TCDS A26WE

Page No. 1 2 3 4 5 6 7 8 9 Rev. No. 8 6 6 6 6 6 6 6 6 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A26WE Revision 8 Weatherly 620 620TP 620A 620B 620B-TG November 5, 2014 TYPE CERTIFICATE DATA SHEET A26WE Type Certificate Holder: Weatherly Aircraft Company 2034 W/ Potomac Avenue Chicago, Illinois 60622-3152 Type Certificate Ownership Record GBECK, Inc. (D.B.A.) Weatherly Aviation Company, Inc., 2100 Flightline Drive. Lincoln, California 95648 transferred ownership of TC A26WE to Weatherly Aircraft Company on November 6, 2000 I - Model 620 (Restricted Category) Approved October 24, 1979 (See ALL MODEL Section) (See NOTES Section) Engine Pratt & Whitney R985-AN-1, AN-3, or AN-14B Fuel 80/87 Minimum Grade Aviation Gasoline. Alternate fuel is 100LL. Engine Limits Engine Model AN-1 & AN-3 HP RPM In. Hg. Press Alt. Takeoff (1 min.) at SL 450 2300 37.5 SL Maximum Continuous at SL 350 2100 33.0 SL Maximum Continuous 350 2100 32.0 3000 ft. (Rated Pressure Alt.) 350 2100 31.0 6000 ft. Straight line variation of manifold pressure between points listed. Engine Model AN-14B HP RPM In. Hg. Press Alt. Takeoff (1 min.) at SL 450 2300 36.5 SL Maximum Continuous at SL 350 2100 31.5 SL Maximum Continuous 350 2100 30.5 3000 ft. (Rated Pressure Alt.) 350 2100 29.5 6000 ft. 350 2100 29.0 7800 ft. Straight line variation of manifold pressure between points listed. Propeller & Propeller Limits Hartzell HC-B3R30-4 or -4B Hub with R10152-5½ R Blades Diameter: Not over 95½ ins.; Not under 95½ ins. Pitch settings at 30" station: (Constant Speed) - 16° Low, 28° High Static RPM at maximum throttle setting not over 2300 RPM; not under 2200 RPM. Airspeed Limits Without Spreader or Tip Vanes VNE - Never Exceed 176 mph (153 knots) IAS or CAS VNO - Normal Operating 140 mph (122 knots) IAS or CAS VA - Maneuvering 129 mph (112 knots) IAS or CAS With P/N 50453 Spreader Installed VNE - Never Exceed 155 mph (135 knots) IAS or CAS A26WE 2 With P/N 50520 Tip Vanes Installed VNE - Never Exceed 166 mph (144 knots) IAS or CAS Airspeed limits are unchanged with Cowl Speed Ring installed P/N 50784 per Drawing 50783 Maximum Operating Altitude 15,500 ft. C.G. Range Inches aft of datum (+22.1) to (+26.0) at all weights Empty Weight C.G. Range None Maximum Weight 4000 lbs. No. of Seats 1 (+68.0) Hopper Capacity 2000 lbs. (+15.0) Baggage Shelf 25 lbs. (+91.25) Fuel Capacity 72.5 gal. total Right Wing Tank 27½ gal. with unusable 2½ gal. (+36.0) Left Wing Tank (combined with center tank) 45 gal. with unusable 5 gal. (+36.0) Oil Capacity 6.7 gal. plus 1 gal. in system (-22.2) Control Surface Rudder Left 20° ± 1° Right 20° ± 1° Elevator Up 27° ± 1° Down 15° ± 1° Aileron Up 26° ± 1½° Down 13½° ± 1½° Serial Nos. Eligible 1501 and subsequent II - Model 620TP (Restricted Category) Approved October 17, 1980 (See ALL MODEL Section) (See NOTES Section) Engine Pratt & Whitney PT6A-11AG Fuel Jet A and Jet B fuel. Refer to P&WC Service Bulletin No. 12144. With certain limitations, automotive diesel fuels are approved for use. Engine Limits Engine HP NP RPM NG RPM Takeoff (5 min. SL) 500 2200 (100%) 38,100 (101.5%) Maximum Cont., SL 350 2000 (91%) 38,100 Maximum Reverse 475 2112 (96%) 38,100 Maximum torque (steady) = 1194 lb. ft. (38.6 psig) (5 min. SL) Maximum torque (accel.) = 1800 lb. ft. (58.3 psig) (5 sec.) Maximum Permissible Temperature Inter-Turb. Temp. Takeoff 1292°F (700°C) Maximum Continuous 1292°F (700°C) Starting Transient 1994°F (1090°C) Oil Temperature Normal range 50°F to 210°F (10°C to 99°C) Maximum 210°F (99°C) 3 A26WE Oil Pressure Normal range (27,000 RPM NG or above) 80-100 psig Minimum 40 psig Maximum 100 psig Fuel Pressure Engine inlet pressure is measured at the inlet to the engine high pressure gear pump. (This point is also the outlet of the Weatherly installed low pressure pump mounted on the engine). Minimum 15 psig Maximum 35 psig Propeller & Propeller Limits Hartzell reversing propeller with Woodward overspeed governor Model HC-B3T Hub No. HC-B3TN-3 Blade No. T10282-6 Diameter Maximum 96 inches Minimum 92 inches Pitch settings at 30 inch radius Low pitch 16° ± 0.5° Propeller spinner, Hartzell P/N 3434-6 Overspeed governor, Woodward P/N A210507 Airspeed Limits Without Spreader or Tip Vanes VNE - Never Exceed 176 mph (153 knots) IAS or CAS VNO - Normal Operating 140 mph (122 knots) IAS or CAS VA - Maneuvering 129 mph (112 knots) IAS or CAS With P/N 50453 Spreader Installed VNE - Never Exceed 155 mph (135 knots) IAS or CAS With P/N 50520 Tip Vanes Installed VNE - Never Exceed 166 mph (144 knots) IAS or CAS C.G. Range Inches 3500 lbs. gross weight (+24.8) to (+22.1) with straight line variation to 4000 lbs. gross weight (+23.6) to (+22.1) Empty Weight C.G. Range None Maximum Weight 4000 lbs. No. of Seats 1 (+68.0) Hopper Capacity 2000 lbs. (+15.0) Baggage Shelf 15 lbs. (+91.25) Fuel Capacity 96 gal. total Right Main Tank with Right Outer Wing Tank, 42 gal., unusable 6 gal. (+36.0) Left Main Tank (combined with center tank) with Left Outer Wing Tank, 54 gal., unusable 6 gal. (+36.0) Oil Capacity 2.3 gal. plus .75 gal. in system (-24.0) Maximum Operating Altitude 15,000 ft. A26WE 4 Control Surface Rudder Left 20° ± 1° Right 20° ± 1° Elevator Up 27° ± 1° Down 15° ± 1° Aileron Up 26° ± 1½° Down 13½° ± 1½° Serial Nos. Eligible 1502 and subsequent, Model 620TP airplanes have the letters TP following the numerical serial number. III - Model 620A (Restricted Category) Approved March 25, 1987 (See ALL MODEL Section) (See NOTES Section) Engine Pratt & Whitney R985-AN-1, AN-3, or AN-14B Fuel 80/87 Minimum Grade Aviation Gasoline. Alternate fuel is 100LL. Engine Limits Engine Model AN-1 & AN-3 HP RPM In. Hg. Press Alt. Takeoff (1 min.) at SL 450 2300 37.5 SL Maximum Continuous at SL 350 2100 33.0 SL Maximum Continuous 350 2100 32.0 3000 ft. (Rated Pressure Alt.) 350 2100 31.0 6000 ft. Straight line variation of manifold pressure between points listed. Engine Model AN-14B HP RPM In. Hg. Press Alt. Takeoff (1 min.) at SL 450 2300 36.5 SL Maximum Continuous at SL 350 2100 31.5 SL Maximum Continuous 350 2100 30.5 3000 ft. (Rated Pressure Alt.) 350 2100 29.5 6000 ft. 350 2100 29.0 7800 ft. Straight line variation of manifold pressure between points listed. Propeller & Propeller Limits Hartzell HC-B3R30-4B Hub with R10152-5½ Blades Diameter: Not over 95½ ins.; Not under 95½ ins. Pitch settings at 30" station: (Constant Speed) - 16° Low, 28° High Static RPM at maximum throttle setting not over 2300 RPM; not under 2200 RPM. Airspeed Limits Without Spreader VNE - Never Exceed 176 mph (153 knots) IAS or CAS VNO - Normal Operating 140 mph (122 knots) IAS or CAS VA - Maneuvering 129 mph (112 knots) IAS or CAS With P/N 50453 Spreader Installed VNE - Never Exceed 155 mph (135 knots) IAS or CAS Airspeed limits are unchanged with Cowl Speed Ring installed P/N 50784 per Drawing 50783 Maximum Operating Altitude 15,500 ft. C.G. Range Inches aft of datum (+22.1) to (+26.75) at all weights Empty Weight C.G. Range None Maximum Weight 4000 lbs. No. of Seats 1 (+68.0) Hopper Capacity 2000 lbs. (+15.0) 5 A26WE Baggage Shelf 25 lbs. (+91.25) Fuel Capacity 72.5 gal. total Right Wing Tank 27½ gal. with unusable 2½ gal. (+36.0) Left Wing Tank (combined with center tank) 45 gal. with unusable 5 gal. (+36.0) Oil Capacity 6.7 gal. plus 1 gal. in system (-22.2) Control Surface Rudder Left 20° ± 1° Right 20° ± 1° Elevator Up 27° ± 1° Down 15° ± 1° Aileron Up 29° ± 1½° Down 11½° ± 1° Serial Nos. Eligible 1520 and subsequent IV - Model 620B (Restricted Category) Approved July 17, 1992 (See ALL MODEL Section) (See NOTES Section) Engine Pratt & Whitney R985-AN-1, AN-3, or AN-14B Fuel 80/87 Minimum Grade Aviation Gasoline. Alternate fuel is 100LL. Engine Limits Engine Model AN-1 & AN-3 HP RPM In. Hg. Press Alt. Takeoff (1 min.) at SL 450 2300 37.5 SL Maximum Continuous at SL 350 2100 33.0 SL Maximum Continuous 350 2100 32.0 3000 ft. (Rated Pressure Alt.) 350 2100 31.0 6000 ft. Straight line variation of manifold pressure between points listed. Engine Model AN-14B HP RPM In. Hg. Press Alt. Takeoff (1 min.) at SL 450 2300 36.5 SL Maximum Continuous at SL 350 2100 31.5 SL Maximum Continuous 350 2100 30.5 3000 ft. (Rated Pressure Alt.) 350 2100 29.5 6000 ft. 350 2100 29.0 7800 ft. Straight line variation of manifold pressure between points listed. Propeller & Propeller Limits Hartzell HC-B3R30-4B Hub with R10152-5½ R Blades Diameter: Not over 95½ ins.; Not under 95½ ins. Pitch settings at 30" station: (Constant Speed) - 16° Low, 28° High Static RPM at maximum throttle setting not over 2300 RPM; not under 2200 RPM. Airspeed Limits Without Spreader VNE - Never Exceed 176 mph (153 knots) IAS or CAS VNO - Normal Operating 140 mph (122 knots) IAS or CAS VA - Maneuvering 129 mph (112 knots) IAS or CAS With P/N 50453 Spreader Installed VNE - Never Exceed 155 mph (135 knots) IAS or CAS Airspeed limits are unchanged with Cowl Speed Ring installed P/N 50784 per Drawing 50783 Maximum Operating Altitude 15,000 ft. C.G. Range Inches aft of datum (+22.1) to (+27.5) at all weights Empty Weight C.G. Range None A26WE 6 Maximum Weight 4000 lbs. No. of Seats 1 (+70.0) Hopper Capacity 2000 lbs. (+15.0) Baggage Shelf 25 lbs. (+93.25) Fuel Capacity 97.5 gal. total Right Wing Tank 40 gal. with unusable 2½ gal. (+36.0) Left Wing Tank (combined with center tank) 57.5 gal. with unusable 5 gal. (+36.0) Oil Capacity 6.7 gal. plus 1 gal. in system (-22.2) Control Surface Rudder Left 20° ± 1° Right 20° ± 1° Elevator Up 27° ± 1° Down 15° ± 1° Aileron Up 29° ± 1½° Down 11½° ± 1° Serial Nos. Eligible 1550 and subsequent V- Model 620B-TG (Restricted Category) Approved March 12, 1997 (See ALL MODEL Section) (See NOTES Section) Engine Allied Signal TPE331-1-151A (See NOTE 7) Fuel Jet A , Jet A-1, Jet B, Jet P-4, and Jet P-5 fuel. Refer to Allied Signal Service Bulletin No. EMS 53111, EMS 53112, EMS 53113, and EMS 53116. (See NOTE 8). Engine Limits Engine HP NP RPM Takeoff (SL) 500∗ 2000 (100%) Maximum Cont., SL 500∗ 2000 (100%) Maximum Reverse 475 1910 (96.5 %) ∗ Maximum steady torque (SL) = 1313 lb. ft (47.0 psig) Ground Idle 64-66% (speed lever low) Flight Idle 94.5-96.5% (speed lever high) Maximum Permissible Temperature Exhaust Gas Temp Takeoff 1047°F (564°C) Maximum Continuous 1047°F (564°C) Starting Transient (1 sec.) 1472°F (800°C) Oil Temperature Type I Oil Normal Range 40°F (-40°C) to 200°F (93°C) Type II Oil Normal Range 40°F (-40°C) to 260°F (127°C) Oil conforming to Allied Signal EMS 53110 ( Type I and Type II) Oil Pressure Normal @ 100% speed (green) 70-120 psig Normal Caution (amber) 50-70 psig Minimum @ 65% speed ground idle 50 psig Maximum 120 psig Fuel Pressure Engine fuel pump inlet pressure is 5 psig plus true vapor pressure of fuel. Engine inlet pressure is measured at the inlet to the engine high pressure gear pump. (This point is also the outlet of the Weatherly installed low pressure pump mounted on the engine). See NOTE 9. 7 A26WE Minimum (red line) 15 psig Normal (amber arc) 15-20 psig Normal (green arc) 20- 50 psig Maximum (red line) 50 psig Propeller & Propeller Limits McCauley reversing propeller with Woodward overspeed governor Model 3GFR34C602/100LA-2 Hub No. 3GFR34C602 Blade No. 100LA-2 Diameter: Maximum 98.0 inches Minimum 96.0 inches Pitch setting at 30 inch radius Low pitch 9.5° ± 0.5° Propeller spinner, McCauley P/N E4858 Overspeed governor, Woodward P/N 895282-14 Propeller Speed Normal 2000 rpm Maximum (5 sec.) 2100 rpm Maximum (5 min.) 2020 rpm Airspeed Limits VMO - Maximum Operating without Spreader 176 mph (153 knots) IAS VMO - Maximum Operating with Spreader 155 mph (135 knots) IAS VNO - Normal Operating 140 mph (122 knots) IAS VA - Maneuvering 129 mph (112 knots) IAS Vy - Best Rate Climb 90 mph ( 78 knots) IAS C.G. Range +19.5 to +26.5 inches aft of datum for all weights. Empty Weight C.G. Range 3328 lb. at +19.1 in. (with optional Spreader P/N 72097 installed 3272 lb. at +17.4 in.) Maximum Weight 4300 lb. (+24.73) See NOTE 11. No. of Seats 1 (+73.0) Hopper Capacity 2000 lb. (+15.0) Baggage Shelf 25 lb. (+93.25) Fuel Capacity 130 gal. total , 14 gal. unusable (+36.0). The fuel tank system consists of 7 interconnected tanks (2 in the left wing, 2 in the right wing, and 3 in wing center section) . Oil Capacity 1.56 gal. total (-54.0) Maximum Operating Altitude 15,000 ft. Control Surface Rudder Left 20° ± 1° Right 20° ± 1° Elevator Up 27° ± 1° Down 15° ± 1° Aileron Up 29° ± 1½° Down 11½° ± 1½° Serial Nos. Eligible 1615, 1636, and 3000 and subsequent Specifications Pertinent to all Models Datum Wing leading edge outboard of fillet ( 6 inches forward of the main gear axle). Level Means Leveling lugs on outboard side of right hand fuselage frame near pilot's seat. A26WE 8 Certification Basis FAR 21.25(a) effective February 1, 1965, with policies contained in CAM 8 Appendix B Airworthiness Requirements for the Special Purpose of: Agricultural Operations under FAR 21.25(b)(1). Note: In accordance with FAR 36.1(a)(2), compliance with the noise requirements was not shown. Therefore, aircraft certificated under this certificate are only eligible for agricultural operations excepted by FAR 36.1(a)(2) and defined under FAR 137.3. 620TP Turboprop Installation: FAR 23, Amendments 23-1 to 23-21; Subpart B - Flight, Subpart E - Powerplant and 23.1305 Powerplant Instruments. (FAR’s 23.221, 23.954, 23.967(a)(6), 23.973(d), 23.1093, 23.1305(q), 23.1305(s), and 23.1305(t) have been waived under the provisions of FAR 21.25) 620B-TG Turboprop Installation: FAR 23, Amendments 23-1 to 23-46; Subpart B - Flight, Subpart E - Powerplant. (FAR’s 23.1305(s) and 23.1305(t) have been waived under the provision of FAR 21.25) Noise Control Act of 1972 Restricted Type Certificate issued October 24, 1979 Application for Type Certificate dated June 16, 1978 Production Basis Production Certificate No. 416 Export Eligibility Aircraft will be eligible for issuance of an Export Certificate of Airworthiness subject to compliance with Federal Aviation Regulations Part 21, Subpart L, Sections 21.321 through 21.339. The applicable procedures are contained in Advisory Circular 21.2. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: 620: (a) FAA Approved Airplane Flight Manual dated October 24, 1979, and FAA approved revisi ons (b) Weatherly Equipment List A-620 620TP: (a) FAA Approved Airplane Flight Manual dated October 15, 1980, and FAA approved revisions (b) Weatherly Equipment list A-620TP 620A: (a) FAA Approved Airplane Flight Manual dated March 25, 1987, and FAA approved revisions (b) Weatherly Equipment List A-620A 620B: (a) FAA Approved Airplane Flight Manual dated July 16, 1992, and FAA approved revisions (b) Weatherly Equipment List A-620B 620B-TG: (a) FAA Approved Airplane Flight Manual dated March 20, 1997, and FAA approved revisions (b) Weatherly Equipment List A-620B-TG NOTE 1. 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. 9 A26WE The certification weight and corresponding center of gravity must include for Models 620, 620A, and 620B undrainable system oil of 2.3 lb. at (-22.2) and unusable fuel of 7.5 gals. at (+36.0). The certificated empty weight and corresponding center of gravity must include for Model 620TP undrainable system oil for 5.25 lb. at (-24.0) and unusable fuel of 12 gals. at (+36.0). The certificated empty weight and corresponding center of gravity must include for Model 620B-TG undrainable system oil for 11.7 lb. at (-54.0) and unusable fuel of 14 gals. at (+36.0). NOTE 2. 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 placard or listing accessible to the pilot. The following placard must be displayed in front of and in clear view of the pilot: "This airplane must be operated as a restricted category airplane in compliance with the operating limitations stated in the form of placards, markings, and manuals." For additional placards, see Weatherly Model 620, 620A, 620B, 620TP, and 620B -TG Airplane Flight Manuals. NOTE 3. 620 and 620A: Alternator 24 volt, Motorola Model AN24N900, Maximum current load is limited to a total load of 20.8 Amps. 620B : Alternator 24 volt, 50 Amps. Skytronics Model JASCO 7555T and/or 70 Amps Model JASCO 7655T with Voltage Controller J12M24SP is approved for thi s installation. 620B-TG: Starter Generator Lucas Aerospace Model 23048-023 with Voltage Regulator General Electric CSV1105-30 is approved for this installation. Maximum current load is limited to a total load of 250 Amps, 28.5 Volts. NOTE 4. 620TP and 620B-TG: Flight into known icing conditions is prohibited. Do not fly into areas of visible moisture when the temperature is below 40°F. NOTE 5. 620TP and 620B-TG: Approved for reverse thrust during ground operation only. NOTE 6. All fuel and oil capacities are in US gallons. NOTE 7. The Allied Signal TPE331-1-151A engine is a derivative of the TPE331 -1 engine approved for this installation. NOTE 8. 620B-TG: When operating at ambient temperature of 0°C or below, the fuel must contain an icing inhibitor, the quantity not to exceed 0.15% by volume in compliance with MIL-I-27686D or E. NOTE 9. 620B-TG: A Fuel Pressure \ Flow Instrument (Electronic International Model FP-5) and a Flow Transducer (EG&G Model FT-8AEXSBLEA-2) may be used as an option to the standard Fuel Pressure Gage with the following placard installed: “Do not rely on the electronic fuel flow instrument to determine fuel quantity level in tanks.” NOTE 10. Noise Certification: This airplane has not been shown to comply with the noise limits in FAR Part 36 and must be operated in accordance with the noise operation limitation required by FAR 91.815. NOTE 11. The 620B-TG model aircraft has been certificated up to a Maximum Gross Weight of 4300 lbs. Any increase in Gross Weight will require FAA evaluation and approval. --- END ---