AD/ROBIN/40 Amdt 1 - Nose Landing Gear Bracket

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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/ROBIN/40 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.
Robin Aviation Series Aeroplanes
AD/ROBIN/40 Amdt 1
Nose Landing Gear Bracket
23/2010
 
Applicability:
Model R 2100, R 2100 A, R 2112, R 2120 U, and R 2160 D aircraft, serial numbers 001 through 378.
Model R 2160 aircraft, serial numbers 001 through 378, and serial numbers
160A-06001 and subsequent.
Model R 2160i aircraft, serial numbers 001 through 378, and serial numbers
160Ai-07007 and subsequent.

Requirement:
Action in accordance with Avions Pierre Robin Service Bulletin (SB) No. 101 Revision 3.
Note:  NZ CAA AD DCA/R2000/15A refers.

Compliance:
Compliance times remain unchanged from 17 January 2008.
For support plates with a width of less than 84mm:
Within 100 hours time in service after 17 January 2008, unless already accomplished within the last 100 hours time in service.  If no cracking is detected, inspect thereafter at intervals not to exceed 100 hours time in service.
If cracks are detected, determine the crack dimensions in accordance with SB No. 101 Revision 3.
If cracks are within the allowable criteria of SB No. 101 Revision 3, inspect at intervals not to exceed 25 hours time in service.
If cracks are outside the allowable criteria of SB No. 101 Revision 3, before further flight, accomplish an approved manufacturer repair, in accordance with SB No. 101 Revision 3.
For support plates with a width of 84mm:
Within 500 hours time in service after 17 January 2008, unless already accomplished within the last 500 hours time in service.  If no cracking is detected, inspect thereafter at intervals not to exceed 500 hours time in service.

 
If cracks are detected, determine the crack dimensions in accordance with SB
No. 101 Revision 3.
If cracks are within the allowable criteria of SB No. 101 Revision 3, inspect at intervals not to exceed 25 hours time in service.
If cracks are outside the allowable criteria of SB No. 101 Revision 3, before further flight, accomplish an approved manufacturer repair, in accordance with SB No. 101 Revision 3.
This Airworthiness Directive becomes effective on 19 November 2010.

Background:
The manufacturer received reports of cracking of the weld securing the nose wheel steering bracket to the nose landing gear leg.
This Directive was issued in response to the related NZ CAA Directive which was issued as a result of Alpha Aviation becoming the Type Certificate holder for Model HR 200 and Model R 2000 series aircraft.  The requirements of this Directive were previously contained in AD/ROBIN/7 Amdt 2.
Amendment 1 of this AD has been raised as a result of EASA cancelling DGAC AD F-1983-206(A)R3 and issuing EASA AD 2010-0231.  This amendment removes reference to being applicable to Model HR 200/100, HR 200/100S, HR 200/120, HR 200/120B, and HR 200/160 aircraft, serial numbers 001 through 378, which are now covered by EASA AD 2010-0231.

Mike Higgins
Delegate of the Civil Aviation Safety Authority
9 November 2010

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