CESSNA 172 R QUESTION BANK
1. Propeller ground clearance : 11’ ¼”
2. Min. turning radius (Pivot point to outboard wingtip): 27’5 ½”
3. Fuel : 100LL – Color Blue
4. Ramp weight: Normal Category-2457lbs
5. Fuel additive should not exceed: 1% for Isopryl alcohol or .10% to .15% for DiEGME
6. Operations must be carried out with caution and only in smooth air: Yellow arc 129-163kts
7. ASI White arc: 33-85 KIAS, Green arc: 44-129 KIAS
8. Max window opening speed- 163 KIAS
9. Oil pressure Min.
Red line 20psi
Normal
Max
Green arc 50-90
Red line 115 psi
10. Abrupt use of controls prohibited above 99 kts (Normal Category); 94 kts (Utility category)
11. Total fuel: 28USG+28USG= 56US Gallons
Unusable 1.5 USG each tank
12. Max. slip or skid duration with one tank dry: 30secs
13. Calibration Card – Magnetic compass- 30° increments
14. Inadvertent icing
– Turn back or change altitude
15. With alternator side of the master switch off, compass deviations of as much as 25° may occur
16.
Maximum airspeed and altimeter variation from normal is 4kts and 30’ in case of alternate static door open in closed window condition.
17. The alternator control unit includes an over voltage sensor which normally will automatically shut down the alternator if the charge voltage reaches approximately 31.5 volts. Restart only when on ground.
18. Best ROC, MSL = 79 KIAS
19. Prior to flight, check that pitot heater is warm to touch within 30sec with battery and pitot heat switches ON
20. Oil: Do not operate with less than 5qts. Fill to 8qts for extended flight
21. RPM drop should not exceed 150 RPM on either magneto or 50 RPM differential between magnetos
22. After starting Oil pressure should indicate pressure within green arc in 30 seconds in summer and approximately 1 minute in very cold weather.
23. Starter duty cycle: Crank the starter for 10 sec. followed by a 20 sec. cool down period, this can be repeated two additional times followed by a 10min. cool down period. After cool down, crank the starter again, three cycles of 10sec followed by 20 seconds of cool down.
24. Alternator check: a Positive verification can be made by loading electrical system momentarily (3 to 5 seconds) with the landing light or operating the wing flaps during engine run up (1800 RPM)
25. Normal en-route climb are performed with flaps up and full throttle and at speeds 5 to 10 kts higher than best ROC speeds for the best combination of performance, visibility and engine cooling.
26. Normal cruising: 60-80% power
27. Until a total of 50 hrs has accumulated or oil consumption has stabilized, cruising should be done at
80% power.
28. Stall warning horn which sounds between 5 to 10 kts above stall in all configurations.
29. Operations in direct cross winds of 15 kts has been demonstrated
30. Min. turning radius with differential braking is approx. 27’
31.
Nose wheel turns through an arc of 10° each side of centre by applying either R/L brake.
This arc can be increased up to 30°

32. Single slot type flaps, mechanical stop provided at 10°,20° and 30° positions
33. Flap system is protected by 10 amp CB
34. Landing gear: Main – tubular spring steel; Nose – Air/Oil shock strut
35. Bottom edge of the fuel filler tab, 17.5 gallons usable in each tank
36. Operating with one tank dry when ¼ full or less do not allow airplane to remain in uncoordinated flight for periods in excess of 30 secs
37. Parking brakes: Set the brakes with rudder pedals, pull the handle aft, and rotate it 90° down
38. Voltage < 24.5 volts, red annunciation volts will flash for approximately 10 seconds before becoming steady.
39. Attitude indicator has index marks 10,20,30,60 and 90 degrees.
40. DG- lower left: adjusts the compass card error to correct for precision, lower right is used to move the heading bug.
41. Avionics Fan operates when Master and Avionics switches are both ON
42. Avoid covering opening on back side of microphone for optimum noise canceling.
43. Stuck microphone is kept continuously for greater than 33 seconds, the transmitter stops transmitting.
44. VSI indicated ROC/ROD in feet per min.
45. Carburetor icing is indicated by loss of RPM in fixed pitch propeller and loss of manifold pressure in constant speed propeller.
46. Engine flooding during start up: Turn off the auxillary fuel pump, Put mixture to idle cut off,
Throttle to half position and crant the engine, once the engine fires put mixture to full rich and move the throttle properly.
47. To get maximum cabin heating, Cabin heat knob fully out and cabin heat knob fully in.
48. Best fuel economy: Peak EGT
49. In voltmeter /OAT Clock pushing upper control button will change the display on the window to:
E.F.C.E (Pushing the upper control button will sequence the window from Voltage to
Fahrenheit ('F') to centigrade ('C') and again back to voltage.)
50. Black smoke from exhaust? Because of spark plug fowling.
51. Alternate static vent positioned at: Centre case of instrument panel
52. ELT annunciator does not light up at Low fuel flow and Low RPM.
53. OAT/ voltmeter gauge select switch may be tested by putting the select button down for 3 seconds to start
54. When oil pressure is below 20psi, OIL PRESS red light illuminates
55. In event of alternate static vent open, air speed indicator will give an error of 4 knots and altimeter error will be ±30’ in closed window conditions.
56. ELT Annunciator does not activate on: Low fuel flow and Low RPM
57. DGI should be aligned regularly on long haul flights for: Precession.
58. Avionics cooling fan switches ON automatically when avionics master is ON
59. In event of static tube blockage: ASI reads error.
60. To permit heavy cabin loading, fuel load can be reduced to 17.5 gallons usable in each tank.
61. Aircraft tyres are 6 ply rated
62. Fuel system verifying is essential to the system operation. Blockages of the system will result in decreased fuel flow and even result in engine stoppage. Verifying is accompanied by an interconnecting live from right to left fuel tank.
63. Fuel flow meter range is: 0 – 11 GPH. Cruising fuel flow 5.6 to 9.3 GPH depending on height, power and OAT.
64. Tyre pressure: Main: 28psi, Nose : 34psi
65. Nose gear: Oleo pneumatic shock strut - Air Pressure 45 psi.
66.
Temperature Lapse Rate as per ISA: 2°C/1000’
67. Full Rich mixture MUST be used when operating above 80% power.
68. For easy starting in cold weather, use Primer.

69. Examination of fuel in the system for contamination should be done after every refueling and before first flight of the day.
70. Max Speed at sea level is 123 kts and max speed at cruise, 80% power at 8000 ft is 122 kts.
71. The airplane is equipped with a 28 V direct current electrical system. The system is powered by a belt driven 60 amp and a 24 volt battery.
72. The fuel selector valve should be in both position for take off, climb, landing, and manoeuvres that involve slip or skid of more than 30 sec. Operation from either Left or Right tank is only for cruise.
73. Altitude loss in a stall is as much as 230 ft.
74. At or below 80% power EGT indication is used to lean the mixture for best performance or economy.
75. Normal take off’s are done with 0-10 o flaps. Using 10 o flaps reduces ground roll by approx
10% and also total distance over obstacle. Flaps more than 10 o is not permitted for take off.
Flaps are to be kept at 10 o till obstacle is cleared and a safe flap retraction speed of 60 kts is achieved. For short take off speed of 57 kts is to be used.
76. Wheel base is 65 inches. Wing span is 36 ft 1 inch. Length of aircraft is 27 ft 2 inches. Height is 8 ft 11 inch. Propellor ground clearance is 11.25 inches. Nose strut is of 2 inches strut.
Wing area is 174 sq ft. Elevator span is 11Ft 4 inches.
77. Engine manufacturer is Textron Lycoming. Type is Normally aspirated, direct drive, air cooled, horizontally opposed, fuel injected, four cylinder engine with 360 cu in in displacement.
78. Propeller manufacturer is McCauley Propellor systems, has two blades with dia of 74 inches and is fixed pitch.. Model number is 1C235/LFA7570.
79. Max Flaps extended speed with 10 o flaps is 108 kts CAS and 110 Kts IAS, with 10 o to 30 o flaps is 84 Kts CAS and 85 Kts IAS.
80. Baggage area for station 1 is 120 lbs and station 2 is 50 lbs. Total baggage allowed is 120 lbs.
81. Engine operation is controlled by a rotary switch which reads Right, Left, Both and Start.
82. In long flights max deviation of compass allowed is 30 o .
83. For first 25 hrs oil to be used is MIL-L-6082 or SAE-J-1966 aviation grade oil. Thereafter this oil is to be drained and till 50 hrs same grade of oil to be used. .After 50 hrs of engine running oil to be used is MIL-L-22852 or SAE-J-1899 aviation grade ashlees dispersant oil.
84. Shock absorption of nose wheel is by air/oil system and of main wheel is by tubular spring coil.
85. Enroute climb speed is 5-10 kts above best rate of climb speed for best visibility and best performance and best cooling.
86. Nose tyre pressure is 34 psi, main tyre is 28 psi and nose strut pressure is 45 psi.
87. Spark plug fault causes misfiring and magneto malfunction causes loss of RPM.
88. Brake oil of the aircraft is MIL-L-5606.
89. Landing with flat main tyres flaps to be at 30 o and with flat nose tyre will be flaps as desired.
90. Magneto check is to be done at 2000 RPM, drop in each magneto off should not be more than 150 RPM and the difference in drop between both magneto’s should not be more than
50 RPM.
91. The communication receiver transmitter works between 118.06 and 136.975 Mhz with an interval of 25 KHz.
92. The nav receiver receives VOR and ILS signals between 108.00 and 117.95 MHz in steps of
50 KHz.
93. Aircraft clock is davtion model 803 digital clock.
94. The Radio communication system is a 760 channel VHF communication receiver and 100
95. channel VHF navigation receiver.
PERFORMANCE - SPECIFICATIONS

* SPEED:
Maximum at Sea Level . . . . . . . . . . . . . . . . . . .
Cruise, 80% Power at 8000 FT . . . . . . .
CRUISE:
. . . . .
Recommended lean mixture with fuel allowance for engine start, taxi, takeoff, climb and 45 minutes reserve.
80% Power at 8000 FT . . . . . . . . . . . .
53 Gallons Usable Fuel
Range
Time
Range at 10,000 FT, 60% power . . . . .
53 Gallons Usable Fuel
RATE OF CLIMB AT SEA LEVEL . . . . . . . . . .
SERVICE CEILING . . . . . . . . . . . . . . . . . . . . . .
TAKEOFF PERFORMANCE:
Ground Roll . . . . . . . . . . . . . . . . . . . . . . . .
Total Distance Over 50 FT Obstacle . . . . .
LANDING PERFORMANCE:
Ground Roll . . . . . . . . . . . . . . . . . . . . . . . .
Total Distance Over 50 FT Obstacle . . . . .
STALL SPEED:
Flaps Up, Power Off . . . . . . . . . . . . . . . . . .
Flaps Down, Power Off . . . . . . . . . . . . . . . .
Range
Time
. . . . . .
. . . . .
. . . . . . .
. . . . . . .
. . . . . . .
. . . . . . .
. . . . .
. . . . . 47 KCAS
MAXIMUM WEIGHT:
Ramp Normal category
Utility .
Takeoff Normal category
Utility
Landing Normal category
Utility
. . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . .
. . . . . . . . . .
. . . . . . . . . . . . . . . . .
. . . . . . . . . .
. . . . .
. . . . .
STANDARD EMPTY WEIGHT . . . . . . . . . . . . .
MAXIMUM USEFUL LOAD . . . . . . . . . . . . . . . .
BAGGAGE ALLOWANCE . . . . . . . . . . . . . . . . .
. . . . . .
2457 LBs
2107 lbs
2450 LBS
2100 lbs
2450 LBS
2100 lbs
1639 LBS
. . . . . . 818 LBS
. . . . . . 120 LBS
123 KNOTS
122 KNOTS
580 NM
4.8 HRS
687 NM
6.6 HRS
. 720 FPM
13,500 FT
945 FT
1685 FT
550 FT
1295 FT
51 KCAS

AIRSPEEDS
AIRSPEEDS FOR NORMAL OPERATION
Unless otherwise noted, the following speeds are based on a maximum weight of 2450 pounds and may be used for any lesser weight.
Takeoff:
Normal Climb Out . . . . . . . . . . . . . . . . . . . . . . . . .
Short Field Takeoff, Flaps 10°, Speed at 50 Feet
Enroute Climb, Flaps Up:
Normal, Sea Level . . . . . . . . . . . . . . . . . . . . . . . .
Normal, 10,000 Feet . . . . . . . . . . . . . . . . . . . . . . .
Best Rate-of-Climb, Sea Level . . . . . . . . . . . . . . .
Best Rate-of-Climb, 10,000 Feet . . . . . . . . . . . . .
Best Angle-of-Climb, Sea Level . . . . . . . . . . . . . . .
Best Angle-of-Climb, 10,000 Feet . . . . . . . . . . . . .
Landing Approach:
Normal Approach, Flaps Up . . . . . . . . . . . . . . . . .
Normal Approach, Flaps 30° . . . . . . . . . . . . . . . . .
Short Field Approach, Flaps 30° . . . . . . . . . . . . . .
Balked Landing:
Maximum Power, Flaps 20° . . . . . . . . . . . . . . . . .
Maximum Recommended Turbulent Air Penetration Speed:
2450 Lbs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2000 Lbs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1600 Lbs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Maximum Demonstrated Crosswind Velocity:
70-80 KIAS
. . . . 57 KIAS
75-85 KIAS
70-80 KIAS
. . .79 KIAS
. . .71 KIAS
. .60 KIAS
. . 65 KIAS
65-75 KIAS
60-70 KIAS
. .62 KIAS
. .55 KIAS
.99 KIAS
.92 KIAS
.82 KIAS
Takeoff or Landing . . . . . . . . . . . . . . . . . . . . . . . . 15 KNOTS
To apply the parking brake, set the brakes with the rudder pedals, pull the handle aft, and rotate it 90° down.
OTHER LIMITATIONS
FLAP LIMITATIONS
Approved Takeoff Range: . . . . . . . . . . . . . . . . . . . . .
Approved Landing Range: . . . . . . . . . . . . . . . . . . . . .
AIRSPEEDS
AIRSPEEDS FOR EMERGENCY OPERATION
0° to 10°
0° to 30°
Engine Failure After Takeoff:
Wing Flaps Up . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Wing Flaps Down . . . . . . . . . . . . . . . . . . . . . . . . . . .
Maneuvering Speed:
2450 Lbs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2100 Lbs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1600 Lbs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Maximum Glide . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Precautionary Landing With Engine Power . . . . . . . . . . . 60 KIAS
Landing Without Engine Power:
Wing Flaps Up . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Wing Flaps Down . . . . . . . . . . . . . . . . . . . . . . . . . . .
65 KIAS
60 KIAS
99 KIAS
92 KIAS
82 KIAS
65 KIAS
65 KIAS
60 KIAS

ELECTRICAL SYSTEM
The airplane is equipped with a 28-volt, direct current electrical system (Refer to
Figure 7-7). The system is powered by a belt-driven, 60-amp alternator and a 24volt battery. The low voltage warning annunciator is incorporated in the annunciator panel and activates when voltage falls below 24.5 volts. If low voltage is detected, the red annunciation VOLTS will flash for approximately 10 seconds before illuminating steadily.
When towing with a vehicle, do not exceed the nose gear turning angle of 30° either side of center
PERFORMANCE-SPECIFICATIONS
(Continued)
WING LOADING: Lbs/Sq Ft . . . . . . . . . . . . . . . . . . . . . .
POWER LOADING: Lbs/HP . . . . . . . . . . . . . . . . . . . . . . .
FUEL CAPACITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
. . .14.1
. .15.3
56 GAL
OIL CAPACITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ENGINE: Textron Lycoming . . . . . . . . . . . . . . . . . . . .
160 BHP at 2400 RPM
PROPELLER: Fixed Pitch, Diameter . . . . . . . . . . . . . . .
8 QTS
IO-360-L2A
. . 75 IN.
* NOTE
Speed performance is shown for an airplane equipped with optional speed fairings which increase the speeds by approximately 2 knots.
There is a corresponding difference in range, while all other performance figures are unchanged when speed fairings are installed.
Keep strut filled with MIL-H-5606 hydraulic fluid per filling instructions placard, and with no load on the strut, inflate with air to 45.0 PSI.
Do not over inflate.
Nose Wheel (5.00-5, 6-Ply Rated Tire)
Main Wheel (6.00-6, 4-Ply Rated Tire)
BrakesMIL-H-5606
Nose Gear Shock Strut
34.0 PSI
28.0 PSI
MIL-H-5606; 45.0 PSI *
DESCRIPTIVE DATA
ENGINE
Number of Engines: 1.
Engine Manufacturer: Textron Lycoming.
Engine Model Number: IO-360-L2A.
Engine Type: Normally aspirated, direct drive, air-cooled, horizontally opposed, fuel injected, four cylinder engine with 360 cu. in. displacement.
Horsepower Rating and Engine Speed: 160 rated BHP at 2400
RPM.

PROPELLER
Propeller Manufacturer: McCauley Propeller Systems.
Propeller Model Number: 1C235/LFA7570.
Number of Blades: 2. Propeller
Diameter: 75 inches. Propeller
Type: Fixed pitch.
FUEL
Approved Fuel Grades (and Colors):
100LL Grade Aviation Fuel (Blue).
100 Grade Aviation Fuel (Green).
NOTE
Isopropyl alcohol or diethylene glycol monomethyl ether (DiEGME) may be added to the fuel supply. Additive concentrations shall not exceed
1% for isopropyl alcohol or 0.10% to 0.15% for DiEGME. Refer to
Section 8 for additional information.
Fuel Capacity:
Total Capacity:
Total Usable:
56.0 U.S. gallons.
53.0 U.S. gallons.
Total Capacity Each Tank: 28.0 U.S. gallons.
Total Usable Each Tank: 26.5 U.S. gallons.
NOTE
OIL
To ensure maximum fuel capacity and minimize cross-feeding when refueling, always park the airplane in a wings-level, normal ground attitude and place the fuel selector in the Left or Right position. Refer to
Figure 1-1 for normal ground attitude dimensions.
Oil Specification:
MIL-L-6082 or SAE J1966 Aviation Grade Straight Mineral Oil: Used when the airplane was delivered from the factory and should be used to replenish the supply during the first 25 hours. This oil should be drained and the filter changed after the first 25 hours of operation. Refill the engine with MIL-L-6082 or SAE
J1966 Aviation Grade Straight Mineral Oil and continue to use until a total of 50 hours has accumulated or oil consumption has stabilized.
Recommended Viscosity for Temperature

Temperature
Above 27°C (80°F)
Above 16°C (60°F)
1°C (30°F) to 32°C (90°F)
18°C (0°F) to 21°C (70°F)
Below -
12°C (10°F)
18°C (0°F) to 32°C (90°F)
MIL-L-6082 or
SAE J1966
Straight
Mineral Oil
SAE Grade
60
50
40
30
20
20W-50
MIL-L-22851 or
SAE J1899
Ashless Dispersant
SAE Grade
60
40 or 50
40
30, 40 or 20W-40
30 or 20W-30
20W-50 or 15W-50
All Temperatures >>> 15W-50 or 20W-50
MIL-L-22851 or SAE J1899 Aviation Grade Ashless Dispersant Oil: Oil conforming to the latest revision and/or supplements to Textron Lycoming
Service Instruction No. 1014, must be used after first 50 hours or once oil consumption has stabilized.
NOTE
When operating temperatures overlap, use the lighter grade of oil.
Oil Capacity:
Sump: 8 U.S. Quarts
Total: 9 U.S. Quarts
MAXIMUM CERTIFICATED WEIGHTS
Ramp Weight Normal Category:
Utility Category:
2457 lbs.
2107 lbs.
Takeoff Weight Normal Category:
Utility Category:
2450 lbs.
2100 lbs.
Landing Weight Normal Category: 2450 lbs.
Utility Category: 2100 lbs.
Weight in Baggage Compartment, Normal Category:
Baggage Area 1 (Station 82 to 108):
Baggage Area 2 (Station 108 to 142):
120 lbs. See note below.
50 lbs. See note below.
NOTE
The maximum combined weight capacity for Baggage Area 1 and

Baggage Area 2 is 120 lbs.
Weight in Baggage Compartment, Utility Category:
In this category, the rear seat must not be occupied and the baggage compartment must be empty.
STANDARD AIRPLANE WEIGHTS
Standard Empty Weight:
Maximum Useful Load, Normal Category:
1639 lbs.
818 lbs.
Maximum Useful Load, Utility Category :
CABIN AND ENTRY DIMENSIONS
468 lbs.
Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6.
BAGGAGE SPACE AND ENTRY DIMENSIONS
Dimensions of the baggage area and baggage door opening are illustrated in detail in Section 6.
SPECIFIC LOADINGS
Wing Loading:
Power Loading:
14.1 lbs./sq. ft.
15.3 lbs./hp.

SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS
KCAS Knots Calibrated Airspeed is indicated airspeed corrected for position and instrument error and expressed in knots. Knots calibrated airspeed is equal to KTAS in standard atmosphere at sea level.
KIAS Knots Indicated Airspeed is the speed shown on the airspeed indicator and expressed in knots.
KTAS
V
V
V
A
FE
NO
Knots True Airspeed is the airspeed expressed in knots relative to undisturbed air which is KCAS corrected for altitude and temperature.
Maneuvering Speed is the maximum speed at which full or abrupt control movements may be used without overstressing the airframe.
Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position.
Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air, then only with caution.
V
V
V
V
NE
S
S
O
X
Never Exceed Speed is the speed limit that may not be exceeded at any time.
Stalling Speed or the minimum steady flight speed is the minimum speed at which the airplane is controllable.
Stalling Speed or the minimum steady flight speed is the minimum speed at which the airplane is controllable in the landing configuration at the most forward center of gravity.
Best Angle-of-Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal distance.
Best Rate-of-Climb Speed is the speed which V
Y
WEIGHT AND BALANCE TERMINOLOGY
Reference Reference Datum is an imaginary vertical plane from Datum which all horizontal distances are measured for balance purposes.
Station Station is a location along the airplane fuselage given in terms of the distance from the reference datum.
Arm Arm is the horizontal distance from the reference datum to the center of gravity (C.G.) of an item.
Moment Moment is the product of the weight of an item multiplied by its arm. (Moment divided by the constant 1000 is used in this handbook to simplify balance calculations by reducing the number of digits.)
Center of Center of Gravity is the point at which an airplane, or Gravity equipment, would balance if suspended. Its distance (C.G.) from the reference datum is found by dividing thetotal moment by the total weight of the airplane. results in the greatest gain in altitude in a given time.

WEIGHT AND BALANCE TERMINOLOGY (Continued)
C.G. Center of Gravity Arm is the arm obtained byArm adding the airplane's individual moments and dividing the sum by the total weight.
C.G. Center of Gravity Limits are the extreme center of Limits gravity locations within which the airplane must be operated at a given weight.
Standard Standard Empty Weight is the weight of a standard Empty airplane, including unusable fuel, full operating fluids Weight and full engine oil.
Basic Empty Basic Empty Weight is the standard empty weight Weight plus the weight of optional equipment.
Useful Load Useful Load is the difference between ramp weight and the basic empty weight.
MAC MAC (Mean Aerodynamic Chord) is the chord of an imaginary rectangular airfoil having the same pitching moments throughout the flight range as that of the actual wing.
Maximum Maximum Ramp Weight is the maximum weight Ramp approved for ground maneuver, and includes the Weight weight of fuel used for start, taxi and runup.
Maximum Maximum Takeoff Weight is the maximum weight Takeoff approved for the start of the takeoff roll.
Weight
Maximum Maximum Landing Weight is the maximum weight Landing approved for the landing touchdown.
Weight
Tare Tare is the weight of chocks, blocks, stands, etc.
used when weighing an airplane, and is included in the scale readings. Tare is deducted from the scale reading to obtain the actual (net) airplane weight.

AIRSPEED LIMITATIONS
Airspeed limitations and their operational significance are shown in Figure 2-
1. Maneuvering speeds shown apply to normal category operations. The utility category maneuvering speed is 92 KIAS at 2100 pounds.
SYMBOL SPEED
V NE Never Exceed Speed
V NO Maximum Structural
Cruising Speed
V
A
Maneuvering
Speed:
2450 Pounds
2000 Pounds
1600 Pounds
V FE Maximum Flap
Extended Speed:
10° Flaps
10° to 30° Flaps
KCAS KIAS REMARKS only with caution.
160 163 Do not exceed this speed in any operation.
126 129 Do not exceed this speed except in
97
91
82
Do not make full or
99 abrupt control
92 movements above
82 this speed.
Do not exceed this
108 110 speed with flaps
84 85 down.
-----
Maximum
Window Open
160 163 Do not exceed this speed with windows
Speed open.
AIRSPEED INDICATOR MARKINGS
Airspeed indicator markings and their color code significance are shown in
Figure 2-2.
MARKING
KIAS
VALUE SIGNIFICANCE
OR RANGE smooth air, and then
White Arc 33 - 85 Full Flap Operating Range. Lower limit is maximum weight V
S0
in landing configuration. Upper limit is maximum speed permissible with flaps extended.

Green Arc
Yellow Arc
44 -129 Normal Operating Range. Lower limit is maximum weight V
S1
at most forward C.G. with flaps retracted.
Upper limit is maximum structural cruising speed.
129-163 Operations must be conducted with caution and only in smooth air.
Red Line 163 Maximum speed for all operations.
Figure 2-2. Airspeed Indicator Markings
POWERPLANT LIMITATIONS
Engine Manufacturer: Textron Lycoming.
Engine Model Number: IO-360-L2A. Maximum
Power: 160 BHP rating.
Engine Operating Limits for Takeoff and Continuous Operations: Maximum
Engine Speed: 2400 RPM.
NOTE
The static RPM range at full throttle is 2065 - 2165 RPM.
Maximum Oil Temperature: 245°F (118°C).
Oil Pressure, Minimum: 20 PSI.
Maximum: 115 PSI.
Fuel Grade: See Fuel Limitations. Oil
Grade (Specification):
MIL-L-6082 or SAE J1966 Aviation Grade Straight Mineral Oil or MIL-L-22851 or SAE J1899 Ashless Dispersant Oil. Oil must comply with the latest revision and/or supplement for Textron Lycoming Service Instruction No. 1014.
Propeller Manufacturer: McCauley Propeller Systems.
Propeller Model Number: 1C235/ LFA7570.
Propeller Diameter: 75 inches.
74 inch minimum.

POWERPLANT INSTRUMENT MARKINGS
Powerplant instrument markings and their color code significance are shown in
Figure 2-3.
GREEN ARC
INSTRUMENT
RED LINE
(MINIMUM)
(NORMAL
OPERATING)
RED
LINE
(MAX)
>>>> Tachometer:
Oil
Temperature
Oil Pressure
Fuel Quantity
>>>>
20 PSI
0
(1.5 Gal. Unusable
Each Tank)
1900 to 2400
RPM
2400
RPM
100 to 245°F 245°F
50 to 90 PSI
>>>>
115
PSI
>>>>
Fuel Flow ---- 0 to 11 GPH >>>>
Vacuum Gage ---- 4.5 - 5.5 in.Hg ----
Figure 2-3. Powerplant Instrument Markings

WEIGHT LIMITS
NORMAL CATEGORY
Maximum Ramp Weight: 2457 lbs.
Maximum Takeoff Weight: 2450 lbs.
Maximum Landing Weight: 2450 lbs.
Maximum Weight in Baggage Compartment:
Baggage Area 1 - Station 82 to 108:120 lbs.
Baggage Area 2 - Station 108 to 142: 50 lbs.
NOTE
The maximum combined weight capacity for baggage areas 1 and 2 is 120 lbs.
UTILITY CATEGORY
Maximum Ramp Weight: 2107 lbs. Maximum
Takeoff Weight: 2100 lbs. Maximum Landing
Weight: 2100 lbs.
Maximum Weight in Baggage Compartment: In the utility category, the baggage compartment and rear seat must not be occupied.
CENTER OF GRAVITY LIMITS
NORMAL CATEGORY
Center of Gravity Range:
Forward: 35.0 inches aft of datum at 1950 lbs. or less, with straight line variation to 40.0 inches aft of datum at 2450 lbs.
Aft: 47.3 inches aft of datum at all weights.
Reference Datum: Lower portion of front face of firewall.
UTILITY CATEGORY
Center of Gravity Range:
Forward: 35.0 inches aft of datum at 1950 lbs. or less, with straight line variation to 36.5 inches aft of datum at 2100 lbs.
Aft: 40.5 inches aft of datum at all weights.
Reference Datum: Lower portion of front face of firewall.
MANEUVER LIMITS
NORMAL CATEGORY
This airplane is certificated in both the normal and utility category. The normal

category is applicable to aircraft intended for non aerobatic operations. These include any maneuvers incidental to normal flying, stalls (except whip stalls), lazy eights, chandelles, and turns in which the angle of bank is not more than 60°.
NORMAL CATEGORY MANEUVERS AND RECOMMENDED EN-TRY SPEED*
Chandelles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Lazy Eights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Steep Turns . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
. . .105 Knots
. .105 Knots
. . .95 Knots
Stalls (Except Whip Stalls) . . . . . . . . . . . . . . . . Slow Deceleration
* Abrupt use of the controls is prohibited above 99 knots.
UTILITY CATEGORY
This airplane is not designed for purely aerobatic flight. However, in the acquisition of various certificates such as commercial pilot and flight instructor, certain maneuvers are required by the FAA. All of these maneuvers are permitted in this airplane when operated in the utility category.
In the utility category, the rear seat must not be occupied and the baggage compartment must be empty .
UTILITY CATEGORY MANEUVERS AND RECOMMENDED ENTRY SPEED*
Chandelles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Lazy Eights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Steep Turns . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Spins . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
. . .105 Knots
. .105 Knots
. . .95 Knots
Slow Deceleration
Stalls (Except Whip Stalls) . . . . . . . . . . . . . . . . Slow Deceleration
* Abrupt use of the controls is prohibited above 92 knots.
Aerobatics that may impose high loads should not be attempted. The important thing to bear in mind in flight maneuvers is that the airplane is clean in aerodynamic design and will build up speed quickly with the nose down. Proper speed control is an essential re-quirement for execution of any maneuver, and care should always be exercised to avoid excessive speed which in turn can impose ex-cessive loads. In the execution of all maneuvers, avoid abrupt use of controls.
FLIGHT LOAD FACTOR LIMITS
NORMAL CATEGORY
Flight Load Factors (Maximum Takeoff Weight - 2450 lbs.):
* Flaps Up . . . . . . . . . . . . . . . . . . . . . . . +3.8g, -1.52g
* Flaps Down . . . . . . . . . . . . . . . . . . . . . +3.0g
* The design load factors are 150% of the above, and in all cases, the structure meets or exceeds design loads.
UTILITY CATEGORY

Flight Load Factors (Maximum Takeoff Weight - 2100 lbs.): * Flaps Up . . . . . .
. . . . . . . . . . . . . . . . . +4.4g, -1.76g
* Flaps Down . . . . . . . . . . . . . . . . . . .
. . +3.0g
* The design load factors are 150% of the above, and in all cases, the structure meets or exceeds design loads.
KINDS OF OPERATION LIMITS
The airplane as delivered is equipped for day VFR and may be equipped for night
VFR and/or IFR operations. FAR Part 91 establishes the minimum required instrumentation and equipment for these operations. The reference to types of flight operations on the operating limitations placard reflects equipment installed at the time of Airworthiness Certificate issuance.
Flight into known icing conditions is prohibited.
FUEL LIMITATIONS
Total Fuel: 56 U.S. gallons (2 tanks at 28.0 gallons each).
Usable Fuel (all flight conditions): 53.0 U.S. gallons.
Unusable Fuel: 3.0 U.S. gallons (1.5 gallons each tank).
NOTE
To ensure maximum fuel capacity and minimize cross-feeding when refueling, always park the airplane in a wings-level, normal ground attitude and place the fuel selector in the Left or Right position. Refer to Figure 1-1 for normal ground attitude definition.
ADDITIONAL FUEL LIMITATIONS
Takeoff and land with the fuel selector valve handle in the BOTH position.
Maximum slip or skid duration with one tank dry: 30 seconds.
Operation on either LEFT or RIGHT tank limited to level flight only.
With 1/4 tank or less, prolonged uncoordinated flight is prohibited when operating on either left or right tank.
Fuel remaining in the tank after the fuel quantity indicator reads 0 (red line) cannot be safely used in flight.
Approved Fuel Grades (and Colors):
100LL Grade Aviation Fuel (Blue).
100 Grade Aviation Fuel (Green).
EMERGENCY PROCEDURES CHECKLIST
Procedures in the Emergency Procedures Checklist portion of this section shown in bold faced type are immediate action items which should be committed to memory.

ENGINE FAILURES
ENGINE FAILURE DURING TAKEOFF ROLL
1. Throttle -- IDLE.
2. Brakes-- APPLY.
3. Wing Flaps -- RETRACT.
4. Mixture -- IDLE CUT OFF.
5. Ignition Switch -- OFF.
6. Master Switch -- OFF.
ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF
1. Airspeed -- 65 KIAS (flaps UP).
60 KIAS (flaps DOWN).
2. Mixture -- IDLE CUT OFF.
3. Fuel Shutoff Valve -- OFF (Pull Full Out).
4. Ignition Switch -- OFF.
5. Wing Flaps -- AS REQUIRED.
6. Master Switch -- OFF.
7. Cabin Door -- UNLATCH.
8. Land -- STRAIGHT AHEAD.
ENGINE FAILURE DURING FLIGHT (Restart Procedures)
1. Airspeed -- 65 KIAS.
2. Fuel Shutoff Valve -- ON (push full in).
3. Fuel Selector Valve -- BOTH.
4. Auxiliary Fuel Pump Switch -- ON.
5. Mixture -- RICH (if restart has not occurred).
6. Ignition Switch -- BOTH (or START if propeller is stopped).
NOTE
If the propeller is windmilling, the engine will restart automatically within a few seconds. If the propeller has stopped (possible at low speeds), turn the ignition switch to START, advance the throttle slowly from idle and lean the mixture from full rich as required for smooth operation.
7. Auxiliary Fuel Pump Switch -- OFF.
NOTE
If the fuel flow indicator immediately drops to zero (indicating an engine-driven fuel pump failure), return the Auxiliary Fuel Pump
Switch to the ON position.
FORCED LANDINGS
EMERGENCY LANDING WITHOUT ENGINE POWER
1. Passenger Seat Backs -- MOST UPRIGHT POSITION.
2. Seats and Seat Belts -- SECURE.
3. Airspeed -- 65 KIAS (flaps UP).

60 KIAS (flaps DOWN).
4. Mixture -- IDLE CUT OFF.
5. Fuel Shutoff Valve -- OFF (Pull Full Out).
6. Ignition Switch -- OFF.
7. Wing Flaps --
AS REQUIRED (30° recommended).
8. Master Switch -- OFF (when landing is assured).
9. Doors -- UNLATCH PRIOR TO TOUCHDOWN.
10. Touchdown -- SLIGHTLY TAIL LOW.
11. Brakes -- APPLY HEAVILY.
PRECAUTIONARY LANDING WITH ENGINE POWER
1. Passenger Seat Backs -- MOST UPRIGHT POSITION.
2. Seats and Seat Belts -- SECURE.
3. Airspeed -- 60 KIAS.
4. Wing Flaps -- 20°.
5. Selected Field -- FLY OVER, noting terrain and obstructions, then retract flaps upon reaching a safe altitude and airspeed.
6. Avionics Master Switch and Electrical Switches -- OFF.
7. Wing Flaps -- 30° (on final approach).
8. Airspeed -- 60 KIAS.
9. Master Switch -- OFF.
10. Doors -- UNLATCH PRIOR TO TOUCHDOWN.
11. Touchdown -- SLIGHTLY TAIL LOW.
12. Ignition Switch -- OFF.
13. Mixture -- IDLE CUTOFF.
14. Brakes -- APPLY HEAVILY.
DITCHING
1. Radio -- TRANSMIT MAYDAY on 121.5 MHz, giving location and intentions and
SQUAWK 7700.
2. Heavy Objects (in baggage area) -- SECURE OR JETTISON (if possible).
3. Passenger Seat Backs -- MOST UPRIGHT POSITION.
4. Seats and Seat Belts -- SECURE.
5. Wing Flaps -- 20° to 30°.
6. Power -- ESTABLISH 300 FT/MIN DESCENT AT 55 KIAS.
NOTE
If no power is available, approach at 65 KIAS with flaps up or at 60 KIAS with
10° flaps.
7. Approach -- High Winds, Heavy Seas -- INTO THE WIND.
Light Winds, Heavy Swells -- PARALLEL TO
SWELLS.
8. Cabin Doors -- UNLATCH.
9. Touchdown -- LEVEL ATTITUDE AT ESTABLISHED RATE OF
DESCENT.
10. Face -- CUSHION at touchdown with folded coat.
11. ELT -- Activate.
12. Airplane -- EVACUATE through cabin doors. If necessary, open window and flood cabin to equalize pressure so doors can be opened.
13. Life Vests and Raft -- INFLATE WHEN CLEAR OF AIRPLANE.
FIRES
DURING START ON GROUND

1. Ignition Switch -- START, Continue Cranking to get a start which would suck the flames and accumulated fuel into the engine.
If engine starts:
2. Power -- 1700 RPM for a few minutes.
3. Engine -- SHUTDOWN and inspect for damage. If engine fails to start:
4. Throttle -- FULL OPEN.
5. Mixture -- IDLE CUT OFF.
6. Cranking -- CONTINUE.
7. Fuel Shutoff Valve -- OFF (Pull Full Out).
8. Auxiliary Fuel Pump -- OFF.
9. Fire Extinguisher -- OBTAIN (have ground attendants obtain if not installed).
10. Engine -- SECURE. a. Master Switch -- OFF. b. Ignition Switch -- OFF
11. Parking Brake -- RELEASE.
12. Airplane -- EVACUATE.
13. Fire -- EXTINGUISH using fire extinguisher, wool blanket, or dirt.
14. Fire Damage -- INSPECT, repair damage or replace damaged components or wiring before conducting another flight.
ENGINE FIRE IN FLIGHT
1. Mixture -- IDLE CUT OFF.
2. Fuel Shutoff Valve -- OFF (Pull Full Out).
3. Auxiliary Fuel Pump Switch -- OFF.
4. Master Switch -- OFF.
5. Cabin Heat and Air -- OFF (except overhead vents).
6. Airspeed -- 100 KIAS (If fire is not extinguished, increase glide speed to find an airspeed - within airspeed limitations - which will provide an incombustible mixture).
7. Forced Landing -- EXECUTE (as described in Emergency Landing Without
Engine Power) .
ELECTRICAL FIRE IN FLIGHT
1. Master Switch -- OFF.
2. Vents, Cabin Air, Heat -- CLOSED.
3. Fire Extinguisher -- ACTIVATE (if available).
4. Avionics Master Switch -- OFF.
5. All Other Switches (except ignition switch) -- OFF.
AFTER DISCHARGING FIRE EXTINGUISHER AND
ASCERTAINING THAT FIRE HAS BEEN EXTINGUISHED,
VENTILATE THE CABIN.
6. Vents/Cabin Air/Heat -- OPEN when it is ascertained that fire is completely extinguished.
If fire has been extinguished and electrical power is necessary for continuance of flight to nearest suitable airport or landing area:
7. Master Switch -- ON.

8. Circuit Breakers -- CHECK for faulty circuit, do not reset.
9. Radio Switches -- OFF.
10. Avionics Master Switch -- ON.
11. Radio/Electrical Switches -- ON one at a time, with delay after each until short circuit is localized.
CABIN FIRE
1. Master Switch -- OFF.
2. Vents/Cabin Air/Heat -- CLOSED (to avoid drafts).
3. Fire Extinguisher -- ACTIVATE (if available).
AFTER DISCHARGING FIRE EXTINGUISHER AND
ASCERTAINING THAT FIRE HAS BEEN EXTINGUISHED,
VENTILATE THE CABIN.
4. Vents/Cabin Air/Heat -- Open when it is ascertained that fire is completely extinguished.
5. Land the airplane as soon as possible to inspect for damage.
WING FIRE
1. Landing/Taxi Light Switches -- OFF.
2. Navigation Light Switch -- OFF.
3. Strobe Light Switch -- OFF.
4. Pitot Heat Switch -- OFF.
NOTE
Perform a sideslip to keep the flames away from the fuel tank and cabin.
Land as soon as possible using flaps only as required for final approach and touchdown.
ICING
INADVERTENT ICING ENCOUNTER
1. Turn pitot heat switch ON .
2. Turn back or change altitude to obtain an outside air temperature that is less conducive to icing.
3. Pull cabin heat control full out and open defroster outlets to obtain maximum windshield defroster airflow. Adjust cabin air control to get maximum defroster heat and airflow.
4. Watch for signs of engine-related icing conditions. An unexplained loss in engine speed could be caused by ice blocking the air intake filter, or, in extremely rare instances, ice completely blocking the fuel injection air reference tubes. Change the throttle position to obtain maximum RPM. This may require either advancing or retarding the throttle, dependent on where ice has accumulated in the system. Adjust mixture, as required, for maximum RPM.
5. Plan a landing at the nearest airport. With an extremely rapid ice build up, select a suitable "off airport" landing site.
6. With an ice accumulation of 1/4 inch or more on the wing leading edges, be prepared for significantly higher stall speed and a longer landing roll.
7. Leave wing flaps retracted. With a severe ice build up on the horizontal tail, the change in wing wake airflow direction caused by wing flap extension could

result in a loss of elevator effectiveness.
8. Open left window and, if practical, scrape ice from a portion of the windshield for visibility in the landing approach.
9. Perform a landing approach using a forward slip, if necessary, for improved visibility.
10. Approach at 65 to 75 KIAS depending upon the amount of the accumulation.
11. Perform a landing in level attitude.
STATIC SOURCE BLOCKAGE
(Erroneous Instrument Reading Suspected)
1. Static Pressure Alternate Source Valve -- PULL ON.
2. Airspeed -- Consult appropriate calibration tables in Section 5.
LANDING WITH A FLAT MAIN TIRE
1. Approach -- NORMAL.
2. Wing Flaps -- 30°.
3. Touchdown -- GOOD MAIN TIRE FIRST, hold airplane off flat tire as long as possible. with aileron control.
4. Directional Control -- MAINTAIN using brake on good wheel as required.
LANDING WITH A FLAT NOSE TIRE
1. Approach -- NORMAL.
2. Flaps -- AS REQUIRED.
3. Touchdown -- ON MAINS, hold nose wheel off the ground as long as possible.
4. When nose wheel touches down, maintain full up elevator as airplane slows to stop.
ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS
AMMETER SHOWS EXCESSIVE RATE OF CHARGE
(Full Scale Deflection)
1. Alternator -- OFF.
WITH THE ALTERNATOR SIDE OF THE MASTER SWITCH OFF,
COMPASS DEVIATIONS OF AS MUCH AS 25° MAY OCCUR.
2. Nonessential Electrical Equipment -- OFF.
3. Flight -- TERMINATE as soon as practical.
LOW VOLTAGE ANNUNCIATOR (VOLTS) ILLUMINATES DURING
FLIGHT (Ammeter Indicates Discharge)
NOTE
Illumination of "VOLTS" on the annunciator panel may occur during low RPM conditions with an electrical load on the system such as during a low RPM taxi. Under these conditions, the annunciator will go out at higher RPM. The master switch need not be recycled since an overvoltage condition has not occurred to deactivate the alternator system.
1. Avionics Master Switch -- OFF.

2. Alternator Circuit Breaker (ALT FLD) -- CHECK IN.
3. Master Switch -- OFF (both sides).
4. Master Switch -- ON.
5. Low Voltage Annunciator (VOLTS) -- CHECK OFF.
6. Avionics Master Switch -- ON.
If low voltage annunciator (VOLTS) illuminates again:
7. Alternator-- OFF.
8. Nonessential Radio and Electrical Equipment -- OFF.
Flight -- TERMINATE as soon as practical
EXECUTING A 180° TURN IN CLOUDS
Upon inadvertently entering the clouds, an immediate plan should be made to turn back as follows:
1. Note the compass heading.
2. Using the clock, initiate a standard rate left turn, holding the turn coordinator symbolic airplane wing opposite the lower left index mark for 60 seconds. Then roll back to level flight by leveling the miniature airplane.
3. Check accuracy of the turn by observing the compass heading which should be the reciprocal of the original heading.
4. If necessary, adjust heading primarily with skidding motions rather than rolling motions so that the compass will read more accurately.
5. Maintain altitude and airspeed by cautious application of elevator control. Avoid over controlling by keeping the hands off the control wheel as much as possible and steering only with rudder.
EMERGENCY DESCENT THROUGH CLOUDS
If conditions prevent return to VFR flight using a 180° turn, a descent through a cloud deck to VFR conditions may be appropriate. If possible, obtain radio clearance for an emergency descent through clouds. To guard against a spiral dive, choose an easterly or westerly heading to minimize compass card swings due to changing bank angles. In addition, keep hands off the control wheel and steer a straight course with rudder control by monitoring the turn coordinator. Occasionally check the compass heading and make minor corrections to hold an approximate course. Before descending into the clouds, set up a stabilized letdown condition as follows:
1. Apply full rich mixture.
2. Reduce power to set up a 500 to 800 ft/min rate of descent.
3. Adjust the elevator trim for a stabilized descent at 70-80 KIAS.
4. Keep hands off the control wheel.
5. Monitor turn coordinator and make corrections by rudder alone.
6. Check trend of compass card movement and make cautious corrections with rudder to stop the turn.
7. Upon breaking out of clouds, resume normal cruising flight.
RECOVERY FROM SPIRAL DIVE IN THE CLOUDS
If a spiral is encountered in the clouds, proceed as follows:

1. Retard throttle to idle position.
2. Stop the turn by using coordinated aileron and rudder control to align the symbolic airplane in the turn coordinator with the horizon reference line.
3. Cautiously apply elevator back pressure to slowly reduce the airspeed to 80
KIAS.
4. Adjust the elevator trim control to maintain an 80 KIAS glide.
5. Keep hands off the control wheel, using rudder control to hold a straight heading.
6. Clear engine occasionally, but avoid using enough power to disturb the trimmed glide.
7. Upon breaking out of clouds, resume normal cruising flight.
SPINS
Should an inadvertent spin occur, the following recovery procedure should be used:
1. RETARD THROTTLE TO IDLE POSITION.
2. PLACE AILERONS IN NEUTRAL POSITION.
3. APPLY AND HOLD FULL RUDDER OPPOSITE TO THE DIRECTION OF
ROTATION.
4. JUST AFTER THE RUDDER REACHES THE STOP, MOVE THE CONTROL
WHEEL BRISKLY FORWARD FAR ENOUGH TO BREAK THE STALL. Full down elevator may be required at aft center of gravity loadings to assure optimum recoveries.
5. HOLD THESE CONTROL INPUTS UNTIL ROTATION STOPS. Premature relaxation of the control inputs may extend the recovery.
AS ROTATION STOPS, NEUTRALIZE RUDDER, AND MAKE A SMOOTH
RECOVERY FROM THE RESULTING DIVE
MAGNETO CHECK
The magneto check should be made at 1800 RPM as follows. Move ignition switch first to R position and note RPM. Next move switch back to BOTH to clear the other set of plugs. Then move switch to the L position, note RPM and return the switch to the
BOTH position. RPM drop should not exceed 150 RPM on either magneto or show greater than 50 RPM differential between magnetos. If there is a doubt concerning operation of the ignition system, RPM checks at higher engine speeds will usually confirm whether a deficiency exists.
An absence of RPM drop may be an indication of faulty grounding of one side of the ignition system or should be cause for suspicion that the magneto timing is set in advance of the setting specified.