# TCDS A31EU: Vulcanair S.p.A. - Type: Type certificate data sheet - Status: Current - Holder: Vulcanair S.p.A. - Revision: 28 - Revised: July 22, 2021 - Product: Aircraft, Small Airplane - Certification basis: Part 23, Part 36 - Registered aircraft: 52, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/b4/60/b460dd1c3bf379d62b00c0d07ee38bbef9c2e0800a8e5d401fc17b1e2ae441fb - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/F577B06475DEC8CF8625871E004D61E9.0001 - Page: https://openairdocs.org/tcds/A31EU ## Models (10) As the data sheet lists them. - P.68C-TC - P.68 Observer 2 - P.68B - P.68 Observer - P.68TC Observer - AP68TP-600 Viator - P.68R - P.68 - P.68C - AP68TP-300 Spartacus ## 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 19 20 21 22 Rev. No. 28 18 22 18 18 13 26 22 26 26 22 22 22 22 25 28 22 22 22 25 27 27 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A31EU Revision 28 Vulcanair S.p.A. P.68 P.68B P.68C P.68C-TC P.68 "OBSERVER" AP68TP-300 "SPARTACUS" P.68TC "OBSERVER" AP68TP-600 "VIATOR" P.68 "OBSERVER 2" P.68R July 22, 2021 TYPE CERTIFICATE DATA SHEET A31EU This data sheet which is a part of Type Certificate No. A31EU 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. Vulcanair S.p.A. Via G. Pascoli, 7 80026 Casoria (Naples), Italy Type Certificate Holder Record Partenavia Costruzioni Aeronautiche S.p.A. Naples, Italy (TC A31EU transferred to Vulcanair) I. Model P.68 (Normal Category), Approved December 7, 1971. Engines. Two Lycoming IO-360-A1B or Two Lycoming IO-360-A1B6 Fuel. 100/130 Minimum grade aviation gasoline Engine Limits. For all operations 2,700 r.p.m. (200HP) (See NOTE 2(C)) Propeller and Propeller Limits. Two Hartzell HC-C2YK-2C/C7666A-4 or Two Hartzell HC-C2YK-2C( ) F/FC7666A-4 Diameter 72 in. (No reduction permitted). Pitch setting at 30 in. station Low 14.2º ± 0.2º, High 81.2º ± 0.3º Governor: Hartzell Model F-6-3A or Woodward Model B210655 or L210844 on left engine and C210655 or R210844 on right engine Spinner: Hartzell Model 836-29 Airspeed Limits (CAS). Never exceed 187.5 knots Maximum structural cruising 149 knots Maneuvering 122 knots Flaps extended (35º) 99 knots Minimum single engine control speed 60 knots (See NOTE 4) A31EU 2 C.G. Range. (+12.8 in.) to (+20.7 in.) at 4100 lb. (+10.2 in.) to (+20.7 in.) at 3310 lb. and less Straight line variation between points. (See NOTE 4) Empty Weight C.G. Range. None. Minimum Crew. 1 pilot. Maximum Weight. 4100 lb. (See NOTE 4) Number of Seats. 6 (2 at - 31.5 in.), (2 at - 2.8 in.), (2 at 34.2 in.) (See NOTE 5) Maximum Baggage. 400 lb. (55.6 in.) Fuel Capacity. 108 gal. total (2 wing tanks 54 gal. each at +30.3) 2.5 gal. unusable per tank (See NOTE 6). Oil Capacity. 16 qt. total (8 qt. in each engine at +4.0) See NOTE 1 for data on unusable fuel and undrainable oil. II. Model P.68B (Normal Category), Approved August 16, 1974. Engines. Two Lycoming IO-360-A1B or Two Lycoming IO-360-A1B6 Fuel. 100/130 Minimum grade aviation gasoline. Engine Limits. For all operations 2,700 r.p.m. (200HP) (See NOTE 2(C)). Propeller and Propeller Limits. Two Hartzell HC-C2YK-2C( )F/FC7666A-4 Diameter 72 in. (No reduction permitted). Pitch setting at 30 in. station: Low 14.2º ± 0.2º , High 81.2º ± 0.3º Governor: Hartzell Model F-6-3A Woodward Model B210655 or L210844 on left engine and C210655 or R210844 on right engine Spinner: Hartzell Model 836-29 Airspeed Limits (CAS). Never exceed 193 kts Max. structural cruise 153 kts Maneuvering 125 kts Flaps extended (35º) 99 kts Min. Single Engine Speed 60 kts C.G. Range. (+12.8 in.) to (+20.7 in.) at 4321 lb. (+10.2 in.) to (+20.7 in.) at 3527 lb. and less. Straight line variation between points. Minimum Crew. 1 pilot. Maximum Weight. 4321 lb. Maximum Landing Weight. 4100 lb. Number of Seats. 6 - (2 at - 37.4 in.), (2 at - 5.7 in.) (2 at + 34.2 in.), (See NOTE 5) Maximum Baggage. 400 lb (at + 60.7 in.) 3 A31EU Fuel Capacity. 108 gal. total (2 wing tanks 54 gal. each at + 30.2 in.) (2.5 gal. unusable per tank) (See NOTE 6). Oil Capacity. 16 qt. total (8 qt. each engine at + 4.0 in.) See NOTE 1 for data on unusable fuel and undrainable oil. III. Model P.68C (Normal Category), Approved July 24, 1980. The model P 68C is same as P 68B except for: 1) fuselage nose change for weather radar installation; 2) hydraulic shock absorber on nose landing gear; 3) modified fuel tanks and increased capacity; and 4) weight & C.G. range increase. Engines. Two Lycoming IO-360-A1B6. Fuel. 100/130 Minimum grade aviation gasoline. Engine Limits. For all operations 2,700 r.p.m. (200 HP) Propeller and Propeller Limits. Two Hartzell HC-C2YK-2C ( ) F/FC7666A-4 Diameter 72 in. (no reduction permitted). Pitch setting at 30 in. station: Low 14.2º ± 0.2º, High 81.2º ± 0.3º Governor: Woodward Model B210655 or ( ) 210844 Spinner: Hartzell Model 836-29 Airspeed Limits (CAS). Never exceed 193 knots (See NOTE 14) Max. structural cruise 153 knots Maneuvering 126 knots Flap extended - VFE (35º) 99 knots Min. single engine speed 60 knots C.G. Range. (+11.81 in.) to (+20.7 in.) at 4387 lb. (See NOTE 14) (+ 9.06 in.) to (+20.7 in.) at 3703 lb. and less Straight line variation between points. Minimum Crew. 1 pilot. Maximum Weight. (See NOTE 14) 4387 lb. Maximum Landing Weight. 4167 lb. (See NOTE 14) Number of Seats. 7 - (2 at -37.4 in.), (2 at -5.7 in.), (3 at +34.2 in.) (See NOTE 5). Maximum Baggage. 400 lb. (at +60.7 in.) Fuel Capacity. A. For S/N 209: 108 gal. total (2 wing tanks 54 gal. each at +30.2 in.) (See NOTE 15) (2.5 gal. unusable per tank) (See NOTE 6). B. As of S/N 210: 142 gal. total (2 wing tanks 71 gal. each at 30.2 in. 2.5 gal. unusable per tank). See NOTE 1. Oil Capacity. 16 qt. total (8 qt. each engine at +4.0 in.) See NOTE 1 for data on unusable fuel and undrainable oil. A31EU 4 IV. Model P.68C-TC (Normal Category), Approved September 10, 1982. The model P 68C-TC is same as P 68C except for: 1) turbocharged engines; 2) modified cabin heating system; and 3) all metal wing leading edge. Engines. Two Lycoming TO-360-C1A6D or Two Lycoming TIO-360-C1A6D Engine Mixed not approved. Fuel. 100/or 100LL Minimum grade aviation gasoline. Engine Limits. (See NOTE 8) For all operations 2,575 r.p.m., 42 in. Hg (210 HP) (For TO-360-C1A6D) or 2,575 r.p.m., 44 in. Hg (210 HP) (For TIO-360-C1A6D) Propeller and Propeller Limits. Two Hartzell HC-C2YK-2C( )F/FC7666A-0 Diameter 76 in. max, 75 in. min. Pitch setting at 30 in. station: Low 15º30' (± 10'), High 81º (± 30') Governor: Woodward Model A210655 or ( ) 210844 Spinner: Hartzell Model 836-29 Airspeed Limits (CAS). Never exceed 193 Knots Max. structural cruise 153 Knots Maneuvering 126 Knots Flap extended - VFE (35°) 99 Knots Min. single engine control speed 63 Knots Altitude Limits. Max. operating altitude: 20,000 ft C.G. Range. (+11.81 in.) to (+20.7 in.) at 4387 lb. (+ 9.06 in.) to (+20.7 in.) at 3703 lb. and less. Straight line variation between points. Minimum Crew. 1 pilot. Maximum Ramp Weight. 4442 lb. Maximum Weight. 4387 lb. Maximum Landing Weight. 4167 lb. Number of Seats. 7 - (2 at -37.4 in.), (2 at -5.7 in.), (3 at +34.2 in.). Maximum Baggage. 400 lb. (at +60.7 in.). Fuel Capacity. 142 gal. total (2 wing tanks 71 gal. each at 30.2 in., 2.5 gal. unusable fuel per tank) (See NOTE 9). Oil Capacity. 16 qt. total (8 qt. each engine at +4.0 in. See NOTE 1 for data on un usable fuel and undrainable oil). V. Model P.68 "OBSERVER" (Normal Category) approved November 3, 1982. The model P 68 "OBSERVER" is ame as P 68B except for: 1) plexiglass fuselage nose, 2) steel truss for nose landing gear attachment, 3) new instrument panel, 4) control system, and 5) increased fuel capacity. 5 A31EU Engines. Two Lycoming IO-360-A1B6 Fuel. 100/130 minimum grade aviation gasoline. Engine Limits. For all operations 2,700 r.p.m. (200 HP). Propeller and Propeller Limits. Two Hartzell HC-C2YK-2C( )F/FC7666A-4 Diameter 72 in. (No reduction permitted). Pitch setting at 30 in. station: Low 14.2º ± 0.2º, High 81.2º ± 0.3º Governor: Woodward Model B210655 or ( ) 210844 Spinner: Hartzell Model 836-29 Airspeed Limits (CAS). Never exceed 193 Kts (See NOTE 13) Max. structural cruise 153 Kts Maneuvering 125 Kts Flap extended (35º) 99 Kts Min. Single Engine Speed 60 Kts C.G. Range. (+12.8 in.) to (+20.7 in.) at 4321 lb. (See NOTE 13) (+10.2 in.) to (+20.7 in.) at 3527 lb. and less. Straight line variation between points. Minimum Crew. 1 pilot. Maximum Weight. (See NOTE 13) 4321 lb. Maximum Landing Weight. 4100 lb. (See NOTE 13) Number of Seats. 7 - (2 at -37.4 in.), (2 at -5.7 in.), (3 at +34.2 in.) Maximum Baggage. 400 lb. (at +60.7 in.) Fuel Capacity. 142 gal. total (2 wing tanks 71 gal. each at +30.2 in.) (See NOTE 15) (2.5 gal. unusable per tank.) Oil Capacity. 16 qt. total (8 qt. each engine at +4.0 in.) See NOTE 1 for data on unusable fuel and undrainable oil. VI. Model AP68TP series 300 Spartacus (Normal Category), Approved May 23, 1984. Engines. 2 Detroit Diesel Allison 250B17C Fuel. Conforming to specification: MIL-T-5624 JP4, JP5, ASTM D-1655, JET B ASTM D-1655, JET A or A1, JP1 relating to ASTM D-1655A Diesel n.1, relating ASTM D-1655, JETA Emergency: MIL-G-5572C, all grades W/O (TCP) Oil. Conforming to specification: MIL-L-7808G and MIL-L-23699B Engine Limits. Take-off and M.C.P. Power: 328 SHP Max. T.O.T.: 810ºC Propeller: 2030 RPM A31EU 6 Propeller and Propeller Limits. a) 2 Hartzell full feathering, reversing, three blades Model HC-B3TF-7A/T10173F-21R Diameter: MAX 80" (2.032 m) MIN 78" (1.981 m) Pitch setting at 30 in. sta. (0.762 m): LOW = 8º ± .5º HIGH = 85º ± 1º REVERSE = -11º ± .5º b) Woodward hydraulic governor, model 8210-018 c) Hartzell spinner, model A-3640 Airspeed Limit (CAS) Maximum operating speed: VMO = 197 Kts (up to 15.000 ft) VMO = 160 Kts (at 25.000 ft) Straight line variation between these points Maneuvering: VA = 143 Kts Flap extended (full) VFE = 119 Kts Minimum single engine speed VMC = 80 Kts Datum. Wing leading edge Leveling Means. Longitudinal lower frame of left rear cabin window. C.G. Range. (+14.64) to (+21.06") at 5732 lbs (+12.20) to (+21.06") at 4850 lbs and less straight line variation between points given. Empty Weight C.G. Range. None. Maximum Weight. Ramp: 5787 lbs Take-off: 5732 lbs Landing: 5445 lbs Zero fuel: 5300 lbs Minimum Crew. 1 pilot Number of Seats. 9 See loading instruction for passenger loading Maximum Baggage. 220 lbs at 100.40" (2.550 m) Fuel Capacity. Total 848 lt (224 U.S. Gals) TANK CAP. GALS ARM L.&R. WING 101 e a + 30.31 L.&R. NACELLE 11 e a + 34.25 Unusable fuel: 1 US GALS each side (See NOTE 1) Oil Capacity. Total 12 qts (11.4 lt) 6 Qts each engine at - 15.75" (-400 m) (See Note 1) Maximum Operating Altitude Limit. 25,000 ft 7 A31EU VII. Model P.68TC OBSERVER (Normal Category) approved September 30, 1985 The model P68TC Observer is same as P68 Observer except for: (1) turbocharged engines; (2) modified cabin heating system; and (3) all-metal wing leading edge. Engines. Two Lycoming TIO 360-C1A6D Fuel. 100 or 100LL Min. grade aviation Gasoline. Engine Limits. (See Note 8) For all operation: 2575 r.p.m., 44 in. Hg (210 HP) Propeller and Two Hartzell HC-C2YK-2C( )F/FC7666A-0 Propeller Limits. Diameter 76 in. max. 75 in. min. Pitch setting at 30 in. station: - low 15.5º ± .10º - high 81º ± .30º Governor: Woodward Model A210655 or A210844 Spinner: Hartzell Model 836-29 a/c modified as per MOD.OBTC/01 Airspeed Limits (CAS). Never Exceed 193 Knots 194 Knots Max. Structural Cruise 153 Knots 154 Knots Maneuvering 125 Knots 132 Knots Flap Extended (35º) 99 Knots 103 Knots Min. Single Engine Control Speed 63 Knots 64 Knots Altitude Limits. Max. Operating Altitude: 20,000 ft. C.G. Range. (+12.8 in.) to (+20.7 in.) at 4321 lb. (+10.2 in.) to (+20.7 in.) at 3527 lb. and less. Straight li ne variation between points. (a/c modified as per MOD.OBTC/01) (+13.71 inc.) to (+18.92 inc.) at 4594 lb. (+10.25 inc.) to (+18.92 inc.) at 3527 lb. and less Straight line variation betwwen points. Minimum Crew. 1 pilot. Maximum Takeoff Weight. 4321 lb. 4594 lb. a/c modified as per MOD. OBTC/01 Maximum Landing Weight. 4100 lb. 4365 lb. a/c modified as per MOD. OBTC/01 Number of Seats. 7 - (2 at -37.4 in.), (2 at -5.7 in.), (3 at +34.2 in.). (a/c modified as per MOD. OBTC/01) 6 - (2 at -37.4 in.), (2 at -5.7 in.), (2 at +34.2 in.). Maximum Baggage. 400 lb. (at +60.7 in.). Fuel Capacity. 142 US Gals total (2 wing tanks 71 gals. each at 30.2 in.) 2.5 gal unusable fuel per tank. See NOTE 9 and 6. Oil Capacity. 16 qts total (8 qts each engine at +4.0 in.). See Note 1 for data on unusable fuel and undrainable oil. A31EU 8 VIII. Model AP68TP-600 Viator (Normal Category), approved December 19, 1986. Engines. 2 Detroit Diesel Allison 250 B17C Fuel. Conforming to specification: MIL-T-5624 JP4, JP5, ASTM D-1655, JET B ASTM D-1655, JET A or A1, JP1 relating to ASTM D-1655A Diesel N.1, relating ASTM D-1655, JET A Emergency: MIL-G-5572c, all grades W/d (TCP) Oil. Conforming to specification: MIL-L-7808G and MIL-L-236998 Engine Limits. Take-off and M.C.P. Power: 328 SHP Max T.O.T.: 810ºC Propeller: 2030 RPM Propeller and Propeller Limits. a) 2 Hartzell full feathering, reversing, three blades Model HC-B3TF-7A/T10173T-21R Diameter: Max 80" (2.032 m) Min 78" (1.981 m) Pitch setting at 30 in. sta. (0.762 m): LOW = 8 deg +/- 0.5 HIGH = 85 deg +/- 1.0 REVERSE " -11 deg +/- 0.5 b) Woodward hydraulic governor, model 8210-018 c) Hartzell spinner, model A-3640 Airspeed Limit. Maximum operating speed: VMO = 200 kts (Up to 15000 ft) (See NOTE 20) VMO = 164 kts (at 25000 ft) Straight line variation between these points Maneuvering: VA = 157 kts Flap extended (full) VFE = 131 kts Gear Operation VLO = 150 kts Gear Extended VLE = 150 kts Minimum single engine VMC = 78 kts Datum. Wing leading edge Leveling Means. Longitudinal lower frame of left rear cabin window C.G. Range. ( + 14.65 ) to ( + 21.36 ) at 6283 lbs (See NOTE 20) ( + 9.58 ) to ( + 21.36 ) at 4740 lbs and less, straight line variation between points given. Empty Weight C.G. Range. None Maximum Weight. Ramp: 6338 lb (See NOTE 20) Take-off: 6283 lb Landing: 6283 lb Zero Fuel: 5622 lb Minimum Crew. 1 pilot Maximum Baggage. 440 lbs at 110.63" (2.810 m) 9 A31EU Fuel Capacity. Total 848 lt (224 U.S. Gals.) TANK CAP. GALS ARM L. & R. WING 101 ea. + 30.31 L. & R. NACELLE 11 ea. + 34.25 Unusable Fuel: 1 U.S. Gals each side (See NOTE 1) Oil Capacity. Total 12 qts (11.4 lt) 6 qts each engine at - 15.75" (- .400 m) (See note 1) Maximum Operating Altitude. 25000 ft IX. Model P.68 OBSERVER 2 (Normal Category), approved July 1, 1993. The model P68 Observer 2 is the same as model P68 Observer except for : a. New instrument panel b. 100 Amps alternator installation c. Up turned wing tips d. Strengthened leafspring e. Oversized main wheel f. Nose wheel steering disengagement g. Increased maximum take off and landing weight (See NOTE 11) Engine. Two Lycoming IO-360-A1B6 Fuel. 100/130 Minimum Grade Aviation Gasoline Engine Limits. For all operations 2700 rpm (200 HP) Propeller and Propeller Limits. Two Hartzell HC-C2YK-2( )F/FC7666A-4 Diameter 72 inc. (No reduction permitted) Pitch setting at 30 inc. station: Low 14.2° ± 0.2° , High 81.2° ± 0.3° Governor: Woodward Models: B210655 or L210844 on left engine and C210655 or R210844 on right engine. Spinner: Hartzell Model 836-29 Airspeed Limits (CAS). Never exceed 194 kts Max. structural cruise 154 kts Maneuvering 132 kts Flap extended (35°) 103 kts Min. Single Engine Speed 58 kts C.G. Range. (+13.71 inc.) to (+18.92 inc.) at 4594 lb. (+10.25 inc.) to (+18.92 inc.) at 3527 lb. and less. Straight line variation between points. Minimum Crew. 1 pilot Maximum Weight. Ramp Weight; 4630 lb. - Maximum Take Off Weight; 4594 lb. Maximum Landing Weight. 4365 lb. A31EU 10 Zero Fuel Weight. 4167 lb. Maximum Baggage. 400 lb. (at +60.7 inc.) Fuel Capacity. 142 gal. total (2 wing tanks 71 gal. at 30.2 inc.) (2.5 gal .unusable per tank) (see NOTE 12) Oil Capacity. 16 qt. total (8 qt. each engine at +4.0 inc.) See NOTE 1 for data on unusable fuel and undrainable oil. X. Model P.68R (Normal Category), Approved February 19, 2014 The model P.68R is derived by P.68B, featuring a retractable landing gear. Engines. Two Lycoming IO-360-A1B6 Fuel. 100 or 100LL Minimum grade aviation gasoline. Engine Limits. For all operations 2700 rpm (200 HP) Propeller and Propeller Limits. Two Hartzell HC-C2YK-2C( )F/FC7666A-4 Diameter 72 in. (no reduction permitted). Pitch setting at 30 inc. station: Low 14.2° ± 0.2° , High 81.2° ± 0.3° Governor: Woodward Models: B210655 or L210844 on left engine and C210655 or R210844 on right engine, or MT-Propeller Model: P-881-30 on left engine and P-881-31 on right engine. Spinner: Hartzell Model 836-29 Airspeed Limits (CAS). Never exceed 193 kts (See NOTE 18) Max. structural cruise 153 kts Maneuvering 125 kts Flap extended - VFE (35º) 99 kts Min. single engine speed 60 kts Max. landing gear extended VLE 131 kts Max. landing gear operating (extension) 131 kts Max. landing gear operating (retraction) 112 kts C.G. Range. (+12.8 in.) to (+20.7 in.) at 4321 lb. (See NOTE 18) (+10.2 in.) to (+20.7 in.) at 3527 lb. and less Straight line variation between points. Minimum Crew. 1 pilot. Maximum Weight. 4321 lb. (See NOTE 18) Maximum Landing Weight. 4321 lb. (See NOTE 18) Number of Seats. 7 - (2 at -37.4 in.), (2 at -5.7 in.), (3 at +34.2 in.) Maximum Baggage. 400 lb. (at +60.7 in.) Fuel Capacity. 142 gal. total (2 wing tanks 71 gal. at 30.2 inc.) (See NOTE 19) (2.5 gal .unusable per tank) 11 A31EU Oil Capacity. 16 qt. total (8 qt. each engine at +4.0 in.) See NOTE 1 for data on unusable fuel and undrainable oil. DATA PERTINENT TO ALL MODELS Datum. Wing leading edge. Leveling Means. Longitudinal lower frame of left rear cabin window. Control Surface Movements. For Models P.68, P.68B, P.68C, P.68C-TC, P.68 "Observer", (See NOTE 20) P.68TC "Observer", P.68 "Observer" 2 and P.68R. Wing flaps Down 35º ± 2° Aileron Up 30° ± 2° Down 17° ± 2° Stabilator L.E. Up 6° ± 2° Down 16° ± 2° Stabilator Tab (with respect to stabilator chord) Down 1° ± 1° Down 15° ± 1° Rudder Right 25° ± 2° Left 25° ± 2° Rudder tab Right 30° ± 2° Left 30° ± 2° For Models AP68TP-300 Spartacus and AP68TP-600 Viator (up to s/n 9004) Wing flaps Down 35° ± 2° Aileron Up 30° ± 2° Down 17° ± 2° Aileron Tab (with aileron neutral) Up 19° ± 2° Down 19° ± 2° Rudder Right 25° ± 2° Left 25° ± 2° Rudder tab Right 20° ± 2° Left 20° ± 2° Elevator Up 26° ± 1° Down 12° ± 1° Elevator Trim Tab (with elevator neutral) Up 10° ± 1° Down 39° ± 1° Serial Numbers Eligible. Each individual aircraft manufactured under this type certificate must be accompanied by an Export Certificate of Airworthiness as noted below under "Import Requirements" when an application for a U.S. airworthiness certificate is made. Model P.68 Observer 2: 384-01-OB2 and subsequent. Model P.68R: 458/R and subsequent. Certification Basis. For Model P.68: FAR 21.17 FAR 23 effective February 1, 1965, including Amendments 23-1 through 23-6. For Models P.68B, P.68 "OBSERVER", and P.68C: FAR 23 effective February 1, 1965, including Amendments 23-1 through 23-6, and FAR 36 effective December 1, 1969, including Amendments 36-1 through 36-9. For Model P.68C-TC, and P.68TC "Observer": FAR 23 effective February 1, 1965, including Amendments 23-1 through 23-6, and 14 CFR Section Amendment Number 23.909 23-7 23.1043 23-7 23.1047 23-7 23.1143 23-7 23.1305 23-7 23.1527 23-7 23.1583 23-7 FAR 36 effective December 1, 1969, including amendments 36-1 through 36-12. A31EU 12 Partenavia Costruzioni Aeronautiche S.p.A. elected to demonstrate compliance, for the Model P 68C-TC and P68TC "Observer", with Subparts E, F (except FAR 23.1309), and G of FAR 23 as amended by Amendment 23-18. Date of application for Type Certificate: January 22, 1969 for P68C-TC; April 30, 1985 for P68TC "Observer". Type Certificate No. A31EU issued December 7, 1971. Amended August 16, 1974, July 24, 1980, September 10, 1982, November 3, 1982, September 30, 1985. For Model P.68TC "Observer" embodies modification No. MOD.OBTC/01. FAR 23 effective February 1/1965, as amended through 23-6 effective August 1, 1967 and: 23.909, 23.1043, 23.1047, 23.1143, 23.1305, 23.1527, 23.1583 as amended through 23-7 and 23.507, 23.509 as amended through 23 -14 effective December 20, 1973, 23.2 and 23.561(b)(2) as amended through 23 -36 effective September 14/1988; 23.629 is amended through 23-31, effective December 28, 1984; 23.1322 as amended through 23-17 effective February 1, 1977; 23.1321(a) as amended by Equivalent Level of Safety, 23.1401 Amd. 20. FAR 36 effective December 1/1969, as amended through 36-16. ICAO/Annex 16, Chapter 10. For Model AP68TP Series 300 "SPARTACUS" FAR 23 effective Feb. 1, 1965 including Amendments 23-1 through 23-6, and 23.45 (23-21) 23.853 (23-25) 23.1145 (23-18) 23.49 (23-21) 23.859 (23-27) 23.1155 (23-7) 23.51 (23-21) 23.901 (23-18) 23.1163 (23-14) 23.65 (23-21) 23.903 (23-26) 23.1165 (23-17) 23.67 (23-21) 23.905 (23-26) 23.1182 (23-14) 23.75 (23-21) 23.929 (23-14) 23.1183 (23-15) 23.77 (23-21) 23.937 (23-7) 23.1189 (23-14) 23.141 (23-17) 23.939 (23-18) 23.1203 (23-18) 23.143 (23-17) 23.943 (23-18) 23.1301 (23-20) 23.145 (23-17) 23.951 (23-15) 23.1303 (23-17) 23.149 (23-21) 23.955 (23-7) 23.1305 (23-26) 23.153 (23-14) 23.959 (23-18) 23.1307 (23-23) 23.155 (23-14) 23.977 (23-17) 23.1323 (23-20) 23.157 (23-14) 23.991 (23-26) 23.1337 (23-18) 23.161 (23-21) 23.1013 (23-15) 23.1501 (23-21) 23.173 (23-14) 23.1015 (23-15) 23.1505 (23-7) 23.175 (23-17) 23.1017 (23-14) 23.1521 (23-21) 23.177 (23-21) 23.1019 (23-15) 23.1527 (23-7) 23.181 (23-21) 23.1027 (23-14) 23.1529 (23-26) 23.201 (23-14) 23.1041 (23-7) 23.1541 (23-21) 23.203 (23-14) 23.1043 (23-21) 23.1545 (23-23) 23.205 (23-14) 23.1045 (23-7) 23.1547 (23-20) 23.207 (23-7) 23.1091 (23-7) 23.1549 (23-28) 23.253 (23-26) 23.1093 (23-18) 23.1555 (23-21) 23.335 (23-7) 23.1103 (23-7) 23.1557 (23-23) 23.361 (23-26) 23.1111 (23-17) 23.1581 (23-21) 23.367 (23-7) 23.1121 (23-18) 23.1583 (23-23) 23.371 (23-26) 23.1125 (23-17) 23.1585 (23-23) 23.629 (23-7) 23.1141 (23-18) 23.1587 (23-21) 23.629 (e)(23-23) 23.1143 (23-17) 23.777 (23-7) SFAR 27, effective Feb. 1, 1974, included Amendments 27-1 through 27-4, and FAR 36 effective Dec. 1, 1965, included Amendments 36-1 through 36-12. Date of application for Type Certification: July 20, 1981. Amended Type Certificate issued : May 23, 1984. 13 A31EU For Model AP68TP-600 "VIATOR" FAR 23 effective February 1, 1965 including amendments 23-1 through 23-6, and 23.2 (23-32) 23.726 (23-27) 23.1145 (23-18) 23.3 (23-28) 23.727 (23-7) 23.1155 (23-7) 23.9 (23-17) 23.729 (23-26) 23.1163 (23-14) 23.45 (23-21) 23.733 (23-17) 23.1165 (23-17) 23.49 (23-21) 23.735 (23-34) 23.1182 (23-14) 23.51 (23-21) 23.777 (23-7) 23.1183 (23-15) 23.65 (23-21) 23.785(g) (23-32) 23.1189 (23-14) 23.67 (23-21) 23.785(h) (23-32) 23.1203 (23-18) 23.75 (23-21) 23.853 (23-25) 23.1301 (23-20) 23.77 (23-21) 23.859 (23-27) 23.1303 (23-17) 23.141 (23-17) 23.901 (23-18) 23.1305 (23-26) 23.143 (23-17) 23.903 (23-26) 23.1307 (23-23) 23.145 (23-17) 23.905 (23-26) 23.1323 (23-20) 23.149 (23-21) 23.929 (23-14) 23.1337 (23-18) 23.153 (23-14) 23.937 (23-7) 23.1435 (23-14) 23.155 (23-14) 23.939 (23-18) 23.1501 (23-21) 23.157 (23-14) 23.943 (23-18) 23.1505 (23-7) 23.16 (23-21) 23.951 (23-15) 23.1521 (23-21) 23.173 (23-14) 23.955 (23-7) 23.1527 (23-26) 23.175 (23-17) 23.959 (23-18) 23.1529 (23-26) 23.177 (23-21) 23.977 (23-17) 23.1541 (23-21) 23.181 (23-21) 23.991 (23-26) 23.1545 (23-23) 23.201 (23-14) 23.1013 (23-15) 23.1547 (23-20) 23.203 (23-14) 23.1015 (23-15) 23.1549 (23-28) 23.205 (23-14) 23.1017 (23-14) 23.1555 (23-21) 23.207 (23-7) 23.1019 (23-15) 23.1557 (23-23) 23.253 (23-26) 23.1027 (23-14) 23.1581 (23-21) 23.335 (23-7) 23.1401 (23-7) 23.1583 (23-23) 23.361 (23-26) 23.1043 (23-21) 23.1585 (23-23) 23.367 (23-7) 23.1045 (23-7) 23.1587 (23-31) 23.371 (23-26) 23.1091 (23-7) 23.479 (23-17) 23.1093 (23-18) 23.507 (23-14) 23.1103 (23-7) 23.509 (23-14) 23.1111 (23-17) 23.629 (23-23) 23.1121 (23-18) 23.723 (23-23) 23.1125 (23-17) 23.725 (23-7) 23.1141 (23-18) 23.1143 (23-17) SFAR 27, effective Feb. 1, 1974, included amendment 27-1 through 27-4, and FAR 36 effective Dec. 1, 1965, included amendments 36-1 through 36-12. Date of application for Type Certificate: July 29, 1986. Date amended type certificate issued: December 19, 1986. For Model P.68 "Observer" 2. FAR 23 effective February 1, 1965, as amended through 23-6 effective August 1, 1967; and, 23.507, 23.509 as amended through 23 -14 effective December 20, 1973; 23.2 and 23.561(b)(2) as amended through 23-36 effective September 14, 1988; 23.629 as amended through 23-31 effective December 28, 1984; 23.1322 as amended through 23-17 effective February 1, 1977; 23.1401 as amended through 23-20 effective September 1, 1977; and 23.1321(a) as amended by an Equivalent Level of Safety. FAR 36 effective December 1, 1969, as amended through 36-18. The Ente Nazionale per l’Aviazione Civile (ENAC) originally type certificated this aircraft under its Type Certificate Number A365. Effective September 28, A31EU 14 2003, the European Aviation Safety Agency (EASA) be gan oversight of this product under their Type certificate Number A 365 on behalf of Italy. For Model P.68R FAR 23 effective Feb. 1, 1965 including Amendments 23-1 through 23-6, plus Amendment 23-7 for 23.561, and Amendment 23-14 for 23.507. Requirements elected to comply: Amendment 23-7 for 23.725, 23.727, 23.729, 23.735, 23.1435, and Amendment 23-14 for 23.867 FAR 36 effective Dec. 1, 1965, included Amendments 36-1 through 36-28 Equivalent Level of Safety: 14 CFR part 23, § 23.807(a)(4), Amdt. 23-49 (ref. EASA CRI D-02 issue 3 dated 21 August 2007 “Crew door upgrading to emergency door resulting from emergency window removal”) 14 CFR part 23, § 23.783(b), Amdt. 23-6 (ref. EASA CRI D-01 issue 2 dated 18 January 2007 “P.68R crew door installation”) The following list provides specific certification basis requirements for the model P68R: S-TEC 55X autopilot Amendment 23-18, §§ 23.1301, 23.1309, 23.1321, 23.1329, 23.1357, 23.1365, 23.1367, 23.1381, 23.1431. Amendment 23 -45 (JAR 23 effective 11 March 1994), §§ 23.29, 23.143, 23.253, 23.601, 23.603, 23.605, 23.607, 23.609, 23.685, 23.689, 23.1529, 23.1581, 23.1583, 23.1585, 23.1589. Amendment 23 - 49: § 23.1359 Extension from Standard Range configuration to Long Range Configuration Amendment 23-7, §§ 23.471, 23.473, 23.477, 23.479, 23.483, 23.485, 23.493. Amendment 23-45 (JAR 23 effective 11 March 1994), §§ 23.601, 23.603, 23.605, 23.609, 23.611, 23.951, 23.959, 23.963, 23.964, 23.967, 23.969, 23.971, 23.975, 23.993, 23.1501, 23.1581, 23.1585 VLE / VLO increase Amendment 23-17, § 23.1309. Amendment 23-45 (JAR 23 effective 11 March 1994), §§ 23.25, 23.29, 23.141, 23.143, 23.601, 23.603, 23.605, 23.607, 23.609, 23.611, 23.1301, 23.1322, 23.1501, 23.1529, 23.1541, 23.1563, 23.1583, 23.1585 MTOW increase up to 4548 lb (2063 kg) 14 CFR, part 36 effective December 1,1969 including Amendments 36-1 through 36-28. Amendment 23-17, §§ 23.572, 23.1323. Amendment 23-45 (JAR 23 effective 11 March 1994), §§ 23.29, 23.143, 23.253, 23.1301, 23.1311, 23.1321, 23.1501, 23.1525, 23.1529, 23.1541, 23.1543, 23.1545, 23.1549, 23.1559, 23.1581, 23.1583, 23.1585, 23.1589 Fixed oxygen system kit installation Amendment 23-9, § 23.1449. Amendment 23-17, § 23.1309. Amendment 23-36, § 23.561. Amendment 23-43, §§ 23.1441, 23.1443, 23.1445. Amendment 23-45 (JAR 23 effective 11 March 1994), §§ 23.601, 23.603, 23.605, 23.625, 23.1357, 23.1367, 23.1501, 23.1529, 23.1541, 23.1581, 23.1583, 23.1585. Amendment 23-49, §§ 23.1447, 23.1451, 23.1453 Landing gear emergency extension system, nitrogen reservoir replacement Amendment 23-14, § 23.1435. Amendment 23-17, § 23.1309. Amendment 23- 45 (JAR 23 effective 11 March 1994), §§ 23.1501, 23.1529. Amendment 23 -54 (JAR 23 effective 01 February 2001), §§ 23.601, 23.603, 23.605 Garmin G950 Avionics installation Amendment 23-7, § 23.1323. Amendment 23-17, § 23.1303. Amendment 23-51, §§23.25, 23.29, 23.601, 23.603, 23.605, 23.607, 23.609, 23.611, 23.613, 23.623, 23.625, 23.627, 23.771, 23.773, 23.777, 23.1301, 23.1309, 23.1311, 15 A31EU 23.1321, 23.1322, 23.1327, 23.1331, 23.1337, 23.1351, 23.1353, 23.1357, 23.1359, 23.1361, 23.1365, 23.1367, 23.1381, 23.1431, 23.1501, 23.1523, 23.1525, 23.1529, 23.1541, 23.1543, 23.1545, 23.1547, 23.1549, 23.1581, 23.1583, 23.1585, 23.1589. Amendment 23 -52, § 23.1305. Amendment 23-57, § 23.1308 Validation Basis. Type Certificate A31EU was issued pursuant to FAR 21.29 in validation of the Registro Aeronautico Italiano (RAI) certification of compliance with the aforementioned certification basis, and in accordance with the standard airworthiness certificate provisions of FAR 21.183(c). Note: The airworthiness provisions of FAR 21.183(d) may be cited as the basis for issuance of standard airworthiness certificates for aircraft imported from a country other than the country of manufacture. Equipment. The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for standard airworthiness certification. In addition, the following items of equipment are required: a) Pre-stall warning indicator, Safe Flight Instrument Corp., Type 164 or equivalent. b) Partenavia - "RAI approved aircraft Flight Manual": 1. Model P 68, dated December 7, 1971 (Document No. 97224/T) or later RAI approved revision, or, 2. Model P 68B, dated May 24, 1974 (Document No. 115.831T) or later RAI approved revision up to S/N 152. 3. Model P 68, maximum T.O. weight 4321 lb. F/M Suppl. C dated June 25, 1975 (Document No. 124.415/T) (See Note 4). 4. Model P 68B, S/N 153 and onward; new issue dated May 23, 1978 (Document No. 148.015/T) or later RAI-approved revision. 5. Model P 68C, dated July 23, 1979 (Document No. 158. 229/T Revision 3) or later RAI approved revision. 6. Models P 68 and P 68B, maximum takeoff weight 4387 lbs. and maximum landing weight 4167 when operated in accordance with AFM Appendix, dated March 23, 1979 (RAI approval No. 156.014/T). 7. a. Model P 68C-TC, dated April 29, 1980 (Document No. 164.503/T) or later RAI-approved revision. b. Model P 68C-TC dated 26 November 1983 (RAI approved No. 195867/T) or later RAI approved revision. 8. Model P 68 "OBSERVER" (RAI approval No. 165678/T), with Revision 1 (RAI approval No. 185817/T) or later RAI approved revision. 9. Model AP68TP Series 300 "SPARTACUS" dated Dec. 9, 1983 (RAI approval No. 196197/T) or later RAI approved revision. 10. Model P68TC "Observer", dated June 18, 1985 (RAI approved No. 210.866/T) or later RAI approved revision. 11. Model P68TC "Observer", Doc No. NOR 10.707-4A (S/N 400-04/OTC and subsequent) reissued August 8, 1994 (RAI approval No.94/2721/MAE) or later RAI approved revision. 12. Model AP68TP-600 "Viator" (RAI approval No. 250540/T for aircraft up to s/n 9004, and RAI approval No. 265727/SMCA for aircraft from s/n 9005 up to s/n 9010) or later RAI approved revision. 13. Model P68 Observer 2 dated November 30, 1989 (RAI approval No. 260429/SCMA) or later RAI approved revision. 14. Model P.68R dated February 2, 2009 (EASA approval No. EASA.A.A.01887) or later EASA approved revision. 15. Model AP68TP-600 "Viator" (EASA approval No. 10051648) or later EASA approved revision. Import requirements The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of the the Ente Nazio nale A31EU 16 per l’Aviazione Civile (ENAC) on behalf of the European Community. The Export C of A should contain the following statement “ Import requirements (cont.) The aircraft covered by this certificate has been examined, tested, and found to comply with EASA TC No. A.385 approved under U.S. Type Certificate No. A 31EU and to be in a condition for safe operation”. Country other than Manufacturer (U.S. bilateral agreement and the original Export Certificate of Airworthiness issued by the country of manufa cture must exist): A U.S. airworthiness certificate may be issued on the basis of a log book certifying statement endorsed by an authorized representative of the civil aviation authority of the exporting country. It is incumbent upon the exporting civil aviation authority to determine that the certifying statement includes evidence of acceptable service history and modification deviations and the following statement: "The aircraft covered by this certificate has been examined, tested, inspected in accordance with the provisions of FAR 21.183)d) or its equivalent, and found to conform to the type design approved under Type Certificate A31EU and is in a condition for safe operation". For issuance of an airworthiness certificate in accordance with 14 CFR Part 21.183(c), The Ente Nazionale per l’Aviazione Civile of Italy must certify that the airplane conforms to the type design and is in a condition for safe operation. The Ente Nazionale per l’Aviazione Civile of Italy will certify that the airplane complies with all applicable mandatory continuing airworthiness information (MCAI) it has issued. 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. Service Information Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 - by the Ente Nazionale per l’Aviazone Civile (ENAC) . (These approvals pertain to the design data only).” · Service Bulletins · Structural Repair Manuals · Vendor Manuals · Aircraft Flight Manuals, and · Overhaul and Maintenance Manuals The FAA accepts such documents and considers them FAA-approved unless one of the following condition exists: · The documents change the limitations, performance, or procedures of the FAA approved manuals; or · The documents make an acoustical or emissions changes to this product’s U.S.type certificate as defined in 14 CFR § 21.93. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case-by-case to EASA to approve on behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. NOTE 1. Current weight and balance report including list of equipment in certificated empty weight, and loading instructions, must be provided for each aircraft at the time of original airworthiness certification. All P68 models: the certificated empty weight and corresponding center of gravity location must include 17 A31EU undrainable oil (1.0 lb. at +4.0), and unusable fuel (30 lb. at +30.3). (See NOTE 6 and 16) AP68TP Series 300 "SPARTACUS" and AP68TP-600 "VIATOR": The certificated empty weight and corresponding center of gravity location must include undrainable oil (1.0 lbs at -15.75 inches) and unusable fuel (13.0 lbs at 34.25 inches). NOTE 2. a) The following placards must be displayed in full view of the pilot: "THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS". In addition, all placards required in the "RAI-approved Airplane Flight Manual" must be installed in the appropriate location. b) Each individual airplane must be equipped with a placard that specifies the kind of operation such as VFR, or IFR, DAY or NIGHT, to which the operation of the airplane is limited by the equipment installed. c) Avoid continuous operation between 2100 rpm and 2350 rpm (for IO-360-A1B engine only). NOTE 3. All the servic e life limits, overhaul limits, instructions for continued airworthiness, airworthiness limitations, special inspections and mandatory maintenance requirements that are published on Partenavia/Vulcanair Aircraft Maintenance Manuals have been approved by RA I in the ’80 and ’90 as shown below and are considered FAA approved: For P.68, P.68B, P.68C, P.68C -TC, P.68 Observer: RAI Approval No. 226.078/T dated 23 December 1986 – RAI Approval No. 94/1365/MAE dated 27 April 1994 – RAI Approval No. 99/2246/MAE dated 09 June 1999 For AP68TP-300 “Spartacus”: RAI Approval No. 285.158/MAE dated 11 December 1992 For P.68TC Observer : RAI Approval No. 95/4.295/MAE dated 18 December 1995 – RAI Approval No 99/2246/MAE dated 09 June 1999 For P.68 Observer 2 : RAI Approval No. 275962/SCMA dated 23 September 1991 - RAI Approval No. 94/1365/MAE dated 27 April 1994 – RAI Approval No. 99/2246/MAE dated 09 June 1999 For AP68TP-600 “Viator”: RAI Approval No. 224.168/T dated 16 October 1986 – EASA Approval dated April 2005 These airworthiness limitations may not be changed without FAA-approval. NOTE 4. The maximum T.O. weight can be increased up to 4321 lb., provided that Servi ce Bulletin No. 21 is applied. With the weight of 4321 lb., the airspeed limits are (CAS): Never exceed 193 Knots Maximum structural cruising 153 Knots Maneuvering 125 Knots Flaps extended (35°) 99 Knots Minimum single engine control speed 60 Knots and the C.G. range is: (+12.8 in.) to (+20.7 in.) at 4321 lb. (+10.2 in.) to (+20.7 in.) at 3527 lb. and less. Straight line variation between points. NOTE 5. The number of seats is 7 (3 passengers on bench-seat at +34.2 in.) for the airplane that incorporates the Service Bulletin Partenavia No. 29. NOTE 6. For the airplane equipped with integral auxiliary fuel wing tanks the fuel capacity is as follows: 153 gal. (2 main wing tanks 54 gal. each at +30.3 in. 2.5 gal. unusable per tank) 45.0 gal. (2 auxiliary wing tanks 22.5 each at +30.3 with 1 gal. unusable per tank). NOTE 7. For Model P.68 and P.68B equipped with Partenavia Kit P/N 68-015 the fuel capacity is: 142 gallons total (2 wing tanks 71 gallon each 30.2 in.) 2.5 gallon unusable per tank. A31EU 18 NOTE 8. For Model P.68C-TC and P.68TC "Observer", operation below 2,400 r.p.m. at manifold pressure above 36 in. Hg. is prohibited. NOTE 9. The P.68C-TC, S/N 208-01TC, is approved with standard and with auxiliary fuel tanks of Model P 68B. See NOTE 6 for total capacity and unusable fuel. NOTE 10. Crew doors for Models P.68C and P.68C-TC are approved when installed per RAI-approved Partenavia Drawing No. 2.2503. For the affected airplanes, the airplane Flight Manual must include the "Supplement I - Crew Door", RAI approval No. 199.649/T April 17, 1984. NOTE 11. The following optional equipment and systems are available: - bubble nose for weather radar installation. - wheel fairing - integral auxiliary fuel tank. - Oversized nose wheel with strengthened wheel fork. NOTE 12. For the airplane equipped with integral auxiliary fuel wing tanks the fuel capacity is as follows: 142 gal. (2 main wing tanks 71 gallons each at 30.2 inch 2.5 gal. Unusable per tank). 42 gal. (2 auxiliary wing tanks 21 gal. each at 30.2 inc. with 2 gal. Unusable per tank). NOTE 13. P.68 Observer aircraft models (S/N's through 383) equipped with Kit P/N 68/051 as per S.B. 79, can be operated with Increased Maximum Take-Off Weight of 4594 lbs and Maximum Landing Weight of 4365 lbs. For those modified aircraft, the Operating Limitations are changed as follows: Airspeed Limits (CAS). Never exceed 194 Kts Max. Structural Cruise 154 Kts Maneuvering 132 Kts Flaps extended: - 35º flaps 103 Kts Minimum single engine speed 58 Kts C.G. Range. Rearward Limits: - 18.92 in. (0,481 m) aft of Datum (31% MAC) at all weights. Forward Limits: - 13.81 in. (0,351 m) aft of Datum (22.45% MAC) at Ramp Weight of 4630 Lbs (2100 Kg). - 13.71 in. (0,348 m) aft of Datum (22.45% MAC) at Maximum Take-Off Weight of 4594 Lbs (2084 Kg). - 10.25 in. (0,260 m) aft of Datum (16.77% MAC) at 3527 Lbs (1600 Kg) or less with straight line variation between these points. Weight Limits. Max. Ramp Weight 4630 Lbs (2100 Kg) Max. Take-Off Weight 4594 Lbs (2084 Kg) Max. Landing Weight 4365 Lbs (1980 Kg) Max. Zero Fuel Weight 4167 Lbs (1890 Kg) For aircraft equipped with Kit P/N 68/051 as per S.B. 79, supplement N (RAI Approval No. 227.006/SCMA dated November 11, 1991) must be attached to the RAI Approved Flight Manual. NOTE 14. P.68C aircraft models equipped with Kit P/N 68/051 as per S.B. 79, can be operated with Increased Maximum Take-Off Weight of 4594 Lbs and Maximum Landing Weight of 4365 Lbs. For those modified aircraft, the Operating Limitations are changed as follows: Airspeed Limits (CAS). Never exceed 194 Kts Max. Structural Cruise 154 Kts Maneuvering 132 Kts Flaps extended: - 15º flaps 152 Kts - 35º flaps 103 Kts 19 A31EU Minimum single engine speed 60 Kts C.G. Range. Rearward Limits: - 18.92 in. (0,481 m) aft of Datum (31% MAC) at all weights. Forward Limits: - 12.80 in. (0,325 m) aft of Datum (20.97% MAC) at Ramp Weight of 4630 Lbs (2100 Kg). - 12.60 in. (0,320 m) aft of Datum (21.16% MAC) at Maximum Take-Off Weight of 4594 Lbs (2084 Kg). - 9.06 in. (0,230 m) aft of Datum (14.84% MAC) at 3704 Lbs (1680 Kg) or less with straight line variation between these points. Weight Limits. Max. Ramp Weight 4630 Lbs (2100 Kg) Max. Take-Off Weight 4594 Lbs (2084 Kg) Max. Landing Weight 4365 Lbs (1980 Kg) Max. Zero Fuel Weight 4167 Lbs (1890 Kg) For aircraft equipped with Kit P/N 68/051 as per S.B. 79, supplement N (RAI Approval No. 277.978/SCMA dated December 23, 1991) must be attached to the RAI Approved Flight Manual. NOTE 15. P.68 Observer (S/N's through 383) and P.68C aircraft models equipped with Kit P/N 68-050 as per S.B. 78, can be operated with optional Auxiliary Fuel Tank System to increase total fuel capacity to 184 US Gals (696 Lts) as detailed below: - 2 wing integral main fuel tanks of 71 US Gals (269 Lts) each at 30.3 in. (0,77 m). Unusable fuel = 2.4 US Gals (9 Lts) for each tank. - 2 wing integral auxiliary fuel tanks of 21 US Gals (79 Lts) each at 30.3 in. (0.77 m). Unusable fuel = 1 US Gals (4 Lts) for each tank. For aircraft equipped with optional Auxiliary Fuel Tank System, supplement L/1 (RAI Approval No. 227.006/SCMA dated November 11, 1991 for P68 Observer a/c model and RAI Approval No. 277.978/SCMA dated December 23, 1991 for P68C a/c model) must be attached to the RAI Approved Flight Manual. NOTE 16. P.68TC "Observer" aircraft models modified as per MOD.OBTC/01, can be operated with optional Auxiliary Fuel Tank System to increase total fuel capacity to 184 US Gals (696 Lts) as detailed below: - 2 wing integral main fuel tanks of 71 US Gals (269 Lts) each at 30.3 in. (0.77 m). Unusable fuel = 2.4 US Gals (9 Lts) for each tank. - 2 wing integral auxiliary fuel tanks of 21 US Gals (79 Lts) each at 30.3 in. (0.77 m). Unusable fuel = 1 US Gals (4 Lts) for each tank. For aircraft equipped with optional Auxiliary Fuel Tank System, supplement L (RAI Approval No. 94/2721/MAE dated August 8, 1994) must be attached to the RAI Approved Flight Manual. NOTE 17. P.68TC "Observer" models (S/N 400-04/OTC and subsequent) models modified per MOD.OBTC/02 Revision 1 are approved with a Cabin Forced Air Heating System Installation. A31EU 20 NOTE 18. P.68R aircraft modified as per MOD P68/151 or applying Vulcanair SB 198 are approved for a Maximum Take-Off Weight of 4548 lb. For those modified aircraft, the Operating Limitations are changed as follows: Airspeed Limits (CAS). Never exceed 197 kts Max. Structural Cruise 157 kts Maneuvering 127 kts Flap extended - VFE (35º) 101 kts Min. single engine speed 60 kts Max. landing gear extended VLE 131 kts Max. landing gear operating (extension) 131 kts Max. landing gear operating (retraction) 112 kts C.G. Range. (+13.54 in.) to (+20.7 in.) at 4548 lb. (+10.2 in.) to (+20.7 in.) at 3527 lb. and less Straight line variation between points. Weight Limits. Max. Take-Off Weight 4548 lb Max. Landing Weight 4321 lb Max. Zero Fuel Weight 4321 lb NOTE 19. P.68R aircraft models modified by Type Design Change No. MOD.P68/150, can be operated with optional Auxiliary Fuel Tank System to increase total fuel capacity to 184 US Gals (696 Lts) as detailed below: - 2 wing integral main fuel tanks of 71 US Gals (269 Lts) each at 30.3 in. (0,77 m). Unusable fuel = 2.4 US Gals (9 Lts) for each tank. - 2 wing integral auxiliary fuel tanks of 21 US Gals (79 Lts) each at 30.3 in. (0.77 m). Unusable fuel = 1 US Gals (4 Lts) for each tank. NOTE 20. AP68TP-600 Viator aircraft from s/n 9005 onwards are approved for a Maximum Take-Off Weight of 6614 lb. For those modified aircraft, the Operating Limitations and Technical Characteristics are changed as follows: Airspeed Limits (CAS). Maximum operating speed: VMO = 200 kts (up to 15000 ft) VMO = 164 kts (at 25000 ft) Straight line variation between these points Maneuvering: VA = 141 kts Flap extended (full) VFE = 131 kts Gear Operation VLO = 150 kts Gear Extended VLE = 150 kts Minimum single engine VMC = 79 kts C.G. Range. (+15.94 in.) to (+20.16 in.) at 6669 lb. (+15.75 in.) to (+20.16 in.) at 6614 lb. (+9.58 in.) to (+20.16 in.) at 4740 lb. and less Straight line variation between points. Weight Limits. Ramp: 6669 lb Take-off: 6614 lb Landing: 6283 lb Zero Fuel: 5622 lb Control Surface Movements. Wing flaps Down 35° ± 2° Aileron Up 30° ± 2° Down 17° ± 2° Aileron Tab (with aileron neutral) Up 24° ± 2° Down 17° ± 2° Rudder Right 25° ± 2° Left 25° ± 2° Rudder tab Right 20° ± 2° Left 20° ± 2° 21 A31EU Elevator Up 17° ± 1° Down 12° ± 1° Elevator Trim Tab (with elevator neutral) Up 15° ± 1° Down 39° ± 1° Noise requirements. FAR 36 effective Dec. 1, 1965, included Amendments 36-1 through 36-28 ICAO Annex 16, Chapter 10 NOTE 21. Approved major changes on Vulcanair P.68 are: Major Change, Level 1, Vulcanair MOD P68/123 – “Sagem Avionics Integrated Cockpit Installation IFR” Applicability: Vulcanair P.68C, P.68C-TC, P.68TC Observer, P.68 Observer 2 Major Change, Level 2, Vulcanair MOD P68/86 – “S-TEC 55X Autopilot Installation” Applicability: Vulcanair P68 Series Major Change, Level 1, Vulcanair MOD P68/240 – “Garmin 950 Avionics Installation” Applicability: Vulcanair P.68 Observer 2, P.68C, P.68C-TC, P.68TC Observer and P.68R Major Change, Level 2, Vulcanair MOD P68/302 – “Installation of MidContinent MD302 Standby Module and activation of TAWS-B and SVS on P.68 Series.” Applicability: Vulcanair P.68C, P.68C-TC and P.68R , SS/NN 469 onwards and SS/NN 458, 463, 465, 466 having incorporated Major Change, Level 1, Vulcanair MOD P68/240. Major Change, Level 1, Vulcanair MOD P68/266 – “Installation of Garmin G950 avionic system and replacement of existing autopilot with S-Tec 2100 model” Applicability: Vulcanair AP68TP-600 “Viator” Certification Basis: Amendment 23-17, § 23.143 Amendment 23-26, § 23.253 Amendment 23-51, §§ 23.25, 23.29, 23.301, 23.303, 23.305, 23.307, 23.395, 23.397, 23.405, 23.561, 23.601, 23.603, 23.605, 23.60 7, 23.609, 23.611, 23.613, 23.619, 23.623, 23.625, 23.627, 23.671, 23.677, 23.685, 23.689, 23.729, 23.771, 23.773, 23.777, 23.867, 23.963, 23.1301, 23.1303, 23.1309, 23.1311, 23.1321, 23.1322, 23.1323, 23.1325, 23.1327, 23.1329, 23.1331, 23.1335, 23.1337, 23.1351, 23.1353, 23.1357, 23.1359, 23.1361, 23.1365, 23.1367, 23.1381, 23.1431, 23.1501, 23.1523, 23.1525, 23.1529, 23.1541, 23.1543, 23.1545, 23.1547, 23.1549, 23.1553, 23.1555, 23.1581, 23.1583, 23.1585, 23.1589 Amendment 23-52, § 23.1305 Amendment 23-57, § 23.1308 Vulcanair MOD P68/328, Applicability Vulcanair S.p.A.P.68R, P68C, P68C -TC, P68TC Observer, P68 Observer 2. Installation of Garmin G1000Nxi avionic system With GFC700 autopilot installation. In addition to the P.68R (Victor), Certification Bas is, the following requirements are applicable at the noted amendment level: Amendment 23-17, § 23.1303 Amendment 23-45, §§ 23.685, 23.689 Amendment 23-51, §§ 23.25, 23.29, 23.601, 23.603, 23.605, 23.607, 23.609, 23.611, 23.613, 23.623, 23.625, 23.627, 2 3.771, 23.773, 23.777, 23.963, 23.1301,23.1305, 23.1311, 23.1321, 23.1322, 23.1327, 23.1331, 23.1337, 23.1351, 23.1353, 23.1357, 23.1359, 23.1361, 23.1365, 23.1367, 23.1381, 23.1431, 23.1501, 23.1523, 23.1525, 23.1529, 23.1541, 23.1543, 23.1545, 23.1547, 23.1549, 23.1581,23.1583, 23.1585, 23.1589 Amendment 23-57, § 23.1308 Amendment 23-61, § 23.1306 Amendment 23-49, § 23.1309 NOTE 22. Major Level 2 Change with approval for FAR23.1308 Amdt 57- “Mod P68/157- Replacing Crossbow AHRS 500 GA with Axitude AX1-200 in SAGEM glass cockpit installation (IFR) Applicability: Vulcanair S.p.A. P68C, P68C-TC, P68TC Observer, P68 Observer 2. A31EU 22 NOTE 23. P.68 Observer 2 and P.68TC Observer airplanes that install increased Maxium Zero Fuel Weight (MZFW) MOD.P68/288 per SB 155 Rev 2 (FAA project AT010066CE-A) must follow the new reduced wing safe life limit of 21,550 flight hours from the previous limit of 23,900 flight hours per FAA AD 2014-10-01. See FAA Global AMOC dated May 30, 2019 for details. Operators must follow AMM 10.702-2 Section 4 (ALS) Revision 2 dated August 31, 2016. This new wing safe life limit remains even if the airplane is later de-modified of MOD.P.68/288. This MZFW modification increases the Zero fuel weight from 4167 lbs. (1890 Kg) to 4336 lbs (1967 Kg) and the maximum number of seats from 6 (2 at -37.4 in.), (2 at -5.7 in.), (2 at +34.2 in.) to 7 (2 at - 37.4 in.), (2 at -5.7 in.), (3 at +34.2 in.). See SB 155 Rev 2 for the required AFM Supplements. NOTE 24. P.68R aircraft from s/n 508 onwards are equipped since new with Garmin G1000 NXi Integrated Flight Deck System and GFC700 Autopilot (as per Type Design Change No. MOD P68/328). NOTE 25. P.68C aircraft from s/n 511 onwards are equipped since new with Garmin G1000 NXi Integrated Flight Deck System and GFC700 Autopilot (as per Type Design Change No. MOD P68/328). NOTE 26. P.68C-TC aircraft from s/n 514 onwards are equipped since new with Garmin G1000 NXi Integrated Flight Deck System and GFC700 Autopilot (as per Type Design Change No. MOD P68/328). NOTE 27. P.68TC Observer aircraft from s/n 514 onwards are equipped since new with Garmin G1000 NXi Integrated Flight Deck System and GFC700 Autopilot (as per Type Design Change No. MOD P68/328). NOTE 28. P.68 Observer 2 aircraft from s/n 514 onwards, plus s/n 495, are equipped since new with Garmin G1000 NXi Integrated Flight Deck System and GFC700 Autopilot (as per Type Design Change No. MOD P68/328). .....END..... ``` ## ADs (38, in force first) - [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 2022-20-10](https://openairdocs.org/ad/2022-20-10): Rudder Structure · Vulcanair P.68, P.68B, P.68C and 5 more. Effective Nov 28, 2022 - [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 2021-26-15](https://openairdocs.org/ad/2021-26-15): Stabilizer Control System · Vulcanair P.68C, P.68C-TC, P.68 Observer and 3 more. Effective Feb 15, 2022 - [AD 2019-06-10](https://openairdocs.org/ad/2019-06-10): Wings · Vulcanair AP68 TP Series 300 Spartacus and AP68TP 600 Viator. Effective Apr 29, 2019 - [AD 2015-18-01](https://openairdocs.org/ad/2015-18-01): Navigation · Vulcanair P.68R. Effective Sep 22, 2015 - [AD 2014-10-01](https://openairdocs.org/ad/2014-10-01): Wings · Vulcanair P 68, P 68 Observer, P 68B and 4 more. Effective Jun 18, 2014 - [AD 2009-24-03](https://openairdocs.org/ad/2009-24-03): Wing spar · Vulcanair P 68, P 68 Observer, P 68B and 2 more. Effective Jan 4, 2010 - [AD 2007-09-08](https://openairdocs.org/ad/2007-09-08): Quick release pin · Vulcanair P 68C, P68 Observer 2 and P68TC Observer. Effective Jun 4, 2007 - [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 2005 - [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005 - [AD 2002-19-08](https://openairdocs.org/ad/2002-19-08): Engine control system · Vulcanair AP68 TP Series 300 Spartacus, P 68, P 68 Observer and 5 more. Effective Nov 8, 2002 - [AD 2000-24-05](https://openairdocs.org/ad/2000-24-05): Nose Landing Gear Upper Strut · Vulcanair P 68 Observer, P68 Observer 2 and P68TC Observer. Effective Jan 5, 2001 - [AD 2000-03-18](https://openairdocs.org/ad/2000-03-18): Airframe Pneumatic Deicing Boots · Vulcanair AP68 TP Series 300 Spartacus and AP68TP 600 Viator. Effective Apr 7, 2000 - [AD 98-04-20](https://openairdocs.org/ad/98-04-20): Airplane Flight Manual (AFM) - Icing Limitations · Vulcanair AP68 TP Series 300 Spartacus, AP68TP 600 Viator and P 68. Effective Mar 13, 1998 - [AD 97-22-10](https://openairdocs.org/ad/97-22-10): Airplane Flight Manual (AFM) - Limitations Section - Power Levers · Vulcanair AP68 TP Series 300 Spartacus and AP68TP 600 Viator. Effective Dec 5, 1997 - [AD 91-22-06](https://openairdocs.org/ad/91-22-06): Placard Operating Limitations · Vulcanair P 68, P 68 Observer, P 68B and 3 more. Effective Nov 12, 1991 - [AD 91-11-14](https://openairdocs.org/ad/91-11-14): Fuel and Janitrol System Lines · Vulcanair P 68 Observer, P 68C and P 68C-TC. Effective Jun 14, 1991 - [AD 89-03-03](https://openairdocs.org/ad/89-03-03): Engine Mounting System · Vulcanair P 68, P 68 Observer, P 68B and 3 more. Effective Feb 16, 1989 - [AD 88-21-04](https://openairdocs.org/ad/88-21-04): Stabilator Trim Tabs · Vulcanair P 68, P 68 Observer, P 68B and 3 more. Effective Oct 27, 1988 - [AD 88-13-08](https://openairdocs.org/ad/88-13-08): Engine Mount · Vulcanair P 68, P 68 Observer, P 68B and 3 more. Effective Jul 13, 1988 - [AD 87-10-12](https://openairdocs.org/ad/87-10-12): Leading Edge Wing Ribs · Vulcanair P 68, P 68B, P 68C and 1 more. Effective Jun 1, 1987 - [AD 87-04-20](https://openairdocs.org/ad/87-04-20): Aileron Control Cable · Vulcanair P 68, P 68 Observer, P 68B and 3 more. Effective Mar 16, 1987 - [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 85-08-06](https://openairdocs.org/ad/85-08-06): Aileron Control · Vulcanair P 68, P 68 Observer, P 68B and 2 more. Effective May 28, 1985 - [AD 83-14-03](https://openairdocs.org/ad/83-14-03): Fin Rear Spar · Vulcanair P 68 and P 68B. Effective Aug 19, 1983 - [AD 83-07-22 R1](https://openairdocs.org/ad/83-07-22-R1): Flap Selector Switch Replacement · Vulcanair P 68B, P 68C and P 68C-TC. Effective Aug 9, 1983 - [AD 83-15-04](https://openairdocs.org/ad/83-15-04): Torque Support Brackets · Vulcanair P 68, P 68 Observer, P 68B and 2 more. Effective Aug 4, 1983 - [AD 83-12-04](https://openairdocs.org/ad/83-12-04): Flap Bellcrank Attach Mountings · Vulcanair P 68, P 68 Observer, P 68B and 2 more. Effective Jun 23, 1983 - [AD 83-07-17](https://openairdocs.org/ad/83-07-17): Fuel Selector Control · Vulcanair P 68B and P 68C. Effective Apr 14, 1983 - [AD 83-05-07](https://openairdocs.org/ad/83-05-07): Oil Cooler Fittings and Hoses · Vulcanair P 68 and P 68B. Effective Mar 17, 1983 - [AD 82-18-11](https://openairdocs.org/ad/82-18-11): Wheel Shaft Universal Joints · Vulcanair P 68 and P 68B. Effective Sep 13, 1982 - [AD 81-07-08](https://openairdocs.org/ad/81-07-08): Longitudinal Trim Tab · Vulcanair P 68 and P 68B. Effective Apr 6, 1981 - [AD 81-07-03](https://openairdocs.org/ad/81-07-03): Propeller Pitch Control System · Vulcanair P 68 and P 68B. Effective Apr 2, 1981 - [AD 80-15-02](https://openairdocs.org/ad/80-15-02): Rudder Control System · Vulcanair P 68 and P 68B. Effective Jul 21, 1980 - [AD 80-01-01](https://openairdocs.org/ad/80-01-01): Stabilator Balance Weight · Vulcanair P 68 and P 68B. Effective Jan 2, 1980 - [AD 2008-24-11](https://openairdocs.org/ad/2008-24-11) (historical): Safe Fatigue Limits (SFL) of the Wing Structure · Vulcanair AP68 TP Series 300 Spartacus, AP68TP 600 Viator, P 68 and 6 more. Effective Jan 2, 2009 - [AD 85-08-04](https://openairdocs.org/ad/85-08-04) (historical): Wing Spars · Vulcanair P 68, P 68 Observer, P 68B and 4 more. Effective May 17, 1985 ## Registered aircraft by registry model (OpenAirDocs) - [Partenavia P.68C](https://openairdocs.org/model/partenavia-p-68c): 20 aircraft (registry code 6780105) - [Partenavia P 68 C/TC](https://openairdocs.org/model/partenavia-p-68-c-tc): 5 aircraft (registry code 6780106) - [Partenavia P 68 OBSERVER](https://openairdocs.org/model/partenavia-p-68-observer): 5 aircraft (registry code 6780103) - [Partenavia P68B](https://openairdocs.org/model/partenavia-p68b): 5 aircraft (registry code 6780104) - [Vulcanair P68C](https://openairdocs.org/model/vulcanair-p68c): 5 aircraft (registry code 6780126) - [Vulcanair P68 OBSERVER 2](https://openairdocs.org/model/vulcanair-p68-observer-2): 4 aircraft (registry codes 6780113, 6780116) - [Partenavia P.68 OBSERVER 2](https://openairdocs.org/model/partenavia-p-68-observer-2): 3 aircraft (registry code 6780109) - [Vulcanair P68 TC OBSERVER](https://openairdocs.org/model/vulcanair-p68-tc-observer): 2 aircraft (registry code 6780128) - [Partenavia P68](https://openairdocs.org/model/partenavia-p68): 1 aircraft (registry code 6780102) - [Partenavia P68-TC OBSERVER](https://openairdocs.org/model/partenavia-p68-tc-observer): 1 aircraft (registry code 6780108) - [Vulcanair P68R](https://openairdocs.org/model/vulcanair-p68r): 1 aircraft (registry code 6780129) - [Partenavia C A S P A AP68TP-300 SPARTACUS](https://openairdocs.org/model/partenavia-c-a-s-p-a-ap68tp-300-spartacus): 0 aircraft (registry code 6780117) - [Vulcanair S P A AP68TP 300 SPARTACUS](https://openairdocs.org/model/vulcanair-s-p-a-ap68tp-300-spartacus): 0 aircraft (registry code 6780139) ## STCs approved under this data sheet (161, first 50) - [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc. - [STC SA03420AT](https://openairdocs.org/stc/SA03420AT): Propeller model MTV-12-B-C-F/CF183-59b propeller installed. MT-Propeller Entwicklung GmbH - [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 SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC - [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc. - [STC 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 SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc. - [STC SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC - [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 SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd. - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine - [STC SA04192NY](https://openairdocs.org/stc/SA04192NY): KFD 900 Primary Flight Display System Additional Functions. Honeywell International Inc - [STC SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC - [STC SA02987CH](https://openairdocs.org/stc/SA02987CH): Installation of the Electroair Electronic Ignition System. Electroair Acquisition Corporation - [STC SA00076IB](https://openairdocs.org/stc/SA00076IB): Installation of Photo luminescent Safety Systems. STG AEROSPACE GERMANY GmbH - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems Inc. - [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC - [STC SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc. - [STC SA09856AC](https://openairdocs.org/stc/SA09856AC): Installation of BendixKing Aerowave 100 In-flight Data Link System for non-essential, non-required aircraft Cabin Systems & Equipments. Honeywell International Inc (Bendix King) - [STC SA09902AC](https://openairdocs.org/stc/SA09902AC): Installation of BendixKing KFD 900 Flight Display System. Honeywell International Inc. (Bendix King) - [STC SA11174SC PAGE 2](https://openairdocs.org/stc/SA11174SC%20PAGE%202): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King) - [STC SA02430SE](https://openairdocs.org/stc/SA02430SE): Fabrication and installation of a camera housing. Airborne Sensor LLC - [STC SA10822SC](https://openairdocs.org/stc/SA10822SC): Installation of EFD1000 Primary Flight Display. Aspen Avionics Inc. - [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation - [STC SA02666SE](https://openairdocs.org/stc/SA02666SE): Installation of a Supplemental Lighting System. Aviation Specialties Unlimited Inc. - [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc - [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation - [STC SA1791CE-D](https://openairdocs.org/stc/SA1791CE-D): Install KAP 100 single axis, KAP 150 two axis, or KFC 150 two axis flight control system with optional KAP 297B vertical speed and altitude selector.. Honeywell International Inc - [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc - [STC SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation - [STC SA00344BO PAGE 2](https://openairdocs.org/stc/SA00344BO%20PAGE%202): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [STC SA00744DE](https://openairdocs.org/stc/SA00744DE): Installation of the Automatic Dependent Surveillance Broadcast (ADS-B) Out Equipment using a Trig Avionics TT31 Transponder and an approved position sensor. Peregrine - [STC SA00765DE](https://openairdocs.org/stc/SA00765DE): Installation of Automatic Dependent Surveillance Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine - [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation - [STC SA02153LA-D PAGE 2](https://openairdocs.org/stc/SA02153LA-D%20PAGE%202): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc. - [STC SA02013CH](https://openairdocs.org/stc/SA02013CH): Installation of Avidyne Corporation Traffic Advisory System (TAS). Avidyne Corporation - [STC SA01828SE](https://openairdocs.org/stc/SA01828SE): Installation of J.P. Instruments (JPI) EDM-960 Primary Engine Data Management System. J. P. Instruments - [STC SA01835WI](https://openairdocs.org/stc/SA01835WI): Installation of Trig Avionics TY-96 or TY-97 VHF Communications Radio. Peregrine - [STC SA00024NY](https://openairdocs.org/stc/SA00024NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K007 on single or multi-engine fixed wing light aircraft incorporating Lycoming reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc - [STC SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC - [STC SA2586NM](https://openairdocs.org/stc/SA2586NM): Installation of J.P. Instruments temperature monitoring systems.. J P Instruments - [STC SA00382BO](https://openairdocs.org/stc/SA00382BO): Installation of Globalstar Antenna and Cradle provisions to support a Globalstar GPS-1700 in non-composite airplanes. Avidyne Corporation - [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley All 161: https://openairdocs.org/tcds/A31EU/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.