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The Flight Design C4

New Four Place IFR equipped Certified aircraft 

 
 

The much anticipated Flight Design C4 program continues development in Europe. The prototype made the flight test in April 2015. 

The Flight Design C4 is an all carbon composite four-place light aircraft based upon the advanced design of the popular Flight Design CT series of aircraft.  Key features are the new Continental IO-360AF Alternate Fuels engine, conceived to “future proof” the C4, an advanced glass panel cockpit by Garmin and an integrated, full airplane parachute system. Flight Design has always designed its planes for excellent cross country performance and the C4 is planned to have up to a 1200 NM (2200km) range.

Due in large part to the structural efficiency of carbon composites, the C4 will also provide true utility with a giant, easy to enter cabin and a very high useful load of 1320 Lbs(600kg).  As a part of the development process, mock ups of the airframe and interior cabin have been shown extensively for customer input on the ergonomic design. 

Flight Design has been very busy with recent developments including adding additional technical staff at the Flight Design Flight Test Center in Kamenz Germany, attaining EASA Design Organization Approval (DOA) and working to finish Production Organization Approval (POA).  These two approvals will allow Flight Design to develop and certify the C4 in a more rapid fashion which is key to keeping the target cost of the C4 completely equipped price of $250,000 (€ 220.000).       

The C4 will first be certified in Europe under ELA (European Light Aircraft Category) by EASA. FAA certification is anticipated under reciprocity between these two leading regulatory agencies.  Flight Design has participated in the creation of ELA and is involved as well with the current Part 23 ARC review with contributions to the technical and regulatory committees.      

In order for the aggressive low price target of the C4 to be achieved, all major components of the aircraft must meet pre-determined functional and cost criteria.  The major cost drivers include the airframe, engine, avionics and certification.  Flight Design has extensive experience and understanding of the airframe and, as you know, our engine selection was made in late 2011 with the alternate fuel capable Continental IO-360-AF being chosen.  BRS Aerospace has been selected as the supplier of the integrated, full airplane parachute system (FAPS) for the C4 and at AirVenture Oshkosh 2013 Flight Design announced the selection of Garmin avionics (The Flight Design Vision Touch) for its new C4 all-carbon composite four-seat light aircraft.

The Flight Design Vision Touch

The Vision Touch suite is based around the Garmin G3X Touch ® system as PFD and MFD (Primary and Multifunction Displays). The G3X Touch is a new product offering from Garmin that features both advanced synthetic vision capabilities and a choice of touch screen and conventional button/knob input as well. The inclusion of this system will give C4 owners the greater situational awareness afforded by synthetic vision and the simplicity of operation through the advanced touch screen displays. Fmi:http://www.garmin.com/us/products/intheair/sportaviation/g3x-touch/ 

The Vision Touch suite also includes other super capable equipment such as the Garmin GTN 750 Black® Nav-Com-GPS system for primary navigation and also as a touch screen input device for entering fl ight plans, either manually or with a preprogrammed fl ight plans on an SD card. The convenient positioning of the GTN 750 will allow comfortablein flight data input. Entering a flight plan will automatically populate the information up to the PFD and MFD screens. Other components include the Garmin GNC255 Nav-Com as a secondary navigation system and back up radio, the Garmin GMA350 audio panel and the Garmin GMC 305 autopilot.   To top off this impressive list are centrally located RC Allen solid-state digital Directional Gyro, Attitude indicator, full-size airspeed and altimeter.

  

 

  
  

 

 

 

 

 

PERFORMANCE DATA

Masses and Capacities:

Empty mass                                          600 kg (1320 lb) typical
MTOM                                                   1200 kg (2640 lb)
Seating Capacity                                  max. 130 kg (287 lb) per seat
Baggage                                                 max. 75 kg (165 lb)
Fuel                                                        265 l (70 gal) total in both wings

Loading Examples:

 
Average Cabin
Loading
Max Fuel Loading
High cabin loading AVGAS
High cabin loading Diesel
Low mass ops
(towing)
Empty Aircraft Mass
600 kg
600 kg
600 kg
600 kg
600 kg
Occupants Mass
4 x 90 kg
= 360 kg
4 x 90 kg
= 360 kg
4 x 120 kg
= 480 kg
4 x 130 kg
= 520 kg
1 x 90 kg
Luggage Mass
4 x 15 kg
= 60 kg
4 x 4.25 kg
= 17 kg
4 x 18.75 kg
= 75 kg
4 x 18.75 kg
= 75 kg
0 kg
Fuel Mass
250 l AVGAS
= 180 kg
265 l Diesel
= 223 kg
62.5 l AVGAS
= 45 kg
54 l Diesel
= 45 kg
50 l Diesel
= 42 kg
 
Endurance
6:25 hrs @ 75%
power
11:45 hrs
@ 75% power
(13:35 @ 65% power)
1:35 hrs
@ 75% power
2:25 hrs
@ 75% power
2:00 hrs
@ towing cycle
Operating Mass
1200 kg
1200 kg
1200 kg
1200 kg
 
732 kg
 
PRICE

Basic Price : US $250,000 (€220.000 EURO excl. VAT) depending on equipment level.

CERTIFICATION

Initial certification by EASA (application filed in Q1 2011)

FAA certification by reciprocity of EASA certification

NOISE LEVEL

ICAO Annex 16 Chapter 10 less than 79.9 dB(A)

…complies with Landeplatz Lärmschutzverordnung (enhanced noise limits).

OPERATIONAL LIMITATIONS

VFR and IFR operation

SPEEDS
Stall speed full flaps V0 (MTOM) 93 km/h 50 kts
Max cruise speed Vh 296 km/h 160 kts
Never exceed speed Vne 360 km/h 195 kts

Maximum Range and Endurance

AVGAS Engine:

Maximum range
1200 NM (2200 km)
… @ 65% power; 32 l/hr; 145 kt
Maximum endurance 10:00 hrs … @ 55% power; 26.5 l/hr
Diesel Engine:
Maximum range
1700 NM (3150 km)
… @ 75% power; 22.5 l/hr; 145 kt
Maximum endurance  13:35 hrs … @ 65% power; 19.5 l/hr

Climb rate:

at MTOW, MP, ISA 0m                                        5 m/s (984 ft/min)

Takeoff @ ISA 0, hard surface:
Takeoff roll                                                          400 m (1312 ft)
Takeoff distance                                                  650 m (2132 ft) to clear 15 m (50 ft) obstacle

SAFETY

Safety:

Three–point safety belts with inertia reel on each seat

Seat belts with airbags optional

BRS Airframe Emergency Parachute installed as standard equipment

 

COCKPIT/EQUIPMENT

Instrumentation / Cockpit:

Flight Instrumentation as Garmin G3X Package Vision Touch Glass Cockpit providing:
Garmin Double Touch Screens GDU 460 and GDU 465 (10.6” landscape format) provide full PFD and full MFD functionality with backup battery
Full EMS functionality
Independent sensor units supporting all functions, installed at convenient locations
Intercom Garmin GMA 350 with aux music input and connection to GPS Audio
Four Headset Telex Echelon 25 XT with plug connectors next to the seats
4 x LEMO Redell Connectors installed for ANR Headset, in addition to standard plugs
Garmin GTN 750 Black System – Nav/Com/GPS providing:
– Intuitive, 6.9″ (diagonal) touch screen operation, graphical flight planning
– Second COM antenna installed to the underside of the fuselage
– Antenna splitter and diplexer to support both VOR / GS receivers from one VOR antenna with all signals
– Installation with G3X Touch – CDI / NAV display on G3X Touch through Dynon ARINC 429;
Back-up Radio Garmin GTR 255A – 8.33kHz / 25kHz installed with GS capable NAV Antenna at the upper vertical tail, linked to G3X Touch EFIS, CDI NAV display
Garmin GTX33 ES Remote Transponder Mode S
G3X suite linked up with Transponder and Transceiver
Integrated GPS functionality with XM capability allows full navigation support
Jeppesen aviation database with terrain and obstacle database (updates / subscription not included!)
KANNAD AF 406 Compact ELT 406 MHz
Analog Instrumentation – providing redundancy together with Glass Screen:
RC Allen digital directional gyro (80 mm)
RC Allen digital attitude indicator (80 mm)
Analog airspeed indicator (80 mm)
Analog one pointer altimeter (80 mm)
Magnetic compass with deviation table

Optional Equipment:
Glider / banner towing system
Float option possible in future
Icing protection under consideration (details in planning)

CABIN

Front seats individually adjustable in length / height (coupled), entire seat can be inclined. Rear seat as bench with two individually shaped seat cushions. Rear seatback folds forward for access to baggage area. Rear seat with ISOFIX child seat attachments.

Cabin doors left / right front seats (hinged front, opening forward), plus left–side rear cabin door (hinged aft, opening rearward), creating an unobstructed, large opening on left side of cabin.
Access to luggage compartment through rear seat bench, or through luggage door in right side of fuselage.

ENGINE/PROPELLER

Propulsion:

— Engines

Gasoline Engine:

• Continental IO-360-AF (Alternative Fuels) CHECK THIS VIDEO!

• 6–cylinder, 180 HP @ 2,550 RPM, fuel–injected, low–compression, naturally–aspirated

• Capable of operating on both 100LL avgas and lower octane alternative fuels

• 2,000 hour TBO, fuel consumption: 7-10 GPH (26.5 – 38.0 l/hr) depending on power setting

Diesel Engine: (Supplier partner to be decided)

• Turbocharged

• 155 – 180 HP @ 2300-2400 RPM

• Fuel: Jet–A, 7.9 gal/hr (30 l/hr) @ max power; 5.9 gal/hr (22.5 l/hr) @ 75% power

• Single–Lever Operation

— Propeller

Hartzell two–blade constant speed propeller.

STRUCTURE/UNDERCARRIAGE

Structure:

All–composite sandwich structure (Carbon / Aramide / Glass)
One–piece, fully–cantilevered wing
Non–pressurized
Undercarriage
Single–beam composite main landing gear
Main wheel size 6.00 – 6’’, nose wheel 4.00 – 6’’
Hydraulic disc brakes
Directly steerable nose wheel

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