Zenair CH 601 XL ZODIAC 2002 Technical specifications

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Document No.:
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Date of Issue:
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Revision:
T
Te ec ch hn ni ic ca al lC Co om mm mi is ss si io on no of f
L
Li ig gh ht tA Ai ir rc cr ra af ft tA As ss so oc ci ia at ti io on no of ft th he eC
Cz ze ec ch hR Re ep pu ub bl li ic c
represented by:
....................................................................................................................
and as the organization authorized by the Ministry of Transportation and
Communications of the Czech Republic to prove compliance with the
microlight airplane category airworthiness requirements, certifies, that the
airplane design, used materials, flight performance and characteristics comply
with the Czech UL-2 airworthiness requirements and the airplane is
categorized to the following group of microlight airplanes:
U
UL LL La a
A
Ae er ro od dy yn na am mi ic ca al ll ly yC Co on nt tr ro ol ll le ed dM Mi ic cr ro ol li ig gh ht tA Ai ir rp pl la an ne es s
Signature: .............................................
Stamp:
Airplane - Type:
Serial Number:
Registration:
This airplane must be operated in compliance with
information and limitations contained in herein.
This Flight Manual must be available aboard the airplane.

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Revision:
0.1 Record of revisions
Any revision of the present manual, except actual weighing data, must be
recorded in the following table.
The new or amended text in the revised pages will be indicated by a black
vertical line in the left hand margin, and the Revision No. and Date will be
shown on the bottom of the page.
Revision No.
Affected
Section
Affected
Pages
Date of
Issue Approved by Date of approval
Date
inserted Signature

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0.3 Table of Contents
Section
GENERAL.........................................................................1
LIMITATIONS ...................................................................2
EMERGENCY PROCEDURES.........................................3
NORMAL PROCEDURES ................................................4
PERFORMANCE..............................................................5
WEIGHT AND BALANCE ................................................6
AIRCRAFT AND SYSTEMS DESCRIPTION ...................7
AIRCRAFT HANDLING, CARE AND MAINTENANCE ..8
SUPPLEMENTS ...............................................................9

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SECTION 1
1. GENERAL
1.1 Introduction
1.2 Certification basis
1.3 Warnings, cautions and notes
1.4 Descriptive data
1.4.1 Aircraft description
1.4.2 Technical data

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1.1 Introduction
The airplane Flight Manual has been prepared to provide pilots with
information for the safe and efficient operation of Z ZE EN NA AI IR RC CH H6 60 01 1
X
XL LZ ZO OD DI IA AC C.
It also contains supplemental data supplied by the airplane manufacturer.
1.2 Certification basis
This aircraft type has been approved in compliance with UL-2 regulation,
which is mandatory certification basis for Microlight category airplanes
approved by Light Aircraft Association of the Czech Republic (LAA CR).
Type Certificate No.: .....................
Approved by: Technical Commission of LAA CR
Date of approval: ............................
Certificate of Airworthiness: „P“

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1.3 Warnings, cautions and notes
The following definitions apply to warnings, cautions and notes in the flight
manual.
WARNING
Means that the non-observation of the corresponding procedure leads to
an immediate or important degradation of the flight safety.
CAUTION
Means that the non-observation of the corresponding procedure leads to
a minor or possible long term degradation of the flight safety.
NOTE
Draws attention to any special item not directly related to safety, but
which is important or unusual.

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1.4 Descriptive data
1.4.1 Aircraft description
Z
ZE EN NA AI IR RC CH H6 60 01 1X XL Lis microlight airplane intended especially for
recreational and cross-country flying, with a limitation to non-aerobatics
operation.
Z
ZE EN NA AI IR RC CH H6 60 01 1X XL Lis a single-engine, all metal, low-wing monoplane of
semimonocoque construction with two side-by-side seats. The airplane is
equipped with a fixed tricycle undercarriage with steerable nose wheel.
The powerplant is composed of ROTAX 912 (80 hp or 100 hp), four
cylinder, four stroke engine and optional propeller by customer’s request.

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1.4.2 Technical data
Wing span ......................................................8.23 m
Wing area .....................................................12.3 m2
Length ............................................................6.1 m
Cockpit width ..................................................1.12 m
Height1.98 .....................................................m

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1.5 Three-view drawing

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SECTION 2
2. LIMITATIONS
2.1 Introduction
2.2 Airspeed
2.3 Airspeed indicator markings
2.4 Powerplant
2.5 Powerplant instrument markings
2.6 Miscellaneous instrument markings
2.7 Weight
2.8 Center of gravity
2.9 Approved maneuvers
2.10 Maneuvering load factors
2.11 Crew
2.12 Kinds of operation
2.13 Fuel
2.14 Maximum passenger seating
2.15 Other limitations
2.16 Limitation placards

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2.1 Introduction
Section 2 includes operating limitations, instrument markings and basic
placards necessary for the safe operation of the aircraft, its engine,
standard systems and standard equipment. Limitations for optional
systems and equipment are shown in Section 9. Supplements.
2.2 Airspeed
Airspeed limitations and their operational significance are shown below:
Speed IAS
[km/h]
KIAS Remarks
VNE Never exceed
speed 260 140
Do not exceed this speed in
any operation.
VNO
Maximum
structural
cruising speed
210 113
Do not exceed this speed
except in smooth air, and
then only with caution.
VAManeuvering
speed 160 86
Do not make full or abrupt
control movement above
this speed, because
under certain conditions
the aircraft may be
overstressed by full
control movement.
VFE
Maximum Flap
Extended
Speed
120 65
Do not exceed this speed
with flaps extended.

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2.3 Airspeed indicator markings
Airspeed indicator markings and their color-code significance are shown
below:
IAS value or rangeMarking
[km/h] KIAS
Significance
White
arc 55÷120 30-65
Positive Flap Operating Range.
Green
arc 70÷210 38-113
Normal Operating Range.
Yellow
arc 210÷260 113-140
Maneuvers must be conducted
with caution and only in
smooth air.
Red line 260 140
Maximum speed for all
operations.

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2.4 Powerplant
Z
ZE EN NA AI IR RC CH H6 60 01 1Z ZO OD DI IA AC C, S/N:
is fitted with ROTAX 912 , S/N
and prop, Type / S/N
Engine Model: ROTAX 912A (or UL) ROTAX 912S (or ULS)
Engine Manufacturer: Bombardier-Rotax GMBH
Max Take-off: 59.6 kW / 80 hp
at 5800 rpm, max.5 min.
73.5 kW / 100 hp
at 5800 rpm, max.5 min.
Max. Continuous: 58 kW / 78 hp
at 5500 rpm
69 kW / 93.8 hp
at 5500 rpm
Power
Cruising: 53 kW / 71 hp
at 4800 rpm
53 kW / 71 hp
at 4800 rpm
Max. Take-off:
Max. Continuous:
Cruising:
Engine speed
Idling:
5800 rpm, max. 5 min.
5500 rpm
4800 rpm
~1400 rpm
Minimum: 60 °C 140 °F 60 °C 140 °F
Cylinder
head
temperature:
Maximum: 150 °C 302 °F 135 °C 275 °F
Minimum: 50 °C 122 °F 50 °C 122 °F
Maximum: 140 °C 284 °F 130 °C 266 °F
Oil
temperature
Optimum: 90 °C - 110 °C 194 - 230°F 90 °C - 110 °C 194 - 230°F
Minimum: 7,0 bar
Maximum: 1,5 bar
Oil
pressure:
Optimum: 1,5-4,0 bar
Fuel: see 2.13
Oil: Automotive engine oil of registered brand with gear additives,
but not aircraft oil (refer to engine Operator’s Manual).
API classification „SF“ or „SG“.
Propeller type
and Manufacturer
iWOODCOMP KLASSIC 170 R
iWOODCOMP VARIA 170
iWARP DRIVE
iSR 2000
For technical data refer to documentation supplied by the
propeller manufacturer.
WARNING
The Rotax 912 UL has not been certified as an aircraft engine and its failure may occur
at any time. The pilot is fully responsible for consequences of such a failure.

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2.5 Powerplant instrument markings
Analogue engine instruments markings and their color-code significance
are shown below.
Function Minimum
Limit
Normal
Operating
Range
Caution
Range
Maximum
Range
Engine speed
[RPM] 1400 1400-5500 5500-5800 5800
R 912
(80 hp)
100-150 °C
212-302 °F 150 °C
302 °F
Cylinder
Head
Temp.
(CHT) R 912
(100 hp)
60 °C
140 °F
60-100 °C
140-212 °F 100-135 °C
212-275 °F
135 °C
275 °F
Exhaust
Gases
Temp. (EGT)
880 °C
1616 ° F
R 912
(80 hp)
50-90 °C
122-194 °F
110-140 °C
230-284 °F
140 °C
284 °F
Oil
Temp.
R 912
(100 hp)
50 °C
122 °F
90-110 °C
194-230 °F 50-90 °C
122-194 °F
110-130 °C
230-266 °F
130 °C
266 °F
Oil
Pressure
1.5 bar
22 psi
1.5-4.0 bar
22-58 psi
4.0-5.0 bar
58-73 psi
7.0 bar
102 psi
cold engine
starting

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2.6 Miscellaneous instrument markings

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2.7 Weight
Empty weight (standard equipment).......... 270 kg 595 lbs.
NOTE
Actual empty weight is shown in SECTION 6, par. 6.2
Max. take-off weight .....................................450 kg 992 lbs.
Max landing weight.......................................450 kg 992 lbs.
Max. weight of fuel .........................................65 kg 143 lbs.
Max.baggage weight .....................................18 kg 40 lbs.
2.8 Center of gravity
Operating C.G. range.................................................... 20÷30 % MAC
2.9 Approved maneuvers
Airplane Category: Normal
Z
ZE EN NA AI IR RC CH H6 60 01 1Z ZO OD DI IA AC Cairplane is approved for normal and below listed
maneuvers:
xSteep turns not exceeding 60° bank
xLazy eights
xChandelles
xStalls (except whip stalls)
WARNING
Aerobatics and intentional spins are prohibited !

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2.10 Maneuvering load factors
Maximum positive limit load factor.......................................+4 g
Maximum negative limit load factor .....................................-2 g
2.11 Crew
Number of seats....................................................... 2
Minimum crew weight.........................................55 kg 121 lb.
Maximum crew weight.....................................see 6.2
WARNING
Do not exceed Maximum takeoff weight 450 kg (992 lbs.) !
2.12 Kinds of operation
There are permitted day VFR (Visual Flight Rules) flights only.
WARNING
IFR (Instrument Flight Rules) flights and intentional flights under icing
conditions are PROHIBITED!
Instruments and equipment for VFR flights:
1 Airspeed indicator (marked according to 2.3)
1 Altimeter
1 Vertical speed indicator
1 Magnetic compass
1 Bank indicator
2 Safety harnesses