STC SE6WE

SE6WE TALCO Aviation 3015 E. New York St, STE A2-270 Aurora, IL 60504 Part 13 the Civil Air Regulations 1E4 Lycoming *See Continuation Sheet 3 of 3

(See continuation sheet 3 of 5) September 26, 1962 8/6/63; 11/27/63; 10/13/64; 9/6/66; 5/2/68; 1/14/69; 2/10/82; 10/30/87;

9/22/95; 9/15/03; 6/26/06; 3/16/07; 3/12/18; 2/2/2021; 8/31/2023 April 19, 1963 for Paul (Vu) Nguyen Manager, Central Certification Branch Compliance & Airworthiness Division Aircraft Certification Service 5

SE6WE 5

SE6WE Date of Issuance: April 19, 1963 Date of Reissuance: August 31, 2023

*Model: IO-540-A1A5, B1A5, B1B5, B1C5, C1B5, C1C5, C2C, C4B5, C4C5, E1A5, E1B5, G1A5, G1B5, G1C5, G1D5, G1E5, J4A5, K1A5, K1B5, K1C5, K1F5, L1A5, M1A5, 1A5, S1A5, K1E5

Description of Type Design Change (continued):

Installation of two Roto-Master Turbochargers Model No. 3DT5FFI0J2, P/N 600572-00 (formerly Rajay Model 315F10, P/N RJ0080-100, or -102) on Lycoming engine models listed above in accordance with FAA sealed Roto-Master (formerly Rajay) Drawing List RJ1000 Revision 1, dated 5/15/83 or later FAA approved revision. This STC establishes the eligibility of the engines listed hereon for operation with the Roto-Master (formerly Rajay) turbocharger in accordance with the engine operation limitations specified. Approval of the engine with the turbocharger in any airplane will be covered by an STC issued against the airplane on which it is installed.

This approval covers engine/turbocharger compatibility only. 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.

ENGINE OPERATING LIMITATIONS:

Where applicable, the following engine limitations supersede those specified on Engine Type Certificate Data Sheet 1E4:

SE6WE Date of Issuance: April 19, 1963 Date of Reissuance: August 31, 2023

Engine Speed (Turbocharged)

IO-540-A1A5, B1A5, B1B5, B1C5, C1B5, C1C5, C2C, C4B5, C4C5, E1A5, E1B5, G1A5, G1B5, G1C5, G1D5, G1E5, J4A5, P1A5, S1A5, K1E5

Takeoff 2575 RPM (5 minutes) Max. Cont. 2575 RPM

IO-540-K1A5, K1B5, K1C5, K1F5, L1A5, M1A5, S1A5, K1E5

Takeoff 2700 RPM (5 minutes) Max. Cont. 2700 RPM

Manifold Pressure (Turbocharged)

Takeoff 29.5 in HgA (5 minutes) Max. Cont. 29.5 in. HgA

Fuel (Minimum grade Aviation gasoline) 100/130

Altitude

Maximum Operating altitude 30,000 ft. MSL (density) 4 5

SE6WE Date of Issuance: April 19, 1963 Date of Reissuance: August 31, 2023

Engine and Turbocharger Operation:

For engines equipped with separate throttle and propeller controls, but no automatic wastegate control, do not operate the turbochargers unless the throttle is wide open. When increasing power, fully open the throttle; then slowly close the wastegate until the desired manifold pressure is obtained. When decreasing power, fully open wastegates;

then close the throttle. For those engines equipped with integrated power controls (i.e., throttle and propeller controlled by a common control), do not operate the turbochargers below 2200 RPM. When increasing power, set desired RPM; then slowly close the wastegates until the desired manifold pressure is obtained. When decreasing power, fully open wastegates; then make further power reduction by the integrated power lever.

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