TCDS 7H1

Page No. 1 2 3 4 5 6 7 Rev. No. 16 - - 14 15 - 16 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 7H1 Revision 16 Airbus Helicopters SE 3130-ALOUETTE II SE 313B-ALOUETTE II SA 3180-ALOUETTE ASTAZOU SA 318B-ALOUETTE ASTAZOU SA 318C-ALOUETTE ASTAZOU January 10, 2014 TYPE CERTIFICATE DATA SHEET NO. 7H1 This data sheet which is a part of type certificate No. 7H1 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: Airbus Helicopters Aeroport Internati onal Marseille Provence 13725 - Marignane - Cedex France TC Holder Record: Eurocopter France changed name to Airbus Helicopters on January 1, 2014. Section I. - Model SE 3130 Alouette II, approved 14 January 1958 - Model SE 313B Alouette II, approved 28 August 1968 Engine Model SE 3130: Turbomeca Ar touse 11B1, IIC, IIC1, IIC2, IIC5, IIC6 Model SE 313B: Turbomeca Artouste IIC5, IIC6 FUEL SPECIFICATION (Latest Amendment) REMARKS FRENCH NATO USA UK AIR 3405 (TRO) F34 D.eng.RD 2453 AVTUR/FA II F35 D.eng.RD 2494 AVTUR AIR 3407 (TR4) F40 MIL-T-5624 (JP.4) D.eng.RD 2486 AVTAG FA II F45 D.eng.RD 2486 AVTAG AVIATION FUELS AIR 3404 (TR5) F42 TR.5 F44 MIL-T-5624 (JP.5) D.eng.RD 2498 AVCAT F12 MIL-G-5572 25 hr. maximum between overhauls Gasoline AIR 3401 F18 F22 MIL-G-5572 D. eng. RD 2485 is is recommended to add 1% to 2 % oil, preferably mineral oil. NAVY 7120 STM Gas Oil = O F75 MIL-F-16884 DEF STAN 31-4 Do not use below - 15°C FUELS 7120 STM Gas Oil = 20 F76 OTHER FUELS Automotive Gasoline DCEA/2D MT 80 F46 DEF 2401 25 hr maximum between overhauls it is recommended to add 1% to 2% oil; preferably mineral oil. Illuminating oil (kerosene) DCEA/IIC F58 V V K 211 DEF 2403 Sulfur: less than 02% Flash point: not less than 38°C. Freezing point: not greater than -40°C. 2 of 7 7H1, Rev 16 FUEL SPECIFICATION (Latest Amendment) REMARKS FRENCH NATO USA UK OTHER FUELS (Cont’d) Automotive Diesel oil 40 Dieso DCEA/21C F54 V V F 800 Class DF 2 TS 10003 Sulfur: less than 1% Kinematic viscosity at 20°C: less than 9 cst. Do not use below O°C. ENGINE OIL SPECIFICATION (L atest Amendment) REMARKS FRENCH NATO USA UK Normal AIR 3512 0.138 Shell Turbine oil 9 Esso Aviation oil 57 Caltex Jet eng. oil heavy DED 2479 Refer to instruction entitled "OIL COLD" in paragraphs 1.6.1 and 1.6.2 in Flight Manual For outside temperature below -10°C AIR 3515 0.135 Aeroshell turbine oil 3 Esso Aviation utility oil F Caltex Jet eng. oil medium heavy Caltex aircraft instrument oil D.Eng.RD 2490 or DEF 2001 For out-side temp. between -15°C +5°C DED 2480 Engine Limits Maximum speed 34,000 r.p.m. Maximum power 400 hp Maximum tail pipe temperature (t4) 550°C for a max. of 15 min. Maximum continuous tail pipe temp. 510°C Rotor limits Maximum speed 420 r.p.m. Minimum speed 280 r.p.m. Constant speed, power-on flight 360 r.p.m. Maximum Weight Model SE 3130 : 3300 lb. Model SE 313B : 3500 lb. (See NOTE 8) Section II. - Model SA 3180 Alouette - Astazou, approved November 25, 1964 - Model SA 318B Alouette - As tazou, approved August 28, 1968 - Model SA 318C Alouette - As tazou, approved August 28, 1968 Engine Turbomeca As tazou IIA power unit 3 of 7 7H1, Rev 16 FUEL SPECIFICATION (Latest Amendment) REMARKS FRENCH NATO USA UK AIR 3405* (TRO) F34 D.eng.RD 2453 AVTUR/FS II F35 D.eng.RD 2494 AVTUR AVIATION AIR 3407* (TR4) F40 MIL-T-5624 (JP.4) D.eng.RD 2454 AVTAG FS II FUELS F45 D.eng.RD 2486 AVTAG AIR 3404* (TR5) F42 TR.5 * F44 MIL-T-5624 (JP.5) D.eng.RD 2498 AVCAT F12 MIL-G-5572 25 hr. maximum between overhauls Gasoline * AIR 3401 F18 F22 MIL-G-5572 D.eng.RD 2485 it is recommended to add 1% to 2% oil. Preferably mineral oil. 7120 STM Gas Oil =O F75 MIL-F-16884 DEF STAN 31-4 Do not use below -15°C For the normal use of this fuel the AZ 156 NAVY FUELS 7120 STM Gas Oil =20 F76 unit containing one of the fuel marked*: -is recommended in all cases. -is essential if the temperature is below 10°C. Automotive Gasoline DCEA/2D MT 80 F46 DEF 2401 25 hr. maximum between overhauls it is recommended to add 1% to 2% oil, preferably mineral oil. OTHER FUELS Illuminating oil (kerosene) DCEA/IIC F58 V V K 211 DEF 2403 Sulfur: less than0.2% Flash point: not less than 38°C. Freezing point: not greater than -40°C Automotive Diesel Oil 40 Dieso DCEA/21C F54 V V F 800 Class DF 2 TS 10003 Sulfur: less than 1% Kinematic viscosity at 20°C less than 9 cst. Do not use below 0°C. For the normal use of this fuel the AZ 156 unit (SNIAS S.B. 28.14) containing one of the fuel marked*: - is recommended in all cases - is essential if the temperature is below 10°C. ENGINE OIL SPECIFICATION (L atest Amendment) REMARKS FRENCH NATO USA UK AIR 3513 0.148 MIL-L-7808 NORMAL AIR 3515 0.135 Aeroshell Turbine Oil 3. Esso Avn. Utility Oil F D.Eng.RD 2490 Use of brands other than those shown opposite requires S.G.A.C. approval. Caltex jet engine oil medium heavy The mixing of oils AIR 3513 and AIR 3515 is not permitted. The system should be flushed when changing from one type to the other. 4 of 7 7H1, Rev 16 Engine Limits Engine speed : 43,500 r.p.m. held c onstant by governor (transient variations of + 1500 r.p.m. are permissible when applyi ng rapid collective - pitch variations) Maximum takeoff power : 523 hp. (See NOTE 6) Maximum continuous power: 473 hp. (See NOTE 6) Maximum tail pipe temperature for starting (30 seconds): 550°C peak value 630°C for period not exceeding 3 seconds (between 5,000 and 10,000 r.p.m.) Maximum for take off : 525°C (See NOTE 6) Maximum continuous ta il pipe temperature : 500°C (See NOTE 6) Rotor limits Maximum speed 420 r.p.m. Minimum speed 280 r.p.m. Constant speed, power-on flight 362 r.p.m. Maximum Weight Model SA 3180 : 3300 lb. Model SA 318B : 3500 lb. (See NOTE 8) Model SA 318C : 3650 lb. (See NOTE 8) Section III, Data Applicable to All Models Airspeed Limits Never Exceed Speed: 105 kt for SE 3130, SE 313B ) See NOTE for SA 3180, SA 318B ) required placard 111 kt for SA 318C ) C.G. Range (107.1) to (120.9) for SE 3130, SE 313B (107.09) to (124.02) for SA 3180, SA 318B , and for SA 318C with speed limitation. Datum 118.11 forward of rotor centroid. Leveling Means Two leveling lugs on body structure LH lower corners and two leveling lugs on body structure RH lower corners. Number of Seats 5. Pilot, co-pilot (51); 3 passengers (87). Maximum baggage 220 lb. under rear seat (86.6) (with 5 persons of 176 lb. ea. on board) or 507 lb. behind pilot's and front passenger's se ats, with rear seat folded (74.8) (One pilot and one front passenger on board). (See NOTE 2 for required placard). Fuel capacity 153 gals. (120), usable 149 gals. Oil Capacity 2 gals. (137 for model SE 3130 and SE 313B) (150 for model SA 3180, SA 318B and SA 318C) Rotor Blade Movements For rigging information, refer to Alouette II or Alouette Astazou Maintenance Manual, as applicable. Serial Nos. Eligible The French Government Certif icate of Airworthiness for Export endorsed as noted under "Import Requirements" must be submitted for each individual helicopter for which application for certification is made. For applications for Standard Airworthiness Certificates made after May1, 2004, a review of historical records is needed to determine if the helicopter was delivered to and operated by the military. If the helicopter has military history, the helicopter is not eligible for a Standard Airworthiness Certificate unless a copy of a Standard Airworthiness Certificate issued at the time of delivery to the military is submitted. Certification Basis CAR 10. CAR 6 effective Janua ry 15, 1951 including Amendment 6-1 through 6-8, plus Special Conditions notified by the U.S. govern ment to the Government of France in FAA letter of May 28, 1957. Type Certificate No. 7H1 issued January 14, 1958 Date of Application October 11, 1955 5 of 7 7H1, Rev 16 The French Direction Generale de l’Aviation Civile (DGAC) originally type certificated this rotorcraft under its type certificate TC 1. The FAA validated this product under U.S. Type Certificate Number 7H1. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the DGAC. Import Requirements The FAA can issue a U.S. airworthiness certificate based on a National Aviation Authority (NAA) Export Certificate of Airworthiness (Export C of A) signed by a representative of the French Generale de l’Aviation Civile (DGAC) on behalf of the European Community. The Export C of A should contain the following statement: “The aircraft covered by this certificate has been examined, tested, and found to comply with the type design approved under U.S. Type Certificate Number 7H1 and to be in a condition for safe operation.” Equipment The basic required equipment as prescrib ed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following item of equipment is required: (a) SGAC approved Alouette II or Alouette Astazou Flight Manual, as applicable. Service Information Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – by the French Generale de l’Aviation Civile (DGAC). Any such documents are accepted by the FAA and are considered FAA approved.  Service Bulletin,  Structural repair manuals,  Vendor manuals,  Aircraft flight manuals, and  Overhaul and maintenance manuals. This applies only to the acce ptance of the type design data. NOTE 1: Current weight and ba lance report, including list of equipment included in certificated empty weight, and loading instructions when necessary, must be provid ed for each helicopter at the time of original certification. In order to obtain the most consistent weight and balance results, all model helicopters should be weighed on jackpoints rather than on skids, wheels or floads. When changes are made to the helicopter which affect the weight and balance refer to the Flight Manual for instructions. The certificated empt y weight and corresponding center of gravity location must include unusable fuel of 26 lb. (120) and undrainable oil of 2.2 lb. (162.2 for models SE 3130, SE 313B and 172.5 for models SA 3180, SA 318B and SA 318C). NOTE 2: The following placards must be displayed: (1) In full view of the pilot: (a) "This helicopter must be operated in compliance with the operating limitations specified in the SGAC approved helicopter Flight Manual". (b) "Never exceed speeds. Variation of Vne with altitude and weight". (b) (1) SE 3130 Alouette II and SA 3180 Alouette Astazou. 6 of 7 7H1, Rev 16 Altitude Sea Level 3,000 ft 6,000 ft 9,000 ft 12,000 ft 13,500 ft Weight (lb) kt kt kt kt kt kt 3,300 105 95 85 3,100 105 100 90 80 2,900 105 105 95 85 75 2,700 105 105 100 90 80 75 2,400 105 105 105 95 85 80 2,200 105 105 105 100 90 85 (b) (2) SE 313B Alouette II and SA 318B Alouette Astazou. Altitude Sea Level 3,000 ft 6,000 ft 9,000 ft 12,000 ft 13,500 ft Weight (lb) kt kt kt kt kt kt 3,500 100 90 80 3,300 105 95 85 3,100 105 100 90 80 2,900 105 105 95 85 75 2,700 105 105 100 90 80 75 2,400 105 105 105 95 85 80 2,200 105 105 105 100 90 85 (b) (3) SA 318C Alouette Astazou Altitude Sea Level 3,000 ft 6,000 ft 9,000 ft 12,000 ft 13,500 ft Weight (lb) kt kt kt kt kt kt 3,650 111 108 95 78 3,500 111 108 95 78 3,300 111 108 95 81 67 3,100 111 108 96 84 73 67 2,900 111 108 98 88 78 73 2,700 111 108 100 92 84 80 2,400 111 108 101 95 89 85 (2) Secured to the floor in the rear right corner: "Maximum baggage 220 pounds under rear seat (+86.6 in) with 5 persons of 176 pounds each on board, or 507 pounds behind pilot and front passenger seats, with rear seat folded (+74.8 in) and one pilot and one front passenger on board". NOTE 3: The retirement times of critical parts are listed in Alouette II Maintenance Manual, or Alouette Astazou Maintenance Manual, chapters 5, SGAC-approved. NOTE 4: These helicopters must be serviced and maintained in conformance with the following manuals, as applicable, of which chapter 5 "Per iodic Inspection" is SGAC approved: (a) Alouette II Maintenance Manual (airframe and engine) (b) Alouette - Astazou Maintenance Manual (airframe and engine) NOTE 5: The Siren Sling and Air Equipm ent rescue hoist are special purpose equipment and should be operated in accordance with the limitations described in CAR 8. Information concerning operation limitations is also contained in the heli copter Flight Manual. NOTE 6: Maximum certificated horsepower for this installation is limited to 400 hp due to rotor transmission limitations. For the same reason, the ma ximum permissible exhaust gas temperatures are limited to: - Takeoff: 490°C (For OAT 15°C and below) and 515°C at OAT: 45°C; Straight line interpretation between 15°C and 45°C. - Maximum continuous : 460°C 7 of 7 7H1, Rev 16 NOTE 7: To convert the model SE 3130 Alouette II to th e Model SA 3180 Alouette-Astazou the following assemblies must be installed in place of the corresponding assemblies designed for the SE 3130 Alouette II in accordance with Sud Aviation modification AM 817: Assembly Drawing No. - Engine Astazou II A 3180-50-50.000 - Oil system (engine and M.G.B.) 3180-54-10.000 - Engine vent 3180-50-50.010 - Clutch unit 3180-63-10.000 - Rear engine mount 3180-21-03.100 or 3180-21-03.200 - Engine controls 3180-76-13.000 - Fuel system 3180-52-00.000.1 - Main gear box 3160-62-00.000.9 - Main rotor shaft 3160.68.10.000.2 - Starter wiring installation 3180.72.22.300 - Spring actuator 3180-89-00.000 - Instrument panel installation 3180-76.50.000 - Firewall asse mbly 3180-59-10.000 - Transmission support platform 3180-27-60.000 (Stainless steel Further, the following equipmen t (optional on Alouette II) must mandatorily be installed. - Servo-unit installation 3130-73-71.000 NOTE 8: (1) to convert the model SE .3130 Alouette II to the Model SE 313B or the model SA 3180 Alouette - Astazou to the Model SA 318B the following modifications are required: - High pitch stop adjusted for 15° - Reinforced main rotor blades P/N 3130-11-20.000 - Body structure reinforced transversal bar P/N 3130-21-15.100 - Artouste IIC5 or IIC6 engines must be installed for model SE 3130 Alouette II only. - Instruction plates P/N 3130-25-20.090, index mark s on pitch indicator P/N 3130-90-00.144, instruction plates P/N 3180-76-26.011. - Modification of marking helicopter 318-00-10.0 06 (Alouette-Astazou) 313B-00-00.020 (Alouette II). - And the following tail rotor g ear box/tail rotor hub modifications: Either: Reinforced tail rotor gear box P/N 3130-66-70.000 and tail rotor head P/N 3130-33-30.000.1. or Fork type rotor hub 3180-33-00.000 and tail rotor blades P/N 3160-34-10.000.6 Tail rotor gear box P/N 3160-66-10.000.1 The following modifications must be embodied before floats are installed: - Reinforced float type landing gear P/N 3130-73-54.500 - Hydraulic dampers on float type landing gear P/N 3130-46-10.560 (2) To convert the model SA 3180 Alouette-Astazou to the model SA 318C the following modifications are required in addition to the foregoing (except instruction plates P/N 3130-25-20.090 and P/N 3180-76- 26.011) - Landing gear reinforced transversal bar P/N 3180-46-10.010 or P/N 3180-46-10.015 - Landing gear shock strut P/N 3180-46-10.100 - Instruction plates P/N 3180-25-10.040 and P/N 3180-76-26.019 - Marking on airspeed indicator P/N 3180-90-00.006 NOTE 9: Effective January 1, 2014, Eurocopter France name was changed to Airbus Helicopters. ...END...