AD/Ecureuil/128 Centre Windshield (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.

Eurocopter AS 350 (Ecureuil) Series Helicopters

AD/ECUREUIL/128 Centre Windshield 11/2007 TX

Applicability:

Model EC 130 B4 helicopters, all serial numbers.

Requirement:

1.    Visually inspect the centre windshield for cracks in accordance with paragraph 2.B.1 of Eurocopter EC130 B4 Alert Service Bulletin (ASB) No. 05A005 Revision 1.

Depending on the findings, the following is required:

2.    If a crack is detected, repair or replace the transparent panel in accordance with ASB No. 05A005 Revision 1, and the applicable Maintenance Manual.

3.    If no cracking is detected, and distortion of the transparent panel is detected during flight, accomplish paragraph 2.B.2 of ASB No. 05A005 Revision 1:

Immediately reduce the airspeed to 70 KIAS or below; and,

Before the next flight, install a placard on the instrument panel, in full view of the pilot, indicating the 70 KIAS airspeed limitation;

4.    If a crack is detected after distortion of the transparent panel has been detected during flight:

Replace the transparent panel with a serviceable part in accordance with ASB No. 05A005 Revision 1.

After replacement of the transparent panel, the airspeed limitation placard may be removed from the instrument panel.

5.    If no cracking is detected during pre-flight inspections after distortion of the transparent has been detected during flight, replace the transparent panel with a serviceable part in accordance with ASB No. 05A005 Revision 1.

Repair or replacement of the transparent panel with any spare part currently available does not constitute terminating action for the pre-flight inspection requirements of Requirement 1 of this Directive.

Note:  EASA Emergency AD 2007-0219-E refers.

Compliance:

1.    Before further flight after 28 August 2007, and thereafter before each flight.

2.    Before further flight.

3.    As specified in Requirement 3.

4.    Not later than the last flight of the day after detection.

5.    Within 50 flight hours or 15 days after detection, whichever occurs first.

This Directive shall be entered on the Maintenance Release as maintenance required. Requirements 1 and 3 may be performed and certified by the Pilot in Command who has been trained by an appropriately qualified person.  In this case, a copy of this Directive is to be carried in the aircraft.

If the helicopter must be returned to a location where the transparent panel can be repaired or replaced, the helicopter may be flown for a maximum of 10 flying hours at a maximum airspeed of 70 knots IAS, with operating crew only.

This Airworthiness Directive becomes effective on 28 August 2007.

Background:

The EASA received reports of in-flight failures of the centre windshield panel.  Investigation revealed failure was caused by crack initiation in the blending radius between the lower and upper sections of the windshield.

David Villiers
Delegate of the Civil Aviation Safety Authority

27 August 2007