# TCDS H6WE: Aero Resources Inc. - Type: Type certificate data sheet - Status: Current - Holder: Aero Resources Inc. - Revision: 1 - Revised: December 15, 1973 - Product: Aircraft, Rotorcraft - Certification basis: Part 27 - Data sheet PDF: https://openairdocs.org/files/sha256/4c/96/4c9608469284f1310e6733333b787ef2382f4e65c7185bcc0dd4f81156fb1619 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/908228529B23925585256714005D0AED.0001 - Page: https://openairdocs.org/tcds/H6WE ## Models (1) As the data sheet lists them. - J-2 Gyroplane ## 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 Rev No. 1 - - - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H6WE Revision 1 Aero Resources (McCulloch) J-2 December 15, 1973 TYPE CERTIFICATE DATA SHEET NO. H6WE This data sheet, which is a part of type certificate No. H6WE, 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: Aero Resources, Inc. 4439 S. Avalon Blvd. Gardena, CA 90248 I - Model J-2 Gyroplane (Normal Category), approved 6 May 1970 Engine Lycoming 0-360-A2D Fuel 100/130 min. Grade aviation gasoline Engine limits 180 HP, 2700 RPM - For all operations Propeller and 1. Aero Resources/McCulloch Model 6100D fixed pitch wood, Diameter 72 in. + .125 propeller limits in. Static rpm: 2300 minimum, 2450 maximum Eligible on S/N 10 and subs with maximum weight of 1500 lbs. 2. Hartzell constant speed (a) Hub HC-C3YR-1RLF with FL7663A-6R blades Diameter: 72 in. Pitch settings at 30 in. sta.: low 10° , high 22.2° Required on S/N 10 & subs when the maximum weight is increased to 1600 lbs., see Note 4. Rotor Limits 1500 lb. Maximum Weight Flight: 480 RPM Maximum; 300 RPM Minimum Spin Up: 500 RPM Maximum; 400 RPM Minimum 1600 lb. Maximum Weight Flight: 500 RPM Maximum; 300 RPM Minimum Spin Up: 520 RPM Maximum; 400 RPM Minimum Airspeed limits (IAS) VNL (Never exceed) 106 MPH (109 MPH CAS) (See FAA Approved Rotorcraft Flight Manual for ground operating limits) H6WE 2 C.G. range 1500 lb. Maximum Weight (See Note 4) Weight Forward Aft 1250 lbs. 74.2 in. 77.7 in. 1386 lbs. 74.2 in. 77.7 in. 1437 lbs. 74.2 in. - - - 1500 lbs. 74.8 in. 76.3 in. 1600 lb. Maximum Weight (See Note 4) Weight Forward Aft 1250 lbs. 72.5 in. 77.7 in. 1386 lbs. 72.5 in. 77.7 in. 1406 lbs. 72.5 in. - - - 1460 lbs. - - - 78.3 in. 1600 lbs. 74.5 in. 76.5 in. (Straight line variation between points shown). Lateral C.G. 1500 lb. Maximum Weight 3.5" Left and 1.5" Right of Centerline 1600 lb. Maximum Weight 3.5" Left and 1.5" Right of Centerline Maximum weight 1500 lbs. (See NOTE 1) For Maximum Weight increase to 1600 lbs. see NOTE 4. No. of seats 2 at +54.0 in. to +57 in. (adjustable) Maximum baggage 95 lbs. at +60 in. (See NOTE 1) Fuel capacity Total, 24.2 U.S. Gal.; Usable, 20.0 U.S. Gal. at +87.5 in. (See NOTE 1) Oil capacity Total 9 quarts; Usable, 6 quarts at +88.4 in. (See NOTE 1) Datum 48.0 in. forward of Bulkhead at forward point of seat box web. Leveling Means Lateral: Lugs at +48.0 Longitudinal: Lugs on R.H. side of seat between +48.0 and +60.0 Rudder Movement 25° +1°, right and left Rotor blade and For rigging information see Manufacturer's Report SA-4 dated 13 April 1973 or later FAA Control Movements approved revision. Rotor Blade Collective Pitch Angle shall not be less than 3.9° or more than 5°. Rotor Blade and 200 to 230 inch-lbs. of torque to move damper Damper setting shaft through low load stage Landing Gear oleo Main: 3.8 + .10 in.; Nose: 2.6 + .10 in. extension (measured at empty weight) Tire pressures Main and Nose: 48 + 4.0 psi. Altitude Limits See FAA Approved Rotorcraft Flight Manual Other operational See FAA Approved Rotorcraft Flight Manual and NOTE 2. limitations 3 H6WE Serial Nos. Eligible S/N 10 and up S/N 10 through 96 were manufactured by the McCulloch Aircraft Corp. and are identified by McCulloch identification plate. S/N 97 and subs. will be manufactured by Aero Resources, Inc. and will be identified by Aero Resources identification plate. Service Life Limits See Note 3 for list of Life Limited Components Certification Basis Model J-2. FAR 27 effective 1 February 1965, Special Conditions No. 27-2-WE-2 issued 23 October 1968, and the following exemption: No. 1084 - FAR 27.65(a)(2) Climb Gradient Type Certification No. H6WE issued 6 May 1970. Date of application 2 November 1966. Production Basis None. Prior to original Certification of each Gyroplane, an FAA representative must perform a detailed inspection for workmanship, materials, conformity to approved technical data and a check of flight characteristics. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installed in the gyroplane for certification. All required equipment that must be installed as well as optional equipment installations are listed in the following manufacturer's report: 205R003 "Equipment List" Service Information Model J-2 Structural Repair Manual Report J-2-68 is FAA approved. All manufacturer's Service Bulletins and other Service Information, when FAA approved, will carry a statement to that effect. NOTE 1. Current weight and balance report, including list of equipment included in certificated empty weight and loading instructions, must be provided for each gyroplane at the time of original airworthiness certification and at all times thereafter (except in the case of operators having an approved weight control system). Ballast, when necessary, must be carried in accordance with the loading instructions in the Rotrocraft Flight Manual. The unusable fuel and oil must be included in the empty weight. (Unusable fuel and oil equals sum of drainable and undrainable). NOTE 2. (a) The following placard must be installed on the Pilot's instrument panel: "This gyroplane must be operated in compliance with the operating limitations specified in the FAA Approved Rotorcraft Flight Manual." (b) Additional required placards are specified in the Limitations section of FAA Approved Rotorcraft Flight Manual. (c) The placards required for export to Canada are specified in the limitations section of FAA Approved Rotorcraft Flight Manual, Report J-2-100 revised July 3, 1973 or later FAA Approved Revision. NOTE 3. Information essential to the proper maintenance of these gryoplanes is contained in the Manufacturer's Handbooks of Maintenance Instructions which is provided with each gyroplane. These handbooks specify that Service Life limited parts be retired according to the following schedule. These valuse of retirement or service life cannot be increased without approval by Chief, Aircraft Engineering Division, FAA Western Region. Service Life Limits Hours Maximum Weight Components Part No. 1500 lbs. 1600 lbs. Blade Assy. Main Rotor 1500 1220 978 * Tail Boom Assy. RH 2100 11750 11750 Tail Boom Assy. LH 2125 11750 11750 H6WE 4 NOTE 3. (Cont'd) Service Life Limits Hours Maximum Weight Components Part No. 1500 lbs. 1600 lbs. Trunnion Horizontal 2604 75800 75800 Stabilizer Controlex Assy. (rudder) 2717 300 300 Cable Assy. Cyclic 27122 1000 1000 Control (Roll) Cable Assy. Cyclic 27401 1000 1000 Control (Pitch) Bellcrank Collective Control 2765 20600 20600 Control Rod Assembly 2777 37400 37400 (Collective) Front Spar Assy. (wing) 2801 39300 15347* Shaft Assy. - Pitch Bearing 6505 5110 2250* Thrust Bearing MRC 210-SZZ-T12 300 300 (Marlin-Rockwell Corp.) Tube Assy. "A" frame "U" 2381 1670 1670 Frame Assy. LH Tube Assy. "A" Frame "U" 2382 1670 1670 Frame Assy. RH Stub Shaft 6638 1438 1438 * When the maximum weight is increased from 1500 lbs. to 1600 lbs., the service life limit may be prorated in the following manner: D = A + C - CA B Where "A" is the actual hours on the component prior to modification "B" is the service life limit for the component @ 1500 lbs G.W. "C" is the service life limit for the compinent @ 1600 lbs G.W. "D" is the revised total prorated service life limit for the component (including the time prior to modification). NOTE 4. The model J-2 Gyroplane, S/N 10 and up, are eligible for a maximum weight of 1600 pounds when modified in accordance with Aero Resources Service Bulletin No. 18A, dated 28 March 1973 or later FAA approved revision. Rotorcraft Flight Manual, Report J-2-100, dated 30 November 1972 or later FAA approved revision is required. ...END... ``` ## ADs (1, in force first) - [AD 72-07-01](https://openairdocs.org/ad/72-07-01): Rotor Clearance and Collective Stick · Aero Resources J-2 Gyroplane. Effective Mar 22, 1972 ## STCs approved under this data sheet (9) - [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 SR02704SE](https://openairdocs.org/stc/SR02704SE): Installation and maintenance of the Sunspot 36 and 46 series lights. AeroLED's Holdings LLC - [STC SR00359BO](https://openairdocs.org/stc/SR00359BO): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [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 SA593CH](https://openairdocs.org/stc/SA593CH): Install Champion SlickSTART magneto booster system.. Champion Aerospace LLC - [STC SA1008WE](https://openairdocs.org/stc/SA1008WE): Installation of Poly-Fiber covering material.. Poly-Fiber Inc. - [STC SH1089NE](https://openairdocs.org/stc/SH1089NE): Installation of a Sensenich W72KZL fixed-pitch wood propeller.. Sensenich Wood Propeller Co - [STC SA6068NM](https://openairdocs.org/stc/SA6068NM): Installation of prerotator bracket in spin-up system to provide for easier operation of collective control lever and its throttle grip.. Aero Design & Sales, Ltd - [STC SH5873NM](https://openairdocs.org/stc/SH5873NM): Main rotor blade installation and balancing procedure.. Aero Design & Sales, Ltd --- 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.