Document ID: chunk:federal_register_of_legislation:F2006B11118:body:0:p2
Version: federal_register_of_legislation:F2006B11118
Segment Type: other
Provision Reference: 
Character Range: 2890–4616

4.

 Gates Learjet 35 and 36 Series Aeroplanes

 AD/LEARJET 35/39 (continued)

              4.         Modification of the shear webs by accomplishing all the actions specified in the Accomplishment Instructions of SB 35/36-51-4 Revision 1 or Revision 2; terminates the initial inspections required by Requirement 1 and the repetitive inspections required by Requirement 2.a.

            Note 1: Where any service bulletin identified in this Directive specifies that the manufacturer may be contacted for disposition of certain repair conditions, repair per a method approved by the Manager, Wichita ACO, FAA.

            Note 2: FAA AD 2004-03-08 Amdt 39-13452 refers.

 Compliance: 1. At the later of the following times:

                  1. Before the accumulation of 3,000 total flight hours; or,

b.        Within 1,200 flight hours or 1 year after 13 May 2004, whichever occurs first.

              2.         a. At intervals not to exceed 1,200 flight hours.

b.        Within the next 1,200 flight hours.

c.         Before further flight.

              3.         At the times specified in the Requirement document.

              a. Before further flight.

              4.         Terminates Requirements 1 and 2.a. inspections.

            This Airworthiness Directive becomes effective on 13 May 2004.

            Background: The manufacturer has received reports that the forward engine beam shear webs may develop cracks. The structural integrity of the engine beam shear web may be compromised depending upon the severity of the crack.

 David Villiers
 Delegate of the Civil Aviation Safety Authority 2 April 2004

 The above AD is notified in the Commonwealth of Australia Gazette on 21 April 2004.