SERVICE MANUAL
REPORT NO . 72-02-04
MODEL NO. TFE731-2-1C
◄
AIRosearch
Pho •rnl•
THE ATTACHED SERVI CE MANUAL
REPORT NO. 72-02-04 IS ISS UED FOR USE
IN SUPPORT OF THE FOLLOWING AIRCRAFT
ENGINE PART NO.
ENGINE MODEL NO.
AIRCRAFT APPLICATION
3070000-1 / -2/ -3 /-4/- 5/
-6 / -7 /-8/-9 / -10/ - 11/
-12/-13
TFE731-2-1C
Falco n 10
Garrett Turbi ne Engine Company
A Divisi on of The Garret t Corporation
P. O. Box 29003
Phoenix, AZ 85038
Attn:
Tec hni ca l Data Distri bution, Dept 77-7
Mail Drop 601
(602) 267-4807
CoQiYr iaht 1981 by The Garrett Corporation
'
REPORT NO . 72-02-04
Apr 15/81
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',I 11'1 I' I M/\MIIAI
TURBOFAN AIRCRAFT ENGINE
PART NO.
MODEL NO.
3070000-1-2/-3/-4/
-5/-6/-7/-8/-9/-10/
-11/-12/-13
TFE731-2-1C
REPORT NO. 72-02-04
(FAA APPROVED)
Aor 15 /81
Al Research
Phoenix
SERVICE MANUAL
TFE731-2-1C
LIST OF EFFECTIVE PAGES
72-02-04
CHAPTER/
SECTION
PAGE
CHAPTER/
SECTION
PAGE
DATE
Apr 15/81
Title Page
List of
Effective
Pages
DATE
1
Record of
Revisions
Apr 15/81
Apr 15/81
Record of
Temporary
Revisions
1
2
Apr 15/81
Apr 15/81
Servi ce
Bulletin
List
1
2
Apr 15/81
Apr 15/81
Apr 15/81
Apr 15/81
Apr 15/81
Apr 15/81
Apr 15/81
Apr 15/81
Apr 15/81
Apr 15/81
Apr 15/81
Apr 15/81
3
4
5
6
7
8
9
10
11
12
List of
Chapters
Apr 15/81
Table of
Contents
Apr 15/81
Introduction 1
2
3
4
Apr 15/81
Apr 15/81
Apr 15/81
81 ank
72-02-04-EFF
Page 1
Apr 15/81
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SERVT CE MANUAL
TFE731-2-1C
RECORD OF REVISIONS
REV
NO.
ISSUE
DATE
DATE
INSERTED
BY
REV
NO.
ISSUE
DATE
DATE
INSERTED
BY
72-02-04-REV-REC
Aor 15/81
Al Research
Phoonlx
SERVICE MANUAL
TFE731-2- 1C
SERVICE BULLETIN LIST
Servi ce
Bul1 et in
Incorp.
Titl e
TFE-GSE SB 1,
Rev 1
No Effect
TFE731 SHAFT STRETCHING FIXTURES - Rework
Shaft Stretching Fixtures to Provide Improved Relief Valve Operation and More
Accurate Pres sure Gage
289900 SB
Rev 1
No. 1,
No Effect
TFE TESTER ASSEMBLY - Modify TFE Trouble
Shooting Tester Assembly to be Compatible with
Fue l Control Part No. 3070800-7
291262 SB
No. 1
No Effect
TFE731 REAR BEARING PULLER ASSEMBLY - Rework
Pu l ler Part No. 291262-1 to Part No. 293711-1
to be Compatible with Turbine Bearing Part No.
358750-2
293187 SB
No. 1
No Effect
TFE - COMPUTER TESTER ASSEMBLY - Modify Computer Tester to Provide Overspeed Simulation
Capability
72 - 3001, Rev 8
No Effect
ENGINE - SERVICE LIFE - Service Life Limits of
Critical Life Limited Components
7.~-3007
No Effect
ENGINE - POWER SECTION - Replacement of Collars
and Retainer of Fan Shaft Assembly and Ring
Gear
72-3011, Rev 3
No Effect
ENGINE - TURBOFAN AIRCRAFT - Adapt TFE731-2 Engine to Either Falcon 10 or Learjet Model 35
and 36 Application
72- 3013, Rev 1
No Effect
ENGINE - WIRING HARNESS - Installation of
Shiel ded Engine Wiring Harness
72-3016
No Effect
ENGINE - BY-PASS FAN REDUCTION GEAR SECTION Remove and Replace Pinion Gear Assembly
72- 3019, Rev 1
No Effect
ENGINE - ACCESSORY DRIVES - Inspection of
Transfer Gearbox Bearing Support
72-3020, Rev 3
No Effect
ENGINE - ACCESSORY DRIVE - Remove and Replace
Transfer Gearbox Bearing Support
72-3021, Rev 2
No Effect
ENGINE COMBUSTION SECTION - Replace Combustion
Li ner with Liner of Improved Design
72-3022, Rev 1
No Effect
ENGINE - COMPRESSOR SECTION - Installation of
Compressor with Increased Low Cycle Fatigue
Life
72-02-04-S -B LIST
Page 1
Apr 15/81
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SERVI CE MANUAL
TFE731-2-IC
SERVICE BULLETIN LI ST (CONT)
Ser vice
Bulletin
Inc or p.
Tit le
72-3024
No Effect
ENGINF - TRANSFER SHAFT - Remove and Renlace
I nternal Retaininq Rinq for Transf er Gearbox
72-3025
No Effect
ENGIN E - RY-PASS SECTION - Replace Fan Spin ner
Support Bolts
72-3026, Rev 6
No Effect
ENGINE - TURBINE SECTION - Replace Hi gh Pressure Turbi ne Blades with Blades of Improved
Design
72-3033, Rev 1
No Effect
ENGINE - TURBINE SECTION - Replace Low Pressure
Turbine Bearing
72-3034, Rev 6
No Effect
ENGINE - OIL COOLER IN STALLATION - Replace
Bypass Duct Panel on Engines Incorporating
Thrust Reverser Manufactured by Grumman Aerospace Corporation
72-3035, Rev 3
No Effect
ENGINE - DUCT - Thrust Reverser Installation
(Manufactured by Grumman Aero- space Corpora-
tion)
72-3037 , Rev 3
No Effect
ENGINE - TURBOFAN AIRCRAFT - Define Enoine Confio uration Reouirements to Meet Aircraft-Enai ne
System Functional Objectives
72- 3038 , Rev 2
No Effect
ENGI NE - MOUNT INSTAL LATION - Replace Enqine
Mount Bolts
72-3039 , Rev 2
No Effect
ENGINE - SUPPnRT HOUS ING AND INTERMEDIATE r.ASE
- Replace Bor escope Inspection Pluq
72-3040, Rev 1
No Effect
ENGINE - FAN DUCT - Installati on of Fan Duct
Set (Split Fan Duct)
72- 3041 , Rev 1
No Effect
ENGINE - PANEL INSTALLATION - Replac e Ioniter
Access Door Part No . 3071837-2
72-3042 , Rev 4
No Effect
ENGINE - COMBUSTION fHAMR ER ASSEMBLY - Repl ace
Combus ti on Liner Part No . 3072448-4 with Improved Comhustion Li ner Pnrt No. ~07 2674 -1
72- 3044
No Effect
ENGINE - ENGINE WIRING HARNESS - Add ,lurnpei- Assembly to Improve EMI Capabilities in Electrica l Sys t em
72-02-04-S-B LIST
Paqe 2
Apr 15/8 l
SER\1T CE MANUAL
TFE- 31-2-lC
SERVICE BULLETIN LIST (CONT)
Service
Bulletin
Incorp.
Title
72-3046
No Effect
ENGINE - ENGINE SUPPORT HOUSING ASSEMBLY Rework Enqine Support Housing Assembl_y to Accept Fan Duct Set Part No. 3072420-3
72-3051
No Effect
ENGINE - ENGINE AND COMPUTER WIRING HARNESS Incorporate New Wiring Harness to Achieve Improved Fliaht Descent Scherlule
72-3053, Rev 1
No Effect
ENGINE - LOW PRESSURE TURBINE ROTOR ASSEMBLY Install Improved Third Staqe LP Turbine Blade
Part No. 3072014-2
72-3054, Rev 2
No Effect
ENGINE - PLANET GEAR ASSEMBLY - Install Planet
Bearing Part No. 3072775-1 or -2
72- 3057, Rev 2
No Effect
ENGINE - LOW PRESSURE TURBINE ASSEMBLY - Install Improved Low Pressure Turbine Rotatinq
Seal
72-3058
No Effect
ENGINE - PLANET GEAR ASSEMBLY - Install Planet
Bearing Part No~ 358733-4
72-3060, Rev 3
No Effect
ENGINE - HIGH PRESSURE IMPELLER - Install HP
Impeller Part No. 3072~39-l
72-3063, Rev 1
No Effect
ENGINE - LOW PRESSURE TURBINE ROTOR ASSEMBLY Install Improved Second Stage LP Turbine Blade
Part No. 3072012-2
72-3064, Rev 1
No Effect
ENGINE - BY-PASS FAN REnucTION GEAR SECTION Install Retaininq (Damper) Rinq on Pinion Gear
Assembly
72-3065, Rev 2
No Effect
ENGINE - LOW PRESSURE TURBINE ROTOR ASSEMBLY Install Improved First Staae LP Turbine Blade
72-3067, Rev 1
No Effect
ENGINE - BY-PASS FAN SUPPORT - Install Seal
Carrier Bolts Part No. 145-131-9007
72-3070
No Effect
ENGINE - BY-PASS SECTION - Rework Fan Duct Set
(Matched) to Increase Interchangeability
72-3076, Rev 1
No Effect
ENGINE - FAN SUPPORT SHAFT AND HOUSING ASSEMBLY
- Rework or Replace Fan Drive Shaft Assembly
72-3077, Rev 1
No Effect
ENGINE - PINION GEAR ASSEMBLY - Reolace Bolts
Attachinq Retainer Plate Part No. 3072379-1 to
Pinion Gear Assembly
72-02-04-S-B LIST
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Apr 15/81
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SERVICE MANUAL
TFE731-2-J. r
SERVICE BULLETIN LI ST (CONT)
Servi ce
Bulletin
I ncorp .
Tit le
72-3078
No Effect
ENG INE - POWER SECTION - Install New Bolts with
Lockwire Feature that Attach Transfer Tubes to
I ntermediate Case
72-3080
No Effect
ENGINE - FAN SUPPORT SHAFT AND HOUSING ASSEMBLY
- Repl ace Anti-Ice Seal Part No. 3071397- 2
72-3081
No Effect
ENGINE - LOW PRESSURE TURBINE ASSEMBLY - Install Nameplate on Low Pressur e Turbine Assembly Part No. 3072276- X for Confiquration Control of Low Pressure Turbine Module Assembly
72-3085, Rev 5
No Effect
ENGINE - FAN SP INNER - Rep l ace Fan Spinner and
Related Anti-Ice Components
72- 3092, Rev 1
No Effect
ENGINE - ACCESSORY DRIVE GEARBOX ASSEMBLY - Install Elastromeric Mounts
72-3095
No Effect
ENGINE - TURRINE SECTION - Repl ace No. 4 and 5
Hi gh Pressure Rotor Carbon Face Seal for Improved Sealinq Capability and Increased Seal
Life
72-3098
No Effect
ENGINE - FAN SHAFT ASSEMBLY - Rework Fan Shaft,
Part No. 307lg55-1
72-3103, Rev 1
No Effect
ENG INE - COMBUSTION SECTION - Rework Combustion
Chamber Liner Part No. 3072448-4 to Part No.
3072674-1
72-3105, Rev 1
No Effect
ENGINE- INSPECTION INTERVALS - Establishinq
Maj or Inspection I nterva l s
72-3113
No Effect
ENGINE - SUPPORT HOUSING - Rep l ace Support
Hou si ng
72-3116
No Effect
ENGINE - LOW PRESSURE COMPRESSOR - Install Ai rOil Seal Rotors with Improved Surface Coatinq
72- 3119
No Effect
ENGINE - TURBINE SECTION - Decrease Turbine End
Shaft Stretch Dimension on Low Pressure Tie Rod
72-3126, Rev 5
No Effect
ENGINE - PLANET GEAR INSTALLATION - Replace
Planet Gears haft As sembly
72-3133
No Effect
ENGINE - FAN BY-PASS STATOR INSTALLATION - Inspect and Replace Fan By- Pass Stator Alignment
Pins
72-02-04-S-B LI ST
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Apr 15/81
Ai Research
Phoenix
SERVICE MANUAL
TFE731-2-1C
SERVICE BULLETIN LIST (CONT)
Service
Bu 11 et in
Inc orp.
Tit le
72-3136~ Rev 1
No Effect
ENGINE - ACCESSORY DRIVE GEARBOX - Replace Annular Ball bearinqs, Part No. 358206
72-3137, Rev 2
No Effect
ENGINE - COMPRESSOR INSTALLATION - Incoroorate
HP Rotating Group Thru st Balance Seal Rotor
(Cancelled)
72-3138
No Effect
ENGINE - HIGH PRESSURE ROTOR AND N07ZLE ASSEMBLY - Replace Inner Diameter Bolts and Sequence
Nozzle Seqments
A72-3140
No Effect
ENGINE - COMPRESSOR INSTALLATION - Replace Tie
Rod
73-3001
No Effect
ENGINE FUEL AND CONTROL - FUEL PUMP ASSEMBLY Replace Fuel Pump Assembly
73-3003
No Eff ect
FUEL - CONTROLLING - Improved Fuel Pump Assembly
73-3004
No Eff ect
FUEL - CONTROLLING - Check for Presence of Fuel
Pump Anti - Icing Valve
73-3005
No Eff ect
FUEL - CONTROLLING - Inspection Reidentification or Replacement of Fuel Pump Assembly
73-3008
No Effect
FUEL - CONTROLLING - Replace Fuel Control with
Fuel Control Incorporatinq New Metering Valve
Part No. 893513-4 and New Metering Valve Set
Part No. 3070877-1 and Restrictor Part No.
3070874-1
No Effect
ENGIN E - FUEL - Cap Flow Divider Drain Port
73-3011, Rev 2
No Effect
ENGINE - CONTROLLING - Install Common Fuel Control on all Turbofan En9ines - Install Pressu re
(PCD) Limi ter with Serarate Identit.Y, Dependinq
upon Fuel Control Application
73-3013
No Effect
ENGINE - FUEL 1.0NTROL - Remove the 3070900 Name
Plate from the Fuel Control Assembl.Y
73-3015, Rev 1
No Effect
ENGI NE - FUEL DISTRIBUTION - Reolace Fuel
Nozzl e Gaskets
73-3016, Rev 1
No Effect
ENGI NE - FUEL MANIFOLD INSTALLATION - Replace
Fuel Manifold Assembly
73-3009, Rev
1
72-02-04-S-B LIST
Paqe 5
Apr 15/81
fo-•:m) AIRosoarch
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PhoonlK
SERVI CE MANUAL
TFE731-2-lr.
SERVICE BULLETIN LIST (CONT)
Service
Bu 11 et in
Incorp.
Titl e
73-3017
No Effect
FUEL - CONTROLLING - Insta l l Fuel Control Part
No. 3070800-8
73-3018, Rev 2
No Eff ect
ENGINE - CONTROLLING - Install Fuel Control
Part No. 3070800-7
73-3019
No Effect
ENGINE - FUEL - Distribution of Sperry V~ckers
Service Rulletin PPF4-094-73-0l, Retention of
Filter Guide in PPF4-094 Series Vane Fuel Pump
Assembly
73-3020
No Effect
ENGINE - SERVICE TUBES CLAMP AND TUBES INSTALLATION - Replaces P3 Tube wi th Larger Tube and
Install Larger Clamps
73-3021
No Effect
ENGINE - FUEL f.ONTROL - Add Packin9s to Manual
Mode and Overspeed Solenoids to Prevent Moisture Leak age into Fuel Control
73-3022
No Effect
ENGINE - FUE L CONTROL - Install Improved Meterinq Valve to Prevent Servo Pressure Requlator
Valve Oscillation
73- 3027, Rev 2
No Effect
ENGINE - FUEL AND CONTROL - Replace Fuel Pump
Assembl y with Fuel Pump Assembly Incorporatin9
Fuel Inlet Temperature Boss
73-3028
No Effect
ENGINE - FUEL - Replace Flow Divider and Drain
Valve with New Fl ow Divider without Dr ain Function
74 -3002 , Rev 4
No Effect
ENGINE IGNITION - Rep l ace Iqniter Plug, Igniter
Gasket and Attaching Rolts and Repair Iqniter
Lead
75 - 3002
No Effect
AIR - ENGINE ANTI-ICING - Inspect Threaded Insert for Mountinq Anti-Ice Seal and Suoport and
Replace when Required
75- 3004
No Effect
ENGINE - MANIFOLD AND ANTI-ICE VALVE INSTALLATION - Replace Anti-Ice Manifold Gasket Part
No. 3072093-1 and Seal Housinq Part No.
3072090-1
75-3007, Rev 2
No Effect
ENGINE - ANTI-If.E SYSTEM - Incorporate Improved
Buffered Air System Components, t o Increase
Anti-Ice System Reli ability
72 -02 -04-S-B LIST
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Apr 15/81
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SFRVICE MANUAL
Tr E731-2-1C
SERVICE BULLETIN LIST (CONT)
Service
Bu 11 et in
Incorp.
Title
75-3008, Rev 1
No Effect
ENGINE - ANTI-ICE SYSTEM - Incorporate Improved
Face Bellows Seal Part No. 307?.683- 3 or -4
76-3002
No Effect
ENG INE CONTROLS - POWER CONTROL - Removal of
Latching Function of 0verspeed Protection Circuit on Elec t ron ic Computer
76-3004
No Effect
ENGINE - CONTROL - Remove and Replace Electronic Computer
A76-3005
No Effect
ENGINE - 1.0NTR0L - One Time Inspection of Transistors within El ectronic Computer Part No.
94g572-5, Series 4, 5, and 6
76-3007
No Effect
ENGINE - CONTROL - Remove and Replace Electronic Computer
76-3008
No Effect
ENGINE CONTROLS - POWER CONTROL - Replace Pneumatic Modulating and Shutoff Valve
76-3009, Rev 1
No Effect
ENGINE - POWER CONTROL - Replace Solenoid Controller Valve
76-3010
No Effect
ENGINE - CONTROL - One Time Inspection of Electronic Computer Part No. 94Q572- 5 or 949572-8
77-3001, Rev 1
No Effect
ENGINE - Nl MOTIONAL PI CKUP - Install Nl Transducer with Chan~e in Des ion and Functional
Requirements
77-3002
No Effect
ENGINE - N2 MOTIONAL PICKUP - Inst all N2 Transducer Incorporating Improved Sealant to Better
With stand the 0peratin9 Environment
77-3003, Rev 2
No Effect
ENGINE - THERMOCOUPLE HARNESS - Rework Thermocouple Harness to Eliminate Moisture Problem
79-3004, Rev 1
No Effect
OIL - COOLING - Rework and Replacement of Oil
Cooler Transfer Tubes
79-3005, Rev 1
No Effect
ENGINE - OIL DISTRIBUT ION - Installation of New
Two Piece Number Three Oil Jet
79-3007
No Effect
ENGINE - ACCESSORY DRIVE GEARBOX ASSEMBLY Remove and Replace Rreather Pressurizing Valve
72-02-04-S-B LI ST
Page 7
!\~r 15/81
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SERVICE MANUAL
TFE731-2-1C
SERV ICE BULLETIN LIST (CONT)
Service
Bulletin
Incorp.
Title
79-3008
No Effect
ENGI NE - OIL TANK FILLER TUBE INSTALLATION Rework of Oil Tank and Oil Filler Tube Adapt er
and C:ao
79-3009 , Rev 1
No Effect
ENGINE - OIL - Testinq of Enaine Oil for the
Presence of Fuel
79- 3012 , Rev 1
No Effect
ENGINE - OIL OISTRIBUTION - Replace Lube anrl
Scavenqe Oil Pump
79-3013 , Rev 3
No Effect
ENGINE - OIL - Reolace Flow Control Thermostat
of Oil Temperature Control Valve
79- 3014, Rev 4
No Effect
ENGINE - OIL - Replace Thermostat Assembly of
Oil Temperature Requlator (Fuel/Oil Cooler)
79-3015, Rev 1
No Effect
ENGINE - OIL - Install Check Valve Part No.
3072693-1 in Oil Vent Line (Cancel led)
79-3017, Rev 1
No Effect
ENGINE - OIL COOLER INSTALLATION - Replace
Air/Oil Cooler and By-Pass Valve to Prevent Oil
Leakaae by Reducing Frettinq at Flow Connections
79-3019, Rev 2
No Effect
ENGINE - OIL LINE INSTALLATION - Replace Tube
Assembly to Transfer Gearbox to Prevent Interference with Fuel Flow Meter Electri cal Connector
79-3022, Rev 1
No Effect
ENGINE - OIL - Replace Oil Tubing to Gearbox
and Fuel/Oil Cooler
79-3023
No Effect
ENGINE OIL - DISTRIBUTION - Installation of
Redesigned Oil Cooler Oil Transfer Tube
72-02-04-S-B LIST
Paae 8
Apr 15/81
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SERVICE MAN UAL
TFE731-2-1C
SE RVI CE BULLETIN LIST (CONT)
Spare Parts
Bulletin
Incorp.
Titl e
TFEOOOl
No Effect
ENGINE - TRANSFER GEARBOX ASSEMBLY - Install
Soeed Pickup Spacer with Interference Fit to
Prevent Relative Rotation
TFE0007
No Effect
ENGINE - FAN DlJCT SET - Pro vi de Washer Part No.
NAS620C416L with Reduced OD at Fan Duct Lonqit udin al Fl anae to Prevent Interference with
Fillet Rad ius
TFE0008
No Effect
ENGI NE - FAN our.T SET - Reolace Screw for Cover
Part No. 3071952-1 to make Compatible with Existing Hardware
TFE0009
ffo Effect
ENGINE - COMPRESSOR INTERSTAGE DIFFUSER ASSEMBLY - Install Nut with Thicker Anti-Rotation
Flanqe for Improved Anti-Rotation
TFEOOlO, Rev 1
No Effect
ENGINE - OIL LINES AND INNER FUEL LINE MANIFOLD
INSTALLATION - Chanqe to Improved Insulation
and Sealant which are Applicable at Hiaher Temperature (Cancelled )
TFEOOll, Rev 1
No Effect
ENGINE - TURBINE SErTION - Replace First and
Second Stage Turbine Blades (Cancelled )
TFE0015, Rev 1
No Effect
ENGINE - FUEL HEATER TUBE INSTALLATION - Chanqe
Clamping Arranqement for Fluid Transfer Tube
Part No. 3072n36-1 to Reduce Possibility of
·
Misalignment During Clampinq
TFE0016
No Effect
ENGINE - PIN ION GEAR ASSEMBLY - Install Lonaer
Bolt for Pinion Gear Retainer Plate
TFE0018
No Effect
ENGINE - ENGINE WIRING HARNE SS - Provide Additional Clamp to Reduce Possibil ity of Nacelle
Interferin9 with Enqine Wirinq Harness
TFE0020
No Effect
ENGINE - FAN DUCT - Rep l ace Bolt and Nut on
Hiah Press ure Bl eed Ross with Bolt and Nut
Utilizinq Different , Self-Locking Features
TFE0021
No Effect
ENGINE - PRESSURE LIMITER VALVE ASSEMBLY Replace Spring Part No. 3070585-1 with Part No.
3070872-1
TFE0024
No Effect
ENGINE - WIRING HARNF.SS IN STALLATION - Additional Support to Prevent Rubbinq at HousinQ
Split Line
72-02-04-S-B LIST
Paae 9
Apr 15/81
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SERV ICE MANUAL
TFE731-2-1C
SERVICE BULLETI N LIST (CONT)
Sp.are Parts
Bulletin
I ncorp.
Tit l e
TFE0026
No Effect
ENGINE - COMRUSTION SECT ION - Incorporate Combu stion Chamber Plenum Case Part No. 3072443-3
TFE0027
No Effect
ENGINE - ACCESSORY DRIVE GEARBOX - Replace Nut
Lock Key Part No. 735~3-?.2 with Part No. 7356323
TFE0028
No Effect
ENGINE - FUEL CONTROL ASSEMBLY - Replace Packing Part No. S9412-015, Used on Gove~nor Lever
Sleeve Part No. 3070609-1, with Packing Part
No. S9413-015 . Add Restrictor Part No. 89S4484 and -5 to Enhance Attainment of Desired Fuel
Press ure Setting
TFE0029
No Effect
ENGINE - BY-PASS DUCT PANEL - Screws Part No.
NAS1100r.E3 -10 Used to Attach Forward End of
Left Hand By-Pass Panel have been Replaced by
Part No. NAS1101CE3-10
TFE0030
No Effect
ENGINE - ACCESSORY DRIVE GEARBOX - Gearbox Access Cover Part No. 3071382-1 has been Replaced
by Part No. 3071382-2
TFE0032, Rev 2
No Effect
ENGINE - IGNITER PLUG ANO LEADS INSTALLATION Install Plug with Thi cker Flange to Prevent
Bending (Cancelled)
TFE0033, Rev 2
No Effect
ENGINE - THERMOCOUPLE HARNESS - Install Improved Thermocouple Harness Part No. 3071849-5
TFE0034
No Effect
ENGINE - ACCESSORY DRIVE HOUSING - Repl ace Al ternator Shaft Seal for Better Seatino Capability
TFE0035
No Effect
ENGINE - FAN SHAFT AND HOUSING ASSEMBLY - Install Gasket of Manufactured Different Material
TFE0036, Rev 1
No Effect
ENGINE - LOW PRESSURE COMPRESSOR AIR - OIL SEAL
- Replace Air-Oil Seal Rotor (r.ancelled)
TFE0037
No Effect
ENGINE - WIRING HARNESS INSTALLATION - Additional Support to Prevent Rubbinq on Transfer
Gearbox Namep1ate
TFE0039
No Effect
ENGINE - PLANET GEAR ASSEMRLY - Install Lonqer
Stud to Provide Required Thread Protrusion Thru
Nut
72-02-04-S-B LIST
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SERVT CE MANUAL
TF E731-2-1C
SERVICE BULL ETIN LI ST (CONT)
Spare Parts
Bu 11 et in
Incorp.
Titl e
TFE0040
No Effect
ENG INE - LOW PRESS URE COMPRESSOR ASSEMBLY Replace LP Fourth Staqe Ax i al Compressor Rot or
Assembly
TFE0041
No Effect
ENGINE - FAN ROTOR - Repl ace Sea l Part No.
3071967-1 with Seal with Imoroved Surface Finish
TFE0042
No Effect
ENGINE - FUEL CONTROL - Replace Fuel Contro l
Flow Pressure Filter
TFE0043
No Effect
ENGINE - FUEL AND OIL LINES - Con ical Seals
Provided to Repair Fuel and Oil Tube Fitting
Leakage
TFE0045
No Effect
ENGINE - OIL AND INNER FUEL LINE MAN IFOLD INSTALLATION - Replace Tubing Insulators
TFE0046
No Effect
ENGINE - FAN SUPPORT SHAFT AND HOUSING ASSEMBLY
- Replace Fan Shaft Seal Rotor
TFE0047, Rev 1
No Effect
ENGINE - TURBINE SECTION - Replace HP Turbi ne
Shroud Attaching Bolt
TFE0048
No Effect
ENGINE - COMPRESSOR SECTION - Replace No. 3
Stationary Oil Seal
TFE0049
No Effect
ENGINE - TRANSFER GEARBOX ASSEMBLY - Inst al l
Speed Pickup Spacer with Ti~hter Tolerance Control
TFE0050
No Effect
ENGINE - INDICATING - Install Thermocouole Harness with Increased Insulation Res i stance at
High Temperature
TFE0051, Rev 1
No Effect
ENGINE - BY-PASS - Insta l l Bal anced Cl amp Nuts
on Planetary Gear shaft Assembly
TFE0052, Rev 1
No Effect
ENGINE - FAN SUPPORT SHAFT AND HOl~ ING ASSEMBLY
- Replace No. 1 Fan Carbon Face Stationary Oi l
Seal
TFE0053
No F.ff ect
ENGINE - OIL TEMPERATURE REGULATOR (FUEL /O IL
r.OOLER) AND FUEL HEATER - Include Additional
Packinq Part Number to Provide Alternate Par ts
TFE0054
No Effect
ENGINE - OIL TANK INSTALLATION - Replace Li qui d
Level Gaqe to Provide Better Sealinq
72-02-04-S-B LI ST
Paqe 11
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SERVICE MANUAL
TFE731-2- J r:
SERVICE BULLETIN LI ST (CONT)
Spare Parts
Bulleti n
I ncorp.
Title
TFE0056, Rev 1
No Effect
ENGINE - OI L PUMP AND CHIP DETECTOR INSTALLATION - Install Improved Chip Detector
TFE0057
No Effect
ENGINE - HIGH PRESSURE COMPRESSOR - Reolace
Diffuser Vane Deswirl to Prevent Disengaqement
from HPC Diffuser
TFE0058
No Effect
ENGINE - HP SHAFT AND COMPRESSOR INTERSTAGE
DIFFUSER - Replace No. 4 Seal with Seal Havina
New Fastener System to Prevent Accidental
Disassembly During Routine Handlinq
TFE0059
No Effect
ENGINE - INTERMEDIATE CASE ASSEMBLY - Replace
No. 3 Seal with Seal Havino New Fastener System
to Prevent Accidental Disassembly Durinq Routine Hand ling
TFE0060
No Effect
ENGINE - GEARSHAFT, SEAL, BEARING, DIFFUSER AND
SUPPORT ASSEMBLY - Replace No. 5 Seal wi th Seal
Havinq New Fastener System to Prevent Accidental Disassembly Durinq Routine Handling
TFE0061, Rev 1
No Effect
ENGINE - BY-PASS SECTION - Include Additional
Fan Rotor Blades to Provide a Greater Selection
by Moment Wei ght for Reoair Installation
TFEOOo2
No Effect
ENGINE - HIGH PRESSURE ROTOR AND NOZZLE ASSEMBLY - Replace Rotor Seal
TFE0063
No Effect
ENGINE - COMPRESSOR INTERSTAGE DIFFUSER ASSEr,1BL Y - Replace Packinq
TFE0064
No Effect
ENGINE - COMPRESSOR INSTALLATION - Replace Tie
Rod
TFE0065
No Effect
ENGINE - OIL PUMP - Replace Oil Pump
TFE0066
No Effect
ENGINE - ACCESSORY DRIVE GEARBOX - Replace
Breather Pressure Valve
TFE0069
No Effect
ENGINE - SURGE BLEED - Reolace Pneumatic
Shutoff Valve
72-02-04- S-B LIST
Page 12
Apr 15/81
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• TFE731-2-1C
LIST or CHAPTERS
Chapter
70
72
Date
Standard Practices
Enqine
Apr 15/81
Apr 15/81
•
72-02-04-fHAPTERS
Apr 15/81
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SERVICE MANUAL
TF[ 731-2-1C
INTRODUCT ION
TABLE OF CONTENTS
SUBJECT
INTRODUCTION
General
How to Use this Service Manu al
General
Engine Identification System
Effectivity Code System and Configuration
Notation Description
Applicable Publications
Abbreviations
CHAPTER/
SECTION/
SUBJECT
PAGE
72-02-02
1
1
1
2
2
2
2
72-02-04- CONTENTS
Apr 15/81
Ai Research
Phoenix
SERVICE MANUAL
TFE731-2-1C
INTRODUCTION
1.
General
A.
Thi s publication provides ser vi ce instructions for support of engines
manufactured by The Garrett Turbine Engine Company, A Division of The
Garrett Corporation , P.O. Box 29003 , Phoenix, AZ 85038. Specific engines covered in this publication are li sted on the title page.
CAUTION:
2.
REFER TO FEDERAL AVIATION REGULATION, PART 43, OR
EQUIVALENT REQUIREMENT FOR COUNTRIES OTHER THAN
UNITED STATES, FOR MAINTENANCE THAT MAY BE PERFORMED
BY PERSONS OTHER THAN FAA CERTIFIED PERSONNEL.
8.
The service in structions provided within this publication detail the
maintenance procedures that are required to support Recommended Routine
Periodic ~nspection Requirements (See GENERAL, INSPECTION/CHECK). These
procedures can be accompli s hed by an operator without the aid of special
tool s or test equipment.
C.
The Light Maintenance Manual, Report No. 72-02-02 provides instructions
for procedures requiring special tools or test equipment.
D.
This publicati on is prepared generally in accordance with Air Transport
Association Specification No. 100. Defini tions of words and terms used
i n this publication are as stipulated therein.
How t o Use This Service Manual
A.
Genera 1
The manual i s di vi ded into subjects i n accordance with Air Transport Assoc i at i on Spec ification No. 100.
The material conta i ned within this pub li cation is subdivided into reasonab ly sma ll topics for ready reference and ease of revision.
To accomp li sh t his, page number blocks are used to separate subjects
i nto topi cs . It i s necessary to use a standard page block system so
that topics may be broken out for special distribution. Page number
blocks used are as follows :
Description and Operation
Trouble Shooting
Servi cing
Removal/Installat i on
Adju stment/Test
Inspect ion/Check
Cleaning/Painting
Approved Repairs
Microfiche
1 through 100
101 through 200
301 through 400
401 through 500
501 throug h 600
601 through 700
701 through 800
801 through 900
901 through 1000
72-02-04-INTRO
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TFE731-2-1C
Index tab sheets are used to subdivide this publication for ease in
locating specific information.
2.
B.
Engine Identification System
Each engine is provided with a nameplat e for identification of the
engine. Information sup plied on the engine nameplate includes model
number, part number and serial number. The model number defines significant features and specification ratings. The part number defines a
group of specific configurations. All engines with the same part number
are interchangeable. The part number is supplemented by a series number, and if applicable, change numbers to define a specific
configuration. A series number is assigned at engine manufacture or
overhaul to identify product improvement changes incorporated beyond the
initially manufactured configurat ion. Individual changes i ncorporated
which are not within the series grouping are identified separately by
change numbers. Changes represented by series and change numbers are
product improvements and do not affect interchangeability of the engine.
Refer to the engine log book for changes incorporated s ince engine production which are not separate ly identified on the nameplate.
Each assembly of the engine which is a complete unit has a separate
nameplate carrying part number, serial number and product improvement
change information. Any assembly is interchangeable with assemblies
having the same part number.
C.
Effectivity Code System and Configuration Notation System
Some of the instructions and information contained in this publication
are applicable only to specific engine model numbers, engine
series/serial numbers or pre or post service bulletin configurations of
engines. When this occurs, the applicability of the material is noted
at the beginning of the paragraph, procedural step, tabl e title, or
figure title. When the applicability of material is to certain engine
model numbers only, applicability is specified by effectivity codes representing engine model numbers. An effectivity code i s assigned for
each engine model number in Table 1, Effectivity Code List. When
material is applicable only to specific engine series/serial numbers, or
only to configurations which are pre or post service bulletin compliance, effectivity is spec ified by direct reference to engine
series/serial numbers or service bulletin number.
3.
Applicable Publications
Other publications applicable to equipment specified in this publication are
listed in Table 2 by report number, along with nomenclature and part number
of the equ ipment covered. Separate publication s for components of the engine, when available, are referenced in the text where applicable and listed
in Table 2.
4.
Abbreviations
None.
72-02-04-INTRO
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SERVICE MANUAL
TFE731-2-1C
Tabl e 1.
Eff ect i vity Code List
Engine Model No.
Eng i ne Part No.
TFE731-2-1C
3070000-1/-2/-3/-4/-5/
-6/-7/-8/- 9/-10/-11/
- 12/-13
Table 2.
Code Symbol
Applicable Publications List
Norn encl at ure
Part No .
Publication
Type
*Turbofan Aircraft Engine
3070000-1/-2/
-3/-4/-5/-6/
-7/-8/-9/-10/
-11/-12/-13
72-00-71
IPC
*Turbofan Aircraft Engine
3070000-1/-2/
-3/-4/-5/-6/
-7/-8/-9/-10/
-11 /-12/-13
72-02-02
LMM
*Illustrated Parts Catalog and Light Maintenance Manual are included
in Microfiche in envelope under tab labled Microfiche.
72-02-04-INTR0
Page 3/4
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Al Research
Phoenix
SERVICE MANUAL
TFE731-2-1C
LIST OF EFFECTIVE PAGES
72-02-04
CHAPTER/
SECTION
PAGE
DATE
of
Effective
Pages
1
Apr 15/81
Record of
Temporary
Revisions
1
2
Apr 15/81
Apr 15/81
CHAPTER/
SECTION
PAGE
DATE
Li st
Table of
Contents
70-00-00
Apr 15/81
1
2
3
4
5
6
7
8
Apr 15/81
Apr 15/81
Apr 15/81
Apr 15/81
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70- EFF
Pagel
Apr 15/81
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'"'"' o"I
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\T ANOARO rRACTICES - (NGIN(
""G"rnrr "1
- - , tand~rd Oisassernbly Procedures
, t~ndard Rea~sernbly Procedures
Replaceable Components
70-00-00
PA(,F
l
1
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70-C0NTENiS
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TFE731-2-1C
STANDARD PRACTICES - F.NGJNE - GENERAL
1.
General
The standard practices and general maintenance instructions presented in
this chapter are reconrnenrled by the enqi ne manuf acturer . Freauent reference
shall be made to thi s chapter by personnel engaged in maintenance activities
outlined in this pub li cati on.
2.
Standard Disassemb ly Procedures
Table 1.
Material or Compound
CAUTION:
NOTE:
Material and Compounds
Manufacturer
ANY SUBSTITUTES USED FOR LISTED INDUSTRIAL MARKING INK OR
YELLOW CHINA MARKER SHALL CONTAIN NO CARBON.
Equivalent substitutes may be used for licted items.
Industrial marking ink
(Vi olet, No. 127-1/2)
Pannier rorp , 207 Sandusky St ,
Pittsburah, PA 15212
Solvent, Stoddard (Federal
Specification P-D-680,
Type I or I I)
Commercially available
Yellow china marker
(No. 170T)
Blaisdell Pencil r.o, Philmont Rd ,
Bethagres , PA 19006
A.
Observe Followina General Procedures Throughout Disassembly or Removal
Operations
(1)
Always keep oorts, bores and passaqes of assemblies or components
sealed with sui table olastic closures between maintenance
procedures. Cover larqe openinqs with plastic sheetinq. Do not
use tape, cardboard or cloth.
70- 00- 00
Page 1
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SERV ICE MANUAL
TFE731-2-1C
2.
A.
(2)
Record manner of lockwiring for rluolication at reassembly.
CAUTION:
(3)
DO NOT USE ANY MARKING DEVICE CONTAINING
CARBON .
Use yellow china marker (.No. 170T) or industrial markinq ink
(Vio l et, No. )27-1/2) for marki ng. Remove al l marks at compl et i on
of task using solvent, Stoddard (Federal Specification P-D-680,
Type I or TI J.
3. Standard Reasserrd:>ly Procedures
Table 2. Materials and Compounds
Material or Compound
NOTE:
Manufacturer
Equivalent substitutes may be used for listed items.
Lint-free cloth
Commerciall y available
Lubricant (OS-124 or
Santovac 5)
Monsanto Co, 800 N Lindberah Blvd, St
Louis, MO 36166
Sol vent, Stoddard (Fe~eral
Specification P-D-680,
Type I or II)
Corrmercially available
A. Observe Following General Procedures at Reassembly
(1)
Exercise extreme care to prevent dirt, dust or foreign particles
from enterina the engine. If any foreign particle i s drooped into
the enqine durina maintenance, stop work until fore ign particle is
located and removed.
( 2)
Cover large openings with plastic sheeting for added protection to
the enqine. Cap open tube ends. If the enC1ine is to be left for
even a short period in a partially disassembled state, cover or cao
all openings .
(3) . Be sure all parts are thoroughly clean before asserrd:>ly.
parts and surfaces with a clean, lint-free cloth .
Wipe all
70-00-00
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3.
A.
(4)
Observe al l specified torque value s durinq reassembly.
(5)
At compl eti on of a~sembly of any components marked for indexinq,
remove index marks usinq so lvent, Stoddard (Federal Specification
P-D-680, Type I or II).
(6)
0-rinq type packinqs used in engine pneumatic systems may be installed without lubr icant. Packinqs used in en~ine fuel system may
be coated with a light coat of enqine fuel. Packinqs used in enqine oil system may be coated with a l iqht coat of enqine oi l. Ensure there is not contamination or excessi ve lubricant on oackinos
at assembly. As an alternative, any packinq may be lubri cated with
lubri cant (OS-124 or Santovac 5).
(7)
Whenever toraue values are i~entified in the applicab le
chapter/section/subject coverinq the part, these specified toraue
val ues do not include frictional toroues developed by self- locki nq
devices or 11 run-down 11 resistance. The frictional resistance or
11
run-down 11 toraue must be added to the specified toraue. When
torque is applied to the bolt and the nut is held stationary, the
hiaher value shall be used. When toraue values are not specified,
conform to standard shoo practice or sources such as FAA Manual
AC65-9, Airframe and Powerplant Mechanics General Handbook.
(8)
Mininum runnina torque values have been established for several
sizes of bolts and self-1ockinq female threads. Rolts and inserts
with running toraues less than the below minimums shal l be
replaced. ·
Bolt/Insert Size
No. 8
No. 10-32
0.250 in .
(9)
Minimum Runninq Toraue
in.-lb
in. - lb
6 in.-lb
4
6
Whenever toraue values are not identified in the aoplicable
chapter/section/subject, follow general guidel ines listed in Tables
3 and 4 for tightening small fasteners.
70-00-00
Paoe 3
Apr 15/81
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SERVICE MANUAL
TFE731-2-1C
NOTE:
Fasteners installed throuqh essentially inelastic bounctaries
will first be tightened to remove vi sible clearance between
parts . During this initial tiqhteninq of the faste ner, the
"run-down" resistance shal l be not ed on the 1 ast rotation just
before establishment of a ten~ile preload in t he fastener. The
fastener s hall t hen be given a steady additional t i ghtenina
movement by the wrench to prorluce a final toroue, that is approximately equal to t he "run-down" torque pl us t he values
shown i n Table 3 for t he respect i ve thread s iz e. This procedure will produce +35/-35 percent accuracy whi ch i s adeauate
for all items not li sted under torq ue val ues below. As a further assistance, Table 4 gives qeneral guidelines for obtaining
the final toroue.
Table 3.
Tiqhtening Small Fasteners
Toraue (in. -lb )
Thread Size
Aluminum Fastener
Cres Fastener
6
5
10
8
10
10
1/4
15
45
5/ 163/8
80
140
· Table 4.
Thread Size
6-32
8 - 32
10-24
1/ 4-20
5/16-18
3/8-24
20
35
75
160
275
Tightening Small Fasteners
Approxim ate Rotation After Run-Down
45 dea
60 deg
40 deg
40 deq
40 dea
60 deq
70-00-00
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Apr 15/81
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SERVICE MANUAL
TFE?:ll-2-lC
3. A.
(10)
Unless otherwise specified , flared tuhinq fittinas (when
not used with conical seal s) and hose fittinas sha ll be
tightened to toraue values specified in Table 5.
Tabl e 5.
Standard Toraue Values for Flared Tuhina Fittings
(Conical Seals Not Used) and Hos e Fittinqs
Torque,
Aluminum Parts
(in.- lb )
Tube
Dash No .
2
3
4
5
6
7
8
10
12
16
20
12-15
20-35
40-60
65-85
100-120
140-160
180- 220
270-330
360-440
500-n~O
660-780
800-960
960-1140
}()80-1320
24
28
32
(11)
Toraue,
A11 Stee 1 Parts
(in. - lb)
35- 40
70-80
100-120
JAO-J i:;o
190- 220
240- 280
300-350
440-500
600-660
840-%0
1080-1320
J ~00-1800
2160-2520
?400- 2880
Conical seals are used at spec if ic locations dur inq enqi ne production to preclude leakage. However, conical seals may be used at
any flared tubing fittinq of appropriate size in fuel and oil systems as a repair to correct leakage at the option of the user.
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CAUTION:
3. A.
PROPER INSTALLATION OF CONICAL SEALS DESCRIBED
IN THE FOLLOWING STEP IS ESSENTIAL TO AVOID
FLOW RESTRI CTION OR s uB::;EQl/ENT LEAKAGE . r.ONI CAL SEALS ARE TO BE USED ONLY ONCE. ENSURE
THAT PREVIOUSLY INSTALLED CONir.AL SEAL IS
REMOVED FROM PLUMBING FITTING BEFORE INSTALL ING NEW CONICAL SEAL.
(12) Unless otherwise specifi ed, flared tubing fittings when used with
conical seals shall be tioht ened to toroue values in Table 6.
When conical seals are used, install conical seals and tighten
fittinqs as follows.
(a)
Select proper conical seal part number for tube assembly beinq installed. (Refer to table 6.)
(b)
Lubricate conical seal and threads of plumbing fittina with
clean enaine oil (72-00-00, GENERAL - SERVICING).
CAUTION:
(c)
DO NOT INSTALL CONICAL SEAL INTO TUBE NUTS.
SEAL SHALL BE INSTALLED ON MALE FITTING ONLY.
Install conical seal onto male flare portion of plumbing
fitting. Flats on conical seal are desiqned to provide
proper positioning of seal onto plumbinq fitt ing to prevent
cocking of seal that could cause flow restriction.
(d) Thread tube nut onto plumbinq fitting several turns with
fingers until joint is snug. If tube nut cannot be tightened
snugly with fingers, disa5semb1e and correct problem to prevent assembly damaqe to conical seal.
CAUTION:
(e)
USE CARE NOT TO TIGHTEN TUBE NUTS MORE THAN
SPECIFIED TO AVOID DAMAGING SEAL. DO NOT
LOOSEN TU!3E NUT AFTER INITIAL TORQUE APPLICATION WITHOUT REPLACING CONICAL SEAL.
Tiahten tube nuts as follows. Conical seal is subject to
co1d creep: therefore, a double tightenino procedure is
reouired.
1 Tighten tube nuts to torque value specified in Table 6.
Torque values are higher than toraue values for tube nuts
without conical seals installed.
2 Allow five minutes elapsed time for cold creep to occur.
3 Recheck toraue on tube nut and, if reauired, further
tighten to toraue value specified in Table 6.
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Tabl e 6.
Standard Torque Value s for Flared Tubing Fittings
Us ed Wi t h Conica l Seal s
Tube
Dash No .
Conical Seal
Part No.
Torque (in.-lb),
All Steel Parts
3
4
5
6
651-525-9003
651-525-9004
651-525-9005
651-525-9006
651-525-9008
110 to 125
165 to 190
225 t o 250
335 to 375
575 to 675
8
4.
Replaceable Components
A.
General
(1)
In addition to the replaceable components outli ned in other chapters in this publication, all plumbing, tubing, fi ttings , brackets,
grommets, and common hardware are replaceable.
(2 ) All packings and gaskets removed during maintenance shall be
replaced with new packings and gaskets.
(3)
All retaining hardware which have tabs to be bent at installati on
(tabbed locking washers, etc. ) shall be replaced when removed and
parts with tabs that have been previously bent shall not be reused.
(4) All female threaded devices incorporating self-locking feature
shall be either replaced at reassembly or self-locking feature
shall be verified to be satisfactory at time of reassembly, as evidenced by noticeable drag when mati ng part is threaded into selflocking part.
70-00-00
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LIST OF EFFECTIVE PAGES
72-02-04
CHAPTER/
SECTION
PAGE
DATE
List of
Effective
Pages
1
2
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Apr 15/81
Record of
Temporary
Revisions
1
2
Apr 15/81
Apr 15/81
Table of
Contents
Apr 15/81
Description
and
Operation
Contents
Apr 15/81
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2
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7
8
9 F/0
19 F/0
20
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11 F/0
12
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15
16
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18
Trouble
Shooti ng
Contents
CHAPTER/
SECTION
Servi cing
Contents
Removal/
Install at ion
Contents
PAGE
DATE
104
105 F/0
106
107 F/0
108
109 F/0
110
111 F/0
112
113 F/0
114
115 F/0
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402
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SECTION
PAGE
Adjustment/
Test
Contents
501
502
503
504
505
506
507
508
509
510
511
512
513
514
515
516
517
518
519
520
521
522
523
524
525
526
527
528
529
530
531
532
533
534
535
536
537
538
Inspection/
Check
Contents
DATE
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CHAPTER/
SECTION
Cleaning/
Painting
Contents
Approved
Repairs
Contents
PAGE
DATE
601
602
603
604
605
606
607
608
609
610
611
612
613
614
615
616
617
618
619
620
621
622
623
624
625
626
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901
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Microfiche
Contents
72 - EFF
Page 2
Apr 15/81
Al Research
Phoonh
SERVICE MANUAL
TF F7 31- 2-1C
GENERAL
TABLE OF CONTENTS
SURJECT
GENERAL
Description and Operati on
*Trouble Shoot ing
Servicing
Removal/Instal l ation
Adjustment / Test
Inspection/r,heck
Cl ean ing/P ainting
Approved Repairs
l'-1icrofiche
CHAPTER/
SECTION/
SUBJECT
PAGE
72-00-00
1
JOl
301
401
501
601
701
801
901
*Trouble shootin9 procedures contained in thi s manual are general in nature
and only isolate the malfunctioning system. Detailed Trouble Shoot ing
procedures are provided in Li qht Maintenance Manual, Repor t No. 72-02- 02.
GENERAL
72-CONTENTS
Apr 15/81
~
' AIResearch
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P hoenix
SERVICE MANUAL
TFE731-2-1C
CHAPTER 72 - DESCRIPT ION AND OPERATION
TABLE OF CONTENTS
SUBJECT
CHAPTER/
SECTION/
SUBJECT
ENGINE
72-00-00
DESCRIPTION AND OPERATION
Engine
Air Inlet Section
Fan Bypass Section
Compressor Section
Combustion Section
Turbine Section
Accessory Drives Section
Engine Fuel and Control System
Fuel Pump
Fuel Control
Electronic Computer
Surge Bleed Control
(Pre SB 73-3028) Flow Divider and Drai n Val ve
(Post SB 73-3028) Flow Divider Valve
Fuel Manifold
Fuel Heating
Inlet Pressure and Temperature Sensor
Additional Fuel System Components
Electrical System
Ignition System
Anti-Icing System
Indicating System
Intersta~e Turbine Temperature
(ITT) {TT5) Sensor
Magnetic Chip Detector
Nl and N2 Transducers
Anti-Ice Pressure Switch
Qi 1 System
Components and Accessories
Directional References
Compressor Core
PAGE
1
4
4
4
4
4
5
5
6
6
6
14
14
14
14
14
15
15
15
15
16
16
16
16
18
18
18
21
21
21
DESCRIPTION AND OPERATION
72-CONTENTS
Apr 15/81
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AiResearch
P hoeni.
SE" PVI CE MANUAL
TFE711-2-1C
GENERAL - DESC RIPT ION AND OPERATION
1.
Engine
The TFE73 1 Engine i s a liohtwe i qht , t wo-s pool geared t ransonic- stage, frontf an, j et-propul sion engine for ai r cr aft. The engi ne is modularized for ease
of maintenance . Desi gn s impli city and inher ent st urdiness eliminate the
need for aerodynamic inlet ouide vanes , vari abl e geomet ry and other s imilar
complexities, and thereby minimize inl et i cing and reduce noise and weight.
In addition to a high-bypass ratio, the enqine i ncorporates recent des i gn
developments to minimize engine generated nois e to a l e vel appr eciably below
that of competitive bu siness jet enqines . The use of a r ever se- flow annular
combustor diminishes engine length and provides the advantage of t he cool skin concept for the external surfaces of the turbine section. An annular
duct serves to bypass fan air for direct thrust.
A spinner hub and an axial-flow fan are located at the forward end of the
engine and are gear-driven by the low pressure spool. The low press ure
s pool consists of a four- stage low pressure compressor and a t hree- stage low
pressure turbine, both mounted on a cornnon shaft. The high press ure spool
consists of a high pressure sinqle-stage centrifugal compressor and a high
pressure sinnle-staae turbine. The hiah pressure compre ssor and tur bine ar e
mounted on a corrrnon shaft. The high press ure spool drives the accessory
section. The spool shafts are concentric and the low-pres sure spool sh aft
passes through the high pressure shaft. (See figure 1. )
Figures 2 throuqh 6 show system functions schematicall y.
physical l ocations of engine components and accessories.
Fi aure 7 shows
Refer to Table 1 for Leading Particulars .
Table 1.
Leading Particulars
Engine Type •• •••••..• • .••....•••.•.... •• •...•••... • •. Two- spool turbofa n engine
Fan ••.••••••••.••..••..•••..• •• •••• • ... . ••.•••••.• . •...• • •• Singl e- stage geared
Low Pressure Compressor ••. .•.... .•. • .•...•.•... • .••••..• . . . .. • Four- stage axial
Low Pressure Turbine ............ .. .... . . . ... .. . .. . . ... . .. . .. Three- stage axial
High Pressure Compressor •• . • • ...•. . .................. Single-stage centrifugal
Hi gh Pressure Turbine .••..••••••.•.....••.••.....••.... . ••.. Sinq l e-staqe axial
Dimensions (approx)
Lenqth .. .. . . ....... . ..... . ... . . . ..... . ........ . ............ . .. .. . . 52 .83 in .
Wi dth . . . • . • . • • . . • • • • • • • • • • • • • • • • • • . . • • • • • • • • • • • • • • • • • . • • • • • • • • . • • • • 34 • 20 i n •
He i ght
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 . 36 i n.
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SERVI CE MANUAL
TFE731- 2- 1C
Table 1.
Leading Particulars (Cont)
Weight ( approx dry weigh t ( lb)) .. .. • •. .. .•... . ... . .. . ... (ore SB 72- 3040) 789 . 5
(oost SB 72- 3040) 790. 5
Ratings
Absolute Altitude ••..•. •.•.. .......•.. . •• . ....•.....•. .. ....... . ... 45, 000 ft
Starting Altitude (ground starts) .. .•..••. ....... ..... Sea level to 15 , 000 f t
Ambient Air Temperature
Operation . •••.••• •.• •..•. •.••..... . . . ..• • . .... .... .. - 54 to 52C (-65 t o 125F)
Starting ••• • ••••.•• •• .... •.•. . •••..•..••.....••.... -40 to 52C (-40 t o 125F)
Exception:
Lowest permissible temperature shall be that at
wh ich the fuel vi scosity is at or above the pour
point .
Oil ConsllTiption . ...... . .... . .. . .......... ... ............ . ... . . . .... 0.05 gal / hr
Electrical Power (nominal)
......... . ... ... ..... . ............. . . .... .. .. 28 vrlc
Speed
Low Pressure Turbine Rotor (·Nl) • • •••• • ••••• • ••• • •••• 20 , 688 rpm {100 percent)
High Pressure Turbine Rotor (N2) ..•.• . .. . •. • .... ..• 29,692 rpm (100 percent)
Lubrication System
-· lubrication Specification ..... .... ......... .. .. Refer t o SERVI CING, Table 301
Fuel System
Fuel Specification
Thrust (uninstalled)
•.•••••. • •..•• ..• ...• •.....•.. Garrett EMS53111, EMS53112,
EMS53113 Cla ss A and B,
EMS53116 (Refer to Aircraft Fli9ht Manual)
•..•..•..... •.•.•••.•. . ••...•....•.......•...••.•. 3230 lb
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ENG INE SUPPORT HOUSING"'
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SERVICE MANUAL
TFE731-2-1C
2.
Air Inlet Section
The air inlet sec tion is located in the front of the enqine directly behind
the fan rotor assembly and is enclosed by the fan inlet and bypass hou sinq
assemblies .
3.
Fan Bypass Section
The fan provides inlet air for the enQine compressor and bypasses a larqe
portion of the inlet air avai lable to the enoine for noise reduction and additional thrust. The bypass section consists of the fan soi nner , fan spinner support, fan rotor assembly, fan bypass stator, fan duct assembly and
the bypass fan support and shaft sec ti on.
4.
Compressor Section
Inlet air enter s the engine through the air inlet section located immediately aft of the fan bypass section. From the air duct it enters the compressor section at the low pressure (four-stage axial) compressor where it
is compressed and forced throuqh the interstaqe diffuser assembly to the
high pressure (single-stage centrifugal) tompressor.
.
Air is further compressed by the ~igh pressure compressor and is discharged
into the combustion section. _
5.
Combustion Section
The compressed air flows into a single reverse-flow annular combu stio~ chamber in the turbine section where it is mixed with atomized fuel supolied by
twelve duple~ fuel nozzles containing primary nozzles used for starting, and
secondary nozzles used in conjunction with the primary no~zles for all other
phases of engine operation. ·The fuel-air mixture is ignited by the two igniter plugs. After ignition cutout, combustion is self-sustaining. The
r:-esultant combustion gases are directed· to the turbine by the transition
liner.
·The combustion chamber plenum assent>ly encloses the entire combustion area
and provi des a plenum for compressed air. The rear end of the plenum assembly provides a register for the turbine bearinq support.
6.
Turbine Section
The turbine section contains four (one high pressure, three low pressure)
axial flow turbine wheels and four stator assemblies. Gases from the combustion section flow through the stator and wheels and exhau st to atmosphere
through the thrust and exhaust nozzle.
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T
731 - 2-lC
7. Accessory Drives Section
The accessory drives section consists of a gearbox module for supplyinq
drive power to engine and aircraft accessories . Primary components of the
modul e are a transfer qearbox nnd an accessory drive gearbox. The transfer
gearbox is dr iven by a vertical shaft from t he hi oh pressure spool and
drives the accessory drive gearbox through a horizontal shaft. The accessory drive gearbox provides s haft power for aircraft accessories (mounted on
the forward face of the accessory drive gear box), the fuel pump, fuel control and t he oil pump.
Three drives are provided on the forward face of the accessory drive gearbox
for customer- furnished accessories s uch as a starter, alternator, hydraulic
pump or similar acce ssories.
The oil pump, mounted on t he aft face of the accessory drive gearbox,
provides for oil pumping and scavenging. A magnetic chip detector is
mounted on the oil pump. The oil pump also has a boss in which a temperature probe may be mounted for measurinq fan gearbox scavenge oil
temperature. An oil filter and oi l filter bypass indi cator valve are
mounted on the accessory drive gearbox. A fuel f i lter is mounted on the
fuel pump mounted on the accessory dr ive gearbox. A1so mounted on the aft
face of the gearbox is _a breather pressurizing valve .
8.
Enqine Fuel and Control System
The engine fuel and cont rol system pressurizes fu el routed to the engine,
meters fuel flow, and delivers atomized .f uel to the combustion section of
the engi ne. Desired fuel temperatures are maintained with oil-to- fuel he at
exchanging.
Fuel flow is controlled by a hydromechani cal fuel control, which contai ns~
fuel shutoff section and a fuel metering sect ion. This unit is mounted on
the fuel pump and provi des the power lever connection point and the fuel
shutoff function. The unit provides mechanical overspeed protection for the
high pressure rotor during normal (automatic mode) enqine operation.
During normal engine operation, a remotely mounted electronic computer performs t he functions of thrust setting, speed governing and acceleration and
deceleration limiting through el ectrical control outputs to the fuel control
i n response to power lever inputs. In t he event of electr ical or computer
failure, or at the option of the pilot, the f uel control will function i ndependently in manual mode to provide for engine oper ation at reduced power at
non-flat rated conditions . The electronic computer also control s the surge
bleed control system in normal operation . When the electroni c computer is
deactivated, the surge bleed valve assumes a one-third ooen position which
allows conservative operation on manu al mode operation. A logic diagram of
the engine fuel and control system is presented in Fi gure 2.
The total enaine fuel and control system consi sts of the fol l owing components, whi ch provide the fun ctions indicated. (See fiqure 3 , or 4.)
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SERVI CE M/\NUf\L
TFF731- ?- 1C
8.
A.
Fue l Pump
The fuel pump pro vides hi gh press ure f uel t o t he enqi ne fue1 and control
system. The unit consi sts of a boost pump el ement , f uel f i lter, rl iff er ent i al press ure i ndi cator (f i lter bypass val ve ) , hi gh press ure pump
e lement and re li ef va lve .
An anti-i cing va l ve is provided withi n t he f uel pump to mix warm fuel
from the fu el heater with the di schar qe f l ow of t he hoost pump to prevent i cing of the fu el f ilter el ement.
The filt er bypass valve on the fu e l pump al)ows bypass of fu el around
the fue l filter when the pressure drop across the f uel filter i s
excessive. An integral delta pressure indi cator vis ual ly flags an excess i ve differential .press ure condition before bypass i na occurs by extending a pin from the valve .
B.
Fuel Control
This unit contains the fuel metering section, power lever input, shutoff
valve, outlet pressurizin9 valve, overspeed solenoid, and a mechani cal
governor that functions .as either an overspeed governor for the high
pressure rotor or provides manual control when the electronic computer
section of the fuel control system is deactivated. When acti vated , the
electronic computer controls fuel flow schedul _inq by electri cally set ting the metering settion pressure drop within the fuel control in accordance with the power lever and engine inputs. · •
C.
Electronic Computer ·
The remotely located electronic computer is basically a hi gh pressur e
rotor speed (N2) governor with provisions for fuel limi t s durinq accel eration and deceleration. The computer portion of the fuel control sys tem performs governing, limitinq and scheduling function s in response t o
power lever and engine inputs. An electri cal input of 15 t o 30 volts de
is required from the aircraft electrical system dur i ng all modes of engine operation. Inputs to the electronic compute~ are en qi ne inlet
pressure (PT2) and temperature (TT2), interstaqe turbine t emperature
( ITT) (TT5), high (N2) and low (Nl) pressure rotor speeds and throttle
position (power lever input) for computinq engi ne control parameters .
The computer derives a control bleed valve area signal used by the surae
bleed control system.
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Apr 15/ 81
Aa
BLEED AREA
Nl = LOW PRESSURE SPOOL SPEED
N2
HIGH PRESSURE SPOOL SPEED
P3
COMPRESSOR DISCHARGE
PRESSURE
PT2: ENGINE INLET TOTAL
PRESSURE
TT2: ENGINE INLET TOTAL
TEMPERATURE
TT5: INTERSTAGE TURBINE
TEMPERATURE
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SERI' . ':E MANUAL
TF r
8 . C.
,1-2-lC
Electronic Computer (Con .
The computer provides an aporopriate output current to the toraue motor
of the fuel control based on the various inout sionals. The computer
may be controlled by an aircraft. manual mode switch and includes an output s ianal f or a cockp i t- ,,vu nted indi cc1tor to show manual mode operation
in the event of los s of i npu t power , computer malfunction or pilot deactivation of the computer power. A computer output is provided for actuation of an aircraft speed switch relay at approximately 50 percent high
pressure spool rpm. This function may be used to automate the start
cycle.
(Pre SB 76-3007) No overspeed protection is supplied by electronic computer durinq manual mode operat ion, regardless of the position (on or
off) of the cockpit switch for computer activation.
(Post SB 76-3007) No overspeed protection is suoplied by the electronic
computer during manual mode operation, regardless of the position (on or
off) of the cockpit switch for computer activation as lona as the
NORMAL/MANUAL switch on the face of the electroni c computer is set to
NORMAL. Overspeed protection circuits of the electronic computer for
both low and high pressure spoo ls remain activated i n the manual mode
provided the cockpit switch for computer activation i s on, and the
NORMAL/MANUAL switch on the face of the electroni c computer is set to
MANUAL (assuming Nl and N2 transducer inputs are available to the
computer) •
.(Pre SB 76-3007) When commanded by an aircraft fuel enrichment switch,
the electronic computer increases fuel scheduling to assist engine
starting. Caution must be exerci sed not to exceed allowable temperature
limits when using this function.
(Post SB 76-3007) The electronic computer automatically provides increased fuel scheduling durin~ engine start s to assist startinq. When
collJTlanded by an aircraft fuel enrichment switch, the electronic computer
maintains increased fuel schedulino beyond the turbine temperature limit
of automatic fue l enrichment cutoff to assist enqine startinq. Caution
must be exercised not to exceed allowable temperature limits . when using
this function.
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SERVI CE MANUAL
TFE711 - 2-lC
8.
0.
Surge Bleed Control
The surge bl~ed control consists of two suroe valve control solenoids
(solenoi ds A and B) i n the solenoid control l er valve (solenoid controller) and a modul ati ng and shutoff (surge hleed) valve whi ch is
opened to prevent low press ure surqe. Bl eed va lve position is control led to maintain an adequate marain from enqine surqe under all ooerating conditions .
(Pre SB 72-3085) The third soleno i d valve (so l enoid C) controls operation of the anti-ice valve.
(Post SB 72-3085) A port in the so lenoid cont r ol l er for the third control solenoid (solenoid C) (not used) is pl uoaed.
E.
(P re SB 73-3028) Flow Divider and Drain Va lve
This unit controls the routing of fu el during engi ne star ti ng to ensure
proper atomi zation of the fuel .
(Pre SB 73-3009) The unit also functions to drain'the primary nozzles
during engine shutdown. A small amount of fuel will flow from the drain
fitting on the unit during each normal engine .shutdown.
(Series 1-37, Post SB 73-3009) The drain vaive boss of the unit is
capped .
F.
(Post SB 73-3028) Flow Divider Valve
Thi s unit controls the routinq of fuel durinq enq~ne start i ng to ens ure
proper atomization of the fuel.
G.
Fuel Manifold
This unit provides routinq and atomizi ng of the fuel to ensure oroper
combustion.
H.
Fuel Hea,ti ng
The fuel heater permits oi l -to-fuel heat exchanging to maintain desired
temperatures and prevent ice formation in the fuel system from cl ogging
the fuel pump assent>1y fuel filter. A portion of the engine fu el suppl y
is diverted throuqh the fuel heater by a thermost ati cally operated anti ice valve located in the f uel pump assembly.
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Apr 15/81
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SERVICE MANUAL
TFE731-2-1C
8.
I.
In let Pressure and Temperature Sensor
An inlet pressure and temperature sensor conta ins el ectrical elements
for sens in g inlet air temperature (TT2) and a pressure tao for sensing
inlet air pressure (PT2). Both in l et par ameters are required b1 t he
electronic computer. An electrical anti-i ci ng element is contained in
the sensor . The sensor is located aft of the forward fan inlet flange
at the 12 o'c lock position.
J. Additional Fuel System Components
Additional f uel system components are the associated fu el lines and
plenun drain valves. No fuel i s allowed to drain from the plenun in
normal operation, but any fuel accumulation during a false start is
drained.
9.
El ectrical System
The electrical system in cludes engine and aircr aft mounted components for
engine control and indicating. Control components include the electron ic
computer, ignition system, solenoid controller and the electrical input
section of the fuel control .
Interconnection of components is provi ded by two electrical harnesses and
aircraft wiring.
Indicating components include the thermocoupl e harness (inter stage turbine
temperature sensor), Nl (low pressure spool) and N2 (high pressure spool)
transducers, and the TT2 (inlet temperature) sensor of the inlet pressure
and temperature sensor, and an electrical chip detector.
(Pre SB 72-3085)
switch.
Indicating components also include an anti - ice pressure
Customer-furnished engine mounted electrical system components may include
a starter-generator, alternator, fire detector, oil pressure and temperature sensors, fuel flow and pressure sensors, engine pressure ratio sensor
and wiring harness.
10.
Ignition System
The engine ignition system is a dual igniter system r equiring a de power
input of from 10 to 30 volts for operation. It i s capable of accepting
over loads of 40 volts for short periods to allow use of series 24 volt batteries for starting. The system includes the ignition unit, igniter plugs
and high voltage shielded output cabl es . Either continuous or intermittent
operation is permi t ted through a cockpit switch. The ignit ion unit is a
solid st ate, high voltage, capacitor discharge type th at provides a spark
rate at the igniter plugs of appro ximately two sparks per second with an
output of 18,000 to 24,000 volts.
72-00-00
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Phoonll
SERVI CE MANUAL
TFE731-2-1C
11.
Anti-Icing System
(Pre SB 72-3085) The anti-icinq system s upplies heated compressor bleed air
{P3) from a combustion chamber - pl enum bl eed port to prevent ice formation
at the fan spi nner. System operation i s controll ed by an aircraft anti-ice
S\'1itch. (See figu r e 5. )
Electrical heati ng elements are used by the inl et pressur e and temperature
sensor to prevent i ce formation on the sensor. Power is s upp lied to the
electrical heating elements whene ver anti-i cina i s selected.
{Pre SB 72-3085) When anti-icinq is sel ected, the anti-ice solenoid of the
solenoid controller is energized. The anti-ice solenoid then shuts off
bleed air pressure to chamber A of the anti-ice valve and vents chamber A
to ambient . Compressor bleed air pressure in chamber B then unseats the
anti-ice va l ve poppet and permits flow of the heated bleed air. Air flow
is di rected to the anti-ice pressure switch and components rece iv in g antii ce ai r. The anti - ice pressure switch actuates to provide cockpit indication of anti-icing whenever anti-icinq air pressure is present.
12.
Indicating System
Indicating system components providing cockpit indications include the
thermocouple harness (interstage turbine temperature sensor) and Nl and N2
transducers, and the electrical magnetic chip detector.
(Pre SB 72-3085)
sure switch.
A.
A cockpit indication is provided for the anti-ice pres-
Interstage Turbine Temperature (ITT) (TT5) Sensor
An internally mounted system of parallel thermocouples i s positioned
between the high and low pressure turbine sections to sense temperature
in this section of the enqine. Two outputs from the thermocouples are
routed from the enqine, one for the fuel system electroni c computer and
the other for cockpit instrumentation.
B.
Magnetic Chip Detector
A magnetic chip detector capable of attracting magneti cal ly permeahle
materials i s provided on the engine oil pump.
The chip detector provides a ground circuit for a warning in di cator in
the cockpit when sufficient magnetic material collects on the detector.
Magnetic material accumulation on the chip detector i s checked visually
by removinq and inspecting the chip detector magnetic pluq.
72-00-00
Page 16
Apr 15/81
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SER'/ICE MANUAL
Tf-17 31-2-lC
□ROM
AIRCRAFT
ANTI- ICE SW
E
I SOLENOID
t
"" =
COMPRESSOR
BLEED AIR (P3)
PART OF
SOLENOI
CONTROL
--------'------'
I
l
~NTHCE
I
VALVE
SPRING
CHAMBER A
COMPRESSOR
BLEED Al R (P3)
FROM
COMBUSTION
CHAMBER
POPPET
CHAMBER B
I
L_ _ _
-- -
-
-PL_E_N -UM-- -
ANTI-ICING AIR
I
J
ANTI-ICE
PRESS SW
__.. TO AIRCRAFT
ANTI-ICE IND
S-48A- 106R1
(Pre SB 72-3085) Anti-Icing System Schematic
Figure 5
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SERVI r.E MPtJUAL
TFE731-/ -1C
12.
C.
Nl and N2 Trans ducers
Two monopol e pickups are provided on the enqine for speed sensinq of
the high and low pressure spools. Each pickup is a dual unit and terminates in a separate connector. One element of each pickup is used by
the fu el control system for speed sianal inputs to the electronic
computer. The remaining element in each pi ckup is for cockpit instrumentation of the s peed of the low pressure (Nl ) and hiqh pressure (N2)
spools .
D.
(Pre SB 73-3028) Anti-I ce Pressure Switch
The anti-ice pressure switch provides a closed circuit for operation of
a signal to the aircraft whenever the anti-ic ino system is operatino.
13.
Oil System
The engine oil supply is contained in the oil tank. Oil is drawn from the
oil tank by the pressure pump element of the lube and scavenge oil pump,
and suppl ied to filtering and temperature controlling components before
routing for lubrication. A filter is provided to remove imourities from
the oil. Engine protection against filter clogging is provided by an oil
filter bypass indicator valve (delta P indicator and bypass valve) located
adjacent to the oil filter. The valve opens when the press ure drop across
the filter is excessive to bypass l ubricating oil around the filter . An
integral delta pressure indicator of the valve visually fl ags a clooqed
filter condition before bypassing occurs . A thermal lockout device on the
delta P indicator prevents actuation under cold oil conditions although the
bypass valve will bypass oil under these conditions. An oJl temperature
regulator (fuel/oil cooler) and three finned surface oil (air/oil) coolers
provide temperature control of both fuel and oil . The fuel /oi l cooler
transfers heat from the lubricating oil to fuel circulated through t he
component. The finned air/oil coolers transfer heat from the lubricating
oil to bypass air.
Oil flow through the fu el/oil cooler and the finned air/oi l coolers is
thermostatical ly controlled to provide optimum operating temperatures. Excess oil press ure with co ld oil is prevented by bypass valves within the
fuel/oil cooler and a temperature control valve installed with the air/oil
coo lers . (See figure 6.)
Pressurized oi l is supplied by a pressure element of the lube and scavenoe
oil pump to the accessory drive and transfer gearbox assemblies, the planet
qear asserrbly and high and low pressure shaft (number 3, 4, 5 and 6) bearings for lubrication. A four- element scavenge pump section of the oil pump
returns the oil to the oil tank . Vent lines interconnect oil sumps to the
oi l tank and a breather press urizing valve. The breather pressurizing
valve provides an ambient vent for the oil system at low altitudes, and at
high altit udes increases the internal engine vent and tank pressure to ensure proper oi l pump operation.
72-00-00
Paqe 18
Apr iS/81
A l Research
Photnh.
SERVICE MANUAL
TFE731 -2-1C
I
BREATHER Pl!ESSURIZING VAL VE
I
,r-HI-SYPHON OUF ICE
OIL lANK
I
NO . • ANOS BEARINGS
PLANET GEARASSY
(NO. I. 2. ANO
TRANSFER GEARBOX ASSY
3 BEARINGSI
ACCESSORY DRIVE GEAUOX ASSY
LUU ANO SCAVENGE
OIL PUMP"
Oil PUMP INLEI
LEGEND
- - - - INLET OIL
I f I I
COMMON SCAVENGE
♦
HIGH PRESSURE Oil
no□□n□□u SCAVENGE Oil
Q Q O ¢ Q VENT llNE
o o :. 6
AP INDICATOR-
b
.:.
OIL PllESSUtf SENSE UNE
A
CUSTOMER CONNECTION
.>•
PIESSUlE DWP
Oil !£MP REGULATOR
, . , -(FUEL / OIL COOLEll
&YP,.SS VALVE_)..-,'li"li,;;;f'..
FUH HUTER
~
A O IL PlESSUlE SENIING PORT
Oi l System Schematic
Figure 6
72-00-00
Paqe 19/20
Apr 15/81
SERVICE MANUAL
TFE731-2-1C
13.
Oi l System (Cont)
A fue l heater provides oil-to-oil heat exchanging to pr event ice formation
in the fuel system from cl ogging the fu el filt er and other components .
Fuel flow t hrough the fuel heater i s t hermost atically controlled by t he
ant i -i cing valve of the fue l pump . An oil press ure bypass va lve prevents
excessive pressure loss with cold oi l.
14 .
Components and Accessor i es
Engine components and accessories are mounted on the fa n i nlet hous i ng , exhaust nozzle , ·fan duct assembly, accessory drive and t ransf er gearboxes,
and combustion chamber plenum as shown in Figure 7.
15.
Directional References
Directional references to fr ont and rear, right and l eft, top and bottom,
and clockwise and counterclockwise are made facing the t urbine di schar ge
duct with the engine in a horizontal position and the accessory dr ive gearbox downward.
16.
Compressor Core
The internal section of the engine encompassing the low pressure and high
pressure compressors consititues the compressor core of the engine.
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Apr 15/81
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Phoenix
SERVICE MANUAL
TFE731-2-1C
OIL FILLER TUBE
LOW PRESSURE BLEED PORT COYER
IGNITION UNIT
FUEL HEATER AND INTEGRAL
BYPASS VAL YE
FAN ROTOR ASSY
FAN SPINNER
-
...~...-~"'
ACCESSORY DRIVE G E A R B O X ~ ~
~
TRANSFER SHAFT COVER TUBE/ /
FUEL PUMP AND
INTEGRAL FUEL
FILTER BYPASS
INDICATOR VALVE
TRANSFER GEARBOX AND
N2 TRANSDUCER
REAR TURSI NE
~[lJ.,..."--•---sEARING OIL
LINES
COMBUSTION CHAMBER
PLENUM DRAIN VALVE
FLOW DIVIDER VAL YE OR
FLOW DIVIDER AND DRAIN VAL VE
F-48A-ll2R6
Engine Components and Accessories (Typical)
Figure 7 (Sheet J of 2)
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n: :~731-2-IC
ANTI-ICE VALVE
INLET PRESSURE AND
TEMPERATURE SENSOR
HIGH PRESSURE
BLEED PORT COVER
FAN DUCT ASSY
SOLENOID CONTROLLER
VALVE
AIR/ OI L COOLERS AND
INTEGRAL BYPASS VALVE
OIL TANK
FILLER ~p
REAR MOUNT--.;;,...----
,
TRANSITION DU
LIQUID LEVEL GAGE
~~
OW PRESSURE BLEED
PORT COVER
- - - - - - FUEL/OIL COOLER AND
INTEGRAL BYPASS VALV E
COMBUSTION CHAMBER PLENUM
REAR MOUNT
NOTE:
NOT SHOWN, ON AFT FACE OF ACCESSORY DRIVE GEARBOX·
OIL FILTER
.
O IL PUMP AND INTEGRAL PRESSURE REGULATOR
OIL FILTER BYPASS INDICATOR VALVE
F--48A-394
Engine Components and Accessories (Typical)
Figure 7 (Sheet 2)
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Paqe 23/24
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\ • -7
Phoenl•
SERVICE MANUAL
TFE7 31-2-1C
CHAPTER 72 - GENERAL - TROUBL ~ SHOOTING
TABLE OF CONTENTS
CHAPTER/
SECTION/
SUBJECT
SUBJECT
ENGINE
72-00-00
TROUBLE SHOOTING
Operational Trouble Shootinq
General
Troubl e Shootina Guide
Trouble Shootin~ Tips
Prepare for Traub le Shooting
Trouble Shootin~ Tables
Trouble Shooting Procedures
PAGE
10]
101
101
102
1()3
]05
117
TROURLE SHOOTING
72-CONTENTS
Apr 15/81
~-:m) AiResearch
t".::'~
Phoonl•
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TF-731-2-lC
1.
Operational Trouble Shooting
WARNING:
A.
AREAS IN PROXIMITY OF ENGINE INLET AND EXHAUST ARE
EXTREMELY HAZARDOUS TO PERSONNEL WHEN ENGINE IS
OPERATING. PERSONNEL SHALL CLEAR THESE AREAS DURING
ENGINE START AND OPERATION TO AVOID INJURY.
Genera 1
The following trouble shooting information is provided as an aid in
locating the most probable cause of a malfunction based on the symptoms
it produces. Though primarily intended for use by maintenance personnel, it may help a pilot or other operator of the engine to gi~e more
meaningful information to maintenance personnel, thereby r~ducing the
time requ ired by field maintenance in locating and correcting the
problem. Values given ar e as representative as possible. However, in
all cases, the Aircraft Flight Manual is to be used as a b~sis _for operating, adjusting and evaluating the performance of the engine installed
in the aircraft.
B.
Trouble Shooting Guide
The trouble shooting guide is based on the indica~ions_which t~e engine
displays to the operator, as well as procedures given in the Aircraft
Flight Manual for starting and operating the engine. The malfunctions
covered in this guide are arranged in the order in which they would appear if the operator followed a normal engine operating schedule. A
normal engine operating schedule includes starting, acceleration, operation at engine takeoff speed, deceleration, and shutdown. Proper operation is depicted by the OK condition path in Tables 101 throug~ 104. If
malfunctions do occur, the procedure numbers at the right in the Fault
Isolation Tables indicate the recommended trouble shooting procedure t o
follow. If malfunctions occur and the trouble shooting procedure is
within the scope of this publication (special tools or test equij'.lllent
not required) the procedure nunbers listed in the Trouble Shooting
Procedure columns in the Fault Isolation Tables indicates the recommended trouble shooting procedure to follow. If malfunctions occur and
the trouble shooting procedure is beyond the scope of this publ ication
(special tools or test equipment required) the procedure number listed
in the LMM Trouble Shooting Procedure columns in the Fault Isolation Tables indicates the recommended trouble shooting procedure to follow in
Light Maintenance Manual, Chapter/Section/Subject 72-00-00, GENERAL TROUBLE SHOOTING. If a trouble shooting procedure is only partially
within the scope of this publication the probable causes and remedies
are listed for the portion of the procedure, then reference is listed to
the Light Maintenance Manual for further trouble shooting. Trouble
Shooting Procedure Numbers listed in this publication for procedures are
the s ame Trouble Shooting Procedure Numbers listed in the Light Maintenance Manual for the corresponding procedures. Each trouble shooting
procedure lists the probable causes and remedies for that problem. After performing the specified remedy, repeat the step at which the
failure was encounterd and complete the test to check out the system.
72-00-00
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SERVI CE MANUAL
TF E731-2 -1 C
1.
B.
Trouble Shoot ing Guide (Cont)
There is not del iberate dup li cation of problems, si nce it is assumed
that the operator would have discovered such a problem during starting
and would ha ve initiated corrective ac tion before proceedi ng with the
checks. However, if a ma lfuncti on would not appear as a symptom until
the aircraft were in fli ght or l anding, etc , then the symptoms for this
malfunction appear in the appropr iate section. Therefore, when the user
of this guide fail s to find a set of symptoms under a later section of
the guide, he i s advised to s t art at the beginning of a routine check
run or flight and see whether he ha s failed to recognize some signi f i cant symptoms earlier. When no tolerances are included on test values
given within the trouble shooting procedures , values li sted are
approximate. All trouble shooting procedures are based on the assumption that applicable control s , electrical circuit breakers , and switches
are positioned properly.
Troubles due to defective customer instrumentation and installation are
not included in the table, except those directly invo lved with engine
operation . Where thi s is a poss ibility, reference is appropriately made
to the Aircraft Maintenance Manual.
C.
Trouble Shooting Tips
(1)
Indications shown in Tables 101 through 104 are provided by the
following aircraft indicators.
(a)
Engine battery de voltmeter (c ustomer-furni shed).
NOTE:
The electronic computer requi res 15 to 32
volts de for normal (automatic) mode of
operation. The aircraft manual mode lamp may
flicker with excessively low voltage suppli ed
to electronic computer, such as when starting
eng ine using aircraft batter ies.
On normal start, the voltage will drop and s lowly rise as rpm
increa ses . A minor drop could be caused by starter rotation
without engagement. Voltage will ri se sudden ly t o normal at
starter cut-out.
(b)
Interstage turbine temperature (ITT) indicator (customerfurnished).
(c)
Rpm indic ators (customer-furnished). Two indi cators provide
readings. Nl (low pressure spool speed) and N2 (high pressure
spool speed).
72-00-00
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SERVI CE MANUAL
TFE731 -2-1C
1.
C.
(1)
{d)
Fuel flow indicator (customer-furni s hed).
(e) Fuel press ure i ndi cator (customer-furnished).
craft l ow press ure fuel boost pump pre~s ure.
Monitors air-
(f)
Oil pressure indicator (customer-furnished).
gear assembly oil inlet pressure.
Indicates planet
{q)
Oil temperature indicator.
Oil temperature should rise to operating tefll)erature, which
will vary with ambient operatinq temperature (lower with lower
temperature).
(2)
D.
Starting time should not exceed 50 seconds.
Prepare for Trouble Shooting
(1)
Make exterior inspection on each engine.
(a)
Engine ai r inlet and area - CLEAR AND CLEAN.
(b}
Fan blades - GENERAL CONDITION.
(c)
Engine exhaust and area - CLEAR.
(d)
Rear turbine blades - GENERAL CONDITION .
(e)
Engine cowlinq - SECURE.
WARNING:
(f)
WHEN SERVICING OIL SYSTEM~ CAUTION SHOULD
BE EXERCISED TO AVOID CONTACT WITH HOT OIL
WHICH MAY OVERFLOW FROM THE TANK DUE TO
EXPANSION.
Engine fuel and oil drains - CLEAR.
WARNING:
INADVERTENT START COULD CAUSE INJURY TO
PERSONNEL.
(2) Check that circuit break ers and switches are positioned as
described in the Aircraft Mai ntenance Manual.
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SERVICE MANUAL
TFE73l-2-1C
NOTE:
1.
D.
Idle thru~t in the manual mode may be hiqher than
normal, but maximum thrust will be at least 80
percent of normal. On a cold day the flat rating
of the engine will be exceeded at full power lever
position. For large excesses in enqine thrust,
the P3 limiter mounted in the fuel control will
protect the ena ine ~v reducing fuel flow in a cyclic manner. The fuel f low will continue to cycle
until the power lever i s retarded.
(3) An electron i c computer caution liaht (manual mode lamp ) is located
on the cockpit instrument panel to indicate if the computer is
ooerating or if the control system is operating in the manual mode .
In the event of a transfer to the manual mode, the liqht will illuminate accompanied normally by a chanqe in enqine ooeratinq
conditions. The action to be taken by the ooerator is as follows.
( a)
Check that engine is operating within limits and reduce oower
as required to brina within limits.
(b)
(Pre SB 76-3007) Cycle computer OFF/ON switch; i ' light
remains ON no automatic overspeed protection is provided
regardless of switch position.
(c)
(Post SB 76-3007) Cycle computer OFF/ON switch; if light
remains ON, leave switch in ON oosition and position
NORMAL/MANUAL switch on the face of the electronic computer to
MANUAL to maintain automatic low (Nl) and hiqh (N2) pressure
spool overspeed protection.
(d)
With the computer in manual mode, the operation of the engine
is mechanically controlled by the operator. Care should be
taken not to exceed enaine limitations. Full enqine power mav
not be available in the manual mode.
·
CAUTION:
(e)
DO NOT DISCONNECT THE ELECTRONIC COMP UTER
UNTIL ELECTRICAL POWER HAS BEEN CUT OFF.
WHEN USING A SUBSTITUTE COMPUTER, THE ENGINE SHOULD BE OPERATED AS IF IT WERE IN
THE MANUAL MODE (i.e., WATCHING ITT, MAXIMUM FLAT RATING, ANO SPEED TO PREVENT EXCEEDING LIMITS) UNTIL COMPUTER HAS BEEN
ADJUSTED IN ACCORDANCE WITH 72-00-00 , GENERAL - ADJUSTMENT/TEST.
Si nce the computer or a. component of the control system may be
faulty, follow the procedures recommended in the troubl e
shooting guide to i so late the faulty component.
72-00-00
Paqe 104
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Al Research
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SERVICE MANUAL
TFE731-2-1C
Table 101
Enqine Startinq -O Thru Idle RPM
POWER
LEVER
SETTING
OK CONDITION PATH
TURN ON COMPUTER
~i
NORMAL
lNOTOK
INITIATE START OBSERVE OR LISTEN FOi! N2
SPEED INCREASE
0
MOVE TO
IDLE AT
ll)'li, N2
N1
% RPM
ITT
FUEL
FLOW
PPH
OIL
PRESS
PSIG
INCREASE
THRU
20
AM81ENT
TO ssr'C
(1575°F)
0
TO
250
0
TO
il!'C !U0°F)
TO 113°C
'6
(235"f)
-
-
ZERO
ZERO
ZERO
AMBIENT
ZERO
ZERO
ZERO
AMBIENT
ZERO
ZERO
ZERO
ZERO
--
3
-
ZERO
ZERO
AMBIENT
ZERO
RISING
NORMALLY
LOW
•
-
N2
ACCEL
RATE
TO'°""
WITH IN
30 SEC
-
IEMP
HiRU
APPROX
•n
NOIOK
NOT OK
K
t;,,
NO CRANKING • STARTER
ENERGIZES
ENGINE CRANKS WITH STARTER
NOIOK ENERGIZED • NO N2 RPM
INDICATION
lP.OUBlE
SHOOllNG
PPOCEDURE
%RPM
..~-~,.
,
ELEK COMP DOES NOT REMAIN
IN NORMAL MOOE
NO CRANKING· STARTER DOES
NOT ENERGIZE
Oil
' LMM
TROUBLE
SHOOTING
PROCEDURE
--
1 OR IA
2
-
AT 10% Ni MCVE POWER
LEVER TO OLE
I
IDLE
-
ABOVE
,.
lESS
THAN
10
AMBIENT
NORMAL
RISING
NORMALLY
LOW
5
NOT OK
ENGINE CRANKS ABOVE 1•%
N2 • ITT DOES NOT RISE NO
AUDIBLE IGNITION SNAP·
FUEL PRESSURE A~O FUEL FLOW
INDICATIONS NORMAL
-
NOT OK
ENGINE CRANKS ABOVE 14%
N2 • ITT DOES NOT RISE •
AUDIBLE IGNlllON SNAP •
NO OR LOW FUEL PRESSURE
AND FUEL FLOW INDICATIONS
IDLE
-
ABOVE
14
LESS
THAN
10
AMBIENT
BELOW
NORMAL
RISING
NORMALLY
LOW
6
-
NOT OK
ENGINE CRANKS ABOVE Tl%
N2 • ITT DOES NOT RISE AUDIBLE IGNITION SNAP NORMAL FUEL PRESSURE
INDICATION - NO OR LOW
FUEL FLOW INDICATION
IDLE
-
ABOVE
14
LESS
THAN
10
AMBIENT
8ELOW
NORMAL
RISING
NORMALLY
LOW
7
-
ENGINE CRANKS ABOVE I•%
Nr ITT DOES NOT RISE AUDIBLE IGNITION SNAPNORMAL FUEL PRESSURE
AND FUEL FLOW INDICATION
IDLE
-
ABOVE
14
LESS
THAN
10
AMBIENT
NORMAL
RISING
NORMALLY
LOW
- -
8
ENGINE LIGHTS Off AND
ACCELERATES BUT NO ITT
INDICATION
IDLE
NORMAL
NOT
RISING
NORMAL
RISING
N ORMALLY
LOW
9
NOT OK
-
NOT OK
LOW Oil PRESSURE
IDLE
NORMAL
RISING
ABOVE
100
NOT
RISING
RISING
10
-
RISING
A80VE
100 &
RISING
RISING
RISING
11
-
OK
...,
.,
NOT OK
OBSERVE THAT ENGINE
CONTINUES TO ACCEl.
TO IDLE. NOTE: STARTER
AND IGNITION CUT OUT
AT 50% N2
I
NOl OK
NO N INDICATION
1
I
IDLE
NORMAL
ABOVE
ABOVE
17 &
5&
NCREASING INCREASING
40
40
20
ZERO
• PROCEDURE REQUIRES SPECIAL TOOLS OR TEST EQUIPMENT, REFER TO LIGHT
MAINTENANCE MANUAL FOR TROUBLE SHOOTING AND REPAIR.
G-48"-659
72-00-00
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SERVICE MANUAL
TFE731-2-1C
Table 101. Engine Startinq -0 Thru Idle RPM (Cont)
POWER
LEVER
SETTING
OK CONDITION PATH
~
OK
~
..,
I
i:7-
ENGINE START \
SYSTEM IS
NORMAL
ITT
fUEL
fLOW
PPH
OIL PRESS
PSIG
OIL TEMP
TROUBLE
SHOOTING
PROCEDURE
• lMM
TROUBLE
SHOOTING
PltOCEOURE
BELOW
10
NORMAL
NO T
RISING
STEADY
RISING
12
---
BELOW
HIGH l.
RISING
HIGH
RISING
RISING
13
---
NORMAL
LOW
RISING
RISING
14
---
ABOVE
10
NORMAL
LOW
RISING
NORMALLY
RISIN G
NORMALLY
IS
---
ABOVE
10
HIGH
HIGH
RISING
NORMALLY
RISING
NORMALLY
---
16
INCREASING
RISING
NORMALLY
RISING
NORMALLY
17
---
N2
ACCEL
RATE
NOT OK
HUNG START - MANUAL
SHUTDOWN
IDLE
SLOW
NOT OK
HCT ST ART - MANUAL
SHUTDOWN
IDLE
NORMAL
NOT 9K
ENGINE LIGHTS-OFF BUT SHUTS
DOWN DURING ACCELEUTION
TO IDLE
IDLE
-
NC1 OK
ENGINE ACCELERATES SLOWLY
OR NOT Al ALL (NORMAL ITT)
IDLE
SLOW
NCTOK
ENGI NE ACCELERATES SLOWLY
OR NOT AT ALL (ITT OR FUEL
FLOW HIGH)
IDLE
SlOW
~NOT OK
ENGINE CONTINUES TO ACCEL
ABOVE IDLE WITH POWER LEVER
IN IDLE
IDLE
NORMAL
% RPM
BELOW
50
BELOW
50
N1
% RPM
,o
INCR NORM INCR NORM
THEN
THEN
DECREASE
DECREASE
ABOVE
50
ABOVE
so
INCREASING INCREASING
INCREAS'G
ABOVE
ABOVE
24
so
• PROCEDURE REQUIRES SPECIAL '!OOLS OR TEST EOUIPMENT, REFER TO LIGHT
MAINTENANa MANUAL fOR TROUBLE SHOOTING ANO REPAIR.
72-00- 00
Paqe 107/108
Apr 15/81
AIResoarch
Phoenl•
SERVICE MANUAL
TFE731 -2-1C
Table 102. Enqine Acceleration to Take-Off
N7
P0W£R
OK CONDITION PAlH
NI
lEIIU
SfTIINC
ACCEL.
RAH
NORMAL
[)
Ill
,tPM
fULL
fl0 "
PPH
OIL
P1t(SS.
PSIG
HO\Jeu
Stt0011,,r
~•0CfDll•l
!ROUBLE
S1'0011NG
PJOCEDURE
Jg
-
~ RPM
APP1t0X
S38'C
(IOOO'F) 10
8S7'C(IS7S'fl
MOVE 10
!AKE-Off
' LIN,
011
I!..,
60'C
11 , o•f 10
lt3•c
12l5'fl
?.00
3810
•6
HIGH
RISING
NORMALLY
ERRATIC
RISING
-.,QRMALLY
NC.N.ALLY
19
-
?0010
MCVE POWER LEVER TO
TAKE-CH 08S[ttVE ACCEL
~
NOi OK
111 HIGH !)\.«ING
ACCELERATION FROM IDLE
!AKEOff
NORMAL
OK
~ff
INCREASING INCRIASINC
ABOVE
ABOVE
IDLE
IDLE
ABOVE
NORMAL
~ISINC,
NCRW.LLY
RISING
ENGIN[ SURGES DU'INC
ACCELERATION
TAK[.
OFf
A!NORMAL
lRRATIC
ERRATIC
NOT OK
LOW lHRUSI
1 A<[.
OFF
-
MAX
lESS !HAN
NOR,...AL
anew OR ABOVE NORMAL
,-.QRM,4L
"0R.y,,-L
l'.:
-
NOT O K
LOW N1 ANO FUEL FLOW
INlllALLY, THEN REI URNING
TO NORMAL
TAK[,
Off
-
LOW THEN
NORMAL
NORMAL
OR A&OVE
NORMAL
LOW THEN
NORMAL
NORMAL
~CPNJo~
-
21
NOT OK
ENGlr-iE OV[RSPEEDS
TAKEerr
A(CEL·
[RATING
A80VE
A80VE
NCRMAL
A80V[
r-iORMAL
NORMAL
s;Q~MAL
MAX
-
22
NOT OK
NO N7 INOIO,TION
TAKE•
OH
-
ZERO
NORMAL
NORMAL
NORMAL
NORMAL
NOl..,_. L
2?
NOT OK
NO N1 INDICATION
TAKE,
OFF
-
r-iQRM,4L
ZERO
NORMAL
NORMAL
NORMAL
"0'MAL
?•
r-iOT OK
NO ITT INDICATION
lAKf.
Off
-
NO™Al
NCRMAL
-
NORMAL
NORMAL
NQO,t,,i.,A.,.
Zj
NOi OK
NI. N2, ANO In ERP.Al IC
TAKl•
Off
-
ERRATIC
ERRATIC
ERRATI C
ERRAIIC
NORM"L
NOIM,<L
-
26
NOi OK
Ill HIGH
TAK[.
Off
LOW OR
lOWCR
MAX
HIGH
NORW"L
NORMAL
'-CRM"l
MAX
r
-
MAX
M._X
NORMAL
NOIMAL
NORMAL
NOUMI
-
28
MAX
MAX
NORMAL
NORMAL
NORMAL
._O...,._L
-
29
N010K
ERRATIC
ENGINE OPER..TING Al 1AKE
CFF 100-. N2, 90'- N1
~
~
~
~
~
~
~
~
~
~
~
~~7
NOi OK
OIL CONSUWPIION
EXCESSIVE
TAKE·
OH
-
NOIOIC
(PRE 5872-3085) OIL FUMES IN
8lEED AIR OR DISCHARGING
FROM 8RlHR. PRESS. VALVE
lAKfOFf
-
MAX
A&OVE
MAX
OR
-
• PROCEDURE REQUIRES SPECIAL TOOLS OR TEST EQUIPMENT, REFER TO LIGHT MIII NIENANCE
MANUAL fOR TROU8LE SHOOTING ANO REPAIR .
72-00-00
Paqe JOQ/110
Apr 15/Rl
AlResearch
P~nla
SERVICE MANUAL
TFE-31-2-lC
Table 102. Engine Acceleration to Take-Off (Cont)
POWER
lEVER
SffilNG
OK CONDITION PATH
N2
NJ
ACCEL.
RATE
~
~~
rJ"
~~
~~7
'lol!PM
"lMM
ITT
FUEL
FLOW
Pf'H
OIL
PRISS.
PSIG
OtL
TEMP
TROU!LI
S>'OOIINC,
?IIOCEOUIE
TROUBLE
SHOOTING
PROCEDU'tf
%RPM
NOT OK
(POST S872-3085) O il FUMES IN
BLEED AIR OR DISCHARGING
FROM BRTHR, PRESS. VALVE
TAKEOff
-
MAX
MAX
NO>.MAL
NORMAL
NORMAL
NOPMAL
-
29A
NOT OK
LOW O IL PRESS Al ALIITU0I
(NORMAL ON GN0I
FLIGHT
ROM!
-
FLIGHT
ROMT
FLIGHT
ROM!
NORMAL
NORMAL
LOW
NORMAL
-
30
NOT OK
HIGH Oil IEMP
TAKIOFF
MAX
MAX
NORMAL
NOIV-«l
LOW OR
NORMAL
HIGH
JI
-
NOT O K
HIGH O IL PRESS
TAKEOff
MAX
MAX
NORMAL
NORMAL
HIGH
NORMAL
32
-
NOT OK
(PRE 5872-3085) NO ENGINE
ANTI-ICE INDICATION
TAKEOFF
-
MAX
MAX
NORMAL
NORMAL
NORMAL
NORMAL
33
-
ENGINE NORMAL Al TAKEOFF
'PROCfllU"E REQUIRES SPECIAL TOOLS OR TEST fO UIPMENT, REFER TO LIGHT MAINTENANCE
MANUAL FOR TROUBLE SHOOTING AN O RIPAIR.
G _.BA-656
72-00-00
Paqe 111/112
Apr 15/81
AIResearch
Phoenb.
SERVICE MANUAL
TFE731- 2-1C
Table 103. Enqine Deceleration to Idle
POWER
LEVER
SETTING
OK CONDITION PATH
NORMAL
MOVE POWER LEVER TO IDLE
~
•
NOT OK
c)
ENGi NE FLAMES OUT WHEN
POWER LEVER RETARDED
NOT OK
ENGi NE DECELERATION SLOW
NOTOK
ENGINE SURGES DURING
DECELERATION
N2
ACCEL.
RATE
N1
% RPM
RETARDED
IDLE
OK
IDLE
FAST
DECEL
FUEL
FLOW
PPH
Oil
PRESS.
PSIG
Oil
TEMP.
APPROX
SJBOC
(10()()0 F) TO
85)0 C(1S75° F)
20010
2,00
38 10 '6
11:P C
(14()0FlJO
113" C
(2350 F)
DECREASING
NORMAL
OR LOW
NORMAL
NORMAL
--
3,4
NORMAL
NORMAL
35
- --
NORMAL
NORMAL
36
---
% RPM
Al
TAKEOFF
DECREASING DECREASING
•f.MM
m
SLOW
ABOVE
ABOVE
ABOVE
ABOVE
DECH
NORMAL
NORMAL
NORMAL
NORMAL
ABNORMAl
DECEL
ERRATIC
ERRATIC
ERRATIC
ERRATIC
TROUBLE
SHOOTING
PROCEDURE
TROUBLE
SHOOTING
PROCEDURE
ENGINE NORMAL AT IDLE
• PROCEDURE REQUIRES SPECIAL TOOLS OR TEST EQUIPMENT , REFER TO LIGHT
MAINTENANCE MANUAL FOR TROUSLE SHOOTING AND REPAIR.
72-00-00
Page 113/11 4
Apr 15/81
Al Research
Phoonh
SERVI CE MANUAL
TFE731-2-IC
Tab le 104. Engine Cut-off
POWER
LfVEP
SETTING
OK CONDITION PATH
NORMAL [ = )
CUT-Off
N2
N1
o.-:. RPM
DECEL
RATE
% RPM
MORE
THAN
30 SEC
lO
0
DECREASE
251 0 0
S8
ITT
APPROX
538' C
(IOOO'f) TO
20,•c
FUEL
FLOW
PPH
OIL
PRESS
PSIC
250
TO
0
46
TO
0
60' C
ll40'f1To
IIJ• C
1235'1
NORMAL
NORMAL
---
(AOO•F)
OIL
TROU8U
SHOOIING
• LMM
l'l'OCEDCftf
TROUBLE
SHOOTINC
PltOCEME
NORw.:.L
::
- -
---
- --
1£,..p
MOVE POWER LEVE~
TO CUT-Cff
OK
NOT OK
ENCINE DOES NOT SHUTDOWN
CUT-GFF
NO
DECEL
58
25
NOT OK
ENCINE ROLLDOWN AFlER
SHUT DOWN IS ABNORMAL
CUT-OFF
--
ZERO
ZERO
~
A
'<.;,'j
NORMAL
38
~
ENCINE IS
NORMAL ON
SHUTDOWN
• PROCEDURE REQUIRES SPECIAL TOOLS OR TEST EQUIPMENT, REFER TO LIGHT
MAINTENANCE MANUAL FOR TROUBLE SHOOTING AN D REPAIR.
72-00-00
Paqe ll!>/116
Apr 15/81
~ AiResearch
~
Phoonlx
SERVICE MANUAL
TFE731-2-1C
PROCEDURE ~
PROBLEM:
No cranki ng - starter does not enerqize.
PROBABLE
CAUSE:
1.
Aircraft batter_y may be weak or dead.
2.
Starter control circui t may be faulty .
3.
Starter may be faulty.
1.
Check battery in accordance with Aircraft Maintenance
Manual.
2.
Check starter control circuit in accordance with Aircraft
Maintenance Manual.
3.
Check starter in accordance with Aircraft Maintenance Manual.
REMEDY:
PROCEDURE 4
PROBLEM:
Engine cranks with starter enerqized - No N2 RPM indication.
PROBABLE
CAUSE:
1. Aircraft N2 indicatinq system may be faulty.
REMEDY:
1.
Check aircraft N2 indicating system in accordance with
Aircraft Maintenance Manual.
2.
Refer to Liqht Maintenance Manual , Chapter/Section/ Subject
72-00-00, GENERAL - TROUBLE SHOOTING for additional
troub le shooti nq .
72-00-00
Paoe 117
Apr 15/ 81
~ AiResearch
~
Phoenix
SERVICE MANUAL
TFE731-?-1C
PROCEDURE 5
PROBLEM:
PROBABLE
CAUSE:
REMEDY :
Enqine cranks above 14 percent N2 - ITT does not ri se - No audibie ignition snap - Fuel pressure and f uel flow inrl ic at i ons nor mal .
1.
Aircraft ignition circuit may be faulty .
2.
Engine iqnition system f aulty.
1.
Check aircraft igniti on sys tem in accordance with Aircraft
Maintenance Manual.
2.
Perform Ignition System Check.
Refer to INSPECTION/CHECK .
PROCEDURE 6
PROBLEM:
PROBABLE
CAUSE:
REMEDY:
Enqine cranks above 14 percent N2 - ITT does not rise - Audible
ignition snap - No or low fuel press ure and fuel flow indications.
1.
Aircraft fuel boost pump or fuel boost pump electrical
circuit may be faulty.
2.
Aircraft fu el shutoff valve or fuel shutoff val ve control
may be f aulty.
1.
Check fuel boost pump and fuel boost pump electrical
circuit i n accordance with Aircraft Maintenance Manual .
2.
Check fue l shutoff valve and fuel shutoff valve cont r ol in accordance wi th Aircraft Maintenance Manual.
72-00-00
Paqe 11B
Apr · 15/81
~ AiResearch
~
Pho enix
SERVICE MANUAL
TFE731-2-1C
PROCEDURE 7
PROBLEM:
Engine crank s above 14 percent N2 - ITT does not rise - Audible
ignition snap - Normal fuel press ure indication - No or low fuel
flow indication.
PROBABLE
CAUSE :
J.
(Pre SB 76-3007) Aircraft fuel enri ch (SPR) circuit may
be faulty.
REMEDY:
l.
Check fuel flow in manual mode. If fuel flow is normal,
check aircraft fuel enri ch circuit i n accordance with Aircraft
Maintenance Manual .
2.
Refer to Light Maintenance Manual, Chapter/Section/Subject
72-00- 00, GENERAL - TROUBLE SHOOTING for additional trouble
shootinq.
72-00-00
Paqe 119
Aor 15/81
Al Research
Phoonlx
SERVICE MANUAL
TFE731-2-1C
PR0CE0UR E 9
PROBLEM:
Engine liohts off and accelerates but no ITT indication.
PROBABLE
CAUSE:
1.
ITT indicator may be defective.
2.
Aircraft circ uit between ITT indicator and ITT thermocouple
harness may be fau lty.
3.
ITT thermocouple harness electrical connector contaminated.
1.
Check ITT indicator in accordance with Aircraft Maintenance
Manua1.
2.
Check aircraft electrical circuit between ITT indicator and ITT
thermocoupl e harness for contaminated connectors and other
faults in accordance with Aircraft Flight Manual.
3.
Check ITT thermocouple harness electrical connector for
contamination .
4.
Refer to Light Maintenance Manual, Chaoter/Section/Subject
72-00-00, GENERAL - TROUBLE SHOOTING for arlditional trouble
sh ooting.
REMEDY:
72-00-00
Paqe J20
Apr 15/81
~ .:::.:; AiResearch
..._
Phoonl•
SERVI CE MANUAL
TF[ 731-2-1C
PROCEDUR E 10
PROBLEM:
Low oil pressure.
PROBABLE
CAUSE:
1.
Low oil supply.
2.
High oil temperature .
3.
Clogged oil filter.
4.
Oil system leak.
5. Aircraft oil press ure indicatina system faulty .
6.
REMEDY:
Oi l pump pressure reoulator setting incorrect.
1. Check oil l evel and if low, reolenish with approved
enqine oil. Refer to SERVI CING.
2.
High oi l temperature could cause low oil pressure.
Refer to PROCEDURE 31.
3.
Check for extended red pin on oil filter bypass valve on
accessory drive gearbox (fioure ~02 ) If extended, insoect
oil filter and chip detector. Refer to INSPECTION/CHECK.
4.
Tighten, reoair, or replace leak i nq component.
5.
Check aircraft oi l pressure indicatinq system i n accordance with Aircraft Maintenance Manua l .
6.
Adjust oil pump pressure regu lator. Refer to ADJUSTMENT/TEST.
...
72-00-00
Paqe 121
Apr 15/81
Ai Research
Phoonlx
SERV ICE M/\NUAL
TFE731-?-1C
PROCEDURE 11
PROBLEM:
No Nl indication.
PROBABLE
CAUSE : 1. Aircraft Nl indication system may be faulty.
REMEDY:
1.
Check aircraft Nl indicating system in accordance with
Aircraft Maintenance Manual .
2.
Refer to Light Maintenance Man ual, Chapter/Section/Subject
72-00-00, GENERAL - TROUBLE SHOOTING for additional
trouble shooting.
PROCEDURE 12
PROBLEM:
Hung start (No or slow acceleration during start) - Manual
shutdown.
PROBABLE
CAUSE:
1. Weak battery.
REMEDY:
1.
Check battery in accordance with Aircraft Maintenance
Manual.
2.
Refer to Li ght Maintenance Manual, Chapter/Section/Subject
72-00-00, GENERAL - TROUBLE SHOOTING for additional
trouble shooting.
72-00-00
Page 122
Apr 15/81
C.:.: ~ AIAesearch
e_..:.•'} P hoonl•
SERVICE MANU/\L
TFE731-2-1C
PROCEDURE 13
PROBLEM :
PROBABLE
CAUSE :
REMEDY:
Hot st ar t - Obser ve overtemperature limits in Aircraft Flight
Manual - (Nl spool accelerates normally) - If exceeded,
shutdown eng i ne.
1.
Electron ic computer in manual mode.
2.
Aircraft ai r condi ti oning bl eed air valve not functioning
properly.
3.
Combustion chamber pl enum dr ai n valve(s) plugged.
4.
Aircraft ITT i ndi cati ng system may be faulty.
5.
Fuel control torque mot or electrical connector loose.
1.
Check manual mode indi cator l ig ht - If on, refer to Light
Maintenance Manual, Chapter/Sec t ion/Subject 72 -00-00, GENERAL INSPECTION/CHECK, PROCEDUR E 1.
2.
Check aircraft air conditioning bl eed ai r valve for proper
operation in accordance with Ai r craft Maintenance Manual.
3.
Remove obstruction from combustion chamber plenum drain
valve. (See figure 7.)
4.
Check aircraft ITT indi c ating sys t em in accordance with
Aircraft Maintenance Manual.
5.
Tighten torque motor el ec tri cal connector on fuel control.
6.
Refer to Light Mai nt enance Manual, Chapter/Section/Subject
72-00-00, GENERAL - TROUBLE SHOOTING for additional
trouble shooting.
72 -00-00
Page 123
Apr 15/81
SERVI CE MANUAL
TFE731-2-1C
PROCEDURE 14
PROB LEM :
Engi ne lights off but shuts down during acceleration to idle.
PROBABLE
CAUSE:
1.
Air in fuel or low fuel suppl y.
2.
Incorrect electroni c computer fu el setting.
1.
Rep l enish fuel su ppl y or bleed fuel system in
accordance with Aircraft Maintenance Manual.
2.
Perform Fuel Type Adjustment Procedure.
REMEDY:
Refer to ADJUSTMENT/TEST.
3. Refer to Light Maintenance Manual, Chapter/Section/Subject
72-00-00, GENERAL - TROUBLE SHOOTING for additional
trouble shooting.
PROCEDURE 15
PROBLEM:
Engine accelerates slowly or not at all .
PROBABLE
CAUSE:
1.
REMEDY:
(Normal ITT) .
Incorrect electronic computer fuel setting.
1. Perform Fuel Type Adjustment Procedure. Refer t o
ADJUSTMENT/TEST.
2.
Refer to Light Maintenance Manual, Chapter/Section/Subject
72-00-00, GENERAL - TROUBLE SHOOTING for additional
trouble shooting.
72-00-00
Page 124
Apr 15/81
c::::..-. _~:,, AiResearch
~
Phoenix
SERVICE MANUAL
TF E731-2-1C
PROCEDURE J. 7
PROBLEM:
Enq ine continues to acce l erate above idle with power lever
in idle pos ition.
PROBABLE
CAUSE:
1.
Fuel control torque motor electrical connector loose.
2.
Incorrect power lever rigging.
1.
Switch to manual mode and recheck. If enqine does not
continue to accelerate above idle with power lever in idle
position, tighten torque motor electrical connector on fuel
contro 1.
2.
If engine continues to accelerate above idle with power lever
in idle position and operating in manual mode, adjust power
lever rigging in accordance with Aircraft Maintenance Manual.
REMEDY:
3. Refer to Light Maintenance Manual, Chapter/Section/Subject
72-00-00, GENERAL - TROUBLE SHOOTING for additional
trouble shootinq.
72-00-00
Paqe 125
Apr 15/81
Al Research
Phoonb
SERVICE M/\NUAL
TFE73l -?-1C
PROCEDURE 18
PROBLEM:
ITT hi gh during accel eration from idle.
PROBABLE
CAUSE:
1. Aircraft system utilizing engine bleed air may be leakino.
REMEDY:
1.
Check aircraft systems utilizinq enqine bleed air for leaks
in accordance with Aircraft Ma intenance Manual.
2.
Refer to Lioht Maintenance Manual, Chapter/Section/Subject
72-00-00, GENERAL - TROUBLE SHOOTING for additional
trouble shootinq.
PROCEDURE 19
PROBLEM:
Enoine surges during acceleration.
PROBABLE
CAUSE:
J.
Incorrect electronic computer fu el sett ing.
REMEDY:
1.
Switch to manual mode and recheck. If enqine accelerates
normally, perform Fuel Type Adjustment Procedure. Refer to
ADJUSTMENT/TEST.
2.
Refer to Light Maintenance Manual, Chapter/Section/Subject
72-00-00, GENERAL - TROUBLE SHOOTING for additional
trouble shootinq.
72-00-00
Page 126
Apr 15/81
Al R esearch
Phoo nl•
SERVI CE MANUAL
TF E731-2-lC
PROCEDURE 20
PROBLEM:
Low thru st.
PROBABLE
CAUSE: 1.
REMEDY:
Check ITT ind ication and manu al mode i ndicator l ioht.
If ITT indication is bel ow normal and manual mode i ndicator liqht i s off, el ectronic comouter Flat Rat/Max Speed
setting may be incorrect.
2.
Incorrect power lever ri ~qinq.
3.
If ITT indication is above normal , aircraft system
utilizing engine bl eed air may be leaki nq.
1.
Perform Maximum Low Pressure Rotor Speed (Nl) Adjustment
Procedure. Refer to ADJUSTMENT/TEST.
2.
Check power lever riqgin~ in accordance 'Wit h
Aircraft Maintenance Manual.
3.
Check aircraft systems utilizing engi ne bl eed
air for leaks in accordance with Ai rcraft
Maintenance Manual.
4.
Refer to Light Maintenance Manual, Chapter/Section/Subject
72-00-00, GENERAL - TROUBLE SHOOTING for add i tional
trouble shootinq.
72-00-00
Paqe 127
Aor 15/81
SERVICE MANUAL
TFE73J.-2-1C
PROCEDURE 23
PROBLEM:
No N2 indi cation .
PROBABLE
CAUSE:
1.
Aircraft N2 i ndicati ng syst em may be faulty.
REMEDY :
1.
Check ai r craft N2 ind icat i n~ sys tem i n accordance
with Ai rcraft Maint enance Manual .
2.
Ref er to Li ght Mai ntenance Manual , Chaoter /Section/Subject
72-00-00, GENERAL - TROUBLE SHOOTING for addit i onal
t roubl e s hooting.
PROCEDURE 24
PROBLEM:
No Nl indication.
PROBABLE
CAUSE:
1.
Ai rcraft Nl indicating system may be faulty.
REMEDY :
1.
Check aircraft Nl indicating system in accor dance
with Aircraft Maintenance Manual.
2.
Refer to Light Maintenance Manual, Chapter/Section/Subject
72-00-00 , GENERAL - TROUBLE SHOOTING for add it i onal
troubl e s hooting.
72-00-00
PaQe 128
Apr 15/ 81
AiResoarch
SERVICE MANUAL
TFE731-2-1C
PROCEDURE 25
PROBLEM:
No ITT indication.
PROBABLE
CAUSE: 1. Aircraft ITT indicatinq system may be faulty.
REMEDY:
2.
ITT thermocouple harness electrical connector contaminated.
J.
Check aircraft ITT indicating system in accordance
with Aircraft Maintenance Manual.
2.
Check ITT thermocouple harness electrical connectors
for contamination.
3.
Refer to Light Maintenance Manual, Chaoter/Section/Subject
72-00-00, GENERAL - TROUBLE SHOOTING for additional
trouble shooting.
72-00-00
Paoe J29
Apr 15/81
...::;.ri\ Al Re search
, .._ /
f'hoonl~
SERVI CE MANUAL
TFE7]1-?- 1C
PROCEDURE 27
PROBLEM:
ITT hiah.
PROBABLE
CAUSE:
1.
If Nl speed is normal, aircraft ITT indicatino syst em
may be faulty.
2.
If Nl speed is below normal, aircraft system utilizinq
engine bleed air may be leakina.
1.
Check ITT indicating system in accordance with aircraft
Maintenance Manual.
2.
Check aircraft systems utilizin9 engine bleed air for leaks
in accordance with Aircraft Maintenance Manual.
3.
Refer to Light Maintenance Manual, Chaoter/Section/Subject
72 -00-00, GENERAL - TROUBLE SHOOTING for addit i onal
trouble shooting.
REMEDY:
Check Nl speerl indi cation.
72-00- 00
Paqe 130
Apr 15/81
AIAesearch
Phoonl x
SERVICE MANUAL
TFE731-2-lC
PROCEDURE 31
PROBLEM:
Hiqh oil temperature.
PROBABLE
CAUSE:
REMEDY:
1.
Low oil suoply.
2.
Aircraft oi l temperature indicatinq system
may be faulty.
3.
Low oil pressure.
1.
Check oil level and if low, reolenish with approved
enq ine oil. Refer to SERVICING.
2.
Check aircraft oil temperature indicatinq ~vstem in
accordance with Aircraft Maintenance Manual.
3.
Check oil pressure, i f low, perform PROCEDURE 10.
4.
Refer to Lioht Maintenance Manual, Chaoter/Section/Subject
72-00-00, GENERAL - TROUBLE SHOOTING for additional
troubl e shooting.
72-00-00
Paqe 131
Apr 15/81
Al Research
SERVICE MANUAL
TFE73l-2-1C
PROCEDURE 32
PROBLEM:
Hiqh oil pressure.
PROBABLE
CAUSE:
1. Aircraft oil pressure indi cating system may be faulty .
REMEDY:
2.
Oil pump press ure requlator settinq incorrect.
1.
Check oil pressure indicating system in
accordance with Aircraft Maintenance Manual .
2.
Adjust oil pump pressure regulator.
ADJUSTMENT/TEST.
3.
Refer to Light Maintenance Manual, Chapter/Section/Subject
72-00-00, GENERAL - TROUBLE SHOOTING for additional
trouble shoot i ng.
Refer to
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PROCEDURE 33
PROBLEM:
(Pre SB 72-3085) No enqi ne anti-i ce indication.
PROBABLE
CAUSE : 1.
REMEDY:
Aircraft ant i-ice power circuit ma.v be faulty.
1.
Check aircraft anti-ice power circuit in accordance with
Aircraft Maintenance Manual.
2.
Refer to Liqht Maintenance Manual, Chapter/Section/Subj ect
72-00-00, GENERAL - TROUBLE SHOOTING for additional
trouble shootino.
PROCEDURE 35
PROBLEM:
Engine deceleration slow.
PROBABLE
CAUSE: 1.
REMEDY:
Incorrect electronic computer fuel settinq.
2.
Aircraft pressure line between inlet pressure and temperature
sensor and electronic computer may be leakin~.
1.
Perform Fuel Type Adjustment Procedure.
ADJUSTMENT/TEST.
2.
Check aircraft pressure line between inlet pressure anrl
temoerature sensor and electronic computer for leak in
accordance with Aircraft Maintenance Manual.
1.
Refer to Li~ht Maintenance Manual, Chaoter/Section/Subject
72-00-00, GENERAL - TROUBLE SHOOTING for additional
trouble ~hooting.
Refer to
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PROCEDURE 36
PROBLEM:
Enqine suroe durinq deceleration.
PROBABLE
CAUSE: 1.
REMEDY:
Incorrect el ectronic computer fuel settinq.
1.
Perform Fuel Tyoe Adjustment Procedure.
to ADJUSTMENT/TEST.
Refer
2.
Refer to Liqht Maintenance Manual, Chapter/Section/Subject
72-00- 00, GENERAL - TROUBLE SHOOTING for additi onal
trouble shootinq.
PROCEDURE 37
PROBLEM:
Engine does not shut down.
PROBABLE
CAUSE:
1.
Aircraft oower l ever linkaqe on fuel control may be loose.
2.
Incorrect aircraft power lever riqqi nq.
1.
Check for loose aircraft power lever linkaqe on fuel
control in accordance with Ai rcraft Maintenance Manual.
2.
Check power lever rigging in accordance with Aircraft
Maintenance Manual.
3.
Refer to Light Maintenance Manual, Chapter/Sect ion/Subject
72-00-00, GENERAL - TROUBLE SHOOTING for additional
troubl e shooti ng.
REMEDY:
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CHAPTER 72 - SERVI CI NG
TABLE OF CONTENTS
SUBJECT
CHAPTER/
SECTION/
SUBJECT
ENGINE
72-00-00
SERVICING
General
Oil System Ser vicing Reau i rements
Requirements for Checki ng Oi l Level
Reauirements for Performi ng Spectroqraohi c
Oil Analysis (SOAP)
.
Requirements for Changi nq Oil
Oil Changi ng
. .
Oil System Draininq
Oil Tank Draining
Accessory Drive Gearbox Drainino
Oil System Fillinq ( Initial Engine Installation)
Fi 11 Oil Tank
Motor Engine
Run Engine
Recheck Oil Level
Oil System Fillinq (System Drained Subsequent
to Engine Installation)
Check Drain Plugs and Oil Fil ter
Fi 11 Oil System
Run Engine
Recheck Oi l Level
Fuel Filter Requirements
Accessory Drive Gearbox Assembly So l i ne Lubri cat ion
PAGE
301
302
302
302
302
304
304
304
304
304
304
306
306
306
306
306
107
307
307
307
308
SERVI CING
72 -CONTENTS
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bL.1~ERAL - SERVICING
1.
General
This section cont ai ns engine serv1c1no reouirements and procedures. - ~:·e
301 lists appr oved enaine lubricatino oils. Tabl e 302 lists mater'?'s ?'~
cornoounds for serv icinq other than oil system servicinq.
Table 301 .
Approved Enoi ne Oils
Oil Brand and Trade Name
Mobil Jet Qi 1 II (Tyoe II)
Exxon/Essa 2380 Turbo Oil (Type II)
Castrol 5000 (Type II)
NOTE:
Oil is to be changed at each 500 hours of operation . The
listed brands of approved oil may be mixed. Other types of oil
are not approved . Refer to Aircraft Fli oht Manual for specific
lubricant to be used.
Table 302.
Material or Compound
NOTE :
Mater ials and Compounds
Manufacturer
Equiva lent subst it utes ma.v be used for listed items.
Grease (Aeroshe ll 17)
(MIL -G- 2)164)
Shell Oil Co, 50 WSOth St, New York,
NY 10020
Grease (Aeros hel l 22 )
(M IL-G-8)322 )
Shell Oil Co, 50 W50th St, New Yor~,
NY 10020
Grease (M IL-G-21164 )
Coounercially available
Grease (Mobi l Grease No.
28) (MIL-G-81322)
Mobil Chemical Co, Chemical Coatinas
Div, 150 E 42nd St, New York, NY
]0017
Grease (Mobil Grease No . 29
(Molybdenum-D i sulphide)
(MIL-G-81827)
Divi 150 E 42nd St, New York, NY
Mobil Chemical Co, Chemical Coatinos
JOO 7
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2.
Oil System Servicing Requirements
A.
B.
Requirement s for Checking Oil Level
(1)
Each post-flight inspection.
(2)
As procedural step of any engine maintenance .
Requirements for Performing Spectrographic Oil Analysis (SOAP) (9 ,
INSPECTION/CHECK) check.
NOTE:
C.
SOAP has proved to be effective at other than the intervals recommended in diagnosing engine problems.
Therefore, it i s recorrrnended an oil sample (with oil
filter) be submitted for analysis when an intermittent
or change in engine operating parameter occurs.
Example: fluctuating oil pressure, change in audible
noise level, etc.
(1)
Each 150 hours of eng ine operation.
(2)
When metal particles are evident on magnetic plug.
(3)
When oil filter bypass valve indicator pin is in extended position.
(4)
When metal particles are evident in drained engine oil.
(5)
When metal particles are evident on removed oil filter.
(6)
After 25 hours of operation following any of the following maintenance procedures . (To establish baseline for subsequent SOAP
checks).
(a)
Oil fill after initial engine installation.
(b)
Each oil change.
(c)
Replacement of planet gear assembly, planet gearshaft, pin ion
gearshaft, or ring gear.
Requirements for Changing Oil
After each 500 hours of engine operation.
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3.
Oil Changing
A. Oil Changing Instructions
(1) Drain oil system in accordance with 4.
Fill oil system in accordance with 6.
(2)
4.
Oil System Draining
NOTE:
A.
If possibl e , oil shall be drained while the engine is still
warm from operation.
Oil Tank Dr aining
(1) Remove dr ain plug (105, figure 301), and discard packing (110) .
Allow oil to drain into sui table container.
B.
(2)
Install new packing (110) on drain plug (105), and install plug .
(3)
Tighten plug t o 120 to 130 inch-pounds torque and lockwire.
Accessory Drive Gearbox Draining
{l)
Remove plug (5, figure 302), and discard pack i ng (10). Allow oil
to drain into suitable container.
(2)
Install new packing (10) on plug (5), and install plug .
(3)
Tighten plug t o 160 inch-pounds.
NOTE:
-5.
Before refilling oil system, replace oil filter
element. Refer to 8, INSPECTION/CHECK.
Oil System Fil l i ng (Initial Engine In stallation )
NOTE:
-A.
Refer to 6, when filling oil system that has been drained
subsequent t o engi ne installation.
Fi 11 Oil Tank
CAUTI ON:
USE ONLY APPROVED OIL {TABLE 301) .
(1)
Remove fi ll er plug (125 or 130, figure 301) .
(2)
Fill tank wi t h oil until li quid level gage or gage (170 or 175) indicates full.
(3)
Reinstall filler plug (125 or 130).
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LIQUID LEVEL GAGE
E-48A-965
105. DRAIN PLUG (IPC FIG. 43)
110. PACKING (S9413-556)
125. FILLER PLUG (572-533 -9103)
(VENDOR PART NO. 83990C)
130. FILLER PLUG (572-533-9201)
(VENDOR PART NO. 84129)
140. PACKI NG {S9413-020 )
(COMPONENT OF ITEM 130)
145. PACKING (S9412-117)
(COMPONENT OF ITEM 130A)
170. GAGE (361-530-9003)
(VENDOR PART NO. 83960A)
(IPC FIGURE 42)
-170A. GAGE {361-530-9004)
(VENDOR PART NO. B3960C)
175. GAGE (361-530-9101)
(VENDOR PART NO. 84130 )
180. PACKING (S9413 -020)
(COMPONENT OF ITEMS
170/170A)
185. PACKING (S9413-117)
(COMPONENT OF ITEM 1708)
-ITEM NOT ILLUSTRATED
Oi l Tank Fi ll er and Drain Ports
Figure 301
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E-48A-964
5.
OIL DRAIN PLUG (IPC FIG. 60)
JO. PACKING (S9413-~~7)
Accessory Drive Gearbox Drai n Pluq
Figure 302
72-00-00
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5. B.
Motor Engine
(1) Motor engine for 15 seconds.
(2) Top off oil tank in accordance with A.
C. Run Engine
D.
WARNING:
AREAS IN PROXIMITY OF ENGINE INLET AND EXHAUST ARE
EXTREMELY HAZARDOU S TO PERSONNEL WHEN ENGINE IS
OPERATING. PERSONNEL SHALL CLEAR THESE AREAS DURING
ENGI NE START AND OPERATION TO AVOID INJURY.
CAUTION:
SHUT DOWN ENGINE IMMEDIATELY IF OIL PRESSURE IS NOT
INDI CATED WITHIN TEN SECONDS.
(1)
Perform normal engine start and accelerate to idle speed in accordance with Aircraft Flight Manual.
(2)
Run eng ine for at least five minutes, then perform normal engine
shutdown.
Recheck Oil Level
(1) Recheck oil level in tank .
(2)
6.
If required, add oil in accordance with A.
Oil System Filling (System Drained Subsequent to Engine Installation)
NOTE : Refer to 5, when filling oil system at time of initial engine installation.
A.
Check Drain Plugs and Oil Filter
(1)
Check drain pl ugs (105 , figure 301 and 5, figure 302) for proper
installation.
(2) Verify oil filter replacement and check for proper install ation .
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TFE731-2-1C
6.
B.
Fill Oil Tank
CAUTION: USE ONLY APPROVED OI L (TABLE 301).
NOTE:
(1)
Total amount of oi l req uired to fill a completely
dr ai ned engi ne i s approx imate ly 12 quarts.
Remove fill er plug (125 or 130, figure 301).
(2 ) Fill tank with oil unt i l liqu id level gage or gage {170 or 175) indi cates full.
(3)
C.
Reinstall f ill er plug (125 or 130) .
Run Engine
WARNING : AREAS IN PROX IMITY OF ENGINE INLET AND EXHAUST ARE
EXTREMELY HAZARDOUS TO PERSONNEL WHEN ENGINES ARE
OPERATING . PERSONNEL SHALL CLEAR THESE AREAS DURING
ENGINE START AND OP ERAT ION TO AVOID INJURY.
CAUTION : SHUT DOWN ENGINE IMMEDIATELY IF OIL PRESSURE IS NOT
INDICATED WITHIN TEN SECONDS .
(1)
Perform normal engine start and accelerate to idle speed i n accordance with Aircraft Flight Manu al.
(2)
Run engine for at l east fi ve mi nu tes , t hen perform normal engine
shutdown.
D. Recheck Oil Level
(1)
Recheck oil level in tank.
(2)
If required, add oil in accordance with B.
7. Fuel Filter Requirements
A.
Clean or replace fuel filter element aft er initial 25 hours of engine
operation .
(1) Refer to 11, Inspection/Check fo r f uel fi l ter element removal and
i nstallation procedures.
(2) Ref er to 3, Cleaning/Painting f or f uel fi lter element clean i ng
procedures.
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8. Accessory Drive Gearbox Assembly Spline Lubrication
A.
Requirements
Lubricate accessory drive gearbox assembly splines prior to instal linq
airframe-furnished accessories.
B.
Lubricate Splines
Pack spline cavity of each drive spline on forward face of accessory
drive gearbox with one of the followinq lubricants.
Grease (Aeroshell 17 (MIL-G-21164))
Grease (Aeroshell 22 (MIL-G-81322))
Grease (Mobil Grease No. 28 (MIL-G-81322))
Grease (Mobil Grease No. 29 (Molybrlenumdisulphide)) (MIL-G-81827)
Grease (MIL-G-21164)
f'.
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CHAPTER 72 - L,I: NERAL - REMOVAL/INSTALLATION
TABLE OF CONTENTS
SUBJECT
CHAPTER/
SECTION/
SUBJECT
ENGINE
72-00-00
REMOVAL/INSTALLATION
General
PAGE
401
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72-CONTENTS
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GENERAL - REM0VAL/IN STAL L/\T f0N
1.
General
Remova l /I ns tallation procedures r esulting from un scherlul erl inspection~ or
malfunctionin9 components are not orovirled in thi s nuhlic~tion . RefRr to
Maintenance Manual, Report No. 72-02-02 .
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CHAPTL 72 - ADJUSTMENT/TEST
TABLE OF CONTENTS
SUBJECT
CHAPTER/
SECTION/
SUBJECT
ENGINE
72-00-00
ADJUSTMENT/TEST
General
Engine Pre-Start Procedure
Engine Start Procedure
Engine Fire on Ground During Start Procedure
Engine Ground Idling Information
Engine Shutdown Procedure
Electronic Computer Adjustment Procedures
Fuel Type Adjustment Procedure
(Pre SB 76-3007) Maximum Low
Pressure Rotor Speed (Nl) Adjustment
Procedures
(Post SB 76-3007) Maximum Low Pressure Rotor
Speed (Nl) Adjustment Procedures
Idle Speed (Nl} Adjustment Procedure
Fuel Control Manual Mode Adjustment Procedure
Oil Pump Pressure Regulator Adjustment Procedure
Engine Calibration Run Procedure
Prepare Engine for Calibration Run
Perform Calibration Run
PAGE
501
501
510
510
511
511
511
512
512
516
522
525
529
532
534
534
534
ADJUSTMENT/TEST
72-CONTENTS
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SERVICE MANUAL
TFE731-2-1C
GENERAL - ADJUSTMENT/TEST
1.
General
Instructions contained in thi s section are pr ovided for use when maintenance
actions are performed on the engine . I nstructions are restricted to t hose
that can be performed without soec ial tool s or test equipment . Comolete and
detailed tests and adjustments of the engine and enaine comoonents are
outlined in Light Maintenance Manual, Report No. 72-02-02, or may be
provided by aporoved service centers where specialized test and calibration
equipment is available.
Table 501 provides operating limits and list s corrective actions required
when engine operatinq limits are exceeded.
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NOTE:
In order to satisfy hiqh auality operational s tanrlards , as well
as ensuring the accuracy of readinqs obtained durinq the test
and calibration of the equipment, it is r ecommended that all
instrumentation and gages to be used be checked on a periodic
hasis aqainst instrumentation and qaqes of known accuracy.
Table 501.
Condition
NOTE:
Operating Limits
Operat i nq Limits
Action if Exceeded
The following operating limits are i ncluded for reference purooses with respect to the corrective maintenance action
reouired if t he limits are exceeded. Refer to Aircraft Fliqht
Manual for specific details regarding engine operation.
ENGINE START TIMES:
(1)
From 10 percent
N2 speed to
light-off
10 seconds (maximum )
(2)
From liqhtoff to idle
50 seconds (maximum)
Air starts
25 seconds (maximum)
from initial fuel
flow to 60 percent
(3)
Abort start. Determine
cause and correct before
further start attemot.
Abort start.
Determine
cause anrl correct before
further start attempt.
N2
Abort start. Determine
cause of failure to
start and correct before
further attempt.
ENGINE OIL PRESSURE:
(At Normal Operating
Temperature)
(1)
Takeoff,
climb, and
cruise
38 to 46 psig
Shut down enaine as soon
as possible. Determine
cause and correct.
(2)
Idle
25 to 46 psiq
Shut down enqine as soon
as possible. Determine
cause and correct.
(3)
Maximum
transient
55 psig (3 minutes
max imum) (See note
oreceedinq oil temperat ure operati ng
limits.
Shut down enq ine as soon
as possible. Determine
cause and correct.
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Table 50 1 .
Condition
Operating Limits (Cont)
Operating Limits
Action if Exceeded
OIL TEMPERATURE :
NOTE:
Starting the engine at temperatures as low as -54C (-65F) is
permitted provided that adequate cranking torque is available
and that the fuel viscosity is at or above the pour point.
If the engine is exposed to extremely cold temperatures {below
- 40C (-40F)) for extended periods , the engine should be heated
prior to attempting a start. During cold oi l temperature
starts, higher than normal oi1 pressure can be expected which
may exceed the maximum allowable tran sients observed during
normal temperatur e starts.
Exceeding idle power with oil temperature below 30C (86F) is
not recommended in the inter est of optimun engi ne and lubrication performance.
In addition, exceeding idle power with oil temperature below
30C (86F) is not recommended due to reduced fuel icing protection from the fuel heater. However, if ambient temperature
prevents attainment of 30C (86F) oil temperature, idl e power
may be exceeded as required.
Starting,
minimum: (See Note)
Continuous operation
mi nimum: 30C (86F)
Heat engine prior to
start.
Maximum: 127C
(261F) up to 30,000
ft, 140C (284F) above
30 ,000 ft.
Determine cause and
correct.
Transient: 149C
(300F) (two minutes
at any operational
altitude)
Determine cause and
correct.
72-00-00
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Table 501.
Condition
Operatinq Limits (Cont)
Operatin9 Limits
Action if Exceeded
PERMISSIBLE OPERATING
RANGES:
(1)
Air starts
Refer to Aircraft
Fl ioht Manual .
Determine cause and
correct.
( 2)
Altitude
Refer to Aircraft
Fliqht Manual.
Determine cause and
correct.
860C (1580F)
Abort start. Attempt
to determine cause and
correct before attemp ting restart.
860C (1580F) to 880C
(1616F) for less
than 10 seconds
Abort start. Enter max
temperature and duration
in excess of limit in
engine log. Determine
cause and correct.
860C (1580F) to 880C
(1616F) for more
than 10 seconds, or
over 880C (1616F)
for less than 5
seconds
Enter max temperature
and duration in excess
of limit in enoine loo.
Determine cause and
correct. Perform static
takeoff power check in
accordance with Aircraft Flioht Manual.
Over 880C (J616F)
for more than 5
seconds
Conduct hot section in spection in accordance
with Lioht Maintenance
Manual, Chapter /Section/Subject 72-00-00
before furt her en~ine
operation.
INTERSTAGE TURBINE
TEMPERATURE (ITT)
( Tt5) :
(1)
Starting
(Ground/Air)
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Table 501.
Conditi on
Operating Limi ts (Cont)
Operating Li mits
Action if Exceeaed
INTERSTAGE TURBINE
TEMPERATURE (ITT)
(Tt5): (Cont)
(1)
(2)
Starti ng
Any time 930C
Conduct overtemperature
(Ground/Air)
(Cont)
(1706F) is attained
or exceeded
hot section inspection
in accordance with
Light Ma intenance
Manual , Chapter/Section/Subject 72-00-00
before further engine
operation.
Takeoff
860C (1580F) f or
5 minutes maximum
Reduce power setting
to br ing ITT within
limits. Enter max
temperature and duration in exces s of
limit in engine log.
If 880C (1616F ) is
attained or exceeded,
conduct hot section
inspection in accordance with Light
Maintenance Manual,
Chapter/Section/Subject 72 -00-00 before fu rther engine
operation .
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Table 501.
Condition
Operatinq Limit s (Cont)
Operati nq Limits
Act ion if Exceeded
870C (1 598F) for
10 seconds maximum
Reduce power settinq to
bring ITT within limits.
Make electronic comouter
Nl adjus tment prior to
next flight. Observe
takeoff ITT limit.
870C (1598F) for
more than 10
seconds or 880C
{1616F) attai ned
Conduct hot section in spection i n accordance
with Liqht Maintenance
Manual, Chapter/Section/
Subject 72-00-00 before further enqine
operation.
930C (1706F)
attai ned or
exceeded
Conduct overtemoerature
hot section inspection
in accordance with
Light Maintenance
Manual, Chapter/Section/
Subject 72-00-00 before further engine
operation .
INTERSTAGE TURBINE
TEMPERATURE (ITT)
(Tt5): (Cont)
(3)
Takeoff
transient
72-00-00
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Table 501 .
Condition
Operating Limits (Cont)
Operatinq Limits
Action if Exceeded
INTERSTAGE TURBINE
TEMPERATURE (ITT)
(Tt5): (Cont)
(4)
Maximum
c 1imb
796C ( 146SF) to
832C (1530F) (30
minute limit )
Reduce power settinq to
bring ITT within limits .
Repeated application of
time limit is not authorized duri nq one takeoff
or landi ng cycle. After
completi on of climb seqment and acceleration to
cruise mach number, or
after 30 mi nutes in ITT
climb range, max cruise
l imitations become
appli cab le.
(5)
Maximum
832C (J.530F)
Reduce power settinq to
(6)
cont i nuous
Maximum
cruise
bring ITT within limits.
Max imum continuous
rating without time
limitation is authorized only for use in
aircraft certifi cation or in emergency
conditions .
795C (1463F)
Reduce power settinq to
bring ITT within limits.
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Table 501 .
Condition
Operati ng Limi ts (Cont)
Operating Limits
Action if Exceeded
ROTOR SPEEDS:
NOTE:
Nl refers to low- pressure- rotor speed:
100 percent= 20 ,688 rpm
N2 refers to high-pressure-rotor speed:
100 percent= 29,692 rpm
(1)
Takeoff and
maximum continuous/c l imb
Refer to Aircraft
Flight Manual.
Reduce power setting to
bring Nl/N2 within limits.
Make necessary electronic
computer adjustmen t prior
to next operation. Observe transient limits.
(2)
Transient
Nl - 100 to 103 percent (1 min)
N2 - 100 to 103 percent (1 min)
Nl - 103 to 105 percent (5 sec)
N2 - 103 to 105 percent (5 sec)
Reduce power setting to
bring Nl/N2 within limits .
Make necessary electronic
(3)
Overspeed
Nl - 105 percent
N2 - 105 percent
computer adjustment prior
to next operation.
serve speed limit.
Ob-
Reduce power setti ng to
bri ng Nl/N2 within
limits. Perform overspeed
inspection in accordance
with Light Maintenance
Manual, Chapter/Section/
Subject 72-00-00 , GENERAL INSPECTION/CHECK any time
105 percent Nl or N2
is exceeded before further engine operation .
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Tabl e 501.
Conditi on
Operating Limits
Action if Exceeded
SUDDEN STOPPAGE OR
EXTERNALLY INDUCED
ENGINE DECELERATION:
Any deceleration of
enqine due to impact
with any object .
Shut down enqinP..
termine cause and
correct.
SHUTDOWN:
Operate for at least
2 min at 38 percent
Nl or below prior
to shutdown.
Check for possible seizure
or rub of the rotors.
Roll down
From point of fuel
cutoff, Nl roll down
time shall be 50
seconds or more and
N2 r oll down time
shall be 30 seconds
or more. N2 shall
roll down at l east
15 seconds prior t o
roll down of Nl.
Check for possible
seizure or rub of the
rotors. Refer to
GENERAL - TROUBLE
SHOOTING.
OIL USAGE RATE:
0.05 qallon per
hour when meas ured
over a 15- hour period.
Inspect engine for external oil leaks. Determine cause and correct.
FUEL INLET PRESSURE:
5 psi above true
vapor pressure but
not to exceed 50
ps iq.
Determine cause and
correct. If limit is exceeded for 10 or more hours
of enaine operation, return
fuel pump to a Garrett
aporoved repair center
for inspection.
IGNITION SYSTEM
OPERATION:
*As reauired.
Check for satisfactory
operation durinq next
ground start.
*NOTE:
•
Operating Limits (Cont)
De-
Use of continuou s iqnition exceot as required will
necessitate premature replacement of igniter pluas .
72-00-00
Paqe 509
Apr 15/81
~ AIResearch
~
Phoenix
SERVI CE MANUAL
TFE731-2-1C
2.
Enqi ne Pre-St art Procedure
WARNING:
AREAS IN PROXIMITY OF ENGIN E INLET AND EX HAUST ARE EXTREMELY HA ZARDOUS TO PERSONNEL WHEN ENGIN E IS OPERATI NG.
PERSONNEL SHALL CLEAR THE SE AREAS DURING ENGIN E START
AND OPERATION TO AVOID INJURY.
CAUTION:
DO NOT RUN ENGINE WITHOUT PROPER AIRCRAFT PR IMARY (CORE)
EXHAUST NOZZLE ANO AIRCRAFT INLET DUCT INSTAL LED. DO
NOT RUN ENGINE ABOVE GROUND IDLE SPEED WITHOUT PROPER
AIRCRAFT FAN BYPASS DUCT INSTALLED . ENGINE DAMAGE WILL
RESULT IF DUCTS ARE NOT USED AS SPECIFIED. REFER TO
AIRCRAFT MAINTENANCE MANUAL FOR INSTALLATION OF DUCTS.
A.
Pre-Start Procedures
NOTE:
Operation of switches and controls as described with
reference to function performed to the enqine does not
reflect a specific installation. Aircraft installat ion
may combine switches with each other and with other
controls. Refer to Aircraft Flioht Manual for cockpit
control arrangement and operation.
(1)
Perform prefliaht inspections outlined in the Aircraft Fliaht
Manua 1.
(2)
Check run-up area for any loose objects in the vicinity of the engine air inlet and rear of the engine. Remove those objects th at
could interfere with the air intake.
(3)
Check all engine controls for freedom of movement .
NOTE:
(4)
3.
If an external power source is used, check to ensure prooer connection and 1000 amp minimum
capacity.
If available, use an external power source for starti no enaine.
Engine Start Procedure
NOTE:
All engine starts made in accordance with procedures of
this manual shall be made in the normal mode (engine electronic computer turned on and operatinq), as specified in
the Aircraft Flight Manual. Except where specificall y
noted in the following procedures, the electronic computer
shall remain operating when running the enqine.
72-00-00
Paoe 510
Apr 15/ 81
~ AiResearch
~
Phoenix
SERVICE MANUAL
TF - 731 - 2-lC
3.
A.
Start Procedures
(1)
Ensure aircraft covers for enoine intake and exhaust are removed.
NOTE:
(2)
4.
Start engine in accornance with Aircraft Fliqht Manual.
Enqine Fire On Ground During Start Procedure
A.
5.
If required to cl ear enqine of fuel, as when attempting a start following a false start, either
allow three minutes for fuel to drain from engi ne
or motor enqine for 15 seconds with power lever at
fuel cutoff posi tion.
Fire on Ground Procedures
(1)
If fire is burninq within tailpipe area, shut off fuel to engine,
then motor engine to blow out fire.
(2)
If fire is in engine compartment or nacelle, move power lever to
fuel cutoff position to manually close fu el shutoff valve, then activate fire extinguisher switch.
Engine Ground Idling Information
A normal characteristic of the engine which may be observed at idle speed
(28.5 percent Nl) is a cyclic increase and decrease of Nl. The cyclinq is
characterized by a sequence as follows: fuel flow increases with no increase in Nl; Nl then increases; fuel flow decreases with no decrease in Nl;
Nl then decreases; cycle repeats. This characteristic is due to normal fuel
pressure changes within the fuel manifold caused by low flow rates which do
not maintain constant flows from all secondary nozzles of the fuel manifold.
This characteristic may be confirmed as the cause of cyclinq by increasinq
the power lever position to provide 2SO to 300 pounds per hour fuel flow,
which stops cycling . The cyc ling characteristic is normal at low flow rates
and has no effect on operation or flioht safety.
6.
Engine Shutdown Procedure
A.
Observe Shutdown Procedures
(1)
Shut down engine in accordance with Aircraft Fliqht Manual.
(2 )
Allow engine cool-down period of at least 15 minutes before installing aircraft covers for engine intake and exhaust.
72-00-00
Paqe Sll
Apr 15/81
,..;:;=:-, AiResearch
Phoenl•
6 -_,,
SERVI CE MANUAL
TFE731- 2-1C
7.
Electronic Computer Adjustment Procedure
NOTE:
Graphs required for computer adjustment give barometri c
pressures in inches of mercury or use press ure altitude in
feet. If desired, convert ei ther parameter us ing graph of
Figure 501.
The following adjustments are requi red when engine operation indi cat es Nl (with power lever angle at maxi mum, aircraft stationary) differs from Nl specified by appli cable
Aircraft Flight Manual curve, when a new or replacement
electronic computer is installed, or when a new or replacement engine is installed.
A.
Fuel Type Adjustment Procedure
(1)
Recommended setting of fuel adjustment for various fuels is listed
in Table 502. Clockwise movement of fuel adjustment knob will decrease (shorten) engine acceleration time. Counterc lockwi se movement of fuel adjustment knob will increase (lengthen) engine accel erat ion time. Excessive clockw i se adjustment is unde si rable si nce
it may result in engine compressor instability (surge) during rapid
power lever advance. Excessive adjustment in the counter clockwise
direction is also undesirable in that it may reduce engine acceleration capability to an undesirable extent and may result in lean
blowout.
(2) A fuel adjustment sett ing of up to one click (or position number)
in either direction from the recommended fuel adjustment (table
502) is allowable to compensate for individual engine characteristics or installation effects.
Table 502.
Recommended Fuel Adjustment
Fuel Used
Jet A/Al / JPS
Jet 8/JP4
Aviation Gasoline (80/87, 100/130,
or 115/145 octane)*
50% or more Jet A/Al/JPS
50% or more Jet B/JP4
50% or more Aviation Gaso line*
*NOTE:
Fuel Adjustment Setting
(See figure 502 or 503)
Position 5
Position 6
Position 7
Position 5
Position 6
Position 7
Use of aviation gaso line is limited to not more than 500
ga llons per 100 hours of operati on other than during
emergency operation.
72-00-00
Page 512
Apr 15/81
SERVI CE MANUAL
TFE731-2-1C
NOTE: AN AIRCRAFT ALTIMETER MAY BE USED TO DETERMINE AMBIUH PRESSURE SY
ADJUSTING THE ALTIMETER TO 29.92 IN. Hg AND READING PRfSSUkE
ALTITUDE DIRECTLY . CORRESPONDING AMBIENT PRESSURE IS SHO WN ON
THIS CURVE.
11000
10800
106()()
/
I 0400
/
10200
/
10000
9800
.,/
9600
9400
9200
9000
8800
J
/
/
8600
,/
8400
8200
8000
j
/
7600
/
7400
,/
7200
7000
6800
/
/
6600
/
..,. 6400
"- 6200
/
/
6000
3 5800
/
.... 5600
'.::; 5400
:: 5200
~ 5000
~ 4800
~
o...
/
.,
/
4400
4200
4000
3800
,
/
/
/
3600
3400
/
3200
.,
/
/
3000
2800
/
2600
/
2400
/
2200
2000
1800
,,
/
/
1600
/
1400
1200
1000
800
400
/
/
/
4600
600
/
/
7800
...,
/
/
/
II'
/
/
/
200
I/
0
30
29
28
27
26
25
24
23
22
21
20
PRESSURE - IN . Hg
G-48A-252
Ambient Pressure Conversion
Fiqure 501
72-00-00
Paqe c;J3
Aor 15/Rl
SERVICE MANUAL
TFE731-2-1C
NOTE:
POSITION NUMBERS SHOWN FOR FUEL ADJUSTMENT ARE ESTABLISHED BY COUNTING DETENT
POSITIONS FROM THE CCW STOP ON lHE CONTROL. POSITION NUMBERS DO NOl APPEAR
ON THE CONTROL.
RED BAND
POSITI ON 9
I
POSITION 8
\
I
POSITION 10
ORANGE BAND
. / POSITION 11 (CW STOP)
POSITION 7 ' -
POSITION 6 -
' - POSITION 1 (CCW STOP)
POSITION d
I
I
\ POSITION 2
POSITION 3
BLUE BAN D
DETAIL A
FUEL ADJUSTMENT
MAXIMUM THRUST SPEED
ADJUSTMENT
(CLOCKWISE TO INCREASE)
C
w
~
ITT LIMITER ADJUSTMENT
(CLOCKWISE TO INCREASE)
i;:
C
--- ◄
0:□e
FLAT-RATE ADJUSTMENT
(COUNTERCLOCKWISE) TO INCREASE)
BACK FACE
FRONT FACE
F-48A-381 R1
(Pre SB 76-3007) El ectroni c Computer
Adjustment Points
Fiqure 502
72-00-00
Page 514
Apr 15/81
Ai Research
Phoo nb
SER VICE MANUAL
TFE731-2-1C
NOTE:
POSITION NUMBERS SHOWN FOR FUEL ADJUSTMENT ARE ESTABLISHED BY COUNTING DETENT
POSITIONS FROM THE CON STOP ON THE CONTROL. POSITION NUMBERS DO NOT APPEAR
ON THE CONTRO L.
RED BAND
POSITION B
\
POSITION 9
POSITION 10
I
_\.-,.-r?","77..-
I
ORANGE BAND
/
POSITION 7 ...___
POSITION 11 (ON STOP)
~OSITION 6 -
'-- POSITION I (CON STOP)
I
POSITION 4
\ POSITI ON 2
I
POSITION 3
BLUE BAND
DETAl'L A
MANUAL MODE
SWITCH
FLAT RATE/ MAXIMUM SPEED ADJUSTMENT
(CLOCKWISE TO INCREASE)
(
.))© ©) ¥~
,-
- - - B-- -
i ~©~ t
' \0~
AL TERNATE IDLE SETTING
POSITI ON (CLOCKWISE TO
INCREASE)
0
~
o.-
+
@)
FUEL
ADJUSTMENT
DETAIL 8
~~
ITT LIMITER ADJUSTMENT
(CLOCKWISE TO INCREASE)
IDLE SETTING (CLOCKWISE
TO INCREASE)
~~
'::ce
"0'--_0
_ ,!
ENGINE FLAT RATE ADJUSTMENT
(COUNTERCLOCKWISE TO INCREASE)
BACK FACE
FRONT FACE
F-48A- 382
(Post SB 76-3007) El ectronic Computer
Adjustment Points
Fiqure 503
72-00-00
Paqe SlS
Apr 15/81
Ai Research
Phoonl x
SERVICE MANUAL
TF E731-2-1C
7.
B.
(Pre SB 76-3007) Maximum Low Pressure Rot or Speed (Nl) Adjustment Procedures
NOTE:
(1)
The following adjustments are required when engine
operation indicates Nl (wi t h power le ver ang l e at maximum, aircraft stationary) differs from Nl specified by
applicable Aircraft Flight Manu al curve, when a new or
replacement electronic computer i s installed or when a
new or replacement engin e i s instal led.
Determine hot or cold day condition as fol lows .
(a)
Note outside air temperature (free air static temperature obtained from ground meteorological sources) and indicated pressure altitude.
(b)
Enter Figure 504 with conditions noted in step (a).
1
If outside air temperature and barometric pressure li nes
intersect in area of graph identified as hot day (abov~
curve), perform hot day adjustment procedure outlined 1n
step (2).
2 If outside air temperature and barometric pressure lines
intersect in an area of graph identified as cold day (below
curve), perform cold day adjustment procedure outlined in
step (3).
(2)
Perform hot day flat-rate (FR) ground check and adjustment procedure as f o11 ows .
(a)
Determine maximum low pressure rotor speed (Nl) in accordance
with Aircraft Flight Manual, using outside air temperature
(free air static temperature obtained from ground meteorological sources) and indicated press ure altitude.
(b)
Determine number of turns for indirect setting of flat-rate
(FR) adjustment on electronic computer as follows.
NOTE :
If intersection of outside air temperature
and indicated pressure altitude lines is
beyond indicated nominal adjustment li mit in
the following step, postpone indirect setting
of flat-rate (FR) adjustment until cooler
temperature prevails.
1 Enter Figure 505 with outside air temperature and locate
intersection of outside air temperature and indicated pressure altitude l i nes.
2 Note corresponding number of turns required.
72-00-00
Page 516
Apr 15/81
Al Research
Phoonl11
SERVICE MAN UAL
TFE731-2-1C
122
50
104
40
86
30
20
68
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~
w
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w
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~
w
0
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V
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HOT DAY
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14
-4
-20
- 22
-30
-40
-40
10000 9000 8000 7000
6000 5000
4000 3000
2000
1000
PRESSURE AL TIT-UDE-vEET
Hot , Co ld Day Definition
Fi gure 504
0
- 1000
G-48A-246R3
72-00-00
Page 517
Apr 15/81
15
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OUTSIDE AIR TEMPERATURE (OAT) - °F
G-48A- 300R2
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SERVICE MANUAL
ff [731-2-lC
7.
B.
(2)
(c) Remove cover 011 rear face of electronic computer. Adjust
flat-rate (FR) adjustment (figure 502) 22 turns
counterclockwi se.
(d)
Adjust maximum speed (MN) adjustment (f i gure 502) 22 turns
counterc lockwi se.
CAUTION:
DO NOT EXCEED ENGINE OPERATING LIMITS WHEN
PERFORMING THE FOLLOWING STEP.
(e) Perform normal eng ine start and accelerate to idle speed in
accordance with Aircraft Flight Manual. Slowly advance power
lever to maximum position (117 t o 122 degrees power lever
angle). Operate engine for two minute minimum at specified
power lever angle to stabilize C'nditions.
CAUTION:
WHEN PERFORMING THE FOLLOWING STEP, DO NOT
EXCEED ITT LIMIT OF 860C (1580F). IF
REQUIRED Nl CANNOT BE SET WITHIN ITT
LIMIT, CONTACT GARRETT FIELD SERVICE .
ENSURE MN ADJUSTMENT DOES NOT INCREASE MN
SCHEDULE ABOVE SETTING OF ITT LIMITER IN
ELECTRONIC COMPUTER (ITT LIMITER IMPROPERLY SET BELOW 860C) . INDICATED ITT
SHOULD GRADUALLY INCREASE WITH GRADUAL IN-
CREASE (CLOCK.WISE ROTATION) OF MN
ADJUSTMENT. IF THIS rs NOT OBSERVED, ITT
LIMITER MAY BE OVERRIDING MN SCHEDULE,
PREVENTING PROPER SETTING OF MN
ADJUSTMENT. FOR THIS CONDITION, ADJUST MN
ADJUSTMENT COUNTERCLOCKWISE UNTIL INDICATED ITT DECREASES WITH DECREASE
(COUNTERCLOCKWI SE ROTATION) OF MN ADJUSTMENT AND TROUBLE SHOOT ELECTRONIC COt-fUTER
FOR LOW ITT LIMITER SETTING PRIOR TO COMPLETING SETTING OF MN SCHEDULE. REFER TO
LIGHT MAINTENANCE MANUAL,
CHAPTER/SECTION/SUBJECT 72-00-00,
ADJUSTMENT/TEST.
(f ) Gradually adjust maximum speed (MN ) adjustment clockwise to
obtain required Nl determined in step (a) .
(g) Adjust f lat rating schedul e by gradual ly turning fl at-rate
(FR ) adjustment clockwise until either indicated Nl or ITT
(select most sensitive indication for engine installati on)
just st art s to decrease, then turn FR adjustment counterclockwise the number of turns determined in step (b).
72-00-00
Page 519
Apr 15/81
Ai Research
Pt,oenlx
SERVICE MANUAL
TFE731-2-1C
7.
B.
(2)
(3)
(h)
Reduce power lever position to idle and perform normal engine
shutdown . Install cover on rear face of electronic computer.
(i)
This comp l etes hot day adjustment procedure.
Perform co ld day maximum speed (MN) ground check and adju stment
procedure as fo ll ows.
(a)
Determine maximum low pressure rotor speed (Nl) in accordance
with Aircraft Fl ig ht Manual, using outside air temperature
(free air st atic temperature obtained from ground meteorological sources) and indicated pressure altitude.
(b)
Determine number of turns for indirect setting of maximum
speed (MN) adjustment on electronic computer as follows.
NOTE:
If intersection of outside air temperature
and indicated pressure al titude l ine is
beyond indi cated nominal adjustment limit in
the following step, postpone i ndirect setting
of maximum speed (MN) adjustment until warmer
temperature prevails.
1 Enter Figure 506 with outside air temperature and locate
intersection of outside ai r temperature and indicated pressure altitude li nes.
2 Note corresponding number of turns required.
(c)
Remove cover on rear face of electron ic computer. Adjust
flat-rate (FR) adjustment (figure 502) 22 turns clockwise.
(d)
Adjust maximum speed (MN) adjustment (figure 502) 22 turns
clockwise.
CAUTION:
(e)
DO NOT EXCEED ENGINE OPERATING LIMITS WHEN
PERFORMING THE FOLLOWING STEP.
Perform normal engine start and accelerate to idle speed in
accordance with Aircraft Flight Manual . Slowly advance power
lever to maximum position (117 to 122 degrees power lever
angle). Operate engine for two minutes minimum at specified
power lever angle to stabi li ze conditions .
72 -00-00
Page 520
Apr 15/81
.--...
",:)
15
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ro
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OUTSIDE AIR TEMPERATURE (OAT\ - ° F
G-48A-302RJ
C.:_-:~
~
AIResearch
Phoenix
SERVICE MANUAL
TFE731-2-1C
7.
B.
C.
(3)
(f)
Gradually adjust flat-rat e (FR) adjustment counterclockwise to
obtain required Nl determined in step (a).
(g)
Adjust max imum speed schedule by gradually turning maximum
speed (MN) adjustment counter clockwi se until either indicated
Nl or ITT (select most sensitive indi cation for engine installation) just starts to decrease, then turn MN adjustment
clockwise the number of t urns determined in step (b).
(h)
Reduce power l ever position t o idle and conduct normal engine
shutdown. Install cover on rear face of el ectronic computer.
(i)
Thi s compl etes cold day adjustment procedure.
(Post SB 76-3007) Maximum Low Press ure Rotor Speed (Nl ) Adjustment
Procedures
NOTE:
(1)
The following adjustments are requi red when engine operation indicates Nl (with power lever angle at maximum,
aircraft stationary) differs from Nl specified by applicable Aircraft Fli ght Manual curve, when a new or
replacement electronic computer is installed, or when a
new or replacement engine is installed.
Perform f lat rate/maximum speed (FR/MN) ground check and adjustment
procedure.
( a)
Set EFR adjustment (figure 503) 22 turns counterclockwise,
then clockwise for the number of turns noted on decal adjacent
to EFR adjustment.
( b)
Refer to Aircraft Flight Manual and determine required Nl for
the prevailing outside air temperature (free air static temperature obtained from ground meteorologi cal sources) and indicated presssure altitude conditions. Record required Nl.
'
(c}
Perform normal engine start and acceler ate to idle speed in
accordance with Aircraft Flight Manual.
CAUTION:
DO NOT EXCEED ENGINE OPERATING LIMITS WHEN PERFORMING THE FOLLOWING STEP.
(d)
Slowly advance power level to maximum position (117 to 122 degrees power lever angle). Operate engine for two minutes minimum at specified power lever angle to stabilize conditions.
(e)
Adjust FR/MN adjustment on electronic computer (figure 503) to
obtain required percent of Nl noted in step (b). Perform normal eng ine shutdown .
72-00-00
Page 52 2
Apr 15/81
~."';...-.) AiAesearch
, ~
/
rhoonlx
SERVICE MANUAL
Tl t:731-2-lC
NOTE:
7.
C.
(2)
Step (1) provides for correct Nl adjus tment at
specific ambi ent (hot or cold day) conditions as
defined by Figure 504. When ambi ent conditions
change from hot to cold or from cold to hot, a
further trim adjustment may be required to obtain
specified Nl at all ambi ent conditions . Perform
step (2) or (3), as applicable, should an Nl error
become evident at changed ambient cond i tions.
If step (1) was performed at co ld day conditions and an Nl error i s
evident at hot day conditions, perform the following at hot day
conditions.
(a)
Refer to Aircraft Flight Manual and determine required Nl for
the prevailing outside air temperature (free air static temperature obtained from ground meteorolog ical sources) and indicated press ure altitude conditions. Record required Nl.
(b)
Perform normal engine start and accelerate to idle speed in
accordance with Aircraft Flight Manual.
CAUTION:
DO NOT EXCEED ENGINE OPERATING LIMITS WHEN
PERFORMING THE FOLLOWING STEP.
(c)
Slowly advance power lever to maximum position (117 to 122 degrees power lever angle). Operate engine for two minutes minimum at maximum power lever angle to stabilize conditions.
Record actual (cockpit indicated) Nl.
(d)
Determine and record amount and direction of Nl error
(difference of required Nl recorded in step (a) and actual Nl
recorded in step {c)).
1 If actual Nl i s higher than required Nl, correct error as
specified in step (e).
2 If actual Nl is lower than required Nl, correct error as
specified in step (f).
(e)
Decrease actual Nl to required Nl as follows.
1 Adjust FR/MN adjustment (figure 503) counterclockwise
(decrease) to provide change in Nl determined in step {d).
One turn provides a change of approximately two percent Nl .
2 Perform normal engi ne shutdown.
3 Adjust EFR adjustment (figure 503) counterclockwise
( increase) for change determined in step (d). One turn
provides a change of approximately 1.2 percent Nl .
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7.
C.
(2)
(f)
Increase actual Nl to requ ired Nl as follows.
1 Adjust FR/MN adjustment (figure 503) cl ockwise (increase)
to provide change in Nl determined in step (d) . One turn
provides a change of approxi mately two percent Nl.
2 Perform normal engine shutdown.
3 Adjust EFR adjustment (figure 503) clockwise (decrease) for
change determined in step (d). One turn provides a change
of approximately 1.2 percent Nl.
(3)
If step (1) was performed at hot day conditions and an Nl error is
evident at cold day conditions, perform the following at cold day
conditions.
(a)
Refer to Aircraft Flight Manual and determine required Nl for
the prevailing outside air temperature (free air static temperature obtained from ground meteorologi cal sources) and indicated pressure altitude conditions. Record required Nl.
(b)
Perform normal engine start and accelerate to idle speed in
accordance with Aircraft Flight Manual.
CAUTION:
DO NOT EXCEED ENGINE OPERATING LIMITS WHEN
PERFORMING THE FOLLOWING STEP.
(c)
Slowly advance power lever to maximum position (117 to 122 degrees power lever angle). Operate engine for two minutes minimum at specified power lever angle to stabi lize conditions.
(d)
Adjust EFR adjustment on electronic computer (figure 503) to
obtain required percent of Nl noted in step (a). One turn
provides a change of approximately 1.2 percent Nl. Perform
normal engine shutdown.
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NOTE:
The adjustment procedures outlined in paragraph D,
are required when engine operation indicates Nl
(with power l ever angle at idle position) differ s
from Nl spec i fied by Figure 507, when a new or
r eplacement el ectronic computer is installed, or
when a new or re pl acement engine is installed.
When performing the adjustment procedures of paragraph D, engine bl eed air demand shall be zero and
engine accessor y dr ive l oading (electrical and hydrauli c) shall be zero or mi nimum achievable.
7.
D.
Idle Speed (Nl) Adjustment Procedure
(1)
Note outside air temperature (free ai r static temperature obtained
from ground meteorologi cal sources) and indicated pressure
altitude.
(2)
Determine low pressure rotor speed (Nl ) r eq uired for noted
conditions.
(3)
(a)
Enter Figure 507 and locate intersecti on of outs i de air temperature and indicated press ure alt i t ude lines.
(b)
Note corresponding Nl percent required.
Perfonn normal engine start and accelerate t o idle speed in accordance with Aircraft Flight Manual. Set power lever to idle.
CAUTION:
NOTE:
IF CAPPING OF SECONDARY FUEL FLOW IS NECESSARY
TO SET IDLE ADJUSTMENT IN THE FOLLOWING STEP,
DO NOT ADVANCE POWER LEVER BEYOND IDLE POSITION
WITHOUT FLOW DIVIDER VALVE RECONN ECTED FOR NORMAL OPERATION.
If Nl cycling occurs and is of such mag nitude t hat
idle adjustment of the foll owing step cannot be
made, shut down engine and cap of f secondary output port (figure 508) of flow di vi der va l ve to allow satisfactory completion of step (1) through
(6). After completion of adjustment, reconnect
secondary output for normal oper ati on.
(4)
Gradually adjust idle setting (f i gure 502 or 503) (clockwise
to increase Nl, counterclockwi se t o decrease Nl) to obtain Nl
determined in step (2).
(5)
Perform normal engine shutdown .
(6)
Thi s completes idle adjustment procedure .
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CONDITIONS:
IDLE POWER SETTING (POWER LEVER ANGLE) = 200
RAM RECOVERY = 100%
CUSTOMER POWER EXTRACTION = 0
FAN EXHAUST N OZZLE AREA = 195 SQ-INCH.
CORE EXHAUST NOZZLE AREA = 105 SQ-INCH.
FLIGHT MACH NUMBER = 0
REFERENCE 1000/o N1 SPEED - 20, 688 RPM
50
'I "
11 11
PRESSURE ALTITUDE
10,000 FT
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SERVICE MANUAL
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8.
Fuel Control Manual Mode Adj ustment Procedure
NOTE:
A.
The adjustment procedures of paragraph A shall be made
when a new or replacement fuel control is installed on
the engine and/or upon engine replacement. Al so, upon
an engine replacement, accompli sh computer
adjustment/test in accordance with paragraph 7.A.
through 7. D. prior to accomplishing the following
adjustments.
Fuel Control Adjustment Procedures
(1)
Adjust manual governor cam adjustment (figure 509) four turns counterclockwise from the flush position then one turn clockwise.
(2)
Perform normal engine start and accelerated to idle speed in accordance with Aircraft Flight Manual.
NOTE:
Manual mode idle rpm (approximately 20 degrees
power lever angle) is not adjustable and may be
higher or l ower than normal mode idle rpm; this is
not cause for fuel control rejection.
~ F L O W DIVIDER VALVE
SECONDARY OUTPUT PORT
F-48A-489
Flow Divider Valve Secondary Output Port
Figure 508
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F-48A- 387
Fuel Control
Figure 509
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8. A.
(3)
De-ener gize elec tronic computer.
CAUTION:
DO NOT EXCEED ENG INE OP ERATING LIMITS OF Nl,
N2, OR ITT WH EN PERFORMING THE FOLLOWING STEP.
( 4)
Sl owly advance power lever t o maxi mum power lever angle (117 to 122
degrees ) in accordance wi t h Aircr aft Flight Manual and operate engi ne f or t wo mi nutes mi ni mum to st abilize conditions, then record
manua 1 mode ITT.
(5)
Return power lever to idle, energize electronic computer, and perform normal engine shut down.
(6)
Subtract manual mode ITT recorded i n step (4) from target ITT of
855C (1561F) . Record resu lt as delta ITT.
(7)
Det ermine number of turns requi r ed f or manual sovernor cam adjustment by di viding delt a ITT recorded in st ep (6) by 38C (68 . 4FJ .
Record number of turns required .
CAUTION:
NOTE:
ANYTIME CLOCKWISE ADJUSTMENT OF MANUAL GOVERNOR CAM
ADJUSTMENT IS REQUIRED WHEN PERFORMING THE FOLLOWING
STEPS (ENGINE SHUTDOWN) , POSITION POWER LEVER TO
MAXIMUM (117 TO 122 DEGREES) POSITION PR IOR TO MAKING ADJUSTMENT . IF ANY RESISTANCE TO CLOCKWISE
ROTATION OF THE MANUAL GOVENOR CAM ADJUSTMENT IS
NOTED, STOP AND INVESTI GATE FOR CAUSE. CONTI NUED
CLOCKWISE ROTATION OF ADJUST SCREW COULD RESULT IN
FAILURE OF CAM FOLLOWER IN FUEL CONTROL.
Clockwise rotat ion of manua l governor cam adjustment
increases manual mode ITT and counterclockwi se rotat ion
decreases manual mode ITT. One ful l rot ati on provi des
a change of approximately 38C (68.4F ) .
(8)
Position power lever to max imum (engine shutdown ), then turn manual
governor cam adjustment (f igure 509) clockwi se t he number of turns
recorded in step (7).
(9)
Return power lever to cutoff. Advance power lever (engine shutdown) to maximum stop and r eturn to cutoff.
(10) Det ermine hot or cold day cond iti ons as fol lows.
(a)
Note outs ide air t emper ature (free air st ati c temper at ure obt ained from ground meteorol ogi cal sources) and indi cated pressure alti t ude.
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8. A.
(10)
(b)
Enter Fi gure 504 with conditions noted in step (a).
1
If outside air temperature and barometric pressure lines
inter sect in an area of graph identified as hot day (above
curve), perform steps (11), (12) and (14).
2 If outside ai r temperature and barometric pressure lines
i ntersect in an area of graph identif ied as cold day
(bel ow curve), perform steps (11), (12) and (13). If
desired, al so perform cold day optional fl i ght check of
step (15) .
(11) Perform normal engine start and accelerate to idl e in accordance
with Aircraft Fli ght Manual.
NOTE:
If engine does not re spond to power lever movement in the following step, the fuel control manual mode cam may be damaged or broken.
(12) De-energize electroni c computer and advance power lever enough to
determine t hat engine responds to power lever movement in manual
mode.
(13)
(Cold day conditions only) Return power lever to idle, energize
electronic computer and perform normal engine shutdown .
(14)
(Hot day conditions only) Perform hot day manual mode check as
follows.
CAUTION:
(a)
DO NOT EXCEED ENGINE OPERATING LIMITS OF
Nl, N2 OR ITT WHEN PERFORMING THE FOLLOWING STEP.
Sl owly advance power lever to maximum power lever angle (117
to 122 degrees) in accordance with Ai rcraft Flight Manual and
operate engine for two minutes minimum to stabilize conditions, then record manual mode ITT .
(b) Return power lever to idle, energize electronic computer and
perform normal engine shutdown.
(c)
Manual mode ITT recorded in step (a) shall be 848C (1558F) t o
860C ( 1580F).
CAUT ION : OBSERVE CAUTION PRECEDING STEP (8) PRIOR
TO PERFORMING THE FOLLOWING STEP.
(d)
'I
If required, turn manual governor cam adjustment (figure 509)
the direc ti on and number of turns required to obtain ITT
within spec if ied limits.
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8.
A.
(14)
(e)
NOTE:
(15)
Return power lever t o cutoff. Advance power lever (eng i ne
shutdown) t o maxi mum stop and retur n to cutof f, then repeat
steps (11) , (12) and (14).
Flight check procedure of st ep (1 5) is not
required, but is t he option of the indi vi dual
operator i f cold day verifi cation i s desi r ed.
(Cold day conditions only) If verification of manual govenor cam
adjustment is desired, perform optional flight check as fol lows.
CAUTION:
DO NOT DEVIATE FROM STEPS (a) AND (b) OR UNWARRANTED FU EL CONTROL REJECTION DUE TO BROKEN
MANUAL MODE CP/>1 OR ENGINE OVERSPEED IN MANUAL
MODE MAY RE SULT.
(a)
The following steps must be performed with ram air temperature (RAT) above -20C (-4F); if RAT is lower than specified ,
postpone flight check until RAT is above -20C (-4F ).
(b)
Establ ish indic ated press ure altitude of 15,000 feet, calibrated airspeed (CAS) of 280 to 300 knots, with no engine
power extract i on, such as, bleed-ai r, electrical load, etc .
(c)
Retard power l ever t o idle and de-energize el ectronic
computer.
CAUTION:
DO NOT EXCEED ENGINE OPERATING LIMITS OF
Nl, N2 OR ITT WHEN PERFORMING THE FOLLOWING STEP.
(d)
With conditions established in steps (a) and (b) and power
lever at maximum, operate engine for two minutes minimum to
stabilize ITT indication, then record manual mode ITT
indication . ITT shall be 848 to 860C (1558 to 1580F).
(e)
Retard power lever to idle and energize electronic computer.
(f)
If flight check manual mode ITT is not within specif i ed limits, determine number of t urns and and direction required t o
adjust manual governor cam adjustment to provide ITT of 84 ~
to 860C (1558 to 1580F). Record number of turns and direction required .
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CAUTION:
8.
9.
A.
(15)
OBSERVE CAUTION PRECEDING STEP (8) PRIOR
TO PERFORMING THE FOLLOWING STEP.
(g)
Turn manual governor cam adjustment (figure 509) t he number of
turns and in direction recorded in step (f).
(h)
Return power lever to cutoff. Advance power lever (engine
shutdown) to maximum stop and retu r n to cutoff, then repeat
step s (11 ), (12) and (13). If desired, also repeat cold day
opt i onal fl i ght check of step (15).
Oil Pump Pressure Regulator Adjustment Procedure
A. Pressure Regulator Adjustment Procedure
(1)
Perform engine start and accelerate to idle speed in accordance
with Aircraft Flight Man ual.
(2 ) Advance power l ever and stabil ize N2 speed at 88 percent rpm.
(3)
Allow engine oi l to reach minimum operating temperature of 60C
( 140F).
CAUTION : PRIOR TO ADJUSTING OIL PUMP PRESSURE REGULATOR
TO CORRECT HIGH OR LOW OI L PRESSURE INDICATION,
ENSURE INDICATION WAS NOT CAUSED BY INSUFFI-
CIENT OIL OR BY FAULTY AIRCRAFT INDICATOR OR
TRANSMITTER.
NOTE:
(4)
NOTE:
One full turn of oil pressure regulator adjusting
stud changes regulator setting approximately two
psig . Rotate clockwise to i ncrease or counterclockwise to decrease. Adju sting stud depth in
oil pump body does not change when adjusted.
Note oil pressure indication. If indication is not within steadystate operation l imi ts specifi ed in Table 501, loosen locknut and
adjust oi l pump pressure regulator adjusting stud (figure 510 ) t o
obtain 40 to 45 psig oil pressure i ndi cation.
If proper adjustment cannot be obtai ned, pressure regulator bypass valve may be sticking. Refer to Light
Maintenance Manual, Chapter/Section/Subject 79-20-03,
MAINTENANCE PRACTICES for pressure regu lator repair, if
applicable.
Refer to STANDARD PRACTICES for general torque values.
Add frictional drag (run-down) torque of selflocking
devices to recorrmended va l ue s.
(5)
Shut down engine. Tighten locknut on pressure regulator adjusting
stud to torque of 30 inch-pounds without changing adjusting stud
position, then insta ll lockwire on l ocknut .
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OIL PRESSURE REGULATOR
/ADJUSTING STUD
F-48A-154
Oil Pressure Regulator
Figure 510
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10. Thi s paragraph i s not used
11 . Engine Calibrati on Run Procedure
NOTE:
A.
Perform t he fo ll owing procedure as required i n Light
Maintenance Manual, Chapter/Section/Subject 72-00-00 ,
and at any time degr adati on of engine performance i s
suspec ted. Recorded paramet er s of ca l i brat ion run may
be comp ared with dat a f rom earli er t est run s , and with
factory data by contacting Garrett Cust omer Ser vice
Engineering. Refer to TROUBLE SHOOTING if engine operating limits prevent performance of the f ollowing
procedures.
Prepare Engine for Calibration Run
CAUTION:
USE EXTREME CARE WHENEVER PLUG (5, FIGURE 512)
IS REMOVED TO PREVENT ANY DI RT OR FOREIGN MATTER FROM ENTERING PORT. FUNCTION OF AN INTERNAL FUEL CONTROL ORIFICE WILL BE AFFECTED BY
ANY CONTAMINATION ENTERING PORT.
(1) Remove plug (5, figure 51 2). Discard packing (10).
(2)
Connect a Oto 250 psig pressure gage to control pneumatic pres sure port for monitoring engine P3 pressure. Connect gage in manner which will allow monitoring while engine is running.
(3)
Ensure aircraft instrumentation for engine Nl, N2, and ITT indi cations are properly calibrated and readout accuracy is as specified
by Aircraft Maintenance Manual.
B. Perform Calibration Run
(1) Turn aircraft to position engine inlet into wind. Leave all systems using engine bleed air turned off throughout the f oll owi ng
procedure.
(2)
Record outside air temperature (OAT), pressure altitude , engine
serial number, and aircraft serial number, (Set altimet er to 29.92
in. Hg to read pressure altitude directly.) Record normal mode
maximum Nl for ambient conditions as specified in Aircraft Fl ight
Manual. (See figure 513 for sample data recording form. )
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ff [731-2-lC
FUEL CONTROL
I
CONTROL PNEUMATIC PRESSURE (PC) PORT
/PRESSURE LIMITER VALVE ASSEMBLY
I
">-.)~
10
/
5
\
~-~
5.
';J~
-V
PLUG (REPORT NO. 73-21-01)
E-48A-963
10.
PACKING (S9412-552)
Connecting P3 Line Pressure Gage
Figure 512
NOTE:
Figure 511 is not used
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TFE7 31-2-1C
TFE7Ji ENGINE CALIBRATI ON RUN DATA SHEET
DATE
AIRCRAFT SERIAL NO.
ENGINE TIME SINCE NEVI
ENGINE SERIAL NO.
ENGINE CYCLES SINCE NEW
OAT _ _ _
PRESSURE ALTIT UDE (SET ALTIMETER
TO 29 . 92 IN. HG. I
MAX Ni FOR AMBIENT CONDITIONS
PER AIRCRAFT FLIGHT MANUAL
MANUAL /I/ODE
Ni AT :
NORMAL MODE Ni AT :
ENGINE PARAMETER
MAXIMUM
2~o BELC'N 4 °0 BELOW 6°0 BELOW
MA X
MAX
MAX
BELOV/
MAX NCRMAL
MODE Ni
4 °0
IDlf
Ni (AIRCRAFT INDICATOR)
N2 (AIRCRAFT INDICATOR \
ITT (AI RCRAFT INDICATOR\
FUEL FLOW (AIRCRAFT INDICATOR\
-
Oil PRESSURE (AIRCRAFT INDICATOR\
C ll TEMPERATURE (AIRCRAFT INDICATOR)
P3 /TEST GAGE PSIGl
ROLL DOWN TIME: Ni
; N2
REMARKS:
MECHANIC
INSPECTOR
G -48A- 555
Engine Calibration Run Data Sheet
Figure 513
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WARNING:
11.
B.
AREAS IN PROXIMITY OF ENGINE INLET AND EXHAUST
ARE EXTREMELY HAZARDOUS TO PERSONN EL WHEN ENGINES ARE OPERATING. PERSONNEL SHALL CLEAR
THESE AREAS DURING ENGI NE START AND OPERATION
TO AVOID INJURY.
(3) Perform normal engine start and accelerate to idle speed in accordance with Aircraft Flight Manual .
CAUTION:
DO NOT EXCEED ENGINE OPERATING LIMITS WHEN
PERFORMING THE FOLLOWING STEPS.
(4)
Advance power lever to maximum. Operate engine at maximum power
lever angle for two minutes to stabilize conditions.
(5)
Record the following data.
recording form.)
(6)
(See figure 513 for sample data
(a)
Nl, N2, ITT, and fuel flow from cockpit indi cators.
(b)
P3 pressure from gage install ed in step A. (2).
Retard power lever to reduce Nl two percent from maximum value
recorded in step (5). Maintain Nl at this point for two minutes
to stabilize conditions, then record data as specified in step
(5).
(7)
Retard power lever to reduce Nl four percent from maximum value
recorded in step (5). Maintain Nl at this point for two minutes
to stabilize conditions, then record data as specified in step
(5).
(8)
Retard power lever to reduce Nl six percent from maximum value
recorded in step (5) . Maintain Nl at this point for two minutes
to stabilize conditions, then record data as specified in step
(5).
(9)
Retard power lever to idle position. Allow two minutes to stabil ize condition, then record data as specified in step (5).
(10) De-energize electronic computer by turning cockpit on/off switch
to off.
CAUTION:
(11)
DO NOT EXCEED ENGINE OPERATING LIMITS WHEN
PERFORMING THE FOLLOWING STEPS.
Slowly advance power lever to obtain four percent less Nl than
maximum Nl recorded in step (5). Ensure ITT limit i s not
exceeded. Allow two minutes to stabilize conditions, then record
data as specified in step (5).
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11.
8.
(12) Retard power lever to idle pos ition. Perform normal engi ne shutdown in accordance with Aircraft Flight Manu al. Record r oll -down
times for Nl and N2.
(13) Disconnect P3 gage installed at control pneumati c pressure port
on fue 1 contra l.
(14)
Install new packing (10, figure 512) on plug (5).
(15)
Install plug (5), tighten to torque value of 30 inch-pounds , and
lockwire.
(16)
Maintain data recorded in the previous steps with permanent engine records. If comparison of recorded data with factory data
is desired, contact Garrett Customer Service Engineering.
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TFf7 31-2-lC
CHAPTER 72
GENERAL - I NSPECT ION/CHECK
TABLE OF CONTENTS
CHAPTER/
SECTION/
SUBJECT
SUBJECT
ENGINE
72-00-00
INSPECTION/C HECK
General
Pre- Instal lation Inspection
General Inspection
Pr e- Flight, Post Flight Inspection
Perform Pre-Flight Inspection
Perform Post Fl i ght Inspection
Per iodic Inspection Requirements
Routi ne Periodi c Inspection
Maj or Inspection
Chi p Detector Inspection
Remove Magneti c Plug
Inspect Chip Detector
Install Maqnetic Plug
Oil Filter Bypass Indicator Valve Inspect i on
Oil Filter Inspection
Remove Oil Filter
Inspect Oil Filter
Install Oil Filter
Spectrographic Oil Analysis Proqram (SOAP) Check
Transfer Gearbox Inspection
Remove Transfer Gearbox Cover
Inspect Interior of Transfer Gearbox
Install Transfer Gearbox Cover
Fuel Fi l ter Inspection
Remove Fuel Filter Element
Inspect Fuel Filter
Install Fuel Filter Element
Accessory Drives Splines Inspection
Fan Rotor Assembly Blades Inspection
Ignition S_ystem Check
Igni ter Plugs, and Igniter Lead Terminals Inspection
Remove Igniter Plugs
Inspect Igniter Plugs
Inspect Iqniter Lead Terminals
Inst al l at i on of Igniter Plugs
PAGE
601
601
1501
601
603
603
603
603
603
607
607
607
607
608
609
609
609
609
611
i
'°'
612
613
613
615
615
615
615
615
617
617
618
618
621
622
622
626
626
INSPECTION /CHECK
72- CONTENTS
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GENERAL - IN SPECTION/CHECK
1.
2.
General
A.
The inspections detai led in thi s section are t hose that can be accomplished without the aid of special tools or te st equipment by an
operator.
B.
Inspection procedures are those whi ch can be performed at field level.
All components or parts removed from the engine shall be given a careful
vi sual i nspect ion for general appearance and obvious damage. A component or part which shows evidence of damage beyond field level repair
capabiliti es shall be replaced and the damaged component or part sent to
an approved service center.
Pre-Installation Inspection
A.
Perform Pre-Installation Inspection
NOTE :
3.
Pre-installation i nspections are of a general nature
and are performed primarily to determine that engines
received from the factory or from overhaul facility
have suffered no shippin g or handling damage.
(1)
Check that lines are secure and free of dents.
(2)
Check that all required components, instruments, and controls are
included.
(3)
Check for tag to determine if engine has been preserved . If engine
has been preserved, proper depreservati on procedures shall be performed after installation. (Refer to Light Maintenance Manu al,
Chapter/Section/Subject 72 -00- 00, GENERAL - SERVICING . )
(4)
Ensure accessory drive spl ines of accessory drive gearbox are lu bricated in accordance with 8 , GENERAL - SERVICING.
General Inspection
A. Perform General Inspection
NOTE :
(1)
The following general in spec tions shall be performed
during any engine maintenance, as applicabl e, for t he
level of maintenance bei ng performed.
Visually inspect all access ible welded, brazed or soldered assemblies for security of joints.
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3.
A.
(2)
Visual ly inspect all accessible tubes for kinks, cracks, excessive
wear, signs of corrosion or other damage. Inspect all fittings for
broken threads, deterioration and cl eanli ness . Refer to Light
Maintenance Manual instructions for performing a vibrat ion check
any time evidence indicates poss ible excessive engine vibration
(cracked brackets, cracked or leaking plumbi ng li nes, etc.).
(3)
Inspect oil drained from engine. If excessive metal particles are
found, perform the following inspections.
(a)
(b)
(c)
Inspect magnetic plug for metal particles in accordance with
6, Chip i•ctector Inspection.
Inspect ci l filter bypass valve in accordance with 7, Oil
Filter Bypass Indicator Valve Inspection.
Remove, inspect, and install new oil filter in accordance with
8, Oil Filter Inspection.
(d)
Forward oil sample and removed oil filter to approved SOAP
laboratory in accordance with 9, Spectrographic Oil Analysis
Program (SOAP) Check.
(e)
Inspect interior of transfer gearbox for metal particles in
accordance with 10, Transfer Gearbox Inspection.
(4)
Check for fuel and oil leaks.
(5)
Check drains and vents for restrictions.
(6)
Check fan inlet for foreign material, obstructions, or damage.
(7)
Check inlet pressure and temperature sensor for security and evidence of damage or clogging.
NOTE:
If oil level has increased since l ast check, or if
the odor of fuel is detected in the oil, test for
presence of fuel in oil, in accordance with Light
Maintenance Manual, Chapter/Section/Subject, 7200-00, Inspection/Check.
(8)
Check oil level.
(9)
Check security of ignition wiring and connections.
(10)
Check for oil seal leakage arou nd starter-generator mount, aircraft
accessory mount and fuel pump mount.
(11)
Check exhaust outlet for damaged turbine blades and tailpipe for
contamination or damage.
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3.
A. (12)
(13)
4.
Check indicator p 1 , on fuel filter bypass indicator valve of fuel
pump. If indicator pin is actuated (extended), remove and clean or
replace fuel filter and clean filter cavity. Refer to 11, Fuel
Filter Inspection.
Check indicator pin on oi l filter bypass indicator valve (figure
602) in accordance with 7.
Pre-Flight, Post Flight Inspections
A.
B.
Perform Pre-Flight Inspection
(1)
Inspect air inlet and exhaust areas for obstruction and evidence of
foreign object damage. Remove any obstructions. Refer to Light
Maintenance Manual to repair or replace damaged engine components.
(2)
Inspect engine air inlet and exhaust areas for evidence of oil
leakage. If evidence of oil leakage is observed, determine cause
and correct in accordance with Light Maintenance Manual.
Perform Post Flight Inspection
(1)
•
Check level of engine lubricating oil and service if required.
(Refer to GtNERAL - SERVICING.)
(2) Check indicator pin on fuel filter bypass indicator valve of fuel
pump. If indicator pin is actuated (extended), remove and clean or
replace fuel filter and clean filter cavity. Refer to 11, Fuel
Filter Inspection.
(3) Check indicator pin on oil filter bypass indicator valve.
7, Oil Filter Bypass Indicator Valve Inspection.
5.
Refer to
Peroidic Inspection Requirements
NOTE:
A.
Periodic serv ic ing requirements, such as oil changing, are not
included in this section. Refer to GENERAL - SERVICING.
Routine Periodic Inspection
Inspections are recommended at intervals of engine operating hours specified in Table 601. Specified inspection intervals should not be exceeded by more than 10 hours of engine operation.
Upon completion of these inspections, make engi ne log book entry noting
engine operating time. Also, maintain inspection records with permanent
engine records. (Refer to Table 602 for sample form.)
•
Items normally replaced during these inspections are contained in Routine Periodic Inspection Kit, Part No. 658523-1. Nomenclature, part
number and quantity of each item contained in kit is provided in Table
603, with a reference to show application. The kit may be procured from
any Garrett approved serv ice center.
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Table 601.
Routine Peri odi c Inspect ion Requi r ements
Nature of Inspection
SOAP check (Refer to 9, Spectroqraphi c
Oil Analysis Program (SOAP) Check.)
NOTE:
Each
150 hr
Each
300 hr
X
SOAP has proved to be effective at other than the interval s
recommended in diagnosing engine problems. Therefore, it i s
recommended an oi l sample (with oil filter) be submitted for
analysis when an intermittent or change in engine operating
parameter occurs . Example: fluctuating oil pressure, change
in audible noi se level, etc.
SOAP check interval is based on engine operatinq hours since
any of the followinq maintenance activities: 011 fill at initial engine installation, l ast oil chanqe, or followinq
replacement of planet qear assembly or planet qearshaft, pini on
gearshaft, or ring gear. A SOAP sample (9, Spectrograohic Oil
Analysis Program (SOAP) Check) is reauired at 25 eA-qine operating hours following any of the specifi ed activities to establish a baseli ne for subsequent checks . Refer to GENERAL SERVICING for oil change requirement.
Chi p Detector - Remove and in spect.
(Refer to 6, Chip Detector Inspection.)
X
Accessory Drive Splines on Accessory Drive
Gearbox - Check for wear. (Refer to 12,
Accessory Drive Sp lines Inspection .)
X
Electrical Wiring and Connections Check for security and damage .
X
Fan Rotor Assembly Blades - Inspect for
f oreiqn object damage . (Refer to 13,
Fan Rotor Assemb ly Blades Ins pection.)
X
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Table 601.
Routine Periodic Insoection Requirements (Cont)
Nature of Inspection
(Pre SB 73-3016) Fuel Man ifol d Assembly Perform cross-flow check. (Refer to Ligh t
Maintenance Manual, Chapter/Section/Subject,
72-00-00, Inspection/Check for fuel manifold
assembly cross-fl ow check instructions . )
NOTE :
Each
J 'iO hr
X
(Pre SB 73-3016) Enqines with more than 700 total ooeratinq
hours shall perform initial check within the next 50 hours
of enqine operation. Subsequent checks should be oerformed
in conjunction with routine schedu l ed 150-hour insoections.
Ignition System - Inspect for serviceability.
(Refer to 14, Ignition System Check.)
X
Plumbing Lines and Connections - Check for
security, leaks, cracks, cuts, or rubbing.
X
Fuel Filter Element - Inspect and clean or
replace. (Refer to 11, Fuel Filter Inspection.)
NOTE:
Each
300 hr
X
Remove and clean or replace fuel fi lter element after ini tial 25 hours of engine operation.
Igniter Plugs and Igniter Lead Terminals - Remove
iqniter plugs and visually insoect igniter plugs
and igniter lead terminals. (Refer to 15, Igniter
Plugs and Igniter Lead Terminal s Inspection .)
X
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Table 602.
Routine Periodic Inspection Record Form
AIRCRAFT SERIAL NO._____
ENGINE SERIAL NO.__ _ _ _ _
DATE
TOTAL ENGINE OPERATING HOURS - - - - - MECHANIC
150 HOUR INSPECTION
(Refer to Table 601)
INSPECTOR
SOAP Check
Chip Detector
Accessory Drive Splines
Electrical Wiring Connectors
Fan Rotor Assembly Blades
Fuel Manifold Cross Flow
Ignition System
Plumbinq Lines, Connections
300 HOUR INSPECTI ON
(Refer t o Table 601}
Fuel Filter Element
Igniter Pluqs, Lead Terminals
Table 603.
Routine Periodic Inspection Kit Part No. 658S23-l
Nomenclature
Part No.
Qty
Application Reference
Packing
S9412-032
1
IPC Fi qure 24, 20
Packing
S9413-012
1
IPC Figure 44, 245
Packing
S9413-036
1
IPC Fiqure fiO, S5
Packing
S9413-557
1
IPC Fiqure 44, 255
Packing
S0413-015
1
IPC Fi gure 63, 2'1
Packinq
S9413-016
1
IPC Fiqure 63, 20
Packing
S9413-212
1
IPC Fiqure 24, 25
Packing
S9413-236
1
IPC Fiqure 64, 80
Gasket
362-509-9002
2
IPC Fiqure 30, 75, 110
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Tl ·731-2-lC
5.
B.
Major Inspection
Refer to Service Bulletin 72-3105 for spec ified interval s for major
periodic inspections .
Refer to Li ght Maintenance Manual, Chapter/Section/Subject 72-00-00,
INSPECTION/CHECK for l isting of major peroidic inspection requirements.
6. Chip Detector Inspection
A.
B.
Remove Magnetic Plug (240, figure 601 )
(1)
Disconnect electrical connector from magnetic plug (240) in accordance with Aircraft Maintenance Manual.
1
(2)
Hold check valve housing with wrench, use second wrench to remove
magnetic plug (240). Discard packing (245) .
Inspect Chip Detector
(1) Check magnetic plug (240) for metal particles.
(2)
(3)
If metal particles are evident, perform the following procedures .
(a)
Reset pin on oil filter bypass valve if extended.
(b)
Remove, inspect and replace oil filter in accordance with 8 ,
Oil Filter Inspection.
(c)
Perform SOAP check, and forward oil sample and removed oil
filter to approved SOAP laboratory in accordance with 9, Spectrographic Oil Analysis Program (SOAP) Check.
(d)
Inspect transfer gearbox for metal particles in accordance
with 10, Transfer Gearbox Inspection.
If metal particles are evident on magneti c plug only (240), none in
oil filter or transfer gearbox, perform the following procedures.
(a) Clean magnetic plug, and reinstall in accordance with 6.C.
Install Magnetic Plug.
(b)
Run engi ne throughout full power range in accordance with Aircraft Flight Manual for 15 minutes. (In cold weather operation, run engine more than 15 minutes if required to obtain
minimum oil temperature of 4C (40F). Determine if engine is
acceptable for continued operation (run did not produce recurranee of initial indication) by repeati ng magnetic plug, oil
filter bypass indi cator valve, SOAP, and transfer gearbox
inspections.
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6.
B.
(3)
(c)
Upon reaching t hree to five hours of engine ooeration following engine run and checks in step 6.B.( 3)(b), repeat maqnetic
plug, oil filter bypass indicator valve, SOAP, and tr ansfer
gearbox inspections.
C.
Install Magnetic Pluq (240)
(1)
Install new packing (245) on magneti c pluq (240).
(2)
Install magnetic plug {240) in check valve hou si no. Hold check
valve housing with wrench, and using a second wrench, tighten maonetic plug (240) to 35 to 40 inch -pounds torque and lockwire.
(3)
Connect electrical connector to maonetic plug (240) in accordance
with Aircraft Maintenance Manual. ·
CHECK VALVE
HOUSING
1
<'v
.A...-240
cl'.....-245
ROTATED
E-48A-962
240.
245 .
MAGNETIC PLUG (IPC FIG. 44)
Chip Detector
Figure 601
PACKING (SQ413-012)
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7.
Oil Filter Bypass Indicator Valve Inspection
A.
8.
Inspect Oil Filter Bypass Indi cator Valve
(1)
Check indicator pin on oil filter bypass vnlve (fiqure 602) .
(2)
If pin i s extended, reset pin, and perform the following
procedures.
(a)
Check magnetic plug of chip detector in accordance with 6,
Chip detector Inspection.
(b)
Remove, inspect and replace oil filter in accorrlance with 8,
Oil Filter Inspection.
(c)
Perform SOAP check, and forward oil sample and removed oil
filter to approved SOAP laboratory in accordance with 9, Soectrograohic Oil Analysis Prooram (SOAP) Check.
(d)
Inspect interior of transfer qearbox for metal particles in
accordance with 10, Transfer Gearbox Inspection.
Oil Filter Inspection
A. Remove Oil Filter
(1) Remove filter cap (40, figure 602). Discard oackina (55) .
(2)
B.
Remove filter (60) from accessory drive gearbox. If same filter
(60) is to be re-installed, inspect oackinq (70) (in place) in
filter . Do not remove packina (70) from filter (60) unless damaqe
is evident .
Inspect Oil Filter
(1)
Visually inspect oil filter for contamination. If any metal chios
are visible through oil filter mesh, perform the following
procedures.
(a) Reset pin on oil filter bypass indicator valve if extended.
(b)
Check magnetic plug of chip detector in accordance with~.
Chip Detector Inspection .
(c)
Perform SOAP check, and forward oil sample and removed oil
filter to approved laboratory in accordance with 9, Spectrographic Oil Analysis Pro9ram (SOAP) Check.
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\ R,/1
~
55
40
\
'
E-48A-966
FILTER CAP {IPC
FIG. 60)
55. PACKING (S9413-036)
40.
60. FILTER
70. PACKING (S9413-214) (INCLUDED
ON NEW FILTER)
Oil Filter Bypass Indicator
Valve, and Oil Filter
Figure 602
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8.
8.
C.
(1)
(d)
Inspect inter i or of transfer gearbox for metal particles in
accordance with 10, Transfer Gearbox Inspection.
(e)
If metal particles are evident on oil filter and maqnetic plug
only, none in transfer gearbox, start preliminary investiqation of source whil e await ing SOAP result~.
(2)
Visually inspect for cracks or break s in outer shell.
(3)
Replace damaged or contaminated filter.
Install Oil Filter
NOTE:
Packing (70, figure 602) is included as part of new filter
(60).
(1)
If filter (60) previously removed is to be reinstalled and packinq
(70) has been removed for damage, apply a liaht coat of engine oil
and install new packing (70). If installing filter (60), wi th
oacking (70) in place, apply a liqht coat of engine oil to internal
diameter of packing without removing packing.
(2)
Install filter (60), seating if firmly on tube in accessory drive
gearbox.
(3)
Apply a light coat of engine oil to new packing (55) and install
packing in packing groove of filter cap (40).
(4)
Apply a light coat of engine lubricatinq oil to threads of f ilter
cap (40) and thread cap onto oil filter cover. Hand tighten cap to
shoulder of cover. Do not tighten cap with wrench. Secure cap {40)
with 1ockwi re.
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9.
Spectrographic Oil Analysis Proqram (SOAP) Check
Table 603.
Equipment and Materials
Equipment or Material
Manufacturer
Sampling kit
PN 294199-1
The Garrett Turbine Engine Companv
A Divi sion of The Garrett Corporation
P.O. Box 29003, Phoenix, AZ 8~038
A.
Perform SOAP Check
CAUTION:
NOTE:
WHEN TAKING OIL SAMPLE FROM ENGINE FOR SOAP CHECK,
ENSURE ALL EQUIPMENT USED IS CLEAN AND NOT CONTAMINATED TO PREVENT OBTAINING FALSE INDICATION OF OIL
CONTAMINATION. ENSURE ENGINE OIL TEMPERATURE IS
HOT. TAKE SAMPLE WITHIN 15 MINUTES AFTER SHUTDOWN.
Whenever leakage of fuel into the oil system is
suspected (odor of fuel detected in oil or oil level
increases), perform Fuel-in-Oil Inspection in accordance with Light Maintenance Manual,
Chapter/Section/Subject 72-00-00, INSPECTION/CHECK.
Materials reauired for performinq SOAP check are contained in Sampling Kit, Part No. 294199-1, The sampling kit contains the following parts:
Plastic bottle (4-ounce)
Plastic bottle (32-ounce)
Blank data farm
SOAP instruction sheet
Filter, Part No. 3070945-1
Packing, Part No. S0413-036
Polyethylene hose (syphon) (1/4 by 24 inches)
Mailing address label
(1)
Remove oil tank filler plug (125 or 130, fiqure 301) and take an
oil analysis sample into clean four-ounce plastic bottle usinq si phon hose. A minimum of one fluid ounce is reauired for sample.
Reinstall oil tank filler plug (125 or 130).
(2)
Identifiy SOAP samp l e with the following data.
(a)
Date of sampl e.
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9.
A.
(2)
{b) Total engine run hours.
{c)
Oil brand and type.
{d)
Quantity oil added since last SOAP sample taken.
{e) Time {engine operatinq hours) since last oil chanoe.
{f)
Time {enqine ooeratinq hours) since last SOAP sample taken.
{g)
Time {engine ooerating hours) since last oil filter chanqe.
{h)
Engine model number and serial number.
{i)
Aircraft number.
(3)
Remove oil filter from enq ine. Refer to 8, Oil Filter Insoection.
Return removed oil filter with samplinq kit .
{4)
Install replacement oil filter on engine.
Inspection.
CAUTION:
(5)
10.
Refer to 8, Oil Filter
ENSURE THAT CONTAINERS {SMALL CONTAINER FOR
SOAP SAMPLE AND LARGE CONTAINER FOR OIL FILTER)
ARE PROPERLY SEALED TO PREVENT LEAKAGE DURING
SHIPMENT.
Prepare sampling kit for shipment in accordance with instructions
provided therein, and forward by most expeditious means to Garrett
Turbine Engine Company A Division of The Garrett Corporation P.O.
Box 5217, Manager Propulsion Field Service Department, Dept 77 -3S,
Phoenix, AZ 85010, ATTN: 628 SOAP PROGRAM or a Garrett approved
laboratory. Oil samples will be examined within 24 hours after
receipt of oil samples at Garrett Turbine Engine Company in
Phoenix, Arizona or a Garrett approved laboratory. If hioh wear is
indicated the user will be notified by telephone or telex within
the 24-hour period after such receipt of oil sample. If examination does not indicate a high wear rate the user will be notified
in writing through normal channels.
Transfer Gearbox Inspection
A. Remove Transfer Gearbox Cover
(1) Remove nuts (55, fiqure 603), washers (60) and cover (65).
(2)
Remove and discard packing (70).
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70
\
ROTATED
E-48A-96I
55.
nO.
NUT (IPC FIG. 64)
WASHER
65. TRANSFER GEARBOX COVER
70. PACKING (S9413-236)
Transfer Gearbox Cover
Fiqure 603
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10.
B.
C.
11.
Inspect Interior of Tra1,r;fer Gearbox
(1)
Check bevel gear teet h. There shal l be no abnormal wear pattern,
excessive wear , or chipped or broken teeth. Replace transfer
gearbox if requirements are not met. Refer to Light Mai ntenance
Manual, Chapter/Section/Subject, 72-60-03.
(2)
Check interior of transfer gearbox for metal particles. If metal
particles are present, check for source and repair in accordance
with Light Maintenance Manual.
Install Transfer Gearbox Cover
(1)
Install new packing (70) on cover (65).
(2)
Install cover (65) and secure with washers (60) and nuts (S5).
(3)
Tighten nuts (55) to torque value of 30 inch-pounds.
Fuel Filter Inspection
Table 604.
Materials and Compounds
Material or Compound
NOTE :
Manufacturer
Equivalent substitutes may be used for listed item.
Lubricating compound
(Liqui-Moly, Grade NV,
Thread Compound)
NOTE:
A.
Lockrey Co, Lubricants Div, Cedar
Shores, Southampton, NY 11968
The following Maintenance Practices do not reauire the
removal of the fuel pump.
Remove Fuel Filter Element
(1) Using wrench on square fitting of filter bowl cover (15, f igure
604), unscrew and remove filter bowl cover .
packing (20).
(2)
B.
Remove and discard
Remove fuel fi lter el ement (30) from filter cavity of fuel pump.
Remove and di scard packinq (2~).
Inspect Fuel Filter
(1)
Inspect filter bowl cover (15) for stripped or damaoed threads, or
any obvious damaqe.
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TFE731-?-1C
20
O _
-30
-15
E-48A-960
15. FILTER BOWL COVER
( I PC FIG. 24 )
20. PACK ING (S9412-032)
25.
30.
Fuel Filter
Fiqure n04
PACKING (SQ413-2J2)
FUEL FILTER ELEMENT
(8n57Ql-4)
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11 .
B.
(2)
Inspect fuel fi l ter element (30) for damage and cl eanli ness.
Refer to Cleaning/Painti ng.
(3) Replace items that do not meet i nspect requirements.
C.
Install Fuel Fil ter Element
(See f igure 604 )
(1)
Install new packings (20, 25) on fu el fi lter element (30) and
fi lter bowl cover (15) .
(2)
Install f uel f i lter element (30) in fi l t er cavity of fuel pump.
(3)
Coat threads of filter bowl cover (15) with light coat of lubri cating compound (Liqui-Moly, Grade NV, thread compound) . Install
filter bowl cover (15), tighten to torque va lue of 40 inch-pounds
and lockwire .
12. Accessory Drive Splines Inspection
Table 605 . Materials and Compounds
Material or Compound
NOTE:
Manufacturer
Equivalent substitutes may be used for listed items.
Solvent (Shell 360)
A.
Shel l Oil Co, 50 W50th St , New York,
NY 10020
Inspect and Lubricate Accessory Drive Splines of Accessory Dr ive Gearbox
(1)
Remove airframe-furni s hed accessor.ies from dri ve pads on forwar d
face of accessory dri ve gearbox in accordance with Ai r craft Mai ntenance Manual.
(2)
Clean splines on accessory drive gearbox and splines on removed
accessory with solvent (Shell 360}.
(3)
Dry splines using a directed air blast of cl ean compressed ai r .
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12.
13.
A.
{4)
Inspect splines on accessory drive qearbox for wear. Maximum allowable depth of internal sp line wear, measured at pitch line of
tooth, is a nominal 0.010 inch . Determine wear depth by comparing
maximum wear area on spline with end where there is no wear. Thi s
11
no wear" area i s normally at extreme aft end of spline where
there is no enqaqement with mating spline of accessory. If allowable wear limit is exceeded, remove and replace gearshaft as
necessary in accordance with Liqht Maintenance Manual,
Chapter/Section/Subject, 72-60-02.
{5)
Lubricate splines in accordance with 8, Servicinq.
{6)
Install accessories on forward face of accessory drive qearbox in
accordance with Aircraft Maintenance Manual.
Fan Rotor Assembly Blades Inspection
A.
Inspect Fan Rotor Assembly Blades
NOTE:
Presence of oil, dirt, salt, or other contamination on fan blades indicates need to perform compressor li quid cleaning procedure. Refer to
Light Maintenance Manual, Chapter/Section/Subject
72-00-00, General - Servicinq.
{1) Check fan blades for foreiqn object damage, erosion, nicks,
cracks, or distortion which may affect balance or blade security.
Rotate fan rotor assembly to check all fan rotor assembly blades.
14.
{2)
If inspection requirements of step {l) are not met, repair or
replace blades of the fan rotor assembly in accordance with Liqht
Maintenance Manual, Chapter/Section/Subject, 72-70-03.
(3)
If foreiqn object damage is evident on any fan blades, perform
borescope inspection on first-staqe compressor blades in accordance with Light Maintenance Manual, Chapter/Section/Subject, 7200-00, Inspection/Check.
Iqnition System Check
A.
Check Ignition System Operation
(1)
Shut off electrical supply to engine.
CAUTION:
BENDING IGNITER LEADS WHEN DISCONNECTING FROM IGNITION UNIT WILL CAUSE DAMAGE TO INTERNAL INSULATION
OF IGNITER LEADS. TO AVOID BENDING IGNITER LEADS,
REMOVE IGNITION UNIT MOUNTING BOLTS BEFORE DISCONNECTING IGNITER LEADS FROM IGNITION UNIT.
(2) Remove bolts (5, fiqure 605) and washers (10, 15).
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TF E731-2-1C
A
35
\
~~
'
'<>-.. ) ,/
~~¥f$~~-40
s
~,
/ti'
~
)
/
' s
'-10
10 '
\
20
22
27
_1
. -30
\ (\.. /
•
-~
.JO..-_, _ /
A
E-48A-959
5. BOLT (IPC FIG. 29)
10. WASHER
J.5 . WASHER
20.
IGNITER LEAD
22 .
IGNITER LEAD
IGNITER LEAD
27 . IGNITER LEAD
30 . IG~ITION UNIT
35. NUT
40. BOLT
25.
Ignition System Check
Figure 605
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TFE731-2- 1C
14.
A.
(3)
Disconnect igniter lead (25) from connector on iqnition unit (30).
(3a)
When iqniter l eads with restraining cables are used, remove nuts
(35) and bolts (40).
WARNING:
ENSURE GOOD ELECTRICAL CONNECTIONS ARE MADE
WHEN PERFORMING THE FOLLOWING STEPS. IF IGNITION UNIT IS NOT BOLTED TO ENGINE, OR IF FABRICATED GROUND LEAD IS NOT SECURELY CONNECTED, ELECTRICAL ARCING WILL CAUSE A FIRE
HAZARD. POOR CONNECTIONS WITH FABRICATED
GROUND MAY DAMAGE CONNECTOR ON IGNITION UNIT .
(4)
Reinstall and tighten one mountinq bolt (5) to provide good electrical ground for ignition unit (30).
(5)
Short internal high voltage socket of connector (for iqniter lead
(25)) on iqnition unit to ground. Ground connection may be accomplished by fabricatinq a ground lead terminated with a 10-40~60
terminal (The Bendix Corp, Electrical Components Division, Sherman
Avenue, Sidney, NY 13838) for connection to ignition unit. Terminal contained in 3070873-1 iqniter lead oarts kit may be used in
lieu of 10-40560 terminal.
(6)
Perform an engine start in accordance with Aircraft Flight Manual.
If unable to start engine, iqniter pluq at 6 o.clock position on
plenum case is not firinq prooerly. Test and Troubleshoot iqni tion system, and replace defective parts as required in accordance
with Light Maintenance Manual, Chapter/Section/Subject 74-00-01.
(7)
Shut down engine, and shut off electrical supply to engine.
(8)
Remove bolt (5), and disconnect ground lead, connPcted in step
(5), from ignition unit (30).
(9)
Reconnect igniter lead (25) to iqnition unit (30), and tighten
connector of igniter lead (25) finger tiaht .
(10)
Disconnect igniter lead (20) from connector on ignition unit.
Short internal high voltaae socket of connector (for iqniter lead
(20)) on iqnition unit (30) to ground with qround lead fabricated
in step (5).
( 11)
Reinstall and tighten one bolt (5) for ignition unit to provide
good electrical ground for ignition unit.
(12)
Tighten igniter lead (25) to torque of 150 inch-pounds.
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14.
A. (13)
Perform an engine start i n accordance with Aircraft Flioht Manual.
If unable to start enai ne , ianiter oluq at 7 a.clock oosition on
plenum case is not fi rina properly. Test and troubleshoot iqnition system, and replace defective oarts as renuired in accordance
with Light Maintenance Manual, Chapter/Section/Subject 74-00-01,
MAINTENANCE PRACTICES.
(14)
Shut down enoine, and shut off electrical suooly to engine.
(15)
Remove bolt (5), and disconnect qround lPad, connected in step
(10), from ignition unit (30).
CAUTION:
BENDING IGNITER LEADS WHEN CONNECTING TO IGNITION UNIT WILL CAUSE DAMAGE TO INTERNAL INSULATION OF IGNITER LEADS. DO NOT MOUNT IGNITION UNIT ON ENG INE BEFORE CONNECTING IGNITER
LEADS TO IGNITION UNIT.
(16) Reconnect iqniter lead (20) to connector on ionition unit (30) .
Tiqhten connector of ioniter l ead (20) finger tiaht .
(17)
Loosen connector of iqniter lead (25) at connector on iqnition
unit until just finoer tight.
(18)
Position ignition unit (30) on enqine. If necessary for ianition
unit to clear fan duct set , install washers (15 ) (maximum of one
at each mounting boss) between mounting bosses and ianition unit.
(19)
Ins ta ll washers (10) and bolts (5) and ti9hten to t orau e of 50
inch-pounds and lockwire .
(20)
Tighten igniter leads (20, 25) at iqntion unit to torque of 150
inch- pounds and lockwire.
(21)
When igniter leads with restraininq cables are used , secure terminals on restraining cables to fan duct set with nut ( 35) and bolt
( 40).
15.
Igniter Plugs and Igniter Lead Terminals Inspection
Table 60fi .
Material or Compound
NOTE:
Material s and Compounds
Manufacturer
Equivalent substitutes may be used for listed item.
High temperature compound
(Fel-Pro C-5A)
Fel-Pro Inc, Div of Felt Products
Mfq Co, 7450 N McCormick Blvd,
Skokie, IL 60076
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15 .
A.
B.
Remove Igniter Plugs
(1)
Shut off electrica l supply to enqine.
(2)
Remove door (35, fiqure 606) from bottom oanel.
(3)
Remove bolts (65, 110 , 120, fiqure 607), and remove iqn iter olugs
(70, 125) and gaskets (75 , 130).
( 4)
Disconnect iqniter lead terminals from igniter pluqs (70, 12s ) .
Inspect Igniter Plugs
NOTE:
An internal rattle may be evident when iqniter plug is
shaken. This is normal and is not cause for rejecting
igniter plug.
(1)
Vi sually inspect igniter plug for broken or missing oarts .
niter plug is broken or parts missing, replace pluq.
If i q-
(2) Visually inspect center electrode and outer shell f or erosion. If
electrode i s eroded 0.030 inch or more below end of ceramic insulator as shown in Figure 608 , replace plug. Uniform erosion on
electrode and outer shell is acceptable. Erosion of outer shell
in spark gap area shall not exceed 0. 330 inch diameter at insula-
tor surface.
(3)
Visually inspect ceramic insulator for cracks or chiooed area as
shown in Figure n08. Ensure normal ceramic insulator erosion is
not misinterpreted as cracking . Reolace igniter oluq if ceramic
insulator is damaged .
(4)
Visually inspect outer shell for burned or flowed metal as shown
in Figure 608. Replace plug if metal i s burned or flowed .
( 5)
Visually inspect grommet mating flanqe of igniter plug for
groovinq. If grooved on one side 0.030 inch deep or more, reolace
pluq.
(6)
Visually inspect for clogqed annul ar passage between i nsulator and
outer shell . If clogged, clean by abrasive blasting in accordance
with Light Maintenance Manual, Chapter/Section/Subj ect, 72-00-00,
GENERAL - CLEANING/PAI NTI NG, or r eplace plug.
(7 )
Visually inspect for cracked or broken ceramic and bent, burned,
or broken or loose pin in the ianiter pluq connector. Replace
damaged pluq.
(8)
Visually insoect for cracked flanges.
If cracked, replace olua .
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TF E731 - 2-lC
A
A
E-48A-967
DOOR (IPC FIG. 11)
35
· n
. 1 Door Remova 1/Installat,o
Bottom Pane Fioure 606
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TFE731-2-1C
E-<iSA-958
75.
110.
115.
120 .
125.
130.
20. IGNITER LEAD (IPC FIG. 30)
22. IGNITER LEAD
25. IGNITER LEAD
27. IGNITER LEAD
65. BOLT
70. IGNITER PLUG
Inaiter Plugs
Figure 607
GASKET (3n2-~09-QQQ2)
BOLT
CLAMP
BOLT
IGNITER PLUG
GASKET (362-509-9002)
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TFE731-2-1C
EROSION OF OUTER SHELL
AT INNER DIAMEHR SHALL
NOT EXCEED 0. 330 INCH
DIAMETER A T CERAMIC
I NSULATOR SURFACE.
CENTER ELECTRODE
CENTER ELECTRODE SHALL NOT EXCEED
0.030 INCH BELOW END OF CERAMIC.
OUTER SHELL
\
\
CERA/v\lC
INSULATOR
vl-- COOLI NG AIR
EXIT HOLES
COOLING AIR
INLET HOLES
UNUSED IGNITER
CRACKS I N CERA/v\lC
INSULATOR
CRACKED INSULATOR
NORMAt: EROS ION
BROKEN CERA/v\lC
INSULATOR
BROKEN INSULATOR
Iqniter Plug Inspection
Figure 608
ABNORMAL EROSION
PORTION OF OUTER
SHELL BURNED AWAY
BURNED OUTER SHEll
F-48A-151R3
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15. C.
Inspect Iqniter Lead Terminals
NOTE: Overheating of igniter lead terminals may be caused by
hot qas leakage, either around iqniter pluq qasket or
through igniter pluq in sulator . If evidence of
overheating or arcinq exists, replace igniter pluq and
gasket associated with damaqed iqniter lead and repair
or replace damaged igniter lead. ·
D.
(1)
Inspect igniter l ead terminals for deformation, cracks, chippinq,
or evidence of arcing. No damage is allowed.
(2)
Replace or repair igniter lead or lead terminals if inspection
requirements are not met. Refer to Light Maintenance Manual,
Chapter/Section/Subject, 74-00-01 for approved repairs.
Installation of Igniter Plugs
CAUTION : BOLTS SECURING IGNITER PLUGS SHALL BE
TIGHTENED ALTERNATELY IN TEN INCH-POUND INCREMENTS UNTIL FINAL TORQUE OF 50 INCH-POUNDS IS
OBTAINED TO PULL IGNITER PLUG IN PLACE EVENLY
WITHOUT COCKING. A GAP MAY EXIST UNDER IGNITER PLUG FLANGE AFTER TIGHTENING BOLTS. DO
NOT TIGHTEN BOLTS TO TORQUE OF MORE THAN 50
INCH-POUNDS AS IGNITER PLUG MOUNTING FLANGES
MAY BE CRACKED.
(1)
Install one new gasket on each igniter pluo. Install clamp on
longer igniter lead at position for bolt (lJO, fiqure 607). Coat
threads of bolts {65, 110, 120} with high temperature comoound
(Fel-Pro C5-A). Secure igniter plugs to enqine with attachinq
bolts (65, 110, 120). Alternately tighten bolts (65, 110, 120) in
ten inch-pound increments to torque of ~O inch-oounds, then lockwire bolts.
(2)
Install igniter leads on iqniter pluqs. Tighten connectors of ianiter l eads at igniter plugs to torque of 150 inch-pounds .
(3)
Install door (35, figure 606) to bottom panel.
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CHAPTER 72 - GENERAL - CLEANING/PAINTING
TABLE OF CONTENTS
SUBJECT
CHAPTER/
SECTION/
SUBJECT
ENGINE
72-00-00
CLEANING/PAINTING
General
Periodic Cleaning Procedures
Clean Standard Metallic Hardware
Fuel Filter Element Cleaning
Clean Fue l Filter Element by Sonic Method
Clean Fuel Filter Element Using Alternate Method
PAGE
701
702
702
702
702
703
CLEANING/PAINTING
72-CONTENTS
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GENERAL - CLEANING/PAINTING
1.
General
A.
The cl eani ng procedures detailed in this section are those that are
required to perform the in spection/check procedures outlined with thi s
publication.
B.
Table 701 provides a li st of all materials and compounds required to
Perform GENERAL - CLEANING/PAINTING.
Tabl e 701.
Material or Compound
NOTE:
Materials and Compounds
Manufacturer
Equivalent substitutes may be used for listed items.
Blackstone ultrasonic cleaner
(SP-103)
J . E. Phillips Co, Inc, P.O. Box 192,
JOn08 Culver Blvd, Culver City, CA
90230
Cleaner (Dowclene)
Dow Corninq Corp, S Saginaw Rd, Midland,
MI 48640
Electrocleaner
(Wyandotte FS)
Wyandotte Chemicals Corp, Wyandotte,
MI 48192
Muriatic acid (35 oercent
HCL, Conrnercial Grade)
Commercially avai lable
Rust stripper
(Oakite Rust Stripper)
Oakite Products Inc, 50 Valley Rd,
Berkeley Heiqhts, NJ 07922
Solvent (Shell 360)
Shell Oil Co , 50 W50th St, New York
NY 10020
So lvent, Stoddard
(Federal Specification
P-D-680, Type I)
Commerc i ally available
72 -00-00
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TFE731-2-JC
2.
Periodic Cleaning Procedures
A.
Clean Standard Metallic Hardware
Clean al l standard hardware with solvent, Stoddard (Federal Specification P-0-680, Type I), then dry with low pressure compressed air .
WARNING:
3.
CLEANING SHALL BE PERFORMED IN A CLEAN, WELL-VENTILATED
ROOM. RUBBER GLOVES AND PROTECTIVE CLOTHI NG SHALL BE
WORN . EXTINGUISHERS AND VAT OR TANK COVERS SHALL BE ON
HANO IN CASE OF FIRE .
Fuel Filter Element Cleaning
NOTE:
A.
Filter element of fuel pump may be cleaned by diooinq
in solvent (Shell 360) and dried with filtered compressed air . However, the sonic cleaninq method should
be employed for a thorough cl eaninq. If sonic cleaninq
eauipment is not available, use alternate method
described below.
Clean Fue1 Filter Element By Sonic Method
NOTE
Beaker is used to conserve cleaner (Dowclene).
Use tap water as transmi tting fluid in sonic
cleaner (SP-103).
(1)
Place filter element in beaker of cleaner (Dowclene). Orient
filter element so open end is uo. Level of cleaner in beaker shall
be below open end of filt er. Place beaker in soni c cleaner .
(2)
Operate sonic cleaner with filter element for five (~) minutes.
Cleaner will become dirty.
(3)
Discard dirty cleaner and rinse filter element and beaker with new
c l eaner usinq plastic squeeze bottle.
(4)
Refill beaker with new cleaner and operate sonic cleaner for five
(5) additional minutes.
(5)
Repeat steps (3) and (4) until cleaner remain s clean after a five
(5) minute operation period.
(6)
Remove filter element and blow dry us inq clean air supply.
(7)
Althouah there may be no apoarent damaqe to oackinq installed in
neck of filter element, replace packing after completion of sonic
clean inq.
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2.
8.
Clean Fuel Filter El em~~t Us inq Alternate Method
(1)
Remove packinq and thoroughly deqrease fuel filter element in cold
solvent, Stoddard (Federal Specif i cation P-0-680, Type I).
(2)
Prepare a solution of rust stripper (Oakite Rust Stripoer) by combining three to five pounds of rust stripper to each qal l on of
water. Maintain prepared solut ion at 72 to 82C (162 to 180F). Employ air agitation to keep sol ution in suspension.
(3)
Soak fuel filter element in ru st stripper (Oakite Rust Stripper)
solution for 30 minutes.
(4)
Remove fuel filter element from solution and rinse thoroughly with
clean water.
(5)
Prepare solution of electrocleaner (Wyandotte FS) by combininq nine
ounces of electrocleaner to each gallon of water. Maintain solution at 22 to 34C (72 to 93F). Inmerse fuel filter element i n
electrocleaner solution for four to s i x minutes. Durino th is
period fuel filter element shall be made an anode for one to two
minutes at a potential of four to seven volts de. Rinse fuel
filter element in cold running tap water.
(6)
Immerse fuel filter element in equal parts muriatic acid (35 percent HCL) and water, by volume, at room temperature for one-half to
one minute. Rinse fuel filter element thorouQhly in cold running
tap water.
(7)
Irrrnerse fuel filter element in electrocleaner solution preoared in
step (5) maintained at temperature of 22 to 34C (72 to 93F) for
four to six minutes. Rinse in cold runnino tap water.
(8)
Rinse fuel filter element in clean hot water. Dry fuel filter element with filtered compressed air. If cleaned fuel filter el ement
is not to be installed i111Tiediately, place in clean container.
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SERVICE MANUAL
TFE731 -2 -1 C
CHAPTER 72 - APPROVED REPAIRS
TABLE OF CONTENTS
SUBJECT
CHAPTER/
SECTION/
SUBJECT
ENGINE
72 - 00 -00
APPROVED REPAIRS
General
PAGE
801
APPROVED REPAIRS
72-CONTENTS
Apr 15/81
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srnvr cE MANUAL
TIT 731-?-JC
GEN[ IU\L - APPROVED REPAIRS
1.
General
Approved repair procedures res ultinq from unscheduled i nspections or malfunctioninq components are not. provided 1n thi~ oublication. Refer to Ma i nt enance Manua l, Report No. 72-02-02.
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TFE731-2-1C
CHAPTER 72 - MI CROF ICHE
TABLE OF CONTENTS
SUBJECT
CHAPTER/
SECTION/
SUBJECT
ENGINE
72-00-00
MICROFICHE
General
Revision Service
Equipment
Readers and Reader/Printers
Filing and Storing Systems
How to Use Garrett Microfiche
The Microfiche Sheet
Microfiche Title Block
Microfiche 11 Eyeball 11 Indicators
Microfiche Included with Service Manual
PAGE
901
901
901
901
901
901
902
902
902
902
902
MICROFICHE
72 -CONTENTS
Apr 15/81
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G1 XERAL - MICROFICHE
1.
Gener al
A.
2.
Revi sion Service
A.
3.
Gar rett techn ical pub lications ar e now bei ng furnis hed in microfiche
form. As with most changes, t his change wil l require some adjustments
by t he users of the publications . The many advantages of microfiche
wi l l out weigh inconven i ences encountered dur ing t he initial transition
fr om the pr i nted publi cat i on to the microfic he form. Although a few
probl ems are expect ed for t hose i nexper ienced with microfiche, acceptance of the mi crofi che f orm is important t o i t s successful use. A few
points are emphas ized i n the f ol l owi ng paragraphs which should smooth
the initial trans ition to the use of Garret t microfiche publications.
Microfiche will vastly reduce the time required t o mai ntain the technic al library. The time consuming task of inserting new r evision pages
into a printed publication is not requ i r ed with mi cr of iche, since each
revis i on to a microfiche publicat i on i s compl ete with in i t self - the entire publi cation is refilmed. Whenever a revi sion to a publication is
received, all of the old microfi che sheets of the publication are
replaced.
Equipment
A. A microfiche reader or reader/printer i s requ i red i n the use of micro-
fiche publications. To obtain a single ful l si ze page from a mi crofiche
sheet, a microfiche printer i s requ i red. For users not already using
microfiche publications, this requires a new piece of equi pment .
8.
Readers and Reader/Printers . All Garrett mi crofi che is produced at a
24:l ratio of reduction. This requires that a len s wi th a cor r esponding
24:1 ratio be used in the reader and reader/ pri nter. The number and
variety of readers and reader/printers available throughout the industry
is quite large. Most are either equipped with a 24: 1 l ens or may have
on installed. Power requirements~ methods of holding the microfiche
sheet, projection technique, and any special control s available vary
substantially from model to model. The proper reduct ion ratio (24 :l )
lens, however, is necessary for use with Garrett mi crof iche .
C.
Fili ng and Storing Systems. Many different products are marked for the
filing and storing of microfiche. Inexpensive holder panels ar e available which can be kept in a three-ring binder. Each s i de of a panel
provides several filing slots . When a single mi crofi che sheet is filed
i n each slot, the tit le blocks of all sheets are visible t o provide easy
handling, indexing, and access.
72-00-00
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TFE73J - ~-1C
4.
How to Use Garrett Microfiche
A.
(See figur e 1)
The Microfi che Sheet. Each mi crof iche sheet carries a title block at
the top of the sheet for identification, and 98 frames (seven rows of 14
frames each). The 98 frames are filmed pages of the publication. At
the beginning of primary sections, eyeball indicators are provided to
subdivide the contents of the publication.
11
B.
Microfiche Title Block. The title block at the top of each microfiche
sheet identifies the equipment covered by the publication, the publication type (illustrated parts catalog, maintenance manual, etc.), the
report number of the publication, the contents of the individual microfiche sheet, the revision number and date of the publication, and a
sequence number for the microfiche sheet in the package (FICHE NO. XXX).
Each sheet has an individual sequence number. The first sheet of the
microfiche publication carries a terminal sheet number to notify the
user of the total number of microfiche sheets in the package (FICHE NO.
1 OF 10, for example).
C.
Microfiche Eyebal1 Indicators. Special titles are filmed within the
microfiche sheet to subdivide the contents of the publication. Each
title frame occupies the space for a printed page and carries a title
large enough to be read without the aid of a microfiche reader. The
title frames are referred to as eyeball indicators because only the
user's unaided eye is required to read the frame. The microfiche sheets
include eyeball indicators at the same locations as plastic tabs are included in the printed publications to identify the start of primary
sec itons. A table of contents is included at the beginning of each primary section of the publication to specify the detailed contents of the
section. When a section of the publication starts on one microfiche
sheet and carries over to a subsequent sheet, an eyeball indicator is
used on the first frame of the subsequent sheet to indicate a
continuation.
11
11
11
5.
11
11
Microfiche Included with Service Manual
A.
Microfiche is provided on the Illustrated Parts Catalog and Light Maintenance Manual for your information and convenience. (See envelopes at
end of manual).
B.
Hard copies of the Illustrated Parts Catalog and/or the Light Maintenance Manual will be provided at a nominal charge upon request. These
publications may be obta ined by contacting Garrett Turbine Engine Company A Division of The Garrett Corporation, P.O. Box 29003, Phoenix, AZ
85038, Attn: Technical Data Destribution, Dept 77-7-601, (602) 2674807.
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SERVICE MANUAL
TF u' 31-2-1C
SEQUENCE NI.JM&ER
Of MICROFICHE
SHEETS
MO0El NO. Tffnl-2
ruUOFAN •en ENGINE
l,C n-00,.-71
F"RCNT M4TT£1
I ~•u Of C':lNT!Nn
tNftiOOUCTtCN
NUMUIU.l INDEX
f !~f' 1 OF 10
>(\ l.
.,.,._, )1 ~I
~~~OR t.:::::j~~□□□□□□□□□□□
□□□□0D□EJ□□□□□□
□□□□□□□□□□□□□□
□□□□□EJ□□□□□□□□
□□□□□□□□□□□□□□ J
□□□□□□□□□□□□□□
□□□□□□□□□□□□□□
.
.
tt Microfiche Publication
Typ,cal Garre .
Fi gure 901
X- 2l8
72-00-00
Page 903/904
Apr 15/81