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40 Cards in this Set
- Front
- Back
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201.1.1 State the function and location of the Cockpit section.
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The area of the fuselage forward of station 247. Includes an avionics compartment, the pilot and co-pilot and associated system components. The battery is in the co-pilot seat-well.
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201.1.1 State the function and location of the Cabin section.
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Interconnects cockpit and transition section. Enter through aft cabin center sliding door on the right side. Contains crew/passenger seats and associated mission equipment.
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201.1.1 State the function and location of the Transition section.
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Interconnects cabin and tail-cone section. It houses fuel cells and associated fuel system components and APU/ECS.
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201.1.1 State the function and location of the Tail cone.
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Inter connects transition and tail rotor pylon section. Supports tail drive shaft and houses tail flight control cables.
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201.1.1 State the function and location of the Tail rotor pylon.
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Foldable section at aft end of aircraft. Hinged to tail cone. Supports stabilator, intermediate/tail gearbox, and tail rotor assembly, lines, and cables.
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201.1.1 State the function and location of the Main rotor pylon.
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Attached to upper cabin section. A protective aerodynamic covering which shelters the aircraft’s major subsystem components. It is also designed to provide smooth air flow induction for cooling of major components.
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201.1.2 State the function and locations of the Wire Strike Protection system.
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Designed to protect the aircraft in cases where airframe comes in contact with wires in its path of flight. Consists of a series of deflectors and cutter blades designed to prevent wires from becoming caught on protrusions which could cause aircraft to crash.
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201.1.3 State the function and location of the following flight control/surface: Main rotor blade
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Attached to main rotor hub. Provides thrust and lift for the aircraft. Consists of titanium cuff and kevlar tipcap. Pressurized with Nitrogen to detect cracks.
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201.1.3 State the function and location of the following flight control/surface: Main rotor head
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Transmit movements of flight controls to the four main rotor blades. Controlled through flight control hydraulic servos, which moves swash plate to change pitch of blades.
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201.1.3 State the function and location of the following flight control/surface: Tail rotor
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A bearingless, controllable pitch, crossbeam type system. Located on top of tail rotor pylon. Controls yaw of aircraft (heading).
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201.1.3 State the function and location of the following flight control/surface: Horizontal stabilator
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Controllable airfoil attached to the lower portion of the tail rotor pylon. Controlled by two series electric screwjack actuators. Can be controlled automatically or with manual slew switch.
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201.1.3 State the function and location of the following flight control/surface: Cyclic stick
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Located in cockpit for pilot and co-pilot. Controls forward, aft, and lateral movements of helicopter.
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201.1.3 State the function and location of the following flight control/surface: Collective stick
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Located in cockpit for pilot and co-pilot. Used to simultaneously change pitch of all main rotor blades. Causes either increase or decrease in lift.
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201.1.3 State the function and location of the following flight control/surface: Rudder pedal
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Two sets in cockpit. Mechanically coupled and control helicopter heading. Also operate toe operated wheel brake master cylinders and are adjustable to leg length.
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201.1.4 State the function and location of the following hydraulic component: Reservoirs
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One for #1 and one for #2 hydraulic pump, backup pump and utility hydraulic pump (SH-60F only). Has a sight window and color coded tape to indicate level of fluid. Located next to each pump. Holds the hydraulic fluid for the pump.
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201.1.4 State the function and location of the following hydraulic component: Pumps
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(1) Backup pump - Located on the deck; electrically operated to supply 1st and 2nd stage hydraulic pressure for flight controls when rotor head is engaged (turning).
(2) Utility pump - Located aft right side main gearbox. Provides hydraulic pressure for sonar reeling machined and rescue hoist when rotor is engaged (turning). On SH-60F only. |
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201.1.4 State the function and location of the following hydraulic component: Servos
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(1) Tail Rotor Servo - One dual stage servo located on tail rotor to move tail rotor blades. Only one stage is pressurized at a time. Normal/Backup.
(2) Pilot Assist Servo - Used to reduce load at collective and cyclic sticks and tail rotor pedals via SAS and DAFCS inputs applied to servos. |
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201.1.5 State the function of the Main landing gear.
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Consists of a non retractable single-wheel assembly. Each assembly is composed of shock struts, drag beam, axle, wheel tire, and wheel brake. The port main landing gear also includes a weight on wheels sensing switch.
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201.1.5 State the function of the Tail landing gear.
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Consists of dual-wheel landing gear, tail wheel lock system and tail bumper. Gear is capable of swiveling 360°. It can be locked in trail position.
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201.1.5 State the function of the Recovery Assist Secure Traverse (RAST) system.
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Provides means to assists landing and securing helicopter on flight deck of a small sea going ship. Includes main probe, tail probe, messenger cable, and main probe hoist.
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201.1.6 State the function and location of the Rescue hoist.
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Located starboard side of aircraft above cabin door. Provides means of rescuing downed personnel. Hoist has a load capacity of 600 lb. Electrically controlled and hydraulically powered. Speed capability of 0 to 215 feet per minute.
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201.1.6 State the function and location of the Cargo hook.
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Located under cabin section. Used to carry external cargo. Loads can be released electrically or manually. It has a load capacity of 6,000 lb.
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201.1.6 State the function and location of the Fire detectors.
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Provides a visual warning in cockpit when there is a fire in either engine or APU compartment. An associated “T” handle warning light will illuminate. There are five flame detectors to provide complete fire surveillance.
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201.1.6 State the function and location of the Fire extinguishers.
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Provides two-shot (main and reserves) fire extinguishing capability. The System consists of only two fire bottles. The bottles are located in the upper deck aft of the APU; charged with 600 PSI Nitrogen and 2.5 lb. Bromotrifluromethane.
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201.1.4 State the function and location of the following hydraulic component: Reservoirs
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One for #1 and one for #2 hydraulic pump, backup pump and utility hydraulic pump (SH-60F only). Has a sight window and color coded tape to indicate level of fluid. Located next to each pump. Holds the hydraulic fluid for the pump.
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201.1.4 State the function and location of the following hydraulic component: Pumps
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(1) Backup pump - Located on the deck; electrically operated to supply 1st and 2nd stage hydraulic pressure for flight controls when rotor head is engaged (turning).
(2) Utility pump - Located aft right side main gearbox. Provides hydraulic pressure for sonar reeling machined and rescue hoist when rotor is engaged (turning). On SH-60F only. |
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201.1.4 State the function and location of the following hydraulic component: Servos
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(1) Tail Rotor Servo - One dual stage servo located on tail rotor to move tail rotor blades. Only one stage is pressurized at a time. Normal/Backup.
(2) Pilot Assist Servo - Used to reduce load at collective and cyclic sticks and tail rotor pedals via SAS and DAFCS inputs applied to servos. |
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201.1.5 State the function of the Main landing gear.
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Consists of a non retractable single-wheel assembly. Each assembly is composed of shock struts, drag beam, axle, wheel tire, and wheel brake. The port main landing gear also includes a weight on wheels sensing switch.
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201.1.5 State the function of the Tail landing gear.
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Consists of dual-wheel landing gear, tail wheel lock system and tail bumper. Gear is capable of swiveling 360°. It can be locked in trail position.
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201.1.5 State the function of the Recovery Assist Secure Traverse (RAST) system.
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Provides means to assists landing and securing helicopter on flight deck of a small sea going ship. Includes main probe, tail probe, messenger cable, and main probe hoist.
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201.1.6 State the function and location of the Rescue hoist.
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Located starboard side of aircraft above cabin door. Provides means of rescuing downed personnel. Hoist has a load capacity of 600 lb. Electrically controlled and hydraulically powered. Speed capability of 0 to 215 feet per minute.
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201.1.6 State the function and location of the Cargo hook.
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Located under cabin section. Used to carry external cargo. Loads can be released electrically or manually. It has a load capacity of 6,000 lb.
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201.1.6 State the function and location of the Fire detectors.
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Provides a visual warning in cockpit when there is a fire in either engine or APU compartment. An associated “T” handle warning light will illuminate. There are five flame detectors to provide complete fire surveillance.
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201.1.6 State the function and location of the Fire extinguishers.
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Provides two-shot (main and reserves) fire extinguishing capability. The System consists of only two fire bottles. The bottles are located in the upper deck aft of the APU; charged with 600 PSI Nitrogen and 2.5 lb. Bromotrifluromethane.
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201.1.7 State the function(s) of the Environmental Control System (ECS).
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Provides heating and cooling for the cockpit, cabin, nose avionics compartment, and transition section.
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201.5.1 What cautions or warnings must be observed when the Rescue Hoist is operating?
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Do not handle explosive material or ordnance unless certified. The emergency shear function electrically activates a pressure cartridge (squib), if P6 is connected and weight on wheel circuit breaker is open. Backup control power switch should be used for emergency use only. Fouling of cable could occur, leading to damage of rescue hoist.
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201.5.1 What cautions or warnings must be observed when the RAST is operating?
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Personnel shall remain clear of main RAST probe. Inadvertent operation of emergency release lever when probe is retracted may cause probe to extend, causing death or personal injury.
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201.5.1 What cautions or warnings must be observed when the Flight Controls are operating?
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All flight control check-outs are done with hydraulic pressure off. To avoid injury, keep hands and feet clear of moving parts. Operate hydraulic pump IAW operating limits to prevent overheating of back-up hydraulic system.
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201.5.2 State the safety precautions that must be observed when the Main Rotor Head is operating.
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Keep clear of main rotor blades. Droop stop malfunction could permit blades to droop within five feet of the ground.
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201.5.2 State the safety precautions that must be observed when the Tail Rotor is operating.
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Keep clear of aft fuselage when tail rotor is turning. Blades will cut your head off.
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