Federal Register of Legislation - Australian Government

Primary content

AD/EC 135/12 Amdt 1 Airworthiness Directives/Pt 105 — Aircraft as made
Tail Rotor Control - Linear Transducer Bearing; Rod & Floor
Administered by: Infrastructure and Regional Development
Exempt from sunsetting by the Legislation (Exemptions and Other Matters) Regulation 2015 s12 item 15
Registered 16 May 2007
Tabling HistoryDate
Tabled HR21-May-2007
Tabled Senate12-Jun-2007
Date of repeal 05 May 2017
Repealed by CASA ADCX 007/17 - Repeal of Airworthiness Directives

 

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/EC 135/12 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.

Eurocopter EC 135 Series Helicopters

AD/EC 135/12 Amdt 1

Tail Rotor Control - Linear
Transducer Bearing; Rod & Floor

6/2007

 

Applicability:

EC 135 helicopters, all models, having the following components installed:

Bearing Part Number (P/N) LN9367GE6N2,

Rod P/N L671M5040205,

Lever P/N L671M5040101 and

Floor P/N L533M1014101, L533M1014102, L533M1014103, L533M1014104, L533M1014105 or L533M1014106

Requirement:

1.    Inspect the affected bearing and modify the floor in accordance with the instructions of Eurocopter Deutschland (ECD) Alert Service Bulletin (ASB) EC135-67A-012 Revision 1 dated 18 October 2006 or later LBA approved revision.

2.    If there is binding and/or abrasion on the floor, replace the bearing in accordance with ECD ASB EC135-67A-012 Revision 1 or later LBA approved revision.

3.    Modify the rod in accordance with ECD ASB EC135-67A-012 Revision 1 or later LBA approved revision.

4.    Repeat the inspection of the affected bearing as required by Requirement 1 of this Directive and carry out any rectification as detailed in Requirement 2 of this AD.

5.    Do not install any of the parts listed in the Applicability section of this AD into a helicopter, unless they have been modified in accordance with ECD ASB
EC135-67A-012 Revision 1 or later LBA approved revision.

Note:  EASA AD 2006-0318R1 dated 27 October 2006 refers.

Compliance:

1.    Remains unchanged as, no later than 7 November 2006.

2.    Before further flight after the effective date of this AD.

3.    Not later than at the next scheduled inspection (800 flight hours) after the effective date of this AD.

 

 

4.    At intervals not to exceed 800 flight hours.

5.    From the effective date of this AD.

 

This Amendment becomes effective on 7 June 2007.

Background:

EASA has been informed of an incident in which impaired controllability of the EC 135 tail rotor was detected.  Examinations have shown that the bearing of the linear transducer was subject to binding and the control range was limited.

Amendment 1 clarifies the modification requirements.

The original issue of this AD become effective on 27 October 2006.


David Punshon
Delegate of the Civil Aviation Safety Authority

26 April 2007