TCDS R00006DE

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION R00006DE Revision 9 Henry Helicopters, LLC OH-58A OH-58A+ OH-58C April 8, 2024 TYPE CERTIFICATE DATA SHEET NO. R00006DE This data sheet which is part of Type Certificate No. R00006DE prescribes conditions and limitations which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Henry Helicopters, LLC 12900 FM 3436 Dickinson, TX 77539 Type Certificate Holder Record: Rotorcraft Developm ent Corporation transferred TC R00006DE to Henry Helicopters, LLC on April 8, 2024. Type Certificate Holder Record: Garlick Helicopter Corporation transferred TC R00006DE to Rotorcraft Development Corporation on February 2, 2009. Type Certificate Holder Record: Garlick Helicopter, In c. transferred TC R00006DE to Garlick Helicopter Corporation on June 29, 2007. I - Model OH-58A, (Restricted Category Military Surplus Helicopter) Approved August 15, 1996 Engine 1- Allison 250-C10D (T63-A-700) (See Note 8 and Note 10 for Alternate Engine) Fuel ASTM D1655 Jet B (See no te 10 for alternate fuels). Engine Limits Torque Output Turbine Gas Gen. Pressure Shaft Speed Out Temp Speed Takeoff (5 minute) 92 psi 103% 749º C 104% M a x i m u m Max. Continuous 79 psi 103% 693º C 104% (See Operator’s Manual TM55-1 520-228-10 for transient limits) NOTE: Powerplant cooling has been demonstrated to be adequate for the following ambient temperature schedule: 125 Degrees F at sea level, decreasing at a lapse rate of 3.6 Degrees F per 1000 feet to 89 Degrees F at the maximum operating altitude of 10,000 feet. Rotor Limits Power Off Power On Maximum 390 RPM Maximum 354 RPM Minimum 330 RPM Minimum 347 RPM Avoid Prolonged Operation Between 172 to 206 RPM. (See Operator’s Manual TM55-1520 228-10 for transient limits) Page No. 1 2 3 4 5 6 7 8 9 Rev. No. 9 7 6 5 6 6 7 5 9 R00006DE Page 2 of 9 I – Model OH-58A (cont’d) Airspeed Limits Never exceed 120 knots CAS. Decrease V NE 3 knots/1000 feet above 3000 feet. V NE will be determined for each Special Purpose Operation and must be FAA approved. Other Limits Flight Hours are counted from takeoff to landing. The helicopter approved under this type certificate is done so under the concept of limited exposure associated with escape from inadve rtent ice encounters, and is prohibited against flight into known icing. The helicopter must be re-evaluated if certification to the General Ice protection Airworthiness Regulations is requested. C.G. Range Straight line variation between points given. Longitudinal C.G. limits +106 to +112 at 3000 lbs. +105.2 to +114.2 at 2500 lbs. +105.2 to +114.2 at 1800 lbs. (Reference C.G. Chart in Operator ’s Manual TM55-1520-228-10 Chapter 6) Empty Weight +105.2 to 114.2 C.G. Range Maximum Weight 3000 lbs. (see Note 12 for external cargo configuration information) Minimum Crew 1 at + 65.0 No. of Seats See Note 22 Maximum Cargo 950 lbs. between station +77 and +114. See Operator’s Manual, TM55-1520-228-10. Fuel Capacity Useable 70.3 Gallons (Tot al Fuel: 71.5 gallons at sta. +116) (See TM55-1520-228-10 for limits with 23.9 aux. fuel cell installed) Oil Capacity 11.2 Pints at sta. + 179.0 Rotor Blade and For rigging information, refer to TM55-1520-228-23-2 Intermediate Maintenance Manual. Control Movements Approved Serial Nos. US Military Surplus OH-58A He licopters as identified in FAA Approved TC R00006DE SN LIST TC03, dated August 15, 1996, or later FAA approved revision. II - Model OH-58A+, (Restricted Category Military Surplus Helicopter) Approved August 15, 1996 Engine 1- Allison 250-C20C (T63-A-720) (See Note 11) Fuel ASTM D1655 Jet B (See No te 10 for alternate fuels) R00006DE Page 3 of 9 II - Model OH-58A+ (cont’d) Engine Limits Torque Output Turbine Gas Gen. Output Shaft Speed Out Temp Speed Takeoff (5 min) 100% 100% 810º C 105% M a x i m u m Max. Continuous 85% 100% 738º C 105% (See Operator’s Manual TM55-1520-228-10 for transient limits). Rotor Limits Power Off Power On Maximum 390 RPM Maximum 354 RPM (Dual Tach Reading 110%) (Dual Tach Reading 100%) Minimum 330 RPM Minimum 347 RPM (Dual Tach Reading 93%) (Dual Tach Reading 98%) Avoid Prolonged Operation Between 172 to 206 RPM. (See Operator’s Manual TM55-1520 228-10 for transient limits) Airspeed Limits Never exceed 120 knots CAS Decrease V NE 3 knots/1000 ft. above 3000 ft. 100 Knots Recommended Maximum for Autorotation V NE will be determined for each Special Purpose Operation and must be FAA approved Other Limits Flight Hours are counted from takeoff to landing. The helicopter approved under this type certificate is done so under the concept of limited exposure associated with escape from inadve rtent ice encounters, and is prohibited against flight into known icing. The helicopter must be re-evaluated if certification to the General Ice protection Airworthiness Regulations is requested. C.G. Range Straight line variation between points given. 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. (Reference C.G. Chart in Operator ’s Manual TM55-1520-228-10 Chapter 6) Empty Weight +105.2 to 114.2 C.G. Range Maximum Weight 3200 lbs. (See note 13 for external cargo configuration information.) Minimum Crew 1 at + 65.0 No. of Seats See Note 22 Maximum Cargo 950 lbs. between station +77 and +114. See Operator’s Manual, TM55-1520-228-10. R00006DE Page 4 of 9 II - Model OH-58A+ (cont’d) Fuel Capacity Useable 70.3 Gallons (Tot al Fuel: 71.5 gallons at sta. +116) (See TM55-1520-228-10 for limits with 23.9 aux. fuel cell installed) Oil Capacity 11.2 Pints at sta. + 179.0 Rotor Blade and For rigging information refer to TM55-1520-228-23-2, Intermediate Maintenance Manual. Control Movements Approval Serial Nos. US Military Surplus OH-58A+ Helicopters as identified in FAA Approved TC R00006DE SN LIST TC03, dated August 15, 1996, or later FAA approved revision. III - Model OH-58C, (Restricted Category Military Surplus Helicopter) Approved August 15, 1996 Engine 1- Allison 250-C20C (T63-A720) (See Note 11) Fuel ASTM D1655 Jet B (See No te 10 for alternate fuels) Engine Limits Torque Output Turbine Gas Gen. Pressure Shaft Speed Out Temp Speed Takeoff (5 minute) 100% 100% 810º C 105% M a x i m u m Max. Continuous 85% 100% 738º C 105% (See Operator’s Manual TM55-1520-228-10 for transient limits) Rotor Limits Power Off Power On Maximum 390 RPM Maximum 354 RPM (Dual Tach Reading 110%) (Dual Tach Reading 100%) Minimum 330 RPM Minimum 347 RPM (Dual Tach Reading 93%) (Dual Tach Reading 98%) Avoid Prolonged Operation Between 172 to 206 RPM. (See Operator’s Manual TM55-1520 228-10 for transient limits) Airspeed Limits Never exceed 120 knots CAS Decrease V NE 3 knots/1000 feet above 3000 feet 100 Knots Recommended Maximum for Autorotation V NE will be determined for each Special Purpose Operation and must be FAA approved Other Limits Flight Hours are counted from takeoff to landing. The helicopter approved under this type certificate is done so under the concept of limited exposure associated with escape from inadve rtent ice encounters, and is prohibited against flight into known icing. The helicopter must be re-evaluated if certification to the General Ice protection Airworthiness Regulations is requested. R00006DE Page 5 of 9 III - Model OH-58C (cont’d) C.G. Range Straight line variation between points given. 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. (Reference C.G. Chart in Operator ’s Manual TM55-1520-228-10 Chapter 6) Empty Weight +105.2 to 114.2 C.G. Range Maximum Weight 3200 lbs. (See note 13 for external cargo configuration information) Minimum Crew 1 at + 65.0 No. of Seats See Note 22 Maximum Cargo 950 lbs. between station +77 and +114. See Operation’s Manual, TM55-1520-228-10. Fuel Capacity Useable 70.3 Gallons (Tot al Fuel: 71.5 gallons at sta. +116) See TM55-1520-228-10 for limits with 23.9 aux. fuel cell installed. Oil Capacity 11.2 Pints at sta. + 179.0 Rotor Blade and For rigging information refer to TM55-1520-228-23-2 Intermediate Maintenance Manual. Control Movements Approval Serial Nos. US Military Surplus OH-58C Helicopters as identified in FAA Approved TC R00006DE SN LIST TC03, dated August 15, 1996, or later FAA approved revision. DATA PERTINENT TO ALL MODELS Datum Station 0 datum is one inch forward of most forward point of fuselage cabin nose section or 55.16 inches fo rward of jack point centerline. Plumb line from ceiling left rear cabin to index plate on floor. Certification Basis General Note: Any alteration to the aircraft for Special Purposes not identified above Require further FAA approval and in additio n may require noise and/or flight testing. Model OH-58A: FAR 21.25(a)(2) effective February 1, 1995, including Amendments 21-1 through 21-71. Type Certificate R00006DE issu ed for the Special Purpose of: 1) External Load Operations under FAR 21.25(b)(7). See Note 11. 2) Agricultural Operations under FAR 21.25(b)(1). See Note 17. 3) Forest and Wildlife Conservation Operations under FAR 21.25(b)(2). See Note 18. Note: In accordance with FAR 36.1(a)(4), compliance with the noise requirements was not shown for the Model OH-58A. Therefore, Model OH-58A aircraft certificated under this Type Certificate are only eligible for the Special Purposes of External Load Operations, Forest and Wildlife Conservation and Agricultural Operations as listed above. R00006DE Page 6 of 9 DATA PERTINENT TO ALL MODELS (cont’d) Model OH-58A+ and OH-58C: FAR 21.25(a)(2) effective February 1, 1965, including Amendments 21-1 through 21-71. Type Certificate R00006DE issued for the Special Purpose of: 1) External Load Operations under FAR 21.25(b)(7). See Note 12. 2) Agricultural Operations under FAR 21.25(b)(1). See Note 17. 3) Forest and Wildlife Conservation Operations under FAR 21.25(b)(2). See Note 18. 4) Aerial Surveying Operations under FAR 21.25(b)(3). See Note 19. 5) Patrolling Operations under FAR 21.25(b)(4). See Note 20. Note: In accordance with FAR 36.1(a)(4), compliance with the noise requirements has been shown for Garlick Models OH-58+ and OH-58C. No determination has been made by the Federal Aviation Administration that the noise levels of this aircraft are or should be acceptable or unacceptable for operation at, into, or out of, any airport. General Note: Any subsequent modifications to the helicopters type certified under this Type Certificate are to have the certification basis for the 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. Production Basis None. No Helicopter may be produced under this approval. (See Note 4) Prior to adding serial numbers to this Type Certificate, each candidate helicopter must undergo a conformity inspection. The conformity inspection will be 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. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis) must be installed in each helicopter for certification. In addition, the Operator’s Manual TM55-1520-228-10 and the applicable FAA approved Rotorcraft Flight Manual Supplement applicable to each model, as listed below dated August 15, 1996, or later FAA approved revision is required. GH-OH58FMS-A for model OH-58A GH-OH58FMS-AP for model OH-58A+ GH-OH58FMS-C for model OH-58C NOTES NOTE 1. A current weight and balance report includ ing list of equipment included in the certificated empty weight and loading instructions when necessary, must be provided for each aircraft at time of original certification. Refer to Chapter 6 of Operator’s Manual (TM55-1520-228-10) or Paragraph 1-43 of Maintenance Manual (TM55-1520-228-23) 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 OP ERATED IN ACCORDANCE WITH THE RESTRICTED CATEGORY OPERATING LIMITATIONS OF FAR 91.313.” R00006DE Page 7 of 9 NOTES (cont’d) NOTE 2 (cont’d) Placard No. 2 “THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE APPROVED HELICOPTER OPERATORS MANUAL. REFER TO TM55-1520-228-10, CHAPTER 5 FOR OPERATING LIMITS AND RESTRICTIONS.” NOTE 3: The helicopter(s) must be serviced, ma intained, and inspected in accordance with the documents specified in Garlick Helicopters, Inc. Instructions for Continued Airworthiness report, GH-OH58-CA1, dated August 15, 1996 (or later revision) or other FAA accepted inspection programs. The Garlick Helicopters, Inc. Report GH-OH58- CA1 is part of the Garlick Helicopters, Inc., Instructions for Continued Airworthiness. Retirement times are listed in FAA approved Airworthiness Limitations Section (section II of the above document) dated August 15, 1996, or later approved revision. NOTE 4: In addition to the standa rd helicopter requirements, the following additional data and/or helicopter configuration requirements must be met for each individual model OH58A, OH-58A+, and OH-58C helicopter upon application for an original Special Airworthiness Certificate: a) A completed application for airworthiness certificate, FAA Form 8130-6 that has correctly identified the type certificate holder’s helicopter and its intended special purpose(s). b) Written confirmation from the certifying office that the affected serial number has been added to the Type Certificate, R00006DE. NOTE: See The Most Current FAA Approved Revision of Type Certificate Data Sheet R00006DE, Serial Number List REPORT NO. RDC-TC03. c) The application for airworthiness certification and the helicopter’s registration certification matches the information on the Type Certificate Holder’s data plate. d) Each helicopter must pass a conformity inspection in accordance with Garlick Helicopters, Inc. Configuration Report, GH-OH58-CR1, dated August 15, 1996 (or current revision). The Configuration Report must contain complete description of each helicopter, any military Modification Work Order (MWO) 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 hidden damage and the military records reviewed for acceptability of any repairs or alterations. e) The maintenance, overhaul, and modification records of each helicopter must be reviewed for military changes that may affect the airworthiness of the helicopter. f) 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. g) The Airworthiness Directives for the helicopter and engine contained in Garlick Helicopters, Inc. Airworthiness Directive Report, GH-OH58-CR, dated August 15, 1996 (or later FAA approved revision) must be complied with. NOTE 5: The aircraft is prohibited from carrying car go for compensation or hire. Carriage of cargo is limited to such cargo that is incidental to the aircraft 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. R00006DE Page 8 of 9 NOTES (cont’d) NOTE 8: Military to Civil or Military to Military en gine changes are allowed provided the replacement engine is of the same make and model as identified in this TCDS. The military or civil replacement engine must have proper military or civil records and have the applicable FAA Airworthiness Inspection accomplished and is in an airworthy condition. NOTE 9: Alternate and emergency fuels are listed in TM55-1520-228-10, Chapter 2, Section XIV and table 2-2. Some limitations apply for the use of certain alternate and emergency fuels. These limitations are listed in this section. NOTE 10: Model OH-58A helicopters having MWO 1520-228-50-6 complied with are powered by the T63-A-720 engine and are operated in accordance with Operating Limitations as outlined in Operator’s Manual TM55-1520-228-10 and Garlick Helicopters, Inc. approved Flight Manual Supplement GH-OH58FMS-AP, dated August 15, 1996 (or later FAA approved revision) is required. This modified model is referred to in some US Army publications as an OH-58A-720 or OH-58A+( A-Plus) and on this data sheet as OH-58A+. NOTE 11: External cargo hook, P/N GH-76334-01, shall be installed on Model OH-58A in accordance with Garlick Helicopters, Inc. Drawing Number GH-76334, Revision A, dated August 5, 1996, or later FAA approved revision. Model OH-58A helicopters with external cargo hook installed in accordance with Drawing Number GH-76334 meet structural and design requirements for a maximum external load of 1500 pounds. Garlick Helicopters FAA approved Flight Manual Supplement GH-OH58-CHFMS, dated August 15, 1996 (or later FAA approved revision) for “External Cargo Hook” is required. Continued airworthiness of the cargo hook installation shall be accomplished in accordance with Garlick Helicopters, Inc. GH-CHCA-76, dated August 15, 1996, or later revision. NOTE 12: External cargo hook P/N GH-76334-01 shall be installed on Models OH-58A+ and OH-58C in accordance with Garlick Helicopters, Inc. Drawing Number GH-76334, Revision A, dated August 5, 1996, or later FAA approved revision. Model OH-58A+ and OH-58C helicopters with external cargo hook installed in accordance with Drawing No. GH-76334 meet structural and design requirements for a maximum external load of 1500 pounds. Garlick Helicopters FAA approved Flight Manual Supplement GH-OH58-CHFMS, dated August 15, 1996, (or later FAA approved revision) for “External Cargo Hook” is required. Continued airworthiness of the cargo hook installation shall be accomplished in accordance with Garlick Helicopters, Inc. GH-CHCA-76, dated August 15, 1996, or later revision. NOTE 13: Bell Helicopter Textron, Inc. has no invo lvement with this Type Certificate. Garlick Helicopters, Inc. is the original holder of TC Number R00006DE. Authority, AWS-100 Memo, dated February 22, 1985. NOTE 14: Engine Oil By-Pass Valve may be removed IAW Garlick Helicopters, Inc. Report Number GH-OH58-OV, dated January 18, 1996, or later approved revision. NOTE 15: Pilot must verify load calculations prior to flight anytime articles are stowed in avionics compartment aft of station 120 to ensure weight and balance CG limits are not exceeded. Maximum allowable weight in avionics compartment shall be 250 lbs. including battery. NOTE 16: Auxiliary Power Plug inst alled in accordance with Garlick Helicopters, Inc. drawing number GH-61500, dated August 5, 1996, or later FAA approved revision. Auxiliary power plug supplies power, as required, to actuate appliances attached to the cargo hook. NOTE 17: To conduct Agriculture Operations under FAR 21.25(b)(1), the aircraft must be modified IAW Garlick Helicopters Report Number GH-OH58-MOD, Revision 1, FAA approved August 6, 1997, or later FAA approved revision. R00006DE Page 9 of 9 NOTES (cont’d) NOTE 18: To conduct Forest and Wildlife Conservation Operations under FAR 21.25(b)(2), the aircraft must be modified IAW Garlick Helicopters, Inc. Drawing Number GH-76334, Revision A, dated August 5, 1996, or later FAA approved revision, External Cargo Hook installation of dispensing of firefighting materials utilizing a water bucket. Any other device installed for this special purpose must be FAA approved. NOTE 19: To conduct Aerial Surveying Operations under FAR 21.25(b)(3), the aircraft must be modified IAW Garlick Helicopters, Inc. Report Number GH-OH58-MOD, Revision 1, dated August 6, 1997, or later FAA approved revision. NOTE 20: To conduct Patrolling Operations under FAR 21.25(b)(4), the aircraft must be modified IAW Garlick Helicopters, Inc. Report Number GH-OH58-MOD, Revision 1, dated August 6, 1997, or later FAA approved revision. NOTE 21: Any Alteration to the type design of this aircraft may require Instructions for Continued Airworthiness (ICAs). Changes to the Type Design by means of a Supplemental Type Certificate (STC) requiring ICAs or changes to existing ICAs must be submitted and reviewed by the Rotorcraft Aircraft Evaluation Division (AED). Type Design Changes by means of a Field Approval that require ICAs must have those ICAs reviewed by the Flight Standards District Office (FSDO) managing the Field Approval, or the Rotorcraft AED. NOTE 22: No person may be carried in this helicopter during flight unless that person is essential to the purpose of the flight. END