Document ID: chunk:federal_register_of_legislation:F2006B04026:body:0
Version: federal_register_of_legislation:F2006B04026
Segment Type: other
Provision Reference: 
Character Range: 0–2313

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

 Beechcraft 55, 58 and 95-55 (Baron) Series Aeroplanes

 AD/BEECH 55/80
 Amdt 1

 Cabin Window Lower and Upper Longerons 11/97

            Applicability: Models 58P and 58PA aircraft having serial numbers listed in Beechcraft (Beech) Service Bulletin (SB) 2630 or Raytheon SB 2691 Revision 1.

            Note: Revision 1 of Raytheon SB 2691 was issued to add serial numbers that were inadvertently omitted from the original issue (now TJ-2 through TJ-121).

 Requirement: 1. For aircraft applicable to Raytheon SB 2691 Revision 1:

             Inspect and reinforce in accordance with Raytheon Aircraft Mandatory SB 2691.

             2.    For aircraft applicable to Beech SB 2630:

             Inspect the cabin window upper longeron (next to the upper aft splice) between the second and third right hand cabin side windows for cracks and missing rivets in accordance with the Accomplishment Instructions section of Beech SB 2630:

                1. If cracks are found in the upper longeron, repair the cracks in accordance with the Accomplishment Instructions section of Beech SB 2630.

b.   If rivets are found missing, install the rivets in accordance with the Accomplishment Instructions section of Beech SB 2630.

            Note: FAA AD 97-09-09 Amdt 39-10005 refers.

 Compliance: 1. Within 100 hours' time in service after 5 December 1996.

             2. Unless already accomplished, within 100 hours' time in service after 9 October 1997.

            The compliance of the initial issue of this Directive remains unchanged as Compliance 1 of this issue.

            Background: The FAA received reports of cracks in the upper and lower longeron near the second right hand cabin window, and missing rivets that are supposed to secure the frame, splice, and longeron together. The actions specified by this Directive are intended to prevent structural cracking to the cabin, which could result in structural failure of the fuselage and loss of the aircraft.

            Amendment 1 is issued in response a new FAA AD which combines the requirements of the initial issue of this Directive with additional requirements at the same location.