TCDS 3A16

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 Rev. No. 95 73 73 73 65 76 76 76 76 80 65 65 86 81 90 90 85 90 95 Page No. 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 Rev. No. 84 84 84 84 84 84 84 84 84 84 84 84 84 84 84 84 84 84 84 Page No. 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 Rev. No. 84 84 84 84 84 84 84 89 84 84 84 81 76 81 78 82 88 88 92 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 3A16 Revision 95 Textron Aviation B95A D55 D95A D55A E95 E55 95-55 E55A 95-A55 56TC 95-B55 A56TC 95-B55A 58 95-B55B (T-42) 58A 95-C55 95 95-C55A B95 G58 October 20, 2022 TYPE CERTIFICATE DATA SHEET NO. 3A16 This data sheet which is part of Type Certificate No. 3A16 prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Textron Aviation Inc. One Cessna Boulevard Wichita, KS 67215 Type Certificate Holder Record: Beech Aircraft Corporation transferred to Raytheon Aircraft Company on April 15, 1996 Raytheon Aircraft Company transferred to Hawker Beechcraft Corporation on March 26, 2007 Hawker Beechcraft Corporation transferred to Beechcraft Corporation on April 12, 2013 Beechcraft Corporation transferred to Textron Aviation Inc. on October 12, 2016 I. Model 95, Travel Air, 4 or 5 PCLM (Normal Category), Approved June 18, 1957 Engines 2 Lycoming O-360-A1A See Item 111 for optional engines. *Fuel 91/96 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (180 hp.) Airspeed Limits Maneuvering 160 m.p.h. (139 knots) (CAS) Maximum structural cr uising 185 m.p.h. (161 knots) Never exceed 240 m.p.h. (208 knots) Flaps extended 130 m.p.h. (113 knots) Landing gear extended 150 m.p.h. (130 knots) 3A16 Rev. 95 2 I. Model 95 (cont'd) C.G. Range (Landing (+79.4) to (+83.0) at 4000 lb. Gear Extended) (+75.0) to (+83.0) at 3480 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 4000 lb. No. of Seats 4 (2 at +85, 2 at +121) or 5 (2 at +85, 2 at +119, 1 at +140) when Item 603(a) installed Maximum Baggage and/or Forward compartm ent (above floorboard) 270 lb. (+ 31) Optional Equipment Rear compartment 270 lb. (+140) (Structural Limits) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover 270 lb. (+135) On and forward of spar cover 200 lb. (+108) For weight and balance information, refer to DOA Flight Manual. Fuel Capacity Tank Capaci ty Gal. Usable Gal. Arm L & R Main 25 ea. 22 ea +75 L & R Aux. 17 ea. 17 ea. +94 Optional Fuel System (Item 106) L & R Main 25 ea. 22 ea. +75 L & R Aux 31 ea. 31 ea. +93 See NOTE 1 for data on unusable fuel Oil Capacity 8 qt. ea. engine (+46) (usabl e 6 qt. ea. engine), total capacity 16 qt. See NOTE 1 for data on system oil Control Surface Movements Wing flaps Down 33° Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 30° Left 30° Tabs (main surface in neutral) Aileron Up 10° Down 10° Elevator Up 10° Down 20° Rudder Right 25° Left 25° Elevator eligible Up 10° Down 23° TD-2, TD-103 and up (main surface in neutral) Serial Nos. Eligible TD-2 through TD-302 Required Equipment Items 1(a) and (b) or 4(a) and (b ), 101(a) and (b), 102(a), 103(a), 201, 202, 205, 206, 301, 302, 304, 401(a), (b), (c), (d) and (ee) and (gg or oo), 601 II. Model B95, Travel Air, 4 or 5 PCLM (Normal Category), Approved November 13, 1959 Engines 2 Lycoming O-360-A1A See Item 111 for optional engines. *Fuel 91/96 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (180 hp.) Rev. 95 3A16 3 II. Model B95 (cont’d) Airspeed Limits Maneuvering 160 m.p.h. (139 knots) (CAS) Maximum structural cr uising 185 m.p.h. (161 knots) Never exceed 240 m.p.h. (208 knots) Flaps extended 130 m.p.h. (113 knots) Landing gear extended 150 m.p.h. (130 knots) C.G. Range (Landing (+80.5) to (+86.0) at 4100 lb. Gear Extended) (+75.0) to (+86.0) at 3480 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 4100 lb. No. of Seats 4 (2 at +85, 2 at +121 or +136) or 5 (2 at +85, 2 at +121, 1 at +150) when Item 603(b) installed Maximum Baggage and/or Forward compartm ent (above floorboard) 270 lb. (+ 31) Optional Equipment Rear compartment 270 lb. (+150) (Structural Limits) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover 270 lb. (+145) On and forward of spar cover 200 lb. (+108) For weight and balance information, refer to DOA Flight Manual. Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L & R Main 25 ea. 22 ea. +75 L & R Aux. 17 ea. 17 ea. +94 Optional Fuel System (Item 106) L & R Main 25 ea. 22 ea. +75 L & R Aux. 31 ea. 31 ea. +93 See NOTE 1 for data on unusable fuel. Oil Capacity 8 qt. ea. engine (+46) (usabl e 6 qt. ea. engine), total capacity 16 qt. See NOTE 1 for data on system oil. Control Surface Wing flaps Down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 34° Left 30° Tabs (main surface in neutral) Aileron Up 10° Down 10° Elevator Up 10° Down 20° Rudder Right 25° Left 25° Serial Nos. Eligible TD-303 through TD-452 Required Equipment Items 1(a) and (b) or 4(a) and (b ), 101(a) and (b), 102(a), 103(a), 201, 202, 205, 206, 301(a) or (b) or (c), 302, 304, 401(e) and (ee) and (gg or oo), 601 3A16 Rev. 95 4 III. Model 95-55, Baron, 4, 5 or 6 PCLM (Normal Category), Approved November 3, 1960 Model 95-A55, Baron, 4, 5 or 6 PCLM (Normal Category), Approved October 9, 1961 Engines 2 Continental IO-470-L *Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2625 r.p.m. (260 hp.) Airspeed Limits Maneuvering 180 m.p.h. (156 knots) (CAS) Maximum structural cr uising 210 m.p.h. (182 knots) Never exceed 257 m.p.h. (223 knots) Flaps extended 130 m.p.h. (113 knots) Landing gear extended 165 m.p.h. (143 knots) C.G. Range (Landing (+79.4) to (+86.0) at 4880 lb. Gear Extended) (+74.0) to (+86.0) at 3800 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 4880 lb. No. of Seats 4 (2 at +85, 2 at +121 or +136) or 5 (2 at +85, 2 at +121, 1 at +150) when Item 603(b) installed or 6 (2 at +85, 2 at +121, 2 at +150) when Item 603(d) installed Maximum Baggage and/or Forward compartm ent (above floorboard) 270 lb. (+ 31) Optional Equipment Rear compartment (aft to Sta. 170.00) 400 lb. (+150) (Structural Limits) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover to Sta. 170.00 400 lb. (+145) When Item 607 installed aft of Sta. 170.00 120 lb. (+180) For weight and balance informat ion, refer to DOA Flight Manual Fuel Capacity Tank Capaci ty Gal. Usable Gal. Arm L & R Main 25 ea. 22 ea. +75 L & R Aux. 31 ea. 31 ea. +93 Optional Fuel System (Item 108) L & R Main 40 ea. 37 ea. +75 L & R Aux. 31 ea. 31 ea. +93 See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. ea. engine (+43) (includes 5.5 lb. unusable), total capacity 24 qt. See NOTE 1 for data on system oil. Control Surface Wing flaps Down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 10° Down 10° Elevator Up 10° Down 23° Rudder Right 25° Left 25° Serial Nos. Eligible Mode l 95-55: TC-1 through TC-190 Model 95-A55: TC-191 through TC-501 (except TC-350 and TC-371) Required Equipment Items 2(b) and (a) or (d) or 9(a) or (b) or 3(a) and (b), 101(d) and (c) or (g), 101(d) and (h) (95-A55), 102(b) or (c), 103(b), 201, 202, 205, 206, 301, 302, 304, 401(gg or oo) and (k) or (q) or (am) (95-55), 501(gg or oo) and (p) or (r) or (t) or (am) (95-A55), 601(a) or (b) or (c) (95-55), 601(b) or (c) (95-A55) Rev. 95 3A16 5 IV. Model B95A, Travel Air, 4, 5 or 6 PCLM (Normal Category), Approved March 9, 1961 Engines 2 Lycoming IO-360-B1A See Item 112 for optional e ngines for S/N TD-506 only. *Fuel 91/96 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (180 hp.) Airspeed Limits Maneuvering 160 m.p.h. (139 knots) (CAS) Maximum structural crui sing 185 m.p.h. (161 knots) Never exceed 240 m.p.h. (208 knots) Flaps extended 130 m.p.h. (113 knots) Landing gear extended 150 m.p.h. (130 knots) C.G. Range (Landing (+80.5) to (+86.0) at 4200 lb. Gear Extended) (+75.0) to (+86.0) at 3600 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 4200 lb. No. of Seats 4 (2 at +85, 2 at +121 or +136) or 5 (2 at +85, 2 at +121, 1 at +150) when Item 603(b) installed or 6 (2 at +85, 2 at +121, 2 at +150) when Item 603(d) installed Maximum Baggage and/or Forward compartm ent (above floorboard) 270 lb. (+ 31) Optional Equipment Rear compartment 400 lb. (+150) (Structural Limits) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover 400 lb. (+145) On and forward of spar cover 200 lb. (+108) For weight and balance information, refer to DOA Flight Manual. Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L & R Main 40 ea. 37 ea. +75 Optional Fuel System (Item 109) L & R Main 25 ea. 22 ea. +75 L & R Aux. 31 ea. 31 ea. +93 See NOTE 1 for data on unusable fuel. Oil Capacity 8 qt. ea. engine (+46) (usabl e 6 qt. ea. engine), total capacity 16 qt. See NOTE 1 for data on system oil. Control Surface Wing flaps Down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 34° Left 30° Tabs (main surface in neutral) Aileron Fixed Elevator Up 10° Down 23° Rudder Right 25° Left 25° Serial Nos. Eligible TD-453 through TD-533 Required Equipment Items 1(a) and (b) or 4(a) and (b), 101(e) or (f), 102(a), 103(a), 201 and 202 or 203 and 204, 205, 206, 301(a) or (b) or (c), 302, 304, 401(gg or oo) and (l) or (s), 601 3A16 Rev. 95 6 V. Model D95A, Travel Air, 4, 5 or 6 PC LM (Normal Category), Approved May 17, 1963 Model E95, Travel Air, 4, 5 or 6 PCLM (Normal Category), Approved October 17, 1967 Engines 2 Lycoming IO-360-B1B *Fuel 91/96 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (180 hp.) Airspeed Limits Maneuvering 160 m.p.h. (139 knots) (CAS) Maximum structural crui sing 185 m.p.h. (161 knots) Never exceed 240 m.p.h. (208 knots) Flaps extended 130 m.p.h. (113 knots) Landing gear extended 166 m.p.h. (144 knots) C.G. Range (Landing (+80.5) to (+86.0) at 4200 lb. Gear Extended) (+75.0) to (+86.0) at 3600 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 4200 lb. No. of Seats 4 (2 at +85, 2 at +121 or +136) or 5 (2 at +85, 2 at +121, 1 at +153) when Item 603(e) or (f) installed or 6 (2 at +85, 2 at +121, 2 at + 150) when Item 603(d) or (g) installed Maximum Baggage and/or Forward compartm ent (above floorboard) 270 lb. (+ 31) Optional Equipment Rear compartment 400 lb. (+150) (Structural Limits) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover 400 lb. (+145) On and forward of spar cover 200 lb. (+108) For weight and balance information, refer to DOA Flight Manual. Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L & R Main 40 ea. 37 ea. +75 Optional fuel system (Item 109) L & R Main 25 ea. 22 ea. +75 L & R Aux. 31 ea. 31 ea. +93 See NOTE 1 for data on unusable fuel. Oil Capacity 8 qt. ea. engine (+46) (usabl e 6 qt. ea. engine), total capacity 16 qt. See NOTE 1 for data on system oil. Control Surface Wing flaps Down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 34° Left 30° Tabs (main surface in neutral) Aileron Fixed Elevator Up 10° Down 23° Rudder Right 25° Left 25° Serial Nos. Eligible Mode l D95A: TD-534 through TD-707 Model E95: TD-708 through TD-721 Rev. 95 3A16 7 V. Model D95A, Model E95 (cont'd) Required Equipment Items 1(a) and (b) or 4(a) and (b) (D95A), 4(a) and (b) (E95), 101(g) and (i), 102(a), 103(a), 201 and 202 or 203 and 204 (D95A), 201 and 202 (E95), 205, 206, 301, 302, 304, 401(u) or (w) and (bb) and (gg or oo) (D95A), 401(dd) and (gg or oo) (E95), 601(b) or (d) VI. Model 95-B55, Baron, 4, 5 or 6 PCLM (Normal Category), Approved September 9, 1963 Model 95-B55A, Baron, 4, 5 or 6 PCLM (Normal Category), Approved October 31, 1968 Engines 2 Continental IO-470-L *Fuel 100/130 minimum grade aviation gasoline Engine Limits For airplanes prior to TC-2285 For all operations, 2625 r.p.m. (260 hp.) For airplanes TC-2285 and after Takeoff and continuous power 2625 r.p.m. (260 hp.) Normal operating power 2550 r.p.m. (252 hp.) (CAS) (IAS) Airspeed Limits Maneuvering 180 m.p.h. (156 knots) 157 knots Maximum structural cruising 210 m.p.h. (182 knots) 183 knots Never exceed 257 m.p.h. (223 knots) 224 knots Flaps extended 15° (S/N TC-2003 and up) 153 knots 28° (See NOTE 3) 130 m.p.h. (113 knots) or 140 m.p.h. (122 knots) 122 knots Landing gear extended 165 m.p.h. (143 knots) or (S/N TC-1157 and up) 175 m.p.h. (152 knots) 153 knots C.G. Range (Landing (+81.0) to (+86.0) at 5100 lb. (See NOTE 3) Gear Extended) (+80.0) to (+86.0) at 5000 lb. (+79.9) to (+86.0) at 4990 lb. (See NOTE 5) (+77.5) to (+86.0) at 4740 lb. (See NOTE 3) (+74.0) to (+86.0) at 3800 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 5000 lb. or 5100 lb. (See NOTE 3) or 4990 lb. (See NOTE 5) No. of Seats 4 (2 at +85, 2 at +121 or +136) or 5 (2 at +85, 2 at +121, 1 at +150) when Item 603(c), (f) or (j) or (m) installed or 6 (2 at +85, 2 at +121, 2 at +150) wh en Item 603(d), (g) or (k) or (n) installed Maximum Baggage and/or Forward compartmen t (above floorboard) 270 or 300 lb. (+ 31) Optional Equipment (See NOTE 3) (Structural Limits) Rear compartmen t (aft to Sta. 170.00) 400 lb. (+150) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover to Sta. 170.00 400 lb. (+145) When Item 607 installed aft of Sta. 170.00 120 lb. (+180) For weight and balance information, refer to DOA Flight Manual. 3A16 Rev. 95 8 VI. Model 95-B55, Model 95-B55A (cont'd) Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L & R Main 25 ea. 22 ea. +75 L & R Aux. 31 ea. 31 ea. +93 Optional Fuel System (Item 108) L & R Main 40 ea. 37 ea. +75 L & R Aux. 31 ea. 31 ea. +93 S/N TC-371, TC-502 through TC-1607 Two leading edge 53 ea. wing 50 ea. wing +75 interconnected tanks with full fuel only in each wing Optional fuel system (Item 116) One leading edge 71 ea. wing 68 ea. wing +82 tanks interconnected with full fuel only with one box section tank in each wing S/N TC-1608 and up Optional fuel system (Item 118) One leading edge 71 ea. wing 68 ea. wing +82 tank interconnected with full fuel only with one box section tank in each wing S/N TC-1475 through TC-1480, TC-1575, TC-1579, TC-1584, TC-1587, TC-1593 only See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. ea. engine (+43) (includes 5.5 lb. unusable), total capacity 24 qt. See NOTE 1 for data on system oil. Control Surface Wing flaps Down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 10° Down 10° Elevator Up 10° Down 23° Rudder Right 25° Left 25° Serial Nos. Eligible TC-371; TC-502 a nd on, except TC-1393, TC-1394, TC-1395, TC-1396 and TC-1402. (TC-955 and on, see NOTE 3) Required Equipment Items 2(b) and (d) or (e) or 9(a) or (b), 101(d) and (h) or (l), 102(c), 103(b), 201, 202, 205, 206, 301, 302, 304, 401(v) and (gg or oo) or 401(x) and (gg or oo) or 401(ac) or 401(an), or 401(ab) and (gg or oo) or 401(ad) or 401(an), or 401(z) and (gg or oo) or 401(ae) or 401(an), or 401(hh) and (oo) or 401(af) or 401(an) (95-B55), or 401(kk) and (oo) or 401(ag) or 401(an) (95-B55A), or 401(nn) and (oo) or 401(ss) or 401(an), or 401(tt) or 401(al), or 401(ah) (95-B55, 95-B55A), 601(b) or (c) VII. Model 95-B55B, Baron, (Military T-42A), 4 PCLM (Normal or Utility Category), Approved August 26, 1964 Engines 2 Continental IO-470-L *Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2625 r.p.m. (260 hp.) Rev. 95 3A16 9 VII. Model 95-B55B (cont'd) Airspeed Limits Maneuvering 180 m.p.h. (156 knots) (CAS) Maximum structural crui sing 210 m.p.h. (182 knots) Never exceed 257 m.p.h. (223 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 165 m.p.h. (143 knots) C.G. Range (Landing (+81.0) to (+83.5) at 5100 lb. (Utility category) Gear Extended) (+81.0) to (+86. 0) at 5100 lb. (Normal category) (+77.5) to (+83.5) at 4740 lb. (Utility category) (+77.5) to (+86.0) at 4740 lb. (Normal category) (+74.0) to (+83.5) at 3800 lb . or less (Utility category) (+74.0) to (+86.0) at 3800 lb. or less (Normal category) Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 5100 lb. No. of Seats 4 (2 at +85, 2 at +121 or +136) or 5 (2 at +85, 2 at +121, 1 at +150) when Item 603(f) installed or 6 (2 at +85, 2 at +121, 2 at +150) when Item 603(g) installed Maximum Baggage and/or Forward compartmen t (above floorboard) 270 or 300 lb. (+ 31) Optional Equipment Rear compartment (aft to Sta. 170.00) 400 lb. (+150) (Structural Limits) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover to Sta. 170.00 400 lb. (+145) For weight and balance information, refer to DOA Flight Manual Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L & R Main 40 ea. 37 ea. +75 L & R Aux. 31 ea. 31 ea. +93 See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. ea. engine (+43) (includes 5.5 lb. unusable), total capacity 24 qt. See NOTE 1 for data on system oil Control Surface Wing flaps Down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 10° Down 10° Elevator Up 10° Down 23° Rudder Right 25° Left 25° Serial Nos. Eligible TF-1 and up. Prior to civil certif ication, 95-B55B airplanes that have been operated by the military must be modified by Beech Dwg. 96-002000. Required Equipment Items 2(b) and (d) or (e) or 9(a) or (b), 101(j) and (k) or (l), 102(c), 103(b), 201, 202, 205, 206, 301, 302, 304, 401(y) and (oo), 601(b) 3A16 Rev. 95 10 VIII. Model 95-C55, Baron, 4, 5 or 6 PCLM (Normal Category), Approved August 18, 1965 Model D55, Baron, 4, 5 or 6 PCLM (N ormal Category), Approved October 17, 1967 Model 95-C55A, Baron, 4, 5 or 6 PCLM (Normal Category), Approved October 31, 1968 Model D55A, Baron, 4, 5 or 6 PCLM (N ormal Category), Approved October 31, 1968 Model E55, Baron, 4, 5 or 6 PCLM (N ormal Category), Approved November 12, 1969 Model E55A, Baron, 4, 5 or 6 PCLM (Normal Category), Approved June 16, 1970 Engines Continental IO-520-C or IO-520-CB Two of either or one of each *Fuel 100/130 minimum grade aviation gasoline Engine Limits For airplanes prior to TE-1171 For all operations, 2700 r.p.m. (285 hp.) For airplanes TE-1171 and after with 2-bladed propellers Takeoff and continuous power 2700 r.p.m. (285 hp.) Normal operating power 2550 r.p.m. (276 hp.) For airplanes TE-1171 and after with 3-bladed propellers Takeoff and continuous power 2700 r.p.m. (285 hp.) Normal operating power 2650 r.p.m. (283 hp.) Airspeed Limits (CAS) (IAS) Maneuvering 180 m.p.h. (156 knots) 156 knots Maximum structural cruising 225 m.p.h. (195 knots) 195 knots Never exceed 257 m.p.h. (223 knots) 223 knots Flaps extended 15° 175 m.p.h. (152 knots) 152 knots 28° 140 m.p.h. (122 knots) 122 knots Landing gear extended 165 m.p.h. (143 knots) or (S/N TE-633 and up) 175 m.p.h. (152 knots) 152 knots C.G. Range (Landing (+78.0) to (+86.0) at 5300 lb. Gear Extended) (+76.9) to (+86.0) at 4990 lb. (See NOTE 5) (+74.0) to (+86.0) at 4200 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 5300 lb. or 4990 lb. (See NOTE 5) No. of Seats 4 (2 at +85, 2 at +121 or +136) or 5 (2 at +85, 2 at +121, 1 at +150) when Item 603(f) or (j) or (m) installed or 6 (2 at +85, 2 at +121, 2 at +150) when Item 603(g) or (k) or (n) installed Maximum Baggage and/or Forward compar tment (above floorboard) 300 lb. (+ 25) Optional Equipment Rear compartment (aft to Sta. 170.00) 400 lb. (+150) (Structural Limits) Aft baggage compartment 120 lb. (+180) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover to Sta. 170.00 400 lb. (+145) Pneumatic Pump Limits For airplanes TE-1084 thr ough TE-1201 equipped with Beech Kit 55-5019, pneumatic pumps are time limited for engine operation to 600 hours for flight into icing conditions. Rev. 95 3A16 11 VIII. Model 95-C55, Model D55, Model 95-C55A, Model D55A, Model E55, Model E55A (cont'd) Fuel Capacity Tank Capaci ty Gal. Usable Gal. Arm L & R Main 25 ea. 22 ea. +75 L & R Aux. 31 ea. 31 ea. +93 Optional fuel system (Item 108) L & R Main 40 ea. 37 ea. +75 L & R Aux. 31 ea. 31 ea. +93 S/N TC-350, TE-1 through TE-942, except TE-938 Two leading edge 53 ea. wing 50 ea. wing +75 interconnected tanks with full fuel only in each wing Tank Capacity Gal. Usable Gal. Arm Optional fuel system (Item 116) One leading edge 71 ea. wing 68 ea. wing +82 tank interconnected with full fuel only with one box section tank in each wing Op tional fuel system (Item 114) Two leading edge 86 ea. wing 83 ea. wing +83 tanks and one box with full fuel only section tank in each wing, all tanks interconnected S/N TE-938, TE-943 and on See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. ea. engine (+43) (includes 5.5 lb. unusable), total capacity 24 qt. See NOTE 1 for data on system oil. Control Surface Wing flap Approach 15° Full down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 10° Down 10° Elevator Up 10° Down 23° Rudder Right 25° Left 25° Serial Nos. Eligible Model 95-C55 and 95-C 55A: TC 350, TE-1 through TE-451, except TE-50 Model D55 and D55A: TE-452 through TE-767 Model E55 and E55A: TE-768 and on Required Equipment Items 2(f) and (e) or 5(a) or 10(a) or (b), 101(l) and (m) on IO-520-C engines or 101(l) and (q) on IO-520-CB engines, 102(d), 103(c) or (e), 201(e), 202(a), 205(f), 206(a), 301(i) and 304(b) (95-C55, 95-C55A, D55, D55A) or 301(m) or (q), 302(d), 401(aa) and (gg) or (oo) or 401(ar) (95-C55) or 401(ll) and (oo) or 401(ar) (95-C55A), or 401(cc) and (gg) or (oo) or 401(jj) and (oo) or 401(ar) (D55) or 401(mm) and (oo) or 401(ar) (D55A), or 401(pp) or 401(uu) or 401(aj) or 401(ar) or 401(as) (E55, E55A), or 405(a) (E55), or 405(d) (E55A), 601(b) or (c) Instrument Markings See NOTE 2(q). For airplane serial s not included, refer to the Airplane Flight Manual. 3A16 Rev. 95 12 IX. Model 56TC, Turbo Baron, 4, 5 or 6 PC LM (Normal Category), Approved May 19, 1967 Model A56TC, Turbo Baron, 4, 5 or 6 PCLM (Normal Category), Approved November 12, 1969 Engines 2 Lycoming TIO-541-E1B4 *Fuel 100/130 minimum grade aviation gasoline