Document ID: chunk:federal_register_of_legislation:F2006B07233:body:0:p2
Version: federal_register_of_legislation:F2006B07233
Segment Type: other
Provision Reference: 
Character Range: 3099–6213

Aircraft SA226 and SA227 series aeroplanes, procedures for preventing an engine flameout while in icing conditions. CASA's predecessor did not issue an AD following the two earlier FAA ADs but required the insertion of Australian unique pages into the Australian AFM.

           The original issue of this Directive retained the AFM requirements from the earlier FAA ADs and also requires a modification to the torque sensing system to allow the igniters to automatically turn on when an engine senses low torque. These actions were intended to prevent a dual engine flameout on the affected aeroplanes by providing a system that automatically turns on the engine igniters when low torque is sensed. When the torque sensing system modification is incorporated, the AFM requirements are no longer necessary.

           Amendment 1 extended the compliance date for Requirements 2 and 3 by three months.

           Amendment 2 further extended the compliance date for Requirements 2 and 3 until 28 February 2003.

           This Amendment again further extends the compliance date for Requirements 2 and 3 until 30 June 2003.

           The original issue of this Airworthiness Directive became effective on 21 March 2002.

           Amendment 1 of this Airworthiness Directive became effective on 4 September 2002.

           Amendment 2 of this Airworthiness Directive became effective on 28 November 2002.

 James Coyne
 Delegate of the Civil Aviation Safety Authority 28 February 2003

 The above AD is notified in the Commonwealth of Australia Gazette on 28 February 2003.

AD/SWSA226/90
 Amdt 3

 Auto Ignition Systems - Annex A 4/2003

             Fairchild Aircraft Models SA226-AT, SA226-T, SA226-T(B) and SA226-TC Aeroplanes
          Procedures to Prevent an Engine Flameout While in Icing Conditions

 The IGNITION MODE switches shall be selected to AUTO/CONT during all operations in actual or potential icing conditions described herein:

          (1)  During takeoff and climb out in actual or potential icing conditions.

        *(2) When ice is visible on, or shedding from propeller(s), spinner(s), or leading edge(s).

        *(3) Before selecting ANTI-ICE, when ice has accumulated.

          (4)  Immediately, any time engine flameout occurs as a possible result of ice ingestion.

(5)  During approach and landing while in or shortly following flight in actual or potential icing conditions.

 *Note: If icing conditions are entered in flight without the engine anti- icing system having been selected, switch one ENGINE system to an ENGINE HEAT position. If the engine runs satisfactorily, switch the second ENGINE system to an ENGINE HEAT position and check that the second engine continues to run satisfactorily.

    For the purpose of this POH/AFM supplement, the following definition applies: "Potential icing conditions in precipitation or visible moisture meteorological conditions:
          (1)  Begin when the OAT is plus 5 degrees C (plus 41 degrees F) or colder, and

          (2)  End when the OAT is plus 10 degrees C (plus