Airworthiness Directives; Airbus Airplanes, 70447-70453 [2014-26986]

Download as PDF Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations (h) Replacement of Forward Crew Oxygen Supply Hose For airplanes identified as Group 2 in Boeing Alert Service Bulletin B787–81205– SB350001–00, Issue 001, dated August 22, 2013: Within 60 months after the effective date of this AD, replace the forward crew oxygen supply hose with a new nonconductive forward oxygen supply hose, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin B787–81205–SB350001–00, Issue 001, dated August 22, 2013. (i) Exception to Service Information Paragraph III.A., ‘‘Verification,’’ of B/E Aerospace Service Bulletin 4421086–35–001, Rev. 002, dated July 9, 2013, has a typographical error. The last sentence in that paragraph states, ‘‘If the decal shows PN 4421086–101, continue with the retrofit steps in paragraph II.B.’’ The sentence should refer to paragraph III.B. of B/E Aerospace Service Bulletin 4421086–35–001, Rev. 002, dated July 9, 2013. (j) Parts Installation Prohibition As of the effective date of this AD, no person may install a distribution manifold having B/E Aerospace P/N 4421086–101; a flexible supply hose having B/E Aerospace P/ N 4421189–016; or a supply hose having Boeing P/N 4421189–023; on any airplane. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (l) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (m) 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 the AD specifies otherwise. (i) Boeing Alert Service Bulletin B787– 81205–SB350001–00, Issue 001, dated August 22, 2013. (ii) B/E Aerospace Service Bulletin 4421086–35–001, Rev. 002, dated July 9, 2013. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766– 5680; Internet https:// www.myboeingfleet.com. (4) For B/E service information identified in this AD, contact B/E Aerospace, Inc., Commercial Aircraft Products Group, 10800 Pfluum Road, Lenexa, KS 66215; phone: 913– 338–9800; fax: 913–469–8419. (5) You may view this service information at 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. (6) 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/ibrlocations.html. Issued in Renton, Washington, on November 5, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–27359 Filed 11–25–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0132; Directorate Identifier 2012–NM–007–AD; Amendment 39–18023; AD 2014–23–07] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. mstockstill on DSK4VPTVN1PROD with RULES (l) Related Information AGENCY: For more information about this AD, contact Susan Monroe, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, Seattle Aircraft Certification Office, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425– 917–6457; fax: 425–917–6590; email: susan.l.monroe@faa.gov. SUMMARY: VerDate Sep<11>2014 16:25 Nov 25, 2014 Jkt 235001 We are superseding Airworthiness Directive (AD) 2004–16– 01 for certain Airbus Model A330–200 and –300 series airplanes and Model PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 70447 A340–200 and –300 series airplanes. AD 2004–16–01 required repetitive inspections for cracking of the chromed area of the left and right piston rods for the main landing gear (MLG) retraction actuators, and related investigative and corrective actions if necessary. This new AD requires repetitive draining of any fluid from the retraction actuator piston rod internal volume and sealing of the vent hole; repetitive ultrasonic inspections of the upper end of the piston rods, and corrective actions if necessary; a one-time ultrasonic inspection (longitudinal and circumferential) of the full length of the piston rod, and corrective actions if necessary; and a terminating modification of the left-hand and righthand MLG retraction actuators. This AD was prompted by reports of the piston rods for the MLG retraction actuators rupturing during flight. We are issuing this AD to prevent cracking of the piston rods for the MLG retraction actuators, which could result in rupture of a piston rod, non-damped extension of the MLG, high loads on the fully extended MLG, and consequent reduced structural integrity of the MLG. DATES: This AD becomes effective December 31, 2014. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 31, 2014. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of August 19, 2004 (69 FR 46979, August 4, 2004). ADDRESSES: You may examine the AD docket on the Internet at http://www. regulations.gov/#!docketDetail;D=FAA2014-0132; 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—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, E:\FR\FM\26NOR1.SGM 26NOR1 70448 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. SUPPLEMENTARY INFORMATION: mstockstill on DSK4VPTVN1PROD with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2004–16–01, Amendment 39–13757 (69 FR 46979, August 4, 2004). AD 2004–16–01 applied to certain Airbus Model A330– 200 and –300 series airplanes and Model A340–200 and –300 series airplanes. The NPRM published in the Federal Register on February 6, 2014 (79 FR 7098; corrected March 20, 2014 (79 FR 15555)). The NPRM was prompted by reports of the piston rods for the MLG retraction actuators rupturing during flight. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2011– 0178R1, dated March 6, 2012, corrected March 7, 2012 (for Model A340–200 and –300 series airplanes); and EASA AD 2011–0179R1, dated March 6, 2012 (for Model A330–200 and –300 series airplanes) (both referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’); to correct an unsafe condition for the specified products. EASA AD 2011–0178R1, dated March 6, 2012, corrected March 7, 2012, states: During an approach phase, the flight crew of an A330 aeroplane had to perform a freefall extension of the left-hand (LH) MLG. Rupture of the LH MLG retraction actuator piston rod was found near the rod attachment point. The inspection revealed at the location of the rupture the presence of corrosion resulting from incorrect application of the anticorrosion protection, and circumferential cracks resulting from normal operational loading effects. Since the above rupture, new cases of crack propagation along the length of the piston rod occurred. These ruptures led to a nondamped extension of the landing gear. Fully extended, the landing gear assembly was submitted to high loads jeopardising its structural integrity. This condition, if not detected and corrected, could lead to MLG failure during landing or roll-out and consequent damage to the aeroplane and injury to occupants. ´ ´ DGAC [Direction Generale de l’Aviation Civile] France issued AD F–2005–098 [http:// ad.easa.europa.eu/blob/easa_ad_2005_5887_ F20050980tb_superseded.pdf/AD_F-2005098_1] (EASA approval 2005–5887) [and AD F–2005–099 [http://ad.easa.europa.eu/blob/ easa_ad_2005_5888_F20050990tb_ superseded.pdf/AD_F-2005-099_2] (EASA approval 2005–5888)] to address this unsafe condition [the FAA issued AD 2004–16–01, Amendment 39–13757 (69 FR 46979, August 4, 2004)]. Since that [DGAC France] AD was issued, the results of extensive investigation VerDate Sep<11>2014 16:25 Nov 25, 2014 Jkt 235001 determined that the presence of water in the internal volume of the piston rod can lead to the formation of ice which represents a potential source of high magnitude tensile hoop stresses in the material of the rod, leading to propagation of longitudinal crack in the body of the piston rod. Prompted by these findings, EASA issued AD 2006–0301 [http://ad.easa.europa.eu/ blob/easa_ad_2006_0301_R2_ superseded.pdf/AD_2006-0301R2_1], partially retaining the requirements of DGAC France AD F–2005–099, which was superseded, and to revise the inspection requirements as follows: a. Extend the repetitive inspections interval for the removal of fluid from the internal volume of the piston rod using flight cycles in lieu of flight hours as this better represents the mechanism for the accumulation of water within the piston rod. b. Remove the preliminary visual inspection from the ultrasonic longitudinal inspection of the upper end of the piston rod. c. Add a new one-time ultrasonic longitudinal and circumferential inspection of the full piston rod length to eliminate any parts that exhibit severe corrosion along the internal length of the piston rod. d. Require installation of new design hollow piston rod Part Number (P/N) 114256328 (Airbus mod. 52980—SB A340– 32–4222 Revision 01) without a vent hole, thus eliminating moisture ingress as the terminating action. EASA AD 2006–0301 was later revised: —at revision 01, to correct a number of typographical errors and to add reference to Airbus SB A340–32–4212 Revision 04, and —at revision 02 to extend the inspections threshold from 3 to 6 years in service usage for retraction actuator piston rod P/N 114256321 issue 06 which was reidentified to P/N 114256326 issue 01 in accordance with the instructions of Airbus SB A340–32–4260. More recently, the sampling of piston rod P/N 114256326 issue 1 and P/N 114256321 issue 06 have confirmed the need to replace all retraction actuator piston rods with a piston rod P/N114256328. For the reasons described above, this [EASA] AD at original issue retained the requirements of EASA AD 2006–0301R2 (http://ad.easa.europa.eu/blob/easa_ad_ 2006_0301_R2_superseded.pdf/AD_20060301R2_1), which is superseded, and required the replacement of all retraction actuator piston rods with a piston rod P/N 114256328, which constitutes terminating action to the repetitive requirements of this AD. This [EASA] AD is revised to clarify that aeroplanes on which Airbus mod. 52980 has been embodied in production are not required to accomplish the reidentification of MLG retraction actuator P/N 114256002–055 which is mentioned in the accomplishment instructions of Airbus SB A340–32–4222 Revision 03. This [EASA] AD has been republished to correct a typographical mistake of the applicable Airbus SB number in the Applicability (in the Note) and in the Reason sections of this [EASA] AD. PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-01320003. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 7098, February 6, 2014; corrected March 20, 2014 (79 FR 15555)), and the FAA’s response to each comment. Request To Reference Latest Service Information Delta Airlines requested that we reference the latest Airbus service information, which is Airbus Service Bulletin A330–32–3180, Revision 05, dated January 27, 2014. Delta Airlines further requested that we provide credit for actions previously accomplished using Airbus Service Bulletin A330–32– 3180, Revision 03, dated January 28, 2011; and Airbus Service Bulletin A330–32–3180, Revision 04, dated July 30, 2013. We agree with Delta Airlines’ comment to reference the latest service information. Airbus Service Bulletin A330–32–3180, Revision 05, dated January 27, 2014, provides the latest information on the modification required by this AD. This service bulletin specifies two additional workhours for re-identification of the part number of the MLG retraction actuator for Model A330–200 and –300 series airplanes at configuration 3, which were modified as described in Airbus Service Bulletin A330–32–3180, Revision 03, dated January 28, 2011. Reidentification of the MLG retraction actuator may be considered as a logical outgrowth of the proposed AD (79 FR 7098, February 6, 2014; corrected March 20, 2014 (79 FR 15555)) requirements. Airbus has also released Service Bulletin A340–32–4222, Revision 04, dated July 30, 2013. This service bulletin also specifies two additional work-hours for re-identification of the part number of the MLG retraction actuator for Model A340 series airplanes. There are currently no U.S.registered Model A340 series airplanes. We have revised paragraphs (s) and (t) of this AD to specify Airbus Service Bulletin A330–32–3180, Revision 05, dated January 27, 2014; and Airbus Service Bulletin A340–32–4222, Revision 04, dated July 30, 2013; as the appropriate sources of service information for the required actions in those paragraphs. We have also revised paragraphs (w)(2) and (w)(3) of this AD to provide credit for previous actions E:\FR\FM\26NOR1.SGM 26NOR1 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations mstockstill on DSK4VPTVN1PROD with RULES accomplished using Airbus Service Bulletin A330–32–3180, Revision 03, dated January 28, 2011; Airbus Service Bulletin A330–32–3180, Revision 04, dated July 30, 2013; and Airbus Service Bulletin A340–32–4222, Revision 03, dated January 28, 2011; as applicable. ‘‘Contacting the Manufacturer’’ Paragraph in This AD Since late 2006, we have included a standard paragraph titled ‘‘Airworthy Product’’ in all MCAI ADs in which the FAA develops an AD based on a foreign authority’s AD. The MCAI or referenced service information in an FAA AD often directs the owner/operator to contact the manufacturer for corrective actions, such as a repair. Briefly, the Airworthy Product paragraph allowed owners/ operators to use corrective actions provided by the manufacturer if those actions were FAA-approved. In addition, the paragraph stated that any actions approved by the State of Design Authority (or its delegated agent) are considered to be FAA-approved. In the NPRM (79 FR 7098, February 6, 2014; corrected March 20, 2014 (79 FR 15555)), we proposed to prevent the use of repairs that were not specifically developed to correct the unsafe condition, by requiring that the repair approval provided by the State of Design Authority or its delegated agent specifically refer to this FAA AD. This change was intended to clarify the method of compliance and to provide operators with better visibility of repairs that are specifically developed and approved to correct the unsafe condition. In addition, we proposed to change the phrase ‘‘its delegated agent’’ to include a design approval holder (DAH) with State of Design Authority design organization approval (DOA), as applicable, to refer to a DAH authorized to approve required repairs for the proposed AD. No comments were provided to the NPRM (79 FR 7098, February 6, 2014; corrected March 20, 2014 (79 FR 15555)) about these proposed changes. However, a comment was provided for an NPRM having Directorate Identifier 2012–NM– 101–AD (78 FR 78285, December 26, 2013). The commenter stated the following: ‘‘The proposed wording, being specific to repairs, eliminates the interpretation that Airbus messages are acceptable for approving minor deviations (corrective actions) needed during accomplishment of an AD mandated Airbus service bulletin.’’ This comment has made the FAA aware that some operators have misunderstood or misinterpreted the Airworthy Product paragraph to allow VerDate Sep<11>2014 16:25 Nov 25, 2014 Jkt 235001 the owner/operator to use messages provided by the manufacturer as approval of deviations during the accomplishment of an AD-mandated action. The Airworthy Product paragraph does not approve messages or other information provided by the manufacturer for deviations to the requirements of the AD-mandated actions. The Airworthy Product paragraph only addresses the requirement to contact the manufacturer for corrective actions for the identified unsafe condition and does not cover deviations from other AD requirements. However, deviations to AD-required actions are addressed in 14 CFR 39.17, and anyone may request the approval for an alternative method of compliance to the AD-required actions using the procedures found in 14 CFR 39.19. To address this misunderstanding and misinterpretation of the Airworthy Product paragraph, we have changed the paragraph and retitled it ‘‘Contacting the Manufacturer.’’ This paragraph now clarifies that for any requirement in this AD to obtain corrective actions from a manufacturer, the actions must be accomplished using a method approved by the FAA, the European Aviation Safety Agency (EASA), or Airbus’s EASA Design Organization Approval (DOA). The Contacting the Manufacturer paragraph also clarifies that, if approved by the DOA, the approval must include the DOA-authorized signature. The DOA signature indicates that the data and information contained in the document are EASA-approved, which is also FAAapproved. Messages and other information provided by the manufacturer that do not contain the DOA-authorized signature approval are not EASA-approved, unless EASA directly approves the manufacturer’s message or other information. This clarification does not remove flexibility previously afforded by the Airworthy Product paragraph. Consistent with long-standing FAA policy, such flexibility was never intended for required actions. This is also consistent with the recommendation of the Airworthiness Directive Implementation Aviation Rulemaking Committee to increase flexibility in complying with ADs by identifying those actions in manufacturers’ service instructions that are ‘‘Required for Compliance’’ with ADs. We continue to work with manufacturers to implement this recommendation. But once we determine that an action is required, any deviation from the requirement must be approved as an alternative method of compliance. PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 70449 Other commenters to the NPRM having Directorate Identifier 2012–NM– 101–AD (78 FR 78285, December 26, 2013) pointed out that in many cases the foreign manufacturer’s service bulletin and the foreign authority’s MCAI might have been issued some time before the FAA AD. Therefore, the DOA might have provided U.S. operators with an approved repair, developed with full awareness of the unsafe condition, before the FAA AD is issued. Under these circumstances, to comply with the FAA AD, the operator would be required to go back to the manufacturer’s DOA and obtain a new approval document, adding time and expense to the compliance process with no safety benefit. Based on these comments, we removed the requirement that the DAHprovided repair specifically refer to this AD. Before adopting such a requirement, the FAA will coordinate with affected DAHs and verify they are prepared to implement means to ensure that their repair approvals consider the unsafe condition addressed in this AD. Any such requirements will be adopted through the normal AD rulemaking process, including notice-and-comment procedures, when appropriate. We also have decided not to include a generic reference to either the ‘‘delegated agent’’ or ‘‘DAH with State of Design Authority design organization approval,’’ but instead we have provided the specific delegation approval granted by the State of Design Authority for the DAH. Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes: • Are consistent with the intent that was proposed in the NPRM (79 FR 7098, February 6, 2014; corrected March 20, 2014 (79 FR 15555)) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 7098, February 6, 2014; corrected March 20, 2014 (79 FR 15555)). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD affects 24 Model A330–200 and –300 series airplanes of U.S. registry. There are no E:\FR\FM\26NOR1.SGM 26NOR1 70450 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations Model A340–200 or –300 series airplanes of U.S. registry. We estimate that it will take about 67 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $56,000 per product (2 actuators). Based on these figures, we estimate the cost of this AD on U.S. operators to be $1,480,680, or $61,695 per product. In addition, we estimate that any necessary follow-on actions will take about 38 work-hours and require parts costing $56,000 (2 actuators), for a cost of $59,230 per product. We have no way of determining the number of aircraft that might need these actions. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. mstockstill on DSK4VPTVN1PROD with RULES Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES–200. 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 VerDate Sep<11>2014 16:25 Nov 25, 2014 Jkt 235001 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. § 39.13 Regulatory Findings (a) Effective Date This AD becomes effective December 31, 2014. 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-2014-0132; 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2004–16–01, Amendment 39–13757 (69 FR 46979, August 4, 2004), and adding the following new AD: ■ 2014–23–07 Airbus: Amendment 39–18023. Docket No. FAA–2014–0132; Directorate Identifier 2012–NM–007–AD. (b) Affected ADs This AD replaces AD 2004–16–01, Amendment 39–13757 (69 FR 46979, August 4, 2004). (c) Applicability This AD applies to Airbus Model A330– 201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340–211, –212, –213, –311, –312, and –313 airplanes; certificated in any category; all manufacturer serial numbers, except for those airplanes that have had Airbus Modification 52980 incorporated in production on both main landing gear (MLG) units, or airplanes that have had Airbus Modification 54500 incorporated in production. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Reason This AD was prompted by reports of the piston rods for the MLG retraction actuators rupturing during flight. We are issuing this AD to prevent cracking of the piston rods for the MLG retraction actuators, which could result in rupture of a piston rod, non-damped extension of the MLG, high loads on the fully extended MLG, and consequent reduced structural integrity of the MLG. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Detailed Inspections At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD: Do a detailed inspection for cracking of the visible chromed area of the MLG retraction actuator piston rods in the fully extended position, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 32–3173, Revision 05, dated September 26, 2008 (for Model A330–200 and –300 series airplanes); or Airbus Service Bulletin A340– 32–4212, Revision 05, dated September 26, 2008 (for Model A340–200 and –300 series airplanes). Repeat the inspection thereafter at intervals not to exceed 8 days until the actions required by paragraphs (j) and (o) of this AD are accomplished. (1) For MLG retraction actuator piston rods that have not had a detailed inspection accomplished as of the effective date of this AD, as described in any applicable service information specified in paragraph (h)(1) or (h)(2) of this AD: At the applicable time E:\FR\FM\26NOR1.SGM 26NOR1 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (i) For MLG retraction actuator piston rods having part number (P/N) 114256309 or P/N 114256321 issue 03: Do the inspection within 60 days after the effective date of this AD, or before the MLG retraction actuator has been in service 36 months, whichever occurs later. (ii) For MLG retraction actuator piston rods having P/N 114256326 issue 01 or P/N 114256321 issue 06: Do the inspection within 60 days after the effective date of this AD, or before the MLG retraction actuator has been in service 72 months, whichever occurs later. (2) For MLG retraction actuator piston rods having P/N 114256309, P/N 114256321 issue 03, P/N 114256326 issue 01, or P/N 114256321 issue 06, that have had a detailed inspection accomplished as of the effective date of this AD, as described in the applicable service information specified in paragraph (h)(1) or (h)(2) of this AD: Inspect within 8 days after the effective date of this AD. (h) Service Information for Determining Airplane Configuration for the Actions Required by Paragraph (g) of This AD (1) For Model A330–200 and –300 series airplanes: (i) Airbus Service Bulletin A330–32–3173, Revision 01, dated June 16, 2004; (ii) Airbus Service Bulletin A330–32–3173, Revision 02, dated May 11, 2005; (iii) Airbus Service Bulletin A330–32– 3173, Revision 03, dated March 13, 2006; (iv) Airbus Service Bulletin A330–32– 3173, Revision 04, dated June 12, 2006; or (v) Airbus Service Bulletin A330–32–3173, Revision 05, dated September 26, 2008. (2) For Model A340–200 and –300 series airplanes: (i) Airbus Service Bulletin A340–32–4212, Revision 01, dated June 16, 2004; (ii) Airbus Service Bulletin A340–32–4212, Revision 02, dated May 11, 2005; (iii) Airbus Service Bulletin A340–32– 4212, Revision 03, dated March 13, 2006; (iv) Airbus Service Bulletin A340–32– 4212, Revision 04, dated June 12, 2006; or (v) Airbus Service Bulletin A340–32–4212, Revision 05, dated September 26, 2008. mstockstill on DSK4VPTVN1PROD with RULES (i) Corrective Action for Cracking If any cracking is found during any inspection required by paragraph (g) of this AD: Before further flight, replace the MLG retraction actuator with a new or serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–32–3173, Revision 05, dated September 26, 2008 (for Model A330– 200 and –300 series airplanes); or Airbus Service Bulletin A340–32–4212, Revision 05, dated September 26, 2008 (for Model A340– 200 and –300 series airplanes). (j) Repetitive Fluid Draining and Vent Hole Sealing At the applicable time specified in paragraph (j)(1) or (j)(2) of this AD: Drain any fluid from the retraction actuator piston rod internal volume and seal the vent hole, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 32–3173, Revision 05, dated September 26, 2008 (for Model A330–200 and –300 series VerDate Sep<11>2014 16:25 Nov 25, 2014 Jkt 235001 airplanes); or Airbus Service Bulletin A340– 32–4212, Revision 05, dated September 26, 2008 (for Model A340–200 and –300 series airplanes). Repeat the draining and sealing thereafter at intervals not to exceed 1,000 flight cycles or 24 months, whichever occurs first. (1) For MLG retraction actuator piston rods that have not been inspected and have not had the fluid drained as of the effective date of this AD, as described in the applicable service information specified in paragraph (k)(1) or (k)(2) of this AD: At the applicable time specified in paragraph (j)(1)(i) or (j)(1)(ii) of this AD. (i) For MLG retraction actuator piston rods having P/N 114256309 or P/N 114256321 issue 03: Do the draining and sealing within 60 days after the effective date of this AD, or before the MLG retraction actuator has been in service 36 months, whichever occurs later. (ii) For MLG retraction actuator piston rods having P/N 114256326 issue 01 or P/N 114256321 issue 06: Do the draining and sealing within 60 days after the effective date of this AD, or before the MLG retraction actuator has been in service 72 months, whichever occurs later. (2) For MLG retraction actuator piston rods having P/N 114256309, P/N 114256321 issue 03, P/N 114256326 issue 01, or P/N 114256321 issue 06, that have been inspected and the fluid drained as of the effective date of this AD, as described in the applicable service information specified in paragraph (k)(1) or (k)(2) of this AD: Do the draining and sealing at the later of the times specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD. (i) Within 1,000 flight cycles or 24 months, whichever occurs first, from the last inspection and fluid drainage accomplished in accordance with the requirements of paragraph (j) of this AD. (ii) Within 60 days after the effective date of this AD. (k) Service Information for Determining Airplane Configuration for the Actions Required by Paragraph (j) of This AD (1) For Model A330–200 and –300 series airplanes: (i) Airbus Service Bulletin A330–32–3173, Revision 02, dated May 11, 2005; (ii) Airbus Service Bulletin A330–32–3173, Revision 03, dated March 13, 2006; (iii) Airbus Service Bulletin A330–32– 3173, Revision 04, dated June 12, 2006; or (iv) Airbus Service Bulletin A330–32– 3173, Revision 05, dated September 26, 2008. (2) For Model A340–200 and –300 series airplanes: (i) Airbus Service Bulletin A340–32–4212, Revision 02, dated May 11, 2005; (ii) Airbus Service Bulletin A340–32–4212, Revision 03, dated March 13, 2006; (iii) Airbus Service Bulletin A340–32– 4212, Revision 04, dated June 12, 2006; or (iv) Airbus Service Bulletin A340–32– 4212, Revision 05, dated September 26, 2008. (l) Ultrasonic Inspection At the applicable time specified in paragraph (l)(1) or (l)(2) of this AD: Do an ultrasonic longitudinal inspection for cracking of the retraction actuator piston rod end, in accordance with the Accomplishment PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 70451 Instructions of Airbus Service Bulletin A330– 32–3173, Revision 05, dated September 26, 2008 (for Model A330–200 and –300 series airplanes); or Airbus Service Bulletin A340– 32–4212, Revision 05, dated September 26, 2008 (for Model A340–200 and –300 series airplanes). (1) For MLG retraction actuator piston rods that have not had a non-destructive test (NDT) inspection as of the effective date of this AD, as described in the applicable service information specified in paragraph (m)(1) or (m)(2) of this AD: At the applicable time specified in paragraph (l)(1)(i) or (l)(1)(ii) of this AD. (i) For MLG retraction actuator piston rods having P/N 114256309 or P/N 114256321 issue 03: Do the inspection within 60 days after the effective date of this AD, or before the MLG retraction actuator has been in service 36 months, whichever occurs later. (ii) For MLG retraction actuator piston rods having P/N 114256326 issue 01 or P/N 114256321 issue 06: Do the inspection within 60 days after the effective date of this AD, or before the MLG retraction actuator has been in service 72 months, whichever occurs later. (2) For MLG retraction actuator piston rods having P/N 114256309, P/N 114256321 issue 03, P/N 114256326 issue 01, or P/N 114256321 issue 06, that have had an NDT inspection as of the effective date of this AD, as described in the applicable service information specified in paragraph (m)(1) or (m)(2) of this AD: Do the inspection at the later of the times specified in paragraphs (l)(2)(i) and (l)(2)(ii) of this AD. (i) Within 1,400 flight hours, 250 flight cycles, or 4 months, whichever occurs first after the date of the last ultrasonic longitudinal inspection performed as described in the applicable service information specified in paragraph (m)(1) or (m)(2) of this AD. (ii) Within 60 days after the effective date of this AD. (m) Service Information for Determining Airplane Configuration for the Actions Required by Paragraph (l) of This AD (1) For Model A330–200 and –300 series airplanes: (i) Airbus Service Bulletin A330–32–3173, dated December 17, 2003; (ii) Airbus Service Bulletin A330–32–3173, Revision 01, dated June 16, 2004; (iii) Airbus Service Bulletin A330–32– 3173, Revision 02, dated May 11, 2005; (iv) Airbus Service Bulletin A330–32– 3173, Revision 03, dated March 13, 2006; (v) Airbus Service Bulletin A330–32–3173, Revision 04, dated June 12, 2006; or (vi) Airbus Service Bulletin A330–32– 3173, Revision 05, dated September 26, 2008. (2) For Model A340–200 and –300 series airplanes: (i) Airbus Service Bulletin A340–32–4212, dated December 17, 2003; (ii) Airbus Service Bulletin A340–32–4212, Revision 01, dated June 16, 2004; (iii) Airbus Service Bulletin A340–32– 4212, Revision 02, dated May 11, 2005; (iv) Airbus Service Bulletin A340–32– 4212, Revision 03, dated March 13, 2006; (v) Airbus Service Bulletin A340–32–4212, Revision 04, dated June 12, 2006; or E:\FR\FM\26NOR1.SGM 26NOR1 70452 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations (vi) Airbus Service Bulletin A340–32– 4212, Revision 05, dated September 26, 2008. (n) Corrective Action for Ultrasonic Inspection; Repetitive Interval (1) If the finding of the inspection required by paragraph (l) of this AD gives an indication of 75 percent or higher of full screen height (FSH) and between 5 and 7 in time base: Before further flight, replace the MLG retraction actuator with a new or serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–32–3173, Revision 05, dated September 26, 2008 (for Model A330– 200 and –300 series airplanes); or Airbus Service Bulletin A340–32–4212, Revision 05, dated September 26, 2008 (for Model A340– 200 and –300 series airplanes). (2) If the finding of the inspection required by paragraph (l) of this AD gives an indication of less than 75 percent FSH and between 5 and 7 in time base: Repeat the inspection required by paragraph (l) of this AD thereafter at intervals not to exceed 1,400 flight hours, 250 flight cycles, or 4 months, whichever occurs first. mstockstill on DSK4VPTVN1PROD with RULES (o) One-Time Ultrasonic Inspections of the Full-Length of the Piston Rod At the applicable time specified in paragraph (o)(1) or (o)(2) of this AD: Do a full-length ultrasonic longitudinal and a fulllength circumferential inspection of the chromium-plated area of the piston rod for cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–32–3173, Revision 05, dated September 26, 2008 (for Model A330– 200 and –300 series airplanes); or Airbus Service Bulletin A340–32–4212, Revision 05, dated September 26, 2008 (for Model A340– 200 and –300 series airplanes). (1) For MLG retraction actuator piston rods having P/N 114256309 or P/N 114256321 issue 03: Inspect at the later of the times specified in paragraphs (o)(1)(i) and (o)(1)(ii) of this AD. (i) Within 1,750 flight hours, 315 flight cycles, or 5 months after the effective date of this AD, whichever occurs first. (ii) Before the MLG retraction actuator has been in service 36 months. (2) For MLG retraction actuator piston rods having P/N 114256326 issue 01 or P/N 114256321 issue 06: Inspect at the later of the times specified in paragraphs (o)(2)(i) and (o)(2)(ii) of this AD. (i) Within 1,750 flight hours, 315 flight cycles, or 5 months after the effective date of this AD, whichever occurs first. (ii) Before the MLG retraction actuator has been in service 72 months. (p) Corrective Action for One-Time Ultrasonic Inspections of the Full-Length of the Piston Rod (1) If the finding of the full-length ultrasonic longitudinal inspection required by paragraph (o) of this AD gives an indication of 75 percent or higher FSH and between 5 and 7 in time base: Before further flight, replace the MLG retraction actuator with a new or serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–32–3173, Revision 05, dated September 26, 2008 (for VerDate Sep<11>2014 16:25 Nov 25, 2014 Jkt 235001 Model A330–200 and –300 series airplanes); or Airbus Service Bulletin A340–32–4212, Revision 05, dated September 26, 2008 (for Model A340–200 and –300 series airplanes). (2) If the finding of the full-length ultrasonic circumferential inspection required by paragraph (o) of this AD gives an indication of 75 percent or higher FSH and between 7 and 9.5 in time base: Before further flight, replace the MLG retraction actuator with a new or serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 32–3173, Revision 05, dated September 26, 2008 (for Model A330–200 and –300 series airplanes); or Airbus Service Bulletin A340– 32–4212, Revision 05, dated September 26, 2008 (for Model A340–200 and –300 series airplanes). (q) Reporting Requirement Report the results (regardless of findings) of the detailed inspection, the fluid drain/ seal of the retraction actuator piston rod, the one-time ultrasonic longitudinal inspection of the piston rod end, and the one-time fulllength ultrasonic longitudinal and circumferential inspection required by this AD, and the findings of the actions required by this AD that cause an actuator to be replaced, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–32–3173, Revision 05, dated September 26, 2008 (for Model A330– 200 and –300 series airplanes); or Airbus Service Bulletin A340–32–4212, Revision 05, dated September 26, 2008 (for Model A340– 200 and –300 series airplanes). Submit the report to Airbus Customer Services Directorate, Attention: SEDCC1 Technical Data and Documentation Services fax: (+33) 5 61 93 28 06; email: sb.reporting@ airbus.com; or via your Airbus resident customer support office. Submit the report at the applicable time specified in paragraph (q)(1) or (q)(2) of this AD. (1) If the actions requiring reporting, as specified in paragraph (q) of this AD, are done on or after the effective date of this AD: Submit the report within 90 days after those actions have been done. (2) If the actions requiring reporting, as specified in paragraph (q) of this AD, were done before the effective date of this AD: Submit the report within 90 days after the effective date of this AD. (r) Terminating Actions for Repetitive Detailed Inspections Accomplishment of the initial drainage of the fluid from the piston, as required by paragraph (j) of this AD; and the full-length ultrasonic longitudinal inspection, and the full-length circumferential inspection, as required by paragraph (o) of this AD; constitutes terminating action for the repetitive detailed inspections required by paragraph (g) of this AD, provided no crack is found during the inspections. (s) Terminating Modification Within 48 months after the effective date of this AD: Modify the left-hand and righthand MLG retraction actuators, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–32–3180, Revision 05, dated January 27, 2014 (for PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 Model A330–200 and –300 series airplanes); or Airbus Service Bulletin A340–32–4222, Revision 04, dated July 30, 2013 (for Model A340–200 and –300 series airplanes). Accomplishment of the modification required by this paragraph terminates the repetitive requirements of this AD for the MLG retraction actuator that is modified. (t) Exception to Re-Identification of the MLG Retraction Actuator The re-identification of the MLG retraction actuator having P/N 114256002–055, which is described in Airbus Service Bulletin A330–32–3180, Revision 05, dated January 27, 2014 (for Model A330–200 and –300 series airplanes); and Airbus Service Bulletin A340–32–4222, Revision 04, dated July 30, 2013 (for Model A340–200 and –300 series airplanes); is not required on airplanes that have Airbus modification 52980 embodied in production. (u) Optional Parts Installation Installation of a retraction actuator piston rod having P/N 114256323, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–32–3174, Revision 02, dated September 16, 2005 (for Model A330–200 and –300 series airplanes); or Airbus Service Bulletin A340–32–4213, Revision 01, dated September 16, 2005 (for Model A340–200 and –300 series airplanes); is an acceptable method of compliance with the requirements of paragraphs (g), (j), (l), and (o) of this AD for that installed MLG retraction actuator. (v) Parts Installation Limitation As of the effective date of this AD, no person may install a piston rod having P/N 114256309, P/N 114256321, or P/N 114256326 issue 01 for the MLG retraction actuator on any airplane, unless the part meets the applicable requirements of this AD at the specified times and intervals. (w) Credit for Previous Actions (1) This paragraph provides credit for the actions required by paragraphs (g), (j), (l), and (o) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraphs (w)(1)(i) through (w)(1)(ix) of this AD. (i) Airbus Service Bulletin A330–32–3173, dated December 17, 2003; (for Model A330– 200 and –300 series airplanes). (ii) Airbus Service Bulletin A330–32–3173, Revision 01, dated June 16, 2004 (for Model A330–200 and –300 series airplanes). (iii) Airbus Service Bulletin A330–32– 3173, Revision 02, dated May 11, 2005 (for Model A330–200 and –300 series airplanes). (iv) Airbus Service Bulletin A330–32– 3173, Revision 03, dated March 13, 2006 (for Model A330–200 and –300 series airplanes). (v) Airbus Service Bulletin A330–32–3173, Revision 04, dated June 12, 2006 (for Model A330–200 and –300 series airplanes). (vi) Airbus Service Bulletin A340–32– 4212, dated December 17, 2003 (for Model A340–200 and –300 series airplanes). (vii) Airbus Service Bulletin A340–32– 4212, Revision 01, dated June 16, 2004 (for Model A340–200 and –300 series airplanes). E:\FR\FM\26NOR1.SGM 26NOR1 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations mstockstill on DSK4VPTVN1PROD with RULES (viii) Airbus Service Bulletin A340–32– 4212, Revision 02, dated May 11, 2005; Revision 03, dated March 13, 2006 (for Model A340–200 and –300 series airplanes). (ix) Airbus Service Bulletin A340–32– 4212, Revision 04, dated June 12, 2006 (for Model A340–200 and –300 series airplanes). (2) This paragraph provides credit for the actions required by paragraph (s) of this AD, if the modification was done before the effective date of this AD using the service information specified in paragraphs (u)(2)(i) through (u)(2)(iv) of this AD. These service bulletins are not incorporated by reference in this AD. (i) Airbus Service Bulletin A330–32–3180, Revision 01, dated August 15, 2005 for Model A330–200 and –300 series airplanes). (ii) Airbus Service Bulletin A330–32–3180, Revision 02, dated April 4, 2007 (for Model A330–200 and –300 series airplanes). (iii) Airbus Service Bulletin A330–32– 3180, Revision 03, dated January 28, 2011. (iv) Airbus Service Bulletin A330–32– 3180, Revision 04, dated July 30, 2013. (v) Airbus Service Bulletin A340–32–4222, Revision 01, dated August 15, 2005 (for Model A340–200 and –300 series airplanes). (vi) Airbus Service Bulletin A340–32– 4222, Revision 02, dated April 4, 2007 (for Model A340–200 and –300 series airplanes). (vii) Airbus Service Bulletin A340–32– 4222, Revision 03, dated January 28, 2011 (for Model A340–200 and –300 series airplanes). (3) This paragraph provides credit for the actions required by paragraph (s) of this AD, if the modification was done before the effective date of this AD using Airbus Service Bulletin A340–32–4222, dated September 20, 2004; and the re-identification was done before the effective date of this AD using Airbus Service Bulletin A340–32–4222, Revision 01, dated August 15, 2005, or Airbus Service Bulletin A340–32–4222, Revision 02, dated April 4, 2007. These service bulletins are not incorporated by reference in this AD. (x) 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. VerDate Sep<11>2014 16:25 Nov 25, 2014 Jkt 235001 (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. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (y) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2011–0178R1, dated March 6, 2012 (corrected March 7, 2012); and Airworthiness Directive 2011–0179R1, dated March 6, 2012; for related information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2014-0132-0003. (2) Service information identified in this AD that is not incorporated by reference in this AD is available at the addresses specified in paragraphs (z)(5) and (z)(6) of this AD. (z) 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 December 31, 2014. (i) Airbus Service Bulletin A330–32–3173, dated December 17, 2003. (ii) Airbus Service Bulletin A330–32–3173, Revision 02, dated May 11, 2005. (iii) Airbus Service Bulletin A330–32– 3173, Revision 03, dated March 13, 2006. (iv) Airbus Service Bulletin A330–32– 3173, Revision 04, dated June 12, 2006. (v) Airbus Service Bulletin A330–32–3173, Revision 05, dated September 26, 2008. (vi) Airbus Service Bulletin A330–32– 3174, Revision 02, dated September 16, 2005. (vii) Airbus Service Bulletin A330–32– 3180, Revision 05, dated January 27, 2014. PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 70453 (viii) Airbus Service Bulletin A340–32– 4212, dated December 17, 2003. (ix) Airbus Service Bulletin A340–32– 4212, Revision 02, dated May 11, 2005. (x) Airbus Service Bulletin A340–32–4212, Revision 03, dated March 13, 2006. (xi) Airbus Service Bulletin A340–32– 4212, Revision 04, dated June 12, 2006. (xii) Airbus Service Bulletin A340–32– 4212, Revision 05, dated September 26, 2008. (xiii) Airbus Service Bulletin A340–32– 4213, Revision 01, dated September 16, 2005. (xiv) Airbus Service Bulletin A340–32– 4222, Revision 04, dated July 30, 2013. (4) The following service information was approved for IBR on August 19, 2004 (69 FR 46979, August 4, 2004). (i) Airbus Service Bulletin A330–32–3173, Revision 01, dated June 16, 2004. (ii) Airbus Service Bulletin A340–32–4212, Revision 01, dated June 16, 2004. (5) For service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 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/ibrlocations.html. Issued in Renton, Washington, on November 5, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–26986 Filed 11–25–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0062; Directorate Identifier 2012–NM–031–AD; Amendment 39–18025; AD 2014–23–09] RIN 2120–AA64 Airworthiness Directives; Fokker Services B.V. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2000–17– 03 for all Fokker Services B.V. Model F.28 Mark 0100 airplanes. AD 2000–17– SUMMARY: E:\FR\FM\26NOR1.SGM 26NOR1

Agencies

[Federal Register Volume 79, Number 228 (Wednesday, November 26, 2014)]
[Rules and Regulations]
[Pages 70447-70453]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-26986]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0132; Directorate Identifier 2012-NM-007-AD; 
Amendment 39-18023; AD 2014-23-07]
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) 2004-16-01 for 
certain Airbus Model A330-200 and -300 series airplanes and Model A340-
200 and -300 series airplanes. AD 2004-16-01 required repetitive 
inspections for cracking of the chromed area of the left and right 
piston rods for the main landing gear (MLG) retraction actuators, and 
related investigative and corrective actions if necessary. This new AD 
requires repetitive draining of any fluid from the retraction actuator 
piston rod internal volume and sealing of the vent hole; repetitive 
ultrasonic inspections of the upper end of the piston rods, and 
corrective actions if necessary; a one-time ultrasonic inspection 
(longitudinal and circumferential) of the full length of the piston 
rod, and corrective actions if necessary; and a terminating 
modification of the left-hand and right-hand MLG retraction actuators. 
This AD was prompted by reports of the piston rods for the MLG 
retraction actuators rupturing during flight. We are issuing this AD to 
prevent cracking of the piston rods for the MLG retraction actuators, 
which could result in rupture of a piston rod, non-damped extension of 
the MLG, high loads on the fully extended MLG, and consequent reduced 
structural integrity of the MLG.

DATES: This AD becomes effective December 31, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 31, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of August 
19, 2004 (69 FR 46979, August 4, 2004).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0132; 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--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; 
email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA,

[[Page 70448]]

1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2004-16-01, Amendment 39-13757 (69 FR 46979, 
August 4, 2004). AD 2004-16-01 applied to certain Airbus Model A330-200 
and -300 series airplanes and Model A340-200 and -300 series airplanes. 
The NPRM published in the Federal Register on February 6, 2014 (79 FR 
7098; corrected March 20, 2014 (79 FR 15555)). The NPRM was prompted by 
reports of the piston rods for the MLG retraction actuators rupturing 
during flight.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2011-0178R1, dated March 6, 2012, corrected March 7, 2012 (for Model 
A340-200 and -300 series airplanes); and EASA AD 2011-0179R1, dated 
March 6, 2012 (for Model A330-200 and -300 series airplanes) (both 
referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''); to correct an unsafe condition for the 
specified products. EASA AD 2011-0178R1, dated March 6, 2012, corrected 
March 7, 2012, states:

    During an approach phase, the flight crew of an A330 aeroplane 
had to perform a free-fall extension of the left-hand (LH) MLG.
    Rupture of the LH MLG retraction actuator piston rod was found 
near the rod attachment point. The inspection revealed at the 
location of the rupture the presence of corrosion resulting from 
incorrect application of the anticorrosion protection, and 
circumferential cracks resulting from normal operational loading 
effects.
    Since the above rupture, new cases of crack propagation along 
the length of the piston rod occurred. These ruptures led to a non-
damped extension of the landing gear. Fully extended, the landing 
gear assembly was submitted to high loads jeopardising its 
structural integrity.
    This condition, if not detected and corrected, could lead to MLG 
failure during landing or roll-out and consequent damage to the 
aeroplane and injury to occupants.
    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France issued AD F-2005-098 [http://ad.easa.europa.eu/blob/easa_ad_2005_5887_F20050980tb_superseded.pdf/AD_F-2005-098_1] (EASA 
approval 2005-5887) [and AD F-2005-099 [http://ad.easa.europa.eu/blob/easa_ad_2005_5888_F20050990tb_superseded.pdf/AD_F-2005-099_2] 
(EASA approval 2005-5888)] to address this unsafe condition [the FAA 
issued AD 2004-16-01, Amendment 39-13757 (69 FR 46979, August 4, 
2004)]. Since that [DGAC France] AD was issued, the results of 
extensive investigation determined that the presence of water in the 
internal volume of the piston rod can lead to the formation of ice 
which represents a potential source of high magnitude tensile hoop 
stresses in the material of the rod, leading to propagation of 
longitudinal crack in the body of the piston rod.
    Prompted by these findings, EASA issued AD 2006-0301 [http://ad.easa.europa.eu/blob/easa_ad_2006_0301_R2_superseded.pdf/AD_2006-0301R2_1], partially retaining the requirements of DGAC France AD F-
2005-099, which was superseded, and to revise the inspection 
requirements as follows:
    a. Extend the repetitive inspections interval for the removal of 
fluid from the internal volume of the piston rod using flight cycles 
in lieu of flight hours as this better represents the mechanism for 
the accumulation of water within the piston rod.
    b. Remove the preliminary visual inspection from the ultrasonic 
longitudinal inspection of the upper end of the piston rod.
    c. Add a new one-time ultrasonic longitudinal and 
circumferential inspection of the full piston rod length to 
eliminate any parts that exhibit severe corrosion along the internal 
length of the piston rod.
    d. Require installation of new design hollow piston rod Part 
Number (P/N) 114256328 (Airbus mod. 52980--SB A340-32-4222 Revision 
01) without a vent hole, thus eliminating moisture ingress as the 
terminating action.
    EASA AD 2006-0301 was later revised:

--at revision 01, to correct a number of typographical errors and to 
add reference to Airbus SB A340-32-4212 Revision 04, and
--at revision 02 to extend the inspections threshold from 3 to 6 
years in service usage for retraction actuator piston rod P/N 
114256321 issue 06 which was re-identified to P/N 114256326 issue 01 
in accordance with the instructions of Airbus SB A340-32-4260.

    More recently, the sampling of piston rod P/N 114256326 issue 1 
and P/N 114256321 issue 06 have confirmed the need to replace all 
retraction actuator piston rods with a piston rod P/N114256328.
    For the reasons described above, this [EASA] AD at original 
issue retained the requirements of EASA AD 2006-0301R2 (http://ad.easa.europa.eu/blob/easa_ad_2006_0301_R2_superseded.pdf/AD_2006-0301R2_1), which is superseded, and required the replacement of all 
retraction actuator piston rods with a piston rod P/N 114256328, 
which constitutes terminating action to the repetitive requirements 
of this AD.
    This [EASA] AD is revised to clarify that aeroplanes on which 
Airbus mod. 52980 has been embodied in production are not required 
to accomplish the reidentification of MLG retraction actuator P/N 
114256002-055 which is mentioned in the accomplishment instructions 
of Airbus SB A340-32-4222 Revision 03.
    This [EASA] AD has been republished to correct a typographical 
mistake of the applicable Airbus SB number in the Applicability (in 
the Note) and in the Reason sections of this [EASA] AD.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0132-0003.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 7098, February 6, 2014; corrected March 20, 2014 (79 FR 15555)), and 
the FAA's response to each comment.

Request To Reference Latest Service Information

    Delta Airlines requested that we reference the latest Airbus 
service information, which is Airbus Service Bulletin A330-32-3180, 
Revision 05, dated January 27, 2014. Delta Airlines further requested 
that we provide credit for actions previously accomplished using Airbus 
Service Bulletin A330-32-3180, Revision 03, dated January 28, 2011; and 
Airbus Service Bulletin A330-32-3180, Revision 04, dated July 30, 2013.
    We agree with Delta Airlines' comment to reference the latest 
service information. Airbus Service Bulletin A330-32-3180, Revision 05, 
dated January 27, 2014, provides the latest information on the 
modification required by this AD. This service bulletin specifies two 
additional work-hours for re-identification of the part number of the 
MLG retraction actuator for Model A330-200 and -300 series airplanes at 
configuration 3, which were modified as described in Airbus Service 
Bulletin A330-32-3180, Revision 03, dated January 28, 2011. Re-
identification of the MLG retraction actuator may be considered as a 
logical outgrowth of the proposed AD (79 FR 7098, February 6, 2014; 
corrected March 20, 2014 (79 FR 15555)) requirements.
    Airbus has also released Service Bulletin A340-32-4222, Revision 
04, dated July 30, 2013. This service bulletin also specifies two 
additional work-hours for re-identification of the part number of the 
MLG retraction actuator for Model A340 series airplanes. There are 
currently no U.S.-registered Model A340 series airplanes. We have 
revised paragraphs (s) and (t) of this AD to specify Airbus Service 
Bulletin A330-32-3180, Revision 05, dated January 27, 2014; and Airbus 
Service Bulletin A340-32-4222, Revision 04, dated July 30, 2013; as the 
appropriate sources of service information for the required actions in 
those paragraphs. We have also revised paragraphs (w)(2) and (w)(3) of 
this AD to provide credit for previous actions

[[Page 70449]]

accomplished using Airbus Service Bulletin A330-32-3180, Revision 03, 
dated January 28, 2011; Airbus Service Bulletin A330-32-3180, Revision 
04, dated July 30, 2013; and Airbus Service Bulletin A340-32-4222, 
Revision 03, dated January 28, 2011; as applicable.

``Contacting the Manufacturer'' Paragraph in This AD

    Since late 2006, we have included a standard paragraph titled 
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD 
based on a foreign authority's AD.
    The MCAI or referenced service information in an FAA AD often 
directs the owner/operator to contact the manufacturer for corrective 
actions, such as a repair. Briefly, the Airworthy Product paragraph 
allowed owners/operators to use corrective actions provided by the 
manufacturer if those actions were FAA-approved. In addition, the 
paragraph stated that any actions approved by the State of Design 
Authority (or its delegated agent) are considered to be FAA-approved.
    In the NPRM (79 FR 7098, February 6, 2014; corrected March 20, 2014 
(79 FR 15555)), we proposed to prevent the use of repairs that were not 
specifically developed to correct the unsafe condition, by requiring 
that the repair approval provided by the State of Design Authority or 
its delegated agent specifically refer to this FAA AD. This change was 
intended to clarify the method of compliance and to provide operators 
with better visibility of repairs that are specifically developed and 
approved to correct the unsafe condition. In addition, we proposed to 
change the phrase ``its delegated agent'' to include a design approval 
holder (DAH) with State of Design Authority design organization 
approval (DOA), as applicable, to refer to a DAH authorized to approve 
required repairs for the proposed AD.
    No comments were provided to the NPRM (79 FR 7098, February 6, 
2014; corrected March 20, 2014 (79 FR 15555)) about these proposed 
changes. However, a comment was provided for an NPRM having Directorate 
Identifier 2012-NM-101-AD (78 FR 78285, December 26, 2013). The 
commenter stated the following: ``The proposed wording, being specific 
to repairs, eliminates the interpretation that Airbus messages are 
acceptable for approving minor deviations (corrective actions) needed 
during accomplishment of an AD mandated Airbus service bulletin.''
    This comment has made the FAA aware that some operators have 
misunderstood or misinterpreted the Airworthy Product paragraph to 
allow the owner/operator to use messages provided by the manufacturer 
as approval of deviations during the accomplishment of an AD-mandated 
action. The Airworthy Product paragraph does not approve messages or 
other information provided by the manufacturer for deviations to the 
requirements of the AD-mandated actions. The Airworthy Product 
paragraph only addresses the requirement to contact the manufacturer 
for corrective actions for the identified unsafe condition and does not 
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request 
the approval for an alternative method of compliance to the AD-required 
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the 
Airworthy Product paragraph, we have changed the paragraph and retitled 
it ``Contacting the Manufacturer.'' This paragraph now clarifies that 
for any requirement in this AD to obtain corrective actions from a 
manufacturer, the actions must be accomplished using a method approved 
by the FAA, the European Aviation Safety Agency (EASA), or Airbus's 
EASA Design Organization Approval (DOA).
    The Contacting the Manufacturer paragraph also clarifies that, if 
approved by the DOA, the approval must include the DOA-authorized 
signature. The DOA signature indicates that the data and information 
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer 
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or 
other information.
    This clarification does not remove flexibility previously afforded 
by the Airworthy Product paragraph. Consistent with long-standing FAA 
policy, such flexibility was never intended for required actions. This 
is also consistent with the recommendation of the Airworthiness 
Directive Implementation Aviation Rulemaking Committee to increase 
flexibility in complying with ADs by identifying those actions in 
manufacturers' service instructions that are ``Required for 
Compliance'' with ADs. We continue to work with manufacturers to 
implement this recommendation. But once we determine that an action is 
required, any deviation from the requirement must be approved as an 
alternative method of compliance.
    Other commenters to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) pointed out that in many cases 
the foreign manufacturer's service bulletin and the foreign authority's 
MCAI might have been issued some time before the FAA AD. Therefore, the 
DOA might have provided U.S. operators with an approved repair, 
developed with full awareness of the unsafe condition, before the FAA 
AD is issued. Under these circumstances, to comply with the FAA AD, the 
operator would be required to go back to the manufacturer's DOA and 
obtain a new approval document, adding time and expense to the 
compliance process with no safety benefit.
    Based on these comments, we removed the requirement that the DAH-
provided repair specifically refer to this AD. Before adopting such a 
requirement, the FAA will coordinate with affected DAHs and verify they 
are prepared to implement means to ensure that their repair approvals 
consider the unsafe condition addressed in this AD. Any such 
requirements will be adopted through the normal AD rulemaking process, 
including notice-and-comment procedures, when appropriate.
    We also have decided not to include a generic reference to either 
the ``delegated agent'' or ``DAH with State of Design Authority design 
organization approval,'' but instead we have provided the specific 
delegation approval granted by the State of Design Authority for the 
DAH.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 7098, February 6, 2014; corrected March 20, 2014 (79 FR 
15555)) for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 7098, February 6, 2014; corrected 
March 20, 2014 (79 FR 15555)).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 24 Model A330-200 and -300 series 
airplanes of U.S. registry. There are no

[[Page 70450]]

Model A340-200 or -300 series airplanes of U.S. registry.
    We estimate that it will take about 67 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts will cost about $56,000 per 
product (2 actuators). Based on these figures, we estimate the cost of 
this AD on U.S. operators to be $1,480,680, or $61,695 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 38 work-hours and require parts costing $56,000 (2 
actuators), for a cost of $59,230 per product. We have no way of 
determining the number of aircraft that might need these actions.
    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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-2014-0132; 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) 
2004-16-01, Amendment 39-13757 (69 FR 46979, August 4, 2004), and 
adding the following new AD:

2014-23-07 Airbus: Amendment 39-18023. Docket No. FAA-2014-0132; 
Directorate Identifier 2012-NM-007-AD.

(a) Effective Date

    This AD becomes effective December 31, 2014.

(b) Affected ADs

    This AD replaces AD 2004-16-01, Amendment 39-13757 (69 FR 46979, 
August 4, 2004).

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 
airplanes; and Model A340-211, -212, -213, -311, -312, and -313 
airplanes; certificated in any category; all manufacturer serial 
numbers, except for those airplanes that have had Airbus 
Modification 52980 incorporated in production on both main landing 
gear (MLG) units, or airplanes that have had Airbus Modification 
54500 incorporated in production.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of the piston rods for the MLG 
retraction actuators rupturing during flight. We are issuing this AD 
to prevent cracking of the piston rods for the MLG retraction 
actuators, which could result in rupture of a piston rod, non-damped 
extension of the MLG, high loads on the fully extended MLG, and 
consequent reduced structural integrity of the MLG.

(f) Compliance

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

(g) Repetitive Detailed Inspections

    At the applicable time specified in paragraph (g)(1) or (g)(2) 
of this AD: Do a detailed inspection for cracking of the visible 
chromed area of the MLG retraction actuator piston rods in the fully 
extended position, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-32-3173, Revision 05, 
dated September 26, 2008 (for Model A330-200 and -300 series 
airplanes); or Airbus Service Bulletin A340-32-4212, Revision 05, 
dated September 26, 2008 (for Model A340-200 and -300 series 
airplanes). Repeat the inspection thereafter at intervals not to 
exceed 8 days until the actions required by paragraphs (j) and (o) 
of this AD are accomplished.
    (1) For MLG retraction actuator piston rods that have not had a 
detailed inspection accomplished as of the effective date of this 
AD, as described in any applicable service information specified in 
paragraph (h)(1) or (h)(2) of this AD: At the applicable time

[[Page 70451]]

specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
    (i) For MLG retraction actuator piston rods having part number 
(P/N) 114256309 or P/N 114256321 issue 03: Do the inspection within 
60 days after the effective date of this AD, or before the MLG 
retraction actuator has been in service 36 months, whichever occurs 
later.
    (ii) For MLG retraction actuator piston rods having P/N 
114256326 issue 01 or P/N 114256321 issue 06: Do the inspection 
within 60 days after the effective date of this AD, or before the 
MLG retraction actuator has been in service 72 months, whichever 
occurs later.
    (2) For MLG retraction actuator piston rods having P/N 
114256309, P/N 114256321 issue 03, P/N 114256326 issue 01, or P/N 
114256321 issue 06, that have had a detailed inspection accomplished 
as of the effective date of this AD, as described in the applicable 
service information specified in paragraph (h)(1) or (h)(2) of this 
AD: Inspect within 8 days after the effective date of this AD.

(h) Service Information for Determining Airplane Configuration for the 
Actions Required by Paragraph (g) of This AD

    (1) For Model A330-200 and -300 series airplanes:
    (i) Airbus Service Bulletin A330-32-3173, Revision 01, dated 
June 16, 2004;
    (ii) Airbus Service Bulletin A330-32-3173, Revision 02, dated 
May 11, 2005;
    (iii) Airbus Service Bulletin A330-32-3173, Revision 03, dated 
March 13, 2006;
    (iv) Airbus Service Bulletin A330-32-3173, Revision 04, dated 
June 12, 2006; or
    (v) Airbus Service Bulletin A330-32-3173, Revision 05, dated 
September 26, 2008.
    (2) For Model A340-200 and -300 series airplanes:
    (i) Airbus Service Bulletin A340-32-4212, Revision 01, dated 
June 16, 2004;
    (ii) Airbus Service Bulletin A340-32-4212, Revision 02, dated 
May 11, 2005;
    (iii) Airbus Service Bulletin A340-32-4212, Revision 03, dated 
March 13, 2006;
    (iv) Airbus Service Bulletin A340-32-4212, Revision 04, dated 
June 12, 2006; or
    (v) Airbus Service Bulletin A340-32-4212, Revision 05, dated 
September 26, 2008.

(i) Corrective Action for Cracking

    If any cracking is found during any inspection required by 
paragraph (g) of this AD: Before further flight, replace the MLG 
retraction actuator with a new or serviceable part, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A330-32-3173, Revision 05, dated September 26, 2008 (for Model A330-
200 and -300 series airplanes); or Airbus Service Bulletin A340-32-
4212, Revision 05, dated September 26, 2008 (for Model A340-200 and 
-300 series airplanes).

(j) Repetitive Fluid Draining and Vent Hole Sealing

    At the applicable time specified in paragraph (j)(1) or (j)(2) 
of this AD: Drain any fluid from the retraction actuator piston rod 
internal volume and seal the vent hole, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-32-3173, 
Revision 05, dated September 26, 2008 (for Model A330-200 and -300 
series airplanes); or Airbus Service Bulletin A340-32-4212, Revision 
05, dated September 26, 2008 (for Model A340-200 and -300 series 
airplanes). Repeat the draining and sealing thereafter at intervals 
not to exceed 1,000 flight cycles or 24 months, whichever occurs 
first.
    (1) For MLG retraction actuator piston rods that have not been 
inspected and have not had the fluid drained as of the effective 
date of this AD, as described in the applicable service information 
specified in paragraph (k)(1) or (k)(2) of this AD: At the 
applicable time specified in paragraph (j)(1)(i) or (j)(1)(ii) of 
this AD.
    (i) For MLG retraction actuator piston rods having P/N 114256309 
or P/N 114256321 issue 03: Do the draining and sealing within 60 
days after the effective date of this AD, or before the MLG 
retraction actuator has been in service 36 months, whichever occurs 
later.
    (ii) For MLG retraction actuator piston rods having P/N 
114256326 issue 01 or P/N 114256321 issue 06: Do the draining and 
sealing within 60 days after the effective date of this AD, or 
before the MLG retraction actuator has been in service 72 months, 
whichever occurs later.
    (2) For MLG retraction actuator piston rods having P/N 
114256309, P/N 114256321 issue 03, P/N 114256326 issue 01, or P/N 
114256321 issue 06, that have been inspected and the fluid drained 
as of the effective date of this AD, as described in the applicable 
service information specified in paragraph (k)(1) or (k)(2) of this 
AD: Do the draining and sealing at the later of the times specified 
in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD.
    (i) Within 1,000 flight cycles or 24 months, whichever occurs 
first, from the last inspection and fluid drainage accomplished in 
accordance with the requirements of paragraph (j) of this AD.
    (ii) Within 60 days after the effective date of this AD.

(k) Service Information for Determining Airplane Configuration for the 
Actions Required by Paragraph (j) of This AD

    (1) For Model A330-200 and -300 series airplanes:
    (i) Airbus Service Bulletin A330-32-3173, Revision 02, dated May 
11, 2005;
    (ii) Airbus Service Bulletin A330-32-3173, Revision 03, dated 
March 13, 2006;
    (iii) Airbus Service Bulletin A330-32-3173, Revision 04, dated 
June 12, 2006; or
    (iv) Airbus Service Bulletin A330-32-3173, Revision 05, dated 
September 26, 2008.
    (2) For Model A340-200 and -300 series airplanes:
    (i) Airbus Service Bulletin A340-32-4212, Revision 02, dated May 
11, 2005;
    (ii) Airbus Service Bulletin A340-32-4212, Revision 03, dated 
March 13, 2006;
    (iii) Airbus Service Bulletin A340-32-4212, Revision 04, dated 
June 12, 2006; or
    (iv) Airbus Service Bulletin A340-32-4212, Revision 05, dated 
September 26, 2008.

(l) Ultrasonic Inspection

    At the applicable time specified in paragraph (l)(1) or (l)(2) 
of this AD: Do an ultrasonic longitudinal inspection for cracking of 
the retraction actuator piston rod end, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-32-3173, 
Revision 05, dated September 26, 2008 (for Model A330-200 and -300 
series airplanes); or Airbus Service Bulletin A340-32-4212, Revision 
05, dated September 26, 2008 (for Model A340-200 and -300 series 
airplanes).
    (1) For MLG retraction actuator piston rods that have not had a 
non-destructive test (NDT) inspection as of the effective date of 
this AD, as described in the applicable service information 
specified in paragraph (m)(1) or (m)(2) of this AD: At the 
applicable time specified in paragraph (l)(1)(i) or (l)(1)(ii) of 
this AD.
    (i) For MLG retraction actuator piston rods having P/N 114256309 
or P/N 114256321 issue 03: Do the inspection within 60 days after 
the effective date of this AD, or before the MLG retraction actuator 
has been in service 36 months, whichever occurs later.
    (ii) For MLG retraction actuator piston rods having P/N 
114256326 issue 01 or P/N 114256321 issue 06: Do the inspection 
within 60 days after the effective date of this AD, or before the 
MLG retraction actuator has been in service 72 months, whichever 
occurs later.
    (2) For MLG retraction actuator piston rods having P/N 
114256309, P/N 114256321 issue 03, P/N 114256326 issue 01, or P/N 
114256321 issue 06, that have had an NDT inspection as of the 
effective date of this AD, as described in the applicable service 
information specified in paragraph (m)(1) or (m)(2) of this AD: Do 
the inspection at the later of the times specified in paragraphs 
(l)(2)(i) and (l)(2)(ii) of this AD.
    (i) Within 1,400 flight hours, 250 flight cycles, or 4 months, 
whichever occurs first after the date of the last ultrasonic 
longitudinal inspection performed as described in the applicable 
service information specified in paragraph (m)(1) or (m)(2) of this 
AD.
    (ii) Within 60 days after the effective date of this AD.

(m) Service Information for Determining Airplane Configuration for the 
Actions Required by Paragraph (l) of This AD

    (1) For Model A330-200 and -300 series airplanes:
    (i) Airbus Service Bulletin A330-32-3173, dated December 17, 
2003;
    (ii) Airbus Service Bulletin A330-32-3173, Revision 01, dated 
June 16, 2004;
    (iii) Airbus Service Bulletin A330-32-3173, Revision 02, dated 
May 11, 2005;
    (iv) Airbus Service Bulletin A330-32-3173, Revision 03, dated 
March 13, 2006;
    (v) Airbus Service Bulletin A330-32-3173, Revision 04, dated 
June 12, 2006; or
    (vi) Airbus Service Bulletin A330-32-3173, Revision 05, dated 
September 26, 2008.
    (2) For Model A340-200 and -300 series airplanes:
    (i) Airbus Service Bulletin A340-32-4212, dated December 17, 
2003;
    (ii) Airbus Service Bulletin A340-32-4212, Revision 01, dated 
June 16, 2004;
    (iii) Airbus Service Bulletin A340-32-4212, Revision 02, dated 
May 11, 2005;
    (iv) Airbus Service Bulletin A340-32-4212, Revision 03, dated 
March 13, 2006;
    (v) Airbus Service Bulletin A340-32-4212, Revision 04, dated 
June 12, 2006; or

[[Page 70452]]

    (vi) Airbus Service Bulletin A340-32-4212, Revision 05, dated 
September 26, 2008.

(n) Corrective Action for Ultrasonic Inspection; Repetitive Interval

    (1) If the finding of the inspection required by paragraph (l) 
of this AD gives an indication of 75 percent or higher of full 
screen height (FSH) and between 5 and 7 in time base: Before further 
flight, replace the MLG retraction actuator with a new or 
serviceable part, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A330-32-3173, Revision 05, dated 
September 26, 2008 (for Model A330-200 and -300 series airplanes); 
or Airbus Service Bulletin A340-32-4212, Revision 05, dated 
September 26, 2008 (for Model A340-200 and -300 series airplanes).
    (2) If the finding of the inspection required by paragraph (l) 
of this AD gives an indication of less than 75 percent FSH and 
between 5 and 7 in time base: Repeat the inspection required by 
paragraph (l) of this AD thereafter at intervals not to exceed 1,400 
flight hours, 250 flight cycles, or 4 months, whichever occurs 
first.

(o) One-Time Ultrasonic Inspections of the Full-Length of the Piston 
Rod

    At the applicable time specified in paragraph (o)(1) or (o)(2) 
of this AD: Do a full-length ultrasonic longitudinal and a full-
length circumferential inspection of the chromium-plated area of the 
piston rod for cracking, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-32-3173, Revision 05, 
dated September 26, 2008 (for Model A330-200 and -300 series 
airplanes); or Airbus Service Bulletin A340-32-4212, Revision 05, 
dated September 26, 2008 (for Model A340-200 and -300 series 
airplanes).
    (1) For MLG retraction actuator piston rods having P/N 114256309 
or P/N 114256321 issue 03: Inspect at the later of the times 
specified in paragraphs (o)(1)(i) and (o)(1)(ii) of this AD.
    (i) Within 1,750 flight hours, 315 flight cycles, or 5 months 
after the effective date of this AD, whichever occurs first.
    (ii) Before the MLG retraction actuator has been in service 36 
months.
    (2) For MLG retraction actuator piston rods having P/N 114256326 
issue 01 or P/N 114256321 issue 06: Inspect at the later of the 
times specified in paragraphs (o)(2)(i) and (o)(2)(ii) of this AD.
    (i) Within 1,750 flight hours, 315 flight cycles, or 5 months 
after the effective date of this AD, whichever occurs first.
    (ii) Before the MLG retraction actuator has been in service 72 
months.

(p) Corrective Action for One-Time Ultrasonic Inspections of the Full-
Length of the Piston Rod

    (1) If the finding of the full-length ultrasonic longitudinal 
inspection required by paragraph (o) of this AD gives an indication 
of 75 percent or higher FSH and between 5 and 7 in time base: Before 
further flight, replace the MLG retraction actuator with a new or 
serviceable part, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A330-32-3173, Revision 05, dated 
September 26, 2008 (for Model A330-200 and -300 series airplanes); 
or Airbus Service Bulletin A340-32-4212, Revision 05, dated 
September 26, 2008 (for Model A340-200 and -300 series airplanes).
    (2) If the finding of the full-length ultrasonic circumferential 
inspection required by paragraph (o) of this AD gives an indication 
of 75 percent or higher FSH and between 7 and 9.5 in time base: 
Before further flight, replace the MLG retraction actuator with a 
new or serviceable part, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-32-3173, Revision 05, 
dated September 26, 2008 (for Model A330-200 and -300 series 
airplanes); or Airbus Service Bulletin A340-32-4212, Revision 05, 
dated September 26, 2008 (for Model A340-200 and -300 series 
airplanes).

(q) Reporting Requirement

    Report the results (regardless of findings) of the detailed 
inspection, the fluid drain/seal of the retraction actuator piston 
rod, the one-time ultrasonic longitudinal inspection of the piston 
rod end, and the one-time full-length ultrasonic longitudinal and 
circumferential inspection required by this AD, and the findings of 
the actions required by this AD that cause an actuator to be 
replaced, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A330-32-3173, Revision 05, dated September 
26, 2008 (for Model A330-200 and -300 series airplanes); or Airbus 
Service Bulletin A340-32-4212, Revision 05, dated September 26, 2008 
(for Model A340-200 and -300 series airplanes). Submit the report to 
Airbus Customer Services Directorate, Attention: SEDCC1 Technical 
Data and Documentation Services fax: (+33) 5 61 93 28 06; email: 
sb.reporting@airbus.com; or via your Airbus resident customer 
support office. Submit the report at the applicable time specified 
in paragraph (q)(1) or (q)(2) of this AD.
    (1) If the actions requiring reporting, as specified in 
paragraph (q) of this AD, are done on or after the effective date of 
this AD: Submit the report within 90 days after those actions have 
been done.
    (2) If the actions requiring reporting, as specified in 
paragraph (q) of this AD, were done before the effective date of 
this AD: Submit the report within 90 days after the effective date 
of this AD.

(r) Terminating Actions for Repetitive Detailed Inspections

    Accomplishment of the initial drainage of the fluid from the 
piston, as required by paragraph (j) of this AD; and the full-length 
ultrasonic longitudinal inspection, and the full-length 
circumferential inspection, as required by paragraph (o) of this AD; 
constitutes terminating action for the repetitive detailed 
inspections required by paragraph (g) of this AD, provided no crack 
is found during the inspections.

(s) Terminating Modification

    Within 48 months after the effective date of this AD: Modify the 
left-hand and right-hand MLG retraction actuators, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A330-32-3180, Revision 05, dated January 27, 2014 (for Model A330-
200 and -300 series airplanes); or Airbus Service Bulletin A340-32-
4222, Revision 04, dated July 30, 2013 (for Model A340-200 and -300 
series airplanes). Accomplishment of the modification required by 
this paragraph terminates the repetitive requirements of this AD for 
the MLG retraction actuator that is modified.

(t) Exception to Re-Identification of the MLG Retraction Actuator

    The re-identification of the MLG retraction actuator having P/N 
114256002-055, which is described in Airbus Service Bulletin A330-
32-3180, Revision 05, dated January 27, 2014 (for Model A330-200 and 
-300 series airplanes); and Airbus Service Bulletin A340-32-4222, 
Revision 04, dated July 30, 2013 (for Model A340-200 and -300 series 
airplanes); is not required on airplanes that have Airbus 
modification 52980 embodied in production.

(u) Optional Parts Installation

    Installation of a retraction actuator piston rod having P/N 
114256323, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A330-32-3174, Revision 02, dated September 
16, 2005 (for Model A330-200 and -300 series airplanes); or Airbus 
Service Bulletin A340-32-4213, Revision 01, dated September 16, 2005 
(for Model A340-200 and -300 series airplanes); is an acceptable 
method of compliance with the requirements of paragraphs (g), (j), 
(l), and (o) of this AD for that installed MLG retraction actuator.

(v) Parts Installation Limitation

    As of the effective date of this AD, no person may install a 
piston rod having P/N 114256309, P/N 114256321, or P/N 114256326 
issue 01 for the MLG retraction actuator on any airplane, unless the 
part meets the applicable requirements of this AD at the specified 
times and intervals.

(w) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraphs (g), (j), (l), and (o) of this AD, if those actions were 
performed before the effective date of this AD using the service 
information specified in paragraphs (w)(1)(i) through (w)(1)(ix) of 
this AD.
    (i) Airbus Service Bulletin A330-32-3173, dated December 17, 
2003; (for Model A330-200 and -300 series airplanes).
    (ii) Airbus Service Bulletin A330-32-3173, Revision 01, dated 
June 16, 2004 (for Model A330-200 and -300 series airplanes).
    (iii) Airbus Service Bulletin A330-32-3173, Revision 02, dated 
May 11, 2005 (for Model A330-200 and -300 series airplanes).
    (iv) Airbus Service Bulletin A330-32-3173, Revision 03, dated 
March 13, 2006 (for Model A330-200 and -300 series airplanes).
    (v) Airbus Service Bulletin A330-32-3173, Revision 04, dated 
June 12, 2006 (for Model A330-200 and -300 series airplanes).
    (vi) Airbus Service Bulletin A340-32-4212, dated December 17, 
2003 (for Model A340-200 and -300 series airplanes).
    (vii) Airbus Service Bulletin A340-32-4212, Revision 01, dated 
June 16, 2004 (for Model A340-200 and -300 series airplanes).

[[Page 70453]]

    (viii) Airbus Service Bulletin A340-32-4212, Revision 02, dated 
May 11, 2005; Revision 03, dated March 13, 2006 (for Model A340-200 
and -300 series airplanes).
    (ix) Airbus Service Bulletin A340-32-4212, Revision 04, dated 
June 12, 2006 (for Model A340-200 and -300 series airplanes).
    (2) This paragraph provides credit for the actions required by 
paragraph (s) of this AD, if the modification was done before the 
effective date of this AD using the service information specified in 
paragraphs (u)(2)(i) through (u)(2)(iv) of this AD. These service 
bulletins are not incorporated by reference in this AD.
    (i) Airbus Service Bulletin A330-32-3180, Revision 01, dated 
August 15, 2005 for Model A330-200 and -300 series airplanes).
    (ii) Airbus Service Bulletin A330-32-3180, Revision 02, dated 
April 4, 2007 (for Model A330-200 and -300 series airplanes).
    (iii) Airbus Service Bulletin A330-32-3180, Revision 03, dated 
January 28, 2011.
    (iv) Airbus Service Bulletin A330-32-3180, Revision 04, dated 
July 30, 2013.
    (v) Airbus Service Bulletin A340-32-4222, Revision 01, dated 
August 15, 2005 (for Model A340-200 and -300 series airplanes).
    (vi) Airbus Service Bulletin A340-32-4222, Revision 02, dated 
April 4, 2007 (for Model A340-200 and -300 series airplanes).
    (vii) Airbus Service Bulletin A340-32-4222, Revision 03, dated 
January 28, 2011 (for Model A340-200 and -300 series airplanes).
    (3) This paragraph provides credit for the actions required by 
paragraph (s) of this AD, if the modification was done before the 
effective date of this AD using Airbus Service Bulletin A340-32-
4222, dated September 20, 2004; and the re-identification was done 
before the effective date of this AD using Airbus Service Bulletin 
A340-32-4222, Revision 01, dated August 15, 2005, or Airbus Service 
Bulletin A340-32-4222, Revision 02, dated April 4, 2007. These 
service bulletins are not incorporated by reference in this AD.

(x) 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: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) 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.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(y) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2011-
0178R1, dated March 6, 2012 (corrected March 7, 2012); and 
Airworthiness Directive 2011-0179R1, dated March 6, 2012; for 
related information. You may examine the MCAI in the AD docket on 
the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-
2014-0132-0003.
    (2) Service information identified in this AD that is not 
incorporated by reference in this AD is available at the addresses 
specified in paragraphs (z)(5) and (z)(6) of this AD.

(z) 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 
December 31, 2014.
    (i) Airbus Service Bulletin A330-32-3173, dated December 17, 
2003.
    (ii) Airbus Service Bulletin A330-32-3173, Revision 02, dated 
May 11, 2005.
    (iii) Airbus Service Bulletin A330-32-3173, Revision 03, dated 
March 13, 2006.
    (iv) Airbus Service Bulletin A330-32-3173, Revision 04, dated 
June 12, 2006.
    (v) Airbus Service Bulletin A330-32-3173, Revision 05, dated 
September 26, 2008.
    (vi) Airbus Service Bulletin A330-32-3174, Revision 02, dated 
September 16, 2005.
    (vii) Airbus Service Bulletin A330-32-3180, Revision 05, dated 
January 27, 2014.
    (viii) Airbus Service Bulletin A340-32-4212, dated December 17, 
2003.
    (ix) Airbus Service Bulletin A340-32-4212, Revision 02, dated 
May 11, 2005.
    (x) Airbus Service Bulletin A340-32-4212, Revision 03, dated 
March 13, 2006.
    (xi) Airbus Service Bulletin A340-32-4212, Revision 04, dated 
June 12, 2006.
    (xii) Airbus Service Bulletin A340-32-4212, Revision 05, dated 
September 26, 2008.
    (xiii) Airbus Service Bulletin A340-32-4213, Revision 01, dated 
September 16, 2005.
    (xiv) Airbus Service Bulletin A340-32-4222, Revision 04, dated 
July 30, 2013.
    (4) The following service information was approved for IBR on 
August 19, 2004 (69 FR 46979, August 4, 2004).
    (i) Airbus Service Bulletin A330-32-3173, Revision 01, dated 
June 16, 2004.
    (ii) Airbus Service Bulletin A340-32-4212, Revision 01, dated 
June 16, 2004.
    (5) For service information identified in this AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
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 November 5, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-26986 Filed 11-25-14; 8:45 am]
BILLING CODE 4910-13-P