Aviation Artur Trendak TERCEL Technical specifications

Edition 1 04 Jul 2016
Change no.:
Document no.: TERCEL-AFM-001-EN
AVIATION ARTUR TRENDAK
FLIGHT MANUAL
GYROCOPTER
SERIAL NUMBER: T&S J22015S
REGISTRATION MARKS:
NUMBER ON FILE:
THE MANUAL WAS APPROVED WITH A DECISION OF PRESIDENT OF THE CIVIL AVIATION AUTHORITY
DATED …………………………………. NO.………………………
“
“
“
ULTRALIGHT” CATEGORY
THIS GYROCOPTER CAN BE USED IN THE “ULTRALIGHT” CATEGORY FOR
LEISURE, SPORTS AND DEMONSTRATION PURPOSES AS WELL AS OTHERS,
EXCLUDING AIR TRANSPORT.
USING THIS GYROCOPTER FOR TRAINING AND PRACTICE TO OBTAIN A
CERTIFICATE OF QUALIFICATIONS OF AN ULTRALIGHT GYROCOPTER PILOT AS
WELL AS HAVE QUALIFICATIONS ENTERED IN THIS CERTIFICATE CAN BE DONE
SOLELY IN A CERTIFIED TRAINING CENTRE.
THE GYROCOPTER MUST BE USED ACCORDING TO THE RESTRICTIONS AND
INFORMATION STATED IN THIS INSTRUCTION MANUAL.
THIS MANUAL MUST ALWAYS BE AVAILABLE ON BOARD THE GYROCOPTER.

Edition 1 04 Jul 2016
Change no.:
Document no.: TERCEL-AFM-001-EN
The manual has been developed as per the requirements of the regulations in Annex No. 5
“Ultralight Aircraft” - of the Decree of the Minister of Infrastructure dated 25 April 2005 on
Excluding the Application of Some of the Laws of the Act on Air Law for Some Sorts of Aircraft
as well as Defining the Conditions and Requirements concerning the Use of this Aircraft (Official
Journal 107 section 904) with subsequent amendments.
It is not allowed to make any entries and supplements in this “Flight Manual” without the consent
of the Civil Aviation Authority.
In case this Manual is lost, you should notify the Civil Aviation Authority instantaneously, and
when outside the border of your country - an equivalent institution.
Any person to find this manual is requested to send it in instantaneously to Urząd Lotnictwa
Cywilnego (Civil Aviation Authority), 02-247 Warszawa, ul. Marcina Flisa 2, Poland, and when
outside the border of your country to an equivalent institution.

AVIATION
Artur Trendak
FLIGHT MANUAL
Organizational Information
Chapter 0
Edition 1 21 Aug 2014
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Document no.: TERCEL-AFM-001-EN
Page 0-1
Chapter 0 Organizational Information
0.1 Register of Changes
Any changes of this manual, except for the up-to-date weighing data, must be recorded in the
table below as well as be approved by the Civil Aviation Authority (CAA).
A new or revised text in changed pages must be marked with a black vertical line on the
margin and a change number. The number of the last change in a given page and its date must be
placed in the page footer. Every time a change is entered, the pages listed in the table below must
be mentioned.
Change no.
Description of change
Pages affected
Entry date
Signature

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Artur Trendak
FLIGHT MANUAL
Organizational Information
Chapter 0
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Document no.: TERCEL-AFM-001-EN
Edition 1 21 Aug 2014
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Aviation
Artur
Trendak
FLIGHT MANUAL
Organizational Information
Chapter 0
Edition 1 21 Aug 2014
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AVIATION
Artur Trendak
FLIGHT MANUAL
Organizational Information
Chapter 0
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Document no.: TERCEL-AFM-001-EN
Edition 1 21 Aug 2014
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0.3 Table of Contents
Chapter
Title
0
Organizational Information
1
General Information
2
Restrictions
3
Emergency Procedures
4
Normal Procedures
5
Performance
6
Weight and Position of the Centre of Gravity
7
Description of the Gyrocopter and its Equipment
8
Manoeuvring, Temporary Operation and Maintenance
9
Supplements

AVIATION
Artur Trendak
FLIGHT MANUAL
General Information
Chapter 1
Page 1-1
Document no.: TERCEL-AFM-001-EN
Edition 1 21 Aug 2014
Change no.:
Chapter 1 General Information
1. page
1.1 Introduction ................................................................................................ 1-2
1.2 Basis for Airworthiness Acknowledgment ................................................ 1-2
1.3 Description of the Gyrocopter .................................................................... 1-2
1.3.1 General Data .......................................................................................... 1-3

AVIATION
Artur Trendak
FLIGHT MANUAL
General Information
Chapter 1
Page 1-2
Document no.: TERCEL-AFM-001-EN
Edition 1 21 Aug 2014
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1.1 Introduction
This manual has been written to provide pilots and engineers with information essential for
safe and effective operation on gyrocopter. The manual also contains basic guidelines
from the gyrocopter manufacturer and also legal requirements concerning the performance of
flights.
The manual is not a substitute for theoretical and
practical training in respect of piloting gyrocopters.
gyrocopter pilots must hold a qualification certificate or a valid licence for ultralight
aircrafts with specialization for gyrocopters. Before flight pilots must become acquainted with the
uniqueness of the gyrocopter. We recommend you read both the Flight Manual and the Service
Manual to be fully familiar with the structure, all the equipment and the driving unit of the
gyrocopter.
The gyrocopter can only be used for flight when it is technically operative and holds a valid
authorization to perform flights. An authorization to perform flights is entered into the ultralight
aircraft book, which is a document identifying an ultralight aircraft and its units as well as
containing details about the history of usage.
The utilized gyrocopter should be entered into aircraft records kept by the Civil Aviation
Authority as well as hold current air third-party insurance.
1.2 Basis for Airworthiness Acknowledgment
The legal basis for operating a gyroplane is provided by national law and its respective
regulations. The instructions and conditions contained have to be considered when operating the
gyroplane. All documented performance data and operating procedures have been identified within
the certification processes for this gyroplane by means of flight test and analysis.
gyrocopter meet German and Polish Civil Airworthiness Requirements. They
comprise requirements and constitute the basis for the issue of Certificates, Permits and Approvals
in accordance with the Air Navigation Order.
1.3 Description of the Gyrocopter
is a two-seat ultralight gyrocopter. The main structural component is the fuselage
which is constructed with composite material. Two metal tail booms are attached from the lower part
of the fuselage to a twin vertical tail unit. This consist of twin stabilizers and rudders on which a
horizontal stabilizer is attached complete with winglets of constructed composite material. A metal
mast is affixed to the fuselage structure, on which the control head with the rotor is mounted.
The two-blade rotor of metal structure is manufactured and delivered as a set (blades plus a
hub) by the AVIATION Artur Trendak Company. The blades, made from drawn aluminium, are
entirely anodized and perfectly balanced.

AVIATION
Artur Trendak
FLIGHT MANUAL
General Information
Chapter 1
Page 1-3
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The is powered with a AAT&S CA 912 ULT engine. It is a Rotax 912 UL engine,
modified by the AVIATION ARTUR TRENDAK Company by adding an Iveco turbocharger. It is
equipped with a three-blade composite propeller DUC FC-R INCONEL.
The undercarriage is a stationary three-wheel one in a set with the front wheel. The main legs
are elastic and made of composite. The front leg is dampened with a wheel pneumatic unit. The
undercarriage is made with wheels with a diameter of 450mm.
The spacious cabin with a width of 136 cm is accessible through a large door on the left and
right sides. Rich glazing ensures optimum visibility. Two ergonomic seats can be set up. Each chair
is equipped with adjustable four-point belts.
1.3.1 General Data
Geometric data
Rotor diameter
8.60
m
Rotor surface
60.82
m2
Rotor blade chord
0.22
m
Overall length (without rotor)
5.04
m
Fuselage width
2.35
m
Track of wheels
2.20
m
Cockpit width
1.36
m
Overall width
2.35
m
Overall height
2.87
m
Wheel diameter
0.45
m
Weight data
kg
lb
Maximum take-off weight
560
1234
Empty weight*
326
718
Load capacity
265
584
Data of the power unit
Engine type
CA 912 ULT
Power
121 KM at 5800 rpm
Reducer ratio
1 : 2.43
Propeller
DUC FC-R INCONEL
Propeller diameter
1.727 m
Capacity of the fuel
tanks
120 litres
*Empty weight including rotor weight(40kg)

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Artur Trendak
FLIGHT MANUAL
General Information
Chapter 1
Page 1-4
Document no.: TERCEL-AFM-001-EN
Edition 1 21 Aug 2014
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AVIATION
Artur Trendak
FLIGHT MANUAL
Restrictions
Chapter 2
Edition 1 21 Aug 2014
Change no.:
Document no.: TERCEL-AFM-001-EN
Page 2-1
Chapter 2 Restrictions
2. page
2.1 Introduction ................................................................................................ 2-2
2.2 Flight Speed ............................................................................................... 2-2
2.3 Speedometer Markings .............................................................................. 2-2
2.4 Driving Unit ............................................................................................... 2-3
2.5 Rotor Rotational Speed ............................................................................... 2-3
2.6 Rotor Tachometer Markings ....................................................................... 2-4
2.7 Weights ....................................................................................................... 2-4
2.8 Position of the Centre of Gravity ................................................................ 2-5
2.9 Manoeuver Limitations ............................................................................... 2-5
2.10 Manoeuvre Load Factor .............................................................................. 2-6
2.11 Crew ............................................................................................................ 2-6
2.12 Sorts of Usage ............................................................................................. 2-6
2.13 Fuel.............................................................................................................. 2-6
2.14 Wind Speed Restrictions............................................................................. 2-6
2.15 Other Restrictions ....................................................................................... 2-7

AVIATION
Artur Trendak
FLIGHT MANUAL
Restrictions
Chapter 2
Page 2-2
Document no.: TERCEL-AFM-001-EN
Edition 1 21 Aug 2014
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2.1 Introduction
Chapter 2 embraces the restrictions of usage, markings of instruments and basic plaques,
crucial to the safe usage of the gyrocopter, its engine, standard systems and standard equipment.
2.2 Flight Speed
Speed restrictions and their importance in usage are presented in the table below:
Speed
IAS
[km/h]
IAS
[kt]
Notes
VNE
Speed never to be
exceeded
182
98
Do not exceed this speed in any usage.
VNO
Maximum structural
cruising speed
130
70
Do not perform full or violent movements with
the control surfaces above this speed, except for
tranquil atmosphere and exercising with
caution.
Vmin
Minimum speed
60
32
The minimum speed of established horizontal
flight.
CAUTION!
Speedometer indications fluctuate during steep climbs and descents due to the changes in
pitch attitude.
2.3 Speedometer Markings
Marking
value or range
Notes
[km/h]
[kt]
Green arch
0÷130
0÷70
Range of normal usage
Yellow arch
130÷182
70÷98
Warning range
Red line
182
98
Never-exceed speed (VNE)
Yellow triangle
100
54
Flight speed at the best rate of climb speed (VY)
Moreover, one of the speed placards below must be installed on the instrument panel in front
of the pilot (corresponding with the units for scaling the speedometer):
I
A
S
VNE = 182 km/h
VY= 105 km/h
VAPP = 90 km/h
1 person
VX= 95 km/h
Vmin = 60 km/h
VAPP = 90 km/h
2 people
I
A
S
VNE = 98 kt
VY= 57 kt
VAPP = 49 kt
1 person
VX= 51 kt
Vmin = 32 kt
VAPP = 49 kt
2 people

AVIATION
Artur Trendak
FLIGHT MANUAL
Restrictions
Chapter 2
Edition 1 21 Aug 2014
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Document no.: TERCEL-AFM-001-EN
Page 2-3
2.4 Driving Unit
Engine model
CA 912 ULT
Rotax 912 UL engine, modified by the AVIATION ARTUR
TRENDAK company by adding the Iveco Turbo Compressor
Power
RPM
Manifold Pressure
Maximum Take-off Power
122 hp
5800
max. 45,5 inHg
Maximum Continuous
Power
115 hp
5500
max. 45,0 inHg
75% Take-off Power
90,75 hp
-
max. 40,0 inHg
Idle
-
1450
max. 31,5 inHg
Oil type
10W40
minimum
normal
maximum
Oil temperature
50 ºC
90-110 ºC
140 ºC
Oil pressure
0,8 bar (above
3500RPM)
2-5 bar(above
3500RPM)
7 bar
Fuel (type)
Lead-free car petrol with the minimum octane number of 91 or above
Min. fuel pressure
0,15 bar
Max. fuel pressure
0,4 bar
Maximum coolant exit
temperature
120 ºC
Maximum cylinder head
temperature
135 ºC
Propeller manufacturer
DUC
Propeller model
Three-blade FC-R INCONEL Std/Inc. Propulsive Left
Propeller diameter
1.72 m
Propeller blade angle
17º (in measurement section, in accordance with the propeller
manual)
2.5 Rotor Rotational Speed
Rotor rotational speed
rpm
normal at maximum weight (MTOW)
360 - 390
normal at minimum weight (~330 kg)
330 - 340
during autorotation
310 ÷ 340
minimum for level flight
340
minimum until the full opening of the
throttle during take-off
180
maximum for using the rotor brake
150

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Artur Trendak
FLIGHT MANUAL
Restrictions
Chapter 2
Page 2-4
Document no.: TERCEL-AFM-001-EN
Edition 1 21 Aug 2014
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WARNING!
Load Factor below 1g during flight cause the rotor rotational speed to fall
and if maintained, it can lead to disaster.
2.6 Rotor Tachometer Markings
Marking
Value or range
[rpm]
Notes
Red arch
0÷200
Warning range
Green arch
200÷420
Normal range
Red arch
420÷500
Warning range
2.7 Weights
Maximum take-off weight (MTOW)
560kg
1234 lb
Nominal proper weight *
326 kg
718lb
Minimum crew weight
60 kg
132 lb
Maximum crew weight
220 kg
485 lb
Maximum one person weight
110 kg
243 lb
Maximum fuel weight
93 kg
205 lb
* - the actual proper weight for a particular model is written in the current weighing report and in
subsection 6.4 of this manual.
The current take-off weight is equal to the sum of the empty gyrocopter weight and the
weights of the crew, luggage and fuel. Under no circumstances, do not exceed the approved
maximum take-off weight (MTOW) equal to 560 kg (1234 lb). Proposed load sheet is presented
below.
Weight
Minimum
Maximum
Empty weight
-----------
----------
Crew weight
Fuel weight
Luggage weight
Total
WARNING!
Exceeding the maximum weight published is prohibited.

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Artur Trendak
FLIGHT MANUAL
Restrictions
Chapter 2
Edition 1 21 Aug 2014
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Document no.: TERCEL-AFM-001-EN
Page 2-5
Space behind the seats is limited to 10 kg (22 lb).
During solo flights, it is recommended to place a ballast on the board (on the seat fastened
with seat belts) to ensure the appropriate balancing of the machine. A ballast in the form of a sack
of sand or a can of water is recommended. The ballast must be protected against movement.
Ballast size is specified below:
Pilot left seat
weight [kg]
Ballast right
seat [kg]
Ballast right
seat [lb]
50 ÷ 60 kg
12 kg
26 lb
60 ÷ 80 kg
10 kg
22 lb
80 ÷ 100 kg
8 kg
18 lb
2.8 Position of the Centre of Gravity
The position of the centre of gravity of the gyrocopter (a sideways view) is specified through
the value of the angle whose apex is located on the transverse axle for rotor head suspension on the
mast, one arm is parallel to the vertical axis of the coordinate system related to the fuselage, and the
other arm passes through the centre of gravity of the gyrocopter. (See subsection 6.3).
The admissible range of the position of the centre of gravity of the gyrocopter in flight:
+1,5º ÷ +8,5º
Operating gyrocopter outside the load limits is prohibited.
2.9 Manoeuver Limitations
The gyrocopter has been classified in the ultralight aircraft category and is subject to
the limits below.
It is forbidden to perform:
aerobatics,
turns in which the roll angle exceeds 60º,
flights in the icing conditions,
flights when wind speed exceeds 60 km/h,
flights in the conditions of severe turbulence,
excessive side slip
low-G manoeuvers (maintain below 1 g)
WARNING!
All aerobatic manoeuvres and turns with a roll angle
of more than 60º are forbidden!
WARNING!

AVIATION
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FLIGHT MANUAL
Restrictions
Chapter 2
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Load Factor below 1g during flight cause the rotor rotational speed to fall
and if maintained, it can lead to disaster.
DIAGRAM: HEIGHT - SPEED
2.10 Manoeuvre Load Factor
Admissible manoeuvre load factor: 0/+3
SAFE
ZONE
DANGEROUS
ZONE

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Artur Trendak
FLIGHT MANUAL
Restrictions
Chapter 2
Edition 1 21 Aug 2014
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Document no.: TERCEL-AFM-001-EN
Page 2-7
2.11 Crew
The gyrocopter is a two-seater with an option with single or a double flight control system.
Minimum crew: 1 pilot.
2.12 Sorts of Usage
This gyrocopter can be used for leisure, sports, display purposes, for training, practice,
exclusive of air carriage and other reasons. Flights can be performed in the Visual Meteorological
Conditions(VMC) covered by Visual Flight Rules(VFR). Specific usage of gyrocopter is described
in Certificate of Registration given by Aviation Authority of country of registration.
2.13 Fuel
capacity of the fuel tanks
120 dm3
admissible quantity of fuel in the tanks
120 dm3
including
consumable fuel
118 dm3
non-consumable fuel
2 dm3
2.14 Wind speed restrictions
The admissible values of wind speed during flight and landing:
direction of wind
speed
headwind
60 km/h
crosswind (90º)
30 km/h
tailwind
0 km/h

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Artur Trendak
FLIGHT MANUAL
Emergency Procedures
Chapter 3
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Page 3-1
Chapter 3 Emergency Procedures
3. page
3.1 Introduction ................................................................................................ 3-2
3.2 Engine Failure ............................................................................................. 3-2
3.2.1 During Take-off ..................................................................................... 3-2
3.2.2 During Flight .......................................................................................... 3-2
3.3 Staring the Engine in Flight ....................................................................... 3-2
3.4 Smoke or Fire.............................................................................................. 3-3
3.4.1 During Taxiing ...................................................................................... 3-3
3.4.2 During Flight .......................................................................................... 3-3
3.5 Gliding ....................................................................................................... 3-3
3.6 Emergency Landing .................................................................................... 3-3
3.7 Flat Tyre at Landing/Taxi .......................................................................... 3-3
3.8 Blocking of the Throttle Lever during Flight.............................................. 3-4

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Artur Trendak
FLIGHT MANUAL
Emergency Procedures
Chapter 3
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Document no.: TERCEL-AFM-001-EN
Edition 1 21 Aug 2014
Change no.:
3.1 Introduction
Chapter 3 contains activities to take if an emergency condition occurs during ground
operation, take-off or in-flight. These procedures are suggested as the best course of action for
coping with the particular condition described, but are not a substitute for sound judgment and
common sense. Since emergencies rarely happen in modern gyrocopter, if proper pre-flight
inspections and equipment maintenance are applied, their occurrence is usually unexpected and the
best corrective action may not always be obvious. Pilots should familiarize themselves with the
procedures given in this section and be prepared to appropriate action when an emergency arise.
Most basic emergency procedures, such as power off landings are a part of normal pilot
training. However, these emergency situations are also discussed here. This information is not
intended to replace such training, but only to provide a source of reference and review, and to
provide information on procedures which are not the same for all gyrocopters. It is suggested that
the pilot review standard emergency procedures periodically to remain proficient in them.
CAUTION:
Plan the flight route so as to allow for potential emergency landing.
3.2 Engine Failure
3.2.1 During Take-off
Evaluate the flight level. If you are above 250 ft (80 m), you can turn back to land. If
are lower, keep up the direction straight ahead.
Reset the throttle to the “minimum” position.
Deactivate the magnetos and the electrical master switch(red key).
Land, attempting to avoid both possible obstacles and violent manoeuvres resulting
with loss of rotor rotational speed.
3.2.2 During Flight
If you have the sufficient flight height, attempt to start the engine in flight (subsection
3.3).
If the height is too small or attempts to restart the engine have not succeeded, perform
emergency landing (subsection 3.6).
3.3 Starting the Engine in Flight
Proceed to gliding.
Make sure all the switches are in an appropriate position - the master switch and the
magnetos are ON.
To start the engine, reset the throttle lever to the “minimum” position.
Activate the starter.
After starting the engine, boost the throttle gradually.

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FLIGHT MANUAL
Emergency Procedures
Chapter 3
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3.4 Smoke or Fire
3.4.1 During Taxiing
Reset the throttle lever to the “minimum” position.
Close Fuel Shut-off valve.
Deactivate the magnetos and the master switch(red key).
Stop the machine and leave it as fast as possible.
Use an appropriate fire extinguisher if available.
3.4.2 During Flight
Close Fuel Shut-off valve.
Deactivate the magnetos and the master switch(red key).
Use an appropriate fire extinguisher if available.
Perform Emergency Landing(subsection 3.6)
3.5 Gliding
Flight with engine shut-off can be safely performed in the full speed range. However,
approaching the ground, observe the restrictions following from the “height - speed” diagram
(page 2-7). In case of a vertical descent, commence accelerating the gyrocopter at a height of 80-
100 m above the ground to be able to land safely.
The highest glide ratio equals 3:1 at speed 100 km/h (54 kt); then the machine heads for an
area seen in the bottom window.
3.6 Emergency Landing
Maintain 100 km/h (54 kt) to achieve best glide ratio.
Chose landing spot.
Land, attempting to avoid both possible obstacles and violent manoeuvres resulting
with loss of rotor rotational speed.
Engage rotor brake as fast as possible after touchdown.
Stop the machine, apply full rotor brake and prepare to leave.
Leave the machine as soon as the rotor stops.
3.7 Flat Tyre at Landing/Taxi
Deactivate the magnetos and the master switch.
Interrupt the take-off.
Attempt to keep up the direction by means of the pedals and the brake.