TCDS 4A12

Page No. 1 2 3 4 5 6 7 8 Rev. No. 12 - 12 - - - - - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 4A12 Revision 12 FLETCHER FU-24 FU-24A January 22, 1979 AIRCRAFT SPECIFICATION NO. 4A12 Type Certificate Holder Frontier-Aerospace Incorporated 2751 Temple Avenue Long Beach, California 90806 I. Model FU-24, 1 PCLM (Normal Category), Approved July 22, 1955 Engine Continental O-470-E (See Items 112, 113, and 114 for optional engines) Fuel 80/87 minimum grade aviation gasoline. O-470-E only (See Items 112, 113, and 114 for other engines Engine limits For all operations, 2600 r.p.m. (225 h.p.) Airspeed limits Maneuvering Vp 111 mph ( 96 knots) CAS Maximum structural cruising Vno 131 mph (114 knots) CAS Never exceed Vne 165 mph (143 knots) CAS Flaps extended Vf 80 mph ( 70 knots) CAS C.G. range (+118.7) to (+125.6) at 3500 lbs. (+110.0) to (+125.6) at 2800 lbs. or less (Straight line variation between points given) Empty weight C.G. range None Datum 100.2 in. ahead of wing leading edge Leveling means Fuselage upper longerons and bulkhead in cargo area Maximum weight 3500 lbs. (See Note 3 for increased weight). No. seats 1 (+98). See Item 405 for additional seats. Maximum cargo 1300 lbs. (+121) to (+164). Maximum airplane weight including cargo shall not exceed 3500 lbs.) Fuel capacity Two wing tanks, 23.5 gals. each (+110). Total usable 44 gals (+110) Oil capacity 3 gals. (+37) Control surface movements Elevator (chord line measured with airplane level) Nose down 20° Nose up 50° Elevator tab (measured with respect to elevator) Trailing edge down 3.5° (elevator 5° nose up) Trailing edge up 9.0° (elevator 20° nose down) Rudder Right 30° Left 30° Aileron Down 10° Up 25° Flaps Down 40° 4A12 Page 2 Required equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: (1, Basic O-470-E engine, 103a, 105ab); or (2, 112, 103b, 105ab, 620); or (3, 112, 103b, 105ab, 620); or 4, 113, 105ab, 621); or (5, 114, 105c, 621, 623); and 201, 202, 403, 404, 611, 612, 613, 614, 615, 618(a) or (b). II.Model FU-24A, 2 PCLM (Normal Category), Approved February 28, 1961 Engine Continental O-470-E (See Items 112 and 113 for optional engines) Fuel 80/87 minimum grade aviation gasoline. O-470-E only (See Items 112, 113 for other engines). Engine limits For all operations, 2600 r.p.m. (225 h.p.) Airspeed limits Maneuvering Vp 111 mph ( 96 knots) CAS Maximum structural cruising Vno 131 mph (114 knots) CAS Never exceed Vne 165 mph (143 knots) CAS Flaps extended Vf 80 mph ( 70 knots) CAS C.G. range (+118.7) to (+125.6) at 3500 lbs. (+110.0) to (+125.6) at 2800 lbs. or less (Straight line variation between points given) Empty weight C.G. range None Datum 100.2 in. ahead of wing leading edge Leveling means Fuselage upper longerons and bulkhead in cargo area Maximum weight 3500 lbs. No. seats 2 (+98). See Item 405 for additional seats. Maximum cargo 1300 lbs. (+121) to (+164). (Maximum airplane weight including cargo shall not exceed 3500 lbs.) Fuel capacity Two wing tanks, 23.5 gals. each (+110). Total usable 44 gals (+110) Oil capacity 3 gals. (+37) Control surface movements Elevator (chord line measured with airplane level) Nose down 20° Nose up 5° Elevator tab (measured with respect to elevator) Trailing edge down 3.5° (elevator 5° nose up) Trailing edge up 9.0° (elevator 20° nose down) Rudder Right 30° Left 30° Aileron Down 10° Up 25° Flaps Down 40° Required equipment In addition to the pertinent required basic equipment specified in CAR 3, the follo wing items of equipment must be installed: (1, Basic O-470-E engine, 103a, 105ab); or (2, 112, 103b, 105ab, 620); or (3, 112, 103b, 105ab, 620); or 4, 113, 105ab, 621); and 201, 202, 406, 407, 611, 612, 613, 614, 615, 618(a) or (b). 4A12 Page 3 Specifications Pertinent to All Models Serial numbers eligible 7,102 and up (For aircraft manufactured in the United States prior to transfer to Type Certificate 4A12 to Air Parts, Ltd., of New Zealand). For aircraft manufactured by Air Parts, Ltd., the New Zealand Civil Aviation Division Certificate of Airworthiness for Export, endorsed as noted under "Import Requirements" must be submitted for each individual aircraft for which application for certification is made. Certification basis CAR 3 as amended to 16 May 1953 original Type Certificate 4A12 issued 22 July 1955. Date of application for type certificate: 13 November 1953 Type Certificate 4A12 reissued 7 November 1972, to Air Parts, Ltd., of New Zealand, transferred on September 20, 1978, to New Zealand Aerospace Ind., Ltd., and reissued January 22, 1979, to Frontier -Aerospace Inc. of Long Beach, California. Import requirements For aircraft manufactured in New Zealand, a United States Airworthiness Certificate may be issued on the basis of a New Zealand Certificate of Airworthiness for Export signed by a representative of the New Zealand Civil Aviation Division containing the following statement: "The aircraft covered by this certificate has been examined and found to comply with CAR 3 as revised 16 May 1953 and conforms to Type Certificate 4A12 and is in a condition for safe operation." Equipment: A Plus (+) or minus (-) sign preceding the weight of an item of equipment indicates net weight change when that item is installed. Propellers and Propeller Accessories (Except De-icing Equipment) 1. (a) Propeller - Hartzell, constant speed, Hub Model HC-82XF-1B, Blades Model 8833 (+11) (Eligible only on Continental O-470-E engine) Diameter: Maximum 88 in., minimum allowable for repairs 86 in. No further reduction permitted. Pitch setting at 30 in. Sta.: Low 10.5°, high 27.0° 65 lbs. (+11) (b) Propeller governor, Woodward No. 210065H 4 lbs. (+18) 2. Propeller - Hartzell, Hub Model HC-92ZF-1B1, Blades Model 8847, including governor installed per FAC Dwg. 244383. (Eligible only on Continental O-470-M or O-470-N engine) Diameter: Maximum 88 n., minimum 88 in. Pitch setting at 30 in. Sta.: Low 12.0°, high 24.4° Use actual weight change 3. Propeller - McCauley Model 2A36C18/90M-4, including governor installed per FAC Dwg. 244384. (Eligible only on Continental O-470-M or O-470-N engine) Diameter: Maximum 86 in., minimum 84 in. Pitch setting at 36 in. Sta.: Low 10°, high 22.3° Use actual weight change (+11) 4. Propeller - McCauley Model D2A36C33/90M-2 including governor installed per FAC Dwg. 244394 (eligible only on Continental IO-470-D engine) Diameter: Maximum 88 in., minimum 84 in. Pitch setting at 36 in. Sta.: Low 8.4°, high 22.3° Use actual weight (+11) 5. Propeller McCauley Model 2A36C43/100R-10 including governor installed per SFC Dwg. 244393 (Eligible only on Continental GIO-470-A engine) Diameter: Maximum 90 in., Minimum 88 in. Pitch setting at 36 in. Sta.: Low 11.3°, high 25.0° Use actual weight (+9) 4A12 Page 4 Engine and Engine Accessories - Fuel and Oil System 101. Starter, Delco-Remy #1109471 14 lbs. (+46) 102. Carburetor air filter, Air Maze No. P-1A 1 lb. (+51) 103. (a) Carburetor - air intake system (less filter) (SFC Dwgs. 244300, 244319, 244322 applicable to O-470-E engine only). Use actual weight (b) Carburetor - air intake system (less filter) (SFC Dwgs. 244300, 248142 applicable to O-470-N and O-470-M engine only). Use actual weight 104. Delete. 105. Fuel pump installation - Editor of following Adel electric fuel booster pumps connected in series with one Romec Model RD7430-2 engine-driven fuel pump. (a) Adel Model 28470-3 per FAC Dwg. 244855 (b) Adel Model 20113 per FAC Dwg. 244820 4 lbs. (+110) (c) One Weldon Tool Co. style "J" Part No. 8001-B fuel booster pump connected in series with engine driven pump per SFC drawing 244887 (eligible only with Item 114 engine installation). Use actual weight (d) One Weldon Tool Co. style "J" Part No. 8001-A fuel booster pump connected in series with engine driven pump per SFC drawing 244891 (eligible only with item 113 engine installation). 106. Delete. 111. Unusable fuel (see NOTE 1 for definition) 18 lbs. (+110) 112. Engine - Continental O-470-M or O-470-N, installed per FAC Dwg. 248142 and FAC E.O. 691, 701, 702, 703, 706, 707, 714, and 715 Item 2 or 3 is required in lieu of Item 1. Fuel - 91/97 minimum grade aviation gasoline. Engine limits: For all operations, 2610 r.p.m. (240 h.p.) Use actual weight change 113. Engine - Continental IO-470-D installed per FAC Dwgs. 248162, 248161, and 244395, including E.O.'s 836, 837, 852, 853, 855, 857 through 865, 867 and 874. Item 4 is required in lieu of Items 1, 2 and 3. Item 621 is required. Fuel: 100 min. grade aviation gasoline. Engine limits: For all operations, 2625 r.p.m. (260 h.p.) Use actual weight 114. Engine - Continental GIO-470-A installed per SFC Dwg. 248165. Item 5 is required in lieu of Items 1, 2, 3, or 4. Items 621 and 623 are required. Eligible on FU-24 only. Fuel: 100 minimum grade aviation gasoline. Engine limits: All operations 3200 r.p.m. (310 h.p.) Use actual weight Landing Gear and Floats 201. Main landing gear: 8.50-6 four-ply rating tires and 8.50-6 wheel assemblies (3500 lb. max. wt.) 52 lbs. (+141) (a) Wheel Assembly Goodrich Model G-3-663-M1 (b) Brake Assembly Goodrich Model D-2-565-1 202. Nose wheel: 8.50-6 four-ply rating tire and 8.50-6 wheel assembly 21 lbs. (+51) (a) Goodrich Model G-3-852 203. Main Landing Gear: 8.50-6 six-ply rating tires and 8.50-6 wheel brake assemblies (4000 lb. max. wt.) 52 lbs. (+141) (a) Wheel Assembly Goodrich Model G-3-663-M1 (b) Brake Assembly Goodrich Model D-2-565-1 4A12 Page 5 Electrical Equipment 301. Generator Delco-Remy No. 1101892, 35 a. 16 lbs. (+44) 302. Battery, Reading (Rebat) No. R33, 12 V 23 lbs. (+58) 303. Voltage Regulator (a) Delco-Remy No. 11188922 lbs. (+62) 304. Electrical installation per SFC Dwgs. 248160 (eligible only with Item 114 engine installation). Use actual weight Interior Equipment 401. Combination seat belt and shoulder harness, Air Associates Model 4465437. 4 lbs. (+110) 402. Inertia reel. American Seating Company Model No. O-3903NN-103 2 lbs. (+110) 403. Instrument Installation per FAC Dwg. 246107 Use actual weight 404. Pilot's seat, AN-7505 modified per FAC Dwg. 243428 Use actual weight 405. Passenger seats (four place) and cover installation per FAC Dwgs. 249500, 249506, 249220 E.O. 667, 249501 E.O. 680. Item 410 is required. Note: C.G. of forward two passengers is at (+131) and aft two passengers is at (+174) Use actual weight change 406. Instrument installation per FAC Dwg. 248150 Use actual weight 407. Pilot seat (dual) installation per FAC Dwg. 248144 Use actual weight 409. Installation - Seat, agricultural airplane per SFC Dwg. 248154 including 243154 doublers and flap controls per 248155 410. Installation - Head rest, passenger per SFC Dwg. 249262. Required with Item 405. Use actual weight 411. Installation - Rear window, passenger compartment per SFC Dwg. 243657. Use actual weight Miscellaneous (Not listed above) 601. Aerial applicator installation per FAC Dwgs. 249233, 249245 and 249247 Note: Item 611 is not required with this installation. The C.G. of the hopper load is at (+135.7) The following placards must be installed in clear view on or adjacent to the hopper: "Hopper Capacity 1250 Pounds" "Approved for non-toxic material only" Use actual weight change 611. Cargo floor installation per FAC Dwg. 249220 Use actual weight 612. Two extended wing tips (a) FAC Dwg. 241403 (required with aileron installation FAC Dwg. 248104) Use actual weight (b) FAC Dwg. 241406 (required with Item 616) Use actual weight (c) FAC Dwg. 241403 (required with Item 617) Use actual weight 613. Two wing leading edge spoilers per FAC Dwg. 241208 Use actual weight 4A12 Page 6 614. Cockpit ventilation and sealing Use actual weight (a) FAC Dwgs. 241183, 241209, 241210, 241211, 243436, 243703, 244216, 244218, 244219, 244220, 244338, 248131, and 248135 (required with Item 112 and O-470-E engine installation) (b) FAC Dwgs. 241183, 241209, 241210, 241211, 243436, 243703, and 249266 (required with Item 113) 615. Cargo compartment control system guards per FAC Dwg. 248122 Use actual weight 616. Friese type aileron installation per FAC Dwgs. 241100-E.O. 671, 241214, 241215, 241216, 241217, 241218, 241220, 241310-E.O. 666, 241344, 241345, 241350, 241515, 248137, 248138, 248139, 241219 Note: Item 612(b) is required in lieu of Item 612(a) 617. Bulged type aileron installation per FAC Dwg. 248141 Use actual weight 618. Elevator control horn installation (a) FAC Dwg. 242526, E.O. 690 Use actual weight (b) FAC Dwg. 248143 619 Extension limit cables, nose gear per SFC Dwg. 249259 Use actual weight 620. Installation - Engine Cowling removable nose per SFC Dwg. 248156 (applicable to O- 470-M and O-470-N engine installations only) Use actual weight 621. Installation - Ventilator, cockpit per SFC Dwg. 249266. Required use actual weight with items 113 and 114 623. Installation - Engine Cowling per SFC Dwg. 248166. Required with Item 114. 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 and at all times thereafter. (b) The fuel tank capacity includes "Unusable" fuel of three gallons, which cannot be used safely in all flight attitudes and which must be included in the empty weight. (c) The airplane must be loaded so that the C.G. is within the specified limits at all times taking into consideration the effects of fuel and cargo released overboard. NOTE 2. The following placards must be displayed in the locations noted: (a). In front of and in clear view of the pilot: (1) "This airplane must be operated as a normal category airplane in compliance with the operating limitations stated in the form of placards and instrument markings. All acrobatic maneuvers, including spins, are prohibited." (2) Caution: "Fuel tank caps must be secure before flight." (3) "No Smoking." (4) "Solo from left seat only." (FU-24A only). (b). On the side of the cockpit: "Maximum Weight and C.G. Range (For 3500 lb. maximum weight) Maximum Weight 3500 lbs. C.G. Range (+118.7) to (+125.6) at 3500 lbs. (+110.0) to (+125.6) at 2800 lbs. and below (Straight line variation between points given) Datum 100.2 inches ahead of wing leading edge. See loading instructions for cargo operations." "Maximum Weight and C.G. Range (For 4000 lb. maximum weight - FU-24 only) Maximum Weight 4000 lbs. C.G. Range (+120.7) to (+125.6) at 4000 lbs. (+110.0) to (+125.6) at 2800 lbs. and below (Straight line variation between points given) Datum 100.2 ahead of wing leading edge. 4A12 Page 7 See loading instruction for cargo operations." "Airspeed and Load Factor Limitations Never exceed speed 165 mph CAS Max. structural cruising 131 mph CAS Maneuvering speed 111 mph CAS Flaps extended speed (3500 lbs) 80 mph CAS Flaps extended speed (4000 lbs) 90 mph CAS Maneuvering load factors 0° flaps +3.8: 40° flaps +2.0" "Significance of Instrument Markings Red Radial Line Max. or Min. allowed Green Arc Normal operation Yellow Arc Cautionary operation White Arc Flap down operating range" "Engine and Propeller Limits, Fuel and Oil (For O-470-E engine) Engine - Continental O-470-E For all operations 2600 r.p.m. (225 h.p.) max. Cylinder Head Temperature 525°F. max. Propeller - Hartzell HC-82XF-1B with 8833 blades Diameter limits 88" to 86" Pitch setting at 30 inch station, Low 10.5°, High 27.0° Fuel - 80/87 minimum grade aviation gasoline Two fuel tanks 23.5 gals. capacity each Total usable fuel 44 gals. The unusable fuel of three gals. total cannot be used safely in flight The fuel gauges read zero when only unusable fuel remains in the tanks. Oil capacity - three gals. Oil inlet temperature 225°F. max." "Engine and Propeller Limits, Fuel and Oil (For O-470-M or O-470-N engine) Engine - Continental O-470-M (or O-470-N) For all operations 2600 r.p.m. (240 h.p.) max. Cylinder Head Temperature 500°F. max. Propeller - McCauley Model 2A36C18/90M-4 Diameter limits 86 in. to 84 in. Pitch setting at 36 in. Sta.: Low 10°, High 22.3° Propeller - Hartzell HC-92ZF-1B1 with 8847 blades Diameter limits 88" max., 88" min. Pitch setting at 30 in. Sta.: Low 12.0°, High 24.4° Fuel - 91/97 minimum grade aviation gasoline Two fuel tanks 23.5 gals. capacity each Total usable fuel 44 gals. The unusable fuel of three gals. total cannot be used safely in flight. The fuel gauges read zero when only unusable fuel remains in the tanks. Oil capacity - 3 gals. Oil inlet temperature 225°F. max." "Engine and Propeller Limits, Fuel and Oil (For IO-470-D engine) Engine - Continental IO-470-D For all operations 2625 r.p.m. (260 h.p.) max. Cylinder Head Temperature 460°F. max. Propeller - McCauley D2A36C33/90M-2 Diameter limits 88" max. to 84" min. Pitch setting at 36 in. Sta.: Low 8.4°, High 22.3° Fuel - 100 minimum grade aviation gasoline Two fuel tanks 23.5 gals. (19.5 imp.) capacity each Total usable fuel 44 gals. (36.5 imp.) The unusable fuel of three gals. (2.5 i mp.) total cannot be used safely in flight. The fuel gauges read zero when only unusable fuel remains in the tanks. 4A12 Page 8 Oil capacity - 3 gals. (2.5 imp.) Temperature limits 225°F. maximum." "Engine and Propeller Limits, Fuel and Oil (For GIO-470-A engine) Engine - Continental GIO-470-A For all operations 3200 r.p.m. (310 h.p. @ 28.8" MP) maximum Recommended Cruise 2800 r.p.m. (233 h.p. @ 26" MP) maximum Cylinder Head Temperature 460°F. maximum Propeller - McCauley 2A36C43/100R-10 Diameter limits 90" max. to 88" min. Pitch setting at 36 in. Sta.: Low 11.3°, High 25.0° Fuel - 100 minimum grade aviation gasoline Two fuel tanks 23.5 gals. capacity each Total usable fuel 44 gallons The unusable fuel of three gallons total cannot be used safely in flight. The fuel gauges read zero when only unusable fuel remains in the tanks. Oil capacity - 15 quarts (U.S.) Oil temperature limits 240°F maximum." (c) In the cargo compartment @ 3500 lb. mx. wt. @ 4000 lb. max. wt. (1) "Max. compt. load 1300 lbs. 1500 lbs. Max. load per lin. ft. 375 lbs. 418 lbs. Max. load per sq. ft. 375 lbs. 386 lbs. (2) All items carried in this compartment must be properly secured" (d) In the passenger compartment: (1) "No smoking" NOTE 3. The Model FU-24 only is eligible for a maximum weight of 4000 pounds when modified in accordance with Drawing List No. 24.7003A, Revision dated September 27, 1965, and operated in accordance with limitations for the 4000 lb. gross weight specified in NOTE 2 of this specification. Items of Equipment required for the 4000 pound maximum weight aircraft are: Items 5, 102, 105c, 114, 202, 203, 403, 404, 611, 612, 613, 614, 615, 618(a) or (b), 621, 623. - END -