# TCDS H1NE: Sikorsky Aircraft Corporation

- Type: Type certificate data sheet
- Status: Current
- Holder: Sikorsky Aircraft Corporation
- Revision: 48
- Revised: January 29, 2021
- Product: Aircraft, Rotorcraft
- Certification basis: Part 29, Part 29, Part 29, Part 29
- Registered aircraft: 198, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/08/99/0899ab9b427b7fc5bcec3d9ad12fc85a28b037d8277b7d4bca80b66324c9a916
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/288F41E936FA17A58625869C005D7C93.0001
- Page: https://openairdocs.org/tcds/H1NE

## Models (4)

As the data sheet lists them.

- S-76D
- S-76B
- S-76C
- S-76A

## What the data sheet says

Some pages are OCR from the scanned FAA data sheet. OCR can misread letters and numbers.

```text
Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 
Rev 48 20 23 20 20 24 21 21 21 48 48 44 44 44 44 47 48 45 
 
41 43 40 48 48 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
H1NE 
Revision No 48 
 
Sikorsky 
Models S-76A 
S-76B 
S-76C 
S-76D 
January 29, 2021 
 
TYPE CERTIFICATE DATA SHEET NO. H1NE 
 
This data sheet, which is part of Type Certificate (TC) Number H1NE, prescribes conditions and limitations under which the 
product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. 
 
TYPE CERTIFICATE (TC) HOLDER: Sikorsky Aircraft Corporation 
 6900 Main Street 
 Stratford, CT 06497-9129 
 
 I. MODEL NUMBER S-76A (Transport Helicopter, Category B), Approved November 21, 1978 
                   (Transport Helicopter, Category A), Approved January 9, 1979 
 
ENGINES  2 Allison Engine Company Model 250-C30, or 2 Model 250-C30S,  
   or 1 each Model 250-C30 and Model 250-C30S. (See Note 11.)  
 
FUEL  PRIMARY:   JP-4/JP-5**/JP-8/Jet A**/Jet A1**/Jet B/GB6537-94(RP-3)**  
 
   ALTERNATE:  **AVGAS/Jet A, A1, or JP5 mixture. 
     Do not use above 4oC (40oF).  (See Note 5.) 
 
     ** For operations below 4oC (40oF), anti-ice additive 
     required. (See Note 6.) 
 
ENGINE LIMITS 
 
SEA LEVEL STATIC / STANDARD DAY                                        
TORQUE 
LIMITS 
GAS GENERATOR 
SPEED  LIMITS (N1) 
POWER TURBINE 
INLET(T5) 
Takeoff (5 minutes) 
Maximum Continuous 
OEI (30 minutes) 
OEI (2-1/2 minutes) 
16 second transient (OEI) 
10 second Transient (Starting) 
104.6% 
104.6% 
104.6% 
111.2% 
111.2% to 155.0% 
- - -  
53,550 (105.0%) 
53,550 (105.0%) 
53,550 (105.0%) 
53,550 (105.0%) 
- - - 
53,550 (105.0%) to 54,060 (106%) 
768  Deg C 
768  Deg C 
798 Deg C 
826 Deg C 
- - - 
826 to 927 Deg C 
 
OUTPUT SHAFT (N2) 
 
 Normal Range 95% to 107% 
 
 Maximum Continuous Varies linearly from 114% at flight autorotation to 107.1% at 2½ -minute 
power. 
 
 Maximum 15-second Varies linearly from 119% at flight autorotation to 109% at 2½-minute  
   power.

Page 2 of 23 H1NE 
 
 Engine torque 100% = 564 foot-pounds 
 
   See Flight Manual for T5 (power turbine inlet temperature) limits and power 
turbine (N2) speed limits. 
ROTOR LIMITS                              
POWER OFF    
Maximum 115% Nr (336 r.p.m.)                                          
Minimum  87% Nr (255 r.p.m.)  
POWER ON                                                              
Maximum 107% Nr (313 r.p.m.)                                         
Minimum 100% Nr (dual engine operation)                                
Minimum  96% Nr (one engine inoperative) (OEI)  
   
AIRSPEED LIMITS 
 
  VNE (never exceed) Power On: 155 knots (CAS), 155 knots (IAS). See Flight Manual for variations of V NE 
with gross weight and density altitude. 
 
 VLE/VLO (gear extended, gear operating):  130 knots (CAS), 130 knots (IAS). 
 
 VNE Power Off: 135 knots (CAS), 141 knots (IAS).  
Below 80 lbs. fuel remaining per tank, reduce airspeed to 120 knots (CAS), 
126 knots (IAS) or less. 
                                           
CENTER OF GRAVITY (C.G.) RANGE            
193 198
198.3
197.8
204.3
205.0
SEE NOTE 10
202 205 210
6,100
6,500
6,900
8,500
8,750 8,750
10,300
10,500
 Minimum allowable weight (6,100 lbs.)
Gross
  Weight (lbs.)
Station - Inches
6,900
 
  For effect of landing gear position, refer to loading section of flight manual.

Page 3 of 23 H1NE 
 
LATERAL C.G. LIMITS + 3.5 inches maximum 
 
EMPTY WEIGHT C.G. RANGE    None 
 
DATUM  200 inches forward of main rotor centroid 
 
LEVELING MEANS Leveling plate at STA 176, BL 35, L.H. and plumb line from upper frame of 
the aft doorway 
 
MAXIMUM WEIGHT 10,500 lbs 
 
MINIMUM CREW 2 (IFR) 
  1 (IFR) when appropriately equipped and operating to approved flight manual 
or flight manual supplement. (See Note 15.) 
  1 (VFR) 
 
NUMBER OF SEATS  2 cockpit 
  13 cabin maximum 
 
MAXIMUM BAGGAGE  600 lbs. 
 
FUEL CAPACITY 286.4 gals. (281.2 usable) at (216.7) (See Note 1.) 
 
OIL CAPACITY   1.27 gals. per engine at (231.0) 
 
MAXIMUM OPERATING (DENSITY) ALTITUDE 
 
  Enroute  15,000 feet 
  Takeoff and landing  6,900 feet 
  or 11,000 feet (for helicopters incorporating Sikorsky Kit P/N 76070-30005) 
 
AMBIENT TEMPERATURE LIMITS: -34.4oC (-30oF) to ISA +36.7oC; not to exceed 48.9oC (120oF) 
 
ROTOR BLADE CONTROL MOVEMENTS For rigging information refer to Maintenance Manual. 
 
MANUFACTURER'S SERIAL NUMBERS  76006, 76007, 760001 thru 760122, 760130 thru 760261, 760263 thru 760268, 
760270 thru 760298, 7 60300 thru 760302, 760304, 760364, 760366, 760369 
thru 760371, 760373, 760374 are eligible. 
 
II. MODEL NUMBER  S-76B (Transport Helicopter, Category B), Approved October 31, 1985 
  (Transport Helicopter, Category A), Approved February 3, 1987 
 
ENGINES   2 Pratt & Whitney Canada (PWC) Model PT6B-36 (Category B only, reference 
S-76B Flight Manual, Supplement No. 2) or 2 PWC Model PT6B-36A or 2 
PWC Model PT6B-36B (reference S-76B Flight Manual, Supplement No. 11)    
 
FUEL  JP-4***/ JP-5**/JP-8/Jet A*/Jet A1*/GB6537-94(RP-3)* 
  Fuels with anti-ice additive can be used without temperature limitation. 
*Fuels without anti-ice additive shall be mixed with appropriate additive below 
+4
oC (40
oF ).  (See Note 6.) 
   ** Not to be used below -26oC (-15oF). 
  *** JP4 not to be used above 10,000 feet pressure altitude. 
 
OIL  PWA 521, Type I or II 
  Low temperature limits for starting: 
   Type I  oil usable to -54oC (-65oF) 
   Type II oil usable to -40oC (-40oF) 
  For approved oil brands, see PWC Service Bulletin No. 11001

Page 4 of 23 H1NE 
 
ENGINE AND TRANSMISSION LIMITS 
 
SEA LEVEL STATIC / STANDARD DAY 
ENGINE 
TORQUE 
LIMITS 
TRANSMISSION 
TORQUE 
LIMITS 
 
GAS GENERATOR 
SPEED LIMITS(N1) 
 
POWER TURBINE 
INLET (T5) 
                                                FOR MODEL PWC PT6B-36 
Takeoff (5 minutes) 
Maximum Continuous 
OEI (2-1/2 minutes) 
OEI (30 minutes) 
15 second Transient  
10 second Transient 
5 second Transient (OEI)  
5 second Transient (Starting) 
2 second Transient(Starting) 
133.0 % 
120.0 % 
141.0 % * 
133.0 % 
- - -  
152.0 % * 
- - - 
- - -  
- - -   
100.0 % 
100.0 % 
136.0 % 
128.0 % 
- - -  
105.0 % 
150.0 % * 
- - - 
- - -  
100.0 % 
100.0 % 
101.6 % 
100.0 % 
- - -  
101.8 %  
- - -  
- - - 
- - -  
816 deg C 
776 deg C 
850 deg C 
816 deg C 
870 deg C 
- - - 
- - -  
940 deg C 
1090 deg C 
* EEC will limit available single-engine torque to 136 % 
 
                                                 FOR MODEL PWC PT6B-36A 
Takeoff (5 minutes) 
Maximum Continuous 
OEI (2-1/2 minutes) 
OEI (30 minutes) 
10 second Transient  
5 second Transient (OEI) 
5 second Transient (Starting) 
2 second Transient (Starting) 
133.0 % 
120.0 % 
- - -  
141.0 % * 
152.0 % * 
- - - 
- - -  
- - -   
100.0 % ** 
100.0 % ** 
136.0 % * 
128.0 %  
115.0 % ** 
150.0 % *  
- - - 
- - -  
100.0 % 
100.0 % 
- - -  
101.6 %  
101.8 % 
- - -  
- - - 
- - -  
816 deg C 
776 deg C 
- - -  
844 deg C 
870 deg C 
- - -   
940 deg C 
1090 deg C 
* EEC will limit available single-engine torque to 136 % 
** EEC will limit available dual-engine torque to total of 202 % 
 
                                                 FOR MODEL PWC PT6B-36B 
Takeoff (5 minutes) 
Maximum Continuous 
OEI (2-1/2 minutes) 
OEI (30 minutes) 
10 second Transient 
10 second Transient  
5 second Transient (OEI) 
5 second Transient (Starting) 
2 second Transient(Starting) 
133.0 % 
120.0 % 
- - -  
141.0 %* 
152.0 %* 
- - -  
- - - 
- - -  
- - -  
100.0 %** 
100.0 %** 
136.0 %* 
128.0 % 
115.0 %** 
- - -  
150.0 %*  
- - - 
- - -  
102.6 % 
102.6 % 
- - -  
104.2 % 
104.7 % 
- - -  
- - -  
- - - 
- - -  
816 deg C 
776 deg C 
- - -  
844 deg C 
- - - 
870 deg C 
- - -  
940 deg C 
1090 deg C  
* EEC will limit available single-engine torque to 136 % 
** EEC will limit available dual-engine torque to total of 202 % 
ROTOR LIMITS 
POWER OFF    
Maximum 115% Nr (336 r.p.m.)                                          
Minimum  91% Nr (266 r.p.m.)  
POWER ON                                                              
Maximum 108% Nr (316 r.p.m.)  except with torque below 26%, then 110% Nr  
Minimum 106% Nr (dual engine operation)                                
Minimum  100% Nr (one engine inoperative) (OEI)

Page 5 of 23 H1NE 
 
AIRSPEED LIMITS 
 VNE (never exceed) Power On: 155 knots (IAS).  See Flight Manual for variations of V NE with 
temperature and pressure altitude. 
 
   With PT6B-36A, or PT6B -36B, VNE above 10,000 feet density altitude at 
actual gross wei ghts greater than 11,000 pounds is BROC (best -rate-of-
climb) airspeed. 
 
 VLE/VLO (gear extended/gear operating): 130 knots (IAS) 
 
VNE Power Off: 136 knots (IAS) 
   Below 80 lbs. fuel remaining per tank, avoid sustained pitch down attitudes 
in excess of 5o nose low. 
CENTER OF GRAVITY (C.G.) RANGE            
11,700
11,400
11,000
9,500
9,250
8,500
7,500
7,350
GROSS
WEIGHT (lbs)
194 197 198.4
199.2
204.3 205 208.2 210
11,400
205
204.3199.2
11,700
197
11,000 198.4
210
9,250
7,500
199
7,350
(minimum allowable weight)
STATION - INCHES
PWC Model PT6B-36A and PT6B-36B Engines
PWC Model PT6B-36 Engines
 
 
  For effect of landing gear position, refer to loading section of flight manual. 
 
LATERAL C.G. LIMITS Up to 11,400 lbs: +3.5 inches maximum 
  Above 11,400 lbs: +2.5 inches maximum 
 
EMPTY WEIGHT C.G. RANGE    None 
 
DATUM   200 inches forward of main rotor centroid 
 
LEVELING MEANS  Leveling plate at STA 176, BL 35, L.H. and plumb line from upper frame of 
the aft doorway

Page 6 of 23 H1NE 
 
MAXIMUM WEIGHT  With PWC PT6B-36 engines:  11,400 pounds 
  With PWC PT6B-36A engines: 11,700 pounds 
  With PWC PT6B-36B engines: 11,700 pounds 
 
MINIMUM CREW  2 (IFR) 
  1 (IFR) when appropriately equipped and operating to approved flight manual 
or flight manual supplement (See Note 15.) 
  1 (VFR) 
 
NUMBER OF SEATS  2 cockpit 
13 cabin maximum 
 
MAXIMUM BAGGAGE  600 lbs. 
 
FUEL CAPACITY  286.4 gals. (281.2 usable) at (216.7) (See Note 1.) 
 
OIL CAPACITY   2.0 gals. per engine 
 
MAXIMUM OPERATING (DENSITY) ALTITUDE 
 
PT6B-36 PT6B-36A PT6B-36B 
Enroute 
Takeoff and Landing                Cat. B: 
                                                 Cat. A: 
10,000 feet 
10,000 feet 
- - -  
15,000 feet 
15,000 feet 
5,000 feet 
15,000 feet 
15,000 feet 
5,000 feet 
 
AMBIENT TEMPERATURE LIMITS -34.4oC (-30oF) to ISA +38oC not to exceed 49oC (120oF) 
   with bleed air Environmental Control Unit (ECU) off or not installed. 
 
   -34.4oC (-30oF) to ISA +35oC not to exceed 43oC (109oF) 
   with bleed air ECU on. 
 
ROTOR BLADE CONTROL MOVEMENTS For rigging information, refer to Maintenance Manual. 
 
MANUFACTURER'S SERIAL NUMBERS  76005, 760262, 760299, 760303, 760310 thru 760363, 760365, 760367, 760368, 
760372, 760379 thru 760382, 760387, 760391, 760393, 760395, 760399, 
760403, 760404, 760409, 760410, 760413, 760414, 760416, 760425, 760427 
through 760430, 760433, 760437, 760439, 760441 through 760445, 760447 
through 760452, 760454, 760455, 760458, 760462, 760465, 760507, 762976 are 
eligible. 
 
 
III. MODEL NUMBER S-76C (Transport Helicopter, Category B), Approved March 15, 1991 
              (Transport Helicopter, Category A), Approved April 12, 1991 
 
ENGINES   2 Turbomeca Arriel 1S1 
    or  
   2 Turbomeca Arriel 2S1 
 or 
2 Turbomeca Arriel 2S2 (See Note 16.) 
 
FUEL   JP-4***/JP-5**/JP-8/Jet A*/Jet A1*/Jet B*/GB6537-94(RP-3)* 
 
   Fuels with anti-ice additive can be used without temperature limitation. 
   *  Fuels without anti -ice additive shall be mixed with appropriate additive 
below +4oC (40oF). (See Note 6.) 
   ** Not to be used below -26oC (-15oF). 
   *** Applicable to Arriel 1S1 only

Page 7 of 23 H1NE 
 
OIL  5 cst synthetic oil for normal use 
   For approved types and brands, refer to S-76C Flight Manual, 
   Sikorsky P/N SA 4047 -76C-1 (W/Arriel 1S1 engine configuration) or S -76C 
Flight Manual, Sikorsky P/N SA 4047 -76C-10 and SA 4047-76C-14 (W/Arriel 
2S1 engine configura tion), or SA 4047 -76C-15 (W/Arriel 2S2 engine 
configuration).  
 
 
ENGINE AND TRANSMISSION LIMITS 
 
Arriel 1S1 Configuration  
SEA LEVEL STATIC / STANDARD DAY 
ENGINE 
TORQUE 
LIMITS 
TRANSMISSION 
TORQUE 
LIMITS 
 
GAS GENERATOR 
SPEED LIMITS(N1) 
 
POWER TURBINE 
INLET (T5) 
Takeoff  
Maximum Continuous 
OEI(2-1/2 minutes) 
OEI (Maximum Continuous)) 
20 second Transient (OEI) 
20 second Transient  
10 second Transient  
5 second Transient (OEI) 
5 second Transient(Starting)  
104.0 % 
104.0 % 
127.0 % 
110.0 % 
148.0 % 
- - -  
- - -  
- - -  
- - -  
100.0 % 
100.0 % 
136.0 % 
128.0 % 
- - -  
- - - 
115.0 % 
150.0 % 
- - - 
100.0 % 
100.0 % 
102.7 %** 
102.2 %* 
105.35 %*** 
105.35 %*** 
- - - 
- - -  
- - -  
845 deg C 
845 deg C 
885 deg C 
868 deg C 
920 deg C 
- - - 
- - - 
- - -  
865 deg C 
    * Cockpit gauge biased to read 101.2 % 
  **  Cockpit gauge biased to read 101.7 % 
***  Cockpit gauge biased to read 104.35 % 
 
Arriel 2S1 Configuration  
SEA LEVEL STATIC / STANDARD DAY  
ENGINE 
TORQUE 
LIMITS 
TRANSMISSION 
TORQUE  
LIMITS  
  
GAS GENERATOR 
SPEED LIMITS(N1) 
 
POWER TURBINE 
INLET (T5) 
Takeoff  (5 minutes) 
30 minute (see Note 13) 
Maximum Continuous 
OEI (30 second)  
OEI (2 minutes) 
OEI (Maximum Continuous) 
20 second Transient  
10 second Transient 
10 second Transient (starting) 
5 second Transient(OEI) 
103.7 % 
103.7 % 
103.7 % 
134.6 % 
126.7 % 
116.7 % 
160.4 % 
- - -  
- - -  
- - -  
100.0 % 
100.0 % 
100.0 %  
136.0 % 
136.0 %  
128.0 %  
- - - 
115.0 %  
- - -  
150.0 % 
101.2 %* 
101.2 %* 
  99.0 %** 
105.8 %**** 
102.4 %*** 
101.2 %* 
102.3 %*** 
- - - 
- - -   
- - -  
 912 deg C 
 912 degC 
 877 deg C 
1000 deg C 
 941 deg C 
 912 deg C 
 - - -  
 - - -  
 865 deg C 
 - - -   
     *  Cockpit gauge biased to read 100.0 %  
    ** Cockpit gauge biased to read  97.8 %  
  *** Cockpit gauge biased to read 101.2 %  
**** Cockpit gauge biased to read 104.6 %

Page 8 of 23 H1NE 
 
 
Arriel 2S2 Configuration  
SEA LEVEL STATIC / STANDARD DAY  
ENGINE 
TORQUE 
LIMITS 
TRANSMISSION 
TORQUE  
LIMITS  
  
GAS GENERATOR 
SPEED LIMITS(N1) 
 
POWER TURBINE 
INLET (T5) 
Takeoff  (5 minutes) 
30 minute (see Note 13) 
Maximum Continuous 
OEI (30 second)  
OEI (2 minutes) 
OEI (Maximum Continuous) 
20 second Transient  
10 second Transient 
10 second Transient (starting) 
5 second Transient(OEI) 
103.7 % 
103.7 % 
103.7 % 
134.9 % 
127.0 % 
115.0 % 
160.4 % 
- - -  
- - -  
- - -  
100 % 
100 % 
100 %  
136 % 
136 %  
128 %  
- - - 
115.0 %  
- - -  
150.0 % 
101.88 %* 
101.88 %* 
99. 71 %** 
105.89 %*** 
102.38 %**** 
101.28 %***** 
102.98 %****** 
- - - 
- - -   
- - -  
930 deg C 
930 deg C 
893 deg C 
996 deg C 
944 deg C 
926 deg C 
 - - -  
 - - -  
 840 deg C 
 - - -   
          *     Cockpit gauge biased to read  100.0 %  
        **     Cockpit gauge biased to read  97.8 %  
      ***     Cockpit gauge biased to read  103.9 %  
    ****     Cockpit gauge biased to read  100.5 % 
  *****     Cockpit gauge biased to read  99.4 % 
******     Cockpit gauage biased to read  101.1% 
 
 Engine Torque  100% = 657.6 foot-pounds 
 
 
ROTOR LIMITS 
 
POWER OFF 
Maximum 115% Nr (336 r.p.m.)  
Minimum  91% Nr (266 r.p.m.)  
POWER ON 
Maximum 108% Nr (316 r.p.m.) except 109% for less than 20 seconds (w/2S1 engine only)  
Maximum 108% Nr (316 r.p.m.)  except with torque below 26%, then 110% Nr (w/1S1 engine only)  
Minimum 106% Nr (dual engine operation) 
Minimum  100% Nr (one engine inoperative) (OEI)  
 
AIRSPEED LIMITS 
 VNE (never exceed) Power On: 155 knots (IAS). See Flight Manual for variations of VNE with  
   temperature and pressure altitude. 
  VLE/VLO(gear extended/gear operating): 130 knots (IAS) 
VNE Power Off: 136 knots (IAS) 
  Below 80 lbs. fuel remaining per tank, avoid sustained pitch down attitude s in 
excess of 5o nose low.

Page 9 of 23 H1NE 
 
CENTER OF GRAVITY (C.G.) RANGE 
11,700
11,000
9,500
9,250
8,500
7,500
7,350
Gross
Weight (lbs)
194 197
199.2
204.3 208.2 210
204.3199.2
11,700
197
11,000
210
9,250
7,500
199
7,350
(minimum allowable weight)
STATION - INCHES
 
 
   For effect of landing gear position, refer to loading section of flight manual. 
 
LATERAL C.G. LIMITS Up to 11,400 lbs:  +3.5 inches maximum  
   Above 11,400 lbs:  +2.5 inches maximum  
   Below 10,800 lbs (w/hoist load,  
   hover only):  +4.5 inches maximum  
 
EMPTY WEIGHT C.G. RANGE    None 
 
DATUM   200 inches forward of main rotor centroid 
 
LEVELING MEANS  Leveling plate at STA 176, BL 35, L.H. and plumbline from upper frame of the 
aft doorway 
 
MAXIMUM WEIGHT  11,700 lbs. 
 
MINIMUM CREW  2 (IFR) 
  1 (IFR) when appropriately equipped and operating to approved flight manual 
or flight manual supplement (See Note 15.) 
   1 (VFR) 
 
NUMBER OF SEATS  2 cockpit 
  13 cabin maximum 
 
  MAXIMUM BAGGAGE  600 lbs. 
 
FUEL CAPACITY  286.4 gals. (281.2 usable) at (216.7) (see Note 1) 
 
OIL CAPACITY   1.27 gals. per engine

Page 10 of 23 H1NE 
 
MAXIMUM OPERATING (DENSITY) ALTITUDE 
  With 1S1 Engine Configuration  
 
 Enroute  15,000 feet 
 Takeoff and landing  Cat. B: 11,000 feet 
   Cat. A:   5,000 feet          
 
  With 2S1 or 2S2 Engine Configuration 
  
 Enroute  15,000 feet  
 Takeoff and landing  Cat. B: 15,000 feet 
    Cat. A: 5,000 feet   
 
AMBIENT TEMPERATURE LIMITS: -34.4oC (-30oF) to ISA +37oC; not to exceed 49oC (120oF) 
 
ROTOR BLADE CONTROL MOVEMENTS For rigging information refer to Maintenance Manual. 
 
MANUFACTURER'S SERIAL NUMBERS  Sikorsky Aircraft Corporation under Production Certificate Number 105:  
760269, 760375 through 760378, 760383 through 760386, 760388 through 
760390, 760392, 760394, 760396 through 760398, 760400 through 760402, 
760405 through 760408, 760411, 760412, 760415, 760417 through 760424, 
760426, 760431, 760432, 760434 through 760436, 760438, 760440, 760446, 
760453, 760456, 760457, 760459 through 760461, 760463, 760464, 760466 
through 760506, 760508 through 760634, 760636, 760637, 760639, 760641, 
760643, 760645, 760647 through 760652, 760654 through 760657, 760659 
through 760685, 760687 through 760689, 760691 through 760693, 760695 
through 760700, 760702, 760703, 760705 through 760707, 760709, 760710, 
760712, 760713, 760715, 760716, 760718, 760719, 760721, 760722, 760724, 
760725, 760727, 760728, 760730, 760732, 760733, 760735, 760736, 760738, 
760742, 760744, 760749, 760752, 760761, 760769, 760794, 760797, 760805 
through 760822 are eligible. 
 
   Keystone Helicopter Corporation for Production under Type Certificate Only:   
   760635, 760638, 760640, 760642, 760644, 760646, 760653 and 760658 are 
eligible. 
 
     Keystone Helicopter Corporation under Production Certificate Number 121NE: 
760686*, 760690, 760694, 760701, 760704, 760708, 760711, 760714, 760717, 
760720, 760723, 760726, 760729, 760731, 760734, 760737, 760739 through 
760741, 760743, 760745 through 760748, 760750, 760751, 760753 through 
760760, 760762 through 760768, 760770 through 760793, 760795, 760796, 
760798 through 760804 are eligible. 
 
* 760686 originally designated as eligible for production by Keystone 
Helicopter Corporation under Type Certificate Only and redesignated upon 
issuance of Production Certificate Number 121NE. 
 
IV. MODEL NUMBER S-76D (Transport Helicopter, Category B), Approved October 12, 2012 
              (Transport Helicopter, Category A), Approved December 19, 2013 
 
ENGINES   2 Pratt and Whitney Canada PW210S 
 
FUEL  
   
ISSUING 
AUTHORITY TYPE (1) SPECIFICATION 
FUEL 
TEMPERATURE 
RANGE (2) 
Commercial 
Jet A ASTM D1655 –40°C (–40°F) to 52°C (126°F) 
Jet A-1 ASTM D1655 –40°C (–40°F) to 52°C

Page 11 of 23 H1NE 
 
(126°F) 
No. 3 Jet Fuel PRC GB6537 –40°C (–40°F) to 52°C (126°F) 
Military 
JP-5 MIL-DTL-5624 –40°C (–40°F) to 52°C (126°F) 
JP-8 MIL-DTL-83133 –40°C (–40°F) to 52°C (126°F) 
NOTES: 
1.  Any approved fuel or mixture of approved fuels may be used. Refer to the Pratt & Whitney 
Canada PW210S Maintenance Manual for a complete li st of acceptable and 
alternate/emergency fuels.  
2.  Fuel anti-icing additive must be used below 4°C (40°F) for fuels supplied without anti -icing 
additive. See Note 6.  
 
 
OIL 
   
Brand Supplier 
AeroShell Turbine Oil 500 
AeroShell Turbine Oil 560 
Shell Oil Company 
 
BP Turbo Oil 2380 Air BP 
Castrol 5000 Castrol Ltd. 
Mobil Jet Oil II Exxon Mobil Chemical Company 
Turbonycoil 600 II Nyco S.A. 
    
 
POWERPLANT LIMITS 
 
OPERATING 
CONDITION 
TIME ENGINE 
TORQUE LIMIT 
(%) 
ITT (C) NG (%) NP 
(%) 
TAKEOFF AEO 5 MIN 100 (1) 932-924 (1)(2) 100.0 (1) 108 
HIP AEO (3) 30 MIN 100 (1) 924 (1) 100.0 (1) 108 
MAXIMUM 
CONTINUOUS 
AEO 
-- 100 (1) 886 98.8 108 
TRANSIENT 
AEO 
20 SEC 136 980 101.8 118 
30 SEC OEI 30 SEC 140 (1) 1006 (1) 102.7 (1) 108 
2 MIN OEI 2 MIN 136 (1) 980 (1) 101.8 (1) 108 
MAXIMUM 
CONTINUOUS 
OEI 
-- 128 (1) 924 (1) 100.0 (1) 108 
TRANSIENT OEI 
 
 
5 SEC 145 
(30 SEC OEI) 
1015 
(30 SEC OEI) 
103.3 
(30 SEC 
OEI) 
115 
141 
(2 MIN OEI) 
989 
(2 MIN OEI) 
102.3 
(2 MIN 
OEI) 
20 SEC 136 
(Max Cont OEI) 
980 
(Max Cont 
OEI) 
101.8 
(Max Cont 
OEI) 
118 
GROUND IDLE 20 SEC -- 790 -- -- 
-- -- 760 -- --

Page 12 of 23 H1NE 
 
OPERATING 
CONDITION 
TIME ENGINE 
TORQUE LIMIT 
(%) 
ITT (C) NG (%) NP 
(%) 
STARTING 2 SEC -- 825 -- -- 
60 SEC -- 750 (4) -- -- 
NOTES: 
1.  Shaded boxes with bold numbers denote EEC controlled limiter values.  
2.  When the ITT increases above 886 C, the Takeoff and Maximum Continuous OEI ITT limits 
will decrease from 932 C to 924 C over a 3 minute period. The limits increase back to 932 C 
when the ITT decreases below 886C.  
3.  Hovering at Increased Power (HIP): Use of Takeoff limits during hover oper ations in excess 
of 5 minutes.  
4.  ITT limiting occurs at 740C.  An automatic abort will be commanded (on ground only) if the 
ITT reaches 765C. 
5.  Limit in parentheses refers to currently selected OEI limit. 
 
Engine Torque  100% = 657.6 foot-pounds 
 
DRIVE SYSTEM LIMITS 
 
 APPROVED GEARBOX OILS 
 
  
TYPE LOW TEMPERATURE LIMIT 
BP Turbo Oil 25 (Preferred) –40°C / –40°F 
Other Approved DOD-PRF-85734 Oils –40°C / –40°F 
 
  
 
 MAIN GEARBOX TORQUE 
 
ALL ENGINES OPERATING (AEO) 
MGB TORQUE (%) NO INSPECTION REQUIRED INSPECTION 
REQUIRED 
0% to 100% Continuous  
100% to 115% 10 SEC >10 SEC 
>115%  Any Occurrence 
 
 
ONE ENGINE INOPERATIVE (OEI) 
MGB TORQUE (%) NO INSPECTION REQUIRED INSPECTION 
REQUIRED 
0% to 128% Continuous  
128% to 136% 2 MIN >2 MIN 
136% to 140% 30 SEC >30 SEC 
140% to 150% 5 SEC >5 SEC 
>150%  Any Occurrence

Page 13 of 23 H1NE 
 
MGB OIL PRESSURE 
 
Maximum: 120 PSI 
Cautionary: 90 PSI to 120 PSI 
Normal: 50 PSI to 90 PSI 
Cautionary: 20 PSI to 50 PSI 
Minimum: 20 PSI 
 MGB OIL TEMPERATURE (see Note 22) 
With v303 Software With v400 Software 
Maximum: 135°C Maximum: 135°C 
Cautionary: 120°C to 135°C Cautionary: 115°C to 135°C 
Normal: 15°C to 120°C Normal: 15°C to 115°C 
Cautionary: –20°C to 15°C Cautionary: –20°C to 15°C 
Minimum: –20°C Minimum: –20°C 
 
ROTOR LIMITS 
 
POWER OFF 
Maximum: 115% 
Normal: 91% to 115% 
Minimum  91% 
Transient Minimum: 74% 
Transient Minimum at touchdown while executing an autorotative landing: 68% 
POWER ON 
Maximum: 115%  
Cautionary: 108% to 115%  
Normal Operating Rotor Speed (AEO): 106% to 108% 
Cautionary (AEO): 91% to 106% 
Normal Operating Rotor Speed (OEI above best rate of climb airspeed): 106% to 108% 
Normal Operating Rotor Speed (OEI up to best rate of climb airspeed): 100% to 108% 
Cautionary (OEI): 91% to 100% 
Transient Minimum: 91% 
Transient Minimum at touchdown during an OEI landing: 68% 
 
 
AIRSPEED LIMITS 
 VNE (never exceed) Power On: 155 knots (IAS). See Flight Manual for variations of VNE PWR ON with  
   density altitude. 
 
  VNE(gear extended/gear operating): 130 knots (IAS) 
 
VNE Power Off: 136 knots (IAS). See Flight Manual for variation of V NE PWR OFF  with density 
altitude.

Page 14 of 23 H1NE 
 
CENTER OF GRAVITY (C.G.) RANGE

Page 15 of 23  HINE
CENTER OF GRAVITY LIMITS AT VARIOUS GROSS WEIGHTS
FOR LATERAL CG GREATER THAN ‡ 2.5 INCHES UP TO AND INCLUDING ‡ 3.5 INCHES
NOTE: DATUM IS 200 INCHES FORWARD OF ROTOR CENTROID
11,400 ￾
11  11.0001  203.3  205.6
202.0
GROSS WEIGHT - 1,000 LB  199.0  210.0
9,500  - 9,500
- 9,250
8,586
7,350
208.3
193  194  195  196 197  198  199  200  201  202  203  204  205  206  207  208  209  210 211
CENTER OF GRAVITY - INCHES AFT OF DATUM
CENTER OF GRAVITY LIMITS AT VARIOUS GROSS WEIGHTS
FOR LATERAL CG GREATER THAN ‡ 3.5 INCHES UP TO AND INCLUDING + 4.5 INCHES
NOTE: DATUM IS 200 INCHES FORWARD OF ROTOR CENTROID
10,800 -
196.6  207.0
GROSS WEIGHT - 1,000 LB  194.0  210.0
- 9,500
- 9,250
- 7,350
_208.3_
193  194  199  200  201  0202%  203 204 205 206 207 208  209 210 211
CENTER OF GRAVITY - INCHES AFT OF DATUM

Page 16 of 23  HINE
Note: For the above charts, the effect of landing gear retraction on center of gravity need not be considered. The
limits depicted in the diagrams are appropriate for flight with main landing gear extended or retracted.
CENTER OF GRAVITY LIMITS AT VARIOUS GROSS WEIGHTS
FOR GROUND OPERATIONS ONLY
NOTE: DATUM IS 200 INCHES FORWARD OF ROTOR CENTROID
12  11,875  -12,000-1  200.3  203.0  I= 11,875  111,784
199.6  204.5205.0.
GROSS WEIGHT ~ 1000 LB  11.000T.  197.0
10
194.0  210.0
- 9,625
9,500
9,250  9,250
- 7,350
208.3
193  194  195  196  197  198  199  200  201  202  203  204  205  206  207  208  209  210  211
CENTER OF GRAVITY ~ INCHES AFT OF DATUM
LATERAL C.G. LIMITS  Up to 11,400 lbs:  +3.5 inches maximum
11,400 Ibs - 11,875 lbs  +2.5 inches maximum
11,875 Ibs - 12,000 1bs (Ground Only) +1.9 inches maximum
SAR (Below 10,800 Ibs, hover)  +4.5 inches maximum
EMPTY WEIGHT C.G. RANGE  None
DATUM  200 inches forward of main rotor centroid
LEVELING MEANS  Leveling plate at STA 176, BL 35, L.H. and plumbline from upper frame of the
aft doorway
MAXIMUM WEIGHT  11,875 Ibs. (takeoff)
12,000 Ibs. (ground operations)
MINIMUM CREW  1 (IFR)
1 (VER)
3 (SAR; 2 Pilots, 1 Hoist Operator)
NUMBER OF SEATS  2 cockpit
12 cabin maximum
MAXIMUM BAGGAGE  600 1bs.
FUEL CAPACITY  Aircraft 761004 through 761036: 298 gals. (290 gals. usable) at (216.8)
(See Note 1.)
Aircraft 761037 and subsequent: 292 gals. (284 gals. usable) at (219.5)
(See Note 1.)

Page 17 of 23 H1NE 
 
OIL CAPACITY   1.281 gal/engine 
 
MAXIMUM OPERATING (DENSITY) ALTITUDE  
   Enroute: 15,000 feet 
    Takeoff and landing: Cat. B: 12,700 feet 
     Cat. A: 3,000 feet Horizontal, 5,000 feet Vertical 
 
AMBIENT TEMPERATURE LIMITS:  -35°C (-31°F) to ISA + 34°C (not to exceed 45°C / 113°F), see Note 22. 
     -35°C (-31°F) to ISA + 37°C (not to exceed 52°C / 126°F), see Notes 22, 23 
 
ROTOR BLADE CONTROL MOVEMENTS For rigging information refer to Maintenance Manual. 
 
MANUFACTURER'S SERIAL NUMBERS Sikorsky Aircraft Corporation under Production Certificate Number 105: 
     761004 and up are eligible. 
 
 
 
THE FOLLOWING DATA IS PERTINENT TO THE S-76A, B & C  MODELS OF THIS 
SERIES 
 
CERTIFICATION BASIS Type Certificate No. H1NE 
   
  Model S-76A (Basic Certification Basis): 
 
  FAR Part 29, February 1, 1965, and amendments 29 -1 through 29 -11; in addition, portions of 
amendments 29 -12, specifically, 29.67, 29.71, 29.75, 29 .141, 29.173, 29.175, 29.931, 
29.1189(a)(2), 29.1555(c)(2), 29.1557(c), portions of amendment 29-13, specifically 29.965, and 
portions of amendment 29-21, specifically 29.1, 29.79, 29.1517, and 29.1587. 
 
  Instrument flight criteria (interim) for S-76 dated February 10, 1977. 
 
  Special Conditions 29-82-NE-3 (Docket No. 17721), dated March 27, 1978. 
 
  Partial Grant of Exemption from FAR 29.811(h), Exemption No. 2542 (Docket No.  17403), 
dated January 9, 1979, for the Model S-76A;. 
 
  Equivalent safety finding for FAR 29.173(b). 
 
  National Environmental Act of 1969. 
 
  Noise Control Act of 1972. 
 
  Compliance with the following optional requirements has been established:  Ditchin g provisions 
FAR 29.563 including 29.801 and 29.807(d) of amendment 29 -12 and ex cluding 29.1411, 
29.1415, and 29.1561 when emergency flotation gear, P/N 76076 -02002, is installed. For over -
water operations, compliance with the operating rules and FAR 29.14 11, 29.1415, and 29.1561 
must be shown. 
 
  Cargo hook FAR 29.865 including 29.25 of amendment 29-12, when cargo hook system, P/N 
76255-02000, is installed. For external load operations, FAR 133, including Amendments 1-4. 
  ---------------------------------------------------------------------------------------------------------------- 
  In addition to the basic certification basis, for the Model S-76B: Portions of Amendment 29-24, 
specifically 29.1325(f); equivalent safety finding for FARs 29.1013(e), 29.1203(a), 29.1181(a) 
(6), and 29.1189(a). 
 
  Partial Grant of Exemption from FAR 29.811(h), Exemption No. 2542 (Docket No. 17403), 
dated July 3, 1985. 
 
 
  ----------------------------------------------------------------------------------------------------------------

Page 18 of 23 H1NE 
 
In addition to the basic certification basis, for the Model S-76C (with Arriel 1S1 Engine 
Configuration): 29.1325 of amendment 29-24, amendment 29-26, specifically 
29.67(a)(2)&(3)(b), 29.923(k), 29.1045(c), 29.1047(a)(4) and 29.1521(h);  29.811 of amendment 
29-30, and amendment 36-14 of FAR 36, Appendix H. 
 
  Special Condition No. 29-ASW-3 (Docket No. 91-ASW-1), dated January 30, 1992 
 
  ---------------------------------------------------------------------------------------------------------------- 
 
 
  In addition to the basic certification basis, for the Model S-76C (with Arriel 2S1 Engine 
Configuration): 29.1325 of amendment 29-24, amendment 29-26, specifically 
29.67(a)(2)&(3)(b), 29.923(k), 29.1045(c), 29.1047(a)(4) and 29.1521(h);  29.811 of amendment 
29-30, amendment 29-34, specifically 29.67(a)(1)(i), 29.923(a),(b)(1)&(3), 29.1143(f), 
29.1305(a)(24)&(25), 29.1521(i)&(j) and 29.1549(e) and Amendment 36-20 of FAR 36, 
Appendix H.  
 
  Special Conditions No. 29-ASW-16 (Docket No. 96-ASW-2), dated August 26, 1996 and 
No. 29-004-SC (Docket No. SW004) dated June 17, 1998. 
 
  ---------------------------------------------------------------------------------------------------------------- 
In addition to the basic certification basis, for the Model S-76C (with Arriel 2S2 Engine 
Configuration): 29.1325 of amendment 29-24, amendment 29-26, specifically 
29.67(a)(2)&(3)(b), 29.923(k), 29.1045(c), 29.1047(a)(4) and 29.1521(h);  29.811 of amendment 
29-30, amendment 29-34, specifically 29.67(a)(1)(i), 29.923(a),(b)(1)&(3), 29.1143(f), 
29.1305(a)(24)&(25), 29.1521(i)&(j) and 29.1549(e) and Amendment 36-20 of FAR 36, 
Appendix H.  
 
  Special Conditions No. 29-ASW-16 (Docket No. 96-ASW-2), dated August 26, 1996 and 
No. 29-004-SC (Docket No. SW004), dated June 17, 1998. 
 
---------------------------------------------------------------------------------------------------------------- 
 
THE FOLLOWING DATA IS PERTINENT TO THE S-76D MODEL OF THIS SERIES 
 
CERTIFICATION BASIS     Model S-76D Certification Basis 
 
14CFR 29 through Amendment 29-52 as follows: 
29.2, 29.21, 29.25, 29.27, 29.29, 29.31, 29.33, 29.45, 29.49, 29.51, 29.53, 29.55, 29.59, 29.60, 
29.61, 29.62, 29.63, 29.64, 29.65, 29.67, 29.71, 29.73, 29.75, 29.77, 29.79, 29.81, 29.83, 29.85, 
29.87, 29.141, 29.143, 29.151, 29.161, 29.171, 29.173, 29.175, 29.177, 29.181, 29.231, 29.235, 
29.239, 29.241, 29.251, 29.301, 29.303, 29.305, 29.307 (main and tail rotor blades only), 29.309, 
29.321, 29.337, 29.339, 29.341, 29.351, 29.361, 29.395, 29.397, 29.399, 29.401, 29.403, 29.411, 
29.413, 29.471, 29.473, 29.475, 29.477, 29.479, 29.481, 29.483, 29.485, 29.493, 29.547, 29.549, 
29.551, 29.561(a)(d), 29.563, 29.571 (main and tail rotor blades only), 29.601, 29.602, 29.603, 
29.605, 29.607, 29.609, 29.610, 29.611, 29.613, 29.619, 29.621, 29.623, 29.629, 29.653, 29.659, 
29.661, 29.663, 29.672, 29.673, 29.674, 29.675, 29.681, 29.683, 29.685, 29.687, 29.691, 29.695, 
29.723, 29.725, 29.727, 29.729, 29.731, 29.733, 29.735, 29.771, 29.773, 29.775, 29.777, 29.779, 
29.783, 29.801, 29.803, 29.805, 29.807, 29.809, 29.811, 29.812(a)(c)(d)(e)(f), 29.813(c)(2), 
29.831, 29.851, 29.853, 29.855, 29.861, 29.863, 29.865 (except (c)(6), see Special Condition), 
29.871, 29.873, 29.877, 29.901, 29.903, 29.907, 29.917, 29.921, 29.931, 29.939, 29.951, 29.953, 
29.954, 29.955, 29.959, 29.961, 29.965, 29.969, 29.971, 29.977, 29.993, 29.995, 29.997, 29.999, 
29.1011, 29.1013, 29.1015, 29.1017, 29.1019, 29.1021, 29.1023, 29.1027, 29.1041, 29.1043, 
29.1045, 29.1047, 29.1049, 29.1091, 29.1093, 29.1103, 29.1121, 29.1123, 29.1141, 29.1143, 
29.1145, 29.1151, 29.1163, 29.1165, 29.1181, 29.1183, 29.1185, 29.1187, 29.1189, 29.1191, 
29.1193, 29.1194, 29.1195, 29.1197, 29.1199, 29.1201, 29.1203, 29.1301, 29.1303, 29.1305, 
29.1307, 29.1309 (new avionics, AFCS, and Electrical Power Generation and Distribution 
System only), 29.1317, 29.1321, 29.1322, 29.1323, 29.1325, 29.1327, 29.1329, 29.1331, 
29.1333, 29.1335, 29.1337, 29.1351, 29.1353, 29.1355, 29.1357, 29.1359, 29.1363, 29.1381, 
29.1383, 29.1385, 29.1387, 29.1389, 29.1391, 29.1393, 29.1395, 29.1397, 29.1401, 29.1411, 
29.1413, 29.1415, 29.1431, 29.1435, 29.1457, 29.1459, 29.1461, 29.1501, 29.1503, 29.1505, 
29.1509, 29.1517, 29.1519, 29.1521, 29.1523, 29.1525 ,29.1527, 29.1529, 29.1541, 29.1543, 
29.1545, 29.1547, 29.1549, 29.1551, 29.1553 ,29.1555, 29.1557, 29.1559, 29.1561, 29.1565,

Page 19 of 23 H1NE 
 
29.1581, 29.1583, 29.1585, 29.1587, 29.1589, A29.1, A29.2, A29.3, A29.4, B29.1, B29.2, 
B29.3, B29.4, B29.5, B29.6, B29.7, B29.8, B29.9, C29.1, E29.1 
 
Except: 
29.1 at 29-21, 29.307 at 29-4 (all but main and tail rotor blades), 29.391 at 29-0, 29.561(b)(c) at 
29-0, 29.561(c) at 29-29 (for engine installation only), 29.571 at 29-20 (all but main and tail 
rotor blades only), 29.625 at 29-0, 29.671 at 29-0, 29.785 at 29-0, 29.787 at 29-12, 29.865 at 29-
12 (External Cargo Hook only), 29.908 at 29-13, 29.923(a)(b1)(b3) at 29-34, 29.923(c) - (o) at 
29-26, 29.927 at 29-3, 29.963 at 29-26, 29.967 at 29-0, 29.973 at 29-0, 29.975 at 29-26, 29.1309 
at 29-14 (all but new avionics, AFCS, and Electrical Power Generation and Distribution System)  
Not Adopted: 
29.427, 29.497, 29.501, 29.505, 29.511, 29.519, 29.521, 29.562, 29.631, 29.679, 29.737, 29.751, 
29.753, 29.755, 29.757, 29.812(b), 29.815, 29.833, 29.859, 29.935, 29.952, 29.957, 29.979, 
29.991, 29.1001, 29.1025, 29.1101, 29.1105, 29.1107, 29.1109, 29.1125, 29.1142, 29.1147, 
29.1157, 29.1159, 29.1399, 29.1419, 29.1433, 29.1439, 29.1522, D29.1 
 
Equivalent Safety Findings: 
Number TD1509BO-R-S-1 for 14CFR Part 29.1401(d) at amendment 29-11; Anticollision light 
system installed in accordance with Sikorsky Drawing 33776-92603. 
 
Number AT01847BO-R-P-1 for 14CFR Part 29.1305 at amendment 29-40 and 14CFR Part 
29.1549 at amendment 29-34; Use of a Power Limit Indicator (PLI) as the primary means for 
indicating/setting power. 
 
Special Conditions: 
No. 29-004-SC (Docket No. SW004), dated June 17, 1998. 
No. 29-036-SC (Docket No. FAA-2011-1026), dated December 09, 2014. 
 
14CFR 36 through Amendment 36-30 as follows: 
36.801, 36.803, 36.805, H36.1 - H36.305 
 
Ditching: 
If emergency flotation gear, P/N 33776-92709, is installed, then compliance has also been shown 
to Amendment 29-52 of 29.563, 29.801 (b), (c), (d) and (e) and 29.807 (b) and (d).  For over-
water operations, compliance with the operating rules and 29.1411, 29.1415, and 29.1561 must 
be shown.  
--------------------------------------------------------------------------------------------------------- 
 
THE FOLLOWING DATA IS PERTINENT TO ALL MODELS OF THIS SERIES 
 
PRODUCTION BASIS Sikorsky Aircraft Corporation 
  Production Certificate Number 105 
 
 
 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) Model S-76A: FAA approved Rotorcraft Flight Manual, Model S-76A Helicopter 
(Publication SA 4047-76-1) 
 
Model S-76B: FAA approved Rotorcraft Flight Manual, Model S-76B Helicopter 
(Publication SA 4047-76B-1). 
 
    In addition:  
    For aircraft equipped with PT6B-36 engines, Supplement No. 2 (Publication SA 4047-76B-1)
  
    For aircraft equipped with PT6B-36B engines, Supplement No. 11 (Publication SA  
    4047-76B-1) 
 
   Model S-76C equipped with Arriel 1S1 engines: FAA approved Rotorcraft Flight Manual, 
Model S-76C Helicopter (Publication SA 4047-76C-1).

Page 20 of 23 H1NE 
 
   Model S-76C equipped wit h Arriel 2S1 engines: FAA approved Rotorcraft Flight Manual, 
Model S-76C Helicopter (Publication SA 4047 -76C-10) for aircraft serial numbers prior to 
760511.   For aircraft ser ial numbers 760511 and subsequent FAA Approved Rotorcraft 
Flight Manual (Publication SA 4047-76C-14).  
 
   Model S-76C equipped with Arriel 2S2 engines: FAA approved Rotorcraft Flight Manual, 
Model S-76C Helicopter (Publication SA 4047 -76C-15) for aircraft serial numbers 760607 
and subsequent. 
 
Model S -76D: FAA approved Rotorcraft Fli ght Manual, Model S -76D Helicopter 
(Publication SA S76D-RFM-000). 
 
(b) DELETED 
 
(c) Special airspeed indicator approved: 
    For use on S-76A only: 
   Aero Mechanism Part No. 8 502C-S20LW, or Aerosonic Part No. 20020 -11190, or 
Aerosonic Part No. 20020-11293 airspeed indicator. 
 
    For use on the S-76B and S-76C: 
    Aerosonic Part No. 20020-11293 airspeed indicator. 
--------------------------------------------------------------------------------------------------------- 
 
N O T E S 
 
NOTE 1:  Current weight a nd balance report, including 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. 
 
  See flight manual loading section for variations of fuel weight and moment -arm with variations of fuel and 
fuel quantity. 
 
NOTE 2: All placards required in the approved rotorcraft flight manual must be installed in the approp riate locations. 
The following placard must be displayed in front of and in clear view of the pilot: 
  "THIS HELICOPTER MUST BE OPERATED IN ACCORD ANCE WITH THE OPERATING 
LIMITS SPECIFIED IN THE FAA APPROVED ROTORCRAFT FL IGHT MAN UAL. THE 
AIRWORTHINESS LIMIT ATIONS SECT ION OF THE ROTORCRAFT MAINTENANCE 
MANUAL MUST BE COMPLIED WITH." 
 
NOTE 3: For Model S -76A: Information essential to the proper maintenance of the helicopter is contained in the 
Sikorsky S -76A Maintenance Manual, Publication SA 4047 -76-2, and the  Airworthiness Limitations and 
Inspection Requirements Manual SA 4047 -76-2-1 provided with each helicopter. The values of retirement 
(service) life contained in Chapter 4 of the Airworthiness Limitations and Inspection Requirements Manual 
SA 4047-76-2-1 or inspection intervals cannot be increased without FAA engineering approval. See Note 10. 
   
  For Model S -76A serial numbers 760295, 760296, 760297, 760298, 760300, and 760301:  Information 
essential to proper maintenance of the helicopter is contained in the Sikorsky S-76A Maintenance Manual SA 
4047-76AA-2 and the Airworthiness Limit ations and Inspection Requirements Manual SA 4047 -76-2-1 
provided with each helicopter.  The values of retirement (service) life contained in Chapter 4 of the 
Airworthiness Lim itations and Inspection Requirements Manual SA 4047 -76-2-1 or inspection interva ls 
cannot be increased without FAA engineering approval. (See Note 10.) 
 
  For Model S -76B: Information essential to the proper maintenance of the helicopter is contained in th e 
Sikorsky S -76B Maintenance Manual, Publication SA 4047 -76B-2, and the Airworth iness Limitations and 
Inspection Requirements Manual SA 4047 -76B-2-1 provided with each helicopter. The values of retirement 
(service) life contained in Chapter 4 of the Airwor thiness Limitations and Inspection Requirements Manual 
SA 4047-76B-2-1 or inspection intervals cannot be increased without FAA engineering approval. (See Note 
10.) 
 
  For Model S -76C:  Information essential to the proper maintenance of the helicopter is co ntained in the S -
76C Maintenance Manual, Publication SA 4047 -76C-2, and the Airw orthiness Limitations and Inspection

Page 21 of 23 H1NE 
 
Requirements Sections, Chapters 4 and 5, of SA 4047-76C-2-1, provided with each helicopter.  The values of 
retirement (service) life contai ned in Chapter 4 of the Maintenance Manual or inspection intervals cannot be 
increased without FAA engineering approval. (See Note 10.) 
 
For Model S-76D:  Information essential to the proper maintenance of the helicopter is contained in the S-
76D Maintenance Manual, Publication SA S76D-AMM-000, and the Airworthiness Limitations and 
Inspection Requirements Sections, Chapters 4 and 5, of SA S76D-AWL-000, provided with each helicopter.  
The values of retirement (service) life contained in Chapter 4 of the Maintenance Manual or inspection 
intervals cannot be increased without FAA engineering approval.  (See Note 10.)  
NOTE 4: DELETED 
 
NOTE 5: For Model S-76A only: Mixture ratio: 1 part AVGAS, Grade 80/87, to 2 parts Jet Fuel (Jet A, Jet 1, or JP -5) 
by volume may be used for unrestricted periods of time. AVGAS, Grade 100/130 (100LL) with a m aximum 
of 2.0 ml/gal lead content may be used in place of grade 80/87 in the same proportions with jet fuel for not 
over 300 hours during any overhaul period. Do not use above 4oC (40oF). Do not use AVGAS containing 
Tri-Cresyl-Phosphate (TCP). 
 
NOTE 6: For Model S-76A only: MIL -T-5624 Grade JP -5 with anti -ice additive conforming to MIL -I-27686 (Philips 
Petroleum Company MB-55 or equivalent) in concentration of 0.035% to 0.15% b y volume. ASTM D-1655 
Jet A, A1, or GB6537 -94 (RP3)  with anti -ice additive confor ming to MIL -I-27686 (Philips Petroleum 
Company MB -55 or equivalent) in concentration of 0.035% to 0.15% by volume. If the AVGAS/Jet Fuel 
mixture is added to JP -4 or Jet B, add anti-ice additive in concentration of 0.035% to 0.15% based only on 
the AVGAS/Jet Fuel volume added. If the jet fuel to be mixed with AVGAS is JP -5, Jet A, or Jet A1, to 
which anti-ice additive has not been added, add anti -ice additive in concentration of 0.035% to 0.15% based 
on entire volume. 
 
  For Model S-76B only: Anti-icing protection additives meeting MIL -D-27686 or equivalent must be present 
in concentrations of 0.035% to 0.15% by volume. 
 
  For Model S-76C only: Anti-icing protection additives meet ing MIL-D-27686 or equivalent must be present 
in concentrations of 0.10% to 0.15% by volume. 
 
For Model S-76D only: The following additives and concentrations are applicable: 
Anti-Icing Additives 
Additive (Trade Name) Max. Concentration Allowed (% by Volume) 
Diethylene Glycol Monomethyl Ether as defined in 
MIL-DTL-85470 or ASTM D4171 Type III 
0.15% 
Ethylene Glycol Monoethyl Ether (Fluid I) as 
defined in GOST 8313 
0.15% 
Mixture of 50% Ethylene Glycol Monoethyl Ether 
(Fluid I) and 50% Methyl Alcohol (Fluid I-M) as 
defined in TU 6-10-1458 
0.3% 
 
 
NOTE 7: DELETED 
 
NOTE 8: Initial Type Certification Data Sheet No. H1NE for Model S -76A was not published. No airworthiness 
certificates were issued, based on Data Sheet No. H1NE (No Revision). 
 
NOTE 9: Model S-76A helicopters have been approved for the Luftfahrt -Bundesamt (LBA). This LBA conf iguration 
must include a modification in accordance with Sikorsky Aircraft Drawing No. 76080 -55007, Kit 
Modification, LBA, PL Sheet 1 of 1, Rev ( -), FD Sheet 1 of 1, Rev ( -). This is an LBA special requirement 
and is not approved for FAA airworthiness certification. 
 
NOTE 10: Model S -76A: When operated at gross weights above 10,300 pounds, the helicopter must comply with 
Revision 14 of the Airworthiness Limitations section, date d May 14, 1985, or subsequent FAA -approved 
revisions of the Airworthiness Limitations and Inspection Requirements Manual SA 4047-76-2-1. 
 
  Model S-76B: All helicopters must comply with Airworthiness Limitations section, dated June 7, 1988, or 
subsequent FAA-approved revisions of Airworthiness Limitations and Inspection Requirements M anual SA 
4047-76B-2-1.

Page 22 of 23 H1NE 
 
  Model S -76C: All helicopters must comply with the Airworthiness Limitations Section, Chapter 4, dated 
March 19, 1991, of Maintenance Manual SA 4047-76C-2-1, or subsequent FAA-approved revisions. 
 
  Model S -76D: All helicopters mus t comply with the Airworthiness Limitations Section, Chapter 4, dated 
October 11, 2012, of Manual SA S76D-AWL-000, or subsequent FAA-approved revisions. 
 
NOTE 11:  Model S-76A: Alternate engine installations with Turbomeca Arriel 1S or 1S1 engines are appr oved under 
STC SH568NE (not in mixed engine configurations).  
 
NOTE 12: Emissions control device Kit Part Number 76070 -30603-011, installed in accordance with CSN 76 -192, is 
approved for installation on the Model S -76C helicopter with the Turbomeca Arriel 1S1 engine installation. 
This device prevents the intentional discharge into the atmosphere of  liquid fuel from the fuel nozzle 
manifolds resulting from the process of engine shutdown following normal flight or ground operations. The 
Model S -76B, and Mode l S -76C helicopter with Turbomeca Arriel 2S1 and 2S2 engines  and the Model 
S-76D with Pratt & Whitney Canada PW210S engines , without modification preclude the intentional 
discharge into the atmosphere of liquid fuel from the nozzle manifolds resulting from  the process of engine 
shutdown.  
 
NOTE 13: The use of the 30 minute power rating requires Supplement No. 12 to the Model S76C Rotorcraft Flight 
Manual, document no. SA 4047-76C-10, or document no. SA 4047-76C-14. Approved procedures for the use 
of the 30 minute power rating for the  Arriel 2S2 engine configuration must be published in the Model S76C 
Rotorcraft Flight Manual, document no. SA 4047-76C-15 prior to the use of this rating. Engine Airworthiness 
Limitations requirements are as specified in Type Certificate Data Sheet No. E00054EN.  For the Model S -
76D, use of the 30 minute power rating is addressed in Rotorcraft Flight Manual SA S76D-RFM-000; Engine 
Airworthiness Limitations requirements are as specified in Type Certificate Data Sheet No. E00083EN. 
 
NOTE 14: The Model S -76B (Pratt & Whitney PT6B -36 engine) and Model S-76C (Turbomeca Arriel 2S1 and Arriel 
2S2 engines)  rotorcraft installations employ electronic engine controls commonly named Full -Authority 
Digital Electronic Controls (FADEC), and are recognized to be potentially more susceptible to 
electromagnetic interference (EMI) than rotorcraft containing non-electronic controls.  EMI may be the result 
of radiated or conducted interference.  For this reason, aircraft modifications that add or change systems that 
have the potential for EMI must be ei ther qualified to an FAA accepta ble standard or tested at the time of 
installation for interference to the FADEC.  This type of testing must employ the particular FADEC’s internal 
diagnostic monitoring equipment as well as external diagnostic monitoring eq uipment, and must be FAA 
approved. 
 
The Model S-76D (Pratt & Whitney Canada PW210S engines)  rotorcraft employs electronic engine controls 
that are recognized to be more susceptible to Electromagnetic Interference (EMI) than manual (non-
electronic) controls used on other rotorcraft. EMI may be the result of radiated or conducted interference. For 
this reason, modifications that add or change systems that have the potential for EMI, must either be qualified 
to an FAA acceptable standard or tested at the time of installation for interference to the engine controls. This 
type of testing must employ the particular engine control’s diagnostic techniques and external diagnostic 
techniques. This testing must be accomplished in accordance with an FAA Engineering approved alternate 
test plan. 
 
NOTE 15: 1-pilot IFR is approved for Models S -76A, S -76B, S-76C, and S-76D when appropriately equipped and 
operating in accordance with a flight manual or flight manual supplement that allows such operation.  For 
Models S -76A, S-76B, and S -76C, 1-pilot IFR ope ration requirements include installation of an S PZ-7000 
Digital Automatic Flight Control System by STC or an SPZ -7600 Digital Automatic Flight Control System 
by STC or as optional equipment.  The following Honeywell Flight Manual Supplements relate to 1-pilot IFR 
operations with the SPZ-7000: 
   Model S-76A SA 4047-76-1 Honeywell Supp No. 27-5130-14-03 
   Model S-76A SA 4047-76-1 Honeywell Supp No. 27-5120-19-01 (S-76A Arriel) 
   Model S-76B SA 4047-76B-1 Honeywell Supp No. 27-5120-10-01  
  The following Sikorsky Flight Manuals and Supplements relate to 1-pilot IFR operations with the SPZ-7600: 
   Model S76C Rotorcraft Flight Manual document no. SA 4047-76C-14 
   Model S76C Rotorcraft Flight Manual document no. SA 4047-76C-15 
   Model S-76A SA 4047-76-1 Supp S-38 
   Model S-76C SA 4047-76C-1 Supp S-15 
   Model S-76C+ SA 4047-76C-10 Supp S-15 
   Model S-76C+ SA 4047-76C-10 Supp 88

Page 23 of 23 H1NE 
 
NOTE 16: Installation of Turbomeca Arriel 2S2 engines requires barrier filter P/N 76302 -07800 or F AA-approved 
alternate. 
 
NOTE 17: DELETED 
 
NOTE 18: DELETED 
 
NOTE 19: DELETED 
 
NOTE 20: Model S-76D, Serial Number 761004 through 761050: If an aircraft does not have Sikorsky drawing 76080 -
70002 installed, Rotorcraft Flight Manual Supplement No. D01 is required. 
 
NOTE 21: DELETED 
 
NOTE 22: Model S76D: Refer to Rotorcraft Flight  Manual, SA S76D -RFM-000 Revision 5 or later FAA approved 
revision, Part 1, Section 2 for Cold Weather Procedures. 
 
NOTE 23: Model S-76D: High Temperature Kit Sikorsky drawin g 33776-94664-011 must be installed for o peration at 
ambient temperatures above 45°C (113°F) 
 
.....END.....
```

## ADs (77, first 50, in force first)

- [AD 2024-20-07](https://openairdocs.org/ad/2024-20-07): Emergency Equipment; Emergency Flotation Section · Apical Emergency Float Kit, P/N 20498 (STC SR00780LA or 12 others). Effective Dec 5, 2024
- [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 2022-03-09](https://openairdocs.org/ad/2022-03-09): Global Positioning System · Sikorsky S-76D. Effective Mar 17, 2022
- [AD 2020-15-17](https://openairdocs.org/ad/2020-15-17): Indicating/recording system · Sikorsky S-76C. Effective Sep 9, 2020
- [AD 2019-19-12](https://openairdocs.org/ad/2019-19-12): Engine Fuel and Control · Sikorsky S-76C. Effective Nov 8, 2019
- [AD 2017-19-01](https://openairdocs.org/ad/2017-19-01): Rotorcraft Flight Control · Sikorsky S-76A, S-76B, S-76C and 1 more. Effective Jan 2, 2018
- [AD 2016-23-10](https://openairdocs.org/ad/2016-23-10): Autopilot System · Sikorsky S-76D. Effective Dec 12, 2016
- [AD 2015-26-10](https://openairdocs.org/ad/2015-26-10): Main Rotor Gearbox · Sikorsky S-76A, S-76B and S-76C. Effective Feb 9, 2016
- [AD 2015-19-51](https://openairdocs.org/ad/2015-19-51): Flight Control System · Sikorsky S-76A, S-76B, S-76C and 1 more. Effective Nov 10, 2015
- [AD 2015-04-05](https://openairdocs.org/ad/2015-04-05): Tail Rotor Drive Shaft · Sikorsky S-76A, S-76B, S-76C and 1 more. Effective Mar 12, 2015
- [AD 2014-08-06](https://openairdocs.org/ad/2014-08-06): Main Rotor Head · Sikorsky S-76A, S-76B and S-76C. Effective Jun 2, 2014
- [AD 2013-22-15](https://openairdocs.org/ad/2013-22-15): Main Rotor Head · Sikorsky S-76A, S-76B and S-76C. Effective Dec 13, 2013
- [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 2012-22-13](https://openairdocs.org/ad/2012-22-13): Engine Controls · Sikorsky S-76C. Effective Dec 20, 2012
- [AD 2012-15-08](https://openairdocs.org/ad/2012-15-08): Main Rotor Brake · Sikorsky S-76A. Effective Sep 21, 2012
- [AD 2010-26-09](https://openairdocs.org/ad/2010-26-09): Navigation · Sikorsky S-76A, S-76B and S-76C. Effective Jan 12, 2011
- [AD 2010-17-16](https://openairdocs.org/ad/2010-17-16): Vertical Stabilizer · Sikorsky S-76A, S-76B and S-76C. Effective Oct 18, 2010
- [AD 2010-10-02](https://openairdocs.org/ad/2010-10-02): Servo actuator · Sikorsky S-76A, S-76B and S-76C. Effective Jun 17, 2010
- [AD 2010-07-02](https://openairdocs.org/ad/2010-07-02): Integrated navigation units (INUs) · 328 Support Services 328-100, 328-300, Jetstream Model 4101 and 26 more. Effective May 3, 2010
- [AD 2010-06-08](https://openairdocs.org/ad/2010-06-08): Emergency flotation system squib connector · Sikorsky S-76C. Effective Apr 1, 2010
- [AD 2007-11-05](https://openairdocs.org/ad/2007-11-05): Main rotor shaft assembly (M/R shaft) · Sikorsky S-76A, S-76B and S-76C. Effective Jun 15, 2007
- [AD 2004-06-04](https://openairdocs.org/ad/2004-06-04): Dual channel autopilot and dual inverters · Sikorsky S-76A, S-76B and S-76C. Effective Apr 15, 2004
- [AD 2003-14-18](https://openairdocs.org/ad/2003-14-18): Main landing gear brake discs (discs) · Sikorsky S-76A, S-76B and S-76C. Effective Aug 25, 2003
- [AD 2003-04-15](https://openairdocs.org/ad/2003-04-15): Rotor Brake Disc (RBD) · Sikorsky S-76A, S-76B and S-76C. Effective Feb 27, 2003
- [AD 2002-21-07](https://openairdocs.org/ad/2002-21-07): Main rotor spindle attachment bolt · Sikorsky S-76A, S-76B and S-76C. Effective Nov 25, 2002
- [AD 2002-15-51](https://openairdocs.org/ad/2002-15-51): Main rotor blade · Sikorsky S-76A, S-76B and S-76C. Effective Oct 18, 2002
- [AD 2002-05-06](https://openairdocs.org/ad/2002-05-06): Main and Nose Landing Gear Parts · Sikorsky S-76A. Effective Apr 22, 2002
- [AD 2001-25-06](https://openairdocs.org/ad/2001-25-06): AHRS WARN Circuits · Sikorsky S-76B and S-76C. Effective Jan 4, 2002
- [AD 2001-22-14](https://openairdocs.org/ad/2001-22-14): Fire Extinguishing System Bottle Cartridges · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 105 more. Effective Dec 10, 2001
- [AD 2001-10-06](https://openairdocs.org/ad/2001-10-06): Main Rotor Shaft Assembly · Sikorsky S-76A, S-76B and S-76C. Effective Jun 21, 2001
- [AD 94-14-20 R1](https://openairdocs.org/ad/94-14-20-R1): Tail Rotor Blade Spar Elliptical Centering Plug · Sikorsky S-76A. Effective Jun 8, 2001
- [AD 2001-03-51](https://openairdocs.org/ad/2001-03-51): Main Rotor Shafts · Sikorsky S-76B and S-76C. Effective Mar 21, 2001
- [AD 2001-01-04](https://openairdocs.org/ad/2001-01-04): Rod Assembly · Sikorsky S-76A, S-76B and S-76C. Effective Feb 2, 2001
- [AD 2000-11-52](https://openairdocs.org/ad/2000-11-52): Main Rotor Blade · Sikorsky S-76A, S-76B and S-76C. Effective Aug 31, 2000
- [AD 2000-12-09](https://openairdocs.org/ad/2000-12-09): Air Conditioning System · Sikorsky S-76A. Effective Jul 28, 2000
- [AD 99-19-30](https://openairdocs.org/ad/99-19-30): Tail Gearbox Forward Fairing · Sikorsky S-76A, S-76B and S-76C. Effective Oct 4, 1999
- [AD 99-11-04](https://openairdocs.org/ad/99-11-04): Rotorcraft Flight Manual - Landing Gross Weights and Climb · Sikorsky S-76A with STC SH568NE. Effective Jul 9, 1999
- [AD 99-07-01](https://openairdocs.org/ad/99-07-01): Rotorcraft Flight Manual - Operating Limitations · Sikorsky S-76C. Effective Apr 7, 1999
- [AD 99-01-09](https://openairdocs.org/ad/99-01-09): Fuel Supply Line · Sikorsky S-76C. Effective Mar 3, 1999
- [AD 98-17-15](https://openairdocs.org/ad/98-17-15): Swashplate Assembly Uniball Bearing Retainer Inspection · Sikorsky S-76A, S-76B and S-76C. Effective Feb 1, 1999
- [AD 96-15-03](https://openairdocs.org/ad/96-15-03): Drive Shaft Assemblies · Sikorsky S-76B. Effective Aug 19, 1996
- [AD 95-22-01](https://openairdocs.org/ad/95-22-01): Fluorescent Lighting System · Aerospace Lighting Fluorescent lighting systems, A310-203, A310-204 and 74 more. Effective Dec 4, 1995
- [AD 91-24-13](https://openairdocs.org/ad/91-24-13): Vertical Pylon Forward Spar Cap and Web · Sikorsky S-76A. Effective Dec 20, 1991
- [AD 91-08-03](https://openairdocs.org/ad/91-08-03): Forward Spar Cap · Sikorsky S-76A. Effective May 3, 1991
- [AD 88-05-01 R1](https://openairdocs.org/ad/88-05-01-R1): Engine Support Cross Beam · Sikorsky S-76B. Effective Jul 16, 1990
- [AD 89-07-12](https://openairdocs.org/ad/89-07-12): Tail Rotor Horn · Sikorsky S-76A and S-76B. Effective Apr 27, 1989
- [AD 87-23-07 R1](https://openairdocs.org/ad/87-23-07-R1): Electrical Door Locking Actuators · Sikorsky S-76A and S-76B. Effective Jan 11, 1989
- [AD 87-25-02](https://openairdocs.org/ad/87-25-02): Ground Connections · Sikorsky S-76A and S-76B. Effective Dec 31, 1987
- [AD 87-12-06](https://openairdocs.org/ad/87-12-06): Generator Control Unit · Sikorsky S-76A and S-76B. Effective Jun 10, 1987

All 77: https://openairdocs.org/tcds/H1NE/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Sikorsky S-76C](https://openairdocs.org/model/sikorsky-s-76c): 78 aircraft (registry code 8143008)
- [Sikorsky S-76B](https://openairdocs.org/model/sikorsky-s-76b): 34 aircraft (registry code 8143007)
- [Sikorsky S-76D](https://openairdocs.org/model/sikorsky-s-76d): 34 aircraft (registry code 8143021)
- [Keystone Helicopter S-76C](https://openairdocs.org/model/keystone-helicopter-s-76c): 23 aircraft (registry codes 4900105, 4900103)
- [Sikorsky S-76A](https://openairdocs.org/model/sikorsky-s-76a): 19 aircraft (registry code 8143006)
- [Sikorsky S-76C-2](https://openairdocs.org/model/sikorsky-s-76c-2): 6 aircraft (registry code 8143009)
- [Sikorsky S-76](https://openairdocs.org/model/sikorsky-s-76): 4 aircraft (registry code 8143010)
- [Keystone Helicopter S-76C-2](https://openairdocs.org/model/keystone-helicopter-s-76c-2): 0 aircraft (registry code 4900104)
- [Sikorsky S-76C+](https://openairdocs.org/model/sikorsky-s-76c-plus): 0 aircraft (registry code 8143023)

## STCs approved under this data sheet (470, first 50)

- [STC SR12301IB](https://openairdocs.org/stc/SR12301IB): Installation of Nginuity DAQ9000 as an alternate Flight Data Acquisition Unit (FDAU). 365 AEROSPACE DDS LIMITED
- [STC SR04465NY](https://openairdocs.org/stc/SR04465NY): Installation of the iPad Mount. Avio Design Group Inc
- [STC SR02727SE](https://openairdocs.org/stc/SR02727SE): Installation and maintenance of the Sunspot 36 and 46 series lights. Whelen Aerospace Technologies
- [STC SR12106IB](https://openairdocs.org/stc/SR12106IB): Installation of Upgrade of Radar Altimeter for 5G Resiliency. Maxcraft Avionics Ltd.
- [STC SR268CH](https://openairdocs.org/stc/SR268CH): Installation of BFG FlightSystems TCAS I (Model TCAS-791/A).. Acron Aviation Inc.
- [STC SR00137DE-D](https://openairdocs.org/stc/SR00137DE-D): Installation of a Life Port "PLUS' System Installation; Serial Number 760288. Air Methods LLC
- [STC SR00138DE-D](https://openairdocs.org/stc/SR00138DE-D): Installation of an Air Methods Emergency Medical Accessory Package; Serial Number 760288. Air Methods LLC
- [STC SR00139DE-D](https://openairdocs.org/stc/SR00139DE-D): Installation of an Air Methods Avionics Upgrade Package; Serial Number 760288. Air Methods LLC
- [STC SR01955SE](https://openairdocs.org/stc/SR01955SE): Installation of a Supplemental Lighting System. Aviation Specialties Unlimited Inc.
- [STC SR02473AK](https://openairdocs.org/stc/SR02473AK): Installation of the L-3 Communications NGT-9000R/RD and NGT-9000/D ADS-B IN/OUT system. StandardAero Atlantic USA Inc.
- [STC SR09011RC](https://openairdocs.org/stc/SR09011RC): Manufacture of an emergency exit window in passenger door.. HELIFAB
- [STC SR09211RC](https://openairdocs.org/stc/SR09211RC): Installation of an external mount life raft deployment system.. HELIFAB
- [STC SR09355RC](https://openairdocs.org/stc/SR09355RC): Installation of 12 place passenger seats. HELIFAB
- [STC SR01367SE](https://openairdocs.org/stc/SR01367SE): Installation of Rockwell Collins Four Tube FDS 2000 Electronic Flight Instrument System (EFIS) and Rockwell Collins AHC 3000 Attitude Heading Reference System (AHRS).. Helifab
- [STC SR02352AK](https://openairdocs.org/stc/SR02352AK): Installation of an AXSYS FLIR Camera System. Helifab
- [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 SR00112BO](https://openairdocs.org/stc/SR00112BO): Installation of  either the OuterLink Corporation CP-2 or  CP-3i SATCOM System in accordance with OuterLink Corporation Master Document List No. D000-0042, Revision N, dated August 19, 2009, or later FAA-approved revision.. Outerlink Corporation
- [STC SR01520SE](https://openairdocs.org/stc/SR01520SE): Installation of a Modularized Main DC Electrical Junction Box.. Helifab
- [STC SR04609NY](https://openairdocs.org/stc/SR04609NY): Installation of Garmin HTAWS (Helicopter Terrain Awareness Warning System). Maxcraft Avionics Ltd.
- [STC SR02322AK](https://openairdocs.org/stc/SR02322AK): Installation of a fixed mounted Max-Vis Enhanced Vision System (EVS) Model 1500. PECO Inc
- [STC SH3200NM](https://openairdocs.org/stc/SH3200NM): Installation of dual Sperry SPZ-7000 digital automatic flight control systems.. Honeywell International Inc
- [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 SH2224NM](https://openairdocs.org/stc/SH2224NM): Installation of dual Sperry EDZ-705 Electronic Flight Instrument Systems, (EFIS).. Honeywell International Inc
- [STC SH2218NM](https://openairdocs.org/stc/SH2218NM): Installation of Sperry digital automatic flight control systems for one or two pilot IFR/VFR operation.. Honeywell International Inc
- [STC SR04440NY](https://openairdocs.org/stc/SR04440NY): Installation of the Mid Continent MD302 Standby Attitude Module. Maxcraft Avionics Ltd.
- [STC SR02667SE](https://openairdocs.org/stc/SR02667SE): Installation of a Honeywell ASPIRE 200 Intermediate Gain (IG) SATCOM system. Honeywell International
- [STC SR00764DE](https://openairdocs.org/stc/SR00764DE): Installation of Automatic Dependent Surveillance - Broadcast (ADS-B) Out functionality using the Trig Avionics TT22 Transponder and Freeflight Systems 1201 Global Positioning System (GPS) with Wide Area Augmentation System (WAAS). Peregrine
- [STC SH5778SW](https://openairdocs.org/stc/SH5778SW): Addition of Electrically Driven Vapor Cycle, Freon or Refrigerant R-134a, Air Conditioning System. Air Comm Corporation
- [STC SR00162DE-D](https://openairdocs.org/stc/SR00162DE-D): Installation of a LifePort 'PLUS' system.. LifePort LLC
- [STC SR00391DE](https://openairdocs.org/stc/SR00391DE): Installation of TREC dual patient handling system.. LifePort LLC
- [STC SR02125LA](https://openairdocs.org/stc/SR02125LA): Installation of a One Man Loading Patient Litter System. LifePort LLC
- [STC SR02432SE](https://openairdocs.org/stc/SR02432SE): Installation of the Twin Rotary Evacuation Carriage (TREC) system. LifePort LLC
- [STC SR02611NY-D](https://openairdocs.org/stc/SR02611NY-D): Installation of the LifePort One Man Loading Patient Litter System. LifePort LLC
- [STC SH8678SW](https://openairdocs.org/stc/SH8678SW): Installation of an electronic bay access door window.. The NORDAM Group LLC
- [STC SH8679SW](https://openairdocs.org/stc/SH8679SW): Installation of a chin window.. The NORDAM Group LLC
- [STC SR04023CH](https://openairdocs.org/stc/SR04023CH): Install air ambulance conversion. Spectrum Aeromed LLC dba Spectrum Aeromed
- [STC SR00847DE](https://openairdocs.org/stc/SR00847DE): Replacement of Honeywell (formerly Sperry) ED-800 cathode ray tube (CRT) display, part number (p/n) 7003110-901/-902, with Esterline CMC Electronics CMA-6800 multi-purpose liquid crystal display (LCD), p/n 100-604045-001/-002, respectively. Peregrine
- [STC SR02418SE](https://openairdocs.org/stc/SR02418SE): Dart Aerospace D076-612-011/-015 Mirror Kits. Dart Aerospace USA Inc.
- [STC SR03551NY](https://openairdocs.org/stc/SR03551NY): Installation of Garmin GTX33H Mode S Transponder and GTS Traffic System. Maxcraft Avionics Ltd.
- [STC SR03573NY](https://openairdocs.org/stc/SR03573NY): Installation of Garmin GTN/GNS() Navigation with EDZ-705 or EDZ-756 EFIS. Maxcraft Avionics Ltd.
- [STC SR04227NY](https://openairdocs.org/stc/SR04227NY): Installation of Garmin GWX Weather Radar System. Maxcraft Avionics Ltd.
- [STC SR00256BO](https://openairdocs.org/stc/SR00256BO): Installation of Universal Avionics Systems Corporation (UASC) Software Control Number (SCN) 31.X in UASC Cockpit Display Computer (UCDC) P/N 3040-05-( ).. Pro Star Aviation, LLC
- [STC SR00264BO](https://openairdocs.org/stc/SR00264BO): Installation of Garmin GMX 200 Multi Function Display.. Pro Star Aviation, LLC
- [STC SR00274BO](https://openairdocs.org/stc/SR00274BO): Installation of an L3 Communications GH-3100 Electronic Standby Instrument System (ESIS) and Optional Emergency Bus. Pro Star Aviation, LLC
- [STC SR00275BO](https://openairdocs.org/stc/SR00275BO): Installation of tail shaft cover antenna mount. Pro Star Aviation, LLC
- [STC SR00287BO](https://openairdocs.org/stc/SR00287BO): Installation of a single UNS-1Fw/Lw Flight Management System (FMS) with embedded Wide Area Augmentation System and a Universal LP/LPV Monitor in accordance with ProStar Installation Data List (IDL) No. 20819-IDL-01, Revision E, dated 4  Feburary 2011, or later FAA-approved revisions.. Pro Star Aviation, LLC
- [STC SR00289BO](https://openairdocs.org/stc/SR00289BO): Installation ofa Kollsman General Aviation Vision System (GAViS ). Pro Star Aviation, LLC
- [STC SR04022NY](https://openairdocs.org/stc/SR04022NY): AF-ADELT improved installation. Caledonian Airborne Systems Ltd
Caledonian House
- [STC SR02445NY-D](https://openairdocs.org/stc/SR02445NY-D): Installation of a Canadian Marconi (CMC) CMA-2012C in place of a RACAL 91 Doppler.. RSG Products
- [STC SR09570RC](https://openairdocs.org/stc/SR09570RC): Installation of Night Vision Goggle Compatible Lighting System. U.S. Cutoms and Border Protection
L&M Rotary Wing Program Office

All 470: https://openairdocs.org/tcds/H1NE/stcs.md

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.