Proposed US military designation: RC-20
TYPE: Long-range business jet
PROGRAMME: Development, then as GIV-X and unannounced, started 2001; first of four development aircraft (c/n 4001/N401SR) flew 30 April 2003, followed by c/n 4002/N442SR on 21 June, c/n 2003/N403SR on 22 June and c/n 4004/N450GA on 18 September; formal announcement and public debut (N450GA) at NBAA Convention in Orlando, Florida 6 October 2003; more than 400 hours of flight testing in 117 sorties completed by early 8 December 2003; FAA certification scheduled for third quarter 2004, followed by EASA validation in fourth quarter, and first customer deliveries in second quarter 2005. Selected 7 October 2003 as aerial platform for Northrop Grumman's submission for the US Army's Aerial Common Sensor (ACS) programme, with requirement for up to 38 aircraft and potential US Navy requirement for up to 20 aircraft.
COSTS: US$33 million (2003).
DESIGN FEATURES: Combines wing and tail unit of G400 with a fuselage stretched by 0.30 m (1 ft 0 in), cabin door repositioned, G550 flight deck and nose section, and Rolls-Royce Tay Mk 611-8C turhofans housed in G550-type nacelles.
POWER PLANT: Two Rolls-Royce Tay Mk 611-8C turbofans, each rated at 61.6 kN (13,850 lb st), with FADEC. Thrust reversers standard.
SYSTEMS: Honeywell 36-150GIV APU, with air-start and run capability up to 11,280 m (37,000 ft). Pressurisation system maintains a 1,830 m (6,000 ft) cabin altitude to 12,500 m (41,000 ft).
AVIONICS: Honeywell Primus Epic PlaneView cockpit, as described for G550, with HUD and EVS standard.
| DIMENSIONS, EXTERNAL: | |
| Wing span | 23.72 m (77 ft 10 in) |
| Length overall | 27.23 m (89 ft 4 in) |
| Height | 7.67 m (25 ft 2 in) |
| DIMENSIONS, INTERNAL: | |
| Cabin: Length | 13.74 m (45 ft 1 in) |
| Max width | 2.23 m (7 ft 4 in) |
| Max height | 1.88 m (6 ft 2 in) |
| Volume | 43,2 m3(1,525 cu ft) |
| Baggage compartment volume | 4.8 m3 (169 cu ft) |
| WEIGHTS AND LOADINGS: | |
| Basic operating weight | 19,504 kg (43,000 lb) |
| Payload: max | 2,722 kg (6,000 lb) |
| with max fuel | 816 kg (1,800 lb) |
| Max fuel weight | 13,381 kg (29,500 lb) |
| Max T-O weight | 33,520 kg (73,900 lb) |
| Max landing weight | 29,937 kg (66,000 lb) |
| Max zero-fuel weight | 22,226 kg (49,000 lb) |
| Max wing loading | 379.6 kg/m2 (77.76 lb/sq ft) |
| Max power loading | 272 kg/kN (2.67 lb/lb st) |
| PERFORMANCE: | |
| Max operating Mach No. (MMO) | M0.88 |
| Normal cruising speed | M0.80 (459 kt; 850 km/h; 528 mph) |
| Time to climb to FL410 | 23 min |
| Initial cruising altitude | 12,500 m (41,000 ft) |
| Maximum certified altitude | 13,716 m (45,000 ft) |
| TO run | 1,661 m (5,450 ft) |
| Landing run | 972 m (3,190 ft) |
| Range with eight passengers at Mach 0.80, NBAA IFR reserves | 4,350 n miles (8,056 km; 5,006 miles) |
