TCDS T00019LA

Page  1  2  3  4  5  6  7  Rev    6 5  4  6  6  6  6    DEPARTMENT OF TRANSPORTATION FEDERAL A VIATION ADMINISTRATION T00019LA Revision 6 Coulson Aviation (USA) Inc. EC-130Q C-130H January 31, 2024 TYPE CERTIFICATE DATA SHEET NO. T00019LA This data sheet, which is a part of Type Certificate No. T00019LA, prescribes the conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the 14 Code of Federal Aviation Regulations (14 CFR). Type Certificate Holder: C oulson Aviation (USA) Inc. 655 South Rock Blvd Reno, NV 89502 I. Model EC-130Q (Restricted Category) Approved August 23, 2013 Engines 4 - Allison T56-A- 15, T56-A-16, T56-A-16A, T56-A-423, or T56-A-423A. Military derived engine, TC not applicable. Intermixing of engines and positions is permissible. Fuel  Commercial aviation turbine fuels conforming to ASTM Specification No. D 1655-62T (Jet A), -66T (Jet A-1), Jet B types, or commercial equivalents of MIL-T-5624, grade JP- 4 or JP-5. Engine Limits Static, Standard Day, Sea Level: Turbine Inlet Temp. Torque Oil Temp RPM Limit Takeoff (5 min.) 1083° C 19,600 in-lbs 100° C Max 102% Military Power (30 min.) 1049° C 19,600 in-lbs 85° C Max 102% Maximum Continuous 1010° C 19,600 in-lbs 85° C Max 102% Propeller and Propeller TC: P-906 Propeller Limits 4 - Hamilton Standard 4 blade electrohydromatic propellers Hub 54H60-91, 54H60-111, or 54H60-117 Blade 7111D-2, A7111D-2, 7111E-2, or A7111E-2 Diameter: 13 ft. 6 in. 2% reduction allowable for repair, no further tolerance permitted Constant speed propeller, full feathering and reverse pitch. Single rotation, four blade assembly with governing speed setting 1020 RPM Propeller assembly is complete with spinner, feathering and reversing provisions, constant speed control, negative torque control and synchrophaser. Intermixing of propellers and positions is permissible. Maximum RPM 1040 (102% RPM), Minimum RPM 1000 (98%) T00019LA                                                                          2      Propeller Limits Blade Angles (degrees) See Note 6 (continued) Feather 92.5 ± 0.20 (a) Low-pitch stop (min. flt idle) 23.25 ± 0.50 (b) High-pitch stop NA (c) Reverse -7.3 to -9.7 ± 0.5 (d) Airspeed Limits (Knots IAS at 100% RPM) VMO (Maximum operating) * V A (Maneuvering) * VB (Turbulent air penetration) * VFE (50% ext Takeoff and Approach) 180K VFE (100% extension for Landing) 145K VLE (Landing gear extended) 165K VLL (Landing Light extended) 165K * See figure 1-4 of FAA Approved AFM, R-EC130Q-TCDS-AFM-1 Maximum Weights Max Ramp Weight: 155,000 lbs. Max Takeoff Weight: 155,000 lbs. w/ Ext Tanks; 150,718 lbs. w/o Ext Tanks Max Landing Weight: 155,000 lbs. w/ Ext Tanks; 150,718 lbs. w/o Ext Tanks Max Zero Fuel Weight: 115,000 lbs. Use FAA Approved Airplane Flight Manual for proper weight restrictions Center of Gravity Refer to Coulson AFM Figure 1-9: C.G. Limitations (C.G.) Range Straight line variation between points given Empty Weight None C.G. Range Datum 573.7 inches forward of jig points (white circled screws) located .75 inches outboard of wing station 65 joint, 2.5 inches aft of leading edge joint. Leveling Means Plumb bob leveling suspension fitting is located left side fu selage, station 637. Leveling grid is directly below the plumb bob fitting on the sidewall lighting shroud. Minimum Crew Three (3): Pilot, Co-pilot, Flight Engineer Number of Seats None, limited to the flight crew and persons essential to operations. Maximum Compartment Length – 624 inches (612” usable) Weights Width – 123 inches Height – 108 inches From Fuselage Station 257-869 (main cargo floor and aft ramp Maximum axle weights: 6000 lbs per axle Aircraft Ramp (Station 737-869): Maximum weight 5,000 lbs. EC-130Q does not contain provisions for palletized cargo. Fuel Capacity Tanks 1 & 4: 1350 US Ga llons each, Fully Serviced (1340 US Gallons Usable) Tanks 2 & 3: 1240 US Gallons each, Fully Serviced (1230 US Gallons Usable) External Tanks: 1400 US Gallons each, Fully Serviced (1400 US Gallons Usable) Auxiliary Tanks: 910 US Gallons each, Fully Serviced (910 US Gallons Usable) Total fuel: 9800 US Gallons, Fully Serviced (9680 US Gallons Usable) Oil Capacity Four nacelle tanks. Capacity each tank = 12US Gallons, 7.5 US Gallon expansion space Maximum Operating 29,000 ft. (limitation due to RVSM constraints) Altitude T00019LA                                                                          3      Control Surface Travel Aileron (Measurements at inboard end of aileron at trailing edge) U p D o w n Boost On : 25Deg (+1, -1.2) or 17.13” (+.52, -.72) 15Deg (+.7, -.5) or 10.33” (+.72, -.52) Trim Tab: 2.41” (±.15”) 2.41” (± .15”) Elevator (Measure elevator travel from top inboard edge above force link tab hinge) U p D o w n Boost On: 40 Deg (± .75) or 40.91” (± .79) 15Deg (+.75) or 15.61” (± .79) Trim Tab: 6 Deg (+5/6) or 1.15” (± .06) 25Deg (+5/6) or 4.77” (± .06”) Rudder (Measure from trailing edge of vertical stabilizer to lower end of rudder trailing edge) L e f t R i g h t Boost On: 37.55" (+1.25, -.82) 37.55" (+1.25, -.82) Trim Tab: 4.38" (+.15) 4.38" (+.15) Serial Numbers Approved  See Coulson Serial Numbers Approved Report, CAG110. Certification Basis Certification basis is 14 CFR 21.25(a)(2) for the special purpose of: (1) Carriage of Cargo Operations (Incidental) under 14 CFR 21.25(b)(7) a. This approval is only for the carriage of cargo incidental to the operator’s business. “Incidental to the operator’s business” means the cargo is not being carried for compensation or hire (for example, the cargo is the property of the operator or a crewmember). b. Internal Cargo Only. This approval is for cargo carried internally on the aircraft. It is not necessary for the cargo to be “outsize” cargo. Nor is it necessary for a standard category aircraft to be unavailable to carry the cargo. Aircraft certified under this type certificate are not eligible for multiple airworthiness certifications under 14 CFR 21.187. Production Basis None. No airplane may be produced under this approval. Equipment The basic required equipment as prescribed in the applicable Airworthiness Regulations (see Certification Basis), must be installed in the aircraft for certification. Aircraft must be modified in accordance with Coulson Aviation Group Documents: CAG1001, Revision NC, dated 07/05/13 or later FAA approved revision and CAG1003, Revision NC, dated 08/08/13 or later FAA approved revision. II. Model C-130H (Restricted Category) Approved December 7, 2020 Engines 4 - Allison T56-A-15. Military derived engine, TC not applicable. Fuel Commercial aviation turbine fuels confor ming to ASTM Specification No. D 1655-62T (Jet A), -66T (Jet A-1), Jet B types, or commercial equivalents of MIL-T-5624, grade JP-4 or JP-5. T00019LA                                                                          4      Engine Limits Static, Standard Day, Sea Level: Turbine Inlet Temp. Torque Oil Temp RPM Limit Takeoff (5 min.) 1083° C 19,600 in-lbs 100° C Max 102% Military Power (30 min.) 1049° C 19,600 in-lbs 85° C Max 102% Maximum Continuous 1010° C 19,600 in-lbs 85° C Max 102% Propeller and Propeller TC: P-906 Propeller Limits 4 - Hamilton Standard 4 blade electrohydromatic propellers Hub 54H60-91, 54H60-111, or 54H60-117 Blade 7111D-2, A7111D-2, 7111E-2, or A7111E-2 Diameter: 13 ft. 6 in. 2% reduction allowable for repair, no further tolerance permitted Constant speed propeller, full feathering and reverse pitch. Single rotation, four blade assembly with governing speed setting 1020 RPM Propeller assembly is complete with spinner, feathering and reversing provisions, constant speed control, negative torque control and synchrophaser. Intermixing of propellers and positions is permissible. Maximum RPM 1040 (102% RPM), Minimum RPM 1000 (98%) Blade Angles (degrees) See Note 6 Feather 92.5 ± 0.20 (a) Low-pitch stop (min. flt idle) 23.25 ± 0.50 (b) High-pitch stop NA (c) Reverse -7.3 to -9.7 ± 0.5 (d) Airspeed Limits (Knots IAS at 100% RPM) VB (Turbulent Air Penetration) 180 KIAS VH (Maximum Recommended Speed) * VD * VFE (50% ext Takeoff and Approach) 183 KIAS VFE (100% extension for Landing) 145 KIAS VLE (Landing gear extended) 168 KIAS VLL (Landing Light extended) 168 KIAS * See figure 1-3 of FAA Approved AFM, R-C130H-TCDS-AFM-1 Maximum Weights Max Normal Ramp Weight: 155,000 lbs. Max Normal Takeoff Weight: 155,000 lbs. Max Normal Landing Weight: 155,000 lbs. Use FAA Approved Airplane Flight Manual for proper weight restrictions Center of Gravity Refer to Coulson AFM Figure 1-4: C.G. Limitations (C.G.) Range Straight line variation between points given Empty Weight None C.G. Range Datum 573.7 inches forward of jig points (white circled screws) located .75 inches outboard of wing station 65 joint, 2.5 inches aft of leading edge joint. Leveling Means Plumb bob leveling suspension fitting is located left side fu selage, station 637. Leveling grid is directly below the plumb bob fitting on the sidewall lighting shroud. T00019LA                                                                          5      Minimum Crew Three (3): Pilot, Co-pilot, Flight Engineer Number of Seats None, limited to the flight crew and persons essential to operations. Maximum Compartment Length – 624 inches (612” usable) Weights Width – 123 inches Height – 108 inches From Fuselage Station 257-869 (main cargo floor and aft ramp Maximum axle weights: 6000 lbs per axle Aircraft Ramp (Station 737-869): Maximum weight 5,000 lbs. Fuel Capacity Tanks 1 & 4: 1350 US Ga llons each, Fully Serviced (1340 US Gallons Usable) Tanks 2 & 3: 1240 US Gallons each, Fully Serviced (1230 US Gallons Usable) External Tanks: 1400 US Gallons each, Fully Serviced (1400 US Gallons Usable) Auxiliary Tanks: 910 US Gallons each, Fully Serviced (910 US Gallons Usable) Total fuel: 9800 US Gallons, Fully Serviced (9680 US Gallons Usable) Oil Capacity Four nacelle tanks. Capacity each tank = 12US Gallons, 7.5 US Gallon expansion space Maximum Operating 29,000 ft. (limitation due to RVSM constraints) Altitude Control Surface Travel Aileron (Measurements at inboard end of aileron at trailing edge) U p D o w n Boost On : 25Deg (+1, -1.2) or 17.13” (+.52, -.72) 15Deg (+.7, -.5) or 10.33” (+.72, -.52) Trim Tab: 2.41” (±.15”) 2.41” (± .15”) Elevator (Measure elevator travel from top inboard edge above force link tab hinge) U p D o w n Boost On: 40 Deg (± .75) or 40.91” (± .79) 15Deg (+.75) or 15.61” (± .79) Trim Tab: 6 Deg (+5/6) or 1.15” (± .06) 25Deg (+5/6) or 4.77” (± .06”) Rudder (Measure from trailing edge of vertical stabilizer to lower end of rudder trailing edge) L e f t R i g h t Boost On: 37.55" (+1.25, -.82) 37.55" (+1.25, -.82) Trim Tab: 4.38" (+.15) 4.38" (+.15) Serial Numbers Approved See Coulson Serial Numbers Approved Report, R-C130-TCDS-SNR. Certification Basis Certification basis is 14 CFR 21.25(a)(2) for the special purpose of: (1) Carriage of Cargo Operations (Incidental) under 14 CFR 21.25(b)(7) a. This approval is only for the carriage of cargo incidental to the operator’s business. “Incidental to the operator’s business” means the cargo is not being carried for compensation or hire (for example, the cargo is the property of the operator or a crewmember). b. Internal Cargo Only. This approval is for cargo carried internally on the aircraft. It is not necessary for the cargo to be “outsize” cargo. Nor is it necessary for a standard category aircraft to be unavailable to carry the cargo. Aircraft certified under this type certificate are not eligible for multiple airworthiness certifications under 14 CFR 21.187. Production Basis None. No airplane may be produced under this approval. T00019LA                                                                          6      Equipment The basic required equipment as prescribed in the applicable Airworthiness Regulations (see Certification Basis), must be installed in the aircraft for certification. Aircraft must be configured in accordance with Coulson Documents: Coulson Aircraft Configuration Report R-C130H-TCDS-ACR, Revision IR, dated September 5, 2020 or later FAA approved revision and Coulson Top Configuration Drawing C-C130H- TCDS-01000, Revision IR, dated September 3, 2020 or later FAA approved revision. NOTES Note 1. Current weight and balance report including list of equipment included in certificated empty weight and loading instructions when necessary, must be in the aircraft at the time of original certification and at all times thereafter. Note 2.  [EC-130Q] Aircraft Center of Balance, determined from NAVAIR 01-1B-40, Technical Manual, Weight and Balance Data, must fall within the percent of the Mean Aerodynamic Chord (MAC) shown on the Coulson AFM Figure 1-9, Center of Gravity limitations. [C-130H] Aircraft Center of Balance, determined from USAF TO-1B-50, Technical Manual, Weight and Balance Data, must fall within the percent of the Mean Aerodynamic Chord (MAC) shown on the Coulson AFM R-C130H-TCDS-AFM-1 Figure 1-4. The weight of the system (unusable) fuel and oil as defined in USAF TO-1B-50. Note 3.  [EC-130Q] The Aircraft must be maintained and serviced in accordance with Coulson Instructions for Continued Airworthiness Document CAU-2013001 Revision A, dated August 21, 2013 or later FAA accepted revision. Any changes or revisions to the Coulson Instructions for Continued Airworthiness, Document CAU-2013001 Revision A, Airworthiness Limitations, Section 2, must be FAA Approved by the Aircraft Certification Office. [C-130H] The Aircraft must be maintained and serviced in accordance with Coulson Instructions for Continued Airworthiness Document R-C130H-TCDS-ICA Revision IR, dated June 30, 2020 or later FAA accepted revision. Any changes or revisions to the Coulson Instructions for Continued Airworthiness, Document R-C130H-TCDS-ICA Revision IR, Airworthiness Limitation Section, Chapter 04, must be FAA Approved by the Aircraft Certification Office. The aircraft may be maintained in accordance with an inspection program recommended by the manufacturer per 14 CFR 91.409 (f) (3) or an FAA Approved inspection program may be developed per 14 CFR 91.409 (f) (4). Note 4. Fuel Loading and Usage 1. Fuel must be loaded and used to provide compliance with the “Fuel Unbalance” limitation contained in Coulson AFM 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. Note 5. [EC-130Q] FAA approved Coulson AFM R-EC130Q-TCDS-AFM-1 must be available in the EC- 130Q aircraft for all flight operations. [C-130H] FAA approved Coulson AFM R-C130H-TCDS-AFM-1 must be available in the C-130H series aircraft for all flight operations. Note 6. (a) Propeller blade angles are measured at the 42 inch stations in accordance with Navair 03-20CBBJ-2 Technical Manual or TO 1C-130H-2-61JG-10-1. T00019LA                                                                          7      (b) Established under the conditions in the Navair 03-20CBBJ-2 Technical manual section 4-14 or TO 1C-130H-2-61JG-10-1. (c) Once feather is adjusted on the blades with the dome installed reverse needs to be 100-102 degrees from that setting. This is checked during overhaul to ensure proper buildup of the dome assembly and is not adjustable on the flight line or at the overhaul shop without violating the feather setting. This is dependent upon lobe and mechanical stop on parts that are the same for all models. Reference NAVAIR 01-75GAE-2-11 section 3-6 or TO 3H1-18-3 section 3.2.3. (d) The reverse angle is equal to the feather angle minus the range of the stop ring (101 ± 1.0 deg) per Navair 03-20CBBJ-2 Technical manual section 4-16. Note 7. Prior to original certification of each aircraft: (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) [EC-130Q] Each airplane is required to incorporate modifications as specified in CAG1001, Revision NC, dated July 5, 2013, or later FAA accepted revision and CAG1003, Revision NC, dated August 8, 2013 or later FAA accepted revision. [C-130H] Each airplane is required to be conf igured IAW Coulson Aircraft Configuration Report R-C130H-TCDS-ACR, Revision IR, dated September 5, 2020 or later FAA approved revision and Coulson Top Configuration Drawing C-C130H-TCDS-01000, Revision IR, dated September 3, 2020 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. (d) [EC-130Q] Compliance must be shown for each airworthiness directive listed in Coulson document CAG1005, Revision NC, dated August 2, 2013, or later approved document. [C-130H] Compliance must be shown for each airworthiness directive listed in Coulson document R-C130H-TCDS-AD, Revision IR, dated September, 2020, or later approved document. –END-