STC SA1457NM

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number SA1457NM This certificate issued to: Aircraft Specialties Part 3 s/ the Civil AiI Fregulations.

Original Product -Type Certificate Number: 3A21 Make: Cessna Model: T210L Description of Type Design Change: Installation of a Continental TS10-520-M(1) engine and a McCauley D3A34C402/90DFA-10 propeller in accordance with Aircraft Specialties photographs 1 through 3.

Limitations and Conditions: Data pertaining to this modification are considered inadequate for duplication in other aircraft. This approval is limited to the installation in Cessna, Model T210L, Serial Number 21060379 only. A copy of this Certificate and Addendum shall be maintained as part of the permanent records for the modified aircraft.

Date of Application: September 17, 1981 Date Reissued:

Date of Issuance: . February 24, 1982 Date Amended:

FEDERAL AVIATION By directi of the Idministrator ( Signature) TO MINISTRATOR Chief, Seattle Area Aircraft Certification office, AND-1005

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) February 24, 1982 Number: SA2457591 Supplemental Type Certificate ADDENDUM NO SA1457NM The conditions and limitations of Type Certificate Data Sheet Number 3A21 apply except where superseded by the following:

Supplemental Type Certificate Data Sheet, which is part of STC SA1457NM prescribes the conditions and limitations under which the product for which the STC was issued meets the airworthiness requirements of the Civil Air Regulations:

Supplemental Type Certificate HOLDER: Aircraft Specialties Cessna T210L (Landplane - Normal Category) as Modified by STC SA1457NM A. Engine: Continental TS10-520-M(1) 310 hp @ 2700 RPM Engine Limits: Takeoff (1 minute) - 310 hp @ 2700 RPM

36.5" Hg manifold pressure Climb - 285 hp @ 2600 RPM and 35" Hg from Sea level to 12,000 feet at 120 mph IAS Cruise - 285 hp @ 2600 RPM and 30" Hg above 12,000 feet Fuel: 100/130 B. Airspeed Limits Vne = 225 mph (196K) (Decrease 4 knots per 1000 feet above 16,000 feet) All other speed as per type data sheet 3A21.

C. Altitude Limits: Maximum operating altitude 22,000 feet D. Propeller: McCauley D3A34C402/90DFA-10 Propeller Limits: 310 hp @ 2700 for 1 minute 285 hp @ 2600 max continuous Max diameter - 80 inches Min diameter - 78 inches Engine Damper Configuration: Two - 6th Order One - 5th Order and One - 4th Order

AA FORM 8110-2-1 (10-69) PAGE 3 OF 4 PAGES C FAA AC 73-2651

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) February 24, 1982 Number SA1457NM All else is the same as Data Sheet 3A21 except:

Placards: Place the following placards on the instrument panel in full view of the pilot:

AVOID CONTINUOUS OPERATION BETWEEN 1850 AND 2150 PROPELLER

RPM FOR POWER SETTINGS ABOVE 24" MANIFOLD PRESSURE.

FOR COOLING PURPOSES Take-off: 36.5 Hg @ 2700 RPM 1 minute M.E.T.O. 35"Hg @ 2600 RPM SL to 12,000 Feet @ 120 mph IAS Climb speed M.E.T.O. 30 Hg @ 2600 RPM above 12,000 feet END

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