Grob G 115 vs SIAI-Marchetti SF.260: Specs Compared

Grob G 115 — licensed reference photograph

ATrainer aircraft

Grob G 115

Basic trainer

Credit

Alan Wilson · CC BY-SA 2.0 · Resized · CC BY-SA 2.0 · Source ↗ · Modified

SIAI-Marchetti SF.260 — licensed reference photograph

BTrainer aircraft

SIAI-Marchetti SF.260

Trainer /Light attack

Credit

Rob Schleiffert · CC BY-SA 4.0 · Resized · CC BY-SA 4.0 · Source ↗ · Modified

First system

Second system

At a glance

Side by side

Length comparisonOne shared metre scale

Grob G 115G 115E · Length

7.79 m

Length source ↗

SIAI-Marchetti SF.260SF-260M · Length

7.1 m

Length source ↗

Lengths retain their source configuration and measurement scope.

Measured figures

Head to head

25 of 37 rows sourced on both sides

7.79mG 115E · Length

7.1mSF-260M · Length

LengthScopes differ

All recorded figures & sources

7.79 m

G 115E · Length

Single source

7.79 m (25 ft 7 in)^[source]

7.1 m

SF-260M · Length

Single source

7.10 m (23 ft 4 in)^[source]

10mG 115E · Wingspan

8.35mSF-260M · over tip-tanks

WingspanScopes differ

All recorded figures & sources

10 m

G 115E · Wingspan

Single source

10.00 m (32 ft 10 in)^[source]

8.35 m

SF-260M · over tip-tanks

Single source

8.35 m (27 ft 5 in) over tip-tanks^[source]

2.82mG 115E · Height

2.41mSF-260M · Height

HeightScopes differ

All recorded figures & sources

2.82 m

G 115E · Height

Single source

2.82 m (9 ft 3 in)^[source]

2.41 m

SF-260M · Height

Single source

2.41 m (7 ft 11 in)^[source]

990kg

1.2t

MassScopes differ

All recorded figures & sources

670 kg

Empty; G 115E · Empty weight

Single source

990 kg

Maximum take-off; G 115E · Max takeoff weight

Single source

670 kg (1,477 lb)^[source]

990 kg (2,183 lb)^[source]

755 kg

Empty; SF-260M · Empty weight

Single source

1,140 kg

Gross; SF-260M · Gross weight

Single source

1,200 kg

Maximum take-off; SF-260M · Max takeoff weight

Single source

755 kg (1,664 lb)^[source]

1,140 kg (2,513 lb)^[source]

1,200 kg (2,646 lb)^[source]

2G 115E · Crew

2SF-260M · Crew

CrewScopes differ

All recorded figures & sources

2 people

G 115E · Crew

Single source

2^[source]

2 people

SF-260M · Crew

Single source

2^[source]

250km/hMaximum; G 115E · Maximum speed

333km/hMaximum; SF-260M · at sea level

SpeedScopes differ

All recorded figures & sources

178 km/h

Cruise; G 115E · long range cruising speed

Single source

250 km/h

Maximum; G 115E · Maximum speed

Single source

250 km/h (160 mph, 130 kn)^[source]

178 km/h (111 mph, 96 kn) (long range cruising speed)^[source]

300 km/h

Cruise; SF-260M · at 75% power at 1,500 m (4,900 ft)

Single source

333 km/h

Maximum; SF-260M · at sea level

Single source

333 km/h (207 mph, 180 kn) at sea level^[source]

300 km/h (190 mph, 160 kn) at 75% power at 1,500 m (4,900 ft)^[source]

1,150km

1,650kmSF-260M · 2 crew, with maximum fuel

RangeScopes differ

All recorded figures & sources

1,150 km

G 115E · 45% power at FL 80, 45 min reserves

Single source

1,150 km (710 mi, 620 nmi) (45% power at FL 80, 45 min reserves)^[source]

1,650 km

SF-260M · 2 crew, with maximum fuel

Single source

1,650 km (1,030 mi, 890 nmi) 2 crew, with maximum fuel^[source]

130kW

190kW

PowerScopes differ

All recorded figures & sources

130 kW

G 115E · 1 × Lycoming AEIO-360-B1F/B 4-cylinder air-cooled horizontally-opposed piston engine

Single source

1 × Lycoming AEIO-360-B1F/B 4-cylinder air-cooled horizontally-opposed piston engine, 130 kW (180 hp)^[source]

190 kW

SF-260M · 1 × Textron Lycoming O-540-E4A5 / Textron Lycoming AEIO-540-D4A5 6-cylinder air-cooled horizontally-opposed piston engine

Single source

1 × Textron Lycoming O-540-E4A5 / Textron Lycoming AEIO-540-D4A5 6-cylinder air-cooled horizontally-opposed piston engine, 190 kW (260 hp)^[source]

12.2m²G 115E · Wing area

10.1m²SF-260M · Wing area

Wing areaScopes differ

All recorded figures & sources

12.21 m²

G 115E · Wing area

Single source

12.21 m 2 (131.4 sq ft)^[source]

10.1 m²

SF-260M · Wing area

Single source

10.10 m 2 (108.7 sq ft)^[source]

6,095mG 115E · Service ceiling

4,700mSF-260M · Service ceiling

Service ceilingScopes differ

All recorded figures & sources

6,095 m

G 115E · Service ceiling

Single source

6,095 m (20,000 ft)^[source]

4,700 m

SF-260M · Service ceiling

Single source

4,700 m (15,300 ft)^[source]

5.3m/sG 115E · 1,050 ft/min

7.6m/sSF-260M · 1,500 ft/min

Rate of climbScopes differ

All recorded figures & sources

5.3 m/s

G 115E · 1,050 ft/min

Single source

5.3 m/s (1,050 ft/min)^[source]

7.6 m/s

SF-260M · 1,500 ft/min

Single source

7.6 m/s (1,500 ft/min)^[source]

Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.

Configuration

Details

Grob G 115 and SIAI-Marchetti SF.260 configuration
Specification	Grob G 115	SIAI-Marchetti SF.260
Type	Basic trainer^[source]	Trainer /Light attack^[source]
Manufacturer	Grob Aircraft^[source]	SIAI-Marchetti Aermacchi Alenia Aermacchi Leonardo S.p.A.^[source]
Status	active^[source]	In service^[source]
Primary users	Royal Air Force Egyptian Air Force Finnish Air Force Royal Navy Army Air Corps (UK)^[source]	Italian Air Force Libyan Air Force Philippine Air Force Belgian Air Force^[source]
Manufactured	1985–present^[source]	1964–2017^[source]
Introduction date	1999^[source]	April 1966 (FAA certification)^[source]
First flight	November 1985^[source]	15 July 1964^[source]
Fuel capacity	143 L (31 imp gal; 38 US gal) usable^[source]	internal: 235 L (62 US gal; 52 imp gal) usable^[source]
Aspect ratio	8.2:1^[source]	6.3:1 excluding tip-tanks^[source]
Airfoil	Eppler 696^[source]	root: NACA 641 1 -212 (modified); tip: NACA 641 1 -210 (modified)^[source]
Propellers	3-bladed Hoffmann HO-V343K-V/183GY Constant-speed propeller , 1.83 m (6 ft 0 in) diameter^[source]	2-bladed Hartzell HC-C2YK-1BF/8477-8R constant-speed propeller , 1.93 m (6 ft 4 in) diameter^[source]
Stall speed	91 km/h (57 mph, 49 kn) (60 degree flap)^[source]	126 km/h (78 mph, 68 kn) flaps and landing gear down^[source]
Never exceed speed	341 km/h (212 mph, 184 kn)^[source]	436 km/h (271 mph, 235 kn)^[source]
g limits	+ 6.0/ - 3.0^[source]	+6 -3 at max aerobatic T-O weight^[source]
Country of origin	Deutschland^[source]Country of design · Entwurfsland	—
Designer	—	Stelio Frati^[source]
Number built	—	900 (2012)^[source]
Capacity	—	1 passenger^[source]
Time to altitude	—	1,500 m (4,900 ft) in 4 minutes 2,300 m (7,500 ft) in 6 minutes 50 seconds 3,000 m (9,800 ft) in 10 minutes^[source]
Take-off run	—	384 m (1,260 ft)^[source]
Landing run	—	345 m (1,132 ft)^[source]
Take-off run to 15 m (50 ft)	—	606 m (1,988 ft)^[source]
Landing run from 15 m (50 ft)	—	606 m (1,988 ft)^[source]
Role	—	Italian light aircraft^[source]
National origin	—	Italy^[source]
Source measurement	—	The original model of the SF.260 was powered by a single Lycoming O-540 engine, capable of providing 260 hp. The standard engine made use of a carburetor , while a fuel injected engine was available as an optional extra. The SF.260 has been described as having the power to be immune to the gyration-like effects of turbulence and possessing a high rate of climb. During the 1980s, aerospace publication Flying stated the SF.260 to be: "the fastest normally aspirated piston single in production". The SF.260 holds the airspeed records for aircraft in its class over the 100 km (62 mi) and 1,000 km (620 mi) closed circuits. Later-built models often made use of turboprop engines; the initial model to be equipped as such, designated as the SF.260TP , was powered by a single Allison Model 250 engine, flat-rated at 350 shp.^[source]SIAI-Marchetti SF.260 · Design; only the objects and conditions stated in this passage The pilot and up to two passengers (or pilot and one student in trainer versions) are accommodated under a broad, extensively glazed canopy . The pilot, who accesses the aircraft via purpose-built walkways along the wing, would be typically seated on the right-hand side of the cockpit; military pilots are trained to control the aircraft using their right hand on the stick and their left on the throttle.^[source]SIAI-Marchetti SF.260 · Design; only the objects and conditions stated in this passage The SF.260WL was intended for pilot training, but was also used for ground support during the war in Chad . Dozens of Italian pilots served as instructors for Libyan cadets from 1977. Their number decreased in 1982, as they were supplemented by a group of 15 Libyan instructors, who had been trained at SIAI Marchetti's facilities in Italy. Libyan SF.260s played an important role during the country's involvement in Chad. They were used as light ground attack aircraft, using machine gun pods, rockets and bombs. Their first known actions took place in February 1978, when they participated in air strikes on the Chadian army garrison of Faya-Largeau together with Mil Mi-25 helicopters. As a result of the sustained bombardment, the majority of the 5,000 troops deployed there fled, and around 1,500 of them were taken prisoners on February 18.^[source]SIAI-Marchetti SF.260 · Operational history / Libya; only the objects and conditions stated in this passage After continuing the advance towards the south, by late November, pro-Libyan units had reached Dougia, only 60 kilometres north of N'Djamena. Libyan SF.260s were forward-deployed there, together with Mi-25s. On 8 December, these aircraft, joined on 12 December by Tu-22 bombers, D-30 howitzers , and M-46 field guns , started attacking N'Djamena. The week-long bombing caused a huge amount of destruction in the Chadian capital, and a number of civilian casualties that remains unknown today. After Habré fled to Cameroon , resistance collapsed and his surviving fighters escaped to Sudan .^[source]SIAI-Marchetti SF.260 · Operational history / Libya; only the objects and conditions stated in this passage F.250 – first prototype powered by 187 kW (250 hp) Lycoming O-540 -AID. The prototype, regn. I-ZUAR, was destroyed in a crash at Sestri Ponente , Genoa on 7 November 1965.^[source]SIAI-Marchetti SF.260 · Variants / Aviamilano; only the objects and conditions stated in this passage F.260 – two prototypes powered by 194 kW (260 hp) Lycoming O-540-E4A5^[source]SIAI-Marchetti SF.260 · Variants / Aviamilano; only the objects and conditions stated in this passage Royal Thai Air Force , 18 SF-260M (1973–1999)^[source]SIAI-Marchetti SF.260 · Operators / Former military operators; only the objects and conditions stated in this passage Length: 7.10 m (23 ft 4 in)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Wingspan: 8.35 m (27 ft 5 in) over tip-tanks^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Height: 2.41 m (7 ft 11 in)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Wing area: 10.10 m 2 (108.7 sq ft)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Empty weight: 755 kg (1,664 lb)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Gross weight: 1,140 kg (2,513 lb)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Max takeoff weight: 1,200 kg (2,646 lb)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Powerplant: 1 × Textron Lycoming O-540-E4A5 / Textron Lycoming AEIO-540-D4A5 6-cylinder air-cooled horizontally-opposed piston engine, 190 kW (260 hp)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Propellers: 2-bladed Hartzell HC-C2YK-1BF/8477-8R constant-speed propeller , 1.93 m (6 ft 4 in) diameter^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Maximum speed: 333 km/h (207 mph, 180 kn) at sea level^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Cruise speed: 300 km/h (190 mph, 160 kn) at 75% power at 1,500 m (4,900 ft)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Stall speed: 126 km/h (78 mph, 68 kn) flaps and landing gear down^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Never exceed speed : 436 km/h (271 mph, 235 kn)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Range: 1,650 km (1,030 mi, 890 nmi) 2 crew, with maximum fuel^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Service ceiling: 4,700 m (15,300 ft)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Rate of climb: 7.6 m/s (1,500 ft/min)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Take-off run: 384 m (1,260 ft)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Landing run: 345 m (1,132 ft)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Take-off run to 15 m (50 ft): 606 m (1,988 ft)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Landing run from 15 m (50 ft): 606 m (1,988 ft)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

FORCETALLY

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Grob G 115

SIAI-Marchetti SF.260

Type

Basic trainer^[source]

Trainer /Light attack^[source]

Manufacturer

Grob Aircraft^[source]

SIAI-Marchetti Aermacchi Alenia Aermacchi Leonardo S.p.A.^[source]

Status

active^[source]

In service^[source]

Primary users

Royal Air Force Egyptian Air Force Finnish Air Force Royal Navy Army Air Corps (UK)^[source]

Italian Air Force Libyan Air Force Philippine Air Force Belgian Air Force^[source]

Manufactured

1985–present^[source]

1964–2017^[source]

Introduction date

1999^[source]

April 1966 (FAA certification)^[source]

First flight

November 1985^[source]

15 July 1964^[source]

Fuel capacity

143 L (31 imp gal; 38 US gal) usable^[source]

internal: 235 L (62 US gal; 52 imp gal) usable^[source]

Aspect ratio

8.2:1^[source]

6.3:1 excluding tip-tanks^[source]

Airfoil

Eppler 696^[source]

root: NACA 641 1 -212 (modified); tip: NACA 641 1 -210 (modified)^[source]

Propellers

3-bladed Hoffmann HO-V343K-V/183GY Constant-speed propeller , 1.83 m (6 ft 0 in) diameter^[source]

2-bladed Hartzell HC-C2YK-1BF/8477-8R constant-speed propeller , 1.93 m (6 ft 4 in) diameter^[source]

Stall speed

91 km/h (57 mph, 49 kn) (60 degree flap)^[source]

126 km/h (78 mph, 68 kn) flaps and landing gear down^[source]

Never exceed speed

341 km/h (212 mph, 184 kn)^[source]

436 km/h (271 mph, 235 kn)^[source]

g limits

+ 6.0/ - 3.0^[source]

+6 -3 at max aerobatic T-O weight^[source]

Country of origin

Deutschland^[source]Country of design · Entwurfsland

—

Designer

—

Stelio Frati^[source]

Number built

—

900 (2012)^[source]

Capacity

—

1 passenger^[source]

Time to altitude

—

1,500 m (4,900 ft) in 4 minutes 2,300 m (7,500 ft) in 6 minutes 50 seconds 3,000 m (9,800 ft) in 10 minutes^[source]

Take-off run

—

384 m (1,260 ft)^[source]

Landing run

—

345 m (1,132 ft)^[source]

Take-off run to 15 m (50 ft)

—

606 m (1,988 ft)^[source]

Landing run from 15 m (50 ft)

—

606 m (1,988 ft)^[source]

Role

—

Italian light aircraft^[source]

National origin

—

Italy^[source]

Source measurement

—

The original model of the SF.260 was powered by a single Lycoming O-540 engine, capable of providing 260 hp. The standard engine made use of a carburetor , while a fuel injected engine was available as an optional extra. The SF.260 has been described as having the power to be immune to the gyration-like effects of turbulence and possessing a high rate of climb. During the 1980s, aerospace publication Flying stated the SF.260 to be: "the fastest normally aspirated piston single in production". The SF.260 holds the airspeed records for aircraft in its class over the 100 km (62 mi) and 1,000 km (620 mi) closed circuits. Later-built models often made use of turboprop engines; the initial model to be equipped as such, designated as the SF.260TP , was powered by a single Allison Model 250 engine, flat-rated at 350 shp.^[source]SIAI-Marchetti SF.260 · Design; only the objects and conditions stated in this passage

The pilot and up to two passengers (or pilot and one student in trainer versions) are accommodated under a broad, extensively glazed canopy . The pilot, who accesses the aircraft via purpose-built walkways along the wing, would be typically seated on the right-hand side of the cockpit; military pilots are trained to control the aircraft using their right hand on the stick and their left on the throttle.^[source]SIAI-Marchetti SF.260 · Design; only the objects and conditions stated in this passage

The SF.260WL was intended for pilot training, but was also used for ground support during the war in Chad . Dozens of Italian pilots served as instructors for Libyan cadets from 1977. Their number decreased in 1982, as they were supplemented by a group of 15 Libyan instructors, who had been trained at SIAI Marchetti's facilities in Italy. Libyan SF.260s played an important role during the country's involvement in Chad. They were used as light ground attack aircraft, using machine gun pods, rockets and bombs. Their first known actions took place in February 1978, when they participated in air strikes on the Chadian army garrison of Faya-Largeau together with Mil Mi-25 helicopters. As a result of the sustained bombardment, the majority of the 5,000 troops deployed there fled, and around 1,500 of them were taken prisoners on February 18.^[source]SIAI-Marchetti SF.260 · Operational history / Libya; only the objects and conditions stated in this passage

After continuing the advance towards the south, by late November, pro-Libyan units had reached Dougia, only 60 kilometres north of N'Djamena. Libyan SF.260s were forward-deployed there, together with Mi-25s. On 8 December, these aircraft, joined on 12 December by Tu-22 bombers, D-30 howitzers , and M-46 field guns , started attacking N'Djamena. The week-long bombing caused a huge amount of destruction in the Chadian capital, and a number of civilian casualties that remains unknown today. After Habré fled to Cameroon , resistance collapsed and his surviving fighters escaped to Sudan .^[source]SIAI-Marchetti SF.260 · Operational history / Libya; only the objects and conditions stated in this passage

F.250 – first prototype powered by 187 kW (250 hp) Lycoming O-540 -AID. The prototype, regn. I-ZUAR, was destroyed in a crash at Sestri Ponente , Genoa on 7 November 1965.^[source]SIAI-Marchetti SF.260 · Variants / Aviamilano; only the objects and conditions stated in this passage

F.260 – two prototypes powered by 194 kW (260 hp) Lycoming O-540-E4A5^[source]SIAI-Marchetti SF.260 · Variants / Aviamilano; only the objects and conditions stated in this passage

Royal Thai Air Force , 18 SF-260M (1973–1999)^[source]SIAI-Marchetti SF.260 · Operators / Former military operators; only the objects and conditions stated in this passage

Length: 7.10 m (23 ft 4 in)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Wingspan: 8.35 m (27 ft 5 in) over tip-tanks^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Height: 2.41 m (7 ft 11 in)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Wing area: 10.10 m 2 (108.7 sq ft)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Empty weight: 755 kg (1,664 lb)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Gross weight: 1,140 kg (2,513 lb)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Max takeoff weight: 1,200 kg (2,646 lb)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Powerplant: 1 × Textron Lycoming O-540-E4A5 / Textron Lycoming AEIO-540-D4A5 6-cylinder air-cooled horizontally-opposed piston engine, 190 kW (260 hp)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Propellers: 2-bladed Hartzell HC-C2YK-1BF/8477-8R constant-speed propeller , 1.93 m (6 ft 4 in) diameter^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Maximum speed: 333 km/h (207 mph, 180 kn) at sea level^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Cruise speed: 300 km/h (190 mph, 160 kn) at 75% power at 1,500 m (4,900 ft)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Stall speed: 126 km/h (78 mph, 68 kn) flaps and landing gear down^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Never exceed speed : 436 km/h (271 mph, 235 kn)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Range: 1,650 km (1,030 mi, 890 nmi) 2 crew, with maximum fuel^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Service ceiling: 4,700 m (15,300 ft)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Rate of climb: 7.6 m/s (1,500 ft/min)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Take-off run: 384 m (1,260 ft)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Landing run: 345 m (1,132 ft)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Take-off run to 15 m (50 ft): 606 m (1,988 ft)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage

Landing run from 15 m (50 ft): 606 m (1,988 ft)^[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage