TCDS A35NM

P a g e . N o . 12345 R e v . N o .----- DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A35NM Revision 1 Heavylift Helicopters Inc. C-130B August 6, 2002 TYPE CERTIFICATE DATA SHEET NO. A35NM This data sheet which is a part of Type Certificate No. A35NM 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 Heavylift Helicopters Inc. 19378 Central Road Apple Valley, CA 92307 Type Certificate Holder Record: Hemet Valley Flying Service transferred TC A35NM to Heavylift Helicopters Inc. on August 6, 2002 I. Model C-130B (Restricted Category) Approved December 24, 1990 Engines 4 Allison turbo-prop T56- A7 or T56-A7-A or 501-D22 Fuel Commercial aviation turbine fuels conforming to ASTM Specification No. D 1655-59T, types Jet B, Jet A-1, or Jet A, or commercial equivalents of MIL-J-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 Take-off (5 minutes) 977/g176C 19,600 in lb. 40 /g176C - 100/g176C Maximum Continuous 932/g176C 18,000 in lb. 60 /g176C - 85/g176C Rated Speed: 100% - 13,820 erpm The maximum allowable power as measured by the torque meter is 19,600 in lb. for take-off. Propeller and Propeller Limits 4 Hamilton Standard hydromatic propellers 54H60-63 Blade A-7081B-2 54H60-97 A-7081B-2 Diameter 13 ft. 6 in. 2% reduction allowable for repair Single rotation, four blade assembly with governing speed setting 1020 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 Feather 92.5 /g177 0.20/g176 (a) (b) Low-pitch stop (min. flt. idle)21.00 /g177 0.50/g176 (a) Ground Idle 10.0 /g176 Reverse -6.0 /g176 /g177 1.0/g176 (b) A35NM Page 2 of 5 (a) Propeller blade angles are measured at the blade 42 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 applicable Model C-130B Maintenance Manual. Propeller Oil MIL-H-5606B Airspeed Limits V MO (Maximum operating) See Fig. 5-4 of T.O. 1C-130B-1 VA (Maneuvering) See Fig. 5-4 of T.O. 1C-130B-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-130B-1 shows stall speeds as a function of gross weight. VFE (Take-off & approach 50%) 183k VFE (Landing 100%) 145k VLO (Landing gear operation) 168k VLE (Landing gear extended) 168k VLL (Landing light extended) 168k Heated Windshield Limitations If electric windshield heat is operative, it must be used for all flight operations. Operation without electric windshield heat, 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. Weight & C.G. Limits (gear up or down) Condition Wt./Lbs. Most FWD (c.g.) % MAC F.S. Most Aft % MAC F.S. Takeoff 135,000 20.8 521.6 30.0 536.8 Landing 118,000 18.6 518.0 30.0 536.8 Zero Fuel 105,000 16.1 513.9 29.2 535.4 Reference USAF T.O. 1C-130B-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 center line of nose gear strut.) MAC 164.5”, leading edge MAC, F.S. 487.4 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, B.L. 64L, and a leveling plate is located on top of the cargo floor curb at approximately W.L. 150, B.L. 64L. Minimum Crew Three (3) - Pilot, Co-Pilot, and Flight Engineer Passengers None, except for essential crew as defined in FAR 91.39. Cargo Compartment Length 40 ft. Width 9 ft. 11 1/2 in. Height 9 ft. Usable volume 3,780 cu. ft. Maximum cargo 35,000 lbs. Reference Loading Data for approved loading schedule: USAF T.O. 1C-130B-9, “Cargo Loading Handbook,” and Supplement No. 141, dated January 4, 1970. A35NM Page 3 of 5 Maximum Fuel Quantity Tank Usable Fuel Total Fuel Arm (full) 1 (outboard) 8,710 lbs. 8,775 lbs. 544.9 2 (inboard) 7,995 lbs. 8,060 lbs. 554.6 3 (inboard) 7,995 lbs. 8,060 lbs. 554.6 4 (outboard) 8,710 lbs. 8,775 lbs. 544.9 Left Aux 5,915 lbs. 5,915 lbs. 556.7 Right Aux 5,915 lbs. 5,915 lbs. 556.7 Total 45,240 lbs. 45,500 lbs. The above fuel weights are not to be exceeded. (Tank Volume may be calculated using fuel density of 6.5 lbs./gal.) Arm varies with fuel loading. Reference Loading Data in USAF T.O. 1C-130B-1. See NOTE 2 for unusable fuel. Oil Capacity Four independent tanks, one in each nacelle above the engine (Arm 442.0). Capacity for each, 8 gallons usable, total 12 gallons. Capacity for all, 32 gallons usable, total 48 gallons. See NOTE 2 for system oil. Maximum Operating Altitude 32,000 ft Other Operating Limitations Aircraft shall be operated in compliance with the operating limitations specified in the following documents: (1) USAF T.O. 1C-130B-1, dated June 1, 1989 (2) USAF T.O. 1C-130B-1-1, dated August 24, 1988 Control Surface Movements Rigging Inst. Drawings Rudder 35 /g176 Right 35 /g176 Left 371951 Elevator 40 /g176 Up 15 /g176 Down 374429 Ailerons 25 /g176 Up 15 /g176 Down 356300 Rudder Tab 25 /g176 Right 25 /g176 Left 371951 Elevator Tab 6 /g176 Up 25 /g176 Down 374429 Aileron Tab 20 /g176 Up 20 /g176 Down 356300 Wing Flap 36 /g176 Down (100%) 372066 Serial Numbers Eligible Surplus military C-130B airp lanes that have been found to comply with the requirements of this data sheet. Certification Basis FAR 21.25 (a) (2) Restricted Category Forest and Wildlife Conservation 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-130B airplane with no major modifications except as required by Hemet Valley Flying Service Drawing List HVFS-130-DL-120 Revision NC, dated October 19, 1990, or later FAA approved revisions. A35NM Page 4 of 5 B. Airplane certified for the special purpose of Forest and Wildlife Conservation with the following limitations: 1. 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. 2. The following placard is to be installed in clear view of the pilot: “Restricted Category” “The carriage of persons or property for compensation or hire is prohibited.” “This airplane must be operated as a restricted category airplane and in compliance with the operating limitations stated in USAF T.O. 1C-130B-1 Section V and in the form of placards, markings and manuals.” 3. Carriage of hazar dous materials is prohibited unless compliance is shown with the applicable regulations in the Code of Federal Regulations Title 49, Part 175 (See AC 21-17, pg. 2, para. 4. a.(3)). NOTE 2 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). For information and method of calculating the airplane center of gravity, refer to T.O. 1C-130B-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 attitude. Unusable (include 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 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 1. Fuel must be loaded and used to provide compliance with the “Fuel Unbalance” limitation contained in USAF T.O. 1C-130B-1. Refer to USAF T.O. 1C-130B-1 for normal fuel management procedures. 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. A35NM Page 5 of 5 NOTE 3 The following documents are required for the Model C-130B: (a) USAF T.O. 1C-130B-1, dated June 1, 1989 “Flight Manual”. (b) USAF T.O. 1C-130B-1-1, dated August 24, 1988. (c) USAF T.O. 1C-130B-9, “Cargo Loading Handbook” and Supplement No. 141 dated January 4, 1990. (d) USAF T.O. 1-1B-40, “Handbook of Weight and Balance Data”. (e) USAF T.O. 1C-130B-5, dated January 31, 1973 and Supplements through February 1, 1990. NOTE 4 The aircraft must be serviced and maintained in accordance with maintenance manuals T.O. 1C-130A-2-1 through 1C-130A-2-13. FAA airworthiness directives for the 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 Prior to civil airworthiness certification, Hemet Valley Flying Service must show that the following have been accomplished: (a) Modification in accordance with FAA approved Hemet Valley Master Drawing List HVFS-130-DL-120 dated October 19, 1990. (b) Compliance with Engine truss mount repairs in Lockheed-Georgia Service Bulletin 82-153, dated December 1, 1966. (c) Compliance with all USAF Technical Orders which affect airworthiness. (d) Inspect all fuel tanks for sealant deterioration and repair as necessary. …..END…..