TCDS A-795

Page No. 1 2 3 4 5 6 7 8 9 10 Rev. No. 19 - - - - - - - - - FEDERAL AVIATION AGENCY A-795 Revision 19 MARTIN 202 202A February 27, 1963 AIRCRAFT SPECIFICATION NO.A-795 Manufacturer Martin-Marietta Corporation Baltimore 3, Maryland I - Model 202, Approved September 3, 1947 Engines 2 P&W Double Wasp CA3, CA15 or CA18 (Item 101) Fuel Aviation Gasoline: Minimum grade 100/130 for all engines. Engine limits (See Item 101) Airspeed limits Vno (Normal Operating) Variable, see table below (T.I.A.S.) Vp (Maneuvering) 170 m.p.h. (148 knots) Vne (Never exceed) Variable, see table below Vf (Flaps down) 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. (157 knots) Maximum Weight (Zero fuel), lb. 35,000 35,500 35,700 35,900 36,000 36,200 Vne (Never exceed) (mph, knots) 292,254 292,254 292,254 284,247 278,242 269,234 Vno (Normal operating) (mph, knots) 255,222 250,218 247,215 245,213 240,209 228,198 C.G. range Takeoff and Landing (Gear Extended) (435.0) to (460.8) Climb and Cruise Gear Extended: (433.0) to (460.8) Gear Retracted: (431.3) to (460.8) Effect of Retracting Landing Gear -64,556 in.lb. Maximum weight (Eligible for takeoff weight in excess of 38,000 lbs. and landing weight in excess of 36,500 lb. only when landing gear equipment Items 202(a) and 206(a) or (c) are installed.) (a) The following maximum weights are permitted when the 30° Approach and 45° Landing Flaps settings are used and the automatic propeller feathering system is operative. Takeoff (Antidetonant Power) 39,900 lb. Takeoff (Dry Power) 39,100 lb. Landing (Antidetonant Power) 38,000 lb. Landing (Dry Power) 37,200 lb. (b) The following maximum weights are permitted when the 18° Approach and 28° Landing Flap settings are used and the automatic propeller system is operative. See NOTE 3 regarding required revisions for the flight manual. Takeoff (Antidetonant Power) 39,900 lb. Takeoff (Dry Power) 39,900 lb. Landing (Antidetonant Power) 38,000 lb. Landing (Dry Power) 38,000 lb. A-795 2 I - Model 202 (cont’d) (c) The following maximum weights are permitted when the automatic propeller feathering system is not utilized or is inoperative. See NOTE 8 regarding required revisions for the Flight Manual. Takeoff (Antidetonant Power) 39,900 lb. Takeoff (Dry Power) 36,150 lb. Landing (Antidetonant Power) 38,000 lb. Landing (Dry Power) 36,150 lb. (d) The maximum zero fuel weights vary from 35,000 to 36,200 pounds. See "Airspeed Limits" for zero fuel weights and corresponding Vne and Vno speeds. Minimum crew 2 - Pilot and Co-pilot (203) Maximum passengers 40 (CAR 4b.432 prior to October 1, 1949) Maximum baggage Maximum Capacity Compartment Station (Lb.) Arm Fwd. Cabin-R.H. 225-316 1150 270 Fwd. Cabin-R.H. 225-304 1000 268 Fwd. Cabin-R.H. 225-343 1500 285 Fwd. Cabin-L.H. 268-343 1000 306 Fwd. Cabin-L.H. 268-304 500 286 Aft-Cabin 676-753 800 715 Aft-Cabin 704-773 600 739 Aft-Cabin 753-832 1500 793 Fwd. Belly 325-385 300 355 Aft-Belly 580-637 400 608 Aft-Belly 580-697 950 638 Fuel Capacity 1010 gal. (458) (505 gal. in 4 interconnected wing fuel cells in right and in left wing) (See NOTE 1(c) for "System Fuel" Oil capacity 39.5 gal. (408) (One 19.75 gal. tank in each nacelle) See NOTE 1(c) for "System Oil" Serial Nos. eligible 9122 and up. For Serial No. 9123-A see NOTE 11. 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, 102(a), 103, 104(a), 105, 106, 107, 201, 202, 205, 206. 301(a), 302, 303, 401, 403, 502. II - Model 202A, Approved July 10, 1950 (Same as Model 202 except for reinforced fuselage and wing, increased fuel capacity, power plant and miscellaneous system changes) Engines 2 P&W Double Wasp CB16 (Item 109) Fuel Aviation Gasoline: Minimum grade 100/130 Engine limits (See Item 109) Airspeed limits Vno (Normal Operating) Variable, see table below (T.I.A.S.) Vp (Maneuvering) 176 m.p.h. (153 knots) Vne (Never exceed) Variable, see table below Vf (Flaps down) (12 1/2° Takeoff) 190 m.p.h. (165 knots) (Landing) 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. (157 knots) 3 A-795 II - Model 202A (cont’d) Maximum Weight (Zero fuel), lb. 35,300 35,800 36,000 36,200 36,300 36,500 Vne (Never exceed) (mph, knots) 292,254 292,254 292,254 284,247 278,242 269,234 Vno (Normal operating) (mph, knots) 255,222 250,218 247,215 245,213 240,209 228,198 C.G. Range Gear Position Max Weight C.G. Range Takeoff Extended 43,000 lb. (442.8) to (460.8) Takeoff and Landing Extended 41,000 lb. (438.6) to (460.8) Takeoff and Landing Extended 34,500 lb. (435.0) to (460.8) Climb and Cruise Retracted 43,000 lb. (431.3) to (460.8) (Straight line C.G. variation with weights shown.) Effect of retracting landing gear -72,700 in. lb. Maximum weight Takeoff (Antidetonant Power) 43,000 lb. Takeoff (Dry Power) 40,000 lb. Landing (Antidetonant Power) 41,000 lb. Landing (Dry Power) 40,000 lb. Zero-Fuel Variable between 35,300 and 36,500 pounds. See "Airspeed Limits" for zero fuel weights and corresponding Vne and Vno speeds. Minimum crew 2 - Pilot and Co-pilot (203) Maximum passengers 40 (CAR 4b.432 prior to October 1, 1949) Maximum baggage Maximum Capacity Compartment Station (Lb.) Arm Fwd. Cabin-R.H. 225-304 1000 268 Fwd. Cabin-L.H. 269-304 500 286 Aft Cabin704-773 600 739 Fwd. Belly 325-385 300 355 Aft. Belly 580-697 950 638 Fuel Capacity 1350 gal. (458) (675 gal. in 6 interconnected wing fuel cells in right and in left wing) (See NOTE 1(c) for "System Fuel") Oil capacity 49 gal. (408) (One 24.5 gal. tank in each nacelle.) (See NOTE 1(c) for "System Oil".) Serial Nos. eligible 14071 and up 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, 102(c), 103, 104(c), 105, 106, 107, 109, 201(b), 202, 205, 206, 301(c), 302, 303, 401(e), 403, 502. Specifications Pertinent to All Models Datum 100 inches forward nose of fuselage Leveling means Longitudinal: Left side, fuselage stations 459 and 485, 3 inches below windows. Lateral: Lower surface of wing rear spar A-795 4 Control surface movements Elevator trim tab 10° Up 20° Down Elevator (Flaps 0°) 30° Up 16° 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 Certification basis Type Certificate No. 795 (CAR 4b) 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) Eligible on Model 202 202 202A Basic Uptilted Nacelle Nacelle 1. 2 Propellers, controllable-Hamilton Standard hubs 23260 with 3 blades: (See NOTE 6 of Prop. No. P-853 for interchangeable blades) (a) Deleted December 19, 1958 (b) Deleted April 17, 1950 (c) 2H17K3-48R; Diameter 157 in. (13'1") Use act. wt. change (304) (301) (301) (d) 2H17K3-50R; Diameter 155 in. (12'11") Use act. wt. change (304) (301) (301) (e) 2H17U3-48R or 2H17AA3-48R; Use act. wt. change (304) (301) (301) Diameter 157 in. (13'1") (f) 2H17U3-50R or 2H17AA3-50R; Use act. wt. change (304) (301) (301) Diameter 155 in. (12'11") (g) 2H17AC3-48R, Diameter 157 in. (13'1") Use act. wt. change (304) (301) (301) Pitch settings at 72 in. Sta.: Low +13°, High +80°, Feathered +80°, Reverse -27°. (See NOTE 4 regarding airplane flight manual revisions required.) 2. 2 Propeller governors Hamilton Standard 4U18 18 lb. (325) (322) (322) 3. 2 Propellers, controllable-Hamilton Standard hubs 43E60 with 3 blades. (a) 6895A-12 1106 lb. (304) (301) (301) Diameter: Max. 13' 1-5/16", min. allowable for repairs 12'9-5/8" Pitch settings at 42 in. Sta.: Low +30.5°, High +95°, Feathered +95°, Reverse -13°. (See NOTES 4 and 9 regarding airplane flight manual revisions required). 4. 2 Propellers, controllable-Hamilton Standard hubs 33E60 with 3 blades: (a) 6899A-12 1040 lb. (304) (301) --- Diameter 158 in. (13'2") Pitch settings at 42 in. Sta.: Low +30.5° High +95°, Feathered +93°, (This propeller not reversible). (See NOTE 9 regarding airplane flight manual revision required). 5 A-795 Engines and Engine Accessories - Fuel and Oil Systems (Model 202 is eligible with 1 1/2 uptilted nacelle and engine Eligible on Model installation. See NOTE 6 for details. Model 202A incorporates 202 202 202A uptilted nacelle) Basic Uptilted Nacelle Nacelle 101. (a) 2 P&W Double Wasp CA3 Engines 4654 lb. (342) (339) - - - with G.E. Ignition +23.5 lb. (342) (339) - - - Engine Limits Alt. H.P. R.P.M. Mp. In.Hg. Low impeller gear ratio 7.29:1 Takeoff (dry) to (5 minutes) S.L. to 3000 2100 2800 53.5 Takeoff (Antidetonant Injection) (5 minutes) S.L. 2400 2800 56.5 Maximum continuous S.L. 1800 2600 45.0 Maximum continuous 6500 1800 2600 44.0 (Straight line manifold pressure variation with altitudes shown) When this item is installed, the flight manual Item 401 must be revised to reflect the installation and the applicable performance. This revision material must be supplied by the applicant. (b) Two P&W Double Wasp CA15 Engines + 66 lb. (342) (339) - - - Engine Limits Alt. H.P. R.P.M. Mp. In.Hg. Low impeller gear ratio 7.29:1 Takeoff (dry) to (5 minutes) S.L. to 3000 2100 2800 53.5 Takeoff (Antidetonant Injection) (5 minutes) S.L. 2400 2800 56.5 Maximum continuous S.L. 1800 2600 45.0 Maximum continuous 6500 1800 2600 44.0 High impeller gear ratio 9.45:1 Maximum continuous 10000 1600 2600 46.5 Maximum continuous 16200 1600 2600 45.0 (Straight line manifold pressure variation with altitudes shown) When this item is installed, the flight manual Item 401(c) only is applicable. Eligible on Model 202 202 202A Basic Uptilted Nacelle Nacelle (c) Two P&W Double Wasp CA18 Engines No weight change (342) (339) - - - with G.E. Ignition -10 lb. (342) (339) - - - Engine Limits Alt. H.P. R.P.M. Mp. In.Hg. Low impeller gear ratio 7.29:1 Takeoff (dry) to (5 minutes) S.L. to 3000 2100 2800 53.5 Takeoff (Antidetonant Injection) (5 minutes) S.L. 2400 2800 56.5 Maximum continuous S.L. 1800 2600 45.0 Maximum continuous 6500 1800 2600 44.0 High impeller gear ratio 9.1:1 Maximum continuous 8000 1675 2600 49.0 Maximum continuous 13500 1675 2600 47.0 (Straight line manifold pressure variation with altitudes shown) When this item is installed, the flight manual Item 401(b) and (d) only are applicable. A-795 6 Eligible on Model 202 202 202A Basic Uptilted Nacelle Nacelle 102. (a) 2 Starters (Jack and Heintz JH-6ER12) 53 lb. (383) (380) - - - (b) 2 Starters (Eclipse 1416-12) 55 lb. (383) (380) - - - (c) 2 Starters (Jack and Heintz JH-6ES12) 55 lb. - - - - - - (381) 103. 2 Feathering pumps (Ham. Std. 66166) 27 lb. (397) (397) (397) 104. (a) 2 Oil Coolers (Airesearch 19233, 16" Dia.) 68 lb. (373) (370) - - - (b) 2 Oil Coolers (Clifford 37984, 16" Dia.) 64 lb. (373) (370) - - - (c) 2 Oil Coolers (Airesearch 19519, 16" Dia.) 69 lb. - - - - - - (370) 105. 2 Fuel Pumps, Engine Driven (Pesco 2P-771-A or -C) 9 lb. (379) (376) (379) 106. 2 Fuel Booster Pumps, Electrically Driven 14 lb. (478) (478) (478) (Thompson TFD-27900-10 Type B5C) (Submerged in fuel tanks) 107. System fuel and oil (See NOTE 1(c) for definition) (a) System fuel 37 lb. (450) (450) (450) (b) System oil 196 lb. (393) (393) (393) 108. Antidetonant system installation, including 215 lb. (404) (404) (404) 15 gal. of fluid at 8 lb. per gallon (G.L.M. Dwg. No. 2021C12679) (See NOTE 2(d)(I) and 2(d)(II) for required placards - Model 202 only) (See NOTE 2(d)(III) for required placard - Model 202A only) (See NOTE 5 for required changes in Flight Manual - Model 202 only) 109. 2 P&W Double Wasp CB16 Engines 4704 lb. --- --- (340) Engine Limits Alt. H.P. R.P.M. Mp. In.Hg. Low impeller gear ratio 7.29:1 Takeoff (dry) (2 minutes) S.L. 2050 2700 55.0 Critical Altitude 6900 2050 2700 53.0 Takeoff (Antidetonant Injection) (2 minutes) S.L. 2400 2800 59.5 Critical Altitude 5000 2400 2800 58.5 Maximum continuous S.L. 1800 2600 48.5 Maximum continuous 9200 1800 2600 46.5 High impeller gear ratio 8.58:1 Maximum continuous 10000 1700 2600 48.5 Maximum continuous 16800 1700 2600 47.5 (Straight line manifold pressure variation with altitudes shown) When this item is installed, Flight Manual Item 401(e) only is applicable. Landing Gear 201. 4 Main wheel-brake assemblies, 12.50-16, Type III, (a) Goodyear Model L12.50-16HBM, Wheel Assembly 292 lb. (474) (474) --- No. 9530250, Brake Assembly No. 9540036 (b) Goodyear Model L12.50-16 HBMG, Wheel Assembly 396 lb. (474) (474) (474) No. 9540381, Brake Assembly No. 9540466 202. 4 Main wheel tires, 12.50-16, Type III, with regular tubes. (a) 10-ply rating (this is required for take-off weights 292 lb. (474) (474) (474) over 38,000 lb. and landing weights over 36,500 lb. (b) 8-ply rating (474) (474) (474) 7 A-795 Eligible on Model 202 202 202A Basic Uptilted Nacelle Nacelle 205. 1 Nose wheel, 32 x 8.8, Type VIIB, Goodrich 37 lb. (218) (218) (218) Model 6103M. Wheel assembly No. H-3-575-M 206. 1 Nose wheel tire with 32 x 8.8, Type VIIB regular tube: (either (a) or (c) below is required for take-off weights over 38,000 lb. and landing weights over 36,500 lb.) (a) 32 x 8.8, Type VIIB, 10-ply rating 43 lb. (218) (218) (218) (b) 32 x 8.8, Type VIIB, 8-ply rating 40 lb. (218) (218) - - - (c) 9.50-16, Type III, 8-ply rating 47 lb. (218) (218) (218) Electrical Equipment 301. (a) 2 Generators (Westinghouse TY-D30 or TY-DA30) 118 lb. (383) (380) - - - (b) 2 Generators (Eclipse Model 1547-1 or 1547-3) 128 lb. (383) (380) - - - (c) 2 Generators (General Electric 2CM75C13) 123 lb. - - - - - - (377) 302. Battery (Exide Model 12-TAS-11) 83 lb. (413) (413) (413) 303. 2 Landing Lights (Grimes G3800A-5) 12 lb. (438) (438) (438) Interior Equipment 401. One of the following FAA Approved Airplane Flight Manuals including any pertinent revisions indicated in NOTES 3, 4, 5 and 8. (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.) Revisions shown are not necessarily mandatory but only reflect the latest revision to the current manuals. (a) Basic Model 202 - Discontinued, not eligible (b) NW Model 202 - Rev. 20 dated 6/3/52 (c) LAN Model 202 - Rev. 10 dated 10/6/51 (d) LAV Model 202 - Rev. 9 dated 12/11/51 (e) Model 202A- Rev. 9 dated 5/15/54 402. Automatic Pilot, Sperry A-12 110 lb. (414) (414) --- (Servo Unit Model 656542-161(3)) (a) Servo stall forces measured at pilot's control: Elevator: Maximum 45 lb., Minimum 21 lb. Aileron: Maximum 38 lb., Minimum 20 lb. Rudder: Maximum 115 lb., Minimum 65 lb. (Approach Coupler not investigated therefore not eligible for installation.) (b) When using autopilot, minimum terrain clearance is 450 feet. (Minimum terrain clearance does not override any higher minimum operational altitudes.) (See NOTE 10 regarding Airplane Flight Manual revision required.) 403. Windshield Wiper installation (Kearfott 2068-5, 5 lb. (170) (170) (170) 2069-2, 2331-2) 404. (a) Cabin Combustion Heater (Stewart Warner 921-B) 30 lb. (256) (256) --- (b) Cabin Combustion Heater (Surface Combustion S-200) 34 lb. --- --- (257) A-795 8 Eligible on Model 202 202 202A Basic Uptilted Nacelle Nacelle 405. Oxygen System Variable 406. Auxiliary Vacuum System (GLM Dwg. No. 2021C23909) 21 lb. (462) (462) - - - 407. Name Plates - Flap Lever - Pilots Pedestal (GLM Dwgs. No. 2021C33729 and 2021C33699) No wt. change Anti-Icing and Deicing Equipment 501. 4 Wing Combustion Heaters (a) Stewart Warner 921-B 118 lb. (462) (462) - - - (b) Surface Combustion S-200 135 lb. - - - - - - (461) 502. Carburetor Anti-icing system (GLM Dwg. No. 2021C11040) 503. Propeller Electric Anti-Icing System 31 lb. (380) (377) - - - 504. Generator Air Scoop Anti-Icing System 3 lb. (380) (377) - - - (GLM Dwg. No. 2021C24106) 505. Alcohol Deicing System (15 gal. at 7 lb. per gallon - - - - - - (434) (GLM Dwg. No. 202A5051030) (a) Propeller deicing equipment: Hamilton Standard boots Model 74467, length 52 in. (b) Carburetor (c) Windshield 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 202(A) (Airline)" and "Weight and Balance Loading Schedule Model 202(A) (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 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 Tank capacities 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) below): (a) "This airplane must be operated in compliance with operating limitations specified in F.A.A. approved airplane operating manual." (b) Automatic Propeller Feathering: I. "Lights ON for all take-off operation" (Model 202) or II. "Lights ON for all take-off operations. When lights are off see Appendix A in flight manual" (Model 202) III. "Switch and lights ON for all take-off conditions" (Model 202A) (c) "Do not lower landing gear by emergency release above 130 m.p.h.". (Located inside emergency gear control access door) (d) When Item 108 is installed the following placards must be included: I. Two minute wet take-off power limit (Model 202 only) "1. Water tank must be full before each take-off 2. Do not exceed 53.5 inches M.P. unless flow lights are ON 3. Do not use water injection longer than 2 minutes on take-off, except for single engine emergency operation when 5 minutes may be used." 9 A-795 NOTE 2. (d) II. One-minute wet take-off power limit (Model 202 only) "1. Minimum water for take-off - 8.5 gallons 2. Maximum manifold pressure without flow lights on - 53.5 inches. 3. Time limit for wet take-off (except in emergency) - 1 min." III. Two-minute wet take-off power limit (Model 202A only): "1. Minimum water for take-off - 11.2 gallons. 2. If flow lights do not come on discontinue WET take-off." or "1. Minimum water for take-off - 11.2 gallons. 2. If A.D.I. pressure falls below 20 psi discontinue WET take-off." (e) "Do not exceed 200 m.p.h. TIAS with either propeller feathered." (This placard not required if Martin Service Bulletin 55 has been complied with) (Model 202 only) (f) "Do not use nose wheel steering for take-off or landing." (This placard not required if Martin Service Bulletin 46 has been complied with) (Model 202 only) (g) Cabin Heater Fire: "Cabin heater switch must be OFF before firing Co2 to heater compartment. Do not fire second shot until a minimum of 2 minutes have elapsed." (h) When reverse thrust propeller operation is provided the following placard must be installed: "Exercise caution in using reverse thrust on runways covered with dust, snow, or other matter which may reduce visibility". NOTE 3. When wing flap setting of 18° Approach and 28° Landing are used, Item 407 must be installed and the Airplane Flight Manual (Item 401) must contain revisions as follows: Item 401(a) - Discontinued, not eligible Item 401(b) - Revision No. 8 and/or 9 Item 401(c) - Revision No. 6 Item 401(d) - Revision No. 4 Item 401(e) - Not eligible NOTE 4. When reversible thrust propeller operation is provided (see NOTE 2(h) for required placard) according to G.L.M. Service Bulletin 62, the Airplane Flight Manual must contain revisions as follows: Item 401(a) - Discontinued, not eligible Item 401(b) - Revision No. 12 Item 401(c) - Revision No. 6 Item 401(d) - Revision No. 6 Item 401(e) - (No revision required) NOTE 5. When Item 108 is installed in the Airplane Flight Manual (Item 401) must contain revisions as follows: (See NOTE 2(d) for required placard) (a) Two-minute wet take-off power limit Item 401(a) - Discontinued, not eligible Item 401(b) - Revision Nos. 6A and 7 Item 401(c) - Revision No. 1 Item 401(d) - Not revised, therefore not eligible Item 401(e) - Revision No. 6 (b) One-minute wet take-off power limit Item 401(a) - Discontinued, not eligible Item 401(b) - Revision Nos. 6A, 7 and 11 Item 401(c) - Not revised, therefore not eligible Item 401(d) - Not revised, therefore not eligible Item 401(e) - Not eligible, deleted by revision 6 NOTE 6. Model 202 eligible for 1 1/2° uptilted nacelle and engine installation, in accordance with Martin Dwg. No. 2021C05036. With this installation, elevator tab compression spring, Martin Dwg. No. 2021C33678, must also be installed. All airplanes incorporating this installation must be identified by adding the letter "A" to the serial number (e.g. Serial Number 0000-A). (Model 202A incorporates uptilted nacelle and engine installation). A-795 10 NOTE 7. Outer wing installations and outer wing flap assemblies eligible in any combination, including unsymmetrical combinations, in accordance with the following Martin drawings: (Model 202 only) Outer Wing Installation 2021C01201 Supplement No. 1 2021C01201 Supplement No. 2 Outer Flap Assembly 2021C13395 Supplement No. 1 2021C13395 Sheet 2 NOTE 8. Operation with the automatic propeller feathering system off or inoperative is permitted provided the Airplane Flight Manual (Item 401) contains the pertinent certification data identified as Appendix A incorporated by one of the following revisions (See NOTE 2(b) II for required placard): Item 401(a) - Discontinued, not eligible Item 401(b) - Revision No. 16 Item 401(c) - Not revised, therefore not eligible Item 401(d) - Not revised, therefore not eligible Item 401(e) - Not eligible Model 202 aircraft certificated only with the automatic propeller feathering system operative (see Items 401(c) or 401(d), may be operated with the automatic propeller feathering system inoperative by Ferry Permit only. Item 401(a), (c) and (d) revisions dated 6/22/49 contain pertinent ferry permit limitations. NOTE 9. When Item 3 or 4 is installed on the Model 202, the Airplane Flight Manual, Item 401, must b e revised as follows: Item 401(a) - Discontinued, not eligible Item 401(b) - Not revised, therefore not eligible Item 401(c) - Revision 9; Item 3 only eligible Item 401(d) - Revision 9; Item 3 only eligible Item 401(e) - No revision required for Item 3; Item 4 not eligible. NOTE 10.When Item 402 is installed on the Model 202, the Airplane Flight Manual, Item 401, must be revised as follows: Item 401(a) - Discontinued, not eligible Item 401(b) - Revision 18 Item 401(c) - Revision 10 Item 401(d) - Revision 8 Item 401(e) - Not eligible NOTE 11. For configuration, performance and FAA Approved Airplane Flight Manual for modified Serial No. 9123-A see Martin Report "Substantiation of Model 202 (9123-A)." This airplane is the same as the basic Model 202 except for CB-16 engines, fuselage length, flight control configuration, aileron boost, oleo drag strut landing gear and miscellaneous system and equipment changes. .....END......