# TCDS H12WE: Helitec Corporation - Type: Type certificate data sheet - Status: Current - Holder: Helitec Corporation - Revision: 1 - Revised: January 24, 2005 - Product: Aircraft, Rotorcraft - Certification basis: Part 21 - Data sheet PDF: https://openairdocs.org/files/sha256/08/f4/08f4b37d8eaf4a1b74e2cff12b0147fec269ee1128524067626885f02c622726 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/FA59AA5B5F12473086256F9C005504E1.0001 - Page: https://openairdocs.org/tcds/H12WE ## Models (1) As the data sheet lists them. - H-S-1N ## 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 H12WE Revision 1 Helitec Corporation H-S-1N Revised January 24, 2005 TYPE CERTIFICATE DATA SHEET NO. H12WE This data sheet which is a part of type certificate No. H12WE prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: This Type Certificate (TC) has been designated as ABANDONED (See Note 6) Type Certificate Holder Record: Helitec Corporation 4930 E. Falcon Dr. Mesa, Arizona 85205 I. Model H-S-1N (Restricted Category) approved April 28, 1980 Engine Wright Cyclone, R-1820-84A/84C Fuel 100/130 or 115/145 min. grade aviation gasoline Engine limits HP RPM M.P. IN.HG. ALT. Fuel Grade 115/145 Maximum continuous 1275 2500 47.5 S.L. Maximum continuous 1275 2500 46.0 3500 ft. Takeoff 1525 2800 56.5 S.L. Takeoff 1525 2800 55.5 700 ft. (Straight Line Manifold Pressure variation with altitudes shown) Fuel Grade 100/130 Maximum continuous 1275 2500 47.5 S.L. Maximum continuous 1275 2500 46.0 3500 ft. Takeoff 1325 2800 50.0 S.L. Takeoff 1325 2800 49.5 2000 ft. (Straight Line Manifold Pressure variation with altitudes shown) Rotor Limits Maximum 258 r.p.m. Minimum 170 r.p.m. Airspeed limits Vne (Never exceed) 120 CAS (See Note 2 for required placard) C.G. range (+130.7) to (+146.7) 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 Maximum weight 12,700 Minimum Crew 1 (pilot) (See note 2) Fuel capacity Location Volume (Gal.) Arm (Inches) Fwd. Tank 100.5 +121 Center Tank 70.0 +184 Aft Tank 92.0 +223 Page No. 1 2 3 Rev. No. 1 1 1 H12WE Page 2 of 3 Revision 1 Oil capacity 12.4 gals. (+75) Rotor Blade & Control Movements For rigging information refer to Maintenance Manual SA4045-15 Other Operating Limitations See Flight Manual NAVWEP-01-230-HLAA-1, TO1H-34H(J)-15-16, dated 6/6/73. Serial Nos. Eligible All Navy serial numbers DATA PERTINENT TO ALL MODELS: Certification Basis FAR 21.25(a)(2) effective February 1, 1965. Type Certificate No. H12WE issued April 28, 1980 for the purpose of: Carriage of external loads, per FAR 133 Date of application for Type Certificate was February 8, 1980 The military helicopters certificated restricted category under Type Certificate No. H12WE with aluminum engine mount fittings P/N 1620-61435-series are not eligible for standard category S-58 configuration. Prior to standard airworthiness certification, information regarding eligibility and modification to be accomplished should be obtained from Sikorsky Aircraft. Production Basis None. Prior to original airworthiness certification of each aircraft, FAA personnel must perform an airworthiness inspection determining condition for safe operation and determine the applicant has conducted a satisfactory flight test. See NOTE 4 for data on Service Bulletins and ADs. Equipment: The basic required equipment as prescribed for the special purpose operation and as necessary for safe operation must be installed in each helicopter. NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions, when necessary, must be in each helicopter at the time of original airworthiness certification and at all times thereafter. NOTE 2. The following placard must be prominently displayed in the cockpit in full view of the pilot (On Instrument Panel): (a) "Avoid fast turns, 15 sec. minimum for 360 degrees." (b) "During extended hovering, close windows and doors and turn vent system on. Close left windows during starting and taxiing." (c) "Avoid taxi turns below 2400 engine r.p.m." (d) "Never exceed speeds. Variation on Vne with altitude, engine r.p.m. and manifold pressure." 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 5,000 - - - - 60 37.0 76 41.0 90 F.T. 10,000 - - - - - - - - - - - - 63 F.T. (e) "Maximum Approved Gross Weight 12,700 lbs." (f) "This helicopter must be operated in compliance with the operating limitations specified in the Navy Flight Handbook, NAVWEP 01-230-HLAA-1, TO1H-34H(J)-15-16, dated June 6, 1973." Revision 1 Page 3 of 3 H12WE (g) "This helicopter has been certified in the rest ricted category for External-Load Operations only." NOTE 3. Replacement times for life-limited parts are specified in Sikorsky S-58 Maintenance Manual Publication No. SA4045-15 Part IV, Section IV, revised March 1, 1971, unless superseded by appropriate Airworthiness Directives. The replacement period can not be extended without FAA approval. NOTE 4. Prior to civil airworthiness certifi cation, the following must be accomplished: (a) The provisions of the following ADs and all subsequent applicable ADs. ADs 57-19-02, 59-16-04, 60-17-03, 60-24-04, 61-01-03, 64-02-06, 66-19-04, 74-15-06, 75-07-07, 75-07-08 and 75-13-01. (b) The provisions of the following Sikorsky Servi ce Bulletins 58B: General-1, General-2, 10-2, 10-3, 10-5, 10-7, 10-10A, 15-1F, 15-2B, 15-3, 15-4H , 15-5C, 15-6A, 15-8, 15-14A, 20-10, 20-2, 20-6B, 20-7A, 20-9A, 20-10, 20-11, 20-12H, 20-14B, 20-15, 25-1, 30-1, 30-4, 35-1A, 35-2, 35-3B, 35-5A, 35-6, 35-7A, 35-8B, 35-9, 35-11, 35-16C, 35-17B , 35-18B, 35-19, 40-1, 40-2, 40-4, 65-1, 65-2A, 65-3B and 65-4A. (c) Deactivate Automatic Flight Control System if installed. NOTE 5. Maintenance will be accomplished in acco rdance to the S-58 Maintenance Manual SA4045-15. Component overhaul intervals shall be in accordance with "Sikorsky Aircraft Engineering Recommended and Customer Approved Component Overhaul Intervals and Replacement Times," Parts I and II, dated 5 September 1956. NOTE 6. This Type Certificate (TC) has been designated "ABANDONED". A “Notice of Intent To Designate as Abandoned Certain Type Certificates Issued in the Restricted Category,” was published by the Federal Aviation Administration (FAA) in the Federal Register on August 8, 2003 (68 FR 47379). That Notice listed this TC. The FAA received no comments on the published Notice. The FAA has been unable to contact this TC holder. Hence, the FAA has determined that this TC holder is not complying with its Continued Operational Safety (COS) responsibilities. Therefore, no additional aircraft will be added to this TC and no additional original airworthiness certificates will be issued based on this TC. The effectiveness of this TC is limited to those aircraft that received original airworthiness certification prior to the incorporation of this note (Date of Incorporation, January 24, 2005). Subsequently, if the TC holder is located and assumes their COS responsibilities, the restriction(s) imposed by this note may be lifted. ...END... ``` ## ADs None name its models. ## STCs approved under this data sheet (4) - [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 SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc. - [STC SA4005NM](https://openairdocs.org/stc/SA4005NM): Precise Flight Inc. Pulselite Control System. Precise Flight Inc - [STC SA4302NM](https://openairdocs.org/stc/SA4302NM): Installation of Electronics Int'l digital automatic engine analyzer.. Electronics International --- 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.