Document ID: chunk:federal_register_of_legislation:F2006B04277:body:0:p1
Version: federal_register_of_legislation:F2006B04277
Segment Type: other
Provision Reference: 
Character Range: 4–3178

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

    Beechcraft 90 and 65-90 (King Air) Series Aeroplanes

AD/BEECH 90/94 Elevator Control Cable 7/99 DM

    Applicability: All Beech Models 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90,
               C90, C90A, E90, F90, and H90 aircraft.

    Requirement: 1. Accomplish the following:

                   1. Remove the pilot's seat and floor panels in the cockpit area on the pilot's side of the aircraft and inspect the entire area for interference or damage between the elevator control cable and equipment under the cockpit floor panels (wire harnesses, stainless steel clamps, etc).

b.   Run a cloth wrap around the control cable to detect broken strands of the control cable (refer 90 Series Maintenance Manual, Sections 5-20-00, 5-20-01, if applicable, and 20-04-00).

                 2.    Accomplish the following:

                   1. Replace or repair any damaged items found during the inspection and cloth wrap procedure specified in Requirement 1 of this Directive. This would include chafing damage and nicks, cuts, and broken strands on the control cable (refer 90 Series Maintenance Manual, Section 20-04-00, for criteria to determine if the cable needs to be replaced).

b.   Secure any component that is interfering with the elevator control cable and install additional supports and clamps as necessary to prevent sagging or further interference between the elevator control cables and equipment under the cockpit floor panels. Use best shop practices and Advisory Circular 43.13-1B as guides for installing the additional supports.

c.    Reinspect the elevator control cables in accordance with the procedures specified in Requirement 1 upon completion of any rework or replacement to assure that there is no interference.

                  d.    Re-install floor panels and pilot's seat.

               Note 1: Raytheon Safety Communique No. 143, dated October 1997, is not considered an alternative method of compliance to this Directive.

               Note 2: FAA Priority Letter AD 99-10-07 refers.

                 Compliance: 1. Upon accumulating 600 hours total time in service on the aircraft or within 10 hours' time in service after 9 June 1999, whichever occurs later.

               2. Before further flight after accomplishment of the Requirement 1 actions. This Airworthiness Directive becomes effective on 9 June 1999.
 COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

           Background: The FAA has received numerous reports of reduced or loss of elevator control on Beech Model 90 series aircraft. In one incident where elevator up control was only available, investigation revealed that the down elevator cable was severed due to chafing between the cable and the windshield de-ice circuit electrical wire. In another incident, the elevator down cable separated because of interference between the cable and the stainless steel clamp that joined two bleed