aircraft maintenance program...manual chapter 05, airworthiness directives, inspection service...

AIRCRAFT MAINTENANCE PROGRAM

EMBRAER ERJ135LR AND ERJ145MP


Copy # _________

EMERGENCY RESPONSE 24HR HOTLINE

+254 727 666 222

P.O.BOX 41937 – 00100 NAIROBI, KENYA

Physical Address:

ALS Limited | ALS Building | Wilson Airport | P.O. Box 41937 - 00100 | Nairobi |

Tel: +254 20 603 706 Fax: +254 20 607 185

Email: [email protected]|

Edition 006 ALS Section 1

Revision 000 AIRCRAFT MAINTENANCE PROGRAM Page 1

Issued 03June2015 EMBRAER ERJ135 AND ERJ145 AIRCRAFT

EMBRAER ERJ135LR AND ERJ145MP AIRCRAFT MAINTENANCE PROGRAM

Cover page

ALS /ERJ135 & ERJ145/LUMP/AMP EDITION 006 REV 000 03June2015

Document Ref: ALS /ERJ135 & ERJ145/LUMP/AMP

Aeroplane model: EMBRAER ERJ135 & ERJ145

Engine type: ROLLS ROYCE AE3007A1/3

APU TYPE AND MODEL: T‐62T‐40C14

AOC number: 58

Approved Maintenance Organization: ALS Ltd

Operator name and address: ALS Ltd, P.O. Box 41937‐00100, Nairobi, Kenya.

Copy No.: 001




Amendment Record

‘A’ – Amendments promulgated by KCAA.

REV NO

PAGES AFFECTED SUBJECT APPROVED BY / DATE

INSERTED BY / DATE

000 ALL PAGES Amendments as per SMRD

Temporary revisions 15‐3 to 15‐8.All pages affected through AMP editing and formatting.




“B” – Amendments raised by the Organization and approved by KCAA

REV NO

PAGES AFFECTED SUBJECT APPROVED BY / DATE

INSERTED BY / DATE




REVISION HIGHLIGHTS Retain all previous highlight pages in this manual for reference. Remove all affected pages and insert attached pages. Enter

revision no. and date inserted on Revision Record Sheet.

Chapter Sub‐Section Page Date Description

ALL ALL ALL 03 June 2015 Amendments as per SMRD Temporary revisions 15‐3

to 15‐8.All pages affected through AMP editing and

formatting.




REVISION HIGHLIGHTS (Cont’d) Retain all previous highlight pages in this manual for reference. Remove all affected pages and insert attached pages.

Enter revision no. and date inserted on Revision Record Sheet.

Chapter Sub‐Section Page Date Description




Distribution List

COPY NO MANUAL HOLDER DETAIL

001. KCAA‐Airworthiness Copy ‐ Paper

002. Central Library Master Copy

003. Managing Director Copy ‐ Server

004. Director of Maintenance Copy ‐ Server

006. Technical Director Copy ‐ Server

011. Quality Control Manager Copy ‐ Server

012. Base Maintenance Manager Copy ‐ Server

110. Line Maintenance, Khartoum Station Copy ‐ CD

111. Line Maintenance, Juba Station Copy ‐ CD

118. Line Maintenance, Niger Station Copy ‐ CD




OPERATOR INFORMATION

Register Name : ALS

Registered Address : Wilson Airport

Nairobi Kenya

East Africa

Aircraft Applicability : EMBRAER ERJ135 & ERJ145

Aircraft Registration : 5Y‐BVY, 5Y‐BVZ, 5Y‐CAV

Aircraft Serial Numbers : 145599, 145661, 145385

Operators Maintenance

Program Reference : ALS /ERJ135 & ERJ145/LUMP/AMP

Edition Number : 006

Revision Number : 000

Date : 03June2015

AIRCRAFT PARTICULARS

Aircraft Type : EMBRAER ERJ135 & ERJ145

Aircraft Manufacturer : EMBRAER

Aircraft Model : EMBRAER 145

Aircraft Serial Numbers : 145599, 145661, 145385

Engine Type : AE3007A1/3

Engine Manufacturer : ROLLS ROYCE

APU Type and Model : APS500R T‐62T‐40C14

APU Manufacturer : Hamilton Sundstrand




APPLICABILITY

This Maintenance program is applicable to the following aircraft operated by ALS Limited:

Manufacturer Model A/C REG. S/N ENGINES APU

EMBRAER

EMBRAER 135

5Y‐BVY 145599 AE3007A1/3

APS500R T‐62T‐

40C14

EMBRAER

EMBRAER 135

5Y‐BVZ 145661 AE3007A1/3

APS500R T‐

62T‐40C14

EMBRAER

EMBRAER 145

5Y‐CAV 145385 AE3007A1/3

APS500R T‐

62T‐40C14




Table of Contents

Section Section & Title Page

01 Title Page Nil

01 Approval Page 2

01 ‘A’ Amendments Record 3

01 ‘B’ Amendments Record 4

01 Revision Highlights 5

01 List of Effective Pages 7

01 Distribution List 15

01 Operator Information 16

01 Aircraft Particulars 16

01 Applicability 17

01 Table of Contents 18

02 GENERAL 1

02 1. Amendment program 2

02 2. Revision History 2

02 3. Operator Certification Statement 3

02 4. Applicability 4

02 5. Responsibilities and Standards 5

02 6. Certificate of Release to Service 5

02 7. Certifying Personnel Responsibilities 5

02 8. Airworthiness Life Limitations 6

02 9. Airworthiness Directives / Service Bulletin Procedure 6

02 10. KCAA Generic Requirements 6

02 11. Instructions for Continued Airworthiness 6

02 12. Changes (Modifications or Repairs) 6

02 13. Scheduled Maintenance Worksheets 6

02 14. Unscheduled maintenance 7

02 15. Reliability Program 7

02 16. Escalation or De‐escalation of Maintenance Time Intervals 7

02 17. Engine Condition Monitoring 8

02 18. Engine maintenance tasks scheduling 9

02 19. Duplicate inspections 11

02 20. Abbreviations 11

02 21. Maintenance Program, Check Cycle and Permitted Variation 15

02 22. Inspection Techniques 36

02 23. Task Codes 38

02 24. Parking, storage and Return to Service 39




02 25. Test flights 43

02 26. Maintenance Check Cycle 44

02 27. Permitted Variations 45

02 28. Scheduled Checks 46

03 LOW UTILIZATION PROGRAM 1

03 Introduction 1

03 1. Routine Inspection Requirements 5

03 2. Systems & powerplant inspection requirements 9

03 3. Structural inspection requirements 69

03 4. Corrosion prevention and control program (CPCP) 272

03 5. Zonal inspection requirements 323

03 6. National requirements 350

03 APPENDIX 1. Certification Maintenance Requirements 352

03 APPENDIX 2. Airworthiness Limitation Requirements (ALIS) 359

03 APPENDIX 3. CAT II maintenance requirements 363

03 APPENDIX 4. RVSM maintenance requirements 365

03 APPENDIX 5. CAT III maintenance requirements 366

03 Embraer recommended maintenance tasks 367

03 Embraer Structured Maintenance Program 374

03 48 Hours Tasks 378

03 Routine tasks 380

03 S1 tasks 384

03 S3 tasks 386

03 S6 tasks 390

03 S12 tasks 399

03 S18 tasks 408

03 S24 tasks 413

03 S36 tasks 437

03 S48 tasks 441

03 S60 tasks 529

03 S72 tasks 533

03 S96 tasks 549

03 S120 tasks 667

03 S144 tasks 682

03 S192 tasks 686

03 Prior winter tasks 719

03 Component limited tasks 721

04 AIRWORTHINESS LIMITATIONS REQUIREMENTS – LIFE LIMITED COMPONENTS 1




04 1. MRB Airworthiness Cycle Life Limit ‐ Landing Gear 3

04 2. MRB Airworthiness Limit ‐ Thrust Reverser 9

04 3. MRB Airworthiness Limit ‐ Components 11

05 ENGINES 1

05 1. General 2

05

2. EMM Scheduled Inspections ‐ Engine Systems and

Components 6

05 3. EMM Airworthiness Cycle Life Limits 9

06 KCAA INSPECTION REQUIREMENTS 1

07 ALS REQUIREMENTS 1




INTENTIONALLY LEFT BLANK



Issued 03June2015 ERJ 135LR AND ERJ 145MP AIRCRAFT


EMBRAER ERJ135LR AND ERJ145MP AIRCRAFT

SECTION 2

GENERAL




Amendment to the Program

1 Amendment Procedure 1.1 Revisions to this Maintenance Program will be prepared by ALS, based on the related

technical documents - namely the Maintenance Review Board Report (MRBR), Scheduled Maintenance Requirements Document (SMRD), Engine Maintenance Manual Chapter 05, Airworthiness Directives, Inspection Service Bulletins, and the Reliability analysis based on Engineering findings and the pilot Reports.

Revisions to the Inspection Program must be approved by the Kenya Civil Aviation Authority and shall not be incorporated into the Company’s Maintenance Program prior to KCAA approval.

Every amendments issue will include a list of highlights indicating significant changes. Each revision should be confirmed in the Record Sheet of Revision. Revision bars are located Right and adjacent to the affected text.

A yearly review will be undertaken to evaluate the effectiveness of the maintenance program as per the Maintenance Control Manual (MCM).

1.2 KCAA “A” amendments must be incorporated in the program without delay and recorded on the amendment record in the front of this book.

1.3 A new list of LEP will be issued following the AMP revisions.

2 Revision History EDITION # REVISION # EFFECTIVE DATE REASON 01 0 MAY 2008 INITIAL AMP 02 0 MAY 2010 INCORPORATE TC MRBR

REVISIONS AND RELIABILITY PROGRAM

03 0 MAY 2010 REPLACE NORMAL UTILIZATION WITH LOW UTILIZATION PROGRAM

04 0 FEB 2013 INCORPORATE TC MRBR REVISIONS AND APPLICABILITY

05 0 APRIL 2013 INCORPORATE ERJ145MP AIRCRAFT AND DELETE RELIABILITY PROGRAM

05 1 NOVEMBER 2013 INCORPORATE SMRD TR REVISIONS 15-2

06 0 JUNE 2015 ADD,DELETE AND EDIT TASKS AS PER SMRD PER SMRD /145-1150AND 1137 REV15.ALL PAGES HAVE UNDERGONE EDITORIAL AND FORMATTING OF AMP




4 APPLICABILITY:

This Maintenance program is applicable to the following aircraft operated by ALS Limited:

MANUFACTURER MODEL A/C REG

A/C S/N

ENGINES APU

EMBRAER ERJ135LR 5Y-BVY 145-599

3007A1/3 HAMILTON SUNDSTRAND APS5000R T-624T-40C14

EMBRAER ERJ135LR 5Y-BVZ 145-661

3007A1/3 HAMILTON SUNDSTRAND APS5000R T-624T-40C14

EMBRAER ERJ145MP 5Y-CAV 145-385

3007A1 HAMILTON SUNDSTRAND APS5000R T-624T-40C14




5 Responsibilities and Standards

5.1 Operator Responsibilities 5.1.1 The Operator is responsible for the aircrafts’ continuing airworthiness in accordance

with KCARS 2013.

5.2 Aircraft Maintenance Program Contents 5.2.1 This Aircraft Maintenance Program is drawn-up from:

• Embraer EMB135 Models and EMB 145 Models Maintenance Review Board Report MRB-145/1150, 16 December 1996 Revision 15 – 28 October 2011

• Embraer EMB135 Models and EMB 145 Models Scheduled Maintenance Requirements Document SMRD-145/1137, 16 December 1996 Revision 15 – 28 October 2011

• AE 3007A Series Maintenance Manual Publication Reference CSP34022 Revision Number 65 Dated 20 January 2013

6 Certificate of Release to Service 6.1 The CRS shall be issued by ALS limited Approved Maintenance Organization.

6.2 On completion of any of the program maintenance checks, a detailed, referenced entry is made in the relevant log books with an appropriate Certificate of Release to Service by certifying person.

6.3 The issue of a Certificate of Release to Service is indicative that all mandatory modifications and inspections have been complied with.

6.4 The Certificate of Release to Service is issued for the following categories:

Airframe category “A” Engine/propeller category “C” Electrical category “X” Instruments/compass/autopilot category “X”

Radio/avionics category “R”

7 Certifying Personnel Responsibilities 7.1 Certifying staff must have the appropriate training, skill and experience. They must

be conversant with the Company Maintenance Procedures and KCAR’s. They will have been given appropriate Authorizations by the Operators Quality Department to carry out Maintenance and to issue Certify Certificate of Release for Service for Scheduled Maintenance in the Categories required on the Certificate of Release to Service on the ERL135 and ERJ145 aircraft. The Authorizations will have been given in accordance with ALS Requirements as stated in the ALS Approved Maintenance Control Manual and listed in the Approved Maintenance Organisations List of Certifying Engineers.




A person approving the return to service of an aircraft or aircraft component after

any inspection performed in accordance with the Civil Aviation (Operation of Aircraft) Regulations shall make entries on the Certificate of Release to Service and or in the maintenance record of that equipment contained in Regulation 33 of the Civil aviation (Amo) Regulations.

7.2 Certifying persons must use their engineering skills and judgment in determining the depth of inspection needed and other matters, which would affect the airworthiness of the aircraft.

7.3 Certifying persons are responsible for recording in the appropriate log book or worksheet, any defect, deficiency or additional maintenance requirement, resulting from the implementation of the program and the issue of the CRS.

8 Airworthiness Life Limitations 8.1 Airworthiness life limits shall be those published by the state of design type

certificate holder and supplemental type certificate holder

9 Airworthiness Directives / Service Bulletin Procedure 9.1 Airworthiness directives and SB to be complied with shall be those issued by ANAC

(state of design of aircraft), FAA and the KCAA. The Procedure of acquisition and implementation is outlined on ALS MCM PART 3 SECTION 5

10 KCAA Generic Requirements 10.1 Forecasting and compliance with the CAA generic requirements shall be recorded in

the Log books.

11 Instructions for Continued Airworthiness 11.1 Instructions for continued airworthiness consists of in-service data published by the

type cert holder in maintenance manuals, service bulletins, service letters etc

12 Changes (Modifications or Repairs) 12.1 KCAA Approved changes, which have been carried out, must be recorded in the

appropriate Log books.

13 Scheduled Maintenance Worksheets 13.1 Worksheets shall be issued and each task signed off after work completion. These

worksheets become part of the maintenance records and must be kept in accordance with KCARS AOC regulation 18 by the operator.

13.2 Any additional maintenance carried out should be certified and suitably referenced scheduled maintenance worksheets and additional worksheets shall be cross-referenced and recorded in the certification areas of the KCAA log books giving




details of airworthiness directives, component changes, scheduled and any additional maintenance carried out.

14 Unscheduled maintenance 14.1 There are occasions which may arise during operations of the aircraft where special

un-programmed maintenance checks will be required dependent on specific circumstances. The range of un-programmed Maintenance Checks is intended to cover events which may normally be expected and are covered in Chapter 5 of the aircraft maintenance manual.

14.2 However, when other circumstances, not covered in Chapter 5 of the aircraft maintenance manual, are encountered, ALS AMO will consult with the ALS AOC who will contact the manufacturer and KCAA for alternate method of compliance.

14.3 If an inspection is required, it must be performed prior to further flight, unless a Special Flight Permit is issued to position the aircraft to a maintenance base where an in depth inspection can be made. All un-programmed events as listed in Chapter 5 have to be reported to KCAA and Manufacturer.

15 Reliability Program The Company has started the Reliability Section to implement fully the requirements of the Reliability Program Manual that has been established to meet the intents of the FAA Advisory Circular 120-17A and the KCAA advisory circular AC-AW010 and AOC Regulation 66 on the Aircraft Maintenance Program (AMP). The Regulations requires that a reliability program be established for aircraft with a maximum takeoff mass above 13,310 Kg. The method for data collection, analysis, corrective actions and reporting specified for the implementation of this program is prescribed in the Maintenance Control Manual, and the Reliability Program Manual which constitutes part of this Approved Maintenance Program.

16 Escalation or De-escalation of Maintenance Time Intervals The time limits shown in the Maintenance Program may be escalated and/or de-escalated in accordance with the Embraer 135LR and 145MP AMP as approved by the KCAA. In addition, the Company may request approval to escalate or de-escalate the time limits of individual tasks based on operating experience and results of the analysis as per the ALS Reliability Program Manual for all aircraft on ALS AOC, supplemented by data from the Company and as approved by the KCAA. Where a task interval is de-escalated, the task will be carried out within the new task repeat interval from the effective date of the Inspection Program revision. However the task must be completed prior to the pre-revision task accomplishment deadline.

NOTE: THESE GUIDELINES DO NOT APPLY TO AIRWORTHINESS LIMITATIONS TASKS, AIRWORTHINESS DIRECTIVES OR LIFE LIMITED PARTS/COMPONENTS WHICH ARE MANADATORY AND CANNOT BE CHANGED, ESCALATED, OR DELETED WITHOUT THE CONSENT OF THE MANUFACTURER AND APPROVED BY THE KCAA.




17 ENGINE CONDITION MONITORING The 3007A series engines are designed to be engines with NO FIXED OVERHAUL PERIOD.

In order to monitor the Engine Condition certain inspections need to be carried out.

17.1 Engine Condition Trend Monitoring is essential to monitor the engines performance trend to assess rapid or gradual decline in performance and to determine when and what maintenance action are to be carried out to restore the engines performance. Engine Performance parameters are continually being monitored and recorded during flight operations and any parameter exceedance alerts recorded and reviewed after flight.

Engine Trend Analysis is done with the Compass Navigator Trend Program. Data automatically recorded by the CMC is downloaded from the aircraft through RS 323 Serial cable to a computer installed with the DAS (Data Acquisition Software).

The file is e-mailed to Pieter-Prins @Rolls-Royce.com, and is then processed through the Compass Navigator Trend Program to perform Engine Trend Analysis.

Engine performance trending is used to monitor engine performance characteristics such as performance level changes, both gradual and step, and provides the operator with an approximate level of engine performance. Critical engine parameter exceedances are also recorded and stored. Performance trend data download should be accomplished within the prescribed interval.

Instructions on how to download the data from the Central Maintenance Computer is contained in the Aircraft Maintenance Instructions.

Instructions on the use of trend programs are contained in the Help files of the program.

Additionally, if directed by a Rolls-Royce Service Bulletin, manual trend data recording can be performed by the Flight Crews. This manual trend data is then processed through the Compass Navigator Trend Program.

Maintenance actions to address the performance level changes are to be initiated within a maximum of 14 calendar days from the performance trend data download. Certain trend changes may require a shorter period to apply specific maintenance action as directed by the manufacturer.

Maintenance actions are to be performed in accordance with the published engine maintenance instructions. The manufacturer is to be requested for recommendations if need be.

The recommended minimum margins for the AE 3007A Series Engines with Compass Version 2.5 and higher is 0.0 for ITT and N2. Environ mental conditions may allow continued operation without exceeding performance limitations.

To establish a trend monitoring program a minimum configuration is required as follows:




1. Aircraft Configuration Items:

- EICAS 17 or higher, Ref. Embraer Service Bulletin 145-31-0020

- CMC 9 or higher, Ref. Embraer Service Bulletin 145-45-0002

2. CMC Download Software

- CMC Download Software

- DAS Software Version DAS-017 or higher, compatible with CMC installed.

3. Compass Navigator Trend Program

- Version 2.5 or higher.

17.2 Engine FADEC control and sensing parameters are actively monitored and faults displayed through the EICAS and the Engine Indicating Display system which requires maintenance actions to be carried out with varying priorities.

FADEC Faults Annunciated by an EICAS Message Time Limited Dispatch Categories: Rolls-Royce EMM TASK 05-14-00-800-802 gives the time limited dispatch (TLD) intervals for fault bits set by the full –authority digital electronic control (FADEC) for the AE3007A Series engine with phase B 4.2 software and subsequent. The phase B 4.2 software and subsequent is used with EICAS 16 or higher and CMC 9igher. Each of the messages can e set by more than one FADEC fault bit. Inspection for the messages is to be carried out as per RR EMM TASK 73-25-10-200-801. Time Limited Dispatch (TLD) categories and Dispatch Interval Messages: ND- No Dispatch, Maintenance must be performed before the aircraft can be dispatched for a flight ST – Short Term Dispatch, Not to exceed 150 FH LT – Long Term Dispatch, Not to exceed 500 FH- or Scheduled Maintenance Inspection NLOTC – No Loss of Thrust Control Recommended not exceeding 120 Calendar Days. NOTE: The Maintenance must be done in the specified time interval from the first time the fault occurred as recorded by the stamp in the CMC.

1. Oil system contamination checks (Chip Detectors –Mag Plugs) are carried out on regular basis to monitor engine internal condition.

2. Mandatory inspections are to be carried out on the engine piece parts, if as a result of the foregoing inspections noted in 1 to 3 here above, the engine is showing any abnormality and has to be physically inspected on Gas Path components to detect deterioration or damage to the rotating parts especially front end and around the high temperature turbine sections.

18. ENGINE MAINTENANCE TASKS SCHEDULING

Task-oriented Scheduled Maintenance




The AE 3007A Series engines maintenance program is based on scheduled maintenance inspection intervals. The Embraer MBBR adopts most of the Rolls-Royce Scheduled Inspection Tasks, where there is duplication, the MRBR engine tasks prevail, as these are operating in an Embraer Airframe.

CAUTION: IN ORDER TO DECREASE THE POTENTIAL FOR MULTIPLE ENGINE INFLIGHT SHUTDOWNS, POWER LOSS, OR OTHER ANOMALY BECAUSE OF MAINTENANCE ERROR, ROOLYS-ROYCE RECOMMENDS THAT OPERATORS PREVENT THE NEED FOR MAINTENANCE ON MULTIPLE ENGINES INSTALLED ON THE SAME AIRCRAFT AT THE SAME TIME. IF IT IS NOT POSSIBLE TO PREVENT MAINTENANCE AT THE SAME TIME, ROLLS-ROYCE RECOMMENDS THAT MORE CONTROLS ARE APPLIED IN ORDER TO MAKE SURE THAT MAINTENACE TASKS HAVE BEEN COMPLETED AS DEFINED. STAGGER WILL BE USED AND OR DIFFERENT ENGINEERS USED IN THE MAINTENANCE OF THE PARALLEL SYSTEMS.

Other Engine Inspections and Mandatory Retirement Schedules come from the RR EMM Chapter 05.

Notes:

A/ If, as a result of an inspection, it is necessary to remove or disassemble the engine, its modules, or components, the engine condition and performance data will be reviewed and used to determine if additional preventative and/or corrective maintenance is necessary before installation or assembly of the engine, the module, or the component.

B/ Mandatory Inspections are applicable at each piece part opportunity for those that have accumulated 100 Cycles or more, as per AE 3007A RR EMM Task 05-13-00-800-801.

Contact the Rolls-Royce representative, if necessary.

Maintenance schedules for the AE 3007A Series Engines is drawn from the following documents:

Compliance with Airworthiness Limitations RR EMM Chapter 05-10-00

Recommended Scheduled Inspections RR EMM Chapter 05-20-00

Recommended Unscheduled Inspections RR EMM Chapter 05-50-00

19 Duplicate inspections 19.1 Flight control systems and engine control systems:

If, as a result of the application of this maintenance Program, any part of either the main or any associated system(s) is dismantled, adjusted, repaired or renewed, that part of the system(s) which has been disturbed shall be subjected to a duplicate




inspection for free movement, range, direction and tension checks and shall be appropriately certified

19.2 Landing gear "emergency" control system:

If a result of the application of this maintenance Program any part of the main or nose landing gear "emergency" or "free fall" control system or any associated system(s) which has been disturbed shall be subjected to a duplicate inspection for free movement, range direction and tension checks and shall be appropriately certified.

• Installation and repair of major structural components. • Installation of aircrafts engines. • Calibration or rigging of components such as engines, navigation equipment

and gearboxes.

20 Abbreviations The following abbreviations are used throughout the AMP.

Abbreviation Meaning Abbreviation Meaning AC Advisory Circular CAA Civil Aviation Authority

(United Kingdom) ACO Aircraft Certification

Office CAAC Civil Aviation

Administration of China

AD Accidental Damage CCMR Candidate Certification Maintenance Requirements

ADC Air Data Computer CMR Certification Maintenance Requirements

AFCS Automatic Flight Control System

CPCP Corrosion Prevention and Control Program

AHRS Altitude and Heading Reference System

CTA Centro Tecnico Aeroespacial

AMTOSS Aircraft Maintenance Task Oriental Support System

CVR Cockpit Voice Recorder

ANAC Agencia Nacional De Aviacao Civil

DAC Departmento De Aviaco Civil (Brazil)

AOA Angle Of Attack DAU Data Acquisition Unit APU Auxiliary Power Unit DG Directional Gyro ASSY Assembly DPI Differential Pressure

Idicator




Abbreviation Meaning Abbreviation Meaning ATA Air Transport

Association DRC Data

Recording/Calculating ATS Air Turbine Starter DRT Discard/Replace Task BITE Built-In Test

Equipment DSM Design Standards

Manual EASA European Aviation

Safety Agency GPU Ground Power Unit

ECS Environmental Control System.

GPWS Ground Proximity Warning System

ED Environmental Deterioration

GVI General Visual Inspection

EGPWS Enhanced Ground Proximity Warning System

HIRF High Intensity Radiated Field

EICAS Engine Indication and Crew Alerting System

HLEIS High Level Exceeding Indication System

ELT Emergency Locator Transmitter

HP High Pressure

EMB Embraer HLEIS High Level Exceeding Indication System

EMDP Engine Motor Driven Pump

HP High Pressure

FAA Federal Aviation Administration

HPT High Pressure Turbine

FADEC Full Authority Digital Engine Control

HYD Hydraulic

FAR Federal Aviation Regulation

IRS Inertial Reference System

FC Flight Cycle IRU Inertial Reference Unit FCOC Fuel Cooled Oil Cooler ISC Industry Steering

Committee FCU Fuel Conditioning Unit JAA Joint Aviation

Authorities (Europe) FD Fatigue Damage JAR Joint Airworthiness

Requirements (Europe FDA Fatigue Damage

Analysis KCAA Kenya Civil Aviation

Authority FDMU Flap Drive Motor Unit KCAR Kenya Civil Aviation

Regulation FDR Flight Data Recorder L/HIRF Lightning/High

Intensity Radiated Field

FFS Flap Flexible Shaft LCU Level Control Unit FH Flight Hour LG Landing Gear FPMU Fuel Pump and

Metering Unit LH Left Hand

FQIS Fuel Quantity Indicating System

LP Low Pressure




Abbreviation Meaning Abbreviation Meaning FSA Flap Screw-Jack

Actuator LPT Low Pressure Turbine

FSL Fuel System Limitation MEL Minimum Equipment List

FWD Forward MFD Multi-Function Display Abbreviation Meaning Abbreviation Meaning MFR Manufacturer SFAR Special Federal

AviationRegulation MLG Main Landing Gear SMRD Scheduled

Maintenance Requirements Document

MLGB Main Landing Gear Bay SPS Stall Protection System MMEL Master Minimum

Equipment Llist SRM Structural Repair

Manual MPD Maintenance Planning

Document SSA System Safety

Assessment MPG Maintenance Planning

Guide SSI Structural Significant

Item MRB Maintenance Review

Board SVC Service Check

MRBR Maintenance Review Board Report

SWG Structural Working Group

MRBRP Maintenance Review Board Report Proposal

SYS System

MSG Maintenance Steering Group

TAI TAI

MSI Maintenance Significant Item

TAT Thermal Aanti-Tce

MTB Motor Transmission Break

TBD TBD

MTBF Mean Time Between Failures

MTBUR Mean Time Between Unscheduled Removal

TBO TBO

MWG Mechanical Working Group

TBR TBR

NAA National Aviation Authority

TC TC

NDI Non-Destructive Inspection

TCAG Transport Canada Aviation Ggroup

NDT Non-Destructive Testing

TCS Touch Control Steering

NLG Nose Landing Gear TR Temporary Revision P/N Part Number VCK Visual Check




Abbreviation Meaning Abbreviation Meaning PCA Power Control

Actuator SB Service Bulletin

PCU Power Control Unit SDI Special Detailed Inspection

PMI Principal Maintenance Inspector

VFCU Ventral Fuel Conditioning Unit

PPH Policy and Procedures Handbook

VFQIS Ventral Fuel Quantity Indicating System

PWG Powerplant Working Group

VHLEIS Ventral High Level Exceeding Indication System

R&M Reliability and Maintainability

VLCU

Ventral Level Control Unit

RBHA Requisito Brasileiro De Homologacao Aernautica

VLLS

Ventral Low Level System

RH Right Hand WG

Working Group

RMU Radio Magnetic Unit WOW

Weight –On-Wheels

RTCA Radio Technical Commission for Aeronautics

YR

Year

RVSM Reduced Vertical Separation Minimum

ZWG Zonal Working Group




21 Maintenance Program, Check Cycle and Permitted Variation

21.1 Maintenance Program

This maintenance program is based on the EMB145 Maintenance Review Board Report (MRB Report) and the EMB145 Scheduled Maintenance Requirements Document (SMRD). The MRB Report has been developed according to FAA Advisory Circular AC 121-22A and Air Transport Association (ATA) MSG-3 Revision 2 document dated September 12, 1993. The initial issue of the MRB Report is based on an anticipated average annual utilization from 2000 to 2700 flight hours and a cycle rate of 1 FC/1.12 FH was assumed. Operators with yearly utilization, less than 1500 FH, shall consult Embraer in order to establish an appropriate scheduled maintenance program to submit to the Regulatory Authority. The EMB145 Scheduled Maintenance Requirements Document (SMRD) section VI gives the Low Utilization Program. This contains a list of all SMRD 1137 (Part I and Part II, maintenance requirements with adequate intervals to cover FAR 91 and FAR 135 operations at any yearly utilization and FAR 121 operating up to 1500 Flight Hours per year. This AMP is prepared using this section of the SMRD as ALS Embraer Aircraft projected annual utilization is below 1500 Flight Hours per year. The missing items from the SMRD low utilization, that is the requirements of the SMRD Part I (MRBR 1150) Appendix A2 (Airworthiness Limitations Requirements) item A2.2 (Life Limited Components) and the requirements from the SMRD Part II (SMRD 1137) section VII (Embraer – Optional Tasks) have been included in the AMP. 22.2 Line Maintenance Checks These higher inspections are supported by the following lower check, that is the Line Maintenance Checks. 21.2 The Pilot Pre Flight Checks The Pre flight checks: Tasks to be accomplished prior to each flight. The preflight check has to be performed at the ramp not earlier than two hours before take-off. It consists of general servicing and visual checks for general condition from the ground level. Preflight checks are not required to be performed in conjunction with a Routine Check or letter inspection. 21.3 The Daily Checks and Inspections: Tasks to be accomplished every 24 hours elapsed time. 21.4 The Weekly Checks and Inspections: Tasks to be accomplished every 7 calendar days ( 168 hours elapsed time). The calendar time as mentioned above is the time period between first “off –block” after weekly ( or higher Programmed maintenance check) and the last “ON-BLOCK” before next weekly check.




21.2.1 Pre Flight Check List

The Pre flight check which is also known as the external safety inspection must be carried out prior to the first flight of the day or whenever the crew-airplane combination changes. When approaching the airplane, take time to watch the area where the airplane is parked and ensure there is enough room for the taxi-out or push back maneuver. In addition, make sure that there will be enough clearance throughout the maneuver.

Task Action Performed By Wheel Chocks In Place External Lights Maintenance personnel should make the external lights check. If necessary flight crew should perform the external lights test, turning the lights ON, and then OFF immediately after checking them.

As required

Emergency/Parking Brake On The recommended work-around sequence; Left FWD Fuselage

Task Action Performed By

Access Doors and Panels Secured Static Ports Particular attention should be paid to the condition of static sources and to the marked area on the fuselage skin near each primary static source.

No Obstruction

Sensors and Pitot Tubes Condition, No Obstruction




Nose Section

Task Action Performed By Windows Condition, Clean and

Undamaged

Windshield Wipers Condition Air Inlets No Obstruction Radome Secured Nose Gear Check if the nose wheel position indication mark is within the nose wheel position indication scale limits.

Check

Wheels and Tires Tires should not be worn past the bottom of the tire grooves.

Condition

Gear Struts/ Wheel Well/ Doors Condition, No Leaks Gear Uplock Hook If the uplock hook is in the LOCKED position, cycle the freefall lever to reposition the uplock to the UNLOCKED position.

Unlocked

Ground Locking Pin Removed Static Discharger Check that the static discharger touches the ground.

Condition

Landing and Taxi Lights Condition, Undamaged

Right FWD Fuselage

Task Action Performed By Hydraulic Compartment (Right side) No Leaks

Oxygen Disc and Recharging Panel (Right side) Check oxygen overpressure green disc in place.

Check

Static Ports, Sensors and Pitot Tubes Condition, No Obstruction Forward Service Door (If applicable) If not in use, Visibly secured Access Doors and Panels Secured Fueling Compartment Door Secured Inspection Lights Condition, Clean and Undamaged

Air Inlets and Outlets No Obstruction and Undamaged Red Beacon Clean and Undamaged Antennas Undamaged Ram Air Inlets No Obstruction and Undamaged

Fluid Drain Holes No Leaks Landing and Emergency Lights Clean and Undamaged




Right Wing

Task Action Performed By Wing Leading Edges Condition Access Doors and Panels Secured Direct Measuring Sticks Pushed In and No Leaks Air Inlets, Outlets and Vents No obstruction and Undamaged Vortilons and Vortex Generators Number and Condition Navigation and Strobe Lights Clean and Undamaged Static Dischargers Number and Condition Flight Control Surfaces and Fairings Flaps must be retracted and spoilers closed.

Surfaces clear and unobstructed

Right Main Gear

Task Action Performed By Wheels and Tires Verify tire pressure (If applicable)

Condition

Main Gear Up Lock Hook If the uplock hook is in the LOCKED position, cycle the freefall lever to reposition the uplock to the UNLOCKED position. Carry out this procedure with pins in place.

Unlocked

Gear Struts/Wheel Wells Condition, No leaks Ground Safety Pin Removed Brake Wear Indicators Check Right AFT Fuselage


Air Inlets and Outlets No Obstruction and Undamaged

Antennas Undamaged Pylon Undamaged Engines Check engines for leaks and obstructions in the air inlets.

Check

Thrust Reverser Doors Flush with Nacelle Access Doors and Panels Secured




Tail Section

Task Action Performed By Horizontal Stabilizer Surfaces clear and unobstructed Logo Lights Clean and undamaged Flight Control Surfaces Surfaces clear and unobstructed Static Dischargers Number and Condition APU Condition Left AFT Fuselage

Task Action Performed By Baggage Door (Lock Panel Closed) Latched Pressurization Static Ports No Obstruction and

undamaged

Air Inlets and Outlets No Obstruction and Undamaged

Antennas Undamaged Pylon Undamaged Engines Check engines for leaks and obstructions in the air inlets.

Check

Thrust Reverser Doors Flush with Nacelle Access Doors and Panels Secured Left Main Gear

Task Action Performed By Wheels and Tires Verify tire pressure (If applicable)

Condition

Main Gear Up Lock Hook If the uplock hook is in the LOCKED position, cycle the freefall lever to reposition the uplock to the UNLOCKED position. Carry out this procedure with pins in place.

Unlocked

Gear Struts/Wheel Wells Condition, No leaks Ground Safety Pin Removed Brake Wear Indicators Check




Left Wing

Task Action Performed By Flight Control Surfaces and Fairings Flaps must be retracted and spoilers closed.

Surfaces clear and unobstructed

Access Doors and Panels Secured Direct Measuring Sticks Pushed In and No Leaks Air Inlets, Outlets and Vents No obstruction and

Undamaged

Vortilons and Vortex Generators Number and Condition

Navigation and Strobe Lights Clean and Undamaged Static Dischargers Number and Condition

Wing Leading Edges Condition Left FWD Fuselage

Task Action Performed By Landing and Emergency Lights Clean and Undamaged Ram Air Inlets No obstruction and Undamaged




21.2.2 Internal Safety Inspection

Task Action Performed By Airplane Manuals and Documents On Board Cockpit Emergency Equipment Check for the availability, status and proper location of the following equipment: - Escape ropes; - Oxygen masks; - Smoke goggles; - Portable Breathing Equipment (PBE); - Fire extinguishers; - Crash Axe; - Flashlights; - Life vests

Check

Reinforced Cockpit Door Vent Louver (if applicable)

Open

Circuit Breaker Panels Verify all circuit breakers IN at the overhead panel, behind the CPT seat and behind the F/O seat. If any CB is pulled verify the reason for it and if there is any operational implication advise the other pilot.

Check

Switches and knobs on the overhead panel must be set as follows:


Generators In GPU Out APU GEN In BATT 1 & 2 Off Essential Power Guarded Out Bus Ties and Shed Buses Shed Buses must be set to OVRD to operate the recirculation fans when the electrical system is energized by the APU generator.

Auto

AC Power In Back-Up In Avionics Master 1 & 2 Out Emergency Lights Off Fire Extinguishing Handle 1 In Fuel Crossfeed Off




Pump Power 1 & 2 Off ICU Panel Out Exterior Lights Off APU Fire Extinguishing Guarded Out APU Master Off APU Fuel Shutoff Guarded Out Ignitions Auto Start/ Stop Selectors Stop Fire Extinguishing Handle 2 In Ailerons & Rudders Shutoff In Engine Pump Shutoff Guarded Out Electric Hydraulic Pumps Off Windshield Heating Off Sensors In Ice Protection Buttons In Ice Detection Override Knob Auto Recirculation & Gasper In Packs 1 & 2 Out Engine & APU Bleed Out Windshield Wipers Off Logo Light Off Dome Light As required Pax Signs Off Switches on the main panel must be set as follows:


ELT Armed AHRS Set

MFD Reversion Normal

ADC, AHRS, SG Reversion Out

DAU 1 & 2 Out




Other mandatory tasks must be set as follows;

Task Action Performed By Radar Off Gear Lever Down Crew Oxygen Make sure that the Shutoff/Regulator Valve is in the ON position.

On

Passenger Oxygen Auto Gust Lock Locked CAUTION: NEVER MOVE CONTROL SURFACES SUCH AS FLAPS AND SPOILERS WITHOUT FIRST MAKING SURE THAT THE AREA IS CLEAR.

Task Action Performed By Speed Brake Closed Emergency/Parking Brake If the airplane is to be pushed back for start and if start is to be performed with the APU, the crew may leave the parking brake released as long as the chocks are in place.

On

Flaps Selector Lever Make sure that the selected position is consistent with the position observed during external inspection. If not, be aware that, once the airplane is energized, if the handle is lifted from the detent, the flaps will move to the commanded position.

Up

Free Fall Lever Compartment The OVERRIDE switch must be in the NORMAL position and guarded. The FREE FALL lever must be full down.

Check




Airplane Power Up APU Start With Batteries

Task Action Performed By Internal Safety Inspection Complete Batteries 1 & 2 Immediately after the batteries are switched ON the aural message “AURAL UNIT OK” can be heard.

Auto

Avionics Master 1 or 2 On Batteries Voltage If battery voltage is below 19 V it must be replaced. If battery voltage is below 24 V report to the maintenance personnel or recharge the affected battery by using the APU generator. In case of recharging, it is recommended that battery 1 be turned OFF before APU start. After APU start wait 3 minutes then select battery 1 to AUTO. The minimum time for battery recharging is 30 minutes.

Check

Backup Battery (EMB-145 XR only) Release the Backup Battery Button momentarily and check if ISIS remains operating normally.

Check

Avionics Master 1 & 2 Once the battery charge is checked, Avionics Master 1 & 2 must be switched OFF before starting the APU.

Off

PUMP PWR Select one of the TANK 2 electric fuel pumps and switch the Pump Pwr Tank 2 to on. However, if TANK 1 has more fuel than TANK 2, use XFEED and select one of the TANK 1 pumps plus the Pump Pwr Tank 1 instead.

On

Fire Detection Check APU Master On/ Wait 3

Seconds/ Start/ Then On

Avionics Master 1 & 2 On APU Bleed (After 3 minutes) Open Air Conditioning As required




APU Start With GPU


Auto

Avionics Master 1 or 2 On Batteries Voltage Check battery voltage on MFD. If battery voltage is below 19 V it must be replaced. If battery voltage is below 24 V report to the maintenance personnel or recharge the affected battery by using the APU generator. In case of recharging, it is recommended that battery 1 be turned OFF before GPU disconnection. After GPU disconnection wait 3 minutes then select battery 1 to AUTO. While GPU is ON, batteries will not be recharged. The minimum time for battery recharging is 30 minutes.

Check

GPU Voltage Check the ELEC page on the MFD if voltage is within 28.0 V (-2.0 V +1.0 V).

Check

Avionics Master 1 & 2 Off GPU When the GPU switch is selected, the “GPU AVAIL” message on it goes off and its yellow stripe lights up.

On

PUMP PWR Switch on one of the TANK 2 electric fuel pumps. However, if TANK 1 has more fuel than TANK 2, use XFEED and switch one of the TANK 1 pumps instead.

On

Fire Detection Check

APU Master On/ Wait 3 Seconds/ Start/

Then On

GPU Off

Avionics Master 1 & 2 On

APU Bleed (After 3 minutes) Open

Air Conditioning As required




GPU Power (No APU)


Auto

Avionics Master 1 or 2 On Batteries Voltage If battery voltage is below 19 V it must be replaced. If battery voltage is below 24 V report to the maintenance personnel or recharge the affected battery by using the generators. In case of recharging, it is recommended that battery 1 be turned OFF before GPU disconnection. After GPU disconnection wait 3 minutes then select battery 1 to AUTO. While GPU is ON, batteries will not be recharged.

Check

GPU Voltage Check the ELEC page on the MFD if voltage is within 28.0 V (-2.0 V +1.0 V).

Check

GPU When GPU button is selected, the “GPU AVAIL” message on it goes off and its yellow stripe lights up.

On




21.5 Time Controlled Maintenance There are several items which do not fit into the Calendar inspection program. These items will be tracked individually and referred to as out of Phase items. Zonal, Structural, Corrosion control and Prevention, Fuel Limitation and Airworthiness Limitation, Inspections are listed in the EMB 135/145 MBRB document and Rolls-Royce Engine Maintenance Manual and will be tracked either separately or by the inspection package they have been placed in. These inspection tasks and their frequencies are listed in Section 02 Listing of Scheduled Tasks of this Manual. In addition to the intervals expressed in letter codes, usage parameters such as:

Item Interval Letter Codes Flight Hours FH Flight Cycles FC or CY A/C Landings LD Engine Cycles EC Thrust Reverser Cycles TRC APU Hours AH APU Cycles AC Months MO Years YE Calendar Days DAYS Operation Days OD Elapsed Calendar Hours hours

21.6 Zonal Inspection Requirements These requirements contain the Zonal Inspection Requirements resulting from MSG-3 analysis. These requirements consist of a series of General Visual Inspections developed for each individual zone of the aircraft. These inspections are intended to check the aircraft system and powerplant installations as well as the aircraft structure for security and general condition. Specific Visual (Failure Finding Tasks), Detailed, or Special Detailed Inspections are restricted to the Systems & Powerplant and Structural Inspection and Rolls-Royce Mandatory Inspection Requirements Sections 02 (Scheduled Inspection Task Lists) of this Manual.




When necessary, seats, carpets, headliner and sidewall trim panels, including insulation, may be removed to permit access and a complete Zonal Inspection. Clean-up procedures should be used prior to performing zonal inspections. 21.7 Structure Inspection Requirements These requirements contain all Structural Inspection Requirements resulting from the MSG-3 analysis. These requirements consist of maintenance tasks and associated intervals developed according to the aircraft certified operating capabilities and are intended to detect and prevent any structural degradation caused by fatigue, environmental deterioration, or accidental damage during the aircraft operational life. Detection of major accidental damage such as that caused by bird strike and large ground handling equipment is considered obvious through various tell-tale signs. The structural Inspection Requirements are based on structural design information, fatigue and Damage Tolerance Analysis Reports and service experience with similar structure and related results. The requirements also take into account the applicability and effectiveness of various methods of preventing, controlling or detecting structural deterioration like thresholds and repeated intervals. Reports of accidental damage to the structure should be submitted to the KCAA, as required under the regulations. In addition, a structural inspection summary should be submitted to EMBRAER for inspection accomplished on all items of this section. All significant structural defects found should be reported. Based on these reports, EMBRAER will evaluate and issue results of the Structural Program for the fleet. 21.8 Corrosion Prevention and Control Program (CPCP) This program contains the Corrosion Prevention Inspection Requirements resulting from MSG-3 analysis. These requirements consist of maintenance tasks and associated intervals developed to prevent structural degradation caused by environmental deterioration during the aircraft operation life. The Corrosion Prevention Requirements are based on an assessment of structural design information and service experience with similar structure and related results. Some SSIs having Fatigue Damage assessed as a critical source of damage according to MSG-3 analysis have been selected to undergo the CPCP basic task. The main purpose of the combination of inspections is to allow a better corrosion control by performing the CPCP basic task at the same time as the fatigue inspections. Reports of Corrosion findings should be submitted to EMBRAER. The model of the report to be used can be found in Part IV of the SMRD and should be properly filled out and submitted to EMBRAER as required. It is not mandatory to report Corrosion Level 1. Level 2 and Level 3 corrosion findings should be submitted as per the table here below:




Level of Corrosion Stage of Finding Reports Deadlines Level 2 Initial Immediately to the manufacturer

Repeat Immediately to the manufacturer Within 60 days (on proposed corrective action to reduce corrosion level 1 or better) – to KCAA

Level 3 Initial Immediately to the manufacturer Repeat Immediately to the manufacturer

Within 7 days (with plan for fleet campaign) to KCAA Within 60 days (on proposed corrective action to reduce corrosion level 1 or better) – to KCAA

21.9 Certification Maintenance Requirements (CMRs) This contains the Certification Maintenance Requirements (CMRs) resulting from the procedures of AC 25-19 and established Certification Maintenance Coordination Committee (CMCC). These CMRs are inspections established through the safety analysis process developed in accordance with RBHA/FAR/JAR.1309/KCAA, aimed at detecting safety significant latent failures which would, in combination with one or other more specific failures or events, result in a hazardous failure condition. CMR Categorization: The CMRs are categorized as One Star or Two Star:

a. One Star CMR (*) – The task and intervals specified are mandatory and cannot be changed, escalated, or deleted without the concurrence of the Manufacturer and approved by KCAA.

b. Two Star CMR (**) – Task intervals may be adjusted in accordance with an operator’s approved escalation practices or an approved Reliability Program and to be approved by the KCAA. The tasks may not be changed or deleted without prior KCAA approval.

The Certification Maintenance Requirements (CMRs) are a result of Engineering Certification analysis and have been approved by Certification Engineering. CMR tasks are embedded in the System and Powerplant section. 21.10 Mandatory Airworthiness Limitation Requirements EMBRAER 135/145 MRBR AIRWORTHINESS LIMITATIONS These Airworthiness Limitations are mandatory actions derived from the certification activities, namely, the Damage Tolerance Analysis and the Fatigue Tests.




These requirements present the maintenance actions established in order to fully comply with the requirements of RBHA/FAR/JAR 25.571/KCAA and therefore, are required to be accomplished in strict compliance with the life limits, maximum intervals limits, inspection methods and SSI location established here in structure and CPCP sections. The Airworthiness Limitations may only be revised with the approval of the Regulatory Authority. The Airworthiness Limitations are a result of Engineering Certification analysis and have been approved by Certification Engineering. These Airworthiness Limitations are mandatory actions derived from certification Fatigue Tests and Ultimate Life limitations are noted on applicable structural inspection requirements and corrosion prevention and control program items as listed in the Airworthiness Limitations section A2.3.3 INSPECTION INTERVAL LIMIT of the MRB. ROLLS-ROYCE ENGINE MAINTENANCE MANUAL AIRWORTHINESS LIMITATION REQUIREMENTS AND INSTRUCTIONS:- The Airworthiness Limitations for model Rolls-Royce AE3007A1 and AE3007A 1/3 engines have been extracted from the relevant sections of Chapter 5 of Rolls-Royce Engine Maintenance Manual – CSP 34022 and are included in Section 5 of this AMP. Rolls-Royce Notice to Operators; Instructions for Operator Requirements:- In order to comply with the TC holders Authority and the KCAA engine record keeping requirements, operators must be able to confirm the engine model history of each LLP in the engine. When the operators send an engine to the Authorized Maintenance Center (AMC), the engine documentation must include LLP engine model history verification. This verification can be as simple as:

- A single statement that references all of the LLP’s in the engine. A single statement about all the engine LLP’s applies if the operator knows the LLP’s have always been operated as a single model since they were introduced into service.

- Verification of each separate LLP in the engine. A statement for each LLP applies if the operator is aware an LLP has operated in more than one engine model during its history (each engine model should be listed with the hours and cycles accumulated in each model) or if an LLP’s engine model history is unknown.

- A statement that says the operator cannot verify the engine model history of a specific LLP.

The AMC will review the operator’s engine model history and will include an engine model statement on each LLP “log card” in the engine logbook. Each LLP “life limit” is published in the EMM, Chapter 5, Airworthiness Limitations section for the respective engine model. If an LLP has been installed into more than one engine model, and if there is a difference in the life limits between those models, the lowest published life limit must be permanently applied to the LLP.




ROLLS- ROYCE ENGINE MAINTENANCE MANUAL CHAPTER 05 AIRWORTHINESS LIMITATIONS SYSTEM DESCRIPTION SECTION. TASK 05-12-00-800-809 – AE 3007A SERIES LIFE LIMITS A.AIRWORTHINESS LIMITATIONS THE AIRWORTHINESS LIMITATIONS SECTION IS APPROVED BY THE MANUFACTURER’S AUTHORITY (FAA) AND THE KCAA AND SPECIFIES MAINTENANCE REQUIRED UNDER SECTION 43.16 AND 91.403 OF THE MANUFACTURER’S AUTHORITY REGULATIONS UNLESS AN ALTERNATIVE PROGRAM HAS BEEN APPROVED BY THE MANUFACTURER’S AUTHORITY AND THE KCAA. NOTE: The following airworthiness limitations have been substantiated based on engineering analysis that assumes this product will be operated and maintained using the procedures and inspections provided in the ICA supplied with this product by the type certificate holder, or its licensees. For engine life limited parts and parts that influence engine life-limited parts, any repair, modification, or maintenance procedure must be assessed for its potential effect on the life of the life-limited parts and must be approved by the TC Holders Authority. It is mandatory that the parts listed under TASK 05-12-00-800-809 – AE 3007A SERIES LIFE LIMITS and indicated in section 5 of the AMP, be replaced upon expiration of the stated operating cycles. The Operator must record both the hours and cycles of engine use. In computing part life, calculations must be based on cycles since time of manufacture. There are some parts that are common to the AE3007- and AE2100 model engines. Rolls-Royce does not recommend the use of any individual part in more than one engine model throughout the life of the part. The life limit of an individual part can be different depending on the engine model in which it is installed. If it is necessary to install a part in a different model engine, you must refer to Chapter 5 of the applicable Maintenance Manuals to find the life limit for the part for both engine models. If the life limit is different for each engine model, you must use the lower of the two limits. B. DEFINITION OF AN ENGINE HOUR Time in service, with respect to maintenance time records, means the time from the moment an aircraft leaves the surface of the runway until it touches it at the next point of landing. For the purpose of documentation, engine operating hours and Flight Hours (FH) shall be considered the same as aircraft time in service. C. DEFINITION OF AN ENGINE CYCLE (EC) An Engine Cycle (EC) is defined as any flight consisting of one take-off and landing, regardless of length of flight. Each touch and go is considered an additional cycle.




D. DEFINITION OF AN ENGINE CYCLE LIFE LIMIT (ECLL) Engine Cycle Life Limit (ECLL) is defined as the maximum allowable cycles for that component. ECLL listed in this document are specific to the AE3007A engine. These components must be replaced when the engine Cycle Life Limit is reached. E. DEFINITION OF ENGINE CYCLES REMAINING (ECR) Engine Cycles Remaining (ECR) is defined as the difference between the ECLL and the total EC. F. RECORD KEEPING (1) Operator Level The operator is responsible for maintaining accurate records of engine cycle usage. Engine cycle usage for each Life Limited part shall be recorded in the engine logbook. It is not necessary to mark engine parts with life usage and doing so could compromise the integrity of the part. To determine the total Engine Cycles on a part, the following calculation must be made: EXAMPLE 1. An engine has flown 6,502 flights (one take-off and landing per flight) and during these flights, has accumulated 84 touch and Go landings. Take-offs and Landings+ Touch and Go landings= Engine Cycles 6502+84= 6586 Engine Cycles To determine the number of Engine Cycles Remaining on the part, the following calculation must be made. EXAMPLE 2 From previous example: a part has 6586 Engine Cycles. The Engine Cycles Life Limit for the part is 20,000 cycles. Engine Cycle Life Limit-Engine Cycles=Engine Cycles Remaining ECLL-EC=ECR 20000-6586= 13414 Engine Cycles Remaining (2) SHOP LEVEL The shop maintenance facility is responsible for maintaining accurate Engine Cycle data for engine, modules, and pars processed under its control. The shop maintenance facility is responsible for maintaining accurate records of engine cycle usage. Engine cycle usage for each Life limited part shall be recorded in the engine logbook. It is not necessary to mark engine parts with life usage and doing so could compromise the integrity of the part. Different AE-engine models can have the same part number components installed in the modules. Total in-service history for a life limited part must be traceable and must be reviewed. If an engine is modified in service to a different engine model, life limited parts will assume the lower published Engine Cycle Life Limit of that part as listed in Chapter 5 for the model involved. Find the Engine Cycle Life Limit in the Life Limits Setion for thye applicable engine model in which you are installing the part and the models in which the part has previously




operated. If the Engine Cycle Life Limit is different for each model, you must use the lower of the two Engine Cycle Life Limits. To account for the Engine Cycles Remaining for a part used in different AE-engine models, the following calculations must be made: EXAMPLE A: The part has 6586 Engine Cycles (EC). The engine is upgraded from an AE 3007A to an AE 3007A1 engine. The Engine Cycles Life Limit (ECLL) as published in Chapter 5 of the AE 3007A series Maintenance Manual is 20,000 cycles for the AE 3007A and 30000 cycles for the AE 3007A1. The part must remain at the lower published ECLL except as noted for parts in the Life Limits Section of the applicable engine models. Therefore the Engine Cycles Remaining (ECR) are 13414. ECLL-EC=ECR 20000-6586= 13414 Engine Cycles Remaining. EXAMPLE B: The same part is now installed in a different AE engine model. Find the ECLL of the part in Chapter 5 of the EMM for the engine model in which you are installing the part. If the life limit is different for each engine model, you must use the lower of the two life limits. If the ECLL for the engine model in which you are installing the part is 15000 cycles, the ECR will be: ECLL-EC=ECR 15000-6586=8414 21.11 Mandatory Inspections The Mandatory Inspections for the AE3007A Series engines are contained in Task Card 05-13-00-800-801 – Mandatory inspections. Sections B1 and B3 are incorporated into the AMP. Section B2 is for the shop inspections when piece part opportunity occurs, so long as the part has done 100 cycles or more since the last mandatory inspection. Piece part opportunity occurs when the part is received as an unserviceable spare or the part is removed from the engine in accordance with the applicable disassembly task. The inspections listed must be performed at the specified interval. 21.12 Mandatory Fuel System Limitations These limitations are mandatory actions derived from the Fuel tank ignition Source Safety Assessment and comply with the requirements of RBHA-E, SFAR 88 and KCAA memorandum ANM112-05-011, Policy Statement on Process of Developing SFAR No. 88 related Instructions for Maintenance and Inspections of Fuel Tank and EASA policy statement on the process for developing instructions and inspection of fuel tank system ignition source prevention – INT/POL/25/12.




These limitations are to maintain the fail-safe features required to prevent and preclude the existence or development of ignition sources in the fuel tank system throughout the operation life of the airplane. IMPLEMENTATION OF FUEL SYSTEM LIMITATIONS The first mandatory inspections must be accomplished at the next C check or at each inspection interval, stated in the Fuel System Limitations Items Tasks, whichever occurs later. For operations under Kenya Civil Aviation Authority (KCAA) jurisdiction these Fuel System Limitations shall be implemented in accordance with any applicable existing Kenya Civil aviation Regulations or, when mandated by applicable Airworthiness Directive. 21.13 Critical Design Configuration Control Limitations (CDCCL) CDLL is a design feature in the aircraft, which is required to prevent and preclude ignition sources in the fuel system. The reason to highlight these features as CDCCLs is to alert that maintenance actions or configuration changes must not affect those design features. Based on the evaluation required by the SFAR 88 rule (Fuel System Safety Review), the following features were identified as CDCCLs. 1) Wing Tanks FQIS/HLEIS harness between wing FCU/LCU and wing fuel tank connector This harness runs from the wing tanks FCU and LCU (if applicable), under the cockpit floor, passes through an interface (pressurized cabin to the fairing) connector on the spur stub spar 1, divides into two and reaches an hermetic tank wall connector on each wing. This harness highlighted as CDCCL in the appropriate AMM procedures to have the correct installation checked avoiding alterations that may violate the design configuration of the Fuel Quantity Indicating System and High Level Exceeding Indication System (if applicable) harness outside the fuel tanks. This check must be accomplished each time any kind of maintenance is performed to, or in the nearby areas that could affect the harness installation. 2) VFQIS/ VHLEIS/ VLLS harness between wing VFCU/VLCU and ventral fuel tank wall connectors. These harnesses are highlighted as CDCCL in the appropriate AMM procedures, to check the correct installation and to avoid alterations that may violate the critical design configuration limitations of the Ventral Fuel Quantity Indicating System, Ventral High Level Exceedance Indicating System and Ventral Low Level Switch harness outside the ventral fuel tank, and must be accomplished each time any kind of maintenance is performed to, or nearby areas that could affect the harness installation. 3) Fuel Pump Connector at the Tank Wall. Fuel Pumps of main wing tanks and auxiliary tanks have hermetic electrical connectors, which are installed on and electrically bonded to the tank wall. This connector is highlighted




as CDCCL in the appropriate Aircraft Maintenance Manual procedures, to check faying surface bonding whenever pump is changed and to assure adequate bonding to any fuel tank in the aircraft. This list contains the following:

a. The features of the items identified in this list must be maintained in a configuration identical to the type design approved for the airplane.

b. Any repair or overhaul to the critical ignition source prevention features of the item identified in this list must be in accordance with the appropriate maintenance manual that is supplied by the design approval holder or with an specific repair or overhaul instruction by a Certification Authority.

c. Any alteration on those CDCCL features in this list are classified as major modification and requires a Certification Authority approval.

21.14 “EWIS” Electrical Wiring Interconnection Sytem EWIS TASKS Tasks with the note “EWIS” (Electrical Wiring Interconnect System) are the scheduled maintenance requirements defined following the instructions for Continuous Airworthiness using an Enhanced Zonal Analysis Procedure (EZAP). Those requirements are included in the Section for – System and Powerplant Inspection Requirements (ARA chapter 20) and Section – Zonal Inspection Requirements. 21.15 Component Overhaul Schedule. These Task Time Limitations are covered under Section 4 of the AMPas Rstoration Items (RS) . The highlights are given here below. Main Generators, APU Starter/Generator, Back-up Battery, Main Battery, Floatation Vests, Main Landing Gear (MLG) Leg Strut Assembly, MLG Trailing Arm Assembly, including wheel axle, MLG Main Side Strut Assembly, MLG Shock Absorber Assembly, MLG Secondary Side Strut Assembly, Nose Landing Gear (NLG) Strut, including Torque Link, Steering Cuff, Sliding Tube and Web Assembly Components; and their attaching parts, NLG Auxiliary Drag Strut. These are called through the following task cards: 24-31-01-900-001-A00; 24-31-01-900-001-A01; 24-34-01-900-001-A00; 24-31-01-900-002-A00; 24-35-01-900-001-A00; 24-36-01-900-001-A00; 25-60-02-900-001-A00; 25-60-02-900-001-A01; 25-60-02-900-001-A02; 25-60-02-900-001-A03; 25-60-02-900-001-A04; 32-10-01-900-001-A00; 32-10-01-900-002-A00; 32-10-02-900-001-A00; 32-10-03-900-001-A00; 32-10-04-900-001-A00; 32-20-01-900-001-A00; 32-20-02-900-001-A00; and 32-20-03-900-001-A00.




22 Inspection Techniques 22.1 Weighing: Periodic aircraft re-weighing for establishment of empty weight and center of gravity is performed at 60 month calendar intervals. Aircraft Weight and balance Control Procedures are described in the Weight and Balance Manual. 22.2 General Inspection Whenever the term “inspect” or “check” for satisfactory conditions is specified in this program, the term is defined as follows. The Zone/System/Item inspection is sufficient to establish, that, at the time of inspection; the Zone/System/Item is free of any defects likely to affect airworthiness and is expected to remain airworthy until the next programmed inspection is due. The inspection must comply with the minimum standards set out hereunder having regard to the materials of construction of the Zone/System/Item. Unless otherwise stated in the program, all the inspection requirements are to be applied without removing an item from the aircraft or dismantling the item in-situ unless this is considered essential, in which case this is specified. This, however, does not preclude removal or dismantling, or such other inspection activity is considered as essential. Where a particular area or item is highlighted in the item it is considered as significant and should be given special attention during inspection. 22.3 High Pressure Bottle Hydrostatic Test There are no specific Federal Aviation Regulations (FAR) for prescribing airworthiness standards of pressure cylinders used in aircraft systems such as oxygen, fire extinguishers and emergency air cylinders that are part of life support systems. Recognizing the lack of test data necessary to consider cylinder aging, internal corrosion, external pressure changes, cycles and extreme temperature changes, the KCAA adopted in the interest of safety, the rules and regulations of the Department of Transportation (DOT) and applicable manufacturer’s Recommendations and CMM as acceptable methods for controlling the hydrostatic test and life limits of pressure cylinders. Accordingly, hydrostatic test, inspection and life limit will be accomplished as set forth in Title 49 (Transportation), Subtitle B (Other Regulations relating to Transportation), Subchapter C (Hazardous Material Regulations), 180.025 (General Requirements for Regulation of Cylinders) for test procedures, unless otherwise specified by the manufacturer’s CMM.

22.4 Control System Components: Inspect for: Correct alignment. No fouling, free movement, distortion, evidence of bowing, scores, chafing, fraying, kinking, evidence of wear, fretting, cracks, loose rivets, deterioration of




protective treatment, corrosion,. Electrical bonding correctly positioned, undamaged and secure. Attachments, connections and locking secure. 22.5 Metal Parts All structural members, honeycomb bonded structure, bodies, or casings of units in systems and in instruments, electrical and radio installations, metal pipes ducting, tubes, rods, levers, etc., inspect for: Cleanliness, evidence of external damage, leaks, overheating or discharge, bulging, obstructions of drainage or vent holes, security, of attachments fasteners and visible connections, locking and bonding. Freedom of cracks (visual) distortion, dents, bolts, screws. Separation of bond, failure of welds and spot welds. Deterioration of protective treatment and corrosion. Correct sealing of fairings, fluid ingress. 22.6 Rubber, Fabric, Fiber Glass and Plastic Parts: Honeycomb bonded structure, ducting, flexible pipes, flexible mountings, seals, insulation of electrical cables, windows etc. inspect for: Separation of bond, cleanliness, cracks, cuts, chafing, kinking, twisting, crushing, sufficient free length for movement, deterioration, crazing, loss of flexibility, overheating, fluid spillage. Security of attachment (supports, packing’s and electrical bonding correctly positioned, serviceable. 22.7 Electrical Motors, Alternators, Generators and Actuators: Inspect for: Cleanliness, obvious damage, corrosion, evidence of overheating, security of attachments and connections. If protective covers are required to be removed: check for cleanliness, pitting or burning of contactors, evidence of overheating and security of contact exposed. 22.8 Electrical looms: For the purposes of electrical inspections, it is understood that the stripping of looms is not normally contemplated, though in particular instances it may be required and will be called for at the discretion of the supervisor. Check for: The condition of external cables within a loom or duct will be taken to indicate the condition of inner cables. The condition of cables entering and leaving a conduit will be taken to indicate the condition of the cables within the conduit, unless otherwise suspected. Duplicate Inspection: 22.9 Flight control systems and engine control systems: If, as a result of the application of this maintenance program, any part of either the main or any associated system(s) is dismantled, adjusted, repaired or renewed, that part of the system(s) which has been disturbed shall be subjected to a duplicate inspection for correct installation, safety engagement of attaching hardware, free movement, range, direction and tension checks and shall be appropriately certified.




22.10 Landing gear “emergency “and “free fall” control system: If, as a result of the application of this maintenance program, any part of the main or nose landing gear “emergency” or “free fall” control system or any associated system(s) which has been disturbed shall be subjected to a duplicate inspection for correct installation, safety engagement of attaching hardware, free movement, range, direction and tension checks and shall be appropriately certified.

- Installation and repair of major structural components - Installation of aircraft engines - Calibration or rigging of components such as engines, navigation equipment and

gearboxes 22.11 Special Precautionary checks: All flight, engine, fuel and landing gear control systems Whenever inspections are made or work is undertaken on any part of above systems, detailed investigation must be made after completion to verify that distortion, tools, rags or any other loose articles or foreign objects cannot impede free movement and safe operation of the system(s). Fuel System: If, as a result of the application of this maintenance program, any part of the fuel system is dismantled, adjusted, repaired or renewed, affected parts of the system shall be checked for free movement and correct operation after completion of work. Panel opening charts: Panel opening charts provide panel identification. For the purpose of physical inspection, panel removal requirements shall not limit the degree of inspection required. Removal of other panels shall be at the discretion of inspection personnel. 23 Task Codes 23.1 DET – An INTENSIVE EXAMINATION of a specific item, installation, or assembly to DETECT DAMAGE, FAILURE or IRREGULARITY. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. INSPECTION AIDS such as mirrors, magnifying lenses, or other means may be necessary. Surface cleaning and elaborate access procedures may be required. A DET can be more than just a visual inspection, since it may include TACTILE ASSESSMENT in which a component or assembly is CHECKED FOR TIGHTNESS OR SECURITY. It may require the removal of such items such as access panels and drip shields, or the moving of the components. 23.2 DIS – (Discard) The REMOVAL FROM SERVICE of an item at a specified life limit.




23.3 DRC – (Data Recording/Calculating) A TRANSFER OF DATA from an aircraft system or component to an independent computer for analysis. 23.4 FNC – A QUANTITATIVE CHECK to determine if one or more functions of an item, PERFORMS WITHIN SPECIFIED LIMITS. 23.5 GVI – A VISUAL EXAMINATION of an interior or exterior area, installation, or assembly to DETECT OBVIOUS DAMAGE, FAILURE or IRREGULARITY. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked. 23.6 LUB- (Lubrication) any act of lubricating for the purpose of maintaining inherent design capabilities. 23.7 OPC – (Operational check) An operational check is a task to DERTERMINE I an item is fulfilling its INTENDED PURPOSE. Since it is a failure finding task, it does not require quantitative tolerances. 23.8 RST – (Restoration) That work (on/off the aircraft) necessary to return the item to a specific standard. RESTORATION may vary from CLEANING or REPLACEMENT of single parts up to a COMPLETE OVERHAUL. 23.9 SDI – An INTENSIVE EXAMINATION of a specific item(s), installation, or assembly to DETECT DAMAGE, FAILURE or IRREGULALITY. The examination is likely to make extensive use of SPECIALIZED INSPECTION TECHNIQUES and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required. 23.10 SVC – (Servicing) Any act of servicing for the purpose of maintaining inherent design capabilities. 23.11 VCK – (Visual Check) A visual check is an observation to determine if an item is fulfilling its intended purpose. Since it is a failure finding task, it does not require quantitative tolerances. 24 Parking, storage and Return to Service Parking: For parking and prolonged parking procedure see AMM 10-00-00




Storage: For the storage procedure see AMM 10-00-00 Return to Service: For the return to service procedure see AMM 10-00-00 24.2 Special Regulations for Parked or Stored Aircraft: An aircraft which has been taken out of operation and is parked or stored for more than 24 hours has to be maintained according to the following rules: All maintenance requirements and checks defined in this maintenance program, which become due during the parking period, may be postponed until the end of the parking period (unless required by AMM 10-00). All deferred complaints and open items, which are programmed for rectification during the parking period, may be postponed until the end of the parking period (unless required by AMM 10-00). All changes of components, which become due during the parking period, may be postponed until the end of the parking period (unless required by AMM 10-00). All EO’s, SB’s, SL’s, SIL’s, AD’s, CDN’s and national Airworthiness Requirements, which become due during the parking period, may be postponed until the end of the parking period, provided there is no specific requirement for the parking/storage period. Provisioning related component, APU or engine removals during the parking/storage period are possible in general. The reinstallation of a component, APU or engine can be postponed until the end of the parking/storage period, but has to be performed in accordance with all relevant procedures. All outstanding work and component replacements must be completed before return of the aircraft back into service. For appropriate handling of a removed component, APU or engine before installation in another aircraft, refer to the relevant procedures. Before the aircraft is returned to service, all postponed maintenance requirements and checks defined in the MS, all components changes as required by the EO’s, SB’s, SL’s, SIL’s, AD’s, CN’s and rectification of deferred complaint/open items have to be performed.




24.2 SPECIAL INSPECTIONS Unscheduled Maintenance Checks are included in the Embraer 135 and 145 Aircraft Maintenance Manuals (AMM), section 05-50-00 and Rolls-Royce Engine Maintenance manual (EMM) section 05-00. These sections contains the recommended inspections and checks required whenever the aircraft has gone through special or abnormal conditions, such as: Description AMM Reference Description AMM Reference Lightning Strike 05-51-01 Landing Gear Free

Fall Condition 05-51-13

Hard Landing 05-51-02 Overheated Wheels 05-51-14 High Drag/Side Load Landing Condition

05-51-03 Landing Gear Tyre Tread Failure

05-51-15

Maximum Operating Speed Exceeded

05-51-04 High Energy Stop 05-51-16

High Load Factor Flight

05-51-05 Fuel Pump Failure 05-51-19

Landing Gear Down Overspeed

05-51-06 Brake Use During Towbarless Towing Operation

05-51-23

Maximum Flap Extended Speed

05-51-07 LH/RH Static Ports Vicinity

05-51-24

Bird Strike 05-51-08 Overweight Landing 05-51-25 Engine Fire Warning 05-51-09 On Ground Gale

Force Winds 05-51-26

Ice or Snow Condition

05-51-010 Severe Turbulence or Buffeting Condition

05-51-27

APU Fire Warning 05-51-11 HIRF/ Lightning 05-51-01




ENGINES Description Rolls-Royce EMM

Task Number Description Rolls-Royce EMM

Task Number Inspection of an Engine Involved in an Accident or Incident

05-50-00-200-801 Inspection of the Engine that has Smoke on Shutdown.

05-50-00-200-808

Inspection after a Fire in or near the Engine or the Nacelle

05-50-00-200-802 Inspection of the Engine after Exceeding the maximum Operating Speed Envelope.

05-50-00-200-809

Inspection of the Engine after operation with Volcanic Ash in the Air.

05-50-00-200-803 Inspection for Severe Turbulence, Buffeting on the ground, or Gale-force Wind.

05-50-00-200-810

Inspection of the Engine for Foreign Object Damage.

05-50-00-200-804 Inspection of the Engine after sudden Entrance into water.

05-50-00-200-811

Inspection for Hard Landing, Side Load Landing or Overweight Landing

05-50-00-200-805 Inspection of the Engine Components or Parts Damaged in Transportation.

05-50-00-200-812

Inspection for Lightning Strike Damage

05-50-00-200-806 Clean the Engine after operation in Corrosive Environment.

05-50-00-100-801

Inspection of the Engine after a sudden Stop

05-50-00-200-807 Flush the Engine after a Fire-extinguishing Agent discharge.

05-50-00-100-802




25 TEST FLIGHTS Non-revenue flight following maintenance actions are not required by Aircraft Manufacturer, except for actions involving items that cannot be properly ground tested to verify that the aircraft’s operational characteristics have not been adversely affected. Service experience has shown that a non-revenue flight is a good practice following actions or repairs which could affect the aircraft’s inherent aerodynamic characteristics.

25.1 Full Test Flight or C of A Test Flight A full test flight contains: General verification of aircraft performance as per the Flight Manual (start, climb, level flight) and correct function of aircraft’s systems, and accomplishment of abnormal procedures (emergency procedures in particular). A full test flight is required after: A Major Structure Check, or Important repairs following an accident, unless relief is obtained by the repair approval, or Related to extensive maintenance actions, at the end of the appropriate major check layover. 25.2 Reduced Test Flight. A reduced test flight only contains verification of certain functions of the aircraft’s systems which are directly or indirectly affected by the tasks accomplished. A reduced test flight is required for actions involving items that cannot be properly tested on ground to verify the aircraft’s operational characteristics. The followings cases fall in this category:

- After flight control surfaces change or reinstallation, unless relief is obtained by proof of the maintenance program of an experienced engineering organization

- After change or reinstallation of both engines - After modification or repair, whenever the necessity for a test flight is stated in the related

documentation (for the modification or repair). - After installation or calibration of major navigation equipment.

25.3 Test Fight Program The following conditions shall be fulfilled during the test flight:

- Meteorological conditions shall be better than minimum conditions for operation, and the forecast must show that these conditions will last for the duration of the flight,

- All maneuvers shall be VMC - The test fight shall be accomplished with a take-off weight not above maximum landing

weight




26 Maintenance Check Cycle Routine inspection and servicing are conducted as per the table here below:

PERIOD IN WHICH THE SCHEDULED INSPECTION ACCOMPLISHMENT IS CONSIDERED ON TIME INSPECTION MAXIMUM ALLOWABLE

TOLERANCE WINDOW FOR ACCOMPLISHMENT(The task due date must be the centre of the window)

06-Month Tasks ± 15 Days 31 Days 12-Month Tasks ± 15 Days 31 Days 18-Month Tasks ± 15 Days 31 Days 24-Month Tasks ± 30 Days 61 Days 36-Month Tasks ± 30 Days 61 Days 48-Month Tasks ± 30 Days 61 Days 60-Month Tasks ± 30 Days 61 Days 72-Month Tasks ± 30 Days 61 Days 96-Month Tasks ± 60 Days 121 Days 120-Month Tasks ± 60 Days 121 Days 144-Month Tasks ± 60 Days 121 Days 180-Month Tasks ± 60 Days 121 Days NOTE: Some tasks with intervals listed above do not have tolerances implemented. Each task shall be consulted in the SMRD related Section in order to determine its correct tolerance value.

This is a flexible maintenance program and consists of tolerance given for the maintenance inspections thresholds and intervals and it is applied only after the approval of the AMP by the KCAA.

The tolerance is applied only for calendar thresholds and calendar intervals and cannot be used if the Flight hour (FH), Flight Cycle (FC) or APU Hour (AH), threshold or interval is reached.




27 Permitted Variations

27.1 The Director of Quality Assurance will grant variations to the approved maintenance program which includes maintenance checks and hard time components.

NOTE: THESE GUIDELINES DO NOT APPLY TO AIRWORTHINESS LIMITATIONS TASKS, AIRWORTHINESS DIRECTIVES OR LIFE LIMITED PARTS/COMPONENTS WHICH ARE MANADATORY AND CANNOT BE CHANGED, ESCALATED, OR DELETED WITHOUT THE CONSENT OF THE MANUFACTURER AND APPROVED BY THE KCAA.

The maximum variation of a prescribed period is indicated below:

a) Items controlled by flight hours: • 5000 flying hours or less: 10% • More than 5000 flying hours: 500 flying hours

b) Items controlled by calendar time: • 1 year or less: 10% or 1 month whichever is the lesser. • More than 1 year, but not exceeding 3 years: 2 months • More than 3 years: 3 months.

c) Items controlled by landing/cycles: • 500 landings/cycles or less: 10% or 25 landing/cycles, whichever is the

lesser. • More than 500 landings/cycles: 10% or 250 landings/cycles, whichever is

the lesser.

For items controlled by more than one limit, e.g. items controlled by flying hours and calendar time or flying hours and landings/cycles, the more restrictive limit should be applied.

27.2 Variation process control

For any further additional tolerance, prior to the commencement of the tolerance the Base Maintenance Manager will ensure the aircraft is inspected to the degree necessary to ensure that it is airworthy, and in a satisfactory condition to operate for the period of the tolerance. Proof of acquiring the necessary components/test equipment to accomplish the task will also be provided to the KCAA.

The Authority may then authorize the Quality control manger to issue variation within specified limits. Depending on the nature of the variation, the Authority may require the AMO to contact the manufacturer to assess the exemption request.




The Quality control manager is responsible to ask for variation to the Authority and

to inform the Maintenance department concerned and Certifying staff on receipt of the Authority acceptance.

The variation shall be recorded in the appropriate aircraft or component logbook.

28 Scheduled Checks 28.1 Scheduled checks on the Embraer ERJ 135LR and ERJ 145MP consist of the

following categories:

28.2 Pre/Post Flight, Emergency, Daily and Weekly Inspections

28.3 Systems and Power plant Tasks

28.4 Life Limited Component Checks

28.5 Engine Maintenance and Engine Life Limited Parts

28.7 KCAA Inspections

28.8 ALS Inspections



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S48 TASKS 144MO THRESHOLD

TOLERANCE EQUAL TO ± 15 Days

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EMBRAER ERJ135LR AND ERJ145MP AIRCRAFT

SECTION 3

LOW UTILIZATION MAINTENANCE PROGRAM

These Requirements can be found in the Scheduled Maintenance Requirements Document (SMRD) Section VI Reference SMRD-145/1137

ALS AIRCRAFT MAINTENANCE PROGRAM


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SECTION III

LOW UTILIZATION PROGRAM

III.1 INTRODUCTION

This section contains a list of all SMRD 1137 (Part I and Part II) maintenance requirements with adequate intervals to cover FAR 91 and FAR 135 operations at any yearly utilization and FAR 121 operating up to 1500 Flight Hours per year. The requirements from the SMRD Part I (MRBR 1150) Appendix A2 (Airworthiness Limitations Requirements) item A2.2 (Life Limited Components) and the requirements from the SMRD Part II (SMRD 1137) Section VII (Embraer – Optional Tasks) are the only exceptions, being not covered by this section. Section VI contents were approved only by ANAC. This section also contains the Flexible Maintenance Program, which consists of tolerances given for the maintenance requirements. The maintenance requirements contained herein have their maximum allowable intervals defined based on those intervals listed in the SMRD 1137 (Part I and Part II) plus a calendar limitation (when applicable) in order to assure the level of safety and reliability of the aircraft. This section also contains the Structured maintenance program, which provides the operators with optimized packages, according to one (1) pre-defined yearly utilization profile. This program application is not an Embraer imposition. Operators can choose between the Structured Program (item III.5) and the maximum intervals (item III.4).

III.2 APPLICABILITY This section has been developed to cover operations under 91, 121, 125 and 135 regulations as follows: For aircraft operating under 91, 125 or 135 regulation, this section provides operators with all information necessary to show compliance with applicable authorities’ regulation regarding Maintenance Inspection Program. Additionally, the information contained herein enable operators to comply with the requirements of 135 regulation to construct a suitable maintenance program. For aircraft operating under 121 regulation and having a utilization rate equal to or less than 1500 FH per year, this section has all info- mation necessary to comply with appendix H of 25 regulation and contains a list of all MRB-1150 and SMRD-1137 maintenance tasks necessary to assure the level of safety and reliability of the aircraft. The tasks intervals listed herein are presented in FH/FC/AH and/or calendar, which means that according to the aircraft utilization profile the operator, can customize the maintenance program according to their needs, but not exceeding the intervals published following the statement "whichever occurs first". However, EMBRAER has prepared the Structured Maintenance Program containing all SMRD 1137 maintenance tasks with adequate calendar intervals based on pre-defined yearly utilization profile as a suggestion to those customers intending to follow a customized maintenance program.



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PERIOD IN WHICH THE SCHEDULED INSPECTION ACCOMPLISHMENT IS CONSIDERED ON TIME

INSPECTION

MAXIMUM

ALLOWABLE TOLERANCE

WINDOW FOR ACCOMPLISHMENT

(the task due date must be the

centre of the window)

120-Month Tasks ± 60 Days 121 Days



NOTE: Some tasks with intervals listed above do not have tolerances imple-mented. Each task shall be consulted in the SMRD related Section in order todetermine its correct tolerance value.

III.3 FLEXIBLE MAINTENANCE PROGRAM The flexible maintenance program consists of a tolerance given for the maintenance inspections thresholds and intervals and it is applied only where local regulatory authorities permit. The tolerance is applied only for calendar thresholds and calendar intervals and cannot be used if the Flight Hour (FH), Flight Cycle (FC) or APU Hour (AH), threshold or interval is exceeded. The table below contains the scheduled inspection interval, its tolerance (maximum number of days to be used when anticipating or postponing an inspection) and the window in which the inspection accomplishment is considered on time. The window must be centered in the task due date so the window is defined as the task

due date plus or minus the tolerance value.



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When the tolerance is correctly applied to a task, following the maximum allowable window (task due date plus or minus the tolerance value), the task accomplishment is still considered on time. This task next due is calculated based on the last scheduled inspection due date (without considering the tolerance application). See examples 1 and 2 below. If the tolerance applied to a task (to anticipate the maintenance stop) is higher than the maximum allowable window (task due date plus or minus the tolerance value), which is not allowed by the Flexible Maintenance Program, this task next due is calculated based on the last performed inspection due date. See example 03 below. This rule assures the task will be accomplished according to its approved calendar interval and threshold at all times and also assures that the tolerance will not be used to extend the tasks intervals and thresholds.

See the examples below:

EXAMPLE 1:

A calendar inspection due at an interval of 12 months was done at 12 and half months (of aircraft operational life). The time applied to the 12 month inspection was equal to plus 15 days, which is the maximum time to per fo rm the inspect ion using the al lowable tolerance

A calendar inspection due at an interval of 12 months was done at 11 and half months (of aircraft operational life). The time applied to the 12 month inspection was equal to minus 15 days, which is the minimum time to perform the inspection using the allowable tolerance. The next inspection due date will be calculated based on the last 12 month scheduled inspection and not based on the last 12 month performed inspection. The due date for the next inspection is 24 months (of aircraft operational life) plus or minus a 15 days tolerance.

. The next inspection due date will be calculated based on the last 12 month scheduled inspection and not based on the last 12 month performed inspection. The due date for the next inspection is 24 months (of aircraft operational life) plus or minus a 15 days tolerance.



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EXAMPLE 3:

A calendar inspection due at an interval of 12 months was done at 11 months (of aircraft operational life). The time applied to the 12 month inspection was equal to minus 30 days, which is higher than the allowable tolerance for a 12MO inspection, according to the Flexible Maintenance Program rules. The next inspection due date will be calculated based on the last 12 month performed inspection and not based on the last 12 month scheduled inspection. The due date for the next inspection is 23 months (of aircraft operational life) plus or minus a 15 days tolerance. This situation will lead to the 12 months inspection becoming out of phase with the 24 months inspection, which is based on the aircraft maintenance start counting date.

III.4 LIST OF SCHEDULED MAINTENANCE REQUIREMENTS

The maintenance requirements are organized by the SMRD 1137 sections and appendixes. Each requirement contains the following information:



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SECTION 1

ROUTINE INSPECTION REQUIREMENTS

FUSELAGE FORWARD SECTION & NOSE LANDING GEAR

REFERENCE NUMBER TYPE CAT DESCRIPTION LU INT EFFECT TOLERANCE

32-20-01-211-001-A00 VCK 9 Visually Check Nose Landing Gear and Spring Cartridges forCondition and Shock Absorber Extension

14 DAYS or

100 FH

ALL Not Applicable

32-33-15-720-001-A00 FNC 8 Functionally Check Landing Gear Accumulator NitrogenPre-Charge (Side Hinged Main Door Model only)

14 DAYS or

100 FH

ALL Not Applicable

32-49-04-212-001-A00 GVI 6 Inspect (Visual Inspection) NLG Tires for Wear and GeneralCondition

14 DAYS or

100 FH

ALL Not Applicable

32-49-05-212-001-A00 GVI 6 Inspect (Visual Inspection) NLG Wheel Assembly 14 DAYS or

100 FH

ALL Not Applicable

34-13-00-212-001-A00 GVI 7 Inspect (Visual Inspection) Pitot/Static Ports for Absence ofForeign Matter

14 DAYS or

100 FH

ALL Not Applicable

35-10-00-211-001-A00 VCK 7 Check Crew Oxygen Pressure 14 DAYS or

100 FH

ALL Not Applicable

35-11-03-211-001-A00 VCK 7 Visually Check Oxygen Cylinder Pressure Relief Disc 14 DAYS or

100 FH

ALL Not Applicable



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WING & MAIN LANDING GEAR (RH & LH)

REFERENCE NUMBER TYPE CAT DESCRIPTION LU INT EFFECT TOLERANCE12-11-03-680-001-A00 SVC 7 Drain Fuel Tanks to Check for the Presence of Water 14 DAYS

or 100 FH

ALL Not Applicable

27-12-01-212-002-A03 GVI 8 Inspect (Visually Inspect) Aileron PCA Rod Ends/Fitting Lugs For Integrity and General Condition PCA P/N 394900-1007

14 DAYSor

100 FH

EMB-145(ALL)

Not Applicable

28-11-00-212-001-A00 GVI 7 Visually Check Under wing Surfaces, Tank Access Panels, Dump Valves and Drain Valves for Absence of Fuel Leakage

14 DAYSor

100 FH

ALL Not Applicable

28-12-03-212-001-A00 GVI 7 Visually Check NACA Air Inlet for Absence of Obstruction 14 DAYSor

100 FH

ALL Not Applicable

28-20-00-212-001-A00 GVI 7 Visually Check Fuel Line Shroud Drains for Absence of FuelLeakage

14 DAYSor

100 FH

ALL Not Applicable

32-10-00-211-001-A00 VCK 9 Visually Check Main Landing Gear, Including Doors andSpring Cartridges

14 DAYSor

100 FH

ALL Not Applicable

32-10-02-211-001-A00 VCK 9 Visually Check MLG Shock Absorber Extension 14 DAYSor

100 FH

ALL Not Applicable

32-49-01-212-001-A00 GVI 6 Inspect (Visual Inspection) MLG Tires for Wear and GeneralCondition

14 DAYSor

100 FH

ALL Not Applicable

32-49-02-212-001-A00 GVI 6 Inspect (Visual Inspection) MLG Wheel Assembly 14 DAYSor

100 FH

ALL Not Applicable

32-49-03-212-001-A00 GVI 6 Inspect (Visual Inspection) Brake Assembly for GeneralCondition

14 DAYSor

100 FH

ALL Not Applicable



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COCKPIT


26-14-00-710-001-A00 OPC 8 Operationally Check Lavatory Smoke Detection System 14 DAYS or

100 FH

ALL Not Applicable

26-15-00-710-001-A00 OPC 8 Operationally Check Baggage Smoke Detection System(Class “D” Baggage Compartment only)

14 DAYS or

100 FH

ALL Not Applicable

29-10-04-710-001-A00 OPC 8 Operationally Check Electric Motor-Driven Pump (EMDP) inAUTO and ON modes

14 DAYS or

100 FH

ALL Not Applicable

30-00-00-710-001-A00 OPC 8 Operationally Check Anti-Icing System Messages 14 DAYS or

100 FH

ALL Not Applicable

72-00-00-970-001-A00 DRC 9 Engine Trend Download/Analysis NOTE: Or 75 FC, whichever occurs first

14 DAYS or

100 FH

ALL Not Applicable



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FUSELAGE AFT SECTION


12-13-01-610-001-A00 SVC 7 Hydraulic System Reservoir Fluid Level Check 14 DAYS or

100 FH

ALL Not Applicable

32-44-02-610-001-A00 SVC 7 Parking/Emerg Brake Nitrogen Accumulator PressureCharge

14 DAYS or

100 FH

ALL Not Applicable

49-11-01-212-001-A00 GVI 7 Inspect (Visual Inspection) APU and Starter Generator AirIntake and Exhaust Ducts for Foreign Material or Obstruction

14 DAYS or

100 FH

ALL Not Applicable

NACELLE SECTION (RH & LH)


71-12-01-212-002-A00 GVI 7 Inspect (Visual Inspection) Engine and Generator CoolingAir Inlets/Outlets for Absence of Foreign Matter

14 DAYS or

100 FH

ALL Not Applicable



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SECTION 2

SYSTEMS & POWERPLANT INSPECTION REQUIREMENTS

CHAPTER 20 – STANDARD PRACTICES - AIRFRAME


20-00-00-140-002-A00 RST - Clean Center Fuselage III Lower Side including wiring, lines and omega beams (Zones: 151, 152, 153, 154,155, 156, 157). NOTE: EWIS

48 MO or

10000 FH

EMB-135LR

EMB-145MP± 30 Days

20-00-00-140-003-A00 RST - Clean Center Fuselage IV Lower Side including wiring, lines and omega beams (Zones: 161, 162). NOTE: EWIS

48 MO or

10000 FH

ALL ± 30 Days

20-00-00-140-004-A00 RST - Clean Center Fuselage IV Upper Side surroundingELT Unit (Zones: 262, 264). NOTE: EWIS

96 MO or

20000 FH

ALL ± 60 Days

20-00-00-140-005-A00 RST - Clean Rear Fuselage I Lower Side, including wiring and lines (Zones: 171, 172). NOTE: EWIS

24 MO or

5000 FH

ALL ± 30 Days



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CHAPTER 20 – STANDARD PRACTICES - AIRFRAME (Continued)


20-00-00-140-006-A00 RST - Clean Rear Fuselage I Lateral Side, including electronic rear compartment wiring (Zones: 271, 272). NOTE: EWIS

48 MO or

10000 FH

ALL ± 30 Days

20-00-00-140-007-A00 RST - Clean Center Fuselage II Lower Side including wiring, lines and omega beams (Zones: 141, 142). NOTE: EWIS

48 MO or

10000 FH

ALL ± 30 Days

20-00-00-140-008-A00 RST - Clean Center Fuselage I Lower Side including wiring, lines and omega beams (Zones: 131, 132). NOTE: EWIS

48 MO or

10000 FH

ALL ± 30 Days

20-00-00-140-009-A00 RST - Clean NLG & FWD Electronic Compartments, FWD Pressure Bulkhead Upper Side (Zones: 113, 114, 213, 214, 215, 216). NOTE: EWIS

96 MO or

20000 FH

ALL ± 60 Days

20-00-00-140-010-A00 RST - Clean C o c k p i t L a t e r a l S i d e a n d F W D P r e s s u r e Bulkhead Upper Side (Zones: 221, 222, 223, 224).

NOTE: EWIS

48 MO or

10000 FH

ALL ± 30 Days

20-00-00-140-011-A00 RST - Clean C o c k p i t L o w e r S i d e a n d F W D P r e s s u r e Bulkhead Lower Side (Zones: 121, 122, 123, and 124). NOTE: EWIS

48 MO or

10000 FH

ALL ± 30 Days

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20-00-00-212-002-A00 GVI - Inspect (General Visual) Center Fuselage III Lower Side - EWIS Components of APU and Engines Generators Power cables, Hydraulic Pumps Power cables and wiring bundles (Zones:151, 152, 153, 154,155, 156, 157). NOTE: EWIS

48 MO or

10000 FH

EMB-135LR EMB-145MP

± 30 Days

20-00-00-212-003-A00 GVI - Inspect (General Visual) Center Fuselage IV Lower Side - EWIS Components of APU and Engines Generators Power cables, Hydraulic Pumps Power cables and wiring bundles (Zones: 161, 162). NOTE: EWIS

48 MO or

10000 FH

ALL ± 30 Days

20-00-00-212-004-A00 GVI - Inspect (General Visual) Rear Fuselage I Lower Side - EWIS Components of APU and Engines Generators Power cables and wiring bundles (Zones: 171, 172 / Task applicable to Baggage Compartment Class D). NOTE: EWIS

24 MO or

5000 FH

ALL ± 30 Days

20-00-00-212-005-A00 GVI - Inspect (General Visual) Rear Fuselage I Lateral Side- EWIS Components of Engines Generators Power cables and wiring bundles (Zones: 271, 272 / Task applicable to Baggage Compartment Class D). NOTE: EWIS

48 MO or

10000 FH

ALL ± 30 Days

20-00-00-212-006-A00 GVI - Inspect (General Visual) Rear Fuselage I Upper Side - EWIS Components of wiring bundles (Zones: 273, 274/ Task applicable to Baggage Compartment Class D).NOTE: EWIS

48 MO or

10000 FH

ALL ± 30 Days


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20-00-00-212-007-A00 GVI - Inspect (General Visual) Rear Fuselage I, Pressure Bulkhead Pressurized area side - EWIS Components of APU Power Cables and wiring bundles (Zones: 275,276). NOTE: EWIS

48 MO or

10000 FH

ALL ± 30 Days

20-00-00-212-008-A00 GVI - Inspect (General Visual) Rear Fuselage II, Structural 48 MO ALL ± 30 Days area aft of rear pressure bulkhead - EWIS Compo- or nents of Power cables and wiring bundles (Zones: 10000 FH 311, 312). NOTE: EWIS

20-00-00-212-009-A00 GVI - Inspect (General Visual) Wing-to-fuselage attachment 48 MO EMB-145MP ± 30 Days fairings - EWIS Components of wiring bundles (Zones: or 191, 192, 193, 194, 195). 10000 FH NOTE: EWIS

20-00-00-212-010-A00 GVI - Inspect (General Visual) Wing-to-fuselage attachment 48 MO EMB-135LR ± 30 Days fairings - EWIS Components of wiring bundles (Zones: or 191, 193, 194, 195). 10000 FH NOTE: EWIS



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20-00-00-212-012-A00 GVI - Inspect (General Visual) NLG Electronic Compart- ment - EWIS Components of wiring bundles (Zones:113, 114). NOTE: EWIS

96 MO or

20000 FH

ALL Not Applicable

20-00-00-212-013-A00 GVI - Inspect (General Visual) Engine Pylon - EWIS Components of Engines Generators Power cables and wiring bundles (Zones: 414, 424). NOTE: EWIS

24 MO or

5000 FH

ALL ± 30 Days

20-00-00-212-014-A00 GVI - Inspect (General Visual) Engines - EWIS Compo- nents of Engines Generators Power cables (Zones:415, 425). NOTE: EWIS

24 MO or

5000 FH

ALL ± 30 Days

20-00-00-220-001-A00 DET - Inspect (Detailed Inspection) - EWIS Components ofWing Tank Unit Harness (Zones: 155, 156, 157, 531,631, 541, 641). NOTE: EWIS

48 MO or

10000 FH

EMB-135LR ± 30 Days

20-00-00-220-002-A00 DET - Inspect (Detailed Inspection) - EWIS Components of Wing Tank Unit Harness (Zones: 531, 631, 541, 641). NOTE: EWIS

48 MO or

10000 FH

EMB-145MP ± 30 Days



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20-00-00-220-003-A00 DET - Inspect (Detailed Inspection) - Electric Fuel PumpConnector (Zones: 155, 156, and 157). NOTE: EWIS

48 MO or

10000 FH


20-00-00-220-004-A00 DET - Inspect (Detailed Inspection) - Electric Fuel PumpConnector (Zones: 531, 631). NOTE: EWIS

48 MO or

10000 FH


20-00-00-220-007-A00 DET - Inspect (Detailed Inspection) Wing Middle Section -EWIS Components of Pilot Valve harness inside the conduit (Zones: 541, 641). NOTE: EWIS

48 MO or

10000 FH

ALL ± 30 Days



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20-00-00-220-008-A00 DET - Inspect (Detailed Inspection) Wing Middle Section -EWIS Components of Vent Valve harness inside the conduit (Zones: 541, 641). NOTE: EWIS

48 MO or

10000 FH

ALL ± 30 Days

20-00-00-220-009-A00 DET - Inspect (Detailed Inspection) FWD Electronic Compartment/ FWD Pressure Bulkhead Upper Side -EWIS Components of wiring bundles (Zones: 213,214, 215, 216). NOTE: EWIS

96 MO or

20000 FH

ALL ± 60 Days

20-00-00-220-010-A00 DET - Inspect (Detailed Inspection) Cockpit Lower Side - EWIS Components of Power cables (Zones: 123,124). NOTE: EWIS

48 MO or

10000 FH

ALL ± 30 Days

20-00-00-220-011-A00 DET - Inspect (Detailed Inspection) Cockpit Lateral Side - EWIS Components of Power cables (Zones: 223,224). NOTE: EWIS

48MO or

10000 FH

ALL ± 30 Days

20-00-00-220-012-A00 DET - Inspect (Detailed Inspection) Center Fuselage I Lower Side - EWIS Components of APU and Engines Generators Power cables, Hydraulic Pumps Power cables and wiring bundles (Zones: 131, 132). NOTE: EWIS

48MO or

10000 FH

ALL ± 30 Days



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20-00-00-220-013-A00 DET - Inspect (Detailed Inspection) Center Fuselage II Lower Side - EWIS Components of APU and Engines Generators Power cables, Hydraulic Pumps Power cables and wiring bundles (Zones: 141, 142). NOTE: EWIS

48MO or

10000 FH

ALL ± 30 Days

CHAPTER 21 – AIR CONDITIONING


21-20-00-710-001-A00 OPC 7 Operationally Check Air Conditioned DistributionSystem

96 MO or

10000 FH

ALL ± 60 Days

21-21-00-720-001-A00 FNC 9 Functionally Check Display Ventilation System 48 MO or

5000 FH

ALL ± 30 Days

21-25-01-710-001-A00 OPC 8 Operationally Check Ram Air Valve 48 MO or

5000 FH

ALL ± 30 Days

21-26-00-710-001-A00 OPC 9 Operationally Check Electronic CompartmentVentilation System

48 MO or

5000 FH

ALL ± 30 Days

21-26-08-960-001-A00 DIS 9 Discard Exhaust Hoses of the Electronic BayCompartment Pre-Mod. SB 145-21-0013

18 MO or

2500 FH

ALL ± 15 Days

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CHAPTER 21 – AIR CONDITIONING (Continued)


21-26-08-960-001-A01 DIS 9 Discard Exhaust Hoses of the Electronic BayCompartment Post-Mod. SB 145-21-0013

180 MO ALL ± 60 Days

21-27-00-710-001-A00 OPC 9 Operationally Check Baggage Compartment Ven-tilation System (including High and Low Speed of Fan) (Baggage Compartment with Ventilation System only)

500 FH ALL Not Applicable

21-27-02-640-001-A00 LUB 8 Lubricate Baggage Compartment Check Valves(Baggage Compartment with Ventilation System only)

48 MO or

5000 FH

ALL ± 30 Days

21-27-02-710-001-A00 OPC 8 Operationally Check Baggage Compartment Check Valve (manual check for free movement and correct seating) (Baggage Compartment with Ventilation System only)

24 MO or

2500 FH

ALL ± 30 Days

21-31-00-710-001-A00 OPC 9 Operationally Check Pressurization Control System inManual Mode

96 MO or

10000 FH

ALL ± 60 Days

21-31-00-720-002-A00 FNC 8 Functionally Check Outflow Valves Pressure ReliefDevices


21-31-00-720-005-A00 FNC 9 Functionally Check Line for Leakage Post-Mod. SB145-21-0002.

96 MO or

10000 FH

ALL ± 60 Days

21-31-03-140-001-A00 RST 6 Clean Electro pneumatic Outflow Valve (Non-smokingFlights)


21-31-03-140-001-A01 RST 6 Clean Electro pneumatic Outflow Valve (SmokingFlights)





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CHAPTER 21 – AIR CONDITIONING (Continued)


21-31-04-140-001-A00 RST 6 Clean Pneumatic Outflow Valve (Non-smoking Flights) 1000 FH ALL Not Applicable

21-31-04-140-001-A01 RST 6 Clean Pneumatic Outflow Valve (Smoking Flights) 400 FH ALL Not Applicable

21-31-08-960-001-A00 DIS 6 Replace Air Filter Element (Non-smoking Flights) 3200 FH ALL Not Applicable

21-31-08-960-001-A01 DIS 6 Replace Air Filter Element (Smoking Flights) 1800 FH ALL Not Applicable

21-51-00-710-001-A00 OPC 8 Operationally Check Cooling Pack System to VerifyECS OFF Signal

48 MO or

5000 FH

ALL ± 30 Days

21-51-00-720-001-A00 FNC 6 Functionally Check Cooling Pack System 96 MO or

10000 FH

ALL ± 60 Days

21-51-00-720-003-A00 FNC 8 Functionally Check Pack Duct Over temperatureProtection

48 MO or

5000 FH

ALL ± 30 Days

21-51-01-130-001-A00 RST 6 Clean Pack Valve Filter Using Ultrasonic Method 2500 FH ALL Not Applicable

21-51-02-170-001-A00 RST 6 Clean Dual Heat Exchanger and Visually CheckCondition of Core


21-51-10-710-001-A00 OPC 8 Operationally Check Pack Leak Switch 72 MO or

10000 FH

ALL ± 30 Days

21-60-00-710-001-A00 OPC 9 Operationally Check Temperature Control 96 MO or

10000 FH

ALL ± 60 Days




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CHAPTER 22 – AUTO FLIGHT


22-11-00-710-001-A00 OPC 9 Operationally Check AFCS Go-Around Mode NOTE: Also Check TCS Mode.

48 MO or

5000 FH

ALL ± 30 Days

CHAPTER 23 – COMUNICATIONS


23-51-00-710-001-A00 OPC 8 Operationally Check Audio System Emergency Mode 500 FH ALL Not Applicable

23-60-00-720-001-A00 FNC 9 Functionally Check Static Discharger 72 MO or

8000 FH

ALL ± 30 Days

23-71-00-710-001-A00 OPC 9 Operationally Check Voice Recorder 4 Channels andArea Microphone NOTE: Or in accordance with Local Regulatory

Authority Requirements.

48 MO or

5000 FH

ALL ± 30 Days

23-71-02-710-001-A00 OPC 9 Operationally Check CVR Underwater Locator Beacon 24 MO ALL ± 30 Days

23-71-02-960-001-A00 DIS 9 Discard CVR Underwater Locator Beacon Battery (*)NOTE: ULB battery change in accordance with

manufacturer's data plate expiration date.

(*) ALL Not Applicable



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CHAPTER 24 – ELECTRICAL POWER


24-31-00-710-001-A00 OPC 9 Operationally Check Main Generation Switching Circuit 5000 FH ALL Not Applicable

24-31-00-710-002-A00 OPC 9 Operationally Check Main Generation Over currentProtection Circuit


24-31-01-900-001-A00 RST 7 Restore Main Generator P/N 30086-010 60 MO or

3200 FH

ALL Not Applicable

24-31-01-900-001-A01 RST 7 Restore Main Generator P/N 30086-011 60 MO or

4000 FH

ALL Not Applicable

24-34-00-710-001-A00 OPC 9 Operationally Check APU Generation Over currentProtection Circuit


24-34-00-710-002-A00 OPC 9 Operationally Check APU Generation Switching Circuit 5000 FH ALL Not Applicable

24-34-01-900-001-A00 RST 7 Restore APU Starter/Generator 48 MO or

1200 AH

ALL Not Applicable

24-34-01-960-001-A00 DIS 7 Discard APU Starter/Generator Brushes 800 AH ALL Not Applicable

24-35-01-720-001-A00 FNC 8 Functionally Check Back-up Battery 6 MO ALL ± 15 Days

24-35-01-900-001-A00 RST 8 Restore Back-up Battery 12 MO ALL Not Applicable

24-36-01-610-001-A00 SVC 6 Service Main Battery MARATHON P/N 32248-001 500 FH ALL Not Applicable

24-36-01-610-001-A02 SVC 6 Service Main Battery MARATHON M3 P/N 32845-001 18 MO or

2000 FH

ALL Not Applicable



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CHAPTER 24 – ELECTRICAL POWER (Continued)


24-36-01-720-001-A00 FNC 6 Functionally Check Main Battery SAFT P/N 442CH1 12 MO or

1000 FH

ALL Not Applicable

24-36-01-900-001-A00 RST 6 Restore Main Battery SAFT P/N 442CH1 12 MO ALL Not Applicable

24-40-00-720-001-A00 FNC 7 Functionally Check GPU Overvoltage Protection 5000 FH ALL Not Applicable

24-54-00-212-001-A00 GVI 7 Inspect (General Visual) PC Power Components NOTE: If PC Power System installed.

48 MO or

5000 FH

ALL ± 30 Days

24-60-00-710-001-A00 OPC 8 Operationally Check Electrical Emergency TransferCircuit


24-60-00-710-002-A00 OPC 9 Operationally Check Electrical Emergency AbnormalAlarm


CHAPTER 25 – EQUIPMENT/FURNISHINGS


25-11-01-140-001-A00 RST 8 Clean Flight Crew Seats Locking System 12 MO or

500 FH

ALL ± 15 Days

25-11-01-220-001-A00 DET 8 Inspect (Detailed Inspection) Cockpit Seats for Security of Attachment to the Track, including Restraint System

48 MO or

4000 FH

ALL ± 30 Days



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CHAPTER 25 – EQUIPMENT/FURNISHINGS (Continued)


25-21-00-212-001-A00 GVI 7 Inspect (General Visual) Passenger Seats (Fabric Cover, Tray, Safety Belt Integrity and Attachment to the Track)

48 MO or

5000 FH

ALL ± 30 Days

25-21-00-220-002-A00 DET 8 Inspect (Detailed Inspection) Flight Attendant Seats Harness, Inertial Reel for Condition and the Seat Bottom for Freedom of Movement and Returning Back to Upright Position

48 MO or

5000 FH

ALL ± 30 Days

25-60-00-212-001-A00 GVI 8 Inspect (General Visual) First Aid Kit and Medical Kit for condition and Validation P/N 106 A, 6240-37, S6-0005-311, S6-01-0005-314,70004-00, 01-00-48, 25-60-109-2, 25-60-109SL, 01-70-90, LAI 5532, 4531 and73S601005107

6 MO ALL ± 15 Days

25-60-02-900-001-A00 RST 8 Restore Flotation Vest PN 3505-101CW, 3505-101W,3500-111W and 2000-105Y NOTE: In accordance with expiration date or Local

Regulatory Authority Requirements.

24 MO ALL Not Applicable

25-60-02-900-001-A01 RST 8 Restore Flotation Vest PN MK3 NOTE: Every 24 MO after 120 MO from date of manufac-

ture; every 12 MO after 168 MO from date of manufacturer; in accordance with expiration date or Local Regulatory Authority Requirements.


25-60-02-900-001-A02 RST 8 Restore Flotation Vest PN MK20SV and MK22SV NOTE: Every 12 MO after 240 MO from date of manu-

facture; in accordance with expiration date or Local Regulatory Authority Requirements.




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25-60-02-900-001-A03 RST 8 Restore Flotation Vest PN 63600-501 (VacuumPacked) NOTE: Every 60 MO for sewn packed; in accordance

with expiration date or Local Regulatory Authority Requirements.


25-60-02-900-001-A04 RST 8 Restore Flotation Vest PN 35-21-02 NOTE: In accordance with expiration date or Local



25-60-04-710-001-A00 OPC 8 Operationally Check Megaphone P/N ACR/EM-1A 6 MO ALL ± 15 Days

25-60-04-960-001-A00 DIS 6 Discard of Megaphone Batteries P/N A CR/EM-1A 12 MO ALL Not Applicable

25-60-05-212-001-A00 GVI 8 Inspect (General Visual) Cockpit Escape Rope P/N120-15112-001

72 MO or

10000 FH

ALL ± 30 Days

25-61-00-212-001-A00 GVI 8 Inspect (General Visual) Emergency LocatorTransmitter for Condition – Proper Installation – Battery Corrosion and Leakage NOTE: Or in accordance with Local Regulatory



25-61-00-710-001-A00 OPC 8 Operationally Check Emergency Locator TransmitterSystem – Proper Operation – Crash Switch Operation NOTE: Or in accordance with Local Regulatory





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25-61-04-960-001-A00 DIS 8 Replace ELT battery ARTEX P/N 452-0130 NOTE: ELT battery change in accordance with

manufacturer data plate expiration date or Local Regulatory Authority Requirements.


25-61-04-960-001-A01 DIS 8 Replace ELT batteries SOCATA P/NsELT90A2560102000 and L94 NOTE: ELT b a t t e r i e s change i n a c c o r d a n c e

wi th manufacturer data plate expiration dateor Local Regulatory Authority Requirements.


25-61-04-960-001-A02 DIS 8 Replace ELT battery ARTEX P/N 452-0133 NOTE: ELT battery change in accordance with

manufacturer data plate expiration date or Local Regulatory Authority Requirements.


CHAPTER 26 – FIRE PROTECTION


26-15-00-720-001-A00 FNC 8 Functionally Check JAMCO Baggage Compartment Smoke Detection System (actuating each Smoke Sensor in the Baggage Compartment with a Smoke Tester) NOTE: Or 3 MO, whichever occurs first

3 MO or

500 FH

ALL Not Applicable

26-15-01-212-001-A00 VCK 8 Visually Check WALTER KIDDE Baggage Compartment Smoke Detection System Maintenance LED

18 MO or

2000 FH

ALL ± 15 Days



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CHAPTER 26 – FIRE PROTECTION (Continued)


26-21-00-720-001-A00 FNC 9 Functionally Check Engine Fire Extinguishing System NOTE: Or in accordance with Local Regulatory Authority

Requirements

36 MO or

10000 FH

ALL Not Applicable

26-21-02-280-001-A00 SDI 9 Inspect Engine Fire Extinguishing Bottle for Weight andCheck Bottle Pressure NOTE: Or in accordance with Local Regulatory

Authority Requirements


26-21-02-720-001-A00 FNC 9 Perform Hydrostatic Check of the Engine FireExtinguishing Bottle


26-21-03-720-001-A00 FNC 9 Functionally Check Engine Fire Extinguishing BottlePressure Switch NOTE: Check at each Bottle Hydrostatic Test (60 MO).


26-21-04-960-001-A00 DIS 9 Discard Engine Fire Extinguishing Bottle Cartridges NOTE: Or in accordance with manufacturer’s

recommendation.


26-21-05-720-001-A00 FNC 9 Functionally Check Two-Way “Tee” Check Valves 72 MO or

10000 FH

ALL Not Applicable

26-22-00-720-001-A00 FNC 9 Functionally Check APU Fire Extinguishing System (between Switch and Bottle Connector) and verify APU isolation by APU Fuel Shutoff Valve actuation NOTE: Or in accordance with Local Regulatory


36 MO or

10000 FH

ALL Not Applicable



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26-22-01-280-001-A00 SDI 9 Inspect APU Fire Extinguishing Bottle for Weight andCheck Bottle Pressure NOTE: Or in accordance with Local RegulatoryAuthority Requirements.


26-22-01-720-001-A00 FNC 9 Perform Hydrostatic Check of APU Fire ExtinguishingBottle


26-22-02-720-001-A00 FNC 9 Functionally Check APU Fire Extinguishing BottlePressure Switch NOTE: Check at each Bottle Hydrostatic Test (60 MO).


26-22-03-960-001-A00 DIS 9 Discard APU Fire Extinguishing Bottle Cartridges NOTE: Or in accordance with manufacturer’s recommendation


26-23-00-720-001-A00 FNC 8 Functionally Check Baggage Compartment Fire Extinguishing System (covering the Pressure Switch, Cartridge, Baggage Fire Extinguishing Switch and Electrical Hardware. Class “C” Baggage Compartment only)

48 MO or

5000 FH

ALL ± 30 Days

26-23-01-280-001-A00 SDI 6 Inspect Baggage Compartment Fire Extinguishing Bottles (High Rate and Metering) for Weight (Class “C” Baggage Compartment only)


26-23-01-720-001-A00 FNC 6 Perform Hydrostatic Check of Baggage CompartmentFire Extinguishing Bottles (High Rate and Metering)




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26-23-02-960-001-A00 DIS 6 Discard Baggage Compartment Fire Extinguishing Bottles (High Rate and Metering) Cartridges (Class “C” Baggage Compartment only) NOTE: 180 months from date of manufacture (DOM) or

120 months from date of installation, whichever occurs first.


26-23-04-720-001-A00 FNC 6 Functionally Check Two Way Check “Tee” Valve(Class “C” Baggage Compartment only)

72 MO or

10000 FH

ALL ± 30 Days

26-24-00-211-001-A00 VCK 8 Visually Check Portable Fire Extinguishers NOTE: Or in accordance with Local Regulatory



26-24-00-280-001-A00 SDI 9 Inspect Portable Fire Extinguishing Bottle for Weight(see Placard attached to the Bottle) NOTE: Or in accordance with Local Regulatory



26-24-01-720-001-A00 FNC 8 Perform Hydrostatic Check of Portable FireExtinguishing Bottles P/N 892480 NOTE: Or in accordance with Local Regulatory



26-24-01-720-001-A01 FNC 8 Perform Hydrostatic Check of Portable Fire Extinguishing Bottles P/N 100-9750, 466090, 898052, A352 Series and C352 Series NOTE: Or in accordance with Local Regulatory



26-25-01-280-001-A00 SDI 6 Inspect Lavatory Fire Extinguisher Bottle for Weight 12 MO ALL Not Applicable



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CHAPTER 27 – FLIGHT CONTROLS

REFERENCE NUMBER

TYPE

CAT DESCRIPTION LU INT EFFECT TOLERANCE

27-11-00-220-001-A00 DET 8 Inspect (Detailed Inspection) Aileron Primary Mechanical Control from Control Wheel to Aileron PCAs, Checking Cables, Pulleys, NRUs, Quadrants, Disconnect System and Mechanical Links

48 MO or

5000 FH

ALL ± 30 Days

27-11-00-640-001-A00 LUB 6 Lubricate Control Wheel Chain 48 MO or

5000 FH

ALL ± 30 Days

27-11-00-720-001-A00 FNC 6 Functionally Check Aileron Primary Mechanical Con- trol Backlash NOTE: Threshold at 15000 FH.

48 MO or

5000 FH

ALL ± 30 Days

27-11-01-720-001-A00 FNC 6 Functionally Check Tension of Aileron Control Cables NOTE: For new cables, check tension of the cable loop

affected at first 500 FH and 1000 FH before escalating to 5000 FH.

48 MO or

5000 FH

ALL ± 30 Days

27-12-00-720-001-A00 FNC 8 Functionally Check Aileron Hydraulic Actuation 96 MO or

10000 FH

ALL ± 60 Days

27-12-00-720-002-A00 FNC 8 Functionally Check Aileron Hydraulic Damping Pre- Mod. S.B. 145-27-0062

6 MO or

400 FH

EMB-145 (ALL)

± 15 Days

27-12-00-720-003-A03 FNC 8 Functionally Check External Leakage of Aileron Hydraulic Actuator Pre-Mod. SB 145-27-0063 for aircraft Certificated Under ANAC/FAA Regulations

12 MO or

1500 FH

EMB-145 (ALL)

± 15 Days



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CHAPTER 27 – FLIGHT CONTROLS (Continued)


27-12-00-720-003-A04 FNC 8 Functionally check External Leakage of Aileron Hydraulic Actuator Post-Mod. SB 145-27-0063 for aircraft Certificated Under ANAC/FAA Regulations

18 MO or

2500 FH

EMB-145 (ALL)

± 15 Days

27-12-00-720-003-A05 FNC 8 Functionally check External Leakage of Aileron Hydraulic Actuator for aircraft Certificated Under EASA Regulations

12 MO or

1000 FH

EMB-145 (ALL)

± 15 Days

27-12-01-212-001-A00 GVI 7 Inspect (Visual Inspection) Aileron PCA Hoses 48 MO or

5000 FH

ALL ± 30 Days

27-12-01-212-002-A04 GVI 8 Inspect (Visual Inspection) Aileron PCA Rod Ends/Fitting Lugs for Integrity and General Condition for aircraft Equipped with PCA P/N 394900-1003 or P/N 394900-1005

25 FH or

3 Days

EMB-145 (ALL)

Not Applicable

27-12-01-212-002-A05 GVI 8 Inspect (Visual Inspection) Aileron PCA Rod Ends/ Fitting Lugs for Integrity and General Condition Post-Mod. SB 145-27-0061 and Post-Mod. SB 145-27-0062 and Post-Mod. SB 145-57-0019 and Pre-Mod. SB145-27-0063

6 MO or

500 FH

EMB-145 (ALL)

± 15 Days

27-12-01-212-002-A06 GVI 8 Inspect (Visual Inspection) Aileron PCA Rod Ends/ Fitting Lugs for Integrity and General Condition Post-Mod. SB 145-27-0061 and Post-Mod. SB 145-27-0062 and Post-Mod. SB 145-57-0019 and Post-Mod.SB 145-27-0063 for aircraft Certificated UnderANAC/FAA Regulations

12 MO or

1000 FH

EMB-145 (ALL)

± 15 Days



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27-12-01-212-002-A07 GVI 8 Inspect (Visual Inspection) Aileron PCA Rod Ends/ Fitting Lugs for Integrity and General Condition Post-Mod. SB 145-27-0061 and Post-Mod. SB 145-27- 0062 a n d P o s t -Mod. SB 145-57-0019 for aircraft Certificated Under EASA Regulations

12 MO or

1000 FH

EMB-145 (ALL)

± 15 Days

27-12-01-720-001-A03 FNC 8 Functionally Check Aileron Actuator DampingComponents and Monitoring Devices Post-Mod. SB145-27-0062 and Pre-Mod. SB 145-27-0063 for aircraftCertificated Under ANAC/FAA Regulations

6 MO or

500 FH

EMB-145 (ALL)

± 15 Days

27-12-01-720-001-A04 FNC 8 Functionally Check Aileron Actuator DampingComponents and Monitoring Devices Post-Mod. SB145-27-0062 a n d P o s t -Mod. SB 145-27-0063 for aircraft Certificated Under ANAC/FAA Regulations

18 MO or

2500 FH

EMB-145 (ALL)

± 15 Days

27-12-01-720-001-A05 FNC 8 Functionally Check Aileron Actuator Damping Compo- nents and Monitoring Devices Post-Mod. SB 145-27-0062 for aircraft Certificated Under EASA Regulations

12 MO or

1000 FH

EMB-145 (ALL)

± 15 Days

27-12-01-720-002-A01 FNC 9 Functionally Check Aileron Actuator force Fight Post-Mod. SB 145-27-0062 for aircraft Certificated Under ANAC/FAA Regulations

24 MO or

5000 FH

ALL ± 30 Days

27-12-01-720-002-A02 FNC 9 Functionally Check Aileron Actuator force Fight Post-Mod. SB 145-27-0062 for aircraft Certificated Under EASA Regulations

12 MO or

1000 FH

EMB-145 (ALL)

± 15 Days



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27-12-03-212-001-A00 VCK 9 Inspect (Visual Inspection) Aileron Damper Rod Ends/Fitting Lugs for Integrity and General Condition Post-Mod. SB 145-27-0063 NOTE: This task is applicable only to aircraft underANAC/FAA Certifications

24 MO or

1000 FH

EMB-145 (ALL)

± 30 Days

27-12-03-720-001-A00 FNC 9 Functionally Check Aileron Damper Damping ForcePost-Mod. SB 145-27-0063 NOTE: This task is applicable only to aircraft underANAC/FAA Certifications

24 MO or

2500 FH

EMB-145 (ALL)

± 30 Days

27-12-03-720-002-A00 FNC 9 Functionally Check External Leakage of AileronDamper Post-Mod. SB 145-27-0063 NOTE: This task is applicable only to aircraft underANAC/FAA Certifications

24 MO or

2500 FH

EMB-145 (ALL)

± 30 Days

27-13-00-710-001-A00 OPC 8 Operationally Check Aileron Solenoid Manifold ShutoffFunction

48 MO or

5000 FH

ALL ± 30 Days

27-14-00-720-001-A00 FNC 9 Functionally Check Roll Trim 48 MO or

5000 FH

ALL ± 30 Days

27-15-00-710-001-A00 OPC 8 Operationally Check Aileron Disconnect System 24 MO or

5000 FH

ALL ± 30 Days

27-15-02-640-001-A00 LUB 8 Lubricate Aileron Disconnect System NOTE: The Plate Mechanism is Bench Lubricated

96 MO or

10000 FH

ALL ± 60 Days



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27-21-01-220-001-A00 DET 9 Inspect (Detailed Inspection) Rudder Primary Mechanical Control Checking Cables, Pulleys and Quadrants

48 MO or

5000 FH

ALL ± 30 Days

27-21-01-720-001-A00 FNC 9 Functionally Check Tension of Rudder Control Cables NOTE: For new cables, check tension of the cableloop affected at first 500 FH and 1000 FH beforeescalating to 5000 FH

48 MO or

5000 FH

ALL ± 30 Days

27-21-02-220-001-A00 DET 8 Inspect (Detailed Inspection) Rudder Main Control Feedback Path, PCU Linkage and Mounting Points, Rudder Actuator Attachments, Hinges, and Connecting Rods NOTE: Requires removal of Concentric andEccentric Pins

48 MO or

5000 FH

ALL ± 30 Days

27-22-00-720-001-A00 FNC 9 Functionally Check Rudder Backlash 48 MO or

5000 FH

ALL ± 30 Days

27-22-01-720-001-A00 FNC 9 Functionally Check Rudder Power Control Unit/ Actuators Differential Pressure

48 MO or

5000 FH

ALL ± 30 Days

27-22-02-212-001-A00 GVI 6 Inspect (Visual Inspection) Rudder Actuators 48 MO or

5000 FH

ALL ± 30 Days

27-31-00-720-001-A00 FNC 6 Functionally Check Elevator Primary MechanicalControl Backlash

48 MO or

5000 FH

ALL ± 30 Days


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27-31-01-220-001-A00 DET 6 Inspect (Detailed Inspection) Elevator Control Cables 48 MO or

5000 FH

ALL ± 30 Days

27-31-01-720-001-A00 FNC 6 Functionally Check Tension of Elevator Control Cables NOTE: For new cables, check tension of the cable loop affected at first 500 FH and 1000 FH before escalating to 5000 FH

48 MO or

5000 FH

ALL ± 30 Days

27-31-04-710-001-A00 OPC 9 Operationally Check Spring/Servo Tab 6 MO or

500 FH

ALL ± 15 Days

27-31-05-220-002-A00 DET 8 Inspect (Detailed Inspection) Spring Tab AttachmentLink

48 MO or

5000 FH

ALL ± 30 Days

27-35-00-640-001-A00 LUB 8 Lubricate Elevator Disconnect System NOTE: The Plate Mechanism is Bench Lubricated

96 MO or

10000 FH

ALL ± 60 Days

27-35-00-710-001-A00 OPC 8 Operationally Check Elevator Disconnect System 24 MO or

5000 FH

ALL ± 30 Days

27-36-00-710-001-A00 OPC 8 Operationally Check Stall Protection System 12 MO or

400 FH

ALL ± 15 Days

27-36-00-720-001-A00 FNC 9 Functionally Check ICE/SPS Speeds Interface Circuit 12 MO or 400 FH

ALL ± 15 Days



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27-40-00-710-002-A00 OPC 9 Operationally Check Backup/Main Cut-out Switch and Quick Disconnect Switch

48 MO or

5000 FH

ALL ± 30 Days

27-40-00-710-003-A00 OPC 9 Operationally Check Lockout Logic of HorizontalStabilizer Control Unit Post-Mod. SB-145-27-0106


27-40-00-720-001-A00 FNC 8 Functionally Check Horizontal Stabilizer Backlash 48 MO or

4000 FH

ALL ± 30 Days

27-40-02-220-001-A00 DET 8 Inspect (Detailed Inspection) Horizontal StabilizerActuator Integrity and Attachments

48 MO or

5000 FH

ALL ± 30 Days

27-40-02-610-001-A00 SVC 6 Service Horizontal Stabilizer Actuator and check for leakage


27-40-03-640-001-A00 LUB 6 Lubricate Main Pitch Trim Switches 2500 FH ALL Not Applicable

27-51-00-212-001-A00 GVI 7 Inspect (Visual Inspection) Flap Mechanical Line 48 MO or

5000 FH

ALL ± 30 Days

27-51-00-220-001-A00 DET 6 Inspect (Detailed Inspection) Flap Flexible Shafts 48 MO or

5000 FH

ALL ± 30 Days



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27-51-00-610-001-A00 SVC 6 Service Flap Screw-jack Actuators Gearbox Pre-Mod. SB 145-27-0118

48 MO or

5000 FH

ALL ± 30 Days

27-51-00-610-001-A01 SVC 6 Service Flap Screw-jack Actuators Gearbox Post-Mod. SB 145-27-0118

72 MO or

10000 FH

ALL ± 30 Days

27-51-00-640-001-A00 LUB 6 Lubricate Flap Screw-Jack Actuators (FSAs) 6 MO or

1000 FH

ALL ± 15 Days

27-51-01-720-001-A00 FNC 8 Functionally Check Flap Transmission Brake HoldingCapability

24 MO or

2500 FH

ALL ± 30 Days

27-51-15-220-001-A00 DET 8 Inspect (Detailed Inspection) Flap Rollers for StructuralIntegrity

96 MO or

10000 FH

ALL ± 60 Days

27-51-17-720-001-A00 FNC 8 Functionally Check MTB (Flap Drive Motor Unit) Holding Capability

48 MO or

5000 FH

ALL ± 30 Days

27-53-00-710-001-A00 OPC 9 Operationally Check FLAP FAIL Message 24 MO or

500 FH

ALL ± 30 Days

27-53-00-710-002-A00 OPC 8 Operationally Check of Take-off Flap Aural Warning and No Take-off Configuration Visual Warning

24 MO or

500 FH

ALL ± 30 Days



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27-63-01-710-001-A00 OPC 9 Operationally Check Spoiler System 48 MO or

5000 FH

ALL ± 30 Days

27-70-00-710-001-A00 OPC 7 Operationally Check Mechanical Gust Lock Mecha- nism

48 MO or

5000 FH

ALL ± 30 Days

27-70-00-720-001-A00 FNC 9 Functionally Check the Gap of Elevator Secondary Stop (Mechanical Gust Lock System only) Pre-Mod. SB 145-27-0079

48 MO or

4000 FH

ALL ± 30 Days

27-71-00-220-001-A00 DET 9 Inspect (Detailed Inspection) Electromechanical GustLock Mechanism

48 MO or

5000 FH

ALL ± 30 Days

27-71-00-710-003-A00 OPC 9 Operationally Check Electromechanical Gust LockSystem

12 MO or

500 FH

ALL ± 15 Days



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CHAPTER 28 – FUEL


28-11-04-710-001-A00 OPC 9 Operationally Check (Manual Check for Free Move- 96 MO ALL ± 60 Days ment and Sealing Condition) Flap Valves (Ribs 1 and 7) or NOTE: Check during Internal Tank Inspection 10000 FH

28-12-01-710-001-A00 OPC 9 Operationally Check (Manual Check) Vent Float 96 MO ALL ± 60 Days Valves (Rib 19) or NOTE: Check during Internal Tank Inspection 10000 FH

28-12-04-710-001-A00 OPC 9 Operationally Check Flap Valve (Manual Check for 96 MO ALL ± 60 Days Free Movement and Sealing Condition) or NOTE: Check during Internal Tank Inspection 10000 FH

28-12-05-211-001-A00 VCK 8 Visually Check Flame Arrestor for Honey Comb 48 MO ALL ± 30 Days Clogging, and Attaching Parts for Security or 5000 FH

28-12-05-710-001-A00 OPC 8 Operationally Check Flame Arrestor in/out Flow 48 MO ALL ± 30 Days Valves for Freedom Movement or 5000 FH




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CHAPTER 28 – FUEL (Continued)


28-21-03-720-001-A00

FNC

9 Functionally Check Relief Valve 96 MO or

10000 FH

ALL ± 60 Days

28-21-04-710-001-A00 OPC 9 Operationally Check Cross feed Valve 48 MO or

5000 FH

ALL ± 30 Days

28-21-10-710-001-A00 OPC 8 Operationally Check Fuel Feed Line Shroud 72 MO or

8000 FH

ALL ± 30 Days

28-22-03-710-001-A00 OPC 8 Operationally check APU Fuel Feed Line Shroud 72 MO or

8000 FH

ALL ± 30 Days


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28-41-00-710-001-A00 OPC 9 Operationally Check Electrical Fuel QuantityIndicating System (Fuel Low Level Logic)

48 MO or

5000 FH

ALL ± 30 Days

28-43-00-720-001-A00 FNC 9 Functionally Check Fuel Temperature IndicationSystem

96 MO or

10000 FH

ALL ± 60 Days

28-44-00-720-001-A00 FNC 9 Functionally Check Low Level Warning System NOTE: Check during Internal Tank Inspection

96 MO or

10000 FH

ALL ± 60 Days

28-45-00-710-001-A00 OPC 9 Operationally Check Low Pressure Warning System 1000 FH ALL Not applicable

28-50-01-220-001-A00 DET 8 Inspect (Detailed Inspection) Fuel Pump ElectricalHarness NOTE: This task complies with Fuel Tank Ignition

Source Prevention (SFAR 88)



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28-50-02-220-001-A00 DET 8 Inspect (Detailed Inspection) Wing Tank Unit NOTE: This task complies with Fuel Tank Ignition

Source Prevention (SFAR 88)


28-50-04-212-001-A00 GVI 8 Inspect (General Visual) Wing Stub Harnesses NOTE: EWIS/SFAR 88


28-50-05-212-001-A00 GVI 8 Inspect (General Visual) Trailing Edge Harnesses NOTE: EWIS/SFAR 88


28-50-06-212-001-A00 GVI 8 Inspect (General Visual) Leading Edge Harnesses NOTE: EWIS/SFAR 88


CHAPTER 29 – HYDRAULIC POWER


29-10-00-710-001-A00 OPC 9 Operationally Check Electric Motor Driven PumpsInput Signals

48 MO or

5000 FH

ALL ± 30 Days

29-10-00-790-001-A00 FNC 9 Functionally Check of Hydraulic Power System forInternal Leakage

96 MO or

10000 FH

ALL ± 60 Days

29-10-01-710-001-A00 OPC 8 Operationally Check Shutoff Valve by means of theHydraulic Panel Switch

48 MO or

5000 FH

ALL ± 30 Days


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CHAPTER 29 – HYDRAULIC POWER (Continued)


29-10-04-900-001-A00 DIS 7 Replace EMDP Brushes 6000 FH ALL Not Applicable

29-10-08-211-001-A00 VCK 9 Visually Check Differential Pressure Indicators for RedPins Popped out

12 MO or

500 FH

ALL ± 15 Days

29-10-10-720-001-A00 FNC 8 Functionally Check Return Filter By-Pass Valve NOTE: 10000 FH if fluid contamination is checked at

5000 FH interval

48 MO or

5000 FH

ALL ± 30 Days

29-10-13-720-001-A00 FNC 9 Functionally Check Priority Valve 48 MO or

5000 FH

ALL ± 30 Days

29-30-03-720-001-A00 FNC 9 Functionally Check Hydraulic Filters DifferentialPressure Indicators NOTE: 10000 FH if fluid contamination is checked at5000 FH interval

48 MO or

5000FH

ALL ± 30 Days

29-30-05-710-001-A00 OPC 9 Operationally Check HYD SYS OVHT Message 96 MO or

10000 FH

ALL ± 60 Days

CHAPTER 30 – ICE AND RAIN PROTECTION


30-11-05-710-001-A00 OPC 9 Operationally Check Wing Leak Thermostat 72 MO or

10000 FH

ALL ± 30 Days


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REFERENCE NUMBER TYPE CAT DESCRIPTION LU INT EFFECT

TOLERANCE

30-12-00-710-001-A00 OPC 8 Operationally Check Electrical Hardware of theHorizontal Stabilizer Thermal Anti-Icing System

48 MO or

5000 FH

ALL ± 30 Days

30-12-05-710-001-A00 OPC 9 Operationally Check Horizontal Stabilizer LeakThermostat

96 MO or

10000 FH

ALL ± 60 Days

30-20-00-220-001-A00 DET 9 Inspect (Detailed Inspection) Thermal Anti-Ice (TAI) Exhaust Duct for Condition and Security of Installation

48 MO or

5000 FH

ALL ± 30 Days

30-20-01-720-001-A00 FNC 9 Functionally Check Thermal Anti-Ice (TAI) Inter bulkhead Assembly for Leakage

48 MO or

5000 FH

ALL ± 30 Days

30-31-00-710-001-A00 OPC 9 Operationally Check Pitot & Anemometric Static PortHeating


30-31-00-710-002-A00 OPC 9 Operationally Check Pressurization Static Port Heating 5000 FH ALL Not Applicable

30-31-08-710-001-A00 OPC 9 Operationally Check Pitot Lines heater NOTE: If Installed.

96 MO or

10000FH

ALL Not Applicable

30-32-00-710-001-A00 OPC 9 Operationally Check AOA Sensor Heating 5000 FH ALL Not Applicable

30-33-00-710-001-A00 OPC 9 Operationally Check TAT Sensor Heating 5000 FH ALL Not Applicable

30-42-00-710-001-A00 OPC 9 Operationally Check Windshield Heating 48 MO or

5000 FH

ALL ± 30 Days

30-43-01-211-001-A00 FNC 9 Visually Check Rain Repellent Coating (RPC) for air- Craft Certificated Under ANAC/EASA Regulations, If Installed.

24 MO or

1500 FH

ALL ± 30 Days




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CHAPTER 31 – INDICATING/RECORDING SYSTEMS


31-21-00-710-001-A00 OPC 9 Operationally Check Digital Clock NOTE: Or in accordance with Local Regulatory

Authority Requirements. Check together with task 31-31-00-720-001-A00

48 MO or

5000 FH

ALL ± 30 Days

31-31-00-710-001-A00 DRC 9 FDR DATA - Personal Computer Downloading 12 MO ALL ± 15 Days

31-31-00-720-001-A00 FNC 6 Functionally Check Flight Data Recorder System NOTE: Or in accordance with Local Regulatory


48 MO or

5000 FH

ALL ± 30 Days

31-31-02-710-001-A00 OPC 9 Operationally Check FDR Underwater Locator Beacon 24 MO ALL ± 30 Days

31-31-02-960-001-A00 DIS 9 Discard FDR Underwater Locator Beacon Battery (*)NOTE: ULB battery change in accordance with

manufacturer's data plate expiration date


31-41-00-710-001-A00 OPC 9 Operationally Check DAU Channel Reversion Function 48 MO or

5000 FH

ALL ± 30 Days



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CHAPTER 32 – LANDING GEAR


32-10-01-900-001-A00 RST 8 Restore Main Landing Gear (MLG) Leg Strut Assy(PNs 2309-2002-Series, 2309-3002-Series, 2309-3100-Series and 2309-4002-Series) NOTE: Or 20000 FC, whichever occurs first

144 MO or

20000 FC

ALL ± 60 Days

32-10-01-900-002-A00 RST 8 Restore MLG Trailing Arm Assy (PNs 2309-2037-Series, 2309-3037-Series and 2309-4037-Series), including wheel axle NOTE: Or 20000 FC, whichever occurs first

144 MO or

20000 FC

ALL ± 60 Days

32-10-02-610-001-A00 SVC 9 Service MLG Shock Absorber NOTE: Or 15 MO, whichever occurs first.

15 MO or

2500 FH

ALL ± 15 Days

32-10-02-900-001-A00 RST 8 Restore MLG Shock Absorber Assy (PNs 2309-2005- Series) NOTE: Or 20000 FC, whichever occurs first

144 MO or

20000 FC

ALL ± 60 Days

32-10-03-900-001-A00 RST 8 Restore MLG Main Side Strut Assy (PNs 2309-2500- Series and 2309-3500-Series) NOTE: Or 20000 FC, whichever occurs first

144 MO or

20000 FC

ALL ± 60 Days

32-10-04-900-001-A00 RST 8 Restore MLG Secondary Side Strut Assy (PNs 2309-2600-Series) NOTE: Or 20000 FC, whichever occurs first

144 MO or

20000 FC

ALL ± 60 Days

32-20-01-610-001-A00 SVC 9 Service NLG Shock Absorber NOTE: Or 15 MO, whichever occurs first

15 MO or

2500 FH

ALL ± 15 Days



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CHAPTER 32 – LANDING GEAR (Continued)


32-20-01-720-001-A00 FNC 8 Functionally Check NLG Leg for Centering Cam Play NOTE: Perform at the opportunity of NLG Leg Strut Restoration


32-20-01-900-001-A00 RST 8 Restore Nose Landing Gear (NLG) Strut (PNs1170B0000-Series; 1170C0000-Series; 2233A0000-Series; and 2666A0000-Series), including Torque Link, Steering Cuff, Sliding Tube and Web Assy compo-nents; and their attaching parts NOTE: Or 20000 FC, whichever occurs first

144 MO or

20000 FC

ALL ± 60 Days

32-20-02-900-001-A00 RST 8 Restore NLG Main Drag Strut (PNs 1172B0000-Series and 1172C0000-Series) NOTE: Or 20000 FC, whichever occurs first

144 MO or

20000 FC

ALL ± 60 Days

32-20-03-900-001-A00 RST 8 Restore NLG Auxiliary Drag Strut (PNs 1173B0000- Series) NOTE: Or 20000 FC, whichever occurs first

144 MO or

20000 FC

ALL ± 60 Days

32-32-00-710-001-A00 OPC 9 Operationally Check Landing Gear Extension and Retraction (Electrical) Indication and Down lockRelays by Channels A and B

48 MO or

5000 FH

ALL ± 30 Days

32-32-02-710-001-A00 OPC 8 Operationally Check Solenoid and Down lock ReleaseButton of the Landing Gear Control Lever

96 MO or

10000 FH

ALL ± 60 Days

32-34-00-640-001-A00 LUB 8 Lubricate Landing Gear (MLG & NLG) and SteeringSystem

6 MO or

400 FH

ALL ± 15 Days




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32-34-00-710-001-A00 OPC 9 Operationally Check Landing Gear EmergencyExtension (Override Switch)

48 MO or

5000 FH

ALL ± 30 Days

32-34-00-720-001-A00 FNC 8 Functionally Check Landing Gear Emergency Extension Pre-Mod. SB 145-32-0036 and/or SB 145-32-0037

6 MO or

500 FH

ALL ± 15 Days

32-34-00-720-001-A01 FNC 8 Functionally Check Landing Gear Emergency Extension Post-Mod. SB 145-32-0036 and Post-Mod. SB 145-32-0037

48 MO or

5000 FH

ALL ± 30 Days

32-34-03-720-001-A00 FNC 8 Functionally Check Condition and Tension of Free-FallControl Cables

72 MO or

10000 FH

ALL ± 30 Days

32-41-00-720-001-A00 FNC 6 Functionally Check Main Brake System 48 MO or

5000 FH

ALL ± 30 Days

32-41-01-710-001-A00 OPC 8 Operationally Check Brake Pedal Transducer 96MO or

10000 FH

ALL ± 60 Days

32-41-07-720-001-A00 FNC 9 Functionally Check Brake Hydraulic Fuse 48 MO or

5000 FH

ALL ± 30 Days

32-41-09-710-001-A00 OPC 8 Operationally Check Return Line Check Valve of MainBrake System

48 MO or

5000 FH

ALL ± 30 Days



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32-44-00-720-001-A00 FNC 8 Functionally Check Emergency Parking Brake System 96 MO or

10000 FH

ALL ± 60 Days

32-44-02-720-001-A00 FNC 8 Functionally Check Hydraulic Accumulator for NitrogenPre-Charge

12 MO or

1000 FH

ALL ± 15 Days

32-44-06-720-001-A00 FNC 8 Functionally Check Thermal Relief Valve of theEmergency/Parking Brake System

72 MO or

10000 FH

ALL ± 30 Days

32-44-08-710-001-A00 OPC 8 Operationally Check Return Line Check Valve ofEmergency/Parking Brake System

48 MO or

5000 FH

ALL ± 30 Days

32-44-10-640-001-A00 LUB 8 Lubricate Mechanical Hardware (Handle) and Roller ofEmergency Parking Brake Valve

48 MO or

5000 FH

ALL ± 30 Days

32-49-01-610-001-A00 SVC 6 Check MLG Tire Inflation Pressure 48 hours ALL Not Applicable

32-49-02-220-001-A00 DET 7 Inspect (Detailed Inspection) of Wheels SpeedTransducer Clip in the Hub Cap Drive Clip. (*) NOTE: At each Tire change


32-49-03-220-001-A00 DET 6 Inspect (Detailed Inspection) of Brake Wear Indicator. (*) NOTE: At each Tire change


32-49-04-610-001-A00 SVC 6 Check NLG Tire Inflation Pressure 48 hours ALL Not Applicable

32-49-07-710-001-A00 OPC 8 Operationally Check Brake Shuttle Valve (*) NOTE: At each Brake replacement




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32-50-00-710-001-A00 OPC 8 Operationally Check Nose wheel Steering SystemDisengage

6 MO or

500 FH

ALL ± 15 Days

32-50-06-720-001-A00 FNC 8 Functionally Check 7-Degree Proximity Switch 48 MO or

5000 FH

ALL ± 30 Days

32-62-00-710-001-A00 OPC 8 Operationally Check Landing Gear Warning System 6 MO or

500 FH

ALL ± 15 Days

CHAPTER 33 – LIGHTS


33-47-03-720-001-A00 FNC 8 Functionally Check White Strobe Lighting SystemPre-Mod. SB 145-33-0008 NOTE: This task is applicable only to aircraft under

ANAC/FAA Certifications

12 MO or

800 FH

ALL ± 15 Days

33-47-03-720-001-A01 FNC 8 Functionally Check White Strobe Lighting SystemPost-Mod. SB 145-33-0008 NOTE: This task is applicable only to aircraft under

ANAC/FAA Certifications

12 MO or

1500 FH

ALL ± 15 Days

33-50-00-710-001-A00 OPC 8 Operationally Check Emergency Lighting System 400 FH ALL Not Applicable

33-50-04-720-001-A00

FNC

8 Functionally Check Emergency Lighting Battery Pack 18 MO ALL Not Applicable



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CHAPTER 33 – LIGHTS (Continued)


33-50-12-280-001-A00 SDI 8 Inspect Photo luminescent Floor Proximity Strip LightsUsing Test Sample NOTE: If installed


33-50-12-720-001-A00 FNC 8 Functionally Check Photo luminescent Floor ProximityStrip Lights System

48 MO or

5000 FH

ALL ± 30 Days

33-51-00-720-001-A00 FNC 8 Functionally Check Rechargeable Flashlight System(MODEL EF-2C)


33-51-00-720-001-A01 FNC 8 Functionally Check Non Rechargeable FlashlightSystem (MODEL EF-1)

6 MO ALL ± 15 Days

CHAPTER 34 – NAVIGATION


34-01-00-720-001-A00 FNC 8 Functionally Check Integrated Standby InstrumentSystem – ISIS NOTE: Or in accordance with Local Regulatory



34-11-00-720-001-A00 FNC 6 Functionally Check Standby Altimeter Indicator NOTE: Or in accordance with Local Regulatory



34-13-00-610-001-A00 SVC 6 Clean Pitot-Static System NOTE: Or in accordance with Local Regulatory


72 MO or

10000 FH

ALL ± 30 Days



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CHAPTER 33 – LIGHTS (Continued)


33-50-12-280-001-A00 SDI 8 Inspect Photoluminescent Floor Proximity Strip LightsUsing Test Sample NOTE: If installed


33-50-12-720-001-A00 FNC 8 Functionally Check Photoluminescent Floor ProximityStrip Lights System

48 MO or

5000 FH

ALL ± 30 Days

33-51-00-720-001-A00 FNC 8 Functionally Check Rechargeable Flashlight System(MODEL EF-2C)


33-51-00-720-001-A01 FNC 8 Functionally Check Non Rechargeable FlashlightSystem (MODEL EF-1)

6 MO ALL ± 15 Days

CHAPTER 34 – NAVIGATION


34-01-00-720-001-A00 FNC 8 Functionally Check Integrated Standby InstrumentSystem – ISIS NOTE: Or in accordance with Local Regulatory



34-11-00-720-001-A00 FNC 6 Functionally Check Standby Altimeter Indicator NOTE: Or in accordance with Local Regulatory



34-13-00-610-001-A00 SVC 6 Clean Pitot-Static System NOTE: Or in accordance with Local Regulatory


72 MO or

10000 FH

ALL ± 30 Days



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CHAPTER 34 – NAVIGATION (Continued)


34-13-00-680-001-A00 SVC 6 Drain Pitot Lines Pre-Mod. SB 145-34-0021 36 MO or

5000 FH

ALL ± 30 Days

34-13-00-680-001-A01 SVC 6 Drain Pitot Lines Post-Mod. SB 145-34-0021 6 MO or

500 FH

ALL ± 15 Days

34-13-00-790-001-A00 FNC 6 Functionally Check Pitot-Static System for Leakage NOTE: Or in accordance with Local Regulatory



34-15-00-720-001-A00 FNC 8 Functionally Check ADC system NOTE: Or in accordance with Local Regulatory



34-21-00-710-001-A00 OPC 9 Operationally Check AHRS DG Mode (AHRS AH-800 only)

48 MO or

5000 FH

ALL ± 30 Days

34-21-03-140-001-A00 RST 6 Clean AHRS Fan Filter 1000 FH ALL Not Applicable

34-22-00-710-001-A00 OPC 9 Operationally Check Electronic Flight InstrumentSystem Reversion Function

48 MO or

5000 FH

ALL ± 30 Days

34-25-00-720-001-A00 FNC 6 Functionally Check Standby Compass for proper compensation NOTE: Or in accordance with Local Regulatory





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CHAPTER 34 – NAVIGATION (Continued)


34-27-03-140-001-A00 RST 6 Clean Dual IRS Mounting Tray Fan Filter (Dual IRS System only)


34-41-00-710-001-A00 OPC 9 Operationally Check GPWS/Windshear 48 MO or

5000 FH

ALL ± 30 Days

34-41-00-710-003-A00 OPC 9 Operationally Check EGPWS/Windshear 48 MO or

5000 FH

ALL ± 30 Days

34-52-00-720-001-A00 FNC 6 Functionally Check Transponder System NOTE: Or in accordance with Local Regulatory



CHAPTER 35 – OXYGEN


35-10-00-710-001-A00 OPC 8 Operationally Check Crew Oxygen Masks EROS 48 MO or

5000 FH

ALL ± 30 Days

35-10-00-710-001-A01 OPC 8 Operationally Check Crew Oxygen Mask Puritan and/orB/E Aerospace

48 MO or

2350 FH

ALL ± 30 Days

35-10-07-720-001-A00 FNC 8 Functionally Check Crew Oxygen Cylinder PressureRegulator NOTE: At the time of Cylinder Hydrostatic Test.




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CHAPTER 35 – OXYGEN (Continued)


35-10-07-720-002-A00 FNC 9 Functionally Check (Hydrostatic Test) Crew OxygenCylinder. NOTE: Or in accordance with Local Regulatory Authority Requirements


35-11-02-212-001-A00 VCK 8 Visually Check Pressure Transducer Indication onMFD Versus External Gauge Indication

24 MO or

2500 FH

ALL ± 30 Days

35-20-00-710-001-A00 OPC 8 Operationally Check Passenger Oxygen System inMANUAL Mode (Chemical Oxygen System only)

12 MO or

2000 FH

ALL ± 15 Days

35-20-00-720-001-A00 FNC 9 Functionally Check Passenger Oxygen System inAUTO Mode (Chemical Oxygen System only)

48 MO or

5000 FH

ALL ± 30 Days

35-20-01-211-001-A00 VCK 8 Visually Check Chemical Oxygen Generator(Chemical Oxygen System only)

48 MO or

5000 FH

ALL ± 30 Days

35-20-01-960-001-A00 DIS 8 Discard Chemical Oxygen Generator (ChemicalOxygen System only)


35-20-04-211-001-A00 VCK 8 Visually Check Passenger Oxygen Mask (ChemicalOxygen System only)

48 MO or

5000 FH

ALL ± 30 Days

35-20-06-212-001-A00 CVI 8 Inspect (General Visual) of Lavatory Gaseous Oxygen Cylinder. (NOTE: POST-MOD SB 145-35-0008)

7500 FH ALL ± 60 Days

35-20-06-960-001-A00 DIS 8 Discard of Passenger Gaseous Oxygen Cylinder. NOTE: From the manufacturing date. POST-MOD SB 145-35-0008


35-21-00-211-001-A00 VCK 8 Visually Check Pressure Indication Between MFD Versus Cylinder Gauge and Charging Gauge Versus Cylinder Gauge (Gaseous Oxygen System (Shuttle Configuration only))

24 MO or

2000 FH




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35-21-00-710-001-A00 OPC 8 Operationally Check Passenger Oxygen System in MANUAL Mode (Gaseous Oxygen System (Shuttle Configuration only))

18 MO or

2000 FH


35-21-00-710-002-A00 OPC 8 Operationally Check "VLV CLOSED" Indication Circuit(Gaseous Oxygen System (Shuttle Configuration only))

18 MO or

2000 FH


35-21-00-710-003-A00 OPC 8 Operationally Check "PAX OXY LOW PRESS" Caution Message (Gaseous Oxygen System (Shuttle Configuration only))

48 MO or

5000 FH


35-21-00-720-001-A00 FNC 8 Functionally Check Passenger Oxygen System in AUTO Mode (Gaseous Oxygen System (Shuttle Configuration only))

48 MO or

5000 FH


35-21-02-211-001-A00 VCK 8 Visually Check Passenger Oxygen Mask Assy (GaseousOxygen System (Shuttle Configuration only))

24 MO or

2000 FH


35-21-04-720-001-A00 FNC 8 Functionally Check (Hydrostatic Test) Passenger Oxygen Cylinder (Gaseous Oxygen System (Shuttle Configuration only))

36 MO EMB-135LR Not Applicable

35-21-04-960-001-A00 DIS 8 Discard Passenger Oxygen Cylinder (GaseousOxygen System (Shuttle Configuration only))

180 MO EMB-135LR Not Applicable

35-21-06-710-001-A00 OPC 8 Operationally Check Electric Pulse/Latching On-Off Valve (Gaseous Oxygen System (Shuttle Configuration only))

60 MO or

2000 FH




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35-21-07-720-001-A00 FNC 8 Functionally Check of Oxygen Sequence Regulator (Gaseous Oxygen System (Shuttle Configuration only))

60 MO or

2000 FH


35-21-15-710-001-A00 OPC 8 Check (Leak) Passenger Oxygen Distribution (HP) Lines (Gaseous Oxygen System (Shuttle Configuration only))

48 MO or

5000 FH


35-21-16-710-001-A00 OPC 8 Check (Leak) Passenger Oxygen Distribution (LP) Lines (Gaseous Oxygen System (Shuttle Configuration only))

48 MO or

5000 FH


35-30-01-211-001-A00 VCK 9 Visually Check Portable Oxygen Cylinder GaugePressure Indication NOTE: Or in accordance with Local Regulatory


12 MO or

500 FH

ALL ± 15 Days

35-30-01-720-001-A00 FNC 9 Functionally Check Portable Oxygen CylinderPressure Regulator NOTE: At the time of Cylinder Hydrostatic Test


35-30-01-720-002-A00 FNC 9 Functionally Check (Hydrostatic Test) PortableOxygen Cylinder NOTE: Or in accordance with Local Regulatory



35-30-02-211-001-A00 VCK 9 Visually Check Continuous Flow Mask 24 MO or

2500 FH

ALL ± 30 Days



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35-30-03-960-001-A00 DIS 8 Discard Protective Breathing Equipment PN MR10042N, 15-40F-11, 15-40F-10, 15-40F and E28180-10


CHAPTER 36 – PNEUMATIC


36-10-01-130-001-A00 RST 6 Clean Crossbleed Valve Filter by Ultrasonic Method 5000 FH ALL Not Applicable

36-11-01-220-001-A00 DET 6 Inspect (Detailed Inspection) Engine Low PressureBleed Air Check Valve P/N 816603-3

48 MO or

5000 FH

ALL ± 30 Days

36-11-02-130-001-A00 RST 9 Clean High-Stage Valve Filter by Ultrasonic Method 5000 FH ALL Not Applicable

36-11-03-130-001-A00 RST 6 Clean Fan Air Valve Filter by Ultrasonic Method 5000 FH ALL Not Applicable

36-11-04-110-001-A00 RST 6 Clean Pre-Cooler by Chemical Method 60 MO or

6000 FH

ALL ± 30 Days

36-11-05-130-001-A00 RST 6 Clean Engine Bleed Valve Filter by Ultrasonic MethodPre-Mod. SB 145-36-0028


36-20-00-710-001-A00 OPC 8 Operationally Check Bleed Valve Indicating Function 96 MO or

10000 FH

ALL ± 60 Days



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CHAPTER 36 – PNEUMATIC (Continued)


36-20-00-720-001-A00 FNC 8 Functionally Check the Over temperature WarningCircuit

96 MO or

10000 FH

ALL ± 60 Days

36-20-00-720-002-A00 FNC 9 Functionally Check Differential Pressure ProtectionFunction Pre-Mod. SB 145-36-0018

72 MO or

10000 FH

ALL ± 30 Days

36-20-02-710-001-A00 OPC 8 Operationally Check Thermal Switch 72 MO or

10000 FH

ALL ± 30 Days

36-20-02-710-002-A00 OPC 8 Operationally Check Massive Leakage Switch 48 MO or

5000 FH

ALL ± 30 Days

CHAPTER 38 – WATER / WASTE


38-32-04-960-001-A00 DIS 7 Replace Waste Drain Valve O’Ring 18 MO ALL ± 15 Days

38-32-10-960-001-A00 DIS 7 Replace Waste Drain Valve Cap Seal 60 MO ALL ± 30 Days



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CHAPTER 45 – CENTRAL MAINTENANCE SYSTEM


45-45-00-970-002-A00 DRC 7 CMC DATA – Personal Computer Downloading 6 MO or

500 FH

ALL ± 15 Days

CHAPTER 49 – AIRBORNE POWER UNIT


49-17-00-160-001-A00 RST 9 Clean APU Drains Post-Mod. SB 145-49-0029 48 MO or

5000 FH

ALL ± 30 Days

49-31-00-710-001-A01 OPC 9 Perform Check of the FADEC BITE Display for FaultMessages (APU Model T-62T-40C14 (APS 500R) only)

400 AH ALL Not Applicable

49-31-04-960-001-A00 DIS 9 Discard Inlet Fuel Filter APU Model T-62T-40C11 (APS500) only


49-31-04-960-001-A01 DIS 9 Discard Inlet Fuel Filter APU Model T-62T-40C14 (APS500R) only)


49-41-03-220-001-A00 DET 6 Inspect (Detailed Inspection) Igniter Plug 1200 AH ALL Not Applicable

49-62-00-710-001-A00 OPC 9 Operationally Check Emergency Shutdown by UsingAPU Fuel Shutoff Switch and Fire Test Switch

72 MO or

10000 FH

ALL ± 30 Days

49-91-00-610-001-A00 SVC 6 Check Oil Level and Service Oil System as required 400 AH ALL Not Applicable



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CHAPTER 49 – AIRBORNE POWER UNIT (Continued)


49-91-00-680-001-A00 SVC 9 Drain and Replace Oil Supply 12 MO or

2000 AH

ALL Not Applicable

49-91-01-960-001-A00 DIS 9 Discard Oil Filter Element 24 MO or

2000 AH

ALL Not Applicable

CHAPTER 52 – DOORS


52-00-00-211-001-A00 VCK 7 Visually Check Locking Red Marks NOTE: Repaint if necessary

48 MO or

5000 FH

ALL ± 30 Days

52-11-00-640-001-A00 LUB 6 Lubricate Standard Main Door Actuating and LockingMechanism

48 MO or

5000 FH

ALL ± 30 Days

52-11-00-720-005-A00 FNC 8 Functionally Check Standard Main Door Actuating, Latching and Locking Mechanism

48 MO or

5000 FH

ALL ± 30 Days

52-12-00-710-001-A00 OPC 9 Operationally Check Alternate Opening System 48 MO or

5000 FH

ALL ± 30 Days

52-12-00-720-001-A00 FNC 7 Functionally Check Main Door Hydraulic AccumulatorNitrogen Charge (Standard Main Door Model only)

24 MO or

2500 FH

ALL ± 30 Days



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CHAPTER 52 – DOORS (Continued)


52-14-00-211-001-A00 VCK 9 Inspect (Visual Inspection) Standard Main Door DrainHoles for Obstruction or Damage

48 MO or

5000 FH

ALL ± 30 Days

52-14-01-710-001-A00 OPC 9 Operationally Check Main Door Drain Valves (StandardMain Door Only)

48 MO or

5000 FH

ALL ± 30 Days

52-18-00-640-001-A00 LUB 6 Lubricate Side-Hinged Main Door Actuating andLocking Mechanism

24 MO or

5000 FH

ALL ± 30 Days

52-18-06-720-001-A00 FNC 8 Functionally Check Side-Hinged Main door Actuating, Latching and Locking Mechanism

48 MO or

5000 FH

ALL ± 30 Days

52-21-00-640-001-A00 LUB 8 Lubricate Passenger Cabin Escape Hatch SupportPins

48 MO or

5000 FH

ALL ± 30 Days

52-21-00-710-001-A00 OPC 8 Operationally Check Passenger Cabin Escape HatchMechanism

48 MO or

5000 FH

ALL ± 30 Days

52-22-00-710-001-A00 OPC 9 Operationally Check Cockpit Emergency Exit 48 MO or

5000 FH

ALL ± 30 Days



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52-22-01-640-001-A00 LUB 9 Lubricate Cockpit Emergency Exit Locking Mechanism 48 MO or

5000 FH

ALL ± 30 Days

52-31-00-640-001-A00 LUB 6 Lubricate Baggage Door Gear Box 48 MO or

5000 FH

ALL ± 30 Days

52-32-00-220-001-A00 DET 7 Inspect Baggage Door Lifting and Lowering Mechanism for General Condition and Torsion Bar for Torsion

48 MO or

5000 FH

ALL ± 30 Days

52-42-01-220-001-A00 DET 9 Inspect (Detailed Inspection) Cockpit UnderfloorAccess Hatch Mechanism

48 MO or

5000 FH

ALL ± 30 Days

52-43-00-640-001-A00 LUB 6 Lubricate Service Door Actuating and LockingMechanism

24 MO or

5000 FH

ALL ± 30 Days

52-43-06-720-001-A00 FNC 8 Functionally Check Service Door Actuating, Latching and Locking Mechanism

48 MO or

5000 FH

ALL ± 30 Days

52-44-01-220-001-A00 DET 9 Inspect (Detailed Inspection) Rear ElectronicCompartment Door Mechanism

48 MO or

5000 FH

ALL ± 30 Days

52-51-00-720-001-A00 FNC 8 Functionally Check Reinforced Cockpit Door 4000 FH ALL Not Applicable

52-71-00-710-001-A00 OPC 8 Operationally Check Forward Electronic CompartmentDoor Warning Message

48 MO or

5000 FH

ALL ± 30 Days



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52-72-00-710-001-A00 OPC 9 Operationally Check Rigging Door Warning Message 48 MO or

5000 FH

ALL ± 30 Days

52-73-00-710-001-A00 OPC 9 Operationally Check Main Door Warning Message 48 MO or

5000 FH

ALL ± 30 Days

52-73-01-720-001-A00 FNC 9 Functionally Check Main Door Warning Microswitches 48 MO or

5000 FH

ALL ± 30 Days

52-74-00-710-001-A00 OPC 9 Operationally Check Service Door Warning Message 48 MO or

5000 FH

ALL ± 30 Days

52-74-01-720-001-A00 FNC 9 Functionally Check Service Door WarningMicroswitches

48 MO or

5000 FH

ALL ± 30 Days

52-75-00-710-001-A00 OPC 8 Operationally Check Emergency Exit WarningMessage

48 MO or

5000 FH

ALL ± 30 Days

52-76-00-710-001-A00 OPC 8 Operationally Check Baggage Door Warning Message 48 MO or

5000 FH

ALL ± 30 Days

52-77-00-710-001-A00 OPC 8 Operationally Check Rear Electronic CompartmentDoor Warning Message

48 MO or

5000 FH

ALL ± 30 Days



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CHAPTER 53 – FUSELAGE


53-00-01-220-001-A00 DET 9 Inspect (Detailed Inspection) Fuselage Drain Valves forObstruction or Damage

48 MO or

5000 FH

ALL ± 30 Days

53-21-02-140-001-A00 RST 7 Clean Main Door-Frame Rollers 48 MO or

5000 FH

ALL ± 30 Days

53-21-02-640-001-A00 LUB 7 Lubricate Main Door Frame Rollers 12 MO or

500 FH

ALL ± 15 Days

53-21-12-140-001-A00 RST 7 Clean Service Door-Frame Rollers 48 MO or

5000 FH

ALL ± 30 Days

53-21-12-640-001-A00 LUB 7 Lubricate Service Door Frame Rollers 6 MO or

500 FH

ALL ± 15 Days

CHAPTER 71 – POWER PLANT


71-10-00-211-001-A00 VCK 9 Visually Check Cowling Seals 48 MOor

5000 FH

ALL ± 30 Days



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CHAPTER 71 – POWER PLANT (Continued)

REFERENCE NUMBER TYPE CAT DESCRIPTION LU INT EFFECT TOLERANCE71-10-00-220-001-A00 DET 9 Inspect (Detailed Inspection) Cowling Inboard/

Outboard Attachment and Surrounding Structure 48 MO

or 5000 FH

ALL ± 30 Days

71-20-00-220-001-A00 DET 8 Inspect (Detailed Inspection) Engine Mounting Assy 48 MOor

5000 FH

ALL ± 30 Days

71-60-01-211-001-A00 VCK 9 Visually Check Air Intake Attachment 48 MOor

5000 FH

ALL ± 30 Days

71-60-01-211-002-A00 VCK 9 Visually Check Air Intake Rear Bulkhead and FireShield

48 MOor

5000 FH

ALL ± 30 Days

CHAPTER 72 – ENGINE


72-21-01-220-001-A00 DET 9 Inspect (Detailed Inspection) Fan Blades 4000 FH ALL Not Applicable

72-21-20-220-001-A00 DET 8 Inspect (Detailed Inspection) Fan Spinner Pre-Mod. Rolls-Royce SB 3007A-72-167


72-63-01-710-001-A00 OPC 9 Operationally Check Starter Drain Adapter Post-Mod. SB AE3007A-72-253 and Pre-Mod. SB AE3007A-72-330




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CHAPTER 73 – ENGINE FUEL AND CONTROL


73-11-10-130-001-A00 RST 6 Clean Fuel Nozzles except P/N 23075904, P/N23077006 and P/N 23087207


73-11-10-130-001-A01 RST 6 Clean Fuel Nozzles P/N 23075904, P/N 23077006 andP/N 23087207


73-21-00-211-001-A00 VCK 9 Visually Check Fuel Pump and Metering Unit for FuelLeakage


73-21-06-720-001-A00 FNC 9 Functionally Check Fuel Filter Impending BypassIndicating System


73-22-01-720-003-A00 FNC 9 Inspect Multi-Function Display for ENG( ) LT FAULT and ENG ( ) SCHED MAINT REPAIR Maintenance Messages

6 MO or

500 FH

ALL ± 15 Days

73-30-04-211-001-A00 VCK 9 Visually Check the FADEC Anti-Vibration Mounts 5000 FH ALL Not Applicable

CHAPTER 74 – IGNITION


74-21-01-220-001-A00 DVI 6 Inspect (Detailed Inspection) Igniters 4000 FH ALL Not Applicable



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CHAPTER 76 – ENGINE CONTROLS


76-12-00-710-001-A00 OPC 8 Operationally Check WOW input signal to FADEC 96 MO or

10000 FH

ALL ± 60 Days

76-13-03-710-001-A00 OPC 8 Operationally Check Idle Lockout NOTE: Only for aircraft with Thrust Reversers

12 MO or

500 FH

ALL ± 15 Days

76-20-00-710-001-A00 OPC 8 Operationally Check Emergency Shutdown System 24 MO or

2500 FH

ALL ± 30 Days

CHAPTER 78 – EXHAUST


78-10-01-212-002-A00 GVI 8 Inspect (Visual Inspection) Plain Exhaust Assy for Damage, Failure or Irregularities (for aircraft without Thrust Reversers only)

72 MO or

8000 FH

ALL ± 30 Days

78-31-00-220-001-A00 DET 8 Inspect (Detailed Inspection) Thrust ReverserStructure

72 MO or

10000 FH

ALL ± 30 Days

78-32-00-211-001-A00 VCK 8 Visually Check Thrust Reverser 1RY and 3RY Locks 12 MO or

500 FH

ALL ± 15 Days



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CHAPTER 78 – EXHAUST (Continued)


78-32-00-710-001-A00 OPC 8 Operationally Check Thrust Reverser 2RY and 3RY Locks

12 MO or

1000 FH

ALL ± 15 Days

78-33-00-720-001-A00 FNC 9 Functionally Check Thrust Reverser Control LeverMicroswitches

96 MO or

10000 FH

ALL ± 60 Days

78-34-01-720-001-A00 FNC 8 Functionally Check Stow/Transit Thrust ReverserMicroswitches for Insulation P/Ns 83-990-137,83-990-152 and 83-990-166

12 MO or

1200 FH

ALL Not Applicable

CHAPTER 79 – OIL


79-25-02-211-001-A00 VCK 9 Visually Check Fuel Cooled Assembly (FCOC) 10000 FH ALL Not Applicable

79-27-00-211-001-A00 VCK 9 Visually Check Oil Plumbing 10000 FH ALL Not Applicable



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CHAPTER 79 – OIL (Continued)


79-34-00-212-001-A00 GVI 6 Inspect Multi-Function Display for ENG1(2) OIL DEBRIS Maintenance Message (Except for aircraft equipped with AE3007 A1E Engine) NOTE: This task is applicable to aircraft Pre-Mod. SB145-79-001 or Post-Mod SB 145-79-002 and Pre-Mod. SB 145-79-003

50 FH EMB-135LR EMB-145MP

Not Applicable

79-34-01-720-001-A00 FNC 9 Functionally Check Indicating Magnetic Plug Assembly 10000 FH ALL Not Applicable

79-37-00-720-001-A00 FNC 9 Functionally Check Oil Filter Impending Bypass Indi- cating System




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CHAPTER 80 – STARTING


80-10-01-720-001-A00 FNC 6 Functionally Check Air Turbine Starter including oil servicing

6 MO or

500 FH

ALL ± 15 Days

80-10-02-160-001-A00 SVC 6 Clean Start Control Valve Filter Pre-Mod. SB 145-80-0003 12 MO or

1000 FH

ALL ± 15 Days

80-10-02-160-001-A01 SVC 6 Clean Start Control Valve Filter Post-Mod. SB 145-80-0003 48 MO or

5000 FH

ALL ± 30 Days



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TASK DEFINITION

General VisualInspection (GVI)

A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or droplight and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked.

Detailed Inspection (DET)

An intensive examination of a specific item, installation or assembly to detect damage, failure or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed, appropriate inspection aids such as mirrors, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.

Special DetailedInspection (SDE)

An intensive examination of a specific item(s), installation, or assembly to detect damage, failure or irregularity. The examination is likely to make extensive use of specialized inspection techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required.

]]

SECTION 3 STRUCTURAL INSPECTION REQUIREMENTS

3.1 GENERAL

This section contains all Structural Inspection Requirements resulting from the MSG-3 analysis. These requirements consist of maintenance tasks and associated intervals developed according to the aircraft certified operating capabilities and are intended to detect and prevent any structural degradation caused by fatigue, environmental deterioration, or accidental damage during the aircraft operational life. Detection of major accidental damage such as that caused by bird strike and large ground handling equipment is considered obvious through various tell-tale signs. The Structural Inspection Requirements are based on an assessment of structural design information, fatigue and damage tolerance evaluations from Damage Tolerance Analysis Reports and service experience with similar structure and related results. The requirements also take into account the applicability and effectiveness of various methods of preventing, controlling or detecting structural deterioration like thresholds and repeated intervals. Upon the performance of the inspection, each individual operator must take into account any type of damage occurrence, such as fatigue, environmental and accidental damage.

3.2 TYPES OF TASKS

The MSG-3 resulting tasks are established to provide timely detection and repair of structural damage which may occur during aircraft normal operation. Specific criteria for applicability and effectiveness

lead to the following task definitions (According to ATA Spec 107 - Visual Inspection Guide):



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3.3 MAINTENANCE TASK INTERVALS

Task intervals are given in Flight Cycles (FC).

3.4 REPORTING OF INSPECTION RESULTS

Reports of structural significant defects should be submitted to the Regulatory Authorities, as required under their regulations. In addition, a structural inspection summary should be submitted to

EMBRAER for inspection accomplished on all items of this section. All significant structural defects found should also be reported. Based on these reports, EMBRAER will evaluate and issue the results of the Structural Program fleet. 3.5 LIST OF SCHEDULED MAINTENANCE REQUIRE-

MENTS PRESENTATION The maintenance requirements are presented per chapter as below:

REFERENCE NUMBER TYPE DESCRIPTION THRESHOLD

(Flight Cycles)INT ZONE EFFECTIVITY

32-10-00-210-801-A00 GVI Externally inspect these MAIN LANDING GEAR components:

• Leg structure equipped (left) (SSI 32-10-01)

– 2,500FC

721/731 ALL

a b c d e f g

a - REFERENCE NUMBER b - TYPE - Task type as defined in 3.2. c - DESCRIPTION - Description of the task to be performed. d - THRESHOLD - The first structural inspection as defined in 3.8. e - INTERVAL - Task interval as defined in 3.3. f - ZONE - Aircraft zone where the task is performed. g - EFFECTIVITY - Task effectivity.



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3.6 FATIGUE THRESHOLD

The first inspection (threshold) for fatigue damage corresponds to a period from the time of first entry into service to the timely detection of fatigue damage. These values of thresholds are applicable only to Structural Significant Items (SSI) previously analyzed by EMBRAER and covered by the Structural Section, where the inspection is controlled in flight cycles. Inspections directly related to fatigue damage detection, based on the MSG-3 analysis, Damage Toler- ance Analysis and Full Scale Fatigue Test, will occur after a thresh-

old(s) proposed by the manufacturer and approved by the regulatory authorities. Such thresholds have been established on the basis of the Full Scale Fatigue Test results factored by an appropriate scatter factor. These are subject to further change as additional fatigue testing results are obtained. The Fatigue Threshold values have also been included in the Airworthiness Limitation Requirements – section A2 of this document in order to establish a Fatigue Threshold Limit for all SSI’s whose inspection is governed by fatigue concerns.

3.7 SSIs FOR WHICH BOTH THE STRUCTURAL INSPECTION AND THE CPCP BASIC TASK ARE TO BE ACCOMPLISHED:

Some SSIs, for which FD (Fatigue Damage) is a critical source of damage according to the MSG-3 process have been selected to have the CPCP basic task performed, it being described in Corro- sion Prevention and Control Program – CPCP, item 4.7, to control fatigue damage which is based on the damage tolerance evaluation, and keep corrosion at Corrosion Level 1 or better.

The CPCP basic task has to be performed at the same time as the fatigue inspection, starting from the first inspection (fatigue threshold), if applicable, and continuing with the fatigue-related inspections defined in each task, in order to guarantee the efficient corrosion control for these SSIs raising fatigue concerns. For the tasks that cover these SSIs, a note has been included in the task description field to ensure the accomplishment of the basic task inspection together with the structural inspection.



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STRUCTURAL INSPECTION REQUIREMENTS


REFERENCE NUMBER

TYPE

DESCRIPTION THRESHOLD

(Flight Cycles) LU INT ZONE EFFECT TOLERANCE

32-10-00-210-801-A00 GVI Externally inspect the MAIN LANDING GEAR components: • Trailing arm - MLG (SSI 32-10-03)

– 96 MO or

5000 FC

721/731 ALL ± 60 Days

32-10-00-220-801-A00 DET Externally inspect the MAIN LANDING GEAR components: • Wheel axle MLG (SSI 32-10-04)

– 48 MO or

2500 FC

721/731 ALL ± 30 Days

32-20-00-210-801-A00 GVI Externally inspect the NOSE LANDING GEAR components: • Strut (main fitting) – NLG(SSI 32-20-12)

– 96 MO or

5000 FC

711 ALL ± 60 Days

32-20-00-210-802-A00 GVI Externally inspect the NOSE LANDING GEAR components: • Auxiliary drag strut bottom stay(SSI 32-20-16)

– 96 MO or

5000 FC

711 ALL ± 60 Days

32-20-00-210-803-A00 GVI Externally inspect the NOSE LANDING GEAR components: • Main drag strut top stay- NLG(SSI 32-20-13)

– 96 MO or

5000 FC

711 ALL ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles) LU INT ZONE EFFECT TOLERANCE

32-20-00-210-804-A00 GVI Externally inspect the NOSE LANDING GEAR components:

• Auxiliary drag strut top stay- NLG (SSI 32-20-15)

– 96 MO or

5000 FC

711 ALL ± 60 Days


• Torque links - NLG (SSI 32-20-17)

– 96 MO or

5000 FC

711 ALL ± 60 Days


• Sliding tube - NLG (SSI 32-20-18)

– 96 MO or

2500 FC

711 ALL ± 60 Days

32-20-00-220-801-A00 DET Externally inspect the NOSE LANDING GEAR components:

• Wheel axle (SSI 32-20-19)

– 48 MO or

2500 FC

711 ALL ± 30 Days



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CHAPTER 52 – DOORS (STANDARD MODEL)

REFERENCE NUMBER

TYPE

DESCRIPTION

THRESHOLD (Flight Cycles)

LU INT ZONE EFFECT TOLERANCE

52-10-00-220-801-A00 DET Internally inspect the MAIN DOOR (STANDARD MODEL) components: • Main door folding flap stops(SSI 52-10-04) NOTE: During this inspection, the

CPCP basic task shall also be performed for this SSI

– 48 MO or

5000 FC

811 ALL ± 30 Days

52-10-00-220-806-A00

DET

Internally inspect the MAIN DOOR (STANDARD MODEL) components: • Main door folding flap structure(SSI 52-10-02)

–

96 MO or

10000 FC

811 ALL ± 60 Days

52-10-00-220-807-A00 DET Internally inspect the MAIN DOOR (STANDARD MODEL) components: • Main door structure (SSI 52-10-01)

– 96 MO or

5000 FC

811 ALL ± 60 Days

52-10-00-220-808-A00 DET Externally inspect the MAIN DOOR (STANDARD MODEL) components: • Main door folding flap structure(SSI 52-10-02)

– 96 MO or

5000 FC

811 ALL ± 60 Days

52-10-00-220-809-A00 DET Externally inspect the MAIN DOOR (STANDARD MODEL) components: • Stop & backup structures (SSI 52-10-03)

144MO or

30000 FC

48 MO or

2502 FC

811 EMB-145MP ± 30 Days



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CHAPTER 52 – DOORS (STANDARD MODEL) (Continued)

REFERENCE NUMBER

TYPE

DESCRIPTION



52-10-00-220-810-A00 DET Internally inspect the MAIN DOOR (STANDARD MODEL) components: • Stop & backup structures (SSI 52-10-03)

144 MO or

30000 FC

48 MO or

5000 FC

811 EMB-145MP ± 30 Days

52-10-00-220-811-A00 DET Externally inspect the MAIN DOOR (STANDARD MODEL) components: • Attachment fittings-to-fuselage &interface parts (SSI 52-10-05)

144 MO or

30000 FC

96 MO or

5000 FC

811 EMB-145MP ± 60 Days

52-10-00-220-812-A00 DET Internally inspect the MAIN DOOR (STANDARD MODEL) components: • Attachment fittings-to-fuselage &interface parts (SSI 52-10-05)

144 MO or

30000 FC

96 MO or

10000 FC

811 EMB-145MP ± 60 Days



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CHAPTER 52 – DOORS (SIDE-HINGED MODEL)

REFERENCE NUMBER

TYPE


(Flight Cycles)


52-10-00-220-813-A00 DET Externally inspect the MAIN DOOR (STANDARD MODEL) components:

• Attachment fittings-to-fuselage &interface parts (SSI 52-10-05)

144 MO or

30000 FC

96 MO or

5000 FC

811 EMB-135LR ± 60 Days

52-10-00-220-814-A00 DET Internally inspect the MAIN DOOR (STANDARD MODEL) components:

• Attachment fittings-to-fuselage &interface parts (SSI 52-10-05)

144 MO or

30000 FC

96 MO or

10000 FC

811 EMB-135LR ± 60 Days

52-10-00-220-815-A00 DET Externally inspect the MAIN DOOR (STANDARD MODEL) components:

• Stop & backup structures(SSI 52-10-03)

144 MO or

30000 FC

48 MO or

2502 FC

811 EMB-135LR ± 30 Days

52-10-00-220-816-A00 DET Internally inspect the MAIN DOOR (STANDARD MODEL) components:

• Stop & backup structures

(SSI 52-10-03)

144 MO or

30000 FC

48 MO or

5000 FC

811 EMB-135LR ± 30 Days

52-10-00-220-801-A01 DET Internally inspect the MAIN DOOR (SIDE-HINGED MODEL) components: • Main door folding flap stops(SSI 52-10-04) NOTE: During this inspection, the


– 48 MO or

5000 FC

811 ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)

LU INT

ZONE

EFFECT

TOLERANCE

52-10-00-220-802-A01 DET Internally inspect the MAIN DOOR (SIDE-HINGED MODEL) components:

• Main door folding flap structure(SSI 52-10-02)

– 96 MO or

10000 FC

811 ALL ± 60 Days

52-10-00-220-805-A01

DET

Internally inspect the MAIN DOOR (SIDE-HINGED MODEL) components:

• Main door structure (SSI 52-10-01)

–

96 MO or

4447 FC

811 ALL ± 60 Days

52-10-00-220-806-A01

DET

Externally inspect the MAIN DOOR (SIDE-HINGED MODEL) components:


–

96 MO or

4447 FC

811 ALL ± 60 Days

52-10-00-220-807-A01

DET

Externally inspect the MAIN DOOR (SIDE-HINGED MODEL) components:

• Main door folding flap structure(SSI 52-10-02)

–

96 MO or

10000 FC

811 ALL ± 60 Days



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CHAPTER 52 – DOORS (SIDE-HINGED MODEL) (Continued)

REFERENCE NUMBER

TYPE


(Flight Cycles)

LU INT

ZONE

EFFECT

TOLERANCE

52-10-00-220-808-A01 DET Externally inspect the MAIN DOOR (SIDE-HINGED MODEL) components:


144 MO or

30000 FC

48 MO or

2502 FC

811 EMB-145MP ± 30 Days



144 MO or

30000 FC

96 MO or

4447 FC

811 EMB-145MP ± 60 Days

52-10-00-220-810-A01 DET Externally inspect the MAIN DOOR (SIDE-HINGED MODEL) components:


144 MO or

30000 FC

48 MO or

2502 FC

811 EMB-135LR ± 30 Days



144 MO or

30000 FC

96 MO or

4447 FC

811 EMB-135LR ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


52-21-00-220-804-A00

DET

Externally inspect the PASSENGER CABIN ESCAPE HATCH components:

• Escape hatch structure(SSI 52-21-06)

144 MO or

30000 FC

96 MO

or 5000 FC

812/822 EMB-145MP ± 60 Days

52-21-00-220-805-A00

DET

Internally inspect the PASSENGER CABIN ESCAPE HATCH components: • Escape hatch structure (SSI 52-21-06)

144 MO or

30000 FC

96 MO

or 5060 FC

812/822 EMB-145MP ± 60 Days

52-21-00-220-806-A00 DET Internally inspect the PASSENGER CABIN ESCAPE HATCH components: • Escape hatch window frame

(SSI 52-21-07)

144 MO or

30000 FC

96 MO or

6060 FC

812/822 EMB-145MP ± 60 Days

52-21-00-220-807-A00 DET Externally inspect the PASSENGER CABIN ESCAPE HATCH components: • Escape hatch structure (SSI 52-21-07)

144 MO or

30000 FC

96 MO or

5000 FC

812/822 EMB-135LR ± 60 Days

52-21-00-220-808-A00 DET Internally inspect the PASSENGER CABIN ESCAPE HATCH components: • Escape hatch structure (SSI 52-21-06)

144 MO or

30000 FC

96 MO or

5060 FC

812/822 EMB-135LR ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


52-21-00-220-809-A00 DET Internally inspect the PASSENGER CABIN ESCAPE HATCH components: • Escape hatch window frame

(SSI 52-21-07)

144 MO or

30000 FC

96 MO or

6060 FC

812/822 EMB-135LR ± 60 Days

52-30-00-220-802-A00 DET Internally inspect the BAGGAGE DOORcomponents: • Baggage door stops and fittings

(SSI 52-30-09)

144 MO or

30000 FC

96 MO or

4318 FC

813 EMB-145MP ± 60 Days

52-30-00-220-803-A00 DET Internally inspect the BAGGAGE DOOR components: • Baggage door stops and fittings

(SSI 52-30-09)

144 MO or

30000 FC

96 MO or

4318 FC

813 EMB-135LR ± 60 Days



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REFERENCE NUMBER

TYPE

DESCRIPTION



52-43-00-210-801-A00 GVI Internally inspect the SERVICE DOORcomponents: • Service door folding flap structure

(SSI 52-43-11) NOTE: During this inspection, the


– 96 MO or

10000 FC

821 ALL ± 60 Days

52-43-00-210-802-A00 GVI Externally inspect the SERVICE DOORcomponents: • Service door folding flap structure

(SSI 52-43-11)

– 10000 FC 821 ALL Not Applicable

52-43-00-220-801-A00 DET Externally inspect the SERVICE DOORcomponents: • Service door window frame

(SSI 52-43-12)

– 96 MO or

5000 FC

821 ALL ± 60 Days

52-43-00-220-803-A00

DET

Internally inspect the SERVICE DOORcomponents: • Service door window frame



–

96 MO or

5000 FC

821 ALL ± 60 Days



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REFERENCE NUMBER

TYPE

DESCRIPTION



52-43-00-220-807-A00 DET Externally inspect the SERVICE DOORcomponents: • Service door stops & backup structure

(SSI 52-43-13)

144 MO or

22000 FC

48 MO or

2465 FC

821 EMB-145MP ± 30 Days

52-43-00-220-808-A00 DET Internally inspect the SERVICE DOORcomponents: • Service door stops & backup structure



144 MO or

22000 FC

48 MO or

4640 FC

821 EMB-145MP ± 30 Days

52-43-00-220-809-A00 DET Externally inspect the SERVICE DOORcomponents: • Service door folding flap stops

(SSI 52-43-14)

144 MO or

30000 FC

96 MOor

4975 FC

821 EMB-145MP ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


52-43-00-220-810-A00 DET Internally inspect the SERVICE DOORcomponents: • Service door folding flap stops



144 MO or

30000 FC

96 MOor

5000 FC

821 EMB-145MP ± 60 Days

52-43-00-220-811-A00 DET Externally inspect the SERVICE DOORcomponents:

• Service door stops & backup structure

(SSI 52-43-13)

144 MO or

22250 FC

48 MOor

2465 FC

821 EMB-135LR ± 30 Days




144 MO or

22250 FC

48 MOor

2465 FC

821 EMB-135LR ± 30 Days

52-43-00-220-813-A00 DET Externally inspect the SERVICE DOORcomponents:

• Service door folding flap stops

(SSI 52-43-14)

144 MO or

30000 FC

96 MOor

4975 FC

821 EMB-135LR ± 60 Days




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REFERENCE NUMBER

TYPE


(Flight Cycles)



(SSI 52-43-14) NOTE: During this inspection, the CPCP basic task shall also be performed for this SSI

144 MO or

30000 FC

96 MOor

5000 FC

821 EMB-135LR ± 60 Days

52-44-00-220-801-A00 DET Externally inspect the REARELECTRONIC COMPARTMENT DOORcomponents: • Rear electronic compartment door

structure (SSI 52-44-01)

144 MO or

12000 FC

48 MOor

10000 FC

272 ALL ± 30 Days

52-44-00-220-802-A00 DET Internally inspect the REARELECTRONIC COMPARTMENT DOORcomponents: • Rear electronic compartment door


144 MO or

12000 FC

48 MOor

10000 FC

272 ALL ± 30 Days




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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-11-00-220-801-A00 DET Internally inspect the FUSELAGEcomponent: • Fuselage skin panel at stringers,

frames/bulkheads, and splices(SSI 53-10-07)

144 MO or

30000 FC

96 MO or

10000 FC

213/214 EMB-135LR ± 60 Days

53-11-00-220-803-A00 DET Internally inspect the FUSELAGEcomponent: • Fuselage skin panel at stringers,

frames/bulkheads, and splices (SSI 53-10-07)

144 MO or

30000 FC

96 MO or

10000 FC

213/214 EMB-145MP ± 60 Days

53-11-00-220-804-A00 DET Internally inspect the FUSELAGEcomponents: • Forward pressure bulkhead (SSI 53-10-26)

144 MO or

24000 FC

96 MO or

10000 FC

115/116215/216





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CHAPTER 53 – FUSELAGE (Continued)

REFERENCE NUMBER

TYPE


(Flight Cycles)


53-11-00-220-805-A00 DET Internally inspect the FUSELAGEcomponents: • Frames (SSI 53-10-43)

– 96 MO or

19737 FC

113/114213/214

EMB-145MPEMB-135LR

± 60 Days

53-11-00-220-807-A00

DET

Internally inspect the FUSELAGEcomponents:

• Forward pressure bulkhead

(SSI 53-10-26)

144 MO or

24000 FC

96 MO or

10000 FC

115/116215/216

EMB-135LR

± 60 Days


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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-12-00-210-801-A00 GVI Externally inspect the FUSELAGEcomponents: • Fuselage skin panel at stringers,

frames/bulkheads, and splices(SSI 53-10-07) NOTE: Applicable to aircraft Pre-Mod.

SB 145-53-0051 or Pre-Mod. SB 145-53-0067

144 MO or

22000 FC

96 MO or

328 FC

123/124223/224

ALL ± 60 Days

53-12-00-220-802-A00 DET Internally inspect the FUSELAGEcomponents: • Windshield cutout structure

(SSI 53-10-17)

144 MO or

10000 FC

96 MO or

5896 FC

223/224 EMB-145MPEMB-135LR

± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-12-00-220-803-A00 DET Internally inspect the FUSELAGEcomponents: • Windshield center post, including its

attachment and lower fitting(SSI 53-10-19)

– 5896 FC 223/224 EMB-145MPEMB-135LR

Not Applicable

53-12-00-220-804-A00 DET Internally inspect the FUSELAGEcomponents: • Cockpit window cutout structure

(SSI 53-10-18)

– 96 MO or

6666 FC

223/224225/226

EMB-145MPEMB-135LR

± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-12-00-220-805-A00 DET Internally inspect the FUSELAGEcomponents: • Windshield lateral post and its

attachment (SSI 53-10-20)

144 MO or

30000 FC

6666 FC 223/224 EMB-135LR Not Applicable

53-12-00-220-806-A00 DET Internally inspect the FUSELAGEcomponents: • Cockpit window rear post and its


– 6666 FC 223/224 EMB-145MP EMB-135LR

Not Applicable



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REFERENCE NUMBER

TYPE

DESCRIPTION



53-12-00-220-807-A00 DET Internally inspect the FUSELAGEcomponents: • Forward pressure bulkhead

(SSI 53-10-26)

120 MO or

18000 FC

96 MO or

10000 FC

121/122 EMB-145MPEMB-135LR

± 60 Days


attachments and lower fitting(SSI 53-10-19) NOTE: Applicable to aircraft Pre-Mod.

SB 145-53-0007

144 MO or

12000 FC

4000 FC 221/222 EMB-145MPEMB-135LR

Not Applicable



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-12-00-220-808-A02

DET

Internally inspect the FUSELAGEcomponents: • Windshield center post, including its

attachments and lower fitting (SSI 53-10-19) NOTE: Applicable to aircraft

Post-Mod. SB 145-53-0007

144 MO or

26166 FC


53-12-00-220-809-A00 DET Internally inspect the FUSELAGEcomponents: • Cockpit floor beams and columns

(SSI 53-10-27)

– 96 MO or

10000 FC

123/124 EMB-145MP EMB-135LR

± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-12-00-220-810-A00 DET Internally inspect the FUSELAGEcomponents: • Windshield cutout structure

(SSI 53-10-17)

144 MO or

20000 FC

96 MO or

5896 FC

225/226 EMB-145MPEMB-135LR

± 60 Days


– 96 MO or

10000 FC

223/224 ALL ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-12-00-220-815-A00

DET

Internally inspect the FUSELAGEcomponents: • Forward pressure bulkhead

(SSI 53-10-26)

120 MO or

18000 FC

96 MO or

9933 FC

221/222

EMB-145MP EMB-135LR

± 60 Days

53-12-00-220-816-A00 DET Externally inspect the FUSELAGEcomponents: • Fuselage skin panel at stringers,

frames/bulkheads, and splices (SSI 53-10-07) NOTE: Applicable to aircraft Post-

Mod. SB 145-53-0051 or Post-Mod. SB 145-53-0067

– 96 MO or

10000 FC

123/124223/224

ALL ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-12-00-220-817-A00 DET Internally inspect the FUSELAGEcomponents: • Windshield lateral post and its


144 MO or

30000 FC

6666 FC 223/224 EMB-145MP Not Applicable


attachments and lower fitting (SSI 53-10-19) NOTE: Applicable to aircraft

Post -Mod. SB 145-53-0007

144 MO or

26000 FC




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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-12-00-250-801-A00

SDE

Internally inspect the FUSELAGE components using Eddy Current inspection method: • Windshield center post, including itsattachment and lower fitting(SSI 53-10-19) NOTE: Applicable to aircraft Pre-Mod.

SB145-53-0058 and the inspection shall be performedon the Eyelet fitting “Only”

20000 FC

2,672 FC 223/224 ALL Not Applicable



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-12-00-250-801-A01 SDE Internally inspect the FUSELAGE components using Eddy Current inspection method: •Windshield center post, including itsattachment and lower fitting (SSI53-10-19) NOTE: Applicable to aircraft Post-

Mod. SB145-53-0058 and the inspection shall be performed on the Eyelet fitting “Only”

– 30000 FC 223/224 ALL Not Applicable

53-21-00-210-801-A00 GVI Externally inspect the FUSELAGEcomponents: •Fuselage skin panel at stringers, frames/bulkheads, and splices (SSI53-20-07)

144 MO or

29400 FC

48 MO or

5000 FC

131/132 EMB-135LR ± 30 Days

53-21-00-210-805-A00 GVI Internally inspect the FUSELAGEcomponents: •Main door attachment fittings and interface parts (SSI 53-20-04)

– 96 MO or

10000 FC

231 ALL ± 60 Days

53-21-00-210-806-A00 GVI Internally inspect the FUSELAGEcomponents: • Service door attachment fittings and

interface parts (SSI 53-20-05)

– 96 MO or

10000 FC

232 ALL ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)



frames/bulkheads, and splices (SSI53-20-07)

144 MO or

29000 FC

48 MO or

5000 FC

131/132 EMB-145MP ± 30 Days

53-21-00-220-802-A00 DET Externally inspect the FUSELAGEcomponents: • Stops and backup structures for main

door (SSI 53-20-01)

144 MO or

25141 FC

48 MO or

3735 FC

231 EMB-135LR ± 30 Days

53-21-00-220-803-A00 DET Internally inspect the FUSELAGEcomponents: • Stops and backup structure for main

door (SSI 53-20-01) NOTE: During this inspection, the


144 MO or

25395 FC

48 MO or

5000 FC

231 EMB-135LR ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-21-00-220-805-A00 DET Internally inspect the FUSELAGEcomponents: • Fuselage skin panel at stringers,


144 MO or

10000 FC

96 MO or

9816 FC

233/234 EMB-145MP EMB-135LR

± 60 Days

53-21-00-220-806-A00 DET Internally inspect the FUSELAGEcomponents: • Frame 15 & 18 LHS splices at

stringers 3L & 16L (SSI 53-20-12) NOTE: During this inspection, the


144 MO or

30000 FC

96 MO or

2979 FC

231/233 EMB-145MP ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-21-00-220-807-A00 DET Externally inspect the FUSELAGEcomponents: • Service door cutout reinforcing

structure (SSI 53-20-10) NOTE: Remove the bumper plate, if

installed

144 MO or

12000 FC

96 MO or

5000 FC

132/232234


53-21-00-220-811-A00 DET Externally inspect the FUSELAGEcomponents: • Fuselage skin longitudinal splice along

main door cutout (SSI 53-20-41)

– 48 MO or

5000 FC

231 EMB-145MP ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-21-00-220-812-A00 DET Externally inspect the FUSELAGEcomponents: • Fuselage skin longitudinal splice along

service door cutout (SSI 53-20-42)

– 96 MO or

5000 FC

232 EMB-145MP ± 60 Days

53-21-00-220-813-A00 DET Externally inspect the FUSELAGEcomponents: • Stops and backup structures for

service door (SSI 53-20-02)

– 48 MO or

5000 FC

232 ALL ± 30 Days

53-21-00-220-814-A00 DET Externally inspect the FUSELAGEcomponents: • Passenger cabin window frame

(SSI 53-20-06)

144 MO or

30000 FC

96 MO or

2500 FC

231 EMB-135LR ± 60 Days

53-21-00-220-815-A00 DET Externally inspect the FUSELAGEcomponents: • Passenger door cutout reinforcing


144 MO or

13000 FC

96 MO or

5000 FC

131/231233




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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-21-00-220-816-A00 DET Externally inspect the FUSELAGEcomponents: • Frames 15 & 18 LHS splices at

stringers 3L & 16L (SSI 53-20-12)

144 MO or

30000 FC

96 MO or

2764 FC

231/233 EMB-135LR ± 60 Days

53-21-00-220-817-A00 DET Externally inspect the FUSELAGEcomponents: • Stringers 6 & 16 splices at frames 20 &

22 (SSI 53-20-13)

144 MO or

30000 FC

96 MO or

2764 FC

232 EMB-135LR ± 60 Days

53-21-00-220-818-A00 DET Internally inspect the FUSELAGEcomponents: • Passenger cabin window frame



144 MO or

20000 FC

96 MO or

5000 FC

231 EMB-135LR ± 60 Days

53-21-00-220-819-A00 DET Internally inspect the FUSELAGEcomponents: • Passenger door cutout reinforcing

structures (SSI 53-20-09) NOTE: During this inspection, the


144 MO or

10000 FC

96 MO or

5000 FC

131/231233/

EMB-145MP EMB-135LR

± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-21-00-220-820-A00 DET Internally inspect the FUSELAGEcomponents: • Service door cutout reinforcing

structures (SSI 53-20-10) NOTE: During this inspection, the


144 MO or

10000 FC

96 MO or

5000 FC

132/232234

EMB-145MP EMB-135LR

± 60 Days

53-21-00-220-821-A00 DET Internally inspect the FUSELAGEcomponents: • Fuselage skin longitudinal splices along

main door cutout (SSI 53-20-41) NOTE: During this inspection, the


144 MO or

30000 FC

96 MO or

4932 FC

231 EMB-135LR ± 60 Days


service door cutout (SSI 53-20-42) NOTE: During this inspection, the


144 MO or

30000 FC

96 MO or

5000 FC

232 EMB-135LR ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-21-00-220-823-A00 DET Internally inspect the FUSELAGEcomponents: • Stringer 6 & 16 splices at frames 20 &

22 (SSI 53-20-13) NOTE: During this inspection, the


144 MO or

30000 FC

96 MO or

2979 FC

232 EMB-145MP ± 60 Days

53-21-00-220-824-A00 DET Internally inspect the FUSELAGEcomponents: • Fuselage skin longitudinal splice



144 MO or

20000 FC

96 MO or

10000 FC

131/132231/232




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REFERENCE NUMBER

TYPE


(Flight Cycles)



frames/ bulkheads, and splices (SSI 53-20-07)

144 MO or

20000 FC

96 MO or

9816 FC

231/232 EMB-145MP EMB-135LR

± 60 Days


144 MO or

18000 FC

96 MO or

10000 FC

233/234 EMB-135LR ± 60 Days

53-21-00-220-827-A00 DET Internally inspect the FUSELAGEcomponents: • Fuselage skin longitudinal splice

(SSI 53-20-08)

144 MO or

20000 FC

96 MO or

10000 FC

233/234 EMB-145MP ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-21-00-220-828-A00 DET Internally inspect the FUSELAGEcomponents: • Frame 15 & 18 LHS splices at

stringers 3 L& 16L (SSI 53-20-12) NOTE: During this inspection, the


144 MO or

30000 FC

96 MOor

2979 FC

231/233 EMB-135LR ± 60 Days

53-21-00-220-829-A00 DET Internally inspect the FUSELAGEcomponents: • Stringer 6 & 16 splices at frames 20 &

22 (SSI 53-20-13) NOTE: During this inspection, the


144 MO or

30000 FC

96 MOor

2979 FC

232 EMB-135LR ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-21-00-220-839-A00

DET

Externally inspect the FUSELAGEcomponents: • Fuselage skin panel at stringers,


–

96 MO or

5000 FC

231/232233/234




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TYPE

DESCRIPTION



53-21-00-220-842-A00

DET

Internally inspect the FUSELAGEcomponents: • Frames (SSI 53-20-43)

144 MO or

18000 FC

96 MO or

9816 FC

233/234

EMB-145MP

± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-21-00-220-846-A00

DET

Externally inspect the FUSELAGEcomponents: • Stops and backup structures for main

door (SSI 53-20-01)

144 MO or

25000 FC

48 MO

or 3735 FC

231 EMB-145MP ± 30 Days

53-21-00-220-847-A00

DET

Internally inspect the FUSELAGEcomponents: • Stops and backup structure for main

door (SSI 53-20-01) NOTE: During this inspection, the


144 MO or

25000 FC

48 MO or

5000 FC

231 EMB-145MP ± 30 Days



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REFERENCE NUMBER

TYPE

DESCRIPTION



53-21-00-220-848-A00 DET Externally inspect the FUSELAGEcomponents: • Passenger cabin window frame

(SSI 53-20-06)

144 MO or

30000 FC

96 MO or

2500 FC

231 EMB-145MP ± 60 Days

53-21-00-220-849-A00 DET Internally inspect the FUSELAGEcomponents: • Passenger cabin window frame



144 MO or

30000 FC

96 MO or

5000 FC

231 EMB-145MP ± 60 Days

53-21-00-220-850-A00 DET Externally inspect the FUSELAGEcomponents: • Frames 15 & 18 LHS splices at

stringers 3L & 16L (SSI 53-20-12)

144 MO or

30000 FC

96 MO or

2764 FC

231 233




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TYPE


(Flight Cycles)


53-21-00-220-851-A00 DET Externally inspect the FUSELAGEcomponents: • Stringers 6 & 16 splices at frames 20 &

22 (SSI 53-20-13)

144 MO or

30000 FC

96 MO or

2764 FC

232 EMB-145MP ± 60 Days

53-21-00-220-852-A00 DET Internally inspect the FUSELAGEcomponents: • Fuselage skin longitudinal splices

along main door cutout (SSI 53-20-41)NOTE: During this inspection, the


144 MO or

30000 FC

96 MO or

4932 FC

231 EMB-145MP ± 60 Days


service door cutout (SSI 53-20-42) NOTE: During this inspection, the


144 MO or

30000 FC

96 MO or

5000 FC

232 EMB-145MP ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-21-00-220-856-A00

DET

Externally inspect the FUSELAGEcomponents:

• Fuselage skin panel at stringers frames/bulkheads and splices (SSI 53-20-07)

144 MO or

21331 FC

96 MO or

5000 FC

231/232

EMB-135LR

± 60 Days

53-21-00-220-857-A00

DET

Externally inspect the FUSELAGEcomponents:

• Fuselage skin panel at stringers frames/bulkheads and splices (SSI 53-20-07)

144 MO or

10000 FC

96 MO or

5000 FC

233/234 EMB-135ER ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-21-00-220-858-A00 DET Internally inspect the FUSELAGEcomponents:

• Fuselage skin longitudinal splice (SSI 53-20-08) NOTE: During this inspection, the CPCP basic task shall also be performed for this SSI

144 MO or

30000 FC

96 MO or

10000 FC

131/132231/232



• Fuselage skin longitudinal splice (SSI 53-20-08)

144 MO or

30000 FC

96 MO or

10000 FC

233/234 EMB-135LR ± 60 Days

53-21-00-220-860-A00 DET Externally inspect the FUSELAGEcomponents:

• Passenger door cutout reinforcing structure (SSI 53-20-09)

144 MO or

22855 FC

48 MO or

5000 FC

131/231233



• Service door cutout reinforcing structure (SSI 53-20-10) NOTE: Remove the bumper plate ifinstalled

144 MO or

25141 FC

48 MO or

5000 FC

132/232234




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TYPE


(Flight Cycles)



• Fuselage skin longitudinal splices along main door cutout (SSI 53-20-41)

144 MO or

30000 FC

96 MO or

5000 FC

231 EMB-135LR ± 60 Days


• Fuselage skin longitudinal splice along service door cutout (SSI 53-20-42)

144 MO or

30000 FC

96 MO or

5000 FC

232 EMB-135LR ± 60 Days



144 MO or

30000 FC

48 MO or

2500 FC

141/142243/244


53-22-00-210-804-A00 GVI Externally inspect the FUSELAGEcomponents: • Fuselage skin panel at stringer,


144 MO or

30000 FC

96 MO or

3831 FC

241/242 EMB-135LR ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-22-00-210-805-A00 GVI Externally inspect the FUSELAGEcomponents: • Fuselage skin panel at stringer,


144 MO or

30000 FC

48 MO or

2500 FC

141/142241/242243/244




144 MO or

30000 FC

96 MO or

10000 FC

243/244 EMB-135LR ± 60 Days

53-22-00-220-802-A00 DET Internally inspect the FUSELAGEcomponents: • Fuselage skin circumferential splice

(SSI 53-20-14)

– 96 MO or

10000 FC

243/244 EMB-145MP ± 60 Days


– 96 MO or

10000 FC

243/244 ALL ± 60 Days



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TYPE


(Flight Cycles)


53-22-00-220-806-A00

DET

Internally inspect the FUSELAGEcomponents: • Fuselage skin panel at stringers,


144 MO or

30000 FC

96 MO

or 10000 FC

243/244 EMB-145MP ± 60 Days


• Fuselage skin circumferential splice (SSI 53-20-14)

144 MO or

30000 FC

96 MO or

10000 FC

243/244 EMB-135LR ± 60 Days



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TYPE


(Flight Cycles)


53-23-00-210-802-A00 GVI Internally inspect the FUSELAGEcomponents: • Over wing fuselage skin panel



– 96 MO or

10000 FC

251/252 EMB-145MP EMB-135LR

± 60 Days



144 MO or

30000 FC

96 MO or

3388 FC

253/254 EMB-135LR ± 60 Days



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TYPE


(Flight Cycles)


53-23-00-210-805-A00 GVI Externally inspect the FUSELAGEcomponents: • Over wing fuselage skin panel

(SSI 53-20-16)

– 96 MO or

9167 FC

251/252 EMB-135LR ± 60 Days

53-23-00-210-808-A00

GVI

Externally inspect the FUSELAGEcomponents: • Over wing Fuselage skin panel

(SSI 53-20-16)

–

96 MO or

10000 FC

251/252 EMB-145MP ± 60 Days


frames/bulkheads, and splices (SSI 53-20-07) NOTE: Applicable to aircraft Pre-Mod.

SB 145-00-0032

144 MO or

30000 FC

96 MO or

3388 FC

253/254 EMB-145MP ± 60 Days



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TYPE


(Flight Cycles)


53-23-00-220-802-A00

DET



144 MO

or 30000 FC

96 MO or

10000 FC

253/254

EMB-135LR

± 60 Days

53-23-00-220-803-A00

DET



144 MO or

30000 FC

96 MO

or 6140 FC

251/252 EMB-135LR ± 60 Days



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119 of 732


REFERENCE NUMBER

TYPE


(Flight Cycles)



– 96 MO or

10000 FC

253/254 ALL ± 60 Days



144 MO or

30000 FC

96 MO or

20000 FC

251/252 EMB-135LR ± 60 Days



144 MO or

30000 FC

96 MO or

10000 FC

251/252 EMB-145MP ± 60 Days

53-23-00-220-808-A00 DET Internally inspect the FUSELAGEcomponents: • Fuselage machined bulkhead

(SSI 53-20-30)

144 MO or

30000 FC

96 MO or

10000 FC

251/252253/254




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(Flight Cycles)





144 MO or

30000 FC

96 MO or

9167 FC

151/152153/154


53-23-00-220-814-A00

DET

Internally inspect the FUSELAGEcomponents: • Fuselage machined bulkhead

(SSI 53-20-30)

144 MO or

30000 FC

96 MO or

9443 FC

251/252253/254




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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-23-00-220-815-A00 DET Externally inspect the FUSELAGEcomponents: • Skin and reinforcement around

escape hatch cutout (SSI 53-20-51)

– 48 MO or

4725 FC

251/252 EMB-135LR ± 30 Days


frames/bulkheads, and splices (SSI 53-20-07) NOTE: Applicable to aircraf t Post-

Mod. SB 145-00-0032, under ANAC/FAA Certifications

144 MO or

30000 FC

96 MO or

2571 FC

253/254 EMB-145MP ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)



escape hatch cutout (SSI 53-20-51) NOTE: Applicable to aircraft Pre-Mod.

SB 145-00-0032

– 48 MOor

4725 FC

251/252 EMB-145MP ± 30 Days


escape hatch cutout (SSI 53-20-51) NOTE: Applicable to aircraft Post-


– 48 MOor

3670 FC

251/252 EMB-145MP ± 30 Days

53-23-00-220-821-A00

DET



144 MO or

30000 FC

96 MO or

20000 FC

251/252 EMB-145MP ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)




144 MO or

30000 FC

96 MO or

10000 FC

253/254 EMB-145MP ± 60 Days




144 MO or

30000 FC

96 MO or

10000 FC

151/152153/154




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TYPE


(Flight Cycles)


53-24-00-210-801-A00

GVI



144 MO or

30000 FC

96 MO

or 5000 FC

263/264 EMB-145MP ± 60 Days



144 MO or

30000 FC

48 MO or

5000 FC

161/162261/262


53-24-00-210-804-A00 GVI Internally inspect the FUSELAGEcomponents: • Fuselage skin circumferential splice

(SSI 53-20-14)

– 96 MO or

10000 FC

263/264 EMB-145MP ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)




144 MO or

30000 FC

96 MO or

4750 FC

263/264 EMB-135LR ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)




144 MO or

30000 FC

48 MO or

5000 FC

161/162261/262


53-24-00-210-812-A00 GVI Externally inspect the FUSELAGEcomponents:

• Fuselage skin panel at stringers frames/bulkheads and splices. (SSI 53-20-07)

144 MO or

30000 FC

96 MO or

10000 FC

263/264 EMB-135LR ± 60 Days



144 MO or

30000 FC

96 MO or

10000 FC

263/264 EMB-135LR ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-24-00-220-806-A00

DET


frames/bulkheads, and splices (SSI 53-20-07) NOTE: Applicable to aircraft Pre-Mod.

SB 145-00-0032

144 MO or

30000 FC

96 MO or

9521 FC

263/264

EMB-145MP

± 60 Days

53-24-00-220-806-A01

DET


frames/bulkheads, and splices (SSI 53-20-07) NOTE: Applicable to aircraft Post-


144 MO or

30000 FC

96 MO or

5337 FC

263/264 EMB-145MP ± 60 Days



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128 of 732


REFERENCE NUMBER

TYPE


(Flight Cycles)



– 96 MO or

9521 FC

263/264 EMB-145MP ± 60 Days



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129 of 732


REFERENCE NUMBER

TYPE


(Flight Cycles)



• Frames (SSI 53-20-43)

144 MO or

30000 FC

96 MO or

10000 FC

263/264 EMB-135LR ± 60 Days



144 MO or

20000 FC

96 MO or

5000 FC

273/274 EMB-135LR ± 60 Days

53-31-00-210-804-A00 GVI Externally inspect the FUSELAGEcomponents: • Fuselage skin panel at pressure

bulkhead (SSI 53-30-15)

144 MO or

20000 FC

96 MO or

10000 FC

171/172 EMB-135LR ± 60 Days



144 MO or

20000 FC

96 MO or

10000 FC

271/272 EMB-135LR ± 60 Days

53-31-00-210-806-A00 GVI Externally inspect the FUSELAGEcomponents: • Fuselage machined bulkhead

(SSI 53-30-30)

144 MO or

20000 FC

10000 FC 271/272273/274

EMB-135LR Not Applicable



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-31-00-210-807-A00 GVI Externally inspect the FUSELAGEcomponents: • Fuselage to vertical stabilizer spar

attachment fitting (SSI 53-30-38) NOTE: During this inspection, the


– 10000 FC 273/274 ALL Not Applicable



– 96 MO or

5000 FC

171/172 EMB-145MPEMB-135LR

± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-31-00-210-810-A00 GVI Internally inspect the FUSELAGEcomponents: • Baggage compartment floor beams

and columns (SSI 53-30-28)

144 MO or

14000 FC

96 MO or

8416 FC

171/172 EMB-145MP ± 60 Days



144 MO or

30000 FC

96 MO or

5000 FC

273/274 EMB-145MP ± 60 Days



144 MO or

20000 FC

96 MO or

5000 FC

273/274 EMB-135LR ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-31-00-210-820-A00 GVI Internally inspect the FUSELAGEcomponents: • Baggage compartment floor beams

and columns (SSI 53-30-28)

– 96 MO or

10000 FC

171/172 EMB-135LR ± 60 Days



144 MO or

30000 FC

96 MO or

5000 FC

273/274 EMB-145MP ± 60 Days



144 MO or

30000 FC

96 MO or

10000 FC

171/172271/272




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TYPE

DESCRIPTION



53-31-00-210-823-A00 GVI Externally inspect the FUSELAGEcomponents: • Fuselage machined bulkhead

(SSI 53-30-30)

144 MO or

30000 FC

10000 FC 271/272273/274

EMB-145MP Not Applicable

53-31-00-220-802-A00 DET Internally inspect the FUSELAGEcomponents: • Fuselage skin panel at pressure


144 MO or

20000 FC

96 MO or

10000 FC

271/272 EMB-135LR ± 60 Days


– 96 MO or

10000 FC

271/272 ALL ± 60 Days



144 MO or

20000 FC

96 MO or

10000 FC

273/274 EMB-135LR ± 60 Days



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Section

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REFERENCE NUMBER

TYPE


(Flight Cycles)



frames/bulkheads, and splices (SSI 53-30-07) NOTE: During this inspection, the

CPCP basic task shall also be performed for this SSI.

144 MO or

14000 FC

96 MO or

10000 FC

271/272 EMB-135LR ± 60 Days

53-31-00-220-808-A00 DET Externally inspect the FUSELAGEcomponents: • Baggage door cutout structure

(SSI 53-30-48)

– 96 MO or

2500 FC

271 EMB-145MP ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-31-00-220-810-A00 DET Internally inspect the FUSELAGEcomponents: • Baggage door lateral L-shape

(SSI 53-30-03)

– 7093 FC 271 EMB-145MP Not Applicable


(SSI 53-30-30)

144 MO or

20000 FC

96 MO or

5000 FC

171/172 EMB-135LR ± 60 Days

53-31-00-220-812-A00 DET Internally inspect the FUSELAGEcomponents: • Rear pressure bulkhead (SSI 53-30-36)

NOTE: During this inspection, the CPCP basic task shall also be performed for this SSI

144 MO or

20000 FC

8778 FC 273/274275/276

EMB-135LR Not Applicable


(SSI 53-30-30)

144 MO or

20000 FC


53-31-00-220-814-A00 DET Internally inspect the FUSELAGEcomponents: • Fuselage to vertical stabilizer spar

attachment fitting (SSI 53-30-38)

144 MO or

20000 FC

96 MO or

10000 FC

273/274 EMB-135LR ± 60 Days



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Section

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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-31-00-220-815-A00 DET Internally inspect the FUSELAGEcomponents: • Bulkhead-to-engine pylon attachment



144 MO or

20000 FC


53-31-00-220-816-A00 DET Internally inspect the FUSELAGEcomponents: • Baggage door cutout structure



144 MO or

30000 FC

96 MO or

7091 FC

271 EMB-145MP ± 60 Days

53-31-00-220-818-A00 DET Internally inspect the FUSELAGEcomponents: • Rear electronic compartment door

cutout structure (SSI 53-30-49) NOTE: During this inspection, the


144 MO or

12000 FC

96 MO or

7342 FC

272 EMB-145MP ± 60 Days


Edition

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137 of 732



REFERENCE NUMBER

TYPE


(Flight Cycles)



frames/bulkheads, and splices (SSI 53-30-07) NOTE: Remove bumper plate, if

installed

– 96 MO or

5000 FC

271/272 EMB-145MPEMB-135LR

± 60 Days


144 MO or

14000 FC

96 MO or

10000 FC

273/274 EMB-135LR ± 60 Days

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Page 138 of 732


REFERENCE NUMBER

TYPE


(Flight Cycles)


53-31-00-220-823-A00

DET

Externally inspect the FUSELAGEcomponents: • Baggage door cutout structure

(SSI 53-30-48)

–

96 MO or

2228 FC

271 EMB-135LR ± 60 Days



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TYPE

DESCRIPTION



53-31-00-220-838-A00

DET

Externally inspect the FUSELAGEcomponents: • Rear electronic compartment door

cutout structure (SSI 53-30-49)

144 MO

or 12000 FC

96 MO

or 4520 FC

272

EMB-135LR

± 60 Days

53-31-00-220-840-A00 DET Externally inspect the FUSELAGEcomponents: • Rear electronic compartment door

cutout structure (SSI 53-30-49)

144 MO or

12000 FC

96 MO or

8101 FC

272 EMB-145MP ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-31-00-220-842-A00

DET

Internally inspect the FUSELAGEcomponents: • Rear electronic compartment door

cutout structure (SSI 53-30-49) NOTE: During this inspection, the


144 MO

or 12000 FC

96 MO

or 5296 FC

272

EMB-135LR

± 60 Days

53-31-00-220-843-A00 DET Internally inspect the FUSELAGEcomponents: • Baggage door cutout structure



144 MO or

19000 FC

96 MO or

4828 FC

271 EMB-135LR ± 60 Days

53-31-00-220-845-A00

DET

Internally inspect the FUSELAGEcomponents: • Baggage door lateral L-shape

(SSI 53-30-03)

–

4828 FC

271 EMB-135LR

Not Applicable



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REFERENCE NUMBER

TYPE


(Flight Cycles)




144 MO or

30000 FC

96 MO or

10000 FC

273/274 EMB-145MP ± 60 Days


frames/bulkheads, and splices (SSI 53-30-07) NOTE: During this inspection, the


144 MO or

30000 FC

96 MO or

10000 FC

271/272 EMB-145MP ± 60 Days

53-31-00-220-848-A00 DET Internally inspect the FUSELAGEcomponents: • Fuselage skin panel at pressure


144 MO or

30000FC

96 MO or

10000 FC

271/272 EMB-145MP ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)



(SSI 53-30-30)

144 MO or

30000 FC

96 MO or

5000 FC

171/172 EMB-145MP ± 60 Days


(SSI 53-30-30)

144 MO or

30000 FC


53-31-00-220-851-A00 DET Internally inspect the FUSELAGEcomponents: • Bulkhead-to-engine pylon attachment



144 MO or

27000 FC




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REFERENCE NUMBER

TYPE

DESCRIPTION



53-31-00-220-852-A00 DET Internally inspect the FUSELAGEcomponents: • Rear pressure bulkhead (SSI 53-30-36)


144 MO or

30000 FC

8778 FC 273/274275/276

EMB-145MP Not Applicable



144 MO or

30000 FC

96 MO or

10000 FC

273/274 EMB-145MP ± 60 Days


144 MO or

20000 FC

96 MO or

10000 FC

273/274 EMB-145MP ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-32-00-210-801-A00 GVI Internally inspect the FUSELAGEcomponents: • APU mounting including its rods

(SSI 53-30-40)

– 96 MO or

20000 FC

313 ALL ± 60 Days



144 MO or

20000 FC



(SSI 53-30-30)

144 MO or

20000 FC


53-32-00-220-803-A00 DET Internally inspect the FUSELAGEcomponents: • Tail cone access door cutout structure

(SSI 53-30-50)

144 MO or

20000 FC

96 MO or

8193 FC

311/312 EMB-135LR ± 60 Days




145 of 732


REFERENCE NUMBER

TYPE

DESCRIPTION



53-32-00-220-808-A00

DET

Externally inspect the FUSELAGEcomponents: • Tail cone access door cutout structure

(SSI 53-30-50)

144 MO

or 20000 FC

96 MO or

10000 FC

311/312

EMB-135LR

± 60 Days

53-32-00-220-810-A00

DET

Internally inspect the FUSELAGEcomponents: • Fuselage machined bulkhead

(SSI 53-30-30)

144 MO or

30000 FC

10000 FC

311/312

EMB-145MP

Not Applicable



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REFERENCE NUMBER

TYPE


(Flight Cycles)




144 MO or

30000 FC


53-32-00-220-812-A00 DET Externally inspect the FUSELAGEcomponents: • Tail cone access door cutout structure

(SSI 53-30-50)

144 MO or

30000 FC

96 MO or

10000 FC

311/312 EMB-145MP ± 60 Days

53-32-00-220-813-A00 DET Internally inspect the FUSELAGEcomponents: • Tail cone access door cutout structure

(SSI 53-30-50)

144 MO or

30000 FC

96 MO or

8193 FC

311/312 EMB-145MP ± 60 Days



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CHAPTER 54 – NACELLE/PYLONS

REFERENCE NUMBER

TYPE


(Flight Cycles)


54-50-00-210-801-A00 GVI Externally inspect the PYLONcomponents: • Pylon Skin (SSI 54-50-04)

144 MO or

18000 FC

48 MO or

5000 FC

414/424 EMB-145MP ± 30 Days

54-50-00-210-802-A00 GVI Externally inspect the PYLONcomponents:

• Pylon Skin (SSI 54-50-04)

144 MO or

18467 FC

48 MO or

5000 FC

414/424 EMB-135LR ± 30 Days

54-50-00-220-801-A00 DET Internally inspect the PYLONcomponents: • Pylon spars I, II, III and IV (SSI 54-50-01)


144 MO or

20000 FC

96 MO or

5000 FC

414/424 EMB-135LR ± 60 Days



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CHAPTER 54 – NACELLE/PYLONS (Continued)

REFERENCE NUMBER

TYPE


(Flight Cycles)


54-50-00-220-802-A00 DET Internally inspect the PYLONcomponents: • FWD engine mounts including bolts

(SSI 54-50-03) NOTE: Applicable to aircraft Pre-Mod.

SB 145-54-0011

144 MO or

20000 FC

48 MO or

4000FC

414/424 EMB-145MPEMB-135LR

± 30 Days

54-50-00-220-803-A00 DET Internally inspect the PYLONcomponents: • Pylon Skin (SSI 54-50-04)


144 MO or

18000 FC

48 MO or

5000 FC

414/424 EMB-145MPEMB-135LR

± 30 Days



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CHAPTER 54 – NACELLE/PYLONS (Continued)

REFERENCE NUMBER

TYPE


(Flight Cycles)


54-50-00-220-808-A00 DET Internally inspect the PYLONcomponents: • AFT Engine Mounts including bolts


SB 145-54-0011

144 MO or

20000 FC

48 MO or

4000 FC

414/424 EMB-145MP EMB-135LR

± 30 Days

54-50-00-220-808-A01 DET Internally inspect the PYLON components: • AFT Engine Mounts including bolts

(SSI 54-50-07) NOTE: Applicable to aircraft

Post-Mod. SB 145-54-0011, and the flight cyclesaccumulated shall be basedon the engine mount components

144 MO or

5000 FC

48 MO or

5000 FC

414/424 EMB-145MP EMB-135LR

± 30 Days



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CHAPTER 57 – WINGS (Continued)

REFERENCE NUMBER

TYPE


(Flight Cycles)


57-26-00-250-814-A01 SDE Externally inspect the WING components using Eddy Current Inspection Method: • Fwd upper Trunnion (SSI 57-26-96)

NOTE: Applicable to aircraft Post-Mod. SB 145-00-0032, under ANAC/FAA Certifications

26000 FC 21620 FC 532/632 EMB-145MP Not Applicable

57-28-00-210-802-A00

GVI

Internally inspect the WING components: • Spar attachment, torque box

(SSI 57-28-57)

–

96 MO

or 10000 FC

541/641

ALL

± 60 Days

57-28-00-210-803-A00 GVI Externally inspect the WING components: • Ribs, torque box (SSI 57-28-60)

– 96 MO or

7229 FC

541/641 EMB-145MP EMB-135LR

± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-28-00-210-804-A00 GVI Externally inspect the WING components: • Lower skin, torque box (SSI 57-28-58)

– 48 MO or

5000 FC

541/641 EMB-145MPEMB-135LR

± 30 Days

57-28-00-210-805-A00 GVI Externally inspect the WING components: • Spar 3 Attachment, torque box

(SSI 57-28-63)

– 96 MO or

10000 FC

541/641 EMB-145MP EMB-135LR

± 60 Days

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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-28-00-210-806-A00 GVI Internally inspect the WING components: • Lower skin, torque box (SSI 57-28-58)

– 96 MO or

10000 FC

541/641 EMB-145MPEMB-135LR

± 60 Days

57-28-00-210-807-A00 GVI Internally inspect the WING components: • Spar 3 attachment, torque box 2

(SSI 57-28-63)

- 96 MO or

10000 FC

541/641 ALL ± 60 Days

57-28-00-210-808-A00 GVI Externally inspect the WING components: • Attachment center flap outboard track

(SSI 57-28-68)

– 96 MO or

3912 FC

541/641 EMB-145MPEMB-135LR

± 60 Days

57-28-00-210-812-A00

GVI

Externally inspect the WING components: • Attachment lugs aileron (SSI 57-28-66)

–

96 MO or

10000 FC

551/651 EMB-135LR ± 60 Days

57-28-00-210-813-A00 GVI Internally inspect the WING components: • Ribs, torque box (SSI 57-28-60)

– 96 MO or

10000 FC

541/641 EMB-145MPEMB-135LR

± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-28-00-210-815-A00 GVI Externally inspect the WING components: • Upper skin, torque box (SSI 57-28-61)

– 96 MO or

5445 FC

532/632 541/641 551/651

EMB-145MP EMB-135LR

± 60 Days

57-28-00-220-801-A00

DET

Externally inspect the WING components: • Tracks/ribs attachment, torque box

(SSI 57-28-62)

–

96 MO

or 10000 FC

532/632541/641

ALL

± 60 Days

57-28-00-220-804-A00

DET

Internally inspect the WING components: • Spar attachment torque box

(SSI 57-28-57)

144 MO or

20000 FC

96 MO or

20000 FC

551/651 EMB-135LR ± 60 Days

57-28-00-220-805-A00 DET Externally inspect the WING components: • Ribs, torque box 3 (SSI 57-28-64)

– 96 MO or

6306 FC

551/651 EMB-145MPEMB-135LR

± 60 Days

57-28-00-220-806-A00 DET Internally inspect the WING components: • Ribs, torque box 3 (SSI 57-28-64)

– 96 MO or

6306 FC

551/651 EMB-145MPEMB-135LR

± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-28-00-220-807-A00 DET Externally inspect the WING components: • Center track and rib15 trailing edge


SB 145-57-0008.

– 96 MO or

2000 FC

541/641 EMB-145MPEMB-135LR

± 60 Days

57-28-00-220-807-A01 DET Externally inspect the WING components: • Center track and rib15 trailing edge

(SSI 57-28-69) NOTE: Applicable to aircraft Post-

Mod. SB 145-57-0008.

– 96 MO or

3275 FC

541/641 EMB-145MPEMB-135LR

± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-28-00-220-813-A00

DET

Internally inspect the WING components:• Spar attachment torque box

(SSI 57-28-57)

144 MO or 30000 FC

96 MO or

20000 FC

551/651

EMB-145MP

± 60 Days

57-28-00-250-803-A00

SDE

Externally inspect the WING components by the Eddy Current Inspection Method: • Spar attachment, torque box

(SSI 57-28-57)

–

30000 FC 532/632 ALL Not Applicable

57-28-00-250-804-A00

SDE

Internally inspect the WING components by the Eddy Current Inspection Method: • Spar attachment, torque box

(SSI 57-28-57)

–

30000 FC 532/632 ALL Not Applicable

57-28-00-250-805-A00 SDE Externally inspect the WING components by the Eddy Current Inspection Method: • Flap track, torque box (SSI 57-28-59)

– 22633 FC 532/632541/641551/651

EMB-145MPEMB-135LR

Not Applicable

57-28-00-250-806-A00 SDE Externally inspect the WING components by the Eddy Current Inspection Method: • Ribs, torque box (SSI 57-28-60)

– 15824 FC 532/632 EMB-145MPEMB-135LR

Not Applicable



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-28-00-250-807-A00 SDE Internally inspect the WING components by the Eddy Current Inspection Method: • Ribs, torque box (SSI 57-28-60)

– 15824 FC 532/632 EMB-145MP EMB-135LR

Not Applicable

57-29-00-210-801-A00

GVI

Internally inspect the WING components: • Ribs, main landing gear bay

(SSI 57-29-71)

–

96 MO or

5000 FC

532/632 ALL ± 60 Days

57-29-00-210-802-A00 GVI Externally inspect the WING components: • Skin/rib attachment, MLGB

(SSI 57-29-72)

– 96 MO or

2500 FC

532/632 ALL ± 60 Days

57-29-00-210-803-A00 GVI Internally inspect the WING components: • Skin/rib attachment, MLGB

(SSI 57-29-72)

– 96 MO or

5000 FC

532/632 ALL ± 60 Days

57-41-00-220-801-A00 DET Internally inspect the WING LEADING EDGE components: • Machined rib flange (SSI 57-41-98)

– 96 MO or

10000 FC

511/611 ALL ± 60 Days


– 96 MO or

10000 FC

512/612 ALL ± 60 Days


– 96 MO or

10000 FC

513/613 ALL ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-50-00-220-801-A00 DET Externally inspect the FLAP components: • Fitting, root spar, flaps (SSI 57-50-74)

– 96 MO or

10000 FC

571/671572/672

EMB-145MP EMB-135LR

± 60 Days

57-50-00-220-802-A00 DET Internally inspect the FLAP components: • Fitting, root spar, flaps (SSI 57-50-74)

– 10000 FC 571/671572/672

EMB-145MP EMB-135LR

Not Applicable

57-50-00-220-803-A00 DET Externally inspect the FLAP components: • Roller attachment (SSI 57-50-76)

– 96 MO or

5000 FC

571/671 572/672

ALL ± 60 Days

57-50-00-220-804-A00 DET Externally inspect the FLAP components: • Flap rollers and torque boxes rollers

(SSI 57-50-78)

– 96 MO or

10000 FC

571/671 572/672

ALL ± 60 Days

57-50-00-240-801-A00

SDE

Externally inspect the FLAP components by the Magnetic Particle Inspection Method: • Flap rollers and Torque boxes rollers

(SSI 57-50-78)

–

30000 FC 571/671 572/672

ALL Not Applicable

57-50-00-250-801-A00

SDE

Externally inspect the FLAP components by the Eddy Current Inspection Method: • Roller attachment (SSI 57-50-76)

–

30000 FC 571/671 572/672

ALL Not Applicable



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-50-00-250-802-A00 SDE Externally inspect the FLAP components by the Eddy Current Inspection Method: • Tracks, flaps (SSI 57-50-80)

– 22633 FC 571/671572/672

EMB-145MP EMB-135LR

Not Applicable

57-52-00-210-802-A00 GVI Internally inspect the FLAP components: • Ribs/skin attachment, inboard flap

(SSI 57-52-79)

– 10000 FC 571/671 EMB-145MPEMB-135LR

Not Applicable

57-52-00-210-803-A00

GVI

Externally inspect the FLAP components: • Ribs/skin attachment, inboard flap

(SSI 57-52-79)

–

96 MO or

2500 FC

571/671

ALL

± 60 Days

57-52-00-210-804-A00 GVI Externally inspect the FLAP components: • Vane inboard/outboard fittings,

inboard flap (SSI 57-52-81)

– 96 MO or

2500 FC

571/671 ALL ± 60 Days

57-52-00-220-802-A00 DET Internally inspect the FLAP components: • Fitting tip, inboard flap (SSI 57-52-73)

– 96 MO or

16797 FC

571/671 EMB-145MPEMB-135LR

± 60 Days

57-52-00-220-803-A00 DET Externally inspect the FLAP components: • Vane center fitting, inboard flap (SSI 57-52-78)

– 96 MO or

3447 FC

571/671 EMB-145MPEMB-135LR

± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-53-00-210-802-A00 GVI Internally inspect the FLAP components: • Ribs/skin attachment, outboard flap

(SSI 57-53-86)

– 10000 FC 572/672 EMB-145MPEMB-135LR

Not Applicable

57-53-00-210-803-A00 GVI Externally inspect the FLAP components: • Ribs/skin attachment, outboard flap

(SSI 57-53-86)

– 96 MO or

2500 FC

572/672 EMB-145MPEMB-135LR

± 60 Days

57-53-00-210-804-A00 GVI Externally inspect the FLAP components: • Vane inboard/outboard fittings,

outboard flap (SSI 57-53-88)

– 96 MO or

2500 FC

572/672 ALL ± 60 Days

57-53-00-210-805-A00 GVI Internally inspect the FLAP components: • Center ribs attachment, outboard flap

(SSI 57-53-87)

– 96 MO or

20000 FC

572/672 EMB-145MPEMB-135LR

± 60 Days

57-53-00-220-801-A00

DET

Externally inspect the FLAP components: • Fitting, tip spar, outboard flap

(SSI 57-53-83)

–

96 MO or

10000 FC

572/672 EMB-145MPEMB-135LR

± 60 Days

57-53-00-220-802-A00 DET Internally inspect the FLAP components: • Fitting, tip spar, outboard flap

(SSI 57-53-83)

– 96 MO or

16797 FC

572/672 EMB-145MPEMB-135LR

± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-53-00-220-805-A00 DET Externally inspect the FLAP components: • Vane center fitting, outboard flap

(SSI 57-53-85)

– 96 MO or

3447 FC

572/672 EMB-145MPEMB-135LR

± 60 Days

57-61-00-210-801-A00

GVI

Externally inspect the AILERONcomponents: • Hinge attachment, aileron

(SSI 57-61-89)

–

96 MO or

3622 FC

573/673 EMB-135LR ± 60 Days

57-61-00-220-801-A00 DET Externally inspect the AILERONcomponents: • Actuator attachment, aileron

(SSI 57-61-90)

– 96 MO or

5000 FC

573/673 EMB-145MPEMB-135LR

± 60 Days

57-61-00-220-802-A00 DET Internally inspect the AILERONcomponents: • Actuator attachment, aileron

(SSI 57-61-90)

– 10000 FC 573/673 EMB-145MP Not Applicable

57-61-00-220-806-A00 DET Internally inspect the AILERONcomponents: • Actuator attachment, aileron

(SSI 57-61-90)

– 5738 FC 573/673 EMB-135LR Not Applicable



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Corrosion level 2

Initial Immediately to the manufacturer

Repeat Immediately to the manufacturer Within 60 days (on proposed corrective action to reduce corrosion level I or bet-ter) - to ACO (Aircraft Certification Office).

Corrosion level 3

Initial Immediately to the manufacturer

Repeat Immediately to the manufacturer Within 7 days (with plan for fleet campaign) to ACO (Aircraft Certification Office).

Within 60 days (on proposed corrective action to reduce corrosion to level I or better) to ACO (Aircraft Certification Office).

SECTION 4 CORROSION PREVENTION & CONTROL PROGRAM (CPCP)

4.1 GENERAL

This section contains the Corrosion Prevention Inspection Require- ments resulting from MSG-3 analysis. These requirements consist of maintenance tasks and associated intervals developed to prevent structural degradation caused by environmental deterioration during the aircraft operational life. The Corrosion Prevention Inspection Requirements are based on an assessment of structural design information and service experience with similar structure and related results. The requirements also take in account that each individual operator is aware and has adequately trained personnel in corrosion identification and detection techniques, and in cleaning and preservation of aircraft structure and components. Upon the performance of the inspection, each individual operator must take into account any type of damage occurrence, such as fatigue, environmental and accidental damage. Some SSIs having FD assessed as a critical source of damage according to the MSG-3 analysis have been selected to undergo the CPCP basic task herein described in item 4.8. The main purpose of the combination of inspections is to allow a better corrosion control by performing the CPCP basic task at the same time as the fatigue inspections.

4.2 REPORTING OF INSPECTION RESULTS

The Operator's Control Program should keep accurate records of all corrosion treatment after detection. Reports of Corrosion findings

should be submitted to EMBRAER. The model of the report to be used can be found in Part IV of the SMRD and should be properly filled out and submitted to EMBRAER as required. Based on these reports, EMBRAER will evaluate and issue a quarterly report with the results of the Corrosion Prevention and Control Program of the fleet. It is not mandatory to report Corrosion Level 1. The operators are requested to report corrosion as follows:



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CORROSION REPORTING LOGIC DIAGRAM

CORROSION DETECTED ON A SSI CLASSIFIED AS LEVEL 1, 2 OR 3

IS LEVEL 1?

YES

REPORT IS NOT MANDATORY.

NO

IS LEVEL 2?

NO

YES

IMMEDIATELY TO THE MANUFACTURER

WITHIN 60 DAYS (ON PROPOSED CORRECTIVE ACTION TO REDUCE CORROSION LEVEL I OR BETTER) TO ACO (AIRCRAFT CERTIFICATION OFFICE).

LEVEL 3: IMMEDIATELY TO THE MANUFACTURER WITHIN 7 DAYS (WITH PLAN FOR FLEET CAMPAIGN) TO ACO (AIRCRAFT CERTIFICATION OFFICE). WITHIN 60 DAYS (ON PROPOSED CORRECTIVE ACTION TO REDUCE CORROSION LEVEL I OR BETTER) TO ACO (AIRCRAFT CERTIFICATION OFFICE).



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4.3 DEFINITION OF CORROSION LEVEL

CORROSION LEVEL 1

Local corrosion occurring between successive inspections, which can be re-worked or blended-out within manufacturer-allowable limits (e.g. SRM, SB, etc). or Local corrosion occurring between successive inspections, which exceeds allowable limits, but can be attributed to an event not typical of operator usage of other aircraft in the same fleet (e.g. chemical spill). or Operator’s experience over several inspections has demonstrated only light corrosion between each scheduled inspection, but the latest inspection and cumulative blend-out now exceeds allowable limits.

CORROSION LEVEL 2 Corrosion level 2 is damage occurring between successive inspections that requires a single rework/blend-out and then exceeds the allowable limits, requiring a repair/reinforcement, or complete/partial replacement of a structural significant item (as defined by the original equipment manufacturers structural repair manual), or a damage occurring between successive inspections that is widespread and requires a single blend-out approaching allowable rework limits. CORROSION LEVEL 3 Corrosion level 3 is damage found during the first or subsequent inspection(s) which is determined (by the operator and the manufacturer) to be an urgent airworthiness concern requiring expeditious action.



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IS THE DAMAGE A POTENTIAL URGENT AIRWORTHINESS

CONCERN IN THE OPERATOR FLEET?

YES

DOES MANUFACTURER CONFIRM DAMAGE IS A POTENTIAL URGENT

AIRWORTHINESS CONCERN?

YES

CORROSION LEVEL BLOCK DIAGRAM

CORROSION DETECTED ON A SSI (STRUCTURAL SIGNIFICANT ITEM)

IS ATTRIBUTED TO NO

AN EVENT NOT TYPICAL?

IS CORROSION BLEND-

OUT BEYOND ALLOWABLE LIMITS?

NO IS WIDESPREAD NO CORROSION?

LEVEL 1

YES

LEVEL 1

YES

APPROACHING

ALLOWABLE REWORK LIMITS ?

LEVEL 1

YES

LEVEL 2

NO LEVEL 2

NO

LEVEL 2

LEVEL 3



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4.4 LOCAL, WIDESPREAD, LIGHT CORROSIONS, APPROACH- ING ALLOWABLE LIMITS, ALLOWABLE LIMITS DEFINITION AND URGENT AIRWORTHINESS CONCERN

LOCAL CORROSION

Corrosion of a skin or web (wing, fuselage, empennage or strut) not exceeding one frame, stringer or stiffener bay.

or Corrosion of a single frame, chord, stringer or stiffener. or Corrosion of more than one frame, chord, stringer or stiffener but, no corrosion on two adjacent members on each side of the corroded members. Local Corrosion examples:

Figure 1. Local Corrosion (Corrosion occurring in non- adjacent skin panel bays)



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Figure 2. Local Corrosion (Corrosion occurring in non- adjacent stringers)

Figure 3. Local Corrosion (Corrosion occurring on non- adjacent frames)



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WIDESPREAD CORROSION

Corrosion of two or more adjacent skin or web bays defined by frame, stringer or stiffener spacing.

or Corrosion of two or more adjacent frames, chords, stringers or stiffeners. Widespread Corrosion examples:

Figure 4: Widespread Corrosion (Corrosion occurring in adjacent frames and skin panels)



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Figure 5: Widespread Corrosion (Corrosion occurring in adjacent frames)

Figure 6: Widespread Corrosion (Corrosion occurring in adjacent skin panels bays)



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LIGHT CORROSION

Light corrosion is corrosion damage so slight that removal and blend-out over multiple repeat interval may be accomplished before material loss exceeds the allowable limits.

APPROACHING ALLOWABLE LIMITS

Approaching allowable limit classification can be used for corrosion very close to allowable limit.

ALLOWABLE LIMIT

The allowable limit is the maximum amount of material (usually expressed in material thickness) that may be removed or blended out without affecting the ultimate design strength capability of the structural member. Allowable limits may be established by the Aircraft Certification Office. The FAA may also establish allowable limits. The Aircraft Certification normally publishes allowable limits in the Structural Repair Manual or in Service Bulletins.

URGENT AIRWORTHINESS CONCERN An urgent airworthiness concern is damage that could jeopardize continued safe operation of any airplane. An urgent airworthiness concern typically requires correction before the next flight and expeditious action to inspect the other airplanes in the operator’s fleet. 4.5 MAINTENANCE TASK INTERVALS The same task types and criteria for applicability and effectiveness of structural tasks are used for the Corrosion Prevention and Control Program with intervals given in calendar time.



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4.6 LIST OF SCHEDULED MAINTENANCE REQUIREMENTS PRESENTATION

The maintenance requirements are presented per chapter as below:

REFERENCE NUMBER

TYPE

DESCRIPTION THRESHOLD INT ZONE EFFECTIVITY52-10-00-220-C06-A00 DET Externally inspect the MAIN DOOR (STANDARD

MODEL) components: • Structure (SSI 52-10-01)

60 MO 30 MO 811 ALL

a b c d e f g

a – REFERENCE NUMBER b – TYPE - Task type. c – DESCRIPTION - Description of the task to be performed. d – THRESHOLD – Corrosion threshold as defined in 4.9.

e – INTERVAL - Task interval as defined in 4.5. f – ZONE - Aircraft zone where the task is performed. g – EFFECTIVITY - Task effectivity.

4.7 BASELINE PROGRAM IMPLEMENTATION REQUIREMENTS

The Baseline Program is subdivided into specific airplane task areas and locations, each having a Repeat Interval for application of the basic task. The CPCP implementation is the starting point for corrosion control and implies that the Corrosion Inhibiting Compound (CIC) is already applied, and the control for subsequent applications (time counted since the delivery of the aircraft) must be initiated. The basic requirements for implementing the CPCP tasks listed in the Baseline Program are as follows:

(a) Regardless of when an operator’s CPCP is approved, the implementation requirements are measured from MRB revision 5.

(b) The implementation age of the CPCP tasks must follow the logic diagram as stated on page 270.

(c) The regions defined by the Structures Working Group for first and subsequent CIC applications are described in the Corro- sion Prevention Manual.

(d) The period for CIC subsequent applications are defined by:

• Period recommended by Embraer (currently 8 years) or;

• CIC integrity affected by contamination or physical damage or;

• Necessity of a structural repair in the region or;

• If there is a presence of multiple layers and/or dirt that can cause difficulty to inspect the structural component.

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(e) The maximum number of CIC layers to be applied to the aircraft structure is two, observing item 4.7. (d) of this introduction. After this limit, it is necessary to remove the old layers before the next application.

(f) To maintain the aircraft structure components controlled at corrosion level 1 or better, the Baseline Program can be adjusted as a result of the operator’s findings and agreement of the Local Regulatory Authorities in conjunction with the

Manufacturer. The intervals may be increased, depending on the finding of each operator (if consistently no greater than level 1 corrosion is found) or reduced (if consistently level 2 or 3 corrosion is found in repeated times).

(g) New tasks may be developed for regions not covered by the CPCP if corrosion levels 2 and 3 are found in repeated times.

(h) Implementation of Age Decision Logic Diagram.

4.8 BASIC TASK

The basic task comprises several steps that are necessary to be followed during the accomplishment of each task listed in this section. Step 7, which is related to the CIC application, will be performed

when indicated in the Baseline Program task description. The following describes the basic task:

(1) Gain access to the area to be inspected. Remove the necessary equipment, access panels, and interior furnishing (E.g. galleys, wardrobes, lining and insulation) to comply with step (3)



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(2) Prior to the inspection, clean the area as required to accomplish step (3). It is not necessary to remove the sealant unless it is deteriorated. A light uniform film of Corrosion Inhibiting Compound (CIC) that has not accumulated dirt or debris will normally allow adequate inspection of the structure without the need for its removal. CIC may require removal if there are multiple layers and/or accumulation of dirt or debris. It is recommended that CIC be removed before the application of the 3rd layer.

(3) Visually inspect all Structural Significant Items (SSI) from a distance considered necessary to detect early signs of corrosion or other types of damage. Pay particular attention in areas where the experience has shown that corrosion may occur. Non-destructive inspections or visual inspections following partial disassembly are required if there are indications of hidden corrosion, such as bulging skins or corrosion running into splices, under fittings, etc. In the task area, check any sealant for integrity to determine if its removal or CIC application is required.

(4) If corrosion is found remove it, evaluate damage and repair or replace all discrepant structure as required, including application of protective finishes, according to Corrosion Prevention Manual.

(5) Report findings with the respective corrosion level determination in accordance with 4.2 and 4.3 above.

(6) Clear any blocked holes or gaps that may hinder drainage.

(7) Apply suitable CIC according to 4.7 above and following the procedures contained in the Corrosion Prevention Manual.

(8) Close/reinstall equipment opened/removed. 4.9 CORROSION THRESHOLD The first inspection (threshold) for the environmental deterioration corresponds to a period from the manufacturing date to the timely detection of such deterioration. These values are applicable only to Structural Significant Items (SSI) previously analyzed by Embraer and covered by CPCP Section, where the inspection is controlled in calendar time (years). After a threshold proposed by the manufacturer and approved by the regulatory authorities, the repetitive inspection directly related to the environmental deterioration will occur based on the MSG3 analysis, manufacturer and operator´s experience. Such thresholds have been established on the basis of the field data analysis taking into account the design characteristics such as the level of protection, material and the exposure to adverse environment. These are subject to further change due to the improvement of each SSI design and the continuing field data collection and analysis.

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SECTION 5

CORROSION PREVENTION AND CONTROL PROGRAM (CPCP)


REFERENCE NUMBER

TYPE


(Flight Cycles)


32-10-00-210-C01-A00 GVI Externally inspect the MAIN LANDING GEAR components: • Leg structure, equipped (left) -

MLG (SSI 32-10-01)

– 60 MO 731 ALL ± 30 Days

32-10-00-210-C02-A00 GVI Externally inspect the MAIN LANDING GEAR components: • Shock absorber piston tube assy -

MLG (SSI 32-10-05)

– 30 MO 721/731 ALL ± 30 Days

32-10-00-210-C03-A00 GVI Externally inspect the MAIN LANDING GEAR components: • Leg structure, equipped (right) -

MLG (SSI 32-10-02)

– 60 MO 721 ALL ± 30 Days

32-10-00-210-C04-A00 GVI Externally inspect the MAIN LANDING GEAR components: • Upper secondary side strut assy -

MLG (SSI 32-10-09)

– 60 MO 721/731 ALL ± 30 Days

32-10-00-210-C05-A00 GVI Externally inspect the MAIN LANDING GEAR components: • Lower secondary side strut assy -

MLG (SSI 32-10-10)

– 60 MO 721/731 ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


32-10-00-210-C06-A00 GVI Externally inspect the MAIN LANDING GEAR components: • Shock absorber cylinder assy -

MLG (SSI 32-10-06)

– 30 MO 721/731 ALL ± 30 Days

32-20-00-210-C01-A00 GVI Externally inspect the NOSE LANDING GEAR components: • Main drag strut bottom stay -

NLG (SSI 32-20-14)

– 30 MO 711 ALL ± 30 Days


REFERENCE NUMBER

TYPE


(Flight Cycles)


52-10-00-220-C02-A00 DET Externally inspect the MAIN DOOR (STANDARD MODEL) components: • Attachment fittings-to-fuselage &


– 30 MO 811 ALL ± 30 Days

52-10-00-220-C06-A00 DET Externally inspect the MAIN DOOR (STANDARD MODEL) components: • Structure (SSI 52-10-01)

48 MO 30 MO 811 ALL ± 30 Days

52-10-00-220-C01-A01 DET Internally inspect the MAIN DOOR (SIDE-HINGED MODEL) components:• Attachment fittings-to-fuselage &


– 120 MO 811 ALL ± 60 Days



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CHAPTER 52 – DOORS (SIDE-HINGED MODEL) (Continued)

REFERENCE NUMBER

TYPE


(Flight Cycles)


52-10-00-220-C02-A01 DET Externally inspect the MAIN DOOR (SIDE-HINGED MODEL) components:• Attachment fittings-to-fuselage &


– 60 MO 811 ALL ± 30 Days

52-10-00-220-C04-A01 DET Internally inspect the MAIN DOORcomponents: • Window frame (SSI 52-10-06)

NOTE: Applicable to side-hingeddoor, only

– 120 MO 811 ALL ± 60 Days

52-10-00-220-C05-A01 DET Externally inspect the MAIN DOORcomponents: • Window frame (SSI 52-10-06)

NOTE: Applicable to side-hingeddoor, only

96 MO 60 MO 811 ALL ± 30 Days

52-10-00-220-C06-A01 DET Externally inspect the MAIN DOOR (SIDE-HINGED MODEL) components:• Structure (SSI 52-10-01)

48 MO 30 MO 811 ALL ± 30 Days

52-30-00-210-C01-A00 GVI Externally inspect the BAGGAGE DOOR components: • Baggage door structure (SSI 52-30-08)

48 MO 30 MO 813 ALL ± 30 Days

52-30-00-210-C02-A00 GVI Internally inspect the BAGGAGE DOOR components: • Baggage door structure (SSI 52-30-08)

– 120 MO 813 ALL ± 60 Days



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52-43-00-210-C01-A00 GVI Externally inspect the SERVICE DOORcomponents: • Service door structure (SSI 52-43-10)

72 MO 30 MO 821 ALL ± 30 Days

52-43-00-210-C02-A00 GVI Internally inspect the SERVICE DOORcomponents: • Service door structure (SSI 52-43-10)

96 MO 60 MO 821 ALL ± 30 Days

52-43-00-220-C01-A00 DET Externally inspect the SERVICE DOORcomponents: • Service door-to-fuselage attachment

fittings & interface parts (SSI 52-43-15)

96 MO 60 MO 821 ALL ± 30 Days

52-43-00-220-C02-A00 DET Internally inspect the SERVICE DOORcomponents: • Service door-to-fuselage attachment

fittings & interface parts (SSI 52-43-15)

– 120 MO 821 ALL ± 60 Days


REFERENCE NUMBER

TYPE


(Flight Cycles)


53-11-00-210-C01-A00 GVI Internally inspect the FUSELAGEcomponents: • Bulkhead 1 structure (SSI 53-10-23)

– 120 MO 113/114 ALL ± 60 Days

53-11-00-210-C02-A00 GVI Externally inspect the FUSELAGEcomponents: • Fuselage skin panel at stringers,


96 MO 60 MO 113/114213/214

ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-11-00-210-C03-A00 GVI Externally inspect the FUSELAGEcomponents: • Nose landing gear bay structure

(SSI 53-10-24)

96 MO 60 MO 113/114 ALL ± 30 Days

53-11-00-210-C05-A00 GVI Internally inspect the FUSELAGEcomponents: • Nose landing gear bay structure

(SSI 53-10-24)

96 MO 60 MO 113/114 ALL ± 30 Days

53-11-00-210-C06-A00 GVI Internally inspect the FUSELAGEcomponents: • Battery compartment cutout


– 120 MO 113/114 ALL ± 60 Days

53-11-00-210-C07-A00 GVI Internally inspect the FUSELAGEcomponents: • Hydraulic compartment cutout


– 120 MO 113/114 ALL ± 60 Days

53-11-00-210-C08-A00 GVI Internally inspect the FUSELAGEcomponents: • Longerons (SSI 53-10-46)

– 120 MO 113/114 ALL ± 60 Days

53-11-00-220-C01-A00 DET Internally inspect the FUSELAGEcomponents: • Nose landing gear fitting, including

bearing cap and Trunnion fitting (SSI 53-10-25) NOTE: Applicable to aircraft Pre-

Mod. SB 145-32-0063

– 15 MO 113/114 ALL ± 15 Days

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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-11-00-220-C01-A01 DET Internally inspect the FUSELAGEcomponents: • Nose landing gear fitting, including

bearing cap and Trunnion fitting (SSI 53-10-25) NOTE: Applicable to aircraft Post-

Mod. SB 145-32-0063.

– 30 MO 113/114 ALL ± 30 Days

53-11-00-220-C02-A00 DET Internally inspect the FUSELAGEcomponents: • Fuselage skin panel at stringers,


– 120 MO 113/114 ALL ± 60 Days

53-11-00-220-C03-A00 DET Internally inspect the FUSELAGEcomponents: • Fuselage skin Circumferential splice

(SSI 53-10-14)

– 120 MO 113/114213/214

ALL ± 60 Days

53-11-00-220-C04-A00 DET Internally inspect the FUSELAGEcomponents: • Fuselage skin panel at pressure


– 120 MO 113/114213/214

ALL ± 60 Days

53-11-00-220-C05-A00 DET Internally inspect the FUSELAGEcomponents: • Frames (SSI 53-10-43)

– 120 MO 113/114213/214

ALL ± 60 Days

53-11-00-220-C07-A00 DET Externally inspect the FUSELAGEcomponents: • Fuselage skin panel at pressure


96 MO 60 MO 113/114213/214

ALL ± 30 Days


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REFERENCE NUMBER

TYPE


(Flight Cycles)




96 MO 60 MO 225/226 ALL ± 30 Days

53-12-00-210-C03-A00 GVI Externally inspect the FUSELAGEcomponents: • Windshield cutout structure

(SSI 53-10-17)

96 MO 60 MO 223/224225/226

ALL ± 30 Days

53-12-00-210-C04-A00 GVI Externally inspect the FUSELAGEcomponents: • Windshield center post, including its

attachments and lower fitting (SSI 53-10-19)

96 MO 60 MO 223/224 ALL ± 30 Days

53-12-00-210-C05-A00 GVI Externally inspect the FUSELAGEcomponents: • Maintenance door cutout structure

(SSI 53-10-49)

96 MO 60 MO 123/124 ALL ± 30 Days

53-12-00-210-C07-A00 GVI Internally inspect the FUSELAGEcomponents: • Windshield panel (SSI 53-10-21)

– 120 MO 223/224 ALL ± 60 Days

53-12-00-210-C10-A00 GVI Externally inspect the FUSELAGEcomponents: • Cockpit window cutout structure

(SSI 53-10-18)

96 MO 60 MO 223/224225/226

ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-12-00-210-C11-A00 GVI Externally inspect the FUSELAGEcomponents: • Windshield panel (SSI 53-10-21)

96 MO 60 MO 223/224 ALL ± 30 Days

53-12-00-210-C12-A00 GVI Externally inspect the FUSELAGEcomponents: • Cockpit window rear post and its


96 MO 60 MO 223/224 ALL ± 30 Days



– 120 MO 123/124223/224225/226

ALL ± 60 Days

53-12-00-220-C02-A00 DET Internally inspect the FUSELAGEcomponents: • Fuselage skin longitudinal splice

(SSI 53-10-08)

– 120 MO 123/124213/214223/224

ALL ± 60 Days

53-12-00-220-C03-A00 DET Internally inspect the FUSELAGEcomponents: • Fuselage skin circumferential splice

(SSI 53-10-14)

– 120 MO 123/124223/224225/226

ALL ± 60 Days

53-12-00-220-C04-A00 DET Internally inspect the FUSELAGEcomponents: • Cockpit floor beams and columns

(SSI 53-10-27)

– 120 MO 123/124 ALL ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)




– 120 MO 123/124223/224

ALL ± 60 Days


– 120 MO 123/124223/224225/226

ALL ± 60 Days

53-12-00-220-C08-A00 DET Internally inspect the FUSELAGEcomponents: • Maintenance door cutout structure

(SSI 53-10-49)

– 120 MO 123/124 ALL ± 60 Days

53-12-00-220-C09-A00 DET Externally inspect the FUSELAGEcomponents: • Fuselage skin panel at pressure


96 MO 60 MO 123/124223/224

ALL ± 30 Days

53-21-00-210-C02-A00 GVI Externally inspect the FUSELAGEcomponents: • Main door attachments fittings and


72 MO 30 MO 231 ALL ± 30 Days

53-21-00-210-C03-A00 GVI Externally inspect the FUSELAGEcomponents: • Service door attachment fittings and


72 MO 30 MO 232 ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-21-00-220-C03-A00 DET Internally inspect the FUSELAGEcomponents: • Stops and backup structures for

service door (SSI 53-20-02)

– 30 MO 232 ALL ± 30 Days



– 30 MO 131/132 ALL ± 30 Days


– 60 MO 231/232131/132

ALL ± 30 Days

53-21-00-220-C07-A00 DET Internally inspect the FUSELAGEcomponents: • Passenger cabin floor beams and

columns (SSI 53-20-11) NOTE: Applicable to aircraft Pre-Mod.

SB 145-53-0026 or SB 145-53-0039 or SB 145-53-0041

– 24 MO 131/132 ALL ± 30 Days


columns (SSI 53-20-11) NOTE: Applicable to aircraft Post-Mod.

SB 145-53-0026, SB 145-53-0039 and SB 145-53-0041

– 30 MO 131/132 ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-22-00-210-C03-A00 GVI Externally inspect the FUSELAGEcomponents: • Passenger cabin window frame

(SSI 53-20-06)

– 60 MO 241/242 ALL ± 30 Days



– 60 MO 141/142241/242

ALL ± 30 Days



SB 145-53-0041

– 48 MO 141/142 ALL ± 30 Days


columns (SSI 53-20-11) NOTE: Applicable to aircraft Pos-Mod.

SB 145-53-0041

– 60 MO 141/142 ALL ± 30 Days

53-22-00-220-C03-A00 DET Internally inspect the FUSELAGEcomponents: • Passenger cabin window frame

(SSI 53-20-06)

– 60 MO 241/242 ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)



(SSI 53-20-08)

– 60 MO 141/142241/242243/244

ALL ± 30 Days


(SSI 53-20-14)

– 60 MO 141/142241/242

ALL ± 30 Days


– 60 MO 141/142241/242

ALL ± 30 Days


(SSI 53-20-06)

– 60 MO 251/252 EMB-145MP EMB-135LR

± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-23-00-210-C04-A00 GVI Internally inspect the FUSELAGEcomponents: • Passenger cabin window frame

(SSI 53-20-06)

– 60 MO 251/252 ALL ± 30 Days



– 60 MO 151/152153/154

ALL ± 30 Days


– 60 MO 151/152153/154251/252

ALL ± 30 Days


(SSI 53-20-08)

– 60 MO 251/252 ALL ± 30 Days



SB 145-53-0041

– 48 MO 151/152153/154

ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)



columns (SSI 53-20-11) NOTE: Applicable to aircraft Post- Mod. SB 145-53-0041

– 60 MO 151/152153/154

ALL ± 30 Days

53-23-00-220-C05-A00 DET Internally inspect the FUSELAGEcomponents: • Skin and reinforcement around

escape hatch cutout (SSI 53-20-51)

96 MO 60 MO 251/252 ALL ± 30 Days

53-23-00-220-C06-A00 DET Externally inspect the FUSELAGEcomponents: • Fuselage skin panel at stringers,


– 60 MO 151/152153/154

ALL ± 30 Days



– 30 MO 261/262 ALL ± 30 Days

53-24-00-210-C02-A00 GVI Internally inspect the FUSELAGEcomponents: • Passenger cabin window frame

(SSI 53-20-06)

– 60 MO 261/262 ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)



(SSI 53-20-06)

– 60 MO 261/262 ALL ± 30 Days

53-24-00-210-C04-A00 GVI Internally inspect the FUSELAGEcomponents: • Fuselage skin circumferential splice

(SSI 53-20-14)

– 60 MO 161/162261/262

EMB-145MPEMB-135LR

± 30 Days

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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-24-00-210-C08-A00 GVI Externally inspect the FUSELAGEcomponents: • Toilet waste valve support

(SSI 53-20-29)

– 30 MO 161/162 EMB-145MP ± 30 Days




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REFERENCE NUMBER

TYPE


(Flight Cycles)




– 60 MO 161/162261/262

ALL ± 30 Days


Columns (SSI 53-20-11) NOTE: Applicable to aircraft Pre-Mod. SB 145-53-0026 or SB 145-53-0041

– 48 MO 161/162 ALL ± 30 Days


Columns (SSI 53-20-11) NOTE: Applicable to aircraft Pos-

Mod. SB 145-53-0026 and SB 145-53-0041

– 60 MO 161/162 ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)



(SSI 53-20-08)

– 60 MO 161/162261/262

EMB-145MPEMB-135LR

± 30 Days


– 60 MO 161/162261/262

ALL ± 30 Days

53-24-00-220-C06-A00

DET

Internally inspect the FUSELAGEcomponents: • Toilet waste valve support

(SSI 53-20-29)

–

30 MO 161/162 EMB-145MPEMB-135LR

± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-31-00-210-C02-A00

GVI

Externally inspect the FUSELAGEcomponents: • Toilet waste drain valve support

(SSI 53-30-29)

–

30 MO

171/172

EMB-135LR

± 30 Days



– 30 MO 171/172 ALL ± 30 Days



96 MO 60 MO 271/272 ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)




96 MO 60 MO 273/274 ALL ± 30 Days


(SSI 53-30-14)

– 30 MO 171/172271/272273/274

ALL ± 30 Days



– 30 MO 171/172 ALL ± 30 Days

53-31-00-220-C06-A00 DET Internally inspect the FUSELAGEcomponents: • Toilet waste drain valve support

(SSI 53-30-29)

– 30 MO 171/172 EMB-135ER EMB-135LR

± 30 Days

53-31-00-220-C07-A00 DET Internally inspect the FUSELAGEcomponents: • Rear pressure bulkhead (SSI 53-30-36)

– 30 MO 171/172 ALL ± 30 Days


– 30 MO 171/172 ALL ± 30 Days




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REFERENCE NUMBER

TYPE

DESCRIPTION



53-31-00-220-C09-A00

DET

Internally inspect the FUSELAGEcomponents: • Fuselage skin longitudinal splice

(SSI 53-30-08)

96 MO

60 MO 271/272273/274

EMB-145MPEMB-135LR

± 30 Days

53-31-00-220-C10-A00

DET

Internally inspect the FUSELAGEcomponents: • Rear pressure bulkhead (SSI 53-30-36)

–

60 MO 271/272 ALL ± 30 Days

53-32-00-210-C01-A00 GVI Externally inspect the FUSELAGEcomponent: • Fuselage skin panel at stringers,


96 MO 60 MO 311/312 ALL ± 30 Days

53-32-00-210-C02-A00 GVI Internally inspect the FUSELAGEcomponents: • Fuselage skin panel at stringers,


96 MO 60 MO 311/312 ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


53-32-00-210-C05-A00 GVI Internally inspect the FUSELAGEcomponents: • Tail cone frame at APU mounting


96 MO 60 MO 311/312 ALL ± 30 Days

53-32-00-220-C01-A00 DET Internally inspect the FUSELAGEcomponents: • Rear pressure bulkhead (SSI 53-30-36)

48 MO 30 MO 311/312 ALL ± 30 Days


96 MO 60 MO 311/312 ALL ± 30 Days


(SSI 53-30-08)

96 MO 60 MO 311/312 ALL ± 30 Days


(SSI 53-30-14)

96 MO 60 MO 311/312 ALL ± 30 Days

54-50-00-220-C01-A00 DET Internally inspect the PYLON components. Pylon yokes III and IV (SSI 54-50-05)

- 30 MO 414/424 ALL ± 30 Days

54-50-00-220-C02-A00 DET Internally inspect the PYLON components. Pylon yokes I and II (SSI 54-50-05)

- 30 MO 414/424 ALL ± 30 Days

54-50-00-220-C03-A00 DET Internally inspect the PYLON components. Pylon yokes I and II upper flange. (SSI 54-50-05)

- 30 MO 414/424 ALL ± 30 Days




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CHAPTER 55 – STABILIZERS

REFERENCE NUMBER

TYPE


(Flight Cycles)


55-10-00-210-C02-A00 GVI Externally inspect the HORIZONTAL STABILIZER components: • U shape, L shape and box structure -

elevator command (SSI 55-10-22)

– 60 MO 337 ALL ± 30 Days

55-10-00-210-C03-A00 GVI Externally inspect the HORIZONTAL STABILIZER components: • Pin, internal and external hinge,

stabilizer (SSI 55-10-24)

– 15 MO 337 ALL ± 15 Days

55-10-00-210-C05-A00 GVI Externally inspect the HORIZONTAL STABILIZER components: • Support quadrant assy, stabilizer

(SSI 55-10-23)

96 MO 60 MO 337 ALL ± 30 Days

55-10-00-210-C06-A00 GVI Externally inspect the HORIZONTAL STABILIZER components: • Skin, from rib sta. YH=990 to rib sta.

YH=2965-lower surface (SSI 55-10-08)

– 60 MO 333/334 ALL ± 30 Days

55-10-00-220-C01-A00 DET Internally inspect the HORIZONTAL STABILIZER components: • Ribs, from rib sta. YH=990 to rib sta.

YH=2965 (SSI 55-10-05)

– 60 MO 333/334 ALL ± 30 Days

55-10-00-220-C02-A00 DET Externally inspect the HORIZONTAL STABILIZER components: • Skin, from rib sta. YH=990 to rib sta.

YH=2965-upper surface (SSI 55-10-03)

– 60 MO 333/334 ALL ± 30 Days



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REFERENCE NUMBER

TYPE


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55-10-00-220-C03-A00 DET Internally inspect the HORIZONTAL STABILIZER components: • Front spar web and cap, from rib sta.

YH=350 to rib sta. YH=2965 (SSI 55-10-10)

– 60 MO 333/334 ALL ± 30 Days

55-10-00-220-C04-A00 DET Internally inspect the HORIZONTAL STABILIZER components: • Front spar web and cap, from fin to rib

sta. YH=350, including center fitting/spar attachment (SSI 55-10-09)

– 60 MO 333/334 ALL ± 30 Days

55-10-00-220-C05-A00 DET Internally inspect the HORIZONTAL STABILIZER components: • Rear spar web & cap, from rib sta.

YH=350 to rib sta. YH=2965, including fitting hinge stabilizer attach to elevator (SSI 55-10-13)

– 60 MO 333/334 ALL ± 30 Days

55-10-00-220-C06-A00 DET Internally inspect the HORIZONTAL STABILIZER components: • Ribs, from rib sta. YH=30 to rib sta.

YH=990 (SSI 55-10-04)

– 60 MO 333/334 ALL ± 30 Days

55-20-00-210-C01-A00 GVI Externally inspect the ELEVATORcomponents: • Skin, between root and sta. YH=160

(SSI 55-20-26)

96 MO 60 MO 335/336 ALL ± 30 Days



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TYPE


(Flight Cycles)


55-20-00-210-C02-A00 GVI Internally inspect the ELEVATORcomponents: • Spars between root and sta. YH=160

(SSI 55-20-25)

96 MO 60 MO 335/336 ALL ± 30 Days

55-20-00-210-C03-A00 GVI Externally inspect the ELEVATORcomponents: • Skin, between sta. YH=160 and sta.

YH=3320 (SSI 55-20-28)

96 MO 60 MO 335/336 ALL ± 30 Days

55-20-00-210-C04-A00 GVI Externally inspect the ELEVATORcomponents: • Tab (SSI 55-20-37)

– 60 MO 335/336 ALL ± 30 Days

55-20-00-210-C05-A00 GVI Internally inspect the ELEVATORcomponents: • Spars, between sta. YH=160 and

sta. YH=3320 (SSI 55-20-27)

96 MO 60 MO 335/336 ALL ± 30 Days

55-20-00-220-C02-A00 DET Internally inspect the ELEVATORcomponents: • Ribs, between root and sta. YH=160

(SSI 55-20-29)

96 MO 60 MO 335/336 ALL ± 30 Days

55-20-00-220-C03-A00 DET Externally inspect the ELEVATORcomponents: • Tab Hinge Fittings (SSI 55-20-36)

72 MO 30 MO 335/336 ALL ± 30 Days



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TYPE


(Flight Cycles)


55-20-00-220-C05-A00 DET Internally inspect the ELEVATORcomponents: • Ribs, between sta. YH=160 and sta.

YH=983.4 (SSI 55-20-30)

96 MO 60 MO 335/336 ALL ± 30 Days

55-20-00-220-C06-A00 DET Internally inspect the ELEVATORcomponents: • Ribs, between sta. YH=3001 and

sta. YH=3320 (SSI 55-20-33)

96 MO 60 MO 335/336 ALL ± 30 Days

55-20-00-290-C01-A00 SDE Internally inspect the ELEVATORcomponents using a boroscope: • Ribs, between sta. YH=983,4 and

sta. YH=1898 (SSI 55-20-31)

– 60 MO 335/336 ALL ± 30 Days

55-20-00-290-C02-A00 SDE Internally inspect the ELEVATORcomponents using a boroscope: • Ribs, between sta. YH=1898 and

sta. YH=3001 (SSI 55-20-32)

– 60 MO 335/336 ALL ± 30 Days

55-30-00-210-C01-A00 GVI Externally inspect the VERTICAL STABILIZER components: • Skin at spars 1, 2, auxiliary spar 41%

and stringers 20% & 35.5% between fuselage & rib sta. ZV=1169 (SSI 55-30-38)

96 MO 60 MO 324 ALL ± 30 Days


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TYPE


(Flight Cycles)


55-30-00-210-C02-A00 GVI Externally inspect the VERTICAL STABILIZER components: • Skin at spar 3, auxiliary spar 52%

and stringers 46.5% & 57.65%,between fuselage & rib sta. ZV=1169 (SSI 55-30-39)

72 MO 30 MO 325 ALL ± 30 Days

55-30-00-210-C03-A00 GVI Externally inspect the VERTICAL STABILIZER components: • Skin at ribs from fuselage to sta.

ZV=1169 (SSI 55-30-47)

96 MO 60 MO 325 ALL ± 30 Days

55-30-00-210-C04-A00 GVI Internally inspect the VERTICAL STABILIZER components: • Ribs (sta. ZV=3461, ZV=2538,

ZV=1677, ZV=1550.5, ZV=1430.5,ZV=1423, ZV=1302, ZV=1169 andZV=915) (SSI 55-30-73)

96 MO 60 MO 325 ALL ± 30 Days


and stringers 20% & 35.5% betweenribs sta. ZV=1169 & sta. ZV=2799 (SSI 55-30-40)

96 MO 60 MO 324 ALL ± 30 Days


and stringers 20% & 35.5% betweenrib sta. ZV=2799 & horizontal stabilizer (SSI 55-30-42)

96 MO 60 MO 324 ALL ± 30 Days

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TYPE


(Flight Cycles)


55-30-00-210-C07-A00 GVI Externally inspect the VERTICAL STABILIZER components: • Skin at windows from fuselage to sta.

ZV=1169 (SSI 55-30-44)

96 MO 60 MO 324 ALL ± 30 Days

55-30-00-210-C08-A00 GVI Externally inspect the VERTICAL STABILIZER components: • Skin at windows between sta.

ZV=2799 and horizontal stabilizer(SSI 55-30-46)

96 MO 60 MO 324 ALL ± 30 Days


and stringers 46.5% & 57.65%,between ribs sta. ZV=1169 & sta. ZV=2799 (SSI 55-30-41)

72 MO 30 MO 325 ALL ± 30 Days

55-30-00-210-C10-A00 GVI Externally inspect the VERTICAL STABILIZER components: • Skin at spar 3, auxiliary spar 52%,

and stringers 46.5% & 57.65%,between rib sta. ZV=2799 &horizontal stabilizer (SSI 55-30-43)

72 MO 30 MO 325 ALL ± 30 Days


ZV=1169 & sta. ZV=2799(SSI 55-30-45)

72 MO 30 MO 325 ALL ± 30 Days



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TYPE


(Flight Cycles)


55-30-00-210-C07-A00 GVI Externally inspect the VERTICAL STABILIZER components: • Skin at windows from fuselage to sta.

ZV=1169 (SSI 55-30-44)

96 MO 60 MO 324 ALL ± 30 Days


ZV=2799 and horizontal stabilizer(SSI 55-30-46)

96 MO 60 MO 324 ALL ± 30 Days


and stringers 46.5% & 57.65%,between ribs sta. ZV=1169 & sta. ZV=2799 (SSI 55-30-41)

72 MO 30 MO 325 ALL ± 30 Days

55-30-00-210-C10-A00 GVI Externally inspect the VERTICAL STABILIZER components: • Skin at spar 3, auxiliary spar 52%,

and stringers 46.5% & 57.65%,between rib sta. ZV=2799 &horizontal stabilizer (SSI 55-30-43)

72 MO 30 MO 325 ALL ± 30 Days


ZV=1169 & sta. ZV=2799(SSI 55-30-45)

72 MO 30 MO 325 ALL ± 30 Days



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TYPE


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55-30-00-210-C12-A00 GVI Externally inspect the VERTICAL STABILIZER components: • Skin at ribs, between sta. ZV=1169

and sta. ZV=2799 (SSI 55-30-48)

72 MO 30 MO 325 ALL ± 30 Days

55-30-00-210-C13-A00 GVI Externally inspect the VERTICAL STABILIZER components: • Skin at ribs, between sta. ZV=2799 and

horizontal stabilizer (SSI 55-30-49)

72 MO 30 MO 325 ALL ± 30 Days

55-30-00-220-C01-A00 DET Internally inspect the VERTICAL STABILIZER components: • Root rib, including bolts (SSI 55-30-70)

96 MO 60 MO 325 ALL ± 30 Days

55-30-00-220-C02-A00 DET Internally inspect the VERTICAL STABILIZER components: • Ribs of horizontal stabilizer actuators

(sta. ZV=3145, ZV=3015 andZV=2799) (SSI 55-30-71)

96 MO 60 MO 325 ALL ± 30 Days

55-30-00-220-C03-A00 DET Internally inspect the VERTICAL STABILIZER components: • Ribs of actuator area (sta. ZV=1932

and ZV=2277) (SSI 55-30-72)

96 MO 60 MO 325 ALL ± 30 Days

55-40-00-210-C01-A00 GVI Externally inspect the RUDDERcomponents: • Front spar - skin attachment (rudder

I) (SSI 55-40-81)

96 MO 60 MO 326 ALL ± 30 Days



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55-40-00-210-C02-A00 GVI Externally inspect the RUDDERcomponents: • Spar - skin attachment (rudder II)

(SSI 55-40-86)

96 MO 60 MO 327 ALL ± 30 Days

55-40-00-210-C03-A00 GVI Externally inspect the RUDDERcomponents: • Rear spar - skin attachment

(rudder I) (SSI 55-40-82)

96 MO 60 MO 326 ALL ± 30 Days

55-40-00-210-C04-A00 GVI Externally inspect the RUDDERcomponents: • LT & RT skin - spar cap attachment


96 MO 60 MO 326 ALL ± 30 Days

55-40-00-210-C05-A00 GVI Externally inspect the RUDDERcomponents: • Ribs - skin attachment (rudder I)

(SSI 55-40-84)

96 MO 60 MO 326 ALL ± 30 Days

55-40-00-210-C06-A00 GVI Externally inspect the RUDDERcomponents: • Hinges - rudder I (SSI 55-40-85)

96 MO 60 MO 326 ALL ± 30 Days

55-40-00-210-C07-A00 GVI Externally inspect the RUDDERcomponents: • LT & RT skin - spar cap attachment

(rudder II) (SSI 55-40-87)

96 MO 60 MO 327 ALL ± 30 Days

55-40-00-210-C08-A00 GVI Externally inspect the RUDDERcomponents: • Ribs - skin attachment (rudder II)

(SSI 55-40-88)

96 MO 60 MO 327 ALL ± 30 Days



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DESCRIPTION



55-40-00-210-C09-A00 GVI Externally inspect the RUDDERcomponents: • Hinges - rudder II (SSI 55-40-89)

96 MO 60 MO 327 ALL ± 30 Days

55-40-00-220-C03-A00 DET Internally inspect the RUDDERcomponents: • Front spar - skin attachment


96 MO 60 MO 326 ALL ± 30 Days

55-40-00-220-C04-A00 DET Internally inspect the RUDDERcomponents: • Spar - skin attachment (rudder II)

(SSI 55-40-86)

96 MO 60 MO 327 ALL ± 30 Days

55-40-00-220-C05-A00 DET Internally inspect the RUDDERcomponents: • Rear spar - skin attachment


96 MO 60 MO 326 ALL ± 30 Days

55-40-00-220-C06-A00 DET Internally inspect the RUDDERcomponents: • LT & RT skin - spar cap attachment


96 MO 60 MO 326 ALL ± 30 Days

55-40-00-220-C07-A00 DET Internally inspect the RUDDERcomponents: • Ribs - skin attachment (rudder I)

(SSI 55-40-84)

96 MO 60 MO 326 ALL ± 30 Days




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55-40-00-220-C08-A00 DET Internally inspect the RUDDERcomponents: • Hinges - rudder I (SSI 55-40-85)

96 MO 60 MO 326 ALL ± 30 Days

55-40-00-220-C09-A00 DET Internally inspect the RUDDERcomponents: • LT & RT skin - spar cap attachment

(rudder II) (SSI 55-40-87)

96 MO 60 MO 327 ALL ± 30 Days

55-40-00-220-C10-A00 DET Internally inspect the RUDDERcomponents: • Ribs - skin attachment (rudder II)

(SSI 55-40-88)

96 MO 60 MO 327 ALL ± 30 Days

55-40-00-220-C11-A00 DET Internally inspect the RUDDERcomponents: • Hinges - rudder II (SSI 55-40-89)

96 MO 60 MO 327 ALL ± 30 Days

CHAPTER 57 – WINGS

REFERENCE NUMBER

TYPE


(Flight Cycles)


57-01-00-220-C01-A00 DET Internally inspect the WING STUBcomponents: • Wing stub - lower skin - rib 2A


– 120 MO 155/156/157

ALL ± 60 Days



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57-01-00-220-C02-A00 DET Internally inspect the WING STUBcomponents: • Wing stub - rib 2A skin supports and

their attachments to web, lowerflange, and FWD & AFT web supports (SSI 57-01-18)

– 60 MO 155/156/157

EMB-145MPEMB-135LR

± 30 Days

57-01-00-220-C03-A00 DET Externally inspect the WING STUBcomponents: • Wing stub - lower skin - rib 2A


– 120 MO 155/156/157

EMB-145MPEMB-135LR

± 60 Days



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TYPE


(Flight Cycles)


57-01-00-220-C04-A00 DET Externally inspect the WING STUBcomponents: • Wing stub - upper skin - rib 2A


– 60 MO 155/156/157

EMB-145MPEMB-135LR

± 30 Days

57-01-00-220-C05-A00 DET Internally inspect the WING STUBcomponents: • Wing stub - Spar 2 - brackets ribs 2A

attachments (SSI 57-01-17)

– 120 MO 155/156/157

EMB-145MPEMB-135LR

± 60 Days

57-01-00-220-C06-A00 DET Internally inspect the WING STUBcomponents: • Wing stub - spar 1 - brackets ribs 2A


– 120 MO 155/156/157

ALL ± 60 Days



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(Flight Cycles)


57-01-00-220-C07-A00 DET Internally inspect the WING STUBcomponents: • Wing stub - upper skin - rib 2A


– 60 MO 155/156/157

EMB-145MPEMB-135LR

± 30 Days

57-10-00-210-C01-A00 GVI Externally inspect the WING STUBcomponents: • Upper skin - tire compartment

composite panel (SSI 57-10-14)

– 120 MO 155/156/157

ALL ± 60 Days

57-10-00-220-C02-A00 DET Internally inspect the WING STUBcomponents: • Spar 3 - lower skin attachments

(SSI 57-10-09)

– 30 MO 155/156/157

ALL ± 30 Days

57-10-00-220-C03-A00 DET Internally inspect the WING STUBcomponents: • Spar 1 - brackets, ribs 1 and 3


– 60 MO 155/156/157

ALL ± 30 Days



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TYPE


(Flight Cycles)


57-10-00-220-C04-A00 DET Internally inspect the WING STUBcomponents: • Upper skin - rib 1 attachments and

spanwise splice of integral panel(SSI 57-10-13)

– 120 MO 155/156/157

EMB-145MPEMB-135LR

± 60 Days

57-10-00-220-C05-A00

DET

Externally inspect the WING STUBcomponents: • Upper skin - rib 1 attachments and

spainwise splice of integral panel(SSI 57-10-13)

–

30 MO 155/156/157

ALL ± 30 Days



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TYPE


(Flight Cycles)


57-10-00-220-C09-A00 DET Externally inspect the WING STUBcomponents: • Rib 4 - lower flange and web

(SSI 57-10-11)

– 60 MO 155/156/157

ALL ± 30 Days

57-10-00-220-C10-A00 DET Internally inspect the WING STUBcomponents: • Spar 3 - center bracket and rib 2


– 30 MO 155/156/157

ALL ± 30 Days

57-10-00-220-C11-A00 DET Internally inspect the WING STUBcomponents: • Rib 4 - lower flange and web

(SSI 57-10-11)

– 30 MO 155/156/157

ALL ± 30 Days

57-10-00-220-C12-A00 DET Internally inspect the WING STUBcomponents: • Rib 2 - Longitudinal stringer-to-web


– 30 MO 155/156/157

ALL ± 30 Days

57-10-00-220-C13-A00 DET Internally inspect the WING STUBcomponents: • Upper skin - tire compartment

composite panel (SSI 57-10-14)

– 30 MO 155/156/157

ALL ± 30 Days

57-10-00-220-C14-A00 DET Internally inspect the WING STUBcomponents: • Spar 2 - center brackets & rib 2

attachments and ribs 1 & 3 webattachments (SSI 57-10-07)

– 60 MO 155/156/157

ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-10-00-220-C15-A00 DET Externally inspect the WING STUBcomponents: • Spar 3 - lower skin attachments

(SSI 57-10-09)

– 30 MO 155/156/157

EMB-145MPEMB-135LR

± 30 Days

57-21-00-210-C01-A00 GVI Externally inspect the WING components:• Upper skin/spar attachment

(SSI 57-21-37)

72 MO 30 MO 531/631 ALL ± 30 Days

57-21-00-210-C02-A00 GVI Externally inspect the WING components:• Skin panels (SSI 57-21-26)

96 MO 60 MO 531/631541/641551/651

EMB-145MP EMB-135LR

± 30 Days



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(Flight Cycles)


57-21-00-210-C05-A00 GVI Externally inspect the WING components:• Upper skin/spar attachment

(SSI 57-21-37)

96 MO 60 MO 541/641551/651

ALL ± 30 Days

57-21-00-210-C06-A00 GVI Externally inspect the WING components:• Lower skin panel chordwise joint

(SSI 57-21-29)

– 60 MO 531/631 ALL ± 30 Days

57-21-00-210-C07-A00 GVI Internally inspect the WING components:• Lower skin panel spanwise joint

(SSI 57-21-30)

– 60 MO 532/632 EMB-145MP EMB-135LR

± 30 Days

57-21-00-210-C09-A00 GVI Internally inspect the WING components:• Skin panels (SSI 57-21-26)

96 MO 60 MO 551/651 ALL ± 30 Days

57-21-00-210-C10-A00 GVI Internally inspect the WING components:• Upper skin/spar stub attachment

(SSI 57-21-39)

– 60 MO 531/631 ALL ± 30 Days

57-21-00-210-C08-A00 GVI Internally inspect the WING components:• Upper skin panel spanwise joint

(SSI 57-21-31)

– 60 MO 532/632541/641

ALL ± 30 Days



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TYPE


(Flight Cycles)


57-21-00-210-C11-A00 GVI Internally inspect the WING components:• Skin panels (SSI 57-21-26)

– 120 MO 531/631541/641

ALL ± 60 Days

57-21-00-210-C12-A00 GVI Internally inspect the WING components:• Upper skin panel spanwise joint

(SSI 57-21-31)

– 120 MO 531/631551/651

ALL ± 60 Days

57-21-00-210-C14-A00 GVI Internally inspect the WING components:• Lower vent hole (SSI 57-21-33)

– 120 MO 541/641 ALL ± 60 Days

57-21-00-210-C15-A00 GVI Internally inspect the WING components:• Lower skin panel spanwise joint

(SSI 57-21-30)

– 120 MO 551/651 ALL ± 60 Days

57-21-00-210-C16-A00 GVI Internally inspect the WING components:• Upper skin/spar attachment

(SSI 57-21-37)

– 120 MO 541/641551/651

ALL ± 60 Days

57-21-00-210-C17-A00 GVI Internally inspect the WING components:• Lower skin/wing stub attachment

(SSI 57-21-38)

– 120 MO 531/631 ALL ± 60 Days

57-21-00-210-C18-A00 GVI Externally inspect the WING components:• Upper skin/wing stub attachment

(SSI 57-21-39)

– 30 MO 531/631 ALL ± 30 Days

57-21-00-210-C19-A00 GVI Externally inspect the WING components:• Lower skin panel spanwise joint

(SSI 57-21-30)

– 60 MO 531/631541/641551/651

ALL ± 30 Days

57-21-00-210-C20-A00 GVI Externally inspect the WING components:• Upper skin panel spanwise joint

(SSI 57-21-31)

– 60 MO 531/631541/641551/651

ALL ± 30 Days



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57-21-00-210-C21-A00 GVI Externally inspect the WING components:• Lower skin access holes (SSI 57-21-32)

96 MO 60 MO 531/631541/641

ALL ± 30 Days

57-21-00-210-C22-A00 GVI Externally inspect the WING components:• Gravity fuel hole (SSI 57-21-35)

96 MO 60 MO 541/641 ALL ± 30 Days

57-21-00-210-C23-A00 GVI Externally inspect the WING components:• Lower skin/wing stub attachment

(SSI 57-21-38)

– 60 MO 531/631 ALL ± 30 Days

57-21-00-210-C24-A00 GVI Internally inspect the WING components:• Gravity fuel hole (SSI 57-21-35)

– 120 MO 541/641 ALL ± 60 Days

57-21-00-210-C25-A00 GVI Internally inspect the WING components:• Upper skin/spar attachment

(SSI 57-21-37)

– 120 MO 531/631 ALL ± 60 Days

57-22-00-220-C01-A00 DET Internally inspect the WING components:• Spar 1, web and stiffeners

(SSI 57-22-40)

– 120 MO 531/631541/641551/651




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57-22-00-220-C03-A00

DET

Internally inspect the WING components:• Spar 1, web and stiffeners

(SSI 57-22-40)

–

30 MO 531/631541/641551/651

EMB-135LR

L

± 30 Days

57-23-00-210-C01-A00 GVI Internally inspect the WING components:• Spar 2/wing stub attachments

(SSI 57-23-48)

– 60 MO 531/631 ALL ± 30 Days

57-23-00-220-C01-A00 DET Externally inspect the WING components:• Spar 2, web and stiffeners

(SSI 57-23-45)

– 60 MO 531/631541/641551/651

ALL ± 30 Days

57-24-00-210-C02-A00

GVI

Externally inspect the WING components:• Spar 3, web and stiffeners

(SSI 57-24-49)

–

60 MO 532/632 ALL ± 30 Days

57-24-00-210-C03-A00

GVI

Internally inspect the WING components:• Spar 3, web and stiffeners

(SSI 57-24-49)

–

60 MO 532/632 ALL ± 30 Days



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TYPE


(Flight Cycles)


57-24-00-210-C04-A00 GVI Externally inspect the WING components:• Spar 3, web cutouts (SSI 57-24-51)

– 60 MO 532/632 ALL ± 30 Days

57-24-00-210-C05-A00 GVI Internally inspect the WING components:• Spar 3, web cutouts (SSI 57-24-51)

– 60 MO 532/632 ALL ± 30 Days

57-25-00-210-C01-A00 GVI Externally inspect the WING components:• Lower skin/rib attachment

(SSI 57-25-54)

96 MO 60 MO 531/631541/641551/651

EMB-145MPEMB-135LR

± 30 Days

57-25-00-210-C02-A00 GVI Externally inspect the WING components:• Upper skin/rib attachment

(SSI 57-25-55)

96 MO 60 MO 531/631541/641551/651

ALL ± 30 Days



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TYPE


(Flight Cycles)


57-25-00-210-C03-A00 GVI Internally inspect the WING components:• Ribs, main box (SSI 57-25-53)

– 120 MO 531/631541/641551/651

EMB-145MPEMB-135LR

± 60 Days

57-25-00-210-C04-A00 GVI Internally inspect the WING components:• Lower skin/rib attachment

(SSI 57-25-54)

– 120 MO 531/631541/641551/651

ALL ± 60 Days

57-25-00-210-C05-A00 GVI Internally inspect the WING components:• Upper skin/rib attachment

(SSI 57-25-55)

– 120 MO 531/631541/641551/651

ALL ± 60 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-26-00-220-C01-A00 DET Internally inspect the WING components:• FWD & aft side brace fittings MLG

(SSI 57-26-56) NOTE: Applicable to aircraft Pre-

Mod. SB 145-32-0063

– 15 MO 532/632 ALL ± 15 Days

57-26-00-220-C01-A01 DET Internally inspect the WING components:• FWD & aft side brace fittings MLG

(SSI 57-26-56) NOTE: Applicable to aircraft Post-

Mod. SB 145-32-0063

– 30 MO 532/632 ALL ± 30 Days

57-26-00-220-C02-A00 DET Internally inspect the WING components:• Lower Bearing Cap (SSI 57-26-94)

NOTE: Applicable to aircraft Pre-Mod. SB 145-32-0063

– 15 MO 532/632 ALL ± 15 Days

57-26-00-220-C02-A01 DET Internally inspect the WING components:• Lower Bearing Cap (SSI 57-26-94)

NOTE 1: Applicable to aircraft Post-Mod. SB 145-32-0063.

NOTE 2: If corrosion is detected on the lower bearing cap internal surface, perform internal inspection on thecorresponding upper trunnion bearing surface

– 30 MO 532/632 ALL ± 30 Days

57-26-00-220-C03-A00 DET Internally inspect the WING components:• Aft upper Trunnion (SSI 57-26-95)


– 15 MO 532/632 ALL ± 15 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-26-00-220-C03-A01 DET Internally inspect the WING components:• Aft upper Trunnion (SSI 57-26-95)

NOTE: Applicable to aircraft Post- Mod. SB 145-32-0063.

– 60 MO 532/632 ALL ± 30 Days

57-26-00-220-C04-A00 DET Internally inspect the WING components:• Fwd upper Trunnion (SSI 57-26-96)

NOTE: Applicable to aircraft Pre- Mod. SB 145-32-0063.

– 15 MO 532/632 ALL ± 15 Days

57-26-00-220-C04-A01 DET Internally inspect the WING components:• Fwd upper Trunnion (SSI 57-26-96)

NOTE: Applicable to aircraft Post- Mod. SB 145-32-0063.

– 60 MO 532/632 ALL ± 30 Days

57-28-00-210-C01-A00 GVI Externally inspect the WING components:• Lower skin, torque box (SSI 57-28-58)

– 30 MO 551/651 ALL ± 30 Days

57-28-00-210-C02-A00 GVI Externally inspect the WING components:• Spar attachment, torque box

(SSI 57-28-57)

48 MO 30 MO 541/641 ALL ± 30 Days

57-28-00-210-C03-A00 GVI Externally inspect the WING components:• Spar attachment, torque box

(SSI 57-28-57)

96 MO 60 MO 532/632 ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-28-00-210-C06-A00 GVI Externally inspect the WING components:• Attachment lugs aileron (SSI 57-28-66)

– 60 MO 551/651 EMB-145MP ± 30 Days

57-28-00-210-C07-A00 GVI Externally inspect the WING components:• Flap actuator attachment fittings

(SSI 57-28-67)

96 MO 60 MO 532/632541/641

ALL ± 30 Days

57-28-00-210-C08-A00 GVI Internally inspect the WING components:• Lower skin, torque box (SSI 57-28-58)

– 60 MO 551/651 ALL ± 30 Days

57-28-00-210-C09-A00 GVI Internally inspect the WING components:• Upper skin, torque box (SSI 57-28-61)

96 MO 60 MO 532/632 ALL ± 30 Days

57-28-00-210-C10-A00 GVI Internally inspect the WING components:• Spar attachment, torque box

(SSI 57-28-57)

– 120 MO 532/632 ALL ± 60 Days

57-28-00-210-C11-A00 GVI Internally inspect the WING components:• Upper skin, torque box (SSI 57-28-61)

– 120 MO 541/641551/651

ALL ± 60 Days

57-28-00-210-C13-A00 GVI Internally inspect the WING components:• Lower skin, torque box (SSI 57-28-58)

– 60 MO 532/632 ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-28-00-210-C14-A00 GVI Internally inspect the WING components:• Tracks/ribs attachment, torque box

(SSI 57-28-62)

– 120 MO 532/632541/641

ALL ± 60 Days

57-28-00-210-C15-A00 GVI Externally inspect the WING components:• Lower skin, torque box (SSI 57-28-58)

– 30 MO 532/632 ALL ± 30 Days

57-28-00-220-C01-A00 DET Externally inspect the WING components:• Spar attachment, torque box

(SSI 57-28-57)

72 MO 30 MO 551/651 ALL ± 30 Days

57-28-00-220-C03-A00 DET Externally inspect the WING components:• Flap track, torque box (SSI 57-28-59)

96 MO 60 MO 532/632541/641551/651

ALL ± 30 Days

57-28-00-220-C05-A00 DET Externally inspect the WING components:• Tracks/rib attachment, torque box 3

(SSI 57-28-65)

– 60 MO 551/651 ALL ± 30 Days

57-28-00-220-C07-A00 DET Externally inspect the WING components:• Attachment actuator lugs, inboard/

outboard spoilers (SSI 57-28-70)

– 60 MO 532/632 ALL ± 30 Days

57-28-00-220-C09-A00 DET Internally inspect the WING components:• Tracks/rib attachment, torque box 3

(SSI 57-28-65)

– 120 MO 551/651 ALL ± 60 Days

57-28-00-220-C11-A00 DET Internally inspect the WING components:• Ribs, torque box (SSI 57-28-60)

96 MO 60 MO 532/632 ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-28-00-220-C12-A00 DET Externally inspect the WING components:• Ribs, torque box (SSI 57-28-60)

96 MO 60 MO 532/632 ALL ± 30 Days

57-41-00-210-C01-A00 GVI Externally inspect the WING LEADING EDGE components: • Wing leading edge 1 skin

(SSI 57-41-94)

48 MO 30 MO 511/611 ALL ± 30 Days

57-42-00-210-C01-A00 GVI Externally inspect the WING LEADING EDGE components: • Wing leading edge 2 skin

(SSI 57-42-95)

48 MO 30 MO 512/612 ALL ± 30 Days

57-42-00-220-C01-A00 DET Externally inspect the WING LEADING EDGE components: • Wing leading edge 2 bottom skin at

connections to lower rear girder &wing lower spar cap (SSI 57-42-97)

– 30 MO 512/612 ALL ± 30 Days

57-43-00-210-C01-A00 GVI Externally inspect the LEADING EDGEcomponents: • Wing leading edge 3 skin

(SSI 57-43-96)

48 MO 30 MO 513/613 ALL ± 30 Days

57-50-00-220-C01-A00 DET Externally inspect the FLAP components:• Tracks/rib attachment, flaps

(SSI 57-50-77)

96 MO 60 MO 571/671572/672

ALL ± 30 Days

57-50-00-220-C02-A00 DET Externally inspect the FLAP components:• Tracks, flaps (SSI 57-50-80)

96 MO 60 MO 571/671572/672

ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-52-00-210-C01-A00 GVI Externally inspect the FLAP components:• Pin and actuator lugs, inboard flap

(SSI 57-52-75)

96 MO 60 MO 571/671 ALL ± 30 Days

57-52-00-220-C01-A00 DET Externally inspect the FLAP components:• Fitting tip spar, inboard flap

(SSI 57-52-73)

96 MO 60 MO 571/671 ALL ± 30 Days

57-53-00-210-C01-A00 GVI Externally inspect the FLAP components:• Pin and actuator lugs, outboard flap

(SSI 57-53-84)

96 MO 60 MO 572/672 ALL ± 30 Days

57-53-00-210-C02-A00 GVI Externally inspect the FLAP components:• Center ribs attachment, outboard

flap (SSI 57-53-87)

96 MO 60 MO 572/672 ALL ± 30 Days

57-61-00-210-C01-A00 GVI Externally inspect the AILERONcomponents: • Hinges attachment, aileron

(SSI 57-61-89)

96 MO 60 MO 573/673 EMB-145MP ± 30 Days

57-61-00-210-C02-A00 GVI Externally inspect the AILERON components: • Spar cap, aileron (SSI 57-61-91)

96 MO 60 MO 573/673 ALL ± 30 Days



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REFERENCE NUMBER

TYPE


(Flight Cycles)


57-70-00-210-C01-A00 GVI Externally inspect the SPOILERcomponents: • Hinges attachment, spoilers

(SSI 57-70-92)

– 60 MO 5712/67125713/6713

ALL ± 30 Days

57-70-00-210-C02-A00 GVI Externally inspect the SPOILERcomponents: • Actuator attachment, spoilers

(SSI 57-70-93)

– 60 MO 5712/67125713/6713

ALL ± 30 Days



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SECTION 5

ZONAL INSPECTION REQUIREMENTS

RADOME

REFERENCE NUMBER

DESCRIPTION LU INT ACCESS (as applicable) EFFECT TOLERANCE

53-Z111-213-001-A00

ZONE 111

External General Visual Inspection

48 MO or

10000 FH

–

ALL

± 30 Days

53-Z111-214-001-A00

ZONE 111

Internal General Visual Inspection

48 MO or

10000 FH

111

ALL

± 30 Days

FORWARD FUSELAGE I

REFERENCE NUMBER


53-Z113-213-001-A00

ZONES 113/114


48 MO or

10000 FH

–

ALL

± 30 Days

53-Z113-214-001-A00

ZONES 113


48 MO or

10000 FH

113DL 113EL

ALL

± 30 Days



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FORWARD FUSELAGE I (Continued)

REFERENCE NUMBER


53-Z114-214-001-A00

ZONE 114

Internal General Visual Inspection NOTE: EWIS

48 MO

or 10000 FH

114CR

ALL

± 30 Days

53-Z213-213-001-A00

ZONES 213/214/


48 MO or

10000 FH

–

ALL

± 30 Days

53-Z213-214-001-A00

ZONES 113/114/213/214/215/216


48 MO

or 10000 FH

113AZ 113BZ 113CZ 114AZ 114BZ

ALL

± 30 Days

FORWARD FUSELAGE II

REFERENCE NUMBER


53-Z123-213-001-A00

ZONES 123/124 External General Visual Inspection

48 MO

or 10000 FH

–

ALL

± 30 Days



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FORWARD FUSELAGE II (Continued)

REFERENCE NUMBER


53-Z123-214-001-A00

ZONES 121/122/123/124 Internal General Visual Inspection NOTE: EWIS

48 MO

or 10000 FH

123BL 221AF 221BF 221CF 221DF 221EF 221FF 221GF 222AF 222BF 222CF 222DF 222EF 222FF 222GF

ALL

± 30 Days

53-Z223-213-001-A00

ZONES 223/224


48 MO or

10000 FH

–

ALL

± 30 Days



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FORWARD FUSELAGE II (Continued)

REFERENCE NUMBER


53-Z223-214-001-A00

ZONES 221/222/223/224


48 MO

or 10000 FH

223AZ/BZ CLW/DLW/

ELW/FLW/GZ/ HZ/IZ

JLW/KLW/ LZ/MZ/NZ/OZ/ PZ/QZ/RZ/SZ/

TZ/UZ 224CRW/

DRW/ERW/ FRW/GZ/ HZ/JRW/

KRW/ 224MZ/NZ

ALL

± 30 Days

53-Z225-213-001-A00

ZONES 225/226 External General Visual Inspection

96MO

or 20000 FH

–

ALL

± 60 Days

53-Z225-214-001-A00

ZONES 225/226 Internal General Visual Inspection NOTE: Perform at the opportunity of CPCP task53-12-00-220-C01-A00 accomplishment.

96 MO

or 20000 FH

225ALC/

BLC/CTC/DTC/ETC/

226ARC/ 226BRC

ALL

± 60 Days


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REFERENCE NUMBER


53-Z131-213-001-A00

ZONES 131/132


48 MO or

10000 FH

–

ALL

± 30 Days

53-Z131-214-001-A00

ZONES 131/132


24 MO

or 5000 FH

231AF/BF CF/DF/EF/

FF/GF/HF/JF232AF/BF 232CF/DF

ALL

± 30 Days

53-Z231-213-001-A00

ZONES 231/232


48 MO or

10000 FH

–

ALL

± 30 Days

53-Z231-214-001-A00

ZONES 231/232


48 MO or

10000 FH

231ALW 231BLW 231CLW 241ALW 241DLW 242ARW 242BRW 242DRW

ALL

±30 Days

53-Z233-213-001-A00

ZONES 233/234


48 MO or

10000 FH

–

ALL

± 30 Days


CENTER FUSELAGE I


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CENTER FUSELAGE I (Continued)

REFERENCE NUMBER


53-Z233-214-001-A00

ZONES 233/234


96 MO or

20000 FH

233ALC 233BLC 233CLC 234ARC 243ALC

ALL

± 60 Days

CENTER FUSELAGE II

REFERENCE NUMBER


53-Z141-213-001-A00

ZONES 141/142

External General Visual Inspection NOTE: EWIS

48 MO

or 10000 FH

-

ALL

± 30 Days

53-Z141-214-001-A00

ZONES 141/142


48 MO

or 10000 FH

231GF/231HF 241AF/241BF 241CF/241DF

241EF/ 242AF/242BF 242CF/242DF

251BF

ALL

± 30 Days

53-Z241-213-001-A00

ZONES 241/242


96 MO or

20000 FH

–

ALL

± 60 Days



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CENTER FUSELAGE II (Continued)

REFERENCE NUMBER


53-Z241-214-001-A00

ZONES 241/242


48 MO or

15000 FH

231BLW 231CLW 241ALW/

BLW/CLW/ DLW/ELW 242ARW/

BRW/CRW/ DRW/ERW

251ALW 251ELW 252ARW 252ERW

ALL

± 30 Days

53-Z243-213-003-A00

ZONES 243/244


96 MO or

20000 FH

–

ALL

± 60 Days

53-Z243-214-001-A00

ZONES 243/244


96 MO or

20000 FH

243ALC/

BLC/CLC/ DLC

253ALC

ALL

± 60 Days



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CENTER FUSELAGE III

REFERENCE NUMBER


53-Z151-214-002-A00

ZONES 151/152/153/154/155/156/157

Internal General Visual Inspection NOTES: EWIS

48 MO or

10000 FH

241DF/ 251AF/251BF251CF/251DF251/EF/251FF251GF/251HF/251JF/252AF/252BF/252CF/

252DF/

EMB-145MP EMB-135LR

± 30 Days



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CENTER FUSELAGE III (Continued)

REFERENCE NUMBER


53-Z155-214-001-A00

ZONES 155/156/157


48 MO

or 10000 FH

155BZ/CZ DZ/EZ/FZ/ GZ/KZ/LZ/ MZ/NZ/QZ/ 156BZ/CZ DZ/EZ/FZ/ GZ/KZ/LZ/ MZ/NZ/QZ/

192AL 192BR

EMB-145MP EMB-135LR

± 30 Days

53-Z251-213-001-A00

ZONES 251/252


96 MO or

20000 FH

–

ALL

± 60 Days

53-Z251-214-001-A00

ZONES 251/252


48 MO or

15000 FH

241CLW 251ALW

BLW/CLW/ DLW/

ELW/FLW/GL W/GRW

252ARW/ BRW/

CRW/DRW/ ERW/FRW

261ALW/CLW262ARW/

CRW

ALL

± 30 Days



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CENTER FUSELAGE III (Continued)

REFERENCE NUMBER


53-Z253-213-001-A00

ZONES 253/254


96 MO or

20000 FH

–

ALL

± 60 Days

53-Z253-214-001-A00

ZONES 253/254


96 MO or

20000 FH

253ALC/

BLC/CLC/ DLC/ELC 263ALC

ALL

± 60 Days

CENTER FUSELAGE IV

REFERENCE NUMBER


53-Z161-214-001-A00

ZONES 161/162


48 MO

or 10000 FH

251JF/251HF

252DF/ 261AF/BF/

CF/DF 262AF/BF/CF

ALL

± 30 Days

53-Z261-213-001-A00

ZONES 261/262


96 MO or

20000 FH

–

ALL

± 60 Days



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CENTER FUSELAGE IV (Continued)

REFERENCE NUMBER


53-Z261-214-001-A00

ZONES 261/262


48 MO or

10000 FH

261ALW/BLW/

CLW/DLW 262ARW/BRW/

CRW/DRW

ALL

± 30 Days

53-Z263-213-002-A00

ZONES 263/264


96 MO or

20000 FH

–

ALL

± 60 Days

53-Z263-214-001-A00

ZONES 263/264


96 MO

or 20000 FH

263ALC/

BLC

ALL

± 60 Days

REAR FUSELAGE I

REFERENCE NUMBER


53-Z171-213-001-A00

ZONES 171/172


24 MO or

5000 FH

–

ALL

± 30 Days



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REAR FUSELAGE I (Continued)

REFERENCE NUMBER


53-Z171-214-001-A00

ZONES 171/172


24 MO

or 5000 FH

271AF/BF/CF/

DF/EF/FF 272AF/BF/CF

/DR

ALL

± 30 Days

53-Z271-213-001-A00

ZONES 271/272/


24 MO or

5000 FH

–

ALL

± 30 Days

53-Z271-214-002-A00

ZONES 271/272/


48 MO

or 10000 FH

271ALW/BLW

272ARW/BRW/ CRW/DR

ALL

± 30 Days

53-Z275-214-001-A00

ZONES 275/276


48 MO

or 10000 FH

272DR

ALL

± 30 Days

53-Z273-213-002-A00

ZONES 273/274


96 MO or

20000 FH

ALL

± 60 Days

53-Z273-214-001-A00

ZONES 273/274


48 MO

or 10000 FH

272DR 273ATC 273BTC 273CTC

ALL

± 30 Days



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WING-TO-FUSELAGE ATTACHMENT FAIRING

REFERENCE NUMBER


53-Z191-213-001-A00

ZONES 191/192/193/194/195


48 MO or

10000 FH

–

EMB-145MP EMB-135LR

± 30 Days

53-Z191-214-001-A00

ZONES 191/192/193/194/195


48 MO

or 10000 FH

191ZB 192LB

193ABB 194ER 195EL

EMB-145MP EMB-135LR

± 30 Days



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REAR FUSELAGE II

REFERENCE NUMBER


53-Z311-213-001-A00

ZONES 311/312


48 MO or

10000 FH

–

ALL

± 30 Days

53-Z311-214-001-A00

ZONES 311/312


48 MO

or 10000 FH

312AR

ALL

± 30 Days

TAIL CONE FAIRING

REFERENCE NUMBER


53-Z313-213-001-A00

ZONE 313


24 MO or

5000 FH

–

ALL

± 30 Days

53-Z313-214-001-A00

ZONE 313


24 MO

or 5000 FH

313

313AL/BL/CL/ DR/GR 312AR

ALL

± 30 Days



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VERTICAL STABILIZER AND RUDDERS

REFERENCE NUMBER


55-Z321-213-001-A00

ZONES 321/322/323


48 MO or

10000 FH

ALL

± 30 Days

55-Z321-214-001-A00

ZONES 321/322/323/337


48 MO or

10000 FH

321 322 323

337AZ 337BZ 337CZ

ALL

± 30 Days

55-Z324-213-001-A00

ZONES 324/325


48 MO or

10000 FH

ALL

± 30 Days

55-Z324-214-001-A00

ZONES 324/325


48 MO

or 10000 FH

324AL/BL/CL/DL

EL/FR/ 325AL/BL/CL/DL

EL/FR/FL/GR/ HR/JR/KR/LR

ALL

± 30 Days

55-Z326-213-001-A00

ZONE 326/327


48 MO or

10000 FH

–

ALL

± 30 Days



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VERTICAL STABILIZER AND RUDDERS (Continued)

REFERENCE NUMBER


55-Z326-214-001-A00

ZONE 326/327


48 MO or

10000 FH

326AL/BL/CL/DL

EL/FL/GL/HL 327AL/BL/CL/DLER/FR/GR/HR

ALL

± 30 Days

HORIZONTAL STABILIZER AND ELEVATOR

REFERENCE NUMBER


55-Z333-213-001-A00

ZONES 331/332/333/334


48 MO or

10000 FH

–

ALL

± 30 Days

55-Z333-214-001-A00

ZONES 331/332/333/334


48 MO or

10000 FH

333AB/BB/CB/DL334AB/BB/CB/DR

ALL

± 30 Days

55-Z335-213-001-A00

ZONES 335/336


48 MO or

10000 FH

–

ALL

± 30 Days



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HORIZONTAL STABILIZER AND ELEVATOR (Continued)

REFERENCE NUMBER


55-Z335-214-001-A00

ZONES 335/336


48 MO or

10000 FH

335AB/BB/CB DB/EB/FB/GB

335HB 336AB/BB/CB DB/EB/FB/GB

336HB

ALL

± 30 Days

POWERPLANT

REFERENCE NUMBER


71-Z411-213-001-A00

ZONES 411/412/413 AND 421/422/423


24 MO or

5000 FH

–

ALL

± 30 Days

71-Z411-214-001-A00

ZONES 411/412/413/415 AND 421/422/423/425


24 MO

or 5000 FH

411 412 413 421 422 423

ALL

± 30 Days



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ENGINE PYLONS

REFERENCE NUMBER


54-Z414-213-001-A00

ZONES 414/424


24 MO or

5000 FH

–

ALL

± 30 Days

54-Z414-214-001-A00

ZONES 414/424


24 MO

or 5000 FH

414AB/BB/ CB/DB/EB/

FT/GT 424AB/BB/CB DB/EB/FT/GT

ALL

± 30 Days

THRUST REVERSER MODULE

REFERENCE NUMBER


78-Z416-213-001-A00

ZONES 416/426


24 MO or

5000 FH

–

ALL

± 30 Days



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THRUST REVERSER MODULE (Continued)

REFERENCE NUMBER


78-Z416-214-001-A00

ZONES 416/426


24 MO

or 5000 FH

416AB/BB/CB/DB/ EB/FB/GB/HT/IZ/ JT/KT/LT/MT/NT/

PR/QL/RR/SL//TR/ UL/VZ/XZ/WZ/YZ/416ZZ/426AB/BB/CB/DB/EB/FB/GB/ HT/JT/KT/LT/MT/ NT/PR/IZ/QL/RR/ SL/TR/UL/VZ/XZ/

WZ/YZ426ZZ

ALL

± 30 Days

PLAIN EXHAUST NOZZLE

REFERENCE NUMBER


78-Z416-213-001-A01

ZONES 416/426

External General Visual Inspection NOTE: For aircraft without Thrust Reversers only

48 MO

or 10000 FH

–

ALL

± 30 Days

78-Z416-214-001-A01

ZONES 416/426

Internal General Visual Inspection NOTE: For aircraft without Thrust Reversers only

48 MO

or 10000 FH

416 426

ALL

± 30 Days



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WING LEADING EDGE

REFERENCE NUMBER


57-Z511-213-001-A00

ZONES 511/611/512/612/513/613


24 MO or

5000 FH

–

ALL

± 30 Days

57-Z511-214-001-A00

ZONES 511/611/512/612/513/613


48 MO

or 10000 FH

511 512 513 611 612 613 561 661

191EL 191FR

ALL

± 30 Days

WING

REFERENCE NUMBER


57-Z531-213-001-A00

ZONES 531/631


48 MO or

10000 FH

–

ALL

± 30 Days



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WING (Continued)

REFERENCE NUMBER


57-Z531-214-001-A00

ZONES 531/631


48 MO

or 10000 FH

531AB/BB/CB 531DB

631AB/BB/CB 631DB

ALL

± 30 Days

57-Z532-213-001-A00

ZONES 532/632


48 MO or

10000 FH

–

ALL

± 30 Days

57-Z532-214-001-A00

ZONES 532/632


48 MO

or 10000 FH

532AB/BB 632AB/BB

ALL

± 30 Days

57-Z541-213-001-A00

ZONES 541/641


48 MO or

10000 FH

–

ALL

± 30 Days

57-Z541-214-001-A00

ZONES 541/641


48 MO

or 10000 FH

541AB/BB/CB/DB/

EB/FT/GB 641AB/BB/CB/DB/

EB/FT/GB

ALL

± 30 Days



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WING (Continued)

REFERENCE NUMBER


57-Z551-213-001-A00

ZONES 551/651/561/661


48 MO or

10000 FH

–

EMB-145MP EMB-135LR

± 30 Days

57-Z551-214-001-A00

ZONES 551/651/561/661


48 MO

or 10000 FH

551AB/ 551BB/ 551CB/ 551DB/ 551EB/ 551FT 651AB/ 651BB/ 651CB/ 651DB 651EB 651FT

EMB-145MP EMB-135LR

± 30 Days



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WING TRAILING EDGE

REFERENCE NUMBER


57-Z571-213-001-A00

ZONES 571/671/5711/6711/5712/6712/5713/6713


48 MO

or 10000 FH

–

ALL

± 30 Days

57-Z571-214-001-A00

ZONES 571/671/5711/6711/5712/6712/5713/6713


48 MO

or 10000 FH

5711 6711

ALL

± 30 Days

57-Z572-213-001-A00

ZONES 572/672/5721/6721/5722/6722


48 MO or

10000 FH

–

ALL

± 30 Days

57-Z572-214-001-A00

ZONES 572/672/5721/6721/5722/6722


48 MO

or 10000 FH

5721 5722 6721 6722

572AB/BB 672AB/BB

ALL

± 30 Days



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WING TRAILING EDGE (Continued)

REFERENCE NUMBER


57-Z573-213-001-A00

ZONES 573/673/5731/6731/5732/6732


48 MO or

10000 FH

–

ALL

± 30 Days

57-Z573-214-001-A00

ZONES 573/673/5731/6731/5732/6732


48 MO

or 10000 FH

5711 6711

ALL

± 30 Days

NOSE LANDING GEAR AND DOORS/FORWARD FUSELAGE I (NLG BAY AREA)

REFERENCE NUMBER


32-Z711-213-001-A00

ZONES 711/713/714/113/114/115/116


24 MO

or 5000 FH

–

ALL

± 30 Days




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MAIN LANDING GEAR AND DOORS / WING (MLG BAY AREA)

REFERENCE NUMBER


32-Z721-213-001-A00

ZONES 721/731/722/732/532/632


24 MO

or 5000 FH

–

ALL

± 30 Days

MAIN DOOR

REFERENCE NUMBER


52-Z811-213-001-A00

ZONE 811


48 MO or

10000 FH

–

ALL

± 30 Days

52-Z811-214-001-A00

ZONE 811


24 MO or

5000 FH

811AW/ BW/CW/ DW/EW/ FW/GW/ HW/JW/ KW/LW/ MW/NW/ PW/QW/ RW/SW/ TW/UW/

VW

ALL

± 30 Days



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MAIN DOOR (Continued)

REFERENCE NUMBER


52-Z811-214-002-A00

ZONE 811

Internal General Visual Inspection (APPLICABLE FOR SIDE HINGED MAIN DOOR ONLY)

24 MO

or 5000 FH

811AW/ BW/CW/ DW/EW/ FW/GW/ HW/JW/ KW/LW/ MW/NW/ PW/QW/ RW/SW/ TW/UW/

VW

ALL

± 30 Days

ESCAPE HATCH

REFERENCE NUMBER


52-Z812-213-001-A00

ZONES 812/822


96 MO or

20000 FH

–

ALL

± 60 Days

52-Z812-214-001-A00

ZONES 812/822


96 MO or

20000 FH

812AW 822AW

ALL

± 60 Days



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BAGAGGE DOOR

REFERENCE NUMBER


52-Z813-213-001-A00

ZONE 813


48 MO or

10000 FH

–

ALL

± 30 Days

52-Z813-214-001-A00

ZONE 813


24 MO or

5000 FH

813AW

ALL

± 30 Days

SERVICE DOOR

REFERENCE NUMBER


52-Z821-213-001-A00

ZONE 821


48MO or

10000 FH

–

ALL

± 30 Days

52-Z821-214-001-A00

ZONE 821


24 MO or

5000 FH

821AW/ BW/CW

ALL

± 30 Days

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BAGAGGE DOOR

REFERENCE NUMBER


52-Z813-213-001-A00

ZONE 813


48 MO or

10000 FH

–

ALL

± 30 Days

52-Z813-214-001-A00

ZONE 813


24 MO or

5000 FH

813AW

ALL

± 30 Days

SERVICE DOOR

REFERENCE NUMBER


52-Z821-213-001-A00

ZONE 821


48MO or

10000 FH

–

ALL

± 30 Days

52-Z821-214-001-A00

ZONE 821


24 MO or

5000 FH

821AW/ BW/CW

ALL

± 30 Days



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SECTION 6

NATIONAL REQUIREMENTS

7.B.1 List of Scheduled EASA System Maintenance Requirements Presentation.

These following tasks are specific for EASA Inspection Requirements.

REFERENCE NUMBER TYPE CAT DESCRIPTION INT EFFECT TOLERANCE

27-21-00-710-001-A00 OPC 7 Operationally Check Rudder Movable Primary StopMechanism

48 MO or

5000 FH

ALL ± 30 Days

27-22-00-720-002-A00 FNC 9 Functionally Check Rudder Hydraulic Damping (*) NOTE: Or in accordance with Local Regulatory


12 MO or

1500 FH

ALL ± 15 Days

27-23-00-710-002-A00 OPC 9 Operationally Check Alerting Light of the Rudder MovablePrimary Stop

24 MO or

2500 FH

ALL ± 30 Days

33-12-00-710-002-A00 OPC 9 Operationally Check Pushbutton Lighting 1000 FH ALL Not Applicable

76-11-04-720-001-A00 FNC 9 Functionally Check Friction Lock Assembly for Pre-LoadValue

24 MO or

2500 FH

ALL ± 30 Days




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7.B.2 List of Scheduled EASA Structural Maintenance Requirements Presentation.

These following tasks are specific for EASA Inspection Requirements.

REFERENCE NUMBER TYPE DESCRIPTION INT ZONE EFFECT TOLERANCE

57-61-00-220-805-A00 DET Internally inspect the AILERON components: • Aileron Actuator fittings (SSI 57-61-12)

48 MO or

5000 FC

573/673 ALL ± 30 Days

7.C.1 List of Scheduled CAAC System Maintenance Requirements Presentation.

These following tasks are specific for CAAC Inspection Requirements.

REFERENCE NUMBER TYPE CAT DESCRIPTION INT EFFECT TOLERANCE

25-63-00-710-001-A00 OPC 8 Operationally Check Portable Emergency LocatorTransmitter System (if installed).

NOTE: Or in accordance with Local Regulatory AuthorityRequirements


25-63-02-960-001-A00 DIS 8 Discard Portable ELT Battery ELTA P/N 05N62123 NOTE: Portable ELT Battery change in accordance with

manufacturer data plate expiration date or local Regulatory Authority Requirements





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APPENDIX 1

CERTIFICATION MAINTENANCE REQUIREMENTS

A1.2 LIST OF CMR’S APPLICABLE TO AIRCRAFT UNDER ANAC/FAA CERTIFICATIONS


REFERENCE NUMBER

TYPE

CAT DESCRIPTION LU INT EFFECT TOLERANCE

27-12-00-720-003-A00 FNC (*) Functionally Check External Leakage of Aileron HydraulicActuator Pre-Mod. SB 145-27-0063

12 MO or

1500 FH

EMB-135 (ALL)

± 15 Days

27-12-00-720-003-A01 FNC (*) Functionally Check External Leakage of Aileron HydraulicActuator Post-Mod. SB 145-27-0063

24 MO or

2500 FH

EMB-135 (ALL)

± 30 Days

27-12-01-212-002-A00 GVI (*) Inspect (Visually Inspect) Aileron PCA Rod Ends/FittingLugs for Integrity and General Condition Pre-Mod. SB 145-27-0063

6 MO or

500 FH

EMB-135 (ALL)

± 15 Days

27-12-01-212-002-A01 GVI (*) Inspect (Visually Inspect) Aileron PCA Rod Ends/FittingLugs for Integrity and General Condition Post-Mod. SB 145-27-0063

24 MO or

1000 FH

EMB-135 (ALL)

± 30 Days

27-12-01-720-001-A00 FNC (*) Functionally Check Aileron Actuator Damping Components and Monitoring Devices Post-Mod. SB 145-27-0062 and Pre-Mod. SB 145-27-0063

6 MO or

500 FH

EMB-135 (ALL)

± 15 Days

27-12-01-720-001-A01 FNC (*) Functionally Check Aileron Actuator Damping Components and Monitoring Devices Post-Mod. SB 145-27-0062 and Post-Mod. SB 145-27-0063

12 MO or

2500 FH

EMB-135 (ALL)

± 15 Days



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27-12-03-212-001-A00 VCK (*) Inspect (Visual Inspection) Aileron Damper Rod Ends/FittingLugs for Integrity and General Condition Post-Mod. SB 145-27-0063

18 MO or

1000 FH

EMB-135 (ALL)

± 15 Days

27-12-03-720-001-A00 FNC (*) Functionally Check Aileron Damper Damping Force Post- Mod. SB 145-27-0063

24 MO or

2500 FH

EMB-135 (ALL)

± 30 Days

27-12-03-720-002-A00 FNC (*) Functionally Check External Leakage of Aileron DamperPost-Mod. SB 145-27-0063

24 MO or

2500 FH

EMB-135 (ALL)

± 30 Days

27-25-00-710-001-A00 OPC (*) Operationally Check Rudder Pedals Auto Shutoff andRudder Manual Shutoff Functions

12 MO or

2500 FH

ALL ± 15 Days

27-31-05-220-001-A00 DVI (*) Inspect (Detailed Inspection) Servo Tab Failsafe ActuationLink

48 MO or

5000 FH

ALL ± 30 Days

27-62-00-720-001-A00 FNC (*) Functionally Check G. Spoiler/Speed Brake Valves, ControlCircuit and Associated Messages

72 MO or

10000 FH

ALL ± 30 Days



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30-11-00-720-001-A00 FNC (*) Functionally Check Pressure Sensors of the Wing ThermalAnti-Icing System (Bench Test)

48 MO or

5000 FH

ALL ± 30 Days

30-12-00-720-001-A00 FNC (*) Functionally Check Pressure Sensors of the Horizontal Sta- bilizer Thermal Anti-Icing System (Bench Test)

48 MO or

5000 FH

ALL ± 30 Days

30-21-00-720-001-A00 FNC (*) Functionally Check Pressure Sensors of the Engine Ther- mal Anti-Icing System (Bench Test)

48 MO or

5000 FH

ALL ± 30 Days



32-63-00-710-001-A00 OPC (*) Operationally Check Air/Ground System 6 MO or

500 FH

ALL ± 15 Days



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78-33-00-710-001-A00 OPC (*) Operationally Check Air/Ground Input Signal to ThrustReverser System

6 MO or

1000 FH

ALL ± 15 Days

78-33-00-710-002-A00 OPC (*) Operationally Check Wheel Speed Input Signal to ThrustReverser System

6 MO or

1000 FH

ALL ± 15 Days

78-33-01-710-001-A00 OPC (*) Operationally Check Isolation Control Unit 6 MO or

1000 FH

ALL ± 15 Days

78-34-00-710-001-A00 OPC (*) Operationally Check Thrust Reverser Indicating System 72 MO or

10000 FH

ALL ± 30 Days



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27-12-00-720-003-A02 FNC (*) Functionally Check External Leakage of Aileron HydraulicActuator

24 MO or

1000 FH

EMB-135 (ALL)

± 30 Days

27-12-01-212-002-A02 GVI (*) Inspect (Visual Inspection) Aileron PCA Rod Ends/FittingLugs for Integrity and General Condition.

48 MO or

1000 FH

EMB-135 (ALL)

± 30 Days

27-12-01-720-001-A02 FNC (*) Functionally Check Aileron Actuator Damping Components and Monitoring Devices Post-Mod. SB 145-27-0062

12 MO or

1000 FH

EMB-135 (ALL)

± 15 Days

27-12-01-720-002-A00 FNC (*) Functionally Check Aileron Actuator Force Fight Post-Mod. SB 145-27-0062

24 MO or

1000 FH

EMB-135 (ALL)

± 30 Days

27-25-00-710-001-A00 OPC (*) Operationally Check Rudder Pedals Auto Shutoff andRudder Manual Shutoff Functions

24 MO or

2500 FH

ALL ± 30 Days

27-31-05-220-001-A00 DVI (*) Inspect (Detailed Inspection) Servo Tab Failsafe ActuationLink

48 MO or

5000 FH

ALL ± 30 Days

27-62-00-720-001-A00 FNC (*) Functionally Check G. Spoiler/Speed Brake Valves, ControlCircuit and Associated Messages

96 MO or

10000 FH

ALL ± 60 Days

A1.3 LIST OF CMR’S APPLICABLE TO AIRCRAFT UNDER EASA CERTIFICATION




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CHAPTER 30 – ICEAND RAIN PROTECTION


30-11-00-720-001-A00 FNC (*) Functionally Check Pressure Sensors of the Wing ThermalAnti-Icing System (Bench Test)

48 MO or

5000 FH

ALL ± 30 Days

30-12-00-720-001-A00 FNC (*) Functionally Check Pressure Sensors of the Horizontal Sta- bilizer Thermal Anti-Icing System (Bench Test)

48 MO or

5000 FH

ALL ± 30 Days

30-21-00-720-001-A00 FNC (*) Functionally Check Pressure Sensors of the Engine Ther- mal Anti-Icing System (Bench Test)

48 MO or

5000 FH

ALL ± 30 Days



32-63-00-710-001-A00 OPC (*) Operationally Check Air/Ground System 6 MO or

500 FH

ALL ± 15 Days



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78-33-00-710-001-A00 OPC (*) Operationally Check Air/Ground Input Signal to ThrustReverser System

12 MO or

1000 FH

ALL ± 15 Days

78-33-00-710-002-A00 OPC (*) Operationally Check Wheel Speed Input Signal to ThrustReverser System

12 MO or

1000 FH

ALL ± 15 Days

78-33-01-710-001-A00 OPC (*) Operationally Check Isolation Control Unit 12 MO or

1000 FH

ALL ± 15 Days

78-34-00-710-001-A00 OPC (*) Operationally Check Thrust Reverser Indicating System 72 MO or

10000 FH

ALL ± 30 Days



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APPENDIX 2

AIRWORTHINESS LIMITATION REQUIREMENTS (ALIS)

REFERENCE NUMBER TYPE DESCRIPTION LU INT EFFECT TOLERANCE

28-11-00-720-001-A00 FNC Functionally Check critical bonding integrity of selected conduits inside the wing tank, Fuel Pump and FQIS connectors at tank wall by conductivity measurements


28-21-01-220-001-A00 DET Inspect Electric Fuel Pump Connector 10000 FH ALL Not Applicable

28-23-03-220-001-A00 DET Inspect Pilot Valve harness inside the conduit 20000 FH ALL Not Applicable

28-23-04-220-001-A00 DET Inspect Vent Valve harness inside the conduit 20000 FH ALL Not Applicable

28-41-01-720-001-A01

FNC

Functional Check of the Safe Life Features of the FuelConditioning Unit (FCU):

• Initial Functional Check;

• External Visual Inspection;

• Internal Visual Inspection;

• Functional Check of the Safe-Life Feature;

• Final Functional Check. NOTE: The flight hours accumulated shall be based on the fuel conditioning unit component


28-41-03-220-001-A00 DET Inspect FQIS harness for clamp and wire jacket integrity 20000 FH ALL Not Applicable

FUEL SYSTEM LIMITATIONS (FSL)



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REFERENCE NUMBER TYPE DESCRIPTION THRESHOLD (Flight Cycles)

INT ZONE EFFECTIVITY

53-12-00-210-802-A00 GVI Internally insect the FUSELAGE components:

Windshield lateral post and its attachment (SSI 53-10-20)

NOTE: Applicable to aircraft Post-Mod.

SB 145-53-0079

22060 22060 FC 223 ALL

53-12-00-250-802-A00 SDE Externally insect the FUSELAGE componentsusing Eddy Current method:


NOTE: Applicable to aircraft Pre-Mod.

SB 145-53-0079

11590 11590 FC 223 ALL

53-12-00-250-802-A01 SDE Externally insect the FUSELAGE componentsusing Eddy Current method:



SB 145-53-0079

22060 22060 FC 223 ALL

53-12-00-250-803-A00 SDE Internally insect the FUSELAGE components using Eddy Current method:



SB 145-53-0079

11590 11590 FC 223 ALL

CHAPTER 53 - FUSELAGE



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53-31-00-250-801-A00 SDE Externally insect the FUSELAGE components using Eddy Current method:

Fuselage skin panel at stringers, frames/ bulkheads, and splices (SSI 53-30-07)


SB 145-53-0080

- 6000 FC 273/274 ALL

53-31-00-250-802-A00 SDE Externally insect the FUSELAGE components using Eddy Current method:



SB 145-53-0080

- 20000 FC 273/274 ALL

53-31-00-210-824-A00 GVI Externally insect the FUSELAGE components:



SB 145 53 0081

- 9000 FC 311/312 ALL

53-31-00-210-825-A00 GVI Externally insect the FUSELAGE components:



- 20000 FC 311/312 ALL




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54-50-00-220-812-A00 DET Internally insect the PYLON components:

Pylon Yokes I and II (SSI 54-50-05)


SB 145-54-0011 or Pre-Mod. SB 145-54-0013

20000 20000 FC 414/424 EMB-145MPEMB-135LR




SB 145-54-0011 and Post-Mod. SB 145-54-0013

30000 30000 FC 414/424 ALL




SB 145-54-0013.

20000 20000 FC 414/424 EMB-145XR




SB 145-54-0013.

30000 30000 FC 414/424 EMB-145XR



57-28-00-220-817-A00 DET Externally inspect the WING components:

Attachment lugs aileron (SSI 57-28-66)

- 8895 FC 551/651 EMB-135LR

57-28-00-220-817-A00 DET Externally inspect the AILERON components:

Hinge attachment, aileron (SSI 57-61-89)

- 5356 FC 573/673 EMB-135LR





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APPENDIX 3

CAT II MAINTENANCE REQUIREMENTS


22-11-00-720-003-A00 FNC 8 Functionally Check Category II Monitoring Function 24 MO or 80 FH ALL ± 30 Days

30-41-00-710-001-A00 OPC 9 Operationally Check Windshield Wiper

NOTE 1: Applicable to all aircraft under FAA Certifications

NOTE 2: Applicable to aircraft under ANAC/EASA Certification, If installed

48 MO or

5000 FH

ALL ± 30 Days

30-42-00-710-001-A00 OPC 9 Operationally Check Windshield Heating 48 MO or 5000 FH ALL ± 30 Days

34-01-00-720-001-A00 FNC 8 Functionally Check Integrated Standby Instrument - ISIS NOTE: Or in accordance with Local Regulatory Authority

Requirements


34-11-00-720-001-A00 FNC 6 Functionally Check Standby Altimeter Indicator NOTE: Or in accordance with Local Regulatory Authority

Requirements

24 MO or

5000 FH

ALL Not Applicable

34-12-00-720-001-A00 FNC 6 Functionally Check Standby Airspeed Indicator NOTE: Or in accordance with Local Regulatory Authority

Requirements

24 MO or

5000 FH

ALL Not Applicable

34-13-00-790-001-A00 FNC 6 Functionally Check Pitot Static System for Leakage 5000 FH ALL Not Applicable

34-15-00-720-001-A00 FNC 8 Functionally Check ADC System NOTE: Or 1YE, whichever occurs first


34-24-00-710-001-A00 OPC 6 Operationally Check Standby Attitude Indicator 24 MO Or 5000 FH

ALL ± 30 Days

34-41-00-710-001-A00 OPC 9 Operationally Check GPWS/WINDSHEAR 24 MO Or 5000 FH

ALL ± 30 Days

34-41-00-710-003-A00 OPC 9 Operationally Check EGPWS/WINDSHEAR 48 MO Or 5000 FH

ALL ± 30 Days



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APPENDIX 4 RVSM MAINTENANCE REQUIREMENTS

REERENCE NUMBER TYPE CAT DESCRIPTION LU INT EFFECT TOLERANCE

22-11-00-720-004-A00 FNC 6 Functionally Check AFCS Altitude Hold Mode and Alti- tude Pre-Select Mode

48 MO or

4000 FH

ALL ± 30 Days

34-13-04-280-001-A00 SDI 6 Inspect (Special Inspection) RVSM Critical Region (Skin) for Waviness (aircraft identified in and have not accomplished SB 145-34-0110)


34-13-04-280-001-A01 SDI 6 Inspect (Special Inspection) RVSM Critical Region (Skin) for Waviness (including aircraft identified in and are Post-Mod SB 145-34-0110)

48 MO or

5000 FH

ALL ± 30 Days

34-13-04-280-002-A00 SDI 6 Inspect (Special Inspection) Static Port Surrounding Plate for Flushness and Integrity (aircraft identified in and have not accomplished SB 145-34-0110)


34-13-04-280-002-A01 SDI 6 Inspect (Special Inspection) Static Port Surrounding Plate for Flushness and Integrity (including aircraft iden-tified in and are Post-Mod SB 145-34-0110)

48 MO or

5000 FH

ALL ± 30 Days

34-13-04-280-003-A00 SDI 6 Inspect (Special Inspection) Passenger Gaseous Oxy-gen Service Panel (panel P/N 145-51705-001, attached by livelock stud xnut) installed in RVSM Critical Region for Flushness and Integrity (aircraft identified in and have not accomplished SB 145-34-0110)


34-13-04-280-003-A01 SDI 6 Inspect (Special Inspection) Passenger Gaseous Oxy-gen Service Panel (panel P/N 145-51705-001, attached by livelock stud xnut) installed in RVSM Critical Region for Flushness and Integrity (including aircraft identified in and are Post-Mod SB 145-34-0110)

48 MO or

5000 FH

ALL ± 30 Days



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APPENDIX 5 CAT III MAINTENANCE REQUIREMENTS


34-23-05-710-001-A00 OPC 9 Operationally Check HGS Computer Fan 24 MO or

4000 FH

ALL ± 30 Days

34-26-03-140-001-A00 RST 6 Clean Single IRU Mounting Tray Fan Filter (SingleIRS System only)


34-32-03-212-001-A00 GVI 6 Inspect (General Visual) VOR/LOC Antenna 24 MO or

4000 FH

ALL ± 30 Days



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EMBRAER RECOMMENDED MAINTENANCE TASKS

CHAPTER 12 – SERVICING


12-15-02-610-001-A00 SVC Sterilize Water Reservoir 24 MO or

5000 FH

ALL ± 30 Days

CHAPTER 21 – AIR CONDITIONING


21-23-05-710-001-A00 OPC Operationally Check Toilet Gasper Hose Filter (if installed) (*) NOTE: Initial inspection since new, "48 MO or 5000 FH" check.

24 MOor

2500 FH

ALL ± 30 Days

21-25-01-211-001-A00 VCK Visually Check Ram Air Flap Valve 1000 FH ALL Not Applicable

21-51-02-170-002-A00 RST Clean Dual Heat Exchanger on the Aircraft 1500 FH ALL Not Applicable

21-51-13-211-001-A00 VCK Visually Check Water Spray Nozzles 6 MO or

500 FH

ALL ± 15 Days

21-60-08-960-001-A00 DIS Replace Torque Motor Dual Valve Air Filter Element Post-Mod. SB145-21-0039

48 MOor

5000 FH

ALL ± 30 Days



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CHAPTER 23 – COMMUNICATIONS


23-12-04-212-001-A00 GVI Visual Inspection of the VHF Antenna 48 MO or

5000 FH

ALL ± 30 Days

23-31-00-710-002-A00 OPC Operationally Check Back-up/Emergency Cabin Interphone System 48 MO or

5000 FH

ALL ± 30 Days

23-31-00-710-003-A00 OPC Operationally Check Loudspeakers 48 MO or

5000 FH

ALL ± 30 Days

CHAPTER 24 – ELECTRICAL POWER


24-34-01-900-002-A00 RST Restore APU Starter Generator 48 MO or

800 AH

ALL ± 30 Days

CHAPTER 25 – EQUIPMENT/FURNISHINGS


25-40-01-220-001-A00 DET Inspect (Detailed Inspection) Lavatory Waste Disposal Door 6 MO or

500 FH

ALL ± 15 Days



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35-10-00-910-001-A00 FNC Leak Test Crew Oxygen System Lines (*) NOTE: Together with MRBR Task 35-10-07-720-002-A00

(*) ALL ± 30 Days



52-31-00-710-001-A00 OPC Operational Check Baggage Door Actuating and Locking Mecha- nism

18 MO or

2500 FH

ALL ± 15 Days



53-04-02-212-001-A00 GVI Inspect (Visual Inspection) the Naca-Air-Intake at Forward Wing- To-Fuselage Fairing Polyurethane Film for Integrity NOTE: Zone 191.

24 MO or

2500 FH

ALL ± 30 Days

53-11-01-220-001-A00 DVI Inspect (Detailed Inspection) the Presence of Water on theRadome

48 MO or

5000 FH

ALL ± 30 Days

53-11-05-212-001-A00 GVI Inspect (Visual Inspection) the Radome Poleyurethane Film 500 FH ALL Not Applicable

53-11-06-212-001-A00 GVI Inspect (Visual Inspection) the Naca-Air-Intake at Forward Fuselage I Polyurethane Film for Integrity NOTE: Zones 113 and 114

24 MO or

2500 FH

ALL ± 30 Days



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CHAPTER 55 – STABILIZERS


55-10-00-212-001-A00 GVI Inspect (Visual Inspection) the Horizontal Stabilizer Leading-Edge Root-Fairing and Horizontal Stabilizer-Tip Polyurethane Film for Integrity NOTE: Zones 333 and 334

24 MO or

2500 FH

ALL ± 30 Days

55-30-00-212-001-A00 GVI Inspect (Visual Inspection) the Vertical Stabilizer Leading-EdgePolyurethane Film for Integrity NOTE: Zone 323

24 MO or

2500 FH

ALL ± 30 Days

CHAPTER 56 – WINDOWS


56-10-01-720-001-A00 FNC Functionally Check Torque of Windshield Attaching Bolts Pre- Mod. SB 145-56-0006

24 MO or

2500 FH

ALL ± 30 Days

56-10-01-720-001-A01 FNC Functionally Check Torque of Windshield Attaching Bolts Post- Mod. SB 145-56-0006 NOTE: First check at 500 FH after windshield installation

72 MO or

10000 FH

ALL ± 30 Days

56-10-01-720-002-A00 FNC Functionally Check Windshield Anti-Static Coating for Continuity 72 MO or

10000 FH

ALL ± 30 Days

56-20-01-220-001-A00 DVI Inspect (Detailed Inspection) Passenger Cabin Windows forDelamination except P/N P03014-1

48 MO or

5000 FH

ALL ± 30 Days



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57-43-00-212-001-A00 GVI Inspection (Visual Inspect) the Wing-Tip Polyurethane Film forIntegrity NOTE: Zones 561 and 661.

24 MO or

2500 FH

ALL ± 30 Days

CHAPTER 76 – ENGINE CONTROLS


76-12-01-212-001-A00 GVI Inspect (Visual Inspection) Resolver Attachments to the ThrustLevers

96 MO or

10000 FH

ALL ± 60 Days

Recommended Tasks Prior to the Winter

REFERENCE NUMBER TYPE DESCRIPTION EFFECT TOLERANCE

30-11-05-710-001-A00 OPC Operationally Check Wing Leak Thermostat ALL Not Applicable

30-12-00-710-001-A00 OPC Operationally Check Electrical Hardware of the Horizontal StabilizerThermal Anti-icing System

ALL Not Applicable

30-12-05-710-001-A00 OPC Operationally Check Horizontal Stabilizer Leak Thermostat ALL Not Applicable

30-20-00-220-001-A00 DET Inspect (Detailed Inspection) Thermal Anti-ice (TAI) Exhaust Duct forCondition and Security of Installation

ALL Not Applicable

30-20-01-720-001-A00 FNC Functionally Check Thermal Anti-ice (Tai) Inter bulkhead Assembly forLeakage

ALL Not Applicable



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REFERENCE NUMBER TYPE DESCRIPTION EFFECT TOLERANCE

30-31-00-710-002-A00 OPC Operationally Check Pressurization Static Port Heating ALL Not Applicable

30-42-00-710-001-A00 OPC Operationally Check Windshield Heating ALL Not Applicable

52-21-00-710-001-A00 OPC Operationally Check Passenger Cabin Escape Hatch Mechanism ALL Not Applicable



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III.5 EMBRAER STRUCTURED MAINTENANCE PROGRAM

INTRODUCTION

The Embraer Structured Maintenance Program consists of a simplified method to comply with all the maintenance requirements defined in the SMRD 1137 (Scheduled Maintenance Requirements Document) Part I and Part II. The requirements from the SMRD Part I (MRBR 1150) Appendix A2 (Airworthiness Limitations Requirements) item A2.2 (Life Limited Components) and the requirements from the SMRD Part II (SMRD 1137) Section VII (Embraer – Optional Tasks) are the only exceptions, being not covered by this program and requiring a separate control. Operators are not obligated to follow Embraer Structured Maintenance Program since it is a suggestion to maximize the aircraft availability, reduce the number of different maintenance packages and improve operators maintenance planning. If the operators choose not to use the Structured Maintenance Program totally or partially, they must obey the maximum allowable intervals and tolerances of each maintenance requirement (item VI.4 of this section). The Structured Maintenance Program was developed considering one (1) pre-defined operational profile. The pre-defined operational profile covers aircraft operating up to the values stated in the table below. There are two annual limitations (Flight Hours and Flight Cycles) and one quarterly limitation (Flight Hours) to be followed. It is mandatory that the aircraft does not exceed the annual limitations defined for each profile prior to one year and the quarterly limitation prior to three (3) consecutive months. If one of the limitations from the table below is exceeded, the Structured Maintenance Program is no longer valid and the operator shall contact EMBRAER for support. See the limitations on the table below

Limitations (Up to) P1

Annual 600 FC

900 FH

Quarterly 225 FH MAIN PACKAGES

The S M R D t a s k s w e r e g r o u p e d i n t o m a j o r p a c k a g e s t o b e performed as follows: 48 HOURS TASKS - Each consecutive 48 hours; S1 – Each one (1) month; S3 – Each three (3) months; S6 – Each six (6) months; S12 – Each twelve (12) months; S18 – Each eighteen (18) months; S24 – Each twenty four (24) months; S36 – Each thirty six (36) months; S48 – Each forty eight (48) months; S60 – Each sixty (60) months; S72 – Each seventy two (72) months; S96 – Each ninety six (96) months; S120 – Each one hundred and twenty (120) months; S144 – Each one hundred and forty four (144) months; S192 – Each one hundred and ninety two (192) months; ROUTINE – Each 100FH or 14 Days (Whichever occurs first); PRIOR WINTER – Before the winter season.

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TASKS CONTROLLED BY THE COMPONENT LIFE

The maintenance requirements identified as Component Limited Tasks must be controlled according to each component life (this chapter includes APU tasks and also tasks with specific intervals such as "Each Tire Change" and "Each Brake Replacement"). These tasks require a separate control by the operators since the component life is not necessarily the same as the aircraft life. All tasks NOT identified as Component Limited Tasks must be controlled according to the aircraft life.

TOLERANCE APPLICATION

The SMRD tasks listed in the Structured Maintenance Program have tolerances applied according to the rules stated on item VI.3 (Flexible Maintenance Program) except for the tolerance values applied to each requirement. For those following the Structured Maintenance Program, all the tasks with tolerance applied have only one tolerance value (15 Days). The tolerance value of each maintenance requirement can be found together with each requirement interval.

PLANNING INSTRUCTION

The operator shall plan the aircraft major maintenance stoppages (from S1 to S192) as follows: - Verify the aircraft current operational life (in months); - Based on this information, perform the packages that are multiple of the aircraft operational life; Besides the packages listed above, it is also necessary to perform those tasks that require a separate control, as defined in the paragraphs above as the SMRD Part I (MRBR 1150) Appendix A2 (Airworthiness Limitation Requirements).

EXAMPLE 01:

For an aircraft with 47 months of operational life, the operator shall perform all major packages that are multiple of 47 months. Based on the major packages (from S1 to S192) definition, it means the operator shall perform the package S1 (each month) at this time. EXAMPLE 02:

For an aircraft with 48 months of operational life, the operator shall perform all major packages that are multiple of 48 months. Based on the major packages (from S1 to S192) definition, it means the operator shall perform the packages S1 (each month), S2 (each two months), S3 (each three months), S6 (each six months), S12 (each twelve months), S24 (each twenty four months) and S48 (each forty eight months) at this time. III-3.5. COMPONENT LIMITED REQUIREMENTS The Structured Maintenance Program contains a list of maintenance requirements which intervals are based on each component life. These requirements require a separate control by the operators since the component life is not the same as the aircraft life. These requirements intervals and tolerances are the same as the intervals and tolerances defined in the MPG 1483 and follow the rules defined in the MPG Sections 01 and 03.




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The following figure illustrates the examples above: MAINTENANCE REQUIREMENTS PRESENTATION

The maintenance requirements presentation follows the same rule as the MRBR 1150 and SMRD 1137. The maintenance requirements are organized by the tasks intervals and than by SMRD 1137 sections and appendixes. Each requirement contains the following information:

TASK NUMBER

SMRD SECTION

TASK DESCRIPTIION EFFECTIVITY MECH. SIGN INSP. SIGN.

a b c d e f

a – TASK NUMBER - Numbering as defined in 1.8 b – SMRD SECTION - SMRD sections as per MRBr-1150 and SMRD-1137 documents c – TASK DESCRIPTION - Description of the task to be performed d – EFFECTIVITY - Task effectivity as defined in 1.9 e – MECH. SIGN. - Reserved for Mechanics signature for customers using these forms for recording maintenance. f – INSP. SIGN. - Reserved for Inspectors signature for customers using these forms for recording maintenance.

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The Component Limited Tasks contain the following information:

TASK NUMBER

SMRD SECTION

TASK DESCRIPTIION EFFECTIVITY INT TOLERANCE MECH. SIGN. INSP. SIGN.

a b c d e f g h

a – TASK NUMBER - Numbering as defined in 1.8 b – SMRD SECTION - SMRD sections as per MRBr-1150 and SMRD-1137 documents c – TASK DESCRIPTION - Description of the task to be performed d – EFFECTIVITY - Task effectivity as defined in 1.9 e – INT - Interval as defined in 3.3 f – TOLERANCE - Task tolerance as defined in VI.3. g – MECH. SIGN. - Reserved for Mechanics signature for customers using these forms for recording maintenance. h – INSP. SIGN. - Reserved for Inspectors signature for customers using these forms for recording maintenance.



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Engine Model: Aircraft Model: APU Model: Engine 1 Serial Number:

Engine 2 Serial Number:

Hours:

Hours:

Cycles:

Cycles:

Aircraft Serial Number:Aircraft Hours: Aircraft Landings:

APU Serial Number:APU Hours: APU Cycles:

48 HOURS TASKS: To be performed at every 48 Hours. Package Performed in: / / Tolerance is Not Applicable

TASK NUMBER SMRD SECTION

TASK DESCRIPTION EFFECTIVITY MECH. SIGN. INSP. SIGN.

32-49-01-610-001-A00 SYSTEM Check MLG Tire Inflation Pressure ALL

32-49-04-610-001-A00 SYSTEM Check NLG Tire Inflation Pressure ALL



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ROUTINE TASKS: To be performed at every 14 Days or 100 Flight Hours (whichever occurs first). Package Performed in: / / Tolerance is Not Applicable



12-11-03-680-001-A00 ROUTINE Drain Fuel Tanks to Check for the Presence of Water ALL

12-13-01-610-001-A00 ROUTINE Hydraulic System Reservoir Fluid Level Check ALL

26-14-00-710-001-A00 ROUTINE Operationally Check Lavatory Smoke Detection System ALL

26-15-00-710-001-A00 ROUTINE Operationally Check Baggage Smoke Detection System

(Class "D" Baggage Compartment only)

ALL

27-12-01-212-002-A03 ROUTINE Inspect (Visually Inspect) Aileron PCA Rod Ends/Fitting Lugs

For Integrity and General Condition PCA P/N 394900-1007

EMB-145 (ALL)

27-12-01-212-002-A04 SYSTEM Inspect (Visual Inspection) Aileron PCA Rod Ends/Fitting Lugs

for Integrity and General Condition for aircraft Equipped with

PCA P/N 394900-1003 or P/N 394900-1005

EMB-145 (ALL)

28-11-00-212-001-A00 ROUTINE Visually Check Underwing Surfaces Tank Access Panels

Dump Valves and Drain Valves for Absence of Fuel Leakage

ALL

28-12-03-212-001-A00 ROUTINE Visually Check NACA Air Inlet for Absence of Obstruction ALL

28-20-00-212-001-A00 ROUTINE Visually Check Fuel Line Shroud Drains for Absence of Fuel

Leakage

ALL

29-10-04-710-001-A00 ROUTINE Operationally Check Electric Motor-Driven Pump (EMDP) in

AUTO and ON modes

ALL

30-00-00-710-001-A00 ROUTINE Operationally Check Anti-Icing System Messages ALL

32-10-00-211-001-A00 ROUTINE Visually Check Main Landing Gear Including Doors and Spring

Cartridges

ALL

32-10-02-211-001-A00 ROUTINE Visually Check MLG Shock Absorber Extension ALL

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32-20-01-211-001-A00 ROUTINE Visually Check Nose Landing Gear and Spring Cartridges for

Condition and Shock Absorber Extension

ALL

32-33-15-720-001-A00 ROUTINE Functionally Check Landing Gear Accumulator Nitrogen Pre-

Charge (Side Hinged Main Door Model only)

ALL

32-44-02-610-001-A00 ROUTINE Parking/Emerg Brake Nitrogen Accumulator Pressure Charge ALL

32-49-01-212-001-A00 ROUTINE Inspect (Visual Inspection) MLG Tires for Wear and General

Condition

ALL

32-49-02-212-001-A00 ROUTINE Inspect (Visual Inspection) MLG Wheel Assembly ALL

32-49-03-212-001-A00 ROUTINE Inspect (Visual Inspection) Brake Assembly for General Con-

dition

ALL

32-49-04-212-001-A00 ROUTINE Inspect (Visual Inspection) NLG Tires for Wear and General

Condition

ALL

32-49-05-212-001-A00 ROUTINE Inspect (Visual Inspection) NLG Wheel Assembly ALL

34-13-00-212-001-A00 ROUTINE Inspect (Visual Inspection) Pitot/Static Ports for Absence of

Foreign Matter

ALL

35-10-00-211-001-A00 ROUTINE Check Crew Oxygen Pressure ALL

35-11-03-211-001-A00 ROUTINE Visually Check Oxygen Cylinder Pressure Relief Disc ALL

49-11-01-212-001-A00 ROUTINE Inspect (Visual Inspection) APU and Starter Generator Air

Intake and Exhaust Ducts for Foreign Material or Obstruction

ALL

71-12-01-212-002-A00 ROUTINE Inspect (Visual Inspection) Engine and Generator Cooling Air

Inlets/Outlets for Absence of Foreign Matter

ALL



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Hours:

Cycles:

Cycles:






72-00-00-970-001-A00 ROUTINE Engine Trend Download/Analysis

NOTE: Or 75 FC whichever occurs first.

ALL

79-34-00-212-001-A00 SYSTEM Inspect Multi-Function Display for ENG1(2) OIL DEBRIS

Maintenance Message (Except for aircraft equipped with

AE3007 A1E Engine)

NOTE: This task is applicable to aircraft Pre-Mod. SB 145-79-

001 or Post-Mod SB 145-79-002 and Pre-Mod. SB 145-79-

003.

EMB-145MP

EMB-135LR



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S1 TASKS: To be performed at every 1 Month. Package Performed in: / / Tolerance is Not Applicable



26-24-00-211-001-A00 SYSTEM Visually Check Portable Fire Extinguishers NOTE: Or in accordance with Local Regulatory Authority Requirements.

ALL


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S3 TASKS TOLERANCE EQUAL TO ± 15 Days


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S3 TASKS: To be performed at every 3 Months. Package Performed in: / / Tolerance equal to ± 15 Days.



21-31-04-140-001-A01 SYSTEM Clean Pneumatic Outflow Valve (Smoking Flights) ALL

27-12-00-720-002-A00 SYSTEM Functionally Check Aileron Hydraulic Damping Pre-Mod. S.B.

145-27-0062

EMB-145 (ALL)

27-36-00-710-001-A00 SYSTEM Operationally Check Stall Protection System ALL

27-36-00-720-001-A00 SYSTEM Functionally Check ICE/SPS Speeds Interface Circuit ALL

32-34-00-640-001-A00 SYSTEM Lubricate Landing Gear (MLG & NLG) and Steering System ALL

33-50-00-710-001-A00 SYSTEM Operationally Check Emergency Lighting System ALL




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Hours:

Cycles:

Cycles:



S3 TASKS: To be performed at every 3 Months. Package Performed in: / / Tolerance is Not Applicable



26-15-00-720-001-A00 SYSTEM Functionally Check JAMCO Baggage Compartment Smoke Detection System (actuating each Smoke Sensor in the Bag- gage Compartment with a Smoke Tester).

ALL

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TASK NUMBER SMRD SECTION TASK DESCRIPTION EFFECTIVITY MECH. SIGN. INSP. SIGN.

21-51-13-211-001-A00 EMB-RECOMM Visually Check Water Spray Nozzles ALL

22-11-00-720-003-A00 CAT II Functionally Check Category II Monitoring Function ALL

24-35-01-720-001-A00 SYSTEM Functionally Check Back-up Battery ALL

25-11-01-140-001-A00 SYSTEM Clean Flight Crew Seats Locking System ALL

25-40-01-220-001-A00 EMB-RECOMM Inspect (Detailed Inspection) Lavatory Waste Disposal

Door

ALL

25-60-04-710-001-A00 SYSTEM Operationally Check Megaphone P/N ACR/EM-1A ALL

27-12-01-212-002-A00 CMR/ANAC-FAA Inspect (Visually Inspect) Aileron PCA Rod Ends/Fitting

Lugs for Integrity and General Condition Pre-Mod. SB

145-27-0063

EMB-135 (ALL)

27-12-01-212-002-A05 SYSTEM Inspect (Visual Inspection) Aileron PCA Rod Ends/Fitting

Lugs for Integrity and General Condition Post-Mod. SB

145-27-0061 and Post-Mod. SB 145-27-0062 and Post-

Mod. SB 145-57-0019 and Pre-Mod. SB 145-27-0063

EMB-145 (ALL)

27-12-01-720-001-A00 CMR/ANAC-FAA Functionally Check Aileron Actuator Damping Compo-

nents and Monitoring Devices Post-Mod. SB 145-27-

0062 and Pre-Mod. SB 145-27-0063

EMB-135 (ALL)

27-12-01-720-001-A03 SYSTEM Functionally Check Aileron Actuator Damping Compo-


0062 and Pre-Mod. SB 145-27-0063 for aircraft Certifi-

cated Under ANAC/FAA Regulations

EMB-145 (ALL)

27-31-04-710-001-A00 SYSTEM Operationally Check Spring/Servo Tab ALL



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27-51-00-640-001-A00 SYSTEM Lubricate Flap Screw-Jack Actuators (FSAs) ALL

27-53-00-710-001-A00 SYSTEM Operationally Check FLAP FAIL Message ALL

27-53-00-710-002-A00 SYSTEM Operationally Check of Take-off Flap Aural Warning and

No Take-off Configuration Visual Warning

ALL

27-71-00-710-003-A00 SYSTEM Operationally Check Electromechanical Gust Lock Sys-

tem

ALL

29-10-08-211-001-A00 SYSTEM Visually Check Differential Pressure Indicators for Red

Pins Popped out

ALL

32-34-00-720-001-A00 SYSTEM Functionally Check Landing Gear Emergency Extension

Pre-Mod. SB 145-32-0036 and/or SB 145-32-0037

ALL

32-50-00-710-001-A00 SYSTEM Operationally Check Nose wheel Steering System

Disen- gage

ALL

32-62-00-710-001-A00 SYSTEM Operationally Check Landing Gear Warning System ALL

32-63-00-710-001-A00 CMR/ANAC-FAA Operationally Check Air/Ground System ALL

32-63-00-710-001-A00 CMR/EASA Operationally Check Air/Ground System ALL

33-47-03-720-001-A00 SYSTEM Functionally Check White Strobe Lighting System Pre-

Mod. SB 145-33-0008

NOTE: This task is applicable only to aircraft under

ANAC/FAA Certifications.

ALL



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33-51-00-720-001-A01 SYSTEM Functionally Check Non Rechargeable Flashlight Sys-

tem (MODEL EF-1)

ALL

34-13-00-680-001-A01 SYSTEM Drain Pitot Lines Post-Mod. SB 145-34-0021 ALL

35-30-01-211-001-A00 SYSTEM Visually Check Portable Oxygen Cylinder Gauge Pres- sure Indication NOTE: Or in accordance with Local Regulatory Authority Requirements.

ALL

45-45-00-970-002-A00 SYSTEM CMC DATA - Personal Computer Downloading ALL

53-21-02-640-001-A00 SYSTEM Lubricate Main Door Frame Rollers ALL

53-21-12-640-001-A00 SYSTEM Lubricate Service Door Frame Rollers ALL

72-63-01-710-001-A00 SYSTEM Operationally Check Starter Drain Adapter Post-Mod. SB AE3007A-72-253 and Pre-Mod. SB AE3007A-72-330

ALL

73-22-01-720-003-A00 SYSTEM Inspect Multi-Function Display for ENG( ) LT FAULT and ENG ( ) SCHED MAINT REPAIR Maintenance Mes- sages

ALL

76-13-03-710-001-A00 SYSTEM Operationally Check Idle Lockout NOTE: Only for aircraft with Thrust Reversers.

ALL

78-32-00-211-001-A00 SYSTEM Visually Check Thrust Reverser 1RY and 3RY Locks ALL

78-33-00-710-001-A00 CMR/ANAC-FAA Operationally Check Air/Ground Input Signal to Thrust Reverser System

ALL


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78-33-01-710-001-A00 CMR/ANAC-FAA Operationally Check Isolation Control Unit ALL

78-33-00-710-002-A00 CMR/ANAC-FAA Operationally Check Wheel Speed Input Signal to Thrust

Reverser System

ALL

80-10-01-720-001-A00 SYSTEM Functionally Check Air Turbine Starter including oil ser-

vicing

ALL


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S6 TASKS: To be performed at every 6 Months. Package Performed in: / / Tolerance is Not Applicable.


21-27-00-710-001-A00 SYSTEM Operationally Check Baggage Compartment Ventilation

System (including High and Low Speed of Fan) (Bag-

gage Compartment with Ventilation System only)

ALL

23-51-00-710-001-A00 SYSTEM Operationally Check Audio System Emergency Mode ALL

24-36-01-610-001-A00 SYSTEM Service Main Battery MARATHON P/N 32248-001 ALL

24-60-00-710-002-A00 SYSTEM Operationally Check Electrical Emergency Abnormal

Alarm

ALL

27-40-00-710-003-A00 SYSTEM Operationally Check Lockout Logic of Horizontal Stabi-

lizer Control Unit Post-Mod. SB-145-27-0106

ALL

34-26-03-140-001-A00 CAT III Clean Single IRU Mounting Tray Fan Filter (Single IRS

System only)

ALL

34-27-03-140-001-A00 SYSTEM Clean Dual IRS Mounting Tray Fan Filter (Dual IRS Sys-

tem only)

ALL

53-11-05-212-001-A00 EMB-RECOMM Inspect (Visual Inspection) the Radome Poleyurethane

Film

ALL

72-21-20-220-001-A00 SYSTEM Inspect (Detailed Inspection) Fan Spinner Pre-Mod.

Rolls-Royce SB 3007A-72-167

ALL




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Hours:

Cycles:

Cycles:



S6 TASKS: To be performed at every 6 Months after a 144 Months Threshold. Package Performed in: / / Tolerance equal to ± 15 Days.


53-12-00-210-801-A00 STRUCTURAL Externally inspect the FUSELAGE components:

• Fuselage skin panel at stringers frames/bulkheads and splices (SSI 53-10-07) NOTE: Applicable to aircraft Pre-Mod. SB 145-53-0051 or Pre-Mod. SB 145-53-0067.

ALL




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Cycles:

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21-25-01-211-001-A00 EMB-RECOMM Visually Check Ram Air Flap Valve ALL

21-31-03-140-001-A01 SYSTEM Clean Electro pneumatic Outflow Valve (Smoking Flights)

ALL

21-31-04-140-001-A00 SYSTEM Clean Pneumatic Outflow Valve (Non-smoking Flights) ALL

25-61-00-212-001-A00 SYSTEM Inspect (General Visual) Emergency Locator Transmitter

for Condition

• Proper Installation

• Battery Corrosion and Leakage

NOTE: Or in accordance with Local Regulatory Authority

Requirements.

ALL

25-61-00-710-001-A00 SYSTEM Operationally Check Emergency Locator Transmitter

System

• Proper Operation

• Crash Switch Operation


Requirements.

ALL

27-12-00-720-003-A00 CMR/ANAC-FAA Functionally Check External Leakage of Aileron Hydrau-

lic Actuator Pre-Mod. SB 145-27-0063

EMB-135 (ALL)

27-12-00-720-003-A02 CMR/EASA Functionally Check External Leakage of Aileron Hydrau-

lic Actuator

EMB-135 (ALL)

27-12-00-720-003-A03 SYSTEM Functionally Check External Leakage of Aileron Hydrau-

lic Actuator Pre-Mod. SB 145-27-0063 for aircraft Certifi-


EMB-145 (ALL)



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27-12-00-720-003-A05 SYSTEM Functionally check External Leakage of Aileron Hydrau-

lic Actuator for aircraft Certificated Under EASA Regula-

tions

EMB-145 (ALL)

27-12-01-212-002-A01 CMR/ANAC-FAA Inspect (Visually Inspect) Aileron PCA Rod Ends/Fitting

Lugs for Integrity and General Condition Post-Mod. SB

145-27-0063

EMB-135 (ALL)

27-12-01-212-002-A02 CMR/EASA Inspect (Visual Inspection) Aileron PCA Rod Ends/Fitting

Lugs for Integrity and General Condition

EMB-135 (ALL)

27-12-01-212-002-A06 SYSTEM Inspect (Visual Inspection) Aileron PCA Rod Ends/ Fit-

ting Lugs for Integrity and General Condition Post-Mod.

SB 145-27-0061 and Post-Mod. SB 145-27-0062 and

Post-Mod. SB 145-57-0019 and Post-Mod. SB 145-27-

0063 for aircraft Certificated Under ANAC/FAA Regula-

tions

EMB-145 (ALL)

27-12-01-212-002-A07 SYSTEM Inspect (Visual Inspection) Aileron PCA Rod Ends/ Fit-

ting Lugs for Integrity and General Condition Post-Mod.

SB 145-27-0061 and Post-Mod. SB 145-27-0062 and

Post-Mod. SB 145-57-0019 for aircraft Certificated

Under EASA Regulations

EMB-145 (ALL)

27-12-01-720-001-A01 CMR/ANAC-FAA Functionally Check Aileron Actuator Damping Compo-


0062 and Post-Mod. SB 145-27-0063

EMB-135 (ALL)



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27-12-01-720-001-A02 CMR/EASA Functionally Check Aileron Actuator Damping Compo-


0062

EMB-135 (ALL)



0062 for aircraft Certificated Under EASA Regulations

EMB-145 (ALL)

27-12-01-720-002-A00 CMR/EASA Functionally Check Aileron Actuator Force Fight Post-

Mod. SB 145-27-0062

EMB-135 (ALL)

27-12-01-720-002-A02 SYSTEM Functionally Check Aileron Actuator force Fight Post-

Mod. SB 145-27-0062 for aircraft Certificated Under

EASA Regulations

EMB-145 (ALL)

27-12-03-212-001-A00 CMR/ANAC-FAA Inspect (Visual Inspection) Aileron Damper Rod

Ends/Fitting Lugs for Integrity and General Condition

Post-Mod. SB 145-27-0063

EMB-135 (ALL)

27-12-03-212-001-A00 SYSTEM Inspect (Visual Inspection) Aileron Damper Rod

Ends/Fitting Lugs for Integrity and General Condition

Post-Mod. SB 145-27-0063. NOTE: This task is applica-

ble only to aircraft under ANAC/FAA Certifications.

EMB-145 (ALL)

27-22-00-720-002-A00 NATIONAL REQ Functionally Check Rudder Hydraulic Damping

(*) NOTE: Or in accordance with Local Regulatory


ALL

27-25-00-710-001-A00 CMR/ANAC-FAA Operationally Check Rudder Pedals Auto Shutoff and

Rudder Manual Shutoff Functions

ALL



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Engine Model:

Engine 1 Serial Number: Hours: Cycles:


Aircraft Model: Aircraft Serial Number: Aircraft Hours: Aircraft Landings:

APU Model: APU Serial Number: APU Hours: APU Cycles:



28-45-00-710-001-A00 SYSTEM Operationally Check Low Pressure Warning System ALL

31-31-00-710-001-A00 SYSTEM FDR DATA - Personal Computer Downloading ALL

32-10-02-610-001-A00 SYSTEM Service MLG Shock Absorber ALL

32-20-01-610-001-A00 SYSTEM Service NLG Shock Absorber ALL

32-44-02-720-001-A00 SYSTEM Functionally Check Hydraulic Accumulator for Nitrogen

Pre-Charge

ALL

33-12-00-710-002-A00 NATIONAL REQ Operationally Check Pushbutton Lighting ALL

33-47-03-720-001-A01 SYSTEM Functionally Check White Strobe Lighting System Post-

Mod. SB 145-33-0008



ALL

33-51-00-720-001-A00 SYSTEM Functionally Check Rechargeable Flashlight System

(MODEL EF-2C)

ALL

34-21-03-140-001-A00 SYSTEM Clean AHRS Fan Filter ALL

35-20-00-710-001-A00 SYSTEM Operationally Check Passenger Oxygen System in

MANUAL Mode (Chemical Oxygen System only)

ALL

53-11-00-220-C01-A00 CORROSION Internally inspect the FUSELAGE components:

• Nose landing gear fitting including bearing cap and

trunnion fitting (SSI 53-10-25)

NOTE: Applicable to aircraft Pre-Mod. SB 145-32-0063.

ALL



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55-10-00-210-C03-A00 CORROSION Externally inspect the HORIZONTAL STABILIZER com-

ponents:

• Pin internal and external hinge stabilizer (SSI 55-10-

24)

ALL

57-26-00-220-C01-A00 CORROSION Internally inspect the WING components:

• FWD & aft side brace fittings MLG (SSI 57-26-56)


ALL


• Lower Bearing Cap (SSI 57-26-94)


ALL


• Aft upper Trunnion (SSI 57-26-95)


ALL


• Fwd upper Trunnion (SSI 57-26-96)


ALL

73-21-00-211-001-A00 SYSTEM Visually Check Fuel Pump and Metering Unit for Fuel

Leakage

ALL



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Cycles:





78-32-00-710-001-A00 SYSTEM Operationally Check Thrust Reverser 2RY and 3RY

Locks

ALL

78-33-00-710-001-A00 CMR/EASA Operationally Check Air/Ground Input Signal to Thrust Reverser System

ALL

78-33-00-710-002-A00 CMR/EASA Operationally Check Wheel Speed Input Signal to Thrust Reverser System

ALL

78-33-01-710-001-A00 CMR/EASA Operationally Check Isolation Control Unit ALL

80-10-02-160-001-A00 SYSTEM Clean Start Control Valve Filter Pre-Mod. SB 145-80- 0003

ALL



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Hours:

Cycles:

Cycles:





24-36-01-720-001-A00 SYSTEM Functionally Check Main Battery SAFT P/N 442CH1 ALL

25-63-00-710-001-A00 NATIONAL REQ Operationally Check Portable Emergency Locator Trans-

mitter System (if installed)


Requirements.

ALL

78-34-01-720-001-A00 SYSTEM Functionally Check Stow/Transit Thrust Reverser Micro-

switches for Insulation P/Ns 83-990-137 83-990-152 and

83-990-166

ALL



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Hours:

Cycles:

Cycles:





21-26-08-960-001-A00 SYSTEM Discard Exhaust Hoses of the Electronic Bay Compart-

ment Pre-Mod. SB 145-21-0013

ALL

21-51-02-170-002-A00 EMB-RECOMM Clean Dual Heat Exchanger on the Aircraft ALL

26-15-01-212-001-A00 SYSTEM Visually Check WALTER KIDDE Baggage Compartment

Smoke Detection System Maintenance LED

ALL

27-12-00-720-003-A04 SYSTEM Functionally check External Leakage of Aileron Hydrau-

lic Actuator Post-Mod. SB 145-27-0063 for aircraft Certif-

icated Under ANAC/FAA Regulations

EMB-145 (ALL)



0062 and Post-Mod. SB 145-27-0063 for aircraft Certifi-


EMB-145 (ALL)

35-21-00-710-001-A00 SYSTEM Operationally Check Passenger Oxygen System in

MANUAL Mode (Gaseous Oxygen System (Shuttle Con-

figuration only))

EMB-135LR

35-21-00-710-002-A00 SYSTEM Operationally Check "VLV CLOSED" Indication Circuit

(Gaseous Oxygen System (Shuttle Configuration only))

EMB-135LR

38-32-04-960-001-A00 SYSTEM Replace Waste Drain Valve O'Ring ALL

52-31-00-710-001-A00 EMB-RECOMM Operational Check Baggage Door Actuating and Locking

Mechanism

ALL



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Hours:

Cycles:

Cycles:





24-36-01-610-001-A02 SYSTEM Service Main Battery MARATHON M3 P/N 32845-001 ALL

30-43-01-211-001-A00 SYSTEM Visually Check Rain Repellent Coating (RPC) for aircraft Certificated Under ANAC/EASA Regulations, If installed. (*) NOTE: 24 MO or 1500 FH Whichever occurs first.

ALL

33-50-04-720-001-A00 SYSTEM Functionally Check Emergency Lighting Battery Pack ALL



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Hours:

Hours:

Cycles:

Cycles:





12-15-02-610-001-A00 EMB-RECOMM Sterilize Water Reservoir ALL

20-00-00-140-005-A00 SYSTEM Clean Rear Fuselage I Lower Side including wiring and

lines(Zones: 171 172).

NOTE: EWIS

ALL

20-00-00-212-004-A00 SYSTEM Inspect (General Visual) Rear Fuselage I Lower Side -

EWIS Components of APU and Engines Generators

Power cables and wiring bundles (Zones: 171 172 / Task

applicable to Baggage Compartment Class D).

NOTE: EWIS

ALL

20-00-00-212-013-A00 SYSTEM Inspect (General Visual) Engine Pylon - EWIS Compo-

nents of Engines Generators Power cables and wiring

bundles (Zones: 414 424).

NOTE: EWIS

ALL

20-00-00-212-014-A00 SYSTEM IInspect (General Visual) Engines - EWIS Components

of Engines Generators Power cables (Zones: 415 425).

NOTE: EWIS

ALL

21-23-05-710-001-A00 EMB-RECOMM Operationally Check Toilet Gasper Hose Filter (if

installed)

(*) NOTE: Initial inspection since new S48 check.

ALL

21-27-02-710-001-A00 SYSTEM Operationally Check Baggage Compartment Check

Valve (manual check for free movement and correct

seating) (Baggage Compartment with Ventilation System

only)

ALL



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Hours:

Cycles:

Cycles:





21-31-03-140-001-A00 SYSTEM Clean Electropneumatic Outflow Valve (Non-smoking

Flights)

ALL

21-51-01-130-001-A00 SYSTEM Clean Pack Valve Filter Using Ultrasonic Method ALL

23-71-02-710-001-A00 SYSTEM Operationally Check CVR Underwater Locator Beacon ALL

27-12-00-720-003-A01 CMR/ANAC-FAA Functionally Check External Leakage of Aileron Hydrau-

lic Actuator Post-Mod. SB 145-27-0063

EMB-135 (ALL)

27-12-01-720-002-A01 SYSTEM Functionally Check Aileron Actuator force Fight Post-

Mod. SB 145-27-0062 for aircraft Certificated Under

ANAC/FAA Regulations

ALL

27-12-03-720-001-A00 CMR/ANAC-FAA Functionally Check Aileron Damper Damping Force

Post-Mod. SB 145-27-0063

EMB-135 (ALL)

27-12-03-720-001-A00 SYSTEM Functionally Check Aileron Damper Damping Force

Post-Mod. SB 145-27-0063



EMB-145 (ALL)

27-12-03-720-002-A00 CMR/ANAC-FAA Functionally Check External Leakage of Aileron Damper

Post-Mod. SB 145-27-0063

EMB-135 (ALL)

27-12-03-720-002-A00 SYSTEM Functionally Check External Leakage of Aileron Damper

Post-Mod. SB 145-27-0063



EMB-145 (ALL)



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Hours:

Cycles:

Cycles:





27-15-00-710-001-A00 SYSTEM Operationally Check Aileron Disconnect System ALL

27-23-00-710-002-A00 NATIONAL REQ Operationally Check Alerting Light of the Rudder Mov-

able Primary Stop

ALL

27-25-00-710-001-A00 CMR/EASA Operationally Check Rudder Pedals Auto Shutoff and

Rudder Manual Shutoff Functions

ALL

27-35-00-710-001-A00 SYSTEM Operationally Check Elevator Disconnect System ALL

27-40-02-610-001-A00 SYSTEM Service Horizontal Stabilizer Actuator and check for leak-

age

ALL

27-40-03-640-001-A00 SYSTEM Lubricate Main Pitch Trim Switches ALL

27-51-01-720-001-A00 SYSTEM Functionally Check Flap Transmission Brake Holding

Capability

ALL

31-31-02-710-001-A00 SYSTEM Operationally Check FDR Underwater Locator Beacon ALL

32-10-00-210-C02-A00 CORROSION Externally inspect the MAIN LANDING GEAR compo-

nents:

• Shock absorber piston tube assy - MLG (SSI 32-10-

05)

ALL


nents:

• Shock absorber cylinder assy - MLG (SSI 32-10-06)

ALL



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Hours:

Cycles:

Cycles:





32-10-07-212-001-A00 EMB-RECOMM Inspect (Visual Inspection) the Main Landing Gear Doors

Polyurethane Film for integrity

NOTE: Zones 722 and 732.

ALL

32-20-00-210-C01-A00 CORROSION Externally inspect the NOSE LANDING GEAR compo-

nents:

• Main drag strut botton stay - NLG (SSI 32-20-14)

ALL

32-20-07-212-001-A00 EMB-RECOMM Inspect (Visual Inspection) the Nose Landing Gear

Doors Polyurethane Film for integrity


ALL

32-Z711-213-001-A00 ZONAL External General Visual Inspection

NOTE: EWIS

ALL


NOTE: EWIS

ALL

34-13-04-280-001-A00 RVSM Inspect (Special Inspection) RVSM Critical Region (Skin)

for Waviness (aircraft identified in and have not accom-

plished SB 145-34-0110)

ALL

34-13-04-280-002-A00 RVSM Inspect (Special Inspection) Static Port Surrounding

Plate for Flushness and Integrity (aircraft identified in and

have not accomplished SB 145-34-0110)

ALL



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Hours:

Cycles:

Cycles:





34-13-04-280-003-A00 RVSM Inspect (Special Inspection) Passenger Gaseous Oxy-

gen Service Panel (panel P/N 145-51705-001 attached

by livelock stud xnut) installed in RVSM Critical Region

for Flushness and Integrity (aircraft identified in and have

not accomplished SB 145-34-0110)

ALL

34-23-05-710-001-A00 CAT III Operationally Check HGS Computer Fan ALL

34-32-03-212-001-A00 CAT III Inspect (General Visual) VOR/LOC Antenna ALL

34-41-00-710-001-A00 CAT II Operationally Check GPWS/WINDSHEAR ALL

35-10-00-710-001-A01 SYSTEM Operationally Check Crew Oxygen Mask Puritan and/or

B/E Aerospace.

ALL

35-11-02-212-001-A00 SYSTEM Visually Check Pressure Transducer Indication on MFD

Versus External Gauge Indication

ALL

35-21-00-211-001-A00 SYSTEM Visually Check Pressure Indication Between MFD Ver-

sus Cylinder Gauge and Charging Gauge Versus Cylin-

der Gauge (Gaseous Oxygen System (Shuttle Configu-

ration only))

EMB-135LR

35-21-02-211-001-A00 SYSTEM Visually Check Passenger Oxygen Mask Assy (Gaseous

Oxygen System (Shuttle Configuration only))

EMB-135LR

35-21-06-710-001-A00 SYSTEM Operationally Check Electric Pulse/Latching On-Off

Valve (Gaseous Oxygen System (Shuttle Configuration

only))

EMB-135LR

35-21-07-720-001-A00 SYSTEM Functionally Check of Oxygen Sequence Regulator

(Gaseous Oxygen System (Shuttle Configuration only)

EMB-135LR



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Hours:

Cycles:

Cycles:





35-30-02-211-001-A00 SYSTEM Visually Check Continuous Flow Mask ALL

52-10-00-220-C02-A00 CORROSION Externally inspect the MAIN DOOR (STANDARD

MODEL) components:

• Attachment fittings-to-fuselage & interface parts

(SSI 52-10-05)

ALL

52-12-00-720-001-A00 SYSTEM Functionally Check Main Door Hydraulic Accumulator

Nitrogen Charge (Standard Main Door Model only)

ALL

52-18-00-640-001-A00 SYSTEM Lubricate Side-Hinged Main Door Actuating and Locking

Mechanism

ALL

52-43-00-640-001-A00 SYSTEM Lubricate Service Door Actuating and Locking Mecha-

nism

ALL

52-Z811-214-001-A00 ZONAL Internal General Visual Inspection ALL

52-Z811-214-002-A00 ZONAL Internal General Visual Inspection (APPLICABLE FOR

SIDE HINGED MAIN DOOR ONLY)

ALL



53-04-02-212-001-A00 EMB-RECOMM Inspect (Visual Inspection) the Naca-Air-Intake at

Forward Wing-To-Fuselage Fairing Polyurethane Film

for Integrity

NOTE: Zone 191.

ALL


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Hours:

Hours:

Cycles:

Cycles:






• Nose landing gear fitting including bearing cap and

trunnion fitting (SSI 53-10-25)

NOTE: Applicable to aircraft Post-Mod. SB 145-32-0063.

ALL

53-11-06-212-001-A00 EMB-RECOMM Inspect (Visual Inspection) the Naca-Air-Intake at

Forward Fuselage I Polyurethane Film for Integrity


ALL


• Stops and backup structures for service door

(SSI 53-20-02)

ALL


• Fuselage skin panel at stringers frames/bulkheads

and splices (SSI 53-20-07)

ALL


• Passenger cabin floor beams and columns

(SSI 53-20-11)


or SB 145-53-0039 or SB 145-53-0041.

ALL




421 of 732



Hours:

Hours:

Cycles:

Cycles:






• Passenger cabin floor beams and columns

(SSI 53-20-11)

NOTE: Applicable to aircraft Post-Mod. SB 145-53-0026

SB 145-53-0039 and SB 145-53-0041.

ALL

53-24-00-210-C01-A00 CORROSION Externally inspect the FUSELAGE components:



ALL


• Toilet waste valve support (SSI 53-20-29)

EMB-145MP


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Hours:

Cycles:

Cycles:






• Toilet waste valve support (SSI 53-20-29)

EMB-145MP


• Toilet waste drain valve support (SSI 53-30-29)

EMB-135LR



EMB-135LR




ALL



ALL



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Hours:

Cycles:

Cycles:






• Fuselage skin panel at pressure bulkhead (SSI 53-30-

15)

ALL



EMB-135LR


• Rear pressure bulkhead (SSI 53-30-36)

ALL


• Frames (SSI 53-30-43)

ALL

53-Z131-214-001-A00 ZONAL Internal General Visual Inspection

NOTE: EWIS

ALL

53-Z171-213-001-A00 ZONAL External General Visual Inspection ALL


NOTE: EWIS

ALL




NOTE: EWIS

ALL

54-50-00-220-C01-A00 CORROSION Internally inspect the PYLON components:

• Pylon yokes III and IV(SSI 54-50-02)

ALL



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Hours:

Cycles:

Cycles:






• Pylon yokes I and II (SSI 54-50-05)

ALL


• Pylon yokes I and II upper flange (SSI 54-50-06)

ALL



NOTE: EWIS

ALL

55-10-00-212-001-A00 EMB-RECOMM Inspect (Visual Inspection) the Horizontal Stabilizer

Leading-Edge Root-Fairing and Horizontal Stabilizer-Tip

Polyurethane Film for Integrity


ALL



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Hours:

Cycles:

Cycles:





55-30-00-212-001-A00

EMB-RECOMM

Inspect (Visual Inspection) the Vertical Stabilizer Lead-

ing-Edge Polyurethane Film for Integrity

NOTE: Zone 323.

ALL

56-10-01-720-001-A00

EMB-RECOMM

Functionally Check Torque of Windshield Attaching Bolts

Pre-Mod. SB 145-56-0006

ALL

57-10-00-220-C02-A00

CORROSION

Internally inspect the WING STUB components:

• Spar 3 - lower skin attachments (SSI 57-10-09)

ALL



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Hours:

Cycles:

Cycles:





57-10-00-220-C05-A00 CORROSION Externally inspect the WING STUB components:

• Upper skin - rib 1 attachments and spainwise splice of

integral panel (SSI 57-10-13)

ALL

57-10-00-220-C10-A00 CORROSION Internally inspect the WING STUB components:

• Spar 3 - center bracket and rib 2 attachments (SSI 57-

10-10)

ALL


• Rib 4 - lower flange and web (SSI 57-10-11)

ALL


• Rib 2 - Longitudinal stringer-to-web attachments (SSI

57-10-12)

ALL


• Upper skin - tire compartment composite panel (SSI

57-10-14)

ALL


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Hours:

Hours:

Cycles:

Cycles:







EMB-145MP

EMB-135LR

57-21-00-210-C18-A00 CORROSION Externally inspect the WING components:

• Upper skin/wing stub attachment (SSI 57-21-39)

ALL


• Spar 1 web and stiffeners (SSI 57-22-40)

EMB-135LR


• FWD & aft side brace fittings MLG (SSI 57-26-56)


ALL



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Hours:

Cycles:

Cycles:







NOTE 1: Applicable to aircraft Post-Mod. SB 145-32-

0063.

NOTE 2: If corrosion is detected on the lower bearing

cap internal surface perform internal inspection on the

corresponding upper trunnion bearing surface.

ALL


• Lower skin torque box (SSI 57-28-58)

ALL



ALL

57-42-00-220-C01-A00 CORROSION Externally inspect the WING LEADING EDGE compo-

nents:

• Wing leading edge 2 bottom skin at connections to

lower rear girder & wing lower spar cap (SSI 57-42-97)

ALL

57-43-00-212-001-A00 EMB-RECOMM Inspection (Visual Inspect) the Wing-Tip Polyurethane

Film for Integrity


ALL




NOTE: EWIS

ALL



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Hours:

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Cycles:





73-11-10-130-001-A00 SYSTEM Clean Fuel Nozzles except P/N 23075904 P/N 23077006

and P/N 23087207

ALL

76-11-04-720-001-A00 NATIONAL REQ Functionally Check Friction Lock Assembly for Pre-Load

Value

ALL

76-20-00-710-001-A00 SYSTEM Operationally Check Emergency Shutdown System ALL



NOTE: EWIS

ALL


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Hours:

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Cycles:





21-31-08-960-001-A01 SYSTEM Replace Air Filter Element (Smoking Flights) ALL




432 of 732

S24 TASKS 48MO THRESHOLD TOLERANCE

EQUAL TO ± 15 Days

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52-10-00-220-C06-A00 CORROSION Externally inspect the MAIN DOOR (STANDARD

MODEL) components:

• Structure (SSI 52-10-01)

ALL

52-10-00-220-C06-A01 CORROSION Externally inspect the MAIN DOOR (SIDE-HINGED

MODEL) components:

• Structure (SSI 52-10-01)

ALL

52-30-00-210-C01-A00 CORROSION Externally inspect the BAGGAGE DOOR components:

• Baggage door structure (SSI 52-30-08)

ALL



ALL


• Spar attachment torque box (SSI 57-28-57)

ALL


nents:

• Wing leading edge 1 skin (SSI 57-41-94)

ALL


nents:

• Wing leading edge 2 skin (SSI 57-42-95)

ALL

57-43-00-210-C01-A00 CORROSION Externally inspect the LEADING EDGE components:

• Wing leading edge 3 skin

(SSI 57-43-96)

ALL



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52-43-00-210-C01-A00 CORROSION Externally inspect the SERVICE DOOR components:

• Service door structure (SSI 52-43-10)

ALL


• Main door attachments fittings and interface parts

(SSI 53-20-04)

ALL


• Service door attachment fittings and interface parts

(SSI 53-20-05)

ALL

55-20-00-220-C03-A00 CORROSION Externally inspect the ELEVATOR components:

• Tab Hinge Fittings (SSI 55-20-36)

ALL

55-30-00-210-C02-A00 CORROSION Externally inspect the VERTICAL STABILIZER compo-

nents:

• Skin at spar 3 auxiliary spar 52% and stringers 46.5%

& 57.65% between fuselage & rib sta. ZV=1169 (SSI 55-

30-39)

ALL


nents:


& 57.65% between ribs sta. ZV=1169 & sta. ZV=2799

(SSI 55-30-41)

ALL



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nents:


& 57.65% between rib sta. ZV=2799 & horizontal stabi-

lizer (SSI 55-30-43)

ALL


nents:

• Skin at windows between sta. ZV=1169 & sta.

ZV=2799 (SSI 55-30-45)

ALL


nents:

• Skin at ribs between sta. ZV=1169 and sta. ZV=2799

(SSI 55-30-48)

ALL


nents:

• Skin at ribs between sta. ZV=2799 and horizontal sta-

bilizer (SSI 55-30-49)

ALL


• Upper skin/spar attachment (SSI 57-21-37)

ALL



ALL



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21-31-08-960-001-A00 SYSTEM Replace Air Filter Element (Non-smoking Flights) ALL

34-13-00-680-001-A00 SYSTEM Drain Pitot Lines Pre-Mod. SB 145-34-0021 ALL

35-10-00-910-001-A00 EMB-RECOMM Leak Test Crew Oxygen System Lines

NOTE: Together with Task 35-10-07-720-002-A00.

ALL


• Baggage door cutout structure (SSI 53-30-48)

EMB-135LR

57-28-00-220-807-A00 STRUCTURAL Externally inspect the WING components:

• Center track and rib15 trailing edge (SSI 57-28-69)


EMB-145MP

EMB-135LR

73-21-06-720-001-A00 SYSTEM Functionally Check Fuel Filter Impending Bypass Indi-

cating System

ALL



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S36 TASKS: To be performed at every 36 Months. Package Performed in: / / Tolerance is Not Applicable.


26-21-00-720-001-A00 SYSTEM Functionally Check Engine Fire Extinguishing System


Requirements.

ALL

26-22-00-720-001-A00 SYSTEM Functionally Check APU Fire Extinguishing System

(between Switch and Bottle Connector) and verify APU

isolation by APU Fuel Shutoff Valve actuation


Requirements.

ALL



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TASK NUMBER SMRD SECTION TASK DESCRIPTION EFFECTIVITY MECH. SIGN. INSP. SIGN. 20-00-00-140-002-A00

SYSTEM

Clean Center Fuselage III Lower Side including wiring

lines and omega beams (Zones: 151 152 153 154 155

156 157).

NOTE: EWIS

EMB-145MP

EMB-135LR

20-00-00-140-003-A00 SYSTEM Clean Center Fuselage IV Lower Side including wiring

lines and omega beams (Zones: 161 162).

NOTE: EWIS

ALL

20-00-00-140-006-A00 SYSTEM Clean Rear Fuselage I Lateral Side including electronic

rear compartment wiring (Zones: 271 272).

NOTE: EWIS

ALL

20-00-00-140-007-A00 SYSTEM Clean Center Fuselage II Lower Side including wiring


NOTE: EWIS

ALL



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20-00-00-140-008-A00 SYSTEM Clean Center Fuselage I Lower Side including wiring


NOTE: EWIS

ALL

20-00-00-140-010-A00 SYSTEM Clean Cockpit Lateral Side and FWD Pressure Bulkhead

Uppe Side (Zones: 221 222 223 224).

NOTE: EWIS

ALL

20-00-00-140-011-A00 SYSTEM Clean Cockpit Lower Side and FWD Pressure Bulkhead

Lower Side (Zones: 121 122 123 124).

NOTE: EWIS

ALL

20-00-00-212-002-A00 SYSTEM Inspect (General Visual) Center Fuselage III Lower Side

• EWIS Components of APU and Engines Generators

Power cables Hydraulic Pumps Power cables and wiring

bundles (Zones:151 152 153 154 155 156 157).

NOTE: EWIS

EMB-145MP

EMB-135LR



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20-00-00-212-003-A00 SYSTEM Inspect (General Visual) Center Fuselage IV Lower Side




NOTE: EWIS

ALL

20-00-00-212-005-A00 SYSTEM Inspect (General Visual) Rear Fuselage I Lateral Side

• EWIS Components of Engines Generators Power

cables and wiring bundles (Zones: 271 272 / Task appli-

cable to Baggage Compartment Class D).

NOTE: EWIS

ALL

20-00-00-212-006-A00 SYSTEM Inspect (General Visual) Rear Fuselage I Upper Side

• EWIS Components of wiring bundles (Zones: 273 274

/ Task applicable to Baggage Compartment Class D).

NOTE: EWIS

ALL

20-00-00-212-007-A00 SYSTEM Inspect (General Visual) Rear Fuselage I Pressure Bulk-

head Pressurized area side - EWIS Components of APU

Power Cables and wiring bundles (Zones: 275 276).

NOTE: EWIS

ALL

20-00-00-212-008-A00 SYSTEM Inspect (General Visual) Rear Fuselage II Structural area

aft of rear pressure bulkhead - EWIS Components of

Power cables and wiring bundles (Zones: 311 312).

NOTE: EWIS

ALL



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20-00-00-212-009-A00 SYSTEM Inspect (General Visual) Wing-to-fuselage attachment

fairings - EWIS Components of wiring bundles (Zones:

191 192 193 194 195).

NOTE: EWIS

EMB-145MP

20-00-00-212-010-A00 SYSTEM Inspect (General Visual) Wing-to-fuselage attachment

fairings - EWIS Components of wiring bundles (Zones:

191 193 194 195).

NOTE: EWIS

EMB-135LR

20-00-00-220-001-A00 SYSTEM Inspect (Detailed Inspection) - EWIS Components of

Wing Tank Unit Harness (Zones: 155 156 157 531 631

541 641).

NOTE: EWIS

EMB-135LR



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20-00-00-220-002-A00 SYSTEM Inspect (Detailed Inspection) - EWIS Components of

Wing Tank Unit Harness (Zones: 531 631 541 641).

NOTE: EWIS

EMB-145MP

20-00-00-220-003-A00 SYSTEM Inspect (Detailed Inspection) - Electric Fuel Pump Con-

nector (Zones: 155 156 157).

NOTE: EWIS

EMB-135LR

20-00-00-220-004-A00 SYSTEM Inspect (Detailed Inspection) - Electric Fuel Pump Con-

nector (Zones: 531 631).

NOTE: EWIS

EMB-145MP



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20-00-00-220-007-A00 SYSTEM Inspect (Detailed Inspection) Wing Middle Section

• EWIS Components of Pilot Valve harness inside the

conduit (Zones: 541 641).

NOTE: EWIS

ALL

20-00-00-220-008-A00 SYSTEM Inspect (Detailed Inspection) Wing Middle Section

• EWIS Components of Vent Valve harness inside the

conduit (Zones: 541 641).

NOTE: EWIS

ALL

20-00-00-220-010-A00 SYSTEM Inspect (Detailed Inspection) Cockpit Lower Side

• EWIS Components of Power cables (Zones: 123

124).

NOTE: EWIS

ALL

20-00-00-220-011-A00 SYSTEM Inspect (Detailed Inspection) Cockpit Lateral Side

• EWIS Components of Power cables (Zones: 223

224).

NOTE: EWIS

ALL

20-00-00-220-012-A00 SYSTEM Inspect (Detailed Inspection) Center Fuselage I Lower

Side




NOTE: EWIS

ALL



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20-00-00-220-013-A00 SYSTEM Inspect (Detailed Inspection) Center Fuselage II Lower

Side




NOTE: EWIS

ALL

21-21-00-720-001-A00 SYSTEM Functionally Check Display Ventilation System ALL

21-25-01-710-001-A00 SYSTEM Operationally Check Ram Air Valve ALL

21-26-00-710-001-A00 SYSTEM Operationally Check Electronic Compartment Ventilation

System

ALL

21-27-02-640-001-A00 SYSTEM Lubricate Baggage Compartment Check Valves (Bag-

gage Compartment with Ventilation System only)

ALL

21-51-00-710-001-A00 SYSTEM Operationally Check Cooling Pack System to Verify ECS

OFF Signal

ALL

21-51-00-720-003-A00 SYSTEM Functionally Check Pack Duct Overtemperature Protec-

tion

ALL

21-60-08-960-001-A00 EMB-RECOMM Replace Torque Motor Dual Valve Air Filter Element

Post-Mod. SB 145-21-0039

ALL

22-11-00-710-001-A00 SYSTEM Operationally Check AFCS Go-Around Mode

NOTE: Also Check TCS Mode.

ALL

22-11-00-720-004-A00 RVSM Functionally Check AFCS Altitude Hold Mode and Alti-

tude Pre-Select Mode

ALL



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23-12-04-212-001-A00 EMB-RECOMM Visual Inspection of the VHF Antenna ALL

23-31-00-710-002-A00 EMB-RECOMM Operationally Check Back-up/Emergency Cabin Inter-

phone System

ALL

23-31-00-710-003-A00 EMB-RECOMM Operationally Check Loudspeakers ALL

23-71-00-710-001-A00 SYSTEM Operationally Check Voice Recorder 4 Channels and

Area Microphone


Requirements.

ALL

24-54-00-212-001-A00 SYSTEM Inspect (General Visual) PC Power Components

NOTE: If PC Power System installed.

ALL

25-11-01-220-001-A00 SYSTEM Inspect (Detailed Inspection) Cockpit Seats for Security

of Attachment to the Track including Restraint System.

ALL

25-21-00-212-001-A00 SYSTEM Inspect (General Visual) Passenger Seats (Fabric Cover

Tray Safety Belt Integrity and Attachment to the Track)

ALL

25-21-00-220-002-A00 SYSTEM Inspect (Detailed Inspection) Flight Attendant Seats Har-

ness Inertial Reel for Condition and the Seat Bottom for

Freedom of Movement and Returning Back to Upright

Position

ALL

26-23-00-720-001-A00 SYSTEM Functionally Check Baggage Compartment Fire Extin-

guishing System (covering the Pressure Switch Car-

tridge Baggage Fire Extinguishing Switch and Electrical

Hardware. Class "C" Baggage Compartment only)

ALL



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27-11-00-220-001-A00 SYSTEM Inspect (Detailed Inspection) Aileron Primary Mechanical

Control from Control Wheel to Aileron PCAs Checking

Cables Pulleys NRUs Quadrants Disconnect System

and Mechanical Links

ALL

27-11-00-640-001-A00 SYSTEM Lubricate Control Wheel Chain ALL

27-11-01-720-001-A00 SYSTEM Functionally Check Tension of Aileron Control Cables

NOTE: For new cables check tension of the cable loop

affected at first S6 and S12 before escalating to S48.

ALL

27-12-01-212-001-A00 SYSTEM Inspect (Visual Inspection) Aileron PCA Hoses ALL

27-13-00-710-001-A00 SYSTEM Operationally Check Aileron Solenoid Manifold Shutoff

Function

ALL

27-14-00-720-001-A00 SYSTEM Functionally Check Roll Trim ALL

27-21-00-710-001-A00 NATIONAL REQ Operationally Check Rudder Movable Primary Stop

Mechanism

ALL

27-21-01-220-001-A00 SYSTEM Inspect (Detailed Inspection) Rudder Primary Mechani-

cal Control Checking Cables Pulleys and Quadrants

ALL

27-21-01-720-001-A00 SYSTEM Functionally Check Tension of Rudder Control Cables



ALL



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27-21-02-220-001-A00 SYSTEM Inspect (Detailed Inspection) Rudder Main Control Feed-

back Path PCU Linkage and Mounting Points Rudder

Actuator Attachments Hinges and Connecting Rods

NOTE: Requires removal of Concentric and Eccentric

Pins.

ALL

27-22-00-720-001-A00 SYSTEM Functionally Check Rudder Backlash ALL

27-22-01-720-001-A00 SYSTEM Functionally Check Rudder Power Control Unit/ Actua-

tors Differential Pressure

ALL

27-22-02-212-001-A00 SYSTEM Inspect (Visual Inspection) Rudder Actuators ALL

27-31-00-720-001-A00 SYSTEM Functionally Check Elevator Primary Mechanical Control

Backlash

ALL

27-31-01-220-001-A00 SYSTEM Inspect (Detailed Inspection) Elevator Control Cables ALL

27-31-01-720-001-A00 SYSTEM Functionally Check Tension of Elevator Control Cables



ALL

27-31-05-220-001-A00 CMR/ANAC-FAA Inspect (Detailed Inspection) Servo Tab Failsafe Actua-

tion Link

ALL

27-31-05-220-001-A00 CMR/EASA Inspect (Detailed Inspection) Servo Tab Failsafe Actua-

tion Link

ALL

27-31-05-220-002-A00 SYSTEM Inspect (Detailed Inspection) Spring Tab Attachment

Link

ALL



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27-40-00-710-002-A00 SYSTEM Operationally Check Backup/Main Cut-out Switch and

Quick Disconnect Switch

ALL

27-40-00-720-001-A00 SYSTEM Functionally Check Horizontal Stabilizer Backlash ALL

27-40-02-220-001-A00

SYSTEM

Inspect (Detailed Inspection) Horizontal Stabilizer Actua-

tor Integrity and Attachments

ALL

27-51-00-212-001-A00 SYSTEM Inspect (Visual Inspection) Flap Mechanical Line ALL

27-51-00-220-001-A00 SYSTEM Inspect (Detailed Inspection) Flap Flexible Shafts ALL

27-51-00-610-001-A00 SYSTEM Service Flap Screw-jack Actuators Gearbox Pre-Mod.

SB 145-27-0118

ALL

27-51-17-720-001-A00 SYSTEM Functionally Check MTB (Flap Drive Motor Unit) Holding

Capability

ALL

27-63-01-710-001-A00 SYSTEM Operationally Check Spoiler System ALL

27-70-00-710-001-A00 SYSTEM Operationally Check Mechanical Gust Lock Mechanism ALL

27-70-00-720-001-A00 SYSTEM Functionally Check the Gap of Elevator Secondary Stop

(Mechanical Gust Lock System only) Pre-Mod. SB 145-

27-0079

ALL

27-71-00-220-001-A00 SYSTEM Inspect (Detailed Inspection) Electromechanical Gust

Lock Mechanism

ALL

28-12-05-211-001-A00 SYSTEM Visually Check Flame Arrestor for Honey Comb Clogging

and Attaching Parts for Security

ALL



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28-12-05-710-001-A00 SYSTEM Operationally Check Flame Arrestor in/out Flow Valves

for Freedom Movement

ALL

28-21-04-710-001-A00 SYSTEM Operationally Check Cross feed Valve ALL

28-41-00-710-001-A00 SYSTEM Operationally Check Electrical Fuel Quantity Indicating

System (Fuel Low Level Logic)

ALL

29-10-00-280-001-A00 EMB-RECOMM Check Hydraulic Fluid (Analysis) ALL

29-10-00-710-001-A00 SYSTEM Operationally Check Electric Motor Driven Pumps Input

Signals

ALL

29-10-01-710-001-A00 SYSTEM Operationally Check Shutoff Valve by means of the

Hydraulic Panel Switch

ALL

29-10-10-720-001-A00 SYSTEM Functionally Check Return Filter By-Pass Valve

NOTE: S120 if fluid contamination is checked at S60

interval.

ALL

29-10-13-720-001-A00 SYSTEM Functionally Check Priority Valve ALL

29-30-03-720-001-A00 SYSTEM Functionally Check Hydraulic Filters Differential Pres-

sure Indicators

NOTE: S120 if fluid contamination is checked at S60.

ALL



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30-11-00-720-001-A00 CMR/ANAC-FAA Functionally Check Pressure Sensors of the Wing Ther-

mal Anti-Icing System (Bench Test)

ALL

30-11-00-720-001-A00 CMR/EASA Functionally Check Pressure Sensors of the Wing Ther-

mal Anti-Icing System (Bench Test)

ALL

30-12-00-710-001-A00 SYSTEM Operationally Check Electrical Hardware of the Horizon-

tal Stabilizer Thermal Anti-Icing System

ALL

30-12-00-720-001-A00 CMR/ANAC-FAA Functionally Check Pressure Sensors of the Horizontal

Stabilizer Thermal Anti-Icing System (Bench Test)

ALL

30-12-00-720-001-A00 CMR/EASA Functionally Check Pressure Sensors of the Horizontal

Stabilizer Thermal Anti-Icing System (Bench Test)

ALL

30-20-00-220-001-A00 SYSTEM Inspect (Detailed Inspection) Thermal Anti-Ice (TAI)

Exhaust Duct for Condition and Security of Installation

ALL

30-20-01-720-001-A00 SYSTEM Functionally Check Thermal Anti-Ice (TAI) Inter bulkhead Assembly for Leakage

ALL

30-21-00-720-001-A00 CMR/ANAC-FAA Functionally Check Pressure Sensors of the Engine

Thermal Anti-Icing System (Bench Test)

ALL

30-21-00-720-001-A00 CMR/EASA Functionally Check Pressure Sensors of the Engine

Thermal Anti-Icing System (Bench Test)

ALL

30-41-00-710-001-A00 CAT II Operationally Check Windshield Wiper NOTE 1: Applicable to all aircraft under FAA Certifications NOTE 2: Applicable to aircraft under ANAC/EASA Certification, If installed.

ALL

30-42-00-710-001-A00 CAT II Operationally Check Windshield Heating ALL

30-42-00-710-001-A00 SYSTEM Operationally Check Windshield Heating ALL



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31-21-00-710-001-A00 SYSTEM Operationally Check Digital Clock


Requirements. Check together with task 31-31-00-720-

001-A00.

ALL

31-31-00-720-001-A00 SYSTEM Functionally Check Flight Data Recorder System


Requirements.

ALL

31-41-00-710-001-A00 SYSTEM Operationally Check DAU Channel Reversion Function ALL


nents:

• Leg structure equipped (left) - MLG (SSI 32-10-01)

ALL


nents:

• Leg structure equipped (right) - MLG (SSI 32-10-02)

ALL


nents:

• Upper secondary side strut assy - MLG (SSI 32-10-

09)

ALL


nents:

• Lower secondary side strut assy - MLG (SSI 32-10-

10)

ALL



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32-10-00-220-801-A00 STRUCTURAL Externally inspect the MAIN LANDING GEAR compo-

nents:

• Wheel axle MLG (SSI 32-10-04)

ALL

32-20-00-210-806-A00 STRUCTURAL Externally inspect the NOSE LANDING GEAR compo-

nents:

• Sliding tube - NLG (SSI 32-20-18)

ALL


nents:

• Wheel axle (SSI 32-20-19)

ALL

32-32-00-710-001-A00 SYSTEM Operationally Check Landing Gear Extension and

Retraction (Electrical) Indication and Downlock Relays

by Channels A and B

ALL

32-34-00-710-001-A00 SYSTEM Operationally Check Landing Gear Emergency Exten-

sion (Override Switch).

ALL

32-34-00-720-001-A01 SYSTEM Functionally Check Landing Gear Emergency Extension

Post-Mod. SB 145-32-0036 and Post-Mod. SB 145-32-

0037

ALL

32-41-00-720-001-A00 SYSTEM Functionally Check Main Brake System ALL

32-41-07-720-001-A00 SYSTEM Functionally Check Brake Hydraulic Fuse. ALL

32-41-09-710-001-A00 SYSTEM Operationally Check Return Line Check Valve of Main

Brake System

ALL



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32-44-08-710-001-A00 SYSTEM Operationally Check Return Line Check Valve of Emer-

gency/Parking Brake System

ALL

32-44-10-640-001-A00 SYSTEM Lubricate Mechanical Hardware (Handle) and Roller of

Emergency Parking Brake Valve

ALL

32-50-06-720-001-A00 SYSTEM Functionally Check 7-Degree Proximity Switch ALL

33-50-12-720-001-A00 SYSTEM Functionally Check Photo luminescent Floor Proximity Strip Lights System

ALL

34-13-04-280-001-A01 RVSM Inspect (Special Inspection) RVSM Critical Region (Skin)

for Waviness (including aircraft identified in and are Post-

Mod SB 145-34-0110)

ALL

34-13-04-280-002-A01 RVSM Inspect (Special Inspection) Static Port Surrounding

Plate for Flushness and Integrity (including aircraft iden-

tified in and are Post-Mod SB 145-34-0110)

ALL

34-13-04-280-003-A01 RVSM Inspect (Special Inspection) Passenger Gaseous Oxy-

gen Service Panel (panel P/N 145-51705-001 attached

by livelock stud xnut) installed in RVSM Critical Region

for Flushness and Integrity (including aircraft identified in

and are Post-Mod SB 145-34-0110)

ALL

34-21-00-710-001-A00 SYSTEM Operationally Check AHRS DG Mode (AHRS AH-800

only)

ALL

34-22-00-710-001-A00 SYSTEM Operationally Check Electronic Flight Instrument System

Reversion Function

ALL

34-41-00-710-001-A00 SYSTEM Operationally Check GPWS/Windshear ALL



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34-41-00-710-003-A00 CAT II Operationally Check EGPWS/WINDSHEAR ALL

34-41-00-710-003-A00 SYSTEM Operationally Check EGPWS/Windshear ALL

35-10-00-710-001-A00 SYSTEM Operationally Check Crew Oxygen Masks EROS ALL

35-20-00-720-001-A00 SYSTEM Functionally Check Passenger Oxygen System in AUTO

Mode (Chemical Oxygen System only)

ALL

35-20-01-211-001-A00 SYSTEM Visually Check Chemical Oxygen Generator (Chemical

Oxygen System only)

ALL

35-20-04-211-001-A00 SYSTEM Visually Check Passenger Oxygen Mask (Chemical Oxy-

gen System only)

ALL

35-21-00-710-003-A00 SYSTEM Operationally Check "PAX OXY LOW PRESS" Caution

Message (Gaseous Oxygen System (Shuttle Configura-

tion only))

EMB-135LR

35-21-00-720-001-A00 SYSTEM Functionally Check Passenger Oxygen System in AUTO

Mode (Gaseous Oxygen System (Shuttle Configuration

only))

EMB-135LR

35-21-15-710-001-A00 SYSTEM Check (Leak) Passenger Oxygen Distribution (HP) Lines


EMB-135LR

35-21-16-710-001-A00 SYSTEM Check (Leak) Passenger Oxygen Distribution (LP) Lines


EMB-135LR

36-10-01-130-001-A00 SYSTEM Clean Crossbleed Valve Filter by Ultrasonic Method ALL

36-11-01-220-001-A00 SYSTEM Inspect (Detailed Inspection) Engine Low Pressure

Bleed Air Check Valve P/N 816603-3

ALL

36-11-02-130-001-A00 SYSTEM Clean High-Stage Valve Filter by Ultrasonic Method ALL



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36-11-03-130-001-A00 SYSTEM Clean Fan Air Valve Filter by Ultrasonic Method ALL

36-11-05-130-001-A00 SYSTEM Clean Engine Bleed Valve Filter by Ultrasonic Method

Pre-Mod. SB 145-36-0028.

ALL

36-20-02-710-002-A00 SYSTEM Operationally Check Massive Leakage Switch ALL

49-17-00-160-001-A00 SYSTEM Clean APU Drains Post-Mod. SB 145-49-0029 ALL

52-00-00-211-001-A00 SYSTEM Visually Check Locking Red Marks

NOTE: Repaint if necessary.

ALL

52-10-00-220-801-A00 STRUCTURAL Internally inspect the MAIN DOOR (STANDARD

MODEL) components:

• Main door folding flap stops (SSI 52-10-04)

NOTE: During this inspection the CPCP basic task shall

also be performed for this SSI.

ALL

52-10-00-220-801-A01 STRUCTURAL Internally inspect the MAIN DOOR (SIDE-HINGED

MODEL) components:

• Main door folding flap stops (SSI 52-10-04)



ALL

52-10-00-220-C02-A01 CORROSION Externally inspect the MAIN DOOR (SIDE-HINGED

MODEL) components:

• Attachment fittings-to-fuselage & interface parts (SSI

52-10-05)

ALL



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Hours:

Cycles:

Cycles:





52-11-00-640-001-A00 SYSTEM Lubricate Standard Main Door Actuating and Locking

Mechanism

ALL

52-11-00-720-005-A00 SYSTEM Functionally Check Standard Main Door Actuating Latch-

ing and Locking Mechanism

ALL

52-12-00-710-001-A00 SYSTEM Operationally Check Alternate Opening System ALL

52-14-00-211-001-A00 SYSTEM Inspect (Visual Inspection) Standard Main Door Drain

Holes for Obstruction or Damage

ALL

52-14-01-710-001-A00 SYSTEM Operationally Check Main Door Drain Valves (Standard

Main Door Only)

ALL

52-18-06-720-001-A00 SYSTEM Functionally Check Side-Hinged Main door Actuating

Latching and Locking Mechanism

ALL

52-21-00-640-001-A00 SYSTEM Lubricate Passenger Cabin Escape Hatch Support Pin ALL

52-21-00-710-001-A00 SYSTEM Operationally Check Passenger Cabin Escape Hatch

Mechanism

ALL

52-22-00-710-001-A00 SYSTEM Operationally Check Cockpit Emergency Exit ALL

52-22-01-640-001-A00 SYSTEM Lubricate Cockpit Emergency Exit Locking Mechanism ALL

52-31-00-640-001-A00 SYSTEM Lubricate Baggage Door Gear Box ALL

52-32-00-220-001-A00 SYSTEM Inspect Baggage Door Lifting and Lowering Mechanism

for General Condition and Torsion Bar for Torsion

ALL

52-42-01-220-001-A00 SYSTEM Inspect (Detailed Inspection) Cockpit Underfloor Access

Hatch Mechanism

ALL


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Hours:

Cycles:

Cycles:





52-43-06-720-001-A00 SYSTEM Functionally Check Service Door Actuating Latching and

Locking Mechanism

ALL

52-44-01-220-001-A00 SYSTEM Inspect (Detailed Inspection) Rear Electronic Compart-

ment Door Mechanism

ALL

52-51-00-720-001-A00 SYSTEM Functionally Check Reinforced Cockpit Door ALL

52-71-00-710-001-A00 SYSTEM Operationally Check Forward Electronic Compartment

Door Warning Message

ALL

52-72-00-710-001-A00 SYSTEM Operationally Check Rigging Door Warning Message ALL

52-73-00-710-001-A00 SYSTEM Operationally Check Main Door Warning Message ALL

52-73-01-720-001-A00 SYSTEM Functionally Check Main Door Warning Micro switches ALL

52-74-00-710-001-A00 SYSTEM Operationally Check Service Door Warning Message ALL

52-74-01-720-001-A00 SYSTEM Functionally Check Service Door Warning Micro switches

ALL

52-75-00-710-001-A00 SYSTEM Operationally Check Emergency Exit Warning Message ALL

52-76-00-710-001-A00 SYSTEM Operationally Check Baggage Door Warning Message ALL

52-77-00-710-001-A00 SYSTEM Operationally Check Rear Electronic Compartment Door

Warning Message

ALL




53-00-01-220-001-A00 SYSTEM Inspect (Detailed Inspection) Fuselage Drain Valves for

Obstruction or Damage

ALL



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Hours:

Cycles:

Cycles:





53-11-01-220-001-A00 EMB-RECOMM Inspect (Detailed Inspection) the Presence of Water on

the Radome

ALL


• Fuselage skin longitudinal splice along main door cut-

out (SSI 53-20-41)

EMB-145MP


• Stops and backup structures for service door (SSI 53-

20-02)

ALL


• Frames (SSI 53-20-43)

ALL

53-21-02-140-001-A00 SYSTEM Clean Main Door-Frame Rollers ALL

53-21-12-140-001-A00 SYSTEM Clean Service Door-Frame Rollers ALL


• Passenger cabin window frame (SSI 53-20-06)

ALL




ALL



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Cycles:






• Passenger cabin floor beams and columns (SSI 53-

20-11)


ALL



20-11)

NOTE: Applicable to aircraft Pos-Mod. SB 145-53-0041.

ALL



ALL



ALL



ALL


• Frames (SSI 53-20-43)

ALL


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EMB-145MP

EMB-135LR



ALL


• Skin and reinforcement around escape hatch cutout

(SSI 53-20-51)

EMB-135LR



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Cycles:







(SSI 53-20-51)


EMB-145MP



(SSI 53-20-51)


under ANAC/FAA Certifications.

EMB-145MP




ALL


• Frames (SSI 53-20-43)

ALL



ALL



20-11)


ALL



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20-11) NOTE: Applicable to aircraft Post-Mod. SB 145-53-0041.

ALL




ALL



ALL



ALL



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Cycles:







EMB-145MP EMB-135LR

53-24-00-220-C01-A00

CORROSION

Internally inspect the FUSELAGE components:



ALL



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Hours:

Hours:

Cycles:

Cycles:






• Passenger cabin floor beams and Columns (SSI 53-

20-11)


or SB 145-53-0041.

ALL


• Passenger cabin floor beams and Columns (SSI 53-

20-11)

NOTE: Applicable to aircraft Pos-Mod. SB 145-53-0026

and SB 145-53-0041.

ALL



EMB-145MP

EMB-135LR


• Frames (SSI 53-20-43)

ALL



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Hours:

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Cycles:





53-31-00-220-808-A00

STRUCTURAL

Externally inspect the FUSELAGE components:


EMB-145MP



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Hours:

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Cycles:







ALL






NOTE: EWIS

ALL



NOTE: EWIS

ALL



NOTE: EWIS

ALL


NOTE: EWIS

ALL



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Hours:

Cycles:

Cycles:






NOTES: EWIS

EMB-145MP

EMB-135LR

53-Z155-214-001-A00 ZONAL Internal General Visual Inspection NOTE: EWIS

EMB-145MP EMB-135LR

53-Z161-214-001-A00 ZONAL Internal General Visual Inspection NOTE: EWIS

ALL



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Cycles:





53-Z191-213-001-A00 ZONAL External General Visual Inspection EMB-145MP EMB-135LR


NOTE: EWIS

EMB-145MP

EMB-135LR



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53-Z213-213-001-A00

ZONAL


ALL


NOTE: EWIS

ALL



NOTE: EWIS

ALL








NOTE: EWIS

ALL


NOTE: EWIS

ALL


NOTE: EWIS

ALL



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NOTE: EWIS

ALL

55-10-00-210-803-A00 STRUCTURAL Externally inspect the HORIZONTAL STABILIZER com-

ponent:

• Fitting hinge support stabilizer (SSI 55-10-21)

ALL

55-10-00-210-804-A00 STRUCTURAL Internally inspect the HORIZONTAL STABILIZER com-

ponent:


24)

ALL


ponents:

• U shape L shape and box structure - elevator com-

mand (SSI 55-10-22)

ALL


ponents:

• Skin from rib sta. YH=990 to rib sta. YH=2965-lower

surface (SSI 55-10-08)

ALL



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Cycles:





55-10-00-220-813-A00 STRUCTURAL Internally inspect the HORIZONTAL STABILIZER com-

ponents:


24)

EMB-145MP

EMB-135LR



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55-10-00-220-C01-A00

CORROSION

Internally inspect the HORIZONTAL STABILIZER com-

ponents:

• Ribs from rib sta. YH=990 to rib sta. YH=2965 (SSI

55-10-05)

ALL


ponents:

• Skin from rib sta. YH=990 to rib sta. YH=2965-upper


ALL

55-10-00-220-C03-A00 CORROSION Internally inspect the HORIZONTAL STABILIZER com-

ponents:

• Front spar web and cap from rib sta. YH=350 to rib

sta. YH=2965 (SSI 55-10-10)

ALL


ponents:

• Front spar web and cap from fin to rib sta. YH=350

including center fitting/ spar attachment (SSI 55-10-09)

ALL




474 of 732



Hours:

Hours:

Cycles:

Cycles:






ponents:

• Rear spar web & cap from rib sta. YH=350 to rib sta.

YH=2965 including fitting hinge stabilizer attach to eleva-

tor (SSI 55-10-13)

ALL


ponents:

• Ribs from rib sta. YH=30 to rib sta. YH=990 (SSI 55-

10-04)

ALL

55-20-00-210-801-A00 STRUCTURAL Internally inspect the ELEVATOR components:

• Elevator horn mass balance weights and attachments

(SSI 55-20-90)

ALL


• Tab wheel drive support fittings (SSI 55-20-35)

ALL


• Tab (SSI 55-20-37)

ALL

55-20-00-290-C01-A00 CORROSION Internally inspect the ELEVATOR components using a

boroscope:

• Ribs between sta. YH=9834 and sta. YH=1898 (SSI

55-20-31)

ALL


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Cycles:





55-20-00-290-C02-A00 CORROSION Internally inspect the ELEVATOR components using a

boroscope:


55-20-32)

ALL

55-30-00-210-803-A00 STRUCTURAL Internally inspect the VERTICAL STABILIZER compo-

nents:

• Fin-to-horizontal stabilizer support actuators including

bolt (SSI 55-30-75)

ALL


nents:

• Fitting hinge support (SSI 55-30-76)

ALL





NOTE: EWIS

ALL









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56-20-01-220-001-A00 EMB-RECOMM Inspect (Detailed Inspection) Passenger Cabin Windows

for Delamination except P/N P03014-1

ALL


• Wing stub - rib 2A skin supports and their attachments

to web lower flange and FWD & AFT web supports (SSI 57-01-18)

EMB-145MP EMB-135LR


• Wing stub - upper skin - rib 2A attachment (SSI 57-01-

19)

EMB-145MP EMB-135LR



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Hours:

Hours:

Cycles:

Cycles:






• Wing stub - upper skin - rib 2A attachments (SSI 57-

01-19)

EMB-145MP EMB-135LR

57-10-00-220-804-A00 STRUCTURAL Internally inspect the WING STUB components:

• Lower skin - ribs 1 2 & 3 attachments and tire compart-

ment wall attachments (SSI 57-10-02)



EMB-145MP

EMB-135LR



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57-10-00-220-806-A00 STRUCTURAL Externally inspect the WING STUB components:

• Lower skin - ribs 1 2 & 3 attachments and tire compart-

ment wall attachments (SSI 57-10-02)



EMB-145MP

EMB-135LR



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57-10-00-220-C03-A00

CORROSION


• Spar 1 - brackets ribs 1 and 3 attachments (SSI 57-10-

04)

ALL

57-10-00-220-C09-A00

CORROSION

Externally inspect the WING STUB components:


ALL


• Spar 2 - center brackets & rib 2 attachments and ribs 1

& 3 web attachments (SSI 57-10-07)

ALL



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Hours:

Hours:

Cycles:

Cycles:






• Lower skin/spar attachments (SSI 57-21-36)

ALL


• Lower skin panel spanwise joint (SSI 57-21-30)

ALL


• Upper skin panel spanwise joint (SSI 57-21-31)

ALL


• Lower skin panel chordwise joint (SSI 57-21-29)

ALL



EMB-145MP

EMB-135LR



ALL



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Hours:

Hours:

Cycles:

Cycles:






• Upper skin/spar stub attachment (SSI 57-21-39)

ALL



ALL



ALL


• Lower skin/wing stub attachment (SSI 57-21-38)

ALL


• Skin panels (SSI 57-21-26)

EMB-135LR



EMB-145MP



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Hours:

Hours:

Cycles:

Cycles:






• Spar 2/wing stub attachments (SSI 57-23-48)

ALL



ALL

57-24-00-210-C02-A00

CORROSION

Externally inspect the WING components:


ALL



ALL


• Spar 3 web cutouts (SSI 57-24-51)

ALL



ALL



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Hours:

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Cycles:






• FWD & AFT side brace fittings - MLG (SSI 57-26-56)


EMB-145MP

EMB-135LR

57-26-00-220-C03-A01

CORROSION

Internally inspect the WING components:



ALL




ALL



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Hours:

Hours:

Cycles:

Cycles:







EMB-145MP

EMB-135LR


• Attachment lugs aileron (SSI 57-28-66)

EMB-145MP



ALL



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ALL


• Tracks/rib attachment torque box 3 (SSI 57-28-65)

ALL


• Attachment actuator lugs inboard/ outboard spoilers

(SSI 57-28-70)

ALL


• Skin/rib attachment MLGB

(SSI 57-29-72)

ALL

57-52-00-210-803-A00 STRUCTURAL Externally inspect the FLAP components:

• Ribs/skin attachment inboard flap (SSI 57-52-79)

ALL


• Vane inboard/outboard fittings inboard flap (SSI 57-

52-81)

ALL



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Hours:

Hours:

Cycles:

Cycles:






• Ribs/skin attachment outboard flap (SSI 57-53-86)

EMB-145MP

EMB-135LR


• Vane inboard/outboard fittings outboard flap (SSI 57-

53-88)

ALL

57-61-00-220-805-A00 NATIONAL REQ Internally inspect the AILERON components:

• Aileron Actuator fittings (SSI 57-61-12)

ALL

57-70-00-210-C01-A00 CORROSION Externally inspect the SPOILER components:

• Hinges attachment spoilers (SSI 57-70-92)

ALL

57-70-00-210-C02-A00 CORROSION Externally inspect the SPOILER components:

• Actuator attachment spoilers (SSI 57-70-93)

ALL


NOTE: EWIS

ALL


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Hours:

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NOTE: EWIS

ALL



NOTE: EWIS

ALL



NOTE: EWIS

ALL

57-Z551-213-001-A00 ZONAL External General Visual Inspection EMB-145MP

EMB-135LR


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Hours:

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Cycles:






NOTE: EWIS

EMB-145MP

EMB-135LR



NOTE: EWIS

ALL



NOTE: EWIS

ALL



NOTE: EWIS

ALL

71-10-00-211-001-A00 SYSTEM Visually Check Cowling Seals ALL


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71-10-00-220-001-A00 SYSTEM Inspect (Detailed Inspection) Cowling Inboard/ Outboard

Attachment and Surrounding Structure

ALL

71-20-00-220-001-A00 SYSTEM Inspect (Detailed Inspection) Engine Mounting Assy ALL

71-60-01-211-001-A00 SYSTEM Visually Check Air Intake Attachment ALL

71-60-01-211-002-A00 SYSTEM Visually Check Air Intake Rear Bulkhead and Fire Shield ALL

72-21-01-220-001-A00 SYSTEM Inspect (Detailed Inspection) Fan Blades ALL

74-21-01-220-001-A00 SYSTEM Inspect (Detailed Inspection) Igniters ALL


NOTE: For aircraft without Thrust Reversers only

ALL


NOTE: For aircraft without Thrust Reversers only

ALL

80-10-02-160-001-A01 SYSTEM Clean Start Control Valve Filter Post-Mod. SB 145-80-

0003

ALL


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S48 TASKS 96MO THRESHOLD TOLERANCE

EQUAL TO ± 15 Days



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27-11-00-720-001-A00 SYSTEM Functionally Check Aileron Primary Mechanical Control

Backlash

NOTE: Threshold at S96.

ALL

52-10-00-220-C05-A01 CORROSION Externally inspect the MAIN DOOR components:

• Window frame (SSI 52-10-06)

NOTE: Applicable to side-hinged door only.

ALL

52-43-00-210-C02-A00 CORROSION Internally inspect the SERVICE DOOR components:

• Service door structure (SSI 52-43-10)

ALL

52-43-00-220-C01-A00 CORROSION Externally inspect the SERVICE DOOR components:

• Service door-to-fuselage attachment fittings & inter-

face parts (SSI 52-43-15)

ALL




ALL


• Nose landing gear bay structure (SSI 53-10-24)

ALL


• Nose landing gear bay structure (SSI 53-10-24)

ALL



15)

ALL



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Cycles:








ALL


• Windshield cutout structure (SSI 53-10-17)

ALL


• Windshield center post including its attachments and

lower fitting (SSI 53-10-19)

ALL


• Maintenance door cutout structure (SSI 53-10-49)

ALL


• Cockpit window cutout structure (SSI 53-10-18)

ALL


• Windshield panel (SSI 53-10-21)

ALL


• Cockpit window rear post and its attachment (SSI 53-

10-22)

ALL



15)

ALL



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(SSI 53-20-51)

ALL




ALL



15)

ALL



EMB-145MP

EMB-135LR



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53-32-00-210-C01-A00 CORROSION Externally inspect the FUSELAGE component:



ALL




ALL


• Tail cone frame at APU mounting attachment

(SSI 53-30-39)

ALL


• Frames (SSI 53-30-43)

ALL



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54-50-00-220-808-A01 STRUCTURAL Internally inspect the PYLON components:

• AFT Engine Mounts including bolts (SSI 54-50-07)


and the flight cycles accumulated shall be based on the

engine mount components.

EMB-145MP

EMB-135LR


ponents:

• Support quadrant assy stabilizer (SSI 55-10-23)

ALL


• Skin between root and sta. YH=160 (SSI 55-20-26)

ALL

55-20-00-210-C02-A00 CORROSION Internally inspect the ELEVATOR components:

• Spars between root and sta. YH=160 (SSI 55-20-25)

ALL



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Hours:

Cycles:

Cycles:






• Skin between sta. YH=160 and sta. YH=3320 (SSI 55-

20-28)

ALL


• Spars between sta. YH=160 and sta. YH=3320 (SSI

55-20-27)

ALL


• Ribs between root and sta. YH=160 (SSI 55-20-29)

ALL


• Ribs between sta. YH=160 and sta. YH=983.4 (SSI

55-20-30)

ALL



55-20-33)

ALL


nents:

• Skin at spars 1 2 auxiliary spar 41% and stringers 20%

& 35.5% between fuselage & rib sta. ZV=1169 (SSI 55-

30-38)

ALL



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Cycles:

Cycles:






nents:

• Skin at ribs from fuselage to sta. ZV=1169 (SSI 55-30-

47)

ALL

55-30-00-210-C04-A00 CORROSION Internally inspect the VERTICAL STABILIZER compo-

nents:

• Ribs (sta. ZV=3461 ZV=2538 ZV=1677 ZV=1550.5

ZV=1430.5 ZV=1423 ZV=1302 ZV=1169 and ZV=915)

(SSI 55-30-73)

ALL


nents:


& 35.5% between ribs sta. ZV=1169 & sta. ZV=2799 (SSI

55-30-40)

ALL


nents:


& 35.5% between rib sta. ZV=2799 & horizontal stabilizer

(SSI 55-30-42)

ALL


nents:

• Skin at windows from fuselage to sta. ZV=1169 (SSI

55-30-44)

ALL



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Hours:

Cycles:

Cycles:






nents:

• Skin at windows between sta. ZV=2799 and horizon-

tal stabilizer (SSI 55-30-46)

ALL


nents:

• Root rib including bolts (SSI 55-30-70)

ALL


nents:

• Ribs of horizontal stabilizer actuators (sta. ZV=3145

ZV=3015 and ZV=2799) (SSI 55-30-71)

ALL


nents:

• Ribs of actuator area (sta. ZV=1932 and ZV=2277)

(SSI 55-30-72)

ALL

55-40-00-210-C01-A00 CORROSION Externally inspect the RUDDER components:

• Front spar - skin attachment (rudder I) (SSI 55-40-81)

ALL


• Spar - skin attachment (rudder II) (SSI 55-40-86)

ALL


• Rear spar - skin attachment (rudder I) (SSI 55-40-82)

ALL



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• LT & RT skin - spar cap attachment (rudder I) (SSI 55-

40-83)

ALL


• Ribs - skin attachment (rudder I) (SSI 55-40-84)

ALL


• Hinges - rudder I (SSI 55-40-85)

ALL


• LT & RT skin - spar cap attachment (rudder II) (SSI

55-40-87)

ALL


• Ribs - skin attachment (rudder II) (SSI 55-40-88)

ALL


• Hinges - rudder II (SSI 55-40-89)

ALL

55-40-00-220-C03-A00 CORROSION Internally inspect the RUDDER components:

• Front spar - skin attachment (rudder I) (SSI 55-40-81)

ALL


• Spar - skin attachment (rudder II) (SSI 55-40-86)

ALL


• Rear spar - skin attachment (rudder I) (SSI 55-40-82)

ALL



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Hours:

Cycles:

Cycles:






• LT & RT skin - spar cap attachment (rudder I) (SSI 55-

40-83)

ALL


• Ribs - skin attachment (rudder I) (SSI 55-40-84)

ALL


• Hinges - rudder I (SSI 55-40-85)

ALL


• LT & RT skin - spar cap attachment (rudder II) (SSI

55-40-87)

ALL


• Ribs - skin attachment (rudder II) (SSI 55-40-88)

ALL


• Hinges - rudder II (SSI 55-40-89)

ALL



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Cycles:







EMB-145MP

EMB-135LR



ALL



ALL


• Lower skin access holes (SSI 57-21-32)

ALL


• Gravity fuel hole (SSI 57-21-35)

ALL



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Engine Model:



Aircraft Model:Aircraft Serial Number: Aircraft Hours: Aircraft Landings:

APU Model:APU Serial Number: APU Hours: APU Cycles:

Package Performed in: / /

Hours:

Hours:

Cycles:

Cycles:

S48 TASKS: To be performed at every 48 Months after a 96 Months Threshold.Tolerance equal to ± 15 Days.



• Lower skin/rib attachment (SSI 57-25-54)

EMB-145MP

EMB-135LR


• Upper skin/rib attachment (SSI 57-25-55)

ALL

57-28-00-210-C03-A00

CORROSION



ALL


• Flap actuator attachment fittings (SSI 57-28-67)

ALL


• Upper skin torque box (SSI 57-28-61)

ALL



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Hours:

Cycles:

Cycles:




• Flap track torque box (SSI 57-28-59)

ALL


• Ribs torque box (SSI 57-28-60)

ALL



ALL

57-50-00-220-C01-A00 CORROSION Externally inspect the FLAP components:

• Tracks/rib attachment flaps (SSI 57-50-77)

ALL


• Tracks flaps (SSI 57-50-80)

ALL


• Pin and actuator lugs inboard flap (SSI 57-52-75)

ALL


• Fitting tip spar inboard flap (SSI 57-52-73)

ALL


• Pin and actuator lugs outboard flap (SSI 57-53-84)

ALL


• Center ribs attachment outboard flap (SSI 57-53-87)

ALL



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Hours:

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Cycles:



57-61-00-210-C01-A00 CORROSION Externally inspect the AILERON components:

• Hinges attachment aileron (SSI 57-61-89)

EMB-145MP

57-61-00-210-C02-A00 CORROSION Externally inspect the AILERON components:

• Spar cap aileron (SSI 57-61-91)

ALL



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Cycles:





52-10-00-220-808-A01

STRUCTURAL

Externally inspect the MAIN DOOR (SIDE-HINGED

MODEL) components:

• Stop & backup structures (SSI 52-10-03)

EMB-145MP



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52-10-00-220-809-A00 STRUCTURAL Externally inspect the MAIN DOOR (STANDARD

MODEL) components:


EMB-145MP


MODEL) components:


EMB-145MP

52-10-00-220-810-A01 STRUCTURAL Externally inspect the MAIN DOOR (SIDE-HINGED

MODEL) components:


EMB-135LR


MODEL) components:


EMB-135LR



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MODEL) components:


EMB-135LR

52-43-00-220-807-A00

STRUCTURAL

Externally inspect the SERVICE DOOR components:

• Service door stops & backup structure (SSI 52-43-13)

EMB-145MP



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52-43-00-220-808-A00 STRUCTURAL Internally inspect the SERVICE DOOR components:




EMB-145MP

52-43-00-220-811-A00 STRUCTURAL Externally inspect the SERVICE DOOR components:


EMB-135LR





EMB-135LR

52-44-00-220-801-A00 STRUCTURAL Externally inspect the REAR ELECTRONIC

COMPARTMENT DOOR components:

• Rear electronic compartment door structure

(SSI 52-44-01)

ALL



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52-44-00-220-802-A00 STRUCTURAL Internally inspect the REAR ELECTRONIC

COMPARTMENT DOOR components:

• Rear electronic compartment door structure

(SSI 52-44-01)

ALL

53-12-00-250-801-A00 STRUCTURAL Internally inspect the FUSELAGE components using

Eddy Current inspection method:

• Windshield center post including its attachment and


NOTE: Applicable to aircraft Pre-Mod. SB145-53-0058

and the inspection shall be performed on the Eyelet

fitting "Only".

ALL




EMB-135LR




EMB-145MP



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Cycles:






• Stops and backup structures for main door

(SSI 53-20-01)

EMB-135LR

53-21-00-220-803-A00 STRUCTURAL Internally inspect the FUSELAGE components:

• Stops and backup structure for main door

(SSI 53-20-01)



EMB-135LR


• Frame 15 & 18 LHS splices at stringers 3L & 16L (SSI

53-20-12)



EMB-145MP



EMB-135LR

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Hours:

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• Frames 15 & 18 LHS splices at stringers 3L & 16L

(SSI 53-20-12)

EMB-135LR


• Stringers 6 & 16 splices at frames 20 & 22 (SSI 53-20-

13)

EMB-135LR


• Stringer 6 & 16 splices at frames 20 & 22 (SSI 53-20-

13)



EMB-145MP


• Frame 15 & 18 LHS splices at stringers 3 L& 16L

(SSI 53-20-12)



EMB-135LR

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Cycles:






• Stringer 6 & 16 splices at frames 20 & 22

(SSI 53-20-13)



EMB-135LR

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Hours:

Hours:

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Cycles:






• Stops and backup structures for main door

(SSI 53-20-01)

EMB-145MP


• Stops and backup structure for main door

(SSI 53-20-01)



EMB-145MP

53-21-00-220-848-A00

STRUCTURAL



EMB-145MP

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Hours:

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Cycles:






• Frames 15 & 18 LHS splices at stringers 3L & 16L

(SSI 53-20-12)

EMB-145MP


• Stringers 6 & 16 splices at frames 20 & 22

(SSI 53-20-13)

EMB-145MP


• Passenger door cutout reinforcing structure

(SSI 53-20-09)

EMB-135LR

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53-22-00-210-801-A00

STRUCTURAL




EMB-135LR



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Engine Model:



Aircraft Model: Aircraft Serial Number: Aircraft Hours: Aircraft Landings:

APU Model: APU Serial Number: APU Hours: APU Cycles:

S48 TASKS: To be perf Tolerance equal to ± 15

ormed at every 48 Months after a 144 Months Threshold. Package Performed in: / / Days.


53-22-00-210-805-A00

STRUCTURAL


• Fuselage skin panel at stringer frames/bulkheads and

splices (SSI 53-20-07)

EMB-145MP




EMB-135LR





EMB-145MP



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Cycles:










EMB-145MP




EMB-135LR

53-24-00-210-811-A00

STRUCTURAL




EMB-145MP



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54-50-00-210-801-A00 STRUCTURAL Externally inspect the PYLON components:


EMB-145MP

54-50-00-210-802-A00 STRUCTURAL Externally inspect the PYLON components:


EMB-135LR


• FWD engine mounts including bolts (SSI 54-50-03)


EMB-145MP

EMB-135LR



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EMB-145MP

EMB-135LR

521 of 732 ALS AIRCRAFT MAINTENANCE PROGRAM


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Hours:

Hours:

Cycles:

Cycles:






• AFT Engine Mounts including bolts (SSI 54-50-07)


EMB-145MP

EMB-135LR


• Pylon Yokes III and IV (SSI 54-50-02)


EMB-145MP

EMB-135LR

521 of 732 ALS AIRCRAFT MAINTENANCE PROGRAM


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Hours:

Cycles:

Cycles:






• Pylon Yokes III and IV (SSI 54-50-02)


EMB-145MP

EMB-135LR



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Hours:

Cycles:

Cycles:






• Pylon Yokes I and II (SSI 54-50-05)


EMB-145MP

EMB-135LR

55-10-00-220-818-A00 STRUCTURAL Externally inspect the HORIZONTAL STABILIZER

component:

• Skin from rib sta. YH=350 to rib YH=990 upper

surfaces (SSI 55-10-02)

EMB-135LR


components:

• Skin from fin to sta. YH=350 - upper surface

(SSI 55-10-01)

EMB-135LR



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Cycles:

Cycles:






components:

• Skin from fin to sta. YH=350 - lower surface

(SSI 55-10-06)

EMB-135LR


• Spar 2 - brackets and rib 2A web attachments

(SSI 57-10-27)

EMB-135LR



(SSI 57-10-27)

EMB-145MP



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Hours:

Cycles:

Cycles:






• Upper skin/spar attachments (SSI 57-21-37)

EMB-145MP

EMB-135LR



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S48 TASKS 192MO THRESHOLD TOLERANCE EQUAL TO ± 15 Days



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54-50-00-230-802-A00 STRUCTURAL Internally inspect the PYLON components by Liquid Pen-

etrant Inspection Method:

• FWD Engine Mounts including bolts (SSI 54-50-03)


and the flight cycles accumulated shall be based on the

engine mount components.

EMB-145MP

EMB-135LR

ALS Edition 006 Section 03 AIRCRAFT MAINTENANCE PROGRAM


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Hours:

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Cycles:





54-50-00-250-804-A00 STRUCTURAL Internally inspect the PYLON components by the Eddy

Current method:



EMB-145MP

EMB-135LR



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Hours:

Cycles:

Cycles:





21-51-02-170-001-A00 SYSTEM Clean Dual Heat Exchanger and Visually Check Condi-

tion of Core

ALL

24-31-00-710-001-A00 SYSTEM Operationally Check Main Generation Switching Circuit ALL

24-31-00-710-002-A00 SYSTEM Operationally Check Main Generation Overcurrent Pro-

tection Circuit

ALL

24-34-00-710-001-A00 SYSTEM Operationally Check APU Generation Overcurrent Pro-

tection Circuit

ALL

24-34-00-710-002-A00 SYSTEM Operationally Check APU Generation Switching Circuit ALL

24-40-00-720-001-A00 SYSTEM Functionally Check GPU Overvoltage Protection ALL

24-60-00-710-001-A00 SYSTEM Operationally Check Electrical Emergency Transfer Cir-

cuit

ALL

30-31-00-710-001-A00 SYSTEM Operationally Check Pitot & Anemometric Static Port

Heating

ALL

30-31-00-710-002-A00 SYSTEM Operationally Check Pressurization Static Port Heating ALL

30-32-00-710-001-A00 SYSTEM Operationally Check AOA Sensor Heating ALL

30-33-00-710-001-A00 SYSTEM Operationally Check TAT Sensor Heating ALL

34-13-00-790-001-A00 CAT II Functionally Check Pitot Static System for Leakage ALL

34-13-00-790-001-A00 SYSTEM Functionally Check Pitot-Static System for Leakage


Requirements.

ALL

36-11-04-110-001-A00 SYSTEM Clean Pre-Cooler by Chemical Method ALL

38-32-10-960-001-A00 SYSTEM Replace Waste Drain Valve Cap Seal ALL



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Hours:

Cycles:

Cycles:





57-52-00-220-803-A00

STRUCTURAL

Externally inspect the FLAP components:

• Vane center fitting inboard flap (SSI 57-52-78)

EMB-145MP

EMB-135LR



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Hours:

Cycles:

Cycles:






• Vane center fitting outboard flap (SSI 57-53-85)

EMB-145MP

EMB-135LR

73-30-04-211-001-A00

SYSTEM

Visually Check the FADEC Anti-Vibration Mounts

ALL



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21-31-00-720-002-A00 SYSTEM Functionally Check Outflow Valves Pressure Relief

Devices

ALL

21-51-10-710-001-A00 SYSTEM Operationally Check Pack Leak Switch ALL

23-60-00-720-001-A00 SYSTEM Functionally Check Static Discharger ALL

25-60-05-212-001-A00 SYSTEM Inspect (General Visual) Cockpit Escape Rope P/N 120-

15112-001

ALL

26-23-04-720-001-A00 SYSTEM Functionally Check Two Way Check "Tee" Valve (Class

"C" Baggage Compartment only)

ALL

27-51-00-610-001-A01 SYSTEM Service Flap Screw-jack Actuators Gearbox Post-Mod.

SB 145-27-0118

ALL

27-62-00-720-001-A00 CMR/ANAC-FAA Functionally C h e c k G . Spoiler/Speed Brake Valves

Control Circuit and Associated Messages

ALL

28-21-10-710-001-A00

SYSTEM

Operationally Check Fuel Feed Line Shroud

ALL

28-22-03-710-001-A00 SYSTEM Operationally check APU Fuel Feed Line Shroud ALL



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Cycles:

Cycles:





30-11-05-710-001-A00 SYSTEM Operationally Check Wing Leak Thermostat ALL

32-34-03-720-001-A00 SYSTEM Functionally Check Condition and Tension of Free-Fall

Control Cables

ALL

32-44-06-720-001-A00 SYSTEM Functionally Check Thermal Relief Valve of the

Emergency/Parking Brake System

ALL

34-13-00-610-001-A00 SYSTEM Clean Pitot-Static System


Requirements.

ALL

36-20-00-720-002-A00 SYSTEM Functionally Check Differential Pressure Protection

Function Pre-Mod. SB 145-36-0018

ALL

36-20-02-710-001-A00 SYSTEM Operationally Check Thermal Switch ALL

49-62-00-710-001-A00 SYSTEM Operationally Check Emergency Shutdown by Using

APU Fuel Shutoff Switch and Fire Test Switch

ALL


MODEL) components:


ALL


MODEL) components:


ALL



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Hours:

Cycles:

Cycles:





55-10-00-220-819-A00

STRUCTURAL


ponents:

• Skin splice at upper and lower surface (SSI 55-10-16)

EMB-135LR

55-10-00-220-820-A00

STRUCTURAL


ponents:

• Rear spar center fitting (SSI 55-10-18)

EMB-135LR

55-10-00-220-821-A00

STRUCTURAL


ponents:

• Front/Rear auxiliary spar center fitting (SSI 55-10-19)

EMB-135LR



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Hours:

Cycles:

Cycles:





55-10-00-220-822-A00 STRUCTURAL Internally inspect the HORIZONTAL STABILIZER

components:

• Front spar center fittings (SSI 55-10-20)

EMB-135LR

56-10-01-720-001-A01 EMB-RECOMM Functionally Check Torque of Windshield Attaching Bolts

Post-Mod. SB 145-56-0006

NOTE: First check at 500 FH after windshield

installation.

ALL

56-10-01-720-002-A00 EMB-RECOMM Functionally Check Windshield Anti-Static Coating for

Continuity

ALL


• Lower skin - spanwise splice at spar 2 access holes

stringers integral milled panels & spanwise splice of




EMB-135LR



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Hours:

Cycles:

Cycles:






• Spar 1 - Auxiliary cap attachments & auxiliary cap

splice at wing attachments (SSI 57-10-05)



EMB-135LR


• Spar 1 - Lower skin attachments (SSI 57-10-03)



EMB-135LR


• Lower skin - Spanwise splice at spar 2 access holes



NOTE 1: During this inspection the CPCP basic task

shall also be performed for this SSI.

NOTE 2: Applicable to aircraft Pre-Mod.

SB 145-00-0032.

EMB-145MP



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Hours:

Cycles:

Cycles:






• Lower skin Spanwise splice at spar 2 access holes






0032 under ANAC/FAA Certifications.

EMB-145MP





EMB-135LR






EMB-135LR



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Section

Page



Hours:

Hours:

Cycles:

Cycles:






• Attachment center flap outboard track (SSI 57-28-68)

EMB-145MP

EMB-135LR


• Attachment lugs aileron (SSI 57-28-66)

EMB-135LR



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Section

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Hours:

Cycles:

Cycles:






• Center track and rib15 trailing edge (SSI 57-28-69)


EMB-145MP

EMB-135LR

78-10-01-212-002-A00 SYSTEM Inspect (Visual Inspection) Plain Exhaust Assy for

Damage Failure or Irregularities (for aircraft without

Thrust Reversers only)

ALL

78-31-00-220-001-A00 SYSTEM Inspect (Detailed Inspection) Thrust Reverser Structure ALL

78-34-00-710-001-A00 CMR/ANAC-FAA Operationally Check Thrust Reverser Indicating System ALL

78-34-00-710-001-A00 CMR/EASA Operationally Check Thrust Reverser Indicating System ALL



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Section

Page

s




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Hours:

Cycles:

Cycles:





26-21-05-720-001-A00 SYSTEM Functionally Check Two-Way "Tee" Check Valves ALL

57-61-00-210-801-A00 STRUCTURAL Externally inspect the AILERON components:

• Hinge attachment aileron (SSI 57-61-89)

EMB-135LR

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005 ALS Section 03

Revision

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Hours:

Cycles:

Cycles:





52-10-00-220-809-A01

STRUCTURAL

Internally inspect the MAIN DOOR (SIDE-HINGED

MODEL) components:


EMB-145MP


MODEL) components:


EMB-135LR



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Hours:

Cycles:

Cycles:





52-30-00-220-802-A00 STRUCTURAL Internally inspect the BAGGAGE DOOR components:

• Baggage door stops and fittings (SSI 52-30-09)

EMB-145MP

52-30-00-220-803-A00 STRUCTURAL Internally inspect the BAGGAGE DOOR components:

• Baggage door stops and fittings (SSI 52-30-09)

EMB-135LR





EMB-145MP

EMB-135LR



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Cycles:






• Fuselage skin panel at stringer frames/bulkheads and

splices (SSI 53-20-07)

EMB-135LR

53-24-00-210-806-A00

STRUCTURAL




EMB-135LR

53-31-00-220-838-A00

STRUCTURAL


• Rear electronic compartment door cutout structure

(SSI 53-30-49)

EMB-135LR



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nents:




EMB-145MP



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20-00-00-140-004-A00 SYSTEM Clean Center Fuselage IV Upper Side surrounding ELT

unit (Zones: 262 264).

NOTE: EWIS

ALL

20-00-00-140-009-A00 SYSTEM Clean NLG & FWD Electronic Compartments FWD Pres-

sure Bulkhead Upper Side (Zones: 113 114 213 214

215

216).

ALL

20-00-00-212-012-A00 SYSTEM Inspect (General Visual) NLG Electronic Compartment -

EWIS Components of wiring bundles (Zones: 113 114).

NOTE: EWIS

ALL

20-00-00-220-009-A00 SYSTEM Inspect (Detailed Inspection) FWD Electronic Compart-

ment/ FWD Pressure Bulkhead Upper Side - EWIS Com-

ponents of wiring bundles (Zones: 213 214 215 216).

NOTE: EWIS

ALL

21-20-00-710-001-A00 SYSTEM Operationally Check Air Conditioned Distribution System ALL

21-31-00-710-001-A00 SYSTEM Operationally Check Pressurization Control System in

Manual Mode

ALL

21-31-00-720-005-A00 SYSTEM Functionally Check Line for Leakage Post-Mod. SB 145-

21-0002.

ALL

21-51-00-720-001-A00 SYSTEM Functionally Check Cooling Pack System ALL



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21-60-00-710-001-A00 SYSTEM Operationally Check Temperature Control ALL

27-12-00-720-001-A00 SYSTEM Functionally Check Aileron Hydraulic Actuation ALL

27-15-02-640-001-A00 SYSTEM Lubricate Aileron Disconnect System

NOTE: The Plate Mechanism is Bench Lubricated.

ALL

27-35-00-640-001-A00 SYSTEM Lubricate Elevator Disconnect System

NOTE: The Plate Mechanism is Bench Lubricated.

ALL

27-51-15-220-001-A00 SYSTEM Inspect (Detailed Inspection) Flap Rollers for Structural

Integrity

ALL

27-62-00-720-001-A00 CMR/EASA Functionally Check G. Spoiler/Speed Brake Valves Con-

trol Circuit and Associated Messages

ALL

28-11-04-710-001-A00 SYSTEM Functionally Check G. Spoiler/Speed Brake Valves Con-

trol Circuit and Associated Messages

ALL

28-11-04-710-001-A00 SYSTEM Operationally Check (Manual Check for Free Movement

and Sealing Condition) Flap Valves (Ribs 1 and 7)

NOTE: Check during Internal Tank Inspection.

ALL

28-12-01-710-001-A00 SYSTEM Operationally Check (Manual Check) Vent Float Valves

(Rib 19)


ALL

28-12-04-710-001-A00 SYSTEM Operationally Check Flap Valve (Manual Check for Free

Movement and Sealing Condition)


ALL

28-21-03-720-001-A00 SYSTEM Functionally Check Relief Valve ALL

28-43-00-720-001-A00 SYSTEM Functionally Check Fuel Temperature Indication System ALL



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28-44-00-720-001-A00 SYSTEM Functionally Check Low Level Warning System


ALL

29-10-00-790-001-A00 SYSTEM Functionally Check of Hydraulic Power System for Inter-

nal Leakage

ALL

29-30-05-710-001-A00 SYSTEM Operationally Check HYD SYS OVHT Message ALL

30-12-05-710-001-A00 SYSTEM Operationally Check Horizontal Stabilizer Leak Thermo-

stat

ALL

30-31-08-710-001-A00 SYSTEM Operationally Check Pitot Lines Heater

NOTE: If installed

ALL

32-10-00-210-801-A00 STRUCTURAL Externally inspect the MAIN LANDING GEAR compo-

nents:

• Trailing arm – MLG (SSI 32-10-03)

ALL


nents:

• Strut (main fitting) – NLG (SSI 32-20-12)

ALL


nents:

• Auxiliary drag strut bottom stay (SSI 32-20-16)

ALL


nents:

• Main drag strut top stay- NLG (SSI 32-20-13)

ALL


nents:

• Auxiliary drag strut top stay- NLG (SSI 32-20-15)

ALL



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nents:

• Torque links – NLG (SSI 32-20-17)

ALL

32-32-02-710-001-A00 SYSTEM Operationally Check Solenoid and Downlock Release

Button of the Landing Gear Control Lever

ALL

32-41-01-710-001-A00 SYSTEM Operationally Check Brake Pedal Transducer ALL

32-44-00-720-001-A00 SYSTEM Functionally Check Emergency Parking Brake System ALL

36-20-00-710-001-A00 SYSTEM Operationally Check Bleed Valve Indicating Function ALL

36-20-00-720-001-A00 SYSTEM Functionally Check the Overtemperature Warning Circuit ALL


MODEL) components:

• Main door folding flap structure (SSI 52-10-02)

ALL


MODEL) components:


ALL


MODEL) components:


ALL


MODEL) components:


ALL



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Cycles:






MODEL) components:


ALL


• Service door folding flap structure (SSI 52-43-11)



ALL


• Service door window frame (SSI 52-43-12)

ALL


• Service door window frame (SSI 52-43-12)



ALL

52-Z812-213-001-A00

ZONAL


ALL

52-Z812-214-001-A00

ZONAL


ALL



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• Frames (SSI 53-10-43)

EMB-145MP

EMB-135LR




EMB-145MP

EMB-135LR



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Hours:

Cycles:

Cycles:






• Cockpit window cutout structure (SSI 53-10-18)

EMB-145MP

EMB-135LR


• Cockpit floor beams and columns (SSI 53-10-27)

EMB-145MP

EMB-135LR



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Hours:

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Cycles:






• Frames (SSI 53-10-43)

ALL





or Post-Mod. SB 145-53-0067.

ALL


• Main door attachment fittings and interface parts (SSI

53-20-04)

ALL


• Service door attachment fittings and interface parts

(SSI 53-20-05)

ALL


• Fuselage skin longitudinal splice along service door

cutout (SSI 53-20-42)

EMB-145MP



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53-21-00-220-839-A00

STRUCTURAL




EMB-145MP

53-22-00-220-802-A00

STRUCTURAL



EMB-145MP



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Hours:

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Cycles:






• Frames (SSI 53-20-43)

ALL


• Overwing fuselage skin panel (SSI 53-20-16)



EMB-145MP

EMB-135LR


• Overwing fuselage skin panel (SSI 53-20-16)

EMB-135LR



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Hours:

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Cycles:






• Overwing Fuselage skin panel (SSI 53-20-16)

EMB-145MP


• Frames (SSI 53-20-43)

ALL

53-24-00-210-804-A00

STRUCTURAL



EMB-145MP



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53-24-00-220-807-A00

STRUCTURAL


• Frames (SSI 53-20-43)

EMB-145MP



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Cycles:








EMB-145MP

EMB-135LR



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53-31-00-210-820-A00

STRUCTURAL


• Baggage compartment floor beams and columns

(SSI 53-30-28)

EMB-135LR

53-31-00-220-803-A00

STRUCTURAL


• Frames (SSI 53-30-43)

ALL



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NOTE: Remove bumper plate if installed.

EMB-145MP

EMB-135LR



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53-31-00-220-845-A00

STRUCTURAL Internally inspect the FUSELAGE components:

• Baggage door lateral L-shape (SSI 53-30-03)

EMB-135LR

53-31-00-250-801-A00

AIRWORTHINESS

LIMITATION

Externally inspect the FUSELAGE components using Eddy Current Method:

Fuselage skin panel at stringers, frames/ bulkheads, and splices (SSI 53-30-07). NOTE: Applicable to aircraft PRE-MOD SB 145-53-0080.

ALL

53-32-00-210-801-A00

STRUCTURAL Internally inspect the FUSELAGE components: - APU

mounting including its rods (SSI 53-30-40)

ALL

53-Z225-213-001-A00

ZONAL External General Visual Inspection

ALL



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NOTE: Perform at the opportunity of CPCP task 53-12-

00-220-C01-A00 accomplishment.

ALL











NOTE: EWIS

ALL




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ponents:

• Skin from fin to sta. YH=350 - lower surface

(SSI 55-10-06)

EMB-145MP


ponents:

• Skin from rib sta. YH=350 to rib sta. YH=990 - upper


EMB-145MP



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component:

• Elevator support fittings (SSI 55-10-15)

EMB-145MP

EMB-135LR


component:


ALL


components:

• Rear spar web and cap from fin to rib sta. YH=350

including center fitting/ spar attachment (SSI 55-10-12)

EMB-145MP



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components:

• Root rib (SSI 55-10-17)

ALL


component:

• Skin from rib sta. YH=350 to rib YH=990 - upper


EMB-145MP


components:

• Rear spar center fitting (SSI 55-10-18)

EMB-145MP


components:

• Skin from fin to sta. YH=350 - upper surface

(SSI 55-10-01)

EMB-145MP



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Cycles:






• Torque tube fittings (SSI 55-20-34)

ALL


• Tab wheel drive support fittings (SSI 55-20-35)

ALL

55-30-00-210-802-A00 STRUCTURAL Internally inspect the VERTICAL STABILIZER

components:

• Spar 2 (web and cap) from fuselage contour line to tip

rib sta. ZV=3015 (SSI 55-30-67)

EMB-145MP

EMB-135LR




571 of 732



Hours:

Hours:

Cycles:

Cycles:






components:


rib (SSI 55-30-68)

EMB-145MP

EMB-135LR


components:


rib including attachment bolts (SSI 55-30-63)

EMB-145MP

EMB-135LR



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Hours:

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Cycles:






components:

• Fin-to-fuselage attachment fitting to spar 3 (SSI 55-

30-54)

EMB-145MP

EMB-135LR


components:

• Fin-to-fuselage attachment fitting to auxiliary spar

41% (SSI 55-30-56)

EMB-145MP

EMB-135LR



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Hours:

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Cycles:






components:

• Fin-to-fuselage attachment fitting to bulkhead 78

(SSI 55-30-60)

EMB-145MP

EMB-135LR


components:


(SSI 55-30-61)

EMB-145MP

EMB-135LR



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components:


(SSI 55-30-62)

EMB-145MP

EMB-135LR


components:

• Fin-to-fuselage attachment fitting to spar 1

(SSI 55-30-58)

EMB-145MP

EMB-135LR



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components:


(SSI 55-30-59)

EMB-145MP

EMB-135LR


components:

• Spar 41% (web and cap) from sta. ZV=1550.5

including attachment bolts (SSI 55-30-66)

EMB-145MP

EMB-135LR



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57-41-00-220-801-A00 STRUCTURAL Internally inspect the WING LEADING EDGE

components:

• Machined rib flange (SSI 57-41-98)

ALL


components:


ALL


components:


ALL


• Fitting root spar flaps (SSI 57-50-74)

EMB-145MP

EMB-135LR



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Hours:

Hours:

Cycles:

Cycles:






• Lower skin - spanwise splice at spar 2 access holes

stringers integral milled panel & spanwise splice of inte-

gral panel (SSI 57-10-01)

EMB-145MP

EMB-135LR






NOTE 2: Applicable to aircraft Pre-Mod. SB 145-00-

0032.

EMB-145MP




NOTE 1: During this inspection, the CPCP basic task


NOTE 2: Applicable to aircraft Post- Mod. SB

145-00-0032, under ANAC/FAA Certifications

EMB-145MP



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SB 145-00-0032.

EMB-145MP





NOTE 2: Applicable to aircraft Post-Mod.

SB 145-00-0032 under ANAC/FAA Certifications.

EMB-145MP




EMB-145MP





EMB-145MP



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EMB-145MP






EMB-145MP


• Spar 2 - Auxiliary cap attachments and auxiliary cap



EMB-145MP



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Hours:

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Cycles:










EMB-145MP




EMB-135LR

57-10-00-250-801-A01 STRUCTURAL Externally inspect the WING STUB components using




ALL

57-21-00-210-804-A00 STRUCTURAL Internally inspect the WING components:


ALL



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EMB-145MP

EMB-135LR



ALL



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Hours:

Cycles:

Cycles:






• Actuator access holes (SSI 57-21-34)

EMB-145MP

EMB-135LR


• Actuator access holes (SSI 57-21-34)

EMB-145MP

EMB-135LR


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ALL



ALL



EMB-135LR



EMB-145MP


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Hours:

Cycles:

Cycles:







EMB-135LR


• Lower Skin access holes (SSI 57-21-32)

ALL




EMB-145MP



EMB-145MP

EMB-135LR



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Hours:

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Cycles:






• Lower vent hole (SSI 57-21-33)

EMB-145MP

EMB-135LR



EMB-145MP

EMB-135LR



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Hours:

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Cycles:









EMB-145MP



EMB-145MP

EMB-135LR



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Hours:

Cycles:

Cycles:






• Spar 1/leading edge attachments (SSI 57-22-43)

EMB-145MP

EMB-135LR


• Spar 1/ leading edge attachments (SSI 57-22-43)

ALL



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Hours:

Cycles:

Cycles:






• Spar 2/Wing Stub Attachments (SSI 57-23-48)

EMB-145MP

EMB-135LR


• Spar 2/web cutouts (SSI 57-23-47)

ALL


• Spar 2/web and stiffeners (SSI 57-23-45)

ALL



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Cycles:







EMB-145MP

EMB-135LR


• FWD & AFT side brace fittings - MLG (SSI 57-26-56)


EMB-145MP

EMB-135LR



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57-26-00-220-804-A00

STRUCTURAL



ALL



ALL



ALL



ALL



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Hours:

Cycles:

Cycles:







EMB-145MP

EMB-135LR


• Spar 3 Attachment torque box (SSI 57-28-63)

EMB-145MP

EMB-135LR



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Cycles:







EMB-145MP

EMB-135LR


• Spar 3 attachment torque box 2 (SSI 57-28-63)

ALL

57-28-00-210-812-A00 STRUCTURAL Externally inspect the WING components: Attachment lugs aileron (SSI 57-28-66)

EMB-135LR



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Hours:

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Cycles:







EMB-145MP

EMB-135LR



EMB-145MP

EMB-135LR



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Hours:

Cycles:

Cycles:






• Tracks/ribs attachment torque box (SSI 57-28-62)

ALL


• Ribs torque box 3 (SSI 57-28-64)

EMB-145MP

EMB-135LR




595 of 732



Hours:

Hours:

Cycles:

Cycles:






• Ribs torque box 3 (SSI 57-28-64)

EMB-145MP

EMB-135LR


• Ribs main landing gear bay (SSI 57-29-71)

ALL


• Skin/rib attachment MLGB (SSI 57-29-72)

ALL


• Roller attachment (SSI 57-50-76)

ALL


• Flap rollers and torque boxes rollers (SSI 57-50-78)

ALL



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Cycles:





57-52-00-220-802-A00 STRUCTURAL Internally inspect the FLAP components:

• Fitting tip inboard flap (SSI 57-52-73)

EMB-145MP

EMB-135LR



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Hours:

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Cycles:






• Center ribs attachment outboard flap (SSI 57-53-87)

EMB-145MP

EMB-135LR



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Hours:

Cycles:

Cycles:






• Fitting tip spar outboard flap (SSI 57-53-83)

EMB-145MP

EMB-135LR


• Fitting tip spar outboard flap (SSI 57-53-83)

EMB-145MP

EMB-135LR



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57-61-00-210-801-A00

STRUCTURAL

Externally inspect the AILERON components:

• Hinge attachment aileron (SSI 57-61-89)

EMB-135LR

57-61-00-220-801-A00

STRUCTURAL

Externally inspect the AILERON components:

• Actuator attachment aileron (SSI 57-61-90)

EMB-145MP

EMB-135LR

57-61-00-220-806-A00

STRUCTURAL

Internally inspect the AILERON components:


EMB-135LR

57-61-00-220-809-A00

STRUCTURAL


Hinge attachment aileron (SSI 57-61-89)

EMB-135LR

76-21-00-710-001-A00

SYSTEM

Operationally Check WOW input signal to FADEC

ALL



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Cycles:





76-12-01-212-001-A00 EMB-RECOMM Inspect (Visual Inspection) Resolver Attachments to the

Thrust Levers

ALL

78-33-00-720-001-A00 SYSTEM Functionally Check Thrust Reverser Control Lever

Micro switches

ALL



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Hours:

Cycles:

Cycles:





52-10-00-220-811-A00

STRUCTURAL

Externally inspect the MAIN DOOR (STANDARD

MODEL) components:


(SSI 52-10-05)

EMB-145MP

52-10-00-220-812-A00

STRUCTURAL

Internally inspect the MAIN DOOR (STANDARD

MODEL) components:


(SSI 52-10-05)

EMB-145MP



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MODEL) components:


(SSI 52-10-05)

EMB-135LR


MODEL) components:


(SSI 52-10-05)

EMB-135LR



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Cycles:





52-21-00-220-804-A00 STRUCTURAL Externally inspect the PASSENGER CABIN ESCAPE

HATCH components:

• Escape hatch structure (SSI 52-21-06)

EMB-145MP

52-21-00-220-805-A00 STRUCTURAL Internally inspect the PASSENGER CABIN ESCAPE

HATCH components:


EMB-145MP


HATCH components:

• Escape hatch window frame (SSI 52-21-07)

EMB-145MP



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52-21-00-220-807-A00 STRUCTURAL Externally inspect the PASSENGER CABIN ESCAPE

HATCH components:


EMB-135LR


HATCH components:


EMB-135LR


HATCH components:

• Escape hatch window frame (SSI 52-21-07)

EMB-135LR



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Cycles:

Cycles:






• Service door folding flap stops (SSI 52-43-14)

EMB-145MP





EMB-145MP



EMB-135LR



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EMB-135LR

53-11-00-220-801-A00 STRUCTURAL Internally inspect the FUSELAGE component:



EMB-135LR

53-11-00-220-803-A00

STRUCTURAL

Internally inspect the FUSELAGE component:



EMB-145MP



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• Forward pressure bulkhead (SSI 53-10-26)

EMB-145MP

53-11-00-220-807-A00

STRUCTURAL



EMB-135LR



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EMB-135LR



EMB-145MP

EMB-135LR



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EMB-135LR



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EMB-135LR



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EMB-145MP

EMB-135LR


• Service door cutout reinforcing structure

(SSI 53-20-10)

NOTE: Remove the bumper plate if installed.

EMB-145MP


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• Passenger door cutout reinforcing structure

(SSI 53-20-09)

EMB-145MP





EMB-135LR


• Passenger door cutout reinforcing structures

(SSI 53-20-09)



EMB-145MP

EMB-135LR


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• Service door cutout reinforcing structures

(SSI 53-20-10)



EMB-145MP

EMB-135LR


• Fuselage skin longitudinal splices along main door




EMB-135LR


• Fuselage skin longitudinal splices along service door




EMB-135LR



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EMB-145MP


• Fuselage skin panel at stringers frames/ bulkheads


EMB-145MP

EMB-135LR


• Frames (SSI 53-20-43)

EMB-135LR



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EMB-145MP



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53-21-00-220-842-A00

STRUCTURAL


• Frames (SSI 53-20-43)

EMB-145MP



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EMB-145MP






EMB-145MP


• Fuselage skin longitudinal splices along service door




EMB-145MP



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EMB-135LR




EMB-135LR





EMB-135LR



EMB-135LR



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• Service door cutout reinforcing structure

(SSI 53-20-10)

NOTE: Remove the bumper plate if installed.

EMB-135LR




EMB-135LR


• Fuselage skin longitudinal splice along service door


EMB-135LR




EMB-135LR



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EMB-145MP



EMB-135LR



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EMB-135LR




EMB-135LR




EMB-135LR




EMB-145MP


• Fuselage machined bulkhead (SSI 53-20-30)

EMB-145MP



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53-23-00-220-813-A00

STRUCTURAL





EMB-135LR



EMB-135LR



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EMB-145MP




EMB-145MP





EMB-145MP



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53-24-00-210-801-A00

STRUCTURAL




EMB-145MP

53-24-00-210-812-A00

STRUCTURAL



and splices.(SSI 53-20-07)

EMB-135LR

53-24-00-220-801-A00

STRUCTURAL




EMB-135LR



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53-24-00-220-806-A00

STRUCTURAL





EMB-145MP






EMB-145MP



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• Frames (SSI 53-20-43)

EMB-135LR




EMB-135LR


• Fuselage skin panel at pressure bulkhead

(SSI 53-30-15)

EMB-135LR



(SSI 53-30-15)

EMB-135LR



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• Baggage compartment floor beams and columns

(SSI 53-30-28)

EMB-145MP



(SSI 53-30-15)

EMB-145MP



(SSI 53-30-15)

EMB-135LR




EMB-145MP




629 of 732



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(SSI 53-30-15)

EMB-145MP



(SSI 53-30-15)

EMB-135LR




EMB-135LR






EMB-135LR



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TASK NUMBER SMRD SECTION TASK DESCRIPTION EFFECTIVITY MECH. SIGN. INSP. SIGN. 53-31-00-220-811-A00

STRUCTURAL



EMB-135LR


• Fuselage to vertical stabilizer spar attachment fitting

(SSI 53-30-38)

EMB-135LR





EMB-145MP



(SSI 53-30-49)



EMB-145MP



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• Frames (SSI 53-30-43)

EMB-135LR

53-31-00-220-840-A00

STRUCTURAL



(SSI 53-30-49).

EMB-145MP

53-31-00-220-842-A00

STRUCTURAL



(SSI 53-30-49)



EMB-135LR



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EMB-135LR




EMB-145MP

53-31-00-220-847-A00

STRUCTURAL






EMB-145MP



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(SSI 53-30-15)

EMB-145MP



EMB-145MP



(SSI 53-30-38)

EMB-145MP



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53-31-00-220-855-A00

STRUCTURAL


• Frames (SSI 53-30-43)

EMB-145MP



(SSI 53-30-38)

EMB-135LR


• Tail cone access door cutout structure (SSI 53-30-50)

EMB-135LR



EMB-135LR



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(SSI 53-30-38)

EMB-145MP



EMB-145MP



EMB-145MP



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• Pylon spars I II III and IV (SSI 54-50-01)



EMB-135LR


• Pylon spars I II III and IV (SSI 54-50-01)



EMB-145MP


components:

• Skin from rib sta. YH=350 to rib sta. YH=990 - upper


EMB-135LR



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55-10-00-220-837-A00 STRUCTURAL

Internally inspect the HORIZONTAL STABILIZER

components:

• Rear spar web and cap from fin to rib sta. YH=350

including center fitting/spar attachment (SSI 55-10-12)

EMB-135LR



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55-30-00-210-801-A00

STRUCTURAL

Internally inspect the VERTICAL STABILIZER

components:

• Rear spar actuator support fitting (elevator)

(SSI 55-30-77)

EMB-135LR


components:

• Rear spar actuator support fitting (elevator)

(SSI 55-30-77)

EMB-145MP



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components:

• Fin-to-horizontal stabilizer attachment fitting to spar 3

(SSI 55-30-50)

EMB-135LR


components:

• Spar 1 - tip rib attachment (SSI 55-30-53)

EMB-135LR

55-30-00-220-803-A00 STRUCTURAL Externally inspect the VERTICAL STABILIZER

components:

• Rudder hinge fittings (SSI 55-30-78)

EMB-135LR


components:


EMB-135LR



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components:

• Fin-to-horizontal stabilizer attachment fitting to

auxiliary spar 52% (SSI 55-30-51)

EMB-135LR


components:



EMB-135LR


components:

• Tip rib (SSI 55-30-69)

EMB-135LR



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components:



EMB-145MP


components:

• Fin-to-horizontal stabilizer attachment fitting to spar 3

(SSI 55-30-50)

EMB-145MP


components:



EMB-145MP



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EMB-145MP


components:

• Spar 1 - tip rib attachment (SSI 55-30-53)

EMB-145MP


components:

• Tip rib (SSI 55-30-69)

EMB-145MP



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55-30-00-220-841-A00

STRUCTURAL

Externally inspect the VERTICAL STABILIZER

components:

• Rudder hinge fittings (SSI 55-30-78)

EMB-145MP



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(SSI 57-10-27)

EMB-135LR



(SSI 57-10-27)

EMB-145MP



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EMB-145MP



EMB-135LR



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57-10-00-220-833-A00

STRUCTURAL






SB 145-00-0032.

EMB-145MP







EMB-145MP





EMB-135LR



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57-10-00-250-801-A00

STRUCTURAL

Externally inspect the WING STUB components using



NOTE : Applicable to aircraft Pre-Mod. SB 145-57-0047.

ALL


• Lower skin - rear fitting-to-skin attachments and spars

1 & 2 - stub-to-wing attachments (SSI 57-11-17)

EMB-135LR

57-11-00-220-809-A00

STRUCTURAL


• Fuselage bulkhead at frame 50 and its attachments to

frame 50 (SSI 57-11-25)



EMB-135LR



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57-11-00-220-814-A00

STRUCTURAL


• Spar 1 - lower front fitting attachments and spar 2 -

lower rear fitting attachments (SSI 57-11-18)

EMB-145MP

57-11-00-220-816-A00

STRUCTURAL


• Spar 2 - Titanium fitting attachments and fuselage

bulkhead at frame 46 (SSI 57-11-20)

EMB-135LR



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EMB-135LR


• Spar 3 and rib 4 rod-end link (SSI 57-11-22)



EMB-135LR


• Spar 2 -Titanium fitting attachments and fuselage

bulkhead attachments at frame 46 (SSI 57-11-20)



EMB-135LR



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57-11-00-220-824-A00

STRUCTURAL


• Spar 3 - Fuselage bulkhead attachments at frame 50

L - shape fuselage frame 50 attachments & fuselage

stringers attachments (SSI 57-11-21)



EMB-135LR


• Spar 1 - Titanium fitting attachments fuselage

bulkhead attachments at frame 40 L - shape fuselage

frame 40 attachments & fuselage stringers attachments

(SSI 57-11-19)



EMB-135LR

ALS



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• Spar 1 - Lower front fitting attachments and spar 2 -




EMB-135LR

57-11-00-220-831-A00

STRUCTURAL


• Spar 1 - Lower front fitting attachments and spar 2 -




EMB-145MP

ALS



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57-11-00-220-834-A00

STRUCTURAL


• Fuselage bulkhead attachments to frame 46

(SSI 57-11-24)



EMB-135LR

ALS



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• Spar 1 - lower front fitting attachments and spar 2 -




EMB-135LR






EMB-145MP




EMB-145MP

ALS



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57-11-00-220-843-A00

STRUCTURAL



bulkhead attachments at frame 40 L - shape fuselage


(SSI 57-11-19)



EMB-145MP



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• Spar 2 -Titanium fitting attachments and fuselage

bulkhead attachments at frame 46 (SSI 57-11-20)



EMB-145MP


• Spar 2 - Titanium fitting attachments and fuselage

bulkhead at frame 46 (SSI 57-11-20)

EMB-145MP



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EMB-145MP


• Spar 3 and rib 4 rod-end link (SSI 57-11-22)



EMB-145MP



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(SSI 57-11-24)



EMB-145MP



(SSI 57-11-24)



EMB-145MP



frame 50 (SSI 57-11-25)



EMB-145MP


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• Lower skin/spar attachments

(SSI 57-21-36)

EMB-135LR



ALL



EMB-145MP



EMB-135LR


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EMB-135LR



EMB-145MP



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57-21-00-220-804-A00

STRUCTURAL



EMB-145MP

EMB-135LR



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57-21-00-220-819-A00

STRUCTURAL



EMB-145MP



EMB-135LR

57-22-00-210-805-A00

STRUCTURAL


• Spar 1 cap (SSI 57-22-41)

EMB-135LR



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• Spar 1 cap (SSI 57-22-41)

EMB-145MP


• Spar 2 cap (SSI 57-23-46)

EMB-135LR



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• Spar 2 cap (SSI 57-23-46)

EMB-145MP



EMB-135LR



EMB-135LR



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EMB-145MP



EMB-145MP



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• Spar 3 cap (SSI 57-24-50)

EMB-145MP

57-28-00-220-804-A00

STRUCTURAL



EMB-135LR



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57-28-00-220-813-A00

STRUCTURAL



EMB-145MP



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28-21-01-220-001-A00 FUEL SYS LIMIT Inspect Electric Fuel Pump Connector ALL 28-41-01-720-001-A01

FUEL SYS LIMIT

Functional Check of the Safe Life Features of the Fuel

Conditioning Unit (FCU):

• Initial Functional Check;

• External Visual Inspection;

• Internal Visual Inspection;

• Functional Check of the Safe-Life Feature;

• Final Functional Check.

NOTE: The flight hours accumulated shall be based on

the fuel conditioning unit component.

ALL



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28-50-01-220-001-A00 SYSTEM Inspect (Detailed Inspection) Fuel Pump Electrical

Harness

NOTE: This task complies with Fuel Tank Ignition Source

Prevention (SFAR 88).

ALL

28-50-02-220-001-A00 SYSTEM Inspect (Detailed Inspection) Wing Tank Unit

NOTE: This task complies with Fuel Tank Ignition Source

Prevention (SFAR 88).

ALL

28-50-04-212-001-A00

SYSTEM

Inspect (General Visual) Wing Stub Harnesses

NOTE: EWIS/SFAR 88.

ALL

28-50-05-212-001-A00 SYSTEM Inspect (General Visual) Trailing Edge Harnesses

NOTE: EWIS/SFAR 88.

ALL

28-50-06-212-001-A00 SYSTEM Inspect (General Visual) Leading Edge Harnesses

NOTE: EWIS/SFAR 88.

ALL

33-50-12-280-001-A00 SYSTEM Inspect Photo luminescent Floor Proximity Strip Lights

Using Test Sample

NOTE: If installed

ALL

52-10-00-220-C01-A01 CORROSION Internally inspect the MAIN DOOR (SIDE-HINGED

MODEL) components:


(SSI 52-10-05)

ALL



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52-10-00-220-C04-A01 CORROSION Internally inspect the MAIN DOOR components:

• Window frame (SSI 52-10-06)

NOTE: Applicable to side-hinged door only.

ALL

52-30-00-210-C02-A00 CORROSION Internally inspect the BAGGAGE DOOR components:

• Baggage door structure (SSI 52-30-08)

ALL

52-43-00-220-C02-A00 CORROSION Internally inspect the SERVICE DOOR components:

• Service door-to-fuselage attachment fittings &


ALL


• Bulkhead 1 structure (SSI 53-10-23)

ALL


• Battery compartment cutout structure (SSI 53-10-44)

ALL


• Hydraulic compartment cutout structure

(SSI 53-10-45)

ALL


• Longerons (SSI 53-10-46)

ALL




ALL



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• Fuselage skin Circumferential splice (SSI 53-10-14)

ALL



(SSI 53-10-15)

ALL


• Frames (SSI 53-10-43)

ALL


• Windshield panel (SSI 53-10-21)

ALL


• Cockpit window rear post and its attachment

(SSI 53-10-22)

EMB-145MP

EMB-135LR



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ALL



ALL



ALL


• Cockpit floor beams and columns (SSI 53-10-27)

ALL



(SSI 53-10-15)

ALL


• Frames (SSI 53-10-43)

ALL


• Maintenance door cutout structure (SSI 53-10-49)

ALL


• Baggage door lateral L-shape (SSI 53-30-03)

EMB-145MP



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Cycles:






• Wing stub - lower skin - rib 2A attachment

(SSI 57-01-15)

ALL


• Wing stub - lower skin - rib 2A attachment

(SSI 57-01-15)

EMB-145MP

EMB-135LR


• Wing stub - Spar 2 - brackets ribs 2A attachments

(SSI 57-01-17)

EMB-145MP

EMB-135LR


• Wing stub - spar 1 - brackets ribs 2A attachments

(SSI 57-01-16)

ALL



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• Upper skin - tire compartment composite panel

(SSI 57-10-14)

ALL


• Upper skin - rib 1 attachments and spanwise splice of


EMB-145MP

EMB-135LR



ALL



ALL


• Lower vent hole (SSI 57-21-33)

ALL



ALL


• Upper skin/spar attachment (SSI 57-21-37

ALL



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• Lower skin/wing stub attachment (SSI 57-21-38)

ALL


• Gravity fuel hole (SSI 57-21-35)

ALL



ALL



EMB-145MP



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• Ribs main box (SSI 57-25-53)

EMB-145MP

EMB-135LR


• Lower skin/rib attachment (SSI 57-25-54)

ALL


• Upper skin/rib attachment (SSI 57-25-55)

ALL



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57-26-00-250-813-A03 STRUCTURAL Externally inspect the WING components using Eddy

Current inspection method:


NOTE 1: Applicable only to trunnion P/N

145-67014-011/012.



EMB-145MP



ALL



ALL


• Tracks/ribs attachment torque box (SSI 57-28-62)

ALL


• Tracks/rib attachment torque box 3 (SSI 57-28-65)

ALL

73-11-10-130-001-A01 SYSTEM Clean Fuel Nozzles P/N 23075904 P/N 23077006 and

P/N 23087207

ALL

79-25-02-211-001-A00 SYSTEM Visually Check Fuel Cooled Assembly (FCOC) ALL

79-27-00-211-001-A00 SYSTEM Visually Check Oil Plumbing ALL

79-34-01-720-001-A00 SYSTEM Functionally Check Indicating Magnetic Plug Assembly ALL



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79-37-00-720-001-A00 SYSTEM Functionally Check Oil Filter Impending Bypass

Indicating System

ALL




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• Windshield lateral post and its attachment

(SSI 53-10-20)

EMB-135LR



(SSI 53-10-20)

EMB-145MP


• Bulkhead-to-engine pylon attachment (SSI 53-30-35)



EMB-135LR



Issued 03June2015 EMBRAER 135LR AND ERJ145MP AIRCRAFT 681 of 732



Hours:

Hours:

Cycles:

Cycles:






• Bulkhead-to-engine pylon attachment (SSI 53-30-35)



EMB-145MP

54-50-00-250-802-A00 STRUCTURAL Internally inspect the PYLON components by the Eddy

Current method:

• Pylon Yokes I and II upper flange (SSI 54-50-06)

NOTE: Applicable to aircraft Pre-Mod. SB145-54-0008

EMB-145MP

EMB-135LR



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21-26-08-960-001-A01 SYSTEM Discard Exhaust Hoses of the Electronic Bay Compart-

ment Post-Mod. SB 145-21-0013

ALL

32-20-01-720-001-A00 SYSTEM Functionally Check NLG Leg for Centering Cam Play

NOTE: Perform at the opportunity of NLG Leg Strut

Restoration.

ALL

53-31-00-210-824-A00 AIRWORTHINESS LIMITATION


• Fuselage skin panel at stringers, frames/ bulkheads, and splices (SSI 53-30-07) NOTE: Applicable to aircraft PRE-MOD

SB 145-53-0081.





EMB-135LR



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EMB-145MP


components:

• Skin splice at upper and lower surface (SSI 55-10-16)

EMB-145MP



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57-11-00-220-829-A00

STRUCTURAL



frame 40 (SSI 57-11-23)



EMB-135LR



frame 40 (SSI 57-11-23)



EMB-135LR



(SSI 57-11-24)



EMB-135LR


Hinge attachment, aileron (SSI 57-28-66)

EMB-135LR



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28-11-00-720-001-A00 FUEL SYS LIMIT Functionally Check critical bonding integrity of selected

conduits inside the wing tank Fuel Pump and FQIS

connectors at tank wall by conductivity measurements

ALL

28-23-03-220-001-A00

FUEL SYS LIMIT

Inspect Pilot Valve harness inside the conduit

ALL

28-23-04-220-001-A00 FUEL SYS LIMIT Inspect Vent Valve harness inside the conduit ALL

28-41-03-220-001-A00 FUEL SYS LIMIT Inspect FQIS harness for clamp and wire jacket integrity ALL


• Service door folding flap structure (SSI 52-43-11)

ALL

53-12-00-210-802-A00

STRUCTURAL



(SSI 53-10-19)


EMB-135LR

53-12-00-220-808-A02

STRUCTURAL





EMB-135LR



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53-12-00-220-818-A00

STRUCTURAL




NOTE: Applicable to aircraft Post -Mod.

SB 145-53-0007.

EMB-145MP

53-12-00-250-801-A01 STRUCTURAL Internally inspect the FUSELAGE components using




NOTE: Applicable to aircraft Post-Mod. SB145-53-0058

and the inspection shall be performed on the Eyelet

fitting "Only".

ALL

53-12-00-250-802-A00 STRUCTURAL Externally inspect the FUSELAGE components using Eddy Current method:


(SSI 53-10-20)


ALL

53-12-00-250-802-A01 STRUCTURAL Externally inspect the FUSELAGE components using Eddy Current method:


(SSI 53-10-20)


ALL



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53-12-00-250-803-A00 STRUCTURAL Internally inspect the FUSELAGE components using Eddy Current method:


(SSI 53-10-20)


ALL



EMB-135LR



(SSI 53-30-38)



ALL



EMB-145MP



EMB-135LR



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53-31-00-220-850-A00 STRUCTURAL Internally inspect the FUSELAGE components using Eddy Current method:


EMB-145MP

53-31-00-250-802-A00 AIRWORTHINESS LIMITATION

Externally inspect the FUSELAGE components using Eddy Current method:

• Fuselage skin panel at stringers, frames/ bulkheads, and splices (SSI 53-30-07). NOTE: Applicable to aircraft POST-MOD SB 145-53-0080.



EMB-135LR



EMB-145MP



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54-50-00-220-812-A00

STRUCTURAL

Internally inspect the PYLON components:



EMB-145MP

EMB-135LR

54-50-00-220-812-A01

STRUCTURAL

Internally inspect the PYLON components:



SB 145-54-0011 and Post-Mod. SB 145-54-0013.

EMB-145MP

EMB-135LR

54-50-00-250-802-A01

STRUCTURAL

Internally inspect the PYLON components by the Eddy

Current method:

• Pylon Yokes I and II upper flange (SSI 54-50-06)

NOTE: Applicable to aircraft Post-Mod. SB145-54-0008

EMB-145MP

EMB-135LR



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Cycles:






components:

• Front/Rear auxiliary spar center fitting (SSI 55-10-19)

EMB-145MP


components:

• Front spar center fittings (SSI 55-10-20)

EMB-145MP


components:

• Front and rear auxiliary spar webs and caps including

center fitting/spar attachment (SSI 55-10-11)

EMB-145MP



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55-10-00-220-835-A00

STRUCTURAL

Internally inspect the HORIZONTAL STABILIZER

components:

• Front and rear auxiliary spar webs and caps including

center fitting/spar attachment (SSI 55-10-11)

EMB-135LR

55-10-00-240-801-A00

STRUCTURAL

Externally inspect the HORIZONTAL STABILIZER

components by the magnetic particle inspection method:

• Pin internal and external hinge stabilizer

(SSI 55-10-24)

EMB-135LR

55-10-00-240-802-A00

STRUCTURAL

Externally inspect the HORIZONTAL STABILIZER



(SSI 55-10-24)


EMB-145MP



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(SSI 55-10-24)



EMB-145MP


components by the eddy current inspection method:


EMB-135LR





EMB-145MP



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EMB-145MP


components:

• PCU support fittings (SSI 55-30-80)

EMB-135LR


components:

• PCU support fittings (SSI 55-30-80)

EMB-145MP



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Section

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components:

• Fin-to-fuselage attachment fitting to auxiliary spar

52% (SSI 55-30-55)

EMB-145MP

EMB-135LR


components:


bolt (SSI 55-30-75)

EMB-135LR


components:

• Actuator support fittings (rudder) (SSI 55-30-79)

EMB-135LR



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Section

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components:

• Fin-to-fuselage attachment fitting to spar 2

(SSI 55-30-57)

EMB-145MP

EMB-135LR


components:

• Spar 52% (web and cap) from fuselage contour line to

tip rib including attachment bolts (SSI 55-30-64)

EMB-145MP

EMB-135LR



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components:

• Spar 41% (web and cap) from sta. ZV=2538 to tip rib

including attachment bolts (SSI 55-30-65)

EMB-145MP

EMB-135LR


components:


bolt (SSI 55-30-75)

EMB-145MP



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components:

• Actuator support fittings (rudder) (SSI 55-30-79)

EMB-145MP

55-30-00-250-801-A00

STRUCTURAL

Externally inspect the VERTICAL STABILIZER



EMB-135LR



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EMB-145MP






EMB-145MP



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bulk head attachments at frame 40 L - shape fuselage


(SSI 57-11-19)

EMB-135LR



frame 50 (SSI 57-11-25)



EMB-135LR







EMB-135LR




702 of 732



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bulkhead attachments at frame 40 L shape fuselage


(SSI 57-11-19)

EMB-145MP







EMB-145MP



frame 40 (SSI 57-11-23)



EMB-145MP



frame 40 (SSI 57-11-23)

EMB-145MP




703 of 732



Hours:

Hours:

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Cycles:







frame 50 (SSI 57-11-25)



EMB-145MP

57-11-00-250-801-A00 STRUCTURAL Internally inspect the WING STUB components by using

Eddy Current Inspection Method:



ALL

57-21-00-250-802-A00 STRUCTURAL Externally inspect the WING components by using Eddy

Current method:


EMB-135LR


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Current method:



EMB-145MP


Current method:




EMB-145MP



ALL



EMB-135LR



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EMB-145MP

57-22-00-250-803-A00 STRUCTURAL Externally inspect the WING components by Using Eddy

Current Inspection Method:


EMB-145MP

EMB-135LR



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• FWD & AFT side brace fittings (SSI 57-26-56)

EMB-145MP

EMB-135LR




NOTE: Applicable only to trunnion P/N 145-67014-

001/002/003/004/ 005/006/007/008.

EMB-135LR





011/012.

EMB-135LR



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009/010/013/014.

EMB-135LR




EMB-135LR

57-26-00-250-810-A00

STRUCTURAL

Externally inspect the WING components using Eddy



EMB-135LR



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57-26-00-250-812-A00

STRUCTURAL

Externally inspect the WING components using Eddy




EMB-145MP






EMB-145MP




NOTE 1: Applicable only to trunnion P/N 145-67014-

001/002/ 003/004/005/006/007/008.


0032.

EMB-145MP



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001/002/ 003/ 004/005/006/007/008.



EMB-145MP





011/012.


0032.

EMB-145MP





009/010/ 013/014.


0032.

EMB-145MP



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009/010/ 013/014.



EMB-145MP





EMB-145MP






EMB-145MP



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57-28-00-250-803-A00

STRUCTURAL

Externally inspect the WING components by the Eddy



ALL


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57-28-00-250-804-A00 STRUCTURAL Internally inspect the WING components by the Eddy



ALL

57-28-00-250-805-A00 STRUCTURAL Externally inspect the WING components by the Eddy


• Flap track torque box (SSI 57-28-59)

EMB-145MP

EMB-135LR


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57-28-00-250-806-A00 STRUCTURAL Externally inspect the WING components by the Eddy



EMB-145MP

EMB-135LR

57-28-00-250-807-A00 STRUCTURAL Internally inspect the WING components by the Eddy



EMB-145MP

EMB-135LR



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Cycles:






• Fitting root spar flaps (SSI 57-50-74)

EMB-145MP

EMB-135LR

57-50-00-240-801-A00 STRUCTURAL Externally inspect the FLAP components by the

Magnetic Particle Inspection Method:

• Flap rollers and Torque boxes rollers (SSI 57-50-78)

ALL

57-50-00-250-801-A00 STRUCTURAL Externally inspect the FLAP components by the Eddy


• Roller attachment (SSI 57-50-76)

ALL



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57-50-00-250-802-A00 STRUCTURAL Externally inspect the FLAP components by the Eddy


• Tracks flaps (SSI 57-50-80)

EMB-145MP

EMB-135LR



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Cycles:






• Ribs/skin attachment inboard flap (SSI 57-52-79)

EMB-145MP

EMB-135LR



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Cycles:






• Ribs/skin attachment outboard flap (SSI 57-53-86)

EMB-145MP

EMB-135LR

57-61-00-220-802-A00 STRUCTURAL Internally inspect the AILERON components:


EMB-145MP



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PRIOR WINTER TASKS TOLERANCE IS NOT APPLICABLE



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PRIOR WINTER TASKS: To be performed once a year, prior to the winter season. Package Performed in: / / Tolerance is Not Applicable


30-11-05-710-001-A00 EMB-RECOMM Operationally Check Wing Leak Thermostat ALL

30-12-00-710-001-A00 EMB-RECOMM Operationally Check Electrical Hardware of the

Horizontal Stabilizer Thermal Anti-icing System

ALL

30-12-05-710-001-A00 EMB-RECOMM Operationally Check Horizontal Stabilizer Leak

Thermostat

ALL

30-20-00-220-001-A00 EMB-RECOMM Inspect (Detailed Inspection) Thermal Anti-ice (Tai)

Exhaust Duct for Condition and Security of Installation

ALL

30-20-01-720-001-A00 EMB-RECOMM Functionally Check Thermal Anti-ice (Tai) Interbulkhead

Assembly for Leakage

ALL

30-31-00-710-002-A00 EMB-RECOMM Operationally Check Pressurization Static Port Heating ALL

30-42-00-710-001-A00 EMB-RECOMM Operationally Check Windshield Heating ALL

52-21-00-710-001-A00 EMB-RECOMM Operationally Check Passenger Cabin Escape Hatch

Mechanism

ALL



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COMPONENT LIMITED TASKS

AVAILABLE TOLERANCE IS DESCRIBED IN EACH TASK



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COMPONENT LIMITED TASKS: To be performed based on each component limitation. Package Performed in:__/ / Available tolerance is described in each task.

TASK NUMBER SMRD SECTION TASK DESCRIPTION EFFECTIVITY INT TOLERANCE MECH. SIGN. INSP. SIGN.

23-71-02-960-001-A00 SYSTEM Discard CVR Underwater Locator Beacon Battery

(*) NOTE: ULB battery change in accordance with

manufacturer's data plate expiration date.

ALL (*) See

description

note

N/A

24-31-01-900-001-A00 SYSTEM Restore Main Generator P/N 30086-010 ALL 60 MO

or

3200 FH

N/A

24-31-01-900-001-A01 SYSTEM Restore Main Generator P/N 30086-011 ALL 60 MO

or

4000 FH

N/A

24-34-01-900-001-A00 SYSTEM Restore APU Starter/Generator ALL 48 MO

or

1200 AH

N/A

24-34-01-900-002-A00 EMB-RECOMM Restore APU Starter/Generator ALL 48 MO

or

800 AH

± 30 Days

24-34-01-960-001-A00 SYSTEM Discard APU Starter/Generator Brushes ALL 800 AH N/A

24-35-01-900-001-A00 SYSTEM Restore Back-up Battery ALL 12 MO N/A

24-36-01-900-001-A00 SYSTEM Restore Main Battery SAFT P/N 442CH1 ALL 12 MO N/A

25-60-00-212-001-A00 SYSTEM Inspect (General Visual) First Aid Kit and Medical

Kit for condition and Validation P/N 106 A 6240-

37 S6-0005-311 S6-01-0005-31470004-00 01-

00-48 25-60-109-2 25-60-109SL 01-70-90 LAI

5532 4531 and 73S601005107

ALL 6 MO ± 15 Days



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25-60-02-900-001-A00 SYSTEM Restore Flotation Vest PN 3505-101CW 3505-

101W 3500-111W and 2000-105Y

NOTE: In accordance with expiration date or

Local Regulatory Authority Requirements.

ALL 24 MO N/A

25-60-02-900-001-A01 SYSTEM Restore Flotation Vest PN MK3

NOTE: Every 24 MO after 120 MO from date of

manufacture; every 12 MO after 168 MO from

date of manufacturer; in accordance with expira-

tion date or Local Regulatory Authority Require-

ments.

ALL 48 MO N/A

25-60-02-900-001-A02 SYSTEM Restore Flotation Vest PN MK20SV and MK22SV

NOTE: Every 12 MO after 240 MO from date of

manufacture; in accordance with expiration date

or Local Regulatory Authority Requirements.

ALL 120 MO N/A

25-60-02-900-001-A03 SYSTEM Restore Flotation Vest PN 63600-501 (Vacuum

Packed)

NOTE: Every 60 MO for sewn packed; in

accordance with expiration date or Local Regula-

tory Authority Requirements.

ALL 120 MO N/A

25-60-02-900-001-A04 SYSTEM Restore Flotation Vest PN 35-21-02

NOTE: In accordance with expiration date or

Local Regulatory Authority Requirements.

ALL 12 MO N/A

25-60-04-960-001-A00 SYSTEM Discard of Megaphone Batteries

P/N A CR/EM-1A

ALL 12 MO N/A



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25-61-04-960-001-A00 SYSTEM Replace ELT battery ARTEX P/N 452-0130

NOTE: ELT battery change in accordance with

manufacturer data plate expiration date or Local


ALL 26 MO N/A

25-61-04-960-001-A01 SYSTEM Replace ELT batteries SOCATA P/Ns

ELT90A2560102000 and L94

NOTE: ELT batteries change in accordance with



ALL 48 MO N/A

25-61-04-960-001-A02 SYSTEM Replace ELT battery ARTEX P/N 452-0133

NOTE: ELT battery change in accordance with



ALL 60 MO N/A

25-63-02-960-001-A00 NATIONAL REQ Discard Portable ELT Battery ELTA P/N

05N62123

NOTE: Portable ELT Battery change in

accordance with manufacturer data plate expira-

tion date or local Regulatory Authority Require-

ments.

ALL 60 MO N/A

26-21-02-280-001-A00 SYSTEM Inspect Engine Fire Extinguishing Bottle for

Weight and Check Bottle Pressure

NOTE: Or in accordance with Local Regulatory


ALL 12 MO ± 15 Days



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COMPONENT LIMITED TASKS: To be performed based on each component limitation. Package Performed in: /__/ Available tolerance is described in each task.


26-21-02-720-001-A00 SYSTEM Perform Hydrostatic Check of the Engine Fire

Extinguishing Bottle

ALL 60 MO N/A

26-21-03-720-001-A00 SYSTEM Functionally Check Engine Fire Extinguishing

Bottle Pressure Switch

NOTE: Check at each Bottle Hydrostatic Test

(60 MO).

ALL 60 MO N/A

26-21-04-960-001-A00 SYSTEM Discard Engine Fire Extinguishing Bottle

Cartridges

NOTE: Or in accordance with manufacturer’s

recommendation.

ALL 72 MO N/A

26-22-01-280-001-A00 SYSTEM Inspect APU Fire Extinguishing Bottle for Weight

and Check Bottle Pressure




26-22-01-720-001-A00 SYSTEM Perform Hydrostatic Check of APU Fire

Extinguishing Bottle

ALL 60MO N/A

26-22-02-720-001-A00 SYSTEM Functionally Check APU Fire Extinguishing Bottle

Pressure Switch

NOTE: Check at each Bottle Hydrostatic Test (60

MO).

ALL 60MO N/A

26-22-03-960-001-A00 SYSTEM Discard APU Fire Extinguishing Bottle Cartridges

NOTE: Or in accordance with manufacturer's

recommendation.

ALL 72MO N/A



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26-23-01-280-001-A00 SYSTEM Inspect Baggage Compartment Fire

Extinguishing Bottles (High Rate and Metering)

for Weight (Class "C" Baggage Compartment

only)

ALL 12MO ± 15 Days

26-23-01-720-001-A00 SYSTEM Perform Hydrostatic Check of Baggage Compart-

ment Fire Extinguishing Bottles (High Rate and

Metering)

ALL 60MO N/A

26-23-02-960-001-A00 SYSTEM Discard Baggage Compartment Fire

Extinguishing Bottles (High Rate and Metering)

Cartridges (Class "C" Baggage Compartment

only)

NOTE: 180 months from date of manufacture

(DOM) or 120 months from date of installation

whichever occurs first.

ALL 120MO N/A

26-24-00-280-001-A00 SYSTEM Inspect Portable Fire Extinguishing Bottle for

Weight (see Placard attached to the Bottle)



ALL 12MO N/A

26-24-01-720-001-A00 SYSTEM Perform Hydrostatic Check of Portable Fire

Extinguishing Bottles P/N 892480



ALL 60MO N/A



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26-24-01-720-001-A01 SYSTEM Perform Hydrostatic Check of Portable Fire

Extinguishing Bottles P/N 100-9750 466090

898052 A352 Series and C352 Series



ALL 144MO N/A

26-25-01-280-001-A00 SYSTEM Inspect Lavatory Fire Extinguisher Bottle for

Weight

ALL 12MO N/A

29-10-04-900-001-A00 SYSTEM Replace EMDP Brushes ALL 6000FH N/A

31-31-02-960-001-A00 SYSTEM Discard FDR Underwater Locator Beacon Battery

(*) NOTE: ULB battery change in accordance with

manufacturer’s data plate expiration date.

ALL (*) See

description

note

N/A

32-10-01-900-001-A00 SYSTEM Restore Main Landing Gear (MLG) Leg Strut Assy

(PNs 2309-2002-Series 2309-3002-Series 2309-

3100-Series and 2309-4002-Series).


ALL 144 MO

or

20000 FC

± 60 Days

32-10-01-900-002-A00 SYSTEM Restore MLG Trailing Arm Assy

(PNs 2309-2037-Series 2309-3037-Series and

2309-4037-Series) including wheel axle.


ALL 144 MO

or

20000 FC

± 60 Days

32-10-02-900-001-A00 SYSTEM Restore MLG Shock Absorber Assy

(PNs 2309-2005-Series)


ALL 144 MO

or

20000 FC

± 60 Days



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32-10-03-900-001-A00 SYSTEM Restore MLG Secondary Side Strut Assy

(PNs 2309-2600-Series)


ALL 144 MO

or

20000 FC

± 60 Days

32-10-04-900-001-A00 SYSTEM Restore MLG Secondary Side Strut Assy

(PNs 2309-

2600-Series)

NOTE: Or 20000 FC, whichever occurs first

all

32-20-01-900-001-A00 SYSTEM Restore Nose Landing Gear (NLG) Strut

(PNs 1170B0000-Series; 1170C0000-Series;

2233A0000-Series; and 2666A0000-Series)

including Torque Link Steering Cuff Sliding Tube

and Web Assy components; and their attaching

parts



32-20-02-900-001-A00 SYSTEM Restore NLG Main Drag Strut

(PNs 1172B0000-Series and 1172C0000-Series)



32-20-03-900-001-A00 SYSTEM Restore NLG Auxiliary Drag Strut

(PNs 1173B0000-Series)



32-49-02-220-001-A00 SYSTEM Inspect (Detailed Inspection) of Wheels Speed

Transducer Clip in the Hub Cap Drive Clip

(*) NOTE: At each Tire change.

ALL (*) See

description

note

N/A



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32-49-03-220-001-A00 SYSTEM Inspect (Detailed Inspection) of Brake Wear

Indicator

(*) NOTE: At each Tire change.

ALL (*) See

description

note

N/A

32-49-07-710-001-A00 SYSTEM Operationally Check Brake Shuttle Valve

(*) NOTE: At each Brake replacement.

ALL (*) See

description

note

34-01-00-720-001-A00 CAT II Functionally Check Integrated Standby

Instrument – ISIS



ALL 5000 FH N/A

34-01-00-720-001-A00 SYSTEM Functionally Check Integrated Standby

Instrument System – ISIS



ALL 5000 FH N/A

34-11-00-720-001-A00 CAT II Functionally Check Standby Altimeter Indicator



ALL 24 MO

or

5000 FH

N/A

34-11-00-720-001-A00 SYSTEM Functionally Check Standby Altimeter Indicator



ALL 5000 FH N/A

34-12-00-720-001-A00 CAT II Functionally Check Standby Airspeed Indicator



ALL 24 MO

or

5000 FH

N/A



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34-15-00-720-001-A00 CAT II Functionally Check ADC System

NOTE: Or 1YE whichever occurs first.

ALL 2000 FH N/A

34-15-00-720-001-A00 SYSTEM Functionally Check ADC system



ALL 5000 FH N/A

34-24-00-710-001-A00 CAT II Operationally Check Standby Attitude Indicator ALL 24 MO

or

5000 FH

± 30 Days

34-25-00-720-001-A00 SYSTEM Functionally Check Standby Compass for proper

compensation




34-52-00-720-001-A00 SYSTEM Functionally Check Transponder System




35-10-00-910-001-A00 EMB-RECOMM

Leak Test Crew Oxygen System Lines NOTE: Together with Task 35-10-07-720-002-A00

ALL

35-10-07-720-001-A00 SYSTEM Functionally Check Crew Oxygen Cylinder

Pressure Regulator

NOTE: At the time of Cylinder Hydrostatic Test.

ALL 60 MO N/A

35-10-07-720-002-A00 SYSTEM Functionally Check (Hydrostatic Test) Crew

Oxygen Cylinder



ALL 60 MO N/A

35-20-01-960-001-A00 SYSTEM Discard Chemical Oxygen Generator (Chemical

Oxygen System only)

ALL 180 MO N/A



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35-20-06-212-001-A00 SYSTEM Inspect (General Visual) of Lavatory Gaseous

Oxygen Cylinder.

NOTE: POST-MOD SB 145-35-0008

ALL

35-20-06-960-001-A00 SYSTEM Discard of passenger Gaseous Oxygen

Cylinder. NOTE: From the manufacturing date

POST-MOD SB 145-35-0008

ALL

35-21-04-720-001-A00 SYSTEM Functionally Check (Hydrostatic Test) Passenger

Oxygen Cylinder (Gaseous Oxygen System

(Shuttle Configuration only))

EMB-135LR 36 MO N/A

35-21-04-960-001-A00 SYSTEM Discard Passenger Oxygen Cylinder (Gaseous

Oxygen System (Shuttle Configuration only))

EMB-135LR 180 MO N/A

35-30-01-720-001-A00 SYSTEM Functionally Check Portable Oxygen Cylinder

Pressure Regulator

NOTE: At the time of Cylinder Hydrostatic Test.

ALL 60 MO N/A

35-30-01-720-002-A00 SYSTEM Functionally Check (Hydrostatic Test) Portable

Oxygen Cylinder



ALL 60 MO N/A

35-30-03-960-001-A00 SYSTEM Discard Protective Breathing Equipment PN

MR10042N 15-40F-11 15-40F-10 15-40F and

E28180-10

ALL 120 MO N/A

49-31-00-710-001-A01 SYSTEM Perform Check of the FADEC BITE Display for

Fault Messages (APU Model T-62T-40C14 (APS

500R) only)

ALL 400 AH N/A

49-31-04-960-001-A00 SYSTEM Discard Inlet Fuel Filter APU Model T-62T-40C11

(APS 500) only

ALL 800 AH N/A



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49-31-04-960-001-A01 SYSTEM Discard Inlet Fuel Filter APU Model T-62T-40C14

(APS 500R) only)

ALL 1200 AH N/A

49-41-03-220-001-A00 SYSTEM Inspect (Detailed Inspection) Igniter Plug ALL 1200 AH N/A

49-91-00-610-001-A00 SYSTEM Check Oil Level and Service Oil System as

required

ALL 400 AH N/A

49-91-00-680-001-A00 SYSTEM Drain and Replace Oil Supply ALL 12 MO

or

2000 AH

N/A

49-91-01-960-001-A00 SYSTEM Discard Oil Filter Element ALL 24 MO

or

2000 AH

N/A





EMBRAER ERL135LR AND ERJ145MP AIRCRAFT

SECTION 4




AIRWORTHINESS

LIMITATIONS REQUIREMENTS

– LIFE LIMITED COMPONENTS

These Requirements can be found in the Scheduled Maintenance Requirements Document (SMRD) part 1 (Maintenance Review Board Report (MRBR) 1150) Appendix A2 (Airworthiness Limitations Requirements) Item A2.2 (Life Limited components)




4.1 MRB Airworthiness Cycle Life Limit - Landing

Gear

These Requirements can be found in the E145 Maintenance Review Board Report (MRBR) – MRB-145/1150 Appendix 2 – Airworthiness Limitation Requirements.





DESCRIPTION PART NUMBER LIFE LIMIT (FC)

EMB‐145MP EMB‐135LR

MLG LEG STRUT ELEB

Leg Strut Left (LH)

2309‐2006‐001 60000 60000

2309‐2006‐501 60000 60000

2309‐2006‐503 60000 60000

2309‐2006‐601 60000 60000

2309‐2015‐001 60000 60000

2309‐2015‐601 60000 60000

Leg Strut Right (RH)

2309‐2006‐002 60000 60000

2309‐2006‐502 60000 60000

2309‐2006‐504 60000 60000

2309‐2006‐602 60000 60000

2309‐2015‐002 60000 60000

2309‐2015‐602 60000 60000

Trunnion Axle 2309‐2025‐001 60000 60000

Shock Absorber attachment axle

2309‐2029‐001 60000 60000

Main side strut attachment axle (Pivot Pin)

2309‐2032‐001 60000 60000

2309‐2032‐003 60000 60000

2309‐2032‐005 60000 60000

Trailing arm axle (left) 2309‐2055‐001 60000 60000

2309‐2055‐003 60000 60000

Trailing arm axle (right) 2309‐2055‐002 60000 60000

2309‐2055‐004 60000 60000




CHAPTER 32 – LANDING GEAR (CONTINUED)



MLG LEG STRUT ELEB

Trailing Arm 2309‐2009‐505 60000 60000

2309‐2009‐607 60000 60000

2309‐2009‐609 60000 60000

2309‐2009‐611 60000 60000

2309‐2009‐613 60000 60000

2309‐2009‐615 60000 60000

2309‐2009‐617 60000 60000

2309‐2038‐007 60000 60000

2309‐2038‐605 60000 60000

2309‐2038‐607 60000 60000

2309‐2038‐609 60000 60000

2309‐2038‐611 60000 60000

2309‐2038‐613 60000 60000

Wheel Axle 2309‐2040‐001 60000 60000

Pivot

2309‐2050‐001 60000 60000

2309‐2050‐003 60000 60000

2309‐2050‐601 60000 60000

Cardan Joint

2309‐2048‐001 15760 15760

2309‐2048‐003 35365 35365

2309‐2050‐005 48948 48948







MLG SHOCK ABSORBER ELEB

Piston Tube 2309‐2058‐001 60000 60000

Cylinder

2309‐2056‐001 60000 60000

2309‐2056‐003 60000 60000

2309‐2056‐005 60000 60000

Bearing Cap 2309‐2066‐001 60000 60000

2309‐2082‐001 60000 60000

MLG SECONDARY SIDE STRUT ELEB

Upper Secondary Side Strut

2309‐2609‐001 60000 60000

2309‐2611‐001 60000 60000

2309‐2611‐003 60000 60000

Lower Secondary Side Strut

2309‐2603‐001 60000 60000

2309‐2624‐001 60000 60000

Cardan 2309‐2618‐001 60000 60000

Shaft 2309‐2621‐001 60000 60000

Bolt 2309‐2626‐001 60000 60000

Pivot pin 2309‐2613‐001 60000 60000

Spring

2309‐2651‐001 20000 20000

2309‐2651‐003 20000 20000

2309‐2651‐005 60000 60000

MLG MAIN SIDE STRUT ELEB

Upper Main Side Strut

2309‐2503‐001 60000 60000

2309‐2504‐001 60000 60000

2309‐2524‐001 60000 60000

Lower Main Side Strut

2309‐2511‐001 60000 60000

2309‐2532‐001 60000 60000

2309‐2532‐003 60000 60000

2309‐2532‐005 60000 60000

Shaft 2309‐2515‐001 60000 60000

Pivot Pin 2309‐2516‐001 60000 60000

2309‐3516‐001 60000 60000







NLG LEG STRUT Liebherr

Sliding Tube 1170‐1401 60000 60000

Wheel axle

1170‐1402 60000 60000

1170‐1403 60000 60000

1170‐1431 60000 60000

1170‐1432 60000 60000

1170‐1433 60000 60000

1170‐1434 60000 60000

Steering Cuff 1170A2300‐01 60000 60000

1170A2500‐01 60000 60000

1170A3200‐01 60000 60000

Torque Link 1170‐0301 60000 60000

Torque Link pin 1170‐0001 60000 60000

Torque Link central bolt 1170‐0002 60000 60000

Main Fitting

1170‐1301 20000 20000

1170‐1302 60000 60000

1170‐1303 60000 60000

1170‐1304 60000 60000

1170‐1305 60000 60000

2233‐0101 60000 60000

2233‐0103 60000 60000

Main drag strut attachment pin

1170‐0070 60000 60000

Pintle pin 1170‐0032 60000 60000







NLG MAIN DRAG STRUT Liebherr

Main drag strut top stay 1172‐0501 20000 20000

1172‐0601 60000 60000

Main drag strut bottom stay

1172‐0201 60000 60000

Pintle pin 1172‐0007 60000 60000

1172‐0037 60000 60000

Hinge point bolt 1172‐0001 60000 60000

NLG AUXILIARY DRAG STRUT Liebherr

Upper auxiliary drag strut 1173‐0201 60000 60000

Lower auxiliary drag strut 1173‐0101 60000 60000

Hinge point bolt 1173‐0001 60000 60000

Cardan joint KSL113608V 60000 60000

Downlock Spring

1173A0300‐01 60000 60000

1173A0600‐01 60000 60000

1173A07 00‐01

60000 60000

Auxiliary Drag Strut assy 1173B0000‐02 6000 (***) 6000 (***)

Note: (***) The life limit is applicable “only” for Part Numbers 1173B0000‐02, Auxiliary Drag Strut

assy. Which are engraved with serial numbers SP010‐96, SP011‐96, SP012‐96 and SP013‐96.




4.2 MRB Airworthiness Limit - Thrust Reverser





CHAPTER 78 –THRUST REVERSER

DESCRIPTION PART NUMBER LIFE LIMIT ‐ THRUST REVERSER CYCLE (TRC)


THRUST REVERSER

Primary Door Lock Actuator

TY2038‐01A 60250 60250

TY2038‐02A 60250 60250

Pivot Door Actuator

TY2039‐03A 1800 1800

TY2039‐03B 1800 1800

TY2039‐03C 1800 1800

TY2039‐05B 15000 15000

TY2039‐05B‐629 15000 15000

TY2039‐05B‐629‐7 60250 60250

TY2039‐05B‐7 60250 60250

TY203‐10A 15000 15000

TY2039‐11A 60250 60250

TY2039‐14A 60250 60250

Directional Control Unit TY2038‐02A 60250 60250

Lock Sequencer

TY2047‐02A 60250 60250

TY2047‐03A 60250 60250

TY2047‐03B 60250 60250

Tertiary Lock

TY2037‐02A 1500 1500

TY2138‐01A 13100 13100

TY2138‐01B 13100 13100

TY2560‐01A 61500 61500

Isolation Control Unit

TY2041‐03A 60250 60250

TY2041‐02B 1932 1932

TY2041‐02A 1932 1932

TY2041‐01A 1932 1932




4.3 MRB Airworthiness Limit - Components






DESCRIPTION PART NUMBER LIFE LIMIT ‐MONTHS (MO)


FLIGHT CONTROLS

Flap Drive Motor Unit 363250‐1003 (*) 1500 N/A

Note: (*) The life limit is applicable “only” for Serial Numbers 00101, 00102, 00103, 00104, 00105,

00106, 00107, 00108, 00109, 00110.


DESCRIPTION PART NUMBER LIFE LIMIT ‐ MONTHS (MO)


OXYGEN

Oxygen Cylinder 176250‐50 180 MO 180 MO

4441009‐050 180 MO 180 MO

CHAPTER 36 – PNEUMATIC

DESCRIPTION PART NUMBER LIFE LIMIT – FLIGHT HOURS (FH)


PNEUMATIC

Low Pressure Bleed‐Air Check Valve

816603‐1 1600 FH 1600 FH

816603‐1 1600 FH 1600 FH

CHAPTER 49 – APU

DESCRIPTION PART NUMBER LIFE LIMIT –FLIGHT HOURS (MO)


APU

Non‐Silenced APU C‐14 (APS 500R) Exhaust Duct

145‐63730‐401 2500 FH 2500 FH

145‐63730‐601 2500 FH 2500 FH



Issued 03June2015 EMBRAER ERJ 135LR AND ERJ 145MP AIRCRAFT


EMBRAER ERJ 135LR AND ERJ 145MP AIRCRAFT

SECTION 5

ENGINES




SECTION 5.1

ENGINES GENERAL




Engine Condition Monitoring The 3007A series engines are designed to be engines with NO FIXED OVERHAUL PERIOD.

In order to monitor the Engine Condition certain inspections need to be carried out.

1. Engine Condition Trend Monitoring is essential to monitor the engines performance trend to

assess rapid or gradual decline in performance and to determine when and what

maintenance action are to be carried out to restore the engines performance. Engine

Performance parameters are continually being monitored and recorded during flight

operations and any parameter exceedance alerts recorded and reviewed after flight.

Engine Trend Analysis is done with the Compass Navigator Trend Program. Data

automatically recorded by the CMC is downloaded from the aircraft through RS 323 Serial

cable to a computer installed with the DAS (Data Acquisition Software).

The file is e‐mailed to Pieter‐Prins @Rolls‐Royce.com, and is then processed through the

Compass Navigator Trend Program to perform Engine Trend Analysis.

Engine performance trending is used to monitor engine performance characteristics such as

performance level changes, both gradual and step, and provides the operator with an

approximate level of engine performance. Critical engine parameter exceedances are also

recorded and stored. Performance trend data download should be accomplished within the

prescribed interval.

Instructions on how to download the data from the Central Maintenance Computer is

contained in the Aircraft Maintenance Instructions.

Instructions on the use of trend programs are contained in the Help files of the program.

Additionally, if directed by a Rolls‐Royce Service Bulletin, manual trend data recording can be

performed by the Flight Crews. This manual trend data is then processed through the

Compass Navigator Trend Program.

Maintenance actions to address the performance level changes are to be initiated within a

maximum of 14 calendar days from the performance trend data download. Certain trend

changes may require a shorter period to apply specific maintenance action as directed by the

manufacturer.

Maintenance actions are to be performed in accordance with the published engine

maintenance instructions. The manufacturer is to be requested for recommendations if need

be.




The recommended minimum margins for the AE 3007A Series Engines with Compass Version

2.5 and higher is 0.0 for ITT and N2. Environ mental conditions may allow continued

operation without exceeding performance limitations.

To establish a trend monitoring program a minimum configuration is required as follows:

(a) Aircraft Configuration Items:

‐ EICAS 17 or higher, Ref. Embraer Service Bulletin 145‐31‐0020

‐ CMC 9 or higher, Ref. Embraer Service Bulletin 145‐45‐0002

(b) CMC Download Software

‐ CMC Download Software

‐ DAS Software Version DAS‐017 or higher, compatible with CMC installed.

© Compass Navigator Trend Program

‐ Version 2.5 or higher.

2. Engine FADEC control and sensing parameters are actively monitored and faults displayed

through the EICAS and the Engine Indicating Display system which requires maintenance

actions to be carried out with varying priorities.

FADEC Faults Annunciated by an EICAS Message

Time Limited Dispatch Categories:

Rolls‐Royce EMM TASK 05‐14‐00‐800‐802 gives the time limited dispatch (TLD) intervals for

fault bits set by the full –authority digital electronic control (FADEC) for the AE3007A Series

engine with phase B 4.2 software and subsequent.

The phase B 4.2 software and subsequent is used with EICAS 16 or higher and CMC 9igher.

Each of the messages can e set by more than one FADEC fault bit. Inspection for the

messages is to be carried out as per RR EMM TASK 73‐25‐10‐200‐801.

Time Limited Dispatch (TLD) categories and Dispatch Interval Messages:

ND‐ No Despatch, Maintenance must be performed before the aircraft can be dispatched for

a flight

ST – Short Term Despatch, Not to exceed 150 FH

LT – Long Term Despatch, Not to exceed 500 FH‐ or Scheduled Maintenance Inspection

NLOTC – No Loss of Thrust Control, Recommended not to exceed 120 Calendar Days.

NOTE: The Maintenance must be done in the specified time interval from the first time the

fault occurred as recorded by the stamp in the CMC.

3. Oil system contamination checks (Chip Detectors –Mag Plugs) are carried out on regular basis

to monitor engine internal condition.




4. Mandatory inspections are to be carried out on the engine piece parts , if as a result of the

foregoing inspections noted in 1 to 3 here above, the engine is showing any abnormality and

has to be physically inspected on Gas Path components to detect deterioration or damage to

the rotating parts especially front end and around the high temperature turbine sections.

MAINTENANCE SCHEDULING

Task‐oriented Scheduled Maintenance

The AE 3007A Series engines maintenance program is based on scheduled maintenance

inspection intervals. The Embraer MBBR adopts most of the Rolls‐Royce Scheduled Inspection

Tasks, where there is duplication, the MRBR engine tasks prevail, as these are operating in an

Embraer Airframe.

CAUTION: IN ORDER TO DECREASE THE POTENTIAL FOR MULTIPLE ENGINE INFLIGHT

SHUTDOWN, POWER LOSS, OR OTHER ANOMALY BECAUSE OF MAINTENANCE ERROR, ROOLYS‐

ROYCE RECOMMENDS THAT OPERATORS PREVENT THE NEED FOR MAINTENANCE ON MULTIPLE

ENGINES INSTALLED ON THE SAME AIRCRAFT AT THE SAME TIME. IF IT IS NOT POSSIBLE TO

PREVENT MAINTENANCE AT THE SAME TIME, ROLLS‐ROYCE RECOMMENDS THAT MORE

CONTROLS ARE APPLIED IN ORDER TO MAKE SURE THAT MAINTENACE TASKS HAVE BEEN

COMPLETED AS DEFINED. STAGGER WILL BE USED AND OR DIFFERENT ENGINEERS USED IN THE

MAINTENANCE OF THE PARALLEL SYSTEMS.

Other Engine Inspections and Mandatory Retirement Schedules come from the RR EMM Chapter

05.

Notes:

A/ If, as a result of an inspection, it is necessary to remove or disassemble the engine, its

modules, or components, the engine condition and performance data will be reviewed and used

to determine if additional preventative and/or corrective maintenance is necessary before

installation or assembly of the engine, the module, or the component.

B/ Mandatory Inspections are applicable at each piece part opportunity for those that have

accumulated 100 Cycles or more, as per AE 3007A RR EMM Task 05‐13‐00‐800‐801.

Contact the Rolls‐Royce representative, if necessary.

Maintenance schedules for the AE 3007A Series Engines is drawn from the following documents:

Compliance with Airworthiness Limitations RR EMM Chapter 05‐10‐00

Recommended Scheduled Inspections RR EMM Chapter 05‐20‐00

Recommended Unscheduled Inspections RR EMM Chapter 05‐50‐00




5.2 RR AE3007A1 and AE3007A1/3 EMM

Scheduled Inspections

Engine Systems and Components

These Requirements can be found in the Engine Maintenance Manual EMM 05-21-00-

800-801.




SCHEDULED INSPECTIONS

TASK REFERENCE SYSTEM/ITEM TASK DESCRIPTION INTERVAL

79‐30‐00‐200‐801 Oil Contamination Inspection 50 Flight Hour or 5 Flight Days (Note 13)

ECTM‐AE 3007A1 &A1/3 ‐ 001

Engine Engine Trend Analysis As frequently as possible not to exceed 7 Calendar Days or 70 Flight Leg Intervals

SB AE 3007A‐79‐009 Oil Tank (Pre SB AE 3007A‐79‐009)

General Visual 400 Flight Hour

72‐00‐00‐200‐801 Air Inlet Section (fan assembly)

General Visual 500 Flight Hour

72‐21‐20‐200‐802 Fan Spinner (Pre SB AE 3007A‐72‐167 only)

Detailed Inspection 500 Flight Hour

72‐63‐10‐700‐801 Starter Drain Adapter (Post SB AE 3007A‐72‐253 and Pre SB AE 3007A‐72‐330 only)

Adjustment/Test 800 Flight Hour

72‐00‐00‐200‐801 Fuel Pump – and –Metering Unit

General Visual 1,000 Flight Hour

73‐11‐10‐000‐801 73‐11‐10‐400‐801

Fuel Nozzles (All Fuel Nozzles Not to Include P/N 23075904, 23077006, 23087207, or 23090046)

Remove the Fuel Nozzle. Install the New or Cleaned Fuel Nozzle.

2,000 Flight Hour

73‐11‐10‐000‐801 73‐11‐10‐400‐801

Fuel Nozzles P/N 23075904, 23077006, 23087207, or 23090046)

Remove the Fuel Nozzle. Install the New or Cleaned Fuel Nozzle.

10,000 Flight Hour

73‐37‐10‐700‐801 Fuel Indicating System Functional Test 3,000 Flight Hour

73‐25‐10‐200‐803 Fadec Anti‐vibration Mounts

Detailed Inspection 4,000 Flight Hour

72‐21‐15‐200‐801 Fan Blades Detailed Inspection 4,000 Flight Hour

74‐21‐10‐000‐801 74‐21‐10‐000‐802 74‐21‐10‐400‐801 and 74‐21‐10‐400‐802

Igniters Remove the Igniters Install the new Igniters

4,000 Flight Hour




SCHEDULED INSPECTIONS (Continued) TASK REFERENCE SYSTEM/ITEM TASK DESCRIPTION INTERVAL

79‐37‐10‐700‐801 Magnetic‐indicating plug

Functional Test 8,000 Flight Hour

05‐13‐00‐800‐801 Maintenance messages Inspect /Check for Refer to Task 05‐14‐00‐800‐802 for Dispatch limitations/EMM 73‐25‐10

250 Flight Hour

75‐43‐10‐200‐802 P2.5 Sensor Inspect 6 Months




5.3 RR AE3007A1 and AE3007A1/3 EMM

Airworthiness Cycle Life Limits

These Requirements can be found in the Engine Maintenance Manual EMM 05-12-00-

800-809.




EMB‐145MP AND EMB‐135LR ENGINE AE 3007A SERIES LIFE LIMITS

DESCRIPTION PART NUMBER LIFE LIMIT ‐ (FC)

EMB‐145MP

AE 3007A1

EMB‐135LR

AE 3007A1/3

AE 3007A SERIES LIFE LIMITS

Fan Wheel 2305865 20000 (5000, Note 1)

20000 (5000, Note 1)

23061670 19400 19400

23077611 20000 20000

Forward Fan Blade Retainer

23062491 20000 20000

Fan Drive Shaft

23058320 30000 30000

23065332 30000 30000

23074382 30000 30000

1st‐stage Compressor Wheel

23064901 12500 12500

23065041 20000 20000

23084156 30000 30000

2nd ‐stage Compressor Wheel

23050752 20000 20000

23084157 20000 20000

3rd ‐stage Compressor Wheel

23050753 20000 20000

23065303 20000 20000

23084158 20000 20000

4th ‐stage Compressor Wheel

23050754 20000 20000

23071259 20000 20000

23084159 20000 20000


23050735 20000 20000

23065605 20000 20000

23071260 20000 20000

23084160 20000 20000


23062666 20000 20000

23071261 20000 20000

23071396 20000 20000

23074717 20000 20000

23084161 30000 30000


23062667 20000 20000

23071262 20000 20000

23071397 20000 20000

23074217 20000 20000

23074719 20000 20000

23084162 30000 30000

23084350 30000 30000




EMB‐145MP AND EMB‐135LR ENGINE AE 3007A SERIES LIFE LIMITS (CONTINUED)


EMB‐145MP

AE 3007A1

EMB‐135LR

AE 3007A1/3



23061628 20000 20000

23071263 20000 20000

23074721 20000 20000

23084163 30000 30000


23061629 20000 20000

23071264 20000 20000

23074722 20000 20000

23084164 30000 30000


2361630 20000 20000

23071265 20000 20000

23074723 20000 20000

23084165 30000 30000


23061631 20000 20000

23066231 20000 20000

23074724 20000 20000

23084166 30000 30000


23061632 20000 20000

23071267 20000 20000

23074725 20000 20000

23084167 30000 30000


23061633 20000 20000

23071268 20000 20000

23074213 20000 20000

23084168 30000 30000


23061634 20000 20000

23071269 20000 20000

23074214 20000 20000

23084169 30000 30000

23084284 30000 30000






EMB‐145MP

AE 3007A1

EMB‐135LR

AE 3007A1/3


Compressor Shaft Cone

23050728 7500 3500

23070729 7500 3500 (9300, Note 2)

23073282 20000 20000

23076016 20000 20000

23076017 7500 3500 (9300, Note 2)

23084170 30000 30000

1st‐stage Gas – generator‐pressure ‐ turbine Wheel

23069115 30000 30000

23069591 30000 (20000, Note 3)

30000 (20000, Note 3)

23070664 8400 8400

23079946 30000 30000

23088784 30000 30000

23088906 30000 30000

2nd ‐stage Gas – generator‐pressure ‐ turbine Wheel

23069438 9500 9500

23074462 9500 (20000, Note 4)

9500 (20000, Note 4)

23074644 9500 9500

23075345 9500 (23000, Note 5)

9500 (23000, Note 5)

23084520 23000 23000

23084781 20000 20000

23088817 20000 20000

23088818 20000 20000

1st to 2nd stage Turbine Spacer

23070989 13100 13100

23072849 13100 13100

23015364 13100 13100

23076778 30000 30000

23089137 30000 30000

1st‐stage Low –pressure ‐ turbine Wheel

23060111 30000, Note 6 (20000, Note 7)

30000, Note 6 (20000, Note 7)

23070355 30000, Note 6

30000, Note 6

23073957 30000, Note 6 (20000, Note 8)

30000, Note 6 (20000, Note 8)

23074586 30000 30000

23074587 30000 30000

23076801 30000 30000






EMB‐145MP

AE 3007A1

EMB‐135LR

AE 3007A1/3


2 nd‐stage Low –pressure ‐ turbine Wheel

23058312 30000 (20000, Note 9)

30000 (20000, Note 9)

23070356 30000 30000

23074270 30000 30000

23074308 30000 30000

23074312 30000 30000

23079220 30000 30000

23079221 30000 30000

23088281 30000 30000

23088282 30000 30000

23090961 30000 (20000, Note 10)

30000 (20000, Note 10)

23090973 30000 30000

23090974 30000 30000

23090975 30000 30000

3 Rd‐stage Low –pressure ‐ turbine Wheel

23070046 30000 (20000, Note 11)

30000 (20000, Note 11)

23070357 30000 30000

23079224 30000 30000

23090977 30000 (20000, Note 12)

30000 (20000, Note 12)

23090978 30000 30000

Low – Pressure – Turbine – Interstage Spacer

23054049 30000 30000

Low – Pressure – Turbine – Forward Shaft

23059694 24000 24000

23067076 30000 30000

23074538 30000 30000

23078229 30000 30000




NOTES

Note 1: For Fan Wheel P/N 23058865 the following Serial Numbers have

5000 Cycle Life Limit:

MW63584 MW67915 MW67942 MW67968

MW67809 MW67916 MW67946 MW67970

MW67810 MW67918 MW67951 MW67973

MW67811 MW67919 MW67952 MW67976

MW67820 MW67920 MW67953 MW67977

MW67875 MW67922 MW67954 MW67998

MW67877 MW67923 MW67955 MW70581

MW67883 MW67924 MW67956 MW70584

MW67884 MW67925 MW67960 MW70586

MW67887 MW67927 MW67961 MW70588

MW67906 MW67931 MW67962 MW70590

MW67908 MW67932 MW67964 MW70598

MW67912 MW67933 MW67966 MW70599

MW67914 MW67935 MW67967 MW70602

Note 2: Accumulated Life Limit only for Compressor Shaft Cone Assemblies

processed with slurry deburr.

Part Number 23070729 or 23076017(**)

Serial Numbers Serial Numbers Serial Numbers

MM78599 MM78653 MM78659

MM78615 MM78654 MM78660

MM78632 MM78655 MM78661

MM78650 MM78656 MM78662

MM78651 MM78657 MM78663

MM78652 MM78658 MM78665 AND UP

The (**) indicates that the serial number can be associated with either part number.




Note 3: For 1st – stage high – pressure – turbine wheel P/N 23069591, the

following Serial Numbers have 20000 Flight Cycles Life Limit:

Part Number 23069591

Serial Numbers Serial Numbers Serial Numbers Serial Numbers

MM119837 MM143107 MM500591 MM500958

MM142683 MM143255 MM500647 MM500962

MM142812 MM143272 MM500665 MM504103

MM142819 MM143309 MM500685 MM504105

MM142827 MM182400 MM500724 MM504108

MM142843 MM182632 MM500807 MM504155

MM142870 MM182653 MM500835 MM504182

MM142873 MM182691 MM500890 MM504185

MM142944 MM182734 MM500924 MM504194

MM142956 MM182761 MM500937 MM504230

MM142969 MM182803 MM500944 MM504444

MM142977 MM182811 MM500948 MM504589

MM142991 MM182842 MM500950 MM504799

MM142993 MM183020 MM500955 ‐‐‐‐‐‐

MM143087 MM500563 MM500957 ‐‐‐‐‐‐

Note 4: For 2nd – stage high – pressure – turbine wheel P/N 23074462, the



MM504890 MM505017 MM505046

MM504963 MM505025 MM505048

MM504990 MM505034 MM505054

MM504995 MM505041 MM505055

MM505007 MM505045 MM505056

All MM prefix Serial Numbers higher than MM505060

All Serial Numbers with MW prefix




Note 5: For 2nd – stage high – pressure – turbine wheel P/N 23075345, the



MM507646 MM508211 MM508319

MM508144 MM508221 MM508320

MM508153 MM508241 MM508322

MM508176 MM508248 MM508337

MM508186 MM508251 MM508338

MM508188 MM508264 MM508382

MM508205 MM508305 MM508387

MM508208 MM508311 ‐‐‐‐‐‐‐‐‐‐

Note 6: The total in‐service history for a life limited part must be reviewed

prior to installation. If the engine was upgraded from an AE 3007A to an AE

3007A1, A1/1, A1/3, A1P, or A3 engine then have to find the cycle life limit.

See table below.

TABLE 1 – AE 3007A1, A1/1, A1/3, A1P, or A3 CHAPTER 5 CYCLE LIFE LIMIT AFTER CONVERSION FROM AE 3007A

ENGINE CYCLES ACCULATED AS AE 3007A NEW CHAPTER 5 CYCLE LIFE LIMIT

1‐1000 29500

1001‐2000 29000

2001‐3000 28500

3001‐4000 28000

4001‐5000 27500

5001‐6000 27000

6001‐7000 26500

7001‐8000 26000

8001‐9000 25500

9001‐10000 25000

10001‐1100 24500

11001‐12000 24000

12001‐13000 23500

13001‐14000 23000

140001 + 20000




Note 7: For 1st – stage Low – pressure – turbine wheel P/N 23060111, the



GX51818 WD131885 WY45747

GX51820 WD209960 WY45749

WD53865 WY13069 WY45758

WD53866 WY13102 WY46589

WD53867 WY45724 WY46592

WD53874 WY45735 WY46594

WD62757 WY45737 WY46596

WD62761 WY45739 WY46827

WD76521 WY45744 WY46833

WD89206 WY45746 ‐‐‐‐‐‐‐‐‐‐

Note 8: For 1st– stage Low – pressure – turbine wheel P/N 23073957, Serial

Number WD245173 the Cycle Life Limit remains at 20000 Flight Cycles.


MM507646 MM508211 MM508319

MM508144 MM508221 MM508320

MM508153 MM508241 MM508322

MM508176 MM508248 MM508337

MM508186 MM508251 MM508338

MM508188 MM508264 MM508382

MM508205 MM508305 MM508387

MM508208 MM508311 ‐‐‐‐‐‐‐‐‐‐

Note 9: For 2nd – stage Low – pressure – turbine wheel P/N 23058312, the



WD212941 WD53644 WY45630 WY46843

WD21953 WD76723 WY45652 WY46859




Note 10: For 2nd – stage Low – pressure – turbine wheel P/N 2390961, the



WD212941 WD53644 WY45630 WY46843

WD21953 WD76723 WY45652 WY46859

Note 11: For 3rd – stage Low – pressure – turbine wheel P/N 23070046, the


Serial Numbers

WD188051 WD80520 WD80563 WY13880 WY13924

Note 12: For 3rd – stage Low – pressure – turbine wheel P/N 23090977, the


Serial Numbers

WD188051 WD80520 WD80563 WY13880 WY13924






SECTION 6




KCAA INSPECTION REQUIREMENTS




SECTION 6 KCAA INSPECTIONS REFERENCE NUMBER

TYPE CAT DESCRIPTION LU INT EFFECT TOLERANCE

EMB/AMP/KCAA/001 Inspection of all onboard Safety and Emergency Equipments ANNUAL ALL NIL EMB/AMP/KCAA/002 Certificate of Airworthiness Renewal Inspection Requirements

IAW AWS CAA-AC-AWS003A and Part 5 of ALS Maintenance Control Manual

ANNUAL ALL NIL

EMB/AMP/KCAA/003 Standby Compass Calibration Check ANNUAL ALL NIL EMB/AMP/KCAA/004 Pitot Static System In-Situ, Altimeters and Airspeed Indicators

Calibrations and Leak Checks ANNUAL ALL NIL

EMB/AMP/KCAA/005 Check of the Stall Warning System In-Situ including Anti-Icing System

ANNUAL ALL NIL

EMB/AMP/KCAA/006 Inspection of the Placards and Markings ANNUAL ALL NIL EMB/AMP/KCAA/007 Inspection of the Engine Instruments for Correct Limitation

Markings ANNUAL ALL NIL

EMB/AMP/KCAA/008 Check of all Emergency Escape Hatches and Doors ANNUAL ALL NIL EMB/AMP/KCAA/009 Check of the Electrical Generating System Failure Warning

System ANNUAL ALL NIL

EMB/AMP/KCAA/010 Check of Emergency Power Supply System ANNUAL ALL NIL EMB/AMP/KCAA/011 Emergency Locator Transmitter Function Performance and

Battery Condition and Replacement Limitation Date ANNUAL ALL NIL

EMB/AMP/KCAA/012 Check of FDR Function and Data Download Calibration and Storage, including ULD Battery Replacement Limitation Date.

ANNUAL ALL NIL

EMB/AMP/KCAA/013 Check of CVR Function Recording and Playback, including ULD Battery Replacement Limitation Date.

ANNUAL ALL NIL




SECTION 6 KCAA INSPECTIONS (Continued)

EMB/AMP/KCAA/014 Check of all Cockpit, Cabin and Cargo Hold hand held Fire Extinguishing Equipment for Serviceability, Re-Weigh and Correct Extinguishing Agent.

ANNUAL ALL NIL

EMB/AMP/KCAA/015 Check of Emergency Break in Markings Visible and Correctly Applied

ANNUAL ALL NIL

EMB/AMP/KCAA/016 Check of Radio Communications, Navigation and Transponder Receiving and Transmitting Equipment for Serviceability

ANNUAL ALL NIL

EMB/AMP/KCAA/017 Check of Aircraft Structure and Engine Electrical Bonding ANNUAL ALL NIL EMB/AMP/KCAA/018 Flight and Engine Performance Tests ANNUAL ALL NIL






SECTION 7




ALS REQUIREMENTS




SECTION 7 ALS REQUIREMENTS REFERENCE NUMBER

TYPE CAT DESCRIPTION LU INT EFFECT TOLERANCE

EMB/AMP/ALS/001 Load the Navigation Data Base Every 28 Days ALL NIL