1. Cargas de Diseño
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VIADUCTO AEROPUERTO DE ORURO
CARGAS DE DISEÑO
Avión Boing 737‐300
Distancia entre ejes delantero y trasero del tren de aterrizaje: 12.45m
Distancia entre puntos de apoyo del tren trasero: 5.23m
Distancia entre ruedas de un punto de apoyo del eje trasero: 0.77m
Condición 1: Rodaje por la pista
Máximo peso total: 140,000 lb.
Máxima carga transmitida en un punto de apoyo del tren trasero: 63,000 lb. (45%)
Coeficiente de impacto (AASHTO 3.8), Longitud de cálculo=12m: 30% (1.3)
Carga estática equivalente de diseño: 81,900 lb (37,150 kgf)
Fuerza de frenado (μ=0.8): 112,000 lb (50,802 kgf).
Condición 2: Aterrizaje
Máximo peso total: 114,000 lb.
Máxima carga transmitida en un punto de apoyo del tren trasero: 57,000 lb. (50%)
Coeficiente de impacto en el contacto del tren de aterrizaje con la pista (Ref.1, Ref.2): 50%
(1.5)
Carga estática equivalente de diseño: 85,500 lb (38,780 kgf)
Avión Hércules C‐130
Distancia entre ejes: 9.09m ‐1.52m
Distancia entre puntos de apoyo del tren trasero: 4.34m
Condición 1: Rodaje por la pista
Máximo peso total: 155,000 lb.
Máxima carga transmitida a cada lado del tren trasero: 69,750 lb. (45%)
Coeficiente de impacto (AASHTO 3.8), Longitud de cálculo=12m: 30% (1.3)
Carga estática equivalente de diseño: 90,675 lb (41,130 kgf)
Fuerza de frenado (μ=0.8): 124,000 lb (56,245 kgf).
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Condición 2: Aterrizaje
Máximo peso total: 130,000 lb.
Máxima carga transmitida a cada lado del tren trasero: 65,000 lb. (50%)
Coeficiente de impacto en el contacto del tren de aterrizaje con la pista (Ref.1, Ref.2): 50%
(1.5)
Carga estática equivalente de diseño: 97,500 lb (44,225 kgf)
Carga estática equivalente de diseño en cada rueda trasera: 48,750 lb (22,112 kgf)
Avión BAE 146‐200
Distancia entre ejes delantero y trasero del tren de aterrizaje: 11.20m
Distancia entre puntos de apoyo del tren trasero: 4.72m
Condición 1: Rodaje por la pista
Máximo peso total: 42,200 kgf.
Máxima carga transmitida en un punto de apoyo del tren trasero: 18,990 kgf. (45%)
Coeficiente de impacto (AASHTO 3.8), Longitud de cálculo=12m: 30% (1.3)
Carga estática equivalente de diseño: 24,687 kgf
Fuerza de frenado (μ=0.8): 33,760 kgf
Condición 2: Aterrizaje
Máximo peso total: 36,740 kgf. Máxima carga transmitida en un punto de apoyo del tren trasero: 18,370 kgf. (50%)
Coeficiente de impacto en el contacto del tren de aterrizaje con la pista (Ref.1, Ref.2): 50%
(1.5)
Carga estática equivalente de diseño: 27,555 kgf
Consideraciones para el análisis estructural longitudinal
1. La condición crítica para el diseño estructural es el aterrizaje.
2. Los coeficientes de impacto son los mismos para todas las aeronaves de diseño
consideradas.
Referencias
Ref.1: Aircraft Landing Gear Design: Priciples and Practices. Norman S. Currey. (pág. 79).
Ref.2: Updates to 737 ‐Conditional Maintenance Inspection Procedures.
(http://www.boeing.com/commercial/aeromagazine/aero_14/conditional_story.html#tab1)
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ANEXO 1
CARACTERÍSTICAS DEL BOING 737‐300
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D6-58325-6
30 JULY 2007
2.2.3 GENERAL DIMENSIONS
MODEL 737-300
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D6-58325-6
18 DECEMBER 2010
CHARACTERISTICS UNITS
MODEL 737-300
CFM56-3B1 ENGINES (20,000 LB SLST) CFM56-3B2 ENGINES (22,000 LB SLST)
MAX DESIGN POUNDS 125,000 130,500 135,500 137,500 140,000 140,000
TAXI WEIGHTKILOGRAMS 56,699 59,194 61,462 62,369 63,503 63,503
MAX DESIGN POUNDS 124,500 130,000 135,000 137,000 139,500 139,500
TAKEOFF WEIGHTKILOGRAMS 56,472 58,967 61,235 62,142 63,276 63,276
MAX DESIGN POUNDS 114,000 114,000 114,000 114,000 116,600 116,600
LANDING WEIGHTKILOGRAMS 51,710 51,710 51,710 51,710 52,889 52,889
MAX DESIGN POUNDS 105,000 105,000 106,500 106,500 109,600 109,600
ZERO FUEL WEIGHTKILOGRAMS 47,627 47,627 48,308 48,308 49,714 49,714
OPERATING POUNDS 69,400 71,870 72,540 72,540 72,540 72,540
EMPTY WEIGHT (1)KILOGRAMS 31,479 32,600 32,904 32,904 32,904 32,904
MAX STRUCTURAL POUNDS 35,600 33,130 33,960 33,960 33,960 33,960
PAYLOADKILOGRAMS 16,148 15,028 15,404 15,404 15,404 15,404
SEATING CAPACITY TWO-CLASS 128: 8 FIRST CLASS AND 120 ECONOMY
ALL-ECONOMY 134 AT SIX ABREAST; FAA EXIT LIMIT: 149
MAX CARGO VOLUME CUBIC FEET 1,068 929 (2) 841 (3) 917 (4) 792 (5) 792 (5)
- LOWER DECKCUBIC METERS 30.2 26.3 (2) 23.8 (3) 26.0 (4) 22.4 (5) 22.4 (5)
USABLE FUEL US GALLONS 5,311 5,701 (2) 6,121 (3) 5,803 (4) 6,295 (5) 6,295 (5)
LITERS 20,102 21,578 (2) 23,168 (3) 21,964 (4) 23,827 (5) 23,827 (5)
POUNDS 35,584 38,197 (2) 41,011 (3) 38,880 (4) 42,177 (5) 42,177 (5)
KILOGRAMS 16,141 17,326 (2) 18,602 (3) 17,636 (4) 19,131 (5) 19,131 (5)
NOTES: (1) OPERATING EMPTY WEIGHT FOR BASELINE MIXED CLASS CONFIGURATION.
CONSULT WITH AIRLINE FOR SPECIFIC WEIGHTS AND CONFIGURATIONS.
(2) AIRPLANE WITH 390 GAL (1,475 L) AUXILIARY FUEL TANK IN AFT CARGO COMPARTMENT
(3)
AIRPLANE WITH 810 GAL (3,065 L) AUXILIARY FUEL TANK IN AFT CARGO COMPARTMENT(4) AIRPLANE WITH 500 GAL (1,893 L) AUXILIARY FUEL TANK IN AFT CARGO COMPARTMENT
(5) AIRPLANE WITH 1,000 GAL (3,785 L) AUXILIARY FUEL TANK IN AFT CARGO COMPARTMENT
2.1.6 GENERAL CHARACTERISTICS
MODEL 737-300
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D6-58325-6
FEBRURAY 2006 435
737-300 737-400 737-500
MAXIMUM DESIGNTAXI WEIGHT
LB 125 ,000 TO 140,000 139,000 143,000 144,000 150,500 116,000 TO 134,000
KG 56,699 TO 63,503 63,049 64,864 65,317 68,266 52,617 TO 60,781
PERCENT OF WEIGHT
ON MAIN GEAR SEE SECTION 7.4
STANDARD TIRES AND BRAKES
NOSE GEAR TIRE SIZE IN 27 x 7.75 – 15
10 PR
27 x 7.75 – 15
12 PR
27 x 7.75 – 15
12 PR
NOSE GEAR TIRE
PRESSURE
PSI 166 171 172 173 177 186
KG/CM2 11.67 12.02 12.09 12.16 12.44 13.08
MAIN GEAR TIRE SIZE IN H40 x 14.5 – 19
24 PR
H40 x 14.5 – 19
26 PR
H42 x 16
– 19
26 PR
H40 x 14.5 – 19
24 PR
MAIN GEAR TIRE
PRESSURE (1)
PSI 180 TO 201 203 209 211 185 170 TO 194
KG/CM2 12.65 TO 14.13 14.27 14.69 14.83 13.00 11.95 TO 13.64
LOW PRESSURE TIRES
NOSE GEAR TIRE SIZE IN 24 x 7.75 – 15
10 PR
24 x 7.75 – 15
12 PR
24 x 7.75 – 15
12 PR
NOSE GEAR TIRE
PRESSURE
PSI 166 171 172 173 (NA) 186
KG/CM2
11.67 12.02 12.09 12.16 (NA) 13.08MAIN GEAR TIRE SIZE IN H42 X 16 – 19
24 PR
H42 X 16 – 19
24 PR
(NA) H42 X 16 – 19
24 PR
MAIN GEAR TIRE
PRESSURE (1)
PSI 152 TO 170 171 176 177 (NA) 144 TO 164
KG/CM2 10.69 TO 11.95 12.02 12.37 12.44 (NA) 10.12 TO 11.53
NOTE: (1) SEE SEC 7.11 - TIRE INFLATION CHART, FOR TIRE PRESSURES AT INTERMEDIATE WEIGHTS.
7.2.4 LANDING GEAR FOOTPRINT
MODEL 737-300, -400, -500
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D6-58325-6
OCTOBER 2005 439
V NG = MAXIMUM VERTICAL NOSE GEAR GROUND LOAD AT MOST FORWARD CENTER OF GRAVITY
VMG = MAXIMUM VERTICAL MAIN GEAR GROUND LOAD AT MOST AFT CENTER OF GRAVITY
H = MAXIMUM HORIZONTAL GROUND LOAD FROM BRAKING
NOTE: ALL LOADS CALCULATED USING AIRPLANE MAXIMUM DESIGN TAXI WEIGHT
VNG VMG PER H PER STRUT
MODEL UNITS
MAXIMUM
DESIGN
TAXIWEIGHT
STATIC AT
MOST FWDC.G.
STATIC +
BRAKING 10FT/SEC2 DECEL
STRUT AT
MAX LOAD
AT STATIC AFT C.G.
STEADY
BRAKING 10FT/SEC2DECEL
AT
INSTANTANEOUSBRAKING (= 0.8)
737-300 LB 125,000 154,000 22,700 58,300 19,400 46,600
KG 56,700 69,854 10,297 26,445 8,800 21,138
737-300 LB 130,500 15,300 23,100 60,600 20,300 48,500
KG 59,194 6,940 10,478 27,488 9,208 21,999
737-300 LB 135,500 15,200 23,400 62,200 21,000 49,800
KG 61,462 6,895 10,614 28,214 9,526 22,589
737-300 LB 137,500 15,600 24,300 63,200 21,400 50,500
KG 62,370 7,076 11,022 28,667 9,707 22,907
737-300 LB 139,000 15,600 24,400 63,600 21,600 50,900
KG 63,050 7,076 11,068 28,849 9,798 23,088737-300 LB 140,000 14,500 23,400 63,600 21,700 50,900
KG 63,504 6,577 10,614 28,849 9,843 23,088
737-400 LB 139,000 15,900 23,000 64,900 21,600 51,900
KG 63,050 7,212 10,433 29,438 9,798 23,542
737-400 LB 143,000 16,000 20,800 67,100 22,200 53,700
KG 64,864 7,258 9,435 30,436 10,070 24,358
737-400 LB 144,000 12,200 19,700 66,900 22,400 56,500
KG 65,318 5,534 8,936 30,346 10,161 25,628
737-400 LB 150,500 16,500 24,400 70,600 23,400 56,500
KG 68,266 7,484 11,068 32,024 10,614 25,628
737-500 LB 116,000 17,100 25,000 53,700 18,000 42,900
KG 52,617 7,757 11,340 24,358 8,165 19,459
737-500 LB 125,000 17,300 25,800 57,700 19,400 46,200
KG 56,700 7,847 11,703 26,173 8,800 20,956
737-500 LB 134,000 17,300 26,400 61,800 20,800 49,400
KG 60,781 7,847 11,975 28,032 9,435 22,407
7.3.2 MAXIMUM PAVEMENT LOADS
MODEL 737-300, -400, -500
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ANEXO 2
CARACTERÍSTICAS DEL HÉRCULES C‐130
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DIMENSIONES:
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External Dimensions Value
Wing span 132.6 ft / 40.41 m
Wing aspect ratio 10.1
Length overall 97.75 ft / 29.79 m
Height overall 38.8 ft / 11.84 m
Tailplane span 52.7 ft / 16.05 m
Wheel track 14.25 ft / 4.34 m
Propeller diameter 13.5 ft / 4.11 m
Wing area (gross) 1,745 sq. ft / 162.12m2
Internal dimensions ValueCabin length (excl. ramp) 40 ft / 12.19 m
Cabin length (incl. ramp) 50.7 ft / 15.44 m
Max. width 10.25 ft / 3.12 m
Max. height 9 ft / 2.74 m
Total useable volume 4,551 cu ft / 128.9 m3
Weights and loadings Value
Operating weight empty 75,562 lbs / 34,274 kg
Max. fuel weight (internal) 45,900 lbs / 20,819 kg
Max. payload, 2.5g 41,790 lbs / 18,955 kg
Max normal T-O weight 155,000 lbs / 70,305 kg
Max. overload T-O weight 175,000 lbs / 79,380 kg
Max. normal landingweight
130,000 lbs / 58,965 kg
Max. overload landing
weight 155,000 lbs / 70,305 kg
Max zero-fuel weight,2.5g
117,350 lbs / 53,230 kg
Max. wing loading(normal)
88.83 lb/sq ft / 433.7kg/m2
Max. power loading(normal)
8.44 lbs/shp / 5.14kg/kW
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Previous Page Table of Contents Next Page
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C-130H and L-100-30Specifications and Systems
WEIGHTS POWER PLANTSC-130H
O p e r a t i n g , e q u i p p e d . 7 4 , 0 7 8 l b
Maximum payload @ 2.5 g . 43,274 lb
Takeoff:
L-100-30
72,943 lb
52,057 lb
Maximum . .155,000 lb 155,000 lb
Maximum emergency
overload. . . . .175,000 lb (not applicable)
Landing:
Maximum . . . . .130,000 lb 135,000 lb
Maximum @ 5 fps sink rate .155,000 lb (not applicable)Maximum emergency overload
@ 5 fps sink rate .175,000 lb (not applicable)
ENGINES - Four Allison turboprops are installed on each
Hercules aircraft. C-130Hs have the T56-A-15 model;
L-100-30s use the 501-D22A. Each engine has 4910
equivalent shaft horsepower available, but as installed in
the airframe, the maximum permissible output is limited
to 4200 shaft horsepower at the propeller. The power
section has a 14-stage, axial-flow compressor coupled
directly to a 4-stage turbine. The engine maintains a
constant speed of 100% (13.820 RPM) in flight. A
gearbox ratio of 13.54 to 1 converts the high engine
RPM to a propeller speed of 1021 RPM. For lower noise
levels during ground operations, an engine speed of 72%
may be selected.
CARGO COMPARTMENT DATA
6Total volume, including
ramp. _. . . . .4500cuft
Width . . . 10.0 ft
Height. . . . . 9.0 ft
Floor length, excluding
r a m p . . . . . . . . . . . . . . . 41.0 ft
Ramp length .
. 10.3 ft
Maximum ramp angle to
6057 cu ft
10.0 ft
9.0 ft
56.0 ft
10.3 ft
ground . . .
Floor height to ground,
loaded . .
Aft side doors (2).
width/height. . . .
Maximum fioor loading
(local area) . . . .
11.5deg 11.5deg
3.4 ft 3.4 ft
3.0/6.0 ft (not applicable)
50 psi 50 psi
Tiedowns include 5000-pound rings on ramp and fuselage
side walls and 10,000.pound rings on a 20-inch grid
pattern in the floor; also, 25,000.pound rings can be in-
stalled at selected floor locations.
FUEL CAPACITY (usable)
Internal. . . . . . . . 6960 gal 6960 gal
Pylon tanks . . . . . 2720 gal 2720 gal
T o t a l 9680 gal 9680 gal
The single point refueling rate for both models is 600
gpm: the fuel dumping rate is 500 gpm.
P R O P E L L E R S Both m od e l s a r e e q u i p p e d w i t h
four-blade Hamilton Standard Hydromatic propellers,
13.5 feet in diameter. These propellers have feathering
and reversing capability, and incorporate low-pitch
stop and pitch lock features.
AUXILIARY POWER An auxiliary power unit (APU)
supplies bleed air during ground operations for starting
engines and for air conditioning. It also drives an AC
generator. On the C-130H, the APU may be operated in
flight to provide emergency AC power.
ASSISTED TAKEOFF - An option available on C-130H
models provides fittings for IOOO-pound thrust solid fuel
units for assisted takeoff (ATO).
AIR CONDITIONING/PRESSURIZATION
Two independently operated air conditioning units
provide conditioned air to the cargo compartment and
flight station. The air supplied is also used to pressurizethe fuselage, maintaining a safe and comfortable cabin
environment at high altitudes.
ANTI-ICING/DEICING
Engine bleed air heats wing and empennage leading edges,
the radome, and the engine air inlet ducts. Propellers,
pitot tubes, and NESA windows in the flight station are
electrically heated.
Previous Page Table of Contents Next Page
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ANEXO 3
CARACTERÍSTICAS DEL BAE 146‐200
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Especificaciones BAe 146
BAe-146-100 BAe-146-200 BAe-146-300
Dimensions
Length (m) 26.16 28.55 30.99
Wingspan (m) 26.34 26.34 26.34
Height (m) 8.61 8.61 8.59
Wing area (m2) 77.3 77.3 77.3
Weight
Maximum take-off weight (kg) 38 102 42 184 44 225
Maximum landing weight (kg) 35 153 36 741 38 329
Operating empty weight (kg) 23 300 23 800 24 800
Maximum zero fuel weight (kg) 31 071 34 020 36 514
Maximum payload (kg) 6 650 8 075 9 500
Standard fuel capacity (litres) 11 728 11 728 11 728
Performance
Range with max payload (km) 2 174 2 365 2 181
Cruise speed (km/h) 750 750 750
Maximum speed (km/h) 890 890 890
Maximum operating altitude (m) 9 500 9 500 9 500
Engines Honeywell ALF 502R-5,
4 x 6970 lb
Honeywell ALF 502R-5,
4x6970 lb
Honeywell ALF 502R-5,
4 x 6970 lb
Cabin Data
Passengers (1-class) 70 85 100
Economy seat pitch (cm) 79 79 79
Cabin length (m) 15.42 17.81 20.20
Cabin width (m) 3.42 3.42 3.42
Cabin height (m) 2.03 2.03 2.03
Aisle width (m) 0.53 0.53 0.53
Seat width (m) 0.54 0.54 0.54
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TCDS No.: EASA.A.182 BAe 146 / AVRO 146-RJ Series Page 8/18Issue 2.0 Date: 20 October 2010
10. Air Speeds: Refer to the Aircraft Flight Manual.
11. Maximum Operating Altitude: 31,000 ftPre change series HCM50043 aircraft are limitedto 30,000 ft.
12. All Weather Capability: CAT ICAT II for aircraft modified in accordance withchange HCM40350A.
13. Maximum Weights:
Basic Series 100 Series 200 Series 300
Maximum Total WeightAuthorised
34,700 kg(76,500 lb)
40,823 kg(90,000 lb)
43,318 kg(95,500 lb)
Maximum Take-offWeight
34,473 kg(76,000 lb)
40,596 kg(89,500 lb)
43,091 kg(95,000 lb)
Maximum LandingWeight
32,817 kg(72,350 lb)
35,153 kg(77,500 lb)
37,648 kg(83,000 lb)
Maximum Zero FuelWeight
29,483 kg(65,000 lb)
32,204 kg(71,000 lb)
35,153 kg(77,500 lb)
Variations in aircraft maximum weights are allowed through modification action. This willresult in an amendment to the Aircraft Flight Manual. The following is a list of absolutemaximums which may not be allowed in combination. Reference should be made to theAircraft Flight Manual and applicable Service Bulletins:
Absolute Series 100 Series 200 Series 300
Maximum Total WeightAuthorised
38,328 kg(84,500 lb)
42,410 kg(93,500 lb)
45,359 kg(100,000 lb)
Maximum Take-offWeight
38,101 kg(84, 000 lb)
42,184 kg(93,000 lb)
45,132 kg(99,500 lb)
Maximum LandingWeight
35,153 kg(77,500 lb)
36,740 kg(81,000 lb)
39,235 kg(86,500 lb)
Maximum Zero FuelWeight
31,071 kg(68,500 lb)
34,745 kg(76,600 lb)
36,514 kg(80,500 lb)
14. Centre of Gravity Range: Refer to the Aircraft Flight Manual.
15. Datum: Refer to the Weight and Balance Manual.
16. Standard Mean Chord (SMC): 2.934 m (9.625 ft)
Note: Leading edge of SMC is1.038 m (3.405 ft) forward of the CG datum.
17. Levelling Means: Refer to the Weight and Balance Manual.
18. Minimum Flight Crew: Two (Pilot and Co-pilot) for all types of flight.
19. Maximum Seating Series 100 - 100Capacity (Including Crew): Series 200 - 118
Series 300 - 118 Increasing to 124 for aircraft withType III under wing exits, introduced by changeHCM40301A.