# TCDS 1H11: Centerpointe Aerospace Inc. - Type: Type certificate data sheet - Status: Current - Holder: Centerpointe Aerospace Inc. - Revision: 20 - Revised: September 19, 2019 - Product: Aircraft, Rotorcraft - Certification basis: Part 29, CAR 6 - Registered aircraft: 25, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/9a/19/9a191a02c57fee6ad23cd21b61c54bae5409168c8a4714e050714a79f4d2e3c4 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/EB12A0A5441419C586258567003A8F74.0001 - Page: https://openairdocs.org/tcds/1H11 ## Models (15) As the data sheet lists them. - S-58J - S-58FT - S-58C - S-58A - S-58HT - S-58F - S-58G - S-58ET - S-58DT - S-58D - S-58H - S-58B - S-58BT - S-58E - S-58JT ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 Rev. No. 17 16 16 18 16 18 18 17 17 16 16 16 16 16 17 18 18 16 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1H11 Revision 20 Centerpointe Aerospace Inc. S-58A S-58J S-58B S-58BT S-58C S-58DT S-58D S-58ET S-58E S-58FT S-58F S-58HT S-58G S-58JT S-58H Military Models (See Note 6, 7, 8) September 19, 2019 HELICOPTER SPECIFICATION NO. 1H11 Type Certif icate Holder Centerpointe Aerospace Inc 279 Blackland Road Royse City, TX 75189 Type Certificate Holder Record California Helicopter Airways Inc. became Centerpointe Aerospace Inc. on September 19, 2019. I. - Model S-58A, S-58B, S-58C, 14 PLCH, Approved August 2, 1956, Model S-58D, 14 PLCH, Approved December 15, 1961, Model S-58E, 14 PLCH, A pproved May 27, 1971, Model S-58F, S-58G, S-58H, S-58J, 14 PLCH, Approved March 15, 1972. (See Note 6, 7, 8 for Military versions.) Engine 1. Wright Cyc lone 989C9HE-2 or 2. Wright Cyclone 998C9HE-2 engine (Same limitations as for Wright 989C9HE-2) Fuel 115/145, 100/130 mini mum grade aviation gasoline Engine limits M.P. HP R.P.M. in Hg. Alt. Fuel Grade 115/145 Maximum continuous 1275 2500 47.5 S.L. Maximum continuous 1275 1500 46.0 3500 ft. Takeoff (five minutes) 1525 2800 56.5 S.L. Takeoff (five minutes) 1525 2800 55.5 700 ft. (Straight line manifold pressure variation with altitudes shown) Fuel Grade 100/130 (Item 401(f) required) Maximum continuous 1275 2500 47.5 S.L. Maximum continuous 1275 2500 46.0 3500 ft. Takeoff (five minutes) 1425 2800 53.0 S.L. Takeoff (five minutes) 1425 2800 52.0 2900 ft. (Straight line manifold pressure variation with altitude shown) Rotor limits Maxi mum 258 r.p.m. Minimum 170 r.p.m. See NOTE 3 for required placard. Airspeed lim its Maximum never exceed 120 knots CAS (117 knot IAS). See NOTE 3 for required placard. C.G. range (+129.6) to (+146. 7) 20 Sikorsky Aircraft transferred TC 1H11 to California Helicopter Airways Inc. on May 06, 2015. 1H11 2 E mpty wt. C.G. range None M aximum weight 12,700 lb. for S-58A, S-58B, S-58C, (See Item 604 for higher weight) 13,000 lb. for S-58D and S-58E 12,500 lb. for S-58F, S-58G, S-58H, S-58J. (See NOTE 9 for these Models). No . seats 14 Pilot and co-pilot: (+93) Passengers: (S-58A): 3 at (+131), 1 at (+162), 1 at (+175), 1 at (+180), 1 at (+198), 1 at (+211), 1 at (+218), 3 at (+254). (S-58C): 3 at (+131), 3 at (+174), 3 at (+211), 3 at (+254) (also S-58G) (See item 402 for model S-58B, S-58D, S-58E, S-58F, S-58H, S-58J seating arrangements to 16) M aximum baggage (S-58A) Lower shelf 260 lb. (+97) Upper shelf 100 lb. (+95) (S-58B, S-58D, S-58E) 200 lb./sq.ft. (+82.5 to +246) (S-58C) 200 lb./sq.ft. (+82.5 to +112) (See NOTE 5 for cargo capacity.) (Refer to the appropriate Helicopter Flight Manual for additional information.) F uel Capacity See NOTE 1 for data on system fuel and oil. 12 Cell Configuration S-58A, S-58B, S-58C, S-58F, S-58G USABLE FUEL (Pump Type Transfer System) Location Volume (Gal) Maximum Weight (lb.) Arm (In.) Forward Tank 124 744 121 Center Tank 69 414 184 Aft Tank 92 552 223 TOTAL 285 1710 12 Cell Configuration S-58D, S-58E, S-58H, S58J USABLE FUEL (Ejector Type Transfer System) Location Volume (Gal.) Maximum Weight (lb.) Arm (In.) Forward 99 594 121 Center Tank 68 408 184 Aft Tank 87 522 233 TOTAL 254 1524 11 Cell Configuration S-58E, S-58D, S-58H, S-58J USABLE FUEL (Ejector Type Transfer System) Location Volume (Gal.) Maximum Weight (lb.) Arm (In.) Forward Tank 99 594 121 Center Tank 68 408 184 Aft Tank 87 522 233 TOTAL 254 1524 3 1H11 Oil Capacity 10.5 gal. (+75) Rotor blade movements For rigging information refer to Maintenance Manual. Serial Nos. eligible 58310, 58312, 58324, 58333, 58350, 58356, 58363, 58387, 58388, 58395, 58396, 58403, 58410, 58414, 58432, 58449, 58462, 58470, 58482, 58519, 58530, 58534, 58700, 58775, 58807, 58836, 58898, 581016, 581573, (See NOTE 6, 7, 8 for other S/N's eligible) Required equipment In addition to the pertinent required basic equipment specified in CAR 6, the following items of equipment must be installed: 102, 104, 105, 111, 112, 201, 202, 205, 206, 301, 302, 303, 401 Certification basis Type Certificate No. 1H11 (CAR 6, January 15, 1951 and Amendment 6-1 through 6-6). The Model S-58C is eligible for scheduled air carrier operation. II- Model S-58BT, S-58DT, S-58ET, 14 PLCH, Approved 18 February 1972 Model S-58FT, S-58HT, S-58JT, 14 PLCH, Approved 27 March 1972 (See NOTE 6, 7, 8 for Military Versions) (See NOTE 10 regarding Supplemental Type Certification of P&WA ACL PT6T-3 Conversion) Engine 1. Pratt & Whitney Aircraft of Canada, Ltd. PT6T-3 Twin Power Section Turboshaft (Ref. NOTE 5 Engine Type Certificate Data Sheet No. E22EA) or 2. Pratt & Whitney Aircraft of Canada, Ltd. PT6T-6 Twin Power Section Turboshaft (Ref. NOTE 5 Engine Type Certificate Data Sheet No. E22EA) Fuel 1. PT6T-3 Twin Power Section Turboshaft: JP-1, JP-4 and JP-5 conforming to current issue of PWA Specification No. 522. Emergency use of aviation gasoline, all grades; (MIL-G-5572) is permitted for a total time period not exceeding 150 hours during any overhaul period. 2. PT6T-6 Twin Power Section Turboshaft: Fuels conforming to PWA Specification No. 522 and CPW-46, and later revisions. Emergency use of MIL-G-5572, Grades 80/87, 91/98, 100/130, and 115/145, is permitted for a total time period not exceeding 150 hours, or 450 hours using a 1:3 mixture of aviation gasoline and aviation kerosene, during any overhaul period. 3. See NOTE 14. Engine limits 1. PT6T-3 Twin Power Section Turboshaft: Sea Level Static, Standard Day Conditions. Total power output Shaft Power Turbine Gas Gen. Power Turbine RFM Item 401(o) hp. r.p.m. r.p.m. Inlet Temp T5 Takeoff (5 min.) 1505 3300(100%) 38100(100%) 810°C Maximum continuous 1262 29700(90%)Max. 38100(100%) 765°C 29040(88%)Min. Transient limit (10 sec) (101.5%) 850°C Starting limit (2 sec) 1090°C Total power output, Meeting FAR 29, Category "A" Powerplant Installation Requirements 1H11 4 Engine limits (Cont'd) Shaft Power Turbine Gas. Gen. Power Turbine RFM Item 401(p) or 401(s) hp. r.p.m. r.p.m. Inlet Temp T5 Takeoff (5 min.) 1625 33000 (100%) 38100 (100%) 810°C Maximum continuous 1420 31020 (94%)Max. 38100 (100%) 765°C 30360 (92%)Min. Transient limit (10 sec) (101.5%) 850°C Starting limit (2 sec) 1090°C Single power section 900 33000 (100%) 38100 (100%) 810°C See NOTE 10 2. PT6T-6 Twin power Section Turboshaft: Sea Level Static, Standard Day Conditions. Total power output Meeting FAR 29, Category "A" Power Plant Installation Requirements Shaft Power Turbine Gas. Gen. Exhaust Gas RFM Item 401(s) hp. r.p.m. r.p.m. Temp T7 Takeoff (5 min.) 1625 33000 (100%) 38400 (100.8%) 624°C Maximum continuous 1420 31020 (94%)Max. 38400 (100.8%) 593°C 30360 (92%)Min. Transient limit (5 sec) 39100 (102.6%) 645°C Starting limit (2 sec) 760°C Single power section 970 33000 (100%) 38400 (100.8%) 624°C See NOTE 13. Rotor limits Maximum 258 r.p.m. (104% Nr) Minimum 170 r.p.m. (68% Nr) Airspeed limits Never exceed 120 knots CAS (117 knots IAS) See NOTE 3 for required placard. C.G. range (+129.6) to (+146.7) Empty wt. C.G. range None Maximum weight 13000 lb. for S-58BT, S-58DT, S58ET 12500 lb. for S-58FT, S-58HT, S-58JT No. seats 14 pilot and co-pilot: (+93) Passengers (see Item 402 for cabin seating arrangements) (S-58DT, S-58HT) 1 at 131, 1 at 148, 1 at 166, 1 at 174, 1 at 183, 1 at 189, 1 at 201, 1 at 205, 1 at 218, 1 at 221, 1 at 236, 1 at 237. (S-58ET, S-58JT) 2 at 96, 1 at 112, 1 at 116, 1 at 135, 1 at 156, 2 at 176, 2 at 196, 2 at 215 (see Item 402 for other seating arrangements) Maximum baggage (S-58BT, S-58DT, S-58ET) 200 lb./sq. ft. (+82.5 to +246) (Refer to the appropriate Helicopter Flight Manual for additional information.) 5 1H11 Fuel Capacity See NOTE 1 for data on system fuel and oil 12 Cell Configuration S-58BT, S-58ET, S-58FT, S-58JT USABLE FUEL (Pump Type Transfer System) Location Volume (Gal.) Maximum Weight (lb.) Arm (In.) Forward Tank 120 816 121 Center Tank 69 469 184 Aft Tank 90 612 223 TOTAL 279 1897 12 Cell Configuration S-58BT, S-58ET, S-58FT, S-58JT USABLE FUEL (Ejector Type Transfer System) Location Volume (Gal.) Maximum Weight (lb.) Arm (In.) Forward Tank 123 837 121 Center Tank 62 422 184 Aft Tank 88 598 223 TOTAL 273 1857 11 Cell Configuration S-58DT, S-58ET, S-58HT, S-58JT USABLE FUEL (Ejector Type Transfer System) Location Volume (Gal.) Maximum Weight (lb.) Arm (In.) Forward Tank 94 639 121 Center Tank 62 422 184 Aft Tank 88 598 223 TOTAL 244 1659 Oil Capacity Each Engine Power Section 1.6 gal. (0.75 usable) +40.0 In. Rotor Blade Movements For rigging information, refer to Maintenance Manual. Serial Nos. Eligible Production of turbine models is not planned, but rather conversion of the reciprocating engine models to turbine models. All S-58B's, S-58D's, S-58E's, S-58F's, S-58H's, and S-58J's serial numbers are eligible for conversion. (See NOTE 6, 7, 8 for other serial numbers eligible). Required Equipment Basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installed in the helicopter for certification: Also Items 103, 106, 108, to 125 except 111, 201, 202, 205, 206, 304, 305, 401. Also 126(a) required with P&W Aircraft PT6T-3 engine installation. Item 126(b) required with P&W Aircraft PT6T-6 engine installation. 1H11 6 Certification basis Type Certificate No. 1H11 (CAR 6, January 15, 1951, and Amendment 6-1 through 6-6); In addition, for configuration I, (Sikorsky Kit No. 580000-10000-011) portions of FAR 29 dated 1 February 1965 including Amendments 29-1 through 29-3, specifically; 29.73; 29.361(a); 29.901(b)(5); 29.903(c); 29.927(b); 29.939; 29.955(a); 29.997(e); 29.1041(a); 29.1091(f); 29.1093(b); 29.1121(h); 29.1181(a); 29.1185; 29.1187(a) through (d); 29.1189(a)(1), (b), (d), (e) and (f); 29.1191(a), (c), (d), and (f); 29.1193(a) through (d); 29.1194; 29.1195(a) and (c); 29.1203; 29.1303(e); 29.1305(a)(3), (a)(4), (a)(6) through (a)(15), and (c), also; Special Conditions 27-33-EA-8 (Docket No. 10991) dated 14 April 1971, and Exemption No. 1154 (Docket No. 10310) dated 10 July 1970. For Configuration II, (Sikorsky Kit No. 58000-10000-012) the certification basis of Configuration I applies except for deletion of Special Flight Condition No. 1 of Special Conditions 27-33-EA-8 (Docket No. 10991) dated 14 April 1971 and addition of the following applicable FAR 29 requirements: 29.33; 29.45; 29.51; 29.63; 29.65; 29.75; (a) and (c)(1); 29.79(a) and (b)(1); 29.141; 29.171; 29.173; 29.175; 29.231; 29.241; 29.251; 29.663(b); 29.303(b); 29.951; 29.953(a); 29.961; 29.967(a) and (e); 29.971(a), (b) and (c); 29.973(b); 29.975(a); 29.977; 29.991(c)(2) and (3); 29.993(c) and (e); 29.995; 29.1011(b); 29.1017(b); 29.1019; 29.1023(b); 29.1047(a); 29.1049; 29.1103(b) and (c); 29.1123; 29.1141(d) and (e); 29.1163(b) and (d); 29.1187(e); 29.1189(c); 29.1193(e); 29.1195(b); 29.1305(b); 29.1501; 29.1509; 29.1517; 29.1581; 29.1587(b)(1). In addition, FAR 29.1505 (Ref. Revision 4 FMS No. 16 to RFM SA4045-12 (Item 401(p)): FAR 25.801, 25.807(d) (Ref. FMS No. 13 to RFM SA4047-17 (Item 401(dd)). Configuration II differs from Configuration I in that the rotorcraft complies with the FAR 29 Category "A" Power Plant installation requirements when operating under Configuration II. Refer to Item 401 (p) for additional differences. A Configuration II rotorcraft can be flown as a Configuration I rotorcraft, but a Configuration I rotorcraft cannot be flown as a Configuration II rotorcraft. Specifications Pertinent to all Models: Datum 137.7 inches forward of main rotor centroid Leveling Means Plumb bob from top of cabin door frame to scale on lower door sill Production basis Production Certificate No. 105 (S-58A, S-58B, S-58C, S-58D, S-58E, S-58F, S-58G, S-58H, S-58J, S-58BT, S-58DT, S-58ET, S-58FT, S-58HT and S-58JT) 7 1H11 Equipment: (a) "x" indicates applies (b) "-" indicates does not apply (c) "_./" indicates item No. of previous revision Twin Power Reciprocating Section Engine and Engine Accessories - Fuel and Oil System Engine Turboshaft 102. Starter Model AN4116R3 28 lb. (+22) x - 112./ 103. Starter generator, Lear Siegler 23046-0019 - x 103./ 104. Fuel Pump - engine driven AN4101-1 3 lb. (+31) x - 104./ 105. Fuel pump, boost, Romec RG11260-A1 4 lb. (+121) x - 113./ 106. Fuel pump, boost, Lear Siegler P/N RG17020A-1 - x 109./ 107. Master mechanical fuel shut-off valve installation in accordance with x - Sikorsky Kit Dwg. No. S1607-3041. Item 401(k) required with this installation. 116./ 108. Fuel shut-off valve, Aerospace Controls AV16B1847D - x 117./ 109. Manual fuel drain valve, Koehler 8151-4AF - x 118./ 110. Fuel filter drain valve, Koehler 3-116965 - x 105./ 111. Oil cooler, engine, Airesearch Model No. 88340 36 lb. (+66) x - 106./ 112. Oil cooler, transmission, Harrison Radiator 28 lb. (+199) x - Model No. 852534 114./ 113. Oil cooler, (four) radiator, Harrison 8538233 - x 115./ 114. Oil cooler, blower (a) Dynamic Air M141S-1A - x (b) Torin A27583 - x 119./ 115. Manual oil drain valve, Koehler 8151-8AV - x 120./ 116. Oil pump, angle gear box, Lear Siegler RG34000C - x 121./ 117. Hydraulic pump, N.Y. Airbrake 67WL200-2 - x 122./ 118. Torquemeter Transmitter, Bendix 58450-10012-101 - x 123./ 119. Torquemeter Indicator, Bendix 6300-C49A-155-B1 - x 124./ 120. Engine Tachometer generator (Ng), MS25038-4 - x 125./ 121. Engine Tachometer generator (Nf), MS25038-2 - x 126./ 122. Engine Tachometer Indicator (Ng), General Electric 8DJ1CAA-2 - x 127./ 123. Engine Tachometer, Indicator (Nf), included Item 125 - x 128./ 124. Main Rotor Tachometer generator, MS25038-2 - x 129./ 125. Triple Tachometer Indicator, (a) Kollsman P/N 58450-10011-101 - x (b) Kollsman A5590110010 - x 130./ 126a. Engine T5 Gas Temperature Indicator, Lewis 152B33 - x b. Engine T7 Gas Temperature Indicator, Lewis 71700 (See NOTE 3) - x 107./ 127. Auxiliary 85 gal. fuel tank installation in 60 lb. (+223) x - accordance with Sikorsky Dwg. No. S1630-62703 Fuel arm (+223) (S-58C and S-58G) 108./ 128. Auxiliary 60 gal. fuel tank installation in accordance with x x Sikorsky Kit Dwg. No. S1607-3106. (S-58A, S-58B, S-58C, S-58F, S-58G, S-58BT, S-58FT) Use actual wt. change 129. Auxiliary 150.5 gal. fuel tank installation in accordance with - x Sikorsky Kit Dwg. No. S1630-62245-5. (Installation of basic tank P/N 58088-30008 as modified by 58088-30010 mod. kit.) (S-58BT, S-58DT, S-58ET, S-58FT, S-58HT) Item 401 (bb) required with this installation. See NOTE 3 for operating limitations. 110./ 130. Chip detector installation in accordance with Sikorsky Kit x x Dwg. No. S1607-4598. Item 401(1) required with this installation. 1H11 8 Twin Power Reciprocating Section Engine Turboshaft Landing Gear 201. Two main wheel-brake assemblies, 11.00-12, Type III 39 lb. (+101) x (a) Goodyear Model L12HBM Wheel assembly No. 530884G Brake assembly No. 530886SG 202. Two main wheels, 6-ply rating tires, 11.00-12, Type III, 31 lb.(+101) x x with regular tubes 205. Tail wheel assembly, 6.00-6, Type III 4 lb. (+440) x x (a) Goodyear Model L6HBD Wheel assembly No. 9531065 206. Tail wheel 6-ply rating tire, 6.00-6, Type III, 11 lb. (+440) x x with regular tube. Dunlop tube and tire size 11.00-12, Type 20, No. 6, 1EXX, nylon 8 ply rating may be used as an alternate on Models S-58BT, S-58DT, and S-58ET. 207. Emergency inflatable float gear installed in accordance with x x Sikorsky Dwg. No. S1625-55030 for S-58A, S-58B, 338 lb. (+164) S-58D, S-58E, S-58F, S-58H, S-58J, S-58BT, S-58DT, S-58ET, S-58FT, S-58HT, S-58JT. Sikorsky Dwg. No. S1625-55000 for S-58C, S-58G. Additional modifications in accordance with Sikorsky Dwg. No. S1607-2556 are required when Item 209 is installed. Item 401(d) required with this installation on reciprocating models. Item 401(v) required with this installation on turboshaft models. See NOTE 3 for operating limitations. 208. Emergency flotation gear. Use actual wt. change x x (a) P/N S1625-56000 installed in accordance with Sikorsky Kit Dwg.S6107-2515 and Sikorsky Service Information Circular No. 1625-1188. (S-58B, S-58D, S-58E, S-58F, S-58H, S-58J Item 401(e) and/or Item 401(h) required with this installation) (S-58BT, S-58DT, S-58ET, S-58FT, S-58HT, S-58JT, Item 401(w) and/or Item 401(x) required with this installation). (b) P/N S1625-56100 installed in accordance with Sikorsky - x Kit Dwg. No. S1607-2515 and Sikorsky Service Information Circular No. S1625-1123 (S-58C, S-58G Item 401(e) and/or 401(h) required with this installation). (maximum weight 12,700 lbs.). See NOTE 3 for operating limitations. 209. Main landing gear installation in accordance with Sikorsky Dwg. No. S1607-2552A. Use actual wt. 210. Salvage flotation gear installed in accordance with Sikorsky x x Dwgs. S1607-2571-4, -7, -8. Use actual wt. (S-58B, S-58C, S-58D, S-58E, S-58F, S-58G, S-58H, S-58J Item 401(n) required with this installation) (S-58BT, S-58DT, S-58ET, S-58FT, S-58HT, S-58JT, Item 401(y) required with this installation) See NOTE 3 for operating limitations. 211. Ditching flotation system installation in accordance with x x Sikorsky Dwgs. S1607-2571-4, -7, or -8, and Sikorsky Dwg. 58088-20073 (modified door); Item 401(dd) required with this installation. 9 1H11 Twin Power Reciprocating Section Engine Turboshaft Electrical Equipment 301. Generator (a) 30V, 300 amp., Eclipse Red Bank Model 30E20-9-1A, 45 lb. (+19) x - 30E20-11A or 30E20-49A 302. Battery (a) 24V, 24 amp. hr., Model AN3151-2 56 lb. (+77) x - (b) 24V, 26 amp. hr., Model AN3150-2 80 lb. (+77) x - 303. Two inverters, 250 V.A. output, Model AN3532-2 17 lb. (+76) x - 304. Battery Sontone (a) Sonotone CA21H-1, 22 amp hr., 28V - x (b) Sonotone CA5, 35 amp hr., 28V - x 305. Inverters (two) AN3532-3, 250VA, 11V, 400 cycle - x 306. Relay & Sensor Assembly 58550-10249-042 Interior Equipment 401. (a) FAA approved Rotorcraft Flight Manual dated August 2, 1956, x - reissued June 28, 1957, revised 13 August 1972 (RFM 4045-12) (b) Supplement No. 1 dated August 2, 1956, reissued June 10, 1958, x - revised August 28, 1983, to item 401(a). Contains operational information for Item 602. (c) Supplement No. 2 dated August 2, 1956, reissued April 25, 1958, x - revised August 28, 1973 to Item 401(a). Contains operational information for Item 603. (d) Supplement No. 3 dated December 10, 1956, reissued May 7, 1958, x - revised 21 October 1971, to Item 401(a). Required when Item 207 is installed.` (e) Supplement No. 4 dated February 18, 1957, reissued May 7, 1958, x - revised October 21, 1971, to item 401(a). Required when Item 208 is installed. (f) Supplement No. 5 dated October 9, 1957, reissued June 10, 1958, revised April 23, 1959, to Item 401(a). Required when grade 100/130 fuel is used. (g) Supplement No. 6 dated December 30, 1957, reissued June 18, 1958, revised October 21, 1960, to Item 401(a). Required when Item 604 is installed. (h) Supplement No. 7 dated April 25, 1958, revised 28 August 1973, to x - Item 401(a). Contains operational information when both Item 208 and Item 603 are installed. (i) Supplement No. 8 dated May 7, 1958, revised December 15, 1961, to x - Item 401(a). Required when Item 605 is installed. (j) Supplement No. 9 dated February 24, 1959, to Item 401(a) x - Contains operational information when Ejector Fuel System is used on S-58B. (k) Supplement No. 11 dated November 13, 1959, to Item 401(a). x - Required when Item 107 is installed. (l) Supplement No. 12 dated October 17, 1960 to Item 401(a). x - Required when Item 130 is installed. (m) Supplement No. 13 dated December 15, 1961, revised May 27, 1971, x - to Item 401(a). Required for the model S-58D and S-58E. (n) Supplement No. 14 dated March 5, 1965, revised October 20, 1971, x - to Item 401(a). Required when Item 210 is installed. 1H11 10 Twin Power Reciprocating Section Engine Turboshaft (o) Supplement No. 15 dated 15 April 1971, revised 30 November 1973, x - to Item 401(a). Required for installation of UACL PT6T-3 engine in Model S-58B, S-58D, S-58E, S-58F, S-58H and S-58J. Required for configuration I aircraft. (p) Supplement No. 16 dated 5 November 1971, revised 10 April 1973, x - to Item 401(a). Required for installation of UACL PT6T-3 engine, meeting FAR 29, Category A Power Plant Installation requirements in S-58B, S-58D, S-58E, S-58F, S-58H and S-58J. Required for configuration II aircraft. See NOTE 12. (q) Supplement No. 17 dated 15 March 1972, revised 27 March 1972 to x - Item 401(a). Required for the Model S-58F, S-58G, S-58H, S-58J (air taxi operations). (r) Supplement No. 18 dated 30 June 1972 to Item 401(a). Required when Item 602 is used in isolated Mountain Operations Above 8000 feet Density Altitude. (s) FAA Approved Rotorcraft Flight Manual dated November 5, 1971, - x reissued April 18, 1973, revised September 13, 1977 See NOTE 12. (t) Supplement No. 1 dated April 20, 1973 to Item 401(s). Required - x when Item 602 is installed. (u) Supplement No. 2 dated April 20, 1973 to Item 401(s). Required - x when Item 603 is installed. (v) Supplement No. 3 dated April 20, 1973 revised July 15, 1976 to Item 401(s). Required when item 207 is installed. (w) Supplement No. 4 dated April 20, 1973 to Item 401(s). Required - x when Item 208 is installed. Canceled. (x) Supplement No. 5 dated April 20, 1973 to Item 401(s). Required when Items 603 and 208 are installed. Canceled. (y) Supplement No. 6 dated April 20, 1973, revised March 28, 1978, - x to Item 401(s). Required when Item 210 is installed. (z) Supplement No. 7 dated April 20, 1973, revised July 15, 1976, to Item 401(s). Required when Item 602 is used in Isolated, Mountain Operations above 8000 feet Density Altitude. (aa) Supplement No. 8 dated June 5, 1973, revised March 28, 1975 to - x Item 401(s). Required when Item 608 is installed. (bb) Supplement No. 10 dated May 2, 1974, revised March 27, 1975 - x to item 401(s). Required when Item 129 is installed. (cc) Supplement No. 12 dated May 2, 1974, revised May 2, 1978 - x to Item 401(s). Required when Item 609 is installed. (dd) Supplement No. 13, dated April 10, 1975 revised March 28, 1978, to item 401(s) when Item 211 is installed. 402. Optional cabin seating arrangements, Sikorsky Dwg. Nos.; (a) S1650-61750, 12 Place (S-58B, S-58D, S-58F, S-58H, S-58BT, x x S-58DT, S-58FT, S-58HT). (b) S1650-61760, 14 Place (S-58B, S-58F, S-58BT, S-58FT). x x (c) S1607-5091, 15 Place (S-58B, S-58F, S-58BT, S-58FT). x x (d) S1607-5094, 16 Place (S-58B, S-58D, S-58E, S-58F, S-58H, S-58J, S-58BT, S-58ET, S-58FT, S-58JT). NOTE: Seating configuration with more than 15 seats in cabin must have a secondary emergency exit on the left side of the cabin. 403. Litters installed in accordance with Sikorsky Dwg. Use actual wt. x x No. S1650-61770 (S-58B, S-58D, S-58BT, S-58DT). 404. Pilot and copilot seat, Aerosmith Model C-111. x x 11 1H11 Twin Power Reciprocating Section Engine Turboshaft Miscellaneous Equipment (not listed previously) 601. Hydraulic pump, variable delivery, N.Y. Airbrake Model No. 67WB200 (S-58A, S-58B, S-58C, S-58F, S-58G, S-58BT, S-58DT, S-58ET, S-58FT, S-58HT, S-58JT). (a) Transmission-driven 8 lb. (+156) x x (b) Engine-driven 8 lb. (+125) x - 602. Cargo sling installation (S-58A, S-58B, S-58C, S-58D, S-58E, S-58F, S-58G, S-58H, S-58J Item 401(b) or 401(r) required with this installation. S-58BT, S-58DT, S-58ET, S-58FT, S-58HT, S-58JT Item 401(t) or 401(z) required with this installation). (a) Sikorsky Dwg. No. S1650-62150, (4000 lb.) x x (b) Sikorsky Dwg. No. S1650-62195, (5000 lb.) x x See NOTE 4 for operating limitations. 603. Hoist installation in accordance with Sikorsky Dwg. No. x x S1650-61700 (S-58A, S-58B, S-58C, S-58D, S-58E, S-58F, S-58G, S-58H, S-58J). Item 401(c) and/or 401(h) required with this installation. S-58BT, S-58DT, S-58ET, S-58FT, S-58HT, S-58JT Item 401(u) and/or Item 401(x) required with this installation). See NOTE 4 for operating limitations. 604. Modifications for increase in gross weight of S-58A, S-58B, x - S-58C to 13,000 lb. in accordance with Sikorsky Kit Dwg. No. S1605-1700A. Item 401(g) required with this installation Fuel 115/145 minimum grade aviation gasoline Rotor limits See NOTE 3 for required placard. Airspeed Never exceed 107 knots IAS. See NOTE 3 for required placard. Maximum weight 13,000 lb. 605. Automatic Stabilization Equipment installed in accordance with x x Sikorsky Dwg. No. S1605-4600. Item 401(i) required with this installation. 606. Omitted. - - 607. Modified nose door assembly and relocation of fixed equipment in x - accordance with Sikorsky Kit Dwg. No. S1607-4554 Use act. wt. change (S-58A, S-58B, S-58C, S-58F, S-58G). - x 608. IFR Mod Kit No. 58000-10001-002. - x Item 401(aa) required with this installation. See NOTE 3 for operating limitations. 609. Product improvement items as defined by Sikorsky Dwg. No. - x 58000-10000-014. Item 401(cc) required with this installation. See NOTE 3 for operating limitations. 610. Bifilar vibration absorber installation in accordance with - x Sikorsky Modification Kit 58070-10003. Model S58T series only. NOTE 1. Current weight and balance report, including list of equipment included in certificated weight empty, and loading instructions must be in each helicopter at the time of original certification and at all times thereafter. In the case of Air Carrier operators having an approved weight control system, the weight and balance report need not be in the helicopter. When changes are made to the helicopter which affect weight and balance refer to the Flight Manual for instructions. 1H11 12 NOTE 2. Information essential to the proper maintenance of the helicopter including retirement time of critical components is contained in the Sikorsky S-58 Maintenance Manual provided with each helicopter. Sikorsky Publication No. SA4045-15, Part IV, S58 Maintenance Manual, is applicable to Sikorsky Model S-58A, S-58B, S-58C, S-58D, S-58E, S-58F, S-58G, S-58H and S-58J helicopters. Sikorsky Publication No. SA4047-20, Equalized Inspection and maintenance Program (which supersedes Sikorsky Publication No. SA4045-15T, Part IV, S-58T Maintenance Manual) is applicable to Sikorsky Model S-58BT, S-58DT, S-58ET, S-58FT, S-58HT, and S-58JT helicopters. The values of retirement or service life cannot be increased without FAA engineering approval. NOTE 3. The following placards must be displayed on the instrument panel in full view of the pilot: (a) All model S-58 series and S-58T series: (i) "THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE FAA APPROVED ROTORCRAFT FLIGHT MANUAL." (ii) "AVOID FAST TURNS, 15-SEC. MINIMUM FOR 360 DEGREES." (iii) "DURING EXTENDED HOVERING, CLOSE WINDOWS AND DOORS AND TURN VENT SYSTEM ON. CLOSE LEFT WINDOW DURING STARTING AND TAXIING." except when Item 207, 208, or 210 is installed. (iv) "DO NOT FLY AT A PRESSURE ALTITUDE MORE THAN 3500 FEET ABOVE TAKE- OFF ALTITUDE." (Required when Item 208 or 210 with U.S. Rubber Floats Model Nos. PE-E-1005-1 and PE-E-1005-2 is installed.) (v) "DO NOT FLY AT A PRESSURE ALTITUDE MORE THAN 6300 FEET ABOVE TAKE- OFF ALTITUDE." (Required when Item 208 or 210 with Air Cruisers Floats Model Nos. 11D11149 and 11D11150 is installed.) (vi) "DO NOT MAKE WATER CONTACT ABOVE 20 KNOTS." (Required when Item 208 or 210 is installed.) (vii) "DURING EXTENDED HOVERING, SIDEWARD AND REARWARD FLIGHT, CLOSE WINDOWS AND DOORS AND TURN VENT SYSTEM ON. CLOSE LEFT WINDOW DURING STARTING AND TAXIING." (Required when Item 207, 208 or 210 is installed.) (viii) "LOCK TAIL WHEEL PRIOR TO TAKE-OFF WHEN THE TAIL WHEEL TYPE FLOAT IS INSTALLED." (Required when Item 207 is installed). (ix) "DO NOT INFLATE FLOATS ABOVE 60 KNOTS IAS. DO NOT EXCEED 60 KNOTS WITH FLOATS INFLATED." (Required when Item 207 is installed.) (b) All model S-58 series only, except as indicated: (i) "AVOID TAXI TURNS BELOW 2400 ENGINE R.P.M." (ii) Never exceed speeds. Variation of Vne with altitude, engine r.p.m. and manifold pressure. (S-58A, S-58B, S-58C, S-58F, S-58G when Item 604 is not installed). 2200 r.p.m. 2300 r.p.m. 2400 r.p.m. 2500 r.p.m. Alt. IAS M.P. IAS M.P. IAS M.P. IAS M.P. S.L. 72 35.5 87 38.7 103 42.3 117 47.5 5000 -- -- 60 37.0 76 41.0 90 F.T. 10000 -- -- -- -- -- -- 63 F.T. (iii) Never exceed speeds. Variation of Vne with altitude, engine r.p.m. and manifold pressure. Required when Item 604 is installed (S-58A, S-58B, S-58C). Required for the S-58D, S-58E. 2300 r.p.m. 2400 r.p.m. 2500 r.p.m. Alt. IAS M.P. IAS M.P. IAS M.P. S.L. 77 38.7 93 42.3 107 47.5 4000' -- -- 71 41.5 85 F.T. 8000' -- -- -- -- 63 F.T. 13 1H11 NOTE 3. (Cont'd) (c) All model S-58T series only, except as indicated: (i) "AVOID TAXI TURNS BELOW 88% Nr." (ii) "MAXIMUM SIDEWARD FLIGHT SPEED NOT TO EXCEED 25 KNOTS." (iii) "FUELING INSTRUCTIONS" Required with Item 401(p) or 401(s). "1. SERVICE FROM ALL THREE FILLER NECKS 2. ALLOW SUFFICIENT TIME FOR LEVEL TO STABILIZE 3. TOP OFF AS NECESSARY" (adjacent to center and aft fuel cell filler caps) (iv) "NO. 2 FUEL QTY (Required with Item 401(p) or 401(s)). ADD BOTH NEEDLES" (v) (below No. 2 Fuel Quantity Indicator) "PASSENGER CAPACITY IS LIMITED TO 15 PERSONS WHEN EXTERNAL AUXILIARY FUEL SYSTEM IS INSTALLED" (Required when Item 129 is installed.) (Required with Item 401(bb)). (vi) "USE AUXILIARY FUEL FIRST." "AUXILIARY TANK USABLE FUEL IS 870 LBS. WITH THE BASIC TANK P/N 58088- 30008 988 LBS. AS MODIFIED BY 58088-30010). (Required when Item 129 is installed. Required with Item 401(bb)). (vii) "ACCURATE FOR GROUND ATTITUDE ONLY." (Required when Item 129 is installed. Required with Item 401(bb)). (viii) Variation of Vne with altitude, main rotor r.p.m. and gross weight. (See below) (Required with Item 401(p) or 401(s)). 13000 lb. or Below Takeoff Gross Weight 89% NR 99% NR Vne Altitude KIAS KIAS Versus Density Altitude Sea Level 107 117 Power On 2000 96 117 Not to be Moved in Flight 4000 85 106 6000 74 95 8000 63 84 10000 73 12000 62 12000 lb. 11000 lb. or below POWER OFF Vne 93% NR Density 81-91% Nr 92-104% Nr Altitude KIAS Altitude KIAS Altitude KIAS KIAS Sea Level 117 Sea Level 117 Sea Level 107 117 3500 117 5000 117 2000 96 117 4000 115 6000 111 4000 85 106 6000 104 8000 100 6000 74 95 8000 93 10000 89 8000 63 84 10000 82 12000 78 10000 73 12000 71 14000 67 12000 62 13500 62 15000 62 15000 62 (ix) Never exceed speeds. Variation of Vne speed with Altitude. (See placard below) Required with Item 401(o). 1H11 14 Vne at 89% Nr Takeoff Gross Weights Density 12,700 Pounds 12,700 to Altitude and Below 13,000 Pounds S.L. 117 KIAS 107 KIAS 4000 ft. 95 KIAS 85 KIAS 5000 ft. 90 KIAS 79 KIAS 8000 ft. 74 KIAS 63 KIAS 10000 ft. 63 KIAS (x) Torque Limits Placard (see below). Required with Item 401(o). TAKE-OFF POWER MAX. CONTINUOUS POWER Percent Torque @ Nr = 100% Percent Torque @ Nr = 89% Pres Pres Alt Temp °C Alt Temp °C 1000 1000 -20 -10 0 10 20 30 40 -20 -10 0 10 20 30 40 -1 108 106 103 101 99 96 93 -1 101 98 96 94 93 91 89 0 106 104 101 100 97 93 90 0 100 98 96 94 92 90 88 1 104 102 100 97 94 90 87 1 100 98 96 94 92 89 87 2 102 100 98 94 91 87 84 2 99 97 95 93 91 88 86 3 100 97 95 91 88 84 81 3 99 96 94 92 89 86 83 4 98 94 91 87 84 81 78 4 98 95 92 89 86 83 80 5 95 91 88 84 81 78 74 5 96 92 89 86 83 80 77 6 91 87 84 81 78 74 71 6 93 89 86 83 80 77 74 7 88 84 81 78 75 71 68 7 90 86 83 80 77 74 71 8 84 81 77 74 71 68 65 8 86 83 80 77 74 71 68 9 81 77 74 71 68 65 62 9 83 80 77 74 71 68 65 10 77 73 71 68 65 62 59 10 80 77 74 71 68 65 62 (xi) Variation of Vne with altitude, main rotor r.p.m. and gross weight (see below). Required when Item 609 is installed. Required with Item 401(cc). VNE VS ALTITUDE PWR ON 93% NR T.O. GROSS WT (LBS.) 11000 12000 13000 OR BELOW ALTITUDE KIAS KIAS KIAS 2000 & Less 117* 3500 108* 4000 115* 106 5000 109* 100 6000 111* 104 95 8000 100 93 84 10000 89 82 73 12000 78 71 62 13500 70 62 14000 67 15000 62 *FOR IFR FLIGHT REDUCE THESE SPEEDS TO 107 KIAS 15 1H11 POWER OFF Vne DENSITY 81-91% Nr 92-104% Nr ALTITUDE KIAS KIAS SEA LEVEL 107 117* 2000 96 117* 4000 85 106 6000 74 95 8000 63 84 10000 -- 73 12000 -- 62 15000 -- 62 *FOR IFR FLIGHT REDUCE THESE SPEEDS TO 107 KIAS (xii) "BATTERY STARTS ON GROUND PROHIBITED" (in vicinity of T7 indicator on aircraft equipped with PT6T-6 engine. Placard not required if the DC/DC converter, P/N 58550- 10347-101, is installed.) (xiii) Variation of Vne with altitude, main rotor r.p.m. and gross weight (see below). Required when Item 608 is installed. Required with Item 401(aa). TAKEOFF Gross Weight 13000 lb. 12000 lb. 11000 lb. or Below ALTITUDE KIAS ALTITUDE KIAS ALTITUDE KIAS SEA LEVEL 117* SEA LEVEL 117* SEA LEVEL 117* Vne versus 2000 117* 3500 117* 5000 117* DENSITY 4000 106 4000 115* 6000 111* ALTITUDE 6000 95 6000 104 8000 100 POWER ON 8000 84 8000 93 10000 89 93% Nr 10000 73 10000 82 12000 78 12000 62 12000 71 14000 67 - - 13500 62 15000 62 *FOR IFR FLIGHT REDUCE THESE SPEEDS TO 107 KIAS POWER OFF Vne DENSITY 81-91% Nr 91-104% Nr ALTITUDE KIAS KIAS SEA LEVEL 107 117* 2000 96 117* 4000 85 106 6000 74 95 8000 63 84 10000 -- 73 12000 -- 62 15000 -- 62 *FOR IFR FLIGHT REDUCE THESE SPEEDS TO 107 KIAS 1H11 16 NOTE 4. The hoist (Item 603) and the cargo sling (Item 602) are special purpose equipment and are to be operated in accordance with the limitations described in CAR 8 or FAR 133 as applicable. Information concerning the operating limitations is also contained in Items 401(b), 401(c), 401(r), 401(h), 401(t), 401(u), 401(z), and (x). NOTE 5. The cabin floor area for Model S-58C is structurally satisfactory for a uniformly distributed loading of 200 p.s.f. between Stations 112 and 246 and for 100 p.s.f. between Stations 246 and 296 when used for cargo purposes. NOTE 6. Military model CH-34A (formerly H-34A), CH-34C (formerly H-34C), VH-34C (formerly H-34C), HH-34F (formerly HUS-1G), UH-34D (formerly HUS-1), UH-34E (formerly HUS-1A), VH-34D (formerly HUS- 1Z), SH-34G (formerly HSS-1), SH-34H (formerly HSS-1F), SH-34J (formerly HSS-1N), UH-34G and UH- 34J aircraft manufactured by Sikorsky Aircraft may be converted to models of the S-58 type shown on page 1 provided the converted aircraft conforms to a specific model in accordance with FAR 21.183(d). Any serial number in the "Serial Numbers Eligible" sections which has a "D" suffix applies only to the aircraft having a nameplate with a "D" suffix and an aircraft with a nameplate bearing the same Arabic number without the suffix "D" is not eligible. NOTE 7. The following helicopters have been converted (reference: NOTE 6): Surplus Eligible For Serial Military Certification as Number Model Civil Model Modifier 58-112 H34C S58E Chicago Helicopters Airways Chicago, Illinois 58-269 CH34C S58E Heli-Crane, Inc. Maryland Heights, Missouri 58-279 H34A S58E Carson Helicopters, Inc. Perkasie, Pennsylvania 58-317 CH34C S58E Chicago Helicopters Airways 58-328 H34A S58ET Sikorsky Aircraft Stratford, Connecticut 58-336 H34A S58E Imperial Airways, Inc. South St. Paul, Minnesota 58-354 H34A S58ET Sikorsky Aircraft 58-374 H34A S58ET Sikorsky Aircraft 58-378 H34A S58ET Sikorsky Aircraft 58-412 CH34C S58E Chicago Helicopter Airways 58-437 S58B S58BT Sikorsky Aircraft 58-524 HUS-1 S58D Chicago Helicopter Airways 58-531 CH34C S58J Pacific Crown Aviation, Inc. 58-540 CH34C S58E Chicago Helicopter Airways 58-601 H34A S58ET Sikorsky Aircraft 58-673 CH34C S58ET Orlando Helicopter Airways, Inc. P.O. Box 2802, Orlando, Florida 58-658 UH34J S58BT Chicago Helicopter Airways 58-692 S58B S58BT Sikorsky Aircraft 58-700 S58B S58BT Sikorsky Aircraft 58-721 H34A S58ET Sikorsky Aircraft 58-727 H34G S58ET Chicago Helicopter Airways 58-730 S58H Pacific Crown Aviation 58-735 S58J Edward Chopot 58-738 CH34C S58E Chicago Helicopter Airways 58-740 H34G S58E Carson Helicopters, Inc. 58-743 UH34J S58B Chicago Helicopter Airways 58-750 H34A S58ET Hawaii Helicopter International 58-761 HSS-1 S58B Moore Aviation, Inc. 58-775 S58B S58ET Sikorsky Aircraft 17 1H11 Surplus Eligible For Serial Military Certification as Number Model Civil Model Modifier 58-777 HSS-1 S58B Carson Helicopters, Inc. 58-780 H34A S-58ET Hawaii Helicopter International Lihue, Hawaii 58-787 UH34D S58D Chicago Helicopter Airways 58-827 H34A S58ET Sikorsky Aircraft 58-855 H34G S58ET Sikorsky Aircraft 58-856 H34G S58E Hawaii Helicopter International 58-869 CH34C S58J Edward Chopot Hamilton, Montana 58-879 H34A S58ET Sikorsky Aircraft 58-926 HSS1N S58B Carson Helicopters, Inc. 58-941 CH34C S58E Chicago Helicopter Airways 58-956 H34A S58ET Sikorsky Aircraft 58-960 H34A S58JT Utility Helicopters, Inc. Long Beach, California 58-1070 H34A S-58ET Sikorsky Aircraft 58-1071 H34A S58ET Sikorsky Aircraft 58-1091 H34A S58ET Sikorsky Aircraft 58-1097 H34G S58E Imperial Airways, Inc. 58-1105 H34G S58E Imperial Airways, Inc. 58-1112 H34A S58ET Sikorsky Aircraft 58-1117 H34A S58ET Sikorsky Aircraft 58-1120 H34A S58ET Sikorsky Aircraft 58-1122 H34A S58ET Sikorsky Aircraft 58-1124 H34A S58ET Sikorsky Aircraft 58-1126 H34A S58ET Sikorsky Aircraft 58-1128 H34A S58ET Sikorsky Aircraft 58-1129 H34A S58ET Sikorsky Aircraft 58-1147 HUS-1 S58D Carson Helicopters, Inc. 58-1148 HU34D S58D Carson Helicopters, Inc. 58-1158 SH34J S58BT Carson Helicopters, Inc. 58-1186 H34A S58JT Utility Helicopters, Inc. 58-1193 UH34D S58D Orlando Helicopter Airways, Inc. 58-1214 HUS-1 S58D Chicago Helicopter Airways 58-1225 UH34D S58B Chicago Helicopter Airways 58-1227 HUS-1 S58D Chicago Helicopter Airways 58-1272 S58J 58-1402 HUS-1 S58D Carson Helicopters, Inc. 58-1438 UH34D S58D Chicago Helicopter Airways 58-1439 HUS-1 S58D Carson Helicopters, Inc. 58-1458 H34A S58ET Sikorsky Aircraft 58-1459 H34A S58E(J) Bering Associates Anchorage, Alaska 58-1461 UH-34D S58D John A. Haertsch Tucson, Arizona 58-1464 HUS-1 S58D Carson Helicopters, Inc. 58-1487 UH34D S58D Chicago Helicopter Airways 58-1491 HUS-1 S58D Carson Helicopters, Inc. 58-1492 UH34A S58D Chicago Helicopter Airways 58-1493 H34A S58ET Sikorsky Aircraft 58-1503 H34A S58ET Sikorsky Aircraft 58-1514 H34 S58ET Sikorsky Aircraft 58-1519 UH34D S58DT Chicago Helicopter Airways 1H11 18 Surplus Eligible For Serial Military Certification as Number Model Civil Model Modifier 58-1527 H34G S58ET Orlando Helicopter Airways 58-1536 H34A S58ET Sikorsky Aircraft 58-1537 H34A S58ET Sikorsky Aircraft 58-1538 H34A S58ET Sikorsky Aircraft 58-1547 H34A S58ET Sikorsky Aircraft 58-1551 H43A S58E Orlando Helicopter Airways, Inc. 58-1561 H34A S58ET Sikorsky Aircraft 58-1564 H34G S58ET Orlando Helicopter Airways, Inc. 58-1565 H34A S58ET Sikorsky Aircraft 58-1567 H34G S58E Chicago Helicopter Airways 58-1570 H34A S58ET Sikorsky Aircraft 58-1575 H34A S58E Lake Line Helicopters, Inc. Eden Prairie, Minnesota 58-1576 H34G S58E Utility Helicopters, Inc. 58-1589 H34G S58ET Orlando Helicopter Airways, Inc. 58-1606 H34A S58ET Sikorsky Aircraft 58-1607 CH34A S58E Helicopter Minut Men, Inc. Columbus, Ohio 58-1613 H34A S58ET Sikorsky Aircraft 58-1618 H34G S58E Chicago Helicopter Airways 58-1626 H34A S58ET Sikorsky Aircraft 58-1627 H34A S58E Olympic Helicopters Inc. Boeing Field, Seattle, Washington 58-1630 H34A S58ET Sikorsky Aircraft 58-1632 H34A S58ET Sikorsky Aircraft 58-1637 H34A S58ET Sikorsky Aircraft 58-1639 H34A S58ET Sikorsky Aircraft 58-1646 H34A S58ET Sikorsky Aircraft 58-1648 CH34A S58E Western Helicopters, Inc. Rialto, California 58-1657 H34A S58ET Sikorsky Aircraft 58-1659 HUS-1 S58ET Sikorsky Aircraft 58-1663 H34G III S58JT Air Aisa Ltd. 58-1672 H34G S58ET Orlando Helicopter Airways, Inc. 58-1673 H34G S58ET Orlando Helicopter Airways, Inc. 58-1677 H34G-III S58JT Air Asia, Ltd. 58-1720 UH34D S58D 4C's Helicopters, Inc. Martinez, California 58-1732 H34G S58E(J) Trans Alaska Helicopters Anchorage, Alaska 58-1787 UH34D S58D Orlando Helicopter Airways, Inc. 58-1809 UH34D S58D Carson Helicopters, Inc. NOTE 8. The applicant for an airworthiness certificate for military versions of the S-58 series rotorcraft will be required to provide the information to the local Manufacturing Inspection District Office (MIDO), Manufacturing Inspection Field Representative (MIFR), or Manufacturing Inspection Satellite Office (MISO). After February 24, 1981, Sikorsky Aircraft will not provide Type Design information regarding eligibility and modifications to be accomplished for airworthiness certification of any military version of the S-58 type rotorcraft. 19 1H11 NOTE 9. Except for a difference in Maximum Weight, the following models are identical to each other including all limits: S-58F identical to S-58B S-58G identical to S-58C S-58FT identical to S-58BT S-58H identical to S-58D S-58HT identical to S-58DT S-58J identical to S-58E S-58JT identical to S-58ET NOTE 10. Initially the Pratt & Whitney Aircraft PT6T-3 engine installation in the S -58B and S-58E was approved via a Supplemental Type Certificate (SH71EA dated 15 April 1971, amended 27 May 1971, 5 November 1971 and 21 January 1972) issued to Sikorsky Aircraft. Subsequently, Sikorsky Aircraft requested that the turbine configured aircraft be added to Helicopter Type Certificate 1H11 as new models, which was accomplished on 18 February 1972 and 27, March 1972. Special service instructions are provided in SSI 129A for conversion to turbine aircraft. NOTE 11. The Pratt & Whitney Aircraft PT6T-3 engine may be installed in a military aircraft which has been converted to either an S-58B, S-58D, S-58E, S-58H or S-58J under the provisions of NOTE 6, 7, and 8. NOTE 12. Supplement No. 16 to Item 401(a) became Rotorcraft Flight Manual SA4047-17, Item 401(s) for S-58T series configuration II. See certification basis. NOTE 13. Sikorsky Modification Kit No. 58070-30000 covers Pratt & Whitney Aircraft PT6T-6/PT6T-3 power package replacement. NOTE 14. Use of the combustion heater installed on rotorcraft equipped with Pratt & Whitney Aircraft PT6T-6 or PT6T-3 engine power package is prohibited unless the heater installation is FAA approved for operation with turbine engine type fuels. ...END... ``` ## ADs (23, in force first) - [AD 2024-12-10](https://openairdocs.org/ad/2024-12-10): Main Rotor Drive System · Centerpointe Aerospace S-58BT, S-58DT, S-58ET and 3 more. Effective Aug 26, 2024 - [AD 2023-11-07](https://openairdocs.org/ad/2023-11-07): Ground Proximity System · Airbus Helicopters 47, 206, 210 and 237 more. Effective Jun 22, 2023 - [AD 95-26-08](https://openairdocs.org/ad/95-26-08): Main Rotor Shaft · Sikorsky S-58A, S-58B, S-58BT and 12 more. Effective Jan 4, 1996 - [AD 95-10-09](https://openairdocs.org/ad/95-10-09): Transmission Main Gear Box Ring Gear · Sikorsky S-58A, S-58B, S-58BT and 12 more. Effective Jun 16, 1995 - [AD 94-12-07](https://openairdocs.org/ad/94-12-07): Gear Box Assembly · Sikorsky S-58BT, S-58DT, S-58ET and 3 more. Effective Aug 1, 1994 - [AD 89-25-01](https://openairdocs.org/ad/89-25-01): Engine Fire Extinguishing System · Sikorsky S-58A, S-58B, S-58BT and 12 more. Effective Dec 26, 1989 - [AD 60-17-03 R1](https://openairdocs.org/ad/60-17-03-R1): Main Rotor Blade Assemblies · Sikorsky S-58A, S-58B, S-58BT and 12 more. Effective Feb 2, 1989 - [AD 64-02-06 R1](https://openairdocs.org/ad/64-02-06-R1): Pylon and Tail Cone Fittings · Sikorsky S-58A, S-58B, S-58BT and 12 more. Effective Dec 27, 1988 - [AD 86-25-05](https://openairdocs.org/ad/86-25-05): Gearbox Pinions Or Gears · Sikorsky S-58A, S-58B, S-58BT and 12 more. Effective Jan 5, 1987 - [AD 85-17-08](https://openairdocs.org/ad/85-17-08): Main Rotor Head Bolts · Sikorsky S-58A, S-58B, S-58BT and 12 more. Effective Jan 13, 1986 - [AD 82-01-07](https://openairdocs.org/ad/82-01-07): Horizontal Hinge Pins · Sikorsky S-58A, S-58B, S-58BT and 12 more. Effective Feb 1, 1982 - [AD 78-21-05](https://openairdocs.org/ad/78-21-05): Tail Rotor Blades · Sikorsky S-58BT, S-58DT, S-58ET and 3 more. Effective Nov 30, 1978 - [AD 78-05-01](https://openairdocs.org/ad/78-05-01): Fuel Bypass Lines · Sikorsky S-58BT, S-58DT, S-58ET and 3 more. Effective Mar 31, 1978 - [AD 74-15-06](https://openairdocs.org/ad/74-15-06): Tail Rotor Gear Box · Sikorsky S-58A, S-58B, S-58BT and 12 more. Effective Dec 30, 1977 - [AD 75-13-01](https://openairdocs.org/ad/75-13-01): Main Rotor Assembly · Sikorsky S-58A, S-58B, S-58BT and 12 more. Effective May 20, 1977 - [AD 59-16-04](https://openairdocs.org/ad/59-16-04): Damper Trunnion Bolt · Sikorsky S-58A, S-58B, S-58BT and 12 more. Effective Apr 8, 1975 - [AD 75-07-07](https://openairdocs.org/ad/75-07-07): Emergency Hatch Handles · Sikorsky S-58B, S-58BT, S-58D and 9 more. Effective Apr 8, 1975 - [AD 75-07-08](https://openairdocs.org/ad/75-07-08): Tail Assembly · Sikorsky S-58A, S-58B, S-58BT and 12 more. Effective Apr 8, 1975 - [AD 66-19-04](https://openairdocs.org/ad/66-19-04): Tail Rotor Blades · Sikorsky S-58A, S-58B, S-58BT and 20 more. Effective Aug 14, 1966 - [AD 61-01-03](https://openairdocs.org/ad/61-01-03): Input Bevel Gear · Sikorsky S-58A, S-58B, S-58BT and 12 more. Effective Dec 30, 1960 - [AD 60-24-04](https://openairdocs.org/ad/60-24-04): Electrical Cable · Sikorsky S-58A, S-58B, S-58BT and 12 more. Effective Nov 28, 1960 - [AD 57-19-02](https://openairdocs.org/ad/57-19-02): Engine Cooling Fan Assembly · Sikorsky S-58A, S-58B, S-58BT and 12 more - [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 ## Registered aircraft by registry model (OpenAirDocs) - [Sikorsky S-58JT](https://openairdocs.org/model/sikorsky-s-58jt): 5 aircraft (registry codes 8141807, 8141838) - [Sikorsky S-58C](https://openairdocs.org/model/sikorsky-s-58c): 3 aircraft (registry code 8141806) - [Sikorsky S-58ET](https://openairdocs.org/model/sikorsky-s-58et): 3 aircraft (registry code 8141803) - [Sikorsky S58E](https://openairdocs.org/model/sikorsky-s58e): 3 aircraft (registry code 8141811) - [Sikorsky S-58](https://openairdocs.org/model/sikorsky-s-58): 2 aircraft (registry code 8141801) - [Sikorsky S-58H](https://openairdocs.org/model/sikorsky-s-58h): 2 aircraft (registry code 8141839) - [Sikorsky S-58J](https://openairdocs.org/model/sikorsky-s-58j): 2 aircraft (registry code 8141814) - [Sikorsky S-58B](https://openairdocs.org/model/sikorsky-s-58b): 1 aircraft (registry code 8141804) - [Sikorsky S-58BT](https://openairdocs.org/model/sikorsky-s-58bt): 1 aircraft (registry code 8141840) - [Sikorsky S-58D](https://openairdocs.org/model/sikorsky-s-58d): 1 aircraft (registry code 8141808) - [Sikorsky S-58DT](https://openairdocs.org/model/sikorsky-s-58dt): 1 aircraft (registry code 8141842) - [Sikorsky S-58T](https://openairdocs.org/model/sikorsky-s-58t): 1 aircraft (registry code 8141800) - [Sikorsky S-58A](https://openairdocs.org/model/sikorsky-s-58a): 0 aircraft (registry code 8141802) - [Sikorsky S-58E](https://openairdocs.org/model/sikorsky-s-58e): 0 aircraft (registry code 8141809) - [Sikorsky S-58F](https://openairdocs.org/model/sikorsky-s-58f): 0 aircraft (registry code 8141837) - [Sikorsky S-58FT](https://openairdocs.org/model/sikorsky-s-58ft): 0 aircraft (registry code 8141805) - [Sikorsky S-58G](https://openairdocs.org/model/sikorsky-s-58g): 0 aircraft (registry code 8140709) - [Sikorsky S-58HT](https://openairdocs.org/model/sikorsky-s-58ht): 0 aircraft (registry code 8141841) ## STCs approved under this data sheet (38) - [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 SR04549AT](https://openairdocs.org/stc/SR04549AT): Conversion of the Pratt & Whitney PT6T-3 to the PT6T-3B configuration. Centerpointe Aerospace - [STC SA5783NM](https://openairdocs.org/stc/SA5783NM): Fabrication of Onboard Systems Model 7 CROPHAWK spray flow measuring system.. Onboard Systems International - [STC SH5780NM](https://openairdocs.org/stc/SH5780NM): Fabrication of Onboard Systems model E-46 cargo hook load weigh system.. Onboard Systems International - [STC SR02704SE](https://openairdocs.org/stc/SR02704SE): Installation and maintenance of the Sunspot 36 and 46 series lights. AeroLED's Holdings LLC - [STC SR04483CH](https://openairdocs.org/stc/SR04483CH): Installation of NASI NREM18M Air Conditioning Module. National Aircraft Service Inc. (NASI) - [STC SR00359BO](https://openairdocs.org/stc/SR00359BO): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [STC SH464NE](https://openairdocs.org/stc/SH464NE): Installation of an Alternate Float Bottle System.. California Helicopter Parts Inc - [STC SH513NE](https://openairdocs.org/stc/SH513NE): Replacement of auxiliary fuel boost pumps with Parker Hannifin-Airborne inline auxiliary fuel booster pump. California Helicopter Parts Inc - [STC SR02394AK](https://openairdocs.org/stc/SR02394AK): Replacement of existing landing and/or hover light bulbs with Light Emitting Diode (LED) lighting system. Seaplanes North LLC - [STC SR03310CH](https://openairdocs.org/stc/SR03310CH): Installation of NASI Air Conditioning Module. National Aircraft Service Inc - [STC SA2693NM](https://openairdocs.org/stc/SA2693NM): Installation of Electronics International digital volt/amp gauges and accessories.. Electronics International Inc. - [STC SR00968CH](https://openairdocs.org/stc/SR00968CH): Reduce take-off gross weight from 13,000 to 12,500 lbs. During passenger and internal cargo carrying operations. (S-58ET s/n 58-855). Midwest Truxton International, Inc. - [STC SR00889CH](https://openairdocs.org/stc/SR00889CH): Reduction of standard passenger seating from sixteen to nine seats or less.. Construction Helicopters, Inc - [STC SR00042SE](https://openairdocs.org/stc/SR00042SE): Modification to allow the use of Configuration II aircraft performance limits.. Glacier Helicopter Inc - [STC SA1626NM PAGE 2](https://openairdocs.org/stc/SA1626NM%20PAGE%202): Installation of Electronics Int'l Digital EGT/CHT Instruments and accessories. (201 Series). Electronics International - [STC SH8030SW](https://openairdocs.org/stc/SH8030SW): Installation of an engine fire detection system.. California Helicopter Intn'l, Inc - [STC SH2212NM](https://openairdocs.org/stc/SH2212NM): Installation of Silver Instruments Fueltron IIIPT-IGS, IIIPT-IPS, IIIPT-ILS, IIIPT-IKS digital fuel flow indicating system.. Arnav Systems Inc - [STC SH770NW](https://openairdocs.org/stc/SH770NW): Installation of a weighing system.. Onboard Systems - [STC SH4570NM](https://openairdocs.org/stc/SH4570NM): Approval for takeoffs and landings up to and including 12,000 feet density altitude is authorized.. Air One Helicopters, Inc - [STC SA4302NM](https://openairdocs.org/stc/SA4302NM): Installation of Electronics Int'l digital automatic engine analyzer.. Electronics International - [STC SH4539NM](https://openairdocs.org/stc/SH4539NM): Establish a nine passenger seat configuration.. Air One Helicopters, Inc - [STC SH1010GL](https://openairdocs.org/stc/SH1010GL): Reduction of standard passenger seating from sixteen to nine seats or less.. Brainerd Helicopters, Inc - [STC SH4507NM](https://openairdocs.org/stc/SH4507NM): Approval for takeoffs and landings up to and including 12,000 feet densiy altitude is authorized.. Los Angeles County Sheriff's Department Aero Bureau - [STC SA513NE](https://openairdocs.org/stc/SA513NE): Replacement of auxiliary fuel boost pumps with Parker-Hannifin-Airborne in-line auxiliary fuel booster pumps.. California Helicopter International - [STC SH4477NM](https://openairdocs.org/stc/SH4477NM): Installation of FC/FT-10 digital fuel flow indicating system.. Arnav Systems, Inc - [STC SH1215GL](https://openairdocs.org/stc/SH1215GL): Reduction of standard passenger seating from sixteen to nine seats or less.. Midwest Truxton International, Inc. - [STC SH142WE](https://openairdocs.org/stc/SH142WE): Installation of electronic weighing system c-40.. Onboard Systems - [STC SH2572NM](https://openairdocs.org/stc/SH2572NM): Increased takeoff and landing density altitude limit.. North American Heli Svc Inc - [STC SH919GL](https://openairdocs.org/stc/SH919GL): Removal of all seats with the exception of two (2) passenger seats at station 93 and two (2) crew seats directly above.. Jet Services, Inc - [STC SH661GL](https://openairdocs.org/stc/SH661GL): Reduction of passenger seat con- figuration from 16 to 9 passenger seats by removing the two-man seat(P/N 1650-61339) and the five-man seat (P/N 1607-5096-1).. Air 76 Inc - [STC SH453NW](https://openairdocs.org/stc/SH453NW): Installation of an electronic weighing system (for monitoring cargo weight). Measurement Systems Intl - [STC SH1194EA](https://openairdocs.org/stc/SH1194EA): Conversion from original 12 passenger configuration to a 9 passenger configuration.. Carson Helicopters Inc - [STC SH268WE](https://openairdocs.org/stc/SH268WE): Installation of stainless steel fire shields around aluminum engine mount fittings (P/N S1620-61435) of HSS, HUS, H-34 military series helicopters. (S-58 SERIES Military versions HSS, HUS, H-34). TBM, Inc - [STC SH206GL](https://openairdocs.org/stc/SH206GL): Installation of HUS-1 titanium firewall with intumescent coating.. Midwest Heli Airways Inc - [STC SH109GL](https://openairdocs.org/stc/SH109GL): Installation of CH-34A titanium firewall with intumescent coating.. Lake Line Helicopters Inc - [STC SA77GL](https://openairdocs.org/stc/SA77GL): Installation of Bendix weather radar RDR-1200.. Chicago Heli Airways Inc - [STC SH3NE](https://openairdocs.org/stc/SH3NE): Norton AC3093K radome installation and Bendix RDR 110 radar system installation.. Oxford Avionics, Inc --- 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.