# TCDS 1H15: Sikorsky Aircraft

- Type: Type certificate data sheet
- Status: Current
- Holder: Sikorsky Aircraft
- Revision: 18
- Revised: January 21, 2014
- Product: Aircraft, Rotorcraft
- Certification basis: Part 29
- Registered aircraft: 48, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/32/0c/320c8ff68bdd9156a1eb27fa80613ec0499562a804815264e728b5780c11be97
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/A569985827B10996862585CB00585E88.0001
- Page: https://openairdocs.org/tcds/1H15

## Models (4)

As the data sheet lists them.

- S-61R ((USAF CH-3C, CH-3E))
- S-61N
- S-61L
- S-61NM

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
DEPARTMENT OF TRANSPORTATION  
FEDERAL AVIATION ADMINISTRATION 
1H15 
Revision No 18 
SIKORSKY AIRCRAFT 
MODEL 
S-61L 
S-61N 
S-61R (USAF CH-3C, CH-3E) 
S-61NM 
 
January 21, 2014  
TYPE CERTIFICATE DATA SHEET 1H15 
This data sheet, which is part of Type Certificate Number 1H15, prescribes conditions and limitations under which the product 
for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Administration. 
Type Certificate (TC) Holder: Sikorsky Aircraft 
Stratford, CT 
I. MODEL NUMBER: S-61L (Transport Helicopter - Categories A & B) 
Approved: November 2, 1961 
Engines: 2 General Electric CT58-110-1 (with Hamilton Standard Fuel Control JFC-26). See 
NOTE 9 for optional engines. 
Fuel: Aviation Kerosene JP4 or JP5 (General Electric Company Specification Number D50T 
F2 or subsequent revisions thereto.) 
Engine Limits: Sea Level Static - Standard Day 
 SHAFT  
HP 
POWER TURBINE  
RPM 
GAS GEN  
RPM 
POWER TURBINE  
INLET (T5) 
Takeoff (5 min) 1,250 21,275(112.0%Nf) 26,300(100%Ng) 1,250o F (677oC) 
One engine inoperative (30 min) 1,250 21,275(112.0%Nf) 26,300(100%Ng) 1,250o F (677oC) 
(See NOTE 7)     
One engine inoperative (2 1/2 min) 1,350 21,275(112.0%Nf) 26,840(102%Ng) 1,300o F (704oC) 
(See NOTE 6)     
Maximum continuous 1,050 21,275(112.0%Nf) 26,300(100%Ng) 1,175o F (635oC) 
Maximum transient (2 sec)    1,544o F (840oC) 
Starting (4 sec)    1,544o F (840oC) 
Allowable maximum overspeed  23,100(122.0%Nf) 27,600(105%Ng)   
Takeoff and maximum continuous horsepower (hp) ratings are normally obtained at 
a power turbine speed of 18,966 rpm (100%Nf) 
Total power for two-engine operation is limited to 2,300 hp. for takeoff and 2,100 
hp. maximum continuous. (See NOTE 10 for alternate limits.) 
See NOTE 11 for variation of sea-level static power limits below 59oF. 
Rotor Limits: Maximum 225 r.p.m. 
Minimum 184 r.p.m. 
Airspeed Limits: Never exceed 146 m.p.h. (127 knots) CAS. 
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 
Rev. No. 18 12 17 16 17 17 12 12 17 18 15 18 17

1H15 2 of 13 
  
 
254 258 276 280 
I. MODEL NUMBER:  S-61L (cont’d) 
C.G. Range: Category A (except (+258.0) to (+276.0) at 19,000 lb 
vertical and edge procedures) (+258.0) to (+277.3) at 18,000 lb 
and Category B (+254.0) to (+280.0) at 16,000 lb or less 
Category A (+258.0) to (+276.0) at 
(Vertical and edge procedures) 
19,000 lb or less 
 
 
 19,000 
 18,000 
Gross  
Weight 
 (Lbs.) 
 
 16,000 
 
Station - Inches 
Empty Weight C.G. Range: None 
Maximum Weight: Category A: 19,000 lb. (See Rotorcraft Flight Manual for lesser maximum weights for 
various Category A takeoff and landing procedures.) 
Category B: 19,000 lb. 
(See NOTE 12 for maximum weight while carrying external loads.) 
Minimum Crew: 2 (pilot, copilot) 
Maximum Passengers: 39, limited by emergency exit requirements 
Maximum Baggage: Serial numbers (S/N) prior to 61266: 
600 lb (+130) 
600 lb (+168) 
300 lb (+374) 
300 lb (+408) 
S/Ns 61266 through 61424: 
670 lb (+129) 
690 lb (+168) 
660 lb (+267) 
590 lb (+340) 
530 lb (+374) 
530 lb (+407) 
S/Ns 61425 and subsequent: 
670 lb (+130) 
690 lb (+168) 
660 lb (+267) 
590 lb (+340) 
530 lb (+380) 
450 lb (+407) 
The under-floor baggage bins must not be loaded in excess of 400 lbs. per square foot 
within the maximum limits specified above. The cabin floor, when used for cargo 
purposes, should not be loaded in excess of 200 lbs. per square foot forward of Station 
323 and 150 lbs. per square foot aft of Station 323.

3 of 13 1H15 
I.  MODEL NUMBER:  S - 61L (cont’d  
Fuel Capacity: 410 gal. (210 gal at (204), 200 gal at (306).) 
Oil Capacity: 5 gal. (181) (2 tanks 2.5 gal each) 
Rotor Blade & Control Movements: For rigging information, refer to Maintenance Manual. 
Serial Numbers Eligible: 61031, 61032 (See NOTE 14), 61033, 61060, 61266, 61362, 61363, 61425, 61426, 
61427, 61428, 61453, 61454 
II.  MODEL NUMBER:  S-61N (Amphibious Transport Helicopter -  Categories A & B)  
(Model S-61N is the same as the Model S-61L except for the fuselage modified to 
provide a hull, the addition of sponsons with retractable landing gear and a modified 
tail rotor pylon.) See NOTE 5 for a fixed (land type) landing gear installation. See 
NOTE 13 for approval at higher gross weights. 
Approved: September 9, 1963 
Engines: 2 General Electric CT58-110-1 (with Hamilton Standard Fuel Control JFC-26). See 
NOTE 9 for optional engines. 
Fuel: Aviation Kerosene JP4 or JP5 (General Electric Company Specification Number D50T 
F2 or subsequent revisions thereto) 
Engine Limits: Sea level static - standard day 
 SHAFT  
HP 
POWER TURBINE  
RPM 
GAS GEN  
RPM 
POWER TURBINE  
INLET (T5) 
Takeoff (5 min) 1,250 21,275(112.0%Nf) 26,300(100%Ng) 1,250o F (677oC) 
One engine inoperative (30 min) 1,250 21,275(112.0%Nf) 26,300(100%Ng) 1,250o F (677oC) 
(See NOTE 7)     
One engine inoperative (2 1/2 min) 1,350 21,275(112.0%Nf) 26,840(102%Ng) 1,300o F (704oC) 
(See NOTE 6)     
Maximum continuous 1,050 21,275(112.0%Nf) 26,300(100%Ng) 1,175o F (635oC) 
Maximum transient (2 sec)    1,544o F (840oC) 
Starting (4 sec)    1,544o F (840oC) 
Allowable maximum overspeed  23,100(122.0%Nf) 27,600(105%Ng)  
(15 sec.)  
Takeoff and maximum continuous horsepower ratings are normally obtained at a 
power turbine speed of 18,966 rpm (100%Nf) 
Total power for two-engine operation is limited to 2,300 hp. for takeoff and 2,100 hp. 
maximum continuous. (See NOTE 10 for alternate limits.) 
See NOTE 11 for variation of sea-level static power limits below 59oF. 
Rotor Limits: Maximum 225 r.p.m. 
Minimum 184 r.p.m. 
Airspeed Limits: Never exceed 150 m.p.h. (130 knots) CAS.

1H15 4 of 13 
II. MODEL NUMBER: S-61N (cont’d) 
C.G. Range: Category A (except (+258.0) to (+276.0) at 19,000 lb 
vertical and edge procedures) (+254.0) to (+280.0) at 16,000 lb or less  
and Category B 
Category A (+258.0) to (+276.0) at 19,000 lb or less 
(Vertical and edge procedures) 
(Above values apply to aircraft with two-tank fuel system. Refer to Flight Manual for 
additional limitations associated with the three-tank fuel system.) 
 
 19,000  
 
Gross 
Weight 
(Lbs.) 
16,000 
 
   254 258 276 280 
Station - Inches 
Empty Weight C.G. Range: None 
Maximum Weight: Category A: 19,000 lb. (See Rotorcraft Flight Manual for lesser maximum weights for  
various Category A takeoff and landing procedures.) 
Category B: 19,000 lb. 
Minimum Crew: 2 (pilot, copilot) 
Maximum Passengers: 39, limited by emergency exit requirements 
Maximum Baggage: Forward Compartment: 
Above floor: 650 lb (+153) (if galley not installed) or  
590 lb (+151) (if galley installed) 
Below floor: 1,500 lb (+148) 
Aft Compartment (below floor): 1,000 lb (+340) 
Baggage Rack: 500 lb (+370)  
Below-floor areas of forward compartment should not be loaded in excess of 86.5 lbs 
per square foot and aft compartment in excess of 65 lbs per square foot, within the total 
limits identified above. 
The cabin floor, when used for cargo purposes, should not be loaded in excess of 200 
lbs per square foot forward of Station 323 and 150 lbs per square foot aft of Station 
323. 
Fuel Capacity: 410 gal (210 gal at (204), 200 gal at (306).) (Two-tank system) 
654 gal (210 gal at (204), 244 gal at (265), 200 gal at (306).) (Three-tank system) 
Oil Capacity: 5 gal. (181) (2 tanks 2.5 gal each). 
Rotor Blade & Control Movements: For rigging information, refer to Maintenance Manual.  
Serial Numbers Eligible: 61032 (See NOTE 14), 61143, 61159, 61164, 61216, 61220 through 61225, 61242, 
61257, 61258, 61267, 61268, 61269, 61270, 61297, 61298, 61299, 61361, 61364, 
61365, 61424, 61465 through 61476, 61487 through 61493, 61702 through 61705, 
61711 through 61722, 61735 through 61757, 61758 through 61762, 61764, 61765, 
61766 through 61778, 61806 through 61827.

5 of 13 1H15 
III. MODEL NUMBER: S-61R (Amphibious Transport Helicopter - Category B)  
(Model S-61R is the same as the Model S-61L except for the fuselage modified for a 
complete hull, a rear-loading ramp, airfoil shaped sponsons, retractable landing gear 
and a modified tail rotor pylon.) 
Approved: December 30, 1963 
Engines: 2 General Electric CT58-110-1 (with Hamilton Standard Fuel Control JFC-26). See 
NOTE 9 for optional engines. 
Fuel: Aviation Kerosene JP4 or JP5 (General Electric Company Specification Number 
D50TF2 or subsequent revisions thereto) 
Engine Limits: Sea level static - standard day 
SHAFT POWER TURBINE GAS GEN POWER TURBINE 
HP RPM RPM INLET (T5)  
Takeoff (5 min) 1,250 21,275(112.0%Nf)26,300(100%Ng) 1,250o F (677oC) 
Maximum continuous 1,050 21,275(112.0%Nf)26,300(100%Ng) 1,175o F (635oC) 
Maximum transient (2 sec) 1,544o F (840oC) 
Starting (4 sec) 1,544o F (840oC) 
Allowable maximum overspeed 23,100(122.0%Nf)27,600(105%Ng)  
(15 sec.) 
Takeoff and maximum continuous horsepower ratings are normally obtained at a 
power turbine speed of 18,966 rpm (100%Nf) 
Total power for two-engine operation is limited to 2,500 hp. for takeoff and 2,100 hp. 
maximum continuous. 
See NOTE 11 for variation of sea-level static power limits below 59oF. 
Rotor Limits: Maximum 225 r.p.m. 
Minimum 184 r.p.m. 
Airspeed Limits: Never exceed 165 m.p.h. (143 knots) CAS. 
C.G. Range: (+258.0) to (+276.0) 
Empty Weight C.G. Range: None 
Maximum Weight: 19,500 lb. 
Minimum Crew: 2 (pilot, copilot) 
Maximum Passengers: None 
Maximum Baggage: The cabin floor area between Stations 137.0 and 379.5 is structurally satisfactory for a 
uniformly distributed loading of 200 p.s.f. when used for cargo purposes. 
Fuel Capacity: 683 gal. (337 gal at (+215.3), 346 gal at (+317.3) 
Oil Capacity: 5.9 gal. (182.5) (2 tanks 2.95 gal each). 
Rotor Blade & Control Movements: For rigging information, refer to Maintenance Manual. 
Serial Numbers Eligible: 61501 through 61507, 61510 through 61517, 61521 through 61551, 61554 through 
61575, 61583 through 61585, 61587 through 61592, 61594, 61596, 61604 through 
61606, 61608 through 61617, 61620 through 61621, 61628.

1H15 6 of 13 
IV. MODEL NUMBER: S-61NM ( Transport Helicopter - Categories A & B)  
(The model S-61NM consists of S-61N components (tail cone and pylon, stabilizer and 
landing gear) combined with an S-61L fuselage.) 
Approved: July 12, 1974 
Engines: 2 General Electric CT58-110-1 (with Hamilton Standard Fuel Control JFC-26). See 
NOTE 9 for optional engines. 
Fuel: Aviation Kerosene JP4 or JP5 (General Electric Company Specification Number D50T 
F2 or subsequent revisions thereto) 
Engine Limits: Sea level static - standard day 
 SHAFT  
HP 
POWER TURBINE  
RPM 
GAS GEN  
RPM 
POWER TURBINE  
INLET (T5) 
Takeoff (5 min) 1,250 21,275(112.0%Nf) 26,300(100%Ng) 1,250o F (677oC) 
One engine inoperative (30 min) 1,250 21,275(112.0%Nf) 26,300(100%Ng) 1,250o F (677oC) 
(See NOTE 7)     
One engine inoperative (2 1/2 min) 1,350 21,275(112.0%Nf) 26,840(102%Ng) 1,300o F (704oC) 
(See NOTE 6)     
Maximum continuous 1,050 21,275(112.0%Nf) 26,300(100%Ng) 1,175o F (635oC) 
Maximum transient (2 sec)    1,544o F (840oC) 
Starting (4 sec)    1,544o F (840oC) 
Allowable maximum overspeed  23,100(122.0%Nf) 27,600(105%Ng)  
(15 sec.)  
Takeoff and maximum continuous horsepower ratings are normally obtained at a 
power turbine speed of 18,966 rpm (100%Nf) 
Total power for two-engine operation is limited to 2,300 hp. for takeoff and 2,100 hp. 
maximum continuous. (See NOTE 10 for alternate limits.) 
See NOTE 11 for variation of sea-level static power limits below 59oF. 
Rotor Limits: Maximum 225 r.p.m. 
Minimum 184 r.p.m. 
Airspeed Limits: Never exceed 150 m.p.h. (130 knots) CAS. 
C.G. Range: Category A (except (+258.0) to (+276.0) at 19,000 lb 
vertical and edge (+254.0) to (+280.0) at 16,000 lb or less  
procedures) and Category B 
Category A (+258.0) to (+276.0) at 19,000 lb or less 
(Vertical and edge procedures) 
 
 19,000  
 
Gross 
Weight 
(Lbs.) 
16,000 
 
   254 258 276 280 
Station - Inches

Production Basis: Production Certificate No. 105 
7 of 13 1H15 
IV. MODEL NUMBER:  S-61NM  (cont’d)  
Empty Weight C.G. Range: None 
Maximum Weight: Category A: 19,000 lb. (See Rotorcraft Flight Manual for lesser maximum weights for 
various Category A takeoff and landing procedures.) 
Category B: 19,000 lb. 
Minimum Crew: 2 (pilot, copilot) 
Maximum Passengers: 39, limited by emergency exit requirements 
Maximum Baggage: 670 lb (+130) 
690 lb (+168) 
660 lb (+267) 
590 lb (+340) 
530 lb (+380) 
450 lb (+407) 
The under-floor baggage bins must not be loaded in excess of 400 lbs per square foot 
within the maximum limits specified above. The cabin floor, when used for cargo 
purposes, should not be loaded in excess of 200 lbs per square foot forward of Station 
323 and 150 lbs per square foot aft of Station 323. 
Fuel Capacity: 410 gal (210 gal at (204), 200 gal at (306).) 
Oil Capacity: 5 gal. (181) (2 tanks 2.5 gal each). 
Rotor Blade & Control Movements: For rigging information, refer to Maintenance Manual. 
Serial Number Eligible: 61454 
THE FOLLOWING DATA IS PERTINENT TO ALL MODELS OF THIS SERIES: 
Datum: 267.4 in. forward of main rotor centroid 
Leveling Means: Leveling plates on sill and upper frame of forward door 
Certification Basis: CAR 7, August 1, 1956, including Amendments 7-1 through 7-4 and Special 
Conditions for Turbine Power Rotorcraft in FAA letter to Sikorsky Aircraft, March 31, 
1961. FAA Administrator telegram, Performance Requirements, dated August 7, 1961. 
Amendment 29-3 to Part 29 of the Federal Aviation Regulations, effective February 25, 
1968, eliminated the requirements of CAR 7.350(e) by deleting FAR 29.771(e) and 
FAR 29.771(f). 
Model S-61L: Exemption No. 178, dated August 9, 1961, and Exemption No. 186, 
dated October 6, 1961, and Exemption No. 244, dated January 30, 1963. 
Models S-61N and S-61NM: Exemption No. 186A, dated November 28, 1962. 
Model S-61R: Exemption No. 292, dated January 3, 1964. 
Model S-61N at 19,000 to 20,500 lbs gross weight: FAR 29.563, FAR 29.801, and 
FAR 29.807 of Amendment 12, effective February 1, 1977, to FAR Part 29. 
Type Certificate (TC) issued: November 2, 1961 
Date of Application: October 21, 1959

1H15 8 of 13 
Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see certification 
basis) must be installed in the helicopter for certification. In addition, the following items of equipment are 
required: 
(a) FAA Approved Rotorcraft Flight Manual, Model S-61L Helicopter (Publication No. SA 4045-30), 
dated November 2, 1961, reissued August 1, 1962. Revised January 29, 1982 (S/Ns prior to 61425) 
(i) Supplement No. 1, dated November 2, 1961. Reissued August 1, 1962. (S-61L Acceptable 
Engine Fuels and Oils) 
(ii) Supplement No. 3, dated September 9, 1963. Revised January 28, 1964. (S-61N Limited 
Amphibian) 
(iii) Supplement No. 5, dated August 27, 1964. Revised September 27, 1972. (S-61L AFCS) 
(iv) Supplement No. 11, dated October 6, 1964. Revised January 12, 1965. (S-61L HIR - Basic) 
(v) Supplement No. 12, dated October 6, 1964. Revised January 12, 1965. (S-61L HIR 
Operational) 
(vi) Supplement No. 13, dated June 8, 1965. Revised September 27, 1972. (S-61L Cargo Sling) 
(vii) Supplement No. 14, dated October 29, 1965. Reissued May 5, 1967. Revised May 20, 1980. 
(S-61L, CT58-140-1 and -2 engine) 
(viii) Supplement No. 15, dated December 30, 1965. Revised May 27, 1969. (S-61L, S/N 61266) 
(ix) Supplement No. 17, dated May 7, 1968. Revised September 12, 1979. (S-61, Vertical 
Operations, Ground-Level and Pinnacle Heliports) 
(x) Supplement No. 18, dated May 7, 1968. Revised September 12, 1979. (S-61L, Vertical 
Operations, Pinnacle Heliport) 
(xi) Supplement No. 19, dated May 31, 1968. Reissued August 9, 1968. Revised September 12, 
1979. (S-61L Edge Procedures) 
(xii) Supplement No. 20, dated July 12, 1968. (S-61L, CT58-110-2 Engine) 
(xiii) Supplement No. 21, dated August 13, 1970. (S-61L, Engine Inlet Screens) 
(xiv) Supplement No. 22, dated December 6, 1973. Reissued November 21, 1974. Revised May 20, 
1980. (S-61L, Icing Equipment, -1401 and -2 engines) 
(xv) Supplement No. 23, dated February 22, 1974. Revised October 3, 1980. (S-61L, 22,000 
Pounds Operation) 
(b) FAA Approved Rotorcraft Flight Manual, Model S -61L Helicopter (Publication No. SA 4045 -100), 
dated April 10, 1970. Revised January 29, 1982. (S/Ns 61425 and subsequent) 
(i) Supplement No. 1, dated May 15, 1970. Revised September 12, 1979. (Vertical Operation, 
Ground-level Heliports) 
(ii) Supplement No. 2, dated May 15, 1970. Revised September 12, 1979. (Vertical Operations, 
Elevated Heliports) 
(iii) Supplement No. 3, dated September 9, 1970. Revised September 12, 1979. (Edge Procedures) 
(iv) Supplement No. 4, dated December 6, 1973. Reissued November 21, 1974. Revised May 20, 
1980. (Icing Equipment, -140 engines) 
(v) Supplement No. 5, dated August 13, 1970. (Engine Inlet Screens) 
(vi) Supplement No. 6, dated April 15, 1974. Revised October 3, 1980. (22,000 Pound Operation) 
(c) FAA Approved Rotorcraft Flight Manual, Model S -61N Helicopter, (Publication No. SA 4045-82), 
dated September 9, 1963. Reissued December 17, 1971. Revised November 27, 1981. 
(i) Supplement No. 11, dated July 12, 1974. (S-61NM) 
(ii) Supplement No. 12, dated November 25, 1975. Revised April 14, 1978. (S/N 61749 only) 
(iii) Supplement No. 13, dated February 10, 1977. (S/N 61761 only) 
(iv) Supplement No. 14, dated March 30, 1977. Revised October 5, 1977. (S/N 61764 only)  
(v) Supplement No. 15, dated September 9, 1977. Revised September 12, 1979. 
(vi) Supplement No. 16, dated October 20, 1977. Revised October 3, 1980. 
(d) FAA Approved Rotorcraft Flight Manual, Model S-61R Helicopter (Publication No. SA 4045-78), dated 
December 30, 1963. Reissued May 8, 1964. Revised December 11, 1964. 
(i) Supplement No. 1, dated October 29, 1965. Revised June 22, 1966. (CT58-140-1 engine) 
(ii) Supplement No. 2, dated October 20, 1977.

9 of 13 1H15 
NOTE 1: Current weight and balance report including list of required equipment and list of equipment included in 
certificated empty weight, and loading instructions when necessary, must be provided for each helicopter at the 
time of original certification. 
NOTE 2: The following placard must be displayed in front of and in clear view of the pilot: 
"THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING 
LIMITATIONS SPECIFIED IN THE FAA APPROVED HELICOPTER FLIGHT MANUAL." 
NOTE 3: Information essential to the proper maintenance of the helicopter is contained in the manufacturer's maintenance 
manual provided with each helicopter, which specifies that service life limited parts be retired in accordance with 
the following: 
Models S-61L, S-61N, and S-61NM  
Section 2C. "List of retireable parts and time limits," of Sikorsky Service Bulletin No. 61B General-1L, dated 
December 16, 1981 or latest revision. 
Model S-61R 
Part Number 
Service Life  
(Hours)  
Main Rotor Blade Assembly S6117-20101 8,000 
Primary Servo Trunnion Assembly S6165-20232 7,700 
Primary Servo Housing Assembly S6165-20202 8,100 
Control Horn Eyebolt S6112-23072 10,600 
Main Transmission T.T.O. Bearing SB2103-2 200 
(As installed in MGB P/N S6137-23000-1 thru -9 or 
subsequent approved MGB. See note 9) 
  
Rotary Wing Head Damper Piston S6110-26019-0 3,400 
Rod Assembly S6110-26019-1 3,400 
Rotary Wing Head, Damper, S6110-26403-2 5,100 
Cylinder and Head Assembly   
Rotary Wing Head, Damper, Piston Rod S6110-26020-2 5,400 
Rotary Wing Head, Damper, NAS 627-H-14 4,400 
Lower Attachment Bracket Bolts   
Rotary Wing Head, Damper, Trunnion S6110-26045-7 2,400  
NOTE 4: Prior to civil certification, military Model CH-3C andCH-3E helicopters must be modified in accordance with 
instructions provided by Sikorsky Aircraft. 
NOTE 5: A modification of the Model S-61N, replacing the amphibious landing gear with a Sikorsky Model S-61L fixed 
land type gear in accordance with Sikorsky Aircraft Drawing S6107-25112, "Modification Kit, Sponson to Fixed 
Landing Gear," has been approved for operations at 20,500 lbs. gross weight. With this modification, the Model 
S-61N is converted to a Transport Helicopter (Categories A & B). 
NOTE 6: Engine controls must be set to this rating for Category A vertical operation (Ground-level and Elevated Heliports) 
and Category A Elevated Heliport Edge Procedures. 
NOTE 7: If take-off power is used in cumulative excess of 5 minutes during any one emergency, the engine must be 
inspected in accordance with G.E. Commercial Engine Service Memorandum CT58-110-1, Maintenance No. 19, 
April 17, 1962. 
NOTE 8: The hoist and cargo sling are special purpose equipment and information concerning the operating limitations for 
this equipment is contained in the Rotorcraft Flight Manual.

1H15 10 of 13 
(15 sec.)  
NOTE 9: Optional engines eligible for installation and the applicable limitations: 
Engines (2): (a) General Electric CT58-110-2 (with Hamilton Standard Fuel Control JFC-26) NOTE: 
Eligible on S-61L and S-61N models only. 
Engine Limits: Sea Level Static - Standard Day (Same as CT58-110-1) 
(b) General Electric CT58-140-1 (with Hamilton Standard Fuel Control JFC-26) 
Engine Limits: Sea Level Static - Standard Day 
Takeoff (5 min) 
One engine inoperative (30 min) 
(See NOTE 7) 
One engine inoperative (2 1/2 min) 
(See NOTE 6) 
Maximum continuous 
Maximum transient (2 sec) 
Starting (2 sec) 
Allowable maximum overspeed 
SHAFT  
HP 
POWER TURBINE  
RPM 
GAS GEN  
RPM 
POWER TURBINE  
INLET (T5) 
1,400 
1,400 
1,500 
1,250 
21,275(112.0%Nf)  
21,275(112.0%Nf) 
21,275(112.0%Nf)  
21,275(112.0%Nf) 
23,100(122.0%Nf) 
26,300(100%Ng) 
26,300(100%Ng) 
26,800(102%Ng) 
26,300(100%Ng) 
27,600(105%Ng) 
1,285o F (696oC)  
1,285o F (696oC) 
1,330o F (721oC) 
1,220o F (660oC) 
1,545o F (840oC) 
1,740o F (950oC) 
(15 sec.)  
Takeoff and maximum continuous horsepower ratings are normally obtained at a 
power turbine speed of 18,966 rpm (100%Nf) 
Total power for two-engine operation is limited to 2,300 hp. for takeoff for S-61L/N 
rotorcraft (See NOTE 10 for alternate limits) and 2,500 hp. for takeoff for S-61R (CH-
3E, HH-3E) rotorcraft. Maximum continuous total power for two-engine operation is 
limited to 2,100 hp. 
See NOTE 11 for variation of sea-level static power limits below 59oF. 
The use of optional engine Model CT58-140-1 in the S-61 L, S-61N and S-61NM is 
permitted only when main gearbox part numbers S6135-20600-12 through -15, -18 
through -28,  -31 through -48 is installed, and left engine cowl, part number S6130-
80142, is modified for increased cooling provisions per Sikorsky Engineering Order 
No. 65718. Refer to Rotorcraft Flight Manual for use of engine inlet duct, part number 
S6130-80179, with oil tank mounting ring, part number S6132-80205. 
Use of the optional engine Model CT58-140-1 in the S-61R is permitted when the main 
gearbox part numbers are S6137-23000-017 or -018. 
(c) General Electric CT58-140-2 (with Hamilton Standard Fuel Control 725725-1). 
Engine Limits: Sea Level Static - Standard Day 
Takeoff (5 min) 
One engine inoperative (30 min) 
(See NOTE 7) 
One engine inoperative (2 1/2 min) 
(See NOTE 6) 
Maximum continuous 
Maximum transient (2 sec) 
Starting (2 sec) 
Allowable maximum overspeed 
SHAFT  
HP 
POWER TURBINE  
RPM 
GAS GEN  
RPM 
POWER TURBINE  
INLET (T5) 
1,400 
1,400 
1,500 
1,250 
21,275(112.0%Nf)  
21,275(112.0%Nf) 
21,275(112.0%Nf)  
21,275(112.0%Nf) 
23,100(122.0%Nf) 
26,300(100%Ng) 
26,300(100%Ng) 
27,200(103.4%Ng) 
26,300(100%Ng) 
27,600(105%Ng) 
1,285o F (696oC)  
1,285o F (696oC) 
1,397o F (758oC) 
1,220o F (660oC) 
1,545o F (840oC) 
1,740o F (950oC)

11 of 13 1H15 
Total power for two-engine operation is limited to 2,300 hp. for takeoff for S -61L/N 
rotorcraft (See NOTE 10 for alternate limits). 
See NOTE 11 for variation of sea-level static power limits below 59°F.

1H15 12 of 13 
NOTE 9: (cont’d) The use of optional engine Model CT58-140-2 in the S-61L, S-61N, and S-61NM is 
permitted only when main gearbox part numbers S6135-20600--12 through -15, - 18 
through -28, -31 through -48 is installed, and left engine cowl, part number S6130-80142, 
is modified for increased cooling provisions per Sikorsky Engineering Order No. 65718. 
Refer to Rotorcraft Flight Manual for use of engine inlet duct, part number S6130-80179, 
with oil tank mounting ring, part number S6132-80205. 
Use of the optional engine Model ST-58-140-2 is not permitted in the S-61R. 
NOTE 10: Two-engine operation limits are increased to 2,500 hp. for takeoff when the S6135-20600-12 through -15, -18 
through -28 or -31 through -48 main transmission is installed. The maximum continuous limit of 2,100 hp. is 
unchanged. 
NOTE 11: Below 59oF the sea-level static power limits vary as follows: 
CT58-110-1, CT58-110-2 CT58-140-1 CT58-140-2 
2-1/2 Min helicopter No variation - engine is flat 
rated at 1,350 hp. at 59oF 
and below. 
Takeoff and 30 Min. Helicopter            Increases from 1,250 hp. 
at 59oF to 1,350 hp. at 
+23oF and flat rated below 
this temperature. 
Max. Continuous Increases linearly from 
1,050 hp. at 59oF to 1,230 
hp. at 29oF and flat rated at 
1,230 hp. at 29oF and 
below. 
Increases linearly from 
1,500 hp. at 59oF to 1,545 
hp. at -65oF. 
Increases linearly from 
1,400 hp. at 59oF to 1,510 
hp. at 22oF and to 1,540 
hp. at -65oF. 
Increases linearly from 
1,250 hp. at 59oF to 1,390 
hp. at 39oF and flat rated at 
1,390 hp. at 39oF and 
below. 
Increases linearly from 
1,500 hp. at 59oF to 1,560 
hp. at -65oF. 
Increases linearly from 
1,400 hp. at 59oF to 1,530 
hp. at 13oF and to 1,560 
hp. at -65oF. 
 
NOTE 12: The maximum rotorcraft-external load weight is 22,000 lb. under the condition specified in the following 
Rotorcraft Flight Manual Supplements, in accordance with FAR 133 operations: S -61L Supplement No. 6; 
S-61N Supplement No. 16. 
NOTE 13: Model S-61N (Transport Helicopter - Categories A & B) 
Date Approved: September 9, 1977 
The S-61N is approved for operations at gross weights from 19,000 to 20,500 pounds when the following 
components are installed: 
Main Rotor Blades, P/Ns 61170-20201-055 and subsequent, S6115-20501-041 and subsequent, and S6115 -
20601-047, -048, and subsequent. 
Tail Rotor Blades, P/N S6117-30101-043 and subsequent. 
Engines, G.E. CT58-140-1 and 140-2. 
Main Gearbox, P/Ns S6135-20600-12 through -15, -18 through -28, -31 through -048. 
Bifilar Assembly, P/N S6112-23039-017 or S6112-23039-018. 
Beam, Pitch Control (Tail Gearbox), P/N S6135-66705-1. 
Airspeed Limits:  
Category A: Never exceed 140 m.p.h. (122 knots) IAS 
Category B: Never exceed 144 m.p.h. (125 knots) IAS

254 258 275.6 276 280 
13 of 13 1H15 
C.G. Range:  
(258.0) to (275.6) at 20,500 lbs. 
(258.0) to (276.0) at 19,000 lbs. 
(254.0) to (280.0) at 16,000 lbs. or less 
(Above values apply to aircraft with two-tank fuel system. Refer to Flight Manual for additional limitations 
associated with the three-tank fuel system.) 
 
 20,500 
 
19,000 
Gross 
 
Weight 
 (Lbs.) 
 
 16,000 
 
Station - Inches 
Empty Weight C.G. Range: None 
Maximum Weight: Category A: 20,500 lb. (See Rotorcraft Flight Manual for lesser maximum weights for 
various Category A takeoff and landing procedures.) 
Category B: 20,000 lb. 
Above 19,000 lbs. gross weight, the helicopter is approved for over-water flights 
and emergency w ater landings provided that life saving equipment is installed that 
meets the requirements of FARs 29.1411, 29.1415, and 29.1561. 
NOTE 14: See Carson's Rotorcraft Aircraft Records for Sikorsky Model S-61L (S/N 61032) and STC SH1261EA, amended 
January 22, 1982, for Rotorcraft Model status (FAA Form 8130-6, December 17, 1981, FAA Forms 337, dated 
December 15 and 17, 1981) - Conversion of S-61L (S/N 61032 only) to S-61N and fuel tanks and system 
installation (total of five fuel tanks) and required applicable FAA approved (Carson and Sikorsky) documents. 
NOTE 15: The following helicopters have been converted:  
Surplus Eligible For 
Serial Military Certification as 
Number Model  Civil Model Modifier 
61551 CH-3C S-61R Carson Services, Inc. 
END
```

## ADs (58, first 50, in force first)

- [AD 2026-15-17](https://openairdocs.org/ad/2026-15-17): Main Rotor Gearbox · Glacier Helicopter CH-3E, S-61A, S-61D and 12 more. Effective Sep 10, 2026
- [AD 2026-11-05](https://openairdocs.org/ad/2026-11-05): Rotorcraft flight control; Rotorcraft servo system · Carson Helicopters S-61L, SH-3H, CH-3E and 11 more. Effective Jul 9, 2026
- [AD 2023-11-07](https://openairdocs.org/ad/2023-11-07): Ground Proximity System · Airbus Helicopters 47, 206, 210 and 237 more. Effective Jun 22, 2023
- [AD 2022-05-10](https://openairdocs.org/ad/2022-05-10): Cabin Equipment/Furnishings · Airbus Helicopters AS332L, AS332L1, AS332L2 and 57 more. Effective Apr 20, 2022
- [AD 2021-05-19](https://openairdocs.org/ad/2021-05-19): Tail Rotor Control System · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective May 7, 2021
- [AD 2013-06-51](https://openairdocs.org/ad/2013-06-51): Equipment/Furnishings · Agusta A109, A109A, A109A II and 43 more. Effective Jul 15, 2013
- [AD 2013-05-17](https://openairdocs.org/ad/2013-05-17): Aircraft Fuel Filter/Strainer · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective Apr 26, 2013
- [AD 2007-01-05](https://openairdocs.org/ad/2007-01-05): Main gearbox input left and right freewheel unit (IFWU) assembly · Sikorsky S-61L, S-61N, S-61NM and 1 more. Effective Feb 14, 2007
- [AD 2004-15-22](https://openairdocs.org/ad/2004-15-22): Bearing chip detector · Sikorsky S-61L, S-61N, S-61NM and 1 more. Effective Sep 7, 2004
- [AD 2002-20-05](https://openairdocs.org/ad/2002-20-05): Rescue hoists · Agusta A109, A109A, A109A II and 31 more. Effective Nov 7, 2002
- [AD 2000-13-06](https://openairdocs.org/ad/2000-13-06): Web Fittings · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective Jul 18, 2000
- [AD 98-26-02](https://openairdocs.org/ad/98-26-02): Shaft · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective Jan 20, 1999
- [AD 97-19-06](https://openairdocs.org/ad/97-19-06): Blade Trailing Edge Pocket Assemblies · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective Oct 6, 1997
- [AD 91-12-01](https://openairdocs.org/ad/91-12-01): Sleeve & Spindle Assemblies · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective Jul 8, 1991
- [AD 89-04-01 R3](https://openairdocs.org/ad/89-04-01-R3): Truss Tube Assemblies · Sikorsky S-61N and S-61NM. Effective Feb 5, 1990
- [AD 90-01-04](https://openairdocs.org/ad/90-01-04): Main Rotor Hub Upper Plate · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective Feb 5, 1990
- [AD 89-07-09](https://openairdocs.org/ad/89-07-09): Main Rotor Gearbox · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective Apr 20, 1989
- [AD 85-18-05 R2](https://openairdocs.org/ad/85-18-05-R2): Main Rotor Blades · Sikorsky S-61A, S-61L, S-61N and 3 more. Effective Feb 8, 1989
- [AD 87-15-11](https://openairdocs.org/ad/87-15-11): Gearbox Brackets · Sikorsky S-61A, S-61L, S-61N and 3 more. Effective Aug 10, 1987
- [AD 86-23-08](https://openairdocs.org/ad/86-23-08): Main Rotor Hub Lower Plate · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective Apr 21, 1987
- [AD 84-25-01](https://openairdocs.org/ad/84-25-01): Main Gearbox Inspection · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective Jan 19, 1985
- [AD 84-11-03](https://openairdocs.org/ad/84-11-03): Possible Flange Failure · Sikorsky S-61A, S-61L and S-61N. Effective Jun 6, 1984
- [AD 84-01-51](https://openairdocs.org/ad/84-01-51): Rotary Wing Head Shaft Nut · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective Mar 27, 1984
- [AD 74-20-07 R5](https://openairdocs.org/ad/74-20-07-R5): Main Rotor Blades · Sikorsky S-61A, S-61L, S-61N and 3 more. Effective Dec 30, 1983
- [AD 78-20-05 R4](https://openairdocs.org/ad/78-20-05-R4): Main Rotor Spindles · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective May 25, 1983
- [AD 76-08-01 R1](https://openairdocs.org/ad/76-08-01-R1): Tail Rotor Pylon · Sikorsky S-61A, S-61D, S-61E and 2 more. Effective Dec 29, 1980
- [AD 80-17-07](https://openairdocs.org/ad/80-17-07): Horizontal Hinge Pins · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective Aug 15, 1980
- [AD 78-05-07](https://openairdocs.org/ad/78-05-07): Main Landing Gear · Sikorsky S-61N. Effective Apr 13, 1978
- [AD 74-20-09](https://openairdocs.org/ad/74-20-09): Main Rotor Blades · Sikorsky S-61A, S-61L, S-61N and 2 more. Effective Feb 25, 1977
- [AD 76-06-01](https://openairdocs.org/ad/76-06-01): Hydraulic Pumps · Erickson Air-Crane S-64A, S-64E, S-64F and 12 more. Effective Mar 24, 1976
- [AD 76-03-02](https://openairdocs.org/ad/76-03-02): Fractures in Barrel Nuts · Sikorsky S-61L, S-61N, S-61NM and 1 more. Effective Feb 17, 1976
- [AD 75-26-10](https://openairdocs.org/ad/75-26-10): Component Replacement · Sikorsky S-61L, S-61N and S-61NM. Effective Jan 2, 1976
- [AD 68-19-07](https://openairdocs.org/ad/68-19-07): Rotor Blade Spindles · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective Dec 23, 1975
- [AD 75-17-33](https://openairdocs.org/ad/75-17-33): Baggage Doors · Sikorsky S-61L, S-61N and S-61NM. Effective Oct 3, 1975
- [AD 75-12-01](https://openairdocs.org/ad/75-12-01): Main Rotor Blades · Sikorsky S-61L, S-61N, S-61NM and 1 more. Effective Jun 12, 1975
- [AD 74-25-05](https://openairdocs.org/ad/74-25-05): Main Rotor Blades · Sikorsky S-61L, S-61N, S-61NM and 1 more. Effective Nov 6, 1974
- [AD 74-25-06](https://openairdocs.org/ad/74-25-06): Takeoff Gross Weight Limitation · Sikorsky S-61L, S-61N and S-61NM. Effective Oct 16, 1974
- [AD 73-15-01](https://openairdocs.org/ad/73-15-01): Rear Fuselage and Pylon Fittings · Sikorsky S-61A, S-61D, S-61E and 2 more. Effective Jul 27, 1973
- [AD 72-25-04](https://openairdocs.org/ad/72-25-04): Loss of Main Rotor Control · Sikorsky S-61A, S-61D, S-61L and 3 more. Effective Dec 15, 1972
- [AD 72-16-06](https://openairdocs.org/ad/72-16-06): Electrical Feeder Wire Gage · Sikorsky S-61A, S-61L, S-61N and 1 more. Effective Aug 10, 1972
- [AD 72-03-01](https://openairdocs.org/ad/72-03-01): Alum. Forgings Flight Control System · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective Feb 1, 1972
- [AD 71-21-03](https://openairdocs.org/ad/71-21-03): Link in Servo Valve Input Linkage · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective Oct 7, 1971
- [AD 71-05-01](https://openairdocs.org/ad/71-05-01): Main Landing Gear Axle · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective Feb 23, 1971
- [AD 68-20-08](https://openairdocs.org/ad/68-20-08): Functional Test of AFCS · Sikorsky S-61A, S-61L and S-61N. Effective Jan 14, 1971
- [AD 70-15-01](https://openairdocs.org/ad/70-15-01): Cabin Heater Blower · Sikorsky S-61A, S-61L, S-61N and 1 more. Effective Jul 22, 1970
- [AD 70-09-03](https://openairdocs.org/ad/70-09-03): Tail Gear Box Pitch Beams · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective May 8, 1970
- [AD 70-08-03](https://openairdocs.org/ad/70-08-03): Heater Inlet Check Valve · Sikorsky S-61A, S-61L, S-61N and 1 more. Effective Mar 17, 1970
- [AD 68-21-06](https://openairdocs.org/ad/68-21-06): Deactivate AFCS · Sikorsky S-61A, S-61L and S-61N. Effective Oct 24, 1968
- [AD 67-29-05](https://openairdocs.org/ad/67-29-05): Rotary Wing Hub Hinge Pins · Sikorsky S-61A, S-61D, S-61E and 5 more. Effective Oct 30, 1967
- [AD 66-19-04](https://openairdocs.org/ad/66-19-04): Tail Rotor Blades · Sikorsky S-58A, S-58B, S-58BT and 20 more. Effective Aug 14, 1966

All 58: https://openairdocs.org/tcds/1H15/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Sikorsky S-61N](https://openairdocs.org/model/sikorsky-s-61n): 45 aircraft (registry code 8142104)
- [Sikorsky S-61L](https://openairdocs.org/model/sikorsky-s-61l): 1 aircraft (registry code 8142102)
- [Sikorsky S-61NM](https://openairdocs.org/model/sikorsky-s-61nm): 1 aircraft (registry code 8142105)
- [Sikorsky S-61R](https://openairdocs.org/model/sikorsky-s-61r): 1 aircraft (registry code 8142106)
- [Sikorsky CH 3C](https://openairdocs.org/model/sikorsky-ch-3c): 0 aircraft (registry code 8142108)
- [Sikorsky CH3E](https://openairdocs.org/model/sikorsky-ch3e): 0 aircraft (registry code 8142112)
- [Sikorsky S-61R (CH-3E)](https://openairdocs.org/model/sikorsky-s-61r-ch-3e): 0 aircraft (registry code 8142000)
- [Sikorsky/Carson Services S61N](https://openairdocs.org/model/sikorsky-carson-services-s61n): 0 aircraft (registry code 8142111)

## STCs approved under this data sheet (115, first 50)

- [STC SR04465NY](https://openairdocs.org/stc/SR04465NY): Installation of the iPad Mount. Avio Design Group Inc
- [STC SR01858SE](https://openairdocs.org/stc/SR01858SE): Manufacture of the Isolair, Inc., Eliminator II Model 4600-S61 Fire Fighting System. Isolair Inc.
- [STC SR00218IB](https://openairdocs.org/stc/SR00218IB): Installation of the Cockpit Door. Croman Corporation
- [STC SR00220IB](https://openairdocs.org/stc/SR00220IB): Installation of Replacement Avionics Shelves. Croman Corporation
- [STC SR00283SE](https://openairdocs.org/stc/SR00283SE): Removal of a 50 inch section from the forward fuselage between stations 110 and 160 and reinstallation of forward cabin with associated fabricated parts.. Croman Corporation
- [STC SR00427SE](https://openairdocs.org/stc/SR00427SE): Fabrication and installation of a Helipro Model H9661N01-01, -03, -05, -07, -51, -53, -55, -57, -59 or -61 logging utility system. Croman Corporation
- [STC SR00814SE](https://openairdocs.org/stc/SR00814SE): Fabrication of reinforcement kit - aft fuselage station 493. For model S61A, applies to S/N 61094. For model S61NM, applies to S/N 66454. Croman Corporation
- [STC SR01264SE](https://openairdocs.org/stc/SR01264SE): Fabrication of Helipro replacement windshields. Croman Corporation
- [STC SH3319NM](https://openairdocs.org/stc/SH3319NM): Installation of Precise Flight Pulselite Control Unit in the
Landing /Taxi Recognition Visual Control Light system,. Precise Flight Inc
- [STC SR02279AK](https://openairdocs.org/stc/SR02279AK): Installation of dual Rockwell Collins FDS 2000 flight displays, dual AHS 3000 attitude and heading reference systems, dual Garmin GNS 530 navigation systems and supporting avionics equipment. Croman Corporation
- [STC SR09236RC](https://openairdocs.org/stc/SR09236RC): Installation of a Modular Harness. Croman Corporation
- [STC SR04501CH](https://openairdocs.org/stc/SR04501CH): The certification of various configurations of cockpit side windows. CHI Aviation
- [STC SR01127SE](https://openairdocs.org/stc/SR01127SE): Modification of main rotor blade part number 61170-20201 in accordance with Master Drawing List RR 9633-08, Revision A, dated September 17, 2002, or later FAA approved revision.  Retirement life for the modified main rotor blade, part number RR-61170-20201 is 21,200 total time in service.. Park Technologies, LLC
- [STC SR00039IB](https://openairdocs.org/stc/SR00039IB): Installation of Coulson Aircrane Limited (CAL) Hoist Replacement Parts. Coulson Aircrane Ltd.
- [STC SR09490RC](https://openairdocs.org/stc/SR09490RC): Installation of nine passenger seat configuration. McHenry Priestley Aviation LLC
- [STC SR00681SE](https://openairdocs.org/stc/SR00681SE): Fabrication of Onboard Systems Model 200-243-00 or 200-243-01 Cargo Hook Load Weigh System. Onboard Systems International
- [STC SR01552SE](https://openairdocs.org/stc/SR01552SE): Fabrication and installation of an external aerial liquid dispensing tank. Carson Helicopters Inc
- [STC SR04607NY](https://openairdocs.org/stc/SR04607NY): Installation of Garmin GTX Transponder System. Maxcraft Avionics Ltd.
- [STC SR04609NY](https://openairdocs.org/stc/SR04609NY): Installation of Garmin HTAWS (Helicopter Terrain Awareness Warning System). Maxcraft Avionics Ltd.
- [STC SR04483CH](https://openairdocs.org/stc/SR04483CH): Installation of NASI NREM18M Air Conditioning Module. National Aircraft Service Inc. (NASI)
- [STC SR00925DE](https://openairdocs.org/stc/SR00925DE): Installation of Garmin GTX 335/335R and GTX345/345R transponders to provide ADS-B Out and In functionality. Peregrine
- [STC SR04401NY](https://openairdocs.org/stc/SR04401NY): Increase of Out of Ground Effect (OGE) Hover Performance. Carson Helicopters Inc
- [STC SR04122NY](https://openairdocs.org/stc/SR04122NY): The Installation of Carson Helicopters, Inc. Composite Tail Rotor Blade and Pitch Sleeve, part number 428-600-1,. Carson Helicopters Inc
- [STC SR02596SE](https://openairdocs.org/stc/SR02596SE): Installation of Olympic Aero Services, Inc. Additional Telemetry Unit (ATU). OLYMPIC AERO SERVICES INC.
- [STC SR02487NY](https://openairdocs.org/stc/SR02487NY): Increased Category A Performance for the Sikorsky S-61L, S-61N and S-61NM Helicopters.. Carson Helicopters, Inc
- [STC SR03324NY](https://openairdocs.org/stc/SR03324NY): One Helicopter-only conversion of Sikorsky Model S-61L S/N 61428 to an S-61N configuration. Carson Helicopters, Inc
- [STC SR02583SE](https://openairdocs.org/stc/SR02583SE): Installation of a 9 passenger seat configuration for side-facing seats. Croman Corporation
- [STC SR02507NY](https://openairdocs.org/stc/SR02507NY): Installation of a 600 pound capacity Goodrich AC rescue hoist system P/N 44311-10-2. Carson Helicopters, Inc
- [STC SR03664NY](https://openairdocs.org/stc/SR03664NY): Installation of the Engine Inlet Barrier Filter System (IBFS). Coulson Aircrane Ltd.
- [STC SR02267SE](https://openairdocs.org/stc/SR02267SE): Fabrication of replacement transmission fittings. Croman Corporation
- [STC SR02394AK](https://openairdocs.org/stc/SR02394AK): Replacement of existing landing and/or hover light bulbs with Light Emitting Diode (LED) lighting system. Seaplanes North LLC
- [STC SR03310CH](https://openairdocs.org/stc/SR03310CH): Installation of NASI Air Conditioning Module. National Aircraft Service Inc
- [STC SH5125NM](https://openairdocs.org/stc/SH5125NM): Installation of Croman 10,000 lbs. cargo sling system and associated fuselage mounting hardpoints.. Croman Corporation
- [STC SR02501LA](https://openairdocs.org/stc/SR02501LA): Removal of the Bendix 30E20-11-C 300 Amp Starter Generator and installation of the AMETEK Aerospace MG105A-1, 300 Amp Starter Generator. Carson Helicopters, Inc
- [STC SR01426SE](https://openairdocs.org/stc/SR01426SE): Fabrication and installation of components for a left seat pilot-in-command operation.. Croman Corporation
- [STC SR01480SE](https://openairdocs.org/stc/SR01480SE): Fabrication and installation of an external firefighting tank.. Carson Helicopters, Inc
- [STC SR02327AK](https://openairdocs.org/stc/SR02327AK): Manufacture side-facing seat mounting structure. Carson Helicopters, Inc
- [STC SR00319SE](https://openairdocs.org/stc/SR00319SE): Modification of Part Number S6137-23009-6 main transmission rear cover per. Croman Corporation
- [STC SR01534SE](https://openairdocs.org/stc/SR01534SE): Installation of the transmission input modification to the main gear box. Croman Corporation
- [STC SR02248SE](https://openairdocs.org/stc/SR02248SE): Installation of a Supplemental Lighting System.. Aviation Specialties Unlimited Inc.
- [STC SR01853NY](https://openairdocs.org/stc/SR01853NY): Installation of a SkyTrac ISAT-100 / ISAT-200 Airborne Position/Data Communicator. SkyTrac Systems Ltd.
- [STC SR00465SE](https://openairdocs.org/stc/SR00465SE): Installation of a Mechanical Specialties Model 611 cargo hook. Mechanical Specialties Inc
- [STC SR09232RC](https://openairdocs.org/stc/SR09232RC): Installation of a ground inverter.. Vector Aerospace Helicopter Services USA Inc.
- [STC SR09233RC](https://openairdocs.org/stc/SR09233RC): Installation of a Solid State Voltage Regulator. Vector Aerospace Helicopter Services USA Inc.
- [STC SR02190SE](https://openairdocs.org/stc/SR02190SE): Installation of steel transmission fitting fabricated in accordance with Croman Drawing S-6120-62113-CRO41, Revision D, dated January 8, 1982, or later Federal Aviation Administration (FAA) approved revision; installed in accordance with Croman Installation Instructions S-6120-62113-CRO41-Inst, Revision IR, dated August 10, 2011, or later FAA- approved revision.. Croman Corporation
- [STC SR01771NY](https://openairdocs.org/stc/SR01771NY): Increase of Out of Ground Effect (OGE) Hover Performance.. Carson Helicopters Inc
- [STC SR02335AK](https://openairdocs.org/stc/SR02335AK): Installation of two or three tank fuel quantity indicating systems when installed. Carson Helicopters, Inc
- [STC SR02336AK](https://openairdocs.org/stc/SR02336AK): Installation of an Integrated Cockpit Display System (ICDS) with an Attitude and Heading Reference System (AHRS) for Dual Pilot Instrument Flight Rules Category A and B operation in accordance with Vector Aerospace Helicopter Services Inc. Master Drawing List , HP 61-34-33-105, Revision A, dated February 28, 2011, or later FAA approved revision.. Carson Helicopters, Inc
- [STC SR02999NY](https://openairdocs.org/stc/SR02999NY): Installation of Auxiliary External Torque Gauge and External Load Meter  in accordance with VIH Aerospace Inc., Master Document List VS61-0715J-MDL, Revision A,  Dated January 24, 2011, approved by Transport Canada Civil Aviation (TCAA) on February 15, 2011, or later TCCA approved revisions.. VIH Aerospace Inc
- [STC SR02087SE](https://openairdocs.org/stc/SR02087SE): Limit the standard passenger seating configuration to 19 or less on the Sikorsky S-61N rotorcraft. Croman Corporation

All 115: https://openairdocs.org/tcds/1H15/stcs.md

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