STC SA02988NY

This certificate issued to

Part 3 of the Civil Air Regulations.

Installation of Pratt & Whitney Canada PT6A-34 or PT6A-35 Turboprop Engine and Hartzell HC-B3TN- 3(D)(Y)/T10282(N)(B,K)+4 propeller in accordance with Viking Air Limited Master Document Index VT3MK20000 Issue 3, dated Feb. 1, 2011, Transport Canada approved Feb. 3, 2011, or later Transport Canada approved revisions.

1. Maintenance must be in accordance with Viking Air Limited Instructions for Continued Airworthiness VT3MK20003, Rev A, 04 Jul 2008 and VT3MK20082, Rev IR, 01 Oct 2008 or later Transport Canada accepted revisions.

2. Operation must be in accordance with the Transport Canada Approved Viking Air Limited Airplane Flight Manual specified as follows:

Viking Air Limited 9574 Hampden Road Sidney, British Columbia Canada V8L 5V5

A-815 Make: de Havilland (Viking Air Limited) Model: DHC-3

Date of application: August 20, 2009

Date of issuance: July 18, 2011 Date reissued:

(Signature) Anthony Socias Manager New York Aircraft Certification Office

(Title)

FAA Form 8110-2-1(10-69) Page 2 of 3 Number SA02988NY

Configuration PWC PT6A-34 / -34AG PWC PT6A-35

1. Wheels / Skis AFM 041699.3 TCCA Approved 16 Dec 2008 or later Transport Canada approved revision.

AFM 041699.4 TCCA Approved 16 Dec 2008 or later Transport Canada approved revision.

2.Amphibious Floats AFM 041699.1 TCCA Approved 16 Dec 2008 or later Transport Canada approved revision.

AFM 041699.2 TCCA approved 16 Dec 2008 or later Transport Canada approved revision.

3.Seaplane Floats AFM 041699.5 TCCA Approved 03 Feb 2011 or later Transport Canada approved revision.

AFM 041699.6 TCCA Approved 03 Feb 2011 or later Transport Canada approved revision.

3. The maximum takeoff weight in the seaplane configuration is limited to 8000 lbs for US registered aircraft.

4. The following modifications are required to be installed concurrent with the installation of this STC:

For all configurations:

1. Viking Air Ltd. STC SA01243NY (Installation of Flutter Prevention Modification)

2. Viking Air Ltd. STC SA03000NY (Bleed Air heating system)

5. The following is mandatory for Configuration 3 (Seaplane Floats):

1. Viking Air Limited STC SA2009NY (DHC-3 9000 Pounds Aircraft Gross Weight Increase Modification) with the following exceptions: Items 1, 2, 3, 4, and 5 of SA02009NY as noted under Limitations and Conditions.

Items 6, 7 and 8 under Limitations and Conditions of SA2009NY call out required actions described in Tag Aerospace Report 037002-MMS, Maintenance Manual Supplement, Rev. A, dated May 4, 2007 and are required for this installation as is the installation of 8100 Floats installed per STC SA1995NY.

6. The following is optional for Configurations 1 & 2 (Wheels / Skis & Amphibious Floats):

1. Viking Air Limited STC SA2009NY (DHC-3 9000 Pounds Aircraft Gross Weight Increase Modification) with the following exceptions: Items 1, 2, 3, 4, and 5 of SA02009NY as noted under Limitations and Conditions.

Items 6, 7 and 8 under Limitations and Conditions of SA2009NY call out actions described in Tag Aerospace Report 037002-MMS, Maintenance Manual Supplement, Rev. A, dated May 4, 2007 and are required for this installation if the installer opts to install SA2009NY.

7. Basis of Certification Based on 14 CFR §§ 21.115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the Viking DHC-3 turbine engine conversion is as follows:

a. Type Certificate No. A-815 issued under CAR 10. (ICAO Annex 8, 2nd Edition (Transport Category D), and CAR 3 as amended to November 1, 1949 for parts not changed or not affected by the change.

FAA Form 8110-2-1(10-69) Page 3 of 3 Number SA02988NY

b. Title 14 CFR Part 23, dated February 1, 1965, including Amendments 23-1 through 23-55 for the change and all areas affected by the change. The following lists the Federal Aviation Regulations complied with through Amendment Level 23-55.

Subpart A – General: Sec. 23.1, 23.2, 23.3 Subpart B – Flight: Sec. 23.21 through 23.253 Subpart C – Structures: Sec. 23.301 through 23.572 Subpart D – Design & Construction: Sec. 23.601 through 23.867 Subpart E – Powerplant: Sec. 23.901 through 23.1193 Subpart F – Equipment: Sec. 23.1301 through 23.1431 Subpart G – Operating Limitations & Information: Sec. 23.1501 through 23.1589

c. The following lists the exceptions to compliance with Amendment 23-55 to the Federal Aviation Regulations.

CAR 3.124 - Spinning. In lieu of [Sec. 23.221(a)] CAR 3.445 - Fuel tank filler connection. In lieu of [Sec. 23.973(f)] CAR 3.655(a) - Flight and navigation instruments. In lieu of [Sec. 23.1303(e)] CAR 3.761 - Fuel quantity indicator. In lieu of [Sec. 23.1553]

d. Title 14 CFR Part 34, dated September 10, 1990, including Amendments 34-1 through 34-04 for the change and all areas affected by the change. The following lists the Federal Aviation Regulations complied with through Amendment Level 34-04.

All Sections except for Sec. 34.30 and Sec. 34.31.

e. Title 14 CFR Part 36, dated February 1, 1965, including Amendments 36-1 through 36-28 for the change and all areas affected by the change. The following lists the Federal Aviation Regulations complied with through Amendment Level 36-28.

Subpart A – General: Sec. 36.1, 36.2, 36.3, 36.5, 36.9 Subpart G – Propeller Driven Small Airplanes and Propeller-Driven, Commuter Category Airplanes: 36.501(c)

8. Compatibility of this design change with previously approved modifications must be determined by the installer.

9. If the holder agrees to permit another person to use the certificate to alter the product, the holder shall give the other person written evidence of that permission.

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