TCDS 1A7

Page No. 1 2 3 4 5 Rev. No. 10 9 9 10 9 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1A7 Revision No. 10 MARTIN 404 June 1, 1978 AIRCRAFT SPECIFICATION NO. 1A7 Type Certificate Holder Martin-Marietta Corporation Baltimore, Maryland 21220 I - Model 404, Approved October 5, 1951 Engines 2 P&W Double Wasp CB3 or CB16 (Item 101(a) or (b)) Fuel Aviation gasoline: Minimum grade 100/130 for all engines Engine limits P&W Double Wasp CB3 (Low Blower only) and CB16: m.p. Alt. h.p. r.p.m. in.-hg. Low impeller gear ratio 7.29:1 (CB3 and CB16) Takeoff (dry) (2 minutes) S.L. 2050 2700* 55.0 Critical altitude 6900 2050 2700* 53.0 *(See NOTE 3 for propeller governor re-setting prior to "dry" takeoff.) Takeoff (antidetonant S.L 2400 2800 59.5 injection) (2 minutes) Critical altitude 5000 2400 2800 59.0 Maximum continuous S.L. 1800 2600 48.5 Maximum continuous 9200 1800 2600 46.5 High impeller gear ratio 8.58:1 (CB16 only) Maximum continuous 10000 1700 2600 48.5 Maximum continuous 16800 1700 2600 47.5 (Straight line manifold pressure variation with altitudes shown.) Airspeed limits Vno (Normal Operation) Variable, see table below (CAS) Vne (Never exceed) Variable, see table below Vp (Maneuvering) 180 m.p.h. (150 knots) Vf (Flaps down 0° to 12 1/2°) 190 m.p.h. (165 knots) Vf (Flaps down 12 1/2° to 45°) 150 m.p.h. (130 knots) Vle (Landing Gear Extended) 190 m.p.h. (165 knots) Vlo (Landing Gear Operation) (Ext.) 190 m.p.h. (165 knots) (Ret.) 180 m.p.h. (156 knots) Max. Wt. (Zero fuel), lb. 41,000 42,500 Vne (Never exceed) m.p.h. 301* 285 Knots 261* 247 Vno (Normal Operating) m.p.h. 265* 247 Knots 230* 214 *Above 20,000 ft. reduce maximum values of Vne and Vno 6 m.p.h. (5.22 knots) per 1000 ft. 1A7 2 C.G. range Condition Max. Weight, lb. Gear Position C.G. Range Takeoff 44,900 Down 440.2 - 461.4 Takeoff & 43,000 Down 439.2 - 461.4 Landing 38,000 & less Down 436.8 - 461.4 Flight All Weight Up 432.6 - 461.4 (Straight line C.G. variation with weights shown) Effect of retracting landing gear -75,121 in.-lb. (Item 203(a)) -72,636 in.-lb. (Item 203(b)) Datum 87 inches forward nose of fuselage Leveling means Longitudinal: Left side, fuselage stations 389.5 and 411 at water level 19.75 (Battery hatch area) Lateral: Fuselage station 389.5 at water level 4.76 (Battery hatch area) Maximum weights Takeoff (Antidetonant Power) 44,900 lb. Takeoff (Dry Power) 41,500 lb. Landing (Antidetonant Power) 43,000 lb. Landing (Dry Power) 40,200 lb. Zero-Fuel Variable between 41,000 and 42,500 lb. See "Airspeed Limits" for zero fuel weights and corresponding Vne and Vno speeds. Minimum crew 2 - Pilot and Co-pilot (190) Maximum passengers 50 (CAR 4b.43) Maximum baggage Compartment Station Max. Capacity (Lb.) Arm Fwd. Cabin-R.H. 212-243 900 228 Fwd. Cabin-R.H. 212-330 1700 273 Fwd. Cabin-L.H. 255-290 800 273 Fwd. Cabin-L.H. 255-330 2000 293 Aft cabin 730-799 600 766 Aft belly 536-723 1600 643 Fuel capacity 1370 gal. (458) (685 gal. in 6 interconnected wing fuel cells in each wing) See NOTE 1(c) for "System Fuel." Oil capacity 54 gal. (408) (One 27 gal. tank in each nacelle.) See NOTE 1(c) for "System Oil". Control surface movements Elevator trim tab 10° Up 20° Down Elevator (flaps 0°) 30° Up 18° Down Aileron trim tab 12° Up 12° Down Aileron 30° Up 15° Down Rudder 25° Left 25° Right Rudder trim tab 17 1/2° Left 17 1/2° Right Flaps 45° Down Serial Nos. eligible 14101 and up, except U.S. Coast Guard aircraft Nos. 14290 and 14291. (Refer to pertinent ACA Forms 317 or 970 for non-conformity items on Coast Guard Aircraft.) Required equipment In addition to the pertinent required basic equipment specified in CAR 4b, the following items of equipment must be installed: Items 1, 2, 101(a) or (b), 102(a) or (b), 103, 104, 105, 106, 107, 201(a), 202(a), 203(a) or (b), 205(a), 206(a), 301, 302, 303, 304, 401(a) or (b), 402, 404, 501, 502, 503(b). 3 1A7 SPECIFICATIONS PERTINENT TO ALL MODELS Certification basis Type Certificate No. 1A7 (CAR 4b, as amended to October 1, 1949 and Amendment 4b-6 effective March 5, 1952, Paragraph 4b.120 only) Production basis Production Certificate No. 106 Equipment: A plus (+) or minus (-) sign preceding the weight of an item indicates net weight change when that item is installed. Propellers and Propeller Accessories (except Deicing Equipment) 1. 2 Propellers, controllable - Hamilton Standard hubs 43E60 with 3 blades: (a) 6895A-12 1205 lb. (302) Diameter: Max. 13'1-5/16", min. allowable for repairs 12'9-5/8". Pitch settings at 42 in. Sta.: Low +30 1/2, feathered +95°, reverse -11°. The maximum time to automatically feather an engine from take-off r.p.m. at V2 speed is 10 seconds. 2. 2 Propeller governors (Hamilton Standard 5U18) 26 lb. (317) Engines and Engine Accessories - Fuel and Oil Systems 101. (a) 2 P&W Double Wasps CB3 (Airplane Flight Manual) 4687 lb. (340) Item 401(a) only is applicable) (b) 2 P&W Double Wasps CB16 (Airplane Flight Manual 4751 lb. (340) Item 401(b) only is applicable) 102. (a) 2 Starters (Jack & Heintz JH6ER-12) 55 lb. (385) (b) 2 Starters (Eclipse-Pioneer 36E00-4) 55 lb. (385) 103. 2 Feathering pumps (Ham. Std. 66166) 29 lb. (395) 104. 2 Oil coolers (Airesearch 19519 or 86687, 16" dia.) 63 lb. (379) 105. 2 Fuel pumps, engine-driven (Thompson TF2100 or TFD2100 8 lb. (381) 106. 2 Fuel submerged fuel pumps, electrically driven 14 lb. (470) (Thompson TFD-27900-10 or -15, Type B5C) 107. System fuel and oil (See NOTE 1(c) for definition) (a) System fuel 37 lb. (463) (b) System oil 196 lb. (409) 108. Antidetonant system installation (including 16 gal. of fluid at 8 lb. per gallon) 250 lb. (417) Landing Gear 201. 4 Main wheel-brake assemblies, 12.50-16, Type III, (a) Goodyear Model L12.50-16 HBM, Wheel Assembly No. 9540512, 389 lbs. (473) Brake Assembly No. 9540494 202. (a) 4 Main wheel tires, 12.50-16, Type III, 10-ply rating, with regular tubes 312 lb. (473) 203. 2 Main gear shock strut assemblies (a) Menasco 527000 (Martin Dwg. No. E-100007) 570 lb. (481) (b) Menasco 511001 (Martin Dwg. No. 404-4900135) 518 lb. (481) 205. (a) 1 nose wheel, 9.50-16, Type III, Goodyear Wheel Assembly No. 9530759 31 lb. (205) 206. (a) 1 nose wheel tire, 9.50-16, Type III, 10-ply rating, with regular tube 53 lb. (205) 1A7 4 Electrical Equipment 301. 2 Generators (Eclipse-Pioneer 30E02-11B or -11C) 130 lb. (387) 302. Battery (Exide 12T-AS11) 83 lb. (400) 303. 2 Landing Lights (Grimes G-3800A-6) 12 lb. (445) 304. 2 Inverters (Eclipse-Pioneer 1518-1-F) 73 lb. (375) Interior Equipment 401. One of the following FAA Approved Airplane Flight Manuals. (The Manual may be carried as part of, or bound with, the operator's "Approved Operator's Manual", but must remain in the airplane and must retain its identity as an individual manual.) (a) EAL Model 404, Revision 4 dated 9/4/62 (b) TWA Model 404, Revision 5 dated 10/15/52 7 lb. (167) 402. Windshield wiper installation (Marquette Motor D1600-1 with Marquette 16-2E6-1/64 Rev. C valve or Alco Motor XW2068-5 or XW2069-2 with valve XW2331-2) 403. 2 cabin combustion heaters (Surface Combustion 77A63) 55 lb. (358) 404. Oxygen system (Includes both protective and supplemental) (a) EAL Maint. Manual (Vol. V) Series 20-2 Page 1. 53 lb. (332) (b) TWA Maint. Manual Series 20-2 Page 1. 100 lb. (302) Anti-icing and Deicing Equipment 501. 4 wing combustion heaters (Surface Combustion (Janitrol) 99A50) 158 lb. (467) 502. Carburetor heat anti-icing system26 lb. (358) (GLM Dwg. No. 404-5051100 or 404-5051200) 503. Alcohol deicing system (including 16 gal. at 7 lb. per gallon) 212 lb. (521) (EAL Maintenance Manual Vol. V Series 18-2 pages 11 and 13; TWA Maintenance Manual Series 18-2 pages 11 and 13). (a) Propeller deicing equipment Hamilton Standard Boots Model 74467, length 52 inches. (b) Carburetor. 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). (b) Refer to Martin Engineering Reports "Actual Weight and Balance Model 404 (Airline)" and "Weight and Balance Loading Schedule Model 404 (Airline)" for interior arrangement, equipment list, weight and balance and loading schedule for any particular airplane. (c) "System Fuel and Oil" is that amount required to fill both the systems and the tanks up to the tank outlets to the engines, when the airplane is in the level attitude. "System Fuel and Oil" and all hydraulic fluid must be included in the certificated weight empty. (See Item 107 for fuel and oil quantities). (d) Fuel and Oil capacities listed do not include any "System Fuel and Oil". Oil tank does include propeller feathering oil (2 gal.). NOTE 2. The following placards must be displayed on the instrument panel in full view of the pilot (except as noted in (c), (e) and (f) below): (a) "This airplane must be operated in compliance with operating limitations specified in F.A.A. approved airplane operating manual." 5 1A7 (b) Automatic Propeller Feathering: "Lights ON for all take-off operations". (c) "Emergency gear extension - Do not lower above 130 m.p.h.". (Located inside emergency gear control access door.) (d) Landing gear control handle: "Caution: Lever must return to neutral after each operation". (e) Forward Cabin Door: "This door to be open during all take-offs and landings". (Located on forward side of cabin inner door at Sta. 330.) (f) Forward entrance door restraining bar (EAL only): "Warning - Bar must not be across doorway during take-off and landing". (Installed on restraining bar). NOTE 3. When antidetonant injection is not used for takeoff, the propeller governors must be reset prior to takeoff in order to limit the dry takeoff engine r.p.m. to 2700. .....END.....