Pilatus Aircraft Ltd. CH Stans SWITZERLAND. (Straight line manifold pressure variation with altitude shown)

Transcription

1 F of 2 This Data Sheet which is a part of Type Certificate No. F 5 10 prescribes conditions and limitations under which the product for which the Type Certification was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Pilatus Aircraft Ltd. CH - 30 Stans SWITZERLAND 1. Data Pertinent to the Particular Models 1.1 Models: PC- Approved: December 1, 1959 PC--H1 Approved: December 10, 193 PC--H2 Approved: August 2, Engine: LYCOMING GSO-480-B1A - Engine Limits: HP RPM M.P. Altitude Take-off S.L. Take-off ft. Max. Continuous S.L. Max. Continuous ft. (Straight line manifold pressure variation with altitude shown) - Propeller and Prop. Limits: HARTZELL, three blades, constant speed, non-feathering Hub: HC-83 X 20-1B or HC-A3 X 20-1D Blades: 9333C-0 to 5 Diameter maximum 93 in. Diameter minimum 88 in. (no further reduction permitted) Pitch setting at 30 in. station: low 15, high 3 - Fuel: 100/130 minimum grade aviation gasoline - Oil: Straight mineral oil SAE 20 to 50, or Detergent oil according to Lycoming Service Instruction No. 1014, latest issue. Capacity: 3.5 US-Gal. ( mm) 20. September 200

2 F of 2 - Equipment required: - Carburetor STROMBERG PS-BD - Starter BENDIX 5-22-C - Generator BENDIX 30B-24-1-A - Fuel pump (engine driven) LEAR ROMEC Mod. RG Fuel booster pump SECONDO MONA DM 21 - Oil Cooler GALLAY E 94/3 - Battery VARLEY 24,19/25 C 1.2 Models: PC-/350 Approved: April 9, 192 PC-/350-H1 Approved: December 10, 193 PC-/350-H2 Approved: August 2, Engine: LYCOMING IGO-540-A1A - Engine Limits: HP RPM Take-off full throttle at S.L. Max. Continuous full throttle at S.L. - Propeller and Prop. Limits: HARTZELL three blades, constant speed, feathering Hub: HC-B3Z-30-2B Blades: ½ Diameter maximum 93.5 in. Diameter minimum 93.5 in. (no reduction permitted) Pitch setting at 30 in. station: low 15, high 8 - Fuel: 100/130 minimum grade aviation gasoline - Oil: Straight mineral oil SAE 20 to 50, or Detergent oil according to Lycoming Service Instruction No. 1014, latest issue. Capacity: 3.5 US-Gal. ( mm) - Equipment required: - Fuel Injection Unit BENDIX RS 10 ED 2 - Generator BENDIX 30 B 24-1-A - Starter BENDIX 5-22-C - Fuel pump (engine driven) LEAR ROMEC Mod. RG Fuel booster pump SECONDO MONA SM 21 - Oil Cooler GALLAY E 94/3 - Battery VARLEY 24.19/25 C. 20. September 200

3 F of Models: PC-/A Approved: November 2, 192 PC-/A-H1 Approved: December 10, 193 PC-/A-H2 Approved: August 2, Engine: TURBOMECA ASTAZOU II E or ASTAZOU II G - Engine Limits: SHP RPM Alt. Power (%) EGT Max. ( C) Take-off ,500 S.L (max. 5 min.) Max. Continuous 43 43,500 S.L Starting transient 30 sec less than 3 sec Propeller and Prop. Limits: RATIER FIGEAC turbine propeller, electrically controllable, feathering and reversing Hub: FH -1-0 Blades: FH.20 Diameter maximum 2.5 m Diameter minimum 2.45 m (no further reduction permitted) Pitch setting at 0.85 m station Reverse -14 (mechanical stop) Starting -1.5 Flight minimum +2.5 (electrical stop) Feathering +8 (mechanical stop) - Fuel: Aviation kerosene according to ASTM-D-155, Jet A or A1 (AIR 3405, TRO) or MIL-T-524 (JP-4) and ASTM-D-155, Jet B (AIR 340, TR4) or MIL-T-524 (JP-5) (AIR 3404,TR5) - Oil: Straight mineral turbine oil according to UK Spec. D. Eng. RD 2490 (AIR 3515) Total system capacity: 8 liters (+ 590 mm) - Equipment required: - Starter/Generator AIR EQUIPMENT Oil Cooler GALLAY E 5130 or E Fuel filter ZENITH 204 FZ-A/BC - Fuel booster pump BRONZAVIA or Battery SAFT 4000 or 401 or 40 - Battery overtemperature warning system (PILATUS Service Bulletin No. 122) 20. September 200

4 F of Model: PC-/A1-H2 Approved: February 29, Engine: TURBOMECA ASTAZOU XII - Engine Limits: SHP Alt. O.A.T ( C) RPM Power (%) EGT Max. ( C) Take-off 53 S.L , Max. Continuous 53 S.L , Starting max less than 3 sec Power above 90 % limited to 5 min. Note: The original engine output of 00 SHP at S.L. is flat rated to 53 SHP by a fuel limiter. 53 SHP are, therefore, available up to 9000 ft. at ISA condition. - Propeller and Prop. limits: HAMILTON STANDARD fully reversing and feathering, hydraulically controllable Hub: Blades: 23 LF A Diameter maximum 102 in. Diameter minimum in. (no further reduction permitted) Pitch setting at 42 in. station: Reverse: /- 0.5 Flight Minimum: Feathering: /- 1 - Fuel: Aviation kerosene according to ASTM-D-155, Jet A or A1 (AIR 3405, TRO) or MIL-T-524 (JP-4) and ASTM-D-155, Jet B (AIR 340, TR 4) or MIL-T-524 (JP-5) (AIR 3404, TR 5) - Oil: Synthetic Turbine Oil according to MIL-L-808 (AIR 3513) Total system capacity: 13 litres (-40 mm) - Equipment required: - Starter/Generator LABINAL Fuel booster pump BRONZAVIA D - Fuel filter ZENITH 204 FZ-A/BC - Oil Cooler GALLAY E One or two batteries MARATHON MA5 or SAFT 40 - Battery overtemperature warning system (PILATUS S.B. No. 122) 20. September 200

5 F of Model: PC-/A2-H2 Approved: January 22, Engine: TURBOMECA ASTAZOU XIV E1 - Engine Limits: SHP Alt. O.A.T. ( C) RPM Torque (%) EGT Max. ( C) Take-off 580 S.L , Max. Continuous 580 S.L , Power above 480 C EGT limited to 5 minutes Fuel flow maximum litres/h Note: The original engine output of 80 SHP at S.L. is flat rated to 580 SHP by a fuel limiter. 580 SHP are, therefore, available up to 12,000 ft. ISA condition, or up to 34 C OAT at S.L. - Propeller and Prop. Limits: HAMILTON STANDARD fully reversing and feathering, hydraulically controllable Hub: 23LF-351 Blades: 101A-0 Diameter maximum 102 in. Diameter minimum in. (no further reduction permitted) Pitch setting at 42 in. station: Reverse: /-0.5 Flight Minimum: Feathering: /-1 Starting: /-2 (zero thrust) - Fuel: Aviation kerosene according to ASTM-D-155, Jet A or A1 (AIR 3405, TRO) or MIL-T-524 (JP-4) and ASTM-D-155, Jet B (AIR 340, TR4) or MIL-T-524 (JP-5) (AIR 3404, TR5) - Oil: Synthetic Turbine Oil according to MIL-L-808 (AIR 3513 or AIR 3514) Total system capacity: 13 liters (-40 mm) - Equipment required: - Starter/Generator SEB Fuel booster pump BRONZAVIA D - Fuel filter ZENITH 204 FZA/AC - Oil Cooler GALLAY E Two batteries SAFT Model 40 - Battery overtemperature warning system (PILATUS S.B. No. 122) 20. September 200

6 F 5-10 of 2 1. Model: PC-/B-H2 Approved: June 8, Engine: P&W PTA-A - Engine Limits: SHP Torque (psi) G.G. RPM Prop. RPM ITT ( C) Take-off max ,100 2, min. (101.5 %) (100 %) Max. Continuous ,100 2, (101,5 %) (100 %) Starting (max. 2 sec) Max. reverse Propeller and Prop. Limits: HARTZELL three blades, feathering and reversing, constant speed, hydraulically controllable. Hub: Blades: HC-B3TN-3C T-1013 C or CH Diameter maximum 101 in. Diameter minimum 99 in. (no further reduction permitted) Pitch setting at 30 in. station: Reverse: Minimum Feathering: /- 1 Flight Minimum: 0 - Fuel: Aviation kerosene conforming to UACL Specification No. 522 and later revisions. - Oil: Synthetic Turbine Oil conforming to UACL Service Bulletin No. 1, latest issue. Total system capacity: 12.5 litres (+ 95 mm) *) - Equipment required: - Starter/Generator LEAR SIEGLER or Propeller Governor WOODWARD Propeller Overspeed Governor WOODWARD Reversing Valve BENDIX AL N-1 - Gas Generator Tachom. GENERAL ELECTRIC 2 CM 9 - Torque Transmitter THOMAS EDISON Fuel aux. pump LEAR ROMEC RG L - Fuel booster pump ADEL or STEINHEIL D Fuel filter ZENITH 204 FZ-A/BC or P/N AIR MAZE *) - Oil Cooler HARRISON AP 09 AN One battery SONOTONE MA-5 or SAFT Models 401 or 40 or GILL BB 38T or Varta F20/40H1CT - Battery overtemperature warning system (PILATUS S.B. No. 122) AIR MAZE filter in connection with FCU Bleed Valve only. See S.B. No September 200

7 F 5-10 of 2 1. Model: PC-/B1-H2 Approved: August, 19 - Engine: P&W PTA-20, PTA-20A, PTA-20B, PTA-/C20 - Engine Limits: SHP Torque (psi) G.G. RPM Prop. RPM ITT ( C) Take-off and max. continuous up to 21 C at S.L ,100 (101.5 %) 2,200 (100 %) 50 Starting (max. 2 sec) Max. reverse Propeller and Prop. Limits: HARTZELL three blades, feathering and reversing, constant speed, hydraulically controllable Hub: HC-B3 TN-3C or D Blades: T-1013C or CH or T-1018C or CH *) Diameter maximum 101 in. 101 in. Diameter minimum 99 in. 99 in. (no further reduction permitted) Pitch setting at 30 in. station: Reverse: minimum Feathering: /- 1.0 Flight Minimum: Fuel: Aviation kerosene conforming to UACL Specification No. 522 and later revisions. - Oil: Synthetic Turbine Oil conforming to UACL Service Bulletin No. 1, latest issue. Total system capacity: 12.5 litres (+ 95 mm) 20. September 200

8 F of 2 - Equipment required: - Starter/Generator LEAR SIEGLER OR /004 - Propeller governor WOODWARD Overspeed governor WOODWARD Gas generator tachometer GENERAL ELECTRIC 2C M9 - Torque transmitter THOMAS EDISON Fuel auxiliary pump LEAR SIEGLER RG L - Fuel booster pump ADEL or STEINHEIL D Fuel filter ZENITH 204 FZ A/BC or P/N AIR MAZE **) - Oil cooler HARRISON AP 09 AN One battery SONOTONE MA-5 or SAFT Models 401 or 40 or GILL BB 38T or Varta F20/40H1CT - Battery overtemperature warning system (PILATUS S.B. No. 122) *) **) According to FAA S.T.C. No. SA 545 EA, the aircraft model designation with the T-1018 propeller blades installed is PC-/B1A-H2. AIR MAZE filter in connection with FCU Bleed Valve only. See S.B. No September 200

9 F of Model: PC-/B2-H2 Approved: June 30, Engine: P&W PTA-2 - Engine Limits: SHP Torque (psi) G.G. RPM Prop. RPM ITT ( C) Take-off up to 43 C ,100 2, (101.5 %) (100 %) Max. continuous and ,100 2, enroute emergency (101.5 %) (100 %) Starting (max. 2 sec) Acceleration (max. 2 sec) ,500 2, (102. %) (110 %) Max. reverse (1 min) Propeller and Prop. Limits: HARTZELL three blades, feathering and reversing, constant speed, hydraulically controllable Hub: HC-B3TN-3D Blades: T-1013C or CH or T-1018C or CH Diameter maximum 101 in. 101 in. Diameter minimum 99 in. 99 in. (no further reduction permitted) Pitch setting at 30 in. station: Reverse: minimum Feathering: /- 0.5 Flight minimum Fuel: Aviation kerosene conforming to UACL Service Bulletin No. 1244, latest issue. - Oil: Synthetic Turbine Oil conforming to UACL Service Bulletin No. 1001, latest issue. Total system capacity litres (+ 95 mm) 20. September 200

10 F of 2 - Equipment required: - Starter/Generator LEAR SIEGLER or or /004 or GE 2 CM-302 A3 - Overspeed governor WOODWARD Gas generator tacho-generator GENERAL ELECTRIC 2C M9 or AN2CM9ABZ - Propeller tacho-generator GENERAL ELECTRIC 2C M9 or AN2CM9ABZ - Torque transmitter THOMAS EDISON or Kulite IPTS1DF10000D - Fuel auxiliary pump LEAR SIEGLER RG L or Conelec 01 - Fuel booster pump ADEL or STEINHEIL D 1030 or LEAR SIEGLER D Fuel filter ZENITH 204 FZ A/BC or P/N (AIR MAZE) - Oil cooler HARRISON AP 09 AN One battery MARATHON MA 5 or SAFT model 401 or 40 or GILL BB 38T or Varta F20/40H1CT - Battery overtemperature warning system (PILATUS S.B. No. 122) 20. September 200

11 F of Model: PC-/B2-H4 Approved: November 20, 1985 December 8, 198 (new engine power setting) - Engine: P&W PTA-2 - Engine Limits: SHP Torque (psi) G.G. RPM Prop. RPM ITT ( C) Take-off up to 43 C , (101.5 %) (100 %) Max. continuous and , enroute emergency (101.5 %) (100 %) Starting (max. 2 sec) Acceleration ,500 2, (max. 2 sec) (102.%) (110 %) Max. reverse (1 min) Propeller and Prop. Limits: HARTZELL three blades, feathering and reversing, constant speed, hydraulically controllable Hub: Blades: HC-B3TN-3D T-1018C or CH modified acc. to drawing or T-1018CR Diameter maximum 101 in. Diameter minimum 99 in (no further reduction permitted) Pitch setting at 30 in. station: Reverse: minimum Feathering: /- 0.5 Flight minimum: Fuel: Aviation kerosene conforming to UACL Service Bulletin No. 1244, latest issue. - Oil: Synthetic Turbine Oil conforming to UACL Service Bulletin No. 1001, latest issue. Total system capacity litres (+ 95 mm) 20. September 200

12 F of 2 - Equipment required: - Starter/Generator LEAR SIEGLER or or /004 or GE 2 CM-302 A3 - Overspeed governor WOODWARD Gas generator tacho-generator GENERAL ELECTRIC 2C M9 or AN2CM91BZ - Propeller tacho-generator GENERAL ELECTRIC 2C M9 or AN2CM9ABZ - Torque transmitter THOMAS EDISON or Kulite IPT S1DF10000D - Fuel auxiliary pump LEAR SIEGLER RG L or Conelec 01 - Fuel booster pump ADEL or STEINHEIL D 1030 or LEAR SIEGLER D Fuel filter ZENITH 204 FZ A/BC or P/N (AIR MAZE) - Oil cooler HARRISON AP 09 AN One battery MARATHON MA 5 or SAFT model 401 or 40 or GILL BB 38T or Varta F20/40H1CT - Battery overtemperature warning system (PILATUS S.B. No. 122). - Stabilizer Trim Actuator ELECTRO MECH EM Wing tip color: the color of the composite wing tips must not exceed a solar absorptivity of September 200

13 F of Model: PC-/C-H2 Approved: December 1, 19 - Engine: AIRESEARCH TPE D - Engine Limits: SHP Torque (psi RPM EGT ( C) Take-off (max. 5 min.) ,30 51 (100 %) Max. continuous , (100 %) Absolute maximum ,820 - (max. 5 sec.) (105 %) Starting (max. 10 sec) (max. 1 sec) - Propeller and Prop. Limits: HARTZELL three blades, feathering and reversing, constant speed, hydraulically controllable Hub: Blades: HC-B3TN-5C T-1018C or CH Diameter maximum 101 in. Diameter minimum 99 in. (no further reduction permitted) Pitch setting at 30 in. station: Reverse: /- 0.5 Feathering: + 8 +/- 1.0 Start: + 2 +/- 0.3 Flight minimum: + 5 +/ Fuel: Turbine Fuels as specified in GARRETT Service Information Letter P Oil: Synthetic Turbine Oils conforming to MIL-L-808 D or MIL-L-808 F or MIL-L-2399A as listed in GARRETT document No. OE Total system capacity: 11 liters (+ 390 mm) - Equipment required: - Starter/Generator LEAR SIEGLER or GE 2 CM-302 A3 - Unfeathering pump WELDON TOOL A 4033 A - Torque transmitter THOMAS EDISON Fuel auxiliary pump LEAR SIEGLER RG A - Fuel booster pump ADEL or STEINHEIL D Fuel filter ROCKWELL OW Oil cooler HARRISON AP 14 AN One or two batteries SONOTONE MA-5 or SAFT model 01 or 0 - Battery overtemperature warning system (PILATUS S.B. No. 122). 20. September 200

14 F of Model: PC-/C1-H2 Approved: July 15, Engine: AIRESEARCH TPE Engine Limits: SHP Torque (psi) RPM EGT ( C) (2) Take-off and max ,30 51 continuous at S.L. (1) (100 %) Absolute maximum ,81 - (max. 5. sec.) (105 %) Max. cruise , Starting (max. 10 sec) (max. 1 sec) Note 1: Note 2: This power is limited to 5 min. except in an emergency. At OAT 2 C EGT varies with OAT as shown on cockpit placard. - Propeller and Prop. Limits: HARTZELL three blades, feathering and reversing, constant speed, hydraulically controllable Hub: Blades: HC-B3TN-5C T-1018 C or CH Diameter maximum 101 in. Diameter minimum 99 in. (no further reduction permitted) - Pitch setting at 30 in. station: Reverse /-0.5 Feathering + 8 +/-1.0 Start + 2 +/-0.3 Flight minimum + 5 +/ Fuel: Turbine Fuels as specified in GARRETT Service Information Letter P Oil: Synthetic Turbine Oils conforming to MIL-L-808 D or MIL-L-808 F or MIL-L-2399A as listed in GARRETT document No. OE Total system capacity: 11 liters (+ 390 mm) 20. September 200

15 F of 2 - Equipment required: - Starter/Generator LEAR SIEGLER or GE 2 CM-302 A3 - Unfeathering pump WELDON TOOL A 4033 A - Torque transmitter THOMAS EDISON Fuel auxiliary pump LEAR SIEGLER RG A - Fuel booster pump ADEL or STEINHEIL D Fuel filter ROCKWELL OW Oil cooler HARRISON AP 14 AN One or two batteries SONOTONE MA-5 or SAFT model 01 or 0 - Battery overtemperature warning system (PILATUS S.B. No. 122). 20. September 200

16 F of 2 2. Data Pertinent to all Models 2.1 Airworthiness Requirements and Categories The aircraft comply with the US Civil Air Regulations, Part 3 of the 15 th May 195, Category Normal, incl. Amd. 3-1 to 3-5; the turbine engined models in addition comply with the Special Conditions, notified by letters FAA to the Swiss Federal Air Office, dated Nov. 14, 192 resp. Jan. 4, Technical Data 2.21 Distinctive Features Single-engined, strut-braced high-wing plane, all-metal construction, with fixed main and tail landing gear Principal Dimensions all models except B2-H4 B2-H4 - Wing span 15.2 m 15.8 m - Length 10.9 m 10.9 m - Height (static) 3.2 m 3.2 m - Chord length 1.9 m 1.9 m - Wing area 28.5 m m 2 - Airfoil NACA 4-514, constant over span 2.23 Fuel Capacity NACA 4-514, constant over span PC- and PC-/350 Series (Piston Engines) Total Capacity: 105 or 12 US-Gal. (2 tanks of 52.5 or 3.5 US-Gal. at mm) Usable Capacity: 104 or 12 US-Gal. (2 tanks of 52 or 3 US-Gal. at mm) PC-/A, /B and /C Series (Turbine Engines) Total Capacity: 130 or 13 US-Gal. (2 tanks of 3.5 or 85 US-Gal. at mm, 1 booster pump tank of 3 US-Gal. at mm) Usable Capacity: 128 or 10 US-Gal. (2 tanks of 2.5 or 83.5 US-Gal. at mm, 1 booster pump tank of 3 US-Gal. at ) 20. September 200

17 F of Airspeed Limits (in conformity with CAR 3) all models except B2-H4 B2-H4 Knots km/h Knots km/h - Never exceed Maximal structural cruising Maneuvering Flaps extended Weight and Balance Limitations 2.41 Maximum Gross Weight Model Without Index H With Index H1 With Index H2 With Index H4 Gross Weight 190 kg (4322 lbs) 201 kg (4444 lbs) 2200 kg (4850 lbs) 2800 kg (13 lbs) 2.42 Maximum Landing Weight All models except B2-H4 B2-H Empty Weight Center of Gravity: equal to max. Gross Weight 20 kg (584 lbs) NIL 2.44 Operating Center of Gravity All models except PC-/B2-H4: PC-/B2-H4 345 to 34 mm at 2200 kg (25 % - 34 % MAC) 3209 to 34 mm at 1450 kg (11 % - 34 % MAC) 308 to 322 mm at 2800 kg (32 % - 38 % MAC) 3209 to 322 mm at 1450 kg (11 % - 38 % MAC) Straight line variation between points given Datum 3 m in front of vertical tangent to the wing leading edge. 2.4 Leveling Means T-rails on the cabin floor horizontal; leveling marks on each side of the fuselage. 20. September 200

18 F of Cabin Load Limits 2.51 Number of Seats normal 8, with single seats (2 at mm, 2 at 3850 mm, 2 at mm, 2 at mm) maximum 11, with 3 benches (triple seats) (1 at mm, 1 at mm, 1 at mm) single seats may be stowed behind the cabin, accessible through a door on fuselage right hand side (2 kp at +30 mm) 2.52 Freight/Baggage After removing of the seats or benches respectively, the entire cabin may be used as freight space. Max. floor loading 488 kp/m 2 Max. loading of the trap doors 300kp 2. Control Surface Movements - Elevator Up 30 +/- 1 Down 25 +/- 1 Flettner tab Down 5 +/- 2 Up 32 +/- 2 - Horizontal stabilizer Nose Down 10 +/- 0.5 Nose Up 2 +/- 0.5 Neutral Nose Down 3 - Rudder Right 30 +/- 1.5 Left 30 +/- 1.5 Rudder tab Right +/- 1 Left +/- 1 - Aileron Up 20 +/- 1 Down /- 1 Flettner tab Down 20 +/- 1 Up /- 1 Trim tab (R.H.) Up 20 +/- 2 Down 18, Neutral up 2 - Landing flaps Up 0 Landing pos. 38 +/- 2 *) Take-off pos. 28 +/- 2 *) Landing position 45 permitted for S/N up to 522, for H2 and H4 versions: 38. Note: Flettner tabs on aileron and elevator, and aileron trim tabs are optional; if not installed, fixed tabs on elevator (up 3 ) and aileron (neutral) are mandatory. For H4 on elevator one flettner tab (set to 0 ) and two fixed trim tabs (set 10 up) are mandatory. 2. Max. Operating Altitude 25,000 ft 2.8 Maneuvering Load Factors Without Index H Model Designation With With Index H1 Index H2 With Index H4 Max. positive Max. negative September 200

19 F of Equipment 2.91 Electrical Equipment (a) Reverse current relay AN (b) 3 Navigation lights (c) 2 Cabin lights (d) 2 Rotating beacon lights, one above and one below the fuselage *) (e) Landing lights, retractable in wing, GRIMES G-300A4 (A5) *) (f) Instrument lights GRIMES A-8990-ER-Y-328 (Post Light) and/or B-22 and B-10 (Eye Brows) *) Mandatory if night flying required 2.92 Landing Gear (a) Main landing gear oleo struts P/N or P/N (b) Main landing gear wheels GOODYEAR / DUNLOP 24 x in. with GOODYEAR / DUNLOP tires GA 284, 24 x (2 x 1 kp at mm), or oversize main wheels x 12 in. with GOODYEAR / DUNLOP tires x 12 in. (2 x 24 kp at mm) (c) Brakes GOODYEAR P/N E (single piston) (2 x 3.5 kp at mm), or brakes GOODYEAR P/N (double piston) (2 x 3. kp at mm) (d) Tail landing gear P/N 403. with GOODYEAR / DUNLOP wheel with tire (all models H2 and H4 ) or tail landing gear P/N (for models other than H2 and H4 permitted) (e) Oleo/pneumatic strut P/N or mandatory for H4 tail landing gear Cabin (a) Double door on the right hand side, or sliding door on the right hand side (b) Double door on the left hand side, or emergency exit in window on the left hand side (c) Cockpit doors on the right and left hand sides (optional) (mandatory for H4 model) (d) Pilot s seat with safety belts P/N (fixed), or /51 (e) Co-pilot s seat P/N or /1 with safety belts (4.5 kp at mm), or Co-pilot s seat P/N or (de luxe) with safety belts (.5 kp at mm) (f) passenger seats P/N /140 or /33, with safety belts, 3 left and 3 right, 4.5 kp each (distance according to para 2.51) or passenger seats P/N /018 or /332 (de luxe) with safety belts, 3 left and 3 right,.5 each (distance according to para. 2.51) or 3 benches with safety belts P/N (PILATUS Service Bulletin No. 0), 12 kp each, or P/N , 13 kp each (distance according to para. 2.51) 20. September 200

20 F of 2 (g) Standard shoulder harness for pilot and co-pilot according to Dwg (0.8 kp each at mm), or shoulder harness system type PACIFIC 2 B2 SA 2X 15 for pilot and co-pilot according to Dwg (0.5 kp each at mm), or P/N /501 (with locking device) (0. kp each) (h) Shoulder harness and head support Dwg. No (0. kp each at mm) (i) Clogged fuel filter warning light (turbine engined models only) (k) Sliding door on the left hand side in accordance to FAA STC SA 43EA. (l) Direct vision window in windshield or in pilot door window Flight Aids (a) Electrical stall warning system, type Safe Flight No. 14 (Transmitter) and C-3113 (Buzzer) (b) Pitot tube with heating, AN Radio Equipment (optional) - 01 Radio equipment, listed in the Swiss Federal Office for Civil Aviation TM Navigation aids for spraying and supply dropping: a) DECCA NAVIGATOR Mk. 8A (23.9 kp at mm) b) DECCA HI-FIX (18.0 kp at mm) c) DECCA NAVIGATOR Mk. 8A and DECCA HI-FIX paras (a) plus (b) above (32.2 kp at mm) d) DECCA DOPPLER RADAR, type 2, and GYROSIN Compass CL 11 (4. kp at mm) e) Radio Altimeter SR 54 A (. kp at mm) f) DECCA AGRI-FIX (.5 kp at mm) g) Radio altimeter TRT AHV September 200

21 F of Optional Equipment - 01 Dual control according to Dwgs and Seat stowing device behind frame, with door on the right hand side of the fuselage, according to Dwg. 2./5 (S.B. No. 4) - 03 Electrical flap control according to Service Bulletin No. 95 (plus-difference) - 04 a) Electrically operated horizontal stabilizer system Dwg (plus difference). (Not valid for PC-/B2-H4) (kp) (mm) AFM Suppl. No. required b) Two motor trim actuator system Rotostat in horizontal stabilizer control, Dwg. V (S.B. No. 10) - 0 Trap doors and control Dwg. No /1 (plus difference, i.e. blind cover deducted) negligible a) Ski installation consisting of: - main and tail skis and operating cylinders hydraulic system (fixed) b) Ski installation H4 as detailled in AFM Supplement stretchers with supports Dwg Brackets for stretcher support attachment Dwg Stretcher support assembly Dwg Oxygen installation (SCOTT 8500) Dwg /18, consisting of: - fixed installation - 2 oxygen cylinders, charged De-Luxe cabin ventilating system Dwg September 200

22 F of 2-13 Fittings and reinforcement on the fuselage for float attachment: - for long front struts, Dwg for short front struts, Dwg Floats - EDO , total weight net weight or EDO , total wt. (short front strut) net weight Tail wheel debris guard, Dwg Dirt scrapers on main wheels x 12, Dwg /03 Total: Fiberglass laminate on wings and tail plane noses: - on wings Total: - on horizontal stabilizer - on vertical fin i - 18 Fuel ferry tank installation in the cabin (3 x 200 liters) with fuel transfer installation, Dwg Fuel ferry tank installation in the cabin (200 liters) with fuel transfer installation, Dwg. V Fuel under wing tank installation, Dwg /0 (2 x 49 US-Gal.) Dwg (2 x 3 US-Gal.) Dwg /322 (2 x 4 US-Gal.) / Installation for parachutist s operation as detailed in AFM Supplement Agricultural equipment as detailed in AFM Supplement Engine air intake filter system, model Mk 3B Aileron trim system mechanical electrical September 200

23 F of 2-25 a) Propeller De-icing system Goodrich No.E 129 b) Hot-Prop - 2 Basic equipment for target sack winch - fittings electrical power supply installation, Dwg protective plates attachment points on fuselage belly, Dwg Target sack winch as detailed in AFM Suppl PTA-20B Engine control system for quiet operation (PILATUS Service Bulletin No. 121) Autopilot Basic equipment for Zeiss RMK 21/23 aerial camera installation: - fittings for camera adapter - drain collector tube, Dwg. V electrical power supply installation, Dwg Zeiss RMK 21/23 aerial camera installation, Dwg. V Fittings for hand camera suspension in cabin l. and r., Dwg. V negligible - 33 External store hard points (PIL. S.B. No. 43) - one suspension point on each wing - two suspension points on each wing Engine compressor wash ring (PILATUS Service Bulletin No. 94) Tow coupling assembly Fire fighting installation (water tank 211 US-Gal. 800 litres, Dwg Windshield curtains Rudder trim electrical September 200

24 F of 2 3. Documents 3.1 Flight Manuals Swiss Federal Office for Civil Aviation approved Flight Manual as listed in the following table with appendix for actual weight and balance included. Model PC- PC--H1 PC--H2 Report No Model PC-/350 PC-/350-H1 PC-/350-H2 Report No Model PC-/A PC-/A-H1 PC-/A-H2 Report No Model PC-/A1-H2 PC-/A2-H2 - Report No Model PC-/B-H2 PC-/B1-H2 PC-/B2-H2 (up to S/N 824) Report No Model - - PC-/B2-H2 (from S/N 825) Report No. 191 Model - - PC-/B2-H4 (up to S/N 824) Report No Model - - PC-/B2-H4 (from S/N 825) Report No Model PC-/C-H2 PC-/C1-H2 - Report No Flight Manual Supplements Swiss FOCA approved Supplements as listed in the following table: Report No. Applicable for PORTER Model Subject Operating Category 1029 PC-/350-H1 Seaplane with floats EDO PC--H2 Seaplane with floats PC-/350-H2 EDO Normal Normal 20. September 200

25 F of Seaplane with floats Normal 1104 PC-/A-H2 PC-/B-H2 PC-/B1-H2 PC-/B2-H2 EDO or EDO Fuel ferry tank installation (barrels in cabin) Restricted CAM 8 while in overweight PC-/C -H2 PC-/C1-H2 58 ltrs. Agriculture version Restricted CAM All models except Cabin doors removed, sliding Normal PC-/C1-H2 and PC-/B2-H4 door/hatch door open (parachuting) PC-/C1-H All models H2 except PC-/B2-H2 Wing fuel tanks 44 ltrs. Normal 1320 All models except H4 Ski operation Normal All models H2 up to S/N 824 Underwing tanks 32 ltrs. 4 ltrs. 48 ltrs. Restricted CAM 8 while in overweight PC-/B2-H2 applicable from S/N 825 Underwing tanks 48 ltrs All models except H4 Electrically operated landing Normal (Standard for H4) flaps 1422 PC-/B1-H2 Engine Air Intake Normal PC-/B2-H2 Filter Mk. 3B 1424 All models Aileron Trim System Normal mechanical 1490 All TURBO PORTER Fuel ferry tank V Restricted CAM 8 while in models except H4 (190 ltr. in cabin) overweight 1504 PC-/B and C series up to Propeller de-icing system Normal S/N All models Target sack winch Normal PC-/A,B and C series Autopilot Normal except H4 152 PC-/B2-H2 Operation with Q-STOL Normal PC-/B2-H2 engine control system 152 PC-/B1-H2 PC-/B2-H2 up to S/N PC-/B2-H2 from S/N All TURBO PORTER models (except H4 ) (noise abatement procedure) Electrical Stabilizer Trim System Normal Operation with aircraft in overweight condition 159 PC-/B Series Aircraft Rocket Engine Normal 12 All TURBO PORTER Sailplane towing Normal models 153 All TURBO PORTER Fire Fighting models except H4 Restricted CAM 8 while in overweight Restricted CAM 8 while in overweight 20. September 200

26 F of All TURBO PORTER models except H4 Spray Equipment Restricted CAM 8 while in overweight 1804 all PC- Weather Radar King KWX 5 Normal 1812 all PC- RNAV King KNS 81 Normal 1813 all PC- RNAV and TACAN King KNS Normal PC-/B2-H4 Cabin doors removed, sliding Normal door/hatch door open (parachuting) 1825 *) PC-/B2-H4 Ski operation Normal 182 PC-/B2-H4 Underwing tanks 32 ltrs. Normal up to S/N 824 PC-/B2-H4 4 ltrs. 48 ltrs. from S/N PC-/B1-H2 Electrical Stabilizer Trim Normal PC-/B2-H2 System (two motor drive actuator) 184 all PC- Weather Radar Bendix Normal RDS all PC- Rudder Trim System Normal electrical 1849 all PC- Aileron Trim System Normal electrical 1850 PC-/B2-H4 Emergency Battery System Normal 1859 PC-/B2-H4 Fuel ferry tanks installation (barrels in cabin) 58 ltrs. Restricted CAM 8 (due to fuel in cabin) 180 PC-/B2-H4 Fuel ferry tank V ltrs. in cabin Restricted CAM 8 (due to fuel in cabin) 181 PC-/B2-H4 Agricultural equipment Restricted CAM 8 (max. zero fuel weight exceeded) 182 PC-/B2-H4 Fire Fighting Restricted CAM 8 (max. zero fuel weight exceeded) 188 PC-/B2-H4 Q-Operation Normal 1898 PC-/B2-H4 Micronair Underwing Spray Pod System 1904 PC-/B2-H4 Air Intake Filter System Normal 1905 all PC- Omega/VLF Nav. System Normal Global GNS-500A all PC- Color Weather Radar Bendix Normal RDS all PC- Remote Computer Unit Normal Bendix IU-2023B 1914 all PC- Propeller De-Icing System Normal from S/N 825 (HOT-PROP) 1915 PC-/B2-H4 Camera Assy (Floor Hatch) Normal 1948 PC-/B2-H4 Reduced Noise Operation Normal (Adjustable Propeller Lever) all PC- GPS System TNL-2000 Normal all PC- GPS Nav System KLN 90 Normal Restricted CAM 8 (due to agricultural approved equipment) 20. September 200

27 F of all PC- Emergency Fuel Control Normal (MOR) 0205 all PC- GPS Nav System KLN 90A Normal all PC- Onboard Oxygen System I Normal all PC- Color Weather Radar Normal RDR all PC- GPS Nav System KLN 90B Normal all PC- Onboard Oxygen System II Normal 0214 PC-/B1-H2, B2-H2 & De-Icing System for FAA STC Normal B2-H4 4-Blade Propeller 0218 all PC- KLN 90B B-RNAV (RNP-5) Normal GPS Nav System 0220 all PC- Horizontal Stabilizer Trim Warning System Normal *) Operation with Skis prohibited when Underwing Tanks are installed. 3.3 Maintenance Documents PC- PC- Service Manual (up to H2 models) Maintenance Manual Doc. No (for H4 model) 4.0 Notes NOTE 1. Manufacturer Serial Numbers (MSN) 2001 thru 2092 were manufactured by Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter and Fairchild-Hiller Corporation) in the United States of America under a license agreement and are covered by this Type Certificate No. TC F September 200