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Copyright © ASPEQ Limited 2011 1 of 16
WB-FCL5 Workbook
Subject 031: Mass and Balance – Aeroplane
Revision 7
IMPORTANT NOTE This workbook is for use in flight crew examinations ONLY and is not to be made available for any other purpose. Not all examinations will require the use of this workbook, however, when the use of this workbook is required, candidates will be directed to the appropriate diagram in the text of the question. You are not permitted to copy or remove any part of this workbook from the examination room. Once the examination has been completed, return the workbook to the exam supervisor with your examination paper. Failure to comply with these instructions may result in your examination answers not being accepted.
2 of 16 Copyright © ASPEQ Limited 2011
DIAGRAM 31.2
Loading Data – Single Reciprocating Engine Aircraft (SRE)
General Information
This loading data is for a generic small aeroplane which is configured as follows:
Monoplane
Single reciprocating engine
Constant speed propeller
Retractable undercarriage
DATUM FIREWALL
870mm
1,930mm
2,450mm
DATUM FIREWALL
870mm
1,930mm
Maximum Take-off Mass 2,000kg
Maximum Landing Mass 2,000kg
Basic Empty Mass (BEM) 1,288kg
CG at BEM 2,150mm
BEM Moment 2,769kg-m
CG Forward Limit 1,930mm
CG Aft Limit 2,450mm
CG does not change when undercarriage is extended or retracted.
Crew weight 90kg
Passenger weight use actual weights
Maximum floor loading 350kg/m2
Maximum fuel load 300 litres
Fuel Arm 2,170mm
Fuel density 0.72kg/lt (unless otherwise stated)
Copyright © ASPEQ Limited 2011 3 of 16
DIAGRAM 31.4
Seating and Baggage Arrangement (SRE)
BAGGAGE ZONE C BAGGAGE ZONE B
BAGGAGE ZONE A
FIREWALL SEATS
3 and 4
SEATS
5 and 6
SEATS
1 and 2
BAGGAGE/LOAD ZONE ARM (mm)
A 2,743
B 3,810
C 4,572
Centre of Gravity Envelope (SRE)
2,000
1,800
1,600
1,400
1,200
CENTRE OF GRAVITY (mm aft of datum)
MA
SS
(k
g)
1,900 2,000 2,2002,100 2,5002,4002,300
4 of 16 Copyright © ASPEQ Limited 2011
DIAGRAM 31.5
Loading Manifest (SRE)
ITEM MASS (kg) ARM (mm) MOMENT (kg-m)
BASIC AIRCRAFT 1,288 2,150 2,769
SEATS 1 & 2 2,007
SEATS 3 & 4 2,972
SEATS 5 & 6 3,861
BAGGAGE ZONE A 2,743
BAGGAGE ZONE B 3,810
BAGGAGE ZONE C 4,572
ZERO FUEL MASS
FUEL LOAD 2,170
RAMP MASS
SUBTRACT START, RUN-UP, TAXI
FUEL
TAKE-OFF MASS
SUBTRACT TRIP FUEL
LANDING MASS
Copyright © ASPEQ Limited 2011 5 of 16
DIAGRAM 31.6
Loading Data – Light Twin Reciprocating Engine Aircraft (LTA)
General Information
This loading data is for a generic light twin-engine aeroplane which is configured as follows:
Monoplane
Two reciprocating engines
Two counter-rotating constant speed propellers
Retractable undercarriage
DATUM
1,960mm
2,080mm
2,410mm
Maximum Take-off Mass 2,800kg
Maximum Zero Fuel Mass 2,600kg
Basic Empty Mass (BEM) 1,660kg
CG at BEM 2,120mm
BEM Moment 3,519kg-m
CG Forward Limit 2,080mm
CG Aft Limit 2,410mm
CG does not change significantly when undercarriage is extended or retracted.
Crew weight 90kg
Passenger weight use actual weights
Maximum floor loading 600kg/m2
Maximum fuel load 350 litres
Fuel Arm 2,330mm
Fuel density 0.72kg/lt (unless otherwise stated)
6 of 16 Copyright © ASPEQ Limited 2011
DIAGRAM 31.8
Seating and Baggage Arrangement (LTA)
SEATS
5 and 6 BAGGAGE ZONE D BAGGAGE ZONE C
SEATS
3 and 4
SEATS
1 and 2
BAGGAGE ZONE A BAGGAGE ZONE B
DIAGRAM 31.10
Centre of Gravity Envelope (LTA)
2,800
2,600
2,400
2,200
2000
1800
1,600
MA
SS
2,5002,4002,100 2,200 2,3001,900
CENTRE OF GRAVITY (mm aft of datum)
MA
SS
(k
g)
2,5002,4002,100 2,200 2,3002,000
CENTRE OF GRAVITY (mm aft of datum)
Copyright © ASPEQ Limited 2011 7 of 16
DIAGRAM 31.12
Loading Manifest (LTA)
ITEM MASS (kg) ARM (mm) MOMENT (kg-m)
BASIC AIRCRAFT 1,660 2,120 3,519.2
SEATS 1 & 2 1,550
SEATS 3 & 4 2,510
SEATS 5 & 6 3,440
BAGGAGE ZONE A 720
BAGGAGE ZONE B 2,570
BAGGAGE ZONE C 3,580
BAGGAGE ZONE D 4,720
ZERO FUEL MASS
FUEL LOAD 2,330
RAMP MASS
TAXI FUEL
TAKE-OFF MASS
TRIP FUEL
LANDING MASS
8 of 16 Copyright © ASPEQ Limited 2011
DIAGRAM 31.14
Loading Data – Medium Range Jet (MRJ)
General Information
This performance data is for a generic medium range jet transport aircraft which is configured as follows:
Monoplane
Two high-bypass turbo-fan engines
Retractable undercarriage
Performance Class A
Structural Data
Maximum Ramp Mass 63,030kg
Maximum Take-off Mass 62,800kg
Maximum Landing Mass 54,900kg
Maximum Zero Fuel Mass 51,300kg
Fuel Data
Maximum Fuel Load 20,175 litres
Taxi Fuel 1,200kg/hr
APU fuel consumption 115kg/hr
Fuel density 0.80kg/lt (unless otherwise stated)
Operational Cost Index 25 (“CI 25”, unless otherwise stated)
Air Conditioning
Increase fuel consumption by 1% when operating packs at “HI FLOW”
Icing
Increase fuel consumption as follows:
Engine anti-ice only 70kg/hr
Engine and wing anti-ice 180kg/hr
Loading Data
CG at BEM 10.73m
BEM Moment 370,185kg-m
CG Limits As per the C of G envelope (see Diagram 31.20)
Cargo Data
Compartment 1 Volume 16.89m3
Maximum Mass 3,300kg
Arm 9.20m
Compartment 2 Volume 21.32m3
Maximum Mass 4,200kg
Arm 22.11m
Maximum floor loading 1,600kg/m2
Copyright © ASPEQ Limited 2011 9 of 16
DIAGRAM 31.16
Passenger distribution showing balance arms. If the passenger load is low, zones B, C, and
D are the preferred seating areas.
Passenger Distribution
Balance Arms (m)
Table of Passenger Zones, Number of Passengers, and Balance Arms
ZONE NO. PAX B.A.
A 15 7.10
B 18 9.65
C 24 12.62
D 24 16.02
E 24 19.42
F 18 22.40
G 18 24.95
DIAGRAM 31.18
Loading Manifest (MRJ)
ITEM MASS (kg) ARM (m) MOMENT (kg-m)
BASIC AIRCRAFT 34,500 10.73 370,185
CREW 450* 8.00 3,598*
ZONE A 7.10
ZONE B 9.65
ZONE C 12.62
ZONE D 16.02
ZONE E 19.42
ZONE F 22.40
ZONE G 24.95
CARGO COMPARTMENT 1 9.20
CARGO
COMPARTMENT 2
22.11
FUEL – WING TANKS 16.27
FUEL – CENTRE TANK 15.01
RAMP MASS
TAXI FUEL
TAKE-OFF MASS
TRIP FUEL
LANDING MASS
* Standard crew = 2 pilots, 2 forward cabin crew and 1 aft cabin crew.
7.10 9.65
12.62
16.02
19.42
22.40 24.95
10 of 16 Copyright © ASPEQ Limited 2011
DIAGRAM 31.20
Centre of Gravity Envelope (MRJ)
65,000
60,000
55,000
50,000
45,000
40,000
35,000
4 16128 20 322824
MAXIMUM TAKE-OFF MASS 62,800kg
MAXIMUM LANDING MASS 54,900kg
MAXIMUM ZF MASS 51,300kg
CENTRE OF GRAVITY LIMITS (%MAC)
4 128 16 20 24 28 32
AIR
CR
AF
T M
AS
S (
kg
)
Copyright © ASPEQ Limited 2011 11 of 16
DIAGRAM 31.22
Horizontal Stabilizer Trim Setting (MRJ)
The mean aerodynamic chord (MAC) extends from 15.64m aft of the datum to 19.00m aft of the
datum. Trim settings may be expressed as either %MAC or Stabiliser Trim Units.
1
2
3
4
5
6
0 10 20155 25 30
CENTRE OF GRAVITY (%MAC)
ST
AB
ILIS
ER
TR
IM U
NIT
SNOSEDOWN
NOSEUP
FLAPS 5
FLAPS 15
10 20155 25 30
CENTRE OF GRAVITY (%MAC)
ST
AB
ILIS
ER
TR
IM U
NIT
SNOSEDOWN
NOSEUP
FLAPS 5
FLAPS 15
16.6016.4016.2016.0015.8015.60 16.80
MOMENT ARM (m)
12 of 16 Copyright © ASPEQ Limited 2011
DIAGRAM 31.24
Fuel Index Correction Table
Fuel Mass (kg) Index Units Fuel Mass (kg) Index Units
500 -1.0 9,330 -0.3
750 -1.5 9,580 -0.9
1,000 -1.9 9,830 -1.5
1,250 -2.3 10,080 -2.1
1,500 -2.6 10,330 -2.7
1,750 -3.0 10,580 -3.3
2,000 -3.3 10,830 -3.9
2,500 -3.7 11,080 -4.5
3,000 -4.3 11,330 -5.1
3,500 -4.7 11,580 -5.7
4,000 -5.1 11,830 -6.3
4,500 -5.4 12,080 -6.9
5,000 -5.7 12,330 -7.5
5,500 -5.9 12,580 -8.1
6,000 -6.0 12,830 -8.7
6,500 -6.1 13,080 -9.3
7,000 -5.9 13,330 -9.9
7,500 -5.0 13,580 -10.5
7,670 -4.6 13,830 -11.1
7,830 -4.1 14,080 -11.7
8,000 -3.7 14,330 -12.3
8,170 -3.2 14,580 -12.9
8,330 -2.6 14,830 -13.5
8,500 -2.1 15,080 -14.1
8,630 -1.6 15,330 -14.8
8,750 -1.1 15,580 -15.4
8,880 -0.6 15,830 -16.3
9,000 -0.1 16,080 -17.1
Tanks 1 and 2 full 9,080 +0.3 Centre tank full 16,140 -17.3
Usable fuel quantities in lines = 20kg (included in the tables). Interpolation not necessary!
For mass figures not printed in these tables the index of the next higher mass is applicable.
Copyright © ASPEQ Limited 2011 13 of 16
DIAGRAM 31.26
ITEM MASS (kg)
BASIC AIRCRAFT 34,500
CREW 450
ZONE A 609
ZONE B 957
ZONE C 870
ZONE D 936
ZONE E 1,120
ZONE F 870
ZONE G 696
CARGO COMPARTMENT 1 3,200
CARGO COMPARTMENT 2 4,400
FUEL – WING TANKS 6,600
FUEL – CENTRE TANK 0
RAMP MASS 55,208
DIAGRAM 31.28
ITEM MASS (kg) ARM (mm) MOMENT (kg-m)
BASIC AIRCRAFT 1,660 2,120 3,519.2
SEATS 1 & 2 85 1,550 131.75
SEATS 3 & 4 170 2,510 426.7
SEATS 5 & 6 0 3,440 0
BAGGAGE ZONE A 50 720 36
BAGGAGE ZONE B 0 2,570 0
BAGGAGE ZONE C 120 3,580 429.6
BAGGAGE ZONE D 0 4,720 0
ZERO FUEL MASS
FUEL LOAD 300 2,330
RAMP MASS
TAXI FUEL 20 2,330
TAKE-OFF MASS
TRIP FUEL 220 2,330
LANDING MASS
14 of 16 Copyright © ASPEQ Limited 2011
DIAGRAM 31.30
ITEM MASS (kg)
BASIC AIRCRAFT 1,660
SEATS 1 & 2 85
SEATS 3 & 4 170
SEATS 5 & 6 0
BAGGAGE ZONE A 50
BAGGAGE ZONE B 0
BAGGAGE ZONE C 120
BAGGAGE ZONE D 0
ZERO FUEL MASS
FUEL LOAD 300
RAMP MASS
TAXI FUEL 20
TAKE-OFF MASS
DIAGRAM 31.32
ITEM MASS (kg)
BASIC AIRCRAFT 34,500
CREW 450
ZONE A 609
ZONE B 957
ZONE C 870
ZONE D 936
ZONE E 1,120
ZONE F 870
ZONE G 696
CARGO COMPARTMENT 1 3,200
CARGO COMPARTMENT 2 4,400
FUEL – WING TANKS 6,600
FUEL – CENTRE TANK 0
RAMP MASS
TAXI FUEL -120
TAKE-OFF MASS
Copyright © ASPEQ Limited 2011 15 of 16
DIAGRAM 31.34
16 of 16 Copyright © ASPEQ Limited 2011
DIAGRAM 31.36