Section 1Subj. AFM • Flight Manual P92-JS (EN)

FLIGHT MANUAL

Doc. No. 92/61 - Edition No. 3: May 25, 2010
Revision No. 5: July 12, 2022

P92-JS

MANUFACTURER: COSTRUZIONI AERONAUTICHE TECNAM S.r.l.

AIRCRAFT MODEL: P92-JS

TYPE CERTIFICATE: No. EASA A.412 (SO/A-340)

SERIAL NUMBER: ...............................

YEAR OF MANUFACTURE: ...............................

REGISTRATION MARKS: ...............................

This manual contains information to be provided to the pilot as required by EASA, in addition to further information provided by the manufacturer.

This manual must always be carried on board the aircraft.

The aircraft must be operated in accordance with the information and limitations contained in this document.

Revision Log

Any revision to this Manual, except actual weighing data, shall be recorded in the following table and, in the case of Approved Sections, countersigned by the competent airworthiness authority.

New or amended text in revised pages will be indicated by a black vertical line in the left margin; the revision number and date will be shown on the left side of the page.

Rev. No.	Sections Affected	Pages Affected	Date	EASA/DOA Approval
1	6	10 to 14	25/02/2015	DOA
	7	14, 16	25/02/2015	DOA
	9	22, 24	25/02/2015	DOA
	9	25 to 28	25/02/2015	DOA
2	1	6	16/06/2015	DOA
	2	4, 5, 7, 11	16/06/2015	EASA
	4	8, 9	16/06/2015	EASA
	7	12, 14, 16	16/06/2015	DOA
	9	29 to 32	16/06/2015	DOA
3	0	All	09/09/2016	DOA
3	6	10 to 13	09/09/2016	DOA
4	0	All	15/07/2019	DOA
4	6	11 to 13	15/07/2019	DOA
5	0	1, 2, 4, 6	12/07/2022	DOA
	2	3	12/07/2022	DOA
	4	5, 9	12/07/2022	DOA
	5	13	12/07/2022	DOA
	7	18	12/07/2022	DOA

List of Effective Pages

Section	Revision
Section 0	Rev 5
Section 1	Rev 2
Section 2	Rev 5
Section 3	Rev 0
Section 4	Rev 5
Section 5	Rev 5
Section 6	Rev 4
Section 7	Rev 5
Section 8	Rev 0
Section 9	Rev 2

General Index

Contents	Section
General	Section 1
Limitations	Section 2*
Emergency Procedures	Section 3*
Normal Procedures	Section 4*
Performance	Section 5**
Weight and Balance / Equipment List	Section 6
Aircraft and Systems Description	Section 7
Handling, Servicing and Maintenance	Section 8
Supplements	Section 9*

* Section approved by EASA

** Section partially approved by EASA

Sections 2, 3, 4, 5 are approved by EASA: No. 10030344 dated 11.06.2010

Section 9 (suppl. 1) is approved by EASA: No. 2004-1787 dated 02.03.2004

Section 9 (suppl. 2) is approved by EASA: No. 2004-6324 dated 17.06.2004

SECTION 1 - GENERAL

Introduction

The P92-JS is a two-seat single-engine aircraft with strut-braced high rectangular wing, fixed main landing gear and steerable nose wheel.

This Flight Manual has been prepared to provide pilots and instructors with the information necessary for 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 terminology commonly used.

Certification Basis

Aircraft

This aircraft type has been approved by EASA/ENAC in accordance with JAR-VLA dated April 26, 1990 with amendments 91/1 and 92/1.

Noise Certification Basis

JAR-36 Sub. C Edition: May 23, 1997 - ICAO/Annex 16 Chap. 10 edition 1993

Warnings - Cautions - Notes

The following definitions apply to warnings, cautions and notes used in the Flight Manual.

WARNING Indicates that failure to observe the corresponding procedure results in an immediate or significant degradation of flight safety.

CAUTION Indicates that failure to observe the corresponding procedure results in a minor or more or less long-term degradation of flight safety.

NOTE Draws attention to any special item not directly related to safety but which is important or unusual.

Three-View Drawing

Main dimensions:

Wing span: 8.7 m
Fuselage width: 1.8 m
Height: 2.5 m
Length: 6.4 m
Stabilator span: 2.9 m

NOTE

Dimensions shown refer to an aircraft weight of 550 kg (and 600 kg) and normal tire pressure.
Propeller ground clearance: 320 mm
Propeller ground clearance with flat nose tire and nose gear strut compressed: 102 mm
Minimum ground turning radius: 5.5 m

Descriptive Data

WING

Parameter	MTOW 550 kg	MTOW 600 kg
Wing span	8.7 m	8.7 m
Wing chord	1.4 m	1.4 m
Wing area	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	1.5deg	1.5deg

FUSELAGE

Parameter	MTOW 550 kg	MTOW 600 kg
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

Parameter	MTOW 550 kg	MTOW 600 kg
Stabilator span	2.900 m	2.900 m
Vertical fin span	1.230 m	1.230 m

LANDING GEAR

Parameter	MTOW 550 kg	MTOW 600 kg
Track	1.800 m	1.800 m
Wheelbase	1.600 m	1.600 m
Main gear tires	Air Trac 5.00-5
Cleveland wheel and brake kit	199-102
Nose wheel tire	Sava 4.00-6

Control Surface Deflections

Surface	Deflection	Tolerance
Ailerons	Up 20deg / Down 15deg	+/- 2deg
Stabilator	Up 18deg / Down 3deg	+/- 1deg
Trim tab	2deg ; 12deg	+/- 1deg
Rudder	Right 25deg / Left 25deg	+/- 1deg
Flaps	0deg - 38deg	+/- 1deg

Engine

Manufacturer	Bombardier-Rotax GmbH
Model	912 S2
Certification basis	FAR 33 Amendment 15
Austrian type certificate	No. TW 9-ACG dated Nov. 27, 1998
Type	4 horizontally opposed cylinders with total displacement of 1352 cc, mixed cooling (liquid cooled heads and air cooled cylinders), dual carburetors, integrated reduction gear with torsional damper.
Maximum power	73.5 kW (98.6 hp) @ 5800 rpm (max. 5 min.)
Continuous power	69.0 kW (92.5 hp) @ 5500 rpm (continuous)

Propeller

Manufacturer	HOFFMANN Propeller
Certification basis	CAR Part 14
Type certificate	SO/E 30 dated 10/12/1999
Model	HO17GHM A 174 177C
Number of blades	2
Diameter	1740 mm (no reduction allowed)
Type	Fixed pitch - wood

Fuel

Fuel type	EN 228 Premium EN 228 Premium plus AVGAS 100LL (see Section 2.9)
Fuel tanks	2 wing tanks integral with wing leading edge with fuel filter 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 with option)

Oil System

System type	Pressure circulation, with external oil tank
Oil	Automotive oil type API "SF" or "SG", preferably synthetic or semi-synthetic
Oil capacity	3.0 liters

Cooling

System type	Mixed air and liquid, pressurized closed circuit
Coolant	Antifreeze and water mixture
Capacity	3 liters

Maximum Certified Weights

Parameter	550 kg Version	600 kg Version
Maximum takeoff weight (MTOW)	550 kg	600 kg
Maximum landing weight	550 kg	600 kg
Maximum baggage weight	20 kg	20 kg

Standard Weights

Parameter	550 kg Version	600 kg Version
Standard empty weight	325 kg	325 kg
Maximum useful load	225 kg	275 kg

Specific Loads

Parameter	550 kg Version	600 kg Version
Wing loading	45.8 kg/m²	50 kg/m²
Power loading	5.6 kg/hp	6.1 kg/hp

Abbreviations and Terminology

Airspeed Terminology and Symbols

KCAS: Knots Calibrated Airspeed - The indicated airspeed corrected for position and instrument errors, expressed in knots.
KIAS: Knots Indicated Airspeed - The speed shown on the airspeed indicator, expressed in knots.
KTAS: Knots True Airspeed - The speed relative to undisturbed air, obtained by correcting KCAS for altitude and temperature, expressed in knots.
V_FE: Maximum Flap Extended Speed - The maximum speed permitted with flaps in a prescribed extended position.
V_NO: Maximum Structural Cruising Speed - The speed that should not be exceeded except in smooth air, and then only with caution.
V_NE: Never Exceed Speed - The speed limit that must never be exceeded under any circumstances.
V_S: Stall Speed
V_S0: Stall Speed in Landing Configuration
V_S1: Stall Speed in Clean Configuration (flaps 0deg)
V_X: Best Angle of Climb Speed - The speed that produces maximum altitude gain for a given horizontal distance.
V_Y: Best Rate of Climb Speed - The speed that produces maximum altitude gain in a given time.
V_r: Rotation Speed - The speed at which the aircraft rotates about the pitch axis during takeoff.
V_LO: Lift-off Speed - The speed at which the aircraft typically lifts off the ground.
V_obs: Obstacle Clearance Speed - The speed at which the aircraft clears a 15 m obstacle during takeoff or landing.

Meteorological Terminology

OAT: Outside Air Temperature - The free air static temperature expressed in degrees Celsius (degC).
T_S: Standard Temperature - Is 15degC at sea level and decreases by 2degC per 1000 ft of altitude.
H_P: Pressure Altitude - The altitude read on an altimeter when the barometric scale is set to 1013 mb.

Engine Power Terminology

RPM: Revolutions Per Minute - The number of propeller revolutions per minute; multiplied by 2.4286 gives engine rpm.

Performance and Flight Planning Terminology

Crosswind Speed: The crosswind component for which adequate control of the aircraft during takeoff and landing is guaranteed.
Usable Fuel: The fuel available for flight planning.
Unusable Fuel: The quantity of fuel that cannot be safely used during flight.
g: The acceleration of gravity.
TOR: Take-Off Run - The takeoff ground roll distance measured from the actual start to the point of wheel lift-off.
TOD: Take-Off Distance - The total takeoff distance measured from start to clearance of a 15 m obstacle.
GR: Ground Roll - The distance measured during landing from actual touchdown to the point of stop.
LD: Landing Distance - The distance measured during landing from clearance of a 15 m obstacle to actual stop.
S/R: Specific Range - The distance (in nautical miles) that can be expected at a specific power setting and/or flight configuration per kg of fuel consumed.

Weight and Balance Terminology

Datum: An imaginary vertical plane from which all horizontal distances are measured for balance purposes.
Arm: The horizontal distance from the datum reference to the center of gravity (C.G.) of an item.
Moment: The product of an item's weight multiplied by its arm.
C.G. (Center of Gravity): The point at which the aircraft, or equipment, would balance if suspended. Its distance from the datum reference is found by dividing the total moment by the total weight of the aircraft.
Standard Empty Weight: The weight of a standard aircraft, including unusable fuel, operating fluids and engine oil.
Basic Empty Weight: The standard empty weight plus the weight of optional equipment.
Useful Load: The difference between takeoff weight and basic empty weight.
Maximum Weight: The maximum certified weight of the aircraft.
Maximum Takeoff Weight (MTOW): The maximum weight approved for the start of the takeoff run.
Maximum Landing Weight: The maximum weight approved for ground contact during landing.
Tare: The weight of chocks, blocks, stands, etc. used when weighing an aircraft, and is included in scale readings. Tare is subtracted from the scale reading to obtain the actual (net) weight of the aircraft.

Unit Conversion Table

Temperature

From	Formula	To
Fahrenheit [degF]	(degF - 32) x 5/9	Celsius [degC]
Celsius [degC]	(degC x 9/5) + 32	Fahrenheit [degF]

Forces

From	Multiply by	To
Kilograms [kg]	2.205	Pounds [lbs]
Pounds [lbs]	0.4536	Kilograms [kg]

Speed

From	Multiply by	To
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

From	Multiply by	To
Atmospheres [atm]	14.7	Pounds/square inch [psi]
Pounds/square inch [psi]	0.068	Atmospheres [atm]

Length

From	Multiply by	To
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

From	Multiply by	To
Liters [l]	0.2642	US Gallons [US Gal]
US Gallons [US Gal]	3.785	Liters [l]

Area

From	Multiply by	To
Square meters [m²]	10.76	Square feet [sq ft]
Square feet [sq ft]	0.0929	Square meters [m²]

P92-JS FLIGHT MANUAL

Section 0: Introduction | Section 1: General

Edition 3 - Revision 5 - July 12, 2022

English version for educational purposes - Always refer to the original document

Manual Index Section 2: Limitations