Zenair STOL CH 701 Specifiche tecniche

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Flight Manual

ZENAIR

STOL CH 701

Serial

number:

Regi tration:

Czech Aircraft Works, Czech Republic

edition. 3 CZ

March 99

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General 2

Limitations

Emergency procedures

Normal procedures

Performance

Weight and balance/equipment list 1

Aircraft and systems description

Aircraft handling, servicing

nrui

maintenance

Supplements

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.

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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.

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Three-view drawing:

30.7”

(780 mm.)

87.5" (2220 mm.) I27FI. 18220mm)

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2. Limitations

his section

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

VNO

VFE

Speed

Never exceed speed

Maximum structural

cruising speed

Manoeuvring speed

Maximum Flap

extended speed

Airspeed indicator markings:

IAS (kt)

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)

Green arc

Yellow arc

Red line

Significance

Positive Flap Operating

Range

Normal Operating Range

Manoeuvres must

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

continuous:

................................................ .77 H P

Maximum Engine RPM, take-off..

..........................

800

continuous

........................

5,,

500

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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

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 -

800

5 800

Oil emDerature

deg.C 50

90- 110 110-

140

Cyl. head temp.

deg.C

150

Fuel (bar)pressure

0.15 0.4

Oil (bar)pressure

1.5

4-5

Weight:

Basic Empty weight.....................................................

760

kg.

Maximum take-off weight ..........................................

450 kg

Maximum landing weight.. .........................................

450 kg

Maximum cockpit weight ..........................................

.190

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

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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

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Limitation placards:

he following limitation placards are placed inside the cockpit:

Never-exceed speed

.......................................................94 kt

Manoeuvring speed

......................................................... 62

Maximum speed for f aps extended

............................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

100

140

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.

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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:

Set airspeed for best rate of Descent 45 kt, flaps up

2. Shut off fuel

3. Shut off engine

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:

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

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

the air.

1. Cabin heat off

2. Fuel off

3. Ignition off

4. Electrics off

Perform an emergency landing

Do not attempt to re tart engine after in-flight fire !!!!!!

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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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