Airworthiness Directive · Amendment 39-14686 · Airbus Model A300 B2-203 and A300 B4-203 Airplanes; Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310-200 and -300 Series Airplanes
Airbus Model A300 B2-203 and A300 B4-203 Airplanes; Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310-200 and -300 Series Airplanes
This AD applies to the following Airbus airplanes, certificated in any category.
(1) Model A300 B2-203 and A300 B4-203 airplanes, as identified in Airbus Service Bulletin A300-22A0115, Revision 02, dated March 7, 2000.
(2) Model A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R, B4-622R, A300 F4-605R, F4-622R, and A300 C4-605R Variant F airplanes, except those modified in production by Airbus Modification 12932.
(3) Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, except those modified in production by Airbus Modification 12931.
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300 series airplanes and all Model A300-600 and A310 series airplanes. That AD currently requires repetitive inspections of the pitch trim system to detect continuity defects in the autotrim function, and follow-on corrective actions if necessary. For certain airplanes, this new AD requires replacing the flight augmentation computers (FACs) with new improved FACs. This AD also revises the applicability of the existing AD. This AD results from the development of a final action intended to address the unsafe condition. We are issuing this AD 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.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
For Model A300 B2-203 and A300 B4-203 airplanes in a forward-facing cockpit configuration; all Model A310-200 and -300 series airplanes; and Model A300-600 series airplanes, except those with Modification 12277 installed in production: At the applicable time specified by paragraph (f)(1) or (f)(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, as applicable; 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. Replacement of both FACs in accordance with paragraph (g) of this AD terminates the inspection requirements of this paragraph.
(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 December 20, 2000 (the effective date of AD 2000-23-07), whichever occurs later.
(2) For all other airplanes: Inspect within 20 days after December 20, 2000.
For airplanes identified in paragraphs (c)(2) and (c)(3) of this AD: At the time specified in Table 1 of this AD, replace the two FACs with new FACs in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-22-6050, dated October 8, 2004; or A310-22-2058, dated April 6, 2005; as applicable.
| Airplane model/series | Configuration | Required compliance time after the effective date of this AD |
|---|---|---|
| A300-600 | Without accomplishment of Airbus Service Bulletin A300-22-6041, Revision 01, dated February 21, 2001, or previous version, or Modification 12277 | 24 months. |
| And without accomplishment of Airbus Service Bulletin A300-22-6050, dated October 8, 2004, or Modification 12932 | ||
| With accomplishment of Airbus Service Bulletin A300-22-6041, Revision 01, dated February 21, 2001, or previous version, or Modification 12277 | 36 months. | |
| And without accomplishment of Airbus Service Bulletin A300-22-6050, dated October 8, 2004, or Modification 12932 | ||
| A310 | Without accomplishment of Airbus Service Bulletin A310-22-2052, Revision 01, dated November 8, 2001, or previous version, or Modification 12277 | 24 months. |
| And without accomplishment of Airbus Service Bulletin A310-22-2058, dated April 6, 2005, or Modification 12931 | ||
| With accomplishment of Airbus Service Bulletin A310-22-2052, Revision 01, dated November 8, 2001, or previous version, or Modification 12277 | 36 months. | |
| And without accomplishment of Airbus Service Bulletin A310-22-2058, dated April 6, 2005, or Modification 12931 |
On or after the effective date of this AD, no person may install, on any airplane, any FAC having part number (P/N) B471AAM7 (for Model A300-600 series airplanes) or FAC P/N B471ABM4 (for Model A310 series airplanes), unless the FAC is in compliance with 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.
