Getting to Grips with Aircraft Performance
V2 vs V3 差异报告

This document is about Airbus aircraft, that is aircraft with a maximum takeoff weight that exceeds 57 000 kg.

This document is about Airbus aircraft, that is aircraft with a maximum takeoff weight that exceeds 5 700 kg.

For Airbus aircraft, this configuration is CONF FULL.

In case of a system failure that affects landing performance, Airbus operational documentation (FCOM) indicates the correction to be applied to VREF to take into account the failure:

For other Airbus aircraft, VGA is the climb speed for go-around, regardless of the number of engines that are operative.

For Airbus aircraft (except A220), this configuration is CONF FULL.

In case of a system failure that affects landing performance, Airbus provides the correction, to be applied to Vref to take into account the failure, as an output of the EFB computation.

For A220, VREF is the minimum speed at a height of 50 ft above the runway threshold for the flap selected. In other words, VREF = VLS for the flaps selected.

压力高度标注使用大写 ZP，与正文小写 Zp 不一致。

统一为 Zp：3.3.1 节两个插图框及 D-17 图（含标题 “Zp Curve vs. Weight at Fixed Mach Number”）均改为小写 Zp。

a curve that displays load factor vs. Mach number will have the same form as the one displayed in Illustration F17.

a curve that displays load factor vs. Mach number will have the same form as the one displayed in Illustration D-22.

E-11: A319 Performance Profile - Oxygen System that lasts for 22 Minutes

E-13: A319 Descent Profiles - Engine + Cabin Pressurization Failures

E-16: A319 Obstacle clearance profile

E-11: A319 Performance Profile - Oxygen System that Lasts for 22 Minutes - Air OPS CAT.IDE.A.230 allowance

E-13: A319 Descent Profiles - Engine + Cabin Pressurization Failures - Air OPS CAT.IDE.A.230 allowance included

E-16: A319 Obstacle Clearance Profile - Air OPS CAT.IDE.A.230 allowance included

the Missed Approach procedure design criteria are outlined as follows

constraint must be checked one engine inoperative

procedures that consider normal operations (all engine operative)

develop their own contingency procedure for a Missed Approach

submit the procedure to the competent authority

the design criteria for the Missed Approach procedure are defined as follows

constraint must be checked with One Engine Inoperative

procedures that consider normal operations (all engines operative)

develop their own procedure for the possibility of a Missed Approach with One Engine Inoperative

submit the procedure to the appropriate authority

In the example above, the performance computation for Landing Dispatch is based on WET SNOW. The drag effect of the contaminant is not considered, or is considered only for the minimum depth.

In the example above, the performance computation for Landing Dispatch is based on WET SNOW. For RLD computation, the drag effect depends on the contaminant type. This drag effect is either not considered, or is considered only for the minimum depth of that contaminant.

Drift Down / drift down；FL250、FL300；5,000 feet；Illustration F-5 :；vs / versus 混用

Drift-Down / drift-down；FL 250、FL 300；5 000 feet；Illustration F-5:；vs. 统一