Airworthiness Directives; Airbus Airplanes, 26716-26720 [2013-10908]

Download as PDF 26716 Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules EC635 is not type-certificated in the U.S. this proposed AD and placed it in the AD docket. Costs of Compliance We estimate that this proposed AD would affect 246 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. Modifying the injection tubes would require about 4.5 work-hours at an average labor rate of $85 per hour and required parts would cost about $900, for a cost of $1,282 per helicopter and a total cost to U.S. operators of $315,372. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by Reference, Safety. mstockstill on DSK4VPTVN1PROD with PROPOSALS Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; 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. We prepared an economic evaluation of the estimated costs to comply with VerDate Mar<15>2010 17:07 May 07, 2013 Jkt 229001 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 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 adding the following new airworthiness directive (AD): ■ Eurocopter Deutschland GmbH: Docket No. FAA–2013–0398; Directorate Identifier 2011–SW–065–AD. (a) Applicability This AD applies to Eurocopter Deutschland GmbH (ECD) Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters with a fire extinguishing system part number (P/N) L262M1808101, P/N L262M1812101, or P/N L262M1812102 installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as deformation of the fire extinguishing system injection tubes during an engine fire, which could result in impaired distribution of the fire extinguishing agent, failure of the fire extinguishing system to contain a fire, and subsequent loss of control of the helicopter. (c) Comments Due Date We must receive comments by July 8, 2013. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions (1) Within 30 days, modify each fire extinguishing system injection tube by removing and replacing a section of the tubing in accordance with the Accomplishment Instructions, paragraph 3.B., of Eurocopter EC135 Alert Service Bulletin No. EC135–26A–003, Revision 2, dated December 19, 2011. (2) Do not install an injection tube, P/N L262M1810101, P/N L262M1811801, or P/N L262M1809101, on any helicopter unless it has been modified as required by this AD. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 AD. Send your proposal to: Matt Wilbanks, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email matt.wilbanks@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (g) Additional Information (1) The subject of this AD is addressed in European Aviation Safety Agency AD No. 2011–0172, dated September 7, 2011. (h) Subject Joint Aircraft Service Component (JASC) Code: 2620: Extinguishing System. Issued in Fort Worth, Texas, on April 26, 2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2013–10911 Filed 5–7–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0365; Directorate Identifier 2012–NM–223–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede an existing airworthiness directive (AD) that applies to all Airbus Model A330– 200 and –300 series airplanes, and Model A340–200 and –300 series airplanes. The existing AD currently requires a repetitive inspection program on certain check valves in the hydraulic systems that includes, among other things, inspections for lock wire presence and integrity, traces of seepage or black deposits, proper torque, alignment of the check valve and manifold, installing new lock wire, and corrective actions if needed. Since we issued that AD, additional in-service reports of check valves loosening at lower flight cycle thresholds than previously reported have been received. This proposed AD would expand the applicability, reduce the compliance SUMMARY: E:\FR\FM\08MYP1.SGM 08MYP1 Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules time, change torque values of the check valve tightening, and require a repetitive inspection program for certain check valves in the hydraulic systems on airplanes that have had a certain modification embodied during production or in-service. We are proposing this AD to detect and correct such check valve loosening, which could result in hydraulic leaks, possibly leading to the loss of all three hydraulic systems and consequent loss of control of the airplane. DATES: We must receive comments on this proposed AD by June 24, 2013. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus SAS— Airworthiness Office—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 https://www.airbus.com. You may review copies of the 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. mstockstill on DSK4VPTVN1PROD with PROPOSALS 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 this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA VerDate Mar<15>2010 17:07 May 07, 2013 Jkt 229001 98057–3356; telephone 425–227–1138; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2013–0365; Directorate Identifier 2012–NM–223–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On November 16, 2009, we issued AD 2009–24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009). That AD required actions intended to address an unsafe condition on Airbus Model A330–200 and –300 series airplanes, and Model A340–200 and –300 series airplanes. Since we issued AD 2009–24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009), the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2012–0244R1, dated January 25, 2013 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: An A330 operator experienced a yellow hydraulic circuit low level due to a loose check valve, Part Number (P/N) CAR401. During the inspection on the other two hydraulic systems, the other three check valves P/N CAR401 were also found to be loose with their lock wire broken in two instances. Airbus A340 aeroplanes are also equipped with P/N CAR401 high pressure manifold check valves. Additional cases of P/N CAR401 check valve loosening have been reported on aeroplanes having accumulated more than 1,000 [total] flight cycles (FC). The check valve fitted on the Yellow hydraulic system is more affected, due to additional system cycles induced by cargo door operation. This condition, if not detected and corrected, could result in hydraulic leaks, possibly leading to the loss of all three hydraulic systems and consequent loss of control of the aeroplane. To address this unsafe condition, EASA issued Emergency AD 2009–0223–E [which PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 26717 corresponds to FAA AD 2009–24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009)] to require an inspection programme to detect any check valve loosening and if necessary, to apply the applicable corrective actions. EASA AD 2010–0145, which superseded EASA EAD 2009–0223–E retaining its requirements, was issued to expand the applicability to the newly certified models A330–223F and A330–243F. Prompted by further reported in-service events of check valve P/N CAR401 loosening before reaching the threshold of 700 FC, EASA AD 2011–0139, which superseded EASA AD 2010–0145, retaining its requirements, was issued to: —extend the requirement to identify the P/ N CAR401 check valves to all aeroplanes, and to —reduce the inspection threshold for aeroplanes fitted with check valve P/N CAR401, either installed in production through Airbus modification 54491, or installed in service through Airbus Service Bulletin (SB) A330–29–3101 or Airbus SB A340–29–4078. EASA AD 2012–0070, which superseded EASA AD 2011–0139, retaining its requirements, was issued to require an increased torque value of the check valve tightening and High Pressure (HP) manifold re-identification. Since EASA AD 2012–0070 was issued, additional in-service events have been reported on aeroplanes fitted with check valves on which the increased torque value had been applied. Based on those events, it has been concluded that the action to retorque the check valves with an increased value is not a satisfactory terminating action for addressing the issue of those check valves. For the reasons described above, this new [EASA] AD partially retains the requirements of EASA AD 2012–0070, which is superseded. Additionally, for aeroplanes equipped with P/N CAR401 on which the increased torque value has been applied, this new [EASA] AD requires repetitive inspections of the check valves and HP manifolds. Finally, this [EASA] AD also requires application of a lower torque value when a check valve P/N CAR401 is installed on an aeroplane. This [EASA] AD is considered to be an interim action and further AD action may follow. Note: the reporting and the torque value increase requirements for check valves P/N CAR401 of EASA AD 2012–0070 are no longer part of this new [EASA] AD. This proposed AD would expand the applicability to include Model A330– 200 freighter series airplanes, reduce the compliance time for initial inspection, and change torque values of the check valve tightening. The corrective actions include replacing seal assemblies, retorquing the check valve, and replacing the lock wire. You may obtain further information by examining the MCAI in the AD docket. E:\FR\FM\08MYP1.SGM 08MYP1 26718 Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules Relevant Service Information Airbus has issued the following service information. • Airbus Alert Operators Transmission A29L001–12, dated October 11, 2012. • Airbus Mandatory Service Bulletin A330–29–3111, Revision 02, dated June 23, 2011. • Airbus Mandatory Service Bulletin A340–29–4086, Revision 02, dated June 23, 2011. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. mstockstill on DSK4VPTVN1PROD with PROPOSALS Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 67 products of U.S. registry. The actions that are required by AD 2009–24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009), and retained in this proposed AD take about 8 work-hours per product, at an average labor rate of $85 per work hour. Based on these figures, the estimated cost of the currently required actions is $680 per product. We estimate that it would take about 2 work-hours per product to comply with the new basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $11,390, or $170 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. 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. VerDate Mar<15>2010 17:07 May 07, 2013 Jkt 229001 We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 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 airworthiness directive (AD) 2009–24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009), and adding the following new AD: ■ PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 Airbus: Docket No. FAA–2013–0365; Directorate Identifier 2012–NM–223–AD. (a) Comments Due Date We must receive comments by June 24, 2013. (b) Affected ADs This AD supersedes AD 2009–24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009). (c) Applicability This AD applies to Airbus Model A330– 201, –202, –203, –223, –223F, –243, –243F, –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. (d) Subject Air Transport Association (ATA) of America Code 29, Hydraulic Power. (e) Reason This AD was prompted by multiple reports of hydraulic line check valves loosening. We are issuing this AD to detect and correct such check valve loosening, which could result in hydraulic leaks, possibly leading to the loss of all three hydraulic systems and consequent loss of control of the airplane. (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Retained Actions This paragraph restates the requirements of paragraph (g) of AD 2009–24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009). Except for Model A330– 223F and A330–243F airplanes: Do the actions required by paragraphs (g)(1) and (g)(2) of this AD. (1) For airplanes that do not have Airbus Modification 54491 embodied in production, or Airbus Service Bulletin A330–29–3101 or Airbus Service Bulletin A340–29–4078 embodied in service: Within 100 flight cycles or 28 days after December 14, 2009 (the effective date of AD 2009–24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009)), whichever occurs first, inspect the check valves on the blue, green, and yellow hydraulic systems to identify their part numbers (P/Ns), in accordance with the instructions of Airbus All Operators Telex (AOT) A330–29A3111, Revision 1, dated October 8, 2009 (for Model A330–200 and -300 series airplanes); or AOT A340– 29A4086, Revision 1, dated October 8, 2009 (for Model A340–200 and –300 series airplanes). Accomplishment of the inspection required by paragraph (h) of this AD terminates the requirements of this paragraph. (i) If check valves having P/N CAR401 are installed on all three hydraulic systems, before further flight, do the actions specified in paragraph (g)(2)(i) of this AD. After accomplishing the actions required by paragraph (g)(2)(i) of this AD, do the actions specified in paragraphs (g)(2)(ii) and E:\FR\FM\08MYP1.SGM 08MYP1 mstockstill on DSK4VPTVN1PROD with PROPOSALS Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules (g)(2)(iii) of this AD at the applicable compliance times specified in those paragraphs. Accomplishment of the inspection required by paragraph (i) of this AD terminates the requirements of this paragraph. (ii) If check valves having P/N CAR401 are not installed on all three hydraulic systems, no further action is required by this paragraph until any check valve having P/N CAR400 is replaced with a check valve having P/N CAR401. If any check valve having P/N CAR400 is replaced by a check valve having P/N CAR401, before further flight, do the inspection specified in paragraph (g)(1) of this AD to determine if all three hydraulic systems are equipped with check valves having P/N CAR401. Accomplishment of the inspection required by paragraph (h) of this AD terminates the requirements of this paragraph. (2) For airplanes on which Airbus Modification 54491 was embodied in production, or Airbus Service Bulletin A330– 29–3101 or Airbus Service Bulletin A340– 29–4078 was embodied in service, do the actions specified in paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD. (i) Except as required by paragraph (g)(1)(i) of this AD, at the applicable times specified in paragraphs (g)(2)(i)(A) and (g)(2)(i)(B) of this AD, as applicable: Do the inspection program (detailed inspection of the lock wire for presence and integrity, a detailed inspection for traces of seepage or black deposits, and an inspection for proper torque) on yellow and blue high pressure manifolds, install new lock wires, and do all applicable corrective actions, in accordance with the instructions of paragraph 4.1.1 of Airbus AOT A330–29A3111, Revision 1, dated October 8, 2009 (for Model A330–200 and –300 series airplanes); or AOT A340– 29A4086, Revision 1, dated October 8, 2009 (for Model A340–200 and –300 series airplanes). Do all applicable corrective actions before further flight. Accomplishment of the inspection required by paragraph (h)(1) of this AD terminates the requirements of this paragraph. (A) For airplanes on which Airbus Modification 54491 has been embodied in production: At the later of the times specified in paragraphs (g)(2)(i)(A)(1) and (g)(2)(i)(A)(2) of this AD. (1) Before the accumulation of 1,000 total flight cycles since first flight but no earlier than the accumulation of 700 total flight cycles since first flight. (2) Within 100 flight cycles or 28 days after December 14, 2009 (the effective date of AD 2009–24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009)), whichever occurs first. (B) For airplanes on which Airbus Service Bulletin A330–29–3101 or A340–29–4078 was embodied in service: At the later of the times specified in paragraphs (g)(2)(i)(B)(1) and (g)(2)(i)(B)(2) of this AD. (1) Within 1,000 flight cycles since the embodiment of Airbus Service Bulletin A330–29–3101 or A340–29–4078 but no earlier than 700 flight cycles after the embodiment of Airbus Service Bulletin A330–29–3101 or A340–29–4078. (2) Within 100 flight cycles or 28 days after December 14, 2009 (the effective date of AD VerDate Mar<15>2010 17:07 May 07, 2013 Jkt 229001 2009–24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009)), whichever occurs first. (ii) Within 900 flight hours after accomplishment of paragraph (g)(2)(i) of this AD, do the inspection program (detailed inspection of the lock wire for presence and integrity, a detailed inspection for traces of seepage or black deposits, and an inspection for proper torque) and install a new lock wire on the green high pressure manifold; and do an inspection (detailed inspection for traces of seepage or black deposits, and detailed inspection to determine alignment of the check valve and manifold) on the yellow and blue high pressure manifolds, and do all applicable corrective actions; in accordance with the instructions of paragraph 4.1.2 of Airbus AOT A330–29A3111, Revision 1, dated October 8, 2009 (for Model A330–200 and –300 series airplanes); or AOT A340– 29A4086, Revision 1, dated October 8, 2009 (for Model A340–200 and –300 series airplanes). Do all applicable corrective actions before further flight. Accomplishment of the inspection program required by paragraph (i) of this AD terminates the requirements of this paragraph. (iii) Within 900 flight hours after accomplishment of paragraph (g)(2)(ii) of this AD, and thereafter at intervals not to exceed 900 flight hours, do the inspection program (detailed inspection for traces of seepage or black deposits, and detailed inspection to determine alignment of the check valve and manifold) on the green, yellow, and blue high pressure manifolds, and do all applicable corrective actions, in accordance with the instructions of paragraph 4.1.3 of Airbus AOT A330–29A3111, Revision 1, dated October 8, 2009 (for Model A330–200 and –300 series airplanes); or AOT A340– 29A4086, Revision 1, dated October 8, 2009 (for Model A340–200 and –300 series airplanes). Do all applicable corrective actions before further flight. Accomplishment of the inspection program required by paragraph (i) of this AD terminates the requirements of this paragraph. (h) New Inspection and Actions For airplanes equipped with check valves having P/N CAR400; and for airplanes equipped with check valves having P/N CAR401, except for airplanes on which Airbus Modification 201384 has been embodied during production, or on which Airbus Service Bulletin A330–29–3119 (for Model A330–200, –200F, and –300 series airplanes) or Airbus Service Bulletin A340– 29–4091 (for Model A340–200 and –300 series airplanes) has been embodied in service: Within 900 flight hours after the effective date of this AD, inspect the check valves on the blue, green, and yellow hydraulic systems to identify their part numbers, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–29–3111, Revision 02, dated June 23, 2011 (for Model A330–200, –200F and –300 series airplanes); or Airbus Mandatory Service Bulletin A340– 29–4086, Revision 02, dated June 23, 2011 (for Model A340–200 and –300 series airplanes). Accomplishment of the actions required by this paragraph terminates the PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 26719 requirements specified in paragraphs (g)(1) and (g)(1)(ii) of this AD. (1) If check valves having P/N CAR401 are installed on all three hydraulic systems: Before further flight, do the inspection program (detailed inspection for red mark presence and alignment integrity of the check valve and manifold, a detailed inspection for traces of seepage or black deposits, and an inspection for proper torque) on yellow and blue high pressure manifolds, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–29– 3111, Revision 02, dated June 23, 2011 (for Model A330–200, –200F, and –300 series airplanes); or Airbus Mandatory Service Bulletin A340–29–4086, Revision 02, dated June 23, 2011 (for Model A340–200 and –300 series airplanes). Accomplishment of the actions required by this paragraph terminates the requirements specified in paragraph (g)(2)(i) of this AD. (2) If check valves having P/N CAR401 are not installed on all three hydraulic systems, no further action is required by this paragraph until any check valve having P/N CAR400 is replaced with a check valve having P/N CAR401. If any check valve having P/N CAR400 is replaced by a check valve having P/N CAR401: Before further flight after such replacement, do the actions specified in paragraph (h) of this AD, to determine if all three hydraulic systems are equipped with check valves having P/N CAR401. If check valves having P/N CAR401 are installed on all three hydraulic systems: Before further flight, do the actions specified in paragraphs (h)(1) and (i) of this AD. (i) New Repetitive Inspection Program and Corrective Actions Within 900 flight hours after accomplishment of paragraph (h)(1) of this AD, do the inspection program (detailed inspection for red mark presence and alignment integrity of the check valve and manifold, a detailed inspection for traces of seepage or black deposits, and an inspection for proper torque) on the green, yellow, and blue system check valves, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–29– 3111, Revision 02, dated June 23, 2011 (for Model A330–200, –200F, and –300 series airplanes); or Airbus Mandatory Service Bulletin A340–29–4086, Revision 02, dated June 23, 2011 (for Model A340–200 and –300 series airplanes). Repeat the inspection program thereafter at intervals not to exceed 900 flight hours. Do all applicable corrective actions before further flight. Accomplishment of the actions required by this paragraph terminates the requirements specified in paragraphs (g)(1)(i), (g)(2)(ii), and (g)(2)(iii) of this AD. (j) New Repetitive Inspection for Certain Airplanes For airplanes equipped with check valves having P/N CAR401 and on which Airbus Modification 201384 has been embodied during production, or on which Airbus Service Bulletin A330–29–3119 (for Model A330–200, –200F, and –300 series airplanes); E:\FR\FM\08MYP1.SGM 08MYP1 26720 Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules or Airbus Service Bulletin A340–29–4091 (for Model A340–200 and –300 series airplanes) has been embodied in service: Within 1,000 flight hours after the effective date of this AD, do a general visual inspection of the green, yellow, and blue high pressure manifolds and check valves having P/N CAR401 for any sign of rotation of the check valve head, and for any signs of hydraulic fluid leakage or seepage (including black deposits), in accordance with the instructions of Airbus Alert Operators Transmission A29L001–12, dated October 11, 2012. Repeat the inspection thereafter at interval not to exceed 900 flight hours. (k) New Corrective Action for Certain Airplanes If, during any inspection required by paragraph (j) of this AD, any sign of rotation of the check valve head is found, or any sign of hydraulic fluid leakage or seepage (including black deposits) is found: Before further flight, do all applicable corrective actions, in accordance with the instructions of Airbus Alert Operators Transmission A29L001–12, dated October 11, 2012. (l) No Terminating Action Accomplishment of the corrective actions required by this AD does not constitute terminating action for the repetitive inspections required by this AD. mstockstill on DSK4VPTVN1PROD with PROPOSALS (m) Replacement Check Valve Torque Value As of the effective date of this AD, at each replacement of a check valve with a check valve having P/N CAR401, apply a torque of 141 to 143 newton metre (N.m) (103.98 to 105.45 pounds-foot (lbf.ft)) during installation. (n) Credit for Previous Actions (1) This paragraph restates the credit specified in paragraph (g)(2)(iv) of AD 2009– 24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009). This paragraph provides credit for actions required by paragraph (g)(2)(i) of this AD, if those actions were performed before December 14, 2009 (the effective date of AD 2009–24–09), using Airbus AOT A330–29A3111, dated September 2, 2009 (for Model A330–200 and –300 series airplanes); or AOT A340– 29A4086, dated September 2, 2009 (for Model A340–200 and –300 series airplanes). (2) This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Airbus AOT A330–29A3111, dated September 2, 2009; or Revision 1, dated October 8, 2009 (for Model A330–200 and –300 series airplanes); or AOT A340–29A4086, dated September 2, 2009; or Revision 1, dated October 8, 2009 (for Model A340–200 and –300 series airplanes). After the effective date of this AD all inspections and corrective actions, as required by paragraph (i) of this AD, must be accomplished in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–29–3111, Revision 02, dated June 23, 2011, or Airbus Mandatory Service Bulletin A340–29–4086, Revision 02, dated June 23, 2011; as applicable. VerDate Mar<15>2010 17:07 May 07, 2013 Jkt 229001 (o) No Reporting Although the service information specified in paragraphs (o)(1) through (o)(5) of this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement. (1) Airbus Alert Operators Transmission A29L001–12, dated October 11, 2012. (2) Airbus Mandatory Service Bulletin A330–29–3111, Revision 02, dated June 23, 2011. (3) Airbus Mandatory Service Bulletin A340–29–4086, Revision 02, dated June 23, 2011. (4) Airbus AOT A330–29A3111, Revision 1, dated October 8, 2009. (5) Airbus AOT A340–29A4086, Revision 1, dated October 8, 2009. (p) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, 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. AMOCs approved for AD 2009–24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009) are approved as AMOCs for the corresponding provisions of this AD, except AMOC ANM–116–11–172 is not approved as an AMOC for the corresponding provisions of this AD. (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. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information European Aviation Safety Agency Airworthiness Directive 2012–0244R1, dated January 25, 2013; and the following service information; for related information. (i) Airbus Alert Operators Transmission A29L001–12, dated October 11, 2012. (ii) Airbus Mandatory Service Bulletin A330–29–3111, Revision 02, dated June 23, 2011. (iii) Airbus Mandatory Service Bulletin A340–29–4086, Revision 02, dated June 23, 2011. PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 (iv) Airbus AOT A330–29A3111, Revision 1, dated October 8, 2009. (v) Airbus AOT A340–29A4086, Revision 1, dated October 8, 2009. (2) For service information identified in this AD, contact, Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330–A340@airbus.com; Internet https://www.airbus.com. You may review copies of the 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. Issued in Renton, Washington, on April 26, 2013. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–10908 Filed 5–7–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0366; Directorate Identifier 2011–NM–024–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede an existing airworthiness directive (AD) that applies to certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–300, 747–400, 747–400D, and 747SR series airplanes. The existing AD requires, for certain airplanes, inspection to determine the material of a main entry door (MED) reveal; repetitive inspections of certain reveals for cracking; a detailed inspection of certain reveals for a sharp edge and cracking; and corrective action if necessary. That AD also allows a certain replacement as an optional action for certain inspections of certain airplanes. Since we issued that AD, an operator reported a crack found in a 6061 machined aluminum one-piece corner reveal. This proposed AD would add, for certain airplanes, an inspection to determine material type of MED reveals, repetitive inspections for cracking of 6061 machined aluminum one-piece corner reveals, and replacement with 6061 machined aluminum two-piece corner reveals if necessary. This SUMMARY: E:\FR\FM\08MYP1.SGM 08MYP1

Agencies

[Federal Register Volume 78, Number 89 (Wednesday, May 8, 2013)]
[Proposed Rules]
[Pages 26716-26720]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-10908]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0365; Directorate Identifier 2012-NM-223-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to all Airbus Model A330-200 and -300 series 
airplanes, and Model A340-200 and -300 series airplanes. The existing 
AD currently requires a repetitive inspection program on certain check 
valves in the hydraulic systems that includes, among other things, 
inspections for lock wire presence and integrity, traces of seepage or 
black deposits, proper torque, alignment of the check valve and 
manifold, installing new lock wire, and corrective actions if needed. 
Since we issued that AD, additional in-service reports of check valves 
loosening at lower flight cycle thresholds than previously reported 
have been received. This proposed AD would expand the applicability, 
reduce the compliance

[[Page 26717]]

time, change torque values of the check valve tightening, and require a 
repetitive inspection program for certain check valves in the hydraulic 
systems on airplanes that have had a certain modification embodied 
during production or in-service. We are proposing this AD to detect and 
correct such check valve loosening, which could result in hydraulic 
leaks, possibly leading to the loss of all three hydraulic systems and 
consequent loss of control of the airplane.

DATES: We must receive comments on this proposed AD by June 24, 2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus SAS--Airworthiness Office--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 https://www.airbus.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at 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 this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: 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.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0365; 
Directorate Identifier 2012-NM-223-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On November 16, 2009, we issued AD 2009-24-09, Amendment 39-16068 
(74 FR 62208, November 27, 2009). That AD required actions intended to 
address an unsafe condition on Airbus Model A330-200 and -300 series 
airplanes, and Model A340-200 and -300 series airplanes.
    Since we issued AD 2009-24-09, Amendment 39-16068 (74 FR 62208, 
November 27, 2009), the European Aviation Safety Agency (EASA), which 
is the Technical Agent for the Member States of the European Community, 
has issued EASA Airworthiness Directive 2012-0244R1, dated January 25, 
2013 (referred to after this as ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI states:

    An A330 operator experienced a yellow hydraulic circuit low 
level due to a loose check valve, Part Number (P/N) CAR401. During 
the inspection on the other two hydraulic systems, the other three 
check valves P/N CAR401 were also found to be loose with their lock 
wire broken in two instances. Airbus A340 aeroplanes are also 
equipped with P/N CAR401 high pressure manifold check valves.
    Additional cases of P/N CAR401 check valve loosening have been 
reported on aeroplanes having accumulated more than 1,000 [total] 
flight cycles (FC). The check valve fitted on the Yellow hydraulic 
system is more affected, due to additional system cycles induced by 
cargo door operation.
    This condition, if not detected and corrected, could result in 
hydraulic leaks, possibly leading to the loss of all three hydraulic 
systems and consequent loss of control of the aeroplane.
    To address this unsafe condition, EASA issued Emergency AD 2009-
0223-E [which corresponds to FAA AD 2009-24-09, Amendment 39-16068 
(74 FR 62208, November 27, 2009)] to require an inspection programme 
to detect any check valve loosening and if necessary, to apply the 
applicable corrective actions.
    EASA AD 2010-0145, which superseded EASA EAD 2009-0223-E 
retaining its requirements, was issued to expand the applicability 
to the newly certified models A330-223F and A330-243F.
    Prompted by further reported in-service events of check valve P/
N CAR401 loosening before reaching the threshold of 700 FC, EASA AD 
2011-0139, which superseded EASA AD 2010-0145, retaining its 
requirements, was issued to:

--extend the requirement to identify the P/N CAR401 check valves to 
all aeroplanes, and to
--reduce the inspection threshold for aeroplanes fitted with check 
valve P/N CAR401, either installed in production through Airbus 
modification 54491, or installed in service through Airbus Service 
Bulletin (SB) A330-29-3101 or Airbus SB A340-29-4078.

    EASA AD 2012-0070, which superseded EASA AD 2011-0139, retaining 
its requirements, was issued to require an increased torque value of 
the check valve tightening and High Pressure (HP) manifold re-
identification.
    Since EASA AD 2012-0070 was issued, additional in-service events 
have been reported on aeroplanes fitted with check valves on which 
the increased torque value had been applied. Based on those events, 
it has been concluded that the action to re-torque the check valves 
with an increased value is not a satisfactory terminating action for 
addressing the issue of those check valves.
    For the reasons described above, this new [EASA] AD partially 
retains the requirements of EASA AD 2012-0070, which is superseded. 
Additionally, for aeroplanes equipped with P/N CAR401 on which the 
increased torque value has been applied, this new [EASA] AD requires 
repetitive inspections of the check valves and HP manifolds. 
Finally, this [EASA] AD also requires application of a lower torque 
value when a check valve P/N CAR401 is installed on an aeroplane.
    This [EASA] AD is considered to be an interim action and further 
AD action may follow.
    Note: the reporting and the torque value increase requirements 
for check valves P/N CAR401 of EASA AD 2012-0070 are no longer part 
of this new [EASA] AD.

This proposed AD would expand the applicability to include Model A330-
200 freighter series airplanes, reduce the compliance time for initial 
inspection, and change torque values of the check valve tightening. The 
corrective actions include replacing seal assemblies, re-torquing the 
check valve, and replacing the lock wire.
    You may obtain further information by examining the MCAI in the AD 
docket.

[[Page 26718]]

Relevant Service Information

    Airbus has issued the following service information.
     Airbus Alert Operators Transmission A29L001-12, dated 
October 11, 2012.
     Airbus Mandatory Service Bulletin A330-29-3111, Revision 
02, dated June 23, 2011.
     Airbus Mandatory Service Bulletin A340-29-4086, Revision 
02, dated June 23, 2011.

The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 67 products of U.S. registry.
    The actions that are required by AD 2009-24-09, Amendment 39-16068 
(74 FR 62208, November 27, 2009), and retained in this proposed AD take 
about 8 work-hours per product, at an average labor rate of $85 per 
work hour. Based on these figures, the estimated cost of the currently 
required actions is $680 per product.
    We estimate that it would take about 2 work-hours per product to 
comply with the new basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of the proposed AD on U.S. operators to be $11,390, or $170 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2009-24-09, Amendment 39-16068 (74 FR 62208, November 27, 2009), and 
adding the following new AD:

Airbus: Docket No. FAA-2013-0365; Directorate Identifier 2012-NM-
223-AD.

(a) Comments Due Date

    We must receive comments by June 24, 2013.

(b) Affected ADs

    This AD supersedes AD 2009-24-09, Amendment 39-16068 (74 FR 
62208, November 27, 2009).

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F, -243, -243F, -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.

(d) Subject

    Air Transport Association (ATA) of America Code 29, Hydraulic 
Power.

(e) Reason

    This AD was prompted by multiple reports of hydraulic line check 
valves loosening. We are issuing this AD to detect and correct such 
check valve loosening, which could result in hydraulic leaks, 
possibly leading to the loss of all three hydraulic systems and 
consequent loss of control of the airplane.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Retained Actions

    This paragraph restates the requirements of paragraph (g) of AD 
2009-24-09, Amendment 39-16068 (74 FR 62208, November 27, 2009). 
Except for Model A330-223F and A330-243F airplanes: Do the actions 
required by paragraphs (g)(1) and (g)(2) of this AD.
    (1) For airplanes that do not have Airbus Modification 54491 
embodied in production, or Airbus Service Bulletin A330-29-3101 or 
Airbus Service Bulletin A340-29-4078 embodied in service: Within 100 
flight cycles or 28 days after December 14, 2009 (the effective date 
of AD 2009-24-09, Amendment 39-16068 (74 FR 62208, November 27, 
2009)), whichever occurs first, inspect the check valves on the 
blue, green, and yellow hydraulic systems to identify their part 
numbers (P/Ns), in accordance with the instructions of Airbus All 
Operators Telex (AOT) A330-29A3111, Revision 1, dated October 8, 
2009 (for Model A330-200 and -300 series airplanes); or AOT A340-
29A4086, Revision 1, dated October 8, 2009 (for Model A340-200 and -
300 series airplanes). Accomplishment of the inspection required by 
paragraph (h) of this AD terminates the requirements of this 
paragraph.
    (i) If check valves having P/N CAR401 are installed on all three 
hydraulic systems, before further flight, do the actions specified 
in paragraph (g)(2)(i) of this AD. After accomplishing the actions 
required by paragraph (g)(2)(i) of this AD, do the actions specified 
in paragraphs (g)(2)(ii) and

[[Page 26719]]

(g)(2)(iii) of this AD at the applicable compliance times specified 
in those paragraphs. Accomplishment of the inspection required by 
paragraph (i) of this AD terminates the requirements of this 
paragraph.
    (ii) If check valves having P/N CAR401 are not installed on all 
three hydraulic systems, no further action is required by this 
paragraph until any check valve having P/N CAR400 is replaced with a 
check valve having P/N CAR401. If any check valve having P/N CAR400 
is replaced by a check valve having P/N CAR401, before further 
flight, do the inspection specified in paragraph (g)(1) of this AD 
to determine if all three hydraulic systems are equipped with check 
valves having P/N CAR401. Accomplishment of the inspection required 
by paragraph (h) of this AD terminates the requirements of this 
paragraph.
    (2) For airplanes on which Airbus Modification 54491 was 
embodied in production, or Airbus Service Bulletin A330-29-3101 or 
Airbus Service Bulletin A340-29-4078 was embodied in service, do the 
actions specified in paragraphs (g)(2)(i), (g)(2)(ii), and 
(g)(2)(iii) of this AD.
    (i) Except as required by paragraph (g)(1)(i) of this AD, at the 
applicable times specified in paragraphs (g)(2)(i)(A) and 
(g)(2)(i)(B) of this AD, as applicable: Do the inspection program 
(detailed inspection of the lock wire for presence and integrity, a 
detailed inspection for traces of seepage or black deposits, and an 
inspection for proper torque) on yellow and blue high pressure 
manifolds, install new lock wires, and do all applicable corrective 
actions, in accordance with the instructions of paragraph 4.1.1 of 
Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009 (for 
Model A330-200 and -300 series airplanes); or AOT A340-29A4086, 
Revision 1, dated October 8, 2009 (for Model A340-200 and -300 
series airplanes). Do all applicable corrective actions before 
further flight. Accomplishment of the inspection required by 
paragraph (h)(1) of this AD terminates the requirements of this 
paragraph.
    (A) For airplanes on which Airbus Modification 54491 has been 
embodied in production: At the later of the times specified in 
paragraphs (g)(2)(i)(A)(1) and (g)(2)(i)(A)(2) of this AD.
    (1) Before the accumulation of 1,000 total flight cycles since 
first flight but no earlier than the accumulation of 700 total 
flight cycles since first flight.
    (2) Within 100 flight cycles or 28 days after December 14, 2009 
(the effective date of AD 2009-24-09, Amendment 39-16068 (74 FR 
62208, November 27, 2009)), whichever occurs first.
    (B) For airplanes on which Airbus Service Bulletin A330-29-3101 
or A340-29-4078 was embodied in service: At the later of the times 
specified in paragraphs (g)(2)(i)(B)(1) and (g)(2)(i)(B)(2) of this 
AD.
    (1) Within 1,000 flight cycles since the embodiment of Airbus 
Service Bulletin A330-29-3101 or A340-29-4078 but no earlier than 
700 flight cycles after the embodiment of Airbus Service Bulletin 
A330-29-3101 or A340-29-4078.
    (2) Within 100 flight cycles or 28 days after December 14, 2009 
(the effective date of AD 2009-24-09, Amendment 39-16068 (74 FR 
62208, November 27, 2009)), whichever occurs first.
    (ii) Within 900 flight hours after accomplishment of paragraph 
(g)(2)(i) of this AD, do the inspection program (detailed inspection 
of the lock wire for presence and integrity, a detailed inspection 
for traces of seepage or black deposits, and an inspection for 
proper torque) and install a new lock wire on the green high 
pressure manifold; and do an inspection (detailed inspection for 
traces of seepage or black deposits, and detailed inspection to 
determine alignment of the check valve and manifold) on the yellow 
and blue high pressure manifolds, and do all applicable corrective 
actions; in accordance with the instructions of paragraph 4.1.2 of 
Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009 (for 
Model A330-200 and -300 series airplanes); or AOT A340-29A4086, 
Revision 1, dated October 8, 2009 (for Model A340-200 and -300 
series airplanes). Do all applicable corrective actions before 
further flight. Accomplishment of the inspection program required by 
paragraph (i) of this AD terminates the requirements of this 
paragraph.
    (iii) Within 900 flight hours after accomplishment of paragraph 
(g)(2)(ii) of this AD, and thereafter at intervals not to exceed 900 
flight hours, do the inspection program (detailed inspection for 
traces of seepage or black deposits, and detailed inspection to 
determine alignment of the check valve and manifold) on the green, 
yellow, and blue high pressure manifolds, and do all applicable 
corrective actions, in accordance with the instructions of paragraph 
4.1.3 of Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009 
(for Model A330-200 and -300 series airplanes); or AOT A340-29A4086, 
Revision 1, dated October 8, 2009 (for Model A340-200 and -300 
series airplanes). Do all applicable corrective actions before 
further flight. Accomplishment of the inspection program required by 
paragraph (i) of this AD terminates the requirements of this 
paragraph.

(h) New Inspection and Actions

    For airplanes equipped with check valves having P/N CAR400; and 
for airplanes equipped with check valves having P/N CAR401, except 
for airplanes on which Airbus Modification 201384 has been embodied 
during production, or on which Airbus Service Bulletin A330-29-3119 
(for Model A330-200, -200F, and -300 series airplanes) or Airbus 
Service Bulletin A340-29-4091 (for Model A340-200 and -300 series 
airplanes) has been embodied in service: Within 900 flight hours 
after the effective date of this AD, inspect the check valves on the 
blue, green, and yellow hydraulic systems to identify their part 
numbers, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A330-29-3111, Revision 02, dated 
June 23, 2011 (for Model A330-200, -200F and -300 series airplanes); 
or Airbus Mandatory Service Bulletin A340-29-4086, Revision 02, 
dated June 23, 2011 (for Model A340-200 and -300 series airplanes). 
Accomplishment of the actions required by this paragraph terminates 
the requirements specified in paragraphs (g)(1) and (g)(1)(ii) of 
this AD.
    (1) If check valves having P/N CAR401 are installed on all three 
hydraulic systems: Before further flight, do the inspection program 
(detailed inspection for red mark presence and alignment integrity 
of the check valve and manifold, a detailed inspection for traces of 
seepage or black deposits, and an inspection for proper torque) on 
yellow and blue high pressure manifolds, and do all applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-29-3111, 
Revision 02, dated June 23, 2011 (for Model A330-200, -200F, and -
300 series airplanes); or Airbus Mandatory Service Bulletin A340-29-
4086, Revision 02, dated June 23, 2011 (for Model A340-200 and -300 
series airplanes). Accomplishment of the actions required by this 
paragraph terminates the requirements specified in paragraph 
(g)(2)(i) of this AD.
    (2) If check valves having P/N CAR401 are not installed on all 
three hydraulic systems, no further action is required by this 
paragraph until any check valve having P/N CAR400 is replaced with a 
check valve having P/N CAR401. If any check valve having P/N CAR400 
is replaced by a check valve having P/N CAR401: Before further 
flight after such replacement, do the actions specified in paragraph 
(h) of this AD, to determine if all three hydraulic systems are 
equipped with check valves having P/N CAR401. If check valves having 
P/N CAR401 are installed on all three hydraulic systems: Before 
further flight, do the actions specified in paragraphs (h)(1) and 
(i) of this AD.

(i) New Repetitive Inspection Program and Corrective Actions

    Within 900 flight hours after accomplishment of paragraph (h)(1) 
of this AD, do the inspection program (detailed inspection for red 
mark presence and alignment integrity of the check valve and 
manifold, a detailed inspection for traces of seepage or black 
deposits, and an inspection for proper torque) on the green, yellow, 
and blue system check valves, and do all applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A330-29-3111, Revision 02, dated 
June 23, 2011 (for Model A330-200, -200F, and -300 series 
airplanes); or Airbus Mandatory Service Bulletin A340-29-4086, 
Revision 02, dated June 23, 2011 (for Model A340-200 and -300 series 
airplanes). Repeat the inspection program thereafter at intervals 
not to exceed 900 flight hours. Do all applicable corrective actions 
before further flight. Accomplishment of the actions required by 
this paragraph terminates the requirements specified in paragraphs 
(g)(1)(i), (g)(2)(ii), and (g)(2)(iii) of this AD.

(j) New Repetitive Inspection for Certain Airplanes

    For airplanes equipped with check valves having P/N CAR401 and 
on which Airbus Modification 201384 has been embodied during 
production, or on which Airbus Service Bulletin A330-29-3119 (for 
Model A330-200, -200F, and -300 series airplanes);

[[Page 26720]]

or Airbus Service Bulletin A340-29-4091 (for Model A340-200 and -300 
series airplanes) has been embodied in service: Within 1,000 flight 
hours after the effective date of this AD, do a general visual 
inspection of the green, yellow, and blue high pressure manifolds 
and check valves having P/N CAR401 for any sign of rotation of the 
check valve head, and for any signs of hydraulic fluid leakage or 
seepage (including black deposits), in accordance with the 
instructions of Airbus Alert Operators Transmission A29L001-12, 
dated October 11, 2012. Repeat the inspection thereafter at interval 
not to exceed 900 flight hours.

(k) New Corrective Action for Certain Airplanes

    If, during any inspection required by paragraph (j) of this AD, 
any sign of rotation of the check valve head is found, or any sign 
of hydraulic fluid leakage or seepage (including black deposits) is 
found: Before further flight, do all applicable corrective actions, 
in accordance with the instructions of Airbus Alert Operators 
Transmission A29L001-12, dated October 11, 2012.

(l) No Terminating Action

    Accomplishment of the corrective actions required by this AD 
does not constitute terminating action for the repetitive 
inspections required by this AD.

(m) Replacement Check Valve Torque Value

    As of the effective date of this AD, at each replacement of a 
check valve with a check valve having P/N CAR401, apply a torque of 
141 to 143 newton metre (N.m) (103.98 to 105.45 pounds-foot 
(lbf.ft)) during installation.

(n) Credit for Previous Actions

    (1) This paragraph restates the credit specified in paragraph 
(g)(2)(iv) of AD 2009-24-09, Amendment 39-16068 (74 FR 62208, 
November 27, 2009). This paragraph provides credit for actions 
required by paragraph (g)(2)(i) of this AD, if those actions were 
performed before December 14, 2009 (the effective date of AD 2009-
24-09), using Airbus AOT A330-29A3111, dated September 2, 2009 (for 
Model A330-200 and -300 series airplanes); or AOT A340-29A4086, 
dated September 2, 2009 (for Model A340-200 and -300 series 
airplanes).
    (2) This paragraph provides credit for actions required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using Airbus AOT A330-29A3111, dated 
September 2, 2009; or Revision 1, dated October 8, 2009 (for Model 
A330-200 and -300 series airplanes); or AOT A340-29A4086, dated 
September 2, 2009; or Revision 1, dated October 8, 2009 (for Model 
A340-200 and -300 series airplanes). After the effective date of 
this AD all inspections and corrective actions, as required by 
paragraph (i) of this AD, must be accomplished in accordance with 
the Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-29-3111, Revision 02, dated June 23, 2011, or Airbus Mandatory 
Service Bulletin A340-29-4086, Revision 02, dated June 23, 2011; as 
applicable.

(o) No Reporting

    Although the service information specified in paragraphs (o)(1) 
through (o)(5) of this AD specifies to submit certain information to 
the manufacturer, this AD does not include that requirement.
    (1) Airbus Alert Operators Transmission A29L001-12, dated 
October 11, 2012.
    (2) Airbus Mandatory Service Bulletin A330-29-3111, Revision 02, 
dated June 23, 2011.
    (3) Airbus Mandatory Service Bulletin A340-29-4086, Revision 02, 
dated June 23, 2011.
    (4) Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009.
    (5) Airbus AOT A340-29A4086, Revision 1, dated October 8, 2009.

(p) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, 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. AMOCs 
approved for AD 2009-24-09, Amendment 39-16068 (74 FR 62208, 
November 27, 2009) are approved as AMOCs for the corresponding 
provisions of this AD, except AMOC ANM-116-11-172 is not approved as 
an AMOC for the corresponding provisions of this AD.
    (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.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
European Aviation Safety Agency Airworthiness Directive 2012-0244R1, 
dated January 25, 2013; and the following service information; for 
related information.
    (i) Airbus Alert Operators Transmission A29L001-12, dated 
October 11, 2012.
    (ii) Airbus Mandatory Service Bulletin A330-29-3111, Revision 
02, dated June 23, 2011.
    (iii) Airbus Mandatory Service Bulletin A340-29-4086, Revision 
02, dated June 23, 2011.
    (iv) Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009.
    (v) Airbus AOT A340-29A4086, Revision 1, dated October 8, 2009.
    (2) For service information identified in this AD, contact, 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
Internet https://www.airbus.com. You may review copies of the 
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.

    Issued in Renton, Washington, on April 26, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-10908 Filed 5-7-13; 8:45 am]
BILLING CODE 4910-13-P

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