# TCDS H1NM: Wright Kevin - Type: Type certificate data sheet - Status: Current - Holder: Wright Kevin - Revision: 1 - Revised: March 19, 1984 - Product: Aircraft, Rotorcraft - Certification basis: Part 21 - Data sheet PDF: https://openairdocs.org/files/sha256/88/0f/880ff32b4df801eb1cae7a82a219fb8ad40cd1a1b4336f3f88ac758b05ed4715 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/7E5B0D19C063E9A2852567150053A28F.0001 - Page: https://openairdocs.org/tcds/H1NM ## Models (1) As the data sheet lists them. - H-21B ## 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 Rev. No. 1 - - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H1NM Revision 1 WRIGHT (Vertol) H-21B March 19, 1984 TYPE CERTIFICATE DATA SHEET NO. H1NM This data sheet which is a part of type certificate No. H1NM 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 Kevin Wright P.O. Box 1254 San Juan Capistrano, CA 92693 1. Model U.S. Air Force H21B (Restricted Category) approved October 5, 1983 Engine Wright R-1820-103A Fuel 100/130 or 115/145 maximum grade Engine limits HP RPM MAP ALT. (ft) Low Ratio Supercharger Maximum Continuous 1275 2500 46.5 S.L. 1275 2500 45.5 3000 Take-Off (30 min) 1425 2700 51.5 S.L. 1425 2700 50.5 1300 High Ratio Supercharger Maximum Continuous 980 2500 43.0 10,800 Take-Off (5 min) 1100 2600 50.0 9,800 Rotor Limits Power On Power Off 233 to 258 rpm 250 to 300 rpm Airspeed limits Vne (never exceed) 110 knots IAS (See Note 2(b) for required placard) C.G. range Sta. 319.0 to Sta. 339.5 at 15,200 lb. Sta. 319.0 to Sta. 360.5 at 13,500 lb. or less (See Center of Gravity Envelope) Datum 100 inches forward of forward rotor centerline H1NM 2 319 325 335 339.5 345 355 360.5 10,000 11,000 12,000 13,000 14,000 15,000 13,500 pounds 15,200 pounds Between RotorscL Gross Weight (pounds) Balance Station (inches from Datum Line) Center of gravity envelope Maximum weight 15,200 lb. Minimum Crew 1 (pilot) Fuel capacity 300 gallon usable, fully serviced 304 gallon Oil capacity 21.5 gallon Other Operating Limitations USAF T.O. 1H-21 (C) B-1 Flight Manual Serial Nos. Eligible All USAF serial numbers with AFTO Form 100A (Accessory Replacement Record) which completely describe the maintenance history of the helicopter. Certification basis FAR 21.25(a)(2). Type Certificate No. H1NM dated October 5, 1983, issued for the purpose of: Carriage of external loads, agricultural (frost control), and banner towing. Date of application for Type Certificate: March 4, 1983 Production basis None. No helicopters may be produced under this approval. Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: (a) USAF T.O. IH-21(c) B-1 Flight Manual When conducting external load operations the cargo sling must be installed in accordance with Section V of T.O. IH-21-2-2 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. 3 H1NM NOTE 2. The following placards must be displayed in the cockpit in full view of the pilot: (a) This helicopter must be operated in accordance with the operating limitations noted in USAF T.O. 1H-21 (C) B-1 Flight Manual. (b) ALT (FT) VNE IAS KNOTS 2500 rpm 2400 rpm 2300 rpm S.L. 110 101 93 2000 97 89 81 4000 85 77 69 6000 73 65 - 8000 60 60 - 10,000 60 60 - NOTE 3. Information essential to the proper maintenance of the helicopter including retirement time of critical components is contained in T.O. 1H-21(C) B-6. The values of retirement or service life cannot be increased without FAA engineering approval. NOTE 4. Prior to civil airworthiness certification, the provisions of AD 58-20-4, AD 60-23-5, AD 64-19-6, AD 64-27-4, AD 68-6-1, and any follow-on applicable ADs must be accomplished. ...END... ``` ## ADs None name its models. ## STCs approved under this data sheet (1) - [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.