# TCDS 4H12: Schweizer RSG LLC

- Type: Type certificate data sheet
- Status: Current
- Holder: Schweizer RSG LLC
- Revision: 33
- Revised: April 29, 2020
- Product: Aircraft, Rotorcraft
- Certification basis: Part 21, CAR 6, CAR 8
- Registered aircraft: 457, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/31/9c/319c2ca7a034af362ec2d6129f74843033ce26398b00504170bedcd9adac1af5
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/B669502810A97AE78625855E003BD797.0001
- Page: https://openairdocs.org/tcds/4H12

## Models (6)

As the data sheet lists them.

- 269B
- 269D
- 269A-1
- 269A
- 269C
- 269C-1

## What the data sheet says

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

```text
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
TYPE CERTIFICATE DATA SHEET NO. 4H12 
This data sheet, which is a part of Type Certificate No. 4H12, prescribes conditions and limitations under which the 
product for which the Type Certificate was issued meets the airworthiness requirements of the Civil Air Federal 
Aviation Regulations. 
TC Holder: Schweizer RSG LLC 
3901 N. Main St. 
Fort Worth, TX 76106 
TC Holder Record Sikorsky Aircraft Corporation transferred TC 4H12 to 
Schweizer RSG LLC on January 25, 2018 
Schweizer Aircraft Corporation transferred TC 4H12 to 
Sikorsky Aircraft Corporation on September 26, 2011 
I - Model 269A Helicopter (Normal Category), Approved April 9, 1959 
Engine Lycoming HO-360-B1A, HO-360-B1B, O-360-C2D, HIO-360-B1A or HIO-360-B1B 
Fuel 91/96 Minimum grade aviation gasoline 
Engine Limits HP RPM MP IN HG Altitude Feet 
HO-360-B1A, -B1B 
Max. Continuous 160 2900 26.0 S.L.
Max. Continuous 160 2900 24.8 4000
Takeoff 160 2900 25.0 To 300 above terrain
Max. power rating (5 min.) 180 2900 Full Throttle More than 300 above terrain 
O-360-C2D
Max. Continuous 160 2700 26.0 S.L.
Max. Continuous 160 2700 24.8 4000
Takeoff (5 min.) 165 2900 26.0 S.L.
HIO-360-B1A, -B1B 
Max. Continuous 160 2900 26.2 S.L.
Max. Continuous 160 2900 25.2 3700
Takeoff and Max. power (5 min.) 180 2900 Full Throttle 
Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 
Rev. 33 20 20 20 20 30 31 33 23 26 33 26 29 33 25 28 23 
Page 18 19 20 
Rev. 29 28 32 
4H12 
Revision 33  
Schweizer RSG 
269A 
269A-1 
269B,269C 
269C-1, 269D 
April 29, 2020

4H12 Page 2 of 20 
 
 
 
 
 
Rotor Limits and Engine Operating Speeds 
(With 269B1145, 269B1145-1, 269B1145-25, or 269A1190 
Main Rotor Blades) 
 
Power Off 
(Rotor Tach) 
Max. 530 rpm 
Min. 400 rpm 
 
Power On 
(Engine Tach) 
Max. 2900 rpm 
Min. 2700 rpm 
 
(With other than 269B1145, 269B1145-1, 269B1145-25, or 
269A1190 Main Rotor Blades) 
Max. 530 rpm 
Min. 400 rpm 
Max. 2900 rpm 
Min. 2500 rpm 
 
Airspeed Limits (IAS) Vne (Never Exceed) S.L. 86 mph (75 knots)For reduction of Vne with altitude, RPM, 
and accessories installed - see Rotorcraft Flight Manual. 
 
Altitude Limits Avoid operational areas as shown in the Rotorcraft Flight Manual. 
 
C.G. Range Station (95) to (100) 
(Longitudinal) For limits with accessories installed - see Rotorcraft Flight Manual. 
 
C.G. Range (Lateral) See Loading Instructions in Rotorcraft Flight Manual. 
 
Leveling Means Top of Main Rotor Hub 
 
Maximum Weight S/N --0001 through --0008 1550 lbs. 
S/N --0011 through --0314 1550 lbs. (Max. weight may be increased to 1600 lbs. if all 
the following components are installed): 
 
Component Part Number 
Blade Assembly - Main Rotor 269A1131, 269A1131-1, 269B1145, 269B1145-25 or 
269B1145-1 
Blade Dampers - Main Rotor 269A1222, 269A1927 or 269A1927-3 
Engine Lycoming HO-360-B1A, HO-360-B1B, 
HIO-360-B1A, or HIO-360-B1B 
 
Landing Gear Assembly 269A3240 
 
S/N --0315 and up 1670 lbs.   (See NOTE 1) 
 
No. Seats 2,  Station (84.9) 
 
Maximum Cargo See Loading Instructions to Rotorcraft Flight Manual. 
 
Fuel Capacity 25 gal. Sta. (107) (S/N --0001 through--0314) 
25 gal. or 30 gal.   Sta. (107) (S/N --0315 and subsequent) 
 
Oil Capacity 2 gal. (Sta. 91) 
 
Landing Gear 200 psi front and rear (S/N --0011 and subsequent) 
Oleo Pressure  75 psi front, 150 psi rear (S/N --0001 through 0008)

Page 3 of 20 4H12 
 
 
 
Serial Nos. Eligible  --0001 through --0008,  --0011 and up (See NOTE 6 for Serial Number Coding) Serial 
Numbers --0650 thru --1109 were manufactured under the Delegation Option 
Authorization provisions of FAR 21. 
Serial Numbers --0315 thru --1109 were delivered to the U.S. Army as TH-55A trainers. 
Prior to issuance of FAA Certificate of Airworthiness for these Helicopters, conformance 
with the FAA approved type design data must be established. In addition, all deviations 
listed on the "Conformity Certificate - Military Aircraft" FAA Form 8130-2 or prior FAA 
Form 970 for the particular serial number helicopter must be eliminated and FAA 
approved installations substituted therefore. 
 
The following serial numbered U.S. Army TH-55A Helicopters and their respective data 
plates have been destroyed: 0317, 0318, 0319, 0321, 0332, 0333, 0340, 0351, 0356, 
0389, 0406, 0471, 0472, 0474, 0479, 0480, 0490, 0491, 0492, 0495, 0513, 0515, 0520,  
0541, 0545, 0547, 0552, 0562, 0604, 0648, 0652, 0670, 0671, 0686, 0702  and 0709.  
 
II - Model 269A-1 Helicopter (Normal Category), Approved August 23, 1963 
 
Engine Lycoming HIO-360-B1A or HIO-360-B1B 
 
Fuel 91/96 Minimum grade aviation gasoline 
 
Engine Limits HP RPM  MP IN HG Altitude Feet 
Max. Continuous 160 2900 26.2 S.L. 
Max. Continuous 160 2900 25.2 3700 
Takeoff and Max. power (5 min.) 180 2900 Full Throttle 
 
Rotor Limits and Engine Operating Speeds Power Off(Rotor Tach) Power On (Engine Tach) 
Max. 530 rpm 
Min. 400 rpm 
 
Airspeed Limits (IAS) Vne (Never Exceed) S.L. 86 mph (75 knots) 
Max. 2900 rpm 
Min. 2700 rpm 
For reduction of Vne with altitude, RPM, and accessories installed - see Rotorcraft Flight 
Manual. 
 
Altitude Limits Avoid operational areas as shown in the Rotorcraft Flight Manual. 
 
C.G. Range Station (95) to (100) 
(Longitudinal) For limits with accessories installed - see Rotorcraft Flight Manual. 
 
C.G. Range (Lateral) See Loading Instructions in Rotorcraft Flight Manual. 
 
Leveling Means Top of Main Rotor Hub 
Maximum Weight 1670 lbs.  (See NOTE 1) 
No. Seats 2, Station (84.9) 
Maximum Cargo See Loading Instructions in Rotorcraft Flight Manual 
Fuel Capacity  25 Gal. or 30 gal. Sta. (107) 
Oil Capacity 2 gal. (Sta. 91)

4H12 Page 4 of 20 
 
 
 
Landing Gear 200 psi 
Oleo Pressure 
 
Serial Nos. Eligible --0001 and up (See NOTE 6 for Serial Number coding) 
 
 
III - Model 269A-2 Helicopter (Normal Category), Approved October 10, 1966 
Deleted 15 May 1970 
 
 
IV - Model 269B Helicopter (Normal Category), Approved December 30, 1963 
Model 269B Helicopter (Restricted Category), Approved February 1, 1965 
 
Engine Lycoming HIO-360-A1A 
 
Fuel 100/130 Minimum grade aviation gasoline 
 
Engine Limits HP RPM  MP IN HG Altitude Feet 
Max. Continuous 160 2900 23.5 S.L. 
Max. Continuous 160 2900 22.0 7200 
Takeoff 180 2900 26.1 S.L. 
Max. power rating (5 min.) 180 2900 25.0 3900 
 
 
Rotor Limits and Engine Operating Speeds Power Off (Rotor Tach) Power On (Engine Tach) 
Max. 530 rpm 
Min. 400 rpm 
Max. 2900 rpm 
Min. 2700 rpm 
 
Airspeed Limits (IAS) Normal Category: Vne (Never Exceed) S.L. 87 mph (76 knots) 
Restricted Category: Vne (Never Exceed) S.L. 66 mph (57 knots) 
Maximum sideward speed, 10 mph. 
 
For reduction of Vne with altitude, RPM, and accessories installed - see Rotorcraft Flight 
Manual. 
 
Altitude Limits Avoid operational areas as shown in the Rotorcraft Flight Manual. 
 
C.G. Range Station (95) to (101) 
(Longitudinal) For limits with accessories installed - see Rotorcraft Flight Manual. 
 
C.G. Range (Lateral) See Loading Instructions in Rotorcraft Flight Manual. 
 
Leveling Means Top of Main Rotor Hub 
Maximum Weight 1670 lbs.  (See NOTE 1) 
No. Seats  (Normal Category): 3, (2 at Station 84.9; 1 at Station 78.5) 
(Restricted Category): 1, Station 84.9 Left Side 
 
Maximum Cargo See Loading Instructions in Rotorcraft Flight Manual 
Fuel Capacity  25 Gal. or 30 gal. Sta. (107)

Page 5 of 20 4H12 
 
 
 
Oil Capacity 2 gal. (Sta. 91) 
 
Landing Gear 200 psi 
Oleo Pressure 
 
Serial Nos. Eligible --0001 and up (See NOTE 6 for Serial Number coding) 
Serial Numbers --0236 thru --0457 were manufactured under the Delegation Option 
provisions of FAR 21. 
 
V - Model 269C Helicopter (Normal Category), Approved 15 May 1970 
Model 269C Helicopter (Restricted Category), Approved March 14, 1973 
 
Engine Lycoming HIO-360-D1A   
Fuel 100/130 Minimum grade aviation gasoline 
Engine Limits HP RPM MP IN HG Altitude Feet 
For 1900 lbs. Configuration All Operations: 190 3200 25.6 S.L. 
(Configuration - a or b of RFM) 190 3200 24.1 4850 
For 2050 lbs. Configuration Single RPM 190 3200 26.0 S.L. 
Operations: ( Configuration - c of RFM) 190 3200 24.7 4200 
For Dual Engine RPM Operation 190 3200 26.0 S.L. 
190 3200 24.7 4200 
154 2800-2900 24.5 S.L. 
 
Rotor Limits and Engine Operating Speeds Power Off (Rotor Tach) Power On (Engine Tach) 
Max. 504 rpm 
Min. 390 rpm 
 
 
Airspeed Limits (IAS) Vne (Never Exceed) S.L. 109 mph (95 knots) 
Max. 3200 rpm 
Min. 3000 rpm 
Min. 2800rpm for Dual RPM Operation 
For reduction on Vne with altitude with accessories installed, for dual rpm operation and 
for restricted category operation, see Rotorcraft Flight Manual. 
 
Altitude Limits Avoid operational areas as shown in the Rotorcraft Flight Manual. 
 
C.G. Range Sta. (95.0) to Sta. (101.0) 
(Longitudinal) For limits with accessories installed, see Rotorcraft Flight Manual. 
 
C.G. Range (Lateral) See Loading Instructions in Rotorcraft Flight Manual. 
 
Leveling Means Top Of Main Rotor Hub. 
 
Maximum Weight  For reduction of maximum weight with accessories installed and for dual rpm operation 
see Rotorcraft Flight Manual. 
 
Normal Category: S/N --0004 through --0209 1900 lbs. (See NOTE 1). 
Maximum weight may be increased to 2050 lbs. if Modification M10078 is 
accomplished. 
 
S/N --0210 and up    2050 lbs. (See NOTE 1.)

4H12 Page 6 of 20 
 
 
 
Restricted Category with Agricultural Kit No. 269A4153 and -3: 
S/N --0004 through -0209 1900 lbs. (See NOTE 1.) 
Maximum weight may be increased to 2150 lbs. if Modification M10078 is 
accomplished. 
 
S/N --0210 and up 2150 lbs.  (See NOTE 1.) 
 
The landing gear and support structure S/N --0004 and up are not structurally 
substantiated for operation above 2050 lbs. The cross beams must be inspected 
following landing above 2050 lbs. 
 
No. Seats 3, (2 at Station 83.2; 1 at Station 80.0) 
Maximum Cargo See Loading Instructions and Limitations in Rotorcraft Flight Manual. 
Fuel Capacity 30 gal Sta. (107) 
49 gal with Optional Tank Sta. (107) 
 
SN: 1743, 1744, 1746 thru 1803.  or if modified by incorporation of Kit SA-269K-089 
30.0 gal Sta. (108.5) 
65.2 gal with Optional Tank   Sta. (108.5) 
 
SN: 1804 and Subseq. 
33.0 gal Sta. (108.5) 
66.0 gal with Optional Tank Sta. (108.5) 
 
Oil Capacity 2 gal. Sta. (91) 
 
Landing Gear 269A3240  “Standard” Landing Gear 
Oleo pressure 350 psi front (P/N 269A3150-5,-15,-19) 
560 psi rear (P/N 269A3150-7) 
725 psi rear (P/N 269A3150-9, -17, -21) 
 
269A3260 “Extended Height” Landing Gear 
350 psi front (P/N 269A3150-23) 
560 psi rear  (P/N 269A3150-27) 
 
 
Serial Nos. Eligible  --0004 and up except Serial Number 1246, 1643 and 1660 (See NOTE 6 for Serial 
Number coding). Serial Numbers --0004 thru --0082 were manufactured under the 
Delegation Option provisions of FAR 21. 
 
 
 
Data Pertinent for Models 269A, A-1, B, C 
 
Datum 100 inches forward of main rotor centerline 
 
Other Operating See Rotorcraft Flight Manual.  See NOTE 2 for required placards.  See NOTE 4 for 
Limitations maintenance.

Page 7 of 20 4H12 
 
 
 
Main Rotor Blade (Relative to Rigging Position) 
Movements Collective travel (all models) 12o + 1o (low pitch stop to be established in accordance 
with HMI to obtain proper auto rotation RPM). 
 
Model 269A, 269A-1, 269B 
Cyclic, forward 7.5o to 9.4o 
aft 6.0o to 7.5o 
left 6.5o to 7.5o 
right 5.3o to 6.3o 
Model 269C 
Cyclic,  forward 8.5o to 9.75o 
aft 6.5o to 7.5o 
left 6.5o to 7.5o 
right 4.5o to 6.5o 
Main Rotor Blade Friction Dampers (269A1222, 269A1927, 269A1927-3. 
Damper Setting Torque to move the damper shaft through the low load stage: 200 in-lb. minimum, 230 
in-lb. maximum. 
 
Tail Rotor Blade Models 269A, 269A-1, 269B with 269A6004 or 269A6003 Tail Rotor Assembly +20o 
Collective Pitch +1o (thrust to right); -10o +1o (thrust to left) 
Models 269A, 269A-1, 269B with 269A6034 or 269ASK16 Tail Rotor Assembly + 25o 
+ 1o (thrust to right); -12o + 1o (thrust to left) 
Model 269C with 269A6034-7 Tail Rotor Assembly +26o +1o (thrust to right); -12o +1o 
(thrust to left) 
 
FAA/DOA APPROVED HELICOPTER FLIGHT MANUALS 
 
Model 269A (configuration "a"), CSP-AA-1, dated April 7, 1964, revised 10/30/2003 
Model 269A-1, CSP-AA-2, dated May 13, 1964, revised 10/30/2003 
Model 269A (configuration "b"), CSP-AB-1. dated April 8, 1964, revised 10/30/2003 
Model 269A (configuration "c"), CSP-AC-1, dated July 9, 1964, revised 10/30/2003 
Model 269A (configuration "d"), (U.S. Army TH-55A Primary Trainer), CSP-AD-1, dated 11/5/64, revised 
10/30/2003 
 
Model 269B (configuration "a"), CSP-BA-1, December 30, 1963, revised 10/30/2003 
Model 269B (configuration "b"), CSP-BA-2, February 5, 1968, revised 10/30/2003 
Model 269C, CSP-C-1, dated March 9, 1973, reissued September 21, 1988, revised December 7, 2012 
Service Life Limits See NOTE 3 for list of life limited components.

4H12 Page 8 of 20 
 
 
 
Certification Basis Models 269A, 269A-1, 269B (Normal Category): 
CAR Part 6 dated January 15, 1951, including Amendments 6-1 through 6-7 and 6-8, 
except for CAR 6.604(c). In addition, compliance with CAR 6.401(b) effective May 17, 
1958 and CAR 6.637 effective April 1, 1957 has been required, based on the conditions 
of Director, Bureau of Flight Standards letter dated March 27, 1959, granting extension 
of effectiveness of Application for Type Certificate until July 1, 1959. 
Model 269B (Restricted Category): CAR Part 8 dated October 11, 1950. 
Model 269C (Normal Category): CAR Part 6 dated 15 January 1951, including 
Amendments 6-1 through 6-7 and 6-8, except CAR 6.604(c).  In addition, compliance 
with CAR 6.401(b) effective 17 May 1958, CAR 6.637 effective 1 April 1957 and FAR 
27.1323 of Amendment 27-2 effective 25 February 1968 in lieu of CAR 6.612(a) has 
been required. Model 269C was approved under the Delegation Option Authorization 
Provisions of FAR21. 
Model 269C (Restricted Category): FAR 21.25 dated February 1, 1965. 
Type Certificate 4H12 issued April 9, 1959. 
Date of Application for Type Certificate, January 23, 1956. 
 
Production Basis FAA PC Number 22SW.  
 CAAC PC Number PC0044A-HD. 
  
 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations 
(See Certification Basis) must be installed in the helicopter for certification. All required 
equipment that must be installed as well as optional equipment installations are listed in 
the following Hughes/Schweizer reports: 
 
JW-00-1 "Equipment List, Model 269A Helicopter" 
HTC-63-19 "Equipment List, Model 269A-1 Helicopter" 
269B-X-8001 "Equipment List, Model 269B Helicopter" (including conversation 
instructions for Model 269B CAR Part 6 or Part 8 certification basis). 
 
JX-80-45 "Equipment List, Model 269C Helicopter"  Configuration a. 
JX-80-42 "Equipment List, Model 269C Helicopter"  Configuration b. 
JX-80-43 "Equipment List, Model 269C Helicopter" Configuration c. 
SA-269C-22-4 “Equipment List, Model 269C Helicopter S/N 1796 – Subseq.” 
 
VI - Model 269D Helicopter (Normal Category). Approved September 14, 1992 
See item VI(a) for optional Model 269D Configuration A 
Engine Rolls-Royce 250-C20W  Gas Turbine 
Fuel Grade JP-4 or JP-5 per MIL-T-5624, 
Jet A, A-1, or B per ASTM D-1655, and 
Grade JP-8 per MIL-T-83133. 
 
Refer to Rotorcraft Flight Manual and/or Rolls-Royce Operation and Maintenance 
manual   for limitation and special operating conditions.

Page 9 of 20 4H12 
 
 
Engine Limits  220 HP Maximum Continuous, 57.8 psi Torque, 
738oC maximum TOT. 
Take off: 235 HP 5 min. Limit, 61.7 psi Torque 
810oC maximum TOT. maximum N1 = 105% rpm 
N1 idle speed: 59% to 65% 
100% N1 = 50,970 RPM o o TOT limits: Start up and shut down - 810  C to 927 C for 10 sec 
Installed Power Turbine Limit (91% N2) = 30,294 RPM 
Installed Power Output Shaft Limit  (91% N2) = 5,475 RPM 
Rotor Limits and Normal Operating Range:  466 RPM to 471 RPM  (90% N2 to 91% N2) 
Engine Operating Max. RPM: Power On - 471 RPM (91% N2) 
Speeds Min. RPM: Power On - 466 RPM (90% N2) 
Max. RPM: Power Off - 504 RPM 
Min. RPM: Power Off - 410 RPM 
 
Airspeed Limits Vne (Never Exceed)   Sea Level 108 KIAS Power-On / 94 KIAS during Autorotations 
For reduction of Vne with altitude, see Rotorcraft Flight Manual 
Limits unchanged for any combination of cabin doors on or off 
 
Altitude Limits  Avoid operational areas shown in the Rotorcraft Flight Manual 
Max. Certified Pressure Altitude: - 10,000ft 
- 12,800ft. equip. with 269A1002-11 Main Rotor Inst. 
and 269D7100-3 "ext. height" Landing Gear 
 
C.G. Range 
(Longitudinal) Fwd: 94.1 inches at 2230 lbs varying linearly to 92.0 inches at 1750 pounds and 
below. 
Aft: 96.0 inches at 2230 lbs varying linearly to 101.0 inches at 1750 lbs and below. 
 
(Lateral) Right: Buttline +2.4 inches at 2230 lbs varying linearly to +4.5 inches at 1750 lbs and 
below 
Left: Buttline -0.9 inches at 2230 lbs varying linearly to -3.0 inches at 1750 lbs and 
below 
C.G. Range Equipped with 269A1002-11 Main Rotor Inst. and 269D7100-3 “extended height” 
Landing Gear 
(Longitudinal) Fwd: 94.2 inches at 2260 lbs varying linearly to 92.0 inches at 1800 pounds and 
below. 
Aft: 96.0 inches at 2260 lbs varying linearly to 101.0 inches at 1800 lbs and below. 
(Lateral) Right: Buttline +2.4 inches at 2260 lbs varying linearly to +4.5 inches at 1800 lbs and 
below 
Left: Buttline -0.9 inches at 2260 lbs varying linearly to -3.0 inches at 1800 lbs and 
below 
 
Lateral "+" CG is right of aircraft centerline, "-" is left of aircraft centerline when looking 
forward. 
 
Leveling Means Top of Main Rotor hub 
Datum 100 inches forward of main rotor HUB centerline 
Maximum Weight Normal Category Operations - 2230 lbs 
- 2260 lbs equip. with 269A1002-11 Main Rotor Inst. 
and 269D7100-3 "ext. height" Landing Gear 
 
No. of Seats 3 Place Configuration (2 at Station 68.6, 1 at Station 78.6) 
4 Place Configuration (2 at Station 68.6, 2 at Station 78.6)

4H12 Page 10 of 20 
 
 
 
 
Controls Solo flight & P.I.C. - Refer to rotorcraft flight manual. 
Refer to Rotorcraft Flight Manual when three sets of controls are installed. 
 
Max. Cargo Stowage Area Behind R/H Seat sta. 84.0 - Limited to 50 lbs 
Stowage Area Behind L/H Seat sta. 84.0 - Limited to 50 lbs 
Optional Remote Baggage Compartment sta. 125.0 - Limited to 60 lbs 
 
Fuel Capacity  Standard Capacity - 60.8 U.S. Gallons (Station 104.20), (60.0 Gal usable) 
Unusable Fuel - 0.8 U.S. Gallons 
 
Extended Range Capacity - 74.1 U.S. Gallons (Station 104.20), (73.0 Gal usable) 
Unusable Fuel - 1.1 U.S. Gallons 
Engine Oil Capacity 4.5 Quarts (Oil Tank Capacity 3.0 Quarts) (Station 114.40) 
Engine Oil Type MIL-L-7808 (reference Roll-Royce  Maintenance Manual 10W2) 
MIL-L-23699 
Engine Oil Limitations Continuous operating range 0oC to 107oC 
Oil Pressure 50 - 130 psi with following minimums: 
90 psi at or above 79% N1 
50 psi below 79% N1 
Landing Gear 269A3240-9 Landing Gear 
Oleo Pressure 350 psi Front (P/N 269A3150-15, -19) 
725 psi Rear (P/N 269A3150-9, -17, -21) 
 
269D7100-3 “extended height” Landing Gear 
350 psi Front (P/N 269A3150-23) 
725 psi Rear  (P/N 269A3150-25) 
 
Starter/Generator 150 amps maximum continuous operation. 
Limits Consecutive Cranking Limits: 
60 seconds - ON   60 seconds - OFF 30 
seconds - ON   60 seconds -  OFF 30 
seconds - ON      30 minutes - OFF 
 
Operating Limitations If configured with external screened engine plenum inlet, Alternate Air must  be selected 
for all operations in visible moisture at temperatures at or below 5oC. 
After alternate air door is selected for operation in visible moisture at or below 5 oC, the 
door must remain open until after landing and the primary air inlet and the forward and 
aft bulkheads located at the rear station of the engine bellmouth are inspected and cleared 
of ice accumulation. 
 
Flight into known icing is prohibited. 
Instrument flight is prohibited. 
Refer to Rotorcraft Flight Manual for solo requirements.

Page 11 of 20 4H12 
 
 
 
 
Other Operating See Rotorcraft Flight Manual. See Note 2 for required placards.  See Note 4 for 
Limitations maintenance information. 
 
Serial Numbers Eligible  - 0001 and subsequent except Serial No. 0007, 0013, 0011, 0017, 0030 and all serial 
numbers containing the suffix “M” or “MB” (See note 11). 
 
 
Main Rotor Blade Collective Pitch: 
Movement Full Travel 12o +/- 1o 
At Down Stop 0.75 R, 2.5o +/- 1.5o (low pitch stop to be established in accordance with 
HMI to obtain proper auto rotation RPM). 
Cyclic, forward 8.5o to 9.5o 
aft 9.5o to 10.0o 
left 6.5o to 7.5o 
right 6.0o to 7.0o 
Tail Rotor Blade Established at 3/4 radius, 
Collective Pitch Right Pedal (thrust to left)  11o to 13o 
Left Pedal (thrust to right)  27o to 29o 
Service Life Limits See Note 8 for life limited Components 
 
Certification Basis The certification basis for the Model 269D includes that of the 269C CAR Part  6, dated 
January 15, 1951, including Amendment 6-1 through 6-7, and 6-8 except CAR 6.604(c). 
Compliance with CAR 6.401(b) effective 17 May 1958, CAR 6.637 effective 1 April  
1957 and FAR 27.1323 Amendment 27-2 effective 25 February 1968 in lieu of CAR 
6.612(a) has been shown. Applicable FAR requirements covering the turbine engine 
installation per FAR 27 thru Amendments 27-21 in effect at time of application 
(November 3, 1987) and noise standards per FAR 36 at time of certification are:  
 
FAR 21.35(b)(2) ; 27.73(a)(2)(ii); 27.361(a); 27.395; 27.397; 27.399; 27.671;  
27.901(b)(4)(c); 27.903(c); 27.907; 27.931; 27.939; 27.951(c); 27.955; 27.959; 27.961;  
27.963; 27.965; 27.969; 27.971; 27.973; 27.975; 27.977(a)(2)(b)(c)(d); 27.993; 27.995;  
27.997; 27.999; 27.1013(c); 27.1015; 27.1019; 27.1091(d)(e); 27.1093(b); 27.1121;  
27.1141(d); 27.1143(d); 27.1145(b); 27.1191(a); 27.1194; 27.1195; 27.1305(f)(g)(n  
thru s); 27.1323; 27.1353(f)(g); 27.1461; 27.1521(b)(5), (c)(3)(d thru f); 27.1529;  
27.1557(c)(i)(iii); 27.1583(b)(1); FAR 36 Appendix J, Amendment 20. 
 
Production Basis PC Number 22SW.  
 
Equipment The required equipment as prescribed in the applicable airworthiness regulations (see 
Certification Basis) must be installed in the helicopter for certification. All required 
equipment that must be installed as well as optional equipment installations are listed in 
Schweizer Report No. SA-269D-22-2. 
 
FAA APPROVED HELICOPTER FLIGHT MANUAL 
CSP-D-1 (60 gallon fuel system) 
Model 269D, dated September 14, 1992.  Reissued July 28, 1993. 
Revision August 26, 2010. 
 
CSP-D-7 (73 gallon fuel system) 
Model 269D, dated November 16, 1993.  Revision August 26, 2010.

4H12 Page 12 of 20 
 
 
 
VI (a) - Model 269D Configuration A Helicopter (Normal Category). Approved September 28,  2000 
data same as for standard configuration (item VI) except as shown 
Engine Limits 232 HP Maximum Continuous, 62.2 psi Torque, 738oC maximum TOT. 
Take off: 253 HP 5 min. Limit, 67.6 psi Torque  (280 HP 5 min. Limit, 74.9 psi Torque 
for S/N 0043-A, 0045-A & Subs. and any other aircraft retrofitted by the SA-269DK-027 
Kit),  810oC maximum TOT. 
Transient Over Torque: 263 HP 15 sec. Limit, 70.3 psi Torque (290 HP 15 sec. Limit,  
77.6 psi Torque for S/N 0043-A, 0045-A & Subs. and any other aircraft retrofitted by the 
SA-269DK-027 Kit), 810oC maximum TOT. 
Maximum N1 = 105% rpm 
N1 idle speed: 59% to 65% 
100% N1 = 50,970 RPM o o TOT limits: Start up and shut down - 810  C to 927 C for 10 sec 
Installed Power Turbine Limit (90% N2) = 29,961 RPM 
Installed Power Output Shaft Limit  (90% N2) = 5,414 RPM 
Rotor Limits and Normal Operating Range:  466 RPM to 471 RPM  (89% N2 to 90% N2) 
Engine Operating Max. RPM: Power On - 471 RPM (90% N2) 
Speeds Min. RPM: Power On - 466 RPM (89% N2) 
Max. RPM: Power Off - 500 RPM 
Min. RPM: Power Off - 410 RPM 
 
Airspeed Limits Vne (Never Exceed)   Sea Level: 
110 kias Power-On (2301-2550 lbs G.W.) 
120 kias Power-On (2300 lbs and below) 
94 kias during Autorotations 
110 kias Doors-Off Operation (any combination cabin door(s) off) 
For reduction of Vne with altitude, see Rotorcraft Flight Manual 
Altitude Limits Avoid operational areas shown in the Rotorcraft Flight Manual 
Max. Certified Pressure Altitude: - 13,000 ft 
 
C.G. Range 
(Longitudinal) Fwd: 94.0 inches at 2550 lbs varying linearly to 92.0 inches at 2000 lbs and 
below. 
Aft: 96.0 inches at 2550 lbs varying linearly to 101.0 inches at 2000 lbs and below. 
 
(Lateral) Right: Buttline +2.0 inches at 2550 lbs varying linearly to +4.0 inches at 2000 lbs and 
below 
Left:  Buttline –1.0 inches at 2550 lbs varying linearly to -3.0 inches at 2000 lbs and 
below 
 
Lateral "+" CG is right of aircraft centerline, "-" is left of aircraft centerline when 
looking  forward. 
 
Maximum Weight Normal Category Operations - 2550 lbs 
Take-Off and Landing above 4,000 ft density altitude limited to 2,500 lbs or less  
 
Landing Gear  350 psi Front (P/N 269A3150-23) 
725 psi Rear  (P/N 269A3150-25) 
 
Serial Numbers Eligible Optional configuration for production helicopters SN 0026 and subsequent and for  all

Page 13 of 20 4H12 
 
 
 
other helicopters incorporating Retrofit Kit no. SA-269D-K-20. Production 
Configuration A helicopters have “-A” at the end of S/N. Retrofit Configuration A 
helicopters have no “-A” at the end of S/N. Both production and retrofit helicopters 
have  an additional “Configuration A” Data Plate affixed next to standard data plate.  
 
Certification Basis The certification basis for the Model 269D Configuration A is the same as the Model 
269D along with the following FAR 27 compliance upgrades as of January 1, 1999: 
 
FAR 27.337; 27.339; 27.341; 27.547; 27.923 and 27.927. 
 
Tail Rotor Blade Established at 3/4 radius, 
Collective Pitch Right Pedal (thrust to left)  11o to 13o 
Left Pedal (thrust to right)  28o to 29o 
FAA APPROVED HELICOPTER FLIGHT MANUAL 
CSP-D-8 Model 269D Configuration A, dated September 28, 2000, Revised 
August 26, 2010. 
 
VII - Model 269C-1 Helicopter (Normal Category)  Approved July 31, 1995 
 
Engine Textron Lycoming HO-360-C1A, FAA Type Certificate E-286. 
Textron Lycoming HIO-360-G1A, FAA Type Certificate 1E10. 
 
Fuel  Grade 100/130 (green) or 115/145 (purple) or 100LL (blue), MIL-F-5572; Minimum 
grade aviation gasoline. 
 
Engine Limits HP RPM MP IN HG Altitude Feet 
 
 
Rotor Limits and Engine 
Max. Continuous 180 2700 Full Throttle S.L. 
Operating Speeds Power Off (Rotor Tach) Power On (Engine Tach) 
Max. 504 rpm Max. 2700 rpm 
Min. 390 rpm Min. 2534 rpm 
 
Airspeed Limits Vne(Never Exceed); S.L. 94 knots (108 mph) 
Vne with Doors-Off; 90 knots (104 mph) 
For reduction of Vne with altitude see Rotorcraft Flight Manual 
 
Altitude Limits Takeoff/Landing - 8,000 ft density altitude 
Enroute - 10,000 ft density altitude 
 
C.G. Range Station (95.0) to Station (101.0) 
(Longitudinal) 
 
C.G. Range (Lateral) See Loading instructions in Rotorcraft Flight Manual 
Leveling Means Top of Main Rotor Hub 
 
Datum 100 inches forward of Main Rotor centerline 
 
Maximum Weight 1750 lbs 
 
No. Seats 2,  (2 at station 83.2) Right Hand PIC 
3,  (2 at station 83.2, 1 at station 80.0) Left Hand PIC 
Maximum Cargo See Loading Instructions and Limitations in Rotorcraft Flight Manual. 
Fuel Capacity S/N 0001 thru 0105 
Standard 
Total Capacity 35.2 U.S. gallons, station 108.5

4H12 Page 14 of 20 
 
 
Usable Capacity 35.0 U.S. gallons, station 108.5 
Standard + Auxiliary (optional) 
Total Capacity 65.2 U.S. gallons, station 108.5 
Usable Capacity 63.0 U.S. gallons, station 108.5 
S/N 0106 and Subsequent 
Standard 
Total Capacity 33.0 U.S. gallons, station 108.5 
Usable Capacity 32.5 U.S. gallons, station 108.5 
Standard + Auxiliary (optional) 
Total Capacity 66.0 U.S. gallons, station 108.5 
Usable Capacity 64.0 U.S. gallons, station 108.5 
 
Oil Capacity 2.0 gallons, station 91 
 
Landing Gear 350 psi front (P/N 269A3150-19) 
Oleo Pressure 725 psi rear (P/N 269A3150-21) 
Serial Nos. Eligible - 0001 and subsequent except Serial Nos. -0002, 0013, and -0255 
Main Rotor Blade (Relative to rigging position) 
Movements Collective Travel 12° ± 1° (low pitch stop to be established in accordance with HMI to 
obtain proper auto rotation RPM). 
 
Cyclic,  forward 8.5o to 9.75o 
aft 6.5o to 7.5o 
left 6.5o to 7.5o 
right 4.5o to 6.5o 
Tail Rotor Blade +26° ± 1° (thrust to right); -12° ± 1° (thrust to left) 
Service Life Limits See Note 9. 
Certification Basis (Normal Category): CAR Part 6 dated 15 January 1951, including Amendments 6-1 
through 6-7 and 6-8, except CAR 6.604(c). In addition, compliance with CAR 6.401(b) 
effective 17 May 1958, CAR 6.637 effective 1 April 1957, FAR 27.1323 of Amendment 
27-2 effective 25 February 1968 in lieu of CAR 6.612(a), and noise standards per FAR 
Part 36 Appendix J, Amendment 20 has been shown. 
 
Other Operating See Rotorcraft Flight Manual.  See NOTE 2 for required placards.  See NOTE 4 for 
Limitations maintenance. 
 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations 
(See Certification Basis) must be installed in the helicopter for certification. All required 
equipment that must be installed as well as optional equipment installations are listed in 
the Schweizer Report SA-269C-22-5. 
 
Production Basis PC Number 22SW.  
 
FAA APPROVED HELICOPTER FLIGHT MANUAL 
CSP-C1-1 
Model 269C-1, dated July 31, 1995, revised 12/11/09.

Page 15 of 20 4H12 
 
 
 
Note: Applicable To All Models Except When Specifically Indicated 
 
NOTE 1.  Current weight and balance report, including list of equipment including certificated empty  weight and 
loading instructions, must be provided for each helicopter at the time of original airworthiness 
certification and at all times thereafter (except in the case of operators having an appropriate weight 
control system). Ballast, when necessary, must  be carried in accordance with the loading instructions 
in the Rotorcraft Flight Manual. 
 
NOTE 2. The following placard must be installed in clear view of the pilot: 
 
"This Helicopter must be operated in compliance with the operating limitations 
specified in the pertinent Rotorcraft Flight Manual." 
 
For additional placards, see the pertinent Rotorcraft Flight Manual. 
 
NOTE 3. (a) The retirement times of critical parts are listed in the following table. These values  of retirement 
or service life cannot be increased without approval by FAA Engineering. (See NOTE 8 for Model 
269D & Note 9 for Model 269C-1)): 
 
  
 
Model 269A 
Model 269A 
S/N 0011 
& Subs. 
Models269A-1 
 
 
Model 269C 
 
 
Description 
 
 
Part Number 
S/N 0001 
thru 0008 
Hours 
& 269B S/N 
0001 & Subs. 
Hours 
S/N 0004 
& Subs. 
Hours 
Blade Assembly - M/R 269-1100 
269A1125 
1366  
1366 
 
 269A1131 1366 1366  
 269A1131-1 
269A1160 
1366 1366  
5500 
 269A1185-1,-7   5500 
 269A1185-9 
269A1190 
  
5500 
3050 
 269A1190-1  5500  
 269B1145  1366  
 269B1145-1  1366  
 269B1145-25  1366  
Pitch Brg. Shaft - M/R 269A1240-7   3600 
Dampers-Elastomeric - M/R See Note 3(e) 269A1290-1, –3  6000 6000

4H12 Page 16 of 20 
 
 
 
 
Mast - M/R 269-2165 
269A2010-5, -15 
1900   
13590 
 
Thrust Bearing - M/R 
 
269A5050-73 
  
3000 
 
 269A5050-63, -95   3000 
 269A5050-50, -51 300 300  
Tail Boom Assy (when 269ASK16 or 269A2320 with  17370  
269A6034 T/R is installed) 269A2324 –13,  -11    
 center attach fitting    
 installed    
 269A2320 with  4100  
 269A2324 Basic,  -7    
 center attach fitting    
 installed    
Tail Boom Assy 269A2320-7 with   2100 
 269A2324-11 center    
 attach fitting installed    
 269A2320-7 with   500 
 269A2324-7 center    
 attach fitting installed    
 269A2320-9  17370  
 269A2320-11   2100 
 269A2320-17,-21   4200 
 269A2320-19   2100 
Tail Boom Struts (see note 3F ) 269A2015-5   500 
 269A2015-11, -13, -15,   10700 
 -17, -113, -213, -215    
Stab. Assy - Vert. 269A2419-3   20540 
Stab. Assy - Horiz. 269-2500 2500   
 269A2511  2500  
(when 269A2516 zero time Stab. is 269A2516  2500  
installed with 269ASK16 or     
269A6034 T/R)     
 269A2516  3070  
 269A2516-9   2500 
 269A2516-21   4200 
Main Gear Box Pinion Assy 269-5103 2250   
 269A5103  6000 6000 
 269A5103-9  6000 6000 
 269A5103-21  6000 6000 
 269A5103-31, -41, -51,  6000 6000 
 -55    
Main Rotor Drive Shaft 269-5301 1195   
 269A5305-3, -103  3000  
 269A5305-11, -111   1900 
Main Rotor Drive Shaft (splined) 269A5326-1, -5   3200 
Main Rotor Hub (splined) 269A5325-1   8000 
Carrier Assembly-Ring Gear, see item 3h 269A5194 6000 6000 6000 
Lower Pulley Coupling Shaft 269-5412 1500   
Lower Pulley Coupling Shaft 269A5504-3  1500 1500 
(269A5504-5 Assy)     
Lower Pulley Coupling Shaft 269A5559-3  6000 6000 
(269A5559 Assy)

Page 17 of 20 4H12 
 
 
 
Idler Pulley Bearings 269A5050-58 
269A5050-62 
 200  
600 
Shaft - Input T/R GB 269-5609 1800   
 269A5609  3000  
See NOTE 3(d) 369A5406  UNLIM. 8600 
See NOTE 3(d) 369A5425,  -3,  -5  UNLIM. 8600 
 269A5626-3,  -5   8600 
Drive Spline - Aft End 269-5607 1800   
T/R Drive Shaft 269A5607  3000  
Shaft Assy - T/R Drive 269-5701 3000   
(includes end fittings) 269A5701,  -3  3000  
Shaft Assy - T/R Drive 269A6040,-BSC M  3000  
 269A6040-5, -5M  3000  
 269A6040-7,-9, -9M   6000 
 269ASK09  3000  
Spline Adapter Fitting 269ASK04  20000  
Blade Assy - T/R 269A6035,  -17,  -21  5000  
 269A6035M  5000  
 269ASK15  5000  
 269A6035-9, -19, -23   9000 
 269-6100 960   
 269A6124  960  
 269A6124-9  960  
Retention Straps - T/R 369A1706  2800 3540 
 269A6065  2800 3540 
 269A6065-507  2800 5100 
 369A1706-505,  -507  2800 5100 
Torsion Shaft - T/R Blade (Note 7) 269-6108 1200   
 269A6108  1200  
 269A6219  1200  
Hub - T/R 269-6204 960   
 269A6221  960  
 269A6247  960  
Bellcrank - Lat. Pitch 269-7506 900   
Idler Mixer 269A7506  900  
 
NOTE 3.  (b)  It is prohibited to interchange life limited components between different series of helicopters (i.e. 
369/269). Components which have been interchanged between series of helicopters prior to revision 
19 of this TCDS may continue in service to their respective retirement lives. Life limited components 
interchanged between Models, configurations, or previously between series must be restricted to the 
lowest service life indicated for the Models or configurations affected. Parts are applicable only on 
Models under which a service life is listed. Interchanged components with known service hours but 
without Model application identification may not exceed the lowest life listed for any applicable 
Model. If the service hours are not known, regardless of Model application, the component cannot be 
interchanged to Models that list the component as limited life. 
 
(c) Life limited components removed when life limit has been reached must be destroyed or 
permanently marked to prevent return to service. 
 
(d) Input Gearshaft assy. T/R, P/N 369A5406 (Input Only), 369A5425 and 369A5425- 3 having 
accumulated any Military (OH-6A Model 369A) time in service must be limited to a total service life 
of 530 hours.

4H12 Page 18 of 20 
 
 
 
(e) (Elastomeric Dampers) Mandatory inspection required in accordance with the 269 Series 
"Helicopter Maintenance Instruction" (HMI) requirements at 600-hour intervals for operation up to 
4200 hours and at 300-hour intervals thereafter to a total damper operational service time of 6000 
hours. For Models 269A, 269A-1 and 269B Main Rotor Elastomeric Dampers P/N 269A1290 can 
only be used with Main Rotor Blades P/N 269A1190-1. 
 
(f) AD 76-18-01 required modifying 269A2015-5 to 269A2015-11 configuration within 500 hours or 
by September 7, 1977 in any case. 
 
(g) Alpha and/or numeric suffixes added to part numbers denote special manufacturing or handling 
procedures and do not alter the replacement requirements of the part. For example, 269A5305- 11 and 
269A5305-11M2 are subject to the same requirements. 
 
(h) 269A5193 Carrier is part of 269A5194 Carrier Assembly 
 
NOTE 4. Information essential to the proper maintenance of these helicopters is contained in the Manufacturer's 
Handbook of Maintenance Instructions, which is provided with each helicopter. 
 
NOTE 5. Deleted. 
 
NOTE 6. Aircraft serial numbers are coded to show the month and year of manufacture sequence. 
 
EXAMPLES:  640103, 1150015 
6 4 0103 
11 5 0015 
Serial number in consecutive 
order from 0001 for each model 
Year of 
Manufacture 
4 - 1964 
5 - 1965 
Month of Manufacture 6  - June 
11 - November 
 
Model 269C Helicopters, S/N 1065, S/N 1075 and subsequent will be delivered without the manufacturing date 
coding as part of the serial number.  Serial numbers are prefixed by the letter "S" starting with S/N S1166 and up. 
Aircraft produced under FAA PC Number 22SW will have serial numbers with prefixed letter “S.”  Aircraft 
produced under CAAC PC Number 0044A-HD will have serial numbers with prefixed “CS.” 
 
NOTE 7. The limited service life for all P/N 369A1706 or 269A6065 tension torsion strap assemblies used on any 
269A Configuration d (TH-55A) series helicopter, while the helicopter was operated by the U.S. 
Army, is reduced to 1531 hours as defined in Schweizer Service Information Notice No.N -214. All 
such parts in service or spares inventory, which have exceeded 1531 hours total time in service, must 
be removed and scrapped. 
 
The TH-55A is a military helicopter with no civil counterpart. For conversion to the Model 269A, 
contact the manufacturer. 
 
NOTE 8 (a)  The retirement times of critical parts for Model 269D are listed in the Handbook of Maintenance 
Instructions, Appendix B, CSP-D-4, Airworthiness Limitations Section, dated 
March 11, 2010. These values of retirement or service life cannot be increased without approval by 
FAA Engineering. 
 
(b)  The retirement times of critical parts for Model 269D Configuration “A” are listed in the 
Handbook of Maintenance Instructions, Appendix B, CSP-D-11, Airworthiness Limitations Section, 
dated March 11, 2010. These values of retirement or service life cannot be increased without approval 
by FAA Engineering.

Page 19 of 20 4H12 
 
 
 
(d) It is prohibited to interchange life limited components between different series of helicopters (i.e. 
369/269). Components which have been interchanged between series of helicopters prior to revision 
19 of this TCDS may continue in service to their respective retirement lives. Life limited components 
interchanged between Models, configurations, or previously between series must be restricted to the 
lowest service life indicated for the Models or configurations affected. Parts are applicable only on 
Models under which a service life is listed. Interchanged components with known service hours but 
without Model application identification may not exceed the lowest life listed for any applicable 
Model. If the service hours are not known, regardless of Model application, the component cannot be 
interchanged to Models that list the component as limited life. 
 
(e) Life limited components removed when life limit has been reached must be destroyed or 
permanently marked to prevent return to service. 
 
(f) Alpha and/or numeric suffixes added to part numbers denote special manufacturing or handling 
procedures and do not alter the replacement requirements of the part. For example, 269A5305- 11 and 
269A5305-11M2 are subject to the same requirements. 
 
NOTE 9.  (a)  The retirement times of critical parts for Model 269C-1 are listed in the following table. These 
values of retirement or service life cannot be increased without approval by FAA  Engineering. 
 
 
(b) 
Description 
 
Part Number 
S/N 0001 & Subq 
Hours 
Main Rotor Blade 269A1185-1,-7 5,500 
 269A1185-9 3,050 
Pitch Bearing Shaft 269A1240-7 4,000 
Elastometic Dampers 269A1290-3 6,000 
M/R Input Pinion 269A5103-51, -55 8,000 
M/R Drive Shaft (bolted) 269A5305-111 2,000 
M/R Drive Shaft (splined) 269A5326-1 4,000 
M/R Hub (splined) 269A5325-1 8,000 
T/R Drive Shaft 269A6040-7,-9,-9M 6,000 
Shaft-Input T/R GB 269A5626-5 8,600 
T/R Blade 269A6035-23 9,000 
T/R T-T Straps 269A6065-507 5,100 
Main Rotor Mast 269A2010-5, -15 13,590 
Tail Boom Assy. 269A2320-13 2,100 
 269A2320-15 4,200 
Tail Boom Strut 269A2015-11,-13, 10,700 
 
Horizontal Stab. 
-15,-17,-113,-213,-215 
269A2516-21 
 
4,200 
Lower Pulley Coupling Shaft 269A5559-3 6,000 
Thrust Bearing-M/R 269A5050-63, -95 4,200 
Carrier Assy-Ring Gear  see item 9(h) 269A5194 8,000 
 
(c) It is prohibited to interchange life limited components between different series of helicopters (i.e. 
369/269). Components which have been interchanged between series of helicopters prior to revision 
19 of this TCDS may continue in service to their respective retirement lives. Life limited components 
interchanged between Models, configurations, or previously between series must be restricted to the 
lowest service life indicated for the Models or configurations affected. Parts are applicable only on 
Models under which a service life is listed. Interchanged components with known service hours but 
without Model application identification may not exceed the lowest life listed for any applicable 
Model. If the service hours are not known, regardless of Model application, the component cannot be 
interchanged to Models that list the component as limited life.

4H12 Page 20 of 20 
 
 
 
(d) Life limited components removed when life limit has been reached must be destroyed or 
permanently marked to prevent return to service. 
 
(e) The 269A2402 Vertical Stabilizer is part of the 269A2320-13 Tail Boom Assembly. The Vertical 
Stabilizer has the same service life (2,100 hours) as does the Tail Boom and therefore the vertical 
stabilizer shall be retired with the Tail Boom Assembly. 
 
(f) Some Parts may appear to be interchangeable between the Model 269C-1 and other 269 series 
helicopters. However due to differences in maintenance schedules, only the most current dash 
numbers as defined in Note 9(b) are applicable for installation on the Model  269C-1. 
 
(g) Alpha and/or numeric suffixes added to part numbers denote special manufacturing or handling 
procedures and do not alter the replacement requirements of the part. For example, 269A5305- 11 and 
269A5305-11M2 are subject to the same requirements. 
 
(h) 269A5193 Carrier is part of 269A5194 Carrier Assembly. 
 
NOTE 10. Noise Substantiation: 
 
Although not part of the Certification Basis, the Model 269C Helicopter is compliant with the 
requirements of FAR Part 36 Appendix J, Amendment 20. 
 
NOTE 11. Model 269D, Configuration M or MB: 
 
Helicopter serial numbers containing the suffix “M” or “MB” that have been delivered to a foreign 
customer as Model 269D, Configuration M or MB (military) helicopters. These aircraft  are not eligible 
for issuance of an FAA Certificate of Airworthiness. Life limited components flown on Configuration 
M or MB aircraft are not eligible for installation on 269D, Configuration A or 269D helicopters.  
 
 
 
 
…..END…..
```

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- [AD 78-26-04](https://openairdocs.org/ad/78-26-04): Tail Rotor Hub Assembly · Schweizer 269A, 269A-1, 269B and 6 more. Effective Dec 27, 1978
- [AD 78-25-04](https://openairdocs.org/ad/78-25-04): Pinion Assemblies · Schweizer 269A, 269A-1, 269B and 1 more. Effective Dec 18, 1978
- [AD 78-02-02](https://openairdocs.org/ad/78-02-02): Tail Rotor Control Pedals · Schweizer 269A, 269A-1, 269B and 1 more. Effective Jan 24, 1978
- [AD 77-23-08](https://openairdocs.org/ad/77-23-08): Cracks in Main Rotor Blades · Schweizer 269A, 269A-1 and 269B. Effective Dec 27, 1977
- [AD 77-07-01](https://openairdocs.org/ad/77-07-01): Clutch Actuator · Schweizer 269A, 269A-1, 269B and 1 more. Effective Apr 4, 1977
- [AD 76-10-02](https://openairdocs.org/ad/76-10-02): Lateral control · Schweizer 269A, 269A-1, 269B and 1 more. Effective May 21, 1976
- [AD 75-15-02](https://openairdocs.org/ad/75-15-02): Throttle and Engine Power Control · Schweizer 269A, 269A-1 and 269B. Effective Jul 15, 1975
- [AD 74-21-04](https://openairdocs.org/ad/74-21-04): Canopy Slats · Schweizer 269A, 269A-1, 269B and 1 more. Effective Apr 4, 1975
- [AD 75-08-12](https://openairdocs.org/ad/75-08-12): Actuator and Cover · Schweizer 269A, 269A-1, 269B and 1 more. Effective Mar 7, 1975
- [AD 73-11-01](https://openairdocs.org/ad/73-11-01): Idler Pulley Bearing Failure · Schweizer 269C. Effective May 21, 1973
- [AD 71-20-05](https://openairdocs.org/ad/71-20-05): Idler Pulley Bearings · Schweizer 269A, 269A-1 and 269B. Effective Dec 18, 1971
- [AD 70-08-01](https://openairdocs.org/ad/70-08-01): Flapping Hinge Bolts · Schweizer 269A, 269A-1 and 269B. Effective Apr 14, 1970
- [AD 70-01-06](https://openairdocs.org/ad/70-01-06): Lateral pitch idler bell crank · Schweizer 269A, 269A-1 and 269B. Effective Jan 17, 1970
- [AD 69-04-03](https://openairdocs.org/ad/69-04-03): Rotor Blade · Schweizer 269A, 269A-1 and 269B. Effective Mar 22, 1969
- [AD 68-26-01](https://openairdocs.org/ad/68-26-01): Lower Coupling Drive Shaft · Schweizer 269A, 269A-1 and 269B. Effective Dec 21, 1968

All 67: https://openairdocs.org/tcds/4H12/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Schweizer 269C](https://openairdocs.org/model/schweizer-269c): 115 aircraft (registry code 8059502)
- [Hughes 269A](https://openairdocs.org/model/hughes-269a): 97 aircraft (registry code 4470402)
- [Schweizer 269C-1](https://openairdocs.org/model/schweizer-269c-1): 84 aircraft (registry code 8059504)
- [Hughes 269C](https://openairdocs.org/model/hughes-269c): 74 aircraft (registry code 4470504)
- [Hughes 269B](https://openairdocs.org/model/hughes-269b): 31 aircraft (registry code 4470502)
- [Hughes TH-55](https://openairdocs.org/model/hughes-th-55): 13 aircraft (registry code 4471002)
- [Schweizer 269D](https://openairdocs.org/model/schweizer-269d): 12 aircraft (registry code 8059501)
- [Hughes TH-55A](https://openairdocs.org/model/hughes-th-55a): 7 aircraft (registry code 4471004)
- [Schweizer TH55A/269A](https://openairdocs.org/model/schweizer-th55a-269a): 6 aircraft (registry code 8059503)
- [Hughes 269A-1](https://openairdocs.org/model/hughes-269a-1): 5 aircraft (registry code 4470404)
- [Schweizer HUGHES 269C](https://openairdocs.org/model/schweizer-hughes-269c): 4 aircraft (registry code 8059500)
- [Schweizer RSG 269C](https://openairdocs.org/model/schweizer-rsg-269c): 3 aircraft (registry code 8059498)
- [Schweizer 300C](https://openairdocs.org/model/schweizer-300c): 2 aircraft (registry code 8059320)
- [Schweizer RSG 269C-1](https://openairdocs.org/model/schweizer-rsg-269c-1): 2 aircraft (registry code 8059499)
- [Schweizer 269A](https://openairdocs.org/model/schweizer-269a): 1 aircraft (registry code 8059506)
- [Schweizer Aircraft Co USA SCHWEIZER 300C/269C](https://openairdocs.org/model/schweizer-aircraft-co-usa-schweizer-300c-269c): 1 aircraft (registry code 8059507)
- [Hughes 269A (TH55)](https://openairdocs.org/model/hughes-269a-th55): 0 aircraft (registry code 4470405)
- [Hughes-Filipoff 269A](https://openairdocs.org/model/hughes-filipoff-269a): 0 aircraft (registry code 4470403)
- [Schweizer 300CB](https://openairdocs.org/model/schweizer-300cb): 0 aircraft (registry code 8059321)
- [Sikorsky 269C](https://openairdocs.org/model/sikorsky-269c): 0 aircraft (registry code 8140301)
- [Sikorsky 269D](https://openairdocs.org/model/sikorsky-269d): 0 aircraft (registry code 8143022)

## STCs approved under this data sheet (134, first 50)

- [STC SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position  Light System, and applicable associated power supplies. Whelen Aerospace Technologies
- [STC SR00210SE](https://openairdocs.org/stc/SR00210SE): Installation of an Isolair Model 3900-300 agricultural spray tank system. (269D Restricted Category ONLY). Isolair Inc.
- [STC SR00004DE](https://openairdocs.org/stc/SR00004DE): Installation of an SX-5 searchlight.. Dart Aerospace Company
- [STC SR00006DE](https://openairdocs.org/stc/SR00006DE): Installation of Inframetics IRTV-445G infrared imaging system.. Dart Aerospace Company
- [STC SR00152DE](https://openairdocs.org/stc/SR00152DE): Installation of a FLI-MAP (fast laser imaging - mapping airborne platform) terrain mapping equipment system using an organic tissue eye-safe laser beam. (269C S/N 1704 only). Dart Aerospace Company
- [STC SR00364DE](https://openairdocs.org/stc/SR00364DE): Installation of Video Tracker System.. Dart Aerospace Company
- [STC SR00581DE](https://openairdocs.org/stc/SR00581DE): Installation of Light Detection and Ranging (LIDAR).. Dart Aerospace Company
- [STC SH2726NM](https://openairdocs.org/stc/SH2726NM): Installation of a cabin heater.. Dart Aerospace USA Inc.
- [STC SH5248NM](https://openairdocs.org/stc/SH5248NM): Installation of external pod, camera mount, and 12 volt power provision.. Dart Aerospace USA Inc.
- [STC SH4036NM](https://openairdocs.org/stc/SH4036NM): Installation of door actuators.. Dart Aerospace USA Inc.
- [STC SR00038DE](https://openairdocs.org/stc/SR00038DE): Installation of supplemental lubrication kit for lower drive shaft.. Dart Aerospace USA Inc.
- [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 SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC
- [STC SR01838AT](https://openairdocs.org/stc/SR01838AT): Installation of Cyclic Friction Release Levers.. Thoroughbred Aviation Maintenance Inc
- [STC SR00711SE](https://openairdocs.org/stc/SR00711SE): Fabrication of Onboard Systems Model 200-244-00 cargo hook kit. Onboard Systems International
- [STC SH1152NW](https://openairdocs.org/stc/SH1152NW): Installation of the Automatic Flagman Model 135 Control Stick Grip. Air Products & Parts LLC
- [STC SR02704SE](https://openairdocs.org/stc/SR02704SE): Installation and maintenance of the Sunspot 36 and 46 series lights. AeroLED's Holdings LLC
- [STC SH2334SO](https://openairdocs.org/stc/SH2334SO): Installation of a cabin heater/defroster. Schweizer RSG LLC
- [STC SH34WE](https://openairdocs.org/stc/SH34WE): Installation of 'Tote-All' luggage/cargo carrier.. Schweizer RSG LLC
- [STC SH7WE](https://openairdocs.org/stc/SH7WE): Fabrication of Precision Helicopters Model 4887 Cargo Rack System. Schweizer RSG LLC
- [STC SH8WE](https://openairdocs.org/stc/SH8WE): Installation of Tote-All luggage/cargo carrier.
NOTE:  Hughes Lateral Trim Assembly 269/A9935-3 required with this installation.. Schweizer RSG LLC
- [STC SR02124SE](https://openairdocs.org/stc/SR02124SE): Installation functionality. of Data Garmin Required: transponders: (1) Garmin GTX Master 345/345R Drawing with List ADS-B (MDL), Out and In 005-00734-A4, functionality;. Garmin International Inc
- [STC SA615EA](https://openairdocs.org/stc/SA615EA): Installation of a Whelen Anti-Collision Strobe Light System as replacement for originally installed anti-collision lights.. Whelen Aerospace Technologies
- [STC SR00359BO](https://openairdocs.org/stc/SR00359BO): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies
- [STC SH444NE](https://openairdocs.org/stc/SH444NE): Installation of Whelen Strobe Lights. Schweizer RSG LLC
- [STC SH445NE](https://openairdocs.org/stc/SH445NE): Installation of Engine Idle Overspeed Control System. Schweizer RSG LLC
- [STC SH586EA](https://openairdocs.org/stc/SH586EA): Installation of Hartzell Anti-Overspeed kits (D-3520-1 and D-3520-2). Schweizer RSG LLC
- [STC SH1065NE](https://openairdocs.org/stc/SH1065NE): Installation of Airwolf Model AFC-500 full flow engine oil filter P/N AFC-500.. Airwolf Filter Corporation
- [STC SA2586NM](https://openairdocs.org/stc/SA2586NM): Installation of J.P. Instruments temperature monitoring systems.. J P Instruments
- [STC SR02487AK](https://openairdocs.org/stc/SR02487AK): Installation of L-3 Communications Avionics Systems ESI-500 Standby Instrument System. ADS-B Technologies, LLC
- [STC SR01802WI](https://openairdocs.org/stc/SR01802WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel per ASTM D7547.. Swift Fuels LLC
- [STC SR02470AK](https://openairdocs.org/stc/SR02470AK): Installation of the L-3 Communications NGT -1000/2000/2500 ADS-B System. ADS-B Technologies, LLC
- [STC SR02471AK](https://openairdocs.org/stc/SR02471AK): Installation of the L-3 Communications NGT -9000/9000R ADS-B System. ADS-B Technologies, LLC
- [STC SR02394AK](https://openairdocs.org/stc/SR02394AK): Replacement of existing landing and/or hover light bulbs with Light Emitting Diode (LED) lighting system. Seaplanes North LLC
- [STC SH1839NM](https://openairdocs.org/stc/SH1839NM): Installation of Skytronics, Part No. 7150T-300-1 Alternators. Hartzell Engine Technologies, LLC
- [STC SR03281CH](https://openairdocs.org/stc/SR03281CH): Installation of  Garmin G500H Flight Display System, including GDU 620 PFD/MFD, GTN 650 Control and Display, GRS 77H AHRS, GMU 44 Magnetometer, GTP 59 Temperature Probe and Midcontinent Instrument MD302 Standby Attitude Module. University Aerospace Foundation
- [STC SA00432SE](https://openairdocs.org/stc/SA00432SE): Installation of EGT 701 series fuel flow instrument.. J P Instruments
- [STC SA00861SE](https://openairdocs.org/stc/SA00861SE): Installation of J.P. Instruments (JPI) fuel flow indicating system. J P Instruments
- [STC SH202WE](https://openairdocs.org/stc/SH202WE): Installation of controls for pilot-in-command on right side.. Allen J Gerbino, Gerbino Flight Systems
- [STC SH249WE](https://openairdocs.org/stc/SH249WE): Installation of a searchlight kit.. Allen J Gerbino, Gerbino Flight Systems
- [STC SH258WE](https://openairdocs.org/stc/SH258WE): Installation of MCT-10 mounting rack.. Allen J Gerbino, Gerbino Flight Systems
- [STC SH259WE](https://openairdocs.org/stc/SH259WE): Installation of utility compartment.. Allen J Gerbino, Gerbino Flight Systems
- [STC SH286WE](https://openairdocs.org/stc/SH286WE): Installation of Tayburn antenna deployment system.. Allen J Gerbino, Gerbino Flight Systems
- [STC SH290WE](https://openairdocs.org/stc/SH290WE): Installation of a 'T' instrument console.. Allen J Gerbino, Gerbino Flight Systems
- [STC SH152WE](https://openairdocs.org/stc/SH152WE): Installation of Hoskins Model 700801 Anti-collision light system. BF Goodrich Aerospace
- [STC SH152AWE](https://openairdocs.org/stc/SH152AWE): Installation of Hoskins Model 700801 Anti-collision light system in accordance with Hoskins Drawing No. 10-201969, Rev D. Dated August 14, 1972.. BF Goodrich Aerospace
- [STC SH1018CE](https://openairdocs.org/stc/SH1018CE): Install landing gear damper piston.. Kinzie Industries Inc.
- [STC SH1047CE](https://openairdocs.org/stc/SH1047CE): Install modified landing gear damper.. Kinzie Industries Inc.
- [STC SH1099CE](https://openairdocs.org/stc/SH1099CE): Installation of cabin heater and engine exhaust tail pipe extension.. Kinzie Industries Inc.
- [STC SH1138CE](https://openairdocs.org/stc/SH1138CE): Installation of engine exhaust tail pipe extension.. Kinzie Industries Inc.

All 134: https://openairdocs.org/tcds/4H12/stcs.md

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