Originally designed in the 1960s as a STOL utility aircraft for both civil and military use. The first prototype flew in 1971.
One hundred and seventy were sold by GAF / ASTA.
Certification in accordance with the Australian Department of Transport air regulation 27 approves the use of N24A as an 18-place airliner in regular public transport as well as in normal operation. N24A is an improved version of the previous ‘stretched’ Nomad N24. It has increased passenger and load carrying capacity with an all-up-weight of 9400 pounds from the original 8500 pounds.

Production ceased in 1984 after safety concerns following a number of accidents and the loss of 54 lives.
Boeing obtained the type certificate via its 1999 acquisition of Rockwell, which had previously acquired ASTA.
Gippsland Aeronautics purchased the GAF N24 Nomad type certificate from Boeing Australia and planned to restart production.

Gallery

N-24
Engine: 2 x Allison 250-B17B, 400 hp.
Seats: 18.
Wing loading: 27 lb/sq.ft.
Pwr loading: 10.5 lb/hp.
Gross wt: 8750 lb.
Empty wt: 4844 lb.
Equipped useful load: 3811 lb.
Payload max fuel: 1451 lb.
Range max fuel/75%: 964nm/5.7hr.
Range max fuel /55%: 1071nm/7.7hr.
Ceiling: 22,500 ft.
Max cruise: 167 kt.
Max range cruise: 140 kt.
Vmc: 62 kt.
Stall: 52-70 kt.
1.3 Vso: 68 kt.
ROC: 1430 fpm.
SE ROC: 280 fpm @ 87 kt.
SE ceiling: 9000 ft.
Min field length: 1100 ft.
Fuel cap: 1770/2360 lb.

N24A
Engines: 2 x Allison 250-B17C, 400 shp.
Props: Hartzell 3-blade, 90-in.
Seats: 17.
Length: 47 ft.
Height: 18.2 ft.
Wingspan: 54.2 ft.
Wing area: 320 sq.ft.
Wing aspect ratio: 9.1.
Maximum ramp weight: 9450 lbs.
Maximum takeoff weight: 9400 lbs.
Standard empty weight: 5480 lbs.
Maximum useful load: 3970 lbs.
Maximum landing weight: 9200 lbs.
Wing loading: 20.9 lbs/sq.ft.
Power loading: 12.2 lbs/hp.
Maximum usable fuel: 1770 lbs.
Best rate of climb: 1313 fpm.
Service ceiling: 23,300 ft.
Maximum single-engine rate of climb: 240 fpm @ 96 kts.
Single-engine climb gradient: 113 ft/nm.
Single-engine ceiling: 11,390 ft.
Maximum speed: 173 kts.
Normal cruise @ 8,000 ft: 169 kts.
Fuel flow @ normal cruise: 335 pph.
Endurance at normal cruise: 5.3 hrs:
Stalling speed clean: 72 kts.
Stalling speed gear/flaps down: 57 kts.
Turbulent-air penetration speed: 134 kts.
Takeoff distance (50ft) 1,710 ft
Landing distance (50 ft) 1,380 ft

In 1965 design studies were started by GAF to find a follow-on production commitment. Interest expressed from commercial operators lead to a twin engined utility transport. Production commenced on the prototypes in January 1970 with flight testing beginning in 1971.

GAF Nomad N22 Article

Conversion to N.22A allowed an increase in AUW.

The final version, launched in May 1985, was the N22C, aimed at the commuter airline market and offering an increased all-up weight of 4,060kg. The N22C was a post-production variant with increased weights, strengthened undercarriage, improved tail structural design and other modifications. Most Nomads delivered from storage after production ended were to this standard and some earlier aircraft were modified.

Three military variants of the N22/N24 Nomad, the utility Missionmaster, the coastal surveillance Searchmaster B with 1200 scan Bendix radar, and the Searchmaster L with 3600 scan Litton radar, were built for five customers.

The Nomad is designed and built by the Government Aircraft Factories in Australia in two models. These are the short-takeoff-and-landing (STOL) Nomad N22B and the Nomad N24A commuter aircraft. Variations on the basic aircraft include the Mission Master, the Search Master for maritime surveillance work, and a photographic and mapping model. The aircraft have proven successful in many countries, often flying over rugged terrain in climates ranging from tropical to subarctic. Its STOL capability, originally developed for Australian military use, has made it ideal for operations in rugged areas such as the highlands of Papua, New Guinea. The N22B, capable of carrying up to 12 passengers, can take off in only 800 feet. The larger N24A is a later development of the basic aircraft capable of carrying more passengers and cargo.

The Nomad is characterized by simplicity of construction and systems, which contribute to its economy of operation. Its two Allison 250-B17C turboprops are rated at 420 shp, producing more than two horsepower per pound of engine weight. The B17C offers an improved single-engine high-altitude performance capability and a more rugged gearbox.

The Royal Thai Air Force received 20 N22B Missionmasters.

Gallery

N22B
Engines: 2 x Allison 250-B17, 416 shp.
Props: Hartzell 3 blade reversible 7 ft 6 in.
Fuel cap: 1030 lt.
Wing span: 54.0 ft (16.46 m).
Length: 41.2 ft (12.57 m).
Height (tail section): 18.12 ft (5.52m).
Main wheel track: 10.6 ft (3.23m).
Wheel base: 12 ft (3.66 m).
Propeller ground clearance: 4 ft (1.22m).
Wing area: 324 sq.ft (30.2 sq.m).
Wing loading at max. gross weight: 26.2 lbsft) 127.9 kg/ sq.m).
Power loading at max. gross weight: 10.2 lbs eshp (4.64 kg eshp).
(Excluding flight deck) – Cabin length: 17.5ft (5.34m).
Cabin height: 5.13ft (1.57m).
Cabin volume: 360 cu.ft (10.2 cu.m).
Cabin door size: 4.06 ft x 4.33 ft (1.24 m x 1.32m).
Baggage compartment volume (nose): 28 cu.ft ( 0.79 cu.m).
Baggage compartment volume (rear): 30 cu.ft (0.85 cu.m).
Take of pwr: 416 eshp (400shp).
Maximum continuous: 400 eshp (385 shp).
Maximum cruise: 380 eshp (366 shp).
Normal internal fuel tanks (usable): 227 Imp gals (1030 lt, 268 U S gals).
Maximum take-off: 8500 lbs (3856 kg).
Maximum landing: 8500 lbs (3856 kg).
Typical operating empty (including commercial interior and avionics): 4730 lbs (2146 kg).
Max fuel capacity (usable): 1793 lbs (813.5 kg).
Tyre size – Nosewheel: 35 p.s i. (241.1 KPa).
Mainwheels (dual): 29 p s i. (199.8 KPa).
All performance quoted at 8500 lbs (3856 kg) TO weight – STOL
Ground roll: 600 ft (183 m).
Distance over 50 ft: 1050 ft (320 m).
FAR 23 Ground roll: 800 ft (244 m).
Distance over 50 ft: 1360 ft (415 m).
STOL Ground roll: 250 ft (76 m).
Distance over 50 ft: 635 ft (194 m).
FAR 23 (no reverse thrust) Ground roll: 655 ft (200 m).
Distance over 50 ft: 1150 ft (351 m).
Stalling Flaps retracted: 68 knots EAS.
Flaps extended: 49 knots EAS.
ROC take-off rating: 1440 fpm (439 m/min).
ROC max. cruise rating: 1260 fpm (384 m/min).
ROC Single engine wax. continuous: 220 fpm (67 m/min).
Service ceiling: 22,500 ft (6858m).
Single engine max continuous rating service ceiling: 10,000 ft (3050 m).
Max. cruise speed — ISA, 5000 ft (1 525 m): 169 kt.
Cruise speed 90% power ISA 5000 ft: 165 kt.
Long range cruise speed 145 kts
TAS: 50 NM wth 3300 lbs (1496kg) payload; 860nm wth 1617lb (733kg).
Max cruise speed (168 knots TAS) range: 50nm wth 3280 lbs (1470 kg) payload; 730nm wth 1617 lbs (733 kg) payload.

N22C Nomad
Engine: 2 x Allison 250.
Installed pwr: 630 kW.
Span: 16.5 m.
Length: 12.6 m.
Wing area: 30 sq.m.
Empty wt: 2092 kg.
MTOW: 4060 kg.
Payload: 1630 kg.
Vne: 200 kts.
Cruise speed: 304 kph.
Initial ROC: 445 m / min.
Ceiling: 7620 m.
T/O run (to 15m): 400 m.
Ldg run (from 15m): 385 m.
Fuel internal: 1018 (+335) lt.
Range (std fuel): 1460 km.
Capacity: 13 pax.