STC SA3784WE

Depart. a of asportation -federal biatic Admin. ation United States of America aes Supplemental Type Certificate Number: SA370LnE This certificate issued to: Richard E. Wallace Purt 3 /the Civil Air Regulalions, dated November 1, 1949.

Original Product - Type Bertificate Lumber 5A5 Make: Cessna Alrded: 305A, Landplane only. Normal and Utility Description of Type Design Change: Category, N62364, Serial No. 23484 Installation of Continental 0-470-15 engine, McCauley 243601/90M Constant Speed Propeller, extended engine cowl lip, Jasco 50 amp alternator, modified 24 volt electrical system and associated changes in accordance with Richard Wallace Report No. 1 dated September 21, 1978.

See continuation sheets 3 and L.

Limitations and Conditions: Data not suitable for reproduction of installation in other aircraft; therefore, they are satisfactory for Cessna 305A, N62364, Serial No. 23484 only. No additional modifications of this type are to be approved solely by reference to this Supplemental Type Certificate or to the data submitted therefor. A copy of this certificate and Fichard Wallace Report No. 1 shall be maintained as part of the permanent records for this modified aircraft.

November 9, 1978 Date Amended:

AVIATION By Direction of the Administrator FEDE sichfaden Tisembles CANISTEATON (lony chief, As resist Modification Brunen..

mr hak.

This certificate may be transferred in accordance with BAR 2 45 FAA FORM B110-2 (10-68) Page 1 of 4 Pages

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA3784WE Make: NOV 9 1978 Supplemental Type Certificate ADDENDUM NO. SA378LWE The conditions and limitations of Aircraft Specification No. 5A5 apply except as follows:

This Addendum, which is part of Supplemental Type Certificate No. SA3784WE, 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 permanent records.

Supplemental Type Certificate Folder: Richard H. Wallace.

and Utility I - Model 305A, (Landolane only), Normal/Category, as modified by STC SA378LWE.

Engine Continental 0-470-15 Engine Limits Takeoff (one minute) 2600 RPM (213 HP) All other operations 2300 RPM (190 HP Propeller and Propeller Limits McCauley 2A36C1/90M constant speed Hub Model : 2A36C1 Blade Model: 90M-0 Diameter : 90" Maximum 88" Minimum Pitch Settings at 36 in. Sta. - Low 7.0° High 22.5° Governor : Woodward 210105 Maximum Weight 2100 1bs.

Powerplant Instrument Markings Tachometer: Maximum - 2600 RPM (Red Radial) Caution - 2300 - 2600 RPM (Yellow Arc) Normal - 1600 - 2300 RPM (Green Arc) Oil Temperature Gage:

Maximum - 107°C (Red Radial)

47.

PAGE 3 OF 4 PAGES FAA AC 73-2651

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA378LNE NOV 9 1978 Make:

Powerplant Instrument Markings (Continued) Certification Basis Cylinder Head Temperature Gage:

450°F (232 C) (Red Radial) (Bayonet type thermocouple on #4 cylinder) Oil Pressure Gage:

Minimum - 30 psi (Red Radial) Maximum - 60 psi (Red Radial) Green Arc between 30 and 60 psi Same as specified by Aircraft Specification No. 5A5.

Required Equipment In addition to the equipment applicable and required by Aircraft Specification No. 5A5, the equipment specified by Richard Wallace Report No. 1 mist be installed as a result of the incorporation of this SIC.

NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions when necessary, must be in the aircraft.

NOTE 2. The following placards must be installed in clear view of the pilot:

a. Adjacent to alterator switch:

ALTERNATOR" "DO NOT TURN OFF ALTERNATOR IN FLIGHT EXCEPT IN EMERGENCY"

b. On instrument panel near oil temperature gage:

ICLIMB AT 100 MPH MINIMUM FOR ENGINE OIL COOLING"

c. At the propeller control:

#PUSH TO INCREASE RPM".

- END -

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