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The origin of the 421 (and 414) traces back to the 411, the 421 began it's life as a pressurised development of the 411.
The prototype 421 took to the skies for the first time in October 1965 (three years after the 411). In comparison to the 411 on which it was based, the 421 introduced a cabin pressurisation system, more powerful geared and turbocharged GTSIO-520-D engines and a higher max takeoff weight. First improvements to the 421 were offered with the 421A of 1969, but the 421B Golden Eagle of 1970 featured a number of significant improvements including lengthened nose and wing span, while the engines retained their power to higher altitudes than before. The final expression of the 421 was the 421C available from late 1975, with a bonded wet wing and no tip tanks, higher vertical tail, more efficient props and new trailing link undercarriage.
The 414 was developed as a less powerful, lighter, simpler and lower cost 421. First flown in 1968, it entered production in 1969. It features the wings and fuselage of the 401 and 402 (themselves lighter developments of the 411), plus direct drive, rather than geared engines. The improved 414A Chancellor appeared in 1978, introducing the bonded wet wing without tip tanks. It remained in production until 1985. |
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| Seating (normal) |
6 |
Max Takeoff (lbs) |
6,840 |
| Seating (maximum) |
8 |
Certified Ceiling (ft) |
26,000 |
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| Engines |
2 Continental GTSIO-520D |
To (Sealevel, ISA Temp) (ft) |
2,516 |
| Output lbs ea. Flat Rating |
374 shp |
Landing Distance (ft) |
2,110 |
| Maximum Mach No. |
- |
Max Range (fuel) (nm) |
1,320 |
| High Speed Cruise (Kts) |
240 |
Max Range (payload) (nm) |
526 |
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| Flight Time 300nm |
- |
Flight Time 1000nm |
- |
| Flight Time 600nm |
- |
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| External |
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Internal |
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| Length (ft) |
33.80 |
Length (ft) |
- |
| Height (ft) |
11.70 |
Height (ft) |
- |
| Span (ft) |
39.90 |
Width: Max floor (ft) |
- |
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