Document ID: chunk:federal_register_of_legislation:F2008L01342:body:0:p2
Version: federal_register_of_legislation:F2008L01342
Segment Type: other
Provision Reference: 
Character Range: 2793–5781

modification or the required wing spar lower cap replacement is done.  After each replacement, initially inspect upon reaching 3,500 total hours time in service on either wing spar lower cap, and repetitively inspect thereafter at intervals not to exceed 450 hours time in service until the wing spar centre splice joint modification or the required wing spar lower cap replacement is done.

   For all affected Models AT-300 and AT-301 aircraft with reciprocating engines, the 450-hour repetitive inspections required by this Directive are terminated after the wing spar centre splice joint modification is incorporated in accordance with Requirement 2.b. or when the wing lower spar caps are replaced.  The replacement specified in Requirement 2.c. is still applicable.

   If cracks are detected during any inspection required by this Directive, before further flight, replace the wing lower spar cap.

      2. Replace each wing lower spar cap in accordance with the applicable aircraft maintenance manual, as follows:

        a. For all affected Models AT-300 and AT-301 aircraft with reciprocating engines and that do not incorporate the wing spar centre splice joint modification:

        Upon reaching 5,000 total hours time in service on either wing spar lower cap or within 25 hours time in service after 7 May 2003 (the compliance time of the previous issue of this Directive), whichever occurs later.  Replace each time the safe life limit of 5,000 total hours time in service on either wing spar lower cap is reached.  After each replacement, inspect as specified in Requirement 1 until the wing spar centre splice joint modification or the required wing spar lower cap replacement is done.

        b. The safe life limit of the wing spar lower cap for aircraft specified in Requirement 2.a. may be extended to 7,000 hours time in service by incorporating the wing spar centre splice joint modification in accordance with Snow Engineering Co. Service Letter 55, revised 23 October 2002; or Snow Engineering Co. Service Letter 55, revised 4 October 2004; or later FAA approved revisions, with the following requirements:

           (i) This modification must be accomplished no earlier than 4,600 total hours time in service on the wing spar lower cap, and no later than 5,000 total hours time in service on the wing spar lower cap.

                     (ii) Immediately before incorporating the modification, accomplish an eddy-current inspection for cracks in accordance with Snow Engineering Co. Process Specification 197, revised 4 June 2002, or later FAA approved revision.

                     (iii) After each replacement, inspect as specified in Requirement 1 until the wing spar centre splice joint modification or the required wing spar lower cap replacement is done.

                  c. For all affected Models AT-300 and AT-301 aircraft with reciprocating engines that do incorporate the wing spar centre splice joint modification accomplished