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Lycoming TIO-541

From Wikipedia, the free encyclopedia
TIO-541
Lycoming TIO-541
Type Piston aero-engine
National origin United States
Manufacturer Lycoming Engines
First run 1963
Major applications Beechcraft Duke
Beechcraft Baron
Produced 1965–present
Developed from Lycoming O-540

The Lycoming TIO-541 engine is a turbocharged, fuel-injected, horizontally opposed, six-cylinder aircraft engine featuring three cylinders per side, manufactured by Lycoming Engines.[1][2]

The TIO-541 family of engines includes the TIGO-541 turbocharged, fuel-injected, geared, horizontally opposed engine.[2]

There is no carburetted, non-turbocharged version of the engine, which would have been designated O-541 and therefore the base model is the TIO-541.[1]

Design and development

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The TIO-541 family of engines covers a range from 310 hp (231 kW) to 450 hp (336 kW). The engine has a fuel injection system which meters fuel in proportion to the induction airflow. The engine has a displacement of 541.5 cubic inches (8.87 litres) and produces a maximum of 450 hp (336 kW) in its TIGO-541 version. The cylinders have air-cooled heads.[1][2]

The first TIO-541-A1A was type certified on 23 February 1965 on the regulatory basis of CAR 13 effective 15 June 1956 as amended to 13-1 through 13-4.[1]

Variants

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TIO-541-A1A
Six-cylinder, turbocharged, fuel-injected, 310 hp (231 kW) engine, dry weight 449 lb (204 kg), AiResearch T-1823 turbosupercharger, certified 23 February 1965. Has top induction, down exhaust and side-mounted accessory drives. Provisions for a single-acting, controllable-pitch propeller and internal piston cooling oil jets.[1]
TIO-541-E1A4
Six-cylinder, turbocharged, fuel-injected, 380 hp (283 kW) engine, dry weight 595 lb (270 kg), AiResearch T-1823 turbosupercharger, certified 16 December 1966. Similar to the -A1A but with higher horsepower rating, different cylinder heads, cam shaft, crankshaft and extra counterweights. Incorporates cabin pressurization venturi.[1]
TIO-541-E1B4
Six-cylinder, turbocharged, fuel-injected, 380 hp (283 kW) engine, dry weight 595 lb (270 kg), AiResearch T-1823 turbosupercharger, certified 16 December 1966. Similar to the -E1A4 but without the cabin pressurization venturi.[1]
TIO-541-E1C4
Six-cylinder, turbocharged, fuel-injected, 380 hp (283 kW) engine, dry weight 586 lb (266 kg), AiResearch T-1879 turbosupercharger, certified 21 October 1969. Similar to the -E1A4 but with a different turbosupercharger with cast bracket, cast transition and a separate wastegate.[1]
TIO-541-E1D4
Six-cylinder, turbocharged, fuel-injected, 380 hp (283 kW) engine, dry weight 584 lb (265 kg), AiResearch T-1879 turbosupercharger, certified 21 October 1969. Similar to the -E1B4 but with a different turbosupercharger with cast bracket, cast transition and a separate wastegate.[1]
TIGO-541-B1A
Six-cylinder, turbocharged, fuel-injected, geared, 450 hp (336 kW) engine, dry weight 663 lb (301 kg), AiResearch T-1879 turbosupercharger, certified 12 February 1970. Similar to the -C1A but with a higher power rating and without provisions for cabin bleed air.[2]
TIGO-541-C1A
Six-cylinder, turbocharged, fuel-injected, geared, 400 hp (298 kW) engine, dry weight 703 lb (319 kg), AiResearch T-1879 turbosupercharger, certified 19 November 1968. Has internal piston cooling oil jets, side-mounted accessory drives and a single oil supply from the propeller governor. Provisions for a reverse-pitch propeller control.[2]
TIGO-541-D1A
Six-cylinder, turbocharged, fuel-injected, geared, 450 hp (336 kW) engine, dry weight 706 lb (320 kg), AiResearch T-18A21 turbosupercharger, certified 26 June 1969. Similar to the -C1A but with a higher power rating and a different turbocharger with provisions for cabin bleed air.[2]
TIGO-541-D1B
Six-cylinder, turbocharged, fuel-injected, geared, 450 hp (336 kW) engine, dry weight 710 lb (322 kg), AiResearch T-18A51 turbosupercharger, certified 3 December 1976. Similar to the -D1A but with an integral wastegate turbocharger and a revised exhaust system and with low drag cylinders.[2]
TIGO-541-E1A
Six-cylinder, turbocharged, fuel-injected, geared, 425 hp (317 kW) engine, dry weight 706 lb (320 kg), AiResearch T-18A21 turbosupercharger, certified 26 June 1969. Similar to the -D1A but with a lower power rating, different turbocharger spring rate and a variable absolute pressure controller.[2]
TIGO-541-G1AD
Six-cylinder, turbocharged, fuel-injected, geared, 450 hp (336 kW) engine, dry weight 714 lb (324 kg), AiResearch T-18A21 turbosupercharger, certified 1 May 1975. Similar to the -D1A but it includes an intercooler, a dual magneto and a fuel injector with fuel head enrichment.[2]

Applications

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TIO-541
TIGO-541

Specifications (TIO-541-A1A)

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Data from TYPE CERTIFICATE DATA SHEET NO. E10EA[1]

General characteristics

  • Type: Six-cylinder, air-cooled, horizontally opposed, direct-drive, fuel-injected, turbosupercharged aircraft engine
  • Bore: 5.125 in (130 mm)
  • Stroke: 4.375 (111 mm)
  • Displacement: 541.5 in³ (8.87 litres)
  • Dry weight: 449 lb (249 kg) dry

Components

  • Turbocharger: AiResearch turbosupercharger model T-1823
  • Fuel system: Bendix RSA 10AD1
  • Fuel type: 100LL avgas
  • Cooling system: air-cooled

Performance

See also

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References

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Wikimedia Commons has media related to Lycoming TIO-541.
  1. ^ a b c d e f g h i j Federal Aviation Administration (April 1986). "TYPE CERTIFICATE DATA SHEET NO. E10EA, Revision 7". Retrieved 2009-01-13.
  2. ^ a b c d e f g h i Federal Aviation Administration (April 1986). "TYPE CERTIFICATE DATA SHEET NO. E19EA, Revision 4". Retrieved 2009-01-13.
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