1. UH-60 Performance Planning
Version date
January 2006

2. Terminal Learning objective (TLO):
At the completion of this lesson the student will:
Action: Completion of the performance planning card (PPC) DA Form R.
Condition: As a UH-60 aviator.
Standard: In accordance with TC 1-237, TM , TM CL.
Safety Requirements: None
Environmental Considerations: None

3. Enabling Learning Objective (ELO) #1:
Action: Define the purpose of the Performance Planning Card (PPC) DA R.
Condition: Given a blank Performance Planning Card (PPC) DA R, TC 1-237, TM , and TM CL.
Standard: In accordance with Performance Planning Card (PPC) DA R, TC 1-237, TM , and TM CL, and classroom instruction.

4. 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

5. 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.

6. Prepare a Performance Planning Card - Task 1010
STANDARDS: Appropriate common standards plus the following additions/modifications:
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 pounds.
d. Engine torque factor (ETF) 0.03.
Compute values within following parameters:
a. Torque values + 2 percent.
b. Weight values pounds.
c. Fuel flow pounds per hour.
d. Airspeeds + 5 knots.

7. Prepare a Performance Planning Card - Task 1010
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 page ARRIVAL DATA UPDATES

8. 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

9. DATA BASIS The data provided generally is based on one of three categories.
Flight Test Data
Calculated Data
Estimated Data

10. 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.

11. 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.

12. 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.

13. DA FORM 5701-60-R UH-60 PERFORMANCE PLANNING CARD

14. 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 R, TC 1-237, TM , and TM CL.
Standard: In accordance with Performance Planning Card (PPC) DA R, TC 1-237, TM , and TM CL, and classroom instruction.

15. DA R
Description
Departure
Remarks
Cruise
Arrival

16. 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.

17. Enabling Learning Objective (ELO) #3:
Action: Define terms and compute a Performance Planning Card.
Condition: Given a blank Performance Planning Card (PPC) DA R, TC 1-237, TM , and TM CL.
Standard: In accordance with Performance Planning Card (PPC) DA R, TC 1-237, TM , and TM CL, and classroom instruction.

18. Departure Section 1.0 + .90 = 1.90 x 1/2 = .95 From Log Book or… 240
+25
14,000
+19
150
2,000
.95
1.0
.90
From Log Book or…
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE.
= 1.90 x 1/2 = .95

19. Torque Factor Chart Two Instances Chart is not needed:
FAT 35oC or higher
ETF/ATF is 1.0

20. Determine Torque Ratio(s)
14,000
240
150
+25
+19
.95
1.0 .9
1.0
.91
.91

21. Determine Torque Ratio(s)
14,000
240
150
+25
+19
1.0
.95
.90
.955
1.0
.91
.955

22. Max Torque Available (MTA)
Upper Portion
Read Torque here for 1.0
Read Torque here for other than1.0
Lower Portion

23. Determine MTA
14,000
240
150
+25
+19
2,000
.955
1.0
.91
106
Enter the MAXIMUM TORQUE AVAILABLE chart from the left at the Maximum Forecast Temperature and move across to the Maximum Forecast Pressure Altitude. Read down ward and stop at the bottom of the first chart and read Specification Torque Available – per engine. I came up with 102%. This is the torque value that a 1.0 ETF, a “Specification” engine, will produce at the desired FAT and PA. If you have a 1.0 ATF Aircraft you just computed Maximum Torque Available. But we don’t have a 1.0 ATF or ETF so we have to correct. You may continue down the chart to the lower half or you may use your calculator. Less do the first one with the chart and compare the figures. Continuing down to the lower chart using that 102% vertical line until you intercept the #1 TR, .953 Line and move left and read the maximum Torque Available. I came up with 97% MTA for the #1 engine.
106%

24. 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%.

25. Determine MTA
1.0
.955
.91
14,000
240
150
+25
+19
2,000
106 96
Enter the MAXIMUM TORQUE AVAILABLE chart from the left at the Maximum Forecast Temperature and move across to the Maximum Forecast Pressure Altitude. Read down ward and stop at the bottom of the first chart and read Specification Torque Available – per engine. I came up with 102%. This is the torque value that a 1.0 ETF, a “Specification” engine, will produce at the desired FAT and PA. If you have a 1.0 ATF Aircraft you just computed Maximum Torque Available. But we don’t have a 1.0 ATF or ETF so we have to correct. You may continue down the chart to the lower half or you may use your calculator. Less do the first one with the chart and compare the figures. Continuing down to the lower chart using that 102% vertical line until you intercept the #1 TR, .953 Line and move left and read the maximum Torque Available. I came up with 97% MTA for the #1 engine.
106 x .91 = 96.46

26. Determine MTA Additional Method 96% 14,000 240 150 +25 +19 2,000
.955
1.0
.91
106 96
Enter the MAXIMUM TORQUE AVAILABLE chart from the left at the Maximum Forecast Temperature and move across to the Maximum Forecast Pressure Altitude. Read down ward and stop at the bottom of the first chart and read Specification Torque Available – per engine. I came up with 102%. This is the torque value that a 1.0 ETF, a “Specification” engine, will produce at the desired FAT and PA. If you have a 1.0 ATF Aircraft you just computed Maximum Torque Available. But we don’t have a 1.0 ATF or ETF so we have to correct. You may continue down the chart to the lower half or you may use your calculator. Less do the first one with the chart and compare the figures. Continuing down to the lower chart using that 102% vertical line until you intercept the #1 TR, .953 Line and move left and read the maximum Torque Available. I came up with 97% MTA for the #1 engine.
96%
Additional Method

27. Determine MTA
14,000
240
240
150
150
+25
+25
+19
+19
2,000
.955
.955
1.0
.91
101
106 96
Enter the MAXIMUM TORQUE AVAILABLE chart from the left at the Maximum Forecast Temperature and move across to the Maximum Forecast Pressure Altitude. Read down ward and stop at the bottom of the first chart and read Specification Torque Available – per engine. I came up with 102%. This is the torque value that a 1.0 ETF, a “Specification” engine, will produce at the desired FAT and PA. If you have a 1.0 ATF Aircraft you just computed Maximum Torque Available. But we don’t have a 1.0 ATF or ETF so we have to correct. You may continue down the chart to the lower half or you may use your calculator. Less do the first one with the chart and compare the figures. Continuing down to the lower chart using that 102% vertical line until you intercept the #1 TR, .953 Line and move left and read the maximum Torque Available. I came up with 97% MTA for the #1 engine.
106 X .955 =

28. Determine Max Allowable GWT OGE
14,000
240
150
+25
+20
2,000
.955
1.0
.91
101
106 96
20,880
20,880

29. Determine Max Allowable GWT IGE
106
14,000
240
150
+25
+19
2000
.95
1.0
.90
.955
1.0
.91
101 96
+22,000
20,880
22,000

30. 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 page 4-17
14,000
240
150
+25
+19
2,000
.95
1.0
.90
.955
1.0
.91
101
106 96
20,880
22,000 85 92
85%
92%

31. Compute if OGE Hover Capability does not exist
Max Hover Height IGE
14,000
240
150
+25
+19
2,000
.95
1.0
.90
.955
1.0
.91
101
106 96
20,880
22,000 85 92
OGE
Compute if OGE Hover Capability does not exist
Note. If OGE capability does exist, place OGE in this block.

32. Predicted Hover Torque (Dual Engine)
Forecast Takeoff Conditions
14,000
240
150
+25
+19
2,000
.95
1.0
.90
.955
1.0
.91
101
106 96
20,880
22,000 85 92
OGE 53
53%

33. Predicted Hover Torque (Single Engine)
14,000
240
150
+25
+19
Dual Engine Predicted Hover Torque x 2
(53 x 2 = 106)
Note. If not applicable (NA) is recorded in the appropriate blocks, the aircraft may still be capable of sustaining single engine hover at a lower wheel height.
2,000
.95
1.0
.90
.955
1.0
.910
101
106 96
20880
22,000 85 92
OGE 53 NA
Do we have single engine hover capability?

34. Min SE - IAS w & w/o Stores
14,000
240
150
+25
+19
2,000
.95
1.0
.90
.955
1.0
.91
101
106 96
20,880
22,000 85 92
OGE 53
106 NA NA
1/2 MTA of the Weakest Engine
96 x 1/2 = 48%
17 kts
48%

35. Enabling Learning Objective (ELO) #4:
Action: Determine zero fuel weight.
Condition: Given a blank Performance Planning Card (PPC) DA R, TC 1-237, TM , and TM CL, wheel height, hover torque, free air temperature and PA, indicated fuel weight.
Standard: In accordance with Performance Planning Card (PPC) DA R, TC 1-237, TM , and TM CL, and classroom instruction.

36. Zero Fuel Weight
Zero Fuel Weight on is computed using estimates and averages
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
.90
240
+25
14,000
+19
150
20,880
.91
2,000 85 92
106 NA
101 53 NA
.955
OGE 96
22,000

37. Zero Fuel Weight Prior to Hover note: FAT FAT: 20oC PA PA: 200
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
At a Hover note:
Wheel Height
Hover Torque
FAT: 20oC
PA: 200
Fuel: 2000
Height: 10
Torque: 53

38. Zero Fuel Weight 14,000 - 2000= 12,000 14,000 FAT: 20oC PA: 200
Height: 10
Torque: 53

39. Zero Fuel Weight
.95
1.0
.90
240
+25
14,000
+19
150
20,880
.91
2,000 85 92
106 NA
101 53 NA
.955
OGE 96
22,000
12,000
Note. Although data needed to compute zero fuel weight is noted at a hover, the calculation should be made when practical.

40. 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

41. Cruise Chart
FIND THIS CHART

42. The continuous torque available is
Also referred to as MAXIMUM
CONTINUOUS POWER (MCP)
(TC 1-212)

43. (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
237-10)
Max TQ for 1.0 engine
(above Transmission Limit of 100%)
Max TQ for 0.9 engine
(below Transmission
Limit of 100%)

44. 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 )
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
237-10)
.85 Lowest allowable

45. Max Torque Available Cruise
1,000 20
Step 1: Enter the chart at the bottom with the ATF and follow the slant of the line up to Dual Engine Cruise IAS.
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.
If the ATF is between 1.0 and 0.9
Interpolation is another method to
obtain this value.
101

46. Critical Torque 1/2 MTA of Low ETF Engine
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%.

47. MIN / MAX - IAS (Optional)
1,000 20 48
101
106 97
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE.
If MTA is Right of GWT then MIN IAS = 0 kts

48. MIN / MAX - IAS
157 20 48
101
106 97
157
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE.

49. Cruise - IAS / TAS
124 20 48
101
106 97
157
120
124
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE.

50. Cruise Torque
1,000 20
106 48
101 97
157
120
124 52
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE. 52

51. Cruise Fuel Flow
850
1,000 20 48
101
106 97
157 52
850
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE.

52. 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

53. Continuous Torque Available (Optional)
1,000 20 48
101
106 97
157
120
124 52
850 78
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE.
“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
is predicated on the weakest engine.” TC page 4-23 78

54. Max Range-IAS / Torque (Optional)
1,000 20
129 48
101
106 97
157
120
124 52
850 78
129 60
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE. 60

55. Max Endurance / Max R/C-IAS (Optional)
1,000 20
106 48
157
850
101 97
120
124
129 60
2) Determine torque increase per engine (MTA minus Max End IAS Torque)
101 (max tq) – 34 (tq at 63kts)
=67 (to be used with climb charts)
1)Enter the bottom of the 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 63 52 78
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE.

56. Climb/Descent Charts Find the Proper chart Chapter 7 Section VII
Page 7-151
Rate of Descent
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE.
Find the Proper chart
Rate of Climb

57. Climb Chart
3300+
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE.
3) Enter at 67 % and move up to the aircraft gross weight. Note the rate of climb for the next step.

58. 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 feet. (In this case greater than 1400 FT / MIN.)
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE.

59. Max R/C-IAS / Torque Bring 12kts from Airspeed Correction System chart
5) Add (or subtract) value from Airspeed Correction Chart to/from Max End IAS
63+12=75
1,000 20
106 48
157
850
101 97 78
120
124
129 60 52
Bring 12kts from Airspeed Correction System chart
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE.

60. MIN / MAX - IAS (single engine)
1,000 20
114 48
101
106 97
157 17
114
120
124 52
850 78
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE.
129 60 63 75 17
Use 1/2 MTA of the Weakest Engine
97 x 1/2 = 48 (CT)

61. Cruise - IAS/TAS (single engine) (Optional)87
1,000 20 48
101
106 97
157 80 87 52
850
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE. 78

62. Cruise Torque (Single Engine)
(Optional)
1,000 20 48
101
106 97
157
120
124 52 72
850 78
129 60
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE. 36
X 2 = 72

63. Cruise Fuel Flow (Single Engine) (Optional)
1047
X 1/2 = 523
1,000 20 48
101
106 97
157
120
124 52 72
850
523 78
129 60
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE.

64. Continuous Torque Available (Single Engine)
1,000 20 48
101
106 97
157
120
124 52 72
850
523 78 76
129 60 76

65. Max Altitude - MSL (Dual & Single Engine) (Optional)
Compute Max Altitude-MSL based on Max End-IAS.
Note. Several different cruise charts may have to be referenced when computing Max Altitude-MSL.
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 Altitude-MSL single engine block.
Max Altitude - MSL (Dual & Single Engine) (Optional)
1,000 20
106 48
850
101 97 78
129 60
523
157 52
120
124 76 72

66. 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.
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.
Note: If the max allowable gwt is less than the aircraft gwt, then the aircraft cannot maintain single engine level flight for the conditions. As fuel is burned, single engine capability during flight may be possible.
TC Page 4-27
1,000 20
106 48
101 97 78
129 60
523 52
120 76 72
124
849
157
20,000
20,000

67. Optimum IAS at Max Allowable GWT (Single Engine) (Optional)
1,000 20
106 48
850
101 97 78
129 60
523
157 52
20,000 76
120
124 72
20,000 73
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE. 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.
TC page 4-27

68. Max Angle
1,000 20
106 48
850
101 97 78
129 60
20,000 76
120
124 72
523
157 52 73
Use the Onset of Blade Stall chart in the -10, Chapter 5, Figure 5-9, Page 5-20
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE.

69. Max Angle
-10, Chapter 5
Figure 5-9
Page 5-20
59o

70. Max Angle
1,000 20
106 48
850
101 97 78
129 60
20,000 76
120
124 72
523
157 52 73 59
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE.
59o

71. Vne - IAS 193 -10, Chapter 5 Figure 5-6 Page 5-14 1,000 20 106 48 850
101 97 78
129 60
20,000 76
120
124 72
523
157 52 73 59
193
Our aircraft today has the weakest engines possible. Don’t you just love Maintenance? The #2 engine is a <click> .85. What is the minimum ETF that the #1 engine can be? Since, the minimum ATF is .90, #1 must be at least a .95 ETF and it is. So the average of the two is .90. With our Aircraft Gross Weight of 19,800 pounds, we’re definitely within 3,000 pounds of our maximum allowable gross weight, but let’s look at how to quickly determine the Max GWT OGE.
193
-10, Chapter 5
Figure 5-6
Page 5-14

72. Do we need to complete the Arrival Section?
DEPARTURE ARRIVAL
12,000
12,500
250
+25
14,000
240
150
+25
+19
.955
1.0
.91
101
106 96
2,000
20,880
.95
1.0
.90
.955
1.0
.91
101
106 96
20,880
22,000 85 92
OGE 53
106 NA
Complete the Arrival Section if arrival conditions at destination differ significantly from Departure conditions
Do we need to complete the Arrival Section?

73. 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.

74. Enabling Learning Objective (ELO) #5:
Action: Update the Performance Planning Card.
Condition: Given a completed Performance Planning Card (PPC) DA R, TC 1-237, TM , and TM CL, indicated fuel, and updated takeoff and/or landing environmental conditions.
Standard: In accordance with Performance Planning Card (PPC) DA R, TC 1-237, TM , and TM CL, and classroom instruction.

75. 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
GO/NO-GO OGE

76. 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
+25
1.0
.955
.91
106
101 96
20,880
22,000 48 85 92
OGE 8

77. Update Aircraft Weight
Determine the aircraft weight using the zero fuel method. What does your aircraft weigh?
12, = 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

78. 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 R, TC 1-237, TM , and TM CL.
Standard: In accordance with Performance Planning Card (PPC) DA R, TC 1-237, TM , and TM CL, and classroom instruction.

79. Update Max Torque Available
Read MTA at intersection of PA and FAT
If ATF is between .9 and 1.0 interpolate MTA
P-35

80. Update Max Torque Available
To Interpolate:
1. Determine Multiplication Factor: ATF .95 is 5/10th the difference between ATF .90 and Mult. Factor = .5
ATF = 90%
ATF = 81%
4. Subtract .9 MTA from 1.0 MTA: = 9%
P-35

81. 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:
= 85.5%
7. Round down:
MTA = 85%
P-35

82. 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
P-53

83. Update Max Allowable GWT OGE
To Interpolate:
1. Determine Multiplication Factor: ATF .95 is 5/10th the difference between ATF .90 and Mult. Factor = .5
Max GWT = 18,600
Max GWT = 17,300
4. Subtract .9 Max GWT from 1.0 Max GWT:
18, ,300 = 1,300
P-53

84. 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, = 17,950
Max Allowable GWT = 17,950
P-53

85. 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
P-53

86. Update GO/NO-GO OGE To Interpolate:
1. Determine Multiplication Factor: ATF .95 is 5/10th the difference between ATF .90 and Mult. Factor = .5
Go/No-Go = 77%
Go/No-Go = 70%
4. Subtract .9 Go/No-Go from 1.0 Go/No-Go:
= 7%
P-53

87. 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:
= 73.5 %
7. Round down:
Go/No-Go OGE = 73%
P-53

88. 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, = 19,450 lb
P-50

89. 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, = 18,950
19,450 – 18,950 = 500 lb
500 x .5(ATF) = 250 lb
18, = 19,200 lb
P-53

90. 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.