Mh-60R Natops Cards

Front 1

Engine Malfunction in Flight
12-9

Back 1

1. Control Nr.
2. CONTGCY PWR switch - ON.
3. Single-engine conditions - Establish.
4. ENG ANTI-ICE switches - As required.
5. External cargo/stores/fuel - Jettison/dump, as required.
6. Identify malfunction.
*W x 2

Front 2

Engine High-Side Failure in Flight
12-9

Back 2

1. Engine Malfunction in Flight emergency procedure - Perform.
2. PCL (malfunctioning engine) - Retard to set:
a. Torque 10% below good engine, or
b. Matched Ng, or
c. Matched TGT.
*C / N

Front 3

Engine High-Side Failure on Deck
12-11

Back 3

1. PCLs - IDLE.

Front 4

Engine Low-Side Failure
12-11

Back 4

1. Engine Malfunction in Flight emergency procedure - Perform.
* C

Front 5

Engine Torque or TGT Spiking/Fluctuations
12-12

Back 5

If an engine instrument is spiking/fluctuating and inducing secondary indications in Ng, Np, and/or Nr:
1. Engine Malfunction in Flight emergency procedure - Perform.
If fuel contamination is suspected:
2. LAND AS SOON AS POSSIBLE.
*W

Front 6

Compressor Stall
12-13

Back 6

1. Engine Malfunction in Flight emergency procedure - Perform.
2. PCL (malfunctioning engine) - IDLE.
*C

Front 7

Engine High Speed Shaft Failure
12-14

Back 7

1. Engine Malfunction in Flight emergency procedure - Perform.
2. PCL (malfunctioning engine) - OFF.
*C

Front 8

Abort Start
12-19

Back 8

1. PCL - OFF.
2. ENGINE IGNITION switch - OFF.
3. Starter - ENGAGE.
*C

Front 9

Engine Malfunction During Hover/Takeoff
12-21

Back 9

1. Control Nr.
2. CONTGCY PWR switch - ON.
If a suitable landing site exists or unable to transition to forward flight:
3. Set level attitude, eliminate drift, cushion landing.
If able to transition to forward flight:
4. Engine Malfunction in Flight emergency procedure - Perform.

Front 10

Dual-Engine Failure in Flight/Hover
12-22

Back 10

1. Collective - Full down, enter autorotation.
2. Immediate Landing/Ditching emergency procedure - Perform.
If time and altitude permit:
3. Engine Air Restart emergency procedures - Perform.
*W x 5

Front 11

Single-Engine Failure in Flight
12-24

Back 11

1. Engine Malfunction in Flight emergency procedure - Perform.
*W

Front 12

Engine Air Restart
12-25

Back 12

1. APU Emergency Start procedure - As required.
2. ENGINE IGNITION switch - NORM.
3. Fuel selector lever(s) - DIR or XFD.
4. PCL(s) - OFF.
5. Starter(s) - ENGAGE, motor engine.
6. PCL(s) - IDLE (TGT 80 C or less, if time permits).
7. PCL(s) - Advance to FLY after starter dropout.
*W x 2 / C / N x 2

Front 13

APU Emergency Start
12-30

Back 13

1. ECS - OFF.
2. AIR SOURCE ECS/START switch - APU.
3. FUEL PUMP switch - APU BOOST.
4. APU CONTR switch - ON.
5. APU GENERATOR switch - Check ON.

Front 14

Unusual Vibrations On Deck
12-35

Back 14

1. Collective - Lower.
2. PCLs - OFF.
3. Rotor brake - Apply as required.
*C

Front 15

Hung Droop Stop(s)
12-37

Back 15

1. Re-engage rotor to greater than 75 percent Nr.
*N

Front 16

LOW ROTOR RPM Warning Light On
12-37

Back 16

1. Control Nr.

Front 17

Main Transmission Malfunction
12-41

Back 17

If failure is imminent:
1. LAND IMMEDIATELY.
If secondary indications are present:
2. LAND AS SOON AS POSSIBLE.
*W x 3 / N

Front 18

Tail/Intermediate Transmission Malfunction
12-43

Back 18

If failure is imminent:
1. LAND IMMEDIATELY.
If failure is not imminent:
2. LAND AS SOON AS POSSIBLE.
*W x 2

Front 19

INPUT CHIP (#1/#2) Caution Lights On
12-44

Back 19

1. Main Transmission Malfunction emergency procedure - Perform.
*N

Front 20

Loss of Tail Rotor Drive Altitude and Airspeed Sufficient to Establish Autorotation
12-45

Back 20

1. PAC call - "AUTO, AUTO, AUTO."
2. Autorotation - Establish. Center tail rotor pedals.
3. Drive failure - Attempt to verify.
4. Immediate Landing/Ditching emergency procedure - Perform.
5. PCLs - OFF when directed (prior to the flare).
*W x 2

Front 21

Loss of Tail Rotor Drive Altitude and Airspeed Not Sufficient to Establish Autorotation
12-45

Back 21

1. PAC call - "HOVER, HOVER, HOVER."
2. Collective - Lower.
3. PNAC - Hands on PCLs.
4. PCLs - OFF when directed (approximately 20 to 30 feet).
*W / C

Front 22

Loss of Tail Rotor Control
12-50

Back 22

1. Collective/Airspeed - Adjust as required to control yaw.
*W x 5

Front 23

Hydraulic System Warning
12-52

Back 23

1. LAND IMMEDIATELY.

Front 24

#1 Primary Servo or #1 Transfer Module Leak
12-55

Back 24

1. SERVO switch - 1st OFF.
2. Land as soon as practical.
If the BACKUP RSVR LOW caution also appears or the backup pump fails:
3. LAND AS SOON AS POSSIBLE.
If the #2 PRI SERVO caution and/or HYD warning appears:
4. LAND IMMEDIATELY.
*C

Front 25

#2 Primary Servo or #2 Transfer Module Leak
12-57

Back 25

1. SERVO switch - 2nd OFF.
2. Land as soon as practical.
If the BACKUP RSVR LOW caution also appears or the backup pump fails:
3. LAND AS SOON AS POSSIBLE.
If the #1 PRI SERVO caution and/or HYD warning appears:
4. LAND IMMEDIATELY.

Front 26

Boost Servo Hardover
12-60

Back 26

1. SAS/BOOST pushbutton - OFF.

Front 27

Utility Pump Caution Lights
12-60

Back 27

1. Stop Dome.
*C

Front 28

AFCS DEGRADED Caution Light On
12-62

Back 28

1. Safe altitude and airspeed - Establish (waveoff/Instrument Takeoff [ITO], as required).
*N

Front 29

Stabilator Auto Mode Failure
12-65

Back 29

1. PAC call - "STAB, STAB, STAB."
2. Cyclic - Arrest pitch rate.
3. Collective - Do not reduce.
4. MAN SLEW SWITCH - Adjust to 0 degrees.
*W x 6 / N

Front 30

Unusual Attitude Recovery
12-67

Back 30

1. Level wings.
2. Nose on horizon.
3. Center ball.
4. Stop rate of climb/descent.
5. Control airspeed.

Front 31

Total AC Power Failure/Dual Generator Failure
12-68

Back 31

1. Safe altitude and airspeed - Establish.
2. Stabilator - Check position, slew as required.
3. APU Emergency Start Procedure - Perform.
*W x 3 / N x 3

Front 32

#1 or #2 FUEL FLTR BYPASS or #1 or #2 FUEL PRESS Caution Lights
12-79

Back 32

1. Fuel selector lever (affected engine) - XFD (DIR if currently in XFD).
*W

Front 33

#1 and #2 FUEL FLTR BYPASS or #1 and #2 FUEL PRESS Caution Lights
12-80

Back 33

1. LAND AS SOON AS POSSIBLE.
2. APU Emergency Start procedure - Perform.
*W x 2 / N

Front 34

External Engine Fire
12-84

Back 34

1. Confirm Fire.
2. Engine Malfunction in Flight emergency procedure - Perform.
3. PCL (affected engine) - OFF.
4. Engine T-handle (affected engine) - Pull.
5. FIRE EXTGH switch - MAIN (RESERVE if required or ac power is off).
If airborne and fire continues:
6. LAND IMMEDIATELY.
If fire appears extinguished:
7. LAND AS SOON AS POSSIBLE.
*N

Front 35

Internal Engine Fire
12-85

Back 35

1. Starter - Engage. Motor Engine.

Front 36

APU Fire
12-85

Back 36

1. APU T-Handle - Pull.
2. Confirm Fire.
3. FIRE EXTGH switch - RESERVE (MAIN if required and available).
If airborne and fire continues:
4. LAND IMMEDIATELY.
If fire appears extinguished:
5. LAND AS SOON AS POSSIBLE.
If on ground:
6. Fire extinguisher - As required.
*W / N

Front 37

Cockpit Fire/Cabin Fire
12-86

Back 37

If source is known:
1. Affected power switches and cbs - Secure.
2. Portable Fire Extinguisher - As required.
If fire continues or source is unknown:
3. Cabin/doors/vents/ECS - CLOSE/OFF, as required.
4. Unnecessary electrical equipment and cbs - Secure.
If fire continues:
5. LAND AS SOON AS POSSIBLE.

Front 38

Smoke and Fumes Elimination
12-87

Back 38

1. Airspeed - Adjust, as required.
2. Doors/windows/vents - Open.
3. Aircraft - Yaw, as required.

Front 39

Immediate Landing/Ditching (Pilot)
12-87

Back 39

1. Crew and passengers - Alert.
2. Shoulder harness - Locked.
3. External cargo/stores/fuel - Jettison/dump, as required.
4. Searchlight - As required.
5. MAYDAY/IFF - TRANSMIT/EMER.
In the flare:
6. Windows - Jettison, as required.
After landing:
7. PCLs - OFF.
8. Rotor brake - ON.
9. Copilot collective - STOW.
After all violent motion stops:
10. Egress.
*W x 3 / C

Front 40

Underwater Egress
12-92

Back 40

1. HABD - As required.
2. Cord(s) - Disconnect.
3. Door/Window - Open/jettison.
4. Place hand on known reference point.
5. Harness - Release.
6. Exit helicopter.
After egress:
7. Swim clear of helicopter and inflate LPU.
*W x 6

Front 41

Cargo Hook Emergency Release
12-93

Back 41

1. Cyclic EMERGENCY RELEASE/CABLE SHEAR - Press.
*W

Front 42

FLIR Uncommanded Lasing
12-109

Back 42

1. MASTER ARM - SAFE.
2. LASER SELECT - SAFE.
If lasing continues:
3. FLIR - OFF.

Front 43

Hellfire Missile Hangfire
12-111

Back 43

If rocket motor ignites and aircraft yaws:
1. Adjust controls as required to maintain straight-and-level flight.
*W / C / N x 2

Front 44

All Stores Jettison
12-115

Back 44

1. ALL STORE JETT - Press.
*N x 8

Front 45

SNAG Caution Light
12-134

Back 45

1. Stop dome.
*C

Front 46

Loss of Sonar Dome
12-139

Back 46

1. Sonar Cable Cut procedures - As required.

Front 47

TGT Limits
4-2

Back 47

0 - 810: Cont/Green
810 - 851: 30 Mins/Yellow
(N: 851 - 878: 10 Mins/Yellow [EDECU max power check only])
851 (878) - 903: 2.5 Mins/Red
903 - 949: 12 Sec/Red
949: Max/Red

Front 48

Nr Limits
4-3

Back 48

<96: Avoid/Red
96 - 101: Cont/Green
101 - 120: Prec/Yellow
120: Max/Red
123 for FCF/Red
127, 137, 142: Overspeed Latch/Red
N: 123 authorized for Auto/Red

Front 49

Np Limits
4-2

Back 49

<96: Avoid/Red
96 - 101: Cont/Green
101 - 120: 12 Sec/Yellow
120: Max
N: Avoid 20 - 40 & 60 - 75

Front 50

Ng Limits
4-3

Back 50

0 - 98: Cont/Green
98 - 102: 30 Min/Yellow
102 - 105: 12 Sec/Red
105: Max/Red

Front 51

Dual Engine <80 KIAS TRQ Limits
4-3

Back 51

0 - 120: Cont/Green
120 - 144: 10 Sec/Yellow
144: Max/Red

Front 52

Dual Engine >80 KIAS TRQ Limits
4-3

Back 52

0 - 106: Cont/Green
106 - 127: 10 Sec/Yellow
127: Max/Red

Front 53

Single Engine TRQ Limits
4-3

Back 53

0 - 135: Cont/Green
135 - 144: 10 Sec/Yellow
144: Max/Red

Front 54

XMSN T
4-3

Back 54

-50 - 105: Cont/Green
105 - 120: Prec/Yellow
120: Max/Red

Front 55

XMSN P
4-3

Back 55

20: Min/Red
20 - 30: Idle & Transient/Yellow
30 - 65 (45 - 60 level flight): Cont/Green
65 - 130: Prec/Yellow
130: Max/Red

Front 56

ENG OIL T
4-4

Back 56

-50 - 135: Cont/Green
135 - 150: 30 Min/Yellow
150: Max/Red

Front 57

ENG OIL P
4-4

Back 57

22: Min/Red
22 - 26: Prec/Yellow (Green <70% Ng)
26 - 100: Cont/Green
100 - 120: Prec/Yellow
120: Max/Red

Front 58

Engine Start <16 C
4-4

Back 58

1st: 60 Sec
2nd: 60 Sec
3rd: 60 Sec
4th: 30 Min

Front 59

Engine Start 16 - 52 C
4-4

Back 59

1st: 60 Sec
2nd: 30 Min

Front 60

Engine Motor (Ignition Off)
4-4

Back 60

2 Min ON / 5 Min OFF
2 Min ON / 30 Min OFF

Front 61

Prohibited Maneuvers
4-9

Back 61

1. Aerobatic Flight
2. Practice full-autorotation landings
3. Intentional approaches into or inducement of retreating blade stall

Front 62

Land Immediately
12-7

Back 62

Execute a landing without delay. The primary consideration is to ensure the survival of the occupants

Front 63

Land as soon as Possible
12-7

Back 63

Execute a landing at the first site at which a safe landing can be made.

Front 64

Land as soon as Practicable
12-7

Back 64

Extended flight is not recommended. The landing site and duration of flight are at the discretion of the PIC.

Front 65

Abort Start Criteria
12-19

Back 65

1. Ng does not reach 14% within 6 seconds after starter initiation
2. No oil pressure within 30 seconds agter starter initiation (do not motor engine)
3. No light-off within 30 seconds agter moving PCL to Idle
4. ENG STARTER advisory disappears before reaching 52% Ng
5. TGT reaches 851 C before idle is attained

Front 66

Rescue Hoist Cable Cut
12-95

Back 66

1. Emergency shear switch - SHEAR
If unable:
2. Direct pilot to press EMER REL button

Front 67

RAST Messenger Jettison
12-99

Back 67

1. Cyclic EMERGENCY RELEASE/CABLE SHEAR - Press
*C

Front 68

All Emergency Steps
12-6

Back 68

1. Maintain control of the aircraft
2. Alert crew
3. Determine the precise nature of the problem
4. Complete the applicable emergency procedure or take action appropriate for the problem
5. Determine landing criteria and land as required

Front 69

Minimum planned fuel on landing
4-5

Back 69

600 lbs.

Front 70

Rotor engagement and disengagement limitations
4-5

Back 70

Max for rotor engagement/disengagement 45 knots any direction

Front 71

1. Vne
2. Sideward/Rearward flight
3. Autorotation
4-5

Back 71

1. 180 KIAS
2. 35 knots
3. 100 KIAS

Front 72

1. Boost off
2. Two SAS inoperative in IMC
3. Either PRI SERVO PRESS caution
4-5

Back 72

1. 140 KIAS
2. 125 KIAS
3. 125 KIAS

Front 73

1. Cabin door opening/closing
2. Searchlight in fixed position other than stowed
3. Searchlight in transition
4-6

Back 73

1. 60 KIAS
2. 160 KIAS
3. 100 KIAS

Front 74

1. Dome at trail
2. Dome below trail
3. Winshield wipers operating
4-6

Back 74

1. 100 KIAS, 45 AOB
2. 70 KIAS, 15 AOB
3. 130 KIAS

Front 75

Sonobuoy Launch Limits
4-6

Back 75

a. 70 - 150' up to 100 KIAS with dome at trail
b. Above 100 KIAS, 150' or above with dome seated

Front 76

Slope landing limits
4-9

Back 76

a. 9 nose up
b. 12 cross-slope
c. 6 down

Front 77

Gross weight limits
4-10

Back 77

23,500 Max
23,500 aviation ships
22,500 air-capable ships

Front 78

1. External load limit
2. Rescue hoist limit
3. Internal load weight limt
4-10

Back 78

1. 6000 lbs
2. 600 lbs
3. 300 lbs sqft

Front 79

The HMU responds to the PCL for:
2-8

Back 79

1. Fuel shutoff.
2. Setting engine start fuel flow with automatic acceleration to ground idle.
3. Setting permissible Ng up to maximum.
4. Fuel priming.
5. DECU override capability (LOCKOUT).

Front 80

The Ng overspeed valve is set to trip at ________ Ng.
2-9

Back 80

110 +/- 2% Ng

Front 81

The overspeed system is actuated at _______ Np.
2-11

Back 81

120

Front 82

The maximum Contingency Range Power (CRP) limiter will prevent further increase in fuel flow to the engine at _______.
2-11

Back 82

891 C +/- 10 C

Front 83

When TGT approaches ______, the DECU prevents any further increase in fuel flow to the engine. The Intermediate Power Range (IRP) limiter will prevent this at ______.
2-11

Back 83

851 C, 839 C +/- 10 C

Front 84

(DECU) Detects a hot start when TGT exceeds _____ with Ng below _____and Np below _____ and automaticlly stops fuel by tripping the _____.
2-12

Back 84

900 C, 60%, 50%, ODV

Front 85

(DECU) Fuel flow is restored when TGT either decreases to _____or after _____, whichever occurs _____.
2-12

Back 85

300 C, 25 sec., first

Front 86

Hydraulic system pressure:
2-70

Back 86

3000 psi, with the exception of the roll and pitch trim actuators. (1000 psi).

Front 87

#1 / #2 / Backup hydraulic pump fluid capacity:
3-16

Back 87

1 U.S. quart

Front 88

Utility hydrauilc pump fluid capacity:
3-17

Back 88

0.92 U.S. quart

Front 89

#1 / #2 / Backup / Utility hydraulic fluid product:
3-14

Back 89

MIL SPEC: MIL-PRF-83282
NATO CODE: H-537
Substitute: None

Front 90

(#1 / #2 / Backup hydraulic pumps)
Piston movement of up to ______ into the ______ zone is acceptable.
3-17

Back 90

3/8 inch, blue (overserviced)

Front 91

Main tanks usable gallons/pounds with JP-5:
3-8

Back 91

6.8 lb/gal: 590 gallons / 4012 pounds

Front 92

Main tanks usable gallons / pounds with JP-8:
3-8

Back 92

6.7 lb/gal: 590 gallons / 3953 pounds

Front 93

1. Pressure fueling limit:
2. Internal fuel cell pressure limit:
3-9

Back 93

1. 55 psi
2. 2 psi

Front 94

The NHC nozzle has a built-in ______ and an on/off flow control handle. Emergency breakaway is initiated when ______ of straight tensile pull is exerted on the automatic breakaway coupling.
8-36

Back 94

45-psi pressure regulator, 450 ±50 pounds

Front 95

Rotor brake caution illuminates when:
12-38

Back 95

Hydraulic pressure greater than 6 to 8 psi is registered at pressure switch.

Front 96

MAIN XMSN PRESS LOW caution activates at ______ from a sensor located in the ______.
2-30

Back 96

14 psi, #1 accessory module

Front 97

MAIN XMSN OIL HOT caution activates at ______ from a sensor located at the ______.
2-30

Back 97

117 C, oil cooler input to the MGB manifold

Front 98

APU oil capacity / type:
3-14

Back 98

2 U.S. quarts / MIL SPEC: MIL-PRF-23699, NATO CODE: O-156, Substitute: None

Front 99

Main Transmission capacity / type:
3-14

Back 99

7.5 U.S. gallons / MIL SPEC: DOD-PRF-85734, Substitute: None

Front 100

IGB/TGB capacity / type:
3-14

Back 100

2.75 U.S. pints / MIL SPEC: DOD-PRF-85734, Substitute: None

Front 101

Rescue hoist capacity / type:
3-14

Back 101

1.16 U.S. quarts / MIL SPEC: MIL-PRF-23699, NATO CODE: O-156, Substitute: None

Front 102

Engine starter capacity / type:
3-14

Back 102

200 cc / MIL SPEC: MIL-PRF-23699, NATO CODE: O-156, Substitute: None

Front 103

Engine oil capacity / type:
3-14

Back 103

2 U.S. quarts / MIL SPEC: MIL-PRF-23699, NATO CODE: O-156
Substitute: MIL SPEC: MIL-PRF-7808, NATO CODE: O-148

Front 104

External power requirements:
3-19

Back 104

115/200V, 3-phase, 400 Hz ac power.

Front 105

A minimum of ______ should be maintained from other aircraft or structures and ______ should be maintained from any operating radar set.
3-1

Back 105

50 feet, 75 feet

Front 106

PRIST in aerosol cans is ______ for use
3-7

Back 106

not authorized

Front 107

The engine oil filter PDI has a thermal lock out below ______
2-15

Back 107

38 C

Front 108

A malfunctioning anti-ice/start bleed valve is indicated by any of the following:
2-17

Back 108

1. Illumination of the ENG ANTI-ICE ON advisory light with above 90 percent Ng or above 94 percent Ng if OAT is 15 °C or greater.
2. No illumination of the ENG ANTI-ICE ON advisory light when Ng drops below approximately 88 percent Ng. (Ng may vary on a sliding scale depending on OAT.)
3. No illumination of the ENG ANTI-ICE ON advisory light when the ENG ANTI-ICE switch is selected ON.
4. No rise in TGT when ENG ANTI-ICE switch is selected ON.

Front 109

INLET ANTI-ICE advisory will illuminate when ______
2-19

Back 109

bleed air heats the engine inlet to approximately
93 °C

Front 110

(INLET ANTI-ICE) The bellows begins closing the valve when the OAT reaches ______ and should be completely closed by ______.
2-20

Back 110

4 C, 13 C

Front 111

1. Antiflapping restraints out:
2. Droop stops out:
3. Droop stops in:
2-21

Back 111

1. 35% Nr or greater
2. approx. 70% Nr
3. approx. 50% Nr

Front 112

The tail rotor head and blades are installed on the right side of the tail pylon, canted ______, and provide ______ of the total lifting force in a hover
2-23

Back 112

20° upward, 2.5 percent

Front 113

External fuel tank capacity:
2-34

Back 113

120 gallons / JP-5: 816 pounds / JP-8: 804 pounds

Front 114

Emergency jettison of external fuel tanks via the ALL STORE JETT pushbutton (PB) is inhibited when less than ______ (approximately ______ pounds) remain in tank.
2-35

Back 114

40 gallons, 272

Front 115

The main cells’ interconnect level is approximately ______.
2-34

Back 115

270 to 600 pounds per side

Front 116

APU fuel consumption at rated power:
2-41

Back 116

150 lbs per hour

Front 117

As the accumulator pressure drops below ______, the APU ACCUM LOW advisory appears
2-43

Back 117

2650 psi

Front 118

Stabilator airspeed/angle limits:
12-66

Back 118

0/150 KIAS
10/100 KIAS
20/80 KIAS
30/60 KIAS
40/45 KIAS