Warm-Up – 12/11 – 10 minutes

1. Warm-Up – 12/11 – 10 minutes Utilizing your notes and past knowledge answer the following questions: • Define the effect of load factors and stalling speeds. • What is the maximum speed at which an aircraft may be stalled safely called? • What is the only way this type of stall can be induced at an airspeed above normal stalling with an added load factor? • What action should a pilot perform in extremely rough air to prevent possible stall? • Describe the two types of loads that can damage an aircraft.

2. Questions / Comments

3. Warm-Up – 12/11 – 10 minutes Utilizing your notes and past knowledge answer the following questions: • Define the effect of load factors and stalling speeds. • What is the maximum speed at which an aircraft may be stalled safely called? • What is the only way this type of stall can be induced at an airspeed above normal stalling with an added load factor? • What action should a pilot perform in extremely rough air to prevent possible stall? • Describe the two types of loads that can damage an aircraft.

4. Load Factors and Stalling Speeds • A study of this effect has revealed that the aircraft’s stalling speed increases in proportion to the square root of the load factor.

5. Warm-Up – 12/11 – 10 minutes Utilizing your notes and past knowledge answer the following questions: • Define the effect of load factors and stalling speeds. • What is the maximum speed at which an aircraft may be stalled safely called? • What is the only way this type of stall can be induced at an airspeed above normal stalling with an added load factor? • What action should a pilot perform in extremely rough air to prevent possible stall? • Describe the two types of loads that can damage an aircraft.

6. Load Factors and Stalling Speeds • The maximum speed at which an aircraft may be stalled safely is now determined for all new designs. • This speed is called the “design maneuvering speed” (VA).

7. Warm-Up – 12/11 – 10 minutes Utilizing your notes and past knowledge answer the following questions: • Define the effect of load factors and stalling speeds. • What is the maximum speed at which an aircraft may be stalled safely called? • What is the only way this type of stall can be induced at an airspeed above normal stalling with an added load factor? • What action should a pilot perform in extremely rough air to prevent possible stall? • Describe the two types of loads that can damage an aircraft.

8. Load Factors and Flight Maneuvers • High Speed Stalls • The only way this stall can be induced at an airspeed above normal stalling with anadded load factor, which may be accomplished by a severe pull on the elevator control.

9. Warm-Up – 12/11 – 10 minutes Utilizing your notes and past knowledge answer the following questions: • Define the effect of load factors and stalling speeds. • What is the maximum speed at which an aircraft may be stalled safely called? • What is the only way this type of stall can be induced at an airspeed above normal stalling with an added load factor? • What action should a pilot perform in extremely rough air to prevent possible stall? • Describe the two types of loads that can damage an aircraft.

10. Load Factors and Flight Maneuvers • Rough Air • All standard certificated aircraft are designed to withstand loads imposed by gusts of considerable intensity. • In extremely rough air it is wise to reduce the speed to the design maneuvering speed.

11. Warm-Up – 12/11 – 10 minutes Utilizing your notes and past knowledge answer the following questions: • Define the effect of load factors and stalling speeds. • What is the maximum speed at which an aircraft may be stalled safely called? • What is the only way this type of stall can be induced at an airspeed above normal stalling with an added load factor? • What action should a pilot perform in extremely rough air to prevent possible stall? • Describe the two types of loads that can damage an aircraft.

12. Load Factors and Flight Maneuvers • The limit load is a force applied to an aircraft that causes a bending of the aircraft structure that does not return to the original shape.

13. Load Factors and Flight Maneuvers • The ultimate load is the load factor applied to the aircraft beyond the limit load and at which point the aircraft material experiences structural failure (breakage).

14. Questions / Comments

15. THIS DAY IN AVIATION • December 11 • 1917 — Katherine Stinson flies 606 miles from San Diego to San Francisco, setting a new American non-stop distance record.

16. THIS DAY IN AVIATION • December 11 • 1928 — Privates Sidney R. Glover and Paul W. Lemons are awarded the Soldiers Medal for rescuing Major Junius W. Jones, United States Air Corps, and Maj. Samuel T. Stewart, C.A.C, from drowning after an airplane crash into the Mississippi River near Fort Leavenworth, Kansas.

17. Questions / Comments

18. December 2013

19. Questions / Comments

21. Chapter 4 – Aerodynamics of Flight FAA – Pilot’s Handbook of Aeronautical Knowledge

22. Today’s Mission Requirements • Mission: • Identify in writing the forces acting on an aircraft in flight. • Describe how the forces of flight work and how to control them with the use of power and flight controls essential to flight. • Describe in writing how design, weight, load factors, and gravity affect an aircraft during flight maneuvers. • EQ: Describe the importance of Aeronautical Knowledge for the student pilot learning to fly.

23. Load Factors and Flight Maneuvers • Rate of Turn • The rate of turn (ROT) is the number of degrees (expressed in degrees per second) of heading change that an aircraft makes.

24. Load Factors and Flight Maneuvers • Radius of Turn • If the bank angle is held constant and the airspeed is increased, the radius of the turn changes (increases). • A higher airspeed causes the aircraft to travel through a longer arc due to a greater speed.

25. Two aircraft have flown into a canyon by error. The canyon is 5,000 feet across and has sheer cliffs on both sides. The pilot in the top image is flying at 120 knots. After realizing the error, the pilot banks hard and uses a 30° bank angle to reverse course. This aircraft requires about 4,000 feet to turn 180°, and makes it out of the canyon safely.

26. The pilot is flying at 140 knots and also uses a 30° angle of bank in an attempt to reverse course. The aircraft, although flying just 20 knots faster than the aircraft in the top image, requires over 6,000 feet to reverse course to safety. Unfortunately, the canyon is only 5,000 feet across and the aircraft will hit the canyon wall. The point is that airspeed is the most influential factor in determining how much distance is required to turn. Many pilots have made the error of increasing the steepness of their bank angle when a simple reduction of speed would have been more appropriate.

27. Weight and Balance • Weight and balance computations should be part of every preflight briefing. • Never assume three passengers are always of equal weight.

28. Weight and Balance • Instead, do a full computation of all items to be loaded on the aircraft, including baggage, as well as the pilot and passenger.

29. Weight and Balance • It is recommended that all bags be weighed to make a precise computation of how the aircraft CG is positioned.

30. Weight and Balance • Aircraft are certificated for weight and balance for two principal reasons: • 1. The effect of the weight on the aircraft’s primary structure and its performance characteristics. • 2. The effect of the location of this weight on flight characteristics, particularly in stall and spin recovery and stability.

31. Weight and Balance Datum is at front face of firewall Moment (in.-lb) M = Fd = weight ● arm Force Weight (lb) Distance Arm (in.) Item 37.4 1,460 54,604 Empty weight ? 37.0 5,920 160 Pilot 6,660 180 37.0 Co-pilot 240 45.3 10,872 Fuel 72.8 24,752 340 Rear seat passengers 1,898 20 94.9 Baggage 1 0 n/a 0 Baggage 2 2,400 ? 104,706 ? Total What now? Determine whether the plane is safe to fly.

32. Weight and Balance From Pilot Operating Handbook (POH) Center of Gravity Moment Envelope 2,500 2,400 2,300 2,200 Safe to fly? 2,100 Barely! 2,000 Loaded Airplane Weight (lb) 1,900 1,800 1,700 1,600 1,500 90 80 100 110 45 50 60 70 Loaded Airplane Moment (in.-lb/1000)

33. Effect of Weight on Flight Performance • A heavier gross weight results in a longer takeoff run and shallower climb, and a faster touchdown speed and longer landing roll.

34. Effect of Weight on Flight Performance • The detrimental effects of overloading on performance are not limited to the immediate hazards involved with takeoffs and landings.

35. Effect of Weight on Flight Performance • Overloading has an adverse effect on all climb and cruise performance which leads to overheating during climbs, added wear on engine parts, increased fuel consumption, slower cruising speeds, and reduced range.

36. Effect of Weight on Flight Performance • In some aircraft, it is not possible to fill all seats, baggage compartments, and fuel tanks, and still remain within approved weight or balance limits. • For example, in several popular four-place aircraft, the fuel tanks may not be filled to capacity when four occupants and their baggage are carried. • In a certain two-place aircraft, no baggage may be carried in the compartment aft of the seats when spins are to be practiced. • It is important for a pilot to be aware of the weight and balance limitations of the aircraft being flown and the reasons for these limitations.

37. Effect of Weight on Aircraft Structure • Structural failures which result from overloading may be dramatic and catastrophic, but more often they affect structural components progressively in a manner that is difficult to detect and expensive to repair.

38. Effect of Weight on Aircraft Structure • Habitual overloading tends to cause cumulative stress and damage that may not be detected during preflight inspections and result in structural failure later during completely normal operations.

39. Effect of Weight on Aircraft Structure • In loading an aircraft with either passengers or cargo, the structure must be considered. • Seats, baggage compartments, and cabin floors are designed for a certain load or concentration of load and no more.

40. Effect of Weight on Aircraft Structure • For example, a light plane baggage compartment may be placarded for 20 pounds because of the limited strength of its supporting structure even though the aircraft may not be overloaded or out of CG limits with more weight at that location.

42. Questions / Comments

43. 1. Create (1) quiz question with answer about today’s lesson. 3. List 3 things you learned today. 2. List 2 things you have questions about today’s lesson. Lesson Closure - 3 – 2 - 1

44. Effect of Load Distribution • The effect of the position of the CG on the load imposed on an aircraft’s wing in flight is significant to climb and cruising performance.

45. Effect of Load Distribution • With forward loading, “nose-up” trim is required in most aircraft to maintain level cruising flight. • Nose-up trim involves setting the tail surfaces to produce a greater down load on the aft portion of the fuselage, which adds to the wing loading and the total lift required from the wing if altitude is to be maintained.

46. Effect of Load Distribution • This requires a higher AOA of the wing, which results in more drag and, in turn, produces a higher stalling speed.

47. Effect of Load Distribution • With aft loading and “nose-down” trim, the tail surfaces exert less down load, relieving the wing of that much wing loading and lift required to maintain altitude. • The required AOA of the wing is less, so the drag is less, allowing for a faster cruise speed.

48. Effect of Load Distribution • The recovery from a stall in any aircraft becomes progressively more difficult as its CG moves aft. • This is particularly important in spin recovery, as there is a point in rearward loading of any aircraft at which a “flat” spin develops.

49. Effect of Load Distribution • A flat spin is one in which centrifugal force, acting through a CG located well to the rear, pulls the tail of the aircraft out away from the axis of the spin, making it impossible to get the nose down and recover.

50. Effect of Load Distribution • To summarize the effects of load distribution: • The CG position influences the lift and AOA of the wing, the amount and direction of force on the tail, and the degree of deflection of the stabilizer needed to supply the proper tail force for equilibrium.