AUTO GYRO Calidus Owner's manual

Pilot Operating Handbook

RSUK0060_POH_CD Revision 7.0, Issue Date17.01.2019 1
RotorSport UK Ltd
Poplar Farm
Prolley Moor
Wentnor
Bishops Castle
SY9 5EJ
Company Reg No 5486550
Phone: [phone]
Fax: [phone]
Email: [e-mail]
Approval number DAI/9917/06
RSUK0060
Pilot’s Operating Handbook
for the Calidus Gyroplane

RSUK0060_POH_CD Revision 7.0, Issue Date17.01.2019 2
Flight and Operation Manual for the Calidus Gyroplane
Model: Calidus
Serial number: RSUK/CALS/_____________________________________
Registration: G- _____________________________________________
Engine: 914UL or 912ULS serial ____________________________
Propeller: HTC 1,73m ground adjustable propeller
or
Ivoprop DL3-68 in-flight adjustable propeller
Rotor: Autogyro 8.4m RotorSystem II (red end caps, silver
spacers) or
Autogyro 8.4m RotorSystem II TOPP (blue end caps, silver
spacers)
Note that the orginal AAN approved the use of orange
end cap rotors. These are no longer in service.
Aircraft manufacturer and
Type Approval holder: RotorSport UK Ltd
Prolley Moor,
Wentnor,
Bishops Castle,
Shropshire,
SY9 5EJ
Owner: _______________________________________________
_______________________________________________
_______________________________________________
This flight manual is always to be carried on board of the aircraft and must be kept in
current, up-to-date status. The latest revisions and version status are available at
www.rotorsport.org. Extent and revision status of the manual is recorded in the revision log
and the table of contents.
This gyroplane may be operated only in strict compliance with the limitations and
procedures contained in this manual.
The manual is not a substitute for competent theoretical and practical training on the
operation of this aircraft. Failure to adhere to its provisions or to take proper flight
instruction can have fatal consequences.

RSUK0060_POH_CD Revision 7.0, Issue Date17.01.2019 3
REVISION LOG
Rev. Change summary Date Signature
1.0 First formal release 14.01.11
2.0 Not recorded 12.09.11
3.0 Starter fuse changed to 100A under MC-192/SB-042
p74, Flymap AHRS unit added p56, p59 (with EASA ref),
p60, Flymap AHRS placard p21. Explanation of MC-
194/SB-044 Reverse airflow ground cooling system
(p45)
Section 7 Comment on sunlight and damp storage
conditions (p86).
02.04.12
4.0 Warning on Binx nuts (p38), different rpm gauges (p62),
nitrogen-filled tyres (p64) and pressures clarified in
Checklist. 5hr greasing added (p39-40), ATR833 audio
socket (p76), AI option (p62). Improved pre-rotator
gearbox (p44), cooler unblanking highlighted (p91),
turbo cooling note (p46), UL91 and Mogas E10 (p18),
rotor brake technique (p46), Section 3.15 introduced
(p30), Clutch Brake MC260 (p44)
01.07.13
5.1 Section 9 IVO-prop added (p93-98), info on MC-258
cabin heater on P74 and 84 added.
10.06.14
6.0 TOPP rotor option added
p2,p5,p6,p9,p14,p15,p19,p31,p32,p36,
p46,p48
12.4.16
7.0 Rotorhead III added, MTOW increased, operational
ceiling increased. British and German manuals
amalgamated.
17.01.19
Pilots Flight and Operation Manual Document approval
Signature
Position: Flight test CVE
Signature
Position: Head of Engineering
This document is to approve the release of the AutoGyro Pilots Handbook
POH_CD_4.0 for use with the Calidus aircraft within the UK market.
Within the UK market RotorSport UK Ltd is considered by the UK CAA to be the
Manufacturer and the Type Approval holder.

RSUK0060_POH_CD Revision 7.0, Issue Date17.01.2019 4
Differences to be noted by UK operator owners.
1. The approved aircraft configurations within the UK market are shown in TADS BG04,
available from the UK CAA website.
2. The only rotor options permissible are those shown on page 2 and in the TADS.
3. The Approved Operational Limitations are;
Aerobatic Limitations
Aerobatic manoeuvres are prohibited
Manoeuvres involving a deliberate reduction in normal ‘g’ shall be avoided
Loading Limitations
Maximum Total Weight Authorised: 500kg or 560Kg (914UL engines only,
from aircraft serial no. RSUK/CALS/037)
Maximum Empty Weight 311.6 kg (914UL at 500Kg MTOW)
371.6Kg (914UL at 560Kg MTOW
309Kg (912ULS, 500Kg MTOW)
Maximum Pilot Weight front seat 125 kg
Minimum Pilot Weight front seat 65 kg
Maximum Occupant Weight rear seat 120 kg
Front seat occupants under 65 kg in weight must carry suitable ballast
Engine Limitations
Maximum take-off (max. 5 minutes) 5800 rpm
Max. continuous 5500 rpm
Max. CHT 135ºC
Max CT (where fitted) 120 ºC
Min. oil temp. 50ºC
Max. oil temp. 130ºC
Min. oil pressure 0.8 bar
Normal operating range 2-5bar
Max. oil pressure 7 bar
Air Speed Limitations
Maximum indicated air speed (IAS) 90 mph, or 120mph if SB-039
incorporated, or 120mph if SB-039 incorporated and Rotor System II TOPP rotor
variant fitted (blue end caps)
Other Limitations
The aircraft shall be flown by day in Visual Meteorological Conditions only.
Flight in icing conditions is prohibited (not placarded)
Flight in strong gusty winds or wind velocities of more than 45mph (40 kts) is
prohibited. (not placarded)

RSUK0060_POH_CD Revision 7.0, Issue Date17.01.2019 5
Manoeuvre Limitations
Aerobatic manoeuvres are prohibited.
Manoeuvres involving a deliberate reduction in normal ‘g’ shall be avoided.
Maximum bank angle 60 degrees from vertical
Cross-wind Limitations
The maximum cross-wind component for takeoff is 22kts.
Landing should always be made into wind where practical. The maximum landing
crosswind 15kts.
The aircraft operator is reminded to read the aircraft CAA Operational Limitations
(part of the Permit to Fly) the aircraft specific limitations of operation.
4. The legal basis for the operation of this CALIDUS autogyro is regulated in the
Airworthiness Approval Notification (AAN29266), issued by the UK Civil Aviation Authority
(CAA). It has been shown to comply with the requirements of BCAR Section T issue 3 (and
issue 5 where appropriate), and is considered as a factory built aircraft. Reference must be
made to the Permit to Fly limitations issued by the CAA for each individual aircraft.
5. The CG limits approved during the aircraft UK type approval are 485 to 255mm forward of
the mainwheel datum, and 795 to 895mm above the CG datum (the mainwheel axle is the 0
CG datum in x and z). These limits are unchanged when MC-385 “Calidus upgrade to
560kg MTOW” is embodied.
Remember - Fuel loading permissible is 500kg minus occupant weight, minus aircraft
empty weight, minus any baggage or items added to the aircraft since weighed. Aircraft
empty weight is placarded. Mogas nominal density is 0.72kg/ltr (check for the type of fuel
used).
Example: 500Kg – 275Kg (empty wt) – 90Kg (rear seat occupant) – 90Kg (pilot) – 10Kg
(rear seat luggage) = 35Kg. Useful fuel load (assuming both fuel tanks fitted) is 35/0.72 =
48.6ltrs.
Maximum possible fuel load (assuming both fuel tanks fitted) is 75ltrs, 54Kg
If ballast is required to meet the minimum front seat loading condition of 65Kg, then it
should be in the form of thin lead sheet placed behind and under the pilot seat cushion.
Carrying of bags or other items inside the aircraft is possible, due to the design of the inside
construction covering the control cables and linkages.
WARNING! If carried, ensure there is no control obstruction! Bags fitted into the rear seat
must be securely attached to the seat harness, and included in the weight/balance
calculation.
This is especially important with an open canopy, take care that items inside the cockpit do
not get blown out!
6. Approved panel layout at the time of writing are; Day VFR UK, Ipad, and Garmin G3X.
7. Aircraft equipped with rotorhead III are permitted to have an increased altitude ceiling of
12,000ft and MTOW increase to 560Kg.
8. Propellers: HTC 3 blade. Pitch angle: 20.5deg 912ULS, 22deg 914UL (ground
adjustable to suit engine and working environment). Take account of the propeller concave

RSUK0060_POH_CD Revision 7.0, Issue Date17.01.2019 6
face whilst measuring (see Maint. Manual RSUK0061). Propeller is pitched for max ground
rpm of 5500.
For the Ivoprop DL3-68, refer to manual RSUK0325.
9. GENERAL PLACARDS AND MARKINGS:
In conformity with BCAR Section T the following placards and markings are installed:
- All emergency controls are coloured red.
- All cockpit controls are clearly marked as to their function and method of operation.
- Fuel and oil filler openings are clearly marked, together with the grade or type required.
- Fuel tank capacity is clearly marked.
- Loading conditions are clearly marked as follows:
Loading conditions. This may indicate an MTOW of 500 or 560Kg
Throttle, choke and brake control marking
Limitations if fitted with orange end-cap rotor system
Aircraft Payload Specification
Front seat pilot: 125Kg max, 65Kg min
Pilot must carry ballast to meet 65Kg min.
Rear seat passenger 120Kg max
Empty weight (as measured) Kg
MTOW 500Kg
Aircraft must only be flown solo from the front
seat.
MAX
↑
THROTTLE
CHOKE
↓
ON
BRAKE
↓
ENGAGE
OPERATING LIMITATIONS
Aerobatic Limitations
Aerobatic manoeuvres are prohibited.
Manoeuvres involving a deliberate reduction in normal ‘g’ shall be avoided.
CG Range Limits (Gyroplane) – refer to Pilots Handbook data.
Airspeed Limitations
Maximum Indicated Airspeed (Vne): 90mph
Other Limitations
This aircraft shall be flown by day and under Visual Flight Rules only.
Smoking in the aircraft is prohibited

RSUK0060_POH_CD Revision 7.0, Issue Date17.01.2019 7
Limitations if fitted with red end-cap RotorSystemII under SB-039, or SB-039 is embodied
and Rotorsystem II TOPP variant is fitted (blue end caps)
Occupant warning (in front and rear cockpits) Fitted beside front
seat and back of front seat
Auxiliary socket (where fitted,
marked ‘12v 5A on the panel) Roll trim indicator (where fitted)
Coolant header tank Engine oil tank
OCCUPANT WARNING
This aircraft has not been certificated to an
International Requirement
L R
Roll Trim
Front seat back
straps limit stops
must be fitted if rear
stick is fitted
OPERATING LIMITATIONS
Aerobatic Limitations
Aerobatic manoeuvres are prohibited.
Manoeuvres involving a deliberate reduction in normal ‘g’ shall be avoided.
CG Range Limits (Gyroplane) – refer to Pilots Handbook data.
Airspeed Limitations
Maximum Indicated Airspeed (Vne): 120mph
Other Limitations
This aircraft shall be flown by day and under Visual Flight Rules only.
Smoking in the aircraft is prohibited
Coolant Header Tank.
Filled with 50/50
water/antifreeze
Oil tank
Capacity 3 ltrs.
Use Shell VSX or
equivalent Motorcycle
oil SF or SG

RSUK0060_POH_CD Revision 7.0, Issue Date17.01.2019 8
Alternative header tank and oil tank placard;
Fuel tank beside the filler neck (shows 39ltrs capacity if only one tank installed).
Low voltage placard mounted on instrument panel.
Warning lamp placards. (where not annotated on panel)
Fuel capacity: 75 ltrs
Preferred fuel:
EN228 MOGAS super or super plus
(AVGAS 100LL permissible)
Continuously lit Low Volt lamp indicates
electrical demand exceeds supply, and
the battery is being drained. If lit in flight,
reduce demand until unlit. If not possible,
expedite landing.
Canopy
unlocked
ENGINE OIL:
Capacity 3.4 ltr.
AEROSHELL OIL SPORT
PLUS 4 or equivalent in
accordance with BRP Rotax
service instructions
COOLANT HEADER
TANK:
Replenish with 50 / 50
Ethylene Glycol antifreeze
and destilled water

RSUK0060_POH_CD Revision 7.0, Issue Date17.01.2019 9
Pressure gauge placard
(unless panel annotated)
Luggage lockers 2Kg max
Removable map bag
(where fitted) 1Kg max
Static ports – ring around saying ‘Static Port – do not obstruct!’
Canopy handle ‘Ensure locked down before flight!’
On top of control stick (either type of stick grip)
(L roll and R Roll only if roll-trim system fitted)
R Roll
L Roll
Trim, Brake
Pre rotate, PTT
Baggage load
2Kg MAX
Baggage load
1Kg MAX

RSUK0060_POH_CD Revision 7.0, Issue Date17.01.2019 10
Day VMC Only. Do not rely on this display.
Fuel cut-off valve Interlock placard (unless engraved on
panel)
Placard above switch, where fitted, for Airbox GPS (adjacent to ‘Nav’ sw). ‘Off’ placard is
fitted below the switch.
Where a Flymap L GPS has been fitted with an AHRS unit, the following placard must be
affixed adjacent to the Flymap GPS.
Instructor pack (where fitted). Brake placard only where brake is fitted.
Off
On
Fuel cut-off
valve
Pre
-
rotator &
rotor brake
interlock
release
GPS
OFF
Ignition cut off
switches.
To switch off, lift
safety flaps and
pull toggles
backwards.
MAX
↑
THROTTLE
BRAKE
↓
ENGAGE

RSUK0060_POH_CD Revision 7.0, Issue Date17.01.2019 11
- Other
If the compass deviation is more than 5° on all headings, then a deviation placard
must be present.
GPS placard (where a GPS is fitted) Canopy placards for the operating lever
(Placard may be a different shape) Inside Outside
Alternative similar placards are acceptable.
Instrument placards as section 2.5
The aircraft is fitted with a permanently attached fireproof plate with the aircraft registration
number and serial no. marked on it, on front of the instrument panel.
The registration letters are placed high on the tail fin, and are 60cm long, 30cm high. This
has been accepted as best practice compliance to CAP523, the CAA standard for aircraft
registration. Alternative markings and position of markings is acceptable provided they
comply with this standard.
Note that all placards must have the same units of measure as the instruments.
COMPASS DEVIATION
For N 30 60
Set
For E 120 150
Set
For S 210 240
Set
For W 300 330
Set
Calibration by: date:
GPS unit not for navigational
use. The unit, software & charts
are not approved or certified to
any national standard. Warning!
Charts or software may not be up
to date.
Lift handle
to unlock
canopy.
Ensure
locked
down
before
flight!
To open
Canopy
lock
handle
To lock

RSUK0060_POH_CD Revision 7.0, Issue Date17.01.2019 12
If an IVO-prop in-flight variable pitch propeller is fitted in combination with a 914UL
turbocharged engine the following placard is fitted adjacent to the manifold pressure gauge
or combined engine rpm/manifold pressure gauge, as applicable.
AAN29345 releases.
AAN and addendum Purpose of release and comment
AAN29266 Original aircraft approval with 912ULS and 914UL engines, HTC
propeller and 8.4m rotorsystem. Vne restricted to 90mph (from
120mph)
Addendum 1 Vne restriction removed with fitment of RotorSystem II red end cap
version. All UK Calidus were upgraded to this rotorsystem.
Addendum 2 Release of the fitment of in-flight pitch adjustable DL3-68 Ivoprop
propeller and max empty weight increase.
Addendum 3 Rotorsystem II TOPP (blue end caps) approved for use
Addendum 4 Release of the 914 engined aircraft at 560Kg MTOW (Rotorhead III
version). Increase of maximum altitude to 12,000ft.
Note!
It is the pilot/operators responsibility to operate the Calidus aircraft within the
Permit Limitations issued by the UK Civil Aviation Authority issued for the
aircraft, regardless of permitted limits within the AAN and associated
Addendums above.
Max manifold pressure (take off): 39.9in Hg Max
continuous manifold pressure: 35.4in Hg
ENGINE RPM
LIMITS
MAX CONTINUOUS
5,500
MAXIMUM
5,800

APPENDIX
Ownership change form
APPENDIX
LIST OF APPENDICES
Operator Registration Form

APPENDIX
Ownership change form
This form is supplied to enable the new owner to register the change of ownership,
so that he/she may receive any service or other information relating to the aircraft.
The information is stored on a computer, and is only used within RotorSport Sales
and Service Ltd for the above purpose.
If the new owner does not register, then they will not be automatically updated,
which may lead to unsafe flight or an un-airworthy aircraft.
Return this form by email to;
[email protected]
Aircraft type Aircraft serial No.
Aircraft Registration No. Aircraft Engine No.
Logbook Aircraft hours Logbook Engine hours
Old owners name and address
Signature & date
New owners name and address
Email:
Signature & date
RSS Office use only
Date entered onto database Acknowledgement sent (date) Job completed by:

AutoGyro_POH_Calidus Revision 4.0 – Issue Date 17.JAN..2019 Pre-pages 1
Pilot Operating Handbook
for Gyroplane Calidus

AutoGyro_POH_Calidus Revision 4.0 – Issue Date 17.JAN..2019 Pre-pages 2
All rights reserved. Under the copyright laws, this manual may not be copied, in whole or in part, without the written
consent of AutoGyro GmbH. AutoGyro reserves the right to change or improve its products and to make changes in the
content of this manual without obligation to notify any person or organisation of such changes or improvements.
Notifications to the Civil Aviation Authorities or other organisations based on legal regulations are unaffected.
MTOsport, Calidus, Cavalon, the AutoGyro logo and word picture mark are trademarks or registered trademarks of
AutoGyro AG, registered in Germany and other countries.
Other company and product names mentioned herein may be trademarks of their respective companies. Mention of third-
party products is for informational purposes only and constitutes neither an endorsement nor a recommendation. AutoGyro
assumes no responsibility with regard to the performance or use of these products. All understandings, agreements, or
warranties, if any, take place directly between the vendors and the prospective users.
U.S. and foreign patents of AutoGyro AG are used in the Calidus and Cavalon gyroplanes - (US.Pat.No. 8,690,100;
US.Pat.No. D699,153)
Every effort has been made to ensure that the information in this manual is accurate. AutoGyro GmbH is not responsible
for printing or clerical errors.

AutoGyro_POH_Calidus Revision 4.0 – Issue Date 17.JAN..2019 Pre-pages 3
Pilot Operating Handbook for Gyroplane Calidus
Model: ______________________________________________
Serial number: ______________________________________________
Registration: ______________________________________________
Type certificate number: ______________________________________________
Aircraft manufacturer and
type certificate holder: AutoGyro GmbH
Dornierstraße 14
D-31137 Hildesheim
Tel.: [phone]
Fax: [phone]
Distribution partner: ______________________________________________
______________________________________________
______________________________________________
Owner: ______________________________________________
______________________________________________
______________________________________________
This flight manual is always to be carried on board of the aircraft and must be kept in
current, up-to-date status. The latest revisions and version status is available at www.auto-
gyro.com. Extent and revision status of the manual is recorded in the revision log and the
table of content.
This gyroplane may be operated only in strict compliance with the limitations and
procedures contained in this manual.
The manual is not a substitute for competent theoretical and practical training on the
operation of this aircraft. Failure to adhere to its provisions or to take proper flight
instruction can have fatal consequences.
Applicability
This manual is applicable for all Calidus models.

AutoGyro_POH_Calidus Revision 4.0 – Issue Date 17.JAN..2019 Pre-pages 4
REVISION LOG
Rev. Change summary Date
2.0 AutoGyro GmbH, unrecorded 01.05.2011
2.1 AutoGyro GmbH, unrecorded 01.10.2011
2.2 AutoGyro GmbH, unrecorded 01.04.2012
2.3 AutoGyro GmbH, unrecorded 01.11.2012
2.4 AutoGyro GmbH, unrecorded 24.06.2013
3.0 AutoGyro GmbH, unrecorded 16.06.2014
3.1 AutoGyro GmbH, unrecorded 11.01.2018
4.0 Handbook fully revised to cover all models, incorporate
rotorhead III, new heater system, cowls etc. All pages
updated. UK POH information incorporated
17.JAN.2019

Pilot Operating
Handbook
Calidus
Table of Contents
List of Effective Pages
AutoGyro_POH_Calidus Revision 4.0 – Issue Date 17.JAN.2019 Index / LOEP 1
CONTENTS
SECTION 1 - GENERAL................................................................................................... 1-1
1.1 Introduction....................................................................................................1-1
1.2 Certification ................................................................................................... 1-1
1.3 Performance Data and Operating Procedures ...............................................1-1
1.4 Definition of Terms ........................................................................................ 1-2
1.5 Important Note...............................................................................................1-2
1.6 Three-view of the Calidus .............................................................................. 1-3
1.7 Description .................................................................................................... 1-4
1.8 Technical Data ..............................................................................................1-4
1.9 Rotor .............................................................................................................1-4
1.10 Engine........................................................................................................... 1-5
1.11 Propeller........................................................................................................ 1-5
1.12 Unit Conversion.............................................................................................1-6
1.13 Abbreviations and Terminology ..................................................................... 1-7
SECTION 2 - LIMITATIONS .............................................................................................2-1
2.1 General .........................................................................................................2-1
2.2 Environmental Limitations..............................................................................2-2
2.3 Colour Code for Instrument Markings ............................................................2-3
2.4 Airspeed Limitations and Instrument Markings............................................... 2-4
2.5 Rotor Speed Limitations and Instrument Markings.........................................2-4
2.6 Power Plant Limitations and Instrument Markings..........................................2-5
2.7 Weight and Balance ...................................................................................... 2-7
2.8 Flight Crew .................................................................................................... 2-8
2.9 Kinds of Operation.........................................................................................2-8
2.10 Fuel ............................................................................................................... 2-9
2.11 Minimum Equipment.................................................................................... 2-10
2.12 Placards ...................................................................................................... 2-11
SECTION 3 - EMERGENCY PROCEDURES ...................................................................3-1
3.1 Engine Failure ...............................................................................................3-1
3.2 Air Restart Procedure .................................................................................... 3-2
3.3 Landing into Trees or High Vegetation........................................................... 3-2
3.4 Degradation of Engine Power ........................................................................3-3
3.5 Evacuating the Aircraft................................................................................... 3-3
3.6 Smoke and Fire .............................................................................................3-3
3.7 Canopy Open in Flight...................................................................................3-4
3.8 Off-field Landing ............................................................................................ 3-4
3.9 Flight Control Malfunction .............................................................................. 3-5
3.13 Warning Lights .............................................................................................. 3-8
3.14 Parameters out of Limits.............................................................................. 3-11
3.15 Additional Cockpit Indications......................................................................3-12
3.16 Loss of Visibility...........................................................................................3-12