Document ID: chunk:federal_register_of_legislation:F2006B04597:body:0:p1
Version: federal_register_of_legislation:F2006B04597
Segment Type: other
Provision Reference: 
Character Range: 0–3076

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 39.1 (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.

 Bell 212 Series Helicopters

                                                        AD/BELL 212/64 Vertical Fin Spar 13/2002 DM

           Applicability: Model 212 helicopters, with a vertical fin spar cap, part number (P/N) 212-030-125- 001, with retrofit kit, P/N 212-704-087 installed; vertical fin left- hand spar cap (spar cap), P/N 212-030-125-001, without the retrofit kit installed; or spar cap, P/N 212- 030-447-001 or P/N 212-030-447-101, installed.

              Requirement: 1. Modify and visually inspect each spar cap, P/N 212-030-125-001, not modified by retrofit kit, P/N 212-704-087 or spar cap P/N 212-030-447-001, for a crack, loose fasteners, or corrosion in accordance with Part I (A1), paragraphs 1, 2, 3, 4, 6, and 7 of Bell Helicopter Textron Alert Service Bulletin (ASB) No. 212-00-110 Revision A, dated 15 February 2001. Thereafter, visually inspect each affected spar cap in accordance with Part I (A2), paragraphs 1, 2, 3, 5, and 6 of ASB 212-
              00-110 Revision A.

              Before further flight, repair any loose fastener or corrosion.

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

              2.        For each spar cap, P/N 212-030-125-001, modified by retrofit kit, P/N 212-704- 087, or spar cap, P/N 212-030-447-101:

                  1. Modify and inspect each spar cap for a crack, loose fastener, corrosion, or disbanding in accordance with Part II (A1), paragraphs 1, 2, 3, 4, 5, 7, 8, 9, and 10 of ASB 212-00-110 Revision A. Thereafter, visually inspect each affected spar cap in accordance with Part II (A2), paragraphs 1, 2, 3, 5, and 6 of ASB 212-00-110 Revision A.

                 b.         Inspect each spar cap for disbonding using a hammer in accordance with Part II (B), paragraphs 1 through 13 of ASB 212-00-110 Revision A.

                 c.         Modify the vertical fin, and fluorescent penetrant inspect each spar cap in accordance with Part II (C1), paragraphs 1 through 8, and 10 through 12 of ASB 212-00-110 Revision A. Thereafter, fluorescent penetrant inspect 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