DO NOT BEGIN THIS WORK UNTIL YOU HAVE COMPLETED ALL REQUIRED ASSIGNED READING AND EXERCISES. Gardner Textbook Review Questions to prepare for Class #11 Answer these on notebook paper (or a text file) then correct or improve your answers (using another color) by referring to the answers provided. Gardner Textbook Review Questions for Class #11, (Gardner pg 8-22, 23, 24) Use Figure 8-7, (Gardner pg 8-6) for problems 1-4. GL08-01 Determine the moment with the following data: Empty Weight Pilot and front passenger Fuel (std tanks) Oil 8qts A ― 69.9 lbs-in. B ― 74.9 lbs-in. C ― 77.0 lbs-in.

Weight, lbs

Moment / 1,000

1,350 340 Capacity 15

51.5 0.2

GL08-02 What is the maximum amount of fuel that may be aboard the airplane on takeoff if it is loaded as follows? Empty Weight 1,350 51.5 Pilot and front passenger 340 Rear passengers 310 Baggage 45 Oil 8qts 15 0.2 A ― 24 gal. B ― 34 gal. C ― 40 gal.

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GL08-03 What is the maximum amount of baggage that may be loaded aboard the airplane for the CG to remain within the loading envelope? Empty Weight 1,350 51.5 Pilot and front passenger 250 Rear passengers 400 Baggage Fuel 30 gal Oil 8qts 15 0.2 A ― 120 lbs. B ― 105 lbs. C ― 90 lbs. GL08-04 Calculate the moment of the airplane and determine which category is applicable. Empty Weight 1,350 51.5 Pilot and front passenger 310 Rear passengers 96 Fuel 30 gal Oil 8qts 0.2 A ― 79.2, utility category. B ― 80.8, utility category. C ― 81.2, normal category. Use Figure 8-8 and 8-9 (on Gardner pages 8-8 and 8-9) for review problems 5, 6, and 7: GL08-05 Determine if the airplan weight and balance are within limits. Front seat occupants 340 lbs Rear seat occupants 295 lbs Fuel 44 gal Baggage 56 lbs A ― Within limits B ― 20 lbs overweight, CG within limits. C ― Weight within limits, CG out of limits forward.

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GL08-06 Which action can adjust the airplane's weight to maximum gross weight and the CG within limits for takeoff? Front seat occupants 425 lbs Rear seat occupants 300 lbs Fuel, main tanks 44 gal A ― Drain 12 gallons of fuel. B ― Drain 9 gallons of fuel. C ― Transfer 12 gallons of fuel from the main tanks to the auxiliary tanks. GL08-07 What effect does a 35 gallon fuel burn have on the weight and balance if the airplane weighed 2,890 pounds and the moment/100 was 2,452 at takeoff? A ― Weight is reduced by 210 lbs and the CG is unaffected. B ― Weight is reduced to 2,680 lbs and the CG moves forward. C ― Weight is reduced by 210 lbs and the CG is aft of limits. GL08-08 After takeoff, which airspeed would permit the pilot to gain the most altitude in a given period of time? A ― Cruising climb speed. B ― Best rate of climb speed. C ― Best angle of climb speed. GL08-09 Which combination of atmospheric conditions will reduce aircraft takeoff and climb peformance? A ― Low temperature, low relative humidity, and low density altitude. B ― High temperature, low relative humidity, and low density altitude. C ― High temperature, high relative humidity, and high density altitude. GL08-10 How can pressre altitude be determined? A ― Set the field elevation in the altimeter setting window and read the indicated altitude. B ― Set the altimeter to zero and read the value in the altimeter setting window. C ― Set 29.92 in the altimeter setting window and read the indicated altitude. GL08-11 (Refer to Figure 8-18 on Gardner Page 8-17.) What fuel flow should a pilot expect at 11,000 feet on a standard day with 65 percent maximum continuous power? A ― 10.6 gallons per hour. B ― 11.2 gallons per hour. C ― 11.8 gallons per hour.

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GL08-12 What effect does higher density altitude have on propeller efficiency? A ― Increased efficiency due to less friction on the propeller blades. B ― Reduced efficiency because the propeller exerts less force than at lower density altitudes. C ― Increased efficiency because the propeller exerts less force on the thinner air. GL08-13 An airplane is usually affected by ground effect at what height above the surface? A ― Between 100 and 200 feet above the surface in calm wind conditions. B ― Less than half of the airplane's wingspan above the surface. C ― Twice the length of the airplane's wingspan above the surface. GL08-14 Which adverse effect must a pilot be aware of as a reslt of the phenomenon of ground effect during takeoff? A ― Difficulty in getting airborne even though airspeed is sufficient for normal takeoff. B ― Becoming airborne before reaching recommended takeoff speed. C ― Settling back to the surface immediately after becoming airborne. GL08-15 If you plan to land at an airport where the elevation is 7,500 feet, the indicated approach airspeed should be A ― the same speed as that used at a sea level airport. B ― lower than that used at a sea level airport. C ― higher than that used at a sea level airport. GL08-16 As altitude increases, the indicated airspeed at which a given airplane stalls in a particular configuration will. A ― decrease as the true airspeed decreases. B ― decrease as the true airspeed increases. C ― remain the same as at low altitude.

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GL08-17 Of what practical value is pressure altitude? A ― To use on all aircraft performance charts since the charts are based on pressure altitude B ― To use for obstacle clearance at higher altitudes where accurate altimeter settings are not available. C ― To use for computer solutions to determine density altitude, true altitude, true airspeed, etc. GL-08-18 Determine the approximate grond roll distance for takeoff under the following conditions. See Figure -12 on Gardner, Page 8-12. OAT 95° F Pressure Altitude 2,000 feet Takeoff weight 2,500 lbs Wind (headwind) 20 knots A ― 650 feet B ― 800 feet C ― 1,000 feet GL08-19 What effect, if any, does high humidity have on aircraft performance? A ― It increases performance. B ― It decreases performance. C ― It has no effect on performance.

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Homework Exercise to prepare for Class #11. Answer these on notebook paper then correct or improve your answers (using another color) by referring to the answer sheet. 1. What is the term for the reference plane from which all horizontal measurements are made in order to determine the arm used for weight and balance calculations? 2. How is unusable fuel defined? 3. What does basic empty weight include? a. The weight of full oil. b. The weight of minimum fuel. c. The weight of full fuel. 4. If your weight check shows that the airplane will exceed the maximum ramp weight specified in the POH, which of the following actions would be appropriate? a. Take off at that weight, but not taxi. b. Rearrange the load to bring it within CG limits. c. Remove passengers, cargo, or fuel until the weight limit is reached. 5. What is the weight of 42 gallons of aviation gasoline? a. 242 pounds. b. 248 pounds. c. 252 pounds. 6. The moment for a rear seat passenger is 14,800 inch-pounds. If this passenger sits in the front seat, will his/her moment be higher or lower? The following blank chart is one that you are going to want to memorize. Faithfully using this format on virtually all weight and balance problems will help assure that you solve the problem correctly:

Weight

Arm

Moment

Empty Airplane Front Seats Back Seats Fuel Baggage TOTAL

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7. True/False. Moment is expressed in inches. Why or why not? 8. You are planning a trip with three friends. You and your front seat passenger weigh a total of 366 pounds. The rear seat passengers each weigh 173 pounds. The suitcases and bags weigh 150 pounds total. Assume that 120 pounds of the bags will be in baggage area A and the remainder in baggage area B. Using the following graph, find the total moment so far (we haven’t dealt with the fuel or empty weight yet).

9. (Continued From question 8.) This airplane has an empty weight of 1,850 pounds, and the empty weight moment is 64,900 inch-pounds. It has a maximum allowable gross weight of 3,100 pounds, so how much usable fuel can be loaded and still remain within weight and CG limits? (Use the following moment envelope.)

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10. (Continued From question 9.)The center of gravity of this fully loaded airplane (using all the data from question 8 and 9 above) will be how many inches from the datum? 11. If flight had been attempted without changing the load distribution in the last question, what flight characteristics could be expected? a. Tail-heaviness, requiring additional forward trim. b. Light control forces, longitudinal instability, and a higher cruise speed for the power setting used. c. All of the above. 12. Compared to a lightly loaded airplane, what flight characteristics can be expected from a heavily loaded airplane? a. It will stall at a higher speed, cruise at a slower speed, and have less range. b. It will land at a lower speed, cruise at a higher speed, and stall at a higher angle of attack. c. It will have a higher cruise speed and range, a reduced rate of climb, and stall at the same speed.

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13. Select the true statement(s) regarding operating limitations: a. Operating limitations are often referred to as the flight or performance envelope. b. Operating limitations establish the boundaries within which the airplane must be flown. c. The FARs specify that operating limitations must be published in the approved flight manual, approved manual material, markings, and placards; or any combination of these. 14. Describe how density altitude affects aircraft performance. 15. True/False. Takeoff performance depends primarily on factors that can be measured or calculated in advance such as density altitude, pressure altitude, temperature, wind, aircraft weight, and runway gradient and surface. 16. Refer to Figure 37. Determine the headwind and crosswind components for a departure on runway 18 with a reported wind (reported by ATIS) of 210 at 20 knots. 17. What is the runway gradient? a. The material used to surface the runway. b. The amount of change in runway height over its length. c. The direction of the runway as it relates to magnetic north. 18. Name the three important factors that the pilot must consider when planning the climb segment of a flight. 19. Select the items that would be found on a cruise performance chart. a. Time, fuel, and distance to climb. b. Fuel consumption and airspeed at various power settings. c. Power required for level flight, including maximum level flight speed and L/Dmax. 20. True/False. Landing weight is not a factor that must be considered during an approach.

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