AD/Do 228/10 Fuselage Frame 19 (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 228 Series Aeroplanes

AD/DO 228/10 Fuselage Frame 19 4/2007 DM

Applicability:

Model 228-100, -101, -200, -201, -202, and -212, all serial numbers.

Requirement:

1.    Visually inspect fuselage frame 19 in accordance with RUAG Aerospace Alert Service Bulletin ASB-228-266 original issue, dated 1 December 2006, or later EASA approved revision.

2.    If any crack is detected that is equal to or exceeds 5mm in length, contact RUAG Aerospace for instructions.

If a crack is detected that is less than 5mm in length, flights may be resumed.

If any discrepancy is detected during any Requirement 1 inspection, within 7 calendar days after the inspection, report the findings to RUAG Aerospace.

Any approved repair instructions subsequently supplied by RUAG Aerospace must be accomplished within the time period specified in those instructions.

Note:  EASA AD 2007-0028 refers.

Compliance:

Requirement 1.a. For aircraft that are operated 50% or more of their flights from gravel runways or other unpaved surfaces, accomplish within 10 flight cycles after
19 February 2007.

Requirement 1.b. For aircraft not affected by the Requirement 1.a. operation and that have not yet accumulated 50% of the applicable fatigue life time limit of flight cycles time in service since new, as established in the Dornier 228 Time Limits/Maintenance Checks Manual, accomplish within 1,200 flight cycles after 19 February 2007.

Requirement 1.c. For aircraft not affected by the Requirement 1.a. operation and that have already accumulated or exceeded 50% of the applicable fatigue life limit of flight cycles time in service since new, as established in the Dornier 228 Time Limits/Maintenance Checks Manual, accomplish within 100 flight cycles after
19 February 2007.

2.    Before further flight.

This Airworthiness Directive becomes effective on 19 February 2007.

Background:

During a maintenance inspection, cracks were detected on the centre section of fuselage frame 19.  Fuselage frame 19 supports the rear side of the main landing gear.  The investigation on the cause of the cracking is still in progress.  Such cracking, unless detected and corrected, could result in failure of frame 19, and subsequent collapse of a main landing gear.  The requirements of this Directive are considered to be an interim action.

David Villiers
Delegate of the Civil Aviation Safety Authority

9 February 2007