Note: If a fire is indicated, the ENGINE FAILURE/FIRE CHECKLIST should be called for by the PF and initiated by the PM after flap retraction.
* If an engine failure occurs prior to V2, maintain V2 up to the altitude required for obstacle clearance. If an engine failure occurs after V2 but less than V2+10 knots, maintain the speed reached at the time of the engine failure. If an engine failure occurs at a speed higher than V2+10 knots with the flaps at takeoff setting, increase pitch attitude to reduce speed to and maintain V2+10 knots until clear of obstacles. Flight directors driven by -930 and above computers will supply pitch commands to maintain the above engine failure speeds.
Note: Flight directors driven by -904 or -906 computers will supply pitch commands to maintain V2+10 knots regardless of speed at the time of engine failure. If an engine fails during takeoff, disregard the pitch commands and maintain the appropriate engine failure speed (described above) by reference to the airspeed indicator. Following erroneous pitch commands may result in a flight path below the minimum required to provide obstacle clearance.
(Continued)
** Normally, flap retraction after an engine failure occurs at 800 feet AGL.
Obstacle clearance requirements may define non-standard flap retraction
altitudes. If non-standard altitudes are required, they will be noted on
the JEPP 10-7 page.
Note: When making a reduced thrust takeoff, all performance requirements are met with reduced thrust. If desired, the operating engine may be left at reduced thrust for climbout.
Rotation And Initial Climb (Single Engine)
If engine failure occurs after V1 during takeoff roll, the PF should apply rudder as required to keep the aircraft tracking straight ahead on the runway. The amount of rudder required to track straight ahead will be very close to the amount of rudder needed to maintain wings level after rotation and during initial climbout. After VR speed is attained rotate the aircraft, using normal rate of rotation, to approximately 13. of pitch. Gear retraction will not be initiated until a positive rate of climb has been verified on the IVSI and altimeter and called by either pilot. Avoid pumping the elevator -establish an attitude and check the speed trend. Avoid following flight director pitch commands below 200 feet AGL as this may lead to oscillation in pitch attitude.
Rudder should be used to hold wings level and maintain a constant heading. Avoid rapid or large movements of the rudder. The delay between a rudder input and change in aircraft motion can lead to oscillation in roll. The control wheel should be centered except when making small inputs to correct bank angle or heading. Rudder trim should be used as required but do not allow trimming the aircraft to distract from maintaining proper aircraft control, especially during the first 200 feet of climb.
Engine No. 2 Inoperative
After cleanup and acceleration, the climbout is made at single engine climb speed until pattern altitude or enroute climb clear of all obstructions. Single engine climb speed is below maneuvering speed and bank angle should be limited to 15.. Once level at pattern or enroute altitude (and clear of all obstructions), a maneuvering speed should be attained to restore normal maneuvering ability.
* * * *
MD-80 Sec. 2 Page 11
Flight Manual Continental Rev. 08/01/98 #27
1st 2nd SLAT RETRACT EXTERNAL EXTERNAL SPEED +20K BUG BUG
RECEIVE PROPER FLIGHT DIRECTOR CUES. BANK ANGLE SHOULD BE LIMITED TO 15° BUT UP TO 25° MAY BE USED FOR SPECIAL ENGINE
OUT DEPARTURE PROCEDURE.
If “TAKEOFF FLEX” is used then assumed temperature will show in the bottom
of the throttle window of the FMA before and after autothrottles are selected “EPR”
will show in the top of the throttle window of the FMA after autothrottles are selected.
MD802001
Engine Failure After Takeoff V1 Profile
Engine Failure After Takeoff V1 Profile
INTENTIONALLY LEFT BLANK
REVERSER DEPLOYED OR REVERSE
THRUST / UNLOCK LIGHT ON INFLIGHT
IMMEDIATE ACTION
Autothrottles .......................................................... DISENGAGED Throttle (Affected Engine) .................................................... IDLE
SECONDARY ACTION
Reverse Thrust Lever...................... DOWN (FORWARD THRUST)
Note: Reverser may not stow above 200 KIAS. Throttle should be left in idle position until reverser is stowed. 中國航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：MD-80 Flight Manual 麥道80飛行手冊 1(23)
