IAGSA Aircraft Assessment Guide

AIRCRAFT GUIDANCE TOOL

Introduction

Airborne geophysical surveys present many challenges and risks dependent on the airborne platform utilized in the conduct of the airborne works
Various aircraft models are available world-wide for use in geophysical applications, where some aircraft are better suited to some conditions than others:
- Fit-for-purpose equipment is a fundamental consideration prior to any safe operations
- Safety in the air begins with planning with the right people and equipment on the ground prior to operations
- Choice of the correct aircraft type / platform for the height and terrain types will aide in overall safer operations across the industry
The choice of the RIGHT AIRCRAFT for the RIGHT ENVIRONMENT and TASK is paramount to the safety and success of the program. For example, low-level incidents have significant potential for adverse impacts on human life, property damage, and reputational impacts to the industry and operators alike
There is a belief that decreasing survey height may improve the quality of geophysical data and it is recommended that this be carefully reviewed on a project-by-project basis. Safe survey heights continue to be a cause for concern to the industry, and have manifested in a number of fatal accidents over the years
The intention is to build upon the information provided in Section 2.1.3 of the Safety Manual (Minimum Safe Survey Height) and provide these to both operators and clients alike for their due diligence and consideration
The IAGSA Technical Committee have worked collaboratively to build the Aircraft Guidance Tool (AGT) to assist / guide members with aircraft selection for their surveys

IAGSA Aircraft Guidance Tool Revision 1

Cessna 172

1956 - 1986
1998 - Present

All-metal, four-place, high-wing airplane, fixed tricycle landing gear.

Information

Year of certification	Engine type	Number of Engines	Weight conditions	Model and Engine variants
Model C172 A ~ Q	Piston	Single	Model 172: Max takeoff: 2,450 lbs
1955 - 1982 (latest model before hiatus)				– Lycoming O-300-A/B/C/D (145hp)
				– Lycoming O-320-E2D (150hp)
Model C172 R-S				– Lycoming IO-360-L2A (160 hp)
1996 - Present				– Mod. Lycoming IO-360-L2A (180 hp)

Cessna 180

1956 -1976

The Cessna 180 series is a single-engine high-wing tailwheel all-metal utility monoplane

Information

Year of certification	Engine type	Number of Engines	Weight conditions	Model and Engine variants	IAGSA Operators
Model 180	Piston	Single	MCTOW – 2550 lbs. [1156 kg] – Model 180 – 2650 lbs. (1202 kg) – Model 180B through 180F – 2800 lbs. (1270 kg) - Model 180G,H,J,K	180, 180A, 180B, 180C, 180D, 180E, 180F	EDCON-PRJ (Cloudstreet Flying Service)
Approved December 23, 1952				– Continental O-470-A or O-470-J – Model 180
Model 180A				– Continental O-470-K – Model 180 through 180B
Approved December 17, 1956				– Continental O-470-L or O-470-R – 180C through 180F
Model 180B
Approved August 22, 1958				180G, 180H, 180J, 180K
Model 180C				– Continental O-470-L or O-470-R – Model 180G and 180H
Approved July 8, 1959				– Continental O-470-R or O-470-S – Model 180J
Model 180D				– Continental O-470-U – Model 180K
Approved June 14, 1960
Model 180E
Approved September 21, 1961
Model 180F
Approved June 25, 1962
Model 180G
Approved July 19, 1963
Model 180H
Approved June 17, 1964
Model 180J
Approved October 13, 1972
Model 180K
Approved August 19, 1976

Cessna 206

1962 - 1986
1998 - Present

Single-engine, all-metal, six-place, high-wing (strut braced) airplane, fixed tricycle landing gear.

Information

Year of certification	Engine type	Number of Engines	TODR @ 5000’ ASL (ISA Cond.)	Weight conditions	Model and Engine variants	IAGSA Operators
Model 206 - certified on 19 July 1963	Piston	Single	Ground roll: 1,060 ft* landing roll: 738 ft* C206H takeoff dist: 1,970ft* landing dist: 1,395ft C206H distance to/from 50 obs @ S.L & ISA	C206: Max Takeoff: 3,300lbs - 3,800 (CT206H)	Model 206H	EON Geosciences Inc.
Model U206 - (U "Utility") - 08 Oct 1964					– Lycoming IO-540-AC1A5 2700 RPM (300 hp)
Model P206 - (P - passanger - )08 Oct 1964
…27 varients (link) 1964 ~ 1976					Model T206H
Model 206H - (Stationair) - 26 November 1997					– Lycoming TIO-540-AJ1A 2500 RPM (310 hp)
STC engine conversion: Soloy MKII Turbine 206 -
					Model U206F
					– Continental IO-520F

					STC engine Modification: Soloy MKII Turbine 206
					Rolls-Royce 250-B17/F2

Cessna 210

1957 - 1986

Single-engine, all-metal, six-place, high-wing (cantilever) airplane, Retractable landing gear.

Information

Year of certification	Engine type	Number of Engines	TODR @ 5000’ ASL (ISA Cond.)	Weight conditions	Model and Engine variants
Model 210	Piston	Single	Take off: 2,160 ft Landing: 1,500ft	C210:	Model 210
Approved 1959				MGTW: 4000 lbs	Continental IO-470-E, 260bhp
					Model 210A
Models 210A ~ R, 1961 - 1986					Continental IO-470-E, 260bhp
					Model 210B,C,5,5A
Model P210 (Pressurized Centurion)					Continental IO-470-S, 260bhp
					Model 210D,E,F,G,H
Riely Turbine P-210 (Conversion of Pressurised 210P to a PT6A-112)					Continental IO-520-A 285bhp
					Model T210F,G,H
					Continental TSIO-520-C 285bhp
					Model T210J
					Continental TSIO-520-H 285bhp
					Model 210J
					Continental IO-520-J 285bhp
					Model 210K,L,M,N,R
					Continental IO-520-L 285hp (T/O 5min 300hp)
					Model T210K,L
					Continental TSIO-520-H 285bhp
					Model T210M,N
					Continental TSIO-520-R 285hp (T/O 5min 310hp)
					Model P210N
					Continental TSIO-520-P/ Continental TSIO-520-AF 285hp (T/O 5min 310hp)
					Model P210R,T210R
					Continental TSIO-520-CE 325hp
					Model: Riley Turbine P-210
					Pratt&Whitney Canada PT6A-112 500shp
					Model: P-210
					Rolls-Royce 250-B17F/2

PA-31 Navajo

1967 - 1984

Retractable undercarriage, six- to eight-seat twin-engined corporate and commuter transport aircraft

Information

Year of certification	Engine type	Number of Engines	TODR @ 5000’ ASL (ISA Cond.)	Weight conditions	Model and Engine variants	IAGSA Operators
Model PA-31	Piston	Twin	Take off: 1,312 ft Landing: 1,886 ft	Model PA-31	Model PA-31	Xcalibur Multiphysics
Approved February 24, 1966				Max weight	2x Lycoming TIO-540-A1A, TIO-540-A1B, TIO-540-A2A, TIO-540-A2B, TIO-540-A2C	EON Geosciences Inc.
				6,500 lbs. – Take off; 6,200 lbs. – Landing	(2,575 r.p.m., 310 hp)
Model PA31-300				or 6,500 lbs. – Take off or landing
Approved June 12, 1967				(SN# dependent)	Model PA31-300
					2x Lycoming IO-540-M1A5
Model PA31-325				Model PA31-300	For all operations, 2700 r.p.m. (300 hp)
Approved May 31, 1974.				Max weight 6,000 lbs.
					Model PA31-325
Model PA31-350				Model PA31-325	Lycoming TIO-540-F2BD & LTIO-540 F2BD
Approved May 3, 1972				6,500 lbs. - Takeoff or Landing	(2,575 r.p.m., 325 hp)

				Model PA31-350	Model PA31-350
				Max weight 7,000 lbs. - Takeoff; 7,000 lb. - Landing	Lycoming TIO-540-J2BD, & LTIO 540-J2BD
					Lycoming TIO-540-J2B & LTIO-540-J2B
					(2,575 r.p.m., 350 hp)

PA-23 Aztec

1952 - 1981

Four-to-six-seat twin-engined light aircraft aimed at the general aviation market

Information

Year of certification	Engine type	Number of Engines	TODR @ 5000’ ASL (ISA Cond.)	Weight conditions	Model and Engine variants
Model PA-23	Piston	Twin	Take off: 1,695 ft* Landing: 1,695 ft* * dist to clear a 50' obs	Model PA-23	Model PA-23
Approved January 29, 1954				Max weight 3500 lbs	2x Lycoming O-320 Series
					(Item 113A)
Model PA-23-160				Model PA-23-160	All operations, 2700 r.p.m. (150 hp)
Approved October 14, 1957				Max weight 3,800 lbs.
					Model PA-23-160
Model PA-23-235				Model PA-23-235	2x Lycoming O-320 Series (Item 113B)
Approved January 22, 1962				Max weight 4,800 lbs.	For all operations, 2700 r.p.m. (160 hp)

Model PA-E23-250				Model PA-E23-250	Model PA-23-235
Approved June 21, 1965				Max weight 4,940 lbs. - Landing 4,995 lbs	2x Lycoming O-540 series (Item 113D
				Takeoff Max - zero fuel: 4,400 lbs. (Normally aspirated) 4,500 lbs	All operations, 2575 r.p.m. (235 hp)
Model PA-23-250				Takeoff Max - zero fuel: 4,500 lbs. (Turbocharged)
Approved January 21, 1975					Model PA-E23-250
				Model PA-23-250	2x Lycoming IO-540 series (See Item 113C)
				Max weight 5,200 lbs	For all operations, 2575 r.p.m. (250 hp)
				Takeoff 4,940 lbs. - Landing Max - zero fuel: 4,500 lbs. (turbocharged)
				Takeoff 4,940 lbs. - Landing Max - zero fuel: 4,500 lbs. (turbocharged)	Model PA-23-250
					2 Lycoming I-540 series (See Item 113C)
					All operations 2575 r.p.m. (250 hp)

BN2B Islander

1965 - Present

Twin Engine High-wing cantilever monoplane with a rectangular fuselage and fixed tricycle landing gear, used as a light utility aircraft or regional airliner

Information

Year of certification	Engine type	Number of Engines	TODR @ 5000’ ASL (ISA Cond.)	Weight conditions	Model and Engine variants
Model BN-2	All Piston, with the exception of Model BN-2T-4R (Turbine	Twin	Take off: 1,218 ft Landing: 1650 ft (at sea level in ISA)	Model BN-2	Model BN-2
Approved December 19, 1967				Max Take off and Landing weight: 5700lbs	2x Lycoming O-540-E4C5
					For all operations, 2,700 r.p.m (260 hp.)
Model BN-2A				Model BN-2A
Approved September 5, 1968				Max Take off and Landing weight: 6000lbs	Model BN-2A
					2x Lycoming O-540-E4C5
Model BN-2A-6				Model BN-2A-6	For all operations, 2,700 r.p.m (260 hp.)
Approved October 22, 1970				Max Take off and Landing weight: 6200lbs
					Model BN-2A-6
Model BN-2A-8				Model BN-2A-8	2x Lycoming O-540-E4C5
Approved June 28, 1971				Max Take off and Landing weight: 6200lbs	For all operations 2,700 r.p.m (260 hp.)

Model BN-2A-2				Model BN-2A-2	Model BN-2A-8
Approved June 28, 1971				Max Take off and Landing weight: 6300lbs	2x Lycoming O-540-E4C5
					For all operations 2,700 r.p.m. (260 hp.)
Model BN-2A-9				Model BN-2A-9
Approved May 30, 1972				Max Take off and Landing weight: 6300lbs	Model BN-2A-2
					2x Lycoming IO-540-K1B5
Model BN-2A-3				Model BN-2A-3	For all operations 2,700 r.p.m. (300 hp.)
Approved May 30, 1972				Max Take off and Landing weight: 6300lbs
					Model BN-2A-9
Model BN-2A-20				Model BN-2A-20	2x Lycoming O-540-E4C5
Approved May 16, 1974				Max Take off and Landing weight: 6300lbs	For all operations 2,700 r.p.m. (260 hp.)

Model BN-2A-21				Model BN-2A-21	Model BN-2A-3
Approved May 16, 1974				Max Take off weight: 6600lbs	2x Lycoming IO-540-K1B5
				Max Landing weight: 6300lbs	For all operations 2,700 r.p.m. (300 hp.)
Model BN-2A-26
Approved April 6, 1977				Model BN-2A-26	Model BN-2A-20
				Max Take off and Landing weight: 6300lbs	2x Lycoming IO-540-K1B5
Model BN-2A-27					For all operations 2,700 r.p.m. (300 hp.)
Approved April 6, 1977				Model BN-2A-27
				Max Take off weight: 6360lbs	Model BN-2A-21
Model BN-2B-20				Max Landing weight: 6300lbs	2x Lycoming IO-540-K1B5
Approved September 24, 1979					For all operations 2,700 r.p.m. (300 hp.)
				Model BN-2B-20
Model BN-2B-21				Max Take off and Landing weight: 6560lbs	Model BN-2A-26
Approved September 24, 1979					2x Lycoming O-540-E4C5
				Model BN-2B-21	For all operations 2,700 r.p.m. (260 hp.)
Model BN-2B-26				Max Take off and Landing weight: 6600lbs
Approved September 24, 1979					Model BN-2A-27
				Model BN-2B-26	2 Lycoming O-540-E4C5
Model BN-2B-27				Max Take off and Landing weight: 6200lbs	For all operations 2,700 r.p.m. (260 hp.)
Approved September 24, 1979
				Model BN-2B-27	Model BN-2B-20
Model BN-2T				Max Take off and Landing weight: 6360lbs	2x Lycoming IO-540-K1B5
Approved July 15, 1982					For all operations 2,700 r.p.m. (300 hp.)
				Model BN-2T
Model BN-2T-4R				Max Take off and Landing weight: 6600lbs.	Model BN-2B-21
Approved December 1, 1994.				With NB-M-1218 - Max Take off weight: 7000lbs	2x Lycoming IO-540-K1B5
				Max Landing weight: 6800lbs	For all operations 2,700 r.p.m. (300 hp.)

				Model BN-2T-4R	Model BN-2B-26
				Max Take off and Landing weight: 8500lbs	2x Lycoming O-540-E4C5
					For all operations 2,700 r.p.m. (260 hp.)

					Model BN-2B-27
					2x Lycoming O-540-E4C5
					For all operations 2,700 r.p.m. (260 hp.)

					Model BN-2T
					2 Detroit Diesel Allison 250-B17C turbopropeller.
					Flat rated to 320 shp (equivalent to 830 ft. lb. of torque at the maximum propeller governed RPM of 2030)

		Model BN-2T-4R
		2x Allison 250-B17F/1 turbopropeller

Cessna 208B Grand Caravan

1984 - Present

Turbine Single-engine, all-metal, six-place, high-wing airplane, fixed tricycle landing gear.

Information

Year of certification	Engine type	Number of Engines	TODR @ 5000’ ASL (ISA Cond.)	Weight conditions	Model and Engine variants	IAGSA Operators
Model 208, Caravan (engine: PT6A-114 - 600 shp)	Turbine	Single	Ground roll: 1,399ft* landing roll: 1,004ft* C208EX takeoff dist: 2,160ft* landing dist: 1,836ft C208EX distance to/from 50 obs @ S.L & ISA	Model 208, Caravan	Model 208, Caravan	Xcalibur Multiphysics
11PCLM – Approved October 23, 1984				Max Take off weight: 8000lbs	(Serial Number and/or Service kit dependent)	Geotech South Africa
11PCSM – Approved October 23, 1984				Max Landing weight: 7800lbs	– Pratt & Whitney, PT6A-114 Turbo Prop - 600 Shaft horsepower	CAE Aviation
				Max take off weight with APEIII kit installed - 9062lbs	– Pratt & Whitney, PT6A-114A Turbo Prop - 675 Shaft horsepower	Sander Geophsyics Ltdf (SGL)
Model 208B, Caravan				Max Landing weight with APEIII kit installed - 9000lbs		Thomson Airborne Geophysical Survey
2PCLM – Approved October 9, 1986
11PCLM – Approved December 13, 1989				Model 208B, Caravan
				Max Take off weight: 8750lbs	Model 208B, Caravan
Model 208B, Caravan (PT6A-114A - 675 shp)*				Max Landing weight: 8500lb	(Serial Number and/or Service kit dependent)
Type certificate A37CE issued by FAA on June 15th 1998				Max take off weight with APEIII kit installed - 9062lbs	– Pratt & Whitney, PT6A-114 Turbo Prop - 600 Shaft horsepower
				Max Landing weight with APEIII kit installed - 9000lbs	– Pratt & Whitney, PT6A-114A Turbo Prop - 675 Shaft horsepower
Model 208B, Grand Caravan EX (PT6A-140 - 867 shp)**
S/N 208B2197 and 208B5000				Model 208B, Caravan - S/N 208B2197 and 208B5000 and on
Approved December 21, 2012				Max Take off weight: 8807lbs	Model 208B, Caravan - S/N 208B2197 and 208B5000 and on
				Max Landing weight: 8750lbs	– PT6A-140 Turbo Prop - 867 Shaft horsepower
				Max take off weight with APEIII kit installed - 9062lbs	– PT6A-140 Turbo Prop - 867 Shaft horsepower
				Max Landing weight with APEIII kit installed - 9000lbs

				Model 208B, Supervan
				Max Take off weight: 8807lbs
				Max Landing weight: 8750lbs
				Max take off weight with APEIII kit installed - 9062lbs
				Max Landing weight with APEIII kit installed - 9000lbs

Cessna 208B Supervan

1984 - Present

The conversion uses a flat-rated 900 hp Honeywell engine.

Information

Year of certification	Engine type	Number of Engines	TODR @ 5000’ ASL (ISA Cond.)	Weight conditions	Model and Engine variants	IAGSA Operators
Model 208, Caravan (engine: PT6A-114 - 600 shp)	Turbine	Single	Ground roll: 1,399ft* landing roll: 1,004ft* C208EX takeoff dist: 2,160ft* landing dist: 1,836ft C208EX distance to/from 50 obs @ S.L & ISA	Model 208, Caravan	Model 208, Caravan	Xcalibur Multiphysics
11PCLM – Approved October 23, 1984				Max Take off weight: 8000lbs	(Serial Number and/or Service kit dependent)	Geotech South Africa
11PCSM – Approved October 23, 1984				Max Landing weight: 7800lbs	– Pratt & Whitney, PT6A-114 Turbo Prop - 600 Shaft horsepower	CAE Aviation
				Max take off weight with APEIII kit installed - 9062lbs	– Pratt & Whitney, PT6A-114A Turbo Prop - 675 Shaft horsepower	Sander Geophsyics Ltdf (SGL)
Model 208B, Caravan				Max Landing weight with APEIII kit installed - 9000lbs		Thomson Airborne Geophysical Survey
2PCLM – Approved October 9, 1986
11PCLM – Approved December 13, 1989				Model 208B, Caravan
				Max Take off weight: 8750lbs	Model 208B, Caravan
Model 208B, Caravan (PT6A-114A - 675 shp)*				Max Landing weight: 8500lb	(Serial Number and/or Service kit dependent)
Type certificate A37CE issued by FAA on June 15th 1998				Max take off weight with APEIII kit installed - 9062lbs	– Pratt & Whitney, PT6A-114 Turbo Prop - 600 Shaft horsepower
				Max Landing weight with APEIII kit installed - 9000lbs	– Pratt & Whitney, PT6A-114A Turbo Prop - 675 Shaft horsepower
Model 208B, Grand Caravan EX (PT6A-140 - 867 shp)**
S/N 208B2197 and 208B5000				Model 208B, Caravan - S/N 208B2197 and 208B5000 and on
Approved December 21, 2012				Max Take off weight: 8807lbs	Model 208B, Caravan - S/N 208B2197 and 208B5000 and on
				Max Landing weight: 8750lbs	– PT6A-140 Turbo Prop - 867 Shaft horsepower
				Max take off weight with APEIII kit installed - 9062lbs	– PT6A-140 Turbo Prop - 867 Shaft horsepower
				Max Landing weight with APEIII kit installed - 9000lbs

				Model 208B, Supervan
				Max Take off weight: 8807lbs
				Max Landing weight: 8750lbs
				Max take off weight with APEIII kit installed - 9062lbs
				Max Landing weight with APEIII kit installed - 9000lbs

Pilatus Porter PC-6

1959 - 2019

Pilatus PC-6 is designed as a Short Takeoff and Landing (STOL) utility aircraft.

Information

Year of certification	Engine type	Number of Engines	TODR @ 5000’ ASL (ISA Cond.)	Weight conditions	Model and Engine variants	IAGSA Operators
15 variants namely :	Turbine	Single	650 ft	Model PC-6	Model PC-6	NRG
PC-6/350, PC-6/ A, PC-6/ A1, PC-6/ A2, PC-6/ B, PC-6/ B1, PC-6B2-H2,				Max Take off weight: 6200 lbs	Pratt & Whitney Canada PT6A-27 single turboprop engine
PC- 6/ C, PC-6/ C1, PC-6/ C2-H2, PC-6/ D-H3, AU-23A peace maker, OV-12				Max Landing weight: 5800 lbs
Chiricahua UV-20A, and PC-8 Twin Porters
PC-6/B2-H4				high absorbency undercarriage - land on rough, short, sandy, rocky, soft airfields

PAC 750

2001 - Present

Utility aircraft low-wing monoplane design with fixed tricycle undercarriage.

Information

Year of certification	Engine type	Number of Engines	TODR @ 5000’ ASL (ISA Cond.)	Weight conditions	Model and Engine variants	IAGSA Operators
Model PAC 750XL	Turbine	Single	Take-Off Ground Roll: 721 ft / 220 m (ISA, SL) Landing Ground Roll: 543 ft / 166 m (SL	Model P-750XL	Model P-750 XL	Xcalibur Multiphysics
Approved March 10, 2004				Max Take off weight: 7500 lbs	Pratt & Whitney PT6A-34	Kiwi Air Ltd
				Max Landing weight: 7125 lbs	Max continuous - 633 Shaft Horsepower - sea level	UTS Geophysics
Renamed as P-750 XSTOL in March 2004 following FAA accreditation					Max cruise 750 Shaft Horsepower - sea level	Kiwi Air Ltd

Air Tractor AT502, AT504

1986 - Present

Aircraft made for agricultural, firefighting and a variety of utility applications

Information

Year of certification	Engine type	Number of Engines	TODR @ 5000’ ASL (ISA Cond.)	Weight conditions	Model and Engine variants	IAGSA Operators
Model AT502:	Turbine	Single	AT502B - 1,140 ft @9,400lbs AT502XP - 1,308ft @10,480lbs AT504 - 1,150ft @9,600lbs	Model AT502 - S/N 502-0001 to 502-0061	Model AT502	Xcalibur Multiphysics
S/N 502-0001 to 502-0061 - Approved June 23, 1987				Max Take off weight: 8,500 lbs	As per AT 502B below
S/N 501-0062 and later - Approved June 23, 1987				Max Landing weight: 8,000 lbs
					Model AT502 A
Model AT502A:				Model AT502 - S/N 502-0062 and later	Pratt & Whitney PT6A-45R - Max continuous - 1020 Shaft Horsepower - ISA+18.3°C
Approved April 10, 1992				Max Take off weight: 9,200 lbs	Pratt & Whitney PT6A-45A - Max continuous - 1020 Shaft Horsepower - ISA+18.3°C
				Max Landing weight: 8,000 lbs	Pratt & Whitney PT6A-45B - Max continuous - 1020 Shaft Horsepower - ISA+18.3°C
Model AT502B:					Pratt & Whitney PT6A-60AG - Max continuous - 1020 Shaft Horsepower
Approved December 8, 1992				Model AT502A	Pratt & Whitney PT6A-65B - Max continuous - 1020 Shaft Horsepower
				Max Take off weight: 9,400 lbs	Pratt & Whitney PT6A-65AG - Max continuous - 1020 Shaft Horsepower
Model AT502 XP:				Max Landing weight: 8,000 lbs	Pratt & Whitney PT6A-140AG - Max continuous - 810 Shaft Horsepower
Introduced 2016
				Model AT502 B	Model AT502 B
Model AT504:				Max Take off weight: 9,400 lbs	Pratt & Whitney PT6A-15AG - all ops - 680 Shaft Horsepower - ISA+6.7°C
Approved December 8, 1992				Max Landing weight: 8,000 lbs	Pratt & Whitney PT6A-27 - all ops - 680 Shaft Horsepower - ISA+6.7°C
					Pratt & Whitney PT6A-34 - all ops - 750 Shaft Horsepower - ISA+15.6°C
				Model AT502 XP	Pratt & Whitney PT6A-34 AG - all ops - 750 Shaft Horsepower - ISA+15.6°C
				Max Take off weight: 10,480 lbs	Pratt & Whitney PT6A-36 - all ops - 750 Shaft Horsepower - ISA+15.6°C
				Max Landing weight: 8,000 lbs	Pratt & Whitney PT6A-34B - all ops - 750 Shaft Horsepower - ISA+15.6°C

				Model AT504	Model AT502 XP
				Max Take off weight: 9,600 lbs	Pratt & Whitney PT6A-140AG - 867 Shaft Horsepower
				Max Landing weight: 8,000 lbs
					Model AT504
					Pratt & Whitney PT6A-34 AG - all ops - 750 Shaft Horsepower - ISA+15.6°C

Air Tractor AT802

1986 - Present

Aircraft made for agricultural, firefighting and a variety of utility applications

Information

Year of certification	Engine type	Number of Engines	TODR @ 5000’ ASL (ISA Cond.)	Weight conditions	Model and Engine variants
Model AT802 A	Turbine	Single	2,000 ft	Model AT802 A	Model AT802 A
				Max Take off weight: 16,000 lbs	Pratt & Whitney PT6A-65AG
				Max Landing weight: 16,000 lbs
Model AT802 F:

Fletcher FU-24

1954 - 1992

Aircraft made for agricultural, firefighting and a variety of utility applications

Information

Year of certification	Engine type	Number of Engines	TODR @ 5000’ ASL (ISA Cond.)	Weight conditions	Model and Engine variants
Model FU-24:	Piston	Single	1,060 ft	Model FU-24:	Model FU-24:
Original Type Certificate 4A12 issued 22 July 1955.				Max weight: 3500 lbs.	Continental O-470-E - For all operations 2,600 r.p.m. (225 hp.)
Type Certificate 4A12 reissued 7 November 1972				Eligible for 4000lbs i.a.w approved modification	Optional - Continental O-470-M or O-470-N - For all operations 2,600 r.p.m. (240 hp.)
				Model FU-24A:	Optional - Continental IO-470-D - For all operations 2,625 r.p.m. (260 hp.)
Model FU-24A:				Max weight: 3500 lbs.	Optional - Continental GIO-470-A - For all operations 3,200 r.p.m. (310 hp.)
Original Type Certificate 4A12 issued 22 July 1955.					Model FU-24A:
Type Certificate 4A12 reissued 7 November 1972				Model FU24-924:	Continental O-470-E
				Max weight: 4600 lbs.
Model FU24-924:					Model FU24-924:
Approved 20 September 1979.				Model FU24-924A:	Lycoming IO-720-A1A or A1B - For all operations 2,650 r.p.m. (400 hp.)
				Max weight: 4600 lbs.
Model FU24-924A:					Model FU24-924A:
Approved 20 September 1979.					Lycoming IO-720-A1A or A1B - For all operations 2,650 r.p.m. (400 hp.)

Basler DC3 Conversion

1990 - Present

Extensive remanufacturing process with state-of-the-art components

Information

Year of certification	Engine type	Number of Engines	TODR @ 5000’ ASL (ISA Cond.)	Weight conditions	Model and Engine variants	IAGSA Operators
Model BT67	Turbine	Twin	4,150 ft	Model BT67	Model BT67	Xcalibur Multiphysics
Approved 1990				Max Take off weight: 30 000lb	Pratt & Whitney PT6A-67R	Spectrem Air
Number manufactured: 90				Max Landing weight: 28700 lb		Bell Geospace

Merlin III

The Merlin III is a 10-11 seater, twin turboprop business aircraft with retractable undercarriage

Information

Year of certification	Engine type	Number of Engines	Weight conditions	Model and Engine variants
Model SA226-T (Merlin IIIA)	Turbine	Twin	Model SA226-T (Merlin IIIA)	Model SA226-T (Merlin IIIA)
Approved 27 July 1970.			Max Take off weight: 12,500 lbs	TPE 331-3U-303G - Max Continuous - 840 Shaft Horsepower
			Max Landing weight: 11,500 lbs	TPE 331-3U-304G - Max Continuous - 840 Shaft Horsepower
Model SA226-T(B) (Merlin IIIB)
Approved 3 November 1978.			Model SA226-T(B) (Merlin IIIB)	Model SA226-T(B) (Merlin IIIB)
			Max Take off weight: 12,500 lb (or 14,000lbs in restricted category)	TPE 331-10U-501G - Max Continuous - 900 Shaft Horsepower
Model SA227-TT (Merlin IIIC)			Max Landing weight: 12,500 lbs	TPE 331-10U-502G - Max Continuous - 900 Shaft Horsepower
Approved 18 May 1981.				TPE 331-10U-511G - Max Continuous - 900 Shaft Horsepower
			Model SA227-TT (Merlin IIIC)	TPE 331-10U-512G - Max Continuous - 900 Shaft Horsepower
			Max Take off weight: 13,230 lb
			Max Landing weight: 13,230 lbs	Model SA227-TT (Merlin IIIC)
				TPE 331-10U-503G - Max Continuous - 900 Shaft Horsepower
				TPE 331-10U-513G - Max Continuous - 900 Shaft Horsepower

PA-31T Cheyenne

1974 - 1985

6 to 11 seater (model dependent) twin turboprop with retractable undercarriage

Information

Year of certification	Engine type	Number of Engines	TODR @ 5000’ ASL (ISA Cond.)	Weight conditions	Model and Engine variants	IAGSA Operators
Model PA-31T	Turbine	Twin	PA-31T: 2,000 ft	Model PA-31T	Model PA-31T	Xcalibur Multiphysics
Approved 3 May 1972.				Max Take off weight: 9,000 lbs	Pratt & Whitney PT6A-28 - Max Continuous - 620 Shaft Horsepower - ISA+18°C
				Max Landing weight: 9,000 lbs
Model PA-31T1					Model PA-31T1
Approved 6 March 1978.				Model PA-31T1	Pratt & Whitney PT6A-11 - Max Continuous - 455 Shaft Horsepower - ISA+18°C
				Max Take off weight: 8,700 lbs
Model PA-31T2				Max Landing weight: 8,700 lbs	Model PA-31T2
Approved 12 February 1981.					Pratt & Whitney PT6A-135 - Max Continuous - 620 Shaft Horsepower - ISA+24°C
				Model PA-31T2
Model PA-31T3				Max Take off weight: 9,474 lbs	Model PA-31T3
Approved 25 February 1982.				Max Landing weight: 9,000 lbs	Pratt & Whitney PT6A-11 - Max Continuous - 500 Shaft Horsepower - ISA+18°C

				Model PA-31T3
				Max Take off weight: 9,000 lbs
				Max Landing weight: 9,000 lbs

King Air 90

1964 - Present

The Beechcraft King Air is a line of American utility aircraft produced by Beechcraft. The King Air line comprises a number of twin-turboprop models that have been divided into two families. The Model 90 and 100 series developed in the 1960s are known as King Airs

Information

Year of certification	Engine type	Number of Engines	Weight conditions	Model and Engine variants	IAGSA Operators
Model A90	Turbine	Twin	A90 - 9300 lbs	PT6A-20 (x2 550 shp)	Terraquest Ltd.
Model B90			B90 - 96500 lbs	PT6A-20 (x2 550 shp)
Model C90 - TC: 3A20, approved May 15th 1998			C90 - 9650 lbs	PT6A-21 (x2 550 shp)
model C90GTx			C90GTx: -10485 lbs	PT6A-34B (x2 750 shp)
Model E90			E90 - 10100 lbs	PT6A-28 (x2 680 shp)
Model H90			H90 9300 lbs	PT6A-34B (x2 750 shp)

Model 100				Model 100 is a B90 with a 50" strech snf x2 PT6A-28 (750 shp)
Model A100
Model B100				Model B100 - two 715shp Garrett TPE-331 engines (715 shp)
Model C100				Model C100 - xe PT6A-135 (750 shp)

DHC-6 Twin Otter

2008 - Present
1965 - 1988

The DHC-6 Twin Otter aircraft – a high winged, un-pressurized twin engine turbine powered aircraft with fixed tricycle land gear. Designed as a rugged Short Take Off and Landing (“STOL”) commuter, the Twin Otter was capable of carrying passengers and cargo into remote unimproved locations.

Information

Year of certification	Engine type	Number of Engines	TODR @ 5000’ ASL (ISA Cond.)	Weight conditions	Model and Engine variants	IAGSA Operators
Model DHC6 series 100	Turbine	Twin	1200 feet	DHC6-100:	DHC6-100: 2 Pratt & Whitney Canada Inc. PT6A-20 (550 SHP, 579 shp up to 21°C OAT)	Xcalibur Multiphysics
Type Certificat A-82 issued on March 07, 1966				Max Takeoff: 11,000 lbs		Sander Geophysics Ltd. (SGL)
				Max Landing: 11,000 lbs
Model DHC6 Series 200				DHC6-200: 2 Pratt & Whitney Canada Inc. PT6A-20	DHC6-200: Pratt & Whitney Canada Inc. PT6A-20 (550 SHP, 579 shp up to 21°C OAT)
Approved March 29, 1968				Max Takeoff: 11,579 lbs
				Max Landing: 11,400 lbs
Model DHC6 Series 300				DHC6-300: 2 Pratt & Whitney Canada Inc. PT6A-27	DHC6-300: 2 Pratt & Whitney Canada Inc. PT6A-27 (620 shp, 652 shp up to 33°C OAT)
Approved April 25, 1969				Max Takeoff: 12,500 lbs
				Max Landing: 12,300 lbs
Model DHC6 Series 320				DHC6-320: 2 Pratt & Whitney Canada Inc. PT6A-27	DHC6-300: 2 Pratt & Whitney Canada Inc. PT6A-27 (620 shp, 652 shp up to 33°C OAT)
Approved January 23, 1970				Max Takeoff: 12,500 lbs	STC: 2 Pratt & Whitney Canada Inc. PT6A-34
				Max Landing: 12,300 lbs
Model DHC6 Series 400				DHC6-400: 2 Pratt & Whitney Canada Inc. PT6A-34	DHC6-400: 2 Pratt & Whitney Canada Inc. PT6A-27 (620 shp, 652 shp up to 42°C OAT)
Approved June 24, 2010				Max Takeoff: 12,500 lbs
				Max Landing: 12,300 lbs

Reims F406 Caravan II

1983 - 2013

Twin Engine Turboprop, Non-pressurised, Retrackable undercarriage. Produced by Reims Aviation Industies

Information

Year of certification	Engine type	Number of Engines	TODR @ 5000’ ASL (ISA Cond.)	Weight conditions	Model and Engine variants	IAGSA Operators
The maiden flight of the aircraft took place in September 1983 and the initial production aircraft flew first in April 1985	Turbine	Twin		Reims F406	F406 Pratt & Whitney PT6A -112 (x2 500 shp)	Kiwi Air Ltd
	Turbine	Twin		Max takeoff: 9,360 - 10,361 lbs		NRG

AS350BA

Single turbine-engine light utility helicopter, all-metal, pilot & 6 pax (depending on config)

Information

Year of certification	Engine Type	Number of Engines	HOGE Ceiling at Max Internal Weight	Maximum External Payload	Model and Engine variants	IAGSA Operators
Model AS350 BA	Turbine	Single	6500ft	998 Kg	Turbomeca Arriel 1B - 641 shp	UAH
Approved May 17, 1991	Turbine	Single	6500ft	998 Kg

AS 350 B2

1992 - 2010 approximately

Single turbine-engine light utility helicopter, all-metal, pilot & 6 pax (depending on config)

Information

Year of certification	Engine Type	Number of Engines	HOGE Ceiling at Max Internal Weight	Maximum External Payload	Model and Engine variants	IAGSA Operators
Model AS350 B2	Turbine	Single	7550ft	1146 Kg		UAH
Approved April 26, 1989					Turbomecca Arriel 1D1	NRG
						Skyhorse Aviation

AS350B3 - H125

1997 - Present as H125

Single turbine-engine light utility helicopter, all-metal, pilot & 6 pax (depending on config)

Information

Year of certification	Engine Type	Number of Engines	HOGE Ceiling at Max Internal Weight	Maximum External Payload	Model and Engine variants	IAGSA Operators
Model AS350 B3	Turbine	Single	11200ft	1402 kg		UAH
Approved October 14, 1996					Turbomecca Arriel 1D1	Geotech Ltd
						NRG
						Skyhorse Aviation
						Sander Geophysics Ltd. (SGL)

EC 130 B4

1999 - Present

Single turbine-engine light utility helicopter

Information

Year of certification	Engine Type	Number of Engines	HOGE Ceiling at Max Internal Weight	Maximum External Payload	Model and Engine variants	IAGSA Operators
Introduced in 2001	Turbine	Single	8325ft	1162 Kg	Turbomecca Arriel 2D

Bell 206 L4

1975 - 2017

Single Turbine-engine light utility helicopter

Information

Year of certification	Engine Type	Number of Engines	HOGE Ceiling at Max Internal Weight	Maximum External Payload	Model and Engine variants	IAGSA Operators
Introduced in 1975	Turbine	Single	6500ft	882 Kg	Allison 250-C30P 317 SHP

Bell 206 B3

1971 - 2010

Single Turbine- engine light utility helicopter

Information

Year of certification	Engine Type	Number of Engines	HOGE Ceiling at Max Internal Weight	Maximum External Payload	Model and Engine variants
Introduced in 1977	Turbine	Single	5300ft	608 Kg	Allison 250-C20B
					Allison 250-C20J
					Allicon 250- C20R

AS 355 NP

1975 - 2016

Twin Turbine-engine light utility helicopter

Information

Year of certification	Engine Type	Number of Engines	HOGE Ceiling at Max Internal Weight	Maximum External Payload	Model and Engine variants	IAGSA Operators
Introduced in 1979	Turbine	Twin	7180ft	909 Kg	Turbomecca Arrius 1A1 (557 SHP)

MIL MI-8

1975 - 2016

Twin Turbine-engine Medium utility helicopter

Information

Year of certification	Engine Type	Number of Engines	HOGE Ceiling at Max Internal Weight	Maximum External Payload	Model and Engine variants	IAGSA Operators
Introduced in 1967	Turbine	Twin	14,700ft	Gross weight 11,100 Kg	Klimov TV2-117A turboshaft engines (1677DHP)

Purpose and Intent

To provide a tool to aide and guide in the overall risk assessment of, and decision-making process, airborne platform with the key objective to enhance safety in the use of correct platforms.
1. Assist and guide end-users (both clients and operators) in making an informed decision of platform capabilities under various survey conditions. This will be done through a review of survey hazards in relation to the platforms and let users make a choice on the most suitable range (grouping) of the platforms available. To educate and guide.
2. The most important consideration of this tool is to assist in considering if a survey can be safely flown at the contemplated survey height with a given range of airborne geophysical platforms under specific survey conditions (i.e. terrain condition, elevation, weather, etc…). Members do not need to be reminded of the increased risks associated with low level flying projects.
3. This links clearly to the IAGSA mission / values / purpose and raising the profile of the industry more broadly as safe and efficient with the passage of time
IAGSA TC has generated a summary of most platforms currently used by the industry and present some of the basic characteristics for the user. This provides an additional resource as part of IAGSA safety toolbox in order to conduct safe low-level surveys and build a better understanding of available platforms and capabilities. This drawn upon information available publicly and centralizes it for our members
It also shows the various platforms used by IAGSA member companies
All known and current airborne geophysics platforms have been provided within the tool based on OEM specifications and facts – from public and other sources – and consolidated for our membership into a handy ready-reference guidance tool

Legal disclaimer

DISCLAIMER:

End-Users of the Aircraft Guidance Tool (AGT) agree that:

The International Airborne Geophysics Safety Association (IAGSA) is not under any legal obligation to supply this information to its membership, nor will it have any liability to end-users or of any nature whatsoever with respect to the purpose or interpretation of the AGT;
IAGSA reserves all of its rights (in its absolute discretion, at any time, and without notice to end-users) in supplying this general information to its membership;
IAGSA does not accept responsibility for (and any end-user releases IAGSA from any liability in relation to) any interpretation they may place on this information in the AGT, or for any opinion or conclusion that end-users or any of their representatives may form as a result of use of the AGT.

Comments – martin@iagsa.ca