SOCATA TBM

https://en.wikipedia.org/wiki/SOCATA_TBM

The SOCATA TBM (now Daher TBM) is a family of high performance single-engine
turboprop light business and utility aircraft manufactured by Daher. It was
originally collaboratively developed between the American Mooney Airplane
Company and French light aircraft manufacturer SOCATA.

The design of the TBM family originates from the Mooney 301, a comparatively
low-powered and smaller prototype Mooney developed in the early 1980s. Following
Mooney's acquisition by French owners, Mooney and SOCATA held a series of
in-depth discussions on the potential for co-developing a new enlarged turboprop
design derived from the earlier 301; these resulted in the formation of a joint
venture for the purpose of developing and manufacturing the envisioned aircraft,
which was designated as the TBM 700. From the onset, emphasis was placed upon
the design's speed, altitude, and reliability. Upon its entry onto the market in
1990, it held the distinction of being the first high-performance single-engine
passenger/cargo aircraft to enter production.

Shortly after launch, the TBM 700 was a market success, which quickly led to the
production of multiple variants and improved models, often incorporating more
powerful engines and new avionics, amongst other features. The TBM 850 is the
production name assigned to the TBM 700N, an improved version of the aircraft
powered by a single Pratt & Whitney PT6A-66D. In March 2014, an aerodynamically
refined version of the TBM 700N, marketed as the TBM 900, was made available.

Origins

In the early 1980s, the Mooney Airplane Company of Kerrville, Texas, designed a
six-seat pressurised light aircraft, powered by a single 360 hp (268 kW) piston
engine, which they designated the Mooney 301. On 7 April 1983, the prototype 301
conducted its maiden flight. During 1985, the Mooney Aircraft Company was
acquired by new French owners, who promptly took an interest in the further
development of the fledgling 301. Coinciding with the company's acquisition,
French light aircraft manufacturer SOCATA, who had identified a vacant market
position for a purpose-built optimised single-engine aircraft capable of fast
personal transport and light cargo duties, identified the piston-powered 301 as
a potential starting point to satisfy this niche.

Accordingly, talks soon commenced between Mooney and SOCATA on the subject of
producing a turboprop-powered derivative of the 301. The product that emerged
from these discussions was a new design, referred to as the TBM 700, which was
considerably heavier than the original 301 while provisioned with more than
twice the available power. The prefix of the designation, TBM, originated from
the initials "TB", which stands for Tarbes, the French city in which SOCATA is
located, while the "M" stands for Mooney. At the time of its conception, while
several aviation companies had studied or were otherwise considering the
development of such an aircraft, the envisioned TBM 700 was the first
high-performance single-engine passenger/cargo aircraft to enter production.
From the onset, key performance criteria were established for the design,
demanding a high level of reliability while also being capable of an unequalled
speed/altitude combination amongst the TBM 700 other single-engined peers.

Consequently, during June 1987, a joint venture, named TBM International, was
established with the aim of completing development of the TBM 700 design and to
perform the manufacture of the new aircraft; the ownership of the joint venture
was divided between Mooney and SOCATA's parent company Aérospatiale. A pair of
separate production lines for the TBM 700 were planned, one located at Mooney's
facility in Kerrville, Texas, which was intended to cater to the American
market, and the other based at SOCATA's factory in Tarbes, which was set to
produce aircraft for customers throughout the rest of the world. However, during
the late 1980s and early 1990s, Mooney was afflicted by persistent fiscal
shortfalls; consequently, in May 1991, Mooney chose to withdraw from
participation in the joint venture, leaving SOCATA as the primary company
involved in the programme.

On 14 July 1988, the first TBM 700 prototype conducted the type's maiden flight.
Flight testing proved that virtually all of the established goals of the design
had been achieved, leading to quick progress towards production. On 31 January
1990, type certification was received from French authorities; it was followed
by the awarding of US Federal Aviation Administration (FAA) certification on 28
August 1990. During early 1990, the first delivery of a TBM 700 occurred; the
first production batch of 50 aircraft were sold out almost instantly. Early
feedback received from operators and pilots was typically positive about the
capabilities of the new aircraft, often praising its speed and generous power
margins amongst other attributes.

Design

The SOCATA TBM is a single-engined turboprop-powered low-wing monoplane, capable
of seating a maximum of seven people. It is composed mainly of aluminium and
steel construction, but with the tail surfaces built of Nomex honeycomb. The
wing features a very effective Fowler flap, comprising 80 per cent of the
trailing edge's span, for the purpose of lowering the aircraft's stall speed.
The TBM 700 is outfitted with a retractable tricycle landing gear arrangement,
newer models feature stronger main landing gear wheels and tougher tyres. The
TBM 900 model features automatic torque limiting for “set and forget” power
management, which is of particularly use during takeoffs; according to Aviation
Week, while this function does reduce the high workload associated with managing
the PT6A engine, it is not as capable as a full FADEC arrangement.


Role
Executive transport and civil utility

National origin
France

Manufacturer
SOCATA
Daher

First flight
14 July 1988

Introduction
1990

Status
In production

Primary users
French Army
French Air Force

Produced
1988–present

Number built
945 (As of October 2019)

Unit cost

TBM910: US$4.07M, TBM930: US$4.346M (2019)

Since its introduction, around 30 have served in commercial aviation and in
October 2018, 17 were still used for the role in 10 companies, mostly in the US,
among a global fleet of 900. In 2017, 57 units were shipped. Daher claims direct
operating costs are $2.48 per nautical mile. Owner-operators fly 90% of all
TBMs, while they account for 20% to 30% of the larger Pilatus PC-12 sales. The
aircraft is used by both private individuals, corporations and charter and hire
companies.

Military operators

France

*French Air Force – 15 in service (2016).
*French Army Light Aviation (ALAT) – 8 in service (2016)


Specifications (TBM 900)

General characteristics
Crew: 1 or 2
Capacity: 4-6 (including flight crew) / 636 kg (1,402 lb) max payload
Length: 10.72 m (35 ft 2 in)
Wingspan: 12.833 m (42 ft 1 in)
Height: 4.355 m (14 ft 3 in)
Wing area: 18 m2 (190 sq ft)
Aspect ratio: 6.4
Airfoil: root: RA 16-43 ; tip: RA 13.3-43
Empty weight: 2,097 kg (4,623 lb)
Max takeoff weight: 3,354 kg (7,394 lb)
Fuel capacity: 1,100 l (290 US gal) usable
Powerplant: 1 × Pratt & Whitney Canada PT6A-66D turboprop engine, 630 kW (850
shp)
Propellers: 5-bladed Hartzell constant-speed propeller

Performance
Maximum speed: 611 km/h (380 mph, 330 kn) maximum cruise at 8,534 m (28,000 ft)
Cruise speed: 467 km/h (290 mph, 252 kn) long-range cruise
Range: 3,304 km (2,053 mi, 1,784 nmi) with max fuel at long-range cruise and
9,449 m (31,001 ft)
Service ceiling: 9,449 m (31,001 ft)
Time to altitude: 9,449 m (31,001 ft) in 18 minutes 45 seconds

Fuel consumption: 208 l/h (55 gal/h; 46 imp gal/h) / 164 kg/h (362 lb/h) at 593
km/h (368 mph; 320 kn) TAS, FL310, normal cruise, at 2,858 kg (6,301 lb)
Take-off run: 726 m (2,382 ft)
Landing run: 741 m (2,431 ft)

Avionics

2 GMA 1347C Dual digital audio controller with integrated marker beacon
receiver, intercom and public address capability on outer side for pilot and
co-pilot
2 GDU 1040A, 10’’ PFD display with three axis flight dynamics, airspeed,
altitude, vertical speed, HSI w/ perspective modes, turn, bank side slip,
NAV/COM frequencies indication and AP annunciation
1 GDU 1500 15’’ multi-function display with engine (w/ optimum TRQ setting
display), pressurization, electrical, fuel, flaps and trims indication, Crew
Alerting System (CAS), aircraft synoptics and super large navigation mapping
system.
2x GIA 63W Nav/Com/ILS/WAAS GPS
2x GEA 71 Engine and airframe interface unit
2x GRS 77 Attitude and Heading Reference System (AHRS)
2x GMU 44 triaxial magnetometer
2x GDC 74B digital air-data computers with dual probe system
1x GTX33 Mode S transponder with Extended Squitter (ES)
1x GCU 475 remote FMS control panel conveniently located on the central console
1x GMC 710 autopilot mode controller located in upper central panel
4x GSA 81 torque flight servos (yaw, pitch, pitch trim and roll)
1x GTA 82 adapter for yaw auto trim device
Digital Backup instrumentation altitude, airspeed and altimeter indicator



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