AIRWORTHINESS DIRECTIVE
CAA-AD-T-016/1999
Date of issue: February 03, 2000
AIRCRAFT - LOSS OF AUTOTRIM FUNCTION - INSPECTION
Applicability: AIRBUS INDUSTRIE A300FFCC, A300-600 and A3l0 aircraft certified in any category.
Effective date: Upon receipt.
Compliance: Required as indicated in DGAC AD T2000-007-301(B).
Remarks: The compliance of this AD must be recorded in Aircraft Logbook, where applicable the requirements of this AD must be integrated into Aircraft Technical Documentation. Address inquiries concerning this AD to: Civil Aviation Authority, Airworthiness Division, Ruzyne Airport, 160 08 Prague 6, Czech Republic, tel: 420 2 33320922, fax: 420 2 20562270.
Ing. Pavel MATOUŠEK
Director of Airworthiness Division, CAA CZ
TELEGRAPHIC AIRWORTHINESS DIRECTIVE RELEASED BY THE DIRECTION GENERALE DE L'AVIATION CIVILE (France)
THIS TEXT IS NOT SENT TO FOREIGN OPERATORS OF AIRCRAFT NON REGISTERED IN FRANCE.
IT IS UP TO THE NATIONAL AUTHORITIES TO FORWARD IT TO THEM ON RECEIPT.
No T2000-007-301(B)-AIRBUS INDUSTRIE-A300FFCC, A300-600 and A310 Aircraft
TITLE: L0SS OF AUTOTRIM FUNCTION (ATA 22)
APPLICABILITY:
AIRBUS INDUSTRIE A300FFCC, A300-600 and A3l0 aircraft certified in any category.
REASON:
Recently, an A300-600 aircraft flying with the Auto-Pilot 1, Pitch trim l and 2 engaged was unable to hold the vertical speed selected by the crew.
A maintenance check further revealed that this situation was due to an open wire between the Flight Control Computer l (FCC 1) and the Flight Augmentation Computer 1 (FAC 1).
If left uncorrected, this failure can lead to a potential out of trim situation and, if the Auto-Pilot is disconnected, to a sudden change of Pitch attitude.
COMPLIANCE: Before January 31, 2000 if not already accomplished
ACTION:
To detect and correct a defect of Auto-Trim function,
a) Perform the Pitch Trim system check described in paragraph 42 of the following AIRBUS INDUSTRIE All Operator Telex (AOT) for:
i) A3OOFFCC aircraft: (AOT) A300 - 22A0ll5 of December 23, 1999,
ii) A300-600 aircraft: (AOT) A300-600 - 22A6042 of December 23, 1999,
iii) A310 aircraft: (AOT) A310 - 22A2053 of December 23, 1999.
b) If a continuity defect is discovered : before the next flight repair the involved wire, using the Aircraft Schematic Manual (ASM) 22-27-00, and perform again the system check described in paragraph a) above.
c) Report the system check's result--whatever it is-- to AIRBUS INDUSTRIE.
NOTE: Inquiries regarding the technical content of this TAD should be made to:
DGAC France
Jean BEIJARD
Tel.: (33) 01.41.09. 42.29 - Fax: (33) 01.41.09.42.20 (or 43.19)
or to
AIRBUS INDUSTRIE
Yves REGIS
Tel: (33) 05.61.93.3l.8l - Fax: (33) 05.61.93.45.80i)
REF: AIRBUS INDUSTRIE AOT A300 - 22A0ll5 of December 23, 1999
AIRBUS INDUSTRIE AOT A310 - 22A2053 of December 23, 1999
AIRBUS INDUSTRIE AOT A300-600 - 22A6042 of December 23, l999
EFFECTIVE DATE: Upon receipt from JANUARY 4, 2000