DEPARTMENT OF TRANSPORTATION
  
FEDERAL AVIATION ADMINISTRATION
  
TYPE CERTIFICATE DATA SHEET NO. H6WE	H6WE
Revision 1
Aero Resources
(McCulloch)
J-2
December 15, 1973	

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)

	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 	   Control Movements	FAA 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

	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

	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...