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the source for the ECS packs), it is recommended that one power
lever be advanced above idle with the isolation valve open and the
opposite engine bleed air be selected off.
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Pneumatics System Block
Diagram: SN 1000-1284
Not Having ASC 364
Figure 1
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Pneumatics System Block
Diagram: SN 1285 and
Subsequent; SN 1000-
1284 Having ASC 364
Figure 2
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Pneumatics System Block Diagram Key
Figure 3
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BLEED AIR Control Panel
Figure 4
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BLEED CONFIG Indicator: SPZ-8000 Equipped Airplanes Having ASC 422A
Figure 5
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Main Entrance Door Seal
System
Figure 6
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Baggage Door Seal
System
Figure 7
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Cargo Door Seal System
Figure 8
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External Starting Air Connection
Figure 9
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APU
2A-49-10: General
The Gulfstream IV is equipped with a GTCP 36-100(G) gas turbine Auxiliary Power Unit
(APU) that serves as an auxiliary supply of electrical power and pneumatic pressure for
airplane systems. The APU is installed in the tail section of the airplane, aft of the
pressure bulkhead within a stainless steel and titanium enclosure. The APU is mounted
transversely on supports, or rails, for ease of maintenance and repair.
The APU can supply both electrical and pneumatic power on the ground, but is restricted
to providing only electrical power in ßight. On the ground, the APU may be started with
the airplane batteries or with an external DC power source. When the APU reaches
normal operating RPM, it is capable of powering the full airplane electrical system and
supplying pneumatic bleed air for air conditioning and engine starting. APU bleed air
output is rated at a nominal 253¡C (487¡F) at a pressure of 47.6 psi minimum. Minimum
bleed air pressure under full load is 30 psi.
In the air, the APU alternator can produce thirty (30) kVA at twenty-two thousand (22,000)
feet, with a linear reduction with altitude to 15 kVA at thirty thousand (30,000) feet for
airplanes SN 1000-1155 (except 1034). On airplanes Serial Number (SN) 1156 and
subsequent (and 1034) the APU air intake is modiÞed with an airscoop that increases
airßow to the APU, allowing a higher operating envelope. For these airplanes, the APU
alternator will supply 30 kVA up to 30,000 feet with a linear reduction of sixty-seven
percent (67%) to 20 kVA at maximum operating altitude of 35,000 feet. This expansion of
the operating envelope requires shedding some of the airplane electrical load. On SN
1156 to 1429 (and 1034) an Electrical Load Warning System (ELWS) provides
indications to the crew of excessive electrical loads and automatically sheds some nonessential
items to reduce the electrical load on the APU. For airplanes SN 1430 and
subsequent, electrical loads are monitored and reduced if necessary by the ßight crew in
response to Crew Alerting System (CAS) messages. For more information, see the
description of the APU AC Power System in section 2A-24-00 of this manual.
The APU assembly is composed of the following subsystems:
• 2A-49-20: APU Powerplant Assembly and Accessories
• 2A-49-30: APU Controls and Indications
2A-49-20: APU Powerplant Assembly and Accessories
1. APU Powerplant:
The APU powerplant assembly is composed of the following subsystems:
• Basic Powerplant
• Starting and Ignition
• Electronic and Fuel Controls
　
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