Gulfstream V User manual

DIMENSIONS AND AREAS, MAJOR COMPONENT LOCATIONS
2A-06-10: General
The Gulfstream V is powered by two BMW / Rolls Royce BR710 high bypass ratio
turbofan engines mounted on pylons located on the aft upper fuselage. The aircraft is
supported by a fully retractable tricycle landing gear.
The fuselage is of semimonocoque metal construction.All areas are pressurized with the
exception of the nose radome and aft equipment (tail) compartment. The fuselage is
divided lengthwise into an above-floor section and a below-floor section.
The wing contains the integral fuel tanks in its primary structure. Forward of the fuel
tanks, on the leading edge, wing anti-icing ducts and landing lights are installed. Aft of
the fuel tanks, on the trailing edge, primary and secondary flight controls are installed.
The primary flight controls are the ailerons, with the left aileron having an adjustable trim
tab. Secondary flight controls include the flaps (one per side) and spoilers (three per
side). Winglets are installed at the outboard end of each wing to aid in drag reduction and
improve fuel economy. Also contained within the wing is the main landing gear
supporting structure.
The tail section of the aircraft consists of a fixed vertical stabilizer and an adjustable
horizontal stabilizer. Primary flight controls contained within the tail section are left and
right elevators attached to the trailing edge of the horizontal stabilizer, and a rudder
attached to the trailing edge of the vertical stabilizer. The elevators have adjustable trim
tabs incorporated, whereas rudder trim is accomplished by displacement of the entire
surface.
The Dimensions, Areas and Major Component Locations section is divided into the
following subsections:
•2A-06-20: Principal Dimensions
•2A-06-30: Entrances, Exits and External Access Doors
•2A-06-40: Flight Crew Station Components
2A-06-20: Principal Dimensions
1. Dimensions, Areas and Distances:
See Figure 1 through Figure 4 for principal dimensions, areas and distances.
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Exterior Dimensions and Areas
Figure 1
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Fuselage Dimensions and Areas
Figure 2
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Turning Dimensions and Distances
Figure 3
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2. General Weight Data:
A. Maximum Takeoff Gross Weight (TOGW): 90,500 lb (41050 kg)
B. Maximum Zero Fuel Weight: 54,500 lb (24721 kg)
C. Maximum Usable Fuel Weight:
(1) Aircraft Production Numbers 501 Through 548 Without ASC 50:
41,026 lb (18610 kg)
(2) Aircraft Production Numbers 549 And Subsequent, Aircraft
Production Numbers 501 Through 548 With ASC 50:
41,300 lb (18734 kg)
Danger and Caution Areas
Figure 4
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D. Manufacturer’s Bare Empty Weight: 38,000 lb (17236 kg)
E. Maximum Wing Loading (at TOGW): 78.3 lb / ft
2
(10.83m/kg)
3. General Powerplant Data:
A. Manufacturer: BMW / Rolls Royce
B. Model: BR710A1-10
C. Number Installed: 2
D. Takeoff Thrust (Sea Level): 14,750 lb (6691 kg)
E. Fan Area / Radius: 1826.79 in
2
/ 24.114 in
F. Takeoff Thrust-To-Weight Ratio: 0.325
4. External Component Locations:
A. Antenna Locations:
NOTE:
See Section 2A-23-00: Communications, for
descriptions of the aircraft antennas.
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External Antennas
Figure 5
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B. Light Locations:
NOTE:
See Section 2A-33-00: Lighting for descriptions of the
external lights.
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External Lights
Figure 6
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2A-06-30: Entrances, Exits and External Doors
(See Figure 7.)
For a description of operation of the following components, see Section 2A-52-00: Doors
System Description.
•Main Entrance Door
•External Baggage Door
•Internal Baggage Door
•Tail Compartment Door
•Emergency Exit Windows
For a description of the DOORS synoptic page, see Section 2B-03-00: Engine
Instruments and Crew Alerting system.
Entrances, Exits and External Doors
Figure 7
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Entrances, Exits and External Doors
Figure 8 (Sheet 1 of 5)
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Entrances, Exits and External Doors
Figure 8 (Sheet 2 of 5)
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Entrances, Exits and External Doors (Airplanes 501 - 674)
Figure 8 (Sheet 3 of 5)
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Entrances, Exits and External Doors (Airplanes 675 and Subsequent)
Figure 8 (Sheet 4 of 5)
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Entrances, Exits and External Doors
Figure 8 (Sheet 5 of 5)
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2A-06-40: Flight Crew Station Components
1. Cockpit Layout and Components:
(See Figure 9 through Figure 16.)
NOTE:
The panels, units and components shown in Figure 9
through Figure 16 are representative of installed
equipment. See the appropriate system descriptions
for the most current configuration.
2. Electronic Equipment Rack Layout and Components:
(See Figure 17 and Figure 18.)
The Gulfstream V has two (2) Electronic Equipment Racks (EERs) located aft of
the cockpit: the Left EER (LEER) and Right EER (REER). Each EER contains the
following items necessary for the safe and efficient operation of the aircraft:
•Electrical and avionics units and components, primarily designed as Line-
Replaceable Units (LRUs).
•A Circuit Breaker (CB) panel.
•A Power Distribution Box (PDB) with an associated CB panel.
In addition, the LEER contains a System Monitor/Test panel. This panel is used
for refueling, and for system maintenance, testing and fault isolation.
NOTE:
The panels, units and components shown in Figure 17
and Figure 18 are representative of installed
equipment. See the appropriate system descriptions
for the most current configuration.
3. Flight Compartment Seating:
A. General:
Seating in the flight compartment is provided for three (3) occupants: Pilot,
Copilot, and Observer. Seats for the pilot and copilot are identical and
remain accessible at all times. Each uses a five (5) point harness for the
safe restraint of the occupant.
B. Operation of the Pilot’s and Copilot’s Seats:
(See Figure 19.)
For optimum comfort and safety, the following description is provided to
ensure the seat is properly adjusted and positioned:
(1) Adjust the thigh pads, if adjustable thigh pads are fitted, to
approximately mid-position.
(2) Adjust the lumbar in/out support and up/down support to the out and
down positions.
(3) Adjust the recline angle to approximately mid-position.
(4) Adjust the back cushion to approximately mid-position.
(5) Ensure the occupant is correctly positioned in the seat pan.
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(6) Adjust the recline angle until the shoulders are positioned at the
desired sitting angle.
(7) Adjust the lumbar in/out support and up/down support to the desired
positions.
(8) Using the vertical adjustment control and fore/aft track lock control,
position the seat to properly align the occupant with the Design Eye
Locator on the center windshield post.
(9) Verify thigh pads “break away” to allow sufficient movement on the
rudder pedals and toe brakes.
C. Operation of the Observer’s Seat:
(See Figure 20.)
The observer’s seat is normally stowed until needed. A four (4) point
harness is used to restrain the occupant.
The seat is accessed by lifting the handle at the base of the seat and
manually pulling the seat out of the stowage area. When the seat is out, the
same handle is used to allow movement to either of two (2) use positions,
or to allow stowage.
With the seat out, the seat pan is pushed down for occupancy and held
down by the occupant’s weight. Upon rising, the seat pan automatically
retracts.
CAUTION
ENSURE THE LAPBELT RESTRAINT IS PROPERLY
STORED IN THE RESTRAINT POCKET PRIOR TO
ALLOWING THE SEAT PAN TO CLOSE. FAILURE TO
DO SO COULD CUT OR FRAY THE LAPBELT
RESTRAINT.
When seated, the following adjustments can be made:
•Forward or Aft Positioning: Lifting a paddle-type lever on the right
hand side of the seat allows positioning and locking in a forward or
aft position. There are no intermediate positions.
•Vertical Positioning: Rotation of a handle on the right hand side of
the seat allows a six (6) inch vertical positioning range. To go up, the
occupant must lift some weight off of the seat. To go down, the
occupant must remain on the seat.
•Swivel Positioning: Rotation of a handle on the left hand side of the
seat allows counter-clockwise rotation to a forward-facing or
rearward-facing position. There are no intermediate positions.
•Recline Positioning: Rotation of a handle on the right hand side of
the backrest allows reclining up to thirty (30) degrees from vertical in
three (3) degree increments. The backrest will automatically return
to the upright position by rotation of the handle and removing weight
from the backrest.
•Armrest Positioning: The left and right armrests are stowed in a
cavity on the backrest shroud. For use, they are pulled out and
rotated forward to the normal position. Adjustment controls are
located on the forward underside of the armrests.
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•Tray Table Provisions: There exists a provision for a detachable tray
table, normally stored nearby, to be attached to the seat pan. When
attached, the table is capable of 180 degrees of rotation to ensure
comfort.
4. Standard Aircraft Equipment and Furnishings:
The equipment listed in the following tables is supplied as standard equipment on
each aircraft:
Cockpit Furnishings
Quantity Item
2 Logo Button
2 Battery Flashlight (SN 501 – 630)
2 Rechargeable Maglite (SN 631 & subs)
3 Smoke Goggles
Publications
Quantity Item
1 Weight and Balance Report
2 Engine Log Book
1 Aircraft Log Book
1 APU Log Book
1 Flight Manual
Ground Support
Quantity Item
1 Protective Covers and Plugs Kit
2 Main Landing Gear Safety Pin
2 Main Landing Gear Door Safety Pin
1 Nose Landing Gear Safety Pin
1 Nose Landing Gear Door Safety Pin
4 Brake Heat Pack Half Life Spacer
1 Aileron/Elevator Disconnect Handle
Reset Tool
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Cockpit Areas
Figure 9
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Cockpit Overhead Panel
Figure 10
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