飞机一般限制

航空发表于 2010-7-25 16:06:47

飞机一般限制
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航空发表于 2010-7-25 16:07:15

A project supported by AIRBUS and the CAAC Date of the module • Table of contents • Flight operations duties • European Applicable Regulation • General • General aircraft limitations • Payload Range • Operating limitations • In flight performance • One engine inoperative performance • Flight planning • weight and balance A project supported by AIRBUS and the CAAC Date of the module 1 - Limit load factors 2 - Maximum speed 3 - Minimum speed 4 - Other limitations ( environmental envelope and engine limitations ) 5 - Maximum structural weights Table of Contents A project supported by AIRBUS and the CAAC Date of the module 1 - Limit load factors 2 - Maximum speed 3 - Minimum speed 4 - Other limitations ( environmental envelope engine limitations ) 5 - Maximum structural weights Table of Contents A project supported by AIRBUS and the CAAC Date of the module  Aerodynamics loads nz (load factor) g m Acceleration m A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module  Manoeuvering limit load factors  - (JAR /FAR 25.1531, 25.333)  Flaps retracted or slats extended:  - 1 nz < + 2.5  Flaps and slats extended:  0 < nz < + 2 A project supported by AIRBUS and the CAAC Date of the module 1 - Limit load factors 2 - Maximum speed 3 - Minimum speed 4 - Other limitations ( environmental envelope engine limitations ) 5 - Maximum structural weights Table of Contents A project supported by AIRBUS and the CAAC Date of the module  Maximum operating limit speed (or Mach number) - VMO (or MMO) - (JAR/FAR 25.1505) Pressure Altitude CAS VMO = 350 MMO = 0.82 A 320 - 200 24 600 ft A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module  Maximum manoeuvering speed: VA -  (JAR/FAR 25.1507,25.335)  Maximum speed at which the flight controls can be fully deflected without structural damage VA full SPEED deflection A project supported by AIRBUS and the CAAC Date of the module  Maximum manoeuvering speed: VA - (JAR /FAR 25.1507) CAS VMO = 350 MMO = 0.82 A 320 - 200 24 600 ft VA M = 0.78 250 350 Pressure Altitude A project supported by AIRBUS and the CAAC Date of the module  Maximum flaps extended operating speeds: VFE (JAR/FAR 25.1511) F la p s le v e r p o s itio n E C AM in d ic a tio n S la ts p o s itio n F la p s p o s itio n V F E F lig h t p h a s e 1 1 8 0 2 3 0 A p p ro a c h 1 1 + F 1 8 1 0 2 1 5 T a k e o ff 2 2 2 2 1 5 2 0 0 A p p ro a c h T a k e o ff 3 3 2 2 2 0 1 8 5 L a n d in g A p p ro a c h T a k e o ff F U L L F u ll 2 7 3 5 1 7 7 L a n d in g A project supported by AIRBUS and the CAAC Date of the module  Maximum landing gear speeds: (JAR /FAR 25.1515)  VLE (In flight: landing gear extended): 280 kt/ M 0.67 available when the landing gear is in the fully extended position A project supported by AIRBUS and the CAAC Date of the module  Maximum landing gear speeds: (JAR/FAR 25.1515)  VLE (In flight: landing gear extended): 280 kt/ M 0.67  VLO RET: (landing gear operating: retraction) : 220 kt  VLO EXT: (landing gear operating: extension): 250 kt  Maximum tyre speed:  195 kt (ground speed) A project supported by AIRBUS and the CAAC Date of the module 1 - Limit load factors 2 - Maximum speed 3 - Minimum speed 4 - Other limitations ( environmental envelope engine limitations ) 5 - Maximum structural weights Table of Contents A project supported by AIRBUS and the CAAC Date of the module  Definition - Reference stall speed VSR (JAR 25.103)  VSR  Vs1g  Vs1g is the stall speed under load factor (nz) equal to 1: (The aeroplane can develop a lift equal to its weight) Remark: In JAR 25 VSR is expressed as: VCLMAX is the stall speed under a load factor equal to nzw Vs g mg oSCz 1  2  max zw CLMAX SR n V  V A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module  Vs1g Stall condition 1 n=1 No altitude loss Suitable for VsFAR < Vs1g A320,A330,A340,B777….  VsFAR Stall condition 2 n <1 Altitude loss Suitable for swept wing aircraft VsFAR < Vs1g A300,A310,B757,B767…. A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module  Minimum control speed, take off climb: VMCA - (JAR/FAR 25.149)  It is the calibrated airspeed, at which, when the critical engine is suddenly made inoperative; it is possible to maintain the control of the aeroplane (that engine remaining inoperative) and maintain straight flight with angle of bank of not more than 5° A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module Minimum control speed on the ground : VMCG - (JAR/FAR 25.149)  It is the calibrated airspeed, during the take off ,at which, when the critical engine is suddenly made inoperative; it is possible to maintain the control of the aeroplane with the use of the primary aerodynamics controls alone A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module 1 - Limit load factors 2 - Maximum speed 3 - Minimum speed 4 - Other limitations ( environmental envelope and engine limitations ) 5 - Maximum structural weights Table of Contents A project supported by AIRBUS and the CAAC Date of the module -5000 0 5000 10000 15000 20000 25000 30000 35000 40000 45000 -80 -60 -40 -20 0 20 40 60 ISA. ISA + 35°C Take off and landing 39 100 ft 8 000 ft A 320 - 200 Environmental envelop A project supported by AIRBUS and the CAAC Date of the module  Engine limitations - (JAR/FAR 25.1521) Example: CFM56 - 5A1 Operating Condition Time Limit EGT °C MAXIMUM ROTOR SPEED N1% N2% STARTING 725 MAX CONTINUOUS Continu 855 TAKE OFF and 5 mn (normal) 890 102 105 GO AROUND 10 mn (one engine out) 890 102 105 A project supported by AIRBUS and the CAAC Date of the module 1 - Limit load factors 2 - Maximum speed 3 - Minimum speed 4 - Other limitations ( environmental envelope engine limitations ) 5 - Maximum structural weights Table of Contents A project supported by AIRBUS and the CAAC Date of the module Structure Systems Propulsion Empty weight A project supported by AIRBUS and the CAAC Date of the module Empty weight Cabin equipment Crew Catering Dry operating weight (Dow) Basic weight (BW) A project supported by AIRBUS and the CAAC Date of the module Dow Traffic load Zero fuel weight (ZFW) Take-off weight (TOW) Landing weight Trip fuel Reserve A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module Parking Trip fuel Alternate fuel Touchdown Brakes release En route reserve Go around PROC DEP Alternate Holding DEST Taxi fuel A project supported by AIRBUS and the CAAC Date of the module  JAR OPS  Route: GREATER of (5% of the planned trip fuel or an amount subject to the approval of the authority) or (quantity to fly for 5 min at holding speed at 1500 ft above destination)  Alternate: Calculated to the most distant alternate airport  Holding: quantity to fly for 30 mn at holding speed at 1500 ft above the alternate airport  FAR 121 - international flight  Route: a quantity to fly during a period equivalent to 10% of the total flight time (departure/destination)  Alternate: idem  Holding: idem A project supported by AIRBUS and the CAAC Date of the module  Maximum weights  Maximum structural take-off weight: MTOW FAR/JAR 25: R/C= - 360ft/mn tow <= MTOW (1) A project supported by AIRBUS and the CAAC Date of the module  Maximum weights  Maximum structural take-off weight: MTOW  Maximum structural landing weight: MLW FAR/JAR 25: R/C = - 600ft/mn lw = tow - TF <= MLW or tow <= MLW + TF (2) A project supported by AIRBUS and the CAAC Date of the module  Maximum weights  Maximum structural take-off weight: MTOW  Maximum structural landing weight: MLW  Maximum zero fuel weight: MZFW mg A project supported by AIRBUS and the CAAC Date of the module  Maximum weights  Maximum zero fuel weight: MZFW Max efforts at the root for m = const when mWF=0 mg L/2 L/2 mWFg mWFg nz > 1 A project supported by AIRBUS and the CAAC Date of the module  Maximum weights  Maximum structural take-off weight: MTOW  Maximum structural landing weight: MLW  Maximum zero fuel weight: MZFW zfw <= MZFW tow <= MZFW + take-off fuel ( tow = zfw + take-off fuel ) (3) A project supported by AIRBUS and the CAAC Date of the module  Effects on fueling 1 -Wing tanks 2 - Fuselage tanks mg mFFg A project supported by AIRBUS and the CAAC Date of the module  Effects on fuel management 1 - Fuselage tanks 2 -Wing tanks mg A project supported by AIRBUS and the CAAC Date of the module  Effects on fuel management mg mFFg Opposite case when mWF = 0 zfw = dow + load + mFF <= MZFW A project supported by AIRBUS and the CAAC Date of the module  Maximum weights » Maximum structural take-off weight: MTOW » Maximum structural landing weight: MLW » Maximum zero fuel weight: MZFW » Maximum ground-taxiing weight: MGTW

忙盲忙 发表于 2010-7-28 08:56:38

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文刚发表于 2010-12-2 20:21:14

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dingzhili 发表于 2011-3-6 21:55:59

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guanshyy 发表于 2011-3-30 12:55:10

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airportcn 发表于 2011-5-17 11:25:34

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bocome 发表于 2011-7-31 09:43:06

Flight Crew Training Manual

sheikhcn 发表于 2011-8-15 15:22:29

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coindong 发表于 2011-10-9 17:08:50

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飞机一般限制

楼主辛苦啦！