C-130T Fe

Front 1

True or False

WHEN OPENING THE OXYGEN SHUTOFF VALVE AFTER IT HAS BEEN TURNED TO THE OFF POSITION, OPEN RAPIDLY TO THE ON POSITION.

Back 1

False

Front 2

True or False

AFTER TAKEOFF FROM SLUSHY RUNWAYS, CYCLE THE LANDING GEAR TO REDUCE THE POSSIBILITY OF DOORS FREEZING IN THE CLOSED POSITION.

Back 2

True

Front 3

True or False

FOR ALL OPERATIONS BELOW 1,000 FEET AGL, THE PILOT NOT FLYING SHALL PLACE HIS/HER HAND AT THE BASE OF THE THROTTLES.

Back 3

True

Front 4

True or False

IF A HOT BRAKE IS SUSPECTED OR A MAIN WHEEL WELL FIRE EXISTS, SET BOTH BRAKES.

Back 4

False

Front 5

True or False
OPERATION OF THE AIRCRAFT IN THE RED AREA OF THE WEIGHT LIMITATION CHART SHOULD BE AVOIDED. IF FLIGHT IS CONDUCTED IN THIS AREA, AN ENTRY MUST BE MADE IN THE AIRCRAFT RECORDS.

Back 5

True

Front 6

True or False
WHEN MIXING PASSENGERS & CARGO ON AIRCRAFT, CAUTION SHOULD BE EXERCISED DURING GROUND OPERATIONS TO PREVENT AIRCRAFT TIPPING AFT BECAUSE OF POSSIBLE AFT CG W/ NO PASSENGERS ON BOARD.

Back 6

True

Front 7

True or False

THE AIRCRAFT SHALL BE CHOCKED PRIOR TO INSTALLATION OF NOSE PIN.

Back 7

True

Front 8

True or False

IF PROPELIF THE PROPELLER CONTINUES TO ROTATE OR IS ROTATING BACKWARDS AND ENGINE WAS NOT SHUT DOWN DUE TO ANY OF THE ENGINE SHUTDOWN CONDITIONS, RESTART MAY BE PERFORMED IN ACCORDANCE WITH AIRSTART PROCEDURES.

Back 8

True

Front 9

True or False
SECONDARY FUEL MANAGEMENT WILL OCCUR ANY TIME THERE IS USABLE FUEL IN THE EXT AND/ OR AUX TANKS & THE MAIN TANKS ARE PARTIALLY FILLED, OR WHEN THE PRESCRIBED FUEL WEIGHT DIFFERENCE BETWEEN EACH INBOARD & OUTBOARD MAIN TANK IS NOT OBSERVED.

Back 9

True

Front 10

True or False

THE PROPELLER ANTI-ICING SYSTEM IS A CONTINUOUS HEATING TYPE SYSTEM.

Back 10

True

Front 11

True or False

THE PROPELLER DEICING SYSTEM IS A CONTINUOUS HEATING TYPE SYSTEM.

Back 11

False

Front 12

True or False

DURING ENGINE SHUTDOWN PROCEDURES, IF A FIRE INDICATION PERSISTS, A BREAK IN THE BLEED-AIR MANIFOLD MAY EXIST.

Back 12

True

Front 13

True or False

SURFACES COVERED WITH LOOSE SNOW GENERALLY PROVIDE BETTER BRAKING THAN SURFACES COVERED WITH COMPACTED SNOW.

Back 13

True

Front 14

True or False
AN IMPROPERLY ADJUSTED OR MALFUNCTIONING NTS SYSTEM CONTINUOUSLY RECEIVING NTS'S WILL CAUSE A PROPELLER TO MOVE TO A HIGH BLADE ANGLE. THE RESULTANT LOAD MAY CAUSE AN ENGINE STALL OR FLAMEOUT.

Back 14

True

Front 15

DURING COLD WEATHER STARTS, LEAVE THE THROTTLES IN THE GROUND IDLE DETENT UNTIL OIL TEMPERATURE REACHES ___________ º C.

Back 15

40º C

Front 16

DO NOT EXCEED _________ KIAS WITH THE RAMP UP AND LOCKED AND THE CARGO DOOR OPEN.

Back 16

185 Knots

Front 17

DO NOT ALLOW THE PITOT HEAT TO REMAIN ON FOR MORE THAN __________ SECONDS ON THE GROUND.

Back 17

30 Seconds

Front 18

A ROLLING TAKEOFF IS PERMITTED PROVIDED CHARTED TAKEOFF POWER IS ESTABLISHED WITHIN ________ SECONDS AFTER THE AIRCRAFT BEGINS ITS TAKEOFF ROLL.

Back 18

5 Seconds

Front 19

ENGINE SHUTDOWN SHOULD NOT BE ACCOMPLISHED WHEN TAXI SPEED, WIND VELOCITY, OR A COMBINATION OF WIND VELOCITY AND TAXI SPEED IS GREATER THAN ________ KNOTS.

Back 19

20 Knots

Front 20

A TACH GENERATOR FAILURE MAY BE INDICATED BY.

Back 20

-RPM DECREASE OR FLUCTUATIONS
-FUEL FLOW INCREASE OF FLUCTUATIONS
-TORQUE DECREASE OR FLUCTUATION

Front 21

ON AIRCRAFT WITH FOAM INSTALLED, IF FUEL IN NO 1 OR 4 TANKS EXCEEDS ______lbs OR TOTAL FUEL IN ALL MAIN TANKS EXCEEDS ___________lbs, THE AIRCRAFT MAXIMUM LANDING RATE IS 300 FPM.

Back 21

6,150 or 23,310 Lbs

Front 22

OPERATING MORE THAN ________ ENGINES FROM ONE MAIN TANK BOOST PUMP MAY RESULT IN FLAME-OUT OF ONE OR MORE ENGINES DUE TO FUEL STARVATION.

Back 22

2 Engines

Front 23

MAXIMUM INDICATED TURBINE INLET TEMPERATURE FOR TAKE-OFF IS _________ º C.

Back 23

1083º C

Front 24

INDICATED TURBINE INLET TEMPERATURE FOR MILITARY IS __________ º C.

Back 24

1049ºC

Front 25

MAXIMUM TURBINE INLET TEMPERATURE FOR CLIMB IS ___________ ºC

Back 25

1010ºC

Front 26

INIDCATED TURBINE INLET TEMPERATURE FOR MAX CONTINUOUS IS ________ºC

Back 26

1010ºC

Front 27

MAXIMUM INDICATED TORQUE AT OIL TEMPERATURE -40º C TO 0º C IS __________ IN LBS

Back 27

MINIMUM

Front 28

WHAT ACTION IS REQUIRED IF TURBINE INLET TEMPERATURE EXCEEDS 830º C (EXCLUDING MOMENTARY OVERSHOOT AND PEAK TURBINE INLET TEMPERATURE AT 94% RPM) DURING START.

Back 28

Record the discrepancy

Front 29

NOT USE FUEL ENRICHMENT IF ENGINE INDICATES A TURBINE INLET TEMPERATURE OF _______ºC OR MORE PRIOR TO ENGINE START ON THE GROUND.

Back 29

100ºC

Front 30

WHEN RESTARTING AN ENGINE THAT HAS BEEN SHUT DOWN IN FLIGHT, BE SURE THAT THE TURBINE INLET TEMPERATURE FOR THAT ENGINE HAS DROPPED BELOW _________ºC.

Back 30

200ºC

Front 31

DURING ENGINE RUN UP, WHEN ADVANCING THE THROTTLES TO THE POINT WHERE THE FUEL CORRECTION LIGHTS ARE EXTINGUISHED, THE TURBINE INLET TEMPERATURE SHOULD INDICATE BETWEEN _______ AND ________ ºC

Back 31

800-840ºC

Front 32

THE START VALVE LIGHT SHOULD ILLUMINATE WITHIN _______ SECONDS.

Back 32

5 Seconds

Front 33

DURING ENGINE STARTS, POSITIVE OIL PRESSURE INDICATION IS REQUIRED BY ________ % RPM.

Back 33

35%

Front 34

REDUCTION GEAR INDICATED OIL PRESSURE MAY EXCEED _________ PSI DURING WARM UP WITH AMBIENT TEMPERATURE BELOW________º C

Back 34

250 psi at 15ºC

Front 35

REDUCTION GEAR INDICATED OIL PRESSURE FOR TAKE OFF AND FLIGHT OPERATION IS _________ PSI MINIMUM TO ________PSI MAXIMUM.

Back 35

150 – 250 psi

Front 36

POWER SECTION INDICATED OIL PRESSURE FOR TAKE OFF AND FLIGHT OPERATION IS _______PSI MINIMUM TO ___________ MAXIMUM.

Back 36

50 – 60 psi

Front 37

NORMAL INDICATED OIL TEMPERATURE IS FROM ________ºC TO _______ºC

Back 37

60 - 85ºC

Front 38

ALL ENGINES SHALL BE ON CROSSFEED OPERATION WHEN TOTAL FUEL IS LESS THAN _________ LBS

Back 38

6,000 lbs

Front 39

WHEN ANY FUEL TANK IS BELOW _________ LBS OF FUEL, THAT TANK WILL BE PLACED ON CROSSFEED OPERATION.

Back 39

1,000 lbs

Front 40

UTILITY HYDRAULIC SYSTEM NORMAL LIMITS ARE ________ TO _________ PSI WITH A MAXIMUM OF _________PSI

Back 40

2,900 – 3,200 with a maximum of 3,500 psi

Front 41

AUXILIARY HYDRAULIC SYSTEM NORMAL LIMITS ARE _________ TO ________ PSI WITH A MAXIMUM OF __________PSI.

Back 41

2900-3300 with a maximum of 3,500 psi

Front 42

HYDRAULIC PRESSURE AS LOW AS ________ PSI MAY BE EXPERIENCED IN LOW SPEED GROUND IDLE AND IS ACCEPTABLE AS LONG AS THE NORMAL LIMITS ARE ATTAINED AT 100%

Back 42

2,550 psi

Front 43

A POSITIVE HYDRAULIC PRESSURE INDICATION SHOULD BE NOTED BY THE TIME THE ENGINE IS ON SPEED, AND THE NORMAL OPERATING PRESSURE SHOULD BE INDICATED WITHIN __________ SECONDS AFTER THE ENGINE IS ON SPEED AT 100% RPM

Back 43

30 Seconds

Front 44

WHEN PERFORMING AN ENGINE BLEED AIR REGULATOR CHECK, IF INDIVIDUAL REGULATOR PRESSURES ARE NOT WITHIN APPROXIMATELY _______ PSI OF EACH OTHER, PLACE THE ENGINE BLEED AIR SWITCHES TO OFF OR OVERRIDE FOR TAKE-OFF

Back 44

3 psi

Front 45

USABLE FUEL QUANTITY (FOR THE WING TANKS) IS BASED ON ________ DEGREE NOSE UP ATTITUDE AND WINGS LEVEL.

Back 45

4º

Front 46

DURING TAXI, REVERSE PROPELLERS IN SYMMETRICAL PAIRS AND CHECK RPM, TURBINE INLET TEMPERATURE, FUEL FLOW & TORQUE DIFFERENTIAL: IF TORQUE DIFFERENTIAL IS GREATER THAN ______________ INCH POUNDS, COMPENSATE ON SUBSEQUENT REVERSING AND RECORD THE DISCREPANCY.

Back 46

1,000 lbs

Front 47

WHEN DOWN SHIFTING TO LOW SPEED GROUND IDLE, THE COPILOT WILL MONITOR THE ENGINE INSTRUMENTS AND BE PREPARED TO SHUT DOWN THE ENGINE IF A STALL OR OVER TEMPERATURE OF __________º C OR GREATER OCCURS.

Back 47

850ºC

Front 48

INDICATED RPM FOR LOW SPEED GROUND IDLE IS _________% MINIMUM TO ____________% MAXIMUM.

Back 48

69 – 75.5%

Front 49

INDICATED RPM FOR FLIGHT IDLE IS ________% MINIMUM TO __________% MAXIMUM.

Back 49

92.5 – 100.5%

Front 50

THE SAFETY COUPLING IS PROVIDED TO DECOUPLE THE POWER SECTION FROM THE REDUCTION GEAR IF NEGATIVE TORQUE APPLIED TO THE REDUCTION GEAR EXCEEDS APPROXIMATELY NEGATIVE __________ IN POUNDS.

Back 50

-6,000 in lbs

Front 51

THE OPERATING LIMITS OF THE MAIN TANK FUEL BOOST PUMPS _______ TO _________ PSI.

Back 51

15 – 24 psi

Front 52

THE AUXILLARY AND EXTERNAL FUEL TANK EMPTY LIGHTS WILL BE ILLUMINATED WHENEVER OUTPUT FLOW PRESSURE IS BELOW APPROXIMATELY __________PSI.

Back 52

23 psi

Front 53

THE #3 MAIN TANK FUEL BOOST PUMP RECEIVE POWER FROM THE ________ BUS.

Back 53

Main AC

Front 54

WHAT IS THE MAXIMUM FUEL IMBALANCE WING TO WING?

Back 54

1,500 lbs

Front 55

THE ELECTRICAL VOLTAGE LIMITS FOR THE AC GENERATORS ARE ________ TO ________ VAC.

Back 55

110 – 125

Front 56

WHAT IS THE MAXIMUM ALLOWABLE DC LOAD?

Back 56

1.03 amps

Front 57

WHICH OF THE FOLLOWING MIGHT INDICATE A LOSS OR PARTIAL LOSS OF THE ESSENTIAL AC BUS.

Back 57

-ERRATIC AUTOPILOT OPERATION (NOT PILOT INDUCED)
- ILLUMINATION OR FLICKERING No. 2 FUEL BOOST PUMP LOW PRESSURE LIGHT
- ILLUMINATION OF PILOT AND COPILOT PITOT HEAT OFF LIGHTS

Front 58

DURING GROUND TESTING AND OPERATIONS, THE PROPELLER ANTI-ICE/DE-ICE SYSTEM SHOULD BE OPERATED ONLY ON AN ENGINE THAT IS RUNNING AND NEVER MORE THAN ________ CYCLES.

Back 58

2 cycles

Front 59

IN THE EVENT A WING LEADING EDGE OVERHEAT LIGHT ILLUMINATES DURING IN-FLIGHT OPERATION, THE FIRST STEP IS.

Back 59

Turn the Wing Anti Icing Switch off

Front 60

THE UTILITY HYDRAULIC SYSTEM NORMALLY OPERATES WHICH OF THE FOLLOWING SYSTEMS?

Back 60

FLAPS, NORMAL BRAKES, LANDING GEAR, NOSEWHEEL STEERING, PORTION OF THE FLIGHT CONTROLS

Front 61

THE ENGINE DRIVEN HYDRAULIC PUMP WARNING LIGHTS WILL ILLUMINATE WHEN PUMP OUTPUT PRESSURE DROPS BELOW _________ PSI.

Back 61

1,000 psi

Front 62

WHEN THE ENGINE BLEED AIR REGULATOR SWITCH IS IN OVRD POSITION, THE ENGINE BLEED AIR REGULATOR VALVE _____________.

Back 62

Fully Open

Front 63

THE CARGO COMPARTMENT REFRIGERATOR OVERHEAT LIGHT ILLUMINATES WHEN AN OVERHEAT CONDITION OF _____________?

Back 63

200º F

Front 64

THE APU WILL START AND OPERATE AT ALTITUDES UP TO _________ FEET.

Back 64

20,000 Feet

Front 65

FUEL FOR THE APU IS GRAVITY FED FROM THE __________ FUEL TANK.

Back 65

#2 Main fuel tank

Front 66

WHEN OPERATING THE APU WITH LESS THAN ________ POUNDS OF FUEL IN THE #2 MAIN TANK, TURN THAT FUEL BOOST PUMP ON TO MAINTAIN SURGE BOX FUEL LEVEL.

Back 66

2,000 lbs

Front 67

DO NOT EXCEED __________ KTS WITH THE LANDING LIGHT EXTENDED.

Back 67

170 Knots

Front 68

AFTER TURNING, MOVE THE AIRCRAFT APPROXIMATELY ________ FEET FORWARD IN A STRAIGHT LINE TO RE ALIGN THE MAIN LANDING GEAR.

Back 68

5 Feet

Front 69

CONDUCT HOLDING OPERATIONS AT _________KIAS OR _________ KIAS ABOVE MAXIMUM ENDURANCE AIRSPEED IF MAXIMUM ENDURANCE IS REQUIRED.

Back 69

170 KIAS or 20 KIAS above Max Endurance

Front 70

IN THE EVENT IT BECOMES NECESSARY TO MAKE A CIRCLING APPROACH TO ALIGN THE AIRCRAFT WITH THE RUNWAY, MAINTAIN __________ UNTIL ON FINAL APPROACH.

Back 70

150 KIAS or Computed approach speed whichever is greater

Front 71

WHEN EXECUTING A GO-AROUND AT LOW AIRSPEEDS WITH ONE OR TWO ENGINES INOPERATIVE, RAISE THE FLAPS IN ________% INCREMENTS WITH AIRSPEED INCREASING APPROXIMATELY _________KNOTS BETWEEN RETRACTION INCREMENTS.

Back 71

10% w/ airspeed increasing approximately 5 Knots

Front 72

IF PROPELLER ROTATION CONTINUES AFTER FEATHER HAS BEEN INITIATED, SLOW THE AIRCRAFT TO A MINIMUM SAFE AIRSPEED, BUT NOT LESS THAN____________.

Back 72

2 ENGINE VMCA (135 MINIMUM)

Front 73

ENGINE GROUND STARTING MAY BE ACCOMPLISHED WITH A STANDARD AIR STARTING UNIT THAT WILL DELIVER A MINIMUM OF _________PPM AIRFLOW AT ___________PSI PRESSURE.

Back 73

90 PPM @ 25 psi

Front 74

WHAT IS THE NATO CODE FOR JP-8

Back 74

F-34

Front 75

THE APU STARTER DUTY CYCLE IS LIMITED TO ____ MINUTE ON AND _____ MINUTES OFF.

Back 75

1 on 4 off

Front 76

WHAT IS THE NORMAL CABIN DIFFERENTIAL PRESSURE RANGE?

Back 76

-1.2 to 15.8 IN HG

Front 77

WHAT IS THE EMERGENCY BRAKE ACCUMULATOR PRELOAD PRESSURE LIMITS?

Back 77

1,000 psi +/- 100

Front 78

WHEN THE TEMPERATURE IN THE LEADING EDGE REACHES APPROXIMATELY _______ THE WARNING LIGHT FOR THAT AREA ILLUMINATES.

Back 78

200º F

Front 79

THE HYDRAULIC SUCTION BOOST PUMP WARNING LIGHT WILL ILLUMINATE IF PRESSURE OUTPUT DROPS BELOW APPROXIMATELY ____ PSI.

Back 79

20 psi

Front 80

DO NOT STATICALLY CHANGE THE BLADE ANGLE OF A PROPELLER WHICH HAS BEEN EXPOSED TO PROLONGED TEMPERATURES OF _______ OR BELOW.

Back 80

0º C

Front 81

NOSE WHEEL TURN LIMIT IS __________ DEGREES WHEN GROSS WEIGHT EXCEEDS 155,000 LBS.

Back 81

20º

Front 82

MAXIMUM ALLOWABLE DC VOLTMETER LIMITS ARE __________.

Back 82

30 VDC

Front 83

WHEN THE STARTER BRINGS THE APU UP TO APPROXIMATELY _______%, A SWITCH OPERATED BY OIL PRESSURE CLOSES TO COMPLETE THE FUEL AND INGNITION CIRCUITS.

Back 83

10%

Front 84

WHAT IS THE MAX SPEED FOR AIR DEFLECTOR DOOR EXTENSION?

Back 84

150 KIAS

Front 85

THE BAT DISCHARGE LIGHT SHOULD EXTINGUISH APPROXIMATELY ____________ SECONDS AFTER MOMENTARY HIGH DC LOADS.

Back 85

30 Seconds

Front 86

AVERAGE FUEL FOR TAXI AND RUN-UP PRIOR TO TAKE OFF IS ________LBS, FOR TAXI WITHOUT RUN-UP THE AVERAGE FUEL REQUIREMENT IS _______ LBS.

Back 86

1,000/500 lbs

Front 87

DO NOT EXCEED ____________ KIAS WHEN ANY FLIGHT CONTROL SURFACE IS PAINTED, UNLESS THE UNDERSIDE HAS BEEN STENCILED WITH, SUBSEQUENT REPAINTING RESTRICTED TO MINOR TOUCHUP UNLESS PERFORMED AT DEPOT LEVEL.

Back 87

250 Knots

Front 88

0-15% FLAPS THE CAUTION LIMITS FOR RUDDER BOOSTER PRESSURE IS _________ PSI TO ________ PSI.

Back 88

1,400 – 1,600 psi

Front 89

THE MAX CROSSWIND RECOMMENDED FOR LANDING IS ________ KNOTS.

Back 89

35 Knots

Front 90

PROPELLER BLADE DEICING AMP LIMITS ___________ TO __________ AMPS.

Back 90

60 – 90 amps

Front 91

WHICH ENGINE ICE DETECTION PROBES ACTIVATE THE ICE DETECTION SYSTEM?

Back 91

2 & 3

Front 92

WHAT IS THE MINIMUM OXYGEN REGULATOR PRESSURE FOR NORMAL USE?

Back 92

50 psi

Front 93

AT _____________ RPM THE 5TH AND 10TH STAGE BLEED AIR VALVES OPEN.

Back 93

Below 94%

Front 94

WITHIN _________ SECONDS THE START VALVE OPEN LIGHT WILL EXTINGUISH, INDICATING THAT THE STARTER VALVE IS CLOSED.

Back 94

15 Seconds

Front 95

MAX REVERSE GIVES REVERSE THRUST WITH ENGINE POWER APPROX _________% OF TAKE OFF POWER.

Back 95

40%

Front 96

THERE ARE __________OVERHEAT DETECTORS SET AT __________ º F IN THE TURBINE SECTION.

Back 96

4 detectors @ 700º F

Front 97

THERE ARE ________ OVERHEAT DETECTORS SET AT __________ º F IN THE NACELLE AND HORSE COLLAR AREA.

Back 97

8 detectors @ 300 º F

Front 98

THE ODS SYSTEM IS BROKEN DOWN INTO ____________ ZONES.

Back 98

11 Zones

Front 99

THE PITCHLOCK ASSEMBLY IS MAINTAINED IN THE ____________________.

Back 99

Barrel Assembly

Front 100

THE LOW PITCH STOP MECHANISM IS MAINTAINED IN THE _________.

Back 100

Dome

Front 101

THE NTS SYSTEM IS LOCKED OUT WHEN THE THROTTLES ARE MOVED BELOW THE ____________ RANGE.

Back 101

Flight Idle

Front 102

THE SYNCHROPHASER ELECTRONIC UNIT PROVIDES CIRCUITS FOR THE FOLLOWING GOVERNING FUNCTION.

Back 102

-THROTTLE ANTICIPATION
-SPEED STABILIZATION
–SYNCHROPHASING

Front 103

THE DUMP PUMPS WILL ALLOW ALL BUT _________ LBS FROM THE OUTBOARD TANKS TO BE DUMPED.

Back 103

1,600 lbs

Front 104

THE DUMP PUMPS WILL ALLOW ALL BUT _____________LBS FROM THE INBOARD TANKS TO BE DUMPED OVERBOARD.

Back 104

1,500 lbs

Front 105

THE FUEL STRAINER BYPASS LIGHT WILL ILLUMINATE AT __________PSID.

Back 105

4 psid

Front 106

THE FUEL LOW PRESSURE LIGHTS WILL ILLUMINATE AT ________PSI.

Back 106

8.5 psi

Front 107

TWO _________VOLT BATTERIES ARE LOCATED IN A FUSELAGE COMPARTMENT FORWARD OF THE CREW ENTRANCE DOOR.

Back 107

24 VDC

Front 108

THERE IS __________GALLONS OF HYDRAULIC FLUID IN THE UTILITY HYDRAULIC SYSTEM RESERVOIR.

Back 108

6.5 Gallons

Front 109

LANDING GEAR WARNING HORN WILL SOUND WHEN___________________.

Back 109

FLAPS 80% OR GREATER WITH LANDING GEAR UP

Front 110

THE FLIGHT STATION AND CARGO COMPARTMENT AIR PACK REGULATORS PROVIDE AT SEA LEVEL ______________ POUNDS PER MINUTE OF AIRFLOW.

Back 110

70 PPM

Front 111

THE NESA WINDOW PANELS DO NOT OPERATE AUTOMATICALLY WHEN EXPOSED TO EXTREME TEMPERATURES BELOW ___________ DEGREES.

Back 111

-45º F

Front 112

THE APU INLET DOOR IS ENERGIZED TO CLOSE AFTER THE SPEED HAS DECREASED TO ___________ % RPM THROUGH AN OIL PRESSURE SWITCH THAT ACTUATES AT APPROX ____________ PSI.

Back 112

18% 20 psi

Front 113

AN OFF FLAG APPEARS IN THE IAS COUNTER WINDOW UNTIL THE AIRCRAFT SPEED EXCEEDS _____________KIAS

Back 113

60 KIAS

Front 114

DO NOT EXCEED ________ KIAS BELOW __________ FEET WITH AN INOP WINDSHIELD ANTI ICING SYSTEM.

Back 114

187 Knots below 10,000 feet

Front 115

NORMAL LANDING WEIGHT FOR THE C-130T IS _________POUNDS.

Back 115

130,000 lbs

Front 116

PROPELLER SPINNER ANTI ICING AND DE ICING LIMITS ARE.

Back 116

65 – 90 amps

Front 117

IF DURING FLIGHT, THE TORQUE, TURBINE INLET TEMPERATURE, AND FUEL FLOW ARE NEAR ZERO AND POWER SECTION OIL PRESSURE IS LOW, HYDRAULIC PRESSURE, AC GENERATOR, RPM AND GEAR BOX OIL PRESSURE ARE NORMAL, WHAT DOES IT INDICATE.

Back 117

IN FLIGHT DECOUPLE

Front 118

DURING AIRSTART, NORMAL LIGHTOFF SHOULD OCCUR BY _________% RPM. WHAT ACTION IS NECESSARY IF LIGHTOFF IS NOT OBTAINED BY _________% ENGINE RPM?

Back 118

30%, 40% Condition Lever Feather

Front 119

THE FIRST STEP IN THE EPCS NO REV LIGHT PROCEDURE IS?

Back 119

PERFORM ENGINE SHUTDOWN PROCEDURE

Front 120

AN ENGINE START SHOULD BE DISCONTINUED, UNDER NORMAL CONDITIONS, IF THE TIME REQUIRED FOR ENGINE TO ACCELERATE TO ON SPEED EXCEEDS _________ SECONDS.

Back 120

60 Seconds

Front 121

THE RECOMMENDED AIRSPEED IS ___________ KNOTS IN SEVERE TURBULENCE / THUNDERSTORM PENETRATION.

Back 121

65 KNOTS ABOVE POWER OFF STALL NOT TO EXCEED 180 KNOTS

Front 122

THE NTS SYSTEM OPERATES WHEN NEGATIVE TORQUE REACHES APPROXIMATELY __________ IN LBS

Back 122

-1,260 in lbs +/- 600

Front 123

WHEN IS THE NTS SYSTEM INOPERATIVE?

Back 123

THROTTLES BELOW FLIGHT IDLE

Front 124

THE CROSSOVER POINT AT WHICH THROTTLE TRAVEL ACTUATES SWITCHES TO GO FORM TEMPERATURE LIMITING TO TEMPERATURE CONTROLLING IS ___________º

Back 124

65º

Front 125

WHAT UNIT PROVIDES AUTOMATIC CONTROL OF ALL FUNCTIONS INVOLVED IN THE ENGINE STARTING CYCLE?

Back 125

Speed Sense Control

Front 126

WING FUEL WEIGHT SHOULD NEVER VARY MORE THAN __________LBS BETWEEN SYMETRICAL TANKS.

Back 126

1,000 lbs

Front 127

WHEN MAKING AN APU BLEED AIR CHECK, THE PRESSURE IS CHECKED FROM __________PSI TO __________ PSI. THE TIME REQUIRED SHOULD NOT BE LESS THAN __________ SECONDS.

Back 127

30 to 15 psi in no less than 16 seconds

Front 128

HOW MANY PORTABLE FIRE EXTINGUISHERS ARE CARRIED IN THE AIRCRAFT?

Back 128

4

Front 129

HOW MANY PRC 149'S ARE LOCATED ON THE AIRCRAFT?

Back 129

5

Front 130

HOW MANY CRASH AXES ARE LOCATED ON THE AIRCRAFT.

Back 130

3

Front 131

WING FUEL WEIGHT SHOULD NEVER VARY MORE THAN _____ TO _____LBS MORE IN AN OUTBOARD TANK THAN AN INBOARD TANK.

Back 131

500 to 1,000 lbs

Front 132

WHEN MAKING AN ENGINE BLEED AIR CHECK, THE PRESSURE IS CHECKED FROM __________PSI TO __________ PSI. THE TIME REQUIRED SHOULD NOT BE LESS THAN __________ SECONDS.

Back 132

65 to 35 psi in no less than 30 seconds

Front 133

DO NOT EXCEED ____ KNOTS WITH NOSEGEAR DEFLECTED 60º.

Back 133

5 Knots

Front 134

FOR CRUISE CONDITIONS, A REDUCED POWER SETTING OF ______°C SHOULD BE USED TO THE MAXIMUM EXTENT POSSIBLE TO PRESERVE

ENGINE LIFE.

Back 134

932º C