Zenith STOL CH750 Technical specifications

Issued: 01.02.2020 Revision 0, Dat. 01.02.2020 AFM20200201
AFM
AIRPLANE FLIGHT MANUAL
ZENITH STOL CH 750
Serial number: 75-8316
Registration: HB-YRC

Zenith STOL CH 750 Airplane Flight Manual HB-YRC
Issued: 01.02.2020 Revision 0, Dat. 01.02.2020 Page 2-93
Airplane
Designer & Kit Manufacturer: ... Zenith Aircraft Company
Type: ...…………………………..... STOL CH 750
Builder: …………………………... Michel Ruf
Serial No: …………………………. 75-8316
Registration: …………………….. HB-YRC
The builder / owner is responsible for the appropriate correctness of the
content of this manual
Date of Issue: 01.02.2020
The Builder: Michel Ruf Signature:
Approval of Section 2 and Agreement of Sections 1, 6, 7 and 8 by EAS on
behalf of FOCA:
Date:
Name:
Stamp and Signature:
Partial approval (pages …) of Section 5 and agreement of sections 3, 4
by EAS on behalf of FOCA:
Date:
Name:
Stamp and Signature:
Final approval by EAS Certification:
Date:
Name:
Stamp and Signature:
This aeroplane is to be operated in compliance with information and
limitations contained herein.

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0.1 RECORD OF REVISIONS
Any revision of the present manual, except actual weight record, must be
recorded in the following table and in case of agreed sections endorsed by the
EAS.
The new or amended text in the revised pages will be indicated by a black
vertical line in the left hand margin, and the revision no. and the date will be
shown in the footer at the bottom of the page.
Rev.
No.
Affected
Section
Affected
Pages
Date
Approval
Date
Date
Inserted
Signature
0
First
Issue
First
Issue
01.02.2020

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0.2 TABLE OF CONTENTS
GENERAL Section 1 Page 6-10
LIMITATIONS Section 2 Page 11-23
EMERCENCY PROCEDURES Section 3 Page 24-35
NORMAL PROCEDURES Section 4 Page 36-49
PERFORMANCE Section 5 Page 50-57
WEIGHT AND BALANCE / EQUIPMENT Section 6 Page 58-66
LIST
AIRCRAFT AND SYSTEMS DESCRIPTION Section 7 Page 67-85
ARCRAFT HANDLING, SERVICE & Section 8 Page 86-90
MAINTENANCE
SUPPLEMENTS Section 9 Page 90-93

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1. GENERAL
1.1 INTRODUCTION
1.2 CERTIFICATION BASIS
1.3 WARNINGS, CAUTIONS & NOTES
1.4 DESCRIPTIVE DATA
1.5 THREE-VIEW DRAWING

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1.1 INTRODUCTION
The aeroplane Flight Manual has been prepared to provide pilots and instructors
with information for the safe and efficient operation of this homebuilt airplane.
This manual includes the material required to be furnished to the pilot of
homebuilt airplanes. It may also contain references or supplemental data,
supplied by the equipment manufacturers.
1.2 CERTIFICATION BASIS
This type of aircraft is not certified in accordance with published Standard
Airworthiness Requirements.
It is authorized for flight in accordance with FOCA regulation MZ-275.001 in the
special category homebuilt.
1.3 WARNINGS, CAUTIONS AND NOTES
The following definitions apply to warnings, cautions and notes used in the flight
manual.
NOTE:draws the attention to any special item not directly
related to safety but which is important or unusual.
CAUTION:means that the non-observation of the
corresponding procedure leads to a minor or to a more or less
long term degradation of the flight safety.
WARNING:means that the non-observation of the
corresponding procedure leads to an immediate or important
degradation of the flight safety.

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1.4 DESCRIPTIVE DATA
Kind of Airplane:
Side by side 2 place, bubble doors, single engine, high wing with struts, sheet
aluminum with blind and solid rivets, airplane
The landing gear is of conventional three gear design. Leas spring main gear
with independent hydraulic brakes and a steerable nose wheel.
The airplane is equipped with a 100hp Rotax 912 ULS engine turning a
ground adjustable 3-blade Warp-Drive propeller.
Specifications:
Wing Span ....................................................................................... 9.1 m
Wing Area .....................................................................................13.4 m2
Wing Chord ..................................................................................... 1.5 m
Horizontal Tail Span ........................................................................ 2.6 m
Horizontal Tail Area ........................................................................2.0 m2
Maximum Height (Rudder Tip)......................................................... 2.6 m
Length .............................................................................................. 6.7 m
Wheel Span (track) ......................................................................... 1.8 m
Maximum Take-Off Weight (MTOW): ............................................600 kg
Empty Weight..................................................................................360 kg
Useful Load………………………………………………… ................240 kg
Baggage Capacity (maximum) .........................................................18 kg
Wing Loading, Gross ............................................................... 26.8 kg/m2
Seats ........................................................................................................2
Tire Size
Main Gear...................................... 8.00 –6 in, 4 PLY, Max 20 psi
Nose Wheel .................................. 8.00 –6 in, 4 PLY, Max 20 psi

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DESCRIPTIVE DATA (CNTD)
Structural Limit Loads Clean
Positive .............................................................................+4.00 G
Negative ............................................................................-2.00 G
Structural Limit Loads Full Flaps
Positive .............................................................................+2.00 G
Negative ............................................................................-0.00 G

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1.5 THREE-VIEW DRAWING

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2. LIMITATIONS
2.1. INTRODUCTION
2.2. AIRSPEED
2.3. AIRSPEED INDICATOR MARKINGS
2.4. POWERPLANT
2.5 POWERPLANT INSTRUMENT MARKINGS
2.6 MISCELLANEOUS INSTRUMENT MARKINGS
2.7. WEIGHT LIMITS
2.8. CENTER OF GRAVITY
2.9. APPROVED MANEUVERS
2.10 MANEUVERING LOAD FACTORS
2.11 FLIGHT CREW
2.12 KINDS OF OPERATION
2.13 FUEL
2.14 MAXIMUM PASSENGER SEATING
2.15 OTHER LIMITATIONS
2.16 PLACARDS

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2.1 INTRODUCTION
Section 2 includes operating limitations, instrument markings, and basic
placards necessary for safe operation of the aircraft, its engine, standard
systems and standard equipment.
The limitations included in this section have been approved by EAS, on behalf
of FOCA.
2.2 AIRSPEED
Airspeed limitations and their operational significance are shown below
Speed
MPH IAS
Remarks
VS0
Stall speed with flaps
43
Flaps full extended (PWR Off)
VS
Stall speed clean
45
(PWR Off)
VX
Best angle of climb speed
60
Flaps 0 –½
VY
Best rate of climb speed
62
Flaps Up
VFE
Maximum flap extended speed
75
Do not exceed this speed with
flaps extended
VA
Maneuvering speed
80
Do not make full or abrupt
control movement above this
speed, because under certain
conditions the aircraft may be
overstressed by full control
movement
VNO
Maximum structural cruising
speed
100
Do not exceed this speed
except in smooth air, and then
only with caution
VNE
Never exceed speed (glide or
dive, smooth air)
125
Do not exceed this speed in
any operation
Caution: - 2 mph / 1000 ft
Best rate of descent
60
Flaps Down
Best angle of glide
67
Flaps up

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Airspeed for normal field length and STOL conditions
2.3 AIRSPEED INDICATOR MARKINGS
Airspeed Indicator markings and their color-code significance are shown
below.
Markings
MPH IAS
Significance
White
arc
43 –75
Positive full flap operating range.
Green
arc
45 –100
Normal operating range.
Blue
Line
80
Maneuvering speed.
Yellow
arc
100 - 125
Maneuvers must be conducted with caution and only
in smooth air.
Red
Line
125
Maximum speed for all operations.
Take off normal field length
55
Flaps Up
Take off short field
55
Flaps middle position
Landing final approach normal field
length
55 - 60
Flaps ½ and 2000 RPM
Landing final approach short field
55 - 60
No Throttle, Flaps Full Down on
short final
(Leads to a very steep approach)
Caution: Hard landing possible
Best rate of descent
60
Flaps Down and 2000 RPM (to
prevent too much engine cooling)
Best angle of glide
67
Flaps up

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2.4 POWER PLANT
Engine Manufacturer........................................................................Rotax
Engine Type ............................................................................ 912 ULS 2
Engine performance (ISA Conditions):
Maximum Power Take-off (max. 5 min.).......................100 HP / 73.5 kW
Maximum Power Continuous..........................................94 HP / 69.0 kW
Maximum RPM Take-off (max. 5 min.)....................................5’800 RPM
Maximum RPM Continuous .....................................................5’500 RPM
Engine operating limits:
RPM
Take-off.............................................. 5’800 RPM (max. 5 min.)
Maximum Continuous...............................................5’500 RPM
75 %..........................................................................5’000 RPM
Idle…………..............................................................1’400 RPM
Oil Pressure
Max. Oil Pressure..............................................................7 bar
Normal Oil Pressure ......................2.0 –5.0 bar (> 3’500 RPM)
Min. Oil Pressure....................................0.8 bar (< 3’500 RPM)
Attention: For a short period admissible at cold start
Min. Oil Pressure............................ 0.8 bar (below 3’500 RPM)
Max. Cooling Water Temperature (Cyl. 2 + 3)................. 120°C
Oil Temperature
Max. Oil Temperature...................................................... 130°C
Normal Oil Temperature.........................................90° –110°C
Min. Oil Temperature......................................................... 50°C

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POWERPLANT cntd
EGT
Max. EGT......................................................................... 880°C
Operating Temperature
Max. Engine Start............................... + 50°C (Ambient Temp.)
Min. Engine Start..........................................- 25°C (Oil Temp.)
Fuel Grade: Unleaded fuel min RON 95, MOGAS EN228 super,
EN228 Super Plus, UL 91 AVGAS or AVGAS 100LL
Oil Grade: Use only Oil with RON 424 classification. API SG 15W-
40 / AeroShell Sport Plus4 SAE 10W40
For latest information concerning suitable lubricants
refer to SL-912-016
Oil consumption max. 0.06 l / hour
Coolant: Conventional coolant on ethylene glycol basis, 50:50
water mix
Use of water free coolant (i.e. Evans) is prohibited
Propeller Manufacturer and Model:
Warp-Drive, 3-blade ground adjustable, Metal LE, Dia. 177.8 cm (70”)
Adjustable blade angle: 11.5°

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2.5 POWERPLANT INSTRUMENT MARKINGS
Power plant instrument markings and their color code significance are shown
below
Instru-
ment
Red arc/bar
lower
prohibited
range
Yellow arc
caution
range
Green arc
normal
operating
range
Yellow arc
caution
range
Red arc/bar
Upper
prohibited
range
Engine
RPM
-
-
1’400 - 5’500
RPM
5’500 - 5’800
RPM
> 5’800
RPM
Oil
Pressure
< 0.8 bar
0.8 –2.0 bar
2.0 –5.0 bar
5.0 –7.0 bar
> 7.0 bar
Oil
Temp
< 50°C
50-90°C
90-110°C
110-130°C
> 130°C
Cooling
Temp
50-100°C
100-120°C
> 120°C
EGT
> 880°C
Fuel
Pressure
< 0.15 bar
0.15–0.4 bar
> 0.4 bar
2.6 MISCELLANEOUS INSTRUMENT MARKINGS
Instru-
ment
Red arc/bar
lower
prohibited
range
Yellow arc
caution
range
Green arc
normal
operating
range
Yellow arc
caution
range
Red arc/bar
Upper
prohibited
range
Voltage
< 12 VDC
12 –13 VDC
13 –15 VDC
15 –16 VDC
> 16 VDC
Ammeter
-
-
0 –11 A
12 - 17 A
> 19 A

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2.7 WEIGHT LIMITS
Maximum Take-off Weight.............................................................600 Kg
Maximum Landing Weight..............................................................600 Kg
Maximum Weight in Baggage Compartment...................................18 Kg
2.8 CENTER OF GRAVITY
Datum Reference Wing leading edge
Mean Aerodynamic Cord (MAC) 1480 mm (+/- 15) mm
Maximum Forward Station MAC 19 % / 280 mm
Maximum Aft Station MAC 34 % / 500 mm
See Section 6 “Weight & Balance” for further information.
2.9 APPROVED MANEUVERS
This airplane is accepted for flights as per the Normal Category. Intentional
spins and aerobatics maneuvers are prohibited.
2.10 MANEUVERING LOAD FACTORS
Flight load limits Flaps up Positive + 4.0 G
Negative - 2.0 G
Flaps extended Positive + 2.0 G
Negative - 0.0 G
2.11 FLIGHT CREW
1 Pilot
2.12 KIND OF OPERATION
VFR day operation only

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2.13 FUEL
Tank capacity:
Left Wing Tank.....................................................................45 l / 12 USG
Right Wing Tank...................................................................45 l / 12 USG
Total Fuel .............................................................................90 l / 24 USG
Usable Fuel....................................................... 40 l / 10.5 USG per Tank
Unusable Fuel....................................................... 5 l / 1.5 USG per Tank
Approved Fuel Grades:
- Unleaded min RON 95
- MOGAS EN228 Super, EN228 Super Plus
- AVGAS 100LL
- UL 91 AVGAS
2.14 MAX PASSENGER SEATING
1 Passenger
2.15 OTHER LIMITATIONS
Service Ceiling: 14’000 feet
2.16 PLACARDS
Various placards are placed in the cabin and outside of the aircraft and engine
compartment.
Outside:
1. HOMEBUILT on each side of aircraft
2. HB-YRC left side below HS, identification plate
3. FUEL CAPACITY 45 L / 12 USG AVGAS 100LL / UL 91 / MOGAS
EN 228 MIN RON 95 at each fuel cap
4. OIL GRADE API SJ/CF EAVVA C52 AIRMAX on oil door

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PLACARDS (ctnd)
5. 38 psi / 2 bar at left and right main gear
6. STATIC PORT on each side of aircraft
7. DRAIN VALVE at bottom of aircraft and bottom of each wing
8. TEMP SENSOR at bottom of aircraft
Panel:
1. HB-YRC center panel
2. This aircraft has been issued a PERMIT TO FLY in the special
category, subcategory HOMEBUILT. It complies only partially
with internationally agreed standards right side panel
3. No AEROBATIC maneuvers including spin
Operational Limitation: VFR DAY only horizontal top bar
4. THROTTLE PULL TO CLOSE lower left and right side panel
5. < CHOKE PULL TO ON lower left side panel
6. CARB HEAT PULL TO ON center left side panel
7. Switches
MASTER ALT / BAT
---------- OFF ----------
center left side panel
FLAPS UP
DOWN
center left side panel

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PLACARDS (ctnd)
FUEL PUMP / ESSENTIAL BUS / AUTO PILOT
------------------------- OFF -------------------------------
center left side panel
8. Breaker Switches
LIGHTS
STROBE / NAV / LANDING
--------------- OFF --------------
center left side panel
9. Indicator Lights
ALTERNATOR WARNING upper left side panel
EFIS / EMS WARNING upper left side panel
10. Circuit Breakers
OVER VOLTAGE center right side panel
ALTERNATOR center right side panel
11. Speeds in MPH IAS
VNE 125 mph –2mph / 1000 ft
VA 80 mph / Best Glide 67 mph
Vx 60 mph / Vy 62 mph
Vr 45 mph / Vref 60 mph
Under EFIS
12. Compass correction card left side of compass