UH--60 Performance Planning
UH
Version date
January 2006
1
Terminal Learning objective (TLO):
At the completion of this lesson the student will:
Action: Completion of the performance planning
card (PPC) DA Form 5701-60-R.
Condition: As a UH-60 aviator.
Standard: In accordance with TC 1-237, TM 11520-237-10, TM 1-1520-237-CL.
Safety Requirements: None
Environmental Considerations: None
2
Enabling Learning Objective (ELO) #1:
Action: Define the purpose of the Performance
Planning Card (PPC) DA 5701-60-R.
Condition: Given a blank Performance Planning
Card (PPC) DA 5701-60-R, TC 1-237, TM 1-1520237-10, and TM 1-1520-237-CL.
Standard: In accordance with Performance
Planning Card (PPC) DA 5701-60-R, TC 1-237,
TM 1-1520-237-10, and TM 1-1520-237-CL, and
classroom instruction.
3
Complete a PPC using the following data:
Departure Data
A/C weight: 14,000 lbs
ETF: 1.0 and .90
Departure Temp. 19 degrees C
Departure P.A. 150 Ft
Max. Temp. 25 degrees C
Max. P.A. 240 Ft
Fuel weight 2000 lbs
Cruise Data
Cruise Altitude 1,000 Ft
Temp. 20 degrees C
4
Prepare a Performance Planning Card
- Task 1010
When will a PPC be completed?
All Flights
Note. Performance planning items shaded in grey box are
not required to be completed each time a performance
planning card (PPC) is computed. These values should
be completed when, based on the proposed mission, the
information may be required for the flight. Additionally,
these items will be annotated in the procedures as
OPTIONAL after the item name.
5
Prepare a Performance Planning Card
- Task 1010
STANDARDS: Appropriate common standards plus the following
additions/modifications:
1.
Calculate PPC values using accurate conditions for the time of
takeoff within the following parameters:
a. Free air temperature (FAT) + 5 degrees Celsius.
b. Pressure altitude (PA) + 1,000 feet.
c. Gross weight + 500 pounds.
d. Engine torque factor (ETF) 0.03.
2.
Compute values within following parameters:
a. Torque values + 2 percent.
b. Weight values + 500 pounds.
c. Fuel flow + 100 pounds per hour.
d. Airspeeds + 5 knots.
6
Prepare a Performance Planning Card
- Task 1010
3.
4.
Determine performance planning data necessary to complete the
mission.
Correctly determine aircraft weight, maximum torque available,
maximum allowable gross weight (OGE), and GO/NO GO (OGE)
using tabular data found in the CL when an update is required.
Note. Updates – Care should be taken to monitor the accomplishment
of the mission. The PPC should be updated in flight or on the
ground as the mission progresses if the requirements below are
met. Updates are required when there is the intent to land and/or
takeoff and when operating within 3,000 pounds of the MAX
ALLOWABLE GWT (OGE) and there is an increase of 500 feet
pressure altitude, and/or 5 degrees Celsius from the planned
PPC.
Ref: TC 1-237 page 4-29 ARRIVAL DATA UPDATES
7
Prepare a Performance Planning Card
- Task 1010
Planning:
The aviator will evaluate
aircraft performance, departure, en route
and approach data, notices to airmen
(NOTAM), and appropriate FLIP or DOD
publications.
Ref: AR 95-1, p. 17, Para. 5-2 a
8
DATA BASIS
The data provided generally is based on one
of three categories.
Flight Test Data
Calculated Data
Estimated Data
9
PERFORMANCE DATA
BASIS CLEAN
The clean configuration assumes all doors
and windows are closed and includes the
following external configuration:
-
Fixed provisions for ESSS
Main and tail rotor deice system.
Mounting brackets for IR jammer and chaff dispenser.
The HIRSS with Baffles installed.
Includes wire strike protection system.
10
NOTE:
Aircraft which have an external configuration
which differs from the clean configuration
may be corrected for drag differences on
cruise performance as discussed in Section
VI Drag.
11
PERFORMANCE DATA BASIS
HIGH DRAG
-
The high drag configuration assumes all
doors and windows are closed and includes the
following external configuration.
ESSS installed.
Two 230-gallon tanks mounted on the outboard
pylons.
Inboard vertical pylons empty
IR jammer and chaff dispenser installed.
HIRSS with baffles are installed
Main and tail rotor de-ice and wire strike systems
installed.
12
DA FORM 5701-60-R
UH-60 PERFORMANCE PLANNING
CARD
13
Enabling Learning Objective (ELO) #2:
Action: Describe the four major areas of the
Performance Planning Card.
Condition: Given a blank Performance
Planning Card (PPC) DA 5701-60-R, TC 1237, TM 1-1520-237-10, and TM 1-1520-237CL.
Standard: In accordance with Performance
Planning Card (PPC) DA 5701-60-R, TC 1237, TM 1-1520-237-10, and TM 1-1520-237CL, and classroom instruction.
14
DA 5701-60-R
Description
Departure
Remarks
Cruise
Arrival
15
Arrival Section
Arrival data. Complete this section in its entirety if
arrival conditions at destination have increased from
DEPARTURE in any of the following by the
minimum amount: 5 degrees Celsius, 1,000 feet PA,
or 500 pounds.
16
Enabling Learning Objective (ELO) #3:
Action: Define terms and compute a
Performance Planning Card.
Condition: Given a blank Performance
Planning Card (PPC) DA 5701-60-R, TC 1237, TM 1-1520-237-10, and TM 1-1520-237CL.
Standard: In accordance with Performance
Planning Card (PPC) DA 5701-60-R, TC 1237, TM 1-1520-237-10, and TM 1-1520-237CL, and classroom instruction.
17
Departure Section
14,000
240
150
+25
+19
2,000
.95
1.0
.90
From Log Book or…
1.0 + .90 = 1.90 x 1/2 = .95
18
Torque Factor Chart
Two Instances
Chart is not
needed:
•FAT 35oC or higher
•ETF/ATF is 1.0
19
Determine Torque Ratio(s)
14,000
240
150
.95
+25
+19
1.0
1.0
.9
.91
.91
20
Determine Torque Ratio(s)
14,000
240
150
.95
.955
+25
1.0
1.0
+19
.90
.91
.955
21
Max Torque Available (MTA)
Upper Portion
Read Torque
here for 1.0
Read Torque here
for other than1.0
Lower Portion
22
Determine MTA
14,000
240
150
+25
+19
2,000
.95
.955
1.0
1.0
.90
.91
106
106%
23
Engine Bleed Air
• With engine bleed air turned on, the
maximum available torque is reduced as
follows:
• Engine anti-ice on: Reduce torque
determined by a constant 16%.
• Cockpit heater on: Reduce torque
available by 4%.
• Both on: Reduce torque available by 20%.
24
Determine MTA
14,000
240
150
+25
+19
2,000
.95
.955
1.0
1.0
106
.90
.91
96
106 x .91 = 96.46
25
Determine MTA
14,000
240
150
+25
+19
2,000
.95
.955
1.0
1.0
106
.90
.91
96
96%
Additional
Method
26
Determine MTA
14,000
240
240
150
150
+25
+25
+19
+19
1.0
1.0
106
.90
.91
96
2,000
.95
.955
101
106 X .955 = 101.23
27
Determine Max Allowable GWT OGE
14,000
240
150
+25
+20
2,000
.95
.955
101
1.0
1.0
.90
.91
106
96
20,880
20,880
28
Determine Max Allowable GWT IGE
14,000
240
150
+25
+19
2000
+22,000
20,880
.95
1.0
.955
101
1.0
106
.90
.91
96
22,000
29
Determine GO/NO-GO Torque
Note: GO/NO is computed using the maximum forecast
pressure altitude and temperature for the mission. When the
actual temperature is less than maximum, the torque
required to hover at a given gross weight is less.
TC 1-237 page 4-17
14,000
240
150
+25
+19
2,000
.95
.955
101
20,880
85
85%
92%
1.0
1.0
106
.90
.91
96
22,000
92
30
Max Hover Height IGE
14,000
240
150
+25
+19
2,000
.95
.955
101
20,880
85
1.0
1.0
106
.90
.91
96
22,000
92
OGE
Compute if OGE Hover Capability does not exist
Note. If OGE capability does exist, place OGE in this block.
31
Predicted Hover Torque (Dual Engine)
Forecast Takeoff
Conditions
14,000
240
150
+25
+19
2,000
.95
1.0
.955
1.0
101
20,880
.90
.91
96
106
22,000
85
92
OGE
53
53%
32
Predicted Hover Torque (Single
Engine)
14,000
240
150
+25
+19
Dual Engine
Predicted Hover Torque x 2
2,000
(53 x 2 = 106)
.95
1.0
.90
.955
1.0
.910
Note. If not applicable (NA) is recorded in the appropriate
blocks, the
101
106
96
22,000 hover at a lower
aircraft may still be capable of sustaining 20880
single engine
wheel height.
85
OGE
53
92
106
NA
Do we have single engine hover capability?
33
Min SE - IAS w & w/o Stores
14,000
240
150
+25
+19
2,000
.95
1.0
.955
101
.90
1.0
106
20,880
22,000
85
92
.91
96
OGE
53
106
17
17 kts
NA
NA
1/2 MTA of the
Weakest Engine
96 x 1/2 = 48%
34
Enabling Learning Objective (ELO) #4:
Action: Determine zero fuel weight.
Condition: Given a blank Performance
Planning Card (PPC) DA 5701-60-R, TC 1237, TM 1-1520-237-10, and TM 1-1520-237CL, wheel height, hover torque, free air
temperature and PA, indicated fuel weight.
Standard: In accordance with Performance
Planning Card (PPC) DA 5701-60-R, TC 1237, TM 1-1520-237-10, and TM 1-1520-237CL, and classroom instruction.
35
Zero Fuel Weight
• Zero Fuel Weight on 365-4
is computed using
estimates and averages
14,000
240
150
+25
+19
2,000
• Actual weights may vary
greatly
• If the PC feels that an
accurate weight cannot be
estimated, compute an
adjusted zero fuel weight.
.95
1.0
.955
101
1.0
106
20,880
22,000
85
92
.90
.91
96
OGE
53
106
17
NA
NA
36
Zero Fuel Weight
•
There will be times due to winds,
surface, or any other condition that
cause the hover torque to be
inaccurate so that you will be unable
to use the method below.
• Prior to Hover note:
– FAT
– PA
– Total Indicated Fuel
FAT: 20oC
PA: 200
Fuel: 2000
Height: 10
• At a Hover note:
– Wheel Height
– Hover Torque
Torque: 53
37
Zero Fuel Weight
14,000 - 2000= 12,000
FAT:
20oC
14,000
PA: 200
Fuel: 2000
Height: 10
Torque: 53
38
Zero Fuel Weight
14,000
240
150
+25
+19
2,000
12,000
.95
1.0
.955
101
1.0
106
20,880
22,000
85
92
.90
.91
96
OGE
53
106
17
NA
NA
•Note. Although data needed to compute zero fuel
weight is noted at a hover, the calculation should be
made when practical.
39
Remarks Section
• Record mission information such as:
– Drag Factors
– Fuel Requirements
– GO/NO-GO for sling loads
– What chart you are using for your Cruise data
– And anything else for your mission
40
Cruise Chart
FIND THIS CHART
41
The continuous torque available is
Also referred to as MAXIMUM
CONTINUOUS POWER (MCP)
(TC 1-212)
42
Max TQ for 1.0 engine
(above Transmission
Limit of 100%)
The maximum torque available
is presented on each chart as
either the transmission torque
limit or torque available-30 min
for an ATF of 1.0 with an ATF=
0.9 scale at the bottom of the
torque scale. The max trq
available for a helicopter with
an ATF value between these
shall be interpolated. (TM 1-1520237-10)
Max TQ for 0.9 engine
(below Transmission
Limit of 100%)
43
The Max Trq available,
single-engine, is
presented on each chart
as an SE-30MIN line at
half the actual max trq
available for an ETF of
1.0, with an ETF = 0.85
scale below the trq
scale. The max trq
available for engines
with an ETF value
between these must be
interpolated using the
same procedure as for
duel-engine. (TM 11520-237-10)
At zero airspeed, the trq
represents the trq required to
hover out of ground effect.
In general, mission planning
for low-speed flight should
be based on hover out of
ground effect. (TM 1-1520237-10)
.85 Lowest allowable
44
Max Torque Available Cruise
Step 1: Enter the chart at the bottom with the ATF and
follow the slant of the line up to Dual Engine Cruise IAS.
1,000
20
Step 2: Read straight down to get your Max Torque. If
the ATF is between 1.0 and 0.9, interpolation is another
method to obtain this value.
101
106
97
Maximum torque available can be
Derived from the cruise chart by
Referencing the torque available
30-min (T700) or 10-min (T701)
ATF 1.0 line.
101
If the ATF is between 1.0 and 0.9
Interpolation is another method to
45
obtain this value.
Critical Torque
1,000
20
48
101
106
97
1/2 MTA of Low ETF Engine
Dual Engine Torque Value, which when
exceeded, may not allow the aircraft to
maintain % RPMR within normal limits
under single-engine operations in the
same flight conditions
Conservatism was used in determining CT as 97% divided
by 2 is 48.5%.
46
MIN / MAX - IAS (Optional)
1,000
20
48
101
106
0
0
47
If MTA is Right of GWT then MIN IAS = 0 kts
97
MIN / MAX - IAS
157
20
48
101
0
106
97
157
48
Cruise - IAS / TAS
124
20
48
101
0
120
106
97
157
124
49
Cruise Torque
1,000
20
48
101
0
120
106
97
157
124
52
52
50
Cruise Fuel Flow
850
1,000
20
48
101
0
120
106
97
157
124
52
850
51
Fuel Flow
• With bleed air extracted, fuel flow
increases:
• Engine anti - ice on-About 60 lbs/hr
• Heater on - About 20 lbs/hr
• Both on - About 80 lbs/hr
52
Continuous Torque Available (Optional)
1,000
20
48
78
101
157
0
120
124
52
850
78
106
97
“Enter the cruise chart at the selected cruise IAS. Move left or
right as appropriate to the Torque Available-Continuous line,0.9
or 1.0 using the ETF for the weakest engine. If the ETF of the
Weakest engine is between 0.9 and 1.0, then Interpolation is
required. The TORQUE AVAILABLE-CONTINUOUS
53
is predicated on the weakest engine.” TC 1-237 page 4-23
Max Range-IAS / Torque
(Optional)
1,000
20
129
48
101
0
120
106
97
157
124
52
850
78
129
60
60
54
Max Endurance / Max R/C-IAS
1)Enter the bottom of the
(Optional)
appropriate cruise chart at the
aircraft GWT. Move up the
gross weight line to intersection
of the gross weight line and the
max end and R/C line. Record
the value. 63 kts
2) Determine torque increase
per engine (MTA minus Max
End IAS Torque)
1,000
20
48
101
0
120
106
97
157
124
52
850
78
129
63
60
101 (max tq) – 34 (tq at 63kts)
=67 (to be used with climb charts)
55
Climb/Descent Charts
Chapter 7
Section VII
Page 7-151
Rate of Descent
Find the
Proper
chart
Rate of Climb
56
Climb Chart
3300+
3) Enter at 67 % and move up to the
aircraft gross weight. Note the rate of
climb for the next step.
57
Airspeed System Correction
Chapter 7
Section IX
Page 7-156
Add 12 kts
4) Enter at the bottom of
the chart using 63 kts max
endurance airspeed. Move
up to the previously
determined rate of climb of
+3300 feet. (In this case
greater than 1400 FT /
MIN.)
58
Max R/C-IAS / Torque
5) Add (or subtract) value from
Airspeed Correction Chart
to/from Max End IAS
63+12=75
1,000
20
48
101
0
120
Bring 12kts from
Airspeed Correction
System chart
106
97
157
124
52
850
78
129
63
60
75
59
MIN / MAX - IAS (single engine)
1,000
114
20
48
101
0
120
157
124
106
97
17
114
52
850
78
129
63
60
75
17
Use 1/2 MTA of the Weakest Engine
97 x 1/2 = 48 (CT)
60
Cruise - IAS/TAS (single engine)
(Optional)
87
1,000
20
48
101
0
120
157
124
52
850
78
129
60
63
75
106
17
80
97
114
87
61
Cruise Torque (Single Engine)
(Optional)
1,000
20
48
101
0
120
157
124
52
850
78
129
60
63
75
36 X 2 = 72
106
17
80
97
114
87
72
62
Cruise Fuel Flow (Single Engine)
(Optional)
1047 X 1/2 = 523
1,000
20
48
101
0
120
157
124
52
850
78
129
63
106
17
80
97
114
87
72
523
60
75
63
Continuous Torque Available
(Single Engine)
1,000
20
48
101
0
120
157
124
52
850
97
114
87
72
523
76
78
129
63
106
17
80
60
75
76
64
Compute Max Altitude-MSL
based on Max End-IAS.
Max Altitude - MSL
(Dual & Single
Engine) (Optional)
Note. Several different cruise
charts may have to be referenced
when computing Max AltitudeMSL.
Note. To achieve your Max
Altitude-MSL you must fly max
End-IAS.
Note. Ensure you account for
changes in FAT as you change
Cruise charts.
Note. When single engine
capability does not exist at the
planned cruise altitude, this
block is required to be computed.
Note. If level flight cannot be
maintained either with or without
stores, record NA in Max AltitudeMSL single engine block.
1,000
20
48
101
0
120
157
124
52
850
97
114
87
72
523
76
78
129
63
106
17
80
60
75
65
Max Allowable GWT-Single
Engine (Optional)
Step1: Using the SE 30 Min or 2.5 MIN line, enter the
bottom of the Cruise chart at the lowest ETF.
1,000
20
Step 2: Follow
the slant of the line up to the
intersection of the Max End and R/C line then read the
indicating max allowable gross weight.
48 allowable
101gwt is less than
106 the97
Note: If the max
aircraft
17
114
gwt, then the aircraft cannot
maintain single
engine
0
157
120
124
80
87
level flight for the conditions.
As fuel is burned,
single
52
72
engine capability during flight may be possible.
849
TC 1-237 Page 4-27
20,000
129
63
523
76
78
60
75
20,000
66
Optimum IAS at Max Allowable GWT
(Single Engine) (Optional)
1,000
20
48
101
0
120
20,000
157
124
52
850
73
97
114
87
72
523
76
78
129
63
106
17
80
60
75
20,000
73
Read left or right for optimum IAS – KTS at maximum
allowable gross weight. If the maximum torque
available line is right of the gross weight lines, enter
MAX ALLOWABLE GWT according to the operator’s
manual.
67
TC 1-237 page 4-27
Max Angle
1,000
20
48
Use the Onset of Blade
Stall chart in the -10,
Chapter 5, Figure 5-9,
Page 5-20
101
0
120
157
124
52
850
97
114
87
72
523
76
78
129
63
106
17
80
60
75
20,000
73
68
Max Angle
-10, Chapter 5
Figure 5-9
Page 5-20
59o
69
Max Angle
1,000
20
59
48
101
0
120
157
124
52
850
97
114
87
72
523
76
78
129
63
106
17
80
60
75
20,000
73
59o
70
Vne - IAS
1,000
20
59
48
101
0
120
157
124
52
850
106
17
80
97
114
87
72
523
76
78
129
63
193
60
75
20,000
73
193
-10, Chapter 5
Figure 5-6
Page 5-14
71
Arrival Section
DEPARTURE
ARRIVAL
12,500
14,000
240
150
+25
250
+19
.955
101
2,000
12,000
.95
.955
101
20,880
22,000
85
92
OGE
53
1.0
1.0
106
106
+25
.90
.91
96
1.0
106
.91
96
20,880
NA
Complete the Arrival Section if arrival conditions at
destination differ significantly from Departure conditions
Do we need to complete the Arrival Section?
72
Tabular Data
• Standard # 4. Correctly determine aircraft
weight, maximum torque available,
maximum allowable gross weight (OGE),
and GO/NO-GO (OGE) using tabular data
found in the –CL when an update is
required.
73
Enabling Learning Objective (ELO) #5:
Action: Update the Performance Planning Card.
Condition: Given a completed Performance
Planning Card (PPC) DA 5701-60-R, TC 1-237,
TM 1-1520-237-10, and TM 1-1520-237-CL,
indicated fuel, and updated takeoff and/or
landing environmental conditions.
Standard: In accordance with Performance
Planning Card (PPC) DA 5701-60-R, TC 1-237,
TM 1-1520-237-10, and TM 1-1520-237-CL, and
classroom instruction.
74
Updates
Note. Updates-Care should be taken to monitor the
accomplishment of the mission. The PPC should
be updated in flight or on the ground as the mission
progresses if the requirements below are met.
Updates are required when there is intent to land
and/or takeoff and when operating within 3,000
pounds of the Max Allowable GWT (OGE) and
there is an increase of 500 feet pressure altitude,
and/or 5 degrees Celsius from the planned PPC.
UPDATE:
Aircraft Weight
Max Torque Available
Max Allowable GWT OGE
75
GO/NO-GO OGE
Change in Arrival Conditions
During your flight you receive a change in mission requiring you to pick
up an internal load of 4000 lb at a field location with the following
conditions.
• Arrival Temp = +35oC
• Arrival PA = 3,000
• Internal fuel weight is 1200 lb
Is an update required?
Yes
12,500
250
.955
101
48
20,880 22,000
85
92
OGE
+25
1.0
106
96
.91
96
96
8
76
Update Aircraft Weight
 Determine the aircraft weight using the zero fuel
method. What does your aircraft weigh?
• 12,000 + 1200 = 13,200 pounds
 Will you be within 3000 lb of MAX
ALLOWABLE GWT (OGE)?
• Yes, our weight with the load is 17,200
pounds. Tab data indicates Max Allowable
GWT-OGE to be 17,950 pounds.
 Is an update required?
• Yes
77
Enabling Learning Objective (ELO) #6:
Action: Correctly determine maximum torque
available, maximum gross weight (OGE), and
GO/NO-GO (OGE) using tabular data found in
the CL.
Condition: Given a completed Performance
Planning Card (PPC) DA 5701-60-R, TC 1-237,
TM 1-1520-237-10, and TM 1-1520-237-CL.
Standard: In accordance with Performance
Planning Card (PPC) DA 5701-60-R, TC 1-237,
TM 1-1520-237-10, and TM 1-1520-237-CL, and
classroom instruction.
78
Update Max Torque Available
• Read MTA at intersection of
PA and FAT
• If ATF is between .9 and 1.0
interpolate MTA
79
P-35
Update Max Torque Available
To Interpolate:
1. Determine Multiplication
Factor: ATF .95 is 5/10th the
difference between ATF .90
and 1.0. Mult. Factor = .5
2. 1.0 ATF = 90%
3. .9 ATF = 81%
4. Subtract .9 MTA from 1.0
MTA: 90 - 81 = 9%
80
P-35
Update Max Torque Available
5. Multiply results of step 4
by Multiplication Factor:
9 x .5 = 4.5%
6. Add the results of Step 5
to .9 ATF MTA:
81 + 4.5 = 85.5%
7. Round down:
MTA = 85%
81
P-35
Update Max Allowable GWT OGE
• Read Max Allowable GWT
at intersection of PA and FAT
• If ATF is between .9 and 1.0
interpolate Max Allowable
GWT
82
P-53
Update Max Allowable GWT OGE
To Interpolate:
1. Determine Multiplication
Factor: ATF .95 is 5/10th the
difference between ATF .90
and 1.0. Mult. Factor = .5
2. 1.0 Max GWT = 18,600
3. .9 Max GWT = 17,300
4. Subtract .9 Max GWT
from 1.0 Max GWT:
18,600 - 17,300 = 1,300
83
P-53
Update Max Allowable GWT OGE
5. Multiply results of step 4
by Multiplication Factor:
1,300 x .5 = 650
6. Add the results of Step 5
to .9 ATF Max GWT:
17,300 + 650 = 17,950
Max Allowable GWT = 17,950
84
P-53
Update GO/NO-GO OGE
• Read Go/No-Go OGE at
intersection of PA and FAT
• If ATF is between .9 and 1.0
interpolate Go/No-Go OGE
85
P-53
Update GO/NO-GO OGE
To Interpolate:
1. Determine Multiplication
Factor: ATF .95 is 5/10th the
difference between ATF .90
and 1.0. Mult. Factor = .5
2. 1.0 Go/No-Go = 77%
3. .9 Go/No-Go = 70%
4. Subtract .9 Go/No-Go
from 1.0 Go/No-Go:
77 - 70 = 7%
86
P-53
Update GO/NO-GO OGE
5. Multiply results of step 4
by Multiplication Factor:
7 x .5 = 3.5 %
6. Add the results of Step 5
to .9 Go/No-Go Torque:
70 + 3.5 = 73.5 %
7. Round down:
Go/No-Go OGE = 73%
87
P-53
How to determine values that require two pages.
Temp: 27
PA: 2500
ATF: .95
• Read Max Allowable GWT at
intersection of PA and FAT
• If ATF is between .9 and 1.0
interpolate Max Allowable
GWT (as previously described)
20,100 – 18,800 = 1300 lb
1300 x .5(ATF) = 650 lb
18,800 + 650 = 19,450 lb
88
P-50
How to determine values that require two pages.
continued
Temp: 27
PA: 2500
ATF: .95
• Read Max Allowable GWT at
intersection of PA and FAT
• If ATF is between .9 and 1.0
interpolate Max Allowable
GWT (as previously described)
19,600 – 18,300 = 1300 lb
1300 x .5(ATF) = 650 lb
18,300 + 650 = 18,950
19,450 – 18,950 = 500 lb
500 x .5(ATF) = 250 lb
18,950 + 250 = 19,200 lb
89
P-53
SUMMARY
The purpose of the performance planning card (PPC).
When the PPC is to be completed.
The four major sections of the PPC.
Define terms and compute values.
Determine zero fuel weight.
Updates to the PPC.
The use of tabular data found in the - CL.
90
91