View image in the official source

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/SWSA226/90 Amdt 2 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.

View image in the official source

Fairchild (Swearingen) SA226 and SA227 Series Aeroplanes

AD/SWSA226/90

Amdt 3

Auto Ignition Systems 4/2003 TX

Model Serial Numbers

Aircraft Models Service Bulletin (Kit Drawing)

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 50 degrees F) or warmer.''

The procedures and conditions described in this Annex supersede any other POH/AFM procedures or conditions.

Fairchild Aircraft Models SA227-AC, SA227-AT and SA226-TT Aeroplanes Procedures to Prevent an Engine Flameout While in Icing Conditions

The IGNITION MODE switches shall be selected to OVERRIDE or, for those aircraft which have the auto-relite system installed, CONTINUOUS OR AUTO 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 50 degrees F) or warmer.''

The procedures and conditions described in this Annex supersede any other POH/AFM procedures or conditions.