1. cargas de diseño

8/17/2019 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


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)


Avión Hércules C‐130

Distancia entre ejes: 9.09m ‐1.52m




Máxima carga transmitida a cada lado del tren trasero: 69,750 lb. (45%)



Fuerza de frenado (μ=0.8): 124,000 lb (56,245 kgf).


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Máxima carga transmitida a cada lado del tren trasero: 65,000 lb. (50%)


(1.5)


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



Máximo peso total: 42,200 kgf.

Máxima carga transmitida en un punto de apoyo del tren trasero: 18,990 kgf. (45%)


Carga estática equivalente de diseño: 24,687 kgf

Fuerza de frenado (μ=0.8): 33,760 kgf


Máximo peso total: 36,740 kgf. Máxima carga transmitida en un punto de apoyo del tren trasero: 18,370 kgf. (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


TAKEOFF WEIGHTKILOGRAMS 56,472 58,967 61,235 62,142 63,276 63,276


LANDING WEIGHTKILOGRAMS 51,710 51,710 51,710 51,710 52,889 52,889


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.

1. cargas de diseño

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