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2. Description of Subsystems, Units and Components:
A. Surface Lock System:
(See Figure 26.)
A single T-shaped handle, located on the right side of the cockpit center
pedestal and labeled GUST LOCK, controls the gust lock system. A spring
loaded trigger is incorporated in the gust lock handle to prevent the handle
from inadvertently being pulled. Releasing the trigger and then raising and
pulling the GUST LOCK handle aft actuates conventional mechanical
linkage consisting of cables, springs, latches and a bungee rod. Moving the
ailerons and rudder to the neutral position and the elevator to the trailing
edge down position allows the gust lock to engage and lock the flight
controls as their linkages reach the locking position. Releasing the trigger
and then lowering the GUST LOCK handle releases the gust lock.
Safety features prevent the gust lock from inadvertently engaging or a
failure of the system preventing gust lock release. With the gust lock
released, the bungee rod acts as a fixed rod to prevent inadvertent flight
control locking. If the gust lock fails when engaged, the springs will unlock
the gust lock.
B. Mechanical Power Lever Interlock:
A mechanical interlock is incorporated in the GUST LOCK handle
mechanism that restricts simultaneous movement of the power levers to a
maximum of six percent above ground idle with the gust lock engaged.
Force applied to advance both power levers simultaneously cannot
override the interlock. To prevent any hydraulic forces acting upon an
engaged gust lock, the gust lock should be released prior to engine starting
and not engaged until all hydraulic pressures read zero.
3. Controls and Indications:
(See Figure 26.)
4. Limitations:
A. Flight Manual Limitations:
There are no limitations for the gust lock system at the time of this revision.
OPERATING MANUAL
2A-27-00 PRODUCTION AIRCRAFT SYSTEMS
Page 84
October 11/02
Revision 8
B. Other Operational Limitations:
The gust lock is effective in protecting the flight controls in wind gusts up to
60 knots.
CAUTION
ENSURE HYDRAULIC PRESSURE IS DEPLETED
PRIOR TO ENGAGING GUST LOCK. CYCLE THE
CONTROLS WITH THE CONTROL COLUMN,
CONTROL WHEEL AND RUDDER PEDALS TO
DEPLETE ANY RESIDUAL PRESSURE.
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-27-00
Page 85
October 11/02
Revision 8
GUST LOCK Handle
Figure 26
OPERATING MANUAL
2A-27-00 PRODUCTION AIRCRAFT SYSTEMS
Page 86
October 11/02
Revision 8
FUEL
2A-28-10: General
1. Introduction:
The fuel system contains and supplies all the necessary fuel for the two turbofan
engines and the Auxiliary Power Unit (APU). There are two integral (wet wing) fuel
tanks, each formed by the respective wing’s structure. Low pressure fuel is
delivered from the tanks to the engine-driven pumps and the APU.
The fuel tanks can be fueled by the conventional “over-the-wing” method or from
a single-point pressure fueling adapter. Defueling may be accomplished by
suction or pumping; any remaining pockets of fuel may then be drained.
Each wing tank contains a fuel hopper as a separate compartment within the tank.
Low pressure fuel is pumped from the hopper through a fuel feed line to the
engine-driven pumps by fuel boost pumps (two per wing). A hydraulic fluid-to-fuel
heat exchanger inside each hopper is used for cooling hydraulic fluid.
An intertank valve in the right fuel hopper allows simultaneous defueling of both
tanks. A crossflow shutoff valve in the left hopper allows fuel balance to be
adjusted.
A fuel temperature bulb installed in the left hopper provides a signal for cockpit
indications of fuel temperature.
A tank vent system provides adequate venting while the aircraft is on the ground.
In flight, this same system slightly pressurizes the tanks.
2. Subsystems Within the Fuel System:
The fuel system is divided into the following subsystems:
• 2A-28-20: Fuel Storage System
• 2A-28-30: Fuel Distribution System
• 2A-28-40: Fuel Indication System
3. Engine Fuel Grades:
A. Kerosene Type:
Fuel conforming to any of the following specifications is approved for use.
Fuels conforming to ASTM Specification ES2-74 are also eligible. Mixing of
fuels is permissible.
Kerosene Type
American British Canadian
ASTM D1655-89, Jet A DEF STAN 91-87 CAN/CGSB-3.23-M86
ASTM D1655-89, Jet A-1 DEF STAN 91-91
MIL-T-83133A, Grade JP-8
French USSR I.A.T.A.
Air 3405/C T-1, TS-1, RT (GOST
10227-86)
T-7 (GOST 12308-66)
1988 Kerosene Type
B. Wide Cut JP-4 Type:
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湾流4操作手册 Gulfstream IV Operating Manual 2(30)
