STC SA3777NM

Number SA3777NM This certificate, issued to Vazar, Inc.

3025 Eldridge Ave.

Bellingham, WA 98225

Part 3 of the Civil Air Regulations.

Original Product⎯Type Certificate Number: A-815 Make: Bombardier (de Havilland) Model: DHC-3 (Otter) Description of the Type Design Change: Installation of a Pratt and Whitney PT6A-34, -34AG, -135, or -135A turbine engine, Hartzell propeller on the landplane or the seaplane equipped with Edo 7490 or 7170 floats.

These modifications are to be performed in accordance with the data listed below or later FAA approved revisions.

PT6A Engine Installation SA-MDL-020987 Revision R, dated 11/8/04 Installation Instructions SAIP-021087 Revision E, dated 8/26/04 Edo 7490 Amphibious Floats Installation Drawing 23300 Revision Cb, dated 4/9/57 Edo 7170 Seaplane Floats Installation Drawing 12700 Revision Ca, dated 1/11/57

(See Limitations and Conditions for Approved Combinations.)

Limitations and Conditions: Approval of this change in type design applies to the above model aircraft only. This approval should not be extended to aircraft on which other previously approved modifications are incorporated unless it is determined that the relationship between this change and any of those other previously approved modifications, including changes in type design, will introduce no adverse effect upon the airworthiness of that aircraft. A copy of this Certificate and the Airplane Flight Manual Supplement (AFMS) Report 041288, Revision J, dated January 24, 2005, or later FAA approved revision, must be maintained as part of the permanent records for the modified aircraft.

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

(See Continuation Sheets for additional Limitations and Conditions.)

Date of application: March 27, 1986 Date reissued: December 15, 1995; May 15, 2003 Date of issuance: June 2, 1988 Date amended: April 23, 1993; August 9, 1996;

June 14, 2002; May 15, 2003;

January 31, 2005; July 12, 2005

(Signature) Acting Manager, Seattle Aircraft Certif nicatio Office (Title)

Number SA3777NM

Vazar, Inc.

Reissued: December 15, 1995; May 15, 2003 Amended: April 23, 1993; August 9, 1996;

June 14, 2002; May 15, 2003; January 31, 2005; July 12, 2005

The conditions and limitations of Aircraft Specification No. A-815 apply except as follows:

This Addendum, which is part of Supplemental Type Certificate No. SA3777NM, prescribes conditions and limitations under which the product for which the STC was issued meets the airworthiness requirements of the Civil Air Regulations. A copy of this addendum shall be maintained as part of the modified aircraft's permanent records.

Supplemental Type Certificate Holder: Vazar, Inc.

Landplane:

Engine: Pratt and Whitney PT6A-135, -135A Propeller: HC-B3TN-3D/T10282 or HC-B3TN-3D/T10282+4 or HC-B3TN-3AEY/T10290+2

Engine: Pratt and Whitney PT6A-34, -34AG Propeller: HC-B3TN-3D/T10282 or HC-B3TN-3D/T10282+4

Airspeed Limits (CAS):

(mph) (knots) Maximum Operating Limit Speed VMO 147 128 Maneuvering Speed VA 129 112 Flap Extended Speed VFE 95 83

Seaplane/Skiplane:

Engine: Pratt and Whitney PT6A-135, -135A Propeller: HC-B3TN-3D/T10282 or HC-B3TN-3D/T10282+4 or HC-B3TN-3AEY/T0290+2 Floats: Edo 7170 Straight Floats, Edo 7490 Amphibious Floats Skis: Wheeled Ski Installation per TCDS A-818 Misc. Item 300

Engine: Pratt and Whitney PT6A-34, -34AG Propeller: HC-B3TN-3D/T10282 or HC-B3TN-3D/T10282+4 Floats: Edo 7170 Straight Floats, Edo 7490 Amphibious Floats Skis: Wheeled Ski Installation per TCDS A-818 Misc. Item 300

Airspeed Limits (CAS):

(mph) (knots) Maximum Operating Limit Speed VMO 137 119 Maneuvering Speed VA 129 112 Flap Extended Speed VFE 95 83

FAA FORM 8110-2- 1 (10-69) PAGE 3 OF 7 PAGES

Number SA3777NM

Vazar, Inc.

Reissued: December 15, 1995; May 15, 2003 Amended: April 23, 1993; August 9, 1996;

June 14, 2002; May 15, 2003; January 31, 2005; July 12, 2005

Data Pertaining to Landplane and Seaplane

Engine Operating Limits:

PT6-135/-135A Shaft Horsepower HP Gas Generator RPM - Ng % RPM Indicated Torque PSI Prop Shaft Speed - Np RPM Max ITT °C

Take Off 750 101.5 59.1 1900 805

Max Continuous 750 101.5 59.1 1900 805

Starting --- 102.6 --- --- 1090

Momentary (2 sec)

102.6 68.2 2090 880

PT6-34/-34AG Shaft Horsepower HP Gas Generator RPM - Ng % RPM Indicated Torque PSI Prop Shaft Speed - Np RPM Max ITT °C

Take Off 750 101.6 58.7 2200 790

Max Continuous 750 101.6 58.7 2200 790

Starting --- --- --- --- 1090

Momentary (2 sec)

102.6 68.4 2420 850

Fuel: JP5 (MIL-T-5624), Jet A or Jet A-1 conforming to Pratt & Whitney SB 1244 or ASTM-F1655. Anti-icing additive per MIL-SPEC 127686E or 3GP-526A must be blended into aircraft fuel in concentrations not less than 0.06 percent or more than

0.15 percent.

Oil: See Pratt & Whitney PT6 Engine Service Bulletin Nos. 1001, 3001, 4001, and 12001 for approved brand oils.

Oil Capacity: 18 qts (6 qts usable)

FAA FORM 8110-2- 1 (10-69) PAGE 4 OF 7 PAGES

Number SA3777NM

Vazar, Inc.

Reissued: December 15, 1995; May 15, 2003 Amended: April 23, 1993; August 9, 1996;

June 14, 2002; May 15, 2003; January 31, 2005; July 12, 2005

Propeller and Propeller Limits: HC-B3TN-3DY/T10282 HC-B3TN-3DY/T10282+4 HC-B3TN-3AEY/T10290N+2

Diameter: 100.5 to 102.5 inches 100.5 to 106.0 inches 100.0 to 104.0 inches Blade Angle Limits:

30.0 inch blade station 30.0 inch blade station 42.0 inch blade station Feather 87° ± 1.0° 8 7° ± 1.0° 78° ± 1.0° Low Pitch 21° ± 0.1° 2 1° ± 0.1° 12° ± 0.1° Reverse –15° ± 0.5° –15 ° ± 0.5° -16° ± 0.5° Governor: Woodward 210632 Woodward 210632 Woodward 210632 Spinner: Hartzell 8203065-1P Hartzell 8203065-1P Hartzell 8203065-1P

Control Surface Movements:

Flaps: Inboard Leading Edge Down 24° ± 2° Inboard Trailing Edge Down 45° ± 2° Outboard Leading Edge Down 18° ± 2°

Maximum Operating Altitude: 16,000 feet

Certification Basis: CAR 3 as amended to November 1, 1949

The following requirements are added to apply to the airplane equipped with the turbo-prop engine and to introduce equivalent or higher levels of safety than those of the basic airplane.

23.45 23.49 23.51 23.65 23.75 23.77

23.251 23.253 23.335 23.361 23.363 23.371

23.629 (e, f) 23.901 23.903 23.905 23.907 23.925

23.929 23.933 23.937 23.939 23.943 23.951

23.954 23.955 23.957 23.959 23.961 23.977

23.991 23.997 23.1013 23.1017 23.1019 23.1027

23.1041 23.1045 23.1091 23.1093 23.1103 23.1111

23.1121 23.1123 23.1141 23.1143 23.1145 23.1153

23.1155 23.1163 23.1165 23.1182 23.1183 23.1189

23.1191 23.1193 23.1301 23.1303 23.1307 23.1309

23.1321 23.1322 23.1323 23.1331 23.1337 23.1351

23.1353 23.1357 23.1416 23.1419 23.1461 23.1501

23.1505 23.1521 23.1527 23.1529 23.1545 23.1549

23.1557 23.1581 23.1583 23.1585 23.1587 23.1589 of FAR 23, dated November 2, 1984, including Amendments 23-1 through 23-31.

Special Federal Aviation Regulation 27, as amended by 27–1 and 27–2.

FAA FORM 8110-2- 1 (10-69) PAGE 5 OF 7 PAGES United States of America Department of Transportation_Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet)

Number SA3777NM

Vazar, Inc.

Reissued: December 15, 1995; May 15, 2003 Amended: April 23, 1993; August 9, 1996;

June 14, 2002; May 15, 2003; January 31, 2005; July 12, 2005

Addendum to Notes, Aircraft Specification No. A-815

NOTE 2. The following placards must be displayed as noted:

(d) At the appropriate fuel tank filler openings:

"Fuel 50, 61, or 102 U.S. Gal. Cap.

JET A, JET A-1, JP-5"

(e) At the Oil tank filler opening:

"Approved oils - DO NOT MIX BRANDS Oil System Capacity 18 qts"

(f) On EPA can door:

"EPA DRAIN and PROPERLY DISPOSE OF"

(g) At the flap position indicator:

"CRUISE" "TAKEOFF"

(h) On the instrument panel in clear view of the pilot:

Landplane:

"WARNING: DO NOT USE REVERSE POWER IN FLIGHT. AT HIGH TAXI SPEEDS

USE REVERSE POWER ONLY IF TAIL WHEEL IS LOCKED AND HELD FIRMLY ON THE GROUND"

Seaplane:

"WARNING: DO NOT USE REVERSE POWER IN FLIGHT"

NOTE 5. Compliance with FAR 36, Appendix F, was shown for the landplane with PT6A-135/-135A engine, with the following procedures:

Level fly over at 1000 ft AGL at 1900 propeller RPM.

The certified noise level is 76.0 dB(A). This noise level reflects correction of “as measured” data to a standard 77°F, 70% R.H. acoustic day as well as a 0.3 dB(A) credit resulting from aircraft takeoff and climb characteristics. The related airplane gross weight is 8000 lb. and the FAR 36 limit is 80.0 dB(A).

No determination has been made by the Federal Aviation Administration that the noise level of this airplane is or should be acceptable or unacceptable for operation at, into, or out of any airport.

FAA FORM 8110-2- 1 (10-69) PAGE 6 OF 7 PAGES United States of America Department of Transportation_Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet)

Number SA3777NM

Vazar, Inc.

Reissued: December 15, 1995; May 15, 2003 Amended: April 23, 1993; August 9, 1996;

June 14, 2002; May 15, 2003; January 31, 2005; July 12, 2005

NOTE 6. The corrected noise level of this airplane is 84.0 dB determined by flight tests when operated at Maximum Continuous Power (64.5 psi Torque and 2000 RPM). No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable for operation at, into, or out of any airport.

The above statement notwithstanding, the noise level stated above has been verified by and approved by the Federal Aviation Administration in noise level test flights conducted in accordance with FAR Part 36, Appendix G, Amendment 22, Noise Standards: Airplane Type and Airworthiness Certification. The airplane noise is in compliance with all FAR Part 36 noise standards applicable to this type.

NOTE 7. This STC has been found to be compatible with the combination of the Edo 7850 float installation and the Baron STOL kit installed per STC SA00287NY.

NOTE 8. This STC has been found to be compatible with the installation of the Wipaire Wipline 8000 amphibian or seaplane floats.

NOTE 9. This STC shall not be extended to other float installations without an evaluation of the flight, ground, and water handling characteristics

NOTE 10. This STC is found to be compatible with the combination of new elevator servo-tab and redundant control linkage kit per STC SA01059SE.

- END -

FAA FORM 8110-2- 1 (10-69) PAGE 7 OF 7 PAGES