80 FR 81168 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 249 (December 29, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 249 (December 29, 2015)
| Page Range | 81168-81174 | |
| FR Document | 2015-31603 |
[Federal Register Volume 80, Number 249 (Tuesday, December 29, 2015)] [Rules and Regulations] [Pages 81168-81174] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-31603] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0648; Directorate Identifier 2013-NM-136-AD; Amendment 39-18344; AD 2015-25-06] 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) 2010-06-04, for certain Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, B4-2C airplanes; Model A310 series airplanes; Model A300 B4-600 series airplanes; and Model A300 B4-600R series airplanes. AD 2010-06-04 required repetitive inspections to detect cracks of the pylon side panels (upper section) at rib 8; and corrective actions if necessary. This new AD continues to require repetitive inspections for cracking of the pylons 1 and 2 side panels (upper section) at rib 8 with reduced compliance times, and corrective actions if necessary. This AD also requires repetitive post-repair and post-modification inspections and repair if necessary. This AD also removes certain airplanes having a certain modification from the applicability. This AD was prompted by reports of cracks found on pylon side panels at rib 8 and a fleet survey and updated fatigue and damage tolerance analyses. We are issuing this AD to detect and correct cracking of pylon side panels (upper section) at rib 8, which could lead to reduced structural integrity of the pylon primary structure, which could cause detachment of the engine from the fuselage. DATES: This AD becomes effective February 2, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 2, 2016. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of April 15, 2010 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572)). ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0648; 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 final rule, 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-2014- 0648. 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 2010-06-04, [[Page 81169]] Amendment 39-16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572)). AD 2010-06-04 applied to certain Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, B4-2C airplanes; Model A310 series airplanes; Model A300 B4-600 series airplanes; and Model A300 B4-600R series airplanes. The NPRM published in the Federal Register on September 22, 2014 (79 FR 56526). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013-0136R1, dated July 30, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on certain Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, B4-2C airplanes; Model A310 series airplanes; Model A300 B4-600 series airplanes; and Model A300 B4-600R series airplanes. The MCAI states: Cracks were found on pylon side panels (upper section) at rib 8 on Airbus A300, A310 and A300-600 aeroplanes equipped with General Electric engines. Investigation of these findings indicated that this problem was likely to also affect aeroplanes of this type design with other engine installations. This condition, if not detected and corrected, could lead to reduced strength of the pylon primary structure, possibly resulting in pylon structural failure and in-flight loss of an engine. Prompted by these findings, EASA issued AD 2008-0181 [http://www.regulations.gov/#!documentDetail;D=FAA-2009-0789-0002] [which corresponds to FAA AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572))] to require repetitive detailed visual inspections [of the pylon side panels (upper section) at rib 8] and, depending on aeroplane configuration and/or findings, the accomplishment of applicable corrective action(s). Since that [EASA] AD was issued, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to substantiate the second A300-600 Extended Service Goal (ESG2) exercise. The results of these analyses have shown that the risk for these aeroplanes is higher than initially determined and consequently, the threshold and interval must be reduced to allow timely detection of these cracks and the accomplishment of applicable correction action(s). EASA issued AD 2013-0136 [http://ad.easa.europa.eu/ad/2013-0136R1] which retained the requirements of EASA AD 2008-0181, which was superseded, and required the inspections to be accomplished within reduced thresholds and intervals. After publication of EASA AD 2013-0136, it appeared that Airbus Mod 03599 had no influence on the aeroplane configuration affected by this AD. At the same time Airbus Service Bulletin (SB) A30-54- 6015 Revision 3 was not integrally taken into account as this revision no longer identifies configuration 3 aeroplanes. For the reasons described above, EASA [AD] 2013-0136 is revised to exclude Airbus Mod 03599 from the applicability and to delete the reference to the configuration 3 for A300-600 aeroplanes. Corrective actions include doing a repair. This AD also provides an optional modification (installing a doubler), which would terminate the repetitive inspections. Required actions also include repetitive post- repair and post-modification inspections and repair if necessary. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0648-0002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM (79 FR 56526, September 22, 2014) and the FAA's response. Request To Revise Method Used To Determine Compliance Times United Parcel Service (UPS) requested that we revise the proposed compliance times to be less complex. UPS stated that the proposed compliance times contain a method known as ``Average Flight Time'' (AFT) which results in a variable flight hour limit and adds unnecessary complexity to the threshold table and subsequent inspection actions. UPS added that use of the AFT method, along with a lack of standard procedures for implementing the AFT method would create uncertainty for operators and inspectors trying to determine the correct compliance time. UPS stated that in review of prior FAA ADs, including AD 98-18-02, Amendment 39-10718 (63 FR 45689, August 27, 1998), that the FAA does not concur with the AFT compliance time methodology as ``. . . such adjustments may not address the unsafe condition in a timely manner'' and ``. . . they (AFT compliance times) do not fit into the AD tracking process for operators or for Principle Maintenance Inspectors (PMIs) attempting to ascertain compliance with ADs.'' UPS compiled a table of fixed compliance times that it suggested would be simpler to use instead of the proposed AFT-based compliance times. We disagree with the commenter's request to revise the compliance times in this AD. The compliance times, as proposed, use fixed flight- cycle and flight-hour compliance times. For only Model A310 series airplanes, the compliance times depend on whether airplanes are short range or long range airplanes. We acknowledge that this causes additional complexity in tracking and forecasting airplane utilization; however, the inspection schedule was created by Airbus to offer operators the greatest flexibility. Operators may elect to inspect within the range that complies with both the long range and short range utilization in order to reduce the complexity. We have not changed this AD in this regard. Regarding AD 98-18-02, Amendment 39-10718 (63 FR 45689, August 27, 1998), at the time the FAA issued AD 98-18-02, the required actions in Airbus Industrie Service Bulletin A300-57-6027, Revision 2, dated September 13, 1994, contained inspection thresholds and intervals based on airplane flight cycles, and provided instructions for adjusting the flight cycle threshold and interval using each individual airplane's AFT utilization. The FAA did not agree with the AFT method because it could result in a different inspection threshold and interval for each individual airplane, and the FAA did not agree with adjusting a flight cycle based threshold and interval using the average flight time utilization without also having a related flight hour based threshold and interval. Conclusion We reviewed the available data, including the comment received, 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 (79 FR 56526, September 22, 2014) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 56526, September 22, 2014). Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. The service information describes procedures for repetitive inspections for cracking of the pylons 1 and 2 side panels (upper section) at rib 8 with reduced compliance times, and corrective actions if necessary. This service information also describes procedures for post- modification and post-repair detailed inspections for cracking, as applicable, of the left-hand (LH) and right-hand (RH) side panels of pylons 1 and 2, and repair if necessary. This [[Page 81170]] 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. Airbus Service Bulletin A300-54-0075, Revision 03, excluding Appendixes 1, 2, 3, and 5; including Appendix 4; dated March 27, 2013. Airbus Service Bulletin A310-54-2018, Revision 03, excluding Appendixes 1, 2, 3, and 5; including Appendix 4; dated April 11, 2013. Airbus Service Bulletin A300-54-6015, Revision 03, excluding Appendixes 1, 2, 3, and 5; including Appendix 4; dated April 11, 2013. Airbus has also issued the following service information. This service information describes procedures for modifying by installing a doubler on the LH pylon 1 and RH pylon 2, on pylon side panels (upper section), at rib 8. 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. Airbus Service Bulletin A300-54-0081, dated August 11, 1993. Airbus Service Bulletin A310-54-2024, dated August 11, 1993. Airbus Service Bulletin A300-54-6021, Revision 02, dated May 21, 2008. Costs of Compliance We estimate that this AD affects 156 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection [retained actions 4 work-hours x $85 per $0 $340.............. $53,040. from AD 2010-06-04, Amendment hour = $340. 39-16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572))]. Inspection [new actions]....... 24 work-hours x $85 per 0 $2,040 per $318,240 per hour = $2,040 per inspection cycle. inspection cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Repair............................. 58 work-hours x $85 per $3,910................ $8,840. hour = $4,930. Optional Modification.............. Up to 48 work-hours x $85 Up to $1,026.......... Up to $5,106. per hour = $4,080. ---------------------------------------------------------------------------------------------------------------- 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 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-2014-0648; 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) 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010); corrected [[Page 81171]] May 4, 2010 (75 FR 23572)), and adding the following new AD: 2015-25-06 Airbus: Amendment 39-18344. Docket No. FAA-2014-0648; Directorate Identifier 2013-NM-136-AD. (a) Effective Date This AD becomes effective February 2, 2016. (b) Affected ADs This AD replaces AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572)). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category. (1) Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4-2C airplanes, on which Airbus Modification 02434 has been embodied in production. (2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, except those on which Airbus Modification 10432 has been embodied in production. (3) Airbus Model A300 B4-601, B4-603, B4-605R, B4-620, B-622, and B4-622R airplanes, except those on which Airbus Modification 10432 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 54, Nacelles/ Pylons. (e) Reason This AD was prompted by reports of cracks found on pylon side panels at rib 8 and a fleet survey and updated fatigue and damage tolerance analyses. We are issuing this AD to detect and correct cracking of pylon side panels (upper section) at rib 8, which could lead to reduced structural integrity of the pylon primary structure, which could cause detachment of the engine from the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Actions and Compliance With Revised Service Information This paragraph restates the requirements of paragraph (f) of AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572)), with revised service information. Accomplishing the initial inspection required by paragraph (h) of this AD terminates the requirements of this paragraph. (1) For Configuration 01 airplanes as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: At the applicable time specified in table 1 to paragraph (g) of this AD, except as required by paragraphs (g)(2) and (g)(3) of this AD, perform a detailed visual inspection of the pylons 1 and 2 side panels (upper section) at rib 8, in accordance with paragraph 3.B. of the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(9)(i) through (g)(9)(iii) of this AD or paragraphs (k)(1), (k)(2), or (k)(3) of this AD. Repeat the inspection at the time specified in table 1 to paragraph (g) of this AD. Table 1 to Paragraph (g) of This AD--Compliance Times for Configuration 1 Airplanes ---------------------------------------------------------------------------------------------------------------- And repeat the That have Inspect before the inspection at For Model-- accumulated-- accumulation of-- Or within-- intervals not to exceed-- ---------Whichever occurs later--------- ---------------------------------------------------------------------------------------------------------------- A300 B2-1C, B2-203, and B2K-3C <=17,500 total 5,350 total flight 2,500 flight 4,300 flight airplanes. flight cycles \1\. cycles. cycles \2\. cycles. A300 B2-1C, B2-203, and B2K-3C >17,500 total 20,000 total 250 flight cycles 4,300 flight airplanes. flight cycles \1\. flight cycles or \2\. cycles. 40,000 total flight hours, whichever occurs first. A300 B4-103, B4-203, and B4-2C <=18,000 total 5,350 total flight 2,000 flight 4,300 flight airplanes. flight cycles \1\. cycles. cycles \2\. cycles. A300 B4-103, B4-203, and B4-2C >18,000 total 20,000 total 250 flight cycles 4,300 flight airplanes. flight cycles \1\. flight cycles or \2\. cycles. 40,000 total flight hours, whichever occurs first. A300 B4-601, B4-603, B4-605R, B4- <=18,000 total 4,200 total flight 2,000 flight 3,600 flight 620, B4-622, and B4-622R flight cycles \1\. cycles. cycles \2\. cycles. airplanes. A300 B4-601, B4-603, B4-605R, B4- >18,000 total 20,000 total 250 flight cycles 3,600 flight 620, B4-622, and B4-622R flight cycles \1\. flight cycles or \2\. cycles. airplanes. 40,000 total flight hours, whichever occurs first. A310-200 airplanes with GE CF6- <=18,000 total 9,700 total flight 1,500 flight 6,700 flight 80A3 or Pratt & Whitney engines. flight cycles \1\. cycles or 19,400 cycles \2\. cycles or 13,400 total flight flight hours, hours, whichever whichever occurs occurs first. first. A310-200 airplanes with GE CF6- >18,000 total 19,500 total 250 flight cycles 6,700 flight 80A3 or Pratt & Whitney engines. flight cycles \1\. flight cycles or \2\. cycles or 13,400 55,500 total flight hours, flight hours, whichever occurs whichever occurs first. first. A310-200 airplanes with GE CF6- <=18,000 total 7,800 total flight 1,500 flight 5,800 flight 80C2 engines. flight cycles \1\. cycles or 15,600 cycles \2\. cycles or 11,600 total flight flight hours, hours, whichever whichever occurs occurs first. first. A310-200 airplanes with GE CF6- >18,000 total 19,500 total 250 flight cycles 5,800 flight 80C2 engines. flight cycles \1\. flight cycles or \2\. cycles or 11,600 55,500 total flight hours, flight hours, whichever occurs whichever occurs first. first. A310-300 SR \3\ airplanes with <=18,000 total 8,600 total flight 1,500 flight 6,700 flight Pratt & Whitney JT9D engines. flight cycles \1\. cycles or 24,000 cycles \2\. cycles or 18,700 total flight flight hours, hours, whichever whichever occurs occurs first. first. A310-300 SR \3\ airplanes with >18,000 total 19,500 total 250 flight cycles 6,700 flight Pratt & Whitney JT9D engines. flight cycles \1\. flight cycles or \2\. cycles or 18,700 55,500 total flight hours, flight hours, whichever occurs whichever occurs first. first. A310-300 SR \3\ airplanes with <=18,000 total 7,000 total flight 1,500 flight 5,700 flight GE engines. flight cycles \1\. cycles or 19,600 cycles \2\. cycles or 15,900 total flight flight hours, hours, whichever whichever occurs occurs first. first. A310-300 SR \3\ airplanes with >18,000 total 19,500 total 250 flight cycles 5,700 flight GE engines. flight cycles \1\. flight cycles or \2\. cycles or 15,900 55,500 total flight hours, flight hours, whichever occurs whichever occurs first. first. [[Page 81172]] A310-300 SR \3\ airplanes with <=18,000 total 7,000 total flight 1,500 flight 5,800 flight Pratt & Whitney 4000 engines. flight cycles \1\. cycles or 19,600 cycles \2\. cycles or 16,200 total flight flight hours, hours, whichever whichever occurs occurs first. first. A310-300 SR \3\ airplanes with >18,000 total 19,500 total 250 flight cycles 5,800 flight Pratt & Whitney 4000 engines. flight cycles \1\. flight cycles or \2\. cycles or 16,200 55,500 total flight hours, flight hours, whichever occurs whichever occurs first. first. A310-300 LR \4\ airplanes with <=18,000 total 5,900 total flight 1,500 flight 6,000 flight Pratt & Whitney JT9D engines. flight cycles \1\. cycles or 29,500 cycles \2\. cycles or 30,300 total flight flight hours, hours, whichever whichever occurs occurs first. first. A310-300 LR \4\ airplanes with >18,000 total 19,500 total 250 flight cycles 6,000 flight Pratt & Whitney JT9D engines. flight cycles \1\. flight cycles or \2\. cycles or 30,300 55,500 total flight hours, flight hours, whichever occurs whichever occurs first. first. A310-300 LR \4\ airplanes with <=18,000 total 4,800 total flight 1,500 flight 5,100 flight GE engines. flight cycles \1\. cycles or 24,100 cycles \2\. cycles or 25,500 total flight flight hours, hours, whichever whichever occurs occurs first. first. A310-300 LR \4\ airplanes with >18,000 total 19,500 total 250 flight cycles 5,100 flight GE engines. flight cycles \1\. flight cycles or \2\. cycles or 25,500 55,500 total flight hours, flight hours, whichever occurs whichever occurs first. first. A310-300 LR \4\ airplanes with <=18,000 total 4,800 total flight 1,500 flight 5,200 flight Pratt & Whitney 4000 engines. flight cycles \1\. cycles or 24,000 cycles \2\. cycles or 26,300 total flight flight hours, hours, whichever whichever occurs occurs first. first. A310-300 LR \4\ airplanes with >18,000 total 19,500 total 250 flight cycles 5,200 flight Pratt & Whitney 4000 engines. flight cycles \1\. flight cycles or \2\. cycles or 26,300 55,500 total flight hours, flight hours, whichever occurs whichever occurs first. first. ---------------------------------------------------------------------------------------------------------------- \1\ As of April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572))). \2\ After April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010; corrected May 4, 2010 (75 FR 23572))). \3\ ``SR'' applies to airplanes with average flights less than 4 flight hours. \4\ ``LR'' refers to airplanes with average flights of 4 or more flight hours. (2) For Model A300 and A300-600 airplanes that have accumulated more than 40,000 total flight hours as of April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572))): Within 250 flight cycles after April 15, 2010, do the actions specified in paragraph (g)(1) of this AD. (3) For Model A310 airplanes that have accumulated more than 55,500 total flight hours as of April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572))): Within 250 flight cycles after April 15, 2010, do the actions specified in paragraph (g)(1) of this AD. (4) For Configuration 01 airplanes, as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: If a crack is found during any inspection required by paragraph (g)(1) of this AD, before further flight, install a doubler, in accordance with paragraph 3.C. of the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(9) of this AD. (5) For Configuration 02 airplanes, as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: At the applicable time specified in paragraph 1.E.(2) of the applicable service bulletin identified in paragraphs (g)(9)(i) through (g)(9)(iii) of this AD, or within 250 flight cycles after April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39- 16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572))), whichever occurs later, perform a detailed visual inspection of the pylons 1 and 2 side panels (upper section) at rib 8, in accordance with paragraph 3.B. of the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(9) of this AD. (6) For Configuration 03 airplanes, as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: At the applicable time specified in paragraph 1.E.(2) of the applicable service bulletin identified in paragraphs (g)(9)(i) through (g)(9)(iii) of this AD, or within 250 flight cycles after April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39- 16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572))), whichever occurs later, perform a detailed visual inspection, and a high frequency eddy current inspection as applicable, of the pylons 1 and 2 side panels (upper section) at rib 8, in accordance with paragraph 3.B. of the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(9) of this AD. (7) For Configuration 02 and 03 airplanes, as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: If a crack is found during any inspection required by paragraph (g)(1), (g)(5), or (g)(6) of this AD, before further flight, repair in accordance with paragraph 3.C. of the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(9) of this AD. (8) For all airplanes, except those in Configuration 01, as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: Repeat the inspection specified in paragraph (g)(1), (g)(5), or (g)(6) of this AD, as applicable, at the intervals specified in paragraph 1.E.(2) of the applicable service bulletin identified in paragraph (g)(9)(i) through (g)(9)(iii) of this AD. (9) For the actions specified in paragraph (g) of this AD, use the applicable service bulletin identified in paragraphs (g)(9)(i) through (g)(9)(iii) of this AD, or paragraph (k)(1), (k)(2), or (k)(3) of this AD. (i) Airbus Mandatory Service Bulletin A300-54-0075, excluding Appendixes 1, 2, and 3, Revision 02, dated June 26, 2008 (For Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4-2C airplanes). (ii) Airbus Mandatory Service Bulletin A300-54-6015, excluding Appendixes 1, 2, and 3, Revision 02, dated June 26, 2008 (For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes). (iii) Airbus Mandatory Service Bulletin A310-54-2018, excluding Appendixes 1, 2, and 3, Revision 02, dated June 26, 2008 (for Model A310 series airplanes). (h) New Repetitive Inspections and Repair Except as required by paragraphs (l)(1) and (l)(2) of this AD, at the applicable times specified in paragraph 1.E., ``Compliance,'' of the applicable service bulletin identified in paragraph (k) of this AD: Do a detailed inspection for cracking of the pylons 1 and [[Page 81173]] 2 side panels (upper section) at rib 8, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (k) of this AD. Accomplishing the inspection required by this paragraph terminates the requirements of paragraph (g)(1) through (g)(9) of this AD. (1) If any cracking is found, before further flight, do a high frequency eddy current (HFEC) inspection to confirm the crack, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (k) of this AD. (i) If any crack indication is confirmed during the HFEC inspection specified in paragraph (h)(1) of this AD, and the crack is less than 20 mm, before further flight, repair, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (k) of this AD. (ii) If any crack indication is confirmed during the HFEC inspection specified in paragraph (h)(1) of this AD and the crack is greater than or equal to 20 mm, before further flight, repair 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). (2) If no cracking is found, or if crack indication is not confirmed during the HFEC inspection required by paragraph (h)(1) of this AD, at the applicable interval specified in paragraph 1.E., ``Compliance,'' of the applicable service bulletin identified in paragraph (k) of this AD, repeat the inspection specified in paragraph (h) of this AD, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (k) of this AD until the modification specified in paragraph (i) is done. (i) Optional Modification Modifying by installing a doubler on the left hand (LH) pylon 1 and right hand (RH) pylon 2, on pylon side panels (upper section), at rib 8, in accordance with the Accomplishment Instructions of the service information identified in paragraph (i)(1), (i)(2), or (i)(3) of this AD; as applicable; terminates the repetitive inspections specified in paragraph (h)(2) of this AD. (1) Airbus Service Bulletin A300-54-0081, dated August 11, 1993. (2) Airbus Service Bulletin A310-54-2024, dated August 11, 1993. (3) Airbus Service Bulletin A300-54-6021, Revision 02, dated May 21, 2008. (j) Post-Modification and Post-Repair Repetitive Inspections and Corrective Actions For airplanes on which the modification has been done as specified in paragraph (i) of this AD, and airplanes on which the repair has been done as specified in paragraph (h) of this AD: At the applicable compliance time specified in paragraph 1.E., Compliance,'' of the applicable service bulletin identified in paragraph (k) of this AD, do the post-modification and post-repair detailed inspections for cracking, as applicable, of the LH and RH side panels of pylons 1 and 2, in accordance with the applicable service bulletins identified in paragraph (k) of this AD. Repeat the inspections thereafter at the times specified in paragraph 1.E., ``Compliance'' of the applicable service bulletin specified in paragraph (k) of this AD. If any cracking is found, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. This repair is not a terminating action for the repetitive inspections required by this paragraph. (k) New Service Information Use the applicable service bulletin identified in paragraphs (k)(1) through (k)(3) of this AD to accomplish the inspections required by paragraphs (g), (h), and (j) of this AD. (1) Airbus Service Bulletin A300-54-0075, Revision 03, excluding Appendixes 1, 2, 3, and 5; including Appendix 4; dated March 27, 2013 (for Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4- 2C airplanes). (2) Airbus Service Bulletin A310-54-2018, Revision 03, excluding Appendixes 1, 2, 3, and 5; including Appendix 4; dated April 11, 2013 (for Model A310-203, -204, -221, -222, -304, -322, -324, and - 325 airplanes). (3) Airbus Service Bulletin A300-54-6015, Revision 03, excluding Appendixes 1, 2, 3, and 5; including Appendix 4; dated April 11, 2013 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes). (l) Exceptions (1) Where the compliance time column in the tables in paragraph 1.E., ``Compliance,'' of the applicable service bulletin identified in paragraph (k) of this AD specifies a ``threshold'' in ``FC'' or ``FH,'' and does not specify from repair or service bulletin embodiment, those compliance times are total flight cycles and total flight hours. (2) Where the tables in paragraph 1.E., ``Compliance,'' of the applicable service bulletin specified in paragraph (k) of this AD specifies ``grace period after the receipt of the service bulletin,'' this AD requires compliance within the corresponding compliance time after the effective date of this AD. (m) Credit for Previous Actions (1) This paragraph restates the credit provided by paragraph (f)(9) of AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572)) with no changes. This paragraph provides credit for initial inspections required by paragraph (g) of this AD, if those actions were performed prior to April 15, 2010 (the effective date of AD 2010-06-04) using the applicable service bulletins specified in paragraphs (m)(1)(i) through (m)(1)(vi) of this AD, which are not incorporated by reference in this AD. (i) Airbus Service Bulletin A300-54-0075, dated August 11, 1993. (ii) Airbus Service Bulletin A300-54-0075, Revision 01, dated November 9, 2007. (iii) Airbus Service Bulletin A300-54-6015, dated August 11, 1993. (iv) Airbus Service Bulletin A300-54-6015, Revision 01, dated November 9, 2007. (v) Airbus Service Bulletin A310-54-2018, dated August 11, 1993. (vi) Airbus Service Bulletin A310-54-2018, Revision 01, dated November 16, 2007. (2) This paragraph provides credit for initial inspections required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using the applicable service bulletins specified in paragraphs (m)(2)(i) through (m)(2)(ix) of this AD. (i) Airbus Service Bulletin A300-54-0075, dated August 11, 1993, which is not incorporated by reference in this AD. (ii) Airbus Service Bulletin A300-54-0075, Revision 01, dated November 9, 2007, which is not incorporated by reference in this AD. (iii) Airbus Service Bulletin A300-54-0075, Revision 02, dated June 26, 2008. (iv) Airbus Service Bulletin A300-54-6015, dated August 11, 1993, which is not incorporated by reference in this AD. (v) Airbus Service Bulletin A300-54-6015, Revision 01, dated November 9, 2007, which is not incorporated by reference in this AD. (vi) Airbus Service Bulletin A300-54-6015, Revision 02, dated June 26, 2008. (vii) Airbus Service Bulletin A310-54-2018, dated August 11, 1993, which is not incorporated by reference in this AD. (viii) Airbus Service Bulletin A310-54-2018, Revision 01, dated November 16, 2007, which is not incorporated by reference in this AD. (ix) Airbus Service Bulletin A310-54-2018, Revision 02, dated June 26, 2008. (3) This paragraph provides credit for initial inspections required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using the applicable service bulletins specified in paragraphs (m)(3)(i) and (m)(3)(ii) of this AD. (i) Airbus Service Bulletin A300-54-6021, dated August 11, 1993, which is not incorporated by reference in this AD. (ii) Airbus Service Bulletin A300-54-6021, Revision 01, dated November 16, 2007, which is not incorporated by reference in this AD. (n) 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]. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager [[Page 81174]] of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (ii) AMOCs approved previously for AD 2010-06-04, Amendment 39- 16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572)); are approved as AMOCs for the corresponding provisions of 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 EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013-0136R1, dated July 30, 2013, for related information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0648-0002. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(5) and (p)(6) of this AD. (p) 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 February 2, 2016. (i) Airbus Service Bulletin A300-54-0075, Revision 03, excluding Appendixes 1, 2, 3, and 5; including Appendix 4; dated March 27, 2013. (ii) Airbus Service Bulletin A300-54-0081, dated August 11, 1993. (iii) Airbus Service Bulletin A300-54-6015, Revision 03, excluding Appendixes 1, 2, 3, and 5; including Appendix 4; dated April 11, 2013. (iv) Airbus Service Bulletin A300-54-6021, Revision 02, dated May 21, 2008. (v) Airbus Service Bulletin A310-54-2018, Revision 03, excluding Appendixes 1, 2, 3, and 5; including Appendix 4; dated April 11, 2013. (vi) Airbus Service Bulletin A310-54-2024, dated August 11, 1993. (4) The following service information was approved for IBR on April 15, 2010 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572)). (i) Airbus Mandatory Service Bulletin A300-54-0075, excluding Appendixes 1, 2, and 3, Revision 02, dated June 26, 2008. (ii) Airbus Mandatory Service Bulletin A300-54-6015, excluding Appendixes 1, 2, and 3, Revision 02, dated June 26, 2008. (iii) Airbus Mandatory Service Bulletin A310-54-2018, excluding Appendixes 1, 2, and 3, Revision 02, dated June 26, 2008. (5) 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. (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 December 8, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-31603 Filed 12-28-15; 8:45 am] BILLING CODE 4910-13-P
![81168 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations
Bulletin 100–25–21, Revision 01, dated (iv) Bombardier Temporary Revision (TR) post-modification inspections and
February 26, 2013, which is not incorporated 5–2–53, dated October 1, 2009, to Section 5– repair if necessary. This AD also
by reference in this AD. 10–40, ‘‘Certification Maintenance removes certain airplanes having a
Requirements,’’ in Part 2 of Chapter 5 of
(n) Other FAA AD Provisions certain modification from the
Bombardier Challenger 300 BD–100 Time
The following provisions also apply to this Limits/Maintenance Checks. applicability. This AD was prompted by
AD: (5) For service information identified in reports of cracks found on pylon side
(1) Alternative Methods of Compliance this AD, contact Bombardier, Inc., 400 Côte- panels at rib 8 and a fleet survey and
(AMOCs): The Manager, New York Aircraft Vertu Road West, Dorval, Québec H4S 1Y9, updated fatigue and damage tolerance
Certification Office (ACO), ANE–170, FAA, Canada; telephone 514–855–5000; fax 514– analyses. We are issuing this AD to
has the authority to approve AMOCs for this 855–7401; email thd.crj@ detect and correct cracking of pylon side
AD, if requested using the procedures found aero.bombardier.com; Internet http:// panels (upper section) at rib 8, which
in 14 CFR 39.19. In accordance with 14 CFR www.bombardier.com.
39.19, send your request to your principal could lead to reduced structural
(6) You may view this service information
inspector or local Flight Standards District at the FAA, Transport Airplane Directorate,
integrity of the pylon primary structure,
Office, as appropriate. If sending information 1601 Lind Avenue SW., Renton, WA. For which could cause detachment of the
directly to the New York ACO, send it to information on the availability of this engine from the fuselage.
ATTN: Program Manager, Continuing material at the FAA, call 425–227–1221. DATES: This AD becomes effective
Operational Safety, FAA, New York ACO, (7) You may view this service information February 2, 2016.
1600 Stewart Avenue, Suite 410, Westbury, that is incorporated by reference at the The Director of the Federal Register
NY 11590; telephone 516–228–7300; fax National Archives and Records
516–794–5531. Before using any approved
approved the incorporation by reference
Administration (NARA). For information on of certain publications listed in this AD
AMOC, notify your appropriate principal the availability of this material at NARA, call
inspector, or lacking a principal inspector, as of February 2, 2016.
202–741–6030, or go to: http://
the manager of the local flight standards The Director of the Federal Register
www.archives.gov/federal-register/cfr/ibr-
district office/certificate holding district locations.html. approved the incorporation by reference
office. The AMOC approval letter must of certain other publications listed in
specifically reference this AD. Issued in Renton, Washington, on this AD as of April 15, 2010 ((75 FR
(2) Contacting the Manufacturer: As of the December 11, 2015.
11428, March 11, 2010); corrected May
effective date of this AD, for any requirement Michael Kaszycki, 4, 2010 (75 FR 23572)).
in this AD to obtain corrective actions from Acting Manager, Transport Airplane
a manufacturer, the action must be ADDRESSES: You may examine the AD
Directorate, Aircraft Certification Service.
accomplished using a method approved by docket on the Internet at http://
[FR Doc. 2015–32080 Filed 12–28–15; 8:45 am] www.regulations.gov/
the Manager, New York ACO, ANE–170,
FAA; or Transport Canada Civil Aviation BILLING CODE 4910–13–P #!docketDetail;D=FAA-2014-0648; or in
(TCCA); or Bombardier, Inc.’s TCCA Design person at the Docket Management
Approval Organization (DAO). If approved by Facility, U.S. Department of
the DAO, the approval must include the DEPARTMENT OF TRANSPORTATION Transportation, Docket Operations, M–
DAO-authorized signature.
Federal Aviation Administration 30, West Building Ground Floor, Room
(o) Related Information W12–140, 1200 New Jersey Avenue SE.,
(1) Refer to Mandatory Continuing 14 CFR Part 39 Washington, DC.
Airworthiness Information (MCAI) Canadian For service information identified in
Airworthiness Directive CF–2010–06R1, [Docket No. FAA–2014–0648; Directorate this final rule, contact Airbus SAS,
dated August 8, 2013, for related information. Identifier 2013–NM–136–AD; Amendment Airworthiness Office—EAW, 1 Rond
This MCAI may be found in the AD docket 39–18344; AD 2015–25–06] Point Maurice Bellonte, 31707 Blagnac
on the Internet at http://www.regulations.gov Cedex, France; telephone +33 5 61 93 36
by searching for and locating Docket No. RIN 2120–AA64
FAA–2015–1199. 96; fax +33 5 61 93 44 51; email
(2) Service information identified in this Airworthiness Directives; Airbus account.airworth-eas@airbus.com;
AD that is not incorporated by reference is Airplanes Internet http://www.airbus.com. You
available at the addresses specified in may view this referenced service
AGENCY: Federal Aviation
paragraphs (p)(5) and (p)(6) of this AD. information at the FAA, Transport
Administration (FAA), Department of
(p) Material Incorporated by Reference Airplane Directorate, 1601 Lind Avenue
Transportation (DOT).
SW., Renton, WA. For information on
(1) The Director of the Federal Register ACTION: Final rule.
approved the incorporation by reference
the availability of this material at the
(IBR) of the service information listed in this SUMMARY: We are superseding FAA, call 425–227–1221. It is also
paragraph under 5 U.S.C. 552(a) and 1 CFR Airworthiness Directive (AD) 2010–06– available on the Internet at http://
part 51. 04, for certain Airbus Model A300 B2– www.regulations.gov by searching for
(2) You must use this service information 1C, B2–203, B2K–3C, B4–103, B4–203, and locating Docket No. FAA–2014–
as applicable to do the actions required by B4–2C airplanes; Model A310 series 0648.
this AD, unless this AD specifies otherwise.
(3) The following service information was
airplanes; Model A300 B4–600 series FOR FURTHER INFORMATION CONTACT: Dan
approved for IBR on February 2, 2016. airplanes; and Model A300 B4–600R Rodina, Aerospace Engineer,
(i) Bombardier Service Bulletin 100–25–21, series airplanes. AD 2010–06–04 International Branch, ANM–116,
Revision 02, dated July 25, 2013. required repetitive inspections to detect Transport Airplane Directorate, FAA,
(ii) Reserved. cracks of the pylon side panels (upper 1601 Lind Avenue SW., Renton, WA
(4) The following service information was section) at rib 8; and corrective actions 98057–3356; telephone 425–227–2125;
jstallworth on DSK7TPTVN1PROD with RULES
approved for IBR on May 5, 2011, (76 FR if necessary. This new AD continues to fax 425–227–1149.
17758, March 31, 2011). require repetitive inspections for
(i) Bombardier Service Bulletin A100–21– SUPPLEMENTARY INFORMATION:
08, dated June 18, 2009.
cracking of the pylons 1 and 2 side
panels (upper section) at rib 8 with Discussion
(ii) Bombardier Service Bulletin 100–25–
14, dated June 30, 2008. reduced compliance times, and We issued a notice of proposed
(iii) Bombardier Service Bulletin 100–25– corrective actions if necessary. This AD rulemaking (NPRM) to amend 14 CFR
21, dated June 30, 2008. also requires repetitive post-repair and part 39 to supersede AD 2010–06–04,
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![Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations 81169
Amendment 39–16228 ((75 FR 11428, 3 was not integrally taken into account as compliance times depend on whether
March 11, 2010); corrected May 4, 2010 this revision no longer identifies airplanes are short range or long range
(75 FR 23572)). AD 2010–06–04 applied configuration 3 aeroplanes. airplanes. We acknowledge that this
For the reasons described above, EASA causes additional complexity in tracking
to certain Airbus Model A300 B2–1C,
[AD] 2013–0136 is revised to exclude Airbus
B2–203, B2K–3C, B4–103, B4–203, B4– Mod 03599 from the applicability and to
and forecasting airplane utilization;
2C airplanes; Model A310 series delete the reference to the configuration 3 for however, the inspection schedule was
airplanes; Model A300 B4–600 series A300–600 aeroplanes. created by Airbus to offer operators the
airplanes; and Model A300 B4–600R greatest flexibility. Operators may elect
series airplanes. The NPRM published Corrective actions include doing a to inspect within the range that
in the Federal Register on September repair. This AD also provides an complies with both the long range and
22, 2014 (79 FR 56526). optional modification (installing a short range utilization in order to reduce
The European Aviation Safety Agency doubler), which would terminate the the complexity. We have not changed
(EASA), which is the Technical Agent repetitive inspections. Required actions this AD in this regard.
for the Member States of the European also include repetitive post-repair and Regarding AD 98–18–02, Amendment
Union, has issued EASA Airworthiness post-modification inspections and 39–10718 (63 FR 45689, August 27,
Directive 2013–0136R1, dated July 30, repair if necessary. You may examine 1998), at the time the FAA issued AD
2013 (referred to after this as the the MCAI in the AD docket on the 98–18–02, the required actions in
Mandatory Continuing Airworthiness Internet at http://www.regulations.gov/ Airbus Industrie Service Bulletin A300–
Information, or ‘‘the MCAI’’), to correct #!documentDetail;D=FAA-2014-0648- 57–6027, Revision 2, dated September
an unsafe condition on certain Airbus 0002. 13, 1994, contained inspection
Model A300 B2–1C, B2–203, B2K–3C, Comments thresholds and intervals based on
B4–103, B4–203, B4–2C airplanes; airplane flight cycles, and provided
We gave the public the opportunity to instructions for adjusting the flight cycle
Model A310 series airplanes; Model
participate in developing this AD. The threshold and interval using each
A300 B4–600 series airplanes; and
following presents the comment individual airplane’s AFT utilization.
Model A300 B4–600R series airplanes.
received on the NPRM (79 FR 56526, The FAA did not agree with the AFT
The MCAI states:
September 22, 2014) and the FAA’s method because it could result in a
Cracks were found on pylon side panels response.
(upper section) at rib 8 on Airbus A300, A310 different inspection threshold and
and A300–600 aeroplanes equipped with Request To Revise Method Used To interval for each individual airplane,
General Electric engines. Investigation of Determine Compliance Times and the FAA did not agree with
these findings indicated that this problem adjusting a flight cycle based threshold
was likely to also affect aeroplanes of this United Parcel Service (UPS) requested
and interval using the average flight
type design with other engine installations. that we revise the proposed compliance
time utilization without also having a
This condition, if not detected and times to be less complex. UPS stated
related flight hour based threshold and
corrected, could lead to reduced strength of that the proposed compliance times
interval.
the pylon primary structure, possibly contain a method known as ‘‘Average
resulting in pylon structural failure and in- Flight Time’’ (AFT) which results in a Conclusion
flight loss of an engine. variable flight hour limit and adds
Prompted by these findings, EASA issued We reviewed the available data,
unnecessary complexity to the threshold including the comment received, and
AD 2008–0181 [http://www.regulations.gov/
#!documentDetail;D=FAA-2009-0789-0002] table and subsequent inspection actions. determined that air safety and the
[which corresponds to FAA AD 2010–06–04, UPS added that use of the AFT method, public interest require adopting this AD
Amendment 39–16228 ((75 FR 11428, March along with a lack of standard procedures as proposed except for minor editorial
11, 2010); corrected May 4, 2010 (75 FR for implementing the AFT method changes. We have determined that these
23572))] to require repetitive detailed visual would create uncertainty for operators minor changes:
inspections [of the pylon side panels (upper and inspectors trying to determine the • Are consistent with the intent that
section) at rib 8] and, depending on correct compliance time. UPS stated
aeroplane configuration and/or findings, the
was proposed in the NPRM (79 FR
that in review of prior FAA ADs, 56526, September 22, 2014) for
accomplishment of applicable corrective
action(s). including AD 98–18–02, Amendment correcting the unsafe condition; and
Since that [EASA] AD was issued, a fleet 39–10718 (63 FR 45689, August 27, • Do not add any additional burden
survey and updated Fatigue and Damage 1998), that the FAA does not concur upon the public than was already
Tolerance analyses have been performed in with the AFT compliance time proposed in the NPRM (79 FR 56526,
order to substantiate the second A300–600 methodology as ‘‘. . . such adjustments September 22, 2014).
Extended Service Goal (ESG2) exercise. The may not address the unsafe condition in
results of these analyses have shown that the a timely manner’’ and ‘‘. . . they (AFT Related Service Information Under 1
risk for these aeroplanes is higher than compliance times) do not fit into the AD CFR Part 51
initially determined and consequently, the
tracking process for operators or for Airbus has issued the following
threshold and interval must be reduced to
allow timely detection of these cracks and Principle Maintenance Inspectors service information. The service
the accomplishment of applicable correction (PMIs) attempting to ascertain information describes procedures for
action(s). compliance with ADs.’’ repetitive inspections for cracking of the
EASA issued AD 2013–0136 [http:// UPS compiled a table of fixed pylons 1 and 2 side panels (upper
ad.easa.europa.eu/ad/2013-0136R1] which compliance times that it suggested section) at rib 8 with reduced
retained the requirements of EASA AD 2008– would be simpler to use instead of the compliance times, and corrective
jstallworth on DSK7TPTVN1PROD with RULES
0181, which was superseded, and required proposed AFT-based compliance times. actions if necessary. This service
the inspections to be accomplished within information also describes procedures
We disagree with the commenter’s
reduced thresholds and intervals.
After publication of EASA AD 2013–0136, request to revise the compliance times for post-modification and post-repair
it appeared that Airbus Mod 03599 had no in this AD. The compliance times, as detailed inspections for cracking, as
influence on the aeroplane configuration proposed, use fixed flight-cycle and applicable, of the left-hand (LH) and
affected by this AD. At the same time Airbus flight-hour compliance times. For only right-hand (RH) side panels of pylons 1
Service Bulletin (SB) A30–54–6015 Revision Model A310 series airplanes, the and 2, and repair if necessary. This
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![81170 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations
service information is reasonably • Airbus Service Bulletin A300–54– course of business or by the means
available because the interested parties 6015, Revision 03, excluding identified in the ADDRESSES section.
have access to it through their normal Appendixes 1, 2, 3, and 5; including • Airbus Service Bulletin A300–54–
course of business or by the means Appendix 4; dated April 11, 2013. 0081, dated August 11, 1993.
identified in the ADDRESSES section. Airbus has also issued the following • Airbus Service Bulletin A310–54–
• Airbus Service Bulletin A300–54– 2024, dated August 11, 1993.
service information. This service
• Airbus Service Bulletin A300–54–
0075, Revision 03, excluding information describes procedures for
6021, Revision 02, dated May 21, 2008.
Appendixes 1, 2, 3, and 5; including modifying by installing a doubler on the
Appendix 4; dated March 27, 2013. LH pylon 1 and RH pylon 2, on pylon Costs of Compliance
• Airbus Service Bulletin A310–54– side panels (upper section), at rib 8. We estimate that this AD affects 156
2018, Revision 03, excluding This service information is reasonably airplanes of U.S. registry. We estimate
Appendixes 1, 2, 3, and 5; including available because the interested parties the following costs to comply with this
Appendix 4; dated April 11, 2013. have access to it through their normal AD:
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Inspection [retained actions from 4 work-hours × $85 per hour = $340 .......... $0 $340 .......................... $53,040.
AD 2010–06–04, Amendment
39–16228 ((75 FR 11428,
March 11, 2010); corrected
May 4, 2010 (75 FR 23572))].
Inspection [new actions] .............. 24 work-hours × $85 per hour = $2,040 per 0 $2,040 per inspection $318,240 per inspec-
inspection cycle. cycle. tion cycle.
We estimate the following costs to do required based on the results of the determining the number of aircraft that
any necessary repairs that would be inspection. We have no way of might need these repairs:
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Repair .................................. 58 work-hours × $85 per hour = $4,930 ....................... $3,910 ................................ $8,840.
Optional Modification ........... Up to 48 work-hours × $85 per hour = $4,080 ............. Up to $1,026 ...................... Up to $5,106.
Authority for This Rulemaking not have a substantial direct effect on evaluation, any comments received, and
the States, on the relationship between other information. The street address for
Title 49 of the United States Code the national government and the States, the Docket Operations office (telephone
specifies the FAA’s authority to issue or on the distribution of power and 800–647–5527) is in the ADDRESSES
rules on aviation safety. Subtitle I, responsibilities among the various section.
section 106, describes the authority of levels of government.
the FAA Administrator. ‘‘Subtitle VII: List of Subjects in 14 CFR Part 39
For the reasons discussed above, I
Aviation Programs,’’ describes in more certify that this AD:
detail the scope of the Agency’s Air transportation, Aircraft, Aviation
1. Is not a ‘‘significant regulatory safety, Incorporation by reference,
authority. action’’ under Executive Order 12866; Safety.
We are issuing this rulemaking under 2. Is not a ‘‘significant rule’’ under the
the authority described in ‘‘Subtitle VII, DOT Regulatory Policies and Procedures Adoption of the Amendment
Part A, Subpart III, Section 44701: (44 FR 11034, February 26, 1979);
General requirements.’’ Under that Accordingly, under the authority
3. Will not affect intrastate aviation in delegated to me by the Administrator,
section, Congress charges the FAA with Alaska; and
promoting safe flight of civil aircraft in the FAA amends 14 CFR part 39 as
4. Will not have a significant
air commerce by prescribing regulations follows:
economic impact, positive or negative,
for practices, methods, and procedures on a substantial number of small entities PART 39—AIRWORTHINESS
the Administrator finds necessary for under the criteria of the Regulatory DIRECTIVES
safety in air commerce. This regulation Flexibility Act.
is within the scope of that authority
Examining the AD Docket ■ 1. The authority citation for part 39
because it addresses an unsafe condition
continues to read as follows:
that is likely to exist or develop on You may examine the AD docket on
jstallworth on DSK7TPTVN1PROD with RULES
products identified in this rulemaking the Internet at http:// Authority: 49 U.S.C. 106(g), 40113, 44701.
action. www.regulations.gov/#!docketDetail;D= § 39.13 [Amended]
FAA-2014-0648; or in person at the
Regulatory Findings
Docket Management Facility between 9 ■ 2. The FAA amends § 39.13 by
We determined that this AD will not a.m. and 5 p.m., Monday through removing Airworthiness Directive (AD)
have federalism implications under Friday, except Federal holidays. The AD 2010–06–04, Amendment 39–16228 ((75
Executive Order 13132. This AD will docket contains this AD, the regulatory FR 11428, March 11, 2010); corrected
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![81174 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations
of the local flight standards district office/ Office—EAW, 1 Rond Point Maurice impeller function and RAT pump
certificate holding district office. The AMOC Bellonte, 31707 Blagnac Cedex, France; pressurization capability, which, if
approval letter must specifically reference telephone +33 5 61 93 36 96; fax +33 5 61 preceded by a total engine flame-out,
this AD. 93 44 51; email account.airworth-eas@
(ii) AMOCs approved previously for AD
could result in the loss of control of the
airbus.com; Internet http://www.airbus.com.
2010–06–04, Amendment 39–16228 ((75 FR (6) You may view this service information airplane.
11428, March 11, 2010); corrected May 4, at the FAA, Transport Airplane Directorate, DATES: This AD becomes effective
2010 (75 FR 23572)); are approved as AMOCs 1601 Lind Avenue SW., Renton, WA. For February 2, 2016.
for the corresponding provisions of this AD. information on the availability of this The Director of the Federal Register
(2) Contacting the Manufacturer: As of the material at the FAA, call 425–227–1221.
effective date of this AD, for any requirement approved the incorporation by reference
(7) You may view this service information
in this AD to obtain corrective actions from of certain publications listed in this AD
that is incorporated by reference at the
a manufacturer, the action must be National Archives and Records as of February 2, 2016.
accomplished using a method approved by Administration (NARA). For information on ADDRESSES: You may examine the AD
the Manager, International Branch, ANM– the availability of this material at NARA, call docket on the Internet at http://
116, Transport Airplane Directorate, FAA; or 202–741–6030, or go to: http://
EASA; or Airbus’s EASA DOA. If approved
www.regulations.gov/
www.archives.gov/federal-register/cfr/ibr- #!docketDetail;D=FAA-2015-0076; or in
by the DOA, the approval must include the locations.html.
DOA-authorized signature. person at the Docket Management
Issued in Renton, Washington, on Facility, U.S. Department of
(o) Related Information December 8, 2015. Transportation, Docket Operations, M–
(1) Refer to Mandatory Continuing Michael Kaszycki, 30, West Building Ground Floor, Room
Airworthiness Information (MCAI) EASA Acting Manager, Transport Airplane W12–140, 1200 New Jersey Avenue SE.,
Airworthiness Directive 2013–0136R1, dated Directorate, Aircraft Certification Service. Washington, DC.
July 30, 2013, for related information. You
may examine the MCAI in the AD docket on [FR Doc. 2015–31603 Filed 12–28–15; 8:45 am] For Airbus service information
the Internet at http://www.regulations.gov/ BILLING CODE 4910–13–P identified in this final rule, contact
#!documentDetail;D=FAA-2014-0648-0002. Airbus SAS, Airworthiness Office—
(2) Service information identified in this EAL, 1 Rond Point Maurice Bellonte,
AD that is not incorporated by reference is DEPARTMENT OF TRANSPORTATION 31707 Blagnac Cedex, France; telephone
available at the addresses specified in +33 5 61 93 36 96; fax +33 5 61 93 45
paragraphs (p)(5) and (p)(6) of this AD. Federal Aviation Administration 80; email airworthiness.A330A340@
(p) Material Incorporated by Reference airbus.com; Internet http://
14 CFR Part 39 www.airbus.com. For Hamilton
(1) The Director of the Federal Register
approved the incorporation by reference [Docket No. FAA–2015–0076; Directorate Sundstrand service information
(IBR) of the service information listed in this Identifier 2013–NM–246–AD; Amendment identified in this AD, contact Hamilton
paragraph under 5 U.S.C. 552(a) and 1 CFR 39–18350; AD 2015–26–02] Sundstrand, Technical Publications,
part 51. Mail Stop 302–9, 4747 Harrison
(2) You must use this service information RIN 2120–AA64
Avenue, P.O. Box 7002, Rockford, IL
as applicable to do the actions required by
Airworthiness Directives; Airbus 61125–7002; telephone 860–654–3575;
this AD, unless this AD specifies otherwise.
(3) The following service information was Airplanes fax 860–998–4564; email
approved for IBR on February 2, 2016. tech.solutions@hs.utc.com; Internet
(i) Airbus Service Bulletin A300–54–0075, AGENCY: Federal Aviation http://www.hamiltonsundstrand.com.
Revision 03, excluding Appendixes 1, 2, 3, Administration (FAA), Department of You may view this referenced service
and 5; including Appendix 4; dated March Transportation (DOT). information at the FAA, Transport
27, 2013. ACTION: Final rule. Airplane Directorate, 1601 Lind Avenue
(ii) Airbus Service Bulletin A300–54–0081, SW., Renton, WA. For information on
dated August 11, 1993. SUMMARY: We are adopting a new the availability of this material at the
(iii) Airbus Service Bulletin A300–54– airworthiness directive (AD) for all
6015, Revision 03, excluding Appendixes 1, FAA, call 425–227–1221. It is also
Airbus Model A330–200, A330–200 available on the Internet at http://
2, 3, and 5; including Appendix 4; dated Freighter, and A330–300 series
April 11, 2013. www.regulations.gov by searching for
(iv) Airbus Service Bulletin A300–54–
airplanes; and Airbus Model A340–200, and locating Docket No. FAA–2015–
6021, Revision 02, dated May 21, 2008. A340–300, A340–500, and A340–600 0076.
(v) Airbus Service Bulletin A310–54–2018, series airplanes. This AD was prompted
Revision 03, excluding Appendixes 1, 2, 3, by a report that, during a production FOR FURTHER INFORMATION CONTACT:
and 5; including Appendix 4; dated April 11, flight test, the ram air turbine (RAT) did Vladimir Ulyanov, Aerospace Engineer,
2013. not pressurize the green hydraulic International Branch, ANM–116,
(vi) Airbus Service Bulletin A310–54– system. For certain airplanes, this AD Transport Airplane Directorate, FAA,
2024, dated August 11, 1993. requires identification of the part 1601 Lind Avenue SW., Renton, WA
(4) The following service information was 98057–3356; telephone 425–227–1138;
approved for IBR on April 15, 2010 ((75 FR
number, serial number, and standard of
the RAT pump, RAT module, RAT fax 425–227–1149.
11428, March 11, 2010); corrected May 4,
2010 (75 FR 23572)). actuator, and RAT lower gearbox SUPPLEMENTARY INFORMATION:
(i) Airbus Mandatory Service Bulletin assembly; replacement of the balance
A300–54–0075, excluding Appendixes 1, 2, weight screw, modification of the Discussion
and 3, Revision 02, dated June 26, 2008. actuator coil spring, modification of the We issued a notice of proposed
jstallworth on DSK7TPTVN1PROD with RULES
(ii) Airbus Mandatory Service Bulletin actuator, an inspection of the anti-stall rulemaking (NPRM) to amend 14 CFR
A300–54–6015, excluding Appendixes 1, 2, valve for correct installation in the RAT part 39 by adding an AD that would
and 3, Revision 02, dated June 26, 2008.
(iii) Airbus Mandatory Service Bulletin
pump housing; and corrective actions if apply to all Airbus Model A330–200,
A310–54–2018, excluding Appendixes 1, 2, necessary. For certain other airplanes, A330–200 Freighter, and A330–300
and 3, Revision 02, dated June 26, 2008. this AD requires re-identification or series airplanes; and Airbus Model
(5) For service information identified in replacement of the RAT module. We are A340–200, A340–300, A340–500, and
this AD, contact Airbus SAS, Airworthiness issuing this AD to prevent loss of the A340–600 series airplanes. The NPRM
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Document Created: 2015-12-29 10:15:03
Document Modified: 2015-12-29 10:15:03
| 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 February 2, 2016. | |
| 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 81168 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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