STC SE96SO

SE96SO TALCO Aviation 3015 E. New York St, STE A2-270 Aurora, IL 60504 Part 13 the Civil Air Regulations dated June 15, 1956 3E1 Continental-Teledyne IO-470-D, E, M, N, S, U, and V

(See continuation sheet 3 of 5) October 21, 1963 1/14/69, 2/10/82, 10/30/87, 9/22/95, 11/14/03, 6/26/06, 3/16/07, 3/12/18, 2/2/2021; 8/31/2023 March 31, 1964 May 27, 1966, July 27, 1971, February 6, 1979, July 15, 1983 for Paul (Vu) Nguyen Manager, Central Certification Branch Compliance & Airworthiness Division Aircraft Certification Service 5

SE96SO 5

SE96SO Date of Issuance: March 31, 1964 Date Amended: July 15, 1983 Date of Reissuance: August 31, 2023

Description of Type Design Change (continued):

Installation of two (2) Roto-Master Turbochargers Model 3DT5FF10J2, P/N 600572-00 (formerly Rajay Model 315F10, P/N RJ0080-102) on Continental-Teledyne engine models listed above in accordance with FAA sealed Roto-Master (formerly Rajay) Drawing No. R00404, dated April 4, 1963 and Revision C, dated January 25, 1979 or later FAA approved revision.

This STC establishes the eligibility of the engines listed for operation with the Roto-Master turbochargers in accordance with the engine operation limitations specified.

The installer must determine whether this design change is compatible with previously approved modifications. If the holder agrees to permit another person to use this certificate to alter a product, the holder must give the other person written evidence of that permission. This approval covers engine turbocharger compatibility only. A copy of this STC must be included in the permanent records of each engine modified in accordance with this STC.

ENGINE OPERATING LIMITATIONS

Where applicable, the following engine limitations supersede those specified on Engine Type Certificate Data Sheet 3E1 as applicable:

SE96SO Date of Issuance: March 31, 1964 Date Amended: July 15, 1983 Date of Reissuance: August 31, 2023

Engine Speed (Turbocharged)

Manifold Pressure Engine Speed

Takeoff 29.5" Hg.A 2625 RPM (5 minutes)

Max. Cont. 27.0" Hg.A 2500 RPM

-No fuel mixture leaning allowed at and above 75% of takeoff power.

NOTE: To extend the maximum continuous power of the engine throughout the altitude envelope (Sea Level to 25,000 feet), an engine fuel boost pump may be required. This boost pump must be capable of delivering 100% of fuel flow required to produce maximum continuous power of the engine and within the -2 psi to +10 psi pressure limits at the inlet to the engine driven fuel pump.

Fuel: Minimum grade Aviation gasoline 100/130

Altitude: Maximum operating altitude - 25,000 MSL (Density)

SE96SO Date of Issuance: March 31, 1964 Date Amended: July 15, 1983 Date of Reissuance: August 31, 2023

ENGINE AND TURBOCHARGER OPERATION:

-Do not operate the turbochargers unless the throttle is wide open.

-When increasing power, fully open the throttle, then slowly close the waste-gate until the desired manifold pressure is obtained.

-When decreasing power, fully open wastegate, then close throttle.

CAUTION: During turbocharger mode of operation at high altitude, selection of idle power by closing the throttle will result in unstable engine operating and/or power loss. Appropriate engine operation procedures or system design to prevent this must be established as part of the aircraft certification.

This approval covers engine-turbocharger compatibility only. For power limitations with this installation, refer to Roto-Master Drawing R00404. The approval of this change in type design applies basically to IO-470-D, E, M, N, S, U engines only. This determination should include consideration of significant changes in weight distribution such as an increase in the fixed disposable weight in the aircraft fuselage.

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