not have federalism implications serial numbers.
this NPRM. under Executive Order 13132. This
proposed AD would not have a (d) Subject
FAA’s Determination and Requirements Air Transport Association (ATA) of
substantial direct effect on the States, on
of This Proposed AD America 32, Landing Gear.
the relationship between the national
This product has been approved by Government and the States, or on the (e) Reason
the aviation authority of another distribution of power and This AD was prompted by a determination
country, and is approved for operation responsibilities among the various that existing maintenance requirements and
in the United States. Pursuant to our levels of government. airworthiness limitations are inadequate to
bilateral agreement with the State of For the reasons discussed above, I ensure the structural integrity of the airplane.
Design Authority, we have been notified certify this proposed regulation: We are issuing this AD to prevent failure of
of the unsafe condition described in the 1. Is not a ‘‘significant regulatory certain system components, which could
MCAI and service information result in reduced structural integrity of the
action’’ under Executive Order 12866; airplane.
referenced above. We are proposing this
2. Is not a ‘‘significant rule’’ under the
AD because we evaluated all pertinent (f) Compliance
DOT Regulatory Policies and Procedures
information and determined an unsafe Comply with this AD within the
(44 FR 11034, February 26, 1979);
condition exists and is likely to exist or compliance times specified, unless already
develop on other products of the same 3. Will not affect intrastate aviation in
done.
type design. Alaska; and
4. Will not have a significant (g) Retained Revision of Airworthiness
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Costs of Compliance economic impact, positive or negative, Limitation Section (ALS)
We estimate that this proposed AD on a substantial number of small entities This paragraph restates the requirements of
affects 177 airplanes of U.S. registry. under the criteria of the Regulatory paragraph (h) of AD 2009–18–15,
The ALS revision required by AD Flexibility Act. Amendment 39–16011 (74 FR 48143,
September 22, 2009). For Model A300, A310,
2009–18–15, Amendment 39–16011 List of Subjects in 14 CFR Part 39 and A300–600 series airplanes: Within 3
(74 FR 48143, September 22, 2009), months after October 27, 2009 (the effective
takes about 1 work-hour per product, at Air transportation, Aircraft, Aviation date of AD 2009–18–15), revise the ALS of
an average labor rate of $85 per work- safety, Incorporation by reference, the instructions for continued airworthiness
hour. Based on these figures, the Safety. (ICA) to incorporate the applicable document
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![Federal Register / Vol. 80, No. 134 / Tuesday, July 14, 2015 / Proposed Rules 40947
called Model A300–600 series airplanes): 5 61 93 36 96; fax +33 5 61 93 45 80; email Ground Floor, Room W12–140, 1200
Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and airworthiness.A330-A340@airbus.com; New Jersey Avenue SE., Washington,
‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’ Internet http://www.airbus.com. You may DC 20590–0001.
of Part 1, ‘‘Safe Life Airworthiness Limitation view this service information at the FAA,
Items,’’ Revision 01, dated September 5,
• Hand Delivery: Deliver to the
Transport Airplane Directorate, 1601 Lind
2013, of the Airbus A300–600 ALS. Avenue SW., Renton, WA. For information ‘‘Mail’’ address between 9 a.m. and 5
(3) For Model A310 series airplanes: on the availability of this material at the p.m., Monday through Friday, except
Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and FAA, call 425–227–1221. Federal holidays.
‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’
of Part 1, ‘‘Safe Life Airworthiness Limitation Issued in Renton, Washington, on June 25, Examining the AD Docket
Items,’’ dated Revision 01, September 5, 2015.
You may examine the AD docket on
2013, of the Airbus A310 ALS. Jeffrey E. Duven,
the Internet at http://
Manager, Transport Airplane Directorate, www.regulations.gov or in person at the
(k) New Limitation: No Alternative Actions
Aircraft Certification Service.
or Intervals Docket Operations Office between 9
[FR Doc. 2015–17201 Filed 7–13–15; 8:45 am] a.m. and 5 p.m., Monday through
After accomplishment of the revision
required by paragraph (j) of this AD, no BILLING CODE 4910–13–P Friday, except Federal holidays. The AD
alternative actions (e.g., inspections) or docket contains this proposed AD, the
intervals may be used unless the actions or European Aviation Safety Agency
intervals are approved as an alternative DEPARTMENT OF TRANSPORTATION (EASA) AD, the economic evaluation,
method of compliance (AMOC) in and other information. The street
accordance with the procedures specified in Federal Aviation Administration
paragraph (l) of this AD.
address for the Docket Operations Office
14 CFR Part 39 (telephone 800–647–5527) is in the
(l) Other FAA AD Provisions ADDRESSES section. Comments will be
The following provisions also apply to this [Docket No. FAA–2015–2714; Directorate available in the AD docket shortly after
AD: Identifier 2014–SW–052–AD] receipt.
(1) Alternative Methods of Compliance For service information identified in
(AMOCs): The Manager, International RIN 2120–AA64
this proposed AD, contact Airbus
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to Airworthiness Directives; Airbus Helicopters, Inc., 2701 N. Forum Drive,
approve AMOCs for this AD, if requested Helicopters Grand Prairie, TX 75052; telephone
using the procedures found in 14 CFR 39.19. (972) 641–0000 or (800) 232–0323; fax
In accordance with 14 CFR 39.19, send your AGENCY: Federal Aviation (972) 641–3775; or at http://
request to your principal inspector or local Administration (FAA), DOT. www.airbushelicopters.com/techpub.
Flight Standards District Office, as ACTION: Notice of proposed rulemaking You may review the referenced service
appropriate. If sending information directly (NPRM). information at the FAA, Office of the
to the International Branch, send it to ATTN: Regional Counsel, Southwest Region,
Dan Rodina, Aerospace Engineer, SUMMARY: We propose to adopt a new 2601 Meacham Blvd., Room 663, Fort
International Branch, ANM–116, Transport airworthiness directive (AD) for Airbus
Airplane Directorate, FAA, 1601 Lind Worth, Texas 76137.
Helicopters Model AS332C1, AS332L1,
Avenue SW., Renton, WA 98057–3356; FOR FURTHER INFORMATION CONTACT:
telephone 425–227–2125; fax 425–227–1149.
AS332L2, EC225LP, AS–365N2, AS 365
Robert Grant, Aviation Safety Engineer,
Information may be emailed to: 9-ANM-116- N3, EC 155B, and EC155B1 helicopters
Safety Management Group, FAA, 2601
AMOC-REQUESTS@faa.gov. Before using with an energy absorbing seat (seat).
Meacham Blvd., Fort Worth, Texas
any approved AMOC, notify your appropriate This proposed AD would require
76137; telephone (817) 222–5110; email
principal inspector, or lacking a principal inspecting for the presence of labels that
inspector, the manager of the local flight robert.grant@faa.gov.
prohibit stowing anything under the
standards district office/certificate holding seat. If a label is missing or not clearly SUPPLEMENTARY INFORMATION:
district office. The AMOC approval letter visible to each occupant, installing a
must specifically reference this AD. Comments Invited
(2) Contacting the Manufacturer: As of the
label would be required. This proposed
AD is prompted by the discovery that We invite you to participate in this
effective date of this AD, for any requirement rulemaking by submitting written
in this AD to obtain corrective actions from required labels had not been
systematically installed. The proposed comments, data, or views. We also
a manufacturer, the action must be
accomplished using a method approved by actions are intended to prevent objects invite comments relating to the
the Manager, International Branch, ANM– from being stowed under the seat as economic, environmental, energy, or
116, Transport Airplane Directorate, FAA; or these objects could reduce the energy- federalism impacts that might result
the European Aviation Safety Agency absorbing function of the seat, resulting from adopting the proposals in this
(EASA); or Airbus’s EASA Design
in injury to the seat occupants during an document. The most helpful comments
Organization Approval (DOA). If approved by reference a specific portion of the
the DOA, the approval must include the accident.
proposal, explain the reason for any
DOA-authorized signature. DATES: We must receive comments on
recommended change, and include
(m) Related Information this proposed AD by September 14, supporting data. To ensure the docket
2015. does not contain duplicate comments,
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA ADDRESSES: You may send comments by commenters should send only one copy
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Airworthiness Directive 2013–0248, dated any of the following methods: of written comments, or if comments are
October 14, 2013, for related information. • Federal eRulemaking Docket: Go to filed electronically, commenters should
This MCAI may be found in the AD docket http://www.regulations.gov. Follow the submit only one time.
on the Internet at http://www.regulations.gov online instructions for sending your We will file in the docket all
by searching for and locating Docket No.
FAA–2015–2461.
comments electronically. comments that we receive, as well as a
(2) For service information identified in • Fax: 202–493–2251. report summarizing each substantive
this AD, contact Airbus SAS, Airworthiness • Mail: Send comments to the U.S. public contact with FAA personnel
Office—EAL, 1 Rond Point Maurice Bellonte, Department of Transportation, Docket concerning this proposed rulemaking.
31707 Blagnac Cedex, France; telephone +33 Operations, M–30, West Building Before acting on this proposal, we will
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Document Created: 2018-02-23 09:19:45
Document Modified: 2018-02-23 09:19:45
| 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 August 28, 2015. | |
| Contact | Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. | |
| FR Citation | 80 FR 40942 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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