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Aviation History
1985
1985 - 1243.PDF
DEFENCE Handle • release seeing and toad equalizer va.ve latch-only Roller conveyors ACS ramp rail Creating rollers [ *ri L 1 JP + TLR J [JP+TLR" r 5T8xBtTLR 1 CFV 5T8x8+TLR 5T EXPAN VAN TAC INTERP 2 1/2T VAN 5T EXPAN VAN \l TAC INTERP l 2 1/2T VAN CMD | j JP +TLR | LT REC |. HMMWV "" j VEH • L-^=zz. CFV ^~=^-^ Apc _POST_ M880 [JPTTT^] ^ )AT + TLRH [STTRK + I I/2TTLR1LJEEP =\~r- i^"- —=- —H[JEEP G GOA + APC APC M5TTRK + 1 1/2TTLR I !^g^Bga&^ C-17 LANDING CHARACTERISTICS | | Dry runway r~\ Wet runway J E 3f- C-130H C-5 C-141 C-130H C-141 C-5 FY C-17 C-5 C-5/C-17 funding $ x 1,000 million) 1985 0-123 2-1 1986 0-460 2-26 1987 1988 0-880 2-59 2-21 1989 2 28 line. The actual time that the production peak is first attained will be decided in 1987. The FSD phase includes preliminary design up to crit ical design reviews, followed by detail design, then tooling design and fabrication. Three C-17s will be built in FSD. One will fly, and the two static test airframes will be used for load estimation and fatigue- life prognosis. No full-scale engineering mockup is plan ned; instead, assembly of the flight-test aircraft will be brought forward by six months. The early start will give enough leeway to deter mine fits and tolerances of components and systems. By not building a mockup, the company estimates that it will save some $138 million. But McDonnell Douglas has built engineering devel opment mockups of the C-17 cargo compartment, a separate cargo floor, cockpit, wing carry-through section, empennage, and engine pylon. The cargo compartment mockup has been load demon strated to its design capacity of 170,0001b fully loaded. The ramp has a 40,0001b limit. This compares with ramp- load limits of 5,0001b on the C-130 Hercules, 7,5001b on the C-141 Starlifter, and 15,0001b each on the nose and tail ramp of the C-5 Galaxy. The cargo compartment floor mockup is a 20ft section which includes the ramp hinge, roller sections, air drop system (ADS) rails, and logis tics rails for cargo to be ground offloaded. Three types of control configurations are being tested for cargo hand- Left The cargo compartment's floor loading is 112lb/in2 (up to 6,200lb/ft length). Maximum payload is 172,2001b ling; push-pull rods, hydrau lics, and electrical. The ramp has two completely separate 3,0001b/in2 hydraulic systems and two electrical systems to enhance combat offload survivability. The paratroop doors are 43in wide and 80in high, and shielded by wind deflectors when open. Paratroop drop limits are 115kt-250kt from 300ft to 25,000ft. Up to 120 combat-ready paratroopers can be carried, or 244 troops. In the maxpax role the C-17 can be fitted with toilets, known (rather coyly for para troops) as "comfort pallets". The loadmaster's station is just aft of the flightdeck, seated at a console over looking the cargo compart ment. A single loadmaster can operate all systems and func tions aft of his station, open ing and closing the aft doors and ramp, para doors, oxygen, internal lights, and load/ paratroop "standby" and "go" lights. All of the loadmaster's controls are triple redundant. Two-crew cockpit The cockpit has four seats; but only two-pilot operation on normal sorties. Each pilot has two head-down Efis displays plus a Hud. All the usual flight and navigation instrumentation (GPS com patible) can be displayed, plus air drop aiming points. A crew rest area is just behind the cockpit. The C-17 will also set new standards in ground oper ations. The aircraft's reverse thrust exhausts forward and upward to avoid stirring up clouds of dust and debris. The tail-cone-mounted auxiliary power unit also exhausts up and away from the ground. The 75kVA APU will deliver up to 3001b/min of bleed air. The supercritical section wing is span limited to 165ft by a requirement for the C-17 to reverse out from between two other C-17s, each parked 25ft from the centre aircraft, and to be able to turn round on a 50ft taxiway. The C-17's turning circle is 82ft. Footprint per maingear wheel is 43,7001b at maximum gross weight and nominal e.g. each nosewheel has a foot print of 22,8001b. FLIGHT International, 27 April 1985
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