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P92-JS
Flight Manual
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Tecnam P92-JS Flight Manual

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P92-JS
I N T R O D U C TION
FLIGHT MANUAL
i-1
FLIGHT MANUAL
Doc. n° 92/61 Issue n°3: 25th May 2010
Revision No.0
P92-JS
MANUFACTURER: COSTRUZIONI AERONAUTICHE TECNAM S.r.l.
AIRCRAFT MODEL: P92-JS TYPE CERTIFICATION: n° EASA A.412 (SO/A-340)
SERIAL NUMBER: ............................................................….....
BUILD YEAR: ..............................................................…….....
REGISTRATION MARKINGS: .......................................................
This manual contains information to be furnished to the pilot as required by EASA in addition to further information supplied by manufacturer.
This manual must always be present on board the aircraft. The aircraft is to be operated in compliance with information and limitations
contained herein. Sections 2, 3, 4, 5 are approved by EASA: n° 10030344 on 11.06.2010 Section 9 (supp.1) is approved by EASA: n° 2004-1787 on 02.03.2004 Section 9 (supp. 2) is approved by EASA: n° 2004-6324 on 17.06.2004. Section 9 (supp.3) is approved under DOA privileges: n° MOD92/51.10.06.2009 Section 9 (supp.4) is approved under DOA privileges: n° MOD92/52.10.06.2009 Section 9 (supp.5) is approved under DOA privileges: n° MOD92/53.10.06.2009
P92-JS
I N T R O D U C TION
FLIGHT MANUAL
i-2
RECORD OF REVISIONS
Any revisions to the present Manual, except actual weighing data, must be recorded in the following table and, in case of approved Sections, endorsed by the responsible airworthiness authority.
New or amended text in the revised pages will be indicated by a black vertical line in the left-hand margin; Revision No. and date will be shown on the left-hand side of the page.
RECORD OF REVISIONS
Revision
No.
Affected
sections
Affected
pages
Date
Approval
EASA
Date
Date
Inserted
Signature
P92-JS
I N T R O D U C TION
FLIGHT MANUAL
i-3
LIST OF EFFECTIVE PAGES
Section
Pages
Revision
Section 0
Pages 1 thru 4
Rev 0
Section 1
Pages 1 thru 12
Rev 0
Section 2
Pages 1 thru 10
Rev 0
Section 3
Pages 1 thru 8
Rev 0
Section 4
Pages 1 thru 12
Rev 0
Section 5
Pages 1 thru 14
Rev 0
Section 6
Pages 1 thru 12
Rev 0
Section 7
Pages 1 thru 16
Rev 0
Section 8
Pages 1 thru 4
Rev 0
Section 9
Pages 1 thru 24
Rev 0
P92-JS
I N T R O D U C TION
FLIGHT MANUAL
i-4
TABLE OF CONTENTS
General
Section 1
Limitations
Section 2*
Emergency procedures
Section 3*
Normal procedures
Section 4*
Performance
Section 5**
Weight & Balance / Equipment list
Section 6
Aircraft and Systems description
Section 7
Aircraft handling, servicing and maintenance
Section 8 Supplements
Section 9*
*
Section approved by EASA
**
Section partially approved by EASA
FLIGHT MANUAL
1-1
P92-JS
S E C T I O N 1
GENERAL
SECTION 1
GENERAL
TABLE OF CONTENTS
INTRODUCTION ...................................................................................................... 2
CERTIFICATION BASIS .......................................................................................... 2
WARNINGS - CAUTIONS - NOTES ........................................................................ 2
THREE-VIEW DRAWING ........................................................................................ 3
DESCRIPTIVE DATA ............................................................................................... 4
CONTROL SURFACES TRAVEL LIMITS .............................................................. 4
ENGINE...................................................................................................................... 5
PROPELLER .............................................................................................................. 5
FUEL .......................................................................................................................... 6
OIL SYSTEM ............................................................................................................. 6
COOLING................................................................................................................... 6
MAXIMUM CERTIFIED WEIGHTS ........................................................................ 7
STANDARD WEIGHTS ............................................................................................ 7
SPECIFIC LOADINGS .............................................................................................. 7
ABBREVIATIONS AND TERMINOLOGY ............................................................. 8
UNIT CONVERSION CHART ................................................................................ 11
FLIGHT MANUAL
I-2
P92-JS
S E C T I O N 1
GENERAL
INTRODUCTION
The P92-JS is a twin seat single engine aircraft with a strut-braced rectangular high wing, fixed main landing gear and steerable nosewheel.
This Flight Manual has been prepared to provide pilots and instructors with information for the safe and efficient operation of this aircraft.
This Flight Manual contains 9 sections. Section 1 provides basic data and information of general interest. It also contains definitions and explanations of symbols, abbreviations and commonly used terminology.
CERTIFICATION BASIS
Aircraft
This type of aircraft has been approved by EASA/ENAC in accordance with JAR-VLA of April 26 1990 with amendments 91/1 and 92/1.
Noise Certification Basis
JAR-36 Sub. C Issue: 23 May 1997 ICAO/Annex 16 Chap.10 issue 1993
WARNINGS - CAUTIONS - NOTES
The following definitions apply to warnings, cautions and notes used in
the Flight Manual.
Means that the non-observation of the corresponding procedure leads to an immediate or
important degradation of the flight safety.
Means that the non-observation of the corresponding procedure leads to a minor or to a more or less long
term degradation of the flight safety.
Draws the attention to any special item not directly related to safety but which is important or unusual.
WARNING
CAUTION
NOTE
FLIGHT MANUAL
1-3
P92-JS
S E C T I O N 1
GENERAL
THREE-VIEW DRAWING
Dimensions shown refer to aircraft weight of 550kg (and 600 kg) and
normal operating tire pressure.
Propeller ground clearance 320mm Propeller ground clearance with deflated front tire and nosewheel
shock absorber compressed by 102mm
Minimum ground steering radius 5.5m
NOTE
FLIGHT MANUAL
I-4
P92-JS
S E C T I O N 1
GENERAL
DESCRIPTIVE DATA
WING
For 550 kg
MTOW
For 600 kg
MTOW
Wing span:
8.7 m
8.7 m
Wing chord
1.4 m
1.4 m
Wing surface
12 m2
12 m2
Wing loading
45.8 kg/m2
50.0 kg/m2
Aspect ratio
6.31
6.31
Taper ratio
1.0
1.0
Dihedral
1.5°
1.5°
FUSELAGE
Overall length
6.400 m
6.400 m
Overall width
1.100 m
1.100 m
Overall height
2.500 m
2.500 m
EMPENNAGE
Stabilator span
2.900 m
2.900 m
Vertical tail span
1.230 m
1.230 m
LANDING GEAR
Wheel track:
1.800 m
1.800 m
Wheel base:
1.600 m
1.600 m
Main gear tires: Air Trac; Cleveland wheel hub and brakes kit:
5.00-5
199-102
5.00-5
199-102
Nose gear tire: Sava
4.00-6
4.00-6
CONTROL SURFACES TRAVEL LIMITS
Ailerons
Up 20° down 15 ° 2°
Stabilator
Up 18° down 3° 1°
Trim-Tab
2° ; 12° 1°
Rudder
RH 25° LH 25° 1°
Flaps
0° -38° 1°
FLIGHT MANUAL
1-5
P92-JS
S E C T I O N 1
GENERAL
ENGINE
Manufacturer:
Bombardier-Rotax GmbH
Model
912 S2
Certification basis
FAR 33 Amendment 15
Austrian Type­Certification No.
n° TW 9-ACG of 27 Nov. 1998
Type:
4 cylinder horizontally-opposed twins with overall displacement of 1352 c.c., mixed cooling, (water-cooled heads and air­cooled cylinders), twin carburettors, integrated reduction gear with torque damper.
Maximum power:
(engine’s rpm)
73.5 kW (98.6 hp) @ 5800 rpm (max.5 min.)
69.0 kW (92.5 hp) @ 5500 rpm (continuous)
PROPELLER
Manufacturer:
HOFFMANN Propeller
Certification basis:
CAR Part 14
Type-Certification No.:
SO/E 30 of 10/12/1999
Model:
HO17GHM A 174 177C
Number of blades:
2
Diameter:
1740 mm (no reduction permitted)
Type:
Fixed pitch - wood
FLIGHT MANUAL
I-6
P92-JS
S E C T I O N 1
GENERAL
FUEL
Fuel grade:
High octane gasoline DIN 51600,
O-NORM 1103 (red)
Unleaded gasoline DIN 51603,
O-NORM 1101
AVGAS 100LL (see Section 2.9)
Fuel tanks:
2 wing tanks integrated within the wing's leading edge with fuel strainer located in engine cowling.
Capacity of each wing tank
35 liters (optional 45 liters)
Total capacity:
70 liters (optional 90 liters)
Total usable fuel
66.8 liters. (86.8 liters)
OIL SYSTEM
Oil system type:
Forced, with external oil reservoir
Oil:
Automotive grade API "SF" or "SG" type oil preferably synthetic or semi-synthetic
Oil Capacity:
3.5 liters
COOLING
Cooling system:
Mixed air and liquid pressurized closed circuit system
Coolant:
Antifreeze and water liquid mixture
Capacity
3 liters
FLIGHT MANUAL
1-7
P92-JS
S E C T I O N 1
GENERAL
For 550 kg MTOW
For 600 kg MTOW
MAXIMUM CERTIFIED WEIGHTS
Maximum take-off weight:
550 kg
600 kg
Maximum landing weight:
550 kg
600 kg
Maximum baggage weight
20 kg
20 kg
STANDARD WEIGHTS
Standard Empty Weight
325 kg
325 kg
Maximum Useful Load
225 kg
275 kg
SPECIFIC LOADINGS
Wing Loading
45.8 kg/m2
50 kg/m2
Power Loading
5.6 kg/hp
6.1 kg/hp
FLIGHT MANUAL
I-8
P92-JS
S E C T I O N 1
GENERAL
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.
KIAS
Knots Indicated Airspeed is the speed shown on the airspeed indicator and expressed in knots.
KTAS
Knots True Airspeed is the airspeed expressed in knots relative to undisturbed air which is KCAS corrected for altitude and temperature.
VFE
Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position.
VNO
Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air, then only with caution.
VNE
Never Exceed Speed is the speed limit that may not be exceeded at any time.
VS
Stalling Speed.
VS0
Stalling speed in landing configuration
VS1
Stalling speed in clean configuration (flap 0°)
VX
Best Angle-of-Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal distance.
VY
Best Rate-of-Climb Speed is the speed which results in the greatest gain in altitude in a given time.
Vr
Rotation speed: is the speed at which the aircraft rotates about the pitch axis during takeoff
VLO
Lift off speed: is the speed at which the aircraft generally lifts off from the ground.
Vobs
Obstacle speed: is the speed at which the aircraft flies over a 15m obstacle during takeoff or landing
FLIGHT MANUAL
1-9
P92-JS
S E C T I O N 1
GENERAL
METEOROLOGICAL TERMINOLOGY
OAT
Outside Air Temperature is the free air static temperature expressed in degrees Celsius (°C).
TS
Standard Temperature is 15°C at sea level pressure altitude and decreased by 2°C for each 1000 ft of altitude.
HP
Pressure Altitude is the altitude read from an altimeter when the barometric subscale has been set to 1013 mb.
ENGINE POWER TERMINOLOGY
RPM
Revolutions Per Minute: is the number of revolutions per minute of the propeller, multiplied by 2.4286 yields engine RPM.
AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY
Crosswind Velocity
is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing is guaranteed.
Usable fuel
is the fuel available for flight planning.
Unusable fuel
is the quantity of fuel that cannot be safely used in flight..
g
is the acceleration of gravity.
TOR
is the takeoff distance measured from actual start to wheel liftoff point
TOD
is total takeoff distance measured from start to 15m obstacle clearing
GR
is the distance measured during landing from actual touchdown to stop point
LD
is the distance measured during landing, from 15m obstacle clearing to actual stop.
S/R
is specific range, that is, the distance (in nautical miles) which can be expected at a specific power setting and/or flight configuration per kilo of fuel used.
FLIGHT MANUAL
I-10
P92-JS
S E C T I O N 1
GENERAL
WEIGHT AND BALANCE TERMINOLOGY
Datum
is an imaginary vertical plane from which all horizontal distances are measured for balance purposes.
Arm
is the horizontal distance from the reference datum to the center of gravity (C.G.) of an item.
Moment
is the product of the weight of an item multiplied by its arm.
C. G.
Center of Gravity is the point at which the airplane, or equipment, would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane.
Standard Empty Weight
Standard Empty Weight is the weight of a standard airplane, including unusable fuel, full operating fuels and full engine oil.
Basic Empty Weight
is the standard empty weight plus the weight of optional equipment.
Useful Load
is the difference between takeoff weight and the basic empty weight.
Maximum Weight
is the maximum certified weight of the aircraft.
Maximum Takeoff Weight
is the maximum weight approved for the start of the takeoff run.
Maximum Landing Weight
is the maximum weight approved for the landing touch down.
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.
FLIGHT MANUAL
1-11
P92-JS
S E C T I O N 1
GENERAL
UNIT CONVERSION CHART
MULTIPLYING
BY
YIELDS
TEMPERATURE
Fahrenheit
[°F]
5 9
32 F
Celsius
[°C]
Celsius
[°C]
9 5
32
 
 
C
Fahrenheit
[°F]
FORCES
Kilograms
[kg]
2.205
Pounds
[lbs]
Pounds
[lbs]
0.4536
Kilograms
[kg]
SPEED
Meters per second
[m/s]
196.86
Feet per minute
[ft/min]
Feet per minute
[ft/min]
0.00508
Meters per second.
[m/s]
Knots
[kts]
1.853
Kilometers / hour
[km/h]
Kilometers / hour
[km/h]
0.5396
Knots
[kts]
PRESSURE
Atmosphere
[atm]
14.7
Pounds / sq. in
[psi]
Pounds / sq. in
[psi]
0.068
Atmosphere
[atm]
LENGTH
Kilometers
[km]
0.5396
Nautical miles
[nm]
Nautical miles
[nm]
1.853
Kilometers
[km]
Meters
[m]
3.281
Feet
[ft]
Feet
[ft]
0.3048
Meters
[m]
Centimeters
[cm]
0.3937
Inches
[in]
Inches
[in]
2.540
Centimeters
[cm]
VOLUME
Liters
[l]
0.2642
U.S. Gallons
[US Gal]
U.S. Gallons
[US Gal]
3.785
Liters
[l]
AREA
Square meters
[m2]
10.76
Square feet
[sq ft]
Square feet
[sq ft]
0.0929
Square meters
[m2]
FLIGHT MANUAL
I-12
P92-JS
S E C T I O N 1
GENERAL
INTENTIONALLY LEFT BLANK
FLIGHT MANUAL
2-1
P92-JS
S E C T I O N 2
LIMITATIONS
SECTION 2
LIMITATIONS
TABLE OF CONTENTS
INTRODUCTION ...................................................................................................... 2
AIRSPEED LIMITATIONS ....................................................................................... 2
AIRSPEED INDICATOR MARKINGS ..................................................................... 3
POWERPLANT LIMITATIONS ............................................................................... 4
PROPELLER .............................................................................................................. 5
POWERPLANT INSTRUMENT MARKINGS ......................................................... 6
OTHER INSTRUMENT MARKINGS ...................................................................... 6
WEIGHTS .................................................................................................................. 7
CENTER OF GRAVITY RANGE ............................................................................. 7
APPROVED MANEUVERS ...................................................................................... 8
MANEUVERING LOAD FACTOR LIMITS ............................................................ 8
FLIGHT CREW .......................................................................................................... 8
KINDS OF OPERATION ........................................................................................... 9
FUEL .......................................................................................................................... 9
MAXIMUM PASSENGER SEATING .................................................................... 10
CROSSWIND LIMITATIONS ................................................................................ 10
LIMITATION PLACARDS ..................................................................................... 10
FLIGHT MANUAL
Date: Issue 3: 25th May 2010
2-2
P92-JS
S E C T I O N 2
LIMITATIONS
INTRODUCTION
Section 2 includes operating limitations, instrument markings, and basic placards necessary for safe operation of the P92-JS, its engine, standard systems and standard equipment.
Refer to section 9 for possible variations to:
AIRSPEED LIMITATIONS
Airspeed limitations and their operational significance are shown below:
S P E E D
550 kg
MTOW
600 kg
MTOW
REMARKS
KIAS
KCAS
KIAS
KCAS
V
NE
Never exceed speed
134
128
141
135
Never exceed this speed in any operation.
V
NO
Maximum Structural Cruising Speed
106
102
110
106
Never exceed this speed unless in smooth air, and then only with caution.
V
A
Maneuvering speed
93
90
97
94
Do not make full or abrupt control movements above this speed as this may cause stress in excess of limit load factor
V
FE
Maximum flap extended speed
68
66
71
69
Never exceed this speed for any given flap setting.
NOTE
FLIGHT MANUAL
2-3
P92-JS
S E C T I O N 2
LIMITATIONS
AIRSPEED INDICATOR MARKINGS
Airspeed indicator markings and their color code are explained in the following table
Refer to section 9 of this Flight Manual for operational limitations for aircraft fitted with optional equipment.
MARKING
550 kg
MTOW
600 kg
MTOW
SIGNIFICANCE
KIAS
White arc
43* - 68
41 - 71
Positive Flap Operating Range (lower limit is VSO, at maximum weight and upper limit is maximum speed permissible with flaps extension to maximum positive)
Green arc
48* – 106
46 - 110
Normal Operating Range (lower limit is VS1 at maximum weight and most forward c.g. with flaps retracted and upper limit is maximum structural speed VNO).
Yellow
arc
106 - 134
110- 141
Maneuvers must be conducted with caution and only in smooth air.
Red line
134
141
Maximum speed for all operations.
For P92-JS with MTOW = 550kg the low limit of the white arc is 1.1 VS0 while the low limit of the green arc is 1.1V
S1
CAUTION
FLIGHT MANUAL
Date: Issue 3: 25th May 2010
2-4
P92-JS
S E C T I O N 2
LIMITATIONS
POWERPLANT LIMITATIONS
The following table lists operating limitations for aircraft installed engine: ENGINE MANUFACTURER: Bombardier Rotax GmbH. ENGINE MODEL: 912 S2 MAXIMUM POWER: (see table below)
Max Power
kW (hp)
Max RPM.
RPM prop (eng.)
Time max.
(min.)
Maximum
73.5 (98.6)
2388 (5800)
5
Max cont.
69 (92.5)
2265 (5500)
-
The static rpm range at full throttle (carburetors heat: Off) is 2100 100 prop. rpm.
TEMPERATURES:
Max cylinder heads
135° C
Cooling liquid, monitored at cylinder heads
135° C
Max Oil:
130° C
Min Oil
50° C
OIL PRESSURE:
Min
0.8 bar
Max
5 bar
ENGINE START, OPER. TEMP:
OAT Min
-25° C
OAT Max
+50° C
Admissible pressure for cold start is 7 bar maximum for short periods.
WARNING
NOTE
FLIGHT MANUAL
2-5
P92-JS
S E C T I O N 2
LIMITATIONS
FUEL PRESSURE:
Min
2.2 psi
Max
5.8 psi
VISCOSITY
Use viscosity grade oil as specified in the following table:
Use of Aviation Grade Oil with or without additives is not permitted
COOLANT:
Mixture: 80% concentrated antifreeze (e.g. BASF Glysantin Anticorrosion or equivalent) with anticorrosion additive and 20% demineralized water.
PROPELLER
MANUFACTURER: HOFFMANN Propeller
MODEL: HO17GHM-174 177C or HO17GHM A 174 177C
PROPELLER TYPE: Wood twin blade fixed pitch
DIAMETER: 1740 mm (no reduction permitted)
WARNING
FLIGHT MANUAL
Date: Issue 3: 25th May 2010
2-6
P92-JS
S E C T I O N 2
LIMITATIONS
POWERPLANT INSTRUMENT MARKINGS
Powerplant instrument markings and their color code significance are shown below:
INSTRUMENT
RED LINE
Minimum limit
GREEN ARC
Normal
operating
YELLOW ARC
Caution
RED LINE
Maximum
limit
Prop tach
RPM
--------
580-2265
2265-2388
2388
Oil Temp.
°C
50
90-110
50 - 90
110-130
130
Cylinder heads and coolant temp.
°C
--------
0 - 135
------
135
Oil pressure
bar
0.8
2 – 5
0.8 – 2
5 – 7
(1)
7
Fuel Press.
psi
2.2
2.2 – 5.8
----
5.8
Fuel quantity
liters
--------
(2)
----
----
-----
OTHER INSTRUMENT MARKINGS
INSTRUMENT
RED LINE
Minimum
limit
GREEN ARC
Normal operating
YELLOW ARC
Caution
RED LINE
Maximum limit
Suction gage
4 in. Hg
4,5 - 5,5 in. Hg.
------
------
Voltmeter
10 Volt
12 - 14 Volt
------
------
1 Admissible pressure for cold start is 7 bar maximum for short periods.
2
Unusable fuel for each tank is 1.6 litres
FLIGHT MANUAL
2-7
P92-JS
S E C T I O N 2
LIMITATIONS
WEIGHTS
550 kg MTOW
600 kg MTOW
Maximum takeoff weight
550 kg
600 kg
Maximum landing weight
550 kg
600 kg
Maximum zero fuel weight
550 kg
600 kg
Maximum baggage weight (2.18 m from datum)
20 kg
20 kg
NOTE
Refer to section 6 for correct stowing and loading of baggage.
CENTER OF GRAVITY RANGE
Ref. for levelling
Cabin floor
Datum
Propeller support flange without spacer
Forward limit
1.727 m (23% MAC) aft of datum for all weights
Aft limit
1.769 m (26% MAC) aft of datum for all weights
It is the pilot's responsibility to insure that the airplane is properly loaded. Refer to section 6 for appropriate instructions.
WARNING
FLIGHT MANUAL
Date: Issue 3: 25th May 2010
2-8
P92-JS
S E C T I O N 2
LIMITATIONS
APPROVED MANEUVERS
This aircraft is certified in the CS-VLA category. CS-VLA applies to airplanes intended for non-aerobatic operation only. Non-
aerobatic operation includes:
Any maneuver pertaining to “normal” flight Stalls (except whip stalls) Lazy eights Chandelles Turns in which the angle of bank is not more than 60°
Acrobatic maneuvers, including spins, are not approved Recommended entry speed for each approved maneuver is as follows:
MANEUVER
KIAS
550 kg MTOW
600 kg MTOW
Lazy eights
93
97
Chandelles
93
97
Steep turns max 60°
93
97
Stalls
Slow Deceleration (1 Kts/sec.)
Slow Deceleration (1 Kts/sec.)
MANEUVERING LOAD FACTOR LIMITS
Maneuvering load factors are as follows:
FLAPS
0°
+3.8
- 1.9
38°
+1.9
0
FLIGHT CREW
Minimum crew for flight is one pilot seated on the left side.
FLIGHT MANUAL
2-9
P92-JS
S E C T I O N 2
LIMITATIONS
KINDS OF OPERATION
The airplane, in standard configuration, is approved only for day VFR operation with terrain visual contact. Minimum equipment required is as follows:
Altimeter Airspeed Indicator Heading Indicator Fuel Gage Oil Pressure Indicator Oil Temp. Indicator Cylinder Heads Temp. Indicator Outside Air Temp. indicator Tachometer Chronometer First Aid Kit Hand-held fire extinguisher
For further standard equipment refer to section 6. Flight into expected and/or known icing conditions is prohibited.
FUEL
TWO TANKS: 35 liters each (45 liters optional) TOTAL FUEL CAPACITY: 70 liters (90 liters) USABLE FUEL: 66.8 liters (86.8 liters) UNUSABLE FUEL: 3.2 liters (3.2 liters)
During all phases of flight engine fuel feed must be supplied by both tanks. Compensate uneven fuel tank levels by acting on fuel taps located in cabin.
APPROVED FUEL
High octane gasoline DIN 51600, O.NORM 1103 Unleaded gasoline DIN 51603, O.NORM 1101 AVGAS 100LL (see Warning below)
Prolonged use of Aviation Fuel Avgas 100LL results in greater wear of valve seats and greater combustion deposits inside cylinders due to higher lead content. It is therefore suggested to avoid using this type of fuel unless strictly necessary.
WARNING
FLIGHT MANUAL
Date: Issue 3: 25th May 2010
2-10
P92-JS
S E C T I O N 2
LIMITATIONS
MAXIMUM PASSENGER SEATING
Only one passenger is allowed on board this aircraft.
CROSSWIND LIMITATIONS
Maximum allowed crosswind component is 15 Kts (refer to section 5 for further details).
LIMITATION PLACARDS
The following limitation placards must be placed in plain view on the aircraft. Near the airspeed indicator a placard will state the following:
MANEUVERING SPEED VA=93 KIAS
MANEUVERING SPEED VA=97 KIAS
On the left hand side of the dashboard a placard will state the following:
THIS AIRPLANE IS CLASSIFIED AS A VERY LIGHT AIRPLANE
APPROVED FOR DAY VFR ONLY, IN NON-ICING CONDITIONS. ALL AEROBATIC MANEUVERS INCLUDING INTENTIONAL SPIN ARE PROHIBITED. SEE FLIGHT MANUAL FOR OTHER LIMITATIONS.
NO SMOKING
Near baggage compartment a placard will state the following:
FASTEN TIE-DOWN NET
MAXIMUM WEIGHT 20 kg
MAX. PRESS 12.5 Kg/dm2
For 550 kg MTOW
For 600 kg MTOW
FLIGHT MANUAL
3-1
P92-JS
S E C T I O N 3
EMERGENCY PROCEDURES
SECTION 3
EMERGENCY PROCEDURES
TABLE OF CONTENTS
INTRODUCTION ...................................................................................................... 2
ENGINE FAILURES .................................................................................................. 2
AIR START ................................................................................................................ 4
SMOKE AND FIRE ................................................................................................... 4
GLIDE ........................................................................................................................ 5
LANDING EMERGENCIES ...................................................................................... 5
RECOVERY FROM UNINTENTIONAL SPIN ........................................................ 6
OTHER EMERGENCIES .......................................................................................... 7
FLIGHT MANUAL
3-2
P92-JS
S E C T I O N 3
EMERGENCY PROCEDURES
INTRODUCTION
Section 3 includes checklists and detailed procedures to be used in the event of emergencies. Emergencies caused by a malfunction of the aircraft or engine are extremely rare if appropriate maintenance and pre-flight inspections are carried out.
In case of emergency, suggestions of the present section should be considered and applied as necessary to correct the problem.
Before operating the aircraft, the pilot should become thoroughly familiar with the present manual and, in particular, with the present section. Further, a continued and appropriate training should be provided.
AIRSPEEDS FOR SAFE OPERATION IN EMERGENCY SITUATIONS - IAS
550 kg MTOW
600 kg MTOW
Engine failure after takeoff
60 Kts
60 Kts
Engine failure during flight
66 Kts
69 Kts
Manoeuvring speed
93 Kts
97 Kts
Maximum glide
66 Kts
69 Kts
ENGINE FAILURES
Should an emergency arise, the basic guidelines described in this section should be considered and applied as necessary to correct the problem.
ENGINE FAILURE DURING TAKEOFF RUN
1. Throttle: idle (fully out)
2. Brakes: apply as needed
3. Magnetos: OFF.
4. Flap: retract
5. Generator switch and Master switch: OFF.
6. Fuel shutoff valves: OFF
7. Electric fuel pump: OFF
8. Inform TWR
FLIGHT MANUAL
3-3
P92-JS
S E C T I O N 3
EMERGENCY PROCEDURES
ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF
1. Speed 60 KIAS
2. Locate landing area
3. Throttle: idle (fully out)
4. Fuel shutoff valves: OFF.
5. Electric fuel pump: OFF
6. Magnetos OFF.
7. Flaps: as needed.
8. Generator switch and Master switch: OFF.
9. Inform TWR
ENGINE FAILURE DURING FLIGHT
IRREGULAR ENGINE RPM
1. Throttle: check position and adjustment wheel
2. Carb heat: ON
3. Electric fuel pump: ON
4. Fuel shutoff valves: both ON
5. If engine RPMs remain irregular land as soon as possible at closest
airport.
LOW FUEL PRESSURE
If the fuel pressure indicator falls below the 2.2 psi limit, it is necessary to apply the following procedure:
1. Electric fuel pump: ON
2. Fuel shutoff valves: both ON
3. Land at closest airport
LOW OIL PRESSURE
1. Check oil temperature:
If stable within green arc: Land as soon as possible at closest
airport
If increasing:
2. Reduce engine throttle to 70 KIAS
3. Land as soon as possible and be alert for impending engine fault and
consequent emergency landing.
FLIGHT MANUAL
3-4
P92-JS
S E C T I O N 3
EMERGENCY PROCEDURES
AIR START
1. Altitude: preferably below 4000 ft
2. Carb heat: ON
3. Fuel shutoff valves: both ON
4. Electric fuel pump: ON
5. Throttle: middle position
6. Generator switch and Master switch: ON.
7. Magnetos: BOTH.
8. Ignition key to START
9. If engine restarts, keep an eye on instrument readings and land as soon as
possible, otherwise see procedure for: Forced landing
SMOKE AND FIRE
ENGINE FIRE WHILE PARKED OR DURING TAKEOFF
1. Fuel shutoff valves: OFF
2. Electric fuel pump: OFF
3. Cabin heat: OFF
4. Abort takeoff if possible.
5. If engine is running, use up remaining fuel in carburetors.
6. Magnetos: OFF.
7. Master switch: OFF.
8. Generator switch: OFF.
9. Warn bystanders to clear the area as fast as possible.
10. Without removing the engine cowling use a CO2 or a powder fire
extinguisher to put out flames directing spray towards cowling's air intakes.
DO NOT USE WATER to put out fire and do not open engine cowling until absolutely confident that fire is extinguished.
WARNING
FLIGHT MANUAL
3-5
P92-JS
S E C T I O N 3
EMERGENCY PROCEDURES
ENGINE FIRE DURING FLIGHT
1. Fuel shutoff valves: OFF.
2. Electric fuel pump: OFF
3. Cabin heat: OFF
4. Throttle: all in.
5. Magnetos: OFF.
6. Do not attempt air start.
7. Flaps as necessary.
8. Carry out emergency procedure for forced landing.
CABIN FIRE DURING FLIGHT
1. Master switch: OFF
2. Cabin heat: OFF
3. Door vents: open
4. Direct fire extinguisher towards flame base
5. Carry out emergency procedure for forced landing
GLIDE
1. Flaps: retract
2. Speed at: 600 kg 69KIAS
550 kg 66KIAS 450 kg 60KIAS
3. Glide ratio is 12.2 therefore with 1000ft elevation it is possible to cover
~3.8 km (~2 nautical miles) in zero wind conditions.
LANDING EMERGENCIES
FORCED LANDING WITHOUT ENGINE POWER
1. Suggested airspeed 69 KIAS for 600kg MTOW, 66 KIAS for 550kg
MTOW, 60 KIAS for 450kg.
2. Locate most suitable terrain for emergency landing, possibly upwind.
3. Fuel shutoff valves: OFF.
4. Electric fuel pump: OFF.
5. Magnetos: OFF.
6. Tighten safety belts, release door safety lock and unlatch doors.
7. Flaps: full
8. When certain to land, Generator switch and Master switch: OFF.
9. Touchdown at 42 KIAS
FLIGHT MANUAL
3-6
P92-JS
S E C T I O N 3
EMERGENCY PROCEDURES
POWER-ON FORCED LANDING
1. Prompt descent slope.
2. Flaps as required.
3. Select terrain area most suitable for emergency landing and flyby
checking for obstacles and wind direction.
4. Tighten safety belts, release door safety lock and unlatch doors.
5. Before touchdown: fuel shutoff valves: OFF.
6. Electric fuel pump: OFF
7. Carb heat: OFF
8. Flaps: full
9. After touchdown: magnetos: OFF.
10. Generator switch and Master switch: OFF.
LANDING WITH A FLAT NOSE TIRE
1. Pre-landing checklist: complete
2. Flaps: full
3. Land and maintain aircraft NOSE HIGH attitude as long as possible.
After touchdown.
LANDING WITH A FLAT MAIN TIRE
1. Pre-landing checklist: complete
2. Landing approach as usual.
3. Touchdown with GOOD TIRE FIRST and hold aircraft off flat tire as long
as possible.
RECOVERY FROM UNINTENTIONAL SPIN
Should an unintentional spin occur, the following recovery procedure should be used:
1. Adjust throttle to idle (full outward position)
2. Apply and hold full rudder opposite to the direction of spin.
3. Move and hold stick forward until spin is halted.
4. Neutralize rudder
5. Make a smooth recovery by pulling the stick back gently averting speeds
in excess of V
NE
and maximum load factor.
6. Readjust throttle to restore engine power.
FLIGHT MANUAL
3-7
P92-JS
S E C T I O N 3
EMERGENCY PROCEDURES
OTHER EMERGENCIES
UNINTENTIONAL FLIGHT INTO ICING CONDITIONS
1. Get away from icing conditions by changing altitude or direction of flight
in order to reach an area with warmer external temperature.
2. Avoid possible freeze-up of control surfaces by recurrently moving them.
3. Carb heat: ON
4. Increase RPMs to avoid ice formation on propeller blades.
5. Cabin heat: ON
In case of ice formation on wing leading edge, stall speed may increase.
CARBURETOR HEAT
AT TAKEOFF
At takeoff, given the unlikely possibility of ice formation at full throttle, carburetor heat is normally OFF.
IN FLIGHT
With external temperatures below 15° C, or on rainy days or with humid, cloudy, hazy or foggy conditions or whenever a power loss is detected, turn carb heat to ON until engine power is back to normal.
ELECTRIC POWER SYSTEM MALFUNCTION
Electric power supply system malfunctions may be avoided by carrying out inspections as scheduled and prescribed in the Service Manual. Causes for malfunctions are hard to establish but, in any case, problems of this nature must be dealt with immediately. The following may occur:
WARNING
FLIGHT MANUAL
3-8
P92-JS
S E C T I O N 3
EMERGENCY PROCEDURES
GENERATOR LIGHT ILLUMINATES
Generator light may illuminate for a faulty alternator or when voltage is above 16V, in this case the overvoltage sensor automatically shuts down the alternator.
In both cases proceed as follows:
1. Generator switch and master switch: OFF.
2. Generator switch and master switch: ON.
If the problem no longer persists, normal alternator charging will resume and the warning light will turn off proving voltage surcharge was temporary; no further action is required.
If light remains illuminated, a generator malfunction is confirmed. In this case, set Generator switch to OFF and continue flight on battery power alone; the battery is capable of supplying the electrical system for about 26 min. with normal flight loads including operation of: com/nav, flap and trim.
TRIM SYSTEM FAILURE
LOCKED CONTROL
In case the trim control should not respond, act as follows:
1. Check switch for correct position
2. Adjust speed to control aircraft without excessive stick force
3. Land aircraft as soon as possible.
RUNAWAY
If trim position indicator reads displacement without pilot's action on trim control, follow procedure below:
1. Trim power switch OFF
2. Adjust speed to control aircraft without excessive stick force
3. Land aircraft as soon as possible.
FLIGHT MANUAL
4-1
P92-JS
S E C T I O N 4
NORMAL PROCEDURES
SECTION 4
NORMAL PROCEDURES
TABLE OF CONTENTS
INTRODUCTION ...................................................................................................... 2
RIGGING AND DERIGGING ENGINE COWLING ................................................ 2
PRE-FLIGHT INSPECTIONS ................................................................................... 3
CHECKLISTS ............................................................................................................ 6
FLIGHT MANUAL
4-2
P92-JS
S E C T I O N 4
NORMAL PROCEDURES
INTRODUCTION
Section 4 contains checklists and the procedures for the conduct of normal operation.
RIGGING AND DERIGGING ENGINE COWLING
UPPER COWLING:
I. Parking brake ON. II. Fuel shutoff valves OFF. III. Generator switch OFF, Master switch OFF, Magnetos OFF. IV. Unlatch all four butterfly Cam-locks mounted on the cowling by rotating
them 90° counterclockwise while slightly pushing inwards.
V. Remove engine cowling paying attention to propeller shaft passing
through nose.
VI. To assemble: rest cowling horizontal insuring proper fitting of nose base
reference pins.
VII. Secure latches by applying light pressure, check for proper assembly and
fasten Cam-locks.
Butterfly Cam-locks are locked when tabs are horizontal and open when tabs are vertical. Verify tab is below latch upon closing.
LOWER COWLING
I. After disassembling upper cowling, bring propeller to horizontal position. II. Using a standard screwdriver, press and rotate 90° the two Cam-locks
positioned on lower cowling by the firewall.
III. Pull out the first hinge pin positioned on the side of the firewall, then,
while holding cowling, pull out second hinge pin; remove cowling with downward motion.
IV. For installation follow reverse procedure.
WARNING
FLIGHT MANUAL
4-3
P92-JS
S E C T I O N 4
NORMAL PROCEDURES
PRE-FLIGHT INSPECTIONS
Before each flight, it is necessary to carry out a complete inspection of the aircraft starting with an external inspection followed by an internal inspection as hereby detailed.
CABIN INSPECTION
A Flight Manual: check that a copy is on board B Weight and balance: check if within limits C Safety belts used to lock controls: free D Flight controls: activate flight controls to insure unhindered movement of
control rods and surfaces.
E Parking brake: engage F Throttle: adjust friction lock G Magnetos: OFF H Master switch: ON I Voltmeter: check (10-12 V); Ammeter check (red). J Generator switch: ON, check generator switch is illuminated. K Fuel pump: ON, check light ON, audible sound and correct operation of
fuel pressure indicator.
L Avionics switch: ON, check operation; when finished, reposition switch to
OFF
M Flaps control: activate control to full extension checking travel limits and
instrument indication.
N Trim control: activate control to full scale checking travel limits and
instrument indication
O Acoustic stall warning: check operation P Navigation lights and strobe-light: check operation Q Landing light: check operation R Generator switch: OFF S Master switch: OFF T Fuel level: check level on the basis of flight plan
FLIGHT MANUAL
4-4
P92-JS
S E C T I O N 4
NORMAL PROCEDURES
U Baggage: check for proper stowage with tie-down net.
Fuel level indicated by the fuel quantity indicators (on the instrument panel) is only indicative. For flight safety, pilot should verify actual fuel quantity embarked before takeoff.
EXTERNAL INSPECTION
To carry out the external inspection it will be necessary to follow the
checklist below with the station order outlined in fig. 4-1.
Visual inspection is defined as follows: check for defects, cracks, detachments, excessive play, unsafe or improper installation as well as for general condition. For control surfaces, visual inspection also involves additional check for freedom of movement and security.
A Left hand fuel filler cap: check visually for desired fuel level and secure.
Left tank vent: check for obstructions.
FIG. 4-1
WARNING
WARNING
FLIGHT MANUAL
4-5
P92-JS
S E C T I O N 4
NORMAL PROCEDURES
B Remove protection cap and check pitot mounted on left strut is
unobstructed, do not blow inside vents, place protection cap inside aircraft. C Left side leading edge and wing skin: visual inspection D Left aileron: visual inspection E Left flap and hinges: visual inspection F Left main landing gear; check inflation 14 psi (1.0 bar), tire condition,
alignment, fuselage skin condition. G Horizontal tail and tab: visual inspection. H Vertical tail and rudder: visual inspection. I Right side main landing gear; check inflation 14 psi (1.0 bar), tire
condition, alignment, fuselage skin condition. L Right flap and hinges: visual inspection. M Right aileron: visual inspection. N Right leading edge and wing skin: visual inspection. O Check freedom of movement of stall detector microswitch on right side
leading edge, activate Master switch and check cabin acoustic warning
signal is operative, deactivate Master switch. P Right side fuel filler cap: check visually for desired fuel level and secure.
Right side tank vent: check for obstructions. Q Right side static port: check for obstructions, do not blow inside vents (read
note). R Nose wheel strut and tire: check inflation 11 psi (0.8 bar), tire condition
and condition of rubber shock absorber discs. S Propeller and spinner condition: check for nicks and security. T Open engine cowling and perform the following checklist:
I. Check no foreign objects are present. II. Check the cooling circuit for losses, check coolant reservoir level,
insure radiator honeycomb is unobstructed.
III. Check lubrication circuit for losses, check oil reservoir level,
insure radiator honeycomb is unobstructed.
FLIGHT MANUAL
4-6
P92-JS
S E C T I O N 4
NORMAL PROCEDURES
IV. Open both fuel shutoff valves, inspect fuel circuit for losses, check
integrity of fireproof protection braids, drain circuit using a cup to collect fuel by opening the specific drainage valve located on the firewall, close shutoff fuel valves. Check for water or other contaminants.
Drainage operation must be carried out with aircraft parked on level surface.
V. Check integrity of silent-block suspensions. VI. Check connection and integrity of air intake system, visually
inspect that ram air intake is unobstructed.
VII. Check that all parts are secure or safetied.
U Close engine cowling. V Check left side static vent is unobstructed. Z Remove tow bar and chocks.
NOTE
Avoid blowing inside left strut mounted pitot and inside airspeed indicator system's static vents as this may damage instruments.
CHECKLISTS
BEFORE STARTING ENGINE (after preflight inspection)
I. Flight planning, fuel consumption, refueling. II. Check correct aircraft loading and correct CG position (see section 6). III. Seat position and safety belts adjustment IV. Doors secured V. Parking brake ON.
Avionics general switch must be OFF during engine startup to avoid damage to avionics instrumentation.
CAUTION
FLIGHT MANUAL
4-7
P92-JS
S E C T I O N 4
NORMAL PROCEDURES
STARTING ENGINE
I. Circuit Breakers: check IN II. Master switch ON. Check Voltmeter and Ammeter III. Fuel shutoff valves: both ON. IV. Electric fuel pump ON; (check for audible pump noise and fuel pressure) V. Engine throttle to idle. VI. Choke as needed. VII. Set Magnetos switch to: BOTH. VIII. Propeller area: CLEAR
Check to insure no person or object is present in the area close to
propeller.
IX. Ignition key set to: START. X. Generator switch “ON” and check Ammeter “green”. XI. Propeller rpm: 1000-1100 rpm XII. Choke OFF XIII. Check engine instruments XIV. Check oil pressure rise within10 sec. (maximum cold value 7 bar) XV. Electric fuel pump: OFF XVI. Check fuel pressure XVII.Electric fuel pump: ON
WARNING
FLIGHT MANUAL
4-8
P92-JS
S E C T I O N 4
NORMAL PROCEDURES
BEFORE TAXIING
I. Radio and utilities ON. II. Altimeter: reset. III. Navigation lights: as required IV. Request control tower O.K., parking brake OFF and taxi.
TAXIING
I. Brakes: CHECK II. Flight instruments: CHECK
PRIOR TO TAKE-OFF
I. Parking brake ON. II. Turn on navigation lights, strobe light, and landing light III. Check engine instruments:
Oil temperature 50-110 °. Cylinder heads temperature max 135 °. Oil pressure 2-5 bar. Fuel pressure 2.2 – 5.8 psi
IV. Check ammeter to insure alternator is charging. V. Propeller at 1700 rpm and test Magnetos (speed drop with only one
ignition circuit must not exceed 130 propeller’s rpm).
VI. Check fuel level indicators. VII. Flaps at 15° (takeoff) VIII. Stick free and zero trim IX. Seat belts fastened and doors secured.
FLIGHT MANUAL
4-9
P92-JS
S E C T I O N 4
NORMAL PROCEDURES
TAKEOFF AND CLIMB
I. TWR: OK for takeoff II. Check for clear final and wind on runway. III. Parking brake OFF, IV. Carburetor heat: OFF V. Taxi to line-up VI. Full throttle (approx. 2100 100 propeller rpm) VII. Rotation speed Vr=47 Kts for 550 kg MTOW and Vr=48 Kts for
600kg MTOW.
VIII. Rotation and takeoff IX. Slight braking to stop wheel spinning. X. Flaps retracted XI. Landing light OFF. XII. Trim adjustment XIII. Establish climb rate XIV. Electric fuel pump: OFF
CRUISE
I. Reach cruising altitude II. Set power and engine rpm's for cruise. III. Check engine instruments
Oil temperature 90°-110 ° C. Temperature cylinder heads 90° 135 °.C Oil pressure 2 - 5 bar. Fuel pressure 2.2 – 5.8 psi
IV. Carburetor heat as needed, see paragraph on carb. heat in Section 3.
FLIGHT MANUAL
4-10
P92-JS
S E C T I O N 4
NORMAL PROCEDURES
NOTE
Compensate unpredicted asymmetrical fuel consumption between left and right fuel tanks by closing appropriate fuel shutoff valve inside cabin.
BEFORE LANDING
I. Contact TWR. II. Electric fuel pump ON III. Turn on landing light. IV. Check runway final and establish descent and approach to final. V. Extend flaps gradually to maximum deflection of 38°. VI. Optimal touchdown speed: 44Kts for 550kg MTOW and 45Kts for
600kg MTOW
BALKED LANDING
I. Full throttle II. Flaps position: TO III. Speed: 60 KIAS (63KIAS) for 550kg MTOW (600kg)
NORMAL LANDING
I. Land and taxi. II. Flaps to 0°. III. Parking brake ON. IV. Turn off landing, navigation and strobe lights.
ENGINE SHUT DOWN
I. Keep engine running at 1200 rpm for about two minutes in order to
reduce latent heat.
II. Electric fuel pump: OFF
FLIGHT MANUAL
4-11
P92-JS
S E C T I O N 4
NORMAL PROCEDURES
III. Turn off all electrical utilities. IV. Set magnetos switch to OFF. V. Set Generator switch and Master switch to OFF. VI. Set both fuel shutoff valves to OFF.
POSTFLIGHT CHECK
I. Insert hood over pitot tube on left side wing strut. II. Lock controls using seat belts.
FLIGHT MANUAL
4-12
P92-JS
S E C T I O N 4
NORMAL PROCEDURES
INTENTIONALLY LEFT BLANK
FLIGHT MANUAL
5-1
P92-JS
S E C T I O N 5
PERFORMANCE
SECTION 5
PERFORMANCE
TABLE OF CONTENTS
PERFORMANCE ....................................................................................................... 2
INTRODUCTION ...................................................................................................... 2
USE OF PERFORMANCE CHARTS ......................................................................... 2
AIRSPEED INDICATOR SYSTEM CALIBRATION (APPROVED DATA) .................. 3
STALL SPEED (APPROVED DATA) .............................................................................. 5
CROSSWIND ............................................................................................................. 6
TAKEOFF PERFORMANCE (APPROVED DATA) ........................................................ 7
CLIMB PERFORMANCE .......................................................................................... 9
CRUISE .................................................................................................................... 10
BALKED LANDING................................................................................................ 12
LANDING DISTANCE (Approved data) ................................................................. 13
CONSEQUENCES FROM RAIN AND INSECT ..................................................... 14
NOISE DATA ........................................................................................................... 14
FLIGHT MANUAL
5-2
P92-JS
S E C T I O N 5
PERFORMANCE
PERFORMANCE
INTRODUCTION
This section provides all necessary data for accurate and comprehensive planning of flight activity from takeoff to landing. Data reported in graphs and/or tables were determined by using:
“flight test data” with conditions as prescribed by JAR-VLA aircraft and engine in good condition average piloting techniques
Each graph or table was determined according to ICAO Standard Atmosphere (ISA - m.s.l.); evaluations of the impact on performance was carried out by theoretical means for:
airspeed external temperature altitude weight type and condition of runway
Sections approved by ENAC are highlighted by the writing “Approved data” immediately following the paragraph.
USE OF PERFORMANCE CHARTS
Performance data is presented in tabular or graphical form to illustrate the effect of different variables such as altitude, temperature and weight. Given information is sufficient to plan journey with required precision and safety. Additional information is provided for each table or graph.
FLIGHT MANUAL
5-3
P92-JS
S E C T I O N 5
PERFORMANCE
AIRSPEED INDICATOR SYSTEM CALIBRATION
(Approved data)
Graph shows calibrated airspeed V
CAS
as a function of indicated airspeed V
IAS
.
Fig. 5-1. CALIBRATED VS INDICATED AIRSPEED (BOTH MTOW)
Example:
Given
Find
V
IAS
= 78 Kts
V
CAS
= 75 Kts
NOTE
Indicated airspeed assumes 0 instrument error
40
50
60
70
80
90
100
110
120
130
140
40 50 60 70 80 90 100 110 120 130 140
IAS (kts)
CAS (kts)
78
75
FLIGHT MANUAL
5-4
P92-JS
S E C T I O N 5
PERFORMANCE
Fig. 5-2. ICAO CHART
Example:
Given
Find
Temperature = 20°C
Ts = 12°
Pressure altitude = 1600 ft
FLIGHT MANUAL
5-5
P92-JS
S E C T I O N 5
PERFORMANCE
STALL SPEED (Approved data)
CONDITIONS: - weight 550 kg
- engine idle
- no ground effect
LATERAL BANKING
0°
30°
45°
60°
FLAPS
KIAS
KCAS
KIAS
KCAS
KIAS
KCAS
KIAS
KCAS
0°
44
43
47
46
52
51
63
61
15°
42
41
45
44
50
49
60
58
38°
40
39
42
41
47
46
56
55
CONDITIONS: - weight 600 kg
- engine idle
- no ground effect
LATERAL BANKING
0°
30°
45°
60°
FLAPS
KIAS
KCAS
KIAS
KCAS
KIAS
KCAS
KIAS
KCAS
0°
46
45
49
48
54
53
66
64
15°
44
43
47
46
52
51
63
61
38°
41
40
44
43
49
48
58
56
NOTE
Altitude loss during conventional stall recovery as demonstrated during test flights is approximately 100 ft with banking under 30°.
FLIGHT MANUAL
5-6
P92-JS
S E C T I O N 5
PERFORMANCE
CROSSWIND
Maximum demonstrated crosswind velocity is 15 Kts
Example:
Given
Find
Wind direction = 30°
Headwind = 17.5 Kts
Wind velocity = 20 Kts
Crosswind = 10 Kts
Fig. 5-3. CROSSWIND CHART
FLIGHT MANUAL
5-7
P92-JS
S E C T I O N 5
PERFORMANCE
TAKEOFF PERFORMANCE (Approved data)
TAKEOFF DISTANCE
CONDITIONS:
- Flaps: 15°
MTOW=550kg
MTOW=600kg
- Engine: full throttle (see Sect.4)
- VR =
47 KIAS
48 KIAS
- Runway: dry, compact, grass
- V
obs
=
56 KIAS
58 KIAS
- Slope: 0° Wind: zero
- VLO =
49 KIAS
51KIAS
- R/C 200 ft/min
1. Decrease distances by 10% for each 10 Kts of headwind.
Increase distances by 20 % for each 10 Kts of tailwind
2. For dry and paved runway operation decrease ground
run by 6 %
NOTE
Example:
Given
Find
O.A.T. = 15°C
TOD = 253m
Pressure-altitude = 2900 ft MTOW = 600kg Weight = 450 Kg
TOR = 117 m
Fig. 5-4. TAKEOFF PERFORMANCE
FLIGHT MANUAL
5-8
P92-JS
S E C T I O N 5
PERFORMANCE
CLIMB RATE IN TAKEOFF CONFIGURATION (Approved data) CONDITIONS:
550 kg MTOW
600 kg MTOW
- Flaps:
15°
15°
- Engine:
full throttle
full throttle
- V
obs
:
56 KIAS
58 KIAS
Climb rate in demonstrated ISA s.l. conditions is 850 ft/min at maximum takeoff weight of 550 kg and 750ft/min at maximum takeoff weight of 600 kg.
FLIGHT MANUAL
5-9
P92-JS
S E C T I O N 5
PERFORMANCE
CLIMB PERFORMANCE
CLIMB RATE IN CLEAN CONFIGURATION CONDITIONS:
- Flaps: 0°
- Engine: full throttle
- VY = 70KIAS for 550kg MTOW
- VY = 73KIAS for 600kg MTOW - R/C residual 100 ft/min.
12000
14000
8000
10000
4000
6000
2000
-2000
PRESSURE ALTITUDE (ft)
RATE OF CLIMB (ft/m')
10
TEMPERATURE (deg.C)
-20 -10
0
20
200
30
400
0
1400
1000
600 800
1200
0
2000
4000
ISA
550 kg
500
450
8000
6000
10000
14000
12000
16000
600 kg
Example:
Given
Find
O.A.T. = 17°C
Rate of climb = 700 ft/min
Pressure altitude = 5600 ft
Weight = 550 Kg
FLIGHT MANUAL
5-10
P92-JS
S E C T I O N 5
PERFORMANCE
CRUISE
CONDITIONS:
- ISA
- Maximum takeoff weight = for both MTOW (1) Fuel tanks 2x35 liters (less the unusable fuel)
(2) Fuel tanks 2x45 liters (less the unusable fuel)
Pressure altitude HP: 0 ft OAT: +15°C
Propeller
RPM
Speed KTAS
Consumption
(l/h)
1
Endurance (hrs)
1
Range (N.m.)
(1)
(2)
(1)
(2)
55%
1900
96
15
4.5
5.8
431
599
65%
2050
102
18
3.7
4.9
382
495
75%
2150
108
20
3.4
4.4
364
472
Pressure altitude HP: 2000 ft OAT: +11°C
Propeller
RPM
Speed KTAS
Consumption
(l/h)
1
Endurance (hrs)
1
Range (N.m.)
(1)
(2)
(1)
(2)
55%
1950
98
15
4.5
5.8
440
571
65%
2070
106
18
3.7
4.9
397
515
73%
2150
109
19
3.5
4.6
387
501
Pressure altitude HP: 4000 ft OAT: +7°C
Propeller
RPM
Speed KTAS
Consumption
(l/h)
1
Endurance (hrs)
1
Range (N.m.)
(1)
(2)
(1)
(2)
55%
2020
101
15
4.5
5.8
454
588
60%
2080
105
17
4.0
5.1
416
540
70%
2150
110
18.5
3.6
4.7
401
520
Pressure altitude HP: 6000 ft OAT: +3°C
Propeller
RPM
Speed KTAS
Consumption
(l/h)
1
Endurance (hrs)
1
Range (N.m.)
(1)
(2)
(1)
(2)
55%
2060
104
15
4.5
5.8
467
606
60%
2150
108
17
4.0
5.1
429
556
1
Range and endurance are intended approximate and referred to a “zero” wind
condition.
FLIGHT MANUAL
5-11
P92-JS
S E C T I O N 5
PERFORMANCE
Pressure altitude HP: 8000 ft OAT: -0.8°C
Propeller
RPM
Speed KTAS
Consumption
(l/h)
1
Endurance (hrs)
1
Range (N.m.)
(1)
(2)
(1)
(2)
55%
2120
99
15
4.5
5.8
445
578
58%
2150
102
16
4.2
5.4
428
556
Pressure altitude HP: 10000 ft OAT: -5°C
Propeller
RPM
Speed KTAS
Consumption
(l/h)
1
Endurance (hrs)
1
Range (N.m.)
(1)
(2)
(1)
(2)
55%
2150
100
15
4.5
5.8
450
585
Pressure altitude HP: 12000 ft OAT: -9°C
Propeller
RPM
Speed KTAS
Consumption
(l/h)
1
Endurance (hrs)
1
Range (N.m.)
(1)
(2)
(1)
(2)
50%
2150
98
14
4.8
6.2
475
617
1
Range and endurance are intended approximate and referred to a “zero” wind
condition.
FLIGHT MANUAL
5-12
P92-JS
S E C T I O N 5
PERFORMANCE
BALKED LANDING
RATE OF CLIMB: BALKED LANDING
CONDITIONS:
- Maximum weight = 550 kg 600kg - Flaps: 38°
- V
Obs
= 48 KIAS 50 KIAS - Engine: full throttle max 5’
NOTE
During balked landing maneuver, flaps should be retracted immediately after applying full power.
Fig.5-6. BALKED LANDING (MTOW=550KG)
Example:
Given
Find
Pressure altitude = 7000 ft
Rate of climb = 230 ft/min
Conditions: ISA
NOTE
If the maximum takeoff weight is 600 kg, the rate of climb decreases about 10%
FLIGHT MANUAL
5-13
P92-JS
S E C T I O N 5
PERFORMANCE
LANDING DISTANCE (Approved data)
CONDITIONS:
- Maximum weight = 550 kg (600kg) - Engine: throttle idle
- Brakes: maximum braking - Runway: dry, compact, grass
- Slope: 0° - Wind: zero
- Conditions: ISA - Flaps: 38°
Hp (ft)
0
1000
2000
3000
4000
5000
6000
7000
GR (m)
100
103
106
109
112
116
119
123
LD (m)
252
256
260
264
268
273
279
282
- Maximum weight = 600kg - Engine: throttle idle
- Brakes: maximum braking - Runway: dry, compact, grass
- Slope: 0° - Wind: zero
- Conditions: ISA - Flaps: 38°
Hp (ft)
0
1000
2000
3000
4000
5000
6000
7000
GR (m)
120
124
127
131
134
139
143
148
LD (m)
302
307
312
317
322
328
335
338
NOTE
1. Decrease distances by 10% for each 10 Kts of headwind. Increase
distances by 20 % for each 10 Kts of tailwind;
2. For dry and paved runway operation increase ground run by 10%;
3. If it becomes necessary to land without flap extension (flap
malfunction), increase approach speed by 10 Kts, increase by 40% distance pertaining to flap setting at 38° and increase V
obs
to 58 KIAS
(61KIAS) for 550 kg MTOW (600 kg);
4. V
obs
(speed over obstacle) is 48 KIAS (50 KIAS) for 550 kg MTOW
(600 kg);
FLIGHT MANUAL
5-14
P92-JS
S E C T I O N 5
PERFORMANCE
CONSEQUENCES FROM RAIN AND INSECT
Flight tests have demonstrated that neither rain nor insect impact build-up on leading edge have caused substantial variations to aircraft's flight qualities. Such variations fall within JAR-VLA tolerance limits as they are not above: 5 Kts for stalls, 100 ft/min for climb rates and 50 m for takeoff runs.
NOISE DATA
Noise level was determined according to JAR-36 Sub.C Ed.23 May 1997 ICAO/Annex 16 Chap.10 Issue 1993, and results are shown in the following table:
550 kg MTOW
600 kg MTOW
Noise Level (db)
63.6
65.0
FLIGHT MANUAL
P92-JS
S E C T I O N 6
WEIGHT & BALANCE
6-1
SECTION 6
WEIGHT & BALANCE /
EQUIPMENT LIST
TABLE OF CONTENTS
INTRODUCTION ...................................................................................................... 2
AIRCRAFT WEIGHING PROCEDURES ................................................................. 2
WEIGHING REPORT ................................................................................................ 3
WEIGHT AND BALANCE ....................................................................................... 5
LOADING .................................................................................................................. 8
EQUIPMENT LIST .................................................................................................... 8
FLIGHT MANUAL
6-2
P92-JS
S E C T I O N 6
WEIGHT & BALANCE
INTRODUCTION
This section describes the procedure for establishing the basic empty weight and moment of the aircraft. Loading procedure information is also provided.
AIRCRAFT WEIGHING PROCEDURES
PREPARATION
a. Carry out weighing procedure inside closed hangar b. Remove from cabin any objects left unintentionally a. Insure on board presence of:
Flight manual, airnavigation certificate, navigation charts etc.
d. Align nose wheel e. Drain fuel via specific drain valve. f. Oil, hydraulic fluid and coolant to operating levels g. Move sliding seats to most forward position h. Raise flaps to fully retracted position (0°) i. Place control surfaces in neutral position j. Place scales (min. capacity 150 kg) under each wheel
LEVELING
a. Level the aircraft using the cabin floor as datum b. Center bubble on level by deflating nose tire
WEIGHING
a. Record weight shown on each scale b. Repeat weighing procedure three times c. Calculate empty weight
DETERMINATION OF C.G. LOCATION
a. Drop a plumb bob tangent to the leading edge (in non-tapered area of one
half-wing, approximately one meter from wing root) and trace reference mark on the floor.
b. Repeat operation for other half-wing. c. Stretch a taught line between the two marks d. Measure the distance between the reference line and main wheel axis e. Using recorded data it is possible to determine the aircraft's C.G. location
and moment (see following table)
FLIGHT MANUAL
P92-JS
S E C T I O N 6
WEIGHT & BALANCE
6-3
WEIGHING REPORT
Model P92-JS S/N: ________ Weighing n°____ Date:_________ Datum: Propeller support flange w/o spacer. –Equipment list, date: _____ MAC: 1400 mm
Kg
meters
Nose wheel weight
W1 =
Plumb bob distance LH wheel
AL =
LH wheel weight
WL =
Plumb bob distance RH wheel
AR =
RH wheel weight
WR =
Average distance (AL+ AR)/2
A =
W
2
= WL+WR =
Bob distance from nose wheel
B =
Empty weight
(1)
We = W1 + W2 =
D
W A W B
We
2 1
m
DD%
.
14
100
Empty weight moment: M = [(D+1.405) .We] = Kg . m
Maximum takeoff weight
WT =
550 kg
WT =
600 kg
Empty weight
We =
We =
Sign: ____________
Maximum payload W
T
- We
Wu =
Wu =
1 - Including unusable fuel (2.3 kg).
B
W1
Plumb Line
A
W2=WL+WR
1405
DATUM
D
Horizontal Reference
FLIGHT MANUAL
6-4
P92-JS
S E C T I O N 6
WEIGHT & BALANCE
WEIGHING REPORT
Model P92-JS S/N: ________ Weighing n°____ Date:_________
Datum: Propeller support flange w/o spacer. –Equipment list, date: _____
MAC: 1400 mm
Kg
meters
Nose wheel weight
W1 =
Plumb bob distance LH wheel
AL =
LH wheel weight
WL =
Plumb bob distance RH wheel
AR =
RH wheel weight
WR =
Average distance (AL+ AR)/2
A =
W
2
= WL+WR =
Bob distance from nose wheel
B =
Empty weight
(1)
We = W1 + W2 =
D
W A W B
We
2 1
m
DD%
.
14
100
Empty weight moment: M = [(D+1.405) .We] = Kg . m
Maximum takeoff weight
WT =
550 kg
WT =
600 kg
Empty weight
We =
We =
Sign: ____________
Maximum payload W
T
- We
Wu =
Wu =
1 - Including unusable fuel (2.3 kg).
B
W1
Plumb Line
A
W2=WL+WR
1405
DATUM
D
Horizontal Reference
FLIGHT MANUAL
P92-JS
S E C T I O N 6
WEIGHT & BALANCE
6-5
WEIGHT AND BALANCE
To determine the aircraft's CG location and to verify that the CG falls within the predetermined CG travel range, it is necessary to use the chart in the following page. Chart reports CG location as a function of the empty weight moment with respect to the datum as yielded by weighing report.
USE OF “WEIGHT & BALANCE” CHART (page 6-6)
In order to use the graph it is necessary to know the value of the moment arm with respect to the datum. Once this value is found on the abscissa, a parallel to the oblique lines is drawn until it intersects the ordinate relative to the weight of pilot and passenger. From this point, a new line is drawn horizontally up to limit value of 180 kg and, from here, a parallel to the oblique lines is drawn until it intersects with the abscissa relative to fuel weight carried on board. A horizontal line is then drawn through this point up to limit value of 70 liters and a new parallel to the oblique lines is drawn until abscissa is intercepted relative to baggage loaded on board behind the seats. Another horizontal line is drawn and it is thus possible to verify that the intersection of this segment with the vertical abscissa relative to the aircraft's takeoff total weight falls within the shaded area which represents the admissible CG range as a function of total weight.
Pages 6 and 7 show charts of CG travel as a function of aircraft weight, distances in meters of pilots and baggage from datum (propeller support flange) is also provided.
EXAMPLE (see page 6-6)
Empty weight moment = 562 kg m Pilot and passenger = 160 kg Fuel = 50 Lit Baggage = 15 kg Takeoff weight = 536 kg
FLIGHT MANUAL
6-6
P92-JS
S E C T I O N 6
WEIGHT & BALANCE
1100
536
50
Fuel - Lt. (0.72 kg/l)
0
30
90 70
600 500
Total weight - Kg
550 450 400 350
100
Pilot + Passenger - Kg
Moment (empty) - Kg m
900
1000
800
600
700
562
500
0
20 40 60 80
50
120 140 160
200
180
Luggage - Kg
100 20
26% CMA
23% CMA
FIG. 6-1 Weight & balance chart
FLIGHT MANUAL
P92-JS
S E C T I O N 6
WEIGHT & BALANCE
6-7
Fig 6-2. C.G. RANGE CHART.
Fig 6-3. LOAD POSITION WITH RESPECT TO DATUM
FLIGHT MANUAL
6-8
P92-JS
S E C T I O N 6
WEIGHT & BALANCE
LOADING
Baggage compartment is designed for a maximum load of 20 kg. Baggage size shall prevent excessive loading of utility shelf (maximum pressure 12.5 kg/dm2). Maximum baggage size is: 80x45x32 cm . Baggage shall be secured using a tie-down net to prevent any baggage movement during maneuvers.
Fig 6-4. CABIN DIMENSIONS
EQUIPMENT LIST
The following is a comprehensive list of all TECNAM supplied equipment for the P92-JS. The list consists of the following groups:
A - Engine and accessories B - Landing gear C - Electrical system D - Instruments E - Avionics
the following information describes each listing:
Part-number to uniquely identify the item type.
Item description
Serial number
Weight in kilograms
Distance in meters from datum
NOTE
Items marked with an asterisk (*) are part of basic installation. Additionally, further equipment marked with X in the Inst. column are installed on the aircraft S/N in subject.
FLIGHT MANUAL
P92-JS
S E C T I O N 6
WEIGHT & BALANCE
6-9
EQUIPMENT LIST
A/C S/N
DATE:
REF.
DESCRIPTION & P/N
INST
WEIGHT kg
DATUM m
ENGINE & ACCESSORIES
A1
Engine Rotax 912S2 - p/n 309.120.133
*
59.0
0.32
A2
Prop. HOFFMANN p/n HO17GHM-174-177C or HO17GHM A 174 177C
*
4.50
-0.08
A3
Exhaust and manifolds – p/n SSB-978-480-CC
*
4.50
0.55
A4
Heat exchanger - p/n 92-11-830
*
2.00
0.55
A5
Oil Reservoir (full) - p/n 956.137
*
4.00
0.61
A6
Oil radiator - p/n 886 025
*
0.40
0.07
A7
Liquid coolant radiator. - p/n 995.697
*
0.90
0.33
A8
Air filter K&N- p/n 33-2544
*
0.40
0.60
A9
Vacuum instr. system – RA215CC Rapco
3.00
0.25
A10
Vacuum valve RA2H3-12
0.100
0.71
A11
0.110
0.71
A12
Fuel pump p/n 21-11-342-000
*
0.200
0.71
A13
Fuel tank. 35 LT. P/N 21-1-300-001/2
//
//
A14
Fuel tank. 45 LT. P/N 21-1-340-001/2
//
//
LANDING GEAR AND ACCESSORIES
B1
Main gear spring-leafs - p/n 92-8-300-1
*
5.700
1.930
B2
Main gear wheel rims. - Cleveland 40-78B
*
2.050
1.930
B3
Main gear tires.-Air Trac 5.00-5 AA1D4
*
2.580
1.930
B4
Disk brakes - Cleveland 30-9
*
0.800
1.930
B5
Nose gear wheel rim - p/n 92-8-880-1
*
1.300
0.310
B6
*
1.200
0.460
B7
Nose gear fairing p/n 92-8-410-1/2
x
1.500
0.460
B8
Main gear fairing p/n 92-8-420-1/2
x
1.500
1.930
B9
Nose gear shock p/n 92-8-200-000
*
1.450
0.465
ELECTRICAL SYSTEM
C1
Battery FIAMM 6H4P 12V 18Ah
*
6.00
4.24
C2
Regulator, rectifier - p/n 945.345
*
0.20
0.82
C3
Battery relay - p/n 111-226-5
*
0.30
4.19
C4
Flaps actuator control - SIR Mod. AO-01/M
*
2.20
2.57
C5
Trim actuator control Ray Allen C. T2-10A
*
0.40
5.75
FLIGHT MANUAL
6-10
P92-JS
S E C T I O N 6
WEIGHT & BALANCE
EQUIPMENT LIST
A/C S/N
DATE:
REF.
DESCRIPTION AND P/N
INST
WEIGHT Kg
DATUM m
C6
Overvoltage sensor OS75-14
0.30
0.80
C7
Overvoltage sensor ZEFTRONICS V1510A
0.30
0.80
C8
Strobe light - Aircraft Spr. p/n 2005
0.15
5.52
C9
Navigation lights - AS W1285
0.15
2.30
C10
Stall warning - AS 164R
*
0.10
1.95
C11
Landing light - AS GE 4509
0.50
1.50
INSTRUMENTS
D1
Altimeter - – MIKROTECHINA p/n 1128.10B4 - TSO C10b
0.39
1.20
D2
Altimeter - United Instruments p/n 5934PM­3 - TSO C10b
0.39
1.20
D3
Airspeed ind. – MIKROTECHINA 1106.B0B2
*
0.30
1.20
D4
Compass - Airpath C2400 L4P
*
0.29
1.20
D5
Clock - DAVTRON mod. M 800
*
0.15
1.20
D6
Vertical Speed Indicator – MIKROTECHINA
UL 30-42.2
0.35
1.20
D7
Vertical Speed Indicator - Wultrad Inc. p/n BC-2A
0.35
1.20
D8
Turn and Bank Indicator – FALCON GAUGER
TC02E-3-2
0.56
1.20
D9
Turn and Bank Indicator - Wunltrad Inc. p/n TC-001
0.56
1.20
D10
Attitude Indicator - IFR85 TSOC4c
1.10
1.20
D11
Attitude Indicator - RCA ALLEN INSTR. RCA
22-7
1.10
1.20
D12
Directional Gyro – RCA ALLEN INSTR. RCA
11A-8
1.10
1.20
D13
Directional Gyro – FALCON G.- DG02V-3
1.10
1.20
D14
OAT Indicator –397035001G VDO
*
0.05
1.20
D15
Head temp. Ind. 641-011-7047/-7048 VDO
*
0.10
1.20
D16
Oil temp. ind. - VDO 644-001-7030
*
0.10
1.20
D17
Vacuum instr. UMA Inc. 3-200-12
*
0.10
1.20
D18
Prop. RPM Ind. D1-112-5040 Aircraft Mitchell.
1.10
1.20
FLIGHT MANUAL
P92-JS
S E C T I O N 6
WEIGHT & BALANCE
6-11
EQUIPMENT LIST
A/C S/N
DATA:
REF
DESCRIPTION AND P/N
INST
WEIGHT kg
DATUM m
D19
Prop. RPM Ind. Sorlini (SOR52)
1.10
1.20
D20
Fuel level Ind. GP9745A Uflex
*
0.56
1.20
D21
Oil pressure. ind. – Sorlini (SOR50)
0.10
1.20
AVIONICS AND OTHER
E1
Nav/CommTrans.-Bendix/King, KX155
2.24
1.20
E2
Nav Indicator - Bendix/King KI208
0.46
1.20
E3
Transponder Collins TDR-950
1.36
1.20
E4
Transponder - Bendix/King KT76A
1.36
1.20
E5
Receiver GPS/NAV e r/t COM GNS 430W
2.31
1.20
E6
R/T VHF COMM IC-A200 ICOM
1.20
1.20
E7
ELT ARTEX ME 406
1.10
2.70
E8
Transponder-Garmin GTX328
1.00
1.20
E9
Audio panel –Garmin GMA 340
0.50
1.20
E10
Vor/Loc Indicator –Garmin GI106A
0.64
1.20
E11
Antenna KA 92 GPS
0.27
1.07
E12
Antenna Transp.-Bendix/King KA60
0.35
1.50
E13
Antenna GPS - Garmin 1012
0.17
1.07
E14
Microphone - Telex TRA 100
0.17
1.90
E15
Antenna Garmin GA35
0.27
1.08
E16
Antenna Comm CI 291
*
0.34
3.30
E17
Antenna VOR/ILS CI 138C
0.26
5.60
E18
Antenna ELT
0.21
2.70
E19
Fire extinguisher Fire fighting Enterprises Ltd BA51015-3
*
2.20
2.16
E20
First Aid Kit
*
0.28
2.60
FLIGHT MANUAL
6-12
P92-JS
S E C T I O N 6
WEIGHT & BALANCE
LEFT INTENTIONALLY BLANK
FLIGHT MANUAL
7-1
P92-JS
S E C T I O N 7
SYSTEMS
SECTION 7
AIRCRAFT & SYSTEMS DESCRIPTION
TABLE OF CONTENTS
INTRODUCTION ...................................................................................................... 2
AIRFRAME ................................................................................................................ 2
FLIGHT CONTROLS ................................................................................................ 3
INSTRUMENT PANEL ............................................................................................. 4
SEATS AND SAFETY HARNESS ............................................................................ 5
DOORS ................................................................................................ ....................... 5
Baggage COMPARTMENT ....................................................................................... 5
POWERPLANT .......................................................................................................... 6
FUEL SYSTEM .......................................................................................................... 6
ELECTRICAL SYSTEM............................................................................................ 8
PITOT AND STATIC PRESSURE SYSTEMS ....................................................... 10
BRAKES ................................................................................................................... 11
MARKING & PLACARDS ...................................................................................... 11
PLACARDS OUTSIDE CABIN ............................................................................... 14
FLIGHT MANUAL
7-2
P92-JS
S E C T I O N 7
SYSTEMS
INTRODUCTION
This section provides description and operation of the aircraft and its systems.
AIRFRAME
WING
The wing is constructed of a central light alloy torque box; an aluminum leading edge with integrated fuel tank is attached to the front spar while flap and aileron are hinged to rear spar. Flaps are constructed of a center spar to which front and rear ribs are joined; wrap-around aluminum skin panels cover the flap structure. The aileron is constructed of an aluminum spar to which a formed sheet metal leading edge and metal ribs are attached; a wrap-around. thermosetting synthetic material covers aileron structure.
Fig. 7-1. RIGHT WING EXPLODED VIEW
FLIGHT MANUAL
7-3
P92-JS
S E C T I O N 7
SYSTEMS
FUSELAGE
The front part of the fuselage is made up of a mixed structure: a truss structure with special steel members for cabin survival cell, and a light-alloy semi­monocoque structure for the cabin's bottom section. The aft part of the fuselage is constructed of an aluminum alloy semi-monocoque structure. The engine housing is isolated from the cabin by a stainless steel firewall; the steel stringers engine mount is attached to the cabin's truss structure in four points.
EMPENNAGES
The vertical tail is entirely metal: the vertical stabilizer is made up of a twin spar with stressed skin while the rudder consists of an aluminum torque stringer connected to light alloy ribs and skin. The horizontal tail is an all-moving type (stabilator); its structure consists of an aluminum tubular spar connected to ribs and leading edge; wrap-around thermoretractible synthetic material covers the stabilator structure.
FLIGHT CONTROLS
Aircraft flight controls are operated through conventional stick and rudder pedals. Longitudinal control acts through a system of push-rods and is equipped with a trim tab. Aileron control is of mixed type with push-rods and cables; the cable control circuit is confined within the cabin and is connected to a pair of push-rods positioned in the wings that control ailerons differentially. Aileron trimming is carried out on ground through a small tab positioned on left aileron. Flaps are extended via an electric servo actuator controlled by a switch on the instrument panel. Flaps act in continuous mode, the indicator displays the two positions relative to takeoff (15°) and landing (38°). A breaker positioned on the right side of the instrument panel protects the electric circuit. Longitudinal trim is performed by a small tab positioned on the stabilator and controlled via an electric servo by pushing an Up/Down push-button on the control stick. A shunt switch placed on the instrument panel enables control of either left or right stick; in addition, a safety switch positioned by the trim indicator shuts off power from the circuit in case of emergency (see section 3).
FLIGHT MANUAL
7-4
P92-JS
S E C T I O N 7
SYSTEMS
INSTRUMENT PANEL
The conventional type instrument panel allows placement of a broad range of equipment. Instruments marked with an asterisk (*) are optional.
Fig. 7-2. INSTRUMENT PANEL
CARBURETOR HEAT
Carburetor heat control knob is square shaped and is located just to the left of the center throttle control; when the knob is pulled fully outward from the instrument panel, carbs receive maximum hot air. During normal operation, the knob is OFF.
CABIN HEAT
The cabin heat control knob is positioned on the lower left side of the instrument panel; when knob is pulled fully outward, cabin receives maximum hot air. Vents are located by the rudder pedals and above instrument panel. If necessary, outside fresh air can be circulated inside cabin by opening door vents.
FLIGHT MANUAL
7-5
P92-JS
S E C T I O N 7
SYSTEMS
THROTTLE FRICTION LOCK
It is possible to adjust the engine's throttle friction lock by appropriately tightening the friction lock disk located on the instrument panel near the center throttle control.
SEATS AND SAFETY HARNESS
Aircraft features three point fitting safety belts with waist and diagonal straps adjustable via a sliding metal buckle. Seats are built with light alloy tube structure and synthetic material cushioning. A lever located on the right lower side of each seat allows for seat adjustment according to pilot size.
DOORS
Aircraft doors feature external and internal door handles with door-lock provided externally on left side door. An internal safety latch mechanism is positioned in proximity of door's upper edge and must be used before flight to secure door. Mechanism rotates to engage doorframe to cabin tubular framework.
BAGGAGE COMPARTMENT
The baggage compartment is located behind the pilots' seats. Baggage shall be uniformly distributed on utility shelf and its weight shall not exceed 20kg. Tie­down baggage using adjustable tie-down net.
Before loading baggage, check aircraft's weight and CG location (see section 6).
WARNING
FLIGHT MANUAL
7-6
P92-JS
S E C T I O N 7
SYSTEMS
POWERPLANT
ENGINE ROTAX 912S2, 4 stroke, horizontally-opposed 4 cylinder,
mixed air and water cooled, twin electronic ignition, forced
lubrication Maximum rating – 98.6hp (73.5Kw) @ 5800 rpm/min (2388 rpm/min. prop). Gear reduction ratio - 2.4286:1 For further information see: “Engine Operating Manual”. Engine control instruments are located on right side of instrument panel.
PROPELLER wood twin blade HOFFMAN type: HO17GHM-174 177C or
HO17GHM A 174 177C; for further information see “Service
Manual” for P92-JS and “Propeller Service Manual”.
FUEL SYSTEM
The system is equipped with two aluminum fuel tanks integrated within the wing leading edge and accessible for inspection through dedicated covers. Capacity of individual tank is 35lt (45lt optional) and total usable fuel is 66.8lt (86.8 lt). Each fuel tank is equipped with a cabin installed shutoff valve. A strainer cup with a drainage valve (Gascolator) is located on the engine side of the firewall. Fuel level indicators for each tank are located on instrument panel. Fuel feed is through an engine-driven mechanical pump and through an electric pump for emergencies (normally ON for takeoff) that supplies adequate engine feed in case of main pump failure. All fuel lines located in the engine compartment are protected with fireproof braiding to avoid possible fire. Figure 7-3 illustrates the schematic of the fuel system.
FLIGHT MANUAL
7-7
P92-JS
S E C T I O N 7
SYSTEMS
Fig. 7-3. FUEL SYSTEM SCHEMATIC
FLIGHT MANUAL
7-8
P92-JS
S E C T I O N 7
SYSTEMS
ELECTRICAL SYSTEM
The aircraft's electrical system consists of a 12 Volt DC circuit controlled by the Generator Switch located on the instrument panel. Electricity is provided by an alternator and by a buffer battery placed in the fuselage tail section. Generator light is located on the right side of the instrument panel.
If the ignition key is in the position L, R or BOTH an accidental movement of the propeller may start the engine with possible danger for bystanders.
FIG. 7-4. ELECTRICAL SYSTEM SCHEMATIC
WARNING
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SYSTEMS
GENERATOR LIGHT Generator light (red) illuminates for the following conditions:
Generator failure Failure of regulator/rectifier, with consequent overvoltage sensor set off.
The battery can support energy requirements for 26 min (see page 3-8)
VOLT-AMMETER The voltmeter indicates voltage on bus bar; a positive value of the ammeter
indicates the generator is charging the battery, a negative value indicates the battery's discharge rate.
OIL AND CYLINDER HEADS TEMP. - OIL PRESSURE These instruments are connected in series with their respective sensors. The same
breaker protects all temperature instruments while a second breaker protects oil pressure indicator and other instruments.
O.A.T. INDICATOR A digital Outside Air Temperature indicator (°C) is located on the upper left side
of the instrument panel. The sensor is placed on cabin top.
STALL WARNING SYSTEM The aircraft is equipped with a stall warning system consisting of a sensor located
on the right wing leading edge connected to a warning noisemaker located on the instrument panel.
AVIONICS The central part of the instrument panel holds room for avionics equipment. The
manufacturer of each individual system furnishes features for each system.
EXTERNAL POWER SUPPLY On the right side of the tail cone, an external power is present. Using this device
it is possible to feed the electric system by an external power source. It should be used at the engine start-up in cold weather condition.
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SYSTEMS
Follow this procedure to start the engine using the external power source.
1. Magnetos, Master switch, Generator switch: OFF
2. Open the receptacle door and insert the external power source’s plug into the
socket
3. Engine start-up procedure (see Sect. 4 in this manual)
4. Disconnect the external power source’s plug and close firmly the receptacle
door.
PITOT AND STATIC PRESSURE SYSTEMS
The airspeed indicator system for the aircraft is shown below and consists of two static ports located on the sides of the aircraft forward of the cabin and by a pitot tube located on the left wing strut.
FIG. 7-5. AIRSPEED INDICATOR SYSTEM
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SYSTEMS
BRAKES
The aircraft's braking system is a single system acting on both wheels of main landing gear through disk brakes, the same circuit acts as parking brake via an intercept valve. To activate brakes it is sufficient to verify that brake shut-off valve positioned on tunnel between pilots is OFF, then activate brake lever as necessary. To activate parking brake pull brake lever and set brake shut-off valve to ON.
MARKING & PLACARDS
To compensate for deviation errors of the magnetic compass, the following
correction card is located immediately below compass:
This placard has to be compiled by certified operator with valid and proper
instrumentation.
The following placard is located on the cabin's floor tunnel, near the hydraulic
brake circuit shutoff valve:
Refer to section 9 for possible variations.
For
N
30
60 E 120
150
Steer
For
S
210
240
W
300
330
Steer
DATE
RADIO ON
AIRPATH
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SYSTEMS
Two throttle control knobs are located on instrument panel.
One is positioned centrally while the other is on the upper left-hand side. The following placard is near each one:
A throttle friction lock is located on the instrument panel to maintain desired setting. The following placard is positioned near friction lock:
Refer to section 9 for possible variations.
Fuel shutoff valves are located on cabin truss forward members. RH valve shuts off fuel flow from RH fuel tank; LH valve shuts off fuel flow from LH fuel tank. When valve lever is aligned with truss member, the valve is open; if lever is rotated 90° wrt truss member, the valve is closed. A 20x8mm OPEN - CLOSED placard is placed near each shutoff valve. The following placard is placed near the RH forward truss member shutoff valve:
ON
OFF
LH FUEL TANK
SHUT-OFF VALVE
ON
OFF
LH FUEL TANK
SHUT-OFF VALVE
The cabin heat control knob is located on the instrument panel central area just to the right of the throttle control; the following placard is next to it:
The carburetor heat control knob is located on the instrument panel central area just to the left of the throttle control; the following placard is next to it:
The trim switch control is located on the upper central area of the instrument panel alternatively allocating trim
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SYSTEMS
control to either RH or LH control stick. The following placard is positioned just above it:
A switch located on the upper central area of the instrument panel interrupts power supply to the trim system in case of malfunction. The following placard is positioned near switch:
Circuit breakers are located on lower right side of instrument panel and each breaker is individually marked as follows: (from left to right):
The flap control switch is located on the lower portion of the instrument panel, slightly towards the right. The following placards are just next to it:
A placard measuring 74x7 mm is located on the instrument panel to indicate fire extinguisher position:
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SYSTEMS
Generator and Master switches are located on the lower left side of the instrument
panel and 4 labels are placed around them: one on top, one on RH side, one on bottom and one on LH side:
ON
G
E N E R A T O R
M
A S T E R
OFF
A generator warning light is located on the upper right side
of the instrument panel and is marked with the following label:
PLACARDS OUTSIDE CABIN
The overflow reservoir cap for antifreeze liquid bears the following placard:
Brake fluid reservoir cap bears the following placard:
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SYSTEMS
The following placard is located in proximity of fuel filler caps (28x63mm):
The following placards are located on oil reservoir:
The following label is located below each door for emergency opening:
Main landing gear tire inflation pressure is indicated in the
following label affixed on each spring-leaf strut:
The following label indicates inflation pressure for nose
gear tire and is affixed on nose gear assy:
The 0° reference mark for stabilator balance is located on
left hand side of tail cone in proximity of stabilator
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The following aircraft identification placard is located on tailcone:
TECNAM S.R.L. P92 - JS S/N __________ CERT. N° A-340
On the right side of the tail cone, next to the
battery case access door, is present the following placard (69x17mm):
On the right side of the tail cone, on the power receptacle’s door is present the
following placard (135x25mm).
12 Volt - DC
EXTERNAL POWER RECEPTACLE
On both the main landing gear fairings the following placard (120x22mm) is
present:
NO STEP
BATTERY INSIDE
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GROUND HANDLING & SERVICE
SECTION 8
GROUND HANDLING & SERVICE
TABLE OF CONTENTS
INTRODUCTION ...................................................................................................... 2
AIRCRAFT INSPECTION PERIODS ....................................................................... 2
AIRCRAFT ALTERATIONS OR REPAIRS ............................................................. 2
GROUND HANDLING .............................................................................................. 2
CLEANING AND CARE............................................................................................ 3
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GROUND HANDLING & SERVICE
INTRODUCTION
This section contains factory-recommended procedures for proper ground handling and routine care and servicing. It also identifies certain inspection and maintenance requirements, which must be followed if the aircraft is to retain its new-plane performance and dependability. It is recommended to follow a planned schedule of lubrication and preventive maintenance based on climatic and flying conditions encountered locally.
AIRCRAFT INSPECTION PERIODS
Inspection intervals occur at 100 hours and in accordance with special inspection schedules which are added to regularly scheduled inspections. Correct maintenance
procedures are described in the aircraft’s Service Manual or in the engine’s Service
Manual.
AIRCRAFT ALTERATIONS OR REPAIRS
It is essential that the responsible Airworthiness Authority be contacted prior to any alterations on the aircraft to ensure that airworthiness of the aircraft is not violated. For repairs, refer to aircraft’s Service Manual.
GROUND HANDLING
TOWING
The aircraft is most easily and safely maneuvered by hand by pushing on wing struts near attachments or by pulling it by its propeller near the axle. A tow bar can be fixed onto nose gear fork. Aircraft may be steered by turning rudder or, for steep turns, by pushing lightly on tailcone to lift nose wheel.
PARKING AND TIE-DOWN
When parking airplane outdoors, head it into the wind and set the parking brake. If chocks or wedges are available it is preferable to use the latter. In severe weather and high wind conditions it is wise to tie the airplane down. Tie­down ropes shall be fastened to the wing strut attachments and anchoring shall be provided by ramp tie-downs. Nose gear fork can be used for front tie-down location.
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GROUND HANDLING & SERVICE
Flight controls shall be secured to avoid possible weathervaning damage to moving surfaces. For this purpose, seatbelts may be used to latch control stick to prevent its movement.
JACKING
Given the light empty weight of the aircraft, lifting one of the main wheels can easily be accomplished even without the use of hydraulic jacks. Remove the aluminum panel located between the steel springs and, while one person lifts one half-wing by acting on the spar immediately before the wingtip, another person will place a suitable stand with protective cover under the steel spring attachment.
LEVELING
Aircraft leveling may become necessary to check wing incidence, dihedral or the exact location of CG. Leveling is obtained when the cabin floor and, in transverse direction, the main gear support beam are horizontal.
ROAD TRANSPORT
It is recommended to secure tightly all aircraft components onto the cart to avoid damage during transport. Minimum cart size is 7x2.5 meters. It is suggested to place
wings under the aircraft’s bottom, secured by specific clamps. Secondary
components such as stabilator and struts shall be protected from accidental hits using plastic or other material. For correct rigging and de-rigging procedure, refer to Service Manual.
CLEANING AND CARE
To clean painted surfaces, use a mild detergent such as shampoo normally used
for car finish; use a soft cloth for drying
The plastic windshield and windows should never be dusted when dry; use lukewarm soapy water and dry using chamois only. It is possible to use special glass detergents but, in any case, never use products such as gasoline, alcohol, acetone or other solvents. To clean cabin interior, seats, upholstery and carpet, it is generally recommended to use foam-type detergents.
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LEFT INTENTIONALLY BLANK
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SUPPLEMENTS
SECTION 9
SUPPLEMENTS
TABLE OF CONTENTS
GARMIN GNS 430 GPS/VHF COMM/NAV ............................................................ 3
1 INTRODUCTION .............................................................................................. 3
1.2 GENERAL ...................................................................................................... 3
1.3 LIMITATIONS ................................................................................................. 4
1.4 EMERGENCY PROCEDURES ...................................................................... 5
1.5 NORMAL OPERATION .................................................................................. 5
1.6 PERFORMANCE............................................................................................ 5
1.7 WEIGHT AND BALANCE ............................................................................... 6
1.8 SYSTEMS ...................................................................................................... 6
BANNER TOWING ................................................................................................... 7
2 INTRODUCTION .............................................................................................. 7
2.1 GENERAL ...................................................................................................... 7
2.2 LIMITATIONS ................................................................................................. 7
2.3 EMERGENCY PROCEDURES ...................................................................... 9
2.4 NORMAL PROCEDURES .............................................................................. 9
2.5 PERFORMANCE.......................................................................................... 11
2.6 WEIGHT & BALANCE .................................................................................. 14
EQUIPMENT LIST ................................................................................................. 14
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SUPPLEMENTS
2.7 SYSTEMS .................................................................................................... 15
DIFFERENTIAL BRAKE SYSTEM ....................................................................... 18
3 INTRODUCTION ............................................................................................ 18
3.1 GENERAL .................................................................................................... 18
3.2 LIMITATIONS ............................................................................................... 18
3.3 EMERGENCY PROCEDURES .................................................................... 18
3.4 NORMAL OPERATION ................................................................................ 18
3.5 PERFORMANCE.......................................................................................... 18
3.6 WEIGHT AND BALANCE ............................................................................. 18
3.7 SYSTEMS .................................................................................................... 19
CENTRAL THROTTLE CONTROL SYSTEM ...................................................... 21
4 INTRODUCTION ............................................................................................ 21
4.1 GENERAL .................................................................................................... 21
4.2 LIMITATIONS ............................................................................................... 21
4.3 EMERGENCY PROCEDURES .................................................................... 21
4.4 NORMAL OPERATION ................................................................................ 21
4.5 PERFORMANCE.......................................................................................... 21
4.6 WEIGHT AND BALANCE ............................................................................. 21
4.7 SYSTEMS .................................................................................................... 21
NEW ANALOGICAL INSTRUMENTS PANEL .................................................... 23
5 INTRODUCTION ............................................................................................ 23
5.2 GENERAL .................................................................................................... 23
5.3 LIMITATIONS ............................................................................................... 23
5.4 EMERGENCY PROCEDURES .................................................................... 23
5.5 NORMAL OPERATION ................................................................................ 23
5.6 PERFORMANCE.......................................................................................... 23
5.7 WEIGHT AND BALANCE ............................................................................. 23
5.8 SYSTEMS .................................................................................................... 24
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SUPPLEMENTS
SUPPLEMENT N° 1
GARMIN GNS 430 GPS/VHF COMM/NAV
1 INTRODUCTION
This section contains supplementary information for safe and efficient operation of the aircraft if equipped with a Garmin GNS 430 system.
1.2 GENERAL
1. The GPS GNS 430 Global Positioning System is an integrated system that
contains a GPS navigation system in addition to a VHF COMM radiotransceiver and a VOR/ILS receiver.
2. The system includes an antenna for GPS, a receiver for GPS, a VOR/LOC
antenna, a VOR/ILS receiver, a VHF Comm antenna and a VHF Comm tranceiver.
3. The main function of the VHF Comm is to allow communication with the
control tower.
4. The VOR/ILS function is to receive and demodulate VOR and LOC
signals.
5. The GPS section is dedicated to signal acquisition from the GPS satellite
system and to furnish real-time information with respect to position, speed and time.
6. With appropriate signals the GPS GNS 430 can:
plan VFR/IFR routes, track waypoints and plan non-precision
instrument approaches (GPS, LORAN-C, VOR, VOR-DME, TACAN, NDB, NDB-DME, RNAV) in accordance with AC 20-138;
7. Reference coordinates used for navigation are WGS-84.
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1.3 LIMITATIONS
1. The “Pilot’s guide and Reference” p/n 190-00140-00 rev. F dated July
2000 or later versions, must be available for proper use of the instrument.
2. Only VFR use is permitted.
3. The GPS section must use the following (or more recently approved) software
versions:
The software version of the main subsystem is displayed by the GNS 430 immediately after start-up for 5 seconds. Remaining subsystems software versions may be verified in sub-page 2 of the AUX Group display for “SOFTWARE/DATA BASE VER”.
4. The following default settings must be keyed-in in the SETUP 1 menu of the
GNS430 receiver before any other operation:
DIS, SPD nm kt (select navigation unit to “nautical miles” and “knots”);
ALT,VS ft fpm (select altitude to “feet ” and “feet per minute”); MAP DATUM WGS 84 (select map datum WGS84); POSN deg-min (select grid for nav unit to decimal-minutes);
Subsystem
Software version
MAIN
2.00
GPS
2.00
COMM
1.22
VOR/LOC
1.25
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1.4 EMERGENCY PROCEDURES
1. If the information provided by the Garmin GNS430 is not available or
manifestly wrong, it is necessary to use other navigation instruments.
2. If the message “WARN” appears in the lower left portion of the display, the
receiver cannot be considered useful as a navigation aid. The pilot must use the VLOC receiver or an alternative navigation system.
3. If the message “INTEG” appears in the lower left portion of the display, the
RAIM function is unavailable. The pilot must use the VLOC receiver or an alternative navigation system;
4. In emergency flight conditions, pressing the COM flip-flop knob for 2
seconds will automatically tune-in the 121.500MHz emergency frequency.
1.5 NORMAL OPERATION
1. DETAIL FOR NORMAL OPERATION
Normal operation is described in the “Pilot’s guide and Reference” P/N
190-00140-00 rev. F dated July 2000 or later versions.
2. GARMIN GNS 430 DISPLAY.
Data for GNS 430 system appears on GARMIN GNS430 display. Data source is either the GPS or the VLOC as indicated above the CDI
switch of the GARMIN 430 display.
1.6 PERFORMANCE
No variations.
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SUPPLEMENTS
1.7 WEIGHT AND BALANCE
See section 6 of the present manual.
1.8 SYSTEMS
See “GNS 430 Pilot’s Guide” p/n 190-00140-00 rev. F dated July 2000 or later versions, for a complete description of the system.
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SUPPLEMENTS
SUPPLEMENT NO. 2
BANNER TOWING
2 INTRODUCTION
This section contains supplementary information for a safe and efficient operation of the aircraft if equipped with a hook for towing banners (Mod. Number 92/27).
2.1 GENERAL
CERTIFICATION BASIS
This installation has been certified under the technical specifications listed into the Tecnam Report 92/104.
2.2 LIMITATIONS
Section 2 includes operating limitations, instrument markings, and basic placards necessary for safe banner-towing operations.
APPROVED BANNER DIMENSION
The banner approved to be operated with the P92-JS is of the type equipped with wheels. The maximum banner surface that has been towed during the tests is 140m2.
WEIGHT
The aircraft’s MTOW equipped with a 140m2 banner reaches 460kg. For banners whose surface is lower than 140m2, please refer to the table in paragraf 2.5 in this Section
AIRFIELD ALTITUDE
The highest approved airfield altitude for take-off operations while towing banner of 140m2 is 3000ft.
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SUPPLEMENTS
AIRSPEED
For all flap settings, the minimum towing airspeed is 53 KIAS.
WARNING
The maximum towing airspeed depends on the banner’s surface. For further information, please refer to the banner manufacturer specifications/limitations.
APPROVED MANEOUVRES
The P92-JS, while towing a banner, is cleared to do only the manoeuvres pertinent to normal flight.
DEMONSTRATED CROSS WIND OPERATIONS
The aircraft’s controllability was investigated during take-off with a cross wind velocity of 5 kts.
LIMITATION PALACARDS
On the instrument panel the following limitation placards must be present:
MINIMUM TOWING AIRSPEED = 53 KIAS
REFER TO FLIGHT MANUAL
SUPPLEMENT 9.2 FOR
LIMITATIONS DURING
TOWING OPERATIONS,
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