# TCDS H8WE: Schneck Jack A. - Type: Type certificate data sheet - Status: Current - Holder: Schneck Jack A. - Revision: 2 - Revised: March 5, 1979 - Product: Aircraft, Rotorcraft - Certification basis: Part 21 - Data sheet PDF: https://openairdocs.org/files/sha256/b9/2c/b92cf3a61d64de4b0a41fdff8f7388fc9925d2069f68dc327c070fda90a49418 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/6AE272F97D7ECBCE8525671500533392.0001 - Page: https://openairdocs.org/tcds/H8WE ## Models (1) As the data sheet lists them. - CH-21C ## 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 Rev. No. 2 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H8WE Revision 2 SCHNECK Vertol (Army) CH-21C 5 March 1979 TYPE CERTIFICATE DATA SHEET NO. H8WE This data sheet which is a part of type certificate No. H8WE 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 Jack A. Schneck Route 1, Box 114 Williams, California 95987 I - Model U.S. Army CH-21C (Restricted Category) approved 19 November 1971 Engine Wright R-1820-103 Fuel 115/145 or 100/130 min. grade Aviation Gasoline Engine limits MP Low Impeller Gear Ratio HP RPM IN HG ALT. Maximum Continuous 1275 2500 46.5 S.L. Maximum Continuous 1275 2500 45.5 2200 Take-Off (5 min) 1425 2700 51.5 S.L. Take-Off (5 min) 1425 2700 50.5 1300 (Straight line manifold pressure variation with altitude). NOTE: Operation at 2600 RPM prohibited. High Impeller Gear Ratio Maximum Continuous 980 2500 43.0 10,800 Maximum Continuous 980 2500 42.0 15,600 Take-Off (5 min) 1100 2600 50.0 9,800 Take-Off (5 min) 1100 2600 49.0 13,000 (Straight line manifold pressure variation with altitude). NOTE: Operation at 2700 RPM prohibited. Rotor Limits and Power Off (Rotor Tach.) Power On (Engine Tach.) Engine Operating Maximum 258 RPM Maximum 2500 RPM Speeds Minimum 233 RPM Minimum 2300 RPM Maximum 2700 RPM; 30 minute limit Airspeed limits Vne (Never exceed) 102 knots IAS Sea Level (See FAA approved Rotorcraft Flight Manual Supplement). C.G. range 35 in. fwd. (Sta. 319) to 6.5 in. aft (Sta. 360.5) of datum Datum Point midway between rotors (Sta. 354) H8WE 2 Maximum weight 13,500 pounds (See FAA approved Rotorcraft Flight Manual Supplement for variations with altitude and External Loads). Minimum Crew 1 (pilot) Fuel capacity Main Fuel Tank 304 Gal. (Sta. 395.0) (300 Gal. usable in forward flight) Oil capacity 21.5 Gal. (Sta. 540.3) Other Operating Department of the Army Technical Manual TM 55-1520-205-10 "Operator's Limitations Manual CH-21 Helicopter" dated 1964 and Schneck FAA approved Flight Manual Supplement dated 19 November 1971 or Subsequent FAA Approved Revision. Serial Nos. Eligible All Army Serial Nos. Certification basis FAR 21.25(a)(2) effective 1 February 1965 Type Certificate No. H8WE issued 19 November 1971 for special purposes of: Carriage of external loads per FAR 133 and Agriculture Frost Control by air agitation. Date of Application for Type Certificate 2 April 1971. Production basis None. No helicopter may be produced under this type approval. Prior to original Certification of each aircraft, an FAA representative must perform an inspection for workmanship, materials, and conformity with the approved type design. Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis) must be installed in the helicopter for certification. In addition, equipment necessary for the particular special purpose must be installed. 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 installed in clear view of the pilot. "This helicopter must be operated in compliance with the operating limitations specified in Department of the Army Technical Manual TM 55-1520-205-10 and the FAA approved supplement thereto." For additional placards see flight manual supplement. NOTE 3. Prior to civil airworthiness certification, the following mu st be accomplished: (a) Modifications in accordance with FAA Sealed Jack A. Schneck Drawings AJS, AJS-A, 1JS, 2JS, 3JS, 4JS and 5JS. (b) The provisions of AD 60-7-8. NOTE 4. This model helicopter must be serviced and maintained in compliance with Department of the Army Technical Manual TM 55-1520-205-20, "Organizational Maintenance Manual CH-21C helicopter" dated 1964. .....END.... ``` ## ADs None name its models. ## STCs approved under this data sheet (2) - [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 SH593NW](https://openairdocs.org/stc/SH593NW): Installation of in-flight blade monitoring system.. Columbia Helicopters 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.