Cessna 172S, VH-PXW Quick Reference Handbook
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Last revised: 14 July 2016
© 2016 Airborne Aviation Pty Ltd
www.airborne-aviation.com.au
THIS PAGE INTENTIONALLY LEFT BLANK
Contents
Aircraft Overview
General Information ........................................................................... 1
Equipment and Features ..................................................................... 1
Recency and Restrictions ..................................................................... 1
Panel Photo ....................................................................................... 1
Performance – Specifications
Summary of Aircraft Performance and Specifications .............................. 2
Operating Limitations
Airspeeds .......................................................................................... 3
Power Plant ....................................................................................... 4
Fuel System ...................................................................................... 4
Tyre Pressures ................................................................................... 4
Manoeuvre / Load Limits ..................................................................... 4
Weight & Balance
Weight and Moment Tabulations .......................................................... 5
Loading Arrangements ........................................................................ 6
Centre of Gravity Moment Envelope ...................................................... 7
Sample Configurations ........................................................................ 8
Performance Charts
Takeoff Distances at 2550lbs (MTOW) ................................................... 9
Landing Distances at 2550lbs (MLW) ................................................... 10
Checklists
Normal Operations ............................................................................ 11
Emergency Operations ....................................................................... 22
Resources
Briefings .......................................................................................... 29
Useful Information ............................................................................ 32
NOTICE
The information and figures contained in this booklet are
to be used for general purposes only. This document is
not a substitute for the approved aeroplane flight manual.
Report errors to webmaster@airborne-aviation.com.au
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Aircraft Overview
This C172 is one of our new generation Cessna’s.
It is used as our primary training aeroplane for the Private Pilot Licence.
With a cruise speed of 120kts it is ideal for cross-country navigation
exercises.
Equipment & Features
- Garmin G1000 Avionics Suite (TSO-146 GPS)
- GFC700 integrated Auto-pilot
- Leather Seats
- Airbags
Recency & Restrictions
Private Hire: Company Check Flight.
Dual training: No restrictions.
Recency: Flown any aircraft in the last 45 days
or at the discretion of the CFI.
Panel Photo
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Performance – Standard Specifications
SPEED:
Maximum at Sea Level ....................................................... 126 KTS
Cruise, 75% Power at 8500 FT ............................................ 124 KTS
CRUISE:
Using recommended lean mixture with fuel allowance for engine start, taxi,
takeoff, climb and 45 minutes reserve.
75% Power at 8500 Ft ................................................ Range 518NM
53 Gallons Usable Fuel .............................................. Time 4.25 HRS
RATE OF CLIMB AT SEA LEVEL ................................................... 730 FPM
SERVICE CEILING .................................................................. 14,000 FT
TAKEOFF PERFORMANCE:
Ground Roll ......................................................................... 960 FT
Total Distance Over 50 Ft. Obstacle ...................................... 1630 FT
LANDING PERFORMANCE:
Ground Roll ......................................................................... 575 FT
Total Distance Over 50 Ft. Obstacle ...................................... 1335 FT
STALL SPEED:
Flaps Up, Power Off ............................................................ 48 KIAS
Flaps Down, Power Off ........................................................ 40 KIAS
MAXIMUM WEIGHT:
Ramp ............................................................ 2558 LBS / 1162.7 KG
Takeoff.......................................................... 2550 LBS / 1159.1 KG
Landing ......................................................... 2550 LBS / 1159.1 KG
BASIC EMPTY WEIGHT .......................................... 1747.8 LBS / 794.5 KG
MAXIMUM USEFUL LOAD ........................................ 802.2 LBS / 364.6 KG
BAGGAGE ALLOWANCE ............................................... 120 LBS / 54.5 KG
WING LOADING ............................................................... 14.7 Lbs/Sq Ft
POWER LOADING ................................................................ 14.2 Lbs/HP
FUEL CAPACITY ....................................................... 56 GAL / 213 LITRES
OIL CAPACITY .............................................................................. 8 QTS
ENGINE: Textron Lycoming ................................................... IO-360-L2A
180 BHP at 2700 RPM
PROPELLER: Fixed Pitch, Diameter ................................................. 76 IN
The above performance figures are based on aeroplane weights at 2550
pounds, standard atmospheric conditions, level hard-surface dry runways
and no wind. They are calculated values derived from flight tests
conducted by the Cessna Aircraft Company under carefully documented
conditions and will vary with individual aeroplanes and numerous other
factors affecting flight performance.
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Operating Information
AIRSPEEDS - NORMAL OPERATIONS
Takeoff:
Normal Climb Out ..........................................................75–85 KIAS
Short Field Takeoff, Flaps 10º, Speed at 50 ft ........................ 56 KIAS
Enroute Climb, Flaps Up:
Normal, sea level ........................................................... 75-85 KIAS
Normal, 10,000 Feet ...................................................... 70-80 KIAS
Best Rate-of-Climb, Sea level ............................................... 74 KIAS
Best Rate-of-Climb, 10,000 Feet ........................................... 72 KIAS
Best Angle-of-Climb, Sea level ............................................. 62 KIAS
Best Angle-of-Climb, 10,000 Feet ......................................... 67 KIAS
Landing Approach:
Normal Approach Flaps Up ............................................. 65–75 KIAS
Normal Approach, Flaps FULL ......................................... 60–70 KIAS
Short Field Approach, Flaps FULL .......................................... 61 KIAS
Balked Landing:
Maximum Power, Flaps 20º .................................................. 60 KIAS
V-Speeds:
Vne (never exceed) .......................................................... 163 KIAS
Vno (Maximum structural cruising speed) ............................ 140 KIAS
Vfe (Flaps 10°) ................................................................. 110 KIAS
Vfe (Flaps 20°) ................................................................... 85 KIAS
Vfe (Flaps 30°) ................................................................... 85 KIAS
Maximum Recommended Turbulent Air Penetration Speed:
2550 Lbs ......................................................................... 105 KIAS
2200 Lbs ........................................................................... 98 KIAS
1900 lbs ............................................................................ 90 KIAS
Maximum Demonstrated Crosswind Velocity:
Takeoff or landing ............................................................ 15 KNOTS
Stall Speed:
Flaps Up, Power Off ............................................................ 48 KIAS
Flaps Down, Power Off ........................................................ 40 KIAS
Unless otherwise noted, the speeds listed above are based on a maximum
weight and may be used for any lesser weight. To achieve the performance
specified in the performance section for take-off distance of the aircraft
approved flight manual, the speed appropriate to the particular weight
must be used.
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POWER PLANT
Oil Type ................................................ Ashless Dispersant 100 (SAE 50)
Oil Quantities:
Maximum ............................................................................. 8 QTS
Minimum (Company minimum) ............................................... 5 QTS
Engine operating limits including RPM, pressures, and temperatures, can be
found by referring to the green arcs and red lines on applicable gauges.
Detailed information can also be found in the approved flight manual.
FUEL SYSTEM
Total Capacity ..................................................... 213 litres / 56.0 gallons
Total Usable ...................................................... 201 litres / 53.0 gallons
Fuel Consumption per hour.................................... 40 litres / 10.5 gallons
Approved Fuels:
Option A ......................................... 100LL Grade Aviation Fuel (Blue)
Option B .......................................... 100 Grade Aviation Fuel (Green)
TYRE PRESSURES
Nose wheel ................................................................................. 45 PSI
Main wheels ............................................................................... 38 PSI
MANOEUVRE / LOAD LIMITS
This aeroplane is certified in both the normal and utility categories. Refer to
the approved flight manual for specific details on permitted manoeuvres
and limitations in the utility category.
Normal Category - Flight Load Factors (MTOW 2550 lbs):
Flaps Up ................................................................... +3.8g, -1.52g
Flaps Down ........................................................................... +3.0g
Utility Category - Flight Load Factors (MTOW 2200 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.
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Weight and Balance
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CALCULATING THE MOMENT
The moment is the weight multiplied by the C.G. arm, divided by 1000.
Example: Pilot and front passenger weigh 340lbs, the arm is 37”.
Answer: (340 x 37) / 1000 = 12.58
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SAMPLE CONFIGURATIONS
Listed in the table below are the maximum passenger/baggage weights for
various endurances.
The purpose of this table is to allow you to quickly determine the maximum
load permissible on a particular length flight.
WARNING
THIS TABLE IS PROVIDED AS A GUIDE ONLY. THE AEROPLANE
NEEDS TO BE LOADED WITHIN THE SPECIFIED CENTRE OF
GRAVITY MOMENT ENVELOPE FOUND IN THE APPROVED FLIGHT
MANUAL.
MMAAXXIIMMUUMM PPAASSSSEENNGGEERR && BBAAGGGGAAGGEE WWEEIIGGHHTTS
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- 75% cruise power @ 6000 FT - 10.5 gal / 40 litres per hour
- 45 minute reserve fuel included in flight fuel.
- Taxi fuel not included, add approximately 5 litres.
1.0 Hour Flight
Flight Fuel Required: 18.4 gals / 70.0 litres / 110.9 lbs
Pax / Baggage: 691.3 lbs / 314.2 kg
1.5 Hour Flight
Flight Fuel Required: 23.7 gals / 90.0 litres / 142.6 lbs
Pax / Baggage: 659.1 lbs / 299.6 kg
2.0 Hour Flight
Flight Fuel Required: 29.9 gals / 110.0 litres / 174.2 lbs
Pax / Baggage: 628.0 lbs / 285.4 kg
3.0 Hour Flight
Flight Fuel Required: 39.5 gals / 150.0 litres / 237.6 lbs
Pax / Baggage: 564.6 lbs / 256.6 kg
4.0 Hour Flight
Flight Fuel Required: 50.0 gals / 190.0 litres / 301.0 lbs
Pax / Baggage: 501.2 lbs / 227.8 kg
4.3 Hour Flight (Full fuel)
Flight Fuel Required: 53.0 gals / 201.4 litres / 319.0 lbs
Pax / Baggage: 483.2 lbs / 219.6 kg
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