AD/A320/190 Amdt 2 Engine Pylon Spar Box Ribs (Cth)

AIRWORTHINESS DIRECTIVE

On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/A320/190 Amdt 1 and issues the following AD under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Airbus Industrie A319, A320 and A321 Series Aeroplanes

AD/A320/190 Amdt 2 Engine Pylon Spar Box Ribs 4/2006

Applicability:

Model A318, A319, A320, and A321 aircraft, with Manufacturer Serial Number 0791, 1464, 1660, 1969, 1979, 2026, 2028, 2030, 2032, 2033, 2035, 2037, 2039, 2041, 2043, 2045, 2047, 2050 through 2053, 2055, 2057, 2059, 2060, 2062, 2064, 2066, 2067, 2069, 2071, 2072, 2074, 2078 through 2269, 2271 through 2506, 2508 through 2565, 2567 through 2580, 2582 through 2591, 2593 through 2597, 2600, 2601, 2605, 2607, 2610, or 2615.

Requirement:

1.    The following operational procedure is rendered mandatory for all flights:

In the case of severe turbulence, strictly adhere to reduced speeds as defined in Aircraft Flight Manual Section 4.03.00 Page 03.

Insertion of this Directive in the Aircraft Flight Manual or Aircraft Operations Manual and application of this procedure by flight crew, complies with the above requirement of this Directive.

2.    For aircraft equipped with CFM engines:

Inspect ribs 7, 8, and 9 of the left and right engine pylon spar box and apply all necessary corrective actions in accordance with Airbus All Operators Telex (AOT) A320-54A1015 Revision 1, or later EASA approved revision.

Report the results of the inspection to Airbus in accordance with AOT
A320-54A1015 Revision 1, or later EASA approved revision.

3.    For aircraft equipped with IAE engines:

Inspect ribs 7, 8, and 9 of the left and right engine pylon spar box and apply all necessary corrective actions in accordance with AOT A320-54A1015 Revision 1, or later EASA approved revision.

Report the results of the inspection to Airbus in accordance with AOT
A320-54A1015 Revision 1, or later EASA approved revision.

Note:  DGAC AD F-2006-011 R1 refers.

Compliance:

1.    Effective from 14 January 2006.

2.    Within 6 months after 14 January 2006.

3.    Within 9 months after 14 January 2006.

The compliance times remain unchanged by this Directive issue.

This Amendment becomes effective on 13 April 2006.

Background:

The manufacturer recently discovered that certain engine pylon spar box ribs constructed of stainless steel material may not have been heat-treated in production, prior to installation in the pylon.  The omission of the heat treatment operation results in a significant reduction of the material allowable yield stress.  As a consequence, non heat-treated ribs may not meet all the certification requirements, especially for vertical gust.

Amendment 1 clarified manual applicability in Requirement 1.

Amendment 2 is issued to introduce Revision 1 of the Requirement document.  No additional work is required.

David Punshon
Delegate of the Civil Aviation Safety Authority

2 March 2006