Zenair CH 2000 Trainer with Lycoming 0-235-N2C Engine Trainer Owner's Manual

OWNER'S MANUAL
Model: Zenair CH 2000 Trainer with Lycoming 0-235-N2C Engine
Serial No: 20 -
Registration: = ИН — = ER
Date of Issue: e PO =Z
Sections 2. 3. 4. 5 comprise the Approved Flight Manual. The remaming sections are provided by tne
manufacturer for the information of the operator.
Pages indexed "App" are approved by: Transport Canada Aviation
7
Signature: O
Authority:
S :
Camp K_J. Mansfield
Chief, Flight Test
for Director, Airworthiness
Transport Canada
2 - N
Original Date of approval: > A 7775
Date of issue:
e
=
D
"4
CB
as
ron and limitations contained
o
This airpiane 1s to be operated in compliance with inform
OWNER'S MANUAL
Model: Zenair CH 2000 Trainer with Lycoming 0-235-N2C Engine
Serial No: 20- 0037
Registration: VH- ZEA
Date of Issue: = = ~~
Sections 2. 3. 4. 3 comprise the Approved Flight Manual. The remaining sections are provided by the
manufacturer for the information of the operator.
Pages indexed "App" are approved by: Transport Canada Aviation
7 A
Signature: „сут OA
Va
Authority:
Stamp:
Stamps K_J. Mansfield
Chief, Flight Test
for Director, Airworthmess
Transport Canada
/7 | pe
Original Date of approval: 5 TA (145
Date of issue:
This airplane is to be operated in compliance with information and limitations contained herein.
ZENAIR AIRCRAFT
CH 2000 Trainer
SECTION 0
REVISIONS
OWNER'S MANUAL
LOG OF REVISIONS
tion
Revision Num- Transport Canada
ber and Date Revised Description of Approval/Date
Pages Revision
=0 - 3 Apr 93 All pages Initial issue K.J. Manstield
3 Apr 95
#1 - 7 Apr 93 Update R.J. Mather
7 Apr 93
| #2 - 8 Мау 95 Update K.J. Manstield
8 Mav 93
33 - 19 Jul 93 Update K.J. Manstield
+ Jan 96
#4 -15 Dec 93 Update K.J. Manstield
4 Jan 96
=5 -29 Mar 96 Update K.J. Manstield
| 10 Apr 96
=6 -22 Jul 96 L'pdate K.J. Mansticid
|4 Aug 96
=7-29 Aug 96 - Update S. Didrikson
29 Aug 96
=8-10 Oct 96 Update NJ. Mansticid
10 Oct 96
=9-4 Feb 97 Cpdate K.J. Mansticid
25 Fed 97
=10-16 Dec 97 | Update KN.!. Manstield
| |6- Dec-97,
=11 Dec. 98 7-10 ARS
9-13 pA ALE
СИЕ Flight Teste
for Director, Aircraft Certifica
Tras ant e HA
Note: 0-1 and 0-2 with Update sheet(s) are replaced for each new update.
Rev. #11- Dec 98
0-1
SECTION 0 ZENAIR AIRCRAFT
REVISIONS CH 2000 Trainer
OWNER'S MANUAL
List of Effective Pages
Section Page Date Section Page Date Section Page Date
1-1 8 May 95 o-1 3 Apr 95 9-1 3 Apr 95
1-2 4 Feb 97 2 3 Apr 95 9-2 29 Mar 96
1-3 4 Feb 97 0-3 3 Apr 95 9-3 29 Mar 96
1-4 3 Apr 95 > 19 Jul 95 9-4 3 Apr 95
1-5 3 Apr95 o-5 29 Mar 90 9-5 29 Mar 90
1-0 3 Apr 95 oo 4 Feb 9° 9-0 29 Mar Yo
1-7 3 Apr95 6-7 19 Jui 95 9-7 4 Feb 97
1-8 3 Apr 95 0-8 4 Feb 97 9-8 lo Dec 97
2-1 19 Jul 95 7.1 3 Apr 95 9-9 16 Dec 97
2-2 4 Feb 97 7.2 4 Feb 97 9-19 4 Feb 9”
2-5 4 Feb 97 7.3 29 Mar 90 9-11 4 Feb 97
2 29 Aug Yo 7A 4 Feb 97 9-12 4 Feb 97
2-5 29 Aug 96 7-5 3 Apr 95 9-13 Dec-98
3-1 3 Apr 95 “© 29 Mar 96
3-2 19 Jul 95 TS 29 Mar 30
=3 29 Aug Yo 73 4 Feb 97
3 lo Dec 97 7.9 29 “ku Yo
3-5 3 Apr 95 - 7.10 Dec 28
3-0 3 Apr 95 il 13 ЛД Зо
> 3 Apr 95 42 29 Mar Yo
38 29 Aug vo 31 3 Apr 95
3-9 3 Apr 95 3-2 3 Apr 95
+ | 3 Apr 95 3-3 3 Apr 95
+2 3 Apr 95 3+ 3 Apr 95
+3 15 Dec 95 3-5 3 Act 95
+4 4 Feb 97 3-0 3 Apr 95
+5 15 Dec 95 3-7 29 Mar 96
4-0 4 Feb 97 2-3 3 Apr 95
+7 29 Aug 96 8-2 15 Dec 95
5-1 7 Apr 95 310 3 Apr 95
5-2 10 Oct 96 3-11 15 Dec 95
5-3 10 Oct 96 8-12 29 Mar 96
1 10 Oct 90 5-13 3 Apr 95
3-14 29 Aug 96
0-2 Rev. #11- Dec 98
ZENAIR AIRCRAFT SECTION 0
CH 2000 Trainer REVISIONS
OWNERS MANUAL UPDATE LOG
REV. NO. DATE DATE INSERTED
ISSUED INCORPORATED BY
О, 110 11 — — Incorporated at issue
Note: 0-1 and 0-2 with Update sheet(s) are replaced for each new update.
Rev. #11- Dec 98 | 0-3
TABLE OF CONTENTS
SECTION 1 GENERAL
SECTION 2 LIMITATIONS
SECTION 3 EMERGENCY PROCEDURES
SECTION 4 NORMAL PROCEDURES
SECTION $ PERFORMANCE
SECTION 6 WEIGHT AND BALANCE AND EQUIPMENT LIST
SECTION 7 DESCRIPTION AND OPERATION
OF THE AIRPLANE AND ITS SYSTEMS
SECTION $8 HANDLING, SERVICING AND MAINTENANCE
SECTION 9 OPTIONS
olin i amis Ain
SECTION |
GENERAL
TABLE OF CONTENTS
Introduction ......... LL LL
Certification Basis .......... LL LL LAS
Wamings, Cautions and Notes
Description
3 View Drawings
AAA EE
НЕЕ кН
Fuel 1111 LL LL
Maximum Weight. ......... 2000
Specific Loading . ........ вене)
Symbols and Abbreviations ......... 000 et
Meteorological Terminology . .. .. 421014 LA eee
Power Terminology . . ........... ... ..
Weight and Balance Terminology
ce eee a eee eee
необ SOU
Page
i
dd A A AAA
| 1 | 1 1 | I 1 |
co JJ O ER Y LI LU) LI) WI GI) N
i |
SECTION 1 ZENAIR AIRCRAFT
GENERAL CH 2000 Trainer
SECTION 1
GENERAL
INTRODUCTION
This Owner's Manual is designed for maximum utilization as an operating guide for the pilot. It
includes the matenal required by the regulations to be furnished to the pilot (pages indexed APP). It also
contains supplemental data supplied by the airplane manufacturer.
This manual is not designed as a substitute for adequate and competent flight instruction, knowledge
of current airworthiness directives, applicable air regulations or advisory circulars. It is not intended
be a guide for basic flight instruction or a training manual and should not be used for operational
purposes unless kept in a current status.
Assurance that the airplane is in an air worthy condition is the responsibility of the owner. The pilot
in command 1s responsible for determining that the airplane is safe for flight. The pilot is also responsible
for remaining within the operating limitations as outlined by instrument markings, placards, and this
manual.
Although the arrangement of this manual is intended to increase its in-flight capabilities, it should not
be used solely as an occasional operating reference. The pilot should study the entire manual to
familiarize humself with the limitations, performance, normal and emergency procedures and operational
handling characteristics of the airplane before flight.
The manual has been divided into numbered (arabic) sections. The limitations and emergency
procedures have been placed ahead of the normal procedures, performance and other sections to provide
easier access to information that may be required in flight. The "Emergency Procedures" Section is
quickly available, to present an instant reference. Provisions for expansion and/or updates to this manual +
have been made.
CERTIFICATION BASIS
This type of aircraft has been approved by Transport Canada Aviation in accordance with
Airworthiness standard 523 VLA including Amendment 07.93.
Category of Airworthiness: Utility |
Noise Certification Basis: /C40 Amex 16 and FAR 36- G
WARNINGS, CAUTIONS and Notes
The following definitions apply to warnings, cautions and notes used in the owner's manual.
WARNING: means that the non-observation of the corresponding procedure leads to an immediate
degradation of the flight safety which could result in loss of life or destruction of
equipment.
CAUTION: means that the non-observation ot the corresponding procedure leads to a degradation
of flight safety resulting in damage to the equipment.
NOTE: draws the attention to any item which is important or unusual.
1-1 8 May 95
ZENAIR AIRCRAFT
CH 2000 Trainer
SECTION 1
GENERAL
‚ оо ($5”
215 —— —
Tow) _ : <
NE al
< Q <
a v =
№ 255 8 — |
+ ae a <» or
240 |, a | SNe > |
Cv) | |= 1570 (5-1 | Mes
EN | | 7010 (23-0) ‚m 2
sl a |
to]
À po]
a o
1 {
2434 (8-0)
| 2200 (7-27 |
a780 (23-107)
CH 2000 Trainer
4 Feb 97
SPECIFICATIONS
ZENAIR CH 2000 Trainer
WING SPAN ...... aaa 28 FT. 10 IN.
WING AREA 111001100110 LL LL LL a 137 SQ. FT.
LENGTH . aaa aaa 23 FT
ENGINE .....111111 000 LL LL LL LR LL a Lee 116BHP
PROPELLER (Fixed Pitch Metal)... ... ................ 72 IN.
WING LOADING . 112411111110 0114112 о 11.7 P.S.F.
POWER LOADING . ... 220000000 eee 6 15.1 1b/HP
DESIGN LOADING FACTOR... ..... ... ........ +4 .4/-2.2 C's
CABIN WIDTH... LL LL LL AR LA 1e 46 IN.
FUEL CAPACITY (STANDARD) .......... 28 U.S. GAL. = 106 |.
FUEL CAPACITY (OPTIONAL WING TANK) 2x14 GAL. =2x53 1.
FUEL CAPACITY (OPTIONAL LARGE TANK) 34 U.S. GAL.= 130 1.
1-2
SECTION 1 ZENAIR AIRCRAFT
GENERAL CH 2000 Trainer
ENGINE - 4 Cylinders Horizontally Opposed - Air Cooled
Engine Manufacturer Lycoming
Engine Model Number 0235N2C
Rated Horsepower 116
Rated Speed (rpm) 2800
Bore (inches) 4.375
Stroke (inches) 3.875
Displacement (cubic inches) 233.3
Compression Ratio 8.1:1
PROPELLER - Fixed Pitch - Metal
Propeller Manufacturer Sensenich
Model 72-CK-0-46 or 72-CK
Number of Blades 2
Propeller Diameter (inches) 72
FUEL - Standard
Fuel Capacity
Usable Fuel (U.S. gal) (total)
Fuel grade, Aviation
- Wing Tank Option
Fuel Capacity
Usable Fuel (U.S. gal) (total)
Fuel Grade, Aviation
- Large Tank Option
Fuel Capacity
Usable Fuel (U.S. gal) (total)
Fuel Grade, Aviation
106 liters / 28 U.S. gal.
104 liters / 27.5 U.S. gal
100/100 LL
Jr
x 53 liters/2x14 U.S. ga
2 x 50 liters/2x13 U.S. g
100/100 L
23
2
=D
130 liters/34 U.S. g
128 liters/33.5 U.S. g
100/100 T.L
Ze
Liters 5.7 / 6 US Quarts
Refer to latest issue of Lycoming Service
Instruction 1014
Oil Viscosity at all temperatures Ashless dispersant SAE grades: 15W50 or 20W50
OIL
Oil Capacity
Oil Specification
MAXIMUM WEIGHTS
Maximum Takeoff Weight (lbs)
Maximum Landing Weight (lbs)
Maximum Weights in Baggage Compartment
SPECIFIC LOADINGS
Wing Loading (165 per sq ft)
Power Loading (lbs per hp)
1-3
prod jue
Un —
> ~ —)
1606 lbs (730 kg)
1606 lbs (730 kg)
(18 kg)
4 Feb 97
ZENAIR AIRCRAFT
CH 2000 Trainer
SECTION 1
GENERAL
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
The following definitions are of symbols, abbreviations and terminology used throughout the
handbook and those which may be of added operational significance to the pilot.
General Airspeed Terminology and Symbols
BHP
CAS
GPH
KCAS
C.G.
IAS
KIAS
RPM
S.L.
TAS
V
Va
VFE
Brake horsepower (= rated horsepower of the engine)
Calibrated Airspeed means the indicated speed of an aircraft, corrected for
position and instrument error. Calibrated airspeed 1s equal to true
airspeed in standard atmosphere at sea level.
Gallons (U.S) per Hr fuel consumption.
Calibrated Airspeed expressed in "Knots".
Centre of Gravity.
Indicated Airspeed is the speed of an aircraft as shown on the airspeed
indicator.
Indicated Airspeed expressed in "Knots".
Left
Right
Revolutions per minute.
Sea Level
True Airspeed is the airspeed orf an airplane relative to undisturbed air
which is the CAS corrected for altitude and temperature.
Speed.
Maneuvering Speed is the maximum speed at which application of full
available aerodynamic control will not overstress the airplane.
Maximum Flap Extended Speed is the highest speed permissible with wing
flaps partially or fully extended
(Unless stated otherwise speeds indicated within this manual are true airspeeds, not indicated speeds.)
1-4
SECTION 1 ZENAIR AIRCRAFT
GENERAL CH 2000 Trainer
General Airspeed Terminology and Symbols (continued)
VNE Never Exceed Speed is the speed limit that may not be exceeded at any
time.
YNO Maximum Structural Cruising Speed is the speed that should not be
exceeded except in smooth air and only with caution.
Vg | Stalling Speed or the minimum steady flight speed at which the airplane
1s controllable.
Vso Stalling Speed at which the airplane is controllable in the landing
configuration.
Vx Best Angle-of-Climb Speed 1s the air speed which delivers the greatest
gain of altitude in the shortest horizontal distance.
Vy Best Rate-of-Climb Speed is the air speed which delivers the greatest gain
in altitude in the shortest time.
1-5 3 Apr 95
Mal a Ei des
ZENAIR AIRCRAFT
CH 2000 Trainer
SECTION 1
GENERAL
3 Apr 95
Meteorological Terminology
ISA
OAT
Indicated
Pressure Altitude
Pressure Altitude
Station Pressure
Wind
" Units
International Standard Atmosphere ın which:
The air 1s a dry perfect gas;
The temperature at sea level is 159 Celsius (590 Fahrenheit);
The pressure at sea level is 29.92 inches hg. (1013 mb);
The temperature gradient from sea level up, is: - 1.989 C per 1000 В
or - 6.59 C per 1000 meter, or -3.570 Е рег 1000 В.
Outside Air Temperature is the free air static temperature, obtained
either from inflight temperature indications or ground
meteorological sources, adjusted for instrument error.
The number actually read from an altimeter when the barometric
subscale has been set to 29.92 inches of mercury (1013 mullibars).
Altitude measured from standard sea-level pressure (29.92 in. Hg)
by a pressure or barometric altimeter. It is the indicated pressure
altitude corrected for position and instrument error. In this manual,
altimeter instrument errors are assumed to be zero.
Actual atmospheric pressure at field elevation.
The wind velocities recorded as variables on the charts of this
manual are to be understood as the headwind or tailwind
components of the reported winds.
Speed: Kts (Knots) = 1.15 mph (mules per hour)
Pressure: PSI = Pounds per Square Inch
in Hg = inches ot Mercury
mb = millibar
Distances: in. = inches = 25.4 millimeters
В = foot (feet) = .305 meters
Weights: Kg = kilograms = 2.2 165 = 2.2 pounds
1-6
SECTION 1
GENERAL
ZENAIR AIRCRAFT
CH 2000 Trainer
a Power Terminology
Takeoff Power
Maximum Continuous
Power
Maximum Climb Power
Maximum Cruise Power
Engine Instruments
EGT Gauge
Maximum power permissible for takeoff.
Maximum power permissible continuously during flight.
Maximum power permissible during climb.
Maximum power permissible dunng cruise.
Exhaust Gas Temperature Gauge.
‘Airplane Performance and Flight Planning Terminology
o Climb Gradient
Demonstrated Crosswind
Velocity
1-7
The demonstrated ratio of the change in height during a
portion of a climb, to the horizontal distance traversed in
the same time interval.
The demonstrated crosswind velocity is the velocity of the
crosswind component for which adequate control of the
airplane during takeoff and landing was actually
demonstrated during certification tests.
3 Apr 95
ZENAIR AIRCRAFT
CH 2000 Trainer
SECTION 1
GENERAL
3 Apr 95
Weight and Balance Terminology
Reference Datum
Station
Position or Arm
Moment
Center of Gravity
(C.G.)
C.G. Arm
C.G. Limits
' Usable Fuel
Unusable Fuel
Standard Empty Weight
Empty Weight
Payload
Useful Load
Maximum Takeoff
Weight
An imaginary vertical plane from which all horizontal
distances are measured for balance purposes: wing leading
edge at rib #4
A location along the airplane fuselage center line given in
terms of distance from the reference datum.
The horizontal distance from the reference datum to the
center of gravity (C.G.) of an item parallel to fuselage
centerline.
The product of the weight of an item multiplied by its arm.
(Moment divided by a constant is used to simplify balance
calculations by reducing the number of digits.)
The point at which an airplane would balance if suspended.
[ts distance from the reference datum is found by dividing the
total moment by the total weight of the airplane.
The arm obtained by adding the airplane's individual moments
and dividing the sum by the total weight.
The extreme center of gravity locations within which the
airplane must be operated at a given weight.
Fuel available for flight planning.
Fuel remaining after a runout test has been completed in
accordance with governmental regulations.
Weight of a standard airplane including unusable fuel, full
operating fluids and full oil.
Standard empty weight plus optional equipment.
Weight of occupants, fuel and baggage.
Difference between takeoff weight, and empty weight.
Maximum approved weight.
1-8
SECTION 2
LIMITATIONS
TABLE OF CONTENTS
General ....... ..
Airspeed Limitations.. ... LL LA ae
Airspeed Indicator Markings
Powerplant .......... 000 LL LL AL AAA RS
Powerplant Instrument Markings .
Weight Limits... LA aa Le
Center of Gravity Limits... .... ALL AA оо
Maneuver Limits . . .. .. 11100 LL LL LL LL Le
Flight Load Factors... ... 10 a
Турез оЁ Орегацоп$.............. новее)
Fuel 1111111111 LL LL LL RL LL
Occupants. 1111111101 LL LR LR A ae ee
Limitation Placards . .. 10111 LA NL LL Lee
Weight and C.G. Range... o.oo
Ra AAA E €
RARA AE AE IEA A
Fe
SECTION 2 ZENAIR AIRCRAFT
LIMITATIONS CH 2000 Trainer
SECTION 2
LIMITATIONS
GENERAL
This section includes operating limitations, instrument markings, and basic placards necessary for
safe operation of the airplane, its engine, standard systems and standard equipment.
Note: All airspeeds are knots indicated airspeed unless specified.
AIRSPEED LIMITATIONS
SPEED KIAS KCAS REMARKS
VNE Do not exceed this speed in any
Never Exceed Speed 145 159 operation.
NO Do not exceed this speed except in
Maximum Structural Cruising 108 104 smooth air and then only with caution.
Speed
VA Do not make full or abrupt control
Design Maneuvering Speed 108 104 movements above this speed.
|
VEE | Do not exceed this speed with flaps
Maximum Flap Extended Speed 101 99 | extended.
AIRSPEED INDICATOR MARKINGS
MARKING KIAS VALUE OR RANGE SIGNIFICANCE
White Arc 29 to 101 Full Flap Operating Range. Lower limit 1s
maximum weight stalling speed in'landing
configuration. Upper limit is maximum speed
permissible with flaps extended.
Green Arc 36 to 108 Normal Operating Range. Lower limit 1S maximum
| weight stalling speed with flaps up. Upper limit is
maximum Structural cruising speed.
Yellow Arc 108 to 145 Operations must be conducted with caution and only
In smooth air.
Red Line 143 | Maximum speeds for all operations.
APP
2-1 19 July 95
ZENAIR AIRCRAFT SECTION 2
— CH 2000 Trainer LIMITATIONS
Power plant
Г. Engine Manufacturer: . ................. As Lycoming
| Engine Model: .............. 22000 LL LA 0235N2C
Maximum Power, Take-off: . .......... . 116 BHP
o Continuous: ........... aa 116 BHP
Maximum Engine rpm, Take-off: ........... .... .... 2800
| Continuous: ........... e 2800
Maximum Cylinder Head Temperature: ................... 5009 F
Maximum Oil Temperature: ............. .... ....... 2459 F
Normal: ....... aaa LL 60 to 90 psi
Maximum: ....... aaa LL —.. 115 psi
| Fuel Pressure, Minimum: . ........................ ........ 0.5 psi
Desired: . .. .. as 3 psi
Maximum: ....... 11110101 LL LL LL 8 psi
is Fuel Grade (minimum octane): .......... 100/100LL Grade Aviation Fuel
Oll Grade .......... as Ashless dispersant
SAE grades 15W50 or 20W50
; Propeller Manufacturer: . ......................... .. ... Sensenich
Propeller Model: . .................. ..... 72-CK-0-46 or 72-CK-0-48
Propeller Diameter: Maximum . .................... .... . 72 inches
Minimum ....... aaa 70 inches
| ` Propeller Tolerance (static RPM at full throttle) . . . . Not above 2750 RPM
OUTSIDE TEMPERATURE LIMIT
В Maximum Outside Temperature for proper engine cooling ...... 100°F (38°C)
Extreme Hot temperature operation...................... see page 9-7
INSTRUMENT MARKINGS
po Red Line Green Arc Red Line
INSTRUMENT MINIMUM NORMAL MAXIMUM
LIMIT OPERATING LIMIT
TACHOMETER RPM — — 800 - 2800 2800
OIL TEMPERATURE OF —_ 160 - 220 245
FUEL PRESSURE PSI 3 3-8 8
OIL PRESSURE PSI 15 60 - 90 115
| АММЕТЕК AMPS -75-0 +50-+75
VOLTMETER VOLTS | 10-14
SUCTION Hg Yellow 0 - 4.3 43-61 Yellow 6.1 - 7
| WEIGHT LIMIT
Maximum Take-off weight: ............. .. 1606 Ibs (730 kg)
Maximum Landing weight: .............. о. 1606 Ibs (730 kg)
| Maximum empty weight: with engine oil full and
including unusable fuel ....... 1175 lbs (535 kg)
Maximum weight in Baggage Compartment: ............ 40 lbs (18 kg)
APP
4 Feb 97 2-2
Beh Sa à
SECTION 2 ZENAIR AIRCRAFT
LIMITATIONS CH 2000 Trainer
CENTER OF GRAVITY LIMITS
(See Page 2.5)
MANEUVER LIMITS
- Limited acrobatic maneuvers include:
Entry Speed
Steep Turns 90 KAS
Lazy Eights 100 KAS
Chandelles 100 KAS
Spins: Only airplanes Serial Numbers 20-0022 and subsequent and airplanes Senal
Numbers 20-002 through 20-0021 inclusive which have been modified in
accordance with Zenair Ltd IPL#RS are approved for intentional spins.
When the center of gravity is aft of 420mm (16.5 inches), spins
are prohibited.
Intentional spins prohibited with flaps extended.
FLIGHT LOAD FACTORS
Flap up: Positive + 4.4
Negative - 2.2
Flap extended: Positive 2.2
Negative 0 “
TYPES OF OPERATIONS ;
The airplane is approved for the following operations when equipped in accordance with the prevailing regulations.
Day V.F R.
Night - when equipped with the light option. (see section 9)
Dav/Night VFR/IFR when equipped in accordance with National requirements (see section 9)
x Flight in known or forecast icing conditions is prohibited.
FUEL
Standard tank capacity 106 liters / 28 US gal.
Usable 104 liters / 27.5 US gal.
Wing tank option capacity 2x33 hiters/2x14 US gal.
Usable 2x50 liters/2x13 US gal.
Large tank option capacity 130 liters/34 US gal.
Usable 128 liters/33.5 US gal.
OIL =
See page 1-3
OCCUPANTS
Minimum One Pilot
Maximum One Pilot and One Passenger
APP
-3 4 Feb 97
ty
ZENAIR AIRCRAFT
CH 2000 Trainer
SECTION 2
LIMITATIONS
LIMITATION PLACARDS
The following placards are installed (Boxed items for night flying option)
- On the instrument panel:
RADIOS
. Compass deviation chart
. NO SMOKING
. MANEUVERING SPEED VA = 108 KIAS
CABIN HEAT PULL ON
THROTTLE PULL CLOSE
Registration
USABLE FUEL
”
. Fuel selector: 104 L./27.5 US gal, DEPRESS, ON, OFF
DAY VFR ONLY
IN NON-ICING CONDITIONS
AEROBATIC MANEUVERS
AND SPINS ARE PROHIBITED
SEE OWNER’S MANUAL
(or with Night Flying Option)
+
DAY VFR ONLY
IN NON-ICING CONDITION
AEROBATIC MANEUVERS
AND SPINS -
SEE OWNERS MANUAL
A
(or for spinable aircraft)
-—
DAY AND NIGHT VFR
IN NON-ICING CONDITIONS
DAY AND NIGHT VFR
IN NON-ICING CONDITIONS.
104 L./27.3 US gal AEROBATIC MANEUVERS AEROBATIC MANEUVERS
a AND SPINS ARE PROHIBITED AND SPINS
UP TRIM SEE OWNER'S MANUAL SEE OWNERS MANUAL
FLAP
DOWN DOWN
UP
MASTER MASTER CARB FIELD ALTERNATOR AUXILIARY
BREAKER SWITCH HEAT BKR BREAKER FUEL PUMP BKR
ON ON R BOTH ON ON ON
OFF OFF OFF START OFF OFF OFF ,
OIL OIL STARTER TURN & RADIOS |
PRESS. TEMP. SOLENOID BANK %
FUEL FUEL
PRESS. GAUGE
AUXILIARY
FLAP * STALL TRIM
WARN.
7 12 volts
LIGHT MIXTURE NAV LAND CABIN
MASTER PUSH RICH LIGHT LIGHT STROBES LIGHT
BKR BKR R. BKR BKR BKR
- Beside the red door handles: OPEN T
+ CLOSED
- Baggage area: 18kg/ 40 LBS MAX. SOFT ARTICLES ONLY
CHECK WEIGHT AND BALANCE
- Beside tuel filler AVIATION FUEL
100/100LL
. 106 L./28 US gal
- Oil filler cover: OIL 5.7 L. or 6 US gts.
SAE 20W50
- Left forward fuselage: FUEL DRAIN y
- Rear left side fuselage: (identification plate) ZENAIR LTD
| CH 2000 #(senal)
MIDLAND. ON (date)
Т.А. FA-185 FAA T.C. 4TASCH MFR.APP. 472-94
29 Aug 96 2-4
ZENAIR AIRCRAFT SECTION 2
CH 2000 Trainer LIMITATIONS
WEIGHT AND C.G. RANGE
W |
& | ASIII
700 Ks ‚ NT
:
} N
(sto Lo o 670 Ka (#75 ID N
Ÿ |
N | x
№ See Note NN
600 Kg N | N
(1220 Lbs) NN | N
500 Ka. N | NN
(1100 L6 5) N | =
N NN 1
N N
N | 8
Loo Ke NN N
(Esc US N
/ |
NN] NN
| |
320 mm 250 mm +00 mm H2Omm 43
(12.57) (13.37) (5.7) (6.5) (1.1,
22 %. HAC 25.1 % MAC 27.5% MAL 22% HAC 307% MA
| MAC = 1450 mm (577) “
(a. 5)
26 mm (Fred)
AE
~3 Vm e
NOTE: Intentional spins prohibited: (17.17)
- when Centre of Gravity aft of 420 mm (16.5 inches)
- when flaps extended
- on airplanes Serial Numbers 20-0002 through 20-0021 inclusive unless modified in
accordance with Zenair Ltd. IPL#RS.
2-5 29 Aug 96
Mg ee WEA 8
rs
- Emergency Procedures Check List
SECTION 3
EMERGENCY PROCEDURES
TABLE OF CONTENTS
Amplified Emergency Procedures .
Engine Fire During Start
Engine Power Loss During Takeoff .
Engine Power Loss in Flight
Power off Landing . . .
Fire in Flight. o
Loss or Oil Pressure
Loss of Fuel Pressure .
High Oil Temperature В
Alternator Failure. 2
Spin Recovery |
Carburetor Icing . 11
Engine Roughness .
PO
2 009) LU) LI) TY DIR
CID | —‹
o
(J) ‘52
1
Ch ai hn
SECTION 3 ZENAIR AIRCRAFT
EMERGENCY PROCEDURES CH 2000 Trainer
SECTION 3
EMERGENCY PROCEDURES
GENERAL
The recommended procedures for coping with various tvpes of emergencies and critical situations are
provided by this section.
The first portion of this section consists of an abbreviated emergency check list which supplies an
action sequence for critical situations with little emphasis on the operation of the systems.
The remainder of the section is devoted to amplified emergency procedures containing additional
information to provide the pilot with a more complete understanding of the procedures.
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. Pilots should familiarize
themselves with the procedures given in this section and be prepared to take appropriate action should
an emergency arise.
- Pc NOT TURN ofFF ALTEKNATOR IN FLIGHT Ex. EPT
IN AN EMERGENCY
APP
3-1 3 Apr 95
ZENAIR AIRCRAFT
CH 2000 Trainer
SECTION 3
EMERGENCY PROCEDURES
EMERGENCY PROCEDURES CHECK LIST
ENGINE FIRE DURING START
Starter... continue cranking
( If engine starts)
Power ........... 1700 RPM momentanly
Engine... SHUTDOWN and inspect for damage
(If engine fails to start)
ÍSMItION ...... as OFF
Master Switch... as OFF
Mixture ...... 2..0... IDLE CUT OFF
Fuel... LL OFF
(abandon aircraft and fight tire)
ENGINE FAILURE DURING TAKEOFF
Throttle . . .. IDLE
Brakes... ... APPLY
Wıng FlapsS ............. UP
MixXture ..... IDLE CUT-OFF
lgnition SWItea...... 0111 LL OFF
Master Switch ....... OFF
Airspeed LLL к. 65 KIAS
MIXture . ¡DLE CUT-OFF
Fuel Selector oo. OFF
Ignition SWIteh...... 2111111110 OFF
Wing Flaps. ......... AS REQUIRED
Master SWItCA...... LL OFF
19 July 95
ENGINE FAILURE IN FLIGHT
(Restart Procedure)
Alrspeed...... LL 65 KIAS
Fuel Selector... .... ... | ON
Aux FuelPump.... ON
Mixture 122111111111 0 RICH
Mag. Switch .............. a BOTH
Carburetor Heat ........ ON
Gauges... .... Check for source of power loss
POWER OFF LANDING
Touchdowns should normailv be made at \owest
possible airspeed with full flaps.
When committed to landing:
igniton... 112111000111 OFF
Master SWIteh ... 2111111000 OFF
Fuel selecCtOr OFF
Mixture... о, IDLE CUT OFF
Seat belt and hamness ....... Secure
3-2
SECTION 3
EMERGENCY PROCEDURES
ZENAIR AIRCRAFT
CH 2000 Trainer
PRECAUTIONARY LANDING WITH
ENGINE POWER
Seats, Seat Belts, Shoulder Harnesses . SECURE
Airspeed... 1121111120 65 KIAS (flaps UP)
60 KIAS (flaps down)
Mixture . 1111111101 LLLLLLL RICH
Fuel Selector... ... .... ....... ON
Ignition Switch... ON
Wing Flaps..... .... as required
Master SwitCh . ON
Touchdown... ~~... .. slightly tail low
Brakes. . ... .. as required
FIRE IN FLIGHT
Source Of fire 111111110110 1 000 check
Electrical fire (smoke in cabin):
Master switen anc Alt. Field... . OFF
Vents ...... 1110111110 open
Cabin heat... ... OFF
Fire Extinguisher .. 111222 If and as required
Land as soon as practical.
Engine fire:
Cabin Heat ..... 2.00. OFF
Fuel selector .. 11111111 OFF
Throttle... о) CLOSED
Mixture. 120111110000 IDLE CUT-OFF
Auxiliary fuel pump... OFF
Proceed with POWER OFF LANDING procedure
LOSS OF OIL PRESSURE
Reduce power.
Prepare for power off landing, and land as soon as
practical.
LOSS OF FUEL PRESSURE
Auxiliary fuel pump 1111111112 ON
Fuel selector ...... check "ON"
Land at nearest airport and investigate problem.
APP
3-3
HIGH OIL TEMPERATURE
Land at nearest airport and investigate the
problem. Prepare for power off landing.
ALTERNATOR FAILURE
Verifv failure
Reduce electrical load as much as possible.
Alternator circuit breakers check
AÎt. switen. OFF «for 1 second), then ON
If no input Alt field... OFF
Reduce electrical load and land as soon as
practical.
E e A.
SPIN RECOVERY
Rudder — Full opposite to spin direction.
Ailerons о, Neutral
Pitch 1101111100 Full forward.
When rotation stops, centralize rudder and ease
control wheel back :0 gently recover from dive.
Observe tlap limit speed. if flaps are down.
ENGINE ROUGHNESS
Carburetor heat 11111110 ON
Mixture idjust ror max. smoothness
Auxiliary fuel pump 0 ON
Fuel selector | . check open
Engine gauges 111 LL check
Magneto switen 111220 "BOTH
{tf operation is satisractorv on either one, continue
on that magneto at reduced power and full
"RICH" mixture to first airport.
Prepare tor power off landing,
29 Aug 96
ZENAIR AIRCRAFT
CH 2000 Trainer
SECTION 3
EMERGENCY PROCEDURES
ICING
Inadvertent Icing Encounter
Ensure Pitot heat 1s ON.
Turn back or change altitude to obtain an outside
air temperature that is less conducive to icing.
Pull cabin heat control full out to obtain maximum
defroster air temperature.
Open the throttle to increase engine speed and
minimize ice build-up on propeller blades.
Apply carburetor heat as required. Lean the
mixture for maximum RPM. if carburetor heat is
used continuously.
Plan a landing at the nearest airport. With an
extremely rapid ice build-up. select a suitable "ог
airport” landing site
With ice accumulation on the wing leading edges.
be prepared tor significantly higher stall speed
Leave wing tlaps retracted. With a severe ice
build-up on the horizontal tail. the change in wing
wake airflow direction caused bv wing flap
extension could result in a loss ot elevator
effectiveness.
When the alternate static (1f equipped) 1s used. the
altimeter reading must be decreased bv 100 tt
(and 190 ft. when the deicing window 1s open)
When the pitot 1s not frozen and the alternate
static is used. the airspeed reading will be 29 Kis
too high; in other words: the actual aispeed :s
20 kts lower than indicated.
ELECTRICAL POWER SUPPLY SYSTEM
MALFUNCTIONS
Ammeter Shows Excessive Rate of Charge
(Full scale deflection)
Alternator ~~... OF!
Alternator Circuit Breaker ... 0...) OFF
Nonessential Electrical Equipment 1111 OFF
Flight оо... Terminate as soon as possible
16 Dec 97
Ammeter Indicates Discharge
NOTE
Radios OFF
Alternaror Cire:nt Breaker CHECK ON
Master Sanne OFF
Master Suit iy ON
Radios ON
If Ammeter Continues Indicating Discharge
Alternate OFF
OFF
Ferminate GS SOON àS possibie
г
Nenessental Raco and LElecı equipment
r-
Fughl
СЕСТРА FLAT
decome moremive. the flight
may De continued sales Io
i
Should the tap:
ded tollowine is
e ; 1400
Rept no nnd
Flaps Dow Dio LAN
Cato! © 0 E |, > Cl ’ | x y Os !
“1 11 1 1 No x
à a 4 ITA era UNOS
Flaps tp:
_ И | los O
IDO 1 ts aa N
CAUTO me Pres a Ue andino
bs
SEAN
ELECTRIC TRIN
CA EN ; ; Lu ` т. > a do a o ~ + +. e
ete Ire (Dalferv and
IN case
alrerpato or tE LA Зее ВО
Onger se 108 TO Malo ie 00 TNCR Conte
Drees Fhes may pecome cae neon Nise
“peed 1,1 Ya \ ! HE N ! E LOT 20 nN 1 -
CON e ue Na NETOS
ATEN HSA SÁ DI
AI
LIGHTNING STRIKE
| LA» \ { Pat sage ado ‘ A tives . ис
PASO ob рр strike aha A Te Nedre st
SECTION 3 | ZENAIR AIRCRAFT
EMERGENCY PROCEDURES CH 2000 Trainer
AMPLIFIED EMERGENCY PROCEDURES (GENERAL)
The following paragraphs are presented to supply additional information for the purpose of providing
the pilot with a more complete understanding of the recommended course of action and probable cause of
an emergency situation.
ENGINE FIRE DURING START
Engine fires during start are usually the result of overpriming. The first attempt to extinguish the fire 1s
to try to start the engine and draw the excess fuel back into the induction system and blow the fire out.
[f fire continues more than a few seconds, the engine should be shut down and the fire extinguished by
the best available means.
ENGINE POWER LOSS DURING TAKEOFF
The proper action to be taken if loss of power occurs during takeoff will depend on the circumstances
of the particular situation.
If sufficient runway remains to complete a normal landing, land straight ahead.
Any turn will increase the risk of stall or stall/spin, fatal at low altitude. Land as straight ahead as
practical and maintain a safe airspeed and make only a very shallow turn if necessary to avoid
obstructions. Use of flaps depends on the circumstances. Normally, flaps should be fully extended for
touchdown.
If sufficient altitude has been gained to attempt a restart, maintain a safe airspeed and check the fuel
selector, check the Auxiliarv fuel pump to ensure that it is "ON" and that the mixture is "RICH." The
carburetor heat should be "ON".
If power is not regained, proceed with the Power Off Landing procedure (refer to the emergency
check list).
3-5 3 Apr 95
ZENAIR AIRCRAFT SECTION 3
CH 2000 Trainer EMERGENCY PROCEDURES
ENGINE POWER LOSS IN FLIGHT
Complete engine power loss is usually caused by fuel flow interruption and power will be restored
shortly after fuel flow is restored. If power loss occurs at a low altitude, the first step is to prepare for an
emergency landing. An airspeed of at least 60 KIAS should be maintained.
If altitude permits, check the fuel and turn the Auxiliary fuel pump "ON." Move the mixture control to
"RICH" and the carburetor heat to "ON." Check the gauges for an indication of the cause of the power
loss. If no fuel pressure is indicated, check the tank selector position.
When power is restored move the ca:buretor heat and the Auxiliary fuel pump to "OFF".
If the preceding steps do not restore power, prepare for an emergency landing.
If time permits, turn the ignition switch to "L" then to "R" then back to "BOTH." Move the throttle
and mixture control levers to different settings. This may restore power if the problem is too rich or too
lean a mixture or if there is a partial fuel system restriction. Water in the fuel could take some time to be
used up, and allowing the engine to windmill may restore power. If power loss is due to water, fuel
pressure indications will be normal.
(If engine failure was caused by fuel exhaustion power will not be restored after switching fuel tanks
until the empty fuel lines are filled. This may require up to six seconds. wing tank option only)
If power is not regained, proceed with the Power Off Landing procedure (refer to the emergency check
list). )
POWER OFF LANDING
If loss of power occurs at altitude, trim the aircraft for best gliding angle (60 KIAS) and look for a
suitable field. If measures taken to restore power are not effective, and if time permits, check your charts
for airports in the immediate vicinity; it may be possible to land at one if you have sufficient altitude. If
possible, notify Air Traffic Control or other facility by radio of vour difficulty, position, and intentions.
When committed to a landing, flaps may be used as desired. Turn the fuel selector valve to "OFF"
and pull the mixture out. Shut "OFF" the master and ignition switches. The seat belts and shoulder
harness should be tightened. Touchdown should be normally made at the lowest possible airspeed.
3 Apr 95 3-6
SECTION 3 ZENAIR AIRCRAFT
EMERGENCY PROCEDURES CH 2000 Trainer
FIRE IN FLIGHT
The presence of fire 1s noted through smoke, smell and heat in the cabin. It is essential that the source
of the fire be promptly identified through instrument readings, character of the smoke. or other
indications since the action to be taken differs somewhat in each case. |
Check for the source of the fire first.
If an electrical fire is indicated (smoke in the cabin), the master switch should be turned "OFF." The
cabin vents should be opened and the cabin heat turned "OFF." If installed: use fire extinguisher as
required. A landing should be made as soon as possible.
If an engine fire 1s present, switch the fuel selector to "OFF" and close the throttle. The mixture
should be pulled out. Turn the Auxiliary fuel pump "OFF." In all cases, the cabin heat should be pushed
"OFF." Once final flap configuration is set, select master switch "OFF." Proceed with power off
landing procedure.
LOSS OF OIL PRESSURE
Loss of oil pressure may be either partial or complete. A partial loss of oil pressure usually indicates a
malfunction in the oil pressure regulating system, and a landing should be made as soon as possible to
investigate the cause and prevent engine damage.
A complete loss of oil pressure indication may signify oil exhaustion or may be the result of a faulty
gauge. In either case, proceed toward the nearest airport at reduced power setting, and be prepared for a
forced landing. If the problem is not a pressure gauge malfunction, the engine may stop suddenly.
Maintain altitude until such time as a dead stick landing can be accomplished. Don't change power
settings unnecessarily, as this may hasten complete power loss.
Depending on the circumstances, it may be advisable to make an off airport landing while power is still
available, particularly if other indications of actual oil pressure loss, such as sudden increases in
temperatures, oll or smoke, are apparent, and an airport is not close.
If engine stoppage occurs, proceed with Power Off Landing.
3-7 3 Apr 95
PPR Ry {mY
ZENAIR AIRCRAFT SECTION 3
CH 2000 Trainer EMERGENCY PROCEDURES
LOSS OF FUEL PRESSURE
If loss of fuel pressure occurs, switch the Auxiliary fuel pump "ON" and check the fuel selector.
Land as soon as practical and have the engine driven fuel pump and fuel system checked.
HIGH OIL TEMPERATURE
An abnormally high oil temperature indication may be caused by a low oil level, damaged or improper
battle seals, a defective gauge, or other causes. Land as soon as practical at an appropriate airport and
have the cause investigated.
A steady, rapid rise in oil temperature is a sign of trouble. Land at the nearest airport and let a mechanic
investigate the problem. Watch the oil pressure gauge for an accompanying loss of pressure.
ALTERNATOR FAILURE
Loss of alternator output is detected through negative reading on the ammeter. Before executing the
following procedure, ensure that the reading is negative and not merely low, by actuating an electrically
powered device, such as the flaps. If no increase in the ammeter reading is noted, alternator failure can be
assumed.
The electrical load should be reduced as much as possible. Check the alternator circuit breakers for a
popped circuit.
The next step is to attempt to reset the overvoltage relay. This is accomplished by moving the "ALT"
switch to "OFF" for one second and then to "ON." If the trouble was caused by a momentary
overvoltage condition (16.5 volts and up) this procedure should return the ammeter to a normal reading.
If the ammeter continues to indicate "0" output. or if the alternator will not remain reset, turn the "ALT"
switch "OFF," maintain minimum electrical load and land as soon as practical. All electrical load is being
supplied by the battery only.
SPIN RECOVERY
Apply full rudder opposite to direction of rotation and with ailerons in neutral, push control wheel
forward. When rotation stops, centralize the rudder, and ease back on the control wheel to recover from
the dive.
Observe flap limit speed if flaps are down.
Warning: Intentional spinning is not approved if center of gravity 1s aft of 420mm (16.5 inches),
nor with flaps extended.
29 Aug 96
©)
со
SECTION 3 ZENAIR AIRCRAFT
EMERGENCY PROCEDURES CH 2000 Trainer
CARBURETOR ICING
ENGINE ROUGHNESS
Engine roughness 1s usually due to carburetor icing which is indicated by a drop in RPM, and may be
accompanied by a loss of airspeed or altitude. If too much ice is allowed to accumulate, restoration of
full power may not be possible; therefore, prompt action is required.
Pull carburetor heat on (See Note). RPM will decrease slightly and roughness will increase. Wait for
a decrease in engine roughness and increase in RPM, indicating ice removal. If no change in
approximately one minute, push the carburetor heat to "OFF."
If the engine 15 still rough, adjust the mixture for maximum smoothness. The engine will run rough ¡f
too rich or too lean. The electric fuel pump should be switched to "ON" and the fuel selector checked
to see if fuel contamination is the problem. Check the gauges for abnormal readings. If any gauge
readings are abnormal, proceed accordingly. Move the magneto switch to "L" then to "R," then back
to "BOTH." If operation 1s satisfactory on either magneto, proceed on that magneto at reduced power.
with mixture pushed full "RICH," to a landing at the first available airport.
If roughness persists, prepare for a precautionary landing at pilot's discretion.
NOTE
Partial carburetor heat may be worse than no heat at all, since it
may melt part of the ice, which will refreeze in the intake system.
When using carburetor heat, therefore, always pull full heat, and
when ice is removed, push the control to the full cold position.
3-9 3 Apr 95
SECTION 4
NORMAL PROCEDURES
TABLE OF CONTENTS
General
Airspeeds for Safe Operations
Normal Procedures Check List
Before Starting the Engine
Starting the Engine
Warm-up and Ground Test
Taxiing ....
Betore Take-off
YAA eee RRA AAA a e
Же
Approach
Landings =... ..
Shut Down (Engine)
Tie Down
«he ee ea eae ws
Ss ee eae ea ees
SECTION 4 ZENAIR AIRCRAFT
NORMAL PROCEDURES CH 2000 Trainer
SECTION 4
NORMAL PROCEDURES
GENERAL
Thus section describes the recommended regulatory procedures for the conduct of normal operations
tor the CH 2000 Trainer. All of the regulatory required procedures and those necessary for the safe
operation of the airplane as determined by the operating and design features of the airplane are presented.
Normal procedures associated with those optional systems and equipment which require manual
supplements are provided by Section 9.
These procedures are provided to present a source of reference and review and to supply information
on procedures which are not the same for all aircraft. Pilots should familiarize themselves with the
procedures given in this section in order to become proficient in the normal operations of the airplane.
AIRSPEEDS FOR SAFE OPERATIONS
The following airspeeds are those which are significant to the safe operation of the airplane. These
figures are for standard airplanes flown at gross weight under standard conditions at sea level.
Performance for a specific airplane may vary from published figures depending upon the condition of
the engine, airplane and equipment, atmospheric conditions and piloting technique.
(a) Best Rate of Climb Speed 63 KIAS
(b) Best Angle of Climb Speed 60 KIAS
(c) Turbulent Air Operating Speed: Do not exceed 108 KIAS
(d) Maximum Flap Speed 103 KIAS
(e) Landing Final Approach Speed (Flaps down) 60 KIAS
(f) Maximum Demonstrated Crosswind Velocity 25 KTS
APP
4-1 3 Apr 95
ZENAIR AIRCRAFT SECTION 4
CH 2000 Trainer NORMAL PROCEDURES
WALK-AROUND
NORMAL PROCEDURES CHECK LIST
PREFLIGHT CHECK
1 Unlock and open canopy
2 Check cockpit: Ignition Magnetos 1 — 2 off
Master Switch on
Mixture Control pull out "lean"
Throttle pull out "idle"
Fuel open |
Flaps down
Master Switch off |
APP
3 Apr 95 4-2
AS wp WIE NWR
SECTION 4 ZENAIR AIRCRAFT
NORMAL PROCEDURES CH 2000 Trainer
3 - Check left windshield and canopy for general condition.
- Drain sample from both: sump and gascolator.
- Inspect left main landing gear and tire for general condition (wear, cuts. abrasions, leaking
brakes. tire inflation).
Check Pitot static (remove cover, and dirt). Check Pitot static heat before IFR flight (Master ON).
4 - Check left wing surface and tip for damage.
- Remove left wing ue down.
- Check condition and security of lights.
Wh
- Check left aileron for freedom of movement and security.
- Check left flap for safety.
6 - Check rear fuselage for damage- rear access doors secured.
- Check antennas.
7 - Check elevator and rudder condition and freedom of movement.
- Check cables and hinges.
- Check trim tab for security.
- Remove tail tie down.
- Check condition and security of tail light.
8 - Check right flap for safety.
- Check right aileron for freedom of movement and security.
9 - Check right wing surface and up for damage.
- Remove night wing ue down.
- Check stall warning for freedom movement.
- Check condition and security of lights.
10 - Inspect right landing gear and tire for general condition
(wear. cuts. abrasions. leaking brakes. ure inflauon).
- Check stall warning (Master ON)
- Drain sample from the fuel tank. and the gascolator.
- Check nght windshield and canopy for general condition.
11 - Check engine cowling for damage and security of fasteners.
- Open engine access door and check engine oil dipstick.
- Re-Install engine cowling after completion of engine
compartment check (check secunty of fasteners).
12 - Check engine muffler and exhaust for cracks. nicks. and secunty
13 - (Remove tow bar from nose gear.)
- Check nose gear and tire for general condition
(wear. cuts. abrasions. tire inflation).
- Check air intake for foreign particles.
- Check nose cone for damage
- Check propeller for damage.
| Physically check fuel level in tank(s) before each take off
APP
4-3 15 Dec 95
PR TR PE Wr
ZENAIR AIRCRAFT SECTION 4
CH 2000 Trainer NORMAL PROCEDURES
BEFORE STARTING THE ENGINE
Operate the controls and check for proper operation. Make sure the windshield is clean for best visibility. Check brakes,
and fasten and check safety belt.
STARTING THE ENGINE
- Perform pre-flight inspection.
- Head airplane into wind.
- Lock wheels by either wheel brakes or chocks.
- Master "ON".
- Push carburetor heat control in (closed).
- Turn fuel valve to "ON" position.
- Set throttle back (idle).
- Push mixture control to "Full Rich".
- Switch electric fuel pump "ON".
- Pump throttle to full open and back to idle for 2 to 3 strokes for a cold engine.
- Engage the starter.
- When engine fires, release magneto key to the "Both" position.
- Check oil pressure gauge. If oil pressure is not indicated within thirty seconds, stop
the engine and determine the trouble.
- Alternator and Field "ON".
Primer: - above freezing OAT - one stroke primer should be sufficient.
near freezing temperature - up to three strokes of the primer may be necessary.
- If the engine is under primed--most likely in cold weather with a cold engine--it will not fire
and additional priming will be necessary.
- below -12°C (10°F) OAT, the engine should be preheated.
E AO Le . Cia am
Note: Overpriming or flooding is indicated by intermittent firing followed by puffs of black smoke from the
exhaust.
Excess fuel can be cleared bv pulling the mixture out, pushing the throttle full open and cranking the engine
over several revolutions with the starter.
Caution: The primer must be fully pushed in and locked (1/2 turn) before cranking the engine, to avoid flooding.
WARM-UP AND GROUND TEST
The engine is air cooled and depends on the forward movement of the aircraft to maintain proper cooling. Particular care
is necessary, therefore, when operating the engine on the ground during hot weather to prevent overheating. И 15
recommended that the following procedures be observed.
- Head the aircraft into the wind.
- Adjust the throttle to 1200 rpm for warmup.
- Leave the mixture control in the "Full Rich" setting.
- Avoid prolonged idling at low RPM as this practice may result in fouled plugs. Limit
ground running to minimum time necessary to warm engine for take-off. without overheating it.
- Use of the carburetor hot air on the ground must be held to a minimum.
Dust, sand, etc... can be taken into the engine with the resultant cylinder
and piston ring wear. Carburetor air heat should be used on the ground only to make
certain it is functioning properly.
NOTE: Any ground check that requires full throttle operation must be short to prevent overheating the engine.
APP
4 Feb 97 4-4
SECTION 4 ZENAIR AIRCRAFT
NORMAL PROCEDURES CH 2000 Trainer
TAXIING
With the tricycle configuration, taxiing is easy with the use of the steerable nose wheel. Avoid steering the aircraft with
the brakes. When winds exceed 15 to 20 mph. taxi very slowly and carefully. Position control surfaces to prevent inadvertent
lift-off. |
Check: flight instruments and radio aids: functioning correctly.
BEFORE TAKE-OFF
- Check flaps up.
- Set trim.
- Check fuel selector valve.
- Check map/manual pocket is secured
- Check oil pressure and oil temperature.
- Check fuel quantity.
- Check Volts and Amp meter.
- Check all lights (if installed), select as required.
- Check and set radios and Navigation aids (if installed).
- Check mixture pushed “RICH”, Auxiliary fuel pump "ON".
- Set throttle for 1700 RPM. Check magnetos from "BOTH" to TWO, then from "BOTH" to ONE, and back to
"BOTH" (on either one magneto, the RPM drop is approximately 100).
- Pull carburetor heat to check operation. (RPM will decrease by approximately 100 at 1700 RPM). Push carburetor heat
in after check. |
- Set Altimeter.
- Check pitot heat (if installed): “ON” (switch up) when flving in IFR conditions.
- Check alternate static (if installed) switch (Normal: switch down).
- Fasten seat belts, tighten (but not uncomfortably).
- Check that canopy is locked securely (both doors).
- Check freedom and deflection of controls.
TAKE OFF
- Release brakes.
- Push throttle fully open.
- Check RPM, and gauges.
- Rotate at approxamately 50 KIAS.
CLIMB (at Max. Weight, flaps up)
BEST RATE OF CLIMB (Vv): Approx. 63 KIAS. This will provide the greatest altitude gain in the shortest time.
BEST ANGLE OF CLIMB (Vx): Approx. 60 KIAS. This will provide the greatest altitude gain in the shortest distance.
(steepest angle of climb for short fields with obstruction)
AFTER TAKE OFF
- Auxiliary fuel pump "OFF".
APP
4-5
ZENAIR AIRCRAFT SECTION 4
CH 2000 Trainer NORMAL OPERATIONS
CRUISE RPM
Set 75% power, see page 5-3.
Lower RPM means slower cruise speeds. quieter flying, better fuel economy, lower engine temperatures, and
increased endurance.
PRE LANDING CHECK
Auxiliary Fuel Pump... ALL LL 0 ON
MIXTUre ..... ae RICH
Carburetor heat . . ... LL LL LL LL LL ON
Flaps... . AL LL LL LL As Required
Speeds . ... LL La LL As Required
Harness . . .... LL LL LL LL LL Tight
Lights... A LL LL LL As Required
CROSS WIND LANDING: Approach with one wing low, or use crabbing technique, or a combination
of both. Straighten the aircraft out just before touchdown.
NOTE: Large or full rudder deflection side slip may cause some pitch oscillation at or below normal approach
speeds. This does not affect control of the airplane. Remove pro slip input as required.
MISSED LANDINGS: Apply full power. Maintain 50 KIAS with full flap or 60 KIAS with flap up for best
climb gradient. Continue with circuit pattern. Retract flaps above 50 KIAS, trim at
pattern height. turn downwind then approach etc...
FLAPS UP LANDINGS: APPROACH AT 65 KIAS
AFTER LANDING CHECK
Flaps... LL LL LL LL UP
Lights... LL LL LL As Required
Radiosand Navads . ... о. „As Required
Pitot Heat . 1111111111 LL LL LL LL OFF
SHUT DOWN (Engine)
Magnetos . .. 1111110011 LL LL LL LL Check
Radiosand Navads . ... . ... OFF
External lights... OFF
Auxiharv Fuelpump . .. LL OFF
Михтаге....... 2... PULL/OUT
MAGs. (when propeller stops)... ... 0. OFF
MASTER . LL LL LL OFF
All switches ....... LL LL LL LL OFF
Remove ignition kev when aircraft 1s unattended.
NOTE: The hour-meter counts "engine time" from the moment the master switch 1s tumed on. Do not
forget to tum the master switch off.
TIE DOWN
When the aircraft is not in use, it should be anchored to the tie down rings located under each wing and at
the rear fuselage. Tie the control forward. Make sure the doors are locked on both sides. The optional
canopy cover will minimize dust, or damage to the canopy (and keep curious onlookers out).
NOTE: As the aircraft is not equipped with a "Parking Brake". it 1s important to always tie down the plane
when it 1s not attended.
APP
4 Feb 97 4-6
ZENAIR AIRCRAFT | SECTION 4
CH 2000 Trainer NORMAL OPERATIONS
SPINNING
On airplanes Serial Numbers 20-0022 and subsequent and Serial Numbers 20-0002 through 20-0021
inclusive which have been modified in accordance with Zenair Ltd IPL#RS, intentional spinning has been
approved In this aircraft with wing flaps up, but is prohibited at Center of Gravity positions aft of 420 mm .
(16.5 inches) aft of Datum. A spin can be entered conventionally by applying full rudder in the desired spin
direction and simultaneously applying full aft pitch control at the stall warning speed, maintaining ailerons
at neutral. The aircraft settles into a stabilized spin within the first turn. The spin attitude is steep, with the
pitch attitude 45 to 60 degrees nose down. The spin is generally smooth, but can be slightly oscillatory at
forward CG positions. Each turn takes approximately 2 seconds, for a height loss of 250 feet. Once
stabilized in the spin after the first turn, the spin characteristics do not change for up to six turns if normal
pro-spin controls are maintained. Recovery within 1 1/2 turns can be achieved by applying full rudder
opposite to the spin direction followed immediately by full forward pitch control. At the moment rotation
stops, rudder and control wheel are centralized and the control wheel eased back to recover from the dive.
NOTE:
- More rapid application of spin entry controls at a slightly higher airspeed, or up to full
power for the first turn, may be required for spin entry at forward CG positions.
- Aileron deflection opposite to spin direction or recovery with the control wheel back
could delay spin recovery slightly.
RECOMMENDED SPINNING TECHNIQUE
Check - Maximum aft CG position 420 mm (16.5 inches)
see page 2.5
- Wing flaps up
- No loose articles
- Harness tight
- Clear of controlled airspace, tratfic, built-up areas
- Sufficient altitude
Entry At stall warning or approximately 60 KIAS, apply full rudder in direction
of the desired spin and simultaneously pull control wheel full aft.
Maintain neutral ailerons.
NOTE: At forward CG position use up to full engine power
during the first turn to enhance spin entry. Reduce to
idle after the first tum.
Spin Maintain full rudder in spin direction, full aft control wheel, and neutral ailerons.
Recovery Apply full rudder opposite to spin direction and follow up immediately with full
forward pitch control. When the rotation stops, immediately centralize the rudder
and simultaneously bring the control wheel back to ease out of the ensuing dive.
4-7 29 Aug 96
4
{
cm as
=. менее bay A ar ys pa an
het a a nnn =
+
|
‘
+
3
ame me re ae с
SECTION 5
PERFORMANCE
TABLE OF CONTENTS
Page
General. 1111111011 LL 5-1
Airspeed Calibration ... 1111111111 LL LL LL 5-1
Stall Speed... ... LR LR LL 5-1
Take Off... LL LL 5-2
Chmb...... aa 5-3
Cruise... LL LL LL LL 5-3
Landing Distance... 11111101 LL LL 5-4
Balked Landing ..... LL 5-4
PA AAA A ЛА „М AB
PERFORMANCE CH 2000 Trainer
SECTION 5
PERFORMANCE
GENERAL
All of the required regulatory and complimentary performance information applicable to this aircraft is
provided by this section.- Approved data are indexed APP.
AIRSPEED CALIBRATION
Flapsup | KIAS 40 50 60 70 80 100 120 143
KCAS | 48 51 61 70 79 96 115 139
Flaps down | KIAS 40 50 60 70 80 101
KCAS | 49 52 61 70 79 100
STALL SPEEDS
At 1606 Ibs (730 kg) in KCAS
angle of bank
level 30 deg 45 deg 60 deg
Flaps down 44 47 52 62
Flaps up 48 52 57 68
....At 1606 lbs (750 kg) in KIAS
angle of bank
level 30 deg 45 deg 60 deg
Flaps down 29 42 50 62
Flaps up 36 44 53 68
APP
5-1 7 Арг 95
PEAS ту A Mae DS
ZENAIR AIRCRAFT SECTION 5
CH 2000 Trainer PERFORMANCE
TAKE OFF |
At full power (brake release) flaps up from paved and level runway.
No wind |
Aircraft at 1606 Ibs = 730 kg
Lift off speed = 55 KCAS
Speed at 50 ft = 63 KCAS
Ground roll in meters (100 m = 330 ft )
Pressure ISA ISA ISA Std ISA ISA ISA
altitude ft | Temp. °C | -300C | - 15°C Atm. + 109С | +20°C | +30°С
S.L. 15 290 305 345 370 410 460
2000 11 345 380 420 455 500 560
4000 7 420 470 520 560 620 680
6000 3 510 580 640 700 780 870
8000 -1 620 690 | 780 | 850 960 1100
To clear 50 ft (ground roll included)
Pressure Std Std Std | Std | Siw Std Std
altitude À | Temp. °C | -3090C | - 15°C | Atm. | =10°С | +20°С | +30°C
S.L. 15 395 430 | 465 | 490 520 580
2000 11 470 515 | 560 595 640 700
4000 7 570 620 | 690 735 780 860
6000 3 | 690 770 | 872 940 1000 1100
8000 -1 890 1010 | 1150 1250 1360 1470 ‘
Effect of wind
ground roll 1s distance over 50 ft 1s
for headwind of 10 kts 70% 75%
20 kis 45% 55%
30 kts 25% 30%
of table above of table above
for tailwind up to 10 kts increase distances by 5% for every knot.
—
effect of grass, short mown, hard surface increase the ground roll by approx 20%.
SHORT FIELD TAKE OFF
Same procedure
Note 1: The pilot mav want to lift off at a lower speed depending on aircraft weight and pilot
familiarity with his aircraft.
Note 2: Flaps at intermediate settings will not shorten the take off run, but the rate of climb 1s
deteriorated.
APP
10 Oct 96 | 5-2
SECTION 5
PERFORMANCE
ZENAIR AIRCRAFT
CH 2000 Trainer
CLIMB
Max. Rate of Climb, full power, flaps up, at 1606 lbs (730 kg)
Rate of climb FPM
Pressure Std Vy - Std Std Std Std Std Std
altitude ft | Temp.°C | KCAS - 30°C - 15°C Atm. + 10°C | +20°C | +30°C
S.L. 15 65 910 855 820 800 770 750
2000 11 62 730 750 720 700 680 660
4000 7 60 690 650 615 600 580 560
6000 3 - 58 575 540 510 495 480 465
8000 -1 56 450 430 400 390 380 365
10000 -5 54 340 520 300 290 280 265
Best angle of climb Vy 15s 60 KCAS.
Note - above 3000 ft lean Mixture for maximum RPM
- On a hot day (std +15°C) lean mixture for maximum RPM
CRUISE
Standard atmosphere
Pressure RPM % BHP | TAS US Endurance in
altitude fi Knots gal/Hr Hrs + Min on
27 1/2 US. gal
2800 75.99 6.7 4 Hrs 5 min
2000 2600 65; 95 5.7 4 Hrs 45 min
2400 55 90 49 5 Hrs 30 min
2800 74 102 “65 4 Hrs 10 min
4000 2600 65 97 5.7 4 Hrs 45 min
2400 55 92 4.9 S Hrs 30 min
2800 72 104 6.4 4 Hrs 15 mun
6000 2600 65 100 5.7 4 Hrs 45 mun
2400 55 95 4.9 S Hrs 30 min
2800 70 103 6.2 4 Hrs 25 min
8000 2600 65 101 5.7 4 Hrs 45 min
2400 55 95 4.9 5 Hrs 30 mun
Note: Temperature variations from standard have little (less then 2 %) effect on cruise speed.
At altitude, the correct mixture setting improves endurance.
APP
5-3 10 Oct 96
ZENAIR AIRCRAFT SECTION 3
CH 2000 Trainer PERFORMANCE
LANDING DISTANCE |
Power off, flaps down, maximum braking on paved, level, drv runway.
No wind
At 1606 Ibs (730 kg), speed at 50 ft = 63 KIAS
Pressure total ground roll
altitude ft to clear 50 ft meters
SL. 515 275
2000 535 290 e
4000 560 308 ‘
6000 595 325
8000 640 . 390
( temperature has little effect )
RATE OF CLIMB - FLAPS DOWN - (BALKED LANDING)
The rate of climb with flaps down, full throttle at 1606 ibs (750 kg)
Pressure Std Vy Std Std Std Std Std Std
altitude ft | Temp.”C Kcas - 30% - 1SOC Atm. | +10% | +20% | + 30%
S.L. +15 50 560 530 | 510 495 480 425
2000 RI 50 420 395 380 305 350 300
4000 7 50 270 205 240 230 220 (180)
Best angle of climb Vx 15 48 KCAS at S.L.
Crosswind
The demonstrated takeoff and landing crosswind cumponent is 25 kts..
Noise performance
The aircraft meets ICAO Amex 16 with 71.73 dBA, and FAR 36 appendix G
with 69.2 dBA.
APP
10 Oct 96
.
>
S-4
SECTION 6
WEIGHT AND BALANCE AND EQUIPMENT LIST
TABLE OF CONTENTS
General... aaa
Airplane Weighing Procedure...
Weight and Balance Data and Record
Equipment List (Options)... 111111111100 LL LL
Weight and Balance Determination for Flight
cee esse ae eee eee.
“EE y 2 NEO
SECTION 6 ZENAIR AIRCRAFT
WEIGHT AND BALANCE CH 2000 Trainer
SECTION 6
WEIGHT AND BALANCE
GENERAL
In order to achieve the performance and flying characteristics which are designed into the airplane, it
must be flown with the weight and center of gravity (C.G.) position within the approved operating range
(envelope). Although the airplane offers flexibility of loading, the pilot must insure that the airplane is
loaded within the envelope before attempting to take off.
Misloading carries consequences for any aircraft. An overloaded airplane will not take off, climb or
cruise properly. The heavier the plane is loaded, the less climb pertormance it will have.
Center of gravity 1s a determining factor in flight characteristics. If the C.G. is too far forward in any
airplane, it is difficult to rotate for takeoff or landing. If the C.G. is aft of the approved limit, the airplar.
may rotate prematurely on takeoff or tend to pitch up or down. The aircraft is unstable in pitch. This can
lead to inadvertent stalls and even spins; and spin recovery may become impossible.
A properly loaded airplane, however, will perform as intended. Before the airplane is delivered, 1t 15
weighed, and the corresponding empty weight and C.G. location is computed (the empty weight consists
of the standard empty weight of the airplane plus the optional equipment). Using the empty weight and
C.G. location, the pilot can easily determine the weight and C.G. position for the loaded airplane by -
computing the total weight and moment and then determining whether they are within the approved
envelope. (see fig 2-5)
The empty weight and C.G. location are recorded in the Weight and Balance Record Form (Figure 6-
4). The current values should alwavs be used. Whenever new equipment 1s added or any modification
work 1s done, a new empty weight and C.G. position should be determined and recorded. The owner
should make sure that it 1s done.
A weight and balance calculation is necessary in determining how much fuel or baggage can be
boarded so as to keep within allowable limits. Considering pilot and passenger weight, check calculatio.is
prior to adding fuel or baggage to insure against improper loading
The following pages are forms used in weighing an airplane and in computing the empty weight, C.G.
position, and total weight. Note that the useful load includes fuel, baggage, and passenger.
6-1 3 Apr 95
ZENAIR AIRCRAFT SECTION 6
CH 2000 Trainer WEIGHT AND BALANCE
6.3 AIRPLANE WEIGHING PROCEDURE
Correct empty aircraft weight and C.G. location data 15 presented on page 6-8.
The removal or addition of equipment or airplane modifications may affect basic empty weight and
center of gravity. The following is a weighing procedure to determine this empty weight and center of
gravity location:
Preparation
(1) Be certain that all items checked in the airplane equipment list are installed in the proper
location in the airplane.
(2) Remove dirt, grease, moisture, foreign items such as rags and tools from the
airplane before weighing.
(3) Defuel airplane: Open the fuel drain until all fuel is drained.
CAUTION
Whenever the fuel system is completely drained and fuel 1s re-
plenished, it will be necessary to run the engine for a minimum of
three minutes at 1 000 RPM (on each tank) to insure no air remains
in the fuel supply lines.
(4) Fill with oil to full capacity.
(5) Place pilot and co-pilot seats in rearmost position. Flaps fully up and all control surfaces in
the neutral position. Doors and access panels closed.
(6) Weigh the airplane inside a closed building to prevent errors in scale readings due to wind.
Leveling
(1) With airplane on scales, block main gear.
(2) The horizontal reference is the upper fuselage longeron (door sill)
(3) Level airplane (refer to Figure 6-3) deflating nose wheel tire, to center bubble on level placed
on door sill.
3 Apr 95 6-2
DAFETY AUTHORITY LOAD DATA SHEET
AUSTRALIA
/ Name of Organisation
TMOMSON DESIEN
Aircraft Type
ZENIT CH 2000 Aircraft Reg. VH- <€E7
\ Jpprovec Loading System SECHOM & OF CH2000 OWMELS MANUAL. В
| | >
( Authorised | Date Date of Expiry | Issue
O Ee | 14/2/2000 DEFI TT | .
| —
Empty Alrcraft Weight and Balance
: | ~~
( tem | Weight Arm Index Units | Configuration
| | cers Fo ou
EMPTY WEIGHT | 90853 385-2 17991477 2 SECHS, e
i Empry PLUS
BAScc weEteHr | 509.73 360 13343747 cavsaëlé FUEL
/ |
|
|
|
| |
: | ;
| !
| | |
| | |
| | | |
Remarks
(
Aca; Owl Mga OL
Becomes TUeHT "Avec
y ASIN (A
Approval Stamp
a
Ar
LE
« Nu _
DA 735 (Rev 1/88) Stock No.1'
SECTION 6 ZENAIR AIRCRAFT
WEIGHT AND BALANCE CH 2000 Trainer
Weighing - Airplane Empty Weight
With the airplane level, record the weight shown on each scale. Deduct
the tare, if any from each reading.
Scale Position and Symbol Scale Deduct
| Reading Tare Net Weight
Nose Wheel (N) —
Right Main Wheel (R) R=
Left Main Wheel (L) L=
Empty Weight, (W)=N+R+L | = wee | ee | w=
WEIGHING FORM
Figure 6-1
Empty Weight Center of Gravity
(1) The vertical reference 1s the wing leading edge at rib # 4
(2) The following geometry applies to the CH 2000 airplane when it 1s level.
(3) A plumb line can be used to pick up dimensions from the ground.
(4) Dimensions A and B must be measured! —
| =
LEVEL DOCRSILL =
LEVELING DIAGRAM
Figure 6-3
The empty weight is W=N+ R + L
and the corresponding C.G. 1s positioned at
y - (R:L)xB- NxA_( Y ) - ( YY)
W ( )
6-3 3 Apr 95
ZENAIR AIRCRAFT SECTION 6
CH 2000 Trainer WEIGHT AND BALANCE
NOTE + BASE WEIGHT (S weH FUL OC
AND UNUSABLE FUEL WEIGHT AND BALANCE RECORD
Aircraft Model: CH 2000 Trainer
Serial # 20- 0037
Reoistration 4 V/7 - ZEN
Basic We LS AT |
Emp Wer C.G. Position
kg or-+bs- mm or taches Date Entered by
507-7 0-360 [4/2/2000 Lo Lp Wca Mo. 907583]
The present form is provided to present the current status of the airplane empty weight and a
complete history of previous modifications. Any change to the permanently installed equipment or
modification which affects weight or moment must be entered in the Weight and Balance Record
See equipment list on back
Note: 1 Ib =.464 kg and linch=.0254m
19 July 95 | 6-4
SECTION 6
WEIGHT AND BALANCE
ZENAIR AIRCRAFT
CH 2000 Trainer
EQUIPMENT LIST (OPTIONS)
The following is a list of the optional equipment which may be installed in the CH 2000 Trainer.
This list shows their weight and moment arm.
See latest weight and Center of Gravity sheet with installed equipment.
Item Weight Arm
kg | Ibs m inches
ELT. 1.4 3.2 +1.1 +43
Fire extinguisher + First Aid 5 1.1 0 0
Tow Bar 4 ‚9 +.78 +31
Wheel fairings (set of 3) 5.7 12.5 +2 +8
Propeller Spinner 1 22 -1.05 -41
Vacuum pump 1.2 2.6 -.75 -30
Directional gyro 1.1 2.5 -.15 -6
Artificial horizon 1.2 2.6 -.15 -6
Electric turn and bank 5 1.1 - 15 -6
Rate of climb 3 7 -.15 -6
Cabin light (ea) 3 7 +.75 +30
Landing light (ea) 3 7 +.07 +3
Navigation lights and strobes 5 1.1 +1.9 +75
Strobe power supply 1 2.2 +3. 1 +122
External power plug 4 9 +3.5 +138
Nav. Com. KX155 2.4 5.3 - 28 -11
VOR Dial KI208 4 1.0 -.15 -6
Transponder KT76A 1.4 3.1 -.28 -11
Intercom PM1000II 2 4 -.12 -5
Other Radio (panel mounted) - - -.28 -11
Instruments (panel face) - - -.10 -4
Encoder AK 350 2 4 -.28 -11
Fuel Primer 4 9 -.38 -15
Un
29 Mar 96
PE Rg Te WAR 4
ZENAIR AIRCRAFT SECTION 6
CH 2000 Trainer WEIGHT AND BALANCE
Weight and Balance for Flight
Before each flight, the weight and balance of the loaded airplane should be calculated as follows and checked to fit inside
the approved limits.
Following tables may be used:
1) Empty weight and C.G. position
Use the latest figures from the Weight and Balance record.
2) Fuel in standard rear tank
tity Position
m Ibs.inches
39.4 6620
39.4 4730
49 4 3070
39.4 1180
1.9 | 39.4
Fuel in each wing tank (see e 9-
Gauge tv Position Moment
each tank liters US inches Ibs.inches
1 53 14 . 33 2770
1/2 26 6.8 . 33 1330
0 4 l . 33 ---
Fuel in e rear tank (see page 9-11
tity 1 Position
m Ibs.inches
8400
99 1.04 : 6400
63 1. 4050
1.04 1800
2 . 1.04
Note: 1 U.S. gal fuel = 2.7 kg or 6 lbs. (or 1 liter = .72 kg)
1 m. = 1000 mm.
3) Occupants
Position* Moment*
inches Ibs.inches
16 1600
16 2400
16 3200
16 4000
16 54.4 4800
16 63.6 5600
16 72.4 6400
lbs
45 100
68 150
90 200
115 250
136 300
159 350
181 400
Halle 18
* Note: The exact position of the occupants depends on their geometry (!) and the seat adjustment
(.42 m = 16.5 inches rear to .35 m = 13.5 inches forward).
Above table gives only an average and more accurate results are obtained by using the actual figures.
4 Feb 97 6-6
SECTION 6
WEIGHT AND BALANCE
ZENAIR AIRCRAFT
CH 2000 Trainer
4) Baggage
10
20
30
40
Moment*
Ibs.inches
500
Position*
m inches .m
1.25 50 5.6
1.25 50 11
1.25 50 17
1.25 50 22.5
1000
1500
2000
* Note: Position is 1.25 m or 50 inches when baggage is located in the centre of the baggage area.
Enter the actual figures in a table similar to the following:
Weight Position Moment
kg or lbs m or inches kg.m or Ibs.inches
1) Empty Tes Tas SLI LA +
2) Fuel 7.
3) Occupant
4) Baggage
Total W= M=
(add the
columns)
Loaded Aircraft weight is W = (kg or lbs)
Loaded C.G. position is X y — =
(m or inches)
Check that both W and x fall within the limits on page 6-8.
Note: You may also want to repeat the above calculation corresponding to the aircraft at the end of the
trip, which means with the fuel level as expected at destination.
19 July 95
PE amy Sv Wager
ZENAIR AIRCRAFT SECTION 6
CH 2000 Trainer WEIGHT AND BALANCE
WEIGHT AND C.G. RANGE
XV |
Ka
(Lbs)
700 Kg NX NN
ESS
7
_
ISTo LL
(svete) | eo Ka (175 Lb5>
|
|
S
ce
oor. N Î ote
|
(1320 Lbs) NU
S
SONT
OA
7
A
Z
7.
Loo Ke N | | N
CL ad <
(ESC Las) VS. | N N -
NIN | NX =~
| | | | | | |
320 mm 350 mm 400 mm 420 mm 435 mm ;
(12.6) (13.87) (5.7) (e5) (7.1)
22 °/s HAC 25.1 МАС 27.5% MAC 29% MAC 20% MAC
N
MAC = 145C mm (57 |
| >
(26) 4
|_ 326 mm (Fred)
4 | +35 mm (Rear)
NOTE: Intentional spins prohibited: - (17.17)
- when Centre of Gravity aft of 420 mm (16.5 inches)
- when flaps extended
- on airplanes Serial Numbers 20-0002 through 20-0021 inclusive unless modified in
accordance with Zenair Ltd IPL#RS.
4 Feb 97 6-8
PT RA ANG
бота рен ка
SECTION 7
DESCRIPTION AND OPERATION
OF THE AIRPLANE AND ITS SYSTEMS
TABLE OF CONTENTS
Page
Introduction... LL LL 7-1
The Airplane . . .. LL Le 7-1
Airframe aa но 7-1
Flight Controls. 1112101001 L о 7-3
Engine Controls... .............. LL LL ae 7-3
Instrument Panel... LL 7-5
Landing Gear .......... ....... 7-6
Powerplant and Propeller. ............... Le 7-7
“Fuel System... LL LL 7-8
Electrical System... LL LL 7-10
Pitot-Static System... a 7-11
Heating and Ventilating System
Stall Warning
~FCTION 7 ZENAIR AIRCRAFT
SCRIPTION AND OPERATION CH 2000 Trainer
SECTION 7
DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS
INTRODUCTION
This section provides description and operation of the airplane and its systems. Refer to Section 9,
"Options", for details of optional systems and equipment.
THE AIRPLANE
The CH 2000 Trainer 1s a single-engine, fixed gear, low wing monoplane of all metal construction. It
has two place side by side seating with dual flight controls, and a forty pound baggage capacity.
AIRFRAME
The primary structure, with the exception of the steel tube engine mount, turn over protection, canopy
frame, steel nose gear strut, and isolated areas, 1s of 6061-T6 aluminum sheet metal riveted to aluminum
extrusions with Avex rivets. Composites are used on non structural fairings.
The fuselage is a conventional semi-monocoque structure. Gullwing doors provide easy access from
either side. The baggage area 1s accessible through the cabin.
The wing has a high lift airfoil and Hoerner wing tips to maximize the CH 2000's effective wing span.
The cantilever wings are attached to each side of the fuselage by insertion of the butt ends of the main
spars into a center spar structure which is an integral part of the fuselage. The center spar structure,
located under the seat, provides in effect a continuous main spar with splices at each side of the fuselage.
The fore and aft wing attachments introduce the wing torsion and shear into the fuselage.
7-1 3 Apr 95
SECTION 7
ZENAIR AIRCRAFT
DESCRIPTION AND OPERATION
CH 2000 Trainer
Fuel Primer —— —
CABIN HEAT
CONTROL WHEELS
>
| ~
/ $50
MASTER 7 |
MAG./STARTER |
CARB. HEAT /
MIXTURE (RED)
THROTTLE (BLACK)
TRIM INDICATOR
FLAP CONTROL SWITCH TRIM CONTROL SWITCH
FLAP INDICATOR
INSTRUMENT PANEL CONTROLS
4 Feb 97 7-2
SECTION 7 ZENAIR AIRCRAFT
DESCRIPTION AND OPERATION CH 2000 Trainer
FLIGHT CONTROLS
Dual flight controls are provided as standard equipment. The flight controls actuate the control
surfaces through a cable system.
The horizontal surface (stabilator) 1s of the flying tail design with a trim tab mounted on the trailing
edge. This tab serves the dual function of providing trim control and pitch control forces. The trim tab 1s
actuated by an electric servo, controlled by a rocker switch on the centre console.
The rudder is an all flying rudder and 1s operated by conventional foot pedals.
The ailerons are conventional in design and are operated by turning either control wheel.
The flaps are electrically actuated by a lever switch on the centre console. They are fully covered by
the wing extension. Flap position is monitored by flap position indicator, under the control lever switch.
ENGINE CONTROLS
Engine controls consist of a throttle, a mixture, and a carb. heat "push pull" control. These controls
are located at the lower center of the instrument panel where thev are accessible to both pilot and co-
pilot.
The "Black Handled" throttle control is used to adjust engine RPM. Springs are added to the .
throttle lever arm to ensure that the engine will go to full power if linkages should fail.
The "Red Handled" mixture control is used to adjust the air-to-fuel ratio. The engine 1s shut down
by the placing of the mixture control in the full lean position. In addition, the mixture control has a push
button lock to prevent inadvertent activation of the mixture control. For more information on the leaning
procedure, see the Avco-Lycoming Operator's Manual.
The "Blue Dotted" carburetor heat control has two positions: pull out for ‘ON’, push in for OFF.
7-3 29 Маг 96
SECTION 7
DESCRIPTION AND OPERATION
ZENAIR AIRCRAFT
CH 2000 Trainer
JOLY IAN yHIYL —————
HILIMS MIMI —
XMILSVII LI
HL
S54 AH LT0N+ FOLIE
YI AYNSSFTYd TIO
NOILYOINVN — |
owmanyvy 7 —— |
— KEANE —
SATOULS —
MV —
51575 | IL
в) 4 @
—“
em
Ya yola dY14
339 ‘4 1304/71 110
Y AY РИН ЗУ TIVIS
Mig 1304/105 1YVIS9
UHI HOLOLL ML
NAD SAVE NL
Ваз LHIII NIDQYI
HI1VI A ANY
ON13 SS IJIIY-
YILIH YA
1Y 311 NIdVO
S L10A (4
(140)-— sdHV (9
(AHYL 1118 вс)
эмуля (5
(+ у 1331 40),
ya AM TUNIS Ч
зноб5 334 по (‹
HL Mo (@
‘SS3UJ TION
‘UNH o1íayy YILSATI LIIJIANYLSHI
С О19\У ——
+
HILIAS AY
————— 211/08 YX dJitnd 17304 ‘хпу
VOIS VND VOLVNYZLIV
нэ 11/&5 97313
var YI
HILIMS OLINIYH
HILIMS YILSYH
FJI1LLOANHL
WHOLYDIQNI dvd
YN YILSYH
у Эн TOYLNOD
—
A0 - AT
at
Y 1-71/057 I71.
—- YSINYA MINA
d aroJINYU (140)
—HHYU + HYAL “3 (140)
HOIVDIAN QOFIFASHNY
—— OY4D WVNOILI3F Id (140)
— OULD TVIHOTIYOH (LdO)
—— YOIVDIQHH 03345 IWIILYIA (140)
—— зопуЮ VNNDVA (La0)
MOLVOIONI YILIWILIV
HOUMSG HoIYILRI (140)
(140)
YX I0179
В __— $5YJHOJ DILINDYWY
ANEL
NTP
INSTRUME
4 Feb 97
SECTION 7 ZENAIR AIRCRAFT
DESCRIPTION AND OPERATION CH 2000 Trainer
INSTRUMENT PANEL
The instrument panel (Figure 7-4) 1s designed to accommodate the standard instruments for VFR and
IFR flights, with plenty of room to install the optional avionics and [FR instruments.
Standard instruments include a compass, an airspeed indicator, a tachometer, an altimeter, an ammeter,
an engine cluster. The compass 1s mounted on the dashboard in clear view of the pilot and co-pilot.
Instrument options available for the panel include: vertical speed indicator, attitude gyro, directional
gyro, a turn and slip indicator or turn coordinator, etc... The attitude gyro and directional gyro are
vacuum operated through the use of a vacuum pump (with a vacuum suction gauge) installed on the
engine, while the turn and slip indicator 1s electrically operated.
7.5 3 Apr 95
ZENAIR AIRCRAFT SECTION 7
CH 2000 Trainer DESCRIPTION AND OPERATION
LANDING GEAR
The fixed gear CH 2000 is equipped with 3 - 5.00 x 5 wheels. Single disc hydraulic brake assemblies
are provided on the main gear. |
The nose gear is steerable through a 14 degree arc each side of center by the use of rudder pedals. A
bungee assembly on the nose strut dampens shocks and bumping during taxiing.
The brakes are actuated by toe brake pedals which are attached to the rudder pedals. The master
cylinders are connected to the pedals on the pilot side, and slave cylinders are on the passenger side.
PILOT - a | Passenaer a
SIDE SIDE
BRAKE CYLINDER
29 Mar 96 BRAKE SYSTEM
SECTION 7 ZENAIR AIRCRAFT
DESCRIPTION AND OPERATION CH 2000 Trainer
POWERPLANT AND PROPELLER
The CH 2000 1s powered by a four cylinder direct drive, horizontally opposed engine rated at
116 BHP at 2800 RPM. It is equipped with a starter, a 60 amp 12 volt alternator, shielded ignition
“harness, two magnetos, and fuel pump.
The engine compartment is accessible for inspection by removing the fasteners from the top and
bottom cowling. The engine mount is constructed of steel tubing, and dynafocal attachment is provided
to reduce vibration.
The exhaust system 1s constructed of stainless steel and incorporates dual mufflers with heater shrouds
to supply heated air for the cabin, windshield defroster; and the carburetor deicing system.
The engine 1s air cooled by directing air around the cylinder fins with a good baffling system. Air for
{пе ти ег shrouds 1s also picked up from the nose cowling and carried through duct, to the shrouds.
Heated air enters the carburetor air box through a hose connected to the heater shroud.
A fixed pitch metal propeller 1s installed as standard equipment. The propeller has a 72inch diameter.
The pilot should read and follow the procedures recommended in the Lycoming Operator's Manual for
this engine in order to obtain maximum engine efficiency and time between engine overhauls.
7-7 29 Маг 96
“Ea => OR
ZENAIR AIRCRAFT SECTION 7
CH 2000 Trainer DESCRIPTION AND OPERATION
FUEL SYSTEM
TO SHUT OFF: DEPRESS THE SPRING AND TURN LEFT
FUEL SELECTOR
FUEL SYSTEM
Fuel is stored in one standard rear tank (or in two optional wing tanks, or in one large optional rear
tank.)
The fuel tank selector control is located on the seat panel between the pilot and passenger. It has a
safety lock which has to be pushed down in order to shut off the fuel supply.
An auxiliary electric fuel pump is provided in case of the failure of the engine driven pump. The
electric pump should be ON for all takeoffs and landings (and when switching tanks). The fuel pump
switch is located on the instrument panel.
The fuel drains should be opened daily prior to first flight to check for water or sediment. Each tank
has an individual drain. Check that the drains do not leak after closing them.
The gascolator located near the standard tank drain should also be drained before the first flight of the
day. Refer to page 8-11 for the complete fuel draining procedure.
4 Feb 97 7-8
SECTION 7 ZENAIR AIRCRAFT
DESCRIPTION AND OPERATION CH 2000 Trainer
MECHANICAL FUEL Pump
Po QUANTITY SENDER
FUSELAGE TANK
FILLER CAP
To #4 7
CYLINDER\ 1 E
— _— - — ee J = :
6 AUX] LI ARS — FUEL SELECTOR A GROUNDING PLATE
a ’ 5 _
/ r=
— A
EZ N
a 4, 7
| И
N
>
TS
Se
SP. >
(2
A
=
CA N
6 Qy *
CARBURETOR
GASCO-ATOR
>— SUMP DRAIN
Fuel Quantity and fuel pressure gauges are mounted in a gauge cluster on the instrument panel.
FUEL SYSTEM SCHEMATIC
29 Mar 96
ZENAIR AIRCRAFT SECTION 7
CH 2000 Trainer DESCRIPTION AND OPERATION
ELECTRICAL SYSTEM
The electrical system includes a 14 volt 60 ampere alternator, voltage regulator,
overvoltage relay, battery contacter and a standard 12 volt 35 ampere hour
battery. The batterv is mounted in a vented and drained fiberglass box located at
the rear of the fuselage. with the master switch solenoid just above the battery.
The voltage regulator and overvoltage relay are on the upper left engine side
of the firewall. The master switch and other electrical switches are located on
the instrument panel
WARNING
The optional anti<ollision lights should not be operaung when
flving through cloud, tog or haze, since the reflected light can
produce spatial disorientation. Strobe lights should not be used in
close proximity to the ground such as during taxiing, takeot! or landing.
Standard electrical accessories inciude à starter. an electric fuel pump, an audidie
stall warming indicator. fuel gauge. Amp. and Volt. meter.
The system also provides for such optional electrical accessories as additional
lights and gauges, heated pitot head. and comununication and navigational
equipment.
The master switch is an on /orf toggle switch with a 0A breaker. The alternator
has a 50 À breaker switch. and the пе!а has an orvotf toggle switch. They are
located on the lower lett of the instrument panel.
The ammeter as installed indicates the glectricai load on the alternator In
amperes. With ail the electrical equipment on and the master switch on, the
ammeter wiil indicate the total ampere draw of ail the umits including the bartery.
For exampie. the average conunuous load for night flight with radios on 1s about
30 amperes. This 30 ampere value plus approximately 2 amperes for a fullv
charged battery will appear continuousiy under these flight conditions. The
amount of current shown on the ammeter will teil immediately if the alternator
system 1s operating normally, as the amount of current shown should equal
the total amperage drawn by the electrical equipment which 15 S operating.
The overvoltage relay protects the electronics equipment from a momentary
overvoltage condition (approximately 16.5 volts and up), or a catastrophic
regulator failure.
Dec 98 7-10
SECTION 7 ZENAIR AIRCRAFT
DESCRIPTION AND OPERATION CH 2000 Trainer
PITOT-STATIC SYSTEM
The system supplies both pitot and static pressure for the airspeed indicator, altimeter, and the
optional vertical speed indicator.
Pitot and static pressure are picked up by a pitot head installed on the bottom of the left wing and
carried through pitot and static lines within the wing and fuselage to the gauges on the instrument panel.
To prevent bugs from entering the pitot and static pressure holes, a cover should be placed over the
pitot head, when the aircraft is not in use. A partially or completely blocked pitot head will give erratic
or zero readings on the instruments.
NOTE
During the preflight, check to make sure the pitot cover 1s removed.
ue see ELL Peso
Grana
ue a Ceres
(DY
АС PRE csiyp=)
(sTATIC PRESSURE)
ALTERNATE STAT) Cl
IFR OPTION © ds © ©
PITOT STATIC
( HEATED: IFR OPTION)
PITOT-STATIC SYSTEM
7-11 22 Jul 96
ZENAIR AIRCRAFT SECTION 7
CH 2000 Trainer DESCRIPTION AND OPERATION
HEATING AND VENTILATING SYSTEM
Heat for the cabin interior and the defroster is provided by a shroud attached to the muffler. Heat is
regulated with the control located on the far right side of the instrument panel.
Fresh air is directed into the cabin through the air vents installed in the right and left door windows.
The flow is controlled through rotation.
WARNING: Doors must be closed securely when engine is on: they will fly off when
opened and engine on.
STALL WARNING
An approaching stall is indicated by an audible alarm located under the baggage compartment roof.
The indicator activates at between five to ten knots above stall speed.
29 Mar 96 7-12
— m— Ry
TABLE OF CONTENTS
SECTION 8
AIRPLANE HANDLING, SERVICING AND MAINTENANCE
Page
General . LL LL LL LL 8-1
Airplane Inspection Periods... 0 8-2
Preventative Maintenance . 1111111111 LL 8-3
Airplane Alterations....... о, 3-4
Ground Handling 1111111120 В 8-5
Engine Aur Filter oo LL 8-7
Brake Service 11111101 LL LL LL LR 8-7
Landing Gear Service... 1111111111 LL 3-8
РгореПег Зегу1се....... 2... 8-9
Oil Requirements. 1.111111 11111 LL LL 8-9
Fuel System... LL LL 8-9
Tire Inflation... ....... В 8-11
Battery Service ... 0.) LL LL 8-12
Cleaning . . LL LL LL 8-12
Control Surface Deflections . . ... 8-14
SECTION 8 ZENAIR AIRCRAFT
HANDLING, SERVICING AND MAINTENANCE CH 2000 Trainer
SECTION 8
AIRPLANE HANDLING, SERVICING AND MAINTENANCE
GENERAL
This section provides general guidelines relating to the handling, servicing and maintenance of the
CH 2000 Trainer.
Every owner should stay in close contact with his distributor to obtain the latest information pertaining
to his aircraft and to avail himself of the Aircraft Service Back-up.
In order to allow the owner to get the most efficient use from his/her aircraft and to keep it in the best
mechanical condition, service bulletins and service letters relating to the aircraft are issued from time to
time.
Service Bulletins are of special importance and should be complied with promptly. These are sent to
the latest registered owners and distributors.
Service Letters deal with product improvements and service hints pertaining to the aircraft. They are
sent to the distributors and occasionally (at the factory's discretion) to the latest registered owners, so
they can properly service the aircraft and keep it up to date with the latest changes. Owners should give
careful attention to the Service Letter information.
If an owner is not having his aircraft serviced by an Authorized Service Center, he shouid periodically
check with a distributor to find out the latest information to keep his aircraft up to date.
A Subscription Service for the Service Bulletins and Service Letters is available. This service 1s
offered to interested persons such as owners, pilots and mechanics at a nominal fee, and may be obtained
through the distnbutors.
À service manual, parts catalog, and revisions to both, are available from your distributor. Any
correspondence regarding the airplane should include the airplane model and serial number to ensure
proper response.
8-1 3 Apr 95
E Ty => UU
ZENAIR AIRCRAFT SECTION 8
CH 2000 Trainer HANDLING, SERVICING AND MAINTENANCE
AIRPLANE INSPECTION PERIODS
The official authorities occasionally publish Airworthiness Directives (ADs) that apply to specific
groups of aircraft. They are mandatory changes and are to be complied with within a specified time limit.
When an AD is issued, it is sent to the latest registered owner of the affected aircraft and also to the
subscribers of the service. The owner should periodically check with his distributor or an A € P
mechanic to see whether he has the latest issued AD against his aircraft.
One hundred hour inspections are required by law if the aircraft is used commercially. Otherwise this
inspection is left to the discretion of the owner. This inspection is a complete check of the aircraft and 1ts
systems, and should be accomplished by an Authorized Service Center or by a qualified aircraft and
power plant mechanic who owns or works for a reputable repair shop. The inspection is listed, in detail,
in the inspection report of the appropriate Maintenance Manual.
An annual inspection is required once a year to keep the Airworthiness Certificate in effect. It IS the
same as a 100 hour inspection. This inspection is required whether the aircraft is operated commercially
or for pleasure.
A Progressive Maintenance program is approved by the Authority and 1s available to the owner. lt
involves routine and detailed inspections at 50 hour intervals. The purpose of the program is to allow
maximum utilization of the aircraft, to reduce maintenance inspection cost and to maintain a maximum
standard or continuous airworthiness. Complete details are available from the distributor.
A spectographic analysis of the oil is available from several sources. This system, if used intelligently,
provides a good check of the internal condition of the engine. For this system to be accurate, oil samples
must be sent in at regular intervals, and induction air filters must be cleaned or changed regularly.
3 Apr 95 8-2
SECTION 8 ZENAIR AIRCRAFT
HANDLING, SERVICING AND MAINTENANCE CH 2000 Trainer
PREVENTATIVE MAINTENANCE
The holder of a Private Pilot licence may perform certain preventative maintenance described in the
regulations. This maintenance may be pertormed only on an aircraft which the pilot owns or operates
and which is not used in commercial service. The following is a list of the maintenance which the pilot
may perform:
(a)
(5)
(©)
(а)
(e)
(h)
(1)
(k)
(1)
(m)
(n)
Repair or change tires and tubes.
Service landing gear wheel bearings, such as cleaning, and greasing (bearing replacement not
permitted).
Replace defective safety wire and cotter pins.
Lubrication not requiring disassembly other than removal of non-structural items such as cover
plates, cowling or fairings.
Refinish the exterior or interior of the aircraft (excluding balanced control surfaces) when
removal or disassembly of any primary structure or operating system is not required.
Replace safety belts.
Replace seats or seat parts with replacement parts approved for the aircraft, not involving
disassembly of any primary structure or operating system.
Replace bulbs, reflectors and lenses of position and landing lights.
Replace engine cowling (The two part cowl replacement does not require removal of the
propeller or disconnection of flight controls.)
Replace, clean or set spark plug clearance.
Replace any hose connection, except hydraulic connections, with replacement hoses.
Replace pretabricated fuel lines.
Replace the battery and check fluid level and specific gravity.
Although the above work 1s allowed by law, each individual should make a self analysis as to
whether he has the ability to perform the work.
If the above work is accomplished, an entry must be made in the appropriate logbook. The entry
should contain:
(a)
(b)
(©)
(а)
(e)
The date the work was accomplished.
Description of the work.
Number of hours on the aircraft.
The certificate number of pilot performing the work
Signature of the individual doing the work.
3 Apr 95
ZENAIR AIRCRAFT SECTION 8
CH 2000 Trainer HANDLING, SERVICING AND MAINTENANCE
AIRPLANE ALTERATIONS
If the owner desires to have his aircraft modified, approval for the alteration must be obtained. Major
alterations to the basic airframe or systems require a Supplemental Type Certificate.
The owner or pilot is required to ascertain that the following Aircraft Papers are in order and in the
aircraft.
(a) To be displayed in the aircraft at all times:
(1) Aircraft Airworthiness Certificate
(2) Aircraft Registration Certificate
(3) Aircraft Radio Station License if transmitters are installed.
(b) To be carried in the aircraft at all times:
(1) Aircraft Journey Log.
(2) Owner's manual.
(3) Weight and Balance data (plus a copy of the latest Repair and Alteration Form FAA-337,
if applicable.)
(4) Aircraft equipment list.
Although the aircraft and engine logbooks are not required to be in the aircraft, they should be made
available upon request. Logbooks should be complete and up to date. Good records will reduce
maintenance cost by giving the mechanic information about what has or has not been accomplished.
3 Apr 95 8-4
SECTION 8 ZENAIR AIRCRAFT
HANDLING, SERVICING AND MAINTENANCE CH 2000 Trainer
GROUND HANDLING
(a) By pushing / pulling on the prop near the hub
WARNING: Ignition "OFF"
When Pushing on the wing leading edges, apply hand pressure on the wing rib rivet lines.
WARNING: DO NOT push or lift thru the elevator.
(b) Towing
The airplane may be moved on the ground by the use of the nose wheel steering bar or by
power equipment that will not damage or excessively strain the nose gear steering assembly.
CAUTION
When towing with power equipment, do not turn the nose gear
beyond its steering radius in either direction. as this will result in
damage to the nose gear and steering mechanism.
CAUTION
Do not tow the airplane when the controls are locked.
In the event towing lines are necessary, ropes should be attached to both main gear struts as
high up as possible. Lines should be long enough to clear the nose and/or tail by not
less than fifteen feet, and a qualified person should ride in the pilot's seat to maintain control.
(c) Taxing
Before attempting to taxi the airplane, ground personnel should be instructed and approved
by a qualified person authorized by the owner. Engine starting and shut-down procedures as well
as taxi techniques should be covered. When it is ascertained that the propeller back blast and tax
areas are clear, power should be applied moderately to start the taxi roll, and the following checks
should be performed:
Taxi a few feet forward and apply the brakes to determine their effectiveness.
While taxiing, make slight turns to ascertain the effectiveness of the steering.
Observe wing clearance when taxiing near buildings or other stationary objects. If
possible, station an observer outside the airplane.
When taxiing over uneven ground, avoid holes and ruts.
Do not operate the engine at high RPM when running up or taxiing over ground
containing loose stones, gravel, or any loose material that may cause damage to the
propeller blades.
8-5 3 Apr 95
ZENAIR AIRCRAFT SECTION 8
CH 2000 Trainer HANDLING, SERVICING AND MAINTENANCE
(d) Parking
When parking the airplane, be sure that it is sufficiently protected from adverse weather
conditions and that it presents no danger to other aircraft. When parking the airplane for any
length of time or overnight, it is suggested that 1t be moored securely.
To park the airplane, head it into the wind if possible and use chocks to properly block the
wheels.
(e) Tie Down
The airplane should be tied down for immovability, secunty and protection. The following
procedures should be used for the proper mooring of the airplane:
Head the airplane into the wind if possible.
Retract the flaps.
Block the wheels.
Secure tie-down ropes to the wing tie-down rings and to the tail ring at approximately
45 degree angle to the ground. When using rope of non-synthetic material, leave
sufficient slack to avoid damage to the airplane should the ropes contract.
CAUTION
Use bowline knots, square knots or locked slip knots. Do not use plain slip knots,
NOTE
Additional preparations for high winds include using tie-down ropes from the landing
© gear fork and securing the rudder
Install a pitot head cover if available. Be sure to remove the pitot head cover before
flight.
Cabin doors should be locked when the airplane 1s unattended.
The optional cabin cover will protect the windows trom dust, the interior from ultraviolet
rays, and keep onlookers away!
3 Apr 95 8-6
EES Igy YE Wem ey)
SECTION 8 ZENAIR AIRCRAFT
HANDLING, SERVICING AND MAINTENANCE CH 2000 TRAINER
ENGINE AIR FILTER
The wet type polyurethane foam air filter must be inspected at least once every fifty hours. Under
extremely adverse operating conditions, it may be necessary to inspect the filter more frequently. The
filter 1s disposable and inexpensive and a spare should be kept on hand for a rapid replacement.
(a) Removal of Engine Air Filter
The filter is located in the lower front of the engine compartment and is readily visible for
inspection, and may be removed by the fuilowing procedure:
Remove the upper and lower engine cowling.
Remove the metal screen.
Remove dirty or damaged filter.
(b) Installation Of Engine Air Filter
When replacing the filter, install the new filter and reinstall the metal screen.
BRAKE SERVICE
The brake system is filled with hydraulic fluid MIL-H-5606 (or aero fluid 41). The fluid level should be
checked periodically or at every 50 hour inspection and replenished when necessary.
No adjustment of the brake clearances 1s necessary. If after extended service, brake blocks become
excessively worn, they should be replaced with new segments.
8-7 29 Mar 96
ZENAIR AIRCRAFT SECTION 8
CH 2000 Trainer HANDLING. SERVICING AND MAINTENANCE
LANDING GEAR SERVICE
The main landing gear as well as the nose gear carries 5.00 x 5 wheels. All three tires are four-ply
rating, type III tires with tubes.
Wheels are removed by taking off the (optional fairings). Remove the safety wire and bolts on the
caliper pad, and slide the caliper out. Remove the cotter pin, and knock out the tapered pin. Shde the
wheel assembly off its axle. Mark the tire and wheel for reinstallation; then dismount by deflating the tire,
removing the three through bolts from the wheel and separating the wheel halves. Before re-assembly;
check for side play due to wear, and install shims as required. Repack bearings with grease.
The nose gear bungee should be checked for chaffing, and elasticity.
In jacking the aircraft for landing gear or other service, use a padded sawhorse under the rear fuselage,
and hang the front of the plane off of the engine (ring on crankcase).
3 Apr 95 8-8
SECTION 8 ZENAIR AIRCRAFT
HANDLING, SERVICING AND MAINTENANCE CH 2000 Trainer
PROPELLER SERVICE
The spinner and backing plate should be frequently cleaned and inspected for cracks. Before each
flight the propeller should be inspected for nicks, scratches, and corrosion. If found, they should be
repaired as soon as possible by a rated mechanic, since a nick or scratch causes an area of increased stress
which can lead to serious cracks or the loss of a propeller tip. The back face of the blades should be
painted when necessary with flat black paint to retard glare. To prevent corrosion, the surface should be
cleaned and waxed periodically.
OIL REQUIREMENTS
The oil capacity of the engine is 6 US quarts (5.7 litres), and the minimum safe quantity is 2 US quarts
(2 litres). It is recommended that the oil be changed every 50 hours and sooner under unfavorable
operating conditions. Intervals between oil changes can be increased as much as 100 % on engines
equipped with full flow (cartridge type) oil filters, provided the element 1s replaced each 50 hours of
operation and the specified octane fuel is used. Should fuel other than the specified octane rating for th.
power plant be used, refer to the latest issue of Lycoming Service Letter No. L185 and Lycoming Service
Instruction No. 1014 for additional information and recommended service procedures.
FUEL SYSTEM
(a) Servicing Fuel System
At every 50 hour inspection, the fuel screen in the gascolator and at the carburetor inlet must
be cleaned.
(b) Fuel Requirements
The minimum aviation grade fuel is 100/100 LL. Since the use of lower grades can
cause serious engine damage in a short period of time, the engine warranty is invalidated by the
use of lower octanes and/or mogass.
8-9 15 Dec 95
ZENAIR AIRCRAFT SECTION 8
CH 2000 Trainer HANDLING, SERVICING AND MAINTENANCE
(c) Draining Fuel Strainer, Sumps and Lines
The fuel system sumps and strainer should be drained daily prior to the first flight and
after refueling to avoid the accumulation of contaminants such as water or sediment. Each fuel
tank is equipped with an individual quick drain located at the lower wing surface. The gascolator
is equipped with an individual quick drain located under the fuselage near left wing L.E. Each of
the fuel tank sumps should be drained first. Then the gascolator should be drained with the fuel
selector valve on each individual tank. Each time fuel is drained, sufficient fuel should be allowed
to flow to ensure removal of contaminants. This fuel should be collected in a suitable container,
examined for contaminants, and then discarded.
CAUTION
When draining any amount of fuel, care should be taken to ensure
that no fire hazard exists before starting the engine.
After draining, each quick drain should be checked to make sure it
has closed completely and is not leaking.
3 Apr 95 8-10
SECTION 8 ZENAIR AIRCRAFT
HANDLING, SERVICING AND MAINTENANCE CH 2000 Trainer
(FUSELAGE BOTTOM E FORWARD LEFT WING)
-
}—
- rf —
{ = Е
| + —
TE
== —— SUMP DRAIN
GASCOLATOR [DRAIN
FUEL DRAINS
(d) Draining Fuel System
The bulk of the fuel may be drained from the system by opening the valve(s) at the lower wing
surface (optional wing tanks), or under the fuselage near the left wing L.E. (main tank). The
remaining fuel is drained from the gascolator quick drain with the fuel selector set to each
individual tank. Turn the drain valve stem(s) counter clockwise to hold the drain open.
TIRE INFLATION
For maximum service from the tires, keep them inflated to the proper pressure = 30 psi. All wheels
and tires are balanced before original installation, and the relationship of tire, tube and wheel should be
maintained upon reinstallation. Unbalanced wheels can cause extreme vibration in the landing gear;
therefore, in the installation of new components, it may be necessary to rebalance the wheels with the
tires mounted. When checking tire pressure, examine the tires for wear, cuts, bruises, and slippage.
8-11
pc
Uni
о
®
m
o
(A
ps
ZENAIR AIRCRAFT SECTION 8
CH 2000 TRAINER HANDLING, SERVICING AND MAINTENANCE
BATTERY SERVICE
Access to the 12-volt battery is obtained through the access panel at the rear left fuselage side. The
fiberglass box is strapped down, and secured with AN-3 bolts. The fiberglass box has vent/drain tubes.
The battery should be checked for proper fluid level. DO NOT fill the battery above the baffle plates.
DO NOT fill the battery with acid - use only distilled water. The hydrometer check will determine the
percent of charge in the battery.
If the battery is not up to charge, recharge starting at a 6 amp rate and finishing with a 2 amp rate.
Quick charges are not recommended.
CLEANING
(a) Cleaning Engine Compartment
Before cleaning the engine compartment, place a strip of tape on the magneto vents to prevent
any solvent from entering these units.
Place a large pan under the engine to catch waste.
With the engine cowling removed, spray or brush the engine with solvent or a mixture of
solvent and degreaser may be necessary to brush areas that were sprayed.
CAUTION
Do not spray solvent into the alternator, vacuum pump, starter, or air intakes.
Allow the solvent to remain on the engine trom five to ten minutes. Then rinse the engine
clean with additional solvent and allow 1t to drv.
CAUTION
Do not operate the engine until solvent has evaporated or otherwise been removed.
Remove the protective tape from the magnetos.
Lubricate the controls, bearing surfaces, etc., in accordance with the Lubrication Chart.
29 Mar 96 8-12
NEUN PN SQEES
SECTION 8 ZENAIR AIRCRAFT
HANDLING, SERVICING AND MAINTENANCE CH 2000 Trainer
(b) Cleaning Exterior Surfaces
The airplane should be washed with a mild soap (dishwashing) and water. Harsh abrasives,
alkaline soaps or detergents could make scratches on painted or plastic surfaces or could cause
corrosion of metal. Cover areas where cleaning solution could cause damage. To wash the
airplane, use the following procedure:
Flush away loose dirt with water.
Apply cleaning solution with a soft cloth, a sponge or a soft bristle brush.
To remove exhaust stains, allow the solution to remain on the surface longer.
To remove stubborn oil or grease, use a cloth dampened with naphtha.
Rinse all surfaces thoroughly.
Any good automotive wax may be used to preserve painted surfaces. Soft cleaning cloths
or a chamois should be used to prevent scratches when cleaning or polishing. A heavier
coating of wax on the leading surfaces will reduce the abrasion problems in these areas.
(c) Cleaning Windshield and Windows
Clean only with the special cleaner available from Zenair, to avoid scratches and/or
discolouring, using a woolen cleaning cloth.
CAUTION
Do not use gasoline, alcohol, benzene, carbon tetrachloride, thinner,
acetone, or window cleaning sprays.
CAUTION
Never remove dust with a dry cloth, to avoid scratches.
(d) Cleaning Headliner, Side Panels and Seats
Clean headliner, side panels, and seats with a stiff bristle brush, and vacuum where
necessary.
Soiled upholstery, may be cleaned with a good upholstery cleaner suitable for the material.
Carefully follow the manufacturer's instructions. Avoid soaking or harsh rubbing.
8-13 3 Apr 95
SECTION $ ZENAIR AIRCRAFT
HANDLING, SERVICING AND MAINTENANCE CH 2000 Trainer
The following are the limits within which the control surfaces should deflect:
Ailerons: Neutral in line with flap cover trailing edge
me
Cable Tension 32 lbs + 5
(15 +2 Kg)
TT ~ IST | dea
(SEE 20 A +) K — —
— of
| © [15 | deg
7
Flaps: Neutral when flaps up in wing
Down: 50 + 3° from Neutral
Horizontal tail: Neutral as shown in dwg. (The Fonzontal Tail 1s parallel to the upper fuseizge
—
longeron)
(Nn
Cable Tension 40 lbs +
(18 = 2kg)
Vertical tail: Neutral in line wth the fuseizge
Cable Tension 33 Ibs +5
(15 +2 kg)
| SPINABLE
DA — y AIRCRAFT
LD
S/N 20-0022 AND sUBSEQUENTA
AND §/N 20-0002 TO 20-002!
INCLUSIVE MODIFIED PER
ZENAIR LTD IPL $* RS
FOR NON SPINABLE AIRCRAFT | THE RUDDER.
T DEFLECTIONS ARE 21.5 des. ts (RIGHT oR LEFT)
- CABLE TENSION IS 22 LLs t 5 Cro t 2 ka)
29 Aug 96
TABLE OF CONTENTS
SECTION 9
OPTIONS
BOOK ee ee a ea
BR ee see eee eee
Propeller Spinner
Wheel Fairings
Gyro Option... ........ ..
Fuel System - Wing Tank Option
Schematic of Fuel System... .
Light Option - Extreme Hot and Cold Weather. .
IFR Option...
Limitation Placards tor IFR
IFR Instrument Panel
Large Tank Option ........
Limitation Placards for Large Tank . . ... =
AAA AA
Aaa AE
Page
O
i
`Р
I LU) LY LI IN —
O0
SECTION 9 ZENAIR AIRCRAFT
OPTIONS CH 2000 Trainer
SECTION 9
OPTIONS
GENERAL
This section provides information in the form of Options which are necessary for efficient operation of
the airplane when equipped with one or more of the various optional systems and equipment not provided
with the standard airplane.
All of the Options provided by this section are “Approved” options, and consecutively numbered
as a permanent part of this Manual. The information contained in each Option applies only when the
related equipment is installed in the airplane. No change to limitations or performance is associated with
these options.
9-1 3 Apr 95
ZENAIR AIRCRAFT SECTION 9
CH 2000 Trainer OPTIONS
EMERGENCY LOCATOR TRANSMITTER (ELT)
GENERAL
The E.L.T. consists of a self-contained dual-frequency radio transmitter and battery power supply, and if
ARMED, it is activated by an impact producing a change in velocity of 3.5 ft/sec.or more as may be experienced in
a crash landing. The E.L.T. emits an omni-directional signal on the international distress frequencies of 121.5 and ©
243.0 MHz. General aviation and commercial aircraft, the FAA. and CAP monitor 121.5 MHz, and 243.0 MHz ıs
monitored by the military. Following a crash landing, the E.L. T. will provide line-of-sight transmission up to 100
miles at 10,000 feet. The E.L.T. transmits on both distress frequencies simultaneously at 75 mw rated power
output for 48 continuous hours in the temperature range of -4°F to +131°F (-20°C to +55°C).
The portable E.L.T. unit is mounted on the baggage shelf and is easily accessible for manual activation and /or
removal.
EMERGENCY PROCEDURES
Immediately after a forced landing where emergency assistance is required, the E.L.T. should be utilized as
follows.
1. Ensure EL T. Activation - Turn a radio transceiver ON and select 121.5 MHz. Ifthe EL. T can
be heard transmitting, it was activated by the "g" switch and is functioning properly. If no emergency tone 1S
audible, push the switch to ON.
to
Prior To Sighting Rescue Aircraft - Conserve airplane battery. Do not activate radio transceiver.
A
3. After Sighting Rescue Aircraft - Switch EL T. to OFF, preventing radio interterence. Attempt contact
with rescue aircraft with the radio transceiver set to a frequency of 121.5 MHz. If no contact is established.
push the switch to ON immediately.
4. Following Rescue - Push the switch to ARMED.
NORMAL PROCEDURES (EL TT)
As long as the function selector switch remains in the ARMED position, the E.L.T. automatically activates
following an impact.
Following a lightning strike, or an exceptionally hard landing, the E.L.T. may activate although no emergency
exists. To check vour E.L.T. for inadvertent activation, select 121.5 MHz. on vour radio transceiver and listen for
an emergency tone transmission. If the E.L.T. can be heard transmitting, push the switch to OFF. then to ARMED
for normal operation.
NEVER ACTIVATE the ELT while airborne for any reason.
MAINTENANCE
Refer to the ELT Operation Manual (Battery replacement).
29 Mar 96 9-2
SECTION 9 ZENAIR AIRCRAFT
OPTIONS CH 2000 Trainer
FIRE EXTINGUISHER
The fire extinguisher 1s mounted to the left forward cabin side for easy access. It is to be used and
maintained as per instructions printed on the unit.
TOW BAR
The tow bar is stored behind the forward shelf of the baggage compartment. The hooks are inserted in
the holes (right or left side) and the bar is secured with a quick release clamp. It is used to pull and steer
the aircraft on the ground when the hooks are inserted in the rings provided on the nose gear strut.
PROPELLER SPINNER
The propeller spinner is an option which enhances the look of your aircraft. It has no effect on
performance and/or engine cooling.
WHEEL FAIRINGS
The wheel fairings give a sleek look to your aircraft with no effect on performance. They are made of
a two part fiberglass shell and are easily removed or mounted to their attachment brackets.
Note: In snowy conditions, remove the wheel fairings so that the snow cannot accumulate inside, and
freeze and lock the wheels.
9-3 29 Mar 96
_
ZENAIR AIRCRAFT SECTION 9
CH 2000 Trainer OPTIONS
GYRO OPTION
VACUUM SYSTEM
The vacuum system is designed to operate the air driven gyro instruments. This includes the
directional gyro and artificial horizon when installed. The system consists of an engine driven vacuum
pump, a vacuum regulator, a filter and the necessary plumbing.
VACUUM PUMP
The vacuum pump is a dry type pump. A shear drive protects the pump from damage. If the drive
shears, the gyros will become inoperative.
A vacuum gauge, mounted on the gyro instrument panel provides a pilot check for the system during
operation. A decrease in pressure in a system that remained constant over an extended period may
indicate a dirty filter, dirty screens, possibly a sticky vacuum regulator or leak in the system. Zero
pressure would indicate a sheared pump drive, defective pump, possibly a defective gauge or collapsed
line. In the event of any gauge variation from the norm, the pilot should have a mechanic check the
system to prevent possible damage to the svstem components or eventual failure of the system.
A vacuum regulator is provided in the system to protect the gyros. The valve is set so the normal
vacuum reads 5.0 + 1 inches of mercury, a setting which provides sufficient vacuum to operate all the
gyros at their rated RPM. Higher settings will damage the gyros and with a low setting the gyros will be
unreliable. The regulator is located behind the instrument panel. Vacuum pressure, even though set
correctly, can read lower at very high altitude (above 12,000 ft), and at low engine RPM usually on
approach or during training maneuvers. This is normal and should not be considered a malfunction.
ARTIFICIAL HORIZON |
Gives a visual indication of flight attitude. Bank attitude is presented by a pointer at the top of the
indicator relative to the bank scale which has index marks at 109, 209, 309, 60°, and 909 either side of
the center mark. Pitch and roll attitudes are presented by a miniature airplane superimposed over a
symbolic horizon area divided into two sections by a white horizon bar. The upper "blue sky" area and
the lower "ground" area have arbitrary pitch reference lines useful for pitch attitude control. A knob at
the bottom of the instrument is provided for inflight adjustment of the miniature airplane to the horizon
bar for a more accurate flight attitude indication.
DIRECTIONAL GYRO |
Displays airplane heading on a compass card in relation to a fixed simulated airplane image and index.
The directional indicator will precess slightly over a period of time. Therefore, the compass card should
be set just prior to takeoff, and occasionally re-adjusted on extended flights. A knob on the lower left
edge of the instrument is used to adjust the compass card to correct for any precession.
ELECTRIC TURN AND BANK INDICATOR
Found at the lower left of the instrument panel cluster, directly facing the pilot
3 Apr 95 9-4
ZENAIR AIRCRAFT SECTION 9
CH 2000 Trainer OPTIONS
FUEL SYSTEM
WING TANK OPTION (instead of standard rear tank)
The present page 9.6 and 9.7 replace the pages 7.8 and 7.9 when the wing tank option is
installed.
Placards
- at fuel selector valve: Left Usable Right Usable
and 50 L/13 US gal 50 L/13 US gal
under the fuel gauges:
- Beside the wing tank fillers: Aviation fuel
100/100LL MIN.OCT.
54 L/14 US gal Capacity
The fuel is stored in a Right and Left wing tank , capacity 2 x 53 litres, 2 x 14 US gallons (2 x 50 litres,
2 x 13 US gallons usable).
The fuel tank selector control is located on the seat panel between the pilot and passenger. The handle
points forward Right for right tank, forward Left for left tank. It has a safety lock which has to be pushed
down in order to shut off the fuel supply.
An auxiliary electric fuel pump is provided in case of the failure of the engine driven pump. The
electric pump should be ON for all takeoffs and landings (and when switching tanks). The fuel pump
switch is located on the instrument panel.
The fuel drains should be opened daily prior to first flight to check for water or sediment. Each tan
has an individual drain. Check that the drains do not leak, after closing them.
The gascolator located near the Left wing leading edge under the fuselage, should also be drained
before the first flight of the day. Refer to page 8-11 for the complete fuel draining procedure.
Er,
7
o
ото сие 29 Маг 96
SECTION 9
OPTIONS
ZENAIR AIRCRAFT
CH 2000 Trainer
SCHEMATIC OF FUEL SYSTEM
HOLIYNAYVD
YOLVIOISYO-
HI ха
— — — — —>
MIAN IAD
Nand hog 01
HNVL 134 1431
AIOJINYA 73nd
NS
Là
(7
Y3QNIS IYNSS IMJ 7304 a
dHAd 13nd IVI3(NYHI3W
HNYL 13nd LHD
Ya3aN3S ALILNYND 13N4 4
YIIN YI1M4 -
dV > HNYL 17304
9-6
29 Mar 96
-
SECTION 9 ZENAIR AIRCRAFT
OPTIONS CH 2000 Trainer
LIGHT OPTION
NAVIGATION LIGHTS AND STROBES
Conventional navigation lights are located on the wing tips and the rudder. Strobe lights are also mounted on
the wing tips. ON/OFF switches, found on the instrument panel are labeled (NAV LIGHTS), and (STROBES)
respectively. The switches are ON in the up position.
Strobe lights must be turned off when taxiing in the vicinity of other airplanes, or during night flight through
clouds, fog or haze.
LANDING LIGHTS
Dual landing / taxi lights are mounted in the left wing leading edge. The ON/OFF switch for the landing / taxi
lights 1s found on the instrument panel.
INSTRUMENT LIGHTING
The instrument panel is lighted by 2 spot lights mounted to the cabin ceiling between the occupants” heads. ...e
lights are adjustable directionally and the beam width can be varied. The light intensity can be adjusted and 115
colour changed progressively from white to red. Each unit may be removed from its attachment support for hand
held operation.
COLD WEATHER OPERATION
The “winter baffles” should be installed, if the oil temperature is low during cold weather operation.
With or without “winter baffles”, no oil temperature will be indicated prior to take off if OAT 1s low.
After a suitable warm up of 2 to 3 minutes at 1200 RPM, accelerate the engine several times to higher RPM: if it
accelerates smoothly and the oil pressure remains normal and steadv. it is ready for takeoff.
CAUTION: In order to get rid of the humidity in the oil, the oil temperature should reach at least once during the
dav, 160° F(70° C).
CAUTION: When intending a steady climb to high altitude. the “winter baffles” must be removed when the
weather warms up above OAT of 30°F (0° C).
NOTE: If OAT is oscillating around freezing, the “winter batfles”™ may be left on if the airplane is operated in a
school environment (flying around the pattern, with no prolonged climb). In this case. the oil temperature must be
carefully monitored so as not to exceed 220° F (end of green arc).
(See below how to keep the oil temperature from exceeding the red line.)
EXTREME HOT WEATHER OPERATION
Without the “winter baffles”, up to a Sea Level temperature of 100° F (38°C), the airflow provides proper
engine cooling. If operation above this temperature is required. care must be taken not to overheat the engine. This
1s achieved by:
- minimizing ground warm up
- checking the oil temperature after the full throttle initial climb out: 1f the oil temperature 1s
increasing beyond 220* F (end of Green arc), power must be reduced and/or a faster climb
speed selected (1.e. 70 or 75 KIAS). It is necessary to initiate the corrective action before the
oil reaches the Red line (245* F) as there is a time lag between the engine and oil temperatures.
NOTE: Above procedure is also applicable when the “winter baffles” have not vet been removed for sea level
outside temperature in the 25 to 40°F (-3 to +5*C) range.
CAUTION: When climbing at reduced power or faster speed. the rate of climb 1s reduced.
9-7 4 Feb 97
- >
ZENAIR AIRCRAFT SECTION 9
CH 2000 Trainer OPTIONS
IFR OPTION
The Instrument Flight Rule (I.F.R.) option consists of:
- Night flying (or Light) option (see 9-7),
- Gyro option (see 9-4),
- Outside Air Temperature (OAT) gauge,
- Electically heated pitot static,
- Alternate static source (see 3-4),
- Deicing window in the left cabin door,
- any other national requirements (in particular the electronic communication
and navigation systems).
Following page 9-9 “Limitation placards for IFR”, replaces page 2-4. and page 9-10 “IFR instrument panel”,
replaces page 7-4.
Detailed procedures to check the instruments, navigational aids and radios are given in the operation instruction for
the relevant equipment.
As neither the flying surfaces nor the propeller are equipped with deicing devices. IFR flight into known or forecast
icing conditions 15 prohibited.
However:
1) Should the Airspeed indicator. the altimeter and the rate of climb stop giving information, the pitot static
probe is frozen up. The pitot heat switch is then moved up to "ON". which will melt the accumulated ice.
If this is not effective. the static source switch is moved down to Alternate. This will open the static to the
cabin pressure: Altimeter and rate otf climb will give readings.
With the alternate static, the Altitude must be corrected as tollows:
Alternate static "ON
deicing window closed. subtract 100 tt. rom
cabin heat off or on: indicated altitude
Alternate static “ON”,
deicing window open, subtract 190 ft. trom
cabin heat off or on: indicated altitude
The rate of climb indications are correct.
If the pitot static probe is frozen, the airspeed will not read: Rate of climb and RPM are then the sole
indications to the pilot for an approximation of the speed. If only the static is frozen (not the pitot), and the
alternate static is on, use following indicated airspeeds:
Climb and approach at 83 KIAS
Stall will occur at 33 KIAS (flaps up) and 30 KIAS (flaps down)
(in cruise KIAS = KCAS + 15 kts)
Note: The GPS (Ground Positioning Satellites) speed reading may come in quite handy at this stage.
2) Should the windshield start icing: Pull cabin heat: the left windshield will defrost. If this is ineffective, the
deicing window must be opened and the ice covering the left side of the windshield manually removed. The
deicing window is positioned so that landings can be performed looking through it at the runway and left
edge of the runway,
16 Dec 97 9-8
ZENAIR AIRCRAFT
CH 2000 Trainer
SECTION 9
OPTIONS
LIMITATION PLACARDS FOR IFR (replaces page 2.4)
The tollowing placards are installed (Boxed items for IFR option)
- On the instrument panel
Compass deviation chart
NO SMOKING
MANEUVERING SPEED VA = 108 KIAS
CABIN HEAT PULL ON
THROTTLE PULL CLOSED
Fuel selector: 104 L./27.5 US gal.. DEPRESS. ON. OFF
. Registration
RADIOS
USABLE FUEL
104 L./27.5 US gal.
(for non spmable arrcrail)
eE spinable arrerat)
——— —
DAY AND NIGITI VER OR TER
IN NON-I[CING CONDITIONS,
AEROBATIC MANEUVERS
AND SPINS ARL PROHIDITED
DAY AND NIGHT YTR OR UR
EN NON-ICING CONDITIONS.
AEROBATIC MANEUYERS
AND SPINS
UP TRIM SEE OWNER S MANTENE SEF OWNERS MANUAL
FLAPS
DOWN DOWN
UP
MASTER MASTER CARB FIELD ALTERNATOR ALNILIARY
BREAKER SWITCH L HEAT BRI ARTR FUEL PUMP PKR
ON R BOTH ON ON ON
OFF OFF START OFF OFF Or
OL OIL STARTER TURN & RADIOS PITOT NORMAL
PRESS TEMP. SOLENOID BANK HEAT STATIC SOURCE
ALTERNATE
FUEL FUEL
PRESS. GAUGE
(CPS. VFR USE ONLY *H
FLAPS STALL TRIM CABIN Cor en IFR certitied GPS)
WARN, LIGHT
2 VOIS
LIGHT MIXTURE NAV LAND AND CABIN
MASTER PUSH RICH LIGHT LIGHTS Li PES STROBES LIGHT
BKR BKR Lo BRR KR 'HRR MBER
- Beside the red door handles: OPEN T
+ CLOSED
- Baggage area: 18ke/40 LBS MAX. SOFT ARTICLES ONLY
CHECK WEIGHT AND BALANCE
- Beside tuel tiller: AVIATION FUEL
100/100LL
106 L./28 US gal
- Oil filler cover: OIL 5.7 L. or 6 US gts.
SAE 20W30
- Lett tonward tuselage: FUEL DRAINM
- Rear lett side tusclage: (identification plate) ZENAIR [ID
CH 2000 7 rsemal
MIDLAND ON datos
TABA SEEN ASCII MER Ар НТО |
9-9 16 Вес 97
SECTION 9
ZENAIR AIRCRAFT
CH 2000 Trainer
OPTIONS
м ОГУ ЭН ни Ма.
HOLLIS
У 3 15 \Н
>13 1 Зло -+
FANSSIYS IO
dv 14
YA
y.
Yolo
Vita ———
MIA —
FUN LX
NO VLVIAY /
V4 9 4 1304 / 1 10 9 Hai
YX DNINYIYN Ув
NIE 1304/1058 1YYIS
YH» MHOLQU pIYL —
MAY ANY + NINAL
ANE 11917 HIBYI XAY)
N -
Sa
Vial ‘3 — |
SATONLS _— | /
LHII ‘À 110 — a‘
+ o. _
511515 / И И)
— de /
Мо 1у DIONI
HO LIAS
FILLOHHI
dy 14
dvd
——— HILIMS MNS ана 1304 'XNV
1YaH
fs NOLIMS YXd Yolb Ny 3 LY
/ | M2114S d13H
"YY YI
NHILIMS OLINDYWA
HILIMS NE YILSYH
МЧ наб
133H/MN TOHLNOO
ATA Y ZA |
off Uh Dah Ws a | stas as
pa yr x ns \ NY; J / ~ HILT/AaS HAN
AINV IVA ANY oO о lJ — - — 7 —— 6 HE | ß IM —]— Lv3an LOL!d
Ind "SS 7I9IY —? DT NI _ >,
; OY | —— N > fi LO
‚ f - > | ee I 17. 3
2111 OldYY — AH / A — = —_ TQ) алуы ная
MILI И \ — 9) 7
ON E
a G \ "DIU olav
8 © nl AS VALIHIOHIV
val A — — 4
Vall MIA VI | с « —- Y2HIYd 134
— = >—— d ATOJINYU
y 4 <. — S ..
| a. — C — MNY 4 NWOL ‘ла
bd a | )
0000 SH HOLYDIQNI QFFASHIV
Tr OYLO TVHOILD FMI
SL 10A (4 OYAD VIHOTZIYOM
(1d0)— SAV (9 eee MOLVYDIONT 03345 IYIILYIA
(1 40). 1304 LND HO) (5 F21Y9 WANDVA
Gana 1391 90) (1
У ЯН Ка заса
FYNSSIAS and (€
279 047214 XP — =
5H INVIYA
SOIaY A
od yy —— dI4IL HOla
SSAYd TO U
meee YO LYDIAN
я ЦЗ Нилу
HILLAS INOIYILNI
44%
AOA
мото
SSYJLIOD DILINDVL/
[FR - INSTRUMENT PANEL
9-10
4 Feb 97
ZENAIR AIRCRAFT SECTION 9
CH 2000 Trainer OPTIONS
LARGE FUEL TANK OPTION
The next page (9-12) replaces 2-4 or 9-9.
The large fuel tank, with a usable fuel capacity of 128 liters (33 5 US gal.), simply replaces the standard
tank extending the range of the airplane as given on page 3-3.
NOTE: Special care should be taken to assure the pilot that he is within the limits of the weight and
center of gravity range. (see pages 6-6 and 6-8).
9-11 4 Feb 97
ZENAIR AIRCRAFT
CH 2000 Trainer
SECTION 9
OPTIONS
LIMITATION PLACARDS FOR LARGE FUEL TANK (replaces page 2-4 or 9-9)
The following niacards are installed (Boxed items fer might tlving opticn)
- On the instrument panel:
. Compass deviation chart
. NO SMOKING
DAY VER ONLY
IN NON-ICING CONDITIONS
DAY VFR CNLY
IN NON-ICING CONDITION
AEFROBATIC MANEUVERS AEROBATIC MANEUVERS
CABIN HEAT PULL ON | SEZ CWNER'S MANUAL SEE OWNER'S MANUA:
‚ THROTTLE PULL CLOSE ‘ 4
Fuel selector: 128L/33.5 US gal. DEPRESS, ON, OFF (or with Night Fiving Option) (or for spinable airc=3)
Registration _ _ _ _ _ _ ?
RADICS DAY AND NIGHT VER DAY AND NIGET VFR
USABLE FUEL IN NON-ICING CONDITIONS IN NON-ICING CONDITIONS
128L/33.5 US gal. AEROBATIC MANEUVERS AEROBATIC MANEUVERS
AND SPINS ARE PROHIBITED AND SPINS
UP TRIM SE= OWNER'S MANUAL SE= OWNEX'S MANUAL
FLAP
DOWN DOWN
UP
MASTER MASTER CARB TELD ALTERNATOR AUXILIAR Y
BREAKER SWITCH . HEAT BKR BREAKER FUEL PUMPBKR
ON ON R BOTH ON ON ON
OFF OFF OFF START OFT OFF OFF
OL OIL STARTER TURN & RADIOS
PRESS. TEMP. SCLENOD BANK
FUEL FUEL
PRESS. GAUCE
AUXILIAR Y
FLAP STALL TR CABIN
WARN. LIGHT
Г 1 12 voits
LIGHT MECTURE NAY LAND LAND CABIN |
MASTER PUSH RICH | LIGHT LIGHT LIGHT STROBES LIGHT
BKR KR L. BER KR. BKR BKR BKR
- Besice the red door handles: OPEN T
CLOSED
- Baggage area: 18kg/ 40 LBS MAX. SOFT ARTICLES ONLY
CHECX WEIGHT AND BALANCE
- Beside fuel filler AVIATION FUEL
“100/100LL
130L/34 5 US gal.
- Oil filler cover OIL 5.7L. or 6 US gts.
SAE 20W30
- Le? forward fuselage: FL DRAIN У
- Rear ler nide fuselage: (idenufcation plate) ZENAIR LTD
CH 2000 3(semai”
MIDLAND. ON (ate:
+ Feb 97 TA. SA-185 FAA T.C. 2TASCH MFRAPP, 47294 2-12
ZENAIR AIRCRAFT SECTION 9
CH 2000 Trainer OPTIONS
MECHANICAL TRIM OPTION
When the hand operated mechanical trim option 1s installed, the labels from
pages 2-4, 9-9 and 9-12 are repiaced by following:
| NOSE DOWN
> 14
| NOSE UP
DO
WN
121717)
ELEVATOR TRIM
III NN VI VO
[Е
UP
On page 7-2, 7-3, 7-4 and 9-10 the words “trim switch” are replaced by
“trim control wheel”.
On page 7-3 the words “electric servo” are deleted.
On page 3— the paragraph “electric trim” is deleted
9-13 Dec. 98
(8-2 'sBd)
ey) sejeoipul
NINWYH90Ud O
(0L-Z 'sBd)
ajas e sajedIPul
YHI AHONAN O
1eyo Alowswl
au e USUM —
1ado 3xau aux
Sy] sajedipu| —
AOGNIM A91LS O
} jIYM sIBaddYy
IN! LINSNVEL @
3991 pue Bunqu
lo au) SaIBIIPU]
MOGNIM 3sN 9
»
)
J
|
Le
A
peur
)
y
ve,
a
uf
J
т
©
noun il
(p ‘d) ‘Apjoeup Aouanbay
MOPUIM JS eu) JO UOIDE|ES SMOIIE pue Aouenbe1
MOPUIM AGLS eu) sepiy ‘pjoy pue peysnd USUM —
(y ‘d) ‘esiæa @01A pue Aouenbes; MOPUIM
AGLS 843 Jo} Æouenba:; MOpuiM 3SN ou; sobueyox3 —
[ =>] HOLIMS 39NVHOX3 A9NANDAY4 0
(8-4 ‘d) Buiwweib
-01d jouueys Aiowsw sMOJE 'Pisy pue pauysnd usUM —
(2 -d) ‘Mopum Ag1S ay) ul |suueyd Alowauwl e sjjeday —
[HO] HOLIMS T3INNYHO O
(9 'd) ‘Bunsay
104 Ajjenuew yojenbs au) suedo ‘INO palind uSUM —
(9 ‘d) ‘Joxa| oipne au) sisnipe pue NO Jamod suinj —
TOHINOD FNNTOA BO
(OL-Z 'sBd) :¡euueyo ÁroLISU E sI9ajaS —
(v-€ 'd) “BIP
ZHW | 9u] eBueyo 10U seop qouy siUL 'sdajs ZHY 0G
10 GZ U! Aouenba1; MOPUIM FSN 10 AG1S ay 5эбиецо —
GONH DNINAL T1VNS @
(4 ‘d) ‘Jouueyo
yuejg B SEB jouueyo Aiouieu! pajpajes 8 swe1Do1d —
(01-4 ‘$6а) ‘ечииецо Аошеш е 5129195 —
(v-€ 'sbd) ‘50915
ZHW | ul Aouanbaiy mopuim 3SN 10 AGLS 8yl seBuUeyo —
EONM DONINNL ADHV1 0
©
© ©
-
DOZ2v-1 1S31 HO |
(——) WOO
10d > dio
7 x
o
Lt onan I
Tina 4 HI E
TT
asn
1
Ca!
"=
ww
Da
)
ha
mm
a
Fa
E
-
-
WWO9
N
joued uo. |i
NOLLdIHISZ 7 13NVd | Ни
"OU| WO9|
OOZV—1
HaAIFOSNVHL dANVE HIV dHA |
Y
A
IVANVN NOILONELSNI
">