THE UH-60A/L BLACKHAWK PERFORMANCE PLANNING …

1 THE. UH-60A/L BLACKHAWK . PERFORMANCE PLANNING . CARD. DA Form 5703-R. VERSION November 2003. TABLE OF CONTENTS. TABLE OF CONTENTS.. 2/3. INTRODUCTION.. 4. DA Form 5703-R DATA.. 5. DA Form 5703-R COMPUTATIONS.. 5. SIGNIFICANT CHANGE .. 6-7. DA FORM DA Form 5703-R (Front) .. 8. DEPARTURE.. 9. Pressure Altitude (ITEM 1) .. 9. Free Air Temperature (ITEM 2) .. 9. Aircraft Gross Weight (ITEM 3) .. 9. Fuel Weight (ITEM 4) .. 10. Stores Weight (ITEM5) .. 10. Sling Weight (ITEM 6) .. 10. Engine Torque Factor (ITEM 7) ..10. Aircraft Torque Factor (ITEM 7) ..11. Torque Ratio (ITEM 8) ..11-13. Maximum Torque Available (ITEM 9) .. 14-23. Maximum Allowable Gross Weight OGE/IGE (ITEM 10) .. 24-25. GO/NO GO Torque (ITEM 11) .. 25-29. Maximum Hover Height IGE (ITEM 12) ..30-31. Predicted Hover Torque (ITEM 13) .. 32-33.

2 Min SE-IAS W/O Stores / W/Stores (ITEM 14) .. 34-35. Zero Fuel Weight (ITEM 15) .. 35-36. Remarks (ITEM 16) .. 37. GO/NO GO External Loads.. 38. CRUISE DATA.. 39. Pressure Altitude (ITEM 1) .. 39. Free Air Temperature (ITEM 2) .. 39. Torque Ratio (ITEM 3) .. 39. Maximum Torque Available (ITEM 4) .. 39. Critical Torque (ITEM 5) .. 40. Duel Engine Min/Max Vh-IAS (ITEM 6) .. 41. Cruise Speed IAS/TAS (ITEM 7) .. 44. Cruise/Continuous Torque (ITEMS 8) .. 46. Cruise Fuel Flow (ITEM 9) .. 47. Maximum Endurance IAS/Torque (ITEM 10) .. 49. Maximum Range IAS/Torque (ITEM 10) .. 49. Maximum Rate of Climb IAS/Torque (ITEM 11) .. 50. Dual Engine Maximum Allowable Gross Weight (ITEM 12) .. 52. Dual Engine Optimum IAS at Maximum Allowable Gross Weight (ITEM 12) .. 52. Single-Engine Data .. 53. Single Engine Min/Max Vh-IAS (ITEM 13).

3 56. 2. Single-Engine Cruise Speed IAS/TAS (ITEM 14) ..57. Single-Engine Cruise/Continuous Torque (ITEM 15) .. 57. Single-Engine Cruise Fuel Flow (ITEM 16) .. 58. MAX ALLOWABLE GWT and OPTIMUM IAS AT MAX ALLOWABLE GWT (single- engine) (ITEM 17) .. 60. Single-Engine Maximum Altitude MSL (Item 18).. 62. Emergency Single-Engine IAS (ITEM 19).. 63. Maximum Angle of Bank (ITEM 20) .. 64. Velocity Never to Exceed (ITEM 21) .. 64. ARRIVAL DATA .. 67. UPDATES .. 68. DA FORM DA Form 5703-R (Back) .. 73. HIGH DRAG/EXTERNAL LOAD COMPUTATIONS .. 74. 3. INTRODUCTION. The authors would like to extend their gratitude to CW4 Bill Young who gave the original explanations for the UH-60 DA Form 5703-R. What The numbers Mean . All explanations referenced in this booklet are for the UH-60A and the UH-60L. Item numbers in parenthesis correlate with respective block numbers on the DA Form 5703-R identified in figure 6-5 and 6-6 in TC 1-212 dated 8 March 1996 (Change 1, dated 15 January 2003).

4 Items listed in this document from TC 1-212 (Change 1) are verbatim and incorporate both UH-60A/L . information and are identified with a ( ). Items listed in this document from TM 1-1520-237-10 are verbatim and are identified with a Unless this publication states otherwise, masculine nouns and pronouns do not refer exclusively to men. This booklet contains information in an exercise format and is intended as an aid to understanding the DA Form 5703-R PERFORMANCE PLANNING Card, and how to derive the values, what the numbers mean and how to apply that information towards safe and efficient utilization of the aircraft for given mission conditions. Instructions for completing the DA Form 5703-R can be found in TC 1-212 (Chg-1), the UH-60. Aircrew Training Manual (ATM) Task 1004, the aircraft operator's manual (-10, dated 1 May 2003), and this booklet.

5 AR 95-1, paragraph 5-2, requires crews to familiarize themselves with aircraft PERFORMANCE . Accurate DA Form 5703-R completion and interpretation is critical to safe and successful mission accomplishment. Regular use of this information will enable the aircrew to achieve maximum safe utilization of the helicopter and provide a basis for a sound foundation in PERFORMANCE PLANNING . Failure to complete a DA Form 5703-R would be found as a contributing or non-contributing factor in any incident or accident investigation where a power management was in question. 4. DA Form 5703-R DATA. The purpose of the new DA Form 5703-R and is to give the pilots a dynamic tool to enhance the mission accomplishment in determining the maximum aircraft PERFORMANCE for any given mission scenario. The data presented in the PERFORMANCE charts are primarily derived for a clean UH-60A/L helicopter and are based on US Army test data.

6 The clean configuration assumes all doors and windows are closed and include the following external configurations: Fixed provisions for the External Stores Support System (ESSS). Main and tail rotor deice system. Mounting brackets for infrared (IR) jammer and chaff dispenser. Hover Infrared Suppressor System (HIRSS) with baffles installed. Includes wire strike protection system (WSPS). The data presented in high drag charts are primarily derived for a UH-60A/L with ESSS system installed and the two 230-gallon tanks mounted on the outboard pylons, and are based on US Army test data. The high drag configuration assumes all doors and windows are closed and include the following external configurations: ESSS installed. Two 230-gallon tanks mounted on the outboard pylons. Inboard vertical pylons empty.

7 IR jammer and chaff dispenser installed. HIRSS with baffles installed. Main and tail rotor deice and wire strike protection systems installed. Drag considerations will be discussed briefly in this booklet where appropriate. Drag corrections can be made for either a clean configuration aircraft, or for a High Drag configuration aircraft. DA Form 5703-R COMPUTATIONS. Of first concern to the aviator is the question of when a DA Form 5703-R must be completed. According to the ATM, the aviator will determine and have available aircraft PERFORMANCE data necessary to complete the mission. The DA Form 5703- R is used as an aid in organizing this information, or to handle emergency procedures that may arise during the mission. In accordance with the ATM ( ), the DA Form 5703-R must be used during RL progression, annual Aircrew Training Program (ATP) evaluations, and when required during other training and evaluations.

8 Additionally, when the planned or actual gross weight for departure and/or arrival is within 3,000 pounds maximum allowable gross weight OGE or when the planned or actual gross weight is within 3,000 pounds of the maximum 5. allowable gross weight for cruise (See Figure 28 for computation, Cruise Section). To determine if the DA Form 5703-R must be completed, perform the following procedures: Step 1: DEPARTURE - Compare the maximum allowable gross weight for departure from either the -CL tabular data or appropriate -10 HOVER chart with the planned or actual aircraft gross weight. Step 2: CRUISE Compare the maximum allowable gross weight for cruise from the appropriate -10 CRUISE chart with the planned or actual aircraft gross weight. NOTE. If you were PLANNING to takeoff and depart from low-pressure altitudes, yet cruise at very high altitudes, maximum allowable gross weight for cruise could be the determining factor.

9 For instance, looking at the Tabular data for a Clean Configuration, a .90 ATF UH-60A departing at Sea Level and 20 C will have a Maximum allowable gross weight OGE of 21,000 pounds. This means that if the aircraft weighs more than 18,000 pounds, a DA Form 5703-R will be required. But, since this pilot is PLANNING on cruising at Maximum Range airspeed at his planned cruise of 10,000 feet with a forecast temperature of 0 C, the cruise chart reveals that the Maximum allowable gross weight at the cruise conditions is 20,100 pounds. In this example, a DA Form 5703-R is required anytime the planned gross weight is more than 17,100 pounds. NOTE 1: If the dual-engine maximum torque available exceeds a torque limit, use the tabular data equal to the torque limit, or enter the CRUISE chart at the torque limit line.

10 NOTE 2: If the maximum torque available line used on a CRUISE chart is to the right of the -10, Chapter 5 maximum gross weight limitation line, use the maximum gross weight limit line. SIGNIFICANT CHANGE COMPUTATIONS. Step 3: ARRIVAL - Compare the maximum allowable gross weight for arrival from either the -CL tabular data or appropriate -10 HOVER chart with the planned or actual aircraft gross weight. b. When a significant change in the mission's conditions occurs, recompute all affected values. A significant change is defined as any one of the following: 6. (1) An increase of over 10 degrees C, 2,000 feet PA, and/or 1,000. pounds gross weight. (2) An increase or decrease of an ETF by or more. NOTE: An increase or decrease of .03 ETF, normally caused by inaccurate information or a change in aircraft, can significantly enhance or degrade single engine PERFORMANCE under certain conditions.