TCDS A31EU

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)