80 FR 69846 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 218 (November 12, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 218 (November 12, 2015)
| Page Range | 69846-69852 | |
| FR Document | 2015-27449 |
[Federal Register Volume 80, Number 218 (Thursday, November 12, 2015)] [Rules and Regulations] [Pages 69846-69852] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-27449] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-2461; Directorate Identifier 2013-NM-202-AD; Amendment 39-18310; AD 2015-22-05] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding 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 required 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. This new AD requires revising the maintenance or inspection program to incorporate new maintenance requirements and airworthiness limitations. 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. DATES: This AD becomes effective December 17, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 17, 2015. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of October 27, 2009 (74 FR 48143, September 22, 2009). ADDRESSES: You may examine the AD docket on the Internet at http:// [[Page 69847]] www.regulations.gov/#!docketDetail;D= FAA-2015-2461; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-2461. 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). AD 2009-18-15 applied to 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). The NPRM published in the Federal Register on July 14, 2015 (80 FR 40942). 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/#!documentDetail;D=FAA-2015-2461-0002. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (80 FR 40942, July 14, 2015) or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed, except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM (80 FR 40942, July 14, 2015) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 40942, July 14, 2015). Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. ``Sub-part 1- 2: Life Limits'' and ``Sub-part 1-3: Demonstrated fatigue lives'' of Part 1, ``Safe Life Airworthiness Limitation Items,'' in each of these documents describe procedures for revising the maintenance or inspection program to incorporate new maintenance requirements and airworthiness limitations. For Model A300 series airplanes: 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): 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: 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 AD. Costs of Compliance We estimate that this AD affects 177 airplanes of U.S. registry. The retained 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 takes about 1 work-hour per product to comply with the new ALS revision of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this 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. [[Page 69848]] Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will 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 that this AD: 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. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=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 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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: 2015-22-05 Airbus: Amendment 39-18310. Docket No. FAA-2015-2461; Directorate Identifier 2013-NM-202-AD. (a) Effective Date This AD becomes effective December 17, 2015. (b) Affected ADs (1) This AD replaces AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). (2) Accomplishing certain requirements of paragraph (g) of this AD satisfies the requirements of paragraph A. of AD 84-02-04, Amendment 39-4795 (49 FR 2746, January 23, 1984). (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 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 (49 FR 2746, January 23, 1984). (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 [[Page 69849]] 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: 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 Designation A300 A310 A300-600 Start date date'') ------------------------------------------------- P/N --------------------------------- X X X Landings Calendar time -------------------------------------------------------------------------------------------------------------------------------------------------------- MAIN LANDING GEAR -------------------------------------------------------------------------------------------------------------------------------------------------------- Aft pintle pin.................... 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. 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. Half ball housing (Fwd pintle A32140036200xx....... X ........... ........... December 13, 2007... 13,500 9 years. bearing). 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. A32140042200xx....... X ........... X December 13, 2007... 13,500 9 years. 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. 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. --------------------------------- [[Page 69850]] 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. 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. [[Page 69851]] 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 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-2015-2461-0002. [[Page 69852]] (2) Service information identified in this AD that is not incorporated by reference in this AD is available at the addresses specified in paragraphs (n)(5) and (n)(6) of this AD. (n) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on November 27, 2015. (i) ALS Part 1, ``Safe Life Airworthiness Limitation Items,'' Revision 01, dated September 5, 2013, of the Airbus Model A300 Airworthiness Limitations Section. (ii) ALS Part 1, ``Safe Life Airworthiness Limitation Items,'' Revision 01, dated September 5, 2013, of the Airbus Model A300-600 Airworthiness Limitations Section. (iii) ALS Part 1, ``Safe Life Airworthiness Limitation Items,'' Revision 01, dated September 5, 2013, of the Airbus Model A310 Airworthiness Limitations Section. (4) The following service information was approved for IBR on October 27, 2009 (74 FR 48143, September 22, 2009). (i) Section 05-10-00 of Chapter 05, ``Service Life Limits and Maintenance Checks,'' of the Airbus A300 Aircraft Maintenance Manual (AMM), Revision 28, dated February 27, 1998. (A) The AMM title page; the Record of Revisions, Effective Pages, and Table of Content pages; and Section 05-10-00; for Chapter 05 of Airbus A300 AMM are all dated February 27, 1998. (B) The revision level of Chapter 05 of the Airbus A300 AMM is indicated only in the Record of Revisions section of Chapter 05. (C) The List of Effective Pages (LOEP) for Chapter 05 of the Airbus A300 AMM contains the discrepancies identified in paragraphs (n)(4)(i)(C)(1) through (n)(4)(i)(C)(4) of this AD. (1) The Transmittal Letter page, page 4 of the LOEP and Table of Contents sections, page 2 of Subsection 05-00-01, Subsection 05-10- 00, and page 1 of Subsection 05-11-11, are not listed in the LOEP for Chapter 05 of the Airbus A300 AMM. (2) The LOEP for Chapter 05 of the Airbus A300 AMM does not specify a date for the Record of Revisions page. (3) The LOEP for Chapter 05 of the Airbus A300 AMM identifies three pages for Subsection 05-11-00, Configuration 5; however, only one page exists. (4) The LOEP for Chapter 05 of the Airbus A300 AMM identifies three pages for Subsection 05-11-00, Configuration 9; however, those pages do not exist. (ii) Airbus A300 Airworthiness Limitations Section, ALS Part 1, ``Safe Life Airworthiness Limitations Items'' dated September 6, 2007. (iii) Airbus A300-600 Airworthiness Limitations Section, ALS Part 1, ``Safe Life Airworthiness Limitations Items'' dated December 21, 2006. (iv) Airbus A310 Airworthiness Limitations Section, ALS Part 1, ``Safe Life Airworthiness Limitation Items'' dated December 21, 2006. (5) 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 [email protected]; Internet http://www.airbus.com. (6) 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. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on October 21, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-27449 Filed 11-10-15; 8:45 am] BILLING CODE 4910-13-P
![69846 Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations
and (i) of AD 2013–09–01, Amendment 39– (2) Before using any approved AMOC, Issued in Renton, Washington, on October
17442 (78 FR 27001, May 9, 2013), for the notify your appropriate principal inspector, 11, 2015.
replaced skin panel only. or lacking a principal inspector, the manager Jeffrey E. Duven,
(r) Exceptions to Service Information of the local flight standards district office/ Manager, Transport Airplane Directorate,
Specifications certificate holding district office. Aircraft Certification Service.
(3) An AMOC that provides an acceptable
(1) Where Boeing Service Bulletin 737– [FR Doc. 2015–26616 Filed 11–10–15; 8:45 am]
level of safety may be used for any repair
53A1177, Revision 7, dated June 14, 2013, required by this AD if it is approved by the BILLING CODE 4910–13–P
specifies a compliance time ‘‘after the
Boeing Commercial Airplanes Organization
Revision 7 date of this service bulletin,’’ this
AD requires compliance within the specified Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles DEPARTMENT OF TRANSPORTATION
compliance time after the effective date of
this AD. ACO, to make those findings. For a repair
method to be approved, the repair must meet
Federal Aviation Administration
(2) Where Boeing Service Bulletin 737–
53A1177, Revision 6, dated May 31, 2001; the certification basis of the airplane, and the
approval must specifically refer to this AD. 14 CFR Part 39
and Boeing Service Bulletin 737–53A1177,
Revision 7, dated June 14, 2013; specify to (4) AMOCs approved for AD 2002–07–08, [Docket No. FAA–2015–2461; Directorate
contact Boeing for certain procedures: Do the Amendment 39–12702 (67 FR 17917, April Identifier 2013–NM–202–AD; Amendment
specified actions before further flight using a 12, 2002), are approved as AMOCs for the 39–18310; AD 2015–22–05]
method approved in accordance with the corresponding provisions of this AD.
procedures specified in paragraph (t) of this RIN 2120–AA64
AD. (u) Related Information
(3) Where Boeing Service Bulletin 737– (1) For more information about this AD, Airworthiness Directives; Airbus
53A1177, Revision 6, dated May 31, 2001; contact Jennifer Tsakoumakis, Aerospace Airplanes
and Boeing Service Bulletin 737–53A1177, Engineer, Airframe Branch, ANM–120L, AGENCY: Federal Aviation
Revision 7, dated June 14, 2013; include the FAA, Los Angeles Aircraft Certification
phrase ‘‘or is Boeing or FAA approved,’’ this Administration (FAA), Department of
Office (ACO), 3960 Paramount Boulevard,
AD requires the ‘‘Boeing Approval’’ to be Lakewood, CA 90712–4137; phone: 562–627–
Transportation (DOT).
requested in accordance with the procedures 5264; fax: 562–627–5210; email: ACTION: Final rule.
specified in paragraph (t) of this AD. Jennifer.Tsakoumakis@faa.gov.
SUMMARY: We are superseding
(s) Credit for Previous Actions (2) Service information identified in this
AD that is not incorporated by reference is
Airworthiness Directive (AD) 2009–18–
(1) This paragraph provides credit for the 15, for all Airbus Model A300, A310,
available at the addresses specified in
actions required by paragraph (g) of this AD, and A300 B4–600, B4–600R, and F4–
if those actions were performed before the paragraphs (v)(3) and (v)(4) of this AD.
600R series airplanes, and Model A300
effective date of this AD using the applicable (v) Material Incorporated by Reference C4–605R Variant F airplanes
service information specified in paragraphs
(s)(1)(i), (s)(1)(ii), and (s)(1)(iii) of this AD, (1) The Director of the Federal Register (collectively called Model A300–600
which were incorporated by reference in AD approved the incorporation by reference series airplanes). AD 2009–18–15
2002–07–08, Amendment 39–12702 (67 FR (IBR) of the service information listed in this required revising the Airworthiness
17917, April 12, 2002). paragraph under 5 U.S.C. 552(a) and 1 CFR Limitations section (ALS) of the
(i) Boeing Service Bulletin 737–53A1177, part 51. Instructions for Continued
Revision 4, dated September 2, 1999. (2) You must use this service information Airworthiness (ICA) to require
(ii) Boeing Service Bulletin 737–53A1177, as applicable to do the actions required by additional life limits and/or
Revision 5, dated February 15, 2001, which this AD, unless the AD specifies otherwise.
replacements for certain main landing
continues to be incorporated by reference in (i) Boeing Service Bulletin 737–53A1177,
Revision 7, dated June 14, 2013.
gear and nose landing gear components.
this AD.
(iii) Boeing Service Bulletin 737–53A1177, (ii) Reserved. This new AD requires revising the
Revision 6, dated May 31, 2001, which (3) The following service information was maintenance or inspection program to
continues to be incorporated by reference in approved for IBR on May 17, 2002 (67 FR incorporate new maintenance
this AD. 17917, April 12, 2002). requirements and airworthiness
(2) This paragraph provides credit for the (i) Boeing Service Bulletin 737–53A1177, limitations. This AD was prompted by
actions required by paragraphs (i) through (o) Revision 5, dated February 15, 2001. a determination that existing
of this AD, if those actions were performed (ii) Boeing Service Bulletin 737–53A1177, maintenance requirements and
before the effective date of this AD using Revision 6, dated May 31, 2001. airworthiness limitations are inadequate
Boeing Service Bulletin 737–53A1177, (4) For Boeing service information to ensure the structural integrity of the
Revision 6, dated May 31, 2001, which was identified in this AD, contact Boeing
incorporated by reference in AD 2002–07–08, airplane. We are issuing this AD to
Commercial Airplanes, Attention: Data & prevent failure of certain system
Amendment 39–12702 (67 FR 17917, April Services Management, P.O. Box 3707, MC
12, 2002) and continues to be incorporated components, which could result in
2H–65, Seattle, WA 98124–2207; telephone
by reference in this AD. 206–544–5000, extension 1; fax 206–766–
reduced structural integrity of the
5680; Internet https:// airplane.
(t) Alternative Methods of Compliance
(AMOCs) www.myboeingfleet.com. DATES: This AD becomes effective
(1) The Manager, Los Angeles Aircraft (5) You may view this service information December 17, 2015.
Certification Office (ACO), FAA, has the at FAA, Transport Airplane Directorate, 1601 The Director of the Federal Register
authority to approve AMOCs for this AD, if Lind Avenue SW., Renton, WA. For approved the incorporation by reference
requested using the procedures found in 14 information on the availability of this of certain publications listed in this AD
CFR 39.19. In accordance with 14 CFR 39.19, material at the FAA, call 425–227–1221. as of December 17, 2015.
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send your request to your principal inspector (6) You may view this service information The Director of the Federal Register
or local Flight Standards District Office, as that is incorporated by reference at the
approved the incorporation by reference
appropriate. If sending information directly National Archives and Records
Administration (NARA). For information on
of certain other publications listed in
to the manager of the ACO, send it to the
attention of the person identified in the availability of this material at NARA, call this AD as of October 27, 2009 (74 FR
paragraph (u)(1) of this AD. Information may 202–741–6030, or go to: http:// 48143, September 22, 2009).
be emailed to: 9-ANM-LAACO-AMOC- www.archives.gov/federal-register/cfr/ibr- ADDRESSES: You may examine the AD
Requests@faa.gov. locations.html. docket on the Internet at http://
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![Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations 69847
www.regulations.gov/#!docketDetail;D= European Aviation Safety Agency (EASA). • For Model A300 B4–600, B4–600R,
FAA-2015-2461; or in person at the EASA AD 2007–0092 [http:// and F4–600R series airplanes, and
Docket Management Facility, U.S. ad.easa.europa.eu/blob/easa_ad_2007_ Model A300 C4–605R Variant F
0092.pdf/AD_2007-0092] [which corresponds
Department of Transportation, Docket to FAA AD 2009–06–06, Amendment 39–
airplanes (collectively called Model
Operations, M–30, West Building 15842 (74 FR 12228, March 24, 2009)] was A300–600 series airplanes): Part 1, ‘‘Safe
Ground Floor, Room W12–140, 1200 issued to require compliance to the Life Airworthiness Limitation Items,’’
New Jersey Avenue SE., Washington, requirements as specified in these Revision 01, dated September 5, 2013,
DC. documents. of the Airbus Model A300–600
For service information identified in The revision 02 of Airbus A310 and Airbus Airworthiness Limitations Section.
this AD, contact Airbus SAS, A300–600 ALS Part 4 documents introduces
more restrictive maintenance requirements • For Model A310 series airplanes:
Airworthiness Office—EAW, 1 Rond
and/or airworthiness limitations. Failure to Part 1, ‘‘Safe Life Airworthiness
Point Maurice Bellonte, 31707 Blagnac
comply with the instructions of ALS Part 4 Limitation Items,’’ Revision 01, dated
Cedex, France; telephone +33 5 61 93 36 could result in an unsafe condition [reduced September 5, 2013, of the Airbus Model
96; fax +33 5 61 93 44 51; email structural integrity of the airplane.] A310 Airworthiness Limitations
account.airworth-eas@airbus.com; For the reasons described above, this new Section.
Internet http://www.airbus.com. You [EASA] AD retains the requirements of EASA
may view this referenced service AD 2007–0092, which is superseded, and This service information is reasonably
information at the FAA, Transport requires the implementation of the new or available because the interested parties
Airplane Directorate, 1601 Lind Avenue more restrictive maintenance requirements have access to it through their normal
SW., Renton, WA. For information on and/or airworthiness limitations as specified course of business, or by the means
in Airbus A310 ALS Part 4, Revision 02, or identified in the ADDRESSES section of
the availability of this material at the Airbus A300–600 ALS Part 4, Revision 02, as
FAA, call 425–227–1221. It is also applicable to aeroplane type/model. this AD.
available on the Internet at http://
You may examine the MCAI in the Costs of Compliance
www.regulations.gov by searching for
and locating Docket No. FAA–2015– AD docket on the Internet at http://
www.regulations.gov/#!document We estimate that this AD affects 177
2461. airplanes of U.S. registry.
Detail;D=FAA-2015-2461-0002.
FOR FURTHER INFORMATION CONTACT: Dan The retained ALS revision required by
Rodina, Aerospace Engineer, Comments
AD 2009–18–15, Amendment 39–16011
International Branch, ANM–116, We gave the public the opportunity to (74 FR 48143, September 22, 2009),
Transport Airplane Directorate, FAA, participate in developing this AD. We takes about 1 work-hour per product, at
1601 Lind Avenue SW., Renton, WA received no comments on the NPRM (80 an average labor rate of $85 per work-
98057–3356; telephone 425–227–2125; FR 40942, July 14, 2015) or on the hour. Based on these figures, the
fax 425–227–1149. determination of the cost to the public. estimated cost of the actions that were
SUPPLEMENTARY INFORMATION: required by AD 2009–18–15 is $85 per
Conclusion
Discussion product.
We reviewed the available data and
We issued a notice of proposed determined that air safety and the We also estimate that it takes about 1
rulemaking (NPRM) to amend 14 CFR public interest require adopting this AD work-hour per product to comply with
part 39 to supersede AD 2009–18–15, as proposed, except for minor editorial the new ALS revision of this AD. The
Amendment 39–16011 (74 FR 48143, changes. We have determined that these average labor rate is $85 per work-hour.
September 22, 2009). AD 2009–18–15 minor changes: Based on these figures, we estimate the
applied to all Airbus Model A300, • Are consistent with the intent that cost of this AD on U.S. operators to be
A310, and A300 B4–600, B4–600R, and was proposed in the NPRM (80 FR $15,045, or $85 per product.
F4–600R series airplanes; and Model 40942, July 14, 2015) for correcting the Authority for This Rulemaking
A300 C4–605R Variant F airplanes unsafe condition; and
(collectively called Model A300–600 • Do not add any additional burden Title 49 of the United States Code
series airplanes). The NPRM published upon the public than was already specifies the FAA’s authority to issue
in the Federal Register on July 14, 2015 proposed in the NPRM (80 FR 40942, rules on aviation safety. Subtitle I,
(80 FR 40942). July 14, 2015). section 106, describes the authority of
The European Aviation Safety Agency Related Service Information Under 1 the FAA Administrator. ‘‘Subtitle VII:
(EASA), which is the Technical Agent CFR Part 51 Aviation Programs,’’ describes in more
for the Member States of the European detail the scope of the Agency’s
Airbus has issued the following
Union, has issued EASA Airworthiness authority.
service information. ‘‘Sub-part 1–2: Life
Directive 2013–0248, dated October 14, We are issuing this rulemaking under
Limits’’ and ‘‘Sub-part 1–3:
2013 (referred to after this as the the authority described in ‘‘Subtitle VII,
Demonstrated fatigue lives’’ of Part 1,
Mandatory Continuing Airworthiness Part A, Subpart III, Section 44701:
‘‘Safe Life Airworthiness Limitation
Information, or ‘‘the MCAI’’), to correct General requirements.’’ Under that
Items,’’ in each of these documents
an unsafe condition for all Model A300, section, Congress charges the FAA with
describe procedures for revising the
A310, and A300–600 series airplanes. maintenance or inspection program to promoting safe flight of civil aircraft in
The MCAI states: incorporate new maintenance air commerce by prescribing regulations
The airworthiness limitations for Airbus requirements and airworthiness for practices, methods, and procedures
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aeroplanes are currently published in limitations. the Administrator finds necessary for
Airworthiness Limitations Section (ALS) • For Model A300 series airplanes: safety in air commerce. This regulation
documents. Part 1, ‘‘Safe Life Airworthiness is within the scope of that authority
The mandatory instructions and
airworthiness limitations applicable to the Limitation Items,’’ Revision 01, dated because it addresses an unsafe condition
Aging Systems Maintenance (ASM) are September 5, 2013, of the Airbus Model that is likely to exist or develop on
specified in Airbus A310 or A300–600 ALS A300 Airworthiness Limitations products identified in this rulemaking
Part 4 documents, which are approved by the Section. action.
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![69848 Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations
Regulatory Findings (a) Effective Date Items,’’ dated September 6, 2007, of the
This AD becomes effective December 17, Airbus A300 ALS.
We determined that this AD will not
2015.
have federalism implications under TABLE 1 TO PARAGRAPH (g) OF THIS
Executive Order 13132. This AD will (b) Affected ADs
AD—PARTS SUBJECT TO THE LIFE
not have a substantial direct effect on (1) This AD replaces AD 2009–18–15,
Amendment 39–16011 (74 FR 48143,
LIMITS SPECIFIED IN THE DOCUMENT
the States, on the relationship between
the national government and the States, September 22, 2009). IDENTIFIED IN PARAGRAPH (g)(1)(ii)
or on the distribution of power and (2) Accomplishing certain requirements of OF THIS AD
paragraph (g) of this AD satisfies the
responsibilities among the various requirements of paragraph A. of AD 84–02– Part No.
levels of government. 04, Amendment 39–4795 (49 FR 2746, (P/N) Part name
For the reasons discussed above, I January 23, 1984).
certify that this AD: P/N C61643–2, P/N Main landing gear
(c) Applicability C61643–4, P/N (MLG) shock ab-
1. Is not a ‘‘significant regulatory
This AD applies to Airbus Model A300 B2– C61643–5. sorber end fitting.
action’’ under Executive Order 12866; 1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, P/N A32210001205xx Nose landing gear
2. Is not a ‘‘significant rule’’ under the and B4–203 airplanes; Model A300 B4–601, (NLG) pintle pin.
DOT Regulatory Policies and Procedures B4–603, B4–620, and B4–622 airplanes; P/N C62037–1 .......... NLG shock absorber
(44 FR 11034, February 26, 1979); Model A300 B4–605R and B4–622R bottom.
3. Will not affect intrastate aviation in airplanes; Model A300 F4–605R and F4– P/N 196–0328–501 ... Cross beam (Pratt &
Alaska; and 622R, and A300 C4–605R Variant F Whitney forward
airplanes; and Model A310–203, –204, –221, engine mount).
4. Will not have a significant –222, –304, –322, –324, and –325 airplanes;
economic impact, positive or negative, certificated in any category, all manufacturer (2) For Model A310 series airplanes:
on a substantial number of small entities serial numbers. Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and
under the criteria of the Regulatory ‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’
(d) Subject
Flexibility Act. of Part 1, ‘‘Safe Life Airworthiness Limitation
Air Transport Association (ATA) of Items,’’ dated December 21, 2006, of the
Examining the AD Docket America 32, Landing Gear. Airbus A310 ALS.
You may examine the AD docket on (e) Reason (3) For Model A300 B4–600, B4–600R, and
F4–600R series airplanes, and Model A300
the Internet at http:// This AD was prompted by a determination C4–605R Variant F airplanes (collectively
www.regulations.gov/#!docket that existing maintenance requirements and called Model A300–600 series airplanes):
Detail;D=FAA-2015-2461; or in person airworthiness limitations are inadequate to Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and
at the Docket Management Facility ensure the structural integrity of the airplane. ‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’
between 9 a.m. and 5 p.m., Monday We are issuing this AD to prevent failure of of Part 1, ‘‘Safe Life Airworthiness Limitation
through Friday, except Federal holidays. certain system components, which could Items,’’ dated December 21, 2006, of the
result in reduced structural integrity of the Airbus A300–600 ALS.
The AD docket contains this AD, the airplane.
regulatory evaluation, any comments (h) Retained Initial Compliance Times and
received, and other information. The (f) Compliance Repetitive Inspections
street address for the Docket Operations Comply with this AD within the This paragraph restates the requirements of
office (telephone 800–647–5527) is in compliance times specified, unless already paragraph (i) of AD 2009–18–15, Amendment
the ADDRESSES section. done. 39–16011 (74 FR 48143, September 22, 2009).
(g) Retained Revision of Airworthiness Do the replacement at the applicable time
List of Subjects in 14 CFR Part 39 specified in paragraph (h)(1) or (h)(2) of this
Limitation Section (ALS)
AD, except as provided by paragraph (i) of
Air transportation, Aircraft, Aviation This paragraph restates the requirements of this AD. The replacement must be done
safety, Incorporation by reference, paragraph (h) of AD 2009–18–15, thereafter within the interval specified in the
Safety. Amendment 39–16011 (74 FR 48143, applicable document identified in paragraph
September 22, 2009). For Model A300, A310, (g)(1), (g)(2), or (g)(3) of this AD.
Adoption of the Amendment and A300–600 series airplanes: Within 3 (1) For any life limitation/task that has
Accordingly, under the authority months after October 27, 2009 (the effective been complied with before October 27, 2009
delegated to me by the Administrator, date of AD 2009–18–15), revise the ALS of (the effective date of AD 2009–18–15,
the instructions for continued airworthiness Amendment 39–16011), in accordance with
the FAA amends 14 CFR part 39 as (ICA) to incorporate the applicable document the applicable document listed in paragraph
follows: listed in paragraph (g)(1), (g)(2), or (g)(3) of (g)(1), (g)(2), or (g)(3) of this AD, or in
this AD. Accomplishing the actions specified accordance with paragraph (g) of AD 2009–
PART 39—AIRWORTHINESS in the applicable document satisfies the 18–15, use the last accomplishment of each
DIRECTIVES requirements of paragraph A. of AD 84–02– limitation/task as a starting point for
04, Amendment 39–4795 (49 FR 2746, accomplishing each corresponding
■ 1. The authority citation for part 39 January 23, 1984). limitation/task required by this AD.
continues to read as follows: (1) For Model A300 series airplanes: (2) For any life limitation/task that has not
Incorporate the applicable document listed in been complied with before October 27, 2009
Authority: 49 U.S.C. 106(g), 40113, 44701. paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (the effective date of AD 2009–18–15,
§ 39.13 [Amended] (i) Section 05–10–00, Revision 28, dated Amendment 39–16011), in accordance with
February 27, 1998, of Chapter 05, ‘‘Service the applicable document listed in paragraphs
■ 2. The FAA amends § 39.13 by Life Limits and Maintenance Checks,’’ of the (g)(1), (g)(2), and (g)(3) of this AD, or in
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removing Airworthiness Directive AD Airbus A300 Aircraft Maintenance Manual, accordance with paragraph (g) of AD 2009–
2009–18–15, Amendment 39–16011 (74 except that the parts listed in table 1 to 18–15, the initial compliance time starts from
FR 48143, September 22, 2009), and paragraph (g) of this AD are subject to the life the date of initial entry into service as
limits defined in the document listed in defined in the applicable document.
adding the following new AD: paragraph (g)(1)(ii) of this AD.
2015–22–05 Airbus: Amendment 39–18310. (ii) ‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Sub- (i) Retained Special Compliance Times
Docket No. FAA–2015–2461; Directorate part 1–3: Demonstrated Fatigue Lives’’ of Part This paragraph restates the requirements of
Identifier 2013–NM–202–AD. 1, ‘‘Safe Life Airworthiness Limitation paragraph (j) of AD 2009–18–15, Amendment
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(2) Service information identified in this Airworthiness Limitation Items’’ dated second person from the Entity List
AD that is not incorporated by reference in December 21, 2006. following a proposal submitted by an
this AD is available at the addresses specified (5) For service information identified in ERC member agency, in accordance
in paragraphs (n)(5) and (n)(6) of this AD. this AD, contact Airbus, Airworthiness with the procedure for requesting
Office—EAS, 1 Rond Point Maurice Bellonte,
(n) Material Incorporated by Reference
31707 Blagnac Cedex, France; telephone +33
removal or modification of an Entity
(1) The Director of the Federal Register 5 61 93 36 96; fax +33 5 61 93 44 51; email List entity.
approved the incorporation by reference account.airworth-eas@airbus.com; Internet Finally, this final rule modifies ten
(IBR) of the service information listed in this http://www.airbus.com. existing entries on the Entity List
paragraph under 5 U.S.C. 552(a) and 1 CFR (6) You may view this service information consisting of one entry under China and
part 51. at the FAA, Transport Airplane Directorate, nine entries under Hong Kong to
(2) You must use this service information 1601 Lind Avenue SW., Renton, WA. For provide additional or modified
as applicable to do the actions required by information on the availability of this addresses and/or aliases for these
this AD, unless this AD specifies otherwise. material at the FAA, call 425–227–1221. persons.
(3) The following service information was (7) You may view this service information
approved for IBR on November 27, 2015. that is incorporated by reference at the DATES: This rule is effective on
(i) ALS Part 1, ‘‘Safe Life Airworthiness National Archives and Records November 12, 2015.
Limitation Items,’’ Revision 01, dated Administration (NARA). For information on FOR FURTHER INFORMATION CONTACT:
September 5, 2013, of the Airbus Model A300 the availability of this material at NARA, call Chair, End-User Review Committee,
Airworthiness Limitations Section. 202–741–6030, or go to: http:// Office of the Assistant Secretary, Export
(ii) ALS Part 1, ‘‘Safe Life Airworthiness www.archives.gov/federal-register/cfr/ibr-
Limitation Items,’’ Revision 01, dated Administration, Bureau of Industry and
locations.html.
September 5, 2013, of the Airbus Model Security, Department of Commerce,
A300–600 Airworthiness Limitations Issued in Renton, Washington, on October Phone: (202) 482–5991, Fax: (202) 482–
Section. 21, 2015. 3911, Email: ERC@bis.doc.gov.
(iii) ALS Part 1, ‘‘Safe Life Airworthiness Jeffrey E. Duven, SUPPLEMENTARY INFORMATION:
Limitation Items,’’ Revision 01, dated Manager, Transport Airplane Directorate,
September 5, 2013, of the Airbus Model A310 Aircraft Certification Service. Background
Airworthiness Limitations Section. [FR Doc. 2015–27449 Filed 11–10–15; 8:45 am] The Entity List (Supplement No. 4 to
(4) The following service information was Part 744) identifies entities and other
BILLING CODE 4910–13–P
approved for IBR on October 27, 2009 (74 FR persons reasonably believed to be
48143, September 22, 2009).
(i) Section 05–10–00 of Chapter 05,
involved, or to pose a significant risk of
‘‘Service Life Limits and Maintenance DEPARTMENT OF COMMERCE being or becoming involved, in
Checks,’’ of the Airbus A300 Aircraft activities contrary to the national
Maintenance Manual (AMM), Revision 28, Bureau of Industry and Security security or foreign policy interests of the
dated February 27, 1998. United States. The EAR imposes
(A) The AMM title page; the Record of 15 CFR Part 744 additional license requirements on, and
Revisions, Effective Pages, and Table of limits the availability of most license
Content pages; and Section 05–10–00; for [Docket No. 150911846–5846–01] exceptions for, exports, reexports, and
Chapter 05 of Airbus A300 AMM are all RIN 0694–AG74 transfers (in-country) to those listed.
dated February 27, 1998.
The ‘‘license review policy’’ for each
(B) The revision level of Chapter 05 of the Addition of Certain Persons and
Airbus A300 AMM is indicated only in the listed entity or other person is identified
Record of Revisions section of Chapter 05.
Modification of Certain Entries to the in the License Review Policy column on
(C) The List of Effective Pages (LOEP) for Entity List; and Removal of Certain the Entity List and the impact on the
Chapter 05 of the Airbus A300 AMM Persons From the Entity List availability of license exceptions is
contains the discrepancies identified in
AGENCY: Bureau of Industry and described in the Federal Register notice
paragraphs (n)(4)(i)(C)(1) through adding entities or other persons to the
(n)(4)(i)(C)(4) of this AD. Security, Commerce.
Entity List. BIS places entities and other
(1) The Transmittal Letter page, page 4 of ACTION: Final rule.
persons on the Entity List pursuant to
the LOEP and Table of Contents sections,
SUMMARY: This rule amends the Export sections of part 744 (Control Policy:
page 2 of Subsection 05–00–01, Subsection
05–10–00, and page 1 of Subsection 05–11– Administration Regulations (EAR) by End-User and End-Use Based) and part
11, are not listed in the LOEP for Chapter 05 adding seven persons under ten entries 746 (Embargoes and Other Special
of the Airbus A300 AMM. to the Entity List. The seven persons Controls) of the EAR.
(2) The LOEP for Chapter 05 of the Airbus who are added to the Entity List have The ERC, composed of representatives
A300 AMM does not specify a date for the been determined by the U.S. of the Departments of Commerce
Record of Revisions page. Government to be acting contrary to the (Chair), State, Defense, Energy and,
(3) The LOEP for Chapter 05 of the Airbus where appropriate, the Treasury, makes
A300 AMM identifies three pages for
national security or foreign policy
interests of the United States. These all decisions regarding additions to,
Subsection 05–11–00, Configuration 5; removals from, or other modifications to
however, only one page exists. persons will be listed on the Entity List
under the destinations of China and the Entity List. The ERC makes all
(4) The LOEP for Chapter 05 of the Airbus
A300 AMM identifies three pages for Hong Kong. decisions to add an entry to the Entity
Subsection 05–11–00, Configuration 9; This final rule also removes two List by majority vote and all decisions
however, those pages do not exist. persons from the Entity List. One entity to remove or modify an entry by
(ii) Airbus A300 Airworthiness Limitations requested removal from the Entity List unanimous vote.
mstockstill on DSK4VPTVN1PROD with RULES
Section, ALS Part 1, ‘‘Safe Life Airworthiness in accordance with the procedure for
Limitations Items’’ dated September 6, 2007. ERC Entity List Decisions
requesting removal or modification of
(iii) Airbus A300–600 Airworthiness Additions to the Entity List
Limitations Section, ALS Part 1, ‘‘Safe Life an Entity List entity. The End-User
Airworthiness Limitations Items’’ dated Review Committee (ERC) decided to This rule implements the decision of
December 21, 2006. remove this entity following a review of the ERC to add seven persons under ten
(iv) Airbus A310 Airworthiness information provided in the removal entries to the Entity List. These seven
Limitations Section, ALS Part 1, ‘‘Safe Life request. The ERC decided to remove a persons are being added on the basis of
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Document Created: 2015-12-14 14:53:54
Document Modified: 2015-12-14 14:53:54
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD becomes effective December 17, 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 69846 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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