User:Dennisolcott/Fv4000-2tc
| FV4000-2TC | |
|---|---|
| Type | Certified Piston aero-engine |
| National origin | United States |
| Manufacturer | Hamilton Standard, Toyota |
| Produced | 1996–1997 |
Hamilton Standard Toyota FV4000-2TC Piston Aircraft Engine
The FAA issued a Type Certificate for the Hamilton Standard FV4000-2TC piston aircraft engine on December 21, 1995. [1]
- ^ TCDS Number E00052EN Model FV4000-2TC, https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/0/4f36c245de33402f8525670c0069d991/$FILE/E00052en.pdf
.
From the TCDS description, "An eight cylinder reciprocating engine configured in a V-8 block with a geared propeller drive system on the forward end and an accessory drive system on the aft end. The engine incorporates dual overhead camshafts, four valves per cylinder, a dual channel full authority digital engine control, and liquid cooling."
The engine is 242 cubic inches in displacement and includes a 0.3846:1 reduction gear ratio.
Aviation Week noted the certification in February 1996. [1]
- ^ FAA Certifies Engine Designed By Hamilton Standard, Toyota https://aviationweek.com/awin/faa-certifies-engine-designed-hamilton-standard-toyota
Flight Global reported that, "TOYOTA HAS RECEIVED US Federal Aviation Administration production certification for a piston aero-engine developed jointly with Hamilton Standard. The 270kW (360hp) FV2400-2TC is a twin-turbocharged Vee-8 based on Toyota's Lexus car engine and equipped with a Hamilton Standard full-authority digital engine-control (Flight International, 24-30 April, 1996). " Flight Global noted that production certification took longer as "the engines are to be produced by Toyota and shipped to Hamilton Standard for installation of the control system, testing and delivery to customers." They also reported that the engine "will be marketed directly against established Teledyne Continental and Textron Lycoming engines. [1]
Specifications (FV4000-2TC)
[edit]Data from Type Certificate Data Sheet E00052EN[1]
General characteristics
- Type: Eight-cylinder, V-8, four-stroke Dual Channel Full Authority Digital Engine Control, Liquid Cooling aircraft engine
- Bore: 3.44 in (87 mm)
- Stroke: 3.25 in (83 mm)
- Displacement: 242 cu in (3,966 cc)
- Dry weight: 520 lb (236 kg)
Components
- Fuel type: 100LL avgas minimum grade
- Oil system: 7 US qt (7 L)
- Cooling system: liquid-cooled, 60%LLC / 40% Water
- Reduction gear: 0.3846:1
Performance
- Power output: 360 hp (268 kW) at 5200 rpm
- Compression ratio: 9.7:1
- Specific fuel consumption: 0.502 lbs/hp-hr Max Continuous, 0.382 lb/hp-hr Best Economy
- Oil consumption: 2-3.4 oz/hr
See also
[edit]{{ |lists= *List of aircraft engines }}