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door is powered by the Auxiliary (AUX) hydraulic pump.
3. Baggage Door:
An inward opening, plug-type baggage compartment door is installed on the left
side of the aft fuselage. It can be opened from either inside or outside the aircraft.
Neither electrical nor hydraulic power is required to open the door. See Section
2A-52-40, Baggage Doors, for a description of the baggage door.
4. Tail Compartment Door:
The tail compartment is accessed through an outward opening door on the lower
rear fuselage. A removable telescoping ladder is attached to the door. The ladder
can also be removed and used to reach engine areas for inspection and
maintenance. See Section 2A-52-50, Tail Compartment Door, for a description of
the tail compartment door.
5. Emergency Exit Windows:
A. Aircraft Without ASC 213 (Cargo Door):
The two aft cabin windows on the left and right fuselage are manufactured
and designated as Type II emergency exit windows. Specifically, they are
designated as the primary emergency exits from the cabin. (The main
entrance door and baggage door are Type I emergency exits, designated
as secondary emergency exits, to be used only at the direction of the flight
crew.)
The emergency exit windows can be manually opened from either inside or
outside the aircraft at all times. Pulling the EMERGENCY EXIT handle
releases the window, allowing the window to be pulled inward from its
fuselage frame.
See Section 2A-52-30: Emergency Exits, for a description of the
emergency exit windows.
B. Aircraft With ASC 213 (Cargo Door):
On aircraft with a cargo door, there is a single Type II emergency exit
opposite the main entrance door, and a Type III overwing emergency exit
over each wing where the aft cabin window would normally be located. The
Type II emergency exit measures 44” high and 20” wide, while the Type III
emergency exits are 36” high and 20” wide. They are designated as the
primary emergency exits from the cabin.
Both the Type II and Type III emergency exits can be manually opened
from either inside or outside the aircraft at all times. When inside the
aircraft, releasing and then pulling the EMERGENCY EXIT handle releases
the exit. When outside the aircraft, pushing a flush plate inward releases
the exit.
The main entrance door and baggage door are Type I emergency exits,
designated as secondary emergency exits, to be used only at the direction
of the flight crew. The location, type and number of emergency exits in
aircraft with ASC 213 incorporated meet all civil aviation regulations for
high-denstity seating arrangements (more than 19 passengers).
OPERATING MANUAL
2A-06-00 PRODUCTION AIRCRAFT SYSTEMS
Page 14
May 30/02
Revision 7
External Doors
Figure 7
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-06-00
Page 15
May 30/02
Revision 7
Entrances, Exits and External Doors (Aircraft Without ASC 213)
Figure 8
OPERATING MANUAL
2A-06-00 PRODUCTION AIRCRAFT SYSTEMS
Page 16
May 30/02
Revision 7
2A-06-40: Flight Crew Station Components
1. General:
The Gulfstream IV cockpit is conventionally arranged and contains two flight crew
stations with individually adjustable seats. The logical arrangement of each station
allows easy access to all aircraft controls and displays. A two-piece, electrically
Entrances, Exits and External Doors (Aircraft With ASC 213)
Figure 9
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-06-00
Page 17
May 30/02
Revision 7
heated, bird-proof and splinter-proof windshield and two fixed side windows
enclose the cockpit.
NOTE:
Equipment and furnishings shown in Figure 10
through Figure 19 are representative of the production
standard Gulfstream IV aircraft. Actual layout may
differ due to outfitting. See the appropriate system
descriptions for additional details.
2. Instrument Panels:
(See Figure 12 through Figure 17.)
In front of each crew station is an instrument panel, more commonly known as the
pilot’s and copilot’s flight panel. Each flight panel contains two Display Units
(DUs). One DU is used primarily as a Primary Flight Display (PFD); the other is
used primarily as a Navigation Display (ND). A display controller is located above
each PFD / ND. Each crew station also has a Digital Distance Remote Magnetic
Indicator (DDRMI).
The pilot’s flight panel also has standby engine instruments, an oxygen supply
control panel and a yaw damper / pitch trim control panel. The copilot’s flight panel
also has a Standby Warning Lights Panel (SWLP) (if installed), brake accumulator
　
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