VLJ Category - Introduction
The term Very Light Jet (VLJ) describes a class of small business jets that typically seat four to eight people and are often certified for single-pilot operations.
These aircraft emerged with the goal of reducing operating costs and enabling jet access to smaller airports and shorter runways, essentially allowing more flexible, point-to-point business or personal travel.
The Cessna Citation Mustang
*The Mustang aircraft served as a core reference for a typical, modern VLJ aircraft, in the development of the VSKYLABS VSL 510X. Please note that the VSKYLBS VSL 510X-VLJ is not a direct replica of the Citation Mustang. Various differences in appearance and operations may be noticeable.
The Cessna Citation Mustang (Model 510) is a prime example of the VLJ concept: manufactured by Cessna Aircraft Company in the United States, it first flew on April 23, 2005, and entered service in 2006.
In its standard configuration it carries four passengers in the rear cabin, a toilet, and two-pilot/one-pilot certified cockpit seating.
Designed to bring jet performance into a more accessible segment, the Mustang offered the advantages of twin aft-mounted turbofans, a stand-up cabin, and the ability to be operated by a single pilot, features that made it attractive both for owner-pilots and small charter operations.
Although production ended in 2017 after 479 units were built, the Mustang remains a useful reference platform for high-fidelity simulation and systems-logic modelling.
GENERAL SPECIFICATIONS:
The VSL 510X-VLJ is a very light jet with a maximum cruise speed of 340 knots (391 mph), a service ceiling of 41,000 feet, and an NBAA IFR range of approximately 1,167 nautical miles. It is powered by two Pratt & Whitney PW615F engines, has a capacity of 4-5 passengers and a 1-2 person crew, and features a Garmin G1000 avionics suite (LR X1000).
- Crew: 1-2 pilots.
- Passengers: 4-5.
- Engines: 2 Pratt & Whitney PW615F turbofans, each producing 1,460 lbf of thrust.
- Avionics: Garmin G1000 (LR X1000).
- Overall Height: 13 ft 5 in (4.09 m) Overall Length: 40 ft 7 in (12.37 m) Overall Width: 43 ft 2 in (13.16 m).
- Wing Span (does not include tip lights): 42 ft 9 in (13.03 m) Area: 210.0 ft2 (19.51 m2) Sweepback at leading edge: 11 degrees.
- Horizontal Tail Span (overall) : 17 ft 3 in (5.26 m) Area: 56.5 ft2 (5.25 m2) Sweepback at leading edge: 27 degrees.
- Vertical Tail Height: 5 ft 9 in (1.75 m) Area: 37.5 ft2 (3.48 m2) Sweepback at leading edge: 52 degrees.
- Cabin Interior Height (maximum over aisle): 54 in (1.37 m) Width (window reveal to window reveal): 55 in (1.40 m) Length (forward pressure bulkhead to aft pressure bulkhead): 14 ft 9 in (4.50 m).
- Landing Gear Tread (main to main) 11 ft 10 in (3.61 m) Wheelbase (nose to main): 14 ft 4 in (4.37 m).
PERFORMANCE:
All performance data assumes the standard aircraft configuration operating in International Standard Atmosphere (ISA) conditions with zero wind. Takeoff and landing distances are based on level, dry, hard-surface runways. Actual performance may vary with aircraft configuration, environmental conditions, and operational or ATC procedures.
- Takeoff Runway Length: 3,110 ft (948 m)
*Maximum Takeoff Weight, Sea Level, ISA, 15° Flaps. - Landing Distance: 2380 ft (725 m)
*Sea Level, ISA - Maximum Altitude: 41,000 ft (12,497 m)
- Maximum Cruise Speed (± 3%): 340 KTAS (630 km/hr or 391 mph)
(Mid-Cruise Weight, 35,000 ft (11,668 m), ISA) - NBAA IFR Range (100 nm alternate) (± 4%): 1,150 nm (2,130 km or 1,323 mi)
(Maximum Takeoff Weight, Full Fuel, Optimal Climb and Descent, Maximum Cruise Thrust at 41,000 feet) - Landing Runway Length: 2,390 ft (728 m)
(Maximum Landing Weight, Sea Level, ISA, per Part 23 Commuter Category)
LIMITATIONS
OPERATIONS AUTHORIZED
- Approved for day, night,VFR and IFR operations and flight into known icing conditions (requires all relevant equipment to functions properly).
WEIGHT LIMITATIONS
- Standard Empty Weight *: 5,359 lb (2,431 kg)
- Useful Load: 3,371 lb (1,529 kg)
- Fuel Capacity (usable) at 6.70 lb/gal: 2,580 lb (1,170 kg)
* Standard empty weight includes unusable fuel, full oil, standard interior, and standard avionics. - Maximum Design Ramp Weight: 8730 Pounds
- Maximum Design Takeoff Weight : 8645 Pounds
- Maximum Design Landing Weight: 8000 Pounds
- Maximum Design Zero Fuel Weight: 6750 Pounds
- Minimum Weight in RVSM Airspace: 6300 Pounds
- Maximum Certified Takeoff Weight(Flaps - TAKEOFF/APPROACH): 8645 Pounds
- Maximum Certified Landing Weight: 8000 Pounds
SPEED LIMITATIONS
- Maximum Operating Limit Speeds:
- VMO (Between Sea Level and 27,120 Feet): 250 KIAS
- MMO (Above 27,120 Feet): 0.63 Mach (Indicated)
- Full input of rudder and aileron controls, as well as maneuvers that involve exceeding angle-of-attack near the stall regime, should be limited to speeds below maximum maneuvering speed.
FLAPS EXTENSION SPEEDS
- Maximum Flap Extended Speed - VFE:
- TAKEOFF / APPROACH Detent (15°): 185 KIAS
- LAND Position (30°): 150 KIAS
GEARS, BRAKES AND SPEEDBRAKES
- Maximum Landing Gear Extended Speed - VLE: 250 KIAS
- Maximum Landing Gear Operating Speed - VLO (Extending): 250 KIAS
- Maximum Landing Gear Operating Speed - VLO (Retracting): 185 KIAS
- Maximum Tire Ground Speed: 160 Knots
- Maximum Speed Brake Operation Speed - VSB: No Limit
AUTOPILOT
- Maximum Autopilot Operation Speed: 250 KIAS or 0.63 Mach
SPEED IN ICING CONDITIONS
- Minimum Speed For Sustained Flight In Icing Conditions
(except takeoff, approach and landing): 160 KIAS
TAKEOFF AND LANDING OPERATIONAL LIMITS
- Maximum Altitude Limit: 14,000 Feet
- Maximum Tailwind Component: 10 Knots
- Maximum Demonstrated Crosswind Component (Not Limiting): 25 Knots
- Minimum Fuel Quantity per Wing for Takeoff: 200 Pounds
- The maximum approved fuel imbalance is 200 pounds; however, controllability for safe return and landing has been demonstrated with an emergency fuel imbalance of 600 pounds.
- Autopilot and yaw damper must be disengaged for takeoff and landing
- Takeoff and landings are limited to paved runway surfaces.
- Cabin must be depressurized for landing.
ENROUTE OPERATIONAL LIMITS
- Maximum Operating Altitude: 41,000 Feet
- Maximum Altitude for Extension of Flaps: 18,000 Feet
- Minimum Temperature for Operation of Flaps: -40°C RAT
- Yaw Damper must be engaged above FL300.
LOAD FACTOR
- Flaps - UP (0º): -1.44 to +3.6G at 8645 pounds
- Flaps - TAKEOFF / APPROACH or LAND (15º or 30º): 0.0 to +2.0G at 8645 pounds
CABIN PRESSURIZATION LIMITATIONS
- Normal Cabin Pressurization Limitations: 0.0 to 8.5 (+0.1) PSID
MANEUVER LIMITATIONS
- Acrobatic maneuvers, including spins, are prohibited.
- Intentional stalls are prohibited above 18,000 feet.
BAGGAGE COMPARTMENTS
- Nose Baggage Compartment (L-R): 320 pounds maximum (combined)
- Tailcone Baggage Compartment: 300 pounds maximum (combined)
STANDBY INSTRUMENTS
- The standby flight instruments (ATT, ALT and ASI in the upper block above the MFD) must be functioning prior to takeoff.