TCDS A15NM

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A15NM Revision 4 USDA FOREST SERVICE C-130A August 7, 2006 Type Certificate A15NM was surrendered to the FAA on August 7, 2006. TYPE CERTIFICATE DATA SHEET NO. A15NM This data sheet which is a part of Ty pe Certificate No. A15NM 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 USDA Forest Service 2nd Floor, SW Wing 201 14th Street SW Washington DC 20090-6090 I - Model C-130A, (Restricted Category) Approved August 21, 1985 Engines 4 - Allison turboprop T-56-A9 or T-56-A11 Engines 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 Temp Torque Oil Temp Takeoff (5 minutes) 19,400 in-lb., T-56-A9 100°C Max 19,600 in-lb., T-56-A11 Maximum continuous 16,100 in-lb., T-56-A9 85°C Max 17,500 in-lb., T-56-A11 Propeller and 4 - Hamilton Standard hydromatic propellers Hub 54H60-91 propeller limits 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 1020 prpm (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 23.3° + .50° (a) (min. flt idle) Ground idle, beta 4.0 to 5.5° (c) Reverse -7.0° + 1.0° (b)(d) Page No. 1 2 3 4 5 Rev. No. 4 4 4 4 4 A15NM 2 (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 714325-2 or later installed. Propeller Oil MIL-H-5606B (Ham Std.) OR 4 Aeroproducts, A6341FN-DIA Hydr aulic propellers hub and blade assembly P/N 6506600 with Alpha Prefix -wy de signation serial numbered blades only. Propeller and propeller Diameter 15 feet limits Repair and rework to be in accordance with USAF T.O. 3H3-19-2. Single rotation, three blade assembly with governing speed setting 1016 prpm (13,820 erpm). Propeller assembly is complete with spinner, feathering and reversing provisions, constant speed control, negative torque control, synchrophaser and electrical ice control. Blade Angles Blade angle settings are at the No. 72 Station Feather 82.0° Mechanical low pitch stop 5.9° to 6.5° Flight idle (hydraulic low pitch stop) 7.8° to 8.2° Negative -15.3° to -15.7° Total allowable blade 97.5° angle range Propeller Oil Penola Aviation Instrument Oil, Government No. 1191X, manufactured ESSO (Aero products) Standard Oil Company, Type P-Q Rust Preventative No. 107, Government No. 6603X, manufactured by American Oil Company or Government No. 3106 or 3106X manufactured by Humble Oil and Refining Company, FSN 9150-473-9849. Airspeed limits Vmo (Maximum operating) See T.O. 1C-130A-1, (Knots IAS) Va (Maneuve ring) Section 5, page 5-15 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 (Take-Off & Approach 50%) 180K Vfe (Landing, 100%) 145K Vlo (Landing gear operation) 170K Vle (Landing gear extended) 170K Vll (Landing light extended) 170K Heated windshield If electric windshield heat is operative, it must be used for all flight operations. limitations 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 and (2) The maximum speed limit below 10,000 ft. is 187 KCAS. C.G. range See Fig. 5-6, USAF T.O. 1C-130A-1 3 A15NM Datum Fuselage Station 94.0 W.L. 142.98, BL 0 (NAS 221 screw head on bottom of forward fuselage, 71.0" forward of center line of nose gear strut). M.A.C. 164.5", leading edge F.S. 487.4 Maximum takeoff 124,200 lbs. Maximum landing wt. 96,000 lbs up to 124,200 lb s. See page 5-20 of T.O. 1C-130A-1. Maximum zero fuel weight 97,000 lbs. 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 floor 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. Control surface movements Aileron Up 25° Down 15° (See USAF T.O. Trim Tab Up 20° Down 20° 1C-130A-2-9) Elevator Up 40° Down 15° Trim Tab Up 6° Down 25° Rudder Left 35° Right 35° Trim Tab Left 25° Right 25° Wing Flap Down 36° (100%) Serial Numbers eligible Surplus military C-130A airplanes that have been found to comply with the requirements of this data sheet. Certification basis The certification basis is FAR 21.25(a)(2). 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. This approval applies to: A. Basic United States Air Force C-130A airplane with no major modifications except, as required by U.S.D.A. Forest Service Report No. 130A, Revision 4, or later FAA approved revisions. A15NM 4 B. Airplane certified for the special purpose of ag riculture, forest, and wildlife conservation, and the carriage of cargo with the following limitations: 1. The following placard is to be in stalled 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." 2. Carriage of hazardous materials is prohibited unless compliance is shown with . FAR 21.25, FAR 91 and the applicable regula tions in the Code of Federal Regulations 49, Part 17. 3. Aircraft approved under this type certifi cate may only be used as fire fighting aircraft. NOTE 2. A. Current weight and balan ce 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 gr oss 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 Lim itations Chart (figure 5-6). For information and method of calculating the airplane center of gr avity, 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. 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 altitude. 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 TOTAL 260 Trapped or line 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. 1. Fuel must be loaded and used to provi de compliance with the "Fuel Unbalance" limitation contained in USAF T.O. 1C-130A-1. Re fer to USAF T.O. 1C-130A-1 for normal fuel management procedures. 5 A15NM 2. 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, Cha nge 2, dated March 22, 1981, 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 Ha ndbook," and Supplement No. 1, dated April 28, 1967, must be used to load and restrain cargo. C. USAF T.O. 1-1B-40, "Ha ndbook of Weight and Balance Data". NOTE 4. The aircraft must be serviced and maintain ed in accordance with USAF T.O. 1C-130A-2-1 through 1C-130A-2-13. FAA airworthiness directives for all L-382 series airc raft and Hamilton Standard 54H60 series propellers must be reviewed for applicability and complied with accord ingly. Compliance with applicable Time Compliance Technical Orders for the aircraft and engines must be shown. NOTE 5. C-130A aircraft with Aeroproduc ts propellers with Alpha Prefix Serial Numbered blades are approved for Restricted Category operation. These propellers must be maintained in accordance with USAF T.O. 3H3- 19-2 dated August 1, 1961, Change 28, dated Aprul 7, 1983, or later revision. Propeller inspection interval and replacement times shall be in accordance with US AF T.O. 1C-130A-6 dated July 1, 1982, Change 1, dated October 1, 1982, or later revision. Blad es with numbered serial numbers are not approvedl NOTE 6. Prior to civil airworthiness certification, Reagon En terprises Company must show that the following have been accomplished: (a) Compliance with all USAF Technical Orders which affect airworthiness. (b) Inspect all fuel tanks for sealant deterioration and repair as necessary. .....END.....