Document ID: chunk:federal_register_of_legislation:F2006B04458:body:0:p1
Version: federal_register_of_legislation:F2006B04458
Segment Type: other
Provision Reference: 
Character Range: 4–3394

Bell Helicopter Textron Canada (BHTC) 206 and Agusta Bell 206 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 206/143 Amdt 2 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 206/143                          Tail Boom Skin                              5/2000
Amdt 3                                                                               DM
Applicability: Applies to the  following BHTC Model 206L series helicopters:
           Models              Serial Numbers
           206L                45004 through 45049, 45051 through 45153, and 46601
                               through 46617
           206L-1              45154 through 45790
           206L-3              51001 through 51612
           206L-4              52001 through 52163, 52165 through 52212, and 52214
                               through 52216

                 Requirement: 1. Perform a visual inspection of the tail boom in accordance with BHTC Alert Service Bulletin (ASB) 206L-98-114 or ASB 206L-98-114 Revision A.

                 2.    Accomplish the following:

                   1. Remove the upper and lower supports of the horizontal stabiliser in accordance with the applicable Maintenance Manual.

                  b.   In accordance with section 6.2 of Standard Practices Manual BHT-ALL-SPM, perform a one-time fluorescent penetrant inspection of the tail boom skin in the area at least 20 mm around the edges of the horizontal stabiliser openings.

                 3.    Remove the support plates and visually inspect the entire edge of the horizontal stabiliser opening on both sides of the tail boom for cracks, using a 10x magnifying glass.
 COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

           If any crack is found on the tail boom skin as a result of the above required inspections, replace the tail boom before further flight.

4.    Modify the tail boom in accordance with Parts I, II, and III of Alert Service Bulletin 206L-99-115 Revision D, dated 26 January 2000.

           Note: Transport Canada AD CF-98-42R3 refers.

             Compliance: 1. Unless the initial inspection is already accomplished, before further flight after 29 March 2000; thereafter, inspect before the first flight of each day in accordance with ASB 206L-98-114 Revision A.

2.    Unless already accomplished, before further flight after 29 March 2000.

3.    Within 100 hours time in service after 31 March 1999, and thereafter at intervals not to exceed 110 hours time in service.

4.    Before 31 December 2000, unless already accomplished.

           Compliance with Requirement 4 of this Directive constitutes terminating action for Requirements 1, 2, and 3.