Document ID: chunk:federal_register_of_legislation:F2006B04571:body:0:p1
Version: federal_register_of_legislation:F2006B04571
Segment Type: other
Provision Reference: 
Character Range: 4–3795

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
    SCHEDULE OF AIRWORTHINESS DIRECTIVES

    Bell Helicopter Textron 212 Series Helicopters

AIRWORTHINESS DIRECTIVE

    For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/BELL 212/4 Amdt 21 and issues the following AD under subregulation 39.1 (1) of CAR 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.

    AD/BELL 212/4
    Amdt 22

                                    Airworthiness Limitations  10/2000 TX

    Applicability: For Requirement 1: All Model 212 helicopters.

               For Requirement 2: Model 212 helicopters with main rotor mast, part number 204- 011-450-001, -007, -105, -113, or -119, or main rotor trunnion part number 204-011-
               105-001, or -103, installed.

                 Requirement: 1. Retire components from service at the times specified in the Mandatory Airworthiness Limitations Schedule, Section 4, of the Bell 212 Maintenance Manual (Revision 5 or later), with the following exceptions and additions:

Part Description                           Part Number       Retirement Life
Skid landing gear aft cross tube           205-050-400-035   500 hours
Skid landing gear aft cross tube           205-050-400-053   1000 hours
Drive link to rotating swashplate bolts    20-057-5-30D      500 hours
Float landing gear crosstube assembly    205-050-114-001     Not eligible for
                                         -003                service on
                                         -005                Australian
                                         -007                helicopters
                                         -009
                                         -011
                                         -013
                                         205-706-050-005
                                         -007
                                         -009
                                         -013

                 2. For the main rotor mast and trunnion, determine the accumulated Retirement Index Number (RIN), inspect and action in accordance with the technical requirements of FAA Emergency Airworthiness Directive 2000-15-52.

               Note: A copy of FAA AD 2000-15-52 may be obtained from the FAA Internet site http://av-info.faa.gov/ad or from the Authority.
 COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

 Compliance: For Requirement 1: At the times specified in the Requirement document.

            For Requirement 2: Before further flight after 9 August 2000 for paragraph (a) of the Requirement document, unless already accomplished. As specified in the Requirement document for compliance times of other required actions.

            This Amendment becomes effective on 9 August 2000.

            Background:  This Airworthiness Directive mandates life limits and inspections for critical components, to prevent their failure in service from metal fatigue.

            Amendment 22 is issued in response to a new FAA AD which was prompted by a report of another cracked main rotor mast. Metallurgical inspection revealed that the mast cracked as a result of fatigue in snap