TCDS A-793

P a g e N o . 1234567891 0 1 1 1 2 1 3 1 4 1 5 1 6 1 7 1 8 1 9 2 0 2 1 R e v . N o . 2 62 32 62 32 52 52 32 62 62 62 62 62 32 32 32 32 32 32 32 3 2 3 P a g e N o . 2 22 32 4 R e v . N o . 2 32 52 5 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-793 Revision 26 General Dynamics 240 Series USAF T-29A, VT-29A, T-29B, T-29C, T-29D, & C-131A January 2, 2001 Aircraft Specification A-793 Manufacturer Kelowna Flightcraft R & D Ltd. #1 5855 Kelowna Airport Kelowna, BC, Canada V1V 1S1 I - Model 240-0 Approved December 7, 1948 This Section deleted. All Model 240-0 airplanes have been revised to allow their operation in accordance with the provisions of Section II. II - Model 240-0, -1, -2, -3, -4, -5, -6, -7, -8, -10, -11, -12, -13, -14, -15, -17, -19, -26 Model 240-6 approved December 7, 1948 Model 240-17 approved December 28, 1978 NOTE 8 for explanations of model designations NOTE 14 for required changes to the military T-29A and VT- 29A for operation as a Model 240-17 Engines 2 P&W Double Wasps CA3, CA15, CA18, or R2800-83AM3, -83AM4A or -83AM9 (20:9 propeller reduction gearing); or CB3, CB16, R2800-83AM5, -52WM1 or -99W (20:9 propeller reduction gearing). Note: R2800-97W is equivalent to R2800 CA-18. Fuel 100/130 grade aviation gasoline Engine Limits (Straight line manifold pressure variation with altitudes shown) HP. R.P.M. MP In. Hg. Alt. P&W Double Wasp CA3, CA15, R2800-83AM3 & -83AM4A Low impeller gear ratio 7.29:1 Takeoff (two minutes) (dry) 2100 2800 53.5* S.L. Takeoff (two minutes) (wet) 2400 2800 56.5 S.L. Maximum continuous 1800 2600 45.0 S.L. Maximum continuous 1800 2600 44.0 6500' or (for CA3, CA15 & -83AM4A only) Maximum continuous 1900 2600 47.5 S.L. Maximum continuous 1900 2600 46.5 4900' High impeller gear ratio 9.45:1 (CA15, R2800-83AM3, & -83AM4 only) Maximum continuous 1600 2600 46.5 10000' Maximum continuous 1600 2600 45.0 16200' A-793 Page 2 of 24 Engine Limits (Cont'd) HP. R.P.M. MP In. Hg. Alt. P&W Double Wasp CA18 & R2800-83AM9 Low impeller gear ratio 7.29:1 Takeoff (two minutes) (dry) 2100 2800 53.5* S.L. Takeoff (two minutes) (wet) 2400 2800 56.5 S.L. Maximum continuous 1800 2600 45.0 S.L. Maximum continuous 1800 2600 44.0 6500' Maximum continuous 1900 2600 47.5 S.L. Maximum continuous 1900 2600 46.5 4500' High impeller gear ratio 9.1:1 Maximum continuous 1675 2600 49.0 8000' Maximum continuous 1675 2600 47.0 13500' P&W Double Wasp CB3, CB16, R2800-83AM5, -52WM1 & -99W Low impeller gear ratio 7.29:1 Takeoff (two minutes) (dry) 2050 2700 55.0 S.L. Takeoff (two minutes) (dry) 2050 2700 53.0 6900' Takeoff (two minutes) (dry) 1950 2800 53.0 S.L. Takeoff (two minutes) (dry) 1950 2800 51.0 9800' Takeoff (two minutes) (wet) 2400 2800 59.5 S.L. Takeoff (two minutes) (wet) 2400 2800 59.0 5000 Maximum continuous 1800 2600 48.5 S.L. Maximum continuous 1800 2600 46.5 9200' High impeller gear ratio 8.58:1 (CB16, R2800-83AM5, -52WM1 & -99W only) Maximum continuous 1700 2600 48.5 10000' Maximum continuous 1700 2600 47.5 16800' *54 In. Hg. for R2800-83AM3, -83AM4A, and -83AM9 Airspeed Limits VC (Maximum cruising) (S.L. to 7600') (Above 7600' reduce speed) See NOTE 9 for alternate values 280 m.p.h. 6 m.p.h. (244 knots) ( 5 knots) True Ind. per 1000' VNE (Never exceed) (S.L. to 7600') (Above 7600' reduce speed) See NOTE 9 for alternate values 315 m.p.h. 6 m.p.h. (274 knots) ( 5 knots) True Ind. per 1000' VP (Maneuvering) 180 m.p.h. (157 knots) True Ind. VF (Flaps down) 15° maximum 215 m.p.h. (187 knots) True Ind. VF (Flaps down) 20° maximum 200 m.p.h. (174 knots) True Ind. VF (Flaps down) 30° maximum 178 m.p.h. (155 knots) True Ind. VF (Flaps down) 40° full 160 m.p.h. (139 knots) True Ind. VLE (Landing gear extended) 200 m.p.h. (174 knots) True Ind. VLO (Landing gear operation) (Retracted) 150 m.p.h. (131 knots) True Ind. VLO (Landing gear operation) (Extended) 200 m.p.h. (174 knots) True Ind. A-793 Page 3 of 24 C. G. Range Takeoff and landing (351.4) (17% MAC) to (367.7) (31% MAC) with landing gear extended. Normal enroute operation (346.8) (13% MAC) to (370.1) (33% MAC) with landing gear retracted. Effect of retracting landing gear: -69,160 in. lbs. See NOTE 5 for modifications accomplished. Maximum Weight Takeoff 40,500 lbs. (See NOTE 11 for 41,200 lbs. with fuel dump system) (See NOTE 5 for modifications accomplished) (See NOTE 18 for 41,200 lbs. or 41,790 lbs. without outer panel tanks) (See NOTE 19 for 41,790 lbs. with outer panel tanks) (See NOTE 20 for 42,500 lbs. or 42,400 lbs. with fuel dump installation (with or without outer panel tanks)) Landing 38,600 lbs. (See NOTES 18, 19, and 20 for 39,800 lbs.) Zero fuel 37,400 lbs. (See NOTE 18 for 38,900 lbs. or 38,600 lbs. without outer panel tanks) (See NOTE 19 for 38,900 lbs. with outer panel tanks) (See NOTE 20 for 38,100 lbs., 38,400 lbs., or 38,170 lbs. with fuel dump installation) Minimum Crew 2 - Pilot and Copilot (Sta. 84) Maximum Passengers 40 (CAR 4b.381) Maximum Baggage (See NOTE 4) Fuel Capacity 1000 gal. (one 500 gal. tank in each wing) (Sta.375) Oil Capacity 41 gal. with Item 1(b), (c), or (d) installed (one 20.5 gal. tank in each nacelle) (Sta. 323) 45 gal. with Item 1(a) installed (one 22.5 gal. tank in each nacelle) (Sta. 323) Serial Numbers Eligible 1 and up (566 aircraft were produced) Required Equipment 1.(a), (b), (d), (e), (f), or (g); 111.(a); 115.(a) or (b); 116.(a) or (b); 201.(a) or (b); 202.(b) or (c); 204.(a); 205.(a); 207.(a), (b), or (c); 208.(a) or (b); 209.(a) or (b); 210.(a); 211.(a) or (b); 415. III -Models 240-23, -24, -25, -27, -52, and -53 Model 240-23 Approved September 1, 1950 Model 240-27 Approved July 8, 1963, & June 5, 1979 Models 240-52, 240-53 Approved June 12, 1980 NOTE 10 for eligibility of additional models NOTE 13 for required changes to the Military T29B for operation as a Model 240-27 NOTE 15 for required changes to the Military T-29C for operation as a Model 240-27 NOTE 16 for required changes to the Military T-29D for operation as a Model 240-52 NOTE 17 for required changes to the Military C-131A for operation as Model 240-53 Fuel 100/130 grade aviation gasoline. A-793 Page 4 of 24 Engine Limits Same as Section II Airspeed Limits VC (Maximum cruising) (S.L. to 16500') (Above 16500' reduce speed See NOTE 10 for alternate values 270 m.p.h. 6 m.p.h. (235 knots) ( 5 knots) True Ind. per 1000') VNE (Never exceed) (S.L. to 16500') (Above 16500' reduce speed See NOTE 10 for alternate values 306 m.p.h. 6 m.p.h. (266 knots) ( 5 knots) True Ind. per 1000') VP (Maneuvering) 180 m.p.h. (157 knots) True Ind. VF (Flaps down) 15° maximum 215 m.p.h. (187 knots) True Ind. VF (Flaps down) 20° maximum 200 m.p.h. (174 knots) True Ind. VF (Flaps down) 30° maximum 178 m.p.h. (155 knots) True Ind. VF (Flaps down) 40° full 160 m.p.h. (139 knots) True Ind. VLE (Landing gear extended) 200 m.p.h. (174 knots) True Ind. VLO (Landing gear operation) (Retracted) 150 m.p.h. (131 knots) True Ind. VLO (Landing gear operation) (Extended) 200 m.p.h. (174 knots) True Ind. C. G. Range Takeoff and landing (351.4) (17% MAC) to (367.7) (31% MAC) with landing gear extended. Normal enroute operation (346.8) (13% MAC) to (370.1) (33% MAC) with landing gear retracted. Effect of retracting landing gear: -69,160 in. lbs. See NOTE 5 for modifications accomplished. Maximum Weights Engines (1) CA3, CA15, CA18, CB3, CB16, R2800-83AM3; -83AM4A, -83AM5, -83AM9, -52WM1, -99W (1)(2) CA3, CA15, CA18, CB3, CB16, R2800-83AM4A, -83AM5, -83AM9, -52WM1, -99W (3) CA3, CA15, CA18, CB3, CB16, R2800-83AM4A, -83AM5, -83AM9, -52WM1, -99W (3) CA3, CA15, CA18, CB3, CB16, R2800-83AM4A, -83AM5, -83AM9, -52WM1, -99W Propellers Curtiss C632S-B/740-6C2-0 C632S-B/740-9C2-0 Hamilton Standard 23260/2H17K3-48R 23260/2H17U3-48R or /2H17AA3-48R or /2H17AC3-48R 43E60/6895A-12 Curtiss C632S-B/740-6C2-0 C632S-B/740-9C2-0 Hamilton Standard 23260/2H17K3-48R 23260/2H17U3-48R or /2H17AA3-48R or /2H17AC3-48R 43E60/6895A-12 Curtiss C632S-B/740-9C2-0 Hamilton Standard 43E60/6895A-12 Curtiss C632S-B/740-9C2-0 Hamilton Standard 23260/2H17K3-48R 23260/2H17U3-48R or /2H17AA3-48R or /2H17AC3-48R 43E60/6895A-12 T.O. Gross Wt. 41200 41790 42400 42500 Zero Fuel Wt. 38900 38600/38900(4) 38160/38460(4) 38100/38400(4) Landing Weight 39800 39800 39800 39800 (1) For airplanes modified in accordance with CVAC Service Bulletin 240-377 not incorporating outer panel fuel tanks. (2) For airplanes modified in accordance with CVAC Service Bulletin 240-376A incorporating outer panel fuel tanks. (3) For airplanes modified in accordance with CVAC Service Bulletin 240-308B and 240-426. (4) Upper figure Zero Fuel Wt. without outer panel fuel tanks. Lower figure Zero Fuel Wt. with outer panel fuel tanks. A-793 Page 5 of 24 Minimum Crew 2 - Pilot and Copilot (Sta. 84) Maximum Passengers 40 (CAR 4b.381) (32 for Model 240-23) Maximum Baggage (See NOTE 4) Fuel Capacity 1000 gal. (one 500 gal. tank in each wing) (Sta. 375) 1550 gal. with outer fuel tanks, CVAC 240-1406001 (one 500 gal. and one 275 gal. tank in each wing) (Sta. 375) (Tanks in each wing are interconnected to function as a single 775 gal. tank) Oil Capacity 41 gal. with Item 1(b) or (d) installed (one 20.5 gal. tank in each nacelle ) (Sta.323) 45 gal. with Item 1(a) installed (one 22.5 gal. tank in each nacelle) (Sta. 323) 5 gal. in fuselage (required when outer wing fuel tanks are installed) (Sta. 126) Serial Numbers Eligible 1 and up (566 aircraft were produced) Required Equipment 1.(a), (b), (d), (e), (f), or (g); 111.(a) or (b); 115.(a), (b), (c), or (d); 116.(b); 201.(a) or (b); 202.(b) or (c); 204.(a); 205.(a); 207.(b), or (c); 208.(a) or (b); 209.(a),(b), or (c); 210.(a) or (b); 211.(b); 415. Specifications Pertinent to All Models Datum Station 0 (Fuselage Nose). (Distance from data to centerline rear main wheel 393.1 in.) MAC 116.6 in. L.E. MAC Sta. 331.6 Leveling Means Leveling lugs inside nose wheel well L.H. side. Control Surface Movements Main Surfaces: Elevators 25° Up 12° Down Rudder 18° Left 18° Right Ailerons (Rig 1½° Drooped on Ground) 17° Up 20° Down Flight (Spring) Tabs: Elevator (Rig 7° Up from Chord at Neutral)* 12° Up 12° Down Rudder (Rig 2° to Left of Chord Neutral) 14° Left 10° Right Servo and Trim Tabs (Main Surfaces in Neutral): Elevator, Servo-Trim (Rig 5° Down from chord at Neutral) 3° Up 17° Down Rudder Trim 9° Left 9° Right Aileron Servo-Trim (Rig 1½° Up from Chord at Neutral) 8½° Up 5½° Down Flaps 39° Total Angular Travel *With control column counter-balance and elevator bungee spring disconnected. This up-rigging becomes 9½° with counter-balance and spring connected. A-793 Page 6 of 24 Certification Basis Type Certificate No. A-793 (Transport Category, CAR 4b, effective November 9, 1945, and Amendment 4b-1, effective November 1, 1946) (Model 240-8, certified under the combined requirements of CAR 4b, effective November 9, 1945, and Amendment 4b-1, effective November 1, 1946, and CAR 3, effective November 13, 1945.) Production Basis None at this time. General Dynamics, Convair Division, produced 566 Model 240 aircraft and parts under FAA Production Certificate (PC) Number 605 in San Diego, California, until 1995. PC 605 became invalid when the Type Certificate (TC) was transferred to Tracor Flight Systems, Inc. Tracor was issued FAA Production Certificate 708NM for the production of spare parts and type design changes for the Model 240. The Tracor PC was surrendered in 1998 when the TC was endorsed to Kelowna Flightcraft, Kelowna, BC, Canada Export Eligibility Eligible for export to all countries subject to the provisions of MOP 2-4 except as follows: Canada - Landplane only eligible. Propellers and Propeller Accessories (Except Anti-Icing Equipment) 1. (a) 2 Curtiss-Wright, hubs C632SB with 740-6C2-0 blades 926 lbs. (Sta. 220) Diameter: 13'1" Pitch settings at 42" sta., for use with engines having 2100 hp. dry takeoff power rating only: Reverse -13.5°, minimum low 24°, feathered 91.7° Pitch settings at 42" sta., for use with engines having 2400 hp. wet takeoff power rating: Reverse -17.5°, minimum low 26.5°, feathered 91.7° Following placards required: (1) "Avoid continuous operation in flight below 1500 engine rpm." (2) "Avoid continuous operation on ground between 1250 & 1500 engine r.p.m.." (b) 2 Hamilton Standard, hubs 23260 with 2H17K3- 48R blades 882 lbs. (Sta. 224) Diameter: 13'1" Pitch settings at 72" sta.: Reverse -23°, or -25°, minimum low 14°, feathered 81°. A-793 Page 7 of 24 Propellers and Propeller Accessories (Except Anti-Icing Equipment) (Cont’d) Some airplanes incorporate restricted throttle travel in reverse, limiting reverse power to approximately 75% of the 2400 hp. takeoff rating of the engines. These airplanes have a reverse blade angle of -23°. Airplanes with full power available in reverse have a reverse blade angle of -25° (c) Deleted June 26, 1953 (d) 2 Hamilton Standard, hubs 23260 with 2H17U3- 48R or 2H17AA3-48R blades (See Prop. Spec. P-853 (NOTE 6) for interchangeable blades) 888 lbs. (Sta. 224) Diameter: 13'1" Pitch settings at 72" sta.: Reverse -23°, or -25°, minimum low 14°, feathered 81° Some airplanes incorporate restricted throttle travel in reverse, limiting reverse power to approximately 75% of the 2400 hp takeoff rating of the engines. These airplanes have a reverse blade angle of -23°. Airplanes with full power available in reverse have a reverse blade angle of -25°. 3. 2 Curtiss-Wright, hubs C632SB with 740-9C2-0 blades 980 lbs. (Sta. 220) Diameter: 13'1" Pitch settings at 42" sta., for use with engines having 2100 hp. dry takeoff rating only: Reverse -13.5°, minimum low 24°, feathered 91.7° Pitch settings at 42" sta., for use with engines having 2400 hp. wet takeoff power rating: Reverse -17.5°, minimum low 26.5°, feathered 91.7° Following placards required: (1) "Avoid continuous operation in flight below 1500 engine rpm." (2) "Avoid continuous operation on ground between 1250 & 1500 engine rpm." (f) 2 Hamilton Standard, hubs 43E60 with 6895-12 blades 1080 lbs. (Sta. 224) Diameter: Max. 13’1-5/16”, minimum allowable for repairs 12’9-5/8” No further tolerance permitted Pitch setting at 42” sta.: Reverse –13°; minimum low 29°; feathered 95° A-793 Page 8 of 24 Propellers and Propeller Accessories (Except Anti-Icing Equipment) (Cont’d) (g) 2 Hamilton Standard hubs 23260 with blades 2H17AC3-48R (See Prop. Spec. P-853 (NOTE 6) for interchangeable blades) 906 lbs. (Sta. 224) Diameter: 13'1" Pitch settings at 72" sta.: Reverse -23° or -25°, minimum low 14°, feathered 81° Some airplanes incorporate restricted throttle travel in reverse, limiting reverse power to approximately 75% of the 2400 hp. takeoff rating of the engines. These airplanes have a reverse blade angle of -23°. Airplanes with full power available in reverse have a reverse blade angle of -25°. 111. (a) System fuel 47 lbs. (Sta. 375) (b) System fuel (with outer wing tanks installed) 53 lbs. (Sta. 375) 115. (a) System oil (with Item 1(a) or (e) installed) 133 lbs. (Sta. 275) (b) System oil (with Item 1(b), (d), (f), or (g) installed) 204 lbs. (Sta. 274) (c) System oil (with Item 1(a) or 1(e) and auxiliary oil installed) 145 lbs. (Sta. 275) (d) System oil (with Item 1(b), (d), (f), or (g) and auxiliary oil installed) 216 lbs. (Sta. 274) 116. 4 engine augmenters (a) Deleted December 12, 1950 (b) Muff type augmenters: (1) CVAC Part No. 240-6220195 with any of the following forward augmenter sections: 240-6221107, -0, -168, -172, -182, -190, -202, -250, -252, -260, -262, -264, -268, -280, -290, -300, -314, -360 117. Fuel dump system (See CVAC Service Bulletin 240-426 for part numbers, weight and basic moment changes.) Landing Gear 201. 2 Main Gear Shock Struts (a) Bendix 155370 (Left) and 155371 (Right) 450 lbs. (Sta 396) (b) Bendix 155150 (Left) and 155151 (Right) 444 lbs. (Sta. 396) (c) For Model 240-17, -27, -52, and -53 only Bendix 160570 (Left) and 160570 (Right) (See Notes) 455 lbs. (Sta. 396) (d) Bendix 159695 (Left) and 159696 (Right) (155370/155371 Shock Struts modified per Bendix Service Bulletin No. L.G. 516. Required for 41,200 lbs. and higher maximum take-off weight. Ref. CVAC S.B. 240-308A) 440 lbs. (Sta. 396) A-793 Page 9 of 24 Landing Gear (Cont'd) (e) Bendix 159589 (Left) and 159590 (Right) (155150/155151 Shock Struts modified per Bendix Service Bulletin No. L.G. 516 Required for 41,200 lbs. and higher maximum take-off weight. Ref. CVAC S.B. 240-308A) 454 lbs. (Sta. 396) Notes: 1. Must be used in pairs. Not to be used on other 240 aircraft (use only on 240-17, -27, -52, and -53) 2. Parts in Bendix 155150/155151, 155370/155371, 159589/159590, and 159695/159696 Commercial Gears and Bendix 160570 Military Gears are not interchangeable. 3. The Bendix 160570 Strut can be used in R.H. or L.H. installations depending on component assembly. 202. 4 Main Wheel Brake Assemblies (34 x 9.9) Type VII-B (E.H.P.) (a) Deleted - December 12, 1950 202 (b) Goodyear Model L34 x 9.9 HBM Wheel Assembly No. 9540082 Brake Assembly No. 9540245 Brake Assembly No. 9540485 Brake Assembly No. 9530222* 332 lbs. (Sta. 393) (c) Goodyear Model L34d x 9.9 HBM Wheel Assembly No. 9540316 Brake Assembly No. 9540245 Brake Assembly No. 9540485 Brake Assembly No. 9530222* 334 lbs. (Sta. 393) (d) Goodyear Model L34 x 9.9 for 240-17 Wheel Assembly No. 9540316 Wheel Assembly No. 9540316 M-1 Brake Assembly No. 9540245 Brake Assembly No. 9540245M 334 lbs. (Sta. 393) (e) Goodyear Model L34 x 9.9 for 240-27, -52, -53 Wheel Assembly No. 9540591 Wheel Assembly No. 9540316 M-1 Brake Assembly No. 9540485 334 lbs. (Sta. 393) *Note: Brake assembly must be reworked per S.B. 240-22A II A-793 Page 10 of 24 Landing Gear (Cont’d) 204. (a) 4 Main Wheel 12 Ply Rating Tires (34 x 9.9) Type VII B (Inflation Pressure = 95 PSI) 209 lbs. (Sta. 393) (b) 4 Main Wheel 14 Ply Rating Tires (34 x 9.9) Type VII B (Inflation Pressure = 109 PSI) 209 lbs. (Sta. 393) The maximum permissible weight of a tire and tube is 73.016 lbs. Either new or retreaded, the total weight of a tire and tube must not exceed this limit. 205. 4 Main Wheel Tubes (34 x 9.9) Type VII B, Plain with TR-150 Valve 31 lbs. (Sta. 393) 207. Nose Gear Shock Strut (a) Bendix 155155 131 lbs. (Sta. 92) (b) Menasco 523500 187 lbs. (Sta. 92) (Required for 41,200 lbs. and higher maximum take-off weight. Ref. CVAC S.B. 240-308A. Required for Model 240-17, -27, -52, and -53) (c) For Model 240-0, -10, and -26 only 183 lbs. (Sta. 92) Bendix 159845 (Ref. American Airlines E.A. C.732A. Alternate for Menasco 523500. Requires E.A. C.825 for 41,200 lbs. maximum take-off weight) 208. 2 Nose Wheels (26 x 6) Type II Tire (Model 240) (a) Goodrich Model 2665-M (Includes Fairings) Mag 36 lbs. (95) (b) Goodrich Model 2665-M1 (Without Fairings) Mag 36 lbs. (95) (c) Goodrich Assy. No. G-3-615-M Tube Type (d) Goodrich Assy. No. G-3-615-M1 Tube Type (e) Goodrich Assy. No. G-3-701M Tube Type (f) Goodrich Assy. No. G-3-701M1 Tube Type (g) Goodrich Assy. No. G3-677M1 Tube Type (T-29A only) 240-17 (h) Goodrich Assy. No. G3-704M Tube Type (i) Goodrich Assy. No. G3-704M1 Tube Type A-793 Page 11 of 24 Landing Gear (Cont'd) 2 Nose Wheels (26 x 6.6) Type VII Tire (Model T-29) (See note at end of paragraph 209. for limitations) (j) Goodrich Assy. No. G3-725M Tube Type (T-29A, B, C, D, C-131A) (k) Goodrich Assy. No. G3-725M1 Tube Type (T-29A, B, C, D, C-131A) 2 Nose Wheels (7.50 x 14) Type III with S.B. 240-308B or S.B. 240-397. Requires Menasco Nose Gear Shock Strut (Ref. 207.(b)) and 240-5210103-104 Nose Gear Drag Strut (Ref. 211.(b)). (l) Goodrich Assy. No. G3-902 Tube or Tubeless (m) Goodrich Assy. No. G3-904 Tube Type 209. 2 Nose Wheel Tires (See NOTE 5 regarding Item 209.a) (a) Goodrich Pre Rotating 10 Ply Rating Rotovane (26 x 6) Type II Tube Type Inflation Pressure = 97 PSI 44 lbs. (Sta. 95) (b) 10 Ply Rating (26 x 6) Type II Tube Type Inflation Pressure = 97 PSI 44 lbs. (Sta. 95) (c) 8 Ply Ratings (7.50 x 14) Type III Tube Type 46 lbs. (Sta. 95) with S.B. 240-308B or S.B. 240-397. Requires Menasco Nose Gear Shock Strut (Ref. 207.(b)) and 240-5210103-104 Nose Gear Drag Strut (Ref. 211.(b)). Inflation Pressure = 54 PSI (May be used on 26.6 wheel) 8 Ply Tire Only (d) 12 Ply Rating (26 x 6.6) Type VII Tube Type for G3-725M and M1 Only (240-17, -27, -52, -53) Inflation Pressure = 117.5 PSI (e) 12 Ply Rating (7.50 x 14) Type III for G3-902 Only (with S. B. 240-397 installed) Inflation Pressure = 82 PSI Notes: (1) 26 x 6.6 Tires, Tubes, and Wheels must be used only in pairs on nose wheel installations and the 26 x 6.6 Tires, Tubes, and Wheels are not interchangeable with the 26 x 6 items used on other models of the 240 aircraft. The 7.50 x 14 8 Ply Tires may be used on the 26 x 6 Wheels (Ref. 209.(c)). The 7.50 x 14 8 Ply Tires may be installed provided the Menasco Nose Gear Shock Strut (Ref. 207.(b)) and the 240-5210103-104 Nose Gear Drag Strut (Ref. 211.(b)) have been installed per S.B. 240-308B or S.B. 240-397. A-793 Page 12 of 24 Landing Gear (Cont'd) Notes (2) The tire pressures shown are nominal. (3) The maximum permissible weight of a tire and tube is 30.8 lbs. Either new or retreaded, the total weight of a tire and tube must not exceed this limit. 210. 2 Nose Wheel Tubes (a) (26 x 6) Type II Plain with 2.5 inch TR-150 Valve Bent 70° 9 lbs. (Sta. 95) (b) (7.50 x 14) Type III Plain 9 lbs. (Sta. 95) (c) (26 x 6.6) Type VII for Wheel G3-725 Only (240-17, -27, -52, and -53) 10 lbs. (Sta. 95) 211. Nose Gear Drag Strut (a) CVAC 240-5210101 Assy. 46 lbs. (b) CVAC 240-5210101 Assy. (including 240-5210103 -104 LH Upper Drag Strut) (Required for 41,200 lbs. and higher maximum take-off weight. Ref. CVAC S.B. 240-308A. Required to permit use of 7.50 x 14 Nose Wheel Tires. Ref. CVAC S.B. 240-397) 48 lbs. (c) CVAC 240-5210101-815 Assy. (For 240-17, -27, -52, -53 only) Electrical Equipment 340. 2 landing lights (a) Grimes 3800-3 13 lbs. (Sta. 335) 342. 1 taxi light ( a) General Electric 4560 3 lbs. (Sta. 2) 344. 1 forward position light (a) General Electric 4541 2 lbs. (Sta. 8) 345. 2 generators (a) General Electric 2CM75C4 (300 a.) 120 lbs. (Sta. 299) (b) General Electric 2CM82C1 (375 a.) 120 lbs. (Sta. 299) Interior Equipment 415. FAA Approved Model 240 Airplane Flight Manual. (The Manual may be carried as part of, or bound with, the operator's "Approved Operations Manual", but must retain its identity as an individual manual.) 416. (a) Cabin Supercharger, AiResearch Part No. 52351 50 lbs. (Sta. 408) (b) Cabin Supercharger, AiResearch Part No. 52851, Serial Nos. eligible for (a) and (b), 7-300 and up. A-793 Page 13 of 24 Interior Equipment (Cont'd) (c) Cabin Supercharger, Stratos Model S60-5, installed in accordance with American Airlines' Drawing FYC 1800A. (d) Cabin Supercharger, Stratos Model S60-11, installed in accordance with Pan American World Airways' Report No. LA-442 417. Sperry A-12 Autopilot installed per pages APW-1 through APW-23 of Convair Parts Catalog - Autopilot Section as revised June 15, 1950, and as modified by Sperry Drawing SK No. 5232-65381E (1) Servo Motor Cable Forces Limits Elevator Aileron Rudder 89 lbs. min. 70 lbs. min 50 lbs. min. 130 lbs. max. 89 lbs. max. 71 lbs. max (2) Power Gear Ratios Elevator Aileron Rudder 148:1 104:1 104:1 (3) Maximum speed (TIAS) for autopilot operation: 234 knots The maximum altitude loss during actual Automatic Pilot hard-over malfunctions are listed below: (a) Cruise configuration 350 ft. (b) Approach configuration Note: A FAA Approved Airplane Flight Manual Supplement must be supplied 100 ft. Anti-Icing Equipment (See NOTE 6 regarding operation in icing conditions.) 506. (a) 2 Propeller Deicing Installation (Curtiss propellers), CVAC Drawing No. 240-0060906. (b) 2 Propeller Deicing Installation (Hamilton Standard), CVAC Drawing No. 240-0061906. (c) 2 Propeller Deicing Installation (Hamilton Standard), CVAC Drawing No. 240-0062906. (d) 2 Propeller Deicing Installation (Hamilton Standard), American Airlines E.A. No. C.875 (with manual control inoperative) Miscellaneous 601. Stall Warning Indicator Installation (No longer required equipment) NOTE 1 (a) Current weight and balance report including list of equipment included in certificated weight empty, and loading instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter (except in the case of air carrier operators having an approved weight control system). See Approved Master Equipment List CVAC Report No. ZL-240-002 for Approved Alternate or Additional Items of Equipment. A-793 Page 14 of 24