AD 2004-08-09 Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes; Model A300 B4-600, B4-600R, and F4-600R (Collectively Called A300-600) Series Airplanes; and Model A310 Series Airplanes

Airplanes as listed in Table 1 of this AD, certificated in any category. Table 1.—Applicability Airplane models As listed in Airbus Service Bulletin— A300 B2 and B4 series A300-76-0007, Revision 06, dated August 23, 2001. A300 B2 and B4 series A300-76-0015, Revision 02, dated August 23, 2001. A300 B2 and B4 series A300-76-0016, Revision 03, dated August 23, 2001. A300 B4-620, B4-622, and C4-620 A300-76-6002, Revision 02, dated August 23, 2001. A300 B4-620 A300-76-6003, Revision 04, dated February 26, 2002. A300 B4-601, -603, and -605R A300-76-6007, Revision 01, dated March 14, 2000. A300 B4-601, B4-603, B4-605R, and C4-605R Variant F A300-76-6009, Revision 02, dated October 29, 1999. A310-203, -204, -221, and -222 A310-76-2001, Revision 01, dated March 14, 2000. A310-203 A310-76-2004, Revision 03, dated August 23, 2001. A310-203, -221, and -222 A310-76-2005, Revision 01, dated March 14, 2000. A310-221, -222, and -322 A310-76-2006, Revision 03, dated February 26, 2002. A310-204 and -304 A310-76-2010, Revision 03, dated August 23, 2001. A310-203, -204, and -304 A310-76-2012, Revision 02, dated November 5, 2001.

Required as indicated, unless accomplished previously. To prevent hard points in the throttle control system that could lead to jamming of the throttle control cable, which could result in an asymmetric thrust condition and consequent reduced controllability of the airplane, accomplish the following: Modifications (a) Within 22 months after the effective date of this AD, do the actions specified in paragraphs (a)(1), (a)(2), (a)(3), (a)(4), (a)(5), and (a)(6) of this AD; as applicable. (1) For airplanes listed in Airbus Service Bulletin A300-76-0007, Revision 06, dated August 23, 2001: Install a flexible ice protection boot on the upper fitting of the throttle and fuel shut-off valve control cables in each engine pylon, per the Accomplishment Instructions of that service bulletin. (2) For airplanes listed in Airbus Service Bulletin A300-76-0015, Revision 02, dated August 23, 2001; or A310-76-2001, Revision 01, dated March 14, 2000: Install a heating system for the throttle control system in each engine pylon, per the Accomplishment Instructions of the applicable service bulletin. (3) For airplanes listed in Airbus Service Bulletin A300-76-0016, Revision 03, dated August 23, 2001; A300-76-6002, Revision 02, dated August 23, 2001; or A310-76-2005, Revision 01, dated March 14, 2000: Replace, with new improved parts, the roller and rotation pin of the secondary relay lever of the throttle control system in each engine pylon. Accomplish the replacement per the Accomplishment Instructions of the applicable service bulletin. (4) For airplanes listed in Airbus Service Bulletin A300-76-6007, Revision 01, dated March 14, 2000; or A310-76-2010, Revision 03, dated August 23, 2001: Install a new cooling duct and a new cooling shroud for the throttle control cable, per the instructions in the “Description” section of Airbus Service Bulletin A300-76-6007, Revision 01; or per the Accomplishment Instructions of A310-76-2010, Revision 03; as applicable. Note 1: Airbus Service Bulletins A300-76-6007, Revision 01; and A310-76-2010, Revision 03; refer to GE CF6-80C2 Service Bulletins 71-088, Revision 3, dated March 15, 1991; and 75-021, Revision 3, dated August 5, 1992; for additional service information for accomplishing the installation of a new cooling duct and a new cooling shroud for the throttle control cable. (5) For airplanes listed in Airbus Service Bulletin A300-76-6009, Revision 02, dated October 29, 1999; or A310-76-2012, Revision 02, dated November 5, 2001: Install an elastomer plug filled with grease on the end fitting of the throttle control cable in each engine pylon, per the Accomplishment Instructions of the applicable service bulletin. (6) For airplanes listed in Airbus Service Bulletin A310-76-2004, Revision 03, dated August 23, 2001: Install a sealing sleeve (also called a sealing boot) on the flexible control ball joint of the throttle control cable in each engine pylon (including a detailed inspection for deterioration of the throttle control cable, and replacement of the throttle control cable, as applicable) by doing all actions in and per the Accomplishment Instructions of the service bulletin. Replacement of the throttle control cable, if required, must be accomplished before further flight. Note 2: For the purposes of this AD, a detailed inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.” Accomplishment of Required Actions Per Previous Service Bulletin Revisions (b) Actions accomplished before the effective date of this AD per previous service bulletin revisions are acceptable for compliance with paragraph (a) of this AD; as specified in paragraph (b)(1), (b)(2), (b)(3), (b)(4), (b)(5), and (b)(6) of this AD; as applicable. (1) Accomplishment of the installation required by paragraph (a)(1) of this AD per Airbus Service Bulletin A300-76-007, Revision 05, dated March 14, 2000, is acceptable for compliance with paragraph (a)(1) of this AD. (2) Accomplishment of the installation required by paragraph (a)(2) of this AD per Airbus Service Bulletin A300-76-0015, Revision 01, dated March 14, 2000, is acceptable for compliance with paragraph (a)(2) of this AD. (3) Accomplishment of the replacement required by paragraph (a)(3) of this AD per Airbus Service Bulletin A300-76-016, Revision 02, dated March 14, 2000; or A300-76-6002, Revision 01, dated March 14, 2000; as applicable; is acceptable for compliance with paragraph (a)(3) of this AD. (4) Accomplishment of the installation required by paragraph (a)(4) of this AD per Airbus Service Bulletin A310-76-2010, Revision 02, dated March 14, 2000, is acceptable for compliance with paragraph (a)(4) of this AD. (5) Accomplishment of the installation required by paragraph (a)(5) of this AD per Airbus Service Bulletin A300-76-6009, Revision 01, dated March 5, 1999; or A310-76-2012, Revision 01, dated March 5, 1999; as applicable; is acceptable for compliance with paragraph (a)(5) of this AD. (6) Accomplishment of all actions required by paragraph (a)(6) of this AD (including a detailed inspection for deterioration of the throttle control cable, and replacement of the throttle control cable, as applicable) per Airbus Service Bulletin A310-76-2004, Revision 02, dated March 14, 2000, is acceptable for compliance with paragraph (a)(6) of this AD. Repetitive Inspections and Corrective Actions if Necessary (c) For airplanes listed in Airbus Service Bulletin A300-76-6003, Revision 04, dated February 26, 2002; or A310-76-2006, Revision 03, dated February 26, 2002: Within 500 flight hours after the effective date of this AD, do the inspections and corrective actions, as applicable, required by paragraphs (c)(1) and (c)(2) of this AD, according to the Accomplishment Instructions of the applicable service bulletin. Repeat the inspections and corrective actions, as applicable, thereafter at intervals not to exceed 2,000 flight hours, until paragraph (e) of this AD is accomplished. Although Airbus Service Bulletins A300-76-6003, Revision 04, and A310-76-2006, Revision 03, specify to submit certain information to the manufacturer, this AD does not include such a requirement. (1) Perform a detailed inspection to detect discrepancies of the throttle control cable (also called the “push-pull” cable) and the rack-box connection in each engine pylon, especially in the area of the cable guide having part number 221-1325-501. Discrepancies include excessive wear, damage, chafing of the cable in the area of a cable guide, backlash outside limits specified in the service bulletin, or excessive play. If any discrepancy is found, before further flight, replace the throttle control cable or the rack-box, as applicable, per the applicable service bulletin. (2) Perform a detailed inspection for wear or play of the power lever of the hydromechanical control in the area where the rack-box drive tang is installed in the power lever. If any wear or play is found, before further flight, tighten the drive tang expansion screw to take up play, per the applicable service bulletin. Accomplishment of Required Actions Per Previous Service Bulletin Revisions (d) Inspections and corrective actions accomplished before the effective date of this AD per Airbus Service Bulletin A300-76-6003, Revision 02, dated June 5, 2000; or Revision 03, dated November 9, 2000; or A310-76-2006, Revision 02, dated June 5, 2000; as applicable; are acceptable for compliance with paragraph (c) of this AD. Optional Terminating Action (e) Replacement of the existing throttle control cable assembly with a new improved assembly, per the Accomplishment Instructions of Airbus Service Bulletin A300-76-6004, Revision 01, dated October 11, 2000; or A310-76-2007, Revision 2, dated November 24, 1988; as applicable; constitutes terminating action for the repetitive inspections required by paragraph (c) of this AD. Alternative Methods of Compliance (f) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, is authorized to approve alternative methods of compliance for this AD. Incorporation by Reference (g) Unless otherwise specified in this AD, the actions shall be done in accordance with the applicable service bulletins listed in Table 2 of this AD. Table 2 of this AD follows: Table 2.—Service Bulletins Incorporated by Reference Airbus service bulletin Revision Date A300-76-0007 Revision 06 August 23, 2001. A300-76-0015 Revision 02 August 23, 2001. A300-76-0016 Revision 03 August 23, 2001. A300-76-6002 Revision 02 August 23, 2001. A300-76-6003 Revision 04 February 26, 2002. A300-76-6004 Revision 01 October 11, 2000. A300-76-6007 Revision 01 March 14, 2000. A300-76-6009 Revision 02 October 29, 1999. A310-76-2001 Revision 01 March 14, 2000. A310-76-2004 Revision 03 August 23, 2001. A310-76-2005 Revision 01 March 14, 2000. A310-76-2006 Revision 03 February 26, 2002. A310-76-2007 Revision 2 November 24, 1988. A310-76-2010 Revision 03 August 23, 2001. A310-76-2012 Revision 02 November 5, 2001. Airbus Service Bulletin A310-76-2005, Revision 01, contains the following effective pages:   Page number Revision level shown on page Date shown on page 1-5  01 March 14, 2000. 6-11 Original November 26, 1985. Airbus Service Bulletin A300-76-6004, Revision 01, contains the following effective pages:   Page number Revision level shown on page Date shown on page 1-3, 5  01 October 11, 2000. 4, 6-21 Original October 22, 1986. Airbus Service Bulletin A310-76-2007, Revision 2, contains the following effective pages:   Page number Revision level shown on page Date shown on page 1, 2, 11 2 November 24, 1988. 3-5, 9, 10, 19-21 1 November 19, 1986. 6-8, 12-18 Original September 30, 1986. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Note 3: The subject of this AD is addressed in French airworthiness directive 2001-072(B) R2, dated January 23, 2002. Effective Date (h) This amendment becomes effective on May 24, 2004. Issued in Renton, Washington, on April 6, 2004. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-8544 Filed 4-16-04; 8:45 am] BILLING CODE 4910-13-P