AD/Convair/2 Elevator and Rudder Hinge Pins and Bushings (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.

Kelowna Flightcraft (General Dynamics/Convair) Series Aeroplanes

AD/CONVAIR/2 Elevator and Rudder Hinge Pins and Bushings 5/2006

Applicability:

All model 340, 440, and all such model aircraft converted to turbopropeller power.

Requirement:

1.    Remove the elevators and rudder in accordance with Parts 2.A.1. and 2.B.1., respectively, of the Accomplishment Instructions of General Dynamics, Convair Division, Alert Service Bulletin 640 (340D) A55-7.  Perform a detailed visual inspection of the elevator and rudder hinge pins and bushings to detect wear in accordance with the procedures described in Part 2.B. of the Accomplishment Instructions of Service Bulletin 640 (340D) 55-5; and perform a detailed visual inspection of the elevator and rudder bearing plate assemblies to detect cracks and of the elevator and rudder bearings to detect chattering, looseness, dryness, or binding in accordance with Parts 2.A. and 2.B. of the Accomplishment Instructions of Alert Service Bulletin 640 (340D) A55-7.

If any cracked bearing plate assembly, worn pin or bushing, or defective bearing is found during any inspection, before further flight, replace with serviceable part(s) in accordance with the applicable Service Bulletin.

2.    Perform a hardness test to determine the equivalent strength of the elevator and rudder hinge pins and bushings in accordance with normal maintenance procedures.  If the equivalent strength of any pin or bushing does not meet the type design strength specified below in sub paragraphs 2.a or 2.b. of this requirement, as applicable, replace the discrepant pin or bushing with serviceable parts in accordance with Part 2.A. or 2.B. of the Accomplishment Instructions of Alert Service Bulletin 640 (340D) A55-7.

Elevator and rudder hinge pins and bushings received directly from Convair that bear the Convair mark are excluded from this requirement.  The Convair mark is an etched mark, which appears as follows, and is located on the top of the hinge pin and on the top of the bushing:   CV
  SD

(a)   For aircraft having pin assembly 240-2010908-1, the pins and bushings must meet type design strengths specified as follows:

Part                    Part number   Type Design Strength

Pin   GD/Convair 240-2010904                170-195 ksi

Bushing              GD/Convair 240-2010903-7            120-145 ksi

(b)   For aircraft having pin assembly 240-2010908-3, the pins and bushings must meet type design strengths specified as follows:

Pin   GD/Convair 240-2010904                170-195 ksi

Bushing              GD/Convair 340-2015903                125-145 ksi

Bushing              Allison 9015192   125-145 ksi

3.    Reinstall the elevator and rudder, and ensure that proper mating of the pin and bushing tapered surfaces exists in accordance with Parts 2.A.5. and 2.B.5.of the Accomplishment Instructions of Alert Service Bulletin 640 (340D) A55-7.

4.    Repeat Requirements 1 and 3 in accordance with Item 55-2-9 of General Dynamics, Convair Division , “Supplemental Inspection Document, Model 340/440”, Report No. ZS-34-1000, Revision 1, dated April 15, 1991, including Addenda I, II, and III, all dated April 15, 1991.

Note 1:  Requirement 4 of this Directive restates a requirement for repetitive actions contained in FAA AD 92-06-06.  Accomplishment of Requirements 1 and 3 of this Directive satisfies the corresponding requirements contained in AD 92-06-06.

Note 2:  FAA AD 93-24-06 Amdt 39-8755 refers.

Compliance:

1, 2, and 3.    Unless the initial requirements are already accomplished, before
30 June 2006.

4.    Within 2,000 hours or 2 years after previous compliance, and thereafter at intervals not to exceed 2,000 hours time in service or 2 years, whichever occurs first.

This Airworthiness Directive becomes effective on 11 May 2006.

Background:

The FAA requires certain inspections to prevent the loss of an elevator or rudder, resulting from the installation of a suspected unapproved part.

David Villiers
Delegate of the Civil Aviation Safety Authority

29 March 2006