AD/BEECH 1900/49 Amdt 1 Wing Rear Spar Lower Cap Inspection 2 (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/BEECH 1900/49 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.

Beechcraft 1900 Series Aeroplanes

AD/BEECH 1900/49 Amdt 1 Wing Rear Spar Lower Cap Inspection - 2 9/2008

Applicability:

Model 1900 aircraft, serial number UA-3;

Model 1900C aircraft, serial numbers UB-1 through UB-74, UC-1 through UC-174;

Model 1900D aircraft, serial numbers UE-1 through UE-439;

that have not been modified in accordance with Hawker Beechcraft MSB 57-3816.

Requirement:

1.    Inspect both the left and right wing rear spar lower caps for cracks, and other damage such as loose or missing fasteners; in accordance with Raytheon Mandatory Service Bulletin (MSB) 57-3815 Issued October 2006, or later FAA approved revision.

If cracks are detected during any inspection, before further flight, repair all cracks by obtaining and incorporating an FAA-approved repair scheme from Raytheon Aircraft Company.

2.    Report the inspection results to Raytheon Aircraft Company by following the procedures in MSB 57-3815 Issued October 2006, or later FAA approved revision.

Note:  FAA AD 2006-24-11 Amdt 39-14840 refers.

Compliance:

1.    Within 100 hours time in service or 30 days after 15 December 2006, whichever occurs first.  Inspect thereafter at intervals not to exceed 200 hours time in service.

2.    Report the initial inspection within 10 days after the inspection or 10 days after 15 December 2006, whichever occurs later.  Report each repetitive inspection within 30 days after the inspection.

This Amendment becomes effective on 28 August 2008.

Background:

The FAA received reports of additional fatigue cracks which were detected since inspections were performed in accordance with AD/BEECH 1900/48 (FAA Emergency AD 2006-18-51), which required immediate visual inspections of the affected area.  This directive required cleaning and paint stripping of the affected section of the wing rear spar, and a more rigorous inspection to detect and correct cracking in the wing spar lower caps of certain aircraft before the cracks lead to failure.  Such cracking may result in wing failure which could result in the wing separating from the aircraft with consequent loss of control.

Amendment 1 is issued to allow terminating action in accordance with Hawker Beechcraft MSB 57-3816 which involves cold expansion of fastener holes.  When incorporated, this is terminating action for the inspections required by MSB 57-3815.

David Villiers
Delegate of the Civil Aviation Safety Authority

18 July 2008