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following major system components:
• Bleed air ducting
• Air conditioning system components
• Battery chargers and converters
• Electrical junction boxes
• Engine and APU fire extinguisher bottles and lines
• Elevator and stall barrier control quadrant
• Horizontal stabilizer dwell box assembly
• Utility hydraulic system pump
• Combined and Flight hydraulic system reservoirs and accumulators
• Hydraulic reservoir replenishment system
• Engine oil replenishment system
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.
3. Pylons:
The pylon assembly, located between the engine nacelle and fuselage, supports
the engine and transmits thrust to the airframe. Shaped much like an airfoil, it
contains passageways for engine services and controls. In addition, each pylon
contains a precooler assembly with bypass ducting and a control valve that uses
engine fan air to regulate High Pressure (HP) turbine bleed air temperature.
OPERATING MANUAL
2A-06-00 PRODUCTION AIRCRAFT SYSTEMS
Page 2
May 30/02
Revision 7
4. Powerplant:
The Gulfstream IV is powered by two Rolls-Royce Tay Mark 611-8 high bypass
ratio turbofan engines.
The Tay Mark 611-8 turbofan engine is a two spool engine with a single-stage Low
Pressure (LP) compressor (fan), a three-stage Intermediate Pressure (IP)
compressor, and a twelve stage High Pressure (HP) compressor. Immediately
following the HP compressor is a diffuser case and a turbo-annular combustion
section composed of ten chambers. Hot gases produced in the combustion
section drive a two-stage HP turbine and a three-stage LP turbine. The HP turbine
drives the HP compressor while the LP turbine drives the IP and LP compressors.
Each engine has a hydraulically powered thrust reverser that directs engine thrust
forward to reduce landing roll and brake wear.
Each engine is encased in a nacelle (or cowling) that includes a nose cowl that
forms the engine air inlet, a fixed cowl on the inboard side of the engine, and
upper and lower hinged cowls that allow access to the engine.
For detailed descriptions and illustrations of the engine, its accessories and
systems, see Sections 2A-71-00 through 2A-80-00.
5. Stabilizer:
A fully cantilevered, sweptback vertical stabilizer is attached to the upper rear
fuselage. The High Frequency (HF) antenna is built into the vertical stabilizer
leading edge; the rudder is attached to the trailing edge on the rear spar. At the
top of the rear spar is the horizontal stabilizer pivot point. The VOR/Localizer
antennas are attached to the left and right sides of the vertical stabilizer.
A sweptback horizontal stabilizer is attached to the top of the vertical stabilizer.
The horizontal stabilizer pivots at the vertical stabilizer rear spar, and an actuator
in the forward upper portion of the vertical stabilizer drives the horizontal stabilizer
leading edge up or down to compensate for flap extension or retraction. Elevators
are attached to the trailing edge of the horizontal stabilizer.
6. Wing:
The Gulfstream IV wing is an all metal, fully cantilevered wing with a 3° dihedral
and a sweepback of approximately 27°. Each wing consists of forward and rear
spars covered by aluminum alloy skin panels. Ribs between the forward and rear
spars carry airloads, define airfoil shape and act as fuel baffles for the integral fuel
tanks. A sealed rib at the fuselage centerline and winglet attach point define the
inboard and outboard confines of the wing fuel tank.
A Fowler-type flap and an aileron attach to each wing’s rear spar. A hydraulically
operated single panel ground spoiler and two flight spoiler panels attach to each
wing’s rear structure. When extended, the ground spoiler panels destroy lift and
increase drag during landing rollout. The flight spoilers increase drag in flight to
slow the aircraft.
A winglet is attached to the outboard edge of each wing. Winglets increase the
efficiency of the wing by decreasing drag and improving airflow over the wing’s
upper surface. Vortex generators are installed on the wing’s upper surface to
improve high speed performance and smooth the airflow over the flight controls.
The main landing gear is attached to the wing structure between the forward and
rear spars. When retracted, the landing gear is stored in a covered wheel well.
　
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