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The commercial models of the military S-61, or SH-3, helicopter use the same rotor system with a new and longer fuselage. The S-61L is a landplane model, although its hull is sealed against the possibility of making an emergency landing on water, and all undercarriage units are non-retracting. It seats 28 passengers in the standard airline seating layout and carries a flight crew of 3. The S-61N, which carries 2 fewer passengers, is fully amphibious and can be identified by its twin stabilising floats, into which the main landwheels can be retracted. First flights of the L and N versions were made on 6 December 1960 and 7 August 1962 respectively. The type received FAA certification - the first for a twin-turbine commercial helicopter - in November 1961 and since October 1964 has been cleared for all-weather operation. Current production examples have 1500shp CT58-140 shaft turbines. The only customer so far for the S-61L has been Los Angeles Airways, which has a fleet of seven and on 1 March 1962 became the first operator to put the commercial S-61 into service. Customers up to January 1968 for the S-61N have been British European Airways (four); Greenlandair (four); Pakistan International and San Francisco & Oakland (three each); Helibuss of Norway (two); and Ansett/A.N.A., Brunei Shell Petroleum, the Canadian Dept. of Transport, Elivie of Italy, Japan Air Lines, KLM, Nitto Airways and Petroleum Helicopters Inc. (one each). K.Munson "Helicopters And Other Rotorcraft Since 1907", 1968
The three commercial models of the S-61 β the S-61L, S-61N and the Payloader β used the same dynamic components as the military version, but had a longer fuselage. The S-61L (land version with non-retractable landing gear) could carry 30 passengers and a crew of three while the S-61N, which had amphibious capability, was distinguished by two sponsons into which the landing gear retracted. The former flew on 6 December 1960 and received FAA type approval in November 1961. The main operator of the S-61L was Los Angeles Airways (6), which was the first company in the world to use Sikorsky helicopters. The interior of the S-61N was quite elaborately fitted-out; the spacious cabin had a toilet, storeroom and luggage compartment, and could accommodate 26-28 passengers. Operators of the S-61N included New York Airways (4), Nippon Airways (1), British Airways Helicopters (26), Bristow Helicopters (28), Brunei Shell (2), Elivie (2), Greenlandair (5), Helikopter Service Norway (10), Japan Air Lines (1) and KLM (2). G.Apostolo "The Illustrated Encyclopedia of Helicopters", 1984
| Technical data for Sikorsky S-61N
Engine: 2 x General Electric CT58-110-1 turboshaft, rated at 1000kW,
main rotor diameter: 18.9m,
fuselage length: 18.08m,
height: 5.32m,
take-off weight: 8618kg,
max speed at sea level: 241km/h,
ceiling: 3505m,
range with max fuel: 443km
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| Rick, e-mail, 19.03.2010 | reply |
somebody know something about S-61N avionics and instrument layout on the cockpit? a internet link? or any pictures | | Dale, e-mail, 17.03.2010 | reply |
The FAA Approved Performance Data for Category "A" vertical operations from ground level heliports provides information to determine the conditions at which the helicopter fulfills the performance requirements of FAA Interim Standards Dated October 19, 1962, as amended May 28, 1964. The performance is based on still air and zero bank angle. The following conditions apply
to category An vertical operations from ground-level heliports:
1. Heliport size used for take-off tests was 108 feet by 150 feet.
2. Landing distance demonstrated was 60 feet,
3. Length of helicopter is 72 feet.
Note
For minimum heliport dimensions apply current FAA operations requirements.
4. The maximum acceptable wind capability evaluated during take-off and landing tests was 15 knots crosswind and 0 knots tailwind.
The basic parameters controlling this performance information is the capability
to reject a take-off at the CDP and to establish a single engine flight
path that will not descend less than 35 feet above the take-off surface in
achieving Vtoss.
-F ROM ELEVATED HELIPORT.
The FAA Approved Performance Data for Category A vertical operations from
elevated heliports provides information to determine the conditions at which
the helicopter fulfills the performance requirements of FAA Interim Standards
Dated October 19, 1962, as amended May 28, 1964. The perfcnnance is based
on still air and zero bank angle. The following conditions apply to category
nAN vertical operations from elevated heliports:
1, Heliport size used for take-off tests was 108 feet by 108 feet.
2, Landing distance demonstrated was 30 feet.
3. Length of helicopter is 72 feet-
Note
For minimum heliport dimensions apply current FAA operations requirements. | | khairul Anwar, e-mail, 05.01.2010 | reply |
need info bout s61a-4 tail rotor drive shaft...specification..tq | | fery Irawan, e-mail, 14.12.2009 | reply |
Hi All,
Do you have any cad file for S-61N and S-92 copper.?? | | Tatan, e-mail, 08.12.2009 | reply |
As I know the foot print for main wheel is 374cm2 and tail wheel is 277cm2 however I need to know the dimension of the wheel them selves in height and width. Is somebody can help to advise... many thanks and best regards. | | Zhiyong, e-mail, 29.09.2009 | reply |
Why does some helideck has a dimension of 72.83ft diameter, but the center of aiming circle is about 2.2m in front of the helideck center? | | Gene, e-mail, 28.09.2009 | reply |
Does anyone know of facilities that provide Maintenance Training for the S-61N and S-61L? Either in the US or otherwise? Any information provided will be kept confidential and used for the sole purpose of getting my company's mechanics trained. Thanks! | | Kamlesh, e-mail, 13.09.2009 | reply |
I need the dimensions of Sikorsky S61N Helicopter for helideck designing. | | Lexi, e-mail, 04.05.2009 | reply |
What is the fuel tank capacity for S-61N? Thanks! | |
| | Frank, e-mail, 09.03.2009 | reply |
I know the S61N has got double wheels and that the static contact area of each (rear)wheel is 374cm^2. But I need to know the height and width of the foodprint. Is there somebody who know where to find this information? | | Jorge Sors, e-mail, 05.02.2009 | reply |
I need de dimensions of S61 footprint in order to calculate helideck structure. Thanks | | Y.J.Jo, e-mail, 05.02.2009 | reply |
I also request for the tyre footprint (area,position,dimension,etc.) of the Sikorsky S61N helicopter. i need this to do load analysis for an offshore helideck. thank you | | rahul, e-mail, 11.12.2008 | reply |
i request for the tyre footprint of the Sikorsky S61N helicopter. i need this to do load analysis for an offshore helideck. thank you
rahul | | Tom Hashem, e-mail, 01.11.2008 | reply |
What are the requirments for a S61N Sirkorsky landing site in a remote area: radis of circle,pitch of the land,surface preparation, etc. | | Hill, e-mail, 20.09.2008 | reply |
Have there been any attempts to use biofuels with this helicopter? Thanks | | robert dalziel, e-mail, 07.07.2008 | reply |
I NEED INFORMATION ON THE VOLUME OF THE FUEL TANKS IE. TOTAL FUEL VOLUME OF THE S61 N FOR A PROJECT I AM WORKING ON
THANK YOU AND REGARDS | | byongju-kim, e-mail, 08.05.2008 | reply |
Is SIKORSKY-S61N is a single wheel or double wheel? Can you also give the tyre footprint of it in detail, I'M Structure engineer, so Just need it in my design. | | cmion, e-mail, 02.03.2008 | reply |
S-61N has double main wheels and single tail wheel.. | | lorna, e-mail, 28.01.2008 | reply |
Is S61N is a single wheel or double wheel? Can you also give a the tyre footprint of it, Just need it in my design. Thanks | | Brent, e-mail, 05.01.2008 | reply |
need response for removal of main rotar and or blade removal |
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