# TCDS H8NM: Smith Helicopters - Type: Type certificate data sheet - Status: Historical, Abandoned - Holder: Smith Helicopters - Revision: 1 - Revised: August 8, 2003 - Product: Aircraft, Rotorcraft - Certification basis: Part 21 - Data sheet PDF: https://openairdocs.org/files/sha256/79/30/79309d0599cd11ef795507c9561137494d18b14eacc5077ef42b5fc528cd559a - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/C05AA461FA46728D86256F9C005376CF.0001 - Page: https://openairdocs.org/tcds/H8NM ## Models (1) As the data sheet lists them. - UH-1E ## 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 H8NM Revision 1 SMITH HELICOPTERS UH-1E Revised January 24, 2005 TYPE CERTIFICATE DATA SHEET H8NM This data sheet, which is a part of Type Certificate No. H8NM, 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 13) Type Certificate Holder Record: Smith Helicopters 4800 Lakeridge Drive Ukiah, California 95482 Model U.S. Navy UH-1E (Restricted Category), approved February 4, 1985. Engine: Ly coming T53L11D Fuel: MIL-J-5624, Grade JP-4 or JP-5 Engine Limits: Torque Pressure Output Shaft Speed Exhaust Gas Temp. Gas Gen. Speed (P.S.I.) (R.P.M.) (°C) (R.P.M.) Takeoff (5 minutes) 50.0 (1100 h.p.) 6640 (101%) 638 25,200 (100.5%) Max Continuous 46.0 (900 h.p.) 6640 (101%) 621 24,700 (97.7%) (See Note 1) Rotor Limits: Power Off Power On Maximum 339 r.p.m. (Dual Tach Reading 104.5%) Maximum 324 r.p.m. (Dual Tach Reading 100%) Minimum 294 r.p.m. (Dual Tach Reading 91.0%) Minimum 310 r.p.m. (Dual Tach Reading 97%) Airspeed Limits: Never exceed speed 140 knots up to and including 7500 lbs. G.W. at sea level. Never exceed speed 110 knots from 7500 lbs. to 8500 lbs. G.W. at sea level. Never exceed speed 70 knots from 8500 lbs. to 9500 lbs. G.W. at sea level. Ref. NATOPS Flight Manual NAVAIR 01-110HCA-1. C.G. Range: (a) Longitudinal C.G. Limits (+126.7) to (+132.3) at 9500 lbs. (+125.5) to (+134.4) at 8500 lbs. (+125.0) forward limit at 8150 lbs. (+138.0) aft limit at 7000 lbs. See figure next page: Page No. 1 2 3 Rev No. 1 1 H8NM Page 2 of 3 C.G. Range (cont'd): Weight (Pounds) 125 128 131 13 4 137 9500 8500 7500 6500 5500 4500 Fus elage Sta tion (Inches) (b) Lateral C.G. Limits ± 4.7 in. from centerline of fuselage: Maximum Weight: 9500 lbs., All weight in excess of 8500 lbs. shall be external load only. Minimum Crew: 1 (Pilot) Maximum Cargo: See Flight Manual NAVAIR 01-110HCA-1 limits. Fuel Capacity: 242 gals (STA +136.5) See Note 2 for data on unusable fuel. Oil Capacity: 3.8 gals (STA +157) minimum oil 1 ½ gals. See Note 2 for data on undrainable oil. Other Operating Limitations: This aircraft must be operated in accordance with NATOPS Flight Manual NAVAIR 01-110HCA-1 and Avco/Lycoming FAA approved Maintenance Manual T5311-2 Engine performance data. Serial Numbers Eligible: All U.S. Navy serial numbers. Certification Basis: FAR 21.25(a)(2), effective February 1, 1965. Type Certificate no. H8NM issued February 4, 1985 for the purpose of: (1) Agricultural; (2) Forest and Wildlife Conservation; and (3) Carriage of External Loads FAR Part 133. Date of Application for Type Certificate: October 14, 1984. Production Basis None. No helicopter may be produced under this approval. Prior to original certification of each aircraft, FAA personnel must perform an airworthiness inspection determining that the aircraft is in condition for safe operation and that the applicant has conducted a satisfactory flight test. 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 FAA engineering approved. External Cargo Operations, Part 133, shall be conducted as specified in NAVAIR 01-110HCA-1 Flight Manual. See also Navair Weight and Balance Data, Navair 01-1B-40. Datum: Station 0 (datum is located 7.60 inches aft of the most forward point of the fuselage cabin nose section). Leveling Means: Plumb line from top of left main door frame. Revision 1 Page 3 of 3 H8NM NOTE 1. The generator speed as shown under "Engine Limits" are maximum permissible speeds. The torque pressure output by the engine torque sensing system and the gas generator speed for rated power output varies with individual engines and must be determined during engine calibration and stamped on the engine data plate. The torque pressure and gas generator speed shall be adjusted and displayed on the limit placard (P/N 204-70-149) installed on the instrument panel and must correspond to the engine data plate. Gas generator speed limits also vary with OAT in accordance with the schedule as shown on the limit placard (P/N 204-70-149) on the instrument panel. NOTE 2. Current weight and balance report including list of required equipment and list of equipment included in certificated empty weight, and loading instructions when necessary must be provided for the helicopter at the time of original certification. The certificated empty weight and corresponding C.G. locations must include undrainable oil of 1.72 lbs. (STA.+154) and unusable fuel of 9.0 lbs. (STA.+145) for 242 gal. capacity fuel system. NOTE 3. The following placard must be displayed in front of and in clear view of the pilot: "THIS AIRCRAFT MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS SPECIFIED IN THE AIRCRAFT FLIGHT MANUAL NAVAIR 01-110HCA-1." All placards required in the aircraft flight manual shall be installed in the appropriate locations. NOTE 4. The retirement times of critical parts are listed in NAVAIR 01-110HCA-6 Maintenance Manual. These values of retirement or service life cannot be increased without FAA engineering approval NOTE 5. Prior to Civil Airworthiness Certification the provisions of all applicable AD's a nd mandatory T.O.'s must be accomplished. All follow-on AD's to be complied with. NOTE 6. Rigging information contained in NAVAIR 01-110HCA-2 Maintenance Manual. NOTE 7. This helicopter must be serviced and maintained in conformance with instructions given by the U.S. Navy and Avco/Lycoming Corp in Maintenance Manuals Lycoming No. T5311-2 and NAVAIR 01-110HCA-2. NOTE 8. Maximum permissible exhaust gas temperature vari es with ambient temperature as described in the NAVAIR 01- 110HCA-1 Aircraft Flight Manual and on the face of the ambient temperature gage on the instrument panel. NOTE 9. Anti-icing additive at a concentration not in excess of 0.1% by volume or as recommended by the manufacturer may be used in fuel for this helicopter. NOTE 10. Gross weights above 8500 lbs. are limited to Extern al Cargo Load only and must not be imposed on the landing gear. The retirement times listed in Note 4 are not changed. NOTE 11. All repairs to this aircraft to be performed in accordance with NAVAIR 01-110HCA-3 Structural Repair Manual. NOTE 12. Engine inspections to be performed per Lycoming Engine Inspection Handbook T5311-5. NOTE 13. 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 (7) - [STC SR00119DE](https://openairdocs.org/stc/SR00119DE): Installation of an upgraded 42 degree Tail Rotor gearbox, P/N 212-040-003, and Control Cables. Midwest Aerospace TC LLC - [STC SR09177RC](https://openairdocs.org/stc/SR09177RC): Modification of the vertical fin spar. Midwest Aerospace TC LLC - [STC SH5690NM](https://openairdocs.org/stc/SH5690NM): Installation of Advanced Technology Aircraft Co. engine barrier filter.. WSH, LLC - [STC SR03408CH](https://openairdocs.org/stc/SR03408CH): Install Airwolf Aerospace, LLC Tension-Torsion Strap Assemblies, P/N AA-204-310-101-101 or AA-204-310-101-103. Airwolf Aerospace LLC - [STC SR02413LA](https://openairdocs.org/stc/SR02413LA): Installation of an AKV, Inc Exceedence and Trend Monitoring System kit P/N ETM1000. AKV Inc. - [STC ST04270AT](https://openairdocs.org/stc/ST04270AT): Install the VTOL ASSALT V3 Windscreen Laminate Kit. VTOL LLC - [STC SR09316RC](https://openairdocs.org/stc/SR09316RC): Fabrication, modification, and installation of a new vertical fin spar in accordance with Global Helicopter Technology, Inc., Drawing number VTF-030-801, Revision B, dated April 5, 2001, or later FAA approved revision.. Global Spar LLC --- 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.