Sunday, September 2, 2012

Aircraft Screws








   Machine screws

Materials available include Steel, Stainless steel and Brass.

Countersunk machine screw (Measure: total length).
A Countersunk machine screws is designed to fit flush with the surface of the fastened material for a smooth safe finish.  

Raised Countersunk machine screw.
A raised head on a countersunk machine screw giving a slightly rounded top for a more finished look.

Pan head machine screw (Measure: from under head). A domed head machine screw sits on the surface of the material to be fastened, has a flat underside and can be used with washers.

Cheese Head machine Screw (Measure: from under head). Head style: Slotted. A Cheese head machine screw sits on the surface of the material to be fastened and have a flat underside, can be used with washers.
 
Round Head machine screw (Measure: from under head). Head style: Slotted. A Round head machine screw sits on the surface of the material to be fastened and have a flat underside, can be used with washers.
Shapes of screw head






(a)pan      (b)button     (c)round    (d)truss    (e)flat        (f)oval

Pan head: a low disc with chamfered outer edge.
 
Button or dome head: cylindrical with a rounded top.
 
Round: dome-shaped, commonly used for machine screws.
 
Truss: lower-profile dome designed to prevent tampering.
 
Flat or Countersunk: conical, with flat outer face and tapering inner face allowing
it to sink into the material, very common for wood screws.
 
Oval: countersunk with a rounded top.
 
Cheese head: disc with cylindrical outer edge, height approximately half the
head diameter.
 
Fillister head: cylindrical, but with a slightly convex top surface.
 
Socket head: cylindrical, relatively high, with different types of sockets (hex,
square Torx, etc.)
 
Mirror screw head: countersunk head with a tapped hole to receive a separate
screw-in chrome-plated cover, used for attaching mirrors.
 
N.B: Headless machine screws, called "setscrews" or "grub screws", are also used. They
either have a socket or a slot.

Sunday, June 24, 2012

Thrust Reverser Systems


BASIC PRINCIPLE

To ensure a good braking effect for the aircraft also on contaminated runways (with water or slush) and for the reduction of brake wear, transport aircraft are equipped with thrust reversers. A thrust reverser allows the generation of a rearward-directed thrust force when deployed. To achieve this it redirects the exhaust gas flow at an angle of approximately 120 degrees. Figure 1 shows the direction of the airflow during reverse thrust operation. On turbofan engines with high bypass ratios, only the secondary gas flow is redirected by the thrust reverser because this gas flow generates the larger portion of the engine thrust. This results in a reverse thrust force high enough for braking purposes. To redirect the secondary gas flow only makes mechanical deflector components in the hot gas flow unnecessary. This results in a simpler reverser kinematics with less weight and costs.

          Fig . 1     Direction of the secondary airflow for the generation of the reverse thrust  force


Because the effect of the reverse thrust is independent from the tire friction, the thrust reverser ensures a good deceleration of the aircraft on a contaminated runway with reduced tire friction. During normal runway conditions the use of the thrust reverser requires less use of the wheel brakes for the same aircraft deceleration. The results are less wear of the wheel brakes and a longer operating life of the brake disks.
To have these advantages the higher weight of the engine nacelle must be accepted. To minimize the weight penalty caused by a thrust reverser the designers use a high percentage of composite material for the reverser
and nacelle structure. Usually all engines of an aircraft are equipped with a thrust reverser. But this is not a general rule in any case. An exception is the A380. For weight reduction purposes this aircraft has only two thrust reversers. They are installed on the two inboard engines.


REVERSER OPERATION 


A thrust reverser system is designed for the use on ground only. The system is equipped with safety features preventing the deploying of the reverser during flight. During landing the thrust reverser is deployed shortly after touchdown by selection of the pilot. The best braking effect is achieved at the higher speeds during the landing run because the propulsive efficiency for the reverse thrust has its highest values at the high forward
speeds. With the decreasing aircraft speed it also decreases. During typical flight operation the thrust reverser is used down to a speed of 80 knots. The pilot selects as much thrust as needed. This procedure
ensures an operation with the highest propulsive efficiency and prevents the ingestion of dirt at slow taxi speeds. It is the most efficient way of thrust reverser use in terms of fuel consumption and brake wear.


TYPES OF THRUST REVERSERS


Thrust reversers can be differentiated by the types of their subsystems. These subsystems are the


• Airflow deflection system
• Actuation system
• Control system



The airflow deflection system comprises the structural components necessary for the deflection of the airflow during the operation in the reverse thrust position. For the change between the forward thrust operation and
the reverse thrust operation some components of the airflow deflection system are movable. To achieve its movement an actuation system is installed. This is controlled by the pilots via the thrust lever and the reverser
control system. It is designed to move the reverser components into one of the two end positions. These are the forward thrust (stowed) position or the reverse thrust (deployed) position.

Continued..........






Abbreviations of Aviation



AC...................Alternating Current
ACC................Active Clearance Control
ACOC.............Air-Cooled Oil Cooler
ADC................Air Data Computer
AFDX..............Avionics Full Duplex Switched Ethernet
AIMS...............Aircraft Information Management System
ALF.................Aft Looking Forward
ARINC............Aeronautical Radio Inc.
ASC.................Aircraft System Computer
ASTM..............American Society for Testing and Materials
ATA.................Air Transport Association of America
A/THR.............Auto thrust
AVM................Airborne Vibration Monitoring
CBP................Customer Bleed Pressure
CCS................Common Core System
CDP................Compressor Discharge Pressure
CIT..................Compressor Inlet Temperature
CONT.............Continuous
COTS..............Commercial Off The Shelf
CS...................Certification Standard
DAC................Dual Annular Combustor
DC...................Direct Current
DEU.................Display Electronic Unit
DMC................Display Management Computer
EASA...............European Aviation Safety Agency
ECAM..............Electronic Centralized Aircraft Monitor
ECM.................Engine Condition Monitoring
ECU..................Electronic Control Unit
EEC..................Electronic Engine Control
EFIS.................Elecronic Flight Instrument System
EHSV...............Electrohydraulic Servo Valve
EIA...................Electronic Industries Alliance
EICAS..............Electronic Indication and Crew Alerting System
EIU...................Engine Interface Unit
EIVMU.............Engine Interface and Vibration Monitoring Unit
EPR..................Engine Pressure Ratio
EUROCAE.......European Organisation for Civil Aviation Equipment
E/WD................Engine/Warning Display
FADEC.............Full Authority Digital Engine Control
FCU..................Fuel Control Unit
FDRV...............Fuel Diverter and Return Valve
FF.....................Fuel Flow
FIFO.................First In First Out
FLA..................Forward Looking Aft
FMC.................Flight Management Computer
FMU.................Fuel Metering Unit
FMV.................Fuel Metering Valves
FOB..................Fuel On Board
FRT...................Flat Rate Temperature
ft........................Feet
FWC.................Flight Warning Computer
FWD.................Forward
GRD..................Ground
HMU.................Hydromechanical Unit
HPC..................High Pressure Compressor
HPT...................High Pressure Turbine
IDG...................Integrated Drive Generator
IEEE..................Institute of Electrical and Electronics Engineers
IGN...................Ignition
IMA...................Integrated Modular Avionics
IPC....................Intermediate Pressure Compressor
IPT.....................Intermediate Pressure Turbine
ISA.....................International Standard Atmosphere
LLP....................Life Limited Part
LPC...................Low Pressure Compressor
LPT....................Low Pressure Turbine
LRM...................Line Replaceable Modules
LRU...................Line Replaceable Unit
LVDT................Linear Variable Differential Transformer
MCDU..............Multipurpose Control and Display Unit
MEC..................Main Engine Control
MEMS...............Micro electro mechanical Systems
Mn.....................Mach Number
N1, N2, N3.......Engine Rotor Speeds
OAT..................Outside Air Temperature
ODM.................Oil Debris Monitor
PMC..................Power Management Control
PPBU................Power Plant Build-Up
QEC..................Qick Engine Change
REV...................Reverse
RTD...................Resistive Thermal Device
RTDCA.............Radio Technical Commission for Aeronautics
RTOS................Real Time Operating Systems
RVDT................Rotary Variable Differential Transformer
SAL...................System Address Label
SDAC................System Data Aquisition Computer
SOAP................Spectrographic Oil Analysis Program
TAPS.................Twin Annular Premixing Swirler
TAT...................Total Air Temperature
TBV...................Transient Bleed Valve
TIA....................Telecommunication Industry Association
TLA...................Thrust Lever Angle
TOGA................Take-Off/Go Around
TRA...................Thrust Lever Resolver Angle
TSFC.................Thrust Specific Fuel Consumption
UART.................Universal Asynchronous Receiver-Transmitter
VBV...................Variable Bleed Valve
VSV...................Variable Stator Vane

Sunday, February 12, 2012

Magnetic Chip Detector & SOAP System

The magnetic chip detectors for debris monitoring are installed in the
scavenge pump inlets or in the scavenge oil lines upstream of the pumps
where easy access is ensured.
The filter system is a very important element for the reliability of a recirculatory
lubrication system. Because the oil has to pass through small
holes and passages, even very small particles contaminating the oil could
block the oil flow resulting in a lubrication failure. The normal contaminant
is abrasive material and is released by the bearings and gears during
their normal operation. It is flushed away from the bearings and gears by
the oil and carried with the scavenge oilflow away from the sump. In the
filters of the system the contaminants are removed nearly completely from
the oil. Thus the oil can be supplied again to the bearings and gears. If a
bearing or gear failure develops, larger than normal particles will be found
in the filters and on the magnetic chip detectors.


Fresh oil filled into the lubrication system will gradually dissolve contaminants
and holds microscopic particles in suspension. Bearings, seals and
gears wear, erode and corrode introducing traces of these components into
the oil flow. Thus the condition of the oil, which has been circulated in the
lubrication system for some time, very exactly reflects the condition of the
system. If the system operates normally, the oil contains the amount of
particles, which is typical of the system. The size of the particles is typical
of abrasive contamination. During the development of a bearing or gear
damage the size and the amount of the particles become larger. With the
detection of these particles in the oil a bearing or gear damage can be
recognized in its early stage. These particles are also collected by the oil
filter, but the filter inspection intervals are too long to detect a damage
earTlyo. facilitate the check of the oil system for particles in shorter intervals,
magnetic chip detectors are installed in the scavenge oil flow of each sump
or as a master chip detector in the common scavenge line downstream of
the scavenge pumps. Because the gears and bearings are made of steel, the
magnets of the chip detectors are able to collect the particles (or chips) of
these parts. These chip detectors collect particles from 0.02 to 1 mm in
size. The whole arrangement of magnetic chip detectors is often called debris
monitoring system. In its simplest design the magnetic chip detector is
a tiny bar magnet which protrudes into the scavenge oil flow. Figure 3.9
shows such a chip detector. The check of the chip detectors for collected
particles in fixed time intervals is part of the maintenance checks. To facilitate
the check of these detectors they can be removed from their housing
without a tool. If particles are found on the chip detector, they can be
analyzed in a laboratory to exactly determine the component releasing
these particles into the oil.



The more sophisticated variant of the magnetic chip detector is the electrically
monitored chip detector as shown in Above Figure. Such a chip detector
comprises a set of two magnets. The FADEC ( Full Authority Digital Engine Control ) computer
monitors the resistance between these two magnets. A check and removal of the electrical
monitored chip detector is not necessary until the FADEC computer
sends the corresponding maintenance message.


For the particle monitoring of modern engines Oil Debris Monitors
(ODM) are used. These sensors are based on an inductive measurement
technique which enables the system to detect, count and classify wear
metal particles by size and type (ferromagnetic or non-ferromagnetic).
This allows the system to determine the trend for the amount of particles in
the oil. The ODMs are connected to the FADEC computer or another
computer assigned to this function.

Another tool for the monitoring of the oil-wetted parts is the Spectrographic
Oil Analysis Program (SOAP). Through this analysis the concentration
of particles of the size from 0.001 to 0.02 mm and its specific elements
can be identified. The metal type and concentration may indicate to
the analyst and engineers which part of an engine is failing if a direct assignment
to an engine part is possible. SOAP is used if this program is part
of the engine maintenance schedule. It may be used temporarily if uncertainties
exist about the reliability of engine bearings or gears. Some turbine engine manufacturers mandate SOAP in certain turbine engine maintenance
schedules.

For the monitoring of particle concentration in the oil a periodic analysis
of oil samples, taken from the engine, is made in a laboratory. When the
amount of particles for an element or an element combination increases,
this indicates an increase in wear. If the trend continues, the development
of a damage is imminent. In this phase the particle size also increases and
the presence of the particles can be verified by the magnetic chip detectors.
The verification with the help of a chip detector is important if an assignment
of the analyzed elements to an engine part is not possible.

If SOAP is used, the airline engineering has more time for the observation
of a failure development. This allows a longer planning period for the
engine removal necessary in such case.


Thursday, September 15, 2011

Gyroscope

A rotating mass, or rotor, mounted in such a way, that the spin axis of the rotoris free to rotate about one or more axis at right angles to the spin axis or put another way……….
any rotating mass is said to have gyroscopic properties


Tuesday, September 13, 2011

AIRCRAFT TYRE DEFECTS

NORMAL TREAD WEAR


Possible Causes
Even tread wear  indicates that tire pressure has been maintained at the correct inflation level during service.

Recommendation
Remove the tire from the aircraft if the reinforced fabric (bias) or the aramid cord protector (radial) is exposed, or if the remaining groove depth is less that 1.0mm at any point of the tread surface.


UNEVEN TREAD WEAR (SHOULDER)

Possible Causes
Under inflation will lead to excessive tread shoulder wear.It will also lead to high tire deflection and subsequent heat build up which may result in tire damage.


Recommendation 
If the tire wear limit has been or soon will be reached, remove the tire.

If the wear limit has not been reached, check the pressure and adjust it to the recommended value.If shoulder wear is more pronounced on one side, this type of wear could result from axle flexing. Tire can be kept in service until normal wear removal criteria is reached.


UNEVEN TREAD WEAR (CENTER)

Possible Causes
Over-inflation accelerates center tread wear, reduces tire traction and makes the tread more susceptible to cutting by foreign objects.


Recommendation
If the tire wear limit has been reached or soon will be reached, remove the tire.

If the wear limit has not been reached, check tire pressure and adjust in accordance with maintenance manual standards.


IRREGULAR WEAR / ABRASION

Possible Causes
Refers to abrasive wearing of the tread caused by sudden, strong side forces.




Recommendation
If the reinforced Fabric or Aramid Cord Protector is exposed, remove the tire.


SPOT WEAR

Possible Causes
Skid burns result from brake malfunctions or locking of the wheel, most often during landing.






Recommendation
If the spot wear reaches the reinforced fabric (bias) or aramid cord protector (radial), remove from the aircraft.

*Tires with spot wearing exposing the carcass or radial tire belts more than 10 squire inch area must be scrapped.

If the spot wear does not reach the reinforced fabric (bias) or aramid cord protector (radial), If there is sufficient groove depth in the whole spot wear area.If there is not incipient separation and if vibration is not detected while rolling, leave the tire on the aircraft.


TREAD RUBBER REVERSION

Possible Causes
An oval shaped burn on the tread most often is caused by hydroplaning on wet or frozen runways during landing.




Recommendation
If the rubber reversion reaches the reinforcing fabric (bias) or aramid cord protector (radial), if there is sufficient groove depth in the whole tread rubber reversion area.If there is hot incipient separation and if vibration is not detected while rolling, leave the tire on the aircraft.



THREAD SEPARATION

Possible Causes
Separation of the tread or fabric is caused by overloding.cuts,abnormal heat build up,etc......



Recommendation
A tire with tread or fabric separation must be removed immediately and be checked by the tire manufacture.If tread separation is serious,part of most of tread (Often including the reinforcing fabric in bias tires) may peel off,which in turn may be lead to damage to the aircraft.there for remove the tire immediately.

Early signs of tread separation can manifest themselves in the form of a tread bulge, local uneven wear (depression) or a local tread/ sidewall rubber split.remove the tire immediately.

If the tire is still inflated after aircraft is at parking position, record the pressure after it has cooled down (allow 3 hours).Then deflate the tire before removing the wheel assembly.


CONTINUED.......... 




Saturday, September 10, 2011

Protection and Location of Flight Recorders (black box)



Flight recorders for the retrieval of data for accident investigation purpose must be adequately protected and so located in an aircraft that the recording media will survive in the event of a crash situation .The adverse factors against which protection is necessary are mechanical damage due to impact and acceleration forces,fire damage,and chemical attack by hydraulic,de-icing and fire extinguishing fluids,fuels and acids.Protection must also be afforded against the effect of sea water,and to cater for cases where an accident occurs resulting in wreckage entering deep water,the recording medium container must also be provided with separation and flotation facilities. 



                      The protection facilities are,of course,'built in' to the design of a recorder and so may be considered as the primary means of ensuring survival of the recording media.The location of a recorder in an aircraft is, however, also an important factor to be considered in this respect, and from the evidence of aircraft accidents it is shown that the rear fuselage and tail unit structure is the section most likely to survive, or be the least severely damaged.For this reason therefor,a protected flight data recorder is installed in the rear of an aircraft.

                     In addition to the foregoing protection and location requirements,it is also necessary to provide recorders with means to facilitate their identification in conditions following a crash.This is usually done by adopting a distinctive color scheme;thus, contrary to the 'black box' cliche frequently adopted in news media reports of a crash, the box could well be fluorescent orange.











Friday, September 9, 2011

ATA CHAPTERS


00  Introduction
01  Operations Information
05  Periodic Inspections
      00 General
      10 Time Limits
      20 Scheduled Maintenance Checks
      30 [As Required]
      40 [As Required]
      50 Unscheduled Maintenance Checks
06 Dimensions & Areas
07 Lifting & Shoring
     00 General
     10 Jacking
     20 Shoring
08 Leveling & Weighing
     00 General
     10 Weighing & Balancing
     20 Leveling
09 Towing & Taxiing
    00 General
    10 Towing
    20 Taxiing
10 Parking, Mooring, Storage & Return To Service
    00 General
    10 Parking / Storage
    20 Mooring
    30 Return To Service
11 Placards & Markings
    00 General
    10 Exterior Colour Schemes & Markings
    20 Exterior Placards & Markings
    30 Interior Placards
12 Servicing Routine Maintenance
    00 General
    10 Replenishing
    20 Scheduled Servicing
    30 Unscheduled Servicing
20 Standard Practices - Airframe
21 Air Conditioning
    00 General
    10 Compression
    20 Distribution
    30 Pressurization Control
    40 Heating
    50 Cooling
    60 Temperature Control
    70 Moisture / Air Contaminant Control
    97 Wiring Discrepancies
22 Auto Flight
    00 General
    10 Autopilot
    20 Speed - Attitude Correction
    30 Auto Throttle
    40 System Monitor
    50 Aerodynamic Load Alleviating
    97 Wiring Discrepancies
23 Communications
    00 General
    10 Speech Communications
    15 SATCOM
    20 Data Transmission & Automatic Calling
    30 Passenger Address, Entertainment, & Comfort
    40 Interphone
    50 Audio Integrating
    60 Static Discharging
    70 Audio & Video Monitoring
    80 Integrated Automatic Tuning
    97 Wiring Discrepancies
24 Electrical Power
    00 General
    10 Generator Drive
    20 AC Generation
    30 DC Generation
    40 External Power
    50 AC Electrical Load Distribution
    60 DC Electrical Load Distribution
    70 Primary & Secondary Power
    97 Wiring Discrepancies
25 Equipment / Furnishings
    00 General
    10 Flight Compartment
    20 Passenger Compartment
    30 Buffet / Galley
    40 Lavatories
    50 Cargo Compartments
    60 Emergency
    70 Accessory Compartments
    80 Insulation
    97 Wiring Discrepancies
26 Fire Protection
    00 General
    10 Detection
    20 Extinguishing
    30 Explosion Suppression
    97 Wiring Discrepancies
27 Flight Controls
    00 General
    10 Aileron & Tab
    20 Rudder & Tab
    30 Elevator & Tab
    40 Horizontal Stabilizer / Stabilizer
    50 Flaps
    60 Spoiler, Drag Devices & Variable Aerodynamic Fairings
    70 Gust Lock & Damper
    80 Lift Augmenting
    97 Wiring Discrepancies
28 Fuel
    00 General
    10 Storage
    20 Distribution - Drain Valves
    30 Dump
    40 Indicating
29 Hydraulic Power
    00 General
    10 Main
    20 Auxiliary
    30 Indicating
    97 Wiring Discrepancies
30 Ice & Rain Protection
    00 General
    10 Airfoil
    20 Air Intakes
    30 Pitot & Static
    40 Windows, Windshields, & Doors
    50 Antennas & Radomes
    60 Propellers / Rotors
    70 Water Lines
    80 Detection
    97 Wiring Discrepancies
31 Indicating / Recording Systems
    00 General
    10 Instrument & Control Panels
    20 Independent Instruments
    30 Recorders
    40 Central Computers
    50 Central Warning Systems
    60 Central Display Systems
    70 Automatic Data Reporting Systems
    97 Wiring Discrepancies
32 Landing Gear
    00 General
    10 Main Gear & Doors
    20 Nose Gear / Tail Gear & Doors
    30 Extension & Retraction
    40 Wheels & Brakes
    50 Steering
    60 Position and Warning
    70 Supplementary Gear
    97 Wiring Discrepancies
33 Lights
    00 General
    10 Flight Compartment
    20 Passenger Compartment
    30 Cargo & Service Compartments
    40 Exterior Lighting
    50 Emergency Lighting
    97 Wiring Discrepancies
34 Navigation
    00 General
    10 Flight Environment Data
    20 Attitude & Direction
    30 Landing & Taxiing Aids
    40 Independent Position Determining
    50 Dependent Position Determining
    60 Flight Management Computing
    97 Wiring Discrepancies
35 Oxygen
    00 General
    10 Crew
    20 Passenger
    30 Portable
    97 Wiring Discrepancies
36 Pneumatic
    00 General
    10 Distribution
    20 Indicating
    97 Wiring Discrepancies
37 Vacuum
    00 General
    10 Distribution
    20 Indicating
    97 Wiring Discrepancies
38 Water / Waste
    00 General
    10 Potable
    20 Wash
    30 Waste Disposal
    40 Air Supply
    30 Network Components
45 Central Maintenance System (CMS)
    00 General
    05 CMS / Aircraft General
    19 CMS / Aircraft General
    20 CMS / Airframe Systems
    44 CMS / Airframe Systems
    45 Central Maintenance System
    50 CMS / Structures
    59 CMS / Structures
    60 CMS / Propellers
    69 CMS / Propellers
    70 CMS / Power Plant
    89 CMS / Power Plant
    97 Wiring Discrepancies
46 Information Systems
    00 General
    10 Airplane General Information Systems
    20 Flight Deck Information Systems
    30 Maintenance Information Systems
    40 Passenger Cabin Information Systems
    50 Miscellaneous Information Systems
49 Airborne Auxiliary Power
    00 General
    10 Power Plant
    20 Engine
    30 Engine Fuel & Control
    40 Ignition / Starting
    50 Air
    60 Engine Controls
    70 Indicating
    80 Exhaust
    90 Oil
51 Standard Practices & Structures General
    00 General
    10 Investigation, Cleanup & Aerodynamic Smoothness
    20 Processes
    30 Materials
    40 Fasteners
    50 Support of Airplane for Repair & Alignment Check Procedures
    60 Control-Surface Balancing
    70 Repairs
    80 Electrical Bonding
52 Doors
    00 General
    10 Passenger / Crew
    20 Emergency Exit
    30 Cargo
    40 Service
    50 Fixed Interior
    60 Entrance Stairs
    70 Monitoring & Operation
    80 Landing Gear
53 Fuselage
    00 General (10 through 90 Fuselage Sections)
    10 Main Frame
    20 Auxiliary Structure
    30 Plates-Skin
    40 Attach Fittings
    50 Aerodynamic Fairings
    60 [As Required]
    70 [As Required]
    80 [As Required]
    90 [As Required]
54 Nacelles / Pylons
    00 General
    10 Nacelle
    20 Nacelle
    30 Nacelle
    40 Nacelle
    50 Pylon
    60 Pylon
    70 Pylon
    80 Pylon
55 Stabilizers
    00 General
    10 Horizontal Stabilizer / Stabilator Or Canard
    20 Elevator
    30 Vertical Stabilizer
    40 Rudder
56 Windows
    00 General
    10 Flight Compartment
    20 Passenger Compartment
    30 Door
    40 Inspection & Observation
57 Wings
    00 General
    10 Center Wing
    20 Outer Wing
    30 Wing Tip
    40 Leading Edge & Leading Edge Devices
    50 Trailing Edge & Trailing Edge Devices
    60 Ailerons & Elevators
    70 Spoilers
    80 [As Required]
    90 Wing Folding System
70 Standard Practices Engine
71 Power Plant General
    00 General
    10 Cowling
     20 Mounts
    30 Fire seals
    40 Attach Fittings
    50 Electrical Harness
    60 Air Intakes
    70 Engine Drains
72 Engine Turbine
    00 General
    10 (Turboprop &/Or Front Mounted Driven Propulsor)
    20 Air Inlet Section
    30 Compressor Section
    40 Combustion Section
    50 Turbine Section
    60 Accessory Drives
    70 By-Pass Section
    80 Propulsion Section (Rear Mounted)
73 Engine Fuel & Control
    00 General
    10 Distribution
    20 Controlling
    30 Indicating
    97 Wiring Discrepancies
74 Ignition
    00 General
    10 Electrical Power Supply
    20 Distribution
    30 Switching
    97 Wiring Discrepancies
75 Air
    00 General
    10 Engine Anti-Icing
    20 Cooling
    30 Compressor Control
    40 Indicating
76 Engine Controls
    00 General
    10 Power Control
    20 Emergency Shutdown
    97 Wiring Discrepancies
77 Engine Indicating
    00 General
    10 Power
    20 Temperature
    30 Analyzers
    40 Integrated Engine Instrument Systems
    97 Wiring Discrepancies
78 Exhaust
    00 General
    10 Collector - Nozzle
    20 Noise Suppressor
    30 Thrust Reverser
    40 Supplemental Air
    97 Wiring Discrepancies
79 Oil
    00 General
    10 Storage
    20 Distribution
    30 Indicating
    97 Wiring Discrepancies
80 Starting
    00 General
    10 Cranking