Skyfox Gazelle Handling Notes

Transcription

Pilots Operating
Handbook
Skyfox Gazelle CA25N
Warning
These handling notes are to be used for general information purposes only.
This information cannot be used as a substitute for the actual aircraft flight manual.
Contents
Contents ................................................................................................................................................................. 2
PERFORMANCE - SPECIFICATIONS ................................................................................................................ 3
DESCRIPTIVE DATA ........................................................................................................................................... 4
INTRODUCTION.............................................................................................................................................. 4
INTRODUCTION.............................................................................................................................................. 5
ENGINE ............................................................................................................................................................. 5
PROPELLER ...................................................................................................................................................... 5
FUEL................................................................................................................................................................... 6
OIL ..................................................................................................................................................................... 6
STANDARD AIRPLANE WEIGHTS ............................................................................................................... 6
NORMAL OPERATIONS ..................................................................................................................................... 7
AIRSPEEDS FOR NORMAL OPERATIONS................................................................................................... 7
PREFLIGHT INSPECTION .............................................................................................................................. 8
TAXIING .......................................................................................................................................................... 10
PRE-TAKEOFF ................................................................................................................................................ 11
TAKEOFF......................................................................................................................................................... 11
LANDING ........................................................................................................................................................ 11
LIMITATIONS..................................................................................................................................................... 12
AIRSPEED LIMITATIONS ............................................................................................................................. 12
AIRSPEED INDICATOR MARKINGS .......................................................................................................... 12
POWER PLANT LIMITATIONS ................................................................................................................... 12
CENTRE OF GRAVITY LIMITS .................................................................................................................... 13
FLIGHT LOAD FACTOR LIMITS ................................................................................................................. 13
EMERGENCIES ................................................................................................................................................... 14
AIRSPEEDS FOR EMERGENCY OPERATION ........................................................................................... 14
FIRES ................................................................................................................................................................ 14
FORCED LANDINGS...................................................................................................................................... 15
ROUGH ENGINE OPERATION OR LOSS OF POWER .............................................................................. 16
SYSTEMS EMERGENCIES ............................................................................................................................. 16
PERFORMANCE ................................................................................................................................................. 17
TAKEOFF DISTANCE .................................................................................................................................... 17
CLIMB PERFORMANCE................................................................................................................................ 17
CRUISE PERFORMANCE .............................................................................................................................. 18
LANDING DISTANCE .................................................................................................................................... 18
LOADING ............................................................................................................................................................ 19
Disclaimer
These handling notes have been prepared from the information manuals supplied by aeroplane
manufacturer and are to be used for general information purposes only. The information cannot be used as
a substitute for the actual aircraft flight manual.
Page 2 of 19
PERFORMANCE - SPECIFICATIONS
SPEED:
Cruise, 5,000 RPM at 3,500 Ft
75 Knots
70 Knots
57 Knots
A fuel allowance of 5 litres has been made for taxi, climb and descent. 20 NM has been
CRUISE:
added to the range for climb and descent. No reserve is included.
4,800 RPM at 3,500 Ft
4,200 RPM at 3,500 Ft
RATE OF CLIMB AT SEA LEVEL (520kg, ISA Conditions)
SERVICE CEILING
MAXIMUM ATMOSPHERIC OPERATING TEMPERATURE
TAKEOFF PERFORMANCE
Total Distance Over 50-Ft Obstacle
LANDING PERFORMANCE:
Total Distance Over 50-Ft Obstacle
STALL SPEED (KIAS):
Power Off, Level Flight, 520 Kg
Power Off, 30° Bank, 520 Kg
MAXIMUM DEMONSTRATED CROSSWIND COMPONENT
MAXIMUM WEIGHT:
Takeoff or Landing
STANDARD EMPTY WEIGHT
MAXIMUM USEFUL LOAD
BAGGAGE ALLOWANCE
MINIMUM PILOT WEIGHT
FUEL CAPACITY:
Total Usable
Minimum fuel for take off
Total Wing Tanks
Collector Tank
Range
Time
Range
Time
290 NM
3 Hours 39 Min
279 NM
4 Hours 15 Min
510 FPM
10,000 Feet
39°C
492 Meters
354 Meters
43.0 Knots
45.9 Knots
20.0 Knots
520 Kg
335 Kg
185 Kg
10 Kg
55 Kg
48.0 Litres
10 Litres per tank
52.0 Litres
3.75 Litres
NOTE: Collector tank fuel is not gauged, therefore it is not usable. However, it provides 16
minutes of operation at 75% cruise power when the wing fuel tank gauges indicates empty.
OIL CAPACITY
Maximum
Minimum Operating
ENGINE: Bombardier (Rotax) 912 A1, A2 or A3
81 BHP at 5,800 RPM
PROPELLER: Fixed Pitch, Diameter
2.5 Litres
2.0 Litres
1727 mm
The above performance figures are based on the indicated weights, standard atmospheric conditions, level
hard-surface dry runways and no wind. They are calculated values derived from flight tests conducted by the
aeroplane manufacturer under carefully documented conditions and will vary with individual airplanes and
numerous factors affecting flight performance.
Page 3 of 19
DESCRIPTIVE DATA
Wing Span 9.49m
Tread Width (Mains) 1.9m
Cabin Width 1.02m
Overall Length 5.63m
Chord Length (including
ailerons) 1.067m
Height 2.32m
Figure 1 – Overall Dimensions
Page 4 of 19
INTRODUCTION
The Skyfox Gazelle is a single engine, two place, nose-wheel, high wing monoplane. It is intended as a
light training aircraft for the initial stages of training. The aircraft is equipped for day VFR operations only.
The fuselage construction is chromium-molybdenum steel structure, covered with a poly fibre fabric
which is heat-shrunk for a tight and smooth finish, prior to painting. This construction is also used on the
empennage. The engine cowls, both upper and lower, are constructed in a fire resistant fibre-glass.
The main wings, have two extruded aluminium spars (with an internal web), separated by ten marine
plywood ribs in each wing. The forward spar also forms the leading edge. The wing is covered with a poly
fibre, the same as the fuselage, and heat shrunk before painting. There is a slight wash-out towards the tips,
to reduce the stall tendency at the tips, together with fibreglass shaped wing tips, curled downward, to also
reduce the stall tendency, and enable better control in low speed flight.
The main landing gear is fixed and shock absorption is achieved with rubber-in-shear on the diagonal leg
braces and low pressure tyres. The Nose Wheel is also a fixed gear and comprises shock absorption
through a series of rubber discs inside the leg.
The electrical system consists of a 12 volt, sealed gell battery, the power of which is controlled by a master
solenoid which is activated by the master switch on the instrument panel. An alternator is incorporated in
the engine with an emergency isolation switch on the instrument panel. NOTE: The Alternator MUST
NOT be switched off, except in an emergency.
ENGINE
Number of Engines: 1.
Engine Manufacturer: Bombardier (Rotax) 912 A1, A2 or A3.
Maximum Horsepower Rating and Engine Speed:
Takeoff: 81 BHP at 5,800 RPM. (Maximum 5 minutes)
Continuous: 79 BHP at 5,500 RPM.
Maximum Cylinder Head Temperature: 150°C
Maximum Oil Temperature: 140°C
PROPELLER
Propeller Manufacturer: Allsize Aviation.
Propeller Model Number: CHP1-1
Number of Blades: 2.
Propeller Diameter; 1,727 mm
Propeller Type: Fixed pitch.
Page 5 of 19
FUEL
The CA25N Skyfox has two fuel tanks, one in each wing. Each fuel tank has a capacity of 26 litres and is
cross-vented to the other. The fuel is gravity fed through a finger filter at each tank outlet into a 3.75 litre
collector tank, located behind the seat. From the collector tank. the single fuel line passes through the
electric fuel pump (also behind the seat), to the Fuel Cock located in the centre console in the floor
between the pilots. From the fuel cock the fuel line passes through the firewall to the fuel filter
(gascolator), and up to the engine driven fuel pump. A Low Fuel Pressure warning light is located on the
instrument panel, which indicates low pressure at the carburettor inlet. Fuel drains are located in each
tank, under the Collector tank and at the gascolator.
Approved Fuel Grades (and Colours):
MOGAS (Super) Premium grade gasoline to DIN 51600, O-NORM C1103, EURO RON 95
MOGAS (Unleaded) Premium grade gasoline to DIN 51607, O-NORM C1101, EURO RON 90
100LL Grade Aviation Fuel (Blue).
Fuel Capacity:
Total Fuel Capacity
Total Usable
Minimum fuel for take off
Total Wing Tanks
Collector Tank
55.75 Litres
48.0 Litres
10 Litres per tank
52.0 Litres
3.75 Litres
NOTE: Collector tank fuel is not gauged, therefore it is not usable. However, it provides 16
minutes of operation at 75% cruise power when the wing fuel tank gauges indicates empty.
OIL
Oil Grade (Specification):
Recommended Viscosity for Temperature Range:
-5°C to +40°C, use SAE 20W-50 or SAE 20W-40
-15°C to +40°C, use SAE 15W-40
-25°C to +40°C, use SAE 10W-40
Oil Capacity:
Maximum: 2.5 Litres.
Minimum for normal operations: 2.0 Litres.
Must indicate between MAX and MIN mark on the oil tank dip stick.
STANDARD AIRPLANE WEIGHTS
Standard Empty Weight:
Maximum Takeoff Weight:
Maximum Landing Weight:
Maximum Useful Load:
Maximum Baggage Compartment:
Minimum Pilot Weight:
335 Kg
520 Kg
520 Kg
185 Kg
10 Kg
55 kg
Page 6 of 19
NORMAL OPERATIONS
AIRSPEEDS FOR NORMAL OPERATIONS
Unless otherwise noted, the following speeds are based on a maximum weight of 520kg and may be used
for any lesser weight.
Takeoff:
Normal Climb Out
Short Field Takeoff, Speed at 50 Feet
55 Knots
52 Knots
Climb:
Normal
Best Rate of Climb, Sea Level.
Best Angle of Climb, Sea Level thru 10,000 Feet
55-60 Knots
55 Knots
52 Knots
Landing Approach:
Normal Approach:
Short Field Approach:
60-55 Knots
52 Knots
Balked Landing:
Maximum Power
55 Knots
Maximum Manoeuvring Speed:
80 Knots
Do not make full or abrupt control movements above this speed.
Maximum Demonstrated Crosswind Component
20 Knots
Airspeed Indicator Markings:
Green Arc
Yellow Arc
Red Line
43 to 86 Knots
86 to 93 Knots
93 Knots
Page 7 of 19
PREFLIGHT INSPECTION
While carrying out the following inspection, watch for holes in the fabric or obvious
damage to the airframe.
1) CABIN
a) Pilot's Operating Handbook -- AVAILABLE IN THE AIRPLANE.
b) Throttle Lock -- REMOVE.
c) Master Switch -- OFF.
d) Alternator Switch -- ON.
e) CDI Switches -- BOTH OFF.
f) Fuel Shutoff Valve -- ON.
g) Fuel Quantity Indicators -- CHECK QUANTITY.
h) Seat Belts and Shoulder Harnesses -- CHECK condition and security.
i) Seat Cushions -- SECURE.
2) NOSE
a) Propeller and Spinner -- CHECK for nicks and security.
b) Carburettor Air Filter -- CHECK for restrictions by dust or other foreign matter.
c) Landing Light(s) -- CHECK for condition and cleanliness.
d) Nose Wheel Strut and Tire -- CHECK for proper tyre inflation and signs of excessive wear. CHECK
oleo leg protruding 50 mm or more.
e) Coolant level -- CHECK, Overflow bottle should be approximately half full.
f) Engine Oil Level -- CHECK, do not operate with less than two litres. Oil must be between Max and
Min marks.
3) LEFT WING
a) Front Wing Clevis Pin -- CHECK is in and safety pinned.
b) Fuel Filler Cap -- SECURE and vent clear.
c) Main Wheel Tire -- CHECK for proper inflation and signs of excessive wear.
d) Main Wheel Brake Pads -- CHECK, min 2.5mm thick
e) Left Door -- CHECK for cracks, distortion.
f) Left Bottom Wing Strut -- CHECK bolt for nut and split pin.
4) LEFT WING Leading Edge
a) Left Jury Struts -- CHECK for security and deformity.
b) Left Top Wing Strut -- CHECK attachments for security.
c) Pitot Tube -- REMOVE cover and check opening for stoppage.
d) Stall Warning -- CHECK.
e) Wing Tie-Down -- DISCONNECT.
5) LEFT WING Trailing Edge
a) Wing Tip -- CHECK for damage.
b) Aileron -- CHECK freedom of movement and security. Lightly twist the aileron at each hinge
station checking for integrity.
Page 8 of 19
c) Before first flight of day and after each refuelling, use sampler cup and drain small quantity of fuel
from fuel tank sump quick-drain valve to check for water, sediment and proper fuel grade.
6) FUSELAGE Left Side
a) Turtle Deck Camlocks -- CHECK for security.
b) Aileron Linkages -- CHECK for excessive play and deformity.
c) Baggage Hatch -- CHECK for maximum 10kg load and hatch locked.
d) Left Static Vent -- CHECK for blockages.
7) EMPENNAGE
a) Rudder Cables -- CHECK attachment to rudder horn for security. CHECK exit point and fairing for
excessive wear.
b) Elevator and Rudder Hinge Pins -- CHECK for wear and split pins.
c) Tail Tie-Down -- DISCONNECT.
d) Control Surfaces -- CHECK freedom of movement and for binding or warping.
8) FUSELAGE Right Side
a) Left Static Vent -- CHECK for blockages.
b) Aileron Linkages -- CHECK for excessive play and deformity.
c) Turtle Deck Camlocks -- CHECK for security.
9) RIGHT WING Trailing Edge
a) Before first flight of day and after each refuelling, use sampler cup and drain small quantity of fuel
from fuel tank sump quick-drain valve to check for water, sediment and proper fuel grade.
b) Drain 20ml fuel from collector tank drain cock under the aircraft and check for sediment and water.
c) Aileron -- CHECK freedom of movement and security. Lightly twist the aileron at each hinge
station checking for integrity.
d) Wing Tip -- CHECK for damage.
10) RIGHT WING Leading Edge
a) Right Jury Struts -- CHECK for security and deformity.
b) Right Top Wing Strut -- CHECK attachments for security.
c) Wing Tie-Down -- DISCONNECT.
11) RIGHT WING
a) Front Wing Clevis Pin -- CHECK is in and safety pinned.
b) Fuel Filler Cap -- SECURE and vent clear.
c) Main Wheel Tire -- CHECK for proper inflation and signs of excessive wear.
d) Main Wheel Brake Pads -- CHECK, min 2.5mm thick
e) Right Door -- CHECK for cracks, distortion.
f) Right Bottom Wing Strut -- CHECK bolt for nut and split pin.
g) Drain 20ml fuel from filter drain cock under the engine and check for sediment and water.
12) WINDSCREEN and DOORS
a) Clean if required.
Page 9 of 19
TAXIING
When taxiing, it is important that speed and use of brakes be held to a minimum and that all controls are
utilized (see Taxiing Diagram below) to maintain directional control and balance.
The carburettor heat control knob should be pushed full in during all ground operations unless heat is
absolutely necessary. When the knob is pulled out to the heat position, air entering the engine is not
filtered.
Taxiing over loose gravel or cinders should be done at low engine speed to avoid abrasion and stone
damage to the propeller tips.
The nose wheel is designed to automatically centre straight ahead when the nose strut is fully extended. In
the event the nose strut is over-inflated and the airplane is loaded to a rearward centre of gravity position,
it may be necessary to partially compress the strut to permit steering. This can be accomplished prior to
taxiing by depressing the airplane nose (by hand) or during taxi by sharply applying brakes.
Figure 5 – Taxiing Diagram
Page 10 of 19
PRE-TAKEOFF
NORMAL RUNUPS
1. Brakes -- FULL ON.
2. Throttle -- OPEN to 3850 RPM.
3. Test Left and Right CDI’s separately by switching off each in turn. Engine should continue to run
with only a small RPM drop (up to 300 RPM is acceptable with the maximum differential 115
RPM).
4. Carburettor Heat -- FULL ON. Check for a small RPM drop, then turn off heat.
5. Throttle -- CHECK idle, 1600 – 1800 RPM.
TAKEOFF
NORMAL TAKEOFF
6. Carburettor Heat -- COLD.
7. Throttle -- FULL OPEN.
8. Elevator Control -- LIFT NOSE WHEEL at 45 KIAS to leave ground at 50 KIAS.
9. Climb Speed -- 55-60 KIAS.
SHORT FIELD TAKEOFF
1. Carburettor Heat -- COLD.
2. Brakes -- APPLY.
4. Brakes -- RELEASE.
5. Elevator Control -- LIFT NOSE WHEEL at 45 KIAS to leave ground at 50 KIAS.
6. Climb Speed -- 52 KIAS (until all obstacles are cleared).
LANDING
NORMAL LANDING
1. Airspeed -- 55-60 KIAS.
2. Touchdown -- MAIN WHEELS FIRST.
3. Landing Roll -- LOWER NOSE WHEEL GENTLY.
4. Braking -- MINIMUM REQUIRED.
SHORT FIELD LANDING
1. Airspeed -- MAINTAIN 52 KIAS.
2. Power -- REDUCE to idle as obstacle is cleared.
3. Touchdown -- MAIN WHEELS FIRST.
4. Brakes -- APPLY HEAVILY.
BALKED LANDING (GO-AROUND)
2. Carburetor Heat -- COLD.
3. Airspeed -- 55-60 KIAS.
Page 11 of 19
LIMITATIONS
AIRSPEED LIMITATIONS
SPEED
KIAS
VNE
Never Exceed Speed
93
VNO
Maximum Structural
Cruising Speed
86
VA
Manoeuvring Speed:
80
REMARKS
Do not exceed this speed in any
operation.
Do not exceed this speed except in
smooth air, and then only with
caution.
Do not make full or abrupt control
movements above this speed,
because under certain conditions
the aircraft may be overstressed by
full control movements.
AIRSPEED INDICATOR MARKINGS
MARKING
KIAS VALUE
OR RANGE
SIGNIFICANCE
Green Arc
43-86
Normal Operating Range.
Lower limit is maximum weight Vs at
most forward C.G. with flaps retracted.
Upper limit is maximum structural
cruising speed.
Yellow Arc
86 - 93
Operations must be conducted with
caution and only in smooth air.
93
Maximum speed for all operations.
Red Line
POWER PLANT LIMITATIONS
Engine Manufacturer: Bombardier (Rotax) 912 A1, A2 or A3.
Maximum Horsepower Rating and Engine Speed:
Takeoff: 81 BHP at 5,800 RPM. (Maximum 5 minutes)
Continuous: 79 BHP at 5,500 RPM.
Maximum Cylinder Head Temperature: 150°C
Maximum Oil Temperature: 140°C
Page 12 of 19
Oil Pressure, Minimum: 150 Kpa.
Maximum: 500 Kpa.
Oil Grade (Specification):
Recommended Viscosity for Temperature Range:
-5°C to +40°C, use SAE 20W-50 or SAE 20W-40
-15°C to +40°C, use SAE 15W-40
-25°C to +40°C, use SAE 10W-40
CENTRE OF GRAVITY LIMITS
Centre of Gravity Range:
Forward: 230mm aft of datum at 350kg, with straight line variation to 280mm aft of datum at 520kg.
Aft: 320mm aft of datum at all weights.
Reference Datum: Wing Leading Edge.
FLIGHT LOAD FACTOR LIMITS
Maximum manoeuvring load factor at 520kg:
+3.8g and -1.9g
Page 13 of 19
EMERGENCIES
AIRSPEEDS FOR EMERGENCY OPERATION
Engine Failure After Takeoff
Maximum Glide
55 KIAS
55 KIAS
Precautionary Landing With Engine Power
55 KIAS
Landing Without Engine Power
50 KIAS
FIRES
DURING START ON GROUND
Cranking -- CONTINUE, to get a start which would suck the flames and accumulated fuel through the
carburettor and into the engine.
Fuel Selector -- OFF
If engine starts:
1. Power -- 3000 RPM for at least two minutes.
2. Engine -- SHUTDOWN and inspect for damage.
If engine fails to start:
1. Cranking -- CONTINUE for one minute in an effort to obtain a start.
2. Fire Extinguisher -- OBTAIN (have ground attendants obtain if not installed).
3. Engine -- SECURE.
4. Master Switch -- OFF.
5. Ignition Switch -- OFF.
6. Fuel Selector -- OFF.
7. Fire -- EXTINGUISH using fire extinguisher, wool blanket, or dirt.
8. Fire Damage -- INSPECT, repair damage or replace damaged components or wiring before
conducting another flight.
ENGINE FIRE IN FLIGHT
1. Throttle -- IDLE.
2. Fuel Selector -- OFF'.
4. CDI’s -- OFF.
5. Cabin Heat -- OFF.
6. Airspeed -- 55 KIAS (If fire is not extinguished, increase glide speed to find an airspeed which will
provide an incombustible mixture).
7. Forced Landing -- EXECUTE (as described in Emergency Landing • Without Engine Power).
ELECTRICAL FIRE IN FLIGHT
2. Alternator Switch -- OFF.
3. Fire Extinguisher -- ACTIVATE (if available).
Page 14 of 19
WARNING
After discharging an extinguisher within a closed cabin, ventilate the cabin.
If fire appears out and electrical power is necessary for continuance of flight:
1. Master Switch -- ON.
2. Circuit Breakers -- CHECK for faulty circuit, do not reset.
3. Radio/Electrical Switches -- ON one at a time, with delay after each until short circuit is localized.
4. Vents/Cabin Air/Heat -- OPEN when it is ascertained that fire is completely extinguished.
CABIN FIRE
2. Cabin Heat -- CLOSED (to avoid drafts).
3. Fire Extinguisher -- ACTIVATE (if available).
WARNING
After discharging an extinguisher within a closed cabin, ventilate the cabin.
Land the airplane as soon as possible to inspect for damage.
FORCED LANDINGS
EMERGENCY LANDING WITHOUT ENGINE POWER
1. Airspeed -- 55 KIAS. This speed is higher than the best Lift/Drag speed to enable better control
during approach and landing. For greatest glide range, use 50 KIAS in still air.
2. Fuel Shutoff Valve -- OFF.
3. CDI’s -- OFF.
5. Doors -- UNLATCH PRIOR TO TOUCHDOWN.
6. Touchdown -- SLIGHTLY TAIL LOW.
PRECAUTIONARY LANDING WITH ENGINE POWER
1. Airspeed -- 60 KIAS.
2. Selected Field -- FLY OVER, noting terrain and obstructions, maintaining a safe altitude and
airspeed.
3. Radio and Electrical Switches -- OFF.
4. Airspeed -- 55 KIAS.
6. Doors -- UNLATCH PRIOR TO TOUCHDOWN.
7. Touchdown -- SLIGHTLY TAIL LOW.
8. CDI’s -- OFF.
Page 15 of 19
ROUGH ENGINE OPERATION OR LOSS OF POWER
CARBURETTOR ICING
A gradual loss of RPM and eventual engine roughness may result from the formation of carburettor ice. To
clear the ice, apply full throttle and pull the carburettor heat knob full out until the engine runs smoothly;
then remove carburettor heat and readjust the throttle.
SPARK PLUG FOULING
A slight engine roughness in flight may be caused by one or more spark plugs becoming fouled by carbon
or lead deposits. This may be verified by momentarily switching each CDI off in turn. An obvious power
loss in single ignition operation is evidence of spark plug or magneto trouble.
If the problem does not clear up in several minutes, proceed to the nearest airport for repairs with both
CDI’s on unless extreme roughness dictates the use of a single ignition position.
MAGNETO MALFUNCTION
A sudden engine roughness or misfiring is usually evidence of magneto problems. Switching from BOTH to
either L or R ignition switch position will identify which magneto is malfunctioning. Select different
power settings to determine if continued operation on BOTH magnetos is practicable. If not, switch to the
good magneto and proceed to the nearest airport for repairs.
LOW OIL PRESSURE
If low oil pressure is accompanied by normal oil temperature, there is a possibility the oil pressure gage or
relief valve is malfunctioning. A leak in the line to the gage is not necessarily cause for an immediate
precautionary landing because an orifice in this line will prevent a sudden loss of oil from the engine sump.
However, a landing at the nearest airport would be advisable to inspect the source of trouble.
If a total loss of oil pressure is accompanied by a rise in oil temperature, there is good reason to suspect an
engine failure is imminent. Reduce engine power immediately and select a suitable forced landing field.
Use only the minimum power required to reach the desired touchdown spot.
SYSTEMS EMERGENCIES
EXCESSIVE RATE OF CHARGE
After engine starting and heavy electrical usage at low engine speeds the battery condition will be low
enough to accept above normal charging during the initial part of a flight. However, after ten minutes of
cruising flight, the Voltmeter should be indicating less than fifteen volts. If the charging rate were to
remain above this value on a long flight, the battery would overheat and may rupture. Turn OFF the
ALTERNATOR switch. The flight should be terminated as soon as practicable.
TOTAL ELECTRICAL FAILURE
If a total electric failure occurs in flight, the engine will continue running but the following emergency
procedures should be carried out immediately.
Check Master switch is ON and Alternator switch ON. Switch OFF all unnecessary electrical equipment.
Land as soon as practicable.
Page 16 of 19
PERFORMANCE
TAKEOFF DISTANCE
The Take-Off data has been taken from Flight Testing and is for Take-Offs made on a Hard, Level Surface
(Bitumen) with zero wind. The Take-Off Distance is given for the Aircraft to reach a height of 15 metres
(50 feet), at the Speed of 55 Knots IAS (approximately 5400 RPM) to be reached at that height.
NOTES:
1. The data in the charts has been computed from Actual Flight Tests with the Aeroplane and Engine
in Good Condition and using average piloting techniques.
2. For every 1 knot of head wind component, the take off distance can be reduced by 5 metres.
3. For every 1 knot of tail wind component, the take off distance required MUST be increased by 15
metres.
4. For every degree Celsius above ISA the take off distance MUST be increased by 4 metres.
5. The take off distance on short wet grass must be increased by 7%.
All up
weight
Sea
Level
1000
feet
2000
feet
3000
feet
4 000
feet
5000
feet
6000
feet
520 Kg
492m
522m
554m
588m
622m
663m
705m
CLIMB PERFORMANCE
The Recommended Climb Speed for the "Gazelle" is 55 knots (IAS) (approximately 5400 RPM). Below is
the Climb Rate (Feet/Min) that can be expected at various Temperatures and Pressure Altitudes at 55 Knots
IAS and 520 Kg aircraft weight.
Altitude
0
1,000
2,000
3,000
4,000
5,000
6,000
7,000
8,000
9,000
10,000
1SA1SA-10
594
525
455
385
333
293
248
210
163
123
80
1SA1SA-5
522
482
410
353
310
264
223
182
138
96
55
1SA
510
438
370
330
285
240
200
155
115
70
30
ISA+5
468
398
345
303
257
215
173
128
88
47
10
1SA+10
428
363
322
275
233
193
150
107
63
23
1SA+15
398
340
296
252
210
168
125
83
43
ISA+20
ISA+20
360
313
272
228
188
144
102
59
22
ISA+25
333
292
246
205
163
120
78
40
Page 17 of 19
CRUISE PERFORMANCE
The table below shows RPM, Fuel Flow (Litres per Hour), TAS, and Total Endurance at a Cruise Density
Altitude of 3,500 Feet. The following table has been produced to facilitate Flight Planning. Fuel Deduction
of Five (5) litres has been made for Taxi, Climb and Descent to determine the Total Endurance. 20 NM has
been added to the range for the Climb and Descent. For planning purposes, the Cruise Fuel is 46.75 Litres.
NOTE: Reserve Fuel must be allowed for.
RPM
IAS
CAS
TAS
5400
5200
5000
4800
4600
4400
4200
4000
82
79
75
70
65
62
57
51
84
81
77
72
67
64
59
53
88
85
80
74
71
67
61
54
Fuel Flow
(lt/hr)
18.2
16.6
13.7
12.8
12.4
11.8
11
6
Total Endurance
Range N.M.
2 Hr. 34 Min
2 Hr. 48 Min
3 Hr. 24 Min.
3 Hr. 39 Min.
3 Hr. 46 Min.
3 Hr. 57 Min
4 Hr. 15 Min.
7 Hr. 47 Min.
246
259
292
290
287
285
279
440
CRUISE
The Recommended Cruise Power Setting is 5,000 RPM (75% power). Fuel Consumption is approximately
13.7 Litres per Hour with a TAS of 80 Knots. (5.83 NM per Litre).
ENDURANCE
For Best Endurance Flying it is recommended to Cruise at 4,000 RPM, which gives an Indicated Airspeed
of 51 Knots. Fuel Flow at this Power Setting is 6 Litres Per Hour.
LANDING DISTANCE
The Landing Distance has been calculated from Test Flight on a hard level surface (Bitumen). The Landing
Distance is from the aircraft at a height of 15 metres (50 Feet), at a speed of 55 Knots (IAS), with the
throttle closed.
LANDING DISTANCE REQUIRED (METRES)
All up
Weight
520 Kg
Sea
Level
354m
1000
feet
375m
2000
feet
386m
3000
feet
397m
4000
feet
410m
5000
feet
422m
6000
feet
435m
1. For every 1 Knot of Head Wind Component, the Landing Distance can be reduced by 5 Metres.
2. For every 1 Knot of Tail Wind Component, the Landing Distance Required MUST be increased by
15 Metres.
3. For every Degree Celsius above ISA the Landing Distance MUST be increased by 4 Metres.
4. Landing Distance on Short Wet Grass MUST be increased by 15%.
Page 18 of 19
LOADING
Standard Empty Weight:
Maximum Takeoff Weight:
Maximum Landing Weight:
Maximum Useful Load:
Maximum Baggage Compartment:
Minimum Pilot Weight:
335 Kg
520 Kg
520 Kg
185 Kg
10 Kg
55 kg
Centre of Gravity Range:
Forward: 230mm aft of datum at 350kg, with straight line variation to 280mm aft of datum at 520kg.
Aft: 320mm aft of datum at all weights.
Reference Datum: Wing Leading Edge.
Arm from datum (Wing leading edge)
Fuel
+ 379 mm
Oil
- 410 mm
Coolant
- 750 mm
Occupants
+ 396 mm
Baggage
+1650 mm
SAMPLE AIRPLANE
SAMPLE LOADING PROBLEM
Moment
Weight
(Kg.-mm.
(Kg.)
/1000)
Weight
(Kg.)
Arm
(mm)
335
216
72.36
150
396
59.4
5
1650
8.25
4. ZERO FUEL WEIGHT
490
286
140.01
5. Usable Fuel (At 0.71kg./lt.)
30
379
11.37
6. TAKEOFF WEIGHT
520
291
151.38
Basic Empty Weight (Use the data
pertaining to your airplane as it is
1. presently equipped. Includes
unusable fuel, full oil and full
coolant).
2. Pilot and Passenger
3. Baggage Locker
7.
YOUR AIRPLANE
Arm
(mm)
Moment
(Kg.-mm.
/1000)
As the arms calculated at ZERO FUEL WEIGHT and TAKEOFF WEIGHT are within the Centre of
Gravity range for the aircraft, the loading is acceptable.
The maximum allowable weight capacity for baggage locker is 10 kg.
Page 19 of 19

Skyfox Gazelle Handling Notes

Transcription

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