TCDS H22NM

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H22NM Revision 8 Arrow Falcon by Edgefield Manufacturing OH-58A+ OH-58A OH-58C April 11, 2024 TYPE CERTIFICATE DATA SHEET NO. H22NMA This data sheet, which is part of Type Certificate No. H22NM, 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 Arrow Falcon by Edgefield Manufacturing 27400 Southeast Nelson Road Sandy, Oregon 97055 Arrow Falcon Exporters, Inc. 2081 South Wildcat Way Porterville, Ca. 93257 reissued H22NM to Arrow Falcon by Edgefield Manufacturing on April 11, 2024 I. Model OH-58A+ (Restricted Category Military Surplus Rotorcraft) approved September 25, 1996 Engine Allison 250-C20C (T63-A720) See Note 8 Fuel ASTMD1655 JETB. See AF55-1520-228-10 for other approved fuels. Engine Limits Torque Pressure (Percent) Output r.p.m Exhaust Gas Temperature (oC) Gas Gen Speed Takeoff (5 Min.) 100% 100% 810 105% Max. Cont 85% 100% 738 105% See Flight Manual AF55-1520-228-10 for transient limits. Rotor Limits Power off Power on Maximum 390 RPM (Dual tach 110%) Maximum 354 RPM (Dual tach reading) Rotor 100% Minimum 330 RPM (Dual tach 93%) Minimum 347 RPM (Dual tach reading) Rotor 98% (See Flight Manual for transient limits.) Page 2 of 9 H22NM Revision 7 Page No. 1 2 3 4 5 6 7 8 Rev No. 8 5 5 5 7 5 5 7 Page 3 of 9 H22NM Revision 7 C. G. Range A) Longitudinal C.G. Limits (+107.0 To +111.4) at 3200 lbs. (+ 106.0 To +112.2) at 3000 lbs. (+105.2 To +114.2) at 2500 lbs. (+105.2 To +114.2) at 1800 lbs. Straight line variation between points given. (See Chart) Gross Weight (Lbs) 3200 3000 2500 1800 105.2 106.0 107.0 111.4 112.2 114.2 STA (INS) B) Lateral C.G. Limits 2.6 inches Right 2.4 inches Left Empty Weight C.G. Range Longitudinal Limits (+105.2) to (+114.2) Maximum Weight 3200 lbs. II. Model OH-58A (Restricted Category Military Surplus Rotorcraft) Approved June 26, 1997 Engine Allison 250-ClOD (T63-A700) See Note 8 Fuel ASTMDl655 JETB. See AF55-1520-228-1O for other approved fuels. Engine Limits Torque Pressure (psi) Output r.p.m Exhaust Gas Temperature (oC) Gas Gen Speed Takeoff (5 Min.) 92 103% 749 104% Max. Cont 79 103% 693 104% See Flight Manual AF55-1520-228-10 for transient limits. Note: Powerplant cooling has been demonstrated to be adequate for the following ambient temperature schedule: 125°F at sea level and decreases by 3.6°F per 1000 feet to the operating maximum altitude of 10,000 feet. Rotor Limits Power off Power on Maximum 390 RPM Maximum 354 RPM Minimum 330 RPM Minimum 347 RPM A void prolonged operation between 172 and 206 RPM (See Flight Manual for transient limits.) Page 4 of 9 H22NM Revision 7 C. G. Range A) Longitudinal C.G. Limits (+ 106.0 To +112.2) at 3000 lbs. (+105.2 To + 114.2) at 2500 lbs. (+105.2 To +114.2) at 1800 lbs. Straight line variation between points given. (See Chart) Gross Weight (Lbs) 3000 2500 1800 105.2 106.0 107.0 111.4 112.2 114.2 STA (INS) Empty Weight CG. Range Longitudinal Limits (+105.2) to (+ 114.2) Maximum Weight 3000 lbs. III. Model OH-58C (Restricted Category Military Surplus Rotorcraft) Approved June 26, 1997 Engine Allison 250-C20C (T63-A720) See Note 8 Fuel ASTMD1655 JETB. See AF55-1520-228-10 for other approved fuels. Engine Limits Torque Pressure (Percent) Output r.p.m. Exhaust Gas Temperature (oC) Gas Gen Speed Takeoff (5 Min.) 100% 100% 810 105% Max. Cont 85% 100% 738 105% See Flight Manual AF55-1520-228-10 for transient limits. Rotor Limits Power off Power on Maximum 390 RPM (Dual tach 110%) Maximum 354 RPM (Dual tach reading) Rotor 100% Minimum 330 RPM (Dual tach 93%) Minimum 347 RPM (Dual tach reading) Rotor 98% (See Flight Manual for transient limits.) C. G. Range A) Longitudinal C.G. Limits (+ 107.0 To +111.4) at 3200 lbs. (+ 106.0 To + 112.2) at 3000 lbs. (+ 105.2 To + 114.2) at 2500 lbs. (+105.2 To +114.2) at 1800 lbs. Straight line variation between points given. Page 5 of 9 H22NM Revision 7 C.G. Range (cont’d) Gross Weight (Lbs) 3200 3000 2500 1800 105.2 106.0 107.0 111.4 112.2 114.2 STA (INS) STA (INS) B) Lateral C.G. Limits 2.6 inches Right 2.4 inches Left Empty Weight C.G. Range Longitudinal Limits (+105.2) to (+ 114.2) Maximum Weight 3200 lbs. Data Pertinent To All Models Airspeed Limits Never exceed 138 MPH (120 Knots) CAS, Refer to AF55-1520-228-10 for additional information (AIRSPEED LIMITS). Decrease Vne 3 knots per 1,000 ft. above 3,000 ft. 100 kts recommended maximum for autorotation. Datum Station 0 (datum is 1 inch forward of most forward point of fuselage cabin nose section or 55.16 inches forward of jack point center line). Leveling Means Leveling means is plumb line from ceiling left rear cabin to index plate on floor. Minimum Crew 1 at (+65.0) Number of seats See Note 15 (1 at +65.0 and 2 at +104.0.) Maximum Cargo Total Maximum Cargo Weight of 950 pounds not exceeding 100 lbs. per sq. ft. between (+77) and (+114). Fuel Capacity 71.5 gallons (+116.0) 70.3 useable (See AF55-1520-228-10 for fuel operations limits). Oil Capacity 11.2 pints (+179.0) Control Movements For rigging information, refer to chapter 11 of the Aviation Unit and Intermediate Maintenance Manual TM55-1520-228-23-2. Serial Nos. Approved: Refer to Arrow Falcon Serial Numbers Eligible Report Number AF5145 dated July 10, 1996, or later FAA approved revision. A current copy is on file at the Los Angeles ACO. Certification Basis 14 CFR 21.25 (a) (2) effective February 1, 1965, including Amendments 21-1 through 21-42. Type Certificate No. H22NM for the Special Purpose(s) of: Page 6 of 9 H22NM Revision 7 Certification Basis (cont' d) I) Agricultural Operations under 14 CFR 21.25(b)(1). Note: In accordance with 14 CFR 36.1 (a)( 4), compliance with the noise requirements was not shown. Therefore, aircraft certificated under this type certificate are only eligible for agricultural operations excepted by 14 CFR 36.1 (a)(4) and defined under 14 CFR 137.3. 2) Forest and Wildlife Conservation Operations under 14 CFR 21.25(b)(2) Note: In accordance with 14 CFR 36.1 (a)(4), compliance with the noise requirements was not shown. Therefore, aircraft certificated under this type certificate are only eligible for dispensing fire fighting materials excepted by 14 CFR 36.1 (a)(4) and defined under 14 CFR 137.3. 3) External Load Operation under 14 CFR 21.25(b)(7). Note: In accordance with 14 CFR 36.1(a)(4), compliance with the noise requirements was not shown. Therefore, aircraft certificated under this type certificate are only eligible for external loads operations excepted by 14 CFR 36.1 (a)(4) and defined under 14 CFR 133.1(b). 4) Aerial Survey Operation under 14 CFR 21.25(b)(3) Note: In accordance with 14 CFR 36.1(a)(4), compliance with the noise requirements was not shown. Therefore, aircraft certificated under this type certificate are only eligible for aerial survey operations excepted by 14 CFR 36.1 (a)(4). See note 17. 5) Patrolling Operations under 14 CFR 21.25(4) Note: In accordance with 14 CFR 36.1(a)(4), compliance with the noise requirements was not shown. Therefore, aircraft certificated under this type certificate are only eligible for patrolling operations excepted by 14 CFR 36.1(a)(4). See note 17. Any alteration to the aircraft for Special Purposes not identified above require further FAA approval and in addition may require noise and/or flight testing. General Note: Any subsequent modifications to the helicopters type certified under this Type Certificate are to have the certification basis for that modification established under 14 CFR 21.101 published June 7, 2000, which became effective June 10 ,2003. Otherwise non-significant modifications are to meet the requirements of 14 CFR 27 airworthiness standards, normal category, Amendment 4, effective October 27, 1968, and 14 CFR 27.1529, Instructions for Continued Airworthiness, Amendment 18, effective September 11, 1980. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in or on each helicopter for certification. Date of Application November 6,1995 Production Basis None. No helicopter may be produced under this approval. Prior to adding serial numbers to this Type Certificate, each candidate helicopter must undergo a conformity inspection. The conformity inspection will be Page 7 of 9 H22NM Revision 7 conducted in accordance with a Type Inspection Authorization, Part 1, or request for conformity that will include as a minimum, the inspections contained in the FAA Rotorcraft Directorate Restricted Category conformity document dated September 25, 2001, or later FAA approved revisions. Notes Note 1 A current weight and balance report including list of equipment included in the certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. Refer to Flight Manual AF55-l520-228-10 or Aviation Unit and Intermediate Maintenance Manual, TM55-1520-228-23-2 for C.G. determination. Note 2 The following placards must be prominently displayed in the cockpit in full view of the pilots: Placard No. 1 "THIS ROTORCRAFT MUST BE OPERATED IN ACCORDANCE WITH THE RESTRICTED CATEGORY OPERATING LIMITATIONS OF 14 CFR 91.313." Placard No. 2 "THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE APPROVED ROTORCRAFT FLIGHT MANUAL. REFER TO AF 55-1520-228-10 FOR OPERATING LIMITS AND RESTRICTIONS." Placard No. 3 'VFR OPERATIONS ONLY' Note 3 The helicopter(s) must be serviced, maintained, inspected, repaired, and overhauled in accordance with the documents specified in Arrow Falcon Exporters, Inc. Instructions for Continued Airworthiness Report, AF5132, dated July 5, 1996, as revised or inspected in accordance with other FAA accepted inspection programs. The TC Holder's Instructions for Continued Airworthiness Report is part of the TC Holder's Instructions for Continued Airworthiness. An FAA approved/accepted copy must accompany each helicopter on delivery. Note 4 Prior to obtaining an original Airworthiness Certificate: A Each helicopter must pass a conformity inspection in accordance with Arrow Falcon Exporters, Inc. Configuration Report, AF5146, dated July 10, 1996 or later revision. The Configuration Report must contain a complete description of each helicopter, any military Maintenance Work Orders accomplished on that particular helicopter, and a description of the Special Purpose modification(s) accomplished on that particular helicopter. In addition, each helicopter must pass an inspection for any possible hidden damage and the military records reviewed for acceptability of any repairs or alterations. Page 8 of 9 H22NM Revision 7 B. The maintenance, overhaul, and modification records of each helicopter must be reviewed for military changes that may affect the airworthiness of the helicopter. C. After the required inspections, the aircraft must be found to be in a good state of preservation, repair, and in a condition for safe operation. D. A check by the Type Certificate Holder, of the flight characteristics in accordance with all applicable portions of Sections II and V of the U.S. Army Technical Manual 55-1520-228-MTF Maintenance Test Flight Manual, dated November 1, 1988, as appropriate for each aircraft, or other FAA approved manual. Note 5 This aircraft is prohibited from carrying cargo for compensation or hire. Carriage of cargo is limited to such cargo that is incidental to the aircraft's owner/operator's business, which is other than air transportation. (This note applies to aircraft that have the special purpose, "Carriage of cargo.") Note 6 Restricted Category aircraft may not be operated in a foreign country without the express written approval of that country. Note 7 This aircraft has not been shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the Convention on International Civil Aviation. Note 8 Engine changes are allowed provided the replacement engine is of the same make and model as identified in this TCDS. The replacement engine must have proper military records and have the applicable FAA Airworthiness inspection accomplished. Note 9 The Airworthiness directives for the helicopter and engine contained in Arrow Falcon Exporters, Inc. Airworthiness Directives Report, AF5121 (OH-58A+, OH-58A, and OH-58C) and AF5123 (Engine), dated June 10, 1996, or later FAA Approved revision, must be complied with prior to original airworthiness certification. Note 10 An acceptable method of determining engine cycles from engine total operating time is contained in ARROW FALCON Report No. AF5] 30 dated July 24, 1996, or later FAA Approved revision. This may be used when converting military operating hours to commercial equivalent cycles at the time of initial airworthiness conformity. Note 11 When equipment identified in Arrow Falcon Exporters Inc. Removed Equipment Report Number AF5144 dated July 29, 1996, or later FAA Approved revision, is removed, the helicopter center gravity (CG) will be beyond aft limitations. The pilot shall refer to Arrow Falcon AF55-1520- 228-10, Flight Manual, to determine the amount of ballast to be installed at Sta. 22.2 in order to return the Center of Gravity to specified parameters. Note 12 OH-58A+, OH-58A, and OH-58C helicopters shall have additional systems installed as follows: Description Report No. Battery Temperature Monitor AF5138 Flight Hour Recording Meter Installation AF5133 Page 9 of 9 H22NM Revision 7 Ballast Weight Installation AF5134 Note 13 Flight Manual - Model OH-58A+ helicopters having complied with MWO 1520-228-50-6, which installs the T63-A720 engine, must be operated in accordance with the operating limitations in the Flight Manual AF55-1520- 228-10 dated January 7, 1997, or later FAA Approved revisions. Note 14 Any alteration to the type design of this aircraft may require Instructions for Continued Airworthiness. These instructions must be submitted and accepted by the FTW-AEG, Aircraft Evaluation Group Office, prior to approval for return to service. Note 15 No person may be carried in this helicopter during flight unless that person is essential to the purpose of the flight. Note 16 Alternate or emergency fuels are listed in TM55-1520-228-10 Chapter 2, Section XIV, Table 2-2. Some limitations apply for the use of certain alternate and emergency fuels. These limitations are listed in this section. Note 17 In order to conduct operation under Aerial Survey 14 CFR 21.25(b)(3) or Patrolling Operations under 14 CFR 21.25 wedge style windows at the observer or pilot station must be installed in accordance with Supplemental Type Certificate SA00483SE. …..END…..