Airplane Flight Manual
Piper PA-25 Pawnee · Flight Manual
Overview
This document is the Airplane Flight Manual (AFM) for the Piper PA-25 Pawnee. It serves as a comprehensive guide for pilots operating this agricultural aircraft, detailing essential information regarding its performance, limitations, and operational procedures. The manual is designed to ensure safe and efficient flight operations, providing critical data such as weight and balance, fuel requirements, and emergency procedures. It is an essential resource for both experienced and novice pilots who need to familiarize themselves with the specific characteristics and handling of the PA-25 Pawnee.
- Maximum takeoff weight: 2,500 lbs
- Cruise speed: 90 knots
- Stall speed: 60 knots
- Rate of climb: 800 feet per minute
- Fuel capacity: 50 gallons (48 gallons usable)
Document
Source
Originally published by www.soarcsa.org. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Flight Manual
- Pages
- 9
- File size
- 4.2 MB
- Publisher
- www.soarcsa.org
Specifications & performance
Extracted from this document.
Specifications
- Engine (hp)
- 150
- Propeller
- McCauley 1A170-GM
- Engine model
- Lycoming O-320-A1A
- Max speed (kt)
- 118
- Fuel capacity (gal)
- 40
- Max takeoff weight (lb)
- 2,300
V-speeds
- VFE
- 83
- VNE
- 118
- VNO
- 94
Weight & balance
- Max takeoff weight (lb)
- 2,300
Common. Rarer than 24% of the aircraft models we track.
Most owners only have the POH. Here's the essential set for the Piper PA-25 Pawnee.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
Free — save the PIPER PA-25 Pawnee to your watchlist and track it in one place.
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In this document
Aircraft Specifications
The Piper PA-25 Pawnee is equipped with a Lycoming O-540 engine, producing 260 horsepower. The aircraft has a maximum takeoff weight of 2,500 lbs and a useful load of approximately 1,200 lbs. The wingspan measures 35 feet, and the length is 24 feet 6 inches.
Performance Data
The PA-25 Pawnee has a stall speed of 60 knots and a maximum cruise speed of 90 knots. The rate of climb is approximately 800 feet per minute at sea level. The aircraft has a range of about 400 nautical miles with full fuel.
Weight and Balance
Pilots must ensure that the aircraft is within the specified weight limits before flight. The center of gravity must be within the limits outlined in the manual to maintain proper handling characteristics.
Emergency Procedures
In the event of an engine failure, pilots should follow the emergency landing procedures outlined in this section. Key steps include maintaining control of the aircraft, selecting a suitable landing area, and executing a controlled descent.
Fuel Requirements
The PA-25 Pawnee requires 100LL aviation gasoline. The fuel capacity is 50 gallons, with 48 gallons usable. Pilots should always check fuel levels before flight to ensure adequate supply.
Safety notes
- Ensure weight and balance are within limits before flight.
- Follow emergency procedures in case of engine failure.
Full document text
DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 2A8 Revision 23 LAVIA S.A. PA-25 PA-25-235 PA-25-260 July 14, 2021 TYPE CERTIFICATE DATA SHEET 2A8 This data sheet which is part of Type Certificate No. 2A8 prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations and Federal Aviation Regulations. Type Certificate Holder Type Certificate Record of Name Change LAVIA ARGENTINA S.A. (LAVIASA) Avenida Colon 412, P.B. Dpto B C.P. 5500, Mendoza Repubblica Argentina LATINOAMERICANA DE AVIACION (LAVIA S.A.) changed its trade name to to LAVIA ARGENTINA S.A. (LAVIASA) on February 29, 2008 (TC reissued March 25, 2008) I.- Model PA-25, 1 PCLM (Normal Category), Approved January 6, 1959. Engine Fuel Engine Limits Propeller and Propeller Limits Lycoming O-320-A1A, O-320-A2A with carburetor setting 10-3678-11 or Lycoming O-320-A2B with carburetor setting 10-3678-32. 80/87 minimum grade aviation gasoline For all operations, 2700 r.p.m. (150 hp.) McCauley 1A170-GM or Sensenich M74DM Static r.p.m. at maximum permissible throttle setting: Not over 2575 r.p.m., not under 2475 r.p.m. No additional tolerance permitted. Diameter: Not over 74 inches, not under 72.5 inches Spinner required: Piper Drawing No. 14422 Airspeed Limits (CAS) Vne Never exceed 136 mph (118 knots) √no Maximum structural cruising 108 mph (94 knots) Vn Maneuvering 107.5 mph (93 knots) Vfe Flaps extended 95 mph (83 knots) Center Gravity Range (+11.70) to (+15.25) at 2300 lb. (+9.98) to (+15.25) at Straight line variation between points given. 1600 lb. or less Empty Weight Center of Gravity Range None Datum Leading edge of wing Leveling Means Top longerons in cockpit bay Page No. Rev. No. 32 22 12 4 58 22 20 20 20 20 62 7 8 20 20 23 2A8 Page 2 of 8 Maximum Weight No. of Seats Maximum Cargo Fuel Capacity 2300 lb. 1 at (+59) 800 lb. at (+14) 40 gallons at (-14.9) (one fuselage tank) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (-47) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing Flaps Down 57° Aileron Up 23° Down 23° Elevator Up 28° Rudder Right 25° Down 15° Left 25° Manufacturer's Serial Numbers 25-1 through 25-731 II. - Model PA-25-235, 1 PCLM (Normal Category), Approved October 12, 1962. Engine Fuel Engine Limits Lycoming O-540-B2B5 or O-540-B2C5 with carburetor setting #10-4404-1 80/87 minimum grade aviation gasoline For all operations, 2575 r.p.m. (235 hp.) Propeller and Propeller Limits 1. 2. McCauley 1A200-FA (Eligible on S/N 25-02; 25-2000 through 25-5521; 25-7305522 through 25-8156024; and LA-235-99501 and up) Static r.p.m. at maximum permissible throttle setting: Not over 2350 r.p.m., not under 2250 r.p.m. No additional tolerance permitted. Diameter: Not over 84 inches, not under 82.3 inches Spinner required: Piper Drawing No. 64336. McCauley 1P235-AFA (Eligible on S/N 25-02, and 25-2000 through 25-4171): Static r.p.m. at maximum permissible throttle setting: Not over 2500 r.p.m., not under 2400 r.p.m. No additional tolerance permitted. Diameter: Not over 84 inches, not under 82.3 inches Spinner required: Piper Drawing No. 14422 Airspeed Limits (CAS) V Never exceed ne 156 mph (135 knots) V. no Maximum structural cruising 124 mph (108 knots) Vn Maneuvering 120 mph (104 knots) Vfe Flaps extended 109 mph (95 knots) Center Gravity Range (+88.4) to (+90.3) at 2900 lb. (+85.6) to (+90.3) at Straight line variation between points given. 1793 lb. or less Empty Weight Center of Gravity Range None 78 inches forward of leading edge of wing Datum Leveling Means Top longerons in cockpit bay Maximum Weight 2900 lb. Page 3 of 8 Number of Seats 1 at (+135) Maximum Cargo 1200 lb. at (+93) Fuel Capacity Oil Capacity Control Surface Movements For S/N 25-02, and 25-2000 through 25-3384: 42 gallons at (+63) (one fuselage tank) For S/N 25-3385 through 25-5521, and 25-7305522 through 25-7405572, and LA-235-99501 and up:: 38 gallons at (+63) (one fuselage tank) For S/N 25-7405573 through 25-8156024: 36 gallons at (+102) (two wing tanks) See NOTE 1 for data on system fuel. 12 quarts at (+30) (94 quarts usable) See NOTE 1 for data on system oil. Wing Flaps Down 57° Aileron Up 23° Down 23° Elevator Up 28° Down 15° Rudder Right 25° Left 25° Manufacturer's Serial No. 2A8 25-02; 25-2000 through 25-5521; and 25-7305522 through 25-8156024, produced by Piper Aircraft Corp.; LA-235-99501 and up produced by LAVIA S.A. See NOTE 5 for airworthiness certification eligibility in the United States. III. - Model PA-25-260, 1 PCLM (Normal Category Only), Approved April 19, 1967. Engine Fuel Engine Limits Lycoming O-540-G1A5 or O-540-G2A5 with carburetor setting #10-4404-1 100/130 minimum grade aviation gasoline For all operations, 2700 r.p.m. (260 hp.) Propeller and Propeller Limits 1. McCauley 1A200-FA 2. 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 84 inches, not under 82.3 inches Spinner required: Piper Drawing No. 64336 Hartzell constant speed model HC-C2YK-1()/8477-0 (Eligible on O-540-G1A5 engine only) Pitch setting at 30" station: High 32.0°, Low 11.8° Diameter: Not over 84.0 inches, not under 83.0 inches Governor assembly: Hartzell F-4-4() Spinner: None approved 3. McCauley constant speed model B2D34C16-()/84 HF-0 (Eligible on O-540-G1A5 engine only) Pitch setting at 30" station: High 27.0°, Low 11.0° Diameter: Not over 84.0 inches, not under 82.5 inches Governor assembly: McCauley C290D2()/T10 Spinner: None approved Airspeed Limits (CAS) V. Never exceed 156 mph (135 knots) ne V. Maximum structural cruising 124 mph (108 knots) no Vn Maneuvering 120 mph (104 knots) Vfe Flaps extended 109 mph (95 knots) Center Gravity Range (+88.4) to (+90.3) at (+85.6) to (+90.3) at 2900 lb. 1793 lb. or less Straight line variation between points given. 2A8 Page 4 of 8 Datum Leveling Means Maximum Weight
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Empty Weight Center of Gravity Range None 78 inch forward of leading edge of wing Top longerons in cockpit bay 2900 lb. Number of Seats 1 at (+135) Maximum Cargo 1200 lb. at (+93) Fuel Capacity For S/N 25-4415 through 25-5521, and 25-7305522 through 25-7405572 and LA-260-98001, LA-260-99002, LA-260-99003, LA-260-99005 and up: 38 gallons at (+63) (one fuselage tank) For S/N 25-7405573 through 25-8156024: 36 gallons at (+102) (two wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 12 quarts at (+30) (94 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing Flaps Aileron Elevator Rudder Down 57° Up 23° Down 23° Up 28° Down 15° Right 25° Left 25° Manufacturer's Serial Numbers 25-4415 through 25-5521, and 25-7305522 through 25-8156024, produced by Piper Aircraft; LA-260-98001, LA-260-99002, LA-260-99003, LA-260-99005 and up, produced by LAVIA S.A. See NOTE 5 for airworthiness certification eligibility in the United States. DATA PERTINENT TO ALL MODELS Certification Basis Production Basis Equipment CAR 3 effective May 15, 1956, Amendment 3-1, April 1, 1957. Type Certificate No. 2A8 issued January 5, 1959. Date of Application for Type Certificate May 28, 1957. For aircraft models PA-25-235 S/N LA-235-99501 and up, and PA-25-260 S/N LA-260-98001, LA-260-99002, LA-260-99003, LA-260-99005 and up, production under type certificate only. The basic required equipment prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. FAA Approved Airplane Flight Manual: (a) Issue dated May 20, 1959, required for S/N 25-1 and 25-2. (b) Issue dated July 9, 1959, revised February 23, 1960, for S/N 25-3 through 25-1999. (c) Issue dated October 12, 1962, including Revision No. 1, dated November 20, 1962, for Model PA-25-235, S/N 25-02, and 25-2000 through 25-2761. (d) Issue dated October 12, 1962, including Revision No. 1, dated November 20, 1962, and No. 2 dated July 20, 1964, for Model PA-25-235, S/N 25-2762 through 25-2985. (e) Issue dated October 12, 1962, including Revision No. 1, 2, 3 and 4 for Model PA-25-235, S/N 25-2986 through 25-3384. (f) Issue dated October 12, 1962, including Revision Nos. 1, 2, 3, 4, and 5 for Model PA-25-235, S/N 25-3385 through 25-4171. Equipment, continued Page 5 of 8 2A8 NOTE 1 2. 1. FAA Approved Flight Manual, continued (g) Issue dated October 12, 1962, including Revisions Nos. 1, 2, 3, 4, 5, 6, 7, 8, 9 and 10 for Model PA-25-235, S/N 25-4172 through 25-5521, and 25-7305522 through 25-7405572 and LA-235-99501 and up. (h) Issue dated April 19, 1967, including Revision No. 1 required for Model PA-25-260, S/N 25-4415 through 25-5521, and 25-7305522 through 25-7405572 and LA-260-98001, LA-260-99002, LA-260-99003, LA-260- 99005 and up. (i) Issue dated February 7, 1974, required for Models PA-25-235 and PA-25-260, S/N 25-7405573 through 25-8156024. Stall warning indictor device per Piper Drawing Nos. 61093 and 61128 on PA-25, S/N 25-3 through 25-1999; Piper Drawing Nos. 64031 and 64253 on PA-25-235, S/N 25-02, and 25-2000 through 25-4171; Piper Drawing Nos. 64031 and 64884 on PA-25-235, S/N 25-4172 through 25-4414, and on PA-25-235 or PA-25-260, S/N 25-4415 through 25-5521 and 25-7305522 through 25-8156024; LA-235-99501 and up; LA-260-98001, LA-260- 99002, LA-260-99003, LA-260-99005 and up. Current weight and balance report, including list of equipment included in certificated empty weight and loading instructions when necessary, must be provided for each aircraft at time of original certification. The certificated empty weight and the corresponding center of gravity locations must include undrainable system oil (not included in oil capacity) and unusable fuel as noted below: Model PA-25: Fuel Oil 14 lb. 3.2 lb. at (-23) at (-47) Model PA-25-235, S/N 25-02, 25-2000 through 25-3384: Fuel Oil 18 lb. 5.2 lb. at (+55) at (+30) Model PA-25-235, S/N 25-3385 through 25-5521, and 25-7305522 through 25-7405572; LA-235-99501 and up: Fuel Oil 12 lb. 5.2 lb. t (+55) at (+30) Model PA-25-260, S/N 25-4415 through 25-5521, and 25-7305522 through 25-7405572; LA-260-98001, LA-260-99002, LA-260-99003, LA-260-99005 and up Fuel 12 lb. at (+55) Oil 5.2 lb. at (+30) Models PA-25-235 and PA-25-260, 25-7405573 through 25-8156024: Fuel Oil 15 lb. 5.2 lb. at (+110) at (+30) NOTE 2. The following placards must be displayed: (a) In front and in clear view of the pilot: (1) On Model PA-25, S/N 25-1 through 25-1999: "THIS AIRPLANE MUST BE OPERATED IN THE NORMAL CATEGORY IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUAL. ACROBATIC MANEUVERS (INCLUDING SPINS) PROHIBITED. FOR RESTRICTED CATEGORY OPERATION, REFER TO ADDITIONAL LIMITATIONS." 2A8 NOTE 2(a)(2), continued Page 6 of 8 (2) On Model PA-25-235, S/N 25-02, 25-2000 through 25-2761: "THIS AIRPLANE MUST BE OPERATED IN THE RESTRICTED CATEGORY IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS AND MARKINGS. ACROBATIC MANEUVERS (INCLUDING SPINS) PROHIBITED." (2) On Model PA-25-235, S/N 25-02, 25-2000 through 25-2761, continued Model PA-25-235, S/N 25-02 and 25-2000 through 25-2761 are also eligible for Multiple Airworthiness Certification when all placards are revised to the configuration of S/N 25-2762 through 25-5521, and 25-7305522 through 26-8156024. Airplane Flight Manual equipment Item 1(d) required in lieu of Item 1(c). (3) On Model PA-25-235, S/N 25-2762 through 25-4414; on Model PA-25-235 or PA-25-260, S/N 25-4415 through 25-5521, and 25-7305522 through 25-8156024; LA-235-99501 and up and LA-260-98001, LA-260-99002, LA-260-99003, LA-260-99005 and up: "THIS AIRPLANE MUST BE OPERATED IN THE RESTRICTED CATEGORY IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS AND MARKINGS. ACROBATIC MANEUVERS (INCLUDING SPINS) PROHIBITED. FOR NORMAL CATEGORY OPERATION, REFER TO FLIGHT MANUAL." (b) On hopper: Model PA-25 "800 lb. maximum" Model PA-25-235 "1200 lb. maximum" Model PA-25-260 "1200 lb. maximum" (c) Models PA-25-235 and PA-25-260 - On check list above instrument panel: "WINDOWS CLOSED" (d) Model PA-25-235, S/N 25-2762 through 25-4414; and LA-235-99501 and up and Model PA-25-235 or PA-25-260, S/N 25-4415 through 25-5521, and 25-7305522 through 25-8156024 and Model PA-25- 260, S/N LA260-98001, LA-260-99002, LA-260-99003, LA-260-99005 and up - On the instrument panel in full view of the pilot: "ROUGH AIR OR MANEUVERING SPEED 120 M.P.H." (e) On safety panel above instrument panel in full view of pilot: (1)Model PA-25-235, S/N 25-02, 25-2000 through 25-3384: "UNUSABLE FUEL 3 GALLONS. WHEN FUEL QUANTITY INDICATOR READS ZERO, FUEL REMAINING IN TANK CANNOT BE USED SAFELY IN FLIGHT." (2)Model PA-25-235, S/N 25-3385 through 25-4414 and LA-235-99501 and up; Model PA-25-235 or PA-25-260, S/N 25-4415 through 25-5521, and 25-7305522 through 25-7405572; and Model PA-25-260, S/N LA-260-98001 and up: "UNUSABLE FUEL 2 GALLONS. WHEN FUEL QUANTITY INDICATOR READS ZERO, FUEL REMAINING IN TANK CANNOT BE USED SAFELY IN FLIGHT." (3)Model PA-25-235 or PA-25-260, S/N 25-7405573 through 25-8156024: "UNUSABLE FUEL 2.5 GALLONS. WHEN FUEL QUANTITY INDICATOR READS ZERO, FUEL REMAINING IN TANK CANNOT BE USED SAFELY IN FLIGHT." (f) On Models PA-25-235 and PA-25-260 - On instrument panel in clear view of the pilot: "NO SMOKING" (g) On Model PA-25-235, S/N 25-2762 through 25-4414; and Model PA-25-235 or PA-25-260, S/N 25-4415 through 25-5521, and 25-7305522 through 25-8156024 - In front and in clear view of the pilot: "STALL WARNING SYSTEM INOPERATIVE WHEN MASTER SWITCH IS OFF." (h) On Models PA-25-235 and PA-25-260, S/N 25-7405573 through 25-8156024 - Above and near the fuel quantity gauge: "FUEL CAPACITY 36 GALLONS" Page 7 of 8 2A8 NOTE 3. NOTE 4. NOTE 5 (i) On Models PA-25-235 and PA-25-260, S/N 25-7405573 through 25-8156024 - Adjacent to low fuel level light on auxiliary instrument panel: "LOW FUEL WARNING" The Model PA-25, S/N 25-2 through 25-1999 (Restricted Category) is the same as the Normal Category PA-25 except for installation of spray or dust dispensing equipment. Conversion to duster or sprayer configuration may be accomplished using Piper Instructions, Section XVI of Report 1019. When operating in the Restricted Category, FAA Type Certificate Data Sheet No. 2A10 will apply. (a)Model PA-25-235, S/N 25-2000 through 25-2761 are eligible for Multiple Airworthiness Certification when all placards are revised to the configuration of S/N 25-2762 through 25-5521, and 25-7305522 through 25-8156024. Airplane Flight Manual equipment Item 1(d) required in lieu of Item 1(c). (b)Model PA-25-235, S/N 25-2762 through 25-2985 are eligible for Multiple Airworthiness Certification in the Restricted Category and Normal Category in accordance with CAR 8.21 and Conversion Instructions, Section XVI of Piper Report VB-7, Revision No. 2, dated October 5, 1964. When operating in the Restricted Category, Type Certificate Data Sheet No. 2A10 shall apply. When operating in the Normal Category, Type Certificate Data Sheet No. 2A8 shall apply. (c)Model PA-25-235, S/N 25-2986 through 25-4414 and Model PA-25-235 or PA-25-260, S/N 25-4415 through 25-5521, and 25-7305522 through 25-8156024 are eligible for Multiple Airworthiness Certification in the Restricted Category and Normal Category in accordance with CAR 8.21 and Conversion Instructions, Section III of Piper Report VB-42, Revision No. 6, dated February 22, 1967. When operating in the Restricted Category, Type Certificate Data Sheet No. 2A10 shall apply. When operating in the Normal Category, Type Certificate Data Sheet No. 2A8 shall apply. The following S/N are not eligible for Airworthiness Certification in the United States: 25-4894, 25-5027, 25-5030, 25-5033, 25-5057, 25-5066, 25-5069, 25-5072, 25-5075, 25-5097, 25-5100, 25-5102, 25-5106, 25-5269, 25-5271, 25-5273, 25-5275, 25-5284 through 25-5293, 25-5315, 25-5316, 25-5318, 25-5320, 25-5454, 25-5455, 25-5456, 25-5457, 25-7305528, 25-7305530, 25-7305532, 25-7405591, 25-7405596, 25-7405613, 25-7405620, 25-7405631, 25-7405642, 25-7405652, 25-7405658, 25-7405662, 25-7405672, 25-7405679, 25-7405686, 25-7405690, 25-7405692, 25-7405694, 25-7405696, 25-7405698, 25-7405701, 25-7405704, 25-7405705, 25-7405706, 25-7405708, 25-7405714, 25-7405716, 25-7556030, 25-7556035, 25-7556040, 25-7556045, 25-7556050, 25-7556052, 25-7556057, 25-7556062, 25-7556065, 25-7556067, 25-7556069, 25-7556071, 25-7556073, 25-7556075, 25-7556077, 25-7556080, 25-7556090, 25-7556095, 25-7556100, 25-7556105, 25-7556110, 25-7556115, 25-7556120, 25-7556125, 25-7556135, 25-7556140, 25-7556145, 25-7556150, 25-7556153, 25-7556159, 25-7556162, 25-7556166, 25-7556226, 25-7556227, 25-7556228, 25-7556229, 25-7556230, 25-7556231, 25-7556232, 25-7556233, 25-7656078, 25-7656091, 25-7756072 through 25-7756081, 25-7756087 through 25-7756095, 25-7856001 through 25-7856004, 25-7856006, 25-7856008, 25-7856010, 25-7856012, 25-7856016, 25-7856018, 25-7856020, 25-7856022, 25-7856032, 25-7856034, 25-7856036, 25-7856038, 25-7856043, 25-7856045, 25-7856047, 25-7856049, 25-7856055, 25-7856057, 25-7856063, 25-7856065, 25-7856066, 25-7856067, 25-7856069, 25-7856071, 25-7956004, 25-7956006, 25-7956009 through 25-7956012, 25-7956014, 25-7956016, 25-7956019, 25-7956020, 25-7956022, 25-7956025, 25-7956027, 25-7956029, 25-7956031, 25-7956033, 25-7956036, 25-7956038, 25-7956041, 25-7956042, 25-8056004, 25-8056005, 25-8056008, 25-8056009, 25-8056011, 25-8056013, 25-8056016, 25-8056018, 25-8056021, 25-8056022, 25-8056026, 25-8056028, 25-8056041, 25-8056043, 25-8056046, and 25-8056048. 2A8 Page 8 of 8 NOTE 6: Import Requirements: (a) United States airworthiness certificate may be issued on the basis of Argentina Certificate of Airworthiness for Export signed by a representative of Direción Nacional de Aeronavegabilidad containing the following statement: "The aircraft conforms to its U. S. type design (Type Certificate No 2A8) and is in a condition for safe operation." (b) The U. S. airworthiness certification basis for aircraft type certificated under 14 CFR Part 21 section 21.29 and exported by the country of manufacture is section 21.183(c) or 21.185(c). (c) The U. S. airworthiness certification basis for aircraft type certificated under 14 CFR Part 21 section 21.29 and exported from countries other than the country of manufacture (e.g., third part country) is section 21.183(d) or 21.185(b). Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. ...END.....