Specifications

SECTION I
DESCRIPTION AND SPECIFICATIONS
MODEL 560
ENVIRONMENTAL CONTROL
Cabin pressurization utilizes bleed air from the engines which is routed through precoolers before
being conditioned by an air cycle machine. Temperature is controllable over a wide range and the system
provides sufficient pressure to maintain an 8000-foot cabin at a cruise altitude of 45,000 feet. The oxygen
system automatically supplies oxygen to the cockpit quick-donning masks and to the cabin dropout type
masks in the event of excessive cabin altitude. Additionally, air is conditioned by a vapor cycle machine.
AVIONICS
The standard, factory-installed avionics package includes weather radar, dual altitude reporting
transponders, and a Primus 1000 integrated flight director system which incorporates the autopilot. Air
traffic control and other communication is provided by two VHF transceivers. Navigation equipment
includes a digitally tuned ADF, dual DME and VOR/localizer/glideslope/marker beacon receivers. A GNS-XL
flight management system is installed on the center pedestal. The pilot’s and copilot’s positions are
equipped with a dual electronic flight instrument system (EFIS), and a multifunction display is mounted on
the center instrument panel. An emergency locator beacon, a cockpit voice recorder, and a Flitefone VI
telephone system are also installed as standard equipment.
CABIN DOOR
The passenger/crew entry door is located on the left side of the fuselage at the forward side of the
passenger compartment. The door is flush fitting and the inner surface is covered with upholstery panels
that blend with the airplane interior decor. The door is constructed of frames, pin fittings and stiffeners
covered by an outer skin and an inner upholstered panel. The door is attached to the fuselage structure by
a single hinge. A window is located in the door.
An extruded rubber secondary door seal is installed around the outer edge of the door under the
primary (inflatable) door seal. The primary (inflatable) door seal is a molded rubber continuous ring installed
in a retainer on the door. A rain seal is installed on the cabin door frame next to the door hinge. Bleed air
from the engine provides pressure for inflation of the seal. A bleed air fitting is attached to the fuselage in
the hinge area and when the door is closed and latched. A fitting in the hinge mates with the fuselage fitting
and pressurizes the inside of the hinge. Air is distributed from the hinge to the pressure seal.
The door can be opened from either inside or outside the airplane by handles attached to a common
shaft. Both handles are retained in the stowed position by springs. When either handle is rotated out of the
stowed position, lock pins are retracted into the door, allowing the door to swing outward to the open
position. A hold-open latch on the doorframe retains the door in this position.
Five indicator windows (inspection holes) are installed in the passenger/crew door. The indicator
windows are installed on the inside of the door to provide a visual means of viewing the position of the
linkage. A window is located by each of the two top and bottom locking pins and one window is located by
the inside door handle.
A door warning switch is installed in the fuselage door frame in a position so the forward lower locking
pin actuates the switch.
EMERGENCY EXIT DOOR
A removable emergency exit door is located on the right side of the fuselage toward the forward end
of the passenger compartment. The forward right passenger compartment window is located in the door.
The door is of the plug type and is installed or removed from inside the airplane. This exit is an alternate to
the cabin door in the event of a crash landing and is the primary exit in a ditching situation.
The emergency exit door is locked in place by a latch pin at the top and two retainers at the bottom of
the door. The latch pins are actuated by a latching mechanism and an inside and outside handle. The
retainers at the bottom are fixed and inserted behind two stop blocks installed on the door frame. The outer
handle housing of the emergency door incorporates a moisture drain. Also, the inside surface of the handle
and housing is coated with teflon to prevent ice adhesion.
The emergency exit door is opened by rotating either handle to disengage the latch pin. Remove
locking pin and plastic cover over inside handle when opening door from inside airplane. Allow top of door
to extend inside the airplane until door clears the door frame. Raise door to clear stop blocks and remove
door.
During emergency evacuation, the emergency exit door should be completely removed and thrown
outside the airplane through its own open exit to keep the escape route clear inside the cabin.
I 1-4 Configuration AA 56OMB-01