Curso de Sikorsky

Introduction INTRODUCTION – AIRCRAFT GENERAL – STRUCTURE PUBLICATIONS – MAINTENANCE PROGRAM –

AIRWORTHINESS LIMITATIONS TRANSMISSIONS AND DRIVES ROTOR SYSTEMS – FLIGHT CONTROLS HYDRAULIC SYSTEMS/AUTOMATIC FLIGHT CONTROL

SYSTEM (AFCS) LANDING GEAR ELECTRICAL ICE AND RAIN PROTECTION – AIR CONDITIONING FIRE DETECTION AND PROTECTION FUEL SYSTEM ENGINES AND RELATED SYSTEMS

Sikorsky Family Tree

S61 model derived from military version SH-3A

4 Commercial variants derived from military version

S-61N (RETRACTABLE GEAR)

S-61N (FIXED GEAR)

S-61N “SHORTSKY”

S-61NM

S-61L

S61-A

Aircraft General The Sikorsky S61 helicopter is a five bladed single main rotor system with a

5 blade anti-torque tail rotor. It is powered by two General Electric CT58-140-1 or -2 engines capable of

producing 1500 shaft horsepower. The aircraft is fitted with fixed, non-retractable landing gear. The main

landing gear fitted with two main wheels per side and also a tail landing gear fitted with a single wheel.

Two separate hydraulic systems are used in conjunction with the mechanical linkage of the flight controls. The primary and auxiliary hydraulic systems provide hydraulic boost to the primary servocylinders and the auxiliary servocylinder which is linked to the Automatic Flight Control System (AFCS).

A passenger cabin is provided with seating for up to 19 passengers and or provisions for cargo handling. The aircraft also has external hard points for fitting a cargo hook enabling external loads of up to 10,000 lbs.

The S61 model was issued FAA Type Certificate # 1H15 in 1961 for the “L” model and 1963 for the “N” model.

Dimensions and AreasROTARY WING DISK DIAMETER 62 FT

ROTARY RUDDER DISK DIAMETER 10FT 7.25 IN

WIDTH (BLADES STATIONARY) 62 FT

WIDTH (BLADES REMOVED) 14 FT 8 IN

LENGTH (MAXIMUM) 72 FT 10 IN

LENGTH (MINIMUM) 67 FT 11 IN

HEIGHT (MAXIMUM) 18 FT 11.62 IN

Stations, Water lines, Buttock Lines

Stations: Vertical divisions of the helicopter from forward to aft

Water Lines: Horizontal divisions of the helicopter from bottom to top

Buttock Lines: Vertical divisions of the helicopter from the left and to the right of the center line.

The center line (B/L 0) is a line running through the exact center of the helicopter

Stations, Water Lines, Buttock LinesS-61N

FS “0” is 32 inches forward of the nose

Major Sections and Components

The three major fuselage frames are:FS 110 (Flight Compartment)FS 243.5 (Front support for MGB)FS 290 (Rear support for MGB)

STRUCTURE Fuselage constructed mainly of

aluminum Semi monocoque design utilizing

structural framing and skin plating for strength

Engine compartment skin is stainless steel and heat resistant titanium

Fairings, access doors and covers made of fiberglass

STRUCTURE Pylon supports the intermediate and

tail gearboxes, rotary rudder and horizontal stabilizer.

Pylon acts as a vertical stabilizer in forward flight

Horizontal stabilizer increases stability during forward flight

Fuselage

Main SectionsCockpit (B) Engine Compartment (F)Electronics compartment (C) Transmission Compartment (G)Cabin (H)Rear fuselage (Q)Pylon (R)

Pylon Attached to rear

fuselage Supports IGB, TGB

and rotary rudder Horizontal stabilizer

attached

Horizontal Stabilizer Provides stability

while in forward flight

Rib type airfoil Supported by

tubular strut Discharge wicks to

dissipate static electricity

Horizontal Stabilizer

Cabin Seating Can seat up to 19

passengers without a flight attendant using various seat configurations

Single or double seats

Can be removed for cargo transport

S61-N

DOORS AND EXITSDUAL LATCHING MECHANISMS ENABLED TO BE OPERATED FROM THE INSIDE OR OUTSIDE

Total of 7 exits

Passenger Door

Cockpit Escape hatch Installed either side

of cockpit Can be opened from

inside or outside Sliding window

version Vertical reference

bubble version

Cabin Windows

Can be pushed inside or outside of cabin

Cabin Escape Hatches Dual latch

mechanism Can be easily

removed

Cabin Emergency Door Located L/H rear

cabin Serves as Escape

Hatch

Service Doors Located throughout

helicopter Enables

performance of maintenance and servicing

Main Battery Access

Service Doors

Nose Door

Service Doors Engine Platforms Transmission

Platforms Oil Cooler Access

Panels Engine Exhaust

panels

Engine Platforms Installed left and

right hand side of engines

Work platforms for engine maintenance

Capacity to support two persons only

Engine Service Platform

Transmission Service Platforms

Transmission Platform

Servicing

Servicing FluidsDamper fluid tank: hydraulic fluid Aeroshell Fluid 41 (Mil-H-5606)

Main rotor hinge oil tanks: MIL-L-21260Braco 443 or Shell Rotella 0W30

Primary and Auxiliary oil tanks: Aeroshell Fluid 41

Servicing Fluids

Aeroshell 750

Servicing Fluids

Aeroshell Fluid 41Nitrogen

Aeroshell Fluid 41Nitrogen

Aeroshell Fluid 41

Fluid QuantitiesSystem Capacity (US

Gallons)Capacity (Liters)

Remarks

Fuel 210 794.9 Front tank

244 923.5 Center tank

200 757.1 Aft tank

Engine Oil 2.5 9.5 Oil tank

Primary Hyd 0.45 1.7

Auxiliary Hyd 0.45 1.7

Rotary Wing head oil tank

0.14 0.67

Damper tank 0.57 2.15

MGB 9.0 34.1

IGB 0.29 1.1

TGB 0.38 1.42

Draining

DrainingMain gearbox

Draining

Tail gearbox

Draining

Intermediate gearbox

Draining

Main rotor head

Damper reservoir

Draining

Damper reservoir

Engine oil tank

Draining

Hull drain

Fuel tank drain

Draining

Pitot Drain Tubes

Lubrication

Lubrication

Lubrication

Lubrication

Lubrication

Lubrication

Lubrication

Ground Handling

Mooring and Tie-Down

For jacking main gear 5 ton capacity jacks required

For jacking tail gear 3 ton jack required

Airworthiness Directives




Total of 47 AWD’s issued for aircraft


Total of 17 AWD’s for engine

Airworthiness Limitations

Life limited parts listed on Sikorsky Service Bulletin 61BGen-1

Overhaul limits listed on Sikorsky Service Bulletin 61BGen -2

Airworthiness Limitations

Maintenance Manuals Provide complete maintenance

instructions Manual preparation and format IAW

ATA Specification 100 Airframe manuals provided by Sikorsky Engine manuals provided by General

Electric (CT58 series engine)

Maintenance ManualsGroup/Chapter Title General Contents

5 Time limits Unscheduled maint checks

6 Dimensions & Areas Dimensions, stations

7 Lifting Lifting, hoisting

8 Leveling & weighing Weighing

9 Towing & taxiing Towing

10 Parking & mooring Parking

11 Placards Placards & stencils

20 Standard practices Torquing, shop terms

21 Air conditioning Heater, cooling

22 Auto flight Automatic flight control system

23 Communications Radios


24 Electrical power AC power, DC power

25 Equip/furnishings Cabin compartment, seating

26 Fire protection Engine fire detection and extinguishing

28 Fuel Fuel system

29 Hydraulic power Primary and Aux system

30 Ice & Rain protection Anti-ice, pitot tube heater

31 Intruments Panels / independent instruments

32 Landing gear Main and tail landing gear


33 Lights Interior & exterior lights

34 Navigation Air data instrumentation

51 Structures – general Sealing, bonding, torque

52 Doors Emergency, cargo exits

53 Fuselage Primary & auxiliary structure

54 Pylon Pylon

55 Stabilizer Horizontal stabilizer

56 Windows Cockpit/cabin

60 Standard practices Rotor

Torques


65 Rotors Rotor and Drives

70 Standard practices Engines

Torques

71 Power plant Engine

73 Engine and Fuel control

Controlling

75 Air Air intake

76 Engine controls Power control

77 Engine indicating Power, temp

78 Exhaust Tail pipe

79 Oil Oil tank

80 Starting Cranking, ignition

Maintenance ManualsOther publications include: Structural repair manual Illustrated parts catalog Wiring diagrams Flight manual Overhaul manual Equalized inspection program Major inspection program

Maintenance Program Based on Sikorsky

Equalized inspection program

Approved by Transport Canada

Maintenance Program

Maintenance Program

Transmissions and Drives

Main Gearbox All MGB cases made of magnesium except for ring gear case (which is steel)

Encases steel gears Mounts and drives main

rotor head Changes angle of engine

drive and reduces rpm from engines to rotor shaft

Drives main gearbox accessories

Main rotor shaft inclined 4° forward

203 RPM of main rotor shaft = 100% NR


Main Gearbox Mounts the following accessories: #1 and #2 AC generators, primary and auxiliary hydraulic pumps, DC motor generator, MGB lube and torquemeter pumps, rotor tachometer.

Drives the tail rotor driveshaft

Mounts the rotor brake assembly

Mounts the primary servos Support the aft end of the

engines

Transmissions and DrivesLubrication

2 oil filtersMGB filterTorquemeter filter


Lubrication System Internal wet sump Uses pressure, spray and splash to

lubricate various gears, drives and bearing

1 lube pump & filter 1 torquemeter pump & filter 1 blower fan 1 oil cooler


Regular servicing consists of : Checking oil level and adding oil as

necessary Oil changed at gearbox overhaul Inspecting the chip detector and regular

removal and cleaning of oil filter Only able to adjust oil pressure


An oil cooler and blower assy is provided for MGB cooling

Blower is driven by #2 drive shaft through belt system

Forces air through oil cooler


MGB

IGB

TGB

Main rotor shaft has 4° fwd tilt

Transmission and DrivesTail Driveshaft

Transmits torque from G/B to Rudder head

Drives oil cooler blower fan Rotates at 3030 RPM @ 100% Nr

Consists of 5 sections between MGB and TGB

Located from aft rotor fairing along top of cabin and tail cone, to pylon

Transmissions and DrivesIntermediate Gearbox

Mounted on forward end of pylon

Changes angle of drive 44°

Gear ratio 1 to 1 Oil level sight gage

on L/H side + chip detector

Splash lubricated & air cooled

Transmissions and DrivesTail Gearbox

Mounted top of pylon Changes angle of drive

from IGB and transmits torque to Rotary rudder

Gear reduction ratio of 2.4375:1 from tail driveshaft

Rotates at 1243 RPM @ 100% Nr

Incorporates oil level sight gage and chip detector

Splash lubricated and air cooled

IGB and TGB installation

Rotor System

StationaryScissors

Bifilar

Pitch Horn

Sleeve

Stationary Swashplate

Rotating Swashplate Rotating Scissors

Flap Restraint and Droop Restrainer

Damper Fluid Tank

Swashplate Sliding Sleeve

Oil Reservoir

Vertical Hinge

Horizontal HingeDamper

MIL-H-5606 (Aeroshell Fluid 41)

Hub

Lower Plate

Damper

Lower Pressure Plate

Droop Stop

Swashplate Uniball

Flap Restraint

Spindle

Horizontal Hinge (Spindle) Pin

Bifilar Mount Bolts(Inspect mount area for cracks)

Lower BracketSpacerDowel Plate

Damper Attachment To Spindle Pin(Nut/Thrust Washer/Lock)

Rotating Scissors Bracket must be removed when changing Blue Damper

Pitch Control Rod

Pitot-Static Lines (PitotMast not installed)

Carson Composite M/R Blade

Composite Main Rotor Blade

New high lift composite rotor blade @ same torque setting helicopter will lift 1500 lbs more

ROTARY RUDDER

RIBBED POCKET BLADESDIAMETER 10 ft. 7.25 in.

BLADE AREA (each) 2.46 sq ft

BLADE AREA (disk) 12.3 sq ft

ROTATION Clockwise

SPEED 1243 rpm

OVERSPEED 263 rpm = 130% NR

Tail Rotor Gearbox Oil Level Sight glassesAre different between N and L, 1.42 LitersAeroshell 750

Oil Filler

Tail Rotor Pitch Change Shaft

Grease T/R hub daily with Aeroshell 14

Flap Stop pin fits into flap stop in T/R Spindle (+10 deg)

T/R Buzz Stop restricts leftpedal to 23 deg 12’ (primary stop)

T/R Pitch Beam: keyed to pitch change shaft, loosen torque on nut but do not remove all the way before using puller orpitch beam could fall to floor (it comes off with a bang)

T/R Flapping Hinge: two Needle Bearings, one Inner RaceGrease Daily (should grease at 12 o'clock position)

Inspect white paintedArea daily for cracks IAW SB61B10-18

FLIGHT CONTROLS Provides a means of controlling main

and tail rotor blades Controls boosted by two hydraulic

systems Primary and Auxiliary servocylinders

provide hydraulic boost 3 major systems: cyclic, collective and

directional

Auxiliary servocylinder

Primary servocylinders

Mixing Unit

FLIGHT CONTROLS Controls tubes used on cyclic and

collective system Combination of tubes and control cables

used on directional system Mixing unit enables collective to yaw

coupling. Pitch change in tail rotor when collective pitch changes

Yaw channel negative force gradient spring cancels rudder feedback when auxiliary hydraulics off

NFG SPRING Mechanical advantage

mechanism in yaw channel

Cancels control feedback when AUX hydraulics off

Mechanical spring preloaded to 690 lbs pressure

Before workinBefore working on T/R flight controls you should disconnect the NFGSpring: Center pedals and pin, Loosen Jam Nut and bottom adjusting Nut, this captivates the spring. Set for ¼” clearance on re-installation

Primary Servocylinder Mounted on MGB Attached lower end

to F/C Upper end attached

to stationary swashplate

1500 PSI hydraulic pressure from Primary system

Servo positions are:Left Lateral, Right Lateral

and Fore & Aft

AUXILIARY SERVOCYLINDER

Provides 1500 PSI hydraulic boost

Reduces pressure to 60 PSI for Beeper trim in cyclic channel (roll & pitch)

Mounts servo valves for signal from AFCS

Input rods to Aux Hyd.Servo: Lateral, CollectiveFore and Aft, Yaw leftTo right looking forward

Ensure these bootsDon’t restrict flightcontrols

Output from Aux Servo Going to mixing unit

Bottom of forwardT/R control quadrant

Pressure reducer for beeper trim. Reduces from 1500 psi to 60 psi

Beeper Trim valve

Beeper trim switch

Trim Release switch

Bottom view of the Mixing Unit

Collective to yaw coupling happens in mixing unit, this is a corresponding pitch change in the rudder when collective pitch changes

Top view of the Mixing Unit

Forward Quadrant

Aft Quadrant

Aft Quadrant

Fore and Aft Servo Input

Left Lateral Primary Servo Input

Right Lateral Primary Servo Input

HYDRAULIC POWER Consists of Primary and Auxiliary

hydraulic systems and their indicating systems

Provides power for flight controls Separate hydraulic systems, but they

are electrically interconnected If one system fails, the other one cannot

be shut off

PRIMARY HYDRAULICS SYSTEM

INCLUDES

PRIMARY HYDRAULIC PUMP

FLUID TANK MANIFOLD CHECK VALVES

AND ASSOCIATED PLUMBING

Provides hyd pressure to primary servos

Prevents rotor head vibrations from affecting cyclic and collective controls

System electrical power supply is 28 VDC

PRIMARY PUMP Mounted on MGB

rear cover, right side Variable delivery

piston pump Self priming and

purging Provides regulated

output of 1500 psi pressure

FLUID TANK Mounted on left side

of rear transmission fairing

Vented to atmosphere

Supplies fluid to primary pump

Pressure relief valve opens at 6-8 psid in case filter clogged

PRIMARY MANIFOLD Mounted on right

side of main gearbox

Filters hydraulic fluid Relieves excessive

system pressure Directs fluid to the

primary servos

PRIMARY MANIFOLD Indicator pin on manifold pops out when

filter is clogged 100 ± 20 PSID Pressure relief valve set to 1730 PSI 3 way solenoid valve provided to shut off

hydraulic pressure to primary servos

AUXILIARY HYDRAULICS SYSTEM

INCLUDES

AUXILIARY HYDRAULIC PUMP

FLUID TANK MANIFOLD CHECK VALVES

AND ASSOCIATED PLUMBING

Provides hyd pressure to Auxiliary servocylider

Prevents rotor head vibrations from affecting cyclic and collective control sticks

System electrical power supply is 28 VDC

AUXILIARY PUMP Mounted on MGB

rear cover, right side directly below the primary pump

Variable delivery piston pump

Self priming and purging

Provides regulated output of 1500 psi pressure

FLUID TANK Mounted on right

side of rear xmsn fairing

Vented to atmosphere

Supplies fluid to aux pump

Pressure relief valve opens at 6-8 psid in case filter clogged

AUXILIARY MANIFOLD Mounted on right side

inside rear xmsn fairing

Filters hydraulic fluid Relieves excessive

system pressure Directs fluid to the

auxiliary servocylinder

HYDRAULIC POWER

HYDRAULIC PRESSURE INDICATING

Both primary and aux have a pressure transmitter

Separate indicators mounted on instrument panel

Pressure switches mounted on manifold with warning light on caution panel

AUTOMATIC FLIGHT CONTROL SYSTEM

Assists the pilot in maintaining a selected helicopter attitude in the pitch, roll and yaw axis

Manual correction by the pilot is reduced because the AFCS senses slight changes in flight attitude and corrects for it

AFCS COMPONENTS AFCS amplifier Auxiliary servo and

servo valves Position sensors Channel monitor

panel Pedal micro-switches

Attitude indicators AFCS control panel Co-pilot’s vertical

gyro Single channel lag

amplifier

LANDING GEAR Equipped with fixed

non-retractable gear Consists of air-oil

shock strut Dual wheels and

brakes energy absorption

strut Upper and lower

support tubes

Collapsible Strut

Shock Strut

Main Landing Gear L/H

“V” Struts

Brake Line

SHOCK STRUT Integral part of main

landing gear Hydro-pneumatic

cylinder Floating piston

separates air and oil Hydraulic fluid on

top and nitrogen on bottom

ENERGY ABSORPTION STRUT

Also integral to MLG Secured to MLG

strut and fuselage Upper and lower

strut overlap and secured with shear bolts

Honeycomb core in upper tube

Honeycomb collapsible cores inside struts

TAIL LANDING GEAR Secured to aft end of

fuselage Full swiveling tail gear Comprised of housing,

support , shock strut, yoke, wheel and pneumatic centering cylinder

Tail wheel lock mechanism

Tailwheel lock pin

Tailwheel centeringCylinder, inflate withN2 to 400 – 450 psi

Inflate with N2 for approx 4” extension

Sta 493

TAIL WHEEL LOCK SYSTEM

Allows for the tail wheel to be locked in trailing position for landing

Can be unlock during ground operation for towing and taxiing

WHEELS & BRAKES Dual main wheels on each main gear Single tail wheel Disk type hydraulic brake for each main

wheel Wheels are split rim with tubeless tires Each brake consists of housing, piston ,

brake linings & a steel disk

BRAKE SYSTEM Hydraulic system

operated by the pilot or co-pilot foot pedals

Mounted on pilot and co-pilot directional pedals

BRAKE SYSTEM SYSTEM

COMPRISED OF: Master brake

cylinders Brake assy for each

wheel Mixer valve in each

brake line prevents pressure from one cylinder going into the other

Park brake valve

After bleeding the brakes, the level adjusting screw on each master cylinder must be removed to allow fluid to drain out until it stops

Brake caliper bleed screws

Check valves withConnection for handpump

Brake discs are held inPlace with spring clipsthat break, inspect

Brake Bleed fittings

Mixing Valves

Parking Brake Valve

Mixer valve in each brake line between the pilot and co-pilot. The mixer valve directs pressure from either pilots master brake cylinder. Prevents pressure from going to master cylinder not in use

Brake Master Cylinders

ELECTRICAL TWO ELECTRICAL SUPPLY

SYSTEMS 115/200 volt, 3 Phase, 400 cycles AC 28 Volt DC

ELECTRICAL AC power is provided by : 2 x AC

generators and 1 x inverter

DC power is provided by: 1 x DC motor/generator, 1 x transformer-rectifier and 1 or 2 24-volt batteries

A.C. Circuit Breaker Panel

D.C Prime Switch

D.C. Generator

#1 A.C. Generator

#2 A.C. Generator

Primary HydraulicPump

MGBAccessoryGear case

Vertical Gyros C-14 Compass Ground Inverter

Transformer Rectifier Unit

C.V.R.

#1 Supervisory Panel

#2 Supervisory PanelRad Alt Box

#1 and #2 VHF RadiosD.C. VoltageRegulator

Ground InverterC-14 Gyro Compass

#1 Supervisory Panel

AFCS Electrical Box

Engine Anti-Ice Temp Controllers

Transformer Rectifier Unit (TRU)

Inverter (output) circuit breakers

D.C. External Power Relay

Motorized RelayD.C. Gen RCCRA.C. External Power Contactor

#2 Gen Line Contactor

#2 Relay Junction Box

TRU Automatic Cutout Relay

A.C. External Power Line Contactor

Power Transformer

#1 Gen Line Contactor

A.C. Non-Essential Bus Contactor

#1 Relay Junction Box

Solid State D.C. Gen Voltage Regulator

Carbon Pile D.C.Voltage Regulator

AFCS Electrical Box

Electrical Relay Compartment

Ice and Rain Protection Includes engine air intake anti-icing

system Pitot tube heating system Windshield defroster and anti icing

system Windshield washer and wiper system

Engine intake anti-icing

Wipers are electrically activated and operated.

Speed controlled by a switch mounted on the overhead console

Heating & Air Conditioning

Provides heating or ventilation for cockpit and cabin

Functional sections are: Distribution, Heating, Cooling and Temperature Control

Helicopter normally has one heater in forward cabin, but can also have one in rear cabin on long bodies

Optional electric heater available




Heater Fuel Control


Heater Assembly

Ignition Unit

Heater is 200,000 BTU Janitrol gas operated. Fuel fed from Forward tank


System can be operated in automatic or manual mode

Heater blower can be used to ventilate cabin without the heater

Distribution system consists of a plenum chamber which distributes heated or ventilated air to the ducts in cabin and cockpit

Plenum chamber Constructed of Steel Clamped to

discharge end Distribution center

for directing air

FIRE DETECTION AND PROTECTION

Fire Detection Fire Protection

Fire detection wire

Temperature chart is provided to ensure sufficient extinguisher pressure

FUEL SYSTEMFwd tank supplies fuel to #1 engine and heating system

Aft tank supplies fuel to #2 engine

Total of 4 fuel boost pumps

2 in fwd tank2 in aft tank

Ejectors from center tank transfer fuel to the fwd and aft tanks

Boost Pumps in Collector Can

Pressure Refueling LevelSelector Switches

#1 (Forward) Airframe Fuel Filter

Manual Shut Off Valve

Shut off valve must be closed before cleaning fuel filter

#2 (Aft) Airframe Fuel Filter

Cross feed Valve

#2 Manual Shut Off Valve

Cross feed Valve

Forward Boost Pump Pressure Switches

Forward Transfer Valve

Aft Fuel Bay

Aft Boost Pump Pressure Switches

Aft Transfer Valve

Forward Ejector Pump

Aft Boost Pump Pressure Switches

Aft Collector Can

Aft Dual High Level Shut Off Valves

High Level Shut-Off Valve

Aft Transfer Valve

Forward PressureLevel Refueling Switches

When pressure refueling, maximum allowed pressure is 50 psi (ATA Chap 12)

ENGINES AND RELATED SYSTEMS

5 Main sections1.Compressor2.Combustion3.Gas generator4.Power turbine5.Accessories

5 support bearings to engine components

Centrifugal Fuel Purifier

Make sure you get the old “O” ringOut of the housing and replaceWith a new one on installation

CFP is a serialized and balanced unit, align the match marks on re-assembly

On assembly, re-install the screws in the same location they came out of

Fuel Control Unit Filter

Pull the filter out with a right angle pick,Don’t gronch it with pliers!

FCU density controller

FCU Filter: Change all “O” rings when cleaning, don’t forget to transferThe clip to the new filter if it doesn't have one installed

Static Filter removal tool

Static (lastChance) filter

Nf flexible driveshaftLube with 2 - 3 pumpsOf Mobil 28 every phase II

Stator Vane Actuator (SVA)

Feedback cable

Fuel Control Unit

Nf Tach Generator

Emergency Throttle

Ng topping adjustment rod

Speed Control Throttle Rack

Engine Oil Tank

Dipstick

Oil Filter Housing

Always look inside to make sure the “O” ringDidn’t fall off, it will plug the #1 oil jet if you Leave it in there

Oil Temp Bulb

Accessory Gearbox Chip Detector (wired)

#2 Bearing Scavenge Sump Magnetic Plug

#3 Bearing Scavenge line Magnetic Plug

Nf Right Angle GearboxMagnetic Chip Detector (#4/5 Bearings)

#1 & #2 Low Oil Pressure Switches

#2 Oil Pressure Transmitter#1 Oil Pressure Transmitter

#2 Fuel Pressure Transmitter#1 Fuel Pressure Transmitter

#1 Fuel Pressure (Suction) Switch

Engine Mount – Dimension between mount and yoke Must be > 0.310”

No limits on de-laminationAs long as dim > .310”

“T” Bolts: Balanced with High Speed Shaft and are numbered forProper location, arrow must point out and corner of T Must not touch input coupling. Keep nut with bolt removed,

Engine Mount BushingIsolator

“Don’t You Dare” disconnect HighSpeed Shaft without plugging the hole

Start Master Relay

#1 and #2 Starter Relays

Documents

Curso de Sikorsky