201 Airframe System Eaws H-60S

Front 1

what makes up the airframe system and where is it located, what is its function

Back 1

Airframe system [ref. a, WP 001] A
a. Cockpit section [WP 003 00, p. 2] A B - The cockpit section is the area of the fuselage forward of station 247. It includes an avionics compartment, and also accommodates the pilot and copilot, and associated systems components. Battery is in the copilot seatwell.
b. Cabin section [WP 005 00, p. 2] A B - The cabin section interconnects the cockpit and transition section. The cabin is entered through an aft sliding cabin door on the both sides of the helicopter. The common equipment for MH-60S configurations consist of junction boxes, seats, gunners ICS CSCs, fire extinguishers, first aid kit, search and rescue bag, rescue sling, trail line/weight, marker rack, medical kit, APU pump handle, and relief tube.
c. Transition section [WP 007 00, p. 2] A B - The transition section interconnects the cabin section and the tail cone. It houses the fuel cells and related fuel system

components, mission equipment, and U. It also supports the tail landing gear, oil cooler and right hand stores pylon.
d. Tail cone [WP 008 00, p. 2] A B - The tail cone section interconnects the transition section and the tail rotor pylon. It is made up primarily of aluminum frame members and stringers.
e. Tail rotor pylon [WP 009 00, p. 2] A B - The tail rotor pylon is a foldable section at the aft end of the helicopter. The pylon is supported by and hinged to the tail cone section. It supports the horizontal stabilator, intermediate gearbox, tail gearbox, connecting tail rotor drive shaft, tail rotor assembly, and part of the flight controls.
f. Main rotor pylon [WP 010 00, p. 2] A B - The main rotor pylon is attached to the upper cabin and transition section. The forward section is made up of a sliding controls/accessories access fairing, removable platform, air inlet fairings, and engine air inlets. The midsection includes the #1 and #2 work platform/engine access, left and right oil cooler access, environmental control system (ECS) access, APU inlet, APU access, and exhaust module, hover infrared suppressor system (HIRSS). The aft section contains the fire bottle access and aft fairing. The main rotor pylon is a protective aerodynamic covering, which shelters the helicopter major subsystem components, below it, from the elements. It is also designed to provide smooth airflow induction for cooling of those components.

Front 2

what makes up the Wire strike protection system where is it located, what is its function

Back 2

Functions - The Wire Strike Protection System is designed to protect the helicopter in cases where the airframe comes in contact with wires in its path of flight. The system consists of a series of deflectors and cutter blades designed to prevent wires from becoming caught on protrusions, which could damage the helicopter and cause it to crash. Locations -
Cowling Cutter - (1) Located on the forward most part of the Hydraulics Bay cover. Main Landing Gear Cutter - (2) One is located on each Main landing Gear.
Main Landing Gear Joint Deflector - (2) One located on each side, Flotation Bag Access Cover.
Main Landing Gear Wheel Deflector- (2) One located each side below main landing gear cutter.
Step Deflector - (4) Two located on each side one on each step and one located beneath cockpit doors.
Upper Cutter - (1) Located at aft end of Hyd. Bay access cover
Windshield Deflector - (2) Located on front windshield on both sides of the center window.
Wiper Post Deflector - (2) One located in front of left and right windows.
Total Deflectors - 12
Total Cutters - 4

Front 3

what makes up the Flight controls/surfaces where are they located and what is its function

Back 3

a. Main rotor blades [ref. c, WP 004 00, p. 2] A B - Four main rotor blades provide lift and thrust for the helicopter. Tip cap is swept back at a 20-degree

angle to reduce noise and increased blade performance. They receive power from the main rotor head to which they are attached. The root (inboard end of the main rotor blade) allows bolting the main rotor blades to the main rotor head. A heater mat in the main rotor blade leading edge provides blade deicing, and is connected to the blade deicing system.
b. Main rotor head [ref. c, WP 003 00, pp. 2, 5] A B - The main rotor head transmits the movements of the flight controls to the four main rotor blades. Rotates counterclockwise when viewed from above and is controlled through flight control hydraulic servos.
c. Tail rotor [ref. c, WP 005 00, p. 2] A B - The tail rotor provides directional control and anti-torque reaction, and provides 2.5% lifting force in a hover.
d. Horizontal stabilator [ref. a, WP 009 00, p. 1; ref. j, p. I-2-73] A B The horizontal stabilator is attached to the tail rotor pylon keeping the bird level through forward flight.
e. Cyclic stick [ref. d, WP 003 00, par. 25] A B - The cyclic stick is located in the cockpit. The pilot and copilot each have one. They are mechanically coupled lever-type controls and it controls forward, aft, and lateral movements.
f. Collective stick [ref. d, WP 003 00, par. 26] A B - The collective stick is located in cockpit. Pilot and copilot each have one. Is used to simultaneously change the pitch of all of the main rotor blades. The pitch change causes either an increase or decrease in lift on the entire main rotor disc.
g. Rudder pedal [ref. d, WP 003 00, par. 24] A B - The rudder pedal is located in the cockpit. Pilot and Copilot each have a set. Is mechanically coupled and controls heading. Pedals contain independent toe-operated wheel brake master cylinders and are adjustable to the pilot and copilot leg lengths. Pedals contain switches, which can disengage the AFCS heading hold feature.

Front 4

what makes up the Hydraulic components where are they located and what is the function

Back 4

a. Reservoirs [WP 003 00, par. 85] A B - The reservoirs are on the right side of the upper deck (Hydraulic Bay). They are used to service/refill the pump module reservoirs and the rotor brake system. (In front of the #2 A/C generator).
b. Pumps [WP 003 00, par. 66] A B - The pumps are: #1, 2 and b/u pump modules, Combination pumps and reservoirs. Provides hydraulic pressure from the pump modules to the primary servos.
c. Servos [WP 003 00, pars. 80 thru 81] A B - The servos are: 3 Primary servos, FWD, AFT and Lateral. Absorbs feedback forces from the main rotor. Set of pilot/assist servos reduces load at the collective sticks, and the rudder pedals and longitudinal loads at the cyclic stick.

Front 5

what is the main landing gear and its function

Back 5

.5 Main landing gear [ref. a, WP 011 00, pars. 2, 3] A - The main landing gear supports the helicopter when on the ground, and cushions the helicopter from shock while landing. The weight on wheels switch provides helicopter ground/flight status indications for various helicopters systems.

Front 6

what is the tail landing gear and its function

Back 6

The tail landing gear is a single wheel trailing-arm type, on a universally mounted shock strut. The system is designed to cushion landing shock and facilitate taxiing on the ground. The single wheel gear is

capable of swiveling 360 degrees and can be locked to the trail position by a remotely controlled lock pin.

Front 7

what is the Rescue hoist and its function and location

Back 7

The rescue hoist provides a means of rescuing downed personnel. Has a load capacity of 600 pounds. Located on the starboard side over cabin door.

Front 8

what is the cargo hook and it s function and location

Back 8

The cargo hook is used to carry external cargo. Located underneath the belly of the aircraft with access via the cabin decking.wh

Front 9

what are the fire detectors, their function and location

Back 9

Fire detectors provide visual warning in the cockpit when there is a fire in either the engine compartment or the APU compartment. Location - 5 flame detectors, two in each engine compartment and one for the APU.

Front 10

what are the Fire extinguishers their function and location

Back 10

Fire extinguishers provide two-shot (main and reserve) capability to either main engine compartment or the APU compartment. The system consists of two fire bottles, an overboard-thermal relief outlet and discharge indicator, a direction control valve, and a relay. Location - in overhead of transition section.

Front 11

what is the Environmental Control System (ECS) its function and location

Back 11

ECS provides heating and cooling for the cockpit, cabin areas, nose avionics compartment, and transition section. Consists of an air-cycle machine, water separator, heat exchanger, bleed-air ducting, ECS controller, modulating valve, ECS control panel, and associated valves, sensors, and switches. Supplemental or backup air circulation is provided at all crew stations by manually controlled air inlets for outside air. Lower console cooling is provided by a fan in the lower console. The ECS temperature is monitored by pressure and duct over temperature switches. These switches provide monitoring and protection of the ECS.

Front 12

what warnings and cautions must be observed when working with a rescue hoist

Back 12

Warnings - Do not handle explosive material or ordnance unless certified. Rescue hoist cable is stiff and abrasive. Broken cable strands are sharp. Work gloves should be worn whenever handling rescue hoist cable. The rescue hoist cable must be kept clear of all parts of the aircraft and free from other external obstacles when operating the rescue hoist. Cable abrasion during rescue hoist operations can lead to cable failure. If cable contact or snagging occurs, suspend rescue hoist operations and inspect the cable for damage.

Cautions - The emergency shear function electrically activates a pressure cartridge (squib). If cartridge connector P6 is connected, weight on wheels circuit breaker is open, and EMER REL on either cyclic stick is pressed, hoist will shear. This may also occur using crew hover control panel hoist shear switch. Pressing the auto control - push to reset pushbutton switch on stabilator control panel with electrical power on, turns on the stabilator system. This could damage the stabilator and pylon, if they are folded. Backup control power switch on rescue hoist control panel should be used for emergency operations only. Severe fouling and backwinding of rescue cable can result, leading to damage of rescue hoist. Make certain switch cover is shear wired after use. When paying out rescue hoist cable, cable must not be restrained from motion. Maintain tension on cable during hoist operation to avoid damage to hoist. An observer is necessary to make certain cable feeds properly and does not tangle. Full-in and full-out limit switches do not function in backup control power operations. Operating hoist beyond red and red/white or orange colored warning areas on cable can result in severe damage to hoist and will render hoist inoperable. Operate hoist in the mode carefully and only for time duration specified.

Front 13

what warnings and cautions must be observed when working with Flight controls

Back 13

Warning - This checkout procedure requires moving the flight controls. To prevent injury or damage, keep personnel and equipment away from area of flight controls.
Caution - With hydraulic power on and primary servo input linkage disconnected, primary servo power pistons will extend to their full limit. This will cause damage to swashplate uniball bearing. Stow collective stick prior to exiting the aircraft to prevent damage.

Front 14

what warnings and cautions must be observed when working with tail pylon

Back 14

Warnings- Before folding pylon, make sure that area on left side of tail cone is clear of personnel and obstructions. To prevent injury to personnel and damage to helicopter, adhere to the following: do not fold tail pylon in winds in excess of 45 knots, keep fingers clear of lockpin lug holes during tail rotor pylon and stabilator fold procedures.
To prevent accidental slipping of pylon fold pole, make sure that quick release pin button is extended. Slightly lift on pylon fold pole and grasp quick release pin by collar and pull down verifying that pin is properly locked.
Cautions
Make sure main rotor blade gust lock is engaged and rotor brake is on before folding tail pylon. Failure to electrically or manually index/secure tail rotor system prior to pylon fold may result in high speed windmilling of tail rotor and cause bent/broken extension shaft or housing on TRB positioning actuator. With tail rotor index shaft extended, any rotation of tail rotor can result in damage to index shaft. When folding pylon, left stabilator must be folded before unlocking pylon. Make sure main rotor blade gust lock is engaged and rotor brake is on before folding tail pylon. Make sure stabilator is in full trailing edge down position before folding stabilator.

Front 15

State the safety precautions that must be observed when the following are operating
Main rotor head
Tail rotor
Stabilators

Back 15

a. Main rotor head [ref. b, WP 009 00, par. 1] - Keep clear of helicopter when main rotor blades are turning. Droop stop malfunction could permit blades to droop within 5 feet of ground. In addition, under gusty wind conditions, it may be necessary for pilot to take off unexpectedly. Wear Goggles during ground runup of main rotor blades to keep flying dust, debris, and particles from entering eyes.
b. Tail rotor [ref. b, WP 009 00, par. 1] - Keep clear of aft fuselage when tail rotor is turning. Pilot may have to turn sharply during normal control movements when taxiing into wind gusts.
c. Stabilators [ref. k, WP 004 00, par. 7] - When pylon and stabilator are spread, the stabilator moves trailing edge down when electrical power is first applied. Ensure personnel and equipment are clear of this area prior to applying power. When stabilator is slewed to the 0 degree position (stabilator horizontal), the stabilator provides a head strike hazard. This is especially dangerous when approaching aircraft from the rear (towards trailing edge.)