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Study > Manual : A flight benefits from a strong tail wind which was not forecast on arrival at ?

Question 69-1 : The landing distance required will be longer the approach path will be steeper and threshold speed higher the landing distance will be unaffected the approach path will be steeper

The strong tail wind helps carry the aircraft so less fuel is used with no delays on arrival and with a straight in approach less time spent on the approach procedure the plane will land with more fuel on board than expected .approach and landing speeds are increased the landing distance required is longer exemple 169 the landing distance required will be longer.the landing distance required will be longer.

The centre of gravity of an aeroplane is at 25% of the mean aerodynamic chord ?

Question 69-2 : The mean aerodynamic chord in relation to the leading edge the mean aerodynamic chord in relation to the trailing edge the mean aerodynamic chord in relation to the datum the aeroplane in relation to the leading edge

Longitudinal cg location is normally expressed as a percentage of the mean aerodynamic chord mac from its leading edge exemple 173 the mean aerodynamic chord in relation to the leading edge.the mean aerodynamic chord in relation to the leading edge.

To measure the mass and cg position of an aircraft it should be weighed with a ?

Question 69-3 : 3 points of support 2 points of support 1 point of support 4 points of support

exemple 177 3 points of support.3 points of support.

An aeroplane has a mean aerodynamic chord mac of 134 5 inches .the leading edge ?

Question 69-4 : 18 10% 85 50% 75 60% 10 50%

Leading edge mac is at 625 6 inches aft of the datum.the centre of gravity is at 650 inches aft of the datum 650 625 6 = 24 4 inches from leading edge mac. 24 4 / 134 5 x 100 = 18 10 %

The empty mass of an aircraft is recorded in ?

Question 69-5 : The weighing schedule and is amended to take account of changes due to modifications of the aircraft the loading manifest it differs from dry operating mass by the value of the 'useful load' the weighing schedule if changes occur due to modifications the aircraft must be re weighed always the loading manifest it differs from the zero fuel mass by the value of the 'traffic load'

The empty mass of an aircraft is recorded in the weighing schedule and is amended to take account of changes due to modifications of the aircraft .normally the aircraft is weighed. before entering in service.. every 4 years for individual aircraft.. every 9 years for fleet masses.. every time a modification takes place equipment installed or uninstalled.as the weighing procedure is long and complex the operator is allowed to adjust the empty mass of an aircraft on the weighing schedule between to weighing procedure exemple 185 the weighing schedule and is amended to take account of changes due to modifications of the aircraft.the weighing schedule and is amended to take account of changes due to modifications of the aircraft.

The maximum quantity of fuel that can be loaded into an aircraft's tanks is ?

Question 69-6 : 1196 kg 1437 kg 2302 kg 1916 kg

1 ug gallons = 3 7854 litres.400 usg x 3 7854 = 1514 litres.1514 x 0 79 = 1196 kg

The maximum quantity of fuel that can be loaded into an aircraft's tanks is ?

Question 69-7 : 1738 kg 2785 kg 2098 kg 1798 kg

2200 x 0 79 = 1738 kg exemple 193 1738 kg.1738 kg.

The basic empty mass is 4960 kg the dry operating mass is 5220 kg and the zero ?

Question 69-8 : 2410 kg 2670 kg 1590 kg 820 kg

Useful load = maximum take off mass dry operating mass..useful load = 7630 kg 5220 kg = 2410 kg exemple 197 2410 kg.2410 kg.

The basic empty mass is 4800 kg the dry operating mass is 5050 kg and the zero ?

Question 69-9 : 2960 kg 3210 kg 1800 kg 1160 kg

Useful load = the mass of the aircraft including everything and everyone contained within it at the commencement of take off the total mass of an aircraft ready for a specific type of operation excluding all usable fuel and traffic load.useful load = take off mass dry operating mass..useful load = 8010 kg 5050 kg = 2960 kg exemple 201 2960 kg.2960 kg.

Longitudinal cg location is normally expressed ?

Question 69-10 : As a percentage of the mac from its leading edge as a percentage of the mac from its trailing edge with respect to the neutral point with respect to the centre of pressure

exemple 205 as a percentage of the mac from its leading edge.as a percentage of the mac from its leading edge.

Given .basic empty mass bem 1 200 kg.balance arm of bem 3 0 m.centre of ?

Question 69-11 : 22 % of mac 29 % of mac 34 % of mac 17 % of mac

Com en/annexe php annexe=com031 226 jpg..basic mass cg was at 25% of the mean aerodynamic chord mac with an arm of 3 m . .the length of mac is 2m so the cg is at 0 5 m from leading edge mac..take off mass cg = moment/mass = 4300 / 1460 = 2 945 m..with a cg located at 2 945 m for take off it is at 0 445 m from the leading edge mac.0 445/2 x 100 = 22 25% mac.hwoarangitf .please how do you found the '0 445'm from the leading edge mac thank you..at basic mass the cg is at 25% of the mac for a chord length of 2m and 3m aft of the datum 25% of 2m is 50 cm thus the leading edge of the mac is at 2 5m aft of datum.cg location at take off will be at 2 945 2 5m = 0 445m aft of leading edge of the mac.com en/annexe php annexe=com031 226b jpg exemple 209 22 % of mac.22 % of mac.

Given the following data .distance from datum to centre of gravity 12 53 ?

Question 69-12 : 36 3% mac 47 0% mac 63 4% mac 23 1% mac

Position of the cg on the mac = distance from datum to centre of gravity distance from datum to leading edge..position of the cg on the mac = 12 53 9 63 = 2 9 m.8 m is the lenght of the mac and center of gravity is located on the mac at 2 9 m.8 m is 100% of the length 2 9m is at.2 9 x 100 / 8 = 36 25 % exemple 213 36.3% mac.36.3% mac.

At reference to determine the dry operating index doi for a dom of 35000kg and ?

Question 69-13 : Doi 40 doi 35 doi 45 doi 50

169 exemple 217 doi 40.doi 40.

Which of the following combinations of compartment centroid and maximum load is ?

Question 69-14 : 835 5 in and 3062 kg 421 5 in and 3087 kg 835 5 in and 4187 kg 421 5 in and 2059 lb

171.take care we are talking in inches and in kilograms exemple 221 835.5 in and 3062 kg.835.5 in and 3062 kg.

Given the following data calculate the cg as a %mac mean aerodynamic cord when ?

Question 69-15 : 27 5% 25% 29 25% 30 5%

.mass x arm = moment.460000 n x 15 4 m = 7084000 nm..12000 n of last minute cargo is added to a hold 10 m from the datum .12000 n x 10 m = 120000 nm..new mass is 472000 n.new moment is 7204000 nm..cg position is now 7204000 / 472000 = 15 26 m..in percentage of mean aerodynamic chord it is .lemac is at 14 m therefore cg is 1 26m from lemac.1 26 / 4 6 x 100 = 27 5% mac exemple 225 27.5%.27.5%.

What are the standard masses used for crew ?

Question 69-16 : 85 kg for flight crew 75 kg cabin crew including hand baggage 85 kg for flight crew 75 kg cabin crew not including hand baggage 88 kg for flight crew 76 kg cabin crew not including baggage 88 kg for flight crew 76 kg cabin crew including baggage

Eu ops 1 615 mass values for crew. a an operator shall use the following mass values to determine the dry operating mass .1 actual masses including any crew baggage or.2 standard masses including hand baggage of 85 kg for flight crew members and 75 kg for cabin crew members or.3 other standard masses acceptable to the authority.b an operator must correct the dry operating mass to account for any additional baggage the position of this additional baggage must be accounted for when establishing the centre of gravity of the aeroplane exemple 229 85 kg for flight crew, 75 kg cabin crew, including hand baggage.85 kg for flight crew, 75 kg cabin crew, including hand baggage.

For the medium range twin jet the datum point is located. 235 ?

Question 69-17 : 540 inches forward of the front spar 540 cm forward of the front spar on the nose of the aeroplane at the leading edge of the mean aerodynamic chord mac

In bottom of the appendix you can read .' 2 1 datum point 540inches forward of front spar fs ' exemple 233 540 inches forward of the front spar.540 inches forward of the front spar.

The chemical fluids used to charge the aircraft toilets are counted as ?

Question 69-18 : Part of the variable load part of the payload part of the basic empty mass part of the under load

exemple 237 part of the variable load.part of the variable load.

For this question use annex ecqb 031 054 v2015 01 .calculate the basic empty ?

Question 69-19 : 968 4 kg and 179 7 cm 968 4 kg and 1707000 n cm 9500 kg and 1707000 n cm 9500 kg and 179 7 cm

Ecqb03 july 2016.. .sorry we haven't yet recovered the annex we get only the question and the correct answer this is nice isn't it

For this question use annex ecqb 031 057 v2015 05 .using the loading manifest ?

Question 69-20 : 3210 lbs 3292 lbs 4460 lbs 3410 lbs

Ecqb03 july 2016.. .3735 lb 15 lb 390 120 = 3210 lbs exemple 245 3210 lbs.3210 lbs.

The bem of an aircraft is the basic empty weight of an aircraft without crew ?

Question 69-21 : Weighing schedule at the last date of weighing aircraft manual and includes unusable fuel and liquids in closed systems loading manual and includes unusable fuel operations manual and includes engine oil

The mass of an aircraft is 2000 kg and 400 kg of freight is added to a hold 2 m ?

Question 69-22 : 0 33 m aft 0 4 m forward 0 4 m aft 0 33 m forward

Change of cg = mass added x distance from hold to cg / new total mass..change of cg = 400 x 2 / 2000 + 400 = 0 33 m.we add cargo aft thus the cg will move aft exemple 253 0.33 m aft.0.33 m aft.

Once the mass and balance documentation has been signed prior to flight ?

Question 69-23 : Acceptable last minute change to the load must be documented small load changes are allowed without recalculation no load alterations are allowed acceptable last minute change to the load may be documented

See easa air ops regulation no 965/2012 .cat pol mab 105 mass and balance data and documentation exemple 257 acceptable last minute change to the load must be documented.acceptable last minute change to the load must be documented.

Using the loadsheet on the annex determine the underload and the difference ?

Question 69-24 : 3770 kg and the difference is 7170 kg 3670 kg and the difference is 3770 kg 3770 kg and the difference is 3770 kg 4770 kg and the difference is 7170 kg

Underload = allowed tl total tl.underload = 15000 kg 11230 kg = 3770 kg.difference mtom and actual tom .actual tom = om + tl.actual tom = 44400 kg + 11230 kg = 55630 kg.difference = mtom actual tom.difference = 62800 kg 55630 kg = 7170 kg exemple 261 3770 kg and the difference is 7170 kg.3770 kg and the difference is 7170 kg.

A location in the aircraft which is identified by a number designating its ?

Question 69-25 : Station moment mac index

Station is a location in the aircraft which is identified by a number designating its distance from the datum exemple 265 station.station.

The centre of gravity of a body is that point ?

Question 69-26 : Through which the sum of the forces of all masses of the body is considered to act where the sum of the external forces is equal to zero which is always used as datum when computing moments where the sum of the moments from the external forces acting on the body is equal to zero

exemple 269 through which the sum of the forces of all masses of the body is considered to act.through which the sum of the forces of all masses of the body is considered to act.

Assuming gross mass altitude and airspeed remain unchanged movement of the ?

Question 69-27 : Increased cruise range higher stall speed lower optimum cruising speed reduced maximum cruise range

With a forward cg the aircraft is 'nose heavy' he has a nose down moment thus the downforce on the tail on a steady flight must increase.the total aircraft weight increases and therefore more weight = more drag = more power = reduced maximum cruise range .with an aft cg downforce on the tail on a steady flight is decreased .less weight = less drag = less power = increased cruise range exemple 273 increased cruise range.increased cruise range.

Moment balance arms are measured from a specific point to the body station at ?

Question 69-28 : The datum the focal point the axis the centre of gravity of the aircraft

The datum is an imaginary vertical line chosen on the longitudinal axis of the aircraft specified by the designer from which all horizontal cg measurements are made . 159.in most cases the datum is located in the vicinity of the aircraft nose usually the firewall exemple 277 the datum.the datum.

The centre of gravity of an aircraft is that point through which the total mass ?

Question 69-29 : Parallel to the gravity vector always parallel to the aircraft's vertical axis at right angles to the flight path governed by the distribution of the mass within the aircraft

145.the sum of the aircraft weight acts through the center of gravity towards the earth's center exemple 281 parallel to the gravity vector.parallel to the gravity vector.

When an aircraft is stationary on the ground its total weight will act ?

Question 69-30 : Through its centre of gravity through its centre of pressure through the main wheels of its undercarriage assembly through a point defined as the datum point

Centre of gravity cg is that point through which the force of gravity is said to act on a mass and always acts parallel to the gravity vector exemple 285 through its centre of gravity.through its centre of gravity.

The weight of an aircraft which is in level non accelerated flight is said to ?

Question 69-31 : Vertically through the centre of gravity vertically through the centre of pressure vertically through the datum point always along the vertical axis of the aircraft

Centre of gravity cg is that point through which the force of gravity is said to act on a mass and always acts parallel to the gravity vector exemple 289 vertically through the centre of gravity.vertically through the centre of gravity.

The distance from the datum to the centre of gravity of a mass is known as ?

Question 69-32 : The moment arm or balance arm the index the force the moment

Balance arm is the distance from the datum to the centre of gravity of a mass exemple 293 the moment arm or balance arm.the moment arm or balance arm.

During take off you notice that for a given elevator input the aeroplane ?

Question 69-33 : The centre of gravity may be towards the aft limit the aeroplane is overloaded the centre of gravity is too far forward the centre of pressure is aft of the centre of gravity

If a very small up deflection of the horizontal stabilizer generates a downward force on the tail sufficiently strong to raise the airplane nose this is an indication that the centre of gravity may be towards the aft limit exemple 297 the centre of gravity may be towards the aft limit.the centre of gravity may be towards the aft limit.

The mass displacement caused by landing gear extension ?

Question 69-34 : Creates a longitudinal moment in the direction pitch up or pitch down determined by the type of landing gear creates a pitch up longitudinal moment does not create a longitudinal moment creates a pitch down longitudinal moment

The mass displacement caused by landing gear extension creates a longitudinal moment in the direction pitch up or pitch down determined by the type of landing gear exemple 301 creates a longitudinal moment in the direction (pitch-up or pitch-down) determined by the type of landing gear.creates a longitudinal moment in the direction (pitch-up or pitch-down) determined by the type of landing gear.

The datum used for balance calculations is chosen on the longitudinal axis of ?

Question 69-35 : But not necessarily between the nose and the tail of the aircraft and necessarily situated between the nose and the tail of the aircraft between the leading edge and trailing edge of the wing or at rotor mast for an helicopter and always at the fire wall level

The datum is an imaginary vertical line specified by the designer from which all horizontal c of g measurements are made. /com en/com031 158 jpg..in most cases the datum is located in the vicinity of the aircraft nose usually the firewall exemple 305 but not necessarily between the nose and the tail of the aircraft.but not necessarily between the nose and the tail of the aircraft.

The centre of gravity is the ?

Question 69-36 : Point where all the aircraft mass is considered to be concentrated centre of thrust along the longitudinal axis in relation to a datum line focus along the longitudinal axis in relation to a datum line neutral point along the longitudinal axis in relation to a datum line

Centre of gravity cg is that point through which the force of gravity is said to act on a mass and always acts parallel to the gravity vector exemple 309 point where all the aircraft mass is considered to be concentrated.point where all the aircraft mass is considered to be concentrated.

For the purpose of aeroplane mass and balance calculations the datum point is ?

Question 69-37 : A fixed point from which all balance arms are measured it may be located anywhere on the aeroplane's longitudinal axis or on the extensions to that axis the point through which the sum of the mass values of the aeroplane and its contents is assumed to act vertically a point near the centre of the aeroplane it moves longitudinally as masses are added forward and aft of its location a variable point that is dependent on the load distribution for its location from which all balance arms are measured

The datum point is the point on the aircraft designated by the manufacturer from which all centre of gravity measurements and calculations are made in most cases the datum is located in the vicinity of the aircraft nose usually the firewall it is not necessarily a point 'on' the aircraft exemple 313 a fixed point from which all balance arms are measured. it may be located anywhere on the aeroplane's longitudinal axis or on the extensions to that axis.a fixed point from which all balance arms are measured. it may be located anywhere on the aeroplane's longitudinal axis or on the extensions to that axis.

In calculations with respect to the position of the centre of gravity a ?

Question 69-38 : A reference plane which is chosen by the aircraft manufacturer its position is given in the aircraft flight or loading manual calculated from the loading manifest an arbitrary reference chosen by the pilot which can be located anywhere on the aircraft calculated from the data derived from the weighing procedure carried out on the aircraft after any major modification

The datum is that point on the longitudinal axis or extension thereof from which the centre of gravity of all masses are referenced its position is determined by the manufacturer and found in the loading manual and operating data manual exemple 317 a reference plane which is chosen by the aircraft manufacturer. its position is given in the aircraft flight or loading manual.a reference plane which is chosen by the aircraft manufacturer. its position is given in the aircraft flight or loading manual.

The mass of an item multiplied by it's distance from the datum is it's ?

Question 69-39 : Moment centre of gravity moment arm force

Arm moment arm is the horizontal distance in inches from the reference datum line to the center of gravity of an item.moment is the product of the weight of an item multiplied by its arm moments are expressed in pound inches lb in total moment is the weight of the airplane multiplied by the distance between the datum and the cg exemple 321 moment.moment.

The moment for an item is ?

Question 69-40 : The mass of the item multiplied by it's distance from the datum the mass of the item divided by it's distance from the datum the distance the item is from the datum divided by it's mass the square of the distance the item is from the datum divided by it's mass

The moment is the product of the mass and the balance arm exemple 325 the mass of the item multiplied by it's distance from the datum.the mass of the item multiplied by it's distance from the datum.

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