AD/Do 328/71 Wing Lower Inner Panel (Cth)

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (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.

Dornier 328 Series Aeroplanes

AD/DO 328/71 Wing Lower Inner Panel 7/2008 TX

Applicability:

Model 328-100 aircraft, all serial numbers.

Model 328-300 aircraft, all serial numbers.

Requirement:

1.    Accomplish a detailed visual inspection of the affected area in accordance with the Accomplishment Instructions of 328 Support Services GmbH Alert Service Bulletin ASB-328-57-037 Revision 1 or ASB-328J-57-015 Revision 1, as applicable; or later EASA approved revisions.

a.     If cracks are not detected, repeat the inspection.

b.    If cracks are detected, accomplish an NDI in accordance with
Requirement 2.

If cracking is detected, a non-revenue ferry flight of a maximum of 3 flight cycles is permitted to position the aircraft to a maintenance repair facility, provided the crack indication does not exceed 12.5 mm.  If the crack indication exceeds 12.5 mm, a special flight permit must be requested.

2.    Accomplish an NDI of the affected area in accordance with ASB-328-57-037 Revision 1 or ASB-328J-57-015 Revision 1, as applicable; or later EASA approved revisions.

If cracking is detected during any inspection required by this Directive, before further flight, contact the Type Certificate holder for approved repair instructions; and accomplish the repair.

Send an inspection result report to the Type Certificate holder within 3 days after each required inspection (even if cracks are not detected).  Send the results of any inspection accomplished before the issue of this Directive within 3 days of the effective date of this Directive.

Accomplishment of the NDI, and associated repair if necessary, terminates the inspection requirements of this Directive.

Note:  EASA Emergency AD 2008-0087-E refers.

Compliance:

1.    Unless already accomplished, within 10 flight cycles or 10 flight hours or 7 days after 9 May 2008, whichever occurs first.

a.     If cracks are not detected, repeat the Requirement 1 inspection at intervals not to exceed 50 flight hours.

b.    Before further flight.

2.    Unless already accomplished, within 400 flight hours or 3 months after
9 May 2008, whichever occurs first.

This Airworthiness Directive becomes effective on 9 May 2008.

Background:

During a routine inspection of an aircraft by the operator, cracks were detected on a lower wing panel rear trailing edge, inboard of flap lever arm 1 (rib 5).  A subsequent inspection of other aircraft in the operator’s fleet revealed several more aircraft with cracks at the same location.  This condition, if not corrected, could lead to structural failure of the affected wing panel and possible wing failure, with consequent loss of control.

David Villiers
Delegate of the Civil Aviation Safety Authority

9 May 2008