STC SE90WE

SE90WE TALCO Aviation 3015 E. New York St, STE A2-270 Aurora, IL 60504 Part 13 the Civil Air Regulations 1E10 Lycoming IO-360-A1D6D, A3D6D

(See continuation sheet 3 of 5) April 27, 1977 2/10/82, 10/30/87, 9/22/95, 12/12/03, 6/26/06, 3/16/07, 3/12/18, 2/2/2021;

8/31/2023 December 22, 1977 February 14, 1985, November 21, 1997 for Paul (Vu) Nguyen Manager, Central Certification Branch Compliance & Airworthiness Division Aircraft Certification Service 5

SE90WE 5

SE90WE Date of Issuance: December 22, 1977 Date Amended: November 21, 1997 Date of Reissuance: August 31, 2023

Description of Type Design Change (continued):

Installation of Roto-Master (Rajay) Turbochargers Model 3AT6EE10J2 (325E10-1) P/N 600573-00 (RJ0331-1), on Lycoming engine model listed above in accordance with FAA sealed Roto-Master (Rajay) Drawing No. RJ4202, dated December 14, 1977 and revised January 25, 1985, or later FAA approved revision.

This STC establishes the eligibility of the engines listed for operation with the Roto-Master (Rajay) 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 1E10:

Engine Speed (Turbocharged)

Takeoff and Max. Cont. - 2700 RPM

FAA Form 8110-2 (03/21) Page ___ of ___ United States of America Department of Transportation Federal Aviation Administration Supplemental Type Crtificate (Continuation Sheet) Number:

SE90WE Date of Issuance: December 22, 1977 Date Amended: November 21, 1997 Date of Reissuance: August 31, 2023

Manifold Pressure (Turbocharged)

Takeoff and Max. Cont. - 29.5 in Hg. Abs. Sea Level to 6000 feet altitude

Above 6000 feet and up to 23,000 feet maximum operating altitude, decrease maximum continuous power by reducing manifold pressure by one inch Hg. For each 1000 feet of altitude: this is to assure adequate delivery of fuel flow quantity from engine driven pump to engine.

No fuel Mixture leaning allowed at and above 75% of takeoff and max. Continuous power.

NOTE: To extend the maximum continuous power of the engine throughout the altitude envelope (Sea Level to 23,000 feet) an engine fuel boost pump must be installed. This boost pump must be capable of delivering 100% of fuel required to produce maximum continuous power of the engine and within the -2 psi to +35 psi pressure limits at the inlet to engine driven fuel pump.

Overboost relief valve limit: 30± .25 in. Hg.

Fuel: Minimum grade Aviation gasoline 100/130

Altitude: Maximum operating altitude, 23,000 MSL (Density) 4 5

SE90WE Date of Issuance: December 22, 1977 Date Amended: November 21, 1997 Date of Reissuance: August 31, 2023

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 a part of the aircraft certification.

-END- 5 5