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UH-60 Performance Planning Version date January 2006

UH-60 Performance Planning Version date January 2006. 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.

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UH-60 Performance Planning Version date January 2006

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  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 5701-60-R. Condition: As a UH-60 aviator. Standard: In accordance with TC 1-237, TM 1-1520-237-10, TM 1-1520-237-CL. Safety Requirements: None Environmental Considerations: None

  3. 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 1-1520-237-10, 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.

  4. Complete a PPC using the following data:Departure DataA/C weight: 14,000 lbsETF: 1.0 and .90 Departure Temp. 19 degrees CDeparture P.A. 150 FtMax. Temp. 25 degrees CMax. P.A. 240 FtFuel weight 2000 lbsCruise DataCruise Altitude 1,000 FtTemp. 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 + 500 pounds. d. Engine torque factor (ETF) 0.03. • 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.

  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 1-237 page 4-29 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 BASISThe 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 BASISHIGH 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-RUH-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 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.

  15. DA 5701-60-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 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.

  18. 14,000 240 150 +25 +19 From Log Book or… Departure Section 2,000 .95 1.0 .90 1.0 + .90 = 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 .95 1.0 .90 .955 1.0 .91 106 106%

  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. .95 1.0 .90 .955 1.0 .91 Determine MTA 14,000 240 150 +25 +19 2,000 106 96 106 x .91 = 96.46

  26. Determine MTA 14,000 240 150 +25 +19 2,000 .95 1.0 .90 .955 1.0 .91 106 96 96% Additional Method

  27. .95 1.0 .90 Determine MTA 240 240 150 150 +25 +25 +19 +19 14,000 2,000 .955 .955 1.0 .91 101 106 96 106 X .955 = 101.23

  28. Determine Max Allowable GWT OGE 14,000 240 150 +25 +20 2,000 .95 1.0 .90 .955 1.0 .91 101 106 96 20,880 20,880

  29. 106 Determine Max Allowable GWT IGE 14,000 240 150 +25 +19 2000 .95 1.0 .90 .955 1.0 .91 101 96 20,880 22,000 +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 1-237 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 92% 85%

  31. 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 53 106 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 17 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 5701-60-R, TC 1-237, TM 1-1520-237-10, and TM 1-1520-237-CL, 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 1-237, TM 1-1520-237-10, and TM 1-1520-237-CL, and classroom instruction.

  36. 14,000 240 150 +25 +19 2,000 .95 1.0 .90 1.0 .91 101 106 20,880 85 92 .955 96 53 106 NA 17 NA 22,000 OGE Zero Fuel Weight • Zero Fuel Weight on 365-4 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.

  37. 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 • 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 Fuel: 2000 Height: 10 Torque: 53

  39. 14,000 240 150 +25 +19 2,000 .95 1.0 .90 1.0 .91 101 106 20,880 85 92 .955 96 53 106 NA 17 NA 22,000 OGE Zero Fuel Weight 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. 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 1-1520- 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. 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 1-1520- 237-10) 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 1-1520-237-10) .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. 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%. Critical Torque 20 1,000 48 101 106 97

  47. MIN / MAX - IAS (Optional) 1,000 20 48 101 106 97 0 0 If MTA is Right of GWT then MIN IAS = 0 kts

  48. MIN / MAX - IAS 157 20 48 101 106 97 0 157

  49. Cruise - IAS / TAS 124 20 48 101 106 97 0 157 120 124

  50. 20 1,000 48 106 Cruise Torque 101 97 0 157 120 124 52 52

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