Factors Affecting Approch and landing

APPENDIX H

INTERMEDIATE FLIGHT PREPARATION WORKBOOK

climb gradient with 2 engines operative will be greater than 2.5%. Time and fuel allowances for

a normal go-around are 5 minutes and 250 pounds.

H107. FACTORS AFFECTING APPROACH AND LANDING

Crosswind

The maximum demonstrated crosswind for this aircraft is 25 knots.

Maximum Landing Weight - 2.5% Climb Gradient

The maximum landing weight is determined by the weight at which the aircraft can obtain a

2.5% climb gradient with 1 engine inoperative and the other engine at takeoff thrust at VAC with

the landing gear retracted.

Landing Speeds

Approach, threshold, and touchdown speeds are a function of weight. VREF is computed by

subtracting 2 knots for every 500 lbs of fuel consumed from 118 KTS.

Landing Distance

The total landing distance from the 50-foot obstacle to full stop is obtained by applying

maximum braking as soon after touchdown as practical. Landing distances are based on the

following procedures and assumptions:

A 3 approach at VREF to the 50-foot obstacle height.

Idle thrust at 50 feet.

3. A 1.4-second allowance for the distance traveled during the transition from touchdown to

the taxi attitude (3-point runway contact).

Maximum braking is obtained upon attaining taxi attitude and is continued to a full stop.

The friction coefficient for a dry asphalt or concrete runway corresponds to a RCR of 23.

Speed Brakes

Ground roll distances are not predicated upon the deployment of the speed brakes. However, the

deployment of the speed brakes after wheel brake application will result in shorter ground roll

distances.

H-10 T-1A PERFORMANCE MANUAL EXTRACTS