TCDS 6A6

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 . 1 21 11 11 11 11 11 11 11 11 21 11 11 11 11 11 11 11 11 11 11 1 P a g e N o . 2 22 32 4 R e v . N o . 1 11 11 1 DEPARTMENT OF TRANSPORTATION FEDERAL AVATION ADMINISTRATION 6A6 Revision 12 Tracor (Convair) 340 440 Military C-131B Military C-131D Military C-131E Military C-131F/R4Y-1 January 1, 2001 Aircraft Specification 6A6 Manufacturer Kelowna Flightcraft R & D Ltd. #1 5855 Kelowna Airport Kelowna, BC, Canada V1V 1S1 I - Model 340 Approved March 27, 1952 The Model 340 airplane is basically similar for all dash numbers, the only differences being in the type of equipment and interiors for the customer's airplane. Engines 2 P&W Double Wasp CB3, CB4, CB16, CB17 or Military R-2800-83AM7 (See NOTE 8 and 12) Fuel 100/130 grade aviation gasoline (CB3 and CB16) 108/135 grade aviation gasoline (CB4, CB17 and R-2800-83AM7) Engine Limits HP. R.P.M. M.P. In. Hg. Alt. P&W Double Wasp CB3 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' *(See NOTE 3 for limitations) Takeoff (two minutes) (wet) 2400 2800 59.5 S.L. Takeoff (two minutes) (wet) 2400 2800 59.0 5000' (See Item 103(a) for ADI installation and Engine Specification E-264 for ADI fluid composition) Maximum continuous 1800 2600 48.5 S.L. Maximum continuous 1800 2600 46.5 9200' (Straight line manifold pressure variation with altitude shown) P&W Double Wasp CB16 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' *(See NOTE 3 for limitations) 6A6 Page 2 of 24 Engine Limits (Cont'd) HP. R.P.M. M.P. In. Hg. Alt. P&W Double Wasp CB16 (Cont'd) Takeoff (two minutes) (wet) 2400 2800 59.5 S.L. Takeoff (two minutes) (wet) 2400 2800 59.0 5000' (See Item 103(a) for ADI installation and Engine Specification E-264 for ADI fluid composition) Maximum continuous 1800 2600 48.5 S.L. Maximum continuous 1800 2600 46.5 9200' High impeller gear ratio 8.58:1 Maximum continuous 1700 2600 48.5 10,000' Maximum continuous 1700 2600 47.5 16,800' (Straight line manifold pressure variation with altitude shown) P&W Double Wasp CB4 Takeoff (two minutes) (dry) 2200 2800* 60.0 S.L. Takeoff (two minutes) (dry) 2200 2800* 59.0 5200' *(See NOTE 3 for limitations) Takeoff (two minutes) (wet) 2500 2800 62.0 S.L. Takeoff (two minutes) (wet) 2500 2800 61.5 3700' (See Item 103(a) for ADI installation and Engine Specification E-264 for ADI fluid composition) Maximum continuous 1900 2600 51.5 S.L. Maximum continuous 1900 2600 50.0 7100' (Straight line manifold pressure variation with altitude shown) P&W Double Wasp CB17 and Military R-2800-83AM7 Low impeller gear ratio 7.29:1 Takeoff (two minutes) (dry) 2200 2800* 60.0 S.L. Takeoff (two minutes) (dry) 2200 2800* 59.0 5200' *(See NOTE 3 for limitations) Takeoff (two minutes) (wet) 2500 2800 62.0 S.L. Takeoff (two minutes) (wet) 2500 2800 61.5 3700' (See Item 103(a) for ADI installation and Engine Specification E-264 for ADI fluid composition) Maximum continuous 1900 2600 51.5 S.L. Maximum continuous 1900 2600 50.0 7100' High impeller gear ratio 8.58:1 Maximum continuous 1750 2600 51.5 10,000' Maximum continuous 1750 2600 49.5 15,000' (Straight line manifold pressure variation with altitude shown) Airspeed Limits V NO (Normal Operating) 260 knots True Ind. S.L. to 10,000' VNE (Never Exceed) 293 knots True Ind. S.L. to 10,000' (Above altitudes shown, reduce speed 6 knots per 1000') VA (Maneuvering) 154 knots True Ind. VFE (Flaps Down 0° to 20°) 174 knots True Ind. VFE (Flaps Down 20° to 30°) 156 knots True Ind. 6A6, Rev. 11 Page 3 of 24 Airspeed Limits (Cont'd) V FE (Flaps Down 30° to 40°) 148 knots True Ind. VLE (Landing Gear Extended) 174 knots True Ind. VLO (Landing Gear Operation) (Retraction) 130 knots True Ind. VLO (Landing Gear Operation) (Extension) 174 knots True Ind. C.G. Range See NOTE 1(b) for retraction moment. Forward Aft Gross Weight (lbs.) Landing Gear Position % MAC Sta. % MAC Sta. 39,500 and Below Down (Takeoff & Landing) 13.0 365.8 34.0 389.8 43,000 Down (Takeoff & Landing) 17.0 370.4 34.0 389.8 47,000 Down (Takeoff) 19.0 372.7 34.0 389.8 39,500 and Below Up (Enroute Operation) 8.5 360.6 35.0 390.9 43,000 Up (Enroute Operation) 12.5 365.7 35.0 390.9 47,000 Up (Enroute Operation) 14.9 368.2 35.0 390.9 (Straight line variation between above listed values) Maximum Weight Takeoff 47,000 lbs. (Model 340 airplanes which have the requirements of Service Bulletin 340-144B incorporated which are being operated at the Model 440 weights and performance limitations as contained in the Model 440 FAA Approved Airplane Flight Manual may be operated at increased Maximum Takeoff Weights. See NOTE 7.) Landing 46,500 lbs. Zero Fuel 45,000 lbs. (All weight in airplane above this value must consist of fuel, oil and ADI fluid in the wing) Minimum Crew 2 - Pilot and Copilot (Sta. 84) Maximum Passengers 44 (CAR 4b.362) (Also refer to FAR §91.607) Maximum Baggage Compartment Capacity Max. Floor Loading Arm Fwd. Luggage LH (Sta. 176-243) 200 lbs. 300 lbs. 300 lbs. 25#/ft2 (Shelf 3) 25#/ft2 (Shelf 2) 100#/ft2 (Floor) (210.5) Fwd. Baggage RH (Sta. 131-243) 1800 lbs. 150#/ft 2 (187.0) Belly Compt. (Sta. 193-319) 1000 lbs. 65#/ft 2 (250.0) Aft Baggage (Sta. 730-798) 1800 lbs. 150#/ft 2 (765.0) Fuel Capacity 1730 U.S. gal. (One 865 U.S. gal. tank in each wing) (Sta. 397) (See NOTE 1(d) for "Unmeasurable fuel.") Oil Capacity 30 U.S. gal. in each nacelle (Sta. 339) Serial Numbers Eligible 2 through 311 Required Equipment In addition to the pertinent required basic equipment specified in CAR 4b, the following items of equipment must be installed: 1; 3; 4; 100; 103; 105; 109; 112; 113(a); 114; 200; 201 except (c); 202; 204; 205; 206; 300; 310; 401; 429; 601 6A6 Page 4 of 24 II - Model 340-30 (Original Model 340 prototype modified) Engines 2 P&W Double Wasp CB16 or CB17 Fuel 100/130 grade aviation gasoline (CB16); 108/135 grade aviation gasoline (CB17) Engine Limits HP. R.P.M. M.P. In. Hg. Alt. P&W Double Wasp CB16 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' *(See NOTE 3 for limitations) Takeoff (two minutes) (wet) 2400 2800 59.5 S.L. Takeoff (two minutes) (wet) 2400 2800 59.0 5000' (See Item 103(a) for ADI installation and Engine Specification E-264 for ADI fluid composition) Maximum continuous 1800 2600 48.5 S.L. Maximum continuous 1800 2600 46.5 9200' High impeller gear ratio 8.58:1 Maximum continuous 1700 2600 48.5 10,000' Maximum continuous 1700 2600 47.5 16,800' (Straight line manifold pressure variation with altitude shown) P&W Double Wasp CB17 Low impeller gear ratio 7.29:1 Takeoff (two minutes) (dry) 2200 2800* 60.0 S.L. Takeoff (two minutes) (dry) 2200 2800* 59.0 5200' *(See NOTE 3 for limitations) Takeoff (two minutes) (wet) 2500 2800 62.0 S.L. Takeoff (two minutes) (wet) 2500 2800 61.5 3700' (See Item 103(a) for ADI installation and Engine Specification E-264 for ADI fluid composition) Maximum continuous 1900 2600 51.5 S.L. Maximum continuous 1900 2600 50.0 7100' High impeller gear ratio 8.58:1 Maximum continuous 1700 2600 51.5 10,000' Maximum continuous 1700 2600 49.5 15,000' (Straight line manifold pressure variation with altitude shown) Airspeed Limits V NO (Normal Operating) 234 knots True Ind. S.L. to 16,500' VNE (Never Exceed) 266 knots True Ind. S.L. to 16,500' (Above altitudes shown, reduce speed 6 knots per 1000') VA (Maneuvering) 154 knots True Ind. VFE (Flaps Down 0° to 20°) 174 knots True Ind. VFE (Flaps Down 20° to 30°) 156 knots True Ind. VFE (Flaps Down 30° to 40°) 148 knots True Ind. 6A6, Rev. 11 Page 5 of 24 Airspeed Limits (Cont'd) V LE (Landing Gear Extended) 174 knots True Ind. VLO (Landing Gear Operation) (Retraction) 130 knots True Ind. VLO (Landing Gear Operation) (Extension) 174 knots True Ind. C.G. Range See NOTE 1(b) for retraction moment. Forward Aft Gross Weight (lbs.) Landing Gear Position % MAC Sta. % MAC Sta. 31,000 to 39,500 Down (Takeoff & Landing) 13.0 365.8 34.0 389.8 43,000 Down (Takeoff & Landing) 17.0 370.4 34.0 389.8 46,725 Down (Takeoff) 18.8 372.4 34.0 389.8 31,000 to 39,500 Up (Enroute Operation) 8.5 360.6 35.0 390.9 43,000 Up (Enroute Operation) 12.5 365.7 35.0 390.9 46,725 Up (Enroute Operation) 15.0 368.0 35.0 390.9 (Straight line variation between above listed values) Maximum Weight Takeoff 46,725 lbs. Landing 44,500 lbs. Zero Fuel 43,000 lbs. (All weight in airplane above this value must consist of fuel, oil and ADI fluid in the wing) Minimum Crew 2 - Pilot and Copilot (Sta. 84) Maximum Passengers 22 (CAR 4b.362) Fuel Capacity 1730 U.S. gal. (One 865 U.S. gal. tank in each wing) (Sta. 397) (See NOTE 1(d) for "Unmeasurable fuel.") Oil Capacity 30 U.S. gal. in each nacelle (Sta. 339) Serial Numbers Eligible CVAC No. 1 only Required Equipment In addition to the pertinent required basic equipment specified in CAR 4b, the following items of equipment must be installed: 1(a); 3(a); 4; 100(a) or (b); 103; 109; 112; 113(a); 114; 200; 201(a) or (c); 202; 204; 205; 206; 300; 401; 429; 601 III - Model 440 Approved January 30, 1956 The Military Model C-131E is actually a Model 440. See NOTE 5 for required changes to Military Model C-131E aircraft prior to operation under this section. The Model 440 airplane is basically similar for all dash numbers, the only differences being in the type of equipment and interiors for the customer's airplane. Engines 2 P&W Double Wasp CB3, CB4, CB16, CB17 or Military R-2800-103W (See NOTE 8 and 12) Fuel 100/130 grade aviation gasoline (CB3, CB16 and R-2800-103W at CB16 ratings) 108/135 grade aviation gasoline (CB4, CB17 and R-2800-103W at CB17 ratings) 6A6 Page 6 of 24 Engine Limits HP. R.P.M. M.P. In. Hg. Alt. P&W Double Wasp CB3 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' *(See NOTE 3 for limitations) Takeoff (two minutes) (wet) 2400 2800 59.5 S.L. Takeoff (two minutes) (wet) 2400 2800 59.0 5000' (See Item 103(a) for ADI installation and Engine Specification E-264 for ADI fluid composition) Maximum continuous 1800 2600 48.5 S.L. Maximum continuous 1800 2600 46.5 9200' (Straight line manifold pressure variation with altitude shown) P&W Double Wasp CB16 and Military R-2800-103W 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' *(See NOTE 3 for limitations) Takeoff (two minutes) (wet) 2400 2800 59.5 S.L. Takeoff (two minutes) (wet) 2400 2800 59.0 5000' (See Item 103(a) for ADI installation and Engine Specification E-264 for ADI fluid composition) Maximum continuous 1800 2600 48.5 S.L. Maximum continuous 1800 2600 46.5 9200' High impeller gear ratio 8.58:1 Maximum continuous 1700 2600 48.5 10,000' Maximum continuous 1700 2600 47.5 16,800' (Straight line manifold pressure variation with altitude shown) P&W Double Wasp CB4 Takeoff (two minutes) (dry) 2200 2800* 60.0 S.L. Takeoff (two minutes) (dry) 2200 2800* 59.0 5200' *(See NOTE 3 for limitations) Takeoff (two minutes) (wet) 2500 2800 62.0 S.L. Takeoff (two minutes) (wet) 2500 2800 61.5 3700' (See Item 103(a) for ADI installation and Engine Specification E-264 for ADI fluid composition) Maximum continuous 1900 2600 51.5 S.L. Maximum continuous 1900 2600 50.0 7100' (Straight line manifold pressure variation with altitude shown) 6A6, Rev. 11 Page 7 of 24 Engine Limits (Cont'd) HP. R.P.M. M.P. In. Hg. Alt. P&W Double Wasp CB17 and Military R-2800-103W Low impeller gear ratio 7.29:1 Takeoff (two minutes) (dry) 2200 2800* 60.0 S.L. Takeoff (two minutes) (dry) 2200 2800* 59.0 5200' *(See NOTE 3 for limitations) Takeoff (two minutes) (wet) 2500 2800 62.0 S.L. Takeoff (two minutes) (wet) 2500 2800 61.5 3700' (See Item 103(a) for ADI installation and Engine Specification E-264 for ADI fluid composition) Maximum continuous 1900 2600 51.5 S.L. Maximum continuous 1900 2600 50.0 7100' High impeller gear ratio 8.58:1 Maximum continuous 1750 2600 51.5 10,000' Maximum continuous 1750 2600 49.5 15,000' (Straight line manifold pressure variation with altitude shown) Airspeed Limits V NO (Normal Operating) 260 knots True Ind. S.L. to 13,000' VNE (Never Exceed) 293 knots True Ind. S.L. to 13,000' (Above altitudes shown, reduce speed 6 knots per 1000') VA (Maneuvering) 155 knots True Ind. VFE (Flaps Down 0° to 20°) 174 knots True Ind. VFE (Flaps Down 20° to 30°) 156 knots True Ind. VFE (Flaps Down 30° to 40°) 148 knots True Ind. VLE (Landing Gear Extended) 174 knots True Ind. VLO (Landing Gear Operation) (Retraction) 130 knots True Ind. VLO (Landing Gear Operation) (Extension) 174 knots True Ind. C.G. Range See NOTE 1(b) for retraction moment. Forward Aft Gross Weight (lbs.) Landing Gear Position % MAC Sta. % MAC Sta. 39,500 and Below Down (Takeoff & Landing) 13.0 365.8 34.0 389.8 43,000 Down (Takeoff & Landing) 17.0 370.4 34.0 389.8 48,000 Down (Takeoff) 19.6 373.3 34.0 389.8 49,100 Down (Takeoff) 20.1 373.9 34.0 389.8 49,700 Down (Takeoff) 20.4 374.2 34.0 389.8 39,500 and Below Up (Enroute Operation) 8.5 360.6 35.0 390.9 43,000 Up (Enroute Operation) 12.5 365.7 35.0 390.9 48,000 Up (Enroute Operation) 15.6 368.7 35.0 390.9 49,100 Up (Enroute Operation) 16.2 369.4 35.0 390.9 49,700 Up (Enroute Operation) 16.5 369.7 35.0 390.9 (Straight line variation between above listed values) 6A6 Page 8 of 24 Maximum Weight Takeoff 49,700 lbs. (CB17) (Model 440 airplanes which are being operated per the Supplementary Performance Information contained in Appendix "A" of the Model 440 FAA Approved Airplane Flight Manual and are listed therein.) 49,100 lbs. CB4/CB17 48,000 lbs. CB3/CB16 Landing 47,650 lbs. Zero Fuel 47,000 lbs. 45,000 lbs. - C-131E and R4Y-1/-2 (All weight in airplane above this value must consist of fuel, oil and ADI fluid in the wing) Minimum Crew 2 - Pilot and Copilot (Sta. 84) Maximum Passengers 52 (CAR 4b.362) (Also refer to FAR §91.607) Cargo aircraft, none (for eligibility of Model 440 cargo aircraft as passenger carriers, see NOTE 5, Part 2, for required changes). Maximum Baggage Compartment Capacity Max. Floor Loading Arm Fwd. Luggage LH (Sta. 176-243) (44 Passenger Version Only) (52 Passenger Version Only) 200 lbs. 300 lbs. 300 lbs. N/A 25#/ft2 (Shelf 3) 25#/ft2 (Shelf 2) 100#/ft2 (Floor) N/A (210.5) N/A Fwd. Baggage RH (Sta. 131-243) (44 Passenger Version Only) 1800 lbs. 150#/ft 2 (187.0) Coat Rack Area RH (Sta. 131-179) No Floor or Side Wall Tie Downs (52 Passenger Version Only) 30 Coats Per Rod 210# Per Coat Rod (155.0) Belly Compt. (Sta. 193-319) 1000 lbs. 65#/ft 2 (250.0) Aft Baggage (Sta. 730-798) 1800 lbs. 150#/ft 2 (765.0) Fuel Capacity 1730 U.S. gal. (One 865 U.S. gal. tank in each wing) (Sta. 397) (See NOTE 1(d) for "Unmeasurable fuel.") Oil Capacity 30 U.S. gal. in each nacelle (Sta. 339) Serial Numbers Eligible 312 through 510 (including 327A) Required Equipment In addition to the pertinent required basic equipment specified in CAR 4b, the following items of equipment must be installed: 1; 3; 4; 100; 103; 105; 109; 112; 113(b); 114; 200; 201 except (a), (b) and (c); 202; 204; 205; 206; 300; 310; 405; 429; 601 Specifications Pertinent to All Models Datum Station 0 (Fuselage Nose) MAC 114.3 in. L.E. MAC (Sta. 350.90) Leveling Means Longitudinal leveling lugs inside nose wheel well LH side (Sta. 29.75 and Sta. 48.85). Lateral leveling lugs inside nose wheel well on forward bulkhead (Sta. 9). Control Surface Movements Aileron (angular measurements from streamline) 21½° +2°/-0° Up 21° +2°/-0° Down (Rig 3° ±1° down from streamline) 6A6, Rev. 11 Page 9 of 24 Control Surface Movements (Cont'd) Aileron Trim Tab (angular from tab position when ailerons drooped 3° ±0°) 7° ±½° Up 7° ±½° Down (tabs rigged 2½° ±1° Up from streamline when ailerons drooped 3° ±0°) Aileron Tab Servo Action (angular from streamline) Tab Indicator Setting Tab Position Aileron Position 0° 2½° ±1° Up 3° ±0° Droop 0° 17½° ±2° Down 21½° Up 0° 17° ±2° Up 21° Down NOTE: Settings are measured from a relative position when wing, aileron and tab are streamline. Rudder (angular dimension from stabilizer chord line) 18½° +1°/-0° Right 15° +0°/-1° Left Rudder Flight Tab (angular dimension from stabilizer chord line) 2° Left Rudder Flight Tab Servo Action (angular dimension from stabilizer chord line) Full Right Rudder Pedal 15° ±½° Left Full Left Rudder Pedal 11° ±½° Right NOTE: Rudder chord line and stabilizer chord line coincide at rudder neutral position. Rudder Trim Tab Setting (angular dimension from stabilizer chord line) Tab Control Setting Tab Setting Full Right (clockwise) 9° ±1° Left Full Left (counterclockwise) 9° ±1° Right NOTE: Check deflections with rudder held neutral Rudder Trim Tab Servo Action (angular dimension from rudder chord line) 0° ±2° Left 0° ±2° Right Servo action is negligible. It is measured with rudder at full deflection. NOTE: Rudder chord line and stabilizer chord line coincide at rudder neutral position. Elevator (angular dimension from elevator streamline position 24½° +1°/-0° Up 9½° +1°/-0° Down Elevator Trim Tab (RH) (angular dimension with tab rigged at streamline with elevator and with elevator streamline to stabilizer) 7½° ±½° Up 11½° ±½° Down Elevator Trim Tab (RH) Servo Action (angular dimension from elevator chord line) Tab Position Elevator Position 6¼° ±½° Down 24½° ±0° Up 1° ±½° Down 9½° ±0° Down 6A6 Page 10 of 24 Control Surface Movements (Cont'd) Elevator Servo Tab (LH) (angular dimension from elevator chord line) Tab Position Elevator Position 0° ±0° (at streamline with elevator) 5° Down 12° ±½° Down 24½° ±0° Up ½° ±½° Down 9½° ±0° Down Certification Basis Type Certificate No. 6A6 (Transport Category, CAR 4b, effective July 20, 1950, and Amendment #1, #3, and #5, except smoke detectors not installed in cargo compartments.) Production Basis None at this time. General Dynamics, Convair Division, produced Model 340/440 aircraft, serial numbers 2 through 510, 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 340/440. The Tracor PC was surrendered in 1998 when the TC was endorsed to Kelowna Flightcraft, Kelowna, BC, Canada Equipment Approval for the installation of all items of equipment listed herein has been obtained by the aircraft manufacturer except those items preceded by an asterisk (*). The asterisk denotes that approval has been obtained by someone other than the aircraft manufacturer. An item marked with an asterisk may not have been manufactured under a FAA monitored or approved quality control system. Conformity must be determined if the item is not identified by a Form ACA-186, PMA or other evidence of FAA production approval. Propellers and Propeller Weight Arm Accessories (Except 1. Propellers - Model 340 (Including Original C-131D) Anti-Icing Equipment) (a) 2 Ham. Std. 43E60 Propellers 43E60-9 Hubs, 6895A-8 Blades with de-icing equipment. (Same as 43E60-301 propeller.) 1093 lbs. (227) (b) 2 Ham. Std. 43E60-301 Propellers 6895B-8 Blades with de-icing equipment. (Alternate - Ham. Std. 43E60-325 or 43E60-333 Propeller.) 1150 lbs. (227) (c) 2 Ham. Std. 43E60-319 Propellers 6895D-8 Blades with de-icing equipment. 1150 lbs. (227) (d) 2 Ham. Std. 43E60-325 Propellers 6895E-8 Blades with de-icing equipment. (Including original C-131D installation – Model 340 types). (Alternate - Ham. Std. 43E60-385 Propeller.) 1150 lbs. 1153 lbs. (227) (227) (e) 2 Ham. Std. 43E60-333 Propellers 6895G-8 Blades with de-icing equipment. (Alternate - Ham. Std. 43E60-387 Propeller.) 1150 lbs. 1150 lbs. (227) (227) 6A6, Rev. 11 Page 11 of 24 Propellers and Propeller Accessories (Except Anti-Icing Equipment) (Cont’d) Model 340 aircraft were not originally equipped for propeller reverse indication. Hamilton Standard developed one method of complying with the requirements of CAR Amendment 40-9 by directly aiding operators and by providing the following drawings to modify the propeller system to incorporate reverse indicating lights: SK-33116, SK-33008, SK-29660, SK-32994, SK-29316, SK- 32758, HS-501733 and HS-86415. 2. Propellers - Model 440 (Including Original C-131D) (f) 2 Ham. Std. 43E60-377 Propellers 6895E-8 Blades with de-icing equipment. (Including original C-131D installation - Model 440 types). (Has provisions for propeller reverse indication.) 1152 lbs. (227) (g) 2 Ham. Std. 43E60-435 Propellers 6895E-8 Blades with de-icing equipment. (Has provisions for propeller reverse indication and feather latch.) 1152 lbs. (227) (h) 2 Ham. Std. 43E60-469 Propellers 6895E-8 Blades with de-icing equipment. (Has provisions for propeller reverse indication, feather latch, low-pressure barrel and sensitive low pitch stop per Ham. Std. Bulletin No. 472.) 1159 lbs. (227) Propellers - Military Versions (i) 2 Ham. Std. 43E60-341 Propellers 6895B-8 Blades with de-icing equipment. (C-131B (Model 340-70), C-131F/R4Y-1 (Model 340-71) and C-131E (Model 440-72) only.) 1152 lbs. (227) (j) 2 Ham. Std. 43E60-501 Propellers 6895B-8 Blades with de-icing equipment. (C-131F/R4Y-1 (Model 340-71) only per US Navy Aircraft Service Change (ASC) No. 5. Has provisions for propeller reverse indications.) 1152 lbs. (227) (k) 2 Ham. Std. 43E60-523 Propellers 6895B-8 Blades with de-icing equipment. (C-131E (Model 440-72) only. Has provisions for propeller reverse indications.) 1152 lbs. (227) (l) 2 Ham. Std. 43E60-539 Propellers 6895M-8 Blades with de-icing equipment. (C-131B (Model 340-70), C-131D and C-131E (Model 440-72) only per USAF T.O. 3-1-1.) 1158 lbs. (227) (m) 2 Ham. Std. 43E60-565 Propellers 6895N-8 Blades with de-icing equipment. (C-131B (Model 340-70), C-131D and C-131E (Model 440-72) only per USAF T.O. 3-1-1.) 1158 lbs. (227) Applicable to all propellers: Diameter: Max. 13' 5-5/16" Min. allowable for repairs 13' 1-9/16" Pitch settings at 42" Sta.: Reverse -8°, minimum low 30°, feathered 96° (approx.) 6A6 Page 12 of 24 Propellers and Propeller Accessories (Except Anti-Icing Equipment) (Cont’d) 3. Propeller Governors - Model 340 (Including Original C-131D) (a) 2 Ham. Std. 5U18-1 Constant Speed Control (Including original C-131D installation - Model 340 types) 26 lbs. (236) (b) 2 Ham. Std. 5U18-18 Constant Speed Control 27 lbs. (236) (c) 2 Ham. Std. 5U18-35 Constant Speed Control 28 lbs. (236) Weight Arm Propeller Governors - Model 440 (Including Original C-131D) (d) 2 Ham. Std. 5U18-62 Constant Speed Control (Including original C-131D installation - Model 440 types) 28 lbs. (236) (e) 2 Ham. Std. 5U18-94 Constant Speed Control 28 lbs. (236) (f) 2 Ham. Std. 5U18-115 Constant Speed Control 28 lbs. (236) Propeller Governors - Military Versions (g) 2 Ham. Std. 5U18-28 Constant Speed Control (C-131B, C-131E and C-131F/R4Y-1 only.) 28 lbs. (236) (h) 2 Ham. Std. 5U18-47 Constant Speed Control (C-131B, C-131D and C-131E only per USAF T.O. 3-1-1.) 28 lbs. (236) 4. 2 Propeller Feathering Pumps, Pesco 1E-777-BL-1 (Ham. Std. Dwg. No. 66166-6) 28 lbs. (346) Engine and Engine Accessories - Fuel and Oil Systems 100. Engines (See NOTE 8 and 12) (a) 2 P&W Double Wasp CB16 4800 lbs. (267) (b) 2 P&W Double Wasp CB17 4800 lbs. (267) (c) 2 P&W Military R-2800-103W 4800 lbs. (267) (d) 2 P&W Double Wasp CB3 4734 lbs. (267) (e) 2 P&W Double Wasp CB4 4734 lbs. (267) (f) 2 P&W Military R-2800-83AM7 4800 lbs. (267)