Zenair STOL CH 701 Technische Daten
Flight Manual
ZENAIR
STOL CH 701
Serial
number:
Regi tration:
Czech Aircraft Works, Czech Republic
edition. 3 CZ
-
March 99
1.
General 2
2.
Limitations
4
3.
Emergency procedures
8
4.
Normal procedures
10
5.
Performance
14
.
Weight and balance/equipment list 1
7.
Aircraft and systems description
19
8.
Aircraft handling, servicing
nrui
maintenance
23
9.
Supplements
27
he structure of document was changed according to requirements of BCAR Section S and
changes due to M OW 450 kg with respect to JAR-VLA rules.
1. General
Introduction
he pilot’s handbook has been prepared to provide pilots and instructors with
information for the safe and efficient operation of this UL-aeroplane.
Certification basis
his type of aircraft has been approved by PFA according to British Civil Airworthiness
Requirements CAP 482 Section S Small Light Aeroplanes, Issue 1 including BCAR Paper
S901
proposed amendments.
Descrip
tive
data
CH 701 is a side-by-side two place, strut-braced high wing monoplane with all-metal
structure. CH 701 is a reliable two seat aircraft designed with pilot and passenger comfort in
mind for short-field capability, excellent performance and good visibility. he S OL CH
701 is truly the aircraft which combines the advantages of a conventional aircraft with those
of an advanced Ultralight.
Standard powerplant is Rotax 912, 4-cylinder, 4-stroke, w/ opposed cylinders
Wing span ................................................................ 8,220 mm
Length ......................................................................
6,100 mm
Height.. ..................................................................... 2,350 mm
MAC
........................................................................
1.43 m
Wing area .................................................................
11.33
m.sq.
Wing loading ............................................................ 39.7 kg/m.sq.
Engine ......................................................................
Rotax
912 80 HP
Propeller.. ................................................................. two or three blade composite or wood
Diameter ...................................................................
1700 mm.
Three-view drawing:
30.7”
(780 mm.)
I
87.5" (2220 mm.) I27FI. 18220mm)
2. Limitations
his section
2
includes operating limitations, instrument markings and basic placards
necessary for safe operation of the aeroplane, its engine, standard system and standard
equipment.
Airspeed
Airspeed limitations and their operational significance are shown below:
VNE
r
VNO
VA
VFE
Speed
Never exceed speed
Maximum structural
cruising speed
Manoeuvring speed
Maximum Flap
extended speed
Airspeed indicator markings:
T
IAS (kt)
94
78
6
55
Remarks
Do not exceed this speed in
any operation
Do not exceed this speed
except in smooth and then
only with caution
Do not make full or abrupt
control movement above this
speed, because under certain
condition the aircraft may be
overstressed by full control
movement
Do not exceed this speed with
flaps extended.
Airspeed indicator markings and their colour-code significance are shown below:
Marking
White arc
IAS value or range (kt)
30
-
55
Green arc
34
-
78
Yellow arc
Red line
Significance
Positive Flap Operating
Range
Normal Operating Range
Manoeuvres must
be
conducted with caution and
only in smooth air
Maximum speed for all
operation
Powerplant:
Engine manufacturer.
...................
.
...............................
Rotax
Engine Model:. ............................................................
Rotas 912
Maximum Power, take-off
.......................................... 80
HP
continuous:
................................................ .77 H P
Maximum Engine RPM, take-off..
..........................
5
800
continuous
........................
5,,
500
Maximum Cylinder Head emperature: . . . . . . . 150 deg.C
Maximum Oil temperature. . . . . . . . . . . . . . . . . . . 140 deg. C
Oil Pressure, Minimum. . . . . . . . . . . . . . . . . . . . .
1.5 bar
Maximum . . . . . . .. . . . . . . . . . . . . 5 bar
Fuel Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0. 15 - 0.4 bar
Fuel grade.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Premium grade leaded gas, according to
DlN1600, ONORM C1103 EURO
SUPER ROZ 95 unleaded, according to
DIN51603, ONORM C 1101
Oil grade . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SAE 20 W 50 or SAE 30 High
performance automotive oil API, S6,
Mobil
1,
15
W50,
NO AVIA ION OIL
Propeller manufacturer
Propeller model
Propeller Blade angle
-
see propeller manual
Powerplant instrument markings:
Powerplant instrument markings and their colour code are shown below:
Instrument Red line
Minimum
limit
Green Arc Yellow Arc Red line
Normal operating Caution range Maximum limit
achmeter
500 -5
500 5 500 -
5
800
5 800
Oil emDerature
deg.C 50
90- 110 110-
140
140
Cyl. head temp.
deg.C
150
Fuel (bar)pressure
0.15 0.4
Oil (bar)pressure
1.5
4-5
5
Weight:
Basic Empty weight.....................................................
760
kg.
Maximum take-off weight ..........................................
450 kg
Maximum landing weight.. .........................................
450 kg
Maximum cockpit weight ..........................................
.190
kg
Minimum cockpit weight.. .........................................
.55 kg
Maximum weight in Baggage compartment..
............
.I8 kg
Centre of gravity:
Standard entre of gravity position for empty aircraft is 21.6 % MAC ( 3 10 mm from
reference datum
-
leading edge of slats)
Allowable Range: 20
-
35 % (286 mm to 500 mm)
See section 6 Weight & Balance for details
Approved manoeuvres:
No aerobatics manoeuvres including intentional sppining are approved
Manoeuvring load factors:
Limit load factor: positive 4 negative 2
he ultimate load factors are the limit-load factors multiplied by the safety factor of 1.5
Flight crew:
Minimum number of crew members is 1 and maximum total number of occupants is 2
Kinds of operations:
he aeroplane may be operated in day VFR non-icing condition.
Fuel:
otal capacity:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 litres
Usable fuel
:
. . . . . . . . . . . . . . . . . . . . . . . . . . .
1.5 litres
Unusable fuel
:
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40.5
litres
Approved fuel grades:
. . . . . . . . . . . . . . . . . . . . . . . . . . Premium grade leaded gas, according to
DIN1600,
ONORM Cl 103 EURO
SUPER ROZ 95 unleaded, according to
DlN51603, ONORM C 1101
Limitation placards:
he following limitation placards are placed inside the cockpit:
Never-exceed speed
V
NE
..
.......................................................94 kt
Manoeuvring speed
V
A
..
......................................................... 62
kt
Maximum speed for f aps extended
V
FE
............................55 kt
Maximum Engine RPM,take-off (5 min)
........
5 800
continuous..
.............
5 500
Maximum Cy inder Head Temperature:
.........
150 deg.C
Maximum Oi temperature
.............................
140 deg.C
Maximum oading 18 kg
(40 Ibs)
No oose items
Allowable f el in
litres
baggage weight (kg)
crew weight
(kg) 0 9 18
55 42
42
42
80
42
42 42
100
42
I
42
I
42
140
42
42 42
This aerop ane is c assified as a sma ight
aerop ane approved for day VFR on y, in
non-icing condition. A aerobatics
manoeuvres inc uding intentiona spinning
are prohibited.
3. Emergency proced res
his section provides checklist and amplified procedures for coping with emergencies
that may occur. Emergencies caused by aeroplanes or engine malfunction are extremely
rare if proper preflight inspections and maintenance are practised.
However, should an emergency arise, the basic guidelines described in this section should
be considered and applied to correct the problem.
Emergency landing:
1.
Set airspeed for best rate of Descent 45 kt, flaps up
2. Shut off fuel
3. Shut off engine
4.
ighten seat belts and harness
Avoid tight turns. In some cases, the flaps may be extended before touchdown. Land as usual,
straight ahead power-off approach. Do not try to do any turns
-
the loss of altitude while
gliding is marginal.
Accidental spins:
o recover from a spin:
1.
Pull throttle to idle position
2. push rudder opposite the spin’s rotation
3. bring the pitch control slightly forward.
Fires:
On the ground, before
engine
is started.
1. Go on pushing starter
2. Shut off fuel
3.
Open throttle full as soon as engine starts to blow the fire out
On the ground, engine running.
1. Cabin heat off
2. shut off fuel
3. throttle open to blow fire out
In
the air.
1. Cabin heat off
2. Fuel off
3. Ignition off
4. Electrics off
5.
Perform an emergency landing
Do not attempt to re tart engine after in-flight fire !!!!!!
Fire in cockpit
1. Electrics off
2. Cabin heat off
3. Use fire extinguished
To restart engine in flight (after fuel sfarvafion):
Pull choke before starting and choke in as soon as engine starts.
Note:
Make sure that the aircraft is equipped with a functioning fire extinguisher which is
easily accessible to the pilot. It is recommended to equip the aircraft with an Emergency
Locator ransmitter (EL ) and First Aid Kid.
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