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See the Hydraulic Subsystem Malfunction Guide.
1. Execute the FCS procedures for an Aileron Actuator
Failure.
HYD 1A
HYD 2A
· HYD circuits 1A and 2A pressure low (<1,400
psi). May be caused by battle damage or a dual
circuit HYD leak (e.g., in the right aileron actuator).
Right aileron lost (faired and damped).
See the Hydraulic Subsystem Malfunction Guide.
1. Execute the FCS procedures for an Aileron Actuator
Failure.
2. Execute the HYD 2A For Landing Procedures.
HYD 1B
HYD 2A
· HYD circuits 1B and 2A pressure low (<1,400
psi).
May be caused by battle damage or a dual circuit
HYD leak (e.g., in a LEF, left stabilator, or left
rudder actuator).
Both LEFs lost (frozen).
Left stabilator lost (locked 2° TEU).
Left rudder lost (faired and damped).
See the Hydraulic Subsystem Malfunction Guide.
1. Execute the FCS procedures for a Stabilator
Actuator Failure.
2. Also see remarks for FLAPS OFF caution and
FCS Rudder Actuator Failure.
3. Execute the HYD 2A For Landing Procedures.
A1-F18EA-NFM-000
Figure 12-1. Warning/Caution/Advisory Displays (Sheet 45 of 55)
V-12-47 ORIGINAL
HYD CAUTIONS
INDICATOR · CAUSE / REMARKS CORRECTIVE ACTION
HYD 1A
HYD 2B
· HYD circuits 1A and 2B pressure low (<1,400
psi).
May be caused by battle damage or a dual circuit
HYD leak (e.g., in a TEF, right stabilator, or
right rudder actuator).
Both TEFs lost (locked 5° TED).
Right stabilator lost (locked 2° TEU).
Right rudder lost (faired and damped).
See the Hydraulic Subsystem Malfunction Guide.
CV landings not recommended since approach
speed may be in excess of 200 KCAS.
1. Execute the FLAPS OFF caution procedures
(TEF Failure).
2. Comply with steps 7, 8, and 14 of the FCS Stabilator
Actuator Failure procedure.
3. Also see remarks for FCS Stabilator and Rudder
Actuator Failures.
HYD 1A
HYD 1B
HYD 2A
· Triple HYD circuit failure (e.g., battle damage).
Both LEFs lost (frozen).
Right aileron lost (faired and damped).
Left stabilator lost (locked 2° TEU).
Left rudder lost (faired and damped).
UA flying qualities acceptable. Enough lateral
trim authority is available to balance the failure
induced rolloff up to 0.85 Mach. Jettison all stores
prior to mode transition, since the transition with
stores results in an uncontrollable nose-up tendency.
Mode transition in a clean configuration can
be accomplished (expect a LWD roll near on-speed
AOA). Carrier approach is possible but exhibits
sloppy directional/centerline control.
See the Hydraulic Subsystem Malfunction Guide.
Marginally controllable in PA if stores not jettisoned.
1. Execute the FCS procedures for a Stabilator
Actuator Failure.
2. EMERG JETT button - PUSH (prior to mode
transition)
3. Also see remarks for FLAPS OFF caution and
FCS Aileron and Rudder Actuator Failures.
HYD 1A
HYD 2A
HYD 2B
· Triple HYD circuit failure (e.g., battle damage).
Both TEFs lost (locked 5° TED).
Right aileron lost (faired and damped).
Right stabilator lost (locked 2° TEU).
Right rudder lost (faired and damped).
In UA, full LWD lateral trim and half lateral
stick are required to keep wings level at 0.7 Mach
and 20,000 feet, while full lateral trim is required at
0.6 Mach and 20,000 feet. Lateral authority is lost
around 14° AOA. Mode transition to PA may be
safely accomplished with or without stores. Consider
SEL JETT of right wing stores to balanced
failure induced roll.
See the Hydraulic Subsystem Malfunction Guide.
CV landings not recommended since approach
speed may be in excess of 200 KCAS.
1. Execute the FLAPS OFF caution procedures
(TEF Failure).
2. Comply with steps 7, 8, and 14 of the FCS Stabilator
Actuator Failure procedure.
3. Consider SEL JETT of right wing stores.
4. Also see remarks for FCS Stabilator and Rudder
Actuator Failures.
HYD 1B
HYD 2A
HYD 2B
· Triple HYD circuit failure (e.g., battle damage).
Both LEFs lost (frozen).
Left aileron lost (faired and damped).
Left stabilator lost (locked 2° TEU).
Left rudder lost (faired and damped).
In UA, flying qualities are acceptable with
smooth lateral stick inputs. Wings level can be
maintained up to 0.85 Mach. Mode transition to PA
in any configuration results in an uncontrollable
nose-up tendency.
See the Hydraulic Subsystem Malfunction Guide.
Mode transition to PA uncontrollable: landing not
　
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本文鏈接地址：NATOPS Flight Manual 飛行手冊 2(41)