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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
Airworthiness Directives
Airworthiness Directives
Airworthiness Directives
Total of 47 AWD’s issued for aircraft
Airworthiness Directives
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
Maintenance ManualsGroup/Chapter Title General Contents
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
Maintenance ManualsGroup/Chapter Title General Contents
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
Maintenance ManualsGroup/Chapter Title General Contents
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
Transmissions and Drives
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
Transmissions and Drives
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
Transmissions and Drives
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
Transmissions and Drives
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
Transmissions and Drives
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
Heating & Air Conditioning
Heating & Air Conditioning
Heating & Air Conditioning
Heater Fuel Control
Heating & Air Conditioning
Heater Assembly
Ignition Unit
Heater is 200,000 BTU Janitrol gas operated. Fuel fed from Forward tank
Heating & Air Conditioning
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