TCDS A32EU

Page No. 1 2 3 4 5 6 Rev. No. 2 2 2 2 2 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A32EU Revision 3 IAI, LTD ARAVA 101 ARAVA 101B July 26, 1988 TYPE CERTIFICATE DATA SHEET NO. A32EU This data sheet which is a part of Type Certificate No. A32EU 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 Israel Aircraft Industries Limited, Ben-Gurion Int’l Airport, Israel I. Model Arava 101 (FAR 23/FAR 135 Normal Category), Approved April 28, 1972 Engines 2 United Aircraft of Canada Limited, PT6A-27 Reduction gear ratio: 0.0663:1 Fuel See NOTE 4 Oil See NOTE 5 Engine Limits Rating ESHP SHP Output Shaft RPM % ITT °C Gas Gen. RPM % Takeoff (5 minutes) 715 680 2200 (100) 725 38,100 (101.6) Max continuous 715 680 2200 (100) 725 38,100 (101.6) Reverse - 400 2100 (95.5) - 33,100 ( 88) Propeller Hartzell Hub HC-B3TN-3D Blades T10282 HR or T10282 HRB Diameter 8 ft. 6 in. * Pitch settings at 30” station Static Feather +87.0° Flight fine (stop nut) +19.3° Reverse -15.0° Operating Flight fine (pitch stop) +14.5° Beta warning light +10.0° * See CAA Israel - approved Arava 101 Maintenance Manual for Rigging Instructions Propeller Control Unit Woodward 8210-002 Propeller Overspeed Governor Woodward 210631 A32EU2 Airspeed Limits (CAS) VMO (Maximum operating) 170 knots VFE (Flap operating) 105 knots VA (Maneuvering) 136 knots VMC (Minimum control) *60 knots * Autofeathering system operative C.G. Range Forward limit FUS, Sta. 5079, 200 inches aft of datum. Aft limit FUS. Sta. 5288, 208.2 inches aft of datum. This C.G. Range is applicable for all the A/C weights up to the max. takeoff weight. For all the flight envelope including takeoff and landing. Empty Weight C.G. Range None Maximum Weight Takeoff 12,500 lb Landing 12,500 lb Ramp Weight 12,620 lb Maximum Operating Altitude 15,000 ft. (except as limited by oxygen requirements of FAR 91 and FAR 135). Operation with AVGAS 10,000 ft. Control Surface Movements Aileron Up 16.0° Down 13.4° Spoiler Up 40.0° Flaps 0° to 25.0° Elevator Up 25.0° Down 10.0° Elevator Trim Tab Up 4.0° Down 20.0° Rudders Left 18.0° Right 18.0° Rudders Trim Tab Left 9.0° Right 3.0° See CAA Israel - approved Arava 101 Maintenance Manual for Rigging Instructions Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. See IAI Report 4630/4232 for CAA Israel-approved optional equipment. In addition the following equipment is required: Stall warning system - Safe Flight - Summing Unit P/N C-77606 Flap position transmitter P/N C-77609 Lift Transducer P/N C-77607 Stick Shaker P/N C-77702-2 CAA Israel - approved Airplane Flight Manual, dated April 28, 1972 II. Model Arava 101B (Normal Category), approved November 17, 1980 Model 101B differs from model 101 in having increased maximum T.O.W., L.W., and Z.P.W. for operations in accordance with SFAR 41C, engine changed to PT6A-36. Engines 2 Pratt & Whitney Aircraft of Canada Limited, PT6A-36 Reduction gear ratio: 0.0663:1 Fuel See NOTE 4 Oil See NOTE 5 A32EU3 Engine Limits Rating ESHP SHP Output Shaft RPM % ITT °C Gas Gen RPM % Takeoff (5 minutes) 783 750 2200 (100) 805 38,100 (101.6) Max continuous 783 750 2200 (100)* 805 38,100 (101.6) Reverse - 400 2100 (95.5) - 33,750 ( 90) * 1980 RPM (90%) maximum for normal operation. Propeller Hartzell Propeller Inc. Hub HC-B3TN-3D Blades T10282HR or T10282HRB or T10282R or T10282RB Diameter 102 inches, no reduction allowed *Pitch settings at 30” station Static Feather +87.0° Flight fine (stop nut) +19.3° Reverse -15.0° Operating Flight fine (pitch stop) +14.5° Beta warning light +10.0° * See CAA Israel - approved Arava 101B Maintenance Manual for Rigging Instructions. Propeller Control Unit Woodward 8210-002 Propeller Overspeed Governor Woodward 210631 Airspeed Limits (CAS) VMO (Maximum operating) 170 knots VFE (Flap operating) 120 knots VA (Maneuvering) 145 knots VMC (Minimum control) *70 knots * Autofeathering system operative C.G. Range 5 0 7 9 5 1 1 6 5 3 2 9 FU S . ST A . 2 0 0 2 0 1 . 4 2 0 9 . 8 in c h es af t o f d at u m 2 4 2 5 . 7 8 3 6 % M . A . C. 1 3 , 5 0 0 1 5 , 1 4 0A IRCRA FT W EIGH T (lb . ) Empty Weight C.G. Range None Maximum Weight Takeoff 15,140 lb Landing 15,000 lb Zero Fuel Weight 14,000 lb Ramp Weight 15,260 lb Maximum Operating Altitudes 27,000 ft. (except as limited by oxygen requirements of FAR 91 or FAR 135). A32EU4 Control Surface Movements Aileron Up 16.0° Down 13.4° Aileron Trim Tab Up 10.5° Down 10.5° Spoiler Up 40.0° Flaps 0° to 25° Elevator Up 25.0° Down 10.0° Elevator Trim Tab Up 4.0° Down 20.0° Rudders Left 18.0° Right 18.0° Rudder Trim Tab Left 13.0° Right 7.0° See CAA Israel - approved Arava 101B Maintenance Manual for Rigging Instructions Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. See IAI Report ARV000/801093 for CAA Israel - approved optional equipment In addition the following equipment is required: Stall warning system - Safe Flight- Summing Unit P/N C-77606 Flap position transmitter P/N C-77609 Lift transducer P/N C-77607 Horn P/N C-77602 CAA Israel - approved Airplane Flight Manual, dated October 20, 1980, and with Revision 3 for operations in accordance with SFAR 41C. Approved Installation See Airplane Flight Manual III. Data pertinent to all models Datum 23.6 inches (600 MM) forward of nose, 180.2 inches (4577MM) forward of leading edge MAC 82.3 inches (2090MM) with L.E. at FUS. STA. 4577 Leveling Means Longitudinal - Place a level on cabin floor seat rail. Lateral - Place a level across cabin seat rail. Minimum Crew 1 pilot Number of Seats 19 passengers (in the passenger compartment) Maximum Baggage 550 lb. (75 p.s.f.) between FUS. Stations 7730 and 8840 (304 and 348 in aft of datum) Fuel Capacity (U.S. Gal.) Usable - L.H. Tank 202; R.H. Tank 202; Total - 205.3 per tank (moment ARM 214 in aft of datum) See NOTE 1 for data on system fuel and oil. Oil Capacity (U.S. Gal.) Usable - 1.5 per engine (moment ARM 177.3 in., aft of datum). Total - 3.0 (moment ARM 174.8 in., aft of datum) See NOTE 1 for data on system fuel and oil. Serial Nos. Eligible See “Import Requirements” Import Requirements A U.S. Airworthiness Certificate may be issued on the basis of the Israel CAA “Export Certificate of Airworthiness” signed by a representative of the Civil Aviation Administration of Israel containing the following statement: “The airplane covered by this certificate has been examined, tested and found to conform to the type design approved under Type Certificate No. A32EU, and to be in a condition for safe operation.” (See NOTE 6). A32EU5 Certification Basis FAR 21.29, FAR Part 23, effective February 1, 1965. Including Amendments 23-1 through 23-6, paragraph 23.939 (b) and 23.1141 of FAR 23 Amendment 7, Special Conditions 23-41EU-11 issued May 10, 1972, Compliance has been shown with: - FAR 25.471 through FAR 25.509, FAR 25.573 and FAR 25.721 through FAR 25.735, effective February 14, 1975 for the Arava 101B - Appendix A to FAR Part 135 as adopted by Amendment 135-18, effective July 19, 1970 for the Arava 101 and 101B - SFAR 27, Amendments 27-1 through 27-3 (Fuel Venting) by incorporation of IAI Drawings 101 653-30-00 and 101 653-31-00 for the Arava 101B - SFAR 41, effective October 17, 1979, and SFAR 41C, effective September 13, 1982 for the Arava 101B - FAR 36, Amendments 36-1 through 36-9 for the Arava 101B Compliance has been established with the following optional requirements: - FAR 25.1191 through FAR 25.1201, effective August 1, 1969, Fire Extinguisher System: Arava 101. - FAR 23.979, effective December 20, 1973, Pressure Fueling System: Arava 101B. - FAR 25.1419, effective May 8, 1970, Ice Protection: Arava 101B. Type Certificate No. A32EU, issued April 28, 1972 for the Arava 101 and amended November 17, 1980 for the Arava 101B. Effective date of application for Type Certificate per FAR 21.17 (c) (2), August 1, 1969. Service Information Israel Aircraft Industries Maintenance and Structural Repair Manuals and all Service Bulletins are approved by CAA Israel and include a statement to that effect. NOTES NOTE 1 (a) Current Weight and Balance Report including list of equipment included in certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. (b) Unusable and System Fuel and Oil and all hydraulic fluid must be included with certificated empty weight. Unusable fuel is defined by FAR 23.959. The quantity indicators are calibrated to read zero with this amount in the tanks. System fuel includes fuel in lines, and components which is in addition to unusable. Total airplane unusable fuel is : 6.5 U.S. gal. (ARM 214 in. aft of datum). Total system fuel (undrainable) is : 1.05 U.S. gal. (ARM 189 in. aft of datum). System oil includes oil in lines and coolers and undrainable as follows: Total system unusable is: 1.5 U.S. gal. (ARM 172.3 in. aft of datum). NOTE 2 All placards required in the limitation section of CAA Israel - approved Airplane Flight Manual must be installed in the appropriate locations. Each individual airplane must be fitted with a placard which specifies approved types of operation (such as VFR, IFR, DAY or NIGHT) to which the airplane is limited by the equipment installed. A32EU6 NOTE 3 Section II of the Inspection Schedule, Document P/N 101B-181-201 is FAA - approved and it specifies mandatory replacement time and structural inspection intervals for the landing gear and support structure. These airworthiness limitations may not be changed without FAA approval. Certain engine parts are life limited. These limits are listed in P & WACL Engine Service Bulletin No. 1002. NOTE 4 Arava 101: JP-1, JP-4, and JP-5 fuels conforming to Pratt & Whitney Aircraft of Canada Spec. No. CPW 204 and later revisions. Arava 101B: JP-1, JP-4, and JP-5 fuels conforming to Pratt & Whitney Aircraft of Canada Spec. No. CPW 204 and later revisions. For operation at ambient temperatures below 0°C, anti-icing additives conforming to specifications MIL-I-27686D, MIL-I-27686E or Canadian Spec. 3-GP-526A must be used in accordance with the Airplane Flight Manual. NOTE 5 P & WACL PT6 Engine Service Bulletin No.1001 lists approved brand oils. Note: Oil conforming to specifications MIL-I-7808 not approved for the Arava 101B. NOTE 6 For the Model Arava 101B, the United States Airworthiness Certificate shall be endorsed “This airplane at weights in excess of 5,700 kg does not meet the airworthiness requirements of ICAO as prescribed by Annex 8 of the Convention on International Civil Aviation”. .....END.....