Document ID: chunk:federal_register_of_legislation:F2006B02152:body:0:p1
Version: federal_register_of_legislation:F2006B02152
Segment Type: other
Provision Reference: 
Character Range: 4–3044

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

    Twin Commander (Gulfstream/Rockwell/ Aerocommander 500, 600 and 700) Series Aeroplanes

                           AD/AC/91 Wing - Main Spar Lower Cap Forward Flange at Wing Station 96

               Applicability: MODEL SERIAL NUMBERS (Inclusive) 500  618 to 750
               560A 231 to 450

               560E 433 to 750

               680 242 to 658

               680E 623 to 750

               720 501 to 750

5/95

                 Requirement: 1.  Visually inspect for interference between the forward flange of the main spar lower cap and the outboard flange of the firewall assembly. Inspect in accordance with Twin Commander Service Bulletin (SB) 212, Accomplishment Instructions Part I.

                 2.        Inspect all aircraft, even those without interference, in the following order:

(a)     Remove a section of the wing to nacelle fairing at WS 96 in accordance with paragraphs a. and b. of Twin Commander SB 212, Accomplishment Instructions Part II.

(b)     Remove any interference in accordance with paragraphs c. and d. of Twin Commander SB 212, Accomplishment Instructions Part II.

(c)     Visually inspect the forward flange of the main spar lower cap for corrosion or other surface damage in the radius area.

(d)     Blend corroded or damaged areas with 180 grit abrasive paper, observing the precautions in the figure at the bottom of page 9 of Twin Commander SB 212.

(e)     Inspect the main spar lower cap for cracks using Fluorescent Dye Penetrant in accordance with Twin Commander SB 212, "Inspection Procedure".

(f)      If the spar cap is not cracked, polish any reworked area to a finish of 32RMS or smoother.

                    (g)     Repaint bared areas.

(h)     Repair the access hole in the nacelle in accordance with paragraphs k. to m. of Twin Commander SB 212, Accomplishment Instructions Part II.
 COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

           Note: Although this Directive is similar to FAA AD 94-04-15 and refers to Twin Commander SB 212, it is not identical to either. This Directive takes precedence.

           Compliance: Inspect in accordance with Requirements 1 and 2 before 50 hours' time in service from 27 April 1995, except as follows:

           If Part I of Twin Commander SB 212 was complied with before this Directive was issued on 27 April 1995, re-open the access hole in the nacelle and comply with Requirement 2 before 250 hours' time in service after 27 April 1995.

           If Parts I and II of Twin Commander SB 212 were complied with before this Directive was issued on 27 April 1995, further work may be required. Owners must contact the Authority for advice through their local District Office.

           Background: Two aircraft have been found with cracks caused by fatigue,