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If decision to stop is made -
*1. Throttles - IDLE
If NWS failure is suspected -
*2. Paddle switch - PRESS
A1-F18EA-NFM-000
V-18-2 ORIGINAL
If directional control problem remains -
*3. NWS - ENGAGE (with rudder pedals centered)
*4. EMERG BRK handle - PULL TO DETENT (with brakes released)
*5. Use judicious braking on appropriate side.
*6. HOOK handle - DOWN (if required)
18.10 EMERGENCY CATAPULT FLYAWAY
If flyaway airspeed available -
*1. Throttles - MAX
*2. Rudder pedal - FULL AGAINST YAW/ROLL
*3. EMERG JETT button - PUSH
*4. Maintain 10 to 12° pitch attitude with waterline symbol. Do not exceed 14° AOA (AOA tone). Do
not exceed ½ lateral stick.
If uncontrollable or settle not stopped -
*5. EJECT
If controllable and settle stopped -
*6. Accelerate to on-speed (8.1°) AOA for climb.
18.11 FCS CAUTION or FCES CAUTION LIGHT
*1. Cease maneuvering.
18.12 L or R FUEL INLT CAUTION
*1. Throttle affected engine - OFF
*2. FIRE light affected engine - PUSH
18.13 HYD 1 (2) HOT CAUTION
*1. Throttle affected engine - OFF
18.14 L or R STALL CAUTION
*1. Throttle affected engine - IDLE
If the stall does not clear -
*2. Throttle affected engine - OFF
*3. FIRE light affected engine ± PUSH
A1-F18EA-NFM-000
V-18-3 CHANGE 1
18.15 DUAL L BLEED and R BLEED Warning Lights (which do not go out)
*1. BLEED AIR knob - OFF (DO NOT CYCLE)
*2. Emergency oxygen green ring - PULL
If light(s) still on -
*3. Throttles - Minimum practical for flight
18.16 SINGLE L BLEED or R BLEED Warning Light (which does not go out)
*1. BLEED AIR knob affected engine - OFF (DO NOT CYCLE)
If light still on, do the following in order until the light goes out -
*2. Throttle affected engine - IDLE
*3. Throttle affected engine - OFF
*4. BLEED AIR knob - OFF (DO NOT CYCLE)
If both bleeds secured -
*5. Emergency oxygen green ring - PULL
18.17 FUSELAGE FUEL LEAK
*1. Afterburners - DESELECT
*2. Possible Indications -
· Visual confirmation of fuel leakage
· L or R BOOST LO caution
· FUEL LO caution
· FEED tank fuel quantities
· Engine instruments
*3. Throttle (suspect engine) - OFF
*4. FIRE light (suspect engine) - PUSH
18.18 COCKPIT SMOKE, FUMES, OR FIRE
*1. CABIN PRESS switch - RAM/DUMP
Descend below 25,000 ft (if practical)
18.19 OCF RECOVERY PROCEDURES
*1. Controls - RELEASE, FEET OFF RUDDERS, SPEEDBRAKE IN
If still out of control -
*2. Throttles - IDLE
*3. Altitude, AOA, airspeed, and yaw rate - CHECK
A1-F18EA-NFM-000
V-18-4 CHANGE 1
If command arrow present -
*4. Lateral stick - FULL WITH ARROW
When command arrow removed -
*5. Lateral stick - SMOOTHLY NEUTRAL
When recovery indicated by YAW rate tone removed, side forces subsided, and airspeed
accelerating above 180 KCAS -
*6. Recover
Passing 6,000 ft AGL, dive recovery not initiated -
*7. Eject
18.20 ARS Refueling Hose Jetison.
18.20.1 Hydraulic Pressure Light. If the HYD PRESS light illuminates when the hose is retracted,
reel response may be lost or a hydraulic failure may be imminent.
*1. Receiver aircraft - Disengage
18.21 Deleted
18.22 SINGLE ENGINE FAILURE in LANDING CONFIGURATION
*1. Throttles - MIL (MAX if required)
*2. Maintain on-speed AOA and balance flight.
*3. FLAP switch - HALF
A1-F18EA-NFM-000
V-18-5 (Reverse Blank) CHANGE 1

PART VI
ALL WEATHER PROCEDURES
Chapter 19 - Instrument Flight
Chapter 20 - Extreme Weather Procedures
Chapter 21 - Hot Weather Procedures
Chapter 22 - Cold Weather Procedures
A1-F18EA-NFM-000
63 (Reverse Blank) ORIGINAL

CHAPTER 19
Instrument Flight
19.1 INSTRUMENT FLIGHT
19.1.1 Before Takeoff. If instrument flight is expected immediately following takeoff, thoroughly
check navigation equipment and crosscheck the HUD and standby flight instruments. If flight in icing
conditions is anticipated, perform an engine anti-ice detector test (ENG ANTI ICE switch to TEST).
If icing conditions are anticipated, immediately after takeoff, place the ENG and PITOT ANTI ICE
switches to ON just prior to takeoff roll.
19.1.2 Inflight. During instrument flight, particularly in icing conditions, frequently crosscheck
standby flight instruments to verify that the primary systems are functioning normally. A slowly
flashing velocity vector indicates that the INS is providing valid attitude information but the FCC air
data functions are the source for the velocity vector.
19.1.3 Approaches.
19.1.3.1 Descent. If fuel conservation is of concern, an enroute descent should be flown at 250 KCAS
　
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