TCDS 4H12

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