Document ID: chunk:federal_register_of_legislation:F2006B03658:body:0:p1
Version: federal_register_of_legislation:F2006B03658
Segment Type: other
Provision Reference: 
Character Range: 4–3262

Beechcraft 1900 Series Aeroplanes

AIRWORTHINESS DIRECTIVE

    For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/BEECH 1900/4 Amdt 1 and issues the following 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.

    AD/BEECH 1900/4
    Amdt 2

    Engine Truss Assembly 1/2002

    Applicability: Model Serial Number

               1900 UA-2 and UA-3

               1900C UB-1 through UB-74 and UC-1 through UC-174 1900C UD-1 through UD-6
               1900D UE-1 through UE-302

                 Requirement: 1. If engine truss assembly part number (P/N) 129-910047-1, 129-910047-13, or 129-910047-17 (or FAA-approved equivalent part number) is not installed, accomplish the following:

                     1. Inspect the engine truss assembly for cracks in accordance with the Accomplishment Instructions in Raytheon Aircraft Mandatory Service Bulletin (MSB) No. 2255 Revision 10, Revised June 1999. If cracks are found, before further flight, replace with a part number truss specified in Requirement 1.b.

                    b.        Replace the engine truss assembly with a P/N 129-910047-1, 129-910047- 13, or 129-910047-17 assembly.

                 2.        For aircraft equipped with a P/N 129-910047-1 or 129-910047-13 engine truss assembly (of FAA-approved equivalent part number), inspect for linoil hole mislocation and cracks in Area A in accordance with Part I of the Accomplishment Instructions of MSB SB 71-3144 Revision 1, Revised April 1999. If any mislocated hole or crack is found, before further flight, replace the engine truss assembly.
 COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

3.        For aircraft equipped with a P/N 129-910047-1 or 129-910047-13 engine truss assembly, accomplish the following:

                  1. Inspect the engine cowling support bracket for cracks in accordance with Part III of the Accomplishment Instructions section of MSB SB 71-3144 Revision 1, Revised April 1999, and rework any cracked support bracket. If any cracked bracket is found, before further flight, accomplish any necessary engine cowling rework.

                 b.        Install Kit No. 129-9017-1 reinforcements on the engine cowling support bracket.

4.        For aircraft equipped with a P/N 129-910047-1 or 129-910047-13 engine truss assembly, replace all remaining linoil drive screws (those not in area A) in accordance with Part II of the Accomplishment Instructions section of MSB SB 71-3144 Revision 1, Revised April 1999.

5.        For aircraft equipped with a P/N 129-910047-1 or 910047-13 engine truss assembly, install a P/N 129-910047-15 truss identification placard