AD 2006-25-03 Airworthiness Directives; Airbus Model A300 Airplanes

Models named: A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, B4-203, A300 B4-203, A300 B2-203. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes; all serial numbers; certificated in any category; except for Model A300 B4-203 and A300 B2-203 airplanes in a forward facing crew cockpit certified configuration. Reason (d) The refined study of an in-service event has evidenced the need to perform a periodic test of pitch trim system 2. In the conditions of overriding the automatic pitch torque limiter, the clutch of the pitch trim servo-motor 1 is opened so that electric pitch trim system 1 will disconnect. The question is pending about the availability of the system 2 and its capability to take over the pitch trim function, particularly during a go-around. Failure of pitch trim system 2 to deflect the trimmable horizontal stabilizer (THS) at maximum rate could result in loss of high-speed trim and consequent reduced controllability of the airplane. For such reason, this AD renders mandatory a periodic test to ensure the availability of the pitch trim system 2 and its possibility to deflect the THS at high speed of trim.

Unless already done, do the following actions except as stated in paragraph (f) below: (1) Within 250 flight hours after the effective date of this AD: Perform an operational test of pitch trim system 2 in high speed of trim configuration and if system 2 does not function as specified in the instructions of Airbus Service Bulletin A300-22-0121, dated July 11, 2005; before further flight, return the system to correct operating condition in accordance with the instructions of the service bulletin. (2) The operational test, followed, if necessary, by the corrective action described in the paragraph above, is to be repeated at intervals not exceeding 1,000 flight hours in accordance with the instructions of Airbus Service Bulletin A300-22-0121, dated July 11, 2005. FAA AD Difference (f) When complying with this AD, do the following: Although the Accomplishment Instructions of the referenced service bulletin describe procedures for submitting certain information to the manufacturer, this AD does not include that requirement. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, ATTN: Tom Stafford, Aerospace Safety Engineer, 1601 Lind Avenue, SW., Renton, Washington 98057-3371; telephone (425) 227-1622; fax (425) 227-1149; has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) Notification of Principal Inspector: Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) Return to Airworthiness: When complying with this AD, perform FAA-approved corrective actions before returning the product to an airworthy condition. Related Information (h) This AD is related to MCAI French airworthiness directive F-2005-157, dated September 14, 2005, which references Airbus Service Bulletin A300-22-0121, dated July 11, 2005, for information on required actions. Material Incorporated by Reference (i) You must use Airbus Service Bulletin A300-22-0121, excluding Appendix 01, dated July 11, 2005, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. (3) You may review copies at the Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3371; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on November 20, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-20617 Filed 12-6-06; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions except as stated in paragraph (f) below: (1) Within 250 flight hours after the effective date of this AD: Perform an operational test of pitch trim system 2 in high speed of trim configuration and if system 2 does not function as specified in the instructions of Airbus Service Bulletin A300-22-0121, dated July 11, 2005; before further flight, return the system to correct operating condition in accordance with the instructions of the service bulletin. (2) The operational test, followed, if necessary, by the corrective action described in the paragraph above, is to be repeated at intervals not exceeding 1,000 flight hours in accordance with the instructions of Airbus Service Bulletin A300-22-0121, dated July 11, 2005. FAA AD Difference (f) When complying with this AD, do the following: Although the Accomplishment Instructions of the referenced service bulletin describe procedures for submitting certain information to the manufacturer, this AD does not include that requirement. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, ATTN: Tom Stafford, Aerospace Safety Engineer, 1601 Lind Avenue, SW., Renton, Washington 98057-3371; telephone (425) 227-1622; fax (425) 227-1149; has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) Notification of Principal Inspector: Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) Return to Airworthiness: When complying with this AD, perform FAA-approved corrective actions before returning the product to an airworthy condition. Related Information (h) This AD is related to MCAI French airworthiness directive F-2005-157, dated September 14, 2005, which references Airbus Service Bulletin A300-22-0121, dated July 11, 2005, for information on required actions. Material Incorporated by Reference (i) You must use Airbus Service Bulletin A300-22-0121, excluding Appendix 01, dated July 11, 2005, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. (3) You may review copies at the Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3371; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on November 20, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-20617 Filed 12-6-06; 8:45 am] BILLING CODE 4910-13-P