STC SA3989WE

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SA3989WE This certificate issued to: & Basil Mikhalkin Part Ad sf the CIVIl Air Regulations:

Original Product -Type Certificate Number: 116 Make: Bellanca Model: 14-9, Serial No. 1029 dated March 8, 1977, revised January 9, 1979, revised July 4, 1979. Hartzell HC-C2YK-1BF/F7666A propeller and associated installation components in accordance with Description of Change to Bellanca 14-9, N130E for Instal- lation of Lycoming Engine 0-350-A1D and a Hartzell Constant Speed Propeller, Description of Type Design Change: Installation of Lycoming 0-360-AID engine, Phen cereal interesue recy ds, for this modified aireralahull remain in fied undid ser- N130E for Installation of Lycoming Engine 0-360-A1D and a Hartzell Constant Speed Propeller, dated March 8, 1977, shail be maintained as part of the Limituliandfundilina: Data pertaining to this modification are considered cate. A copy of this certificate and Description of Change to Bellanca 14-9, Supplemental Type Certificate Addendum No. SA3989WE is a part of this certifi- inadequate for duplication in other aircraft. This approval is limited to the installation made in Bellanca Model 14-9, Serial No. 1029, only.

rendered, suspended, revked, or a lermination dale is dhorwise estuldished by the SIdministrater of the Federal Aviation Administration .

Date of Application: September 27, 1976 Date Reissued:

Date of Issuance: July 5, 1979 I ate ume naal:

FEDERAL AVIATIO By Direction of the Administrator TOMINIST PATO GR Jolenam (Signature;

Chief, Aircraft Modification Branch

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rited Soute of Beerice Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA3989WE Make: July 5, 1979 Supplemental Type Certificate ADDENDUM NO. SA3989WE This Addendum, which is part of Supplemental Type Certificate No. SA3989WE, prescribes conditions and limitations under which the product for which the Supplemental Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations. This Addendum supersedes Aircraft Specification No. 716 only where noted.

I - Model Bellanca 14-9 as modified by STC SA3989WE.

Engine: Lycoming 0-360-A1D Fuel: 100/130 Minimum Grade Aviation Gasoline Engine Limits: Maximum continuous: 2600 rpm (175 hp) Takeoff (5 minutes): 2700 rpm (180 hp) Propeller: Hartzell HC-C2YK-1BF/F7666A Diameter: not over 76 in., not under 74.5 in.

Pitch settings at 30 in. sta.:

13.0°, High: 28.5° Hartzel! spinner 825-33 Hartzell hydraulic governor H-1 Oil Capacity: 8 ots. (-34.0) *Powerplant Instrument Markings: Tachometer: 2700 rmp Maximum (Red Line) 2000-2250 rpm Restricted Range (Red Arc) 2250-2600 rpm Normal Operating (Green Arc) Oil Temperature: 118°C Maximum (Red Line) Oil Pressure: 100 psi Maximum (Red Line) 25 psi Minimum (Red Line) 60-90 psi Normal Operating (Green Arc)

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*nical State of Sinarica Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3939NE Make: July 5, 1979 Supplemental Type Certificate ADDENDUM NO. SA3989WE (Continued) *Powerplant Instrument Markings (Continued): Fuel Pressure: 8.0 psi Maximum (Red Line)

0.5 psi Minimum (Red Line) Cyl. Head Temperature: 260°C Maximum (Red Line) 66°-204°C Normal Operating (Green Arc) Serial Numbers Eligible: No. 1029 only Required Equipment: In addition to the equipment applicable and required by Aircraft Specification No. 716, the equipment specified by Description of Change to Bellanca 14-9, N130E for Installation of Lycoming Engine 0-360-A1D and a Hartzell Constant Speed Propeller, dated 3-8-77 must be installed as a result of this STC.

Certification Basis: Part 4a of the Civil Air Regulations Part 36 of the Federal Aviation Regulations Note 1. Current weight and balance report including list of equipnent included in certiticated empty weight, and loading instructions when necessary, must be in the aircraft. The certificated empty weight and corresponding center of gravity location must include undrainable oil of 0 lbs. at (-34). Unusable fuel was not changed by this modification.

Note 2. The following information shall be provided the pilot in the form of placards or markings:

a. At the oil tank filler cap:

"OIL 8 QTS."

FAA FORM B110-2-1 (10-69) PAGE 4 OF 6 PAGES C FAA AC 73-2651

Waitre States of Sherice Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Numbes SA3989WE Make: July 5, 1979 Supplemental Type Certificate ADDENDUM NO. SA3989WE (Continued) Note 2. (Continued)

b. At the wing fuel tank filler openings:

"FUEL, 100/130 AVIATION GRADE FUEL USABLE 20 GAL"

c. At the alternator switch:

"ALTERNATOR, OFF, ON"

DO NOT TURN ALTERNATOR OFF IN FLIGHT EXCEPT FOR EMERGENCY"

d. At propeller pitch control:

"PROP PITCH PUSH IN HIGH RPM"

e. At cowl flap control:

"COWL FLAP PUSH IN CLOSED"

f. On the instrument panel in full view of the pilot:

"TOTAL WEIGHT OF PILOT, PASSENGERS, FUEL, AND BAGGAGE SHALL NOT EXCEED 414 POUNDSỊ

9. Adjacent to the tachometer:

"AVOID CONTINUOUS OPERATION BETWEEN 2000 AND 2250 RPM"

h. At the emergency fuel pump switch:

"EMERGENCY FUEL PUMP" "OFF ON 10" In addition to the placards specified above, the prescribes operating limitations indicated by an asterisk on this STO Addendum must also be displayed by permanent markings.

FAA FORM 6110-2-1 (10-69) PAGE 5 OF 6 PAGES TAL AC 73-2651

Brital State of Scrica Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA3989WE Make: July 5, 1979 Supplemental Type Certificate ADDENDUM NO. SA3989WE (Continued) Note 3. Noise Certification Procedure:

Compliance with FAR 36, Appendix F, was shown with the following procedures:

Level flyover at 1000 ft. AGL at 2600 engine rpm.

The certificated noise level is 70.3 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 1,7 dB (A) credit resulting from aircraft takeoff and climb characteristics. The related airplane maximum weight is 1750 pounds and the FAR 36 limit is 70.6 dB (A).

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FAA FORM 6110-2-1 (10-69) PAGE 6 OF 6 PAGES C FAA AC 73-2651