Document ID: chunk:federal_register_of_legislation:F2007L00566:body:0:p1
Version: federal_register_of_legislation:F2007L00566
Segment Type: other
Provision Reference: 
Character Range: 0–3036

AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/MU-2/65 and issues the following AD under subregulation 39.001(1) of CASR 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.

Mitsubishi MU-2 Series Aeroplanes
AD/MU-2/65 Amdt 1  Engine Torque Indication System  4/2007 DM

Applicability:  Model MU-2B, -10, -15, -20, -25 and -26 aeroplanes, serial number (S/N) 008 through 347 (except for S/N 313 and 321) and Model MU-2B-30, -35 and -36 aeroplanes S/N 501 through 696 (except S/N 652 and 661).
Requirement:       1. For MU-2B, -10, -15, -20 and -30 aeroplanes:
                     a. If not previously accomplished in accordance with the original issue of this Directive, inspect the torque indication system in accordance with Mitsubishi Heavy Industries (MHI) MU-2 Service Bulletin (SB) No. 233A dated
                     14 January 1999 or later revision approved by the Japan Civil Aviation Bureau (JCAB).
                     b. If, during the Requirement 1 inspection, the errors in the torque indication system are found to exceed the allowable limit specified in the SB, repair or replace the torque transmitter in accordance with the SB.
                   2. For MU-2B-25, -26, -35 and -36 aeroplanes:
                     a. If not previously accomplished in accordance with the original issue of this Directive, inspect the torquemeter in accordance with MHI SB No. 233A or later revision approved by the Japan Civil Aviation Bureau (JCAB).
                     b. If, during the Requirement 1 inspection, the errors in the torque indication system are found to exceed the allowable limit specified in the SB, repair or replace the torquemeter in accordance with the SB.
                     c. If not previously accomplished in accordance with the original issue of this Directive, inspect the torque transducer in accordance with MHI SB No. 233A or later revision approved by the Japan Civil Aviation Bureau (JCAB).
                     d. If, during the Requirement 3 inspection, the torque transducer output voltage is found to exceed the allowable limit specified in the SB, adjust the torque transducer output voltage in accordance with the SB.

                3. Accomplish a ground check of the engines in accordance with paragraph 3 of MHI SB No. 233A or later revision approved by the Japan Civil Aviation Bureau (JCAB).
             Note 1:  The holder of a Certificate of Registration of an Australian aircraft is required under Civil