2. TH-67 WEIGHT AND BALANCE WEIGHT AND BALANCE

3. TH-67 WEIGHT AND BALANCE TERMINAL LEARNING OBJECTIVE: At the completion of this lesson the student will: ACTION: Identify weight and balance requirements. CONDITION: Given a TH-67 Aircraft Systems Student Handout, The TH-67 Operator’s Supplement, DD Form 365-4, basic weight information, and pertinent mission information. STANDARD: Identify the weight and balance requirements of the TH-67 helicopter and receive a “GO” by correctly answering 10 of 13 questions on the associated scoreable unit of criterion referenced test 011-0059. TERMINAL LEARNING OBJECTIVE: At the completion of this lesson the student will: ACTION: Identify weight and balance requirements. CONDITION: Given a TH-67 Aircraft Systems Student Handout, The TH-67 Operator’s Supplement, DD Form 365-4, basic weight information, and pertinent mission information. STANDARD: Identify the weight and balance requirements of the TH-67 helicopter and receive a “GO” by correctly answering 10 of 13 questions on the associated scoreable unit of criterion referenced test 011-0059.

4. TH-67 WEIGHT AND BALANCE ADMINISTRATIVE DATA SAFETY CONSIDERATIONS: CLASSROOM: Use care when operating training aids and devices. JOB PERFORMANCE: Personnel performing operations and procedures shall observe all warnings, cautions and notes that are published in the Operators supplement and abide by all safety regulations. RISK ASSESSMENT: Low. ENVIRONMENTAL CONSIDERATIONS: None. ADMINISTRATIVE DATA SAFETY CONSIDERATIONS: CLASSROOM: Use care when operating training aids and devices. JOB PERFORMANCE: Personnel performing operations and procedures shall observe all warnings, cautions and notes that are published in the Operators supplement and abide by all safety regulations. RISK ASSESSMENT: Low. ENVIRONMENTAL CONSIDERATIONS: None.

5. TH-67 WEIGHT AND BALANCE Enabling Learning Objective (ELO) #1 Upon completion of this enabling learning objective the student will: ACTION: Identify the information contained in AR 95-1 pertaining to the control of weight and balance operations of Army aircraft. CONDITION: From the TH-67 Aircraft Systems Student Handout, the student will be able to provide the solutions. STANDARD: Discuss the information in Chapter 7 pertaining to weight and balance operations of Army aircraft in accordance with (IAW) AR 95-1. Enabling Learning Objective (ELO) #1 Upon completion of this enabling learning objective the student will: ACTION: Identify the information contained in AR 95-1 pertaining to the control of weight and balance operations of Army aircraft. CONDITION: From the TH-67 Aircraft Systems Student Handout, the student will be able to provide the solutions. STANDARD: Discuss the information in Chapter 7 pertaining to weight and balance operations of Army aircraft in accordance with (IAW) AR 95-1.

6. TH-67 WEIGHT AND BALANCE Aviation Flight Regulations defines the responsibilities of various agencies ranging from TRADOC on down to the pilot. It also states the individual requirements for weight and balance technicians, aircraft classifications, weight and balance file management, currency, and aircraft weighing requirements. AR 95-1 AR 95-1, Chapter 7.

7. TH-67 WEIGHT AND BALANCE Command Responsibilities. The TRADOC commander will: Command Responsibilities. The TRADOC commander will: AR 95-1 Train weight and balance technicians in: Train weight and balance technicians in: Weighing aircraft. Weighing aircraft. Computing weight and balance. Computing weight and balance. Maintaining weight and balance records. Maintaining weight and balance records. Train Army aviators and flight engineers in computing weight and balance. Train Army aviators and flight engineers in computing weight and balance. Train personnel to provide weight and balance services at support facilities. Train personnel to provide weight and balance services at support facilities. Train weight and balance technicians in: Train weight and balance technicians in: Weighing aircraft. Weighing aircraft. Computing weight and balance. Computing weight and balance. Maintaining weight and balance records. Maintaining weight and balance records. Train Army aviators and flight engineers in computing weight and balance. Train Army aviators and flight engineers in computing weight and balance. Train personnel to provide weight and balance services at support facilities. Train personnel to provide weight and balance services at support facilities.

8. TH-67 WEIGHT AND BALANCE The ATCOM (AMCOM) commander coordinates aviation requirements with other agencies, assists in policy development, prepares technical data, procures data, and makes engineering services available to assist in solving weight and balance problems. The ATCOM (AMCOM) commander coordinates aviation requirements with other agencies, assists in policy development, prepares technical data, procures data, and makes engineering services available to assist in solving weight and balance problems. AR 95-1 Command Responsibilities.

9. TH-67 WEIGHT AND BALANCE Installation and Unit commanders develop command directives and ensure effective application of weight and balance policies and procedures. Commanders also appoint in writing weight and balance technicians. Installation and Unit commanders develop command directives and ensure effective application of weight and balance policies and procedures. Commanders also appoint in writing weight and balance technicians. AR 95-1 Command Responsibilities.

10. TH-67 WEIGHT AND BALANCE Pilots-in-Command will ensure: The accuracy of computations on the DD Form 365-4. The accuracy of computations on the DD Form 365-4. A completed DD Form 365-4 is aboard the aircraft and that the center-of-gravity will remain within allowable limits for the entire flight. A completed DD Form 365-4 is aboard the aircraft and that the center-of-gravity will remain within allowable limits for the entire flight. Actual loading being verified must clearly be within the extremes of the loading shown on the DD Forms 365-4 used for verification. Actual loading being verified must clearly be within the extremes of the loading shown on the DD Forms 365-4 used for verification. NOTE: Several DD Forms 365-4 completed for other typical loading also may be used to satisfy this requirement. Pilots-in-Command will ensure: The accuracy of computations on the DD Form 365-4. The accuracy of computations on the DD Form 365-4. A completed DD Form 365-4 is aboard the aircraft and that the center-of-gravity will remain within allowable limits for the entire flight. A completed DD Form 365-4 is aboard the aircraft and that the center-of-gravity will remain within allowable limits for the entire flight. Actual loading being verified must clearly be within the extremes of the loading shown on the DD Forms 365-4 used for verification. Actual loading being verified must clearly be within the extremes of the loading shown on the DD Forms 365-4 used for verification. NOTE: Several DD Forms 365-4 completed for other typical loading also may be used to satisfy this requirement. AR 95-1 Command Responsibilities.

11. TH-67 WEIGHT AND BALANCE Paragraph 7-2. Technician qualification requirements, commander’s authorization to delegate, and the technicians duties and responsibilities. Paragraph 7-2. Technician qualification requirements, commander’s authorization to delegate, and the technicians duties and responsibilities. AR 95-1 AR 95-1, Chapter 7.

12. TH-67 WEIGHT AND BALANCE Paragraph 7-3. Classifications defined. Class 1 aircraft are those aircraft whose weight or center-of-gravity limits can sometimes be exceeded by loading arrangements normally used in tactical operations. Therefore, limited loading control is needed. Class 1 aircraft are those aircraft whose weight or center-of-gravity limits can sometimes be exceeded by loading arrangements normally used in tactical operations. Therefore, limited loading control is needed. Paragraph 7-3. Classifications defined. Class 1 aircraft are those aircraft whose weight or center-of-gravity limits can sometimes be exceeded by loading arrangements normally used in tactical operations. Therefore, limited loading control is needed. Class 1 aircraft are those aircraft whose weight or center-of-gravity limits can sometimes be exceeded by loading arrangements normally used in tactical operations. Therefore, limited loading control is needed. AR 95-1 AR 95-1, Chapter 7.

13. TH-67 WEIGHT AND BALANCE Class 2 aircraft are those aircraft whose weight or center-of-gravity limits can readily be exceeded by loading arrangements normally used in tactical operations or those aircraft designed primarily for troops and other passengers. Therefore, a high degree of loading control is needed. Class 2 aircraft are those aircraft whose weight or center-of-gravity limits can readily be exceeded by loading arrangements normally used in tactical operations or those aircraft designed primarily for troops and other passengers. Therefore, a high degree of loading control is needed. AR 95-1 AR 95-1, Chapter 7.

14. TH-67 WEIGHT AND BALANCE Paragraph 7-4. Aircraft Weight and Balance File. The file folder will have the aircraft designation and serial number noted on the folder. The weight and balance file folder may be removed from the aircraft provided the following conditions are met: Paragraph 7-4. Aircraft Weight and Balance File. The file folder will have the aircraft designation and serial number noted on the folder. The weight and balance file folder may be removed from the aircraft provided the following conditions are met: AR 95-1 AR 95-1, Chapter 7. The file is readily available for update with equipment changes. The file is readily available for update with equipment changes. Duplicate copies of all DD Forms 365-4 are carried aboard the aircraft. Duplicate copies of all DD Forms 365-4 are carried aboard the aircraft. Local procedures are established to ensure forms are updated and remain valid. Local procedures are established to ensure forms are updated and remain valid. The file is readily available for update with equipment changes. The file is readily available for update with equipment changes. Duplicate copies of all DD Forms 365-4 are carried aboard the aircraft. Duplicate copies of all DD Forms 365-4 are carried aboard the aircraft. Local procedures are established to ensure forms are updated and remain valid. Local procedures are established to ensure forms are updated and remain valid.

15. TH-67 WEIGHT AND BALANCE File content and reference instructions. DD Form 365 Record of Weight and Balance Personnel. DD Form 365 Record of Weight and Balance Personnel. File content and reference instructions. DD Form 365 Record of Weight and Balance Personnel. DD Form 365 Record of Weight and Balance Personnel. AR 95-1 AR 95-1, Chapter 7.

16. DD Form 365 Record of Weight and Balance Personnel SFC

17. TH-67 WEIGHT AND BALANCE DD Form 365-1 Chart A -- Basic Checklist Record. AR 95-1 AR 95-1, Chapter 7.

19. TH-67 WEIGHT AND BALANCE DD Form 365-2 Chart B -- Aircraft Weighing Record. AR 95-1 AR 95-1, Chapter 7.

22. TH-67 WEIGHT AND BALANCE DD Form 365-3 Chart C -- Basic Weight and Balance Record. AR 95-1 AR 95-1, Chapter 7.

23. 100

24. TH-67 WEIGHT AND BALANCE Chart E Loading Data and Special weighing Instructions. (Unless a Chart E is published in the maintenance manual). AR 95-1 AR 95-1, Chapter 7.

25. Figure 6-1 Fuselage Stations

26. TH-67 WEIGHT AND BALANCE DD Form 365-4 Weight and Balance Clearance Form F. DD Form 365-4 Weight and Balance Clearance Form F. AR 95-1 AR 95-1, Chapter 7.

28. TH-67 WEIGHT AND BALANCE Electronic computer data sheets may be used in lieu of any of the DD Form 365 series when information is identical to that required on the DD Form 365 series. AR 95-1 AR 95-1, Chapter 7.

29. TH-67 WEIGHT AND BALANCE Paragraph 7-5. Removal, Addition, or Relocation of Aircraft Equipment. AR 95-1 AR 95-1, Chapter 7. NOTE: When aircraft equipment that is part of the basic weight is added to, removed from, or relocated within the aircraft because of maintenance or specific mission requirements, flight will not be accomplished unless the weight and balance change is documented by one of the following methods:

30. TH-67 WEIGHT AND BALANCE The additions, removals, or relocations are treated as a permanent change by making entries on DD Form 365-3 Chart C and establishes a new basic weight. The additions, removals, or relocations are treated as a permanent change by making entries on DD Form 365-3 Chart C and establishes a new basic weight. AR 95-1 AR 95-1, Chapter 7. (Weight and Balance Technicians responsibility) (Weight and Balance Technicians responsibility)

31. TH-67 WEIGHT AND BALANCE If the changes are temporary (not to exceed 90 days) make entries on DA Form 2408-13 series and DA Form 2408-14. If the changes are temporary (not to exceed 90 days) make entries on DA Form 2408-13 series and DA Form 2408-14. (Pilot in Command’s Responsibility) NOTE: If the change is not returned to its original condition within 90 days the DD Form 365-3 Chart C will be updated to reflect the temporary change. If the changes are temporary (not to exceed 90 days) make entries on DA Form 2408-13 series and DA Form 2408-14. If the changes are temporary (not to exceed 90 days) make entries on DA Form 2408-13 series and DA Form 2408-14. (Pilot in Command’s Responsibility) NOTE: If the change is not returned to its original condition within 90 days the DD Form 365-3 Chart C will be updated to reflect the temporary change. AR 95-1 AR 95-1, Chapter 7.

32. TH-67 WEIGHT AND BALANCE Paragraph 7-6. Reviewing Weight and Balance File. AR 95-1 AR 95-1, Chapter 7. All DD Forms 365-4 in the aircraft file folder and all duplicates in the aircraft and operations area (local policy) will be checked for accuracy at least every 90 days (365 days local policy). New forms must be prepared if changes are required. If no changes are required the DD Form 365-4 will be re-dated and initialed in the block to certify their currency. All DD Forms 365-4 in the aircraft file folder and all duplicates in the aircraft and operations area (local policy) will be checked for accuracy at least every 90 days (365 days local policy). New forms must be prepared if changes are required. If no changes are required the DD Form 365-4 will be re-dated and initialed in the block to certify their currency.

33. TH-67 WEIGHT AND BALANCE Paragraph 7-6. Reviewing Weight and Balance File. AR 95-1 AR 95-1, Chapter 7. All weight and balance records will be review every 12 months. The last day of the month is the final day for completing the review. All weight and balance records will be review every 12 months. The last day of the month is the final day for completing the review.

34. TH-67 WEIGHT AND BALANCE Paragraph 7-7. Aircraft Weighing. Each aircraft will be weighed when: Paragraph 7-7. Aircraft Weighing. Each aircraft will be weighed when: AR 95-1 AR 95-1, Chapter 7. Overhaul or major airframe repairs are accomplished. Overhaul or major airframe repairs are accomplished. Any modifications or component replacements (including painting) have been made for which the weight and center-of-gravity cannot be accurately computed. Any modifications or component replacements (including painting) have been made for which the weight and center-of-gravity cannot be accurately computed. Overhaul or major airframe repairs are accomplished. Overhaul or major airframe repairs are accomplished. Any modifications or component replacements (including painting) have been made for which the weight and center-of-gravity cannot be accurately computed. Any modifications or component replacements (including painting) have been made for which the weight and center-of-gravity cannot be accurately computed.

35. TH-67 WEIGHT AND BALANCE Weight and center-of-gravity data records are suspected to be in error. Weight and center-of-gravity data records are suspected to be in error. The period since the previous weighing reaches 24 months for a Class 2 aircraft or 36 months for a class 1 aircraft. The period since the previous weighing reaches 24 months for a Class 2 aircraft or 36 months for a class 1 aircraft. Weight and center-of-gravity data records are suspected to be in error. Weight and center-of-gravity data records are suspected to be in error. The period since the previous weighing reaches 24 months for a Class 2 aircraft or 36 months for a class 1 aircraft. The period since the previous weighing reaches 24 months for a Class 2 aircraft or 36 months for a class 1 aircraft. AR 95-1 AR 95-1, Chapter 7. Paragraph 7-7. Aircraft Weighing. (continued) Each aircraft will be weighed when: Paragraph 7-7. Aircraft Weighing. (continued) Each aircraft will be weighed when:

36. TH-67 WEIGHT AND BALANCE The weight records supplied with a new aircraft may be used in lieu of initial weighing. The weight records supplied with a new aircraft may be used in lieu of initial weighing. If these weighing criteria are not met, the aircraft status will change to red “X” until they are met. If these weighing criteria are not met, the aircraft status will change to red “X” until they are met. Any maintenance facility providing weighing service will ensure that all aircraft weighing equipment is tested and certified for accuracy. Any maintenance facility providing weighing service will ensure that all aircraft weighing equipment is tested and certified for accuracy. The weight records supplied with a new aircraft may be used in lieu of initial weighing. The weight records supplied with a new aircraft may be used in lieu of initial weighing. If these weighing criteria are not met, the aircraft status will change to red “X” until they are met. If these weighing criteria are not met, the aircraft status will change to red “X” until they are met. Any maintenance facility providing weighing service will ensure that all aircraft weighing equipment is tested and certified for accuracy. Any maintenance facility providing weighing service will ensure that all aircraft weighing equipment is tested and certified for accuracy. AR 95-1 AR 95-1, Chapter 7. Paragraph 7-7. Aircraft Weighing. (continued) Each aircraft will be weighed when: Paragraph 7-7. Aircraft Weighing. (continued) Each aircraft will be weighed when:

37. TH-67 WEIGHT AND BALANCE CHECK ON LEARNING: Question: What is DD Form 365-3 Chart C used for? Answer: DD Form 365-3 Chart C is used to record any permanent changes in the aircraft’s basic weight or center-of-gravity when the aircraft is modified. Question: Define temporary? Answer: Temporary is defined as 90 days or less. CHECK ON LEARNING: Question: What is DD Form 365-3 Chart C used for? Answer: DD Form 365-3 Chart C is used to record any permanent changes in the aircraft’s basic weight or center-of-gravity when the aircraft is modified. Question: Define temporary? Answer: Temporary is defined as 90 days or less.

38. TH-67 WEIGHT AND BALANCE Enabling Learning Objective (ELO) #2 Upon completion of this enabling learning objective the student will: ACTION: Identify the information contained in TM 55- 1500-342-23 pertaining to the weight terms. CONDITION: From the TH-67 Aircraft Systems Student Handout, the student will be able to provide the solutions. STANDARD: Discuss the weight terms in accordance with (IAW) TM 55-1500-342-23. Enabling Learning Objective (ELO) #2 Upon completion of this enabling learning objective the student will: ACTION: Identify the information contained in TM 55- 1500-342-23 pertaining to the weight terms. CONDITION: From the TH-67 Aircraft Systems Student Handout, the student will be able to provide the solutions. STANDARD: Discuss the weight terms in accordance with (IAW) TM 55-1500-342-23.

39. TH-67 WEIGHT AND BALANCE TM 55-1500-342-23. Army Aviation Maintenance Engineering Manual - Weight and Balance. TM 55-1500-342-23 This is the technical manual on weight and balance. It defines the terms associated with performing weight and balance operations and also gives instructions on how to perform the necessary computations used to arrive at takeoff and landing gross weights. In addition, the purposes for the weight and balance forms are identified and the weight and balance files are thoroughly explained. For more complex aircraft, the load adjuster kit is also explained and instructions for its use are provided.

40. TH-67 WEIGHT AND BALANCE Weight Definitions. TM 55-1500-342-23 Basic Weight. Basic weight of an aircraft is that weight which includes all filled hydraulic and oil systems, trapped and unusable fuel, and fixed equipment. Basic Weight. Basic weight of an aircraft is that weight which includes all filled hydraulic and oil systems, trapped and unusable fuel, and fixed equipment. NOTE: The basic weight varies with structural modifications and changes of fixed aircraft equipment. Basic Weight. Basic weight of an aircraft is that weight which includes all filled hydraulic and oil systems, trapped and unusable fuel, and fixed equipment. Basic Weight. Basic weight of an aircraft is that weight which includes all filled hydraulic and oil systems, trapped and unusable fuel, and fixed equipment. NOTE: The basic weight varies with structural modifications and changes of fixed aircraft equipment.

41. TH-67 WEIGHT AND BALANCE Operating Weight. Operating weight includes the basic weight plus aircrew, the aircrew’s baggage, steward’s equipment, and emergency and other equipment that may be required. Operating Weight. Operating weight includes the basic weight plus aircrew, the aircrew’s baggage, steward’s equipment, and emergency and other equipment that may be required. Total Aircraft Weight. Total Aircraft weight is operating weight plus the weight of takeoff fuel and the weight of water injection fluid, if applicable. Total Aircraft Weight. Total Aircraft weight is operating weight plus the weight of takeoff fuel and the weight of water injection fluid, if applicable. Operating Weight. Operating weight includes the basic weight plus aircrew, the aircrew’s baggage, steward’s equipment, and emergency and other equipment that may be required. Operating Weight. Operating weight includes the basic weight plus aircrew, the aircrew’s baggage, steward’s equipment, and emergency and other equipment that may be required. Total Aircraft Weight. Total Aircraft weight is operating weight plus the weight of takeoff fuel and the weight of water injection fluid, if applicable. Total Aircraft Weight. Total Aircraft weight is operating weight plus the weight of takeoff fuel and the weight of water injection fluid, if applicable. TM 55-1500-342-23 Weight Definitions.

42. TH-67 WEIGHT AND BALANCE Zero fuel Weight. Operating weight (ref. 9) plus payload (ref. 13). Zero fuel Weight. Operating weight (ref. 9) plus payload (ref. 13). NOTE: Another way of expressing zero fuel weight is: Takeoff weight (ref. 16) minus takeoff fuel weight (ref. 10). Takeoff condition (Gross Weight). Takeoff gross weight includes the operating weight plus fuel, cargo, passengers, ammunitions, bombs, auxiliary fuel tanks, etc. Takeoff condition (Gross Weight). Takeoff gross weight includes the operating weight plus fuel, cargo, passengers, ammunitions, bombs, auxiliary fuel tanks, etc. Zero fuel Weight. Operating weight (ref. 9) plus payload (ref. 13). Zero fuel Weight. Operating weight (ref. 9) plus payload (ref. 13). NOTE: Another way of expressing zero fuel weight is: Takeoff weight (ref. 16) minus takeoff fuel weight (ref. 10). Takeoff condition (Gross Weight). Takeoff gross weight includes the operating weight plus fuel, cargo, passengers, ammunitions, bombs, auxiliary fuel tanks, etc. Takeoff condition (Gross Weight). Takeoff gross weight includes the operating weight plus fuel, cargo, passengers, ammunitions, bombs, auxiliary fuel tanks, etc. TM 55-1500-342-23 Weight Definitions.

43. TH-67 WEIGHT AND BALANCE Landing Condition (Gross Weight). Landing condition is the takeoff gross weight minus items expended during flight. Landing Condition (Gross Weight). Landing condition is the takeoff gross weight minus items expended during flight. TM 55-1500-342-23 Weight Definitions.

44. TH-67 WEIGHT AND BALANCE Weight versus Aircraft Performance. An aircraft is designed for specific weight limitations which cannot be exceeded without compromising safety. Overloading an aircraft may cause structural failure. An increase in gross weight will have the following effects on aircraft performance: Weight versus Aircraft Performance. An aircraft is designed for specific weight limitations which cannot be exceeded without compromising safety. Overloading an aircraft may cause structural failure. An increase in gross weight will have the following effects on aircraft performance: TM 55-1500-342-23 Increase takeoff distance. Increase takeoff distance. Reduce hover performance. Reduce hover performance. Reduce rate of climb. Reduce rate of climb. Reduce cruising speed. Reduce cruising speed. Increase takeoff distance. Increase takeoff distance. Reduce hover performance. Reduce hover performance. Reduce rate of climb. Reduce rate of climb. Reduce cruising speed. Reduce cruising speed.

45. TH-67 WEIGHT AND BALANCE Reduce stalling speed. Reduce stalling speed. Reduce maneuverability. Reduce maneuverability. Reduce hover ceiling. Reduce hover ceiling. Reduce range. Reduce range. Increase landing distances. Increase landing distances. Instability. Instability. Reduce stalling speed. Reduce stalling speed. Reduce maneuverability. Reduce maneuverability. Reduce hover ceiling. Reduce hover ceiling. Reduce range. Reduce range. Increase landing distances. Increase landing distances. Instability. Instability. TM 55-1500-342-23 Weight versus Aircraft Performance. (continued)

46. TH-67 WEIGHT AND BALANCE CHECK ON LEARNING: Question: What is the definition for basic weight? Answer: Basic weight is that weight that includes all filled hydraulic and oil systems, trapped and unusable fuel, and all fixed equipment (this includes the first aid kit and fire extinguisher). Question: What is the definition of Zero Fuel Weight? Answer: Zero fuel weight is Operating Weight (ref 9) plus Distribution of Allowable Load, Payload, (ref 13). CHECK ON LEARNING: Question: What is the definition for basic weight? Answer: Basic weight is that weight that includes all filled hydraulic and oil systems, trapped and unusable fuel, and all fixed equipment (this includes the first aid kit and fire extinguisher). Question: What is the definition of Zero Fuel Weight? Answer: Zero fuel weight is Operating Weight (ref 9) plus Distribution of Allowable Load, Payload, (ref 13).

47. TH-67 WEIGHT AND BALANCE Enabling Learning Objective (ELO) #3 Upon completion of this enabling learning objective the student will: ACTION: Identify the information contained in TM 55- 1500-342-23 pertaining to balance definitions. CONDITION: From the TH-67 Aircraft Systems Student Handout, the student will be able to provide the solutions. STANDARD: Discuss the balance terms in accordance with (IAW) TM 55-1500-342-23. Enabling Learning Objective (ELO) #3 Upon completion of this enabling learning objective the student will: ACTION: Identify the information contained in TM 55- 1500-342-23 pertaining to balance definitions. CONDITION: From the TH-67 Aircraft Systems Student Handout, the student will be able to provide the solutions. STANDARD: Discuss the balance terms in accordance with (IAW) TM 55-1500-342-23.

48. TH-67 WEIGHT AND BALANCE Balance Definitions. TM 55-1500-342-23 Gross Weight Moment. Gross weight moment is the sum of moments of all items in the gross weight condition. The gross weight moment is the product of gross weight times the arm (W x A = Moment). The distance used in calculating a moment is referred to as the arm or moment arm. The result of W x A is in inch - pounds. Gross weight moment is the sum of moments of all items in the gross weight condition. The gross weight moment is the product of gross weight times the arm (W x A = Moment). The distance used in calculating a moment is referred to as the arm or moment arm. The result of W x A is in inch - pounds.

49. TH-67 WEIGHT AND BALANCE Basic Arm. Basic arm is the distance from the reference datum to the center-of-gravity (CG) of an item placed in the aircraft. It is obtained by dividing the basic moment by the basic weight. Basic Arm. Basic arm is the distance from the reference datum to the center-of-gravity (CG) of an item placed in the aircraft. It is obtained by dividing the basic moment by the basic weight. TM 55-1500-342-23 Balance Definitions.

50. TH-67 WEIGHT AND BALANCE Reference Datum. Reference datum is an imaginary plane perpendicular to the longitudinal axis of the aircraft and is usually located at or near the nose of the aircraft to eliminate arms with a minus value. In the TH-67, the reference datum line is located 55.1 inches forward of the forward jack point centerline. This will place the reference datum at the base of the pitot tube. This will be fuselage station “O”. Reference Datum. Reference datum is an imaginary plane perpendicular to the longitudinal axis of the aircraft and is usually located at or near the nose of the aircraft to eliminate arms with a minus value. In the TH-67, the reference datum line is located 55.1 inches forward of the forward jack point centerline. This will place the reference datum at the base of the pitot tube. This will be fuselage station “O”. NOTE: If a negative arm is encountered, the corresponding moment will be negative. Reference Datum. Reference datum is an imaginary plane perpendicular to the longitudinal axis of the aircraft and is usually located at or near the nose of the aircraft to eliminate arms with a minus value. In the TH-67, the reference datum line is located 55.1 inches forward of the forward jack point centerline. This will place the reference datum at the base of the pitot tube. This will be fuselage station “O”. Reference Datum. Reference datum is an imaginary plane perpendicular to the longitudinal axis of the aircraft and is usually located at or near the nose of the aircraft to eliminate arms with a minus value. In the TH-67, the reference datum line is located 55.1 inches forward of the forward jack point centerline. This will place the reference datum at the base of the pitot tube. This will be fuselage station “O”. NOTE: If a negative arm is encountered, the corresponding moment will be negative. TM 55-1500-342-23 Balance Definitions.

51. TH-67 WEIGHT AND BALANCE Center-of-Gravity. Center-of-gravity is the point at which, if lifted, the helicopter would be balanced. It can be found by dividing the total moments by the total gross weight. Center-of-Gravity. Center-of-gravity is the point at which, if lifted, the helicopter would be balanced. It can be found by dividing the total moments by the total gross weight. TM 55-1500-342-23 Balance Definitions. EXAMPLE: CG = Total Moments Total Weight

52. TH-67 WEIGHT AND BALANCE CHECK ON LEARNING: Question: What is the formula for moment? Answer: The formula for moment is weight times the arm equals the moment (WxA=M) divided by the index. Question: What is the definition of Reference Datum? Answer: Reference Datum is an imaginary plane perpendicular to the longitudinal axis at the nose of the aircraft from which all measurements of arm are taken. CHECK ON LEARNING: Question: What is the formula for moment? Answer: The formula for moment is weight times the arm equals the moment (WxA=M) divided by the index. Question: What is the definition of Reference Datum? Answer: Reference Datum is an imaginary plane perpendicular to the longitudinal axis at the nose of the aircraft from which all measurements of arm are taken.

53. TH-67 WEIGHT AND BALANCE Enabling Learning Objective (ELO) #4 Upon completion of this enabling learning objective the student will: ACTION: Identify the information contained in the TH- 67 Operator’s Supplement pertaining to weight and balance computations. CONDITION: From the TH-67 Aircraft Systems Student Handout, the student will be able to provide the solutions. STANDARD: Discuss the information in chapters five and six pertaining to weight and balance in accordance with (IAW) the TH-67 Operator’s Supplement. Enabling Learning Objective (ELO) #4 Upon completion of this enabling learning objective the student will: ACTION: Identify the information contained in the TH- 67 Operator’s Supplement pertaining to weight and balance computations. CONDITION: From the TH-67 Aircraft Systems Student Handout, the student will be able to provide the solutions. STANDARD: Discuss the information in chapters five and six pertaining to weight and balance in accordance with (IAW) the TH-67 Operator’s Supplement.

54. TH-67 WEIGHT AND BALANCE Limitations Chapter 5. TH-67 Operator’s Supplement Maximum allowable gross weight for hover/flight is 3,350 pounds. Maximum allowable gross weight for hover/flight is 3,350 pounds. VFR CG limits are from stations 106.0 114.2; however, the aft limits are variable depending on aircraft gross weight. Refer to the Operator’s Supplement Figure 6-4. VFR CG limits are from stations 106.0 114.2; however, the aft limits are variable depending on aircraft gross weight. Refer to the Operator’s Supplement Figure 6-4. IFR CG limits are from station 106.0 to 110.0 at 2,400 to 3,350 pounds gross weight. Refer to the Operator’s Supplement Figure 6-4. IFR CG limits are from station 106.0 to 110.0 at 2,400 to 3,350 pounds gross weight. Refer to the Operator’s Supplement Figure 6-4. Maximum allowable gross weight for hover/flight is 3,350 pounds. Maximum allowable gross weight for hover/flight is 3,350 pounds. VFR CG limits are from stations 106.0 114.2; however, the aft limits are variable depending on aircraft gross weight. Refer to the Operator’s Supplement Figure 6-4. VFR CG limits are from stations 106.0 114.2; however, the aft limits are variable depending on aircraft gross weight. Refer to the Operator’s Supplement Figure 6-4. IFR CG limits are from station 106.0 to 110.0 at 2,400 to 3,350 pounds gross weight. Refer to the Operator’s Supplement Figure 6-4. IFR CG limits are from station 106.0 to 110.0 at 2,400 to 3,350 pounds gross weight. Refer to the Operator’s Supplement Figure 6-4.

55. TH-67 WEIGHT AND BALANCE Minimum front seat weight, single pilot, is 170 pounds. Minimum front seat weight, single pilot, is 170 pounds. Lateral CG limits are 3.0 inches left of aircraft centerline and 4.0 inches right of centerline. Refer to the Operator’s Supplement Figure 6-3. Lateral CG limits are 3.0 inches left of aircraft centerline and 4.0 inches right of centerline. Refer to the Operator’s Supplement Figure 6-3. Minimum front seat weight, single pilot, is 170 pounds. Minimum front seat weight, single pilot, is 170 pounds. Lateral CG limits are 3.0 inches left of aircraft centerline and 4.0 inches right of centerline. Refer to the Operator’s Supplement Figure 6-3. Lateral CG limits are 3.0 inches left of aircraft centerline and 4.0 inches right of centerline. Refer to the Operator’s Supplement Figure 6-3. TH-67 Operator’s Supplement Limitations Chapter 5.

56. TH-67 WEIGHT AND BALANCE Chapter six in this book is devoted to weight and balance data. The aircraft classification is stated in this chapter. Charts, figures, and graphs are provided to be used in computing weight and balance data. This chapter is the tool used most often by you, the operator. Paragraph 6-2. This is a class 2 aircraft. Paragraph 6-2. This is a class 2 aircraft. Chapter six in this book is devoted to weight and balance data. The aircraft classification is stated in this chapter. Charts, figures, and graphs are provided to be used in computing weight and balance data. This chapter is the tool used most often by you, the operator. Paragraph 6-2. This is a class 2 aircraft. Paragraph 6-2. This is a class 2 aircraft. TH-67 Operator’s Supplement Chapter 6

57. TH-67 WEIGHT AND BALANCE Figure 6-1 Fuselage Stations. This figure illustrates the various fuselage stations and reference datum lines unique to the TH-67 aircraft. This diagram is used primarily by maintenance personnel to accurately locate the position that equipment is added to, removed from, or relocated to, whenever the basic configuration is altered. The pilot uses this chart to verify the data entered on DA Forms 2408-13-1 and 2408-14-1 is correct. Figure 6-1 Fuselage Stations. This figure illustrates the various fuselage stations and reference datum lines unique to the TH-67 aircraft. This diagram is used primarily by maintenance personnel to accurately locate the position that equipment is added to, removed from, or relocated to, whenever the basic configuration is altered. The pilot uses this chart to verify the data entered on DA Forms 2408-13-1 and 2408-14-1 is correct. TH-67 Operator’s Supplement Chapter 6

58. Figure 6-1 Fuselage Stations

59. TH-67 WEIGHT AND BALANCE Figure 6-3 Lateral vs Longitudinal Center-of-Gravity. This figure depicts 4.0 inches of right cyclic travel and only 3.0 inches of left cyclic travel. The 1.25 degree transmission tilt to the left to help compensate for translating tendency, accounts for the cyclic displacement at a hover. Figure 6-3 Lateral vs Longitudinal Center-of-Gravity. This figure depicts 4.0 inches of right cyclic travel and only 3.0 inches of left cyclic travel. The 1.25 degree transmission tilt to the left to help compensate for translating tendency, accounts for the cyclic displacement at a hover. TH-67 Operator’s Supplement Chapter 6

61. TH-67 WEIGHT AND BALANCE Figure 6-4 Center-of -Gravity Limits Chart. This figure is used to determine the authorized longitudinal limits, at critical gross weights, to verify full longitudinal cyclic control is available. Figure 6-4 Center-of -Gravity Limits Chart. This figure is used to determine the authorized longitudinal limits, at critical gross weights, to verify full longitudinal cyclic control is available. TH-67 Operator’s Supplement Chapter 6

62. Figure 6-4 VFR Center of Gravity Limits Chart

63. TH-67 WEIGHT AND BALANCE Paragraph 6-9 Fuel Loading Tables. These charts are used to accurately determine the weight, arm, and moment of various quantities of primary and alternate fuel. Should the exact quantity not be listed on the chart, it may be necessary to interpolate to arrive at the exact value. Paragraph 6-9 Fuel Loading Tables. These charts are used to accurately determine the weight, arm, and moment of various quantities of primary and alternate fuel. Should the exact quantity not be listed on the chart, it may be necessary to interpolate to arrive at the exact value. TH-67 Operator’s Supplement Chapter 6

64. Fuel Loading Table Page 6-7

65. Fuel Loading Table Page 6-8

66. TH-67 WEIGHT AND BALANCE Paragraph 6-11 Cabin and Baggage Compartment Table of Moments. TH-67 Operator’s Supplement Chapter 6 This table is used to determine the moments of various items the Pilot-in-Command places on board the aircraft. These items include the crew (pilot, copilot, and observer), personal baggage, cargo, and passengers. Actual weight will result in more accurate data. Consequently, if the values you are searching for are not listed on the table, you may need to interpolate to arrive at exact values. This table is used to determine the moments of various items the Pilot-in-Command places on board the aircraft. These items include the crew (pilot, copilot, and observer), personal baggage, cargo, and passengers. Actual weight will result in more accurate data. Consequently, if the values you are searching for are not listed on the table, you may need to interpolate to arrive at exact values.

67. Cabin and Baggage Compartment Table of Moments Page 6-9

68. Cabin and Baggage Compartment Table of Moments Page 6-10

69. TH-67 WEIGHT AND BALANCE CHECK ON LEARNING: Question: Which chapter in the TH-67 Operator’s Supplement is devoted to Weight and Balance? Answer: Chapter six in the TH-67 Operator’s supplement is devoted to Weight and Balance. Question: What class is the TH-67 Aircraft? Answer: The TH-67 is a class two aircraft. CHECK ON LEARNING: Question: Which chapter in the TH-67 Operator’s Supplement is devoted to Weight and Balance? Answer: Chapter six in the TH-67 Operator’s supplement is devoted to Weight and Balance. Question: What class is the TH-67 Aircraft? Answer: The TH-67 is a class two aircraft.

70. TH-67 WEIGHT AND BALANCE Enabling Learning Objective (ELO) #5 Upon completion of this enabling learning objective the student will: ACTION: Apply the weight and balance instructions correctly in preparing a DD Form 365-4 during a practical exercise. CONDITION: From the TH-67 Aircraft Systems Student Handout, the student will be able to provide the solutions. STANDARD: Apply the information discussed in the previous ELO’s in completing the practical exercise in accordance with (IAW) TM 55-1500-342-23. Enabling Learning Objective (ELO) #5 Upon completion of this enabling learning objective the student will: ACTION: Apply the weight and balance instructions correctly in preparing a DD Form 365-4 during a practical exercise. CONDITION: From the TH-67 Aircraft Systems Student Handout, the student will be able to provide the solutions. STANDARD: Apply the information discussed in the previous ELO’s in completing the practical exercise in accordance with (IAW) TM 55-1500-342-23.

71. TH-67 WEIGHT AND BALANCE PRACTICAL EXERCISE #1

72. TH-67 WEIGHT AND BALANCE STEP 1--Insert the identifying information at the top of the form on the TRANSPORT side.

73. FK 489927 100

74. TH-67 WEIGHT AND BALANCE STEP 2-- Reference 1--Enter the basic weight and moment. Obtain this information from the last entry on DD Form 365-3 Chart C. Also, record the INDEX obtained from the top of the moment columns on Chart C. NOTE: If you are completing this form because your mission does not match any of the typical loads on file, you may use the information in reference 1 from the forms in the back of your aircraft’s logbook (or flight planning area) provided they are still current. STEP 2-- Reference 1--Enter the basic weight and moment. Obtain this information from the last entry on DD Form 365-3 Chart C. Also, record the INDEX obtained from the top of the moment columns on Chart C. NOTE: If you are completing this form because your mission does not match any of the typical loads on file, you may use the information in reference 1 from the forms in the back of your aircraft’s logbook (or flight planning area) provided they are still current.

75. FK 489927 22 0 0 239

76. TH-67 WEIGHT AND BALANCE STEP 3-- Reference 2--Leave blank or include “Part of Basic Weight”. STEP 3-- Reference 2--Leave blank or include “Part of Basic Weight”.

77. FK 489927 PART OF BASIC WEIGHT 2 2 0 02329

78. TH-67 WEIGHT AND BALANCE STEP 4-- Reference 3--Enter the number of crewmembers in the item number and record their combined weight in the weight columns and their combined moments in the moments column. Weight X Arm = Moment divided by the index. Use Table 6-11 STEP 4-- Reference 3--Enter the number of crewmembers in the item number and record their combined weight in the weight columns and their combined moments in the moments column. Weight X Arm = Moment divided by the index. Use Table 6-11

80. FK 489927 PART OF BASIC WEIGHT 2 2 0 0 2329 3 605174

81. TH-67 WEIGHT AND BALANCE STEP 5-- Reference 4--Enter the total weight and moment of the crew’s personal equipment that is placed in the baggage compartment. Use Table 6-11. Remember to divide the moment by the index. STEP 5-- Reference 4--Enter the total weight and moment of the crew’s personal equipment that is placed in the baggage compartment. Use Table 6-11. Remember to divide the moment by the index.

83. FK 489927 PART OF BASIC WEIGHT 2 2 0 0 2329 3 605174 50 74

84. TH-67 WEIGHT AND BALANCE STEP 6-- Reference 5--Normally not applicable. STEP 6-- Reference 5--Normally not applicable.

85. TH-67 WEIGHT AND BALANCE STEP 7-- Reference 6--Normally not applicable. The TH-67’s emergency equipment (first aide kit and fire extinguisher) is part of the basic weight. STEP 7-- Reference 6--Normally not applicable. The TH-67’s emergency equipment (first aide kit and fire extinguisher) is part of the basic weight.

86. TH-67 WEIGHT AND BALANCE STEP 8-- Reference 7--Normally not applicable. STEP 8-- Reference 7--Normally not applicable.

87. TH-67 WEIGHT AND BALANCE STEP 9-- Reference 8--Normally not used. STEP 9-- Reference 8--Normally not used.

88. TH-67 WEIGHT AND BALANCE STEP 10-- Reference 9--Total the weight columns and moment columns (references 1 thru 8) and record the total in their respective columns. STEP 10-- Reference 9--Total the weight columns and moment columns (references 1 thru 8) and record the total in their respective columns.

89. FK 489927 PART OF BASIC WEIGHT 2 2 0 0 2329 3 605174 50 74 26752874

90. TH-67 WEIGHT AND BALANCE STEP 11-- Reference 10--Record the quantity of fuel in gallons, fuel weight and fuel moment in their respective columns. Use Fuel Loading Tables Paragraph 6-9. Remember to divide the moment by the index. STEP 11-- Reference 10--Record the quantity of fuel in gallons, fuel weight and fuel moment in their respective columns. Use Fuel Loading Tables Paragraph 6-9. Remember to divide the moment by the index.

92. FK 489927 PART OF BASIC WEIGHT 2 2 0 0 2329 3 605174 50 74 26752874 553 6 59 82.6

93. TH-67 WEIGHT AND BALANCE STEP 12-- Reference 11--Not used in the TH-67. STEP 12-- Reference 11--Not used in the TH-67.

94. TH-67 WEIGHT AND BALANCE STEP 13-- Reference 12--Record the weight and moment totals (references 9 thru 11) in their respective columns. STEP 13-- Reference 12--Record the weight and moment totals (references 9 thru 11) in their respective columns.

95. FK 489927 PART OF BASIC WEIGHT 2 2 0 0 2329 3 605174 50 74 26752874 553 6 59 82.6

96. FK 489927 PART OF BASIC WEIGHT 22 0 0 2329 3 605174 50 7 4 26752874 55 3 659 32283533 82.6

97. TH-67 WEIGHT AND BALANCE STEP 14-- Reference 13--Record the quantity, weight, and location of any passengers that are not crewmembers in the columns provided. Record any additional cargo stored in the baggage compartment (that is not the crew’s personal equipment) in the columns provided. Record the passenger’s weight and moment in their respective columns. On the next line, record the cargo’s total weight and moment in their respective columns. Use table 6-11 or the formula: Weight X Arm = Moment divided by the Index. STEP 14-- Reference 13--Record the quantity, weight, and location of any passengers that are not crewmembers in the columns provided. Record any additional cargo stored in the baggage compartment (that is not the crew’s personal equipment) in the columns provided. Record the passenger’s weight and moment in their respective columns. On the next line, record the cargo’s total weight and moment in their respective columns. Use table 6-11 or the formula: Weight X Arm = Moment divided by the Index.

98. TH-67 WEIGHT AND BALANCE NOTE: Reference 14 and 15 are normally not applicable for helicopters unless specifically required by command policy.

99. TH-67 WEIGHT AND BALANCE STEP 15-- Reference 14--Record zero fuel weight and moment in the place provided. Use the definition for “Zero Fuel Weight” to arrive at the answer, I.e. Operating Weight, reference 9 plus Distribution of Allowable Load reference 13, (cargo and passengers); or, Takeoff Condition reference 16, minus Takeoff Fuel, reference 10. STEP 15-- Reference 14--Record zero fuel weight and moment in the place provided. Use the definition for “Zero Fuel Weight” to arrive at the answer, I.e. Operating Weight, reference 9 plus Distribution of Allowable Load reference 13, (cargo and passengers); or, Takeoff Condition reference 16, minus Takeoff Fuel, reference 10.

100. FK 489927 PART OF BASIC WEIGHT 22 0 0 2329 3 605174 50 7 4 26752874 55 3 659 32283533 2675 2874 82.6

101. TH-67 WEIGHT AND BALANCE STEP 15-- Reference 14--(continued). Using the Zero Fuel weight and moment just solved for, determine the Zero Fuel Center-of-Gravity. Use the formula: Total Moment divided by Total Weight times the Index = Zero Fuel Center-of-Gravity. Round up or down to the nearest tenth of an inch. STEP 15-- Reference 14--(continued). Using the Zero Fuel weight and moment just solved for, determine the Zero Fuel Center-of-Gravity. Use the formula: Total Moment divided by Total Weight times the Index = Zero Fuel Center-of-Gravity. Round up or down to the nearest tenth of an inch.

102. FK 489927 PART OF BASIC WEIGHT 22 0 0 2329 3 605174 50 7 4 26752874 55 3 659 32283533 2675 2874 82.6 107.4

103. TH-67 WEIGHT AND BALANCE STEP 16-- Reference 16--Record sums of weights and moments column totals (reference 12 and reference 13), in their respective columns. STEP 16-- Reference 16--Record sums of weights and moments column totals (reference 12 and reference 13), in their respective columns.

104. 3 22 8 3533

105. TH-67 WEIGHT AND BALANCE STEP 17-- Reference 17--Compute Center-of-Gravity at takeoff using the CG formula: Total Moment divided by Total Weight multiplied by the index = Takeoff Condition (uncorrected) Center-of-Gravity. Always round the CG up or down to the nearest tenth of an inch. Record the result in the space provided. STEP 17-- Reference 17--Compute Center-of-Gravity at takeoff using the CG formula: Total Moment divided by Total Weight multiplied by the index = Takeoff Condition (uncorrected) Center-of-Gravity. Always round the CG up or down to the nearest tenth of an inch. Record the result in the space provided.

106. 32 2 8 3533 109.4

107. TH-67 WEIGHT AND BALANCE STEP 18-- Reference 18--When the takeoff weight, reference 16, or the takeoff CG, reference 17, are not within permissible limits, changes in the amount or distribution of load are required. The necessary load adjustments must be noted in the “Corrections” columns on the left portion of the form. Enter a brief description of the necessary adjustments in the correction area with the arm, item, weight, and moment recorded in the columns provided. STEP 18-- Reference 18--When the takeoff weight, reference 16, or the takeoff CG, reference 17, are not within permissible limits, changes in the amount or distribution of load are required. The necessary load adjustments must be noted in the “Corrections” columns on the left portion of the form. Enter a brief description of the necessary adjustments in the correction area with the arm, item, weight, and moment recorded in the columns provided.

108. TH-67 WEIGHT AND BALANCE STEP 18-- Reference 18--(continued). Remember to record the Index from the 365-3 Chart C at the top of the column and apply it to every moment computation. Total all the weight and moment increases/decreases to obtain the net change(+ or -) in the amount of distribution of the load. Transfer the “Net Difference” weight and moment total to the weight and moment columns reference 18. STEP 18-- Reference 18--(continued). Remember to record the Index from the 365-3 Chart C at the top of the column and apply it to every moment computation. Total all the weight and moment increases/decreases to obtain the net change(+ or -) in the amount of distribution of the load. Transfer the “Net Difference” weight and moment total to the weight and moment columns reference 18.

109. TH-67 WEIGHT AND BALANCE NOTE: If there are any temporary changes listed on DA Forms 2408-13-1 or 2408-14-1, they shall be considered changes in basic aircraft loading and must be treated in the same manner explained in reference 18 above.

111. 32 2 8 3533 109.4 --3 1

112. TH-67 WEIGHT AND BALANCE STEP 19-- Reference 19--Subtract the weight and moment, reference 18, from the weight and moment, reference 16, and record and resulting weight and moment in their respective columns. STEP 19-- Reference 19--Subtract the weight and moment, reference 18, from the weight and moment, reference 16, and record and resulting weight and moment in their respective columns.

113. 32 2 8 3533 109.4 --3 1 32253532

114. TH-67 WEIGHT AND BALANCE STEP 20-- Reference 20--Compute center-of-gravity at takeoff condition (corrected) using the CG formula: Total Moment divided by Total Weight multiplied by the index = Takeoff Condition (corrected) center-of- gravity. Always round the CG up or down to the nearest tenth of an inch. Record the result in the space provided. STEP 20-- Reference 20--Compute center-of-gravity at takeoff condition (corrected) using the CG formula: Total Moment divided by Total Weight multiplied by the index = Takeoff Condition (corrected) center-of- gravity. Always round the CG up or down to the nearest tenth of an inch. Record the result in the space provided.

115. 32 2 8 3533 109.4 --3 1 32253532 109.5

116. TH-67 WEIGHT AND BALANCE STEP 21-- Reference 21--Record the Zero Fuel weight and moment from reference 14 in their respective columns. STEP 21-- Reference 21--Record the Zero Fuel weight and moment from reference 14 in their respective columns.

117. 32 2 8 3533 109.4 --3 1 32253532 109.5 26 7 5 2 874

118. TH-67 WEIGHT AND BALANCE STEP 22-- Reference 22--Subtract reference 22’s weight and moment totals (if any) from reference 21 and record the result on the last line in reference 22’s area. This reference is normally not used in accomplishing the TH-67 mission. STEP 22-- Reference 22--Subtract reference 22’s weight and moment totals (if any) from reference 21 and record the result on the last line in reference 22’s area. This reference is normally not used in accomplishing the TH-67 mission.

119. TH-67 WEIGHT AND BALANCE STEP 23-- Reference 23--Determine how much fuel would be remaining in the fuel tank upon arrival at the destination. Record the amount of fuel in the ITEM column, and record the weight and moment of the remaining fuel in their respective columns. Use the Fuel Loading Table page 6-7. STEP 23-- Reference 23--Determine how much fuel would be remaining in the fuel tank upon arrival at the destination. Record the amount of fuel in the ITEM column, and record the weight and moment of the remaining fuel in their respective columns. Use the Fuel Loading Table page 6-7.

121. 127.32 111.83142.36

122. 109.4 109.5 3 2 2 5 353 2 26 7528 7 4 32283533 19 Gal.

123. TH-67 WEIGHT AND BALANCE STEP 24-- Reference 24--Add the weight and moment columns, reference 23, to the weight and moment columns, reference 22 (if any) and record the results in their respective columns. If there were no entries in reference 22, add the weight and moment columns, reference 23, to the weight and moment columns, reference 21, and record the results in their respective columns. STEP 24-- Reference 24--Add the weight and moment columns, reference 23, to the weight and moment columns, reference 22 (if any) and record the results in their respective columns. If there were no entries in reference 22, add the weight and moment columns, reference 23, to the weight and moment columns, reference 21, and record the results in their respective columns.

124. 109.4 109.5 3 2 2 5 353 2 26 7528 7 4 28023 0 1 6 32283533 19 Gal.

125. TH-67 WEIGHT AND BALANCE STEP 25-- Reference 25--Computed Estimated Landing center- of-gravity using the CG formula: Total Moment divided by Total Weight multiplied by the index = Estimated Landing CG. Always round the CG up or down to the nearest tenth of an inch. Record the result in the space provided. STEP 25-- Reference 25--Computed Estimated Landing center- of-gravity using the CG formula: Total Moment divided by Total Weight multiplied by the index = Estimated Landing CG. Always round the CG up or down to the nearest tenth of an inch. Record the result in the space provided.

126. 109.4 109.5 3 2 2 5 353 2 26 7528 7 4 28023 0 1 6 32283533 107.6 19 Gal.

127. TH-67 WEIGHT AND BALANCE LIMITATIONS Limitations--area in the lower left corner of the page. This area is used to provide the pilot the limitations needed to make an informed decision should a mission change occur. The limitations section is completed as follows: LIMITATIONS

128. TH-67 WEIGHT AND BALANCE LIMITATIONS STEP 1--Allowable Gross Weight. Record the maximum gross weight authorized for hovering/flight from chapter five in the TH-67 Operator’s Supplement in the Takeoff and Landing columns. NOTE: The Fuel column is not computed in the limitations section of the form for most helicopters. LIMITATIONS STEP 1--Allowable Gross Weight. Record the maximum gross weight authorized for hovering/flight from chapter five in the TH-67 Operator’s Supplement in the Takeoff and Landing columns. NOTE: The Fuel column is not computed in the limitations section of the form for most helicopters.

129. 3350

130. TH-67 WEIGHT AND BALANCE LIMITATIONS STEP 2--Record the weight from reference 12 in the Takeoff column. LIMITATIONS

131. 3350 3228

132. TH-67 WEIGHT AND BALANCE LIMITATIONS STEP 3--Reference 9 + Reference 23. Record the sum of the weights of reference 9 and reference 23 in the Landing column. LIMITATIONS

133. 3350 3228 2802

134. TH-67 WEIGHT AND BALANCE LIMITATIONS STEP 4--Allowable Load. This value is used to evaluate any mission changes. Subtract Total Aircraft weight, item 2 above, from Allowable Gross Weight, item 1 above, and record the result in the Takeoff column. Compare this value to the total weight in reference 13. Use the lesser of the two values as allowable gross weight. Subtract Total Aircraft weight, item 2 above, from Allowable Gross Weight, item 1 above, and record the result in the Takeoff column. Compare this value to the total weight in reference 13. Use the lesser of the two values as allowable gross weight.LIMITATIONS STEP 4--Allowable Load. This value is used to evaluate any mission changes. Subtract Total Aircraft weight, item 2 above, from Allowable Gross Weight, item 1 above, and record the result in the Takeoff column. Compare this value to the total weight in reference 13. Use the lesser of the two values as allowable gross weight. Subtract Total Aircraft weight, item 2 above, from Allowable Gross Weight, item 1 above, and record the result in the Takeoff column. Compare this value to the total weight in reference 13. Use the lesser of the two values as allowable gross weight.

135. 3350 122 3228 2802

136. TH-67 WEIGHT AND BALANCE NOTE: This value can also be used in evaluating any mission changes that may occur near the Takeoff phase of the mission. Remember, if the gross weight changes from what is planned, the mission planning data will change. For every 30 pounds change in gross weight, expect a change of 1% in torque.

137. TH-67 WEIGHT AND BALANCE LIMITATIONS STEP 4--Allowable Load. This value is used to evaluate any mission changes (continued). Subtract reference 9 and reference 23, item 3 above, from Allowable Gross Weight in the Landing column, item 1 above, and record the result in the Landing column. Subtract reference 9 and reference 23, item 3 above, from Allowable Gross Weight in the Landing column, item 1 above, and record the result in the Landing column.LIMITATIONS STEP 4--Allowable Load. This value is used to evaluate any mission changes (continued). Subtract reference 9 and reference 23, item 3 above, from Allowable Gross Weight in the Landing column, item 1 above, and record the result in the Landing column. Subtract reference 9 and reference 23, item 3 above, from Allowable Gross Weight in the Landing column, item 1 above, and record the result in the Landing column.

138. 3350 3228 2802 122548

139. TH-67 WEIGHT AND BALANCE NOTE: This value can also be used in evaluating any add on missions upon completion of the mission. Gross weight normally is never a consideration. However, remember the fuel available at the end of the planned mission and the space available in the crew and baggage compartments. These are normally the considerations that may restrict the pilot from accepting additional missions prior to refueling.

140. TH-67 WEIGHT AND BALANCE LIMITATIONS STEP 5--Permissible CG Takeoff. Record the authorized forward and aft limits found at the takeoff gross weight, reference 16 or reference 19 if corrections were required. Use Figure 6-4 to arrive at the fore and aft limitations. Record the values in the spaces provided. LIMITATIONS

141. Figure 6-4 VFR Center of Gravity Limits Chart 3228 106.4 111.5 IMC CG Limits Above 3200 lbs GW IMC CG Limits 2400 to 3200 lbs GW

142. 3350 3228 2802 122548 111.5106.4

143. TH-67 WEIGHT AND BALANCE LIMITATIONS STEP 6--Permissible CG Landing. Record the authorized forward and aft limits found at the estimated landing condition weight, reference 24. Use Figure 6-4 to arrive at the fore and aft limitations. Record the values in the spaces provided. LIMITATIONS

144. Figure 6-4 VFR Center of Gravity Limits Chart 2802 106.0112.9 IMC CG Limits Above 3200 lbs GW IMC Limits 2400 to 3200 lbs GW

145. 3350 3228 2802 122548 106.4 111.5 106.0 112.9

146. TH-67 WEIGHT AND BALANCE LIMITATIONS STEP 7--Permissible CG Zero Fuel Weight. Record the authorized forward and aft limits found at the zero fuel weight, reference 14 or reference 21. Use Figure 6-4 to arrive at the fore and aft limitations. Record the values in the spaces provided. LIMITATIONS

147. Figure 6-4 VFR Center of Gravity Limits Chart 2675 106.0113.4 IMC CG Limits Above 3200 lbs GW IMC CG Limits 2400 to 3200 lbs GW

148. 3350 3228 2802 122548 113.4 112.9 111.5 106.4

149. TH-67 WEIGHT AND BALANCE LIMITATIONS STEP 8--Computed by Signature. Enter the signature of the person computing the form. LIMITATIONS

150. Allan Krausz 3350 3228 2802 122548 106.4111.5 106.0112.9 106.0 113.4

151. TH-67 WEIGHT AND BALANCE LIMITATIONS STEP 9--Weight and Balance Authority Signature. Enter your own signature. You are your own authority after having successfully completed flight school for the aircraft in which you fly. (Local policy may dictate how this block is to be used). LIMITATIONS

152. Allan Krausz Allan Krausz 3350 3228 2802 122548 106.4111.5 106.0112.9 106.0 113.4

153. TH-67 WEIGHT AND BALANCE LIMITATIONS STEP 10--Pilot signature. The pilot -in-command signs the form. (Local policy may dictate how this block is to be used). NOTE: Prior to accepting the aircraft for flight, the pilot-in-command must ensure the requirements of AR 95-1, paragraph 5-2 (h) have been met. LIMITATIONS STEP 10--Pilot signature. The pilot -in-command signs the form. (Local policy may dictate how this block is to be used). NOTE: Prior to accepting the aircraft for flight, the pilot-in-command must ensure the requirements of AR 95-1, paragraph 5-2 (h) have been met.

154. Allan Krausz 3350 3228 2802 122548 106.4111.5 106.0112.9 106.0 113.4 Allan Krausz

155. TH-67 WEIGHT AND BALANCE Practical Exercise #2