CAP698 Performance Manual

Safety Regulation GroupCAP 698 CAA JAR-FCL Examinations Aeroplane Performance Manual Third Edition July 2006 www.caa.co.uk Safety Regulation Group CAP 698 CAA JAR-FCL Examinations Aeroplane Performance Manual Third Edition July 2006 www.caa.co.uk or for personal use. Printed copy available from: TSO.uk/bookshop E-mail: book.co. Gatwick Airport South. Civil Aviation Authority. Published by TSO (The Stationery Office) on behalf of the UK Civil Aviation Authority. Norwich NR3 1GN Telephone orders/General enquiries: 0870 600 5522 Fax orders: 0870 600 5533 www. for use within a company or organisation.caa. Aviation House. To use or reference CAA publications for any other purpose. but may not otherwise be reproduced for publication or for commercial gain.uk/publications. Copies of this publication may be reproduced as training material for students.uk Textphone: 0870 240 3701 . The latest version of this document is available in electronic format at www.orders@tso. ISBN 0 11790 653 0 First published August 1999 Second edition June 2001 Third edition July 2006 Third edition (corrected) September 2006 Enquiries regarding the content of this publication should be addressed to: Personnel Licensing Department.tso. RH6 0YR. where you may also register for e-mail notification of amendments. Safety Regulation Group.CAP 698 CAA JAR-FCL Examinations .co. please contact the CAA at the address below for formal agreement.co. West Sussex.Aeroplane Performance Manual © Civil Aviation Authority 2006 All rights reserved. PO Box 29. ) July 2006 July 2006 July 2006 July 2006 Section Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Section 4 Page 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 Date July 2006 (corr.) July 2006 (corr.) July 2006 (corr.) July 2006 July 2006 July 2006 July 2006 July 2006 July 2006 (corr.) Page iii .) July 2006 July 2006 July 2006 July 2006 (corr.) July 2006 July 2006 July 2006 (corr.) July 2006 July 2006 July 2006 (corr.) 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July 2006 July 2006 (corr.Aeroplane Performance Manual List of Effective Pages Section Page iii iv v vi Revision History Revision History Section 1 Section 1 Section 1 Section 1 Section 2 Section 2 Section 2 Section 2 Section 2 Section 2 Section 2 Section 2 Section 2 Section 2 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 3 Section 4 Section 4 Section 4 1 2 1 2 3 4 1 2 3 4 5 6 7 8 9 10 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 1 2 3 Date July 2006 (corr.) July 2006 (corr. Aeroplane Performance Manual INTENTIONALLY LEFT BLANK July 2006 Page iv .CAP 698 CAA JAR-FCL Examinations . Aeroplane Performance Manual Contents List of Effective Pages Revision History iii 1 Section 1 General Notes Aircraft Description Layout of Data Sheets Definitions Conversions 1 1 2 4 Section 2 Data for Single-Engine Piston Aeroplane (SEP1) General Considerations Take-Off Take-Off Climb En-Route Landing 1 1 6 8 9 Section 3 Data for Multi-Engine Piston Aeroplane (MEP1) General Considerations Take-Off Take-Off Climb En-route Landing 1 1 9 17 17 Section 4 Data for Medium-Range Jet Transport (MRJT1) General Considerations Take-Off Obstacle Clearance En-route Landing 1 7 35 39 45 July 2006 Page v .CAP 698 CAA JAR-FCL Examinations . Aeroplane Performance Manual INTENTIONALLY LEFT BLANK July 2006 Page vi .CAP 698 CAA JAR-FCL Examinations . Max continuous thrust limit box. Fig 3.10 – speed scale of barrier speed . 4.4 – associated conditions. 44 Correction Text of paragraph 2. 'crosswind component' added. Definitions and conversions have been rationalised and known errors have been corrected.Aeroplane Performance Manual Revision History 1st Edition August 1999 CAP 698.) after the page date. '800' corrected to '500'. Fig 4. some errors and omissions have been identified. Fig 3. The affected pages are identified by the word (corr. 2nd Edition The manual was reissued to incorporate CAA House Style.1 .2 and 3. 4. 43.) Revision History Page 1 . Fig 3.1 corrected. Fig 3. 3rd Edition (corrected) September 2006 Since the publication of the third edition. Fig 3. was produced to support training and examinations in JAR-FCL Subject 032 .Performance for Aeroplanes.5 – ROC scale. Figs 4.6 – Associated conditions. 'Inoperative engine feathered' added.2. 'reaction time' corrected to 'recognition time'. 3rd Edition July 2006 June 2001 This edition has been upgraded with digitised graphics.1.10 – 'obstacle speed' corrected to 'barrier speed'. The corrections are as follows: Section/Aircraft 2/SEP 2/SEP 3/MEP 3/MEP 3/MEP 3/MEP 3/MEP 4/MRJT 4/MRJT Page(s) 1 2 5/8 11 13 21/23 23 4 41.At base of graph.24. 'A/C Auto (High)' corrected to 'A/C OFF'.26 and 4. July 2006 (corr.CAP 698 CAA JAR-FCL Examinations .9 and 3.25. 42. CAA JAR-FCL Examinations Performance Manual. '90' changed to '82' and '66' changed to '68'.27. Correction to Example and Solution at paragraph 2. Aeroplane Performance Manual INTENTIONALLY LEFT BLANK July 2006 Revision History Page 2 .CAP 698 CAA JAR-FCL Examinations . Generic Aeroplanes Single-Engine Piston certificated under CS 23 (Light Aeroplanes) Performance Class B Multi-Engine Piston SEP1 certificated under CS 23 (Light Aeroplanes) Performance Class B MEP1 Medium-Range Jet Transport certificated under CS 25 (Large Aeroplanes) Performance Class A MRJT1 2.Aeroplanes 3 3.1 1.General Notes Page 1 . This data will include (but is not limited to) a list of abbreviations and some conversion factors.2 The data sheets in this manual are produced to support training and examinations in JAR-FCL Subject 032 .Mass and Balance . specifically. 2 2.CAP 698 CAA JAR-FCL Examinations .2 Aircraft Description The aeroplanes used in these data sheets are of generic types related to the classes of aeroplane on which the appropriate examinations are based.3 The same set of generic aeroplanes will be utilised in the following subjects: • 031 . A worked example will accompany each graph/table and will demonstrate typical usage.Performance .Performance for Aeroplanes.1 Layout of Data Sheets Each set of data sheets will consist of an introduction that will contain some pertinent information relating to the aircraft and the subject being examined. Candidates must select the correct class of aeroplane for the question being attempted. 3.1 2.Flight Planning and Monitoring . This will be followed by a selection of graphs and/or tables that will provide coverage suitable for the syllabus to be examined.Aeroplanes • 032 . The data contained within these sheets are for training and examination purposes only.Aeroplanes • 033 . are not to be used for the purpose of planning activities associated with the operation of any aeroplane in use now or in the future.Aeroplane Performance Manual Section 1 1 General Notes Introduction Important Notice 1. The data must not be used for any other purpose and.2 July 2006 Section 1 . The maximum permissible total mass of an aeroplane at the start of the take-off run. This may be given in metres or feet.CAP 698 CAA JAR-FCL Examinations . in the same units of measurement. Climb Gradient Elevation Gross Height Gross Performance Height International Standard Atmosphere (ISA) lAS Maximum Structural Landing Mass Maximum Structural Take-Off Mass July 2006 Section 1 . The maximum permissible total mass of an aeroplane on landing (under normal circumstances).92 inches or 760 mm. It may be obtained by setting the sub-scale of a pressure altimeter to 1013 hPa (29. as obtained from the formula:Gradient = Change in Height x 100% Horizontal Distance The vertical distance of an object above mean sea level. Gross height is used for calculating pressure altitudes for purposes of obstacle clearance and the height at which wing flap retraction is initiated. The average performance that a fleet of aeroplanes should achieve if satisfactorily maintained and flown in accordance with the techniques described in the manual. expressed as a percentage. The true height attained at any point in the take-off flight path using gross climb performance. of mercury). The vertical distance between the lowest part of the aeroplane and the relevant datum. A structure of assumed conditions relating to the change of pressure. Altitude The altitude shown on the charts is pressure altitude. or JAA or EASA documentation but are in common use.General Notes Page 2 . The ratio.Aeroplane Performance Manual 4 Definitions Definitions given in italics are not given in ICAO. temperature and density with height in the atmosphere. The airspeed is the reading obtained on a pitot-static airspeed indicator calibrated to reflect standard adiabatic compressible flow at mean sea level. This is the height in the International Standard Atmosphere at which the prevailing pressure occurs. g. temporary below average performance.CAP 698 CAA JAR-FCL Examinations .. provided the aeroplane is flown in accordance with the recommended techniques.B. The mass of an aeroplane.General Notes Page 3 . variations in piloting technique. etc. July 2006 Section 1 . Net Performance Outside Air Temperature (OAT or SAT) Take-Off Mass (TOM) TAS Total Air Temperature (TAT) N. The 'true airspeed' is the speed of the aeroplane relative to the undisturbed air. Net performance is the gross performance diminished to allow for various contingencies that cannot be accounted for operationally e. Net height is used to determine the net flight path that must clear all obstacles by the statutory minimum to comply with the Operating Regulations.Aeroplane Performance Manual Net Height The true height attained at any point in the take-off flight path using net climb performance. The static air temperature plus adiabatic compression (ram) rise as indicated on the Total Air Temperature indicator. Within these data sheets the term 'weight' should be considered to have the same meaning as 'mass'. The free air static (ambient) temperature. It is improbable that the net performance will not be achieved in operation. including everything and everyone contained within it. at the start of the take-off run. 454 = kg kg x 2.3 Lengths Feet (ft) to Metres (m) Feet x 0.205 = lb 5.546 = Litres US Gall x 3.CAP 698 CAA JAR-FCL Examinations .4 Distances Nautical mile (NM) to Metres (m) NM x 1852.Aeroplane Performance Manual 5 Conversions The following conversions. are satisfactory for use in JAR-FCL examinations in 030 subjects.0 = Metres July 2006 Section 1 .1 Mass conversions Pounds (lb) to Kilograms (kg) Kilograms (kg) to Pounds (lb) lb x 0.305 = Metres 5. based on those in ICAO Annex 5.2 Volumes (Liquid) Imperial Gallons to Litres (L) US Gallons to Litres (L) Imp. Gall x 4.General Notes Page 4 .785 = Litres 5. 5. 1.15.25 must not exceed TORA. c) Unless surfaces are available which permit a safe forced landing to be executed.Aeroplane Performance Manual Section 2 Data for Single-Engine Piston Aeroplane (SEP1) 1 1. there is no take-off climb requirement.1.1 below. which is not certificated under CS/FAR 25. 2. not exceed TODA July 2006 (corr.SEP1 Page 1 . The aeroplane.1 General Considerations Performance Classification The specimen aeroplane is a low wing monoplane with retractable undercarriage. not exceed ASDA iii) when multiplied by 1.) Section 2 . It is powered by a single reciprocating engine and a constant speed propeller. b) In instrument meteorological conditions except under special visual flight rules. is a land-plane classified in Performance Class B.3 Aeroplane Limitations Structural Limitations Maximum Take-Off Mass Maximum Landing Mass Maximum Runway Cross Wind 3650 lb 3650 lb 17 kt 2 2.1 Field Length Requirements a) When no stopway or clearway is available the take-off distance when multiplied by 1.CAP 698 CAA JAR-FCL Examinations . d) Above a cloud layer that extends below the relevant minimum safe altitude.1. As explained in paragraph 3. b) When a stopway and/or clearway is available the take-off distance must: i) not exceed TORA ii) when multiplied by 1.3. 1.1 Take-Off Requirements The only take-off requirement for a single engined aeroplane is for the Field Length as detailed in paragraph 2.2 General Requirements An operator shall not operate a single-engine aeroplane: a) At night. 1 Distance Calculation To determine the take-off distance: a) Select the graph appropriate to the flap setting. Parallel the grid lines to the take-off mass input. Parallel the grid lines to the wind component input. One with flaps up (Figure 2. These graphs are used in exactly the same manner. d) Continue horizontally right to the wind component reference line. b) Enter at the OAT.3 x 1. 2. f) Factorise for surface and slope.) Section 2 .2 x 1.2. c) From this point.1) and the other with flaps approach (Figure 2. Example: Flaps Up Aerodrome Pressure Altitude Ambient Temperature Take-Off Mass Wind Component Runway Slope Runway Surface Runway Condition Calculate: Take-Off Distance 5653 ft +15°C 3650 lb 10 kt Head 1.075 4821 ft July 2006 (corr.0 d) Take-off distance should be increased by 5% for each 1% upslope.CAP 698 CAA JAR-FCL Examinations .2 Use of Take-Off Graphs There are two take-off distance graphs. Continue horizontally right to read ground roll distance or proceed parallel to the grid lines to read total distance to 50ft obstacle (TOD). NOTE: The same surface and slope correction factors should be used when calculating TOR or ASD.Aeroplane Performance Manual c) If the runway surface is other than dry and paved the following factors must be used when determining the take-off distance in a) or b) above: Surface Type Grass (on firm soil) up to 20 cm Long Paved Condition Dry Wet Wet Factor x 1. No factorisation is permitted for downslope.5% Uphill Grass Wet Solution: Graphical Distance Surface Factor Slope Factor Take-Off Distance 3450 ft x 1.2).SEP1 Page 2 . travel horizontally right to the mass reference line. e) Proceed horizontally right to the obstacle reference line. Move vertically up to the aerodrome pressure altitude. 2.3 x 1. ......1 Take-Off Distance Flaps Up 7000 3650 3600 3400 3200 3000 2800 73 72 71 70 68 65 84 83 82 80 78 75 6000 IT LT E UD ft 5000 0 .Aeroplane Performance Manual Section 2 .......... DRY SURFACE MASS lb TAKE-OFF SPEED kt ROTATION 50 ft Figure 2.................ft 4000 July 2006 EXAMPLE OAT...................... 3450 ft TAKE-OFF SPEED AT: ROTATION... RETRACT AFTER POSITIVE CLIMB ESTABLISHED COWL FLAPS.........00 10 ISA . OPEN RUNWAY.......lb 3000 2800 30 20 10 0 WIND COMPONENT kt 0 50 OBSTACLE HEIGHT ft 0 DISTANCE .................................. 84 kt 8000 ASSOCIATED CONDITIONS POWER....................... 5653 ft TAKE-OFF MASS....................................................... FULL RICH FLAPS....3650 lb HEAD WIND COMPONENT........... PAVED................................... LEVEL...... UP LANDING GEAR.. 73 kt 50 ft...................... 10 kt GROUND ROLL....................... 1900 ft TOTAL DISTANCE OVER 50 ft OBSTACLE..........SEP1 Page 3 50 60 3600 -40 -30 0 40 -20 -10 10 20 30 OUTSIDE AIR TEMPERATURE ......................................°C 3400 3200 MASS .......................... TAKE-OFF POWER SET BEFORE BRAKE RELEASE MIXTURE....................CAP 698 P S RE SU REFERENCE LINE A RE GU INT E RM IDE L INE ED IAT SN E OT OB A ST AC PPLI C L E HE ABLE IG FO HT R S HE AD W 00 80 REFERENCE LINE REFERENCE LINE T AI LW IN D IN D 00 60 0 400 0 200 SL 3000 2000 1000 CAA JAR-FCL Examinations .............................................................. 15°C PRESSURE ALTITUDE.......................... 2 1.3 2605 ft TODA 4600 ft 1. The factors to be considered are those of slope. d) Now travel horizontally left to the appropriate wind component input. ASDA 4470 ft. c) Enter the right vertical axis with the shortest available de-factored distance at the 50ft height. above.2 1. TORA Given Distances Slope Factor Surface/Condition Factor Regulation Factor De-factored Distance 4250 ft 1. draw a horizontal line left through the mass grid. a) Enter at the ambient temperature. surface. b) From this point. f) From the position marked in b).1 1.0 3220 ft ASDA 4470 ft 1. above.CAP 698 CAA JAR-FCL Examinations . Parallel the grid lines to the wind component reference line. condition and regulation.2 1. travel horizontally right to the mass reference line.1 1.1 1. Parallel the grid lines down to the reference line. Move vertically to the aerodrome pressure altitude. TODA 4600 ft Calculate the Field Length Limited TOW. Only the take-off distance graph is used but the right vertical axis is entered with shortest available de-factored distance. drop vertically to read the field length limited TOW. parallel the grid lines to intersect the horizontal line from e). Mark this position with a pencil.Aeroplane Performance Manual 2.SEP1 Page 4 .15 3030 ft Field Length Limited TOW 3530 lb Using 2605 ft July 2006 Section 2 . Example: Flaps Approach 5653 ft +15°C 10 kt Head 2% Uphill Grass Dry Aerodrome Pressure Altitude Ambient Temperature Wind Component Runway Slope Runway Surface Runway Condition TORA 4250 ft. e) From this point.2 Mass Calculation To calculate the field length limited take-off mass it is necessary to apply the requirements of JAR-OPS. g) At the intersection.2. .......................................................................... 15°C PRESSURE ALTITUDE...............2 Take-Off Distance Flaps Approach 5000 TI AL DE TU ft HE 3000 ISA ......... APPROACH LANDING GEAR....................... PAVED................. 5653 ft TAKE-OFF MASS...............................................................................CAP 698 REF LINE T AIL WI ND REF LINE REF LINE P 00 80 0 600 0 400 0 200 L S 2000 1000 0 30 40 50 60 3600 3400 3200 MASS lb 3000 2800 0 10 20 30 WIND COMPONENT kt 0 50 OBSTACLE HEIGHT ft -40 -30 -20 -10 0 10 20 CAA JAR-FCL Examinations .............. DRY SURFACE MASS lb TAKE-OFF SPEED kt ROTATION 50 ft 3650 3600 3400 3200 3000 2800 67 67 66 65 64 62 77 77 76 75 73 71 6000 Figure 2........... 2200 ft TAKE-OFF SPEED AT: ROTATION.................................................... LEVEL.. 65 kt 50 ft..................... TAKE-OFF POWER SET BEFORE BRAKE RELEASE MIXTURE..... 75 kt 7000 EXAMPLE POWER..00 10 AD WI ND GU INT IDE ER LI M NE ED SN IAT OT EO AP BS PL TA ICA CL E B L HE IGH E FO R TS July 2006 ASSOCIATED CONDITIONS OAT................ 10 kt GROUND ROLL........... RETRACT AFTER POSITIVE CLIMB ESTABLISHED COWL FLAPS..................................................... 3250 lb HEAD WIND COMPONENT..... FULL RICH FLAPS............ OPEN RUNWAY. 1150 ft TOTAL DISTANCE OVER 50 ft OBSTACLE.Aeroplane Performance Manual Section 2 ..SEP1 Page 5 OUTSIDE AIR TEMPERATURE °C DISTANCE ft 4000 S RE RE SU 0 ............................................ Example: Pressure Altitude Ambient Temperature Weight Solution: Graphical ROC TAS Climb Gradient 515 fpm 120 kt 4. above.2. Parallel the grid lines to the appropriate mass input.CAP 698 CAA JAR-FCL Examinations . travel horizontally right to the mass reference line. b) Enter the graph at the ambient temperature.2% 11500 ft -5°C 3600 lb 3. c) Calculate the TAS using the Navigation Computer. b) From this point.2 3. From this point follow the grid lines to reach the reference line and draw a horizontal line through the weight grid. Continue horizontally to the TAS reference line. Move vertically up to the Pressure Altitude. Move vertically up to the pressure altitude. d) Now continue horizontally right to the first vertical axis to read the rate of climb.2 Maximum Weight To determine the maximum weight for a given gradient: a) Enter the graph at the ambient temperature. To determine the climb gradient and rate of climb: a) Use the navigation computer to calculate the TAS. 3. d) Enter the right vertical axis at the appropriate gradient and travel horizontally left to intercept the TAS calculated in c). Example: Aerodrome Pressure Altitude 11000 ft Ambient Temperature +25°C Gradient 4.1 Take-Off Climb Requirements There are no obstacle clearance limits or minimum acceptable climb gradient required by JAR-OPS 1. c) From this point. e) From the pencil mark in b).1 Use of Climb Graph Climb Gradient and Rate of Climb.2. parallel the grid lines to intersect the horizontal line drawn in d) above. travel horizontally right to the weight reference line and mark with a pencil.Aeroplane Performance Manual 3 3. Drop vertically to read the Climb-Limited Take-off weight.2% Solution: TAS Maximum Weight 125 kt 3360 lb July 2006 Section 2 .SEP1 Page 6 . e) Parallel the grid lines to intersect the TAS input then travel horizontally right to the right vertical axis to read the climb gradient. ......2% ASSOCIATED CONDITIONS POWER...................120 kt CLIMB GRADIENT... 3600 lb RATE OF CLIMB...........Aeroplane Performance Manual Section 2 ........SEP1 Page 7 OUTSIDE AIR TEMPERATURE °C CLIMB GRADIENT % 8 1100 1000 900 7 6 July 2006 14 13 12 RATE OF CLIMB ft/min 1400 1300 1200 11 10 9 Figure 2.3 Climb EXAMPLE OAT...-5°C PRESSURE ALTITUDE........0 00 14....................... 4.......... UP COWL FLAPS. AS REQUIRED CLIMB SPEED 100 kt IAS ALL MASSES SL 400 0 600 0 800 0 ...................................... 515 fpm TAS ............................0 00 800 700 600 500 400 300 200 1 100 110 50 60 3600 3400 3200 40 3000 MASS lb 2800 140 130120 90 100 TAS kt 3 2 5 4 12... FULL RICH FLAPS..............................................................CAP 698 REF LINE ISA PRESSURE ALTITUDE ft 200 0 REF LINE 10.......... FULL THROTTLE 2700 rpm MIXTURE................. UP LANDING GEAR..........11.........................................0 00 -50 -40 -30 0 10 20 30 -20 -10 0 2600 CAA JAR-FCL Examinations ...........0 00 16.......500 ft MASS. in the event of engine failure.2.1 En-Route Requirements The aeroplane may not be assumed to be flying above the altitude at which a rate of climb of 300 ft/min is attained.Aeroplane Performance Manual 3.0% = 900 10.3 Distance to Reach given height.SEP1 Page 8 . assume no position error. c) Determine the climb gradient from the graph.5% July 2006 Section 2 . b) Apply the wind component to the TAS to obtain the ground speed.CAP 698 CAA JAR-FCL Examinations . d) Calculate the still air distance using the formula: Still Air Distance (ft) = Height Difference (ft) x 100 Gradient e) Calculate ground distance using the formula: Ground Distance = Still Air Distance x Groundspeed TAS Example: Aerodrome Pressure Altitude Ambient Temperature Wind Component Take-Off Weight 4000 ft +30°C 30 kt tail 3200 lb Calculate the ground distance to reach 950 ft above reference zero from the end of TODR. 110 Ground Distance = 9000 x 4 4.0 x 100 = 9000 ft 140 = 11455 ft = 1. Solution: 100 kt lAS Groundspeed Graph Gradient Still Air Distance = 110 kt TAS = 140 kt = 10. The net gradient of descent.88 NM. shall be the gross gradient of descent increased by a gradient of 0. To calculate the ground distance travelled in order to attain a given height above reference zero: a) Convert the IAS 100 kt to a TAS. d) The landing distance should be increased by 5% for each 1% downslope.15 x 1. Parallel the grid line to the appropriate wind component input.1 Landing Requirements Field Length Requirements a) The landing distance. move horizontally right to the landing mass reference line.CAP 698 CAA JAR-FCL Examinations . Apply the regulatory factor to the landing distance to obtain the landing distance required.SEP1 Page 9 . 5. Move vertically to the aerodrome pressure altitude. from a screen height of 50 ft.15 x 1. d) Travel horizontally right to the ground roll reference line.05 x 1. the landing distance should be multiplied by a factor of 1. Parallel the grid lines to the appropriate landing mass input.15. b) From this point. a factor of 1.Aeroplane Performance Manual 5 5. e) The despatch rules for scheduled (planned) landing calculations are in JAR . must not exceed 70 % of the landing distance available.OPS 1.e. b) If the landing surface is grass up to 20 cm long on firm soil. i.43 2979 ft 3965 ft +25°C 3479 lb 10 kt Head 1% down Grass Wet July 2006 Section 2 . c) If the METAR or TAF or combination of both indicate that the runway may be wet at the estimated time of arrival. the landing distance should be multiplied by a factor of 1. Either continue horizontally to the right vertical axis to read the ground roll distance or parallel the grid lines to the right vertical axis to read the graphical distance. c) Continue from this intersection to the wind component reference line. Example: Normal Landing Aerodrome Pressure Altitude Ambient Temperature Landing Mass Wind Component Runway Slope Runway Surface Runway Condition Calculate Landing Distance Required Solution: Graphical Distance Slope Correction Factor Surface Correction Factor Condition Correction Factor Regulatory Factor Landing Distance Required = 1500 ft x 1. e) Apply the surface and slope factors to the graphical distance to obtain the landing distance. No allowance is permitted for upslope.2 Use of the Landing Field Length Graph Distance Calculations a) Enter at the ambient temperature.43.550 (c).15. ................ PAVED..................... TO MAINTAIN 900 fpm ON FINAL APPROACH FLAPS............ IAS AS TABULATED BRAKING...... 80 kt 3000 79 80 81 81 78 OAT.......................................4 Landing HE AD WI ASSOCIATED CONDITIONS POWER............. 3965 ft LANDING MASS.......................................CAP 698 REF LINE REF LINE WI ND G AP UID IN PLI ELI TE CA NE O RM BL S N B HE ST ED E F OT IG AC IAT OR HT LE E S PRESSURE ALTITUDE ft TA IL ND 1000 10....................................................SEP1 Page 10 OUTSIDE AIR TEMPERATURE °C DISTANCE ft 1500 July 2006 MASS lb 3650 3400 3200 3000 2800 GROUND ROLL....... 1470 ft APPROACH SPEED................................000 8000 6000 0 400 2000 SL 500 REF LINE -40 -30 30 50 -20 -10 0 10 20 40 3600 3400 3200 MASS lb 3000 2800 0 10 20 30 WIND COMPONENT kt 0 50 OBSTACLE HEIGHT ft CAA JAR-FCL Examinations ...... 10 kt SPEED AT 50 ft kt EXAMPLE 2500 2000 Figure 2............................. MAXIMUM ISA ....... LEVEL DRY SURFACE APPROACH SPEED...... DOWN RUNWAY..............Aeroplane Performance Manual Section 2 ................................... DOWN (AMBER) LANDING GEAR........ 25°C PRESSURE ALTITUDE....................... 960 ft TOTAL DISTANCE OVER 50ft OBSTACLE........ 3479 lb HEAD WIND COMPONENT..................... They are the minimum field length and climb gradient requirements. on a multi-engine aeroplane in this class.1. Long Paved Condition Dry Wet Wet Factor x 1. 1.15.CAP 698 CAA JAR-FCL Examinations .700 kg or less.3. is a land-plane and is classified in Performance Class B.25 must not exceed TORA. engines (both of which are supercharged).0 July 2006 Section 3 . These drive counter-rotating.1 General Considerations Performance Classification The specimen aeroplane is a low wing monoplane with retractable undercarriage. b) When a stopway and/or clearway is available the take-off distance must: i) not exceed TORA ii) when multiplied by 1. constant speed propellers.2 General Requirements This class of aeroplane includes all propeller-driven aeroplanes having 9 or less passenger seats and a maximum take-off weight of 5.2 x 1.Aeroplane Performance Manual Section 3 Data for Multi-Engine Piston Aeroplane (MEP1) 1 1. It is powered by twin.3 x 1. The take-off climb requirements are considered in paragraph 3. 2. reciprocating.3 Aeroplane Limitations Structural Limitations Maximum Take-Off Mass Maximum Landing Mass Runway Crosswind Limitation Maximum Demonstrated Crosswind 4750 lb 4513 lb 17 kt 2 2. which is not certificated under CS/FAR 25. The aeroplane.1 Field Length Requirements a) When no stopway or clearway is available the take-off distance when multiplied by 1. Performance accountability for engine failure. not exceed ASDA iii) when multiplied by 1.MEP1 Page 1 . need not be considered below a height of 300 ft 1.1 Take-Off Requirements There are two requirements for take-off with which compliance is necessary. not exceed TODA c) If the runway surface is other than dry and paved the following factors must be used when determining the take-off distance in a) or b) above: Surface Type Grass (on firm soil) up to 20 cm. Parallel the grid lines to the appropriate take-off mass.1 Distance Calculation Procedure To determine the distance used for take-off: a) Select the appropriate graph. No factorisation is permitted for downslope.Aeroplane Performance Manual d) Take-off distance should be increased by 5% for each 1% upslope.MEP1 Page 2 . ii) For take-off distance continue to the ground roll reference line then parallel the grid lines on Figure 3. 2. d) Continue horizontally right to the wind component reference line and parallel the grid lines to the wind component input e) To read the appropriate distance: i) Continue horizontally from the wind component for TOR or ASD as appropriate to the graph used. Example: Normal Take-Off Aerodrome Pressure Altitude Ambient Temperature Take-Off Mass Wind Component Runway Slope Runway Surface Aerodrome Field Lengths 2000 ft +21°C 3969 lb 9 kt Head 1. Travel vertically to the aerodrome pressure altitude.650 ft Surface Factor = x 1. Each set comprises two graphs.2.1 or Figure 3.CAP 698 CAA JAR-FCL Examinations . f) Factorise for surface and slope.5% Uphill Wet Grass Unbalanced Calculate: Take-Off Distance Required Solution: Graphical Distance 1.3 Slope Factor = x 1. c) From this point proceed horizontally right to the mass reference line. as appropriate.15 Take-Off Distance Required = 2652 ft July 2006 Section 3 . b) Enter at the OAT.3. the other for calculating the accelerate-stop distance.075 Take-Off Distance = 2306 ft Regulatory Factor = x 1. 2. NOTE: The same surface and slope correction factors should be used when calculating TOR or ASD. one for determining the take-off run and take-off distance.2 Use of Take-Off Graphs There are two sets of take-off graphs: one for a “normal” take-off with 0° flap and the other for a “maximum effort” (short field) take-off with 25° flap. .. PAVED.... 1650 ft 3500 E UD TIT AL TA IL ft GROUND ROLL July 2006 ASSOCIATED CONDITIONS POWER.........................MEP1 Page 3 OUTSIDE AIR TEMPERATURE °C .................. 21°C PRESSURE ALTITUDE................. 1350 ft TAKE-OFF DISTANCE OVER 50 ft OBSTACLE............ 79 kt IAS COWL FLAPS................................................................... 2800 rpm 40 in MAP FLAPS............. HALF OPEN 3000 ISA P E UR SS RE HE A DW 2500 IND TE MP 00 80 2000 TAKE-OFF DISTANCE ft 0 600 1500 0 400 0 200 SL 1000 500 4500 4000 MASS lb 3500 3000 0 5 10 15 WIND COMPONENT kt -40 -30 10 20 30 -20 -10 0 40 CAA JAR-FCL Examinations ....CAP 698 ND REF LINE WI REF LINE ZERO WIND REF LINE 4750 lb Figure 3...... LEVEL DRY SURFACE LIFT-OFF.........Aeroplane Performance Manual Section 3 ........ 79 kt IAS OBSTACLE AT...1 Take-Off – Normal Procedure EXAMPLE OAT........ 3969 lb HEAD WIND COMPONENT.............. 2000 ft TAKE-OFF MASS.................................................. UP RUNWAY............................................... 9 kt TAKE -OFF GROUND ROLL................................................................................ d) Now travel horizontally left to the appropriate wind component input. Parallel the grid lines to the ground roll reference line. Only the take-off distance graph is used but the right vertical axis is entered with shortest available de-factored distance.Aeroplane Performance Manual 2. c) Enter the right vertical axis at the shortest available de-factored distance at the 50ft height.2 Mass Calculation To calculate the field length limited take-off mass it is necessary to apply the requirements of JAR-OPS. surface condition and regulation. g) At the intersection.CAP 698 CAA JAR-FCL Examinations . parallel the grid lines to intersect the horizontal line from e) above. Examples are shown at page 6. travel horizontally right to the mass reference line. f) From the position marked in b) above.2. Procedure a) Enter at the ambient temperature. The factors to be considered are those of slope.MEP1 Page 4 . Mark this position with a pencil. e) From this point draw a horizontal line left through the mass grid. Move vertically to the aerodrome pressure altitude. July 2006 Section 3 . Parallel the grid lines to the wind component reference line. b) From this point. drop vertically to read the field length limited TOM. ............................ 2000 ft TAKE-OFF MASS.... HALF OPEN BRAKING...........2 Accelerate/Stop Distance – Flaps 0° EXAMPLE OAT................ 9 kt ACCELERATE & STOP DISTANCE.................... 79 kt IAS 6000 HE A T ISA DW IND 5000 EM P 0 800 4000 0 600 0 400 0 200 ACCELERATE & STOP DISTANCE ft SL PRE SSU LT RE A ITUD E ft 3000 2000 4500 4000 MASS lb 3500 3000 0 5 10 15 WIND COMPONENT kt -40 10 20 -30 30 -20 -10 0 40 CAA JAR-FCL Examinations ............................ 21°C PRESSURE ALTITUDE..................................CAP 698 TA IL NOTE: DISTANCES INCLUDE A THREE SECOND RECOGNITION TIME REDUCE DISTANCES BY 7% IF HEAVY DUTY BRAKES ARE FITTED WI ND REF LINE 4750 lb Figure 3.......... TYRES & BRAKES FULL POWER BEFORE BRAKE RELEASE RUNWAY................................. 3280 ft REF LINE ZERO WIND July 2006 (corr........................................ LEVEL DRY SURFACE FLAPS ..... MAXIMUM ABORT SPEED..............Aeroplane Performance Manual Section 3 .... PAVED...... CLOSED AT ENGINE FAILURE COWL FLAPS.......................) ASSOCIATED CONDITIONS STANDARD WHEELS.................. 3970 lb HEAD WIND COMPONENT..MEP1 Page 5 OUTSIDE AIR TEMPERATURE °C .................. ZERO THROTTLES......... TODA: 2.500 ft.Aeroplane Performance Manual Example 1: Maximum Effort Take-Off (Short Field) (Figure 3.3 1457 ft TODA 2600 ft 1.1 1.400 ft.1 1.25 2000 ft 3100 lb Using 2000 ft July 2006 Section 3 .1 1.1) Aerodrome Pressure Altitude Ambient Temperature Wind Component Runway Slope Surface Type Surface Condition TORA: 2500 ft 4000 ft +20°C 5 kt Tail 2% down Concrete Wet No Stopway or Clearway Calculate the field length limited take-off mass Solution: Given Distance Slope Factor Surface Condition Factor Regulation Factor De-factored Distance Field Length Limited TOM 2500 ft ÷1.0 ÷1. Using 1457 ft Example 2: Normal Take-Off (Figure 3.CAP 698 CAA JAR-FCL Examinations .2 1. ASDA: 2.15 1713 ft Field Length Limited TOM 4000 lb.0 1818 ft ASDA 2500 ft 1.3) 2000 ft +30°C 5 kt Tail 2 % Uphill Grass Dry Normal Take-Off Aerodrome Pressure Altitude Ambient Temperature Wind Component Runway Slope Surface Type Surface Condition TORA: 2.600 ft Calculate the field length limited take-off mass Solution: TORA Given Distances Slope Factor Surface/Condition Factor Regulation Factor De-Factored Distance 2400 ft 1.0 ÷1.2 1.2 1.MEP1 Page 6 . ...................MEP1 Page 7 OUTSIDE AIR TEMPERATURE °C ................ 66 kt IAS COWL FLAPS.......................................3 Take-Off – Maximum Effort EXAMPLE OAT... 4250 lb HEAD WIND COMPONENT.... 2000 ft TAKE-OFF MASS............... 21°C PRESSURE ALTITUDE......................1050 ft GROUND ROLL July 2006 ASSOCIATED CONDITIONS POWER.......................... 9 kt TAKE -OFF GROUND ROLL..... HALF OPEN 2000 ISA TEM 1500 P HEA DW TAKE-OFF DISTANCE ft 8000 6000 IND 1000 4000 2000 ft UDE SL ALTIT SURE PRES 500 -40 20 -30 30 -20 -10 0 40 10 4500 4000 3500 MASS lb 3000 0 5 10 15 WIND COMPONENT kt CAA JAR-FCL Examinations .... LEVEL DRY SURFACE LIFT-OFF.......... PAVED..........................Aeroplane Performance Manual Section 3 ........................................... 64 kt IAS OBSTACLE AT................................. 800 ft TAKE-OFF DISTANCE OVER 50 FT OBSTACLE............................ 2800 rpm 40 in MAP BEFORE BRAKE RELEASE FLAPS...............CAP 698 REF LINE REF LINE ZERO WIND TA IL W IN D REF LINE 4750 lb Figure 3........................... 25° RUNWAY.................................................... ............................ 4000 lb HEAD WIND COMPONENT. 3000 ft TAKE-OFF MASS......Aeroplane Performance Manual Section 3 .................................... 10 kt ACCELERATE & STOP DISTANCE..............CAP 698 LW IN NOTE: DISTANCES INCLUDE A THREE SECOND REACTION TIME REDUCE DISTANCES BY 13% IF HEAVY DUTY BRAKES ARE FITTED D TA I REF LINE ZERO WIND REF LINE 4750 lb July 2006 (corr............. 22°C PRESSURE ALTITUDE................ 2100 ft EXAMPLE STANDARD WHEELS..................................................... 25° THROTTLES......... LEVEL DRY SURFACE FLAPS .......4 Accelerate/Stop Distance – Flaps 25° 2000 ACCELERATE & STOP DISTANCE ft 1000 10 20 30 40 4500 4000 3500 MASS lb 3000 0 5 10 15 WIND COMPONENT kt 8000 6000 4000 2000 SL PRE ITUDE E ALT SSUR ft -40 -30 -20 -10 0 CAA JAR-FCL Examinations ................. HALF OPEN BRAKING. CLOSED AT ENGINE FAILURE COWL FLAPS.. MAXIMUM ABORT SPEED............. PAVED....... 64 kt IAS 4000 T ISA HE AD WIN D 3000 EM P Figure 3......) ASSOCIATED CONDITIONS OAT............................................................... TYRES & BRAKES FULL POWER BEFORE BRAKE RELEASE RUNWAY...........................MEP1 Page 8 OUTSIDE AIR TEMPERATURE °C .... 2 Use of Take-Off Climb Data Because the graphs provided only permit the calculation of the rate of climb it is necessary to utilise the following formula to solve take-off climb problems: Time to Climb = Height Difference (ft) x 60 seconds Rate of Climb (fpm) Distance to Climb nm = Height Difference (ft) x Groundspeed (kt) Rate of Climb (fpm) 60 Still Air Gradient of Climb = Rate of Climb (fpm) x 6000% TAS (kt) 6080 July 2006 Section 3 .2 Minimum Gradients of Climb The minimum permissible gradients of climb. 3. if the wing span is less than 60 m. If visual reference for obstacle avoidance is lost. 3. ii) at 1500 ft above the take-off surface level … 0.75%. 600 m Over 15° 600 m.1. then (60 m + ½ wing span) is the semi-width to be used. at the rate of 0. 3.125 x D.MEP1 Page 9 .1 The Obstacle Accountability Area The dimensions of the obstacle accountability area are as follows: a) Starting semi-width at the end of TODA of 90 m. to the maximum semi-width where D is the horizontal distance travelled from the end of TODA or TOD if a turn is scheduled before the end of TODA.1.Aeroplane Performance Manual 3 3. The maximum take-off power setting is limited to 5 minutes from the commencement of the take-off climb.CAP 698 CAA JAR-FCL Examinations . at which point it must be reduced to the maximum continuous power setting. 900 m. c) Maximum Semi-width Condition Change of Track Direction Able to Maintain Visual Guidance or same Accuracy All Other Conditions Maximum Semi-width 0° to 15° 300m. are: a) All engines operating … 4% at screen height b) One engine inoperative: i) at 400 ft above the take-off surface level … measurably positive. All obstacles encountered in the accountability area must be cleared by a vertical interval of 50 ft Turns are not permitted in the take-off climb before the end of the TODR and thereafter the angle of bank must not exceed 15°. The take-off climb extends from 50 ft above the surface at the end of TODR to 1500 ft above the same surface. as specified in JAR-OPS 1. it is assumed that the critical power unit becomes inoperative at this point.1 Take-Off Climb Requirements The take-off climb requirements only apply to aeroplanes with two or more engines. b) The area expands from the appropriate semi-width. Read off rate of climb. maximum take-off power (Figure 3. An example is shown on the graph.CAP 698 CAA JAR-FCL Examinations . 3.2. b) Travel horizontally to the curved graph line.3.Aeroplane Performance Manual 3.5) b) Gear retracted.MEP1 Page 10 . the gradient from 50 ft to the assumed engine failure height is to be the average all-engine gradient x 0.7) NOTE: If a graph is used to show compliance with the obstacle clearance requirement.2 Use of Graph (Figure 3. This is equivalent to the distance travelled with all engines operating x 1.1 Climb graphs There are three graphs provided for climb calculations: a) Gear extended. maximum continuous power (Figure 3.77. maximum take-off power (Figure.2.6) c) Gear retracted. c) From this intersection drop a vertical line to the bottom scale. July 2006 Section 3 .5) a) Enter with the temperature and travel vertically to the pressure altitude. 3. ......... 8000 ft PRESSURE ALTITUDE...CAP 698 NOTE: TAKE-OFF POWER IS LIMITED TO 5 MINUTES OF CONTINUOUS OPERATION July 2006 (corr......... ISA P TEM 000 16.............................. EXTENDED FLAPS.............................. 000 10.... 000 18.......... ASSOCIATED CONDITIONS 000 22....) 000 24.... 10 20 30 40 0 500 1000 RATE OF CLIMB fpm 1500 2000 -40 -30 -20 -10 0 CAA JAR-FCL Examinations ... BOTH ENGINES MIXTURE....MEP1 Page 11 OUTSIDE AIR TEMPERATURE °C .................... 92 kt IAS Figure 3.. 000 14................................... UP MASS......... POWER............ TAKE-OFF POWER.. FULL RICH LANDING GEAR...Aeroplane Performance Manual Section 3 .....5 Take-Off Climb Performance – Gear Extended 1125 fpm RATE OF CLIMB.. 000 12........... 000 20. HALF OPEN SPEED............ 0 800 0 600 0 400 0 200 SL EXAMPLE 10°C OAT... 4750 lb COWL FLAPS................. Travel vertically to the pressure altitude. continue horizontally right to intercept the second interpolated weight (if applicable).CAP 698 CAA JAR-FCL Examinations . 300 Total time = 12. Example 1: Aerodrome Pressure Altitude 10000 ft Ambient Temperature +10°C Take-Off Mass 4000 lb Gear up (Undercarriage Retracted) Flaps 0°.MEP1 Page 12 . b) From this point. c) Drop vertically to read the all-engine-operating rate of climb.3 Use of Graphs (Figure 3.2. Therefore Maximum Take-off Power can be maintained throughout the climb.7) a) Enter with OAT. 92 kt IAS = 110 kt TAS.73 Seconds + 3 minutes 40 seconds = 3 minutes 52.e.6 and Figure 3.414 NM 1650 60 Distance cloud base to 1500 = 1100 x 90 = 5.Aeroplane Performance Manual 3. Solution: All engines rate of climb at take-off power 1650 fpm One engine inoperative rate of climb at take-off power 300 fpm One engine inoperative rate of climb at MCP 220 fpm Time to cloud base at take-off power = 350 x 60 = 12.3 = 0.73 seconds 1650 Time to 1500 ft from cloud base at take-off power = 1100 x 60 = 220 seconds = 3 minutes 40 seconds.414 + 5.5 = 5.73 seconds. travel horizontally right to intercept the interpolated value of takeoff mass.914 NM July 2006 Section 3 . d) From the TOM intersection. Climb speed 92 kt lAS Cloud Base 400 ft above Reference Zero Wind Component 40 kt Head Calculate the distance from the end of TODR to 1500 ft above Reference Zero for the purpose of obstacle clearance. less than 5 minutes.5 NM 300 60 Total Distance = 0. i. G/S = 110 = 20 = 90 kt (Using 50% of head wind component) Distance to cloud base = 350 x 90 x 1. e) Drop vertically to read the one-engine-inoperative rate of climb. ....300 fpm CLOSED ON INOPERATIVE ENGINE INOPERATIVE ENGINE FEATHERED CLIMB SPEED .........HALF OPEN ON OPERATING ENGINE SINGLE ENGINE CLIMB........MEP1 Page 13 OUTSIDE AIR TEMPERATURE ºC ..1650 fpm COWLFLAPS..CAP 698 July 2006 (corr..00 16 0 ..........................00 18 lb 4000 lb 4750 ISA TEM P 0 .........................00 20 0 ..00 14 0 .00 12 0 .....................00 22 0 ...UP 2 ENGINE CLIMB.................6 Take-Off Climb Performance – Gear Retracted U DE 00 80 00 60 00 40 00 20 IT LT SA ES PR SL -20 -10 10 0 20 30 40 1000 2000 RATE OF CLIMB fpm 0 100 200 300 400 RATE OF CLIMB fpm 500 -40 -30 CAA JAR-FCL Examinations .....UP FLAPS..000 ft MIXTURE.00 10 ft lb 00 40 0 lb 475 Figure 3.....10 ºC TAKE-OFF POWER PRESSURE ALTITUDE................... 92 kt IAS NOTE: TAKE-OFF POWER IS LIMITED TO 5 MINUTES OF CONTINUOUS OPERATION 0 ...Aeroplane Performance Manual Section 3 .4000 lb GEAR...10................) EXAMPLE 2 ENGINES SINGLE ENGINE SHADED AREA ABOVE MAX CONT POWER ABSOLUTE CEILING ASSOCIATED CONDITIONS OAT...FULL RICH TAKE-OFF MASS..........00 24 0 ........... 3 ft Clearance = 607.3 ft July 2006 Section 3 . Solution: Figure 3.6 One engine inoperative rate of climb at take-off power 255 fpm Figure 3.600 = 7.9 seconds + 4 minutes 18.7 seconds.3786 = 10214 ft Height gain = 10214 x 255 x 60 = 207. Therefore Maximum Take-Off power can be maintained throughout the take-off climb.3 . 92 kt IAS = 104 kt TAS.8 seconds 255 Total time = 13.8 seconds = 4 minutes 18.9 seconds 1510 Time to 1500 ft from cloud base = 1100 x 60 = 258. G/S = 104 + 20 = 124 kt (Using 150% of tailwind component rounded up) Distance to cloud base = 350 x 124 x 6080 x 1.CAP 698 CAA JAR-FCL Examinations .7 One engine inoperative rate of climb at maximum continuous power 220 fpm Time to cloud base =350 x 60 = 13.MEP1 Page 14 .Aeroplane Performance Manual Example 2: Aerodrome Pressure Altitude Ambient Temperature Take-Off Mass Gear up (Undercarriage Retracted) Flaps 0° Climb Speed Cloud Base Wind Component 6000 ft +20°C 4500 lb 92 kt lAS 400 ft above Reference Zero 13 kt Tail Obstacle in the domain at 14000 ft from the end TODR and 600 ft above Reference Zero Calculate the vertical clearance of the obstacle by the aeroplane.3 = 607.6 All engines rate of climb at take-off power 1510 fpm Figure 3.3 ft 124 x 6080 Height at obstacle = 400 + 207.3 = 3786 ft 1510 60 Distance cloud base to obstacle = 14000 .8 seconds = 4 minutes 32. . 0 800 0 600 0 400 0 200 SL MIXTURE LEANED TO 25°F OF PEAK EGT SINGLE ENGINE 0 lb 350 lb 4000 0 lb 475 Figure 3....... 000 20................5° BANK TOWARDS OPERATING ENGINE 92 kt IAS EXAMPLE 2 ENGINES o ASSOCIATED CONDITIONS BOTH ENGINES AT MAX CONT POWER GEAR & FLAPS UP COWL FLAPS HALF OPEN MIXTURE AS NOTED 92 kt IAS PRESSURE ALTITUDE ft 000 24....1400 fpm 1 ENGINE RATE OF CLIMB.....7 Climb Performance – Gear Retracted Maximum Continuous Power -10 0 10 20 30 40 0 500 1000 1500 2000 RATE OF CLIMB fpm 100 350 600 -40 -30 -20 CAA JAR-FCL Examinations ...... 000 18.MEP1 Page 15 OUTSIDE AIR TEMPERATURE °C ...........................CAP 698 July 2006 2 ENGINE CLIMB 1 ENGINE CLIMB OPERATING ENGINE AT MAX CONT POWER COWL FLAPS HALF OPEN MIXTURE FULL RICH INOPERATIVE ENGINE FEATHERED COWL FLAPS CLOSED GEAR & FLAPS UP 3° ..........10 C PRESSURE ALTITUDE. 000 10.....10..........000 ft MASS..... 000 22....Aeroplane Performance Manual Section 3 .220 fpm ISA MIXTURE FULL RICH TEM lb 00 40 lb 00 35 P 000 16........ 000 12..... 000 14.. 4000 lb 2 ENGINE RATE OF CLIMB.... lb 50 47 OAT. CAP 698 CAA JAR-FCL Examinations .MEP1 Page 16 .Aeroplane Performance Manual INTENTIONALLY LEFT BLANK July 2006 Section 3 . the aeroplane must be able to continue flight at or above the relevant minimum safe altitude to an aerodrome at which the landing requirements can be attained. This must be achieved with: a) The power developed 8 seconds after moving the power controls to the take-off position. i. d) The landing distance should be increased by 5% for each 1% downslope. b) The one-engine-inoperative net gradient of climb is the gross gradient of climb decreased by 0.1 Requirements In the event of engine failure. from a screen height of 50 ft.550 (c).1. 4. No allowance is permitted for upslope. 5.e. must not exceed 70% of the landing distance available. c) Flaps at the landing setting. a factor of 1.15.1 Field Length Requirements a) The landing distance. b) The landing gear (undercarriage) extended. and the landing field length requirement.5%.5%.CAP 698 CAA JAR-FCL Examinations .Aeroplane Performance Manual 4 En-route The en-route phase extends from 1500 ft above the take-off surface level to 1000 ft above the landing aerodrome surface level. e) The despatch rules for scheduled (planned) landing calculations are in JAR-OPS 1. or the net gradient of descent is the gross gradient of descent increased by 0. with the remaining engine(s) set at the maximum continuous setting. They are the climb gradient requirements in the event of a balked landing and a missed approach. 5.1.15.2 Balked Landing Requirements The minimum acceptable gross gradient of climb after a balked landing is 2. c) If the METAR or TAF or combination of both indicate that the runway may be wet at the estimated time of arrival.MEP1 Page 17 . July 2006 Section 3 . To show compliance: a) The aeroplane may not be assumed to be flying above that altitude at which the rate of climb is 300 fpm with all engines operating. d) Climb speed equal to VREF.43. 5 5.5%.1 Landing Requirements There are three requirements for landing with which compliance is necessary. the landing distance should be multiplied by a factor of 1. the landing distance should be multiplied by a factor of 1. b) If the landing surface is grass up to 20 cm long on firm soil. c) The landing gear (undercarriage) retracted. d) The flaps retracted.MEP1 Page 18 .9% Gradient of Climb 102 6080 5. after a missed approach.2 Balked Landing Climb Graph The graph provided for this purpose is constructed for the maximum landing mass of 4513 lb (Figure 3. Now drop a vertical to read the rate of climb. This must be achieved with: a) The critical engine inoperative and the propeller feathered.75% at 1500 ft above the landing surface. c) Convert the rate of climb to a still-air gradient of climb using the formula: Still Air Gradient of Climb = ROC (fpm) x 6000 % TAS (kt) 6080 Example: Aerodrome Pressure Altitude Ambient Temperature Solution: Graphical ROC IAS 85 kt Climb Gradient 3000 ft +22°C = = = 810 fpm.7: One-engine-inoperative grid = 102 kt True Airspeed = 300fpm Rate of Climb = 300 x 6000 = 2. b) The live engine set at maximum continuous power.1. is 0.2 VS1. b) From this point travel horizontally right to intercept the rate of climb graph line. Example: Flaps Up Aerodrome Pressure Altitude Ambient Temperature Aeroplane Mass = 6000 ft = +10°C = 4000 lb Calculate the missed approach gradient of climb: Solution: Use Figure 3.Aeroplane Performance Manual 5.CAP 698 CAA JAR-FCL Examinations . Travel vertically to the aerodrome pressure altitude. Use of Graph: a) Enter at the ambient temperature. 91 kt TAS 810 x 6000 = 8.78% 91 6080 July 2006 Section 3 .3 Missed Approach Requirements The minimum acceptable gross gradient of climb.8). e) Climb speed not less than 1. ......Aeroplane Performance Manual Section 3 .... 40° MASS....................0 00 1 2... 85 kt IAS 10 .8 Balked Landing Climb Performance ASSOCIATED CONDITIONS EXAMPLE 22°C OAT..........................MEP1 Page 19 OUTSIDE AIR TEMPERATURE °C .... 00 0 MP T UD E July 2006 16 ............................................... 4513 lb COWL FLAPS.... EXTENDED FLAPS...........ft CAP 698 RE AL TI 1 4....0 00 ISA TE 0 10 20 30 600 40 400 800 RATE OF CLIMB fpm 1000 -40 -30 -20 -10 CAA JAR-FCL Examinations .......... HALF OPEN SPEED.................. 00 0 PR E SS U 40 00 60 00 80 00 20 00 SL Figure 3............. TAKE-OFF POWER MIXTURE... fpm POWER............................... FULL RICH LANDING GEAR........ 810 RATE OF CLIMB................ 3000 ft PRESSURE ALTITUDE...... move horizontally right to the landing weight reference line. 5. Example: Normal Landing 3000 ft +22°C 3650 lb 10 kt Head 1% Down Grass Wet Aerodrome Pressure Altitude Ambient Temperature Landing Mass Wind Component Runway Slope Runway Surface Runway Condition Calculate Landing Distance Required Solution: Graphical Distance Slope Correction Factor Surface Correction Factor Condition Correction Factor Regulatory Factor Landing Distance Required 2220 ft x 1. Either continue horizontally to the right vertical axis to read the ground roll distance or parallel the grid lines to the right vertical axis to read the landing distance from 50 ft.3. d) Travel horizontally right to the ground roll reference line.15 x 1.1 Distance Calculations a) Enter at the ambient temperature. c) Continue from this intersection to the wind component reference line. b) From this point.Aeroplane Performance Manual 5.05 x 1.10). Move vertically to the aerodrome pressure altitude.CAP 698 CAA JAR-FCL Examinations .15 x 1. Parallel the grid lines to the appropriate landing mass input.43 = 4408ft July 2006 Section 3 . and the other for short field landings with 40° landing flap.9). e) Apply the appropriate factors to the landing distance to obtain the landing distance required.MEP1 Page 20 . Parallel the grid lines to the appropriate wind component input.3 Use of Landing Field Length Graphs There are two landing field length graphs: one for normal landings with 40° landing flap (Figure 3. (Figure 3. ........... 2220 ft BARRIER SPEED......CAP 698 3400 3200 3000 2800 2600 2400 2200 LANDING GROUND ROLL...........22°C PRESSURE ALTITUDE..............10 kt GROSS MASS...............MEP1 Page 21 OUTSIDE AIR TEMPERATURE °C ......................... 3000 ft HEADWIND. 3650 lb EXAMPLE STANDARD WHEELS........................9 Landing Distance Normal Procedure LANDING DISTANCE ft 20 30 40 4500 4000 MASS lb 3500 3000 0 5 10 15 WIND COMPONENT kt MP 8000 6000 4000 2000 SL PRES E ft ITUD E ALT SUR -40 -30 -20 -10 0 10 CAA JAR-FCL Examinations ... TYRES & BRAKES THROTTLES CLOSED FLAPS 40° FULL STALL TOUCHDOWN PAVED..) ASSOCIATED CONDITIONS OAT.Aeroplane Performance Manual Section 3 ....... LEVEL DRY RUNWAY MAXIMUM BRAKING IS 2000 1800 1600 1400 1200 1000 800 600 A TE Figure 3.... 1120 ft TOTAL LANDING DISTANCE OVER 50 ft BARRIER.............. 82 kt WI ND 90 88 78 76 BARRIER SPEED kt 86 84 82 80 REF LINE 4513 lb MAX LANDING WEIGHT HE AD W IN D GROUND ROLL REF LINE REF LINE ZERO WIND TA IL July 2006 (corr......................... CAP 698 CAA JAR-FCL Examinations - Aeroplane Performance Manual 5.3.2 Landing Mass Calculations The procedure for calculating the field length limited landing mass is: a) De-factorise the landing distance available by dividing by the slope correction factor, the surface type correction factor, the surface condition correction factor and the regulatory factor. b) Enter at the ambient temperature. Move vertically to the aerodrome pressure altitude. c) From this point, travel horizontally right to the mass reference line. Mark with a pencil. d) Enter right vertical axis with the distance from a) above. Parallel the grid lines to the ground roll reference line. e) From this point, travel horizontally left to the appropriate wind component input. Parallel the grid lines to the wind component reference line. f) Now draw a line horizontally from this point through the mass grid. g) From the pencil mark in c) above, parallel the grid lines to intersect the horizontal line. Drop vertically to read field length limited landing mass. Example: Short Field Landing 3000 ft +22°C 3733 ft 10 kt Head 1% down Grass Wet Aerodrome Pressure Altitude Ambient Temperature Landing Distance Available Wind Component Runway Slope Runway Surface Runway Condition Calculate the field length limited landing mass Solution: Landing Distance Available Slope Correction Factor Surface Type Correction Factor Surface Condition Correction Factor Regulatory Factor De-factorised LDA Field Length Limited Landing Mass 3733 ft ÷1.05 ÷1.15 ÷1.15 ÷1.43 = 1880 ft = 3800 lb July 2006 Section 3 - MEP1 Page 22 CAP 698 D IN GROUND ROLL REF LINE TA IL REF LINE ZERO WIND LANDING DISTANCE ft P REF LINE 4513 lb MAX LANDING WEIGHT Figure 3.10 Landing Distance Short Field EXAMPLE W July 2006 (corr.) ASSOCIATED CONDITIONS STANDARD WHEELS, TYRES & BRAKES THROTTLES CLOSED FLAPS 40° FULL STALL TOUCHDOWN PAVED, LEVEL DRY RUNWAY MAXIMUM BRAKING OAT................................................................................... 22°C PRESSURE ALTITUDE.................................................... 3000 ft HEADWIND.......................................................................10 kt GROSS MASS.................................................................. 3650 lb LANDING GROUND ROLL...............................................1110 ft TOTAL LANDING DISTANCE OVER 50 ft BARRIER....... 1825 ft BARRIER SPEED............................................................. 74 kt 3500 3000 82 80 70 68 BARRIER SPEED kt 78 76 74 72 2500 IS HE A A DW TE M IND 2000 8000 6000 4000 2000 SL 1500 A SURE PRES D LTITU E ft 1000 500 20 30 40 4500 4000 3500 MASS lb 3000 0 5 10 15 WIND COMPONENT kt -40 -30 -20 -10 0 10 CAA JAR-FCL Examinations - Aeroplane Performance Manual Section 3 - MEP1 Page 23 OUTSIDE AIR TEMPERATURE °C CAP 698 CAA JAR-FCL Examinations - Aeroplane Performance Manual INTENTIONALLY LEFT BLANK July 2006 Section 3 - MEP1 Page 24 1 1.5 Standard Performance Conditions Performance information relates to an average aeroplane of the type and the data are based on: a) Certified engine thrust ratings less installation losses.1.1. which is based on standard day temperatures.1. Maximum zero fuel mass is 51300 kg.2 1. 1. d) Operations on smooth. • 4° transition setting.1.1.2 Flight Over Water Speed The true airspeed to be assumed for the purpose of compliance with legislation governing flight over water and en-route climb performance is 380 knots. On any given occasion. hard-surfaced. It is certificated in the Transport Category (Passenger) and is operated in accordance with CS/FAR 25 Performance Class A. Maximum structural landing mass is 54900 kg.CAP 698 CAA JAR-FCL Examinations . c) Trailing edge flap settings: • 5° or 15° for take-off. 1.4 Maximum Crosswind Component The maximum crosswind component in which the aeroplane has been demonstrated to be satisfactory for take-off and landing is 33 knots. July 2006 Section 4 .Aeroplane Performance Manual Section 4 Data for Medium-Range Jet Transport (MRJT1) 1 1. This wind speed is related to a height of 10 metres.MRJT1 Page 1 .2.1 Aeroplane Limitations Mass (Weight) Maximum structural take-off mass is 62800 kg. • 15°. airbleed and accessory losses. the maximum permitted take-off and landing mass may be less than the structural limits given above.3 Engine Relighting The maximum altitude to be assumed for engine relighting is 25000 feet. 1. 1. 1.1 General Considerations Performance Limitations Performance Classification The specimen aircraft is a landplane powered by two turbo fan engines. 30°. runways. • 22° for approach. b) Full temperature accountability within operational limits except for landing distance. 40° for landing with leading edge devices in the full down position for these flap settings. f) En route climb performance. with a maximum of 5° bank. following the failure of the critical engine at VEF.VMCG July 2006 Section 4 .CAP 698 CAA JAR-FCL Examinations .VMC Approach and Landing Minimum Control Speed . h) Landing field lengths. It is also the minimum speed during take-off.g.88 metres. at which the pilot can continue the take-off and achieve screen height within the take-off distance available. deploy speed brakes) to stop the aeroplane within the accelerate-stop distance available. The minimum speed with a wing engine inoperative where it is possible to decrease thrust to idle or increase thrust to maximum take-off without encountering dangerous flight characteristics.3 Additional Definitions for Class ‘A’ Aeroplanes The minimum flight speed at which the aeroplane is controllable. 1. d) Brake energy limits.3 Power Plant The engines shall not be operated continuously at maximum take-off thrust for periods exceeding 5 minutes.VMCL Decision Speed . The maximum speed during take-off at which the pilot must take the first action (e. reduce thrust. e) Net take-off flight path. when the critical engine suddenly becomes inoperative with the remaining engines at take-off thrust. V1 must not be less than VMCG. b) Take-off climb limits. 1. The minimum speed on the ground at which the take-off can be safely continued.MRJT1 Page 2 .Aeroplane Performance Manual 1.2.2 Wing Span The wingspan of the aeroplane is 28. apply brakes.V1 Ground Minimum Control Speed . g) Landing climb limits. not greater than VR and not greater than VMBE. c) Tyre speed limits. Air Minimum Control Speed .4 Operating Limitations Operational mass (weight) limits are determined from the following performance considerations: a) Take-off field lengths.2. when the critical engine suddenly becomes inoperative with the remaining engines at take-off thrust.2. 1. in the specified landing configuration. The target speed to be attained at the screen height with one engine inoperative.VMBE The maximum speed on the ground from which an aeroplane can safely stop within the energy capabilities of the brakes.all engines operating VT1 . Quick Reference Handbook. The height of an imaginary screen placed at the end of the Take-Off Distance Required and at the beginning of the Landing Distance Required. and used to the point where acceleration to flap retraction speed is initiated. rotation is initiated with the intention of becoming airborne. V4 should be attained by a gross height of 400 feet. The all engines operating take-off climb speed used to the point where acceleration to flap retraction speed is initiated. which is used to determine the landing distance for manual landings. The speed at which the pilot should aim to cross the runway threshold to ensure that the scheduled landing field lengths are consistently achieved.V4 Take-Off Safety Speed .MRJT1 Page 3 .a critical engine inoperative Maximum Threshold Speed .V2 Threshold Speed . Power Management Computer. The speed of the aeroplane.VR Screen Height Steady Initial Climb Speed .Aeroplane Performance Manual Maximum Brake Energy Speed . during the take-off. The speed at the threshold above which the risk of exceeding the scheduled landing field length is unacceptably high. The speed at which.VREF Rotation Speed .CAP 698 CAA JAR-FCL Examinations .VTMAX PMC QRH Reference Landing Speed . at screen height.VT July 2006 Section 4 . The speeds at the threshold are: VTO . Go-around action should normally be taken if it appears that maximum threshold speed will be exceeded. This speed is 15 knots greater than the all-engines operating target threshold speed. b) Enter graph at left vertical axis with windspeed.1 Wind Components for Take-Off and Landing July 2006 (corr.CAP 698 CAA JAR-FCL Examinations . Example: W/V 330/30 Runway 02 Wind angle = 50° Headwind = 19 kt Crosswind = 23 kt left to right.1 a) Calculate the relative direction of the wind to the runway.Aeroplane Performance Manual 1. i. Negative values are tailwinds.e. 50 10 BETW E & RUN EN WIND DIR WAY D ECTIO EGRE N ES 20 40 70 W D IN 65 VE 60 ITY C LO 55 40 30 ANGLE 30 kt 50 45 WIND COMPONENT PARALLEL TO RUNWAY kt 50 40 20 30 25 20 35 60 70 10 10 15 80 5 0 90 100 -10 110 12 14 0 13 0 15 -20 170 0 160 0 0 10 20 30 40 50 60 CROSSWIND COMPONENT kt Figure 4. c) Follow circle until relative direction intercepted. d) From the intersection draw a line horizontally left to the vertical axis to read the along track component. f) The windspeed grids have already been factorised 50% for headwinds and 150% for tailwinds.4 The Determination of Wind Component Use the graph at Figure 4. Therefore the grids may be entered with the reported or calculated along track component.wind direction). (wind direction runway direction) or (runway direction . Note this graph is for use with take-off and landing computations only.MRJT1 Page 4 . e) From the intersection drop a vertical line to intersect the horizontal axis to read the crosswind component.) Section 4 . 5 Conversion of QFE or QNH to Pressure Altitude All altitudes in this manual refer strictly to pressure altitude. = +400 ft = 2900 ft July 2006 Section 4 .63 30.55 29.08 30.96 31.) 28.MRJT1 Page 5 .48 in.76 29.19 30. QNH (IN.Aeroplane Performance Manual 1. Alt.91 29.41 30.07 Correction to elevation for press.CAP 698 CAA JAR-FCL Examinations .34 29.63 30.44 29.66 29.12 29.44 29.02 29.23 29.96 to to to to to to to to to to to to to to to to to to to to to 28.55 29.30 30.41 30.85 30.52 30.87 29.91 29.76 29. If only QFE or QNH are known then it must be used to produce a pressure altitude.02 29.19 30.HG.23 29.34 29.87 29. = 2500 ft = 29.08 30. (ft) +1000 +900 +800 +700 +600 +500 +400 +300 +200 +100 0 -100 -200 -300 -400 -500 -600 -700 -800 -900 -1000 976 979 983 986 990 994 997 1001 1004 1008 1012 1015 1019 1022 1026 1030 1034 1037 1041 1045 1048 QNH (hPa) to to to to to to to to to to to to to to to to to to to to to 979 983 986 990 994 997 1001 1004 1008 1012 1015 1019 1022 1026 1030 1034 1037 1041 1045 1048 1052 Figure 4.97 30.81 28.97 30.30 30.2 QNH To Pressure Altitude Example: Elevation QNH Correction Press Alt.66 29.74 30.12 29.74 30.85 30.52 30.Hg. 50 .82 -27 -25 -23 -20 -18 -16 -14 -11 -9 -7 -5 -2 0 2 4 7 9 11 13 16 .86 -24 -22 -20 -17 -15 -13 -11 -8 -6 -4 -2 1 3 5 8 11 12 14 .84 -26 -23 -21 -19 -17 -14 -12 -10 -8 -5 -3 -1 1 4 6 8 10 13 15 .74 -33 -30 -28 -26 -24 -22 -19 -17 -15 -13 -11 -8 -6 -4 -2 0 3 5 7 9 11 14 16 18 20 22 .78 -30 -28 -25 -23 -21 -19 -17 -14 -12 -10 -8 -5 -3 -1 1 3 6 8 10 12 15 17 19 21 .3 at the appropriate pressure altitude and move along the line to the appropriate indicated Mach number to read the ISA/TAT. To calculate the value of TAT.88 -23 -20 -18 -16 -14 -11 -9 -7 -4 -2 0 2 5 7 9 12 14 .3 TAT in ISA conditions July 2006 Section 4 . which is the true outside air temperature plus the rise due to ram air compression.MRJT1 Page 6 .60 -41 -39 -36 -34 -32 -30 -28 -26 -24 -22 -19 -17 -15 -13 -11 -9 -7 -5 -2 0 2 4 6 8 10 12 15 17 19 21 23 25 27 29 32 Total Air Temperature at ISA (°C) . Compare the actual TAT with the tabulated ISA/TAT to obtain the temperature deviation from standard.40 .CAP 698 CAA JAR-FCL Examinations . enter the table in figure 4.90 -21 -19 -17 -14 -12 -10 -7 -5 -3 0 2 4 6 9 11 13 .Aeroplane Performance Manual 1.6 Total Air Temperature at ISA The cockpit temperature gauge shows the total air temperature (TAT). while flying in ISA conditions.70 -35 -33 -31 -29 -26 -24 -22 -20 -18 -15 -13 -11 -9 -7 -5 -2 0 2 4 6 8 11 13 15 17 19 21 24 26 28 30 32 .92 -20 -17 -15 -13 -10 -8 -6 -3 -1 1 4 6 8 11 13 -41 -39 -37 -35 -33 -31 -29 -27 -25 -23 -21 -18 -16 -14 -12 -10 -8 -6 -4 -2 0 2 4 7 9 11 13 15 17 19 21 23 25 27 Figure 4.80 -29 -26 -24 -22 -20 -17 -15 -13 -11 -8 -6 -4 -2 0 3 5 7 9 12 14 16 18 . Pressure Altitude 1000 ft 36 to 45 35 34 33 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 8 7 6 5 4 3 2 1 Indicated Mach Number 0 -56 -54 -52 -50 -48 -46 -44 -42 -40 -38 -37 -35 -33 -31 -29 -27 -25 -23 -21 -19 -17 -15 -13 -11 -9 -7 -5 -3 -1 1 3 5 7 9 11 13 -25 -23 -21 -19 -17 -15 -13 -11 -8 -6 -4 -2 0 2 4 6 8 10 12 14 16 18 20 22 . with all engines operating. the take-off run is the greatest of: i) All power units operating (dry and wet runway). ii) One power unit inoperative (dry runway). b) The accelerate-stop distance on a wet runway is the greatest of: i) All engines operating. all factorised by 1. plus a distance equivalent to 2 seconds at the V1 for take-off from a wet runway. plus one half of the gross distance from VLOF to the point at which the aeroplane reaches 35 ft.15 to obtain the net TORR. will have to be forgone. assuming the critical engine fails at VEF and the pilot takes the first action to reject the take-off at the V1 for take-off from a wet runway with all engines operating and to decelerate to a full stop on a wet hard surface with one engine inoperative. which could have been carried.1. It does not take into account any stopway or clearway and is. to reach a screen height of 35 ft July 2006 Section 4 . The horizontal distance from the brake release point (BRP) to the point at which the aeroplane is 15ft above the take-off surface. a certain amount of payload. This means that.CAP 698 CAA JAR-FCL Examinations . iii) One power unit inoperative (wet runway). wind component. c) The take-off distance required is the greatest of the following three distances: i) All engines operating. 115% of the horizontal distance travelled. assuming the pilot takes the first action to reject the take-off at the V1 for take-off from a wet runway and to decelerate to a full stop on a wet hard surface.1 Take-Off Field Length Limit The field length limit graph (Figure 4. if either stopway or clearway is available. ii) One engine inoperative. 2. The sum of the distances required to accelerate from BRP to the highest speed reached during the rejected take-off. iii) The accelerate-stop distance on a dry runway. achieved in a manner consistent with the attainment of V2 by 35ft. assuming the critical power unit inoperative at VEF. 2. aerodrome pressure altitude and ambient temperature.1 The maximum take-off mass is determined as the lowest of: • the structural limit • the field length limit • the climb limit (WAT) • the tyre speed limit • the brake energy limit • the obstacle limit.4) accounts for runway slope. The sum of the distances required to accelerate from BRP to the highest speed reached during the rejected take-off. plus a distance equivalent to 2 seconds at the V1 for take-off from a wet runway.2 The Field Length requirements specified in CS 25 are: a) If the take-off distance includes a clearway. a balanced-field take-off. flap position. The total of the gross distance from the start of the take-off run to the point at which VLOF is reached. The horizontal distance from the brakes release point (BRP) to a point equidistant between VLOF and the point at which the aeroplane reaches 35 ft with the critical power unit inoperative.1. The field-length used in the graph is based on the minimum V1 being equal to VMCG.Aeroplane Performance Manual 2 2. therefore.MRJT1 Page 7 . assuming the critical power unit fails at VEF on a dry. f) Proceed horizontally right to the mass grid reference line. hard surface. with a pencil.3 Method of Use of the “Take-Off Performance Field Limit” Graph (Figure 4. assuming the critical power unit fails at VEF on a wet or contaminated hard surface. Example: Field Length Available (TORA) Runway slope Wind Component Flaps PMC Ambient Temperature Aerodrome Pressure Altitude Solution: Field Length Limited TOM 63000 kg 9600 ft 1% Uphill 20 kt Head 15° ON + 33 °C 2.CAP 698 CAA JAR-FCL Examinations .1. draw a vertical line from the reference line through the mass grid. e) Enter at the aerodrome ambient temperature and proceed vertically to the aerodrome pressure altitude.4) a) Enter with Field Length Available (TORA). b) Parallel the grid lines to the appropriate runway slope then continue vertically to the wind component reference line. The horizontal distance from BRP to the point at which the aeroplane attains 35 ft.MRJT1 Page 8 . with a pencil. The horizontal distance from BRP to the point at which the aeroplane attains 15 ft. c) Parallel the grid lines to the appropriate wind component then continue vertically to the flap reference line. If flap is 5°. g) From this point interpolate and follow the grid lines to intersect the vertical line drawn in d) above. Move vertically to the runway slope reference line.Aeroplane Performance Manual ii) One engine inoperative (dry runway). achieved in a manner consistent with the achievement of V2 by 35ft. 2. h) From this intersection draw a horizontal line to read the Field Length Limited TOM i) Apply any corrections necessary. iii) One engine inoperative (wet runway).000 ft July 2006 Section 4 . d) If flap is 15°. draw a vertical line through the weight grid. parallel grid lines then. 4 Take-Off Performance – Field Length Limit Graph July 2006 Section 4 .CAP 698 CAA JAR-FCL Examinations .Aeroplane Performance Manual 70 AIR PO RT P RE S 100 SURE 0 ft AL TIT -1 UD E 0 65 1 3 5 6 7 8 9 60 MINIMUM FIELD LENGTH REQUIRED 4 55 50 ENV IRO 45 A TE SSU MP M ER ED LIM ATU IT RE 40 35 REF LINE 30 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 AIRPORT OAT °C FLAP POSITION UP RUNWAY SLOPE % BASED ON A/C AUTO. INCREASE ALLOWABLE MASS BY 550 kg FOR ENGINE ANTI-ICE ON DECREASE ALLOWABLE MASS BY 350 kg HEAD 40 15 REF LINE 5 WIND 20 kt 0 PMC OFF CORRECTION TAIL 10 REF LINE ALTITUDE TEMPERATURE MASS DECREMENT ft °C kg BELOW 0 ALL 5000 5000 ABOVE 21 0 & ABOVE 21 & BELOW 1660 VALID FOR ANTI-ICE ON OR OFF 2 REF LINE 0 100 m 1000 ft 3 12 4 16 20 24 28 32 36 40 13 14 -2 DOWN 5 7 8 6 9 10 11 12 FIELD LENGTH AVAILABLE ft x1000 Figure 4.MRJT1 Page 9 FIELD LENGTH LIMIT BRAKE RELEASE MASS 1000 kg 2 NME NTA L LI MIT . FOR PACKS OFF. b) Move vertically to the aerodrome pressure altitude.MRJT1 Page 10 . Method of Use a) Enter the graph at aerodrome ambient temperature. d) Apply any corrections necessary.Aeroplane Performance Manual 2.2.2 2. 2.2. c) Travel horizontally left to the flap reference line and apply the appropriate setting to read climb limit mass.2 Use of the Climb Limit Graph (Figure 4. It does not guarantee obstacle clearance.1 Take-Off Climb Requirements During the take-off climb the aeroplane must: a) Attain the most severe gradient requirement of the take-off Net Flight Path b) Avoid all obstacles in the obstacle accountability area by the statutory minimum vertical interval. Example: Field Length Available (TORA) OAT Flaps Solution: Climb Limited TOM 53400 kg 2000 ft + 33°C 15° July 2006 Section 4 .5 guarantees attainment of the most severe gradient requirement of the net flight path.CAP 698 CAA JAR-FCL Examinations .5) The graph at Figure 4. INCREASE ALLOWABLE MASS BY 900 kg.Aeroplane Performance Manual 65 R AI RT PO SU ES PR 60 RE TU TI AL -1 0 DE 1 2 00 10 55 ft 3 CLIMB LIMIT BRAKE RELEASE MASS 1000 kg 4 5 6 9 45 40 EN VI RO NM EN TA LL RE TU RA E MP TE IT ED LIM UM SS A 50 35 30 5 FLAP POSITION 15 10 & BELOW 20 30 40 AIRPORT OAT °C 50 60 70 BASED ON A/C AUTO WITH APU ON OR OFF.CAP 698 CAA JAR-FCL Examinations . FOR PACKS OFF.5 Take-Off Performance – Climb Limit July 2006 IM IT 7 8 Section 4 . REF LINE PMC OFF CORRECTION ALTITUDE ft BELOW 5000 5000 & ABOVE TEMPERATURE °C ALL ABOVE 21 21 & BELOW MASS DECREMENT kg 0 0 1860 Figure 4. FOR OPERATION WITH ENGINE ANTI-ICE ON SUBTRACT 190 kg WHEN AIRPORT PRESSURE ALTITUDE IS AT OR BELOW 8000 ft OR 530 kg WHEN AIRPORT PRESSURE ALTITUDE IS ABOVE 8000 ft.MRJT1 Page 11 . 3 Take-Off Tyre Speed Limit The graph at Figure 4.CAP 698 CAA JAR-FCL Examinations . For 210 mph tyres and/or 15° flap.MRJT1 Page 12 . Proceed vertically to the aerodrome pressure altitude.Aeroplane Performance Manual 2. Correct as necessary. Example: OAT Airfield Pressure Altitude Flaps PMC Tyres Uncorrected limit Correction Solution: Tyre Limit Mass 78900 kg + 33°C 2000 ft 15° ON 210 mph 80400 kg -1500 kg July 2006 Section 4 . Method of Use Enter the graph with aerodrome OAT.6 presents the limitation on take-off weight for 225 mph tyres and 5° flap. apply the correction below the graph. then horizontally left to read the tyre speed limit. MRJT1 Page 13 .Aeroplane Performance Manual 225 MPH TYRES -1 0 80 1 2 3 4 AI O RP 5 75 6 RT FLAPS 5 TYRE SPEED LIMIT MASS 1000 kg 7 ES PR T 9 TI AL RE SU 8 70 E UD 00 10 ft 65 60 55 -40 -30 -20 -10 0 10 20 AIRPORT OAT °C CORRECTION + 6600 kg .6 Take-Off Tyre Speed Limit July 2006 Section 4 .9600 kg .CAP 698 CAA JAR-FCL Examinations .1500 kg + 400 kg per kt -650 kg per kt 30 40 50 60 70 CONDITIONAL DEVIATION 15° Flap 210 mph Tyres 15° Flap + 210 mph Tyres Headwind Tailwind PMC OFF CORRECTION ALTITUDE ft Below 5000 5000 & Above TEMPERATURE °C Above 21 21 & Below Above 21 21 & Below MASS DECREMENT kg 250 210 200 270 Figure 4. high aerodromes or operating with a tail wind. Travel horizontally to OAT. apply the correction below the graph. Generally VMBE will not be limiting except at hot. Always check VMBE when outside the shaded area of the top left grid or when there is a tail wind or when employing the improved climb technique.7 enables the determination of VMBE.Aeroplane Performance Manual 2.CAP 698 CAA JAR-FCL Examinations .5% Uphill 10 kt Head ON July 2006 Section 4 .4 Take-Off Brake Energy Limit Figure 4.MRJT1 Page 14 . then horizontally right to VMBE. Make V1 = VMBE and recalculate the other V speeds for the reduced mass. Method of Use Enter the graph with aerodrome pressure altitude. Drop vertically to take-off mass. If V1 exceeds VMBE. Example: Take-Off Mass Airfield Pressure Altitude Ambient Temperature Runway Slope Wind Component PMC Solution: VMBE = 165 + 3 + 3 =171 kt 64000 kg 5600 ft -10° C 1. 7 Take-Off Brake Energy Limit July 2006 Section 4 .Aeroplane Performance Manual CHECK VMBE WHEN OUTSIDE SHADED AREA OR WHEN OPERATING WITH TAILWIND OR IMPROVED CLIMB 10 PRESSURE ALTITUDE 1000 ft 8 AI ALL FLAPS RP T OR 6 4 2 0 -1 40 45 50 55 60 65 70 T OA °C 0 0 0 -5 -4 -3 0 0 -2 0 -1 10 20 30 40 50 BRAKE RELEASE MASS 1000 kg INCREASE VMBE BY 2 kt FOR 1% UPHILL RUNWAY SLOPE DECREASE VMBE BY 5 kt FOR 1% DOWNHILL RUNWAY SLOPE INCREASE VMBE BY 3 kt FOR 10 kt HEADWIND WIND DECREASE VMBE BY 20 kt FOR 10 kt TAILWIND 44 40 SLOPE 200 190 52 48 60 64 PMC OFF CORRECTION IS -1 kt BR AK E RE LE A 68 EIG W SE HT 1 0 00 56 180 170 160 150 140 ADJUST VMBE FOR SLOPE AND WIND NORMAL TAKE-OFF: DECREASE BRAKE RELEASE MASS BY 300 kg FOR EACH KNOT V1 EXCEEDS VMBE. VR.MRJT1 Page 15 VMBE kt IAS kg . V2 SPEED INCREMENTS FOR THE LOWER CLIMB MASS IMPROVEMENT Figure 4. DETERMINE V1. DETERMINE NORMAL V1.CAP 698 CAA JAR-FCL Examinations . VR. V2 SPEEDS FOR LOWER BRAKE RELEASE MASS IMPROVED CLIMB TAKE-OFF: DECREASE CLIMB MASS IMPROVEMENT BY 160 kg FOR EACH KNOT V1 EXCEEDS VMBE. In no circumstances may V1 be less than the VMCG nor may it exceed VR or VMBE. July 2006 Section 4 . Sub-tables are provided to enable V1 to be corrected for the effects of slope and wind.5.5 V Speeds and % N1 Values The V speeds quoted in Figures 4. 2. V1 can be further adjusted to account for any clearway or stopway by using the following table.9 are those for a balanced-field take-off with no stopway or clearway.MRJT1 Page 16 .8 and 4. This table must not be used if the stopway and/or clearway were used in the determination of the field length limited take-off mass.CAP 698 CAA JAR-FCL Examinations .1 V1 Adjustments Normal V1 KIAS Clearway Minus Stopway (ft) 800 600 400 200 0 -400 -800 100 -4 -2 0 1 1 120 -3 -3 -1 0 1 1 140 -3 -2 -2 -1 0 1 1 160 -2 -1 -1 0 0 1 1 Maximum Allowable Clearway Maximum Allowable Clearway for V1 Reduction (ft) 400 500 550 600 700 750 Field Length (ft) 4000 6000 8000 10000 12000 14000 In the absence of more precise details the above table should be used as a guide to the maximum allowable clearway permitted. The runway is assumed to be hard. level and in still air conditions.Aeroplane Performance Manual 2. MRJT1 Page 17 . take-off is not permitted. Extract V1. enter the table at the top of Figure 4.Aeroplane Performance Manual 2.8 or 4. at the actual take-off mass and interpolate the correction necessary. c) Enter the V speed tables at the actual take-off mass.8 or 4. as appropriate. July 2006 Section 4 . h) Check TORA exceeds TORR.5. g) Compare V1 with VMCG.3 Stabiliser Trim Setting To determine the take-off stabiliser trim setting select the appropriate table and use the actual take-off mass and % MAC centre of gravity to read or calculate the appropriate setting.9.9.5. f) Use the sub-table below Figure 4. to determine the VMCG.2 The Calculation of V Speeds To calculate the V speeds use the tables (at Figure 4.8 or 4. as appropriate.8 or 4. If V1 is less than VMCG. If it does not. Density Sub Graph 40 & below 9 60 80 TEMPERATURE °F 100 120 140 160 F 6 PRESSURE ALTITUDE 1000 ft 3 B 0 A 4& 10 below 20 30 40 TEMPERATURE °C 50 60 70 E D C 2.9 as appropriate) in the following manner: a) Enter the density sub-graph (below) with pressure altitude and ambient temperature to determine which of the columns of the tables should be used. e) Apply the corrections to V1.CAP 698 CAA JAR-FCL Examinations . d) If it is necessary to correct V1 for slope and/or wind component. the take-off mass must be reduced. b) Select the tables appropriate to the flap setting from Figure 4.9. VR and V2. Enter the left column at the ambient temperature and then proceed right along the row to the appropriate aerodrome pressure altitude (interpolating if necessary). Extract VMCG. Alt.% MAC Stab.CAP 698 CAA JAR-FCL Examinations .Aeroplane Performance Manual Figure 4. VMCG Actual OAT °C 55 50 40 30 20 10 -50 °F 131 122 104 86 68 50 -58 0 104 107 111 116 116 116 118 2 103 107 111 113 113 115 Press. X 1000 ft 4 6 8 103 107 111 111 112 99 104 107 108 109 94 98 102 104 105 For A/C packs 'off' increase VMCG by 2 knots Flaps 5° CG. Trim Stabiliser Trim Setting 6 5½ 10 5 14 4½ 18 3¾ 22 3¼ 26 2¾ 30 2¼ For masses at or below 45350 kg subtract ½ unit For masses at or above 61250 kg add ½ unit Stab trim settings must be between 1 and 5 ¾ units July 2006 Section 4 .MRJT1 Page 18 .8 Take-Off Speeds Flaps 5° PMC ON Mass (1000 kg) 70 60 50 40 -2 -3 -2 -2 -2 Slope/Wind V1 adjustment Slope % 0 0 0 0 0 2 4 2 1 1 -15 -3 -3 -4 -4 Wind kt 0 0 0 0 0 40 1 1 1 1 * V1 not to exceed VR Mass (1000 kg) 70 65 60 55 50 45 40 Mass (1000 kg) 70 65 60 55 50 45 40 A V1 158 151 144 137 129 121 113 VR 163 155 148 139 131 123 114 D V1 VR V2 V1 V2 168 161 155 149 142 136 130 V1 158 152 145 138 130 122 113 B VR 164 156 148 140 132 124 116 E VR V2 V1 V2 169 162 155 149 142 135 129 V1 153 146 138 131 122 113 C VR 157 149 141 133 125 116 F VR V2 V2 162 155 148 142 135 128 140 132 124 113 143 134 126 117 148 141 135 128 133 125 114 135 127 118 141 134 127 128 119 128 120 134 126 In shaded area check VMCG for actual temp. % MAC Stab. X 1000 ft 4 6 8 103 107 111 111 112 99 104 107 108 109 94 98 102 104 105 For A/C packs 'off' increase VMCG by 2 knots Flaps 15° CG. VMCG Actual OAT °C 55 50 40 30 20 10 -50 °F 131 122 104 86 68 50 -58 0 104 107 111 116 116 116 118 2 103 107 111 113 113 115 Press.MRJT1 Page 19 . Alt.CAP 698 CAA JAR-FCL Examinations .9 Take-Off Speeds Flaps 15° PMC ON Mass (1000 kg) 70 60 50 40 -2 -3 -2 -2 -2 Slope/Wind V1 adjustment Slope % 0 0 0 0 0 2 4 2 1 1 -15 -3 -3 -4 -4 Wind kt 0 0 0 0 0 40 1 1 1 1 * V1 not to exceed VR Mass (1000 kg) 70 65 60 55 50 45 40 Mass (1000 kg) 70 65 60 55 50 45 40 A V1 150 143 137 130 122 114 104 VR 152 145 139 131 124 116 107 D V1 VR V2 V1 V2 158 152 146 141 135 128 122 V1 145 138 131 123 116 104 B VR 146 140 132 125 117 109 E VR V2 V1 V2 151 146 140 134 128 122 V1 C VR V2 139 131 124 116 104 140 133 125 118 110 F VR 146 140 134 128 122 V2 134 126 118 109 134 126 119 111 140 134 127 121 127 120 111 128 120 112 133 126 120 120 112 121 113 127 120 In shaded area check VMCG for actual temp. Trim Stabiliser Trim Setting 6 5 10 4¼ 14 3¾ 18 3 22 2½ 26 1¾ 30 1 For masses at or below 45350 kg subtract ½ unit For masses at or above 61250 kg add ½ unit Stab trim settings must be between 1 and 5 ¾ units July 2006 Section 4 .Aeroplane Performance Manual Figure 4. 4 92.3 95.7 96.0 96.8 94.2 95.4 94.6 89.8 91.0% N1 Do not operate engine anti-ice 'on' at airport OAT above 10°C (50°F).0 91.2 91.0 95.8 95.4 95.0 94.3 94.4 96.8 90.0 94.6 95.2 91.2 0 94.3 92.9 86.2 90.5 93.8 95.8 96.1 97 .4 93.0 94.0 93.2 96.9 90.6 91.6 92.0 95.3 96.5 94.3 96.8 97 .9 95.3 87 .6 95.1 95.0 96.3 95.8 90.4 92.8 96.9 92.4 94.6 96.6 90.2 95.9 95.5 96.5 89.4 96.9 94.9 95.9 94.0 86.6 93.5 95.4 95.5 2000 93.0 90.5 88.2 93.7 87 .4 97 .1 95.3 95.7 88.5 96.6 88.9 95.8 90.5 94.6 92.6 87 .1 95.3 95.5 95.7 89.3 93.6 92.2 94.3 95.6 95.7 93.1 90.2 86.2 94.2 94.9 93.3 97 .0 90.3 96.9 95.7 88.9 87 .3 88.0 87 .1 95.2 90.4 94. A/C 'auto'.6 95.5 95.4 89.3 87 .0 88.0 96.3 88.3 94.7 90.7 94.4 88.6 94.6 92.9 94.8 86.5 95.9 97 .6 95.5 97 .1 92.6 85.0 95.7 Valid for PMC 'on'.9 91.1 91.4 94.8 95.9 96.0 89.6 95.1 86.3 92.4 94.2 96.8 96.2 87 .4 95.4 90.1 95.4 94.4 91.9 88.2 91.0 96.6 96.1 96.5 90.0 88.4 89.9 96.6 95.2 91.7 88.3 96.8 95.5 90.4 94.4 94.8 91.0 97 .3 90.0 89.1 94.1 88.2 93.9 96.MRJT1 Page 20 .4 96.1 95.1 90.8 96. engine anti-ice 'on' or 'off' For A/C 'off' Add 1.1 94.3 94.8 95.0 89.6 95.8 96.9 93.2 93.2 96.9 89.0 87 .4 96.6 94.5 90.1 95.8 92.2 97 .7 95.3 90.3 90.6 96.1 88.3 92.3 95.0 96.8 95.8 96.8 88.3 94.9 95.2 89.9 85.1 96.0 95.6 91.3 89.4 89.8 95.5 95.1 94.4 93.2 94.3 95.2 89.7 94.1 94.8 94.0 88.7 87 .8 95.5.4 96.3 95.6 87 .9 3000 4000 5000 6000 7000 8000 Figure 4.7 95. Read % N1 in the aerodrome pressure altitude column.0 94.9 92.1 96.CAP 698 CAA JAR-FCL Examinations .1 93.7 92.10 Expanded Maximum Take-Off % N1 Airport OAT °C 54 52 50 48 46 44 42 40 38 36 34 32 30 28 26 24 22 20 18 16 14 12 10 8 6 4 2 0 -2 -4 -6 -8 -10 -12 -14 -16 -18 -20 -22 -24 -26 -28 -30 °F 129 126 122 118 115 111 108 104 100 97 93 90 86 82 79 75 72 68 64 61 57 54 50 46 43 39 36 32 28 25 21 18 14 10 7 3 0 -4 -8 -11 -15 -18 -22 93.8 94.0 91.9 96.5 91.0 95.5 91.4 91.2 96.3 91.3 92.8 89.2 92.6 93.Aeroplane Performance Manual 2.6 93.7 95.6 95.2 93.7 94.3 85.5 94.8 94.9 89.7 93.0 89.1 93.2 95.0 92.1 93.7 94.4 90.1 89.7 91.0 92.6 96. To determine the % N1 values use the following procedure: a) Select the table appropriate to either PMC on or off.8 87 .0 96.3 93.7 95.9 91.1 95.1 89.7 94.7 90.2 88.9 92.8 96.4 88.9 90.6 92.5 94.0 93.5 92.1 88. climb or goaround).5 94.5 96.7 93. July 2006 Section 4 .4 96.7 89.6 89.6 94.5 87 .2 96.2 90.7 95.3 94.5 96.5 96.8 93. c) Enter the left column of the table with either aerodrome ambient temperature or TAT as appropriate.9 96.3 91.7 94.1 96.0 94.2 90.8 91.4 90.3 95.8 94.9 94.1 94.6 93.4 93.0 95.7 95.7 89.3 94.3 93.3 94.0 92.4 86.8 96.6 96.6 94.0 87 . b) Select the table that is appropriate to the phase of flight (take-off.7 90.2 94.7 96.7 94.5 95.1 97 .2 95.4 93.7 92.4 95.9 97 .7 90.6 94.1 91.2 92.0 91.4 % N1 Values All % N1 tables may be used for either engine anti-icing 'on' and 'off' configurations.7 91.6 86.2 95.8 89.2 95.1 90.2 95. Correction is necessary if the air conditioning packs are off.6 95.9 97 .3 96.6 91.8 90.3 96.4 95.3 95.6 90.5 89.9 93.6 94.5 95.3 94.2 92.2 86.9 91.0 1000 93. Pressure Altitude ft -1000 93.7 96.8 95.4 91.5 91.7 89.0 95.9 94.4 95.5 93.9 93.7 94.6 93.9 96.5 96.0 96.9 92.0 89.5 92.0 92.6 94.1 94.3 88.2 89.7 88.6 94.8 92.9 93.9 91.3 94. 9 96.7 92.4 -1.5 85.8 89.5 94.2 95.5 -1.0 95.2 Airport Pressure Altitude (ft) 3000 93.9 95.3 + 0.1 94.1 92.2 -0.8 86.4 94.0 -1.7 Do not operate engine anti-ice 'on' at airport OAT above 10°C (50°F) Maximum Climb % N1 TAT(°C) 50 40 30 20 10 0 -10 -20 -30 -40 -50 A/C Packs Off A/C Packs High Engine A/I On Wing A/I On 0 90.7 20 93.0 + 0.5 92.1 94.4 94.2 92.4 -1.7 96.2 82.0 -1.5 98.9 90.9 96.3 + 0.6 96.6 96.6 93.2 95.0 -1.0 -0.7 95.1 86.11 Maximum T/O & Maximum Climb – % N1 values Maximum Take-Off % N1 Valid for 2 packs on (auto) Engine A/I on or off Airport OAT °C 55 50 45 40 35 30 25 20 15 10 5 0 -10 -20 -30 -40 -50 °F 131 122 113 104 95 86 77 68 59 50 41 32 14 -4 -22 -40 -58 0 93.5 96.3 94.9 93.2 84.7 95.1 96.3 84.5 89.8 95.2 -0.0 Section 4 .7 4000 93.1 91.7 91.1 87 .9 92.1 + 0.0 97 .1 95.8 95.4 -0.8 79.7 96.5 83.0 95.7 95.6 84.0 88.6 95.2 95.2 93.0 -2.7 82.0 94.3 94.0 96.1 83.4 94.2 96.Aeroplane Performance Manual Figure 4.8 94.8 95.9 94.5 93.7 95.6 94.5 93.5 93.2 88.5 97 .2 85.5 + 0.8 94.5 89.6 93.8 91.7 96.7 -0.8 88.3 84.3 86.5 96.2 86.7 90.7 + 0.0 92.6 97 .4 97 .3 96.5 94.7 87 .2 + 0.5 91.6 96.5 5 91.9 + 0.1 95.5 1000 93.9 86.3 97 .0 92.2 86.5 96.6 96.4 99.7 95.6 88.6 96.3 85.6 -1.9 96.9 -1.2 92.3 5000 6000 7000 8000 PMC ON 94.4 99.9 92.6 95.0 96.2 93.1 88.3 93.0 88.CAP 698 CAA JAR-FCL Examinations .8 -1.9 89.0 86.0 92.3 -0.6 94.6 87 .2 95.0 95.0 84.3 95.4 -1.3 84.1 93.2 89.0 96.2 93.1 95.6 95.9 95.1 95.4 92.9 84.1 87 .8 94.6 97 .1 94.6 93.6 89. -0.6 97 .3 -0.3 94.8 92.6 -0.1 97 .9 94.4 96.4 86.0 -2.2 88.6 87 .7 92.0 90.7 96.1 87 .7 -1.9 92.5 95.5 82.6 90.1 95.2 95.0 250/280/0.4 -0.3 -0.3 91.3 82.3 94.1 90.0 % N1 Bleed Adjustment Configuration A/C packs off + 1.3 94.2 95.3 89.4 90.1 95.4 92.0 96.1 93.4 87 .2 97 .7 90.5 82.6 95.6 86.0 94.2 95.6 -1.2 90.MRJT1 Page 21 .6 95.9 2000 93.8 -0.1 90.74M Airport Pressure Altitude x1000 (ft) 10 92.5 84.1 91.2 89.9 85.7 95.8 81.8 97 .2 90.4 91.0 94.7 91.0 -1.5 94.8 88.5 + 0.1 95.6 93.4 97 .8 95.5 96.9 85.6 97 .4 96.5 80.7 86.6 95.9 July 2006 % N1 Corr.1 91.4 88.6 95.5 98.0 95.8 25 30 35 37 Valid for 2 packs on (auto) Engine A/I off 94.9 96.9 96.6 15 93.1 92.1 96.0 96. 0 91.8 95.2 94.4 1000 93.2 96.3 96.1 96.8 95.7 4000 94.6 95.3 96.6 93.0 % N1 Bleed Adjustment TAT °C Configuration A/C Packs Off A/C Packs High Wings A/I All Engines 1 Eng.0 94.4 94.5 90.1 95.4 94.9 97 .6 93.0 96.7 94.7 95.5 96.9 85.4 91.5 89.2 94.8 88.1 87 .0 95.3 91.7 90.2 82.9 92.6 95.5 95.8 86.8 -0.2 84.2 96.8 96.6 -2.5 83.7 96.5 96.7 96.7 96.2 94.1 94.3 92.8 95.3 95.1 96.3 -1.6 95.7 92.1 90.1 94.2 89.5 91.Aeroplane Performance Manual Figure 4.6 94.9 86.0 96.5 96.9 94.5 96.9 94.6 95.2 94.8 92.2 Engine A/I on or off Pressure Altitude (ft) 3000 94.5 97 .3 +60 +1.8 2000 93.3 -1.12 Maximum Go-Around – % N1 values Maximum Go-Around % N1 Valid for 2 packs on (auto) Airport OAT °C 55 50 45 40 35 30 25 20 15 10 5 0 -10 -20 -30 -40 -50 °F 131 122 113 104 95 86 77 68 59 50 41 32 14 -4 -22 -40 -58 TAT °C 58 53 48 43 38 33 28 23 18 13 8 3 -8 -18 -28 -38 -48 0 93.2 95.1 95.1 95.0 90.1 95.0 95.1 95.6 96.3 92.7 95.2 93.7 96.0 86.0 95.2 94.0 94.6 97 .6 86.5 87 .5 93.1 93.6 95.2 93.6 84.CAP 698 CAA JAR-FCL Examinations .2 95.7 82.1 95.1 95.3 85.0 -0.2 94.0 88.5 96.0 84.0 96.3 88.1 95.4 88. -60 +0.5 86.0 91.6 90.7 93.6 96.1 85.8 87 .8 89.0 97 .9 96.5 85.7 97 .3 94.2 89.4 92.7 92.1 95.2 96.MRJT1 Page 22 . Inop.4 87 .9 95.5 84.6 95.1 93.6 89.7 Do not operate engine anti-ice “on” at total air temperature above 10°C (50°F) July 2006 Section 4 .7 92.6 95.8 89.0 87 .6 96.9 94.3 -2.1 83.2 86.6 95.3 5000 6000 7000 8000 PMC ON 94. 9 97 .9 97 .1 96.7 88.9 96.2 87 .1 96.5 96.9 97 .3 90.2 86.8 97 .MRJT1 Page 23 .9 95.5 88.5 92.2 94.3 87 .8 96.8 92.3 95.0 94.7 94.5 96.2 94.2 87 .5 91.0 88.7 91.3 97 .9 94.2 95.8 83.9 97 .8 91.2 97 .6 93.5 92.3 94.9 97 .3 A/C Packs off Valid for Engine A/I on or off Airport Pressure Altitude (ft) 3000 96.8 97 .9 96.6 95.4 96.1 84.1 87 .5 96.1 93.6 90.3 97 .7 98.4 85.6 1000 95.1 95.1 96.8 97 .0 89.6 95.2 96.7 95.4 85.4 96.9 97 .3 97 .8 97 .7 98.2 85.0 86.0 95.9 95.4 94.3 96.8 97 .8 89.8 2000 95.8 97 .3 90.4 96.9 86.1 87 .2 93.1 97 .4 93.1 97 .1 95.0 5000 6000 7000 8000 96.8 97 .9 85.7 97 .4 95.1 96.1 97 .3 96.0 96.4 92.13 % N1 values Maximum Take-Off % N1 Airport OAT °C 55 50 45 40 35 30 25 20 15 10 5 0 -10 -20 -30 -40 -50 °F 131 122 113 104 95 86 77 68 59 50 41 32 14 -4 -22 -40 -58 0 94.1 96.Aeroplane Performance Manual Figure 4.9 96.8 97 .5 89.8 97 .5 For maximum climb and go-around use PMC 'on' % N1 Temperature °C (°F) Above 21 (70) 21 (70) & Below Above 21 (70) 21 (70) & Below Speed Adjustment KIAS VMCG +6 +4 +6 +4 V1 & VR 0 0 0 +1 Take-Off Speeds Adjustment Altitude (ft) Below 5000 5000 & Above July 2006 Section 4 .7 93.4 95.2 89.7 98.5 3000 95.9 96.5 85.4 93.8 95.9 96.9 96.4 96.5 86.0 89.4 93.5 90.1 96.1 96.9 89.7 96.4 96.4 95.1 84.7 94.8 92.7 94.8 91.9 94.0 97 .7 86.5 91.3 97 .6 88.4 95.5 86.2 97 .8 97 .3 97 .7 98.2 97 .5 92.3 96.3 95.7 83.7 84.9 4000 95.3 97 .6 86.3 96.3 96.9 92.4 87 .5 84.1 97 .3 95.9 85.3 95.5 97 .4 96.1 85.6 85.2 5000 6000 7000 8000 PMC OFF 95.8 94.1 97 .7 4000 96.6 84.8 97 .7 92.5 94.1 96.3 96.5 95.8 97 .0 94.2 97 .8 84.3 96.3 95.7 98.7 82.0 93.2 92.2 87 .4 96.0 92.9 95.3 95.5 95.9 95.2 94.3 96.1 96.3 95.4 96.4 94.3 85.2 90.3 96.0 A/C Packs on (Auto) Valid for Engine A/I on or off Airport Pressure Altitude (ft) 2000 94.3 97 .7 98.3 96.4 97 .6 96.9 96.1 97 .0 93.7 87 .6 92.9 94.6 94.8 86.8 95.4 94.5 95.2 88.9 96.9 91.5 97 .2 91.4 84.3 83.8 93.9 90.CAP 698 CAA JAR-FCL Examinations .9 87 .2 86.8 96.7 94.7 84.6 94.4 96.9 97 .8 97 .1 93.1 90.5 92.8 96.0 89.0 90.3 88.2 91.6 93.3 95.3 97 .6 88.4 86.9 96.4 96.7 90.5 83.1 92.8 90.8 97 .3 92.4 94.0 89.8 1000 94.3 90.4 95.8 94.9 83.3 96.8 91.9 97 .9 96.4 88.3 85.7 91.1 97 .9 94.9 96.7 97 .9 96.3 97 .0 88.0 Do not operate engine anti-ice “on” at airport OAT above 10°C (50°F) Maximum Take-Off % N1 Airport OAT °C 55 50 45 40 35 30 25 20 15 10 5 0 -10 -20 -30 -40 -50 °F 131 122 113 104 95 86 77 68 59 50 41 32 14 -4 -22 -40 -58 NOTE: 0 95.7 98.3 95.1 97 .5 89.4 92.3 88.9 96.9 96. If adjusted V1 is less than VMCG. b) Contaminant depths exceeding 13mm (0.6. f) Calculate the V speeds for the actual take-off mass.6 2. Mass & V1 interpolation for 50. b) Select the table(s) appropriate to the depth of contaminant (interpolating if necessary). travel right to the aerodrome pressure altitude column. d) If in the shaded area. if necessary.1 2.CAP 698 CAA JAR-FCL Examinations .460 kg V1 = VMCG = 114 kt At 42460 kg. proceed to the bottom table.MRJT1 Page 24 .5 in) due to spray impingement damage. then re-enter the left table at the actual mass to determine the V1 reduction to be made.. Extract the mass reduction.3 The Determination of Take-Off Mass a) Calculate the normal limiting take-off mass for a dry runway i. g) If not in the shaded area in c) above. Make V1 = VMCG.54 (to 2 dp) Revised Mass = 42. e) The lower of the two values from c) and d) above is the maximum take-off mass for a contaminated runway. VR = 119 kt. field length limit.e. move right to the appropriate aerodrome pressure altitude column.Aeroplane Performance Manual 2.460 kg Limiting Mass interpolation for 5800 ft TORA @ 2000 ft Revised Mass = 44. c) Enter the left column of the top table at the normal limiting take-off mass.2 Contaminated Runway Take-Off Calculations These calculations assume an engine failure at V1 Contaminated runway take-offs are prohibited for: a) Variable or reduced thrust take-offs. Interpolate for mass and pressure altitude. 2.6. Interpolate as necessary. Extract the maximum permissible takeoff mass.6. Example: Airfield Pressure Altitude OAT Flaps TORA Runway Slope Wind Component TOM PMC Runway condition 2000 ft +2°C 5° 5800 ft 2% Down 10 kt Head 50000 kg ON 10 mm Slush Calculate contaminated runway TOM and V speeds. take-off is not permitted. V2 = 131 kt July 2006 Section 4 . Enter the left column with the take-off run available (TORA). h) Apply the reduction to V1. climb limit or obstacle limit. Calculate maximum take-off mass for a contaminated runway by subtracting the mass reduction from the normal limiting take-off mass.000 kg @ 2000 ft = -7.786 kg Maximum Take-Off Mass = 42. 1 16 6.8 17 6.9 22 3.0 14 7 .MRJT1 Page 25 .9 18 5.3 12 7 .08 Inch (2mm) Slush/Standing Water Depth Mass x 1000kg Press Alt (ft) 40 44 48 52 56 60 64 68 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS Mass and V1 Reductions 0 2.6 18 6.0 19 4.4 21 4.CAP 698 CAA JAR-FCL Examinations .6 16 6.Aeroplane Performance Manual Figure 4.A/C Auto or off 0.3 21 4.8 15 7 .2 21 5.3 16 6.9 13 4000 3.2 13 7 .0 19 5.7 18 6.5 15 7 .7 22 4.5 11 8000 4.14 Advisory Information – Contaminated Runways ALL FLAPS One Engine Inoperative .6 10 8.9 20 5.2 8 Field Length Available (ft) (TORA) 5600 5800 6000 6200 6400 6600 6800 7000 7200 7400 7600 7800 8000 8200 8400 8600 8800 9000 V1 = VMCG Limit Mass 1000 kg Pressure Altitude (ft) 0 39 42 45 49 52 55 59 62 65 69 4000 34 37 39 42 45 47 50 53 56 59 62 65 68 71 8000 36 39 41 43 46 48 51 53 56 58 61 64 66 July 2006 Section 4 . 2 10 8.8 7 9.9 8 8.0 11 7 .3 14 6.3 10 7 .3 12 7 .7 5 Field Length Available (ft) (TORA) 5400 5600 5800 6000 6200 6400 6600 6800 7000 7200 7400 7600 7800 8000 8200 8400 8600 8800 V1 = VMCG Limit Mass 1000 kg Pressure Altitude (ft) 0 40 43 47 50 53 56 59 63 66 70 4000 35 38 41 43 46 48 51 54 57 60 63 65 68 8000 36 38 41 43 45 48 50 52 55 57 59 62 64 67 July 2006 Section 4 .4 8 9.5 9 8.7 7 9.2 13 7 .1 8 8.MRJT1 Page 26 .9 12 6.7 5 9.1 7 9.0 16 5.9 5 8000 4.CAP 698 CAA JAR-FCL Examinations .Aeroplane Performance Manual Figure 4.5 6 9.3 16 6.4 5 9.14 Continued Advisory Information – Contaminated Runways ALL FLAPS One Engine Inoperative – A/C Auto or off 0.3 18 5.25 Inch (6mm) Slush/Standing Water Depth Mass x 1000kg Press Alt (ft) 40 44 48 52 56 60 64 68 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS Mass and V1 Reductions 0 3.4 19 4.4 5 4000 4. 0 6 6.5 0 8.2 13 5.2 0 11.5 Inch (13mm) Slush/Standing Water Depth Mass x 1000kg Press Alt ft 40 44 48 52 56 60 64 68 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS 1000 kg KIAS Mass and V1 Reductions 0 4.1 0 13.8 0 4000 5.Aeroplane Performance Manual Figure 4.8 0 10.7 0 13.4 1 Field Length Available (ft) (TORA) 5000 5200 5400 5600 5800 6000 6200 6400 6600 6800 7000 7200 7400 7600 7800 8000 8200 8400 V1 = VMCG Limit Mass 1000 kg Pressure Altitude (ft) 0 38 41 44 48 51 54 56 59 62 65 68 70 4000 35 37 40 42 45 47 50 52 55 57 60 62 64 67 69 8000 36 38 40 42 44 47 49 51 53 55 58 60 62 65 July 2006 Section 4 .8 0 12.5 0 10.5 0 11.8 0 8000 6.5 0 15.4 0 12.5 9 6.CAP 698 CAA JAR-FCL Examinations .5 0 13.8 4 8.2 0 13.0 0 12.0 0 13.MRJT1 Page 27 .8 2 8.2 1 9.3 0 11.14 Continued Advisory Information – Contaminated Runways ALL FLAPS One Engine Inoperative – A/C Auto or off 0. Aeroplane Performance Manual 2.15 a) Select the set of graphs appropriate to the flap setting on the “improved climb performance field length limit” graph (Figure 4. travel horizontally right to the vertical axis to read the increase to apply to VR and V2.1 Method of Use of Figure 4. This is done by holding the aeroplane on the ground until it reaches an increased VR and climbing at an increased V2. d) Continue horizontally right to the reference line of the right-hand graph. Check VMBE. From this point interpolate and follow the grid lines to reach a vertical input in the right-hand graph of the normal climb limit mass. and there is a large excess of available field length over that which is required. h) Add the mass increase to the normal climb mass limit. c) From this intersection move horizontally left to the vertical axis to read the climb mass improvement and horizontally right to the vertical axis to read the increase to apply to V1.16) except that the initial entry point is the tyre limit mass minus the climb limit mass. July 2006 Section 4 . f) Repeat this process in the improved climb performance tyre speed limit graph (Figure 4. b) Enter the relevant left-hand graph with the value of the field length limit mass minus the climb limit mass. which equates to Vx (the speed that will attain the maximum climb gradient). then it is possible to improve the take-off weight and still attain the minimum climb gradient requirement (subject to the limitations of the tyre speed and field length limitations). Travel vertically up to the normal 'climb limit' mass line.MRJT1 Page 28 . e) From this intersection. i) Determine the V speeds for this increased mass.CAP 698 CAA JAR-FCL Examinations .7.15).7 Increased V2 Take-Off If the maximum take-off mass is limited by the minimum acceptable climb gradients of the net flight path. 2. g) The lower of the two mass increases is that which must be used together with its associated speed increases. j) Apply the speed increases to the appropriate speeds. 15 Improved Climb Performance – Field Length Limit July 2006 REF LINE Section 4 . V2 25 20 15 10 8 6 4 2 1 40 0 5 10 15 (FIELD LIMIT MASS) MINUS (CLIMB LIMIT MASS) 1000 kg 20 70 50 60 NORMAL CLIMB LIMIT MASS 1000 kg USE SMALLER OF IMPROVED CLIMB MASS (FIELD LENGTH LIMITS) OR (TYRE SPEED LIMITS) APPLY SPEED INCREMENTS TO NORMAL V1.CAP 698 CAA JAR-FCL Examinations .Aeroplane Performance Manual 6 CLIMB MASS IMPROVEMENT 1000 kg 5 4 3 2 1 0 FLAPS 5 NORMAL CLIMB LIMIT MASS 1000 kg 70 60 50 40 V1 28 24 20 16 14 12 10 8 6 4 2 1 NORMAL TAKE-OFF SPEED INCREMENTS kt VR. V2 25 20 16 14 12 10 8 REF LINE 6 4 2 1 40 0 5 10 15 (FIELD LIMIT MASS) MINUS (CLIMB LIMIT MASS) 1000 kg 20 70 50 60 NORMAL CLIMB LIMIT MASS 1000 kg 5 CLIMB MASS IMPROVEMENT 1000 kg 4 3 2 1 0 FLAPS 15 NORMAL CLIMB LIMIT MASS 1000 kg 70 60 50 40 V1 24 20 16 14 12 10 8 6 4 2 1 NORMAL TAKE-OFF SPEED INCREMENTS kt VR.MRJT1 Page 29 . V2 FOR ACTUAL TAKE-OFF MASS CHECK BRAKE ENERGY LIMITS Figure 4. VR. V2 MASS ADJUSTMENT VR. V2 MASS ADJUSTMENT VR. V2 MASS ADJUSTMENT VR.CAP 698 CAA JAR-FCL Examinations . V2 25 20 15 10 8 6 4 2 1 40 0 5 15 20 25 10 (TYRE LIMIT MASS) MINUS (CLIMB LIMIT MASS) 1000 kg 30 70 50 60 NORMAL CLIMB LIMIT MASS 1000 kg USE SMALLER OF IMPROVED CLIMB MASS (FIELD LENGTH LIMITS OR TYRE SPEED LIMITS) APPLY SPEED INCREMENTS TO NORMAL V1. VR. V2 MASS ADJUSTMENT VR. V2 25 20 15 10 8 6 REF LINE 4 2 1 40 70 50 60 NORMAL CLIMB LIMIT MASS 1000 kg NORMAL TAKE-OFF SPEED INCREMENTS kt 5 CLIMB MASS IMPROVEMENT 1000 kg 4 3 2 1 0 FLAPS 15 NORMAL CLIMB LIMIT MASS 1000 kg V1 70 60 50 40 24 20 18 16 14 12 10 8 6 4 2 1 VR.MRJT1 Page 30 .Aeroplane Performance Manual NORMAL TAKE-OFF SPEED INCREMENTS kt 6 CLIMB MASS IMPROVEMENT 1000 kg 5 4 3 2 1 0 0 5 15 20 25 10 30 (TYRE LIMIT MASS) MINUS (CLIMB LIMIT MASS) 1000 kg 35 FLAPS 5 NORMAL CLIMB LIMIT MASS 1000 kg 70 60 50 40 V1 24 20 18 16 14 12 10 8 6 4 2 1 VR. V2 FOR ACTUAL TAKE-OFF MASS CHECK BRAKE ENERGY LIMITS Figure 4.16 Improved Climb Performance – Tyre Speed Limit July 2006 REF LINE Section 4 . determine the maximum take-off % N1. It is a technique employed to preserve engine life or reduce the noise generated at take-off.8 Reduced Thrust Take-Off The reduced thrust take-off procedure is referred to by a number of different names such as the 'Variable Thrust Take-Off' or the 'Assumed Temperature Take-Off'.0% N1 if air conditioning packs are off.Aeroplane Performance Manual 2.CAP 698 CAA JAR-FCL Examinations . interpolating if necessary.8. Travel right along the line to the column appropriate to the ambient temperature. then the environmental limit becomes the assumed temperature. e) Subtract the value determined at paragraph d) from that at paragraph c) to determine the % N1 to be set at take-off. determine the minimum assumed temperature for the aerodrome pressure altitude.MRJT1 Page 31 . 2. Add 1. c) From the same table.1 Restrictions A reduced thrust take-off is not permitted with: • icy or very slippery runways • contaminated runways • anti-skid unserviceable • reverse thrust unserviceable • increased V2 procedure • the PMC off.17a or b. 2.3 Chart Procedure a) Calculate the maximum assumed temperature from Figure 4. 2. for the assumed temperature to be used. Thus the maximum permissible temperature must be calculated for the actual take-off mass from each of the following: • field limit graph • climb limit graph • tyre-speed limit graph • obstacle limit graph From these temperatures. Read the % N1 adjustment.17d with assumed temperature minus ambient temperature. b) From Figure 4.8.8. The only common parameter to enable comparison is that of temperature. Enter the left column with the actual ambient temperature and read the maximum temperature in the column appropriate to the aerodrome pressure altitude. The assumed temperature used must neither exceed the maximum from paragraph a) above or be below the minimum from paragraph b) above.2 Calculation Procedure It is first necessary to determine the most limiting performance condition. This technique can only be used when the available distance greatly exceeds that which is required. d) Enter the left column of Figure 4. The maximum reduction in thrust permitted is 25% of that required for a normal take-off.17c on bottom line. as appropriate. If it does. July 2006 Section 4 . select the lowest and ensure that it does not exceed the environmental limit. 1000 (ft) 0 159 155 151 148 143 142 142 142 1 159 154 149 145 141 139 138 138 2 154 149 145 141 138 136 136 3 155 150 145 140 136 135 135 4 157 151 145 140 135 131 131 5 6 7 8 151 147 140 135 129 127 152 145 140 135 129 127 155 149 143 137 130 126 151 144 138 132 126 Figure 4. Alt 1000 (ft) 0 71 69 67 65 63 61 61 61 61 1 71 68 66 64 62 60 59 59 59 2 68 66 64 62 60 58 58 58 3 69 67 64 62 59 57 57 57 4 70 67 64 61 59 56 55 55 5 6 7 8 °C 55 50 45 40 35 30 25 20 15 & below 67 64 61 59 56 53 53 68 64 62 59 56 54 53 70 66 63 60 57 54 52 68 64 61 58 55 52 Figure 4.17 a Assumed Temperature Reduced Thrust 1. Based on 25% Take-Off Thrust Reduction July 2006 Section 4 .CAP 698 CAA JAR-FCL Examinations .Aeroplane Performance Manual PMC ON Assumed temp. % N1 = Maximum Take-Off % N1 minus % N1 adjustment Maximum Assumed Temperature °C1 OAT Press. Based on 25% Take-Off Thrust Reduction Maximum Assumed Temperature °F1 OAT °F 130 120 110 100 90 80 70 60 & below Press Alt.MRJT1 Page 32 .17 b Assumed Temperature Reduced Thrust 1. 0 96.4 96.2 95.7 97 . °C (°F) 30 (86) 28 (82) 26 (79) 24 (75) Figure 4.3 4. Minus OAT °C 10 20 30 40 50 60 70 80 90 100 110 °F 18 36 54 72 90 108 126 144 162 180 198 Outside Air Temperature °C °F -40 -40 -20 -4 0 32 3.5 3.3 8.2 95.5 3.0 4.5 97 .6 96.2 94.4 5.1 20 (68) 89.0 94.3 2.5 96.2 91.9 4.8 15.1 95.9 91.7 9.5 PMC ON For A/C off add 1.6 45 113 1.3 5.5 25 77 1.5 5.0 93.2 94.6 95.7 11.6 3.8 93.8 5.1 97 .7 6.8 6.5 16 (61) 90.6 95.4 91.2 90.0 96.CAP 698 CAA JAR-FCL Examinations .0 7 .8 10.6 95.1 7 .7 96.8 94.4 92.7 94.3 94.1 92.7 92.1 22 (72) 89.2 95.6 50 55 122 131 1.2 5 41 3.2 90.6 1.4 91.17 d Assumed Temperature Reduced Thrust July 2006 Section 4 .4 95.0 96.5 15 (59) Minimum Assumed Temp.9 95.1 93.6 97 .6 96.3 94.7 95.MRJT1 Page 33 .5 4000 5000 6000 7000 8000 89.6 6.4 87 .1 95.4 89.6 3.8 10.4 2.4 15.3 94.6 94.5 90.0 40 104 1.6 96.8 92.7 96.0 7 .1 93.8 3.Aeroplane Performance Manual Maximum Take-Off % N1 Valid for 2 packs on (auto) Engine A/I on or off Assumed Temp °C 75 70 65 60 55 50 45 40 35 30 25 20 15 °F 167 158 149 140 131 122 113 104 95 86 77 68 59 0 85.7 3.3 3.3 93.6 3.1 93.6 97 .0 4.2 94.0% N1 Airport Pressure Altitude (ft) 3000 87 .4 94.4 89.5 96.1 96.0 96.0 92.0 11.6 96.2 4.9 15 59 1.6 18 (64) 89.0 97 .1 95.5 8.3 90.0 35 95 1.1 95.9 97 .7 92.6 6.1 96.2 95.0 12.1 4.17 c Assumed Temperature Reduced Thrust % N1 Adjustment for Temperature Difference Assumed Temp.5 2.6 2000 87 .6 20 68 1.0 95.8 6.2 10.5 8.2 94.8 6.8 92.1 10 50 1.3 93.4 2.3 13.5 2.4 Figure 4.6 89.8 3.5 2.2 7 .3 96.0 5.7 95.4 9.4 93.9 94.0 12.2 4.4 87 .2 96.6 89.7 91.7 95.1 14.7 96.1 1000 85.2 30 86 1. f) Always ensure V1 is not less than VMCG shown in Figure 4. c) Further reduce V1 by the amount shown in the table at Figure 4. 19) and if ASDA exceeds 7900 ft. V1 has to be reduced to comply with the take-off requirements.18. This will increase the take-off distance required beyond that which would normally be required and thus decrease the distance to any obstacles encountered after take-off.skid operative V1. 2. set V1 = VMCG. Anti-Skid Inoperative V1 Decrements Field length (ft) 6000 8000 10. b) Recalculate the V speeds for this reduced mass.19.19 VMCG For packs 'OFF' add 2 kt July 2006 Section 4 . Max Take-Off Thrust OAT °C 55 50 45 40 35 30 25 20 15 -50 °F 131 122 113 104 95 86 77 68 59 -58 0 105 107 109 111 113 116 116 116 116 118 VMCG Pressure Altitude (Ft) 2000 103 105 107 109 111 113 113 113 115 4000 6000 8000 9000 101 103 105 107 109 111 111 112 96 99 101 104 105 107 108 109 94 96 98 100 102 104 105 94 96 98 100 102 104 Figure 4. e) If V1 is less than VMCG (see Figure 4.Aeroplane Performance Manual 2.000 V1 Reduction (kt) 28 21 17 14 11 Figure 4.9.CAP 698 CAA JAR-FCL Examinations .18 V1 Decrements d) If the actual take-off mass is already less than the anti-skid inoperative limited takeoff mass ensure V1 does not exceed the anti.MRJT1 Page 34 .9 Anti-Skid Inoperative (Simplified method) Because the accelerate/stop distance will be adversely affected if the anti-skid is inoperative.000 12.000 14.1 Simplified Calculation Method a) Decrease the normal runway/obstacle limited take-off weight by 7700 kg. 3.20 and 4.21). They provide a rapid means of obtaining the value of obstacle clearance after take-off. Runway Slope Obstacle Distance from BRP Obstacle Elevation Take-Off Distance Required Solution: Obstacle Height = Obstacle Limited TOM = 1160 .[1000 . Detailed analysis for the specific case from the aeroplane flight manual may result in a less restrictive weight and can account for the non-use of the air conditioning packs.000 ft 1.1 Obstacle-Limit Mass Determination a) Select the graph appropriate to the flap setting. f) Continue vertically to the aerodrome pressure altitude reference line. Example: Flap Setting Aerodrome Pressure Altitude Ambient Temperature PMC Wind Component. then parallel the grid lines to the appropriate temperature.CAP 698 CAA JAR-FCL Examinations .000 ft + 37°C ON 20 kt Head 2% down 18. e) From this intersection.Aeroplane Performance Manual 3 Obstacle Clearance These graphs are provided for Flaps 5° and Flaps 15° (Figures 4. d) Travel horizontally right to intersect the horizontal distance of the obstacle measured from the brake release point. These graphs are not valid for A/C packs off or for take-offs using the improved climb technique. move vertically up to the ambient temperature reference line. g) Parallel the grid lines from this point to the value of the wind component then continue vertically to read the obstacle limited take-off mass. They are intended for use when a detailed airport analysis is not available.20 and Figure 4.MRJT1 Page 35 . b) Adjust the obstacle elevation to account for runway slope to determine obstacle height as shown on Figure 4.(10000 x 2%)] = 360 ft 51. Parallel the grid lines to the appropriate pressure altitude before continuing vertically to the wind component reference line. c) Enter the bottom left vertical axis at the adjusted obstacle height.160 ft 10.700 kg 5° 1.21.000 ft July 2006 Section 4 . MRJT1 Page 36 .20 Obstacle Limits – Flaps 5° July 2006 Section 4 .CAP 698 CAA JAR-FCL Examinations .1 4420 OBSTACLE HEIGHT MUST BE CALCULATED FROM THE LOWEST POINT OF THE RUNWAY TO CONSERVATIVELY ACCOUNT FOR RUNWAY SLOPE Figure 4.Aeroplane Performance Manual OBSTACLE LIMIT MASS 1000 kg 48 50 52 54 56 58 60 62 HEAD 40 20 0 20 4 2 0 40 30 REF LINE REF LINE REF LINE OAT °C PRESSURE ALT 1000 ft WIND kt TAIL 20 10 0 1000 800 DI ST AN CE 600 400 OM 10 BRA 00 KE 30 ft RE LE 28 AS E 26 24 22 20 18 16 14 FR OBSTACLE HEIGHT ft 200 8 12 10 0 PMC OFF CORRECTION TEMPERATURE MASS °C DECREMENT kg 21.1 & BELOW 4970 ABOVE 21. CAP 698 CAA JAR-FCL Examinations .MRJT1 Page 37 .1 & BELOW 4970 ABOVE 21.1 4420 OBSTACLE HEIGHT MUST BE CALCULATED FROM THE LOWEST POINT OF THE RUNWAY TO CONSERVATIVELY ACCOUNT FOR RUNWAY SLOPE Figure 4.Aeroplane Performance Manual OBSTACLE LIMIT MASS 1000 kg 46 48 50 52 54 56 58 60 HEAD WIND kt 40 20 0 20 4 2 0 40 30 REF LINE REF LINE REF LINE TAIL PRESSURE ALT 1000 ft OAT °C 20 10 0 1000 800 DI ST AN OBSTACLE HEIGHT ft CE 600 400 200 OM 10 BR 0 A 30 0 ft KE RE 28 LE 26 AS 24 E 22 20 18 16 14 12 10 FR 8 0 PMC OFF CORRECTION TEMPERATURE MASS °C DECREMENT kg 21.21 Obstacle Limits – Flaps 15° July 2006 Section 4 . MRJT1 Page 38 .Aeroplane Performance Manual INTENTIONALLY LEFT BLANK July 2006 Section 4 .CAP 698 CAA JAR-FCL Examinations . 900 23.5 96.1 5 96.6 96.7 97 .0 94.100 33.7 95. one pack on.9 -20 98.000 31.5 92.1 -40 95. following engine failure in the cruise for 0.74 Mach TAT °C Pressure Altitude (ft) 37 . One engine inoperative information is based upon one pack operating with the A/C switch on “auto” or “high”.500 18.900 30.Aeroplane Performance Manual 4 4.000 35. for specific weights and temperature deviation.22.5 95. This is based on the net one engine inoperative performance (i.9 -15 98.200 16. while maintaining altitude.2 95.MRJT1 Page 39 .7 -5 97 .8 20 95.6 0 97 .300 32.5 94.1 96.5 90. This is accomplished by setting maximum continuous thrust on the remaining live engine and allowing the speed to reduce. This is the gross level-off altitude.2 95.1 97 .1%).700 19.000 29.22 Driftdown Optimum Driftdown Speed Initial Maximum Continuous % N1 One Engine Inoperative 0.1 15 95.22.1 -30 97 .8 95.1 96.6 96.4 91.900 24.6 10 96.0 96.0 97 .700 33.74 Mach.5 93.5 96.0 98.0 97 .3 89.8 -10 98.2 95.3 98.1 95.1 97 .3 94.1 95.4 96.900 ISA + 15°C 12.1 93.5 95.0 98.1 En-route Maximum % N1 Value In the event of an engine failure during the cruise.6 97 .3 91.5 96.7 95.800 22.CAP 698 CAA JAR-FCL Examinations . Figure 4.2 Level Off Altitude For performance planning purposes the level off altitude should be determined from Figure 4.200 21. to the optimum drift-down speed. The drift down speed and level off altitude (stabilising altitude) may be determined from the lower table of Figure 4.800 26.1 96. The initial maximum continuous %N1 setting.1 96.8 95.2 A/C Auto (High) DriftDown Speed/Level Off Mass (1000 kg) Start driftdown 70 65 60 55 50 45 40 35 Level off 67 62 57 52 48 43 38 33 Optimum Driftdown Speed KIAS 245 237 228 218 209 198 187 175 Level Off Altitude (ft) ISA + 10°C & below 14.7 97 .000 19.3 90.200 17 . it will generally be necessary to reduce speed and descend to a lower altitude.7 96.0 97 .000 27 .7 98.3 98.700 July 2006 Section 4 .900 15.400 ISA + 20°C 11.1 92.4 97 .3 88.23.0 96.400 14.000 -50 93.9 95.0 96.0 -25 98.1 98.2 95.200 20. gross gradient -1.800 27 .0 92. may be determined from the upper table of Figure 4. 4.000 29.700 30.0 94.4 97 .6 96.000 33.1 97 .800 26.8 95.1 96. with normal engine bleed for air conditioning.3 93.6 97 .2 92.e. CAP 698 CAA JAR-FCL Examinations .Aeroplane Performance Manual 1 ENGINE INOPERATIVE 30 28 26 24 LEVEL-OFF PRESSURE ALTITUDE 1000 ft 22 20 18 16 14 12 10 8 6 4 2 0 30 35 40 45 50 55 60 65 GROSS MASS 1000 kg A/C OFF +1 0 +1 °C & 5° BE C +2 LO 0° W C +1 0 +1 °C & BE +2 5°C LO 0° C W IS A A/C AUTO (HIGH) DE VI AT I ON BLEED CONFIGURATION ENG ANTI-ICE ON ENG & WING ANTI-ICE ON A/C AUTO (HIGH) BELOW 17.MRJT1 Page 40 .23 Net Level-Off Altitude July 2006 Section 4 .000 ft MASS ADJUSTMENT kg -1950 -5650 -2500 Figure 4. ) 20 00 70 Section 4 .MRJT1 Page 41 .Aeroplane Performance Manual A/C AUTO (HIGH) 1 ENGINE INOPERATIVE 70 GROSS MASS AT ENGINE FAILURE 1000 kg 65 60 55 50 45 40 35 10 15 & below 70 EQUIVALENT GROSS MASS AT ENGINE FAILURE 1000 kg EQUIVALENT GROSS MASS AT ENGINE FAILURE 1000 kg 45 50 50 0 PRESSURE ALTITUDE 37.24 Driftdown Profiles – Net Flight Path July 2006 (corr.000 ft MAX CONTINUOUS THRUST LIMITS BLEED CONFIGURATION MASS ADJUSTMENT kg ENG ANTI-ICE ON ENG & WING ANTI-ICE ON A/C OFF BELOW 17000 ft +1950 +5650 -1750 65 60 55 50 45 40 35 20 35 ISA DEV °C 30 35 40 PRESSURE ALTITUDE 1000 ft 25 FU EL 20 BU RN FR O M EN 55 15 10 00 G IN E I FA LU RE kg 60 65 15 00 10 5 0 100 HEAD WIND kt 50 0 50 TAIL 100 0 50 100 150 200 250 GROUND DISTANCE FROM ENGINE FAILURE NM 300 REF LINE 5 10 20 25 35 15 30 40 TIME FROM ENGINE FAILURE min 45 50 55 Figure 4.CAP 698 CAA JAR-FCL Examinations . Aeroplane Performance Manual 1 ENGINE INOPERATIVE GROSS MASS AT ENGINE FAILURE 1000 kg PRESSURE ALTITUDE 33.000 ft 70 65 60 55 50 45 40 35 10 15 & below 70 EQUIVALENT GROSS MASS AT ENGINE FAILURE 1000 kg EQUIVALENT GROSS MASS AT ENGINE FAILURE 1000 kg 45 50 55 60 65 70 25 00 65 60 55 50 45 40 35 20 MAX CONTINUOUS THRUST LIMITS BLEED CONFIGURATION MASS ADJUSTMENT kg ENG ANTI-ICE ON ENG & WING ANTI-ICE ON A/C OFF BELOW 17000 ft +1950 +5650 -1750 ISA DEV °C 30 35 40 PRESSURE ALTITUDE 1000 ft 25 20 15 FU EL BU 50 0 RN FR EN 10 GI NE 10 00 OM kg 5 0 100 HEAD 50 WIND kt 0 50 100 0 50 100 150 200 250 GROUND DISTANCE FROM ENGINE FAILURE NM 300 REF LINE 5 10 20 25 35 15 30 40 TIME FROM ENGINE FAILURE min 45 50 55 TAIL Figure 4.MRJT1 Page 42 .) 20 00 LU RE 15 00 FA I Section 4 .25 Driftdown Profiles – Net Flight Path July 2006 (corr.CAP 698 CAA JAR-FCL Examinations .000 TO 35. CAP 698 CAA JAR-FCL Examinations .000 ft 70 65 60 55 50 45 70 65 60 55 50 45 EQUIVALENT GROSS MASS AT ENGINE FAILURE 1000 kg EQUIVALENT GROSS MASS AT ENGINE FAILURE 1000 kg 55 60 65 70 25 00 MAX CONTINUOUS THRUST LIMITS BLEED CONFIGURATION MASS ADJUSTMENT kg ENG ANTI-ICE ON ENG & WING ANTI-ICE ON A/C OFF BELOW 17000 ft +1950 +5650 -1750 30 40 40 10 15 20 & below ISA DEV °C 40 25 45 PRESSURE ALTITUDE 1000 ft 20 50 15 FU EL 50 0 BU RN 10 EN GI KG 5 0 HEAD 100 50 WIND kt 0 50 TAIL 100 0 50 100 150 200 GROUND DISTANCE FROM ENGINE FAILURE NM 250 300 REF LINE 5 10 20 25 35 15 30 TIME FROM ENGINE FAILURE min 40 45 50 55 Figure 4.000 TO 31.) 20 00 LU RE 15 00 NE 10 00 FR OM FA I Section 4 .26 Driftdown Profiles – Net Flight Path July 2006 (corr.MRJT1 Page 43 .Aeroplane Performance Manual 1 ENGINE INOPERATIVE GROSS MASS AT ENGINE FAILURE 1000 kg PRESSURE ALTITUDE 29. CAP 698 CAA JAR-FCL Examinations .MRJT1 Page 44 .) 25 00 UR 20 00 NE FA IL 70 Section 4 .000 ft 70 65 60 55 50 70 65 60 55 50 MAX CONTINUOUS THRUST LIMITS BLEED CONFIGURATION MASS ADJUSTMENT kg ENG ANTI-ICE ON +1950 ENG & WING ANTI-ICE ON +5650 A/C OFF -1750 BELOW 17000 ft 45 45 10 15 20 & below ISA DEV °C 25 45 PRESSURE ALTITUDE 1000 ft 20 55 15 50 0 FU 10 FR OM 10 00 EL BU RN EN GI E kg 5 0 HEAD 100 50 WIND kt 0 50 TAIL 100 0 50 100 150 200 GROUND DISTANCE FROM ENGINE FAILURE NM 250 300 REF LINE 5 10 20 25 35 15 30 TIME FROM ENGINE FAILURE min 40 45 50 55 Figure 4.Aeroplane Performance Manual 1 ENGINE INOPERATIVE GROSS MASS AT ENGINE FAILURE 1000 kg EQUIVALENT GROSS MASS AT ENGINE FAILURE 1000 kg EQUIVALENT GROSS MASS AT ENGINE FAILURE 1000 kg 50 60 65 15 00 PRESSURE ALTITUDE 25.27 Driftdown Profiles – Net Flight Path July 2006 (corr.000 TO 27. b) The landing 'climb limit' (Figure 4. check the wheel thermal plugs have not melted before commencing a take-off.30. and b) and the structural limit.28. a) The field length limited landing mass can be determined from Figure 4. Example 1 Given: Aerodrome Pressure Altitude Aerodrome OAT Wind Component Runway Condition Flap Setting Anti-skid System Spoilers Air Conditioning Icing 2000 ft +33 °C 20 kt Head Wet 30° Inoperative Automatic Auto None forecast 46. This mass ensures the minimum permissible gradient is obtained and should be corrected in accordance with the statements beneath the graph.400 kg 54. If the landing mass exceeds this value then.2 Quick Turnaround Limit The maximum permissible landing mass for a quick turnaround can be determined from Figure 4.28: Field length limited landing mass Figure 4. after 53 minutes. July 2006 Section 4 .900 kg 46.800 kg 60.29).29: Climb limited landing mass Structural limited landing mass Therefore Maximum Landing Mass 5.1 Landing Landing Performance The landing performance calculations are divided into two elements.MRJT1 Page 45 .CAP 698 CAA JAR-FCL Examinations . c) The maximum landing mass is the lower of a). The masses are tabulated for aerodrome pressure altitude and ambient temperature and should be adjusted in accordance with the statement below the tables for runway slope and wind component.Aeroplane Performance Manual 5 5.800 kg Solution: Figure 4. CAP 698 CAA JAR-FCL Examinations - Aeroplane Performance Manual ANTI-SKID OPERATIVE AUTOMATIC SPOILERS 65 ft UD E AIR PO RT PR ES SU RE ALT ITU 0 DE 100 0 ft 10 00 SU RE A LTI T 60 FIELD LENGTH LIMIT MASS 1000 kg WIND kt RUNWAY CONDITION FLAP POSITION 0 2 4 6 8 RE S 2 4 6 RT P AIR PO 8 55 50 45 AUTOMATIC OR MANUAL SPOILERS ANTI-SKID INOPERATIVE 40 15 30 REF LINE 40 WET REF LINE DRY 40 HEAD 20 REF LINE 0 20 TAIL 100 m 1000 ft 3 10 12 4 14 5 16 18 20 22 24 26 9 28 30 10 32 11 6 7 8 FIELD LENGTH AVAILABLE FOR MANUAL SPOILERS, ANTI-SKID OPERATIVE, DECREASE FIELD LENGTH AVAILABLE BY 650 ft. STRUCTURAL MASS LIMITS MUST BE OBSERVED. Figure 4.28 Landing Performance – Field Length Limit July 2006 Section 4 - MRJT1 Page 46 CAP 698 CAA JAR-FCL Examinations - Aeroplane Performance Manual -1 65 0 1 2 3 60 CLIMB LIMIT LANDING MASS 1000 kg 4 5 6 7 55 8 9 AIRPORT PRESSURE ALTITUDE 1000 ft 50 45 REF LINE -50 40 15 30 40 FLAP POSITION -40 -30 -20 -10 0 10 20 30 40 50 60 AIRPORT OAT ºC BASED ON A/C AUTO. FOR PACKS OFF INCREASE: THE FLAPS 40 ALLOWABLE MASS BY 1250 kg, THE FLAPS 30 ALLOWABLE MASS BY 1310 kg, OR THE FLAPS 15 ALLOWABLE MASS BY 1440 kg IF OPERATING IN ICING CONDITIONS DURING ANY PART OF THE FLIGHT WHEN THE FORECAST LANDING TEMPERATURE IS BELOW 8ºC: REDUCE THE FLAPS 40 CLIMB LIMIT MASS BY 4830 kg, REDUCE THE FLAPS 30 CLIMB LIMIT MASS BY 4730 kg, OR REDUCE THE FLAPS 15 CLIMB LIMIT MASS BY 4960 kg FOR ANTI-ICE OPERATION, DECREASE ALLOWABLE MASS BY THE AMOUNT SHOWN IN THE TABLE BELOW ANTI-ICE OPERATION DECREMENT kg FLAPS 15 30 40 ENGINE ONLY 650 600 550 ENGINE & WING 5800 5350 5250 ∗ NOTE: ANTI-ICE BLEED SHOULD NOT BE USED ABOVE 10ºC Figure 4.29 Landing Performance – Climb Limit July 2006 Section 4 - MRJT1 Page 47 CAP 698 CAA JAR-FCL Examinations - Aeroplane Performance Manual Figure 4.30 Quick Turnaround Limit Flaps 15° Aerodrome Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 Flaps 30º Aerodrome Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 Flaps 40° Aerodrome Pressure Altitude (ft) -1000 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 Maximum Quick Turnaround mass (1000 kg) Airport OAT °F °C -60 -51 59 58 56 55 54 54 53 51 50 49 49 -40 -40 57 56 55 54 53 52 51 50 49 49 48 -20 -29 56 55 54 53 52 51 50 49 48 47 46 0 -18 54 54 53 52 51 50 49 48 47 46 45 20 -7 53 52 51 50 49 49 48 47 46 45 44 40 4 52 51 50 49 49 48 47 46 45 44 44 60 16 51 50 49 49 48 47 46 45 44 44 43 80 27 50 49 49 48 47 46 45 44 44 43 42 100 38 49 49 48 47 46 45 44 44 43 42 41 120 49 49 48 47 46 45 130 54 48 47 46 Maximum Quick Turnaround mass (1000 kg) Airport OAT °F °C -60 -51 66 64 63 62 61 60 59 58 56 55 54 -40 -40 64 63 62 60 59 58 57 56 55 54 53 -20 -29 62 61 60 59 58 57 56 55 54 53 52 0 -18 61 60 59 58 57 55 54 54 53 51 50 20 -7 59 59 58 56 55 54 54 52 51 50 49 40 4 58 57 56 55 54 53 52 51 50 49 49 60 16 57 56 55 54 53 52 51 50 49 49 48 80 27 56 55 54 53 52 51 50 49 49 48 47 100 38 55 54 53 52 51 50 49 49 48 47 46 120 49 54 53 52 51 50 130 54 54 53 52 Maximum Quick Turnaround mass (1000 kg) Airport OAT °F °C -60 -51 68 67 66 64 64 62 61 60 59 58 56 -40 -40 67 65 64 63 62 60 59 58 57 56 55 -20 -29 65 64 63 61 60 59 58 57 56 54 54 0 -18 64 62 61 60 59 58 57 55 54 54 53 20 -7 62 61 60 59 58 56 55 54 53 52 51 40 4 60 59 59 57 56 55 54 53 52 51 50 60 16 59 58 57 56 55 54 53 52 51 50 49 80 27 58 57 56 55 54 53 52 51 50 49 49 100 38 57 56 55 54 53 52 51 50 49 49 48 120 49 56 55 54 53 52 51 130 54 55 54 54 Add 350 kg per 1% uphill slope Subtract 1150 kg per 1% downhill slope Add 1100 kg per 10 kt headwind Subtract 7450 kg per 10 kt tailwind July 2006 Section 4 - MRJT1 Page 48 c) From this intersection continue vertically downward to the Braking Configuration reference line.2 Landing a) Enter the left vertical axis at the estimated landing mass and travel horizontally right to a speed of (VREF . The chart enables due allowance to be made for a single stop and. b) From this intersection.3. July 2006 Section 4 .3. From this intersection travel horizontally left to the vertical axis to read the stopping distance in thousands of feet. add one million foot pounds for each taxi mile to obtain the total energy.1 Abandoned Take-Off a) Enter the top left vertical axis at the Regulated Take-Off Mass and travel horizontally right to V1 minus 50% of headwind or plus 150% of tailwind. 5.31.1.1. 5.MRJT1 Page 49 . f) To this value. by using the graph as indicated. drop vertically to the first reference line then follow the gridlines to correct for Pressure Altitude and OAT. c) From this intersection continue vertically downward to read the Brake Energy per Brake in millions of foot pounds.1 Method of Use of the “Brake Cooling Schedule” Graph (Figure 4. Separate sub-graphs are provided for determining the stop distance with manual braking. g) From the value of the total energy on continue vertically downward to determine the advised cooling schedule and recommend cooling time.3) kt corrected for wind component minus 50% of a headwind or plus 150% for a tailwind. select the appropriate sub-graph in Figure 4.3.3 Braking Distance For a manual braked landing with no reverse thrust or for a manual braked landing with normal thrust #2 detent.1. provides advice on the procedure to be adopted and the minimum cooling time.3. drop vertically to the first reference line then follow the gridlines to correct for Pressure Altitude and OAT.Aeroplane Performance Manual 5. then enter the sub-graph at the Brakes ON IRS Ground Speed KIAS and travel vertically up to intersect the equivalent autobrake setting. d) To this value add one million foot pounds for each taxi mile to obtain the total energy. e) From the value of the total energy continue vertically downward to determine the advised cooling schedule and recommended cooling time.31) 5. e) From the intersection continue vertically downward to read the Brake Energy per Brake in millions of foot pounds.31 provides advisory information to enable the operator to avoid brake overheat problems.CAP 698 CAA JAR-FCL Examinations . b) From this intersection. d) Follow the grid-lines to the appropriate braking configuration.3 Brake Cooling Schedule The graph at Figure 4. 5. Clear runway immediately. IV FUSE PLUG MELT No reverse thrust or braking configuration credit allowed in this area. Figure 4.31 Brake Cooling Schedule July 2006 Section 4 .CAP 698 CAA JAR-FCL Examinations .Aeroplane Performance Manual lb 140 kg 65 60 11 0 12 0 70 80 90 RTO MASS X 1000 50 100 45 40 80 120 55 50 10 0 LANDING MASS X 1000 10 120 13 0 60 55 14 0 0 16 kt ED FF E O SP KEON TA ES ED AK CT BR EJE R 15 0 0 12 0 11 0 13 0 60 70 80 14 100 45 40 90 0 15 0 16 0 17 0 18 0 80 PRESS ALT 1000 ft 0 5 10 -20 OAT °C 0 REF LINE 20 40 REF LINE PE NS G S O DIN E AK LAN BR ED 0 19 kt REF LINE MAX MANUAL BRAKING NO REVERSE BRAKING CONFIGURATION MAX AUTOBRAKE LANDING #3 NO REVERSE MAX #1 & #2 #3 #1 & #2 NORMAL REVERSE #2 DETENT 4 8 20 12 16 BRAKE ENERGY PER BRAKE 30 3 30 40 4 40 50 5 50 60 6 60 24 28 FOOT POUNDS x MILLION 70 80 MINS 90 32 36 PARKED AIRBORNE GEAR DOWN AIRBORNE GEAR UP 8 STOP DISTANCE 1000 ft 6 4 2 0 80 0 10 20 0 1 2 0 10 20 COOLING TIME STOP DISTANCE 1000 ft EQUIVALENT AUTO BRAKE SETTING 8 1 2 6 4 EQUIVALENT AUTO BRAKE SETTING MANUAL BRAKE LANDING NO REVERSE 3 MAX MANUAL BRAKE LANDING NORMAL REVERSE #2 DETENT 1 2 3 MAX 2 0 80 100 120 140 160 BRAKES ON IRS GROUNDSPEED kt 100 120 140 160 BRAKES ON IRS GROUNDSPEED kt I NORMAL No special procedure required. Do not set parking brake. II COOLING RECOMMENDED Cool as scheduled. extend gear for at least 7 minutes. Ground cooling schedule recommended prior to take-off. After take-off.MRJT1 Page 50 . III CAUTION Wheel fuse plugs may melt. Alert fire equipment. Delay take-off and inspect after 30 minutes. Do not approach gear or attempt taxi or subsequent take-off before waiting mandatory time shown on quick turnaround limit chart.