# TCDS R00024BO: Sikorsky Aircraft Corporation

- Type: Type certificate data sheet
- Status: Current
- Holder: Sikorsky Aircraft Corporation
- Revision: 28
- Revised: October 4, 2021
- Product: Aircraft, Rotorcraft
- Certification basis: Part 29, Part 36
- Registered aircraft: 50, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/f5/cc/f5cc9eb9c87bf9f475906f4e9d4c65e9f348f62b28bd4117274d34253260ac3b
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/1B04E1B81D203AF1862587650044B304.0001
- Page: https://openairdocs.org/tcds/R00024BO

## Models (1)

As the data sheet lists them.

- S-92A

## What the data sheet says

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

```text
I I I I I I I I I I I I I I I I 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
R00024BO 
Revision 28 
Sikorsky Aircraft 
Model S-92A 
October 4, 2021 
TYPE CERTIFICATE DATA SHEET NO. R00024BO 
This data sheet, which is part of Type Certificat e (TC) Number R00024BO, prescribes conditions and 
limitations under which the product for which the Ty pe Certificate was issued meets the airworthiness 
requirements of the Federal Aviation Regulations. 
TYPE CERTIFICATE (TC) HOLDER: Sikor sky Aircraft Corporation 
6900 Main Street 
Stratford, CT 06615-9129   
MODEL NUMBER S-92A (Transport Helicopter, Category A, Approved 17 
December 2002; Transport Helicopter, Category B, 
Approved May 7, 2004) 
ENGINES 2 General Electric Company Model GE CT7-8 (TC E8NE) or 
2 General Electric Company Model GE CT7-8A (TC E8NE) or 
2 General Electric Company Model GE CT7-8A6 (TC E8NE) 
FUELS JET A, JET B, JET A-1, JP-4, JP-5, JP-8, PRC No. 3, TS-1, RT 
For all operations below –20°C (-4°F) ambient temperature, all fuel used 
must contain MIL-D-27686 or equivalent anti-icing additive. 
ENGINE AND TRANSMISSIONS APPROVED OILS 
See Rotorcraft Flight Manual for list of approved oils. 
HYDRAULIC FLUID MIL-PRF-87257 is authorized for use at all approved ambient 
temperatures. 
MIL-PRF-83282 may only be used at ambient temperatures above -32°C (-
25°F). 
DEICING FLUID Kilfrost DF PLUS (88) 
ENGINE AND TRANSMISSION LIMITS 
Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 
Rev 28 3 3 24 27  27  27  27  27  25 24 26 24 27 28

Page 2 of 15 R00024BO 
CT7-8 Engine 
DUAL ENGINE LIMITS 
Rating Time Q (%) T4.5 
(°C) 
Ng (%) Np (%) Rated SHP 
@ SLS 
Rated 
Np (%) 
Max continuous 100 920 99.9 106 2043 105 
86 (1) when airspeed is greater than 100 KIAS 
30 Min (2) 30 min 100 957 101.5 106 2336 105 
Takeoff 5 min 100 986 102.9 106 2520 105 
Transient 12 sec 987 103.2 116 
10 sec 120 (3) 
SINGLE ENGINE LIMITS 
Rating Time Q (%) T4.5 
(°C) 
Ng (%) Np (%) Rated SHP 
@ SLS 
Rated 
Np (%) 
Max continuous 120 920 99.9 106 2043 105 
OEI 30 min 120 979 102.4 106 2498 100 
OEI 2 min 120 990 102.9 106 2520 100 
OEI 30 sec 135 1010 103.7 106 2600 100 
Transient 5 sec 156(3) 
Max starting peak 1000 
 Shaded box with bold number denotes a FADEC controlled limiter value. 
 Q (%) values are gearbox limits. 
 (1) 86% Q is not a gearbox limit. Its purpose is to limit flight control loads at high speed thereby preserving 
dynamic component replacement times. 
 (2) Rating applies to hovering flight only. 
 (3) Associated with “torque ramp up” due to abnormal rotor droop at FADEC controlled dual or OEI limit. 
 100% Q corresponds to a combined power input from both engines to the MGB of 4,170 shp at a 
rotor speed of 105% (258 rpm). Power turbine speed (Np) of 105% corresponds to 21,945 rpm. 
 Maximum continuous dual engine torque may exceed 100% on one engine to a maximum of 110% 
provided that the torque on the other engine is proportionally less than 100% and the sum of the 
individual torque values does not exceed 200%. 
 Np overspeed trip is at 120%. 
 Ng overspeed trip is at 108.5% 
 When flying at altitudes greater than 8,000 feet at outside air temperatures lower that –20 degrees C, it is 
possible to reach the corrected Ng speed limit of the engine. When this occurs, the engine will not produce 
more power. The only indication that the pilot will see when reaching this limit is that further increase in 
collective will commensurately droop Nr.

Page 3 of 15 R00024BO 
CT7-8A Engine 
DUAL ENGINE LIMITS 
Rating Time Q (%) T4.5 
(°C) 
Ng (%) Np (%) Rated SHP 
@ SLS 
Rated 
Np (%) 
Max continuous 100 935 99.9 106 2043 105 
86 (1) when airspeed is greater than 100 KIAS 
30 Min (2) 30 min 100 988 101.5 106 2336 105 
Takeoff 5 min 100 995 102.9 106 2520 105 
Transient 12 sec 1003 103.2 116 
10 sec 120 (3) 
SINGLE ENGINE LIMITS 
Rating Time Q (%) T4.5 
(°C) 
Ng (%) Np (%) Rated SHP 
@ SLS 
Rated 
Np (%) 
Max continuous 120 988 102.4 106 2498 105 
OEI 2 min 120 1006 102.9 106 2520 100 
OEI 30 sec 141 1049 103.7 106 2740 100 
Transient 5 sec 156(3) 
Max starting peak 1000 
 Shaded box with bold number denotes a FADEC controlled limiter value. 
 Q (%) values are gearbox limits. 
 (1) 86% Q is not a gearbox limit. Its purpose is to limit flight control loads at high speed thereby 
preserving dynamic component replacement times. 
 (2) Rating applies to hovering flight only. 
 (3) Associated with “torque ramp up” due to abnormal rotor droop at FADEC controlled dual or OEI limit. 
 100% Q corresponds to a combined power input from both engines to the MGB of 4,170 shp at a rotor 
speed of 105% (258 rpm). Power turbine speed (Np) of 105% corresponds to 21,945 rpm. 
 Maximum continuous dual engine torque may exceed 100% on one engine to a maximum of 110% provided 
that the torque on t he other engine is proportionally less than 100%  and the sum of the individual torque 
values does not exceed 200%. 
 Np overspeed trip is at 120%. 
 Ng overspeed trip is at 108.5% 
 When flying at altitudes greater than 8,000 feet at outside air temperatures lower that –20 
degrees C, it is possible to reach the corrected Ng speed limit of the engine. When this occurs, 
the engine will not produce more power. The only indication that the pilot will see when reaching 
this limit is that further increase in collective will commensurately droop Nr.

Page 4 of 15 R00024BO 
CT7-8A6 Engine 
DUAL ENGINE LIMITS 
Rating Time Q(%) T4.5(ºC) Ng(%) Np(%) Rated SHP @ SLS Rated Np(%) 
Max continuous 100 946 100.6 106 2329 105 
86 (1) when airspeed is greater than 100 KIAS ** 
30 Min (2) 30 min 100 996 102.9 106 2637 105 
Takeoff 5 min 100 1008 102.9 106 2695 105 
Transient 12 sec 1009 103.2 116 
10 sec 120 (3) 
SINGLE ENGINE LIMITS 
Rating Time Q(%) T4.5(ºC) Ng(%) Np(%) Rated SHP @ SLS Rated Np(%) 
Max continuous 120 996 102.9 106 2637 105 
OEI 2 min 120 1013 102.9 106 2684 100 
OEI 30 sec 141 1097 103.7 106 2845 100 
Transient 5 sec 156(3) 
Max starting peak 1000 
 Shaded box with bold font denotes a FADEC controlled limiter value. 
 Q (%) values are gearbox limits. 
 100% Q corresponds to a combined power input from both engines to the MGB of 4,170 SHP, at a rotor 
speed of 105% (258 RPM). Power turbine speed (NP) of 105% corresponds to 21,945 RPM. 
 Maximum continuous dual engine torque may exceed 100% on one engine to a maximum of 110% provided 
that the torque on the other engine is proportionally less than 100% and the sum of the individual torque 
values does not exceed 200%. 
 Np overspeed trip is at 120%. Ng overspeed trip is at 108.5%. 
 When flying at altitudes greater than 8,500 ft at outside air temperatures lower than −30°C, it is possible to 
reach the corrected Ng speed limit of the engines. When this occurs, the engine will not produce more power. 
The only indication that the pilot will see when reaching this limit is that any further increase in collective will 
commensurately droop Nr. 
 Engine will be shut down by ground idle protection if TGT is above 980°c, power control lever (PCL) is at idle, 
weight on wheels, and engine start cycle is completed. 
Notes: 
1. Greater than 100 KIAS & below a density altitude of 6,000 ft Hd, the torque limit is reduced to 86% Q. greater 
than 100 KIAS & above 6,000 ft Hd, the torque limit is further reduced by 2% Q per 1,000 ft Hd. This is not a 
gearbox limit. Its purpose is to limit flight control loads at high speed to preserve dynamic component 
replacement times. This limit is not FADEC controlled. 
2. Associated with torque ramp up due to abnormal rotor droop at FADEC controlled dual engine or OEI limit. 
3. Rating applies to hovering flight only. 
4. PCL must be at idle for limiter to function.

Page 5 of 15 R00024BO 
ROTOR SPEED LIMITS 
DRIVE SYSTEM LIMITS 
POWER OFF 
Maximum 110% Nr 
Minimum 95% Nr 
POWER ON 
Maximum 110% Nr 
Minimum 95% Nr 
Dual Engine 
Torque (%) No Ins pect Req’d Serviceabilit y Check Remove/Replace MGB 
0% to 100% Continuous 
101% to 120% < 10 sec ≥ 10 sec 
121% to 140% < 10 sec ≥ 10 sec 
greater than 140% Any occurrence 
Single Engine 
Torque (%) No Ins pect Req’d Serviceabilit y Check Remove/Replace MGB 
0% to 120% Continuous 
121% to 140% < 30 sec ≥ 30 sec 
141% to 156% < 5 sec ≥ 5 sec 
greater than 156% Any occurrence 
AIRSPEED LIMITS 
Vne (never exceed) Power On 165 KIAS. See Rotorcraft Flight Manual for variations of 
Vne with gross weight and density altitude. 
Vle/Vlo (gear extended/gear operating) 165 KIAS/165 KIAS. 
Vne with floats “armed” 80 KIAS. 
Vne Power Off 120 KIAS. 
Vne Hoist Extended 120 KIAS. 
Vne Upper Sliding Door Open 120 KIAS. 
Vne External Cargo 120 KIAS. Heavy External Lift

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30000 
25000 
20000 
15000 
340.0 
- 1 
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Weight and Center of Gravity Envelope 
Maximum Gross Weight 26,500 Pounds 
i I -,J ' I 3&0.3: 
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--1 ---, t--- ·t--- :--- -1-- -t- 1--t- --1----- ----1-----t----1"--- 1--- ·t-- ·t--- -1- ,- -- : 1--~ 
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345.0 350.0 355.0 
Aircraft Stat ion (inches) 
Heavy External Lift Limit 
Light External Lift Limit 
Aircraft Without External Load 
360.0 365.0 
Page 6 of 15 R00024BO 
CENTER OF GRAVITY (CG) LIMITS

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30000 
25000 
20000 
Weight and Center of Gravity Envelope 
Maximum Gross Weight 27,700 Pounds 
: 347!.7 36L_, 360.~ 
2a,300 : I i -----;i 
I ' -- r--------------------. 1--?8, 390 
' ' 2~.100--: : : : : : 360.8: 21_,100 
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: 346,8 : : : : : : : : : : : : 
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15000 
340.0 
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345.0 350.0 355.0 360.0 365.0 
Aircraft Station (inches) 
Heavy External Lift Limit 
Light External Lift Limit 
Aircraft Without External Load 
Page 7 of 15 R00024BO 
CENTER OF GRAVITY (CG) LIMITS (CONTINUED)

10 
S-92 Lateral CG Limits 
I ,+3.53 -3.53 I 
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1 
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100,000 lbin. I I 
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15!200 - I I I 
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: +6 17 : : 
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21000--~----- U-----L------~-------1 
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-4.00 
2-&900 ---- ···----~------ ◄···----1 I I 
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23000"§[------~-------i------~-------
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20000--~------~--- ---~------~-------
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49000 --~------ ◄---- --~------➔-------
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1 
--1 ------ .-------1 1------ :-------
1 I I I 
I I -6.17 I 
8 6 4 2 
LH 
0 
Buttline in. 
-2 -4 -6 -8 -10 
RH 
Heavy External Lift Limit 
Light External Lift Limit 
Aircraft Without External Load 
Page 8 of 15 R00024BO 
LATERAL CG LIMITS: 
MAXIMUM GROSS WEIGHT 26,500 POUNDS

10 
5-92 Latera l CG Limits 
: +3.61 : +3r53 -3 73 ;3 61 I I 
- - - - - - ~ - - - - - - - ~ 2~,~o - - - : - - - - -: - - - - - - - 28000- -:- - - - - - _! - - - - - - -:- - - - - - - + -------
I I 27,700 ---,- ,,_ ___ .,... ____ +-----,--- - I I I 
I I I I I I I I 
•••••• J ••••••• L •••••• J •••••• L •••••• · 27000··~····· J ••••••• L •••••• ~ ••••••• 
I I I ______ J _______ L ___ _ ______ L _____ _ 
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100,000 lb1n. 
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······,······ ~r······,·······r······ 
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· 20000 • · ~ · · · · · · ,-4 iio · · · · ~ · · · · · · 1 · · · · · · · 
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26000---- ........................ . 
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- 24000 - , ~------~ ------~------~-------
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: : -4.17 : 
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8 6 4 2 
LH 
0 
Buttl ine in. 
-2 -4 -6 -8 -10 
RH 
Heavy External Lift Limit 
Light Externa l Lift Limit 
Aircraft Without External Load 
Page 9 of 15 R00024BO 
LATERAL CG LIMITS (CONTINUED): 
MAXIMUM GROSS WEIGHT 27,700 POUNDS 
EMPTY WEIGHT C.G. RANGE None 
DATUM 341.2 inches forward of the main rotor centroid 
LEVELING MEANS Leveling plate at STA 238.3, BL 40 RH, and plumbline from 
top of RH forward doorframe. 
MAXIMUM WEIGHT 26,500 pounds 
27,700 pounds with Gross Weight Expansion Option (see 
Note 16) 
28,300 pounds with external load. Heavy External Lift 
MAXIMUM EXTERNAL LOAD 8000 pounds. Heavy External Lift

Page 10of 15 R00024BO 
ALTITUDE LIMITS Takeoff and landing 
11,000 feet density altitude 
Enroute 
15,000 feet density altitude 
10,000 feet pressure altitude in icing conditions 
See Note 11 
AMBIENT TEMPERATURE LIMITS -40°C to ISA+35°C (see Note 9) 
MINIMUM FLIGHT CREW 2 pilots (See Note 8) 
3 (2 pilots, 1 cabin crew) Combination Passenger and 
Cargo 
NUMBER OF SEATS 2 Crew 
1 Observer 
19 Passenger maximum (See Notes 6, 8 and 
14) 
Combination Passenger and Cargo Interior 
Option 
3 Crew 
9 Passenger maximum  
MAXIMUM BAGGAGE 1000 pounds 
Combination Passenger and Cargo Interior Option 
0 pounds 
MAXIMUM CARGO Combination Passenger and Cargo Interior Option 
(See Note 15)  92276-54000-011 kit installed 
1650 lb at 200 lb./sq. ft., Sta 281 to 462 
1100 lb at 200 lb./sq. ft., Sta 340 to 462 
550 lb at 200 lb./sq. ft., Sta 397 to 462 
 92276-54000-012 kit installed 
5000 lb at 200 lb./sq. ft., Sta 281 to 462 
3100 lb at 200 lb./sq. ft., Sta 340 to 462 
1200 lb at 200 lb./sq. ft., Sta 397 to 462 
FUEL CAPACITY 764 gals (pressure refuel) 
713 gals. (gravity refuel) 
4.8 gals. unusable
at Station 362.5 
(See Notes 1 and 7) 
OIL CAPACITY See General Electric Installation Manual SEI-866 
ROTOR BLADE CONTROL MOVEMENTS For rigging information refer to Maintenance Manual

Page 11of 15 R00024BO 
MANUFACTURER’S SERIAL NUMBERS Sikorsky Aircraft Corporation under Production Certificate 
CERTIFICATION BASIS 
Number 105: 
920006 through 920114, 920116 through 920126, 
920128, 920130, 920133, 920137, 920143 and 
subsequent are eligible. 
Keystone Helicopter Corporation for Production under 
Type Certificate Only. 
920115 is eligible 
Keystone Helicopter Corporation under Production 
Certificate Number 121NE: 
920127*, 920129*, 920131, 920132, 920134 through 
920136, 920138 through 920142 are eligible. 
*920127 and 920129 originally designated as eligible for 
production by Keystone Helicopter Corporation under 
Type Certificate Only and redesignated upon addition of 
S-92A to Production Certificate Number 121 NE. 
Type Certificate No. R00024BO 
14 CFR Part 29 Amendments 29-1 to 29-47, inclusive 
14 CFR Part 36 Amendment 24 
Equivalent Safety Findings: 
Number TC0309BO-R/F-1 
14 CFR Part 29.173 Static longitudinal stability 
14 CFR Part 29.175 Demonstration of static longitudinal stability. 
Number TC0309BO-R/F-4 
14 CFR Part 29.177 Static directional stability. 
Number TC0309BO-R/P-1 
14 CFR Part 29.1305(a)(24) Power Plant Instruments. 
Number TC0309BO-R/P-5 
14 CFR Part 29.1 181(a)(4) Designated Fire Zones; Regions Included. 
Special Conditions: 
No. 29-011-SC for Dual-Engine 30 Minute Power 
No. 29-008-SC for High Intensity Radiated Frequency 
Noise Control Act of 1972 
Compliance with the following optional requirements has been 
established: Ditching provisions FAR 29.563 including 29.801 and 
29.807(d) and excluding 29.1411, 29.1415, and 29.1561 when 
emergency flotation system is installed. For extended over-water 
operations, compliance with the operating rules and FAR 29.1411, 
29.1415, and 29.1561 must be shown.

Page 12of 15 R00024BO 
Anticollision light system installed in accordance with Sikorsky Drawing 
33792-52871
 Basis of certification is the same as the S-92A plus the following
 Equivalent Safety Findings: 
Number AT1610BO-R-S-1 
 14 CFR Part 29.1401(d) Anticollision light system 
Passenger Configuration with Side Facing Executive Seats: 
Basis of certification is the same as the S-92A plus the following 
Equivalent Safety Findings: 
Number AT01655BO-R-C-2, Number AT00407MC-R-C-1, and 
Number AT00407MC-R-C-2 
14 CFR Part 29.809(a) Emergency exit arrangement 
14 CFR Part 29.813(c)(2) Emergency exit access 
Special Conditions: 
None 
Combination Passenger and Cargo Configuration: 
Basis of certification is the same as the S-92A plus the following 
Equivalent Safety Findings: 
Number TD1454BO-R-S-1 
14 CFR 29.855(a)(1), (d) Cargo and baggage compartments 
Number TD1454BO-R-C-1 
14 CFR 29.809(a) Emergency exit arrangement 
14 CFR 29.813(c)(2) Emergency exit access 
Special Conditions: 
None 
Search and Rescue (SAR) Automatic Flight Control System (AFCS) 
Installation: 
Basis of certification is the same as the S-92A plus the following 
Equivalent Safety Findings: 
None 
Special Conditions: 
No. 29-023-SC for Installation of a Search and Rescue (SAR) 
Automatic Flight Control System (AFCS) 
If CVR/FDR defined by 33792-54647 is installed, then compliance has also 
been shown to Amendment 29-52 of 14 CFR 29.1457 and 29.1459.

Page 13of 15 R00024BO 
PRODUCTION BASIS Sikorsky  Aircraft Corporation 
Production Certificate Number 105 
Keystone Helicopter Corporation, Production Certificate Number 121 NE, 
under licensing agreement with Sikorsky Aircraft Corporation. 
In the event of an application for a standard airworthiness certificate or, if 
an applicant intends to produce a new aircraft under 14 CFR § 
21.183(d), and the applicant is manufacturing, building, or assembling to 
another person’s type certificate, t he applicant must provide written 
evidence of permission from the type certificate holder. Conduct of such 
activity without written evidence of permission may be a violation of 49 
U.S.C. § 44704(a)(3). 
EQUIPMENT The basic required equipment as prescribed in the applicable 
Airworthiness regulations (see Certification Basis) must be installed in 
the aircraft for certification. 
In addition, the following item(s) of equipment is (are) required: 
Rotorcraft Flight Manual as shown in FAA Approved Sikorsky document 
SA S92A-FMCD-000. This document specifies the applicable flight 
manual number for each aircraft. The applicable flight manual number is 
determined by the aircraft configuration. SA S92A-FMCD-000 will be 
revised as required to add additional rotorcraft flight manual numbers, 
new revisions, and new aircraft as appropriate. 
- NOTES -
NOTE 1 Current weight and balance report, including list of equipment included in certified empty 
weight, and loading instructions, when necessary, must be provided for each rotorcraft at 
the time of original certification. The certificated empty weight and corresponding C.G. 
locations must include un-drainable oil and unusable fuel. 
See Rotorcraft Flight Manual loading section for variations of fuel weight and moment- 
arm with variations of fuel and fuel quantity. 
NOTE 2 The rotorcraft must be operated in accordance with the appropriate FAA-approved 
Rotorcraft Flight Manual as required under “EQUIPMENT”. All placards required in the 
FAA-approved Rotorcraft Flight Manual must be installed in the rotorcraft. The following 
placard must be displayed in front of and in clear view of the pilots: 
“THIS HELICOPTER MUST BE OPERATED IN ACCORDANCE WITH THE 
OPERATING LIMITATIONS SPECIFIED IN THE FAA APPROVED 
ROTORCRAFT FLIGHT MANUAL.” 
All placards listed in the approved flight manual must be installed in the specified 
locations. 
NOTE 3 Information essential to the proper main tenance of the rotorcraft is contained in the 
Sikorsky S-92A Maintenance Manual, SA S92A-AMM-000 and in the Airworthiness 
Limitations and Inspection Requirements Manual, SA S92A-AWL-000. The Airworthiness 
Limitations and Inspection Requirements for gross weights above 26,500 pounds are

Page 14of 15 R00024BO 
contained in document number SIC920010 (see Note 16). The values of retirement 
(service) life are contained in Chapter 4 of the Airworthiness Limitations and Inspection 
Requirements Manual in documents SA S92A-AWL-000 and SIC920010 (if applicable). 
The values of retirement (service) life cannot be changed without FAA Engineering 
approval. Manuals SA S92A-AMM-000 and SA S92A-AWL-000 are provided with each 
helicopter. Manual SIC920010 is provided with helicopters with the 27,700 lb. Gross 
Weight Expansion option. 
NOTE 4 The term “Unlimited Life” is defined as 30 ,000 flight hours for the Model S-92A rotorcraft. 
Operation of individual aircraft beyond 30,000 flight hours is contingent upon a Life 
Extension Program approved by FAA Engineering 
NOTE 5 The model S-92A 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 6 Seating arrangements for 19 passengers maximum have been approved by the FAA. With 
these seating arrangements, seats located along the aisle way shall not have armrests 
installed on the aisle way side of any aisle seat unless the aisle way seat armrest 
incorporates an armrest hold down feature. Installation of the Observer Seat and/or 
Passenger Seat located on the forward starboard bulkhead is prohibited with the 
installation of the Lower Search/Rescue Door. Occupancy of the Passenger Seat located 
on the forward starboard bulkhead is prohibited if Observer Seat is installed. Carriage of 
passengers is prohibited with the installation of the Lower Search/Rescue Door. These 
seating arrangements are shown in the Loading Information section of the FAA-approved 
Rotorcraft Flight Manual. Additional optional seating arrangements or related passenger 
provisions may be approved in accordance with the Type Certificate Basis. 
NOTE 7 See the appropriate FAA approved Rotorcraft Flight Manual for fuel capacities of aircraft 
defined by SER-92020578 Revision -, or later approved revision. 
NOTE 8 See the appropriate FAA approved Rotorcraft Flight Manual for minimum required crew and 
passenger limitations of aircraft defined by SER-92020578 Revision -, or later approved 
revision. 
NOTE 9 Preheat must be used for cold soak starts when the OAT is -13°F (-25°C) or below. See 
Rotorcraft Flight Manual for Cold Weather Procedures. 
NOTE 10 External lift operations utilizing the cargo hook include Heavy External Lift and Light 
External Lift.  Heavy and Light External Lift limitations are defined in the Rotorcraft Flight 
Manual and the Airworthiness Limitations and Inspection Requirements Manual.  
NOTE 11 For flight in icing conditions, aircraft must be equipped with Rotorcraft Ice Protection 
System (RIPS) and Rotorcraft Flight Manual as shown in FAA Approved Sikorsky 
document SA S92A-FMCD-000, Revision 5 and subsequent. For flight into icing 
conditions, RIPS must be turned on. RIPS equipped aircraft are not approved for flight in 
icing conditions above 10,000 ft pressure altitude, or for flight in freezing rain, freezing 
drizzle or Supercooled Large Drop (SLD) icing conditions. 
NOTE 12 Any modifications, alterations, or other changes to the exterior of the aircraft that may affect

Page 15of 15 R00024BO 
the operation or function of the RIPS system, or create an area or surface for ice collection 
that may be released in flight, must be approved by FAA Engineering to allow the approval 
of flight in icing conditions to be continued. 
NOTE 13 The S-92A rotorcraft has not been certified for Category A vertical takeoffs and landings 
from an elevated heliport. 
NOTE 14 The S-92A has been certified for Category A with a maximum passenger seating 
configuration of 19 passenger seats and Category B with a maximum passenger seating 
configuration of 9 or less passenger seats 
NOTE 15 Only serial numbers 920140 and 920142 are eligible for carriage of approved cargo in the 
Passenger and Cargo Configuration. 
NOTE 16 Capability to operate above 26,500 pounds and up to 27,700 pounds aircraft gross weight is 
predicated on the aircraft being structurally modified in accordance with the 92070-10004-
011, 92070-10004-013, 92070-10004-017, 92070-10004-019, or 92070-10004-021 Gross 
Weight Extension (GWE) modification kits.  S-92A Rotorcraft Flight Manual Supplement No. 
14 Part 1 “27,700 lb. Gross Weight Expansion” or S-92A Rotorcraft Flight Manual 
Supplement No. 91 Part 1 “CT7-8A6 Engines, 27,700 LB Gross Weight Expansion” must be 
complied with when operating above 26,500 pounds. The information contained in RFM 
Supplement No. 14 and 91 supplements or supersedes the limitations and procedures in 
the basic Rotorcraft Flight Manual.  When operated at gross weights above 26,500 pounds, 
the helicopter must comply with document number SIC920010 “Airworthiness Limitations 
and Inspection Requirements Gross Weight Expansion (GWE) Supplement No. 1.” The 
information contained in document number SIC920010 supplements or supersedes the 
basic Airworthiness Limitations and Inspection Requirements Manual SA S92A-AWL-000. 
NOTE 17 Special mission equipment installations and associated aircraft modifications defined in 
SER-92020578 Revision -, or later approved revision are intended for military, public, or 
government use aircraft only. 
NOTE 18 All S/Ns on this TCDS meet or exceed the crash resistant fuel system certification basis 
requirements listed in section 44737 of Title 49 U.S.C. 
NOTE 19 The type certificate data sheet for General Electric Company CT7-8A/8A6 series engines 
approves engine operation with certain faults in the engine control system. Operation with 
these faults present, known as Time Limited Dispatch, is approved for the S-92A when the 
aircraft is operated in accordance with Rotorcraft Flight Manual Supplement No. 45, Part 1 
revision 3, or later approved revision. 
.....END.....
```

## ADs (46, in force first)

- [AD 2023-09-07](https://openairdocs.org/ad/2023-09-07): Main Rotor Mast/Swashplate · Sikorsky S-92A. Effective Jun 29, 2023
- [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 2022-11-04](https://openairdocs.org/ad/2022-11-04): Horizontal Stabilizer Structure · Sikorsky S-92A. Effective Jun 27, 2022
- [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 2021-19-17](https://openairdocs.org/ad/2021-19-17): Cabin Equipment/Furnishings, Passenger Compartment Equipment · Sikorsky S-92A. Effective Nov 22, 2021
- [AD 2021-08-18](https://openairdocs.org/ad/2021-08-18): Nose/Tail Landing Gear, Main Landing Gear · Sikorsky S-92A. Effective Apr 29, 2021
- [AD 2020-16-19](https://openairdocs.org/ad/2020-16-19): Rotor Drive Indicating System · Sikorsky S-92A. Effective Sep 21, 2020
- [AD 2019-13-05](https://openairdocs.org/ad/2019-13-05): Fuselage Main, Frame · Sikorsky S-92A. Effective Aug 29, 2019
- [AD 2018-19-09](https://openairdocs.org/ad/2018-19-09): Main Landing Gear and Nose Landing Gear · Sikorsky S-92A. Effective Oct 30, 2018
- [AD 2017-22-01](https://openairdocs.org/ad/2017-22-01): Autopilot System · Sikorsky S-92A. Effective Nov 8, 2017
- [AD 2017-10-10](https://openairdocs.org/ad/2017-10-10): Fire Detection · Sikorsky S-92A. Effective Aug 25, 2017
- [AD 2017-07-09](https://openairdocs.org/ad/2017-07-09): Tail Rotor Gearbox · Sikorsky S-92A. Effective May 12, 2017
- [AD 2017-02-51](https://openairdocs.org/ad/2017-02-51): Tail Rotor Control System · Sikorsky S-92A. Effective Mar 20, 2017
- [AD 2016-24-51](https://openairdocs.org/ad/2016-24-51): Tail Rotor Control System · Sikorsky S-92A. Effective Jan 12, 2017
- [AD 2016-21-02](https://openairdocs.org/ad/2016-21-02): Fire Bottle, Fixed · Sikorsky S-92A. Effective Nov 22, 2016
- [AD 2016-07-01](https://openairdocs.org/ad/2016-07-01): Main Hydraulic System · Sikorsky S-92A. Effective May 5, 2016
- [AD 2016-05-11](https://openairdocs.org/ad/2016-05-11): Rotorcraft Flight Control · Sikorsky S-92A. Effective Mar 28, 2016
- [AD 2015-11-10](https://openairdocs.org/ad/2015-11-10): Main Rotor Gearbox · Sikorsky S-92A. Effective Jul 14, 2015
- [AD 2014-12-11 R1](https://openairdocs.org/ad/2014-12-11-R1): Flight Compartment Equipment · Sikorsky S-92A. Effective Mar 13, 2015
- [AD 2013-19-16](https://openairdocs.org/ad/2013-19-16): JASC Code 2620, Extinguishing System · Sikorsky S-92A. Effective Nov 6, 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 2013-10-01](https://openairdocs.org/ad/2013-10-01): Exterior lighting · Agusta AB139, AW139, MBB-BK 117 C-2 and 7 more. Effective Jun 20, 2013
- [AD 2012-22-09](https://openairdocs.org/ad/2012-22-09): Fuselage Main, Attach Fittings · Sikorsky S-92A. Effective Dec 20, 2012
- [AD 2012-14-08](https://openairdocs.org/ad/2012-14-08): Main Rotor Gearbox · Sikorsky S-92A. Effective Aug 1, 2012
- [AD 2012-08-01](https://openairdocs.org/ad/2012-08-01): Engine (Turbine/Turboprop) · Sikorsky S-92A. Effective May 24, 2012
- [AD 2012-06-24](https://openairdocs.org/ad/2012-06-24): Tail Rotor · Sikorsky S-92A. Effective May 15, 2012
- [AD 2011-16-04](https://openairdocs.org/ad/2011-16-04): Rotorcraft Flight Manual (RFM) · Sikorsky S-92A. Effective Nov 14, 2011
- [AD 2011-12-03](https://openairdocs.org/ad/2011-12-03): Main gearbox (MGB) upper housing assembly · Sikorsky S-92A. Effective Jun 17, 2011
- [AD 2010-24-04](https://openairdocs.org/ad/2010-24-04): Main gearbox (MGB) assembly · Sikorsky S-92A. Effective Dec 6, 2010
- [AD 2010-10-03](https://openairdocs.org/ad/2010-10-03): MGB filter bowl assembly · Sikorsky S-92A. Effective Jun 21, 2010
- [AD 2009-25-10](https://openairdocs.org/ad/2009-25-10): Main gearbox · Sikorsky S-92A. Effective Dec 21, 2009
- [AD 2009-13-01](https://openairdocs.org/ad/2009-13-01): Main gearbox (MGB) filter bowl assembly · Sikorsky S-92A. Effective Jul 1, 2009
- [AD 2007-17-05](https://openairdocs.org/ad/2007-17-05): Shaft and bearing assembly (shaft and bearing assembly) · Sikorsky S-92A. Effective Aug 21, 2007
- [AD 2006-15-19](https://openairdocs.org/ad/2006-15-19): Main gearbox (MGB) upper main housing assembly (housing assembly) · Sikorsky S-92A. Effective Aug 16, 2006
- [AD 2006-11-14](https://openairdocs.org/ad/2006-11-14): Main transmission assembly mounting bolt (bolt) · Sikorsky S-92A. Effective Jun 15, 2006
- [AD 2005-13-13](https://openairdocs.org/ad/2005-13-13): Tail gear box output housing · Sikorsky S-92A. Effective Jul 8, 2005
- [AD 2022-02-01](https://openairdocs.org/ad/2022-02-01) (historical): Main Rotor Mast/Swashplate · Sikorsky S-92A. Effective Feb 18, 2022
- [AD 2021-23-13](https://openairdocs.org/ad/2021-23-13) (historical): Ground Proximity System · Airbus Helicopters K-225, K-190A, K-240 and 237 more. Effective Dec 9, 2021
- [AD 2021-04-16](https://openairdocs.org/ad/2021-04-16) (historical): Nose/Tail Landing Gear, Main Landing Gear · Sikorsky S-92A. Effective Apr 14, 2021
- [AD 2020-26-13](https://openairdocs.org/ad/2020-26-13) (historical): Horizontal Stabilizer Structure · Sikorsky S-92A. Effective Feb 1, 2021
- [AD 2017-14-03](https://openairdocs.org/ad/2017-14-03) (historical): Main Landing Gear and Nose Landing Gear · Sikorsky S-92A. Effective Aug 11, 2017
- [AD 2014-07-04 R1](https://openairdocs.org/ad/2014-07-04-R1) (historical): Main Hydraulic System · Sikorsky S-92A. Effective Sep 30, 2014
- [AD 2014-12-11](https://openairdocs.org/ad/2014-12-11) (historical): Flight Compartment Equipment · Sikorsky S-92A. Effective Sep 8, 2014
- [AD 2014-07-04](https://openairdocs.org/ad/2014-07-04) (historical): Main Hydraulic System · Sikorsky S-92A. Effective May 1, 2014
- [AD 2009-23-51](https://openairdocs.org/ad/2009-23-51) (historical): Main Gearbox (MGB) · Sikorsky S-92A. Effective Feb 19, 2010
- [AD 2009-07-53](https://openairdocs.org/ad/2009-07-53) (historical): Main gearbox filter bowl assembly studs · Sikorsky S-92A. Effective Apr 27, 2009

## Registered aircraft by registry model (OpenAirDocs)

- [Sikorsky S-92A](https://openairdocs.org/model/sikorsky-s-92a): 49 aircraft (registry codes 8141832, 8140300)
- [Keystone Helicopter S-92A](https://openairdocs.org/model/keystone-helicopter-s-92a): 1 aircraft (registry code 4900106)
- [Sikorsky S-92](https://openairdocs.org/model/sikorsky-s-92): 0 aircraft (registry code 8141825)

## STCs approved under this data sheet (120, first 50)

- [STC SR09460RC](https://openairdocs.org/stc/SR09460RC): Installation of a Cabin Door Replacement.. Summit Aviation Inc.
- [STC SR12395IB](https://openairdocs.org/stc/SR12395IB): Camera Replacement Installation must be in accordance with Heli-One Master Drawing List. Heli-One Canada
- [STC SR02443NY-D](https://openairdocs.org/stc/SR02443NY-D): Installation or a Night Vision Goggle (NVG) compatible Lighting system. ATI Engineering Services LLC
- [STC SR04583CH](https://openairdocs.org/stc/SR04583CH): INSTALL HELITAK FT5000 FIRE TANK LIQUID DISPENSING SYSTEM. STANDARDAERO BUSINESS AVIATION SERVICES LLC
- [STC SR02553NY](https://openairdocs.org/stc/SR02553NY): The Passenger Seating Configuration to be done. VIH Aerospace
- [STC SR00160IB](https://openairdocs.org/stc/SR00160IB): Installation of Honeywell RDR-7000 Weather Radar as replacement of the existing Primus-70XA weather radar. SCANDINAVIAN AVIONICS DESIGN ApS
- [STC SR09469RC](https://openairdocs.org/stc/SR09469RC): Installation of an Aft Cabin VIP lavatory. Summit Aviation Inc.
- [STC SR09470RC](https://openairdocs.org/stc/SR09470RC): Installation of a Cabin Extension and Modified Baggage Compartment. Summit Aviation Inc.
- [STC SR09471RC](https://openairdocs.org/stc/SR09471RC): Installation of a VIP State Interior. Summit Aviation Inc.
- [STC SR02158LA](https://openairdocs.org/stc/SR02158LA): Sikorsky S-92A Search and Rescue (SAR)/Cargo Smoke Seal Provisions.. LifePort LLC
- [STC SR01934LA](https://openairdocs.org/stc/SR01934LA): Installation of Search and Rescue (SAR)/Cargo interior configuration. Aeromatrix Composites
- [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 SR00362BO](https://openairdocs.org/stc/SR00362BO): Installation of a Satcom Communications and Flight Data Monitoring System KIT S92-SAT-100. Outerlink Corporation
- [STC SR00086IB](https://openairdocs.org/stc/SR00086IB): Installation of the SAR Grab Handles. VIH Aerospace Inc.
- [STC SR03370AT](https://openairdocs.org/stc/SR03370AT): Structural Provisions for a Composite Ramp Floor Panel. Aeromatrix Composites
- [STC SR09926AC](https://openairdocs.org/stc/SR09926AC): Installation of Night Vision Imaging System (NVIS) / Night Vision Goggle (NVG) Compatible Lighting System. Aero Dynamix Inc.
- [STC SR04564NY](https://openairdocs.org/stc/SR04564NY): Installation of the SkyTrac ISAT Airborne Position / Data Communicator. SkyTrac Systems Ltd
- [STC SR04485NY](https://openairdocs.org/stc/SR04485NY): Installation of a FWD LHS and/0r AFT RHS Emergency Hatch Bubble Window(s). Icarus Aero 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 SR02560NY](https://openairdocs.org/stc/SR02560NY): Installation of LHS Crew Bubble Window. VIH Aerospace Inc
- [STC SR04350NY](https://openairdocs.org/stc/SR04350NY): Installation of Cabin FWD LHS/AFT RHS Emergency Hatch Bubble Windows. Canadian Helicopters Limited
- [STC SR04337NY](https://openairdocs.org/stc/SR04337NY): Installation of SkyTrac ISAT Airborne Position/Data Communicator. SkyTrac Systems Ltd
- [STC SR01948LA](https://openairdocs.org/stc/SR01948LA): Installation of a triple litter stacking system.. LifePort LLC
- [STC SR02666CH](https://openairdocs.org/stc/SR02666CH): Install air ambulance conversion. Spectrum Aeromed LLC dba Spectrum Aeromed
- [STC SR00917DE](https://openairdocs.org/stc/SR00917DE): Installation of Concorde VRLA battery. Concorde Battery Corporation
- [STC SR00826DE](https://openairdocs.org/stc/SR00826DE): Installation of Honeywell Sky Connect Tracker III system. Cert Works LLC
- [STC SR02547SE](https://openairdocs.org/stc/SR02547SE): Installation of a Supplemental Lighting System. Aviation Specialties Unlimited Inc.
- [STC SR02629LA](https://openairdocs.org/stc/SR02629LA): Installation of Engine Inlet Barrier Filter System. Aerometals
- [STC SR02402NY](https://openairdocs.org/stc/SR02402NY): Installation of Alternate Utility Interior. Sikorsky Aircraft Corporation
- [STC SR02685CH](https://openairdocs.org/stc/SR02685CH): Install Internal Cargo Handling System. Telair US LLC
- [STC SR02436NY-D](https://openairdocs.org/stc/SR02436NY-D): Installation of High Intensity Strobe Light (HISL) System. Sikorsky Aircraft Corporation
- [STC SR01973NY-D](https://openairdocs.org/stc/SR01973NY-D): Installation of Keystone Helicopter Replacement Mid Cabin Floor Panel. Sikorsky Aircraft Corporation
- [STC SR01974NY-D](https://openairdocs.org/stc/SR01974NY-D): Installation of a Keystone Helicopter Baggage Retention System.. Sikorsky Aircraft Corporation
- [STC SR01975NY-D](https://openairdocs.org/stc/SR01975NY-D): Installation of a Keystone Helicopter Entry Handrail System.. Sikorsky Aircraft Corporation
- [STC SR01976NY-D](https://openairdocs.org/stc/SR01976NY-D): Installation of a Keystone Helicopter Auxiliary Gauges and Relocation of Fill Ports for the Low Float Pressure Warning System. Sikorsky Aircraft Corporation
- [STC SR01977NY-D](https://openairdocs.org/stc/SR01977NY-D): Installation of a Sunvisor System.. Sikorsky Aircraft Corporation
- [STC SR02103NY-D](https://openairdocs.org/stc/SR02103NY-D): Installation of an Aisle Lighting System.. Sikorsky Aircraft Corporation
- [STC SR02104NY-D](https://openairdocs.org/stc/SR02104NY-D): Installation of a Universal Cockpit Display (UCD) System. Sikorsky Aircraft Corporation
- [STC SR02105NY-D](https://openairdocs.org/stc/SR02105NY-D): Installation of Gooseneck Lighting System.. Sikorsky Aircraft Corporation
- [STC SR02106NY-D](https://openairdocs.org/stc/SR02106NY-D): Installation of a Heads-Up Technologies CMS-400A checklist management system.. Sikorsky Aircraft Corporation
- [STC SR02107NY-D](https://openairdocs.org/stc/SR02107NY-D): Installation of a Honeywell JetMap II System.. Sikorsky Aircraft Corporation
- [STC SR02108NY-D](https://openairdocs.org/stc/SR02108NY-D): Installation of an executive VIP interior. Sikorsky Aircraft Corporation
- [STC SR02112NY-D](https://openairdocs.org/stc/SR02112NY-D): Installation of a Main Gear Box Oil Drip Pan modification. Sikorsky Aircraft Corporation
- [STC SR02113NY-D](https://openairdocs.org/stc/SR02113NY-D): Installation of Cockpit Provisional Storage Containers. Sikorsky Aircraft Corporation
- [STC SR02115NY-D](https://openairdocs.org/stc/SR02115NY-D): Installation of External Camera System. Sikorsky Aircraft Corporation
- [STC SR02119NY-D](https://openairdocs.org/stc/SR02119NY-D): Installation of an Utility Lavatory. Sikorsky Aircraft Corporation
- [STC SR02121NY-D](https://openairdocs.org/stc/SR02121NY-D): Installation of a shelves (Station 643 and/or Station 520). Sikorsky Aircraft Corporation
- [STC SR02124NY-D](https://openairdocs.org/stc/SR02124NY-D): Installation of Jettisonable windows (Cabin &/or Emergency Exit). Sikorsky Aircraft Corporation
- [STC SR02125NY-D](https://openairdocs.org/stc/SR02125NY-D): Installation of Cockpit Pressure Refueling Control System. Sikorsky Aircraft Corporation
- [STC SR02126NY-D](https://openairdocs.org/stc/SR02126NY-D): Installation of a SkyTrac Systems ISAT-100 system.. Sikorsky Aircraft Corporation

All 120: https://openairdocs.org/tcds/R00024BO/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.