Airworthiness Directive · Amendment 39-11977 · Airbus Model A300, A300-600, and A310 Series Airplanes
Airbus Model A300, A300-600, and A310 Series Airplanes
Superseded. A later AD replaced this one: AD 2006-15-06. Comply with the one in force.
This AD applies to the airplanes listed in Table 1. of this AD, certificated in any category:
| Airbus model | Description |
|---|---|
| A300 B2-203 airplanes and A300-B4-203 airplanes | In a forward facing cockpit version, as listed in Airbus Service Bulletin A300-22A0115, Revision 02, dated March 7, 2000. |
| A310 series airplanes | All. |
| A300-600 series airplanes | On which Airbus Modification 12277 has not been accomplished during production. |
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 and all Model A300-600 and A310 series airplanes, that currently requires performing a pitch trim system test to detect any continuity defect in the autotrim function, and follow-on corrective actions, if necessary. This amendment requires repetitive inspections of the autotrim function to detect such defects, and corrective actions, if necessary. This amendment also expands the applicability to include additional airplanes. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent a sudden change in pitch due to an out-of-trim condition combined with an autopilot disconnect, which could result in reduced controllability of the airplane.
To prevent a sudden change in pitch due to an out-of-trim condition combined with an autopilot disconnect, which could result in reduced controllability of the airplane, accomplish the following:
(a) At the applicable time specified by paragraph (a)(1) or (a)(2) of this AD: Perform an inspection of the autotrim function by testing the flight control computer (FCC)/flight augmentation computer (FAC) integrity in logic activation of the autotrim, in accordance with Airbus Service Bulletin A300-22A6042, Revision 01 (for Model A300-600 series airplanes); A300-22A0115, Revision 02 (for Model A300 series airplanes); or A310-22A2053, Revision 01 (for Model A310 series airplanes); all dated March 7, 2000; as applicable. If any discrepancy is found, prior to further flight, perform all applicable corrective actions (including trouble-shooting, replacing the FCC and/or FAC, retesting, checking the wires between certain FCC and FAC pins, and repairing damaged wires) in accordance with the applicable service bulletin. Repeat the inspection thereafter at intervals not to exceed 500 flight hours.
(1) For airplanes on which the pitch trim system test has been performed in accordance with the requirements of AD 2000-02-04, amendment 39-11522: Inspect within 500 flight hours after accomplishment of the test required by that AD, or within 20 days after the effective date of this AD, whichever occurs later.
(2) For all other airplanes: Inspect within 20 days after the effective date of this AD.
(b) For all inspections required by paragraph (a) of this AD: At the applicable time specified by paragraph (b)(1) or (b)(2) of this AD, submit a report of the inspection results (both positive and negative findings) to AI/SE-D32 Technical Data and Documentation Services, Airbus Industrie Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France; fax (+33) 5 61 93 28 06.
(1) For inspections accomplished after the effective date of this AD: Submit the report within 30 days after performing the inspection.
(2) For inspections accomplished prior to the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
