Bell 206 vs PZL SW-4 Puszczyk: Specs Compared

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Bell 206 — licensed reference photograph

AHelicopters

Bell 206

Multipurpose utility helicopter

Credit

Mfield - Matthew Field, http://www.photography.mattfield.com · CC BY 2.5 · Resized · CC BY 2.5 · Source ↗ · Modified

BHelicopters

PZL SW-4 Puszczyk

Multipurpose utility helicopter

First system

Second system

At a glance

Side by side

Length comparisonOne shared metre scale

Bell 206206B Jetranger II · including rotors

11.824 m

Length source ↗

PZL SW-4 PuszczykSW-4 · Length

10.57 m

Length source ↗

Lengths retain their source configuration and measurement scope.

Measured figures

Head to head

24 of 32 rows sourced on both sides

11.82m206B Jetranger II · including rotors

10.57mSW-4 · Length

LengthScopes differ

All recorded figures & sources

11.824 m

206B Jetranger II · including rotors

Single source

38 ft 9.5 in (11.824 m) including rotors^[source]

10.57 m

SW-4 · Length

Configuration

Details

Bell 206 and PZL SW-4 Puszczyk configuration
Specification	Bell 206	PZL SW-4 Puszczyk
Type	Multipurpose utility helicopter^[source]	Multipurpose utility helicopter^[source]
National origin	United States / Canada^[source]	Poland^[source]
Manufacturer	Bell Helicopter^[source]	PZL-Świdnik^[source]
Status	In service^[source]

Number built	7,300^[source]	40^[source]

Manufactured	1962–2017^[source]	1996–present^[source]

Introduction date	1967^[source]	2002^[source]

First flight	December 8, 1962 (206) January 10, 1966 (206A)^[source]	29 October 1996^[source]

Developed from	Bell YOH-4^[source]	—

Variants	Bell OH-58 Kiowa Bell 407^[source]	—

Developed into	Bell 400 TwinRanger^[source]	—

Capacity	4 passengers^[source]	4 passengers^[source]

Fuselage length	31 ft 2 in (9.50 m)^[source]	—

Interior dimensions	7 ft 2 in (2.18 m) length, by 4 ft 2 in (1.27 m) width, by 4 ft 3 in (1.30 m) height, plus 16 ft 3 (453 L) baggage compartment^[source]	—

Main rotor area	873 sq ft (81.1 m 2 )^[source]	64 m 2 (690 sq ft)^[source]

Blade section	– NACA 0012 mod (11.3%)^[source]	—

Maximum speed at 5,000 ft	116 kn (133 mph; 215 km/h) at MTOW^[source]	—

Disk loading	4 lb/sq ft (20 kg/m 2 )^[source]	25 kg/m 2 (5.1 lb/sq ft)^[source]

Power/mass	0.09 hp/lb (0.15 kW/kg)^[source]	0.21 kW/kg (0.13 hp/lb)^[source]

Role	family of two-bladed, single- and twin-engined helicopters ,^[source]	Polish light single-engine multipurpose helicopter^[source]

Source measurement	When the YOH-4A was eliminated by the Army, Bell went about marketing the aircraft. In addition to the image problem, the helicopter lacked cargo space and only provided cramped seating for three passengers. The solution was a redesigned fuselage, sleeker and aesthetically appealing, adding 16 ft 3 (0.45 m 3 ) of cargo space in the process. A Bell executive contributed to the redesign by drawing two lines on a sketch extending the fuselage to where it meets the tail. The redesign was designated Bell 206A, and Bell President Edwin J. Ducayet named it the JetRanger , denoting an evolution from the popular Model 47J Ranger .^[source]Bell 206 · Development / JetRanger; only the objects and conditions stated in this passage The 206L LongRanger is a stretched variant with seating for seven. The fuselage, stretched a total of 30 inches (760 mm), adds two rear-facing seats between the front and rear seats. Since 1975, Bell has produced more than 1,700 LongRangers across all variants. In 1981, a military version, the 206L TexasRanger was released. The original 206L used an Allison 250 -C20R engine, and a series of model upgrades replaced this engine with more powerful versions; the 206L-1 used a 250-C28, and the 206L-3 and 206L-4 used the 250-C30P.^[source]Bell 206 · Development / LongRanger; only the objects and conditions stated in this passage In both applications, the 250-C30P is derated from 650 hp for takeoff and 501 hp continuous. The 206L-3 is transmission-limited to 435 hp for take-off, and the 206L-4 is transmission-limited to 495 hp. The derating of the C30P produces an advantage in hot-day and high-altitude operations, as it can produce the rated horsepower at higher altitudes and temperatures where applications that use the maximum rating of the engine at sea level suffer accelerated performance deterioration with increases in temperature and altitude. The 206L-3 and L-4 have not been offered in a twin configuration under those model designations.^[source]Bell 206 · Development / LongRanger; only the objects and conditions stated in this passage In 2007, Bell announced an upgrade program for the 206L-1 and 206L-3 designed to modify the aircraft to the 206L-4 configuration; modified aircraft are designated 206L-1+ and 206L-3+. Modifications include strengthened structural components (including a new tailboom), improved transmission, upgraded engine for the L-1, all of which result in a maximum gross weight increase of 300 pounds and increased performance.^[source]Bell 206 · Development / LongRanger; only the objects and conditions stated in this passage The basic shape and design of the JetRanger remained unchanged since 1967, but Bell introduced the 206B JetRanger II in 1971. In 1977, the 206B-3 JetRanger III was introduced with its modified tail rotor and more powerful engine. The JetRanger is popular with news media for traffic and news reporting. The LongRanger is commonly used as an air ambulance and as a corporate transport. On September 1, 1982, pilots H. Ross Perot, Jr. and Jay Coburn departed Dallas, Texas in the " Spirit of Texas ", a Bell 206L-1 (N3911Z). They returned on 30 September, 29 days and 3 hours later, completing the first around-the-world helicopter flight.^[source]Bell 206 · Operational history; only the objects and conditions stated in this passage On July 22, 1994, Ron Bower landed his 206B-3 (N206AJ) at Hurst, Texas , setting a new record for around-the-world flight by a helicopter. Bower had departed on June 24 and returned 24 days, 4 hours, 36 minutes and 24 seconds later, averaging 35.62 knots (40.99 mph; 65.97 km/h). Bower had added a 91-US-gallon (340 L) auxiliary fuel tank, which doubled the JetRanger III's range.^[source]Bell 206 · Operational history; only the objects and conditions stated in this passage Upgraded Allison 250-C20J engine and added 2 inches (51 mm) to tail rotor diameter for yaw control.^[source]Bell 206 · Variants / Civilian; only the objects and conditions stated in this passage 137 commercial Bell 206B-3s purchased in 1993 as the primary and instrument helicopter trainer for the US Army at Fort Rucker , Alabama. 35 in VFR configuration and 102 in IFR configuration. The US Army has 181 units as of 2026, of which 121 are in VFR configuration and 60 are in IFR configuration. All TH-67s display US registrations ("N" numbers) and are operated as public use aircraft.^[source]Bell 206 · Variants / Military; only the objects and conditions stated in this passage Capacity: 4 passengers^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage Length: 38 ft 9.5 in (11.824 m) including rotors^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage Fuselage length: 31 ft 2 in (9.50 m)^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage Height: 9 ft 6.5 in (2.908 m)^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage Interior dimensions: 7 ft 2 in (2.18 m) length, by 4 ft 2 in (1.27 m) width, by 4 ft 3 in (1.30 m) height, plus 16 ft 3 (453 L) baggage compartment^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage Empty weight: 1,455 lb (660 kg)^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage Max takeoff weight: 3,200 lb (1,451 kg)^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage Powerplant: 1 × Allison 250-C20 turboshaft engine, 400 hp (298 kW)^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage Main rotor diameter: 33 ft 4 in (10.16 m)^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage Main rotor area: 873 sq ft (81.1 m 2 )^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage Maximum speed: 122 kn (140 mph, 226 km/h) at MTOW (sea level)^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage Maximum speed at 5,000 ft: 116 kn (133 mph; 215 km/h) at MTOW^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage Cruise speed: 120 kn (140 mph, 220 km/h) at MTOW, 5,000 feet^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage Range: 337 nmi (388 mi, 624 km) at MTOW, 5,000 feet, cruise speed, no reserves^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage Service ceiling: 20,000 ft (6,100 m) at MTOW^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage Rate of climb: 1,350 ft/min (6.9 m/s)^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage	The original design for the SW-4 called for it to be powered by a 300 kW (400 shp ) PZL Rzeszow GTD350 turboshaft engine, as featured upon the prototype mockup.^[source]PZL SW-4 Puszczyk · Development / Origins; only the objects and conditions stated in this passage According to PZL-Swidnik, the early SW-4 could reach the rated top speed of about 240 km/h (130 kn ) and a max range with auxiliary fuel tank about 900 km (485 nmi ).^[source]PZL SW-4 Puszczyk · Development / Origins; only the objects and conditions stated in this passage PZL-Świdnik's parent company, AgustaWestland chose to use the SW-4 as the basis for an optionally manned rotorcraft, the PZL-Świdnik SW-4 Solo. In 2011, development of an optionally-manned demonstrator began. The SW-4 Solo was first was shown at the MSPO 2012 in Poland as "SW-4 Solo" RUAS/OPH platform (Rotorcraft Unmanned Air System/Optionally Piloted Helicopter). In 2013, AgustaWestland was given a Royal Navy contract for the SW-4 Solo's development as part of the UK's RWUAS (Rotary Wing Unmanned Air System) Capability Concept Demonstrator (CCD) programme. Development of the SW-4 Solo is also being supported by the Italian Ministry of Defence 's Directorate for Air Armaments under the Italian National Military Research Plan. By September 2015, the SW-4 Solo had performed a total of 26 demonstration flights, which included simulated shipboard integration tests. In November 2015, AgustaWestland stated that the SW-4 Solo was "ready for sale".^[source]PZL SW-4 Puszczyk · Development / Further development; only the objects and conditions stated in this passage The SW-4 is powered by a single 335 kW (450 shp ) (283 kW/380 shp max continuous rated) Rolls-Royce Model 250C20R/2 turboshaft engine, which drives the rotorcraft's three-blade main rotor and two-blade tail rotor. An alternative engine is provided in the form of the 460 kW (615 shp) Pratt & Whitney Canada PW200 /9 turboshaft engine. The main rotor is fully articulated and the rotor blades on both the main and tail rotors are composed of composite materials. The SW-4 uses hydraulic flight controls, the rotorcraft has been promoted as possessing excellent flight controls, and can be flown in both day and night visual flight rules conditions.

Source measurement

When the YOH-4A was eliminated by the Army, Bell went about marketing the aircraft. In addition to the image problem, the helicopter lacked cargo space and only provided cramped seating for three passengers. The solution was a redesigned fuselage, sleeker and aesthetically appealing, adding 16 ft 3 (0.45 m 3 ) of cargo space in the process. A Bell executive contributed to the redesign by drawing two lines on a sketch extending the fuselage to where it meets the tail. The redesign was designated Bell 206A, and Bell President Edwin J. Ducayet named it the JetRanger , denoting an evolution from the popular Model 47J Ranger .^[source]Bell 206 · Development / JetRanger; only the objects and conditions stated in this passage

The 206L LongRanger is a stretched variant with seating for seven. The fuselage, stretched a total of 30 inches (760 mm), adds two rear-facing seats between the front and rear seats. Since 1975, Bell has produced more than 1,700 LongRangers across all variants. In 1981, a military version, the 206L TexasRanger was released. The original 206L used an Allison 250 -C20R engine, and a series of model upgrades replaced this engine with more powerful versions; the 206L-1 used a 250-C28, and the 206L-3 and 206L-4 used the 250-C30P.^[source]Bell 206 · Development / LongRanger; only the objects and conditions stated in this passage

In both applications, the 250-C30P is derated from 650 hp for takeoff and 501 hp continuous. The 206L-3 is transmission-limited to 435 hp for take-off, and the 206L-4 is transmission-limited to 495 hp. The derating of the C30P produces an advantage in hot-day and high-altitude operations, as it can produce the rated horsepower at higher altitudes and temperatures where applications that use the maximum rating of the engine at sea level suffer accelerated performance deterioration with increases in temperature and altitude. The 206L-3 and L-4 have not been offered in a twin configuration under those model designations.^[source]Bell 206 · Development / LongRanger; only the objects and conditions stated in this passage

In 2007, Bell announced an upgrade program for the 206L-1 and 206L-3 designed to modify the aircraft to the 206L-4 configuration; modified aircraft are designated 206L-1+ and 206L-3+. Modifications include strengthened structural components (including a new tailboom), improved transmission, upgraded engine for the L-1, all of which result in a maximum gross weight increase of 300 pounds and increased performance.^[source]Bell 206 · Development / LongRanger; only the objects and conditions stated in this passage

The basic shape and design of the JetRanger remained unchanged since 1967, but Bell introduced the 206B JetRanger II in 1971. In 1977, the 206B-3 JetRanger III was introduced with its modified tail rotor and more powerful engine. The JetRanger is popular with news media for traffic and news reporting. The LongRanger is commonly used as an air ambulance and as a corporate transport. On September 1, 1982, pilots H. Ross Perot, Jr. and Jay Coburn departed Dallas, Texas in the " Spirit of Texas ", a Bell 206L-1 (N3911Z). They returned on 30 September, 29 days and 3 hours later, completing the first around-the-world helicopter flight.^[source]Bell 206 · Operational history; only the objects and conditions stated in this passage

On July 22, 1994, Ron Bower landed his 206B-3 (N206AJ) at Hurst, Texas , setting a new record for around-the-world flight by a helicopter. Bower had departed on June 24 and returned 24 days, 4 hours, 36 minutes and 24 seconds later, averaging 35.62 knots (40.99 mph; 65.97 km/h). Bower had added a 91-US-gallon (340 L) auxiliary fuel tank, which doubled the JetRanger III's range.^[source]Bell 206 · Operational history; only the objects and conditions stated in this passage

Upgraded Allison 250-C20J engine and added 2 inches (51 mm) to tail rotor diameter for yaw control.^[source]Bell 206 · Variants / Civilian; only the objects and conditions stated in this passage

137 commercial Bell 206B-3s purchased in 1993 as the primary and instrument helicopter trainer for the US Army at Fort Rucker , Alabama. 35 in VFR configuration and 102 in IFR configuration. The US Army has 181 units as of 2026, of which 121 are in VFR configuration and 60 are in IFR configuration. All TH-67s display US registrations ("N" numbers) and are operated as public use aircraft.^[source]Bell 206 · Variants / Military; only the objects and conditions stated in this passage

Capacity: 4 passengers^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage

Length: 38 ft 9.5 in (11.824 m) including rotors^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage

Fuselage length: 31 ft 2 in (9.50 m)^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage

Height: 9 ft 6.5 in (2.908 m)^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage

Interior dimensions: 7 ft 2 in (2.18 m) length, by 4 ft 2 in (1.27 m) width, by 4 ft 3 in (1.30 m) height, plus 16 ft 3 (453 L) baggage compartment^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage

Empty weight: 1,455 lb (660 kg)^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage

Max takeoff weight: 3,200 lb (1,451 kg)^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage

Powerplant: 1 × Allison 250-C20 turboshaft engine, 400 hp (298 kW)^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage

Main rotor diameter: 33 ft 4 in (10.16 m)^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage

Main rotor area: 873 sq ft (81.1 m 2 )^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage

Maximum speed: 122 kn (140 mph, 226 km/h) at MTOW (sea level)^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage

Maximum speed at 5,000 ft: 116 kn (133 mph; 215 km/h) at MTOW^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage

Cruise speed: 120 kn (140 mph, 220 km/h) at MTOW, 5,000 feet^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage

Range: 337 nmi (388 mi, 624 km) at MTOW, 5,000 feet, cruise speed, no reserves^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage

Service ceiling: 20,000 ft (6,100 m) at MTOW^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage

Rate of climb: 1,350 ft/min (6.9 m/s)^[source]Bell 206 · Specifications (206B Jetranger II); only the objects and conditions stated in this passage

The original design for the SW-4 called for it to be powered by a 300 kW (400 shp ) PZL Rzeszow GTD350 turboshaft engine, as featured upon the prototype mockup.^[source]PZL SW-4 Puszczyk · Development / Origins; only the objects and conditions stated in this passage

According to PZL-Swidnik, the early SW-4 could reach the rated top speed of about 240 km/h (130 kn ) and a max range with auxiliary fuel tank about 900 km (485 nmi ).^[source]PZL SW-4 Puszczyk · Development / Origins; only the objects and conditions stated in this passage

PZL-Świdnik's parent company, AgustaWestland chose to use the SW-4 as the basis for an optionally manned rotorcraft, the PZL-Świdnik SW-4 Solo. In 2011, development of an optionally-manned demonstrator began. The SW-4 Solo was first was shown at the MSPO 2012 in Poland as "SW-4 Solo" RUAS/OPH platform (Rotorcraft Unmanned Air System/Optionally Piloted Helicopter). In 2013, AgustaWestland was given a Royal Navy contract for the SW-4 Solo's development as part of the UK's RWUAS (Rotary Wing Unmanned Air System) Capability Concept Demonstrator (CCD) programme. Development of the SW-4 Solo is also being supported by the Italian Ministry of Defence 's Directorate for Air Armaments under the Italian National Military Research Plan. By September 2015, the SW-4 Solo had performed a total of 26 demonstration flights, which included simulated shipboard integration tests. In November 2015, AgustaWestland stated that the SW-4 Solo was "ready for sale".^[source]PZL SW-4 Puszczyk · Development / Further development; only the objects and conditions stated in this passage

The SW-4 is powered by a single 335 kW (450 shp ) (283 kW/380 shp max continuous rated) Rolls-Royce Model 250C20R/2 turboshaft engine, which drives the rotorcraft's three-blade main rotor and two-blade tail rotor. An alternative engine is provided in the form of the 460 kW (615 shp) Pratt & Whitney Canada PW200 /9 turboshaft engine. The main rotor is fully articulated and the rotor blades on both the main and tail rotors are composed of composite materials. The SW-4 uses hydraulic flight controls, the rotorcraft has been promoted as possessing excellent flight controls, and can be flown in both day and night visual flight rules conditions.