GSAC

AIRWORTHINESS DIRECTIVE

released by DIRECTION GENERALE DE L'AVIATION CIVILE

Inspection and/or modifications described below are mandatory. No person may operate a product to which this

Airworthiness Directive applies except in accordance with the requirements of this Airworthiness Directive.

Translation of `Consigne de Navigabilité' ref. : 97-113-221(B) R2

In case of any difficulty, reference should be made to the French original issue.

Landing gear free fall extension

This Airworthiness Directive applies to AIRBUS INDUSTRIE A300, A310 and A300-600 aircraft, all certified models and all serial numbers, on which AIRBUS INDUSTRIE modification No. 04443 has not been embodied, and which are not fitted with the door and landing gear alternate release device using the yellow hydraulic system, post mod 02781, (AIRBUS INDUSTRIE Service Bulletins A300-32-272 or A300-32-332) and pre mod 03433.

In order to detect and prevent any incorrect rigging of the landing gear free fall control mechanism, in which case the cockpit control handle could reach its mechanical stop (after 20.4 turns) before landing gear release and extension take place, the following measures are rendered mandatory from the effective date of this Airworthiness Directive :

1. Within 600 flight hours following the effective date of this Airworthiness Directive at original issue, perform an operational test (aircraft on wheels) of the landing gear free fall mechanism and readjust if required, in accordance with the instructions of paragraph 4.2.1. of A.O.T. 32-14 Rev.1 dated March 13,1997.

Note 1: Inform AIRBUS INDUSTRIE of all inspection results including nil findings.

Note 2: On the effective date of this Airworthiness Directive at original issue, aircraft having already performed A.O.T. 32-14 dated February 3,1997 successfully are not affected by paragraph 1 of this Airworthiness Directive.

2. Before March 31,1998, perform a functional test (aircraft on jacks) in accordance with the instructions of paragraph 4.2.2. of AIRBUS INDUSTRIE A.O.T. No. 32-14 Rev.1 dated March 13,1997.

3. Repeat the functional test described above at one year intervals.

4. Before the 30th of November 2002, modify the kinematic of the free fall control mechanism, in accordance with the instructions of AIRBUS INDUSTRIE Service Bulletins A300-32-425 Rev.1, A310-32-2111 Rev. 2 or A300-32-6072 Rev.1.

No further action in accordance with the present Airworthiness Directive is required after application of the AIRBUS INDUSTRIE Service Bulletins A300-32-425 Rev.1, A310-32-2111 Rev. 2 or A300-32-6072 Rev.1.

Ref.:

AIRBUS INDUSTRIE A300/A300-600/A310 A.O.T. 32-14 dated 03/02/1997

AIRBUS INDUSTRIE A300/A300-600/A310 A.O.T. 32-14 Rev. 1 dated 13/03/1997

AIRBUS INDUSTRIE Service Bulletins A300-32-272, A300-32-332, A300-32-425 Rev. 1,

A310-32-2111 Rev. 2, A300-32-6072 Rev. 1

(or any later approved revision).

This Revision 2 replaces Airworthiness Directive 97-113-221(B) R1 dated 03/12/1997.

Original AD: May 17, 1997

Revision 1: December 13, 1997

Revision 2: August 22, 1998