http://www.iasa-intl.com/peteranalysis.htm

The AD at the bottom of the page is particularly interesting--dated right after rollover, it refers to problems found in 1999.

-- Anonymous, January 05, 2002

Answers

The A300 has a rudder limiter that places variable stops on the actuator input, depending upon airspeed. Two computers electrically drive the stops.

. . .

2000-02-24 AIRBUS INDUSTRIE: Amendment 39-11542. Docket 99-NM-247-AD.

Applicability: Model A300, A310, and A300-600 series airplanes; certificated in any category; except those airplanes on which Airbus Modification 10438 has been installed, or on which Airbus Service Bulletin A300-27-0182, Revision 2, A300-27-6023, Revision 2, or A300-27-2065, Revision 2, each dated June 30, 1999, has been accomplished.

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 (d) 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.

Compliance: Required as indicated, unless accomplished previously.

To prevent corrosion of the spring rod assemblies of the rudder servo controls, which could result in the jamming of the rudder servo controls and consequent reduced controllability of the airplane, accomplish the following:

(a) For airplanes on which the spring rod assemblies of the rudder servo controls have not been modified in accordance with Airbus Service Bulletin A300-27-182, dated March 16, 1995, or Revision 1, dated November 21, 1996 (for Model A300 series airplanes); A310-27-2065, dated March 16, 1995, or Revision 1, dated March 10, 1997 (for Model A310 series airplanes); or A300-27-6023, dated March 16, 1995, or Revision 1, dated March 10, 1997 (for Model A300-600 series airplanes); as applicable; as of the effective date of this AD: Within 1 year after the effective date of this AD, accomplish the actions specified in either paragraph (a)(1) or (a)(2) in accordance with Airbus Service Bulletin A300-27-182, Revision 2 (for Model A300 series airplanes); or A310-27-2065, Revision 2 (for Model A310 series airplanes); or A300-27-6023, Revision 2 (for Model A300-600 series airplanes); each dated June 30, 1999; as applicable.

(1) Replace the spring rod assemblies with improved spring rod assemblies; or

(2) Modify the existing spring rod assemblies and re-identify all modified spring rod assemblies.

(b) For airplanes on which the spring rod assemblies of the rudder servo controls have been modified in accordance with Airbus Service Bulletin A300-27-182, dated March 16, 1995, or Revision 1, dated November 21, 1996 (for Model A300 series airplanes); or A310-27-2065, dated March 16, 1995, or Revision 1, dated March 10, 1997 (for Model A310 series airplanes); or A300-27-6023, dated March 16, 1995, or Revision 1, dated March 10, 1997 (for Model A300-600 series airplanes); as applicable; as of the effective date of this AD: Within 1 year after the effective date of this AD, perform a one-time visual inspection to verify that all spring rod assemblies of the rudder servo controls have the same part numbers, in accordance with Airbus Service Bulletin A300-27-182, Revision 2 (for Model A300 series airplanes); or A310-27-2065, Revision 2 (for Model A310 series airplanes); or A300-27-6023, Revision 2 (for Model A300-600 series airplanes); each dated June 30, 1999; as applicable.

(1) If all three spring rod assemblies have P/N A2727086500400, A2727086500600, or A2727114900000, no further action is required by this AD.

(2) If any spring rod assembly has a P/N other than P/N A2727086500400, A2727086500600, or A2727114900000, prior to further flight, re-identify all spring rod assemblies to the P/N specified in the applicable service bulletin, in accordance with the applicable service bulletin.

(c) As of the effective date of this AD, no person shall install on any airplane a spring rod assembly having P/N A2727086500200.

-- Anonymous, January 07, 2002