STC SE85WE

SE85WE TALCO Aviation 3015 E. New York St, STE A2-270 Aurora, IL 60504 Part 13 the Civil Air Regulations 1E4E Lycoming IO-540-K1G5D Installation of two Roto-Master turbochargers Model 3DT5FF10J2, P/N 600572-00 (formerly Rajay Model No. 315F10-2, P/N RJ 0080-102), on Lycoming engine model listed above in accordance with FAA Approved Rotor-Master (formerly Rajay) Drawing List No. RJ 1000, Revision "G", dated October 26, 1977, or later FAA approved revisions. This STC established the eligibility of the engine listed for operation with the Roto-Master turbochargers in accordance with the engne operating limitaitons specified.

(See continuation sheet 3 of 4) June 30, 1977 February 10, 1982; June 9, 1988; March 3, 2020; February 2, 2021;

August 31, 2023 November 8, 1977 May 24, 1983 for Paul (Vu) Nguyen Manager, Central Certification Branch Compliance & Airworthiness Division Aircraft Certification Service 4

SE85WE 4

SE85WE Date of Issuance: November 8, 1977 Date Amended: May 24, 1983 Date of Reissuance: August 31, 2023

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 1E4:

Engine Speed (Turbocharger)

Takeoff and Max. Cont. - 2,700 RPM

Manifold Pressure (Turbocharged)

Takeoff and Max. Cont. 29.5 in. Hg. Abs. Sea Level to 8,000 feet altitude.

- Above 8,000 feet and up to 22,000 feet maximum operating altitude, decrease maximum continuous power by reducing manifold pressure by one inch Hg. for each 1,000 feet of altitude; this is to assure adequate delivery of fuel flow quantity from the engine driven pump to the engine.

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

SE85WE Date of Issuance: November 8, 1977 Date Amended: May 24, 1983 Date of Reissuance: August 31, 2023

NOTE: To extend the maximum continuous power of the engine throughout the altitude envelope (Sea Level to 22,000 feet), an alternate engine fuel pump must be installed. This boost pump must be capable of delivering 100% of fuel flow required to produce maximum continuous power of the engine and within the -4 psi to +40 psi pressure limits at the inlet to the engine driven fuel pump.

Overboost relief valve limit: 32 ± .5 in. Hg.

Overboost relief valve light seating: 30.5 ± .5 in. Hg. (Option)

Fuel: Minimum grade Aviation gasoline 100/130

Altitude: Maximum operating altitude 22,000 MSL (Density)

CAUTION: During turbocharger mode of operation at high altitude, selection of idle power by closing the throttle will result in unstable engine operation and/or power loss.

Appropriate engine operation procedures or system design to prevent this must be established as a part of the aircraft certification.

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