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Pilot / Copilot Seats
Figure 19
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-06-00
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May 30/02
Revision 7
OPERATING MANUAL
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2A-06-00 PRODUCTION AIRCRAFT SYSTEMS
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May 30/02
AIR CONDITIONING
2A-21-10: General
The air conditioning system for the Gulfstream IV is designed to provide all areas within
the pressure vessel with a safe and comfortable temperature and pressure (cabin
altitude) throughout the aircraft’s operating envelope. The system employs a “dual pack”
concept and, although each pack is controlled separately, failure of one pack still leaves
the remaining pack capable of supplying conditioned air to both cabin and cockpit, if
required.
To achieve this function, the air conditioning system provides the flight crew with a
means to accomplish the following:
• Control, regulate and monitor the amount of conditioned air within the pressure
vessel to achieve and maintain selected or preprogrammed cabin pressure
(altitude), while still allowing exchange of the air at regular intervals for occupant
comfort. This is accomplished by modulation of a single outflow valve. The outflow
valve is automatically controlled by the cabin pressure controller in the normal
operating mode, but can be controlled manually.
• Select and control bleed air entering and exiting two environmental control system
refrigeration pack assemblies, referred to as the Left and Right ECS Packs.
Source air into the ECS Packs is provided to a bleed air manifold by either
external air or APU air (while on the ground), or by the aircraft’s engines (on
ground or in flight). Through use of an isolation valve, air from the bleed air
manifold can be directed to either ECS Pack. This results in a constant mass of
conditioned air for all areas within the pressure vessel.
• Control the temperature of conditioned air delivered to the cockpit and cabin areas
(referred to as zones) within the pressure vessel. This is done using the two ECS
packs to cool incoming air and deliver it to a conditioned air manifold. Valves mix
hot bleed air with cold conditioned air to modulate the temperature of the air
coming from the manifold into the pressure vessel. Cockpit control and indication
is also provided.
The Air Conditioning system is divided into the following subsystems:
• 2A-21-20: Pressurization Control System
• 2A-21-30: Airflow and Temperature Control System
2A-21-20: Pressurization System
1. General Description:
The pressurization system controls, regulates and monitors the amount of
conditioned air within the pressure vessel to achieve and maintain a safe and
comfortable cabin pressure (cabin altitude), up to the airplane’s maximum
operating altitude. While normally preprogrammed, cabin altitude can also be
controlled manually. Cabin conditioned air is also exchanged at regular intervals
for occupant comfort.
With airflow supplied from the ECS packs, the pressurization system maintains
cabin altitude by regulating the amount of air exhausted overboard through a
single outflow valve. Once the flight crew has programmed the system, operation
is virtually automatic.
The pressurization system is capable of maintaining a cabin altitude of 6,550 feet
at a maximum inflight altitude of 45,000 feet. Sea level cabin pressure can be
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-21-00
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May 30/02
Revision 7
maintained to a maximum inflight altitude of 22,000 feet. If cabin altitude should
exceed 10,000 feet, warnings and annunciations are provided to the flight crew so
that appropriate action may be taken.
The pressurization system performs the following functions:
• Automatically maintains selected cabin altitude through isobaric
pressurized operation
• Automatically limits maximum cabin pressure differential
• Provides safety pressure relief operation
• Provides negative (vacuum) pressure differential control
• Allows manual barometric correction for pre-programmed Landing Field
Elevation (LFE)
• Permits manual cabin altitude control through control of the outflow valve
• Automatically limits cabin altitude rate-of-change to a maximum of 3,000
feet-per-minute (FPM) during pressurization and depressurization
• Provides crew-selected cabin altitude rate-of-change
• Regulates and smooths cabin pressurization to prevent pressurization
surges or “bumps”
• Provides rapid cabin ventilation for smoke removal
Normally the pressurization system limits cabin pressurization differential to 9.55
　
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