C-130J Super Hercules Whatever the Situation, We'll Be There
LOCKHEED C-130 Hercules · Pilot's Operating Handbook
Overview
The document provides a comprehensive overview of the Lockheed C-130J Hercules, detailing its capabilities, performance upgrades, and various configurations. It highlights the aircraft's versatility and improvements over previous models, making it a preferred choice for military transport across the globe.
- The C-130J Hercules is used by over 60 nations.
- More than 2,300 C-130 aircraft have been delivered since 1956.
- The C-130J-30 version offers 30% more usable cargo volume.
- The aircraft features a new propulsion system with Rolls-Royce engines.
- It has set 54 world records for performance metrics.
- Maintenance man-hours per flight hour are reduced by up to 68%.
- The C-130J includes advanced avionics and a two-person flight station.
- It is capable of various missions including airlift, refueling, and search and rescue.
Document
Source
Originally published by lockheedmartin.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type ·
- Pilot's Operating Handbook
- File size ·
- 7.1 MB
- Publisher ·
- lockheedmartin.com
- Language ·
- en
Specifications & performance
Extracted from this document.
Specifications
- Height (ft) ·
- 38 ft 10 in.
- Length (ft) ·
- 112 ft 9 in.
- Wingspan (ft) ·
- 132 ft 7 in.
- Cargo volume cu (ft) ·
- 6,022 cu ft
- Cargo floor width (ft) ·
- 10 ft
- Cargo floor height (ft) ·
- 9 ft
- Cargo floor length (ft) ·
- 55 ft + 10 ft 8 in.
Performance
- Max range nmi ·
- 3,510 n.mi.
- Airdrop speed kias ·
- Up to 250 KIAS
- Service ceiling (ft) ·
- 29,000 ft
- Cruising altitude (ft) ·
- 27,000 ft
- Max cruise speed (kt) ·
- 355 kts
- Normal landing roll (ft) ·
- 1,630 ft
- Normal takeoff roll (ft) ·
- 3,000 ft
- Range with payload nmi ·
- 2,200 n.mi.
- Takeoff dist over 50 ft (ft) ·
- 5,850 ft
- Max effort landing dist over 50 ft (ft) ·
- 3,510 ft
Weight & balance
- Max fuel (lb) ·
- 43,562 lb
- Max payload (lb) ·
- 47,333 lb
- Max landing weight (lb) ·
- 135,000 lb
- Max takeoff weight (lb) ·
- 164,000 lb
- Max zero fuel weight (lb) ·
- 129,000 lb
- Operating weight empty (lb) ·
- 87,667 lb
What is the C-130J Super Hercules Whatever the Situation, We'll Be There?
The C-130J Super Hercules Whatever the Situation, We'll Be There is a pilot's operating handbook for the LOCKHEED C-130 Hercules.
Where does the C-130J Super Hercules Whatever the Situation, We'll Be There come from?
This copy of the C-130J Super Hercules Whatever the Situation, We'll Be There was originally published by lockheedmartin.com and is hosted on Sprinkle as a free, searchable reference copy.
Most owners only have the POH. Here's the essential set for the LOCKHEED C-130 Hercules.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins on file
- Type Certificate (TCDS)
More LOCKHEED C-130 Herculesmanuals & documents
In this document
Introduction
The introduction outlines the C-130 Hercules as a benchmark for military transport aircraft, emphasizing its versatility and reliability.
Recent Capability/Performance Upgrades
This section details enhancements made to the C-130J, including improved structural components and advanced systems for better operational performance.
General Characteristics
General characteristics of the C-130J are provided, including dimensions and cargo specifications.
Performance
Performance metrics such as maximum speed, takeoff distances, and range capabilities are discussed.
Technology Improvements
This section highlights technological advancements in the C-130J, including avionics and diagnostic systems.
Competitive Comparison
A comparison of the C-130J with other aircraft, showcasing its advantages in design and capabilities.
Safety notes
- Ensure compliance with operational limits to maintain safety.
- Use caution when operating in high-hot conditions.
- Follow maintenance guidelines to ensure aircraft reliability.
- Be aware of the aircraft's weight limits during loading.
- Utilize the Terrain Awareness and Warning System for safety.
Full document text
C-130J Super Hercules Whatever the Situation, We’ll Be There 1 The C-130 Hercules is the standard against which military transport aircraft are measured. Versatility, reliability, and ruggedness make it the military transport of choice for more than 60 nations on six continents. More than 2,300 of these aircraft have been delivered by Lockheed Martin Aeronautics Company since it entered production in 1956. During the past five decades, Lockheed Martin and its subcontractors have upgraded virtually every system, component, and structural part of the aircraft to make it more durable, easier to maintain, and less expensive to operate. In addition to the tactical airlift mission, versions of the C-130 serve as aerial tanker and ground refuelers, weather reconnaissance, command and control, gunships, firefighters, electronic recon, search and rescue, and flying hospitals. The newest Hercules, the C-130J, has the same rugged good looks of its predecessors, but in fact is a greatly improved airplane with the performance and capability to prove it. Compared to the earlier C-130E, the maximum speed is 21 percent higher, Introduction Note: In general this document and its contents refer to the C-130J-30, the stretched/advanced version of the Hercules. INTRODUCTION 1 RECENT CAPABILITY/PERFORMANCE UPGRADES 4 SURVIVABILITY OPTIONS 5 GENERAL ARRANGEMENT 6 GENERAL CHARACTERISTICS 7 TECHNOLOGY IMPROVEMENTS 8 COMPETITIVE COMPARISON 9 CARGO COMPARTMENT 10 CROSS SECTIONS 11 CARGO ARRANGEMENT 12 CAPACITY AND LOADS 13 ENHANCED CARGO HANDLING SYSTEM 15 COMBAT TROOP SEATING 17 Paratroop Seating 18 Litters 19 GROUND SERVICING POINTS 20 GROUND OPERATIONS 21 FLIGHT STATION LAYOUTS 22 Instrument Panel 22 Overhead Panel 23 Center Console 24 USAF AVIONICS CONFIGURATION 25 MAJOR SYSTEMS 26 Electrical 26 Environmental Control System 27 Fuel System 27 Hydraulic Systems 28 Enhanced Cargo Handling System 29 Defensive Systems 29 PERFORMANCE 30 Maximum Effort Takeoff Roll 30 Normal Takeoff Distance (Over 50 Feet) 30 Maximum Effort Landing Roll 31 Normal Landing Distance (Over 50 Feet) 31 Payload Range 32 WORLD RECORDS 33 Table of Contents 3 climb time is reduced by up to 50 percent, cruising altitude is up to 40 percent higher, and range is up to 40 percent longer. With new engines and props, the J has set 54 world records for rate of climb, cruise speed, and both distance and altitude with payload. The C-130J incorporates these major improvements: • A new propulsion system featuring four 4,591 pshp Rolls-Royce AE2100D3 engines and composite, six-bladed Dowty Aerospace R391 propellers with significantly improved fuel economy and high-hot performance. • Two-person flight station including four multifunctional LCD displays; two holographic head-up displays (HUD); and electronic, digital readouts for aircraft operating, communicating, and navigating systems. The displays and aircraft general lighting are compatible with the USAF’s night-vision imaging system. • A 1553 data bus, two mission computers, and two backup bus interface units provide dual redundancy for the Hercules’ systems. In addition, the computers provide for an integrated diagnostics system that monitors and records the status of the aircraft’s structure and systems. Introduction Introduction 2 The C-130J-30, the stretched/advanced version of the Hercules, offers operators 55 feet of cargo compartment length – an additional 15 feet over the original “short” aircraft. The additional 15 feet is provided by inserting a 100-inch forward and an 80-inch aft plug to the fuselage. This translates into 30 percent more usable volume for increased seating, litters, pallets, or airdrop platforms. This additional capability provides significant advantages when transporting personnel or delivering priority cargo by reducing the number of sorties needed to complete the mission. In addition to the significant increases in operational capability and performance, the C-130J offers a greater value when compared to any other tactical airlifter: System reliability and maintainability are improved by up to 50 percent; maintenance man-hours per flight hour are decreased by up to 68 percent; and flight and maintenance manpower are reduced by up to 50 percent, resulting in a 47 percent lower squadron operating and support cost. 5 4 Recent Capability/Performance Upgrades Survivability Options • Center Wing Box improvement to provide Enhanced Service Life (ESL) by strengthening structural components such as Hat Sections (stringers), Beam Caps and Webs, Wing Attach Fittings, and Engine Truss Mounts. The ESL wing was originally developed for the USAF Special Operations C-130s in support of Severe Mission Operations. • Reduced Vertical Separation Minima (RVSM) for worldwide operations in CNS/ATM controlled airspace. Access to RVSM airspace increases true air speed and range while reducing fuel consumption, e.g., enhances long-range cruise performance. • Data Transfer and Diagnostic System (DTADS) Interface Unit for maintenance management of critical aircraft systems using a Windows Operating System. DTADS encompasses in-flight and post-flight analysis, ground maintenance processing, structural health monitoring, and engine life management. DTADS is scheduled to become available in 2010. • Small Arms Armor Kit, available as Customer- Furnished Equipment (CFE), provides protection for the pilot and co-pilot, crew station and bunk, forward and aft loadmaster stations, paratroop doors, nose wheel well, and liquid oxygen converter. • Explosive Suppressant Tank Foam is available as CFE for the main and auxiliary fuel tanks, which aids in protecting against ballistic penetration and lightning strikes. Subsequent to the USAF Operational Test and Evaluation Acceptance of the C-130J combat delivery aircraft in 2006, several performance enhancements by Lockheed Martin Aeronautics were developed, tested, verified, qualified,
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accepted, and incorporated into the basic aircraft configuration. These include: • Terrain Awareness and Warning System (TAWS), a forward-looking awareness and warning system, for improved in-flight situational awareness. The TAWS operates in conjunction with the existing Ground Collision Avoidance System (GCAS) as independent complementary systems providing visual and obstacle Voice Warning Alerts (VWA) to the crew. • Identification Friend or Foe (IFF) Transponder Mode S with Enhanced Surveillance for use in civil Communications, Navigation, and Surveillance/Air Traffic Management (CNS/ATM) airspace. The IFF has growth capability to Mode 5. • Communications, Navigation, and Identification (CNI) common software upgrade developed for all customers including updated chute ballistic tables, new track offset, additional drift down performance pages, and re-host of the Takeoff and Landing Data (TOLD) from the CNI to the Mission Computer (MC). • TOLD re-hosted in MC Operational Flight Program (OFP), enabling additional and enhanced capabilities pertaining to charts and calculations for hot/high takeoffs, assault landing weight, modified minimum field length maximum effort takeoff, climb gradients, wind corrections, and temperature deviation expansion to ISA +/-45°C. Recent Capability/Performance Upgrades Dimensions Wingspan Length Height Cargo Floor Length (Floor + Ramp) Width (Minimum) Height (Minimum) Area (Floor + Ramp) Cargo Volume Weights Max Takeoff Weight (2.5g) Max Takeoff Weight (2.25g) Max Landing Weight, 9 fps Max Landing Weight Operating Weight Empty Max Payload (2.5g) (Note 2) Max Fuel (JP-8) Max Zero Fuel Weight (Note 1) Max Zero Fuel Weight (Note 2) Performance Max Cruise Speed Airdrop Speed Takeoff Dist Over 50 ft (S/L, ISA, 164,000 lb) Normal Takeoff Roll (S/L, ISA, 164,000 lb) Max Effort Landing Dist Over 50 ft (S/L, ISA, 135,000 lb) Normal Ground Roll (S/L, ISA, 135,000 lb) Max Effort Max Range (Without Tanks) Range (40,000-lb Payload – 2.5-g Mission) Cruising Altitude (T/O at MTOW) Service Ceiling (T/O at MTOW) Crew Power Plant 132 ft 7 in. 112 ft 9 in. 38 ft 10 in. 55 ft + 10 ft 8 in. 10 ft 9 ft 550 + 107 sq ft 6,022 cu ft 164,000 lb 175,000 lb 162,000 lb 164,000 lb 87,667 lb 47,333 lb 43,562 lb 129,000 lb 135,000 lb 355 kts Up to 250 KIAS 5,850 ft 3,100 ft 3,000 ft 1,630 ft 3,510 n.mi 2,200 n.mi 27,000 ft 29,000 ft 2 Pilots + Loadmaster 4 Rolls-Royce AE2100D3, 4,591 pshp Turboprop Engines (4 Dowty R391, 6-Blade Propellers, All Composite) Note 1: Structural Reserve Fuel Note 2: With Wing Bending Relief Fuel 7 6 General Characteristics FEET 0 10 20 30 40 50 14 ft 2 in. (4.32 m) 52 ft 8 in. (16.05 m) 38 ft 10 in. (11.84 m) External Fuel Tanks (Optional) 112 ft 9 in. (34.37 m) 11 ft 6 in. (3.50 m) 40 ft 4 in. (12.30 m) 132 ft 7 in. (40.38 m) 14 ft 3 in. (4.34 m) General Arrangement 9 8 Competitive Comparison AIRCRAFT • Two-Person Flight Deck Crew • Provisions for Auxiliary Crew Member Station • Ergonomically Designed Cockpit • Interchangeable Panel Layout • Soft Panels • Advanced Communications and Navigation Systems • New Electrical System • 1553B Data Bus Architecture • Integrated Diagnostic System • Head-Up Display (Dual) – Certified Primary Flight Instrument • 250 KIAS Airdrop Speed Ramp and Door • Single Cross-Ship Fuel Manifold • Defensive Systems • Air Traffic and Ground Collision Avoidance Systems • Enhanced Cargo Handling System (USAF Configuration) • Color Digital Map Display • Color Weather Radar/Ground Mapping Radar • Night-Vision Imaging System (NVIS) Compatible (Flight Deck and Cargo Compartment) PROPULSION • Rolls-Royce AE2100D3, Flat Rated at 4,591 pshp • Full-Authority Digital Electronic Control (FADEC) • Dowty R391 Six-Bladed Composite Propeller Technology Improvements Model C-130J-30 55 ft 8 97 24 128 92 A400M (Proposed) 58 ft 9 66 24 120 120 C-17 65 ft 18 36 40 102 102 C-130E/H C-130J (Short) 40 ft 6 74 16 92 64 Cargo Floor #463L Pallets Litters CDS Bundles Combat Troops Para- troops 11 10 10 ft 5 in. 9 ft 2 in. Cargo Floor Forward Cargo Floor 10 ft 9 ft Litter Stanchion Bracket Wing Center Section Lower Surface Center Cargo Ramp Pendulum Arm Aft 1 in. 10 ft 9 ft Cross Sections Load Sta 1022.25 (C of Ramp Hinge)L Paratroop Door 9 ft Cargo Floor Static Ground Line 13 ft 11 in. Maximum at 4 ft 6 in. Above Cargo Floor 55 ft 10 ft 3 in. 3 ft 5 in. 9 ft 2 in. Bottom of A-Frame Litter Stanchion Bracket 13 ft 5 in. 10 ft Cargo Compartment 13 sq ft (sq m) 32 (2.98) 76 (7.06) 77 (7.16) 77 (7.16) 75 (6.97) 75 (6.97) 77 (7.16) 76 (7.06) 27 (2.51) 71 (6.60) 15 (1.39) 697 607 517 428 365 Inch 787 877 967 1027 1083 1133 C D E F G H I J K L M Compartment Load Station Centroid Area cu ft (cu m) 292 (8.17) 684 (19.15) 692 (19.37) 692 (19.37) 678 (18.98) 676 (18.92) 692 (19.37) 684 (19.15) 219 (6.13) 454 (12.71) 73 (2.04) Volume 2 12 12 Ramp SUMMARY OF CARGO COMPARTMENT CAPACITY AND MAXIMUM ALLOWABLE FLIGHT LOADS lb (kg) 5,700 (2,585) 11,500 (5,216) 21,000 (9,525) 38,000 (17,236) 45,000 (20,412) 45,000 (20,412) 34,000 (15,422) 19,500 (8,845) 3,500 (1,588) 4,500 (2,041) 500 (744) Maximum Individual Compartment Capacity psi (kg sq cm) 50 (3.52) 50 (3.52) 50 (3.52) 50 (3.52) 50 (3.52) 50 (3.52) 50 (3.52) 50 (3.52) 50 (3.52) 50 (3.52) 50 (3.52) Concentrated Loads – All Areas lb/ft (kg/m) 1,400 (2,083) 1,400 (2,083) 1,400 (2,083) 1,400 (2,083) 1,400 (2,083) 3,000 (4,464) 3,000 (4,464) 3,000 (4,464) 500 (744) 500 (744) 500 (744) Running Loads per Treadway 13 lb/ft (kg/m) lb (kg) lb/ft (kg/m) 1,600 (2,381) 2,000 (907) 2,000 (907) 2,000 (907) 2,000 (907) 2,000 (907) 2,000 (907) 2,000 (907) 2,000 (907) 2,800 (4,167) 450 (204) 450 (204) 1,000 (1,488) 3,200 (4,762) 3,200 (4,762) 3,200 (4,762) 450 (204) 1,600 (2,381) 1,600 (2,381) 1,600 (2,381) 1,600 (2,381) 1,600 (2,381) 1,600 (2,381) 1,600 (2,381) 500 (744) 5 6 2,800 (4,167) 14 2,800 (4,167) 2,800 (4,167) 14 5 5 500 (744) 500 (744) Running Loads Between Treadways Tongue Load Between Treadways Palletized and Containerized Cargo MAXIMUM LOAD RATE 11 11 11 Capacity and Loads 12 Model C-130J-30 55 ft 8 97 24 128 92 Cargo Floor #463L Pallets Litters CDS Bundles Combat Troops Para- troops 1 2 3 4 5 8 100 in. 80 in. The C-130J-30 Can Carry 90 Percent of the U.S. Army and USAF Combat Equipment 7 6 Cargo Arrangement 15 14 RECONFIGURATION TIME IN MINUTES Aircraft Slick Floor to Pallets Pallets to Slick Floor Winching Centerline Vertical Restraint Tow Plate C-130E/H C-130J-30 Improvement 15 5 67% 24 5 79% 24 8 67% 10 1 90% 21 1 95% CDS Center Vertical Restraint Rails Electric Locks Recessed Electric Tow Plate 250-Knot Ramp and Door Underfloor Electric Winch Loadmaster Console Flipover Rollers/Low-Profile Rails Enhanced Cargo Handling System lb (kg) lb (kg) lb (kg) lb (kg) 6,000 (2,722) 2,300 (1,043) 2,300 (1,043) 2,300 (1,043) 950 (431) 950 (431) 950 (431) 5,000 (2,268) 5,000 (2,268) 5,000 (2,268) 2,000 (907) 2,000 (907) 2,000 (907) 2,000 (907) 2,000 (907) 2,000 (907) 2,000 (907) 2,000 (907) 450 (204) 450 (204) 450 (204) 6,000 (2,722) 6,000 (2,722) 2,500 (1,134) 2,500 (1,134) 2,500 (1,134) 13,000 (5,897) 13,000 (5,897) 13,000 (5,897) Treadways Between Treadways Pneumatic Tires, 100 psi (689.5 KPA) Maximum Pressure Hard Rubber Tires and Steel Wheels 7 5,000 (2,268) 5,000 (2,268) 5,000 (2,268) 5,000 (2,268) 5,000 (2,268) 5,000 (2,268) 5,000 (2,268) 5,000 (2,268) 1,200 (544) 1,200 (544) 1,200 (544) 7 7 2,300 (1,043) 16 2,300 (1,043) 15 7 10 6,000 (2,722) 16 6,000 (2,722) 15 MAXIMUM AXLE LOAD Treadways Between Treadways 1 Do not exceed overall airplane restrictions. 2 The ramp (load stations 1023 through 1141) contains the aft 19 in. (48.26 cm) of compartment K and compartments L and M. The maximum allowable flight load permitted on the ramp is 5,000 lb (2,268 kg) and the load center of gravity must be located at or forward of the ramp centroid (load station 1063). 3 Adequate shoring shall be used to contain tongue loads within psi limits. 4 4-ft (1.22 m) minimum distance between axles. Total wheeled load not to exceed compartment capacities listed for pallets or containers. 5 Palletized or containerized cargo centroids will not fit in these compartments. 6 The cargo loading system restraint rail sections 5 and 6 are limited to 8,500 lb (3,856 kg) total weight restraint. 7 Axle loads must not be forward of load station 357. 8 Maximum cargo height in the cargo compartments is 108 in. (274.3 cm). When roller conveyors are installed, maximum cargo height is reduced 2-5/8 in. (6.7 cm). 9 Maximum height of cargo secured to the cargo ramp is 81 in. (205.7 cm) at ramp station 8 and 77 in. (195.5 cm) at ramp station 10. When roller conveyors are installed, maximum cargo height is reduced 2-5/8 in. (6.7 cm). 10 See figure 4-7 for hard rubber tire and steel wheel limitations. 11 These allowables are separate and not additive. If both center floor and treadways are loaded, the total load cannot exceed the maximum treadway load. 12 3,000 lb/ft (4,464 kg/m) between load station 537 and load station 882. 13 1,600 lb/ft (2,381 kg/m) between load station 1011 and load station 1017. 14 3,200 lb/ft (4,762 kg/m) between load station 537 and load station 882. 15 13,000 lb/ft (5,897 kg/m) between load station 537 and load station 882. 16 5,000 lb/ft (2,268 kg/m) between load station 537 and load station 882. Capacity and Loads 17 16 128 Ground Troops 20-Inch Seating 16 16 4 4 4 4 33 33 7 7 Combat Troop Seating Multifunction Control Display RETN SAVE TNG CAWS 0 1 2 3 4 5 6 DAY OFF 7 9 8 Loadmaster Station (Near Crew Entrance Door) Enhanced Cargo Handling System 5 5 5 5 5 5 4 5 5 4 4 5 5 4 4 4 5 5 4 4 5 97 Litters Attendants 19 Litters 18 92 Paratroops 24-Inch Seating Safety Men Loadmaster Seats 13 13 27 27 3 3 3 3 1 1 Paratroop Seating 21 20 Nose Wheel 60-deg. Turn Radius Wingtip Radius 89 ft 8 in. Main Gear Radius 15 ft 4 in. Main Gear Radius 31 ft 4 in. Horizontal Tip Radius 73 ft 9 in. Nose Gear Radius 46 ft 8 in. Outer Propeller Radius 65 ft Vertical Clearances Wingtip Vertical Stabilizer Tip Inboard Propeller Outboard Propeller 12 ft 38 ft 10 in. 6 ft 6 ft 8 in. Minimum Space Required for Turning is 179 Feet 4 Inches With the Nose Gear Turned to the Maximum of 60 Degrees at Taxi Speeds Under 5 Knots Ground Operations 80 2 4 Unsurfaced Soil Strength – CBR 6 8 10 90 100 110 Gross Weight – 1,000 Pounds 120 130 140 150 Note Number of Passes Is Based on Main Landing Gear Tire Inflation Pressure for Marginal Strength Airfields. A Pass Is Defined as One Landing and One Takeoff. CBR (Dirt, Grass) 100 Passes 10 Passes Maximum Recommended Weight for Marginal Strength Airfields FEET 0 10 20 30 40 50 Water Toilet Jack Point Wing Fuel Hydraulic Jack Point Aux Tank Fuel Oxygen Engine Starter Engine Oil External Tank Fuel (Optional) Propeller Oil Urinals Wing Fuel Hydraulics Galley Jack Points Both Sides Oxygen Water Pneumatic Electrical (Left Side) Hydraulic Flight Station Air-Conditioning System Cargo Compartment Air-Conditioning System Single-Point Refuel Ground Servicing Points 22 1 4 27 26 3 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 3 9 8 7 6 5 4 3 2 1. Oxygen Regulator 2. Oxygen Mask Stowage Box 3. Reading Light Control 4. Headset Interface Unit 5. Control Boost Panel 6. Console Light 7. Oil Cooler Flaps Panel 8. Electrical Panel 9. Pressurization Panel 10. Fuel Management Panel 11. Air Cond Panel 12. Copilot HUD Panel 13. Wipers panel 14. Emergency Exit Lights Extinguish 15. ELT Panel 16. APU Pane 17. Engine Start Panel 18. Fire Panell 19. Prop Sync Panel 20. ATCS Panel 21. Propeller Control Panel 22. Pilot HUD Panel 23. FADEC Panel 24. Exterior Lighting Panel 25. Voice Recorder Microphone Panel 26. Ice Protection Panel 12 11 10 3 9 8 7 6 5 4 3 2 13 14 15 16 17 18 19 20 21 22 23 24 25 3 26 27 4 1 Overhead Panel Flight Station Layouts 1 Oxygen Regulator 2 Oxygen Mask Stowage Box 3 Reading Light Control 4 Headset Interface Unit 5 Control Boost Panel 6 Console Light 7 Oil Cooler Flaps Panel 8 Electrical Panel 9 Pressurization Panel 10 Fuel Management Panel 11 Air Cond Panel 12 Co-pilot HUD Panel 13 Wipers Panel 14 Emergency Exit Lights Extinguish 15 ELT Panel 16 APU Panel 17 Engine Start Panel 18 Fire Panel 19 Prop Sync Panel 20 ATCS Panel 21 Propeller Control Panel 22 Pilot HUD Panel 23 FADEC Panel 24 Exterior Lighting Panel 25 Voice Recorder Microphone Panel 26 Ice Protection Panel 27 Bleed Air Panel 23 1 5 7 8 12 11 10 7 7 9 8 7 6 5 2 3 4 3 2 1 Instrument Panel Flight Station Layouts 1 Reference Set/Mode Select Panel (Two Places) 2 Inclinometer (Two Places) 3 Avionics Management Unit (Two Places) 4 Communication/Navigation/ Electronic Circuit Breaker Panel 5 Mode Annunciator Panel (Two Places) 6 Air Diverter Handle (Two Places) 7 Color Multipurpose Display Unit (CMDU) 8 Hydraulic Control Panel 9 Landing Gear/Landing Lights Panel 10 Flap and Trim Indicator Panel 11 Standby Altimeter/ Airspeed Indicator 12 Standby Attitude Indicator 1 Pilot Lighting Panel 2 Radar Control Panel 3 Co-pilot Lighting Panel 4 Intercommunications System Control Panel (Three Places) 5 Communication/Navigation/ Identification Management Unit (Three Places) 6 Remote Heading and Course Selector (Two Places) 7 Throttle Quadrant Assembly 8 Cursor Control Panel 9 Wing-Flaps Control Quadrant Panel 10 Headset Interface Unit Panel 11 Intercommunications System Monitor Panel 12 Trim Panel 13 Defensive Systems Panel 14 Aerial Delivery Panel 15 Automatic Flight Control System Panel 25 24 Qty Color Multipurpose Display Unit (CMDU) 4 Head-Up Display (HUD) 2 Global Digital Map Unit (GDMU) 1 Mission Computer 2 Avionic Management Unit (AMU) 2 Comm/Nav/Breaker Panel 1 Multichannel Dimming Unit 3 VHF AM/FM Comm Radio, AN/ARC-222 (MXF-626) 2 UHF Communication Radio, AN/ARC-164 2 HF Communication Radio, AN/ARC-190 2 HF Secure Voice, KYV-5 (ANDVT) (Group A) 2 VHF/UHF Secure Voice, KY-58 (Group A) 4 SATCOM (Group A) 1 UHF Satellite Terminal System (USTS) (Group A) 1 Intercommunication System 1 Embedded Global Positioning System/INS (EGI) 2 CNI-System Processor 2 CNI-Management Unit 3 Low-Power Color Radar, APN-241 1 Formation Station Keeping Equipment, SKE 2000 1 Distributed Air Data System 1 Radar Altimeter, HG9550 2 Tactical Air Navigation, AN/ARN-153 2 VHF Omnirange/Instrument Landing System/Marker Beacon, AN/ARN-147 (One Marker Beacon) 2 Automatic Direction Finder, AN/ARN-149 2 UHF Direction Finder, DF-301E 1 Identification Friend or Foe, APX-119 1 Group A Provisions for 2nd IFF 1 Terrain Awareness and Warning System 1 Group A Provisions for Second Enhanced Traffic Alert and Collision Avoidance Subsystem 1 Digital Autopilot/Flight Director 2 Missile Warning System, AN/AAR-47 (Group A) 1 Countermeasures Dispensing System, AN/ALE-47 (Group A) 1 Radar Warning Receiver, AN/ALR-56M (Group A) 1 Ground Proximity Warning System 1 Integrated Precision Radar Approach System 1 USAF Avionics Configuration 1 10 5 9 8 7 6 5 4 2 3 12 11 4 13 14 15 6 5 4 1 Center Console Flight Station Layouts 27 26 ENVIRONMENTAL CONTROL SYSTEM • The aircraft’s environmental control system (ECS) is capable of stabilizing the cockpit environment from a heat soak temperature condition at external ambient temperature of +120°F (+49°C) to +84°F (+28.8°C) within 30 minutes from cooling operation ECS start. The ECS is capable of increasing the cabin average temperature from -22°F (-30°C) to +41°F (+5°C) within 20 minutes. • Cargo-floor heating is accomplished by using hot air circulating through an underfloor manifold. • A forced-air cooling system is provided for the flight-station displays and certain rack-mounted avionics and electrical equipment. • A system for pressurizing the flight station and cargo compartment is supplied by engine compressor bleed air. This electronically controlled pneumatic system is capable of maintaining a maximum of 8,000-foot cabin altitude at 32,200-foot flight altitude. The aircraft is pressurized and depressurized in accordance with a preprogrammed schedule and under rate control while in the automatic mode. A separate backup manual control of the pressurization system provides outflow valve operation in case of a failure in the automatic system. FUEL SYSTEM • The fuel system uses a common cross-ship manifold that serves as a refueling system, a fuel supply crossfeed, a direct feed system, a ground defueling system, and a fuel jettisoning system. The fuel system consists of tanks, pumps, piping, valves, flowmeters, strainers, and quantity gage units. • Fuel system design and performance is based on the use of fuel conforming to JP-8 (MIL-T-83133). • The system is compatible with JP-4, JP-5, Jet A, Jet A-1, and Jet B fuels with or without anti-icing Major Systems ELECTRICAL • The electrical system includes four regulated transformer rectifier units, five AC generators, controls, and conversion equipment needed to satisfy and control the diversified power requirements of the various electrical and electronic equipment and other systems. Secondary distribution uses electronic and electromechanical circuit breakers. • Four 40/50-kVA oil-cooled, three-phase AC generators constitute the primary AC power source. Each engine-driven generator has an overtorque shaft disconnect and an individual generator control unit. A fifth 40/50-kVA air-cooled, three- phase AC generator is mounted on the auxiliary power unit as an additional AC power source. • Two 24-volt, 42-ampere-hour (beginning of life), sealed, lead acid, and maintenance-free batteries are installed in a battery compartment in the lower left forward fuselage. A control switch in the flight station disconnects the batteries from the electrical system. With fully charged batteries, sufficient battery power is available to operate standby instruments and other flight-critical components for approximately 30 minutes after complete loss of primary aircraft power. When required, one battery can provide electrical power for APU starting. • Four regulated 200-ampere transformer rectifiers convert AC power to DC power. Two 1-kVA inverters provide uninterruptable electrical power for the essential avionics bus and the main avionics bus. • Regulated power supplies (RPSs) provide filtered and regulated DC power to the flight station consoles. The RPS is powered by two independent 28-VDC power sources. Major Systems • The auxiliary system furnishes hydraulic power for normal ramp and cargo door operation. The system also provides pressure for wheel brake operation, NLG extension, and down lock in the event of utility system failure. ENHANCED CARGO HANDLING SYSTEM (ECHS) • The ECHS allows the load-crew to control all aspects of logistic and airdrop operations by providing computer-controlled event sequencing of all onload, offload, airdrop, and emergency functions from a single location. The multifunction control/display, located at the loadmaster position, provides control and display of all ECHS functions. The aircraft is capable of performing aerial delivery missions using manual, computer, or combined computer- and manual-controlled modes. DEFENSIVE SYSTEMS • Missile Warning System, AN/AAR-47 • Countermeasures Dispensing System, AN/ALE-47 • Radar Warning Receiver, AN/ALR-56M 29 28 Major Systems Major Systems additive. Deviations and flight restrictions are required for use of some fuels other than JP-8. • Group A provisions are provided on the lower side of each outer wing at outer-wing station 81.0 for optional installation of pylons and tanks. When the tanks/pylons are installed, each tank has a usable fuel capacity of 1,379 U.S. gallons (9,377 pounds or 18,754 pounds per aircraft). • The aircraft has the capability for single-point refueling (SPR) which is integrated into the fuel management system and controlled via the fuel management panel. Refueling quantities can be set for each tank. A manual over-the-wing fuel-filler cap is installed in each main tank. • Defueling normally is through the ground single-point refueling system using the fuel boost and dump pumps to supply pressure. Defuel quantities can be set for each tank at the fuel management panel. • Fuel dump controls are located on the fuel management panel located in the flight station. • Receiver P3I provisions are available for aerial refueling. • Tanker P3I provisions are included. HYDRAULIC SYSTEMS • Three separate hydraulic systems are controlled by engine-mounted or electrically driven pumps. The pumps for the booster system are mounted on engines three and four, and the pumps for the utility system are mounted on engines one and two. The auxiliary system is powered by an electrically driven pump located in the aft fuselage. Normal operating pressure is 3,000 pounds per square inch. • The booster system operates one-half of each control surface actuator. • The utility system operates the landing gear (including doors and steering), wing flaps, wheel brakes, and one-half of each control surface actuator. 31 30 Landing Roll – ft Landing Distance (Over 50 ft) – ft MAXIMUM EFFORT LANDING ROLL NORMAL LANDING DISTANCE (Over 50 Feet) (Four Engines/100 Percent Flaps/Standard Day) (100 Percent Flaps/Standard Day) Gross Weight – 1,000 lb Gross Weight – 1,000 lb 3,500 6,000 5,500 5,000 4,500 4,000 3,500 3,000 2,500 2,000 80 90 100 110 120 130 140 150 160 170 180 3,000 2,500 2,000 1,500 1,000 80 90 100 110 120 130 140 8 6 4 2 0 8 6 4 2 0 Altitude – 1,000 ft Altitude – 1,000 ft Performance Takeoff Distance – ft NORMAL TAKEOFF DISTANCE (Over 50 Feet) Takeoff Distance Over 50-Foot Obstacle (Four Engines/50 Percent Flaps/Standard Day) Gross Weight – 1,000 lb 9,000 8,000 7,000 6,000 5,000 4,000 3,000 2,000 1,000 80 90 100 110 120 130 140 150 160 170 0 2 4 6 8 Altitude – 1,000 ft 6,000 5,000 4,000 3,000 2,000 1,000 0 8 6 2 0 80 100 120 140 160 180 Takeoff Roll – ft Gross Weight – 1,000 lb MAXIMUM EFFORT TAKEOFF ROLL (Standard Day) Altitude – 1,000 ft 4 Performance 33 32 World Records Payload – 1,000 lb PAYLOAD RANGE Standard Day, MIL-C-5011A Reserves (Foam in Tanks) USAF Configuration Wing Relief Fuel Range – n.mi 00 1,000 2,000 3,000 4,000 10 20 30 40 50 175,000 lb 164,000 lb Performance LOCKHEED MARTIN C-130J CLAIMS 54 WORLD RECORDS The following records have been certified as world records: Class C-1.N Turboprop, Group II, Heavy Airplanes (132,276 to 176,368 lb) Records broken 15 Records set 6 Total 21 Closed Circuit (Speed and Distance) NEW RECORD USA, 396.17 mph; Lockheed Martin C-130J, 4/20/99 Breaks old record by 8 percent while carrying twice the payload BREAKS these existing records: 1,000 km speed with following payloads: 0 kg; 1,000 kg; 2,000 kg; 5,000 kg; 10,000 kg 54 WORLD RECORDS All in production-standard, unmodified aircraft These flights demonstrate that the C-130J can: • Carry a useful payload quickly over typical mission distance. • Get in and out of short fields quickly and carry useful payload. • Quickly climb to altitude with a significant payload. • Be flown a strategic distance quickly without external tanks or stopping to refuel. 35 34 World Records World Records ESTABLISHES these records: 1,000 km speed with 15,000 and 20,000 kg payloads NEW RECORD USA, 394.87 mph; Lockheed Martin C-130J, 4/20/99 Breaks old record by 16 percent while carrying twice the payload BREAKS these existing records: 2,000 km speed with following payloads: 0 kg; 1,000 kg; 2,000 kg; 5,000 kg; 10,000 kg ESTABLISHES these records: 2,000 km speed with 15,000 and 20,000 kg payloads Altitude NEW RECORD USA, 36,560 feet; Lockheed Martin C-130J, 4/20/99 Breaks old record by 18 percent while carrying twice the payload BREAKS these existing records: Altitude with following payloads: 0 kg; 1,000 kg; 2,000 kg; 5,000 kg; 10,000 kg ESTABLISHES these records: Altitude with 15,000 and 10,000 kg payloads The following short takeoff and landing (STOL) records have been certified as U.S. national records. STOL Aircraft, Class N, Group II, Turboprop Records broken 1 Records set 28 Total 29 Closed Circuit NEW RECORD USA, 371.6 mph; Lockheed Martin C-130J, 5/14/99 ESTABLISHES these records: 1,000 km speed with following payloads: 0 kg; 1,000 kg; 2,000 kg; 5,000 kg; 10,000 kg NEW RECORD USA, 371.96 mph, Arlen Rens (pilot), Lyle Schaefer (co-pilot), Lockheed Martin C-130J, 5/14/99 ESTABLISHES these records: 2,000 km speed with following payloads: 0 kg; 1,000 kg; 2,000 kg; 5,000 kg; 10,000 kg NEW RECORD USA, 22,300 lb; Lockheed Martin C-130J, 5/14/99 BREAKS this existing record: Greatest load to 2,000 meters NEW RECORD USA, 40,386 feet; Lockheed Martin C-130J, 5/14/99 ESTABLISHES these records: Absolute altitude with following payloads: 0 kg; 1,000 kg; 2,000 kg; 5,000 kg; 10,000 kg NEW RECORD USA, 39,052 feet; Lockheed Martin C-130J, 5/14/99 ESTABLISHES this record: Greatest altitude in horizontal flight (Note: Must hold this altitude for a minimum of 90 seconds) Time-to-Climb NEW RECORD USA, 3 min 49 sec; Lockheed Martin C-130J, 5/14/99 37 World Records ESTABLISHES these records: To 3,000 meters with following payloads: 1,000 kg; 2,000 kg; 5,000 kg; 10,000 kg NEW RECORD USA, 8 min 0 sec; Lockheed Martin C-130J, 5/14/99 ESTABLISHES these records: Time-to-climb to 6,000 meters with following payloads: 1,000 kg; 2,000 kg; 5,000 kg; 10,000 kg NEW RECORD USA, 15 min 12 sec; Lockheed Martin C-130J, 5/14/99 ESTABLISHES these records: Time-to-climb to 9,000 meters with following payloads: 1,000 kg; 2,000 kg; 5,000 kg; 10,000 kg Speed Over a Recognized Course NEW RECORD USA, 413.99 mph; Lockheed Martin C-130J, 12/7-8/99 ESTABLISHES these records: Speed over a recognized course, unlimited class; speed over a recognized course, class C-1.N Duration: 10 hours 58 minutes 14 seconds NEW RECORD USA, 417 mph; Lockheed Martin C-130J, 2/12-13/00 ESTABLISHES these records: Speed over a recognized course with 34,000 pounds of payload, unlimited class; speed over a recognized course with 34,000 pounds of payload, class C-1.N Duration: 9 hours 31 minutes 36 The information provided herein represents the opinions of Lockheed Martin Aeronautics Company. It does not constitute an offer to sell and is not warranted or guaranteed. Specifications and performance of individual aircraft may vary and will be governed by the terms and conditions of other documents. Lockheed Martin Aeronautics Company is not responsible for the accuracy or reliability of any opinion, advice or statement made herein and will not be liable for any damages of any kind, in any way relating to this information or its use. Lockheed Martin Aeronautics Company Marietta, Georgia A12-37957A001 Lockheed Martin Aeronautics Company Dept. 002H, MZ 0264 86 South Cobb Drive Marietta, GA 30063-0264 www.lockheedmartin.com