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(0.917 times the published glidepath angle). For example, 0.917× 3.0° = 2.75°.
Calculate the θΔISAlow using formula 3-4.
Formula 3-4
( [ ])
( )
o
low
1
l w
= Published Glidepath Angle
where a = PFAF altitude - LTP Elevation
e = 0032 49
r =
019 00038
. .
tan
.
n
.
ISA ta
ISA a
a
a e
a
r
θ
Δ
θ
θ −
Δ
× + × +
= +
+ ×
Example
[ ]
( [ ])
( )
1
low
where a = 2,000 - 400
e = 29 2 0032 1 600 49
1 600
r =
3
1600 12698
276
3052982
019 00
038
160
0
. . , .
,
tan
.
tan .
.
. . ,
θ ISA −
Δ
− × + × +
+ −
= =
+ ×
If the effective glidepath angle is less than 0.917θ, calculate the ΔISAlow to
achieve an angle of 0.917θ using formula 3-5.
Formula 3-5
( )
( )
( )
( )
where el = PFAF altitude - b
b = 0917 elevation
r =
a = PFAF altitude - LTP eleva
0032 49
019 0
tio
0 8
n
03
. .
tan .
tan
low . .
r LT
el
P
a
ISA
a
a
θ
θ
×
− − × −
+
Δ =
+ ×
Example
( )
( )
( )
( )
13356 0032 1 600 49
3025
019 00038 1 600
where el = 2000 - b
b = 30,529.82 275 400
r = 1600
3
a = 2,000 - 400
. . , .
.
. . ,
tan .
,
tan
ISAlow
− − × −
Δ = =−
+ ×
× +
Determine the published low temperature limitation for the procedure derived
from formula 3-6, using the ΔISALOW derived from formula 3-3 or 3-5 as
appropriate. If the temperature history for the location indicates the low
temperature limitation is frequently encountered during established busy
6/3/05 8260.52
Par 3.2.1 Page 3-5
recovery times, consider raising the glidepath angle to the lowest angle (within
table 3-1 limits) that will make the approach usable more often.
Formula 3-6
NAbelow = ISA + ΔISALOW
Example
[ ]
[ ]
10 4 25 4 15 C
or
1.8 -15 32 5°F
NAbelow = .+ − . = − °
× + =
Higher than ISA temperatures produce higher effective angles than the designed
glidepath angle. Determine the maximum ΔISAHIGH (above ISA) that will produce
the maximum allowed glidepath angle (α) using formula 3-7 where the maximum
glidepath angle is 1.13 times the table 3-1 maximum value for the fastest
published approach category.
Formula 3-7
( )
( )
( )
( )
where =
=
=
= PFAF altitude - LTP elevation
= Maximum Al
0032 49
019 00038
-
tan
tan
. .
HIGH . .
eh c PFAF altitude
c r LTPelevation
a
r
a
eh a
ISA
a
α
θ
α
× +
− × −
Δ =
+ ×
lowed Glidepath Angle
θ = Published Glidepath Angle
Example
( )
( )
( )
( )
where = 2208.46 2000
= 30529.82 339 400
1600
=
3
= 2000 - 400
208 46 0032 1600 49
243°C
019 00038 1600
-
tan .
tan
. . .
.
HIGH . .
eh
c
r
a
ISA
× +
− × −
Δ = =
+ ×
Determine the published high temperature limitation for the procedure derived
from formula 3-8.
Formula 3-8
NAabove = ISA + ΔISAHIGH
Example
10 4 33 68 4408 C
or
18 4408 32 11134°F
. . .
. . .
NAabove = + = °
× + =
8260.52 6/3/05
Page 3-6 Par 3.3
3.3 TURNS IN THE FAS.
Fly-by turns are not allowed in the FAS. Where turns are necessary, use an RF
leg. Design procedures that incorporate an RF turn in the final segment to
establish the aircraft on a straight segment aligned with the runway centerline
prior to reaching DA. The Final Rollout Point (FROP) is the initial fix of the
straight segment (see figure 3-1). Locate the FROP at the greatest distance
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