Piper PA-31 Navajo

PA-31 Navajo cabin

The 30th production Navajo, fitted with two-bladed propellers and early two-part airstair cabin entry door (without the third door, introduced later)

PA-31P Pressurized Navajo, modified with winglets

PA-31-350 Chieftain in service with Air South West, at Dublin Airport in 1994

1980 PA-31-350 Navajo Chieftain

PA-31P-350 Mojave

At the request of company founder William T. Piper, Piper began development of a six- to eight-seat twin-engined corporate and commuter transport aircraft in 1962 under the project name Inca.[2][6] The type, now designated the PA-31 and looking like a scaled-up Twin Comanche, was officially announced in late 1964 after its first flight on 30 September that year.[1][6] It was a low-wing monoplane with a conventional tail, powered by two 310 hp (231 kW) Lycoming TIO-540-A turbocharged engines in so-called "tiger shark" cowlings, a feature shared with the Twin Comanche and also the PA-23 Aztec.[6][7][8] As testing proceeded two cabin windows were added to each side of the fuselage and the engines moved further forward.[8][9] The PA-31, now named "Navajo" after a Native American tribe, was not certified by the Federal Aviation Administration (FAA) until 24 February 1966, and deliveries did not begin until the following year, after the type was recertified in mid-1966 with an increase in maximum takeoff weight (MTOW) from 6,200 lb (2,812 kg) to 6,500 lb (2,948 kg).[2][10]

The PA-31-300 was the next model, certified by the FAA in June 1967.[10] This model was the only one of the PA-31 series not to have turbocharged engines. A pair of 300 hp (224 kW) Lycoming IO-540-M1A5 engines were fitted to the PA-31-300, driving two-bladed propellers.[10] Following the introduction of the PA-31-300 the turbocharged model began to be known unofficially as the PA-31-310. The PA-31-300 was only produced in 1968 and 1969 and had the smallest production total for any PA-31 series model, with only 14 aircraft built.[2][11]

The next member of the family was also Piper's first pressurized aircraft, the PA-31P Pressurized Navajo, certified in late 1969.[12] Development of the PA-31P had begun in January 1966, before the FAA had awarded the PA-31 a type certificate.[13] The PA-31P was powered by 425 hp (317 kW) Lycoming TIGO-541-E engines and compared to earlier models had a longer nose, fewer and smaller windows, 25 US gal (95 l) fuel tanks in the engine nacelles and a one-piece airstair cabin entry door instead of the split pair of doors on the unpressurized models.[2][12][13] MTOW was greatly increased at 7,800 lb (3,538 kg).[12] Also known unofficially as the PA-31P-425, the PA-31P was produced from 1970 to 1977.[2]

In 1971 Piper introduced improvements to the PA-31 model. The Navajo B featured air conditioning, increased baggage space achieved by the addition of storage lockers in the rear part of extended nacelles, a third door next to the cabin entry doors to facilitate the loading of baggage, and an optional separate door for the pilot to enter the cockpit.[3][14]

In September 1972, Piper unveiled the PA-31-350 Navajo Chieftain, a stretched version of the Navajo B with more powerful engines and counter-rotating propellers to prevent critical engine handling problems.[15] The fuselage was lengthened by 2 ft 0 in (0.61 m), allowing for up to ten seats in total.[10][15] Variants of the Lycoming TIO-540 developing 350 hp (261 kW) were fitted to the Chieftain, with an opposite-rotation LTIO-540 installed on the right-hand wing; MTOW was increased to 7,000 lb (3,175 kg).[10] The Chieftain's introduction was delayed by a flood at Piper's factory at Lock Haven, Pennsylvania caused by Hurricane Agnes, and deliveries did not commence until 1973.[15][16] In 1974, Piper used a Navajo B as the basis for developing a new model, the PA-31-325 Navajo C/R.[17] The Navajo C/R had lower-power versions of the counter-rotating engines of the Chieftain, rated at 325 hp (242 kW).[10] After certification of the PA-31-325 in May 1974, production commenced in the 1975 model year.[17] The Navajo B was also superseded in the 1975 model year, by the Navajo C version of the PA-31 model.[17]

Piper established its T1000 Airliner Division in May 1981 at its Lakeland, Florida factory.[18] There were two aircraft in the T1000 series. The T1020, or more accurately the PA-31-350T1020 was a PA-31-350 Chieftain optimized for and marketed for the commuter airline market. It featured reduced fuel capacity compared to the standard Chieftain, with the 40 US gal (151 L) auxiliary fuel tanks in each wing of the Chieftain not fitted to the T1020.[10] It also had reduced baggage capacity (600 lb (272 kg) maximum instead of the Chieftain's 700 lb (318 kg) maximum) and up to eleven seats.[10] The first T1020 was delivered in December 1981.[19] The second aircraft in the T1000 stable was the T1040 – the PA-31T3 model. The T1040 was a hybrid, featuring the main fuselage of the PA-31-350T1020 with the nose and tail of the PA-31T1 Cheyenne I.[20] The wings were similar to the Cheyenne I's, but with reduced fuel capacity and baggage lockers in the engine nacelles similar to those of the Chieftain.[12] An optional underbelly cargo pod was also available.[12][20] The Pratt & Whitney Canada PT6A-11 turboprop engines were the same as those of the Cheyenne I.[12] Deliveries of the T1040 began in July 1982.[19] A T1050 variant with a fuselage stretch of 11 ft 6 in (3.51 m) and seating capacity for 17 was proposed as a factory conversion of existing aircraft, but did not proceed.[20]

The last member of the PA-31 family to enter production was the PA-31P-350 Mojave. Like the T1040 the Mojave was a hybrid, but whereas the T1040 was essentially a turboprop Chieftain the Mojave was more or less a piston-engined version of the Cheyenne.[21] The Mojave combined the fuselage of the Cheyenne I with the tail of the Chieftain.[21] The wings were similar to the Chieftain's, but with greater structural strength, a 4 ft (1.2 m) increase in wingspan and greater fuel capacity of 243 US gal (920 l).[21] The engines were slightly different variants of the Chieftain's TIO-540 and LTIO-540, being fitted with intercoolers, and like the Chieftain, had baggage lockers on the rear part of the nacelles.[21] The Mojave's MTOW of 7,200 lb (3,266 kg) was 200 lb (91 kg) higher than the Chieftain's.[10][12] Certified in 1983, like the T1020 and T1040 the Mojave was introduced at a time of economic recession and was produced only in 1983 and 1984; combined production of the T1020, T1040 and Mojave amounted to fewer than 100 aircraft.[12][16][20] Two experimental PA-31-353s were also built in the mid-1980s.[16]

PA-31 Navajo

Initial production version, also known unofficially as the PA-31-310.[2][10]

PA-31-300 Navajo

Variant of the Navajo with normally aspirated engines; 14 built.[2][11]

PA-31 Navajo B

Marketing name for 1971 improved variant with 310 hp (231 kW) Lycoming TIO-540-E turbo-charged piston engines, new airconditioning and optional pilot access door and optional wide utility door.[3]

PA-31 Navajo C

Marketing name for 1974 improved variant with 310 hp (231 kW) Lycoming TIO-540-A2C engines and other minor improvements.[3]

PA-31P Pressurized Navajo

Pressurized version of the PA-31 Navajo, powered by two 425-hp (317-kW) Lycoming TIGO-541-E1A piston engines.[2][12]

PA-31-325 Navajo

Referred to as the "Navajo C/R" for Counter-rotating; variant of Navajo with counter-rotating engines introduced with the PA-31-350 Chieftain. 325 hp (242 kW) Lycoming TIO-540 / LTIO-540 engines

PA-31-350 Chieftain

Stretched version of the Navajo with more powerful 350-hp (261-kW) counter-rotating engines (a Lycoming TIO-540 and a Lycoming LTIO-540) to eliminate critical engine issues.

PA-31P-350 Mojave

Piston-engined variant of the PA-31T1 Cheyenne I; 50 aircraft built.[12]

PA-31-350T1020

Also known as the T1020/T-1020; variant of the PA-31-350 Chieftain optimised for commuter airline use, with less baggage and fuel capacity and increased seating capacity (nine passengers). First flight September 25, 1981. 21 built.[10][25][26]

PA-31T3

Also known as the T1040/T-1040; turboprop-powered airliner with fuselage of the PA-31-350T1020, and wings, tail and Pratt & Whitney Canada PT6A-11 engines of PA-31T Cheyenne. First flight July 17, 1981. 24 built.[16][27]

PA-31-353

Experimental version of PA-31-350; two built.[16]

EMB 820C, license-built Chieftain

T1050

Unbuilt airliner variant with fuselage lengthened by 11 ft 6 in (3.51 m) compared to the PA-31-350.

EMB 820C

Version of Chieftain built under license by Embraer in Brazil.

Neiva Carajá

Turboprop conversion of EMB 820C, fitted with two Pratt & Whitney Canada PT6A-27 engines flat-rated to 550shp. The Carajá's MTOW of 8,003 pounds (3,630 kg) was 1,000 pounds (454 kg) more than that of the Chieftain.[24]

PA-31-325 Navajo Panther conversion

Colemill Panther

Re-engined Navajo with 350 hp (261 kW) Lycoming TIO-540-J2B engines, four-blade Hartzell "Q-Tip" propellers and optional winglets. Conversion designed by Colemill Enterprises of Nashville, Tennessee.[28][29] The supplemental type certificates (STCs) were subsequently sold to Mike Jones Aircraft Sales, which continues to convert PA-31, PA-31-325 and PA-31-350 variants with Colemill-developed features.[30][31]

Spain

• A PA-31P Pressurized Navajo formerly operated by the Spanish Air Force is on display at the Museo del Aire in Madrid.[37]

Piper PA-31 Navajo instrument panel

PA-31-350 Navajo Chieftain

Data from Jane's All The World's Aircraft 1976–77 [39]

General characteristics

• Crew: 1 or 2
• Capacity: 5 to 7 passengers
• Length: 32 ft 7 ¹⁄₂ in (9.94 m)
• Wingspan: 40 ft 8 in (12.40 m)
• Height: 13 ft 0 in (3.96 m)
• Wing area: 229 sq ft (21.3 m²)
• Airfoil: NACA 63₄415 at root, 63₁212
• Empty weight: 3,930 lb (1,783 kg)
• Max takeoff weight: 6,500 lb (2,948 kg)
• Fuel capacity: 190 US gal (160 imp gal; 720 L) total, 187 US gal (156 imp gal; 710 L) useable
• Powerplant: 2 × Lycoming TIO-540-A air-cooled six-cylinder horizontally opposed piston engine, 310 hp (230 kW) each
• Propellers: 3-bladed Hartzell metal, fully feathering propellers, 6 ft 8 in (2.03 m) diameter

Performance

• Maximum speed: 261 mph (420 km/h, 227 kn) at 15,000 ft (4,600 m)
• Cruise speed: 238 mph (383 km/h, 207 kn) at 20,000 ft (6,100 m) (econ. cruise)
• Stall speed: 73 mph (117 km/h, 63 kn) (flaps down)
• Never exceed speed: 272 mph (438 km/h, 236 kn) [10]
• Range: 1,165 mi (1,875 km, 1,012 nmi) at 20,000 ft (6,100 m) (econ. cruise speed)
• Service ceiling: 26,300 ft (8,000 m)
• Rate of climb: 1,445 ft/min (7.34 m/s)

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