Hh-65C Uscg Boldface Eps

Front 1

MAJOR FADEC/GOVERNOR FAILURE

Back 1

1. COMPLETE THE “BIG 4.”
2. TRNG SWITCH − FLT.
*** 3. FADEC BACK−UP SWITCH (affected engine) − BACK−UP.

Hint 1

1. FADEC # FAIL caution light illuminated.
2. Red ENGINE STATUS light on the overhead quadrant illuminated.
3. DUAL ENGINE FLI DISPLAY with OEI.
4. Affected engine will not respond to collective movement due to Fuel Flow metering being frozen at the rate present when the FADEC failed.

Front 2

ENGINE EMERGENCIES IN−FLIGHT − GENERAL
(BIG "4")

Back 2

1. Nr − MAINTAIN.
2. AIRSPEED/ALTITUDE − CONTROL AND SET LIMITS.
3. WHEELS/FLOATS − AS REQUIRED.
4. ANALYZE.

Front 3

MAIN GEARBOX FAILURE IMMINENT

Back 3

1. LANDING/HOVER CHECKLIST − COMPLETE (200 foot checks at a minimum based on urgency).
2. LAND/DITCH IMMEDIATELY (POWER ON).

Hint 3

1. Loss of XMSN lubrication OR illumination of a GB CHIP warning light with an MGB CHIP annunciation on the VEMD CAUTION/FUEL page in conjunction with any one of the following:
- Yaw kicks
- Abnormal transmission noises
- Unusually high power requirements
2. LOSS of XMSN lubrication AND illumination of a GB CHIP warning light with an MGB CHIP annunciation on the VEMD CAUTION/FUEL page.

Front 4

MGB OVERTORQUE
(0-75 KIAS)

Back 4

>10.0 but < 10.3
1. REDUCE TORQUE TO WITHIN LIMITS, WHEN ABLE.

Front 5

MGB OVERTORQUE
>75 KIAS)

Back 5

>8.8 but < 9.4
1. REDUCE TORQUE TO WITHIN LIMITS, WHEN ABLE.

Front 6

MAIN GEARBOX FIRE

Back 6

1. ATTEMPT TO CONFIRM PRESENCE OF FIRE (alert crew).
2. LANDING/HOVER CHECKLIST − COMPLETE (200 foot checks at a minimum
based on urgency).
If fire confirmed:
3. LAND/DITCH IMMEDIATELY.
If fire NOT confirmed:
3. LAND AS SOON AS POSSIBLE.

Hint 6

1. MGB fire warning light illuminated.

Front 7

ENGINE COMPARTMENT FIRE IN−FLIGHT

Back 7

1. ATTEMPT TO CONFIRM PRESENCE OF FIRE (alert crew).
2. SINGLE ENGINE FLIGHT PROFILE − ESTABLISH.
If fire NOT confirmed:
3. LAND AS SOON AS PRACTICABLE.
If fire confirmed:
3. FADEC CONTROL SWITCH (affected engine) − CONFIRM; IDLE; CONFIRM; OFF.
4. EMERGENCY FUEL SHUTOFF LEVER − CONFIRM; OFF.
5. BOOST PUMPS − (affected engine) − OFF.
6. PRI FIRE EXTINGUISHER BUTTON (affected engine) − CONFIRM; PUSH.
7. SEC FIRE EXTINGUISHER BUTTON (affected engine) − PUSH.
8. LANDING/HOVER CHECKLIST − COMPLETE (200 foot checks at a minimum based on urgency).
If fire no longer evident:
9. ENGINE SHUTDOWN PROCEDURE − COMPLETE.
If fire still persists:
9. LAND/DITCH IMMEDIATELY.

Hint 7

1. FIRE warning light illuminated on the instrument panel.
2. Red warning light illuminated on the corresponding Emergency Fuel Shutoff Lever (EFSL).
3. Flames and/or smoke coming from engine compartment.

Front 8

ENGINE COMPARTMENT FIRE ON DECK

Back 8

1. ATTEMPT TO CONFIRM PRESENCE OF FIRE (alert crew).
2. FADEC CONTROL SWITCHES − BOTH OFF.
3. EMERGENCY FUEL SHUTOFF LEVERS − BOTH OFF.
4. BOOST PUMPS − ALL OFF.
If fire confirmed:
5. PRI FIRE EXTINGUISHER BUTTON (affected engine) − CONFIRM; PUSH.
6. SEC FIRE EXTINGUISHER BUTTON (affected engine) − PUSH.
7. EMERGENCY ELECTRICAL CUTOFF − OFF.
8. ROTOR BRAKE − ON.
9. EVACUATE AIRCRAFT.

Hint 8

1. FIRE warning light illuminated.
2. Possible hand or voice signals from ground crew.
3. Red warning light illuminated on the corresponding Emergency Fuel Shutoff Lever (EFSL).

Front 9

INTERNAL FIRE (CABIN, ELECTRICAL, AND/OR AVIONICS)

Back 9

1. DESIGNATE CREWMAN TO FIGHT FIRE.
2. AFFECTED EQUIPMENT − OFF.
3. HEAT/COOL SWITCHES − OFF.
4. RAM AIR − CLOSED.
5. CABIN SLIDING DOOR − CLOSED.
6. PILOT’S WINDOWS − CLOSED.
7. RACK BLOWER CIRCUIT BREAKER − PULL (for avionics rack fire only − avionics rack panel R4 #4).
8. CIRCUIT BREAKERS − PULL (for affected circuits).
9. LANDING/HOVER CHECKLIST − COMPLETE (200 foot checks at a minimum
based on urgency).
10. EMERGENCY ELECTRICAL CUTOFF − OFF.
If electrical or avionics fire persists:
11. LAND/DITCH IMMEDIATELY.
If fire goes out:
11. LAND AS SOON AS POSSIBLE.

Front 10

SMOKE AND FUME ELIMINATION

Back 10

1. HEAT/COOL SWITCHES − OFF.
2. RAM AIR − OPEN.
3. CABIN SLIDING DOOR − OPEN.
4. PILOTS’ WINDOWS − OPEN.
5. LAND AS SOON AS PRACTICABLE.

Front 11

ENGINE POST−SHUTDOWN FIRE

Back 11

1. FADEC CONTROL SWITCHES − CHECK OFF.
2. BOOST PUMPS − CHECK OFF.
3. EMERGENCY FUEL SHUTOFF LEVER − SHUT OFF (ENSURE 10 SECONDS HAVE ELAPSED PRIOR TO SHUTOFF).
4. CRANK BUTTON − DEPRESS UNTIL TOT DECREASES.
If TOT continues to rise:
5. EMERGENCY ELECTRICAL CUTOFF − OFF.
6. ROTOR BRAKE − ON.
7. EVACUATE AIRCRAFT.

Hint 11

1. TOT rises or does not decrease within 10 seconds after the FADEC control switch has been placed in the OFF position.

Front 12

ROTOR BLADE DAMAGE - up to mild

Back 12

1. LAND AS SOON AS POSSIBLE.

Hint 12

Symptom:
1. Rotor blade damage is known or suspected, with or without secondary indications of up to mild.

Front 13

ROTOR BLADE DAMAGE - more than mild

Back 13

1. LANDING/HOVER CHECKLIST − COMPLETE (200 foot checks at a minimum based on urgency).
2. LAND/DITCH IMMEDIATELY.

Hint 13

Symptoms:
1. Rotor blade damage is known or suspected.
AND
2. Secondary indications (such as vibrations) are more than mild, flight characteristics are drastically altered.

Front 14

NR INDICATING SYSTEM FAILURE

Back 14

1. COMPLETE THE “BIG 4.”

Hint 14

1. One or both Nr gauges fluctuates abnormally or indicates zero.

Front 15

UNCOMMANDED LEFT YAW (ULY)

Back 15

1. IMMEDIATE FULL RIGHT PEDAL, MAXIMUM DEFLECTION.
2. ALTITUDE/OBSTACLES PERMITTING, SMOOTHLY APPLY FORWARD CYCLIC TO INCREASE FORWARD AIRSPEED.
3. ALTITUDE PERMITTING, REDUCE COLLECTIVE.
4. NR SWITCH − HI.

Hint 15

Any uncommanded left yaw not attributable to mechanical failure of the tail rotor drive system.

Front 16

TGB CHIP DETECTED

Back 16

1. ESTABLISH SAFE ALTITUDE AND AIRSPEED FOR POSSIBLE LOSS OF TAIL ROTOR THRUST.
2. LAND AS SOON AS POSSIBLE.

Hint 16

1. Illumination of the GB CHIP warning light and a TGB CHIP annunciation on the VEMD CAUTION/FUEL page.

Front 17

LOSS OF TAIL ROTOR THRUST WHILE HOVERING

Back 17

1. EMERGENCY FUEL SHUTOFF LEVERS − BOTH OFF.
2. MAINTAIN LANDING ATTITUDE.
3. CUSHION LANDING WITH COLLECTIVE.

Hint 17

1. A loss of tail rotor thrust will result in an IMMEDIATE, rapid left yaw acceleration.
2. Tail rotor pedals movable but with no apparent effect.
3. Abnormal vibration or noise from the tail section.
4. Illumination of the GB CHIP warning light and a TGB CHIP annunciation on the VEMD CAUTION/FUEL page.

Front 18

LOSS OF TAIL ROTOR THRUST IN FORWARD FLIGHT OR FIXED TAIL ROTOR PITCH

Back 18

1. DIRECTIONAL CONTROL − MAINTAIN USING CYCLIC AND COLLECTIVE.

Hint 18

1. Uncommanded yaw to the left or right (loss of thrust).
2. Tail rotor pedals movable without effect (loss of thrust).
3. Abnormal vibration or noise from the tail section (loss of thrust or fixed pitch).
4. Possible illumination of the GB CHIP warning light (loss of thrust) with a TGB CHIP annunciation on the VEMD CAUTION/FUEL page. 5. Cannot move pedals either left or right (fixed pitch).

Front 19

DUAL ENGINE FAILURE IN−FLIGHT − GENERAL

Back 19

1. Nr − MAINTAIN.
2. PERFORM AUTOROTATION PROCEDURE.

Hint 19

1. Low Nr horn − ON.
2. Nr − DECAYING.
3. Engine parameters − BOTH ENGINES DECREASING.
4. Possible right yaw.

Front 20

VISUAL AUTOROTATION PROCEDURES

Back 20

1. COMPLETE THE “BIG 4” (airspeed 75−105 KIAS).
2. TURN TOWARD DESIRED LANDING AREA AND/OR INTO THE WIND.
3. AT 200 FT RADALT − WHEELS RECHECK.
4. AT 125 FT RADALT − INITIATE FLARE; INFLATE FLOATS AS REQUIRED.
5. ASSUME LANDING ATTITUDE, ELIMINATING YAW AND DRIFT PRIOR TO
TOUCHDOWN.
6. COLLECTIVE − CUSHION THE LANDING.

Front 21

INSTRUMENT AUTOROTATION PROCEDURES

Back 21

1. COMPLETE THE “BIG 4” (airspeed 75 KIAS).
2. TURN TOWARD DESIRED LANDING AREA AND/OR INTO THE WIND.
3. AT 200 FT RADALT − WHEELS RECHECK.
4. AT 125 FT RADALT − INITIATE FLARE. CONTROL THE RATE TO ARRIVE AT 20
DEGREES NOSE − UP AT 75 FT RADALT; INFLATE FLOATS AS REQUIRED.
5. MAINTAIN FLARE UNTIL DESIRED AIRSPEED IS REACHED − 30 KTS PLUS HALF THE WIND SPEED.
6. ASSUME 5deg NOSE UP, WINGS−LEVEL LANDING ATTITUDE.
7. AT 25 FT RADALT − COLLECTIVE − CUSHION THE LANDING.

Front 22

SINGLE ENGINE FAILURES IN FLIGHT TO INCLUDE: LOW HOVER, HIGH HOVER, AND TAKEOFF/LANDING TRANSITION

Back 22

1. Nr − MAINTAIN.
2. AIRSPEED/ALTITUDE − CONTROL
3. WHEELS/FLOATS − AS REQUIRED.
4. LAND BACK OR CONTINUE FLIGHT.
LANDBACK PROCEDURE:
5. ASSUME LANDING ATTITUDE, ELIMINATE YAW AND DRIFT PRIOR TO TOUCHDOWN.
CONTINUED FLIGHT PROCEDURE:
6. COLLECTIVE − ADJUST TO MAXIMUM POWER, MAINTAINING MINIMUM Nr (at or above 345 RPM).
7. AIRSPEED − CLIMB AT 70−75 KIAS.
8. Nr/OEI − SET AS NECESSARY.
9. ANALYZE

Hint 22

1. Possible Nr droop.
2. Abnormal engine parameters.
3. DIF N1 warning light illuminated.
4. Low Nr horn.
5. Torque, TOT, N1, N2, fuel
pressure decreasing.
6. As engine spools down, additional symptoms will become evident such as Generator Failure, Eng Oil P light.

Front 23

FLAMEOUT

Back 23

1. COMPLETE THE “BIG 4.”
2. ENGINE SHUTDOWN PROCEDURE − COMPLETE.

Hint 23

1. Possible Nr droop.
2. Abnormal engine parameters.
3. DIF N1 warning light illuminated.
4. Low Nr horn.
5. Torque, TOT, N1, N2, fuel pressure decreasing.
6. As engine spools down, additional symptoms will become evident such as Generator Failure, Eng Oil P light.
7. FLI switches to single engine display.
8. ECS disengages.
9. Bleed air shuts off.

Front 24

ENGINE CHIP DETECTED

Back 24

1. COMPLETE THE “BIG 4.”
2. FADEC CONTROL SWITCH (AFFECTED ENGINE) − CONFIRM; IDLE.
3. ENGINE − MONITOR.
If ABNORMAL indications:
4. ENGINE SHUTDOWN PROCEDURE − COMPLETE.
If NORMAL indications:
4. LAND AS SOON AS PRACTICABLE.

Hint 24

1. ENG # CHIP warning light illuminated.
2. Corresponding ENGINE CHIP annunciation on the VEMD CAUTION/ FUEL page.

Front 25

ENGINE GEARBOX/OUTPUT SHAFT FAILURE

Back 25

1. COMPLETE THE “BIG 4.”
2. ENGINE SHUTDOWN PROCEDURE − COMPLETE.

Hint 25

1. N2 significantly above Nr.
2. Zero torque on malfunctioning engine.
3. Possible loud noises from the engine area.

Front 26

N1 DIVERGENCE/PARTIAL POWER LOSS

Back 26

1. COMPLETE THE “BIG 4.”

Hint 26

1. DIF N1 Warning Light illuminated.
2. Single engine FLI display.
3. N1 difference between both engines is greater than 6%.

Front 27

LUBRICATION SYSTEM FAILURE

Back 27

1. COMPLETE THE “BIG 4.”
2. ENGINE SHUTDOWN PROCEDURE − COMPLETE.

Hint 27

1. ENG # OIL P warning light illuminated.
2. Engine oil pressure fluctuates, increases or decreases abnormally.
3. Engine warning light illuminated on the overhead control quadrant.
4. Engine oil pressure less than 25 psi.

Front 28

ENGINE SURGE OR COMPRESSOR STALL IN FLIGHT

Back 28

1. COMPLETE THE “BIG 4.”
[If NORMAL engine parameters or affected engine cannot be identified:]
[2. LAND AS SOON AS PRACTICABLE.]
If ABNORMAL engine parameters and affected engine can be identified:
2. FADEC CONTROL SWITCH (affected engine) − CONFIRM; IDLE.
[3. ENGINE − MONITOR.]
[If NORMAL IDLE parameters:
4. LAND AS SOON AS PRACTICABLE.]
If ABNORMAL IDLE parameters:
4. ENGINE SHUTDOWN PROCEDURE − COMPLETE.

Hint 28

1. Popping or rumbling noises.
2. TOT increases.
3. Torque and N1 decreases.
4. Airframe vibration.

Front 29

ENGINE SURGE OR COMPRESSOR STALL ON DECK

Back 29

1. FADEC CONTROL SWITCH (affected engine) −
OFF.
2. FUEL BOOST PUMPS (affected engine) − OFF.
3. TOT − MONITOR FOR POST SHUTDOWN FIRE.

Hint 29

1. Popping or rumbling noises.
2. TOT increases.
3. Torque and N1 decreasing.
4. Airframe vibration/shuddering.

Front 30

ENGINE OIL COOLER FAN FAILURE
Both engines overheated

Back 30

1. CRUISE AIRSPEED − 120 KIAS MIN.
2. LAND AS SOON AS POSSIBLE.
3. SHUT DOWN ENGINES AS SOON AS POSSIBLE.

Hint 30

1. OIL TEMP warning light illuminated.

Front 31

ENGINE SHUTDOWN PROCEDURE IN−FLIGHT

Back 31

1. SINGLE ENGINE FLIGHT PROFILE − ESTABLISH.
2. FADEC CONTROL SWITCH (affected engine) − CONFIRM; IDLE; CONFIRM; OFF.
3. BOOST PUMPS (affected engine) − OFF.
4. TOT − MONITOR FOR POST SHUTDOWN FIRE.
5. OEI − SET AS REQUIRED.
6. FUEL − TRANSFER/JETTISON AS REQUIRED. (To transfer all useable fuel, the boost pumps on the failed engine side must be ON to drive the transfer injectors.)
7. LAND AS SOON AS PRACTICABLE (Single engine landing procedure).

Front 32

RESTARTING ENGINE IN−FLIGHT

Back 32

1. HEAT − OFF.
2. BOOST PUMPS − ON.
3. EMERGENCY FUEL SHUTOFF LEVER − ENSURE FORWARD.
4. CHECK N1 LESS THAN 17%.
5. PERFORM NORMAL START PROCEDURE.
If engine start successful:
6. LAND AS SOON AS PRACTICABLE.
If engine fails to light off:
6. ENGINE SHUTDOWN PROCEDURE − COMPLETE.

Front 33

ENGINE START EMERGENCIES

Back 33

1. FADEC CONTROL SWITCH − OFF.
2. TOT − MONITOR FOR POST SHUTDOWN FIRE.

Hint 33

1. Insufficient voltage to start.
2. Voltage drops below 17 VDC.
3. TOT rises rapidly and/or appears that it will exceed 750 C (Hot start).
4. The rotor system does not turn by 25% N1.
5. No rise in TOT or N1 within 10 seconds after FADEC CONTROL SWITCH is moved.
6. Engine does not reach 45% N1 by 30 seconds and is no longer accelerating.

Front 34

TORQUE, TOT or N1 INDICATING SYSTEM FAILURE

Back 34

1. COMPLETE THE “BIG 4.”

Hint 34

1. FLI DEGR annunciation on the VEMD.
2. TRQ, TOT or N1 value missing with TRQ, TOT, or N1 label in boldface yellow type.
3. GOV caution light (TOT failure).
4. All other engine parameters normal.

Front 35

PRIMARY HYDRAULIC SYSTEM FAILURE

Back 35

1. CRUISE AIRSPEED − 75 TO 100 KIAS.
2. AVOID ABRUPT MANEUVERS.

Hint 35

1. PRI SERVO P warning light illuminated.
2. SERVO JAM warning light illuminated.
3. LIMIT lights illuminated.
4. HYD2 PRESS < 720 psi.
5. SERVO LIMIT annunciation on the VEMD CAUTION/FUEL page.
6. High−pitched noise from transmission area.
7. Stiffness in flight controls.

Front 36

SECONDARY HYDRAULIC SYSTEM FAILURE

Back 36

1. CRUISE AIRSPEED − 75 TO 100 KIAS.
2. AVOID ABRUPT MANEUVERS.

Hint 36

Symptoms:
1. SEC SERVO P warning light illuminated.
2. SEC HYD LO PRESS warning light illuminated.
3. SERVO JAM warning light illuminated.
4. HYD1 PRESS < 720 psi.
5. SEC HYD ISOLATE warning light illuminated.
(Only if failure is due to a loss of hydraulic fluid.) Possible symptoms:
6. High−pitched noise from transmission area.
7. Stiffness in flight controls.

Front 37

SECONDARY HYDRAULIC SYSTEM LOW FLUID LEVEL

Back 37

1. TAIL HYD ISOLATE SWITCH − NORM.

Hint 37

Symptoms:
1. SEC HYD ISOLATE warning light illuminated.
2. SERVO JAM warning light illuminated.
Possible symptoms:
3. High−pitched noise from transmission area.
4. Stiffness in flight controls.

Front 38

SECONDARY HYDRAULIC PRESSURE HIGH/LOW

Back 38

1. LANDING GEAR HANDLE − DOWN (check wheels down).

Hint 38

Symptoms:
1. SEC SERVO P warning light illuminated.
2. SEC HYD LO PRESS warning light illuminated.
3. SERVO JAM warning light illuminated.
4. HYD1 PRESS < 720 psi.
5. SEC HYD ISOLATE warning light illuminated. (Only if failure is due to a loss of hydraulic fluid.)
Possible symptoms:
6. High−pitched noise from transmission area.
7. Stiffness in flight controls.

Front 39

DUAL AC BUS FAILURE

Back 39

1. FLIGHT CONTROLS − STABILIZE AIRCRAFT.

Hint 39

1. AFCS pitch and roll channels disengaged.
2. Pilot’s and copilot’s ADI, attitude, and heading gyros failed.
3. Loss of cockpit instrument lighting.
4. Loss of all AC powered equipment.

Front 40

AC SYSTEM FAILURE (MAIN AC BUS SHORT, ALTERNATOR, ALTERNATOR CONTROL UNIT OR 115/26 VOLT AC SYSTEM FAILURE)

Back 40

1. FLIGHT CONTROLS − STABILIZE AIRCRAFT.
2. AC 26V XFER SWITCH − PUSH IN THE DIRECTION OF THE ILLUMINATED FAIL LIGHT.
3. AFCS − REENGAGE.

Hint 40

1. One 26 VAC FAIL light illuminated.
2. AFCS pitch and roll channels disengaged.
3. ADI, attitude gyro, and heading gyro failed on one side of the instrument panel.
4. All equipment on one main AC bus inoperative and/or loss of components powered by single phase
115 VAC and 26 VAC from the respective transformer.
5. Alternator FAIL light illuminated (in some cases).
6. BTC CLOSED light illuminated (in some cases).

Front 41

MAIN DC BUS SHORT

Back 41

1. FLIGHT CONTROLS − STABILIZE AIRCRAFT.
2. AFFECTED AUDIO CONTROL PANEL(S) −
ALTN. (Flight Mech audio control panel to ALTN for a #1 DC bus short.)

Hint 41

Possible Symptoms:
1. Loss of all equipment on one main DC bus, to
include, but not limited to:
#1 Copilot
AFCS Yaw
FDS
SCC #2
ICS (CP and FM)
Comm 2
MFD2 (EHSI)
CDU2 & GPS2
VSI−TCAS
Feel Trim
MDL
Starter Eng 1
Fuel Pumps 2 and 3
Eng 1 Overspeed
Radar
#2 Pilot
AFCS Yaw
AFCS Collective
SCC #1
ICS (Pilot)
Comm 1
MFD1 (EHSI)
CDU1 & GPS1
VSI−TCAS
ECS Fan
Rad Alt
Starter Eng 2
Eng 2 Overspeed
Heater O/Heat Light
T/R Hyd Isolate
2. SERVO JAM, SECONDARY HYDRAULIC ISOLATE, and HEATER O/HEAT warning lights (#2, right, main bus only). Landing gear system will have hydraulic power and will extend normally with landing gear handle actuation.)
3. Loss of radar display on MFD2. (#2 right main bus only)
4. Associated generator FAIL light illuminated.
5. Associated battery relay OPEN light illuminated.

Front 42

BATTERY OVER TEMPERATURE/ THERMAL RUNAWAY

Back 42

1. BATT RELAY SWITCHES − BOTH OFF. (To prevent the battery from receiving further charge.)

Hint 42

Possible Symptoms:
1. BATT TEMP warning light illuminated.
2. Smoke and/or fumes from radome or vent.
3. Noises from radome.

Front 43

NVG FAILURE

Back 43

1. ANNOUNCE FAILURE TO THE CREW.
If failure affects pilot at the controls:
2. FLIGHT CONTROLS − CONDUCT POSITIVE TRANSFER TO SAFETY PILOT, FLIGHT CONDITIONS PERMITTING.

Hint 43

1. Low battery LED indicator flashing.
2. Partial or complete degredation of NVG image, including focus, shading, edge glow, bright or dark spots, excessive honeycomb, distortion, flicker, and veiling glare.

Front 44

ENGINE FUEL PRESSURE LOW

Back 44

1. COMPLETE THE “BIG 4.”
2. ENGINE − MONITOR.
If NORMAL indications:
3. LAND AS SOON AS PRACTICABLE.
If ABNORMAL indications:
3. ENGINE SHUTDOWN PROCEDURE − COMPLETE.

Hint 44

1. ENG FUEL P warning light illuminated. (Engine fuel pressure less than 8.4 psi.)

Front 45

FUEL FILTER CONTAMINATION

Back 45

If both fuel filter caution lights illuminated:
1. LAND AS SOON AS POSSIBLE.

Hint 45

1. FUEL FILT caution light(s) illuminated.

Front 46

ATTITUDE GYRO FAILURE

Back 46

1. FLIGHT CONTROLS − STABILIZE AIRCRAFT.
2. AFCS GYRO SELECTOR SWITCH − MOVE IN DIRECTION OF OPERATING GYRO.
3. AFCS − REENGAGE.

Hint 46

1. AFCS caution light on.
2. Pitch and roll channel lights flashing.
3. Pitch and roll channels disengaged.
4. ATT flag on associated ADI may be visible.
5. FDS Command bars/pointer disappear (CP attitude gyro failure only).

Front 47

ATTITUDE GYRO FAILURE DURING REVERSIONARY OPERATION

Back 47

1. FLIGHT CONTROLS − STABILIZE AIRCRAFT.
2. AFCS PITCH AND ROLL CHANNELS − DISENGAGE.

Hint 47

1. Uncommanded movement about the pitch and/or roll axis.
2. ADI does not indicate true aircraft attitude.

Front 48

HEADING GYRO SYSTEM FAILURE

Back 48

1. FLIGHT CONTROLS − STABILIZE AIRCRAFT.

Hint 48

Possible Symptoms:
1. Red HDG failure flag on effected MFD (all display pages).
2. Yellow CWM (Cross Warning Monitor) failure flag on the good MFD (all display pages).
3. STAT page FAIL line − HDG1 or HDG2.
4. Incorrect or spinning heading display.
5. FMS wind information lost (dual heading failure only).
6. Degraded heading hold capability (CP gyro compass failure only).
7. Flag on BDI (CP gyro compass failure only).

Front 49

YAW RATE GYRO FAILURE

Back 49

1. FLIGHT CONTROLS − STABILIZE AIRCRAFT.

Hint 49

Symptoms:
1. Rate−of−turn pointer out of view on affected ADI.
2. AFCS caution light illuminated.
3. Yaw channel light flashing.
4. AFCS yaw channel − Disengaged.

Front 50

DETECTED FD FAILURE

Back 50

1. FLIGHT CONTROLS − STABILIZE AIRCRAFT.

Hint 50

Possible Symptoms:
1. Affected FD command bar/pointer out of view.
2. FD flags on both ADIs.

Front 51

UNDETECTED FD FAILURE

Back 51

1. FLIGHT CONTROLS − STABILIZE AIRCRAFT.

Hint 51

Symptoms:
1. Deviation of the aircraft from the desired flight path.
2. Command bar/pointer centered.

Front 52

AFCS COMPUTER OR SERIES ACTUATOR FAILURE

Back 52

1. FLIGHT CONTROLS − STABILIZE AIRCRAFT.
2. DISENGAGED CHANNELS − ATTEMPT TO REENGAGE.

Hint 52

Symptoms:
1. AFCS caution light illuminated.
2. One or more AFCS channels disengaged.
3. Associated channel light(s) on Avionics Mode Annunciator Panel flashing.
4. P TRIM, R TRIM, or Y TRIM light may be illuminated.

Front 53

AFCS SERIES ACTUATOR HARDOVER (UNDETECTED)/PARALLEL SERVO HARDOVER

Back 53

1. FLIGHT CONTROLS − STABILIZE AIRCRAFT.
2. AFFECTED CHANNEL − DISENGAGE.

Hint 53

Symptoms:
1. Uncommanded aircraft displacement.
2. P TRIM, R TRIM, or Y TRIM light illuminated.

Front 54

COLLECTIVE PARALLEL SERVO HARDOVER

Back 54

1. FLIGHT CONTROLS − STABILIZE AIRCRAFT.
2. COLLECTIVE − C−SYNC DEPRESS AND STABILIZE.

Hint 54

Symptoms:
1. Uncommanded movement of the collective.
2. Command pointer directs proper correction.

Front 55

CYCLIC ARTIFICIAL FEEL (FEEL/TRIM) FAILURE

Back 55

1. FLIGHT CONTROLS − STABILIZE AIRCRAFT.

Hint 55

Symptoms:
1. Unable to reposition cyclic force feel utilizing cyclic SYNC/TRIM REL button or overhead TRIM switch.
or
2. The cyclic has no artificial force feel (clutch disengaged).

Front 56

RADAR ALTIMETER CYCLE OR FAILURE

Back 56

1. COLLECTIVE − C−SYNC DEPRESS AND STABILIZE.

Hint 56

Possible Symptoms:
1. Undesired movement of the collective.
2. RADALT cycles, freezes, or masks.
3. RADALT audio tones heard.
4. FDS collective command pointer centered.

Front 57

CONTROL DISPLAY UNIT (CDU) FAILURE

Back 57

1. FLIGHT CONTROLS − STABILIZE AIRCRAFT.

Hint 57

Symptoms:
1. Annunciation of check STATUS in CDUs.
2. STAT page FAIL line − CDU 1, GPS 1 or CDU 2, GPS 2.
3. Check CDU annunciation on WCA panel.
4. Affected CDU display blank (possible NO DATA annunciation on CDU).
5. FMS information lost to MFD on side of failed CDU.

Front 58

DUAL DATA BUS LOCKUP
SCC FAILURE
STEERING GUIDANCE (STR) FAILURE
DISPLAY CONTROL PANEL (DCP) FAILURE
MFD FAILURE
DUAL MFD FAILURE

Back 58

1. FLIGHT CONTROLS − STABILIZE AIRCRAFT

Front 59

MODE 4 FAILURE

Back 59

1. CHECK IFF: NORM.
2. CHECK ANT: BOTH.
3. CHECK REPLY: TONE.
4. SELECT M−4A/M−4B AS APPROPRIATE.
.....
If Mode 4 WCA light remains illuminated or cycles, Mode 4 fails, or IFF fails and is in high threat area:
5. IMMEDIATELY EXIT AREA.

Hint 59

Symptoms:
Any ONE of the following:
1. Steady M4/IFF WCA light. The transponder computer is installed with power applied, but is not loaded with a valid Mode 4 code, or the transponder computer has failed its self test cycle.
2. Cycling M4/IFF WCA light. A compatible Mode 4 interrogation was received, but no Mode 4 reply was transmitted. Occurs when:
a. Transponder is in STBY.
b. A malfunction in the transponder will not allow Mode 4 reply to be transmitted, or transmits reply at very low power.
c. Neither M−4A nor M−4B is selected.
3. IFF R/T failed or indicates dashed lines or 7700: SCC #2 has possibly failed, IFF DC circuit breaker popped, Copilot’s Avionics Bus short, or #1 DC Bus short exists.

Front 60

MODE 4 AUDIO TONE

Back 60

1. SELECT M−4A/M−4B AS APPROPRIATE.
...
If tone remains and in high threat area:
2. IMMEDIATELY EXIT AREA.

Hint 60

Symptoms:
Audio tone heard in pilot’s and copilot’s headset when aircraft is interrogated.

Front 61

NOSEWHEEL SHIMMY DAMPER FAILURE

Back 61

1. LIFT AIRCRAFT OFF GROUND IMMEDIATELY OR REDUCE TAXI SPEED.

Hint 61

Symptom:
1. Lateral vibration when performing run on/off maneuvers and during high speed taxiing. These vibrations may be quite violent.

Front 62

COPILOT’S STATIC SYSTEM FAILURE

Back 62

1. FLIGHT CONTROLS − STABILIZE AIRCRAFT.
2. AFFECTED FLIGHT DIRECTOR MODES − DESELECT.

Hint 62

Symptoms:
1. Copilot’s altimeter and VSI indicate erratic or erroneous information.
2. Erratic FDS performance.

Front 63

LOST SWIMMER - DAY

Back 63

1. “MARK” POSITION.
2. TRANSITION AND ESTABLISH RIGHT ORBIT.
3. LOOK AND LISTEN FOR RS SIGNAL.
4. WHEN VISUAL − RESUME HOVER POSITION.
If these procedures fail to relocate RS:
5. COMPLETE LEAVING RESCUE SWIMMER ON SCENE PROCEDURE.

Front 64

LOST SWIMMER - NIGHT

Back 64

1. “MARK” POSITION.
2. FLASH LANDING/HOVER LIGHT.
3. LOOK AND LISTEN FOR RS SIGNAL.
4. WHEN VISUAL − CEASE FLASHING LIGHT.
If these procedures fail to relocate RS:
5. COMPLETE LEAVING RESCUE SWIMMER ON SCENE PROCEDURE.

Front 65

LEAVING RESCUE SWIMMER ON SCENE

Back 65

1. “MARK” AND RECORD POSITION.
2. DEPLOY LIGHTED RAFT.
3. DEPLOY DMB.

Front 66

EMERGENCY EGRESS PROCEDURES

Back 66

1. WAIT FOR ALL VIOLENT MOTION TO STOP
2. REFERENCE POINT − HOLD
3. EMERGENCY RELEASE HANDLE − JETTISON
4. CORDS − DISCONNECT
5. SEATBELT/HARNESS − RELEASE AND MAINTAIN REFERENCE
6. EGRESS
7. VEST − INFLATE WHEN CLEAR OF AIRCRAFT.

Front 67

JAMMED SLIDING CABIN DOOR

Back 67

1. FLIGHT MECHANIC − REMAIN SECURED TO AIRCRAFT.

Front 68

UNUSUAL ATTITUDE RECOVERY

Back 68

1. LEVEL THE WINGS.
2. NOSE ON HORIZON.
3. CENTER THE BALL.
4. POWER − ADJUST TO MAINTAIN LEVEL FLIGHT.

Front 69

HEATER OVERHEAT

Back 69

1. HEAT SWITCH - OFF

Hint 69

1. HEATER O/HEAT warning light illuminated

Front 70

SINGLE FUEL BOOST PUMP / EJECTOR / INDICATOR FAILURE

Back 70

1. FUEL BOOST PUMPS (AFFECTIVE SIDE) - BOTH ON

Hint 70

1. Feed tank warning light with fuel indicated in the system.
2. Fuel Caution Page Fuel Boost Pump Pressure indicator fluctuates, drops to 0, increases and decreases abnormally.
3. "Fuel Paramater Overlimit" on VEMD FLI if not on Fuel Caution Page.