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the landing gear warning tone.
OFF Lights test off
2.5.3 Interior Lighting (F/A-18F). All controls for the interior lights of the rear cockpit are located
on the INTR LT panel on the right console. The controls operate in the same manner as those in the
front cockpit with two exceptions. There is no MODE switch on the rear cockpit INTR LT panel, and
the rear cockpit LT TEST switch does not illuminate the AOA indexer lights or annunciate the landing
gear warning tone.
A1-F18EA-NFM-000
I-2-38 ORIGINAL
2.6 HYDRAULIC POWER SUPPLY SYSTEM
The hydraulic power supply system is a dual pressure system (3,000 and 5,000 psi). The aircraft uses
hydraulic power to actuate primary flight control surfaces and to run the following utility hydraulic
functions: landing gear, wheel brakes and anti-skid, hook, launch bar, refueling probe, nosewheel
steering (NWS), gun, and parking brake. Two hydraulic accumulators provide emergency hydraulic
power for critical utility functions.
2.6.1 Hydraulic System. The hydraulic power supply system incorporates two independent hydraulic
systems, HYD 1 and HYD 2 (figure 2-15). Each system is divided into two branches providing four
independent hydraulic circuits identified as 1A and 1B for the left system and 2A and 2B for the right
system. HYD 1 circuits are dedicated solely to flight controls. HYD 2A powers both flight controls and
most utility hydraulic functions. HYD 2B powers the flight controls and arresting hook and pressurizes
both the APU and emergency brake accumulators.
All flight control surface actuators are powered by one HYD 1 circuit and one HYD 2 circuit, either
simultaneously or through hydraulic switching valves.
The utility system operates at 3,000 psi only. Two pressure reducers, one on HYD 2A and one on
HYD 2B reduce utility circuit pressure to 3,000 psi when pump output is 5,000 psi.
2.6.1.1 Hydraulic Pumps. Each system is pressurized by a single, dual pressure (3,000 and 5,000 psi),
variable displacement pump mounted on an AMAD. Pump output pressure is commanded by the
FCCs based on aircraft flight condition; with 5,000 psi utilized during high-speed flight when air loads
are high. One pump is capable of powering the entire flight control system in the event of a single
system failure. A hydraulic pressure transducer relays system pressure to a hydraulic pressure gauge
in the cockpit. Hydraulic cautions (HYD 1A, HYD 1B, HYD 2A, HYD 2B) are set when individual
hydraulic pressure switches detect circuit pressure below 1,400 psi.
2.6.1.1.1 Hydraulic Pressure Gauge. The hydraulic pressure gauge is located on the lower right main
instrument panel. The gauge has individual needles for indicating HYD 1 and HYD 2 system pressure.
Tick marks for 3,000 and 5,000 psi are provided. Two white bands indicate the range of acceptable
operation pressure (2,600 to 3,300 psi and 4,500 to 5,400 psi). Since the gauge is ac powered, actual
hydraulic readings are not provided until the first generator is online following engine start. During
shutdown, pressure readings freeze when the last generator drops offline.
2.6.1.2 Hydraulic Reservoirs. Hydraulic fluid is supplied to each system by a separate hydraulic
reservoir. The HYD 2 reservoir is larger than the HYD 1 reservoir in order to accommodate the utility
system.
2.6.1.2.1 Reservoir Level Sensing (RLS) System. Each reservoir incorporates an RLS system,
designed to isolate a leak in either system circuit. When reservoir fluid level drops to approximately
50%, RLS shuts off circuit A (HYD 1A or HYD 2A caution). If fluid level continues to deplete to
approximately 30%, RLS restores circuit A and shuts off circuit B (HYD 1B or HYD 2B caution). If
alternate circuit shutdown fails to isolate the leak, RLS restores circuit B (no cautions) at approximately
15%, providing hydraulic pressure to both systems until fluid depletion (both cautions).
2.6.1.3 Switching Valves. Hydraulic switching valves are utilized to provide backup hydraulic power
to actuators that are not powered simultaneously by both systems. Two hydraulic circuits, a primary
and a backup, provide power to each switching valve.
A1-F18EA-NFM-000
I-2-39 ORIGINAL
Figure 2-15. Hydraulic Flow
A1-F18EA-NFM-000
I-2-40 ORIGINAL
2.6.1.3.1 Switching Valve Operation. Following a drop in primary circuit pressure (less than 900
(±100 psi)), the switching valve automatically shuts off the primary circuit and tests downstream
pressure to make sure its actuator(s) was not the leakage source which caused the primary circuit loss.
Concurrently, FCC monitoring detects the pressure loss and inhibits FCC actuator failure detection
logic for 10 seconds to allow the switching valve time to function.
If the actuator(s) passes this leak detection test, the switching valve allows the backup circuit to
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本文链接地址：
NATOPS Flight Manual 飞行手册 1(48)
