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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

2.8   Centre of gravity

2.9   Approved manoeuvres

2.10   Manoeuvring load factors

2.11   Crew

2.12   Kinds of operation

2.13   Fuel

2.14   Maximum passenger seating

2.15   Other limitations

2.16   Limitation placards

   

2.1  Introduction

Section 2 includes operating limitations, instrument markings and basic placards
necessary for the safe operation of the aircraft, its engine,
standard systems and standard equipment.

 

2.2  Airspeed

Airspeed limitations and their operational significance are shown below:

Speed		IAS		Remarks
		[km/h]	[kts]
V NE	Never exceed speed	270	146	Do not exceed this speed in any operation.
V A	Manoeuvring speed	160	86	Do not make full or abrupt control movement above this speed, because under certain conditions the aircraft may be overstressed by full control movement.
V NO	Maximum structural cruising speed	190	103	Do not exceed this speed except in smooth air, and then only with caution.
V FE	Maximum Flap. Extending speed	125	67	Do not exceed this speed with flaps extended.

 

2.3  Airspeed indicator markings

 Airspeed indicator markings and their colour-code significance are shown below:

Marking	IAS value or range		Significance
	[km/h]	[kts]
White arc	58-125	31-67	Positive Flap Operating Range.
Green arc	75-190	40-103	Normal Operating Range.
Yellow arc	190-270	103-146	Manoeuvres must be conducted with caution and only in smooth air.
Red line	270	146	Maximum speed for all operations.
	58	31	Stall speed in landing configuration (max. extended flaps, engine on idle)

 

2.4  Powerplant

ROTAX 912 UL engine is installed in the aircraft of S/N 2004 2202

Engine Model:			ROTAX 912A (or UL)	ROTAX 912S (or ULS)
Engine Manufacturer:			Bombardier-Rotax GMBH
Power	Max Take-off:		59.6 kW / 80 hp at 5800 rpm, max.5 min.	73.5 kW   / 100 hp at 5800 rpm, max.5 min.
	Max. Continuous:		58 kW / 78 hp at 5500 rpm	69 kW / 93.8 hp at 5500 rpm
	Cruising:		37.7 kW / 50.6 hp at 4800 rpm	44.6 kW / 59.8 hp at 4800 rpm
Engine speed	Max. Take-off:		5800   rpm, max. 5 min.    5500   rpm   4800   rpm   ~1400   rpm
	Max. Continuous:
	Cruising:
	Idling:
Cylinder head temperature:		Minimum:	60 °C    140 °F	60 °C    140 °F
		Maximum:	150 °C    302 °F	135 °C    275 °F
Oil temperature		Minimum:	50 °C    122 °F	50 °C    122 °F
		Maximum:	140 °C    284 °F	130 °C    266 °F
		Optimum:	90 °C - 110 °C    194 - 230°F	90 °C - 110 °C    194 - 230°F
Oil pressure:		Maximum:	7,0 bar
		Minimum:	0,8 bar
		Optimum:	2,0-5,0   bar
Fuel:			see 2.13
Oil:			Automotive engine oil of registered brand with gear additives, but not aircraft oil (refer to engine Operator´s Manual). API classification „SF“ or „SG“.
Propeller and Manufacturer			V 230C VZLÚ Praha , Czech Republic
Type:			two blade fixed wooden propeller
Propeller diameter:			1625 +2 - 3 mm	63.98 +0.008 -0.01 in
Propeller pitch:			18°20´ - 18°55´

 

 Note !

The Woodcomp Klassic 160/3/R propeller is installed in the EV-97 EUROSTAR model 2000 version R of S/N 2004 2202 The Klassic prop is three blade, on ground adjustable. Propeller diameter – 1600 mm

WARNING The Rotax 912 UL has not been certified as an aircraft engine and its failure may occur at any time. The pilot is fully responsible for consequences of such a failure.

          2.5   Powerplant instrument markings

The analogous powerplant instruments are installed in the EV-97 aeroplane
model 2000 version R, with following colour marking

Function		Minimum Limit	Normal Operating	Caution Range	Maximum Range
Engine speed (RPM)		-	1400-5500	5500-5800	5800
Cylinder Head Tempe-rature (CHT)	R 912 UL	60 °C	60- 100 °C	100- 150 °C	150 °C
	R 912 S			100- 135 °C	135 °C
Oil Tempe-rature	R 912 UL		90- 110 °C	50- 90 °C 110- 140 °C	140 °C
	R 912 S			50- 90 °C 110- 130 °C	130 °C
Oil Pressure		0.8 bar	2.0 - 5.0 bar	0.8 – 2.0 bar 5.0 - 7.0 bar	7.0 bar cold engine starting

 

2.6  Miscellaneous instrument markings

Fuel gauge. A fuel reserve is NOT indicated on this aeroplane.

2.7  Weight

Empty weight (standard equipment)   .......... 275 kg ± 3 %    606 lbs ± 3 %

          Actual empty weight is stated in SECTION 6, Weight & Balance

Max. take-off weight   ........................................ 450   kg    992   lbs

Max landing weight   .......................................... 450   kg    992   lbs

Max. weight of fuel   ............................................ 47   kg     104   lbs

Max.baggage weight   ......................................... 15   kg       33   lbs

2.8  Centre of gravity

Empty aircraft C.G. position (standard)   ..... 18±2   % MAC

Operating C.G. range   ..............................20-34   % MAC

2.9  Approved manoeuvres

Aeroplane Category: Normal

The EV-97 „EUROSTAR“ model 2003 aeroplane is approved for
normal and below listed manoeuvres:

•  Steep turns not exceeding 60° bank

•  Lazy eights

•  Chandelles

•  Stalls (except whip stalls)

Warning

Aerobatics and intentional spins are prohibited !

2.10  Manoeuvring load factors

2.11  Crew

Minimum crew   .......................................................... 1

Minimum crew weight   ..............................    55 kg   ... 121 lb

Maximum crew weight   ................................. see 6.2

Warning

Abide with max. take-off weight 450 kg ( 992 lb )! 

2.12  Kinds of operation

There are permitted day VFR flights only.

Warning
IFR flights and flights under icing conditions are PROHIBITED!

Instruments and equipment for VFR flights:

1 Airspeed indicator (marked according to 0.3 )

1 Altimeter

1 Vertical speed indicator

1 Magnetic compass

1 Bank indicator

2 Safety harnesses

2.13  Fuel

•  automotive premium grade petrol, leaded, according to DIN 516000

•  EUROSUPER RON 95 unleaded accord. to DIN 51607,Ö-NORM 1100

•  AVGAS 100 LL

Due to higher lead content in AVGAS, the wear of valve seats and deposits
in the combustion chamber will increase.
Therefore, use AVGAS only if other fuel types are not available.

For other suitable fuel types refer to the engine Operator´s Manual.

Fuel tank volume   ................................... 65 L     17.2   USgals

Unusable fuel quantity   ............................ 2.9 L    0.77   USgals

2.14  Maximum passenger seating

           Number of seats ......................................................... 2   

2.15  Other limitations

No smoking onboard the aeroplane.

2.16  Limitation placards

The owner (aircraft operating agency) of this aeroplane is responsible for the
readability of placards during the aircraft service life.

The values stated on the placard “LOAD LIMITS,“ are valid for the empty weight of the aircraft
with standard equipment installed. The placard with values valid for the actual empty weight
of the aircraft will be placed in the cockpit.