Airworthiness Directives; Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes, 65897-65901 [E7-22921]

Download as PDF Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules § 786.112 Maintaining records. Persons applying for benefits under this program must maintain records and accounts to document all eligibility requirements specified herein and must keep such records and accounts for 3 years after the date of payment to their dairy operations under this program. Destruction of the records after such date is at the risk of the party required, by this part, to keep the records. § 786.113 liability. Refunds; joint and several (a) Excess payments, payments provided as the result of erroneous information provided by any person, or payments resulting from a failure to meet any requirement or condition for payment under the application or this part, must be refunded to FSA. (b) A refund required under this section is due with interest determined in accordance with paragraph (d) of this section and late payment charges as provided in 7 CFR part 792. Notwithstanding any other regulation, interest will be due from the date of the disbursement to the producer or other recipient of the funds. (c) Persons signing a dairy operation’s application as having an interest in the operation will be jointly and severally liable for any refund and related charges found to be due under this section. (d) In the event FSA determines a participant owes a refund under this part, FSA will charge program interest from the date of disbursement of the erroneous payment. Such interest will accrue at the rate that the United States Department of the Treasury charges FSA for funds plus additional charges as deemed appropriate by the Administrator or provided for by regulation or statute. (e) The debt collection provisions of part 792 of this chapter applies to this part except as is otherwise provided in this part. ebenthall on PROD1PC69 with PROPOSALS § 786.114 Miscellaneous provisions. (a) Payments or any portion thereof due under this part must be made without regard to questions of title under State law and without regard to any claim or lien against the livestock, or proceeds thereof, in favor of the owner or any other creditor except agencies and instrumentalities of the U.S. Government. (b) Any producer entitled to any payment under this part may assign any payments in accordance with the provisions of 7 CFR part 1404. § 786.115 Termination of program. This program will be terminated after payment has been made to those VerDate Aug<31>2005 15:37 Nov 23, 2007 Jkt 214001 applicants certified as eligible pursuant to the application period established in § 786.104. All eligibility determinations will be final except as otherwise determined by the Deputy Administrator. Any claim for payment may be denied once the allowed funds are expended, irrespective of any other provision of this part. Signed at Washington, DC, on November 19, 2007. Glen L. Keppy, Acting Administrator, Farm Service Agency. [FR Doc. E7–22904 Filed 11–23–07; 8:45 am] BILLING CODE 3410–05–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0229; Directorate Identifier 2007–NM–042–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330–200, A330–300, A340–200, and A340–300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all Airbus Model A330–200, A330–300, A340–200, and A340–300 series airplanes. The existing AD currently requires a revision of the airplane flight manual to include procedures for a pre-flight elevator check before each flight, repetitive inspections for cracks of the attachment lugs of the mode selector valve position transducers on the elevator servo controls, and corrective actions if necessary. This proposed AD would retain the existing requirements, reduce the applicability of the existing AD, and add terminating actions. For certain airplanes, this proposed AD would require upgrading the flight control primary computers. This proposed AD results from cracks of the transducer body at its attachment lugs. We are proposing this AD to ensure proper functioning of the elevator surfaces, and to prevent cracking of the attachment lugs, which could result in partial loss of elevator function and consequent reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by December 26, 2007. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 65897 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 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. ADDRESSES: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket 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: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2797; 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–2007–0229; Directorate Identifier 2007-NM–042-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 because of 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 E:\FR\FM\26NOP1.SGM 26NOP1 65898 Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules substantive verbal contact we receive about this proposed AD. Discussion On February 2, 2004, we issued AD 2004–03–24, amendment 39–13468 (69 FR 6549, February 11, 2004), for all Airbus Model A330–200, A330–300, A340–200, and A340–300 series airplanes. That AD requires a revision of the airplane flight manual to include procedures for a pre-flight elevator check before each flight, repetitive inspections for cracks of the attachment lugs of the mode selector valve position transducers on the elevator servo controls, and corrective actions if necessary. That AD resulted from a report of cracks of the transducer body at its attachment lugs. We issued that AD to ensure proper functioning of the elevator surfaces, and to detect and correct cracking of the attachment lugs, which could result in partial loss of elevator function and consequent reduced controllability of the airplane. Actions Since Existing AD Was Issued The preamble to AD 2004–03–24 explains that we consider the requirements ‘‘interim action’’ and were considering further rulemaking. We now have determined that further rulemaking is indeed necessary, and this proposed AD follows from that determination. Relevant Service Information The following service information has been issued: SERVICE INFORMATION Description Airbus Service Bulletin A330–27–3128, dated May 3, 2005 (for Model A330–200 and –300 series airplanes); and Airbus Service Bulletin A340–27–4129, dated May 3, 2005 (for Model A340–200 and –300 series airplanes). Airbus Service Bulletin A340–27–4131, dated February 21, 2005 (for Model A340–200 and –300 series airplanes). Goodrich Actuation Systems Service Bulletin SC4800–27–16, Revision 3, dated May 19, 2006. TRW Service Bulletin SC4800–27–34–09, Revision 1, dated November 9, 2001. ebenthall on PROD1PC69 with PROPOSALS Service information Inspection of the elevator servo control to determine whether part number (P/N) SC4800–7A or –9 is installed, and modification of the four elevator servo controls if necessary. Airbus Service Bulletin A340–27– 4131 refers to Airbus Vendor Service Bulletins LA2K0–27–017 and LA2K1– 27–009, both dated January 25, 2005, as additional sources of service information for upgrading the FCPCs. Airbus Service Bulletins A330–27– 3128 and A340–27–4129 refer to Goodrich Actuation Systems Service Bulletin SC4800–27–16, Revision 3, dated May 19, 2006, as an additional source of service information for accomplishing the modification of the four elevator servo controls. Accomplishing the actions specified in Airbus Service Bulletin A330–27– 3128 or A340–27–4129, as applicable, Goodrich Actuation Systems Service Bulletin SC4800–27–16, and TRW Service Bulletin SC4800–27–34–09, if required, would cancel the requirements of AD 2004–03–24. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, mandated the service information and issued airworthiness directive 2007–0011, dated January 9, 2007, to ensure the continued airworthiness of these airplanes in the European Union. VerDate Aug<31>2005 15:37 Nov 23, 2007 Jkt 214001 Upgrade of flight control primary computers (FCPCs). Inspection of the elevator servo controls, P/N SC4800–10 and SC4800–11, to determine the serial number (S/N) installed, and replacement of the mode selector valve position transducer (MVT) of the elevator servo controls with a new MVT if necessary. Replacement of the eye-end equipped with a self-lubricated bearing with a new eye-end equipped with a roller bearing, greasing of the new eye-end, and reidentification of the servo control. These actions must be done prior to or concurrently with the actions specified in Goodrich Actuation Systems Service Bulletin SC4800–27–16. FAA’s Determination and Requirements of the Proposed AD These airplanes are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. As described in FAA Order 8100.14A, ‘‘Interim Procedures for Working with the European Community on Airworthiness Certification and Continued Airworthiness,’’ dated August 12, 2005, the EASA has kept the FAA informed of the situation described above. We have examined the EASA’s findings, evaluated all pertinent information, and determined that AD action is necessary for airplanes of this type design that are certificated for operation in the United States. This proposed AD would supersede AD 2004–03–24 and would retain the requirements of the existing AD. This proposed AD also would require accomplishing the actions specified in service information described previously. Accomplishing the actions specified in Airbus Service Bulletin A330–27–3128 or A340–27–4129, as applicable, Goodrich Actuation Systems Service Bulletin SC4800–27–16, and TRW Service Bulletin SC4800–27–34– PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 09, if required, would constitute terminating action for the retained requirements of 2004–03–24. This proposed AD also would remove airplanes from the applicability of the existing AD. Changes to Existing AD This proposed AD would retain all requirements of AD 2004–03–24. Since AD 2004–03–24 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table: REVISED PARAGRAPH IDENTIFIERS Requirement in AD 2004–03–24 Paragraph Paragraph Paragraph Paragraph Paragraph Paragraph (a) ...................... (b) ...................... (c) ...................... (d) ...................... (e) ...................... (f) ....................... Corresponding requirement in this proposed AD Paragraph Paragraph Paragraph Paragraph Paragraph Paragraph (f). (g). (h). (i). (j). (k). AD 2004–03–24 affects all Airbus Model A330–200, A330–300, A340–200, and A340–300 series airplanes. The applicability of this proposed AD would E:\FR\FM\26NOP1.SGM 26NOP1 65899 Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules exclude those airplanes on which a reinforced mode selector valve has been installed, which parallels the applicability of EASA airworthiness directive 2007–0011. Costs of Compliance The following table provides the estimated costs for U.S. operators of the affected Model A330–200 and A330– 300 series airplanes to comply with this proposed AD. ESTIMATED COSTS Action Work hours Average labor rate per hour AFM revision (required by AD 2004–03–24) ...... Inspection (required by AD 2004–03–24) ........... 1 4 $80 $80 Inspection (new proposed action) ....................... 1 $80 Currently, there are no affected Model A340–200 and A340–300 series airplanes on the U.S. Register. However, if an affected airplane is imported and placed on the U.S. Register in the future, the proposed upgrade of the FCPCs would take about 2 work hours, at an average labor rate of $80 per work hour. The manufacturer states that it would supply required parts to the operators at no cost. Based on these figures, we estimate the cost of this proposed AD for Model A340–200 and A340–300 series airplanes to be $160 per airplane. 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 Cost per airplane Number of U.S.-registered airplanes $80 ............................... $320, per inspection cycle. $80 ............................... that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have 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 that the 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); 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 proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. 29 29 29 Fleet cost $2,320. $9,280, per inspection cycle. $2,320. 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 Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–13468 (69 FR 6549, February 11, 2004) and adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2007–0229; Directorate Identifier 2007–NM–042–AD. Comments Due Date (a) The FAA must receive comments on this AD action by December 26, 2007. Affected ADs (b) This AD supersedes AD 2004–03–24. Applicability (c) This AD applies to the airplanes identified in Table 1 of this AD, certificated in any category. TABLE 1.—APPLICABILITY Excluding those airplanes on which any of the following— Has been installed— A330–200, A330–300, A340–200, and A340–300 series airplanes. ebenthall on PROD1PC69 with PROPOSALS Airbus model— Airbus modification 50394, 52195, 53969, or 54833 .................................................... In production. Airbus Service Bulletin A330–27–3128, dated May 3, 2005 ........................................ Airbus Service Bulletin A340–27–4129, dated May 3, 2005 ........................................ Airbus Service Bulletin A330–27–3136, Revision 01, dated July 19, 2006 ................. Airbus Service Bulletin A340–27–4135, dated January 12, 2006 ................................ Goodrich Actuation Systems Service Bulletin SC4800–27–16, Revision 03, dated May 19, 2006. In In In In In VerDate Aug<31>2005 15:37 Nov 23, 2007 Jkt 214001 PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 E:\FR\FM\26NOP1.SGM 26NOP1 service. service. service. service. service. 65900 Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules Unsafe Condition (d) This AD results from a report of cracks of the transducer body at its attachment lugs. We are issuing this AD to ensure proper functioning of the elevator surfaces, and to prevent cracking of the attachment lugs, which could result in partial loss of elevator function and consequent reduced controllability of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Requirements of AD 2004–03–24 Airplane Flight Manual (AFM) Revision (f) Within 30 days after February 26, 2004 (the effective date of AD 2004–03–24), revise the Limitations section of the AFM to include a pre-flight elevator check, by including the following language. This may be done by inserting a copy of this AD into the applicable AFM. Thereafter perform the preflight check before every flight in accordance with the procedure. ebenthall on PROD1PC69 with PROPOSALS Prior or During Taxi ‘‘FLIGHT CONTROLS—CHECK 1. AT A CONVENIENT STAGE, PRIOR TO OR DURING TAXI, AND BEFORE ARMING THE AUTOBRAKE, THE PF SILENTLY APPLIES FULL LONGITUDINAL AND LATERAL SIDESTICK DEFLECTION. ON THE F/CTL PAGE, THE PNF CHECKS FULL TRAVEL OF ALL ELEVATORS AND ALL AILERONS, AND THE CORRECT DEFLECTION AND RETRACTION OF ALL SPOILERS. THE PNF CALLS OUT ‘‘FULL UP,’’ ‘‘FULL DOWN,’’ ‘‘NEUTRAL,’’ ‘‘FULL LEFT,’’ ‘‘FULL RIGHT,’’ ‘‘NEUTRAL,’’ AS EACH FULL TRAVEL/NEUTRAL POSITION IS REACHED. THE PF SILENTLY CHECKS THAT THE PNF CALLS ARE IN ACCORDANCE WITH THE SIDESTICK ORDER. NOTE: IN ORDER TO REACH FULL TRAVEL, FULL SIDESTICK MUST BE HELD FOR A SUFFICIENT PERIOD OF TIME. 2. THE PF PRESSES THE PEDAL DISC PUSHBUTTON ON THE NOSEWHEEL TILLER, AND SILENTLY APPLIES FULL LEFT RUDDER, FULL RIGHT RUDDER, AND NEUTRAL. THE PNF CALLS OUT ‘‘FULL LEFT,’’ ‘‘FULL RIGHT,’’ ‘‘NEUTRAL,’’ AS EACH FULL TRAVEL/NEUTRAL POSITION IS REACHED. 3. THE PNF APPLIES FULL LONGITUDINAL AND LATERAL SIDESTICK DEFLECTION, AND SILENTLY CHECKS FULL TRAVEL AND CORRECT SENSE OF VerDate Aug<31>2005 15:37 Nov 23, 2007 Jkt 214001 ALL ELEVATORS AND ALL AILERONS, AND CORRECT DEFLECTION AND RETRACTION OF ALL SPOILERS, ON THE ECAM F/CTL PAGE.’’ Note 1: Full and complete elevator travel (position commanded) can be verified on the ECAM Flight Control Page. A determination of ‘‘correct sense’’ should include verification that there is complete and full motion of the sidesticks without binding. (g) If any pre-flight check required by paragraph (f) of this AD reveals improper function of the elevator: Before further flight, perform the inspections required by paragraph (h) of this AD. Inspections (h) At the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, except as required by paragraph (g) of this AD: Perform a dye penetrant inspection of the attachment lugs of the mode selector valve position transducers on each elevator servo control installed at damping positions 3CS1 and 3CS2. Do the inspection in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–27A3115 or A340–27A4119, both Revision 02, both dated December 30, 2003, as applicable (in paragraphs (h) through (k) of this AD, referred to as ‘‘the service bulletin’’). An inspection that is done before February 26, 2004, is acceptable for compliance with the initial inspection requirement of this paragraph, if the inspection is done in accordance with any of the following Airbus All Operators Telexes (AOTs): AOT A330– 27A3115 or A340–27A4119, dated September 11, 2003, or Revision 01 of each AOT dated September 25, 2003; as applicable. Repeat the inspection thereafter at intervals not to exceed 350 flight cycles, until the applicable actions required by paragraphs (m) and (n) of this AD have been done. (1) If the age of the servo control from the date of its first installation on the airplane can be positively determined: Do the inspection before the accumulation of 1,000 total flight cycles on the elevator servo control, or within 350 flight cycles on the servo control after February 26, 2004, whichever occurs later. (2) If the age of the servo control from the date of its first installation on the airplane cannot be positively determined, do the inspection within 350 flight cycles on the servo control after February 26, 2004. Note 2: The service bulletin refers to Goodrich Actuation Systems Inspection Service Bulletin SC4800–27–13 as an additional source of service information for the inspection. PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Corrective Actions (i) If any crack is found during any inspection required by paragraph (h) of this AD: Before further flight, replace either the transducer or servo control with a new part, in accordance with the service bulletin. Reporting Requirement (j) If any crack is found during any inspection required by paragraph (h) of this AD: Submit a report in accordance with the service bulletin at the applicable time(s) specified in paragraphs (j)(1) and (j)(2) of this AD: Submit reports to Airbus Customer Services, Engineering and Technical Support, Attention: J. Laurent, SEE53, fax +33/ (0)5.61.93.44.25, Sita Code TLSBQ7X. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. (1) For an initial inspection done before February 26, 2004: Submit the report within 30 days after February 26, 2004. (2) For an inspection done after February 26, 2004: Submit the report within 30 days after the inspection. Parts Installation (k) As of February 26, 2004, no person may install the following part on any airplane: A transducer, or a transducer fitted on an elevator servo control, in the operator’s inventory before September 25, 2003, unless that transducer has been inspected in accordance with the service bulletin and is crack free. New Requirements of This AD Upgrade Flight Control Primary Computers (FCPCs) (l) For Model A340–200 and –300 series airplanes: Within 2 months after the effective date of this AD, upgrade the three FCPCs in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340– 27–4131, dated February 21, 2005. Note 3: Airbus Service Bulletin A340–27– 4131 refers to Airbus Vendor Service Bulletins LA2K0–27–017 and LA2K1–27– 009, both dated January 25, 2005, as additional sources of service information for upgrading the FCPCs. Terminating Actions (m) Within 17 months after the effective date of this AD, do the actions specified in Table 2 of this AD. E:\FR\FM\26NOP1.SGM 26NOP1 Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules 65901 TABLE 2.—TERMINATING ACTIONS Inspect— (1) The elevator servo control to determine whether part number (P/N) SC4800–7A or –9 is installed. (2) The elevator servo controls, P/N SC4800–10 and SC4800–11 to determine the serial number (S/N) installed. In accordance with the accomplishment instructions of airbus service bulletin— A330–27–3128, dated May 3, 2005 (for Model A330–200 and –300 series airplanes); or A340– 27–4129, dated May 3, 2005 (for Model A340– 200 and –300 series airplanes); as applicable. None .................................. And if— Then— P/N SC4800–7A or –9 is found installed. Modify the four elevator servo controls. The Accomplishment Instructions of the applicable Airbus service bulletin. S/N 2324 or below is found installed. Replace the mode selector valve position transducer (MVT) of the elevator servo controls with a new MVT. Paragraphs 3.(2) and 3.B.(2) of the Accomplishment Instructions of Goodrich Actuation Systems Service Bulletin SC4800–27–16, Revision 3, dated May 19, 2006. Note 4: Airbus Service Bulletins A330–27– 3128 and A340–27–4129 refer to Goodrich Actuation Systems Service Bulletin SC4800– 27–16, Revision 3, dated May 19, 2006, as an additional source of service information for accomplishing the modification of the four elevator servo controls. (n) Prior to or concurrently with the replacement, if required, specified in paragraph (m)(2) of this AD, replace the eyeend equipped with a self-lubricated bearing with a new eye-end equipped with a roller bearing, grease the new eye-end, and reidentify the servo control, in accordance with paragraph 2.A. of the Accomplishment Instructions of TRW Service Bulletin SC4800–27–34–09, Revision 1, dated November 9, 2001. (o) Accomplishing all of the applicable actions required by paragraphs (m) and (n) of this AD constitutes terminating action for paragraphs (f) through (k) of this AD. Issued in Renton, Washington, on November 13, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–22921 Filed 11–23–07; 8:45 am] Alternative Methods of Compliance (AMOCs) AGENCY: ebenthall on PROD1PC69 with PROPOSALS (p)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Related Information (q) EASA airworthiness directive 2007– 0011, dated January 9, 2007, also addresses the subject of this AD. VerDate Aug<31>2005 15:37 Nov 23, 2007 Jkt 214001 In accordance with— BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0226; Directorate Identifier 2007–NM–187–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–300, –400, and –500 Series Airplanes which could result in rapid decompression of the airplane. DATES: We must receive comments on this proposed AD by January 10, 2008. 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 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). Examining the AD Docket SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 737–300, –400, and –500 series airplanes. This proposed AD would require repetitive inspections for cracking of the body buttock line (BBL) 0.07 floor beam between body station (BS) 651 and BS 676 and between BS 698 and BS 717, and related investigative and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This proposed AD results from reports of cracking in the BBL 0.07 floor beam. We are proposing this AD to prevent failure of the main deck floor beams at certain body stations due to fatigue cracking, You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket 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: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 E:\FR\FM\26NOP1.SGM 26NOP1

Agencies

[Federal Register Volume 72, Number 226 (Monday, November 26, 2007)]
[Proposed Rules]
[Pages 65897-65901]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-22921]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0229; Directorate Identifier 2007-NM-042-AD]
RIN 2120-AA64


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

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to all Airbus Model A330-200, A330-300, 
A340-200, and A340-300 series airplanes. The existing AD currently 
requires a revision of the airplane flight manual to include procedures 
for a pre-flight elevator check before each flight, repetitive 
inspections for cracks of the attachment lugs of the mode selector 
valve position transducers on the elevator servo controls, and 
corrective actions if necessary. This proposed AD would retain the 
existing requirements, reduce the applicability of the existing AD, and 
add terminating actions. For certain airplanes, this proposed AD would 
require upgrading the flight control primary computers. This proposed 
AD results from cracks of the transducer body at its attachment lugs. 
We are proposing this AD to ensure proper functioning of the elevator 
surfaces, and to prevent cracking of the attachment lugs, which could 
result in partial loss of elevator function and consequent reduced 
controllability of the airplane.

DATES: We must receive comments on this proposed AD by December 26, 
2007.

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 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Airbus, 1 
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket 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: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2797; 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-2007-0229; 
Directorate Identifier 2007-NM-042-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 because of 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

[[Page 65898]]

substantive verbal contact we receive about this proposed AD.

Discussion

    On February 2, 2004, we issued AD 2004-03-24, amendment 39-13468 
(69 FR 6549, February 11, 2004), for all Airbus Model A330-200, A330-
300, A340-200, and A340-300 series airplanes. That AD requires a 
revision of the airplane flight manual to include procedures for a pre-
flight elevator check before each flight, repetitive inspections for 
cracks of the attachment lugs of the mode selector valve position 
transducers on the elevator servo controls, and corrective actions if 
necessary. That AD resulted from a report of cracks of the transducer 
body at its attachment lugs. We issued that AD to ensure proper 
functioning of the elevator surfaces, and to detect and correct 
cracking of the attachment lugs, which could result in partial loss of 
elevator function and consequent reduced controllability of the 
airplane.

Actions Since Existing AD Was Issued

    The preamble to AD 2004-03-24 explains that we consider the 
requirements ``interim action'' and were considering further 
rulemaking. We now have determined that further rulemaking is indeed 
necessary, and this proposed AD follows from that determination.

Relevant Service Information

    The following service information has been issued:

                           Service Information
------------------------------------------------------------------------
     Service information                      Description
------------------------------------------------------------------------
Airbus Service Bulletin A330-  Inspection of the elevator servo control
 27-3128, dated May 3, 2005     to determine whether part number (P/N)
 (for Model A330-200 and -300   SC4800-7A or -9 is installed, and
 series airplanes); and         modification of the four elevator servo
 Airbus Service Bulletin A340-  controls if necessary.
 27-4129, dated May 3, 2005
 (for Model A340-200 and -300
 series airplanes).
Airbus Service Bulletin A340-  Upgrade of flight control primary
 27-4131, dated February 21,    computers (FCPCs).
 2005 (for Model A340-200 and
 -300 series airplanes).
Goodrich Actuation Systems     Inspection of the elevator servo
 Service Bulletin SC4800-27-    controls, P/N SC4800-10 and SC4800-11,
 16, Revision 3, dated May      to determine the serial number (S/N)
 19, 2006.                      installed, and replacement of the mode
                                selector valve position transducer (MVT)
                                of the elevator servo controls with a
                                new MVT if necessary.
TRW Service Bulletin SC4800-   Replacement of the eye-end equipped with
 27-34-09, Revision 1, dated    a self-lubricated bearing with a new eye-
 November 9, 2001.              end equipped with a roller bearing,
                                greasing of the new eye-end, and
                                reidentification of the servo control.
                                These actions must be done prior to or
                                concurrently with the actions specified
                                in Goodrich Actuation Systems Service
                                Bulletin SC4800-27-16.
------------------------------------------------------------------------

    Airbus Service Bulletin A340-27-4131 refers to Airbus Vendor 
Service Bulletins LA2K0-27-017 and LA2K1-27-009, both dated January 25, 
2005, as additional sources of service information for upgrading the 
FCPCs.
    Airbus Service Bulletins A330-27-3128 and A340-27-4129 refer to 
Goodrich Actuation Systems Service Bulletin SC4800-27-16, Revision 3, 
dated May 19, 2006, as an additional source of service information for 
accomplishing the modification of the four elevator servo controls.
    Accomplishing the actions specified in Airbus Service Bulletin 
A330-27-3128 or A340-27-4129, as applicable, Goodrich Actuation Systems 
Service Bulletin SC4800-27-16, and TRW Service Bulletin SC4800-27-34-
09, if required, would cancel the requirements of AD 2004-03-24. 
Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The European 
Aviation Safety Agency (EASA), which is the Technical Agent for the 
Member States of the European Community, mandated the service 
information and issued airworthiness directive 2007-0011, dated January 
9, 2007, to ensure the continued airworthiness of these airplanes in 
the European Union.

FAA's Determination and Requirements of the Proposed AD

    These airplanes are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. As described in FAA 
Order 8100.14A, ``Interim Procedures for Working with the European 
Community on Airworthiness Certification and Continued Airworthiness,'' 
dated August 12, 2005, the EASA has kept the FAA informed of the 
situation described above. We have examined the EASA's findings, 
evaluated all pertinent information, and determined that AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    This proposed AD would supersede AD 2004-03-24 and would retain the 
requirements of the existing AD. This proposed AD also would require 
accomplishing the actions specified in service information described 
previously. Accomplishing the actions specified in Airbus Service 
Bulletin A330-27-3128 or A340-27-4129, as applicable, Goodrich 
Actuation Systems Service Bulletin SC4800-27-16, and TRW Service 
Bulletin SC4800-27-34-09, if required, would constitute terminating 
action for the retained requirements of 2004-03-24. This proposed AD 
also would remove airplanes from the applicability of the existing AD.

Changes to Existing AD

    This proposed AD would retain all requirements of AD 2004-03-24. 
Since AD 2004-03-24 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                           Corresponding  requirement in
      Requirement in AD 2004-03-24               this proposed  AD
------------------------------------------------------------------------
Paragraph (a)...........................  Paragraph (f).
Paragraph (b)...........................  Paragraph (g).
Paragraph (c)...........................  Paragraph (h).
Paragraph (d)...........................  Paragraph (i).
Paragraph (e)...........................  Paragraph (j).
Paragraph (f)...........................  Paragraph (k).
------------------------------------------------------------------------

    AD 2004-03-24 affects all Airbus Model A330-200, A330-300, A340-
200, and A340-300 series airplanes. The applicability of this proposed 
AD would

[[Page 65899]]

exclude those airplanes on which a reinforced mode selector valve has 
been installed, which parallels the applicability of EASA airworthiness 
directive 2007-0011.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
of the affected Model A330-200 and A330-300 series airplanes to comply 
with this proposed AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of
                                                 Average                            U.S.-
             Action                Work hours   labor rate   Cost per airplane    registered      Fleet cost
                                                 per hour                         airplanes
----------------------------------------------------------------------------------------------------------------
AFM revision (required by AD                1          $80  $80................           29  $2,320.
 2004-03-24).
Inspection (required by AD 2004-            4          $80  $320, per                     29  $9,280, per
 03-24).                                                     inspection cycle.                 inspection cycle.
Inspection (new proposed action)            1          $80  $80................           29  $2,320.
----------------------------------------------------------------------------------------------------------------

    Currently, there are no affected Model A340-200 and A340-300 series 
airplanes on the U.S. Register. However, if an affected airplane is 
imported and placed on the U.S. Register in the future, the proposed 
upgrade of the FCPCs would take about 2 work hours, at an average labor 
rate of $80 per work hour. The manufacturer states that it would supply 
required parts to the operators at no cost. Based on these figures, we 
estimate the cost of this proposed AD for Model A340-200 and A340-300 
series airplanes to be $160 per airplane.

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 have 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 that the 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); 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 proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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.


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-13468 (69 FR 6549, February 11, 2004) and adding 
the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2007-0229; Directorate Identifier 2007-NM-
042-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by December 
26, 2007.

Affected ADs

    (b) This AD supersedes AD 2004-03-24.

Applicability

    (c) This AD applies to the airplanes identified in Table 1 of 
this AD, certificated in any category.

                         Table 1.--Applicability
------------------------------------------------------------------------
                                   Excluding those
                                  airplanes on which        Has been
        Airbus model--          any of the following--    installed--
 
------------------------------------------------------------------------
A330-200, A330-300, A340-200,   Airbus modification    In production.
 and A340-300 series airplanes.  50394, 52195, 53969,
                                 or 54833.
                                Airbus Service         In service.
                                 Bulletin A330-27-
                                 3128, dated May 3,
                                 2005.
                                Airbus Service         In service.
                                 Bulletin A340-27-
                                 4129, dated May 3,
                                 2005.
                                Airbus Service         In service.
                                 Bulletin A330-27-
                                 3136, Revision 01,
                                 dated July 19, 2006.
                                Airbus Service         In service.
                                 Bulletin A340-27-
                                 4135, dated January
                                 12, 2006.
                                Goodrich Actuation     In service.
                                 Systems Service
                                 Bulletin SC4800-27-
                                 16, Revision 03,
                                 dated May 19, 2006.
------------------------------------------------------------------------


[[Page 65900]]

Unsafe Condition

    (d) This AD results from a report of cracks of the transducer 
body at its attachment lugs. We are issuing this AD to ensure proper 
functioning of the elevator surfaces, and to prevent cracking of the 
attachment lugs, which could result in partial loss of elevator 
function and consequent reduced controllability of the airplane.

Compliance

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

Requirements of AD 2004-03-24

Airplane Flight Manual (AFM) Revision

    (f) Within 30 days after February 26, 2004 (the effective date 
of AD 2004-03-24), revise the Limitations section of the AFM to 
include a pre-flight elevator check, by including the following 
language. This may be done by inserting a copy of this AD into the 
applicable AFM. Thereafter perform the pre-flight check before every 
flight in accordance with the procedure.

Prior or During Taxi

``FLIGHT CONTROLS--CHECK

    1. AT A CONVENIENT STAGE, PRIOR TO OR DURING TAXI, AND BEFORE 
ARMING THE AUTOBRAKE, THE PF SILENTLY APPLIES FULL LONGITUDINAL AND 
LATERAL SIDESTICK DEFLECTION. ON THE F/CTL PAGE, THE PNF CHECKS FULL 
TRAVEL OF ALL ELEVATORS AND ALL AILERONS, AND THE CORRECT DEFLECTION 
AND RETRACTION OF ALL SPOILERS. THE PNF CALLS OUT ``FULL UP,'' 
``FULL DOWN,'' ``NEUTRAL,'' ``FULL LEFT,'' ``FULL RIGHT,'' 
``NEUTRAL,'' AS EACH FULL TRAVEL/NEUTRAL POSITION IS REACHED. THE PF 
SILENTLY CHECKS THAT THE PNF CALLS ARE IN ACCORDANCE WITH THE 
SIDESTICK ORDER.
    NOTE: IN ORDER TO REACH FULL TRAVEL, FULL SIDESTICK MUST BE HELD 
FOR A SUFFICIENT PERIOD OF TIME.
    2. THE PF PRESSES THE PEDAL DISC PUSHBUTTON ON THE NOSEWHEEL 
TILLER, AND SILENTLY APPLIES FULL LEFT RUDDER, FULL RIGHT RUDDER, 
AND NEUTRAL. THE PNF CALLS OUT ``FULL LEFT,'' ``FULL RIGHT,'' 
``NEUTRAL,'' AS EACH FULL TRAVEL/NEUTRAL POSITION IS REACHED.
    3. THE PNF APPLIES FULL LONGITUDINAL AND LATERAL SIDESTICK 
DEFLECTION, AND SILENTLY CHECKS FULL TRAVEL AND CORRECT SENSE OF ALL 
ELEVATORS AND ALL AILERONS, AND CORRECT DEFLECTION AND RETRACTION OF 
ALL SPOILERS, ON THE ECAM F/CTL PAGE.''

    Note 1: Full and complete elevator travel (position commanded) 
can be verified on the ECAM Flight Control Page. A determination of 
``correct sense'' should include verification that there is complete 
and full motion of the sidesticks without binding.

    (g) If any pre-flight check required by paragraph (f) of this AD 
reveals improper function of the elevator: Before further flight, 
perform the inspections required by paragraph (h) of this AD.

Inspections

    (h) At the applicable time specified in paragraph (h)(1) or 
(h)(2) of this AD, except as required by paragraph (g) of this AD: 
Perform a dye penetrant inspection of the attachment lugs of the 
mode selector valve position transducers on each elevator servo 
control installed at damping positions 3CS1 and 3CS2. Do the 
inspection in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A330-27A3115 or A340-27A4119, both Revision 
02, both dated December 30, 2003, as applicable (in paragraphs (h) 
through (k) of this AD, referred to as ``the service bulletin''). An 
inspection that is done before February 26, 2004, is acceptable for 
compliance with the initial inspection requirement of this 
paragraph, if the inspection is done in accordance with any of the 
following Airbus All Operators Telexes (AOTs): AOT A330-27A3115 or 
A340-27A4119, dated September 11, 2003, or Revision 01 of each AOT 
dated September 25, 2003; as applicable. Repeat the inspection 
thereafter at intervals not to exceed 350 flight cycles, until the 
applicable actions required by paragraphs (m) and (n) of this AD 
have been done.
    (1) If the age of the servo control from the date of its first 
installation on the airplane can be positively determined: Do the 
inspection before the accumulation of 1,000 total flight cycles on 
the elevator servo control, or within 350 flight cycles on the servo 
control after February 26, 2004, whichever occurs later.
    (2) If the age of the servo control from the date of its first 
installation on the airplane cannot be positively determined, do the 
inspection within 350 flight cycles on the servo control after 
February 26, 2004.

    Note 2: The service bulletin refers to Goodrich Actuation 
Systems Inspection Service Bulletin SC4800-27-13 as an additional 
source of service information for the inspection.

Corrective Actions

    (i) If any crack is found during any inspection required by 
paragraph (h) of this AD: Before further flight, replace either the 
transducer or servo control with a new part, in accordance with the 
service bulletin.

Reporting Requirement

    (j) If any crack is found during any inspection required by 
paragraph (h) of this AD: Submit a report in accordance with the 
service bulletin at the applicable time(s) specified in paragraphs 
(j)(1) and (j)(2) of this AD: Submit reports to Airbus Customer 
Services, Engineering and Technical Support, Attention: J. Laurent, 
SEE53, fax +33/(0)5.61.93.44.25, Sita Code TLSBQ7X. Under the 
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et 
seq.), the Office of Management and Budget (OMB) has approved the 
information collection requirements contained in this AD and has 
assigned OMB Control Number 2120-0056.
    (1) For an initial inspection done before February 26, 2004: 
Submit the report within 30 days after February 26, 2004.
    (2) For an inspection done after February 26, 2004: Submit the 
report within 30 days after the inspection.

Parts Installation

    (k) As of February 26, 2004, no person may install the following 
part on any airplane: A transducer, or a transducer fitted on an 
elevator servo control, in the operator's inventory before September 
25, 2003, unless that transducer has been inspected in accordance 
with the service bulletin and is crack free.

New Requirements of This AD

Upgrade Flight Control Primary Computers (FCPCs)

    (l) For Model A340-200 and -300 series airplanes: Within 2 
months after the effective date of this AD, upgrade the three FCPCs 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A340-27-4131, dated February 21, 2005.

    Note 3: Airbus Service Bulletin A340-27-4131 refers to Airbus 
Vendor Service Bulletins LA2K0-27-017 and LA2K1-27-009, both dated 
January 25, 2005, as additional sources of service information for 
upgrading the FCPCs.

Terminating Actions

    (m) Within 17 months after the effective date of this AD, do the 
actions specified in Table 2 of this AD.

[[Page 65901]]



                                          Table 2.--Terminating Actions
----------------------------------------------------------------------------------------------------------------
                                  In accordance with
                                  the accomplishment
            Inspect--               instructions of        And if--             Then--           In accordance
                                    airbus service                                                  with--
                                      bulletin--
----------------------------------------------------------------------------------------------------------------
(1) The elevator servo control    A330-27-3128,       P/N SC4800-7A or -  Modify the four     The Accomplishment
 to determine whether part         dated May 3, 2005   9 is found          elevator servo      Instructions of
 number (P/N) SC4800-7A or -9 is   (for Model A330-    installed.          controls.           the applicable
 installed.                        200 and -300                                                Airbus service
                                   series                                                      bulletin.
                                   airplanes); or
                                   A340-27-4129,
                                   dated May 3, 2005
                                   (for Model A340-
                                   200 and -300
                                   series
                                   airplanes); as
                                   applicable.
(2) The elevator servo controls,  None..............  S/N 2324 or below   Replace the mode    Paragraphs 3.(2)
 P/N SC4800-10 and SC4800-11 to                        is found            selector valve      and 3.B.(2) of
 determine the serial number (S/                       installed.          position            the
 N) installed.                                                             transducer (MVT)    Accomplishment
                                                                           of the elevator     Instructions of
                                                                           servo controls      Goodrich
                                                                           with a new MVT.     Actuation Systems
                                                                                               Service Bulletin
                                                                                               SC4800-27-16,
                                                                                               Revision 3, dated
                                                                                               May 19, 2006.
----------------------------------------------------------------------------------------------------------------


    Note 4: Airbus Service Bulletins A330-27-3128 and A340-27-4129 
refer to Goodrich Actuation Systems Service Bulletin SC4800-27-16, 
Revision 3, dated May 19, 2006, as an additional source of service 
information for accomplishing the modification of the four elevator 
servo controls.

    (n) Prior to or concurrently with the replacement, if required, 
specified in paragraph (m)(2) of this AD, replace the eye-end 
equipped with a self-lubricated bearing with a new eye-end equipped 
with a roller bearing, grease the new eye-end, and reidentify the 
servo control, in accordance with paragraph 2.A. of the 
Accomplishment Instructions of TRW Service Bulletin SC4800-27-34-09, 
Revision 1, dated November 9, 2001.
    (o) Accomplishing all of the applicable actions required by 
paragraphs (m) and (n) of this AD constitutes terminating action for 
paragraphs (f) through (k) of this AD.

Alternative Methods of Compliance (AMOCs)

    (p)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

Related Information

    (q) EASA airworthiness directive 2007-0011, dated January 9, 
2007, also addresses the subject of this AD.

    Issued in Renton, Washington, on November 13, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-22921 Filed 11-23-07; 8:45 am]
BILLING CODE 4910-13-P