AD/LC40/3 Amdt 1 - Rudder Hinges and Hinge Brackets

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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/LC40/3 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.
Columbia (formerly Lancair) LC40, LC41 and LC42 Series Aeroplanes

AD/LC40/3 Amdt 1
Rudder Hinges and Hinge Brackets
4/2010
 
Applicability:
Model 300 (LC40-550FG) aircraft, serial numbers 40001 through 40079.
Model 350 (LC42-550FG) aircraft, serial numbers 42001 through 42569, 421001 and subsequent.
Model 400 (LC41-550FG) aircraft, serial numbers 41001 through 41800, 411001 and subsequent.

Requirement:
1.    For aircraft with 25 hours time in service or more as of 15 May 2009:
Remove the rudder, and using 10x visual magnification, inspect all three rudder hinges and rudder hinge brackets for damage, i.e., cracking, deformation, and discolouration.
2.    For aircraft with less than 25 hours time in service as of 15 May 2009:
Without removing the rudder, visually inspect all three rudder hinges and rudder hinge brackets for damage.
Accomplishing the instructions of FAA Letter dated 19 November 2009 to Docket number FAA-2009-0395 grants an alternative method of compliance (AMOC), that allows for the installation of modification kit MK400-27-01 to terminate the requirements of FAA AD 2009-09-09 and this Directive (which was issued in response), and the required recurring inspections.  Notification to the FAA regarding parts order/delivery is not required.
Note 1:  FAA AD 2009-09-09 Amdt 39-15895 refers.
Note 2:  Cessna Aircraft Company Single Engine Service Bulletin SB09-27-01 Revision 1 and Revision 2 refer.

 
 
 
 
Compliance:
1.    Within 10 hours time in service or 30 days after 15 May 2009, whichever occurs first.
Inspect thereafter as follows:
At intervals not to exceed 25 hours time in service or 3 months, whichever occurs first, without removing the rudder, visually inspect all three rudder hinges and hinge brackets for damage.
At intervals not to exceed 50 hours time in service or 6 months, whichever occurs first, remove the rudder, and using 10x visual magnification, inspect all three rudder hinges and rudder hinge brackets for damage.
2.    Upon accumulating 25 hours time in service or within 10 hours time in service after 15 May 2009, whichever occurs later.
Inspect thereafter as follows:
At intervals not to exceed 25 hours time in service or 3 months, whichever occurs first, without removing the rudder, visually inspect all three rudder hinges and rudder hinge brackets for damage.
At intervals not to exceed 50 hours time in service or 6 months, whichever occurs first, remove the rudder, and using 10x visual magnification, inspect all three rudder hinges and rudder hinge brackets for damage.
The compliance times remain unchanged by this issue of the Directive.

 
This Amendment becomes effective on 24 February 2010.

Background:
The FAA received reports of cracked lower rudder hinge brackets on two of the affected aircraft.  Undetected damage in the rudder hinges and rudder hinge brackets could result in failure of the rudder, which could lead to loss of control.
Amendment 1 is issued to introduce an alternative method of compliance to the requirements of this Directive and the required recurring inspections.
The original issue of this AD became effective on 15 May 2009.

Mike Higgins
Delegate of the Civil Aviation Safety Authority
18 February 2010

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