Document ID: chunk:federal_register_of_legislation:F2006B04597:body:0:p2
Version: federal_register_of_legislation:F2006B04597
Segment Type: other
Provision Reference: 
Character Range: 2784–5398

each spar cap in accordance with Part II (C2), paragraphs 1 through 9, and 11 through 14 of ASB 212-00-110 Revision A.

Bell 212 Series Helicopters

 AD/BELL 212/64 (continued)

                 Before further flight, repair any loose fasteners or corrosion.

                 Before further flight, replace any cracked or disbonded spar cap with a serviceable spar cap.

              3.        Replace each affected spar cap with a cold expansion spar cap, P/N 212-030-447- 117S, in accordance with the Accomplishment Instructions, paragraphs 1 through 35, and 37, and Attachments A, B, and C of Bell Helicopter Textron Technical Bulletin No.212-00-184, Revision A, dated 23 April 2001.

           Note 1: This Directive does not apply to tailbooms with spar cap part number 212- 030-447-117 or 117S installed.

           Note 2: Replacement of each spar cap in accordance with the requirements of this Directive is terminating action for further compliance with this Directive.

           Note 3: FAA AD 2002-19-05 Amdt 39-12885 refers.

               Compliance: 1. Within 25 hours time in service after 30 October 2002, unless already accomplished. Thereafter at intervals not to exceed 8 hours time in service.

2.a.        Within 25 hours time in service after 30 October 2002, unless already accomplished. Thereafter, at intervals not to exceed 8 hours time in service.

2.b.       Within 50 hours time in service after 30 October 2002, unless already accomplished. Thereafter at intervals not to exceed 300 hours time in service.

2.c.        Within 50 hours time in service after 30 October 2002, unless already accomplished. Thereafter, fluorescent penetrant inspect at intervals not to exceed 300 hours time in service.

           3. Within 24 months after 30 October 2002.

           This Airworthiness Directive becomes effective on 30 October 2002.

Bell 212 Series Helicopters

 AD/BELL 212/64 (continued)

           Background: The FAA received reports of an accident and four failures of the vertical fin spar cap (spar cap) involving helicopters of the same type design. Fatigue cracks originated from the rivet holes in the area of fin station 60 to 75. Loose rivets, disbonding of the doublers and corrosion contributed to cracking of the spar cap. This Directive establishes additional inspection requirements for the spar cap, and eventual replacement of certain spar caps.

 David Alan Villiers
 Delegate of the Civil Aviation Safety Authority 24 October 2002

 The above AD is notified in the Commonwealth of Australia Gazette on 30 October 2002.