Light amphibian
Be–103
General information on the Be –103 amphibian
• The Be-103 amphibious airplane is an aircraft of normal category and intended for
passengers and cargo transportation to the areas that are hardly to be reached by other
transport systems — with a number of water areas. The airplane is able to perform the VFR
flights day & night.
• The Be-103 amphibian is a low-wing monoplane, monoplane with a draught wing provided
with a root rib extension, with all-moving horizontal tail and tricycle landing gear with nose
wheel. There are fixed slats arranged on the leading edge of the wings at the area of the
ailerons. Implementation of the concept with draught wing providing capability of aquaplaning
on three points (step, LH and RH wings trailing edges) gives a considerable advantages in
stability on water and seaworthiness.
02
Cut-away view
03
General information on the Be –103 amphibian
• The airplane is equipped with two TCM IO–360ES4 piston engines, certified by FAA, Type
Certificate E1CE. The engines with power of 210 h.p. each are installed on the pylons from
both sides of the fuselage aft and above rear part of the wing center section. Such a
configuration prevents water strikes to propellers while taking off and landing on water.
• Airframe design, layout, equipment and systems installed on the airplane meet the
requirements of Part 23 of Russian Aviation Regulations for the airplanes of normal category
and the Be–103 Certification basis, that considers amphibian operation features.
04
Certification
The Be-103 has been certified under the
AP-23 Russian Airworthiness norms for
VFR flights:
• The Type Certificate ST204–Bе–103;
• The Supplemental Type Certificate No.
SТ204–Bе–103/D1;
• The Supplemental Type Certificate No.
SТ204–Bе–103/D2;
• The Supplemental Type Certificate No.
ST204-Be-103/D3
• The Supplemental Type Certificate No.
ST204-Be-103/D4
• The Type Certificate No. SSh 126–Bе–
103 to meet the noise requirements.
The FAA Type Certificate No.A55CE for
IFR flight operations under the FAR-23
(USA) norms was issued on July 11,
2003.
The CTA Type Certificate No.2005T15
under the RBHA-23 (Brazil) norms was
issued on August 03, 2005.
The CAAC Validation of Type Certificate
No.VTC173A under the China norms was
issued on December 22, 2005.
Now the aircraft is in the process of
certification in Europe and Canada.
Production
The Certificate No. ОP 62-PVS on
Approval of the Be-103 Production at
KnAAPO was issued by the Aviation
Register of the Interstate Aviation
Committee on March 25, 2003. It was
valid till June 25, 2005.
New certificate, valid till May 31, 2007,
was issued on May 31, 2005.
In May, 2003 the Production approval
was issued by USA aviation authorities,
and in April, 2005 – by Brazil aviation
authorities (CTA).
06
The Be-103 program development
Receiving of the
Type Certificate
26.12.2001
First flight
15.07.1997
Certification flight and
life-time tests
Manufacture of
experimental
aircraft
1995
Receiving of the Type
Certificate under IFR, in
the mid 2003
Aircraft deliveries to the customers
Production
Certification
1997
Manufacture of the
experimental aircraft
1999
2001
2003
2005
2017
Certification, flight and
life-time tests
Production Certification
First flight for
certification under FAR.23
in the mid 1999
Aircraft deliveries to the
foreign customers
Receiving of the Type Certificate
under FAR.23
May, 2003 – mid 2004
Main Suppliers
VARTA (Germany)
EMERGENCY
ELECTRIC SYSTEM
TELEDYNE CONTINENTAL MOTORS (USA)
ENGINE AND ELECTRIC GENERATOR
MT-PROPELLER GmbH (Germany)
PROPELLER
MICHELIN (France)
TIRES and WHEELS
ADAMS AVIATION SUPPLY COMP. (UK)
NAVIGATION LIGHTS AND RESCUE
EQUIPMENT
GOODRICH (USA)
POWERPLANT ICE
PROTECTION SYSTEM
BENDIX/KING (USA)
AVIONICS
Hawker GmbH (Germany)
PUMPS of HYDRAULIC
SYSTEM
«NAUKA-VOSTOK» (Russia)
HEATING AND VENTILATION
SYSTEM
Juhostroj (Czechia) и
PARKER HANNIFIN CORP. (USA)
FUEL PUMP
TEKhPRIBOR (Russia)
FUEL RESERVE MEASURING
SYSTEM
SCHROTH SAFETY PRODUCTS GmbH (Germany)
SEAT BELTS
«TOPAZ» (Russia)
FLIGHT DATA RECORDING
SYSTEM
07
Westberg (USA)
INDICATORS and SENSORS
SEGPO and KBE (Russia)
NAVIGATION LIGHTS
ELEKTROAVTOMATIK (Russia)
ELECTRIC SYSTEM
Deliveries
The first three Be–103 amphibians
had been delivered to Sky Manor
Airport (Pittstown, New Jersey, USA)
on August, 2003.
Since 2004 two Be-103 aircraft are
operated by KnAAPO Airlines. In
2005 two aircraft were delivered in
Beriev TANTK.
At the present moment 40 Be-103
aircraft are in production for delivery
in 2006-2007 to customers from
China, Cyprus and Brazil.
08
12,3 ft
General view of the Be –103 amphibious aircraft
35,6 ft
41,7 ft
09
Weights
10
• Maximum taxi weight, kg (lb.)
2280
(5022)
• Maximum take-off weight, kg (lb.)
2270
(4998)
• Maximum useful load, kg (lb.)
420
(926)
• Max. weight without fuel, kg (lb.)
2219
(4888)
• Max. fuel weight, kg (lb.)
245
(540)
• Maximum landing weight, kg (lb.)
2270
(4998)
Speeds
• VNE (Never Exceed), km/h (knots)
• VNO (Structural cruising), km/h (knots)
• VA (Maneuvering), km/h (knots)
• VLE max. landing gear extension speed, km/h (knots)
• VMC single engine minimum control speed
• Rate of climb at sea level at takeoff weight of 2270 kg, m/s:
— 2 engines operative
— single engine operation
• Lift-off speed, km/h (knots)
• Landing speed, km/h (knots)
11
240
240
215
183
115
(130)
(130)
(116)
(99)
(62)
5.2
0.4
135–140
130–135
(17)
(1.3)
(72–75)
(70–72)
Dimensions
Length (without radar), m (ft)
Wing span, m (ft)
Height, m (ft)
Wing area, m2 (sq. ft)
Fuselage length, m (ft)
Fuselage maximum width, m (ft)
Cabin length, m (ft)
Cabin width, m (ft)
Cabin height, m (ft)
Cabin volume , m3 (ft3)
Entrance and emergency doors , m (ft)
Aircraft ground turn radius, m (ft)
12
10.65
12.72
3.76
25.1
9.96
1.35
3.2
1.25
1.23
4.6 m3
1.3 х 0.9
8.175
(35)
(41.7)
(12.3)
270.2
(32.7)
(4.43)
(10.5)
(4.1)
(4)
(162)
(4.3 х 3)
(26.8)
Limitations
•Max positive operational maneuvering g-load
•Max negative operational maneuvering g-load
•Max operational flight altitude, m (ft)
•Reserve remaining fuel, kg (lb)
•Take-off and landing on water is
prohibited at night.
•It is prohibited to operate the
aircraft
under
actual
and
predicted
icing
conditions
(outdoor temperature lower +5°C
if raining, drizzling or snowing).
•It is prohibited to flight within
thunderstorm area.
13
+3.45
-1.45
3000 (10000)
10 (33)
Take-off Distances up to 50 ft (15 m)
m
ft
1220 4000
MSA, 3000 ft
MSA+300, SL
1067 3500
914
14
3000
762
2500
609
2000
MSA, SL
from
water
MSA, 3000 ft
MSA+300, SL
MSA, SL
from
ground
457
1500
305
1000
4100
4200
4300
4400
4500
4600
4700
4800
4900
5000
1860
1905
1950
1995
2041
2086
2132
2177
2222
2269
5100 lb
2313 kg
Landing Distances from 50 ft (15 m)
m
ft
610
2000
595
1950
Ground landing
MSA, 3000 ft
MSA+300, SL
580
1900
564
1850
548
1800
533
1750
4100
1860
15
MSA, SL
4200
4300
4400
4500
4600
4700
4800
4900
5000
5100 lb
1905
1950
1995
2041
2086
2132
2177
2222
2269
2313
kg
Payload – Range
Lb.
Kg
772
350
661
300
551
250
441
200
331
150
220
100
110
50
Payload
Range
0
0
16
200
400
600
800
1000
1200
1400
108
216
324
432
540
648
756
1600
Km
864 n.mile
Airdromes
Airdromes :
— airdrome elevation not more than, m (ft)
— runway length not less than, m (ft)
— max crosswind, m/s (knots)
— max down wind
— outside temperature
17
900 (3000)
1188 (3900)
6 (11.6)
2 (3.9)
-30°C to +40°C
Water Areas
Water areas:
— length not less than, m (ft)
— width not less than, m (ft)
— depth at rough water of 0.5 ft not less than, m (ft)
— max wind wave height, m (ft)
— max crosswind, m/s (knots)
— max down wind, m/s (knots)
— outside temperature at ground
18
1500 (5000)
100 (330)
1.5 (4.9)
0.4 (1.31)
3 (5.8)
0
+5°C to +40°C
Basic Passenger Variant
• Cabin capacity — 6 seats.
• In the cabin there is a pilot’s
working place and passengers’
seats per 2 in a row with central
pass of 200 mm (8 in.), seats
spacing of 1220 mm (47 in.) and
860 mm (34 in.).
Passengers’
seats
Pilot seat
19
Luggage compartment
• In the front part of the cabin, the
maritime equipment — anchor,
line, hock and others — is located.
• The back wall of a cabin
separates it from a luggage
compartment (capacity 0,8 m3 (28
cub.ft.).
• In the aft part of the luggage
compartment, the electrical and
heating equipments are located.
Passenger Cabin
The cabin is equipped with six seats: one for
pilot and five for passengers.
The seats are located in three rows.
There is a passage along the cabin to provide
the passengers and pilots to enter, take the
seats and go out of the aircraft between the
seats.
Each seat is equipped with a seat belt fixed to
the seat and consisting of lap belt and two
bandoliers having one lock.
The seats of the first and third row can move
by guide rails in longitudinal direction and can
be fixed.
Each seat can be dismantled without use of
the tool, if required.
21
The Be-103 piloting and control
• The aircraft piloting is accomplished by one pilot,
controlling movable horizontal stabilizer, one pair
of ailerons and rudder with trimmer.
• The control stick and pedals are the command
controls.
• There is provision for installation Instructor’s dual
controls at RH side. The forces from controls to
control surfaces are transferred through push-pull
control linkage in the longitudinal and lateral
control channels and through cable linkage in the
heading channel.
•
•
•
•
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Movable
horizontal
stabilizer
Rudder
Aileron
Rudder trim tab
Aileron
The servos of autopilot systems are connected to the linkage of lateral and longitudinal
channels.
Controllability is provided with spring-loading mechanism, with special loading diagram. This
mechanism is connects the elevator horn with linear electrical mechanism, providing aircraft
trim in longitudinal channel and emergency control in the case of disconnection (failure) of
any linkage element.
To provide control in the case of cable jamming in the longitudinal channel there is
“expanding rod” device provided implemented with linear electrical mechanism.
The rudder trim tab control is of electrical-mechanical type.
Powerplant
• Suppliers: TELEDYNE CONTINENTAL MOTORS (USA) and
MT-PROPELLER GmbH (Germany)
• Engine type:
TCM IO-360 ES4
• Engine weight:
Dry weight
158 kg
348 lb.
Equipped engine
163,35 kg
360 lb.
• Max. capacity (2800 rpm)
210 hp
• Reliable engine start on ground and in flight at ambient air temperature of
(-55°C) - (+ 45°C ) and at heights up to 3000 m / 9843 ft.
• The engine has a standard flange
for propeller fastening.
• The engine is equipped with air-in
system, ignition system, oil and fuel
system
• Type Certificate No. ST 84-D
issued on 22.06.1996 by the
Aviation Register of the Interstate
Aviation Committee
• FAA Type Certificate No.E1CE
dated 28.09.1995
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МТV-12-D-С-F-R(M)/CFR183-17 Propeller
•Three-blade reversal variable pitch
propeller.
• Propeller diameter of 1,83 m (6 ft.).
• Type Certificate No. ST 173-VV issued
by the Aviation Register of the Interstate
Aviation Committee on 17.11.1999
• FAA Type Certificate No. P–25NE dated
10.12.1999
24
The Be-103 amphibian fuel system
Tanks No. 1 and 2
Tanks No. 3 and 4
Fuel system is composed of two autonomous
system for LH and RH engine. These system are of
similar design and connected with cross-feed valve.
• The system is composed of the tanks, fuel tank
venting, fueling, fuel transfer, fuel feeding to the
engines, draining systems. Also there are
implemented the indicating instruments and
devices.
• The tanks No. 3 and 4 are located in the wing
center section. The tanks No. 1 and 2 are located in
the pylon, these tanks are used as fuel consumed
ones.
•
•The fuel system (fig. 5.3) provides adequate fueling and uninterruptible fuel supply to both
engines in defined flight conditions within all the range of engine operation modes.
• Fuel transfer system provides fuel transfer from wing tanks to the pylon ones.
• The fueling is performed through the fillers arranged on the upper panels of the wings and
the pylons.
• Fuel feeding system provides fuel supply to the engines in all the conditions of engine
operation modes.
• There are drain valve installed on the lower panels of the tanks.
25
The Be-103 amphibian chassis
• Landing gear is designed for operation from
concrete and unpaved runways with strength
б5 kgf/sq.cm
• There are oil-nitrogen shock absorbers
implemented in.
• The nose leg is hinged to the airframe,
equipped with wheel without brakes, with tire
400х150. Tire pressure is of 2.4+0.5 kgf/cm2.
• Each main legs of the landing gear is provided
with shock absorber hinged to the wing and
equipped with the wheels with brakes, with tire
of 476х178. Tire pressure is of 3.9+0.2
kgf/cm2.
• Retraction and extension of the landing gear is
performed with hydraulic jack actuated from
the main airborne hydraulic system. The
emergency operation of the landing gear is
performed manually with cable linkage system
– by opening the locks of closed landing gear
position. Actuation of the landing locks in
opened position is provided by weight forces
and air dynamic forces of ram air.
• The parking braking is provided.
26
Main leg
Nose leg
The Be-103 amphibian hydraulic system
Feeding panel
with the pump
Hydraulic accumulator of the landing
gear brakes system
• Hydraulic system provides extraction and extension of the landing gear, main and parking
braking of the wheels of the main legs.
• Electrical hydraulic pump developed by Abex (Germany) is used as the pressure source in the
hydraulic system. The hydraulic pump provides nominal pressure of 16.5 MPa (165 kgf/cm2).
• The piston-type hydraulic accumulator is the pressure source for the brakes actuation while
parked. The charging pressure of the nitrogen chamber of hydraulic accumulator is of 5.8-0.3
Mpa (58-3 kgf/cm2).
• The operational liquid in the hydraulic system is of AMG-10, Russian Standard GOST 6794-75.
27
Cabin heating & ventilation
Air intake
(LH and RH)
Air intake with regulator
Electrical air heater
• Heating and ventilation system provides comfortable and survival conditions for crew
and passengers.
• The heating & ventilation system provides the following:
- cabin ventilation with outside air;
- heating of the air supplied to cabin;
- individual ventilation of pilots and passengers;
- de-fogging of the front canopy area.
28
Electrical power supply system of the Be-103 amphibian
• Electrical power supply systems provides
functioning of the following airborne systems:
- engine start;
- engine operation monitoring;
- fuel system and fuel measuring equipment;
- navigation and radio/radar equipment;
- communication equipment;
- aircraft control system;
- airborne record system;
- icing indication;
- lighting equipment;
- landing gear retraction-extension and
breaking systems.
•
•
•
29
Generators
Voltage
regulator
Storage battery
Distribution device
Rectifier
Two AC generators with the rectifiers built-in are used as the main sources of electrical
power on the airplane. The generators are produced by Teledyne Continental Motors,
Part No. ТСМ 653344, with output power of 1.7 kW (60 A) each.
The storage battery F20/17H1CT developed by “VARTA” is used as emergency power
source. The battery capacity of 17 Ah. The output power of one generator is sufficient to
provide electrical power to all the consumers in the case of failure of the other generator.
The electrical power supply system is developed with fire-proof provisions.
There is ground power connector provided in the airplane to supply the electrical power
from ground source.
The Be-103 amphibian lighting equipment
• The lighting equipment components are divided into the following groups respect to functionality
and arrangement :
- navigation equipment;
- landing & taxing equipment;
- internal lighting equipment.
• Navigation equipment is composed of wing flash and navigation lights A650-PG-28 and А650PR-28 developed by WHELEN, rear navigation light АНО3-Бл , and anchor light ОЯГ-1.
• The red navigation light with wing flashing light A650-PR-28 is installed on the LH wing, and the
green navigation light with wing flashing light A650-PG-28 is installed on the RH wing.
•
•
•
•
30
The rear navigation light АНО3-Бл is
installed in the rear part of the tail tip.
Anchor (parking) light is used when the
airplane is parked on water anchored (in
night conditions). The anchor light ОЯГ-1 is
located on the top of the tail tip.
There are two landing & taxi lights installed in
the leading edges of LH and RH wings. The
lights have part No. АПРФ-2.
Internal lighting equipment provides the
following:
- lighting of instruments and system controls;
- general lighting of pilot station;
- warning indication at pilot station;
- lighting of the passengers’ cabin and
baggage compartment;
- lighting of service compartments.
Rear navigation light
Anchor light
Wing green navigation and
flashing lights
Cabin lights
Lights
Landing &
taxiing lights
Wing red navigation
and flashing lights
Radio communication equipment of the Be-103 amphibian
• Radio
communication
equipment
provides
two-way
radio
communications with air traffic control, switching radio equipment and
listening to the navigation signals.
• The following equipment is defined for installation onboard:
- KY196A VHF radio
- 2 pcs.;
- KMA 24 intercommunication equipment
- 1 pc.;
- headset
- 1 pc.;
- P-855A1 emergency VHF radio
- 1 pc.
VHF radio
Emergency radio
31
Cockpit Instrument Panel-Garmin G1000 Avionics
GDU-1044B Primary
Flight Display (PFD)
Control Wheel Push-ToTalk Switch-Pilot/Co-pilot
GMA-1347 Digital Audio Panel
with Marker Beacon/Intercom
GDU-1044B Multifunctional
Display (MFD)
GTX-33 Transponder-Mode S
w-TIS (Interfaced with MFD)
Emergency Locator Transmitter
Remote Mounted Switch
Master and Alternator
switch
Alternate Static Source
Avionics Switch
Throttle (Push)
Pitot (heated) & static
system panel
Backup Attitude Gyro, Altimeter,
and Airspeed Indicator
Mixture (pull)
Handheld Microphone
Auxiliary Stereo Input Jack
Rudder Pedals
32
GRS-77 attitude and
heading reference system
(AHRS)
GDC-74A Air Data
Computer with OAT
Probe
GDU-1044B Primary
Flight Display
it uses solid-state
sensors to measure
aircraft attitude, rate of
turn, and slip and skid
Replaces the pitot-static
systems in traditional aircraft
instrumentations, it measures
airspeed, altitude and outside
air temperature
GMU-44 Magnetometer
LCD screens Can
be switched
it measures aircraft
heading and is a digital
version of a traditional
compass
GDU-1044B
Multifunctional Display
GEA-71 Engine/Airframe
Computer
It measures a large variety of engine
and airframe parameters, including
engine RPM, manifold pressure, oil
temperature, cylinder head
temperature, exhaust gas temperature,
and fuel level in each tank
GIA-63W
NAV/COM/GPS/WAAS
with GS
Garmin G1000 avionics Special features
• Garmin Safe Taxi & FliteCharts
Garmin Safe Taxi
 Able to taxi around unfamiliar airports with ease.
 It identifies runways, taxiways, FBOs, hangars, and the
aircraft’s exact location on the field.
 SafeTaxi is geo-referenced, pilots will benefit by seeing
their aircraft icon move precisely along the taxiway
diagram
Garmin FliteCharts
 An electronic version of the National Aeronautical Chart
Office (NACO) U.S
 FliteCharts allows pilots to quickly find and view all NACO
Departure Procedures (DP), Standard Terminal Arrival
Routes (STARs), approach charts, and airport diagrams on
the MFD.
Garmin G1000 avionics Special features
• GTX 33 S mode Transponder
• Fuel Range Ring
 Integrated on the Multifunctional Display
 shows the aircraft’s range given its current ground
speed and fuel burn.
 Displays Traffic Information System (TIS-A) alerts.
 provides mode-S bidirectional communications
with Air Traffic Control
 It can indicate traffic in the area as well as
announce itself spontaneously via "squittering"
without prior interrogation.
 Remote Ident and auto standby capability
 Provide a dashed-line ring inside the absolute
(tanks dry) range ring that shows how far you can
fly and still have a certain endurance of fuel still in
the tanks
 Prevents accidents from fuel exhaustion
Garmin G1000 avionics Special features
Electronic Checklists
 An automatic-sensed checklist
 A safety & warning supplement system
 Shows important system messages & status
 provide a final check that the aircraft has been
properly configured for each phase of flight
 Shows failure & Warning messages.
Garmin G1000 avionics Special features
Optional feature & system
 Garmin Synthetic Vision Technology
 Provide sophisticated graphics modelling of terrain,
traffic and obstacles in the flight path.
 The system looks at the entire flight via satellite
and renders a 3D landscape.
Inscriptions
Inscriptions
on
external
surface of the aircraft, in
pilot’s cockpit and cabin are
carried out by agreement with
a customer in a language
specified in the sale contract.
The
external
inscriptions
includes
information
for
ground maintenance and
inspection
as
well
as
warnings and cautions.
The external inscriptions on
operational
hatches
are
intended for indication of
access
to
the
aircraft
systems. They indicate the
following:
• points of fueling and operating fluid discharge;
• access to units and assemblies of the systems.
To provide personnel safety, the areas of safe access are indicated on the wing. Internal
inscriptions include information required for internal general and emergency information,
instructions, warnings and cautions.
33
Aircraft service life and lifetime
• Design assigned service life, flight hours…………………….…………….. 15000
• Assigned Service life:
- landings on the ground (including unpaved fields)………………………. 6000
5000
- landings on water……..………………………………………….......….…..
• The activities to increase number of landings within assigned service life should
be performed during development and operation of the airplane.
20
• Calendar lifetime, years……………………………………………………….
34
Maintenance Features
• on
maintenance
condition
• use of the built-in test
system
• easy
access
assemblies and units
• full
capability
to
autonomous
That provides:
• high level of aircraft readiness (pre-flight preparation is performed during 10 minutes)
• prompt failures discovery
• reduce of operation costs
• maintainability
35
Ground Towing
Ground towing within the airdrome as well as roll in and out of the water is carried
out by means of a tow car.
36
Water Towing
Water towing can
be carried out at
wind speed not
more than 15.5
knots (8 m/s) and
wave height up to
1.6 ft (up to 0.5 m).
The aircraft is towed by nose towing ducks of
the aircraft with the help of a tow cable.
37
Parking and Mooring
During parking, the aircraft should be deenergized, the controls should be stopped
and the accumulators should be taken
away for long parking (for more than 24
hours).
A set of mooring devices, chokes and
safety support are used to prevent the
aircraft from accidental movement during
parking on the slope area, at gust and
engine run-up operations.
Mooring devices provide holding of the
aircraft at wind speed up to 78 knots (40
m/s)
A safety support is provided to prevent
the aircraft from fall to the tail.
38
List of technical documents applicable to the Be-103
• Operational document sheet
• Aircraft logbook
• Engine logbook with certificates for assemblies and purchased items installed in
engine
• Maintenance manual for engine, its systems and assemblies
• Certificates for assemblies and purchased items
• Flight operation manual.
• Load and center of gravity manual.
• Maintenance manual
• Maintenance schedule
• Electric circuit diagram manual
• Maintenance manual for purchased items installed in the aircraft.
• Spare parts lists, list of tools, list of ground support equipment, list of ground test
equipment.
• Acts and measuring tables
• Aileron, horizontal stabilizer and rudder balancing manual
39
Regional Agent
King Join International Pte Ltd
京华国际有限公司
1, North Bridge Road, #16-08 High Street
Centre,
Singapore 179094
Tel: 65-63388707 Fax: 65-63388929
Email: rreg1988@regalindo.com.sg
Mr.
1988@regalindo.com.sg
40