PRIVATE PILOT TEST PREP

3661. WHICH ITEMS ARE INCLUDED IN THE EMPTY WHO OF AN AIRCRAFT?. A)UNUSABLE FUEL AND UNDRAINABLE IOL. B)ONLY THE AIRFRAME, POWERPLANT, AND OPTIONAL EQUIPMENT. C)FULL FUEL TANKS AND ENGINE OIL TO CAPACITY.

3662. AN AIRCRAFT IS LOADED 110 POUNDS OVER MAXIMUM CERTIFICATED GROSS WEIGTH. IF FUEL IS DRAING TO BRING THE AIRCRAFT WEIGHT WHITIN LIMITS, HOW MUCH SHOULD BE DRAINED?. A)15.7 GALLONS. B)16.2 GALLONS. C)18.4 GALLONS.

3663. IF AN AIRCRAFT IS LOCATED 90 POUNDS OVER MAXIMUM CERTIFICATED GROSS WEIGHT AND FUEL GASOLINE IS DRAINED TO BRING THE AIRCRAFT WEIGHT WITHIN LIMITS, HOW MUCH FUEL SHOULD BE DRAINED?. A)10 GALLONS. B)12 GALLONS. C)15 GALLONS.

3663.1 IF 50 POUNDS OF WEIGHT IS LOCATED AT POINT X AND 100 POUNDS AT Z, HOW MUCH WEIGHT MUST BE LOCATED AT POINT Y TO BALANCE THE PLAK?. A) 30 POUNDS. B) 50 POUNDS. C) 300 POUNDS.

3663.2 HOW SHOULD THE 500-POUNDS WEIGHT BE SHIFTED TO BALANCE THE PLANK ON THE FULCRUM?. A) 1 INCH TO THE LEFT. B)1 INCH TO THE RIGHT. C)4.5 INCHES TO THE RIGHT.

3664. GIVEN WEIGHT ARM MOMENT EMPTY WEIGHT 1,495.0 101.4 151,593.0 PILOT AND PASSENGERS 380.0 64.0 ----- FUEL(30 GALLONS USABLE) ------ 96.0 --- THE CG IS LOCATED HOW FAR AFT OF DATUM?. A)CG 92.44. B)CG 94.01. C)CG 119.8.

3665. DETERMINE IF THE AIRPLANE WEIGHT AND BALANCE IS EEHITIN LIMITS FRONT SEAT OCCUPANTS……..340 LB REAR SEAR OCCUPANTS………...295 LB FUEL(MAIN WING TANKS)………44 GAL BAGGAGE…………………………………56 LB. A)20 POUNDS OVERWEIGHT, CG AFT OF AFT LIMITS. B) 20 POUNDS OVERWEIGHT, CG WHITIN LIMITS. C) 20 POUNDS OVERWEIGHT, CG FORWARD FOR FORWARD LIMITS.

3666. WHAT IS THE MAXIMUM AMOUNT OF BAGGAGE THAT CAN BE CARRIED WHEN THE AIRPLANE IS LOADED AS FOLLOWS? FRONT SEAT OCCUPANTS …………………………….....387 LB REAR SEAT OCCUPANTS ……………………………………294 LB FUEL…………………………………………………………………..35 GALLONS. A)45 POUNDS. B)63 POUNDS. C)220 POUNDS.

3667. CALCULATE THE WEIGHT AND BALANCE AND DETERMINE IF THE CG AND THE WEIGHT OD THE AIRPLANE ARE WITHIN LIMITS. FRONT SEAT OCCUPANTS …………………………….....350 LB REAR SEAT OCCUPANTS ……………………………………325 LB BAGGAGE………………………………………………………..27 LB FUEL…………………………………………………………………..35 GAL. A) CG 81.7 OUT OF LIMITS FORWARD. B)CG 83.4 WHITIN LIMITS. C) CG 84.1 WHITIN LIMITS.

3668. DETERMINE IF THE AIRPLANE WEIGHT AND BALANCE IS WHITIN LIMITS. FRONT SEAT OCCUPANTS …………………………….....415 LB REAR SEAT OCCUPANTS ……………………………………110 LB FUEL, MAIN TANKS……………………………………………..44 GAL FUEL. AUX, TANKS……………………………………………….19 GAL BAGGAGE…………………………………………………………….32 LB. A) 19 POUNDS OVERWEIGHT, CG WHITIN LIMITS. B)19 POUNDS OVERWEIGHT, CG OUT OF LIMITS FORWARD. C)WEIGHT WHITIN LIMITS, CG OUT OF LIMITS.

3674. UPON LANDING, THE FRONT PASSENGER(180POUNDS) DEPARTS THE AIRPLANE. A REAR PASSENGER(204 POUNDS) MOVES TO THE FRONT PASSENGER POSITION. WHAT EFFECT DOES THIS HAVE ON THE CG ID THE AIRPLANE WEIGHED 2.690 POUNDS AND THE MOM/100 WAS 2.260 JUST PRIOR TO THE PASSENGER TRANSFER?. A) THE CG MOVES FORWARD APPROXIMATELY 3 INCHES. B) THE WEIGHT CHANGES. BUT THE CG IS NOT AFFECTED. C) THE CG MOVES FORWARD APPROXIMATELY 0.1 INCH.

3675.WHICH ACTION CAN ADJUTS THE AIRPLANE'S WEIGHT TO MAXIMUM GROSS WEIGHT AND THE CG WHITIN LIMITS FOR TAKEOFF? FRONT SEAT OCCUPANTS …………………………….....425 LB REAR SEAT OCCUPANTS ……………………………………300 LB FUEL, MAIN TANKS……………………………………………..33 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 AUXIALIRY TANKS.

3676. WHAT EFFECT DOES A 35 GALLON FUEL BURN HAVE ON THE WEIGHT AND BALANCE IF THE AIRPLANE WEIGHED 2.890 POUNDS AND THE MOM/100 WAS 2,452 AT TAKEOFF?. A)WEIGHT IS REDUCED BY 210 POUNDS AND THE CG IS AFT OF LIMITS. B)WEIGHT IS REDUCED BY 210 POUNDS AND THE CG IS UNAFFECTED. C)WEIGHT IS REDUCED TO 2,680 POUNDS AND THE CG MOVES FORWARD.

3677. WITH THE AIRPLANE LOADED AS FOLLOWS, WHAT ACTION CAN BE TAKEN TO BALANCE THE AIRPLANE? FRONT SEAT OCCUPANTS …………………………….....411 LB REAR SEAT OCCUPANTS ……………………………………100 LB MAIN WING TANKS……………………………………………44 GAL. A)FILL THE AUXILIARY WING TANKS. B)ADD A 100 POUND WEIGHT TO THE BAGGAGE COMPARTMENT. C)TRANSFER 10 GALLONS OF FUEL FROM THE MAIN TANKS TO THE AUXILIARY TANKS.

3669. WHAT IS THE MAXIMUM AMOUNT OF BAGGAGE THAT MAY BE LOADED ABOARD THE AIRPLANE FOR THE CG TO REMAIN WHITIN THE MOMENT ENVELOPE? WEIGHT MOM/1000 EMPTY WEIGHT 1,350 51.5 PILOT AND FRONT PASSENGERS 250 ---- REAR PASSENGER 400 ---- BAGGAGE --- ---- FUEL, 30 GAL --- -- - OIL, 8 QT --- -0.2. A)105 POUNDS. B)110 POUNDS. c) 120 POUNDS.

3670. CALCULATE THE MOMENT OF THE AIRPLANE AND DETERMINE WHICH CATEGORY IS APPLICABLE. WEIGHT MOM/1000 EMPTY WEIGHT 1,350 51.5 PILOT AND FRONT PASSENGERS 310 ---- REAR PASSENGER 96 ---- FUEL, 30 GAL --- -- - OIL, 8 QT --- -0.2. A) 79.2 UTILITY CATEGORY. B) 80.8 UTILITY CATEGORY. C)81.2 NORMAL CATEGORY.

3671. WHAT IS THE MAXIMUM AMOUNT OF FUEL THAT MAY BE ABOARD THE AIRPLANE ON TAKEOFF IF LOADED AS FOLLOWS? WEIGHT MOM/1000 EMPTY WEIGHT 1,350 51.5 PILOT AND FRONT PASSENGERS 340 ---- REAR PASSENGER 310 ---- BAGGAGE 45 ---- OIL, 8 QT --- ---. A) 24 GALLONS. B) 32 GALLONS. C) 40 GALLONS.

3673. DETERMINE THE AIRCRAFT LOADED MOMENT AND THE AIRCRAFT CATEGORY. WEIGHT MOM/1000 EMPTY WEIGHT 1,350 51.5 PILOT AND FRONT PASSENGERS 380 ---- FUEL, 30 GAL 288 -- - OIL, 8 QT --- ----. A) 78.2 NORMAL CATEGORY. B) 79.2 NORMAL CATEGORY. C) 80.4 UTILITY CATEGORY.

3672. DETERMINE THE MOMENT WITHIN THE FOLLOWING DATA. WEIGHT MOM/1000 EMPTY WEIGHT 1,350 51.5 PILOT AND FRONT PASSENGERS 340 ---- FUEL (STD TANKS) CAPACITY ---- OIL, 8 QT --- ----. A) 69.9 POUND-INCHES. B) 74.9 POUND-INCHES. C) 77.6 POUND-INCHES.

3720. WHAT ACTION, IF ANY, SHOULD BE TAKEN FOR LATERAL BALANCE IF THE HELICOPTER IS LOADED AS FOLLOWS? GROSS WEIGHT……………………….………………………1,800 LB PILOT……………….140 LB, 13.5 IN. LEFT OF ''0'' MOM ARM COPILOT…………180 LB, 13.5 IN. RIGHT OF ''0'' MOM ARM. A) ADD 10 POUNDS OF WEIGHT TO THE PILOT'S SIDE. B) DECREASE THE GROSS WEIGHT 50 POUNDS. C) NO ACTION IS REQUIRED.

3721. WHAT ACTION SHOULD BE TAKEN FOR LATERAL BALANCE IF THE HELICOPTER IS LOADED AS FOLLOWS? GROSS WEIGHT……………………….………………………1,800 LB PILOT……………….100 LB, 13.5 IN. LEFT OF ''0'' MOM ARM COPILOT…………200 LB, 13.5 IN. RIGHT OF ''0'' MOM ARM. A) ADD 50 POUNDS OF WEIGHT TO THE PILOT'S SIDE. B) DECREASE THE GROSS WEIGHT 50 POUNDS. C) NO ACTION IS REQUIRED.

3722. DETERMINE THE WEIGHT AND BALANCE OF THE HELICOPTER WEIGHT ARM MOM/1000 EMPTY WEIGHT 1,495 ---- 151.593.0 PILOT AND FRONT PASSENGERS 350 64.0 ---- FUEL,( 40 GAL USABLE) 288 96.0 -- -. A) OVER GROSS WEIGHT LIMIT, BUT WITHIN CG LIMIT. B) WHITIN GROSS WEIGHT LIMIT AND AT THE AFT CG LIMIT. C) OVER GROSS WEIGHT LIMIT AND EXCEEDS THE AFT CG LIMIT.

3723. DETERMINE IF THE HELICOPTER'S CG IS WITHIN LIMITS WEIGHT MOM/1000 EMPTY WEIGHT (INCLUDING OIL) 1,025 102,705 PILOT AND PASSENGERS 345 ---- FUEL, 35 GAL --- -- -. A) OUT OF LIMITS FOR WARD. B) WITHIN LIMITS. C) OUT OF LIMITS AFT.

3724. WHAT EFFECT DOES ADDING A 185-POUND PASSENGER HAVE ON THE CG, IF PRIOR TO BOARDING THE PASSENGER, THE HELICOPTER WEIGHT 1,380 POUNDS AND THE MOMENT IS 136,647.5 POUND-INCHES?. A) THE CG IS MOVED FORWARD 1.78 INCHES. B) THE CG IS MOVED AFT 1.78 INCHES. C) THE CG IS MOVED FORWARD 2.36 INCHES.

3725. HOW IS THE CG OF THE HELICOPTER AFFECTED AFTER A FUEL BURN OF 20 GALLONS? GROSS WEIGHT PRIOR TO FUEL BURN……………………….………………………2,050 LB MOMENT………………………………………………….195,365 LB-IN FUEL ARM…………….………………………………..…..69.9 IN. A) CG SHIFTS FORWARD 1.0 INCH. B) CG SHIFTS FORWARD 0.1 INCH. C) CG SHIFTS AFT 1.0 INCH.

3726. HOW IS THE CG OF THE HELICOPTER AFFECTED WHEN ALL OF THE AUXIALIARY FUEL IS BURNED OFF? GROSS WEIGHT PRIOR TI FUEL BURN……………………………1,660 LB MOMENT……………………………………………………………...159,898.5 LB-IN A) CG MOVES AFT 0.12 INCH. B) CG MOVES FORWARD 0.78 INCH C) CG MOVES FORWARD 1.07 INCHES. A) CG MOVES AFT 0.12 INCH. B) CG MOVES FORWARD 0.78 INCH. C) CG MOVES FORWARD 1.07 INCHES.

3728. DETERMINE IF THE HELICOPTER WEIGHT AND BALANCE IS WHITIN LIMITS. WEIGHT ARM MOMENT EMPTY WEIGHT 1,495.0 101.4 1.515.93 OIL, 8 QT --- 100.5 --- FUEL, 40 GAL --- 96.0 -- - PILOT AND COPILOT 300.0 64.0 ---. A) CG 95.2 INCHES, WHITIN LIMITS. B) CG 95.3 INCHES, WEIGHT AND CG OUT OF LIMITS. C) CG 95.4 INCHES, WHITIN LIMITS.

3727. CALCULATE THE WEIGHT AND BALANCE OF THE HELICOPTER, AND DETERMINE IF THE CG IS WHITIN LIMITS. WEIGHT ARM MOM/1000 EMPTY WEIGHT 1,495.0 101.4 1,151.93 OIL, 8 QT --- 100.5 --- FUEL, 40 GAL --- 96.0 --- PILOT 160.0 64.0 ---. A) CG 90.48 INCHES, OUT OF LIMITS FORWARD. B) CG 95.32 INCHES, WHITIN LIMITS. C) CG 97.58 INCHES, WHITIN LIMITS.

3729. WHAT IS THE CG OF THE GYROPLANE AFTER A 10-GALLON FUEL BURN IF THE ORIGINAL WEIGHT WAS 1,450 POUNDS AND THE MOM/100 WAS 108 POUND-INCHES?. A) OUT OF LIMITS FORWARD. B) OUT OF LIMITS AFT. C) WHITIN LIMITS NEAR THE FORWARD LIMIT.

3730. WHAT IS THE CONDITION OF THE WEIGHT AND BALANCE OF THE GYROPLANE AS LOADED? WEIGHT MOMENT EMPTY WEIGHT 1,074 85.6 OIL, 6 QT --- 1.0 PILOT AND PASSENGER 247 ---- FUEL, 12 GAL --- -- - BAGGAGE 95 ---. A)WHITIN LIMITS. B) OVERWEIGHT. C) OUT OF LIMITS AFT.

3861.CALCULATE THE WEIGHT AND BALANCE OF THE GLIDER, AND DETERMINE IF THE CG IS WHITIN LIMITS. PILOT (FWD SEAT) ………………………………………..160 LB PASSENGER (AFT SEAT)………………………………..185 LB. A) CG 71. 65 INCHES AFT OF DATUM-OUT OF LIMITS FORWARD. B) CG 79.67 INCHES AFT OF DATUM - WHITIN LIMITS. C) CG 83.43 INCHES AFT OF DATUM-WHITIN LIMITS.

3862. HOW IS THE CG AFFECTED RADIO AND OXYGEN EQUIPMENT WEIGHING 35 POUNDS ADDED AT STATION 43.8? THE GLIDER WEIGHS 945 POUNDS WITH A MOMENT OF 78,000.2 POUND-INCHES PRIOR TO AD ING THE EQUIPMENT. A) CG SHIFTS FORWARD 0.79 INCH- OUT OF LIMITS FORWAR. B) CG SHIFTS FORWARD 1.38 INCHES-WITHIN LIMITS. C) CG SHIFTS AFT 1.38 INCHES-OUT OF LIMITS AFT.

3863. WHAT IS THE CG OF THE GLIDER IF THE PILOT AND PASSENGER EACH WEIGHT 215 POUNDS?. A) 74.69 INCHES AFT OF DATUM-OUT OF LIMITS FORWARD. B) 81.08 INCHES AFT OF DATUM-WHITIN LIMITS. C) 81.08 INCHES AFT OF DATUM-OVER MAXIMUM GROSS WEIGHT.

3887. WHAT CONSTITUTES THE PAYLOAD OF A BALLOON?. A) TOTAL GROSS WEIGHT. B) TOTAL WEIGHT OF PASSENGER, CARGO, AND FUEL. C) WEIGHT OF THE AIRCRAFT AND EQUIPMENT.

3888. THE GROSS WEIGHT OF THE BALLOON IS 1,350 POUNDS AND THE OUTSIDE AIR TEMPERATURE ( OAT) IS +51 'F, THE MAXIMUM HEIGHT WOULD BE. A) 5,000 FEET. B) 8,000 FEET. C) 10,000 FEET.

3889. THE GROSS WEIGHT OF THE BALLOON IS 1,200 POUNDS AND THE MAXIMUM HEOGHT THE PILOT NEEDS TO ATTAIN IS 5,000 FEET. THE MAXIMUM TEMPERATURE TO ACHIEVE THIS PERFORMANCE IS?. A) +37 'F. B) +70 'F. C) +97 'F.

3890. DETERMINE THE MAXIMUM PAYLOAD FOR A BALLOON FLYING AT 2,500 FEET AT AN AMBIENT TEMPERATURE OF 91 'F. A) 42O POUNDS. B) 465 POUNDS. C) 505 POUNDS.

3893. DETERMINE THE MAXIMUM WEIGHT ALLOWABLE FOR PILOT AND PASSENGER FOR A FLIGHT AT APPROXIMATELY 1,000 FEET WITH A TEMPERATURE OF 68 'F LAUNCH WITH 20 GALLONS OF PROPANE. A) 580 POUNDS. B) 620 POUNDS. C) 720 POUNDS.

3894. WHAT IS THE MIAXIMUM WEIGHT ALLOWED FOR PILOT AND PASSENGERS FOR A FLIGHT AT 5,000 FEET WITH A STANDARD TEMPERATURE? LAUNCH WITH 20 GALLONS OF PROPANE. A) 670 POUNDS. B) 760 POUNDS. C) 1,095 POUNDS.

3289. IF THE OUTSIDE AIR TEMPERATURE (OAT) AT A GIVEN ALTITUDE IS WARMER THAN STANDARD, THE DENSITY ALTITUDE IS. A) EQUAL TO PRESSURE ALTITUDE. B) LOWER THAN PRESSURE ALTITUDE. C) HIGHER TAN PRESSURE ALTITUDE.

3294. DETERMINE THE DENSITY ALTITUDE FOR THESE CONDITIONS: ALTIMETER SETTING………………………..29.95 RUNWAY TEMPERATURE…………………..+81'F AIRPORT ELEVATION………………………..5,250 FT MSL. A) 4,600 FEET MSL. B) 5,877 FEET MSL. C) 8,500 FEET MSL.

3295. DETERMINE THE PRESSURE ALTITUDE AT AN AIRPORT THAT IS 3,563 FEET MSL WITH AN ALTIMETER SETTING OF 29.96. A) 3,527 FEET MSL. B) 3,556 FEET MSL. C) 3.639 FEET MSL.

3298. DETERMINE THE DENSITY ALTITUDE FOR THESE CONDITIONS: ALTIMETER SETTING………………………..30.35 RUNWAY TEMPERATURE…………………..+25'F AIRPORT ELEVATION………………………..3,894 FT MSL. A) 2,000 FEET MSL. B) 2,900 FEET MSL. C) 3,500 FEET MSL.

3299. WHAT IS THE EFFECT OF A TEMPERATURE DECREASE AND PRESSURE ALTITUDE INCREASE ON THE DENSITY ALTITUDE FROM 90'F AND 1,250 FEET PRESSURE ALTITUDE TO 55'F AND, 1,750 FEET PRESSURE ALTITUDE?. A) 1,700 FOOT INCREASE. B) 1,300 FOOT DECREASE. C) 1,700 FOOT DECREASE.

3386. WHAT ARE THE STANDARD TEMPERATURE AND PRESSURE VALUES FOR SEA LEVEL?. A) 15'C AND 29.92''HG. B) 59'C AND 1013.2 MILLIBARS. C) 59'F AND 29.92''HG.

3394. WHICH FACTOR WOULD TEND TO INCREASE THE DENSITY ALTITUDE AT A GIVEN AIRPORT?. A) AN INCREASE IN BAROMETRIC PRESSURE. B) AN INCREASE IN AMBIENT TEMPERATURE. C) A DECREASE IN RELATIVE HUMIDITY.

3290. WHICH COMBINATION OF ATMOSPHERIC CONDITION WILL REDUCE AIRCRAFT TAKEOFF AND CLIMB PERFORMANCE?. 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.

3291. WHAT EFFECT DOES HIGH DENSITY ALTITUDE HAVE ON AIRCRAFT PERFORMANCE?. A) IT INCREASES ENGINE PERFORMANCE. B) IT REDUCES CLIMB PERFORMANCE. C) IT INCREASES TAKEOFF PERFORMANCE.

3292. WHAT IS THE EFFECT OF A TEMPERATURE INCREASE FROM 25 TO 50'F ON THE DENSITY ALTITUDE IF THE PRESSURE ALTITUDE REMAINS AT 5,000 FEET?. A) 1,200 FOOT INCREASE. B) 1,400 FOOT INCREASE. C) 1,650 FOOT INCREASE.

3293. DETERMINE THE PRESSURE ALTITUDE WITH AN INDICATED ALTITUDE OF 1,380 FEET MSL WITH AN ALTIMETER SETTING OF 28.22 AT STANDARD TEMPERATURE. A) 2,991 FEET MSL. B) 2,913 FEET MSL. C) 3,010 FEET MSL.

3296. WHAT IS THE EFFECT OF A TEMPERATURE INCREASE FROM 35 TO 50'F ON THE DENSITY ALTITUDE IF THE PRESSURE ALTITUDE REMAINS AT 3,000 FEET MSL?. A)1,000 FOOT INCREASE. B) 1,100 FOOT DECREASE. C) 1,300 FOOT INCREASE.

3297. DETERMINE THE PRESSURE ALTITUDE AT AN AIRPORT THAT IS 1,386 FEET MSL WITH AN ALTIMETER SETTING OF 29.97. A) 1,341 FEET MSL. B) 1,451 FEET MSL. C) 1,562 FEET MSL.

3300. 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.

3246. WHAT EFFECT DOES HIGH DENSITY ALTITUDE, AS COMPARED TO LOW DENSITY ALTITUDE, HAVE ON PROPELLER EFFICIENCY AND WHY. A) EFFICIENCY IS INCREASED DUE TO LESS FRICTION ON THE PROPELLER BLADES. B) EFFICIENCY IS REDUCED BECAUSE THE PROPELLER EXERTS LESS FORCE AT HIGH DENSITY ALTITUDES THAN AT LOW DENSITY ALTITUDES. C) EFFICIENCY IS REDUCED DUE TO THE INCREASED FORCE OF THE PROPELLER IN THE THINNER AIR.

3702. DETERMINE THE TOTAL TAKEOFF DISTANCE REQUIRED FOR A GYROPLANE TO CLEAR A 50 FOOT OBSTACLE IF THE TEMPERATURE IS 95'F AND THE PRESSURE ALTITUDE IS 1,700 FEET. A) 1,825 FEET. B) 1,910 FEET. C) 2,030 FEET.

3891. WHAT IS THE MAXIMUM ALTITUDE FOR THE BALLOON IF THE GROOS WEIGHT IS 1,100 POUNDS AND STANDARD TEMPERATURE EXISTS AT ALL ALTITUDES?. A) 1,000 FEET. B) 4,000 FEET. C) 5,500 FEET.

3892. WHAT IS THE MAXIMUM ALTITUDE FOR THE BALLOON IF THE GROSS WEIGHT IS 1,000 POUNDS A STANDARD TEMPERATURE EXISTS AT ALL ALTITUDES?. A) 4,000 FEET. B) 5,500 FEET. C) 11, 000 FEET.

3705. DETERMINATE THE TOTAL DISTANCE REQUIRED FOR TAKEOFF TO CLEAR A 50 FOOT OBSTACLE OAT………………………………………STD PRESSURE ALTITUDE……………..4,000 FT TAKEOFF WEIGHT…………………..2,800 LB HEADWIND COMPONENT…….. CALM. A) 1,500 FEET. B) 1,750 FEET. C) 2,000 FEET.

3706. DETERMINE THE TOTAL DISTANCE REQUIRED FOR TAKEOFF TO CLEAR A 50 FOOT OBSTACLE. OAT………………………………………STD PRESSURE ALTITUDE……………..SEA LEVEL TAKEOFF WEIGHT…………………..2,700 LB HEADWIND COMPONENT…….. CALM. A) 1,000 FEET. B) 1,400 FEET. C) 1,700 FEET.

3707. DETERMINE THE APPROXIMATE GROUND ROLL DISTANCE REQUIRED FOR TAKEOFF OAT………………………………………100'F PRESSURE ALTITUDE……………..2,000 FT TAKEOFF WEIGHT…………………..2,750 LB HEADWIND COMPONENT…….. CALM. A) 1,15O FEET. B) 1,300 FEET. C) 1,800 FEET.

3708. DETERMINE THE APROXIMATE GROUND ROLL DISTANCE REQUIRED FOR TAKEOFF OAT………………………………………95'F PRESSURE ALTITUDE……………..2,000 FT TAKEOFF WEIGHT…………………..2,500 LB HEADWIND COMPONENT……..20 KTS. A) 650 FEET. B) 850 FEET. C) 1,000 FEET.

3703. DETERMINE THE TOTAL TAKEOFF DISTANCE REQUIRED FOR A GYROPLANE TO CLEAR A 50 FOOT OBSTACLE IF THE TEMPERATURE IS STANDARD AT SEA LEVEL PRESSURE ALTITUDE. A) 950 FEET. B) 1,090 FEET. C) 1,200 FEET.

3704. APPROXIMATELY HOW MUCH ADDITIONAL TAKEOFF DISTANCE WILL BE REQUIRED FOR A GYROPLANE TO CLEAR A 50 FOOT OBSTACLE IF THE TEMPERATURE INCREASES FROM 75 TO 90' AT A PRESSURE ALTITUDE OF 2,300 FEET?. A) 160 FEET. B) 200 FEET. C) 2,020 FEET.

3732. WHAT IS THE BEST RATE OF CLIMB SPEED FOR THE HELICOPTER?. A) 24 MPH. B) 40 MPH. C) 57 MPH.

3678. APPROXIMATELY WHAT TRUE AIRSPEED SHOULD A PILOT EXPECT WITH 65 PERCENT MAXIMUM CONTINUOUS POWER AT 9,500 FEET WITH A TEMPERATURE OF 36'F BELOW STANDARD?. A) 178 MPH. B) 181 MPH. C) 183 MPH.

3679. WHAT IS THE EXPECTED FUEL CONSUMPTION FOR A 1,000 NAUTICAL MILE FLIGHT UNDER THE FOLLOWING CONDITIONS? PRESSURE ALTITUDE……………..8,000 FT TEMPERATURE………………………..22'C MANIFOLD PRESSURE…………..20.8 ''HG WIND………………………………………CALM. A)60.2 GALLONS. B) 70.1 GALLONS. C) 73.2 GALLONS.

3680.WHAT IS THE EXPECTED FUEL CONSUMPTION FOR A 500 NAUTICAL MILE FLIGHT UNDER THE FOLLOWING CONDITIONS? PRESSURE ALTITUDE……………..4,000 FT TEMPERATURE………………………..29'C MANIFOLD PRESSURE…………..21.3 ''HG WIND………………………………………CALM. A) 31.4 GALLONS. B) 36.1 GALLONS. C) 40.1 GALLONS.

3681. 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.

3682. DETERMINE THE APPROXIMATE MANIFOLD PRESSURE SETTING WITH 2,450 RPM TO ACHIEVE 65 PERCENT MAXIMUM CONTINUOUS POWER AT 6,500 FEET WITH A TEMPERATURE OF 36'F HIGHER THAN STANDARD A) 19.8'' HG B) 20.8'' HG C) 21.0'' HG. A) 19.8'' HG. B) 20.8'' HG. C) 21.0'' HG.

3698. DETERMINE THE APPROXIMATE LANDING GROUND ROLL DISTANCE PRESSURE ALTITUDE……………..1,250 FT HEADWIND…………………………….8 KTS TEMPERATURE………………………..STD. A) 275 FEET. B) 366 FEET. C) 470 FEET.

3689. DETERMINE THE TOTAL DISTANCE REQUIRED TO LAND OAT………………………………………..32'F PRESSURE ALTITUDE……………..8,000 FT WEIGHT……………………………….2,600 LB HEADWIND COMPONENT……..20 KTS OBSTACLE……………………………… 50 FT. A) 850 FEET. B) 1,400 FEET. C) 1,750 FEET.

3690. DETERMINE THE TOTAL DISTANCE REQUIRED TO LAND OAT………………………………….STD PRESSURE ALTITUDE……………..10,000 FT WEIGHT…………………………….2,400 LB WIND COMPONENT…………..CALM OBSTACLE………………………………50 FT. A) 750 FEET. B) 1,925 FEET. C) 1,450 FEET.

3691. DETERMINE THE TOTAL DISTANCE REQUIRED TO LAND OAT………………………………….90'F PRESSURE ALTITUDE………..3,000 FT WEIGHT…………………………….2,900 LB WIND COMPONENT……………10 KTS OBSTACLE………………………………50 FT. A) 1, 45O FEET. B) 1,550 FEET. C) 1,725 FEET.

3692. DETERMINE THE APPROXIMATE TOTAL DISTANCE REQUIRED TO LAND OVER A 50 FOOT OBSTACLE OAT………………………………….90'F PRESSURE ALTITUDE…………4,000 FT WEIGHT…………………………….2,800 LB HEADWIND COMPONENT………10 KTS. A) 1,525 FEET. B) 1,775 FEET. C) 1,950 FEET.

3693. DETERMINE THE APPROXIMATE LANDING GROUND ROLL DISTANCE PRESSURE ALTITUDE………………..SEA LEVEL HEADWIND…………………………………4 KTS TEMPERATURE…………………………….STD. A) 356 FEET. B) 401 FEET. C) 490 FEET.

3694. DETERMINE THE TOTAL DISTANCE REQUIRED TO LAND OVER A 50 FOOT OBSTACLE PRESSURE ALTITUDE………………..7,500 FT HEADWIND…………………………………8 KTS TEMPERATURE…………………………….32 'F RUNWAY…………………………………HARD SURFACE. A) 1,004 FEET. B) 1,205 FEET. C) 1,506 FEET.

3695. DETERMINE THE TOTAL DISTANCE REQUIRED TO LAND OVER A 50 FOOT OBSTACLE PRESSURE ALTITUDE………………..5,000 FT HEADWIND…………………………………8 KTS TEMPERATURE…………………………….41 'F RUNWAY…………………………………HARD SURFACE. A) 837 FEET. B) 956 FEET. C) 1,076 FEET.

3686. DETERMINE THE APPROXIMATE LANDING GROUND ROLL DISTANCE PRESSURE ALTITUDE………………..5,000 FT HEADWIND………………………………CALM TEMPERATURE…………………………….101 'F. A) 495 FEET. B) 545 FEET. C) 445 FEET.

3697. DETERMINE THE TOTAL DISTANCE REQUIRED TO LAND OVER A 50 FOOT OBSTACLE PRESSURE ALTITUDE………………..3,750 FT HEADWIND…………………………………12 KTS TEMPERATURE…………………………….STD. A) 794 FEET. B) 836 FEET. C) 816 FEET.

3699. DETERMINE THE TOTAL LANDING DISTANCE TO CLEAR A 50 FOOT OBSTACLE IN A GYROPLANE. THE OUTSIDE AIR TEMPERATURE (OAT) IS 75'F AND THE PRESSURE ALTITUDE AT THE AIRPORT IS 2,500 FEET. A) 521 FEET. B) 525 FEET. C) 529 FEET.

3700. APPROXIMATELY HOW MUCH ADDITIONAL LANDING DISTANCE WILL BE REQUIRED FOR A GYROPLANE TO CLEAR A 50 FOOT OBSTACLE WITH AN INCREASE IN TEMPERATURE FROM 40 TO 60'F AT 3,200 FEET PRESSURE ALTITUDE?. A) 4 FEET. B) 8 FEET. C) 12 FEET.

3701. DETERMINE THE TOTAL LANDING DISTANCE TO CLEAR A 50 FOOT OBSTACLE IN A GYROPLANE. THE OUTSIDE AIR TEMPERATURE (OAT) IS 80'F AND THE PRESSURE ALTITUDE IS 3,500 FEET. A) 521 FEET. B) 526 FEET. C) 531 FEET.

3864. HOW MANY FEET WILL THE GLIDER SINK IN 1 STATUTE MILE AT 53 MPH IN STILL AIR?. A) 144 FEET. B) 171 FEET. C) 211 FEET.

3865. AT WHAT SPEED WILL THE GLIDER ATTAIN A SINK RATE OF 5 FEET PER SECOND IN STILL AIR?. A) 75 MPM. B) 79 MPH. C) 84 MPH.

3866. HOW MANY FEET WILL THE GLIDER DESCEND AT MINIMUM SINK SPEED FOR 1 STATUTE MILE IN STILL AIR?. A) 132 FEET. B) 170 FEET. C) 180 FEET.

3867. AT WHAT SPEED WILL THE GLIDER GAIN YHE MOST DISTANCE WHILE DESCENDING 1,000 FEET IN STILL AIR?. A) 44 MPH. B) 53 MPH. C) 83 MPH.

3868. WHAT APPROXIMATE LIFT/DRAG RATIO WILL THE GLIDER ATTAIN AT 68 MPH IN STILL AIR?. A) 10.5:1. B) 21.7:1. C) 28.5:1.

3688.WHAT IS THE CROSSWIND COMPONENT FOR A LANDING ON RUNWAY 18 IF THE TOWER REPORTS THE WIND AS 220' AT 30 KTS?. A) 19 KNOTS. B) 23 KNOTS. C) 30 KNOTS.

3683. WHAT IS THE HEADWIND COMPONENT FOR A LANDING ON RUNWAY 18 IF THE TOWER REPORTS THE WIND AS 220' AT 30 KTS?. A) 19 KNOTS. B) 23 KNOTS. C) 26 KNOTS.

3684. DETERMINE THE MAXIMUM WIND VELOCITY FOR A 45' CROSSWIND IF THE MAXIMUM CROSSWIND COMPONENT FOR THE AIRPLANE IS 25 KNOTS. A) 25 KNOTS. B) 29 KNOTS. C) 35 KNOTS.

3685. WHAT IS THE MAXIMUM WIND VELOCITY FOR A 30' CROSSWIND IF THE MAXIMUM CROSSWIND COMPONENT FOR THE AIRPLANE IS 12 KNOTS?. A) 16 KNOTS. B) 20 KNOTS. C) 24 KNOTS.

3686. WITH A REPORT WIND OF NORTH AT 20 KNOTS, WHICH RUNWAY (6,29, OR 32) IS ACCEPTABLE FOR USE FOR AN AIRPLANE WITH A 13 KNOT MAXIMUM CROSSWIND COMPONENT?. A) RUNWAY 6. B) RUNWAY 29. C) RUNWAY 32.

3687. WITH A REPORT WIND OF SOUTH AT 20 KNOTS, WHICH RUNWAY (10,14, OR 24) IS APPROPRIATE FOR AN AIRPLANE WITH A 13 KNOT MAXIMUM CROSSWIND COMPONENT?. A) RUNWAY 10. B) RUNWAY 14. C) RUNWAY 24.