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generated by single stabilator movement. In PA, this interconnect is stabilator to aileron. In UA, it is
stabilator to aileron and differential TEF. At high airspeed in UA, differential LEFs are also used. In
the yaw axis, the baseline differential stabilator portion of the RSRI continues to be used to counter
the yaw generated by single stabilator movement.
2.9.14 GAIN ORIDE. GAIN ORIDE allows the pilot to select a set of fixed CAS gains when an FCS
malfunction prevents normal CAS gain scheduling (e.g., loss of AOA or pitot-static data). With the
GAIN switch in ORIDE, the FCCs use fixed values for speed, altitude, and AOA depending on the
position of the FLAP switch. These fixed gains cause the LEFs, TEFs, and aileron droop to be driven
to the fixed positions shown in figure 2-24. GAIN ORIDE should generally provide acceptable handling
qualities at flight conditions which approximate the fixed gains. At flight conditions that deviate from
the fixed gains, a slight degradation in handling qualities should be expected. Transition to or from the
landing configuration should be performed at 180 KCAS. In PA, expect aircraft response to be slightly
sluggish, taking longer to stabilize. The aircraft stalls at a lower than nominal AOA since the LEFs are
fixed. For best results, maintain on-speed AOA during the approach and landing.
Flight with GAIN ORIDE selected is prohibited above 10° AOA or above 350 KCAS (flaps AUTO),
200 KCAS (flaps HALF), or 190 KCAS (flaps FULL) to ensure control system stability and to reduce
the potential for departure. When GAIN ORIDE is selected, the amber FLAPS light comes on along
with either the CRUIS advisory (flaps AUTO) or the LAND advisory (flaps HALF or FULL).
A1-F18EA-NFM-000
I-2-74 ORIGINAL
FLAP Switch
LEF
(¡LED)
TEF
(¡TED)
AIL Droop
(¡TED)
Fixed Gains
Mach KTAS Feet ¡AOA
AUTO 5 4 2 0.80 459 39,000 3.5
HALF 21 30 30 0.23 151 500 8.1
FULL 21 40 40 0.21 139 500
8.1
Figure 2-24. GAIN ORIDE Flap Positions and Gain Schedules
2.9.14.1 GAIN Switch. The GAIN switch, located on the FCS panel on the left console, is used to
select GAIN ORIDE. The switch is guarded in the NORM position to prevent inadvertent actuation.
ORIDE Selects fixed CAS gains according to FLAP switch position.
NORM Selects normal CAS gain scheduling.
2.9.15 FCS Failures. The FCS detects failures through three types of BIT: initiated (IBIT), periodic
(PBIT), and maintenance (MBIT). FCS IBIT is performed during Before Taxi Checks to run a
thorough test of the system prior to flight. PBIT is a less thorough test of the FCS and runs
continuously when other BITs are not running. MBIT is typically run by maintenance personnel and
is the most comprehensive test of the FCS.
FCS failures are annunciated by any or all of the following indications: the FCS caution, the FCES
caution light, the ²Flight controls, Flight controls² voice alert, FCS format Xs, and/or BIT Logic
Inspection (BLIN) codes. FCS format Xs and BLIN codes identify the location and type of failure.
However, not all FCS related components/functions are covered by Xs on the FCS format matrix. For
such components/functions, valid BLIN codes may be the only indication of the location of the failure.
Therefore, until the nature of the failure is determined, BLIN codes that appear without Xs should be
treated with the same level of concern as those that do.
Typically, BLIN codes that have three digits or less are generated by PBIT, e.g., 341. 4000-series
BLIN codes are generated by FCS IBIT and use the same last three digits as PBIT, e.g. 4341.
2.9.15.1 FCES Caution Light. The Flight Control Electronic Set (FCES) caution light is located on
the lower right caution lights panel. The primary purpose of the FCES caution light is to alert aircrew
of critical FCS related failures when MC1 is failed. When MC1 is failed, the normal DDI FCS related
cautions are not generated and the FCS format is not available for troubleshooting. When MC1 is
operative, the FCES caution light is merely a secondary indication of an FCS related failure. The
specific FCS cautions which also trigger the FCES caution light are listed in figure 2-25.
2.9.15.2 FCS RESET Button. The FCS RESET button is located on the FCS panel on the left
console. This button is used to perform several FCS related functions. Following detection of FCS
related hardware and/or software failures (e.g., FCS Xs and/or BLIN codes), pressing the FCS RESET
button commands a reset of FCC failure detection circuitry. If the FCS related failure was momentary
and no longer exists, an FCS RESET (a) restores the failed actuator/component, (b) removes all FCS
failure indications (FCS caution, FCES caution light, and Xs; preflight BLIN codes only), and (c)
　
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