Source: https://id.scribd.com/document/91607855/A50NM-Rev-7
Timestamp: 2019-09-23 06:58:35
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Matched Legal Cases: ['art 21', 'art 25', 'art 34', 'art 36', 'art 34', 'art 36', 'art 25']

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DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A50NM Revision 7 DASSAULT AVIATION FALCON 2000 FALCON 2000EX January 3, 2011
TYPE CERTIFICATE DATA SHEET No. A50NM This data sheet which is part of Type Certificate No. A50NM prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the US Federal Aviation Regulations. Type Certificate Holder Dassault Aviation 9 rond Point des Champs Elyses 75008 PARIS FRANCE
The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of manufacture is FAR Sections 21.183(c) or 21.185(c). The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 exported from countries other than the country of manufacture (e.g. third party country) is FAR 21.183(d) or 21.185(b). Notwithstanding that the FAR referenced in the above paragraph does not specifically address or require a foreign civil airworthiness authority certification, such certification is the only practical way for an applicant to show, and the Federal Aviation Administration (FAA) to find conformity to the FAA-approved type design and conditions for safe operation. Additional guidance is contained in FAA Advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States. I. Model Falcon 2000 (Transport Category) approved February 2, 1995 (a) Basic Model Definition Engines 2 engines. CFE Company, Model CFE 738-1-1B (see NOTE 3b) Static, Standard, Sea Level Take-off (5 min) Maximum Continuous
5,725 lb 5,560 lb
(2,547 daN) (2,474,daN)
Maximum Steady State Rotor Speeds Low pressure rotor (N1) High pressure rotor (N2) 5 minutes Continuous
Page Revision Page Revision 1 7 17 6 2 18 6 3 19 6 4 1 5 3 6 7 6 8 3 9 6 10 7 11 4
RPM 9,400 (96.7%) RPM 28,000 (106%) RPM 27,709 (104.9%)
12 7 13 4 14 6 15 6 16 6
(contd) Turbine Interstage Temperature Limits Ground starting Air starting Maximum take-off (5 min) Maximum take-off (2 min) Maximum continuous Airstart transient (10 sec) Airstart transient (2 sec) Oil Temperature Maximum continuous Minimum continuous Maximum transient (3 min) Fuel Pump Inlet Pressure Minimum Maximum Oil Pressure Idle Normal operating range Maximum transient (3 min) 815 C 864 C 877 C 890 C 861 C 890 C 1000 C
138 C 30 C 155 C
5 psi above true vapor pressure 50 psig
30-85 psig 60-85 psig 100 psig (may be exceeded for 2.5 min. in case of a cold start (temp < 0 C))
Thrust reverser use is not approved, unless Dassault Aviation change M3B has been incorporated. Allied Signal Model GTCP36-150 (F2M) Limitation Maximum operating starting altitude Maximum N1 (%) Exhaust gas temperature, Steady Exhaust gas temperature, Starting Maximum oil temperature Minimum oil pressure
35,000 ft 110 746 C 974 C 163 C 35 psi
Operation of the APU with passengers in the cabin and without crew member monitoring is not authorized. Airspeed Limits Unless otherwise stated, speeds are indicated airspeeds VMO (Maximum Operating) 350 kt at sea level, 370 kt at 10,000 ft with straight line variation between those points. 370 kt from 10,000 to 25,000 ft MMO (Maximum Operating) M = 0.862 from 25,000 to 38,000 ft 0.862 at 38,000 ft, 0.85 at 42,000 ft with straight line variation between those points 0.85 above 42,000 ft
Airspeed Limits (contd) VA (Maneuvering) VFE (Slat and Flap Speeds) Slats + Flaps 10 Slats + Flaps 20 Slats + Flaps 40 VLO (Landing Gear Operation) MLO VLE (Landing Gear Extended) MLE VMC (Minimum Control Speed) Flight Windshield Wiper Operation Direct Vision Window 198 kt
200 kt 160 kt 160 kt 190 kt 0.70 245 kt 0.75
90 kt 215 kt 215 kt
a. Without Option M57 Weight (lb) Forward Limit (% MAC) 36,000 16.7 33,000 14 28,660 or less 14 b. With Option M57 Weight (lb) Forward Limit (% MAC) 36,500 17.2 33,000 14 28,660 or less 14 Straight line variation between points. Gear retraction has negligible effect on CG range.
Rearward Limit (% MAC) 26.2 32.5
Rearward Limit (% MAC) 25.8 32.5
Datum is 25% of mean aerodynamic chord (MAC) which coincides with fuselage station FS + 400.43 in (Fuselage station reference +0 is the forward end of the airplane nose cone). 113.69 in
Mean Aerodynamic chord (MAC) Length Zero percent MAC is at FS +372.01 in Leveling Means
Standard bubble type level to be installed on the passenger seat tracks
Weight Limitations Maximum ramp Maximum take-off Maximum landing Maximum zero fuel Minimum flight at 14% CG at 32.5% CG Minimum Crew Maximum Passenger Seats 2 - Pilot and copilot
Without Option M57 36,000 lb 35,800 lb 33,000 lb 28,660 lb 23,075 lb 20,100 lb
With Option M57 36,500 lb 36,500 lb 33,000 lb 28,660 lb 23,075 lb 20,100 lb
19 - limited by emergency exit requirements of Federal Aviation Regulations 25.807(c)
0 - Without passenger provision but incorporating Dassault Ferry flight configuration : M0054.
Baggage compartment (not to exceed 61.4 lb per sq ft)
Nominal - Refer to weight and balance report of each airplane for exact capacity Refer to NOTE 1(b) for data on unusable system fuel and oil Usable Fuel LH outboard wing LH inboard wing LH center wing box LH Feeder tank RH outboard RH inboard wing RH center wing box RH feeder tank Total Usable Total Fuel US Gallons 348.4 213.7 216.9 127 349.2 214.1 217.4 127.3 1,814.0 1830.3 Pounds 2,334 1,432 1,453 851 2,340 1,435 1,457 853 12,155 12,259 Arm (in) 22.64 -27.68 -37.76 -16.34 22.64 -27.68 -37.76 -57.87
Fuels conforming to General Electric specification No. D50TF2, current revision See NOTE 4 for fuel additives The above mentioned fuels and additives are also suitable for the APU Maximum 50 psi
Pressure Fueling Oil Capacity (each engine)
Refer to NOTE 1(b) for data on unusable system fuel and oil Usable 0.55 US gallon Total 1.25 US gallon Oil conforming to General Electric Specification No. D50TR1, or Allied Signal oil Specification EMS 53110, current revision See NOTE 5 47,000 ft Elevator Rudder Aileron Down 16 Right 29 Up 2520 Up 20 Left 29 Down 2450
Maximum Operating Altitude Control Surface Movements
Flaps Control Surface Movements (contd) Airbrakes
Inboard up 68 Center up 50 Outboards up 37 Wing slats Down 30 Stabilizer Electrical stops AND 2 ANU 10 Mechanical stops AND Max 230 ANU Max 1030 Structural stops AND Min 240 ANU Min 11 Rigging tolerances are included in Maintenance Manual
II. Model FALCON 2000EX (Transport Category Airplane) approved March 21, 2003
(a) Basic Model Definition
The Falcon 2000EX is defined by Dassault modification M1802 and differs from the Falcon 2000 in the following major respects: (i) Pratt &Whitney Canada Engines PW308C replace CFE 738-1-1B engines; (ii) New forward and aft fuel tanks are added, (iii) New main and nose landing gear, (iv) New tires and brakes Engines 2 engines. (PRATT & WHITNEY Canada) Model PW308C Turbofan (see NOTE 3b) Static, Standard, Sea Level Take-off (5 min) Maximum Continuous
6,998 lb 6,998 lb
(3,114 daN) (3,114 daN)
Maximum Steady State Rotor Speeds Low pressure rotor (N1) High pressure rotor (N2) Turbine Interstage Temperature Limits Ground start Air start Normal Takeoff (5 min.) Maximum take-off (5 min) Maximum continuous Restarting Max. (air start/ground start) Transient (20 sec) Oil Temperature Maximum Minimum takeoff/ in-flight Maximum transient (90 sec.) Starting (minimum) Fuel Pump Inlet Pressure Minimum Maximum
RPM 10,660 (102.5%) RPM 27,316 (102%)
950 C 950 C 860 C 875 C 860 C 500 C/ 340 C 885 C
135 C 27 C/ 16 C 143 C -40 C
(SEE ENGINE INSTALLATON MANUAL) (SEE ENGINE INSTALLATION MANUAL)
Engine Limits (contd) Oil Pressure Operating Range Minimum at Idle Transient (20 sec.) Transient (90 sec.) Cold start: during starting Thrust Reversers APU
36 to 100 psi 20 psi 0 to 220 psi 10 to 220 psi 240 psi
Thrust reverser use is approved only on the ground. Allied Signal Model GTCP36-150 (F2M) Limitation Maximum operating/starting altitude Maximum N1 (%) Exhaust gas temperature, Steady Exhaust gas temperature, Starting Maximum oil temperature Minimum oil pressure
Operation of the APU with passengers in the cabin and without crew member monitoring is not authorized. Airspeed Limits Unless otherwise stated, speeds are indicated airspeeds VMO (Maximum Operating): 350 kt at sea level, 370 kt at 10,000 ft with straight line variation between those points. 370 kt from 10,000 to 25,000 ft MMO (Maximum Operating): 0.862 from 25,000 to 38,000 ft 0.862 at 38,000 ft, 0.85 at 42,000 ft with straight line variation between those points 0.85 above 42,000 ft VA (Maneuvering) VFE (Slat and Flap Speeds) Slats + Flaps 10 Slats + Flaps 20 Slats + Flaps 40 VLO (Landing Gear Operation) MLO VLE (Landing Gear Extended) MLE 198 kt
200 kt 190 kt 180 kt 190 kt 0.70 245 kt 0.75
Airspeed Limits (contd) VMC (Minimum Control Speed) Flight Windshield Wiper Operation Direct Vision Window Opening CG Range (Gear Extended) 90 kt 215 kt 215 kt
Weight (lb) Forward Limit (% MAC) 40,900 15.7 38,300 14 28,660 or less 14 Straight line variation between points. Gear retraction has negligible effect on CG range.
Rearward Limit (% MAC) 23.4 26.0 32.5
Mean Aerodynamic chord (MAC) Length Zero percent MAC is at FS +372.01 in Leveling Means Weight Limitations (Maximums)
Standard bubble type level to be installed on the passenger seat tracks Without M1826 (serial no.1 only) With M1826 and with M1842 Taxi and Ramp 40,900 lb 41,500 lb 42,400 lb Take-off 40,700 lb 41,300 lb 42,200 lb Landing 38,300 lb 39,300 lb 39,300 lb Zero fuel 29,700 lb 29,700 lb 29,700 lb Minimum flight at 14% CG 23,444 lb at 32.5% CG 21,149 lb 2 - Pilot and copilot 19 - limited by emergency exit requirements of Federal Aviation Regulations 25.807(c) Baggage compartment (not to exceed 61.4 lb per sq ft) 1,600 lb
Minimum Crew Maximum Passenger Seats
Nominal - Refer to weight and balance report of each airplane for exact capacity Refer to NOTE 1(b) for data on unusable system fuel and oil Without M1826 applied (serial no. 1 only) Usable Fuel LH wing+1/2 center wing box RH wing+1/2 center wing box Rear Tank Front Tank Total Usable Total Fuel US Gallons 911 911 244 329 2,395 2,407 Pounds 6,105 6,105 1,630 2,205 16,045 16,127
Fuel Capacity (contd) With M1826 applied (serial no. 2 and on) Usable Fuel LH wing+1/2 center wing box RH wing+1/2 center wing box Rear Tank Front Tank Total Usable Total Fuel US Gallons 909 912 293 383 2,497 2,509 Pounds 6,092 6,112 1,962 2,564 16,730 16,812
Fuels and additives conforming with the specifications listed in the applicable P&WC Maintenance Manual are approved. See NOTE 4 for fuel additives. The above mentioned fuels and additives are also suitable for the APU Fuel anti-icing must be used for fuel temperature below 50 C
Refer to NOTE 1(b) for data on unusable system fuel and oil Usable 0.49 US gallon Total 2.4 US gallon Oils conforming to the Specifications listed in the applicable P&WC Maintenance Manual (P/N 30C3882) are approved 47,000 ft Elevator Rudder Aileron Flaps Airbrakes Down 16 Up 20 Right 29 Left 29 Up 2520 Down 2450 Down 40 Inboard up 68 Center up 50 Outboards up 37 Wing slats Down 30 Stabilizer Electrical stops AND 2 ANU 10 Mechanical stops AND Max 230 ANU Max 1030 Structural stops AND Min 240 ANU Min 11 Rigging tolerances are included in Maintenance Manual
(b) Falcon 2000EX EASy Definition (Approved June 21, 2004)
EASy designation for Falcon 2000EX does not correspond to a model designation. This is only a commercial designation for airplanes on which Major modification numbers M1691, M1745, and M1504 have been embodied.
Major Change Modification number M1691 to the Falcon 2000EX consists of the installation of an Enhanced Avionics System (EASy) based on the Honeywell Primus EPIC product line. This system architecture is mainly built around 2 cabinets called Modular Avionics Units (MAU), 2 Modular Radio Cabinets (MRC), 2 Audio panels, 2 reversionary panels and 4 14.1 inch Liquid Crystal Displays. The pilots have access to the system using the 2 CCDs with multipurpose knob, menu pushbutton, display switch, action pushbuttons and trackball, 2 alphanumeric keyboards and the hard controls. M1745 installs an Oxygen system electro-pneumatic altimetric controller"
M1504 installs an "All falcon Common pressurization system"
M1691, M1745, and M1504 are basic on all Falcon 2000EX aircraft serial numbers 6, 28 and subsequent.
All parameters listed in the preceding sub-section (a) for the basic Falcon 2000EX remain valid for airplanes which incorporate M1691, M1745 and M1504. (c) Falcon 2000DX Definition (Approved October 3, 2007) The DX definition of the Falcon 2000EX does not correspond to a model designation. The Falcon 2000DX is only a commercial designation for Falcon 2000EX airplanes in the EASy configuration on which modifications M3000 and M3001 are installed at production. Modification M3000 defines the airplane and reduces the fuel tank capacity. Modification M3001 installs a new fuel quantity indication system. M3000 and M3001 are basic on all Falcon 2000EX airplanes in the EASy configuration starting with serial number 601 and subsequent. All parameters listed in the preceding sub-section (b) above for the Falcon 2000EX EASy remain valid for airplanes which incorporate M3000 and M3001, except for the following useable fuel.
Front Tank 189 US Gallons Rear Tank 183 US Gallons
1,268 lbs 1,224 lbs
(d) Falcon 2000LX Definition (Approved April 29, 2009) The LX definition of the Falcon 2000EX does not correspond to a model designation. The Falcon 2000LX is only a commercial designation for Falcon 2000EX airplanes in the EASy configuration on which modifications M2846 and M3229 are installed at production. Modification M2846 incorporates API winglets on the airplane and M3229 installs new slats. All parameters listed in the preceding sub-section (b) above for the Falcon 2000EX EASy remain valid for airplanes which incorporate M2846 and M3229.
Data Pertinent to all Models Manufacturer Serial Number Eligible A French "Certificat de Navigabilit pour Exportation" endorsed as noted under "Import Requirements" must be submitted for each individual aircraft for which application for US certification is made. Serial Numbers: For FALCON 2000: Aircraft serial number 1 and up For FALCON 2000EX: Aircraft serial number 1 through 5 and 7 through 27. Serial numbers 6, 28 and subsequent include M1691, M1745, and M1504 as standard (F2000EX EASy definition). Aircraft serial number 601 and subsequent include M3000 and M3001 as standard (F2000DX definition). 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 Direction Generale de l'Aviation Civile (D.G.A.C.) of France on behalf of the European Community. The Export C of A should contain the following statement: The aircraft covered by this certificate has been examined, tested, and found to conform with Type Design approved under U.S. Type Certificate No. A50EU and to be in a condition for safe operation. (a) For FALCON 2000 (basic model):
1. FAR, Part 25 as amended by Amendment 25-1 through 25-69. In addition, Dassault Aviation has elected to comply with amendments 25-71 for 25.365(e), 25-72 for 25.783(g) and 25.177; 25-75 for 25.729(e); 25-79 for 25.811(e)(2) and 25-80 for 25.1316 2. FAR Part 34, original issue (Fuel Venting and Exhaust Emissions) 3. FAA, Part 36 as amended by amendment 36-1 through 36-20 4. FAA, Special Conditions: 25-ANM-90 - High Altitude Operation 25-ANM-91 - High -Intensity Radiated Fields 25-ANM-94 - Automatic Takeoff Thrust Control System 5. FAA Exemption No. 7104A (for side facing sofa) For precision approach and landings, the applicable technical requirements are complemented by FAA Advisory Circulars (AC) 120-29 and AC 120-28(c) For the automatic flight control system, the applicable technical requirements are complemented by AC 25.1329-1A for cruise. Equivalent safety findings exist with respect to the following requirements: Design gust criteria, (refer to Issue Paper (IP) A-5) Use of the 1-g stall speeds instead of minimum speed in the stall as a basis for determining compliance (refer to IP F-1) Rejected take-off and landing performance (refer to IP F-3) N2 Digital Indication (refer to IP P-10) Flight Critical Thrust Reverser Certification (refer to IP P-7) Compliance has been shown to the following optional requirement: Ditching, FAR 25.801 Ice Protection FAR 25.1419 Type Certificate A50NM issued February 2, 1995 Reference date for type certification: November 30, 1989 (b) For Falcon 2000EX (1) For parts of the airplane not changed or not affected by the modifications: Unchanged from basic Falcon 2000 (2) For those parts of the airplane that are changed or are affected by the modifications M1802, M1803, M1804, M1805: The following sections of 14 CFR 25 as amended by amendments 25-1 through 25-98 apply per the FAA derivative aircraft process FAA Order 8110.4B to the changes and areas affected by the changes for the Falcon 2000EX: Subpart B Flight: All the paragraphs are applicable at amendment 25-98 except the following which are applicable as modified in Equivalent Level of Safety Finding Issue
Paper F-4 titled Use of 1-g Stall Speeds Instead of Minimum Speed in the Stall as a Basis for Determining Compliance 25.103, 25.107, 25.111, 25.119, 25.121, 25.125, 25.143, 25.145, 25.147, 25.149, 25.161, 25.175, 25.177, 25.181, 25.201, 25.207, 25.231, 25.233, 25.237 Subpart C Structure: All the paragraphs are applicable at amendment 25-98 Subpart D Design and Construction: The following paragraphs are applicable at amendment 25-98: 25.601 to 25.703, 25.721, 25.723, 25.729, 25.801, 25.863 to 25.869 The following paragraphs are applicable as modified by Equivalent Level of Safety Issue Paper F-4 titled Use of 1-g Stall Speeds Instead of Minimum Speed in the Stall as a Basis for Determining Compliance: 25.735, 25.773 Subpart E Powerplant: All the paragraphs are applicable at amendment 25-98 except the following which is applicable as modified in Equivalent Level of Safety Finding Issue Paper F-4 titled Use of 1-g Stall Speeds Instead of Minimum Speed in the Stall as a Basis for Determining Compliance 25.1001 Subpart F Equipment: The following paragraphs are applicable at amendment 25-98: 25.1301, 25.1305 to 25.1322, 25.1337, 25.1431 The following paragraphs are applicable as modified by Equivalent Level of Safety Issue Paper F-4 titled Use of 1-g Stall Speeds Instead of Minimum Speed in the Stall as a Basis for Determining Compliance: 25.1323, 25.1325, 25.1587 Subpart G Operating Limitations and Information: All the paragraphs are applicable at amendment 25-98 except the following: 25.1515, 25.1522, 25.1523, 25.1525, 25.1529, 25.1531, 25.1547, 25.1561 (3) FAR Part 34, original issue (Fuel Venting and Exhaust Emissions) (4) FAA, Part 36 as amended by amendment 36-1 through 36-24 (5) FAA, Special Conditions: 25-ANM-90 - High Altitude Operation
25-ANM-91 - High -Intensity Radiated Fields 25-ANM-94 - Automatic Takeoff Thrust Control System (6) FAA Exemption No. 8007A (for side facing sofa) (7) Equivalent safety findings according to 14 CFR 21.21(b)(1) for the following subjects: 25.103 & related paragraphs, 1-G Stall Speeds (documented in TAD ELOS Memo AT0021IB-T-F-4) Section 933(a)(1)(ii): Reversing Systems (documented in TAD ELOS Memo AT0012IB-T-P-12) 25.1203(a) Fire Detector System (documented in TAD ELOS Memo AT0021IB-T-P-15) (8) Miscellaneous: For precision approach and landings, the applicable technical requirements are complemented by FAA Advisory Circulars (AC) 120-29 and AC 12028(c) For the automatic flight control system, the applicable technical requirements are complemented by AC 25.1329-1A for cruise. Reference date of application for amendment to type certificate is January 7, 2000.
(c) For FALCON 2000EX airplanes incorporating Dassault modifications M1691, M1745, and M1504 (Falcon 2000EX EASy definition):
(1) For parts of the airplane not changed or not affected by the modifications: Unchanged from basic Falcon 2000EX (2) For those parts of the airplane that are changed or are affected by the modifications M1691, M1745, and M1504: The following sections of 14 CFR 25 as amended by amendments 25-1 through 25-98 apply per the FAA derivative aircraft process FAA Order 8110.4B to the changes and areas affected by the changes for the Falcon 2000EX EASy definition: Subpart B Flight: 25.207 : Stall warning Subpart C Structure: 25.581 : Lightning protection Subpart D Design and Construction: 25.601 : General 25.611 : Accessibility provisions 25.631 : Bird strike damage 25.671(b)(c) : Control systems : general 25.672 : Stability augmentation and automatic and power-operated systems
25.677(b) : Trim systems 25.699 : Lift and drag device indicator 25.703 : Take-Off warning systems 25.729(e) : Retracting mechanism 25.771 (a) (c) (e) : Pilot compartment 25.773(a)(d) : Pilot compartment view 25.777 (a)(b)(c)(d)(e)(f) : Cockpit controls 25.783(e) : Doors 25.789(a) : Retention of items of mass in passenger and crew compartments and galleys 25.791(a)(b) : Passenger information signs and placards 25.812(f) : Emergency lighting 25.841(b)(5)(b)(6) : Pressurised cabins 25.863(c) : Flammable fluid fire protection 25.869(a) : Fire protection : systems Subpart E Powerplant: 25.901 (c) : Installation 25.903 (b) and (d)(2) : Engines 25.1141(a) and (f) : Powerplant controls- General 25.1143(a), (b) and (c) : Engine controls 25.1145(a)(b) : Ignition switches 25.1155 : Reverse thrust and propeller pitch settings below the flight regime 25.1189(f) : Shutoff means 25.1203 (b)(2)(b)(3)(d) : Fire-detector system Subpart F Equipment: 25.1301 : Function and Installations 25.1303 : Flight and Navigation Instruments 25.1305 : Powerplant Instruments 25.1307(c)(d)(e) : Miscellaneous equipments 25.1309 : Equipment, systems and installations 25.1316 : System lightning protection 25.1321 : Arrangement and visibility 25.1322 : Warning, Caution and advisory lights 25.1323 : Airspeed indicating system 25.1325(a)(c)(d)(e)(f)(g) : Static pressure systems 25.1326 : Pitot heat indication systems 25.1327 : Magnetic direction indicator 25.1329 : Automatic pilot system 25.1331 : Instruments using a power supply 25.1333 : Instrument systems 25.1335 : Flight director systems 25.1337(b)(d) : Powerplant instruments 25.1351 : Electrical Systems and Equipment - General 25.1353 : Electrical equipment and installations 25.1355 : Distribution system 25.1357 : Circuit protective devices 25.1381 : Instrument lights 25.1419(c) : Ice protection 25.1431 : Electronic equipment 25.1435 (a)(2) : Hydraulic systems 25.1457 : Cockpit voice recorders 25.1459 : Flight recorders
Subpart G Operating Limitations and Information: 25.1501(b)(c) : General 25.1523 : Minimum flight crew 25.1529 : Instructions for continued airworthiness 25.1541 : Markings and placards - General 25.1543(b) : Instrument markings : General 25.1545 : Airspeed limitation information 25.1547 : Magnetic direction indicator 25.1549 : Powerplant instruments 25.1551 : Oil quantity indicator 25.1553 : Fuel quantity indicator 25.1555 : Control markings 25.1563 : Airspeed placard 25.1581 : Airplane flight manual General 25.1585(a)(b)(d)(e) : Operating procedures
(d) For FALCON 2000EX EASy airplanes incorporating Dassault modifications M3000 and M3001 (Falcon 2000DX definition):
(e) For FALCON 2000EX EASy airplanes incorporating Dassault modification M2846 (Falcon 2000LX definition):
(1) For parts of the airplane not changed or not affected by the modifications: Unchanged from basic Falcon 2000EX EASy (2) For those parts of the airplane that are changed or are affected by the modification M2846:
Based on the application date of September 14, 2006, for Modification M2846, under the provisions of Federal Aviation Regulation 14 CFR 21.101, the applicable type certification standards for the modification to the Model Falcon 2000EX series are as follows: 14 CFR part 25, effective February 1, 1965, including Amendments 25-1 through 25-117. The following are the applicable regulations: Subpart A General 25.1 Applicability. 25.2 Special retroactive requirements. Subpart B Flight 25.21 Proof of compliance. 25.23 Load distribution limits. 25.25 Weight limits. 25.27 Center of gravity limits. 25.29 Empty weight and corresponding center of gravity. 25.31 Removable ballast. 25.101 General. 25.103 Stall speed. 25.105 Takeoff. 25.107 Takeoff speeds. 25.109 Accelerate-stop distance. 25.111 Takeoff path. 25.113 Takeoff distance and takeoff run.
25.115 25.117 25.119 25.121 25.123 25.125 25.143 25.145 25.147 25.149 25.161 25.171 25.173 25.175 25.177 25.181 25.201 25.203 25.207 25.237 25.251 25.253 25.255
Takeoff flight path. Climb: general. Landing climb: All-engines-operative. Climb: One-engine-inoperative. En route flight paths. Landing. General. Longitudinal control. Directional and lateral control. Minimum control speed. Trim. General. Static longitudinal stability. Demonstration of static longitudinal stability. Static lateral-directional stability. Dynamic stability. Stall demonstration. Stall characteristics. Stall warning. Wind velocities. Vibration and buffeting. High-speed characteristics. Out-of-trim characteristics.
Subpart C Structure 25.301 Loads. 25.303 Factor of safety. 25.305 Strength and deformation. 25.307 Proof of structure. 25.321 General. 25.331 Symmetric maneuvering conditions. 25.333 Flight maneuvering envelope. 25.335 Design airspeeds. 25.337 Limit maneuvering load factors. 25.341 Gust and turbulence loads. 25.343 Design fuel and oil loads. 25.345 High lift devices. 25.349 Rolling conditions. 25.351 Yaw maneuver conditions. 25.367 Unsymmetrical loads due to engine failure. 25.373 Speed control devices. 25.391 Control surface loads: General. (d)(e) 25.395 Control system. 25.427 Unsymmetrical loads. 25.445 Auxiliary aerodynamic surfaces. (a) 25.457 Wing flaps. 25.459 Special devices. 25.471 General. (a)(b) 25.473 Landing load conditions and assumptions. (a)(b)(c)(e) 25.479 Level landing conditions. 25.493 Braked roll conditions. 25.495 Turning. 25.519 Jacking and tie down provisions. (c) 25.571 Damage-tolerance and fatigue evaluation of structure. (a)(b)(e) 25.581 Lightning protection. Subpart D Design and Construction 25.601 General. 25.603 Materials. 25.605 Fabrication methods. 25.607 Fasteners.
25.609 25.611 25.613 25.619 25.621 25.623 25.625 25.629 25.651 25.672 25.703 25.863 25.869
Protection of structure. Accessibility provisions. Material strength properties and material design values. Special factors. Casting factors. Bearing factors. Fitting factors. Aeroelastic stability requirements. Proof of strength. Stability augmentation and automatic and power-operated systems. Takeoff warning system. Flammable fluid fire protection. (a)(b) Fire protection: systems. (a)(4)
Subpart E Powerplant 25.954 Fuel system lightning protection. 25.981 Fuel Tank Ignition Prevention (a)(b) 25.1011 Oil Systems; General (b) Subpart F Equipment 25.1301 Function and installation. 25.1309 Equipment, systems, and installations. 25.1316 System lightning protection. 25.1327 Magnetic direction indicator. 25.1329 Automatic pilot system. 25.1351 General. (a)(d) 25.1353 Electrical equipment and installations. (a)(b)(d) 25.1357 Circuit protective devices. (a) 25.1385 Position light system installation. 25.1387 Position light system dihedral angles. 25.1389 Position light distribution and intensities. 25.1391 Minimum intensities in the horizontal plane of forward and rear position lights. 25.1393 Minimum intensities in any vertical plane of forward and rear position lights. 25.1395 Maximum intensities in overlapping beams of forward and rear position lights. 25.1397 Color specifications. 25.1401 Anticollision light system. 25.1419 Ice protection. (introduction paragraph only) 25.1431 Electronic equipment. (a)(c)(d) 25.1443 Minimum mass flow of supplement oxygen. (b)(c) Subpart G Operating Limitations and Information 25.1501 General (b) 25.1503 Airspeed limitations: general. 25.1505 Maximum operating limit speed. 25.1507 Maneuvering speed. 25.1511 Flap extended speed. 25.1513 Minimum control speed. 25.1515 Landing gear speeds. 25.1517 Rough air speed, VRA. 25.1519 Weight, center of gravity, and weight distribution. 25.1527 Ambient air temperature and operating altitude. 25.1529 Instructions for Continued Airworthiness. 25.1531 Maneuvering flight load factors. 25.1533 Additional operating limitations. 25.1581 General. 25.1583 Operating limitations. 25.1585 Operating procedures. 25.1587 Performance information. Appendix A (Sec 25.1)
Appendix C Appendix G Appendix H Appendix H Appendix H Appendix H
(Sec 25.1) (Sec 25.1) (Sec 25.1) (Sec 25.2) (Sec 25.3) (Sec 25.4)
(3) Special conditions: The following Special Conditions are applicable to Modification M2846: a. Docket No. NM-100; Special Conditions No. 25-ANM-90 Dassault Aviation Model Falcon 2000 Airplane; High Altitude Operation. b. Docket No. NM-101; Special Conditions No. 25-ANM-91 Dassault Aviation Model Falcon 2000 Airplane; High Intensity Radiated Fields. (4) Equivalent Safety Findings: According to the provisions of 14 CFR 21.21(b)(1), the following subject has been identified as an equivalent safety findings.
a. Section 25.1419 Ice Protection (documented in TAD ELOS Memo TD0592IB-T-S-101)
(5) Exemptions: FAA Exemption No. 5991 (for side facing sofa).
The Direction Generale de l'Aviation Civile (D.G.A.C.) of France originally type certificated this aircraft under its type certificate Number 185. The FAA validated this product under U.S. Type Certificate Number A50NM. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the D.G.A.C.. Type Definition For the Falcon 2000, the type definition is DASSAULT AVIATION Drawing List 01-130 Ref. DGT 21172 Issue A For the Falcon 2000EX, the type definition is DASSAULT AVIATION document M1802-01-130 (DGT-F/NAV89793) Master Drawing Lists Definition of Falcon 2000EX results of the addition of Falcon 2000 definition plus application of M1802, M1803, M1804, M1805, M1820, M1838 and M2233. From aircraft s/n 2 and on, modification M1826 is applied resulting in an increase in fuel capacity and maximum weights. Definition of the Falcon 2000EX EASy is the result of the basic Falcon 2000EX definition plus application of M1691, M1745, and M1504. Definition of the Falcon 2000DX is the result of the basic Falcon 2000EX in the EASy definition plus application of M3000 and M3001. Definition of the Falcon 2000LDX is the result of the basic Falcon 2000EX in the EASy definition plus application of M2846 and M3229.
The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis) must be installed on the aircraft for certification. The lists of all equipment as well as optional equipment approved
by Direction Gnrale de l'Aviation Civile (DGAC) of France are contained in the documents: For the FALCON 2000, in memos Nos.: DTM 38-2000/90 (01-940) - Equipment list of the basic airplane DTM 38-0735/91 (01-941) - Equipment list of the standard option and other options
In addition, the aircraft must be operated in accordance with the DGAC approved FALCON 2000 Airplane Flight Manual, document DTM 537 approved February 2, 1995 For the FALCON 2000EX: M1802-01-940 (DGT-DTF/NAV81711) Equipment List Basis Aircraft In addition, the aircraft must be operated in accordance with the DGAC approved FALCON 2000EX Airplane Flight Manual, Document No. DGT84278 For the Falcon 2000EX EASy: M1691-01-101 (DGT-DTF/NAV 96502) - Equipment list for F2000EX EASy In addition, the aircraft must be operated in accordance with the Falcon 2000EX EASy Airplane Flight Manual, document DGT88898. For the Falcon 2000LX, the aircraft must be operated in accordance with the Falcon 2000EX EASy Flight Manual, document DGT88898 with Supplement No. 8 included. Service Information Each of the documents listed below that contain a statement that it is approved by the European Aviation Safety Agency (EASA) - or for approvals made before September 28, 2003 - by the Direction Generale de l'Aviation Civile (D.G.A.C.) of France, are accepted by the FAA and are considered FAA approved. Additionally, approvals issued by Dassault Aviation under the authority of EASA approved Design Organization EASA.21J.051 - or for approvals made before September 28, 2003 - under the authority of DGAC Design Organization Approval No. No. F.JA.03 are considered FAA approved. These approvals pertain to the type design only. Dassault Aviation Service Bulletins, except as noted below, Structural repair manuals, Vendor manuals referenced in Dassault Aviation service bulletins Aircraft flight manuals, Repair Instructions. Note: Design changes that are contained in Dassault Aviation Service Bulletins and that are classified as Level 1 Major in accordance with either the US/Direction Generale de l'Aviation Civile (D.G.A.C.) of France or US/EASA Bilateral Aviation Safety Agreement Implementation Procedures for Airworthiness must be approved by the FAA.
NOTES NOTE 1 - Weight and Balance (a) Current weight and balance report including a list of equipment included in certificated empty weight, and loading instructions when necessary must be provided for each aircraft at its delivery. (b) The following must be included in the airplane empty weight: The total unusable fuel, 82 lb, plus The unusable engine oil, 4.1 US gallons, 34 lb, (drainable and trapped oil) at arm + 150 in, and The hydraulic fluid 83 lb at are + 127 in (c) The airplane must be loaded in accordance with the FALCON 2000 Loading Manual (DTM 541) or the FALCON 2000EX Loading Manual (DGT 65), as applicable and the CG must be within the specified limits at all times.
NOTE 2 - Reserved NOTE 3 - Service Life Limits and required Maintenance/Inspections (a) Airframe components which are life limited, and associated retirement times, are presented in DGAC approved chapter 5.40.00 of the FALCON 2000 and Falcon 2000EX Maintenance Manual, and must be replaced as indicated therein. (b) For the Falcon 2000: CFE 738-1-1B engine life limits, established for critical rotating components, are published in the approved Engine Light Maintenance Manual, Report Number 72.08.03, Airworthiness Limitation Section. For the Falcon 2000EX: PW308C engine life limits are listed in the Airworthiness Limitation Section of P&WC Maintenance Manual P/N 30C3882. (c) Required maintenance and inspections to maintain airworthiness based on involving reliability are presented in DGAC approved chapter 5.40.00 of the FALCON 2000 and Falcon 2000EX Maintenance Manuals. NOTE 4 - Fuel Specifications and Additives (a) For information concerning equivalent fuel specifications, see Airplane Flight Manual (b) Additives For the CFE 738 engines; PW308C engines; and GTCP 36-150 auxiliary power unit, the following additive limitations are approved. Anti-icing additives, conforming to AIR 3652 of MIL-I 27686 D or E (JP-4/JP-8) or to MIL-I 85470 (JP-5) or equivalent are approved for use in the fuel in amounts up to 0.15 per cent by volume. SOHIO BIOBOR JF biocide additive, or equivalent, is approved for use in fuel at a concentration not exceeding 270 PPM Anti-static additive is approved for use in fuel at a concentration not exceeding 1 PPM for SHELL ASA 3; and 3 PPM for STADIS 450 NOTE 5 - Qualified Oils (a) Engine: See CFE 738 Engine Installation Manual IM 75 550 for specific oils approved per the subject specification. (b) APU: Brand names of oils approved for use in the APU are listed in the GTCP36-150 Maintenance Manual NOTE 6 - The Model Falcon 2000 (incorporating M1251), Falcon 2000EX, and Falcon 2000EX EASy have been approved to operate in Reduced Vertical Separation Minimum (RVSM) airspace when the airplanes are operated in accordance with Airplane Flight Manual page 1-160-1. Continued airworthiness and operational approval aspects of RVSM must be constructed according to Advisory Circular (AC) 91RVSM, titled Approval of Aircraft and Operators for Flight in Airspace Above Flight Level (FL) 290 Where a 1,000 Foot Vertical Separation Minimum is Applied. ......END.....
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