109c Faa Mpm

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A109CHELICOPTERMODELTHIS MANUAL A109C-MPM 1st ISSUE DATED 26 MAY 2009 REPLACES AND SUPER-SEDES CHAPTERS 04 AND 05 OF THE MANUAL A109C-MM REVISION 13 DATED 29FEBRUARY 2008.

First Issue: 26th May 2009Revision: No. 1 - 30th July 2010

THIS PUBLICATION IS ISSUED BY AGUSTA S.p.A.

This document contains proprietary data and information and shall not be disclosed, reproduced in whole or in part for any purpose, otherthan helicopter operation or maintenance, without prior written authorization from Agusta S.p.A.

AGUSTA PUBLICATION CODE 502052901A

LIST OF EFFECTIVE PAGES

INSERT LATEST REVISED PAGES. DESTROY SUPERSEDED PAGES.

NOTE: The portion of page affected by the revision is indicated by a black vertical line in the outer margin.

CAUTION: Upon receipt of the second and subsequent revisions to this manual, personnel responsible formaintaining this publication in current status will ascertain that all previous revisions have beenreceived and incorporated. Action should be taken promptly if the publication is incomplete.

Dates of original and revised pages are:

Original 1 26-05-2009Revision 1 30-07-2010

Total number of pages in this volume is 180 consisting of the following:

Page No. Revision No. Page No. Revision No. Page No. Revision No.

Title Page 1List of effective pagesA 1H-1 1H-2 0ROTR 1 and ROTR 2 0ROR 1 and ROR 2 0Table of contentsi and ii 0Introductioniii thru viii 0Chapter 04(F.A.A. approved)Refer to applicable List ofEffective Pages contained inChapter 04Issue 3, 22 March 2005Chapter 0505-i thru 5-iii 005-iv blank 005-1 thru 05-146 005-147 and 05-148 1

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HIGHLIGHTS

In this table you can find all changes incorporated in this new edition dated 26th May 2009 that replaced theprevious chapter 5 of maintenance manual.

Revision N. Reason for change

First Issue − Update Section 05-10-00 page 05-9 (Technical Changes), to add the overhaul interval of startergenerator (AW Protocol TPD 2551), Heat exchanger and Cooling Turbine overhaul interval (AWProtocol TPD 2529).

− Update Section 05-50-00 page 05-94 (Technical Change), to modify the note each 50 hours (AWProtocol TPD 1972 and B.T. 109-125).

− Update Section 05-50-00 page 05-94 (Technical Change), to add new inspection on the tail rotoreach 50 hours (AW Protocol B.T. 109-127).

− Update Section 05-50-00 page 05-95 (Technical Change), to add inspection of hydraulic SystemN. 1 pipes (AW Protocol B.T. 109-128).

− Update Section 05-50-00 page 05-98 (Technical Change), to add an inspection on the groovedclamps (AW Protocol TPD 1507 and Temporary Revision 05-1).

− Update Section 05-50-00 page 05-100 (Technical Change), to add new inspection each 3 years andmodify the cross reference (AW Protocol TPD 2291 and B.T. 109-121).

− Update Section 05-50-00 page 05-106 (Technical Change), to modify ″OVERSPEED″ conditionalinspection removed reference to engine overspeed (AW Protocol TPD 2089).

− Update Section 05-50-00 page 05-106 (Technical Change), to modify the point 3. b. on the suddenstoppage-tail rotor (AW Protocol TPD 1536).

− Update Section 05-60-00 page 05-115 (Technical Change), to add new E.C.S. special inspections(AW Protocol TPD 2137).

− Update Section 05-60-00 page 05-125 (Technical Change), to modify the special inspection on theemergency floats (AW Protocol TPD 1617).

− Update Section 05-60-00 page 05-141 (Technical Change), to add new emergency locatortransmitter ″EBC 102A″ or ″EBC 302H″ scheduled inspection (AW Protocol TPD 1869).

Revision 1 - Update Section 05-70 (Technical Change), to add the new T/R duplex bearing and its lubricationinterval (AW Protocol NDC 109-0130-004).

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RECORD OF TEMPORARY REVISIONS

Temporary Revision Interested PagesDate Inserted

Incorporated

No. Date Chapter/Section Page Rev. No. Date

05-1 15-05-2008 05-50-00 05-98 Issue 1 26-05-2009

INSTRUCTIONS: 1. FILE THIS RECORD OF TEMPORARY REVISIONS IN THE FRONT OF THEMANUAL.

2. ONLY ACTIVE TEMPORARY REVISIONS APPEAR IN THIS LIST. ALL OTHERTEMPORARY REVISIONS SHOULD BE REMOVED FROM THE MANUAL.

3. THIS LIST WILL BE REVISED EACH TIME THAT TEMPORARY REVISIONSARE ISSUED, REVISED, OR INCORPORATED BY A NORMAL REVISION, ANASTERISK (*) WILL IDENTIFY TEMPORARY REVISION PAGES PROVIDEDWITH THIS LIST: DESTROY SUPERSEDED, INCORPORATED, OR CAN-CELED TEMPORARY REVISION PAGES.

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RECORD OF REVISIONS

REVISIONNUMBER

ISSUEDATE

DATEINSERTED

BYREVISIONNUMBER

ISSUEDATE

DATEINSERTED

BY

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TABLE OF CONTENTS

Chapter Title

Introduction04 AIRWORTHINESS LIMITATIONS05 SCHEDULE/UNSCHEDULED MAINTENANCE

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INTRODUCTION

SCOPE

This manual contains the necessary information for carrying out the maintenance of the A109C helicopter,manufactured by AGUSTA, Cascina Costa (Varese) Italy.These instructions provide you with specific knowledge of the aircraft and its characteristics: your experience isrecognized, therefore basic maintenance principles are avoided.Instructions in this manual are prepared to be understandable by the least experienced maintenance personnel thatcan be expected to perform the maintenance operations.Execution of the maintenance procedures must be however in accordance with the operations described in thismanual so as to keep the flight characteristics of the helicopter within the terms of the guarantee.This manual provides the best possible instructions but it is not a substitute for sound judgement.

CAUTION: THE INSPECTION AND MAINTENANCE INSTRUCTIONS RELEVANT TO THE ENGINES,AVIONICS, INSTRUMENTS AND ANY OTHER ACCESSORY ARE CONTAINED IN THEPUBLICATIONS ISSUED BY THE MANUFACTURER OF THE AFFECTED ITEM.

ARRANGEMENT

The content of the manual has been divided in accordance with international aeronautical regulations (ATA100),in order to facilitate their use and consultations by operators.The divisions contained refer to functional groups and systems. They do not refer to the physical locations ofcomponents.The general arrangement is as follows:

CHAPTER - A division dealing with the separate treatment of a system, such as rotors, electricalsystem, etc.This division is identified by the first set of digits (i.e. 65-.....;24-.....).

SECTION - A division dealing with the separate treatment of a sub-system component such asmain rotor, tail rotor, etc.This division is identified by the second set of digits (i.e. 65-10..;24-20..).

SUBJECT - A division dealing with a specific subject.This division is identified by the third set of digits (i.e. 65-10-01; 24-20-05).

APPLICABILITY

This manual applies to all A109C helicopters. Whenever the content is applicable to a particular helicopter/s thisfact is indicated before the relevant text by Serial Number of the helicopter/s.

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APPLICABILITY CODE SYSTEM

— Alphabetic code U, used to identify configuration changes connected to the helicopters certified by BritishCivil Aviation Authority.

— Alphabetic code X used to identify optional system/equipment. For example:SECTION 23-10 VHF/AM SYSTEM (COLLINS VHF-22)hX

NUMBERING SYSTEM OF PAGES, PARAGRAPHS, FIGURES AND TABLES

— The pages are numbered consecutively within each chapter. For example:

Number Meaning

29-15 Chapter 29, page 15

— The paragraphs are numbered consecutively within each section. For example:

Number Meaning

29-10-8 Chapter 29, Section 10, eighth paragraph.

— The figures and tables are numbered consecutively with each chapter. For example:

Number Meaning

29-6 Chapter 29, sixth figure or table

DEFINITIONS

Throughout this manual, adjuncts to the text are used to highlight or emphasize important points when necessary.Warnings, cautions and notes which appear in this manual are defined as follows:

WARNING: A MAINTENANCE PROCEDURE, PRACTICE, CONDITION, ETC. WHICH IF NOT COR-RECTLY FOLLOWED, COULD RESULT IN PERSONAL INJURY, OR LOSS OF LIFE.

CAUTION: A MAINTENANCE PROCEDURE, PRACTICE, CONDITION, ETC. WHICH IF NOT STRICTLYOBSERVED, COULD RESULT IN DAMAGE OR DESTRUCTION OF EQUIPMENT.

NOTE: A maintenance procedure, condition or statement which is deemed essential to highlight.

ABBREVIATIONS

Non-standard abbreviations used in this manual are as follows:

— OM: Overhaul Manual

— CMM: Component Maintenance Manual

— COM: Component Overhaul Manual

— FM: Flight Manual

— SRM: Standard Repair Manual

— WD: Wiring Diagram

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UP-DATING

The content of this manual is subject to updating.

Variations and modifications will be introduced as the result of increase of information available, modification ofaircraft and progressive extension of the maintenance operations.Every effort is made to keep this manual current, review conferences with maintenance personnel and a constantreview of maintenance and discrepancy reports assure inclusion of the latest data in the manual. However, wecannot correct an error unless we know of its existence. In this regard it is essential that you do your part byforwarding the attached ″Technical Publications Discrepancy Form″ giving detail of the discrepancy.

PURCHASE OF TECHNICAL PUBLICATIONS

The present manual forms part of a set of publications applicable to the A109C helicopter model. This setcomprises:

Rotorcraft Flight Manual A109C-RFM

Maintenance Planning Manual A109C-MPM

Maintenance Manual A109C-MM

Overhaul Manual A109C-OM

Illustrated Parts Catalog A109C-IPC

Structural Repair Manual A119/A109 SERIES-SRM

Pictorial Tools Usage Manual A119/A109 SERIES-PTUM

Bollettini Tecnici A109

Information Letters —

CUSTOMER SUPPORT & SERVICES - ItalyProduct Support Engineering Dept.

Via per Tornavento, 1521019 Somma Lombardo (VA) Italy

Tel.: (+39) 0331 711345 - Fax: (+39) 0331 711184http://www.agusta.com - e-mail: [email protected].

Operators of the A109C helicopter model may obtain copies of the above publications by writing to the abovestated address.

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TECHNICAL PUBLICATIONS DISCREPANCY FORM

SUBMITTED TO:

Agusta S.p.A.Customer Support & Services - ItalyProduct Support EngineeringVia per Tornavento, 1521019 Somma Lombardo (VA) Italyfax: +39-0331711180E-mail:[email protected]

SUBMITTED BY:

Customer name and address:————————————————————————————————

————————————————————————————————

————————————————————————————————

————————————————————————————————

Phone ———————————————————————————

Fax —————————————————————————————

E-mail ———————————————————————————

IF YOU BELIEVE THAT YOU HAVE DISCOVERED A DISCREPANCY IN THE TECHNICAL PUBLICA-TION, PLEASE IDENTIFY THE PUBLICATION, DESCRIBE THE DISCREPANCY OR DEFICIENCY INDETAIL AND FORWARD TO AGUSTA AT THE ABOVE ADDRESS.

NUMBER: DATE:

PUBLICATION AFFECTED: PUBLICATION TITLE:

ISSUE DATE: CHANGE/REVISION DATE:

AFFECTED PAGE N.: AFFECTED FIGURE:

DISCREPANCY OR DEFICIENCY (DESCRIBE DISCREPANCY WITH TEXT AND/OR SKETCH).

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CHAPTER 04

AIRWORTHINESS LIMITATIONS

F.A.A. APPROVED

LIST OF EFFECTIVE PAGES

INSERT LATEST REVISED PAGES. DESTROY SUPERSEDED PAGES.

NOTE: The portion of page affected by the revision is indicated by a black vertical line in the outer margin andthe approval revision number is printed in the lower margin.

CAUTION: Upon receipt of the second and subsequent revisions to this Chapter 04, personnel responsible formaintaining it in current status will ascertain that all previous revisions have been received andincorporated. Action should be taken promptly if this Chapter 04 is incomplete.

Dates of original and revised pages are:

Issue 3 22 March 2005

Total number of pages in this chapter is 10 consisting of the following:

Page No. Revision No. Page No. Revision No. Page No. Revision No.

A 0B blank 004-i 004-ii blank 004-iii 004-iv blank 004-1 thru 04-3 004-4 blank 0

F.A.A. pages are printed on yellow pages.

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CHAPTER 04 - AIRWORTHINESS LIMITATIONS

TABLE OF CONTENTS

Sect/Para Page

LIST OF REVISED PAGES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 04-iii

04-00 AIRWORTHINESS LIMITATIONS SECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 04-1

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LIST OF REVISED PAGES

Issue/Revision No. Subject F.A.A. Approved

Issue 1 - 18-12-1995

Issue 2 Supersedes Issue 1 dated 18-12-1995 06-09-2002

Issue 3 Supersedes Issue 2 dated 06-09-2002 22-03-2005

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SECTION 04-00

AIRWORTHINESS LIMITATIONS SECTION

NOTE 1 : The Airworthiness Limitations Section is F.A.A. approved for U.S. registered A109C helicopters inaccordance with the provision of CFR section 21-29. In addition, this section is required by F.A.A.Type Certificate Data Sheet No. H7EU and it specifies maintenance required under 14 CFR sections43.16 and 91.163 unless an alternative program has been F.A.A. approved.

NOTE 2 : When components with a retirement life and with the same part number and therefore interchangeableare used promiscuously on A109 models, they must be restricted to the lowest retirement value.

NOTE 3 : The retirement life specified for any given part number contained in this airworthiness limitationsschedule applies to indicated and all successive dash numbers for that item unless otherwise specified.

AIRWORTHINESS LIMITATIONS SCHEDULE

Part Number Denomination Retirementlife (hrs.)

MAIN ROTOR HUB AND BLADES

709-0103-01-101 Blade 25000

109-8101-47-105 Blade pin 25000

709-0101-10-101 Grip assembly 10000

109-0101-95-3 (Bendix) Retention strap 5000 or 8 years from firstinstallation

109-0101-95-105 (Lord ) Retention strap 5000 or 8 years from firstinstallation

109-0101-84-1 Inboard strap pin 5000

109-0101-94-1 Inboard strap fitting 5000

109-0101-23-3 Outboard strap pin 5000

109-0101-24-1 Plate stop 5000

109-0101-78-1 (only) Bolt 5000

109-0101-02-1 Hub assembly 25000

109-0101-04-113 Spindle assembly 25000

109-0101-13-3 Drag pin 4200

109-0101-12-5 Flap pin 4200

109-0101-03-1 Adapter, coupling assembly 25000

109-0101-90-1 Sleeve 4200

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AIRWORTHINESS LIMITATIONS SCHEDULE (Contd)


TAIL ROTOR HUB AND BLADE ASSEMBLY

109-8132-01-1 Blade 3000

109-8131-07-1 Retention strap assembly 6820 (see note 1)

109-8131-08-1 Strap pin 6820 (see note 1)

109-8131-06-1 Strap plug 6820 (see note 1)

109-0131-06-7 (only) Hub assembly 5180 (see note 1)

109-0131-06-101 Hub assembly 3600

109-0131-05-9 Trunnion assembly 12760

109-8131-33-101 Trunnion assembly 12760

109-8131-09-1 Bolt, retention strap 6820 (see note 1)

109-8131-05-109 Grip assembly 1000 (see note 2)

109-8131-29-101 Grip assembly 3000

MAIN ROTOR CONTROLS

109-0110-04-5 Sleeve, spherical 8290

109-0110-55-109 Swashplate - rotating part 23140

109-0110-05-5 Swashplate support 8290

28007GR90 Servo actuator support 15290

FUSELAGE

NAS626-20 Bolt, tail boom to fuselage(4 each)

600

109-0371-28-1 Support 4130

109-0200-02-93 Elevator, LH See note 3

109-0210-03-13 Fitting 15560

MAIN TRANSMISSION SUPPORTS

109-0325-03-5 Rod, aft 3200

109-0325-08-1 (only) Fitting, lower 3340

109-0402-27-113 Fitting, rod 1400

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AIRWORTHINESS LIMITATIONS SCHEDULE (Contd)


TAIL ROTOR (90°) GEARBOX

109-0435-31-1 Sleeve, mounting 10550

109-0445-08-7 Shaft 3740

NOTE 1: The retirement life for the following parts are applicable when the helicopter is equipped with tail rotorhub and grip assy P/N 109-8131-02-127 or tail rotor hub and blade assy P/N 109-8131-02-125. These partsmaintain the same retirement life even if promiscuously used on tail rotor hub and grip or tail rotor huband blade assemblies with a different Part Number than those specified above.

109-8131-07-1 Retention strap assembly 2000

109-8131-08-1 Strap pin 5000

109-8131-06-1 Strap plug 5000

109-0131-06-7 Hub assembly 3600

109-8131-09-1 Bolt, retention strap 5000

NOTE 2: After each flight comply with mandatory Bollettino Tecnico Telegrafico 109-8 Rev. A dated 8/9/91.

NOTE 3: Each 600 hours inspect the LH elevator for cracks. Ref. to Chapter 53.

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CHAPTER 05 - INSPECTION REQUIREMENTS AND

COMPONENT OVERHAUL SCHEDULE

TABLE OF CONTENTS

Sect/Para Page

05-00 GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-1

05-00-1. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-1

05-00-2. Inspection Programs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-1

05-00-3. Permissible Inspection Interval Tolerances . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-4

05-00-4. Glossary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-6

05-00-5. Abbreviations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-6

05-00-6. Division of the Text . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-7

05-10 COMPONENT OVERHAUL SCHEDULE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-9

05-20 SCHEDULED MAINTENANCE CHECKS - STANDARD INSPECTION PROGRAM . . . . 05-11

05-20-1. Airworthiness Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-11

05-20-2. 100 Hour/Annual Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-21

05-20-3. Standard 600 Hour Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-27

05-20-4. 2400 Hour Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-31

05-30 SCHEDULED MAINTENANCE CHECKS - EXTENDED INSPECTION PROGRAM . . . 05-35

05-30-1. Basic 25 Hour/30 Day inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-35

05-30-2. Standard 150 Hour/Annual Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-45

05-30-3. Standard 600 Hour Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-51

05-30-4. 2400 Hour Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-55

05-40 SCHEDULED MAINTENANCE CHECKS - PROGRESSIVE INSPECTION PROGRAM. 05-59

05-40-1. Basic 25 Hour/30 Day Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-59

05-40-2. Progressive 150 Hour/Annual Inspection Phase A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-69

05-40-3. Progressive 150 Hour/Annual Inspection Phase B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-71

05-40-4. Progressive 150 Hour/Annual Inspection Phase C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-73

05-40-5. Progressive 150 Hour/Annual Inspection Phase D . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-75

05-40-6. Progressive 150 Hour/Annual Inspection Phase E . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-77

05-40-7. Progressive 150 Hour/Annual Inspection Phase F . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-79

05-40-8. Progressive 600 Hour Inspection Phase 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-81

05-40-9. Progressive 600 Hour Inspection Phase 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-83

05-40-10. Progressive 600 Hour Inspection Phase 3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-85

05-40-11. Progressive 600 Hour Inspection Phase 4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-87

05-40-12. 2400 Hour Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-89

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Table of Contents - Continued

Sect/Para Page

05-50 UNSCHEDULED MAINTENANCE CHECKS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-93

05-50-1. Special Inspections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-93

05-50-2. Conditional Inspections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-103

05-60 OPTIONAL EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-111

05-70 LUBRICATION AND SERVICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-147

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LIST OF ILLUSTRATIONS

Figure Title Page

05-1 (Sheet 1 of 2). Inspection scheduling programs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-2

05-1 (Sheet 2 of 2). Inspection scheduling programs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 05-3

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SECTION 05-00

GENERAL

05-00-1. DESCRIPTIONThis Chapter contains the inspection requirements concerning the A109C helicopters equipped with ALLISON

250-C20R/1 engines, but does not contain inspection procedures. Such procedures will be found in the pertinent

Chapters of this manual.

The inspections are presented in typographic form suitable for the local reproduction in such a way as to be used

by personnel to perform helicopter inspections and to constitute, if desired, a data collection.

The inspections must be accomplished by qualified personnel to ascertain the airworthiness of the helicopter.

Eventual discrepancies must be eliminated before flight.

Prior to inspection, open or remove as necessary, fairings, cowlings panels and inspection doors.

Flight airworthiness must be determined by inspection of all parts to check the general condition, security of

attachment, cleanliness, freedom of movement and security, in accordance with the operational inspection rules

and instructions contained in the pertinent Chapters of this manual.

The airworthiness of the helicopter is determined by acceptance of all parts with quality standard aircraft practice

and specified instructions contained in the pertinent Chapters of this manual. Each inspected component must meet

pertinent and applicable Airworthiness Directives requirements.

For acceptance requirements and limits refer to the pertinent Chapters of this manual and/or Overhaul Manual.

NOTE : The inspection and maintenance of the engine, electronic equipment, instruments, etc. must be

performed in accordance with the instructions and procedures required by relevant manufacturers and in

accordance with approved maintenance schedule.

NOTE : The inspection and overhaul schedule requirements contained in this Chapter must not be exceeded

without explicit approval.

NOTE : When operating under particular environmental conditions (contaminated ambient, near the sea or

special missions) it is prerogative and responsibility of the operator to increase or intensify the

prescribed inspections as necessary to assure safe operation.

05-00-2. INSPECTION PROGRAMSThe operator may choose from three inspection programs, as indicated in Figure 05-1, designed to provide

flexibility for maximum utilization of the helicopter and to most suit the operator’s needs. The inspection

programs are identified as follows:

NOTE : For the inspection requirements concerning the optional equipment refer to Section 05-60.

1. Standard Inspection Program (refer to Section 05-20). The scheduled inspections consist of an airworthiness

check, 100 hour/annual inspection, standard 600 hour inspection and 2400 hour inspection.

2. Extended Inspection Program (refer to Section 05-30). The scheduled inspections consist of a basic 25

hour/30 day inspection, standard 150 hour/annual inspection, standard 600 hour inspection and a 2400 hour

Inspection.

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05-1

Figure 05-1 (sheet 1 of 2). Inspection scheduling programs.

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05-2

Figure 05-1 (sheet 2 of 2). Inspection scheduling programs.

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05-3

3. Progressive Inspection Program (refer to Section 05-40). The scheduled inspections consist of a basic 25

hour/30 day inspection, progressive 150 hour/annual inspection (divided into phases), progressive 600 hour

inspection (divided into phases) and a 2400 hour inspection.

The operator may decide to interrupt one program and revert to another provided the following is accomplished:

— Changing from standard to extended inspection program:

— Perform the 150 hour/annual hour inspection of the extended inspection program and continue withthe new program.

— Changing from standard to progressive inspection program:

— Perform basic 25 hour/30 day of the progressive program and the preceding cycle phases of theprogressive 150 hour/annual inspection and the progressive 600 hour inspection (if applicable).

— Changing from extended to standard inspection program:

— Perform 100 hour/annual inspection of the standard program and continue with the new program.

— Changing from extended to progressive inspection program:

— Perform preceding cycle phases of the progressive 150 hour/annual inspection and the progressive 600hour inspection (if applicable).

— Changing from progressive to standard inspection program:

— (Helicopter with less than 600 hours). Perform 100 hour/annual inspection and continue with the newprogram.

— (Helicopter above 600 hours). Perform standard 600 hour inspection of the standard program andcontinue with the new program.

— Changing from progressive to extended inspection program:

— (Helicopter with less than 600 hours). Perform 150 hour/annual inspection of the extended programand continue with new program.

— (Helicopter above 600 hours). Perform standard 600 hour inspection of the extended program andcontinue with the new program.

05-00-3. PERMISSIBLE INSPECTION INTERVAL TOLERANCES

In order to facilitate the inspection planning in accordance with the helicopter inspection schedule, the following

tolerances are permissible.

NOTE : Tolerances are not cumulative and they do not change the date at which the next inspection was

scheduled. A practical example, for those pertaining to the extended inspection program is shown below:

Standard 600 hour inspection : Accomplished at 615 hours.

Second standard 600 hour inspection : Accomplished at 1225 hours.

Third standard 600 hour inspection : Inspection is due at 1800 helicopter flight hours but shall

not exceed 1830 flight hours.

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05-4

SCHEDULED MAINTENANCE CHECKS

Standard inspection program

Inspection Tolerance

– Airworthiness check : None.

– 100 hour/annual : 10 hours/3 months.

– Standard 600 hour : 30 hours.

– 2400 hour : 50 hours.

Extended inspection program


– Basic 25 hour/30 day : 5 hours/5 days

– Standard 150 hour/annual : 10 hours/3 months.

– Standard 600 hour : 30 hours.

– 2400 hour : 50 hours.

Progressive inspection program


– Basic 25 hour/30 day : 5 hours/5 days

– Progressive 150 hour/annual : 10 hours/3 months.

– Progressive 600 hour : 30 hours

– 2400 hour : 50 hours

UNSCHEDULED MAINTENANCE CHECKS

Special inspections


– Prior to the first flight of the day : None

– Between 5 - 10 hours of flight (new aircraft or afterreinstallation of major components) : None

– At tire removal : None

– At doors removal/installation : None

– Each 75 hours : 5 hours



– Each 200 hours or 6 months : 10 hours/3 months

– Each 300 hours or 12 months : 10 hours/3 months

– Each 600 hours or 4 years : 30 hours/3 months


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– Each 2 years : 3 months



Lubrication and servicing

The tolerances (hours or calendar) are the same as for the applicable inspections with these exceptions:

Interval Tolerance

– 50 hours or 3 months : 5 hours/5 days

– 100 hours or 6 months : 10 hours/1 month

05-00-4. GLOSSARYFor a correct understanding of the inspection requirements contained in this Chapter, the meaning of the following

terms are defined:

DENT A point where the surface of a body is deformed by a concavity.

CONDITION Term used to determine if the item under examination presents external damage

which could jeopardize its safe operation.

DAMAGE Failure, malfunction, inconvenience. The term is always used to cover its most

extensive meaning.

DISTORTIONS Shape alteration. The term is always used to cover its most extensive meaning.

SECURED Term used to determine if the item under examination is correctly attached;

mainly referred to doors and disconnectable items.

CRACK A partial fracture of an item.

INSPECT Observe, examine.

SECURITY Term used to determine if the item under examination is connected to relative

attachment area.

WEAR Mechanical deterioration due to extensive use. The term is used to indicate

excessive consumption.

05-00-5. ABBREVIATIONSThe following list contains the abbreviations used in this Chapter.

ABBREVIATION MEANING

a.c. Alternating current

A.F.C.S. Automatic flight control system

A/F Airframe

d.c. Direct current

INST. Installation

LH Left hand

MFR Manufacturer

No. Number

P/N Part Number

RH Right hand

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05-00-6. DIVISION OF THE TEXTThis Chapter is divided into these sections:

SECTION 05-10 - Component Overhaul Schedule List of components with overhal interval.

SECTION 05-20-1 - Airworthiness Check Accomplish after the last flight of the day or prior to the firstflight of the following day.

SECTION 05-20-2 - 100 Hour/Annual Inspection Accomplish each 100 hours of flight operation or after 12calendar months, whichever comes first.

SECTION 05-20-3 - Standard 600 Hour Inspection Accomplish each 600 hours of flight operation.

SECTION 05-20-4 - 2400 Hour Inspection Accomplish each 2400 hours of flight operation.

SECTION 05-30-1 - Basic 25 Hour/30 Day Inspection Accomplish each 25 hours of flight operation or after 30calendar days, whichever comes first.

SECTION 05-30-2 - Standard 150 Hour/AnnualInspection

Accomplish each 150 hours of flight operation or after 12calendar months, whichever comes first.

SECTION 05-30-3 - Standard 600 Hour Inspection Accomplish each 600 hours of flight operation.


SECTION 05-40-1 - Basic 25 Hour/30 Day Inspection Accomplish each 25 hours of flight operation or after 30calendar days, whichever comes first.

SECTION 05-40-2 thru -7 - Progressive 150 Hour/Annual Inspection

Six separate phases at 25 hour or 60 calendar days intervals,whichever comes first.

SECTION 05-40-8 thru -11 - Progressive 600 HourInspection

Four separate phases at 150 hour intervals.


SECTION 05-50-1 - Special Inspections Systems or components requiring attention at other than sched-uled time intervals.

SECTION 05-50-2 - Conditional Inspections These inspections must be accomplished as a result of anunusual event occurred during operations (for example afterhard landing, overspeed, etc.).

SECTION 05-60 - Optional Equipment These optional equipment inspections shall be performed onlyif applicable, at prescribed intervals.

SECTION 05-70 - Lubrication and Servicing List of items which require lubrication and servicing.

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SECTION 05-10

COMPONENT OVERHAUL SCHEDULE

The following schedule summarizes, in tabular form, the A109C helicopter components to be submitted to

overhaul, and relevant overhaul intervals.

NOTE : The overhaul interval specified for any given part number contained in this overhaul schedule applies

to indicated and all successive dash numbers.

Part Number Denomination Overhaul interval(Hours)

109-0619-15-11 Blower and cooler assy 1200 (1)

109-0620-66-101 Blower assy 1200 (2)

109-0101-01-115 Main rotor hub assy 4200

109-0101-06-1 • Damper 2400

109-0400-02-107 Main transmission assy 4800

109-0400-03-105 Main transmission assy 4800

109-0440-01-115 Tail rotor (90°) gearbox assy 3600

109-8131-02-115 Tail rotor hub and blade assy 4800

109-0110-42-4/-5/-6 Main rotor servo actuator assy 3600

109-0760-37-1 (only) Self-regulating pump assy 900 (3)

109-0611-53-1 Fuel pump 600 (4)

150SG117Q Starter generator 1000

8585C000 Heat exchanger 3000 (5)

1538D000-002 or1538D000-003

Cooling Turbine 5000 (5)

(1) Only for blower and cooler assy P/N Microtecnica C126171 or C126171 Mod. A.

(2) Only for blower assy P/N Microtecnica C135169-1.

(3) Only the self-regulating pump assy P/N 109-0760-37-1 identified with P/N Magnaghi 0-8077 are subjectto 900 hours overhaul interval.

(4) The 600 hours overhaul interval is applicable to fuel boost pumps assy P/N Mona SM2232 only.

(5) Send to Manufacturer.

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05-10

SECTION 05-20

SCHEDULED MAINTENANCE CHECKS –

STANDARD INSPECTION PROGRAM

05-20-1. AIRWORTHINESS CHECK

AREA No. 1 : Helicopter nose

AREA No. 2 : Fuselage - RH side

AREA No. 3 : Tail boom - RH side

AREA No. 4 : Fins, 90° gearbox, tail rotor, tail skid

AREA No. 5 : Tail boom - LH side

AREA No. 6 : Fuselage - LH side

AREA No. 7 : Cabin interior

Date .................................................

Signature ........................................

Helicopter Registration No. ..........

Helicopter Hours ...........................

INITIAL EACH ITEM AFTER ACCOMPLISHMENT INITIAL

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GENERAL

1. Verify the following:

a. Check log book for recorded discrepancies. Correct any fault that could affectsafety of operations. . . . . . . . . . . . . . . .

b. Expiry of components’ retirement life in accordance with Chapter 04. . . . . . . . . . . . . . . .

c. Components’ overhaul interval in accordance with Section 05-10. . . . . . . . . . . . . . . .

d. Servicing and lubrication in accordance with Section 05-70. . . . . . . . . . . . . . . .

e. Perform applicable optional equipment inspections in accordance with Section05-60. . . . . . . . . . . . . . . .

f. Other inspection requirements. . . . . . . . . . . . . . . .

2. Open cowlings, fairings and inspection doors as necessary. . . . . . . . . . . . . . . .

AREA N° 1 (HELICOPTER NOSE)

1. Nose exterior for cracks, dents, missing and/or loose rivets and screws. . . . . . . . . . . . . . . .

2. Nose air intake for obstructions. . . . . . . . . . . . . . . .

3. External power receptacle for condition and arcing. . . . . . . . . . . . . . . .

4. Nose shock strut for condition, leaks and correct extension. . . . . . . . . . . . . . . .

5. Visually inspect for cracks the nose landing gear strut mount upper portion along itswhole circumference. Also inspect the strut mount in the L.G. mount hornsattachment area to fuselage structure. . . . . . . . . . . . . . . .

6. Nose landing gear wheel for condition, security, tire pressure (visually check) andtire-wheel slippage marks. . . . . . . . . . . . . . . .

7. Nose landing gear doors and relative mechanism for condition and security. . . . . . . . . . . . . . . .

8. Nose compartment access doors for condition, security and correct closure. . . . . . . . . . . . . . . .

9. Nose compartment components for condition and security. . . . . . . . . . . . . . . .

10. Landing lights for condition. . . . . . . . . . . . . . . .

11. Battery for condition and security. Vent lines for condition. . . . . . . . . . . . . . . .

12. Battery quick-release connector for condition and security. . . . . . . . . . . . . . . .

13. Battery temperature sensor connector for security. . . . . . . . . . . . . . . .

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05-12

STANDARD INSPECTION PROGRAM (AIRWORTHINESS CHECK)


14. Accumulators, lines and accessories (visible parts) for condition, security and leaks;discharge by pressing relevant red buttons. . . . . . . . . . . . . . . .

NOTE: Discharging accumulators leads to loss of brake power. Take suitablemeasures.

AREA N° 2 (FUSELAGE - RH SIDE)

1. Windshield and roof transparent panel for condition and cleanliness. . . . . . . . . . . . . . . .

2. External air temperature probe for condition and security. . . . . . . . . . . . . . . .

3. Pitot tube for condition, security and obstructions. . . . . . . . . . . . . . . .

4. Fuselage exterior for cracks, dents, missing and/or loose rivets and screws. . . . . . . . . . . . . . . .

5. Cowlings, fairings and access doors for condition and security. . . . . . . . . . . . . . . .

6. Scoop air intake for foreign matter. . . . . . . . . . . . . . . .

7. Flight controls, levers and supports for condition and security. . . . . . . . . . . . . . . .

8. A.F.C.S. actuators for unusual play, condition and security; electrical connectionsfor condition and security. . . . . . . . . . . . . . . .

9. Servo hydraulic system valves and filters group and visible lines for condition,security and leaks. . . . . . . . . . . . . . . .

10. Hydraulic filters for by-pass indication (red button out: filter clogged). . . . . . . . . . . . . . . .

11. Hydraulic system reservoirs for proper oil level and security of filler caps. Checkreturn line for security. . . . . . . . . . . . . . . .

12. Main rotor hub and blades (2 places) for condition. . . . . . . . . . . . . . . .

13. Main rotor hub cover for condition and security. . . . . . . . . . . . . . . .

14. Main rotor reservoirs (2 places) for correct oil level. Flap and drag hinges and linesfor leaks. . . . . . . . . . . . . . . .

15. Main rotor grips (2 places) for condition and leaks of lubricant. . . . . . . . . . . . . . . .

16. Main rotor flap restrainers and springs (2 places) for condition; upper flap restrainer(yellow spring) for freedom of movement. . . . . . . . . . . . . . . .

17. Main rotor dampers (2 places) for condition, security and correct extension ofcharge indication pin. . . . . . . . . . . . . . . .

18. Main rotor pitch change links (2 places) for condition, security and unusual play. . . . . . . . . . . . . . . .

19. Swashplate boots for condition. . . . . . . . . . . . . . . .

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20. Anticollision light for condition and security. . . . . . . . . . . . . . . .

21. Servo actuator (1 place) for condition, security and leaks. Inspect main rotor servoactuator bleed holes for leaks. . . . . . . . . . . . . . . .

22. Main transmission and accessories for condition, security and leaks of lubricant. . . . . . . . . . . . . . . .

23. Hydraulic pump for leaks. . . . . . . . . . . . . . . .

24. Transmission external oil filter for by-pass indication (white button out: filter clogged). . . . . . . . . . . . . . . .

25. Air intake screen for foreign matter and integrity. . . . . . . . . . . . . . . .

26. Air intake plenum chamber for presence of water; drain holes for obstructions. . . . . . . . . . . . . . . .

27. Air intake plenum chamber and duct for condition, foreign matter, damage and looseattaching hardware. . . . . . . . . . . . . . . .

28. Starter-generator for security. Electrical connections for arcing and/or shortcircuit evidence. . . . . . . . . . . . . . . .

29. Airframe (A/F) fuel filter and compartment for condition, leaks and security. . . . . . . . . . . . . . . .

30. Fuel tank sump cover for condition. Drain sump. . . . . . . . . . . . . . . .

31. Fuel system drain lines and valves for leaks. . . . . . . . . . . . . . . .

32. Drain and vent lines for condition and obstructions. . . . . . . . . . . . . . . .

33. Main landing gear shock strut for condition, leaks and correct extension. . . . . . . . . . . . . . . .

34. Main landing gear side brace for cracks in the visible areas at connection of theshock strut. Ref. to para 32-10-16. . . . . . . . . . . . . . . .

35. Wheel brake for leaks. . . . . . . . . . . . . . . .

36. Main landing gear wheel for condition, security, tire pressure (visually check) andtire-wheel slippage marks. . . . . . . . . . . . . . . .

37. Landing gear bay for leaks and cleanliness; components for condition and security. . . . . . . . . . . . . . . .

38. Fuel filler cap for condition and security. . . . . . . . . . . . . . . .

39. Engine areas for leaks of fuel and/or oil. . . . . . . . . . . . . . . .

40. Accessible wiring and accessories for loose connections and condition. . . . . . . . . . . . . . . .

41. Engine mounts for condition and security. . . . . . . . . . . . . . . .

42. Engine to transmission drive shaft (visible part) for condition. . . . . . . . . . . . . . . .

43. Engine exhaust ducts for condition and security. . . . . . . . . . . . . . . .

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44. Engine to blower drive shaft for condition, security and freedom of axial movement. . . . . . . . . . . . . . . .

45. Blower for condition. . . . . . . . . . . . . . . .

46. Blower supports for condition in particular adjacent to attachment areas. . . . . . . . . . . . . . . .

47. Cooler rear end for foreign matter. . . . . . . . . . . . . . . .

48. Engine auxiliary oil filter for by-pass indication (button out: filter clogged). . . . . . . . . . . . . . . .

AREA N° 3 (TAIL BOOM - RH SIDE)

1. Tail boom exterior (particularly tail boom to fuselage attachment areas) for cracks,dents, missing and/or loose rivets and screws. . . . . . . . . . . . . . . .

2. Anticollision light for condition and security. . . . . . . . . . . . . . . .

3. Antennas for condition and security. . . . . . . . . . . . . . . .

4. Synchronized elevator for condition, unusual play and security. . . . . . . . . . . . . . . .

5. Navigation light for condition and security. . . . . . . . . . . . . . . .

AREA N° 4 (FINS, 90° GEARBOX, TAIL ROTOR AND TAILSKID)

1. Exterior (particularly lower fin and tail skid attachment areas) for cracks, dents,missing and/or loose rivets and screws. . . . . . . . . . . . . . . .

2. Tail rotor long shaft bearing for unusual play and grease leakage. Rubber collar forcondition and integrity. . . . . . . . . . . . . . . .

3. Tail rotor long drive shaft bearing for integrity of slippage marks betweenshaft-collar-bearing and between bearing-hanger. . . . . . . . . . . . . . . .

4. Tail rotor (90°) gearbox for condition, security, oil leaks and correct oil level. . . . . . . . . . . . . . . .

5. Access panels for condition and security. . . . . . . . . . . . . . . .


7. Tail rotor hub and blades for condition, contamination of oil/grease, security andfreedom of flapping. Flap stop bumpers and boots for condition. . . . . . . . . . . . . . . .

8. Tail rotor pitch change mechanism for condition, security and unusual play. . . . . . . . . . . . . . . .

AREA N° 5 (TAIL BOOM - LH SIDE)

1. Tail boom exterior (particularly tail boom to fuselage attachment areas) for dents,missing and/or loose rivets and screws. . . . . . . . . . . . . . . .

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05-15






5. Tail rotor long drive shaft for condition and security, bearings for unusual play andgrease leakage. . . . . . . . . . . . . . . .

6. Rubber collars for condition and integrity. . . . . . . . . . . . . . . .

7. Tail rotor drive shaft bearings for integrity of slippage marks between shaft-collar-bearing and between bearing-hanger. . . . . . . . . . . . . . . .

AREA N° 6 (FUSELAGE - LH SIDE)




4. Cowlings, fairings and access doors for condition and security. . . . . . . . . . . . . . . .

5. Tail rotor middle drive shaft for condition and security, bearings for unusual playand grease leakage. Rubber collars for condition and integrity. . . . . . . . . . . . . . . .

6. Tail rotor drive shaft bearings for integrity of slippage marks between shaft-collar-bearing and between bearing-hanger. . . . . . . . . . . . . . . .

7. Cooler rear end for foreign matter. . . . . . . . . . . . . . . .


9. Blower for condition. . . . . . . . . . . . . . . .

10. Engine to blower drive shaft for condition, security and freedom of axial movement. . . . . . . . . . . . . . . .





15. Starter-generator for security. Electrical connections for arcing and/or shortcircuitevidence. . . . . . . . . . . . . . . .

16. Engine to transmission drive shaft (visible part) for condition. . . . . . . . . . . . . . . .

17. Baggage compartment for cleanliness and cargo (if on board) properly secured. . . . . . . . . . . . . . . .

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18. Baggage compartment access door for condition, security and correct operation. . . . . . . . . . . . . . . .



21. Wheel brake for leaks. . . . . . . . . . . . . . . .

22. Main landing gear wheel for condition, security, tire pressure (visually check) andtire-wheel slippage marks. . . . . . . . . . . . . . . .




26. Main rotor hub and blades (2 places) for condition. . . . . . . . . . . . . . . .

27. Main rotor reservoirs (2 places) for correct oil level. Flap and drag hinges and linesfor leaks. . . . . . . . . . . . . . . .





32. Swashplate and rotating scissors for condition, security and unusual play. . . . . . . . . . . . . . . .

33. Swashplate boots for condition. . . . . . . . . . . . . . . .

34. Main rotor servo actuators (2 places) for condition, security and leaks. Inspect mainrotor servo actuators bleed holes for leaks. . . . . . . . . . . . . . . .



37. Transmission oil for proper level and filler cap for security. . . . . . . . . . . . . . . .

NOTE: If rotor brake has been used, the oil level indication could be lower thanactual level. Ref. to para 12-10-19.

38. Engine oil tanks for proper oil level and filler caps secured. . . . . . . . . . . . . . . .


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40. Air intake plenum chamber for presence of water; drain holes for obstructions. . . . . . . . . . . . . . . .

41. Air intake plenum chamber and duct for condition, foreign matter, damage and looseattaching hardware. . . . . . . . . . . . . . . .




45. Roof transparent panel and windshield for condition and cleanliness. . . . . . . . . . . . . . . .

AREA N° 7 (CABIN INTERIOR)

1. Passenger doors for damage, security and correct operation of locking mechanism. . . . . . . . . . . . . . . .

2. Passenger doors jettison handles for correct position. . . . . . . . . . . . . . . .

3. Safety belts for condition. Release mechanism for operation. . . . . . . . . . . . . . . .

4. Passenger seats for condition and security. . . . . . . . . . . . . . . .

5. Cabin interior for condition. . . . . . . . . . . . . . . .

6. Portable fire extinguisher (if installed) for security and correct charge. . . . . . . . . . . . . . . .

7. Survival equipment (if installed) for condition and security. . . . . . . . . . . . . . . .

8. Check that first aid kit is on-board. . . . . . . . . . . . . . . .

9. Copilot door for damage, security and correct operation. . . . . . . . . . . . . . . .

10. Copilot door jettison handle and relevant safety latch for correct position. . . . . . . . . . . . . . . .

11. Safety belt for condition. Release mechanism for correct operation. . . . . . . . . . . . . . . .

12. Copilot seat for condition and security. . . . . . . . . . . . . . . .

13. Power levers for freedom of movement; leave in OFF position. . . . . . . . . . . . . . . .

14. Check that landing gear lock lever is in the NORMAL position and lockwired. . . . . . . . . . . . . . . .

15. Copilot cyclic, collective and pedals for security (if installed). . . . . . . . . . . . . . . .

16. Lower transparent panel for condition and cleanliness. . . . . . . . . . . . . . . .

17. Pilot door for damage, security and correct operation. . . . . . . . . . . . . . . .

18. Pilot door jettison handle and relevant safety latch for correct position. . . . . . . . . . . . . . . .

19. Pilot safety belt for condition. Release mechanism for correct operation. . . . . . . . . . . . . . . .

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05-18



20. Pilot seat for condition and security. . . . . . . . . . . . . . . .

21. Pilot cyclic, collective and pedals for security. . . . . . . . . . . . . . . .

22. Lower transparent panel for condition and cleanliness. . . . . . . . . . . . . . . .

23. Overhead console for security . . . . . . . . . . . . . . .

24. Magnetic compass(es) for level of fluid. Correction card(s) for legibility. . . . . . . . . . . . . . . .

25. Instruments for condition and security. . . . . . . . . . . . . . . .

26. Accumulators for proper nitrogen precharge value on gages. . . . . . . . . . . . . . . .

For the following checks connect the d.c. supply.

27. Drain LH airframe (A/F) fuel filter while respective fuel pumps are operating. . . . . . . . . . . . . . . .

28. Check LH airframe (A/F) fuel filter by-pass indication by pushing red button onfilter. . . . . . . . . . . . . . . .

29. Drain RH airframe (A/F) fuel filter while respective fuel pumps are operating. . . . . . . . . . . . . . . .

30. Check RH airframe (A/F) fuel filter by-pass indication by pushing red button onfilter. . . . . . . . . . . . . . . .

31. Check following systems for correct operation:

a. Warning, caution and advisory light panel light segments. . . . . . . . . . . . . . . .

b. Voice warning system. . . . . . . . . . . . . . . .

c. Accumulator charging lights. . . . . . . . . . . . . . . .

d. Landing gear indicator lights. . . . . . . . . . . . . . . .

e. Inverters. . . . . . . . . . . . . . . .

f. Fuel system: pumps, shut-off and crossfeed valves for correct operation andpressures. . . . . . . . . . . . . . . .

g. Fuel quantity indication. . . . . . . . . . . . . . . .

h. Instrument and cabin lights. . . . . . . . . . . . . . . .

i. SAS 1 & 2 and ATTD HOLD control panel (for the time strictly necessary tocarry out check) (if installed). . . . . . . . . . . . . . . .

j. Torque matching control system. . . . . . . . . . . . . . . .

k. Magnetic brakes. . . . . . . . . . . . . . . .

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05-19



l. Fire detection system. . . . . . . . . . . . . . . .

m. Communication and navigational systems (self-test, only for systems providedwith this feature). . . . . . . . . . . . . . . .

n. Radio altimeter self-test (if installed). . . . . . . . . . . . . . . .

o. N1/TOT indicators self-test. . . . . . . . . . . . . . . .

p. N2/NR control system. . . . . . . . . . . . . . . .

q. Navigation and anticollision lights. . . . . . . . . . . . . . . .

r. Landing lights. . . . . . . . . . . . . . . .

Disconnect the d.c. electrical supply.

A109C-MPM

05-20-00

05-20



05-20-2. 100 HOUR/ANNUAL INSPECTION

1. GENERAL

a. Perform complete airworthiness check (para 05-20-1) in addition to thefollowing 100 hour/annual inspection. . . . . . . . . . . . . . . .

b. Verify the following:

1) Expiry of components’ retirement life in accordance with Chapter 04. . . . . . . . . . . . . . . .

2) Components’ overhaul interval in accordance with Section 05-10. . . . . . . . . . . . . . . .

3) Servicing and lubrication in accordance with Section 05-70. . . . . . . . . . . . . . . .

4) Perform applicable optional equipment inspections in accordance withSection 05-60. . . . . . . . . . . . . . . .

5) Other inspection requirements. . . . . . . . . . . . . . . .

2. MAIN ROTOR

a. Main rotor blades for condition, voids, swelling and cracks particularly nearroot end, trim tab, tip cap and trailing edge. Ref. to para 62-10-6 thru 62-10-23. . . . . . . . . . . . . . . .

b. Pitch change links for excessive play. Ref. to para 62-30-7. . . . . . . . . . . . . . . .

c. Flap restrainers and springs for security and freedom of movement. Inspectsprings place and springs for condition. . . . . . . . . . . . . . . .

3. MAIN ROTOR CONTROLS

a. Rotating scissors for excessive play. Ref. to para 62-30-8. . . . . . . . . . . . . . . .

b. Non-rotating scissors for abnormal play. . . . . . . . . . . . . . . .

Date .................................................

Signature ........................................




A109C-MPM

05-20-00

05-21

4. MAIN TRANSMISSION

a. Perform operational test of chip detectors circuit on coupling case and uppercase. Ref. to para 63-40-15. . . . . . . . . . . . . . . .

b. Upper case to main case attachment nuts for correct torque (towards highvalue). Ref. to para 63-21-19. . . . . . . . . . . . . . . .

5. FLIGHT CONTROLS

a. Check the following components for condition, clearances, security andbearings for abnormal play:

1) Control tubes. . . . . . . . . . . . . . . .

2) Bellcranks. . . . . . . . . . . . . . . .

3) Supports. . . . . . . . . . . . . . . .

b. A.F.C.S. actuators on roof deck; check slippage marks between body and shaft. . . . . . . . . . . . . . . .

c. Tail rotor servo actuator for condition, security and leaks. . . . . . . . . . . . . . . .

d. Main rotor servo actuators upper rod-end bearing for excessive play and lowerspherical bearing for looseness. Ref. to para 67-30-8. . . . . . . . . . . . . . . .

e. Flight controls for freedom of movement. . . . . . . . . . . . . . . .

6. SERVO HYDRAULIC SYSTEM

a. Flexible tubes for condition and chafing. . . . . . . . . . . . . . . .

7. UTILITY HYDRAULIC SYSTEM

a. Emergency utility hydraulic system for correct charge seal. Ref. to para29-20-11A. . . . . . . . . . . . . . . .

8. POWER PLANT, OIL COOLER BLOWERS AND TAILROTOR DRIVE SHAFTS

a. Engine-blower and tail rotor drive shafts splined adapters for excessive radialplay. . . . . . . . . . . . . . . .

b. Engine-blower and tail rotor drive shafts Thomas couplings for condition andcracks of visible surfaces. . . . . . . . . . . . . . . .

c. Tail rotor middle and long drive shafts for nicks, scorings, corrosion andsecurity. Ref. to para 65-10-9. . . . . . . . . . . . . . . .

d. Check forward shaft for axial freedom of movement. . . . . . . . . . . . . . . .

A109C-MPM

05-20-00

05-22

STANDARD INSPECTION PROGRAM (100 HOUR/ANNUAL INSPECTION)


e. Tail rotor drive shaft bearings for integrity of slippage marks betweenshaft-collar-bearing and between bearing-hanger. Inspect bearings externally onboth sides and seals for damage and wrinklings. . . . . . . . . . . . . . . .

f. Tail rotor drive shaft fittings safety pins for freedom of rotation. If shaft pin istight refer to para 65-10-9. . . . . . . . . . . . . . . .

g. Engine mounts for condition and security especially in structure attachmentarea for cracks and distortions. . . . . . . . . . . . . . . .

h. Blower shafts for freedom of rotation. . . . . . . . . . . . . . . .

i. Blower support group for damage. Impeller for damage and evidence of chafingon blade tips. . . . . . . . . . . . . . . .

j. Oil coolers for leaks, condition and security. . . . . . . . . . . . . . . .

k. Fuel and oil flexible tubes for condition and chafing. . . . . . . . . . . . . . . .

l. Tubes and electrical wiring for condition, chafing, leaks and security ofconnections. . . . . . . . . . . . . . . .

9. LANDING GEAR

a. Nose and main landing gear uplocks for condition, security and integrity ofretaining spring. . . . . . . . . . . . . . . .

b. Nose landing gear actuator bracket to structure attachment bolts for correcttorque. Ref. to para 32-30-23. . . . . . . . . . . . . . . .

c. Main landing gear fittings and surrounding area for cracks, distortions andsecurity. . . . . . . . . . . . . . . .

10. FUSELAGE

a. Visible electrical and electronic component supports for condition and security. . . . . . . . . . . . . . . .

b. Fuselage exterior for corrosion and distortions. . . . . . . . . . . . . . . .

c. Fuselage internal area, particularly area surrounding the attachment points oftail boom for cracks, corrosion and distortions. . . . . . . . . . . . . . . .

d. Service steps and wire ropes for condition, security and integrity. . . . . . . . . . . . . . . .

e. Components between main landing gear bay for condition and security. . . . . . . . . . . . . . . .

f. I.V.S.I static ports for obstructions (IFR only). . . . . . . . . . . . . . . .

g. Drain flight director lines (IFR only). . . . . . . . . . . . . . . .

h. Drain pitot static and dynamic lines. . . . . . . . . . . . . . . .

A109C-MPM

05-20-00

05-23



11. TAIL BOOM

a. Tail boom exterior for corrosion and distortions. . . . . . . . . . . . . . . .

b. Tail boom internal area surrounding the attachment points and relative bracketsto the fuselage for cracks, corrosion and distortions. Ref. to para 53-20-6. . . . . . . . . . . . . . . .

c. Tail boom internal area, synchronized elevator attachment area for security andcracks. Surrounding areas for distortions, cracks and defective and/or missingrivets. . . . . . . . . . . . . . . .

d. Lower fin for condition, security, cracks and defective and/or missing rivets. . . . . . . . . . . . . . . .

e. Tail skid for wear. Inspect tail skid attachment area to lower fin for cracks anddamage. . . . . . . . . . . . . . . .

12. CABIN INTERIOR AND EXTERIOR

a. Remove pilot and passenger doors and inspect jettison mechanism for correctoperation. Ref. to para 52-10-16. . . . . . . . . . . . . . . .

b. Emergency equipment for inspection due dates and expiry. . . . . . . . . . . . . . . .

c. Survival equipment (if installed) for inspection due dates and expiry. . . . . . . . . . . . . . . .

13. TAIL ROTOR (90°) GEARBOX

a. Perform operational test of chip detector circuit. Ref. to para 65-40-6. . . . . . . . . . . . . . . .

b. Tail rotor (90°) gearbox mounting sleeve and surrounding area on tail boomfinal rib for cracks, loose rivets and security. . . . . . . . . . . . . . . .

14. TAIL ROTOR

a. Tail rotor blades for:

1) Scratches, dents, cracks, corrosion and loss of paint. Ref. to para 64-10-6. . . . . . . . . . . . . . . .

2) Voids. Ref. to para 64-10-7. . . . . . . . . . . . . . . .

b. Tail rotor hub for unusual play along flap and pitch axes. . . . . . . . . . . . . . . .

c. Pitch change mechanism bolts connecting links, levers, scissors for wear andexcessive play. . . . . . . . . . . . . . . .

d. Slider bushings for wear. Ref. to para 64-30-5. . . . . . . . . . . . . . . .

e. Sleeve of pitch change mechanism for fretting and/or wear to splines of bushingP/N 109-0133-06-101 and of shaft. Ref. to para 64-30-5. . . . . . . . . . . . . . . .

A109C-MPM

05-20-00

05-24



f. Duplex bearing P/N 109-0133-05-101 of the pitch change mechanism forfreedom of rotation. Ref. to para 64-30-6. . . . . . . . . . . . . . . .

g. Both P/N AN174-14 that connect the two links and the pitch control lever to thehousing of the pitch change mechanism for damage. Ref. to para 64-30-6. . . . . . . . . . . . . . . .

h. Tail rotor hub trunnion covers for cracks (visual inspection, removal notnecessary). . . . . . . . . . . . . . . .

15. COWLINGS

a. Engine-transmission cowlings for cracks and defective and/or missing rivets. . . . . . . . . . . . . . . .

16. ELECTRICAL SYSTEM AND INSTRUMENTS

a. Inverters for security and connections. . . . . . . . . . . . . . . .

b. Generator control boxes and terminals for damage and security. . . . . . . . . . . . . . . .

c. Relays and busses for security and connections. . . . . . . . . . . . . . . .

d. Busses insulation for condition. . . . . . . . . . . . . . . .

e. Remove and recondition the battery. Ref. to para 24-30-17. . . . . . . . . . . . . . . .

f. Perform operational test of d.c. electrical system. Ref. to para 24-30-11. . . . . . . . . . . . . . . .

g. Perform operational test of a.c. electrical system. Ref. to para 24-20-6. . . . . . . . . . . . . . . .

A109C-MPM

05-20-00

05-25




A109C-MPM

05-20-00

05-26

05-20-3. STANDARD 600 HOUR INSPECTION

1. GENERAL

a. Perform complete airworthiness check (para 05-20-1) and 100 hour/annualinspection (para 05-20-2) in addition to the following standard 600 hourinspection. . . . . . . . . . . . . . . .







2. MAIN ROTOR

a. Remove dampers and inspect dampers bushings and pins attaching dampers forwear. Ref. to para 62-20-19. . . . . . . . . . . . . . . .

b. Remove pitch change links and inspect end bearings for excessive play. Ref. topara 62-30-9. . . . . . . . . . . . . . . .

c. Spring holder half-plates for wear. Ref. to para 62-20-25. . . . . . . . . . . . . . . .

d. Flap restrainer strikers for damage. . . . . . . . . . . . . . . .


a. Disconnect pitch change links and rotating scissors. Inspect swashplate duplexbearing for roughness, noise and smoothness of rotation. Ref. to para 62-30-17. . . . . . . . . . . . . . . .

Date .................................................

Signature ........................................




A109C-MPM

05-20-00

05-27

4. FLIGHT CONTROLS

a. Lower spherical bearing of main rotor servo actuators for freedom of movementand correct rotation friction value. Ref. to para 67-30-8. . . . . . . . . . . . . . . .

b. Upper rod-end bearing of main rotor servo actuators for radial play. Ref. to para67-30-8. . . . . . . . . . . . . . . .

c. Levers of main and tail rotor servo actuators; protect with proper compound.Ref. to para 67-30-16.

d. Two half-bodies of main rotor servo actuators for correct torque. Ref. to para67-30-9. . . . . . . . . . . . . . . .

5. FUEL SYSTEM (EXCEPT PUMPS SECONDO MONA MFRP/N SM 2232 AND GLOBE MFR P/N 164A298)

a. Pump brushes for wear. Ref. to para 28-20-14. . . . . . . . . . . . . . . .


a. Perform functional test of low level switch in N°2 servo hydraulic system tank.Ref. to para 29-20-11. . . . . . . . . . . . . . . .

7. LANDING GEAR

a. Main landing gear actuator attachment bolts for correct torque. Ref. to para 32-30-15. . . . . . . . . . . . . . . .

b. Main landing gear fittings and relative stiffening struts attachment bolts forcorrect torque. Ref. to para 32-10-9. . . . . . . . . . . . . . . .

c. Externally inspect nose landing gear shock strut for corrosion, condition anddamage. . . . . . . . . . . . . . . .

d. (Perform at 1200 hours of operation only and subsequently each 600 hours).Inspect mount upper portion of nose landing gear shock strut, using the EDDYCURRENT method, for cracks. Ref. to para 32-20-12. . . . . . . . . . . . . . . .

8. TAIL ROTOR

a. Grip bushings and relative hub contact area for condition, fretting and wear.Ref. to para 64-20-5. . . . . . . . . . . . . . . .

b. Sleeve of pitch change mechanism for wear. Ref. to para 64-30-5. . . . . . . . . . . . . . . .

c. Pitch change mechanism scissor bushings for wear. Ref. to para 64-30-5. . . . . . . . . . . . . . . .

d. Pitch change mechanism for corrosion. . . . . . . . . . . . . . . .

A109C-MPM

05-20-00

05-28

STANDARD INSPECTION PROGRAM (STANDARD 600 HOUR INSPECTION)


e. Duplex bearing P/N 109-0133-05-101 of the pitch change mechanism forfreedom of rotation and greasing. Ref. to para 64-30-7. . . . . . . . . . . . . . . .

f. Inspect bolt P/N 109-8131-09-1 of retention strap for condition, corrosion andwear. Refer to para 64-20-5. . . . . . . . . . . . . . . .

g. Inspect pin P/N 109-8131-08-1 of retention strap for condition, corrosion andwear. Refer to para 64-20-5. . . . . . . . . . . . . . . .

9. ENGINE AUXILIARY OIL FILTER

a. Remove and inspect filter outlet strainer (if installed). Ref. to para 79-20-12. . . . . . . . . . . . . . . .

b. Perform functional test of by-pass line. Ref. to para 79-20-6A. . . . . . . . . . . . . . . .

A109C-MPM

05-20-00

05-29

STANDARD INSPECTION PROGRAM (STANDARD 600 HOUR INSPECTION)



A109C-MPM

05-20-00

05-30

05-20-4. 2400 HOUR INSPECTION

1. GENERAL

a. Perform complete airworthiness check (para 05-20-1), 100 hour/annual inspec-tion (para 05-20-2) and standard 600 hour inspection (para 05-20-3) in additionto the following 2400 hour inspection. . . . . . . . . . . . . . . .







2. MAIN ROTOR

a. Inspect flapping restrainers for wear on bushings. Ref. to para 62-20-23. . . . . . . . . . . . . . . .

b. Remove and inspect drag hinge bearings for damage and corrosion. Ref. to para62-20-10A. . . . . . . . . . . . . . . .

c. Remove and inspect flap hinge bearings for damage and corrosion. Ref. to para62-20-10B. . . . . . . . . . . . . . . .

d. Inspect flexible hoses for damage and oil reservoirs for condition. . . . . . . . . . . . . . . .

e. Inspect retention straps for damage on the polyurethane skin and for conditionof seats for retaining pins. Inspect pins and retaining fittings for corrosion, wearand damage. Ref. to para 62-20-14. . . . . . . . . . . . . . . .

Date .................................................

Signature ........................................




A109C-MPM

05-20-00

05-31


a. Inspect Gleason crown and pignon teeth for abnormal patterns, pitting, scoringand damage. Ref. to para 63-21-16. . . . . . . . . . . . . . . .

b. Inspect coupling gearbox gears for abnormal patterns, pitting, scoring anddamage. Ref. to para 63-21-16. . . . . . . . . . . . . . . .

c. Inspect main rotor brake coupling flange, on transmission tail rotor drive quill,for wear and condition. Ref. to para 63-21-46. . . . . . . . . . . . . . . .

d. Inspect mating surfaces between upper case and mast assembly and ring gearand between ring gear and main case for fretting, corrosion and damage. Ref.to para 63-21-16. . . . . . . . . . . . . . . .

e. Inspect upper case and mast assembly for corrosion and damage. Ref. to para63-21-16. . . . . . . . . . . . . . . .

4. FLIGHT CONTROLS

a. Flight control supports, levers and rods for damage, corrosion, freedom ofmovement and unusual play. . . . . . . . . . . . . . . .

5. FUSELAGE

a. Fuselage for general condition, distortions, nicks, scratches, corrosion, defec-tive and/or missing rivets particularly in area surrounding attachment points ofmain transmission, transmission supports, engine mounts, blower supports, tailboom and landing gear. . . . . . . . . . . . . . . .

b. Cowlings, doors and access panels, service steps for condition, cracks,distortions, defective and/or missing rivets and correct hinge operation. . . . . . . . . . . . . . . .

c. Check fuselage attachment holes with tail boom for corrosion, wear andelongation. Ref. to para 53-10-8. . . . . . . . . . . . . . . .

d. Check transmission antitorque plate and deck structure attachment holes forcorrosion, wear and elongation. Ref. to para 63-21-15. . . . . . . . . . . . . . . .

e. Check engine mount supports for corrosion, wear and elongation of holes. Ref.to para 71-20-6. . . . . . . . . . . . . . . .

f. Check attachment pin between engine fittings and engine mounts for wear. . . . . . . . . . . . . . . .

g. Landing gear doors for cracks, distortions, defective and/or missing rivets,retraction/extension supports and rods for correct movement, corrosion, dentsand damage. . . . . . . . . . . . . . . .

h. Landing gear fittings and retraction/extension mechanism components (sidebrace, V-strut) for correct movement, corrosion, dents and unusual play. . . . . . . . . . . . . . . .

A109C-MPM

05-20-00

05-32

STANDARD INSPECTION PROGRAM (2400 HOUR INSPECTION)


i. Avionic supports for security, cracks, corrosion and condition. . . . . . . . . . . . . . . .

j. Fuel tank bay internal separation wall for cracks and distortions. . . . . . . . . . . . . . . .

6. TAIL BOOM

a. Visually inspect externally and internally for general condition, distortions,cracks, corrosion, defective and/or missing rivets particularly area surroundingfuselage attachment points, synchronized elevator and 90° gearbox. . . . . . . . . . . . . . . .

b. Check tail boom to fuselage attachment bolt holes for corrosion, wear andelongation. Ref. to para 63-20-6. . . . . . . . . . . . . . . .

c. Lower fin for distortions, cracks and corrosion. . . . . . . . . . . . . . . .

d. Fairings and inspection doors for condition, cracks, distortions, defective and/ormissing rivets and correct hinge operation. . . . . . . . . . . . . . . .

7. TAIL ROTOR

a. Disassemble tail rotor hub and inspect all components for wear, condition,corrosion and damage. Ref. to para 64-20-5. . . . . . . . . . . . . . . .

8. MISCELLANEOUS ASSEMBLIES AND INSTALLATIONS

a. In addition to prescribed ″Component Overhaul Schedule″, remove andthoroughly inspect components of assemblies and installations listed below andrelative attachment points in accordance with pertinent procedures laid down inthis manual.

1) Main rotor pitch change link assembly. Ref. to para 62-30-11. . . . . . . . . . . . . . . .

2) Main rotor hub installation. Ref. to para 62-20-9. . . . . . . . . . . . . . . .

3) Rotating scissors assembly. Ref. to para 62-30-14. . . . . . . . . . . . . . . .

4) Non-rotating scissors assembly. Ref. to para 62-30-14D. . . . . . . . . . . . . . . .

5) Transmission support assemblies and relative fittings secured to fuselage.Ref. to para 63-30-5. . . . . . . . . . . . . . . .

6) Engine-transmission shafts installation. Ref. to para 63-10-6. . . . . . . . . . . . . . . .

7) Engine-blower shafts installation. Ref. to para 63-10-6. . . . . . . . . . . . . . . .

8) Tail rotor drive shaft installation. Ref. to para 65-10-9. . . . . . . . . . . . . . . .

9) Tail rotor pitch change mechanism installation. Ref. to para 64-30-5. . . . . . . . . . . . . . . .

10) Engine mount installation. Ref. to para 71-20-6. . . . . . . . . . . . . . . .

A109C-MPM

05-20-00

05-33

STANDARD INSPECTION PROGRAM (2400 HOUR INSPECTION)



A109C-MPM

05-20-00

05-34

SECTION 05-30

SCHEDULED MAINTENANCE CHECKS -

EXTENDED INSPECTION PROGRAM

05-20-1. BASIC 25 HOUR/30 DAY INSPECTION








Date .................................................

Signature ........................................




A109C-MPM

05-30-00

05-35

NOTE: Accomplish the 25 hour/30 day inspection each 25 hours of flight operationor after 30 calendar days, whichever comes first.

GENERAL


a. Expiry of components’ retirement life in accordance with Chapter 04. . . . . . . . . . . . . . . .

b. Components’ overhaul interval in accordance with Section 05-10. . . . . . . . . . . . . . . .

c. Servicing and lubrication in accordance with Section 05-70. . . . . . . . . . . . . . . .

d. Perform applicable optional equipment inspections in accordance with Section05-60. . . . . . . . . . . . . . . .

e. Other inspection requirements. . . . . . . . . . . . . . . .

2. Remove forward and aft transmission cowlings. Open tail rotor drive shaft fairing. . . . . . . . . . . . . . . .


1. Nose exterior for cracks, dents, loose and/or missing rivets and screws. . . . . . . . . . . . . . . .





6. Nose landing gear wheel for condition, security, correct tire pressure (visuallycheck) and tire-wheel slippage marks. . . . . . . . . . . . . . . .




10. Landing lights for condition, security and cleanliness. . . . . . . . . . . . . . . .

11. Battery for condition and security. Vent lines for condition and obstructions. . . . . . . . . . . . . . . .


13. Battery temperature sensor connector for condition and security. . . . . . . . . . . . . . . .

A109C-MPM

05-30-00

05-36

EXTENDED INSPECTION PROGRAM (BASIC 25 HOUR/30 DAY INSPECTION)


14. Accumulators, lines and accessories (visible parts) for condition, security and leaks;discharge accumulators by pressing relevant red buttons. . . . . . . . . . . . . . . .



1. Windshield and roof transparent panel for condition, damage and cleanliness. . . . . . . . . . . . . . . .




5. Cowlings, fairings and access doors for cracks, dents, security and correct closure. . . . . . . . . . . . . . . .




9. Servo hydraulic system valves and filters group and lines for condition, security andleaks. . . . . . . . . . . . . . . .


11. Hydraulic system reservoirs for proper oil level and security of filler caps. Checkreturn line for security. . . . . . . . . . . . . . . .

12. Main rotor hub for damage and condition. . . . . . . . . . . . . . . .

13. Main rotor blades (2 places) for cleanliness, condition and damage. . . . . . . . . . . . . . . .


15. Main rotor reservoirs (2 places) for integrity and correct oil level. Flap and draghinges and lines for leaks. . . . . . . . . . . . . . . .





20. Swashplate boots for condition and integrity. . . . . . . . . . . . . . . .

A109C-MPM

05-30-00

05-37



21. Anticollision light for cleanliness, breakages and security. . . . . . . . . . . . . . . .




25. Transmission external oil filter for by-pass indication (white button out: filterclogged). . . . . . . . . . . . . . . .


27. Air intake plenum chamber and duct for condition, cleanliness, damage and looseattaching hardware; drain holes for obstructions. . . . . . . . . . . . . . . .

28. Starter-generator for condition and security. Electrical connections for arcing and/orshortcircuit evidence. . . . . . . . . . . . . . . .







35. Wheel brake for leaks and condition. . . . . . . . . . . . . . . .

36. Main landing gear wheel for condition, security, correct tire pressure (visuallycheck) and tire-wheel slippage marks. . . . . . . . . . . . . . . .





41. Engine mount for condition and security. . . . . . . . . . . . . . . .

42. Engine-transmission drive shaft for condition and damage. . . . . . . . . . . . . . . .


A109C-MPM

05-30-00

05-38



44. Engine-blower shaft for condition, security and freedom of axial movement. . . . . . . . . . . . . . . .

45. Blower unit for condition. Impeller for damage. . . . . . . . . . . . . . . .


47. Cooler rear end for cleanliness and damage. . . . . . . . . . . . . . . .



1. Tail boom exterior (pay particular attention between tail boom to fuselageattachment areas) for cracks, dents, missing and/or loose rivets and screws. . . . . . . . . . . . . . . .




5. Navigation light for cleanliness, breakages and security. . . . . . . . . . . . . . . .



2. Tail rotor long drive shaft bearing (last bearing) for unusual play. Rubber collar forcondition and integrity. Slippage marks between shaft-collar-bearing and betweenbearing-hanger. Inspect bearing externally on both sides and seals for damage andwrinklings . . . . . . . . . . . . . . .


4. Access panels for condition, security and correct operation. . . . . . . . . . . . . . . .


6. Tail rotor hub and blades for condition, contamination of oil/grease, security andfreedom of flapping. Flap stop bumpers and boots for condition and damage. . . . . . . . . . . . . . . .




A109C-MPM

05-30-00

05-39






5. Tail rotor long drive shaft bearings for unusual play. Rubber collars for conditionand integrity. Slippage marks between shaft-collar-bearing and between bearing-hanger for integrity. Inspect bearings externally on both sides and seals for damageand wrinklings. . . . . . . . . . . . . . . .






5. Tail rotor middle drive shaft for condition and security, bearings for unusual play.Rubber collars for condition and integrity. Slippage marks between shaft-collar-bearing and between bearing-hanger for integrity. Inspect bearings externally onboth sides and seals for damage and wrinklings. . . . . . . . . . . . . . . .


7. Blower unit for condition. Impeller for condition. . . . . . . . . . . . . . . .









16. Baggage compartment for cleanliness and evidence of leaks. . . . . . . . . . . . . . . .



A109C-MPM

05-30-00

05-40





21. Main landing gear wheel for condition, security, correct tire pressure (visuallycheck), and tire-wheel slippage marks. . . . . . . . . . . . . . . .











32. Swashplate and rotating scissors for condition, security and unusual play. . . . . . . . . . . . . . . .









A109C-MPM

05-30-00

05-41













5. Cabin interior for cleanliness and condition. . . . . . . . . . . . . . . .



8. Check first aid kit is on-board. . . . . . . . . . . . . . . .



11. Copilot safety belt for condition. Release mechanism for correct operation. . . . . . . . . . . . . . . .




15. Lower transparent panel for damage, condition and cleanliness. . . . . . . . . . . . . . . .






A109C-MPM

05-30-00

05-42




22. Overhead console for security and condition. . . . . . . . . . . . . . . .


24. Instruments for damage, condition and security. . . . . . . . . . . . . . . .












e. Inverters. . . . . . . . . . . . . . . .

f. Fuel system: pumps, shut-off and crossfeed valves for correct operation and pressures. . . . . . . . . . . . . . . .








A109C-MPM

05-30-00

05-43







r. Landing lights. . . . . . . . . . . . . . . .


A109C-MPM

05-30-00

05-44



05-20-2. STANDARD 150 HOUR/ANNUAL INSPECTION

NOTE: Accomplish the 150 hour/annual inspection each 150 hours of flightoperation or after 12 calendar months, whichever comes first.

1. GENERAL

a. Perform complete basic 25 hour/30 day inspection (para 05-30-1) in addition tothe following standard 150 hour/annual inspection. . . . . . . . . . . . . . . .







2. MAIN ROTOR



c. Flap restrainers and springs for security and freedom of movement. Inspectsprings plate and springs for condition. . . . . . . . . . . . . . . .


a. Rotating scissors for excessive play. Ref. to para 62-30-8. . . . . . . . . . . . . . . .


Date .................................................

Signature ........................................




A109C-MPM

05-30-00

05-45




5. FLIGHT CONTROLS


1) Control tubes. . . . . . . . . . . . . . . .

2) Bellcranks. . . . . . . . . . . . . . . .

3) Supports. . . . . . . . . . . . . . . .









8. POWER PLANT, OIL COOLER BLOWERS AND TAIL RO-TOR DRIVE SHAFTS

a. Engine-blower and tail rotor drive shafts splined adapters for excessive radialplay. . . . . . . . . . . . . . . .

b. Blower and tail rotor drive shafts Thomas couplings for condition and cracks ofvisible surfaces. . . . . . . . . . . . . . . .

c. Blower support group for damage. Evidence of chafing on blade tips. . . . . . . . . . . . . . . .

d. Blower shafts for freedom of rotation. . . . . . . . . . . . . . . .

A109C-MPM

05-30-00

05-46

EXTENDED INSPECTION PROGRAM (STANDARD 150 HOUR/ANNUAL INSPECTION)


e. Oil coolers for leaks, condition and security. . . . . . . . . . . . . . . .

f. Fuel and oil flexible tubes for condition and chafing. . . . . . . . . . . . . . . .

g. Tail rotor middle and long drive shafts for nicks, scorings, corrosion andsecurity. Ref. to para 65-10-9. . . . . . . . . . . . . . . .

h. Check forward shaft for axial freedom of movement. . . . . . . . . . . . . . . .

i. Tail rotor drive shaft fittings safety pins for freedom of rotation. If shaft pin istight refer to para 65-10-9. . . . . . . . . . . . . . . .

j. Engine mounts for condition and security especially in structure attachmentarea for cracks and distortions. . . . . . . . . . . . . . . .

k. Tubes and electrical wiring for condition, chafing, leaks and security ofconnections. . . . . . . . . . . . . . . .

9. LANDING GEAR



c. Main landing gear fittings and surrounding area for cracks, distortions andsecurity. . . . . . . . . . . . . . . .

10. FUSELAGE



c. Fuselage internal area surrounding the attachment points of tail boom forcracks, corrosion and distortions. . . . . . . . . . . . . . . .


e. Components between main landing gear bay for condition and security. . . . . . . . . . . . . . . .

f. I.V.S.I. static ports for obstructions (IFR only). . . . . . . . . . . . . . . .

g. Drain flight director lines (IFR only). . . . . . . . . . . . . . . .

h. Drain pitot static and dynamic lines. . . . . . . . . . . . . . . .

11. TAIL BOOM


A109C-MPM

05-30-00

05-47






e. Tail skid for wear. Inspect tail skid attachment area to the lower fin for cracksand damage.

. . . . . . . . . . . . . . .




c. Survival equipment (if installed) for inspection due dates and expiry.. . . . . . . . . . . . . . .



b. Tail rotor (90°) gearbox mounting sleeve and surrounding area on tail boomfinal rib for cracks, loose rivets and security.

. . . . . . . . . . . . . . .

14. TAIL ROTOR



2) Voids. Ref. to para 64-10-7. . . . . . . . . . . . . . . .



d. Slider bushings for wear. Ref. to para 64-30-5. . . . . . . . . . . . . . . .

e. Sleeve of pitch change mechanism for fretting and/or wear to splines of bushingP/N 109-0133-06-101 and of shaft. Ref. to 64-30-5.

f. Duplex bearing P/N 109-0133-05-101 of the pitch change mechanism forfreedom of rotation. Ref. to para 64-30-6. . . . . . . . . . . . . . . .

g. Bolts P/N AN174-14 that connect the two links and the pitch control lever to thehousing of the pitch change mechanism for damage. Ref. to para 64-30-6. . . . . . . . . . . . . . . .

h. Tail rotor hub trunnion covers for cracks (visual inspection, removal notnecessary). . . . . . . . . . . . . . . .

A109C-MPM

05-30-00

05-48








e. Remove and recondition the battery. Ref. to para 24-30-17. . . . . . . . . . . . . . . .

f. Perform operational test of d.c. electrical system. Ref. to para 24-30-11. . . . . . . . . . . . . . . .

g. Perform operational test of a.c. electrical system. Ref. to para 24-20-6. . . . . . . . . . . . . . . .

A109C-MPM

05-30-00

05-49




A109C-MPM

05-30-00

05-50

05-20-3. STANDARD 600 HOUR INSPECTION

1. GENERAL

a. Perform complete basic 25 hour/30 day inspection (para 05-30-1), 150hour/annual inspection (para 05-30-2) in addition to the following standard 600hour inspection. . . . . . . . . . . . . . . .







2. MAIN ROTOR






a. Disconnect pitch change links and rotating scissors. Inspect swashplate duplexbearing for roughness, noise and smoothness of rotation. Ref. to para 62-30-17. . . . . . . . . . . . . . . .

Date .................................................

Signature ........................................




A109C-MPM

05-30-00

05-51

4. FLIGHT CONTROLS



c. Levers of main and tail rotor servo actuators; protect with proper compound.Ref. to para 67-30-16.


5. FUEL SYSTEM (EXCEPT PUMPS SECONDO MONA MFRP/N SM 2232 AND GLOBE MFR P/N 164A298)




7. LANDING GEAR

a. Main landing gear actuator attachment bolts for correct torque. Ref. to para32-30-15. . . . . . . . . . . . . . . .


c. Externally inspect nose landing gear shock strut for corrosion, condition anddamage.


8. TAIL ROTOR





A109C-MPM

05-30-00

05-52

EXTENDED INSPECTION PROGRAM (STANDARD 600 HOUR INSPECTION)








A109C-MPM

05-30-00

05-53

EXTENDED INSPECTION PROGRAM (STANDARD 600 HOUR INSPECTION)



A109C-MPM

05-30-00

05-54


1. GENERAL

a. Perform complete basic 25 hour/30 day inspection (para 05-30-1), standard 150hour/annual inspection (para 05-30-2) and standard 600 hour inspection (para05-30-3) in addition to the following 2400 hour inspection. . . . . . . . . . . . . . . .







2. MAIN ROTOR



c. Remove and inspect flap hinge bearings for damage and corrosion. Ref. to para62-20-10B.



Date .................................................

Signature ........................................




A109C-MPM

05-30-00

05-55




c. Inspect main rotor brake coupling flange, on transmission tail rotor drive quill,for wear and condition. Refer to para 63-21-46. . . . . . . . . . . . . . . .


e. Inspect upper case and mast assembly for corrosion and damage. Ref. to para63-21-16. . . . . . . . . . . . . . . .

4. FLIGHT CONTROLS


5. FUSELAGE





e. Check engine mount supports for corrosin, wear and elongation of holes. Ref.to para 71-20-6. . . . . . . . . . . . . . . .




A109C-MPM

05-30-00

05-56

EXTENDED INSPECTION PROGRAM (2400 HOUR INSPECTION)




6. TAIL BOOM





7. TAIL ROTOR






3) Rotating and scissors assembly. Ref. to para 62-30-14. . . . . . . . . . . . . . . .







10) Engine mount installation. Ref. to para 71-20-6. . . . . . . . . . . . . . . .

A109C-MPM

05-30-00

05-57

EXTENDED INSPECTION PROGRAM (2400 HOUR INSPECTION)



A109C-MPM

05-30-00

05-58

SECTION 05-40

SCHEDULED MAINTENANCE CHECKS -

PROGRESSIVE INSPECTION PROGRAM

05-40-1. BASIC 25 HOUR/30 DAY INSPECTION








Date .................................................

Signature ........................................




A109C-MPM

05-40-00

05-59

NOTE: Accomplish the 25 hour/30 day inspection each 25 hours of flight operationor after 30 calendar days, whichever comes first.

GENERAL







2. Remove forward and aft transmission cowlings. Open tail rotor drive shaft fairing. . . . . . . . . . . . . . . .


1. Nose exterior for cracks, dents, loose and/or missing rivets and screws. . . . . . . . . . . . . . . .





6. Nose landing gear wheel for condition, security, correct tire pressure (visuallycheck) and tire-wheel slippage marks. . . . . . . . . . . . . . . .




10. Landing lights for condition, security and cleanliness. . . . . . . . . . . . . . . .

11. Battery for condition and security. Vent lines for condition and obstructions. . . . . . . . . . . . . . . .


13. Battery temperature sensor connector for condition and security. . . . . . . . . . . . . . . .

A109C-MPM

05-40-00

05-60

PROGRESSIVE INSPECTION PROGRAM (BASIC 25 HOUR/30 DAY INSPECTION)


14. Accumulators, lines and accessories (visible parts) for condition, security and leaks;discharge accumulators by pressing relevant red buttons.

. . . . . . . . . . . . . . .











9. Servo hydraulic system valves and filters group and lines for condition, security and leaks. . . . . . . . . . . . . . . .


11. Hydraulic system reservoirs for correct oil level and security of filler caps. Checkreturn line for security. . . . . . . . . . . . . . . .










A109C-MPM

05-40-00

05-61







25. Transmission external oil filter for by-pass indication (white button out: filterclogged). . . . . . . . . . . . . . . .
















41. Engine mount for condition and security. . . . . . . . . . . . . . . .



A109C-MPM

05-40-00

05-62




45. Blower unit for condition. Impeller for damage. . . . . . . . . . . . . . . .












2. Tail rotor long drive shaft bearing (last bearing) for unusual play. Rubber collar forcondition and integrity. Slippage marks between shaft-collar-bearing and betweenbearing-hanger. Inspect bearing externally on both sides and seals for damage andwrinklings . . . . . . . . . . . . . . .


4. Access panels for condition, security and correct operation. . . . . . . . . . . . . . . .


6. Tail rotor hub and blades for condition, contamination of oil/grease, security andfreedom of flapping. Flap stop bumpers and boots for condition and damage. . . . . . . . . . . . . . . .




A109C-MPM

05-40-00

05-63






5. Tail rotor long drive shaft bearings for unusual play. Rubber collars for conditionand integrity. Slippage marks between shaft-collar-bearing and between bearing-hanger for integrity. Inspect bearings on both sides and seals for damage andwrinklings. . . . . . . . . . . . . . . .






5. Tail rotor middle drive shaft for condition and security, bearings for unusual play.Rubber collars for condition and integrity. Slippage marks between shaft-collar-bearing and between bearing-hanger for integrity. Inspect bearings externally onboth sides and seals for damage and wrinklings. . . . . . . . . . . . . . . .


7. Blower unit for condition. Impeller for condition. . . . . . . . . . . . . . . .









16. Baggage compartment for cleanliness and evidence of leaks. . . . . . . . . . . . . . . .



A109C-MPM

05-40-00

05-64
















32. Swashplate and rotating scissors for damage and unusual play. . . . . . . . . . . . . . . .









A109C-MPM

05-40-00

05-65













5. Cabin interior for cleanliness and condition. . . . . . . . . . . . . . . .



8. Check first aid kit is on-board. . . . . . . . . . . . . . . .



11. Copilot safety belt for condition. Release mechanism for correct operation. . . . . . . . . . . . . . . .










A109C-MPM

05-40-00

05-66




22. Overhead console for security and condition. . . . . . . . . . . . . . . .


24. Instruments for damage, condition and security. . . . . . . . . . . . . . . .












e. Inverters. . . . . . . . . . . . . . . .

f. Fuel system: pumps, shut-off and crossfeed valves for correct operation and pressures. . . . . . . . . . . . . . . .








A109C-MPM

05-40-00

05-67







r. Landing lights. . . . . . . . . . . . . . . .


A109C-MPM

05-40-00

05-68



05-40-2. PROGRESSIVE 150 HOUR/ANNUAL INSPECTION PHASE A

NOTE: Perform this phased inspection in conjunction with the first basic 25hour/30 day inspection (para 05-40-1) and subsequently after every 150hours of flight operation or after 12 calendar months, whichever comesfirst.

1. GENERAL

a. Verify the following:






2. TAIL ROTOR DRIVE SHAFTS

a. Tail rotor drive shafts Thomas couplings for condition and cracks of visiblesurfaces. . . . . . . . . . . . . . . .

3. FUSELAGE



c. Fuselage internal area surrounding the attachment points of tail boom forcracks, corrosion and distortions. . . . . . . . . . . . . . . .


Date .................................................

Signature ........................................




A109C-MPM

05-40-00

05-69

4. TAIL BOOM





e. Tail skid for wear. Inspect tail skid attachment area to the lower fin for cracksand damage. . . . . . . . . . . . . . . .

A109C-MPM

05-40-00

05-70

PROGRESSIVE INSPECTION PROGRAM (PROGRESSIVE 150 HOUR/ANNUAL INSPECTION - PHASE A)


05-40-3. PROGRESSIVE 150 HOUR/ANNUAL INSPECTION PHASE B

NOTE: Perform this phased inspection in conjunction with the second basic 25hour/30 day inspection (para 05-40-1) and subsequently after every 150hours of flight operation or after 12 calendar months, whichever comesfirst.

1. GENERAL







2. POWER PLANT, OIL COOLER BLOWERS AND TAIL RO-TOR DRIVE SHAFTS

a. Blower and tail rotor drive shafts splined adapters for excessive radial play. . . . . . . . . . . . . . . .

b. Engine-blower shafts Thomas couplings for condition and cracks of visiblesurfaces. . . . . . . . . . . . . . . .

c. Blower support group for damage. Impeller for condition and evidence ofchafing on blade tips. . . . . . . . . . . . . . . .

d. Blower shafts for freedom of rotation. . . . . . . . . . . . . . . .

e. Oil cooler for leaks, condition and security. . . . . . . . . . . . . . . .

f. Fuel and oil flexible tubes for condition and chafing. . . . . . . . . . . . . . . .

Date .................................................

Signature ........................................




A109C-MPM

05-40-00

05-71

g. Tail rotor middle and long drive shafts for nicks, scorings, corrosion andsecurity. Ref. to para 65-10-9. . . . . . . . . . . . . . . .

h. Check forward shaft for axial movement. . . . . . . . . . . . . . . .

i. Tail rotor drive shaft fitting safety pins for freedom of rotation. If shaft pin istight refer to para 65-10-9. . . . . . . . . . . . . . . .

j. Engine mounts for condition and security expecially in strucure attachment areafor cracks and distortions. . . . . . . . . . . . . . . .




c. Survival equipment (if installed) for inspection due dates and expiry. . . . . . . . . . . . . . . .






e. Perform operational test of d.c. electrical system. Ref. to para 24-30-11. . . . . . . . . . . . . . . .

f. Perform operational test of a.c. electrical system. Ref. to para 24-20-6. . . . . . . . . . . . . . . .

A109C-MPM

05-40-00

05-72

PROGRESSIVE INSPECTION PROGRAM (PROGRESSIVE 150 HOUR/ANNUAL INSPECTION - PHASE B)


05-40-4. PROGRESSIVE 150 HOUR/ANNUAL INSPECTION PHASE C

NOTE: Perform this phased inspection in conjunction with the third basic 25hour/30 day inspection (para 05-40-1) and subsequently after every 150hours of flight operation or after 12 calendar months, whichever comesfirst.

1. GENERAL







2. FUSELAGE

a. Components between main landing gear bay for condition and security. . . . . . . . . . . . . . . .

b. I.V.S.I. static ports for obstructions (IFR only). . . . . . . . . . . . . . . .

c. Drain flight director lines (IFR only). . . . . . . . . . . . . . . .

d. Drain pitot static and dynamic lines. . . . . . . . . . . . . . . .


a. Remove and recondition the battery. Ref. to para 24-30-17. . . . . . . . . . . . . . . .

Date .................................................

Signature ........................................




A109C-MPM

05-40-00

05-73


A109C-MPM

05-40-00

05-74

05-40-5. PROGRESSIVE 150 HOUR/ANNUAL INSPECTION PHASE D

NOTE: Perform this phased inspection in conjunction with the third basic 25hour/30 day inspection (para 05-40-1) and subsequently after every 150hours of flight operation or after 12 calendar months, whichever comesfirst.

1. GENERAL







2. LANDING GEAR



c. Main landing gear for cracks, distortion and security. . . . . . . . . . . . . . . .



Date .................................................

Signature ........................................




A109C-MPM

05-40-00

05-75


A109C-MPM

05-40-00

05-76

05-40-6. PROGRESSIVE 150 HOUR/ANNUAL INSPECTION PHASE E

NOTE: Perform this phased inspection in conjunction with the fifth basic 25hour/30 day inspection (para 05-40-1) and subsequently after every 150hours of flight operation or after 12 calendar months, whichever comesfirst.

1. GENERAL







2. MAIN ROTOR



c. Flap restrainers and springs for security and freedom of movement. Inspectsprings plate and springs for condition. . . . . . . . . . . . . . . .


a. Rotating scissors for excessive play. Ref. to 62-30-8. . . . . . . . . . . . . . . .


Date .................................................

Signature ........................................




A109C-MPM

05-40-00

05-77




5. FLIGHT CONTROLS


1) Control tubes. . . . . . . . . . . . . . . .

2) Bellcranks. . . . . . . . . . . . . . . .

3) Supports. . . . . . . . . . . . . . . .







7. TAIL ROTOR



2) Voids. Ref. to para 64-10-7. . . . . . . . . . . . . . . .



A109C-MPM

05-40-00

05-78

PROGRESSIVE INSPECTION PROGRAM (PROGRESSIVE 150 HOUR/ANNUAL INSPECTION - PHASE E)


05-40-7. PROGRESSIVE 150 HOUR/ANNUAL INSPECTION PHASE F

NOTE: Perform this phased inspection in conjunction with the sixth basic 25hour/30 day inspection (para 05-40-1) and subsequently after every 150hours of flight operation or after 12 calendar months, whichever comesfirst.

1. GENERAL







2. POWER PLANT AND OIL COOLER BLOWERS

a. Tubes and electrical wiring for condition, chafing, leaks and security ofconnections. . . . . . . . . . . . . . . .



b. Tail rotor (90°) gearbox mounting sleeve and surrounding area on tail boomfinal rib for cracks, loose rivets and security. . . . . . . . . . . . . . . .

Date .................................................

Signature ........................................




A109C-MPM

05-40-00

05-79

4. TAIL ROTOR

a. Slider bushings for wear. Ref. to para 64-30-5. . . . . . . . . . . . . . . .

b. Sleeve of pitch change mechanism for fretting and/or wear to splines of bushingP/N 109-0133-06-101 and of shaft. Ref. to para 64-30-5. . . . . . . . . . . . . . . .

c. Duplex bearing P/N 109-0133-05-101 of the pitch change mechanism forfreedom of rotation. Ref. to para 64-30-6. . . . . . . . . . . . . . . .

d. Bolts P/N AN174-14 that connect the two links and the pitch control lever to thehousing of the pitch change mechanism. Ref. to para 64-30-6. . . . . . . . . . . . . . . .

e. Tail rotor hub trunnion covers for cracks (visual inspection, removal notnecessary). . . . . . . . . . . . . . . .

A109C-MPM

05-40-00

05-80

PROGRESSIVE INSPECTION PROGRAM (PROGRESSIVE 150 HOUR/ANNUAL INSPECTION - PHASE F)


05-40-8. PROGRESSIVE 600 HOUR INSPECTION PHASE 1

NOTE: Perform this phased inspection in conjunction with the sixth basic 25hour/30 day inspection (para 05-40-1) and subsequently after every 600hours of flight operation.

1. GENERAL







2. MAIN ROTOR






a. Disconnect pitch change links and rotating scissors. Inspect swashplate duplexbearing for roughness, noise and smoothness of rotation. Ref. to para 62-30-17. . . . . . . . . . . . . .

Date .................................................

Signature ........................................




A109C-MPM

05-40-00

05-81


A109C-MPM

05-40-00

05-82

05-40-9. PROGRESSIVE 600 HOUR INSPECTION PHASE 2

NOTE: Perform this phased inspection in conjunction with the twelth basic 25hour/30 day inspection (para 05-40-1) and subsequently after every 600hours of flight operation.

1. GENERAL







2. FLIGHT CONTROLS



c. Levers of main and tail rotor servo actuators: protect with proper compound.Ref. to para 67-30-16. . . . . . . . . . . . . . . .


Date .................................................

Signature ........................................




A109C-MPM

05-83


A109C-MPM

05-84

05-40-10. PROGRESSIVE 600 HOUR INSPECTION - PHASE 3

NOTE: Perform this phased inspection in conjunction with the eighteenth basic 25hour/30 day inspection (para 05-40-1) and subsequently after every 600hours of flight operation.

1. GENERAL







2. LANDING GEAR

a. Main landing gear actuator attachment bolts for correct torque. Ref. to para32-30-15. . . . . . . . . . . . . . . .


c. Externally inspect nose landing gear shock strut for corrosion, condition anddamage. . . . . . . . . . . . . . . .


3. TAIL ROTOR


Date .................................................

Signature ........................................




A109C-MPM

05-85







A109C-MPM

05-86

PROGRESSIVE INSPECTION PROGRAM (PROGRESSIVE 600 HOUR INSPECTION - PHASE 3)


05-40-11. PROGRESSIVE 600 HOUR INSPECTION - PHASE 4

NOTE: Perform this phased inspection in conjunction with the twenty-fourth basic25 hour/30 day inspection (para 05-40-1) and subsequently after every 600hours of flight operation.

1. GENERAL







2. FUEL SYSTEM (EXCEPT PUMPS SECONDO MONA MFRP/N SM2232 AND GLOBE MFR P/N 164A298)


3. UTILITY HYDRAULIC SYTEM





Date .................................................

Signature ........................................




A109C-MPM

05-87


A109C-MPM

05-88


1. GENERAL

a. Perform basic 25 hour/30 day inspection, (para 05-40-1) Phase F of progressive150 hour/annual inspection (para 05-40-7) and Phase 4 of progressive 600 hourinspection in addition to the following 2400 hour inspection (para 05-40-11). . . . . . . . . . . . . . . .







2. MAIN ROTOR



c. Remove and inspect flap hinge bearings for damage and corrosion. Ref. to para62-20-10B. . . . . . . . . . . . . . . .



Date .................................................

Signature ........................................




A109C-MPM

05-89




c. Inspect main rotor brake coupling flange, on transmission tail rotor drive quill,for wear and condition. Ref. to para 63-21-46. . . . . . . . . . . . . . . .


e. Inspect upper case and mast assembly for corrosion and damage. Ref. topara 63-21-16. . . . . . . . . . . . . . . .

4. FLIGHT CONTROLS


5. FUSELAGE





e. Check engine mount supports for corrosion, wear and elongation of holes. Ref.to para 71-20-6. . . . . . . . . . . . . . . .




A109C-MPM

05-90

PROGRESSIVE INSPECTION PROGRAM (2400 HOUR INSPECTION)




6. TAIL BOOM





7. TAIL ROTOR






3) Rotating scissors assembly. Ref. to para 62-30-14. . . . . . . . . . . . . . . .







10) Engine mount installation. Ref. to para 71-20-6. . . . . . . . . . . . . .

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05-91

PROGRESSIVE INSPECTION PROGRAM (2400 HOUR INSPECTION)



A109C-MPM

05-92

SECTION 05-50

UNSCHEDULED MAINTENANCE CHECKS

05-50-1. SPECIAL INSPECTIONS

1. GENERAL

a. Perform applicable optional equipment special inspections in accordance withSection 05-60. . . . . . . . . . . . . . . .

2. PRIOR TO THE FIRST FLIGHT OF THE DAY

a. MAIN AND TAIL ROTOR BLADES (only when protective tape is installed onleading edge)

1) Inspect the tape for proper adhesion, condition, wrinkles, lifting orbreaking at the edges. Ref. to para 62-10-32 and para 64-10-10. . . . . . . . . . . . . . . .

3. BETWEEN 5 AND 10 HOURS OF FLIGHT WHEN AIRCRAFTIS NEW OR AFTER REINSTALLATION OF THE FOLLOW-ING COMPONENTS:

NOTE: If incorrect torque is found, recheck within next 5 to 10 hours of flight.

a. MAIN ROTOR

1) Main rotor hub ring nut bolts for correct torque. Ref. to para 62-20-8. . . . . . . . . . . . . . . .

b. MAIN TRANSMISSION

1) Upper cover main case attachment nuts for correct torque. Ref. topara 63-21-19. . . . . . . . . . . . . . . .

c. POWER PLANT

1) Engine mounts to fuselage attachment bolts for correct torque. Ref. tofigure 71-9. . . . . . . . . . . . . . . .

2) Engine mount to engine attaching nuts for correct torque. Ref. tofigure 71-9. . . . . . . . . . . . . . . .

Date .................................................

Signature ........................................




A109C-MPM

05-50-00

05-93

d. TAIL BOOM

1) Tail boom attachment bolts for correct torque. Ref. to para 53-00-6. . . . . . . . . . . . . . . .

e. TAIL ROTOR (90°) GEARBOX

1) Mounting sleeve attachment bolts for correct torque. Ref. to para 65-20-5. . . . . . . . . . . . . . . .

4. AT EACH WHEEL TIRE REMOVAL

a. LANDING GEAR WHEELS

1) Wheel half rims for cracks. Ref. to para 32-40-17. . . . . . . . . . . . . . . .

5. AT EACH PILOT AND/OR PASSENGER DOORSREMOVAL/INSTALLATION

a. CABIN INTERIOR

1) Emergency jettison mechanism for correct operation. Ref. topara 52-10-16. . . . . . . . . . . . . . . .

6. EACH 25 HOURS

a. MAIN ROTOR

1) Inspect tip cap of main rotor blades for presence of debonds and/or cracks.Ref. to para 62-10-25B. . . . . . . . . . . . . . . .

NOTE: The above prescribed inspection is applicable to main rotor blades P/N709-0103-01 up to S/N 1428 included, preceded by code A5 or EMequipped with tip cap P/N 709-0103-29-101/-107.

7. EACH 50 HOURS

a. MAIN ROTOR

1) Inspect tip cap of main rotor blades for presence of cracks. Ref. to para62-10-25C. . . . . . . . . . . . . . . .

NOTE: The above prescribed inspection is applicable to main rotor blades tip capP/N 709-0103-29-109 that have accumulated 600 (six hundred) flight hours.

b. TAIL ROTOR

1) Inspect the tail rotor blades P/N 109-8132-01-107 tip fairing. Refer to para64-10-8A. . . . . . . . . . . . . . . .

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8. EACH 75 HOURS

a. TAIL ROTOR

1) Check tail rotor for correct dynamic balance. Ref. to para 64-00-7. . . . . . . . . . . . . . . .

9. EACH 100 HOURS

a. SERVO HYDRAULIC SYSTEM

1) Check for interferences between hydraulic pipes 109-0761-64-1 or -103and 109-0761-65-1 or -103 of the N. 1 System with the tail rotor controlrod assy 109-0032-01-41. Ref. to para 29-10-14A. . . . . . . . . . . . . . . .

10. EACH 300 HOURS

a. MAIN ROTOR

1) Main rotor hub ring nut bolts for correct torque. Ref. to para 62-20-8. . . . . . . . . . . . . . . .

b. SERVO HYDRAULIC SYSTEM

1) Clean the hydraulic filter elements. Ref. to para 29-10-39. . . . . . . . . . . . . . . .

c. POWER PLANT AND OIL COOLER BLOWERS

1) Thomas coupling on engine to transmission drive shaft for cracks andcorrosion. Transmission side; remove protective mesh and access door,rotate shaft and inspect the whole coupling surface. Engine side; removethe cowling and repeat the above mentioned inspection. . . . . . . . . . . . . . . .

NOTE: During the inspection move axially the shaft for an easier detection ofcracks.

2) Engine mounts to engine attachment nuts for correct torque. Ref. to figure71-9. . . . . . . . . . . . . . . .

3) Engine-blower Thomas couplings for cracks and corrosion of laminates. . . . . . . . . . . . . . . .

d. FLIGHT CONTROLS

1) Check cyclic for correct friction. Ref. to para 67-12-16A. . . . . . . . . . . . . . . .

e. LANDING GEAR

1) Landing gear wheels (visible part) for paint condition and corrosion. . . . . . . . . . . . . . . .

2) Landing gear uplocks for condition.

3) Perform functional test of extension and retraction system. Ref. to para32-30-9. . . . . . . . . . . . . . . .

4) Raise helicopter and check nose and main landing gear for unusual playand security. . . . . . . . . . . . . . . .

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05-95


f. TAIL BOOM

1) Tail boom vertcal fin internal area surrounding aft spar attachment to thetail boom for cracks. Ref. to para 53-20-12. . . . . . . . . . . . . . . .

g. TAIL ROTOR

1) Hub for excessive play along the flapping axis. Ref. to para 64-20-9.

2) Inspect tail rotor trunnion, cover and bushing for wear. Ref. to para64-20-5. . . . . . . . . . . . . . . .

3) Levers, scissors and links of pitch change mechanism for excessive play. . . . . . . . . . . . . . . .

h. ELECTRICAL SYSTEM AND INSTRUMENTS

1) Perform operational test of the battery overheating detector. Ref. to para24-30-51. . . . . . . . . . . . . . . .

2) Starter-generator brushes for wear. Commutator contacts for wear, pittingsand burnings. Ref. to para 24-30-23. . . . . . . . . . . . . . . .

3) (Only Bendix manufactured cyclic grip) Pin PM21217 and insertsPM21264 and PM21265 of ICS/RADIO trigger switch for signs of wearand/or nicks. Ref. to para 67-12-15. . . . . . . . . . . . . . . .

11. EACH 1200 HOURS

a. MAIN ROTOR CONTROLS

1) Remove and inspect swashplate duplex bearing for damage and corrosion.Ref. to para 63-30-17A. . . . . . . . . . . . . . . .

2) Swashplate teflon rings (pivot sleeve and swashplate) for wear. Ref. topara 62-30-17A. . . . . . . . . . . . . . . .

3) Slider bearings and pivot sleeve slots of swashplate for damage and wear.Ref. to para 62-30-17A. . . . . . . . . . . . . . . .

b. MAIN TRANSMISSION

1) Components and tracks of L.H. and R.H. freewheel units for wear anddamage. Ref. to para 63-21-27. . . . . . . . . . . . . . . .

2) Main transmission mounts for condition and/or chafing with tubing. . . . . . . . . . . . . . . .

c. FLIGHT CONTROLS

1) Main rotor servo actuators dowel pin seats for wear, elongations and/ordistortions. Ref. to para 67-30-8. . . . . . . . . . . . . . . .

2) Main rotor servo actuators lower spherical bearing for nicks and/orevidence of wear. Ref. to para 67-30-8. . . . . . . . . . . . . . . .

d. FUEL SYSTEM (GLOBE PUMPS MFR P/N 164A298 ONLY)

1) Pump brushes for wear. Ref. to para 28-20-14. . . . . . . . . . . . . . . .

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05-96


e. POWER PLANT, OIL COOLER BLOWERS AND TAIL ROTOR DRIVESHAFTS

1) Engine mounts for chafing with tubing. . . . . . . . . . . . . . . .

2) Remove tail rotor drive shafts assembly and inspect bearings for roughness,freedom of rotation and corrosion. Ref. to para 65-10-26. . . . . . . . . . . . . . . .

3) Inspect oil coolers for cleanliness of heat exchanger part. Ref. to para79-20-10. . . . . . . . . . . . . . . .

4) Inspect blower shafts bearings for roughness, freedom of rotation, exces-sive play and condition. Ref. to para 79-20-11A. . . . . . . . . . . . . . . .

f. LANDING GEAR

1) Main landing gear shock strut bearings P/N 1809-4 for wear. Ref. to para32-10-12. . . . . . . . . . . . . . . .

2) Inspect side brace for damage, cracks and corrosion in area surroundingbearings. Inspect ribbed area of side brace for damage and corrosion. Ref.to para 32-10-16. . . . . . . . . . . . . . . .

g. FUSELAGE

1) Boxed beams on engine deck sides for corrosion. Ref. to para 53-10-8. . . . . . . . . . . . . . . .

h. TAIL BOOM

1) Inspect tail boom exterior upper fin for general condition, distortions,corrosion, defective and/or missing rivets. . . . . . . . . . . . . . . .

2) Lower fin attachment points in the area surrounding the reinforcementplates for condition and evidence of bonding failure. . . . . . . . . . . . . . . .

3) Synchronized elevator for condition, dents, corrosion, defective and/ormissing rivets. . . . . . . . . . . . . . . .

4) Tail rotor drive shafts supports for condition and corrosion. . . . . . . . . . . . . . . .

5) Synchronized elevator supports for correct friction. Ref. to para 55-20-5. . . . . . . . . . . . . . . .

i. CABIN INTERIOR AND EXTERIOR

1) Inspect cabin aft wall for cracks. Ref. to para 53-10-8. . . . . . . . . . . . . . . .

j. TAIL ROTOR (90°) GEARBOX

1) Inspect gearing teeth for unusual prints, pitting, scoring, damage andbearings for freedom of rotation and roughness. Ref. to para 65-20-8. . . . . . . . . . . . . . . .

k. TAIL ROTOR

1) Inspect the root plate of tail rotor blade for voids. Ref. to para 64-10-7. . . . . . . . . . . . . . . .

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05-50-00

05-97


12. EACH 200 HOURS OR 6 MONTHS

a. ENGINE AUXILIARY OIL FILTER

1) Replace filter element. Ref. to para 79-20-12. . . . . . . . . . . . . . . .

13. EACH 300 HOURS OR 12 MONTHS

a. MAIN ROTOR

1) Perform dampers leakage test. Ref. to para 12-20-19A. . . . . . . . . . . . . . . .

2) Inspect blade and grip bushings (retention pin seat) for corrosion (gripbushings), nicks and condition. Inspect contact area between blade and gripfor condition and washers bondage. Inspect washers and blade retentionbolts for condition and wear. . . . . . . . . . . . . . . .

b. SERVO HYDRAULIC SYSTEM

1) Splined shaft and relevant seating on hydraulic pumps and main transmis-sion for wear. Ref. to para 29-10-28, 63-21-34 and 63-21-40. . . . . . . . . . . . . . . .

2) Hydraulic components for leaks. . . . . . . . . . . . . . . .

c. UTILITY HYDRAULIC SYSTEM

1) Perform functional test of normal and emergency hydraulic systems. Ref.to para 29-20-11. . . . . . . . . . . . . . . .

2) Hydraulic components for leaks. . . . . . . . . . . . . . . .

d. FUEL SYSTEM

1) Replace airframe (A/F) fuel filter element. Ref. to para 28-20-20. . . . . . . . . . . . . . . .

e. POWER PLANT AND OIL COOLER BLOWERS

1) Spline of engine drive shaft adapter for wear and damage. Ref. to para63-10-6. . . . . . . . . . . . . . . .

2) Adapter splines of engine drive shaft adapter to blower shaft for wear anddamage. Ref. to para 63-10-6. . . . . . . . . . . . . . . .

3) Blower shaft spline for wear and damage. Ref. to para 79-20-10. . . . . . . . . . . . . . . .

4) Perform an inspection to the grooved clamps P/N 4606AC that attach theengine exhaust ducts for cracks and/or corrosion. Ref. to para 71-01-19A. . . . . . . . . . . . . . . .

14. EACH 600 HOURS OR 4 YEARS

a. MAIN ROTOR

1) Spindle and pitch change bearings for condition, wear, corrosion and otherdamage. Spindle rings and grip seals for wear. Ref. to para 62-20-14A. . . . . . . . . . . . . . . .

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05-50-00

05-98



a. LANDING GEAR

1) For helicopters which operate in severe environmental conditions (on seaand/or high humidity). Inspect nose landing gear actuator for corrosion anddamage. Ref. to para 32-30-22. . . . . . . . . . . . . . . .


a. FUEL SYSTEM

1) Perform a functional check of the check valves. Ref. to para 28-20-11A. . . . . . . . . . . . . . . .


a. LANDING GEAR

1) Inspect main landing gear shock struts for corrosion. Ref. to para 32-10-10. . . . . . . . . . . . . . . .

2) Inspect nose landing gear shock strut for corrosion. Ref. to para 32-20-11. . . . . . . . . . . . . . . .

3) For helicopters which do not operate in severe environmental conditions(on sea and/or high humidity). Inspect nose landing gear actuator forcorrosion and damage. Ref. to para 32-30-22. . . . . . . . . . . . . . . .

18. EACH 3600 HOURS

a. MAIN TRANSMISSION

NOTE: The following inspection can be performed without removal main trans-mission from the helicopter.

1) Inspect upper case for:

— Corrosion at servo actuator attachment and support links attachment. . . . . . . . . . . . . . . .

— Fretting, corrosion and other damages at mating surface with ring gear. . . . . . . . . . . . . . . .

— Corrosion and other damages of mast ball and roller bearing and upperroller bearing seat. . . . . . . . . . . . . . . .

2) Inspect planet bearing for (Ref. to para 63-21-22A):

— Freedom of rotation. . . . . . . . . . . . . . . .

— Pitting,scoring, spalling and other damages on tooth. . . . . . . . . . . . . . . .

— Brinneling, spalling, corrosion and ohter damages on rollers and rollerrace. . . . . . . . . . . . . . . .

— Signes of overheating. . . . . . . . . . . . . . . .

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3) Inspect sun gear for (Ref. to para 63-21-22B):

— Spalling, pitting, scoring, abnormal pattern and other damages ontooth. . . . . . . . . . . . . . . .

— Wear, spalling, fretting and other damages on spline. . . . . . . . . . . . . . . .

4) Inspect ring gear for (Ref. to para 63-21-22C):

— Pitting, scoring, abnormal pattern and other damages on tooth. . . . . . . . . . . . . . . .

5) Inspect main case for (Ref. to para 63-21-22D):

— Fretting, corrosion and other damages at mating surface with planetaryring. . . . . . . . . . . . . . . .

6) Inspect gleasom crown teeth and gleason pinion for pitting, scoring,abnormal pattern and other damages (Ref. to para 63-21-22E).

. . . . . . . . . . . . . . .

19. EACH 2 YEARS

a. LANDING GEAR

1) Remove the shock strut (left and right) of main landing gear and inspect theshock strut attachments on the side braces for cracks and corrosion. Ref. topara 32-10-16. . . . . . . . . . . . . . . .

20. EACH 3 YEARS

Accomplish a visual inspection for corrosion and/or possible breakages on cockpit

floor inserts, below the supports P/N 109-0041-02 and P/N 109-0041-07. Ref to para

53-10-8A.

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05-100


21. EACH 12 YEARS

a. LANDING GEAR

1) Replace seals of the following hydraulic components: . . . . . . . . . . . . . . .

NOTE: The 12 years start from the component assy date or last overhaul date.

NOTE: The specified part number contained in the schedule applies to indicateddash and all successive dash numbers.

Part number Denomination

109-0502-86-101 and -102 Main landing gear shock strut

109-0501-28-105 Nose landing gear shock strut

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05-50-00

05-101



A109C-MPM

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05-102

05-50-2. CONDITIONAL INSPECTIONS

1. HARD LANDING

a. If a hard landing is suspected, the following steps shall be complied with:

1) Inspect main and tail rotor blades for evidence of damage, check closely forwrinkled skin. . . . . . . . . . . . . . . .

2) Visually inspect underside of fuselage and tail boom for evidence ofground contact. . . . . . . . . . . . . . . .

3) Visually inspect nose and main landing gear for distortions, cracks, leakageand damage. Wheel half rims for distortion and cracks. Check tire forcondition and evidence of damage. Nose and main landing gear fittings andsurrounding areas for distortions, cracks and damage. . . . . . . . . . . . . . . .

4) Inspect flap stops and main rotor hub for distortions and evidence of hardcontact. . . . . . . . . . . . . . . .

5) Visually inspect main transmission mounts, transmission antitorque platefor distortion and cracks; surrounding areas for loose rivets or otherdamage. . . . . . . . . . . . . . . .

6) Check all cowlings and doors for proper fit and alignment. Misalignedcowlings may indicate a distorted fuselage or tail boom resulting in majorstresses and damage to components. . . . . . . . . . . . . . . .

NOTE: If only minor damage has been found at this point it can reasonably beconcluded that a true hard landing did not occur. Perform an airworthinesscheck or basic 25 hour/30 day inspection (depending upon which programis chosen) and return helicopter to flight status provided no further evidenceof damage is found.If major damage has been found a hard landing has occurred.

Date .................................................

Signature ........................................




A109C-MPM

05-50-00

05-103

b. If a hard landing has occurred the following steps shall be complied with:

1) Remove and send to Agusta the following components for overhaulevaluation:

a) Main rotor hub assembly. . . . . . . . . . . . . . . .

b) Swashplate assembly. . . . . . . . . . . . . . . .

c) Main transmission assembly. . . . . . . . . . . . . . . .

d) Main transmission mount assemblies. . . . . . . . . . . . . . . .

e) Tail rotor drive shaft assemblies. . . . . . . . . . . . . . . .

f) Tail rotor (90°) gearbox and pitch change mechanism assembly. . . . . . . . . . . . . . . .

g) Tail rotor hub assembly. . . . . . . . . . . . . . . .

h) Engine-transmission drive shaft assemblies. . . . . . . . . . . . . . . .

i) Rotating and non rotating scissor assemblies. . . . . . . . . . . . . . . .

j) Main rotor pitch change link assemblies. . . . . . . . . . . . . . . .

k) Nose and main landing gear assemblies. . . . . . . . . . . . . . . .

l) Nose and main landing gear attachments. . . . . . . . . . . . . . . .

m) Main and tail rotor servo actuators. . . . . . . . . . . . . . . .

n) Nose and main landing gear actuators. . . . . . . . . . . . . . . .

o) Nose and main landing gear retraction mechanism. . . . . . . . . . . . . . . .

2) Inspect main rotor blades. . . . . . . . . . . . . . . .

3) Inspect tail rotor blades. . . . . . . . . . . . . . . .

4) Inspect tail skid tube for damage. Inspect tail boom internally andexternally for cracks, distortions, and loose rivets. Inspect the tail boomattachment points for elongated holes and damaged structure. . . . . . . . . . . . . . . .

5) Inspect airframe areas surrounding transmission, engine and landing gearattachment points for cracks, distortion and loose rivets. . . . . . . . . . . . . . . .

6) Inspect fuel tanks bays with particular attention to separation wall forcracks, distortions and damage. . . . . . . . . . . . . . . .

7) Check all cowlings and doors for proper fit, alignment and correctoperation. . . . . . . . . . . . . . . .

8) Completely inspect flight control systems, cyclic, collective, antitorque andelevator for bent or damaged tubes, bellcranks and supports for damagedbearings. . . . . . . . . . . . . . . .

9) Inspect fuel, oil and hydraulic systems for damage and leakage. . . . . . . . . . . . . . . .

10) Inspect engine mounts. . . . . . . . . . . . . . . .

11) Inspect engines in accordance with engine manufacturer’s manuals. . . . . . . . . . . . . . . .

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2. SUDDEN STOPPAGE MAIN ROTOR

Sudden stoppage is defined as any rapid deceleration of the drive system whether

caused by seizure within the helicopter transmission or by contact of the main rotor

blades with the ground or object of sufficient inertia to cause rapid deceleration.

a. If visible damage is evident, remove and send to Agusta the followingcomponents for overhaul evaluation:

1) Main rotor hub assembly. . . . . . . . . . . . . . . .

2) Swashplate assembly. . . . . . . . . . . . . . . .

3) Main transmission assembly. . . . . . . . . . . . . . . .

4) Main transmission mount assemblies. . . . . . . . . . . . . . . .

5) Tail rotor drive shaft assemblies. . . . . . . . . . . . . . . .

6) Tail rotor (90°) gearbox and pitch change mechanism assembly. . . . . . . . . . . . . . . .

7) Tail rotor hub assembly. . . . . . . . . . . . . . . .

8) Engine-transmission drive shaft assemblies. . . . . . . . . . . . . . . .

9) Rotating and non rotating scissor assemblies. . . . . . . . . . . . . . . .

10) Main rotor pitch change link assemblies. . . . . . . . . . . . . . . .

11) Engine-blower shafts. . . . . . . . . . . . . . . .

b. Inspect main rotor blades. . . . . . . . . . . . . . . .

c. Inspect tail rotor blades. . . . . . . . . . . . . . . .

d. Inspect engine mounts at fuselage attachment points for cracks. . . . . . . . . . . . . . . .

e. Inspect airframe areas surrounding transmission, engine and tail boom attach-ment points for cracks, distortions and loose rivets. . . . . . . . . . . . . . . .

f. Inspect main rotor servo actuators for evidence of damage and leakage. Removeand overhaul damaged components. . . . . . . . . . . . . . . .

g. Inspect blower assemblies for damage. . . . . . . . . . . . . . . .

h. Inspect engines in accordance with engine manufacturer’s manuals. . . . . . . . . . . . . . . .

3. SUDDEN STOPPAGE - TAIL ROTOR

a. Remove and replace tail rotor hub and blade assembly. Scrap removedcomponents. . . . . . . . . . . . . . . .

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b. Inspect the tail rotor drive shafts and adapters for cracks using the magneticinspection and eddy current method. Inspect the Thomas couplings fordeformation and fractures using a ten-power magnification lens. Inspect thebonds between tail rotor drive shaft and fittings for integrity. Visually inspectthe tail rotor supports and hanger bearings for cracks and distortion. If damageis found remove and send to Agusta the following components for overhaulevaluation: . . . . . . . . . . . . . . .




c. Inspect tail boom tail rotor (90°) gearbox attachment area and mounting sleevewith particular attention to studs and bolts. . . . . . . . . . . . . . . .

d. Inspect the four tail boom attachment points for cracks, distortions and security.Check torque of mounting bolts. . . . . . . . . . . . . . . .

e. Inspect the tail boom internally for cracks, distortions and loose and/or missingrivets. . . . . . . . . . . . . . . .

f. Inspect synchronized elevator for skin cracks and evidence of damage. . . . . . . . . . . . . . . .

g. Inspect lower fin for security and general condition. Check tail skid forcondition and security. . . . . . . . . . . . . . . .

h. Inspect engines in accordance with engine manufacturer’s manuals. . . . . . . . . . . . . . . .

4. OVERSPEED MAIN ROTOR

Overspeed is defined as any incident in which 115% main rotor RPM limits are

exceeded.

a. Remove and send to Agusta the following components for overhaul evaluation:


2) Tail rotor hub assembly. . . . . . . . . . . . . . . .

b. Closely inspect the following components:

1) Main rotor blades. . . . . . . . . . . . . . . .

2) Tail rotor blades. . . . . . . . . . . . . . . .


4) Main transmission mount assemblies. . . . . . . . . . . . . . . .




8) Engine-transmission drive shafts. . . . . . . . . . . . . . . .

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9) Engine-blower shafts. . . . . . . . . . . . . . . .

10) Blower assemblies. . . . . . . . . . . . . . . .


c. If no damage is found, the components may be retained in service.

5. OVERTORQUE

Overtorque is defined as any incident in which torsional loads are introduced into

helicopter dynamic system in excess of established limits.

a. Refer to engine manufacturer’s manuals for engine overtorque inspectionlimits. . . . . . . . . . . . . . . .

b. Single engine operation.

1) Remove and send to Agusta, for overhaul evaluation, main transmissionassembly P/N 109-0400-02-107 and the transmission drive shaft if thetorque:

a) Exceeds 118% for a period of more than 10 seconds. . . . . . . . . . . . . . . .

2) For main transmission assembly P/N 109-0400-03-105, remove andinspect, in accordance with Overhaul Manual, the interested freewheel ifthe torque:

a) Exceeds 118% for a period of more than 10 seconds. . . . . . . . . . . . . . . .

c. All engine operation.

1) Remove and send to Agusta for overhaul evaluation, main transmissionassembly P/N 109-0400-02-107 and the transmission drive shaft if torque:

a) Exceeds 100% but does not exceed 104% for a period of more than 5minutes. . . . . . . . . . . . . . . .

b) Exceeds 104% but does not exceed 118% for a period of more than 6seconds. . . . . . . . . . . . . . . .

c) Exceeds 118%. . . . . . . . . . . . . . . .

2) For main transmission assembly P/N 109-0400-03-105, remove andinspect, in accordance with Overhaul Manual, the freewheels if the torque:

a) Exceeds 118%. . . . . . . . . . . . . . . .

d. Perform a thorough visual inspection of the following components:

1) Main rotor blades. . . . . . . . . . . . . . . .

2) Tail rotor hub and blade assembly. . . . . . . . . . . . . . . .



A109C-MPM

05-50-00

05-107


5) Tail rotor drive shaft. . . . . . . . . . . . . . . .

6) Tail rotor drive shaft hangers. . . . . . . . . . . . . . . .



9) Engine-transmission drive shafts. . . . . . . . . . . . . . . .

e. If inspection does not reveal any discrepancies or obvious damage to compo-nents they may be retained in service. If evidence of damage is found, removeand evaluate for overhaul all components listed above. . . . . . . . . . . . . . . .

f. Inspect airframe area surrounding transmission, engine and tail rotor (90°)gearbox attachment points for cracks, distortions and loose rivets. . . . . . . . . . . . . . . .

6. ENGINE OVERSPEED, OVERTORQUE ANDOVERTEMPERATURE

If overspeed, overtorque or excessive temperatures occur, perform special inspec-

tions as outlined in engine manufacturer’s manuals. . . . . . . . . . . . . . . .

7. LIGHTNING STRIKE

When the helicopter is suspected of having been struck by a lightning strike, the

following precautionary measures, inspections and maintenance shall be accom-

plished:

a. Visually inspect all external surfaces of the helicopter with particular attentionto main rotor blades and hub, transmission assembly, tail rotor blades and hub,tail rotor (90°) gearbox and vertical fin. Check electrical instruments andsystems. Replace defective and/or damaged parts. . . . . . . . . . . . . . . .

b. Inspect engine in accordance with engine manufacturer’s manuals. . . . . . . . . . . . . . . .

c. If visual indications of damage are present proceed as follows:

1) Inspect main rotor blades. If blades show any of the following indications,scrap blades.

a) Inspect blades for signs of burns. Burn marks may be very minute. . . . . . . . . . . . . . . .

b) Inspect blades in bonded areas for voids. . . . . . . . . . . . . . . .

2) Remove and send to Agusta the following components for overhaulevaluation:

a) Main rotor hub assembly. . . . . . . . . . . . . . . .

b) Main transmission assembly. . . . . . . . . . . . . . . .

3) Inspect all rotating controls for indications of arcing or burning. . . . . . . . . . . . . . . .

a) Replace bearings that do not rotate smoothly. . . . . . . . . . . . . . . .

A109C-MPM

05-50-00

05-108


b) If evidence of arcing or burning is found or bearings do not rotatesmoothly, remove swashplate assembly and send to Agusta foroverhaul evaluation. . . . . . . . . . . . . . . .

c) Replace main and tail rotor pitch change links that have signs of arcingor burning, including attaching hardware. . . . . . . . . . . . . . . .

4) Remove and send to Agusta for overhaul evaluation the followingcomponents:

a) Tail rotor hub assembly. . . . . . . . . . . . . . . .

b) Tail rotor (90°) gearbox assembly. . . . . . . . . . . . . . . .

5) Inspect tail rotor (90°) gearbox attachment point areas for signs of arcingor burning. . . . . . . . . . . . . . . .

6) Inspect vertical fin for an for arcing or burning. . . . . . . . . . . . . . . .

d. If no indications of damage is found proceed as follows:

1) Inspect main rotor hub as follows:

a) Visually inspect bearings of drag, flap and pitch change hinges forsigns of arcing or burning. . . . . . . . . . . . . . . .

b) Check bearings for smoothness of rotation. . . . . . . . . . . . . . . .

c) If there is evidence of arcing or burning, or damaged bearings removemain rotor hub assembly and send to Agusta for overhaul evaluation. . . . . . . . . . . . . . . .

2) Remove main rotor hub assembly and visually inspect bearings for signs ofarcing and burning. Rotate bearing during inspection so that the entiresurface of each ball or roller is inspected.Check bearing for smoothness of rotation. Visually inspect lower bearingrace and driving spline on mast for signs of arcing and/or burning. . . . . . . . . . . . . . . .

a) If there is evidence of arcing and/or burning or damaged bearings,remove main transmission assembly and send to Agusta for overhaulevaluation. . . . . . . . . . . . . . . .

3) Visually inspect tail rotor (90°) gearbox shaft teeth for signs of arcing orburning. Check bearings for smoothness of rotation. . . . . . . . . . . . . . . .

a) If there is evidence of arcing and/or burning or damaged bearings,remove tail rotor (90°) gearbox assembly and send to Agusta foroverhaul evaluation. . . . . . . . . . . . . . . .

8. OPERATIONS IN HIGH CORROSIVE ENVIRONMENTS

If the helicopter operates in high corrosive environments such as marine atmo-

spheres, industrial pollution, agricultural sprays, corrosion soils, abrasive dust and

extreme temperatures refer to Section 20-40.

A109C-MPM

05-50-00

05-109



A109C-MPM

05-50-00

05-110

SECTION 05-60

OPTIONAL EQUIPMENT

For the optional equipment inspection requirements refer to the following list:

Installation number Denomination

1 Rotor brake

2 Environmental control system (ECS)

3 Bleed-air heater

4 Particle separator - engine air induction system

5 Auxiliary fuel tank

6 Flare launcher

7 Emergency floats

8 Snow skids

9 Engine compartment fire extinguishers

10 Emergency medical service (E.M.S.) (typical)

11 Landing search/light

12 Cargo hook

13 External hoist

14 Emergency locator transmitter EBC 102A or EBC 302H

15 Sliding doors

16 Doors enlargement ″A109 MAX II″

A109C-MPM

05-60-00

05-111


A109C-MPM

05-60-00

05-112

Dat

e...

......

......

......

......

......

......

......

......

.

Sign

atur

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AM

STA

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EN

DE

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ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

1.R

OT

OR

BR

AK

Ea.

Rot

orbr

ake

leve

rfo

rfr

eedo

mof

mov

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t;le

ave

hand

lein

forw

ard

lock

edpo

sitio

n.X

......

....

b.D

isc

flan

gesu

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tfo

rse

curi

ty.

XX

Phas

eC

......

....

c.R

otor

brak

elin

ings

for

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r.R

ef.

topa

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9.X

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ase

1...

......

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for

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s.X

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rfor

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XX

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......

....

05-60-00

05-113

A109C-MPM


A109C-MPM

05-60-00

05-114

Dat

e...

......

......

......

......

......

......

......

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AM

STA

ND

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EN

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ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

2.E

NV

IRO

NM

EN

TA

LC

ON

TR

OL

SYST

EM

(EC

S)a.

Ble

edai

rpi

pes,

rele

vant

join

tsan

dlin

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rco

nditi

onan

dse

curi

ty.

XX

Phas

eC

......

....

b.Pe

rfor

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iona

lte

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para

21-4

0-23

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ase

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......

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CIA

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LYE

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spec

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ger.

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Para

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....

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2E

AC

H60

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a.L

ubri

cate

the

turb

ine

blow

er.

Ref

.to

para

21-4

0-39

A.

......

....

05-60-00

05-115

A109C-MPM


A109C-MPM

05-60-00

05-116

Dat

e...

......

......

......

......

......

......

......

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TIO

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AM

STA

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AR

DE

XT

EN

DE

DP

RO

GR

ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

3.B

LE

ED

-AIR

HE

AT

ER

a.B

leed

air

pipe

s,re

leva

ntjo

ints

and

lines

for

cond

ition

and

secu

rity

.X

XPh

ase

C...

......

.b.

Perf

orm

oper

atio

nal

test

ofsy

stem

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ef.

topa

ra21

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24.

XX

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......

....

05-60-00

05-117

A109C-MPM


A109C-MPM

05-60-00

05-118

Dat

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......

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HM

EN

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INST

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TIO

NP

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AM

STA

ND

AR

DE

XT

EN

DE

DP

RO

GR

ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

4.PA

RT

ICL

ESE

PAR

AT

OR

-E

NG

INE

AIR

IND

UC

TIO

NSY

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icle

sepa

rato

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rco

nditi

onan

dse

curi

ty.

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ckej

ecto

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rob

stru

ctio

ns.

XX

X...

......

.

05-60-00

05-119

A109C-MPM


A109C-MPM

05-60-00

05-120

Dat

e...

......

......

......

......

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AM

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AR

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EN

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ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

5.A

UX

ILIA

RY

FU

EL

TA

NK

a.Fu

elfi

ller

cap

for

cond

ition

and

secu

rity

.X

XX

......

....

SPE

CIA

LIN

SPE

CT

ION

S

1.E

AC

H10

YE

AR

Sa.

Tank

and

inte

rnal

com

pone

nts

for

cond

ition

.Pe

rfor

mta

nkpr

essu

rete

st.

Ref

.to

para

28-1

0-14

.

......

....

05-60-00

05-121

A109C-MPM


A109C-MPM

05-60-00

05-122

Dat

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......

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......

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AM

STA

ND

AR

DE

XT

EN

DE

DP

RO

GR

ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

6.F

LA

RE

LA

UN

CH

ER

a.Su

ppor

tan

dfl

are

laun

cher

for

cond

ition

and

secu

rity

.X

XX

......

....

05-60-00

05-123

A109C-MPM


A109C-MPM

05-60-00

05-124

Dat

e...

......

......

......

......

......

......

......

......

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Sign

atur

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TIO

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RO

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AM

STA

ND

AR

DE

XT

EN

DE

DP

RO

GR

ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

7.E

ME

RG

EN

CY

FL

OA

TS

a.C

ylin

der

pres

sure

gaug

ere

adin

gin

acco

rdan

cew

ithdi

agra

mon

plac

ard

loca

ted

near

gaug

e.

XX

X...

......

b.E

lect

rica

lha

rnes

san

dco

nnec

tors

for

cond

ition

and

secu

rity

.X

XX

......

....

c.St

owed

floa

tsan

dpr

otec

tive

cove

rsfo

rco

nditi

onan

dcl

eanl

ines

s.X

XX

......

....

d.Fl

oats

and

fitti

ngfo

rco

nditi

onan

dse

curi

ty.

XX

X...

......

.

SPE

CIA

LIN

SPE

CT

ION

S

1.E

AC

HY

EA

R(f

rom

the

firs

tin

stal

lati

on)

a.Pe

rfor

mop

erat

iona

lte

stof

the

elec

tric

alci

rcui

ts.

Ref

.to

para

25-6

2-9.

......

....

b.In

spec

tth

efl

oats

and

pres

sure

bottl

es.

Ref

.to

para

25-6

2-13

....

......

.c.

Perf

orm

ale

akag

ete

stof

floa

ts.

Ref

.to

para

25-6

2-14

....

......

.

2.E

AC

H3

YE

AR

Sa.

Insp

ect

and

perf

orm

hydr

osta

ticte

stof

pres

sure

bottl

esw

hose

prev

ious

test

has

been

perf

orm

edbe

fore

1stJu

ly20

06.

......

....

CA

UT

ION

:T

hehy

dros

tatic

test

mus

tbe

perf

orm

edfo

llow

ing

DO

T-SP

8162

and

rule

s

prin

ted

onde

cal

inst

alle

don

bottl

e.

3.E

AC

H5

YE

AR

Sa.

Insp

ect

and

perf

orm

hydr

osta

ticte

stof

pres

sure

bottl

esw

hose

prev

ious

test

has

been

perf

orm

edaf

ter

1stJu

ly20

06.

......

....

CA

UT

ION

:T

hehy

dros

tatic

test

mus

tbe

perf

orm

edfo

llow

ing

DO

T-SP

8162

rule

spr

inte

d

onde

cal

inst

alle

don

bottl

e.

05-60-00

05-125

A109C-MPM


A109C-MPM

05-60-00

05-126

Dat

e...

......

......

......

......

......

......

......

......

.

Sign

atur

e...

......

......

......

......

......

......

....

Hel

icop

ter

Reg

istr

atio

nN

o....

......

...

Hel

icop

ter

Hou

rs...

......

......

......

......

...

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IAL

EA

CH

ITE

MA

FT

ER

AC

CO

MP

LIS

HM

EN

T

INST

AL

LA

TIO

N

INSP

EC

TIO

NP

RO

GR

AM

STA

ND

AR

DE

XT

EN

DE

DP

RO

GR

ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

SPE

CIA

LIN

SPE

CT

ION

S(C

ont.

)

5.E

AC

H15

YE

AR

Sa.

Rep

lace

floa

ts,

valv

esan

dpr

essu

rebo

ttles

.

NO

TE

:Fi

ftee

nye

ars

star

tfr

omth

em

anuf

actu

rer

date

onth

em.

......

....

05-60-00

05-127

A109C-MPM


A109C-MPM

05-60-00

05-128

Dat

e...

......

......

......

......

......

......

......

......

.

Sign

atur

e...

......

......

......

......

......

......

....

Hel

icop

ter

Reg

istr

atio

nN

o....

......

...

Hel

icop

ter

Hou

rs...

......

......

......

......

...

INIT

IAL

EA

CH

ITE

MA

FT

ER

AC

CO

MP

LIS

HM

EN

T

INST

AL

LA

TIO

N

INSP

EC

TIO

NP

RO

GR

AM

STA

ND

AR

DE

XT

EN

DE

DP

RO

GR

ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/Annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

8.SN

OW

SKID

Sa.

Snow

skid

s,fi

tting

san

dbu

ngee

cord

sfo

rda

mag

ean

dse

curi

ty.

XX

X...

......

.

05-60-00

05-129

A109C-MPM


A109C-MPM

05-60-00

05-130

Dat

e...

......

......

......

......

......

......

......

......

.

Sign

atur

e...

......

......

......

......

......

......

....

Hel

icop

ter

Reg

istr

atio

nN

o....

......

...

Hel

icop

ter

Hou

rs...

......

......

......

......

...

INIT

IAL

EA

CH

ITE

MA

FT

ER

AC

CO

MP

LIS

HM

EN

T

INST

AL

LA

TIO

N

INSP

EC

TIO

NP

RO

GR

AM

STA

ND

AR

DE

XT

EN

DE

DP

RO

GR

ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/Annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

9.E

NG

INE

CO

MPA

RT

ME

NT

FIR

EE

XT

ING

UIS

HE

RS

a.B

ottle

pres

sure

with

inlim

itssh

own

onre

leva

ntpl

acar

d.X

XX

......

....

b.In

dica

tor

disc

for

inte

grity

.X

XX

......

....

c.V

ent

tubi

ngfo

rob

stru

ctio

ns.

XX

X...

......

.

SPE

CIA

LIN

SPE

CT

ION

1.D

EL

ET

ED

......

....

......

....

2.E

AC

H6

YE

AR

Sa.

Rep

lace

cart

ridg

es.

NO

TE

The

retir

emen

tlif

eof

the

cart

ridg

e,w

hen

inst

alle

d,is

6ye

ars,

how

ever

the

tota

l

life

ofth

eca

rtri

dge

is9

year

s(c

ombi

natio

nst

ock

time

and

inst

alle

dtim

e).

......

....

3.E

AC

H5

YE

AR

Sa.

Perf

orm

hydr

osta

ticte

stof

bottl

es.

CA

UT

ION

:T

hehy

dros

tatic

test

mus

tbe

perf

orm

edfo

llow

ing

DO

Tru

les

prin

ted

on

deca

lin

stal

led

onbo

ttle.

......

....

05-60-00

05-131

A109C-MPM


A109C-MPM

05-60-00

05-132

Dat

e...

......

......

......

......

......

......

......

......

.

Sign

atur

e...

......

......

......

......

......

......

....

Hel

icop

ter

Reg

istr

atio

nN

o....

......

...

Hel

icop

ter

Hou

rs...

......

......

......

......

...

INIT

IAL

EA

CH

ITE

MA

FT

ER

AC

CO

MP

LIS

HM

EN

T

INST

AL

LA

TIO

N

INSP

EC

TIO

NP

RO

GR

AM

STA

ND

AR

DE

XT

EN

DE

DP

RO

GR

ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

10.

EM

ER

GE

NC

YM

ED

ICA

LSE

RV

ICE

(E.M

.S.)

(TY

PIC

AL

)a.

Supp

ort

stru

ctur

efo

rco

nditi

onan

dse

curi

ty.

XX

X...

......

.b.

Oxy

gen

cylin

ders

for

secu

rity

and

prop

erch

arge

indi

catio

n.X

XX

......

....

c.U

nion

san

dox

ygen

hose

sfo

rco

nditi

onan

dse

curi

ty.

XX

X...

......

.

SPE

CIA

LIN

SPE

CT

ION

S1.

EA

CH

3Y

EA

RS

a.Pe

rfor

mhy

dros

tatic

test

ofox

ygen

cylin

ders

....

......

.

CA

UT

ION

:T

hehy

dros

tatic

test

mus

tbe

perf

orm

edfo

llow

ing

DO

Tru

les

prin

ted

onde

cal

inst

alle

don

bottl

e.b.

Che

ckpr

essu

rere

duci

ngva

lve.

......

....

2.E

AC

H6

YE

AR

Sa.

Ove

rhau

lpr

essu

rere

duci

ngva

lve.

......

....

3.E

AC

H15

YE

AR

Sa.

Rep

lace

oxyg

enbo

ttle.

......

....

05-60-00

05-133

A109C-MPM


A109C-MPM

05-60-00

05-134

Dat

e...

......

......

......

......

......

......

......

......

.

Sign

atur

e...

......

......

......

......

......

......

....

Hel

icop

ter

Reg

istr

atio

nN

o....

......

...

Hel

icop

ter

Hou

rs...

......

......

......

......

...

INIT

IAL

EA

CH

ITE

MA

FT

ER

AC

CO

MP

LIS

HM

EN

T

INST

AL

LA

TIO

N

INSP

EC

TIO

NP

RO

GR

AM

STA

ND

AR

DE

XT

EN

DE

DP

RO

GR

ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

11.

LA

ND

ING

/SE

AR

CH

LIG

HT

a.L

andi

ng/s

earc

hlig

htfo

rco

nditi

onan

dse

curi

ty.

XX

X...

......

.

05-60-00

05-135

A109C-MPM


A109C-MPM

05-60-00

05-136

Dat

e...

......

......

......

......

......

......

......

......

.

Sign

atur

e...

......

......

......

......

......

......

....

Hel

icop

ter

Reg

istr

atio

nN

o....

......

...

Hel

icop

ter

Hou

rs...

......

......

......

......

...

INIT

IAL

EA

CH

ITE

MA

FT

ER

AC

CO

MP

LIS

HM

EN

T

INST

AL

LA

TIO

N

INSP

EC

TIO

NP

RO

GR

AM

STA

ND

AR

DE

XT

EN

DE

DP

RO

GR

ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

12.

CA

RG

OH

OO

Ka.

Che

ckop

erat

ion

ofem

erge

ncy

carg

ore

leas

esy

stem

.Lea

veho

okin

stow

edpo

sitio

n.R

ef.

topa

ra25

-90-

14.

XX

X...

......

.

b.C

argo

hook

com

pone

nts

and

elec

tric

alco

nnec

tions

for

cond

ition

and

secu

rity

.X

XX

......

....

c.R

earv

iew

mir

ror

for

dam

age,

clea

nlin

ess

and

secu

rity

.X

XX

......

....

d.C

argo

hook

supp

ortin

gfr

ame,

fitti

ngs

and

surr

ound

ing

fuse

lage

area

for

corr

osio

nan

d

dam

age.

XX

Phas

eC

......

....

05-60-00

05-137

A109C-MPM


A109C-MPM

05-60-00

05-138

Dat

e...

......

......

......

......

......

......

......

......

.

Sign

atur

e...

......

......

......

......

......

......

....

Hel

icop

ter

Reg

istr

atio

nN

o....

......

...

Hel

icop

ter

Hou

rs...

......

......

......

......

...

INIT

IAL

EA

CH

ITE

MA

FT

ER

AC

CO

MP

LIS

HM

EN

T

INST

AL

LA

TIO

N

INSP

EC

TIO

NP

RO

GR

AM

STA

ND

AR

DE

XT

EN

DE

DP

RO

GR

ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

13.

EX

TE

RN

AL

HO

IST

a.H

oist

com

pone

nts

for

cond

ition

,se

curi

tyan

dle

aks.

XX

X...

......

.b.

Ele

ctri

cal

conn

ectio

nsfo

rco

nditi

onan

dse

curi

ty.

XX

X...

......

.c.

Cab

lecu

tter

elec

tric

alco

nnec

tions

for

cond

ition

and

secu

rity

.X

XX

......

....

d.C

heck

hois

top

erat

ion

byre

elin

g-ou

tan

dre

elin

g-in

appr

oxim

atel

yon

em

eter

ofca

ble;

cabl

ean

dte

rmin

alfo

rco

nditi

onan

dse

curi

ty.

XX

X...

......

.

e.C

heck

oper

atio

nof

full-

inlim

itsw

itch.

XX

X...

......

.f.

Step

bar

prot

ectio

nfo

rco

nditi

onan

dse

curi

ty.

XX

X...

......

.g.

Ext

erna

lho

ist

mou

nt,

fitti

ngs

and

surr

ound

ing

fuse

lage

area

for

corr

osio

nan

dda

mag

e.X

XPh

ase

C...

......

.

SPE

CIA

LIN

SPE

CT

ION

S

1.A

FT

ER

TH

EL

AST

FL

IGH

TO

FT

HE

DA

Y(I

FU

SED

)a.

Aft

erth

ela

stfl

ight

ofth

eda

y,pe

rfor

min

spec

tion

spec

ifie

din

para

25-9

0-17

....

......

.

2.E

AC

H5

YE

AR

Sa.

Rep

lace

cabl

ecu

tter

cart

ridg

eof

exte

rnal

hois

t....

......

.

NO

TE

:Fi

veye

ars

star

tfr

omda

teof

cabl

ecu

tter

cart

ridg

em

anuf

actu

re.

05-60-00

05-139

A109C-MPM


A109C-MPM

05-60-00

05-140

Dat

e...

......

......

......

......

......

......

......

......

.

Sign

atur

e...

......

......

......

......

......

......

....

Hel

icop

ter

Reg

istr

atio

nN

o....

......

...

Hel

icop

ter

Hou

rs...

......

......

......

......

...

INIT

IAL

EA

CH

ITE

MA

FT

ER

AC

CO

MP

LIS

HM

EN

T

INST

AL

LA

TIO

N

INSP

EC

TIO

NP

RO

GR

AM

STA

ND

AR

DE

XT

EN

DE

DP

RO

GR

ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

14.

EM

ER

GE

NC

YL

OC

AT

OR

TR

AN

SMIT

TE

R

SPE

CIA

LIN

SPE

CT

ION

S

1.E

AC

H12

MO

NT

HS

a.In

spec

tat

tach

men

tsu

ppor

tfo

rco

nditi

onan

dse

curi

ty.

......

....

b.In

spec

tE

LTca

sean

dan

tenn

afo

rpr

oper

inst

alla

tion.

......

....

c.In

spec

tba

ttery

for

corr

osio

n....

......

.d.

Che

ckth

eop

erat

ion

ofco

ntro

lsan

dcr

ash

sens

or.R

efer

topa

ra25

-60-

39D

or25

-60-

39G

....

......

.

2.E

AC

H2

YE

AR

S(F

orE

LTP

/NE

BC

302H

)a.

Rep

lace

batte

ry.

......

....

NO

TE

:T

heba

ttery

has

tobe

repl

aced

inon

eof

the

follo

win

gca

ses:

−If

batte

ryis

expi

red

(see

date

onE

LTla

bel)

.

−A

fter

itha

sbe

enus

edin

emer

genc

y.

−A

fter

anac

cide

ntal

activ

atio

nof

unkn

own

dura

tion.

−A

fter

the

unit

has

been

intr

ansm

issi

onfo

rm

ore

than

1ho

ur.

NO

TE

:If

the

beac

onis

stor

edin

alo

catio

nw

here

the

aver

age

ambi

ent

tem

pera

ture

is

norm

ally

abov

e80

°F,

the

batte

rysh

ould

bere

plac

edsi

xm

onth

sso

oner

(for

ELT

P/N

EB

C10

2A).

05-60-00

05-141

A109C-MPM


A109C-MPM

05-60-00

05-142

Dat

e...

......

......

......

......

......

......

......

......

.

Sign

atur

e...

......

......

......

......

......

......

....

Hel

icop

ter

Reg

istr

atio

nN

o....

......

...

Hel

icop

ter

Hou

rs...

......

......

......

......

...

INIT

IAL

EA

CH

ITE

MA

FT

ER

AC

CO

MP

LIS

HM

EN

T

INST

AL

LA

TIO

N

INSP

EC

TIO

NP

RO

GR

AM

STA

ND

AR

DE

XT

EN

DE

DP

RO

GR

ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

15.

SLID

ING

DO

OR

Sa.

Pass

enge

rdo

ors

jetti

son

win

dow

(ext

erna

lly)

for

dam

age

and

secu

rity

ofw

indo

w.

Seal

reta

iner

for

inte

grity

and

corr

ect

posi

tion.

XX

X...

......

.

b.H

inge

dpa

nels

jetti

son

hand

lefo

rco

rrec

tpo

sitio

n.X

XX

......

....

c.Pa

ssen

ger

door

sje

ttiso

nw

indo

w(i

nter

nally

)fo

rda

mag

e,se

curi

ty;

reta

iner

and

fille

r

prop

erly

seat

ed.

Che

ckst

rap

isse

cure

d.

XX

X...

......

.

d.Pa

ssen

ger

door

sfo

rda

mag

e,se

curi

tyan

dco

rrec

top

erat

ion

oflo

ckin

gde

vice

san

d

mec

hani

cal

stop

s.

XX

X...

......

.

05-60-00

05-143

A109C-MPM


A109C-MPM

05-60-00

05-144

Dat

e...

......

......

......

......

......

......

......

......

.

Sign

atur

e...

......

......

......

......

......

......

....

Hel

icop

ter

Reg

istr

atio

nN

o....

......

...

Hel

icop

ter

Hou

rs...

......

......

......

......

...

INIT

IAL

EA

CH

ITE

MA

FT

ER

AC

CO

MP

LIS

HM

EN

T

INST

AL

LA

TIO

N

INSP

EC

TIO

NP

RO

GR

AM

STA

ND

AR

DE

XT

EN

DE

DP

RO

GR

ESS

IVE

Init

ial

Airworthinesscheck

100hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

25hour/30day

150hour/annual

600hour

2400hour

16.

DO

OR

SE

NL

AR

GE

ME

NT0A

109

MA

XII0

a.Pe

rfor

mop

erat

iona

lte

stof

mic

rosw

itche

sof

pass

enge

rdo

ors

open

syst

em.

XX

Phas

eC

......

....

05-60-00

05-145

A109C-MPM


A109C-MPM

05-60-00

05-146

SECTION 05-70

LUBRICATION AND SERVICING

The following table contains the lubrication and servicing intervals for items of the A109C helicopter model.

CAUTION FOR INFORMATION CONCERNING THE PRODUCTS USED AND THE LUBRICATIONAND SERVICING PROCEDURES REFER TO CHAPTER 12.

LEGEND

L : LUBRICATE

S : SERVICE

R : REPLACE

ItemOn

condition100hrs

300hrs

50 hrsor

3 months

100 hrsor

6 months

150 hrsor

12 months

300 hrsor

12 months

600 hrsor

24 monthsNote

N°1 hydraulic system reservoir S

N°2 hydraulic system reservoir S

Main rotor dampers (4 places) S S 1

Main rotor head reservoir (4 places) S R

Main transmission S R 2, 3

Tail rotor 90° gearbox S R

N°1 engine oil tank S 4

N°2 engine oil tank S 4

Main fuel tanks S

Auxiliary fuel tank S

Landing gear shock struts (3 places) S S S 5, 6

Landing gear tires (3 places) S S

Utility hydraulic system accumulators(2 places)

S S

Servo hydraulic system accumulators(2 places)

S

Main rotor swashplate L

Main rotor grips (4 places) L

Main rotor servo actuators (3 places) L

Tail rotor drive shaft bearings (7places).

L

Duplex bearing P/N 109-0133-05-101- Tail rotor pitch change mechanism

L

Duplex bearing P/N 109-0133-05-103- Tail rotor pitch change mechanism

L

NOTE 1: Every 300 hours service and bleed without removing damper from the helicopter.The above procedure must be performed regardless of the charge indicator position.

NOTE 2: Perform transmission oil level check after engines shut down without operating rotor brake.

NOTE 3: In addition to oil replacement, replace oil filter of main transmission.

A109C-MPM

05-70-00

05-147Rev. 1

NOTE 4: Refer to engine manufacturer’s manual for engine oil change schedule.

NOTE 5: Every 150 hours or 12 months service with nitrogen.

NOTE 6: Every 600 hours or 24 months service landing gear shock strut with hydraulic fluid.

A109C-MPM

05-70-00

05-148 Rev. 1

109c Faa Mpm

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