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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 — the S-61L, S-61N and the Payloader — 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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| Lucrezia, e-mail, 15.03.2021 | reply |
During transfer the Sikorsky S-61N Sea King (G-ATBJ) took off for a hover check and pitched nose-down, striking the ground on its nose before coming to rest on its landing gear, 1 February 2018. | | Patrizia, e-mail, 22.02.2021 | reply |
Manufacturer: Sikorsky Aircraft, one of the pioneer developers of helicopters dating back to the 19. Lockheed Martin, a giant aerospace conglomerate, bought the company from United Technologies in 2015. | | Mike, e-mail, 28.01.2018 | reply |
Logging pilots and aircraft technicians for S61N required in NZ | | alfred, e-mail, 16.02.2013 | reply |
I remember seeing a cross section of rotor blade that had some
sort of wood compound included, can someone confirm this for
me as my pal thinks I am pulling his leg.
Thanks
Alf | | Don Hillberg, e-mail, 31.08.2010 | reply |
Margret Duffy had info on LAA (Los Angeles Airways) She has passed away and gave some of the info to my brother.Our father,aunts,uncles,and others close to the family worked for Mr Burlin.....its a small world... | | M v.d. Burg, e-mail, 30.12.2010 | reply |
How many rotations does make the main rotor of Sikorsky S-61N in a minute. Please answer me. | | danny, e-mail, 30.12.2010 | reply |
Weet iemand misschien hoeveel omwentelingen per minuut de hoofdroter maakt (s-611n Sikorsky)
bedankt alvast | | hH.A.Welboren-van Mullem, e-mail, 30.12.2010 | reply |
Hoeveel omwentelingen per minuut maken de rotorbladen ? | | David Hanlon, e-mail, 23.05.2011 | reply |
Any body know the Shore Hardness of the helicopter tyres? | |
| | Charles belsom, e-mail, 15.06.2010 | reply |
Does anyone have a response to Carrol1234 concerning the contact area, shape, for static load and dynamic load. | | Gene, e-mail, 13.07.2011 | reply |
Hello All,
Does anyone now if FAA /EASA approved maintenance training is available for new S61N Mechanics? | | Pepijn, e-mail, 06.08.2011 | reply |
Has anyone the safety manuals for alluminum rotor blades used in 1973-1974. And procedures after 12 spar failures in pocket nr 12 on rotor blade nr 3 | | sliders, e-mail, 04.09.2011 | reply |
Current LEA S61n Licensed Engineer | | Ellen, e-mail, 11.11.2013 | reply |
I need information on the fuel oil tank volume of S61N £¬S-92 and Superpuma.Thank you Very much. | | Ken, e-mail, 24.06.2013 | reply |
I crewed for SFO Helicopter Airlines in 1964-65 and one oddity on our S-61Ns and S-62s is that they all carried boat anchors and battery powered "mooring lights" as a nautical requirement - just in case you wanted to anchor out for the night! | | 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. |
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