# STC SE60WE

- Type: Supplemental type certificate
- Status: Current, Reissued
- Holder: TALCO Aviation, United States
- Description: Installation of two Rajay Turbochargers P/N RJ 0327-1 or -2 and 9 lb. Sonic nozzle.
- Applied: January 30, 1973
- Status date: August 31, 2023
- Product: Engine
- Data sheets: [TCDS 1E4](https://openairdocs.org/tcds/1E4)
- Certificate PDF: https://openairdocs.org/files/sha256/04/7a/047ac2f4b8a4c0afd01354ed9e06423c3ae4d22ed69b75b7bb3376de0e2349f3
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID187024038420231115173201.0001
- DRS record last changed: December 5, 2025
- Page: https://openairdocs.org/stc/SE60WE

## ADs that name it (1)

- [AD 2002-19-03](https://openairdocs.org/ad/2002-19-03): Crankshaft · Lycoming Engines IO-540-A1A5, IO-540-AA1A5, IO-540-AA1B5 and 81 more. Effective Sep 20, 2002. Named in the applicability

## Approved models (15)

- Lycoming Engines IO-540-A1A5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4))
- Lycoming Engines IO-540-B1A5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4))
- Lycoming Engines IO-540-B1B5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4))
- Lycoming Engines IO-540-B1C5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4))
- Lycoming Engines IO-540-E1A5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4))
- Lycoming Engines IO-540-E1B5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4))
- Lycoming Engines IO-540-E1C5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4))
- Lycoming Engines IO-540-G1A5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4))
- Lycoming Engines IO-540-G1B5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4))
- Lycoming Engines IO-540-G1C5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4))
- Lycoming Engines IO-540-G1D5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4))
- Lycoming Engines IO-540-G1E5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4))
- Lycoming Engines IO-540-G1F5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4))
- Lycoming Engines IO-540-P1A5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4))
- Lycoming Engines IO-540-S1A5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4))

## What the certificate says

Read from the PDF's text layer, without the form's printed wording; the layout is lost and the order can differ. The PDF is the record.

SE60WE TALCO Aviation 3015 E. New York St, STE A2-270 Aurora, IL 60504 Part 13 the Civil Air Regulations 1E4 Lycoming IO-540-A1A5, B1A5, B1B5, B1C5, E1A5, E1B5, E1C5, G1A5, G1B5, G1C5, G1D5, G1E5, G1F5, P1A5, S1A5 Installation of two Rajay Turbochargers P/N RJ 0327-1 or -2 and 9 lb. ±1 Sonic nozzle on Lycoming Engine Models listed above in accordance with FAA sealed Rajay Drawing List No. RJ 5099. This STC establishes the eligibility of the engines listed hereon for operation with the Rajay Turbocharger in accordance with the engine operating limitations specified. Approval of the engine with a turbocharger in any airplane will be covered by an STC issued against the airplane on which it is installed.

(See continuation sheet 3 of 4) January 30, 1973 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 March 14, 1973 May 14, 1973, September 19, 1973 for Paul (Vu) Nguyen Manager, Central Certification Branch Compliance & Airworthiness Division Aircraft Certification Service 4

SE60WE 4

SE60WE Date of Issuance: March 14, 1973 Date Amended: September 19, 1973 Date of Reissuance: August 31, 2023

This approval covers engine/turbocharge compatibility only.

**ENGINE OPERATING LIMITATIONS**

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

Engine Speed (Turbocharged)

IO-540-A1A5, B1A5, B1B5, B1C5, E1A5, E1B5, E1C5, G1A5, G1B5, G1C5, G1D5, G1E5, G1F5, P1A5, S1A5.

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

Manifold Pressure (Turbocharged) Take off 29.5 HgA (5 minutes)

Max. Cont. 29.5 HgA

Fuel (Minimum grade Aviation gasoline) 100/130

Altitude

Maximum operating altitude 30,000 MSL (density) 3 4

SE60WE Date of Issuance: March 14, 1973 Date Amended: September 19, 1973 Date of Reissuance: August 31, 2023

Maximum Permissible Temperatures:

Exhaust Gas (turbo inlet) 1600˚F@ 100,000 RPM

1650˚F@ 90,000 RPM

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 wastegates 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.

-END- 4 4

## Every issue (3)

- August 31, 2023: Reissued, Current. [certificate](https://openairdocs.org/files/sha256/04/7a/047ac2f4b8a4c0afd01354ed9e06423c3ae4d22ed69b75b7bb3376de0e2349f3)
- March 5, 2018: Reissued, Historical. [certificate](https://openairdocs.org/files/sha256/f6/a5/f6a539dd23230addafb8f22c3a585cdc8577f1074c5d4d18d981f94833982386)
- June 26, 2006: Reissued, Historical. [certificate](https://openairdocs.org/files/sha256/79/5e/795e33bf91421ec52ac4919595165d80081a8b756babce0c8e431d4493afd877)

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