Continental IO-550 explained

The Continental IO-550 engine is a large family of 9 liter fuel injected six-cylinder, horizontally opposed, air-cooled aircraft engines that were developed for use in light aircraft by Teledyne Continental Motors. The first IO-550 was delivered in 1983 and the type remains in production.[1] [2]

The IOF-550 is an Aerosance FADEC equipped version of the same basic engine, the TSIO-550 is a dual turbocharged version and the TSIOL-550 is a liquid-cooled variant.[3]

There is no O-550 engine, which would be a carburetor-equipped variant, hence the base model is the IO-550.

This engine family competes with the Lycoming IO-580 series which are also six-cylinder engines with similar power output and weight.[4]

Design and development

The IO-550 family of engines was developed from the IO-520 series, with the stroke increased from 4.00 to 4.25 inches, increasing the displacement to 552 in³ (9.05 L). The engine family covers a power range from 2800NaN0 to 3600NaN0.

The engines were first developed in the early 1980s and first certified on a regulatory basis of FAR 33, 1 February 1965 amendment, 33-8, 2 May 1977. The first IO-550 model was certified on 13 October 1983.

Variants

IO-550-A
  • 3000NaN0 at 2700 rpm, dry weight 430.722NaN2. Certified 13 October 1983.
    IO-550-B
  • 3000NaN0 at 2700 rpm, dry weight 421.612NaN2. Certified 13 October 1983.
    IO-550-C
  • 3000NaN0 at 2700 rpm, dry weight 433.22NaN2. Certified 13 October 1983.
    IO-550-D
  • 3000NaN0 at 2700 rpm, dry weight 437.11NaN1. Certified 23 June 1988.
    IO-550-E
  • 3000NaN0 at 2700 rpm, dry weight 450.52NaN2. Certified 20 December 1989.
    IO-550-F
  • 3000NaN0 at 2700 rpm, dry weight 437.11NaN1. Similar to the IO-550-A,B & C, with a top-mounted induction system and 12-quart oil sump. Certified 23 June 1988.
    IO-550-G
  • 2800NaN0 at 2500 rpm, dry weight 428.972NaN2. Certified 17 March 1989.
    IO-550-L
  • 3000NaN0 at 2700 rpm, dry weight 438.51NaN1. Certified 23 June 1988.
    IO-550-N
  • 3100NaN0 at 2700 rpm, dry weight 429.972NaN2. Similar to the IO-550-G with increased power rating. Certified 16 August 1996.
    IO-550-P
  • 3100NaN0 at 2700 rpm, dry weight 4290NaN0. Similar to the IO-550-N with oil sump from the IO-550-L. Certified 1 March 2000.
    IO-550-R
  • 3100NaN0 at 2700 rpm, dry weight 439.51NaN1. Similar to the IO-550-N but with the oil sump, oil suction tube and mount legs from the IO-550-B. Certified 1 March 2000.

    FADEC models

    IOF-550-B
  • 3000NaN0 at 2700 rpm, dry weight 447.11NaN1. Similar to the IO-550-B with an Aerosance FADEC fuel and ignition control system. Certified 4 February 2002.
    IOF-550-C
  • 3000NaN0 at 2700 rpm, dry weight 453.21NaN1. Similar to the IO-550-C with an Aerosance FADEC fuel and ignition control system. Certified 4 February 2002.
    IOF-550-D
  • 3000NaN0 at 2700 rpm, dry weight 4551NaN1. Similar to the IO-550-D with an Aerosance FADEC fuel and ignition control system. Certified 4 February 2002.
    IOF-550-E
  • 3000NaN0 at 2700 rpm, dry weight 462.81NaN1. Similar to the IO-550-E with an Aerosance FADEC fuel and ignition control system. Certified 4 February 2002.
    IOF-550-F
  • 3000NaN0 at 2700 rpm, dry weight 460.11NaN1. Similar to the IO-550-F with an Aerosance FADEC fuel and ignition control system. Certified 4 February 2002.
    IOF-550-L
  • 3000NaN0 at 2700 rpm, dry weight 4551NaN1. Similar to the IO-550-L with an Aerosance FADEC fuel and ignition control system. Certified 4 February 2002.
    IOF-550-N
  • 3100NaN0 at 2700 rpm, dry weight 4601NaN1. Similar to the IO-550-N with an Aerosance FADEC fuel and ignition control system. Certified 4 February 2002.
    IOF-550-P
  • 3100NaN0 at 2700 rpm, dry weight 4601NaN1. Similar to the IO-550-P with an Aerosance FADEC fuel and ignition control system. Certified 4 February 2002.
    IOF-550-R
  • 3100NaN0 at 2700 rpm, dry weight 470.51NaN1. Similar to the IO-550-R with an Aerosance FADEC fuel and ignition control system. Certified 4 February 2002.

    Turbocharged models

    TSIO-550-A
  • 3600NaN0 at 2600 rpm, dry weight 4420NaN0 plus two turbochargers of 28.21NaN1 each.
    TSIO-550-B
  • 3500NaN0 at 2700 rpm, dry weight 4420NaN0 plus two turbochargers of 28.21NaN1 each. Similar to the TSIO-550-A except with a 12 quart sump, sonic venturii removed and the two stage fuel pump replaced by a single stage fuel pump.
    TSIO-550-C
  • 3100NaN0 at 2600 rpm, dry weight 4420NaN0 plus two turbochargers of 28.21NaN1 each.
    TSIO-550-E
  • 3500NaN0 at 2700 rpm, dry weight 4420NaN0 plus two turbochargers of 28.21NaN1 each. Similar to TSIO-550-C with the oil sump and maximum continuous power rating of the TSIO-550-B.
    TSIO-550-G
  • 3100NaN0 at 2700 rpm, dry weight 5540NaN0 plus two turbochargers of 28.21NaN1 each. Similar to the TSIO-550-E with smaller surface area intercoolers, different oil sump capacity and power rating.
    TSIO-550-K
  • 3150NaN0 at 2500 rpm, dry weight 5220NaN0 plus two turbochargers of 28.21NaN1 each. Similar to the TSIO-550-E with new oil sump and capacity, decreased maximum continuous power, increased turbo boost pressure, decreased engine speed rating and tapered cylinder barrel fins.

    Turbocharged & FADEC models

    TSIOF-550-D
  • 3500NaN0 at 2600 rpm, dry weight 5580NaN0 plus two turbochargers of 35.21NaN1 each. Similar to the TSIOF-550-J except the exhaust system and low voltage harness.
    TSIOF-550-J
  • 3500NaN0 at 2600 rpm, dry weight 5580NaN0 plus two turbochargers of 35.21NaN1 each. Similar to the TSIO-550-E except for FADEC fuel injection and ignition control, turbochargers, tapered cylinder barrel fins, oil sump and capacity, maximum continuous speed and manifold pressure rating.
    TSIOF-550-K
  • 3150NaN0 at 2500 rpm, dry weight 537.31NaN1 plus two turbochargers of 28.21NaN1 each. Similar to the TSIO-550-K but with FADEC fuel injection and ignition control.

    Liquid-cooled models

    TSIOL-550-A
  • 3500NaN0 at 2700 rpm, dry weight 4020NaN0. Similar to the TSIO-520-NB but with a new cylinder design that uses liquid cooling. The coolant manifold is on top of the cylinder head, with a coolant pump fitted to the starter adapter, driven by the starter adapter shaft and the oil cooler is mounted on the airframe, not the engine. The engine has an AiResearch TA81 turbocharger.
    TSIOL-550-B
  • 3250NaN0 at 2700 rpm, dry weight 5570NaN0. Similar to the TSIO-520-UB but with a new cylinder design that uses liquid cooling. The coolant manifold is on top of the cylinder head, with a coolant pump fitted to the starter adapter, driven by the propeller shaft using sheaves, the oil cooler is mounted on the airframe, not the engine. A coolant tank and coolant lines are added to the installation. The engine has an AiResearch TS06 turbocharger.
    TSIOL-550-C
  • 3500NaN0 at 2600 rpm, dry weight 5460NaN0. Similar to the TSIOL-550-A but with the exhaust system and turbocharger bracket from the TSIOL-550-B. The engine is modified to accept the AiResearch TA81 turbocharger. Neither oil nor coolant radiators are provided with the engine.

    Geared models

    GIO-550-A
  • A special non-certified geared engine developed for the RU-38 Twin Condor covert reconnaissance aircraft, incorporating 3:2 gear reduction to 2267 rpm.[5] [6] [7]

    Applications

    IO-550
    TSIO-550
    TSIOF-550
    TSIOL-550
    GIO-550

    External links

    Notes and References

    1. Web site: Type Certificate Data No. E3SO Revision 10. 2008-12-28. . March 2007. https://web.archive.org/web/20110608192355/http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/0/ad5e08854d63389c862572a4006e2912/$FILE/E3SO.pdf. 8 June 2011. dead.
    2. Web site: Type Certificate Data No. E5SO Revision 6. 21 June 2010. . March 2010. https://web.archive.org/web/20180105180440/http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/0/28811040e5cd10c586257712004008cf/$FILE/E5SO.pdf. 5 January 2018. dead.
    3. Web site: TYPE CERTIFICATE DATA SHEET NO. E4SO Revision 1. 2008-12-28. Federal Aviation Administration. August 1997. https://web.archive.org/web/20180105180434/http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/0/D3AB1F2213075EA48525670E00483A5E?OpenDocument&Highlight=tsiol-550. 2018-01-05. dead.
    4. Web site: TYPE CERTIFICATE DATA SHEET NO. E00004NY, Revision 1. 2009-01-03. Federal Aviation Administration. August 2007. https://web.archive.org/web/20180105180432/http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/0/D2F3A343A114ECB4862573F6004C76F4?OpenDocument&Highlight=580. 2018-01-05. dead.
    5. Web site: Schweizer RU-38A Twin Condor . 2008-06-04. Stoll, Alex. September 2001.
    6. Web site: MANDATORY SERVICE BULLETIN MSB94-4G. 2009-07-14. TELEDYNE CONTINENTAL. October 2005. https://web.archive.org/web/20091116234512/http://www.tcmlink.com/pdf2/MSB94-4G.pdf. 2009-11-16. dead.
    7. Web site: Designations Of U.S. Military Aero Engines. 2009-07-14. Parsch. Andreas. February 2008.
    8. Web site: Supplemental Type Certificate, STC Number: SA09133SC. 9 September 2014. Federal Aviation Administration. 4 November 1999. https://web.archive.org/web/20180105180442/http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/C3897CA52D560C7D862576CD004D7483?OpenDocument&Highlight=sa09133sc. 5 January 2018. dead.
    9. Web site: IO550. 2022-02-10. Summit Aviation. en-US.
    10. https://disciplesofflight.com/cessna-210-centurion/ Cessna 210 Centurion

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