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/27 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/27 Amdt 1
Rudder Pedal Bars
Model R 2100, R 2100 A, R 2112, R 2120 U, R 2160, R 2160 D, and R 2160 I aircraft, serial numbers 1 through 250; and aircraft not fitted with reinforced rudder bars part number (P/N) 27.40.31.010 and P/N 27.40.31.020.
Model HR 200/100, HR 200/100S, HR 200/120, HR 200/120B, and HR 200/160 aircraft, serial numbers 1 through 250, and aircraft not fitted with reinforced rudder bars part number P/N 27.40.31.010 and P/N 27.40.31.020.
Note: This Directive is not applicable to Alpha Aviation Model R 2160 aircraft, serial number 160A-06001 and subsequent. These aircraft are fitted with reinforced rudder bars at manufacture.
1. For Model R 2000 series aircraft, replace the left rudder bar P/N 27.23.05.010 and the right rudder bar P/N 27.23.05.020 with reinforced rudder bars part number (P/N) 27.40.31.010 and P/N 27.40.31.020, in accordance with Avions Pierre Robin Service Bulletin (SB) No.143.
2. For Model HR 200 series aircraft, check the geometrical shape of both the rudder bars in accordance with SB No.143.
If distortion is detected, and found to be equal to or greater than 10mm, replace both rudder bars in accordance with SB No. 143.
Note 1: Reinforced rudder bars part number P/N 27.40.31.010 and P/N 27.40.31.020 have a flat welded reinforcing gusset on the right side and a bent welded reinforcing gusset on the left side.
Note 2: The installation of P/N 27.40.31.010 and P/N 27.40.31.020 rudder bars is terminating action to the requirement of this Directive.
Note 3: NZ CAA AD DCA/R2000/23A refers.
1. Within 50 hours time in service after 15 March 2007 or before 15 June 2007, whichever occurs first, unless already accomplished.
2. Within 100 hours time in service after 15 March 2007, unless already accomplished; and if distortion was detected and found to be less than 10mm, inspect thereafter at intervals not to exceed 500 hours time in service until both rudder bars are replaced with P/N 27.40.31.010 and P/N 27.40.31.020 rudder bars.
This Amendment becomes effective on 15 March 2007.
The manufacturer received a report of rudder bar distortion which occurred during intensive aerobatic operation.
Amendment 1 is issued in response to a NZ CAA AD, which was prompted by the new Type Certificate holder for the HR 200 and R 2000 series aircraft, Alpha Aviation, correcting the applicable aircraft serial number range and including a means of identifying reinforced rudder bars.
Delegate of the Civil Aviation Safety Authority
1 February 2007