TCDS A31NM

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. A31NM This data sheet which is a part of Type Certificate No. A31NM prescribes the conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations (14 CFR). Type Certificate Holder International Air Response (IAR) 2700 N Central Ave Suite 890 Phoenix, Arizona 85004 Type Certificate Holder Record: Rogers Helicopters, Inc. 5508 East Aircorp Way Fresno, California 93727 transferred to International Air Response on September 7, 2021 Heavy Lift Helicopters Inc. 19378 Central Road Apple Valley, CA 92307 transferred to Rogers Helicopters, Inc., on September 2, 2021 Hemet Valley Flying Service transferred TC A31NM to Heavy Lift Helicopters Inc. on August 6, 2002 I. Model C-130A (Restricted Category) Approved January 31, 1990 Engines Four (4) Allison turboprop T-56-A9D Fuel Commercial aviation turbine fuels conforming to ASTM Specification No. D 1655-59T, types Jet B, Jet A-1, Jet A, or commercial equivalents of MIL-T-5624, grade JP-4 or JP-5 Lubricating Oil Synthetic oil conforming to Allison Specification EMS-35 or MIL-L-7808 Engine Limits Static, Standard Day, Sea Level: Turbine Inlet Temperature Torque Oil Temp Takeoff (5 minutes) 977°C 19,400 in lb. 100°C Max Maximum Continuous 927°C 16,100 in lb. 85°C Max Propeller and Propeller Limits Four (4) Hamilton Standard hydromatic propellers Hub 54H60-91 or 54H60-117 Diameter 13 ft 6 in. 2% reduction allowable for repair Constant speed propeller, full feathering and reverse pitch Single rotation, four blade assembly with governing speed setting 1015 rpm (13820 erpm) Propeller assembly is complete with spinner, feathering and reversing provision, constant speed control, negative torque control, synchrophaser, and electrical ice control. Blade Angles Feather 92.5° ± .20° (a) (b) Low-pitch stop (min. flt. idle) 23.3° ± .50° (a) Ground idle, beta 4.0° to 5.5° (c) Reverse -7.0° ± 1.0° (b) (d) Page No. 1 2 3 4 Rev. No. 6 6 6 4 A31NM Revision 6 International Air Response (IAR) C-130A June 05, 2026 Page 2 of 4 A31NM (a) Propeller blade angles are measured at the blade 42.875-inch station with the propeller on a test post under conditions established by the applicable Hamilton Standard Maintenance Manual. (b) Propeller blade angles are indicated on the back-up valve housing under conditions established in the USAF T.O. 1C-130A-2-11 and USAF T.O. 3-1-1. (c) 5.0° to 6.0° with valve housing P/N 714325-2 or later installed (d) -5.5° to -7.5° with valve housing P/N 714325-5 or later installed Propeller Oil MIL-H-83282 Airspeed Limits (knots IAS) VMO (Maximum operating) See T.O. 1C-130A-1 VA (Maneuvering) See T.O. 1C-130A-1 VB (Turbulent air penetration) 65 knots above power off stall speed but not to exceed 180 knots IAS. Fig 6-1, T.O. 1C-130A-1 shows stall speeds measured as a function of gross weight. VFE (Takeoff & Approach, 50%) 180 knots VFE (Landing, 100%) 145 knots VLO (Landing gear operation) 170 knots VLE (Landing gear extended) 170 knots VLL (Landing light extended) 170 knots Heated Windshield Limitations If electric windshield heat is operative, it must be used for all flight operations. Operation without windshield heat on any or all portions of the windshield is permissible provided (1) the airplane is not flown in known icing conditions. C.G. Range See Fig. 5-6, USAF T.O. 1C-130A-1 Datum Fuselage Station 94.0 W.L. 142.98, BL 0 (NAS 221 screw head on bottom of forward fuselage, 71.0” forward of centerline of nose gear strut). MAC 164.5”, leading edge F.S. 487.4 Maximum Takeoff Wt. 124,200 lbs. Maximum Landing Wt. 124,200 lbs. See T.O. 1C-130A-1. Leveling Means Provisions for leveling by plumb line are installed in the cargo compartment on the left side of approximately F.S. 637. A plumb line support bracket is located on the fuselage side panel at approximately W.L. 252, BL 64L, and a leveling plate is located on the top of the cargo door curb at approximately W.L.150, BL 64L. Minimum Crew Three (3) - Pilot, Co-Pilot, and Flight Engineer Passengers None, limited to the flight crew and number of persons essential to operations. Fuel Capacity See page 1-49 of T.O. 1C-130A-1 for fuel capacity and usable fuel. See NOTE 2 for unusable fuel. Oil Capacity Four nacelle tanks (ARM 442.0). Capacity for each tank: 8 gallons usable, 12 gallons total. See NOTE 2 for system oil. Cargo Capacity See USAF T.O. 1C-130A-1 Section 5 Maximum Operating Altitude 40,000 ft. Page 3 of 4 A31NM Control Surface Movements (See USAF T.O. 1C-130A-2-9) Aileron Up 25° Down 15° Aileron trim tab Up 20° Down 20° Elevator Up 40° Down 15° Elevator trim tab Up 6° Down 25° Rudder Left 35° Right 35° Rudder trim tab Left 25° Right 25° Wing Flap Down 36° (100%) Serial Numbers Eligible See International Air Response Serial Numbers Report, IAR-C130A-004 Rev. A, dated June 14, 2023, or later FAA approved revision. Certification Basis The certification basis is 14 CFR §21.25 (a) (2) for the special purposes defined below. 1. Agricultural under 14 CFR §21.25(b)(1) 2. Forest and wildlife conservation under 14 CFR §21.25(b)(2) 3. Aerial surveying under 14 CFR §21.25(b)(3) 4. Patrolling under 14 CFR §21.25(b)(4) 5. Weather control under 14 CFR §21.25(b)(5) 6. Aerial Advertising under 14 CFR §21.25(b)(6) 7. Carriage of Cargo (Incidental) under FAA Order 8110.56B, Chapter 5.2.a.(8) 8. Target Towing under FAA Order 8110.56B, Chapter 5.2.a.(9) 9. Search and Rescue (Non-Transport) under FAA Order 8110.56B, Chapter 5.2.a.(10) 10. Space Vehicle Launch under FAA Order 8110.56B, Chapter 5.2.a.(11) 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. Production Basis None - Prior to original certification of each aircraft, an FAA representative must perform an inspection for workmanship, materials, and conformity with the approved technical data. All applicable Technical Orders affecting airworthiness must be accomplished. Equipment The basic required equipment as prescribed in the applicable Airworthiness Regulations (see Certification Basis), must be installed in the aircraft for certification. NOTE 1 The following limitations apply to all special purpose operations conducted under 14 CFR §21.25: A. In addition to the operating limitations in this data sheet, area, economic, passenger, and other appropriate operating limitations in accordance with FAR 21.25 shall be shown on placards or listings accessible to the pilot. B. The following placard is to be installed in clear view of the pilot. “RESTRICTED CATEGORY This airplane must be operated as a restricted category airplane and in compliance with the operating limitations stated in USAF T.O. 1C-130A-1 section V and in the form of placards markings and manuals.” C. Carriage of hazardous materials is prohibited unless compliance is shown with the applicable regulations in the Code of Federal Regulations 49, Part 175. D. 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 owner/operator's business, which is other than air transportation. NOTE 2 Weight and Fuel: A. Current Weight and Balance Report including list of equipment included in certificated weight empty, and loading instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter. B. The location of the center of gravity for any gross weight configuration, determined from T.O. 1-1B-40, Handbook of Weight and Balance Data, must fall within the percent of the mean aerodynamic chord (MAC) shown on the Center of Gravity Limitations Chart (figure 5-6, reference T.O. 1C-130A-1). For information and method of calculating the airplane center of gravity, refer to T.O. 1C-130A-9, Cargo Loading Handbook and T.O. 1-1B-40, Handbook of Weight and Balance Data. C. The weight of the system fuel and oil as defined below, and hydraulic fluid, must be included in the airplane empty weight. Page 4 of 4 A31NM System Fuel: The weight of all fuel required to fill all lines and tanks up to the zero-fuel point on the fuel gages in the level flight attitude. Unusable (includes drainable and trapped fuel): Tank Lbs.* Arm 1 65 555.3 2 65 565.4 3 65 565.4 4 65 555.3 Left Aux. 0 Right Aux. 0 Trapped or line fuel 149 563.5 *This column includes 41 lbs. of fuel (trapped in lines) distributed to each tank at 5 lbs. per tank. System Oil: The weight of oil remaining in the engine, lines, and tanks after subtracting the usable oil from the total capacity. Total: 221 lbs., Arm 442.0. D. Fuel Loading and Usage: Fuel must be loaded and used to provide compliance with the “Fuel Unbalance” limitation contained in USAF T.O. 1C-130A-1. Refer to USAF T.O. 1C-130A-1 for normal fuel management procedures. Phillips fuel additive PFA-55MB may be used in concentrations not to exceed 0.15 percent by volume. No fuel system anti-icing credit is allowed. NOTE 3 Latest revisions of the following documents are required: A. USAF T.O. 1C-130A-1, and USAF T.O. 1C-130A-1-1 must be available in the C-130A aircraft for all flight operations. B. USAF T.O. 1C-130A-9, “Cargo Loading Handbook,” and Supplement No. 1, must be used to load and restrain cargo. C. USAF T.O. 1-1B-40, “Handbook of Weight and Balance Data”. NOTE 4 The aircraft must be serviced and maintained in accordance with International Air Response Instructions for Continued Airworthiness Document, IAR-C130A-006 Rev. A, dated June 20, 2023, or later FAA accepted revision, or inspected in accordance with other FAA accepted inspection programs. Any changes or revisions to the International Air Response Instructions for Continued Airworthiness Document, IAR-C130A-006 Rev. A, Airworthiness Limitation Section, must be FAA Approved by the Certification Branch. FAA airworthiness directives for all Lockheed L-382 series aircraft and Hamilton Standard 54H60 series propellers must be reviewed for applicability and complied with accordingly. Compliance with applicable Time Compliance Technical Orders for the aircraft and engines must be shown. NOTE 5 C-130A aircraft with Aeroproducts propellers are not approved. NOTE 6 Prior to civil airworthiness certification, International Air Response must show that the following have been accomplished: (a) The basic required equipment necessary for the particular special purpose operation must be installed and an FAA representative must perform a detailed inspection for workmanship, materials, and conformity with the approved technical data, and a check of the flight characteristics. (b) Each airplane is required to configure IAW International Air Response Configuration Report IAR-C130A-001, Rev. A, dated June 25, 2023, or later FAA approved revision. (c) The maintenance, overhaul and modification records of each airplane must be reviewed for military changes that may affect the airworthiness of the aircraft. …..END…..