TCDS A-812

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 Rev No. 27 - - - - - - - - - - - - 27 27 27 27 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-812 Revision 27 Aero Spacelines, Inc. (Boeing) 377 377SGT, 377MG September 1, 1973 AIRCRAFT SPECIFICATION NO. A-812 Type Certificate Holder Aero Spacelines, Incorporated P. O. Drawer B Santa Barbara Airport Santa Barbara, California 93102 I - MODEL 377 (TRANSPORT CATEGORY) APPROVED 3 SEPTEMBER 1948 Engines 4 P&W Wasp Major TSB3-G with two 3-1/2N dampers. Propeller gear ratio .375:1 (See Item 101 for optional engines) Fuel Aviation gasoline: Minimum grade 108/135 or 100/130 (See NOTE 8 for more information on fuel grades) Engine limits See NOTE 4 for more information on limits M.P. Impeller Gear Ratio 6.375:1 HP RPM IN.HG. ALT. (a) Fuel Grade 108/135 or 115/145 (SEE NOTE 8) Take-off, Wet (Two minutes) 3500 9500 60.0 S.L. See NOTE 6 for Water Injection Mixture Take-off, Dry (Two minutes) 3250 2700 60.0 S.L. Maximum continuous 2800 2550 53.5 S.L. Maximum continuous 2800 2550 53.5 1200' (b) Fuel Grade 100/130 (See NOTE 8) Take-off, Wet (Two minutes) 3250 2700 56.5 S.L. See NOTE 6 for Water Injection Mixture Take-off, Dry (Two minutes) 3000 2700 56.0 S.L. Maximum continuous 2650 2500 50.5 S.L. Maximum continuous 2650 2550 50.0 2800' Airspeed limits Vno (Normal operating) 312 MPH (271 Knots) True Ind. (Above 13,600' reduce speed 6 MPH for each additional 1,000') Vne (Never exceed) 351 MPH (305 Knots) True Ind. (Above 13,500' reduce speed 6 MPH for each additional 1,000') Vp (Maneuvering) 237 MPH (206 Knots) True Ind. Vf (Flaps Down 25°) 220 MPH (191 Knots) True Ind. Vf (Flaps Down 30°) 200 MPH (175 Knots) True Ind. Vf (Flaps Down 45°) 186 MPH (162 Knots) True Ind. Vlo (Ldg. Gr. Operation) 230 MPH (200 Knots) True Ind. Vle (Ldg. Gr. Extension) 230 MPH (200 Knots) True Ind. Mach. No. - Never exceed .585 A-812 2 C.G. range (Straight line variation should be used between the forward C.G. locations for each condition group.) Weight Landing Fwd. Limit Aft Limit Condition lbs. Gear Station % MAC Station % MAC Using Item 1(a), Curtiss Propellers C644S-B302/1052/20C4-30, the following limits apply: With Wet Power, Using Fuel Grade 108/135 or 115/145 (see Note 8.) Takeoff 142,500 Down 535.7 28.6 541.8 32.6 Takeoff 140,000 Down 518.4 17.4 541.8 32.6 Takeoff 130,000 Down 515.6 15.6 541.8 32.6 Takeoff 121,700 or Down 514.0 14.6 541.8 32.6 less Landing 121,700 or Down 514.0 14.6 541.8 32.6 less Enroute 142,500 Up 534.7 28.0 544.0 34.0 (Flaps up) 139,500 Up 512.8 13.8 544.0 34.0 114,000 or Up 506.9 10.0 544.0 34.0 less With Dry Power, Using Fuel Grade 108/135 or 115/145 (see Note 8.) Takeoff 138,000 Down 535.7 28.6 541.8 32.6 Takeoff 135,000 Down 517.1 16.6 541.8 32.6 Takeoff 130,000 Down 515.6 15.6 541.8 32.6 Takeoff 121,700 or Down 514.0 14.6 541.8 32.6 less Landing 121,700 Down 524.6 21.4 541.8 32.6 120,500 or Down 514.0 14.6 541.8 32.6 less Enroute 138,000 Up 512.5 13.6 544.0 34.0 (Flaps up) 114,000 or Up 506.9 10.0 544.0 34.0 less With Wet Power, Using Fuel Grade 100/130 (see Note 8) Takeoff 137,600 Down 535.7 28.6 541.8 32.6 Takeoff 135,400 Down 517.2 16.6 541.8 32.6 Takeoff 130,000 Down 515.6 15.6 541.8 32.6 Takeoff 121,700 or Down 514.0 14.6 541.8 32.6 less Landing 121,700 Down 524.6 21.4 541.8 32.6 Landing 120,500 or Down 514.0 14.6 541.8 32.6 less Enroute 137,600 Up 534.7 28.0 544.0 34.0 (Flaps up) 135,000 Up 511.9 13.2 544.0 34.0 114,000 or Up 506.9 10.0 544.0 34.0 less With Dry Power, Using Fuel Grade 100/130 (see Note 8) Takeoff 131,700 Down 535.7 28.6 541.8 32.6 Takeoff 129,000 Down 515.3 15.4 541.8 32.6 Takeoff 121,700 or Down 514.0 14.6 541.8 32.6 less Landing 117,300 Down 535.7 28.6 541.8 32.6 Landing 115,000 or Down 514.0 14.6 541.8 32.6 less Enroute 131,800 Up 511.1 12.7 544.0 34.0 (Flaps up) 114,000 or Up 506.9 10.0 544.0 34.0 less 3 A-812 Using Item (1)b, Ham. Std. Propellers 24260/2J17B3-8W and operating in accordance with PAWA 377-10-26 Airplane Flight Manual D-9405, or BOAC 377-10-32 Airplane Manual D-8529, the following limits apply: Takeoff 145,800 Down 535.7 28.6 541.8 32.6 Takeoff 144,000 Down 519.5 18.1 541.8 32,6 Takeoff 130,000 Down 515.6 15.6 541.8 32.6 Takeoff 121,700 or Down 514.0 14.6 541.8 32.6 less Using Item (1)b, Ham. Std. Propellers 24260/2J17B3-8W and operating in accordance with PAWA 377-10-26 Airplane Flight Manual D-9405, or BOAC 377-10-32 Airplane Manual D-8529, the following limits apply: Landing 121,700 or Down 514.0 14.6 541.8 32.6 less Enroute 145,800 Up 534.7 28.0 544.0 34.0 (Flaps up) 143,500 Up 513.7 14.4 544.0 34.0 114,000 or Up 506.9 10.0 544.0 34.0 With Dry Power, Using Fuel Grade 108/135 or 115/145 (see Note 8) Takeoff 140,600 Down 535.7 28.6 541.8 32.6 Takeoff 138,000 Down 518.0 17.2 541.8 32.6 Takeoff 130,000 Down 515.6 15.6 541.8 32.6 Takeoff 121,700 or Down 514.0 14.6 541.8 32.6 less Landing 121,700 Down 520.8 18.9 541.8 32.6 Landing 120,950 or Down 514.0 14.6 541.8 32.6 less Enroute 140,600 Up 534.7 28.0 544.0 34.0 (Flaps up) 137,500 Up 512.5 13.6 544.0 34.0 114,000 or Up 506.9 10.0 544.0 34.0 less For C.G. limits applying to operation with the automatic feathering system inoperative, refer to the appropriate Airplane Flight Manual. Maximum weight (a) The following sea level maximum weights are permitted when 45° landing, 30° approach, 25° take-off, and 0° enroute flap settings are used and the automatic propeller feathering system is operative. Refer to the appropriate Airplane Flight Manual for maximum permissible weights at various altitudes. See NOTE 8 for limitations covering the mixed or interchangeable use of fuel grades. Landing: (Weight or dry power with 115/145 or 108/135 grade fuel and wet power only with 100/130 grade fuel) 121,700 lbs. (Dry power with 100/130 grade fuel) 117,300 lbs. Take-off: (Dump valves required. See NOTE 3) (Wet power with 115/145 or 108/135 grade fuel) 142,500 lbs. (Wet power with 100/130 grade fuel) 137,600 lbs. (Dry power with 115/145 or 108/135 grade fuel) 138,000 lbs. (Dry power with 100/130 grade fuel) 131,700 lbs. Using Item (1)b, Ham. Std. Propellers 24260/2J17B3-8W & operating in accordance with PAWA 377-10-26 Airplane Flight Manual D-9405, or BOAC 377-10-32 Airplane Flight Manual D-8629 the following limits apply: (Wet power with 115/145 or 108/135 grade fuel) 145,800 lbs. (Dry power with 115/145 or 108/135 grade fuel) 140,600 lbs. (b) Dry Wing Gross Weight (See NOTE 5 regarding 113,900 lbs. required fuel load distribution) (c) For 3-engine ferrying, see NOTE 9 (d) For maximum weights permitted for operation with the automatic propeller feathering System inoperative, refer to the appropriate Airplane Flight Manual. A-812 4 Minimum crew 3 - Pilot and copilot (108.5) and Flight Engineer (148.0) (Additions to be above minimums may be specified by the CAA Air Carrier Safety Division for the long range flights and/or other special conditions.) Maximum passengers 89 (4b.3812) Maximum baggage and MAX. FLOOR cargo COMPARTMENT WEIGHT LOADING PSF ARM Fwd. 12,000 lbs. 100 357.0 Aft 5,000 lbs. 100* 884.0 *Maximum floor loading aft of station 934 is 80 PSF. Fuel capacity See NOTE 1B regarding unusable fuel. (Usable) #1 and #4 Main Tanks (See NOTE 13) 1770 gal. ea. (547.5) (Composed of 12 cells ea.) #2 and #3 Main Tanks 1520 gals. ea. (536.0) (Composed of 4 cells ea.) #5 Alternate Tank 1210 gals. (534.5) (3 cells in fuselage center wing) Oil capacity See NOTE 1C regarding "System Oil". Hamilton Standard propeller installation: 33-1/2 gals. in each nacelle (476.0) & (494.0) Curtiss propeller installation: 35 gals. in each nacelle (476.0) & (494.0) 56 gals. central oil tank (fuselage) (208.0) Serial Nos. eligible 15922 and up MAC 154.4 in. (L. E. of MAC is 491.5) Leveling means Indicator Below Floor in fwd. Baggage compartment (STA. 386) Required equipment In addition to the pertinent required basic equipment specified in CAR 4b, the following items of equipment must be installed: 1(a) or 1(b), 5(a), 7(a) & 8(a), 101(a), 103(a), 103(b) or 103(c), 201, 202, 203, 205, 206, 207, 302, 311, 401, 403, 409(a) or (b), 410 & 447. II - MODEL 377MG (TRANSPORT CATEGORY) APPROVED 14 MARCH 1969 Engines 4 P&W Wasp Major TSB3-G with two 3-1/2N dampers. Propeller gear ratio .375:1. Fuel Aviation gasoline: Minimum grade 108/135 Engine limits See NOTE 4 for more information on limits M.P. Impeller Gear Ratio 6.375:1 HP RPM IN.HG. ALT. (a) Fuel Grade 108/135 or 115/145 (SEE NOTE 8) Take-off, wet (Two minutes) 3500 2700 60.0 S.L. See NOTE 6 for Water Injection Mixture Takeoff, Dry (Two minutes) 3250 2700 60.0 S.L. Maximum Continuous 2800 2550 53.5 S.L. Maximum Continuous 2800 2550 53.5 1200' 5 A-812 Propeller and 1. 4 Hamilton Standard Model No. 34E60/7015-2 (-349) propeller limits Four bladed propellers installed in accordance with Supplemental Type Certificate No. SA-4-175 Diameter - 16' Pitch Settings at 72 inch Station Minimum Low 19.5° Feathered 82° Reverse minus 21° Restrictions: Avoid continuous ground operation between 1300 and 1700 RPM. Avoid continuous flight operation between 1400 and 1700 RPM. Avoid ground operation above 2200 RPM except during the takeoff roll. 5. (a) 1 Synchronizer Control Box Hamilton 40 lb. (170.0) Standard 320300 7. (a) 4 Feathering pumps - Adel 51300 100 lb. (541.5) 8. (a) Propeller Governors - Hamilton tandard 5018-B23AE or 5018-E23AE 53 lb. (451.0) Airspeed limits Vmo Maximum operating) 231 MPH (201 Knots) True Ind. (Above 16,300' reduce speed 4.8 MPH for each additional 1000') Vp Maneuvering) 207 MPH (180 Knots) True Ind. Vf (Flaps Down 25°) 191 MPH (166 Knots) True Ind. Vf (Flaps Down 30°) 191 MPH (166 Knots) True Ind. Vf (Flaps Down 45°) 191 MPH (166 Knots) True Ind. Vlo (Ldg. Gr. Operation) 230 MPH (200 Knots) True Ind. Vle (Ldg. Gr. Extension) 230 MPH (200 Knots) True Ind. Mmo (Maximum Operating) 0.405 C.G. range Most forward - 20% MAC (Sta. 587.8) Most aft - 30% MAC (Sta. 603.6) NOTE: Range given is applicable to all weights with the landing gear down. Maximum weight Landing 130,000 lbs. Takeoff 142,800 lbs. Max. zero fuel 126,120 lbs. NOTE: Maximum weights noted are based on wet take-off power with 115/145 or 108/135 grade fuel only and with auto-feathering operative. Minimum crew Pilot and copilot (108.5), Flight Engineer (148.0), and Crew Cargo Attendant (1230 ) when cargo is being transported. Maximum passengers None. Approved for cargo only. Fuel capacity See NOTE 1B regarding unusable fuel. (usable) #1 and #4 Main Tanks (See NOTE 13) 1770 gals. ea. (617.5) (Composed of 12 cells ea.) #2 and #3 Main Tanks 1520 gals. ea. (606.0) (Composed of 4 cells ea.) Oil capacity See NOTE 1C regarding "System Oil." (546.0) and (564.) 33-1/2 gals. in each nacelle Maximum operating Altitude 20,000 ft. Serial Number eligible 15937 only MAC 159.2 in. (L.E. of MAC is 555.8 in. aft datum) Leveling means Indicator below floor in fwd. baggage compartment (Sta. 356) A-812 6 Required equipment In addition to the pertinent required basic equipment specified in CAR 4b, the equipment specified in CAR 4b, the equipment specified in Aero Spacelines, Inc. Empty Weight Equipment List, Boeing 377 MG-N1037, dated 30 April 1968, revised 23 January 1970, must be installed and operative. SPECIFICATIONS PERTINENT TO ALL MODELS Datum 50 in. fwd. of nose. (Distance from datum to nose jacking cone 228.6 in.) Control surface movements Main surfaces: Elevator: 20° Up 15° Down Aileron: 25° Up 25° Down Rudder: + or - 22° (Boost on) Rudder: + or - 22° (Boost off) Trim Devices: Right elevator tab: + or - 12° (elevator in neutral) Left elevator tab: Up 3° (when flap travels to full down position) Right & left aileron tabs: From 6° droop, travel is 5-12° up and 5° down (Ailerons in neutral) Rudder tab: + or - 20° Aerodynamic Boost Tabs: Right & left Elevator tabs: 15° down elevator, tab moves up 1-1/4° 20° up elevator, tab moves down 8° Right & left Ailerons Tabs: 25° down aileron, tab moves up 27-1/2° 25° up aileron, tab moves down 27-1/2° Aileron neutral, tab is drooped or down 6° Rudder Tab: 0° (Boost on) Certification basis Type Certificate No. A-812 (Transport Category), CAR, Part 04-0, effective 9 November 1945, and amendments 04-1 through 04b-10; and section 4b.292 of Part 4b, dated 1 October 1949. Production basis "None. Prior to original certification of each aircraft a FAA representative must perform a detailed inspection for workmanship, materials, and conformity with the approved technical data, and a check of the flight characteristics." Export eligibility Eligible for export to all countries subject to the provisions of Advisory Circular AC No. 21-2b. EQUIPMENT Propellers and Propeller Accessories (Except Anti-icing Equipment 1. (a) 4 Curtiss propellers, Hubs C6445-B302, 3,869 lbs. (352.0) & (370.0) Blades 1052-2004-30 (including electrical anti-icing provisions installed on propeller assembly such as boots, slip rings, blades and hub electrical equipment, etc.) Diameter 16' 8". Pitch settings at 72" sta.: Reverse -20.3°; Min. low +17.3°, high +57.3°, Feathered +84.5°. Placard required: "Above 312 MPH (TIAS) do not operate between 1500 and 2000 rpm." 7 A-812 (b) 4 Hamilton Standard propellers, Hubs 24260, (1) Blades 2J17B3-8W 3,122 lbs. (352) & (370) (2) Blades 2J17F3-8W Use act. wt. change (352) & (370) (3) Blades 2J17H3-8W Use act. wt. change (352) & (370) Limits for (1), (2), & (3): Diameter 16' 4-7/8" Pitch settings at 72" sta: Reverse -18° Min. low + 18°; Feathered + 86° (4) Blades 2J17Z3-8W Use act. wt. change (352) & (370) Diameter: 16' 4-7/8" Pitch settings at 72" sta: Reverse - 18° Min. low + 20.3°; Feathered +86° The 2J17B3, 2J17F3, 2J17H3 blades, and any of these blades modified to SK-31339, can be used interchangeably in the same propeller provided the prefix letters and cut-off dash numbers of the model designations are the same. The 2J17Z3 blades can be used interchangeably in the same propeller with the 2J17B3, 2J17F3, 2J17H3 blades and any of these blades modified to SK-31339, provided the 2J17Z3 blades are used in pairs and installed in opposite propeller arms and that the prefix letters for the opposite blades and the cut-off dash number for all blades are the same. Placards required: "Avoid ground running under static conditions above 2600 rpm" "Avoid continuous ground operation between 1400 and 2000 rpm" "Avoid continuous operation in flight below 1750 rpm except that 1400 rpm may be used for level cruise but not descent" 5. (a) 1 Synchronizer Control Box - Hamilton Standard 320300 40 lbs. (170.0) 7. (a) 4 Feathering pumps - Hamilton Standard 66166-6 54 lbs. (471.5) 8. (a) 4 Propeller governors - Hamilton Standard 5U18-B23AE or 5U18-E23AE 53 lbs. (381.0) Engine and Engine Accessories - Fuel and Oil System 101. Engines (a) 4 P&W Wasp Major TSB3-G with two 3-1/2N dampers 13,588 lbs. (401.0) & (419.0) (b) 4 P&W Wasp Major B-6 or B-7 with two 3-1/2N dampers 14,336 lbs. (401.0) & (419.0) (c) 4 P&W Wasp Major CB-2 14,680 lbs. (401.0) & (419.0) 102. Fuel dump system (Boeing Dwg. 15-12748, 15-22152, 15-23167) See NOTE 3 for more information on dump valves. 52 lbs. (592.5) 103. Unusable fuel and system oil (a) Unusable fuel, see NOTE 1B 444 lbs. (565.0) (b) System oil (with Curtiss propeller installed), see Note 1C. 514 lbs. (433.0) (c) System oil (with Ham. Std. propellers installed), see Note 1C. 563 lbs. (437.0) 111. 4 G.E. Turbo superchargers (a) Model BH-4-A1 821 lbs. (478.0) (b) Model 7S-BH4-C1 900 lbs. (478.0) 115. Water alcohol injection (Boeing Dwg. 15-25409) with water 532 lbs. (563.0) regulator P&W No. 106486. (Including 60 gals. fluid) Landing Gear 201. 4 Main wheel-brake assemblies, 56", Type I (a) Goodrich Model 5604M, Wheel Assembly No. H-3-626-M-1 968 lbs. (558.0) Brake Assembly No. H-2-555-1 (2 per wheel) 293 lbs. (558.0) 202. 4 Main wheel 22-ply rating nylon tires, 56", Type I 1,000 lbs. (558.0) (Rating: 37,500 lbs. at 110 psi) See NOTE 7 re tire inflation pressure. 203. 4 Main wheel tubes, 56", Type I, Style "D" regular 175 lbs. (558.0) (weight includes 9 lbs. of air per tube). A-812 8 205. 2 Nose wheels, 36", Type I (a) Goodrich (Hayes) Model 3650M, Assembly No. H-3-102-M-1 74 lbs. (121.0) 206. 2 Nose wheel 12-ply rating nylon tires, 36", Type I 111 lbs. (121.0) (Rating: 11910 lbs. at 58 psi) See NOTE 7 re tire inflation pressure. 207. 2 Nose wheel tubes, 36", Type I, Style "S" 22 lbs. (121.0) 208. Boeing (Hydro-Aire, Inc.) anti-skid brake per Hydro-Aire Dwg. 111 lbs. (+359.5) 4700-0 and 4700-1 Electrical Equipment 301. 2 Alternators (Westinghouse A14A-9730 or A-19A-6110) 106 lbs. (460.5) 302. Generators (a) 6 General Electric 2CM75C-1A 365 lbs. (448.5) 304. Batteries, 24 volt, 34 amp. hr. (a) (2) at Sta. 131 and (1) at Sta. 149.5 225 lbs. (137.0) (BACo Dwg. No. 15-23051, Shts. 2, 4, 5, 6, 7) (b) (2) at Sta. 131 (BACo Dwg. No. 15-23051, Sht. 3) 150 lbs. (131.0) 311. 2 Landing lights (Grimes G-3800A-5) 13 lbs. (595.0) Interior Equipment 401. Airplane Flight Manual for Boeing Statocruiser (The manual may be carried as part of, or bound with, the operator's "Approved Operations Manual," but must remain in the airplane and must retain its identity as an individual manual). The following table identifies the Airplane Flight Manuals and the revisions thereto currently approved for each model: Boeing Document No. Latest Date of Latest Boeing of Approved Flight Approved Approved Model No. Manual Revision Revision 377-10-26 (PAWA) D-9405 32 6-15-55 377-10-30 (NWA) D-8626 48 11-15-56 377-10-32 (BOAC) D-8629 14 6- 4-53 377-10-34 (UAL) D-8630 22 12-28-53 402. Automatic Pilot (a) Sperry A12 (Servo unit Part Nos. 661634 (3) & 664237 (1).) 140 lbs. (487.0) (1) Maximum servo output (measured at servo) Elevator 80 (+0 -5) lbs. Rudder 100 (+0 -5) lbs. Aileron 160 (+0 -5) lbs. (See BACo Service Bulletin No. 352, Revision A) (2) Deleted 31 May 1957 (b) Pioneer PB-10 (Servo unit Part No. 15601-1A(3).) 150 lbs. (487.0) (1) Stalled servo drum forces (measured at the servo) Elevator 110 (+0 -5) lbs. Rudder 86 (+0 -10) lbs. Aileron 141 (+0 -10) lbs. (See BACo Service Bulletin No. 271, Revision A) (2) Deleted 31 May 1957 403. Instruments (See Appendix I to the Manufacturer's Equipment List) 409. Windshield Wiper Installation (a) Kearfott Engrg. Co. two-wiper system, BACo Dwg.No. 15-23130 6 lbs. ( 56.0) (b) Kearfott Engrg. Co. three-wiper system, BACo Dwg.No. 15-23531 6 lbs. ( 56.0) 410. Escape rope (Control Cab) (2), BACo 9-14385 2 lbs. ( 81.1) 447. Escape rope (Main Cabin) (8), BACo 15-25306 6 lbs. (596.0) 9 A-812 Anti-Icing and De-Icing Equipment 501. 6 Wing heaters Model 944A (Stewart Warner) 244 lbs. (525.0) 502. 2 Empennage heaters No. G477025 (Stewart Warner) 65 lbs. (1122.0) 512. (a) Curtiss Prop. Elec. anti-icing equipment, less 32 lbs. (505.0) equipment on propeller (Boeing Dwg. 12-25476 & 15-22127) (b) Ham. Std. Prop. Elec. anti-icing equipment less 21 lbs. (492.0) equipment on propeller (Boeing Dwg. 12-25476 & 15-22127) 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. After original certification, the effects on weight and balance due to changes in equipment and/or alterations must be suitably accounted for. B. Unusable fuel, which must be included in the airplane empty weight, is that quantity of fuel in system and in the tanks which is unavailable to the engines under critical flight conditions as defined in CAR 04b.4221. This unusable fuel includes "system fuel", which is defined as that amount required to fill the system and tanks up to the tank outlets to the engine where the airplane is in the level attitude. The fuel gages are calibrated using the unusable fuel level as the zero datum. The distribution of the total amount of unusable fuel (Item 103(a).) is as follows: Total "System" Additional Unusable Fuel Fuel Unusable Fuel Tanks No. 1 & 4 52 lbs. ea. 33 lbs. ea. 19 lbs. ea. Tanks No. 2 & 3 84 lbs. ea. 22 lbs. ea. 62 lbs. ea. Center Tank 108 lbs. 15 lbs. 93 lbs. Lines (Total) 64 lbs. 64 lbs. 0 C. "System oil", which must also be included in the airplane empty weight, is that amount of oil required to fill the oil systems and tanks up to the tank outlets to the engines. The propeller feathering oil is not considered usable oil and, when applicable, is included in "system oil." The oil tank capacities shown in this specification include only the usable oil for which the tanks are to be placarded. Dipstick readings indicate the amount of usable oil. D. The airplane must always be loaded within the C.G. limits specified in this specification, accounting for crew and passenger movement and use of fuel, water injection fluid and oil. Retraction of the landing gear changes the balance moment by 89844 inch pounds and moves the C.G. forward. E. For the interior arrangement of a particular airplane, see Section IV of the Airplane Flight Manual. This gives the location of all passenger and crew member seats, location and capacity of lounges and lavatories for each of the different sleeper and day plane arrangements covered by the above report. Cargo compartments must be placarded for the capacities specified in the approved report. Passenger seats and safety belt installations other than originally provided by the manufacturer must be of an approved type or shown to meet the strength requirements of CAR 4b. NOTE 2. The following placards shall be placed on the instrument panel in full view of the pilot: (a) "This airplane shall be operated in compliance with the operating limitations specified in CAA Approved Airplane Flight Manual." (b) On aircraft with Curtiss C644S-B302/1052-20C4-30 propellers installed: "Above 312 MPH (TIAS) do not operate between 1500 and 2000 RPM." (c) On aircraft with Hamilton Standard 24260/2J17B3-8W propellers or with interchangeable blade models as listed in Propeller Specification No. P-870, NOTE 6, installed: "Avoid continuous ground operation between 1500 and 2000 RPM." "Avoid continuous operation in flight below 1750 RPM except 1400 RPM may be used for level cruise but not for descent." A-812 10 NOTE 3. A. Fuel dump valves (Item 102) must be installed for operation of the airplane at weights in excess of maximum landing weight. Refer to CAA Approved Airplane Flight Manual for limitations and cautionary procedures to be observed during the dumping of fuel. B. When dump valves are installed (Item 102), the amount of usable fuel remaining in the fuel tanks after dumping is as follows: Outer Wing (#1 and #4 Main) 220 gals. each Inner Wing (#2 and #3 Main) 270 gals. each Alternate (#5) Not dumpable NOTE 4. The limits for the TSB3-G, B-6 and B-7 engines are based on 100°F, carburetor air inlet temperature and 31 inches Hg. (absolute) exhaust back pressure. To maintain "Maximum Continuous" power under conditions with higher inlet air temperatures and/or power exhaust back pressure, the manifold pressure may be increased up to a maximum of 56 inches Hg. to compensate for the loss of power, provided neither 43 inches Hg. (absolute) back pressure nor 130°F. carburetor air inlet temperature is exceeded. NOTE 5. Structural Limitations on Fuel Loading and Usage: For Model 377 A. The maximum airplane gross weight with dry wing, i.e., with zero nacelle oil, zero anti-detonant fluid, and zero fuel in tanks No. 1, 2, 3, and 4, must never exceed 113,900 lbs. Dry wing gross weight must include the weight of any fuel carried in the center section tank. B. For pay loads, bringing the airplane up to, but not exceeding, a dry wing gross weight of 109,300 lbs., fuel in tanks No. 1 and 4 must be loaded to equal or exceed fuel in tanks No. 2 and 3, respectively, at any take- off weight up to and including maximum. In flight, fuel quantities in tanks No. 1 and 4 must not be reduced to less than those in tanks No. 2 and 3, respectively. C. For pay loads, bringing the airplane to a dry wing gross weight in the range between 109,300 lbs. and 113,900 lbs. (maximum), fuel may be loaded and used equally from all tanks as outlined in (B) above, provided the take-off weight does not exceed 138,500 lbs. For take-off weights from 138,500 lbs. to maximum, fuel in tanks 2 and 3 must not be loaded to exceed 5,150 lbs. (858 gallons) per tank unless tanks No. 1 and 4 are full. In flight, fuel quantities in tanks No. 1 and 4 must not be reduced to less than those in tanks No. 2 and 3, respectively. If there is a differential distribution of fuel at the start of the flight, fuel may be used equally from all four tanks, or the fuel may be used first from the outboard tanks No. 1 and 4