Page 1 of Jun-2014 EASA.A.059. P Series. Issue 8 EASAA. SpA. Roma ITALY. Avanti II. general

Transcription

1 Page 1 of 21 European Aviation Safety Agency EASAA TYPE CERTIFICATE DATA SHEET EASA.A.059 Type Certificate Holder: SpA Viale Castro Pretorio, Roma ITALY For models: Avanti Avanti II general

2 Page 2 of 21 SECTION A: P.180 Avanti CONTENT AI. AII. AIII. AIV. AV. General Certification Basis Technical Characteristics and Operational Limitations Operating and Service Instructions Notes SECTION B: P.180 Avanti II BI. BII. BIII. BIV. BV. General Certification Basis Technical Characteristics and Operational Limitations Operating and Service Instructions Notes ADMINISTRATIVE SECTION I. Acronyms II. Type Certificatee Holder Record III. Change Record general

3 Page 3 of 21 SECTION A: P. 180 Avanti A.I. General a) Type b) Model c) Variant Airworthiness Category Type Certificate Holder: Manufacturer: Certification Application Date: The ENAC Certification Date: P.180 Avanti - Normal SpA Viale Castro Pretorio, Roma ITALY SpA Via Luigi Cibrario, Genova ITALY until 1998 I..A.M. Rinaldoo Piaggio S.p.A. ITALY December 19th, 1983 March 7 th, The EASA Type Certificate replacess the ENAC Type Certificate No. A 390 A.II Certification Basis Reference Date for determining the applicable equirements: (reserved) (reserved) Airworthiness Requirements: RAI Regolamento Tecnico Part 223, including amendments through , correspondent to FAR 23, effective February 1 st t 1965, inclu ding amendments 23-1 through JAR AWO Subaprt 2, Change 2, dated August 1 st 1996 RVSM specific requirements included in the JAA Leaflet n. 6 rev.1 and a in the FAA Interim Guidance Material 91 RVSM, Ch. 1 For airplanes incorporating the optional Mod. n or equivalent SB : as above, except CS-23 requirements (first issue) applicable to the areas affected by the change (see CRI A-01 A for modd ). P.180 Avanti

4 Page 4 of Requirements elected to comply: Special Federal Aviation Regulationss n. 27, effective 1st February 1974, ncluding amendments 27-1 through FAR 23.2, amendment 36. FAR 91 Appendix A dated August 18, Applicable JAR 23 (first issue dated March 11, 1994) requirements for thee following modifications Vertical fin - aluminum alloy instead of composite Aluminum canard wing instead of composite Aluminum rudder and trim tab and for the relevant Service Bulletins: Replacement of the Composite Forward Wing Assembly with the new metallic one Replacement of the Composite Material Tail- Construction Assembly, in the event of not repairable r damages 14 CFR Part 36, effective 1st Dec. 1969, including amendments 36-1 through cone/ /Vertical Fin Assembly, with w the Metal EASA Certification Specifications CS-23, dated 23/11/2003, paragraph p EASA Special Conditions Special Conditions enclosed too the RAI paper n /SCMA datedd July 21, 1989 (Docket n. 031 CE, Special Conditions n. 23-ACE-29, and Special Condition FAA n. 23-ACE-52) which include the following Issue Papers: Issue Paper C-1 Composite Structures Fatigue/Damage Tolerance C-2 Full Scale Airload Verification C-3 Doors and Exits (Outward Opening) C-4 Lightning Protection of Composite Structure C-6 Forward and Main Wing Flap Interconnection C-7 Loads for P180 Configuration F-1 Buffet Onset Envelope F-2 Effect of Rain or Contamination on Laminar Flow Airfoils F-5 Inadvertent Excursion Beyond Maximum Operating Speed P-6 Propeller Ground Clearance P-7 Propeller marking P-8 Propeller Ice Protection and Exhaust Gas Impingement SE-4 Cockpit Smoke Evacuation SE-5 Protection for Systems from Lightning and High Energy Radio Frequency (HERF) EASA Exemptions: EASA Equivalent Safety Findings: (g) (b)(5) Fuel pressure indication Marking of Air Speed Indicator for V YSE Special Condition 23-ACE-29 No ACE-29 No ACE-29 No ACE-29 No ACE-29 No ACE-29 No ACE-29 No ACE-29 No ACE-29 No ACE-29 No ACE-29 No ACE-29 No ACE-29 No ACE-52 No. 2 None P.180 Avanti

5 Page 5 of EASA Environmental Standards (seee also TCDSN): Noise: ICAO Annex 16,Ed. 1988, Vol. I, Chapter 10. [Airplanes incorporating the optional Mod. n or SB S : ICAO Annex 16, Ed. 1993, Amd. 7, Vol. I, Chapter 10/EASA-CS 36 (see CRI A-01 mod )] Emissions: ICAO Annex 16, Ed. 1993, Vol. II, Part II, Chapterr 2 (fuel venting). A.III Technical Characteristics and Operational Limitations Type Design Definition: Description: P.180 Avanti Type T Design Configuration Piaggio Doc. n. 180-CNF Piaggio P180 Avanti is a bi-turboprop business aircraft with a max seating capability of 11 people including crew. Its peculiar characteristic are the three lifting surface designn (forward wing, main wing, and horizontal stabilizer) and pusher props. 3. Equipment: The list of approved equipment is shown in Piaggio document P.180 Master Equipment List Doc. n Dimensions: Forward Wing Span Main Wing Span Length Height Total Wing Area 3356 mm (11.01 ft) mm (46.04 ft) mm (47.27 ft) 3980 mm ( ft) m 2 ( ft 2 ) 5. Engines: No. 2 Model: Prattt & Whitney of o Canada PT6A-66 turboprop engines, each flat rated at 850 s.h.p. Right Engine Build Spec Left Engine Build Spec Type Certificate: : EASA.IM.E.008 Airplanes ncorporating the Mod. n or SB : Model: Prattt & Whitney of o Canada PT6A-66B turboprop engines, each flat rated at 850 s.h.p. when installed on the aircraft. Right Engine Build Spec Left Engine Build Spec Type Certificate: : EASA.IM.E.008 P.180 Avanti

6 Page 6 of Engine Limits Operating Conditions Takeoff Shaft (shp.) N1 Gas Generator Speed (%) Torque ft-lbs (kgm) Prop. shaft speed (r.p.m.) Maximum Permissible Interstage Temperature ( C) Max. continuous Max. climb , (308,3) Max. cruise Normal Climb Normal Cruise (308,3) Starting Limits (5 sec.) Transient (20 sec.) (380,2) Oil Temperature Starting - 40 C (min.)) Minimum Idle - 40 C 110 C Transient 0 C CC Max. continuous and max. reverse 0 C CC Note: The above mentioned engine limits are applicable to both engine models PT6A-66 and PT6A-66B 6. Propellers: No. Model Type Certificate 2 Hartzell Right: HC-E5N-3L or HC-E5N-3AL (hub) / LE 8218 (each blade) Left: HC-E5N-33 or HC-E5N-3A (hub) / HE 8218 (each blade) The EASA Propeller/enginee Type Certification standard includes that of FAA TC P20NE based on individual EU member state acceptance or certification of this t standardd prior to 28 September Number of blades Sense of Rotation Right propeller rotates Counterclockwise inn view of flight direction Left propeller rotates Clockwise in view of flight direction 6.2. Diameter 2159 mm maximum, 2146 mm minimumm P.180 Avanti

7 Page 7 of Pitch Nominal pitch anglee at 0,761 m (30 ) stationn Minimum on ground: Minimum in flight: Reverse (negative): Feathered: 14 ± 0,5 18 ± 0,5-13 ± 0,5 89 ± 0, Propeller Limits No further reductionn of the minimum diameter is allowed. Stabilized ground operations between 600 and a 900 rpm are prohibited. Stabilized ground operations at or below 6000 rpm are allowed only when the propeller is feathered. Stabilized ground operations between 1300 and 1600 rpm are prohibited. 7. Fluids 7.1 Fuel 7.2 Oil JP4, JP8, JET A, JET A-1, JET B; RP-3 (No.3 Jet Fuel); RTT and TS-1 ( as per GOST ) conformingg to the latestt revision of Pratt P & Whitney Service Bulletin No Fuel Anti-Ice Additive compliant with Specification MIL- I must be used with JET A, JET A1, JET B and RP-3 fuels. Mobile Jet Oil II, AeroShell Turbine Oil 500 andd Castrol Refer also to the Limitations Section of the Pilot s Operatingg Handbook and Airplane Flight Manual (latest revision). 8. Fluid Capacities 8.1 Fuel Total: 1500 lt Usable: 1486 lt Total: 1597 lt Usable: 1583 lt (396.3 US Gal) (392.6 US Gal), or (421.9 US Gal) (418.2 US Gal) for Aeroplanes withh modification n Wing Tankk Extension or SB embodied 8.2 Oil Total: Usable quantity: 25 lt (6.7 US Gal) 9,4 It (2.5 US GaI), Refer to Note 3 for non-drainable oil. P.180 Avanti

8 Page 8 of Air Speeds Speed Maximum operating speed Maneuvering speed Max Flap Extended Speed Max Landing Gear Extended Speed Max Landing Light Operating / Extended Speed Minimum Control Speed V MO M MO M MO (for aeroplanes with modificationn n , or equivalent Service Bulletin n installed) V A V A (for aeroplanes with modificationn n , or equivalent Service Bulletin n installed) V FE V FE (for aeroplanes with modificationn n , or equivalent Service Bulletin n installed) V FE V FE (for aeroplanes with modificationn n , or equivalent Service Bulletin n installed) Max Flap Operating Speed V FO 150 V FO V LO V LO (for aeroplanes with modificationn n , or equivalent Service Bulletin n installed) Max Landing Gear Extended Speed V LE V LLO / V V MC V LLE Condition KIAS up to ft 260 above ft above ft at 5239 kg ( lb) 199 at 5489 kg ( lb) take-off configuration (T.O.) 180 take-off configuration (T.O.) 183 take-off configuration Propeller feathered 100 Propeller windmilling 128 Mach 0,67, or 0,7, or, or, or, or 10. Maximum Operating Altitude: m / ft 11. All-weather Capability: Airplanes with modification n Category II Kit embodied may be authorised to perform Category 2 (Cat. II) operations according to the limitations included in the Supplementt n. 26 of the Pilot s Operating Handbook and Airplane Flight Manual. P.180 Avanti

9 Page 9 of Weights: 12.1 Maximum Weight for Taxi and ramp Take-off Landing kg (11600 lb) kg (11550 lb) kg (10945 lb), or Taxi and ramp 5511 kg (12150 lb) Take-off 5489 kg (12100 lb) Landing 5216 kg (11500 lb) for aeroplanes with modification n , or equivalent Service Bulletin n installed 12.2 Zero Fuel Weight at forward C.G. limit 4309 kg ( 9500 lb) ) at aft C.G. limit 4218 kg ( 9300 lb) ) Straight line variation between b limits given 4445 kg ( 9800 lbs) C.G. whereas (S.N and up airplanes) 13. Centre of Gravity Range: Landing gear extended C.G. range From 5,273 m (207.6 ) 5,340 m ( ) To 5,435 m (214.0 ) 5,435 m (214.0 ) Weight 5239 kg (11550 lbs), or 5511 kg (12150 lbs)] for aeroplanes with modification n , or equivalent Service Bulletin n installed 4,958 m (195.2 ) 5,435 m (214.0 ) 4,927 m (194.0 ) 5,410 m (213.0 ) 4,927 m (194.0 ) 5,328 m (209.8 ) Straightt line variation between limits given. Empty Weight C.G. Range 3967 kg ( 8745 lbs) 3856 kg ( 8500 lbs) 3493 kg ( 7700 lbs) or less None 14. Datum 6,000 m ( ) forward of the rearr pressure bulkhead centerline (at thee intersectionn between the forward pressure bulkhead and the cockpit floor centerline). 15. Mean Aerodynamic Cord (MAC) 1,270 m (50 ) 16. Leveling Means Refer to the P.180 Maintenance Manual Piaggio Doc. n. 9066, Chapter 8, or to the applicable Pilot s Operating Handbook and Airplane Flight Manual, Sec Minimum Flight Crew 1 (Pilot) 18. Maximum Passenger Seating Capacity 11 including flight crew at 1,250 m (49.2 ) station. Refer to the POH/AFM for Passengers and flight crew loading instructions and approved configuration P.180 Avanti

10 Page 10 of Exits (No. and Type) 2 one main door one emergency exit 20. Baggage / Cargo Compartments Compartment Cabin compartment on floor on coat rod Rear compartment Weight Station 23 kg (50 lbs) 5,588 m (220 ) 18,1 kg (40 lbs) 5,588 m (220 ) 181,4 kg (400 lbs) ) 7,569 m (298 ) 21. Wheels and Tires For approved wheels types and tires types, rating, dimensions and a ply rating, refer to applicable Pilot's Operating Handbook and Airplane Flight Manual A.IV Operating and Servicing Instructions 1. Aircraft Flight Manual Pilot s Operating Handbook and Airplane Flight Manual Report n. 6591, RAI approved on July 7, 1992, and subsequentt approved revisions Maintenancee Manual P.180 Maintenance Manual Report n Structural Repair Manual P.180 Structural Repair Manual - Report n. 180-MAN Service Bulletins Refer to Piaggio Report n P.180 Avanti

11 Page 11 of 21 A.V Notes 1. Customized Cabin Interior and Seating Configurations must be b approved 2. Applicable A/C Serial Number from S/N 1004 to Requirements for the issue of the CofA - The minimum required equipment as prescribed in the applicable airworthiness regulations r must be installed on the individual aircraft for certification. - Current weight and balance data, a list of equipment included in the certification empty weight and loading information when necessary must be provided for each aeroplane when the CoA will be issued The certification empty weight and balance data shall include the unusable fuel and the total engine oil as follows: Quantity Station Unusable fuel: 11,24 kg (24.8 lbs) ) 6,319 m (248.8 ) Undrainable fuel: Undrainable oil: Total oil quantity: 3,94 kg k (8.7 lbs) 2,2 kgg (4.9 lbs) 25 Kg (55 lbs) 6,304 m (248.2 ) 6,975 m (274.6 ). 6,975 m (274.6 ). - Aeroplane Flight Manual is required Placards All required placards as appropriate locations. listed in the approved Airplane Flight Manual must be installed in the Continued Airworthinesss Airworthiness Limitations and Servicee Life Limits of some equipment are contained in Chapter 4 (Airworthiness Limitations) and Chapter 5 (Maintenance Schedule and Time Limits) of the Piaggio Report n Painting Changing the color and the t thicknesss of the exterior paint (including registration numbers) for composite components is only permissible after prior approval of the Typee Certificate Holder. P.180 Avanti

12 Page 12 of 21 SECTION B: P. 180 Avanti II B.I General a) Type b) Model c) Variant Airworthiness Category Type Certificate Holder: Manufacturer: Certification Application Date: The EASA Certification Date: P.180 Avanti II - Normal Piaggio Aeroo Industries SpA Viale Castroo Pretorio, Roma ITALY Piaggio Aeroo Industries SpA Via Luigi Cibrario, Genova ITALY October 16 th 2003 October 21 st 2005 B.II Certification Basis 1. Reference Date for determining the applicable equirements October 16 th (reserved) (reserved) Airworthiness Requirements As per para A.II.4, A exceptt the requirements applicable to the areas affected by the PA-05 major change (see CRI A-01) Airplanes incorporating the optional Mod. n or SB : : as above, except the CS 23 requirements (first issue) applicable to the areas affected by the change (see CRI C A 01 modd ) Requirements elected to comply Special Conditions As per para. A.II.5 Special Condition RAI-NTO SE-5 [FAA 23-ACE-52 n.2] Protection for Systems from Lightning and High Energy Radio Frequency is superseded, for this design change, by the new Special Condition originated byy CRI F- 01 (HIRF Protection) and by the conclusions of CRI F-02 (Protection from the Effects of Lightning Strike: Indirect Effects). 7. EASA Exemptions None P.180 Avanti II

13 Page 13 of Equivalent Level of Safety CRI B 02 Equivalent Level of Safety CRI F 05 Equivalent Level of Safety CRI F 06 Equivalent Level of Safety Airspeed Indicator Markings Powerplant Display Instruments Use of Digital only Display forr Engine Oil Pressure and Temperature, Fuel Quantity and Flow 9. EASA Environmental Standards As per para. A.II.9 B.III Technical Characteristics and Operational Limitations 1. Type Design Definition: P.180 Avanti Type Design Configuration Piaggio Doc. n. 180-CNF P.180 Avanti II List of approved type design changes Piaggio Doc. N. 180-CNF Description: 2.1. General The General Description of the P..180 Avanti to P.180 Avanti II, except for the avionics suite. (provided inn A.III, 2 of Section A1) applies 2.2. Avionics The standard avionics package is a Collins Pro Line 21 avionic suite, configured for the P180. as it has been 3. Equipment: The list of approved equipment is shown in Piaggio document P.180 Vendor Item List/Qualification Equipment List Piaggio Doc. n. 180-CRP Dimensions: Forward Wing Span Main Wing Span Length Height Total Wing Area 3356 mm m (11.01 ft) mm m (46.04 ft) mm m (47.27 ft) 3980 mm m (13.05 ft) 16,00 m 2 ( ft 2 ) P.180 Avanti II

14 Page 14 of Engines: No. 2 Model: Prattt & Whitney of o Canada PT6A-66 turboprop engines, each flat rated at 850 s.h.p. Right Engine Build Spec Left Engine Build Spec Type Certificate: : EASA.IM.E.008 Airplanes ncorporating the Mod. n or SB : Model: Prattt & Whitney of o Canada PT6A-66B turboprop engines, each flat rated at 850 s.h.p. when installed on the aircraft. Right Engine Build Spec Left Engine Build Spec Type Certificate: : EASA.IM.E Engine Limits Operating Conditions Takeoff Shaft (shp.) N1 Gas Generator Speed (%) Torque ft-lbs (kgm) Prop. shaft speed (r.p.m.) Maximum Permissible Interstage Temperature ( C) Max. continuous Max. climb (308,3) Max. cruise Normal Climb Normal Cruise (308,3) Starting Limits (5 sec.) Transient (20 sec.) (380,2) Oil Temperature Starting Minimum Idle Transient: Max. continuous and max. reverse - 40 C (min.) - 40 C 110 C 0 C 110 C 0 C 110 C Note: The above mentioned engine limits are applicable to both engine models: PT6A-66 and PT6A-66B. P.180 Avanti II

15 Page 15 of Propellers: No. Model: Type Certificate: 2 Hartzell Right: HC-E5N-3L or HC-E5N-3AL (hub) / LE 8218 (each blade) Left: HC-E5N-33 or HC-E5N-3A (hub) / HE 8218 (each blade) The EASA Propeller/enginee Type Certification standard includes that of FAA TC P20NE based on individual EU member state acceptance or certification of this t standardd prior to 28 September Number of blades: Sense of Rotation Right propeller rotates Counterclockwise in view of flight direction Left propeller rotates Clockwise in view of flight direction 6.2. Diameter 2159 mm maximum, 2146 mm minimum 6.3. Pitch Nominal pitch angle at 0,761 m (30 ) station Minimum on ground 14 ± 0,5 Minimum in flight 18 ± 0,5 Reverse (negative) -13 ± 0,5 Feathered 89 ± 0, Propeller Limits No further reduction of the minimum diameter is allowed. Stabilized ground operations between 6000 and 900 rpmm are prohibited. Stabilized ground operations at or below 6006 rpm are allowed only when the propeller is feathered. Stabilized ground operations between 1300 and 1600 rpm are prohibited. 7. Fluids 7.1. Fuel JP4, JP8, JET A, JET A-1, JET B; RP-3 (No.3 Jet Fuel); RT and TS-1 (as per GOST ) conforming to the latest revision of Pratt & Whitney Service Bulletin No Fuel Anti-Ice Additive compliant with Specification MIL-I M must be used with JET A, JET A1, JET B and RP-3 fuels 7.2. Oil Mobile Jet Oil II, AeroShell Turbine Oil 500 and Castrol Refer also to the Limitationss Section of the Pilot s Operating Handbook and Airplane Flight Manual (latest revision) P.180 Avanti II

16 Page 16 of Fluid capacities 8.1. Fuel Total Usable 1597 l (421.9 US Gal) 1583 l (418.2 US Gal), or Total 1816 l (479.7 US Gal) Usable 1802 l (476.0 US Gal) for aeroplanes with modification n P.180 Extended E Range or S.B embodied 8.2. Oil Total Usable quantity Refer to Notee 3 for non-drainable oil. 25 l (6.7 USS Gal) 9,4 l (2.5 US Gal) 9. Air Speeds Speed Maximum operating speed Maneuvering speed Max Flap Extended Speed V MO M MO V A V A Max Landing Gear Operating Speed (for aeroplanes with modificationn n , or equivalent Service Bulletin n installed) V FE V FE (for aeroplanes with modificationn n , or equivalent Service Bulletin n installed) V FE V FE (for aeroplanes with modificationn n , or equivalent Service Bulletin n installed) Max Flap Operating Speed V FO 150 V FO V LO V LO Condition KIAS up to ft 260 above ft at 5239 kg ( lb) 199 at 5489 kg ( lb) 202 take-off configuration (T.O.) 180 take-off configuration (T.O.) 183 take-off configuration (for aeroplanes with modificationn n , or equivalent Service Bulletin n installed) Mach 0.7, or, or, or, or P.180 Avanti II

17 Page 17 of 21 Speed Condition Max Landing Gear Extended Speed Max Landing Light Operating / Extended Speed Minimum Control Speed V LE V LLO / V V MC V LLE Propeller feathered Propeller windmilling KIAS Mach (contd) 10. Maximum Operating Altitude m / ft f 11. All-weather Capability The airplanes are authorised to performm Category 2 (Cat. II) operations according to the limitations included in the applicable Airplane Flight Manual. 12. Maximum Weight 12.1 Maximum Weight for Taxi and ramp r Take-off Landing 5262 kg (11600 lb) 5239 kg (11550 lb) 4965 kg (10945 lb), or Taxi and ramp r 5511 kg (12150 lb) Take-off 5489 kg (12100 lb) Landing 5216 kg (11500 lb) (for aeroplanes with modification n , orr equivalent Service Bulletin n installed) 12.2 Zero Fuel 4445 kg (9800 lb) 13. Centre of Gravity Range For Landing Gear Extended From 5,273 m (207.6 ) 5,340 m ( ) To 5,435 m (214.0 ) 5,435 m (214.0 ) Weight 5239 kg (11550 lbs), or 5511 kg (12150 lbs)] for aeroplanes with modification n , or equivalent Service Bulletin n installed 4,958 m (195.2 ) 4,927 m (194.0 ) 4,927 m (194.0 ) 5,435 m (214.0 ) 5,410 m (213.0 ) 5,328 m (209.8 ) 3967 kg ( 8745 lbs) 3856 kg ( 8500 lbs) 3493 kg ( 7700 lbs) or less Straightt line variation between limits given Empty Weight C.G. Range none P.180 Avanti II

18 Page 18 of Datum 6,000 m ( ) forward of the rearr pressure bulkhead centerline (at the intersection between the forward pressure bulkhead and the cockpit floor centerline). 15. Mean Aerodynamic Chord (MAC) 1,270 m (50 ) 16. Leveling Means Refer to the P.180 Avanti II Maintenance Manual or to the applicable Pilot s Operating Handbook and Airplane Flight Manual. 17. Minimum Flight Crew 1 (Pilot) 18. Maximum Passenger Seating Capacityy 11 including Flight Crew at 1,250 m (49.2 ) station Refer to the P.180 Avanti II Weight and Balance Manual for Passengers and flight crew loading instructions and approved configuration 19. Exits (No. and Type) 2 one main door one emergency exit 20. Baggage / Cargo Compartments Compartment Cabin compartment on floor on coat rod Rear compartment Weight Station 23 kg (50 lbs) 5,588 m (220 ) 18,1 kg (40 lbs) 5,588 m (220 ) 181,4 kg (400 lbs) ) 7,569 m (298 ) 21. Wheels and Tyres For approved wheels types and tires types, rating, dimensionss and ply rating, refer to applicable Pilot's Operating Handbook and Airplane Flight Manual P.180 Avanti II

19 Page 19 of 21 B.IV Operating and Servicing Instructions 1. Aircraft Flight Manual P.180 Avanti II Airplane Flight Manual Report n.180-man P.180 Avanti II Weight and Balance Manual Report n. 180-MAN Maintenancee Manual P.180 Avanti II Maintenance Manual Report n. 180-MAN Airworthiness Limitations are contained in P.180 Avanti II Chapter 4 (Airworthiness Limitations) Report n. 180-MAN Structural repair Manual P.180 Structural Repair Manual Report n.180-man Service Bulletins Refer to Piaggio Report n P.180 Avanti II

20 Page 20 of 21 B.V Notes 1. Customized Cabin Interior and Seating Configurations must be approved 2. Applicable A/C serial numbers: S/N 1002 and from S/N 1105 and a up. 3. Requirements for the issue of the CofA * The minimum required equipment as prescribed in the applicable airworthiness regulations must be installed on the individual aircraft for certification. * Current weight and balance data, a list of equipment included in the certification empty weight and loading information when necessary must be provided for each aeroplane when the CoA will be issued. * The certification empty weight and balance data shall include the unusable fuel and the total engine oil as follows Unusable fuel: Quantity Station 11,244 kg (24.8 lb) ) 6,319 m (248.8 ) Undrainable fuel: for aeroplanes with modification n P.180 Extended Range or S.B embodied Undrainable oil: Total oil quantity: 3,94 kg (8.7 lb) 7 kg (15.4 lb) 2,2 kg (4.9 lb) 25 Kgg (55 lb) 6,304 m (248.2 ) 6,012 m (236.7 ) 6,975 m (274.6 ) 6,975 m (274.6 ) * Aeroplane Flight Manual is required Placards All required placards as listed in the approved Airplane Flight Manual must be installed in the appropriate locations. Painting Changing the color and the t thicknesss of the exterior paint (including registration numbers) for composite components is only permissible after prior approval of the Typee Certificate Holder. P.180 Avanti II

21 Page 21 of 21 ADMINISTRATIVE SECTION I Acronyms None II Typer Certificate Holder Recordd until 1998 I.A.M. Rinaldo Piaggio S.p.A. III Change Record Issue Date Changes 21-Oct Jan Mar Feb Apr Feb Initial EASA issue replacing ENAC / RAI TCDS - Addition of optional Mod or SB Addition of Mod (P.EASA.A.C.03574) - Editorial changes and corrections - Editorial corrections too engine built specifications - RP-3 fuel type added - list of fuel types corrected - error in sense s of rotation of propeller corrected 11-Oct Russian fuels TS-1 and RT added - all pages: TCDS reformatted - all pages: minor editorial changes - page 10 & 18, Item 21: Wheels and Tires data removed and related reference to Flight Manual added (Mod ). - page 16,, item 8.1 new fuel tank capacity and undrainable fuel capacity values added for aeroplanes with Mod Extended Range installed - page 20,, item 3 new fuel tank capacity and undrainable fuel capacity values added for aeroplanes with Mod Extended Range installed Administrative Section