Velocity Edge GX570 Manual do Utilizador descarregar pdf (Página 9)

August 2011, Preliminary

4. FUSELAGE

3. STRUCTURAL DESIGN CRITERIA

The Citation M2 airframe is conventional in design,

incorporating aluminum alloys, steel and other materi-

als as appropriate. Engineering principles using multi-

ple load paths, low stress levels and small panel size

are incorporated in the primary structure. Design

maneuver limit load factors are -1.52 Gs to +3.8 Gs.

Ultimate loads are defined as 1.5 times the limit loads.

The structure supports a nominal maximum cabin pres-

sure differential of 8.5 psi (.59 bar).

Limit Speeds

at Sea Level to 30,500 ft (9,296 m) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 263 KIAS (487 km/hr, 303 mph)

at 30,500 ft (9,296 m) and above . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Mach 0.71 (indicated)

Flap Extension Speeds

0° to 15° Extension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS (370 km/hr, 230 mph)

15° to 35° Extension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 161 KIAS (298 km/hr, 185 mph)

Landing Gear Operating and Extended Speed

(retracting) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 175 KIAS (324 km/hr, 201 mph)

(extending) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 186 KIAS (344 km/hr, 214 mph)

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 186 KIAS (344 km/hr, 214 mph)

The Model 525 fuselage has a constant circular cross

section and is attached to the wing without any cutouts

for the spar. A dropped isle from just behind the cockpit

through the lavatory makes moving about the cabin eas-

ier. The keyed cabin door is located on the forward left-

hand side of the fuselage. It has 12 locking pins and two

pressure seals and is hinged forward with a folding two-

step entry stair mounted just inside the entrance. A plug-

type emergency exit is located on the aft right-hand side

of the cabin. The windshields are designed to meet bird

resistance requirements of 14 CFR Part 25. Framing

assemblies surround the main door opening, emergency

exit, and windshields to provide structural continuity.

The nose section includes a generous baggage com-

partment from which the avionics bay, oxygen bottle,

and windshield alcohol supply are accessible. Behind

the composite radome is the high-resolution weather

radar antenna and processor.

The aft fuselage houses the major components of the

hydraulic, environmental, electrical distribution, flight con-

trol, and engine fire extinguishing systems. A baggage

compartment is also located in the tailcone. External

access to both the equipment and the baggage area is

provided through a baggage door on the lower left-hand

side of the aft fuselage and removable exterior panels.

5. WING

The straight wing design of the M2 incorporates a natu-

ral laminar flow airfoil. The wing structure is a three spar

design with a shallow drop in the center section to per-

mit attachment of the fuselage without interruption of the

cabin cross-section. Five degrees dihedral contributes to

lateral stability.

Integral fuel tanks are located in each wing. Control sur-

faces on the wing include outboard ailerons, wide span

flaps with a lift-dump feature, and upper and lower surface

speed brakes. The left-hand aileron incorporates a trim tab.

The wing leading edges are anti-iced using engine bleed

air. Aluminum fairings blend the wing and fuselage for

minimum drag. The landing lights consist of industry

proven OSRAM LED technology and are integrated with

a Pulselight system which are mounted below the fuse-

lage in the fairing. The wing tips include LED position

and anti-collision lights and static wicks.

The empennage section is a T-tail design with a one-

piece horizontal stabilizer. The horizontal stabilizer's lead-

ing edge is equipped with pneumatic de-ice boots. The

rudder and the elevators have pilot-controlled trim tabs. A

tail logo light is standard with a red LED ground recognition

light mounted on the top.

6. EMPENNAGE

1 2 3 4 5 6 7 8 9 10 11 12 13 14 ... 23 24

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