STC SA3466WE

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number 543466NE This certificate issued to: Alan Is. Buchner Part 3 of the CIVIL AII Regulations, effective May 15, 1956.

Original Product -Type bertificate Number: 3A21 Make: Cessna Model: 210, N25JC, Serial No. 57008 (Nornal Category) Description of Type Design Change:

Installation of Continental I0-520-A engine and McCauley D3A32C90M/S-82NC-2 constant speed propeller in accordance with Alan I. Buchner Report No. 1 dated 6/9/77.

See Continuation Sheets 3 through 4.

Limitations and Conditions: Data not suitable for reproduction of installation in other aircraft; therefore, they are satisfactory for Cessna 210, N25JC, Serial No. 57008 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. Supplemental Type Certificate Addendum No. SA3466WE is a part of the Certificate. A copy of this Certificate and Alan I. Buchner Report No. 1' shall be maintained as part of the permanent records for this modified aircraft.

Date of Application: February 2, 1976 Date Reissued:

Date of Issuance: . July 29, 1977 Date Amended:

FEDERAL AVIATION By Direction of the Administrator HOlison (Signature ) TOMINISTRAIO Chief, Aircraft Modification Branch (Title) 57008 Supplemental Type Certificate ADDENDUM NO. SA3466WE The conditions and limitations of Type Certificate Data Sheet No. 3A21 apply except as follows:

This Addendum, which is part of Supplemental Type Certificate No. SA3466WE, 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 Holder: Alan I. Buchner.

I - Model Cessna 210, (Normal Category), as modified by STC SA3466WE.

Engine: Continental I0-520-A Fuel: 100 Minimum Grade Aviation gasoline Engine Limits: For all operations 260 HP 2700 RPM @ 26.5" Hg @ S.I.

2700 RPM @ 25.9" He @ 2800 It.

Straight line variation between points given Propeller and Propeller Limits: McCauley D3A320 90M/S-82NC-2 Hub Model: D3A32090M Blade Model: S-82NC-2 Diameter: 80" Maximum

78.5" Minimum Pitch Settings: At 30 in. Sta. - Low 13.8°

28.1° Spinner: McCauley D3669 Woodward Hydraulic Governor: 210270 Oil Capacity: 12 quarts at Sta. (-19.4) (6 qt. useable)

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United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) 7/29/77 (I) Number SA3466WE Powerplant Instrument Markings: Tachometer: Maximum 2700 RPM (red radial) Manifold Pressure Gage: Maximum 26.5 in. Hg. (red radial) 0il Temperature Gage: Maximum 240°F (red radial) Cylinder Head Temperature Gage: Maximun 460°F (red radial) (Bayonet type thermocouple on No. 1 cylinder) Oil Pressure Gage: Minimum - 10 psi (red radial) Maximm - 100 psi (red radial) Normal - green arc between 30 and 60 psi Metered Fuel Pressure Gage: Minimum - 3.5 psi (red radial) Maximum - 18.5 psi (red radial) Serial Numbers Eligible: No. 57008 only Certification Basis:' Same as specified by T.C. Data Sheet No. 3A21 Required Equipment: In addition to the equipment applicable and required by I.C. Data Sheet No. 3A21, the equipment specified by Alan I. Buchner Report No. 1 must be installed as a result of the incorporation of this STC.

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 placard must be installed in front of and in clear view of the pilot:

260 HP ALL OPERATTONS 2700 RPM @ 26.5" HG @ S.L.

2700 RPM @ 25.9" HG @ 2800 FT.

STRATGHT LINE VARTATION WITH ALTITUDE BETWEEN POINTS GIVEN"

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