EXPORT CONTROLLED RollsRoyce

250B17F SERIES OPERATION AND MAINTENANCE

ENGINE SERVICING
1. General
WARNING: FAILURE TO PROPERLY ASSEMBLE COMPONENTS OR PARTS OF THE ENGINE
COULD RESULT IN AN ENGINE FAILURE.
CAUTION: WHEN THE GAS PRODUCER FUEL CONTROL OR POWER TURBINE FUEL
GOVERNOR, ARE REMOVED FROM THE ENGINE, USE EXTREME CARE TO
PREVENT FOREIGN MATERIALS FROM ENTERING THE PNEUMATIC LINES OR
THE PORTS OF THE COMPONENT.
CAUTION: DURING OIL SERVICING OR ANY OTHER MAINTENANCE USE CARE TO ENSURE
THAT NO METAL CHIPS, PARTICLES, OR DEBRIS OF ANY KIND IS ALLOWED TO
ENTER THE ENGINE OIL SYSTEM.
CAUTION: USE PLASTIC OR RAWHIDE HAMMER HEADSNEVER METALWHEN DRIVING
ON ANY PART OF THE ENGINE. NEVER USE PLIERS ON NUTS AND BOLTS.
CAUTION: WHEN MARKING OR IDENTIFYING ANY PART SUBJECTED TO HIGH
TEMPERATURES, DO NOT USE ANY MARKING MATERIAL CONTAINING
GRAPHITE. (SEE TABLE 302).
CAUTION: THE COMPRESSORTOTURBINE COUPLING SHAFT IS A NITRIDED PART AND IS
SUSCEPTIBLE TO HANDLING DAMAGE. ANY HANDLING DAMAGE CAN RESULT IN
CRACK PROPAGATION. IF THE COUPLING IS DROPPED IT MUST BE PROCESSED
BY AN AUTHORIZED OVERHAUL SHOP PRIOR TO FURTHER SERVICE.
CAUTION: ALL ENGINE PARTS SHOULD BE CAREFULLY REEXAMINED FOR MISSING
COMPONENTS OR DAMAGE PRIOR TO FINAL ASSEMBLY OF THE PART.
CAUTION: REMOVAL AND INSTALLATION OF THE STARTER GENERATOR SHOULD BE
ACCOMPLISHED IN A CAREFUL MANNER TO PREVENT COMPONENT DAMAGE.
CONSULT AIRFRAME AND/OR STARTER GENERATOR MAINTENANCE MANUALS
FOR SPECIFIC GUIDELINES.
This section describes engine maintenance requirements. Maintenance functions are grouped by
component assembly or by system of the engine to which they are related.
Some general maintenance practices which do not apply to one specific system or component are
included in addition to a listing of special tools required at the maintenance level.
CAUTION: IF THE FUEL CONTROLTOOVERSPEED GOVERNORTO PROP GOVERNOR PY
LINE IS NOT REMOVED, RESIDUAL OIL WILL ENTER AND CONTAMINATE THE
FUEL CONTROL WHEN THE ENGINE IS TILTED OR INVERTED IN THE TURNOVER
STAND.
Use engine turnover stand 6795579 with 6798316 adapter, to support an engine removed from the
airframe for maintenance. Before installing the engine in the turnover stand, remove the fuel
controltogovernor Py line and cap the open fittings on the fuel control and both governors. Clean the
Py line and reinstall only after the engine is removed from the turnover stand.
2. Special Service Tools
The special service tools required for engine maintenance are as follows:

Tool No. Description

6795579 StandTurnover, Engine Assembly

Used to hold, support and rotate the engine assembly for installation and
removal of components.

6795588 WrenchHolding, 32/64 Pitch, 24 tooth spline

Holds the compressor rotor spur adapter gear shaft while installing or
removing compressor front and rear retaining nuts or adapter shaft nut. Also
used to hold the gas producer turbine shaft while installing or removing the
front and rear bearing nuts.

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Tool No. Description

6795590 PullerBearing, Gas Producer Turbine

Used to remove the No. 8 bearing and the gas producer front labyrinth seal.

6795597 WrenchSpanner, Torquemeter Shaft and Shaft Support Nuts

Used for installation and removal of the spanner nuts on the torquemeter shaft
support and support shaft. Used with 6795974 fixture.

6795614 Puller and PusherIdler Gear Support Shaft, Power and

Accessory Gearbox. Used to install and remove the idler gear support shafts.

6795966 FixtureAssembly, Compressor

Mounts on bench to support compressor assembly during assembly and
disassembly.

6795969 HolderTorquemeter Shaft Support

Used to install and remove the torquemeter shaft support and bearing at the
power and accessories gearbox cover.

6795974 FixtureAligning, Torquemeter Support Shaft

Used to hold and align the torquemeter support shaft while removing and
installing the torquemeter support shaft nut. Used with 6795597 wrench.

6795984 HolderPower Turbine Shaft

Used to hold the power turbine shaft during installation and removal of the
power turbine shaft ball bearing retaining nut. Used with 6795985 wrench.

6795985 WrenchPower Turbine Shaft Ball Bearing Retaining Nut

Used to install and remove the power turbine shaft ball bearing retaining nut.
Use with 6795984 holder.

6796918 DriftInstallation, Turbine and Exhaust Collector

Support Oil Bellows Seal
Used to install and guide the oil bellows seal into the turbine and exhaust
collector support.

6796920 PullerOil Jet, Gas Producer Bearing

Used to remove or install the gas producer ball bearing oil jet tube in the gas
producer support.

6796930 PlateInstallation, Power and Accessory Gearbox Bearings

Used to install the following bearings on their respective shafts: power turbine
governor and tachometer, gas turbine idler, oil pump idler, torquemeter
support, torquemeter shaft support, torquemeter piston, power turbine takeoff,
gas turbine fuel control, starter drive, accessories drive and fuel control drive.
Used with 6796946, 6796947, 6796948, and 6796949 drifts.

6796941 KitInstallation and Removal, Oil Seal

Used to install and remove liptype oil seals in the power and accessories
gearbox.

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Tool No. Description

6796946 DriftInstallation and Removal, Power and Accessory

Gearbox Bearings
Used to install or remove the following bearings: power turbine governor and
tachometer shaft, gas turbine idler shaft and oil pump idler shaft. Used to
remove the following bearings: gas turbine fuel control shaft, starter drive
shaft, accessory drive shaft and fuel pump drive shaft. Used with 6796950
bearing removal plate or 6796930 bearing installation plate.

6796947 DriftInstallation and Removal, Power and Accessory

Gearbox Torquemeter Bearings
Used to install or remove the torquemeter piston ball bearing, torquemeter
support shaft roller bearing, and torquemeter shaft support roller bearing.
Used with 6796950 bearing removal plate or 6796930 bearing installation
plate.

6796948 DriftInstallation and Removal, Power and Accessory

Gearbox Power Turbine Drive Bearings
Used to install or remove the power turbine takeoff drive shaft bearing and to
remove the power turbine main drive pinion bearing. Used with 6796950
bearing removal plate or 6796930 bearing installation plate.

6796949 DriftInstallation, Power and Accessory Gearbox Bearings

Used to install the following bearings on their respective shafts: gas turbine
fuel control, starter drive, accessories drive and fuel pump drive. Used with
6796930 bearing installation plate.

6796950 KitPuller, Power and Accessory Gearbox Bearing Removal

Used to remove the following bearings from their respective shafts: power
turbine governor and tachometer, gas turbine idler, oil pump idler, gas turbine
fuel control, starter drive, accessory drive, fuel pump drive, torquemeter
piston, torquemeter support, torquemeter shaft support, power turbine takeoff
drive and power turbine main drive pinion. Used with 6796946, 6796947, or
6796948 drifts.

6796966 PliersRetaining Ring, Fuel Control Drive Bearing

Used to collapse the snap ring retaining the fuel control drive gear and bearing
assembly during installation or removal.

6798045 WrenchHolding, Gas Producer Turbine

Used to support and hold the gas producer rotor while removing the firststage
turbine nozzle.

6798046 WrenchBearing Locknut, Gas Producer

Used to remove or install the gas producer turbine ball bearing locknut.
Use with 6798045 wrench.

6798047 WrenchOil Sump, Turbine

Used to remove or install the oil sump and nut assembly.

6798089 AdapterSupporting, Turbine Unit Assembly

Used to support the turbine assembly when removing the firststage turbine
nozzle or the oil bellows seal.

6798261 LiftEngine Assembly

Used to lift the engine assembly.

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Tool No. Description

6798292 WrenchGround Idle Adjusting

Used to adjust idle speed.

6798316 AdapterTurnover Stand

Used to adapt 6795579 engine turnover stand to the 250 turboprop engine.

6798807 CompressorLube Oil Filter Poppet Valve

Used to install poppet valve in filter housing.

6798860 PullerLube Oil Filter Cap

Removes the oil filter cap from the oil filter housing assembly.

6798927 CrimperLocknut, Compressor ImpellerAssembly and Turbine

Power Shaft
Used to crimp lock portion of spanner nut into spherical radius of shaft.

6798928 ProtectorPower Turbine Oil BellowsSeal Puller

Used to protect oil bellows seal face when removing oil bellows seal assembly.
Used with 6799973.

6799518 PullerGas Producer Ball Bearing Labyrinth Seal Assembly

Used to remove the ball bearing and oil seal from the gas producer turbine
support.

6799790 AdapterTurning, Engine

Used to turn the gear train when installing the turbine or compressor.

6799952 ClampInstallation, Compressor Discharge Air TubetoOuter

Combustion Case
Used to compress the steel seal ring when installing the compressor discharge
air tube in the combustion outer case. Two (2) required.

6799955 FixtureAssembly Turbine

Used to hold and support the gas producer turbine support.

6799973 PullerSeal, Power Turbine Bellows

Used to remove oil bellows seal from the turbine and exhaust collector sup-
port.

6872165 GageInternal Clearance, Helical Drive Gear

Used to check internal clearance of ball bearings after assembly to helical
drive gear.

6872541 CoverProtective, Power Turbine Support

Prevents entrance of foreign objects into the turbine area.

6872575 PinRigging, Coordinator Lever

Used to rig the propeller governor control cable.

6872646 GuideBearing, Spur Adapter Gearshaft

Used to remove or install the compressor assembly.

6872746 PullerPower Train Drive Gear Bearing

Used to remove bearings from forward and aft ends of power train drive gear.

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Tool No. Description

6872879 KitSpotfacing
Used to machine compressor mounting inserts in the gearbox to required
height.

6872880 FixtureChecking
Used to check height of compressor mounting inserts in the gearbox.

6872881 WrenchInsert
Used to remove or install compressor mounting inserts in the gearbox.

6872882 PullerTurbine Front (No. 5) Bearing

Used to remove No. 5 bearing from the turbine and exhaust collector support.

6872927 WrenchGearbox Flanged Studs

Used to install or remove gearbox studs at compressor mounting location.

6873066 FixtureCompressor Axis Alignment

Used to determine the correct quantity of shims required at the five mounting
pads of the compressor rear diffuser to properly align the compressor rotor
axis. Use with 13 clamp.

6886201 GuidePower Takeoff Roller Bearing

Used to guide power takeoff shaft through the forward roller bearing during
assembly of gearbox housing to cover.

6886204 KitProtector, Compressor Cleaning

Used to cap pressure probe elbows and bleed valve sensing lines and to hold
bleed valve in closed position during compressor cleaning.

6895538 PressGas Producer Turbine Rotor and Bearing

Used to remove the gas producer turbine rotor from the turbine support. Also
used to install the gas producer rear bearing and seal in the gas producer
turbine support.

6895957 Alignment ToolGearbox Oil Tube

Aligns oil tubes during assembly of gearbox cover to housing.

6897875 FixtureFuel Nozzle Holding

Used to hold nozzle during assembly/disassembly.

23003262 CrimperLocknut, Gas Producer Rear Bearing

Used to stake No. 8 bearing spanner nut into lock detent.

23003267 KitCleaning, Power Turbine Support and Oil Nozzle

Used to clean carbon from the power turbine support and oil nozzle.

23006778 GuideBearing Spur Adapter Gearshaft

Used to guide the SAG through the No. 2 1/2 bearing during installation of the
compressor on the power accessory gearbox.

23006785 Installation ToolORing, Spur Adapter Gearshaft

Used to install the Oring on the spur adapter gearshaft.

23007638 WrenchFuel Injector

Used to remove or install the fuel nozzle.

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Tool No. Description

23008725 PusherInstallation, Power Turbine Ball Bearing

Used to install the ball bearing on the power turbine shaft. Used with guide
(2) from 6796918 drift.

23030169 GuideSeal Installation, Starter Pad

Used to install seal in Wet starter pad.

23032992 BracketAccelerometer Mounting

Used to mount the accelerometer on the turbine and the compressor for
engine test and troubleshooting.

23032993 BracketAccelerometer Mounting, Power and Accessory Gearbox

Used to mount the accelerometer on the power and accessory gearbox for
engine test and troubleshooting.

23033027 PullerBearing and Mating Seal Race, Front Compressor

Removes the front compressor bearing and mating seal race from the first
stage compressor wheel.

23033030 DriftInstallation, Compressor Front Bearing Inner Race

and Seal
Seats the compressor front bearing inner race and seal on the compressor
rotor.

23033031 FixtureHolding, Front Bearing Housing

Holds the front bearing housing assembly while installing the front bearing
damper, and front bearing ring seal.
U/W 23033032 and 23033033

23033032 DriftCompressor Front Bearing Outer Race

Used to install the compressor front bearing outer race and compressor front
damper in the front bearing housing assembly. U/W 23033031

23033033 DriftGuided, Compressor Front Bearing Ring Seal

Installs the compressor front ring seal into the front bearing housing assembly.
U/W 23033031.

23033034 PullerCompressor Front Bearing Outer Race

Removes the compressor front bearing outer race and vibration damper
segments from the front bearing housing assembly.

23033035 PullerCompressor Front Bearing Ring Seal

Removes the front bearing ring seal from the front bearing housing assembly.

23034202 Test Set N2 Overspeed Control (250B17F/1 only)

Tests all function of N2 overspeed control.

2550678 ScrewdriverRestrictor, Fuel Control and Governor

Used to remove or install the Px and Py bleeds in the fuel control and the Pg
bleed in the governor.

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3. Consumable Materials
WARNING: EVEN THOUGH ROLLS--ROYCE HAS APPROVED THE CONSUMABLE MATERIALS
IN TABLE 301 FOR USE WITH ROLLS--ROYCE ENGINES, ROLLS--ROYCE ASSUMES
NO LIABILITY FOR INJURY TO PERSONNEL OR DAMAGE TO THE ENVIRONMENT
BY THEIR USE.
Refer to Table 301 for a summary of consumable materials used to maintain the engine. The
Acceptable Source column of the table lists suppliers for each item; any equivalent product is
acceptable. In determining whether or not an item is equivalent, the burden of proof rests with the
operator and his supplier, not with the engine manufacturer. Refer to Table 302 for a listing of pens and
pencils that are approved for marking on hot section parts.

Table 301

Summary of Consumable Materials

Item Material Use Acceptable Source

1 Engine oil Lubricate bearings, pack- Refer to Oil Specification, para 4.C.,
ings, etc. 72--00--00, Engine--Description and
Operation.
2 Carbon removal com- Clean aluminum--coated Gunk Hydroseal Decarbonizer
pound steel parts (MIL--C--25107).
Gunk Laboratories Inc.
630 North Harlem Ave.
Oak Park, Illinois 60302
3 Carbon solvent Cleaning fuel nozzle Penmul L460
Penetone Corp.
74 Hudson Avenue
Tenafly, NJ 07670

4 Cresol base cleaning Clean steel parts Formula No. 3097 (MIL--C--5546).
compound Turco Products Inc.
2400 South Main St.
Wilmington, California 90746

5 Rust preventive com- Coat steel parts after Anti--Corrode 204 (MIL--C--6529,
pound cleaning type 1).
Cities Service Oil Co.
P.O. Box 300
Tulsa, Oklahoma 74102
Shipping container bolts Valvoline TECTYL 890
Ashland Petroleum Company
Division of Ashland Oil Inc.
P. O. Box 391
Ashland, Kentucky 41101
Shipping container bolts Royco 103
Royal Lubricants Company Inc.
River Road
E. Hanover, N.J. 07936

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Table 301 (cont)

Item Material Use Acceptable Source

6 Preservation oil Fuel system preservation MILL6081, Grade 1010 or 1005

NATO Symbol Code 0132 and
0133
Bray K80, K877, K460
Bray Oil Company
1925 North Marina Ave.
Los Angeles, California 94804
McMillan Jet Engine Oil 1005 or 1010
McMillan Ring Free Oil Company,
Inc.
200 Petroleum Building
El Dorado, Arkansas 71730
Royco 460, 481
Royal Lubricants Company, Inc.
River Road
East Hanover, New Jersey 07936
Aeroshell Turbine Oil 2
Shell International Petroleum
Company Ltd.
Shell Centre
London SE1 7 NA
United Kingdom
No. 31100 (MILL6081,
grade 1010)
Atlantic Richfield Co.
260 South Broad Street
Philadelphia, Pennsylvania
19101
(or)
Gulfite 6 (MILL787OA)
Gulf Oil Corp.
439 7th Ave.
Philadelphia, Pennsylvania
15230
Pengard
Penetone Co. Ltd.
Bassington Industrial Estate
Cramlington Northunderland
United Kingdom
7 Cleaner Clean compressor airflow Turbine Cleaner No. 1191 or 715N
path, fuel nozzle, and SafetySolv (MILC43616).
burner drain valve The Brulin Corporation
2920 Dr. Andrew J. Brown Ave.
P.O. Box 270
Indianapolis, Indiana 46206

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Table 301 (cont)

Item Material Use Acceptable Source

NOTE: RollsRoyce strongly recommends strict adherence to the mixture ratios outlined by
each cleaner manufacturer. The mixture ratios do vary from manufacturer to
manufacturer and can be found on each container label. Strict adherence must be
followed to the application procedures described in this manual. This will prevent
compressor or engine and control system damage.
7 Cleaner (cont) Clean compressor airflow 2020 Plus (MILC43616)
path, fuel nozzle, and or B & B 3100
burner drain valve (cont) B&B Chemical Co. Inc.
P.O. Box 796
Miami, Florida 33166
Turco 4181
Turco Products, Inc.
Subsideriary of Elf Atochem
7320 Bolsa Ave.
Westminster, CA 926843600
Brulin 815
Brulin & Co.
P.O. Box 270
Indianapolis, IN 462060270
No. 5884
Turco Products
Division of Purex Corp.
24600 South Main Street
Carson, California 90746
Racasan 512M
Odex Racasan, Ltd.
Cromwell Road
Elesmere Port
South Wirral
L654DP, England
RMC
ECT, Inc.
771 First Ave.
King of Prussia, PA 19422
Aircraft skin cleaner. Used Turboclean 2
as compressor cleaner Kent Chemical Co., Ltd.
George House, Bridwell Lane
Tenterton, Kent TN306HS
England
Compressor wash Rochem GTE (Krankwash)
Rochem U.S. Inc.
589 Franklin Turnpike
Ridgewood, NJ 07450
Penair M5704
Penetone Corporation
74 Hudson Avenue
Tenefly, NJ 07670

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Table 301 (cont)

Item Material Use Acceptable Source

7 Cleaner (cont.) Compressor Wash (cont.) ARDROX 624
Brent Chemicals International
Ardox Division
Ridgeway, Iver, Buckinghamshire
SLO955
England
ARDROX 6345
Sure Chem Industries Pty., Ltd.
23 Amax Ave, Girraween,
New South Wales, 2145
ZOK 27
Airworthy LTD
Wedglen Industrial Estate
Midhurst Sussex
England G299RE

Turco 678310 & 50

Turco Products, Inc.
Subsidiary of ELF AUTOCHEM
7320 Bolsa Avenue
Westminster, CA 9268436000
B&B TC100N1
B&B Tritech, Inc.
Miami, FL 332660776
Ardox 6367 Turbo Clean 2
921 Sherwood Drive
Lake Bluff, IL 600440215
8 Sodium hydroxide and Cleaning Pc filter Commercial
phospheric acid
9 Perchlorethylene or or Cleaning Commercial
methylene chloride
10 Heat resistant paint Gearbox paint repair or Actithane WC100
galvanic corrosion protec- Saran Protective Coatings Co.
tion 17332 Shields
Detroit, Michigan 48212
11 Lacquer reducer Used with Actithane Actithane H251
WC100 Saran Protective Coatings Co.
17332 Shields
Detroit, Michigan 48212

12 Mineral spirits General cleaning Commercial

13 Chemical film Treat cleaned anodized ChemRite A22 (MILC5541).
aluminumalloy parts M and T Chemicals Inc.
Church St.
Matawan, New Jersey 07747

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Table 301 (cont)

Item Material Use Acceptable Source

14 Corrosion resistant alu- Gas producer and power SermeTel 196.

minum paint turbines supports Teleflex Inc.
P.O. Box 218
North Wales, Pennsylvania 19454
15 Lubricant Lubricate accessory Lubriplate 130A or 930AA.
splines Fiske Brothers Refining Co.
129 Lockwood
Newark, New Jersey 07105

ASTM No. 5
Sun Oil Co.
1608 Walnut Street
Philadelphia, Pennsylvania 19103
MILO6081
grade 1010 oil
Atlantic Refining Co.
260 South Broad Street
Philadelphia, Pennsylvania 19101
16 Grease Seal and bearing installa- No. 6249 (MILG23827).
tion and assembly aid Shell Oil Co.
Shell Building
Houston, Texas 77002
ROYCO HF825
Royal Lubricants Co., Inc.
280 Complex,
101 Eisenhower Parkway
Roseland, New Jersey 07068
Starter generator gear- Aeroshell No. 22 (MILG81322)
shaft, fuel control, and Shell Oil Co., Shell Building
power turbine governor Houston, Texas 77002
splines
Mobil No. 28 (MILG81322)
Mobil Oil Corp., P.O. Box 3311
Beaumont, Texas 77704
Single element fuel pump Sundstrand P/N 718050 or 71850
drive shaft internal splines (recommended)
(external splines require Sundstrand Corp.
engine oil) 4751 Harrison Ave.
Rockford, Illinois 61108
Lubricate packings in fuel ASTM No. 5 Oil
control fuel or air passages Sun Oil Company
1608 Walnut Street
Philadelphia, Pennsylvania
19103

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Table 301 (cont)

Item Material Use Acceptable Source

16 Grease (cont) Lubricate packings in fuel Alternates to ASTM No. 5 Oil:
control fuel or air passages 1. 45--55% fuel (MIL--C--7024B,
(cont) Type II) mixed with 45--
55% STP Oil Treatment
2. MIL--D--6081, Grade 1010
oil
Fuel pump and fuel control Plastilube No. 3
drive shafts Warren Refining Division
Parr Inc.
5151 Denison Ave.
Cleveland, Ohio 44102
17 Anti--seize Pc filter threads and exter- DC 550 Fluid
nal threads--protects up to Dow Corning Corp.
232C (450F) South Saginaw Road
Midland, Michigan 48641
Hot section external Never--Seez Nickel Special (NSN165)
threads, compressor tie Bostik, Emhart Chemical Group
bolt (not to be used where Boston Street
exposed to the engine oil Middleton, MA 01949
system) (or)
LOCTITE Nickel Anti--Seize (77164)
Henkel Corp.
1001 Trout Brook Crossing
Rocky Hill, CT 06067
External threads not ex- CP--63 (MIL--L--25681B)
posed to oil system. Pro- E/M Lubricants Inc.
tects to 760C (1400F) P.O. Box 2200
Highway 52, N.W.
West Lafayette, Indiana 47906
18 Calibration fluid Cleaning fuel nozzle tips Stoddard solvent, refined kerosene
(MIL--F--7024, type II) 300--400 of
boiling range.
19 Corrosion compound Inhibiting fingerprint corro- Non--Rust X--210
sion Daubert Chemical Co., Inc.
4700 S. Central Ave.
Chicago, Illinois 60038
20 Weld rod First--stage turbine nozzle X--40 (EMS 70175) or alternate
Haynes 188 (AMS 5801)
20 Engine gray enamel Combustion liner and ex- AISI 349, (29--9 W Mo).
haust collector support (MIL--R--5031, class 6) (AMS 5784).
Turbine and exhaust col- Hastelloy W (AMS 5786)
lector, struts (MIL--R--5031 class 12)
21 Engine gray enamel Gearbox touch--up Actithane WC100 paint and Lacquer
Reducer H251
Saran Protective Coatings Co.
17332 Shields
Detroit, Michigan 48212

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Table 301 (cont)

Item Material Use Acceptable Source

21 Engine gray enamel PU Gray Paint, Code 03--GY--401
(cont.) Color #16251 Fed. Std. 595B
DEFT Chemical,
17451 Von Karmon Ave.
Irvine, CA 92714--6205
22 Petrolatum Metallic seal and bearing Commercial
installation
23 Moisture proof barrier Engine packaging Flexkin 100P (MIL--B--131).
material Acme Backing Corp.
P.O. Box 360
Stamford, Connecticut 06904
24 Marking pencils Marking hot section parts See Table 302.
25 Dehydrating agent Storage and shipment CS--16 (MIL--D--3464).
16--unit bags Filtrol Corp.
3250 East Washington
Los Angeles, California 90023
26 Pressure sensitive Storage and shipment No. 260 Scotch Brand.
masking tape----1-- or 2-- Minnesota Mining and Mfg. Co.
in. (25or 51--mm) width 3M Center
St. Paul, Minnesota 55101
27 Black stencil ink Storage and shipment K--1 (TT--I--559).
March Stencil Machine Co.
707 East B St.
Belleville, Illinois 62222
28 Moisture absorbing rust External engine surfaces No. 606
preventative only Rust--Lick Incorporated
755 Boylston Street
Boston, Massachusetts 02116
Rocket WD40 (MIL--C--23411).
WD--40 Co.
San Diego, California
WD--40
Dr. Oskar Trost
Industrie und
Auto Chemie
2350 Neumuenster
West Germany
WD--40
Betriebs & Werkstatt --
Zubehoer Gmbh
Riedstrasse 25
7302 Ostfildern l--Ruit
West Germany
WD--40
Hawker Pacific, Pty. Ltd.
4--8 Harley Cresent
Condell Park
New South Wales 2200
Australia

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Table 301 (cont)

Item Material Use Acceptable Source

28 Moisture absorbing rust External engine surfaces Pengard

preventative (cont) only (cont) Penetone Co. Ltd.
Bassington Industrial Estate
Cramlington, Northumberland
United Kingdom
Ardrox 3961
Ardrox Limited
Commerce Road
Brentford, Middlesex, England
Ardrox 3961
Ardrox Australia Pty. Ltd.
Birnie Avenue
Lidscombe N.S.W., 2141 Australia
CRC 336
CRC Chemicals Division
C.J. Webb Inc.
Limekiln Pike
Dresher, Pennsylvania 19025
29 Methylethylketone General cleaning Commercial
30 Sealant Assemblyoil bellows No. 1372 W
seal, reduction gear Permatex Co. Inc., Box 1350
mounting flange Flanger Court Bldg.
West Palm Beach, FL 33402

31 High temperature lubri- Where antiseize is speci- NeverSeez Nickel Special

cant fied in this manual. NeverSeez Compound Corp.
2910 South 18th St.
Broadview, Illinois 60153
Bearing Supply and Service
448472 Notre Dame Ave.
Winnipeg 2, Canada
R. A. Rodriguez (U.K.) Ltd.
Station HouseDarkes Lane
Potters Bar
Herts, England

Consolidated Brg, Co. Pty. Ltd.

238 Victoria Rd.
Drummoyne, N.S.W.
Australia
Kyokuto Boeki Kaisha Ltd.
7th Floor, New Otemachi Bldg.
21, 2Chome, Otemachi
ChiyodaKu, Tokyo, 10091
Japan

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Table 301 (cont)

Item Material Use Acceptable Source

31 High temperature lubri- Where antiseize is speci- S. A. Brasileira De Rolamentos

cant (cont) fied in this manual. (cont) E. Mancais BRM
Av. Senador Queiroa, 605
Conj. 1609
Sao Paulo, Brazil
Tekind
Via F. Melzi DEril, 3
20154 Milano, Italy
DSL Super HiTemp
DavisHowland Oil Corporation
200 Anderson Avenue
Rochester, New York 14607
32 Sealer Compressor mounting in- Devcon F (aluminum).
sert installation Devcon Corp.
59 Endicott St.
Danvers, Massachusetts 01923
Resiweld FE186
H. B. Fuller Company
2400 Kasota Ave.
St. Paul, Minnesota 55102

Metal Set A4.

Smoothon Inc.
1000 Valley Road
Gillette, New Jersey 07933
Epon 934
Hysol Div. Dexter Corp.
2850 Willow Pass Road
Pittsburgh, California 94565
Compressor case vane RTV 736 or RTV 732
band bolt holes and man- Dow Corning Corp.
ifold to adapter splitline South Saginaw Road
Midland, Michigan 48640

RTV 106
General Electric Corp.
Waterford, New York 12188
Assemblygearbox split- Scot Clad 776
line Scotch Clad Coatings
Minnesota Mining and Mfg. Co.
3M Centre
St. Paul, Minnesota 55101
DC 994
Dow Corning Corp.
South Saginaw Road

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Table 301 (cont)

Item Material Use Acceptable Source

32 Sealer (cont) Installation of labyrinth sta- Loctite 620 or 602

tionary seal bearing area Loctite Corp.
705 North Mountain Road
Newington, CT 06111
33 Sealant removal Removal of loctite 620 or Loctite chisel solvent
602 Loctite Corp.
705 North Mountain Road
Newington, CT 06111
34 Methyl alcohol (Fed Compressor water rinse Commercial Solvents Corp.,
Spec O--M 232d, grade 245 Park Ave.
A), (British Standard BS New York, N.Y. 10017
506 Amend. 1)
Union Carbide Corp.
Chemicals and Plastics,
270 Park Ave.
New York, N.Y. 10017
35 Desiccant Shipping package humidity No. 88 Absorbent Protective
control Dehydrating Agent (MIL--D--3464)
Delta Packaging Products
4108 North Nashville Avenue
Chicago, Illinois 60634
36 Liquid leak detector Checking for pneumatic SNOOP (meets Mil Spec MIL--L--
leaks 25567C, type 1 oxygen systems)
Indiana Valve & Fitting Inc.
P.O. Box 24267
Indianapolis, Ind 46224
Leak--Tec Formula 372E
American Gas and Chemical Co.
5 Tefnakil Park
Cresskill, New Jersey 07626
37 Adhesive Oil pump gearshaft reten- Loctite 290
tion Loctite Corporation
705 North Mountain Road
Newington, Connecticut 06111
38 Fuel additive Fuel anti--ice Prist (MIL--I--27686E)
PPG Industries Inc.
5629 FM 1960 West
Houston, Texas 77069
Anti--microbial growth Biobor JF Aviation Fuel Additive
MIL--S--53021A Hammonds Technical Services, Inc
910 Franklin Rd.
Houston, TX 77073
Ph: (281) 999--2900
Fax: (281) 582--4224
Email: info@hammondscos.com
Web: www.hammondscos.com

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Table 301 (cont)

Item Material Use Acceptable Source

39 Torque Paint Application of slippage Torque Seal F--900

marks to pneumatic and lu- Organic Products Company
brication system B--nuts P. O. Box 428
Irving, Texas 75060--0428
40 Torque Paint Remover Removal of torque paint F--100 Remover
(slippage marks) Organic Products Company
P.O. Box 428
Irving, Texas 75060--0428
41 Silicone resin----clear Compressor mount repair METROSEAL AP
(AMS 3135) METCO Inc.
1105 Prospect Ave.
Westbury, Long Island,
New York 11590
42 Assembly fluid Assembly aid Ultra Chem Co. 1
Ultra Chem Inc.
1400 N. Walnut Street
Wilmington, Deleware 19899
NOTE: Even though Rolls--Royce has approved these consumables for use with Rolls--Royce en-
gines, Rolls--Royce assumes no liability for injury to personnel or the environment by their
use.
Table 302
Acceptable Marking Pens and Pencils
CAUTION: THESE PENCILS, MARKERS AND PAINT STICKS ARE ALSO APPROVED FOR
MARKING TITANIUM ALLOYS PROVIDING THE MARKINGS ARE REMOVED PRIOR
TO EXPOSURE OF THE PARTS TO TEMPERATURES ABOVE 500F (260C) BY
HEAT TREATMENT OR ENGINE OPERATION.
NOTE: The following pencils, fine tip and wide markers, ball point markers, and paint sticks are approved
for marking iron, nickel and cobalt base alloys which are exposed to temperatures above 800F
(427C) either by heat treatment or engine operation. Markings on these alloys do not have to be
removed from the parts prior to heating above 800F (427C).
The number in the parentheses that follows the manufacturers name corresponds to the address listing
at the end of this table.

Manufacturer Trade Name Number Color

Pencils
Venus (1) Unique 1237 Carmine Red
Berol Corp. (2) Eagle Verithin 745 Carmine Red
A.W. Faber (3) The Winner 2383 Dark Green
Berol Corp. (2) Eagle Verithin 751 True Green
A.W. Faber (3) The Winner 2388 White
Venus (1) Unique 1215 White
Berol Corp. (2) Eagle Verithin 734 White
Venus (1) Unique 1206 Blue
Koh--l--Noor (4) Flexicolor X1800X25 Blue

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Table 302 (cont)

Manufacturer Trade Name Number Color

Pencils (cont)

Berol Corp (2) Eagle Verithin 758 True Blue

Berol Corp (2) Eagle Verithin 737 Orange
A.W. Faber (3) The Winner 2462 Silver
Berol Corp. (2) Eagle Verithin 753 Silver
Eberhard Faber (5) Colorbrite 2101 Silver

Fine Tip Markers

Carters (6) Marks--A--Lot ---- Yellow

Berol Corp. (2) Flash 30 ---- Red
---- Lindy ---- Green
Berol Corp. (2) Flash 30 ---- Blue
---- Lindy ---- Blue
Berol Corp. (2) Flash 32 ---- Blue
Sanford Corp. (12) T.E.C. Marker 3201 Black
Sanford Corp. (12) T.E.C. Marker 13401 Black

Wide Tip Markers

Berol Corp. (2) Liquid Tip 1100 Black

Berol Corp. (2) Eagle Marker 8835 Black
Berol Corp. (2) Liquid Tip 1100 Red
Berol Corp. (2) Eagle Marker 8824 Red
Berol Corp. (2) Eagle Marker 8802 Blue
Berol Corp. (2) Eagle Marker 8816 Yellow
Sanford Corp. (12) T.E.C. Marker 1501 Black

Ball Point Markers

Markall (7) ---- ---- Blue

Markall (7) ---- ---- Yellow

Paint Sticks

Markal Company (7) Paintstik Type B Yellow

Markal Company (7) Paintstik Type B White
Markal Company (7) Paintstik Type B Green
Markal Company (7) Paintstik Type B Brown
Markal Company (7) Paintstik Type B Orange
Markal Company (7) Paintstik Type B Purple
American Art Clay Co. Glass Cellophane 2346 Blue
(8)

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Table 302 (cont)

NOTE: DriMarquette Black Ink, a product of the IrwinHodson Co.(9), is approved for marking on iron,
nickel and cobalt base alloy parts. The markings do not have to be removed prior to exposure
to temperature above 427C (800F).
CAUTION: DRIMARQUETTE BLACK INK MAY BE USED ON TITANIUM ALLOYS BUT MUST
BE REMOVED PRIOR TO EXPOSURE TO TEMPERATURES ABOVE 260C (500F).

LNC3 NUCLEAR GRADE ELECTROLYTE, A PRODUCT OF THE LECTROETCH

COMPANY(10), IS APPROVED FOR ELECTROLYTIC ETCHING ON IRON, NICKEL,
COBALT, TITANIUM, ALUMINUM AND MAGNESIUM ALLOYS. THIS PROCESS
FOR PERMANENT MARKING OF IDENTIFICATION ON PARTS.
NOTE: Pyromarker, a product of Ball Point Metal Marker, Tempil Division, Big Three Industries, Inc.(11),
is approved for marking on iron, nickel and cobalt base alloys and on titanium alloys. Markings
on these alloys do not have to be removed prior to exposure to temperatures above 260C
(500F).
Manufacturer Addresses
(1) VenusEsterbrook Corp.; Lewisburg, Tenn. 37091
(2) Berol Corp.; P.O. Box 1000, Danbury, Conn. 06810
(3) FaberCastell Corp.; P.O. Box 1708, 41 Dickerson St., Newark, New Jersey 07103
(4) KohlNoor Rapidograph Inc.; 100 North Street, Bloomsbury, New Jersey 08804
(5) Eberhard Faber Inc.; Crestwood Industrial Park, WilkesBarre, Pennsylvania 18703
(6) Carters Ink Co.; 275T Wyman St., Waltham, Mass. 02154
(7) Markall Co.; 270 North Washtenaw Ave., Chicago, Ill. 60612
(8) American Art Clay Co. Inc.; 4717 West 16th St., Indianapolis, Ind. 46224
(9) IrwinHodson Co.; Ninth and S.E. Woodward, Portland, Oregon 97202
(10) The Lectroetch Co.; 14925 Elderwood Ave., Cleveland, Ohio 44112
(11) Tempil Division Big Three Industries Inc.; 2901 Hamilton Blvd., South Plainfield, N.J. 07080
(12) Sanford Corp.; Bellwood, IL 60104

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4. Hardware
A. Use 0.020 in. (0.51 mm) diameter stainless steel lockwire, MS20995C20 where lockwire size is
not specified. Double strand lockwire all drilled bolts, plugs, and screws, except those locked with
selflocking nuts or lockwashers. Lockwire bolts in pairs where possible. When reassembling be
sure to safety wherever lockwire was removed. Do not use zinc lockwire. Do not reuse lockwire,
cotter pins, ring seals, lip seals, composition gaskets, and split or tab washers. Selflocking nuts
can be reused if they have a minimum prevailing torque within the limits given in Table 303.
NOTE: It is not necessary to lockwire engine electrical and magnetic connectors that are of the
selflocking, quickdisconnect type.

Table 303

Minimum Prevailing Torque for Used Locknuts

Fine Thread Series Coarse Thread Series

Min Torque Min Torque

Thread Size lbin. (N.m) Thread Size lbin. (N.m)

836 0.7 (0.08) 832 0.7 (0.08)

1032 1 (0.11) 1024 1 (0.11)
1/428 2 (0.23) 1/420 2 (0.23)
5/1624 3 (0.34) 5/1618 3 (0.34)
3/824 5 (0.56) 3/816 5 (0.56)
7/1620 8 (0.90) 7/1614 8 (0.90)
1/220 10 (1.1) 1/213 10 (1.10)
9/1618 13 (1.5) 9/1612 14 (1.60)
5/818 18 (2.0) 5/811 20 (2.30)
3/416 27 (3.1) 3/410 27 (3.10)
7/814 40 (4.5) 7/89 40 (4.50)
112 55 (6.2) 18 51 (5.80)
11/812 73 (8.3) 11/88 68 (7.70)
11/412 94 (10.6) 11/48 88 (9.90)

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5. Torques
A. The following paragraphs contain general torque limits for tightening nuts, bolts, and screws.
(Refer to Table 304). Torque limits for special applications are provided under maintenance for the
specific component. Reuse selflocking nuts having a minimum prevailing torque within the limits
given in Table 303. When the tightening procedure calls for locknut drag to be added to a given
torque value, obtain the drag as follows:
(1) Tighten the nut snug.
(2) Back off one half turn.
(3) Locknut drag is the torque required to first turn the loosened nut.

Table 304

General Torque Limits for Bolts, Nuts, and Screws

Thread
Size Type Torque
832 Screws, bolts and nuts 1215 lb in. (1.41.7 N.m)
836 Screws 1720 lb in. (1.92.3 N.m)
1024 Screws 1222 lb in. (1.42.5 N.m)
1024 Bolts and nuts 2530 lb in. (2.83.4 N.m)
1032 Screws 2226 lb in. (2.52.9 N.m)
1032 Bolts and nuts 3540 lb in. (3.94.5 N.m)
1/420 Bolts and nuts 6065 lb in. (6.87.3 N.m)
1/428 Flat, round, and fillister 5558 lb in. (5.66.6 N.m)
head screws
1/428 Bolts, nuts, and socket 7085 lb in. (7.99.6 N.m)
head screws
5/1624 Bolts and nuts 120150 lb in. (1417 N.m)
5/1624 Selflocking nuts 140170 lb in. (1619 N.m)
3/816 Bolts and nuts 205245 lb in. (2328 N.m)
3/824 Bolts and nuts 240280 lb in. (2732 N.m)
3/824 Selflocking nuts 265300 lb in. (3034 N.m)
5/818 Bolts and Nuts 90100 lb ft. (122136 N.m)
Palnuts 60 or one flat past finger tight

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B. Tighten without the use of a thread lubricant unless one is specified. Threads must be free of burrs
or nicks, and they must turn freely. Complete tightening at the first draw--down causes
overstressing of parts and distorted splitlines. On bolt circles, alternately tighten nuts, bolts, or
screws that are 180 apart to half of minimum torque. Repeat the process, tightening to specified
torque. On splitlines other than bolt circles tighten midsection nuts, bolts, or screws first to half
minimum torque; then tighten remaining threaded parts to half minimum torque. Repeat the
process, tightening to specified torque.
C. When screws are installed with nuts, the torque for the screw shall apply. (Refer to Table 304.) On
nuts with a thread size larger than one inch, tighten nuts to maximum specified torque to seat parts.
Loosen and retighten as specified.
D. When tightening or loosening coupling nuts, make sure the nipple does not turn on the seat of the
mating fitting. Apply torque paint across the fitting threads after tightening them. Bottoming torque
on bushing type parts that seat metal over a seal is the same as for fittings with like thread size.
For correct torque limits, see Tables 305 and 307.
E. When you use an extension wrench that would change the effective length of the torque wrench, it
is necessary to calculate the applied torque from the required torque (Ref. Figure 301A).
6. Universal Fittings (Ref. Figure 301)
A. Fittings With Backup Rings
Use this procedure to install universal fittings with backup rings.
(1) Install the nut on the fitting and run it back until the counterbore of the nut aligns with the upper
inner corner of the gasket groove.
(2) Lubricate the seal and install it on the fitting.
(3) Work the backup ring into the counterbore of the nut.
(4) Turn the nut down until the seal is pushed firmly against the lower threaded section of the
fitting.
(5) Install the fitting into the boss, making certain the nut turns with the fitting, until the seal
touches the boss. Then tighten the fitting one and one--half turns more.
(6) Put a wrench on the nut to prevent its turning, and position the fitting by turning it not more
than one turn.
(7) (Hold the fitting in its position and tighten the nut against the boss.

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Universal Fittings
Figure 301

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Torque Calculations
Figure 301A
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Table 305

Torque Limits for Fuel, Oil, Air, and Drain Lines

Torque in pound inches (N.m)

Thread Size
Application 5/16--24 3/8--24 7/16--20 1/2--20 9/16--18

Steel coupling 35--40 65--100 80--120 150--200 200--250

nuts on steel (3.9--4.5) (7.3--11.3) (9.0--13.6) (17--23) (23--28)
fittings

Steel or aluminum 15--25 25--40 40--65 60--80 80--120

coupling nuts on (3.9--4.5) (2.8--4.5) (4.5--7.3) (6.8--9.0) (9.0--13.6)
aluminum fittings

Aluminum or steel 18--25 50--75 55--80 75--110 100--150

universal fitting (1.7--2.8) (5.6--8.5) (6.2--9.0) (8.5--12.4) (11--17)
locknuts (plain)

Aluminum or steel 18--25 50--75 55--80 100--150

unions (2.0--2.8) (5.6--8.5) (6.2--9.0) (11--17)

Plugs and bleeders 10--16 30--40 40--65 60--80 80--120

(1.1--1.8) (3.4--4.5) (4.5--7.3) (6.8--9.0) (9.0--13.6)

Pipe plugs Tighten enough to seal

Aluminum clamps 40--65 80--120

(4.5--7.3) (9.0--13.6)

Aluminum and steel 150--200 175--225 200--250

universal fitting (17--23) (20--26) (23--28)
bolts

Hose clamps Initial installation 15--20 Retightening

(1.7--2.3) 10--15
(1.1--1.7)

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Table 306

Torque Limits for Steel Couplings on Steel Fittings

Torque
Dash Turbine OD Wrench
No. Inches Size lb in. N.m
2 0.125 3/8 3540 3.94.5
3 0.187 7/16 65100 7.311.3
4 0.250 9/16 80120 9.013.6
5 0.312 5/8 150200 1722
6 0.375 11/16 200250 2228
8 0.500 7/8 325400 3745
10 0.625 1 475575 5465
12 0.750 1 1/4 660780 7588
16 1.000 1 1/2 720960 81108
20 1.250 2 12001500 136170

B. Fittings Without Backup Rings

Use this procedure to install universal fittings without backup rings.
(1) Run the nut on the fitting end back until the washer face is aligned with the upper inner corner
of the gasket groove.
(2) Lubricate the seal and place it in the groove. Use care not to damage seal.
(3) Screw the fitting into the boss until the seal barely touches the boss.
(4) Turn the fitting and nut together until the nut touches the boss.
(5) Put a wrench on the nut to prevent its turning, and position the fitting by turning it in up to 270
or unscrewing it up to 90.
(6) Hold the fitting in its proper position and tighten the nut against the boss.
7. Locknut Installation (See Figure 302)
Install locknuts (klincher or equivalent) with the locking shoulder on the lead side. Tightening presses
the nut against the bolted surface to create the stress required for locking. Nuts installed upside down
will not achieve this desired locking feature.
8. Airframe/Engine Interface Connections
When airframe provided fittings are installed into the engine, refer to Table 307 for the recommended
torque values.
9. Rigid Tube Inspection and Installation
When a component to which rigid tube assemblies are attached is replaced, remove all interfering tube
assemblies to permit easy removal and reinstallation of the component. This precaution will prevent
subsequent damage to the tube assemblies. Tubetofitting alignment should be checked for proper fit,
as described in Flared Tubes and Flanged Tubes, para 9.B. and 9.C. any time such a component is
installed.

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Typical Locknut Installation

Figure 302

Table 307

Recommended Torque for Airframe/Engine

Interface Connections

Torque
Thread Size lb in. (N.m)
0.37524 2540 2.84.5
0.437520 4065 4.57.3
0.50020 6080 6.89.0
0.75016 150200 1723
0.87514 200350 2340
1.062512 300500 3456

A. Inspection
Inspect fuel, control air, and oil tubes as follows:
(1) Inspect tubes for dents, chafing or cracks.
(2) Reject tubes with cracks (dye check) in any area.

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(3) Reject tubes having dents or chafing on the flared ends or on the retention clamps.
(4) Reject tubes with dents exceeding 1/8 in. (3 mm) depth or having a sharp radius.
B. Flared Tubes
WARNING: PROPER TIGHTENING OF ENGINE TUBING CONNECTIONS IS CRITICAL TO
FLIGHT SAFETY. CORRECT TORQUE VALUES MUST BE USED AT ALL TIMES.
EXCESSIVE TORQUE ON PNEUMATIC SENSING SYSTEM CONNECTIONS
RESULTS IN CRACKING OF THE FLARE OR ADJACENT TUBE AREA IN
CONTACT WITH THE FERRULE. THIS PRODUCES AN AIR LEAK WHICH CAN
CAUSE FLAMEOUT, POWER LOSS, OR OVERSPEED.
CAUTION: FAILURE OF ENGINE PNEUMATIC OR FUEL TUBES DUE TO FAULTY
MAINTENANCE PRACTICE COULD CAUSE FLAMEOUT, POWER LOSS, OR
OVERSPEED.
Tube assemblies must fit and be aligned with the mating flare tube fittings to the degree that at both
ends of the assembly the flares shall be uniformly seated in a free state on the cones of the mating
fittings. The fit shall be without distortion or stretching of the tube assembly and to the degree that
the nuts can be fully engaged up to the final onehalf turn with light finger pressure.
CAUTION: THE PRACTICE OF TIGHTENING FITTING LOCK NUTS WITH TUBE
ASSEMBLIES INSTALLED CAN RESULT IN DAMAGE TO THE TUBE WITH
POSSIBLE FAILURE OF THE TUBE ASSEMBLY.
In the event a tube does not align with the mating fittings, reposition the mating fittings to the
degree that proper alignment may be attained. Final tightening of these fittings must be
accomplished before the tube assembly is connected.
CAUTION: EXTREME CAUTION MUST BE OBSERVED WHILE HAND BENDING
PREVIOUSLY FORMED TUBES TO PREVENT EXCESSIVE FLATTENING OF
TUBES AT THE BEND RADIUS.
If proper alignment cannot be attained by repositioning mating flare tube fittings, bend the tube
sufficiently to provide alignment in the free state as specified. Accomplish all bending with the tube
removed from the engine. Adjustment of the fit may be accomplished by bending by hand at
principal bends. In the event the tube cannot be bent by hand, the tube must be clamped in a
fixture or device which will not scratch, indent, crimp, or mark the surface of the tube during the
bending operation. The flattened effect of the cross section of the tube as a result of the reforming
operation must not exceed 15 percent of the tube OD.
CAUTION: MAKE SURE NO LOOSE PARTICLES OF TORQUE PAINT ARE ALLOWED TO
ENTER THE TUBES OR FITTINGS.
WARNING: TUBING BNUTS USED IN INSTALLATIONS EXPOSED TO A HIGH DEGREE OF
VIBRATION AND PRESSURE SURGES ARE SUBJECT TO TORQUE
RELAXATION WHEN IMPROPERLY TIGHTENED.

USE ACCEPTABLE TECHNIQUES AND PRACTICES TO PREVENT TORQUE PAINT

OR TORQUE PAINT REMOVER FROM CONTACTING RUBBER OR PLASTIC MA-
TERIALS OR ENTERING EXPOSED AREAS.

When proper free state alignment is attained, complete the tubing installation by simultaneously
securing the coupling nuts. After all Bnuts are properly tightened to the correct torque values,
remove old torque paint marks to prevent confusion and excessive build up of paint. Apply a new
slippage mark (torque paint) of contrasting color approximately 0.063 inch (1.60 mm) wide
minimum. The mark shall extend down the side of the Bnut and onto the mating fitting. Install
necessary clamping. (Refer to 250B17F Illustrated Parts Catalog, Pub. No. CSP23008, for
clamping requirements.) Make sure that the correct clamps are installed in the correct positions on
all tubing.
Bnuts shall be inspected for indications of slippage at 100 hour maintenance intervals.

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Old slippage marks (torque paint) shall be completely removed, using torque paint remover, and
reapplied each time the Bnut is tightened.
C. Flanged Tubes
WARNING: PROPER TIGHTENING OF ENGINE TUBING CONNECTIONS IS CRITICAL TO
FLIGHT SAFETY. CORRECT TORQUE VALUES MUST BE USED AT ALL TIMES.
EXCESSIVE TORQUE ON PNEUMATIC SENSING SYSTEM CONNECTIONS
RESULTS IN CRACKING OF THE FLARE OR ADJACENT TUBE AREA IN
CONTACT WITH THE FERRULE. THIS PRODUCES AN AIR LEAK WHICH CAN
CAUSE FLAMEOUT, POWER LOSS, OR OVERSPEED.
The alignment of tube fittings with mating sealing surfaces and the securing of tube clips must
conform to the following:
(1) Nut and Nipple Joints. With one end hand tightened, it must be possible to locate the nipple at
the free end in its conical seating, by flexing the tube by hand, without effecting a permanent
set to the assembly. The alignment of the joint must be such that the nut readily engages with
its mating thread.
(2) Setscrew Retained Flanged Adapters. The clearance and parallelism between flange and
mating surface, with the opposite end secured, must be such that the total flange area contact
can be achieved by flexing the tube by hand, without effecting a permanent set to the
assembly. Flange clearance holes must line up with tappings such that bolts can be fitted
without subjecting the tube to a torsional load.
(3) Clipping Points. Locate clips to securing points such that the setscrews can be fitted by flexing
the tube by hand, without effecting a permanent set to the assembly. Tubes which fail to meet
this requirement may be removed from the engine and reformed as follows:
(a) Tubes must be clamped in a fixture which will not scratch, indent, crimp or mark the
surface of the tube during the bending operation.
(b) Retention of the tube during bending should be made in a manner which does not permit
bending or torsional loads across welded or brazed areas.
(c) Tubes which can be corrected for fit only by submitting welded areas to bending or
torsional loads, must be reinspected by Xray or Zyglo for any evidence of weld or braze
fracture prior to reinstallation on the engine.
(d) Reformed tubes must meet the requirements of steps (1) and (2).
(4) When removal of the tube from the engine would result in excessive lost time due to the need
for teardown and rebuild, the tube may be reformed attached to the engine if the following
precautions are followed:
(a) Bending and torsional loads must not be applied across welded or brazed areas.
(b) The tube attachment points are to be loosened after bending (attachment points which
are inaccessible due to the state of assembly are inaccessible due to the state of
assembly are excluded).
(c) Reformed tubes must meet the requirements of steps a and b.
10. Lubricants
CAUTION: DO NOT USE MOLYBDENUM DISULFIED LUBRICANTS ON INTERNAL THREADS OR
ON ANY FUEL, LUBRICATION OR AIR SYSTEM TUBING, HOSE OR FITTINGS.
CAUTION: DO NOT USE SILICONE LUBRICANTS EXCEPT WHERE SPECIFIED. USE
LUBRICANTS RECOMMENDED IN THE ENGINE PUBLICATIONS.
The following lubricants shall be used for assembly of the engine and at regular periodic lubrication of
components.

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Location Lubricant

General use such as installation of bear-- Engine oil

ings, oil seals and packings

Accessory gear splines and splines of Lubriplate 130A, 930AA, or equiv-

engine components alent

Gearbox seal lips and packing roller bear-- Grease (Shell 6249, Mobil 28, en-
ings for ease of assembly gine oil or equivalent)

External spanner nut, nut, bolt and stud threads except male Silicon base molybdenum disul--
threads and attachments and plugs installed in the outer com- fide antiseize compound:
bustion case, turbine supports and and exhaust collector. Also DC550R----protects up to 232C
used on No. 2 bear retaining spanner nut. (450F). CP--63----protects up to
760C (1400F).

Male threads of plugs and attachments installed in the outer Nickel base antiseize compound,
case, turbine supports or exhaust. Also used on threads of bolts NS165, Never Seez Nickel Spe-
at splitlines between the outer case, turbine supports and ex- cial----high temperature, high pres-
haust collector. sure protection; DSL Super Hi--
Temp.

Fuel system preservation See Table 301.

NOTE: Apply a light coat of lubricant by hand; wipe off any excess. Lubricate only the male threads of
fuel and oil lines; wipe the lubricant from the lead threads to prevent it from entering the
system. Do not mix synthetic lubricating oil with petroleum based products and do not
lubricate air system component threads.

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11. Lubrication System Servicing

WARNING: MAINTAIN THE COMPLETE OIL SYSTEM IN ACCORDANCE WITH ENGINE AND
AIRCRAFT INSTRUCTIONS. FAILURE TO MAINTAIN THE OIL SYSTEM CAN
RESULT IN SUDDEN ENGINE STOPPAGE.
WARNING: IF A MAGNETIC PLUG WARNING LIGHT COMES ON DURING FLIGHT, LAND AND
INSPECT THE MAGNETIC PLUGS AS SOON AS POSSIBLE. THIS LIGHT IS AN
INDICATION OF CONDITIONS WHICH COULD CAUSE ENGINE FAILURE. WHEN
FLYING A MULTIENGINE AIRCRAFT, REDUCE THE AFFECTED ENGINE OUTPUT
POWER TO THE MINIMUM REQUIRED FOR FLIGHT AND LAND AS SOON AS
PRACTICABLE. IF THE LIGHT IS ACCOMPANIED BY ABNORMAL NOISES, OIL
PRESSURE OR TEMPERATURE, AND SINGLEENGINE FLIGHT CAN BE
MAINTAINED, SHUT DOWN AFFECTED ENGINE AND LAND AS SOON AS
PRACTICABLE. IF SINGLEENGINE FLIGHT IS NOT POSSIBLE, REDUCE POWER
OF AFFECTED ENGINE TO THE MINIMUM AND LAND AS SOON AS POSSIBLE.
AFTER LANDING, INSPECT THE MAGNETIC PLUGS ON THE AFFECTED ENGINE
FOR THE METAL CONTAMINATION PRIOR TO FURTHER ENGINE OPERATION.
WARNING: OPERATORS MUST MAINTAIN THE ENGINE MAGNETIC DRAIN PLUGS AND
INDICATING SYSTEM IN OPERATING ORDER AND COMPLY WITH AIRCRAFT
FLIGHT MANUAL AND ENGINE OPERATION AND MAINTENANCE MANUAL
INSTRUCTIONS WHEN AN INDICATION IS RECEIVED. NEVER ALLOW AN
ACCEPTABLE SPECTROGRAPHIC OIL ANALYSIS PROGRAM (SOAP) READING TO
OVERRIDE MAGNETIC DRAIN PLUG INDICATIONS.
WARNING: FAILURE TO PROPERLY INSTALL, ALIGN AND TORQUE FUEL, OIL, AND AIR
FITTINGS AND TUBES COULD RESULT IN AN ENGINE FAILURE.
CAUTION: NORMAL ENGINES CONSUME A MINIMAL AMOUNT OF OIL. HOWEVER, ANY
SUDDEN INCREASE IN OIL CONSUMPTION IS INDICATIVE OF OIL SYSTEM
PROBLEMS AND MUST BE CORRECTED. (REFER TO ITEMS 20 AND 21 IN TABLE
101, TROUBLESHOOTING.)
A. General
CAUTION: DO NOT USE SILICONE LUBRICANTS EXCEPT WHERE SPECIFIED. USE
ONLY THE LUBRICANTS RECOMMENDED IN THE ENGINE PUBLICATIONS.
CAUTION: THE GAS PRODUCER TURBINE SUPPORT PRESSURE OIL TUBE SHOULD
NORMALLY NOT BE REMOVED. IF THIS TUBE MUST BE REMOVED, FLUSH
THE TUBE PASSAGE IN THE SUPPORT BEFORE TUBE INSTALLATION.
(REFER TO GAS PRODUCER SUPPORT PRESSURE OIL MANIFOLD
REPLACEMENT, PARA 5, 725000.)
Lubrication system maintenance includes: cleaning and inspecting the magnetic drain plugs;
changing the system oil; cleaning the oil filter; replacing the lube oil filter housing assembly;
adjusting the pressure regulating valve; cleaning and inspecting the turbine pressure oil system
check valve; flushing the gas producer support oil supply passage; inspecting and cleaning the
power turbine support pressure oil nozzle, scavenge oil strut, and external sump; also cleaning of
power turbine labyrinth seals.

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B. Oil Temperature Limit Exceeded

The maintenance actions required when oil temperature limits have been exceeded are governed
by the overtemperature conditions encountered. Specific conditions and their respective
maintenance action requirements are as follows:
(1) Engine oil temperature limit is exceeded during operation above 40 psi (276 kPa) TM pressure
or 165 hp (123 kW). Engine oil temperature exceeds 107C (225F) for a period not
exceeding ten minutes but remains less than 120C (248F). Oil pressure remains normal.
(a) Check for carbon deposits (coking).
(b) Inspect and clean or replace the oil filter.
NOTE: If an external scavenge oil filter is installed, refer to the applicable airframe
manual for service instructions.
(c) Inspect and clean the magnetic drain plugs.
(d) Reservice the oil system with new oil.
(e) Ground run the engine for 10 minutes.
(f) Reinspect the engine/scavenge oil filter(s) and the magnetic drain plugs. If no carbon
particles can be found, return the engine to service. If carbon particles are found, perform
oil system maintenance. (Refer to Oil System Maintenance, para 6.F., 725000.)
(g) Reinspect the oil filter and the magnetic drain plugs after five hours of engine operation.
If carbon particles are found, repeat the maintenance procedure.
(2) Engine oil temperature limit is exceeded during operation above 40 psi (276 kPa) TM pressure
or 165 hp (123 kW). Engine oil temperature exceeds 107C (225F) for a period not
exceeding 10 minutes but remains less than 120C (248F). Oil pressure abnormal.
(a) Overtemperature may adversely affect oil pressure regulation. Replace the oil filter
housing assembly. (Refer to Lube Oil Filter Housing Replacement, para 1.D., 726000.)
If normal oil pressure and oil pressure regulation is restored by replacement of the
housing assembly, send the removed housing assembly to an authorized facility for repair,
noting the reason for removal.
(b) Check for carbon deposits (coking). (Refer to para 11.E., this section.)
(c) Inspect and clean or replace the oil filter. (Refer to para 1.C., 726000.)
NOTE: If an external scavenge oil filter is installed, refer to the applicable airframe
manual for service instructions.
(d) Inspect and clean the magnetic drain plugs. (Refer to para 11.I., this section.)
(e) Reservice the oil system with new oil.
(f) Ground run the engine for 10 minutes.
(g) Adjust engine oil pressure as required.
(h) Reinspect the engine/scavenge oil filter(s) and the magnetic drain plugs. If no carbon
particles can be found, return the engine to service. If carbon particles are found, perform
oil system maintenance. (Refer to Oil System Maintenance, para 6.F., 725000.)
(i) Reinspect the engine/scavenge oil filter(s) and the magnetic drain plugs after five hours of
engine operation. If carbon particles are found, repeat the maintenance procedure.
(3) Engine oil temperature limit is exceeded during operation at 40 psi (276 kPa) TM pressure or
165 hp (123 kW) or less. Oil temperature exceeds 120C (248F) momentarily or 107C
(225F) for a period exceeding 10 minutes.
(a) Remove the engine and send it to an overhaul facility for inspection or repair as required.
(b) Tag the engine indicating that max allowable operating oil temperatures were exceeded.
Give maximum temperature and elapsed time.

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C. Low Oil Pressure Operation

If deterioration in engine oil pressure is experienced, the following sequence of checks is
suggested.
(1) Check the quantity of oil in the tank to be sure it is adequate.
(2) Remove, inspect, clean, and install the magnetic plugs and engine/scavenge filter(s).
(3) Confirm the pressure discrepancy using a direct reading gage.
CAUTION: DO NOT MAKE A PRESSURE REGULATING VALVE ADJUSTMENT TO
CORRECT FOR A RAPID CHANGE IN OIL PRESSURE. THESE CONDITIONS
ARE CAUSE TO SUSPECT OTHER OIL SYSTEM PROBLEMS HAVE
DEVELOPED.
(4) Increase the pressure adjustment if necessary. Check the gage for change in pressure. If no
change in pressure is evident as a result of the adjustment, continue with the sequence of
checks to isolate and correct the fault.
(5) Remove and check the bottom magnetic drain plug. Drain oil from the gearbox. Do not install
the magnetic drain plug, after residual oil has drained, until a check for internal oil leakage has
been made.
NOTE: Leakage from the bottom drain port is an indication that the oil tube packings and/or
oil pump may be leaking. Leakage will also be evident if the check valve is not
properly seated.
(6) If bottom drain port leakage is evident, remove the oil filter housing from the gearbox. (Refer
to Gearbox Housing Lubrication System Components Disassembly, para 2.D., 726000.)
Replace part if any of the following conditions are noted and local repair is not practical.
(a) Excessive wear at the ID of the oilout port.
(b) Pressure regulating valve seat or poppet damage.
(c) Packing seal deterioration.
(7) Install acceptable oil filter housing in accordance with Lube Oil Filter Housing Replacement,
para 1.D., 726000.
(8) If problem persists after oil filter housing replacement, internal leakage of the oil pump and/or
leakage past the packings located at the oil pump ports are the probable causes. Ascertain
fault by inspection and replace part as necessary. (Refer to Gearbox Housing Lubrication
System Components Disassembly, para 2.D., 726000.)
D. Engine Operated With No Oil Pressure
Any engine operated for more than 30 seconds without oil pressure must be removed and sent to
an RollsRoyce Authorized Maintenance Center (AMC) for disassembly and inspection as defined
by the 250B17F Series Engine Overhaul Manual, Pub. No. GTP 52433.
E. Checking for Carbon Buildup
Check for carbon particles in the engine or oil system as follows:
(1) Drain the oil from the engine and from the oil tank. Drain oil through a clean cloth which is
suitable for filtering (detecting) carbon particles.
(2) Inspect the No. 8 bearing and sump area. Do not remove the oil tube and nozzle. (Refer to
appropriate part of Gas Producer Support Pressure Oil Manifold Replacement, para 5.,
725000.)
(3) If carbon buildup is detected during the preceding inspections, measure scavenge oil flow and
clean as required. (Refer to Oil Flow Measurement, para 6.D., 725000.)
F. Oil Change
Change the engine oil at the time interval specified in Table 602, 720000,
EngineInspection/Check or when oil contamination is encountered.

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(1) Drain the engine oil supply tank and engine oil cooler. Where the installation permits, inspect
the oil tank and cooler for carbon and sludge deposits. If deposits are found, remove the oil
tank or oil cooler in accordance with the aircraft manufacturers recommendations. Clean the
tank or cooler using a suitable solvent.

(2) Remove the magnetic drain plugs from the power and accessory gearbox. Allow residual oil to
drain from the magnetic plug openings in the gearbox. Inspect the plugs in accordance with
Magnetic Plug Inspection, para 11.I., this section. Clean the plugs with solvent. Dry with a
clean cloth.

(3) If an accumulation of magnetic particles, debris, chips, flakes or slivers are the cause for oil
change, remove, disassemble, clean and inspect the oil pressure reducer at the compressor
front support inlet to the number one bearing. (Refer to para 3., 72--30--00.)

(4) Remove the oil filter and packing from the filter housing. Discard the packing. Thoroughly
clean the oil filter cavity of all residual oil and sludge. Take the necessary precautions to
prevent residual oil from entering the engine cavity or standpipe. Clean the oil filter. (Refer to
Oil Filter Replacement, para 1.C., 72--60--00.)

(5) Remove and clean the external scavenge oil filter (if installed). Refer to the applicable
airframe manual for cleaning instructions.

NOTE: Some engine bearings feature silver--plated separators. If minute silver particles are
found in the engine oil filter, clean and reinstall the filter. These minute particles are
due to normal bearing wear and are not cause for further corrective action.

(6) Install the magnetic drain plugs. Use new packings lubricated with engine oil. Tighten plugs to
60--80 lb in. (6.8--9.0 N.m) and secure with lockwire.

(7) Install new or cleaned oil filter with new packing. Install the filter cap with a new packing which
has been lubricated with engine oil. Retain cap with two nuts and washers. Tighten nuts to
30--40 lb in. (3.4--4.5 N.m).

WARNING: ONLY DISCRETIONARY MIXING OF OILS WITHIN AN OIL SERIES IS

PERMITTED WITHOUT TIME PENALTY. USE OF MIXED OILS FROM
DIFFERENT SERIES IN AN ENGINE IS LIMITED TO FIVE HOURS TOTAL
RUNNING TIME DURING ONE OVERHAUL PERIOD. ADEQUATE
MAINTENANCE RECORDS MUST BE MAINTAINED TO ENSURE THAT THE FIVE
HOUR LIMIT IS NOT EXCEEDED. FAILURE TO COMPLY WITH OIL MIXING
RESTRICTIONS CAN RESULT IN ENGINE FAILURE.

WARNING: FAILURE TO COMPLY WITH OIL MIXING RESTRICTIONS CAN RESULT IN

ENGINE FAILURE.

(8) Fill the oil supply tank with approved oil.(Refer to Approved Oils, 4.C.(2), 72--00--00,
Engine--Description and Operation.) (Refer to Airframe Manual for proper quantity of oil.)

(9) Disconnect the No. 1 bearing scavenge line at the compressor front support scavenge fitting
and the No. 8 bearing scavenge line at the gas producer support scavenge fitting.

(10) Motor the engine with the starter without ignition until an indication of oil pressure is attained
and oil flow has been verified from the No. 1 and No. 8 scavenge fittings. If flow from these
two fittings or oil pressure are not attained, then refer to CSL TP 2039 for further
troubleshooting recommendations. Reinstall and torque the lines removed in para 11.F.(9).
Torque the lines to 150--200 lb in. (17--23 Nm). When you see oil pressure, start the engine
and operate at Idle for five minutes. Monitor the oil pressure continuously during the
five--minute run.

(11) Note the oil change in the Engine Log book.

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CAUTION: OPERATORS ARE TO MONITOR THE OIL FILTER EACH 25 HOURS OF OPERATION
FOLLOWING A CHANGE FROM MILL7808 OIL TO MILL23699, OR FROM
MILL23699 TO MILL7808. THIS IS TO BE DONE TO DETERMINE IF COKE,
WHICH WAS FORMED DURING PREVIOUS OPERATION WITH EITHER MILL7808
OIL OR MILL23699, IS BECOMING DISLODGED DURING PRESENT OPERATION
FOLLOWING THE OIL CHANGE. IF HEAVY OIL DEPOSITS ARE OBSERVED ON
THE ENGINE FILTER, IT IS SUGGESTED THAT THE ENGINE OIL BE CHANGED
AGAIN. THE OIL IS TO BE DRAINED WHEN THE OIL IS HOT TO OBTAIN THE
MAXIMUM BENEFIT. THE 25HOUR OIL MONITORING IS TO CONTINUE UNTIL THE
NEXT OIL CHANGE PERIOD.

CAUTION: USE OF OILS WHICH ARE NOT INCLUDED IN THE APPROVED OIL LISTING (PARA
4.C., 720000 ENGINEDESCRIPTION AND OPERATION) OR FAILURE TO DRAIN
OIL WITHIN THE PRESCRIBED INTERVAL GIVEN IN TABLE 602 WILL BE
CONSIDERED AS MISUSE UNDER ITEM (4) OF THE WARRANTY POLICY.

G. Emergency Oil Mix

CAUTION: REMOVE AND INSPECT THE OIL FILTER EACH 25 HOURS OF ENGINE
OPERATION IF THE TYPE OF OIL (MILL7808, MILL23699 OR DOD85734)
IS CHANGED.

CAUTION: THE FILTER INSPECTION IS TO DETERMINE IF COKE, WHICH WAS FORMED

DURING PREVIOUS OPERATION, IS BEING DISLODGED DURING THE INITIAL
OPERATION FOLLOWING THE OIL CHANGE.

CAUTION: IF HEAVY CARBON DEPOSITS ARE OBSERVED ON THE ENGINE FILTER, IT IS

SUGGESTED THAT THE ENGINE OIL BE CHANGED AGAIN. THE OIL IS TO BE
DRAINED WHEN THE OIL IS HOT TO OBTAIN THE MAXIMUM BENEFIT. THE
25HOUR OIL MONITORING IS TO CONTINUE UNTIL THE NEXT OIL CHANGE
PERIOD.

CAUTION: USE OF OILS WHICH ARE NOT INCLUDED IN THE APPROVED OILS LISTING
(PARA 4.C.(2)., 720000, ENGINEDESCRIPTION AND OPERATION) OR
FAILURE TO DRAIN OIL WITHIN THE PRESCRIBED INTERVAL GIVEN IN TABLE
602, 720000, ENGINE INSPECTION/CHECK WILL BE CONSIDERED AS
MISUSE UNDER ITEM (4) OF THE WARRANTY POLICY.

The emergency use of mixed oils (oils not in the same series; refer to para 4.C., 720000,
EngineDescription and Operation) is limited to five hours running time. Following an emergency
use of mixed oils, drain the system and clean the filter. (Refer to Oil Filter Replacement, para 1.C.,
726000.) Thoroughly flush the system with engine oil while motoring the engine. Drain and refill
with approved oil in accordance with Oil Change, para 11.F., this section.

H. Cleaning

Clean the lubrication system as follows:

(1) Clean the oil filter element and filter cavity in accordance with Oil Filter, para 1.C., 726000.

(2) Remove and clean the magnetic drain plug on the forward side of the power and accessory
gearbox. (Refer to para 11.I., this section.) While the magnetic plug is removed, motor the
engine with the starter and without ignition long enough to allow one to two ounces (3059
milliliters) of oil to flow from the opening. Observe flow for restriction and/or for extent of oil
contamination. Motoring flushes residual carbon particles from the power and accessory
gearbox. Reinstall magnetic drain plug; tighten to 6080 lb in. (6.89.0 N.m) and secure with
lockwire.

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(3) Detach clamp, then disconnect the power turbine pressure oil tube at the connector (tee).
Loosen the coupling nut at the fireshield end of the pressure oil tube; loosen only enough to
permit movement of the tube from the connector. Remove the screen at the connector end of
the tube. While the tube is disconnected, motor the engine with the starter and without ignition
long enough to allow one to two ounces (3059 milliliters) of oil to flow from the tube. Flush
the screen in mineral spirits and shake dry. Reinstall the screen in the pressure oil tube.
Attach the tube to the connector. Tighten the coupling nut at the connector end of the tube to
200250 lb in. (2328 N.m); tighten coupling nut at the fireshield elbow end of the tube to
80120 lb in. (9.013.6 N.m). Secure tube clamp; tighten clamp nut to 3540 lb in.
(3.94.5 N.m).
I. Magnetic Plug Inspection
WARNING: IF A MAGNETIC PLUG WARNING LIGHT COMES ON DURING FLIGHT, LAND
AND INSPECT THE MAGNETIC PLUGS AS SOON AS POSSIBLE. THIS LIGHT
IS AN INDICATION OF CONDITIONS WHICH COULD CAUSE ENGINE FAILURE.
WHEN FLYING A MULTIENGINE AIRCRAFT, REDUCE THE AFFECTED ENGINE
OUTPUT POWER TO THE MINIMUM REQUIRED FOR FLIGHT AND LAND AS
SOON AS PRACTICABLE. IF THE LIGHT IS ACCOMPANIED BY ABNORMAL
NOISES, OIL PRESSURE OR TEMPERATURE, AND SINGLEENGINE FLIGHT
CAN BE MAINTAINED, SHUT DOWN AFFECTED ENGINE AND LAND AS SOON
AS PRACTICABLE. IF SINGLEENGINE FLIGHT IS NOT POSSIBLE, REDUCE
POWER OF AFFECTED ENGINE TO THE MINIMUM AND LAND AS SOON AS
POSSIBLE. AFTER LANDING, INSPECT THE MAGNETIC PLUGS ON THE
AFFECTED ENGINE FOR METAL CONTAMINATION PRIOR TO FURTHER
ENGINE OPERATION.
Two indicating type magnetic drain plugs are installed in the power and accessory gearbox and one
is installed in the propeller reduction gearbox. If a warning light is received in the cockpit, remove
and visually inspect the magnetic drain plugs. The contamination conditions which may be
encountered on the magnetic plugs are defined as follows:
(1) Paste
(a) Paste is the result of fine soft particles which come from normal wear due to gear mesh,
bearing rotation and/or spline engagement. These particles mix with oil or soft carbon to
form paste.
(b) This condition is normal and is the reason for the 100 hour cleaning interval. Paste
generally does not cause a warning light. If a light is encountered, make the magnetic
plug check in para 11.I. (3), this section.
(c) Clean magnetic plugs with solvent and brush. Wipe dry with clean cloth or blow dry with
filtered shop air. Reinstall, tighten to 6080 lb in. (6.89.0 N.m).
NOTE: Heavy accumulations of paste require inspection and cleaning of the magnetic
plugs at intervals of 25 to 100 hours. Cleaning paste from the plugs is
necessary to ensure that small chips, flakes, and slivers can be detected.
(2) Magnetic Particles
(a) Magnetic particles and debris, chips, flakes, and slivers are possible indications of bearing
or gear failure and/or abnormal wear within the engine.
(b) Chips or flakes exceeding 1/32 in. (0.79 mm) diameter or more than 4 slivers per event
are not acceptable.
1 Remove engine and send to an RollsRoyce Authorized Maintenance Center (AMC).
2 Prior to operation of the replacement engine, do the following:
a If a scavenge oil filter is installed and the filter bypass button has not extended,
clean the airframe provided engine oil lines and replace the scavenge oil filter.

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b Confirm proper operation of the scavenge oil filter impending bypass indicator
by performing the functional check per Facet Service Bulletin No. 090589 (ref.
RollsRoyce TP CSL 2017) for aircraft equipped with this type of external
scavenge filter system.
c If the scavenge oil filter has bypassed, if the impending bypass fails the
functional test, or if no scavenge filter is installed, clean or replace the scavenge
oil filter, oil cooler, oil tank, and lubrication system oil lines per the airframe
manufacturers instructions. Drain and replace the engine oil. (Refer to
EngineServicing, Oil Change, para 11.F., 720000.)
(c) Chips or flakes less than 1/32 in. (0.79 mm) diameter or fewer than 4 slivers per event are
acceptable.
1 If a warning light is encountered, refer to para 11.I.(3), this section.
2 Reinstall the magnetic plug and tighten to 6080 lb in. (6.89.0 N.m).
(3) Magnetic Light Indication
Perform the following maintenance actions following each encounter of magnetic light
indications:
(a) Clean the magnetic drain plugs. Perform a 30minute ground run at power. Observe
engine operation limits and chip warning lights.
1 If operation is normal, remove, inspect, clean, and reinstall the three chip detectors.
Return engine to service.
2 If chips or flakes less than 1/32 in. (0.79 mm) diameter or fewer than four slivers are
encountered during the 30minute run, proceed to the next step.
(b) If a chip light is encountered during the first 30 minute ground run, the following steps
must be taken before the second 30minute ground run.
1 Drain oil.
2 Clean engine oil filter.
3 Flush the aircraft oil system to remove any circulating debris.
4 Clean engine chip detectors.
5 Service engine oil system with fresh, clean oil.
6 Perform a 30minute ground run at power. Observe engine operating limits and chip
warning lights. If operation is normal then remove, inspect, clean, and reinstall both
chip detectors. Return engine to service.
7 If a chip light is encountered during the second 30minute ground run, remove the
engine from service and send to an RollsRoyce Authorized Maintenance Center
(AMC). Clean the aircraft engine oil system per para 11.I.(2), this section.
NOTE: If a warning light illuminates within the next eight operating hours following
a 30 minute ground run, and the cause is determined to be an
accumulation of magnetic particles and debris (chips, flakes or slivers),
remove the engine and send to an RollsRoyce Authorized Maintenance
Center (AMC). Tag engine noting cause for rejection. This note is
applicable only after para 11.I. (3) (b), this section has been completed
(reference Oil Drain and Flush); otherwise, this is another event.
(c) A maximum of four occurrences of magnetic chip warning light encountered within any 50
hours of engine operation requires removal of the engine for shipment to an RollsRoyce
Authorized Maintenance Center (AMC).

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(4) Operational Check

(a) If magnetic plugs are removed for scheduled maintenance, perform an operational check
prior to reinstallation. Connect harness lead and bridge plug with a suitable conductor.
Check each plug separately for proper cockpit indication.
(b) Reinstall magnetic plug, tighten to 6080 lb in. (6.89.0 N.m)
J. Tedeco Manual Zapper
When operating an aircraft utilizing the Tedeco Manual Zapper the following applies:
(1) First Time Chip Light comes on;
The Chip Pulse switch should be activated to on.
(a) If the chip light goes out after activation of the Chip Pulse switch then continue the flight,
make a log book entry accordingly and observe engine operation and warning lights.
(b) If the chip light remains on after activation of the Chip Pulse switch, land and inspect the
magnetic plugs as soon as possible. This light is an indication of conditions which could
cause engine failure. When flying a multiengine aircraft, reduce the affected engine
output power to the minimum required for flight and land as soon as practical. If the light
is accompanied by abnormal noises, oil pressure or temperature, and singleengine flight
can be maintained, shut down affected engine and land as soon as practical. If
singleengine flight is not possible, reduce power of affected engine to the minimum and
land as soon as possible. After landing, inspect the magnetic plugs on the affected engine
for metal contamination prior to further engine operation. Refer to para 11.I., this section,
and make a log book entry accordingly.
(c) If during the 30 minutes following the first activation of the Chip Pulse switch, the chip
light comes on, land as soon as possible. This light is an indication of conditions which
could cause engine failure. When flying a multiengine aircraft, reduce the affected
engine output power to the minimum required for flight and land as soon as practical. If
the light is accompanied by abnormal noises, oil pressure or temperature, and
singleengine flight can be maintained, shut down affected engine and land as soon as
practical. If singleengine flight is not possible, reduce power of affected engine to the
minimum and land as soon as possible. After landing, inspect the magnetic plugs on the
affected engine for metal contamination prior to further engine operation. Refer to para
11.I., this section, and make a log book entry accordingly.
(2) Second Time Chip Light Comes On:
If the chip light comes on a second time within 50 hours of the first time, follow the procedure
in paragraph (1) above.
(3) Third Time Chip Light Comes On:
If the chip light comes on a third time within 50 hours of the first time, do not actuate Chip
Pulse. Land and inspect the magnetic plugs as soon as possible. This light is an indication of
conditions which could cause engine failure. When flying a multiengine aircraft, reduce the
affected engine output power to the minimum required for flight and land as soon as practical.
If the light is accompanied by abnormal noises, oil pressure or temperature, and singleengine
flight can be maintained, shut down affected engine and land as soon as practical. If
singleengine flight is not possible, reduce power of affected engine to the minimum and land
as soon as possible. After landing, inspect the magnetic plugs on the affected engine for
metal contamination prior to further engine operation. Refer to para 11.I., this section, and
make a log book entry accordingly.
NOTE: If a magnetic drain plug warning light received in the cockpit is confirmed to be
caused by an indicating system malfunction and no metal is found on the magnetic
drain plugs, this chip light incident does not count toward the total of four chip lights
in 50 hours.

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(4) Fourth Time Chip Light Comes On;

If the chip light illuminates a fourth time within 50 hours, do not activate Chip Pulse. Land as
soon as possible. This light is an indication of conditions which would cause engine failure.
When flying a multiengine aircraft, reduce the affected engine output power to the minimum
required for flight and land as soon as practical. If the light is accompanied by abnormal
noises, oil pressure or temperature, and singleengine flight can be maintained, shutdown the
affected engine and land as soon as practical. If the singleengine flight is not possible,
reduce power of affected engine to the minimum and land as soon as possible. Remove the
affected engine and send it to a repair facility. Tag engine, noting the reason for rejection.
(5) If the 50 hour time period is obtained with two or fewer chip light indications, a new 50 hour
sequence begins and appropriate adjustments to log entries should be made for previous 50
hour sequence.
K. If quick disconnect magnetic chip detector plugs are installed, inspect the locking pins and flanged
inserts for wear as follows:
(1) Inspect the 3 locking pins for proper condition and wear. The minimum allowable pin diameter
on any one pin is 0.070 in. (1.78 mm). The plug should be replaced by a serviceable item if
any one or more pin is worn to less than 0.070 in. (1.78 mm) diameter. (See Figure 303.)
NOTE: The point of wear is usually on the side of the pin nearest the spring loaded ring.
Push the ring back to obtain better access for inspection.
(2) Inspect the insert for proper condition and wear of the locking cam slot. The material
remaining between the end of the cam slot and the edge of the insert must be more than 0.068
in. (1.73 mm). (See Figure 303.) Replace the insert with a serviceable item if the area is
worn to less than 0.068 in. (1.73 mm). (Refer to Commercial Engine Bulletin 250B17F TP
CEB 722052 for details of insert replacement.)
NOTE: If local personnel, tooling, and facilities are inadequate for replacement, send the
gearbox assembly to an Authorized Maintenance Center (AMC).
(3) Reinstall serviceable magnetic plug.
(4) Reconnect electrical wiring as applicable.
(5) Replenish engine oil as necessary.
(6) Make the appropriate entry relative to the magnetic plug inspection on the Inspection Check
Sheet maintained as a part of the engine records.

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Quick Disconnect Magnetic Plug Wear Limits

Figure 303
12. Preservation and Depreservation
Areas of the engine requiring preservation are the oil system, fuel system and the compressor.
A. Inactive Engine Preservation.
Preserve stored engines (not in shipping container) or any engine installed in stored aircraft as
follows:
(1) Preserve the oil system in accordance with Oil System Preservation, para 12.B., if shutdown
period will exceed 45 days. Represerve at least each 90 days if stored outdoors and each 180
days if stored indoors.
(2) Preserve the fuel system in accordance with Fuel System Preservation, para 12.C., if
shutdown period will exceed 45 days. Represerve at least each 90 days if stored outdoors and
each 180 days if stored indoors.
(3) Preserve the compressor and engine gas path in accordance with Compressor Preservation,
para 12.E., if warranted by local corrosive conditions. Represerve at least each 30 days if
stored outdoors and each 90 days if stored indoors.
(4) Install compressor inlet cover. Attach No. 88 Absorbent Protective Dehydrating Agent, or
equivalent (MILD3464) to exhaust collector stack covers and install. Ensure that desiccant
does not contact metal surfaces. Inspect desiccant periodically (based on local humidity
conditions) and rejuvenate as necessary.
(5) During storage use a flagged wedge to hold the compressor bleed valve closed. Also, cover
the diffuser vent orifice hole and gearbox overboard vent.
(6) Store engines indoors if not installed in an aircraft or engine shipping container. Engine
Manufacturer recommends that installed engines be stored indoors if possible.
B. Oil System Preservation.
If the engine will be inactive for over 45 days, the oil system shall be preserved as follows:

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(1) For engines not installed in airframe or shipping container

(a) Remove oil filter cap and magnetic plugs. Service as necessary.
(b) Using 6799790 adapter and speed handle, turn engine while supplying clean, approved
engine oil to the filter housing. Continue until fresh oil drains from gearbox.
(c) Install new filter cap and magnetic plug packings. Install cap and plugs. (Refer to Oil
Filter Replacement, para 1.C., 726000 and to para 9.C., this section.)
(2) For operable engines installed in airframe:
(a) Service engine oil system (Refer to para 11.E., this section.)
CAUTION: DO NOT EXCEED AIRFRAME MANUFACTURER STARTER ENGAGEMENT
LIMITS.
(b) Motor engine at least two minute to ensure oil flow to all engine bearings.
C. Fuel System Preservation.
If the engine will be stored for over 45 days the fuel system shall be preserved as follows:
(1) For engines not installed in airframe:
(a) Remove the hose from the fuel nozzle; place the open hose end in a bucket.
(b) Loosen the clamp supporting the two tubes (Po) and (P1) between the fuel control and the
fuel pump. Remove the control bypass (Po) tube and plug the (Po) opening in the fuel
control.
(c) Supply filtered (10 micron) MILL6081 grade 1010 oil (Atlantic Refining Co. No. 31100 or
equivalent) or alternate MILL7870A oil (Gulf Oil Corp. Gulflite 6 or equivalent) at 50
psig (345 kPag) to the fuel inlet of a static engine.
(d) Move the fuel control cutoff lever to the open position.
(e) When oil is observed flowing into the container, remove the oil supply to the pump and
move the fuel control cutoff lever to the closed position.
WARNING: FAILURE TO PROPERLY INSTALL, ALIGN AND TIGHTEN FUEL, OIL, AND
AIR FITTINGS AND TUBES COULD RESULT IN AN ENGINE FAILURE.
(f) Permit the excess oil to drain from the fuel system before removing the plug and
reassembling the fuel system components. Tighten hose coupling to 80120 lb in.
(9.013.6 N.m); tighten (Po) tube coupling nuts to 150200 lb in. (1723 N.m); tighten
clamp nut to 3540 lb in. (3.94.5 N.m).
(2) For operable engines installed in airframe:
(a) Remove the hose from the fuel nozzle; place the open hose end in a bucket.
(b) Supply MILL6081 grade 1010 oil (Atlantic Refining Co. No. 31100 or equivalent) or
alternate MILL7870A oil (Gulf Oil Corp. Gulflite 6 or equivalent) to the fuel pump inlet.
CAUTION: DO NOT EXCEED STARTER LIMITATIONS WHILE MOTORING THE
ENGINE.
(c) Move the condition lever to the maximum position and motor the engine with the starter
(without ignition). When oil is observed flowing into the bucket, move the condition lever
to the FUEL OFFFEATHER position. Remove the oil supply to the pump inlet.
WARNING: FAILURE TO PROPERLY INSTALL, ALIGN AND TIGHTEN FUEL, OIL, AND
AIR FITTINGS AND TUBES COULD RESULT IN AN ENGINE FAILURE.
(d) Permit excess oil to drain from the fuel control then reinstall the fuel line. Tighten hose
coupling to 80120 lb in. (9.013.6 N.m).

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D. Fuel System Depreservation.

Depreserve the engine fuel system by making a normal start.
NOTE: In case of a false start or a start is not completed in a total time of one minute, return the
condition lever to FUEL OFFFEATHER position and motor the engine without ignition for
10 seconds.
E. Compressor Preservation
Application of preservative to the compressor shall be made as warranted by local corrosive
conditions encountered. In no case, when operating in a corrosive environment, shall the shutdown
period exceed 5 days without preserving the compressor.
(1) For engines not installed in airframe.
(a) Disconnect the fuel system pressure sensing (Pc) line from the Pc filter at the diffuser
scroll. Hold the Pc filter while disconnecting the coupling nut. Cap the line and the Pc
filter.
(b) Disconnect the bleed control valve pressure sensing (Pc) line from the elbow at the
diffuser scroll. Cap the line and the scroll fitting.
(c) Block the bleed control valve in the closed position using 6886204 compressor protector
cleaning kit.
(d) Ensure cockpit engine antiicing switch is off.
(e) Spray onequarter pint (0.1 liter) of preservative into the engine while it is being motored
with the starter and without ignition (ignition circuit breaker pulled). Use RustLick No.
606, Rocket WD40, or equivalent for the preservation. Use a sprayer with a quick
opening valve and a nozzle sized to spray onequarter pint (0.1 liter) of preservative in l
to 3 seconds. Hold the can of sprayer 8 to 12 in. (2030 cm) in front of the compressor.
Allow the preservative to be drawn into the compressor while spraying in a circular motion
which covers the entire intake area. As an alternate method of application use an aerosol
pressuretype spray can. Spray preservative from the can for 15 to 20 seconds while the
engine is being motored. Spray in a circular motion which covers the entire intake area.
CAUTION: DO NOT EXCEED 10% N1 RPM MOTORING SPEED. DO NOT INJECT A
SOLID STREAM OF FLUID INTO THE COMPRESSOR.
(f) Reconnect the control system and bleed control valve pressure sensing lines. Tighten
coupling nuts to 80120 lb in. (9.013.6 N.m). On configurations having a Pc filter, hold
the filter while tightening the coupling nut.
(g) Remove the wedge which was used to block the bleed control valve in the closed
position.
(h) Install the inlet and exhaust collector covers and keep the engine in a static condition after
preservative application.
CAUTION: THIS EXCEPTION TO THE RECOMMENDED WATER RINSE IS FOR
PRESERVATION REMOVAL ONLY AND DOES NOT ALTER THE
REQUIREMENT FOR DAILY WATER RINSE FOLLOWING EXPOSURE TO A
SALT WATER ENVIRONMENT. (REFER TO COMPRESSOR CLEANING,
PARA. 6., 723000.)
(i) Before starting the engine, remove the preservative and soft contaminants by water
rinsing and drying the compressor in accordance with the procedure given in Compressor
Cleaning, para 6., 723000.
NOTE: Operation of the engine prior to removal of compressor preservative may
contribute to early contamination of the compressor blades with a resultant
decrease in compressor efficiency. The recommended water rinse may be
omitted only if available power is closely monitored and a compressor cleaning
schedule is established.

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(2) For operable engine installed in airframe.

NOTE: To prevent the preservative from baking dry, be sure the compressor is cool to the
touch (bare hand) before application is made.
(a) Disconnect the fuel system pressure sensing (Pc) line from the Pc filter at the diffuser
scroll. Hold the Pc filter while disconnecting the coupling nut.
(b) Disconnect the bleed control valve pressure sensing (Pc) line from the diffuser scroll. Cap
the line and the scroll fitting.
(c) Block the bleed control valve in the closed position using the 6886204 compressor
protector cleaning kit.
(d) Ensure cockpit engine antiice switch is off.
CAUTION: DO NOT EXCEED 10% N1 RPM MOTORING SPEED. DO NOT INJECT A
SOLID STREAM OF FLUID INTO THE COMPRESSOR.
(e) Spray onequarter pint (0.1 liter) of preservative into the engine while it is being motored
with the starter and without ignition (ignition circuit breaker pulled). Use RustLick No.
606, Rocket WD40, or equivalent for the preservation. Use a sprayer with a quick
opening valve and a nozzle sized to spray onequarter pint (0.1 liter) of preservative in 1
to 3 seconds. Hold the can of sprayer 8 to 12 in. (2030 cm) in front of the compressor.
Allow the preservative to be drawn into the compressor while spraying in a circular motion
which covers the entire intake area. As an alternate method of application use an aerosol
pressuretype spray can. Spray preservative from the can for 15 to 20 seconds while the
engine is being motored. Spray in a circular motion which covers the entire intake area.
(f) Reconnect the control system and bleed control valve pressure sensing lines. Tighten
coupling nuts to 80120 lb in. (9.013.6 N.m), hold the Pc filter while tightening the
coupling nut.
(g) Remove the wedge which was used to block the bleed control valve in the closed
position.
(h) Install the inlet and exhaust collector covers and keep the engine in a static condition after
spraying with preservative.
CAUTION: THIS EXCEPTION TO THE RECOMMENDED WATER RINSE IS FOR
PRESERVATION REMOVAL ONLY AND DOES NOT ALTER THE
REQUIREMENT FOR DAILY WATER RINSE FOLLOWING EXPOSURE TO A
SALT WATER ENVIRONMENT. (REFER TO COMPRESSOR CLEANING,
PARA 5., 723000.)
(i) Before starting the engine, remove the preservative and soft contaminants by water
rinsing and drying the compressor in accordance with the procedure given in Compressor
Cleaning, para 5., 723000.
NOTE: Operation of the engine prior to removal of compressor preservative may
contribute to early contamination of the compressor blades with a resultant
decrease in compressor efficiency. The recommended water rinse may be
omitted only if available power is closely monitored and a compressor cleaning
schedule is established.

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