Airworthiness Directives; Airbus Model A330-200 and -300 Airplanes and Model A340-200, -300, -500, and -600 Airplanes, 39790-39795 [2010-16181]

Download as PDF 39790 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0790; Directorate Identifier 2008–NM–177–AD; Amendment 39–16285; AD 2010–10–06] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330–200 and –300 Airplanes and Model A340–200, –300, –500, and –600 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: Uncontained APU [auxiliary power unit] generator failures on ground have occurred on Airbus A330 aircraft in service. APU generator design is common to all A330 and A340 aircraft. Preliminary investigations confirmed that these failures have resulted in structural damage to the APU compartment and, in one case, to the stabiliser compartment. Loose APU generator parts can lead to damage to the APU firewall, reducing its fire extinguishing capability and potentially leading to a temporary uncontrolled fire. Although the root cause has not yet been determined, the investigation showed a sequence of events where a collapse of the Drive End Bearing (DEB) leads to an uncontained failure. Evidence has also shown that the DEB failures are not instantaneous, and therefore, the detection of small debris could indicate early stage of a DEB failure. jlentini on DSKJ8SOYB1PROD with RULES * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective August 17, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 17, 2010. On June 26, 2007 (72 FR 31973, June 11, 2007), the Director of the Federal Register approved the incorporation by VerDate Mar<15>2010 16:12 Jul 12, 2010 Jkt 220001 reference of certain other publications listed in this AD. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 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 include an AD that would apply to the specified products. That NPRM was published in the Federal Register on September 25, 2009 (74 FR 48872), and proposed to supersede AD 2007–18–04, Amendment 39–15184 (72 FR 50042, August 30, 2007). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Uncontained APU [auxiliary power unit] generator failures on ground have occurred on Airbus A330 aircraft in service. APU generator design is common to all A330 and A340 aircraft. Preliminary investigations confirmed that these failures have resulted in structural damage to the APU compartment and, in one case, to the stabiliser compartment. Loose APU generator parts can lead to damage to the APU firewall, reducing its fire extinguishing capability and potentially leading to a temporary uncontrolled fire. Although the root cause has not yet been determined, the investigation showed a sequence of events where a collapse of the Drive End Bearing (DEB) leads to an uncontained failure. Evidence has also shown that the DEB failures are not instantaneous, and therefore, the detection of small debris could indicate early stage of a DEB failure. To address this subject, EASA issued Emergency AD 2007–0188–E, requiring repetitive inspections of the APU generator Scavenge filter element and filter housing and of the APU generator Drain plug for signs of small debris coming from the APU generator, allowing detection of the early stage of APU generator failure. That AD was later revised to extend the compliance time and to provide another option for the repetitive inspection. Subsequently, another uncontained APU generator failure occurred on ground on an PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 A330 aircraft, operated within the provisions of MMEL [master minimum equipment list] item 36–11–01, with similar structural damages as the previous APU generator burst events. The investigation of this event revealed that the inspection required by paragraph 4 of AD 2007–0188R1 before the first flight under the MMEL rectification interval had not been performed and that the APU generator had not been properly installed (two seal plates instead of one). Consequently, EASA issued AD 2008– 0017, superseding AD 2007–0188R1 and requiring the following additional actions: —a visual inspection of the APU generator seal plate fitting, —an inspection following MMEL item 36– 11–01 or 24–22–01 rectification and —an inspection each time a new or serviceable APU generator or APU is installed on an aircraft. EASA issued AD 2008–0017R1 to cancel the inspection of paragraph 4 for A330 aircraft, when operated within the provisions of MMEL item 36–11–01 further to ETOPS [Extended-Range Twin-Engine Operations Performance Standards] certification of A330 APU. Finally, Airbus has developed a secondary housing for the APU generator that is designed to contain APU generator parts in the event of an APU generator burst. For the above described reasons, this AD retains the requirements of EASA AD 2008– 0017R1, which is superseded, and adds the requirement to install a secondary housing on the APU generator. After installation of the secondary APU generator housing on an aircraft, the repetitive inspections of this AD are no longer required for that aircraft. This AD retains the requirements of AD 2007–18–04. The new requirements include inspecting the APU generator scavenge oil filter element for contamination, the APU generator drain plug for contamination, and the APU generator scavenge filter housing for contamination, and a terminating action (installing a secondary housing line replaceable unit). Applicable corrective actions include, depending on the findings, replacing or reinstalling the APU generator scavenge oil filter and packing, replacing or reinstalling the APU generator drain plug, and replacing or reinstalling the APU generator scavenge filter housing. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information The NPRM cited Airbus Service Bulletins A330–24–3045, dated June 13, 2008; A340–24–4058, dated June 13, 2008; and A340–24–5022, dated June 23, 2008. Airbus has released the following new service bulletins: E:\FR\FM\13JYR1.SGM 13JYR1 39791 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations TABLE—NEW SERVICE INFORMATION Airbus— Revision— Mandatory Service Bulletin A330–24–3045 .................................................................................................... Mandatory Service Bulletin A340–24–4058 .................................................................................................... Mandatory Service Bulletin A340–24–5022 .................................................................................................... We have also revised paragraphs (h)(2), (h)(3), and (h)(4) of this AD to clarify that doing the installation terminates the inspection requirements of those paragraphs. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. jlentini on DSKJ8SOYB1PROD with RULES The latest revisions of the service information make minor updates and specify that no additional work is necessary on airplanes modified in accordance with the original documents. We have revised this final rule to incorporate the latest revisions of the service information. We have also added paragraph (h)(6) and Table 5 to this AD to give credit for actions done in accordance with the original service information. We have reidentified subsequent tables accordingly. Conclusion Request To Include a Terminating Modification for Actions Required by Paragraphs (h)(3) and (h)(4) of the NPRM EVA Airways Corporation (EVA) requests that we revise the NPRM to include a terminating modification for actions required by paragraphs (h)(3) and (h)(4) of the NPRM. Accomplishing the actions specified in paragraph (h)(5) of the NPRM would terminate the actions required by paragraphs (g)(2), (g)(3), and (h)(2) of the NPRM. EVA refers to a message it received from Airbus and states that installing the APU generator secondary housing terminates the repetitive inspections specified in paragraphs (g)(2), (g)(3), (h)(2), (h)(3), and (h)(4) of the NPRM. We agree with the commenter’s request. The EASA AD specifies that installing the secondary housing line replacement unit terminates repetitive inspections. We have also received information from Airbus indicating that installing the APU generator secondary housing terminates the repetitive inspections required by paragraphs (h)(3) and (h)(4) of the NPRM. We have revised paragraph (h)(5) of this final rule to specify that installing the APU generator secondary housing terminates the repetitive inspections specified in paragraphs (g)(2) and (g)(3) of this AD and the inspections specified in paragraphs (h)(2), (h)(3), and (h)(4) of this AD. We have also revised paragraphs (g)(2) and (g)(3) of this final rule to clarify that doing the installation required by paragraph (h)(5) of this AD terminates the repetitive inspections. VerDate Mar<15>2010 16:12 Jul 12, 2010 Jkt 220001 Explanation of Changes Made to This AD In paragraphs (g)(1), (g)(2), and (g)(3) of this AD, we have clarified that the service information specified in Table 2 or Table 3 of this AD is acceptable for compliance with the applicable actions. We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Explanation of Change to Costs of Compliance Since issuance of the NPRM, we have increased the labor rate used in the Costs of Compliance from $80 per workhour to $85 per work-hour. The Costs of Compliance information, below, reflects this increase in the specified hourly labor rate. Costs of Compliance We estimate that this AD will affect about 41 products of U.S. registry. The actions that are required by AD 2007–18–04 and retained in this AD take about 11 work-hours per product, PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 01 01 01 Dated— October 1, 2008. October 1, 2008. November 27, 2008. at an average labor rate of $85 per work hour. Required parts cost $0 per product. Based on these figures, the estimated cost of the currently required actions is $935 per product. We estimate that it will take about 10 work-hours per product to comply with the new basic requirements of this AD. The average labor rate is $85 per workhour. Required parts will cost about $0 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these costs. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $34,850, or $850 per product. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this 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 this AD: E:\FR\FM\13JYR1.SGM 13JYR1 39792 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 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); and 3. 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. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–15184 (72 FR 50042, August 30, 2007) and adding the following new AD: ■ 2010–10–06 Airbus: Amendment 39–16285. Docket No. FAA–2009–0790; Directorate Identifier 2008–NM–177–AD. Effective Date (a) This airworthiness directive (AD) becomes effective August 17, 2010. jlentini on DSKJ8SOYB1PROD with RULES Affected ADs (b) This AD supersedes AD 2007–18–04, Amendment 39–15184. Applicability (c) This AD applies to the airplanes certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD. (1) Airbus Model A330–201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342, and –343 series airplanes, VerDate Mar<15>2010 16:12 Jul 12, 2010 Jkt 220001 all serial numbers, except those on which Airbus modification 56985 has been embodied in production. (2) Airbus Model A340–211, –212, –213, –311, –312, and –313 series airplanes; and Model A340–541 and A340–642 airplanes; all serial numbers, except those on which Airbus modification 56985 has been embodied in production. Subject (d) Air Transport Association (ATA) of America Code 24: Electrical power. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Uncontained APU [auxiliary power unit] generator failures on ground have occurred on Airbus A330 aircraft in service. APU generator design is common to all A330 and A340 aircraft. Preliminary investigations confirmed that these failures have resulted in structural damage to the APU compartment and, in one case, to the stabiliser compartment. Loose APU generator parts can lead to damage to the APU firewall, reducing its fire extinguishing capability and potentially leading to a temporary uncontrolled fire. Although the root cause has not yet been determined, the investigation showed a sequence of events where a collapse of the Drive End Bearing (DEB) leads to an uncontained failure. Evidence has also shown that the DEB failures are not instantaneous, and therefore, the detection of small debris could indicate early stage of a DEB failure. To address this subject, EASA issued Emergency AD 2007–0188–E, requiring repetitive inspections of the APU generator Scavenge filter element and filter housing and of the APU generator Drain plug for signs of small debris coming from the APU generator, allowing detection of the early stage of APU generator failure. That AD was later revised to extend the compliance time and to provide another option for the repetitive inspection. Subsequently, another uncontained APU generator failure occurred on ground on an A330 aircraft, operated within the provisions of MMEL [master minimum equipment list] item 36–11–01, with similar structural damages as the previous APU generator burst events. The investigation of this event revealed that the inspection required by paragraph 4 of AD 2007–0188R1 before the first flight under the MMEL rectification interval had not been performed and that the APU generator had not been properly installed (two seal plates instead of one). Consequently, EASA issued AD 2008– 0017, superseding AD 2007–0188R1 and requiring the following additional actions: —a visual inspection of the APU generator seal plate fitting, —an inspection following MMEL item 36– 11–01 or 24–22–01 rectification and —an inspection each time a new or serviceable APU generator or APU is installed on an aircraft. EASA issued AD 2008–0017R1 to cancel the inspection of paragraph 4 for A330 aircraft, when operated within the provisions PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 of MMEL item 36–11–01 further to ETOPS [Extended-Range Twin-Engine Operations Performance Standards] certification of A330 APU. Finally, Airbus has developed a secondary housing for the APU generator that is designed to contain APU generator parts in the event of an APU generator burst. For the above described reasons, this AD retains the requirements of EASA AD 2008– 0017R1, which is superseded, and adds the requirement to install a secondary housing on the APU generator. After installation of the secondary APU generator housing on an aircraft, the repetitive inspections of this AD are no longer required for that aircraft. This AD retains the requirements of AD 2007–18–04, which superseded AD 2007–12– 10, Amendment 39–15088. The new requirements include inspecting the APU generator scavenge oil filter element for contamination, the APU generator drain plug for contamination, and the APU generator scavenge filter housing for contamination, and a terminating action (installing a secondary housing line replaceable unit). Applicable corrective actions include, depending on the findings, replacing or reinstalling the APU generator scavenge oil filter and packing, replacing or reinstalling the APU generator drain plug, and replacing or reinstalling the APU generator scavenge filter housing. RESTATEMENT OF REQUIREMENTS OF AD 2007–12–10, WITH NO CHANGES Actions and Compliance (f) Unless already done, do the following actions. (1) For airplanes on which the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness is before March 1, 2007: Within 63 days after June 26, 2007 (the effective date of AD 2007–12–10), in accordance with the instructions of Airbus All Operators Telex (AOT) A330–24A3042, A340–24A4056, or A340–24A5020, all Revision 02, all dated April 12, 2007; as applicable, inspect the inlet screen (last chance filter) for the generator scavenge-oil pump for signs of debris and, as applicable, apply all associated corrective actions before further flight. (2) For Model A330 aircraft operating under MMEL (master minimum equipment list) Item 24–22–01 ‘AC Main Generation’ or MMEL Item 36–11–01 ‘Bleed Air Supply System Failure’ and on which the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness is before March 1, 2007: As of June 26, 2007, before each flight, perform a check of the differential pressure indicator button on the lube filter and the generator scavenge filter in accordance with the instructions of Airbus AOT A330–24A3042, Revision 02, dated April 12, 2007, until accomplishment of paragraph (g)(5) of this AD. Note 1: The repetitive checks before each flight specified in paragraph (f)(2) of this AD are not required for airplanes operated under E:\FR\FM\13JYR1.SGM 13JYR1 39793 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations MMEL Item 36–11–01, provided the APU generator has been removed or deactivated in accordance with the instructions of Airbus AOT A330–24A3042, Revision 02, dated April 12, 2007. (3) Actions done before June 26, 2007, in accordance with the applicable Airbus service information in Table 1 of this AD are acceptable for compliance with the corresponding provisions of paragraph (f) of this AD. TABLE 1—ACCEPTABLE EARLIER REVISIONS OF SERVICE INFORMATION Airbus all operators telex— A330–24A3042 A330–24A3042 A340–24A4056 A340–24A4056 A340–24A5020 A340–24A5020 Revision— .................................................................................................................... .................................................................................................................... .................................................................................................................... .................................................................................................................... .................................................................................................................... .................................................................................................................... RESTATEMENT OF REQUIREMENTS OF AD 2007–18–04, WITH REVISED SERVICE INFORMATION Actions and Compliance (g) Unless already done, do the following actions. (1) For airplanes on which the date of issuance of the original French airworthiness Dated— Original ........................................... 01 ................................................... Original ........................................... 01 ................................................... Original ........................................... 01 ................................................... certificate or the date of issuance of the original French or EASA export certificate of airworthiness is on or before July 1, 2007: Within 30 days after September 14, 2007 (the effective date of AD 2007–18–04), in accordance with the instructions of paragraph 4.2.1 of the applicable Airbus service information specified in Table 2 or 3 March March March March March March 22, 29, 22, 29, 22, 29, 2007. 2007. 2007. 2007. 2007. 2007. of this AD, clean and inspect the APU generator scavenge oil filter element and housing and inspect the APU generator drain plug to detect metallic debris, and apply all applicable associated corrective actions before further flight. After the effective date of this AD, use only the service information specified in Table 3 of this AD. TABLE 2—SERVICE INFORMATION Airbus all operators telex— Revision— A330–24A3044 .................................................................................................................................................... A330–24A3044 .................................................................................................................................................... 01 02 A340-24A4057 ..................................................................................................................................................... A340–24A5021 .................................................................................................................................................... 02 01 Dated— July 20, 2007. December 20, 2007. August 14, 2007. July 20, 2007. TABLE 3—NEW SERVICE INFORMATION Airbus all operators telex— Revision— A330–24A3044 .................................................................................................................................................... A340–24A4057 .................................................................................................................................................... 03 03 A340–24A5021 .................................................................................................................................................... 02 (2) Within 450 aircraft flight hours or 200 APU operating hours, whichever occurs later, after accomplishing the inspection required by paragraph (g)(1) of this AD, in accordance with the instructions of paragraph 4.2.2 of the applicable Airbus information specified in Table 2 or Table 3 of this AD: Inspect the APU generator scavenge oil filter element and housing and the APU generator drain plug to detect metallic debris; and apply all applicable associated corrective actions before further flight. Repeat the inspections thereafter at intervals not to exceed 450 aircraft flight hours or 200 APU operating hours, whichever occurs later until the installation required by paragraph (h)(5) of this AD is done. After the effective date of this AD, use only the service information specified in Table 3 of this AD. (3) For airplanes on which the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness is after July 1, 2007: Within 450 aircraft flight hours or 200 APU operating hours after September 14, 2007, whichever occurs later, in accordance with the instructions of paragraph 4.2.2 of the applicable Airbus service information specified in Table 2 or Table 3 of this AD: Inspect the APU generator scavenge oil filter element and housing and the APU generator Dated— May 26, 2008. December 20, 2007. December 20, 2007. drain plug to detect metallic debris; and apply all applicable associated corrective actions before further flight. Repeat the inspections thereafter at intervals not to exceed 450 aircraft flight hours or 200 APU operating hours, whichever occurs later until the installation required by paragraph (h)(5) of this AD is done. After the effective date of this AD, use only the service information specified in Table 3 of this AD. (4) Actions done before September 14, 2007, in accordance with the applicable Airbus service information in Table 4 of this AD are acceptable for compliance with the corresponding provisions of paragraph (g) of this AD. jlentini on DSKJ8SOYB1PROD with RULES TABLE 4—ACCEPTABLE EARLIER REVISIONS OF SERVICE INFORMATION Airbus all operators telex— Revision— Dated— A330–24A3044 ....................................................................................................................... A340-24A4057 ........................................................................................................................ A340-24A4057 ........................................................................................................................ A340–24A5021 ....................................................................................................................... Original ............................................ Original ............................................ 01 .................................................... Original ............................................ July July July July VerDate Mar<15>2010 16:12 Jul 12, 2010 Jkt 220001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\13JYR1.SGM 13JYR1 5, 2007. 5, 2007. 20, 2007. 5, 2007. 39794 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations (5) For Model A330 aircraft operating under MMEL Item 24–22–01, ‘‘AC Main Generation,’’ or MMEL Item 36–11–01, ‘‘Bleed Air Supply System Failure’’: Unless the APU generator has been deferred in accordance with the MMEL by deactivation (quill shaft removed) or removal, the inspection required by paragraph (g)(2) or (g)(3), as applicable, of this AD must be performed prior to the first flight of the specified MMEL repair time interval. Accomplishing the actions in this paragraph terminates the actions required by paragraph (f)(2) of this AD. Note 2: For A330 aircraft, MMEL Item 24– 22–01 (AC Main Generation) and/or MMEL Item 36–11–01 (Bleed Air Supply System Failure) require that the APU be used during the entire flight. NEW REQUIREMENTS OF THIS AD Actions and Compliance (h) Unless already done, do the following actions. (1) As of the effective date of this AD, before further flight after an APU generator or an APU is installed on the airplane: Inspect the APU generator scavenge oil filter element for contamination (including metallic particles), the APU generator drain plug for contamination (including metallic particles), and the APU generator scavenge filter housing for contamination (including metallic particles), in accordance with paragraph 4.2 of the applicable service information specified in Table 3 of this AD. Do all applicable corrective actions before further flight in accordance with paragraph 4.2 of the applicable service information specified in Table 3 of this AD. (2) Within 450 aircraft flight hours or 200 APU operating hours, whichever occurs later, after accomplishing the inspection required by paragraph (h)(1) of this AD, do the inspection as required by paragraph (g)(2) of this AD. Doing the installation required by paragraph (h)(5) of this AD terminates the requirements of this paragraph. (3) For Model A330 airplanes operated within the provisions of MMEL Item 24–22– 01, ‘‘AC Main Generation,’’ that are dispatched with the APU operating during the entire flight in accordance with the provisions of MMEL Item 24–22–01: Perform the inspection required by paragraph (g)(2) of this AD at the applicable time in paragraph (h)(3)(i) or (h)(3)(ii) of this AD, unless the APU generator is removed or deactivated (quill shaft removed as described in the MMEL item). Doing the installation required by paragraph (h)(5) of this AD terminates the requirements of this paragraph. (i) Before the first flight of the MMEL rectification interval. (ii) Before the first flight following MMEL rectification. (4) Removing or deactivating the APU generator, or rendering the APU inoperative, in accordance with paragraph 4.3 of the applicable service information specified in Table 3 of this AD, defers the inspection required by paragraph (g)(2) of this AD. The deferred inspection must be performed before further flight after the system is reactivated. Doing the installation required by paragraph (h)(5) of this AD terminates the requirements of this paragraph. (5) Within 6 months after the effective date of this AD, install a secondary housing line replaceable unit (LRU) over the end of the APU generator, in accordance with the Accomplishment Instructions of the applicable service information specified in Table 6 of this AD. Performing this modification terminates the repetitive inspections required by paragraphs (g)(2) and (g)(3) of this AD, and the inspections required by paragraphs (h)(2), (h)(3), and (h)(4) of this AD. (6) Actions accomplished before the effective date of this AD in accordance with service information in Table 5 of this AD are acceptable for compliance with the corresponding actions specified in this AD. TABLE 5—SERVICE INFORMATION ACCEPTABLE FOR PREVIOUS COMPLIANCE FAA AD Differences Note 3: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (i) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Airbus service bulletin— Dated— Related Information A330–20–3045 .................... A340–24–4058 .................... A340–24–5022 .................... June 13, 2008. June 13, 2008. June 23, 2008. (j) Refer to MCAI EASA Airworthiness Directive 2008–0173, dated September 15, 2008, and the service information identified in Table 6 of this AD for related information. TABLE 6—SERVICE INFORMATION REQUIRED BY THIS AD Airbus— ........................................................................................................................................... ........................................................................................................................................... ........................................................................................................................................... ........................................................................................................................................... 02 03 02 03 AOT A340–24A5020 ........................................................................................................................................... AOT A340–24A5021 ........................................................................................................................................... 02 02 Mandatory Service Bulletin A330–24–3045 ........................................................................................................ Mandatory Service Bulletin A340–24–4058 ........................................................................................................ Mandatory Service Bulletin A340–24–5022 ........................................................................................................ jlentini on DSKJ8SOYB1PROD with RULES AOT AOT AOT AOT Revision— A330–24A3042 A330–24A3044 A340–24A4056 A340–24A4057 01 01 01 Material Incorporated by Reference (k) You must use the service information contained in Table 7 of this AD, as VerDate Mar<15>2010 16:12 Jul 12, 2010 Jkt 220001 applicable, to do the actions required by this AD, unless the AD specifies otherwise. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\13JYR1.SGM 13JYR1 Dated— April 12, 2007. May 26, 2008. April 12, 2007. December 20, 2007. April 12, 2007. December 20, 2007. October 1, 2008. October 1, 2008. November 27, 2008. 39795 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations TABLE 7—ALL MATERIAL INCORPORATED BY REFERENCE Airbus— AOT AOT AOT AOT Revision— A330–24A3042 A330–24A3044 A340–24A4056 A340–24A4057 ........................................................................................................................................... ........................................................................................................................................... ........................................................................................................................................... ........................................................................................................................................... 02 03 02 03 AOT A340–24–A5020 ......................................................................................................................................... AOT A340–24A5021 ........................................................................................................................................... 02 02 Mandatory Service Bulletin A330–24–3045 ........................................................................................................ Mandatory Service Bulletin A340–24–4058 ........................................................................................................ Mandatory Service Bulletin A340–24–5022 ........................................................................................................ 01 01 01 Dated— April 12, 2007. May 26, 2008. April 12, 2007. December 20, 2007. April 12, 2007. December 20, 2007. October 1, 2008. October 1, 2008. November 27, 2008. (The AOT document number, revision level, and date are indicated on only page 1 of these documents.) (1) The Director of the Federal Register approved the incorporation by reference of the service information contained in Table 8 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51. TABLE 8—NEW MATERIAL INCORPORATED BY REFERENCE Airbus— Revision— AOT A330–24A3044 ........................................................................................................................................... AOT A340–24A4057 ........................................................................................................................................... 03 03 AOT A340–24A5021 ........................................................................................................................................... 02 Mandatory Service Bulletin A330–24–3045 ........................................................................................................ Mandatory Service Bulletin A340–24–4058 ........................................................................................................ Mandatory Service Bulletin A340–24–5022 ........................................................................................................ 01 01 01 (2) The Director of the Federal Register previously approved the incorporation by reference of the service information Dated— May 26, 2008. December 20, 2007. December 20, 2007. October 1, 2008. October 1, 2008. November 27, 2008. contained in Table 9 of this AD on June 26, 2007 (72 FR 31973, June 11, 2007). TABLE 9—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE Revision level— Airbus all operators telex— jlentini on DSKJ8SOYB1PROD with RULES A330–24A3042 ......................................................................................................................................................... A340–24A4056 ......................................................................................................................................................... A340–24A5020 ......................................................................................................................................................... (3) 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, e-mail: airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. (4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may also review copies of the 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: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. VerDate Mar<15>2010 16:12 Jul 12, 2010 Jkt 220001 Issued in Renton, Washington, June 23, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. Dated— 02 02 02 April 12, 2007. April 12, 2007. April 12, 2007. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [FR Doc. 2010–16181 Filed 7–12–10; 8:45 am] [Docket No. FAA–2010–0684; Directorate Identifier 2010–CE–031–AD; Amendment 39–16360; AD 2010–14–15] BILLING CODE 4910–13–P PO 00000 RIN 2120–AA64 Airworthiness Directives; Aircraft Industries a.s. (Type Certificate G60EU ´ ´ Previously Held by LETECKE ZAVODY a.s. and LET Aeronautical Works) Model L–13 Blanik Gliders AGENCY: Federal Aviation Administration (FAA), DOT. Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\13JYR1.SGM 13JYR1

Agencies

[Federal Register Volume 75, Number 133 (Tuesday, July 13, 2010)]
[Rules and Regulations]
[Pages 39790-39795]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-16181]

[[Page 39790]]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0790; Directorate Identifier 2008-NM-177-AD;
Amendment 39-16285; AD 2010-10-06]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A330-200 and -300
Airplanes and Model A340-200, -300, -500, and -600 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. This AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:

We are issuing this AD to require actions to correct the unsafe
condition on these products.

DATES: This AD becomes effective August 17, 2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 17,
2010.
On June 26, 2007 (72 FR 31973, June 11, 2007), the Director of the
Federal Register approved the incorporation by reference of certain
other publications listed in this AD.

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 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 include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on September 25, 2009
(74 FR 48872), and proposed to supersede AD 2007-18-04, Amendment 39-
15184 (72 FR 50042, August 30, 2007). That NPRM proposed to correct an
unsafe condition for the specified products. The MCAI states:

Uncontained APU [auxiliary power unit] generator failures on
ground have occurred on Airbus A330 aircraft in service. APU
generator design is common to all A330 and A340 aircraft.
Preliminary investigations confirmed that these failures have
resulted in structural damage to the APU compartment and, in one
case, to the stabiliser compartment. Loose APU generator parts can
lead to damage to the APU firewall, reducing its fire extinguishing
capability and potentially leading to a temporary uncontrolled fire.
Although the root cause has not yet been determined, the
investigation showed a sequence of events where a collapse of the
Drive End Bearing (DEB) leads to an uncontained failure. Evidence
has also shown that the DEB failures are not instantaneous, and
therefore, the detection of small debris could indicate early stage
of a DEB failure.
To address this subject, EASA issued Emergency AD 2007-0188-E,
requiring repetitive inspections of the APU generator Scavenge
filter element and filter housing and of the APU generator Drain
plug for signs of small debris coming from the APU generator,
allowing detection of the early stage of APU generator failure. That
AD was later revised to extend the compliance time and to provide
another option for the repetitive inspection.
Subsequently, another uncontained APU generator failure occurred
on ground on an A330 aircraft, operated within the provisions of
MMEL [master minimum equipment list] item 36-11-01, with similar
structural damages as the previous APU generator burst events. The
investigation of this event revealed that the inspection required by
paragraph 4 of AD 2007-0188R1 before the first flight under the MMEL
rectification interval had not been performed and that the APU
generator had not been properly installed (two seal plates instead
of one).
Consequently, EASA issued AD 2008-0017, superseding AD 2007-
0188R1 and requiring the following additional actions:
--a visual inspection of the APU generator seal plate fitting,
--an inspection following MMEL item 36-11-01 or 24-22-01
rectification and
--an inspection each time a new or serviceable APU generator or
APU is installed on an aircraft.
EASA issued AD 2008-0017R1 to cancel the inspection of paragraph
4 for A330 aircraft, when operated within the provisions of MMEL
item 36-11-01 further to ETOPS [Extended-Range Twin-Engine
Operations Performance Standards] certification of A330 APU.
Finally, Airbus has developed a secondary housing for the APU
generator that is designed to contain APU generator parts in the
event of an APU generator burst.
For the above described reasons, this AD retains the
requirements of EASA AD 2008-0017R1, which is superseded, and adds
the requirement to install a secondary housing on the APU generator.
After installation of the secondary APU generator housing on an
aircraft, the repetitive inspections of this AD are no longer
required for that aircraft.

This AD retains the requirements of AD 2007-18-04. The new requirements
include inspecting the APU generator scavenge oil filter element for
contamination, the APU generator drain plug for contamination, and the
APU generator scavenge filter housing for contamination, and a
terminating action (installing a secondary housing line replaceable
unit). Applicable corrective actions include, depending on the
findings, replacing or reinstalling the APU generator scavenge oil
filter and packing, replacing or reinstalling the APU generator drain
plug, and replacing or reinstalling the APU generator scavenge filter
housing. You may obtain further information by examining the MCAI in
the AD docket.

Relevant Service Information

The NPRM cited Airbus Service Bulletins A330-24-3045, dated June
13, 2008; A340-24-4058, dated June 13, 2008; and A340-24-5022, dated
June 23, 2008. Airbus has released the following new service bulletins:

[[Page 39791]]

Table--New Service Information
------------------------------------------------------------------------
Airbus-- Revision-- Dated--
------------------------------------------------------------------------
Mandatory Service Bulletin 01 October 1, 2008.
A330-24-3045.
Mandatory Service Bulletin 01 October 1, 2008.
A340-24-4058.
Mandatory Service Bulletin 01 November 27, 2008.
A340-24-5022.
------------------------------------------------------------------------

The latest revisions of the service information make minor updates
and specify that no additional work is necessary on airplanes modified
in accordance with the original documents. We have revised this final
rule to incorporate the latest revisions of the service information. We
have also added paragraph (h)(6) and Table 5 to this AD to give credit
for actions done in accordance with the original service information.
We have reidentified subsequent tables accordingly.

Comments

We gave the public the opportunity to participate in developing
this AD. We considered the comment received.

Request To Include a Terminating Modification for Actions Required by
Paragraphs (h)(3) and (h)(4) of the NPRM

EVA Airways Corporation (EVA) requests that we revise the NPRM to
include a terminating modification for actions required by paragraphs
(h)(3) and (h)(4) of the NPRM. Accomplishing the actions specified in
paragraph (h)(5) of the NPRM would terminate the actions required by
paragraphs (g)(2), (g)(3), and (h)(2) of the NPRM. EVA refers to a
message it received from Airbus and states that installing the APU
generator secondary housing terminates the repetitive inspections
specified in paragraphs (g)(2), (g)(3), (h)(2), (h)(3), and (h)(4) of
the NPRM.
We agree with the commenter's request. The EASA AD specifies that
installing the secondary housing line replacement unit terminates
repetitive inspections. We have also received information from Airbus
indicating that installing the APU generator secondary housing
terminates the repetitive inspections required by paragraphs (h)(3) and
(h)(4) of the NPRM. We have revised paragraph (h)(5) of this final rule
to specify that installing the APU generator secondary housing
terminates the repetitive inspections specified in paragraphs (g)(2)
and (g)(3) of this AD and the inspections specified in paragraphs
(h)(2), (h)(3), and (h)(4) of this AD. We have also revised paragraphs
(g)(2) and (g)(3) of this final rule to clarify that doing the
installation required by paragraph (h)(5) of this AD terminates the
repetitive inspections. We have also revised paragraphs (h)(2), (h)(3),
and (h)(4) of this AD to clarify that doing the installation terminates
the inspection requirements of those paragraphs.

Explanation of Changes Made to This AD

In paragraphs (g)(1), (g)(2), and (g)(3) of this AD, we have
clarified that the service information specified in Table 2 or Table 3
of this AD is acceptable for compliance with the applicable actions.

Conclusion

We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting the
AD with the changes described previously. We also determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.

Differences Between This AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.

Explanation of Change to Costs of Compliance

Since issuance of the NPRM, we have increased the labor rate used
in the Costs of Compliance from $80 per work-hour to $85 per work-hour.
The Costs of Compliance information, below, reflects this increase in
the specified hourly labor rate.

Costs of Compliance

We estimate that this AD will affect about 41 products of U.S.
registry.
The actions that are required by AD 2007-18-04 and retained in this
AD take about 11 work-hours per product, at an average labor rate of
$85 per work hour. Required parts cost $0 per product. Based on these
figures, the estimated cost of the currently required actions is $935
per product.
We estimate that it will take about 10 work-hours per product to
comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts will cost about $0 per
product. Where the service information lists required parts costs that
are covered under warranty, we have assumed that there will be no
charge for these costs. As we do not control warranty coverage for
affected parties, some parties may incur costs higher than estimated
here. Based on these figures, we estimate the cost of this AD to the
U.S. operators to be $34,850, or $850 per product.

Authority for This Rulemaking

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

Regulatory Findings

We determined that this 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 this AD:

[[Page 39792]]

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); and
3. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.

Examining the AD Docket

You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
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 Amendment 39-15184 (72 FR
50042, August 30, 2007) and adding the following new AD:

2010-10-06 Airbus: Amendment 39-16285. Docket No. FAA-2009-0790;
Directorate Identifier 2008-NM-177-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective August
17, 2010.

Affected ADs

(b) This AD supersedes AD 2007-18-04, Amendment 39-15184.

Applicability

(c) This AD applies to the airplanes certificated in any
category, identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 series airplanes, all
serial numbers, except those on which Airbus modification 56985 has
been embodied in production.
(2) Airbus Model A340-211, -212, -213, -311, -312, and -313
series airplanes; and Model A340-541 and A340-642 airplanes; all
serial numbers, except those on which Airbus modification 56985 has
been embodied in production.

Subject

(d) Air Transport Association (ATA) of America Code 24:
Electrical power.

Reason

(e) The mandatory continuing airworthiness information (MCAI)
states:
Uncontained APU [auxiliary power unit] generator failures on
ground have occurred on Airbus A330 aircraft in service. APU
generator design is common to all A330 and A340 aircraft.
Preliminary investigations confirmed that these failures have
resulted in structural damage to the APU compartment and, in one
case, to the stabiliser compartment. Loose APU generator parts can
lead to damage to the APU firewall, reducing its fire extinguishing
capability and potentially leading to a temporary uncontrolled fire.
Although the root cause has not yet been determined, the
investigation showed a sequence of events where a collapse of the
Drive End Bearing (DEB) leads to an uncontained failure. Evidence
has also shown that the DEB failures are not instantaneous, and
therefore, the detection of small debris could indicate early stage
of a DEB failure.
To address this subject, EASA issued Emergency AD 2007-0188-E,
requiring repetitive inspections of the APU generator Scavenge
filter element and filter housing and of the APU generator Drain
plug for signs of small debris coming from the APU generator,
allowing detection of the early stage of APU generator failure. That
AD was later revised to extend the compliance time and to provide
another option for the repetitive inspection.
Subsequently, another uncontained APU generator failure occurred
on ground on an A330 aircraft, operated within the provisions of
MMEL [master minimum equipment list] item 36-11-01, with similar
structural damages as the previous APU generator burst events. The
investigation of this event revealed that the inspection required by
paragraph 4 of AD 2007-0188R1 before the first flight under the MMEL
rectification interval had not been performed and that the APU
generator had not been properly installed (two seal plates instead
of one).
Consequently, EASA issued AD 2008-0017, superseding AD 2007-
0188R1 and requiring the following additional actions:

--a visual inspection of the APU generator seal plate fitting,
--an inspection following MMEL item 36-11-01 or 24-22-01
rectification and
--an inspection each time a new or serviceable APU generator or APU
is installed on an aircraft.

EASA issued AD 2008-0017R1 to cancel the inspection of paragraph
4 for A330 aircraft, when operated within the provisions of MMEL
item 36-11-01 further to ETOPS [Extended-Range Twin-Engine
Operations Performance Standards] certification of A330 APU.
Finally, Airbus has developed a secondary housing for the APU
generator that is designed to contain APU generator parts in the
event of an APU generator burst.
For the above described reasons, this AD retains the
requirements of EASA AD 2008-0017R1, which is superseded, and adds
the requirement to install a secondary housing on the APU generator.
After installation of the secondary APU generator housing on an
aircraft, the repetitive inspections of this AD are no longer
required for that aircraft.

This AD retains the requirements of AD 2007-18-04, which superseded
AD 2007-12-10, Amendment 39-15088. The new requirements include
inspecting the APU generator scavenge oil filter element for
contamination, the APU generator drain plug for contamination, and
the APU generator scavenge filter housing for contamination, and a
terminating action (installing a secondary housing line replaceable
unit). Applicable corrective actions include, depending on the
findings, replacing or reinstalling the APU generator scavenge oil
filter and packing, replacing or reinstalling the APU generator
drain plug, and replacing or reinstalling the APU generator scavenge
filter housing.

RESTATEMENT OF REQUIREMENTS OF AD 2007-12-10, WITH NO CHANGES

Actions and Compliance

(f) Unless already done, do the following actions.
(1) For airplanes on which the date of issuance of the original
French airworthiness certificate or the date of issuance of the
original French or EASA export certificate of airworthiness is
before March 1, 2007: Within 63 days after June 26, 2007 (the
effective date of AD 2007-12-10), in accordance with the
instructions of Airbus All Operators Telex (AOT) A330-24A3042, A340-
24A4056, or A340-24A5020, all Revision 02, all dated April 12, 2007;
as applicable, inspect the inlet screen (last chance filter) for the
generator scavenge-oil pump for signs of debris and, as applicable,
apply all associated corrective actions before further flight.
(2) For Model A330 aircraft operating under MMEL (master minimum
equipment list) Item 24-22-01 `AC Main Generation' or MMEL Item 36-
11-01 `Bleed Air Supply System Failure' and on which the date of
issuance of the original French airworthiness certificate or the
date of issuance of the original French or EASA export certificate
of airworthiness is before March 1, 2007: As of June 26, 2007,
before each flight, perform a check of the differential pressure
indicator button on the lube filter and the generator scavenge
filter in accordance with the instructions of Airbus AOT A330-
24A3042, Revision 02, dated April 12, 2007, until accomplishment of
paragraph (g)(5) of this AD.

Note 1: The repetitive checks before each flight specified in
paragraph (f)(2) of this AD are not required for airplanes operated
under

[[Page 39793]]

MMEL Item 36-11-01, provided the APU generator has been removed or
deactivated in accordance with the instructions of Airbus AOT A330-
24A3042, Revision 02, dated April 12, 2007.

(3) Actions done before June 26, 2007, in accordance with the
applicable Airbus service information in Table 1 of this AD are
acceptable for compliance with the corresponding provisions of
paragraph (f) of this AD.

Table 1--Acceptable Earlier Revisions of Service Information
------------------------------------------------------------------------
Airbus all operators telex-- Revision-- Dated--
------------------------------------------------------------------------
A330-24A3042.................. Original......... March 22, 2007.
A330-24A3042.................. 01............... March 29, 2007.
A340-24A4056.................. Original......... March 22, 2007.
A340-24A4056.................. 01............... March 29, 2007.
A340-24A5020.................. Original......... March 22, 2007.
A340-24A5020.................. 01............... March 29, 2007.
------------------------------------------------------------------------

RESTATEMENT OF REQUIREMENTS OF AD 2007-18-04, WITH REVISED SERVICE
INFORMATION

Actions and Compliance

(g) Unless already done, do the following actions.
(1) For airplanes on which the date of issuance of the original
French airworthiness certificate or the date of issuance of the
original French or EASA export certificate of airworthiness is on or
before July 1, 2007: Within 30 days after September 14, 2007 (the
effective date of AD 2007-18-04), in accordance with the
instructions of paragraph 4.2.1 of the applicable Airbus service
information specified in Table 2 or 3 of this AD, clean and inspect
the APU generator scavenge oil filter element and housing and
inspect the APU generator drain plug to detect metallic debris, and
apply all applicable associated corrective actions before further
flight. After the effective date of this AD, use only the service
information specified in Table 3 of this AD.

Table 2--Service Information
------------------------------------------------------------------------
Airbus all operators telex-- Revision-- Dated--
------------------------------------------------------------------------
A330-24A3044................... 01 July 20, 2007.
A330-24A3044................... 02 December 20, 2007.
A340[dash]24A4057.............. 02 August 14, 2007.
A340-24A5021................... 01 July 20, 2007.
------------------------------------------------------------------------

Table 3--New Service Information
------------------------------------------------------------------------
Airbus all operators telex-- Revision-- Dated--
------------------------------------------------------------------------
A330-24A3044................... 03 May 26, 2008.
A340-24A4057................... 03 December 20, 2007.
A340-24A5021................... 02 December 20, 2007.
------------------------------------------------------------------------

(2) Within 450 aircraft flight hours or 200 APU operating hours,
whichever occurs later, after accomplishing the inspection required
by paragraph (g)(1) of this AD, in accordance with the instructions
of paragraph 4.2.2 of the applicable Airbus information specified in
Table 2 or Table 3 of this AD: Inspect the APU generator scavenge
oil filter element and housing and the APU generator drain plug to
detect metallic debris; and apply all applicable associated
corrective actions before further flight. Repeat the inspections
thereafter at intervals not to exceed 450 aircraft flight hours or
200 APU operating hours, whichever occurs later until the
installation required by paragraph (h)(5) of this AD is done. After
the effective date of this AD, use only the service information
specified in Table 3 of this AD.
(3) For airplanes on which the date of issuance of the original
French airworthiness certificate or the date of issuance of the
original French or EASA export certificate of airworthiness is after
July 1, 2007: Within 450 aircraft flight hours or 200 APU operating
hours after September 14, 2007, whichever occurs later, in
accordance with the instructions of paragraph 4.2.2 of the
applicable Airbus service information specified in Table 2 or Table
3 of this AD: Inspect the APU generator scavenge oil filter element
and housing and the APU generator drain plug to detect metallic
debris; and apply all applicable associated corrective actions
before further flight. Repeat the inspections thereafter at
intervals not to exceed 450 aircraft flight hours or 200 APU
operating hours, whichever occurs later until the installation
required by paragraph (h)(5) of this AD is done. After the effective
date of this AD, use only the service information specified in Table
3 of this AD.
(4) Actions done before September 14, 2007, in accordance with
the applicable Airbus service information in Table 4 of this AD are
acceptable for compliance with the corresponding provisions of
paragraph (g) of this AD.

Table 4--Acceptable Earlier Revisions of Service Information
------------------------------------------------------------------------
Airbus all operators telex-- Revision-- Dated--
------------------------------------------------------------------------
A330-24A3044................... Original.......... July 5, 2007.
A340[dash]24A4057.............. Original.......... July 5, 2007.
A340[dash]24A4057.............. 01................ July 20, 2007.
A340-24A5021................... Original.......... July 5, 2007.
------------------------------------------------------------------------

[[Page 39794]]

(5) For Model A330 aircraft operating under MMEL Item 24-22-01,
``AC Main Generation,'' or MMEL Item 36-11-01, ``Bleed Air Supply
System Failure'': Unless the APU generator has been deferred in
accordance with the MMEL by deactivation (quill shaft removed) or
removal, the inspection required by paragraph (g)(2) or (g)(3), as
applicable, of this AD must be performed prior to the first flight
of the specified MMEL repair time interval. Accomplishing the
actions in this paragraph terminates the actions required by
paragraph (f)(2) of this AD.

Note 2: For A330 aircraft, MMEL Item 24-22-01 (AC Main
Generation) and/or MMEL Item 36-11-01 (Bleed Air Supply System
Failure) require that the APU be used during the entire flight.

NEW REQUIREMENTS OF THIS AD

Actions and Compliance

(h) Unless already done, do the following actions.
(1) As of the effective date of this AD, before further flight
after an APU generator or an APU is installed on the airplane:
Inspect the APU generator scavenge oil filter element for
contamination (including metallic particles), the APU generator
drain plug for contamination (including metallic particles), and the
APU generator scavenge filter housing for contamination (including
metallic particles), in accordance with paragraph 4.2 of the
applicable service information specified in Table 3 of this AD. Do
all applicable corrective actions before further flight in
accordance with paragraph 4.2 of the applicable service information
specified in Table 3 of this AD.
(2) Within 450 aircraft flight hours or 200 APU operating hours,
whichever occurs later, after accomplishing the inspection required
by paragraph (h)(1) of this AD, do the inspection as required by
paragraph (g)(2) of this AD. Doing the installation required by
paragraph (h)(5) of this AD terminates the requirements of this
paragraph.
(3) For Model A330 airplanes operated within the provisions of
MMEL Item 24-22-01, ``AC Main Generation,'' that are dispatched with
the APU operating during the entire flight in accordance with the
provisions of MMEL Item 24-22-01: Perform the inspection required by
paragraph (g)(2) of this AD at the applicable time in paragraph
(h)(3)(i) or (h)(3)(ii) of this AD, unless the APU generator is
removed or deactivated (quill shaft removed as described in the MMEL
item). Doing the installation required by paragraph (h)(5) of this
AD terminates the requirements of this paragraph.
(i) Before the first flight of the MMEL rectification interval.
(ii) Before the first flight following MMEL rectification.
(4) Removing or deactivating the APU generator, or rendering the
APU inoperative, in accordance with paragraph 4.3 of the applicable
service information specified in Table 3 of this AD, defers the
inspection required by paragraph (g)(2) of this AD. The deferred
inspection must be performed before further flight after the system
is reactivated. Doing the installation required by paragraph (h)(5)
of this AD terminates the requirements of this paragraph.
(5) Within 6 months after the effective date of this AD, install
a secondary housing line replaceable unit (LRU) over the end of the
APU generator, in accordance with the Accomplishment Instructions of
the applicable service information specified in Table 6 of this AD.
Performing this modification terminates the repetitive inspections
required by paragraphs (g)(2) and (g)(3) of this AD, and the
inspections required by paragraphs (h)(2), (h)(3), and (h)(4) of
this AD.
(6) Actions accomplished before the effective date of this AD in
accordance with service information in Table 5 of this AD are
acceptable for compliance with the corresponding actions specified
in this AD.

Table 5--Service Information Acceptable for Previous Compliance
------------------------------------------------------------------------
Airbus service bulletin-- Dated--
------------------------------------------------------------------------
A330-20-3045............................ June 13, 2008.
A340-24-4058............................ June 13, 2008.
A340-24-5022............................ June 23, 2008.
------------------------------------------------------------------------

FAA AD Differences

Note 3: This AD differs from the MCAI and/or service information
as follows: No differences.

Other FAA AD Provisions

(i) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, FAA, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19.
Send information to ATTN: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-1138; fax (425) 227-1149. Before using any approved AMOC on any
airplane to which the AMOC applies, notify your principal
maintenance inspector (PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal inspector, your local Flight
Standards District Office.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.

Related Information

(j) Refer to MCAI EASA Airworthiness Directive 2008-0173, dated
September 15, 2008, and the service information identified in Table
6 of this AD for related information.

Table 6--Service Information Required by This AD
------------------------------------------------------------------------
Airbus-- Revision-- Dated--
------------------------------------------------------------------------
AOT A330-24A3042............... 02 April 12, 2007.
AOT A330-24A3044............... 03 May 26, 2008.
AOT A340-24A4056............... 02 April 12, 2007.
AOT A340-24A4057............... 03 December 20, 2007.
AOT A340-24A5020............... 02 April 12, 2007.
AOT A340-24A5021............... 02 December 20, 2007.
Mandatory Service Bulletin A330- 01 October 1, 2008.
24-3045.
Mandatory Service Bulletin A340- 01 October 1, 2008.
24-4058.
Mandatory Service Bulletin A340- 01 November 27, 2008.
24-5022.
------------------------------------------------------------------------

Material Incorporated by Reference

(k) You must use the service information contained in Table 7 of
this AD, as applicable, to do the actions required by this AD,
unless the AD specifies otherwise.

[[Page 39795]]

Table 7--All Material Incorporated by Reference
------------------------------------------------------------------------
Airbus-- Revision-- Dated--
------------------------------------------------------------------------
AOT A330-24A3042............... 02 April 12, 2007.
AOT A330-24A3044............... 03 May 26, 2008.
AOT A340-24A4056............... 02 April 12, 2007.
AOT A340-24A4057............... 03 December 20, 2007.
AOT A340-24-A5020.............. 02 April 12, 2007.
AOT A340-24A5021............... 02 December 20, 2007.
Mandatory Service Bulletin A330- 01 October 1, 2008.
24-3045.
Mandatory Service Bulletin A340- 01 October 1, 2008.
24-4058.
Mandatory Service Bulletin A340- 01 November 27, 2008.
24-5022.
------------------------------------------------------------------------
(The AOT document number, revision level, and date are indicated on only
page 1 of these documents.)

(1) The Director of the Federal Register approved the
incorporation by reference of the service information contained in
Table 8 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.

Table 8--New Material Incorporated by Reference
------------------------------------------------------------------------
Airbus-- Revision-- Dated--
------------------------------------------------------------------------
AOT A330-24A3044............... 03 May 26, 2008.
AOT A340-24A4057............... 03 December 20, 2007.
AOT A340-24A5021............... 02 December 20, 2007.
Mandatory Service Bulletin A330- 01 October 1, 2008.
24-3045.
Mandatory Service Bulletin A340- 01 October 1, 2008.
24-4058.
Mandatory Service Bulletin A340- 01 November 27, 2008.
24-5022.
------------------------------------------------------------------------

(2) The Director of the Federal Register previously approved the
incorporation by reference of the service information contained in
Table 9 of this AD on June 26, 2007 (72 FR 31973, June 11, 2007).

Table 9--Material Previously Incorporated by Reference
------------------------------------------------------------------------
Revision
Airbus all operators telex-- level-- Dated--
------------------------------------------------------------------------
A330-24A3042..................... 02 April 12, 2007.
A340-24A4056..................... 02 April 12, 2007.
A340-24A5020..................... 02 April 12, 2007.
------------------------------------------------------------------------

(3) 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, e-mail: airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(4) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(5) You may also review copies of the 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: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

Issued in Renton, Washington, June 23, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-16181 Filed 7-12-10; 8:45 am]
BILLING CODE 4910-13-P

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