AD 2006-26-10 Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes

Models named: A300, A300 B4-220, A300 B4-203, A300 B2-203, A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R, B4-622R. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Airbus Model A300 airplanes; certificated in any category; except the following airplanes: (1) Model A300 B4-220, A300 B4-203, and A300 B2-203 airplanes in a forward facing crew cockpit certified configuration; (2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; (3) Model A300 B4-605R and B4-622R airplanes; (4) Model A300 F4-605R and F4-622R airplanes; and (5) Airbus Model A300 C4-605R Variant F airplanes.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Revision of Airplane Flight Manual (AFM) (f) Within 14 days after the effective date of this AD, do the action specified in paragraph (f)(1) or (f)(2) of this AD. (1) Revise the Normal Procedures section of the Airbus A300 Flight Manual to include the information in Airbus A300 Temporary Revision (TR) 4.03.00/04, Issue 02, dated November 18, 2003, as specified in the TR. Note 1: This may be done by inserting a copy of TR 4.03.00/04, Issue 02, in the AFM. When the TR or the statement specified in paragraph (f)(2) of this AD has been included in the general revisions of the AFM, the general revisions may be inserted in the AFM, provided the relevant information in the general revision is identical to that in the TR or paragraph (f)(2) of this AD. (2) Revise the Normal Procedures section of the Airbus A300 Flight Manual to include the following operational procedure. This may be done by inserting a copy of this AD in the AFM. “APPROACH AND LANDING” PITCH TRIM —Set TRIM to 1° UP —Set both PITCH TRIM levers to OFF Note: Check pitch trim wheel and report any movement to maintenance.” Determination if Pitch Trim Control Wheel Moves (g) Following accomplishment of the AFM revision required by paragraph (f) of this AD: After each landing and before shutting down the engines, do the AFM procedures specified in Airbus A300 TR 4.03.00/04, Issue 02, dated November 18, 2003, or paragraph (f)(2) of this AD. Determination if Servomotor Moves (h) Before further flight after any movement reported in accordance with paragraph (g) of this AD, determine which servomotor moves the pitch trim control wheel, and do applicable other specified actions in accordance with Airbus A300 TR 22-001, dated April 11, 2003, to Chapter 22-23-00 of the Airbus A300 Fault Isolation Manual. Note 2: Airbus A300 TR 22-001 contains a typographical error. The TR incorrectly refers to “MM 22-23-39” as the appropriate source of service information for replacing the pitch trim actuator; the correct reference is “MM 22-23-29.” Optional Replacement of the Pitch Trim Servomotors (i) Replace the pitch trim servomotors in the attachment area of the horizontal and vertical stabilizers with new servomotors, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-22-0119, dated May 13, 2005. Note 3: Airbus Service Bulletin A300-22-0119, dated May 13, 2005, refers to Thales Service Bulletin V1AM-22-005, Revision 01, dated July 27, 2005, as an additional source of service information for doing the replacement. Repetitive Preventative Maintenance Tasks (j) Within 12,000 flight hours after replacing one or both servomotors in accordance with paragraph (h) or (i) of this AD, or within 6 months after the effective date of this AD, whichever occurs later, do the preventative maintenance task of the pitch trim servomotor(s), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-22-0120, excluding Appendix 01, dated May 13, 2005. Repeat the preventative maintenance task thereafter at intervals not to exceed 12,000 flight hours. Note 4: Airbus Service Bulletin A300-22-0120, dated May 13, 2005, refers to Thales Service Bulletin V1AM-22-006, Revision 01, dated July 26, 2005, as an additional source of service information for doing the preventative maintenance task. Removal of AFM Revision (k) After accomplishing the actions specified in paragraph (i) and the initial task in paragraph (j) of this AD, the AFM revision required by paragraph (f) of this AD may be removed, and the requirements of paragraphs (g) and (h) of this AD are no longer required. No Reporting (l) Although Airbus Service Bulletin A300-22-0120, dated May 13, 2005, specifies to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (m)(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) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (n) French airworthiness directives F-2003-291 R1, dated July 6, 2005, and F-2005-109, dated July 6, 2005, also address the subject of this AD. Material Incorporated by Reference (o) You must use the service information in Table 1 of this AD to do the actions that are required by this AD, unless the AD specifies otherwise. If the optional replacement is done, you must use the service information in Table 2 of this AD to do the replacement. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Table 1.—Material Incorporated by Reference for Required Actions Service information Revision/issue level Date (1) Airbus A300 Temporary Revision 22-001 to Chapter 22-23-00 of the Airbus A300 Fault Isolation Manual Original April 11, 2003. (2) Airbus A300 Temporary Revision 4.03.00/04 to Airbus 300 Flight Manual Issue 02 November 18, 2003. (3) Airbus Service Bulletin A300-22-0120, excluding Appendix 01 Original May 13, 2005. Table 2.—Material Incorporated by Reference for Optional Actions Service information Revision level Date Airbus Service Bulletin A300-22-0119 Original May 13, 2005. Issued in Renton, Washington, on December 21, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-399 Filed 1-16-07; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of a sudden nose-up movement after disengagement of the autopilot in cruise. We are issuing this AD to ensure that the flightcrew is aware of the procedures for resetting the trim and pitch trim levers after each landing and to prevent failure of the servomotors of the pitch trim systems during flight. Failure of the servomotors of the pitch trim systems could result in uncommanded nose-up movement of the control surface of the pitch trim systems after disengagement of the autopilot in cruise.