# TCDS 2A13: Piper Aircraft Inc. - Type: Type certificate data sheet - Status: Current - Holder: Piper Aircraft Inc. - Revision: 66 - Revised: October 10, 2025 - Product: Aircraft, Small Airplane - Certification basis: Part 23, CAR 3 - Registered aircraft: 18,521, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/28/43/284334b7de705d5549fb9484e57a264b4266d02d8ccc67981e08d5295057c1b1 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID125895332520251113164724.0001 - Page: https://openairdocs.org/tcds/2A13 ## Models (18) As the data sheet lists them. - PA-28R-180 (Arrow 180) - PA-28R-201 - PA-28-150 - PA-28-201T - PA-28-236 - PA-28-140 (Cherokee 140, Cruiser) - PA-28R-201T - PA-28S-160 - PA-28R-200 (Arrow 200) - PA-28-160 - PA-28S-180 - PA-28-161 - PA-28RT-201 - PA-28-180 (Cherokee 180) - PA-28-151 - PA-28-181 - PA-28-235 - PA-28RT-201T ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Revision No. 66 48 48 48 48 48 64 48 48 48 48 48 48 48 48 48 48 48 Page No. 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 Revision No. 65 50 65 65 63 48 57 50 63 63 59 48 48 48 48 48 59 65 Page No. 37 38 39 40 41 42 43 44 45 46 47 Revision No. 61 64 66 59 65 65 65 65 59 62 65 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 2A13 Revision 66 Piper Aircraft, Inc PA-28-140 PA-28-151 PA-28-150 PA-28-161 PA-28-160 PA-28-181 PA-28-180 PA-28R-201 PA-28-235 PA-28R-201T PA-28S-160 PA-28-236 PA-28S-180 PA-28RT-201 PA-28R-180 PA-28RT-201T PA-28R-200 PA-28-201T October 10, 2025 TYPE CERTIFICATE DATA SHEET NO. 2A13 This data sheet, which is a part of Type Certificate 2A13, 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 Piper Aircraft, Inc. 2926 Piper Drive Vero Beach, Florida 32960 Type Certificate Holder Record The New Piper Aircraft, Inc transferred TC 2A13 to Piper Aircraft, Inc on August 7, 2006. I - Model PA-28-160 (Cherokee), 4 PCLM (Normal Category), Approved October 31, 1960, for S/N 28-03; 28-1 through 28-4377; and 28-1760A. Engine Lycoming O-320-B2B or O-320-D2A with carburetor setting 10-3678-32 Fuel 91/96 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (160 hp) Propeller and Propeller Limits Sensenich M74DM or 74DM6 on S/N 28-1 through 28-1760, and 28-1760A. Sensenich M74DMS or 74D6S5 on S/N 28-1761 through 28-4377. Static r.p.m. at maximum permission throttle setting not over 2425 r.p.m., not under 2325 r.p.m. No additional tolerance permitted. Diameter: Not over 74", not under 72.5". Propeller Spinner Piper P/N 14422-00 on S/N 28-1 through 28-1760, and 28-1760A. Piper P/N 63760-04 or P/N 65805-00 on S/N 28-1761 through 28-4377. See NOTE 11. Airspeed Limits Never exceed 171 mph (148 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS Maneuvering 129 mph (112 knots) CAS Flaps Extended 115 mph (100 knots) CAS 2A13 Page 2 of 47 Center of Gravity Range (+84.0) to (+95.9) at 1650 lb. or less (+85.9) to (+95.9) at 1975 lb. (+89.2) to (+95.9) at 2200 lb. Straight line variation between points given. Empty Weight C. G. Range None Maximum Weight 2200 lb. No. of Seats 4 (2 at +85.5, 2 at +118.1) Maximum Baggage 125 lb. at (+142.8) on S/N 28-1 through 28-1760, and 28-1760A. See NOTE 8. 200 lb. at (+142.8) on S/N 28-1761 through 28-4377. Fuel Capacity 50 gallons at (+95) ( 2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+32.5), 6 quarts usable See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (± 2°) Up 0° Down 40° Ailerons (± 2°) Up 30° Down 15° Rudder (± 2°) Left 27° Right 27° Stabilator (± 2°) Up 18° Down 2° Stabilator Tab (± 1°) Up 3° Down 12° Nose Wheel Travel (±1°) Left 30° Right 30° (Effective on S/N 28-1 through 28-3377, and 28-1760A) (1) Left 22° Right 22° (Effective S/N 28-3378 through 28-4377) Manufacturer's Serial Nos. 28-03; 28-1 through 28-4377; and 28-1760A. II - Model PA-28-150 (Cherokee), 4 PCLM (Normal Category), Approved June 2, 1961, for S/N 28-03; 28-1 through 28-4377; and 28-1760A. Engine Lycoming O-320-A2B or O-320-E2A with carburetor setting 10-3678-32 Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (150 hp) Propeller and Propeller Limits Sensenich M74DM or 74DM6 on S/N 28-1 through 28-1760, and 28-1760A. Sensenich M74DMS or 74DM6S5 on S/N 28-1761 through 28-4377. Static r.p.m. at maximum permissible throttle setting not over 2375 r.p.m., not under 2275 r.p.m. No additional tolerance permitted. Diameter: Not over 74", not under 72.5". Propeller Spinner Piper P/N 14422-00 on S/N 28-1 through 28-1760, and 28-1760A. Piper P/N 63760-04 or 65805-00 on S/N 28-1761 through 28-4377. See NOTE 11. Airspeed Limits Never exceed 171 mph (148 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS Maneuvering 129 mph (112 knots) CAS Flaps Extended 115 mph (100 knots) CAS Page 3 of 47 2A13 Center of Gravity Range (+84.0) to (+95.9) at 1650 lb. or less (+85.9) to (+95.9) at 1975 lb. (+88.4) to (+95.9) at 2150 lb. Straight line variation between points given. Empty Wt. C. G. Range None Maximum Weight 2150 lb. No. of Seats 4 (2 at +85.5, 2 at +118.1) Maximum Baggage 125 lb. at (+142.8) on S/N 28-1 through 28-1760, and 28-1760A. See NOTE 8. 200 lb. at (+142.8) on S/N 28-1761 through 28-4377. Fuel Capacity 50 gallons at (+95) ( 2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+32.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (± 2°) Up 0° Down 40° Ailerons (± 2°) Up 30° Down 15° Rudder (± 2°) Left 27° Right 27° Stabilator (± 1°) Up 18° Down 2° Stabilator Tab (± 1°) Up 3° Down 12° Nose Wheel Travel (± 2) Left 30° Right 30° (Effective on S/N 28-03; 28-1 through 28-3377; and 28-1760A) ( 2) Left 22° Right 22° (Effective on S/N 28-3378 through 28-4377) Manufacturer's Serial Nos. 28-03; 28-1 through 28-4377; and 28-1760A. III - Model PA-28-180 (Cherokee), 4 PCLM (Normal Category), Approved August 3, 1962; 2 PCLM (Utility Category), Approved December 6, 1966, for S/N 28-03; 28-671 through 28-5859; and 28-7105001 through 28-7205318. Engine Lycoming O-360-A3A or 0-360-A4A with carburetor setting 10-3878 or 10-4164-1 Fuel 91/96 minimum grade aviation gasoline Engine Limits S/N 28-671 through 28-1760, and 28-1760A (except S/N 28-1571 and S/N 28-1573) (See NOTE 4): Maximum permissible takeoff, 2475 r.p.m. For all other operations, 2700 r.p.m. (180 hp) S/N 28-1571; 28-1573; 28-1761 through 28-5859; and 28-7105001 through 28-7205318: For all operations, 2700 r.p.m. (180 hp) Propeller and Propeller Limits Sensenich M76EMM or 76EM8 on S/N 28-671 through 28-1760, and 28-1760A (except S/N 28-1571 and S/N 28-1573). Sensenich M76EMMS or 76EM8S5 on S/N 28-1571, 28-1573; 28-1761 through 28-5859; and 28-7105001 through 28-7205318. Static r.p.m. at maximum permissible throttle setting not over 2450 r.p.m., not under 2275 r.p.m. No additional tolerance permitted. Diameter: Not over or under 76". See NOTE 10. 2A13 Page 4 of 47 Propeller Spinner Piper P/N 14422-00 on S/N 28-671 through 28-1760, and 28-1760A. Piper P/N 63760-04 or 65805-00 on S/N 28-1761 through 28-5859; and 28-7105001 through 28-7205318. See NOTE 11. Airspeed Limits Never exceed 171 mph (148 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS Maneuvering 129 mph (112 knots) CAS Flaps Extended 115 mph (100 knots) CAS Center of Gravity Range Utility Category (See NOTE 9) (+84.0) to (+86.5) at 1650 lb. or less (+85.8) to (+86.5) at 1950 lb. Normal Category (See NOTE 15) (S/N 28-671 through 28-5859) (+84.0) to (+95.9) at 1650 lb. or less (+85.9) to (+95.9) at 1975 lb. (+89.2) to (+95 9) at 2200 lb. (+92.1) to (+94.5) at 2400 lb. Normal Category (S/N 28-7105001 through 28-7205318) (+84.0) to (+95.9) at 1650 lb. or less (+87.0) to (+95.9) at 2150 lb. (+87.8) to (+95.9) at 2200 lb. (+91.0) to (+94.5) at 2400 lb. Straight Line Variation Between Points Given 2400 2200 2000 1800 1600 84 86 88 90 92 94 96 Normal Only Aft Limit Normal Aft Limit Utility Fuselage Station - Inches Normal & Utility 2400 2200 2000 1800 1600 84 86 88 90 92 94 96 Aft Limit Normal Fuselage Station - Inches (S/N 28-7105001 thru 28-7205318) Normal & Utility Aft Limit Utility Normal Only (S/N 28-671 thru 28-5859) Lbs. Lbs. Empty Weight C. G. Range None Page 5 of 47 2A13 Maximum Weight Normal Category: 2400 lb. Utility Category: 1950 lb. No. of Seats Normal Category: 4 (2 at +85.5, 2 at +118.1) Utility Category: 2 (2 at +85.5) Maximum Baggage Eligible Normal Category Only: 125 lb. at (+142.8) on S/N 28-671 through 28-1760, and 28-1760A. See NOTE 8. 200 lb. at (+142.8) on S/N 28-1761 through 28-5859, and 28-7105001 through 28-7205318. Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+32.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (± 2°) Up 0° Down 40° Ailerons (± 2°) Up 30° Down 15° Rudder (± 2°) Left 27° Right 27° Stabilator (± 1°) Up 18° Down 2° Stabilator Tab (± 1°) Up 3° Down 12° Nose Wheel Travel (± 2°) Left 30° Right 30° (Effective on S/N 28-671 through 28-3377) ( 2) Left 22° Right 22° (Effective on S/N 28-3378 through 28-5859, and 28-7105001 through 28-7205318) Manufacturer's Serial Nos. 28-03; 28-671 through 28-5859; and 28-7105001 through 28-7205318. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers: 28-4704 28-4745 28-4754 28-4763 28-4776 28-4791 28-4795 28-4826 28-4834 28-4859 28-4875 28-4879 28-4891 28-4907 28-4919 28-4922 28-4935 28-4945 28-4946 28-4947 28-4955 28-4959 28-4961 27-4964 28-4967 28-4968 28-4971 28-4975 28-4977 28-4985 28-4995 28-4999 28-5004 28-5007 28-5015 28-5017 28-5018 28-5019 28-5020 28-5023 28-5026 28-5027 28-5028 28-5031 28-5039 28-5041 28-5046 28-5051 28-5053 28-5057 28-5060 28-5061 28-5062 28-5063 28-5064 28-5066 through 28-5859, and 28-7105001 through 28-7205318 under the delegation option provisions of FAR 21. See NOTE 17 and 20. IV - Model PA-28S-160 (Cherokee), 4 PCSM (Normal Category), Approved February 25, 1963, for S/N 28-1 through 28-1760; and S/N 28-1760A. Engine Lycoming O-320-D2A with carburetor setting 10-3678-32 (See NOTE 18) Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (160 hp) Propeller and Propeller Limits McCauley 1A175-GM Static r.p.m. at maximum permissible throttle setting not over 2360 r.p.m., not under 2260 r.p.m. No additional tolerance permitted. Diameter: Not over 79", not under 78". 2A13 Page 6 of 47 Propeller Spinner Piper P/N 14422-00 spinner required. Airspeed Limits Never exceed 153 mph (133 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS Maneuvering 129 mph (112 knots) CAS Flaps Extended 115 mph (100 knots) CAS Center of Gravity (+85.1) to (+93.5) at 1850 lb. or less (+87.0) to (+93.5) at 2100 lb. (+87.9) to (+93.5) at 2140 lb. Straight line variation between points given. Empty Weight C. G. Range None Maximum Weight 2140 lb. No. of Seats 4 (2 at +85.5, 2 at +118.1) Maximum Baggage 125 lb. at (+142.8) Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+32.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 30° Down 15° Rudder (±2°) Left 27° Right 27° Stabilator (±1°) Up 18° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Manufacturer's Serial Nos. 28-03; 28-1 through 28-1760; and 28-1760A. V - Model PA-28S-180 (Cherokee), 4 PCSM (Normal Category), Approved May 10, 1963, for S/N 28-671 through 28-5859, and 28-7105001 through 28-7105234. Engine Lycoming O-360-A3A or 0-360-A4A with carburetor setting 10-4164-1 See NOTE 19. Fuel 100/130 minimum grade aviation gasoline Engine Limits S/N 28-671 through 28-1760, and 28-1760A (except S/N 28-1571 and S/N 28-1573): Maximum permissible takeoff, 2350 r.p.m. For all other operations, 2700 r.p.m. (180 hp) See NOTE 4. S/N 28-1571; 28-1573; 28-1761 through 28-5859; and 28-7105001 through 28-7105234: For all operations, 2700 r.p.m. (180 hp) Propeller and Propeller Limits McCauley 1A200-FA8248 on S/N 28-671 to 28-1760, and 28-1760A. McCauley 1A200-DFA8248 on S/N 28-1761 through 28-5859, and 28-7105001 through 28-7105234. Static r.p.m. at maximum permissible throttle setting not over 2190 r.p.m., not under 2140 r.p.m. No additional tolerance permitted. Diameter: Not over 82", not under 81". Page 7 of 47 2A13 Propeller Spinner Spinner required. Piper P/N 14422-00 on S/N 28-671 through 28-1760, and 28-1760A. Piper P/N 63760-04 or 65805-00 on S/N 28-1761 through 28-5859, and 28-7105001 through 28-7105234. Airspeed Limits Never exceed 153 mph (133 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS Maneuvering 129 mph (112 knots) CAS Flaps Extended 115 mph (100 knots) CAS Center of Gravity (+85.1) to (+92.5) at 1850 lb. or less (+87.0) to (+92.5) at 2100 lb. (+89.8) to (+92.5) at 2222 lb. Straight line variation between points given. Empty Weight C. G. Range None Maximum Weight 2222 lb. No. of Seats 4 (2 at +85.5, 2 at +118.1) Maximum Baggage 125 lb. at (+142.8) Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+32.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 30° Down 15° Rudder (±2°) Left 27° Right 27° Stabilator (±1°) Up 18° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Manufacturer's Serial Nos. 28-671 through 28-5859, and 28-7105001 through 28-7105234. See NOTE 30. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers: 28-4704 28-4745 28-4754 28-4763 28-4776 28-4791 28-4795 28-4826 28-4834 28-4859 28-4875 28-4879 28-4891 28-4907 28-4919 28-4922 28-4935 28-4945 28-4946 28-4947 28-4955 28-4959 28-4961 27-4964 28-4967 28-4968 28-4971 28-4975 28-4977 28-4985 28-4995 28-4999 28-5004 28-5007 28-5015 28-5017 28-5018 28-5019 28-5020 28-5023 28-5026 28-5027 28-5028 28-5031 28-5039 28-5041 28-5046 28-5051 28-5053 28-5057 28-5060 28-5061 28-5062 28-5063 28-5064 28-5066 through 28-5859, and 28-7105001 through 28-7105234 under the delegation option provisions of FAR 21. See NOTE 17 and 20. 2A13 Page 8 of 47 VI - Model PA-28-235 (Cherokee Pathfinder), 4 PCLM (Normal Category), Approved July 15, 1963, for S/N 28-10001 through 28-11378, and 28-7110001 through 28-7210023. Engine Lycoming O-540-B2B5, O-540-B1B5, or O-540-B4B5 with carburetor setting 10-4404, 10-5042, or 10-5054. (Baffle P/N 68759 required with 10-5054 setting.) Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations, 2575 r.p.m. (235 hp) Propeller and Propeller Limits McCauley 1P235PFA80 Static r.p.m. at maximum permissible throttle setting not over 2300 r.p.m., not under 2125 r.p.m. No additional tolerance permitted. Diameter: Not over 80", not under 78.5". or Hartzell HC-C2YK-1/8468A-4 or HC-C2YK-1( )F/F8468A-4 Pitch: High 27° ± 2°, Low 13.5° ± .2° at 30" station. Diameter: Not over 80", not under 80". Governor assembly: Hartzell F-4-3 ( ) or F-4-13 See NOTE 21. or Approved for Use with O-540-B4B5 Engine Only: Sensenich M80BMM or 80BM8 Pitch from 69" to 71". Static r.p.m. at maximum permissible throttle setting not over 2300 r.p.m., not under 2150 r.p.m. No additional tolerances permitted. Diameter: Not over 80", not under 78.5". Propeller Spinner Piper P/N 65209-00 or P/N 63760-03 with fixed pitch propeller. Spinner required. Piper P/N 65435-0 or P/N 68713 or P/N 66785 spinner tip and P/N 66786 spinner shell or P/N 67790-0 spinner, P/N 67791-0 bulkhead, P/N 67793-0 bulkhead and P/N 99499-0 plate. Two each P/N 67794-0 cuff, or Kit 760 452V with constant speed propeller. See NOTE 14. Airspeed Limits Never exceed 197 mph (171 knots) CAS Maximum structural cruising 156 mph (136 knots) CAS Maneuvering 138 mph (120 knots) CAS Flaps Extended 115 mph (100 knots) CAS Center of Gravity Range S/N 28-10001 through 28-11378 (See NOTE 16): (+81.5) to (+93.5) at 2100 lb. or less (+91.5) to (+93.5) at 2900 lb. S/N 28-7110001 through 28-7210023: (+85.1) to (+93.5) at 2100 lb. or less (+86.0) to (+93.5) at 2600 lb. (+91.5) to (+93.5) at 2900 lb. Straight line variation between points given. Empty Weight C. G. Range None Maximum Weight 2900 lb. No. of Seats 4 (2 at +85.5, 2 at +118.1) Maximum Baggage 200 lb. at (+142.8) Page 9 of 47 2A13 Fuel Capacity 84 gallons at (+95) (50 gallons in 2 wing tanks, 34 gallons in 2 tip tanks). See NOTE 1 for data on system fuel. Oil Capacity 12 quarts at (+34.1) (9 ¼ quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 30° Down 15° Rudder (+2°) Left 27° Right 27° Stabilator (±1°) Up 18° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±2°) Left 30° Right 30° (Effective on S/N 28-10001 through 28-11039) (2) Left 22° Right 22° (Effective on S/N 28-11040 through 28-11378, and 28-7110001 through 28-7210023) Manufacturer's Serial Nos. 28-10001 through 28-11378, and 28-7110001 through 28-7210023. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers 28-11063, 28-11064, 28-11070, 28-11072 through 28-11378, and 28-7110001 through 28-7210023 under the delegation option provisions of FAR 21. See NOTE 17 and 20. VII - Model PA-28-140 (Cherokee Cruiser), 2 PCLM (Utility or Normal Category); 1950 lb. Maximum Weight, Approved February 14, 1964; 2150 lb. Maximum Weight, Approved June 17, 1965; for S/N 28-20001 through 28-26946, and 28-7125001 through 28-7725290. Engine Lycoming O-320-E2A with carburetor setting 10-3678-32 or O-320-E3D with carburetor setting 10-5009 Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations 2700 r.p.m (150 hp) Propeller and Propeller Limits For 1950 lb. maximum weight - Normal Category; S/N 28-20001 through 28-20939; or Utility Category, S/N 28-20001 through 28-26946, and 28-7125001 through 28-7725290: Sensenich M74DM or 74DM6 Static r.p.m. at maximum permissible throttle setting not over 2425 r.p.m., not under 2150 r.p.m. No additional tolerance permitted. Diameter: Not over 74", not under 72.5". For 2150 lb. maximum weight - Normal Category; S/N 28-20940 through 28-26946, and 28-7125001 through 28-7725290: Sensenich M74DM or 74DM6 Static r.p.m. at maximum permissible throttle setting not over 2425 r.p.m., not under 2275 r.p.m. No additional tolerance permitted. Diameter: Not over 74", not under 72.5". Propeller Spinner Piper P/N 14422-00. See NOTE 11. Airspeed Limits Never exceed 171 mph (148 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS Maneuvering 129 mph (112 knots) CAS Flaps Extended 115 mph (100 knots) CAS 2A13 Page 10 of 47 Center of Gravity Range Utility Category (+84.0) to (+86.5) at 1650 lb. or less (+85.8) to (+86.5) at 1950 lb. Normal Category (+84.0) to (+95.9) at 1650 lb. or less (+85.9) to (+95.9) at 1975 lb. (+88.4) to (+95.9) at 2150 lb. Straight line variation between points given. 84 86 88 90 92 94 96 2250 2150 2050 1950 1850 1750 1650 Aft Limit Utility Normal & Utility Aft Limit Normal Normal Only Fuselage Station - Inches Lbs. Empty Weight C. G. Range None Maximum Weight Normal Category: 1950 lb. on S/N 28-20001 through 28-20939 (See NOTE 6). 2150 lb. on S/N 28-20940 through 28-26946, and 28-7125001 through 28-7725290. Utility Category: 1950 lb. on S/N 28-20001 through 28-26946, and 28-7125001 through 28-7725290. No. of Seats 2 at (+85.5) Maximum Baggage Eligible Normal Category Only: 100 lb. at (+117) on S/N 28-20001 through 28-20939 (See NOTE 12). 200 lb. at (+117) on S/N 28-20940 through 28-26946, and 28-7125001 through 28-7725290. 300 lb. at (+117 and +133) on S/N 28-20940 through 28-26946, and 28-7125001 through 28-7725290 (See NOTE 13). Fuel Capacity 50 gallon at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+32.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 30° Down 15° Rudder (±2°) Left 27° Right 27° Stabilator (±1°) Up 18° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±2°) Left 30° Right 30° (Effective on S/N 28-20001 through 28-21845; 28-21931 through 28-21934; and 28-7425001 through 28-7725290) (±2°) Left 22° Right 22° (Effective on S/N 28-21846 through 28-21930; 28-21935 through 28-26946; and 28-7125001 through 28-7325674) Page 11 of 47 2A13 Manufacturer's Serial Nos. 28-20001 through 28-26946; and 28-7125001 through 28-7725290. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers 28-24677, 28-24682, 28-24697, 28-24698, 28-24700, 28-24703, 28-24704, 28-24705, 28-24706, 28- 24709, 28-24710, 28-24712, 28-24713, 28-24714, 28-24715 through 28-26946, and 28- 7125001 through 28-7725290 under the delegation option provisions of FAR 21. See NOTE 17 and 20. VIII - Model PA-28-140 (Cherokee Cruiser), 4 PCLM (Normal Category), 2 PCLM (Utility Category), Approved June 17, 1965, for S/N 28-20001 through 28-26946, and 28-7125001 through 28-7725290. Engine Lycoming O-320-E2A with carburetor setting 10-3678-32 or 10-5009 or O-320-E3D with carburetor setting 10-5009 Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations 2700 r.p.m. (150 hp) Propeller and Propeller Limits Sensenich M74DM or 74DM6 Static r.p.m. at maximum permissible throttle setting not over 2425 r.p.m., not under 2275 r.p.m. No additional tolerance permitted. Diameter: Not over 74", not under 72.5". Propeller Spinner Piper P/N 14422-00. See NOTE 11. Airspeed Limits Never exceed 171 mph (148 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS Maneuvering 129 mph (112 knots) CAS Flaps Extended 115 mph (100 knots) CAS Center of Gravity Range Utility Category (+84.0) to (+86.5) at 1650 lb. or less (+85.8) to (+86.5) at 1950 lb. Normal Category (+84.0) to (+95.9) at 1650 lb. or less (+85.9) to (+95.9) at 1975 lb. (+88.4) to (+95 9) at 2150 lb. Straight line variation between points given. 84 86 88 90 92 94 96 2250 2150 2050 1950 1850 1750 1650 Aft Limit Utility Normal & Utility Aft Limit Normal Normal Only Fuselage Station - Inches Lbs. 2A13 Page 12 of 47 Empty Weight C. G. Range None Maximum Weight Normal Category: 2150 lb. Utility Category: 1950 lb. No. of Seats Normal Category: 4 (2 at +85.5, 2 at +117) Utility Category: 2 (2 at +85.5) Maximum Baggage Eligible Normal Category only: 100 lb. at (+117) on S/N 28-20001 through 28-20939 (See NOTE 12). 200 lb. at (+117) on S/N 28-20940 through 28-26946; and 28-7125001 through 28-7725290. 300 lb. at (+117 and +133) on S/N 28-20940 through 28-26946; and 28-7125001 through 28- 7725290 (See NOTE 13). Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+32.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 30° Down 15° Rudder (±2°) Left 27° Right 27° Stabilator (±1°) Up 18° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±2°) Left 30° Right 30° (Effective on S/N 28-20940 through 28-21845; 28-21931 through 28-21934; and 28-7425001 through 28-7725290) ( 2) Left 22° Right 22° (Effective on S/N 28-21846 through 28-21930; 28-21935 through 28-26946; and 28-7125001 through 28-7325674) Manufacturer's Serial Nos. 28-20001 through 28-26946, and 28-7125001 through 28-7725290. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers 28-24677, 28-24682, 28-24697, 28-24698, 28-24700, 28-24703, 28-24704, 28-24705, 28-24706, 28-24709, 28-24710, 28-24712, 28-24713, 28-24714, 28-24715 through 28-26946, and 28-7125001 through 28-7725290 under the delegation option provisions of FAR 21. See NOTE 17 and 20. IX - Model PA-28R-180 (Arrow), 4 PCLM (Normal Category), Approved June 8, 1967, for S/N 28R-30002 through 28R-31270, and 28R-7130001 through 28R-7130013. Engine Lycoming IO-360-B1E Injector Bendix type RSA-5ADI Parts List No. 2524297 Fuel 100/130 minimum grade aviation gasoline Engine limits For all operations, 2700 r.p.m. (180 hp) Propeller and Propeller Limits Hartzell constant speed Model HC-C2YK-( )/7666A-0 or HC-C2YK-1( )F/F7666A Pitch: High 29.0 ± 1°, Low 13.0° ± .2° at 30" Station. Diameter: Not over 76", not under 74.5". Governor Assembly: Hartzell F-2-2 ( ) or F-2-7 ( ) Avoid continuous operation between 2000 - 2200 r.p.m. Page 13 of 47 2A13 Propeller Spinner Piper P/N 68713 or P/N 66785 spinner tip and P/N 66786 spinner shell, or P/N 67790-0 spinner, P/N 67791-0 bulkhead, P/N 67793-0 bulkhead, and P/N 99499-0 plate. Two each P/N 67794-0 cuff or Kit 760 410V. See NOTE 11. Airspeed Limits Never exceed 214 mph (186 knots) CAS Maximum structural cruising 170 mph (148 knots) CAS Maneuvering 134 mph (116 knots) CAS Flaps extended 125 mph (109 knots) CAS Maximum gear extension 150 mph (130 knots) CAS Maximum gear retraction 125 mph (109 knots) CAS Center of Gravity Range (+81.0) to (+95.9) at 1925 lb. or less (+91.0) to (+95.9) at 2500 lb. Straight line variation between points given. Moment due to retracting of landing gear (+819 in-lb.) Empty Weight C. G. Range None Maximum Weight 2500 lb. No. of Seats 4 (2 at +85.5, 2 at +118.1) Maximum Baggage 200 lb. at (+142.8) Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+29.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 30° Down 15° Rudder (±2°) Left 27° Right 27° Stabilator (±1°) Up 18° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±2°) Left 30° Right 30° Manufacturer's Serial Nos. 28R-30002 through 28R-31270, and 28R-7130001 through 28R-7130013. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers: 28R-30538 28R-30546 28R-30559 28R-30586 28R-30587 28R-30602 28R-30603 28R-30605 28R-30624 28R-30627 28R-30638 28R-30639 28R-30642 28R-30684 28R-30697 28R-30708 28R-30726 28R-30739 28R-30740 28R-30747 28R-30750 28R-30752 28R-30759 28R-30760 28R-30766 28R-30776 28R-30779 28R-30785 28R-30787 28R-30795 28R-30801 28R-30809 28R-30815 28R-30819 28R-30821 28R-30824 28R-30827 28R-30832 28R-30835 28R-30838 28R-30842 28R-30845 28R-30849 28R-30853 28R-30857 28R-30860 28R-30865 28R-30866 28R-30867 28R-30868 28R-30869 28R-30872 28R-30874 28R-30875 28R-30877 through 28R-31270, and 28R-7130001 through 28R-7130013 under the delegation option provisions of FAR 21. See NOTE 17 and 20. 2A13 Page 14 of 47 X - Model PA-28R-200 (Arrow), 4 PCLM (Normal Category), Approved January 16, 1969, S/N 28R-35001 through 28R-35820 and 28R-7135001 through 28R-7135229. Engine Lycoming IO-360-C1C Injector Bendix Type RSA-5AD1, Parts List Number 2524450 Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (200 hp) Propeller and Propeller Limits Hartzell constant speed Model HC-C2YK-1 ( )/7666A-2 or HC-C2YK-1 ( )F/F7666A Pitch: High 29.0° ±2°, Low 14.0° ±2° at 30 " Station Diameter: Not over 74", not under 72.5" Governor Assembly: Hartzell F-2-7 ( ) Avoid continuous operation between 2000 - 2350 r.p.m. Propeller Spinner Piper P/N 66785 spinner tip and P/N 66786 spinner shell or P/N 67790-0 spinner, P/N 67791-0 bulkhead, P/N 67793-0 bulkhead, and P/N 99499-0 plate. Two each P/N 67794-0 cuff or Kit 760 410V. See NOTE 11. Airspeed Limits Never exceed 214 mph (186 knots) CAS Maximum structural cruising 170 mph (148 knots) CAS Maneuvering 134 mph (116 knots) CAS Flaps Extended 125 mph (109 knots) CAS Maximum gear extension 150 mph (130 knots) CAS Maximum gear retraction 125 mph (109 knots) CAS Center of Gravity Range (+81.0) to (+95.9) at 1925 lb. or less (+90.0) to (+95.9) at 2600 lb. Straight line variation between points given. Moment due to retracting of landing gear (+819 in-lb.) Empty Weight C. G. Range None Maximum Weight 2600 lb. No. of Seats 4 (2 at +85.5, 2 at +118.1) Maximum Cargo 200 lb. (at +142.8) Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+29.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 30° Down 15° Rudder (±2°) Left 27° Right 27° Stabilator (±1°) Up 18° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±2°) Left 30° Right 30° Manufacturer's Serial Numbers 28R-35001 through 28R-35820, and 28R-7135001 through 28R-7135229. The manufacturer is authorized to issue airworthiness certificates for airplanes serial numbers 28R-35001 through 28R-35820, and 28R-7135001 through 28R-7135229 under the delegation option provisions of FAR 21. Page 15 of 47 2A13 XI - Model PA-28R-200 (Arrow II), 4 PCLM (Normal Category), Approved December 2, 1971, for S/N 28R-7235001 through 28R-7635545. This series differs from the basic PA-28R-200 (Item X) by the addition of a five-inch fuselage extension, larger horizontal tail, wing span increase, gross weight increase, and other minor changes. Engine Lycoming IO-360-C1C (See NOTE 22) Lycoming IO-360-C1C6 (See NOTE 23) Injector Bendix Type RSA-5AD1, Part List Number 2524450 Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (200 hp) Propeller and Propeller Limits Hartzell Constant Speed Model HC-C2YK-1 ( ) or HC-C2YK-1( ) F Blade Model 7666A-2 or F7666A-2 (See NOTE 22) Pitch: High 29.0° ± 2°, Low 14.0° ± .2° at 30" Station. Diameter: Not over 74", not under 72.5". Governor Assembly: Hartzell F-2-7( ) Avoid continuous operation between 2000 - 2350 r.p.m. or McCauley Constant Speed Model B2D34C213, Blade Model 90DHA-16 (See NOTE 23) Pitch: High 27.5° ± .5°; Low 12.5° ± .2° at 30" Station. Diameter: Not over 74", not under 73". Governor Assembly: Hartzell F-2-7 ( ) Avoid continuous operation between 1500 and 1950 r.p.m. below 15" manifold pressure. Propeller Spinner For the Hartzell Propeller: Piper P/N 66785-00 spinner tip, P/N 66786 spinner shell and P/N 68734-0 bulkhead or P/N 99374-0 spinner installation (same as Kit No. 760 410V). See NOTE 11. For the McCauley Propeller: Piper P/N 66785 spinner tip and P/N 66786 spinner shell or P/N 67790-0 spinner, P/N 67791-0 bulkhead, P/N 67793-0 bulkhead, and P/N 99499-0 plate. Two each P/N 67794-0 cuff, or Kit 760 410V. Spinner and attachment plate installation P/N 35828-2. See NOTES 11 and 23. Airspeed Limits Never exceed 214 mph (186 knots) CAS Maximum structural cruising 170 mph (148 knots) CAS Maneuvering 131 mph (114 knots) CAS Flaps Extended 125 mph (109 knots) CAS Maximum gear extension 150 mph (130 knots) CAS Maximum gear retraction 125 mph (109 knots) CAS Center of Gravity Range (+80.0) to (+93.0) at 1800 lb. or less (+82.0) to (+93.0) at 2300 lb. (+87.3) to (+93.0) at 2650 lb. Empty Weight C. G. Range None Maximum Weight 2650 lb. No. of Seats 4 (2 at +80.5, 2 at +118.1) Maximum Cargo 200 lb. (at +142.8) Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+24.5) (6 quarts usable) See NOTE 1 for data on system oil. 2A13 Page 16 of 47 Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 30° Down 15° Rudder (±2°) Left 27° Right 27° Stabilator (±1°) Up 16° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±2°) Left 30° Right 30° Manufacturer's Serial Numbers 28R-7235001 through 28R-7635545. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers 28R-7235001 through 28R-7635545 under the delegation option provisions of FAR 21. See NOTE 20. XII - Model PA-28-180 (Archer), 4 PCLM (Normal Category), 2 PCLM (Utility Category), Approved May 22, 1972, for S/N 28- E13, and 28-7305001 through 28-7505260. This series differs from the basic PA-28-180 (Item III) by the addition of a five inch fuselage extension, wing span increase, larger horizontal tail, gross weight increase and other minor changes. Engine Lycoming O-360-A4A or O-360-A4M with carburetor settings 10-3878 or 10-5193 Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (180 hp) Propeller and Propeller Limits Sensenich or 76EM8S5 or M76EMMS Static r.p.m. at maximum permissible throttle setting not over 2425 r.p.m., not under 2325 r.p.m. No additional tolerance permitted. Diameter: Not over or under 76". Propeller Spinner Piper P/N 65805-00. See NOTE 11. Airspeed Limits Never exceed 171 mph (148 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS Maneuvering 127 mph (110 knots) CAS Flaps Extended 115 mph (100 knots) CAS Center of Gravity Range Normal Category (+82.0) to (+93.0) at 2050 lb. or less (+87.4) to (+93.0) at 2450 lb. Utility Category (+82.0) to (+86.5) at 1950 lb. or less Straight line variation between points given. Page 17 of 47 2A13 Fuselage Station - Inches Lbs. 84 86 88 90 92 94 2100 2000 1900 1800 1700 1600 82 2200 2300 2400 2500 Aft Limit Utility Normal Only Normal & Utility Aft Limit Normal Empty Weight C. G. Range None Maximum Weight Normal Category: 2450 lb. Utility Category: 1950 lb. No. of Seats Normal Category: 4 (2 at +80.5 2 at +118.1) Utility Category: 2 (2 at +80.5) Maximum Baggage 200 lb. at (+142.8) Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+27.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 30° Down 15° Rudder (±2°) Left 27° Right 27° Stabilator (±1°) Up 14° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±2°) Left 22° Right 22° (S/N 28-E13, 28-7305001 through 28-7305601) (±2°) Left 30° Right 30° (S/N 28-7405001 through 28-7505260) Manufacturer's Serial Numbers 28-E13, and 28-7305001 through 28-7505260. The manufacturer is authorized to issue airworthiness certificates for airplanes serial numbers 28-7305001 through 28-7505260 under the delegation option provisions of FAR 21. See NOTE 20. XIII - Model PA-28-235 (Cherokee Pathfinder), 4 PCLM (Normal Category), Approved June 9, 1972, for S/N 28E-11, and 28-7310001 through 28-7710089. This series differs from the basic PA-28-235 (Item VI) by the addition of a five inch fuselage extension, larger horizontal tail, gross weight increase, and other minor changes. Engine Lycoming O-540-B4B5 with carburetor setting 10-5404 Fuel 80/87 minimum grade aviation gasoline 2A13 Page 18 of 47 Engine Limits For all operations, 2575 r.p.m. (235 hp) Propeller and Propeller Limits Hartzell HC-C2YK-1( )F/F 8468A-4 Pitch: High 27  2, Low 13.5   .2 at 30" station. Diameter: Not over 80", not under 80". Governor Assembly: Hartzell F-4-3( ) or F-4-13 ( ). See NOTE 21. Propeller Spinner P/N 99374 Spinner Installation. Spinner required. Airspeed Limits Never exceed 197 mph (171 knots) CAS Maximum structural cruising 156 mph (135 knots) CAS Maneuvering 138 mph (119 knots) CAS Flaps Extended 115 mph (99 knots) CAS Center of Gravity Range (+79.0) to (+91.5) at 1900 lb. or less (+82.0) to (+91.5) at 2500 lb. (+88.0) to (+91.5) at 3000 lb. Straight line variation between points given. Empty Weight C. G. Range None Maximum Weight 3000 lb. No. of Seats 4 (2 at +80.5, 2 at +118.1) Maximum Baggage 200 lb. at (+142.8) Fuel Capacity 84 gallons (50 gallons in 2 wing tanks at (+95) and 34 gallons in 2 tip tanks at (+95)) See NOTE 1 for data on system fuel. Oil Capacity 12 quarts at(+29.1) (9¼ quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 30° Down 15° Rudder (±2°) Left 27° Right 27° Stabilator (±2°) Up 16° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±2°) Left 22° Right 22 (S/N 28-E11, 28-7310001 through 28-7310176) (±2°) Left 30° Right 30° (S/N 28-7410001 through 28-7710089) Manufacturer's Serial Numbers 28-E11, and 28-7310001 through 28-7710089. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers 28-E11, and 28-7310001 through 28-7710089 under the delegation option provisions of FAR 21. See NOTE 20. XIV - Model PA-28-151 (Cherokee Warrior), 4 PCLM (Normal Category), 2 PCLM (Utility Category), Approved August 9, 1973, for S/N 28-7415001 through 28-7715314. Engine Lycoming O-320-E3D with carburetor setting 10-5009, or 10-5009N, or 10-5135 Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (150 hp) Page 19 of 47 2A13 Propeller and Propeller Limits Sensenich M74DM6 Static r.p.m. at maximum permissible throttle setting not over 2375 r.p.m., not under 2275 r.p.m. No additional tolerance permitted. Diameter: Not over 74", not under 72". or McCauley 1C160 EGM 7653 Static r.p.m. at maximum permissible throttle setting not over 2400 r.p.m., not under 2300 r.p.m. No additional tolerance permitted. Diameter: Not over 76", not under 74.5". Propeller Spinner Piper P/N 35323. See NOTE 11. Airspeed Limits Never exceed 176 mph (153 knots) CAS Maximum structural cruising 140 mph (122 knots) CAS Maneuvering 124 mph (108 knots) CAS Flaps Extended 125 mph (109 knots) CAS (S/N 28-7415001 through 28-7515449) Flaps Extended 115 mph (100 knots) CAS (S/N 28-7615001 through 28-7715314) Center of Gravity Range Normal Category (+83.0) to (+93.0) at 1950 lb. or less (+87.0) to (+93.0) at 2325 lb. Utility Category (+83.0) to (+86.5) at 1950 lb. or less Straight line variation between points given. Empty Weight C. G. Range None Maximum Weight Normal Category: 2325 lb. Utility Category: 1950 lb. No. of Seats Normal Category: 4 (2 at +80.5, 2 at +118.1) Utility Category: 2 (2 at +80.5) Maximum Baggage Eligible Normal Category only: 200 lb. at (+142.8) Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+27.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing Flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 23° Down 17° (S/N 28-7415001 through 28-7515449) Ailerons (±2°) Up 25° Down 12.5° (S/N 28-7615001 through 28-7715314) Rudder (±2°) Left 27° Right 27° Stabilator (±1°) Up 14° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±1°) Left 30° Right 30° 2A13 Page 20 of 47 Manufacturer's Serial Numbers 28-7415001 through 28-7715314. The manufacturer is authorized to issue airworthiness certificates for airplanes serial numbers 28-7415001 through 28-7715314 under the delegation option provisions of FAR 21. XV - A.- Model PA-28-181 (Archer II), 4 PCLM (Normal Category), 2 PCLM (Utility Category), Approved July 8, 1975, for S/N 28-7690001 through 28-8690056; 28-8690061; 28-8690062; and 2890001 through 2890205. Engine Lycoming O-360-A4M with carburetor settings 10-3878 or 10-5193 or Lycoming O-360-A4A with carburetor setting 10-5193. Fuel 100/130 minimum grade aviation gasoline Engine Limits Applicable to S/N 28-7690001 through 28-7990589: For all operations, 2700 r.p.m. (180 hp) Applicable to S/N 28-8090001 through 28-8690056; 28-8690061; 28-8690062; and 2890001 through 2890205: For takeoff 5 minutes at 2700 r.p.m. (180 hp) For maximum continuous operation, 2650 r.p.m. (178 hp) Propeller and Propeller Limits Sensenich 76EM8S5 For S/N 28-7690001 through 28-7790607: Static r.p.m. at maximum permissible throttle setting, not over 2425 r.p.m., not under 2325 r.p.m. at sea level, ISA conditions. (Reference aircraft Maintenance Manual for test procedure to determine approved static r.p.m. under nonstandard conditions.) No additional tolerance permitted. Diameter: Not over or under 76". For S/N 28-7890001 through 28-8690056; 28-8690061; 28-8690062; and 2890001 through 2890205: Static r.p.m. at maximum permissible throttle setting, not over 2340 r.p.m., not under 2240 r.p.m. at sea level, ISA conditions. (Reference aircraft Maintenance Manual for test procedure to determine approved static r.p.m. under nonstandard conditions.) No additional tolerance permitted. Diameter: Not over or under 76". Propeller Spinner Piper P/N 65805-00. See NOTE 11. Airspeed Limits Never exceed 171 mph (148 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS For S/N 28-7690001 thru 28-7690467: Maneuvering 124 mph (108 knots) CAS For S/N 28-7790001 thru 28-7990589, 28-8090001 through 28-8690056, 28-8690061, 28-8690062, and 2890001 through 2890205: Maneuvering @ 2550 lbs. 128 mph (111 knots) CAS Maneuvering @ 1634 lbs. 102 mph ( 89 knots) CAS Flaps Extended 115 mph (100 knots) CAS Center of Gravity Range Normal Category (+82.0) to (+93.0) at 2050 lb. or less (+88.6) to (+93.0) at 2550 lb. Utility Category (+82.0) to (+93.0) at 2050 lb. or less (+83.0) to (+93.0) at 2130 lb. Straight line variation between points given. Empty Weight C. G. Range None Maximum Weight Normal Category: Ramp - 2558 lb. * Page 21 of 47 2A13 Takeoff - 2550 lb. Utility Category: Ramp - 2138 lb. * Takeoff - 2130 lb. * - Ramp weights for S/N 28-8090001 through 28-8690056; 28-8690061; 28-8690062; and 2890001 through 2890205 only. No. of Seats Normal Category: 4 (2 at +80.5, 2 at +118.1) Utility Category: 2 (2 at +80.5) Maximum Baggage 200 lb. at (+142.8) Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+27.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 25° Down 12.5° Rudder (±2°) Left 27° Right 27° Stabilator (±1°) Up 14° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±2°) Left 30° Right 30° Manufacturer's Serial Numbers 28-7690001 through 28-8690056; 28-8690061; 28-8690062; and 2890001 through 2890205. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers 28-7690001 through 28-8690056; 28-8690061; 28-8690062; and 2890001 through 2890205 under the delegation option provisions of FAR 21. See NOTE 20. XV - B.- Model PA-28-181 (Archer III), 4 PCLM (Normal Category), 2 PCLM (Utility Category), Approved August 30, 1994, for S/N 2890206 through 2890231, 2843001 and up, 2881001 and up, and 28010001 and up. Engine Lycoming O-360-A4M with carburetor settings 10-6102 or 10-5193 for aircraft prior to S/N 2843501 or Lycoming IO-360-B4A engine with injector model RSA-5AD1, Lycoming Part Number 61J28702, Avstar Part Number AV 2581600 Fuel 100 or 100LL aviation grade fuel Engine Limits For all operations, 2700 r.p.m. (180 hp) Propeller and Propeller Limits Sensenich 76EM8S14-0-62 Static r.p.m. at maximum permissible throttle setting, not over 2340 r.p.m., not under 2240 r.p.m. at sea level, ISA conditions. (Reference aircraft Maintenance Manual for test procedure to determine approved static r.p.m. under nonstandard conditions.) No additional tolerance permitted. Diameter: Not over or under 76". Propeller Spinner Piper P/N 83349-12 Airspeed Limits Never exceed 171 mph (148 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS Maneuvering @ 2550 lbs. 128 mph (111 knots) CAS Maneuvering @ 1634 lbs. 102 mph ( 89 knots) CAS Flaps Extended 115 mph (100 knots) CAS 2A13 Page 22 of 47 Center of Gravity Range Normal Category (+82.0) to (+93.0) at 2050 lb. or less (+88.6) to (+93.0) at 2550 lb. Utility Category (+82.0) to (+93.0) at 2050 lb. or less (+83.0) to (+93.0) at 2130 lb. Straight line variation between points given. Empty Weight C. G. Range None Maximum Weight Normal Category: Ramp - 2558 lb. Takeoff - 2550 lb. Utility Category: Ramp - 2138 lb. Takeoff - 2130 lb. No. of Seats Normal Category: 4 (2 at +80.5, 2 at +118.1) Utility Category: 2 (2 at +80.5) Maximum Baggage 200 lb. at (+142.8) Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+27.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps Up 0° (±1°) Down 10°, 25°, 40° (±2°) Ailerons (±2°) Up 25° Down 12.5° Rudder (±1°) Left 28° Right 28° Stabilator (±1°) Up 14° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±2°) Left 30° Right 30° (S/N 2890206 through 2890231) (±1°) Left 20° Right 20° (S/N 2843001 & up, 2881001 & up, and 28010001 and up) Manufacturer's Serial Numbers 2890206 through 2890231, 2843001 and up, 2881001 and up, and 28010001 and up. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers 2890206 through 2890231, 2843001 and up, 2881001 and up, and 28010001 and up under the delegation option provisions of FAR 21. Lycoming IO-360-B4A available on airplane serial numbers 2843821, 2843852 and up, 2881001 and up, and 28010001 and up. XV - C.- Model PA-28-181 (Piper Pilot 100i), 3 PCLM (Normal Category), Approved November 16, 2020, for S/N 28020001 and up. Engine Lycoming IO-360-B4A engine with injector model RSA-5AD1, Lycoming Part Number 61J28702, Avstar Part Number AV 2581600 . Fuel 100 or 100LL aviation grade fuel Engine Limits For all operations, 2700 r.p.m. (180 hp) Propeller and Propeller Limits Sensenich 76EM8S14-0-62 Static r.p.m. at maximum permissible throttle setting, not over 2340 r.p.m., not under 2240 r.p.m. at sea level, ISA conditions. (Reference aircraft Maintenance Manual for test procedure to determine approved static r.p.m. under nonstandard conditions.) No additional tolerance permitted. Diameter: Not over or under 76". Page 23 of 47 2A13 Propeller Spinner Piper P/N 83349-12 Airspeed Limits Never exceed 171 mph (148 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS Maneuvering @ 2550 lbs. 128 mph (111 knots) CAS Maneuvering @ 1634 lbs. 102 mph ( 89 knots) CAS Flaps Extended 115 mph (100 knots) CAS Center of Gravity Range (+82.0) to (+93.0) at 2050 lb. or less (+88.6) to (+93.0) at 2550 lb. Straight line variation between points given. Empty Weight C. G. Range None Maximum Weight Ramp - 2558 lb. Takeoff - 2550 lb. No. of Seats 3 (2 at +80.5, 1 at +118.1) Maximum Baggage 200 lb. at (+142.8) Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+27.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps Up 0° (±1°) Down 10°, 25°, 40° (±2°) Ailerons (±2°) Up 25° Down 12.5° Rudder (±1°) Left 28° Right 28° Stabilator (±1°) Up 14° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±1°) Left 20° Right 20° Manufacturer's Serial Numbers 28020001 and up. XVI - A. - Model PA-28-161 (Warrior II), 4 PCLM (Normal Category), 2 PCLM (Utility Category), Approved October 22, 1976, for S/N 28-7716001 through 28-8216300, and 2841001 through 2841365 (Cadet only) Engine Lycoming O-320-D3G with carburetor setting 10-5135, 10-5009 or 10-5217, or Lycoming O-320-D2A with carburetor setting 10-5135 or 10-5217. Fuel 100 octane minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (160 hp) Propeller and Propeller Limits Sensenich 74DM6-0-60 Static r.p.m. at maximum permissible throttle setting not over 2430 r.p.m., not under 2330 r.p.m., at sea level, ISA conditions. (Reference aircraft Maintenance Manual for test procedure to determine approved static r.p.m. under nonstandard conditions.) No additional tolerance permitted. Diameter: Not over 74", not under 72". 2A13 Page 24 of 47 or Sensenich 74DM6-0-58 Static r.p.m. at maximum permissible throttle setting not over 2465 r.p.m., not under 2365 r.p.m., at sea level, ISA conditions. (Reference aircraft Maintenance Manual for test procedure to determine approved static r.p.m. under nonstandard conditions.) No additional tolerance permitted. Diameter: Not over 74", not under 72". Propeller Spinner Piper P/N 35323 or P/N 36850. See NOTE 11. Airspeed Limits Never exceed 160 KIAS Maximum structural cruising 126 KIAS Maneuvering at 2325 lb. gross weight 111 KIAS Maneuvering at 1531 lb. gross weight 88 KIAS Flaps Extended 103 KIAS Center of Gravity Range Normal Category (+83.0) to (+93.0) at 1950 lb. or less (+87.0) to (+93.0) at 2325 lb. See NOTE 27. Utility Category (+83.0) to (+93.0) at 1950 lb. or less (+83.8) to (+93.0) at 2020 lb. Straight line variation between points given. Empty Weight C.G. Range None Maximum Weight Normal Category: 2325 lb. Utility Category: 2020 lb. Ramp: 2332 lb. (Cadet only) See NOTE 27. No. of Seats Normal Category: 4 (2 at +80.5, 2 at +118.1) Utility Category: 2 (+2 at +80.5) Maximum Baggage Eligible Normal Category only: 200 lb. at(+142.8) 50 lb. (Cadet only) Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+27.5) (6 quarts usable) See NOTE 1 for data system oil. Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 25° Down 12.5° Rudder (±2°) Left 27° Right 27° Stabilator (±1°) Up 14° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±1°) Left 30° Right 30° S/N 28-7716001 thru 28-8216300 (±1°) Left 20° Right 20° S/N 2841001 thru 2841365 (See Note 29) Manufacturer's Serial Numbers 28-7716001 through 28-8216300, and 2841001 through 2841365 (Cadet only). The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers 28-7716001 through 28-8216300, and 2841001 through 2841365 under the delegation option provisions of FAR 21. See NOTE 20. Page 25 of 47 2A13 XVI - B. Model PA-28-161 (Warrior II), 4 PCLM (Normal Category), 2 PCLM (Utility Category), Approved July 1, 1982, for S/N 28-8316001 through 28-8616057, and 2816001 through 2816109. Engine Lycoming O-320-D3G with carburetor setting 10-5135, 10-5009 or 10-5217, or Lycoming O-320-D2A with carburetor setting 10-5135 or 10-5217. Fuel 100 octane minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (160 hp) Propeller and Propeller Limits Sensenich 74DM6-0-60 Static r.p.m. at maximum permissible throttle setting not over 2430 r.p.m., not under 2330 r.p.m. at sea level, ISA conditions. (Reference aircraft Maintenance Manual for test procedure to determine approved static r.p.m. under nonstandard conditions.) No additional tolerance permitted. Diameter: Not over 74", not under 72". or Sensenich 74DM6-0-58 Static r.p.m. at maximum permissible throttle setting not over 2465 r.p.m., not under 2365 r.p.m., at sea level, ISA conditions. (Reference aircraft Maintenance Manual for test procedure to determine approved static r.p.m. under nonstandard conditions.) No additional tolerance permitted. Diameter: Not over 74", not under 72". Propeller Spinner Piper P/N 36850. See NOTE 11. Airspeed Limits Never exceed 160 KIAS Maximum structural cruising 126 KIAS Maneuvering at 2440 lb. gross weight 111 KIAS See NOTE 26. Maneuvering at 1531 lb. gross weight 88 KIAS Flaps Extended 103 KIAS Center of Gravity Range Normal Category (+83.0) to (+93.0) at 1950 lb. or less (+88.3) to (+93.0) at 2440 lb. See NOTE 26. Utility Category (+83.0) to (+93.0) at 1950 lb. or less (+83.8) to (+93.0) at 2020 lb. Straight line variation between points given Empty Weight C.G. Range None Maximum Weight Normal Category: Ramp - 2447 lb. Takeoff - 2440 lb. See NOTE 26. Utility Category: Ramp - 2027 lb. Takeoff - 2020 lb. No. of Seats Normal Category: 4 (2 at +80.5, 2 at +118.1) Utility Category: 2 (2 at +80.5) Maximum Baggage Eligible Normal Category only: 200 lb. at (+142.8) Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+27.5) (6 quarts usable) See NOTE 1 for data on system oil. 2A13 Page 26 of 47 Control Surface Movements Wing flaps Up 0° (±1°) Down 40° (±2°) Ailerons (±2°) Up 25° Down 12.5° Rudder (±2°) Left 27° Right 27° S/N 28-8316001 thru 28-8416095 Rudder (±1°) Left 28° Right 28° S/N 28-8416096 & Up, 2816001 thru 2816109 Stabilator (±1°) Up 14° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±1°) Left 30° Right 30° S/N 28-8316001 thru 28-8416095 (±1°) Left 20° Right 20° S/N 28-8416096 & Up, 2816001 thru 2816109 (See Note 29) Manufacturer's Serial Nos. 28-8316001 through 28-8616057, and 2816001 through 2816109. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers 28-8316001 through 28-8616057, and 2816001 through 2816109 under the delegation option provisions of FAR 21. See NOTE 20. 28-8616006{this serial number aircraft has been reported stolen and its airworthiness condition is unknown} XVI - C. Model PA-28-161 (Warrior III), 4 PCLM (Normal Category), 2 PCLM (Utility Category), Approved July 1, 1994, for S/N 2816110 through 2816119, and 2842001 and up. Engine Lycoming O-320-D3G with carburetor setting 10-5135, 10-5009 or 10-5217 Fuel 100 or 100LL aviation grade gasoline Engine Limits For all operations, 2700 r.p.m. (160 hp) Propeller and Propeller Limits Sensenich 74DM6-0-60 Static r.p.m. at maximum permissible throttle setting not over 2430 r.p.m., not under 2330 r.p.m., at sea level, ISA conditions. (Reference aircraft Maintenance Manual for test procedure to determine approved static r.p.m. under nonstandard conditions.) No additional tolerance permitted. Diameter: Not over 74", not under 72". Propeller Spinner Piper P/N 36850. See NOTE 11. Airspeed Limits Never exceed 160 KIAS Maximum structural cruising 126 KIAS Maneuvering at 2440 lb. gross weight 111 KIAS See NOTE 26. Maneuvering at 1531 lb. gross weight 88 KIAS Flaps Extended 103 KIAS Center of Gravity Range Normal Category (+83.0) to (+93.0) at 1950 lb. or less (+88.3) to (+93.0) at 2440 lb. See NOTE 26. Utility Category (+83.0) to (+93.0) at 1950 lb. or less (+83.8) to (+93.0) at 2020 lb. Straight line variation between points given Page 27 of 47 2A13 Empty Weight C.G. Range None Maximum Weight Normal Category: Ramp - 2447 lb. Takeoff - 2440 lb. See NOTE 26. Utility Category: Ramp - 2027 lb. Takeoff - 2020 lb. No. of Seats Normal Category: 4 (2 at +80.5, 2 at +118.1) Utility Category: 2 (2 at +80.5) Maximum Baggage Eligible Normal Category only: 200 lb. at (+142.8) Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+27.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps Up 0° (±1°) Down 10°, 25°, 40° (±2°) Ailerons (±2°) Up 25° Down 12.5° Rudder (±1°) Left 28° Right 28° Stabilator (±1°) Up 14° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±1°) Left 20° Right 20° Manufacturer's Serial Nos. 2816110 through 2816119, and 2842001 and up. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers 2816110 through 2816119, and 2842001 and up under the delegation option provisions of FAR 21. XVII - Model PA-28R-201 (Arrow III), 4 PCLM (Normal Category), Approved November 3, 1976, for S/N 28R-7737002 through 28R-7837317; 2837001 through 2837061; and 2844001 and up. Engine Lycoming IO-360-C1C6 Injector Bendix Type RSA-5AD1, Part List Number 2524450 Precision Airmotive (PAC) formerly Bendix: Part List Number PAM 2524450-9 Fuel 100 or 100LL aviation grade gasoline Engine Limits For all operations, 2700 r.p.m. (200 hp) Propeller and Propeller Limits McCauley Constant Speed Hub Model B2D34C213, Blade Model 90 DHA-16 Pitch: High 27.5° ± .5°, Low 12.5 ± .2° at 30" station. Diameter: Not over 74", not under 73". Governor Assembly: Hartzell Model F-2-7 ( ) Avoid continuous operation between 1500 and 1950 r.p.m. below 15" manifold pressure. or Hartzell Constant Speed Hub Model HC-C2YK-1( )F, Blade Model F7666A-2R Pitch: High 29.0° ± 2°, Low 14.0° ± .2° at 30" station. Diameter: Not over 74", not under 72". Governor Assembly: F-2-7 ( ) Propeller Spinner For McCauley propeller: Piper P/N 35828-2 For Hartzell propeller: Piper P/N 99374 See NOTE 11. 2A13 Page 28 of 47 Airspeed Limits Never exceed 183 KIAS Maximum structural cruising 146 KIAS Maneuvering 118 KIAS Flaps Extended 103 KIAS Maximum Gear Extension 129 KIAS Maximum Gear Retraction 107 KIAS Center of Gravity Range (+82.0) to (+91.5) at 2375 lb. or less (+88.9) to (+91.5) at 2750 lb. Straight line variation between points given. Moment due to retraction of gear (+819 in-lb.) Empty Weight C.G. Range None Maximum Weight 2750 lb. No. of Seats 4 (2 at +80.5, 2 at +118.1) Maximum Baggage 200 lb. at (+142.8) Fuel Capacity 77 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+24.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps Up 0° (±1°) Down 10°, 25°, 40° (±2°) Ailerons (±2°) Up 25° Down 12.5° Rudder (±1°) Left 28° Right 28° Stabilator (±1°) Up 16° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±2°) Left 30° Right 30° Manufacturer's Serial Numbers 28R-7737002 through 28-7837317; 2837001 through 2837061; and 2844001 and up. The manufacturer is authorized to issue airworthiness certificates for airplanes serial numbers 28R-7737002 through 28-7837317; 2837001 through 2837061; and 2844001 and up under the delegation option provisions of FAR 21. See NOTE 20. XVIII - Model PA-28R-201T (Turbo Arrow III), 4 PCLM (Normal Category), Approved October 8, 1976, for S/N 28R-7703001 through 28R-7803373, and 2803001 through 2803012. Engine Continental TSIO-360-F or TSIO-360-FB Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2575 r.p.m. at 41" Hg. manifold pressure (200 hp) Propeller and Propeller Limits 1 Hartzell Hub Model BHC-C2YF-1BF, Blade Model F8459A-8R Pitch Setting at 30" Station: High: 29° ± 1.0°, Low: 14.4° ± 0.2°. Diameter: Not over 76", not under 75". Governor: Hartzell E-5 or Woodward G210681 Avoid continuous operation between 2000 and 2200 r.p.m. with engine manifold pressure above 32" Hg. Avoid continuous ground operation in cross and tail winds of over 10 knots between 1700 and 2100 r.p.m. Propeller Spinner Hartzell P/N C3568 Spinner Assembly. See NOTE 11. Page 29 of 47 2A13 Airspeed Limits Never exceed 183 KIAS Maximum structural cruising 146 KIAS Maneuvering 119 KIAS Flaps Extended 103 KIAS Maximum Gear Retraction 107 KIAS Maximum Gear Extension 129 KIAS Maximum Gear Extended 129 KIAS Center of Gravity Range (+86.0) to (+90.0) at 2900 lb. (+78.0) to (+90.0) at 2240 lb. or less Straight line variation between points given. Moment due to retraction of landing gear (+819 in-lb.) Empty Weight C. G. Range None Maximum Weight Ramp: 2912 lb. Takeoff: 2900 lb. No. of Seats 4 (2 at +80.5, 2 at +118.1) Maximum Baggage 200 lb. at (+142.8) Fuel Capacity 77 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+13.5) (5 quarts usable) See NOTE 1 for data on system oil. Maximum Operating Altitude 20,000 feet Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 25° Down 12.5° Rudder (±1°) Left 28° Right 28° Stabilator (±1°) Up 16° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±2°) Left 30° Right 30° Manufacturer's Serial Numbers 28R-7703001 through 28R-7803373, and 2803001 through 2803012. The manufacturer is authorized to issue airworthiness certificates for airplanes serial numbers 28R-7703001 through 28R-7803373, and 2803001 through 2803012 under the delegation option provisions of FAR 21. See NOTE 20. XIX - Model PA-28-236 (Dakota), 4 PCLM (Normal Category), Approved June 1, 1978, for S/N 28-7911001 through 28-8611008; 2811001 through 2811050. Engine Lycoming O-540-J3A5D with carburetor setting 10-5054 Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2400 r.p.m. (235 hp) Propeller and Propeller Limits Hartzell HC-F2YR-1( )F/F 8468A-4R Pitch: High 32° ±2°, Low 16.25° ± ¼°. Diameter: Not over 80", not under 78". Governor Assembly: Hartzell F-4-21( ) 2A13 Page 30 of 47 Propeller Spinner Hartzell P/N C3568 Spinner Assembly. See NOTE 11. Airspeed Limits Never exceed 197 mph (171 knots) CAS Maximum structural cruising 156 mph (135 knots) CAS Maneuvering at 3000 lb. 140 mph (122 knots) CAS Maneuvering at 1761 lb. 108 mph (94 knots) CAS Flaps Extended 115 mph (100 knots) CAS Center of Gravity Range (+79.8) to (+92.0) at 1900 lb. or less (+82.5) to (+92.0) at 2500 lb. (+88.5) to (+92.0) at 3000 lb. Straight line variation between points given. Empty Weight C. G. Range None Maximum Weight 3000 lb. Number of Seats 4 (2 at +80.5, 2 at +118.1) Maximum Baggage 200 lb. at (+142.8) Fuel Capacity 77 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 12 quarts at (+29.1) (9 1/2 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 25° Down 12.5° Rudder (±1°) Left 28° Right 28° Stabilator (±1°) Up 16° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±1°) Left 30° Right 30° Manufacturer's Serial Numbers 28-7911001 through 28-8611008; and 2811001 through 2811050. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers 28-7911001 through 28-8611008; and 2811001 through 2811050; under the delegation option provisions of FAR 21. See NOTE 20. XX - A. Model PA-28RT-201 (Arrow IV), 4 PCLM (Normal Category), Approved November 13, 1978, for S/N 28R-7918001 through 28R-7918267. Engine Lycoming IO-360-C1C6 Injector Bendix Type RSA-5AD1, Part List Number 2524450 Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (200 hp) Propeller and Propeller Limits McCauley Constant Speed Hub Model B2D34C213, Blade Model 90 DHA-16 Pitch: High 27.5° ±.5°, Low 12.5° ±.2° at 30" station. Diameter: Not over 74", not under 73". Governor Assembly: Hartzell Model F-2-7 ( ) Avoid continuous operation between 1500 and 1950 r.p.m. below 15" manifold pressure. or Hartzell Constant Speed Hub Model HC-C2YK-1( )F, Blade Model F7666A-2R Pitch: High 29.0° ± 2°, Low 14.0° ± .2° at 30" station. Diameter: Not over 74", not under 72". Governor Assembly: Hartzell Model F-2-7( ) Page 31 of 47 2A13 Propeller Spinner For the McCauley propeller: Piper P/N 35828-2 For the Hartzell propeller: Piper P/N 99374 See NOTE 11. Airspeed Limits Never exceed 190 KIAS Maximum structural cruising 149 KIAS Flaps extended 108 KIAS Maximum gear extension 130 KIAS Maximum gear retraction 109 KIAS Maximum gear extended 130 KIAS Maneuvering at 2750 lb. 121 KIAS Maneuvering at 1863 lb. 96 KIAS Center of Gravity Range (+85.5) to (+93.0) at 2400 lb. or less (+90.0) to (+93.0) at 2750 lb. Straight line variation between points given. Moment due to retraction of gear (+819 in-lb.) Empty Weight C. G. Range None Maximum Weight 2750 lb. No. of Seats 4 (2 at +80.5, 2 at +118.1) Maximum Baggage 200 lb. at (+142.8) Fuel Capacity 77 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+24.5) 6 quarts usable See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 25° Down 12.5° Rudder (±1°) Left 33° Right 33° Stabilator (±1°) Up 14° Down 10° Stabilator Tab Up 2.5° (±1°) Down 10 (±.5°) Nose Wheel Travel (±2°) Left 30° Right 30° Manufacturer's Serial Numbers 28R-7918001 through 28R-7918267. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers 28R-7918001 through 28R-7918267 under the delegation option provisions of FAR 21. XX - B. Model PA-28RT-201 (Arrow IV), 4 PCLM (Normal Category), Approved November 13, 1978, for S/N 28R-8018001 through 28R-8218026. Engine Lycoming IO-360-C1C6 Injector Bendix Type RSA-5AD1, Part List Number 2524450 Fuel 100/130 minimum grade aviation gasoline Engine Limits For 5-minute takeoff, 2700 r.p.m. (200 hp) For maximum continuous operation, 2650 r.p.m. (196 hp) Propeller and Propeller Limits McCauley Constant Speed Hub Model 2D34C215, Blade Model 90 DJA-14E Pitch: High 27.5° ± .5; Low 12.5°  .2° at 30" station. Diameter: Not over 76", not under 75". Governor Assembly: Hartzell Model F-2-7 ( ) Avoid continuous operation between 1400 and 1750 r.p.m. below 15" manifold pressure. 2A13 Page 32 of 47 Propeller Spinner Piper P/N 35828-2. See NOTE 11. Airspeed Limits Never exceed 190 KIAS Maximum structural cruising 149 KIAS Flaps Extended 108 KIAS Maximum gear extension 130 KIAS Maximum gear retraction 109 KIAS Maximum gear extended 130 KIAS Maneuvering at 2750 lb. gross weight 121 KIAS Maneuvering at 1863 lb. gross weight 96 KIAS Center of Gravity Range (+85.5) to (+93.0) at 2400 lb. or less (+90.0) to (+93.0) at 2750 lb. Straight line variation between points given. Moment due to retraction of gear (+819 in-lb.) Empty Weight C. G. Range None Maximum Weight 2750 lb. Number of Seats 4 (2 at +80.5, 2 at +118.1) Maximum Baggage 200 lb. at (+142.8) Fuel Capacity 77 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+24.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 25° Down 12.5° Rudder (±1°) Left 33° Right 33° Stabilator (±1°) Up 14° Down 10° Stabilator Tab Up 2.5° (±1°) Down 10 (±.5°) Nose Wheel Travel (±2°) Left 30° Right 30° Manufacturer's Serial Numbers 28R-8018001 through 28R-8218026. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers 28R-8018001 through 28R-8218026 under the delegation option provisions of FAR 21. See NOTE 20. Page 33 of 47 2A13 XXI - Model PA-28RT-201T (Turbo Arrow IV), 4 PCLM (Normal Category), Approved November 13, 1978, for S/N 28R-7931001 through 28R-8631005, and 2831001 through 2831038. Engine Continental TSIO-360-FB Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2575 r.p.m., 41" Hg. manifold pressure (200 hp) Propeller and Propeller Limits 1 Hartzell Hub Model BHC-C2YF-1( )F, Blade Model F8459A-8R Pitch: High 29° ± 1.0°, Low 14.4° ± .2° at 30" station. Diameter: Not over 76", not under 75". Governor: Hartzell E-5 or Woodward G210681 Avoid continuous operation between 2000 and 2200 r.p.m. with engine manifold pressure above 32" Hg. Avoid continuous ground operation in cross and tail winds of over 10 knots between 1700 and 2100 r.p.m. or 1 Hartzell Hub Model PHC-C3YF-1( )F, Blade Model F7663-2R Pitch: High 33° ± 1°, Low 13.2° ± .2°. Diameter: Not over 76", not under 72". Governor: Hartzell E-5, Woodward G210681 or G210776 Propeller Spinner For the Hartzell Hub Model BHC-C2YF-1( )F: Hartzell P/N C3568 Spinner Assembly For the Hartzell Hub Model PHC-C3YF-1( )F: Piper PS50077-80 Spinner Assembly (Hartzell C3570) See NOTE 11. Airspeed Limits Never exceed 193 KIAS Maximum structural cruising 152 KIAS Maneuvering at 2900 lb. 124 KIAS Maneuvering at 1893 lb. 97 KIAS Flaps Extended 108 KIAS Maximum Gear Retraction 111 KIAS Maximum Gear Extension 133 KIAS Maximum Gear Extended 133 KIAS Center of Gravity Range (+89.0) to (+93.0) at 2900 lb. (+85.0) to (+93.0) at 2240 lb. or less Straight line variation between points given. Moment due to retraction of landing gear (+819 in-lb.) Empty Weight C. G. Range None Maximum Weight Ramp: 2912 lb. Takeoff: 2900 lb. No. of Seats 4 (2 at +80.5, 2 at +118.1) Maximum Baggage 200 lb. at (+142.8) Fuel Capacity 77 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+13.5) (5 quarts usable) See NOTE 1 for data on system oil. 2A13 Page 34 of 47 Maximum Operation Altitude 20,000 feet Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 25° Down 12.5° Rudder (±1°) Left 33° Right 33° Stabilator (±1°) Up 14° Down 10° Stabilator Tab Up 2.5° (±1°) Down 10 (±.5°) Nose Wheel Travel (±2°) Left 30° Right 30° Manufacturer's Serial Numbers 28R-7931001 through 28R-8631005, and 2831001 through 2831038. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers 28R-7931001 through 28R-8631005, and 2831001 through 2831038 under the delegation option provisions of FAR 21. See NOTE 20. XXII - Model PA-28-201T (Turbo Dakota), 4 PCLM (Normal Category), Approved December 14, 1978, for S/N 28-7921001 through 28-7921095. Engine Continental TSIO-360-FB Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2575 r.p.m., 41" Hg. manifold pressure (200 hp) Propeller and Propeller Limits 1 Hartzell Hub Model BHC-C2YF-1( )F, Blade Model F8459A-8R Pitch: High 29° ± 1.0°, Low 14.4° ± .2° at 30" station. Diameter: Not over 76", not under 75". Governor: Hartzell E-5 or Woodward G210681 Avoid continuous operation between 2000 and 2200 r.p.m. with engine manifold pressure above 32" Hg. Avoid continuous ground operation in cross and tail winds of over 10 knots between 1700 and 2100 r.p.m. Propeller Spinner Hartzell P/N C3568 Spinner Assembly. See NOTE 11. Airspeed Limits Never exceed 169 KIAS Maximum structural cruising 140 KIAS Maneuvering at 2900 lb. 122 KIAS Maneuvering at 1841 lb. 96 KIAS Flaps Extended 102 KIAS Center of Gravity Range (+86.0) to (+90.0) at 2900 lb. (+78.0) to (+90.0) at 2240 lb. or less Straight line variation between points given. Empty Weight C. G. Range None Maximum Weight 2900 lb. No. of Seats 4 (2 at +80.5, 2 at +118.1) Maximum Baggage 200 lb. at (+142.8) Fuel Capacity 77 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+13.5) (5 quarts usable) See NOTE 1 for data on system oil. Page 35 of 47 2A13 Maximum Operation Altitude 20,000 feet Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 25° Down 12.5° Rudder (±2°) Left 27° Right 27° Stabilator (±1°) Up 16° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Nose Wheel Travel (±1°) Left 30° Right 30° Manufacturer's Serial Numbers 28-7921001 through 28-7921095. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers 28-7921001 through 28-7921095 under the delegation option provisions of FAR 21. See NOTE 20. DATA PERTINENT TO ALL MODELS Datum 78.4" forward of wing leading edge (straight wing only). 78.4" forward of inboard intersection of straight and tapered sections (semi-tapered wings). Leveling Means Two screws left side fuselage below window. Certification Basis Type Certificate No. 2A13 issued October 31, 1960. Date of Application for Type Certificate, February 14, 1958. Delegation Option Authorization granted per FAR 21, Subpart J, July 17, 1968. PA-28-140 and PA-28-151: CAR 3 effective May 15, 1956, including Amendments 3-1, 3-2, and 3-4; paragraphs 3.304 and 3.705 of Amendment 3-7 effective May 3, 1962; FAR 23.955 and 23.959 as amended by Amendment 23-7 effective September 14, 1969; and FAR 23.1327 and 23.1547 as amended by Amendment 23-20 effective September 1, 1977. PA-28-150, PA-28-160, PA-28-180, PA-28-235, PA-28S-160, PA-28S-180, PA-28R-180, and PA-28R-200: CAR 3 effective May 15, 1956, including Amendments 3-1 and 3-2; paragraphs 3.304 and 3.705 of Amendment 3-7 effective May 3, 1962; FAR 23.955 and 23.959 as amended by Amendment 23-7 effective September 14, 1969; and FAR 23.1327 and 23.1547 as amended by Amendment 23-20 effective September 1, 1977. PA-28-161: CAR 3 effective May 15, 1956, including Amendments 3-1 and 3-2; paragraph 3.387(d) of Amendment 3-4; paragraphs 3.304 and 3.705 of Amendment 3-7 effective May 3, 1962; FAR 23.955 and 23.959 as amended by Amendment 23-7 effective September 14, 1969; FAR 23.1557(c)(1) as amended by Amendment 23-18 effective May 2, 1977; FAR 23.1327 and 23.1547 as amended by Amendment 23-20 effective September 1, 1977; and FAR 36 effective December 1, 1969, through Amendment 36-4. For aircraft equipped with Piper factory installed optional Avidyne Entegra system and Mid-Continent Model 4300-411 Electric Attitude Indicator (See Piper Report VB-1892, Appendix E), the additional certification basis for installation specific items only is: 14 CFR Part 23 regulations FAR 23.301, 23.337, 23.341, 23.473, 23.561(b)(3), 23.607, 23.611, as amended by Amdt. 23-48; FAR 23.303, 23.307, 23.601, 23.609, 23.1367, 23.1381 issued on 02/01/65; FAR 23.305, 23.613, 23.773, 23.1525, 23.1549 as amended by Amdt. 23-45; FAR 23.603, 23.605 as amended by Amdt. 23-23; FAR 23.777, 23.955, 23.1191, 23.1337 as amended by Amdt. 23-51; FAR 23.1301, 23.1327, 23.1335 as amended by Amdt. 23-20; FAR 23.867, 23.1303, 23.1307, 23.1309, 23.1311, 23.1321, 23.1323, 23.1329, 23.1351, 23.1353, 23.1359, 23.1361, 23.1365, as amended by Amdt. 23-49; FAR 23.1305 as amended by Amdt. 23-52; FAR 23.1322, 23.1331, 23.1357, 23.1431 as amended by Amdt. 23-43; FAR 23.1325, 23.1543, 23.1545, 23.1555, 23.1563, 23.1581, 23.1583, 23.1585 as amended by Amdt. 23-50; FAR 23. 771 as amended by Amdt. 23-14; FAR 23.1501, 23.1541 as amended by Amdt. 23-21; FAR 23.1523 as amended by Amdt. 23-34; FAR 23.1529 as amended by Amdt. 23-26; Special Condition for HIRF (Docket # CE207), date July 30, 2004. 2A13 Page 36 of 47 PA-28-181: CAR 3 effective May 15, 1956, including Amendments 3-2 and 3-4; paragraphs 3.304 and 3.705 of Amendment 3-7 effective May 3, 1962; FAR 23.207, 23.221, 23.955 and 23.959 as amended by Amendment 23-7 effective September 14, 1969; FAR 23.1557(c)(1) as amended by Amendment 23-18 effective May 2, 1977; and FAR 23.1327 and 23.1547 as amended by Amendment 23-20 effective September 1, 1977. FAR 36, Appendix G, Amendment 36-16 for the PA-28-181 (Archer III, Piper Pilot 100i), S/N 2890206 through 2890231, 2843001 and up, 2881001 and up, 28010001 and up and 28020001 and up. For aircraft equipped with Piper factory installed optional Avidyne Entegra system and Mid-Continent Model 4300-411 Electric Attitude Indicator (See Piper Report VB-1892, Appendix E), as installed by Piper Drawing Number 85191, the additional certification basis for installation specific items only is: 14 CFR Part 23 regulations FAR 23.301, 23.337, 23.341, 23.473, 23.561(b)(3), 23.607, 23.611, as amended by Amdt. 23-48; FAR 23.303, 23.307, 23.601, 23.609, 23.1367, 23.1381 issued on 02/01/65; FAR 23.305, 23.613, 23.773, 23.1525, 23.1549 as amended by Amdt. 23-45; FAR 23.603, 23.605 as amended by Amdt. 23-23; FAR 23.777, 23.955, 23.1191, 23.1337 as amended by Amdt. 23-51; FAR 23.1301, 23.1327, 23.1335 as amended by Amdt. 23-20; FAR 23.867, 23.1303, 23.1307, 23.1309, 23.1311, 23.1321, 23.1323, 23.1329, 23.1351, 23.1353, 23.1359, 23.1361, 23.1365, as amended by Amdt. 23-49; FAR 23.1305 as amended by Amdt. 23-52; FAR 23.1322, 23.1331, 23.1357, 23.1431 as amended by Amdt. 23-43; FAR 23.1325, 23.1543, 23.1545, 23.1555, 23.1563, 23.1581, 23.1583, 23.1585 as amended by Amdt. 23-50; FAR 23. 771 as amended by Amdt. 23-14; FAR 23.1501, 23.1541 as amended by Amdt. 23-21; FAR 23.1523 as amended by Amdt. 23-34; FAR 23.1529 as amended by Amdt. 23-26; Special Condition for HIRF (Docket # CE207), date July 30, 2004. For aircraft equipped with Piper factory installed optional Garmin International Model G1000 Integrated Avionics system and the Aspen Evolution Model EFD 1000 Standby Instrument, as installed by Piper Drawing Number 107500, the additional certification basis for installation specific items only is: 14 CFR Part 23 regulations: 23.207(a)(b)(c) as amended by Amdt. 23-45; 23.21, 23.23(a), 23.25, 23.29, 23.251, 23.301(a)(b)(c), 23.303, 23.305, 23.307, 23.337, 23.341(a)(c), 23.473, 23.561(a)(b)(3)(e), 23.601, 23.603, 23.605(a), 23.607, 23.609, 23.611, 23.613, 23.625, 23.773(a)(1)(2), 23.777(a)(b), 23.867, 23.1301, 23.1305(a)(1)(2)(3)(b)(2)(4)(i), 23.1306, 23.1307, 23.1308(a)(b)(c), 23.1309(a)(1)(2)(b)(c)(d)(e), 23.1311, 23.1321, 23.1322, 23.1323(a)(c), 23.1325(a)(b)(1)(2)(i), 23.1326, 23.1327(a), 23.1329(d)(g)(h), 23.1335, 23.1337(b)(1)(4), 23.1351(a)(1)(2)(i)(b)(1)(i)(3)(c)(4)(d), 23.1353, 23.1357, 23.1359(c), 23.1361(c), 23.1365, 23.1367, 23.1381, 23.1431(a)(b)(e), 23.1501, 23.1507, 23.1523, 23.1525, 23.1529, 23.1541(a)(b), 23.1543(b)(c), 23.1545(a)(b), 23.1549(a)(b)(c), 23.1553, 23.1555(a)(b), 23.1563(a), 23.1581(a)(c), 23.1583(g)(h)(m), 23.1585(j), 23.1589(a) as amended by Amdt. 23-61; 23.1303(a)(b)(c)(f) as amended by Amdt. 23-62 For aircraft equipped with Piper factory installed optional Lycoming Fuel Injected IO-360- B4A engine, as installed by Piper Drawing Number 107500, the additional certification basis for installation specific items only is: 3.71, 3.73, 3.74, 3.75, 3.76, 3.171(a), 3.172, 3.173, 3.174, 3.186, 3.188, 3.195(a)(2)(b), 3.241, 3.291, 3.292, 3.293, 3.294, 3.295, 3.296, 3.301, 3.302, 3.306, 3.307, 3.384, 3.386(a), 3.411(a)(b), 3.415, 3.416(a)(b), 3.417, 3.419, 3.422(a)(1)(2)(b)(c)()(2), 3.429, 3.430, 3.437(a)(b)(e)(f), 3.438, 3.440, 3.441(a)(1)(b)(c), 3.442, 3.443, 3.444, 3.445, 3.446(a), 3.448, 3.449(a)(b), 3.550, 3.551, 3.552, 3.553, 3.554, 3.562, 3.570, 3.572, 3.575(a), 3.576, 3.581, 3.582, 3.583, 3.584, 3.585, 3.586, 3.605(a)(b), 3.611, 3.615, 3.616, 3.617, 3.618, 3.623, 3.624(a)(b), 3.625, 3.627, 3.628, 3.629, 3.630, 3.633, 3.635, 3.638, 3.651, 3.652, 3.655(c)(2), 3.671, 3.673, 3.674, 3.681(a), 3.685, 3.693, 3.744, 3.745(a), 3.746(a)(c), 3.747, 3.755(a)(b), 3.762, 3.777(a), 3.778(b), 3.779, as amended by 3-2; 14 CFR Part 23.1101 and as amended by Amdt. 23-43; 23.955(a)(c)(1)(3)(e)(1), 23.1093(a)(5), and 23.1105 as amended by Amdt. 23-51; 23.1337(b)(1)(4) and 23.1549(a)(b)(c) as amended by Amdt. 23- 61. Page 37 of 47 2A13 For aircraft equipped with Piper factory installed optional Garmin G1000 NXi as installed by Piper Drawing Number 107500, the additional certification basis for installation specific items only is: 14 CFR Part 23.21, 23.23(a), 23.25(a)(b), 23.29, 23.301(a)(b)(c), 23.303, 23.305, 23.307, 23.337, 23.341(a)(c), 23.473, 23.561(a)(b)(3)(e), 23.601, 23.603, 23.605(a), 23.607, 23.609, 23.611, 23.613, 23.625, 23.627, 23.771(a), 23.773(a)(1)(2), 23.777(a)(b), 23.867, 23.1301(a)(b)(c)(d), 23.1305(a)(1)(2)(3)(b)(2)(4)(i), 23.1306, 23.1307, 23.1308(a)(b)(c), 23.1309(a)(1)(2)(b)(c)(d)(e), 23.1311(a)(1)(2)(3)(4)(5)(6)(7)(b)(c), 23.1321(a)(c)(d)(5)(e), 23.1322(a)(b)(c)(d)(e), 23.1323(a)(c), 23.1325(a)(b)(1)(2)(i), 23.1326(a)(b), 23.1327(a), 23.1329(h), 23.1335, 23.1337(b)(1)(4), 23.1351(a)(1)(2)(i), 23.1353(h), 23.1357(a)(b)(c)(d), 23.1359(c), 23.1365, 23.1381(a)(b)(c), 23.1383(c), 23.1385(a)(b)(c)(d), 23.1387(a)(b)(c)(d)(e), 23.1389(a)(b)(c), 23.1391, 23.1393, 23.1395(a)(b), 23.1397(a)(b)(c), 23.1401(a)(b)(c)(d)(e)(f), 23.1431(a)(b)(e), 23.1523, 23.1525, 23.1541(a)(b), 23.1543(b)(c), 23.1545(a)(b), 23.1549(a)(b)(c), 23.1501, 23.1529, 23.1553, 23.1555(a)(b), 23.1581(a)(c), 23.1583(g)(h)(m), 23.1585(j), 23.1589(a) as amended by Amndt. 23-61. 14 CFR 23.1303(a)(b)(c)(f) as amended by Amndt. 23-62 CAR3 sections 3.581, 3.582, 3.583, 3.586, 3.635, effective May 15, 1956 including Amendment 3-2. For aircraft equipped with Piper factory installed optional Garmin G1000 NXi Phase II and GFC700 AFCS (or Garmin G1000NXi Phase II only), as installed by Piper Drawing Number 107500, the additional certification basis for installation specific items only is: CAR3 sections 3.581, 3.582, 3.583, 3.586 effective May 15, 1956 including Amendment 3- 2 14 CFR Part 23.21(b), 23.23(a), 23.25(a)(b), 23.29, 23.143(a)(b), 23.207(a)(b)(c)(d)(e), 23.301(a)(b)(c), 23.303, 23.305, 23.307, 23.337, 23.341(a)(c), 23.397, 23.399, 23.473, 23.561(a)(b)(3)(e), 23.601, 23.603, 23.605(a), 23.607, 23.609, 23.611, 23.613, 23.625, 23.627, 23.681, 23.683, 23.693, 23.771(a), 23.777(a)(b), 23.779, 23.867, 23.1141(d), 23.1301(a)(b)(c)(d), 23.1305(a)(1)(2)(3)(b)(2)(4)(i), 23.1306, 23.1308, 23.1309(a)(1)(2)(b)(c)(d)(e), 23.1311(a)(1)(2)(3)(4)(5)(6)(7)(b)(c), 23.1321(c)(d)(5)(e), 23.1322(a)(b)(c)(d)(e), 23.1323(a)(c), 23.1325(a)(b)(1)(2)(i), 23.1327(a), 23.1329(a)(1)(b)(c)(d)(e)(f)(g)(h), 23.1335, 23.1337(b)(1)(4), 23.1351(a)(1)(2)(i), 23.1353(h), 23.1357(a)(b)(c)(d), 23.1359(c), 23.1365, 23.1367(a)(b)(c)(d), 23.1381(a)(c), 23.1431(a)(b)(e), 23.1501, 23.1523, 23.1525, 23.1529, 23.1541(a)(b), 23.1543(c), 23.1545(a)(b), 23.1549(a)(b)(c), 23.1553, 23.1555(a), 23.1581(a)(c), 23.1583(g)(h)(m), 23.1585(a)(1)(j), 23.1589(a) as amended by Amndt. 23-61; 14 CFR 23.1303(a)(b)(c)(f) as amended by Amndt. 23-62 For aircraft equipped with Piper factory installed optional Garmin G5 standby instrument, as installed by Piper Drawing Number 107569 Rev G or later FAA approved revision, the additional certification basis for installation specific items only is: 14 CFR Part 23.303, 23.307(a), 23.1306(a)(b), 23.1381(a)(b), as amended by Amndt. 23-0 14 CFR Part 23.771(a) as amended by Amndt. 23-14 14 CFR Part 23.1301(d), 23.1327(a)(1)(2), as amended by Amndt. 23-20 14 CFR Part 23.1541(a)(b)(c) as amended by Amndt. 23-21 14 CFR Part 23.601, 23.603, 23.605(a) as amended by Amndt. 23-23 14 CFR Part 23.1529 as amended by Amndt. 23-26 14 CFR Part 23.1322(a)(e), 23.1357(a)(b)(c)(d), as amended by Amndt. 23-43 14 CFR Part 23.305, 23.613(a)(b), 23.773(a)(2) as amended by Amndt. 23-45 14 CFR Part 23.301(a), 23.337(a)(b), 23.607(b) as amended by Amndt. 23-48 14 CFR Part 23.1307, 23.1309(b)(1)(2)(4)(e), 23.1321(c)(e), 23.1351(a)(1)(2)(i), 23.1359, 23.1365(a)(b)(c)(d)(e), 23.1431(b) as amended by Amndt. 23-49 14 CFR Part 23.1325(a)(b), 23.1543(b), 23.1581(a)(b)(d)(f) as amended by Amndt. 23-50 14 CFR Part 23.25(a)(b), 23.29, 23.1308(a)(b)(c) as amended by Amndt. 23-61 14 CFR Part 23.251(a), 23.561(a)(b)(3)(c), 23.777(a)(b), 23.853(a), 23.1301(a)(b)(c), 23.1303(a)(b)(c)(f), 23.1309(a)(1)(2), 23.1311(a)(1)(2)(3)(6)(7)(b), 23.1323(a)(b)(c), 23.1331(a)(b)(1)(c), 23.1353(h), 23.1431(a), 23.1545(a)(b)(c), 23.1555(a)(b), 23.1583(m), 23.1585(a) as amended by Amndt. 23-62 14 CFR Part 23.2515(a)(b), 23.2520(a)(b) as amended by Amndt. 23-64 2A13 Page 38 of 47 For aircraft equipped with Piper factory installed High Temperature Operation Improvements, as installed by Piper Drawing Number 107500-011,-012 Rev AD or later FAA approved revision, the additional certification basis for installation specific items only is: CAR Part 3 Amdt 3-2 - 3.71, 3.73, 3.74, 3.75, 3.76, 3.171(a), 3.172, 3.173, 3.174, 3.186, 3.188, 3.291, 3.292, 3.293, 2.294, 3.295, 3.296, 3.301, 3.302, 3.306, 3.307, 3.386(a), 3.411, 3.429, 3.430, 3.437(a)(b)(e)(f), 3.438, 3.440, 3.441(a)(1)(b)(c), 3.442, 3.443, 3.444, 3.445, 3.446(a), 3.448, 3.449(a)(b), 3.550, 3.551, 3.552, 3.553, 3.554, 3.562, 3.570, 3.572, 3.575(a), 3.576, 3.581, 3.582, 3.583, 3.584, 3.585, 3.586, 3.623, 3.624, 3.625, 3.633, 3.638, 3.651, 3.652, 3.655(b), 3.674, 3.744, 3.755(a)(b), 3.764(a)(b)(d), 3.777(b), 3.778(b), 3.779 14 CFR Part 21 Amdt. 21-97 – 21.93(b) 14 CFR Part 23 Amdt. 23-50 – 23.1521(a)(b)(5)(c)(4) 14 CFR Part 23 Amdt. 23-51 – 23.779(b)(2), 23.955(a)(c)(1)(3)(e)(1), 23.975(b) 14 CFR Part 23 Amdt. 23-61 – 23.1301(d), 23.1309(a)(1)(2)(b), 23.1311(a)(1)(2)(3)(4)(6)(7), 23.1321(a)(e), 23.1322(a)(b)(c)(d)(e), 23.1337, 23.1359(c), 23.1543(b)(c), 23.1549(a)(b)(c), 23.1581(a)(1)(2)(c), 23.1583(b), 23.1585(j) For Piper Pilot 100i aircraft is equipped with the Lycoming Fuel Injected IO-360-B4A engine, and the Garmin G5 standby instrument and is defined by Piper Drawing 28G00A001 Revision NEW or later FAA approved revision. The additional certification basis is: CAR Part 3 Amdt 3-2 – 3.171, 3.172, 3.173, 3.174, 3.185, 3.186 (a)(b), 3.187, 3.188, 3.189, 3.190, 3.191, 3.212, 3.213, 3.214, 3.215, 3.216, 3.217, 3.218, 3.219, 3.222, 3.223, 3.224, 3.242, 3.243, 3.244, 3.248, 3.249, 3.253, 3.254, 3.255, 3.256, 3.393, 3.411 (b), 3.581, 3.582, 3.583, 3.584, 3.585, 3.586, 3.624 14 CFR Part 21 Amndt. 21-97 – 21.93 (b) 14 CFR Part 23 Amndt. 23-Orig – 23.21 (a)(1)(b), 23.305 (b), 23.399, 23.601. 23.609, 23.627, 23.671, 23.1367, 23.1381 (a)(b)(c), 23.1519, 23.1543 (b) 14 CFR Part 23 Amndt. 23-7 – 23.395 (a)(1), 23.689 (a)(2)(3)(b) 14 CFR Part 23 Amndt. 23-14 – 23.771 (a), 23.1182 14 CFR Part 23 Amndt. 23-17 – 23.685 (a)(c)(d) 14 CFR Part 23 Amndt. 23-20 – 23.1301 (d), 23.1327 (a)(b), 23.1335, 23.1547 (a)(b)(c)(d)(e) 14 CFR Part 23 Amndt. 23-21 – 23.1501 (a)(b), 23.1541 (a)(b), 23.1555 (a)(b) 14 CFR Part 23 Amndt. 23-23 – 23.603, 23.605 (a) 14 CFR Part 23 Amndt. 23-26 – 23.1529 14 CFR Part 23 Amndt. 23-33 – 23.777 (a), 14 CFR Part 23 Amndt. 23-34 – 23.863 (a)(b), 23.1523 14 CFR Part 23 Amndt. 23-43 – 23.993, 23.1322 (a)(b)(c)(d)(e), 23.1357 (a)(b)(c)(d) 14 CFR Part 23 Amndt. 23-45 – 23.23 (a), 23.251, 23.397, 23.613 (a)(b)(c), 23.773 (a)(2), 23.1525, 23.1549 (a)(b)(c) 14 CFR Part 23 Amndt. 23-48 – 23.607, 23.611 14 CFR Part 23 Amndt. 23-49 – 23.677 (a)(d), 23.785 (a)(1)(2)(d)(j)(n)(1)(2)(3), 23.1307, 23.1321 (a)(c)(d)(5)(e), 23.1326 (a)(b), 23.1329 (a)(1)(2)(b)(c)(d)(e)(f)(g)(h), 23.1351 (a)(1)(2)(i)(b)(1)(i)(ii)(iii)(3)(c)(4)(d)(e), 23.1359 (a)(b)(c), 23.1361 (a)(c), 23.1365 (a)(b)(c)(1)(2)(d)(e)(f), 23.1383 (a)(b)(c) 14 CFR Part 23 Amndt. 23-50 – 23.25, 23.143 (c), 23.1325 (a)(b)(1)(2)(i), 23.1521 (a)(b)(1)(c)(1)(4), 23.1543 (b)(c), 23.1553, 23.1581 (a)(b)(2)(c) 14 CFR Part 23 Amndt. 23-51 – 23.955 (a)(2)(3)(4)(c), 23.963 (e), 23.1183, 23.1337 (a)(b)(1)(c) 14 CFR Part 23 Amndt. 23-52 – 23.1305 (a)(1)(2)(3)(b)(2)(4)(i) 14 CFR Part 23 Amndt. 23-53 – 23.901 (a)(b)(1)(e) 14 CFR Part 23 Amndt. 23-61 – 23.29, 23.207 (a)(b), 23.625, 23.867, 23.1563 (a), 23.1589 (a) 14 CFR Part 23 Amndt. 23-62 – 23.561 (a)(b)(3)(e), 23.777 (a)(b), 23.853 (a), 23.1193 (a)(b)(c)(d)(e), 23.1301 (a)(b)(c), 23.1303 (a)(b)(c)(f), 23.1309 (a)(1)(2)(b)(c)(d), 23.1310 (a), 23.1311 (a)(1)(2)(3)(4)(5)(6)(7)(b)(c), 23.1323 (a)(b)(c)(d), 23.1331 (a)(b)(1)(2)(c), 23.1353 (a)(b)(c)(d)(e)(h), 23.1431 (a)(b)(e), 23.1545 (a)(b)(1)(2)(3)(4), 23.1555 (a)(b)(d)(3), 23.1559 (c), 23.1583 (d)(h)(j)(m), 23.1585 (a)(j) 14 CFR Part 23 Amndt. 23-64 – 23.2335, 23.2510, 23.2515, 23.2520 For PA-28-181 aircraft equipped with main wing spar assembly, defined by Piper drawing 28W57A013, the additional certification basis for the main wing spar assembly structure is: 14 CFR 23.1529, 23.2010, 23.2240(a) as amended by Amendment 23-64 effective August 30, 2017. Page 39 of 47 2A13 For PA-28-181 (Pilot 100i) aircraft equipped with optional non-Halon fire extinguisher additional certification basis for installation specific items only is: 14 CFR 23.851, 23.1529, 23.1561 as amended by Amdt. 23-62 For PA-28-181 (Archer III) aircraft equipped with optional non-Halon fire extinguisher additional certification basis for installation specific items only is: 14 CFR 23.851, 23.1301, 23.1529, 23.1541, 23.1561 as amended by Amdt. 23-62 For PA-28-181 (Archer III) aircraft equipped with optional System Release 7 or later and Garmin GDL 60 Datalink, as installed by Piper Drawing Number 107569 Rev K or later FAA approved revision, the additional certification basis for installation specific items only is: 14 CFR Part 23.21, 23.303, 23.307(a), 23.601, 23.609(a)(1)(2)(3), 23.627, 23.1367(c)(d) as amended by Admt 23-0 14 CFR 23.867 as amended by Admt 23-7 14 CFR 23.771(a) as amended by Admt 23-14 14 CFR 23.1301(a)(b)(c)(d) as amended by Admt 23-20 14 CFR 23.29, 23.1501(a)(b) as amended by Admt 23-21 14 CFR 23.603(a)(1)(2)(3)(b), 23.605(a) as amended by Admt 23-23 14 CFR 23.1529 as amended by Admt 23-26 14 CFR 23.1523 as amended by Admt 23-34 14 CFR 23.1322(a)(b)(c)(d)(e), 23.1357(a)(b)(c)(d) as amended by Amdt 23-43; 14 CFR 23.23(a), 23.305, 23.613(a)(b)(1)(2)(c)(d)(e), 23.773(a)(1)(2), 23.1525 as amended by Admt 23-45 14 CFR 23.301(a)(b)(c), 23.337(a)(1)(2)(3)(b)(1)(2)(c), 23.341(a)(c), 23.473(a)(b)(1)(2)(d)(e)(g), 23.607(a)(b), 23.611 as amended by Admt 23-48 14 CFR 23.1307, 23.1309(a)(1)(2)(b)(c)(d)(e), 23.1311(a)(1)(2)(3)(4)(6)(7)(b)(c), 23.1351(a)(1)(2)(i), 23.1353(h), 23.1359(c), 23.1431(a)(b)(e), 23.1365 as amended by Admt 23-49 14 CFR 23.25(a)(b), 23.1581(a)(c), 23.1583(g)(h)(m), 23.1585(j), 23.1589(a) as amended by Admt 23-50 14 CFR 23.1308(a)(b)(c) as amended by Admt 23-57 14 CFR 23.1306 as amended by Admt 23-61 14 CFR 23.251(a), 23.561(a)(b)(3)(e), 23.777(a)(b), 23.1303(a)(b)(c)(f) as amended by Admt 23-62 14 CFR 23.2505, 23.2510 as amended by Admt 23-64 14 CFR 23.2500(b) as amended by Admt 23-65. PA-28R-201: CAR 3 effective May 15, 1956, including Amendments 3-1 and 3-2; paragraphs 3.304 and 3.705 of Amendment 3-7 effective May 3, 1962; FAR 23.965 of FAR 23 effective February 1, 1965; FAR 23.221, 23.955, 23.959 and 23.1091 as amended by Amendment 23-7 effective September 14, 1969; FAR 23.967(e)(2) as amended by Amendment 23-14 effective December 20, 1973; FAR 23.1093 as amended by Amendment 23-15 effective October 31, 1974; FAR23.1557(c)(1) as amended by 23- 18 effective May 2, 1977; FAR 23.1327 and 23.1547 as amended by Amendment 23-20 effective September 1, 1977; and FAR 36 effective December 1, 1969, through Amendment 36-4 (no acoustical change). For aircraft equipped with Piper factory installed optional Avidyne Entegra system and Mid-Continent Model 4300-411 Electric Attitude Indicator (See Piper Report VB-1892, Appendix E), the additional certification basis for installation specific items only is: 14 CFR Part 23 regulations FAR 23.301, 23.337, 23.341, 23.473, 23.561(b)(3), 23.607, 23.611, as amended by Amdt. 23-48; FAR 23.303, 23.307, 23.601, 23.609, 23.1367, 23.1381 issued on 02/01/65; FAR 23.305, 23.613, 23.773, 23.1525, 23.1549 as amended by Amdt. 23-45; FAR 23.603, 23.605 as amended by Amdt. 23-23; FAR 23.777, 23.955, 23.1191, 23.1337 as amended by Amdt. 23-51; FAR 23.1301, 23.1327, 23.1335 as amended by Amdt. 23-20; FAR 23.867, 23.1303, 23.1307, 23.1309, 23.1311, 23.1321, 23.1323, 23.1329, 23.1351, 23.1353, 23.1359, 23.1361, 23.1365, as amended by Amdt. 23-49; FAR 23.1305 as amended by Amdt. 23-52; FAR 23.1322, 23.1331, 23.1357, 23.1431 as amended by Amdt. 23-43; FAR 23.1325, 23.1543, 23.1545, 23.1555, 23.1563, 23.1581, 23.1583, 23.1585 as amended by Amdt. 23-50; FAR 23. 771 as amended by Amdt. 23-14; FAR 23.1501, 23.1541 as amended by Amdt. 23-21; FAR 23.1523 as amended by Amdt. 23-34; FAR 23.1529 as amended by Amdt. 23-26; Special Condition for HIRF (Docket # CE207), date July 30, 2004. 2A13 Page 40 of 47 PA-28R-201T: CAR 3 effective May 15, 1956, through Amendment 3-2 including paragraphs 3.304 and 3.705 of Amendment 3-7 effective May 3, 1962; FAR 23.965 of FAR 23 effective February 1, 1965; FAR 23.221, 23.901, 23.909, 23.955, 23.959, 23.1041, 23.1043, 23.1047, 23.1143, and 23.1527 as amended by Amendment 23-7 effective September 14, 1969; FAR 23.1441 as amended by Amendment 23-9 effective June 17, 1970; FAR 23.967(e)(2) as amended by Amendment 23-14 effective December 20, 1973; FAR 23.1305 as amended by Amendment 23-15 effective October 31, 1974; FAR 23.1327 and 23.1547 as amended by Amendment 23-20 effective September 1, 1977; and FAR 36 effective December 1, 1969, through Amendment 36-4. PA-28-236: CAR 3 effective May 15, 1956, through Amendment 3-2; paragraphs 3.84a of Amendment 3-4 effective January 15, 1951, 3.304 and 3.705 of Amendment 3-7 effective May 3, 1962; FAR 23.221, 23.955, 23.959 and 23.1091 as amended by Amendment 23-7 efftective September 14, 1969; FAR 23.1093 as amended by Amendment 23-17 effective February 1, 1977; FAR 23.1557(c)(1) as amended by Amendment 23-18 effective May 2, 1977; FAR 23.1327 and 23.1547 as amended by Amendment 23-20 effective September 1, 1977; FAR 23.1581(b)(2) as amended by Amendment 23-21 effective March 1, 1978; and applicable portions of FAR 36 as amended by Amendment 36-9 effective April 3, 1978. PA-28RT-201: CAR 3, effective May 15, 1956, through Amendment 3-2; paragraphs 3.304 and 3.705 of Amendment 3-7 effective May 3, 1962; FAR 23.965 of FAR 23 effective February 1, 1965; FAR 23.207, 23.221, 23.955, 23.959, and 23.1091 as amended by Amendment 23-7 effective September 14, 1969; FAR 23.201, 23.203, 23.427(c), and 23.967(e)(2) as amended by Amendment 23-14 effective December 20, 1973; FAR 23.1093 as amended by Amendment 23-15 effective October 31, 1974; FAR 23.1557(c)(1) as amended by Amendment 23-18 effective May 2, 1977; FAR 23.1327 and 23.1547 as amended by Amendment 23-20 effective September 1, 1977; FAR 23.1581(b)(2) as amended by Amendment 23-21 effective March 1, 1978; and applicable portions of FAR 36 as amended by Amendment 36-10 effective July 31, 1978. PA-28RT-201T: CAR 3 effective May 15, 1956, through Amendment 3-2; paragraphs 3.304 and 3.705 of Amendment 3-7 effective May 3, 1962; FAR 23.207, 23.221, 23.901, 23.909, 23.955, 23.959, 23.1041, 23.1043, 23.1047, 23.1091, 23.1143, and 23.1527 as amended by Amendment 23-7 effective September 14, 1969; FAR 23.201, 23.203, 23.427(c), and 23.967(e)(2) as amended by Amendment 23-14 effective December 20, 1973; FAR 23.1093 and 23.1305 as amended by Amendment 23-15 effective October 31, 1974; FAR 23.1557(c)(1) as amended by Amendment 23-18 effective May 2, 1977; FAR 23.1327 and 23.1547 as amended by Amendment 23-20 effective September 1, 1977; FAR 23.1581(b)(2) as amended by Amendment 23-21 effective March 1, 1978; and applicable portions of FAR 36 as amended by Amendment 36-10 effective July 31, 1978. Compliance with FAR 23.1441 as amended by Amendment 23-9 effective June 17, 1970, will be established with optional oxygen equipment. PA-28-201T: CAR 3 effective May 15, 1956, through Amendment 3-2; paragraphs 3.304 and 3.705 of Amendment 3-7 effective May 3, 1962; FAR 23.965 of FAR 23 effective February 1, 1965; FAR23.207, 23.221, 23.901, 23.909, 23.955, 23.959, 23.1041, 23.1043, 23.1047, 23.1091, and 23.1527 as amended by Amendment 23-7 effective September 14, 1969; FAR 23.201 and 23.203 as amended by Amendment 23- 14 effective December 20, 1973; FAR 23.1305 as amended by Amendment 23-15 effective October 31, 1974; FAR 23.1093 and 23.1143 as amended by Amendment 23-17 effective February 1, 1977; FAR 23.1557(c)(1) as amended by Amendment 23-18 effective May 2, 1977; FAR 23.1327 and 23.1547 as amended by Amendment 23-20 effective September 1, 1977; FAR 23.1581(b)(2) as amended by Amendment 23-21 effective March 1, 1978; and applicable portions of FAR 36 as amended by Amendment 36-10 effective July 31, 1978. Compliance with FAR23.1441 as amended by Amendment 23-9 effective June 17, 1970, will be established with optional oxygen equipment. Equivalent Safety Finding: CAR 3.757 for Models PA-28-161, PA-28R-201, PA-28R-201T, PA-28-236, PA-28RT-201, PA-28RT-201T, and PA-28-201T only. Production Basis Production Certificate No. 206 issued and the manufacturer authorized to issue airworthiness certificates under the delegation option provisions of FAR 21. Page 41 of 47 2A13 Equipment The basic required equipment as prescribed in the applicable airworthiness regulation (see Certification Basis) must be installed in the aircraft for certification. In addition, the following documents are required: MODEL AFM/POH REPORT NO. APPROVED SERIAL EFFECTIVITY PA-28-140 AFM VB-160 2/14/64 28-20001 through 28-26946, and 28-7125001 through 28-7125641 AFM VB-339 7/21/71 28-7225001 through 28-7325674 AFM VB-557 5/14/73 28-7425001 through 28-7625275 POH VB-770 6/16/76 28-7725001 through 28-7725290 PA-28-150 AFM VB-166 6/2/61 28-1 through 28-4377 PA-28-151 AFM VB-573 7/25/73 28-7415001 through 28-7615435 POH VB-780 6/18/80 28-7715001 through 28-7715314 PA-28-160 AFM VB-168 10/25/60 28-1 through 28-4377, and 28-1760A PA-28S-160 AFM VB-177 2/25/63 28-1 through 28-1760, and 28-1760A PA-28-161 POH VB-880 12/16/76 28-7716001 through 28-8216300 POH VB-1180 7/1/82 28-8316001 through 28-8616057, and 2816001 through 2816119 POH VB-1610 7/12/95 2842001 and up POH Supp. VB-1546 6/30/92 28-8316001 through 28-8616057, and 2816001 through 2816119 (See NOTE 28) POH VB-1360 9/9/88 2841001 through 2841365 POH Supp. VB-1545 5/29/92 2841001 through 2841365 (See NOTE 28) POH VB-1565 7/1/94 2816110 through 2816119 PA-28-180 AFM VB-163 8/3/62 28-671 through 28-5600 AFM VB-210 4/22/69 28-5601 through 28-5859, and 28- 7105001 through 28-7205091 AFM VB-355 9/1/71 28-7205092 through 28-7205318 AFM VB-437 5/22/72 28-7305001 through 28-7305601 and 28-E13 AFM VB-558 5/14/73 28-7405001 through 28-7505260 PA-28S-180 AFM VB-179 5/10/63 28-671 through 28-5859, and 28-7105001 through 28-7105234 PA-28-181 POH VB-760 8/15/75 28-7690001 through 28-7690467 POH VB-790 6/18/76 28-7790001 through 28-7990589 POH VB-1120 7/2/79 28-8090001 through 28-8690056, 28-8690061, 28-8690062, and 2890001 through 2890205 POH VB-1611 7/12/95 2843001 and up POH VB-1563 8/19/94 2890206 through 2890231 POH VB-2266 4/16/2013 2843701, 2843703 and up POH VB-2596 10/03/2016 2843852, 2843854 and up POH POH VB-2749 VB-2960 12/22/2017 11/16/2020 2843823, 2881001 and up, and 28010001 and up (See NOTE 31) 28020001 and up (See NOTE 31) PA-28R-180 AFM VB-173 6/8/67 28R-30001 through 28R-31270, and 28R-7130001 through 28R-7130013 2A13 Page 42 of 47 (continued) MODEL AFM/POH REPORT NO. APPROVED SERIAL EFFECTIVITY PA-28R-201 POH VB-870 12/21/76 28R-7737001 through 28R-7837317 POH VB-1365 9/15/88 2837001 through 2837061 POH VB-1612 7/12/95 2844001 and up PA-28R-200 AFM VB-175 1/9/69 28R-35001 through 28R-35820, and 28R-7135001 through 28R-7135229 AFM VB-343 10/14/71 28R-7235001 through 28R-7335446 AFM VB-560 5/14/73 28R-7435001 through 28R-7635545 PA-28R-201T POH VB-800 12/20/76 28R-7703001 through 28R-7803373 POH VB-1370 11/9/89 2803001 through 2803012 PA-28-235 AFM VB-170 7/15/63 28-10001 through 28-11378, and 28-7110001 through 28-7210023 AFM Supp. VB-357 8/25/71 28-10001 through 28-11378, and 28-7110001 through 28-7110023 AFM VB-442 6/9/72 28-7310001 through 28-7310176 and 28-E11 AFM VB-559 5/14/73 28-7410001 through 28-7610202 POH VB-810 1/21/77 28-7710001 through 28-7710089 PA-28-236 AFM FT-124, App E. 6/1/78 28-7911001 through 28-8611008, and OR 2811001 through 2811050 POH VB-910 6/1/78 28-7911001 through 28-8611008, and 2811001 through 2811050 PA-28RT-201 AFM FT-121, App C. 11/7/78 28R-7918001 through 28R-8218026 OR POH VB-930 11/30/78 28R-7918001 through 28R-7918267 PA-28RT-201 POH VB-1130 9/14/79 28R-8018001 through 28R-8218026 PA-28RT-201T AFM FT-130, App E. 11/7/78 28R-7931001 through 28R-8631005, and OR 2831001 through 2831038 POH VB-940 11/30/78 28R-7931001 through 28R-8631005, and 2831001 through 2831038 PA-28-201T AFM FT-126, App E. 12/14/78 28-7921001 through 28-7921095 OR VB-920 1/25/79 28-7921001 through 28-7921095 NOTE 1: Current weight and balance report, including list of equipment included in certification empty weight and loading instructions, when necessary, must be provided for each aircraft at the same time of original certification. The certificated empty weight and corresponding center of gravity location must include undrainable system oil (not included in the oil capacity) and unusable fuel as noted below. Unusable Fuel and Oil Quantity Applicable Models and Serial Numbers Fuel 12.0 lb. at (+103.0) PA-28R-180, PA-28R-200: all Serial Nos. PA-28-180: S/N 28-E13, and 28-7305001 through 28-7505260 Fuel 12.0 lb. at (+103.0) PA-28-235: S/N 28-E11, and S/N 28-7310001 through 28-7710089 Fuel 12.0 lb. at (+103.0) PA-28-151: S/N 28-7415001 through 28-7715314 Fuel 2.2 lb. at (+103.0) PA-28-140, PA-28-150, PA-28-160: all Serial Nos. Fuel 2.2 lb. at (+103.0) PA-28-180: S/N 28-03, S/N 28-671 through 28-5859, and 28-7105001 through 28-7205318 Oil 1.8 lb. at (+27.5) PA-28-140, PA-28-150, PA-28-160, PA-28-180: S/N 28-03, 28-1 through 28-1760, and 28-1760A Oil 1.8 lb. at (+27.5) PA-28-151: S/N 28-7415001 through 28-7715314 Page 43 of 47 2A13 Unusable Fuel and Oil Quantity Applicable Models and Serial Numbers Oil 1.8 lb. at (+40.5) PA-28-150, PA-28-160: S/N 28-1761 through 28-4377 PA-28-180: S/N 28-1761 through 28-5859, and 28-7105001 through 28-7205318 Oil 1.8 lb. at (+35.5) PA-28-180: S/N 28-E13, 28-7305001 through 28-7505260 Oil 1.8 lb. at (+36.5) PA-28R-180: all Serial Nos. Oil 3.9 lb. at (+35.6) PA-28R-200: S/N 28R-35001 through 28R-35820, and 28R-7135001 through 28R-7135229 Fuel 2.3 lb. at (+103.0) PA-28-235: S/N 28-10001 through 28-11378, and 28-7110001 Oil 2.4 lb. at (+41.0) through 28-7210023 Oil 2.4 lb. at (+36.0) PA-28-235: S/N 28-E11, and 28-7310001 through 28-7710089 Oil 3.9 lb. at (+30.6) PA-28R-200: S/N 28R-7235001 through 28R-7635545 Oil 1.8 lb. at (+35.5) PA-28-181: S/N 28-7690001 through 28-8690056, Fuel 12.0 lb. at (+103.0) 28-8690061, 28-8690062, and 2890001 through 2890231, 2843001 and up, 2881001 and up, 28010001 and up, and 28020001 and up Fuel 30.0 lb. at (+103.0) PA-28R-201: S/N 28R-7737001 through 28R-7837317, 2837001 Oil 3.9 lb. at (+30.6) through 2837061, and 2844001 and up Fuel 30.0 lb. at (+103.0) PA-28R-201T: S/N 28R-7703001 through 28R-7803373, 2803001 through 2803012 Oil 6.0 lb. at (+19.1) PA-28-161 Cadet: S/N 2841001 through 2841365 Fuel 12.0 lb. at (+103.0) PA-28-161: S/N 28-7716001 through 28-8616057, and Oil 1.8 lb. at (+27.5) 2816001 through 2816119 and 2842001 and up Fuel 30.0 lb. at (+103.0) PA-28-236: S/N 28-7911001 through 28-8611008, and Oil 5.2 lb. at (+36.0) 2811001 through 2811050 Fuel 30.0 lb. at (+103.0) PA-28RT-201: S/N 28R-7918001 through 28R-8218026 Oil 3.9 lb. at (+30.6) Fuel 30.0 lb. at (+103.0) PA-28RT-201T: S/N 28R-7931001 through 28R-8631005, Oil 6.0 lb. at (+19.1) 2831001 through 2831013 Fuel 30.0 lb. at (+103.0) PA-28-201T: S/N 28-7921001 through 28-7921095 Oil 6.0 lb. at (+19.1) NOTE 2 The following placards must be displayed in clear view of the pilot: In Normal Category Aircraft "THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUAL." In aircraft certificated in both Normal and Utility Categories "THIS AIRPLANE MUST BE OPERATED AS A NORMAL OR UTILITY CATEGORY AIRPLANE IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUALS." Reference AFM for additional required placards. 2A13 Page 44 of 47 NOTE 3 Instructions for Continued Airworthiness, including Airworthiness Limitations (e.g., Life Limits, if applicable), are identified in the following manuals: (a) PA-28-140, PA-28-150, PA-28-160, PA-28-180, PA-28-235, PA-28R-180 and PA-28R-200 – Service Manual 753-586 (some content applies to PA-28S-160 and PA-28S-180) (b) PA-28-151 and PA-28-161 (S/Ns through 2816119) – Service Manual 761-539 (c) PA-28-161 (Cadet, S/Ns 2841001 through 2841365) – Service Manual 761-829 (d) PA-28-161 (S/Ns 2842001 & up) – Airplane Maintenance Manual 761-882 (e) PA-28-181 (S/Ns 28-7690001 through 2890231) – Airplane Maintenance Manual 761-679 (f) PA-28-181 (S/Ns 2843001 and up, 2881001 and up, 28010001 and up, 28020001 and up) – Airplane Maintenance Manual 761-883 (S/Ns 2843001 and up, 2881001 and up, 28010001 and up, 28020001 and up) – Airplane Maintenance Manual Supplement 767-111 (SNs 2881041, 28020001 and up) (g) PA-28-201T – Airplane Maintenance Manual 761-702 (h) PA-28-236 – Airplane Maintenance Manual 761-681 (i) PA-28R-201 (SNs 28R-7737002 through 28R-7837317, 2837001 through 2837061) and PA-28R-201T – Service Manual 761-639 (j) PA-28R-201 (SNs 2844001 and up) – Airplane Maintenance Manual 761-895 (k) PA-28RT-201T and PA-28RT-201T – Airplane Maintenance Manual 761-694 Note: See NOTE 30 for converted seaplane configurations (identifed as NOTE 3 prior to Revision 64). NOTE 4 Takeoff r.p.m. for Models PA-28-180 and PA-28S-180, S/N 28-671 through 28-1760, and 28-1760A, restricted due to fuel flow capability of the emergency pump. NOTE 5 The Models PA-28-150, PA-28-160, PA-28-180; S/N 28-03, 28-1 through 28-5859, and 28-7105001 through 28-7205318 and PA-28-235; S/N 28-10001 through 28-11378, and 28-7110001 through 28-7210023, may be operated with the door removed in accordance with the FAA approved Airplane Flight Manual Supplement, Piper Report VB-182, dated September 3, 1963. The Model PA-28-140 may be operated with the door removed in accordance with the FAA approved Airplane Flight Manual Supplement dated August 12, 1965. NOTE 6 The Model PA-28-140, 2 PCLM (Normal Category Only), S/N 28-20001 through 28-20939 may be converted: (a) To a maximum weight of 2150 lb. by the installation of Piper Kit 756 962 and Sensenich propeller M74DM58. (b) To the four place, 4 PCLM (See Item VIII), configuration in accordance with Piper Drawing 65599. NOTE 7 The Model PA-28-140, 2 PCLM, S/N 28-20940 through 28-26946, and 28-7125001 through 28-7725290, may be converted to the four place, 4 PCLM (See Item VIII), configuration by the installation of Piper Kit 756 941 and appropriate seats. NOTE 8 The maximum cargo allowable of 125 lb. for S/N 28-1 through 28-1760, and 28-1760A may be increased to 200 lb. in accordance with Piper Service Spares Letter No. 242. NOTE 9 The Model PA-28-180 (Normal Category), S/N 28-671 through 28-3832, may be operated in Utility Category in accordance with Service Spares Letter No. 258. NOTE 10 All PA-28 models with Lycoming O-360-A3A engine and Sensenich propeller Model M76EMM-0, M76EMMS-0, 76EM8S5-0, or 76EM8-0 must avoid continuous operation between 2150 and 2350 r.p.m. Placards must be installed in accordance with Piper Service Letter No. 526, and Airplane Flight Manual Supplement No. 1, dated April 22, 1969. Page 45 of 47 2A13 NOTE 11 The Models PA-28-140, PA-28-150, PA-28-151, PA-28-160, PA-28-180; S/N 28-03, 28-1 through 28-5859, and 28-7105001 through 28-7205318; PA-28R-180 and PA-28R-200 may be operated with the spinner dome removed, or with the spinner dome and rear bulkhead removed. The PA-28-151, S/N 28-7415001 through 28-7715314, may be operated with the spinner dome removed, or with the spinner dome and front and rear bulkheads removed. The PA-28-180, S/N 28-7305001 through 28-7505260, and the PA-28-181; S/N 28- 7690001 through 28-8690062, and 2890001 through 2890205, may be operated with the spinner dome removed. The PA-28R-201; S/N 28R-7737002 through 28R-7837317, 2837001 through 2837061, and 2844001 and up, may be operated with the spinner dome removed. The PA-28R-201T; S/N 28R-7703001 through 28R-7803373, and 2803001 through 2803012, may be operated with the spinner dome removed. The PA-28-161, S/N 28-7716001 through 28-8216300 may be operated with the spinner dome and front and rear bulkheads removed. The PA-28-161; S/N 28-8316001 through 28-8616057, 2816001 through 2816119, and PA-28-161 (Cadet), S/N 2841001 through 2841365, may be operated with the spinner dome removed, or with the spinner dome and front and rear bulkheads removed. The PA-28-236; S/N 28-7911001 through 28-8611008, and 2811001 through 2811050, may be operated with the spinner dome removed. The PA-28RT-201, S/N 28R-7918001 through 28R-8218026, may be operated with the spinner dome removed. The PA-28RT-201T; S/N 28R-7931001 through 28R-8631005, and 2831001 through 2831013, may be operated with the spinner dome removed. The PA-28-201T, S/N 28-7921001 through 28-7921095, may be operated with the spinner dome removed. NOTE 12 Maximum baggage may be increased to 200 lb. at (+117) by the installation of Piper Kit 756 962 and Sensenich propeller M74DM-58 or 74DM6-0-58. Maximum baggage may be increased to 300 lb. (200 lb. at +117 and 100 lb. at +133) by the installation of Piper Kit 756 962, Sensenich propeller M74DM-58 or 74DM6-0-58 and when modified in accordance with Piper Drawing 66671. NOTE 13 Maximum baggage may be increased to 300 lb. (200 lb. at +117 and 100 lb. at +133) when modified in accordance with Piper Drawing 66671. NOTE 14 The Model PA-28-235; S/N 28-10001 through 28-11378, and 28-7110001 through 28-7210023, may be operated with the spinner dome removed, or with the spinner dome and rear bulkhead removed on the constant speed propeller installation only. NOTE 15 The Model PA-28-180, S/N 28-671 through 28-5859, may be operated to the expanded C.G. envelope: (a) For S/N 28-671 through 28-3072 by the installation of P/N 65280-00 tube - Landing Gear Strut Piston in accordance with Piper Service Letter 567 and in accordance with FAA approved Airplane Flight Manual Supplement No. 2, dated September 14, 1970, for Model PA-28-180 (Piper Report VB-261). (b) For S/N 28-3073 through 28-5859 in accordance with FAA approved Airplane Flight Manual Supplement No. 2, dated September 14, 1970, for Model PA-28-180 (Piper Report VB-261). NOTE 16 The Model PA-28-235, S/N 28-10001 through 28-11378, may be operated to the expanded C.G. envelope in accordance with FAA approved Airplane Flight Manual Supplement No. 1, dated September 14, 1970, for Model PA-28-235 (Piper Report VB-274). NOTE 17 The following serial numbered aircraft are not eligible for import certification to the U.S.: 28-5035, 28-5047, 28-5178, 28-5262, 28-5397, 28-5435, 28-11077, 28-11101, 28-11140, 28-11180, 28-11200, 28-11212, 28-11227, 28-11254, 28-11255, 28-24660, 28-24701, 28R-30861, 28R-30952, 28R-30972, 28R-31043, and 28R-31091. These aircraft have identification plates stamped "Ensenblado en Colombia." NOTE 18 Two propeller flange bushings must be replaced with Lycoming #72068S bushings at propeller blade positions corresponding to noncounterbored bolt holes in order to use the McCauley propeller. NOTE 19 Two propeller flange bushings must be replaced with Lycoming #72060S index bushing and Lycoming #721061S bushing, at flange index mark and opposite, in order to use the McCauley propellers. A spacer, Piper P/N 79528-0, is also required between propeller and engine flange. NOTE 20 The following model and serial number aircraft are not eligible for import certification to the U.S.: PA-28-140: 28-24660, 28-24701, 28-7225490, 28-7225491, 28-7225492, 28-7225493, 28-7225494, 28-7225495, 28-7225496, 28-7225497, 28-7225498, 28-7225499, 28-7325238, 28-7325371, 28-7325372, 28-7325373, 28-7325374, 28-7325375, 28-7325376, 28-7325377, 28-7325378, 28-7325379, 28-7325508, 28-7325516, 28-7325525, 28-7325526, 28-7325555, 28-7325556, 28-7325557, 28-7325558, 28-7325580, 28-7325581, 28-7325599, 28-7325600, 28-7425217, 28-7425222, 28-7425224, 28-7425271, 28-7425272, 28-7425273, 28-7425274, 28-7425275, 28-7425276, 28-7425277, 28-7425278, 28-7425279, 28-7425304, 28-7425305, 28-7425306, 28-7425307, 28-7425383, 28-7425384, 28-7525142, 28-7525144, 28-7525177, 2A13 Page 46 of 47 28-7525180, 28-7525181, 28-7525182, 28-7525197, 28-7525201, 28-7525215, 28-7525216, 28-7525217, 28-7525218, 28-7525230, 28-7525238, 28-7525243, 28-7525244, 28-7525246, 28-7525247, 28-7625060, 28-7625061, 28-7625130, 28-7625144, 28-7625272, 28-7625273, 28-7625274, 28-7625275, 28-7725053, and 28-7725188. PA-28-161: 28-7816330, 28-7916235, 28-8016266, 28-8116157, 28-8116158, 28-8316031, 28-8316032, 28-8616007, 2816006, 2816020, 2816021, and 2816022. PA-28-180: 28-5047, 28-5178, 28-5262, 28-5397, 28-5435, 28-7305315, 28-7305316, 28-7305499, 28-7405136, 28-7405137, 28-7405138, 28-7405139, 28-7405158, 28-7405160, 28-7405161, 28-7405167, 28-7405184, 28-7405185, 28-7405186, 28-7405187, 28-7405223, 28-7505138, 28-7505148, 28-7505159, 28-7505168, 28-7505169, 28-7505179, 28-7505189, and 28-7505260. PA-28-181: 28-7690362, 28-7790343, 28-7790344, 28-7790388, 28-7790533, 28-7790571, 28-7790605, 28-7890060, 28-7890185, 28-7890290, 28-7890351, 28-7890352, 28-7890406, 28-7890407, 28-7890463, 28-7890464, 28-7890465, 28-7890466, 28-7890480, 28-7890481, 28-7890507, 28-7890508, 28-7890509, 28-7890510, 28-7890534, 28-7890550, 28-7890551, 28-7990158, 28-7990251, 28-8090203, 28-8090243, 28-8090274, 28-8090349, 28-8190032, 28-8190098, 28-8190099, 28-8190174, 28-8190175, 28-8190200, 28-8190201, 28-8190261, 28-8190262, 28-8190317, 28-8190318, 28-8290020, 28-8290021, 28-8290022, 28-8290122, 28-8290123, 28-8290124, 28-8290125, 28-8290146, 28-8290147, 28-8290148, 28-8290149, 28-8390031, 28-8390032, 28-8390057, 28-8390058, 28-8390059, 28-8390060, 28-8690061, 28-8690062, 2890035, and 2890036. PA-28-201T: 28-7921085 PA-28-235: 28-11077, 28-11101, 28-11140, 28-11180, 28-11200, 28-11212, 28-11227, 28-11254, 28-11255, 28-11370, 28-11371, 28-11372, 28-11373, 28-7310074, 28-7310152, 28-7310153, 28-7310172, 28-7410074, 28-7410078, 28-7410089, 28-7410090, 28-7510072, 28-7510073, 28-7610087, 28-7610168, 28-7710033, 28-7710068, and 28-7710089. PA-28-236: 28-7911027, 28-7911028, 28-7911029, 28-7911030, 28-7911136, 28-7911219, 28-7911220, 28-7911221, 28-7911252, 28-8011020, 28-8011021, 28-8011062, 28-8011092, 28-8011093, 28-8011094, 28-8011107, 28-8111030, 28-8111038, 28-8111058, 28-8111068, 28-8111069, 28-8111070, 28-8411021, 28-8411022, 28-8411023, 28-8411024, 28-8411026, 28-8411027, 28-8411028, and 28-8411029. PA-28R-180: 28R-31091 PA-28R-200: 28R-7335201, 28R-7335202, 28R-7335326, 28R-7335328, 28R-7335377, 28R-7335387, 28R-7335395, 28R-7335397, 28-7435214, 28-7435229, 28-7435252, 28-7435253, 28R-7535146, 28R-7535149, 28R-7535167, 28R-7535168, 28R-7535214, 28R-7535217, and 28R-7635377. PA-28R-201: 28R-7737119, 28R-7837076, 28R-7837148, 28R-7837149, 28R-7837188, 28R-7837189, 28R-7837225, 28R-7837226, 28R-7837248, 28R-7837249, 28R-7837273, 28R-7837274, 28R-7837294, 28R-7837316, and 28R-7837317. PA-28R-201T: 28R-7703069, 28R-7703132, 28R-7703184, 28R-7703185, 28R-7703285, 28R-7703382, 28R-7803064, 28R-7803156, 28R-7803207, 28R-7803208, 28R-7803251, 28R-7803291, 28R-7803292, 28R-7803293, 28R-7803294, 28R-7803295, 28R-7803299, 28R-7803300, 28R-7803317, 28R-7803318, 28R-7803319, 28R-7803320, 28R-7803344, 28R-7803360, 28R-7803361, 28R-7803370, 28R-7803371, 28R-7803372, and 28R-7803373. PA-28RT-201: 28R-8118029, 28R-8118054, 28R-8118078, 28R-8218015, and 28R-8218016. PA-28RT-201T: 28R-7931122, 28R-7931205, 28R-7931206, 28R-7931262, 28R-7931296, 28R-7931297, 28R-8031062, 28R-8131029, 28R-8131083, and 28R-8131183. In addition, aircraft having the following serial number are not eligible for import certification to the U.S.: AR28-7325238, AR28-7325371, AR28-7325372, AR28-7325373, AR28-7325374, AR28-7325375, AR28-7325376, AR28-7325377, AR28-7325378, AR28-7325379, AR28-7305315, AR28-7305316, AR28-7335201, AR28-7335202, AR28-7325508, AR28-7325516, AR28-7325525, AR28-7325526, AR28-7310152, AR28-7310153, AR28-7325555, AR28-7325556, AR28-7325557, AR28-7325558, AR28-7305480, AR28-7305499, AR28-7335326, AR28-7335328, AR28-7325580, AR28-7325581, AR28-7325599, AR28-7325600, AR28-7335395, and AR28-7335397. Page 47 of 47 2A13 NOTE 21 Engines with serial numbers ending with "A" require the F-4-13 propeller governor assembly. Other engines require the F-4-3( ) propeller governor assembly. NOTE 22 Hartzell Propeller HC-C2YK-1( )/7666A-2 or HC-C2YK-1( )F/F7666A-2 approved with IO-360-C1C engine only (S/N 28R-7235001 through S/N 28R-7635516). NOTE 23 McCauley Propeller B2D34C213/90DHA-16 approved with IO-360-C1C6 engine only (S/N 28R-7635517 through 28R-7635545). NOTE 24 On Models PA-28-161; S/N 28-7816001 through 28-8616057, and S/N 2816001 through 2816109, and PA-28-181; S/N 28-7890001 through 28-8690056, 28-8690061, 28-8690062, 2890001 through 2890231, 2843001 and up, 2881001 and up, and 28010001 and up, the wheel fairings but not the landing gear strut fairings may be removed. NOTE 25 On Models PA-28-201T; S/N 28-7921001 through 28-7921095, and PA-28-236; S/N 28-7911001 through 28-8611008, and 2811001 through 2811050, the wheel fairings alone or the wheel fairings but not the landing gear strut fairings may be removed. NOTE 26 With installation of Piper Kit 88050, PA-28-161 2325 lb. Maximum Gross Weight Modification, the following weights apply: Normal Category: Ramp - 2332 lb. Takeoff - 2325 lb. Utility Category: Ramp - 2027 lb. Takeoff - 2020 lb. (See POH VB-1180 Supplement dated October 5, 1985.) NOTE 27 With installation of Piper Kit 88168, PA-28-161 Cadet 2202 lb. Maximum Gross Weight Modification, the following weights apply: Normal Category: Ramp - 2209 lb. Takeoff - 2202 lb. Utility Category: Ramp - 2027 lb. Takeoff - 2020 lb. (See POH VB-1410 dated March 14, 1990.) NOTE 28 POH Supplement VB-1546 is applicable to POH VB-1180. POH Supplement VB-1545 is applicable to POH VB-1360. Supplements VB-1545 and VB-1546 restrict maximum r.p.m. limitation to 2600 r.p.m. for foreign countries requiring reduced noise level operation. NOTE 29 If S/N 28-7716001 thru 28-8416095 has kit Piper P/N 764-975 removing bungee steering and installing solid rod steering, rig nose wheel travel (±10) 200 left 200 right. NOTE 30 The Models PA-28-160 and PA-28-180, S/N 28-508 to 28-1760, and 28-1760A may be converted to the seaplane configuration, PA-28S-160 and PA-28S-180, in accordance with Piper Drawing No. 62008. The Model PA-28-180, S/N 28-1761 through 28-5859, and 28-7105001 through 28-7205318, may be converted to the seaplane configuration, PA-28S-180, in accordance with Piper Drawing No. 65680. NOTE 31 For PA-28-181 (Archer III or Piper Pilot 100i) equipped with optional non-Halon Fire Extinguisher, the following applicable POH revision level (or later approved) is required: POH Rev. Serial Effectivty VB-2749 10 Archer III: 2881991 and up, and 28010001 and up VB-2960 6 Piper Pilot 100i: 28020252 and up ...END... ``` ## ADs (91, 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 2024-10-04](https://openairdocs.org/ad/2024-10-04): Wing, Attach Fittings · Piper PA-28-181, PA-28R-201, PA-44-180 and 1 more. Effective Jun 6, 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 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 2020-26-16](https://openairdocs.org/ad/2020-26-16): Wing Spar · Piper PA-28-151, PA-28-161, PA-28-181 and 12 more. Effective Feb 16, 2021 - [AD 2020-24-05](https://openairdocs.org/ad/2020-24-05): Wing Spar · Piper PA-28-140, PA-28-150, PA-28-160 and 4 more. Effective Dec 28, 2020 - [AD 2018-07-03](https://openairdocs.org/ad/2018-07-03): Placard and Markings · Piper PA-28-140, PA-28-150, PA-28-151 and 12 more. Effective Apr 20, 2018 - [AD 2017-14-04](https://openairdocs.org/ad/2017-14-04): Engine Oil · Piper PA-28-140, PA-28-150, PA-28-151 and 22 more. Effective Aug 15, 2017 - [AD 2016-07-21](https://openairdocs.org/ad/2016-07-21): Wing Ribs/Bulkhead · Piper PA-28-161, PA-28-181 and PA-28R-201. Effective Apr 26, 2016 - [AD 2013-02-13](https://openairdocs.org/ad/2013-02-13): Stabilizer Control System · Piper PA-28-140, PA-28-150, PA-28-151 and 33 more. Effective Mar 11, 2013 - [AD 2010-26-04](https://openairdocs.org/ad/2010-26-04): Engine · Piper PA-28-161 with STC SA03303AT. Effective Feb 1, 2011 - [AD 2010-15-10](https://openairdocs.org/ad/2010-15-10): Control wheel shafts · Piper PA-28-140, PA-28-150, PA-28-151 and 33 more. Effective Aug 31, 2010 - [AD 2009-05-05](https://openairdocs.org/ad/2009-05-05): Primary Flight Displays · Avidyne Primary Flight Display (S-TEC STC SA09543AC-D or 2 others). Effective Apr 3, 2009 - [AD 2006-12-07](https://openairdocs.org/ad/2006-12-07): ECi cylinder assemblies · Aerostar AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 386 more. Effective Jul 11, 2006 - [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 2005-19-20](https://openairdocs.org/ad/2005-19-20): Bushing screw thread expanders · Piper PA-28-160, PA-28-161, PA-28-180 and 1 more. Effective Nov 4, 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 2004-14-12](https://openairdocs.org/ad/2004-14-12): Control wheel attaching hardware · Piper PA-28-161, PA-28-181, PA-28R-201 and 8 more. Effective Aug 10, 2004 - [AD 2001-23-17](https://openairdocs.org/ad/2001-23-17): GNS 430 units · Cessna 172, 182, 206 and 209 more. Effective Dec 28, 2001 - [AD 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 99-26-05](https://openairdocs.org/ad/99-26-05): Induction Air Filter · Lavia Argentina PA-25, PA-25-235, PA-25-260 and 5 more. Effective Jan 13, 2000 - [AD 99-05-09](https://openairdocs.org/ad/99-05-09): Induction Air Filter · Piper PA-23-235, PA-23-250, PA-23-250 (Navy UO-1) and 20 more. Effective Mar 19, 1999 - [AD 96-10-01 R1](https://openairdocs.org/ad/96-10-01-R1): Landing Light Support and Seal Assembly · Piper PA-28-140, PA-28-150, PA-28-160 and 1 more. Effective Dec 14, 1998 - [AD 97-01-01 R1](https://openairdocs.org/ad/97-01-01-R1): Main Gear Sidebrace Stud · Piper PA-24, PA-24-250, PA-24-260 and 10 more. Effective Dec 8, 1998 - [AD 96-10-03](https://openairdocs.org/ad/96-10-03): Flap Handle Attach Bolt · Piper PA-28-140, PA-28-150, PA-28-151 and 28 more. Effective Jun 14, 1996 - [AD 94-14-14](https://openairdocs.org/ad/94-14-14): Nose Landing Gear Modification · Piper PA-28R-180, PA-28R-200, PA-28R-201 and 5 more. Effective Aug 19, 1994 - [AD 87-08-08 R3](https://openairdocs.org/ad/87-08-08-R3): Lower spar cap · Piper PA-28-140, PA-28-150, PA-28-151 and 28 more. Effective May 22, 1989 - [AD 86-17-01](https://openairdocs.org/ad/86-17-01): Ammeter Replacement · Piper PA-28-150, PA-28-160, PA-28-180 and 20 more. Effective Aug 21, 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 82-06-11 R1](https://openairdocs.org/ad/82-06-11-R1): Nose Landing Gear, Inspect, Rig, Modify · Piper PA-28R-200, PA-28R-201, PA-28R-201T and 2 more. Effective Jun 16, 1982 - [AD 81-23-05](https://openairdocs.org/ad/81-23-05): Seat Springs and Battery Box · Piper PA-28-151 and PA-28-161. Effective Mar 8, 1982 - [AD 81-11-02 R1](https://openairdocs.org/ad/81-11-02-R1): Oil Drain Valves · Piper PA-28R-200, PA-28R-201 and PA-28RT-201. Effective Oct 2, 1981 - [AD 80-19-01](https://openairdocs.org/ad/80-19-01): Carbon Monoxide In Cabin · Piper PA-28R-180, PA-28R-200, PA-28R-201 and 1 more. Effective Sep 12, 1980 - [AD 80-14-02](https://openairdocs.org/ad/80-14-02): Throttle Cable · Piper PA-28-181, PA-32-300 and PA-32R-300. Effective Jul 10, 1980 - [AD 80-14-03](https://openairdocs.org/ad/80-14-03): Bendix, King or Narco Transmitters · Piper PA-28-161, PA-28-181, PA-28-201T and 16 more. Effective Jul 1, 1980 - [AD 79-26-05](https://openairdocs.org/ad/79-26-05): Oil and Fuel System Hoses · Piper PA-28-140, PA-28-150, PA-28-151 and 28 more. Effective Jan 3, 1980 - [AD 79-22-02](https://openairdocs.org/ad/79-22-02): Fuel Leakage · Piper PA-28-161, PA-28-181, PA-28-201T and 6 more. Effective Oct 26, 1979 - [AD 69-22-02](https://openairdocs.org/ad/69-22-02): Failure of Control Wheel · Piper PA-28-140, PA-28-150, PA-28-160 and 4 more. Effective Jul 30, 1979 - [AD 79-13-03](https://openairdocs.org/ad/79-13-03): Fire Hazard Prevention · Piper PA-28-161, PA-28-181, PA-28-201T and 5 more. Effective Jun 8, 1979 - [AD 79-07-02](https://openairdocs.org/ad/79-07-02): Batteries · Aircraft Parts & Development A, A-2, A-3 and 149 more. Effective Apr 3, 1979 - [AD 79-02-05](https://openairdocs.org/ad/79-02-05): Fuel Flow · Piper PA-28-161, PA-28R-201 and PA-28R-201T. Effective Jan 29, 1979 - [AD 78-25-03](https://openairdocs.org/ad/78-25-03): Hose Assemblies · Piper PA-23-250, PA-28R-180, PA-28R-200 and 11 more. Effective Jan 15, 1979 - [AD 78-23-01](https://openairdocs.org/ad/78-23-01): Fuel Drain Assembly · Piper PA-28-235, PA-32-260, PA-32-300 and 4 more. Effective Nov 3, 1978 - [AD 77-23-03](https://openairdocs.org/ad/77-23-03): Rod End Bearings · Piper PA-28-140, PA-28-151, PA-28-161 and 12 more. Effective Nov 14, 1977 - [AD 77-12-01](https://openairdocs.org/ad/77-12-01): Fuel System · Piper PA-28-235, PA-32-260, PA-32-300 and 1 more. Effective Jun 10, 1977 - [AD 77-01-03](https://openairdocs.org/ad/77-01-03): Carburetor Air Filter Boxes · Piper PA-28-151. Effective Jan 14, 1977 - [AD 77-01-01](https://openairdocs.org/ad/77-01-01): Fuel Quantity Gauge · Piper PA-28-140, PA-28-150, PA-28-151 and 7 more. Effective Jan 7, 1977 - [AD 76-15-08](https://openairdocs.org/ad/76-15-08): Nose Gear Trunnion · Piper PA-28R-180, PA-28R-200 and PA-32R-300. Effective Sep 24, 1976 - [AD 76-18-04](https://openairdocs.org/ad/76-18-04): Fuel Valve · Piper PA-28-235, PA-32-260, PA-32-300 and 1 more. Effective Sep 10, 1976 All 91: https://openairdocs.org/tcds/2A13/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Piper PA-28-140](https://openairdocs.org/model/piper-pa-28-140): 4,259 aircraft (registry code 7102802) - [Piper PA-28-181](https://openairdocs.org/model/piper-pa-28-181): 3,549 aircraft (registry codes 7102807, 7102832) - [Piper PA-28-180](https://openairdocs.org/model/piper-pa-28-180): 3,504 aircraft (registry code 7102808) - [Piper PA-28-161](https://openairdocs.org/model/piper-pa-28-161): 1,526 aircraft (registry codes 7102803, 7102834) - [Piper PA-28R-200](https://openairdocs.org/model/piper-pa-28r-200): 1,223 aircraft (registry code 7102811) - [Piper PA-28-151](https://openairdocs.org/model/piper-pa-28-151): 961 aircraft (registry codes 7102805, 7104223) - [Piper PA-28-235](https://openairdocs.org/model/piper-pa-28-235): 859 aircraft (registry code 7102810) - [Piper PA-28R-180](https://openairdocs.org/model/piper-pa-28r-180): 536 aircraft (registry code 7102809) - [Piper PA-28-236](https://openairdocs.org/model/piper-pa-28-236): 480 aircraft (registry code 7102815) - [Piper PA-28R-201T](https://openairdocs.org/model/piper-pa-28r-201t): 368 aircraft (registry code 7102813) - [Piper PA-28R-201](https://openairdocs.org/model/piper-pa-28r-201): 352 aircraft (registry codes 7102816, 7102833) - [Piper PA-28RT-201T](https://openairdocs.org/model/piper-pa-28rt-201t): 255 aircraft (registry code 7102817) - [Piper PA-28-160](https://openairdocs.org/model/piper-pa-28-160): 253 aircraft (registry code 7102806) - [Piper PA-28RT-201](https://openairdocs.org/model/piper-pa-28rt-201): 178 aircraft (registry code 7102818) - [Piper PA-28-150](https://openairdocs.org/model/piper-pa-28-150): 123 aircraft (registry code 7102804) - [Piper PA-28-201T](https://openairdocs.org/model/piper-pa-28-201t): 62 aircraft (registry code 7102819) - [New Piper PA-28-181](https://openairdocs.org/model/new-piper-pa-28-181): 16 aircraft (registry code 7103201) - [New Piper PA-28-161](https://openairdocs.org/model/new-piper-pa-28-161): 15 aircraft (registry code 7103200) - [Piper PA-28S-180](https://openairdocs.org/model/piper-pa-28s-180): 1 aircraft (registry code 7102814) - [Piper/Valdes-Ervin PA-28-235](https://openairdocs.org/model/piper-valdes-ervin-pa-28-235): 1 aircraft (registry code 7102820) - [New Piper PA-28R-201](https://openairdocs.org/model/new-piper-pa-28r-201): 0 aircraft (registry code 7103203) - [Piper / Beaumont PA-28-140](https://openairdocs.org/model/piper-beaumont-pa-28-140): 0 aircraft (registry code 7102822) - [Piper PA-28S-160](https://openairdocs.org/model/piper-pa-28s-160): 0 aircraft (registry code 7102812) - [Piper/Anderson PA 28-180](https://openairdocs.org/model/piper-anderson-pa-28-180): 0 aircraft (registry code 7102821) - [Piper/Flores Richard PA 28-181](https://openairdocs.org/model/piper-flores-richard-pa-28-181): 0 aircraft (registry code 7102823) - [Piper/Miller PA-28-140](https://openairdocs.org/model/piper-miller-pa-28-140): 0 aircraft (registry code 7102800) ## STCs approved under this data sheet (651, first 50) - [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of existing instrument panel lights dimmer control.. TCW Technologies, LLC - [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC - [STC SA12428CH](https://openairdocs.org/stc/SA12428CH): Installation of the Lycoming Engines Electronic Ignition System (EIS). Lycoming Engines, An Operating Division of AVCO Corporation - [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 SA02661LA](https://openairdocs.org/stc/SA02661LA): Installation to enlarge the existing main landing gear over-wing access hole in the upper wing skin. M2 Aviation Soultions LLC - [STC SA01147WI](https://openairdocs.org/stc/SA01147WI): Installation of Concorde FLA or VRSLA series batteries in Piper Light Airplanes.. Concorde Battery Corporation - [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 SA04463NY](https://openairdocs.org/stc/SA04463NY): Installation of MT-Propeller Entwicklung GmbH model MTV-9-B/198-52( ) 3-blade, constant speed propeller and spinner. MT- Propeller Entwicklung GmbH - [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc. - [STC SA01866WI](https://openairdocs.org/stc/SA01866WI): Installation of Garmin GFC 500 Autopilot with Electronic Stability and Protection. Garmin International Inc. - [STC SA04075CH](https://openairdocs.org/stc/SA04075CH): Installation of Dynon EFIS-D10A EAA sales kit part number 102778-000. Dynon Avionics Inc. - [STC SA01005DE](https://openairdocs.org/stc/SA01005DE): Installation of a EarthX ETX900-TSO Lithium battery. EarthX Inc. - [STC SA12195SE](https://openairdocs.org/stc/SA12195SE): Installation of Absolute Solutions LLC Gear Warning System Upgrade. Absolute Solutions LLC - [STC SA12181IB](https://openairdocs.org/stc/SA12181IB): Installation of the MT-Propeller Entwicklung GmbH model MTV-12-D/188-53() propeller. MT-Propeller Entwicklung GmbH - [STC SA00081NY](https://openairdocs.org/stc/SA00081NY): Installation of Iceman Aviation Supplies, Inc. Carburetor Ice Detector.. Alcor LLC - [STC SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC - [STC SA02168AT](https://openairdocs.org/stc/SA02168AT): Modification of engine exhaust system for improved engine performance by installation of a Laminar Flow System Extractor Exhaust System.. Power Flow Systems Inc. - [STC SA316SO](https://openairdocs.org/stc/SA316SO): Carburetor ice detector.. LegacySTC.com - [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc. - [STC SA04046CH PAGE 2](https://openairdocs.org/stc/SA04046CH%20PAGE%202): Installation of L-3 GENESIS (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc. - [STC SA00037WI](https://openairdocs.org/stc/SA00037WI): Installation of B & C Specialty Products BC100-1 battery.. B & C Specialty Products Inc - [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 SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC - [STC SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation - [STC SA01941LA](https://openairdocs.org/stc/SA01941LA): Installation of stabilizer trim handle and cabin door handle. McFarlane Aviation LLC - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc. - [STC SA02532AT](https://openairdocs.org/stc/SA02532AT): Installation of subject Michelin tires on appropriate aircraft. For Michelin 5, 6, 8, and 10-inch rim diameter tires on General Aviation Aircraft.. Michelin North America Inc. - [STC SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc. - [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 SA00720CH](https://openairdocs.org/stc/SA00720CH): Installation of McCauley Propeller Model B3D36C431/80VSA-1.. McCauley Propeller Systems - [STC SA04400NY](https://openairdocs.org/stc/SA04400NY): Installation of the Integrated Back-up Battery System (IBBS). TCW Technologies LLC - [STC SA01435LA](https://openairdocs.org/stc/SA01435LA): Installation of engines modified with Firewall Forward Technologies LLC modified camshaft. Centri-Lube Technologies LLC - [STC SA04192NY](https://openairdocs.org/stc/SA04192NY): KFD 900 Primary Flight Display System Additional Functions. Honeywell International 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 - [STC SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC - [STC SA224CE](https://openairdocs.org/stc/SA224CE): Installation of Model A3000 main skis and NB-1200 nose skis.. F.Atlee Dodge Aircraft Services - [STC SA319CE](https://openairdocs.org/stc/SA319CE): Installation of Wipaire Skis Inc. Model 2500 (Aircraft Skis) (FluiDyne) Wheel skis. F.Atlee Dodge Aircraft Services - [STC SA00060AT](https://openairdocs.org/stc/SA00060AT): Installation of flap gap seals.. Whelen Aerospace Technologies All 651: https://openairdocs.org/tcds/2A13/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.