Specific Cessna152a

Q Que ue_ 1 What is the Max speed of a Cessna 152A at sea level 2 What is the Cruise speed of a Cessna 152A @75% 3 What is the Endurance of a Cessna 152A @75% and at 8500offt a(standard tank)?@75% 4 Whatpower is the Endurance Cessna 152A andrange at 8500 (long range tank)? 5 What ispower the Max of aft Cessna 152A @ 10,000 ft (standard tank)? 152A @ 10,000 ft 6 What is the Max range of a Cessna (long range tank)? 7 What is the Rate of climb of a Cessna 152A at sea level? 8 What is Service ceiling a Cessna 152A? 9 What is the Takeoff performance: ground roll? 10 What is the Takeoff performance: over 50ft obstacle?

A 108 KNOTS 105 KNOTS 310nm, 3.0hrs. 530nm, 5.2hrs. 365nm, 4.1hrs. 615nm, 6.9hrs.

B 106 KNOTS 108 KNOTS 312nm, 3.2hrs 630nm, 5.2hrs. 370nm, 4hrs. 610nm, 6.5hrs.

C 112 KNOTS 118 KNOTS 306nm, 3.15 hrs. 530nm, 5.1hrs 365nm, 4.2hrs 615nm, 6.8hrs.

D 109 KNOTS 109 KNOTS 310nm, 3.1hrs 520nm, 5.0hrs. 360nm, 4.3hrs 610nm, 6.7hrs.

Ans A A A A A A

715 fpm.

710 fpm

712 fpm.

475 fpm

A

14,700 ft. 725ft. 1340ft.

12,700 ft. 730 ft. 1320ft.

14,000 ft. 710 ft. 1325ft.

13,700 ft 715 ft. 2325ft

A A A

11 12 13 14 15

What is the Landing performance: ground roll? What is the landing performance: over 50ft obstacle? What is the Stall speed: flaps up, power off? What is the Stall speed: flaps down, power off? What is the Max ramp weight?

475ft. 1200ft 48knots 43 knots. 1675 lb

425ft. 1275ft 43 knots 48 knots 1170 lb.

415ft. 1215ft. 44 knots. 46 knots 1670 lb.

445ft. 1234ft 46 knots 44 knots 1175 lb.

A A A A A

16

What is the Max takeoff/landing weight?

1670 lb.

1675 lb.

1170 lb.

544 lb.

A

17 18 19 20 21 22 23 24

What is the Standard empty weight? What is the Max useful load? What is the Total baggage allowance? What is the Wing loading factor? What is the Power loading factor? What is the Total fuel capacity (standard)? What is the Total fuel capacity (long range)? What is the Total oil capacity?

1131 lb. 544 lb. 120 lb. 10.5 lbs/sq.ft 15.5 lbs/hp 26 gal 26 gal 7 quarts

1130 lb. 540 lb. 40lb. 105 lbs/sq.ft. 10.5 lbs/hp. 39 gal 39 gal 8 quarts

25 26 27 28 29 30 31

What is the diameter of the propeller? THE AIRCRAFT COMMONLY CALLED “CESSNA 152A” IS CERTIFIED UNDER FAAISTYPE THE VNE OF CESSNA 152A THE VNO OF CESSNA 152A IS THE VA OF CESSNA 152A IS THE VFE OF CESSNA 152A IS THE WINDOW OPEN SPEED OF CESSNA 152A IS

69 inches 3A19 AS CESSNA MODEL NUMBER 168 KNOTS 122 KNOTS (KCAS) AND 125 106 KNOTS (KCAS) AND 108 87 KNOTS (KCAS) AND KNOTS 14585 KNOTS (KCAS) AND 149 KNOTS (KIAS)

68 inches 19A3 AS CESSNA 186 KNOTS 121 KNOTS (KCAS) AND 160 KNOTS (KCAS) AND 78 KNOTS (KCAS) AND 154 KNOTS (KCAS) AND 194 KNOTS (KIAS)

544 lb. 1131 lb. 60 kg. 15.5 lbs/sq.ft. 10.5 lbs/sq.ft. 13 gal 13 gal 7.5 quarts

1171 lb 500 LB 120 kg. 15 lbs/sq.ft 10 lbs/sq.ft. 18.5 gal. 18.5 gal. 6 quarts

72 inches 71 inches 3A91 AS CESSNA MODEL 3A19 AS CESSNA MODEL NUMBER 152A AND A152AAND 172 KNOTS (KCAS) 182 NUMBER KNOTS (KCAS) 125 KNOTS (KCAS) AND 152 KNOTS (KCAS) AND KNOTS (KIAS) KNOTS (KIAS) 108152 KNOTS (KCAS) AND 180121 KNOTS (KCAS) AND 106 KNOTS (KIAS) 160 KNOTS (KIAS) 85 KNOTS (KCAS) AND 87 58 KNOTS (KCAS) AND 78 KNOTS(KCAS) (KIAS) AND KNOTS(KCAS) (KIAS) AND 149 KNOTS 194 KNOTS 145 KNOTS (KIAS) 154 KNOTS (KIAS)

A A A A A A A A A A A A A A A

32

THE WHITE ARC ON THE ASI OF CESSNA 152A IS

FROM VSO TO VNE

33 THE GREEN ARC ON THE ASI OF CESSNA 152A IS

FROM VSO TO VNE

34 THE YELLOW ARC ON THE ASI OF CESSNA 152A IS

FROM VSO TO VNE

FROM 35 FULL FLAP OPERATING B AND C ARE CORRECT KNOTS TO 85 RANGE KNOTS (KIAS) FROM 40 FROM VS TO MAXIMUM PREVIOUS TWO OPTIONS KNOTS TO 125 STRUCTURAL CRUISING ARE CORRECT KNOTS (KIAS) SPEED

FROM 35 FROM 125 KNOTS TO 172 KNOTS TO 125 KNOTS (KIAS) KNOTS (KIAS) FROM VSO TO FROM 35 FROM 125 KNOTS TO 172 VNE KNOTS TO 125 KNOTS (KIAS) KNOTS (KIAS) AVCO LYCOMING LYCOMING MCCAULEY ACCESSORY AVCO DIVISION

D D

FROM 40 KNOTS TO 125 KNOTS (KIAS)

C

172 KNOTS (KIAS)

D

ACCESSORY DIVISION FROM MCCAULEY

A

35

THE RED LINE ON THE ASI OF CESSNA 152A IS

36

THE NAME OF THE ENGINE MANUFACTURE IS

37

THE ENGINE MODEL NUMBER IS

0235N2C

0-233.3-N2C

0-235-M2C

0-255-N2C

A

38

THE ENGINE BHP IS

180 BHP

108 BHP

233.3 BHP

235 BHP

B

39

THE MAXIMUM ENGINE SPEED FOR ALL OPERATIONS

40

THE STATIC RPM IS CHECKED WITH

41 THE VALUE OF STATIC RPM AT SEA LEVEL UNDER STANDARD CONDITIONS IS

2550 REVOLUTIONS PER MINUTE

2505 2055 REVOLUTIONS PER 5250 REVOLUTIONS PER REVOLUTION MINUTE MINUTE S PER MINUTE

CARBURETOR CARBURETOR CARBURETOR HEAT OFF, CARBURETOR HEAT OFF, HEAT ON, FULL HEAT OFF, FULL THROTTLE , AND FULL THROTTLE , FULL THROTTLE, AND THROTTLE MIXTURE LEAN TO MAX BREAKS UNAPPLIED, AND FULL MIXTURE LEAN TO MAX RPM MIXTURE LEAN TO MAX RPM, AND RPM FULL MIXTURE 2250-2350

2350-2450

2280-2380

2380-2880

A

C

C

42

AMONG THE FOLLOWING, WHICH ENGINE OIL IS USED

43

THE PROPELLER IS

MIL-L-6082 MIL-L-6082 MIL-L-22851 AVIATION AVIATION GRADE AVIATION GRADE STRAIGHT STRAIGHT GRADE MINERAL OIL MIL-L-6082 MINERAL OIL MIL- STRAIGHT AVIATION GRADE L-22851 AVIATION MINERAL OIL ASHLESS DISPERSENT GRADE ASHLESS MIL-L-22815 OIL DISPERSENT OIL AVIATION GRADE ASHLESS DISPERSENT OIL

MIL-L-6082 AVIATION GRADE STRAIGHT MINERAL OIL MIL-L-2851 AVIATION GRADE ASHLESS DISPERSENT OIL

A

MANUFACTURED AS ABOVE BY MC CAULEY AND HAS THE ACCESSORY MAXIMUM DIVISION DIAMETER OF 69”

AS ABOVE AND CAN BE MOVED ONLY AT THE SPEED OF 2550 RPM (MAXIMUM ENGINE SPEED)

C

AS ABOVE AND HAS A MODEL NUMBER 1A103/TCM6958

44

NORMAL AND MAXIMUM OIL TEMPERATURE LIMITS ARE

45 MINIMUM, NORMAL AND MAXIMUM LIMITS FOR OIL PRESSURE ARE 46

WHAT IS THE FUEL QUANTITY LEFT IN THE LEFT TANK WHEN THE FUEL LEVEL INDICATOR FOR THE LEFT TANK IS AT E

47

THE NORMAL OPERATING RANGE FOR THE SUCTION GAUGE IS BETWEEN WHAT STATIONS AREA IS BAGGAGE AREA 1 AND BAGGAGE AREA 2

48

49

AT WHICH SPEED ARE CHANDELLES DONE

100º-245º F AND 255º F RESPECTIVELY

200º-245º F AND 255º F RESPECTIVEL Y

115º-245º F AND 245º F RESPECTIVELY

100º-245º F AND 245º F RESPECTIVELY

D

2.5 PSI, 6.0-9.0 PSI, 11.5 PSI

25 PSI, 60-90 PSI, 115 PSI

25 PSI, 60-190 PSI, 245 PSI

125 PSI, 160-190 PSI, 245 PSI

B

1.5 GALLONS OF UNUSABLE FUEL

.75 GALLONS FOR STANDARD TANKS AND .95 GALLONS FOR LONGRANGE TANKS

B

4.5 TO 5.6 INCHES OF MERCURY STATION 50-74 AND STATION 74-92

C

130 KIAS

A

.75 GALLONS OF .75 GALLONS USABLE FUEL OF UNUSABLE FUEL

4.4 TO 5.5 INCHES 5.5 TO 4.5 4.5 TO 5.4 INCHES OF HG OF HG INCHES OF HG 52-74 STATION 50-76 STATION STATION 50-76 AND AND STATION 67- AND STATION STATION 76-94 94 63-92 105 KIAS

115 KIAS

108 KIAS

C

50 51

WHAT DOES THE ORIGINAL AIRWORTHINESS CERTIFICATE OF THE CESSNA 152A STATE MAXIMUM GLIDE SPEED, AND WHICH OF THE FOLLOWINGTAKE PLACE AT 60 KNOTS

52

WHAT IS THE MANEUVERING SPEED AT ALL WEIGHTS

53

ENGINE FAILURE DURING TAKE OFF ROLL, THE FIRST THREE PRECAUTIONARY STEPS FOR X ARE

54

DAY-NIGHT

VFR-IFK

DAY-NIGHT-VFR-IFR

DAY-NIGHT-TRR-YRR

C

PRECAUTIONARY LANDING WITH ENGINE POWER

LANDING WITHOUT ENGINE POWER FLAPS UP

LANDING WITHOUT ENGINE POWER FLAPS DOWN

NONE OF THE ABOVE

C

108 KIAS

106 KCAS

BOTH 1 AND 2 ARE CORRECT

ALL OF THE ABOVE ARE WRONG

C

BRAKES APPLY, THROTTLE BRAKES APPLY, THROTTLE IDLE, BRAKES THROTTLE IDLE, IDLE, BRAKES THROTTLE IDLE, APPLY, WING FLAPS WING FLAPS APPLY, MIXTURE IDLE CUT OFF RETRACT RETRACT IGNITION SWITCH OFF

THE CORRECT SEQUENCE OF ACTIONS FOR IGNITION SWITCHMASTER ENGINE FAILURE IMMEDIATELY AFTER TAKE OFF; OFF SWITCH-OFF ARE MAINTAIN AIRSPEED 60 KNOTS, MIXTUREIDLE CUT OFF AND

FUEL SHUT OFF VALVEOFF

WING FLAPS-AS REQUIRED

D

C

55

ENGINE FAILURE DURING FLIGHT IS THE RESTART PROCEDURE FOR X AIRSPEED 60 KIAS

56 EMERGENCY LANDING WITHOUT ENGINE POWER IS THE FIRST STEP FOR

57

WHAT IS THE AIRSPEED DURING EMERGENCY LANDING WITHOUT ENGINE POWER

PRIMER IN AND CARBURETOR CARBURETOR HEAT ON, LOCKED, FUEL HEAT ON, PRIMER IN AND LOCKED, SHUTOFF VALVE FUEL FUEL SHUTOFF VALVE OFF, MIXTURE SHUTOFF OFF RICH VALVE OFF, MIXTURE RICH SEATS, SEAT BELTS, SHOULDER HARNESSESSECURE 65 KIAS (FLAPS UP)

MIXTURE-IDLE FUEL SHUTOFF VALVEOFF

55 KIAS (FLAPS DOWN)

60 KIAS (FLAPS UP)

58 WHAT IS THE AIRSPEED AND FLAPS SETTING FOR AIRSPEED 60 AIRSPEED 60 AIRSPEED 55 KIAS, WING A PRECAUTIONARY LANDING WITH ENGINE KIAS, WING FLAPS KIAS, WING FLAPS 20º POWER 20º FLAPS 30º

NONE OF THE ABOVE

D

WING FLAPS-AS REQUIRED

A

BOTH 2 AND 3 ARE CORRECT

A

NONE OF THE ABOVE

A

59

PRECAUTIONARY LANDING WITH ENGINE POWER; SELECT THE INCORRECT STEP FOR A

MASTER SWITCH OFF

IGNITION RADIO AND ELECTRICAL SWITCH OFF SWITCHES OFF

FUEL SHUTOFF VALVE OFF

D

60

DURING DITCHING, WHAT SHOULD THE RATE OF DESCENT SHOULD BE

200 FT/MIN

300 FT/MIN

400 FT/MIN

150 FT/MIN

B

61

DURING AN ENGINE FIRE ON GROUND WITH THE ENGINE RUNNING WHAT SHOULD THE RPM BE

1200

1700

2280

2250

B

62

WHAT SHOULD THE INITIAL ACTION BE FOR A ENGINE FIRE ON GROUND WITH THE ENGINE FAILING TO RESTART

CONTINUE CRANKING

THROTTLEFULL OPEN

MIXTURE-IDLE CUT OFF

ALL OF THE ABOVE

B

63

WHAT SPEED SHOULD BE MAINTAINED FOR AN ENGINE FIRE IN FLIGHT

AIRSPEED 85 KIAS

NONE OF THE ABOVE

C

64

WHAT SHOULD THE FLAPS BE WHILE LANDING WITH A FLAT MAIN TIRE

UP

20º

30º

AS DESIRED

D

65

WHAT SHOULD THE FIRST STEP BE FOR A CABIN FIRE

FIRE EXTINGUISHERACTIVATE

VENTS CABIN AIR-CLOSED

MASTER SWITCH-ON

NONE OF THE ABOVE

D

AIRSPEED 65 KIAS AIRSPEED 75 KIAS

66

WHAT MANOEUVRE SHOULD ONE PERFORM DURING WING FIRE

67 STATE WHETHER TRUE OR FALSE: DURING WING FIRE, LAND WITH FLAPS DOWN

LOOP

SIDE SLIP

FACE THE WIND

ROLL

B

TRUE

FALSE

C

D

B

NONE OF THE ABOVE

C

55 TO 65 KIAS

A

68

WHAT SHOULD THE FIRST STEP BE DURING AN INADVERTENT ICING CONDITION ENCOUNTER

TURN BACK OR CHANGE ALTITUDE

PULL CABIN PITOT HEAT SWITCH ON HEAT CONTROL 60FULL TO 70OUT KIAS 70 TO 80 KIAS

69

WHAT SHOULD THE AIRSPEED BE DURING A LANDING APPROACH IN AN ICING CONDITION

65 TO 75 KIAS

70

WHAT SHOULD THE FLAPS BE WHILE LANDING WITH A FLAP MAIN TIRE

UP

20º

30º

AS DESIRED

D

71

WHAT SHOULD THE FIRST STEP BE IF THE AMMETER SHOWS AN EXCESSIVE RATE OF CHANGE

ALTERNATOR CIRCUIT BREAKER PULL

ALTERNATOROFF

NONESSENTIAL ELECTRICAL EQUIPMENT-OFF

NONE OF THE ABOVE

B

72 WHEN AN AMMETER SHOWS EXCESSIVE RATE OF ALTERNATOR-OFF ALTERNATOR CHANGE , CHOOSE THE INCORRECT CIRCUIT ALTERNATIVE BREAKERPUSH ALTERNATOR MASTER CIRCUIT SWITCH-OFF BREAKER-CHECK IN

FLIGHT-TERMINATE AS SOON AS PRACTICAL

NON ESSENTIAL ELECTRICAL EQUIPMENTOFF

B

ALTERNATOR-OFF

ALTERNATOR-OFF

D

73

WHAT SHOULD THE FIRST STEP BE IF THE LOW VOLTAGE LIGHT ILLUMINATES DURING FLIGHT

74

WHAT SHOULD THE AIRSPEED BE WHEN LANDING WITHOUT ELEVATOR CONTROL

50 KIAS

55 KIAS

60 KIAS

65 KIAS

B

75

WHAT DEGREE OF FLAPS ARE USED WHEN LANDING WITHOUT ELEVATOR CONTROL

0º

10º

20º

30º

C

76

WHICH INSTRUMENT SHOULD THE PILOT RELY WHEN THE VACUUM SYSTEMFAILS IN CLOUDS

ATTITUDE INDICATOR

NONE OF THE ABOVE

B

77

WHILE EXECUTING A 180º TURN IN CLOUDS WHEN THERE IS A VACUUM SYSTEM FAILURE, HOW LONG SHOULD

60 SECONDS

120 SECONDS

A

TURN DIRECTIONAL INDICATOR COORDINATO R 30 SECONDS

90 SECONDS

78

WHAT IS THE RATE OF DESCENT DURING AN EMERGENCY DESCENT THROUGH CLOUDS

300 TO 500 FT/MIN

500 TO 800 FT/MIN

500 TO 700 FT/MIN

550 TO 750 FT/MIN

B

79

WHAT IS THE DESCENT AIRSPEED DURING AN EMERGENCY DESCENT THROUGH CLOUDS

55 KIAS

60 KIAS

65 KIAS

70 KIAS

D

80

WHAT IS THE FIRST STEP DURING AN EMERGENCY DESCENT THROUGH CLOUDS

FULL CARBURETOR HEAT

FULL RICH MIXTURE

KEEP HANDS OFF CONTROL WHEEL

NONE OF THE ABOVE

B

81

WHAT IS THE FIRST STEP DURING RECOVERY FROM A SPIRAL DIVE

THROTTLE OPEN

NONE OF THE ABOVE

D

82

WHAT IS THE AIRSPEED WHILE RECOVERING FROM A SPIRAL DIVE

ADJUST TRIMMER USE TO NORMAL OPPOSITE FLIGHT AILERON AND RUDDER 55 KIAS 60 KIAS

65 KIAS

70 KIAS

D

83

FLIGHT INTO ICING CONDITION IS

NOT PERMITTED

PROHIBITED

NOT APPROVED

PERMITTED

B

84

WHAT IS THE FIRST STEP IN A SPIN RECOVERY

THROTTLE IDLE

AILERONS NEUTRAL

FULL OPPOSITE RUDDER

NONE OF THE ABOVE

B

85

CARBURETOR ICING

SPARK PLUG FOULING

MAGNETO MALFUNCTION

NONE OF THE ABOVE

B

86 WHAT IS THE PROBABLE CAUSE FOR A GRADUAL LOSS OF RPM AND EVENTUAL ENGINE ROUGHNESS

CARBURETOR ICING

SPARK PLUG FOULING

MAGNETO MALFUNCTION

NONE OF THE ABOVE

A

87

WHAT IS THE PROBABLE CAUSE FOR A SUDDEN ENGINE ROUGHNESS OF MISFIRING

CARBURETOR ICING

SPARK PLUG FOULING

MAGNETO MALFUNCTION

NONE OF THE ABOVE

C

88

WHAT IS THE PROBABLE CAUSE FOR A DROP IN OIL PRESSURE IS ACCOMPANIED BY NORMAL OIL TEMPERATURE

OIL PRESSURE GAGE FAILURE

OIL RELIEF VALVE FAILURE

LEAK IN THE LINE TO THE GAGE

ALL OF THE ABOVE

D

89

WHAT IS THE PROBABLE CAUSE WHEN A TOTAL A VACUUM AN ENGINE LOSS IN OIL PRESSURE IS ACCOMPANIED BY A SYSTEM FAILURE FAILURE RISE IN OIL TEMPERATURE WHAT SHOULD HAPPEN TO THE BATTERY IF THE OVERHEAT EVAPORATE CHARGING RATE WERE TO REMAIN IN THE THE EXCESS OF THE RATE OF CHARGE ELECTROLYT E

LOSS OF HYDRAULIC PRESSURE

LOSS OF RPM

B

MELT

BOTH 1 AND 2

D

90

WHAT IS THE PROBABLE CAUSE FOR A SLIGHT ENGINE ROUGHNESS IN FLIGHT

91

WHAT IS THE FIRST STEP DURING A BAIL OUT

RELEASE SEAT BELT AND SHOULDER HARNESS

PULL EMERGENCY D-RING

UNLATCH DOOR

NONE OF THE ABOVE

C

92

WHAT IS THE FIRST STEP WHEN WINDSHIELD DAMAGE HAS OCCURRED

OPEN THE SIDE WINDOWS

REDUCE AIRSPEED

OPEN DOOR

NONE OF THE ABOVE

A

93

WHAT IS THE INITIAL INDICATION OF AN ELECTRICAL FIRE

ODOR OF BURNING INSULATION

INCREASE IN OIL TEMPERATURE

C

94

WHAT AIRCRAFT ATTITUDE SHOULD BE USED FOR LANDING IN ICING CONDITIONS

LEVEL ATTITUDE

NOSE DOWN ATTITUDE

TAIL DOWN ATTITUDE

NONE OF THE ABOVE

A

95

WHAT DOES SECTION 3 DEALS WITH

NORMAL PROCEDURES

PERFORMAN CE

LIMITATIONS

NONE OF THE ABOVE

D

2

3

4

1

B

96 IN TEMPERATURES NEAR FREEZING - UPTO HOW MANY STRIKES OF THE PRIMER MAYBE NECESSARY

ENGINE FAILURE LOSS IN RPM

97

RPM DROP SHOULD NOT EXCEED ---- RPM ON EITHER MAGNETO OR SHOW GREATER THAN --RPM DIFFERENTIAL BETWEEN MAGNETOS

125,50

50,125

125,100

125,75

A

DURING AN ALTERNATOR CHECK IT IS PREFERABLE THAT—LIGHTS BE USED INSTEAD OF --- LIGHTS 99 WHAT IS THE RPM RANGE WITH CARB, HEAT OFF AND MIXTURE LEANED TO MAXIMUM RPM IN POWER CHECK BEFORE T/O

TAXI, LANDING

LANDING, TAXI

STROBE, TAXI

READING, LANDING

A

2380 TO 2550

2200 TO 2550

2280 TO 2380

2180 TO 2280

C

100 FULL THROTTLE RUN UPS OVER LOOSE GRAVEL IS ESPECIALLY HARMFUL TO WHICH OF THE FOLLOWING

CARBURETOR

WINGS

PROPELLER

AIR COLLER

C

101 USING 10 DEG WING FLAPS REDUCES THE TOTAL DISTANCE OVER AN OBSTACLE BY APPROX , HOW MUCH PERCENT

15

20

5

10

D

102 ON A SHORT FIELD WITH WHAT DEG WING FLAPS AND AN OBSTACLE CLEARANCE SPEED OF HOW MUCH KIAS SHOULD BE USED

10º AND 55 KIAS

10º AND 54 KIAS

20º AND 60 KIAS

20º AND 54 KIAS

B

98

103

FOR THE BEST COMBINATION OF PERFORMANCE, VISIBILITY AND ENGINE COOLING, SPEEDS SHOULD BE HOW MANY KNOTS HIGHER THAN THE BEST RATE OF CLIMB

5 TO 12 KNOTS

10 TO 12 KNOTS

10 TO 15 KNOTS

5 TO 10 KNOTS

D

104 LEANING IS NOT RECOMMENDED UNTIL A TOTAL OF THE FOLLOWING HOURS HAS ACCUMULATED

25 HRS

100 HRS

50 HRS

75 HRS

C

105 IN ORDER TO ENSURE PROPER SETTING OF THE PISTON RINGS, THE FOLLOWING SHOULD BE DONE

CRUISE AT 75% POWER

AS IN (A) UNTIL A TOTAL OF 50 HRS HAS ACCUMALATE D

AS IN (A) AND UNTIL A TOTAL OF 25 HRS HAS ACCUMALATED

AS IN © AND IT IS APPLICABLE TO NEW ENGINES AS WELL

B

106 TO ACHIEVE THE RECOMMENDED LEAN MIX FUEL CONSUMPTION FIGURES THE MIX SHOULD BE LEANED UNTIL THE ENGINE RPM PEAKS AND DROPS --- TO --- RPM

50-75 RPM

15-25 RPM

25-50 RPM

10-25 RPM

D

107 THE STALL WARNING HORN PRODUCES A SIGNAL --- TO --- KNOTS BEFORE ACTUAL STALL IS REACHED

05-10 KNOTS

10-15 KNOTS

0-05 KNOTS

15-20 KNOTS

A

108

FOR A SHORT FIELD LANDING IN SMOOTH AIR MAKES AN APPROACH AT

64 KNOTS AND 20 DEGREES

60 KNOTS AND 20 DEGREES

54 KNOTS AND 30 DEGREES

55 KNOTS AND 30 DEGREES

C

109

IN A BLAKED LANDING WING FLAP SETTING SHOULD BE REDUCED

10 DEGREES

20 DEGREES

30 DEGREES

NONE OF THE ABOVE

B

-18ºC AND -7ºC

0ºC AND 20ºC

-18ºF AND -7ºF

BOTH B AND C ARE CORRECT

A

110 PREHEAT IS GENERALY REQ. WITH OAT BELOW --DEG. C AND RECOMMENDED IN TEMP BELOW --DEG C 111

THE CERTIFIED NOISE LEVEL FOR 152 A AT 1670 LB. IS

63.3 DB

63.6 DB

66.3 DB

66.6 DB

C

112

A PROLONGED STALL THAT RESULTS IN A NOSE DOWN RAPID ROTATION OF THE A/C FOLLOWING A HELICAL PATH

IMMELMANN

SPIRAL DIVE

CUBAN EIGHT

NONE OF THE ABOVE

D

113

FOLLOWING STEPS SHOULD BE DONE TO RECOVER FROM A SPIN

114

A 360-DEG TURN EXECUTED IN A VERTICAL PLANE 115 A COORDINATED MANEUVER IN WHICH THE A/C IS ROLLED 360 DEG ALONG THE LONGITUDINAL AXIS OF THE A/C

AILERONS NEUTRAL

APPLY AND HOLD RUDDER IN THE DIRECTION OF ROTATION

THROTTLE IDLE

AS IN A AND C

D

BARREL ROLL

LOOP

SNAP ROLL

AILERON ROLL

B

BARREL ROLL

LOOP

SNAP ROLL

AILERON ROLL

A

116

ENTRY SPEED FOR THE BARREL ROLL IS

105 KNOTS

100 KNOTS

115 KNOTS

130 KNOTS

C

117

A COORDINATED MANEUVER IN WHICH A/C IS ROLLED 360 DEG ALONG THE LONGITUDINAL AXIS BUT IS TIGHTER THAN THE BARREL ROLL

CUBAN EIGHT

LOOP

SNAP ROLL

AILERON ROLL

D

118

AN ACCELERATED STALL MANEUVER IN WHICH YAW FROM FULL RUDDER DEFLECTION PRODUCES A ROLL

BARREL ROLL

LOOP

SNAP ROLL

AILERON ROLL

C

119

ENTRY TO THE SNAP ROLL IS DONE AT --- KIAS

105 KNOTS

100 KNOTS

80 KNOTS

130 KNOTS

C

CUBAN EIGHT

LOOP

SNAP ROLL

AILERON ROLL

A

4.0 TO 4.5 AT G 130 KNOTS

3.5 TO 4.0 AT G 130 KNOTS

D

120 THE______________ MANEUVER CONSISTING OF APPROX. ¾ OF THE NORMAL LOOP AND A DIVING ½ ROLL IN THE OPPOSITE DIRECTION BY ANOTHER ¾ OF A LOOP AND ½ ROLL 121

CUBAN 8 IS DONE AT

4.0 TO 4.5 G AT 115 3.5 TO 4.0 G KNOTS AT 115 KNOTS

122 THE COMBINATION OF A ½ LOOP FOLLOWING BY ½ ROLL

IMMELMANN

LOOP

CUBAN EIGHT

VERTICAL REVERSEMENT

A

123 THE MANEUVER, WHICH IS ½ SNAP ROLL FROM A STEEP TURN IN 1 DIRECTION TO STEEP TURN IN OPPOSITION DIRECTION

IMMELMANN

LOOP

CUBAN EIGHT

VERTICAL REVERSEMENT

D

124

THE ENTRY SPEED FOR A VERTICAL REVERSEMENT IS

125

MINIMUM TURNING RADIUS OF THE AIRPLANE DURING TAXI USING DIFFERENTIAL BRAKING AND NOSE WHEEL STEERING IS 126 WING FLAP SYSTEM IS

60-70º AT 80 KNOTS

60-70º AT 110 KNOTS

50-60º AT 105 KNOTS

50-60º AT 100 KNOTS

A

25 FT APPROX

26 FT APPROX

25 FT 1 INCH APPROX

26 FT 1 INCH APPROX

C

DOUBLE SLOT WITH MAX. DEF. OF 30’

SINGLE SLOT WITH MAX. DEF. OF 10’

DOUBLE SLOT WITH MAX. DEF. OF 10’

SINGLE SLOT WITH MAX. DEF. OF 30’

D

127

WHEEL BASE LENGTH IS

55”

56”

57”

58”

D

128

24’ 1”

33’ 4”

32’ 8 ½”

32’ 7 ½”

B

129

WING SPAN WITH CONICAL CAMBER WING TIP AND STROBE LIGHTS IS WING AREA IS

159 ½ SQ. FT

156 ½ SQ. FT

158 ¼ SQ. FT

156 ¼ SQ. FT

A

130

AVCO. LYCOMING 0-235-N2C IS

235 CU. IN DISPLACEMENT WITH 108 BHP AT 2550 RPM

233 CU. IN DISPLACEMENT WITH 108 BHP AT 2550 RPM

A

233.3 CU. IN 233.5 CU. IN DISPLACEMENT DISPLACEME WITH 108 BHP AT NT WITH 108 2550 RPM BHP AT 2550 RPM

131

FUEL CAPACITY IN PORT WING TANK

STANDARD TANKS 13 GALL. AND 0.75 UNUSABLE

132

OIL CAPACITY

MAX. 7 QUARTS AND MIN 6 QUARTS

133

TRAKE OFF PERFORMANCE WITH 50 FT. OBSTACLE

1200 FT

134 MIN. RANGE WITH 75% POWER AT 8500 FT. WITH STANDART TANKS

STANDARD TANKS 26 GALL. AND 1.75 UNUSABLE

STANDARD TANKS 19.5 GALL. AND 0.75 UNUSABLE

STANDARD TANKS 19.5 GALL. AND 1.75 UNUSABLE

MAX. 7 MAX. 6 QUARTS AND MIN MAX. 6 QUARTS AND MIN QUARTS AND 4 QUARTS 5 QUARTS MIN 4 QUARTS 1260 FT

310 NM IN 3 HRS 300 NM IN 3.10 OF TIME HRS OF TIME

A

B

1360 FT

1340 FT

D

615 NM IN 4.1 HRS OF TIME

615 NM IN 6.9 HRS OF TIME

A

135

STANDARD WEIGHT OF EMPTY A/C

1670 LBS

1675 LBS

1131 LBS

544 LBS

C

136

LANDING PERFORMANCE MIN. GROUND ROLL

725 FT

1340 FT

475 FT

1200 FT

C

137

TOTAL UN USABLE FUEL AFTER A LONG CROSS COUNTRY OF TOTAL FLYING TIME OF 3 HRS IS

0.75 GALL

0.75 LITRES

1.5 LITERS

1.5 GALLONS

D

138

THE LANDING GEAR OF A/C IS

TRICYCLE TYPE WITH STEERABLE NOSE WHEEL

TWO MAIN WHEELS HAVING T.P. OF 21 PSI

SHOCK ABSORPTION BY TUBULAR SPRING STEEL MAIN LANDING GEAR

ALL THE ABOVE

D

139

THE WING FLAP SYSTEM CIRCUIT PROTECTED BY

5 AMPERE CKT. BREAKER

10 AMPERE CKT. BREAKER

15 AMPERE CKT. BREAKER

NONE OF THE ABOVE

C

140

THE GROUND ADJUSTABLE TRIM TAB IS AT

AFT OF MAIN LANDING GEAR

AFT OF ELEVATOR

AFT OF AILERON

AFT OF RUDDER BASE

D

141

THE ALTERNATOR CONTROL UNIT PROTRCTED BY OVER VOLTAGE SENSOR WHICH TRIPS OUT THE CIRCUIT AT

IF CHARGE VOLTAGE REACHES 30 VOLTS (APPROX.)

IF CHARGE VOLTAGE REACHES 12 VOLTS (APPROX.)

A

142

IF TOTAL LOSS OF OIL PRESSURE IS ACCOMPANIED BY A RISE IN OIL TEMP

ENGINE IS NEW TO SET

ENGINE FAILURE

D

IF CHARGE IF CHARGE VOLTAGE VOLTAGE REACHES 31.5 REACHES 24 VOLTS (APPROX.) VOLTS (APPROX.) ENGINE ENGINE IS PRODUCING MAX. SET AT BEST POWER AT LEVEL MIXTURE RATIO

143

NOSE WHEEL IS TURNED BY A SPRING-LOADED STEERING BUNGEE

AN ARC OF APPROX. 78.0* EACH SIDE OF CENTERLINE

AN ARC OF AN ARC OF APPROX. 8.5* AN ARC OF APPROX. 8.5* APPROX. 7.7* EACH SIDE OF EACH SIDE OF CENTERLINE CENTERLINE

C

144

MAJOR ENGINE ACCESSORIES ARE

VOR, ADF AND VHF TRANSCEIVER

FIRST AID BOX AND FIRE EXTINGUISHE R DGI, DOWN DRAFT, LOSS OF RPM R - L - START RIGHT FUEL HYDRAULICAL 24 VOLTS SPLIT 10.5 CAUTION! DAY - NIGHT AFT 36.0* AT MAX SAE 40 VNO ARM 3A 19 AS

145 MAJOR ENGINE INSTRUMENTS ARE 146 THE A/C ENGINE IS EQUIPPED WITH _______ 147 USED OF FULL CARBURETOR HEAT AT FULL 148 IGNITIONS AND STARTER OPERATION IS 149 THE PRIME DRAWS ITS FUEL FROM 150 FUEL QUANTITY METER IS OF 151 AIRPLANE IS EQUIPPED WITH 152 THE MASTER SWITCH IS A TYPE 153 WING LOADING OF A/C IS 154 ON CONTROL LOCK ITS PRINTED 155 THE A/C IS CERTIFIED FOR FOLLOWING FLIGHT 156 CENTER OF GRAVITY RANGE ( IF FRONT FACE OF 157 PICK OUT THE ODD ONE 158 USE MULTI- VISCOSITY OIL AT ALL 159 WHAT IS THE SYMBOL FOR MINIMUM STEADY 160 THE POINT AT WHICH AN A/C OR EQUIPMENT , 161 CESSNA IS CERTIFIED UNDER FAA TYPE

ASI, VSI AND UP-DRAFT, FLOAT EXTRA RPM OFF- R - L START LEFT FUEL TANKS ELECTRICALLY 28 VOLTS DC SPLIT - ROCKER, 15.5 LBS./SQFT AT CAUTION! DAY - NIGHT - VFR AFT 36.5* AT ALL MAX RAMP SAE 30 VA C.G. ARM 3A 15 AS CESSNA

FLAP MOTOR AND TRIM TAB

STARTER, ALTERNATOR, OIL COOLER

D

TACHO METER, OIL TEMP DIRECT FUEL INJECTION RPM REMAINS 0FF - START - R - L FUEL STRAINER THERMO SENSOR TYPE A BELT DRIVEN 60 AMP BOTH HALF IS BAT AND 10.5 LBS./H.P AT SEA CAUTION! REMOVE DAY - NIGHT - IFR ONLY AFT 35.5* AT ALL MAX LANDING WEIGHT SAE 50 VS STATION 3A 20 AS CESSNA MODEL

AMMETER AND LOW UP-DRAFT, FLOAT TYPE THE VALUE MAY VARY UP OFF - R - L - BOTH - START FUEL STRAINER AND MECHANICALLY ALL THE ABOVE NONE OF THE ABOVE 15.5 LBS./H.P AT SEA CAUTION! REMOVE DAWN - DUSK - VFR - IFR AFT 35.0* AT ALL MAX USEFUL LOAD 1131 SAE 60 VSO CENTER OF GRAVITY 3A 25 AS CESSNA MODEL

C A B D C A D A B C A A D C D D B

162 163 164 165 166 167 168 169 170 171 172 173 174 175 176 177 178 179 180 181 182 183 184 185 186 187 188 189 190 191

NEVER EXCEED SPEED IN ANY OPERATIONS MAX. SPEED WITH FLAPS DOWN (EXTENDED) YELLOW ARC SPEED OPERATION MUST BE SUCTION GAUGE READS IN WHITE ARC OF AIS STARTS FROM MAXIMUM OIL TEMPERATURE RANGE IS OIL GRADE SPECIFICATION IS IF CARBURETOR HEAT OFF AND MIXTURE INVERT FLIGHT IS PROHIBITED THE STRUCTURE MEET OR EXCEEDS DESIGN USE OF FLAP IS RESTRICTED IN AEROBATICS IN CASE OF ENGINE FAILURE DURING TAKE OFF THE AMMETER INDICATES THE AMOUNT OF DURING LOW RPM CONDITION ELECTRICAL CIRCUITS IN CESSNA 152 A THE STALL WARNING SYSTEM OF THIS AIRCRAFT LANDING WITHOUT ELEVATOR CONTROL DURING START ON GROUND THE FIRE OCCURS FORCED LANDING WITH ENGINE POWER, ENGINE FAILURE DURING TAKE OFF ROLL, FIRST ENGINE FIRE DURING FLIGHT WHAT TOPICS DOES SECTION 8 COVER WHAT INFORMATION IS DISPLAYED ON THE WHERE IS THE IDENTIFICATION PLATE LOCATED WHAT IS TO BE DISPLAYED ON THE A/C AT ALL WHAT IS TO BE CARRIED ON A/C AT ALL TIMES WHAT CAN BE AVAILABLE ON REQUEST WHILE TOWING , WHAT ANGLE OF NOSE GEAR WHAT SHOULD BE REMOVED FROM THE A /C WITH RESPECT TO THE WIND DIRECTION , HOW

172 KTS UNDER 85 KTS 125-172 KIAS 4.5-5.4 IN HG IN VSO - VFE 118º C MIL-L-6082 STATIC RPM DUE TO HIGH FLAP UP= -3 G TO 0-10 DEGREE THROTTLE IS ALTERNATOR TO LOW VOLTAGE PUSH TO PNEUMATIC TYPE TRIM FOR CONTINUE 60 - 70 KTS APPLY BRAKES MIXTURE IDLE HANDLING AND OWNERS NAME OUTSIDE LEFT FUEL PILOT’S CERTIFICATE OF 30° EITHER SIDE FLIGHT RELEASE TAIL INTO THE

125 KTS 87 KTS 125-172 KIAS 4.5-5.4 IN HG VSO - VS 108º C MIL-L-6958 STATIC RPM DUE TO FIXED FLAP UP= -3 G 10-20 DEGREE FLAPS ARE BATTERY TO AMMETER PULL - OFF ELECTRIC TRIM FOR SHUT DOWN 70 - 80 KTS CUT FUEL FLOW EMERGENCIE SERIAL NO. ON FIREWALL FLIGHT PLAN OPERATIONS AIRPLANE 45° EITHER RUDDER IRRESPECTIV

149 KTS UNDER ISA 108 KTS 40-125 KIAS ONLY IN NIL 4.5-5.4 IN HG IN NORMAL VA - VSO 180º C MIL-L-22851 ASHLESS STATIC RPM RANGE IT IS NOT PROHIBITED FLAP DOWN= -3 G TO 20-30 DEGREE OTHER BRAKES ARE REQUIRED IF ALTERNATOR IS LOW VOLTAGE LIGHT BOTH BOTH THIS SYSTEM TRIM AIRCRAFT BY CONTINUE CRANKING60 - 55 KTS CUT MIXTURE THROTTLE TO IDLE GENERAL MANUFACTURERS NAME CABIN FLOOR BELOW ADDRESS OF QUALITY ASSURANCE CERTIFICATE OF 60° EITHER SIDE OF PITOT COVER HEAD INTO THE WIND

168 KTS UNDER ISA 125 KTS 40-125 KIAS ONLY IN 4.5-5.4 IN HG IN NORMAL DOES NOT HAVE A LIMIT 80º C MIL-L-22581 ASHLESS STATIC RPM RANGE 1900DUE TO WET SUMP OF OIL FLAP DOWN= -3 G TO +3.5 NONE OF THE ABOVE AS MIXTURE IS TO BE RICH ALL ABOVE OPTIONS ARE LOW VACUUM LIGHT WITH NONE OF THE ABOVE NONE OF THE ABOVE AIRCRAFT CAN NOT BE CONTINUE CRANKING 50 - 55 KTS FUEL SHUT OFF VALVEOPEN WINDOWS AND LIMITATIONS NONE OF THE ABOVE ON INSTRUMENT PANEL AIRWORTHINESS NONE OF THE ABOVE WEIGHT SCHEDULE 90° EITHER SIDE OF CERTIFICATE OF BROADSIDE FACING WIND

A A B C A A C A C B D C D D C A B C C B A A B C D A B A B C

192 193 194 195 196 197 198 199 200 201 202 203 204 205 206 207 208 209 210 211 212 213 214 215 216 217 218 219 220 221

WHILE PUSHING THE TAIL CONE , HOW CAN BY APPLYING WHAT LEVELING IS ACCOMPLISHED BY PLACING HORIZONTAL LONGITUDINAL LEVELING CAN BE 94.63 & 132.94 FOR HOW MANY DAYS CAN THE A/C BE STORED 30 DAYS ON EVERY 7TH DAY OF STORAGE HOW MANY 10 REVOLUTIONS WHAT ARE THE OIL SPECIFICATIONS MIL-L-6083 ,MIL-LTHE A/C SHOULD NOT BE OPERATED WITH LESS 7 FOR NORMAL FLIGHTS OF LESS THAN 3 HRS. 5 FOR EXTENDED FLIGHTS OF MORE THAN 3 HRS. 5 WHEN SHOULD THE OIL CHANGE BE MADE EVERY 100 AFTER WHAT TIME DURATION SHOULD THE OIL 3 MONTHS WHAT ARE THE APPROVED FUEL GRADES 100LL AND ATF ___ & ___ CAN BE ADDED TO FUEL SUPPLY IN FUEL SHOULD WHAT IS THE CAPACITY OF STANDARD FUEL 15 GALLONS WHAT IS THE CAPACITY OF LONG RANGE TANKS 25 GALLONS WHAT IS THE ANTI ICING FLUID CALLED MIL-F-5566 WITH WHAT APPARATUS CAN THE INCLINOMETER WHAT IS THE NOSE WHEEL TIRE PRESSURE 20 PSI MAIN WHEEL TIRE PRESSURE 25 PSI WHAT IS THE BRAKE FLUID GRADE W-120 OIL AND GREASE STAINS CAN BE REMOVED BY KEROSENE WHAT WILL REMOVE ICE ACCUMULATION ISOPROPYL WHAT ARE THE REPLACEABLE DOOR POST MAP S2243-1 & S2243-2 WHAT TOPIC DOES SECTION 9 COVER LIMITATIONS WHAT IS THE TYPE OF CLOCK INSTALLED IN THE TITAN QUARTZ HOW IS THE INTENSITY OF THE BACKLIGHT OF PUSH PULL WHAT IS DISPLAYED WHEN OPERATING IN THE TIME OF DAY IN AT WHAT INTERVALS DOES THE COLON BLINK 15 SECS IN HOW MUCH TIME DOES THE CLOCK MODE 1 SEC USING WHICH BUTTON ON THE AIRCRAFT CLOCK RIGHT HAND

BY STEERING LONGITUDINA 95.63 & 133.94 60 DAYS 25 MIL-L-6082 4 6 6 NEVER 6 MONTHS ATF AND JP5 MOGAS 13 GALLONS 19.5 GALLONS EGME CHAMOIS 21.5 PSI 21 PSI W-100 STODDARD KEROSENE S2242-1 & SUPPLEMENT ROLEX RADIO LT DATE AND 10 SECS 1.5 SECS UPPER

BY APPLYING PRESSURE NONE OF THE ABOVE VERTICAL LEVELING THREE DIMENSIONAL 94.63 & 133.94 95.63 & 132.94 90 DAYS 45 DAYS 5 REVOLUTIONS 15 REVOLUTIONS MIL-L-6082 ,MIL-L-22852 MIL-L-6072 ,MIL-L-22851 8 6.5 4 8 4 7 ST 1 CHANGE AFTER 25 ONLY AT OVERHAUL 9 MONTHS AT ENGINE OVERHAUL 100LL GRADE AVIATION JP5, JP7 AND MOGAS JP5 AND JP7 ISOPROPYL ALCOHOL OR 29 GALLONS 20 GALLONS 13 GALLONS 20 GALLONS MIL-H-5606 NONE OF THE ABOVE DIFFERENTIAL DIFFRENTIAL PRESSURE 30 PSI 25 PSI 30 PSI 25.3 PSI MIL-H-5606 NONE OF THE ABOVE 100LL PETROL PETROL TURPENTINE S2243-1 & S2242-2 S2244-1 & S2243-2 GENERAL EMERGENCY ASTRO TEACH LC - 2 NONE OF THE ABOVE 5 AMP CIRCUIT BREAKER 10 AMP CIRCUIT BREAKER TIME OF DAY IN HOURS, NONE OF THE ABOVE 1 SEC 1.5 SECS 2.5 SECS 15 SECS LEFT HAND BUTTON CENTRE BUTTON

A B A A C B B A B C B C D B B A C C B C B A A B C B A B B C

222 223 224 225 226 227 228 229 230 231 232 233 234 235 236 237 238 239 240 241 242 243 244 245 246 247 248 249 250 251

WHERE IS THE GROUND SERVICE PLUG BEHIND A DOOR IS USING A GROUND SERVICE PLUG RECEPTACLE YES WHERE IS THE STANDBY VACUUM PUMP UNDER THE IS IFR FLIGHT RECOMMENDED WITH AN NO AT WHAT ALTITUDE DOES THE SUCTION GAUGE 15,000 FT AT WHAT TEMP. SHOULD THE WINTERIZATION KIT BELOW 20 C WHEN IS THE ELT ACTIVATED IMPACT OF 1G WHAT FREQUENCIES DOES THE ELT OPERATE ANY PRESET WHAT IS THE RANGE OF TRANSMISSION OF THE 100 MILES AT WHAT IS THE POWER OUTPUT AND FOR HOW 25 MW. RATED WHAT IS THE TEMP RANGE OF TRANSMISSION OF 10 C TO 25 C WHAT COLOR IS THE ELT UNIT AND WHERE IS BRIGHT ORANGE , WHAT IS THE FREQUENCY RANGE OF THE ADF 100 KHZ TO 1000 WHAT IS THE SYSTEM OF THE ADF COMPRISED RECIEVER, WHAT IS THE OPERATIONAL RANGE OF NAV/COM 118.000 TO BETWEEN WHAT FREQUENCIES DOES THE 108.00 TO 117.95 ON WHAT FREQUENCIES DOES THE TRANSMITS ON WHAT IS THE NO. OF CHANNELS THE GLIDE CAN 40 CHANNELS WHAT IS THE SPACING BETWEEN CHANNELS AND SPACING 250 KHZ WHEN IS THE GLIDE SLOPE INDICATOR WHEN G.S FLAG ABOVE WHAT ALTITUDE IS THE TRANSPONDER’S ABOVE 5000 FT. MARK THE CORRECT STATEMENT REGARDING THEY ARE WHAT EFFECT WILL THE FORWARD MOTION OF HAVE NO EFFECT GYRO-OPERATED FLIGHT INSTRUMENTS ARE ARRANGED SIDE AVIONICS EQUIPMENT ARE STACKED APPROX CENTER TACHOMETER, AMMETER, ECONOMY MIXTURE LEFT NOSE WHEEL CAN BE TURNED BY A TOW BAR BY 30 DEGREES WHEN RUDDER PEDALS ARE PRESSED THE 8.5, 30 MIN TURNING RADIUS OF THE AIRPLANE IS 25 FEET 1 INCH WING FLAPS ARE DOUBLE SLOTTED

BEHIND A BETWEEN THE PILOT NO ONLY IN COLD WEATHER NEXT TO THE MOUNTED ON THE AFT YES ONLY WHEN CLEARANCE 14,700 FT 10,000 FT BELOW 10 F BELOW 30 F IMPACT OF 5G DURING A STEEP TURN INTERNATION THE FREQUENCY 10 MILES AT 50 MILES AT 5,000 FT 75 MW. RATED 75 MW. RATED POWER O C TO 100 C -20 C TO 50 C RED, UNDER YELLOW, ON THE 200 KHZ TO 200 KHZ TO 500 KHZ RECIEVER, RECIEVER, BEARING 118.000 TO 118.000 TO 135.975 MHZ. 108.00 TO 108.00 TO 117.95 MHZ IN TRANSMITS TRANSMITS ON 1090 30 CHANNELS 20 CHANNELS SPACING 100 SPACING 150 KHZ APART WHEN INDICATOR NEVER FAILS ABOVE 1000 ABOVE 1000 FT. AND IN FORMED CONTAIN BALANCE TRIM NOSE TRIM NOSE DOWN SIDE BY SIDE ONE ABOVE ANOTHER LEFT RIGHT RIGHT CENTRE 15 DEGREES 20 DEGREES 30, 8.5 25, 7.5 30 FEET 2 25 FEET 2 INCHES SINGLE AS IN A AND DEFLECTION

AT LOCATION 530 ONLY AFTER ROTATING THERE IS NO STANDBY WITH SPECIAL 13,000 FT BELOW 20 F WHEN EXCEEDING VNE ON ALL MILITARY 100 MILES AT 5,000 FT 15 MW. RATED POWER -4 DEGREES F TO +131 BLACK, ALONG WITH THE 50 KHZ TO 700 KHZ RECIEVER AND BEARING 118.000 TO 135.975 MHZ. 108.00 TO 117.95 MHZ IN TRANSMITS ON 900 MHZ 10 CHANNELS SPACING 150 KHZ APART , NONE OF THE ABOVE ABOVE 10,000 FT. AND IN NONE OF THE ABOVE CAUSE AIRCRAFT TO YAW ONE ABOVE ANOTHER ABOVE LOWER HALF 45 DEGREES 7.5, 25 10 FEET 2 INCHES AS IN B AND DEFLECTION

A B C A A D B B A C D A B C A B C A C A B C C C A B A A A D

252 WING FLAP SYSTEM IS PROTECTED BY 253 THE AIRPLANE HAS...........BRAKE SYSTEM 254 A CONTROL LOCK IS PROVIDED TO PREVENT 255 MAJOR ENGINE ACCESSORIES INCLUDE 256 MARK THE MOST CORRECT STATEMENT 257 IGNITION STARTER SWITCH IS LABELED 258 USE OF FULL CARBURETOR HEAT AT FULL 259 CARBURETOR IS OF THE TYPE 260 ENGINE IS COOLED BY 261 PROPELLER OF THE A/C IS 262 ELECTRICAL SYSTEM OF THE AIRPLANE 263 LOW VOLTAGE LIGHT ILLUMINATES 264 THE COLOR OF THE LOW VOLTAGE LIGHT IS 265 ELECTRICAL CIRCUITS ARE PROTECTED BY 266 RADIO LT CONTROLS 267 PITOT HEAT SWITCH IS PROTECTED BY A 268 IF THE VACUUM SYSTEM FAILS, THEN THE GYRO 269 LOW VACCUUM LIGHT INDICATES 270 SUCTION GAGE WILL READ......AT 20000FEET 271 ACCELEROMETER IS CALIBRATED FROM 272 MARK THE CORRECT STATEMENT 273 STALL WARNING SYSTEM IS OF.........TYPE 274 STALL WARNING INDICATOR GIVES A

15 AMP HYDRAULICALLYAILERONS ONLY ELEVATOR, TACHOMETER IS START-BOTH-L-RRISE IN RPM BY UP-DRAFT, FLOAT RAM AIR SINGLE-BLADED, 28 VOLT DC AND AMMETER FLASHING GREEN PUSH-TO-RESET INTENSITY OF 60 AMP TURN & SLIP AMMETER 4.5 INCHES HG -5G TO +5G OAT IS INSTALLED HYDRAULIC 5 TO 10 KNOTS

25 AMP PNEUMATIC AILERONS & TACHOMETER AS IN A & IS OFF-L-RLOSS IN RPM FIXED JET, ENGINE TWO-BLADED, 24 VOLT DC UNDER LOW SERIES OF PULL-OFF INTENSITY OF 5 AMP DIRECTIONAL LOW VACUUM 4.7 INCHES -5G TO +10G OAT IS PNEUMATIC 10 TO 15

10 AMP 30 AMP AIR PRESSURED NONE OF THE ABOVE RUDDERS & ELEVATORS RUDDERS & AILERONS STARTER, BELT-DRIVEN NONE OF THE ABOVE AS IN B & INDICATES AS IN C MAX. SPEED OF OFF-R-L-START-BOTH OFF-R-L-BOTH-START LOSS IN RPM BY RISE IN RPM BY APPROX. BOTH ALL ARE CORRECT AVIONICS FAN ALL THE ABOVE TWO-BLADED, VARIABLE NONE OF THE ABOVE AS IN A AND BELT AS IN B AND BELT DRIVEN DUE TO EXCESS ALL THE ABOVE RED WHITE BOTH NONE OF THE ABOVE INTENSITY OF ALL ARE WRONG 15 AMP CIRCUIT FLIP SWITCH SUCTION GAGE ARTIFICIAL HORIZON LOW VACUUM IN THE LOW RPM CONDITIONS 4.0 INCHES HG 4.1 INCHES HG +5G TO +10G 0 TO +10G AS IN A AND CALIBRATED OAT IS INSTALLED ON MECHANICAL NONE OF THE ABOVE AT STALL NONE OF THE ABOVE

A A B C B D B A A B A B C C C C A B C B B B A