Rolls-Royce RR300 series Operation And Maintenance Manual

OPERATION and MAINTENANCE

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Initial issue 20 January 2008 Revision 6 Aug.15/2012

Publication ref. CSP21009

Export controlled

This document may contain information whose export is restricted by the Arms Export Control Act (Title 22, U.S.C., Sec 2751, Et Seq.) or the Export Administration Act of 1979, as ammended, (Title 50, U.S.C., App. 2401, Et Seq.). Violations to these export laws are subject to severe criminal penalties. This technical data is exported from the United States in accordance with the Export Administration regulations. Diversion contrary to U.S. law is prohibited. This technical data has been identified as 9E991, No License Required, by the Global Trade Compliance Office, Rolls-Royce Corp.

Liability disclaimer

This information is given in good faith, based on the latest information available. No warranty or other representation is given concerning such information, which must not be taken as establishing any contractual or other commitment by the company or any of its subsidiaries or associated companies

RR300 Series

Notice

The procedures, guidelines, and information set forth in this publication are based solely upon the Rolls-Royce FAA approved type design and are intended only for the operation, maintenance, repair and overhaul of Rolls-Royce type design parts. Rolls-Royce has no knowledge regarding the applicability of these procedures and guidelines or subsequent revisions thereof to parts designed and/or manufactured by entities other than Rolls-Royce or Rolls-Royce approved vendors and suppliers.

Proprietary rights legend Rolls-Royce Corporation

These technical data and the information embodied herein are the property of and proprietary to Rolls-Royce Corporation, and shall not, without prior written permission of Rolls-Royce Corporation be disclosed or duplicated in whole or in part. This legend shall be included on any reproduction of this data in whole or in part.

Printed in USA

Federal Aviation Administration Approved

Aug.15/2012

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Date

OPERATION and MAINTENANCE

Publication Ref: CSP21009

TRANSMITTAL LETTER No.6

Remove: Incorporate: Reason For Change:

CHAPTER 05

List of Effective Pages Page 1/2 Page 1/2

05-50-00-100-801 All Pages Pages 701 and 702 Revised - Changed

internal and external flush task sequence numbers WP191890

CHAPTER 72

List of Effective Pages Pages 1 to 3/4 Pages 1 to 3/4

72-00-00-100-803 All Pages Pages 701 to 703/704 Deleted tasks for external

rinse - WP191891

72-30-00-200-801 All Pages Pages 601 to 605/606 Revised - Revised

illsutration, FIG. 602 to match RR300 part WP195413

72-30-00-300-801 All Pages Pages 801 to 803/804 Revised - Revised

illustration, FIG. 801 to match RR300 part WP209753

72-30-05-200-801 All Pages Pages 601 to 603/604 Note added & illustration

modified - WP207805

72-40-50-300-801 All Pages Page 801/802 Revised - Task Deleted,

cannot repair dents in combustion liner assembly at OMM level - WP

217855.

72-60-10-000-805 All Pages Pages 401 to 404 Revision - Change to add

new removal tool 23083912 - WP215606

Remove: Incorporate: Reason For Change:

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72-60-10-400-805 All Pages Pages 401 to 406 Revision - Change to add

new installation tool 23083918 - WP215607

CHAPTER 73

List of Effective Pages Pages 1 and 2 Pages 1 and 2

CONTENTS Pages 1 and 2 Pages 1 to 3/4

73-11-10-700-801 Pages 501 to 503/504 First Issue - Test the fuel

nozzle - WP 209769

73-11-10-200-801 All Pages Pages 601 to 603/604 Revised - Added

instructions to inspection table to clean the fuel nozzle - WP 209768

73-11-10-100-801 Pages 701 to 705/706 First Issue - Clean the fuel

nozzle without disassembly - WP 209767

CHAPTER 79

List of Effective Pages Page 1/2 Page 1/2

79-23-10-400-801 All Pages Pages 401 to 404 Revised - Oil change

process to add bleeding of the #1 and 8 scavenge lines along with bleeding of the filter bowl WP191608

79-33-10-700-801 All Pages Pages 501 to 503/504 Revised - WP120364 :

Added tooling and changed nomenclature of part - WP120364

79-33-15-700-801 All Pages Pages 501 to 503/504 Revised - WP120366 :

Changed part nomenclature - WP120366

Record of Revisions Sheet Record incorporation

of TL 6 and date of incorporation on RECORD OF CERTIFIED REVISIONS

2

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INTRODUCTION

A. General

(1) Operation and Maintenance Manual

(a) The engine model designation used throughout this manual (RR300 Series) refers to the same

engine model (250-C300/A1) that is both stamped on the engine data plate and listed on the official Engine Type Certificate, Number E4CE, issued by the FAA. The RR300 Series Operation and Maintenance Manual (OMM) is part of a set of manuals that helps the operator do the necessary maintenance to the engine. It is written so a technician who does not know the engine can:

- Do the maintenance and the servicing of the engine systems and components

- Isolate failures of the engine systems and components.

- Use the OMM when the engine is installed on the aircraft.

(b) Rolls-Royce technical publications, in whole or in part, cannot be utilized as a means to

establish serviceability of material not manufactured or approved by Rolls-Royce. Rolls-Royce technical publications and documents are developed solely for use in support of applicable Rolls-Royce parts. Parts, materials, or processes not approved by Rolls-Royce were not considered in the development of Rolls-Royce technical publications due to Rolls-Royce not having knowledge of any specifications or design criteria for parts, overhaul or repair processes of parts or material not authorized by Rolls-Royce. Therefore, Rolls-Royce technical publications must not be used to support or maintain engines, modules, or parts using details, parts, materials, or processes that are not Rolls-Royce approved. Rolls-Royce disclaims any liability for the performance or the failure to perform of engines, modules or parts that have been maintained or supported using parts, materials, or processes not authorized by Rolls-Royce.

(2) Related Manuals

(a) The manuals included in the set are the:

- Operation and Maintenance Manual (OMM)

- Line Level Illustrated Parts Catalog (LLIPC).

B. Potential Safety Issues

(1) When performing maintenance on RR300 Series engines, the approved maintenance facilities are

responsible for reporting safety related items. Safety related items must be reported to Rolls-Royce Customer Service (REF. Section L.) and the Federal Aviation Administration. Refer to FAR 145.221 Service Difficulty Reports.

C. The Specifications of this Manual

(1) This manual is written to the Air Transport Association of America Specification No. 100 (ATA 100),

Revision 31. The writing rules and the vocabulary are in accordance with the ASD Simplified Technical English, Specification ASD-STE-100, Issue 3. All the spelling is in American English.

D. Manual Content

(1) Manual Frontmatter.

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(a) The OMM contains a set of manual frontmatter and a set of chapters. The manual frontmatter

includes:

- The Title page

- The Record of Revisions

- The Frontmatter List of Effective Pages

- The Table of Contents

- The List of Service Bulletins

- The Introduction.

(2) The Chapter Number System.

(a) The OMM has these groups of chapters:

1 General

- Chapter 05 - Time Limits/Maintenance checks

- Chapter 12 - Engine Servicing

- Chapter 70 - Standard Practices - Engine

2

Power Plant

- Chapter 71 - Power Plant

- Section 1 - Engine Description

- Section 2 - Engine Performance and Operation

3 Engine

- Chapter 72 - Engine

- Chapter 73 - Engine Fuel and Control

- Chapter 74 - Ignition

- Chapter 75 - Air

- Chapter 77 - Engine Indicating

- Chapter 79 - Oil

- Chapter 80 - Starting.

(3) Tab Dividers.

(a) At the front of each chapter there is a yellow tab card. The chapter number and title are printed

on the tab. There is also a yellow tab card at the front of the Introduction.

(4) Identification Code.

(a) An identification code that has six numbers divides the chapter into its related parts. This

identification code is divided into three elements. Each element contains two numbers. The code divides the data into:

- Chapter/System (First element)

- Section/Sub-system (Second element)

- Subject/Unit (Third element).

(5) The List of Temporary Revisions.

(a) The List of Temporary Revisions (LETR) lets the operator make a record of the Temporary

Revisions (TRs) that affect each Chapter.

(6) The Page Number System.

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(a) A system of page numbers divides each Chapter-Section-Subject (CH-SE-SU) into page

blocks and topics, as follows:

- Page Block 1 - Description and Operation

- Page Block 101 - Fault Isolation

- Page Block 201 - Maintenance Practices

- Page Block 301 - Servicing

- Page Block 401 - Removal/Installation

- Page Block 501 - Adjustment/Test

- Page Block 601 - Inspection/Check

- Page Block 701 - Cleaning/Painting

- Page Block 801 - Repairs.

(b) The page identification code, which includes the CH-SE-SU code, is given at the bottom right

side of each page.

(7) The Chapter List of Effective Pages (LEP).

(a) The LEP of a chapter gives a list, in page block sequence, of pages contained in the chapter.

The LEP includes a list of the Contents and the LEP pages.

(b) The data adjacent to each page number on the LEP shows the correct revision date for that

page. The number of pages contained in a chapter and the data on each page must agree with the LEP data.

(c) Each time a chapter has a revision, a new LEP is issued to give the new revision date of the

changed pages.

(8) The Chapter Contents Pages.

(a) The chapter contents pages gives a list, in CH-SE-SU number sequence, of the subjects

included in a chapter. The topics for each subject are shown in page block sequence.

(9) The Figure Number System.

(a) The figure number system in a page block is the same as the page number system. For

example, the second figure in a Maintenance Practices page block is FIG. 202. The figures for each task are at the end of the task.

(10) Data in this Manual.

(a) The data in this manual includes:

- The data necessary to do the scheduled maintenance tasks

- The data that describes the engine, its structure and systems, and tells how the systems operate

- The procedures and related safety precautions for on-wing servicing and maintenance necessary for continued airworthiness.

E. Page Block and Topic Contents

(1) Page Block 1 - Description and Operation.

(a) This topic gives sufficient data to train maintenance persons to know the function, the

configuration, the operation and the control of the system or component.

(2) Page Block 101 - Fault Isolation.

(a) This topic gives the procedures to isolate and correct faults in a system or component.

(3) Page Block 201 - Maintenance Practices.

(a) This topic includes all maintenance procedures, applicable to a CH-SE-SU, easily contained in

one page block. Page Block 201 is also for those maintenance procedures that are not related to the topics of other page blocks.

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(4) Page Block 301 - Servicing.

(a) This page block contains the applicable data for the scheduled and the unscheduled servicing.

(5) Page Block 401 - Removal/Installation.

(a) This topic gives the data necessary for the removal and installation of a unit/assembly.

(6) Page Block 501 - Adjustment/Test.

(a) This topic gives the data necessary to adjust and/or do a test of a system, sub-system,

assembly, or unit. There are two types of tests:

1 The Operational Test is the procedure to make sure that a system, sub-system, assembly,

or unit operates. Special equipment is not necessary for this test.

2 The Functional Test is the procedure to make sure that a system, subsystem, assembly,

or unit is correctly adjusted and operates fully to its specification. The test usually uses special equipment to measure the performance of the system, sub-system, assembly, or unit.

(7) Page Block 601 - Inspection/Check.

(a) This topic gives the data necessary to make sure that a system, sub-system, assembly, unit, or

part is serviceable.

1

Inspection Tables tables are divided into four categories.

a The first category is ITEM. The ITEM category contains the engine component, or

sub-assembly of that component. The type of damage or condition of the part or sub-assembly is directly under the part nomenclature and is hyphenated.

b The second category is the SERVICEABLE LIMIT. The SERVICEABLE LIMIT is

defined as the maximum degree of a specified condition which can be accepted and lets the part be placed back into service without repair. No other action is necessary.

c The third category is the REPAIR LIMIT. The REPAIR LIMIT is defined as the

maximum degree of a specified condition which can be repaired. Any condition exceeding this limit cannot be corrected by the specified repair procedure; therefore, the part must be replaced.

d The fourth category is ACTION NECESSARY. The ACTION NECESSARY is defined

as the recommended corrective action for a given condition.

(8) Page Block 701 - Cleaning/Painting.

(a) This topic gives the data necessary to clean and/or paint parts or areas of the engine.

(9) Page Block 801 - Repairs.

(a) This topic gives repair procedures that are necessary during on-wing maintenance and are not

included in another manual.

F. Effectivity

(1) The EFFECTIVITY Block.

(a) The effectivity block is located in the lower left corner of the page. The effectivity block

identifies engine model, maintenance data, or other maintenance information that applies to the configuration of the engine. The data must be considered satisfactory for all of the engine models when the effectivity block has been removed or is blank.

G. How to Use this Manual

(1) The Applicable Data.

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(a) To find the data applicable to your task:

1 Refer to the list of chapters in para D. (2)(a) of this Introduction and find the chapter

related to the necessary data.

2 Read the yellow tab cards to identify the necessary chapter.

3 Open the manual at the start of the applicable chapter and refer to the contents pages.

NOTE: The contents page of each chapter gives a list of the data/procedures in the

related chapter. The list is in CH-SE-SU sequence. The page blocks of each CH-SE-SU are in number sequence.

4 Identify the CH-SE-SU on the contents page.

5 Identify the page block applicable to the necessary data (Refer to para D. (6) of this

Introduction for a list of the page block numbers and their titles).

6 An example of the procedure given in the above para G. (1)(a) of this Introduction is as

follows:

a

To find the data to remove and install a fuel nozzle, you must:

- Identify that the item is part of the fuel system.

- Refer to the List of Chapters in para D. (2)(a)2 Power Plant.

- Identify Chapter 73 - Engine Fuel and Control.

- Use the yellow tab cards in the manual to find Chapter 73 - Engine Fuel and Control.

- Refer to the Contents at the start of Chapter 73 and identify the necessary data, which is 73-11-10, Page Block 401 - Fuel Nozzle Removal/Installation.

- Open the manual at 73-11-10, Page Block 401, where you will find the necessary procedures to remove and install the fuel nozzle.

(2) Aircraft Maintenance Task Oriented Support System (AMTOSS).

(a) AMTOSS Codes.REF. FIG. 1

1 AMTOSS codes are included in page blocks 201 thru 801. AMTOSS gives each of the

maintenance procedures (tasks) and the primary steps of the procedures (subtasks) a different number identification code.

2 The identification code numbers have a minimum of five elements and a maximum of

seven elements. These elements are an extension of the three-element ATA 100 CH-SE-SU numbers. Refer to FIG. 1 for an example of task and subtask code.

(b) Function Codes.

1 The function codes in the AMTOSS task (T) and subtask (S) numbers show the type of

work that has to be done. The function codes used and a description of each is in the list that follows:

2 Function code 000 - Removal.

APPL FC APPLICATION OF THE FUNCTION CODES

T 000 REMOVAL

EFFECTIVITY: ALL

The subtask content of the removal task must mirror that of its associated installation task. In particular, the 400 function codes used must bear a direct relation to the 000 codes. This number is only used for a task title line, i.e., Remove the Fuel Nozzle.

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APPL FC APPLICATION OF THE FUNCTION CODES

T/S 010 REMOVE/OPEN FOR ACCESS

S 020 REMOVE UNIT/COMPONENT/or any part of the UNIT Removal of

T/S 040 DEACTIVATE

S 080 REMOVE TEST/SUPPORT EQUIPMENT

Remove or open a panel, door, component, etc. to gain access to the task subject or to allow the core subtask to be done. Includes removal/disconnection of items that impede access but are not related to the task subject.

the Unit (the ATA breakdown subject) including all attaching and connected parts. This can also include capping of lines, electrical connectors, etc.

Deactivation of the system. Covers making a system component etc. inoperable for maintenance by means other than circuit breaker, blocking tools, etc., which are covered by specific codes.

Remove or disconnect any tool that has been defined as special or standard and that is not covered by function codes 941/942.

3 Function code 100 - Cleaning.

APPL FC APPLICATION OF THE FUNCTION CODES

T 100 CLEANING

This is not to be used for preparation for another task. This number is only used in a task title line.

T/S 110 CHEMICAL

Use chemical agent(s) to clean. Includes preparation of the chemical.

T/S 120 ABRASIVE

Remove unwanted materials with WET/DRY particle impingement.

T/S 130 ULTRASONIC (SOUND WAVES)

Remove unwanted surface material and other materials caught in the surface using high-frequency sound.

T/S 140 MECHANICAL

Remove unwanted materials with a brush, lint-free cloth or other mechanical procedure.

T/S 150 STRIPPING

Removal of paint, etc. from metal or non-metal surfaces using mechanical or chemical process. Also includes the removal of any residue from the process.

T/S 160 MISCELLANEOUS CLEANING

T/S 170 FLUSHING

EFFECTIVITY: ALL

Remove unwanted material with compressed air, suction, by hand, etc.

Flush unwanted material through and out of a component or system with fluid.

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4 Function code 200 - Inspection/Check.

APPL

T 200 INSPECTION/CHECK

T/S 210 GENERAL VISUAL

T/S 220 DETAILED DIMENSIONAL

T/S 230 PENETRANT

T/S 240 MAGNETIC

T/S 250 EDDY CURRENT

FC APPLICATION OF THE FUNCTION CODES

This number is only used in a task title line, i.e. Inspect the Desiccator Crystals.

Full inspection of ZONE/SYSTEM/SUBSYSTEM/COMPONENT/PART to find structural damage, failure, and/or deterioration. Gives the proper corrective maintenance procedure if necessary. Not to be used for FOD checks, during job close-up, etc.

Inspect dimensions, conditions, or indications of COMPONENTS/SUBSYSTEMS/SYSTEMS. Compare with specifications in the original design documentation to decide whether further maintenance is required. Include checks of indicators and other readouts to confirm that a value is within limits.

Find surface cracks with dye penetrant techniques.

Find surface cracks in a material by means of magnetic fields.

Use electromagnetic waves to find internal cracks, porosity, very small openings, unwanted materials, or non-homogeneous material structure.

T/S 260 X-RAY/HOLOGRAPHIC

To find internal cracks, porosity, very small openings, unwanted materials, or non-homogeneous material structure.

T/S 270 ULTRASONIC

To find internal cracks, porosity, very small openings, unwanted materials, or non-homogeneous material structure.

T/S 280 SPECIFIC/SPECIAL

For procedures NOT INCLUDED in codes 210-270 and 290. Includes abnormal operation and continued service procedures.

T/S 281 SAMPLING

Procedures to obtain small representative quantities of materials (gas, liquid, or solid) for the purpose of analysis.

T/S 290 BORESCOPE

To do an internal examination of a component, part and/or assembly.

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5 Function code 300 - Repair.

APPL

T 300 REPAIR

T/S 310 WELDING/BRAZING

T/S 320 MACHINING/RENAMING/BLENDING

T/S 330 COMPOSITE

T/S 340 FIBERGLASS/PLASTIC/HONEYCOMB/EPOXY

T/S 350 MISCELLANEOUS REPAIR

T/S 360 LEAKAGE REPAIR Repair leaks (except by application of

T/S 370 PAINTING

FC APPLICATION OF THE FUNCTION CODES

This number is only used in a task title line.

Join parts together by any welding or brazing method.

Repair metal parts or assemblies.

Repair composite materials.

Repair fiberglass, plastic, honeycomb or epoxy materials. Also includes adhesive bonding, rubber molding, fiberglass molding, silicone rubber bonding/molding, etc.

Repair those materials or parts not included above.

sealants/compounds -see code 390).

Application of primer and top coat to any area. Includes surface pre-treatment and cleaning, mixing, application, and curing.

T/S 380 SPECIAL

For procedures NOT INCLUDED in codes 210-270 and 290. Includes abnormal operation and continued service procedures.

T/S 390 SEALING

Apply fairing compounds, sealants, or other materials to control corrosion, fill clearance, prevent leakage, provide a hold, or smooth aerodynamically. Includes preparation of materials, cleaning of surfaces, mixing and curing.

6 Function code 400 - Installation.

APPL FC APPLICATION OF THE FUNCTION CODES

T 400 INSTALLATION

This number is only used in a task title line, i.e. Install the Fuel Nozzle.

T/S 410 INSTALL/CLOSE FOR ACCESS

Install or close a panel, door, component, etc. used to gain access to the task subject or to allow the core subtask to be done. Includes installation/re-connection of items that impeded access but are not related to the task subject.

T/S 420 INSTALL UNIT/COMPONENT Installation of the Unit (the ATA

breakdown subject) includes all attaching and connected parts. This is the core Subtask of an installation task for the complete ATA subject number unit.

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APPL FC APPLICATION OF THE FUNCTION CODES

T/S 440 DEACTIVATE

T/S 480 INSTALL TEST/SUPPORT EQUIPMENT

7 Function code 500 - Material Handling.

APPL FC APPLICATION OF THE FUNCTION CODES

Deactivation of a system. Covers making a system component, etc. operable after maintenance by means other than circuit breakers, blocking tools, etc., which are covered by specific codes.

Install or connect any tool that has been defined as special or standard, and the purpose of which is to show or simulate the condition, position, status, etc. of a system component. Does NOT include test equipment installed as an integral part of the core subtask unless the installation is sufficiently complex to warrant a separate subtask. Includes items that are not physically connected to the aircraft, such as a radio test transmitter. Also includes rigging pins, etc. installed for purposes other than rigging the system in which they are fitted (see code 941).

T 500 MATERIAL HANDLING

This number is only used in a task title line.

T/S 530 PACKING

Packing consists of installation of parts, sub-assemblies, or assemblies in shipping containers. This includes all capping of lines, installation of plugs, etc. Applicable to prepare a component after removal from aircraft for storage.

T/S 540 UNPACKING

Unpacking is defined as the removal of items, sub-assemblies, or assemblies from shipping containers. This includes all removal of all protection material. The component that is the subject of an installation task is to be considered as unpacked, depreserved, etc.

T/S 550 STORAGE/RETURN TO SERVICE

Storage is the safekeeping of the aircraft/engine and assemblies/sub-assemblies until required for use. Can require specific procedures not covered by any other function codes. Return to service is the specific procedure to prepare for operation.

S 560 MARSHALLING

Marshalling refers to the collecting of individual parts, sub-assemblies, or assemblies prior to release for assembly. This function code must be used for replacement component preparation before installation. One subtask must cover the complete preparation procedure.

T 580 AIRCRAFT HANDLING

T/S 581 LIFTING

EFFECTIVITY: ALL

See breakdown below.

ATA Chapter 7.

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APPL FC APPLICATION OF THE FUNCTION CODES

T/S 582 JACKING

T/S 583 SHORING

T/S 584 TOWING

T/S 585 TAXIING

T/S 586 LEVELING AND WEIGHING

8 Function code 600 - Servicing/Preserving/Lubrication.

APPL FC APPLICATION OF THE FUNCTION CODES

T 600 SERVICING/PRESERVING/LUBRICATION

ATA Chapter 7. Includes lifting and lowering the jacks.

ATA Chapter 7.

ATA Chapter 9.

ATA Chapter 8.

This number is only used in a task title line.

T/S 610 SERVICING

To keep in good operational condition, including procedures not specified by other breakdowns in this series. Includes replenishing (filling) of fluids (oil, hydraulic, water, etc.).

T/S 614 GAS CHARGING/DISCHARGING

Tires, accumulators, etc.

T/S 620 PRESERVING

This is the preparation of a component/part for safekeeping from decomposition or deterioration. Includes preparation for storage by applying a preservative layer to, and desiccants in, hardware. It also includes the prevention of microbial growth in fuel tanks, application of corrosion inhibitants and protection, etc. Does not include aircraft storage, which is covered by Function Code 550.

T/S 630 DEPRESERVING

Depreserving pertains to removing the preservative layer and/or desiccants form the component/part in preparation for installation or operation.

T/S 640 LUBRICATING

ONLY for PURE lubrication tasks and subtasks. Lubricate moving parts.

T/S 650 FUELING/DEFUELING

Fuel movement for all operational and maintenance purposes.

T/S 660 DEICING/ANTI-ICING

EFFECTIVITY: ALL

Removal and prevention of ice and snow build-up on parked aircraft and applications to prevent the accumulation of ice and snow.

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APPL FC APPLICATION OF THE FUNCTION CODES

T/S 670 DISINFECT/SANITIZE

T/S 680 DRAIN FLUID

9 Function code 700 - Testing.

APPL FC APPLICATION OF THE FUNCTION CODES

T 700 TESTING

T/S 710 OPERATIONAL

Core subtask for health conditions. Can include draining (where integral to the task), cleaning and handling of lavatory components, etc.

During servicing or other maintenance procedures, such as water, oil, fuel, lavatories, etc. This is the other half of replenishing when the system is to be emptied and filled.

This number is only used in a task title line.

An operational test verifies that the system or component is operable, without taking into account specifications and tolerances that are usually established for overhaul or major maintenance periods. The test requires no special equipment. Can include BITE functions.

T/S 720 FUNCTIONAL

A functional test verifies that a system or component is functioning within the minimum design specifications. This test is more detailed than an operational test and can require special test equipment. Values and tolerances must be specified. Can include BITE functions.

T/S 730 SYSTEM

Contains all specifications and tolerances necessary to make sure the system and its components are performing at maximum design efficiency. The test must be sufficiently thorough to detect early signs of wear, deterioration, and calibration drift. The test can require special test equipment. Values and tolerances must be specified. The test is self-contained and can duplicate another test. Can include BITE functions.

T/S 740 BITE

Used for tasks (and subtasks where the test is part of a task procedure). Those checks conducted using Built-In Test Equipment (BITE) and Maintenance Diagnostic System (MDS) including the power-up test.

T/S 750 SPECIAL

Used for tasks (and subtasks where the test is part of a taskprocedure). Special checks such as smoke check, sniff checks, etc.

T/S 760 ELECTRICAL

EFFECTIVITY: ALL

Electrical checks to determine continuity, voltage, resistance, etc.

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APPL FC APPLICATION OF THE FUNCTION CODES

T/S 780 PRESSURE

T/S 790 LEAK

10 Function code 800 - Miscellaneous.

APPL FC APPLICATION OF THE FUNCTION CODES

T 800 MISCELLANEOUS

T/S 810 FAULT ISOLATION

Establishes the ability of a normally pressurized system or component to operate properly.

Make sure a system or component does not leak or does so within specified limits. Procedures for application of leak check solutions.

This number is only used in a task title line.

Fault isolation consists of the following procedures:

- Operating the engine to locate the prime suspect deficient system

- Operating an improperly functioning system or component in order to locate the cause of the malfunction

- Performing a series of prescribed checks to isolate a failed part or component.

T/S 820 ADJUSTING/ALIGNING/CALIBRATING

Make a physical correction to ensure proper placement, operation or testing of a system or component.

T/S 830 RIGGING

Check, and, as necessary, adjust mechanically operated systems such as flight control cables, actuator arms, push-pullrods, etc. Includes installing and removing rigging pins, blocks, boards, etc. where specifically used to give an indication of the state of rigging.

T/S 840 PREPARE FOR . . ., RESTORE . . ., TO NORMAL . . .

Used when separate tasks are provided for preparing for maintenance or restoring to normal after maintenance when these procedures are lengthy and identical for several applications.

T/S 850 OPERATOR MODIFICATION INCORPORATION

Operator use only. Complete tasks only.

T/S 860 AIRCRAFT/SYSTEM CONFIGURATION

Make sure the aircraft is in an approved condition for maintenance or to return it to an operational configuration. This code also covers operating any system or component in order to accomplish a task. Also specifically covers the following operations:

- Energize electrical network

- De-energize electrical network

- Pressurize hydraulics

- De-pressurize hydraulics

- Circuit breaker opening

- Circuit breaker closing.

T/S 870 BLEEDING

EFFECTIVITY: ALL

Remove air from a system or unit filled with fluid.

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APPL FC APPLICATION OF THE FUNCTION CODES

T/S 880 HEATING/COOLING

11 Function code 900 - Change = Removal + Installation.

APPL FC APPLICATION OF THE FUNCTION CODES

T 900 CHANGE = REMOVAL + INSTALLATION

T/S 910 STANDARD PRACTICES

T/S 930 PAINT MARKING

T 940 JOB SET-UP/CLOSE-UP

Application of heating or cooling required for removal, installation, adjustment, or testing.

This code links the removal and installation procedures of a component or item.

Refer out of normal tasks to this code. Task can only be located in Chapter 20, 51, and 70.

To paint markings and letters.

See breakdown below.

S 941 JOB SET-UP

Covers the positioning of general support equipment NOT covered by the codes 480/080. Specifically: access platforms, steps, warning notices, and fire extinguishers.

S 942 JOB CLOSE-UP

Covers the removal of general support equipment NOT covered by the codes 480/080. Specifically: access platforms, steps, warning notices, and fire extinguishers.

S 950 MASKING

Masking or unmasking required for painting, cleaning, surfaceprotections, etc.

T/S 960 REPLACE

The removal and installation of minor components (O-rings, etc.) when completely covered within one subtask. Normally only for limited use within servicing tasks.

S 965 TRANSFER PARTS

To be used for the transfer of parts from the removed component to the installed component.

S 970 DATA RECORDING/CALCULATING

Recording of data required for monitoring, testing, adjusting, checking, etc., and subsequent calculation.

S 980 MANUAL OPERATION OR POSITIONING

Manually positioning or operating a system component or unit that is normally powered, such as turning engine rotor manually, translating thrust reversers, etc.

S 990 ILLUSTRATIONS

EFFECTIVITY: ALL

To be used when creating illustration tasks only.

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H. Abbreviations and Terms

(1) The following terms and abbreviations will be used in this manual.

ABBREVIATIONS AND TERMS

TERM DEFINITION

AGB Accessory Gearbox

GI Ground Idle

GPT Gas Producer Turbine

ID Inside Diameter

IGN Ignition

ISA International Standard Atmosphere

MGT Measured Gas Temperature

LP Low Pressure

MCT Maximum Continuous

MTO Maximum Takeoff

OD Outside Diameter

PT Power Turbine

RMS Root Mean Square

RPM Revolutions per Minute

Wf Engine Fuel Flow Rate

I. Conversions

(1) The following conversion factors will be used in this manual.

CONVERSIONS

U.S. Metric

1 in. (inch) 25.4 mm (millimeters)

1 in.² (square inch) 6.4516 cm² (square centimeters)

1 ips (inch per second) 2.54 cm/s (centimeters per second)

1 SFM (surface foot per minute) 0.3048 SMM (surface meters per minute)

°F (degrees Fahrenheit) 9/5 (°C) + 32 (°C = degrees Celsius)

1 US gal (US gallon) 3.785 liters

1 US gal (US gallon) 0.8326 Imperial gallons

1 psi (pound per square inch) 6894.757 Pa (Pascals)

1 psi (pound per square inch) 6.894757 kPa (kiloPascals)

1 psi (pound per square inch) 6894.757 N/m² (Newtons per square meter)

1 inHg (inch of mercury at 32 °F (0 °C) 0.03389 bar

1 inHg (inch of mercury at 32 °F (0 °C) 25.40 mmHg (millimeters of mercury)

EFFECTIVITY: ALL

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CONVERSIONS

U.S. Metric

1 inHg (inch of mercury at 32 °F (0 °C) 0.4912 psi (pounds per square inch)

1 inHg (inch of mercury at 32 °F (0 °C) 3.387 kPa (kiloPascals)

1 ft-lb (pound-foot) 1.35582 Nm (Newton-meters)

1 in-lb (pound-inch) 0.112985 Nm (Newton-meters)

1 lbf (pound force) 4.44822 N (Newtons)

1 tonf (ton force) 8896.44 N (Newtons)

1 lb (pound) 0.45359 kg (kilograms)

1 oz (ounce) 28.3495 g (grams)

1 SCFM (Standard Cubic Foot per Minute) 28.317 SLM (Standard Liters per Minute)

J. Revisions and Service Bulletins

(1) Issue of Revisions.

(a) The manufacturer regularly issues revisions to the maintenance manual to keep it at the correct

standard. The revisions add, remove, and/or change data as necessary. All revisions are by replacement of pages. You must not use hand-written revisions.

(b) A letter of Transmittal is sent with each revision. The transmittal letter:

- Is the authority to put the revision into the manual

- Gives instructions on how to put the revision into the manual.

(c) You are recommended to keep the transmittal letters at the front of the manual for reference.

(d) Each revision has a specified number and date. Revisions start at No. 1 and continue in

sequence.

(e) A Record of Revisions page is located at the front of the manual. When you put a revision into

the manual, you must write the revision number and its issue date on the Record of Revisions page.

(f) A vertical block line or an upper case "R" at the left side of a page shows that the data adjacent

to the line has changed. If a black line is aligned with the page number and date, this means that the data has not changed, but some of the data on the page has moved to or from a different page.

(2) Temporary Revisions.

(a) When it is necessary to include data in the manual quickly, a Temporary Revision (TR) is

issued. The first page of the TR gives the transmittal instructions. The data/instructions in a TR replace the equivalent data/instructions in the manual. A TR can also be used to include data before the subsequent revision.

(b) Each TR is printed on yellow paper. The TR numbers are in sequence and start at - 1 in each

chapter. The chapter number goes in front of the TR number to give each TR an identification code. For example 72-1, 72-2, 72-3, and so on, 79-1, 79-2, 79-3, and so on.

(c) The data/instructions in a TR are included in a revision (usually, the subsequent revision to the

manual) or a subsequent TR replaces it. When a revision includes the data/instructions of a TR, the transmittal letter includes an instruction to remove the applicable TR. When a subsequent TR replaces a TR, the subsequent TR includes an instruction to remove the applicable TR. You must not remove a TR from the manual unless you get an instruction to do so in the Transmittal Letter of a revision or on the first page of a subsequent TR.

EFFECTIVITY: ALL

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(d) In each chapter, immediately after the List of Effective Pages page, is a Record of Temporary

Revisions page. When you put a TR into the manual, you must write the TR number and the date you put the TR into the manual on the Record of Temporary Revisions. When you remove a TR from the manual, you must write the date you removed the TR from the manual on the Record of Temporary Revisions.

(3) Service Bulletins and Service Letters

(a) At the front of this manual, immediately after the Table of Contents, is the Service Bulletin List.

The data given includes the service bulletin (SB) number, title, date, and the date of incorporation into this manual, if applicable. When applicable, review engine records for compliance with all mandatory service bulletins, inspections and Airworthiness Directives.

K. Consumable Materials

(1) Non-restricted Consumable Materials. You can use equivalent materials as an alternative to the

materials in these lists. You can get the materials from local suppliers and/or manufacturers.

MATERIALS

Acetone O-A-51

Acid, sulfuric

Alcohol, isobutyl MIL-E-463

Alcohol, isopropyl TT-I-735

Compound, antisieze CP-63

Compound, antisieze NSN-165

Compound, anti-sieze, Lubriplate 130A

Dessicant MIL-D-3464

Dichromate, sodium

Oil, engine AS5780 HPC

Oil, engine MIL-PRF-23699

Oil, lubricating MIL-L-7808

Oil, preservation MIL-L-6081 grade 1010 or

MIL-L-7870A

Perchloroethylene

Sodium bicarbonate O-S-576

SPECIFICATION

Solution, cleaning (Ref. Paragraph K.(2))R

Solvent, dry-cleaning P-D-680

Solvent, Pentatone ECS

Solvent, Stoddard MIL-PRF-680

Spirits, mineral, EMS-6

Trichloroethane MIL-T-81533

Water, distilled

EFFECTIVITY: ALL

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(2) The Approved Manufacturers column of the table lists a supplier for each item; equivalent products

are permitted. To find if an item is equivalent, the operator and supplier must show proof, not the manufacture engineer. The consumable materials used to maintain the engine are in the table that follows:

MATERIAL

Engine Oil Refer to Section

Lubricant Lubriplate 130A Fiske Brothers Refining Co.

Grease ROYCO HF-825 Royal Lubricants Co., Inc.

SPECIFICATION APPROVED MANUFACTURERS USE

12-10-79, Table 1, Approved Oils.

129 Lockwood Newark, New Jersey 07105

280 Complex 101 Eisenhower Parkway Roseland, New Jersey 07068

Sundstrand P/N 718050 or 71850 (recommended)

ASTM No. 5 Oil Sun Oil Co.

Sundstrand Corp. 4751 Harrison Avenue Rockford, Illinois 61108

1608 Walnut Street Philadelphia, Pennsylvania 19103

Lubricate bearings, packings, fuel pump external drive splines and starter-generator and front spare accessory drive splines that require engine oil.

Lubricate accessory splines (Starter-generator and front spare accessory drive splines and fuel pump external drive splines that require engine oil are not included).

Seal and bearing installation and assembly aid.

Fuel pump drive shaft (internal splines, external splines require engine oil and are not included).

Lubricate packings in fuel control air passages.

Alternates to ASTM No. 5 Oil:

- 45 to 55% fuel (MIL-C-7024B, Type II) mixed with 45 to 55% STP oil treatment.

- MIL-D-6081, Grade 1010 oil.

Lubriplate Aero Fiske Brothers Refining Company

Lubriplate Division 1500 Oakdale Avenue Toledo, Ohio 43605

Petrolatum Commercial Assembly aid.

Sealer Scot Clad 776 Scotch Clad Coatings Minnesota

Mining and Mfg. Co. 3M Center St. Paul, Minnesota 55119

Fuel pump and fuel control drive shafts (Argo Tech/TRW pumps).

Gearbox splitline.

EFFECTIVITY: ALL

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MATERIAL SPECIFICATION APPROVED MANUFACTURERS USE

Sealer (cont) DC 994 Dow Corning Corp.

South Saginaw Road Midland, Michigan 48641

RTV 732 or RTV 736 Dow Corning Corp.

South Saginaw Road Midland, Michigan 48641

RTV 106 General Electric Corp.

Waterford, New York 12188

Devcon F (aluminum)

Reisweld FE 186 H.B. Fuller Co.

Metal Set A-4 Smooth-on Inc.

Epon 934 Hysol Div. Dexter Corp.

Scotch-Weld 2214 Product of the 3M Company

Devcon Corp. 59 Endicott Street Danvers, Massachusetts 01923

2400 Kasota Avenue St. Paul, Minnesota 55102

1000 Valley Road Gillette, New Jersey 07933

2850 Willow Pass Road Pittsburgh, California 94565

Adhesives and Sealers Division 2501 Hudson Road St. Paul, Minnesota 55119

Gearbox splitline.

Compressor case splitline.

Compressor mounting insert installation.

Hysol EA9432NA, EA934, EA9394

Epocast 938-A1, 938-A2

Magnobond 6398 Magnolia Plastics Inc.

Loctite 620 or 602 Loctite Corp.

Sealant No. 1372 W Permatex Co. Inc.

Silicone resin-clear (AMS

3135)

METCOSEAL AP METCO Inc.

Locktite Corp. 705 North Mountain Road Newington, Connecticut 06111

Huntsman Advanced Materials 10003 Woodloch Forest Drive The Woodlands, Texas 77380

5547 Peachtree Industrial Boulevard Chamblee, Georgia 30341-2296

705 North Mountain Road Newington, Connecticut 06111

Box 1350 Flagler Court Bldg. West Palm Beach, Florida 33402

1105 Prospect Avenue Westbury, Long Island, New York 11590

Installation of labyrinth stationary seal bearing area.

Assembly-oil bellows seal.

Compressor mount repair.

EFFECTIVITY: ALL

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MATERIAL SPECIFICATION APPROVED MANUFACTURERS USE

Silicone resin-clear (AMS

3135) (cont)

Assembly fluid Ultra Chem No. 1 Ultra Chem Inc.

Antiseize compound

Methylethyl-ketone Commercial General cleaning.

Carbon removal compound

1-2531 Dow Corning Corp.

South Saginaw Road Midland, Michigan 48640

1400 N. Walnut Street Wilmington, Delaware 19899

Never-Seez Nickel Special (NSN 165) Bostik

DC 550 FLUID Dow Corning Corp.

CP-63 (MIL-L-25681B)

Gunk Hydroseal Decarbonizer (MIL-C-25107)

Emhart Chemical Group Boston Street Middleton, Massachusetts 01949

South Saginaw Road Midland, Michigan 48641

E/M Lubricants Inc. P.O. Box 2200 Highway 52 N.W. West Lafayette, Indiana 47906

Gunk Laboratories Inc. 630 North Harlem Avenue Oak Park, Illinois 60302

Compressor mount repair.

Assembly aid.

Hot section external threads (not used on parts that have contact with the engine oil system) or assembly compressor adapter nut.

External threads protect up to 450°F (232°C).

External threads not exposed to oil system. Protects to 1400°F (760°C).

Clean aluminum coated steel parts.

Cresol base cleaning compound

Cleaner Turbine Cleaner No.

Formula No. 3097 (MIL-C-546)

1191 (MIL-C-43616)

20-20 Plus (MIL-C-43616)

Turbo Clean or Turbo Clean 2

R-MC ECT, Inc.

Turco Products Inc. Subsidiary of ELF Autochem 7320 Bolsa Avenue Westminster, California 94684-3600

The Brulin Corp. P.O. Box 270 2920 Dr. Andrew J. Brown Avenue Indianapolis, Indiana 46206

B & B Chemicals Co. Inc. P.O. Box 796 Miami, Florida 33166

Kent Chemical Co., Ltd. George House, Bridwell Lane Tenterton Kent TN306HS England

771 First Avenue King of Prussia, Pennsylvania 19422

Clean steel parts.

Clean compressor air flow path; clean fuel nozzle tip and burner drain valve.

EFFECTIVITY: ALL

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MATERIAL SPECIFICATION APPROVED MANUFACTURERS USE

NOTE: Rolls-Royce recommends you obey the mixture ratios identified by each aircraft skin cleaner manufacturer. The mixture ratios change from manufacturer to manufacturer and can be found on each container label. You must obey the application procedure described in this manual. This will prevent compressor or engine and control system damage.

Cleaner (cont) Penair M5704 Penetone Corp.

74 Hudson Avenue Tenafly, New Jersey 07670

B & B 3100 B & B Chemical Co. Inc.

P.O. Box 796 Miami, Florida 33166

No. 5884 Turco Products, Inc.

Subsidiary of ELF Autochem 7320 Bolsa Avenue Westminster, California 94684-3600

Racasan 512-M Odex Racasan, Ltd.

Cromwell Road Elesmere Port South Wirral L654DP, England

ARDROX 624 Brent Chemicals International

Ardrox Division Ridgeway, Iver Buckinghamshire SLO955, England

AERDROX 6345 Sure Chem Industries Pty., Ltd.

23 Amex Avenue Girraween, New South Wales, 2145

Compressor wash.

EFFECTIVITY: ALL

Rochem GTE (krankwash)

ZOK 27 Airworthy Ltd.

Turco 6783-10 and Turco 6783-50

B & B TC-100N-1 B & B Tritech, Inc.

Ardrox 6367-Turbo Clean 2

Rochem, Inc. 5619 S. Wayside Drive Houston, Texas 77087

Wedglen Industrial Estate Midhurst Sussex G299RE, England

Turco Products, Inc. Subsidiary of ELF Autochem 7320 Bolsa Avenue Westminster, California 94684-3600

Miami, Florida 33266-0766

921 Sherwood Drive Lake Bluff, Illinois 60044-0215

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MATERIAL SPECIFICATION APPROVED MANUFACTURERS USE

Perchlorethylene or Methylene chloride

Mineral spirits Commercial General cleaning.

Calibration fluid Stoddard solvent,

refine kerosene (MIL-F-7024, type II) 300 to 400°F (148.9 to 204.4°C) boiling range.

Carbon solvent Penmul L460 Pentetone Corp.

Brulin No. 815 QR The Brulin Corp.

Turco No. 4181 Turco Products, Inc.

Commercial Cleaning agent.

Commercial Cleaning fuel nozzle tips.

Cleaning fuel nozzle. 74 Hudson Avenue Tenafly, New Jersey 07670

P.O. Box 270 2920 Dr. Andrew J. Brown Avenue Indianapolis, Indiana 46206-0270

Subsidiary of ELF Autochem 7320 Bolsa Avenue Westminster, California 94684-3600

Rust preventative compound

Preservation oil No. 31100

Anti-corrode 204 (MIL-C-6529, type 1)

Valvoline TECTYL 890

Royco 103 Royal Lubricants Co., Inc.

(MIL-L-6081, Grade

1010)

Gulflite 6 (MIL-L-7870A)

MIL-6081, Grade 1010 or 1005 NATO Symbol Code 0-132 and 0-133 Bray, K-80, K-877, K-460

Cities Service Oil Co. P.O. Box 300 Tulsa, Oklahoma 74102

Ashland Petroleum Co. Division of Ashland Oil Inc. P.O. Box 391 Ashland, Kentucky 41101

River Road East Hanover, New Jersey 07936

Atlantic Richfield Co. 260 South Broad Street Philadelphia, Pennsylvania 19101

Gulf Oil Corp. 429 7th Avenue Pittsburgh, Pennsylvania 15230

Bray Oil Co. 1925 North Marina Avenue Los Angeles, California 94804

Coat steel parts after cleaning.

Shipping container bolts.

Fuel system preservation.

EFFECTIVITY: ALL

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MATERIAL SPECIFICATION APPROVED MANUFACTURERS USE

Preservation oil (cont)

Chemical film treat

Moisture absorbing rust preventative

McMillan Jet Oil 1005 or 1010

Royco 460, 481 Royal Lubricants Co., Inc. East

Aeroshell Turbine Oil2Shell International Petroleum Co.,

Chem-Rite A22 (MIL-C-5541)

No. 606 Rust-Lick Inc.

Rocket WD 40 (MIL-C-23411)

WD-40 Dr. Oskar Trost Industrie and Auto

McMillan Ring Free Oil Co., Inc. 200 Petroleum Building El Dorado, Arizona 71730

River Road Hanover, New Jersey 07936

Ltd. Shell Centre London SE1 7NA, United Kingdom

M and T Chemicals Inc. Church Street Matawan, New Jersey 07747

755 Boylston Street Boston, Massachusetts 02116

WD 40 Co. San Diego, California

Chemie 2350 Numuenster West Germany

Fuel system preservation.

Cleaned anodized aluminum alloy parts.

External engine surfaces only.

Heat resistant paint

Engine grey enamel

WD-40 Betriebs and Werkstatt-Zubehoer

GmbH Riedstrasse 257302 Ostfildern 1-Ruit West Germany

WD-40 Hawker Pacific Pty., Ltd.

4-8 Harley Crescent Condell Park New South Wales 2200 Australia

Ardrox 3961 Ardrox Limited

Commerce Road Brentford, Middlesex, England

Ardrox 3961 Ardrox Australia Pty. Ltd.

Birnie Avenue Lidscombe N.S.W. 2141, Australia

CRC 3-36 CRC Chemicals Division

C.J. Webb Inc. Limekiln Pike Dresher, Pennsylvania 19025

Actithane WC100 Saran Protective Coatings Co.

17332 Shields Detroit, Michigan 48212

Actithane WC100 Paint and Lacquer Reducer H251

Saran Protective Coatings Co. 17332 Shields Detroit, Michigan 48212

Gearbox paint repair or galvanic corrosion protection.

Gearbox touch-up.

EFFECTIVITY: ALL

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MATERIAL SPECIFICATION APPROVED MANUFACTURERS USE

Engine grey enamel (cont)

Corrosion resistant aluminum paint

Weld rod X-40 (EMS 70175) or

Weld rod AISI 349 (29-9 W

Weld rod Hastelloy W (AMS

Marking pencils See Acceptable Marking Pens and

Moisture proof barrier material

PU Grey Paint, Code 03-GY-401 Color #16251 Fed. Std. 595B

Sermetel 196 Teleflex Inc.

alternate Haynes 188 (AMS 5801)

Mo) (MIL-R-5031, Class 6) (AMS 5784)

5786) (MIL-R-5031, Class 12)

Flexkin 100P (MIL-B-131)

DEFT Chemical 17451 Von Karmon Avenue Irvine, California 92714-6205

P.O. Box 218 North Wales, Pennsylvania 19454

Commercial First-stage turbine nozzle.

Commercial Combustion liner and exhaust

Commercial Turbine and exhaust collector,

Pencils Table.

Acme Backing Corp. P.O. Box 360 Stamford, Connecticut 06904

Gearbox touch-up.

Gas producer and power turbine

support.

collector support.

struts.

Marking hot section parts.

Engine packing.

Dehydrating Agent 16-unit bags

Pressure sensitive masking tape: 1- or 2- in. (25- or 51- mm) width.

Black stencil K-1 (TT-I-559) March Stencil Machine Co.

Methyl alcohol Fed. Spec O-M

Desiccant No. 88 Absorbent

CS-16 (MIL-D-3464) Filtrol Corp.

3250 East Washington Los Angeles, California 90023

No. 260 Scotch Brand

232d, Grade A; Rolls-Royce EMS-125. British Standard BS 506 Amend. 1.

Protective Dehydrating Agent (MIL-D-3464)

Minnesota Mining and Mfg. Co. 3M Center St. Paul, Minnesota 55101

707 East B Street Belleville, Illinois 62222

Commercial Solvents Corp. 245 Park Avenue New York, New York 10017 or Union Carbide Corp. Chemicals and Plastics 270 Park Avenue New York, New York 10017

Delta Packing Products 4108 North Nashville Avenue Chicago, Illinois 60634

Storage and shipment.

Compressor water rinse.

Shipping package humidity

control.

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MATERIAL SPECIFICATION APPROVED MANUFACTURERS USE

Liquid leak detector

Corrosion compound

Sodium hydroxide and phosphoric

Sealant removal Loctite “chisel”

Adhesive Loctite 290 Loctite Corp.

SNOOP (meets MIL Spec (MIL-L-25567C), type I, oxygen systems)

Leak-Tec Formula 372E

Non-Rust X-210 Daubert Chemical Co., Inc.

Ardrox 3968 Chemetall Aerospace

solvent

Indiana Valve and Fitting Inc. P.O. Box 24267 Indianapolis, Indiana 46224

American Gas and Chemical Co. 5 Tefnakil Park Cresskil, New Jersey 07626

4700 S. Central Avenue Chicago, Illinois 60038

Technologies Trakehner Str. 3 D-60487 Frankfurt Main Germany

Commercial Cleaning Pc filter Bendix control

Loctite Corp. 705 North Mountain Road Newington, Connecticut 06111

705 North Mountain Road Newington, Connecticut 06111

Checking for pneumatic leaks.

Inhibiting fingerprint corrosion.

system.

Removal of Loctite 620 or 602.

Oil pump gearshaft retention.

Fuel additive Prist (MIL-I-27686E) PPG Industries Inc.

5629 FM 1960 West Houston, Texas 77069

Biobor JF Aviation Fuel Additive

Torque paint Torque Seal F-900 Organic Products Co.

Torque paint remover

High temperature lubricant

F-100 Remover Organic Products Co.

Never-Seez Nickel Special

Hammonds Technical Services, Inc. 910 Franklin Road Houston, Texas 77073 Ph: (281) 999-2900 Fax: (281) 582-4224 Email: info@hammondscos.com Web: www.hammondscos.com

P.O. Box 428 Irving, Texas 75060-0428

Never-Seez Compound Corp. 2910 South 18th Street Broadview, Illinois 60153

Bearing Supply and Service 448-472 Notre Dame Avenue Winnipeg 2, Canada

Fuel anti-ice.

Anti-microbial growth MIL-S-53021A.

Application of marks to pnuematic and lubrication system “B” nuts to show movement.

Removal of torque paint.

Where anti-seize is specified in this manual.

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MATERIAL SPECIFICATION APPROVED MANUFACTURERS USE

High temperature lubricant (cont)

R.A. Rodriguez (U.K.) Ltd. Station House-Darkes Lane Potters Bar Herts, England

Consolidated Brg, Co. Pty. Ltd. 238 Victoria Road Drummoyne, N.S.W. Australia

Kyokuto Boeki Kaisha Ltd. 7th Floor, New Otemachi Bldg. 2-1, 2-Chrome Otemachi Chiyoda-Ku, Tokyo, 100-91 Japan

S.A. Brasileira De Rolamentos E. Mancais BRM Av. Senador Queiroa 605 Conj. 1609 Sao Paulo, Brazil

Tekind Via F. Malzi D'Eril, 3 20154 Milano, Italy

DSL Super HI-Temp Davis-Howland Oil Corp.

200 Anderson Avenue Rochester, NY. 14607

Where anti-seize is specified in

this manual.

NOTE: Even though Rolls-Royce has approved these consumables for use with Rolls-Royce engines. Rolls-Royce assumes no liability to personnel or the environment by their use.

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 that get to temperatures above 800°F (427°C) by heat treatment or engine operation. Markings on these alloys do not have to be removed from the parts before heating above 800°F (427°C). These pencils, markers, and paint sticks are also approved for marking titanium alloys if the markings are removed before the parts get to temperatures above 500°F (260°C) by heat treatment or engine operation.

(3) The acceptable marking pens and pencils used to maintain the engine are in the table that follows:

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

Venus (1) Unique 1215 White

A.W. Faber The Winner 2388 White

Berol Corp. (2) Eagle Verithin 734 White

Venus (1) Unique 1206 Blue

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MANUFACTURER TRADE NAME NUMBER COLOR

Koh-1-Noor (4) Flexicolor X1800X25 Blue

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 30 Blue

Sanford Corp. (12) T.E.C. Marker 3201 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 Marker

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

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Markal Company (7) Paintstik Type B Purple

American Artclay Co. (8) Glass Cellophane 2346 Blue

NOTE: Dri-Marquette Black Ink, a product of the Irwin-Hodson Co. (9), is approved for marking on iron, nickel, and cobalt alloy parts. The markings do not have to be removed before they get to temperature above 800°F (427°C).

NOTE: Dri-Marquette Black Ink may be used on titanium alloys but must be removed before they get to temperatures above 500°F (260°C).

NOTE: LNC-3 Nuclear Grade Electrolyte, a product of the Lectroetch Co. (10), is approved for electrolytic etching on iron, nickel, cobalt, titanium, aluminum, and magnesium alloys. This process is 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 before they get to temperatures above 500°F (260°C).

Manufacturer Addresses

(1) Venus-Esterbrook Corp.; Lewisburg, Tennessee 37091 (2) Berol Corp.; P.O. Box 1000, Danbury, Connecticut 06810 (3) Faber-Castell Corp.; P.O. Box 1708, 41 Dickerson Street, Newark, New Jersey 07103 (4) Koh-1-Noor Rapidograph Inc.; 100 North Street, Bloomsbury, New Jersey 08804 (5) Eberhard Faber Inc.; Crestwood Industrial Park, Wilkes-Barre, Pennsylvania 18703 (6) Carters Ink Co.; 275-T Wyman Street, Waltham, Massachusetts 02154 (7) Markall Co.; 270 North Washtenaw Avenue, Chicago, Illinois 60612 (8) American Art Clay Co. Inc.; 4717 West 16th Street, Indianapolis, Indiana 46224 (9) Irwin-Hodson Co.; Ninth and S.E. Woodward, Portland, Oregon 97202 (10) The Lectroetch Co.; 14925 Elderwood Avenue, Cleveland, Ohio 44112 (11) Tempil Division Big Three Industries Inc.; 2901 Hamilton Boulevard, South Plainfield, New Jersey 07080 (12) Sanford Corp.; Bellwood, Illinois 60104

L. Customer Support Information

(1) If you find it necessary to write to Rolls-Royce about the manual, please write to:

Manager, Publication Services

Rolls-Royce Corporation

P. O. Box 420

Speed Code U-15

or contact

Rolls-Royce Corporation

PO Box 420, Speed Code P-38

Indianapolis, Indiana 46206-0420

USA

Toll Free (North America)+1-(888) 255-4766

Phone: +1 (317) 230-2720R

Fax: +1 (317) 230-3381

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Figure 1

INTRODUCTION

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CHAPTER 05

LIST OF EFFECTIVE PAGES

CHAPTER SECTION OTHER SUBJECT PAGE IDENT DATE 05

Contents 1 Dec.15/11 Contents 2 Dec.15/11 00-00 1/ Sep.15/10

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604

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CHAPTER SECTION OTHER SUBJECT PAGE IDENT DATE 05

--------------- END ---------------

CHAPTER SECTION OTHER SUBJECT PAGE IDENT DATE 05

C=CONFIG B=BREAKOUT

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CHAPTER 05

The RR300 Series is designed as an engine with a fixed preventative maintenance interval (PMI) 2000 hours, 3000 cycles, or 12 years, whichever comes first. If, as a result of an inspection, it is necessary to remove an engine or a component, the owner/operator mustR use past experience with the engines condition to determine if additional preventative and/or corrective maintenance is necessary before installation of the engine or the component. Contact a Rolls-Royce representative, if necessary.

Maintenance scheduling for the RR300 Series engine is determined by:

- Compliance with the Airworthiness Limitations (REF. 05-11-00)

- Rolls-Royce recommended scheduled maintenance checks (REF. 05-20-00)

- Rolls-Royce recommended unscheduled maintenance checks (REF. 05-50-00)

- Rolls-Royce recommended fault isolation instructions

- Rolls-Royce Service Bulletin effectivity and compliance statements

For purposes of this section, "disassembly" is defined as the level of disassembly, for any reason, of the engine or the components that allows for inspection of the exposed piece parts. It is not intended to require disassembly beyond the level necessary to do the applicable scheduled or unscheduled maintenance or inspections.

These maintenance reviews and actions are to be performed in accordance with the provisions of Federal Aviation Regulations (FAR) Parts 43.13 and 43.15.

These maintenance reviews and actions are to be documented in accordance with the provisions of FAR parts 43.9 or 43.11, as appropriate.

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TASK 05-10-00-800-801

1. RR300 SERIES TIME LIMITS

A. General

This section contains the life limits for the critical engine parts. Refer to section 05-11-00 (Airworthiness Limitations) and section 05-12-00 (Life Limits) for specific information.

R R

Scheduled inspections for the RR300 Series engine are shown in section 05-21-00. Scheduled maintenance checks are shown in section 05-20-00.

TIME LIMITS

SYSTEM DESCRIPTION SECTION

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TASK 05-11-00-800-801

1. Airworthiness Limitations

A. Airworthiness Limitations

OPERATORS ARE REQUIRED BY THE FAA TO COMPLY WITH THE PARTS LIFE LIMITATIONS INDICATED HEREIN. THE OPERATOR ALONE MUST MAINTAIN RECORDS OF BOTH HOURS AND CYCLES. BOTH TOTAL TIME AND ACCUMULATED CYCLES OF APPLICABLE COMPONENTS MUST BE RECORDED IN PART I SERVICE RECORD AND PART VI CYCLE RECORD PAGES RESPECTIVELY FOR THE COMPRESSOR ASSEMBLY AND TURBINE ASSEMBLY. FAILURE TO RECORD HOUR AND CYCLE DATA OF APPLICABLE PARTS IN THE LOG BOOK WILL RESULT IN THOSE PARTS BEING REPLACED AT THE OPERATOR'S EXPENSE WHEN ENGINES OR COMPONENTS ARE RETURNED FOR PMI OR SCHEDULED MAINTENANCE. REFER TO LOG BOOK ENTRIES, PARAGRAPH 1.C. OF THIS TASK,R FOR EXAMPLES OF LOG BOOK ENTRIES PERTAINING TO CYCLE AND HOUR RECORDS ON LIFE LIMITED PARTS.

NOTE

: All Life Limited Parts removed from a type certified product must be tagged to identify the

part. The tag or record must include the part number, serial number and current life status of the part, hours, and cycles. Each time the part is removed, either a new tag or record must be created, or the existing tag or record must be updated with the current life status of the part. The tag or record must remain with the part at all times when not installed. When a life limited part is removed from service due to meeting the published life limits, vibropeen or etch the words "life expired" next to or under the part number. A life limited part, other than new (however, proper paper work to provide traceability is still required), must have a tag or record attached.

THIS AIRWORTHINESS LIMITATIONS SECTION HAS BEEN APPROVED BY THE FEDERAL AVIATION ADMINISTRATION (FAA). IT SPECIFIES MAINTENANCE REQUIRED UNDER SECTIONS 43.16 AND 91.403 OF THE FEDERAL AVIATION REGULATIONS UNLESS AN ALTERNATIVE PROGRAM HAS BEEN APPROVED BY THE FAA.

The parts listed under the compressor rotor, the gas-producer-turbine rotor, the power-turbine rotor must be replaced when the life-limit is reached (see section 05-12-00, Life LimitsR ). The operator must record both hours and cycles of engine use. In computing part life, calculations must be based on cycles or hours accumulated since time of manufacture.

The inspections in section 05-21-00 (Scheduled Inspections) are mandatory and must be performed at the stated intervals.

B. Life Limited Parts

Chapter 05-12-00 contains FAA approved life limitations for those engine parts that are life limited.

Life limits of parts are based on total hours or total cycles, which ever occurs first.

(1) Definition of an Engine Hour

Operating hours with respect to maintenance records means the time from the moment an aircraft leaves the surface of the earth until it touches at the next point of landing.

(2) Definition of an Engine Cycle

A cycle is defined as a start or start attempt when fuel ignition occurred. The operator is required to keep a record of engine cycles.

AIRWORTHINESS LIMITATIONS

SYSTEM DESCRIPTION SECTION

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C. Log Book Entries

CAUTION: WHENEVER AN ENGINE, COMPRESSOR OR TURBINE IS PUT IN SERVICE, THE

CURRENT NUMBER OF CYCLES AND OPERATING HOURS ON THE LIFE LIMITED PARTS SHOULD BE REVIEWED AND COMPARED WITH THE MAXIMUM LIMITS SPECIFIED.

(1) Maintenance of the Total Time and Cycle Records is the operator's responsibility. This

information appears in the Part V Assembly Record of the Turbine and Compressor Log Book pages. The number of cycles remaining on a part can be determined by subtracting current cycles from the maximum cycles specified. The lowest number of cycles remaining for any part in the turbine or compressor can now be added to the present cycle count. This figure must be entered in the appropriate Part VI page in the column headed by "Cycle Reading Not to Exceed". This figure will provide a projected cycle count at which the component must be removed from service unless time (maximum operating hours) is the limiting parameter. Other information such as Cycle Reading at Installation, Date, Engine Serial Number, and Owner must be entered on the Part VI page at this time. Also make appropriate entries in the applicable Part I Service Record page.

(2) At time of compressor or turbine removal, the number of cycles must be recorded in the

"Removed Cycle Reading" column of the applicable Cycle Record Page VI page. Also, the number of cycles acquired on the turbine or compressor in this installation must be recorded in the "Cycles This Installation" column (subtract cycle counter reading at installation from cycle counter reading at removal).

(3) Make appropriate entries regarding removal in the applicable Part I Service Record page.

(4) Be sure to return all turbine or compressor pages of respective components with the

components at time of overhaul or repair.

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TIME LIMITS/MAINTENANCE CHECKS

SYSTEM DESCRIPTION SECTION

TASK 05-12-00-800-801

1. RR300 SERIES LIFE LIMITS

A. Compressor Rotor

CAUTION: DO NOT TOUCH TITANIUM PARTS WITH BARE HANDS. WEAR CLEAN, LINT FREE,

WHITE COTTON GLOVES OR USE PROTECTIVE ANTI-PERSPIRANT HAND CREAM. THE PARTS MUST BE KEPT IN A PROTECTIVE MATERIAL. IF YOU TOUCH TITANIUM PARTS WITH BARE HANDS CORROSION TO THE PART CAN OCCUR.

Maximum

Operating

Nomenclature Part No. Description

Impeller RR30000332 Original 10000 15000

B. Gas Producer Turbine Rotor Assembly

CAUTION

CAUTION: DO NOT INSTALL FIRST AND SECOND STAGE TURBINE WHEELS WHICH HAVE

: DO NOT INSTALL A TURBINE WHEEL WITH PERMITTED WHEEL RIM CRACKS IN A

PREVENTATIVE MAINTENANCE INTERVAL (PMI) REPAIR. PERMITTED WHEEL RIM CRACKS IN A TURBINE WHEEL CAN ONLY BE USED DURING A TIME CONTINUED REPAIR. ENGINE MALFUNCTION CAN OCCUR.

INDICATIONS THAT THE BLADE TIPS HAVE RUBBED OTHER PARTS. IF COMPRESSOR COMPONENTS FAIL THEY CAN ENTER THE AIRFLOW OF THE ENGINE AND CAUSE THE TIPS OF THE FIRST AND SECOND STAGE TURBINE BLADES TO RUB THE SECOND STAGE TURBINE NOZZLE RING. STRESS IN THE BLADES AND FATIGUE FAILURE CAN OCCUR. FIRST AND SECOND STAGE TURBINE WHEELS MUST BE REMOVED FROM SERVICE IF THE TIP OF ONE BLADE HAS A RUB INDICATION.

Hours

Maximum

Cycles

Nomenclature Part No. Description

1st-stage Wheel RR30000235 Original 2025 3000

1st-stage WheelR RR30000465R New Coating (Alt)R 2025R 3000R

1st-stage WheelR RR30000481R New Coating (Alt)R 2025R 3000R

2nd-stage Wheel RR30000237 Original 2025 3000

2nd-stage WheelR RR30000482R Subsequent releaseR 2025R 3000R

Gas Producer Turbine Tie-Bolt

2nd-stage Turbine Nozzle

EFFECTIVITY: ALL

Maximum Operating

Hours

23068265 Original ---- 9000

23084419 Original 2025 3000

SYSTEM DESCRIPTION SECTION-801

05−12−00

Maximum

Cycles

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C. Power Turbine Rotor Assembly

CAUTION: DO NOT INSTALL A TURBINE WHEEL WITH PERMITTED WHEEL RIM CRACKS IN A

PREVENTATIVE MAINTENANCE INTERVAL (PMI) REPAIR. PERMITTED WHEEL RIM CRACKS IN A TURBINE WHEEL CAN ONLY BE USED DURING A TIME CONTINUED REPAIR. ENGINE MALFUNCTION CAN OCCUR.

Maximum Operating

Nomenclature Part No. Description

3rd-stage Wheel RR30000236 Original 4050 6000

4th-stage Wheel RR30000240 Original 4050 6000

Hours

Maximum

Cycles

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TIME BETWEEN OVERHAULS AND ON-CONDITION ACCESSORIES AND COMPONENTS

TASK 05-13-00-800-801

1. Time Between Overhauls

A. Time Between Overhauls

(1) This section gives information on the RR300 accessories recommended time between

overhauls (TBO).

Component

SYSTEM DESCRIPTION SECTION

P/N

Recommended

TBO Hours

Fuel Pump and Filter (Goodrich)

Fuel Control (Honeywell)

Power Turbine Governor (Honeywell)

Fuel Nozzle RR30000242 2000

Starter-generator RR30000412 1000

(2) RR300 - On-condition accessories and components

- Accumulators (Fuel System Pneumatic)

- Anti-ice Solenoid Valve

- Anti-ice Air Valve

- Anti-ice Switch

- Burner Drain Valve

- Combustion Liner

- Compressor Discharge Air Tubes

- Double Check Valve

- Engine Monitoring Unit

- Fuel System Check Valve

- Generator Control Unit

- Igniter Lead

- Igniter Plug

- Ignition Exciter

- MGT Harness

- N1 Speed Sensor

- N2 Speed Sensor

- Oil Filter Assembly

- Oil Pressure Sensors - TMOP and MOP

- Outer Combustion Case

23074705 3500

RR30000454 2000

23076061 23086749

2000

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- Pc Air Filter

- Temperature Sensor Bulb - MOT

- Thermocouple

- Tubes and Hoses (Fuel, Lube and Air)

- Turbine Oil Check Valve

(a) Accessories and components can stay in service if operation and condition is satisfactory

at the 200-hour and 400-hour scheduled inspections (Ref. TASK 05-20-00-800-801).

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SCHEDULED MAINTENANCE CHECKS

SYSTEM DESCRIPTION SECTION

TASK 05-20-00-800-801

1. Scheduled Maintenance Checks

A. General

This section contains Rolls-Royce's recommendations for a scheduled maintenance program for the RR300 Series engine. These recommendations MUST be followed by operators who have not established an airworthiness-authority-approved program based on Maintenance Steering Group - 3 (MSG-3) analysis or other approved methodology.

CAUTION: DO NOT FAIL TO CORRECTLY ASSEMBLE THE COMPONENTS OR PARTS OF THE

ENGINE. ENGINE MALFUNCTION CAN OCCUR.

The RR300 Series is designed as an engine with a fixed Preventative Maintenance Interval (PMI). If, as a result of an inspection, it is necessary to remove the engine or a component, the owner/operator mustR use past experience with the engines condition to find if additional preventative and/or corrective maintenance is necessary before installation of the engine or the component. Contact a Rolls-Royce representative, if necessary.

These maintenance reviews and actions are to be done in accordance with the provisions of FAR Parts 43.13 and 43.15.

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SCHEDULED INSPECTIONS

SYSTEM DESCRIPTION SECTION

TASK 05-21-00-800-801

1. Scheduled Inspections

A. Engine Systems and Components

This section contains the Rolls-Royce recommended inspection items for the 200 hour inspection and the 400 hour or 12 month (whichever occurs first) inspection. If the engine operation conditions are specified for the operator to do the 100 hour inspections, TABLE 601, the 200 Hour Inspection Checksheet, can be used to do the inspection.

WARNING: DO NOT DO MAINTENANCE ON THE ENGINE WITHOUT READING THE APPLICABLE

TASK IN THE OPERATION AND MAINTENANCE MANUAL. IF YOU DO NOT FOLLOW THE INSTRUCTIONS IN THE APPLICABLE MAINTENANCE TASK YOU CAN CAUSE INJURY OR DEATH.

CAUTION: DO NOT DO MAINTENANCE ON THE ENGINE WITHOUT READING THE APPLICABLE

TASK IN THE OPERATION AND MAINTENANCE MANUAL. IF YOU DO NOT FOLLOW THE INSTRUCTIONS IN THE APPLICABLE MAINTENANCE TASK YOU CAN CAUSE DAMAGE TO THE ENGINE.

CAUTION

CAUTION: DO NOT FAIL TO COLLECT THE FUEL FROM THE TYGON TUBE ATTACHED TO THE

: DO NOT FAIL TO CORRECTLY EXAMINE AND/OR REPAIR COMPONENTS OR PARTS

OF THE ENGINE. ENGINE MALFUNCTION CAN OCCUR.

AIRCRAFT PRESSURE PORT. THIS CAN CAUSE FUEL TO COLLECT IN THE ENGINE COMPARTMENT. FIRE OR DAMAGE TO THE EQUIPMENT CAN OCCUR.

TABLE 601 - 200 Hour Inspection

200 Hour Inspection Checksheet

Owner________________________________________________ Date________________

A/C Make/Model_____________________ S/N_________ Reg. No._____ TSN__________

Engine S/N_________________________ TSN____________ TSO___________________

This inspection checksheet is to be used when performing scheduled inspections. This form may be

locally reproduced and/or expanded to reflect the aircraft operating environment. Keep the completed

sheets as a permanent part of the aircraft engine records. Detailed information regarding each inspection item is contained in the referenced Operation and Maintenance Manual paragraphs.

Item Inspection/Maintenance Action REFERENCE X Initial

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1 Examine the engine for loose or missing bolts, broken

or loose connections, security of mounting accessory and broken or missing lock wire. Check accessible areas for obvious damage and indications of fuel or oil leakage.

NOTE: If excessive cracks, chafing, fretting, loose

connections or other issues are identified, inspect the engine for possible vibration causes.

2 Examine all the B-nuts and make sure that the torque

paint is applied and is aligned correctly. If missing, loosen the B-nut, torque, and apply the torque paint.

3 Examine mounting and support bolts to be sure they

are tight, lockwired and in good condition. Check security of screws and rivets.

4 Remove all unwanted material that can go into the

compressor inlet.

5 Examine Pc filter for correct clamping. TASK 73-11-20-400-801

6 Examine the fuel system components that you can

access, tubes, and connections for security, damage or leakage. Remove, examine and clean if necessary.

TASK 72-00-00-200-801

TASK 70-00-00-910-801 TASK 70-00-00-910-808 TASK 73-00-00-400-801 TASK 79-00-00-400-801

OEM AMM

TASK 72-00-00-200-801 and OEM AMM

TASK 72-00-00-200-801 TASK 73-00-00-000-801 TASK 73-00-00-100-801 TASK 73-00-00-200-801 TASK 73-00-00-400-801

7 Examine the fuel control and power turbine governor

linkage for freedom of operation, full travel and proper rigging. Check security of linkage for loose or worn linkage and linkage bolts.

7AR Remove, Inspect, Clean, and Install Fuel Nozzle. TASK 73-11-10-100-801R

8 Examine compressor inlet and impeller leading edges

for foreign object damage.

9 Clean the engine gas path. TASK 72-00-00-100-801

10 Examine the electrical harnesses for loose, chafed,

frayed or broken wires. Make sure the connectors are torqued correctly.

11 Examine the horizontal and vertical fireshields for

damage.

12 Examine the compressor scroll for cracks or breaks at

the anti-ice air valve, Pc fitting, customer bleed port, and all welds. If cracks or breaks are found, check engine for possible vibration causes.

TASK 73-23-10-700-801 and OEM AMM

and OEM AMMR

TASK 05-50-00-200-801

TASK 72-00-00-200-801 OEM AMM

TASK 72-00-00-200-801

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13 Examine the anti-icing valve, N1 and N2 sensors,

TMOP, MOP, and MOT sensors for loose, chafed, frayed or broken wires, loose connectors, and security of attachment.

14 Examine compressor discharge air tubes for damage or

deterioration.

15 Examine the outer combustion case for condition of all

surfaces, welds, and the brazed screen reinforcement in the armpit area.

16 Without disassembly, examine the turbine assemblies

and engine exhaust collector supports for condition of welded joints, for cracks and buckling.

17 Examine the starter-generator brushes for wear. TASK 80-11-25-400-801

18 Examine the oil level in the tank. If the engine has been

idle for more than 15 minutes, motor the engine for 30 seconds with the starter before checking tank quantity. Motoring normally scavenges oil from the gearbox back to the aircraft oil tank.

19 Examine the oil bypass indicator. Remove and examine

R R R

R R R R R R

the oil filter. Record the collection of metal particles, unwanted material, or carbon particles.

NOTE:R If the oil bypass indicator is extended or metal

particles or unwanted material are found, then do a full inspection of the lubrication system (drain the oil, do a flow check, examine and clean the external sump and struts, and install a new oil filter).

TASK 72-00-00-200-801

OEM AMM

TASK 79-21-10-000-801 TASK 79-21-10-200-801 TASK 79-21-10-400-801 TASK 79-37-00-200-801

20 Examine magnetic chip detector plugs. TASK 79-37-00-200-801

21 Service the engine oil system, if necessary.

NOTE: Maximum interval between oil change is 400

hours or 12 months (whichever occurs first).

NOTE: When you do the 400 Hour or 12 Month

Inspection Check, Step 5 of the 400 Hour or 12 Month Inspection Checksheet must be done before you drain the oil.

22 Clean the burner drain valve. TASK 72-40-33-100-801

23 Examine the ignition lead for burning, chafing, cracking

of conduit, loose connectors, and broken lockwire.

24 Do the engine functional test. TASK 72-00-00-700-801R

25 Do the engine vibration test. TASK 72-00-00-700-803R

26 Do the engine trend check. TASK 72-00-00-700-802R

27 Download the EMU summary data. TASK 77-51-00-200-801

EFFECTIVITY: ALL

12-10-79 and OEM AMM

TASK 74-21-15-200-801

SYSTEM DESCRIPTION SECTION-801

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28 Examine the engine records for compliance with all

mandatory bulletins, inspections and airworthiness directives.

29 Examine the engine records for time limited parts

components, accessories.

30 Record component changes, inspection compliance,

etc., in logbook as necessary.

31 Examine the engine after operation in a corrosive

environment.

TABLE 602 - 400 Hour Inspection

400 Hour or 12 month (whichever occurs first) Inspection Checksheet

This inspection checksheet is to be used when performing scheduled inspections. This form may be

locally reproduced and/or expanded to reflect the aircraft operating environment. Keep the completed

sheets as a permanent part of the aircraft engine records. Detailed information regarding each inspection item is contained in the referenced Operation and Maintenance Manual paragraphs.

Item Inspection/Maintenance Action REFERENCE X Initial

1 Record component changes, inspection compliance,

etc., in the logbook.

After you do the 200 hour inspection do the steps that follow:

TASK 05-11-00-800-801

TASK 05-50-00-200-814

TASK 05-11-00-800-801

2R Visually examine the power turbine governor weep hole

R

R R

R

R R

R R R

R

R R

R

R R R R

CAUTION: AIRCRAFT INSTALLED ENGINE FUEL PUMP FILTER DIFFERENTIAL PRESSURE

nearest to the accessory gearbox to make sure it is free of unwanted material. Remove unwanted material.

3R Visually examine the power turbine governor weep hole

nearest to the accessory gearbox for oil leakage. If you find oil leakage, remove and replace the power turbine governor.

4R Visually examine the fuel control unit weep hole

nearest to the accessory gearbox to make sure it is free of unwanted material. Remove unwanted material.

5R Visually examine the fuel control unit weep hole

nearest to the accessory gearbox for oil leakage. If you find oil leakage, remove and replace the fuel control unit.

WARNING SYSTEMS AND/OR OPERATING EXPERIENCE MAY DICTATE REPLACEMENT AT A LESSER TIME INTERVAL. IN NO INSTANCE SHOULD THE 400 HR REPLACEMENT INTERVAL BE EXCEEDED.

6 Replace the fuel pump filter element. TASK 73-21-10-000-802

TASK 73-29-10-400-801, SUBTASK 73-29-10-210-001

TASK 73-29-10-000-801 and 73-29-10-400-801

TASK 73-23-10-400-801, SUBTASK 73-23-10-210-001

TASK 73-23-10-000-801 and 73-23-10-400-801

TASK 73-21-10-400-802

EFFECTIVITY: ALL

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WARNING: DO NOT GET TURBINE FUEL ON YOUR SKIN, IN YOUR EYES, OR ON YOUR

CLOTHING. DO NOT BREATHE THE FUMES. USE ONLY IN AN AREA WITH CONTINUOUS AIRFLOW. INJURY TO PERSONNEL CAN OCCUR. WEAR CHEMICAL RESISTANT CLOTHING, RUBBER GLOVES, RUBBER APRON, BOOTS, GOGGLES AND A FACESHIELD. IF YOU GET IT ON YOUR SKIN OR IN YOUR EYES, FLUSH WITH WATER. GET MEDICAL AID.

CAUTION: WHEN THERE IS EVIDENCE THAT THE FUEL PUMP FILTER HAS BEEN BYPASSED,

OR ANY TIME THE FUEL PUMP FILTER IS REPLACED THE FUEL PUMP FILTER MUST BE EXAMINED. IF ANY CONTAMINATION IS FOUND, THEN EXAMINE AND CLEAN THE FUEL CONTROL INLET FILTER. IF A LARGE AMOUNT OF CONTAMINATION IS FOUND, THEN THE FUEL CONTROL AND THE FUEL NOZZLE MUST BE REMOVED AND REPLACED. REFERENCE MUST ALSO BE MADE TO THE AIRFRAME MAINTENANCE MANUAL FOR FUEL SYSTEM MAINTENANCE FOLLOWING FUEL CONTAMINATION.

CAUTION: DO NOT OPERATE THE ENGINE WITH WATER OR CONTAMINATION IN THE FUEL.

POWER LOSS OR ENGINE MALFUNCTION CAN OCCUR.

CAUTION: DO NOT REFUEL AIRCRAFT FROM REMOTE REFUELING SITES (DRUMS, ETC.)

WITHOUT THE USE OF AN EXTERNAL LOW PRESSURE FUEL FILTER. THIS WILL PREVENT ENGINE FUEL SYSTEM CONTAMINATION. IF YOU FAIL TO USE AN EXTERNAL LOW PRESSURE FUEL FILTER, ENGINE MALFUNCTION AND DAMAGE CAN OCCUR.

7 Remove and replace the fuel nozzle. TASK 73-11-10-900-801

8 Purge the air from the fuel system. TASK 73-00-00-700-801

9 Measure the oil flow from the scavenge passage of the

external sump. It is recommended that the external sump not be removed for this check.

NOTE: This step must be performed before draining

oil.

10 Drain the oil system. OEM AMM

11 Remove and replace the oil filter. Note any

accumulation of metal chips, debris, or carbon particles. Conduct further inspection of the lube system and/or engine gear train/bearings if metal chips or debris are found.

12 Remove, clean, examine, and install the turbine

pressure oil tube screen assembly.

13 Examine the No. 6 and 7 bearing pressure oil nozzle.

Clean internal carbonous deposits from nozzle.

TASK 72-50-00-700-801R

TASK 79-21-10-000-801 TASK 79-21-10-200-801 TASK 79-21-10-400-801

TASK 72-57-10-100-801, SUBTASK 72-57-10-110-001 TASK 72-57-10-100-801, SUBTASK 72-57-10-140-002

TASK 72-57-10-100-801

14 Examine the scavenge oil strut in the power turbine

support. Clean carbonous deposits from strut.

15 Examine the external sump. Clean internal carbonous

deposits from the sump or replace if necessary.

EFFECTIVITY: ALL

TASK 72-57-15-000-801

TASK 72-57-15-100-801 TASK 72-57-15-200-801

SYSTEM DESCRIPTION SECTION-801

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16 Examine and clean the No. 1 bearing oil pressure

reducer. The reducer can be removed for access.

17 Remove, clean, examine, and install the engine Pc

filter.

NOTE: This step can be done earlier if engine

performance is not satisfactory.

18 Test the MGT harness. TASK 77-21-10-700-801

19 Download the EMU diagnostic data. TASK 77-51-00-200-802

20 Do the engine inspection after operation in a corrosive

environment.

TASK 72-30-05-100-801 TASK 72-30-05-200-801

TASK 73-11-20-000-801 TASK 73-11-20-100-801 TASK 73-11-20-200-801 TASK 73-11-20-400-801

TASK 05-50-00-200-814 NTO RR300-014R

EFFECTIVITY: ALL

SYSTEM DESCRIPTION SECTION-801

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UNSCHEDULED MAINTENANCE CHECKS

TASK 05-50-00-800-801

1. Unscheduled Maintenance Check

A. General

This section contains the maintenance checks and inspections that are necessary in special or unusual conditions. These maintenance checks and inspections are not related to the items in section 05-10-00 (Time Limits).

Use the tasks in this section if these unusual events have occurred:

- Unwanted material has entered the engine and/or blocked the air inlet during aircraft operation (foreign object damage)

- There was a hard landing

- There was a lightning strike

- The engine suddenly stopped

- There was a bird ingestion

- The engine has been involved in an accident or an incident

- There has been a fire in the engine or in the engine compartment

- The engine was operated in an over-torque condition

- The engine inlet was blocked

- The engine was operated with high vibration

- The engine was submerged in water

- The engine had snow, ice or water ingestion

- The engine was operated in a corrosive or erosive environment

Fault isolation data for other conditions (such as engine vibration, overtemperature, overspeed,etc.) are in the applicable chapter-section-subject.

The RR300 Series is designed as an engine with a fixed preventative maintenance interval (PMI), 2000 hours or 3000 cycles, whichever comes first. If an unscheduled inspection finds that you need to the remove an engine or component, the owner/operator must use past experience with the engines condition to find what additional preventive and/or corrective maintenance actions are required before reinstallation. Consult with Rolls-Royce, if necessary.

SYSTEM DESCRIPTION SECTION

EFFECTIVITY: ALL

SYSTEM DESCRIPTION SECTION-801

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UNSCHEDULED MAINTENANCE CHECKS

INSPECTION/CHECK

TASK 05-50-00-200-801

1. Do the Inspection for Foreign Object Damage

A. General

This task gives you the procedure to examine an engine for foreign object damage (FOD). Do this task when unwanted material has entered the engine. For example, tools, nuts, bolts, washers, birds, ice, or hail can go into the engine, and can cause internal damage.

(1) If unwanted material went into the engine:

- The compressor section can have damage

- The combustor section can have damage

- The turbine section can have damage.

(2) If a part of the air inlet or all of the air inlet was blocked by the unwanted material entering the

engine, then do the compressor inlet blockage inspection.R

B. Materials

None

C. Consumable Materials

None

D. Expendable Parts

None

E. Standard Tools and Equipment

(1) Warning signs.

F. Special Tools and Equipment

None

G. References

(1) TASK 05-50-00-200-810, Examine the Compressor Inlet for Blockage.

(2) TASK 72-30-00-200-801, Do the Inspection of the Compressor.

(3) TASK 72-40-50-200-801, Do the Inspection of the Combustion Liner Assembly.R

(4) TASK 72-50-00-200-801, Do the Inspection of the Turbine Assembly.

(5) TASK 79-37-00-200-801, Do the Inspection of the Magnetic Plug.R

H. Job Set-Up

SUBTASK 05-50-00-860-001

(1) Make the aircraft safe

(a) Open the applicable circuit breakers.

(b) Put up the applicable warning signs.

EFFECTIVITY: ALL

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I. Procedure

SUBTASK 05-50-00-220-001

WARNING: DO NOT TOUCH THE COMPONENTS OF THE ENGINE UNTIL THEY ARE COOL.

THE TEMPERATURE STAYS HIGH AFTER THE ENGINE STOPS. THE HIGH TEMPERATURES CAN CAUSE INJURY TO PERSONS.

(1) Examine the engine for foreign object damage (FOD).

(a) If available, examine the engine data from before and after the possible FOD incident for

compressor vibration and turbine vibration.

(b) Use a bright light to examine the inlet ducting and the compressor front support struts and

the leading edges of the impeller.

(c) Do the inspection of the compressor section (REF. TASK 72-30-00-200-801).

(d) Do the inspection of the combustion liner assembly (REF. TASK 72-40-50-200-801).R

(e) Do the inspection of the turbine assembly (REF. TASK 72-50-00-200-801).

(f) Do the inspection of the magnetic plug (REF. TASK 79-37-00-200-801).R

(g) If engine vibration occurred, do the steps that follow.

1

(h) Examine the compressor air inlet for blockage (REF. TASK 05-50-00-200-810).

Do the fault isolation for excessive vibration.

J. Job Close-Up

SUBTASK 05-50-00-860-002

(1) Return the engine to service.

(a) Close the applicable circuit breakers.

(b) Remove the applicable warning signs.

EFFECTIVITY: ALL

INSPECTION/CHECK-801

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UNSCHEDULED MAINTENANCE CHECKS

INSPECTION/CHECK

TASK 05-50-00-200-802

1. Do the Inspection for Hard Landing Damage

A. General

This task gives you the procedures to examine the engine after a hard landing.

B. Materials

None

C. Consumable Materials

None

D. Expendable Parts

None

E. Standard Tools and Equipment

(1) Warning signs.

F. Special Tools and Equipment

None

G. References

(1) TASK 72-00-00-000-801, Remove the Engine.

(2) TASK 72-00-00-400-801, Install the Engine.

(3) TASK 72-30-00-200-801, Do the Inspection of the Compressor Section

(4) TASK 72-40-50-200-801, Do the Inspection of the Combustion Liner AssemblyR

(5) TASK 72-50-00-200-801, Do the Inspection of the Turbine Assembly.

(6) TASK 79-37-00-200-801, Do the Inspection of the Magnetic Plug.R

(7) OEM Aircraft Maintenance Manual, AMM.R

H. Job Set-Up

SUBTASK 05-50-00-860-003

(1) Make the aircraft safe.

(a) Open the applicable circuit breakers.R

(b) Put up the applicable warning signs.

EFFECTIVITY: ALL

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I. Procedure

SUBTASK 05-50-00-210-002

WARNING: DO NOT TOUCH THE COMPONENTS OF THE ENGINE UNTIL THEY ARE

(1) Examine the engine for hard landing damage.R

R R R

R R

NOTE: An engine has experienced a hard landing when the landing force is more than 10g's

(a) Examine the exhaust collector for metal particles and other unwanted material.

(b) Examine the engine mounts for damage.

(c) Do the inspection of the compressor section (REF. TASK 72-30-00-200-801).

(d) Do the inspection of the combustion liner (REF. TASK 72-40-50-200-801).R

(e) Do the inspection of the turbine section (REF. TASK 72-50-00-200-801).

(f) If you find damage or see indications of internal damage, do the inspection of the

(g) Examine all tubes and hoses for damage and leaks. Replace the tube/hose, or repair the

(h) Make a visual inspection of the installed engine for external damage from airframe

(i) If there are indications of hard landing damage that cannot be repaired on-wing or a

COOL.THE TEMPERATURE STAYS HIGH AFTER THE ENGINE STOPS. THE HIGH TEMPERATURES CAN CAUSE INJURY TO PERSONS.

or when the limits for a hard landing condition is more than described in the OEM Aircraft Maintenance Manual.

magnetic plugs (REF. TASK 79-37-00-200-801).R

leaks as necessary.

components.

landing that is more than 10g's, then do the steps that follow.

1

Remove the engine (REF. TASK 72-00-00-000-801).

2 Install a new engine (REF. TASK 72-00-00-400-801).

3 Put a tag on the engine that tells you that the engine was removed because of hard

landing damage.

4 Send the damaged engine to an approved maintenance facility for repair.

NOTE: Engines that have landing forces exceeding 10g must be sent to an

approved maintenance facility. Airframe conditions that can be used as an indication that the 10g landing force limit has been exceeded are in the OEM Aircraft Maintenance Manual.

J. Job Close-Up

SUBTASK 05-50-00-860-004

(1) Return the engine to service.

(a) Close the applicable circuit breakers.

(b) Remove the applicable warning signs.

EFFECTIVITY: ALL

INSPECTION/CHECK-802

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UNSCHEDULED MAINTENANCE CHECKS

INSPECTION/CHECK

TASK 05-50-00-200-803

1. Do the Inspection for Lightning Strike Damage

A. General

This task gives you the procedure to examine an engine for damage caused by a lightning strike. An engine lightning strike can cause electrical arcing between parts. If the engine was hit by lightning, damage can result in the areas that follow:

- Steel parts (the bearings, the gears, and other steel parts) can become magnetized.R

- The seals, the packings and the gaskets, and all rubber materials can have fire or heat damage.R

- The electrical wiring and components can have damage.R

- Arc damage to bearing balls, rollers, and races.R

- Metal transfer on bearings.R

- Metal can be transferred from one part to another.

B. Materials

None

C. Consumable Materials

None

D. Expendable Parts

None

E. Standard Tools and Equipment

(1) Warning signs.

F. Special Tools and Equipment

None

G. References

(1) TASK 72-00-00-000-801, Remove the Engine.

(2) TASK 72-00-00-200-801, Do the General Visual Inspection of the Engine.R

(3) TASK 72-00-00-400-801, Install the Engine.

(4) TASK 79-21-10-200-801, Do the Inspection of the Power and Accessory Gearbox Oil Filter.

(5) TASK 79-37-00-200-801, Do the Inspection of the Magnetic Plug.R

(6) Engine Performance and Operation, 71-00-01.

(7) OEM Aircraft Maintenance Manual, AMM.

H. Job Set-Up

SUBTASK 05-50-00-860-005

(1) Make the aircraft safe.

(a) Open the applicable circuit breakers.

(b) Put up the applicable warning signs.

EFFECTIVITY: ALL

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I. Procedure

SUBTASK 05-50-00-210-003

WARNING: DO NOT TOUCH THE COMPONENTS OF THE ENGINE UNTIL THEY ARE COOL.

THE TEMPERATURE STAYS HIGH AFTER THE ENGINE STOPS. THE HIGH TEMPERATURES CAN CAUSE INJURY TO PERSONS.

(1) Examine the engine for indications of a lightning strike

(a) If a lightning strike occurs in the area of the engine (as evidenced by charring, burn marks

or pitting associated with electrical arcing on the engine compartment or inlet), then do the steps that follow:

1 Remove the engine (REF. TASK 72-00-00-000-801).

2 Install a new engine (REF. TASK 72-00-00-400-801).

3 Put a tag on the engine that tells you that the engine was removed because of

damage caused by a lightning strike.

4

Send the damaged engine to an approved maintenance facility for repair.

(b) Where the aircraft is known or suspected of having been involved in a lightning strike, and

entry/exit points either cannot be found or appear to be away from the engine, do the steps that follow:

1 Examine the engine compartment for indications of lightning strike damage.

2 Examine the starter-generator for damage.

R R).

R R

3 Examine the engine harnesses for damage (REF. TASK 72-00-00-200-801 or OEM

AMM

4 Manually rotate N1 and N2 systems and check for binding and unusual noise.

5 Do the inspection of the power and accessory gearbox oil filter (REF. TASK

79-21-10-200-801).

6 Do the inspection of the magnetic plugs (REF. TASK 79-37-00-200-801).R

7 Operate the engine for 30 minutes on the ground (REF. 71-00-01).

8 Examine the magnetic plugs again for metal contamination (REF. TASK

79-37-00-200-801).

9 Listen for unusual noise on coastdown and unusually short coastdown time.

(c) Remove all the tools and equipment from the work area. Make sure the work area is

clean.

J. Job Close-Up

SUBTASK 05-50-00-860-006

(1) Return the engine to service.

(a) Close the applicable circuit breakers.

(b) Remove the applicable warning signs.

EFFECTIVITY: ALL

INSPECTION/CHECK-803

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UNSCHEDULED MAINTENANCE CHECKS

INSPECTION/CHECK

TASK 05-50-00-200-804

1. Do the Inspection of the Engine After a Sudden Stop

A. General

This task gives you the procedure to examine an engine for damage caused by a sudden stop. A sudden stop is momentary or full stop that is not commanded, in which the engine does not coast down normally. This can occur when a physical object stops the helicopter main rotor during normal operation. When there is a sudden stop, it is possible that the helicopter main rotor has hit the ground, water, trees, or other obstacles. Damage can result to the items that follow:

- The power-turbine blades.

- The power-turbine vanes.

- The power-turbine bearings.

- The gearbox bearings.

- The gearbox gears.

- The power-turbine coupling.R

- The engine mounts.R

B. Materials

None

C. Consumable Materials

None

D. Expendable Parts

None

E. Standard Tools and Equipment

(1) Warning signs.

F. Special Tools and Equipment

None

G. References

(1) TASK 72-00-00-000-801, Remove the Engine.

(2) TASK 72-00-00-400-801, Install the Engine.

(3) TASK 72-30-00-200-801, Do the Inspection of the Compressor Section.

(4) TASK 79-37-00-200-801, Do the Inspection of the Magnetic Plug.R

(5) Engine Operation, 71-00-01.

H. Job Set-Up

SUBTASK 05-50-00-860-007

(1) Make the aircraft safe.

(a) Open the applicable circuit breakers

(b) Put up the applicable warning signs.

EFFECTIVITY: ALL

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I. Procedure

SUBTASK 05-50-00-210-004

WARNING: DO NOT TOUCH THE COMPONENTS OF THE ENGINE UNTIL THEY ARE COOL.

(1) Examine the engine after a sudden stop.

NOTE: The following specific items and/or functions are the minimum required actions when

NOTE: If the engine must be removed from the airframe as a result of the rotor sudden

(a) If a drive system component malfunctions, or the aircraft main rotor blade(s) hits an object,

R R

(b) If a drive system component malfunctions, or if a main rotor blade(s) hits an object during

(c) If a drive system component malfunctions, or a main rotor blade(s) hit an object during

THE TEMPERATURE STAYS HIGH AFTER THE ENGINE STOPS. THE HIGH TEMPERATURES CAN CAUSE INJURY TO PERSONS.

you do a sudden stoppage inspection. Each incident must be accomplished on an "if necessary" basis possibly requiring more than these minimum requirements. Engines that have had sudden stoppage do not require repair automatically. This must be determined and is the responsibility of the service facility doing the inspection.

stoppage, then the operator must give all the details about the incident to the approved maintenance facility. This information must include a description of damage to the airframe power train and mounts and other applicable information.

and damage occurs which is field repairable in accordance with aircraft manufacturer's recommendations, do the steps that follow:

1

Examine the magnetic plugs for metal contamination (REF. TASK 79-37-00-200-801).

2 Examine the engine inlet for foreign objects.

3 Examine the compressor for foreign object damage (REF. TASK 72-30-00-200-801).

4 Motor the engine and check for unusual noise (REF. TASK 71-00-01).

5 Operate the engine for 30 minutes on the ground (REF. TASK 71-00-01).

6 Examine the magnetic plugs for metal contamination (REF. TASK

79-37-00-200-801).

operation, and damage occurs that requires removal from service of the main rotor blade or aircraft main rotor drive system component do the steps that follow:

1 Remove the engine (REF. TASK 72-00-00-000-801).

2 Install a new engine (REF. TASK 72-00-00-400-801).

3 Put a tag on the engine that tells you that the engine was removed because of

damage caused by a sudden stoppage/engagement.

4 Send the damaged engine to an approved maintenance facility for repair.

operation and the engine or transmission mounts are fractured or misaligned, do the steps that follow:

1 Remove the engine (REF. TASK 72-00-00-000-801).

2 Install a new engine (REF. TASK 72-00-00-400-801).

3 Put a tag on the engine that tells you that the engine was removed because of

damage caused by a sudden stoppage/engagement.

4 Return engine to an approved maintenance facility for overhaul inspection.

EFFECTIVITY: ALL

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J. Job Close-Up

SUBTASK 05-50-00-860-008

(1) Return the engine to service.

(a) Close the applicable circuit breakers.

(b) Remove the applicable warning signs.

EFFECTIVITY: ALL

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UNSCHEDULED MAINTENANCE CHECKS

INSPECTION/CHECK

TASK 05-50-00-200-805

1. Do the Inspection for the Damage Caused by Bird Ingestion

A. General

This task gives you the procedure to examine an engine for damage caused by bird ingestion. Do this task when one or more birds have entered the engine while in operation.

B. Materials

None

C. Consumable Materials

None

D. Expendable Parts

None

E. Standard Tools and Equipment

(1) Warning signs.

F. Special Tools and Equipment

None

G. References

(1) TASK 05-50-00-200-801, Do the Inspection for Foreign Object Damage.

(2) TASK 72-00-00-100-801, Clean the Engine Gas Path.

(3) TASK 73-11-20-200-801, Do the Inspection of the Pc Air Filter Assembly.

H. Job Set-Up

SUBTASK 05-50-00-860-009

(1) Make the aircraft safe.

(a) Open the applicable circuit breakers.

(b) Put up the applicable warning signs.

I. Procedure

SUBTASK 05-50-00-210-005

(1) Do the inspection for the damage caused by bird ingestion.

(a) Do the inspection of the Pc air filter assembly (REF. TASK 73-11-20-200-801).

(b) Do the inspection for foreign object damage (REF. TASK 05-50-00-200-801).

(c) Clean the engine gas path (REF. TASK 72-00-00-100-801).

(d) Remove all the tools and equipment from the work area. Make sure the work area is

clean.

EFFECTIVITY: ALL

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J. Job Close-Up

SUBTASK 05-50-00-860-010

(1) Return the engine to service.

(a) Close the applicable circuit breakers.

(b) Remove the applicable warning signs.

EFFECTIVITY: ALL

INSPECTION/CHECK-805

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UNSCHEDULED MAINTENANCE CHECKS

INSPECTION/CHECK

TASK 05-50-00-200-806

1. Do the Inspection of an Engine Involved in an Accident or Incident

A. General

This task gives you the procedure to find the damage if the engine was involved in an accident or an incident. It is possible that the engine has internal damage including visible external damage.

The owner/operator must make sure that an engine that was involved in an accident or incident is examined and/or repaired before the engine is operated again.

B. Materials

None

C. Consumable Materials

None

D. Expendable Parts

None

E. Standard Tools and Equipment

(1) Warning signs.

F. Special Tools and Equipment

None

G. References

(1) TASK 05-50-00-200-801, Do the Inspection for Foreign Object Damage.

(2) TASK 05-50-00-200-802, Do the Inspection for Hard Landing Damage.

(3) TASK 05-50-00-200-803, Do the Inspection for Lightning Strike.

(4) TASK 05-50-00-200-804, Do the Inspection of the Engine after a Sudden Stop.

(5) TASK 05-50-00-200-805, Do the Inspection of the Engine caused by Bird Ingestion.

(6) TASK 05-50-00-200-807, Do the Inspection after a Fire in the Engine.

(7) TASK 05-50-00-200-809, Do the Inspection of the Engine after an Overtorque Condition.

(8) TASK 05-50-00-200-810, Do the Inspection for Compressor Inlet Blockage.

(9) TASK 05-50-00-200-812, Do the Inspection for Engine Submerged in Water.

(10) TASK 05-50-00-200-813, Do the Inspection for Snow. Ice or Water Ingestion.

(11) TASK 72-00-00-000-801, Remove the Engine.

(12) TASK 72-00-00-400-801, Install the Engine.

(13) TASK 77-51-00-200-802, Do the Engine Monitoring Unit Diagnostic Data Download.R

(14) TASK 79-37-00-200-801, Do the Inspection of the Magnetic Plug.R

EFFECTIVITY: ALL

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H. Job Set-Up

SUBTASK 05-50-00-860-011

(1) Make the aircraft safe.

(a) Open the applicable circuit breakers

(b) Put up the applicable warning signs.

I. Procedure

SUBTASK 05-50-00-210-006

WARNING: DO NOT TOUCH THE COMPONENTS OF THE ENGINE UNTIL THEY ARE COOL.

THE TEMPERATURE STAYS HIGH AFTER THE ENGINE STOPS. THE HIGH TEMPERATURES CAN CAUSE INJURY TO PERSONS.

(1) Examine the engine for damage.

(a) Download the engine monitoring unit diagnostic data (REF. TASK 77-51-00-200-802).R

(b) If it is possible that there is foreign object damage (FOD) in the engine, or if you do not

know the details of the accident/incident, do the inspection for FOD (REF. TASK 05-50-00-200-801).

(c) If the engine was in a hard landing, or if you do not know the details of the

accident/incident, do the inspection for hard landing damage (REF. TASK 05-50-00-200-802).

(d) If the engine had a lightning strike, or if you do not know the details of the

accident/incident, do the inspection for a lightning strike of the engine (REF. TASK 05-50-00-200-803).

(e) If the engine has suddenly stopped, or if you do not know the details of the

accident/incident, do the inspection for a sudden stop of the engine (REF. TASK 05-50-00-200-804).

(f) If the engine has had a bird ingestion, or if you do not know the details of the

accident/incident, do the inspection of the engine for bird ingestion (REF. TASK 05-50-00-200-805).

(g) If the engine has had a fire, or if you do not know the details of the accident/incident, do

the inspection of the engine for fire damage (REF. TASK 05-50-00-200-807).

(h) If the engine has been overtorqued, or if you do not know the details of the

accident/incident, do the inspection of the engine after an overtorque condition (REF. TASK 05-50-00-200-809).

(i) If the engine compressor inlet was blocked, or if you do not know the details of the

accident/incident, do the inspection for compressor inlet blockage (REF. TASK 05-50-00-200-810).

(j) If the engine was submerged in water, or if you do not know the details of the

accident/incident, do the inspection for engine submerged (REF. TASK 05-50-00-200-812).

(k) If the engine had snow, ice or water ingestion, or if you do not know the details of the

accident/incident, do the inspection for engine with snow. ice or water ingestion (REF. TASK 05-50-00-200-813).

(l) Do the inspection of the magnetic plug (REF. TASK 79-37-00-200-801).R

EFFECTIVITY: ALL

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(m) If there are indications of damage caused by an accident/incident that cannot be repaired

while installed in the aircraft, do the steps that follow

1 Remove the engine (REF. TASK 72-00-00-000-801).

2 Install a serviceableR engine (REF. TASK 72-00-00-400-801).

3 Put a tag on the engine that tells you that the engine was removed because of

4 Send the damaged engine to an approved maintenance facility for repair

(n) Remove all the tools and equipment from the work area. Make sure the work area is

clean.

J. Job Close-Up

SUBTASK 05-50-00-860-012

(1) Return the engine to service.

(a) Close the applicable circuit breakers.

(b) Remove the applicable warning signs.

accident/incident damage.

EFFECTIVITY: ALL

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UNSCHEDULED MAINTENANCE CHECKS

INSPECTION/CHECK

TASK 05-50-00-200-807

1. Do the Inspection after a Fire in the Engine

A. General

This task gives you the procedure to find the damage if there was a fire in the engine or in the engine compartment. You must find the cause of the fire and correct it.

B. Materials

None

C. Consumable Materials

None

D. Expendable Parts

None

E. Standard Tools and Equipment

(1) Warning signs.

F. Special Tools and Equipment

None

G. References

(1) TASK 72-00-00-000-801, Remove the Engine.

(2) TASK 72-00-00-200-801, Do the General Visual Inspection of the Engine.R

(3) TASK 72-00-00-400-801, Install the Engine.

(4) OEM Aircraft Maintenance Manual, AMM.

H. Job Set-Up

SUBTASK 05-50-00-860-013

(1) Make the aircraft safe.

(a) Open the applicable circuit breakers.

(b) Put up the applicable warning signs.

I. Procedure

SUBTASK 05-50-00-210-007

WARNING

(1) Do the inspection after a fire in the engine.

(a) Examine the engine components and accessories and airframe installed generator control

unit, main oil temperature probe and other airframe mounted hardware for the conditions that follow:

EFFECTIVITY: ALL

: DO NOT TOUCH THE COMPONENTS OF THE ENGINE UNTIL THEY ARE COOL.

THE TEMPERATURE STAYS HIGH AFTER THE ENGINE STOPS. THE HIGH TEMPERATURES CAN CAUSE INJURY TO PERSONS.

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(b) Examine the tubes and the hoses for the conditions that follow:

R R

(c) Examine the wiring and the electrical harnesses for damage (REF. TASK

(d) Examine the engine inlet, the exhaust duct, the turbine blades, and the turbine vanesR for

(e) If there are indications of damage caused by fire in the engine that cannot be repaired

(f) Remove all the tools and equipment from the work area. Make sure the work area is

- Examine for dirt, grease, or other unwanted materials.

- Examine the electrical connections.

- Examine for signs of overheating and burns.

- Examine for signs of leakage.

- If necessary, do the maintenance action to correct the unsatisfactory condition.

- Examine for dents and chafing.

- Examine for cuts and deterioration.

- Examine for connections that are loose.

- Examine for overheating and burns.

- If necessary, do the maintenance action to correct the unsatisfactory condition.

72-00-00-200-801 or OEM AMM).

the conditions that follow:

- Examine for dirt and other unwanted material.

- Examine for other damage.

while installed in the aircraft, then do the steps that follow:

1

Remove the engine (REF. TASK 72-00-00-000-801).

2 Install a new engine (REF. TASK 72-00-00-400-801).

3 Put a tag on the engine that tells you that the engine was removed because of

damage caused by fire.

4 Send the damaged engine to an approved maintenance facility for repair.

clean.

J. Job Close-Up

SUBTASK 05-50-00-860-014

(1) Return the engine to service.

(a) Close the applicable circuit breakers.

(b) Remove the applicable warning signs.

EFFECTIVITY: ALL

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UNSCHEDULED MAINTENANCE CHECKS

INSPECTION/CHECK

TASK 05-50-00-200-808

1. Do the Inspection of the Engine after a Compressor Stall or Surge

A. General

This task gives you the procedures to examine the engine after a compressor stall or surge.

B. Materials

None

C. Consumable Materials

None

D. Expendable Parts

None

E. Standard Tools and Equipment

(1) Warning signs.

F. Special Tools and Equipment

None

G. References

(1) TASK 72-30-00-200-801, Do the Inspection of the Compressor Section.

H. Job Set-Up

SUBTASK 05-50-00-860-027

(1) Make the aircraft safe.

(a) Open the applicable circuit breakers.

(b) Put up the applicable warning signs.

I. Procedure

SUBTASK 72-50-00-210-015

(1) Do the inspection of the compressor section.

(a) Do the inspection of the compressor section (Ref. TASK 72-30-00-200-801).

J. Job Close-Up

SUBTASK 05-50-00-860-028

(1) Return the engine to service.

(a) Close the applicable circuit breakers.

(b) Remove the applicable warning signs.

EFFECTIVITY: All

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UNSCHEDULED MAINTENANCE CHECKS

INSPECTION/CHECK

TASK 05-50-00-200-809

1. Do the Inspection of the Engine after an Over-torque Condition

A. General

This task gives you the procedure to examine an engine after an over-torque condition. The operator must monitor the torque made by the engine. Damage can result to the items that follow:

- The engine mount.R

- The gas generator blades.

- The gas generator vanes.

- The gearbox mounted accessories.

- The N1 gear train.R

- The N2 gear train.R

- The power turbine blades.

- The power turbine coupling shaft.R

- The power turbine vanes.

B. Materials

None

C. Consumable Materials

None

D. Expendable Parts

None

E. Standard Tools and Equipment

(1) Warning signs.

F. Special Tools and Equipment

None

G. References

(1) TASK 72-00-00-000-801, Remove the Engine.

(2) TASK 72-00-00-400-801, Install the Engine.

H. Job Set-Up

SUBTASK 05-50-00-860-017

(1) Make the aircraft safe.

(a) Open the applicable circuit breakers.

(b) Put up the applicable warning signs.

EFFECTIVITY: ALL

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I. Procedure

SUBTASK 05-50-00-210-008

WARNING: DO NOT TOUCH THE COMPONENTS OF THE ENGINE UNTIL THEY ARE COOL.

THE TEMPERATURE STAYS HIGH AFTER THE ENGINE STOPS. THE HIGH TEMPERATURES CAN CAUSE INJURY TO PERSONS.

(1) If you overtorque the engine, do the steps that follow.

(a) If the overtorque was more than 244 ft-lbs. for more than five minutes, then remove the

engine (REF. TASK 72-00-00-000-801) and install a replacement engine (REF. TASK 72-00-00-400-801).

(b) If the overtorque was more than 288 ft-lbs. for more than sixteen seconds, then remove

the engine (REF. TASK 72-00-00-000-801) and install a replacement engine (REF. TASK 72-00-00-400-801).

(c) If the overtorque was more than 430 ft-lbs.,R then remove the engine (REF. TASK

72-00-00-000-801) and install a replacement engine (REF. TASK 72-00-00-400-801).

(d) Put a tag on the engine that tells you that the engine was removed because of damage

caused by an engine overtorque condition.

(e) Send the damaged engine to an approved maintenance facility for repair.

(f) Remove all the tools and equipment from the work area. Make sure the work area is

clean.

J. Job Close-Up

SUBTASK 05-50-00-860-018

(1) Return the engine to service.

(a) Close the applicable circuit breakers.

(b) Remove the applicable warning signs.

EFFECTIVITY: ALL

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UNSCHEDULED MAINTENANCE CHECKS

INSPECTION/CHECK

TASK 05-50-00-200-810

1. Examine the Engine Inlet for Blockage

A. General

This task gives you the procedures to examine the compressor assembly if the engine has been operated with theR inlet air restricted because of foreign objects or materials that are in the compressor inlet. Conditions in which blockage has occurred are as follows:

- Foreign objects or materials found in the inlet during inspection of the aircraft when not in operation.R

- Power loss encountered following a restriction at the engine inlet area while the engine is in

R R before ingestion, or which cause a noticeable increase in measured gas temperature, can be

operation.R Objects or materials which were large enough to have stopped at the front support struts considered to have caused engine inlet blockage.

B. Materials

None

C. Consumable Materials

None

D. Expendable Parts

None

E. Standard Tools and Equipment

None

F. Special Tools and Equipment

None

G. References

(1) TASK 05-50-00-200-801, Do the Inspection for Foreign Object Damage (FOD).

(2) TASK 72-00-00-000-801, Remove the Engine.

(3) TASK 72-00-00-400-801, Install the Engine.

H. Job Set-Up

SUBTASK 05-50-00-860-019

(1) Make the aircraft safe.

(a) Open the applicable circuit breakers.

(b) Put up the applicable warning signs.

EFFECTIVITY: ALL

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I. Procedure

SUBTASK 05-50-00-210-009

WARNING: DO NOT TOUCH THE COMPONENTS OF THE ENGINE UNTIL THEY ARE COOL.

THE TEMPERATURE STAYS HIGH AFTER THE ENGINE STOPS. THE HIGH TEMPERATURES CAN CAUSE INJURY TO PERSONS.

(1) Examine the engine inlet for blockage.

(a) Foreign objects or materials found in the inlet during inspection of the aircraft when not in

operation.

1 If you find that the blockage was not there during the last operation of the engine,

2 If you find that the blockage was there during the last operation of the engine, remove

(b) Power loss encountered following a restriction at the compressor inlet area while the

engine is in operation.

1 Remove the engine (REF. TASK 72-00-00-000-801).

2 Install a new engine (REF. TASK 72-00-00-400-801).

3 Put a tag on the engine that tells you that the engine was removed because of an

4 Send the damaged engine to an approved maintenance facility for repair.

(c) Objects or materials which were large enough to have stopped at the front support strutsR

before ingestion, or which cause a large rise in measured gas temperature.

NOTE: Blockage in flight can usually be found by the inspection after landing (blockage

1 Remove the engine (REF. TASK 72-00-00-000-801).

2 Install a new engine (REF. TASK 72-00-00-400-801).

3 Put a tag on the engine that tells you that the engine was removed because of an

(d) Do the inspection for foreign object damage (FOD) (REF. TASK 05-50-00-200-801).

(e) Remove all the tools and equipment from the work area. Make sure the work area is

clean.

remove the foreign object or material and leave the engine in service.

the foreign object or material, if necessary.

a Remove the engine (REF. TASK 72-00-00-000-801).

b

Install a new engine (REF. TASK 72-00-00-400-801).

c Put a tag on the engine that tells you that the engine was removed because of

an engine inlet blockage.

d Send the damaged engine to an approved maintenance facility for repair.

engine inlet blockage.

still exists). Some blockage can be followed by ingestion before an inspection can be done.

engine inlet blockage.

EFFECTIVITY: ALL

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J. Job Close-Up

SUBTASK 05-50-00-860-020

(1) Return the engine to service.

(a) Close the applicable circuit breakers.

(b) Remove the applicable warning signs.

EFFECTIVITY: ALL

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UNSCHEDULED MAINTENANCE CHECKS

INSPECTION/CHECK

TASK 05-50-00-200-811

1. Do the Vibration Inspection of the Engine

A. General

This task gives you the procedures to do an inspection for vibration indications.

B. Materials

None

C. Consumable Materials

None

D. Expendable Parts

None

E. Standard Tools and Equipment

(1) Warning signs.

F. Special Tools and Equipment

None

G. References

(1) TASK 72-00-00-000-801, Remove the Engine.

(2) TASK 72-00-00-400-801, Install the Engine.

(3) TASK 72-00-00-700-801, Do the Test of the Engine.

(4) TASK 72-30-00-200-801, Do the Inspection of the Compressor Assembly.

(5) TASK 72-40-50-200-801, Do the Inspection of the Combustion Liner Assembly.R

(6) TASK 72-50-00-200-801, Do the Inspection of the Turbine Assembly.

H. Job Set-Up

SUBTASK 05-50-00-860-021

(1) Make the aircraft safe.

(a) Open the applicable circuit breakers.

(b) Put up the applicable warning signs.

I. Procedure

SUBTASK 05-50-00-210-010

WARNING

(1) Do the vibration inspection.

EFFECTIVITY: ALL

: DO NOT TOUCH THE COMPONENTS OF THE ENGINE UNTIL THEY ARE COOL.

THE TEMPERATURE STAYS HIGH AFTER THE ENGINE STOPS. THE HIGH TEMPERATURES CAN CAUSE INJURY TO PERSONS.

NOTE: Procedures are provided for evaluating vibration, identifying vibration sources, and

analyzing vibration levels.

(a) Do a test of the engine (REF. TASK 72-00-00-700-801).

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CAUTION: DO NOT CONTINUE TO OPERATE THE ENGINE WITH HIGH VIBRATION

(b) If the engine vibration is found after you did the test of the engine, or if you have the

vibration symptoms found in the 200-hourR inspection, do the steps that follow:

1 Do the inspection of the compressor assembly, (REF. TASK 72-30-00-200-801).

2 Do the inspection of the combustion liner assembly, (REF. TASK 72-40-50-200-801).R

3 Do the inspection of the turbine assembly, (REF. TASK 72-50-00-200-801).

4 If the inspections listed above did not find a cause for the engine vibration, then do

5 Remove all the tools and equipment from the work area. Make sure the work area is

LEVELS. THIS WILL CAUSE EXCESSIVE ENGINE AND COMPONENT WEAR AND CAN CAUSE ENGINE FAILURE AND ENGINE REMOVAL.

the steps that follow:

a Remove the engine (REF. TASK 72-00-00-000-801).

b Install a new engine (REF. TASK 72-00-00-400-801).

c Put a tag on the engine that tells you that the engine was removed because of

vibrations.

d

Send the damaged engine to an approved maintenance facility for repair.

clean.

J. Job Close-Up

SUBTASK 05-50-00-860-022

(1) Return the engine to service.

(a) Close the applicable circuit breakers.

(b) Remove the applicable warning signs.

EFFECTIVITY: ALL

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UNSCHEDULED MAINTENANCE CHECKS

INSPECTION/CHECK

TASK 05-50-00-200-812

1. Do the inspection for Engine Submerged in Water

A. General

This task gives you the procedures to do if the engine has been completely or not fully submerged in water.

B. Materials

None

C. Consumable Materials

None

D. Expendable Parts

None

E. Standard Tools and Equipment

(1) Warning signs

F. Special Tools and Equipment

None

G. References

(1) TASK 72-00-00-000-801, Remove the Engine.

(2) TASK 72-00-00-400-801, Install the Engine.

H. Job Set-Up

SUBTASK 05-50-00-860-023

(1) Make the aircraft safe

(a) Open the applicable circuit breakers.

(b) Put up the applicable warning signs.

I. Procedure

SUBTASK 05-50-00-210-011

WARNING

(1) Do the inspection of the engine submerged.

: DO NOT TOUCH THE COMPONENTS OF THE ENGINE UNTIL THEY ARE COOL.

THE TEMPERATURE STAYS HIGH AFTER THE ENGINE STOPS. THE HIGH TEMPERATURES CAN CAUSE INJURY TO PERSONS.

(a) If the engine has been completely or not fully submerged in water, do the steps that follow:

1 Remove the engine (REF. TASK 72-00-00-000-801).

2 Install a new engine (REF. TASK 72-00-00-400-801).

3 Put a tag on the engine that shows that it was submersed. Give details of the

submersion. Record the amount of time that the engine was in operation, or how much time had passed after engine shutdown, and how long the engine was submerged, and the condition of the water.

EFFECTIVITY: ALL

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4 Return the engine to a approved maintenance facility as soon as possible.

5 Remove all the tools and equipment from the work area. Make sure the work area is

J. Job Close-Up

SUBTASK 05-50-00-860-024

(1) Return the engine to service.

(a) Close the applicable circuit breakers.

(b) Remove the applicable warning signs.

clean.

EFFECTIVITY: ALL

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UNSCHEDULED MAINTENANCE CHECKS

INSPECTION/CHECK

TASK 05-50-00-200-813

1. Do the Inspection for Snow, Ice or Water Ingestion

A. General

This task gives you procedures to examine the engine if you have ingested heavy amounts of snow, ice or water when the engine is in operation.

B. Materials

None

C. Consumable Materials

None

D. Expendable Parts

None

E. Standard Tools and Equipment

(1) Warning signs

F. Special Tools and Equipment

None

G. References

(1) TASK 05-50-00-200-801, Do the Inspection for Foreign Object Damage.

(2) TASK 05-50-00-200-810, Do the Inspection for Compressor Inlet Blockage.

H. Job Set-Up

SUBTASK 05-50-00-860-025

(1) Make the aircraft safe.

(a) Open the applicable circuit breakers.

(b) Put up the applicable warning signs.

I. Procedure

SUBTASK 05-50-00-210-012

WARNING

(1) Examine the engine if large amounts of snow, ice, or water have been ingested.

: DO NOT TOUCH THE COMPONENTS OF THE ENGINE UNTIL THEY ARE COOL.

THE TEMPERATURE STAYS HIGH AFTER THE ENGINE STOPS. THE HIGH TEMPERATURES CAN CAUSE INJURY TO PERSONS.

(a) Do the inspection for foreign object damage (REF. TASK 05-50-00-200-801).

(b) Do the inspection for compressor inlet blockage (REF. TASK 05-50-00-200-810).

EFFECTIVITY: ALL

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J. Job Close-Up

SUBTASK 05-50-00-860-026

(1) Return the engine to service.

(a) Close the applicable circuit breakers.

(b) Remove the applicable warning signs.

EFFECTIVITY: ALL

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UNSCHEDULED MAINTENANCE CHECKS

INSPECTION/CHECK

TASK 05-50-00-200-814

1. Do the Inspection of the Engine after Operation in a Corrosive Environment

A. General

This task gives you procedures to examine the first-stage turbine blade airfoils in an engine that was operated in a corrosive environment, near a seashore, or in an area of heavy airborne industrial contamination.

B. Materials

None

C. Consumable Materials

None

D. Expendable Parts

None

E. Standard Tools and Equipment

(1) Signs, warning

F. Special Tools and Equipment

(1) Fiberscope (borescope), Olympus 4 mm direct view, IF4D5-15, or equivalent.

G. References

(1) TASK 72-00-00-000-801, Remove the Engine.

(2) TASK 72-00-00-400-801, Install the Engine.

(3) TASK 72-40-30-000-801, Remove the Outer Combustion Case Assembly.

(4) TASK 72-40-30-400-801, Install the Outer Combustion Case Assembly.

(5) TASK 72-40-50-000-801, Remove the Combustion Liner Assembly.

(6) TASK 72-40-50-400-801, Install the Combustion Liner Assembly.

(7) TASK 73-11-10-000-801, Remove the Fuel Nozzle.

(8) TASK 73-11-10-400-801, Install the Fuel Nozzle.

H. Job Set-Up

SUBTASK 05-50-00-860-029

(1) Make the aircraft safe.

(a) Open the applicable circuit breakers.

(b) Put up the applicable warning signs.

I. Procedure

SUBTASK 05-50-00-280-002

(1) Do the visual or the borescope inspection of the first-stage turbine wheel airfoils.

(a) If you are to do the visual inspection without the borescope, then do step 1.I.(2).

(b) If you are to do the visual inspection with the borescope, then do step 1.I.(3).

EFFECTIVITY: ALL

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SUBTASK 05-50-00-210-010

WARNING: DO NOT TOUCH THE COMPONENTS OF THE ENGINE UNTIL THEY ARE COOL.

THE TEMPERATURE STAYS HIGH AFTER THE ENGINE STOPS. THE HIGH TEMPERATURES CAN CAUSE INJURY TO PERSONNEL.

(2) Visually examine the first-stage turbine wheel airfoils (airfoils).

(a) Remove the outer combustion case (Ref. TASK 72-40-30-000-801).

(b) Remove the combustion liner (Ref. TASK 72-40-50-000-801).

(c) Examine the airfoils to the limits that follow:

1 Turn the compressor impeller with your hand to turn the turbine wheel to examine the

airfoils.

ITEM

Airfoils

- Light corrosion (equal on all blades)

- Extended corrosion (not equal damage to blade tips)

(d) Install the combustion liner (Ref. TASK 72-40-50-400-801).

(e) Install the outer combustion case (Ref. TASK 72-40-30-400-801).

SUBTASK 05-50-00-290-001

WARNING: DO NOT TOUCH THE COMPONENTS OF THE ENGINE UNTIL THEY ARE COOL.

(3) Do the borescope inspection of the first-stage turbine wheel airfoils (airfoils).

(a) Remove the fuel nozzle (Ref. TASK 73-11-10-000-801).

WARNING: DO NOT EXTEND THE BORESCOPE TOO FAR INTO THE ENGINE. DAMAGE

(b) Put the borescope in the outer combustion case.

(c) Examine the airfoils to the limits that follow:

1 Turn the compressor impeller with your hand to turn the turbine wheel to examine the

SERVICEABLE LIMITS REPAIR LIMITS ACTION NECESSARY

Permitted. There is no limit to the

quantity.

None permitted. Not repairable. Remove the engine (Ref.

THE TEMPERATURE STAYS HIGH AFTER THE ENGINE STOPS. THE HIGH TEMPERATURES CAN CAUSE INJURY TO PERSONS.

TO THE BORESCOPE AND ENGINE DISASSEMBLY CAN RESULT.

airfoils.

Examine again at each 200 hours to make sure that more damage has not occurred.

TASK 72-00-00-000-801). Install a replacement engine (Ref. TASK 72-00-00-400-801).

ITEM SERVICEABLE LIMITS REPAIR LIMITS ACTION NECESSARY

Airfoils

- Light corrosion (equal on all blades)

EFFECTIVITY: ALL

Permitted. There is no limit to the

quantity.

Examine again at each 200 hours to make sure that more damage has not occurred.

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ITEM SERVICEABLE LIMITS REPAIR LIMITS ACTION NECESSARY

- Extended corrosion (not equal damage to blade tips)

(d) Remove the borescope from the outer combustion case.

(e) Install the fuel nozzle (Ref. TASK 73-11-10-400-801).

J. Job Close-Up

SUBTASK 05-50-00-860-030

(1) Put the engine back in service.

(a) Close the applicable circuit breakers.

(b) Remove the applicable warning signs.

None permitted. Not repairable. Remove the engine (Ref.

TASK 72-00-00-000-801). Install a replacement engine (Ref. TASK 72-00-00-400-801).

EFFECTIVITY: ALL

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UNSCHEDULED MAINTENANCE CHECKS

CLEANING/PAINTING

TASK 05-50-00-100-801

1. Clean the Engine after Operation in a Corrosive Environment

A. General

This task gives you the procedure to water rinse an engine that was operated in a corrosive atmosphere, near a seashore, or in an area of heavy airborne industrial waste. Frequent inspections for signs of salt material and corrosion are necessary to find the corrosive environment in which the engine was operated. If corrosive material stays on the engine components, permanent damage can occur.

An engine which has been operated in a corrosive environment must be water rinsed to remove the water soluble corrosive material from the internal surfaces of the engine.

Corrosive environments can be found up to 150 miles inland, near metropolitan areas, and around other areas where industrial pollutants, sulfur laden atmosphere, pesticides, herbicides, salt water can be found. These conditions will change with the climate, wind direction and wind velocity.

An engine that has been operated in a corrosive environment must have the water rinse procedure done after the last flight of the day.

Additionally, an engine operated in a corrosive environment must have the external rinse procedure done every 15 days, unless inspection shows a more frequent requirement.

B. Materials

None

C. Consumable Materials

None

D. Expendable Parts

None

E. Standard Tools and Equipment

(1) Signs, warning.

F. Special Tools and Equipment

None

G. References

(1) TASK 72-00-00-100-803, Rinse the Gas Path.R

(2) TASK 72-00-00-100-804, General External Cleaning of the Engine.R

H. Job Set-Up

SUBTASK 05-50-00-860-027

(1) Make the aircraft safe.

(a) Open the applicable circuit breakers.

(b) Put up the applicable warning signs.

EFFECTIVITY: ALL

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I. Procedure

SUBTASK 05-50-00-170-001

WARNING: DO NOT TOUCH THE COMPONENTS OF THE ENGINE UNTIL THEY ARE COOL.

THE TEMPERATURE STAYS HIGH AFTER THE ENGINE STOPS. THE HIGH TEMPERATURES CAN CAUSE INJURY TO PERSONS.

(1) Clean the engine after operation in a corrosive environment.

(a) Flush the internal surfaces of the engine with water after the last flight of the day (Ref.

TASK 72-00-00-100-803R).

(b) Clean the external surfaces of the engine once every fifteen days (Ref. TASK

72-00-00-100-804R).

(c) Remove all the tools and equipment from the work area. Make sure the work area is

clean.

J. Job Close-Up

SUBTASK 05-50-00-860-028

(1) Return the engine to service.

(a) Close the applicable circuit breakers.

(b) Remove the applicable warning signs.

EFFECTIVITY: ALL

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CHAPTER 12

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CHAPTER SECTION OTHER SUBJECT PAGE IDENT DATE 12

R Contents 1/ Mar.1/10

2 R 10-73 1 Mar.1/10 R 10-73 2 Mar.1/10 R 10-79 1 Mar.1/10 R 10-79 2 Mar.1/10 R 10-79 301 Mar.1/10 R 10-79 302 Mar.1/10 R 10-79 303/ Mar.1/10

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CHAPTER 12

CLEAN AND FREE FROM CONTAMINATION CAN RESULT IN A DECREASE IN ENGINE PERFORMANCE OR CAN CAUSE ENGINE MALFUNCTION. ROLLS-ROYCE TEST OF JELLY TYPE CONTAMINATION SHOWS IT CAN GET THROUGH AIRCRAFT AND ENGINE FILTERS WITHOUT INDICATION FROM THE IMPENDING BYPASS INDICATOR. THIS CAN CAUSE BLOCKAGE OF THE FUEL NOZZLE SCREEN. IF JELLY TYPE CONTAMINATION, OR ANY OTHER FUEL SYSTEM CONTAMINATION IS FOUND IN THE AIRCRAFT OR ENGINE FUEL SYSTEM, ALL OF THE AIRCRAFT AND ENGINE FUEL SYSTEMS MUST BE EXAMINED.

(1) If you find gel-like material in the aircraft or engine fuel system, examine the complete aircraft and

engine fuel system.

NOTE

: It is very important that you keep the highest standards of cleanliness when you do

maintenance on the aircraft and engine fuel system.

(2) Primary. Fuels conforming to the following military and commercial specifications are approved for

unrestricted use in RR300 Series engines.

(a) MIL-DTL-5624, Grade JP-4 and JP-5

(b) MIL-DTL-83133, Grade JP-8

(c) ASTM D-6615, Jet B

(d) ASTM D-1655, Jet A or A1

(e) GOST 10227-86 (Russia), Grades TS-1 and RTR

(f) GSTU 320.00149943.007-97 (Ukraine), Grade RTR

(g) GSTU 320.00149943.011-99 (Ukraine), Grade TS-1R

(h) STAS 5639-88 (Romania), Grade THR

(3) Emergency

(a) There are no approved emergency fuels for the RR300/A1 engine.

(4) Cold Weather

(a) MIL-DTL-5624, Grade JP-4

(b) ASTM-D-6615, Jet B

(c) AVGAS-jet fuel mixture

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WARNING: AT AMBIENT TEMPERATURES BELOW +40°F (4.44°C) SOME TYPE OF FUEL

CAUTION: AVGAS-JET FUEL MIXTURES USING GRADE 91 OR GRADE 100LL AVGAS MUST

CAUTION: GRADE 100 AVGAS IS NOT APPROVED FOR USE IN AVGAS-JET FUEL

(d) The AVGAS-jet fuel mixture is an alternative fuel which can be used if cold start problems

occur when JP-4 or commercial Jet B cannot be obtained. The mixture must be one part by volume AVGAS to two parts by volume jet fuel. The AVGAS must meet ASTM D 910, grade 80, 91, or 100LL (low lead). The jet fuel can be MIL-DTL-5624 (Grade JP-5), MIL-DTL-83133 (Grade JP-8), ASTM-D-1655 (Jet A or A1).

R R R R

(e) Fuel additives (Russia) Fluid I (Ethylene glycol monoethyl ether - GOST 8313) and Fluid IM (a

mix of 50% Liquid I and 50% methyl alcohol-TU-6-10-1458) with a concentration of 0.1-0.3% by volume are approved for anti-icing with GOST 10227, Grades TS-1 and RT (Russia). No other fuel additives are Rolls-Royce approved.

(f) STAS 5639-88, Romanian TH fuel is comparable to ASTM D-1655 except the TH fuel could

have lower lubricity which can lead to increased wear in pumping elements of the fuel pump and fuel control. Rolls-Royce recommends the first fuel pump elements and fuel controls that reach TBO be sent to an AMC for analysis of possible gear wear.

ICING PROTECTION IS REQUIRED, SUCH AS AN ANTI-ICING ADDITIVE OR A MEANS OF AIRCRAFT FUEL ICE ELIMINATION. ENGINE FLAMEOUT COULD RESULT FROM FAILURE TO USE FUEL ICING PROTECTION.

BE RESTRICTED TO 300 HOURS PER OVERHAUL PERIOD DUE TO THE HIGHER LEAD CONTENT OF THE FUEL. THERE IS NO LIMIT FOR ENGINE OPERATION USING THE AVGAS-JET FUEL MIXTURE AS LONG AS GRADE 80 AVGAS IS USED AND THE 1:2 VOLUME RATIO IS OBSERVED. FAILURE TO OBEY THE STATED TIME LIMITS WILL RESULT IN DAMAGE TO THE ENGINE.

MIXTURES. GRADE 100 AVGAS HAS A HIGHER LEAD CONTENT THAN APPROVED FUELS. USE OF GRADE 100 AVGAS WILL RESULT IN DAMAGE TO THE ENGINE.

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ENGINE OIL SYSTEM

SYSTEMS DESCRIPTION SECTION

General

A. The engine oil system is serviced as necessary. The oil that is used to service the engine must be in the

table that follows.

R R R R R

R R R

CAUTION: DO NOT OPERATE THE ENGINE WITH OILS FROM A DIFFERENT CLASS OR

SPECIFICATION MIXED TOGETHER FOR MORE THAN THE FIVE HOUR LIMIT. ONLY SPECIFIED OILS IN AN OIL CLASS CAN BE MIXED WITHOUT A TIME LIMIT. MAINTENANCE RECORDS MUST BE KEPT TO MAKE SURE YOU DO NOT OPERATE FOR MORE THAN THE FIVE HOUR LIMIT. ENGINE MALFUNCTION CAN OCCUR.

CAUTION:R DO NOT FAIL TO USE THE ENGINE AND AIRCRAFT MANUALS TO KEEP THE

COMPLETE OIL SYSTEM IN A SATISFACTORY CONDITION. ENGINE MALFUNCTION CAN OCCUR.

CAUTION: IF HEAVY CARBON OR COKE DEPOSITS ARE FOUND ON THE ENGINE FILTER

DURING REGULAR INSPECTIONS, IT IS RECOMMENDED THE FILTERS BE REPLACED; CONTINUE TO MONITOR BYPASS INDICATORS.

CAUTION

CAUTION: FAILURE TO COMPLY WITH OIL MIXING RESTRICTIONS CAN RESULT IN ENGINE

CAUTION: REMOVE AND INSPECT THE OIL FILTER AFTER 25 HOURS OF ENGINE OPERATION

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

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

CAUTION: USE OF OILS WHICH ARE NOT INCLUDED IN THE APPROVED OILS LISTING, OR

CAUTION:R DO NOT FAIL TO MAKE SURE THAT THE OIL FLOWS FROM THE GAS PRODUCER (#8

Oil Specification

: DO NOT USE AN OIL THAT IS NOT INCLUDED IN THE APPROVED OILS TABLE.

DAMAGE TO THE ENGINE OR ENGINE FAILURE CAN OCCUR. IF YOU USE AN OIL THAT IS NOT LISTED, IT WILL BE CONSIDERED MISUSE UNDER THE PROVISIONS OF THE ENGINE WARRANTY.

FAILURE.

IF THE TYPE OF OIL (NON AS5780 HPC) WAS MIXED IN AN EMERGENCY. (THERE IS A 5-HOUR LIMIT FOR THE USE OF MIXED OILS).

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

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 25 HOUR OIL MONITORING IS TO CONTINUE UNTIL THE NEXT OIL CHANGE PERIOD.

FAILURE TO DRAIN OIL WITHIN THE PRESCRIBED INTERVAL GIVEN IN TASK 05-21-00-200-801, WILL BE CONSIDERED AS MISUSE UNDER THE PROVISIONS OF THE WARRANTY POLICY.

BEARING SCAVENGE) WHEN THE ENGINE OIL SYSTEM IS DRAINED AND SERVICED. ENGINE MALFUNCTION CAN OCCUR.

NOTE: WHILE CONSIDERABLE LABORATORY DATA IS AVAILABLE TO DEMONSTRATE THE

COMPATIBILITY OF ONE SYNTHETIC TURBINE OIL WITH OTHER TURBINE OILS MEETING THE SAME SPECIFICATION (AIRLINE EXPERIENCE DOES DEMONSTRATE THIS PROPERTY), THE INDISCRIMINATE MIXING OF APPROVED OILS DURING THE OPERATIONAL USE OF THE OIL IS NOT RECOMMENDED. HOWEVER, THERE MAY BE CIRCUMSTANCES WHERE EMERGENCY TOP--OFF, INADVERTENT MIXING, OR CHANGE-OVER BY "TOP--OFF" TO ANOTHER BRAND CAN OCCUR. THESE ARE ACCEPTED PRACTICES.

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(1) The RR300 series engines are qualified and certified for use with AS5780 High Performance

Capability Class (HPC) lubrication oils. The vendor brands of AS5780 HPC lubricating oils which have been engine tested and approved for use in the RR300 series engine are given in TABLE 1.

Approved Oil

(2) This table shows the approved oil for the RR300 Series Engines.

TABLE 1 Approved Oils

APPROVED OIL

MJO 254 AS5780 High

BPTO 2197 AS5780 HPC Air BP Lubricants

Lubrication

(3) The types of oil recommended at specific ambient temperatures are as follows:

-40°F (-40°C) and above............................AS5780 High Performance Capability Class (HPC).

NOTE: Because of availability, reduced coking and better lubricating qualities at higher

temperatures, AS5780 HPC oils are to be used in the RR300 series engines.

NOTE: Check the engine oil quantity within 15 minutes of engine shutdown to avoid a false

indication of excessive oil consumption. If the 15 minutes has been exceeded, motor the engine for 30 seconds with the starter before checking tank quantity. Motoring normally scavenges oil from the gearbox back to the aircraft oil tank. Check the airframe flight manual; some installations can require an engine to be operated for at least a minute at ground idle to make sure that scavenging of the engine gearbox is satisfactory.

NOTE: Always refer to the airframe flight manual for proper oil servicing instructions; specific

requirements can be different for different models.

SPECIFICATION MANUFACTURERS USE

Exxon Mobil Lubricants Performance Capability Class (HPC)

and Petroleum Spec.

234 Daniels Way,

Swedesboro, NJ.

08085-1820

Six Campus Drive, Maple

Plaza II, Parsipanny, NJ.

07054, USA

Lubrication and operation in temperatures from

-40.0°F (-40°C) and above

Lubrication and operation in temperatures from

-40.0°F (-40°C) and above

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ENGINE OIL SYSTEM

SERVICING

TASK 12-10-79-600-801

1. Service the Oil System of the Engine

CAUTION: DO NOT USE OIL THAT IS NOT INCLUDED IN THE APPROVED OILS TABLE. THIS WILL

VOID THE WARRANTY AND ENGINE DAMAGE CAN OCCUR.

CAUTION: THE OIL MUST BE DRAINED IN THE APPROVED INTERVAL. IF IT IS NOT, THIS WILL VOID

THE WARRANTY AND ENGINE DAMAGE CAN OCCUR.

A. General

This task gives you the procedure to service the oil system of the engine.

B. Materials

None

C. Consumable Materials

None

D. Expendable Parts

None

E. Standard Tools and Equipment

(1) Signs, warning.

F. Special Tools and Equipment

None

G. References

None

(1) 12-10-79, Engine Oil System, Systems Description.

(2) TASK 79-23-10-000-801, Remove the Power-and-accessory Gearbox Oil Filter.

(3) TASK 79-23-10-200-801, Do the Inspection of the Power-and-accessory Gearbox Oil Filter.

(4) TASK 79-23-10-400-801, Install the Power-and-accessory Gearbox Oil Filter.

(5) TASK 79-37-00-000-801, Remove the Magnetic Plug.

(6) TASK 79-37-00-200-801, Do the Inspection of the Magnetic Plug.

(7) TASK 79-37-00-400-801, Install the Magnetic Plug.

(8) OEM Aircraft Maintenance Manual, AMM.

H. Job Set-Up

SUBTASK 12-10-79-940-001

(1) Make the aircraft safe.

(a) Open the applicable circuit breakers.

(b) Put up the applicable warning signs.

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I. Procedure

SUBTASK 12-10-79-680-001

(1) Drain the oil from the airframe oil tank.

(a) Drain the oil from the airframe oil tank (REF. OEM AMM).

SUBTASK 12-10-79-020-001

(2) Remove the magnetic plugs from the power-and-accessory gearbox.

(a) Remove the magnetic plugs from the power-and-accessory gearbox (REF. TASK

79-37-00-000-801).

SUBTASK 12-10-79-280-001

(3) Do the inspection of the magnetic plugs.

(a) Do the inspection of the magnetic plugs (REF. TASK 79-37-00-200-801).

SUBTASK 12-10-79-020-002

(4) Remove the power-and-accessory gearbox oil filter.

(a) Remove the power-and-accessory gearbox oil filter (REF. TASK 79-23-10-000-801).

SUBTASK 12-10-79-420-001

(5) Install the magnetic plugs in the power-and-accessory gearbox.

(a) Install the magnetic plugs in the power-and-accessory gearbox (REF. TASK

79-37-00-400-801).

SUBTASK 12-10-79-610-001

CAUTION

(6) Fill the airframe oil tank.

SUBTASK 12-10-79-210-001

(7) Do the inspection of the power-and-accessory gearbox oil filter.

SUBTASK 12-10-79-420-002

(8) Install the power-and-accessory gearbox oil filter.

: DO NOT OPERATE THE ENGINE WITH OIL FROM A DIFFERENT CLASS OR

SPECIFICATION MIXED TOGETHER FOR MORE THAN THE FIVE HOUR LIMIT. ENGINE MALFUNCTION CAN OCCUR.

(a) Fill the airframe oil tank (REF. 12-10-79 and OEM AMM).

(a) Do the inspection of the power-and-accessory gearbox oil filter (REF. TASK

79-23-10-200-801).

(a) Install the power-and-accessory gearbox oil filter (REF. TASK 79-23-10-400-801).

SUBTASK 12-10-79-710-001

(9) Do the test of the engine.

(a) Use the starter to motor the engine until an indication of oil pressure is shown (REF. OEM

AMM).

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(b) Start the engine and operate at idle for five minutes. Make sure to monitor the oil

pressure.

(c) Record the oil change in the maintenance records.

J. Job Close-Up

SUBTASK 12-10-79-940-002

(1) Put the aircraft back in service.

(a) Close the applicable circuit breakers.

(b) Remove the applicable warning signs.

EFFECTIVITY: ALL

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CHAPTER 70

LIST OF EFFECTIVE PAGES

CHAPTER SECTION OTHER SUBJECT PAGE IDENT DATE 70

Contents 1/ Oct.15/11

2 00-00 201 Sep.15/10 00-00 202 Sep.15/10 00-00 203 Sep.15/10 00-00 204 Sep.15/10 00-00 205 Sep.15/10 00-00 206 Sep.15/10 00-00 207 Sep.15/10 00-00 208 Sep.15/10 00-00 209 Sep.15/10 00-00 210 Sep.15/10 00-00 211 Sep.15/10 00-00 212 Sep.15/10 00-00 213 Sep.15/10 00-00 214 Sep.15/10 00-00 215 Sep.15/10 00-00 216 Sep.15/10 00-00 201 Mar.1/10 00-00 202 Mar.1/10 00-00 203 Mar.1/10 00-00 204 Mar.1/10 00-00 205/ Mar.1/10

206 R 00-00 201 Dec.15/11 R 00-00 202 Dec.15/11

00-00 201 Jun.15/11

00-00 202 Jun.15/11 R 00-00 201 Dec.15/11 R 00-00 202 Dec.15/11

00-00 201 Mar.1/10

00-00 202 Mar.1/10

00-00 201/ Mar.1/10

202 00-00 601 Sep.15/10 00-00 602 Sep.15/10 00-00 603 Sep.15/10 00-00 604 Sep.15/10 00-00 605 Sep.15/10 00-00 606 Sep.15/10 00-00 607 Sep.15/10 00-00 608 Sep.15/10 00-00 601 Mar.1/10 00-00 602 Mar.1/10 00-00 603 Mar.1/10 00-00 604 Mar.1/10 00-00 601 Jan.20/08 00-00 602 Jan.20/08 00-00 603/ Jan.20/08

604 00-00 701 Mar.1/10 00-00 702 Mar.1/10 00-00 801 Mar.1/10 00-00 802 Mar.1/10 00-00 803/ Mar.1/10

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CHAPTER 70

CONTAIN TRICRESYL PHOSPHATE. USE IN AN AREA WITH CONTINUOUS AIRFLOW. KEEP AWAY FROM HEAT, SPARKS, AND OPEN FLAMES. DO NOT GET IT ON YOUR SKIN OR IN YOUR EYES. WEAR GOGGLES, CHEMICAL-RESISTANT GLOVES, AND SAFETY CLOTHING. IF YOU GET IT ON YOUR SKIN, CLEAN WITH SOAP AND WATER. IF YOU GET IT IN YOUR EYES, FLUSH WITH WATER. GET MEDICAL AID.

CAUTION

(1) Use the values and procedures that follow to torque the bolts, the nuts, or the screws, unless

: DO NOT APPLY LUBRICANT TO THE ELECTRICAL CONNECTOR UNLESS

SPECIFIED DIFFERENTLY. DAMAGE TO THE ELECTRICAL HARNESS CAN OCCUR.

specified differently.

(a) Make sure you reference the appropriate table to determine the correct torque value for

the fastener you are about to torque.

(b) Lubricate all engine fasteners as specified in installation task.

(c) Use a smooth and continuous motion when you use the torque wrench.

(d) If a nut is installed on a bolt, apply the torque to the nut.

(e) If a screw is installed with a nut, apply the torque to the nut.

(f) In most installations, if a fastener is removed with a wrench, it is a bolt. If a fastener is

removed with a screwdriver, it is a screw.

(g) Torque all the internal wrenching (Allen) bolts the same as you would torque the bolts.

(h) If a set screw (any head type) is installed, torque to the screw torque limit.

(i) When you torque double-ended bolts with more than one thread size, torque to the limit

for the smallest thread size.

(j) Torque all sizes of pal nuts to 60 degrees or one flat more than finger tight.

(k) If the bolts, the nuts, or the screws are in a circle that contains metal O-ring gaskets,

tighten in a circular pattern until the bolts, the nuts, or the screws are tightened to the specified torque.

1 Do step (k) again, as necessary, to make sure the bolt, the nut or the screw keeps its

torque.

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(l) If the bolts, the nuts, or the screws are in a circle, tighten the bolts, the nut, or the screws

180 degrees apart (crossing pattern) that follows:

1 Tighten the bolts, the nuts, or the screws in a crossing pattern to half of the minimum

2 Torque the bolts, the nut, or the screws in the crossing pattern again to the specified

3 Do step 2 again, as necessary, to make sure the bolt, the nut, or the screw keeps its

(m) If the bolts, the nuts, or the screws are on a splitline (not a circle), do the procedure that

follows:

1 Tighten the mid-section bolts, the mid-section nuts, or the mid-section screws first to

2 Torque the bolts, the nuts, or the screws to the specified torque value. Tighten the

3

(n) If you install a spanner nut with a thread size larger than 1.00 in. (25.4 mm), do the

procedure that follows:

1 Tighten the spanner nut with your fingers.

2 Tighten the spanner nut to the maximum specified torque.

3 Loosen the spanner nut and tighten again to the specified torque.

(o) If the slot in a castle nut or the lockwire hole in a bolt or screw is not aligned when you get

to the minimum torque limit do the procedure that follows:

1 Tighten to the next aligned position. Do not torque more than the maximum torque

2 If you cannot get the correct alignment, loosen the nut one-half turn and then tighten

CAUTION: TABLE 202 CONTAINS TORQUE VALUES FOR SELF-LOCKING FASTENERS.

(p) If you are required to torque the self-locking fastener above the drag torque, do the

procedure that follows:

1 Use a swing scale or a dial-type torque wrench to measure the drag torque of the

2 Record the drag torque of the self-locking fastener.

3 Add the torque from the applicable maintenance manual to the drag torque of the

4 Torque the self-locking fastener to the value you calculated in step 3.

torque.

half of the minimum torque. Tighten all the remaining bolts, nuts, or screws to half the minimum torque.

mid-section bolts, the nuts, or the screws first, then tighten theremaining bolts, the nuts or the screws.

Do step 2 again, as necessary, to make sure the bolts, the nuts, or the screws keep their torque.

limit.

again.

THE DRAG TORQUE IS INCLUDED IN THE VALUES IN TABLE 202. TORQUE THE SELF-LOCKING FASTENERS ABOVE THE DRAG TORQUE ONLY WHEN REQUIRED BY THE APPLICABLE MAINTENANCE MANUAL. SELF-LOCKING FASTENER AND ENGINE DAMAGE CAN OCCUR.

self-locking fastener. Measure the drag torque while you turn the self-locking fastener.

NOTE: The drag torque is the torque required to make the self-locking fastener

continue to turn.

self-locking fastener.

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CAUTION: DO NOT MIX UNITS WHEN YOU CALCULATE THE TORQUE. IF THE TORQUE

(q) If an extension is used with the torque wrench, calculate the torque as follows:

NOTE: If you use the torque wrench at 90 degrees to the extension, the torque value is

1 If the torque wrench is the swing scale or dial indicator type (length that cannot be

REQUIREMENT IS IN-LB, YOU MUST MAKE ALL OF THE MEASUREMENTS AND CALCULATIONS IN INCHES AND POUNDS. IF THE TORQUE REQUIREMENT IS FT-LB, YOU MUST MAKE ALL OF THE MEASUREMENTS AND CALCULATIONS IN FEET AND POUNDS. IF THE TORQUE REQUIREMENT IS NM, YOU MUST MAKE ALL OF THE MEASUREMENTS AND CALCULATIONS IN NEWTONS AND METERS.

the same as on the torque wrench.

changed) calculate the correct torque with the formula below:

(T x L)

S =

(L + E)

S = The corrected torque wrench reading

T = The torque that is specified for the fastener

L = The length of the torque wrench

E = The length of the extension.

NOTE: The length of the wrench (L) is the distance between the center of the

square drive and the center of the hand grip. The length of the extension (E) is the distance between the center of the openings.

a If it is necessary to attach the extension at an angle that is not a 180 degree

angle, the corrected length of the assembly will be L + E(1). The E(1) length must be used for length E in the formula.

TABLE 201 - Standard Torque Values for Bolts Installed with Steel Tension-Type Nuts, Steel Tapped Holes,

and Steel Inserts (Without Self-Locking Features)

Without Self-Locking Features

Thread Size Torque (in-lb) Torque (ft-lb)

4 - 40 6.0-8.0 in-lb (0.7-0.9 Nm)

4 - 48 6.0-8.0 in-lb (0.7-0.9 Nm)

6 - 32 7.0-9.0 in-lb (0.8-1.0 Nm)

6 - 40 9.0-11.0 in-lb (1.0-1.2 Nm)

8 - 32 12.0-15.0 in-lb (1.4-1.6 Nm)

8 - 36 17.0-20.0 in-lb (2.0-2.2 Nm)

10 - 24 25.0-30.0 in-lb (2.9-3.9 Nm)

10 - 32 35.0-40.0 in-lb (4.0-4.5 Nm)

1/4 - 20 60.0-65.0 in-lb (6.8-7.3 Nm)

1/4 - 28 70.0-85.0 in-lb (8.0-9.6 Nm)

5/16 - 18 105.0-115.0 in-lb (11.9-12.9 Nm)

EFFECTIVITY: ALL

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EXPORT CONTROLLED

PROPRIETARY DATA - UNSECURED DATA

PROPRIETARY DATA - UNSECURED COPY

Without Self-Locking Features

Thread Size Torque (in-lb) Torque (ft-lb)

5/16 - 24 120.0-150.0 in-lb (13.6-16.9 Nm)

3/8 - 16 18.0-20.0 ft-lb (23.2-27.6 Nm)

3/8 - 24 20.0-23.0 ft-lb (27.2-31.6 Nm)

7/16 - 14 30.0-32.0 ft-lb (39.6-44.0 Nm)

7/16 - 20 34.0-38.0 ft-lb (45.2-52.5 Nm)

1/2 - 20 47.0-54.0 ft-lb (65.0-73.4 Nm)

9/16 - 12 60.0-65.0 ft-lb (81.4-88.1 Nm)

9/16 - 18 65.0-75.0 ft-lb (88.2-101.0 Nm)

5/8 - 18 90.0-100.0 ft-lb (122.0-135.6 Nm)

TABLE 202 - Standard Torque Values for Bolts Installed with Steel Tension-Type Nuts, Steel Tapped Holes,

and Steel Inserts (With Self-Locking Features)

With Self-Locking Features

Thread Size Torque (in-lb) Torque ft-lb

4 - 40 6.0-8.0 in-lb (0.7-0.9 Nm)

4 - 48 6.0-8.0 in-lb (0.7-0.9 Nm)

6 - 32 8.0-10.0 in-lb (0.9-1.1 Nm)

6 - 40 10.0-12.0 in-lb (1.1-1.3 Nm)

8 - 32 13.0-17.0 in-lb (1.5-1.9 Nm)

8 - 36 19.0-22.0 in-lb (2.2-2.4 Nm)

10 - 24 27.0-32.0 in-lb (3.1-3.6 Nm)

10 - 32 37.0-42.0 in-lb (4.2-4.7 Nm)

1/4 - 20 65.0-70.0 in-lb (7.4-7.9 Nm)

1/4 - 28 74.0-89.0 in-lb (8.4-10.0 Nm)

5/16 - 18 113.0-123.0 in-lb (12.8-13.9 Nm)

5/16 - 24 140.0-170.0 in-lb (15.9-19.2 Nm)

3/8 - 16 19.0-21.0 ft-lb (24.6-29.0 Nm)

3/8 - 24 23.0-25.0 ft-lb (30.0-33.9 Nm)

7/16 - 14 31.0-33.0 ft-lb (41.5-45.9 Nm)

7/16 - 20 35.0-38.0 ft-lb (46.8-54.1 Nm)

1/2 - 20 49.0-55.0 ft-lb (67.1-74.5 Nm)

9/16 - 12 63.0-68.0 ft-lb (84.8-91.5 Nm)

9/16 - 18 67.0-77.0 ft-lb (90.9-104.4 Nm)

5/8 - 18 93.0-103.0 ft-lb (125.6-139.2 Nm)

EFFECTIVITY: ALL

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Rolls-Royce RR300 series Operation And Maintenance Manual

SERVICE BULLETIN LIST

INTRODUCTION

TABLE OF CONTENTS

TABLE OF CONTENTS

TABLE OF CONTENTS