B 737 Performance Takeoff Landing Last Rev 02062004

B 737 Performance Takeoff & Landing Last Rev: 02/06/2004

Takeoff Performance • • Takeoff Performance Basics Definitions: Runway Takeoff Distances Definitions: Takeoff Speeds JAR 25 Requirements Engine failure Optimisation – improved climb Reduced takeoff

Takeoff Performance Basics What is the Gross Takeoff Flight Path ? • It is the vertical flight path that a new aircraft flown by test pilots under ideal conditions would achieve. It is adjusted for the Minimum Engine. It starts where the aircraft passes 35 ft and ends at a minimum of 1500 ft What is the Net Takeoff Flight Path ? • This is the vertical flight path that could be expected in operation with used aircraft. It also starts at 35 ft and ends at a minimum of 1500 ft

Takeoff Performance Basics • The Net Gradient would be calculated as follows: Gross Gradient p% x D Net Gradient Distance = D

Takeoff Distances • RUNWAY This is the ACN capable hard surface • CLEARWAY - This is an area, under the control of the airport, 152 m (500 ft) minimum width, with upward slope not exceeding 1. 25%. Any obstacles penetrating the 1. 25% plane will limit the Clearway • STOPWAY - A surface capable of supporting the aircraft in an RTO. Its width must be greater than or equal to that of the runway. It may not be used for landings

Takeoff Distances CLEARWAY RUNWAY STOPWAY TORA ASDA TODA MAX 1. 25%

Takeoff Distances • TORA- Take. Off Run Available. This is the physical runway limited by obstacle free requirements • ASDA - Accelerate-Stop Distance Available. This is the distance available for accelerating to V 1 and then stopping. It may include the physical runway and any stopway available • TODA - Take. Off Distance Available. This is the distance available to achieve V 2 at the appropriate screen height. It may include physical runway, stopway and clearway • Note: Not more than ½ the Air Distance may be in the Clearway (Air Distance is distance from lift-off to 35 ft) • The Takeoff Run is defined as the distance from brake release to ½ the Air Distance • Wet Runway calculations do not allow use of Clearway

Takeoff Performance Basics The Takeoff Phase is from brake release to 1500 ft or the point where the last obstacle has been cleared, if higher Three basic limitations must be taken into account: • Field Length • Climb Gradients • Obstacle Clearance Other limitations are also restrictive and are covered during discussion on these basic limitations. They are: • Structural • Tire Speed • Brake Energy

Takeoff Speeds V 1

Takeoff Speeds V 1 “official definition” “…pilot's initiation of the first action (e. g. applying brakes, reducing thrust, deploying speed brakes) to stop the aeroplane during accelerate-stop tests…” JAR 25. 107(a)

Takeoff Speeds V 1, the Takeoff « action » speed, is the speed used as a reference in the event of engine or other failure, in taking first action to abandon the take-off. The V 1 call must be done so that it is completed by V 1. V 2 VEF V 1 35’

Takeoff Speeds VR • VR is the speed at which rotation is initiated, so that in the case of an engine failure, V 2 will be reached at a height of 35 feet using a rotation rate of 2º-3º / second • Regulations prohibit a RTO after rotation has been initiated, thus VR must be greater than V 1. VR V 1

Takeoff Speeds V 2 • V 2 is the takeoff safety speed. This speed will be reached at 35 feet with one engine inoperative.

Takeoff Speeds HEIGHT AT END OF TODA • Effects on the screen height of continuing a takeoff with an engine failure prior to VEF 35 Ft 2 Engine 10 Ft 1 sec -16 -8 0 SPEED OF ENGINE FAILURE RELATIVE TO VEF +4 +8

Takeoff Speeds • V 1(MCG) - The Minimum Ground Control Speed • This is the speed at which, in the case of a failure of the Critical Engine, it is possible to control the aeroplane by aerodynamic means only without deviating from the runway centreline by more than 30 ft, while maintaining takeoff thrust on the other engine(s). Maximum rudder force is restricted to 68 Kg (150 lbs) • In demonstrating V 1(MCG), the most critical conditions of weight, configuration and CG will be taken into consideration • Crosswind is not considered in V 1(MCG) determination • Obviously VEF must be greater than V 1(MCG) , or the aircraft would be uncontrollable on the ground with an engine inoperative: VEF V 1(MCG)

Takeoff Speeds • VMC - The Minimum Control Speed • This is the speed, when airborne, from which it is possible to control the aeroplane by aerodynamic means only with the Critical Engine Inoperative while maintaining takeoff thrust on the other engine(s) • The demonstration is made with not more than 5º Bank into the live engine, Gear retracted (as this reduces the directional stability) and the most Aft CG (as this reduces the Rudder Moment. ) • (VMC may increase as much as 6 Kts. / º Bank from demonstration with wings level and Ball centred)

Field Length Criteria • The Takeoff distance required for a given weight and given V 1 is the greater of three different distances: Actual All-Engine Takeoff Distance x 1. 15 Actual All-Engine Takeoff Distance (As Demonstrated in Tests) V 1 One Engine Inoperative Takeoff Distance VEF V 1 One Engine Inoperative Accelerate-Stop Distance V > V 2 35 ft 15% Safety Margin V 2 35 ft

Field Length Criteria • The greater of the 3 distances is the JAR Field Length required • If V 1 is chosen such as the 1 -Engine-Inoperative Accelerate-Go and Accelerate-Stop distances are equal, the necessary field length is called Balanced and the corresponding V 1 is known as a Balanced V 1

Field Length Criteria MTOW Fixed Runway Length ACCELERATE GO RANGE OF POSSIBLE WEIGHTS ACCELERATE STOP BALANCED V 1

JAR 25 Takeoff Flight Path Flap retraction 400 Ft Min Gear Retracted Lift-Off V 2 Clean Acceleration TO Thrust 35 ft TWIN 1500 Ft or Clear of Obstacles Clean MCT Max 5 min 1 st Segment 2 nd Segment 3 rd Segment >0 2. 4% acceleration or 1. 2% avail. 4 th Segment 1. 2%

Obstacle Clearance • For Obstacle Clearance a Net Takeoff Flight Path is considered • It is not demonstrated, but rather calculated from the Gross Flight Path by reducing the gradients by a safety margin: Twin 0. 8% • It also will take wind into account, using 50% of the Headwind Component and 150% of the Tailwind Component, thus giving a further safety margin. • The Net Takeoff Flight Path must clear all obstacles by 35 Ft

Obtacle Vs Climb 1 st Segment 2 nd Segment 3 rd Segment 4 th Segment Gross Flight Path V 2 Net Flight Path 35 ft

Obstacle Clearance • The minimum height for flap retraction is 400 ft AAL (gross) • TNT A B 737 : we use 800 ft AAL minimum • If there is a high obstacle in the 3 rd or 4 th segment, we could extend the second segment to ensure that the obstacle was cleared by 35 ft. Provided it still remains in the 3 rd or 4 th Segment • We now have a Minimum Gross and Minimum Net Acceleration Height which is then corrected for elevation and temperature to give a Minimum Gross Acceleration Altitude

Obstacle Clearance Extended Second Segment Minimum Gross Acceleration Height Minimum Net Acceleration Height 35 Ft 400 Ft

Acceleration Altitude • The extension of the second segment and raising of the EFFRA (JAR : EOAA) is limited as takeoff thrust must be maintained until acceleration altitude is attained • The Takeoff Thrust is limited to 5 minutes and this restricts the extension of second segment

Engine Failure Procedure • • • The Standard Engine Out Procedure (EOP) is therefore: Maintain Runway Track Climb to the EFFRA at V 2 Accelerate and Retract Flaps Set MCT (max 5 min after TO power setting) Climb to the 1500 ft AGL at Flap up man. speed And then? ? ?

Distance to clear 1500 ft (B 737) 3 rd segment: Accel 150 kts 220 kts 0. 23 m/s² 8 NM 4 th segment: 1. 2% 1500 ft @ 220 kts 70 ft/NM 7 NM 2 nd segment: 2. 4% 1000 ft @ 150 kts 150 ft/NM 7 NM 1 st segment: >0% 140 – 150 kts 0'30" 3'00" 2'30" 2'00"

Obstacle Clearance • Only obstacles within a certain lateral distance of the flight path are taken into account in performance calculations • For each runway, Obstacle Cone is constructed for Straight Ahead or Turning Engine Out Procedures (EOP) • Wind is not considered therefore correct tracking is important • There is not a large margin for error for a jet airplane

Obstacle Clearance Flight Path 3000 ft width = 0. 125 x D 300 ft 21600 ft 3000 ft

Obstacle Clearance Flight Path

Obstacle Clearance • Bank Angle has a large effect on the climb performance and therefore Obstacle Clearance GRADIENT 2. 4% 0. 6% 1. 8% 0 15 30 BANK ANGLE

Optimisation - Improved climb • Depending on the design of the aircraft and on the flap setting, the maximum climb angle speed is usually 15 to 30 kts higher than 1. 13 VSR • However, the selection of a V 2 higher than the minimum will increase TOD • The V 2/VS optimisation is called « Improved Climb Method » • This method consists thus in increasing the climd limited TOW at the expense of the field limited TOW. It is only applicable if runway length permits • In order to obtain consistent field length, V 1 and VR have to increase if V 2 increases: if the runway allows an increase of V 2, thus an increase in TOD, it will also allow an increase of the ASD, thus also of V 1

Optimisation - Improved climb Drag Curve Given TOW TO Flaps Gear UP Depending on Flap Setting, the Max Angle Speed is typically 1. 13 VS + 15 to 30 Kts Vs 1. 13 Vs 1. 28 Vs EAS

Optimisation - Improved climb • In order to achieve the higher V 2, the VR speed must be increased • The V 1 speed must also be increased to ensure that there is sufficient runway to accelerate, lose and engine and be able to continue the takeoff at higher weight • As V 1 is higher, the VMBE speed must be checked for brake energy limits as this may become limiting

Reduced Thrust Takeoff • When the actual TOW is below the maximum allowable TOW for the actual OAT, it is desirable to reduce the engine thrust • This thrust reduction is a function of the difference between actual and maximum TOW • JAA requires that the reduced thrust may not be less than 75% of the full takeoff thrust. Specific figures may apply for different airplanes/engines

Reduced Thrust Takeoff Assumed temperature MAX TOW Allowed TOW Flat rated thrust If the actual TOW is less than the maximum weight for the actual temperature, we can determine an assumed temperature, at which the actual weight would be equal to the maximum allowed TOW EGT limited thrust Act TOW OAT Assumed temperature Temp Having determined this assumed temperature, we can compute the take-off thrust for that temperature

Reduced Thrust Takeoff Limitations • Since thrust may not be reduced below 75% of the full thrust, a max assumed temp can be determined • The assumed temperature may not be less than the OAT • No reduced thrust on standing water, and on contaminated or slippery runways • No reduced thrust with antiskid inop or PMC OFF • No reduced thrust for windshear, low visibility takeoff

Reduced Thrust Takeoff It’s safe OAT = 30°C weight is MTOW V 1 Margin at V 1 OAT = 10°C ASS. TEMP = 30°C weight is MTOW V 1

RTO execution operational margin

Landing and Go-Around • • Landing Distance Approach Climb Landing Climb Procedure Design Missed Approach Gradient

Landing Distance • JAR 25 defines the landing distance as the horizontal distance required to bring the airplane to a standstill from a point 50 ft above the Runway Threshold. • They are determined for Standard Temperatures as a function of: Ø Weight Ø Altitude Ø Wind (50% Headwind and 150% Tailwind) Ø Configuration (Flaps, Manual/Auto-Speedbrakes, Brakes) • They are determined from a Height of 50 ft at VREF on a Dry (or Wet), Smooth Runway using Max Brakes, full Antiskid and Speedbrakes but No Reversers

Landing Distance • Boeing describes the braking technique as “Aggressive”. The Brakes are fully depressed at touchdown • Runway Slope is NOT accounted for • Non standard temperatures are NOT accounted for • Approach speed Additives are NOT accounted for • These are considered to be covered by the extra margins used to define certified landing distances

Landing Distance V = 1. 23 VS 1 G Landing Distance 60% Runway Length 50 ft Actual Landing Distance Dry Factor = 1. 67 Required Landing Distance Wet Landing Distance = 1. 15 x Required Landing Distance Wet Factor = 1. 15

Approach Climb What is Approach Climb ? 2. 1%

Approach Climb • Aircrafts are certified to conduct a missed approach and satisfy a Gradient of 2. 1% - GROSS • The configuration is: One Engine Inoperative Gear Up Go Around Flaps (15 on 737) G/A Thrust • Speed must be 1. 4 VSR (Strictly speaking, the Flap Setting must be an intermediate flap setting corresponding to normal procedures whose stalling speed is not more than 110% of the final flap stalling speed)

Landing Climb What is Landing Climb ? 3. 2%

Landing Climb • Aircrafts are certified to conduct a missed approach and satisfy a Gradient of 3. 2% - GROSS • The configuration is: All Engines Operating Gear Down Landing Flaps (30 or 40 on 737) G/A Thrust • The speed must be 1. 13 VSR and VMCL • It is also a requirement that full G/A thrust must be available within 8 seconds of the thrust levers forward from idle

JAA Low Visibility Climb • An Aircraft must be certified to conduct a missed approach and satisfy a Gradient of 2. 5% - GROSS or the published Missed Approach Gradient • The configuration is: One Engine Inoperative Gear Up Go Around Flap (15 on a 737) G/A Thrust • This is only applicable if Low Visibility Procedures will be conducted with a DH of below 200 Ft or No DH

Max Landing Weight The maximum landing weight for dispatch is the least of the: • • • Field Limited Landing Weight Approach Climb Limited Landing Weight Landing Climb Limited Landing Weight JAA LVP G/A Climb Gradient Limited Landing Weight Structural Limited Landing Weight

Procedure Missed Approach Gradient 3. 9% GROSS MAP + 0. 6% + 0. 8% 98 Ft 2. 5% NET

Procedure Missed Approach Gradient Some specific procedures require a Net gradient of more than 2. 5%. This will be indicated on the Chart

Procedure Missed Approach Gradient • A conflict exists between JAR 25 and ICAO • JAR 25 requires a Approach Climb Gradient of 2. 1% Gross and a Landing Climb gradient of 3. 2% Gross • ICAO requires a missed approach procedure gradient of at least 2. 5% Net which may require at least 3. 9% Gross • And Tailwind has not been accounted for

Procedure Missed Approach Gradient …but what if you lose on the go-around from a normal approach ? . . . • The case of an engine failure during Go-Around is not considered as this is deemed a remote possibility!!!

Landing Performance Data Which is the more restrictive? D Fn Both Engines 5 x Thrust Available on 1 Engine 75% EAS • With Twins, the Approach Climb will be the most limiting

Procedure Missed Approach Gradient • Remember the Go-Around procedure is designed for 1 engine inop • With all engines operating, this should not be a problem • With 1 engine inop, generally this should not be a problem • If the Go Around procedure is very different to EOP procedure, then it may be prudent to use this procedure • Some airfields may specify this if terrain clearance is critical

Factors affecting landing distance (Typical)

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