Military

The purpose of this appendix is to list aircraft characteristics and planning considerations for the use of utility and cargo aircraft. It is not designed to cover all aircraft characteristics, but those deemed critical in the planning of successful utility and cargo helicopter operations.

This section discusses aircraft characteristics, capabilities and limitations of the UH-60A/L Black Hawk helicopter.

a. Characteristics.

(1) The UH-60A/L is a twin-engine, single rotor helicopter. Primary mission capability of the helicopter is air assault and air movement. Secondary missions include SASO, CSAR, C² platform, CASEVAC, and air Volcano (mine setting) during day, night, visual, and instrument conditions.

(2) The aircraft is approximately 65 feet long with, approximately, a 54-foot main rotor span.

(3) Maximum gross weight for the UH-60A is 22,000 pounds. Maximum gross weight for the UH-60L is 22,000 pounds. (With an external load exceeding 8,000 pounds, the maximum gross weight is 23,500 pounds.)

(4) Maximum airspeed is 193 knots with a normal cruise speed of 130 knots. However, the speed for any mission will vary greatly depending on load configuration (internal or external), time of day, weather conditions, METT-T, etc.

(5) The minimum crew for tactical missions is four, two pilots and two crew chiefs. It is essential that two crew chiefs be used when conducting air assault, NVG operations, and sling loads.

(6) The aircraft can be operated in light or moderate turbulence.

(7) The aircraft can be operated in IMC.

b. Capabilities.

(1) The UH-60A cargo hook can carry external loads up to 8,000 pounds. The UH-60L cargo hook can carry external loads up to 9,000 pounds.

(2) With seats install, the UH-60A/L can carry up to 11 combat-loaded troops. With seats removed, the UH-60A/L can carry up to 16 combat-loaded troops or up to 20 troops without full combat load.

(3) Aircraft internal loads can be up to maximum gross weight, with a limitation of aircraft space and loading not to exceed 300 pounds per square foot.

c. Limitations.

(1) UH-60A/L endurance is 2.5 hours without external fuel tanks and 5.0 hours with external fuel tanks.

(2) UH-60A/L combat radius is approximately 225 kilometers.

(3) UH-60A/L combat radius, with external fuel tanks installed, is approximately 450 kilometers.

(4) The UH-60A/L shall not be started or shutdown in winds (including gusts) in excess of 45 knots.

(5) UH-60A/L helicopters with the following equipment installed can fly into trace or light icing conditions; however, flight into light is not recommended without the blade deice kit:

• Windshield anti-ice.
• Pitot heat.
• Engine anti-ice.
• Engine inlet anti-ice modulating valve.
• Insulated ambient air sensor.

For flights into moderate icing conditions, all the equipment listed above and the blade deice kit must be installed and operational.

This section discusses aircraft characteristics, capabilities, and limitations of the CH-47D Chinook helicopter.

a. Characteristics.

(1) The CH-47D is a twin-engine, tandem rotor helicopter designed for transportation of cargo, troops, and weapons during day, night, visual, and instrument conditions.

(2) The aircraft fuselage is approximately 50 feet long. With a 60-foot rotor span, on each rotor system, the effective length of a CH-47D (with blades turning) is approximately 100 feet from the most forward point of the forward rotor to the most rearward point on the aft rotor.

(3) Maximum gross weight is 50,000 pounds.

(4) Maximum airspeed is 170 knots with a normal cruise speed of 130 knots. However, speed for any mission will vary greatly depending on load configuration (internal or external), time of day, weather conditions, METT-T, etc.

(5) The minimum crew for tactical operations is four, two pilots, one flight engineer, and one crew chief. For more complex missions, such as NVG operations and air assaults, commanders may consider using five crew members and add one additional crew chief.

(6) The aircraft can be operated in light or moderate turbulence.

(7) The aircraft can be operated in IMC.

b. Capabilities.

(1) Cargo hook (external load). The limits presented below are structural limitations only.

(a) The structural limit of the forward and aft hook is 17,000 pounds.

(b) The maximum single load that can be suspended as a tandem load from the forward and aft hooks is 25,000 pounds.

(c) The center cargo hook is limited to a maximum load of 26,000 pounds.

(2) Load configuration. Consideration must be given to the advantages and disadvantages of any particular external load configuration. For example, while it is generally true that a tandem load will ride better and permit a higher airspeed, it is also true that a tandem load usually requires ground personnel to attach the load to the aircraft. All appropriate references must be researched to insure compliance with any directives regarding load configuration, that is, many loads allow center hook or tandem hook attachment.

(3) Internal load.

(a) Troop seating arrangement for up to 31 fully equipped ground troops is provided in the CH-47D. This is broken down by 10 three-man seats and 3 one-man seats (See Figure A-1). This total number varies greatly due to the configuration of the aircraft's interior. For example, is the aircraft equipped with a single ERFS tank, or is the crew required to carry additional survival equipment due to extreme weather? This factor requires extensive consideration before committing a specific number of aircraft with a specific ACL to a given mission. Additionally, the troop commander's jump seat may be available, but is unwieldy and time consuming to use. Troops are normally loaded and unloaded through the lowered aft cargo door and ramp.

(b) The CH-47D litter arrangement provides for up to 24 litters. These 24 litters are configured in six tiers of four litters each (see Figure A-2). In this 24-litter configuration, it may be possible to leave the three, one-man seats in position. It is not necessary to remove the troop seats to install the litters.

(c) Cargo loading (internal). The dimensions of the cargo compartment are 366 inches long, 90 inches wide, and 78 inches high. These dimensions are uniform throughout the cargo compartment. However, there are some restrictions when fitting items through the two doors; reference TM 55-1520-240-10. This same TM should be referenced for detailed information on tie-down points, etc.

(d) Helicopter internal cargo handling system. CH-47D units have the necessary equipment for four aircraft to be equipped with HICHS. This system provides for quick loading, securing, and unloading of palletized cargo. The system generally uses either the 463L pallet (up to 3 simultaneously) or warehouse wooden pallets (up to 10, depending on size). While cargo can be carried without the use of the HICHS, this system expedites the loading and unloading process.

(e) Winch/hoist system. The CH-47D is equipped with a 3,000 pounds capacity hydraulically operated winch that can be employed in either of two modes. For the purpose of loading and unloading cargo internally, this system is used in the CARGO mode. This mode permits the winching of cargo up to 3,000 pounds on a straight-line pull, or up to 12,000 pounds. with the aid of pulley blocks. The remaining mode, described as the RESCUE mode, permits the use of this system as a rescue hoist (up to 600 pounds) and is not used for cargo loading.

b. Limitations.

(1) CH-47D endurance is 2.5 hours without ERFS tank(s) and 4.0 hours with one ERFS tank installed.

(2) The combat radius of the CH-47D is approximately 225 kilometers.

(3) The combat radius of the CH-47D, with one ERFS tank installed, is approximately 350 kilometers.

(4) The aircraft shall not be started or shutdown in winds (including gusts) in excess of 30 knots.

(5) Continuous flight in light-icing conditions below 5 degrees C is not recommended since blade damage can occur from asymmetric ice shedding.

This section discusses aircraft characteristics, capabilities, and limitations of the UH-1H helicopter.

a. Characteristics.

(1) The UH-1H is a single engine, single rotor helicopter. Primary mission capability of the helicopter is air movement of supplies and personnel. Secondary missions include SASO, air assault, and C² operations under day, night, visual, and instrument conditions.

(2) The aircraft is approximately 57 feet long with a 48-foot main rotor span.

(3) Maximum gross weight is 9,500 pounds.

(4) Maximum airspeed is 124 knots (roof mounted pitot tube) or 112 knots (nose mounted pitot tube), with a normal cruise speed of 100 knots. However, the speed for any mission will vary greatly depending on the load configuration, time of day, and weather conditions.

(5) The minimum crew for tactical operations is three, two pilots and one crew chief.

(6) The aircraft can be operated in IMC.

b. Capabilities.

(1) The UH-1H cargo hook can carry external loads up to 4,000 pounds.

(2) With seats install, the UH-1H can carry up to 11 combat-loaded troops.

(3) Aircraft internal loads can be up to maximum gross weight, with a limitation of aircraft space and loading not to exceed 100 pounds per square foot.

c. Limitations.

(1) The UH-1H endurance is approximately 2.5 hours without auxiliary fuel tanks and approximately 6 hours with auxiliary fuel tanks. Note: The auxiliary fuel tanks in the UH-1H are mounted internally, which reduces the passenger and cargo carrying capacity of the helicopter.

(2) The aircraft shall not be started with winds in excess of 30 knots or a gust spread of 15 knots or greater.

(3) Intentional flight into known moderate icing conditions is prohibited.

(4) Intentional flight into moderate turbulence is not recommended. Flight into severe or extreme turbulence is prohibited.

Figure A-3 shows the strategic air movement planning factors for UH-60 and CH-47.