Appendix 1 TABLE 2
LOW ALTITUDE SPEED COMMAND TOLERANCES (STILL AIR)
MODE CONDITION TRANSITION IAS (KTS) STEADY STATE IAS (KTS) +5 TAKEOFF CRITICAL ENGINE Before 35 feet, as close Vz -0 FAILURE VEF < V2 as practical to the speed profile demonstrated durirs performance tests.
CRITICAL ENGINE FAILURE +5 Vz < VEF < (V2 +X) VEr -5 (Note 1.) VEr -2 (Note 2.)
CRITICAL ENGINE FAILURE VEF > (V2 + X) (V½ + X) -5 (Note 3.) (V½ + X) + All Engines N/A Operating TAKEOFF, Critical Engine (V½ + X) -5 (Note 3.) (V½ + x) = NOISE Failure During THRUST Thrust Cutback
CUTBACK All Engines Operating (Vz + X) -2 LANDING Critical Engine (REF +XX) -55 (Note 5.) VREF +XX) *2 APPROACH Failure During GO-AROUND Transition (Initiated at VREF + All Engines (VeEr +XX) - 5 (Note 6.) Veer +Xx) -2 XX during Operating stabilized approach) +5 LANDING All Engs Operating N/A APPROACH & Critical Engine Failure NOTES:
Less than VEr -2 not to exceed 10 sec.; Less than V½ not to exceed 5 sec; Not less than V½ -2 Ness than (V, +3x) -2 not to exceed 10 sec.
Except in pitch limited conditions
3. Less than (REr +X) -2 not to exceed 10 sec.; Less than 1.2Vs1 not to exceed 5 sec.; Not less than 1.2 si -2 *: kes At engine sad not to exce 10 see Not less than 1.2%
9. XX = Landing approach wind speed/gust additive 2