# TCDS 3A21: Textron Aviation Inc. - Type: Type certificate data sheet - Status: Current - Holder: Textron Aviation Inc. - Revision: 50 - Revised: November 18, 2021 - Product: Aircraft, Small Airplane - Certification basis: Part 23, CAR 3 - Registered aircraft: 3,252, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/59/9d/599d896e2ba92f656fe30b855a275972dbc5013cc471345683b2e7be0ff9da57 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/376CF0AE3D6AEAAA862587950056344E.0001 - Page: https://openairdocs.org/tcds/3A21 ## Models (28) As the data sheet lists them. - 210J - P210N - 210D - 210R - T210M - 210 - 210M - 210-5A (205A) - 210H - T210R - 210B - 210E - T210F - 210-5 (205) - 210L - T210G - 210A - 210G - T210N - T210L - P210R - T210H - 210K - 210C - 210F - T210J - T210K - 210N ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 3A21 Revision 50 Textron Aviation Inc 210 210K 210A T210K 210B 210L 210C T210L 210D 210M 210E T210M 210F 210N T T210F P210N 210G T210N T T210G 210R 210H P210R T T210H T210R 210J 210-5 (205) T T210J 210-5A (205A) November 18, 2021 TYPE CERTIFICATE DATA SHEET NO. 3A21 This data sheet which is part of Type Certificate No.3A21 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, Kansas 67215 Type Certificate Holder Record Cessna Aircraft Company transferred to Textron Aviation Inc. on July 29, 2015 I. Model 210, 4 PCLM (Normal Category), Approved April 20, 1959 Engine Continental IO-470-E *Fuel 100/130 minimum grade aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 b.hp.) Propeller and 1. (a) Hartzell HC-A2XF-1/8433-2 Propeller Limits Diameter: not over 82 in., not under 80 in. Pitch settings at 30 in. sta.: low 13.5°, high 28.0° (b) Cessna spinner 0752006 or 2. (a) McCauley D2A36C33/90M-8 or D2A34C49/90A-8 or D2A34C58/90AT-8 Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 10.8°, high 25.8° (b) Cessna spinner 0752004 3. Woodward hydraulic governor 210270, 210280, 210340 or 210345 Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev.No. 50 30 30 27 47 29 47 47 47 47 47 27 47 47 47 47 40 40 44 44 Page No. 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 Rev.No. 44 30 30 27 27 50 27 29 27 27 27 27 31 31 34 36 40 48 44 44 Page No. 41 42 43 44 45 Rev.No. 44 44 46 46 46 3A21 Page 2 of 45 Rev. 50 I. Model 210 (cont’d) *Airspeed Limits (CAS) Never exceed 200 m.p.h. (174 knots) Maximum structural cruising 175 m.p.h. (152 knots) Maneuvering 130 m.p.h. (113 knots) Flaps extended 110 m.p.h. ( 96 knots) Landing gear operating speed 160 m.p.h. (139 knots) Landing gear extension speed 160 m.p.h. (139 knots) C.G. Range (Landing (+38.4) to (+46.5) at 2900 lb. Gear Extended) (+34.5) to (+46.5) at 2550 lb. or less Straight line variation between points given. Moment change due to retracting landing gear (+2456 in.-lb.) Empty Wt. C.G. Range None *Maximum Weight 2900 lb. No. of Seats 2 (2 at +36, 2 at +70) Maximum Baggage 120 lb. (+95) Fuel Capacity 65 gal. (55 gal. usable); two 32.5 gal. tanks in wings at +48. See NOTE 1 for data on unusable fuel Oil Capacity 12 qt. (-19.4), 6 qt. usable See NOTE 1 for data on undrainable oil Control Surface Wing flaps Up 0° Down 38° +2°, -1° Movements Ailerons Up 20° ±2° Down 14° ±2° Elevator Up 26°30' ±1° Down 22° ±1° Elevator tab Up 25° +1°, -0° Down 15° +1°, -0° Rudder Right 24° ±1° Left 24° ±1° (measured parallel to 0.0 W.L.) Serial Nos. Eligible Model 210: 618, 57001 through 57575 (1960 Model) II. Model 210A, 4 PCLM (Normal Category), Approved June 14, 1960 Engine Continental IO-470-E *Fuel 100/130 minimum grade aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 b.hp.) Propeller and 1. (a) Hartzell HC-A2XF-1/8433-2 Propeller Limits Diameter: not over 82 in., not under 80 Pitch settings at 30 in. sta.: low 13.5°, high 28.0° (b) Cessna spinner 0752006 or 2. (a) McCauley D2A36C33/90M-8 or D2A34C49/90A-8 or D2A34C58/90AT-8 Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 10.8°, high 25.8° (b) Cessna spinner 0752004 3. Woodward hydraulic governor 210270, 210280, 210340, 210345 Rev. 50 Page 3 of 45 3A21 II. Model 210A (cont’d) *Airspeed Limits (CAS) Never exceed 200 m.p.h. (174 knots) Maximum structural cruising 175 m.p.h. (152 knots) Maneuvering 130 m.p.h. (113 knots) Flaps extended 110 m.p.h. ( 96 knots) Landing gear operating speed 160 m.p.h. (139 knots) Landing gear extended speed 160 m.p.h. (139 knots) C.G. Range (Landing (+38.4) to (+44.4) at 2900 lb. Gear Extended) (+33.7) to (+44.4) at 2250 lb. or less Straight line variation between points given. Moment change due to retracting landing gear (+2456 in.-lb.) Empty Wt. C.G. Range None *Maximum Weight 2900 lb. No. of Seats 4 (2 at +36, 2 at +70) Maximum Baggage 120 lb. (+103) Fuel Capacity 65 gal. (55 gal. usable); two 32.5 gal. tanks in wings at +48. See NOTE 1 for data on unusable fuel Oil Capacity 12 qt. (-19.4), 6 qt. usable See NOTE 1 for data on undrainable oil Control Surface Wing flaps Up 0° Down 38° +2°, -1° Movements Ailerons Up 20° ±2° Down 14° ±2° Elevator Up 26°30' ±1° Down 22° ±1° Elevator tab Up 10° +2°, -0° Down 25° +2°, -0° Rudder Right 24° ±1° Left 24° ±1° (measured parallel to 0.0. W.L.) Serial Nos. Eligible Model 210A: 616, 21057576 through 21057840 (1961 Model) III. Model 210B, 4 PCLM (Normal Category), Approved June 27, 1961 Model 210C, 4 PCLM (Normal Category), Approved June 14, 1962 Engine Continental IO-470-S *Fuel 100/130 minimum grade aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 b.hp.) Propeller and 1. (a) Hartzell HC-A2XF-1/8433-2 Propeller Limits Diameter: not over 82 in., not under 80 in. Pitch settings at 30 in. sta.: low 13.5°, high 28.0° (b) Cessna spinner 0752006 or 2. (a) McCauley D2A36C33/90M-8 or D2A34C49/90A-8 or D2A34C58/90AT-8 Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 10.8°, high 25.8° (b) Cessna spinner 0752004 3. Woodward hydraulic governor 210270, 210280, 210340, 210345, 210451, 210452 3A21 Page 4 of 45 Rev. 50 III. Model 210B, Model 210C (cont’d) *Airspeed Limits (CAS) Never exceed 225 m.p.h. (196 knots) Maximum structural cruising 190 m.p.h. (165 knots) Maneuvering 132 m.p.h. (115 knots) Flaps extended 110 m.p.h. ( 96 knots) Landing gear operating speed 160 m.p.h. (139 knots) Landing gear extended speed 160 m.p.h. (139 knots) C.G. Range (Landing (+39.2) to (+45.0) at 3000 lb. Gear Extended) (+33.0) to (+45.0) at 2250 lb. or less Straight line variation between points given. Moment change due to retracting landing gear (+2456 in.-lb.) Empty Wt. C.G. Range None *Maximum Weight 3000 lb. No. of Seats 4 (2 at +36, 2 at +70) Maximum Baggage 120 lb. (+103) Fuel Capacity 65 gal. (63.4 gal. usable); two 32.5 gal. tanks in wings at +48. See NOTE 1 for data on unusable fuel Oil Capacity 12 qt. (-19.4), 6 qt. usable. See NOTE 1 for data on undrainable oil Control Surface Wing flaps Up 0° Down 40° +1°, -2° Movements Ailerons Up 20° ±2° Down 14° ±2° Elevator Up 26°30' ±1° Down 18° ±1° Elevator tab Up 20° +1°, -0° Down 20° +1°, -0° Rudder Right 24° ±1° Left 24° ±1° (measured parallel to 0.0 W.L.) Serial Nos. Eligible Model 210B: 21057841 through 21058085 (1962 Model) Model 210C: 21058086 through 21058139 and 21058141 through 21058220 (1963 Model) IV. Model 210-5 (205), 6 PCLM (Normal Category), Approved June 14, 1962 Model 210-5A (205A), 6 PCLM (Normal Category), Approved July 19, 1963 Engine Continental IO-470-S *Fuel 100/130 minimum grade aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 b.hp.) Propeller and 1. (a) Ha rtzell HC-A2XF-1A13.5/8433-2 Propeller Limits Diameter: not over 82 in., not under 80 in. Pitch settings at 30 in. sta.: low 13.5°, high 28.0° (b) Cessna spinner 0752614 or 2. (a) McCauley D2A36C33/90M-8 or D2A34C49/90A-8 or D2A34C58/90AT-8 Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 10.8°, high 25.8° (b) Cessna spinner 0752614 3. Woodward hydraulic governor 210270, 210280, 210340, 210345, 210451, 210452 Rev. 50 Page 5 of 45 3A21 IV. Model 210-5 (205), Model 210-5A (205A) (cont’d) *Airspeed Limits (CAS) Never exceed 210 m.p.h (182 knots) Maximum structural cruising 170 m.p.h. (148 knots) Maneuvering 138 m.p.h. (120 knots) Flaps extended 110 m.p.h. ( 96 knots) C.G. Range (Landing (+40.5) to (+47.4) at 3300 lb. Gear Extended) (+33.0) to (+47.4) at 2250 lb. or less Straight line variation between points given. Empty Wt. C.G. Range None *Maximum Weight 3300 lb. No. of Seats 6 (2 at +36, 2 at +69, 2 at +100) Maximum Baggage Reference weight and balance data Fuel Capacity 65 gal. (63.4 gal. usable); two 32.5 gal. tanks in wings at +48. See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. (-19.4), 6 qt. usable. See NOTE 1 for data on undrainable oil. Control Surface Wing flaps Up 0° Down 40° +1°, -2° Movements Ailerons Up 20° ±2° Down 14° ±2° Elevator Up 26°30' ±1° Down 18° ±1° Elevator tab Up 20° +1°, -0° Down 20° +1°, -0° Rudder Right 24° ±1° Left 24° ±1° (measured parallel to 0.0. W.L.) Serial Nos. Eligible Model 210-5 (205) : 641, 205-0001 through 205-0480 (1963 Model) Model 210-5A (205A) : 205-0481 through 205-0577 (1964 Model) V. Model 210D, 4 PCLM (Normal Category), Approved July 19, 1963 Engine Continental IO-520-A *Fuel 100/130 minimum grade aviation gasoline *Engine Limits For all operations, 2700 r.p.m. (285 b.hp.) Propeller and 1. (a) McCauley D2A34C58/90AT-8 Propeller Limits Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 10.3°, high 25.8° (b) Cessna spinner 0752004 (c) Woodward hydraulic governor D210452 2. McCauley constant speed propeller installation (with incorporation of Cessna Service Kit SK210-171) (a) McCauley D2A37C230 hub with 90REB-8 blades Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: Low 12.8°, high 28.3° (b) Cessna spinner 0752004-2 (c) Woodward hydraulic governor D210452 3A21 Page 6 of 45 Rev. 50 V. Model 210D (cont’d) *Airspeed Limits (CAS) Never exceed 225 mph. (196 knots) Maximum structural cruising 190 mph. (165 knots) Maneuvering 134 mph. (116 knots) Flaps extended 110 mph. ( 96 knots) Landing gear operating speed 160 mph. (139 knots) Landing gear extended speed 160 mph. (139 knots) C.G. Range (Landing (+39.2) to (+46.6) at 3100 lb. Gear Extended) (+33.0) to (+46.6) at 2250 lb. or less Straight line variation between points given. Moment change due to retracting landing gear (+2456 in.-lb.) Empty Wt. C.G. Range None *Maximum Weight 3100 lb. No. of Seats 4 (2 at +36, 2 at +70) Maximum Baggage Reference weight and balance data Fuel Capacity 65 gal. (63.4 gal. usable); two 32.5 gal. tanks in wings at +48. See Note 1 for data on unusable fuel. Oil Capacity 12 qt. (-19.4), 6 qt. usable. See Note 1 for data on undrainable oil. Control Surface Wing flaps Up 0° Down 40° +1°, -2° Movements Ailerons Up 21° ±2° Down 14°30' ±2° Elevator Up 26°30' ±1° Down 18° ±1° Elevator tab Up 20° +1°, -0° Down 10° +1°, -0° Rudder Right 24° ±1° Left 24° ±1° (measured parallel to 0.0. W.L.) Serial Nos. Eligible Model 210D: 21058221 through 21058510 (1964 Model) VI. Model 210E, 4 PCLM (Normal Category), Approved September 17, 1964 Engine Continental IO-520-A *Fuel 100/130 minimum grade aviation gasoline *Engine Limits For all operations, 2700 rpm. (285 b.hp.) Propeller and 1. (a) McCauley E2A34C64/90AT-8 Propeller Limits Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 10.3°, high 25.8° (b) Cessna spinner 1250411 (c) Woodward hydraulic governor D210452 2. (a) McCauley E2A34C73/90AT-8 Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 10.3°, high 25.8° (b) Cessna spinner 1250415 (c) Woodward hydraulic governor D210452 Rev. 50 Page 7 of 45 3A21 VI. Model 210E (cont’d) Propeller and 3. McCauley constant speed propeller installation (with Propeller Limits (cont’d) incor poration of Cessna Service Kit SK210-171) (a) McCauley E2A37C233 hub with 90REB-8 blades Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: Low 12.8°, high 28.3° (b) Cessna spinner 1250415 (c) Woodward hydraulic governor D210452 *Airspeed Limits (CAS) Never exceed 225 mph. (196 knots) Maximum structural cruising 190 mph. (165 knots) Maneuvering 134 mph. (116 knots) Flaps extended 110 mph. ( 96 knots) Landing gear operating speed 160 mph. (139 knots) Landing gear extended speed 160 mph. (139 knots) C.G. Range (Landing (+39.2) to (+46.6) at 3100 lb. Gear Extended) (+33.0) to (+46.6) at 2250 lb. or less Straight line variation between points given. Moment change due to retracting landing gear (+2456 in.-lb.) Empty Wt. C.G. Range None *Maximum Weight 3100 lb. No. of Seats 4 (2 at +36, 2 at +70) Maximum Baggage Reference weight and balance data Fuel Capacity 65 gal. (63.4 gal. usable); two 32.5 gal. tanks in wings at +48. See Note 1 for data on unusable fuel. Oil Capacity 12 qt. (-19.5), 6 qt. usable See Note 1 for data on undrainable oil. Control Surface Wing flaps Up 0° Down 40° +1°, -2° Movements Ailerons Up 21° ±2° Down 14°30' ±2° Elevator Up 26°30' ±1° Down 18° ±1° Elevator tab Up 20° +1°, -0° Down 10° +1°, -0° Rudder Right 24° ±1° Left 24° ±1° (measured parallel to 0.0. W.L.) Serial Nos. Eligible Model 210E: 21058511 through 21058715 (1965 Model) VII. Model T210F, 4 PCLM (Normal Category), Approved August 3, 1965 Engine Continental TSIO-520-C *Fuel 100/130 minimum grade aviation gasoline *Engine Limits For all operations, 2700 r.p.m., 32.5 in. Hg. mp. (285 b.hp.) Propeller and 1. (a) McCauley E2A34C70/90AT-8 Propeller Limits Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 11.8°, high 32.0° (b) Cessna spinner 1250415 (c) Woodward hydraulic governor G210452 3A21 Page 8 of 45 Rev. 50 VII. Model T210F (cont’d) Propeller and Propeller Limits (cont’d) *Airspeed Limits (CAS) C.G. Range (Landing Gear Extended) Empty Wt. C.G. Range *Maximum Weight No. of Seats Maximum Baggage Fuel Capacity Oil Capacity Control Surface Movements Serial Nos. eligible 2. (a) McCauley D3A32C77/82NK-2 Diameter: not over 80 in., not under 78 in. Pitch settings at 30 in. sta.: low 13.2°, high 32.5° (b) Cessna spinner 1250419-2 (c) Woodward hydraulic governor G210452 3. (a) McCauley D3A32C88/82NC-2 Diameter: not over 80 in., not under 78 in. Pitch settings at 30 in. sta.: low 14.0°, high 33.0° (b) Cessna spinner 1250419-2 (c) Woodward hydraulic governor G210452 4. McCauley constant speed propeller installation (with incorporation of Cessna Service Kit SK210-171) (a) McCauley E2A37C234 hub with 90REC-8 blades Diameter: not over 82 in., not under 80 in. Pitch settings at 30 in. sta.: Low 14.3°, high 34.5° (b) Cessna spinner 1250415 (c) Woodward hydraulic governor G210452 Never exceed 225 mph. (196 knots) Maximum structural cruising 190 mph. (165 knots) Maneuvering 131 mph. (114 knots) Flaps extended 110 mph ( 96 knots) Landing gear operating speed 160 mph. 139 knots) Landing gear extended speed 160 mph. (139 knots) (+39.0) to (+46.6) at 3300 lb. (+33.0) to (+46.6) at 2480 lb. or less Straight line variation between points given. Moment change due to retracting landing gear (+2456 in.-lb.) None 3300 lb. 4 (2 at +36, 2 at +70) Reference weight and balance data 65 gal. (63 gal. usable); two 32.5 gal. tanks in wings at +48. See Note 1 for data on unusable fuel. 12 qt. (-19.4), 6 qt. usable. See Note 1 for data on undrainable oil. Wing flaps Up 0° Down 40° +1°, -2° Ailerons Up 21° ±2° Down 14°30' ±2° Elevator Up 26°30' ±1° Down 18° ±1° Elevator tab Up 20° ±1° Down 20° ±1° Rudder Right 24° ±1° Left 24° ±1° (measured parallel to 0.0. W.L.) Model T210F: T210-0001 through T210-0197 (1966 Model) Rev. 50 Page 9 of 45 3A21 VIII. Model 210F, 4 PCLM (Normal Category), Approved August 3, 1965 Engine Continental IO-520-A *Fuel 100/130 minimum grade aviation gasoline *Engine Limits For all operations, 2700 rpm. (285 b.hp.) Propeller and 1. (a) McCauley E2A34C73/90AT-8 Propeller Limits Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 10.3°, high 25.8° (b) Cessna spinner 1250415 (c) Woodward hydraulic governor D210452 2. (a) McCauley D3A32C77/82NK-2 Diameter: not over 80 in., not under 78 in. Pitch settings at 30 in. sta.: low 11.3°, high 27.6° (b) Cessna spinner 1250419-2 (c) Woodward hydraulic governor D210452 3. (a) McCauley D3A32C88/82NC-2 Diameter: not over 80 in., not under 78 in. Pitch settings at 30 in. sta.: low 13.8°, high 28.1° (b) Cessna spinner 1250419-2 (c) Woodward hydraulic governor D210452 4. McCauley constant speed propeller installation (with incorporation of Cessna Service Kit SK210-171) (a) McCauley E2A37C233 hub with 90REB-8 blades Diameter: not over 82 in., not under 80 in. Pitch settings at 30 in. sta.: Low 12.8°, high 28.3° (b) Cessna spinner 1250415 (c) Woodward hydraulic governor D210452 *Airspeed Limits (CAS) Never exceed 225 mph. (196 knots) Maximum structural cruising 190 mph. (165 knots) Maneuvering 131 mph (114 knots) Flaps extended 110 mph ( 96 knots) Landing gear operating speed 160 mph (139 knots) Landing gear extended speed 160 mph. (139 knots) C.G. Range (Landing (+39.0) to (+46.6) at 3300 lb. Gear Extended) (+33.0) to (+46.6) at 2400 lb. or less Straight line variation between points given. Moment change due to retracting landing gear (+2456 in.-lb.) Empty Wt. C.G. Range None *Maximum Weight 3300 lb. No. of Seats 4 (2 at +36, 2 at +70) Maximum Baggage Reference weight and balance data Fuel Capacity 65 gal. (63 gal. usable), two 32.5 gal. tanks in wings at +48. See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. (-19.4), 6 qt. usable See NOTE 1 for data on undrainable oil. 3A21 Page 10 of 45 Rev. 50 VIII. Model 210F (cont’d) Control Surface Wing flaps Up 0° Down 40° +1°, -2° Movements Ailerons Up 21° ±2 Down 14°30' ±2° Elevator Up 26°30' ±1° Down 18° ±1° Elevator tab Up 20° ±1° Down 20° ±1° Rudder Right 24° ±1° Left 24° ±1° (measured parallel to 0.0. W.L.) Serial Nos. Eligible Model 210F: 21058716 through 21058818 (1966 Model) IX. Model T210G, 4 PCLM (Normal Category), Approved August 23, 1966 Model T210H, 4 PCLM (Normal Category), Approved August 16, 1967 Engine Continental TSIO-520-C *Fuel 100/130 minimum grade aviation gasoline *Engine Limits For all operations, 2700 rpm., 32.5 in. Hg. mp. (285 b.hp.) Propeller and 1. (a) McCauley E2A34C70/90AT-8 Propeller Limits Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 11.8°, high 32.0° (b) Cessna spinner 1250415 (c) Woodward hydraulic governor G210452 (d) McCauley hydraulic governor C290D2/T2 or C290D4/T2 2. (a) McCauley D3A32C88/82NC-2 Diameter: not over 80 in., not under 78 in. Pitch settings at 30 in. sta.: low 14.0°, high 33.0° (b) Cessna spinner 1250419-2 (c) Woodward hydraulic governor G210452 (d) McCauley hydraulic governor C219D2/T2 or C290D4/T2 3. (a) McCauley D3A32C77/82NK-2 (T-210G Only) Diameter: not over 80 in., not under 78 in. Pitch settings at 30 in. sta.: low 13.2°, high 32.5° (b) Cessna spinner 1250419-2 (c) Woodward hydraulic governor G210452 4. McCauley constant speed propeller installation (with incorporation of Cessna Service Kit SK210-171) (a) McCauley E2A37C234 hub with 90REC-8 blades Diameter: not over 82 in., not under 80 in. Pitch settings at 30 in. sta.: Low 14.3°, high 34.5° (b) Cessna spinner 1250415 (c) Woodward hydraulic governor G210452 *Airspeed Limits (CAS) Never exceed 225 mph. (196 knots) Maximum structural cruising 190 mph (165 knots) Maneuvering 135 mph. (117 knots) Flaps extended 110 mph. ( 96 knots) Landing gear operating speed 160 mph. (139 knots) Landing gear extended speed 160 mph. (139 knots) C.G. Range (Landing (+39.7) to (+47.8) at 3400 lb. Gear Extended) (+35.5) to (+47.8) at 2800 lb. or less Straight line variation between points given. Moment change due to retracting landing gear (+2456 in.-lb.) Rev. 50 Page 11 of 45 3A21 IX. Model T210G, Model T210H (cont’d) Empty Wt. C.G. Range None *Maximum Weight 3400 lbs. No. of Seats 4 (2 at +36, 2 at +70) Maximum Baggage Reference weight and balance data. Fuel Capacity 90 gal. (89 gal. usable), two 45.0 gal. tanks in wings at +43. See Note 1 for data on unusable fuel Oil Capacity 12 qt. (-19.4), 6 qt. usable. See Note 1 for data on undrainable oil Control Surface Wing flaps Up 0° Down 30° Movements Ailerons Up 20° ±2° Down 15° ±2° Elevator Up 23° ±1° Down 15° ±1° Elevator tab Up 20° ±1° Down 5° ±1° Rudder Right 24° ±1° Left 24° ±1° (measured parallel to 0.0. W.L.) Serial Nos. Eligible Model T210G: T210-0198 through T210-0307 (1967 Model) Model T210H: T210-0308 through T210-0392 (1968 Model) X. Model 210G, 4 PCLM (Normal Category), Approved August 23, 1966 Model 210H, 4 PCLM (Normal Category), Approved August 16, 1967 Engine Continental IO-520-A *Fuel 100/130 minimum grade aviation gasoline *Engine Limits For all operations, 2700 rpm. (285 b.hp.) Propeller and 1. (a) McCauley E2A34C73/90AT-8 Propeller Limits Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 10.3°, high 25.8° (b) Cessna spinner 1250415 (c) Woodward hydraulic governor D210452 (d) McCauley hydraulic governor C290D2/T5 or C290D3/T5 2. (a) McCauley D3A32C88/82NC-2 Diameter: not over 80 in., not under 78 in. Pitch settings at 30 in. sta.: low 13.8°, high 28.1° (b) Cessna spinner 1250419-2 (c) Woodward hydraulic governor D210452 (d) McCauley hydraulic governor C290D2/T5 or C290D3/T5 3. McCauley constant speed propeller installation (with incorporation of Cessna Service Kit SK210-171) (a) McCauley E2A37C233 hub with 90REB-8 blades Diameter: not over 82 in., not under 80 in. Pitch settings at 30 in. sta.: Low 12.8°, high 28.3° (b) Cessna spinner 1250415 (c) McCauley hydraulic governor C290D2/T5 or C290D3/T5 3A21 Page 12 of 45 Rev. 50 X. Model 210G, Model 210H (cont’d) *Airspeed limits (CAS) Never exceed 225 mph (196 knots) Maximum structural cruising 190 mph (165 knots) Maneuvering 135 mph. (117 knots) Flaps extended 110 mph. ( 96 knots) Landing gear operating speed 160 mph. (139 knots) Landing gear extended speed 160 mph. (139 knots) C.G. Range (Landing (+39.7) to (+47.8) at 3400 lb. Gear Extended) (+35.5) to (+47.8) at 2800 lb. or less Straight line variation between points given. Moment change due to retracting landing gear (+2456 in.-lb.) Empty wt. C.G. Range None *Maximum Weight 3400 lb. No. of Seats 4 (2 at +36, 2 at +70) Maximum Baggage Reference weight and balance data Fuel Capacity 90 gal. (89 gal. usable); two 45.0 gal. tanks in wings at +43. See Note 1 for data on unusable fuel. Oil Capacity 12 qt. (-19.4); 6 qt. usable See Note 1 for data on undrainable oil. Control Surface Wing flaps Up 0° Down 30° Movements Ailerons Up 20° ±2° Down 15° ±2° Elevator Up 23° ±1° Down 15° ±1° Elevator tab Up 20° ±1° Down 5° ±1° Rudder Right 24° ±1° Left 24° ±1° (measured parallel to 0.0. W.L.) Serial Nos. Eligible Model 210G: 21058819 through 21058936 (1967 Model) Model 210H: 21058937 through 21059061 (1968 Model) XI. Model T210J, 4 PCLM (Normal Category), Approved July 17, 1968 Engine Continental TSIO-520-H *Fuel 100/130 minimum grade aviation gasoline *Engine limits For all operations, 2700 rpm., 32.5 in. Hg. mp. (285 b.hp.) Propeller and 1. (a) McCauley E2A34C70/90AT-8 Propeller Limits Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 11.8°, high 32.0° (b) Cessna spinner 1250415 (c) Woodward hydraulic governor G210452 (d) McCauley hydraulic governor C290D2/T2 or C290D4/T2 2. (a) McCauley D3A32C88/82NC-2 Diameter: not over 80 in., not under 78 in. Pitch settings at 30 in. sta.: low 14.0°, high 33.0° (b) Cessna spinner 1250419-2 (c) Woodward hydraulic governor G210452 (d) McCauley hydraulic governor C219D2/T2 or C290D4/T2 Rev. 50 Page 13 of 45 3A21 XI. Model T210J (cont’d) Propeller and 3. McCauley constant speed propeller installation (with Propeller Limits (cont’d) incor poration of Cessna Service Kit SK210-171) (a) McCauley E2A37C234 hub with 90REC-8 blades Diameter: not over 82 in., not under 80 in. Pitch settings at 30 in. sta.: Low 14.3°, high 34.5° (b) Cessna spinner 1250415 (c) Woodward hydraulic governor G210452 (d) McCauley hydraulic governor C219D2/T2 or C219D4/T2 Airspeed Limits (CAS) Never exceed 225 mph. (196 knots) Maximum structural cruising 90 mph. (165 knots) Maneuvering 135 mph (117 knots) Flaps extended 110 mph. ( 96 knots) Landing gear operating speed 160 mph (139 knots) Landing gear extended speed 160 mph (139 knots) C.G. Range (Landing (+39.7) to (+47.8) at 3400 lb. Gear Extended) (+35.5) to (+47.8) at 2800 lb. or less Straight line variation between points given. Moment change due to retracting landing gear (+2456 in.-lb.) Empty wt. C.G. Range None *Maximum Weight 3400 lb. No. of Seats 4 (2 at +36, 2 at +70) Maximum Baggage Reference weight and balance data. Fuel Capacity 90 gal. (89 gal. usable), two 45.0 gal. tanks in wings at +43. See Note 1 for data on unusable fuel. Oil Capacity 10 qt. (-12.5), 8 qt. usable See Note 1 for data on undrainable oil. Control Surface Wing flaps Up 0° Down 30° Movements Ailerons Up 20° ±2° Down 15° ±2° Elevator Up 23° ±1° Down 15° ±1° Elevator tab Up 20° ±1° Down 5° ±1° Rudder Right 24° ±1° Left 24° ±1° (measured parallel to 0.0. W.L.) Serial Nos. Eligible Model T210J: 21058140, T210-0393 through T210-0454 (1969 Model) XII. Model 210J, 4 PCLM (Normal Category), Approved July 17, 1968 Engine Continental IO-520-J *Fuel 100/130 minimum grade aviation gasoline *Engine Limits For all operations, 2700 rpm. (285 b.hp.) 3A21 Page 14 of 45 Rev. 50 XII. Model 210J (cont’d) Propeller and 1. (a) McCauley E2A34C73/90AT-8 Propeller Limits Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 10.3°, high 25.8° (b) Cessna spinner 1250415 (c) Woodward hydraulic governor D210452 (d) McCauley hydraulic governor C290D2/T5 or C290D3/T5 2. (a) McCauley D3A32C88/82NC-2 Diameter: not over 80 in., not under 78 in. Pitch settings at 30 in. sta.: low 13.8°, high 28.1° (b) Cessna spinner 1250419-2 (c) Woodward hydraulic governor D210452 (d) McCauley hydraulic governor C290D2/T5 or C290D3/T5 3. McCauley constant speed propeller installation (with incorporation of Cessna Service Kit SK210-171) (a) McCauley E2A37C233 hub with 90REB-8 blades Diameter: not over 82 in., not under 80 in. Pitch settings at 30 in. sta.: Low 12.8°, high 28.3° (b) Cessna spinner 1250415 (c) Woodward hydraulic governor D210452 (d) McCauley hydraulic governor C290D2/T5 or C290D3/T5 *Airspeed Limits (CAS) Never exceed 225 mph. (196 knots) Maximum structural cruising 190 mph (165 knots) Maneuvering 135 mph. (117 knots) Flaps extended 110 mph. ( 96 knots) Landing gear operating speed 160 mph. (139 knots) Landing gear extended speed 160 mph. (139 knots) C.G. Range (Landing (+39.7) to (+47.8) at 3400 lb. Gear Extended) (+35.5) to (+47.8) at 2800 lb. or less Straight line variation between points given. Moment change due to retracting landing gear (+2456 in.-lb.) Empty Wt. C.G. Range None *Maximum Weight 3400 lb. No. of Seats 4 (2 at +36, 2 at +70) Maximum Baggage Reference weight and balance data Fuel Capacity 90 gal. (89 gal. usable); two 45.0 gal. tanks in wings at +43. See Note 1 for data on unusable fuel. Oil Capacity 10 qt. (-12.5); 8 qt. usable See Note 1 for data on undrainable oil. Control Surface Wing flaps Up 0° Down 30° Movements Ailerons Up 20° ±2° Down 15° ±2° Elevator Up 23° ±1° Down 15° ±1° Elevator tab Up 20° ±1° Down 5° ±1° Rudder Right 24° ±1° Left 24° ±1° (measured parallel to 0.0. W.L.) Serial Nos. Eligible Model 210J: 21059062 through 21059199 (1969 Model) Rev. 50 Page 15 of 45 3A21 XIII. Model 210K/T210K, 6 PCLM (Normal Category), Approved September 26, 1969 Model 210L/T210L, 6 PCLM (Normal Category), Approved October 7, 1971 Model 210K/210L Engine Continental IO-520-L *Fuel 100/130 minimum grade aviation gasoline *Engine Limits Takeoff (5 min.) at 2850 rpm. (300 hp.) For all other operations, 2700 r.p.m. (285 hp.) Propeller and 1. Model 210K/210L (S/N 21059200 through 21060539) Propeller Limits (a) McCauley E2A34C73/90AT-8 Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 10.3°, high 25.8° (b) Cessna spinner 1250419 (c) Woodward hydraulic governor 2104562 (d) McCauley hydraulic governor C290D2/T4 or C290D4/T4 2. (a) McCauley D3A32C88/82NC-2 Diameter: not over 80 in., not under 78.5 in. Pitch settings at 30 in. sta.: low 11.5°, high 28.1° (b) Cessna spinner 1250419-2 (c) Woodward hydraulic governor 210462 (d) McCauley hydraulic governor C290D2/T4 or C290D4/T4 3. McCauley constant speed propeller installation (with incorporation of Cessna Service Kit SK210-171) (a) McCauley E2A37C233 hub with 90REB-8 blades Diameter: not over 82 in., not under 80 in. Pitch settings at 30 in. sta.: Low 12.8°, high 28.3° (b) Cessna spinner 1250415 (c) Woodward hydraulic governor 210462 (d) McCauley hydraulic governor C290D2/T4 or C290D4/T4 Model T210K/T210L Engine Continental TSIO-520-H *Fuel 100/130 minimum grade aviation gasoline *Engine Limits For all operations, 2700 rpm., 32.5 in. Hg. mp. (285 b.hp.) Propeller and 1. Model T210K/T210L (S/N 21059200 through 21060539) Propeller Limits (a) McCauley E2A34C70/90AT-8 Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 11.8°, high 32.0° (b) Cessna spinner 1250415 (c) Woodward hydraulic governor G210452 (d) McCauley hydraulic governor C290D2/T2 or C290D4/T4 2. (a) McCauley D3A32C88/82NC-2 Diameter: not over 80 in., not under 78.5 in. Pitch settings at 30 in. sta.: low 14.0°, high 33.0° (b) Cessna spinner 1250419-2 (c) Woodward hydraulic governor G210452 (d) McCauley hydraulic governor C290D2/T2 or C290D4/T2 3A21 Page 16 of 45 Rev. 50 XIII. Model 210K/T210K, Model 210L/T210L (cont’d) Model T210K/T210L (cont’d) Propeller and Propeller Limits (cont’d) 3. McCauley constant speed propeller installation (with Incorporation of Cessna Service Kit SK210-171) (a) McCauley E2A37C234 hub with 90REC-8 blades Diameter: not over 82 in., not under 80 in. Pitch settings at 30 in. sta.: Low 14.3°, high 34.5° (b) Cessna spinner 1250415 (c) Woodward hydraulic governor G210452 (d) McCauley hydraulic governor C290D2/T2 or C290D4/T2 Models 210K/210L/T210K/T210L *Airspeed Limits (CAS) Model 210K/T210K, 210L/T210L (S/N 21059200 through 21061039) Never exceed 225 m.p.h (196 knots) Maximum structural cruising 190 m.p.h (165 knots) Maneuvering 135 m.p.h (117 knots) Flaps extended (210K/T210K) 110 m.p.h ( 96 knots) Flaps extended (210L/T210L) 120 m.p.h (104 knots) Landing gear operating speed 160 m.p.h (139 knots) Landing gear extended speed 160 m.p.h (139 knots) (IAS) (See NOTE 4 on use of IAS) Model 210L/T210L (S/N 21061040 through 21061573) Never exceed 199 knots Maximum structural cruising 168 knots Maneuvering 119 knots Flaps extended 105 knots Landing gear operating speed 140 knots Landing gear extended speed 140 knots C.G. Range (Landing Gear Extended) (+42.5) to (+53.0) at 3800 lb. (+37.0) to (+53.0) at 3000 lb. or less Straight line variation between points given. Moment change due to retracting landing gear (+3207 in.-lb.) Empty Wt. C.G. Range None *Maximum Weight 3800 lb. No. of Seats Standard 6 (2 at +34 to +46, 2 at +61 to +77, 2 at +101) Optional 4 (2 at +34 to +46, 2 at +77) (210K/T210K) Maximum Baggage Reference weight and balance data Fuel Capacity 90 gal. (89 gal. usable); two 45.0 gal. tanks in wings at +43 See NOTE 1 for data on unusable fuel. Oil Capacity 10 qt. (-12.5); 8 qt. usable See NOTE 1 for data on undrainable oil. Control Surface Wing flaps Up 0° Down 30° +1°, -2° Movements Ailerons Up 20° ±2° Down 15° ±2° Elevator Up 23° ±1° Down 17° ±1° Elevator tab Up 25° ±1° Down 10° ±1° Rudder Right 24° ±1° Left 24° ±1° (measured parallel to 0.0 W.L.) Rudder Right 27°13' ±1° Left 27°13' ±1° (measured perpendicular to hinge line) Rev. 50 Page 17 of 45 3A21 XIII. Model 210K/T210K, Model 210L/T210L (cont’d) Models 210K/210L/T210K/T210L (cont’d) Serial Nos. Eligible Models 210K/T210K: 21059200 through 21059351 (1970 Model) 21059352 through 21059502 (1971 Model) Models 210L/T210L: 21059503 through 21059719 (1972 Model) 21059720 through 21060089 (1973 Model) 21060090 through 21060539 1974 Model) 21060540 through 21061039 1975 Model) 21061040 through 21061041 1976 Model) 21061043 through 21061573 (1976 Model) XIV. Model 210M/T210M, 6 PCLM (Normal Category), October 7, 1976 Model 210M Engine Continental IO-520-L *Fuel Model 210M (S/N 21061574 through 21062273) 100/130 minimum grade aviation gasoline Model 210M (S/N 21062274 through 21062953) 100LL/100 minimum grade aviation gasoline *Engine Limits Takeoff (5 min.) at 2850 r.p.m. (300 hp.) For all other operations, 2700 r.p.m. (285 hp.) Propeller and 1. Model 210M (S/N 21061574 through 21062273) Propeller Limits (a) McCauley D3A32C88/82NC-2 Diameter: not over 80 in., not under 78.5 in. Pitch settings at 30 in. sta.: low 11.5°, high 28.1° (b) Cessna spinner 1250419-2 (c) Woodward hydraulic governor 210462 (d) McCauley hydraulic governor C290D4/T4 2. Model 210M (S/N 21062274 and up) (a) McCauley D3A34C404/80VA-0 Diameter: not over 80 in., not under 78.5 in. Pitch settings at 30 in. sta.: low 11.0°, high 27.0° (b) Cessna spinner 1250419 (c) McCauley hydraulic governor C290D4/T4 *Airspeed Limits (IAS) 1. Model 210M (S/N 21061574 through 21062273) (See NOTE 4 on use of IAS) Never exceed 199 knots Maximum structural cruising 168 knots Maneuvering 119 knots Flaps extended 105 knots Landing gear operating speed 140 knots Landing gear extended speed 140 knots 2. Model 210M (S/N 21062274 through 21062953) Never exceed 199 knots Maximum structural cruising 168 knots Maneuvering 119 knots Flaps extended 115 knots Landing gear operating speed 140 knots Landing gear extended speed 199 knots 3A21 Page 18 of 45 Rev. 50 XIV. Model 210M/T210M (cont’d) Model T210M Engine Continental TSIO-520-R *Fuel Model T210M (S/N 21061574 through 21062273) 100/130 minimum grade aviation gasoline Model T210M (S/N 21062274 through 21062953) 100LL/100 minimum grade aviation gasoline Engine Limits Takeoff (5 min. at 2700 r.p.m., 36.5 in. Hg. mp. (310 hp.) For all other operations 2600 r.p.m., 35 in. Hg. mp. (285 hp.) Propeller and 1. (a) McCauley D3A34C402/90DFA-10 Propeller Limits Diameter: not over 80 in., not under 78.5 in. Pitch settings at 30 in. sta.: low 12.4°, high 28.5° (b) Cessna spinner 1250419-10 (c) McCauley hydraulic governor C290D4/T2 (d) Woodward hydraulic governor G210452 *Airspeed Limits (IAS) 1. Model T210M (S/N 21061574 through 21062273) (See NOTE 4 on use of IAS) Never exceed 195 knots Maximum structural cruising 165 knots Maneuvering 119 knots Flaps extended 105 knots Landing gear operating speed 140 knots Landing gear extended speed 140 knots 2. Model T210M (S/N 21062274 through 21062953 Never exceed 195 knots Maximum structural cruising 165 knots Maneuvering 119 knots Flaps extended 115 knots Landing gear operating speed 140 knots Landing gear extended speed 195 knots Models 210M/T210M C.G. Range (Landing (+42.5) to (+53.0) at 3800 lb. Gear Extended) (+37.0) to (+53.0) at 3000 lb. or less Straight line variation between points given Moment change due to retracting landing gear (+3207 in.-lb.) Empty Wt. C.G. Range None *Maximum Weight 3800 lb. No. of Seats 6 (2 at +34 to +46, 2 at +61 to +77, 2 at +101) Maximum Baggage Reference weight and balance data Fuel Capacity 90 gal. (89 gal. usable), two 45.0 gal. tanks in wings at +43. See NOTE 1 for data on unusable fuel Oil Capacity 10 qt. (-12.5), 8 qt. usable Rev. 50 Page 19 of 45 3A21 XIV. Model 210M/T210M (cont’d) Models 210M/T210M (cont’d) Control Surface Wing flaps Up 0° Down 30° +1°, -2° Movements Ailerons Up 20° ±2° Down 15° ±2° Elevator Up 23° ±1° Down 17° ±1° Elevator tab Up 25° ±1° Down 10° ±1° Rudder Right 24° ±1° Left 24° ±1° (measured parallel to 0.0 W.L.) Rudder Right 27° 13' ±1° Left 27° 13' ±1° (measured perpendicular to hinge line) Serial Nos. Eligible Models 210M/T210M: 21061574 through 21062273 (1977 Model) 21061042, 21062274 through 21062954 (1978 Model) XV. Model P210N, Pressurized Centurion, 6 PCLM (Normal Category), Approved August 10, 1977 Engine Model P210N (S/N P21000001 through P21000760: Continental TSIO-520-P Model P210N (S/N P21000761 and up): Continental TSIO-520-AF *Fuel 100LL/100 minimum grade aviation gasoline *Engine Limits Model P210N (S/N P21000001 through P21000760) Takeoff (5 min.) at 2700 r.p.m., 36.5 in. Hg. mp. (310 hp.) For all other operations 2600 r.p.m., 33.5 in. Hg. mp. (285 hp.) Model P210N (S/N P21000761 and up) Takeoff (5 min.) at 2700 r.p.m., 35.5 in. Hg. mp. (310 hp.) For all other operations, 2600 r.p.m., 34.5 in. Hg. mp. (285 hp.) Propeller and 1. (a) McCauley D3A34C402/90DFA-10 Propeller Limits Diameter: not over 80 in., not under 78.5 in. Pitch settings at 30 in. sta.: low 12.4°, high 28.5° Model P210N (S/N P21000001 through P21000760) Avoid continuous operation between 1850 and 2150 r.p.m. above 24 in. mp. Model P210N (S/N P21000761 and up) Avoid continuous operation between 1850 and 2150 r.p.m. above 23 in. mp. (b) Cessna spinner 1250419 (c) McCauley hydraulic governor C290D4/T2 *Airspeed Limits (IAS) 1. M odel P210N (S/N P21000001 through P21000150) (See NOTE 4 on use of IAS) Never exceed 200 knots Maximum structural cruising 167 knots Maneuvering 130 knots Flaps extended 115 knots Landing gear operating speed 140 knots Landing gear extended speed 200 knots 2. Model P210N (S/N P21000151 and up) Never exceed 200 knots Maximum structural cruising 167 knots Maneuvering 130 knots Flaps extended 115 knots Landing gear operating speed 165 knots Landing gear extended speed 200 knots 3A21 Page 20 of 45 Rev. 50 XV. Model P210N (cont’d) C.G. Range (Landing (+43.9) to (+52.0) at 4000 lb. Gear Extended) (+42.5) to (+52.0) at 3800 lb. (+37.0) to (+52.0) at 3000 lb. or less Straight line variation between points given Moment change due to retracting landing gear (+3207 in.-lb.) S/N P21000001 through P21000150 (+2907 in.-lb.) S/N P21000151 and up Empty Wt. C.G. Range None *Maximum Weight 4000 lb. takeoff and flight 3800 lb. landing 4016 lb. ramp, S/N 21000151 and up No. of Seats 6 (2 at +34 to +46, 2 at +61 to +77, 2 at +101) Maximum Baggage Reference weight and balance data Fuel Capacity 90 gal. (89 gal. usable), S/N P21000001 through P21000760 90 gal. (87 gal. usable), S/N P21000761 and up two 45.0 gal. tanks in wings at +43 See NOTE 1 for data on unusable fuel. Oil Capacity 10 qt. (-12.5); 8 qt. usable Control Surface Movements Wing flaps Up 0° Ailerons Up 20° ±2° Elevator Up 23° ±1° Elevator tab Up 25° ±1° Rudder Right 24° ±1° (measured parallel to 0.0 W.L.) Rudder Right 27° 13' ±1° (measured perpendicular to hinge line) Down Down Down Down Left Left 30° +1°, -2° 15° ±2° 17° ±1° 10° ±1° 24° ±1° 27° 13' ±1° Serial Nos. Eligible Model P210N: P21000001 through P21000150 (1978 Model) P21000151 through P21000385 (1979 Model) P21000386 through P21000590 (1980 Model) P21000591 through P21000760 (1981 Model) P21000761 through P21000811 (1982 Model) P21000812 through P21000834 (1983 Model) XVI. Model 210N/T210N, Centurion/Turbo System Centurion, 6 PCLM (Normal Category), approved October 19, 1978 Model 210N Engine Continental IO-520-L *Fuel 100LL/100 minimum grade aviation gasoline *Engine Limits Takeoff full throttle (5 min.) at 2850 r.p.m. (300 hp. rating) For all other operations, full throttle 2700 r.p.m. (285 hp. rating) Propeller and 1. (a) McCauley D3A34C404/80VA-0 Propeller Limits Diameter: not over 80 in., not under 78.5 in. Pitch settings at 30 in. sta.: low 11.0°, high 27.0° (b) Cessna spinner 1250419 (c) McCauley hydraulic governor C290D4/T4 Rev. 50 Page 21 of 45 3A21 XVI. Model 210N/T210N (cont’d) Model 210N (cont’d) *Airspeed Limits (IAS) 1. Model 210N (S/N 21062954 and up) (See NOTE 4 on Use of IAS) Never exceed 200 knots Maximum structural cruising 165 knots Maneuvering 125 knots Flaps extended 115 knots Landing gear operating speed 165 knots Landing gear extended speed 200 knots C.G. Range (Landing (+42.5) to (+53.0) at 3800 lb. Gear Extended) (+37.0) to (+53.0) at 3000 lb. or less Straight line variation between points given Moment change due to retracting landing gear (+2907 in.-lb.) Empty Wt. C.G. Range None *Maximum Weight 3800 lb. 3812 lb. ramp No. of Seats 6 (2 at +34 to +46, 2 at +61 to +77, 2 at +101) Maximum Baggage Reference weight and balance data Fuel Capacity 90 gal. (89 gal. usable), S/N 21062955 through 21064535 90 gal. (87 gal. usable), S/N 21064536 and up two 45.0 gal. tanks in wings at +43 See NOTE 1 for data on unusable fuel. Oil Capacity 10 qt. (-12.5), 8 qt. usable Control Surface Movements Wing flaps Up 0° Ailerons Up 20° ±2° Elevator Up 23° ±1° Elevator tab Up 25° ±1° Rudder Right 24° ±1° (measured parallel to 0.0 W.L.) Rudder Right 27° 13' ±1° (measured perpendicular to hinge line) Down Down Down Down Left Left 30° +1°, -2° 15° ±2° 17° ±1° 10° ±1° 24° ±1° 27° 13' ±1° Serial Nos. Eligible Model 210N: 21062955 through 21063640 21063641 through 21064135 21064136 through 21064535 21064536 through 21064772 21064773 through 21064822 21064823 through 21064897 (1979 Model) (1980 Model) (1981 Model) (1982 Model) (1983 Model) (1984 Model) Model T210N Engine Continental TSIO-520-R Fuel 100LL/100 minimum grade aviation gasoline *Engine Limits Takeoff (5 min.) at 2700 r.p.m., 36.5 in. Hg. mp. (310 hp. rating) For all other operations 2600 r.p.m., 35 in. Hg. mp. (285 hp. rating) 3A21 Page 22 of 45 Rev. 50 XVI. Model 210N/T210N (cont’d) Model T210N (cont’d) Propeller and 1. (a) McCauley D3A34C402/90DFA-10 Propeller Limits Diameter: not over 80 in., not under 78.5 in. Pitch settings at 30 in. sta.: low 12.4°, high 28.5° Avoid continuous operation between 1850 and 2150 r.p.m.. above 24 in. mp. (b) Cessna spinner 1250419 (c) McCauley hydraulic governor C290D4/T2 or Woodward hydraulic governor G210452 *Airspeed Limits (IAS) 1. Model T210N (S/N 21062954 and up) (See NOTE 4 on Use of IAS) Never exceed 203 knots Maximum structural cruising 168 knots Maneuvering 130 knots Flaps extended 115 knots Landing gear operating speed 165 knots Landing gear extended speed 203 knots C.G. Range (Landing (+43.9) to (+52.0) at 4000 lbs. Gear Extended) (+42.5) to (+53.0) at 3800 lbs. (+37.0) to (+53.0) at 3000 lbs. Straight line variation between points given Moment change due to retracting landing gear (+2907 in.-lb.) Empty Wt. C.G. Range None *Maximum Weight 4000 lb. takeoff and flight 3800 lb. landing 4016 lb. ramp No. of Seats 6 (2 at +34 to 46, 2 at +61 to +77, 2 at +101) Maximum Baggage Reference weight and balance data Fuel Capacity 90 gal. (89 gal. usable), S/N 21062955 through 21064535 90 gal. (87 gal. usable), S/N 21064536 and up two 45.0 gal. tanks in wings at +43 See NOTE 1 for data on unusable fuel. Oil Capacity 10 qt. (-12.5); 8 qt. usable Control Surface Movements Wing flaps Up 0° Ailerons Up 20° ±2° Elevator Up 23° ±1° Elevator tab Up 25° ±1° Rudder Right 24° ±1° (measured parallel to 0.0 W.L.) Rudder Right 27° 13' ±1 (measured perpendicular to hinge line) Down Down Down Down Left Left 30° +1°, -2° 15° ±2° 17° ±1° 10° ±1° 24° ±1° 17° 13' ±1° Serial Nos. Eligible Model T210N: 21062955 through 21063640 (1979 Model) 21063641 through 21064135 (1980 Model) 21064136 through 21064535 (1981 Model) 21064536 through 21064772 (1982 Model) 21064773 through 21064822 (1983 Model) 21064823 through 21064897 (1984 Model) Rev. 50 Page 23 of 45 3A21 XVII. Model P210R, Pressurized Centurion, 6 PCLM (Normal Category), Approved September 24, 1984 Engine Continental TSIO-520-CE *Fuel 100LL/100 minimum grade aviation gasoline *Engine Limits For all operations 2700 r.p.m., 37 in. Hg. mp. (325 hp.) Propeller and Propeller Limits 1. (a) (b) (c) McCauley D3A36C410/80VMB-0 Diameter: not over 80 in., not under 78.5 in. Pitch settings at 30 in. sta.: low 14.2°, high 36.5° Cessna spinner 2150150 McCauley hydraulic governor C290D4/T2 *Airspeed Limits (IAS) Never exceed Maximum structural cruising Flaps extended Maneuvering Landing gear operating speed Landing gear extended speed 200 knots 167 knots 115 knots 130 knots 165 knots 200 knots C.G. Range (Landing Gear Extended) (+42.0) to (+52.0) at 4100 lb. (+37.0) to (+52.0) at 3350 lb. or less Straight line variation between points given Moment change due to retracting landing gear (+2907 in.-lb.) Empty Wt. C.G. Range None *Maximum Weight 4100 lb. takeoff and flight 3900 lb. landing 4116 lb. ramp No. of Seats 6 (2 at +34 to 46, 2 at +61 to +77, 2 at +101) Maximum Baggage Reference weight and balance data Fuel Capacity Std.: 90 gal. (87 gal. usable) Two 45.0 gal. tanks in wings at +42.5 Opt.: 120 gal. (115 gal. usable) Two 60.0 gal. tanks in wings at +42.5 See NOTE 1 for data on unusable fuel Oil Capacity 10 qt. (-12.5), 8 qt. usable Maximum Operating Altitude 25,000 ft. Control Surface Movements Wing flaps Up 0° Ailerons Up 20° ±2° Elevator Up 25° ±1° Elevator tab Up 20° ±1° Rudder Right 24° ±1° (measured parallel to 0.0 W.L.) Rudder Right 27° 13' ±1° (measured perpendicular to hinge line) Down Down Down Down Left Left 30° +1°, -2° 15° ±2° 20° ±1° 15° ±1° 24° ±1° 27° 13' ±1° Serial Nos. Eligible Model P210R: P21000835 through P21000866 (1985 Model) P21000867 through P21000874 (1986 Model) 3A21 Page 24 of 45 Rev. 50 XVIII. Model T210R, Turbo System Centurion, 6 PCLM (Normal Category), Approved December 4, 1984 Model 210R, Centurion, 6 PCLM (Normal Category), Approved December 20, 1984 Model 210R Engine Continental IO-520-L *Fuel 100LL/100 minimum grade aviation gasoline *Engine Limits Takeoff full throttle (5 min.) at 2850 r.p.m. (300 hp. rating) For all other operations, full throttle 2700 r.p.m. (285 hp. rating) Propeller and Propeller Limits 1. (a) McCauley D3A34C404/80VA-0 Diameter: not over 80 in., not under 78.5 in. Pitch settings at 30 in. sta.: low 11.0°, high 27.0° (b) Cessna spinner 1250419 (c) McCauley hydraulic governor C290D4/T4 *Airspeed Limits (IAS) (See NOTE 4 on use of IAS) Never exceed Maximum structural cruising Maneuvering Flaps extended Landing gear operating speed Landing gear extended speed 200 knots 167 knots 125 knots 115 knots 165 knots 200 knots C.G. Range (Landing) Gear Extended) (+40.33) to (+52.0) at 3850 lb. (+37.0) to (+52.0) at 3350 lb. or less Straight line variation between points given Moment change due to retracting landing gear (+2907 in.-lb.) Empty Wt. C.G. Range None *Maximum Weight 3850 lb. 3862 lb. ramp No. of Seats 6 (2 at +34 to 46, 2 at +61 to +77, 2 at +101) Maximum Baggage Reference weight and balance data Fuel Capacity Std.: 90 gal. (87 gal. usable) Two 45.0 gal. tanks in wings at +42.5 Opt: 120 gal. (115 gal. usable) Two 60 gal. tanks in wings at +42.5 See NOTE 1 for data on unusable fuel. Oil Capacity 10 qt. (-12.5), 8 qt. usable Control Surface Movements Wing flaps Up 0° Ailerons Up 20° ±2° Elevator Up 25° ±1° Elevator tab Up 20° ±1° Rudder Right 24° ±1° (measured parallel to 0.0 W.L.) Rudder Right 27° 13' ±1° (measured perpendicular to hinge line) Down Down Down Down Left Left 30° +1°, -2° 15° ±2° 20° ±1° 15° ±1° 24° ±1° 27° 13' ±1° Serial Nos. Eligible Model 210R: 21064898 through 21064949 (1985 Model) 21064950 through 21065009 (1986 Model) Rev. 50 Page 25 of 45 3A21 XVIII. Models T210R, 210R (cont’d) Model T210R Engine Continental TSIO-520-CE *Fuel 100LL/100 minimum grade aviation gasoline *Engine Limits For all operations 2700 r.p.m., 37 in. Hg. mp. (325 hp.) Propeller and 1. (a) McCauley D3A36C410/80VMB-0 Propeller Limits Diameter: not over 80 in., not under 78.5 in. Pitch settings at 30 in. sta.: low 14.2°, high 36.5° (b) Cessna spinner 2150150 (c) McCauley hydraulic governor C290D4/T2 *Airspeed Limits Never exceed 203 knots (IAS) Maximum structural cruising 167 knots Maneuvering 130 knots Flaps extended 115 knots Landing gear operating speed 165 knots Landing gear extended speed 200 knots C.G. Range (Landing (+42.0) to (+52.0) at 4100 lb. Gear Extended) (+37.0) to (+52.0) at 3350 lb. Straight line variation between points given Moment change due to retracting landing gear (+2907 in.-lb.) Empty Wt. C.G. Range None *Maximum Weight 4100 lb. takeoff and flight 3900 lb. landing 4116 lb. ramp No. of Seats 6 (2 at +34 to 46, 2 at +61 to +77, 2 at +101) Maximum Baggage Reference weight and balance data Fuel Capacity Std.: 90 gal. (87 gal. usable) Two 45.0 gal. tanks in wings at +42.5 Opt: 120 gal. (115 gal. usable) Two 60 gal. tanks in wings at +42.5 See NOTE 1 for data on unusable fuel Oil Capacity 10 qt. (-12.5), 8 qt. usable Control Surface Movements Wing flaps Up 0° Down 30° +1°, -2° Ailerons Up 20° ±2° Down 15° ±2° Elevator Up 25° ±1° Down 20° ±1° Elevator tab Up 20° ±1° Down 15° ±1° Rudder Right 24° ±1° Left 24° ±1° (measured parallel to 0.0 W.L.) Rudder Right 27° 13' ±1° Left 27° 13' ±1° (measured perpendicular to hinge line) Serial Nos. Eligible Model T210R: 21064898 through 21064949 (1985 Model) 21064950 through 21065009 (1986 Model) 3A21 Page 26 of 45 Rev. 50 Data Pertinent to All Models Datum Fuselage station 0.0 (front face of firewall) Leveling Means Baggage compartment floor (except for 210-5(205) and 210-5A(205A)). Top of tailcone (except 210K/T210K/P210N and up, screws on left side tailcone). Certification Basis Models 210/210A: Part 3 of the Civil Ai r Regulations effective May 15, 1956, with no amendments. Models 210B, 210C, 210D, 210E, 210F, T210F, 210G, T210G, 210H, T210H, 210J, T210J, 210K, T210K, 210L, T210L, 210M, T210M, 210N, T210N, 210R, 210-5(205), 210-5A(205A): Part 3 of the Civil Air Regulations effective May 15, 1956, and Paragraph 3.112 as amended October 1, 1959. FAR 36 dated December 1, 1969, plus Amendments 36-1 through 36-4 for Models 210M/T210M/210N/210R; Amendments 36-1 through 36-9 for the T210N. In addition, FAR 23.1559 effective March 1, 1978, for the Models 210N/T210N/210R. Models P210N, P210R: Part 3 of the Civil Air Regulations dated May 15, 1956, Paragraph 3.112 as amended October 1, 1959, and 23.365, 23.571, 23.775, 23.841, 23.843, 23.901, 23.909, 23.1041, 23.1043, 23.1143, 23.1305, 23.1325, 23.1441 and 23.1527 of FAR 23 effective February 1, 1965, as amended to February 14, 1975. FAR 36 dated December 1, 1969, plus Amendments 36-1 through 36-6 for P210N; Amendments 36-1 through 36-12 for P210R. Also FAR 23.1559 effective March 1, 1978, for P21000151 and on. Also for P210R, FAR 23.1323 effective September 1, 1977, and FAR 23.1545 effective December 1, 1978. Model T210R: Part 3 of the Civil Air Regulati ons dated May 15, 1956, Paragraph 3.112 as amended October 1, 1959, and 23.901, 23.909, 23.1041, 23.1043, 23.1143, 23.1305 of FAR 23 effective February 1, 1965, as amended to February 14, 1975; FAR 23.1323 effective September 1, 1977; FAR 23.1545 effective December 1, 1978; and FAR 23.1559 effective March 1, 1978; FAR 36 dated December 1, 1969, plus Amendments 36-1 through 36-12. Compliance with ice protection has been demonstrated in accordance with FAR 23.1419, as amended through Amendment 23-14, when ice protection equipment is installed in accordance with the airplane equipment list (Models P210N, T210N, P210R, and T210R only). Compliance for the Carry-Thru Spar Spare (P/N 1210721-1 and 2110020-1) has been demonstrated in accordance with Part 3 of the Civil Air Regulations dated May 15, 1956, and 14 CFR 23.571, 23.572, 23.573 and 23.575 as of Amendment 23-48. Application for type certificate dated August 13, 1956. Type Certificate No. 3A21 issued April 20, 1959, obtained by the manufacturer under delegation option procedures. Equivalent Safety Items (S/N 21061040 through 21064897 (T210 only), and S/N P21000001 through P21000835) Airspeed Indicator Operating Limitations CAR 3.757 (See NOTE 4 for effectivity) CAR 3.778(a) (210 S/N 21061040 through 21065009) (T210 S/N 21061040 through 21064897) (P210 S/N P21000001 through P21000834) Airspeed Indicating System CAR 3.663 (210N, S/N 21062955 through 21064897) (210R, S/N 21064898 through 21065009) Production Basis Production Certificate No. 4. Delegation Option Manufacturer No. CE-1 authorized to issue airworthiness certificates under delegation option provisions of Part 21 of the Federal Aviation Regulations. Rev. 50 Page 27 of 45 3A21 Data Pertinent to All Models (cont’d) Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. This equipment must include a current Airplane Flight Manual (AFM) effective S/N 21062955 and on and P21000151 and on. In addition, the following item of equipment is required: 1. Stall warning indicator, Cessna Dwg. 0511062-4: S/N 21057001 through 21058818 S/N T210-0001 through T210-0197 Cessna Dwg. S-1672-1: S/N 21058819 and up S/N T210-0198 through T210-0454 S/N P21000001 and up NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions when necessary must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity location must include unusable fuel of 60 lb. at (+46) on Models 210 and 210A, 9 lb. at (+46) on the 210B, 210C, 210D, 210E, 210-5(205) 210-5A(205A); 12 lb. at (+46) on the 210F, T210F; and 6 lb. at (+23) on the 210G, T210G, 210H, T210H, 210J, T210J, 210K, T210K, 210L, T210L, 210M, T210M, 210N, T210N, P210N through S/N's 21064535 and P21000760; and 18 lb. at (+38) on S/N's 21064536 and up, and P21000761 and up; and undrainable oil of 0 lb. at (-19) through S/N 21061039 and full oil of 18.8 lb. at (-12.5) S/N 21061040 and On, and S/N P21000001 and On. NOTE 2. The following placards must be displayed in locations as indicated: A. Applicable to Models 210/210A (1) In full view of the pilot: (i) "This airplane must be operated as a normal category airplane in compliance with the operating limitations as stated in the form of placards, markings and manuals. No acrobatic maneuvers, including spins, approved. Maximum maneuvering speed - 130 m.p.h. - CAS. Maximum design weight 2900 lb. Maximum flight maneuvering load factors - Flaps up +3.8, -1.52; Flaps down +3.5. Maximum gear ex tension speed 160 m.p.h. - CAS. Maximum flap extension speeds 10° flaps - 160 m.p.h. - CAS; 10°-40° flaps - 110 m.p.h. - CAS. Before takeoff Before landing 1. Set tabs 1. Gear down 2. Flaps 0-20 2. Flaps down 3. Check induction air-cold 3. Check induction air-cold 4. Mixture rich 4. Mixture rich 5. Propeller full in 5. Propeller full in 6. Check cowl flaps open 6. Check cowl flaps closed 7. Check fuel selector on fullest tank 7. Check fuel selector on fullest tank” or (i) “This airplane must be operated as a normal category airplane in compliance with the operating limitations as stated in the form of placards, markings and manuals. No acrobatic maneuvers, including spins, approved. Maximum maneuvering speed - 130 mph - CAS. Maximum design weight 2900 lb. Ma ximum flight maneuver load factors - Flaps up +3.8, -1.52; Flaps down +3.5. Maximum gear extension speed 160 mph - CAS. Maximum flap extension speeds 10° flaps - 160mph - CAS; 10° - 40° flaps - 110 mph - CAS. Before takeoff Before landing 1. Set tabs 1. Gear down 2. Fuel selector full tank 2. Fuel selector full tank 3. Cowl flaps open 3. Cowl flaps closed 4. Mixture rich 4. Mixture rich 5. Propeller full in 5. Propeller full in 6. Flaps 0° -20° 6. Flaps down” (2) On the control lock: "Control lock - remove before starting engine." (3) On the upper pack cover: "To extend gear manually, place gear handle in full down position, pull emergency handle and pump vertically." 3A21 Page 28 of 45 Rev. 50 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) A. (4) On fuel selector valve plate: "Both off. Left tank - 27.5 gal. Right tank 27.5 gal. Use full rich mixture to switch tanks. Take off and land on fullest tank." (5) On the baggage door: "Maximum baggage 120 lb. For additional loading instructions see weight and balance data." (6) On the fuel tank filler cap: "Tank capacity 32.5 U.S. gallons, 100/130." (7) On the instrument panel directly below the fuel gauge indicators: "Avoid landing approaches in red arc and over 30 second slips under 1/2 tank. (Reference Owner's Manual)." (8) In full view of the pilot: "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP ON ADJUST MIXTURE 2. SELECT OPPOSITE TANK 3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS." B. Applicable to Models 210B/210C (1) In full view of the pilot: "This airplane must be operated as a normal category airplane in compliance with the operating limitations as stated in the form of placards, markings and manuals. No acrobatic maneuvers including spins approved. Maximum maneuvering speed - 132 m.p.h. - CAS. Maximum design weight 3000 lb. Maximum f light maneuvering load factors - Flaps up +3.8, -1.52; Flaps down +3.5. Maximum gear extension speed 160 m. p.h. - CAS; Maximum flap extension speeds 10° flaps - 160 m.p.h. - CAS; 10°-40° flaps - 110 m.p.h. - CAS. Before Takeoff Before Landing 1. Set tabs 1. Gear down 2. Fuel selector 2. Fuel selector full tank 3. Cowl flaps open 3. Cowl flaps closed 4. Mixture rich 4. Mixture rich 5. Propeller full in 5. Propeller full in 6. Flaps 0-20 6. Flaps down.” (2) On the control lock: "Control lock - remove before starting engine." (3) On the upper pack cover: "To extend gear manually, place gear handle in full down position, pull emergency handle and pump vertically." (4) On fuel selector valve plate: "Both off. Le ft tank - 31.7 gal. Right tank - 31.7 gal. Use full rich mixture to switch tanks. Take off and land on fullest tank." (5) On the baggage door: "Maximum baggage 120 lb. For additional loading instructions see weight and balance data." (6) On the fuel tank filler cap: "Tank capacity 32.5 U.S. gallons, 100/130." (7) In full view of the pilot: "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP ON ADJUST MIXTURE 2. SELECT OPPOSITE TANK 3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS." Rev. 50 Page 29 of 45 3A21 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) C. Applicable to Model 210-5(205) and 210-5A(205A) (1) In full view of the pilot: "This airplane must be operated as a normal category airplane in compliance with the operating limitations as stated in the form of placards, markings and manuals. No acrobatic maneuvers including spins approved. Maximum maneuvering speed - 138 m.p.h. - CAS. Maximum design weight 3300 lb. Maximum flight maneuvering load factors - Flaps up +3.8, -1.52; Flaps down +3.0; altitude load in stall recovery 200 ft.; Flap extension speed - 110 m.p.h. - CAS." (2) On the control lock: "Control lock - remove before starting engine." (3) On fuel selector valve plate: "Both off. Left tank - 31.7 gal. Right tank - 31.7 gal. Use full rich mixture to switch tanks. Take off and land on fullest tank." (4) On the fuel tank filler cap: "Tank capacity 32.5 U.S. gallons, 100/130." (5) In full view of the pilot: "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP ON ADJUST MIXTURE 2. SELECT OPPOSITE TANK 3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS SEE PROCEDURE CARD D1189013 FOR EXPANDED INSTRUCTIONS." D. Applicable to Models 210D/210E (1) In full view of the pilot: "This airplane must be operated as a normal category airplane in compliance with the operating limitations as stated in the form of placards, markings and manuals. No acrobatic maneuvers including spins approved. Maximum maneuvering speed - 134 m.p.h. - CAS. Maximum design weight 3100 lb. Maximum flight maneuvering load factors - Flaps up +3.8, -1.52; Flaps down +3.5. Maximum gear extension speed 160 m.p.h. - CAS; Maximum flap extension speeds 10°, flaps - 160 m.p.h. - CAS; 10°-40° flaps - 110 m.p.h. - CAS; altitude loss in stall recovery 130 ft. Before Takeoff Before Landing 1. Set tabs 1. Gear down 2. Fuel selector full tank 2. Fuel selector full tank 3. Cowl flaps open 3. Cowl flaps closed 4. Mixture rich 4. Mixture rich 5. Propeller full in 5. Propeller full in 6. Flaps 0-20 6. Flaps down.” (2) On the control lock: "Control lock - remove before starting engine." (3) On the upper pack cover: "To extend gear manually, place gear handle in full down position, pull emergency handle out and pump vertically." (4) On fuel selector valve plate: "Both off. Left tank - 31.7 gal. Right tank - 31.7 gal. Use full rich mixture to switch tanks. Take off and land on fullest tank." (5) On baggage door: "Maximum weight each child's seat, 140 lb. Refer to weight and balance data for baggage/cargo loading." (6) On the fuel tank filler cap: "Tank capacity 32.5 U.S. gallons, 100/130." (7) Above selector valve: "Turn pump on 'HI' when switching from a dry tank to a tank containing f u e l . " 3A21 Page 30 of 45 Rev. 50 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) D. (8) In full view of the pilot: "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP ON ADJUST MIXTURE 2 SELECT OPPOSITE TANK 3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS." E. Applicable to Models 210F/T210F (1) In full view of the pilot: "This airplane must be operated as a normal category airplane in compliance with the operating limitations as stated in the form of placards, markings and manuals. No acrobatic maneuvers including spins approved. Maximum maneuvering speed - 131.0 m.p.h. - CAS. Maximum design weight 3300 lb. Maximum flight maneuvering load factors - Flaps up +3.8, -1.52; Flaps down +3.0. Maximum gear extension speed 160 m.p.h. - CAS; Maximum flap extension speeds 10° flaps - 160 m.p.h. - CAS; 10°-40° flaps - 110 m.p.h. - CAS; Altitude loss in stall recovery 240 feet. Before Takeoff Before Landing 1. Set tabs 1. Gear down 2. Fuel selector full tank 2. Fuel selector full tank 3. Cowl flaps open 3. Cowl flaps closed 4. Mixture rich 4. Mixture rich 5. Propeller full in 5. Propeller full in 6. Flaps 0-20 6. Flaps down.” (2) On control lock: "Control lock - remove before starting engine." (3) On the power pack cover: "To extend gear manually, place gear handle in full down position, pull emergency handle and pump vertically." (4) On fuel selector valve plate: "Both off. Left tank - 31.5 gal. Right tank - 31.5 gal. Use full rich mixture to switc h tanks. Take off and land on fullest tank." (5) On baggage door: "Maximum weight each child's seat, 140 lb. Refer to weight and balance data for baggage/cargo loading." (6) On the fuel tank filler cap: "Tank capacity 32.5 U.S. gallons, 100/130." (7) Above selector valve: "Turn pump on 'HI' when switching from a dry tank to a tank containing fuel." (8) Near the engine power instruments: (T210F only) *Altitude in Feet Manifold Fuel Flow Sea Level to: Pressure in. Hg. Gal/Hr 19,000 32.5 28 20,000 31.5 26 22,000 29.5 24 24,000 27.5 22 26,000 25.5 20 28,000 23.5 19 30,000 21.5 18 75% power climb - 2500 r.p.m. - 27.5 manifold pressure - 20 g.p.h." (9) On instrument panel above fuel boost pump switch: "Use 'HI' for emergency only ." Rev. 50 Page 31 of 45 3A21 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) (10) In full view of the pilot: "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP ON ADJUST MIXTURE 2. SELECT OPPOSITE TANK 3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS." F. Applicable to Models 210G, T210G, 210H, T210H, 210J, T210J (1) In full view of the pilot: "This airplane must be operated as a normal category airplane in compliance with the operating limitations as stated in the form of placards, markings and manuals. No acrobatic maneuvers , including spins, approved. Maximum maneuvering speed - 135 m.p.h. - (CAS). Maximum design weight 3400 lb. Maximum flight maneuvering load factors - Flaps up +3.8, -1.52; Flaps down +3.0. Maximum gear extension sp eed - 160 m.p.h. - (CAS); Maximum flap extension speeds 10° flaps - 160 m.p.h. - (CAS); 10°-30° flaps - 110 m.p.h. - (CAS); Altitude loss in stall recovery 250 feet. Before Takeoff Before Landing 1. Set tabs 1. Gear down 2. Fuel selector full tank 2. Fuel selector full tank 3. Cowl flaps open 3. Cowl flaps closed 4. Mixture rich 4. Mixture rich 5. Propeller full in 5. Propeller full in 6. Flaps 0-20 6. Flaps down.” (2) On control lock: "Control lock - remove before starting engine" (3) On the power pack cover: "To extend gear manually, place gear handle in full down position, pull emergency handle out and pump vertically." (4) On fuel selector valve plate: "Both off. Left-44.5 gal. Right-44.5 gal. Use full rich mixture to switch tanks. Take off and land on fullest tank." (5) On baggage door: "Maximum weight each child's seat 140 lb. Refer to weight and balance data for baggage/cargo loading." (6) Aft of the filler cap on the adapter plate: "Tank capacity 45.0 U.S. gallons. Service this airplane with 100/130 minimum grade aviation gasoline." (7) Above selector valve: "Turn pump on 'HI' when switching from a dry tank to a tank containing fuel." (8) Near the engine power instruments: (T210G/T210H/T210J) *Altitude in Feet Manifold Fuel Flow Sea Level to: Pressure in. Hg. Gal/Hr 19,000 32.5 28 20,000 31.5 26 22,000 29.5 24 24,000 27.5 22 26,000 25.5 20 28,000 23.5 19 30,000 21.5 18 75% power climb - 2500 r.p.m. - 27.5 manifold pressure - 20 g.p.h." (9) On instrument panel above fuel boost pump switch: "Use 'HI' for emergency only ." 3A21 Page 32 of 45 Rev. 50 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) (10) In full view of the pilot: "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP ON ADJUST MIXTURE 2. SELECT OPPOSITE TANK 3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS." G. Applicable to Model 210K/T210K (S/N 21059200 through 21059351) (1) In full view of the pilot: "This airplane must be operated as a normal category airplane in compliance with the operating limitations as stated in the form of placards, markings and manuals. No acrobatic maneuvers, including spins, approved. Maximum maneuvering speed - 135 m.p.h.(CAS). Maximum design weight 3800 lb. Maximum f light maneuvering load factors - Flaps up +3.8, -1.52; Flaps down +2.0. Maximum gear extension speed - 160 m. p.h.- (CAS); Maximum flap extension speed 10° flaps - 160 m.p.h. - (CAS); 10°-30° flaps - 110 m.p.h. - (CAS); Altitude loss in stall recovery 300 feet. Checklist Placard Before Takeoff Before Landing 1. Adjust trim controls 1. Fuel selector full tank 2. Fuel selector full tank 2. Gear down 3. Cowl flaps open 3. Cowl flaps closed 4. Mixture rich 4. Mixture rich 5. Propeller full in 5. Propeller full in 6. Flaps 0-10 6. Flaps down.” (2) On control lock: "Control lock - remove before starting engine." (3) On the power pack cover: "To extend gear manually, place gear handle in full down position, pull emergency handle and pump vertically." (4) On fuel selector valve plate: "Both off. Left on-44.5 gal. Right on -44.5 gal. Take off and land on fuller tank." (5) On baggage door: "Maximum bagga ge 120 lb. Refer to weight and balance data for baggage/cargo loading." (6) Aft of the filler cap on the adapter plate: "Tank capacity 45.0 U.S. gallons. Service this airplane with 100/130 minimum grade aviation gasoline." (7) Above selector valve: "When switchi ng from a dry tank turn pump on 'HI' momentarily." (8) Above fuel flow and manifold pressure indicator: (Model 210K) "Fuel flow at Full Throttle 2700 r.p.m. 2850 r.p.m. Sea Level 23 gal/hr 24 gal/hr 4000 ft. 21 gal/hr 22 gal/hr 8000 ft. 19 gal/hr 20 gal/hr” (9) Near the engine power instruments: (Model T210K) *Altitude in Feet Manifold Fuel Flow Sea Level to: Pressure in. Hg. Gal/Hr 19,000 32.5 28 20,000 31.5 26 22,000 29.5 24 24,000 27.5 22 26,000 25.5 20 28,000 23.5 19 30,000 21.5 18 75% power climb - 2500 r.p.m. - 27.5 manifold pressure - 20 g.p.h." Rev. 50 Page 33 of 45 3A21 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) (10) On flap control indicator: "a. 0°-10° - T.O. (Takeoff ra nge with blue color code and 160 m.p.h. callout; also mechanical detent at 10°)" "b. 10°-20° - Full (Indices at th ese positions with white color code and 110 m.p.h. callout; also, mechanical detent at 20°." (11) In plain view of the pilot: "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP ON ADJUST MIXTURE 2. SELECT OPPOSITE TANK 3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS.” H. Applicable to Model 210K/T210K (S/N 21059352 through 21059502) Applicable to Model 210L/T210L (S/N 21059503 through 21061039) (1) In full view of the pilot: (a) Applicable to Model 210K/T210K (S/N 21059352 through 21059502) Applicable to Model 210L/T210L (S/N 21059503 through 21061039) "This airplane must be operated as a normal category airplane in compliance with the operating limitations as stated in the form of placards, markings, and manuals. MAXIMUMS Maneuvering speed 135 m.p.h. CAS (117 knots) Gear extension speed 160 m.p.h. CAS (139 knots) Gross weight 3800 lbs. Flight load factor Flaps up +3.8, -1.52 Flaps down +2.0 No acrobatic maneuvers, including spins, approved. Altitude loss in a stall recovery - 300 ft. Known icing conditions to be avoided. This airplane is certificated for the following flight operations as of date of original airworthiness certificate: DAY - NIGHT - VFR - IFR" (As applicable) (b) Applicable to Model 210L/T210L (S/N 21061040 and up) "This airplane must be operated as a normal category airplane in accordance with the operating limitations as stated in the form of placards, markings, and manuals. MAXIMUMS Maneuvering speed (IAS) 119 knots Gear extension speed (IAS) 140 knots Gross weight 3800 lbs Flight load factor Flaps up +3.8, -1.52 Flaps down +2.0 No acrobatic maneuvers, including spins, approved. Altitude loss in a stall recovery - 300 ft. Flight into known icing conditions prohibited. This airplane is certified for the following flight operations as of date of original airworthiness certificate: DAY - NIGHT - VFR - IFR" (As applicable) 3A21 Page 34 of 45 Rev. 50 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) Checklist Placard (Model 210K/T210K)(S/N 21059352 through 21059502) “Checklist Placard” Before Takeoff Before Landing 1. Adjust trim controls 1. Fuel selector full tank 2. Fuel selector full tank 2. Gear down 3. Cowl flaps open 3. Cowl flaps closed 4. Mixture rich 4. Mixture rich 5. Propeller full in 5. Propeller full in 6. Flaps 0-10 6. Flaps down.” Checklist (Model 210L/T210L)(S/N 21059503 through 21060539) (Stowed - not required for flight) “Cessna 210L & T210L or Centurion & Centurion II (as applicable) Checklist” Before Takeoff Before Landing 1. Controls - free and correct 1. Fuel selector - fullest tank 2. Elevator and rudder trim - set 2. Landing gear - DN 160 m.p.h. max 3. Fuel seelctor - fullest tank 3. Mixture - rich 4. Cowl flaps - open 4. Propeller - high r.p.m. 5. Propeller - high r.p.m. 5. Airspeed - 100 m.p.h. flaps up 6. Mixture - as required 90 m.p.h. flaps down” 7. Flaps - 0 to 10 8. Instruments - check and set 9. Seats and belts - secure (2) On control lock: "Control lock - remove before starting engine." (3) On the power pack cover: (210K/T210K) (S/N 21059200 through 21059502) To extend gear manually, place gear handle in full down position, pull emergency handle out and pump vertically." On hand pump cover: (210L/T210L) (S/N 21059503 and up) "Manual gear extension: 1. select gear dow n; 2. pull handle forward; 3. pump vertically." (4) On fuel selector valve plate: "Off. Left on -44.5 gal. Right on -44.5 gal. Takeoff and land on fuller tank." (5) On baggage door: "Maximum baggage 120 lb. Refer to weight and balance data for baggage/cargo loading." (6) Aft of the filler cap on the adapter plate: "Service this airplane with 100/130 minimum aviation grade gasoline. Total capacity 45.0 gal." (7) Above fuel selector valve: "When switc hing from dry tank, turn pump on 'HI' momentarily" (210L/T210L) (S/N 21059503 through 21060089) Above fuel selector valve: "When switchi ng from dry tank, turn Auxiliary fuel pump 'ON' momentarily" (210L/T210L) (S/N 21060090 and up). (8) In front of pilot on lower instrument panel knee pad: "Alternate static air  on." (9) Above ammeter: "Do not turn off alternat or in flight except in emergency." (Model 210K/T210K) (S/N 21059200 through 21059502) (10) Adjacent to overvoltage light: "High voltage" (Models 210L/T210L) (S/N 21059503 and up) Rev. 50 Page 35 of 45 3A21 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) (11) Above left fuel gauge: "Do not turn off a lternator in flight except in emergency." (Models 210L/T210L) (S/N 21059503 through 21059719) (12) Above fuel flow and manifold pressure indicator: (Model 210K/210L) "Fuel flow at full throttle 2700 r.p.m. 2850 r.p.m. S.L. 138 lbs/hr 144 lbs/hr 400 ft. 126 lbs/hr 132 lbs/hr 8000 ft. 114 lbs/hr 120 lbs/hr" (13) Near the engine power instruments: (Models T210K/T210L) "Max. allowable manifold press. & climb fuel flow Alt.-ft/1000 SL-19 20 22 24 26 28 30 M.P.-In. Hg. 32.5 31.5 29.5 27.5 25.5 23.5 21.5 Fluel flow-lbs/hr 168 156 144 132 120 114 108 75% power climb - 2500 r.p.m., 27.5 in. M.P., 120 lbs/hr" (14) On lower surface of right hand wing just outboard of fuselage: "Oxygen filler door." (All models with oxygen) (15) On flap control indicator: (210K/T210K) (S/N 21059352 through 21059502) "a. 0°-10° (Takeoff range with blue color c ode and 160 m.p.h. callout; also mechanical detent a t 1 0 ° ) b. 10°-20° Full (Indices at these positions with white color code and 110 m.p.h. callout; also mechanical detent at 20°)" On flap control indicator: (210L/T210L) (S/N 21059503 through 21061039) "a. 0°-10° (Takeoff range with blue color c ode and 160 m.p.h. callout; also mechanical detent a t 1 0 ° ) b. 10°-20° Full (Indices at these positions with white color code 120 m.p.h. callout; also mechanical detent at 20°)" On flap control indicator: (210L/T210L) (S/N 21051040 and up) "a. 0°-10° (Takeoff range with blue co lor code and 140 knots callout; also mechanical detent at 10°) b. 10°-20° - Full (Indices at these positi ons with white color code and 105 knots callout; also mechanical detent at 20°)" (16) On inside nose wheel doors: "WARNING - before working in wheel well area pull hydraulic pump circuit breaker off." (Model 210L/T210L) (S/N 21059503 and up) (17) In full view of the pilot: "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP ON ADJUST MIXTURE 2. SELECT OPPOSITE TANK 3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS." 3A21 Page 36 of 45 Rev. 50 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) J. Applicable to Model 210M/T210M, 210N/T210N, 210R/T210R (1) In full view of the pilot: (a) Applicable to Model 210M/T210M (S/N 21061574 through 21062273) "This airplane must be operated as a normal category airplane in compliance with operating limitations as stated in the form of placards, markings and manuals. MAXIMUMS Maneuvering speed (IAS) 119 knots Gear extension speed (IAS) 140 knots Gross weight 3800 lbs. Flight load factor Flaps up +3.8, -1.52 Flaps down +2.0 No acrobatic maneuvers, including spins, approved. Altitude loss in a stall recovery - 300 ft. Flight into known icing conditions prohibited. This airplane is certified for the following flight operations as of date of original airworthiness certificate: DAY - NIGHT - VFR - IFR" (As applicable) (b) Applicable to Model 210M/T210M (S/N 21061042, 21062274 through 21062954 "This airplane must be operated as a normal category airplane in compliance with the operating limitations as stated in the form of placards, markings and manuals. " MAXIMUMS Maneuvering speed (IAS) 119 knots Gross weight 3800 lbs. Flight load factor Flaps up +3.8, -1.52 Flaps down +2.0 No acrobatic maneuvers, including spins, approved. Altitude loss in a stall recovery 300 ft. Flight into known icing conditions prohibited. This airplane is certified for the following flight operations as of date of original airworthiness certificate: DAY - NIGHT - VFR - IFR" (As applicable) (c) Applicable to Models 210N/T210N (S/N 21062955 through 21064535) "The markings and placards installed in this airplane contain operating limitations which must be complied with when operating this airplane in the Normal Category. Other operating limitations which must be complied with when operating this airplane in this category are contained in the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. No acrobatic maneuvers, including spins, approved. Flight into known icing conditions prohibited. This airplane is certified for the following flight operations as of date of original airworthiness certificate: DAY - NIGHT - VFR - IFR" (As applicable) (2) On control lock through 21064535: "Contro l Lock - Remove Before Starting Engine." (3) On the hand pump cover: (S/N 21061574 through 21062273) "Manual gear extension: 1. Select gear down; 2. pull handle forward; 3. pump vertically." (S/N 21061042, 21062274 through 21064535) "Manual gear extension: 1. Select gear down; 2. pull handle forward; 3. pump vertically. CAUTION: Do not pump with gear up selected" Rev. 50 Page 37 of 45 3A21 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) (4) On fuel selector valve plate through 21064535: "Off. Left on - 44.5 gal. Right on - 44.5 gal. Takeoff and land on fuller tank." (5) 210M/T210M (S/N 21061042, 21061574 through 21062954) On baggage door: "Maximum baggage 120 lb . Refer to weight and balance data for baggage/cargo loading." 210N/T210N (S/N 21062955 through 21064535) On baggage door: "Maximum baggage 200 lbs. total. Refer to weight and balance data for baggage/cargo loading." (6) Near the wing filler caps: (S/N 21061574 through 21062273) "Service this airplane with 100/130 minimum aviation grade gasoline. Total capacity 45.0 gal." (S/N 21061042, 21062274 through 21064535) "Service this airplane with 100LL/100 minimum aviation grade gasoline. Total capacity 45.0 gal." (7) Near fuel selector valve through 21064535: "When switching from dry tank, turn auxiliary fuel pump on momentarily." (8) In front of pilot on lower instrument panel: (S/N 21061574 through 21062273) "Alternate static air  pull on." (S/N 21061042, 21062274 through 21064535) "Alternate static air pull on." (9) 210M/T210M (S/N 21061042 through 21062954) Adjacent to overvoltage light: "High Voltage." 210N/T210N (S/N 21062955 through 21064535) Adjacent to low voltage light: "Low Voltage" (10) Near the engine power instruments (Model 210M, S/N 21061574 through 21062954): "Fuel Flow at Full Throttle 2700 r.p.m. 2850 r.p.m. S.L. 138 lbs/hr 144 lbs/hr 400 ft. 126 lbs/hr 132 lbs/hr 8000 ft. 114 lbs/hr 120 lbs/hr” "Max. power setting Takeoff (5 min. only) 2850 r.p.m. Max. continuous power 2700 r.p.m." Near the engine power instruments (Model 210N, S/N 21062955 through 21064535: "Min. Fuel Flows at Full Throttle 2700 r.p.m. 2850 r.p.m. S.L. 138 lbs/hr 144 lbs/hr 4000 ft. 126 lbs/hr 132 lbs/hr 8000 ft. 114 lbs/hr 120 lbs/hr 12000 ft. 102 lbs/hr 108 lbs/hr" 3A21 Page 38 of 45 Rev. 50 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) (11) Near the engine power instruments (T210M): (S/N 21061574 through 21062273) "Maximum power setting & fuel flow T.O. (5 min. only): 2700 r.p.m. Normal climb: 2500 r.p.m. 36.5 in. mp., 186 lbs/hr 30.0 in. mp., 126 lbs/hr Max. continuous power: 2600 r.p.m. Alt.-ft/1000 SL-17 18 20 22 24 26 28 30 M.P.-In. Hg. Fuel flow-lbs/hr 35 162 34 156 32 144 30 132 28 120 26 108 24 102 22 96” "Avoid continuous operation between 1850 and 2150 r.p.m. above 24 in. M.P." (S/N 21061042, 21062274 through 21062953) "Maximum power setting & fuel flow T.O. (5 min. only): 2700 r.p.m. Normal climb: 2500 r.p.m. 36.5 in. mp., 186 lbs/hr 30.0 in. mp., 120 lbs/hr Max. continuous power: 2600 r.p.m. Alt.-ft/1000 SL-17 18 20 22 24 26 M.P.-In. Hg. 35 34 32 30 28 26 Fuel flow-lbs/hr 162 156 144 132 120 108 28 24 102 30 22 96” "Avoid continuous operation between 1850 and 2150 r.p.m. above 24 in. M.P." Near the engine power instruments (T210N, S/N 21062955 through 21064535): "Minimum Fuel Flows T.O.: 2700 r.p.m. 36.5 in. mp., 186 lbs/hr Maximum continuous power: 2600 r.p.m. Alt.-ft/1000 SL-17 18 20 22 24 26 28 30 M.P.-In. Hg. Fuel flow-lbs/hr 35 162 34 156 32 144 30 132 28 120 26 108 24 102 22 96” "Avoid continuous operation between 1850 and 2150 r.p.m. above 24 in. M.P." (12) On lower surface of right hand wing just outboard of fuselage through 21064535: “Oxygen filler door." (All models with oxygen.) (13) On flap indicator: (S/N 21061574 through 21062273) a. "0° - 10° - (Partial flap range with bl ue color code and 140 knots callout; also, mechanical detent at 10°)" b. "10°- 20° - Full - (Indices at these pos itions with white color code and 105 knots callout; also, mechanical detent at 20°)" (S/N 21061042, 21062274 through 21063640) a. "0° - 10° - (Partial flap range with blue color code and 150 knots callout; also, mechanical detent at 10°)" b. "10°- 20° - Full - (Indices at these positi ons with white color code and 115 knots callout; also, mechanical detent at 20°)" (S/N 21063641 through 21064535) a. "0° - 10° - (Partial flap range with dark blue color code and 160 knot callout; also, mechanical detent at 10°)" b. "10°- 20° - (Indices at these positions with light blue color code and 130 knot callout; also, mechanical detent at 10°)" c. "20°- 30° - (Indices at these positions with white color code and 115 knot callout)" Rev. 50 Page 39 of 45 3A21 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) (14) On inside nose wheel doors, strut doors and main wheel doors through 21062954 and on inside of nose wheel doors S/N 21064535: "Warning - Before working in the wheel well area pull hydraulic pump circuit breaker off." (15) Applicable to the Model 210M: (S/N 21062274 through 21062954) Near the gear selector handle: "Maximum speed IAS Gear oper. 140 knots Gear down 199 knots" (16) Applicable to the Model T210M: (S/N 21061042, 21062274 through 21062953) Near the gear selector handle: "Maximum speed IAS Gear oper. 140 knots Gear down 195 knots" (17) Applicable to the Model 210N: (S/N 21062955 through 21064535) Near the gear selector handle: "Maximum speed IAS Gear oper. 165 knots Gear down 200 knots" (18) Applicable to the Model T210N: (S/N 21062955 through 21064535) Near the gear selector handle: "Maximum speed IAS Gear oper. 165 knots Gear down 203 knots" (19) Near the airspeed indicator (a) Model 210N (S/N 21062955 through 21064535) "Maneuver Speed 125 KIAS" (b) Model T210N (S/N 21062955 through 21064535) "Maneuver Speed 130 KIAS" (20) Near the fuel cap Models 210N/T210N (S/N 21062955 through 21063640) "For 32 gal. fuel load fill to bottom of filler neck extension." Models 210N/T210N (S/N 21063641 through 21064535) "Capacity 33.5 gallons to bottom of filler neck extension." (21) Near the oil filler Models 210N/T210N (S/N 21062955 through 21064135) "Oil 10 qts." (22) On the nose gear strut Models 210N/T210N (S/N 21062955 through 21064135) "WARNING Release air and fluid pressure before removing any part of this assembly." 3A21 Page 40 of 45 Rev. 50 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) (23) In full view of the pilot: (a) Models 210M/T210M (S/N 21061574 through 21062954) "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP ON ADJUST MIXTURE 2. SELECT OPPOSITE TANK 3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS." (b) Model 210N (S/N 21062955 through 21063640) "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP ON ADJUST MIXTURE 2 SELECT OPPOSITE TANK 3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS SEE P.O.H. FOR EXPANDED INSTRUCTIONS." (c) Model T210N (S/N 21062955 through 21064535) "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP ON, ADJUST MIXTURE 2. SELECT OPPOSITE TANK 3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS SEE P.O.H. FOR EXPANDED INSTRUCTIONS." (24) Effective S/N 21064536 and up: "All placards required in the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual must be installed in the appropriate locations." K. Applicable to Model P210N and P210R (1) In full view of the pilot: Model P210N (S/N P21000001 through P21000150) "This airplane must be operated as a normal category airplane in compliance with the operating limitations as stated in the form of placards, markings and manuals. MAXIMUMS Operating altitude 23,000 ft. Maneuvering speed (IAS) 130 knots Gross weight Takeoff 4000 lbs. Landing 3800 lbs. Flight load factor Flaps up +3.8, -1.52 Flaps down +2.0 No acrobatic maneuvers, including spins, approved. Landing with cabin pressurized is prohibited. Altitude loss in a stall recovery - 300 ft. Flight into known icing conditions prohibited. This airplane is certified for the following flight operations as of date of original airworthiness certificate: DAY - NIGHT - VFR - IFR" (As applicable) Model P210N (S/N P21000151 and up) "The markings and placards installed in this airplane contain operating limitations which must be complied with when operating this airplane in the Normal Category. Other operating limitations which must be complied with when operating this airplane in this category are contained in the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. No acrobatic maneuvers, including spins, apaproved. Landing with cabin pressurized is prohibited. Flight into known icing conditions prohibited. This airplane is certified for the following flight operations as of date of original airworthiness certificate: DAY - NIGHT - VFR - IFR" (As applicable) Rev. 50 Page 41 of 45 3A21 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) K. (2) On control lock through P21000760: "Cont rol Lock - Remove Before Starting Engine." (3) On the hand pump cover through P21000760: "Manual gear extension: 1. Select gear down; 2. pull handle forward; 3. pump vertically. CAUTION: Do Not Pump With Gear Up Selected." (4) On fuel selector valve plate through P21000760: "Off. Left on - 44.5 gal., Right on - 44.5 gal., Takeoff and land on fuller tank" (5) On baggage door through P21000760: "Maximum baggage 200 lbs. total. Raised area aft of baggage door 80 lbs. maximum. Refer to weight and balance data for baggage cargo loading." (6) Near the wing filler caps through P21000760: "Service this airplane with 100LL/100 minimum aviation grade gasoline. Total capacity 45.0 gal." (7) Near fuel selector valve through P21000760: "When switching from dry tank, turn auxiliary fuel pump on momentarily." (8) P210N (S/N P21000001 through P21000150) Adjacent to over voltage light: "HIGH VOLTAGE" P210N (S/N P21000151 through P21000760) Adjacent to low voltage light: "LOW VOLTAGE" (9) Near the engine power instruments through P21000760: "Minimum Fuel Flows TAKEOFF MAX. CONTINUOUS POWER: 2600 RPM 2700 R.P.M. ALT-FT/1000 SL-17 18 19 20 21 22 23 36.5 In.M.P M.P. IN. HG. 35.5 34.5 33.5 32.5 31.5 30.5 29.5 180 LBS/HR Fuel Flow - lbs/hr 162 156 150 144 138 132 126" (10) On flap indicator: P210N (S/N P21000001 through P21000385) a. "0° - 10° - (Partial flap range with dark blue color code and 150 knots callout; also, mechanical detent at 10°)" b. "10°- 20° - Full - (Indices at these positi ons with white color code and 115 knot callout; also, mechanical detent at 20°)" P210N (S/N P21000386 through P21000760) a. "0° - 10° - (Partial flap range with dark blue color code and 160 knot callout; also, mechanical detent at 10°)" b. "10°- 20° - Full - (Indices at these positions with light blue color code and 130 knot callout; also, mechanical detent at 20°)" c. "20°- 30° - (Indices at these positions with white color code and 115 knot callout)" ( F u l l ) (11) On inside nose wheel doors, strut doors and main wheel doors: "Warning - Before working in wheel well area pull hydraulic pump circuit breaker off." 3A21 Page 42 of 45 Rev. 50 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) (12) Near the gear selector handle: P210N (S/N P21000001 through P21000150) "Maximum speed IAS Gear oper. 140 knots Gear down 200 knots" P210N (S/N P21000151 through P21000760) "Maximum speed IAS Gear oper. 165 knots Gear down 200 knots" (13) Near the pilot's outside door handle through P21000760: "Close Open " (14) Near the emergency button to unlock the pilot's cabin door from the outside through P21000760: "Emergency Push to unlock" (15) Near the secondary lock for the inside pilot's door handle through P21000760: “Door Handle Safety Lock Push Flush to Lock Pull To Unlock" (16) Near the pilot's inside door handle through P21000760: "Close Open  Lock" (17) Near the right exit handle through P21000760: "Open  Close  Latch Push Flush to Lock Close and Lock for Flight" (18) Near the airspeed indicator: P210 (S/N P21000151 through P21000760) "Maneuver Speed - 130 KIAS" (19) Near the oil filler: P210N (S/N P21000151 through P21000760) "Oil 10 qts" (20) Near the fuel cap: P210N (S/N P21000151 through P21000760) "For 32 gal. fuel load fill to bottom of filler neck extension." (21) On emergency exit through P21000760: "Emergency Exit - To Open 1. Lift handle (Do not pull inward) 2. Rotate counter clockwise to 'OPEN' position 3. Push door outward" Rev. 50 Page 43 of 45 3A21 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) (22) On the main cabin door through P21000760: "Door Handle Safety Lock Push Flush To Lock Pull to Unlock" And "To Open Door 1. Unlock safety lock (pull out) 2. Rotate handle to 'OPEN' position 3. Push door outward" (23) In full view of the pilot: S/N P21000001 through P21000150 "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP ON ADJUST MIXTURE 2. SELECT OPPOSITE TANK 3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS." S/N P21000151 through P21000760: "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP ON ADJUST MIXTURE 2. SELECT OPPOSITE TANK 3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS SEE P.O.H. FOR EXPANDED INSTRUCTIONS." (24) When equipped with optional EGT gauge: - On the left forward side panel near instrument panel (S/N P21000001 through P21000150): "EGT LIMITATION USE OF EGT GAUGE IS PROHIBITED AT ALL R.P.M. SETTINGS ABOVE 2500 R.P.M. AT ALL ALTITUDES" (25) When equipped with optional EGT gauge: - On the left side panel near instrument panel (S/N P21000001 through P21000150): "EGT LIMITATIONS USE OF EGT GAUGE IS PROHIBITED AT ALL POWER SETTINGS ABOVE 80% AT ALL ALTITUDES; OR ABOVE THE FOLLOWING POWERS AT THE LISTED ALTITUDES WHEN OAT IS ABOVE STANDARD. 75% AT 17,000 FEET OR HIGHER 70% AT 20,000 FEET OR HIGHER 65% AT 22,000 FEET OR HIGHER CONTINUOUS OPERATION LEANER THAN SHOWN IN THE TABLE IS PROHIBITED." EXHAUST GAS TEMPERATURE (°F RICH OF PEAK) POWER 2500 R.P.M. 2400 R.P.M. 2300 R.P.M. 2200 R.P.M. 76 to 80% 100% 75% 75% 50% 71 to 75% 75 75 50 50 66 to 70% 75 50 50 25 61 to 65% 50 50 25 25 56 to 60% 50 25 25 Peak EGT 51 to 55% 25 25 Peak EGT Peak EGT 46 to 50% 25 Peak EGT Peak EGT Peak EGT 45% or less Peak EGT Peak EGT Peak EGT Peak EGT 2105030-1 3A21 Page 44 of 45 Rev. 50 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) (26) Effective P21000761 and up: "All placards required in the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual must be installed in the appropriate locations." NOTE 3. The cylinder head thermistors must be installed as follows: Model Cylinder Head Number 210, 210A (1960-61 Model) 3 210B, 210C, 210D (1962-63-64 Model) 1 210E,210F,210G,210H,210J (1965-66-67-68-69 Model) 2 210F,T210G,T210H,T210J (1966-67-68-69 Model) 5 210K (1970-71 Model) 3 T210K (1970-71 Model) 5 210L (1972-73-74-75-76 Model) 3 T210L (1972-73 Model) 5 T210L (1974-75-76 Model) 1 210M (1977 Model) 3 210M (1978 Model) 1 T210M (1977-78 Model) 1 P210N (1978-81 Model) 5 210N (1979-81 Model) 1 T210N (1979 Model) 1 T210N (1980-81 Model)(Non Air Cond) 5 or 1 T210N (1980-81 Model)(With Air Cond) 1 P210N (1982-83 Model) 4 210N, 210R (1982 Model and up)(Non Air Cond) 4 210N, 210R (1982 Model and up)(With Air Cond) 1 T210N (1982 Model and up) 3 P210R, T210R (1985 Model and up) 1 NOTE 4. The marking of the airspeed indicator with I.A.S. provides an equivalent level of safety to CAR 3.757 when the approved airspeed calibration data presented in Section V of the Pilot's Operating Handbooks listed below is available to the pilot: 210L Cessna P/N D1069-13 (S/N 21061040 through 21061573) T210L Cessna P/N D1070-13 (S/N 21061040 through 21061573 except 21061042) 210M Cessna P/N D1094-13 (S/N 21061574 through 21062273) T210M Cessna P/N D1095-13 (S/N 21061574 through 21062273) 210M Cessna P/N D1122-13 (S/N 21062274 through 21063954) T210M Cessna P/N D1123-13 (S/N 21061042, 21062274 through 21062954) P210N Cessna P/N D1124-13 (S/N P21000001 through P21000150) 210N Cessna P/N D1151-13PH (S/N 21062955 through 21063640) T210N Cessna P/N D1152-13PH (S/N 21062955 through 21063640) P210N Cessna P/N D1153-13PH (S/N P21000151 through P21000385) 210N Cessna P/N D1186-13PH (S/N 21063641 through 21064135) T210N Cessna P/N D1187-13PH (S/N 21063641 through 21064135) P210N Cessna P/N D1188-13PH (S/N P21000386 through P21000590) 210N Cessna P/N D1207-13PH (S/N 21064136 through 21064535) T210N Cessna P/N D1208-13PH (S/N 21064136 through 21064535) P210N Cessna P/N D1209-13PH (S/N P21000591 through P21000760) 210N Cessna P/N D1226-13PH (S/N 21064536 through 21064772) T210N Cessna P/N D1227-13PH (S/N 21064536 through 21064772) P210N Cessna P/N D1228-13PH (S/N P21000761 through P21000811) 210N Cessna P/N D1244-13PH (S/N 21064773 through 21064822) T210N Cessna P/N D1245-13PH (S/N 21064773 through 21064822) P210N Cessna P/N D1246-13PH (S/N P21000812 through P21000834) 210N Cessna P/N D1265-13PH (S/N 21064823 through 21064897) T210N Cessna P/N D1266-13PH (S/N 21064823 through 21064897) 210R Cessna P/N D1288-13PH (S/N 21064898 through 21065009) Rev. 50 Page 45 of 45 3A21 Data Pertinent to All Models (cont’d) NOTE 5. Service information appli cable to Models P210N and P210R: Components subject to the establishment of a retirement life as shown below with the corresponding retirement life hours: Component Name Windshield, rear cabin top windows Side windows, and ice detector light lens Retirement Hours 13,000 hours NOTE 6. 14-volt electrical system (210/T210 series through S/N 21059502) (205 series through S/N 205-0577) 28-volt electrical system (210/T210 series effective S/N 21059503 and On) (P210 series effective S/N P21000001 and On) In addition to the placards specified above, the prescribed operating limitations indicated by an asterisk (*) under Sections I through XVIII of this data sheet must also be displayed by permanent markings. WARNING: Use of alcohol-based fuels can cause serious performance degradation and fuel system component damage, and is therefore prohibited on Cessna airplanes. --- END --- ``` ## ADs (75, first 50, in force first) - [AD 2024-14-03](https://openairdocs.org/ad/2024-14-03): Autopilot System · Garmin GFC 500 Autopilot (STC SA01866WI). Effective Aug 20, 2024 - [AD 2023-09-09](https://openairdocs.org/ad/2023-09-09): Exhaust Turbine System (Recip) · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 292 more. Effective Jul 17, 2023 - [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 2023-02-17](https://openairdocs.org/ad/2023-02-17): Fuselage Main, Structure · Textron 210N, 210R, P210N and 8 more. Effective Mar 20, 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 2020-18-01](https://openairdocs.org/ad/2020-18-01): Fuselage · Textron 172N, 172P, 172Q and 62 more. Effective Nov 12, 2020 - [AD 2020-03-16](https://openairdocs.org/ad/2020-03-16): Fuselage Main, Structure · Textron 210G, 210H, 210J and 9 more. Effective Mar 9, 2020 - [AD 2012-10-52](https://openairdocs.org/ad/2012-10-52): Turbochargers · Cessna T206H, T207A, T210F and 21 more. Effective Jun 26, 2012 - [AD 2012-10-04](https://openairdocs.org/ad/2012-10-04): Wings · Cessna 210G, 210H, 210J and 15 more. Effective Jun 5, 2012 - [AD 2011-10-09](https://openairdocs.org/ad/2011-10-09): Seat Rails and Roller Housing Inspections · Cessna 150A, 150B, 150C and 221 more. Effective Jun 17, 2011 - [AD 2008-26-10](https://openairdocs.org/ad/2008-26-10): Alternate static air source selector valve · Cessna 172, 172A, 172B and 179 more. Effective Jan 5, 2009 - [AD 2008-10-02](https://openairdocs.org/ad/2008-10-02): Part number identification placard · Cessna 172, 172R, 172RG and 64 more. Effective May 12, 2008 - [AD 2006-03-08](https://openairdocs.org/ad/2006-03-08): Vacuum pumps · Aero Advantage 14-19, 14-19-2, 14-19-3 and 299 more. Effective Mar 10, 2006 - [AD 2005-25-08](https://openairdocs.org/ad/2005-25-08): Electronic Flight Information System (EFIS) · B-N Group BN-2A, 172, 180 and 22 more. Effective Jan 23, 2006 - [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 2004-19-01](https://openairdocs.org/ad/2004-19-01): Upper shoulder harness adjusters · Cessna F150G, F150H, F150J and 129 more. Effective Nov 1, 2004 - [AD 2002-26-03](https://openairdocs.org/ad/2002-26-03): Brackett single screen air filter · Cessna 210, 210R, T207A and 21 more. Effective Feb 18, 2003 - [AD 2002-07-01](https://openairdocs.org/ad/2002-07-01): Horizontal Stabilizer Attachment Reinforcement Brackets · Cessna 207, 207A, 210G and 32 more. Effective May 13, 2002 - [AD 2000-06-01](https://openairdocs.org/ad/2000-06-01): Fuel Strainer Assembly · Cessna 150F, 150G, 150H and 163 more. Effective May 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 98-25-02](https://openairdocs.org/ad/98-25-02): Top-mounted Antenna · Bell Helicopter Textron Canada 407, 172, 172A and 243 more. Effective Dec 22, 1998 - [AD 98-20-33](https://openairdocs.org/ad/98-20-33): AFM - Limitation Section - Icing · Cessna T210R. Effective Nov 17, 1998 - [AD 98-05-14 R1](https://openairdocs.org/ad/98-05-14-R1): AFM - Limitations Section - Icing · Cessna P210N, P210R and T210N. Effective Sep 22, 1998 - [AD 98-14-03](https://openairdocs.org/ad/98-14-03): Transponders · Cessna 172, 172A, 172B and 230 more. Effective Aug 16, 1998 - [AD 97-01-13](https://openairdocs.org/ad/97-01-13): Fuel, Oil and Hydraulic Hoses · Cessna 150, 150A, 150B and 232 more. Effective Feb 3, 1997 - [AD 96-12-22](https://openairdocs.org/ad/96-12-22): Full Flow Engine Oil Adapter · Bellanca CH-300 Pacemaker, 120, 140 and 361 more. Effective Jul 31, 1996 - [AD 94-12-08](https://openairdocs.org/ad/94-12-08): Flight Manual Revision · Cessna 210G, 210H, 210J and 15 more. Effective Jul 22, 1994 - [AD 93-13-09](https://openairdocs.org/ad/93-13-09): Air Induction Hose · Engine intercooler (Aircraftsman STC SA2231CE or SA3203NM). Effective Aug 13, 1993 - [AD 91-22-01](https://openairdocs.org/ad/91-22-01): Electrical Wires · Cessna 210, 210-5 (205), 210-5A (205A) and 14 more. Effective Nov 4, 1991 - [AD 88-25-04](https://openairdocs.org/ad/88-25-04): AFM/POH Changes - Magneto · Cessna P210N, T210L, T210M and 2 more. Effective Dec 26, 1988 - [AD 88-22-07](https://openairdocs.org/ad/88-22-07): Hose Assemblies · Cessna P210N, P210R, T207 and 22 more. Effective Nov 24, 1988 - [AD 84-10-01 R1](https://openairdocs.org/ad/84-10-01-R1): Bladder Fuel Cells · Cessna 180, 180A, 180B and 103 more. Effective Jul 5, 1988 - [AD 79-10-14 R1](https://openairdocs.org/ad/79-10-14-R1): Fuel Tank Venting · Cessna 140A, 150, 150A and 172 more. Effective May 30, 1988 - [AD 86-24-07](https://openairdocs.org/ad/86-24-07): Engine Controls Installation · Cessna 150C, 150D, 150E and 142 more. Effective Jan 7, 1987 - [AD 71-09-07 R1](https://openairdocs.org/ad/71-09-07-R1): Exhaust Gases Entering Cabin · Cessna T207, T207A, T210F and 19 more. Effective Nov 26, 1986 - [AD 86-19-11](https://openairdocs.org/ad/86-19-11): Contaminated Fuel · Cessna 177, 177A, 177B and 83 more. Effective Oct 4, 1986 - [AD 85-23-07](https://openairdocs.org/ad/85-23-07): Autopilot Systems · Aerostar PA-60-700P (Aerostar 700P), 172L, 172P and 37 more. Effective Jan 27, 1986 - [AD 76-14-07 R2](https://openairdocs.org/ad/76-14-07-R2): Landing Gear Saddles · Cessna 210, 210A, 210B and 11 more. Effective Aug 28, 1985 - [AD 85-11-07 R1](https://openairdocs.org/ad/85-11-07-R1): Turbocharger Oil Reservoir · Cessna P210N, P210R and T210R. Effective Aug 9, 1985 - [AD 85-10-02](https://openairdocs.org/ad/85-10-02): Engine Induction Airbox · Cessna 206, 207, 207A and 24 more. Effective Jun 20, 1985 - [AD 85-03-01](https://openairdocs.org/ad/85-03-01): Throttle and Mixture Controls · Cessna 206, 207, 210-5 (205) and 31 more. Effective Mar 15, 1985 - [AD 85-02-07](https://openairdocs.org/ad/85-02-07): Fuel Selector · Cessna 206, 207, 207A and 45 more. Effective Mar 6, 1985 - [AD 72-03-03 R3](https://openairdocs.org/ad/72-03-03-R3): Wing Flap Actuators Jack Screw · Cessna F150F, F150G, F150H and 83 more. Effective Oct 15, 1984 - [AD 81-23-03 R2](https://openairdocs.org/ad/81-23-03-R2): Engine Exhaust System · Cessna P210N. Effective Nov 15, 1982 - [AD 82-06-10](https://openairdocs.org/ad/82-06-10): Vacuum-Driven-Attitude Instruments · Cessna 210L, 210M, 210N and 5 more. Effective Apr 15, 1982 - [AD 80-25-07 R1](https://openairdocs.org/ad/80-25-07-R1): Oil Coolers · American Champion 7ECA, 7GCAA, 7GCBC and 39 more. Effective Sep 24, 1981 - [AD 81-19-04](https://openairdocs.org/ad/81-19-04): Hose Assembly · Rajay Hose Assemblies, 500A, 500B and 87 more. Effective Sep 17, 1981 - [AD 81-15-05](https://openairdocs.org/ad/81-15-05): Engine and Airplane Modifications · Cessna P210N. Effective Jul 27, 1981 - [AD 81-15-03](https://openairdocs.org/ad/81-15-03): Engine Inlet Air Filters · Replace existing engine induction air filter (Brackett Aero Filters STC SA693CE or SA71GL). Effective Jul 20, 1981 All 75: https://openairdocs.org/tcds/3A21/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Cessna T210N](https://openairdocs.org/model/cessna-t210n): 466 aircraft (registry code 2073456) - [Cessna P210N](https://openairdocs.org/model/cessna-p210n): 421 aircraft (registry codes 2073454, 2073462) - [Cessna T210M](https://openairdocs.org/model/cessna-t210m): 321 aircraft (registry codes 2073451, 2073452) - [Cessna T210L](https://openairdocs.org/model/cessna-t210l): 305 aircraft (registry code 2073449) - [Cessna 210L](https://openairdocs.org/model/cessna-210l): 234 aircraft (registry code 2073448) - [Cessna 210](https://openairdocs.org/model/cessna-210): 188 aircraft (registry code 2073402) - [Cessna 210-5(205)](https://openairdocs.org/model/cessna-210-5-205): 143 aircraft (registry code 2073202) - [Cessna 210D](https://openairdocs.org/model/cessna-210d): 123 aircraft (registry code 2073414) - [Cessna 210M](https://openairdocs.org/model/cessna-210m): 122 aircraft (registry code 2073450) - [Cessna 210B](https://openairdocs.org/model/cessna-210b): 101 aircraft (registry code 2073410) - [Cessna 210A](https://openairdocs.org/model/cessna-210a): 85 aircraft (registry code 2073408) - [Cessna 210N](https://openairdocs.org/model/cessna-210n): 81 aircraft (registry code 2073453) - [Cessna 210E](https://openairdocs.org/model/cessna-210e): 74 aircraft (registry code 2073416) - [Cessna T210F](https://openairdocs.org/model/cessna-t210f): 65 aircraft (registry code 2073422) - [Cessna 210C](https://openairdocs.org/model/cessna-210c): 57 aircraft (registry code 2073412) - [Cessna 210J](https://openairdocs.org/model/cessna-210j): 56 aircraft (registry code 2073439) - [Cessna 210-5](https://openairdocs.org/model/cessna-210-5): 55 aircraft (registry code 2073404) - [Cessna 210K](https://openairdocs.org/model/cessna-210k): 50 aircraft (registry code 2073446) - [Cessna 210G](https://openairdocs.org/model/cessna-210g): 39 aircraft (registry code 2073430) - [Cessna 210H](https://openairdocs.org/model/cessna-210h): 38 aircraft (registry code 2073436) - [Cessna 210-5A(205A)](https://openairdocs.org/model/cessna-210-5a-205a): 34 aircraft (registry code 2073204) - [Cessna 210F](https://openairdocs.org/model/cessna-210f): 34 aircraft (registry code 2073418) - [Cessna T210R](https://openairdocs.org/model/cessna-t210r): 28 aircraft (registry code 2073459) - [Cessna T210H](https://openairdocs.org/model/cessna-t210h): 26 aircraft (registry code 2073438) - [Cessna T210K](https://openairdocs.org/model/cessna-t210k): 26 aircraft (registry code 2073447) - [Cessna T210G](https://openairdocs.org/model/cessna-t210g): 25 aircraft (registry code 2073432) - [Cessna P210R](https://openairdocs.org/model/cessna-p210r): 22 aircraft (registry code 2073455) - [Cessna T210J](https://openairdocs.org/model/cessna-t210j): 19 aircraft (registry code 2073440) - [Cessna 210-5A](https://openairdocs.org/model/cessna-210-5a): 12 aircraft (registry code 2073406) - [Cessna 205](https://openairdocs.org/model/cessna-205): 1 aircraft (registry code 2073300) - [Cessna 210R](https://openairdocs.org/model/cessna-210r): 1 aircraft (registry code 2073458) ## STCs approved under this data sheet (702, first 50) - [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 SA2528NM](https://openairdocs.org/stc/SA2528NM): Installation of an air to air intercooler in the engine induction system downstream of the turbocharger. (P210N S/N P21000001 THRU P21000834). Western Skyways Aircraft Modifications Inc. - [STC SA2598NM](https://openairdocs.org/stc/SA2598NM): Installation of an air to air intercooler in the engine induction system downstream of the turbocharger. (See specific serial numbers) H S/N T210-308 THRU T210-0392). Western Skyways Aircraft Modifications Inc. - [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 SA01844WI](https://openairdocs.org/stc/SA01844WI): Installation of Garmin GFC 600 Automatic Flight Control System. Garmin International Inc. - [STC SA02069AK](https://openairdocs.org/stc/SA02069AK): Fabrication and installation of the Airglas, Inc., Landes PA32-206LA Nose Fork equipped with up to a 8.50 x 6 tire. Airglas Inc. - [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies - [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 SA01134DE](https://openairdocs.org/stc/SA01134DE): Installation of EarthX ETX680-24-TSO Lithium Battery. EarthX Inc. - [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 SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc. - [STC SA02363CH](https://openairdocs.org/stc/SA02363CH): Installation of Chuck Ney Enterprises, Inc. CNE IO-470-C/N-MOD Model Engine (STC SE02261CH). Cygnet Aerospace Corp. - [STC SA02492AT](https://openairdocs.org/stc/SA02492AT): Installation of FLIR Systems Inc. Models UM LE, Ultramedia, and Star Safire and Helinet Model Cineflex V14 Camera Systems, or L3 Harris Westar Wescam MX-15 Air Surveillance & Reconnaissance Thermal Imaging camera on the same installed Gimbal002. Aero Avionics Inc. - [STC SA3649WE](https://openairdocs.org/stc/SA3649WE): Installation of replacement flexible fuel cell in the wings of the 210 Cessna aircraft.. Aerosport Fuel Cells, LLC - [STC SA01866WI](https://openairdocs.org/stc/SA01866WI): Installation of Garmin GFC 500 Autopilot with Electronic Stability and Protection. Garmin International Inc. - [STC SA01005DE](https://openairdocs.org/stc/SA01005DE): Installation of a EarthX ETX900-TSO Lithium battery. EarthX Inc. - [STC SA11158SC](https://openairdocs.org/stc/SA11158SC): Demonstration of aircraft tolerance to potential electromagnetic interference from certain Transmitting Potable Electronic Devices (T-PEDS). Liberty Partners Inc. - [STC SA3931NM](https://openairdocs.org/stc/SA3931NM): Installation of air to air intercooler in the engine air induction system. Airplane must have STC SA2689SW incorporated.. Western Skyways Aircraft Modifications Inc. - [STC SA04211CH](https://openairdocs.org/stc/SA04211CH): Installation of an engine modified per STC SE0417CH. Western Skyways Aircraft Modifications 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 SA00925WI](https://openairdocs.org/stc/SA00925WI): Installation of MT-Propeller model MTV-14-D/195-30a hydraulic 4-blade constant speed propeller.. MT- Propeller Entwicklung GmbH - [STC SA04678CH](https://openairdocs.org/stc/SA04678CH): Installation of electric air conditions system Kelly Aerospace kit #KATS-20-004. Kelly Aerospace Thermal Systems LLC - [STC SA01330LA](https://openairdocs.org/stc/SA01330LA): Installation of alternate avionics support assembly.. Radiorax Aviation Systems LLC - [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd. - [STC SA01120SE](https://openairdocs.org/stc/SA01120SE): Installation of Door Steward.. Mountain View Aviation LLC - [STC SA02594SE](https://openairdocs.org/stc/SA02594SE): SkyView HDX Instrumentation and Autopilot System manufactured. Dynon Avionics - [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 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 SA00871SE](https://openairdocs.org/stc/SA00871SE): Installation of cockpit sunvisors. Rosen Sunvisor Systems LLC - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA3522WE](https://openairdocs.org/stc/SA3522WE): Installation of Knisley muffler in lieu of original Cessna mufflers.. Aerospace Welding Minneapolis Inc. - [STC SA3732WE](https://openairdocs.org/stc/SA3732WE): Installation of Knisley mufflers in lieu of original Cessna mufflers.. Aerospace Welding Minneapolis Inc. - [STC SA5012NM](https://openairdocs.org/stc/SA5012NM): Installation of a modified exhaust system.. Aerospace Welding Minneapolis Inc. - [STC SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc. - [STC SA1098WE](https://openairdocs.org/stc/SA1098WE): Installation of Roto-Master (Rajay) turbocharged Continental IO-470-E or IO-470-S engine.. TALCO Aviation - [STC SA02575AK](https://openairdocs.org/stc/SA02575AK): Installation of the nose tire scraper P/N TSL-100. Aero Twin Inc. - [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine - [STC SA3104SO-D](https://openairdocs.org/stc/SA3104SO-D): Installation of a Teledyne Continental Motors model 10-550-L engine, a McCauley model D3A34C402/90DFA-10 propeller or a Hartzell PHC-J3YF-1RF/F7691 (propeller and other minor changes. Summit Aviation Inc - [STC SA00306DE](https://openairdocs.org/stc/SA00306DE): Installation of an external infrared imaging system.. Dart Aerospace USA Inc. - [STC SA04400NY](https://openairdocs.org/stc/SA04400NY): Installation of the Integrated Back-up Battery System (IBBS). TCW Technologies LLC - [STC SA04192NY](https://openairdocs.org/stc/SA04192NY): KFD 900 Primary Flight Display System Additional Functions. Honeywell International Inc - [STC SA00631WI](https://openairdocs.org/stc/SA00631WI): Installation of additional equipment for approval for flight into icing.. CAV Ice Protection Inc. - [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 All 702: https://openairdocs.org/tcds/3A21/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.