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Question 88-1 : Which section of the aircraft flight manual describes the centre of gravity limits of the aircraft ? [ Attainment AIM ]

The aircraft limitations section.

An aircraft flight manual afm is a document published by the aircraft manufacturer containing detailed information for the operation of the aircraft, such as the recommended aircraft operating technique for normal, abnormal and emergency operation together with the aircraft performance that should be achieved when the aircraft is operated in accordance with these procedures...a typical afm may contain the following sections... section 1 general. section 2 limitations. section 3 emergency procedures. section 4 normal procedures. section 5 performance. section 6 weight and balance. section 7 description and operation of the airplane and its systems. section 8 airplane handling, servicing and maintenance. section 9 supplements. section 10 operating tips..the limitations section contains only those limitations required by regulation or that are necessary for the safe operation of the aircraft, powerplant, systems, and equipment. it includes operating limitations such as cg and load limits , instrument markings, color coding and basic placards.

Question 88-2 : When must an operator ensure an aircraft is weighed ?

Every 4 years for individual aircraft.

A good rule for these questions is given by the wording 'individual' = 4 years'fleet' = 9 yearsthe other regulation often used is reweighing can be required whenever the cumulative change to the dom exceeds +/ 0.5% of the mlm.for example take the mrjt from cap 696 max landing mass is 54 900 kg x 0.5% = 274.5 kg.if any change or modification causes a weight gain or loss of more than 274.5 kg, then the aircraft must be revised. this revised dom can be determined by actual weighing or calculation.amc1 cat.pol.mab.100 b the mass and centre of gravity cg position of an aircraft should be revised whenever the cumulative changes to the dry operating mass exceed 0.5% of the maximum landing mass or, for aeroplanes, the cumulative change in cg position exceeds 0.5% of the mean aerodynamic chord. exemple 192 Every 4 years for individual aircraft.

Question 88-3 : An aeroplane must be re weighed at certain intervals. when an operator uses 'fleet masses' and provided that changes have been correctly documented, this interval is… ?

9 years for each aeroplane.

If any changes are known, properly documented and also do not change the dom by more than +/ 0.5% of the mlm, then there is no need to reweigh.according to 'easa air ops cat.pol.mab.100 mass and balance, loading'. b the operator shall establish the mass and the cg of any aircraft by actual weighing prior to initial entry into service and thereafter at intervals of four years if individual aircraft masses are used, or nine years if fleet masses are used. the accumulated effects of modifications and repairs on the mass and balance shall be accounted for and properly documented. aircraft shall be reweighed if the effect of modifications on the mass and balance is not accurately known. exemple 196 9 years for each aeroplane.

Question 88-4 : Which one of the following statements below best describes the centre of gravity cg of an aircraft ?

The cg is the point at which the total weight is assumed to be concentrated.

Starting with the cap 696 definition 'the centre of gravity cg is that point through which the force of gravity is said to act on a mass.'the force of gravity acting on a mass gives us weight. so to simply the cap definition the cg is the point through which the weight acts.an aircraft is constructed of many parts, all of which contribute to the weight. the cg is the overall point at which they act along the longitudinal axis.looking at the answers 'the cg is the point at which the sum of the balance arms is nil' > incorrect. balance arms are just the distance from the datum, not the effect.'the cg is the point at which the total weight is assumed to be concentrated' > correct. as described above.'the cg is the point at which the sum of the values of the moments is not zero' > incorrect. at the cg the sum of the weight moments is zero.'the cg is the point at which the total weight is applied and acts in the longitudinal direction' > incorrect. the weight acts vertically downwards with gravity. exemple 200 The cg is the point at which the total weight is assumed to be concentrated.

Question 88-5 : Which one of the following statements below best describes the centre of gravity cg of an aircraft ?

The cg is a theoretical point where all the mass is said to be concentrated.

Centre of gravity cg is the point along the longitudinal axis about which an aircraft would balance if it was possible to suspend it at that point. it is the mass centre of the aircraft or the theoretical point at which the entire mass of the aircraft is assumed to be concentrated and acts vertically downward, parallel to the gravity vector in a level flight or in a steady climb or descent.the cg is not necessarily a fixed point, its location depends on the distribution of weight in the aircraft, but must remain within certain forward and aft limits, for reasons of stability, control and structure, considering both the flight and ground requirements.also, the limitations section contains only those limitations required by regulation or that are necessary for the safe operation of the aircraft, powerplant, systems, and equipment. it includes operating limitations such as cg and load limits , instrument markings, color coding and basic placards. exemple 204 The cg is a theoretical point where all the mass is said to be concentrated.

Question 88-6 : During preparation for take off the flight crew received an acars load sheet message with the note prelim on the header...five minutes later, the ground staff provides a paper copy of the load sheet with the note final on the header. the commander realizes that there are differences between the ?

The commander shall use the paper copy because it is the final version of the load sheet.

Taking the question scenario step by step step 1 during preparation for take off the flight crew received an acars load sheet message with the note prelim on the header. a preliminary load sheet is produced in advance of the flight's departure in order for the crew to plan fuel, often before check in closes, and is based on expected passenger numbers. for example, on an a380, this information is necessary to distribute the correct amount of fuel to the tail trim tank. receiving a load sheet via acars, printed in the cockpit is a normal situation.step 2 five minutes later, the ground staff provides a paper copy of the load sheet with the note final on the header. receiving a second load sheet by hand on paper is also a normal situation. this load sheet has final noted as a header and supersedes the previous prelim version. this is produced once check in has closed and has all the actual figures for the flight. step 3 the commander realises that there are differences between the masses on the paper copy and the acars message. this is normal as the final passenger and baggage figures at the close of check in will differ from the expected totals.step 4 the commander shall use the paper copy because it is the final version of the load sheet. this is the correct answer. the final over rules the earlier prelim load sheet. exemple 208 The commander shall use the paper copy because it is the final version of the load sheet.

Question 88-7 : According to the applicable operational requirements, which one of the following statements is correct regarding the weighing and re weighing procedure of an aircraft ?

Weighing should be accomplished in an enclosed building.

Easa air ops cat.pol.mab.100 mass and balance, loading b the operator shall establish the mass and the cg of any aircraft by actual weighing prior to initial entry into service and thereafter at intervals of four years if individual aircraft masses are used, or nine years if fleet masses are used. the accumulated effects of modifications and repairs on the mass and balance shall be accounted for and properly documented. aircraft shall be reweighed if the effect of modifications on the mass and balance is not accurately known. easa air ops amc1 cat.pol.mab.100 b mass and balance, loading c when weighing an aircraft, normal precautions should be taken consistent with good practices such as 1 checking for completeness of the aircraft and equipment.. 2 determining that fluids are properly accounted for.. 3 ensuring that the aircraft is clean. and. 4 ensuring that weighing is accomplished in an enclosed building.the operator must also account for and document the accumulated effects of modifications and repairs between weighings, by either weighing the equipment added or removed, or by using standard masses. it must re weighed, only if the accumulated effects of these modifications lead to a change of the dom by more than 0.5% of the mlm or the cg shifts by more than 0.5% of the mac. exemple 212 Weighing should be accomplished in an enclosed building.

Question 88-8 : Due to variations in the actual passenger distribution, cargo loading, or fuel distribution in comparison with the data used during the pre flight preparation of the mass and balance documentation, the operator 1 which is/are 2 restrictive than the certified cg limits. ?

1 defines operational cg limits. 2 more

The operator is responsible for producing mass and balance documentation before each flight specifying the load and distribution so that the aircraft commander can determine that the mass and balance limits are not exceeded...when determining the final cg position for flight, there will inevitably be inaccuracies in the loadsheet, in the actual mass of the item and its position on the aircraft. fuel consumption, fuel transfer, passenger movement, crew movement and configuration changes in flight need to be accounted for...also, both the cg position and the safe envelope evolve throughout the flight. indeed, the weight of the aircraft evolves mainly as fuel is burned. as for the cg, its position is sensitive to various phenomena ranging from landing gear, flaps and slats position to passengers or cabin crew movements from one end of the cabin to the other...to allow a margin of safety for these variations, the certified cg limits are reduced to the operational limits, i.e. the operational cg limits are more restrictive than the certified cg limits, because error margins have been taken into account...the operational cg limits are determined by the operator one for take off and another one for zero fuel...although there were attempts at developing systems to measure the aircraft weight and cg position, no robust solution has yet been found. the best way to make sure that the cg remains within a safe envelope throughout the flight, is to both define an operational envelope that includes safety margins and to perform a correct cg calculation. exemple 216 (1) defines operational cg limitsxsx (2) more

Question 88-9 : Where can information on the cg limits of an aircraft be found ?

Aircraft flight manual.

The aircraft flight manual afm is a document provided by the aircraft manufacturer that contains information and instructions on the operation of a specific aircraft. it is a legally required document and must be carried on board the aircraft at all times. it includes the following information... description of the aircraft's systems and dimensions/operating envelope.. normal and abnormal procedures.. aircraft limitations maximum weights, cg limits.. recent changes to aircraft operating techniques.. performance data/calculation techniques. exemple 220 Aircraft flight manual.

Question 88-10 : The basic empty mass bem and the basic empty mass centre of gravity cg position are noted in… ?

The weighing report.

The basic empty mass bem and the basic empty mass center of gravity cg position are typically noted on the aircraft weighing report. this report is prepared after the aircraft has been weighed, and it provides important information about the weight and balance of the aircraft. the information from the weighing report is used to calculate the weight and balance for each flight, and this information is typically recorded on the load and trim sheet. so, while the bem and cg position are not directly noted on the load and trim sheet, they are derived from the information on the weighing report and used to complete the load and trim sheet. exemple 224 The weighing report.

Question 88-11 : The mean aerodynamic chord published in the flight manual of an aeroplane starts at 520 mm and ends at 1700 mm from the datum line. the centre of gravity of a loaded aeroplane is 30% mac...determine the associated distance of the cg position to the datum ?

874 mm

For the swept wing aircraft, it is more convenient, for aerodynamic purposes, to relate the cg position to the mean aerodynamic chord mac of a wing. in this case the cg is expressed as a percentage of its position along the mac %mac from the leading edge lemac.for this question, 30% mac means that the cg is 30% along the mac length. mac length = 1 700 mm 520 mm = 1 180 mm. this corresponds to 1 180 mm x 0.30 = 354 mm aft from the lemac.the lemac is 520 mm aft from the datum, thus the cg position is 520 mm + 354 mm = 874 mm aft of the datum. exemple 228 874 mm

Question 88-12 : An aeroplane with one nose landing gear and two main landing gears is weighed on jacks. based on the following readouts, what is the aircraft bem and cg position nose jack positioned at 161 inches aft of datum reading 6848 kg.each main wheel jack positioned at 757 inches aft of datum reading 11 873 ?

30 594 kg and 623.6 in

The nose gear wheel load is 6848 kg..the main gear wheels load is 2 x 11 873 kg = 23 746 kg two wheels with a single wheel load of 11 873 kg.total mass of aircraft = bem = 6848 kg + 23 746 kg = 30 594 kgmoment is the turning force created by the mass acting over a distance or arm and is calculated by multiplying the arm by the mass or weight moment = arm x mass or weight.moments aft of the datum are by convention positive and moments forward of the datum are negative.the centre of gravity cg can be found by adding all the moments and then dividing the total moment by the total mass or weight cg =total moment / total weight.cg = total moment / total weight = 23 746 kg x 757 in + 6848 kg x 161 in / 30 594 kg = 19 078 250 kg in / 30 594 kg = 623.6 in aft of datum. exemple 232 30 594 kg and 623.6 in

Question 88-13 : The cg is at 25% mac. where is it located ?

Behind the leading edge of the mean aerodynamic chord lemac.

.generally, the centre of gravity cg is expressed as a distance l relative to a datum or reference point, but cg is usually expressed in swept wing aircraft as a distance relative to the mean aerodyanmic chord mac of a wing. the mac mean aerodynamic chord represents the chord of an imaginary airfoil that has the same aerodynamic characteristics as the actual wing. to be more specific, the cg is expressed as a percentage of its position along the mac %mac from the leading edge le , also called lemac.lemac this is the leading edge of the mean aerodynamic chord. it represents 0% of the mac.temac this is the rear edge of the mac and is considered 100% of the mac.if the cg is at a distance l from the datum, then the correct formula to calculate the cg position as a percentage of the mac is l lemac /mac x 100.the cg is at 25% mac, which means it is 25% of the chord length back from the lemac. this means that the cg is located behind the leading edge of the mean aerodynamic chord lemac.note the option 'forward of the trailing edge of the mean aerodynamic chord temac ' is technically true, but it describes the position in relation to the temac which is normally given as a distance and not as a percentage of mac. exemple 236 Behind the leading edge of the mean aerodynamic chord (lemac).

Question 88-14 : The formula l lemac /mac x100 is used to calculate the cg position as a percentage of the mac. if lemac is the distance from the datum to the leading edge and mac is the length of the mean aerodynamic chord, l is the distance between the cg and the... ?

Datum.

..generally, the centre of gravity cg is expressed as a distance l relative to a datum or reference point, but cg is usually expressed in swept wing aircraft as a distance relative to the mean aerodyanmic chord mac of a wing. the mac mean aerodynamic chord represents the chord of an imaginary airfoil that has the same aerodynamic characteristics as the actual wing. to be more specific, the cg is expressed as a percentage of its position along the mac %mac from the leading edge le , also called lemac.... lemac this is the leading edge of the mean aerodynamic chord. it represents 0% of the mac.. temac this is the rear edge of the mac and is considered 100% of the mac....if the cg is at a distance l from the datum, then the correct formula to calculate the cg position as a percentage of the mac is... l lemac /mac x 100 exemple 240 Datum.

Question 88-15 : In the formula to calculate the cg position as a percentage of the mean aerodynamic chord, l lemac /mac x 100, what does the l represent ?

Cg distance from datum

The formula to calculate the cg position as a percentage of the mean aerodynamic chord is l lemac /mac x 100where,mac the length of the mean aerodynamic chord.lemac the distance of the mean aerodynamic chord leading edge from the datum.and l = cg distance from datum temac the distance of the mean aerodynamic chord trailing edge from the datum generally, the centre of gravity cg is expressed as a distance l relative to a datum or reference point, but cg is usually expressed in swept wing aircraft as a distance relative to the mean aerodynamic chord mac of a wing. to be more specific, the cg is expressed as a percentage of its position along the mac %mac from the leading edge le , also called lemac.if the cg is at a distance l from the datum, then the correct formula to calculate the cg position as a percentage of the mac is l lemac /mac x 100. exemple 244 Cg distance from datum

Question 88-16 : The mass of an aircraft is 1950 kg..if 450 kg is added to a cargo hold 1.75 metres from the loaded centre of gravity cg..the loaded cg will move ?

33 cm.

Change of cg = mass added x distance from hold to cg / new total mass..change of cg = 450 x 1.75 / 1950 + 450..change of cg = 0.3281 m 33 cm. exemple 248 33 cm.

Question 88-17 : If nose wheel moves aft during gear retraction, how will this movement affect the location of the centre of gravity cg on the aircraft ?

It will cause the cg to move aft.

If the nose wheel moves aft, the cg moves aft...the 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 252 It will cause the cg to move aft.

Question 88-18 : Where is the centre of gravity of the aeroplane in the diagram.. 185 ?

26.57 cm forward of datum.

Total moments.1 x 1750 + 2.5 x 8130 = 22075 n..sum of total moments / sum of total weight = cg position..22075 n / 9880 kg = 2.2343..2.5 2.2343 = 0.2657 m 26.57 cm. exemple 256 26.57 cm forward of datum.

Question 88-19 : Given..total mass 2900 kg.cg location station 115.aft cg limit station 116..the maximum mass that can be added at station 130 is ?

207 kg.

Mass added / old total mass = change of cg / distance from hold to new cg..mass added = change of cg / distance from hold to new cg x old total mass..mass added = 116 115 / 130 116 x 2900..mass added = 207 kg. exemple 260 207 kg.

Question 88-20 : Given..total mass 7500 kg.centre of gravity cg location station 80.5.aft cg limit station 79.5..how much cargo must be shifted from the aft cargo compartment at station 150 to the forward cargo compartment at station 30 in order to move the cg location to the aft limit ?

62.5 kg.

Mass moved / total mass = change of cg / distance moved..mass moved = change of cg x total mass / distance moved..mass moved = 1 x 7500 kg / 150 30.mass moved = 7500 / 120.mass moved = 62.5 kg....you need to move cg from station 80.5 to station 79.5. exemple 264 62.5 kg.

Question 88-21 : A jet aeroplane, with the geometrical characteristics shown in the appendix, has a take off weight w of 460 000 n and a centre of gravity point g on annex located at 15.40 m from the zero reference point..at the last moment the station manager has 12 000 n of freight added in the forward compartment ?

27.5 %.

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 from the zero reference point...in percentage of mean aerodynamic chord it is.lemac leading edge mean aerodynamic chord is at 14 m therefore cg is at 1.26m from lemac 15.26m 14m..1.26 / 4.6 x 100 = 27.5% mac. exemple 268 27.5 %.

Question 88-22 : The total mass of an aeroplane is 9000 kg. the centre of gravity cg position is at 2.0 m from the datum line. the aft limit for cg is at 2.1 m from the datum line..what mass of cargo must be shifted from the front cargo hold at 0.8 m from the datum to the aft hold at 3.8 m , to move the cg to the ?

300 kg.

2.1 2 x 9000 = mass to moved x 3.8 0.8..900 = mass to moved x 3..mass to moved = 900 / 3 = 300 kg. exemple 272 300 kg.

Question 88-23 : Assume.aircraft actual mass 4750 kg.centre of gravity at station 115.8..what will be the new position of the centre of gravity if 100 kg is moved from the station 30 to station 120 ?

Station 117.69

Mass moved / total mass = change of cg / distance moved..mass moved x distance moved / total mass = change of cg..100 x 90 /4750 = 1.89..new cg location 115.8 + 1.89 = 117.69. exemple 276 Station 117.69

Question 88-24 : Given.aircraft mass 36000 kg.centre of gravity cg is located at station 17 m..what is the effect on cg location if you move 20 passengers total mass 1600 kg from station 16 to station 23 ?

It moves aft by 0.31 m.

We move passangers aft, thus the cg will move aft...mass moved / total mass = change of cg / distance moved..change of cg = mass moved x distance moved / total mass..change of cg = 1600 x 7 / 36000 = 0.31 m. exemple 280 It moves aft by 0.31 m.

Question 88-25 : Given the following information, calculate the loaded centre of gravity cg .. 197 ?

56.53 cm aft datum.

Img133.centre of gravity = 1 369 350 / 24224 = 56.528 aft of datum. exemple 284 56.53 cm aft datum.

Question 88-26 : Given are the following information at take off..given that the flight time is 2 hours and the estimated fuel flow will be 1050 litres per hour and the average oil consumption will be 2.25 litres per hour..the specific density of fuel is 0.79 and the specific density of oil is 0.96..calculate the ?

61.28 cm aft of datum.

Fuel = 2100 l x 0.79 = 1659 kg..huile = 4.5 l x 0.96 = 4.32 kg.. 134.centre of gravity at landing = 1382449.2 / 22560.68 = 61.28 aft of datum. exemple 288 61.28 cm aft of datum.

Question 88-27 : Given that the total mass of an aircraft is 112000 kg with a centre of gravity position at 22.62 m aft of the datum..the centre of gravity limits are between 18 m and 22 m..how much mass must be removed from the rear hold 30 m aft of the datum to move the centre of gravity to the middle of the ?

29344 kg.

.mass moved / total mass = change of cg / distance moved..mass moved = change of cg x total mass / distance moved..mass moved = 22.62 20 x 112000 kg / 30 20..mass moved = 293440 kg / 10..mass moved = 29344 kg...notice the middle of the limits is at 20m cg limits are between 18 m and 22 m. exemple 292 29344 kg.

Question 88-28 : The total mass of an aeroplane is 145000 kg and the centre of gravity limits are between 4.7 m and 6.9 m aft of the datum. the loaded centre of gravity position is 4.4 m aft..how much mass must be transferred from the front to the rear hold in order to bring the out of limit centre of gravity ?

7500 kg.

Change in mass / total mass = change in cg / total distance moved..change in cg = 0.3 from 4.4 m to reach 4.7 m.total distance moved = distance between front hold and rear hold = 8.7 m 2.9 m = 5.8 m...change in mass = total mass x change in cg / total distance moved..change in mass = 145000 x 0.3 /5.8 = 7500 kg. exemple 296 7500 kg.

Question 88-29 : With respect to multi engine piston powered aeroplane, determine the block fuel moment lbs.in. in the following conditions.basic empty mass 3 210 lbs..one pilot 160 lbs..front seat passenger 200 lbs..centre seat passengers 290 lbs total..one passenger rear seat 110 lbs..baggage in zone 1 100 ?

56160.

Block fuel 100 us gal x 6 lbs = 600 lbs.. 141.600 x 93.6 = 56160. exemple 300 56160.

Question 88-30 : With respect to a multi engine piston powered aeroplane, determine the total moment lbs.in at landing in the following conditions.basic empty mass 3210 lbs..one pilot 160 lbs..front seat passenger 200 lbs..centre seat passengers 290 lbs total..one passenger rear seat 110 lbs..baggage in zone 1 100 ?

401338 lbs.in

Take off moment 432226 lbs.in..trip fuel moment 55 x 6 = 330 330 x 93.6 = 30888 lbs.in..ldg 432226 30888 = 401338 lbs.in.. it's given take off moment so 3 us gal. for start up and taxi has already been burned, therefore 55, not 58. exemple 304 401338 lbs.in

Question 88-31 : Determine the cg location at take off in the following conditions.basic empty mass 3210 lb..one pilot 160 lb..front seat passenger 200 lb..centre seat passengers 290 lb total..one passenger rear seat 110 lb..baggage in zone 1 100 lb..baggage in zone 4 50 lb..zero fuel mass 4120 lb..moment at zero ?

91.92 inches aft of datum.

Img141..centre of gravity at take off = 432226.2 / 4702 = 91.92 aft of datum. exemple 308 91.92 inches aft of datum.

Question 88-32 : With respect to a single engine piston powered aeroplane, determine the zero fuel moment lbs.in./100 in the following conditions.basic empty mass 2415 lbs..arm at basic empty mass 77,9 in..cargo zone a 350 lbs..baggage zone b 35 lbs..pilot and front seat passenger 300 lbs total.. 204 ?

2548,8.

Img142 exemple 312 2548,8.

Question 88-33 : The aeroplane has a mass of 51 000 kg in the cruise. the range of safe cg positions, as determined from the appropriate graph in the loading manual, is.. 1050 ?

Forward limit 4% aft limit 29.7% mac.

exemple 316 Forward limit 4% aft limit 29.7% mac.

Question 88-34 : Considering the annex attached to the 50 000 kg mass, determine the displacement of the front limit of the center of gravity when moving from the clean configuration to the flaps and landing gear landing configuration ?

The centre of gravity move back from 4% to 5% mac.

exemple 320 The centre of gravity move back from 4% to 5% mac.

Question 88-35 : Using the weight and balance graph provided in the appendix, determine the range of permissible center of gravity positions for the maximum landing weight of 56245 kg ?

From 5% to 29.2% mac.

exemple 324 From 5% to 29.2% mac.

Question 88-36 : Prior to departure an aircraft is loaded with 16500 litres of fuel at a fuel density of 0.78. this is entered into the load sheet as 16500 kg and calculations are carried out accordingly..as a result of this error, the aircraft is ?

Lighter than anticipated and the calculated safety speeds will be too high.

The aircraft is lighter than anticipated 16500 kg entered into the load sheet instead of 12870 kg...the calculated safety speeds v1, vr, v2 will be too high, they have been computed for an heavier aircraft. you will get airborne earlier you will have much greater margins. exemple 328 Lighter than anticipated and the calculated safety speeds will be too high.

Question 88-37 : An additional baggage container is loaded into the aft cargo compartment but is not entered into the load and trim sheet..the aeroplane will be heavier than expected and calculated take off safety speeds ?

Will give reduced safety margins.

exemple 332 Will give reduced safety margins.

Question 88-38 : Fuel loaded onto an aeroplane is 15400 kg but is erroneously entered into the load and trim sheet as 14500 kg..this error is not detected by the flight crew but they will notice that ?

Speed at which the airplane will leave the ground will be higher than expected.

The airplane is heavier than the pilots think it is... v1 will be reached later, the aeroplane will rotate later than expected..the crew did not detect the error, thus v1 will not change. exemple 336 Speed at which the airplane will leave the ground will be higher than expected.

Question 88-39 : Which of the following is unlikely to have any effect on the position of the centre of gravity on an aeroplane in flight ?

Changing the tailplane horizontal stabiliser incidence angle.

Trimming the stabiliser is a response to a cg change. it does not move the cg. exemple 340 Changing the tailplane (horizontal stabiliser) incidence angle.

Question 88-40 : Which of the following is unlikely to have any effect on the position of the centre of gravity on an aeroplane in flight ?

Changing the tailplane horizontal stabiliser incidence angle.

Trimming the stabiliser is a response to a cg change. it does not move the cg. exemple 344 Changing the tailplane (horizontal stabiliser) incidence angle.


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