# TCDS 5A4: Textron Aviation Inc. - Type: Type certificate data sheet - Status: Current - Holder: Textron Aviation Inc. - Revision: 65 - Revised: November 27, 2017 - Product: Aircraft, Small Airplane - Certification basis: Part 3, Part 21, Part 23, CAR 3 - Registered aircraft: 124, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/46/5e/465e3d1cdb2cd58295801462389d3d3df929c40e7abfc8169b3bb35540b73759 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/246C43961E017D52862581EF005D535F.0001 - Page: https://openairdocs.org/tcds/5A4 ## Models (14) As the data sheet lists them. - J50 - D50E-5990 - D50B - D50 - E50 - B50 - D50E - C50 - G50 - F50 - H50 - 50 - D50A - D50C ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Rev. No. 65 58 59 59 59 58 58 59 59 59 58 59 59 58 Page No. 15 16 17 18 19 20 21 22 23 24 25 26 27 28 Rev. No. 58 59 58 58 63 58 58 58 58 58 59 59 62 64 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 5A4 Revision 65 Textron Aviation 50 (L-23A) D50E-5990 B50 (L-23B) E50 (L-23D, C50 RL-23D) D50 (L-23E) F50 D50A G50 D50B H50 D50C J50 D50E November 27, 2017 TYPE CERTIFICATION DATA SHEET NO. 5A4 This data sheet which is a part of Type Certificate No. 5A4 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 50, Twin Bonanza, (Military L-23A), 6 PCLM (Normal Category), Approved May 25, 1951 Engines Two (2) Lycoming GO-435-C2 or GO-435-C2E Fuel 80/87 minimum grade aviation gasoline Engine limits (See also Takeoff (one minute), 3400 rpm. (260 hp.) limits under Items For all other operations, 3000 rpm. (240 hp.) 2(d) and 2(e)) Airspeed limits Maneuvering 165 mph. (144 knots) (TIAS) Maximum structural cruising 180 mph. (157 knots) Never exceed 227 mph. (197 knots) Design dive 270 mph. (234 knots) Flaps extended 125 mph. (109 knots) Landing gear extended 125 mph. (109 knots) 5A4 2 Rev. 65 I. Model 50 (cont’d) C.G. range (landing (+116.5) to (+124.6) at 5500 lb. gear extended) (+114.0) to (+124.6) at 4550 lb. or less Straight line variation between points given. 112 114 116 118 120 122 124 126 4500 4700 4900 5100 5300 5500 LB. INCHES Empty wt. C.G. range Forward compartment 100 lb. (using baggage Rear compartment 200 lb. placard) (+116.0) to (+116.7) at 4100 lb. (+114.3) to (+115.6) at 3625 lb. (+114.3) to (+115.3) at 3500 lb. Straight line variation between points given. When empty weight C.G. falls within this range, computation of critical fore and aft C.G. positions is unnecessary. Range is not valid for non-standard arrangements. For empty weight C.G. outside, both forward and rearward of the limits given, and for applicable range and pertinent baggage compartment placards, refer to weight and balance section of the operating limitations (loading schedule), or contact the manufacturer. 113 114 115 116 117 3500 3700 3900 4100 LB. INCHES Maximum weight 5500 lb. No. of seats 6 (3 at +116, 3 at +154) Maximum baggage Forward compartment 395 lb. (+ 60) (structural limits) Rear compartment 260 lb. (+193) (For loading instructions, see weight and balance report.) Fuel capacity 134 gal. (4 tanks in wings - two 44 gal. tanks at +139, two 23 gal. tanks at +117) See NOTE 1 for data on system fuel. Oil capacity 24 qt. (12 qt. in each engine at +72) See NOTE 1 for data on system oil. Rev. 65 3 5A4 I. Model 50 (cont’d) Control surface Wing flaps Down 30° movements Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 30° Rudder Right 30° Left 30° Serial Nos. eligible H-1 through H-11, LH-1 through LH-55 Required equipment Items 1, 101(a) and (b), 102(a) or (b), 103(a), 201(a), 202(a) or (b), 205(a), 206(a) or (b), 301(a), (b) or (c), 401(a) and 601 II. Model B50, Twin Bonanza, (Military L-23B), 8 PCLM (Normal Category), Approved July 31, 1953 Engines 2 Lycoming GO-435-C2 or GO-435-C2B or GO-435-C2D6 or GO-435-C2E Fuel 80/87 minimum grade aviation gasoline Engine limits Takeoff (one minute), 3400 rpm. (260 hp.) For all other operations, 3100 rpm. (245 hp.) Airspeed limits Maneuvering 165 mph. (144 knots) (TIAS) Maximum structural cruising 180 mph. (157 knots) Never exceed 227 mph. (197 knots) Design dive 270 mph. (234 knots) Flaps extended 125 mph. (109 knots) Landing gear extended 125 mph. (109 knots) C.G. range (landing (+116.8) to (+124.6) at 6000 lb. gear extended) (+114.0) to (+124.6) at 5350 lb. or less Straight line variation between points given 112 114 116 118 120 122 124 126 5700 5900 6100 5500 LB. INCHES 5300 5A4 4 Rev. 65 II. Model B50 (cont’d) Empty wt. C.G. range Forward compartment 100 lb. (using baggage placards) Rear compartment 200 lb. (+115.7) to (+117.4) at 4500 lb. (+114.3) to (+116.95) at 4253 lb. (+114.3) to (+116.3) at 3900 lb. Straight line variation between points given When empty weight C.G. falls within this range, computation of critical fore and aft C.G. positions is unnecessary. Range is not valid for non-standard arrangements. For empty weight C.G. outside, both forward and rearward of the limits given, and for applicable range and pertinent baggage compartment placards, refer to weight and balance section of the operating limitations (loading schedule), or contact the manufacturer. 113 114 115 116 117 3900 4100 4300 4100 LB. INCHES 118 Maximum weight 6000 lb. No. of seats Maximum 8, Normal 6 (3 at +116, 3 at +154) Maximum baggage Forward compartment 395 lb. (+ 60) (structural limits) Rear compartment 260 lb. (+193) (For loading instructions, see weight and balance report) Fuel capacity 134 gal. (4 tanks in wings - two 44 gal. tanks at +139, two 23 gal. tanks at +117) See NOTE 1 for data on system fuel. Oil capacity 24 qt. (12 qt. in each engine at +72) See NOTE 1 for data on system oil. Control surface movements Wing flaps Down 30° Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 21° Rudder Right 30° Left 30° Serial Nos. eligible CH-12 through CH-110, LH-56 through LH-95 Required equipment Items 2(d) or (e) and (b) with GO-435-C2 or -C2E engines, or 4 with -C2D6 engines, or 6 with -C2B engines, 101(a) or (b), 102(b), 103(a), 201(a), 202(a) or (b), 205(a), 206(a) or (b), 301(b) or (c), 302(a) or (b), 401(d) and 601 III. Model C50, Twin Bonanza, 8 PCLM (Normal Category), Approved October 13, 1954 Engines 2 Lycoming GO-480-F6 ot GO-480-F1A6 Fuel 80/87 minimum grade aviation gasoline Rev. 65 5 5A4 III. Model C50 (cont’d) Engine limits Takeoff (one minute), 3400 rpm. (275 hp.) For all other operations, 3100 rpm. (265 hp.) Airspeed limits Maneuvering 165 mph. (144 knots) (TIAS) Maximum structural cruising 180 mph. (157 knots) Never exceed 230 mph. (200 knots) Design dive 270 mph. (234 knots) Flaps extended 125 mph. (109 knots) Landing gear extended 125 mph. (109 knots) C.G. range (landing (+116.8) to (+124.6) at 6000 lb. gear extended) (+114.0) to (+124.6) at 5350 lb. or less Straight line variation between points given (Refer to Section II for figure.) Empty wt. C.G. range For standard arrangement, refer to empty weight C.G. range under Section II for Model B50. For range with 46 gal. auxiliary fuel tanks, refer to Item 106. Maximum weight 6000 lb. No. of seats Maximum 8, Normal 6 (3 at +116, 3 at +154) Maximum baggage Forward compartment 395 lb. (+ 60) (structural limits) Rear compartment 300 lb. (+193) (For loading instructions, see weight and balance report.) Fuel capacity 134 gal. (4 tanks in wings - two 44 gal. tanks at +139, two 23 gal. tanks at +117) See NOTE 1 for data on system fuel Oil capacity 24 qt. (12 qt. in each engine at +72) See NOTE 1 for data on system oil. Control surface movements Wing flaps Down 30° Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 21° Rudder Right 30° Left 30° Serial Nos. eligible CH-111 through CH-360 Required equipment Items 3, 101(a) and (b), 102(b), 103(a), 201(a), 202(a) or (b), 205(a), 206(a) or (b), 301(b) or (c), 302(a) or (b), 401 (e) or (i) and 601 IV. Model D50, Twin Bonanza, (Military L-23E), 8 PCLM (Normal Category), Approved December 6, 1955 Engines Two (2) Lycoming GO-480-C2C6 or GO-480-C2D6 (See Item 108 for optional engine.) Fuel 100/130 minimum grade aviation gasoline Engine limits Takeoff (one minute), 3400 rpm. (295 hp.) For all other operations, 3100 rpm. (285 hp.) 5A4 6 Rev. 65 IV. Model D50 (cont’d) Airspeed limits Maneuvering 175 mph. (152 knots) (TIAS) Maximum structural cruising 200 mph. (174 knots) Never exceed 252 mph. (219 knots) Design dive 280 mph. (243 knots) Flaps extended 135 mph. (117 knots) Landing gear extended 150 mph. (130 knots) C.G. range (landing (+116.8) to (+124.6) at 6300 lb. gear extended) (+114.0) to (+124.6) at 5350 lb. or less Straight line variation between points given 112 114 116 118 120 122 124 126 5300 5500 5700 5900 6100 6300 LB. INCHES Empty wt. C.G. range None Maximum weight 6300 lb. No. of seats Maximum 8, Normal 6 (2 or 3 at +116, 3 at +154) Maximum baggage Forward compartment 395 lb. (+ 60) (structural limits) Rear compartment 300 lb. (+193) (For loading instructions, see weight and balance report.) Fuel capacity 134 gal. (4 tanks in wings - two 44 gal. tanks at +139, two 23 gal. tanks at +117) See NOTE 1 for data on system fuel. Oil capacity 24 qt. (12 qt. in each engine at +72) See NOTE 1 for data on system oil. Control surface movements Wing flaps Down 30° Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tabs (S/N DH-1 through DH-143, except DH-18) (main surfaces in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 21° Rudder Right 30° Left 30° Tabs (S/N DH-18, DH-144 and up) (main surfaces in neutral) Aileron Up 7-1/2° Down 7-1/2° Tab, Anti-Servo (S/N DH-18, DH-144 and up) (main surface in extreme position) Aileron Up 14° Down 8° Serial Nos. eligible DH-1 through DH-154 Rev. 65 7 5A4 IV. Model D50 (cont’d) Required equipment Items 5, 101(a) and (b), 102(b), 103(a), 201(a), 202(a) or (b), 205(a), 206(a) or (b), 301(b) or (c), 302(a) or (b), 401(h) and 601 or 602 V. Model E50, Twin Bonanza, (Military L-23D, RL-23D), 8 PCLM (Normal Category), Approved December 1, 1956 Engines Two (2) Lycoming GSO-480-A1A6 (Military O-480-1) or GSO-480-B1B6 Fuel 100/130 minimum grade aviation gasoline Engine limits Straight line manifold pressure variation with altitudes shown HP RPM MP ALT Takeoff 340 3400 48.0 S.L. Takeoff 340 3400 44.5 8000 Maximum continuous 320 3200 45.0 S.L. Maximum continuous 320 3200 43.0 7500 Airspeed limits Maneuvering 185 mph. (161 knots) (TIAS) Maximum structural cruising 205 mph. (178 knots) Never exceed 270 mph. (235 knots) Design dive 300 mph. (261 knots) Flaps extended 150 mph. (130 knots) Landing gear extended 150 mph. (130 knots) C.G. range (landing (+118.0) to (+124.6) at 7000 lb. gear extended) (+114.0) to (+124.6) at 5350 lb. or less Straight line variation between points given 112 114 116 118 120 122 124 126 5000 5400 5800 6200 6600 7000 LB. INCHES Empty wt. C.G. range None Maximum weight 7000 lb. No. of seats Maximum 8, Normal 6 (2 or 3 at +116, 3 at +154) Maximum baggage Forward compartment 395 lb. (+ 60) (structural limits) Rear compartment 300 lb. (+193) (For loading instructions, see weight and balance report.) Fuel capacity 180 gal. (4 tanks in wings - two 44 gal. tanks at +139, two 46 gal. tanks at +127) See NOTE 1 for data on system fuel. Oil capacity 32 qt. (16 qt. in each nacelle at +103) See NOTE 1 for data on system oil. 5A4 8 Rev. 65 V. Model E50 (cont’d) Control surface movements Wing flaps Down 30° Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tab, Anti-Servo (main surface in extreme position) Aileron Up 14° Down 8° Tabs (main surface in neutral) Aileron Up 7-1/2° Down 7-1/2° Elevator Up 10° Down 21° Rudder Right 30° Left 30° Serial Nos. eligible EH-1 through EH-70 (LH-96 and on, L-23D), (RLH-1 and on, L-23D remanufactured), (LHC-1 and on, LHD-1 and on, RLHE-1, RLHE-2, LHE-3 and on - different radar versions of RL-23D). Prior to civil certification, L-23D and RL-23D airplanes that have been operated by the military services must be modified by Beech Dwg. 50-001016 and 50-001062, respectively. Required equipment Items 7, 101(c) and (d), 102(c), 103(b), 201(a), 202(a) or (b), 205(a), 206(a) or (b), 301(d) or (e), 302(a) or (b), 401(j) and 602 VI. Model D50A, Twin Bonanza, 8 PCLM (Normal Category), Approved October 29, 1957 Engines Two (2) Lycoming GO-480-G2D6 Fuel 100/130 minimum grade aviation gasoline Engine limits Takeoff (one minute), 3400 rpm. (295 hp.) For all other operations, 3100 rpm. (285 hp.) Airspeed limits Maneuvering 185 mph. (161 knots) (TIAS) Maximum structural cruising 205 mph. (178 knots) Never exceed 270 mph. (235 knots) Design dive 300 mph. (261 knots) Flaps extended 150 mph. (130 knots) Landing gear extended 150 mph. (130 knots) C.G. range (landing (+116.8) to (+124.6) at 6300 lb. gear extended) (+114.0) to (+124.6) at 5350 lb. or less Straight line variation between points given (Refer to Section IV for figure.) Empty wt. C.G. range None Maximum weight 6300 lb. No. of seats Maximum 8, Normal 6 (2 or 3 at +116, 3 at +154) Maximum baggage Forward compartment 395 lb. (+ 60) (structural limits) Rear compartment 300 lb. (+193) (For loading instructions, see weight and balance report.) Fuel capacity 134 gal. (4 tanks in wings - two 44 gal. tanks at +139, two 23 gal. tanks at +117) See NOTE 1 for data on system fuel. Oil capacity 24 qt. (12 qt. in each engine at +72) See NOTE 1 for data on system oil. Rev. 65 9 5A4 VI. Model D50A (cont’d) Control surface movements Wing flaps Down 30° Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 7-1/2° Down 7-1/2° Elevator Up 10° Down 21° Rudder Right 30° Left 30° Tabs, Anti-Servo (main surface in extreme position) Aileron Up 14° Down 8° Serial Nos. eligible DH-155 through DH-198 Required equipment Items 5, 101(a) and (b), 102(d), 103(a), 201(a), 202(a) or (b), 205(a), 206(a) or (b), 301(b) or (c), 302(a) or (b), 401(l) and 602 VII. Model F50, Twin Bonanza, 8 PCLM (Normal Category), Approved October 29, 1957 Engines Two (2) Lycoming GSO-480-B1B6 Fuel 100/130 minimum grade aviation gasoline Engine limits Straight line manifold pressure variation with altitudes shown HP RPM MP ALT Takeoff 340 3400 48.0 S.L. Takeoff 340 3400 44.5 8000 Maximum continuous 320 3200 45.0 S.L. Maximum continuous 320 3200 43.0 7500 Airspeed limits Maneuvering 185 mph. (161 knots) (TIAS) Maximum structural cruising 205 mph. (178 knots) Never exceed 270 mph. (235 knots) Design dive 300 mph. (261 knots) Flaps extended 150 mph. (130 knots) Landing gear extended 150 mph. (130 knots) C.G. range (landing (+118.0) to (+124.6) at 7000 lb. gear extended) (+114.0) to (+124.6) at 5350 lb. or less Straight line variation between points given (Refer to Section V for figure) Empty wt. C.G. range None Maximum weight 7000 lb. No. of seats Maximum 8, Normal 6 (2 or 3 at +116, 3 at +154) Maximum baggage Forward compartment 395 lb. (+ 60) (structural limits) Rear compartment 300 lb. (+193) (For loading instructions, see weight and balance report.) Fuel capacity 180 gal. (4 tanks in wings - two 44 gal. tanks at +139, two 46 gal. tanks at +127) See NOTE 1 for data on system fuel. 5A4 10 Rev. 65 VII. Model F50 (cont’d) Oil capacity 32 qt. (16 qt. in each nacelle at +103) See NOTE 1 for data on system oil. Control surface movements Wing flaps Down 30° Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tabs, Anti-Servo (main surfaces in extreme position) Aileron Up 14° Down 8° Tabs (main surfaces in neutral) Aileron Up 7-1/2° Down 7-1/2° Elevator Up 10° Down 21° Rudder Right 30° Left 30° Serial Nos. eligible FH-71 through FH-96 (except FH-94) Required equipment Items 7, 101(c) and (d), 102(c), 103(b), 201(a), 202(a) or (b), 205(a), 206(a) or (b), 301(d) or (e), 302(a) or (b), 401(m) and 602 VIII. Model D50B, Twin Bonanza, 8 PCLM (Normal Category), Approved November 10, 1958 Engines Two (2) Lycoming GO-480-G2D6 Fuel 100/130 minimum grade aviation gasoline Engine limits Takeoff (one minute), 3400 rpm. (295 hp.) For all other operations, 3100 rpm. (285 hp.) Airspeed limits Maneuvering 185 mph. (161 knots) (TIAS) Maximum structural cruising 205 mph. (178 knots) Never exceed 270 mph. (235 knots) Design dive 300 mph. (261 knots) Flaps extended 150 mph. (130 knots) Landing gear extended 150 mph. (130 knots) C.G. range (landing (+116.8) to (+124.6) at 6300 lb. gear extended) (+114.0) to (+124.6) at 5350 lb. or less Straight line variation between points given (Refer to Section IV for figure.) Empty wt. C.G. range None Maximum weight 6300 lb. No. of seats Maximum 8, Normal 6 (2 or 3 at +116, 3 at +154) Maximum baggage Forward compartment 395 lb. (+ 60) (structural limits) Rear compartment 300 lb. (+193) Rear compartment 125 lb. (+193) with Item 411 (Item 411) Optional baggage compartment 115 lb. (+223) (For loading instructions, see weight and balance report.) Fuel capacity 134 gal. (4 tanks in wings - two 44 gal. tanks at +139, two 23 gal. tanks at +117) See NOTE 1 for data on system fuel. Rev. 65 11 5A4 VIII. Model D50B (cont’d) Oil capacity 24 qt. (12 qt. in each engine at +72) See NOTE 1 for data on system oil. Control surface movements Wing flaps Down 30° Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tabs (main surfaces in neutral) Aileron Up 7-1/2° Down 7-1/2° Elevator Up 10° Down 21° Rudder Right 30° Left 30° Tabs, Anti-Servo (main surfaces in extreme position) Aileron Up 14° Down 8° Serial Nos. eligible DH-199 through DH-236 Required equipment Items 5, 101(a) and (b), 102(d), 103(a), 201(a), 202(a) or (b), 205(a), 206(a) or (b), 301(b) or (c), 302(a) or (b), 401(n) and 602 IX. Model G50, Twin Bonanza, 8 PCLM (Normal Category), Approved November 10, 1958 Engines Two (2) Lycoming IGSO-480-A1A6 Fuel 100/130 minimum grade aviation gasoline Engine limits Straight line manifold pressure variation with altitudes shown HP RPM MP ALT Takeoff 340 3400 48.0 S.L. Takeoff 340 3400 44.5 11,000 Maximum continuous 320 3200 45.0 S.L. Maximum continuous 320 3200 41.3 11,000 Airspeed limits Maneuvering 185 mph. (161 knots) (TIAS) Maximum structural cruising 205 mph. (178 knots) Never exceed 270 mph. (235 knots) Design dive 300 mph. (261 knots) Flaps extended 150 mph. (130 knots) Landing gear extended 150 mph. (130 knots) C.G. range (landing (+118.4) to (+124.6) at 7150 lb. gear extended) (+114.0) to (+124.6) at 5350 lb. or less Straight line variation between points given 112 114 116 118 120 122 124 126 5200 5600 6000 6400 6800 7200 LB. INCHES 5A4 12 Rev. 65 IX. Model G50 (cont’d) Empty wt. C.G. range None Maximum weight Landing 7000 lb. Takeoff 7150 lb. No. of seats Maximum 8, Normal 6 (2 or 3 at +116, 3 at +154) Maximum baggage Forward compartment 395 lb. (+ 60) (structural limits) Rear compartment 300 lb. (+193) Item 411 Optional baggage compartment 115 lb. (+223) Rear compartment 200 lb. (+193) (with Item 411) (For loading instructions, see weight and balance report.) Fuel capacity 180 gal. (4 tanks in wings - two 44 gal. tanks at +139, two 46 gal. tanks at +127) See NOTE 1 for data on system fuel Oil capacity 32 qt. (16 qt. in each nacelle at +103) See NOTE 1 for data on system oil Control surface Wing flaps Down 30° movements Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tab, Anti-Servo (main surface in extreme position) Aileron Up 14° Down 8° Tabs (main surfaces in neutral) Aileron Up 7-1/2° Down 7-1/2° Elevator Up 10° Down 21° Rudder Right 30° Left 30° Serial Nos. eligible GH-94, GH-97 through GH-119 Required equipment Items 7, 101(c) or (e) and (d), 102(c), 103(b), 201( a), 202(a) or (b), 205(a), 206(a) or (b), 301(d) or (e), 302(a) or (b), 401(o) or (p) and 602 X. Model H50, Twin Bonanza, 7 PCLM (Normal Category), Approved November 13, 1959 Engines Two (2) Lycoming IGSO-480-A1A6 Fuel 100/130 minimum grade aviation gasoline Engine limits Straight line manifold pressure variation with altitudes shown HP RPM MP ALT Takeoff 340 3400 48.0 S.L. Takeoff 340 3400 44.0 11,000 Maximum continuous 320 3200 45.0 S.L. Maximum continuous 320 3200 41.3 11,000 Airspeed limits Maneuvering 185 mph. (161 knots) (TIAS) Maximum structural cruising 205 mph. (178 knots) Never exceed 270 mph. (235 knots) Design dive 300 mph. (261 knots) Flaps extended 150 mph. (130 knots) Landing gear extended 150 mph. (130 knots) Rev. 65 13 5A4 X. Model H50 (cont’d) C.G. range (landing (+118.4) to (+125.6) at 7300 lb. gear extended) (+114.0) to (+125.6) at 5350 lb. or less Straight line variation between points given 112 114 116 118 120 122 124 126 5400 5800 6200 6600 7000 7400 LB. INCHES Empty wt. C.G. range None Maximum weight Landing 7000 lb. Takeoff 7300 lb. No. of seats Maximum 7, Normal 6 (crew at +116) (See loading instructions for passenger loading) Maximum baggage Forward compartment 395 lb. (+ 60) (structural limits) Rear compartment 200 lb. (+223) (For loading instructions, see weight and balance report.) Fuel capacity 180 gal. (4 tanks in wings - two 44 gal. tanks at +139, two 46 gal. tanks at +127) See NOTE 1 for data on system fuel Oil capacity 32 qt. (16 qt. in each nacelle at +103) See NOTE 1 for data on system oil Control surface movements Wing flaps Down 30° Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tabs, Anti-Servo (main surfaces in extreme position) Aileron Up 14° Down 8° Tabs (main surfaces in neutral) Aileron Up 7-1/2° Down 7-1/2° Elevator Up 10° Down 22° Rudder Right 30° Left 30° Serial Nos. eligible HH-120 through HH-149 Required equipment Items 7, 101(c) or (e) and (d), 102(c), 103(b), 201(a), 202(a) or (b), 205 (a), 206(a) or (b), 301(d) or (e), 302(a) or (b), 401(v) and 602 XI. Model D50C, Twin Bonanza, 7 PCLM (Normal Category), Approved November 13, 1959 Engines Two (2) Lycoming GO-480-G2D6 Fuel 100/130 minimum grade aviation gasoline 5A4 14 Rev. 65 XI. Model D50C (cont’d) Engine limits Takeoff (one minute), 3400 rpm. (295 hp.) For all other operations, 3100 rpm. (285 hp.) Airspeed limits Maneuvering 185 mph. (161 knots) (TIAS) Maximum structural cruising 205 mph. (178 knots) Never exceed 270 mph. (235 knots) Design dive 300 mph. (261 knots) Flaps extended 150 mph. (130 knots) Landing gear extended 150 mph. (130 knots) C.G. range (landing (+116.8) to (+125.6) at 6300 lb. gear extended) (+114.0) to (+125.6) at 5350 lb. Straight line variation between points given 112 114 116 118 120 122 124 126 5000 5400 5800 6200 6600 7000 LB. INCHES Empty wt. C.G. range None Maximum weight 6300 lb. No. of seats Maximum 7, Normal 6 (crew 2 at +116) (See loading instructions for passenger loading) Maximum baggage Forward compartment 395 lb. (+ 60) (structural limits) Rear compartment 300 lb. (+223) (For loading instructions, see weight and balance report.) Fuel capacity 134 gal. (4 tanks in wings - two 44 gal. tanks at +139, two 23 gal. tanks at +117) See NOTE 1 for data on system fuel. Oil capacity 24 qt. (12 qt. in each engine at +72) See NOTE 1 for data on system oil. Control surface Wing flaps Down 30° movements Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tabs (main surfaces in neutral) Aileron Up 7-1/2° Down 7-1/2° Elevator Up 10° Down 21° Rudder Right 30° Left 30° Tab, Anti-Servo (main surfaces in extreme position) Aileron Up 14° Down 8° Serial Nos. eligible DH-237 through DH-300 Required equipment Items 5, 101(a) and (b), 102(d), 103(a), 201(a), 202(a) or (b), 205(a), 206(a) or (b), 301(b) or (c), 302(a) or (b), 401(u) and 602 Rev. 65 15 5A4 XII. Model D50E, Twin Bonanza, 7 PCLM (Normal Category), Approved November 10, 1960 Model D50E-5990, Twin Bonanza, 7 PCLM (Normal Category), Approved March 21, 1974 Engines Two (2) Lycoming GO-480-G2F6 Fuel 100/130 minimum grade aviation gasoline Engine limits Takeoff (one minute), 3400 rpm. (295 hp.) For all other operations, 3100 rpm. (285 hp.) Airspeed limits Maneuvering 185 mph. (161 knots) (TIAS) Maximum structural cruising 205 mph. (178 knots) Never exceed 270 mph. (235 knots) Design dive 300 mph. (261 knots) Flaps extended 150 mph. (130 knots) Landing gear extended 150 mph. (130 knots) C.G. range (landing (+116.8) to (+125.6) at 6300 lb. gear extended) (+116.1) to (+125.6) at 5990 lb. (D50E -5990) (+115.5) to (+125.6) at 5700 lb. Straight line variation between points given Empty wt. C.G. range None Maximum weight 6300 lb. 5990 lb. (See NOTE 3) No. of seats Maximum 7, Normal 6 (crew 2 at +116) (See loading instructions for passenger loading) Maximum baggage Forward compartment 395 lb. (+ 60) (structural limits) Rear compartment 200 lb. (+223) (For loading instructions, see weight and balance report.) Fuel capacity 134 gal. (4 tanks in wings - two 44 gal. tanks at +139, two 23 gal. tanks at +117) See NOTE 1 for data on system fuel. Oil capacity 24 qt. (12 qt. in each engine at +72) See NOTE 1 for data on system oil. Control surface Wing flaps Down 30° movements Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tabs (main surfaces in neutral) Aileron Up 7-1/2° Down 7-1/2° Elevator Up 10° Down 25° Rudder Right 30° Left 30° Tabs, Anti-Servo (main surface in extreme position) Aileron Up 14° Down 8° Serial Nos. eligible DH-301 through DH-347 Required equipment Items 5, 101(a) and (b), 102(d), 103(a), 201(a), 202(a) or (b), 205(a), 206(a) or (b), 301(b) or (c), 302(a) or (b), 401(ee) and 602 5A4 16 Rev. 65 XIII. Model J50, Twin Bonanza, 7 PCLM (Normal Category), Approved November 16, 1960 Engines Two (2) Lycoming IGSO-480-A1B6 Fuel 100/130 minimum grade aviation gasoline Engine limits Straight line manifold pressure variation with altitudes shown HP RPM MP ALT Takeoff 340 3400 48.0 S.L. Takeoff 340 3400 44.0 11,000 Maximum continuous 320 3200 45.0 S.L. Maximum continuous 320 3200 41.3 11,000 Airspeed limits Maneuvering 185 mph. (161 knots) (TIAS) Maximum structural cruising 205 mph. (178 knots) Never exceed 270 mph. (235 knots) Design dive 300 mph. (261 knots) Flaps extended 150 mph. (130 knots) Landing gear extended 150 mph. (130 knots) C.G. range (landing (+118.4) to (+125.6) at 7300 lb. gear extended) (+114.0) to (+125.6) at 5350 lb. Straight line variation between points given 112 114 116 118 120 122 124 126 5400 5800 6200 6600 7000 7400 LB. INCHES Empty wt. C.G. range None Maximum weight Landing 7000 lb. Takeoff 7300 lb. No. of seats Maximum 7, Normal 6 (crew at +116) (See loading instructions for passenger loading.) Maximum baggage Forward compartment 395 lb. (+ 60) (structural limits) Rear compartment 200 lb. (+223) (For loading instructions, see weight and balance report.) Fuel capacity 180 gal. (4 tanks in wings - two 44 gal. tanks at +139, two 46 gal. tanks at +127) See NOTE 1 for data on system fuel Oil capacity 32 qt. (16 qt. in each nacelle at +103) See NOTE 1 for data on system oil Rev. 65 17 5A4 XIII. Model J50 (cont’d); Control surface movements Wing flaps Down 30° Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tabs, Anti-Servo (main surface in extreme position) Aileron Up 14° Down 8° Tabs (main surfaces in neutral) Aileron Up 7-1/2° Down 7-1/2° Elevator Up 10° Down 22° Rudder Right 30° Left 30° Serial Nos. eligible JH-150 through JH-176 Required equipment Items 7 or 10, 101(c) or (e) and (d), 102(c), 103(b), 201(a), 202(a) or (b), 205(a), 206(a) or (b), 301(d) or (e), 302(a) or (b) or (d), 401(ff) and 602 Specifications Pertinent to All Models Datum 125 in. forward of wing main spar centerline Leveling means Two screws provided on RH side of rear baggage compartment fuselage bulkhead. Plumb bob is used to level. Certification Basis Model 50 Part 3 of Civil Air Regulations effective November 1, 1949, Amendments 1 through 5. Models B50, C50, D50, D50A, D50B, D50C, D50E, E50 and F50 Part 3 of Civil Air Regulations, Amendments 1 through 8 (except 3.668 of Amendment 7). Model D50E-5990 Part 3 of Civil Air Regulations, Amendments 1 through 8 and Para. 23.25 of FAR 23 as amended through Amendment 7. Models G50, H50 and J50 Part 3 of Civil Air Regulations, Amendments 1 through 8 and Para. 3.242 of Amendment 14 (except 3.668 of Amendment 7). Production Basis Production Certificate No. 8. For all models except 50, B50 and S/N CH-111 through CH-352 of Model C50, delegation option manufacturer No. CE-2 authorized to issue airworthiness certificates under delegation option provisions of Part 21 of the Federal Aviation Regulations. Equipment A plus (+) or minus (-) sign preceding the weight of an item of equipment indicates net weight change when that item is installed. 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 (*). This symbol denotes that approval has been obtained by someone other than the aircraft manufacturer. An item so marked may not have been manufactured under a Federal Aviation Administration monitored or approved quality control system. Conformity must be determined if the item is not identified by a Form FAA-186, PMA or other evidence of FAA production approval. 5A4 18 Rev. 65 Specifications Pertinent to All Models (cont’d) Propeller and Propeller Accessories (except deicing equipment) 1. Two Beech constant speed propeller installations (a) Beech B200-115 hub with B200-247-96 blades and ................................................... 62 lb. ea. (+ 47) B200-236 hydraulic motor (for Model 50 only) Pitch settings at 36 in. sta.: low 10.5°, high not under 33.5° Diameter: not over 96 in., not under 94-1/16 in. (b) Beech B200-250 hydraulic governor assembly ............................................................ 3 lb. ea. (+ 90) (c) Beech 50-960009 propeller spinner ............................................................................. 5 lb. ea. (+ 44) 2. Two Beech full-feathering propeller installations (a) Beech 214-100 hub with 214-211-96 blades, 214-200 ................................................ 85 lb. ea. (+ 47) transmission unit and 268-203 spinner (for Model 50 only) Pitch settings at 36 in. sta.: Positive stops in propeller hub low 10-1/2°, high 87° - 93° Stops in 214-200 transmission unit low (hydraulic) 11-1/4° low (electrical) 40° - 50° high (electrical) 83° - 93° Diameter: not over 96 in., not under 94-1/16 in. (Beech 50-960010 spinner eligible in place standard 268-203 spinner; with 50-960010 spinner, propeller weight is 83 lb. ea. (+47)) or (d) Beech 214-102 hub with 272-234-98 aluminum alloy blades ...................................... 102 lb. ea. (+ 47) 214-200 transmission unit and 268-203 or 272-102 spinner (for Model 50 or B50) Pitch settings at 36 in. sta.: Positive stops in propeller hub: low 13°, high 87° - 93° Stops in 214-200 transmission unit: low (hydraulic) 13-3/4° low (electrical) 40° - 50° high (electrical) 83° - 85° Diameter: not over 98-1/2 in., not under 97-1/2 in. Engine limits: takeoff (one minute), 3400 rpm. (260 hp.) for all other operations, 3100 rpm. (245 hp.) Lycoming GO-435-C2 or -C2E engines with nameplate specifying 245 max. continuous hp. at 3100 rpm., Beech 50-939129 oil radiators (Item 102(b)), Beech 50-950030 exhaust stacks, engine tachometers marked with red arc between 2875 and 3075 rpm. indicating the restriction against continuous engine operation in this speed range are required with this propeller. Airplane Flight Manual Supplement (Item 401(b)) also required for Model 50. or (e) Beech 272-100 hub with 272-234-98 aluminum alloy blades, ..................................... 102 lb. (+ 47) 272-200 transmission unit and 268-203 or 272-102 spinner, (for Model 50 or B50) Pitch settings at 36 in. sta.: Positive stops in propeller hub: low 13°, high 87° - 93° Stops in 214-200 transmission unit: low (hydraulic) 13-3/4° low (electrical) 40° - 50° high (electrical) 83° - 85° Diameter: not over 98-1/2 in., not under 97-1/2 in. Engine limits: Takeoff (one minute), 3400 rpm. (260 hp.) For all other operations, 3100 rpm. (245 hp.) Rev. 65 19 5A4 Specifications Pertinent to All Models (cont’d) Propeller and Propeller Accessories (except deicing equipment) (cont’d) 2. (e) Lycoming GO-435-C2 or -C2E engines with nameplate specifying 245 max. continuous hp. at 3100 rpm., Beech 50-939129 oil radiators (Item 102(b)), Beech 50-950030 exhaust stacks, engine tachometers marked with a red arc between 2875 and 3075 rpm. indicating the restriction against continuous engine operation in this speed range are required with this propeller. Airplane Flight Manual Supplement (Item 401(b)) also required for Model 50. and (b) Beech B200-250 hydraulic governor assembly ............................................................ 3 lb. ea. (+ 90) 3. Two Beech full-feathering propeller installations (for Model C50 only) (a) Beech 279-100 hub with 279-234-94.5 aluminum alloy blades and spinner ............... 88 lb. ea. (+ 46) Pitch settings at 36 in. sta.: low 13.5°, high 84° Diameter: not over 94-1/2 in., not under 94 in. or not over 94-1/2 in., not under 92 in. Engine tachometers are to be marked with a red arc (1) between 2250 and 2500 rpm. for 94-1/2 to 94 inch diameter propellers or (2) between 2200 and 2500 rpm. for 94-1/2 to 92 inch diameter propellers indicating restriction against continuous engine operation in the pertinent speed range. or (d) Beech 279-100 hub with 279-207-98 aluminum alloy blades and spinner .................. 88 lb. ea. (+ 46) Pitch settings at 36 in. sta.: low 13.5°, high 84° Diameter: not over 98-1/2 in., not under 97-1/2 in. or not over 94-1/2 in., not under 92 in. Engine tachometers are to be marked with a red arc between 2200 and 2500 rpm. indicating the restriction against continuous engine operation in this speed range. Airplane Flight Manual, Item 401(e), revised May 10, 1955, or item 401(i) dated November 18, 1955, required with this propeller. and (b) Propeller governor, Beech 279-220 (Woodward 210085) ........................................... 3 lb. ea. (+ 53) and (c) Feathering pump, Pesco 111059-011-01 ..................................................................... 7 lb. ea. (+ 86) 4. Two Beech full-feathering installations (for Model B50 with Lycoming GO-435-C2D6 engines) (a) Beech 279 hub with 279-234-94-1/2 aluminum alloy blades and spinner 88 lb. ea. (+ 46) Pitch settings at 36 in. sta.: low 13.5°, high 84° Diameter: not over 94-1/2 in., not under 92 in. Engine tachometers marked with red arc between 2250 and 2450 rpm. indicating restriction against continuous operation in this speed range, and Airplane Flight Manual Supplement, Item 401(d), revised October 21, 1954, are required with this propeller. (b) Propeller governor, Beech 279-220 (Woodward 210085) ........................................... 3 lb. ea. (+ 55) (c) Feathering pump, Pesco 111059-011-01 ..................................................................... 7 lb. ea. (+ 86) (d) Feathering oil tank installation (See Note 1 for unusable oil) ...................................... 7 lb. ea. (+ 77) 5. Two Hartzell full-feathering, three-blade propeller installations (D50, D50A, D50B, D50C, D50E) (a) Hartzell HC-B3XF-2A or HC-A3XF-2A or HC-A3VF-2A hub with .......................... 103 lb. ea. (+ 47) 9333C-3 aluminum alloy blades and spinner Pitch settings at 30 in. sta.: low 16°, high 85.5° Diameter: not over 90 in., not under 89 in. (b) Propeller governor (Woodward 210190 or 210180 or 210150 or ................................ 4 lb. ea. (+ 55) RW 210150 or ZRW 210150 or Z210150 or 210125 or RW 210125) 5A4 20 Rev. 65 Specifications Pertinent to All Models (cont’d) Propeller and Propeller Accessories (except deicing equipment) (cont’d) *6. Two Hartzell full-feathering propeller installations (for Model B50 with GO-435-C2B engines) (a) Hartzell HC-83X20-2C/9333C-3 three-blade full-feathering ...................................... 102 lb. ea. (+ 44) propeller with Aero Design Spinner Dome, Dwg. 3640014 and Hartzell bulkhead C-807-3 Pitch settings at 30 in. sta.: low 16°, high 85° Diameter: not more or less than 90 inches (b) Propeller governor, Hamilton Standard 1Q12 Petrolite Corp., St. Louis, Mo. , ........... 3 lb. ea. (+ 53) FAA Approved Airplane Flight Manual Supplement dated March 27, 1956, required 7. Two Hartzell full-feathering, three-blade propeller installations (E50, F50, G50, H50) (a) Hartzell HC-93Z20-2C1 or HC-B3Z20-2A hub with 10151-8 or................................ 125 lb. ea. (+ 43) 10151-8R aluminum alloy blades and 836 spinner Pitch settings at 30 in. sta.: low 16°, high 87° Diameter: not over 93 in., not under 90 in. (b) Propeller governor (Woodward 210190) ..................................................................... 4 lb. ea. (+ 50) 8. Propeller unfeathering system in accordance with Beech Dwg. 50-960058 ........................ 13 lb. ea. (+ 49) (eligible with Items 7 and 10 only) 9. Propeller unfeathering system in accordance with Beech Dwg. 50-960057 ........................ 13 lb. ea. (+103) (eligible with Item 5 only) 10. Two Hartzell full-feathering, three-blade propeller installations (J50) (a) Hartzell HC-93Z20-2C1 or HC-B3Z20-2A hub with 10151-8 or................................ 125 lb. ea. (+ 43) 10151-8R aluminum alloy blades and 836 spinner Pitch settings at 30 in. sta.: low 16°, high 87° Diameter: not over 93 in., not under 90 in. (b) Propeller governor (Woodward 210365) ..................................................................... 4 lb. ea. (+ 50) Engine and Engine Accessories (Fuel and Oil Systems) 101. Fuel pumps (a) Two electric booster pumps: Adel 24000, 29172 or 56881; ............................................. 3 lb. ea. (+142) Beech 50-920073; or Pesco 122723-112-01 or 122723-113-01 (b) Two engine-driven pumps: Candler-Hill CH4502-1, Thompson TF-900-1,..................... 3 lb. ea. (+ 88) TFD-900-1 or TF-900-3; Pesco 2P-R400-BRD or 2P-R400-BRD-5; Romec RG-9570; or Beech 50-921560-1 (c) Four electric booster pumps: Pesco 122723-112-01 or 122723-113-01 or 122723-113-02; or Adel 29172-1 (Two in auxiliary tanks) ...... .............................................................................................. 3 lb. ea. (+146) (Two in main tanks) ............ .............................................................................................. 3 lb. ea. (+142) (d) Two engine-driven pumps: Pesco 2P-R400-BRD or 2P-R400-BRD-5; .......................... 3 lb. ea. (+ 83) or Romec RG-9570; or Candler-Hill CH4502-1; or Thompson TF-900-1; or Beech 50-921560-3 or 50-921560-23 or 50-389141-7 (e) Four electric booster pumps, Adel 56881-1 (Two in auxiliary tanks) ...... .............................................................................................. 3 lb. ea. (+146) (Two in main tanks) ............ .............................................................................................. 3 lb. ea. (+142) Item 401(p) required for G50 Rev. 65 21 5A4 Specifications Pertinent to All Models (cont’d) Engine and Engine Accessories (Fuel and Oil Systems) (cont’d) 102. Oil radiators (See Note 1 for data on system oil) (a) Two Harrison 8517694 ....... .............................................................................................. 6 lb. ea. (+ 66) or (b) Two Beech 50-939129 ........ .............................................................................................. 8 lb. ea. (+ 66) (c) Two Harrison 8525330 ....... .............................................................................................. 8 lb. ea. (+ 93) (d) Four: two Beech 50-939129 and...................................................................................... 8 lb. ea. (+ 66) two Harrison 8527362 ............................................................................................ 2 lb. ea. (+ 55) 103. Two carburetor air cleaners (a) Beech 189187 ...... ............. .............................................................................................. 1 lb. ea. (+ 64) (b) Air Maze 120993 or 122172 1 lb. ea. (+ 65) 104. Two vacuum pumps (a) Aro A513DB or Pesco 3P-194F, Garwin G-450 or G-455 ................................................ 4 lb. ea. (+ 92) (50, B50, C50, D50, D50A, D50B, D50C, D50E) (b) Pesco 3P-194F, Garwin G-450 or G-455 (E50, F50, G50, H50, J50) ............................... 4 lb. ea. (+ 84) 105. Two starters (a) Eclipse Pioneer (type E80): 756-54, 756-56, 756-60C, 756-62C, 756-62D ..................... 19 lb. ea. (+ 91) or 756-162D; Beech 50-91081 (50, B50, C50, D50, D50A, D50B, D50C, D50E) (b) Bendix 756-10C or Garwin G-760 (E50, F50, G50, H50, J50) ........................................ 19 lb. ea. (+ 83) 106. Two 46 gal. auxiliary fuel tanks at (+127), replacing two standard 23 gal. auxiliary fuel tanks ...... ............. .............................................................................................. +22 lb. (+137) (a) For Model C50 (See Note 1 for data on system fuel) Empty wt. C.G. range (using baggage placards) Straight line variation between points given Forward compartment 100 lb. Rear compartment 200 lb. (+116.1) to (+117.1) at 4500 lb. +114.3) to (+116.5) at 4210 lb. +114.3) to (+115.9) at 3900 lb. (b) or Models D50, D50A, D50B, D50C, D50E (See Note 1 for data on system fuel)) (c), (d), (e), (f) Delete 107. Two 71 gal. auxiliary fuel tanks at (+129), replacing two standard 46 gal. auxiliary ................ +27 lb. (+136) fuel tanks. See Note 1 for data on system fuel (E50, F50, G50, H50, J50) 108. Engines (a) Lycoming GO-480-G2D6 (same limits as for GO-480-C2C6 and C2D6) Two Harrison C-54934 or 8527362 oil coolers, 2 lb. ea. (+55) must be installed in accordance with Beech instructions. Item 401(k) required to replace 401(h). 5A4 22 Rev. 65 Specifications Pertinent to All Models (cont’d) Engine and Engine Accessories (Fuel and Oil Systems) (cont’d) 109. Two Aerojet Model 15NS-250 installed per Beech Mod. C.O. B37082 or Beech kit Dwg. 50-001079 for Models B50, C50, D50, D50A, D50B, E50, F50, G50; per Beech Dwg. 50-910209 or 50-001079 for Models D50C and H50; per Beech Dwg. 50-910209-19 or 50-001079 for Model D50E; per Beech Dwg. 50-910209-15 or 50-001079 for Model J50. (1) Engines charged 98 lb. (+141) (2) Engines not charged 56 lb. (+140) (3) Engines removed 14 lb. (+130) Airplane Flight Manual Supplements as follows required: B50, C50 (S/N CH-111 - CH-352); P/N 50-001080 dated August 27, 1959 C50 (S/N CH-353 - CH-360), D50, D50A, D50B, E50, F50; P/N 50 -001081 dated August 2, 1959, or 50-590127-7 dated April 20, 1962, or later. G50, P/N 50-590116-11 revision dated June 30, 1959, or 50 -590127-7 dated April 20, 1962, or later. H50, J50, P/N 50-590126-7 revision dated November 11, 1960, or 50-590127-7 dated April 20, 1962, or later. D50C, P/N 50-590127-7 dated November 10, 1959, or 50-590127-7 dated April 20, 1962, or later. D50E, P/N 50-590127-7 revision dated October 31, 1960, or later. The gross takeoff weight of B50, C50, D50, D50A, D50B, D50C, D50E, E50, F50 and G50 is increased 100 lb., and the H50 or J50 is increased 50 lb. requiring extension of the forward and aft weight C.G. envelope lines to the values shown below: B50, C50 (+117.2) to (+124.6) at 6100 lb. D50, D50A, D50B (+117.1) to (+124.6) at 6400 lb. D50C (+117.1) to (+125.6) at 6400 lb. D50E (+117.0) to (+125.6) at 6400 lb. E50, F50 (same as G50 (+118.2) to (+124.6) at 7100 lb. with Item 110) G50 (+118.6) to (+124.6) at 7100 lb. H50, J50 (+118.5) to (+125.6) at 7350 lb. 110. Fuel injection engines (a) Two Lycoming IGSO-480-A1A6 installed per Beech Dwg. 50-001085 for Models E50 and F50 S/N eligible EH-1 through EH-70 and FH-71 through FH-96 except FH-94. Limitations: same as set forth in Sections V and VII of this specification except as noted below: C.G. range (landing (+119.6) to (+124.6) at 7300 lb. gear extended) (+114.0) to (+124.6) at 5350 lb. or less Straight line variation between points given. Maximum weight Landing 7000 lb. Takeoff 7300 lb. Airplane Flight Manual Supplement dated September 20, 1963, for Models E50 and F50, Beech P/N 130364. 111. Heated fuel vents - two outboard heated fuel cell vents and two Negligible weight inboard heated fuel cell vents installed per Beech Dwg. 50-001090 (Models 50, B50, C50, D50, D50A, D50B, D50C, D50E, E50, G50, H50 and J50) 112. Two induction air heaters and temperature gage installed per Beech Dwg. ............................... 9 lb. (+112) 50-910235 and 50-590075 or 65-001074 (E50, F50 with Item 110, G50, H50, J50). Airplane Flight Manual Supplement P/N 130042 dated January 15, 1962, or later required. 113. Induction system alcohol and anti-icing (a) Per Beech Dwg. 50-960069 or 65-001076 (with Item 501) for G50, H50, J50. ................ 10 lb. (+105) Airplane Flight Manual Supplement P/N 130062 dated January 10, 1962, or later required. (b) Per Beech Dwg. 50-960069-53 (without Item 501) including pump, ................................ 35 lb. (+111) 3 gal tank, lines and 20 lb. fluid (fluid arm is +114) for J50. Airplane Flight Manual Supplement, P/N 130062, dated January 10, 1962, or later required. Rev. 65 23 5A4 Specifications Pertinent to All Models (cont’d) Engine and Engine Accessories (Fuel and Oil Systems) (cont’d) 114. Rocket engines (1) Engines charged .... ............. .............................................................................................. 106 lb. (+141) (2) Engines not charged ........... .............................................................................................. 58 lb. (+140) (3) Engines removed ... ............. .............................................................................................. 14 lb. (+130) (a) Two Aerojet Model 12NS-350 installed per Beech Dwg. 50-910209 or kit Dwg. 50-001079. Airplane Flight Manual Supplements as follows required: B50, C50 (S/N CH-111 through CH-352), P/N 50-001080 dated February 27, 1964, or March 9, 1965. C50 (S/N CH -353 through CH-360) D50, D50A, D50B, D50C, D50E, E50, F50, G50, H50 and J50, P/N 50 -590127-7 dated February 28, 1964, or March 8, 1965. (b) Two Aerojet Model 12NS-350CBA installed per Beech Dwg. 50-910209 or kit Dwg. 50-001079. Airplane Flight Manual Supplements as follows required: B50, C50 (S/N CH-111 through CH-352) P/N 50-001080 dated March 9, 1965. C50 (S/N CH-353 through CH-360), D50, D50A, D50B, D50C, D50E, E50, F50, G50, H50 and J50 P/N 50 -590127-7 dated March 8, 1965. The gross takeoff weight of B50, C50, D50, D50A, D50B, D50C, D50E, E50, F50, G50 is increased 100 lb. and of H50 and J50 is increased 50 lb. requiring extension of forward and aft weight C.G. envelope lines to the values shown below: B50, C50 (+117.2) to (+124.6) at 6100 lb. D50, D50A, D50B (+117.1) to (+124.6) at 6400 lb. D50C (+117.1) to (+125.6) at 6400 lb. D50E (+117.0) to (+125.6) at 6400 lb. E50, F50 (same as G50 with (+118.2) to (+124.6) at 7100 lb. Item 110) G50 (+118.6) to (+124.6) at 7250 lb. H50, J50 (+118.5) to (+125.6) at 7350 lb. Landing Gear 201. Two main wheel-brake assemblies, 24 x 7.7, Type VII ............................................................. 25 lb. ea. (+142) (a) Goodyear Model L24 x 7.7 HEM wheel assembly No. 530840 or 530840M-1 or 9531395 or 9542891 or A9542623 Brake assembly No. 9530303 202. (a) Two main wheel 6-ply rating tires, 8.50-10 Type III (with regular tubes) ......................... 26 lb. ea. (+142) or (b) Two main wheel 8-ply rating tires, 8.50-10, Type III (with regular tubes) ........................ 27 lb. ea. (+142) 205. One nose wheel, 6.50-10, Type III ............................................................................................ 8 lb. (+ 13) (a) Goodyear Model 610NBM Assembly No. 9521176 or 9544061 206. (a) One nose wheel 4-ply rating tire, 6.50-10, Type III (with regular tube) ............................ 14 lb. (+ 13) or (b) One nose-wheel 6-ply rating tire, 6.50-10, Type III (with regular tube) ............................ 15 lb. (+ 13) Electrical Equipment 301. Generators (a) Two 75 a. Eclipse 1298-1 (50, S/N H-1, H-3, H-4 only) ................................................... 23 lb. ea. (+ 91) (b) Two 50 a. Leece-Neville 24225 with Beech condenser support bracket ............................ 20 lb. ea. (+ 91) (c) Two 75 a. Bendix 1273-1 or Beech 50-910227-7 (D50, D50A, D50B, D50C, D50E) ..... 32 lb. ea. (+ 91) (d) Two 100 a. Bendix 901-9B . .............................................................................................. 27 lb. ea. (+ 82) (e) Two 50 a. Bendix 1345-3-A or 30824-1A ......................................................................... 15 lb. ea. (+ 82) (f) Two 125 a. alternator-rectifiers installed per Beech Dwg. 65-001078 for Models E50, F50, G50, H50, J50 ................................................................................. 29 lb. ea. (+ 82) 5A4 24 Rev. 65 Specifications Pertinent to All Models (cont’d) Electrical Equipment (cont’d) 302. Battery (a) Two 12 v. 37 a. hr. ............. .............................................................................................. 34 lb. ea. (+101) or (b) Two 12 v. 33 a. hr. ............. .............................................................................................. 28 lb. ea. (+104) or (c) Two Sonotone, (1) 22000 type CA24A and (1) 22000 type CA24B, ................................ 52 lb. (+104) installed per Beech Dwg. 50-001089 for Models 50, B50 and C50 (S/N CH-111 through CH-352), Item 401(z) required. (d) Two Sonotone, (1) 22000 type CA24A and (1) 22000 type CA24B, ............................... 52 lb. (+104) installed per Beech Dwg. 50-001089 for Models C50 (CH-353 through CH-360), D50, D50A, D50B, D50C, D50E, E50, F50, G50, H50 and J50. Item 401(y) required. 303. Two landing lights, 4523 General Electric................................................................................. 1 lb. ea. (+113) *304. Anti-collision light installed per Aircraftsmen Dwg. 54AED50-19 ........................................... 3 lb. ea. (+323) 305. Anti-collision light installed per Beech Dwg. 50-364224 .......................................................... 3 lb. ea. (+325) 306. Dual anti-collision lights (a) Installed per Beech Mod. C.O. B38030 ............................................................................. 5 lb. (+234) (Models D50, D50A, D50B, D50C, E50, F50, G50 and H50) (b) Installed per Beech Mod. C.O. B54450 (Models D50C, H50) .......................................... 6 lb. (+234) (c) Installed per Beech Dwg. 50-364258 (Models D50E, J50) ............................................... 5 lb. (+234) 307. Anti-collision light installed per Beech Dwg. 50-001098) ........................................................ 3 lb. (+140) (Models 50, B50, C50, D50, D50A, D50B, D50C, E50, F50, G50, H50) Interior Equipment 401. FAA Approved Airplane Flight Manual (AFM) or Airplane Flight Manual Supplement (AFMS) as noted below: (FAA Approved AFM or AFMS of previous dates also acceptable provided latest manual or supplement not required by optional equipment item). (a) FAA Approved AFM dated January 2, 1953, for Model 50. (b) FAA Approved AFMS revision dated February 10, 1954, for Model 50, pertinent full-feathering metal propellers, Item 2(d) or (e). (c) FAA Approved AFMS dated March 31, 1952, required with Item 405(a) or (b). (d) FAA Approved AFM dated September 10, 1953, or revision dated October 21, 1954, for Model B50, (Revision dated October 21, 1954, required with Item 4). (e) FAA Approved AFM dated October 12, 1954, for Model C50; latest revision dated May 10, 1955, required on airplanes with S/N CH-297 through CH-352. (f) Deleted May 14, 1962. (g) FAA Approved AFMS dated August 5, 1954, required with Item 405(d) for Model B50. (h) DMCR Approved AFM revised February 15, 1957, for Model D50. (i) DMCR Approved AFM dated November 18, 1955, for Model C50, S/N CH-353 through CH-360. (j) DMCR Approved AFM dated December 1, 1956, for Model E50. (Revision dated June 7, 1957, or later required with GSO-480-B1B6 engine). Revision dated July 31, 1964, or later required when rounded tip blades (identified as 10151 -8R) installed. (k) DMCR Approved AFM dated November 18, 1955, and revised August 1, 1957, or later required with Item 108(a). (l) DMCR Approved AFM dated October 25, 1957, for Model D50A. (m) DMCR Approved AFM revised February 17, 1958, for Model F50. Revision dated July 31, 1964, or later required when rounded tip blades (identified as 10151 -8R) installed. (n) DMCR Approved AFM dated November 6, 1958, for Model D50B. (o) DMCR Approved AFM dated April 16, 1963, for Model G50. Revision dated July 31, 1964, or later required when rounded tip blades (identified as 10151-8R) installed. (p) DMCR Approved AFM dated February 22, 1963, for Model G50 required with Item 101(e). Revision dated July 31, 1964, or later required when rounded tip blades (identified as 10151 -8R) installed. Rev. 65 25 5A4 Specifications Pertinent to All Models (cont’d) Interior Equipment (cont’d) 401. (q) Deleted December 4, 1961. (r) Deleted December 4, 1961. (s) DMCR Approved AFMS dated September 1, 1959, required with Item 110 for E50 and F50 only. (t) Deleted December 4, 1961. (u) DMCR Approved AFM dated November 10, 1959, revised April 21, 1960, for Model D50C. (v) DMCR Approved AFM dated February 22, 1963, for Model H50. Revision dated July 31, 1964, or later required when rounded tip blades (identified as 10151-8R) installed. (w) Deleted December 4, 1961. (x) Deleted December 4, 1961. (y) DMCR Approved AFMS dated November 20, 1959 (C50, D50, D50A, D50B, D50C, E50, F50, G50 and H50); revision dated November 11, 1960 (D50E and H50) required with Item 302(d). (z) FAA Approved AFMS dated November 20, 1959, required with Item 302(c) for Models 50, B50 and C50 (S/N CH-111 through CH-352). (aa) DMCR Approved AFMS revised December 20, 1960, required with Item 503. (bb) DMCR Approved AFMS dated April 5, 1960 (C50, D50, D50A, D50B, D50C, E50, F50, G50 and H50), revision dated November 11, 1960 (D50E and J50) required with Item 603. (cc) DMCR Approved AFM for Model H50 revised August 3, 1960, required with Item 406. (dd) DMCR Approved AFM for Model D50C revised August 3, 1960, required with Item 406. (ee) DMCR Approved AFM dated August 6, 1962, or later for Model D50E or DMCR Approved AFM dated October 25, 1960, and revised February 22, 1961, for D50E (S/N's DH -301 through DH-332), or DOA AFM dated October 16, 1973, for Model D50E-5990. (ff) DMCR Approved AFM dated February 22, 1963, for Model J50. Revision dated July 31, 1964, or later required when rounded tip blades (identified as 10151-8R) installed. (gg) DMCR Approved AFMS dated November 11, 1960, required with Item 502(c). (hh) FAA Approved AFMS dated May 2, 1955, required with Item 502(a)(1). (ii) FAA Approved AFMS dated May 10, 1955, required with Item 502(a)(2). (jj) DMCR Approved AFMS dated December 30, 1959, required with Item 502(b). 402. Beech 50-571010-298 cabin heaters (modified Stewart-Warner model 978-MC-24 or 979B-1.) ....... ....... ...... ............. .............................................................................................. 18 lb. (+113) 403. Beech 50-555015 cabin heater (modified surface combustion heater model 83A28), Beech 50-554098 blower and Beech 50-554010 connecting duct. ............................................ 24 lb. (+ 47) 404. Two 3-minute parachute flares, Kilgore-International Wiley SA-8 (Model 50, S/N H-2 through H-5 only). .................................................................................... 49 lb. (+130) 405. Automatic pilot installation (a) Lear L-2C according to Aircraftsmen, Inc. Dwg. 52-ACH-11 and Beech Dwg. 50-000001. (Model 50 only). Item 401(c) required. ................................... 56 lb. (+147) (b) Lear L-2C according to Aircraftsmen, Inc. Dwg. 52-ACH-111 and Beech Dwg. 50-000002. (Model 50 only). Item 401(c) required. ............................ 58 lb. (+160) *(c) Lear L-2C according to Lear Dwg. 700200, Rev. D (1350B approach coupler and 2203D altitude controller eligible but not included in above weight). (B50 and C50 only). AFM Supplement dated December 2, 1954 (B50) or April 6, 1962 (B50 and C50), required. ......................................................................................... 59 lb. (+213) 5A4 26 Rev. 65 Pertinent to All Models (cont’d) Interior Equipment (cont’d) 405. *(d) Lear L-5 according to Lear Dwg. 700252B (Model B50 only) Item 401(g) required. Servo slip clutch stall torque in in.-lb. ±10%: ................................ 87 lb. (+206) L-2C (Item a) L-2C (Item b) L-2C (Item c) L-5 (Item d) Rudder 90 175 175 175 Aileron 40 75 75 75 Elevator 20 40 18 18 The following placard should be installed in a conspicuous place near the automatic pilot controller in full view of the pilot: "See Flight Manual for Autopilot Operations and Limitations." (e) SP-3 per Beech Dwg. 50-500019 or 50-001116 (Retro-Fit Kits) (B50, C50, D50, D50A, D50B, D50C, D50E, E50, F50, G50, H50, J50). AFM Supplement, P/N 130017 dated November 3, 1961, required. .......................................... 33 lb. (+207) (f) SP-3 with altitude hold per Beech Dwg. 50-500019 or 50-001116 (Retro-Fit Kits) (B50, C50, D50, D50A, D50B, D50C, D50E, E50, F50, G50, H50, J50). AFM Supplement P/N 130017 dated November 3, 1961, require d. .............. 38 lb. (+212) (g) Sperry course director coupler per Beech Dwg. 50-500019 or 50-001116 (Retro-Fit Kits) (D50E and J50). Eligible with Items 405(e) or (f) when used in conjunction with ARC CD-3 or CD-4 course directors. ....................................... 5 lb. (+248) 406. Dual control column (T-type) per Beech 35-524575-8. Item 401(cc) required for Model H50, Item 401(dd) required for Model D50C. .......................................... Use act. wt. change 407. High pressure, continuous flow, oxygen system (a) Installed per Beech Dwg. 50-560000 ................................................................................. 43 lb. (+196) (b) Installed per Beech Dwg. 50-560000-113 ......................................................................... 43 lb. (+204) (c) Installed per Beech Mod. C.O. B37091 (Models D50, D50A, D50B, E50, F50, G50). ...... .............................................................................................. 44 lb. (+203) (d) Installed per Beech Dwg. 50-560000-115 (Models D50C, H50). ...................................... 43 lb. (+204) (e) Installed per Beech Dwg. 50-560000-191 (Models D50E, J50). ....................................... 43 lb. (+214) (f) Installed per Beech Dwg. 50-001122-3 or -5 or -7 or -9 and 414-001058 or 414-001059. ............................................................................................. Use act. wt. change 408. 7-place couch and chair arrangement per Beech One chair ............................... 33 lb. (+163) Mod. C.O. B12740 (replacing standard 3-place One 3-place couch ................. 48 lb. (+166) rear seat) (Models D50, E50, D50A, D50B, F50, G50). See Item 414 for subsequent models. 409. Double reclining chair arrangement per Beech Two chairs ............................. 66 lb. (+163) Mod. C.O. B8413 (replacing standard 3-place rear seat) (Models D50, E50, D50A, D50B, F50, G50). 410. AVQ-50 weather avoidance radar (a) Installed per Beech Mod. C.O. B30865 (Model E50 (L-23D), F50, D50A, D50B, G50) ...... ............. ............................................... .............................................. 107 lb. (+119) (b) Installed per Beech Mod. C.O. B42757 (Model D50C, D50E, H50, J50). ........................ 112 lb. (+ 62) 411. Baggage compartment chair and couch arrangement per Beech Mod. C.O. B32305 (D50B and G50, except S/N GH-94). ........ .............................................. 28 lb. (+223) 413. Reclining chair installation per Beech Mod. One chair ............................... 36 lb. (+192) C.O. B37089 - to be used with Item 109 only. (Models D50, D50A, D50B, E50, F50, G50 only). 414. 7-place couch and chair arrangement per Beech Dwg. 50-534300 (replacing two rear left-hand seats). Models H50, D50C, D50E and J50 eligible .................... 48 lb. (+166) Rev. 65 27 5A4 Specifications Pertinent to All Models (cont’d) Interior Equipment (cont’d) 415. 8-place seating arrangement per Beech Dwg. 50-001150 for Models B50, C50, D50, D50A, D50B, E50, F50, G50. ...................................................... Use act. wt. change De-Icing Equipment (Propellers, Wing and Windshield) 501. Propeller anti-icer (with propellers, Items 2(d), 2(e), 3, 4, 5 or 7) (a) 3 gal. tank, pump, lines and 20 lb. of fluid (fluid arm is +114).......................................... 32 lb. (+110) (b) Propeller slinger and blade feed strip installation .............................................................. 1 lb. ea. (+ 49) or (c) Propeller slinger ring and blade feed strip installation (with Item 7 only). ........................ 1 lb. ea. (+ 44) 502. Goodrich type 21 deicer boots (a) Installed per Beech Dwg. 50-970000 for: (1) Model 50, S/N H-1 Flight Supplement, Item 401(hh) ............................................... 140 lb. (+152) (2) Model 50, B50, C50 (S/N CH-111 through CH-296 only) Flight Manual Supplement, Item 401(ii) required. . ................................................... 130 lb. (+153) (3) Model C50 (S/N CH-297 and up), D50, D50A, D50B, E50, F50, G50. .................... 130 lb. (+153) (b) Installed per Beech Mod. C.O. B44414 for Models H50 and D50C. ................................ 130 lb. (+153) D50C. Flight Manual Supplement, Item 401(jj), required. (c) Installed per Beech Mod. C.O. B58747 for Models D50E and J50 Flight Manual Supplement, Item 401(gg) required. ........................................................... 130 lb. (+153) 503. Goodrich type 23 (lightweight) deicer boot installation according to: (a) Beech Dwg. 50-970002, 50-970003 and 50-001114 for H50, J50, D50C, D50E. Airplane Flight Manual Supplement 401(aa) revised December 20, 1960, required. ....... 76 lb. (+130) or (b) Beech Dwg. 50-001114 for Models D50C and H50. Airplane Flight Manual Supplement 401(aa) revised December 20, 1960, required. ............................................. 76 lb. (+130) or (c) Beech Dwg. 50-001105 for Models C50 (S/N's CH-353 through CH-360) D50, D50A, D50B, E50, F50 and G50. Airplane Flight Manual Supplement 401(aa) revised December 20, 1960, required. .............................................................................. 76 lb. (+130) or (d) Beech Dwg. 65-001106-5 for Models G50, H50, J50. Airplane Flight Manual Supplement P/N 130356 dated December 6, 1963, required. ..... 81 lb. (+150) or (e) Beech Dwg. 65-001106-3 for Models E50, F50, G50, H50, J50 Airplane Flight Manual Supplement P/N 130356 dated December 6, 1963, required. The following are required when this item is installed: Item 501(a) and (b) or (c), 602, 603, heated pitot head per Beech Dwg. 50 -320010 and approved antenna masts. . ........................................................................................... 89 lb. (+151) 504. Goodrich electrothermal propeller deicer installation per Beech Dwg. 50-960066 for Model J50. DMCR Approved Airplane Flight Manual Supplement P/N 50-590130-13 dated March 8, 1961, required. .. .............................................................................................. 12 lb. (+ 61) Miscellaneous (not listed above) 601. Safe flight stall warning indicator No. 151 602. Safe flight stall warning indicator 168-2 (heated) or 168-3 (heated) when Item 503 installed. 603. Alternate instrument static air source per Beech Dwg. 50-320010 ............................................ Negligible weight for Models D50C, D50E, H50 and J50, or 50-001106 for Models B50, C50, D50, D50A, D50B, E50, F50 and G50. Item 401(bb) or Flight Manual Supplement dated May 12, 1961, required. 5A4 28 Rev. 65 NOTE 1. Current weight and balance report together with 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. The certificated empty weight and corresponding center of gravity locations must include system (undrainable) oil (not included in oil capacity) and unusable fuel (not included in usable fuel) as fo llows: (a) Models 50 and B50 Fuel 4 lb. at (+134) Oil 5 lb. at (+ 68) with Item 102(a) or 6 lb. at (+ 68) with Item 102(b) (b) Models C50, D50, D50A, Fuel 4 lb. at (+134) (standard arrangement) D50B, D50C, D50E or 14 lb. at (+139) with Item 106 Oil 12 lb. at (+ 79) (including 6 lb. feathering oil) (C50 only) or 6 lb. at (+ 68) (D50, D50A, D50B) (c) Models E50, F50, G50, Fuel 14 lb. at (+139) (standard arrangement) H50, J50 12 lb. at (+132) with Item 107 Oil 8 lb. at (+ 76) NOTE 2. The following placard must be displayed: (a) In front of and in clear view of the pilots: "This airplane must be operated as a normal category airplane in compliance with the Airplane Flight Manual. No acrobatic maneuvers including spins approved." (b) On fuel selector panel: "Use 100/130 or next higher grade fuel only." "Press to purge fuel line." When optional auxiliary tanks installed, "Use auxiliary fuel in level flight only." NOTE 3. Model D50E, when modified per Beech Kit No. 50-5001-1 and re-identified as Model D50E-5990, eligible for 5990 lb. maximum gross weight. ---- END ---- ``` ## ADs (20, in force first) - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022 - [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 2005 - [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005 - [AD 2001-23-17](https://openairdocs.org/ad/2001-23-17): GNS 430 units · Cessna 172, 182, 206 and 209 more. Effective Dec 28, 2001 - [AD 99-05-13 R1 WD](https://openairdocs.org/ad/99-05-13-R1-WD): Withdrawal of AD 99-05-13 · Beech B17B, B17L, B17R (Army UC-43H) and 107 more. Effective Jul 5, 2000 - [AD 98-21-21 R1](https://openairdocs.org/ad/98-21-21-R1): Electric Inflatable Door Seals · Cessna 17-30, 17-30A, 17-31 and 267 more. Effective May 1, 2000 - [AD 97-14-15](https://openairdocs.org/ad/97-14-15): Cabin Side Door And Utility Door Handle · Textron 36, 50, 56TC and 41 more. Effective Sep 2, 1997 - [AD 85-22-05](https://openairdocs.org/ad/85-22-05): Nuts and Bolts Replacement · Textron 100, 200, 200C and 60 more. Effective Nov 12, 1985 - [AD 84-09-01](https://openairdocs.org/ad/84-09-01): Window Emergency Egress Provision · Textron 35, 36, 50 and 60 more. Effective May 25, 1984 - [AD 79-01-02 R2](https://openairdocs.org/ad/79-01-02-R2): In-Flight Fires · Textron 65, 65-80, 65-88 and 17 more. Effective Sep 22, 1980 - [AD 79-13-01](https://openairdocs.org/ad/79-13-01): Powerplant Fire Detection/Containment · Lycoming IGSO-540-A1A or -B1A engines (Tom Roland STC SA76SW). Effective Jul 5, 1979 - [AD 78-11-01](https://openairdocs.org/ad/78-11-01): Powerplant Fires · Textron 65, 65-80, 65-88 and 11 more. Effective Feb 6, 1979 - [AD 78-22-05](https://openairdocs.org/ad/78-22-05): Elevator Control Push Rods · Textron 100, 50, 65 and 31 more. Effective Nov 6, 1978 - [AD 78-05-06](https://openairdocs.org/ad/78-05-06): Flexible Fuel Cells · Cessna 180, 182, 185 and 98 more. Effective Jun 30, 1978 - [AD 62-08-03](https://openairdocs.org/ad/62-08-03): Control Wheels · Textron 35, 35-33, 35-A33 and 33 more. Effective Jul 9, 1970 - [AD 66-02-01](https://openairdocs.org/ad/66-02-01): Air Conditioners · Beechcraft 56TC, 58, 58A and 39 more. Effective Feb 10, 1966 - [AD 64-24-02](https://openairdocs.org/ad/64-24-02): Wing Attach Bolts · Textron 65, D50E and J50. Effective Nov 20, 1964 - [AD 58-13-02](https://openairdocs.org/ad/58-13-02): Tail Light Assembly · Textron B50, C50, D50 and 2 more - [AD 99-05-13](https://openairdocs.org/ad/99-05-13) (historical): Fuel Tank Selector · Beech B17B, B17L, B17R (Army UC-43H) and 107 more. Effective Apr 19, 1999 ## Registered aircraft by registry model (OpenAirDocs) - [Beech D-50](https://openairdocs.org/model/beech-d-50): 21 aircraft (registry code 1152512) - [Beech C-50](https://openairdocs.org/model/beech-c-50): 20 aircraft (registry code 1152510) - [Beech D50E](https://openairdocs.org/model/beech-d50e): 18 aircraft (registry code 1152522) - [Beech D50C](https://openairdocs.org/model/beech-d50c): 16 aircraft (registry code 1152520) - [Beech B50](https://openairdocs.org/model/beech-b50): 13 aircraft (registry code 1152506) - [Beech E50](https://openairdocs.org/model/beech-e50): 11 aircraft (registry code 1152524) - [Beech D50A](https://openairdocs.org/model/beech-d50a): 5 aircraft (registry code 1152516) - [Beech D50B](https://openairdocs.org/model/beech-d50b): 5 aircraft (registry code 1152518) - [Beech H50](https://openairdocs.org/model/beech-h50): 5 aircraft (registry code 1152534) - [Beech J50](https://openairdocs.org/model/beech-j50): 4 aircraft (registry code 1152536) - [Beech 50](https://openairdocs.org/model/beech-50): 2 aircraft (registry code 1152502) - [Beech/Bond E50](https://openairdocs.org/model/beech-bond-e50): 2 aircraft (registry code 1152523) - [Beech F50](https://openairdocs.org/model/beech-f50): 1 aircraft (registry code 1152530) - [Beech G50](https://openairdocs.org/model/beech-g50): 1 aircraft (registry code 1152532) - [Beech D50E-5990](https://openairdocs.org/model/beech-d50e-5990): 0 aircraft (registry code 1152894) - [Douglas C-50](https://openairdocs.org/model/douglas-c-50): 0 aircraft (registry code 3021410) - [Hawker Hunter MK 50](https://openairdocs.org/model/hawker-hunter-mk-50): 0 aircraft (registry code 4230303) ## STCs approved under this data sheet (235, first 50) - [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of existing instrument panel lights dimmer control.. TCW Technologies, LLC - [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC - [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC - [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc. - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc. - [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc. - [STC SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position Light System, and applicable associated power supplies. Whelen Aerospace Technologies - [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc. - [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc. - [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc. - [STC SA01240SE](https://openairdocs.org/stc/SA01240SE): Installation of secondary voltage indication system. Visual Instruments LLC - [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC - [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC - [STC SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc. - [STC SA02532AT](https://openairdocs.org/stc/SA02532AT): Installation of subject Michelin tires on appropriate aircraft. For Michelin 5, 6, 8, and 10-inch rim diameter tires on General Aviation Aircraft.. Michelin North America Inc. - [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine - [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine - [STC SA1686WE](https://openairdocs.org/stc/SA1686WE): Installation of Vibration Isolation Products (VIP) engine mount P/Ns VIP 50525-1 and VIP 50545-1 on various aircraft as shown on FAA Approved Model List (AML) No. SA1686WE.. FTG, Inc. - [STC SA1904WE](https://openairdocs.org/stc/SA1904WE): Installation of Vibration Isolation Products (VIP) engine mount P/N VIP-50804-10 on various aircraft as shown on FAA Approved Model List (AML) No. SA1904WE.. FTG, Inc. - [STC SA390GL](https://openairdocs.org/stc/SA390GL): Install aircraft wheel and brake conversion kit, P/N. 199-88. Kaman Corporation Aircraft Wheel and Brake LLC - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA02254AK](https://openairdocs.org/stc/SA02254AK): Installation of "Single Screen", "2 or 3 Screen", "Dual Screen", or "4 or 6 screen". Genesys Aerosystems Inc. - [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC - [STC SA09856AC](https://openairdocs.org/stc/SA09856AC): Installation of BendixKing Aerowave 100 In-flight Data Link System for non-essential, non-required aircraft Cabin Systems & Equipments. Honeywell International Inc (Bendix King) - [STC SA09902AC](https://openairdocs.org/stc/SA09902AC): Installation of BendixKing KFD 900 Flight Display System. Honeywell International Inc. (Bendix King) - [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King) - [STC SA10822SC](https://openairdocs.org/stc/SA10822SC): Installation of EFD1000 Primary Flight Display. Aspen Avionics Inc. - [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation - [STC SA4240WE](https://openairdocs.org/stc/SA4240WE): Installation of inflatable door seal.. TALCO Aviation Corp. - [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc - [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc - [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation - [STC SA1031CE](https://openairdocs.org/stc/SA1031CE): Installation of King Radio KFC 300Automatic Flight Control System. (D50E S/N DH-333 only). Honeywell International Inc - [STC SA872CE](https://openairdocs.org/stc/SA872CE): SN # DH 320: Installation of Bendix/King KFC 300 Automatic Flight Control System.. Honeywell International Inc - [STC SA01560WI-D](https://openairdocs.org/stc/SA01560WI-D): Installation of the Honeywell KFD 840 Primary Flight Display System.. Honeywell International Inc - [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc - [STC SA00344BO PAGE 1](https://openairdocs.org/stc/SA00344BO%20PAGE%201): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [STC SA615EA](https://openairdocs.org/stc/SA615EA): Installation of a Whelen Anti-Collision Strobe Light System as replacement for originally installed anti-collision lights.. Whelen Aerospace Technologies - [STC SA00744DE](https://openairdocs.org/stc/SA00744DE): Installation of the Automatic Dependent Surveillance Broadcast (ADS-B) Out Equipment using a Trig Avionics TT31 Transponder and an approved position sensor. Peregrine - [STC SA00765DE](https://openairdocs.org/stc/SA00765DE): Installation of Automatic Dependent Surveillance Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine - [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation - [STC SA02153LA-D PAGE 1](https://openairdocs.org/stc/SA02153LA-D%20PAGE%201): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc. - [STC SA02503AK](https://openairdocs.org/stc/SA02503AK): Installation of AMSAFE State of the Art Restraint System (SOARS) inflatable restraints. AMSAFE Inc. - [STC SA02013CH](https://openairdocs.org/stc/SA02013CH): Installation of Avidyne Corporation Traffic Advisory System (TAS). Avidyne Corporation - [STC SA01828SE](https://openairdocs.org/stc/SA01828SE): Installation of J.P. Instruments (JPI) EDM-960 Primary Engine Data Management System. J. P. Instruments - [STC SA01835WI](https://openairdocs.org/stc/SA01835WI): Installation of Trig Avionics TY-96 or TY-97 VHF Communications Radio. Peregrine - [STC SA00024NY](https://openairdocs.org/stc/SA00024NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K007 on single or multi-engine fixed wing light aircraft incorporating Lycoming reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation All 235: https://openairdocs.org/tcds/5A4/stcs.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.