Pursuant to subsection 5.9(2) of the Aeronautics Act, and after taking into account that the exemption is in the public interest and is not likely to affect aviation safety, I hereby exempt Erwin Aero International Ltd. (hereinafter “EAI”), Box 25, Site 5, RR#2, Airdrie, Alberta, Canada from the requirements set out in paragraph 513.07(1)(b) of the Airworthiness Manual made pursuant to section 513.07 of the Canadian Aviation Regulations, with respect to section 3.606 of the Civil Air Regulations, Part 3, dated May 15, 1956, including amendments 3-1 to 3-8 inclusive and section 21 of the Special Conditions for the Type Certification of Multiengine Turbine Powered Aircraft, dated November 6, 1964, subject to the conditions set out in this exemption.
The requirements of the above provisions are detailed in Appendix A to this exemption.
In this exemption:
Icing Conditions – means visible moisture conditions when the appropriate static or total air temperature is near or below freezing.
PURPOSE
The purpose of this exemption is to permit the removal of the engine inlet deflector system on the de Havilland Canada DHC-6 “Twin Otter” Models 100, 200 and 300 aeroplanes and issue the corresponding supplemental type certificate (STC) to EAI. The engine inlet deflector system is part of the original de Havilland Canada DHC-6 “Twin Otter” type design to show compliance with section 3.606 of U.S.Civil Air Regulations, Part 3 and section 21 of the Special Conditions for the Type Certification of Multiengine Turbine Powered Aircraft.
APPLICATION
This exemption applies to EAI only for the supplemental type certificate #SA07-97 which approves the removal of the engine inlet deflector system on the de Havilland Canada DHC-6 “Twin Otter” Models 100, 200 and 300 aeroplanes.
CONDITIONS
This exemption is subject to the following conditions:
Erwin Aero International Ltd. shall record the following Limitations in the de Havilland Canada DHC-6 “Twin Otter” Models 100, 200 and 300 Flight Manual:
- The aeroplane shall be limited to flight in Visual Meteorological Conditions (VMC);
- The aeroplane shall be limited to operations in Outside Air Temperatures (OAT) of +10°C or higher; (Note that this may limit the altitude of specific flights)
- The aeroplane shall not be flown into known or forecast icing conditions, or conditions of sand or dust;
- The aeroplane shall exit, at once, any conditions of inadvertent icing that are encountered; and
- The aeroplane shall be equipped with a functioning means of detecting visible moisture in flight prior to takeoff, for flight at night.
VALIDITY
This exemption shall be in effect until the earliest of:
- the date on which any condition set out in this exemption is breached; or
- the date on which this exemption is cancelled in writing by the Minister where he is of the opinion that it is no longer in the public interest or is likely to affect aviation safety.
DATED at Ottawa, Ontario, Canada this 27th day of September 2007, on behalf of the Minister of Transport, Infrastructure and Communities.
Original signed by Martin J. Eley
Martin J. Eley
Director, National Aircraft Certification
Civil Aviation
Appendix A
REGULATORY REQUIREMENTS
CANADIAN AVIATION REGULATIONS
Part V - Airworthiness
Subpart 13 – Approval of Modification and Repair Designs
Section 513.07 – Applicable Standards
513.07 (1) Subject to subsections (2) to (11), an applicant for a supplemental type certificate, a limited supplemental type certificate or a change to these certificates shall show that the changed aeronautical product meets
- the standards of airworthiness that are in force on the date of application for the proposed change…
…
(3) The changed aeronautical product may comply with an earlier amendment of a standard required under subsection (1) if the Minister determines that the proposed change is not significant in the context of all previous relevant design changes and the related amendments of the applicable standards recorded in the type certificate data sheets…
…
AIRWORTHINESS MANUAL
Chapter 513 – Approval of Modification and Repair Designs
Section 513.07 – Applicable Standards
(1) Pursuant to section 513.07 of the CARs, the standards of airworthiness that apply to a change in type design are:
…
(b) the equivalent standards from Part V of the CARs - if the existing certification basis consists of standards that are no longer accepted in Canada for a new type - unless the Minister allows continued compliance with the existing certification basis.
CIVIL AIR REGULATIONS
Part 3 – Airplane Airworthiness—Normal, Utility, Acrobatic and Restricted
Purpose Categories
Subpart E – Power-plant Installations; Reciprocating Engine
Section 3.606 – Induction System De-Icing and Anti-Icing Provisions
§ 3.606 Induction system de-icing and anti-icing provisions. The engine air induction system shall incorporate means for the prevention and elimination of ice accumulations in accordance with the provisions in this section. It shall be demonstrated that compliance with the provisions outlined in the following paragraphs can be accomplished when the airplane is operating in air at a temperature of 30°F, when the air is free of visible moisture.
- Airplanes equipped with sea level engines employing conventional venturi carburetors shall be provided with a preheater capable of providing a heat rise of 90°F, when the engine is operating at 75 percent of its maximum continuous power.
- Airplanes equipped with altitude engines employing conventional venturi carburetors shall be provided with a preheater capable of providing a heat rise of 120°F, when the engine is operating at 75 percent of its maximum continuous power.
- Airplanes equipped with altitude engines employing carburetors which embody features tending to reduce the possibility of ice formation shall be provided with a preheater capable of providing a heat rise of 100°F, when the engine is operating at 60 percent of its maximum continuous power. However, the preheater need not provide a heat rise in excess of 40°F, if a fluid de-icing system complying with the provisions of §§ 3.607-3.609 is also installed.
SPECIAL CONDITIONS FOR THE TYPE CERTIFICATION
OF MULTIENGINE TURBINE POWERED AIRCRAFT…
21. CAR 3.606 – Engine Ice Protection. Turbine powered aircraft shall be capable of operation throughout the flight power range without accumulation of ice in the air induction system such as to adversely affect engine operation or cause a serious loss of power and/or thrust, under icing conditions defined in CAR 4b.1(b)(7) and (8).
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- Date de modification :