Maintenance Program (MP) Issue 1 Rev. 0 Copy 01

Manual Cover Page
MAINTENANCE PROGRAM (MP)
ACA-ENG-MP-DID
This Maintenance Program is establishing for the Aircraft Model

Legacy 600 EMB-135BJ serial number 14501069.
Approved by Civil Aviation Authority of Thailand
Issue: 1
Revision: 0
05 07 2019
Effective Date: ________/________/________
Type text here

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This document is property of AC Aviation Co., Ltd. Do not Copied or distributed without company allowed.
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GENERAL INFORMATION
MANUAL CONTROL SHEET (MCS)
Authority Position Signature Date (dd/mm/yy)
Prepared by Head of Engineer 05/07/2019
Reviewed by Head of Quality 05/07/2019
Controlled
Copy No.
01
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TABLE OF CONTENTS (TOC)
Contents
GENERAL INFORMATION .................................................................................................................................... A
MANUAL CONTROL SHEET (MCS) ................................................................................................................... A
TABLE OF CONTENTS (TOC)............................................................................................................................. B
LIST OF EFFECTIVE PAGE-1 (LEP) ..................................................................................................................... F
LIST OF EFFECTIVE PAGE-2 (LEP) ..................................................................................................................... G
RECORD of REVISION (ROR) ............................................................................................................................ H
REVISION TRANSMITTAL(RT)............................................................................................................................ I
CONTROL DISTRIBUTION LIST (CDL) ................................................................................................................. J
SECTION-0 GENERAL REQUIREMENTS ................................................................................................................ 1
1.1 Company Statements ................................................................................................................................ 1
1.2 Annual Utilization and Maintenance Review ........................................................................................... 2
1.3 Aircraft Application ................................................................................................................................... 2
1.3.1 MP Owner and Maintenance Oragnization Address .............................................................................. 3
1.4 DOCUMENT REFERENCE ............................................................................................................................ 3
1.5 Flying Times ............................................................................................................................................... 3
1.6 Certification Maintenance Requirements (CMR’s) .................................................................................... 3
1.7 Task Escalation .......................................................................................................................................... 3

1.8 ADs/SBs Assessment .................................................................................................................................. 4
1.9 Fatigue Lives and Airworthiness Limitation Items .................................................................................... 4
2.0 Maintenance Practices and Procedures ................................................................................................... 4

2.1 Area or Zonal Inspection ........................................................................................................................... 4
2.2 Inspection Standards................................................................................................................................. 4
2.3 Condition Monitored Maintenance/Reliability Programe ........................................................................ 4
2.4 Maintenance Requirements ..................................................................................................................... 5
2.5 Specific structural maintenance programs ............................................................................................... 7
2.6 Repairs and Modifications ........................................................................................................................ 7
2.7 RVSM and PBN Maintenance Procedures................................................................................................. 7
2.7.1 RVSM Maintenance Procedures............................................................................................................ 7
2.7.2 PBN Maintenance Procedures .............................................................................................................. 7
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2.8 Ageing Aircraft System .............................................................................................................................. 7

2.9 Critical Design Configuration Control Limitation (CDCCL) ......................................................................... 8
3.0 Aircraft Electrical Wiring Interconnect System (EWIS) .............................................................................. 8
3.1 Limit Of Validity (LOV) ................................................................................................................................ 8
3.2 MP Amendments and Review ................................................................................................................... 8

3.3 Airworthiness Limitation Items (ALIs) ....................................................................................................... 9
3.4 Maintenance Certificate release to service (CRS)...................................................................................... 9
3.5 CVR/FDR Download Procedures ............................................................................................................... 9
3.6 Calibration of the FDR system................................................................................................................... 9

3.7 Pre-Flight /Post-Flight ............................................................................................................................... 9
3.8 Dent And Buckle Mapping ...................................................................................................................... 10
Section 1 Scheduled Maintenance Requirenents - General ............................................................................. 12
1.Introduction ............................................................................................................................................... 12
2.General Rules ............................................................................................................................................. 12
3.Interval ....................................................................................................................................................... 13
4.Flexibility .................................................................................................................................................... 13
5.Implementation Guideline For Maintenance Plan Revisions .................................................................... 15
6.System And Powerplant Requirements ..................................................................................................... 16
7. Structural Requirements ........................................................................................................................... 17
8. Corrosion Requirements ......................................................................................................................... 18
9. Powerplant and APU Rules...................................................................................................................... 19
10. Zonal Requirments ................................................................................................................................ 20
11. List of Scheduled Maintenance Requirments Presentation................................................................... 25
12. Abbreviations ........................................................................................................................................ 27
13. Term&Definitions .................................................................................................................................... 32
SECTION 2 - SCHEDULED MAINTENANCE REQUIREMENTS - LIST OF REQUIREMENTS .................................... 37
CHAPTER 12 – SERVING ................................................................................................................................ 37
CHAPTER 20 - STANDARD PRACTICES – AIRFRAME ...................................................................................... 37
CHAPTER 21 - AIR CONDITIONING ................................................................................................................ 38
CHAPTER 22 - AUTO FLIGHT .......................................................................................................................... 41
CHAPTER 23 - COMMUNICATIONS ............................................................................................................... 41
CHAPTER 24 - ELECTRICAL POWER................................................................................................................ 42
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CHAPTER 25 - EQUIPMENT/FURNISHINGS ................................................................................................... 44

CHAPTER 26 - FIRE PROTECTION................................................................................................................... 46
CHAPTER 27 - FLIGHT CONTROLS .................................................................................................................. 50
CHAPTER 28 - FUEL ....................................................................................................................................... 56
CHAPTER 29 - HYDRAULIC ............................................................................................................................. 63
CHAPTER 30 - ICE AND RAIN PROTECTION ................................................................................................... 64
CHAPTER 31 - INDICATING/RECORDING SYSTEMS ....................................................................................... 66
CHAPTER 32 - LANDING GEAR ....................................................................................................................... 67
CHAPTER 33 - LIGHTS .................................................................................................................................... 73
CHAPTER 34 - NAVIGATION .......................................................................................................................... 74
CHAPTER 35 - OXYGEN .................................................................................................................................. 76
CHAPTER 36 - PNEUMATIC............................................................................................................................ 79
CHAPTER 38 - WASTE AND WATER ............................................................................................................... 80
CHAPTER 49 - AIRBONE POWER UNIT........................................................................................................... 81
CHAPTER 52 - DOORS .................................................................................................................................... 82
CHAPTER 53 - FUSELAGE ............................................................................................................................... 88
CHAPTER 54 - NACELE/PYLONS................................................................................................................... 118
CHAPTER 55 - STABILIZERS .......................................................................................................................... 120
CHAPTER 57 - WINGS .................................................................................................................................. 132
CHAPTER 71 - POWERPLANT ...................................................................................................................... 158
CHAPTER 72 - ENGINE ................................................................................................................................. 160
CHAPTER 73 - ENGINE FUEL AND CONTROL ............................................................................................... 160
CHAPTER 74 - IGNITION .............................................................................................................................. 161
CHAPTER 76 - ENGINE CONTROLS .............................................................................................................. 162
CHAPTER 78 - EXHAUST .............................................................................................................................. 163
CHAPTER 79 - OIL ........................................................................................................................................ 164
CHAPTER 80 - STARTING ............................................................................................................................. 165
SECTION 3 - NATIONAL REQUIREMENTS ........................................................................................................ 167
3.1 GENERAL ............................................................................................................................................ 167
A. Special Rules Pertaining to United States of America FAA Certification ............................................ 167
B. Special Rules Pertaining to EASA Certification.................................................................................... 167
C Special Rules Pertaining to CAAC Certification ................................................................................... 169
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CONTROL DISTRIBUTION LIST (CDL)
Copy No. Name Position/Location
001 Master copy for Company Document Control Center/QA office
002 Master copy for CAAT AIR,CAAT
003 Stephen Christopher Levesque Accountable Manager / General Manger
004 Palang Khamlek Head of Flight Operation
005 Teerapong Prajittanon Head of Engineer
006 Smith Pongstaporn Head of SMS and AVSEC
007 Phrompratan Sorassa Head of Training
008 Songsit Lertcharoon Head of Quality
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SECTION-0 GENERAL REQUIREMENTS
1.1 Company Statements

In the preparation of this Maintenance Programme to meet the requirements of AOCR and CAAT
announcement, the recommendations made by the aircraft, engine and equipment manufacturers have
been evaluated and, where appropriate, have been incorporated.
This Maintenance Schedule lists the tasks and identifies the practices and procedures, which form the basis
for the maintenance programme of the aircraft. The operator undertakes to ensure that these aircraft will
continue to be maintained in accordance with this Programme.
The data contained in this Programme will be reviewed for continued validity at least annually in the light of
operating experience.
It is accepted that this Programme does not prevent the necessity for complying with any new or amended
regulations or requirements published by CAAT from time to time where these new or amended regulations
may override elements of this Programme.
It is understood that compliance with this Programme alone does not discharge the operator from ensuring
that the Programme reflects the maintenance needs of the aircraft, such that continuing safe operation can
be assured. It is further understood that CAAT reserves the right to suspend, vary or cancel approval of the
Maintenance Programme if the CAAT has evidence that the requirements of the Maintenance Programme
are not being followed or that the required standards of airworthiness are not being maintained.
Name: Teerapong Prajittanon Position: Head of Engineering
Signed: .................................................................
On behalf of AC Aviation Company Limited
Date: 29/02/2019
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1.2 Annual Utilization and Maintenance Review

In the preparation of this Maintenance Schedule (ACA-ENG-MP-DID) to meet the requirements of the
AOCR and CAAT announcement, the recommendations made by the manufacturers have been evaluated and,
where appropriate, have been incorporated. It is agreed that it is a duty of the ACA or his contracted
Maintenance Organization or Fleet Technical Management Organization that subsequent maintenance
recommendations, including airworthiness information promulgated in Maintenance Review Board Report,
Maintenance Planning Document, Service Bulletins, and Service Letters, etc., issued by the TCH, should be
evaluated and, where appropriate, should be incorporated in this Schedule by approved amendment
procedures.
The periods/frequencies of the maintenance tasks in this Schedule are generally based on an
anticipated annual utilization of 500 flying hours and large variations in the annual utilization of individual aircraft
could invalidate the effectiveness of certain tasks. If the annual utilization varies by more than 25% from that
anticipated, the ACA accepts that it, or its contracted maintenance organization, must review the maintenance
tasks and periods with a view to making any necessary adjustments.
In addition to variations in utilization, the data contained in this Schedule will be reviewed at least
annually by the ACA’s Maintenance Engineering, or its contracted Maintenance Organization, to ensure that the
detailed requirements continue to be valid in the light of operating experience.
1.3 Aircraft Application

The Legacy 600 model EMB-135BJ is a company aircraft manufactured by Embraer
S.A.(Embraer), Avenida Brig. Faria Lima 2170, PC 075/1, 12227-901 Sao Jose dos Campos, Brazil. It is
under Type Certificate (TC) No. T00011AT. The general information of this aircraft is as follow.
A Aircraft model EMB-135BJ
B Manufacture date October 2008
C Serial No. 14501069
D Registration No. HS-DID
E Engine Manufacture and Model Rolls-Royce model AE3007A1E
F APU Manufacture and Model Hamilton Sundstrand model T-62T-40C14
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1.3.1 MP Owner and Maintenance Oragnization Address
Owner’s address Maintenance

Detail
Organization address
Jet Aviation (Asia Pacific) Pte. Ltd
Name AC AVIATION CO., LTD. MRO CAAT approval No.92/2533.
222 DON MUANG INTERNATIONAL
Jet Aviation (Asia Pacific) Pte. Ltd
AIRPORT HANGAR No.4426
720 West Camp Road Seletar
Address VIPHAVADEE - RANGSIT Rd.
Aerospace Park, Singapore,
SANAMBIN, DONMUANG, BANGKOK
797520 SINGAPORE
10210
+66(0)2-504-3598 +66(0)2-504-3599 T +65 6681 7897
Tel. Contact
+66(0)2-504-3600 F +66(0)2-504-3597 F +65 6681 7874
55 DON MUANG, BANGKOK
Post Address Same Office Address
10211
E-mail info@bangkokjets.com Wee-sing.tan@hawkerpacific.com
Website www.bangkokjets.com www.hawkerpacific.com
1.4 DOCUMENT REFERENCE

1.4.1The document reference shall include these, Name, reference, the revision number and the date of
current revision of the CAAT approved maintenance. The reference number shall print on the cover page.
1.4.2. The document reference list which revelant with Maintenance Program.
Document Name Sourcing Remark

Aircraft Maintenance Manual Part-II (AMM MPP (6020) https://techdata.flyembraer.com Rev.15/ 26APR 19
Structural Repair Manual (SRM-1422) ditto Rev.38/16 MAY 16
Maintenance Planning Guide (MPG-1483) ditto Rev.13/ 27 APR 18
Maintenance Planning Guide Appendix-A (MPG-1483_APPA) ditto Rev.13/ 27 APR 18
Schedule Maintenance Requirements Document Section-II ditto Rev.13/ 27 APR 18
(SMRD-1533)
Standard Wiring Practices Manual (SWPM-4145) ditto Rev.12/ 29 MAR 19
General Maintenance Manual (ACA-ENG-GMM) ACA Engineering office Rev.1
1.5 Flying Times

All periods in this Schedule quoted in 'flying hours' are to be calculated and recorded on a 'Take-Off to
Touch-Down' basis.
1.6 Certification Maintenance Requirements (CMR’s)

It’s not applicable to ACA operation. Refer to Appendix-A
1.7 Task Escalation

Not applicable
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1.8 ADs/SBs Assessment

Chapter 8 of Air Operator’s Certificates Requirements (AOCR) requires the operator to assess
airworthiness directive and manufacturer technical information. Airworthiness Directives (or documents of
comparable intent) are issued by the Authority responsible for the type design of the aircraft/engine concerned
whereas and manufacturer technical information is in the form of Service Bulletins, Letters, Information Leaflets,
etc. resulting from in-service experience.
Compliance with the mandatory requirements of the Authority responsible for the type
design of the aircraft/engine must be achieved unless this requirement is varied by the CAAT.
Continuing Airworthiness and other Service Information must be continuously evaluated
by the Operator or the contracted Maintenance Organisation or Fleet Technical Management Organisation and,
where necessary, appropriate action must be taken to amend the Maintenance Schedule.
AD or SB assessment refer to ACA-ENG-GMM, Part-1, Section .1.5.1 and Section 1.7.2
1.9 Fatigue Lives and Airworthiness Limitation Items

Structural 'fatigue' lives and Airworthiness Limitations Items published by manufacturers are classified by
CAAT as mandatory for aircraft on the Thai register. Refer to Section-1 article 7. Structural Requirements
The Fatigue Threshold values have also been included in the Airworthiness Limitation Requirements –
Appendix A of the Maintenance Planning Guide (MPG-1483).
2.0 Maintenance Practices and Procedures

The practices and procedures necessary to accomplish the requirements of this Schedule, or work
resulting from its application, should be, as a minimum, to the standards recommended in:
a) relevant Maintenance, Overhaul and Repair Manuals and where applicable
b) UKCAA CAP 562 Civil Aircraft Airworthiness Information and Procedures.
Refer to Aircraft Maintenance Manual Part-II (AMM MPP (6020)
2.1 Area or Zonal Inspection

Where the term 'ZONAL' is used in this Schedule, this is to be interpreted to mean that a general visual
inspection is made for the general condition of the structure, systems and components in the specified zone or
area. The inspection must be of sufficient depth to establish that any significant deterioration is identified and
rectified to ensure that the general quality/condition of the zone/area is satisfactory until the next higher inspection
becomes due. Refer to Section-1 article 12. Zonal Requirements . The Airaraft Zoning refer to Appendix-B
2.2 Inspection Standards

Unless otherwise stated, all inspection requirements are to be applied without removing an item from the
aircraft or dismantling the item, group or sub-assembly unless dismantling is considered essential in order to
ensure airworthiness. Where dismantling is required by this Schedule, this is stated against the item concerned.
All significant terms and abbreviations used within this Schedule are defined in accordance with the Type
Certificate Holder’s definitions, or, in the absence of formal definition, those quoted in World Airlines Technical
Operations Glossary.
The inspection standards applied to individual task inspections must meet the requirements of the Type
Certificate Holder’s recommended standards and practices. In the absence of specific manufacturers’ guidance,
refer to UKCAA CAP 562 (Civil Aircraft Airworthiness Information and Procedures) or other approved data, as
appropriate.
2.3 Condition Monitored Maintenance/Reliability Programe

The method of data collection, analysis, corrective actions and reporting specified for the implementation of
this Approved Maintenance Schedule is prescribed in the current Reliability Programme Refer to ACA-ENG-
GMM, article 1.10 Reliability programs, which constitutes part of the Schedule.
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2.4 Maintenance Requirements

ACA ‘s Maintenance Engineer department shall strictly control and maintenance these items which they
are required by CAAT following these below table;
Maintenance Requirement Type/Title THR/INT/TOL Maintenance Reference

Requirement items Requirement
I : 1000 FH or 12
Restore (Overhaul) SAFT Main Ref. MPG-1483 Section-II
MO 24-36-01-900-001-A00
Battery Ref.SMRD-1533 Section-II
No Tolerance
Aircraft battery capacity Functionally Check Back-up
I : 6 MO Ref. MPG-1483 Section-II
checks Battery 24-35-01-720-001-A00
± 15 Days
Restore (Replacement) Back-up I : 12 MO Ref. MPG-1483 Section-II

24-35-01-900-001-A00
Battery No Tolerance
Inspect (General Visual) First Aid I : 6 MO
25-60-01-212-001-A00 Ref. MPG-1483 Section-II
Kit for Condition and Validation ± 15 Days
Functionally Check of Portable Fire
I : 12 MO
Extinguishing Bottle for Weight (See 26-24-00-720-001-A00 Ref. MPG-1483 Section-II
No Tolerance
placard attached to the bottle)
Discard Protective Breathing I : 120 MO
Equipment No Tolerance
Emergency equipment Operationally Check Crew/Pax I : 4000 FH or 48 MO Ref. MPG-1483 Section-II
35-10-00-710-001-A00
Oxygen Masks ± 30 Days
Functionally Check of Flashlight I: 12 MO Ref. MPG-1483 Section-II
33-51-01-720-001-A00
Non Rechargeable Battery ± 15 Days DME CMM 25-60-02
Discard Non Rechargeable I: 24 MO Ref. MPG-1483 Section-II
33-51-03-960-001-A00
Flashlight Battery Pack ± 30 Days DME CMM 25-60-02
Functionally Check of Flashlight I: 12 MO Ref. MPG-1483 Section-II
33-51-01-720-001-A00
Rechargeable Battery (Cockpit) ± 15 Days DME CMM 25-60-11
Restore (Overhaul) Winslow
I : 36 MO
(Vacuum Packed) Life Raft 25-63-01-900-001-A01 Ref. MPG-1483 Section-II
No Tolerance
Assembly
Restore Crew/PAX Emergency Life I : 120 MO
25-60-02-900-001 ZOIAC CMM-63600
Jacket No Tolerance
Operationally Check Cockpit I : 4000 FH or 48 MO
Emergency escape provisions 52-22-00-710-001-A00 Ref. MPG-1483 Section-II
Emergency Exit ± 30 Days
Operationally Check Passenger I : 4000 FH or 48 MO
Cabin Escape Hatch Mechanism ± 30 Days
Functionally Check Standard Main
I : 4000 FH or 48 MO
Door Actuating, Latching and 52-11-00-720-005-A00 Ref. MPG-1483 Section-II
± 30 Days
Locking Mechanism
Visually Check Portable Oxygen I: 500 FH or 12 MO Ref. MPG-1483 Section-II
35-30-01-211-001-A00
Cylinder Gauge Pressure Indication ± 15 Days
Functionally Check (Hydrostatic I : 60 MO Ref. MPG-1483 Section-II
35-30-01-720-002-A00
Test) Portable Oxygen Cylinder No Tolerance
Functionally Check Portable
I : 60 MO Ref. MPG-1483 Section-II
Pressure vessels Oxygen C 35-30-01-720-001-A00
No Tolerance
ylinder Pressure Regulator
Functionally Check Crew Oxygen I : 60 MO Ref. MPG-1483 Section-II
35-10-07-720-001-A00
Cylinder Pressure Regulator No Tolerance
Functionally Check (Hydrostatic I : 60 MO Ref. MPG-1483 Section-II
35-10-07-720-002-A01
Test) Crew Oxygen Cylinder. No Tolerance
Ref. MPG-1483 Section-II
Inspect (General Visual) Aileron I : 4000 FH or 48 MO
Flexible hoses 27-12-01-212-001-A00 Ref. MPG-1483 Section-I
PCA Hoses ± 30 Days ,article 12 Zonal Requirements
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Inspect (Special Inspection) for T : 6 MO 28-11-00-280-001-A01

Ref. SMRD-1533 Section-II
Presence of Microorganisms in the I : 12 MO AMM TASK 28-11-00-
EMB-RECOMM
Fuel Tanks. ± 15 Days 200-803-A
Fuel/Oil Contamination Check Inspect (General Visual) of Multi-
Function Display for ENG 1(2) OIL I : 50 FH or 30 Days 79-34-00-212-001-A00
(Whichever occurs first) Ref. MPG-1483 Section-II
DEBRIS Engine AE3007A1E No Tolerance
Maintenance Message
Restore (Cleaning) Flight Crew I : 500 FH OR 12 MO
Seats Locking System ± 15 Days
Inspect (General Visual) Passenger
Cabin Seats (Fabric, Cover, Safety I : 48 MO
Belt, Seat Movement and ± 30 Days
Seatbelts and Harness
Attachments to the Track
Inspect (Detailed Inspection)
Cockpit Seats for Security of I : 4000 FH or 48 MO
Attachment to the Track, Including ± 30 Days
Restraint System (Seat Belt)
Aircraft Weight and Balance Weight and Balance I : 60 MO 08-10-00-02 Ref. AMM Part-II (6020)
Swing Compass I : 36 MO 34-25-00-720-001-A00
Ref. SMRD-1533 Section-II
CAAT Airworthiness Notices ATC Transponder function test I : 24 MO 34-52-00-720-001-A00
AD 133/2538 Recertify no.1 and 2. Nose unit,air 341501-0101B
I : 24 MO Ref. CAMP system
data processo-navigation computer 341501-0102B
72-00-00-970-001-A00
Engine Health Monitoring trend I : 30 Days Rolls-Royce MM-05-21-00
Engine/APU AMM 72-00-00-970-
Download analysis Ref. SMRD-1533 Section-II
801-A
Check Lavatory Paper of Linen
I : 1000 FH N/A FAA 1974-08-09 R03
Mandatory requirements waste receptacle fire prevention
– Airworthiness directives Inspection for Tube alignment of
I : 5000 FH or 48 MO N/A FAA 2017-04-12 PARA (I)
PITOT 1(2)
Functionally Check AFCS Altitude I: 5000 FH or 48 MO
Hold/Pre-Select Mode ± 30 Days
Inspect (Special Inspection) RVSM I: 5000 FH or 48 MO
Critical Region (Skin) for Waviness ± 30 Days
Maintenance
applicable to Inspect (Special Inspection) Static
RVSM I: 5000 FH or 48 MO
specific aircraft Port Surrounding Plate for 34-13-04-280-002-A00 Ref. MPG-1483 Section-II
± 30 Days
operations Flushness and Integrity
Inspect (Special Inspection) Oxygen
Service Panel for Flushness and I: 5000 FH or 48 MO
Integrity (Passenger Gaseous ± 30 Days
Oxygen System Only)
Operationally Check Voice
I : 4000 FH or 48 MO
Recorder 4 Channels and Area 23-71-00-710-001-A00 Ref. MPG-1483 Section-II
± 30 Days
Microphone
Operationally Check Underwater I : 24 MO
Locator Beacon ± 30 Days
Flight recorder systems Discard CVR Underwater Locator I: 72 MO
Beacon Battery No Tolerance
FDR DATA - Personal Computer I : 12 MO
Downloading ± 15 Days
Operationally Check FDR I : 24 MO
Underwater Locator Beacon ± 30 Days
Discard FDR Underwater Locator I : 72 MO
Beacon Battery No Tolerance
Operationally Check Entertainment I : 4000 FH or 48 MO
In-Flight Entertainment system 23-35-21-710-001-A00 Ref. MPG-1483 Section-II
Cabinet Fans ± 30 Days
Functionally Check Transponder
MODE “ S “ Transponder Ref. CAAT (ENG-01)
System and Check the correct I : 24 MO 34-52-00-720-001-A00
ICAO 24-BIT Requirement
Mode S address
Special Rules Pertaining to EASA Ref. MPG-1483 Ref. MPG-1483
National Requirements Ref. MPG-1483 Section-III
Certification Section-III Section-III
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2.5 Specific structural maintenance programs

The structural maintenance program is designed to provide timely detection and repair of structural damage
which may occur. Detection of corrosion, stress corrosion, minor accidental damage and fatigue cracking by
visual and/or NDT procedures considered. The Specific structural are these;
a) Door
b) Fuselage
c) Nacelles/Pylons
d) Stabilizers
e) Windows
f) Wings
The Structural repair shall refer to SRM manual and SSID shall refer to Corrosion control manual which
issued by TCH.
Noted: No repeat inspection for repair assessment in SRM. The Aircraft Zoning refer to Appendix-B
2.6 Repairs and Modifications
Repairs or modifications which have been carried out to the aircraft, engine, components or radio after
original manufacturer must be recorded in the appropriate maintenance log book.
Any repair, modification or STC that contains Instructions for Continued Airworthiness (ICA’s) shall have
the ICA included in this program. Scheduled Inspection Checklists and Worksheets shall be amended to include
the additional ICA instructions
Refer to ACA-ENG-GMM, Part-1, Section 1.7
2.7 RVSM and PBN Maintenance Procedures
2.7.1 RVSM Maintenance Procedures

Refer to Operation Manual (OM) Part-A Appendix B – Special Operations
- Chapter 2 RVSM 2.2 RVSM maintenance procedures
- Chapter 2 RVSM 2.2.1 Maintenance Program
- Chapter 2 RVSM 2.2.5 Maintenance Training
2.7.2 PBN Maintenance Procedures
Refer to Operation Manual (OM) Part-A Appendix B – Special Operations

- Chapter 1 PBN 1.5 PBN maintenance program
2.8 Ageing Aircraft System
Not applicable by refer from manufacturer.
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2.9 Critical Design Configuration Control Limitation (CDCCL)
Refer to Critical Design Configuration Control Limitation (CDCCL) refer to Appendix-A,section A2.4
and A2.5 in Maintenance Planning Guide (MPG-1483)
For Maintenance requirements refer to Scheduled Maintenance Requiremetns Documents (SMRD-
1533) Section-II
3.0 Aircraft Electrical Wiring Interconnect System (EWIS)
EWIS refer to Standard Wiring Practices Manual (SWPM-4145).
3.1 Limit Of Validity (LOV)
Not applicable by refer from manufacturer. TCH apply the DSG concept.
The Design Service Goal (DSG) is the period of time in Flight Hours and Flight Cycles
established at design and/or certification during which the aircraft structures will be inspected as per
Maintenance Program Requirements and will be reasonably free from significant cracking. The DSG for
Legacy EMB-135BJ (Legacy 600) is defined as 55,000FH and 20,000FC (whichever occurs first). ACA
Company shall should contact TCH (Embraer) for more information when aircraft reaches 36,000FH or
13,000FC (65% of DSG).
Reports of structural significant defects should be submitted to the CAAT, as required under
CAAT regulations. In addition, a structural inspection summary shall be submitted to TCH (EMBRAER)
for inspection accomplished on all items of this section. All significant structural defects found shall also
be reported. Based on these reports, TCH (EMBRAER) will evaluate and issue the results of the
Structural Program fleet. The report should show the task or the SSI and zone, the aircraft accumulated
flight cycles and age, and a description of the structural significant defects.
3.2 MP Amendments and Review
This Maintenance Programme must be reviewed as least annually to ensure that it stills reflect the
latest TCH maintenance publications and procedures. In case of those data were amended during that period or
modifications, STC’s or repairs having an impact on continuing airworthiness have been incorporated, this
Maintenance Programme must be revised in the shortest delay.
In case of need the amendment to the Maintenance Schedule.Head of Engineer shall submitted to
CAAT for agreement and subsequent approval. To request for approval of the Maintenance Schedule
amendment, an operator shall write to CAAT. The letter shall be accompanied by the Maintenance Schedule
Amendment Request Form (See Section-4 Appendix-D).
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3.3 Airworthiness Limitation Items (ALIs)
This Airworthiness Limitations items has been compiled to collate the component lives for Legacy 600.
The ALIs is refer to Maintenance Planning Guide (MPG-1483) , Appendix-A.
3.4 Maintenance Certificate release to service (CRS)
Refer to ACA-ENG-GMM, Part-1 Continuing Airworthiness Procedure, Section 1.3.1.5 “Maintenance

Certification.
3.5 CVR/FDR Download Procedures
AC Aviation determined the CVR/FDR data download by carry out to Contracted Maintenance. The
interval time of data download is 12 months Downloaded data shall keep in electronic device such as
DVD/Server computer at Operation office.
A flight recorder system shall be considered unserviceable if there is a significant period of poor quality
data, unintelligible signals, or if one or more of the mandatory parameters is not recorded correctly. The criteria
to judgement the equipment inoperative is 95% of parameters that necessary to be recorded in flight recorder
system are listed (refer to ADCA for the Air Navigation by Aeroplane of AOC holders)
3.6 Calibration of the FDR system
Calibration of the FDR system shall be:
3.6.1 For those parameters which have sensors dedicated only to the FDR and are not checked by
other means, recalibration shall be carried out at least every 5 years.
3.6.2 When the parameters of altitude and airspeed are provided by sensors that are dedicated to the
FDR system, there shall be a recalibration performed as at least every 2 years.
3.7 Pre-Flight /Post-Flight
Maintenance Pre-flight inspection is to be performed before the first flight of the day. The objective of
this inspection is to ensure that the aircraft is ready to fly and accordance with Airworthiness regulations of
CAAT.
Post-Flight is to be performed after flight complete. The objective of this inspection is to check/find out
any damage or defect of Aircraft.
Refer ACA-ENG-MP-DID-F01 Preflight inspection form (see appendix C-1)
Refer ACA-ENG-MP-DID-F02 Postflight inspection form (see appendix C-2)
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3.8 Dent And Buckle Mapping
The “Dent & Buckle Mapping” allows to know the presence and the location of external structural
damages not involving flight safety. Where an external structural damage not involving flight safety is found in
the airplane, Engineer or Certifying Staff must fill in the form reporting all related information (dimensions, SRM
references, engineering communication, etc.) Dent and Buckle chart refer to ACA-ENG-MP-DID-F03
Reference manual
- EMB-135BJ ANAC APPROVED STRUCTURAL REPAIR MANUAL (SRM-1422)

- AIRCRAFT MAINTENANCE MANUAL PART II AMM-145/6020
Remark : At any Annual-Check, the Dent and Buckle chart shall verify the growth size of damaged, if found any
damaged over specification. These damaged must be repair by approved MRO and report to TCH by refer to
SRM-1422.
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Section 1 Scheduled Maintenance Requirenents- REVISION : 0
General
DATE : 05/07/2019
Section 1 Scheduled Maintenance Requirenents - General

1.Introduction
This manual outlines the initial minimum scheduled maintenance inspection requirements for the EMB-
135 BJ aircraft, as approved by the Origin of TCH .
The EMB -135 BJ Maintenance Planning Guide Report is considered a part of the Instructions for
Continued Airworthiness complying with appendix H of RBHA-25, appendix H FAR 25, and JAR 25.
The EMB-135BJ version aircraft is defined as follows:
– Aircraft Not Equipped with Ventral Fuel Tank and AE3007A2 Engines, commercially called Legacy 600 and
identified in the MPG as L600.
This document also brings identification of the aircraft model to which each task is applicable. The
objective of the expression "effectivity" is to define the applicability of each task. The effectivity described here
is applicable to all sections throughout this document. The task effectivity is:
– L600, applicable to model EMB-135BJ.
The intent of the MPG is to provide owners/operators with scheduled maintenance requirements to
assure aircraft continued airworthiness. The MSG-3 analysis methodology was used to generate the
maintenance requirements. It was also developed in accordance with the guidelines stated in the EMB-135BJ
Procedures Guideline (PG-135/1388).
"Maintenance Requirement" is every action that needs to be performed periodically in order to avoid
hazard to the aircraft that may have safety operational or economic impacts.
This document also contains information useful for maintenance planning.
This report is based on an average annual utilization equal or lower than 2,700 FH and a cycle rate
equal or lower than 1 FC/2.75 FH. This rate is included for information only and shall not be used for intervals
conversion.
The Legacy EMB-135BJ MPG Report has been developed based on EMB-145 MRB Report (MRB
145/1150 Revision 5), and followed the procedures contained in the EMB-135BJ Procedures Guideline (PG-
135/1388)
2.General Rules
Engineer and /or Contracted Maintenance shall work out details and responsibilities for accomplishing
the maintenance procedures required by this document and associated technical manuals.
Within this document, the terms "check", "inspection" and "test" are not intended to designate a level of
skill required to accomplish the requirement.
Lubrication and servicing requirements specified in this manual arise from the MSG-3 analysis, and do
not necessarily represent the complete lubrication and servicing program for the aircraft. Therefore,
Engineer and /or Contracted Maintenance should refer to the AMM Chapter 12, for complete
instructions.
Task and interval requirements quoted in the MPG Report are identified from application of MSG-3 logic
and shall not be unduly influenced by National Requirements coming from the Airworthiness Authority / Agency
(e.g. FAA) or any other body within the country of the signing MPG member (e.g. DOT in the USA). MPG
Section or Appendix to cover National Requirements should only be required when either agreement cannot be
reached between MPG members on the outcome of the application of MSG-3 logic or there is a regulatory
reason why the result must be managed in a different way by carriers operating under the registry of the signing
MPG state (e.g. FAA requirements on handling Fuel Tank Safety and EWIS tasks).
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3.Interval
The intervals are given in Flight Hours (FH), Flight (operational) Cycles (FC), APU Operating Hours (AH), APU
Cycle (AC) or Calendar Time (MO), used when appropriate.
Whenever a task has dual frequencies, it must be accomplished at WHICHEVER PERIOD OCCURS FIRST.
The maintenance start counting date of the aircraft is the date informed in an Embraer Technical Disposition
with a recommended date to start counting calendar requirements.
4.Flexibility
The flexible maintenance program consists in a tolerance for the maintenance inspection threshold and
maintenance inspection intervals and is applied only where local regulatory authorities permit.
The tolerance is applied only for calendar threshold and calendar intervals and cannot be used if the Flight Hour
(FH), Flight Cycle (FC) or APU hour (AH), APU Cycle (AC) threshold or interval were 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.
PERIOD IN WHICH THE SCHEDULED INSPECTION ACCOMPLISHMENT IS CONSIDERED ON TIME

INSPECTION MAXIMUM ALLOWABLE WINDOW FOR ACCOMPLISHMENT
TOLERANCE (the task due date must be the center of the window)
06-Month Tasks ± 15 Days 31 Days
NOTE: Some tasks with intervals listed above do not have tolerances implemented. Each task shall be
consulted in the MPG related Section in order to determine its correct tolerance value.
The task tolerance can be applied to the tasks at all times, even in two consecutive inspections provided the
correct tolerance value of each task is observed. Tolerance values greater than the ones defined for each task
are not allowed to be applied to the calendar intervals and calendar thresholds.
SOME MPG TASKS DO NOT HAVE TOLERANCES IMPLEMENTED AND SHALL NOT BE POSTPONED
WITHOUT APPROVED BY Head of Engineer and Head of Quality and Head of Safety and Head of Operation.
If the operator decides to anticipate the inspection applying tolerance values greater than the correct ones, ALL
the subsequent checks shall also be anticipated in order to avoid maintenance tasks coming due out of phase
with the major maintenance packages.
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The MPG tasks tolerances are identified as follows:
TOLERANCE MEANING
Not Applicable Tolerance is Not Applicable
± 15 Days Task Maximum Allowable Tolerance
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
bellow.
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 examples below:
EXAMPLE 1:
A calendar inspection due at an interval of 12 months was done at 12 and a half months (of aircraft operational
life). The time applied to the 12 month inspection was equal to plus 15 days, which the maximum 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 performedinspection. 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 2:
A calendar inspection due at an interval of 12 months was done at 11 months and a 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 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.
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 12 MO 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.
5.Implementation Guideline For Maintenance Plan Revisions

Revisions to the Maintenance Plan which introduce a requirement or change an existing requirement
should be evaluated for incorporation into an operator’s maintenance program. Incorporation should be made at
the next suitable opportunity by following the guideline presented below:
•When a new maintenance requirement is introduced to the Maintenance Plan, it should be accomplished in the
next scheduled threshold/ interval for that maintenance requirement. If there is a safety concern with the new
maintenance requirement, then an immediate dedicated implementation guideline will be provided in the
"Dedicated Bridging" topic through the BRIDGING PROGRAM available in Front Matter folder.
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•When an existing maintenance requirement is amended (threshold/interval reduced or increased) in the

Maintenance Plan, it should be accomplished in the next scheduled threshold/interval for that maintenance
requirement. If there is a safety concern with the amended maintenance requirement, then an immediate
dedicated implementation guideline will be provided in the "Dedicated Bridging" topic through the BRIDGING
PROGRAM available in Front Matter folder.
The implementation guideline does not apply to Airworthiness Limitation Items. Interval for tasks
accomplishment resulting from Airworthiness Directives is defined by the instructions contained in those
documents.
This Implementation Guideline does not have any relation with the tolerance applied to requirements’ interval
and threshold, described in the MPG-1483 Section 1 – Scheduled Maintenance Requirement – General, “Topic
4. Flexibility”.
6.System And Powerplant Requirements

A list of candidates for Maintenance Significant Items (MSI) was proposed by the manufacturer and approved
by the Regulatory Authorities. Each candidate was reviewed and, if selected as MSI, was subjected to the
MSG-3 logic for system and powerplant. The MSG-3 for System and Powerplant was used to develop an on-
wing scheduled maintenance program. With the exception of life-limited parts, this process does not normally
include detailed off-wing shop maintenance procedures. Off-wing detailed procedures are in accordance with
the manufacturer’s Instructions for Continued Airworthiness.
6.1 MSIs that did not Generated Tasks

This section contains a list of all MSI’s that did not generate any task after original MSG-3 analysis during the
development of inspection requirements for the EMB-145 aircraft. Also, during the analysis review for
development of the inspection requirements for the EMB-135BJ version aircraft, some additional MSI’s related
to new systems did not generate any tasks. Follow the EMB-145 original list of MSI and EMB-135BJ list of
additional MSI that did not generate any task:
MSI No. MSI DESCRIPTION MSI No. MSI DESCRIPTION

34-43 TCAS 73-31 FUEL FLOWMETER ASSY
34-51 DME 73-32 ENGINE FUEL TEMPERATURE
34-53 ADF 73-33 ENGINE FUEL FILTER IMPENDING BY-PASS
34-56 GPS 73-35 FUEL FLOW SENSING SYSTEM
34-61 FMS HONEYWELL 73-37 FUEL QUALITY
34-62 FMS UNIVERSAL 74-11 PERMANENT MAGNET ALTERNATOR
38-40 AIR SUPPLY 74-13 IGNITION EXCITER ASSY
49-11 APU COWLING 75-31 AIR SYSTEM
49-33 FUEL CONSUMPTION INDICATING 75-33
COMPRESSOR VARIABLE VANE ACTUATION SYSTEM
49-42 APU STARTING
49-53 COMPRESSOR CONTROL 75-41 ENGINE AIR TEMPERATURE
49-71 RPM INDICATING 75-43 ENGINE AIR PRESSURE
49-72 EGT INDICATING 77-11 SPEED INDICATING
49-74 MAINTENANCE INDICATING 77-41 INTEGRATED ENGINE INSTRUMENT SYSTEM
49-81 EXHAUST COLLECTOR 79-11 OIL TANK
49-93 OIL SYSTEM WARNING 79-21 OIL PRESSURIZATION
71-30 ENGINE FIRE SEALS ASSY 79-31 OIL TEMPERATURE SYSTEM
71-51 ENGINE HARNESS ASSY 79-32 LOW OIL PRESSURE WARNING
71-72 ENGINE VENT ASSY 79-33 OIL PRESSURE SYSTEM
72-25 FAN FRAME, VANE & SUPPORT ASSEMBLY
79-35 OIL QUANTITY SYSTEM
72-37 COMPRESSOR CASE ASSEMBLY
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7. Structural Requirements
Structural 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 obvius 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.
Design Service Goal (DSG) is the period of time in Flight Hours and Flight Cycles established at design
and/or certification during which the aircraft structures will be inspected as per Maintenance Program
Requirements and will be reasonably free from significant cracking. The DSG for Legacy EMB-135BJ (Legacy
600) is defined as 55,000FH and 20,000FC (whichever occurs first). Aircraft operators should contact Embraer
for more information when aircraft reaches 36,000FH or 13,000FC (65% of DSG) if they intend to overcome the
aircraft DSG (55,000FH or 20,000FC).
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.
Reports of structural significant defects should be submitted to the CAAT , as required under CAAT
regulations. In addition, a structural inspection summary should be submitted to TCH (EMBRAER) for
inspection accomplished on all items of this section. All significant structural defects found should also be
reported. Based on these reports, TCH (EMBRAER) will evaluate and issue the results of the Structural
Program fleet. The report should show the task or the SSI and zone, the aircraft accumulated flight cycles and
age, and a description of the structural significant defects.
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 TCH (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 Tolerance Analysis and Full Scale Fatigue Test, will occur
after a threshold(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 –
Appendix A of this document in order to establish a Fatigue Threshold Limit for all SSI’s whose inspection is
governed by fatigue concerns.
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 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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8. Corrosion Requirements
Corrosion 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.
8.1 Reporting Of Inspection Results
AC Aviation and Maintenance Contracted 's control program shall keep accurate records of all corrosion
treatment after detection. Reports of corrosion findings should be sent to TCH at address
contact.center@embraer.com.
Based on these reports, TCH (Embraer) will evaluate the results of the Corrosion Prevention and
Control Program of the fleet, and propose adjustments, when necessary.
It is not mandatory to report corrosion level 1. For corrosion levels 2 and 3 definition and reporting, refer
to Corrosion Prevention Manual (CPM) chapter 51-11-01.
8.2 Definition Of Corrosion Level
Corrosion level is a means of determining the effectiveness of a CPCP relative to a given corrosion
finding in terms of the severity of corrosion and the potential consequences to the continued airworthiness of
the owner's/operator’s fleet. The corrosion level 1 definition is given as follows:
Corrosion Leve 1
Damage occurring between successive inspections that is within allowable damage limits;
or,
Damage occurring between successive inspections that does not require structural reinforcement, replacement
or new damage tolerance based inspections;
or,
Corrosion occurring between successive inspections that exceeds allowable limits but can be attributed to an
event not typical of operator usage of other aircraft in the same fleet;
or,
Light corrosion occurring repeatedly between inspections that eventually requires structural reinforcement,
replacement or new damage tolerance based inspections.
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9. Powerplant and APU Rules
9.1 Powerplant rule

The logic used to develop an on-aircraft scheduled maintenance program, includes the periodic
inspection requirements specified by Rolls Royce for both the task oriented (trend monitoring) and the fixed-
interval (hard-time) maintenance programs. Operators may choose between both of them. To accomplish the
tasks in a task-oriented maintenance program, ACA company and Maintenance Contracted must follow the
tasks listed in the MPG, SECTION 2 - SCHEDULED MAINTENANCE REQUIREMENTS - LIST OF
REQUIREMENTS. Conversely, when accomplishing the fixed interval program, operators must follow the
sequence of tasks listed in the AE3007 Maintenance Manual (P/N CSP34022) in its latest revision status.
In addition to the schedule inspection requirements, the engine task-oriented maintenance program
requires that the operator should monitor engine operation and health through information obtained from:
Cockpit (EICAS) Engine Instrumentation

Cockpit (EICAS) Messages
Cockpit (MFD) Maintenance Messages Aircraft (CMC) Maintenance Data Engine Trend Monitoring Chart
Analysis
Note The CMC download interval is every 30 days. The company that intends to change from a maintenance
program to the other must follow the instructions contained in AE3007 Maintenance Manual (P/N CSP34022)
Chapter 5 in its latest revision status.
There are some tasks that accomplish the same maintenance requirements that are presented in the MPG and
in the AE3007 Maintenance Manual. These tasks are listed in the cross-reference table as below:
MPG-1483 REFERENCE RR AE3007 MAINTENANCE

NUMBER MANUAL TASK P/N CSP34022
71-Z411-214-001-A00 72-00-00-200-801
72-20-00-212-001-A00
73-21-00-211-001-A00
79-25-02-211-001-A00
(DELETED)
79-27-00-211-001-A00
72-21-01-220-001-A00 72-21-15-200-801
72-62-01-212-001-A00 72-63-10-200-804
72-63-01-710-001-A00 72-63-10-700-801
73-11-00-960-001-A00 73-21-10-000-802
73-11-10-130-001-A00 73-11-10-000-801
73-11-10-130-001-A01 73-11-10-400-801
73-21-06-720-001-A00 73-37-10-700-801
MPG-1483 REFERENCE RR AE3007 MAINTENANCE

NUMBER MANUAL TASK P/N CSP34022
73-22-01-720-003-A00 73-25-10
73-30-04-220-001-A00 73-25-10-000-801
73-25-10-200-803
73-25-10-400-801
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74-21-01-960-001-A00 74-21-10-000-801
74-21-10-000-802
74-21-10-400-801
79-34-00-212-001-A00 79-30-00-200-801
74-21-10-400-802
79-34-00-212-001-A01
79-34-01-720-001-A00 79-37-10-700-801
79-37-00-720-001-A00 79-37-15-700-801
9.2 APU Rule
The minimum on aircraft maintenance Inspection/Requirements for the APU is contained in this document. In
addition to the minimum maintenance program, Engineer shall perform monthly monitor the health of the APU in
order to ensure the availability and economic operation of the equipment. This health monitoring is performed
through information obtained from:
- APU FADEC
- Aircraft (CMC) Maintenance Data
Note : The MSG-3 logic was used to develop an initial minimum on-aicraft APU maintenance requirements. This
process establishes the minimum maintenance requirements that an operator may use to develop their own
initial maitenance program. For Hamilton Sundstrand recommended maintenance/inspection items and
Airworthiness Limitation related to this APU refer to latest revision of Hamilton Sundstrand publications Model
Number T-62T-40C14, Type APS 500R.
10. Zonal Requirments
The Zonal inspection requirements consist of a series of General Visual Inspections (GVI) developed for
defined zones in accordance with MSG-3 methodology. A General Visual Inspection (GVI) is a visual
examination of an internal area, installation or assembly to detcted obvius damage, failure or irregularity.
A zonal inspection is essentiallly a GVI of an area or zone to detect obvious unsatisfactory conditions and
discrepancies of any system and structural items, including the L/HIRF protections.
Also, the Legacy 600 uses the Enhanced Zonal Analysis Procedure (EZAP) in accordance with the guidelines
stated in the MSG-3 document.
For the zones that contain electrical wiring and have potential for presence of combustible material, the
enhanced zonal analysis is performed and permits the identification of stand-alone inspections (either General
Visual Inspection or Detailed Inspection) as well as tasks to minimize the possibility of accumulation of
combustible materials (restoration - cleaning tasks). The application of this procedure ensures that appropriate
attention is given to wiring installatiions. All EZAP requirements generated are presented in the SECTION 2 -
SCHEDULE MAINTENANCE REQUIREMENTS - LIST OF REQUIREMENTS.
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When necessary, access panel, fairings, doors, seats, carpets, headliner and sidewall trim panels, including
insulation, may be removed/opened to give access and permit a complete zonal inspection.
Control surface deflection may also be necessary. Clean-up procedures should be used prior to performing
zonal inspections. Any panels, fairings, or other items opened/removed to gain access to the zone under
inspection should also be inspected.
The GVI zonal inspection encompasses the following, but are not limited to:
• Examination of components for proper mounting or attachment to the related support or adjacent
equipment, comprising: safetying, clamp looseness, excessive play, misalignment, loose tubing and
hoses or electrical connections, missing rivets, bolts or screws, and loose connections or hinges.
• Inspection of structural parts, for loose rivets, nicks, dents, cracks, separation of bonding, corrosion,
jamming, cleaning, erosion, deformation, warp, deteriorated protective treatment, and overheating.
• Inspection of ducts, hoses, and piping system components (such as hydraulic, fuel, air conditioning,
pitot-static, oxygen, etc.) for nicks, dents, cleaning, cracks, chafing, leakage, distortion, wear,
corrosion, clogging, cuts, and overheating.
• Inspection of electrical and electronic system cabling for erosion, poor insulation, cuts, deformation,
poor cleaning, chafing, overheating, defective soldering, including such items as loose wires,
connectors backshell looseness, and shields termination at tag-rings, strain reliefs and presence of
corrosion associated with HIRF protection.
• Inspection of parts or areas made out of composite, plastic, fabric, etc. for delamination, scratches,
uncleanliness, cracks, chafing, crazing, deterioration, erosion, wear, distortion, defective protection,
flaking, bruise, loss of flexibility, overheating, and contamination.
• Inspection of parts of flight control mechanisms for alignment, distortion, buckling, cleaning, cuts,
tears, chafing, fraying and wear of cables, cracks, separation of bonding, jamming, and corrosion.
10.1 EWIS Tasks

Tasks with the note "EWIS" (Electrical Wiring Interconnection 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 SECTION 2 - SCHEDULED MAINTENANCE
REQUIREMENTS - LIST OF REQUIREMENTS (ATA chapter 20).
10.2 List Of SSI’s that were transferred from Structural Inspection Program to Zonal
Inspection Program
SSI SIDE ZONE DESCRIPTION REFERENCE NUMBER

32-10-07 EXT 721/731 GVI OF UPPER MAIN BRACE STRUT ASSY - MLG 32-Z721-213-001-A00
32-10-08 EXT 721/731 GVI OF LOWER MAIN BRACE STRUT ASSY - MLG 32-Z721-213-001-A00
53-10-20 EXT 223/224 GVI OF WINDSHIELD LATERAL POST AND ITS ATTACHMENT 53-Z223-213-001-A00
57-22-44 EXT 531/631 GVI OF SPAR 1 WING STUB ATTACHMENT 57-Z531-213-001-A00
57-28-63 EXT 541/641 GVI OF SPAR 3 ATTACHMENT, TORQUE BOX 57-Z541-213-001-A00
57-50-82 EXT 571/671 GVI OF SKIN BETWEEN SPAR, FLAPS 57-Z571-213-001-A00
572/672 57-Z572-213-001-A00
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10.3 List Of Inspection that were transferred from System & Powerplant Inspection
Program to Zonal Inspection Program
SYSTEM AND POWERPLANT INSPECTION PROGRAM ZONAL PROGRAM

REFERENCE NUMBER DESCRIPTION CATEGORY REFERENCE NUMBER
21-21-02-212-001-A00 Perform a General Visual Inspection of Air Conditioning 7 53-Z123-214-001-A00
System Outlets

System Ducts

System Ducts 53-Z141-214-001-A00
53-Z151-214-002-A00
53-Z161-214-001-A00
53-Z171-214-001-A00

21-23-04-212-001-A00 Perform a General Visual Inspection of Inlet Muffler Screen 7 53-Z151-214-002-A00

for Obstruction
21-24-02-212-001-A00 Perform a General Visual Inspection of Inlet Muffler Screen 7 53-Z161-214-001-A00

for Obstruction
25-27-00-212-001-A00 Perform a General Visual Inspection of Partitions 9 53-Z231-214-001-A00

Attaching Points for Condition and Security 53-Z241-214-001-A00
53-Z261-214-001-A00

System Outlets
26-22-04-212-001-A00 Perform a General Visual Inspection of APU Discharge 9 53-Z313-214-001-A00

Piping for Cracks, Bent or
Loose Fittings
26-23-05-212-001-A00 Perform a general visual inspection of discharge piping for 6 53-Z273-214-002-A00

cracks, bent and loose fittings, and nozzles for damage. 53-Z273-214-002-A01
27-21-01-212-001-A00 Perform a General Visual Inspection of Mechanical 9 53-Z171-214-001-A00

Linkage in the Autopilot Tie-In
27-21-01-212-002-A00 Perform a General Visual Inspection of Main Control Input 9 53-Z123-214-001-A00

Path 53-Z131-214-001-A00
53-Z141-214-001-A00
53-Z151-214-002-A00
53-Z161-214-001-A00
53-Z171-214-001-A00
53-Z273-214-002-A00
53-Z273-214-002-A01
53-Z311-214-001-A00
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27-21-04-212-001-A00 Perform a General Visual Inspection of Trailing Rudder 6 55-Z326-214-001-A00

Connecting Rods
27-31-01-212-001-A00 Perform a General Visual Inspection of Elevator 6 53-Z123-214-001-A00

Disconnect System
27-31-01-212-002-A00 Perform a General Visual Inspection of Stick Pusher 6 53-Z123-214-001-A00

Actuator Mechanical Linkage to FWD Quadrant
27-31-01-212-003-A00 Perform a General Visual Inspection of Elevator Control 6 53-Z123-214-001-A00

Cables 53-Z131-214-001-A00
53-Z141-214-001-A00
53-Z151-214-002-A00
53-Z161-214-001-A00
53-Z171-214-001-A00
55-Z324-214-001-A00

27-62-00-212-001-A00 Perform a General Visual Inspection of Spoilers Surface 6 57-Z571-214-001-A00

Hinge Points
28-11-05-212-001-A00 Perform a General Visual Inspection of Fuel Filler Cap 9 57-Z541-214-001-A00

Seal for Condition
28-12-02-212-001-A00 Perform a General Visual Inspection of Tank Vent 9 57-Z531-214-001-A00
plumbing for Looseness Fitting
28-21-02-212-001-A00 Perform a General Visual Inspection of Ejector Pump for 9 57-Z531-214-001-A00
Integrity and that the
Screen and Nozzle are not Closed
28-21-09-212-001-A00 Perform a General Visual Inspection of Motive Fuel Supply 9 57-Z531-214-001-A00

Line for Leakage
29-10-17-212-001-A00 Perform a General Visual Inspection of Tubing 6 53-Z123-214-001-A00
53-Z131-214-001-A00
53-Z141-214-001-A00
53-Z151-214-002-A00
53-Z161-214-001-A00
53-Z171-214-001-A00
32-10-08-212-001-A00 Perform a General Visual Inspection of Main Landing gear 9 32-Z721-213-001-A00
Door Seals
NOTE: If installed
32-20-05-212-001-A00 Perform a General Visual Inspection of Door 6 32-Z711-213-001-A00

32-20-06-212-001-A00 Perform a General Visual Inspection of Nose Landing Gear 9 32-Z711-213-001-A00
Door Seals
NOTE: If installed.
32-33-00-212-001-A00 Perform a General Visual Inspection of LG Extension and 6 32-Z711-213-001-A00
Retraction 32-Z721-213-001-A00
System Components
36-11-09-212-001-A00 Perform a General Visual Inspection of Duct Lines 9 53-Z151-214-002-A00

53-Z161-214-001-A00
53-Z171-214-001-A00
53-Z311-214-001-A00
55-Z324-214-001-A00
49-20-60-212-001-A00 Perform a General Visual Inspection of APU AIR Inlet Duct 9 53-Z313-214-001-A00
Assy 53-Z313-214-001-A01
52-18-04-212-001-A00 Perform a General Visual Inspection of Locking 6 52-Z811-214-001-A00

Mechanism And Actuation Path
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52-18-05-212-001-A00 Perform a General Visual Inspection of Pivoting 6 52-Z811-214-001-A00

Mechanism
52-31-00-212-001-A00 Perform a General Visual Inspection of Baggage Door 6 52-Z813-214-001-A00

Actuating and Locking
Mechanism

71-10-00-212-001-A00 Perform a General Visual Inspection of Cowling 9 71-Z411-214-001-A00
Aerodynamic Surfaces for
Condition and Security
71-10-00-212-002-A00 Perform a General Visual Inspection of the Cowling 9 71-Z411-214-001-A00
Pressure Relief Door for
71-52-01-212-001-A00 Perform a General Visual Inspection of Engine Bonding 9 71-Z411-214-001-A00
Straps for General
71-60-01-212-001-A00 Perform a General Visual Inspection of the Air Intake 9 71-Z411-214-001-A00

Aerodynamic Surfaces for
71-71-00-212-001-A00 Perform a General Visual Inspection of Engine Drain Assy 9 71-Z411-214-001-A00

for Security/ Cracks
72-21-00-212-001-A00 Perform a General Visual Inspection on the Fan Assy 6 71-Z411-213-001-A00
72-21-03-212-001-A00 Perform a General Visual Inspection on the Fan Bladesç 6 71-Z411-213-001-A00
72-63-01-212-001-A00 Perform a General Visual Inspection on the Accessory 6 71-Z411-214-001-A00

Drive Gearbox Assy
72-73-00-212-001-A00 Perform a General Visual Inspection on the Outer Bypass 9 71-Z411-214-001-A00
Duct and Rear Support
Assy
73-13-00-212-001-A00 Perform a General Visual Inspection on the Primary 6 71-Z411-214-001-A00

System Plumbing
74-30-02-212-001-A00 Perform a General Visual Inspection of Electrical Harness 6 71-Z411-214-001-A00
for Condition and
Chafing
76-11-00-212-001-A00 Perform a General Visual Inspection on the Engine Control 9 71-Z411-214-001-A00

Harness
77-21-00-212-001-A00 Perform a General Visual Inspection on the Harness 9 71-Z411-214-001-A00
78-10-01-212-001-A00 Perform a General Visual Inspection on the plain exhaust 9 78-Z416-214-001-A00

assy to detect damage failure or irregularities
78-31-00-212-001-A00 Perform a General Visual Inspection on the thrust 9 78-Z416-214-001-A00

reverser structure to detect damage, failure, or
irregularities
79-25-00-211-001-A00 Perform a General Visual Inspection on the Fuel Cooled 9 71-Z411-214-001-A00
Oil Cooler Assy (FCOC)
79-25-02-211-001-A00 Visually Check Fuel Cooled Assembly (FCOC) 9 71-Z411-214-001-A00
NOTE: Applicable only for Task Oriented Maintenance 71-Z411-214-001-A01
Program
80-10-00-212-001-A00 Perform a General Visual Inspection on the Ducts for 6 71-Z411-214-001-A00

Cracks and General
Condition
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11. List of Scheduled Maintenance Requirments Presentation
The maintenance requirements are presented per chapter as below:
MAINTENANCE CAT / THR/INT/

REQUIREMENT MAINTENANCE
REQUIREMENT SOURCE CSD ZONES TOLERANCE EFFECT
TYPE/TITLE PROCEDURE
a b c d e f g h
a - MAINTENANCE REQUIREMENT
The AMTOSS (Aircraft Maintenance Task Oriented Support System) numbering system is used to
generate the reference number at the Legacy BJ – MPG and is also used as a cross-reference between
the Legacy BJ – MPG and the EMBRAER Aircraft Maintenance Manual, Non-Destructive Inspection
Manual, and Corrosion Prevention and Control Manual. To find the applicable task on the Aircraft
Maintenance Manual, it is necessary to consult the cross-reference table on the Introduction of the
Aircraft Maintenance Manual. The EMBRAER manuals contain the information on how to perform the
tasks herein. The Reference Number is based on ATA-100 Specification.
b - SOURCE
The source column defines to which maintenance requirement program belongs:
• SYSTEM (SYS) - Maintenance Requirements derived from the MSG-3 System and Powerplant
analysis.
• STRUCTURE (STR) - Maintenance Requirements derived from the MSG-3 Structures Analysis
(Accidental Damage critical source).
• ZONAL (ZNL) - Maintenance Requirements derived from the MSG-3 Zonal Analysis.
• CORROSION PREVENTION & CONTROL PROGRAM (CPCP) - Maintenance Requirements derived
from the MSG-3 Structures Analysis (Environmental Damage critical source).
• CAT II - Maintenance Requirements necessary to assure the level of performance and reliability of the
related systems, to comply with the performance requirements for CAT II operation prescribed in AC 120-
29 and JAR AWO Subpart 2 document.
c - CAT/CSD
The following categories (CAT) are established based on Systems and Powerplant MSG-3 methodology,
where the associated functional failure effect is evaluated and categorized as following.
• 5 - Evident Safety
• 6 - Evident Operational
• 7 - Evident Economic
• 8 - Hidden Safety
• 9 - Hidden Non-Safety
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Structures Critical Source of Damage (CSD): The following classification is based on the Environmental
Deterioration and Accidental Damage aspects and susceptibility, being the most critical published with
the task.
• AD - Accidental Damage
• ED - Environmental Damage
d - REQUIREMENT TYPE/TITLE
• Description of the maintenance requirement.
e - ZONES - Zones of the aircraft where each task is accomplished. refer to AMM 06-30-00-1 for a full
map and description of the zones.
f- THR / INT / TOLERANCE
• THRESHOLD: Time for accomplishment of first instance of related maintenance action.

• INTERVAL: Maximum time at which each requirement must be accomplished. This interval may be
defined in FH (Flight Hours), FC (Flight Cycles) or MO (Calendar Months), or a combination of them,
observing the related notes (NOTE), when applicable.
• TOLERANCE: Task Tolerance as defined in the item 6. FLEXIBILITY described in this section.
g - MAINTENANCE PROCEDURE - Maintenance task which covers each specific requirement. Tasks
listed in this column may refer to the following manuals:
• AMM - Aircraft Maintenance Manual

• NDI - Non-Destructive Inspection
• CPM - Corrosion Prevention Manual
h - EFFECT - Maintenance requirement must be complied according to aircraft applicability:
• L600 (Legacy 600)

• L650 (Legacy 650)
• ALL (Both: Legacy 600 and Legacy 650)
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12. Abbreviations
Table 1 - List of Abbreviations
AC ADVISORY CIRCULAR
ACO AIRCRAFT CERTIFICATION OFFICE
AD ACCIDENTAL DAMAGE
ADC AIR DATA COMPUTER
AFCS AUTOMATIC FLIGHT CONTROL SYSTEM
AH APU OPERATING HOURS
AHRS ATTITUDE AND HEADING REFERENCE SYSTEM
ALI AIRWORTHINESS LIMITATION INSTRUCTIONS
AMTOSS AIRCRAFT MAINTENANCE TASK ORIENTED SUPPORT SYSTEM
ANAC AGÊNCIA NACIONAL DE AVIAÇÃO CIVIL
AOA ANGLE OF ATTACK
APU AIRBORNE POWER UNIT
ASSY ASSEMBLY
ATA AIR TRANSPORT ASSOCIATION
ATS AIR TURBINE STARTER
BITE BUILT-IN TEST EQUIPMENT
CAA CIVIL AVIATION AUTHORITY (UNITED KINGDOM)
CAAC CIVIL AVIATION ADMINISTRATION OF CHINA
CCMR CANDIDATE CERTIFICATION MAINTENANCE REQUIREMENT
CDCCL CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS
CMC CENTRAL MAINTENANCE COMPUTER
CMR CERTIFICATION MAINTENANCE REQUIREMENT
CPCP CORROSION PREVENTION AND CONTROL PROGRAM
CVR COCKPIT VOICE RECORDER
DAC DEPARTAMENTO DE AVIAÇÃO CIVIL (BRASIL)
DET DETAILED INSPECTION
DG DIRECTIONAL GYRO
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Table - List of Abbreviations (CONTINUED)
DIS DISCARD
DPI DIFFERENTIAL PRESSURE INDICATOR
DRC DATA RECORDING/CALCULATING
DRT DISCARD/REPLACE TASK
DSM DESIGN STANDARDS MANUAL
EASA EUROPEAN AVIATION SAFETY AGENCY
ECS ENVIRONMENTAL CONTROL SYSTEM
ED ENVIRONMENTAL DETERIORATION
EICAS ENGINE INDICATION AND CREW ALERTING SYSTEM
EMB EMBRAER
EMDP ENGINE MOTOR DRIVEN PUMP
EWIS ELECTRICAL WIRING INTERCONNECTION SYSTEM
FAA FEDERAL AVIATION ADMINISTRATION (USA)
ADEC FULL AUTHORITY DIGITAL ENGINE CONTROL
FAR FEDERAL AVIATION REGULATION
FC FLIGHT CYCLE
FCOC FUEL COOLED OIL COOLER
FCU FUEL CONDITIONING UNIT
FD FATIGUE DAMAGE
FDA FATIGUE DAMAGE ANALYSIS
FDR FATIGUE DAMAGE RATING
FDR FLIGHT DATA RECORDER
FFS FLAP FLEXIBLE SHAFT
FH F LIGHT HOUR
FPMU FUEL PUMP AND METERING UNIT
FQIS FUEL QUANTITY INDICATION SYSTEM
FR FRAME
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FSA FLAP SCREW-JACK ACTUATOR

FSL FUEL SYSTEM LIMITATION
FNC FUNCTIONAL CHECK
FUS FUSELAGE
FWD FORWARD
GPU GROUND POWER UNIT
GPWS GROUND PROXIMITY WARNING SYSTEM
GVI GENERAL VISUAL INSPECTION
HLEIS HIGH LEVEL EXCEEDING INDICATION SYSTEM
HP HIGH PRESSURE
HPT HIGH PRESSURE TURBINE
HYD HYDRAULIC
IN INSPECTION
ISC INDUSTRY STEERING COMMITTEE
JAR JOINT AIRWORTHINESS REQUIREMENTS (EUROPE)
LCU LEVEL CONTROL UNIT
LG LANDING GEAR
LH LEFT HAND
LP LOW PRESSURE
LUB LUBRICATION
LWR LOWER
LPT LOW PRESSURE TURBINE
MEL MINIMUM EQUIPMENT LIST
MMEL MASTER MINIMUM EQUIPMENT LIST
MFD MULTI-FUNCTION DISPLAY
MFR MANUFACTURER
MLG MAIN LANDING GEAR
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MLGB MAIN LANDING GEAR BAY

MO MONTH
MPD MAINTENANCE PLANNING DOCUMENT
MPG MAINTENANCE PLANNING GUIDE
MRB MAINTENANCE REVIEW BOARD
MRBR MAINTENANCE REVIEW BOARD REPORT
MRBRP MAINTENANCE REVIEW BOARD REPORT PROPOSAL
MSG MAINTENANCE STEERING GROUP
MSI MAINTENANCE SIGNIFICANT ITEM
MTBF MEAN TIME BETWEEN FAILURES
MTBUR MEAN TIME BETWEEN UNSCHEDULED REMOVALS
MWG MECHANICAL WORKING GROUP
NDI NON-DESTRUCTIVE INSPECTION
NDT NON-DESTRUCTIVE TESTING
NLG NOSE LANDING GEAR
NRU NEUTRAL RECOVERY UNIT
OPC OPERATIONAL CHECK
OVHT OVERHEAT
PCA POWER CONTROL ACTUATOR
PCU POWER CONTROL UNIT
PMI PRINCIPAL MAINTENANCE INSPECTOR
PPH POLICE PROCEDURE HANDBOOK
PG PROCEDURE GUIDELINES
PWG POWERPLANT WORKING GROUP
RBHA REQUISITO BRASILEIRO DE HOMOLOGAÇÃO AERONÁUTICA
R&M RELIABILITY AND MAINTAINABILITY
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RH RIGHT HAND
RTCA RADIO TECHNICAL COMMISSION FOR AERONAUTICS
RST RESTORATION
RVSM REDUCED VERTICAL SEPARATION MINIMUM
SDE SPECIAL DETAILED INSPECTION
SDI SPECIAL DETAILED INSPECTION
SFAR SPECIAL FEDERAL AVIATION REGULATION
SMRD SCHEDULED MAINTENANCE REQUIREMENTS DOCUMENT
SRM STRUCTURAL REPAIR MANUAL
SSA SYSTEM SAFETY ANALYSIS
SSI STRUCTURAL SIGNIFICANT ITEM
SVC SERVICE CHECK
SYS SYSTEM
SWG STRUCTURAL WORKING GROUP
TAI THERMAL ANTI-ICE
TAT TOTAL AIR TEMPERATURE
TBD TO BE DETERMINED
TBO TIME BETWEEN OVERHAULS
TBR TIME BETWEEN REMOVALS
TCAG TRANSPORT CANADA AVIATION GROUP (CANADA)
TCS TOUCH CONTROL STEERING
VC VISUAL CHECK
VCK VISUAL CHECK
YR YEAR
WG WORKING GROUP
WOW WEIGHT-ON-WHEEL
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13. Term&Definitions
TERMS DEFINITIONS
ACCIDENTAL DAMAGE (AD) Physical deterioration of an item caused by contact or impact with an object or influence
which is not a part of the aircraft, or by human error during manufacturing, operation of the
aircraft, or maintenance practices.
AGE EXPLORATION A systematic evaluation of an item based on analysis of information collected from in-
service experience.It verifies the item resistance to a deterioration process with respect to
increasing age.
AIRWORTHINESS LIMITATIONS A section of the instructions for continued airworthiness that contains each mandatory
replacement time, structural inspection interval, and related structural inspection task. This
section may also be used to define a threshold for fatigue-related inspections and the need
to control corrosion to level 1 or better. The information contained in the Airworthiness
Limitations section may be changed to reflect service and/or test experience or new analysis
methods.
AIRWORTHINES LIMITATION ITEMS FOR In terms of SFAR88, mandatory maintenance of the fuel system that can include Critical
SFAR 88 Design Configuration Control Limitations (CDCCL), inspections, or other procedures
determined necessary to ensure that unsafe conditions identified by the SFAR 88 Mandatory
Action Advisory Board do not occur and are not introduces into the fuel system as a result of
maintenance actions, repairs, or alterations throughout operational life of the airplane.
CORROSION PREVENTION AND A program of maintenance tasks implemented at a threshold designed to controll an
CONTROL PROGRAM (CPCP) aircraft structure to
Corrosion Level 1 or better.
CRITICAL DESIGN CONFIGURATION Are airworthiness limitations that define the features of the design whose integrity must be
CONTROL LIMITATIONS maintained to ensure ignition sources will not develop in the fuel tank system.
DAMAGE TOLERANCE A qualification standard for aircraft structure. An item is judged to be damage-tolerant if it
can sustain damage and the remaining structure can withstand reasonable loads without
structural failure or excessive structural deformation until the damage is detected.
DELAMINATION DISBOND Structural separation or cracking normally in the plane of the structure caused by
accidental damage, environmental effects and/or cyclic loading.
DISCARD The removal from service of an item at a specified life limit.
DIRECT ADVERSE EFFECT ON 1. Direct:

OPERATING SAFETY To be direct, the functional failure or resulting secondary damage must achieve its
effect by itself, not in combination with other functional failure (no redundancy exists and
it is a primary dispatch item).
2. Adverse Effect on Safety:
This implies that the consequences are extremely serious or possibly catastrophic and
might cause the loss of aircraft or injury to occupants.
3. Operating:
This is defined as the time interval during which passengers and crew are on board for the
purpose of flight.
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TERMS DEFINITIONS
ECONOMIC EFFECTS Failure effects which do not prevent aircraft operation, but are economically
undesirable due to added labor and material cost for aircraft or shop repair.
ELECTRICAL WIRING EWIS (ELECTRICAL WIRING INTERCONNECTION SYSTEM) means any
INTERCONNECTON SYSTEM wire, wiring device, or combination of these, including termination devices,
(EWIS) installed in any area of the airplane for the purpose of transmitting electrical
energy, including data and signals, between two or more intended termination
points. This includes wires and cables; bus bars; the termination point on
electrical devices, including those on relays, interrupters, switches, contactors,
terminal blocks and circuit breakers, and other circuit protection devices;
connectors, including feed-through connectors; connector accessories;
electrical grounding and bonding devices and their associated connections;
electrical splices; materials used to provide additional protection for wires,
including wire insulation, wire sleeving, and conduits that have electrical
termination for the purpose of bonding; shields or braids; clamps and other
devices used to route and support the wire bundle; cable tie devices; labels or
other means of identification; pressure seals; EWIS components inside
shelves, panels, racks, junction boxes, distribution panels, and backplanes
of equipment racks, including, but not limited to, circuit board backplanes, wire
integration units, and external wiring of equipment.
ENVIRONMENTAL Physical deterioration of an item strength or resistance to failure as a

DETERIORATION (ED) result of chemical interaction with the climate or environment.
FAILURE The inability of an item to perform within previously specified limits.
FAILURE CAUSE Why the functional failure occurs.
FAILURE EFFECTS What the result of a functional failure is.
FATIGUE DAMAGE (FD) The initiation of a crack or cracks due to cyclic loading and subsequent
propagation.
FATIGUE RELATED Inspections on specific aircraft selected from those which have the
SAMPLING INSPECTION highest operating age/usage in order to identify the first evidence of
PROGRAM deterioration in their condition caused by fatigue damage.
FLIGHT CYCLE A complete take-off and landing sequence.
FLIGHT HOUR With respect to maintenance time records, means the time from the moment
an aircraft leaves the surface at the earth until it touches it at the next point of
landing.
FUEL SYSTEM LIMITATIONS Mandatory maintenance inspections or other procedures determined
necessary to ensure that unsafe conditions do not occur and are not introduced
into the fuel system, each limitation will describe the specific maintenance and
inspection task, frequency and any other special requirements.
FUNCTION The normal characteristic actions of an item.

FUNCTIONAL CHECK A quantitative check to determine if one or more functions of an item is/are
within specified limits.
FUNCTIONAL FAILURE How an item failed to perform its function.
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TERMS DEFINITIONS
HIDDEN FUNCTION 1. A function which is normally active and whose cessation will not be
evident to the operating crew during performance of normal duties.
2. A function which is normally inactive and whose readiness to perform, until
it is needed, will not be evident to the operating crew during performance of
normal duties.
INHERENT LEVEL OF That level which is built into the unit and, therefore, inherent in its design. This
RELIABILITY AND SAFETY is the highest level of reliability and safety that can be expected from a unit,
system, or aircraft if it receives effective maintenance.
To achieve higher levels of reliability generally requires modification or
redesign.
INSPECTION-DETAILED An intensive visual examination of a specific structural area, system,
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 by the inspector. Inspection aids such as mirrors,
magnifying lenses, etc. may be used. Surface cleaning and elaborate access
procedures may be required.
INSPECTION-GENERAL A visual examination of an interior or exterior area, installation or assembly to
VISUAL (SURVEILLANCE) detect obvious damage, failures or irregularity. This level of inspection is made
under normally available lighting conditions such as daylight, hangar lighting,
flashlight or drop-light 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.
INSPECTION-SPECIAL DETAILED 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.
ITEM Any level of hardware assembly (i.e., system, sub-system, module,
accessory, component, unit, part, etc.).
LUBRICATION AND SERVICING Any act of lubricating or servicing for the purpose of maintaining inherent
design capabilities.
MAINTENANCE Items identified by the manufacture whose failure:
SIGNIFICANT ITEM - (MSI) a. Could affect safety (on ground or in flight), and/or b. Is undetectable during
operations, and/or
c. Could have significant operational impact, and/or d. Could have significant
economic impact
MULTIPLE ELEMENT The simultaneous cracking of multiple load path discrete elements working at
FATIGUE DAMAGE similar stress levels.
MULTIPLE SITE FATIGUE DAMAGE The presence of a number of adjacent, small cracks that might coalesce to
form a single long crack.
NON-METALLICS Any structural material made from fibrous or laminated components bonded
together by a medium. Material such as graphite epoxy, boron epoxy, fiber
glass, kevlar epoxy, acrylics and the like are non-metallics. Non-metallics
include adhesive used to join other metallic or non-metallic structural
materials.
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TERMS DEFINITIONS
OPERATING CREW Operating Crew:
NORMAL DUTIES Qualified cockpit and cabin attendant personnel who are on duty.
Normal Duties:
Those duties associated with the operation of the aircraft, on a daily basis, to
include the following:
a. Procedures and checks performed during aircraft operation;
b. Recognition of abnormalities or failures by the operating crew through the
use of normal physical senses (e.g., odor, noise vibration, temperature,
visual observation of damage or failure, changes in physical in-puts, force
requirements, etc.)
OPERATIONAL CHECK An operational check is a task to determine that an item is fulfilling its
intended purpose. Does not require quantitative tolerances. This is a
failure-finding task.
OPERATIONAL EFFECTS Failure effects which interfere with the completion of the aircraft
mission. These failures cause delays, cancellations, ground or flight
interruptions, high drag coefficients, altitude restrictions, etc.
OTHER STRUCTURE Structure which is judged not to be a Structural Significant Item.
"Other Structure" is defined both externally and internally within zonal
boundaries.
REPEAT INTERVAL The interval expressed in flight cycles, flight hours and/or calendar time,
between successive accomplishments of a specific maintenance task.
RESIDUAL STRENGTH The strength of a damaged structure.
RESTORATION That work necessary to return the item to a specific standard.
Restoration may vary from cleaning or replacement of single parts up to a
complete overhaul.
SAFE-LIFE STRUCTURE Structure which is not practical to design or qualify as damage tolerant. Its
reliability is protected by discard limits which remove items from service
before fatigue cracking is expected.
SCHEDULED MAINTENANCE Any of the maintenance opportunities which are prepackaged and are
CHECK accomplished on a regular basis.
STRUCTURAL Any detail, element, or assembly, which contributes significantly to carry
SIGNIFICANT ITEM - (SSI) flight, ground, pressure or control loads and whose failure could affect the
structural integrity necessary for the safety of the aircraft.
STRUCTURAL ASSEMBLY One or more structural elements which together provide a basic structural
function.
STRUCTURAL DETAIL The lowest functional level in an aircraft structure. A discrete region or area of
a structural element, or a boundary intersection of two or more elements.
STRUCTURAL ELEMENT Two or more structural details which together form an identified manufacturer
assembly part.
STRUCTURAL FUNCTION The mode of action of aircraft structure. It includes acceptance and
transfer of specified loads in items
(details/elements/assemblies) and provides consistently adequate aircraft
response and flight characteristics.
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General
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TERMS DEFINITIONS
SYSTEM SAFETY A quantitative analysis used to determine compliance with applicable
ASSESSMENT (SSA) certification requirements (e.g. FAR
25.1309).
SYSTEM SAFETY The input items provided to the Industry Steering Committee/Working Group
ASSESSMENT ITEM (SSAI) from the manufacturer's design engineering group as a result of System Safety
Assessment. Each item includes the failure cause, suggested task, and
theoretical maximum interval.
TASKS-MAINTENANCE An action or set of actions required to achieve a desired outcome which
restores an item to or maintains an item in serviceable condition, including
inspection and determination of condition.
THRESHOLD The initial accomplishment of a specific maintenance task expressed in flight
cycle, flight hours, and/or calendar time.
VISUAL CHECK A visual check is an observation to determine that an item is fulfilling its
intended purpose. Does not require quantitative tolerances. This is a failure-
finding task
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Section 2 Scheduled Maintenance Requirements – REVISION : 0
List Of Requirements
DATE : 05/07/2019
SECTION 2 - SCHEDULED MAINTENANCE REQUIREMENTS - LIST OF REQUIREMENTS
CHAPTER 12 – SERVING
MAINTENANCE CAT/ THR/INT/

SOURCE REQUIREMENT TYPE/TITLE ZONES EFFETC
REQUIREMENT CSD TOLERANCE
12-13-01-610-001-A00 SYS 7 Service (Replenish) Hydraulic System Reservoir 193 I: 250 FH No ALL
Tolerance
CHAPTER 20 - STANDARD PRACTICES – AIRFRAME

Not Applicable with Legacy 600
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CHAPTER 21 - AIR CONDITIONING

REQUIREMENT SOURCE CSD REQUIREMENT TYPE/TITLE ZONES TOLERANCE EFFETC
21-20-00-710-001-A00 SYS 7 Operationally Check Air Conditioned Distribution System 223/224 I: 8000 FH ALL
225/226 or
96 MO
± 60 Days
21-21-00-720-001-A00 SYS 9 Functionally Check Display Ventilation System 221/222 I: 4000 FH ALL
or
48 MO
± 30 Days
21-25-01-710-001-A00 SYS 8 Operationally Check Ram Air Valve 223/224 I: 4000 FH ALL
225/226 or
48 MO
± 30 Days
21-26-00-710-001-A00 SYS 9 Operationally Check Electronic Compartment Ventilation 113 I: 4000 FH ALL
System or
48 MO
± 30 Days
21-26-08-960-001-A01 SYS 9 Discard Exhaust Hoses of the Electronic Bay Compartment 113 I: 180 MO ALL
± 60 Days
21-27-00-710-001-A00 SYS 9 Operationally Check Baggage Compartment Ventilation System 813 I: 2000 FH No ALL
(including high and low speed of fan Tolerance
21-27-02-640-001-A00 SYS 8 Lubricate Baggage Compartment Check Valves 813 I: 4000 FH ALL
or
48 MO
± 30 Days
21-27-02-710-001-A00 SYS 8 Operationally Check Baggage Compartment Check Valve 813 I: 2500 FH ALL
(manual check for free movement and corrected seating) or
24 MO
± 30 Days
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DATE : 05/07/2019
CHAPTER 21 - AIR CONDITIONING (CONTINUED)

21-31-00-710-001-A00 SYS 9 Operationally Check Pressurization Control System in Manual 223/224 I: 8000 FH ALL
Mode 225/226 or
96 MO
± 60 Days
21-31-00-720-002-A00 SYS 8 Functionally Check Outflow Valves Pressure Relief Devices 191 I: 6000 FH No ALL
272 Tolerance
21-31-00-720-005-A00 SYS 9 Functionally Check Line for Leakage 191 I: 8000 FH or ALL
223 96 MO
272 ± 60 Days
21-31-03-140-001-A00 SYS 6 Restore (Cleaning) Electropneumatic Outflow Valve (Non- 272 I: 2500 FH No ALL
smoking flights Tolerance
21-31-03-140-001-A01 SYS 6 Restore (Cleaning) Electropneumatic Outflow Valve (Smoking 272 I: 1000 FH No ALL
flights) Tolerance
21-31-04-140-001-A00 SYS 6 Restore (Cleaning) Pneumatic Outflow Valve (Non-smoking 272 I: 1000 FH No ALL
flights) Tolerance
21-31-04-140-001-A01 SYS 6 Restore (Cleaning) Pneumatic Outflow Valve (Smoking flights.) 272 I: 500 FH No ALL
Tolerance
21-31-08-960-001-A00 SYS 6 Discard Air Filter Element (Non- smoking flights) 272 I: 3200 FH No ALL
Tolerance
21-31-08-960-001-A01 SYS 6 Discard Air Filter Element (Smoking flights) 272 I: 1800 FH No ALL
Tolerance
21-32-01-720-001-A00 SYS 9 Functionally Check Cabin Pressure Acquisition Module (CPAM) 224 I: 10000 FH ALL
Post-Mod. S.B. 145LEG-00-0007 or with an equivalent No Tolerance
modification factory- incorporated
21-51-00-710-001-A00 SYS 8 Operationally Check Cooling Pack System to Verify ECS OFF 191 I: 4000 FH ALL
Signal or
48 MO
± 30 Days
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DATE : 05/07/2019
CHAPTER 21 - AIR CONDITIONING (CONTINUED)

REQUIREMENT SOURCE CSD REQUIREMENT TYPE/TITLE ZONES TOLERANC EFFETC
E
21-51-00-720-001-A00 SYS 6 Functionally Check Cooling Pack System 191 I: 8000 FH ALL
or
96 MO
± 60 Days
21-51-00-720-003-A00 SYS 8 Functionally Check Pack Duct Overtemperature Protection 191 I: 4000 FH ALL
or
48 MO
± 30 Days
21-51-01-130-001-A00 SYS 6 Restore (Cleaning) Pack Valve Filter Using Ultrasonic Method 191 I: 2500 FH ALL
No Tolerance
21-51-02-170-001-A00 SYS 6 Restore (Cleaning) Dual Heat Exchanger and Visually Check 191 I: 4000 FH ALL
Condition of Core No Tolerance
21-51-10-710-001-A00 SYS 8 Operationally Check Pack Leak Switch 191 I: 8000 FH ALL
or
72 MO
± 30 Days
21-60-00-710-001-A00 SYS 9 Operationally Check Temperature Control 223/224 I: 8000 FH ALL
225/226 or
96 MO
± 60 Days
21-60-08-960-001-A00 SYS 9 Discard Torque-Motor Dual-Valve Filter 191 I: 8000 FH ALL
No Tolerance
21-71-01-900-001-A00 SYS 9 Restore (Cleaning) Ozone Converter 194/195 I: 6000 FH ALL
NOTE: If installed No Tolerance
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CHAPTER 22 - AUTO FLIGHT

REQUIREMENT CSD TOLERANC
22-11-00-710-001-A00 SYS 9 Operationally Check AFCS Go-Around Mode 223/224 E I: 4000 FH ALL
NOTE: Also Check TCS Mode 225/226 or
48 MO
± 30 Days
22-11-00-720-003-A00 CAT II - Functionally Check Category II Monitoring Function 223/224 I: 1000 FH ALL
NOTE: Only for CAT II operation 225/226 or
24 MO
± 30 Days
22-11-00-720-004-A00 SYS 6 Functionally Check AFCS Altitude Hold Mode and Altitude 223/224 I: 5000 FH ALL
Pre-Select Mode 225/226 or
NOTE: Only for RVSM operation 48 MO
± 30 Days
CHAPTER 23 - COMMUNICATIONS
23-24-01-960-001-A00 SYS 7 Discard of CMU battery 223/224 I: 72 MO No ALL
NOTE: CMU Battery change in accordance with manufacturer’s 225/226 Tolerance
data plate expiration date, if installed.
23-35-21-710-001-A00 SYS 9 Operationally Check Entertainment Cabinet Fans 223/224 I: 4000 FH ALL
225/226 or
231 48 MO
± 30 Days
23-51-00-710-001-A00 SYS 8 Operationally Check Audio System Emergency Mode 223/224 I: 500 FH No ALL
225/226 Tolerance
23-60-00-720-001-A00 SYS 9 Functionally Check Static Discharger 321/327 I: 8000 FH ALL
335/336 or
561/573 72 MO
661/673 ± 30 Days
711
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CHAPTER 23 - COMMUNICATIONS (CONTINUED)

23-71-00-710-001-A00 SYS 9 Operationally Check Voice Recorder 4 Channels and Area 225 I: 4000 FH ALL
Microphone or
NOTE: Or in accordance with Local Regulatory Authority 48 MO
Requirements ± 30 Days
23-71-02-710-001-A00 SYS 9 Operationally Check Underwater Locator Beacon 272 I: 24 MO ALL

± 30 Days
23-71-02-960-001-A00 SYS 9 Discard CVR Underwater Locator Beacon Battery 272 I: 72 MO No ALL
NOTE: ULB battery change in Accordance with Manufacturer’s Tolerance
Dataplate Expiration date
CHAPTER 24 - ELECTRICAL POWER

E
24-31-00-710-001-A00 SYS 9 Operationally Check Main Generation Switching Circuit 223/224 I: 4000 FH ALL
225/226 No Tolerance
24-31-00-710-002-A00 SYS 9 Operationally Check Main Generation Overcurrent Protection 114 I: 4000 FH ALL
Circuit’ 223 No Tolerance
24-31-01-900-001-A00 SYS 7 Restore (Overhaul) Main Generator Part Number 30086-010 413/423 I: 3200 FH ALL
NOTE: If installed. or
60 MO
No Tolerance
24-31-01-900-001-A01 SYS 7 Restore (Overhaul) Main Generator Part Number 30086-011 413/423 I: 3600 FH ALL
NOTE: If installed. or
60 MO
No Tolerance
24-34-00-710-001-A00 SYS 9 Operationally Check APU Generation Overcurrent Protection 114/223 I: 4000 FH ALL
Circuit No Tolerance
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CHAPTER 24 - ELECTRICAL POWER (CONTINUED)

E
24-34-00-710-002-A00 SYS 9 Operationally Check APU Generation Switching Circuit 223/224 I: 4000 FH ALL
24-34-01-220-001-A00 SYS 7 Inspect (Detailed Inspection) APU Starter/Generator Brushes 313 I: 400 AH ALL
No Tolerance
24-34-01-900-001-A00 SYS 7 Restore (Overhaul) APU Starter/ Generator 313 I: 1200 AH ALL
or
48 MO
No Tolerance
24-35-01-720-001-A00 SYS 8 Functionally Check Back-up Battery 114 I: 6 MO ALL
NOTE: From the manufacture date or last restoration. ± 15 Days
24-35-01-900-001-A00 SYS 8 Restore (Replacement) Back-up Battery 114 I: 12 MO ALL
NOTE: From the manufacture date or last restoration. No Tolerance
24-36-01-900-001-A00 SYS 6 Restore (Overhaul) SAFT Main Battery 113 I: 1000 FH ALL
NOTE: If installed or
NOTE: From the manufacture date or last restoration. 12 MO
No Tolerance
24-40-00-720-001-A00 SYS 7 Functionally Check GPU Overvoltage Protection 113 I: 4000 FH ALL
No Tolerance
24-60-00-710-001-A00 SYS 8 Operationally Check Electrical Emergency Transfer Circuit 113 I: 4000 FH ALL
No Tolerance
24-60-00-710-002-A00 SYS 9 Operationally Check Electrical Emergency Abnormal Alarm 113 I: 500 FH ALL
No Tolerance
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CHAPTER 25 - EQUIPMENT/FURNISHINGS

25-11-01-140-001-A00 SYS 8 Restore (Cleaning) Flight Crew Seats Locking System 223/224 I: 500 FH ALL
225/226 or
12 MO
± 15 Days
25-11-01-220-001-A00 SYS 8 Inspect (Detailed Inspection) Cockpit Seats for Security of 223/224 I: 4000 FH ALL
Attachment to the Track, Including Restraint System (Seat Belt) 225/226 or
48 MO
± 30 Days
25-21-00-212-001-A00 SYS 9 Inspect (General Visual) Passenger Cabin Seats (Fabric, 251/252 I: 48 MO ALL
Cover, Safety Belt, Seat Movement and Attachments to the ± 30 Days
Track
25-21-00-220-002-A00 SYS 8 Inspect (Detailed Inspection) Flight Attendant Seats Harness, 231 I: 4000 FH ALL
Inertial Reel for Condition and the Seat Bottom for Freedom of or
Movement and Returning Back to Upright Position 48 MO
NOTE: If installed ± 30 Days
25-26-00-212-001-A00 SYS 9 Inspect (General Visual) of Credenza, Closets and 230/240 I: 48 MO ALL
Entertainment Cabinet for Integrity And Security 250/260 ± 30 Days
25-27-02-211-001-A00 SYS 8 Visually Check Lavatory/Baggage Door Sealing for Condition, 271/272 I: 12 MO ALL
Integrity and Security ± 15 Days
25-30-06-212-001-A00 SYS 9 Inspect (General Visual) of Galley Structure Lower Attachment 232 I: 48 MO ALL
Points (On the Tracks) ± 30 Days
25-40-04-212-001-A00 SYS 9 Inspect (General Visual) of Lavatory Structure Lower 161/162 I: 48 MO ALL
Attachment Points ± 30 Days
25-60-01-212-001-A00 SYS 8 Inspect (General Visual) First Aid Kit for Condition and 231 I: 6 MO ALL
Validation ± 15 Days
NOTE: in accordance with Local Regulatory Authority
Requirements
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CHAPTER 25 - EQUIPMENT/FURNISHINGS (CONTINUED)

25-60-02-900-001-A03 SYS 8 Restore (Overhaul) Flotation Vest PN 63600-Series (Vacuum 223/224 E I: 120 MO ALL
Packed) 241/242 No Tolerance
NOTE: Every 60 MO for sewn packed; in accordance with 251/252
manufacturer’s data plate expiration date or Local Regulatory 261
Authority Requirements.
25-60-04-212-001-A00 SYS 8 Inspect (General Visual) Cockpit Escape Rope 225/226 I: 48 MO ALL
± 30 Days
25-60-05-212-001-A00 SYS 8 Inspect (General Visual) of Lifeline for integrity and general 252 I: 48 MO ALL
conditions ± 30 Days
CHAPTER 25 - EQUIPMENT/FURNISHINGS (CONTINUED)

25-61-00-212-001-A00 SYS 8 Inspect (General Visual) Emergency Locator Transmitter for 262 I: 12 MO ALL
Condition ± 15 Days
- Proper Installation
- Battery Corrosion and Leakage
NOTE: Or in accordance with Local Regulatory Authority
Requirement
25-61-00-710-001-A00 SYS 8 Operationally Check Emergency Locator Transmitter System 262/223 I: 12 MO ALL
- Proper Operation 224 ± 15 Days
- Crash Switch Operation
Requirements
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25-61-04-960-001-A02 SYS 8 Discard ELT battery ARTEX P/N 452-0133 262 I: 60 MO No ALL
NOTE: ELT battery replacement in accordance with Tolerance
manufacturer’s dataplate expiration date or Local Regulatory
Authority Requirements.
25-63-01-900-001-A01 SYS 8 Restore (Overhaul) Winslow (Vacuum Packed) Life Raft 223/224 I: 36 MO No ALL
Assembly 241/242 Tolerance
251/252
261/262
CHAPTER 26 - FIRE PROTECTION

26-14-00-710-001-A00 SYS 8 Operationally Check Lavatory Smoke Detector (Actuating The 263 I: 6000 FH ALL
Smoke Sensor With Smoke) or
96 MO
No Tolerance
26-14-01-960-001-A00 SYS 8 Discard JAMCO Lavatory Smoke Detector 263 I: 180 MO No ALL
Tolerance
26-15-00-710-001-A00 DELETED
26-15-01-140-001-A00 SYS 6 Restore (Cleaning) Baggage Smoke Detectors / Cleaning of 271/272 I: 48 MO ALL
Baggage Smoke Detectors 273/274 ± 30 Days
26-21-00-720-001-A00 SYS 9 Functionally Check Engine Fire Extinguishing System 312 I: 36 MO No ALL
NOTE: Or in accordance with Local Regulatory Authority Tolerance
Requirements
26-21-02-280-001-A00 DELETED
26-21-02-720-001-A00 SYS 9 Functionally Check (Hydrostatic Test) of the Engine Fire 312 I: 60 MO No ALL
Extinguishing Bottle Tolerance
NOTE: From the manufacture date or last task accomplishment.
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26-21-02-720-002-A00 SYS 9 Functionally Check Engine Fire Extinguishing Bottle for Weight 312 I: 12 MO ALL
and Check Bottle Pressure ±15 Days
Requirements.
26-21-03-720-001-A00 SYS 9 Functionally Check Engine Fire Extinguishing Bottle Pressure 312 I: 60 MO No ALL
Switch Tolerance
26-21-04-960-001-A00 SYS 9 Discard Engine Fire Extinguishing Bottle Cartridges 312 I: 72 MO No ALL
NOTE: 108 MO from Date of Manufacturing or 72 MO from Date Tolerance
of Installation, whichever occurs first.
NOTE: Or, at operator discretion, perform this task at each
bottle hydrostatic test
CHAPTER 26 - FIRE PROTECTION (CONTINUED)

26-21-05-720-001-A00 SYS 9 Functionally Check Engine Fire Extinguishing Two-Way "TEE" 312 I: 8000 FH ALL
Check Valves or
72 MO
No Tolerance
26-22-00-720-001-A00 SYS 9 Functionally Check APU Fire Extinguishing System (Between 156 I: 36 MO No ALL
switch and bottle connector) and Verify APU isolation by APU 312 Tolerance
Fuel Shutoff Valve actuation
Requirements
26-22-01-280-001-A00 DELETED
26-22-01-720-001-A00 SYS 9 Functionally Check (Hydrostatic Test) of APU Fire Extinguishing 312 I: 60 MO No ALL
Bottle Tolerance
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26-22-01-720-002-A00 SYS 9 Functionally Check APU Fire Extinguishing Bottle for Weight 312 I: 12 MO ALL
and Check Bottle Pressure ± 15 Days
NOTE: Or in accordance with local regulatory authority
requiremetns.
26-22-02-720-001-A00 SYS 9 Functionally Check APU Fire Extinguishing Bottle Pressure 312 I: 60 MO No ALL
Switch Tolerance
26-22-03-960-001-A00 SYS 9 Discard APU Fire Extinguishing Bottle Cartridges 312 I: 72 MO No ALL
NOTE: 108 MO from Date of Manufacturing or 72 MO from Date Tolerance
of Installation, whichever occurs first.
26-23-00-720-001-A00 SYS 8 Functionally Check Baggage Fire Extinguishing System 220 I: 4000 FH ALL
(Covering the Pressure Switch, Cartridge, Bagg Fire Exting. 272/273 or
Switch and Electrical Hardware) 114 48 MO
± 30 Days
26-23-01-280-001-A00 DELETED
CHAPTER 26 - FIRE PROTECTION (CONTINUED)

26-23-01-720-001-A00 SYS 6 Functionally Check (Hydrostatic Test) of Baggage Fire 272 I: 120 MO No ALL
Extinguishing Bottles (high rate and metering) Tolerance
NOTE: From the manufacture date or last task accomplishment
26-23-01-720-002-A00 SYS 6 Functional Check Baggage Compartment Fire Extinguishing 272 I: 60 MO ALL
Bottles (high rate and metering) for Weight ± 30 Days
NOTE: From the manufacture date or last task accomplishment
26-23-02-960-001-A00 SYS 6 Discard Baggage Fire Extinguishing Bottles Cartridges (high 272 I: 120 MO No ALL
rate and metering) Tolerance
NOTE: 180 MO from date of manufacturing or 120 MO from
date of installation, whichever occurs first.
bottle hydrostatic test.
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26-23-04-720-001-A00 SYS 6 Functionally Check Baggage Fire Extinguishing Two-Way 272 I: 8000 FH ALL
"TEE" Check Valve or
72 MO
± 30 Days
26-24-00-720-001-A00 SYS 8 Functionally Check of Portable Fire Extinguishing Bottle for 261/262 I: 12 MO No ALL
Weight (See placard attached to the bottle) 232 Tolerance
NOTE: Or in accordance with Local Regulatory Authority 223
Requirements 231/241
26-24-00-960-001-A00 SYS 8 Discard Portable Fire Extinguisher P/N BA21741 Series 223 I: 120 MO No ALL
231/232 Tolerance
241
261/262
26-24-00-960-001-A01 SYS 8 Discard Portable Fire Extinguisher P/N RT A1200. 223 I: 144 MO No ALL
231/232 Tolerance
241
261/262
26-25-00-280-001-A00 DELETED
26-25-01-720-001-A00 SYS 9 Functionally Check Lavatory/Galley Fire Extinguishing Bottle for 232/261 I: 12 MO ALL
Weight (See Placard Attached to the Bottle) No Tolerance
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CHAPTER 27 - FLIGHT CONTROLS

E
27-11-00-220-001-A00 SYS 8 Inspect (Detailed Inspection) Aileron Primary Mechanical 123 I: 4000 FH ALL
Control from Control Wheel to Aileron PCAs, Checking Cables 221/222 or
Pulleys, NRUs, Quadrants, Disconnect System and Mechanical 231/241 48 MO
Links 242 ± 30 Days
251/252
551/651
27-11-00-640-001-A00 SYS 6 Lubricate Control Wheel Chain 123 I: 4000 FH ALL
or
48 MO
± 30 Days
27-11-00-720-001-A00 SYS 6 Functionally Check Aileron Primary Mechanical Control 123 T: 12000 FH ALL
Backlash 551/651 or
NOTE: Threshold at 12000 FH or 96 MO, whichever occurs first 96 MO
I: 4000 FH
or
48 MO
± 30 Days
27-11-01-720-001-A00 SYS 6 Functionally Check Tension of Aileron Control Cables 123 I: 4000 FH ALL
NOTE: For new cables, check tension at first 6 MO and 12 MO 221/222 or
before escalating to 4000 FH or 48 MO 241/242 48 MO
251/252 ± 30 Days
551/651
27-12-00-720-001-A00 SYS 8 Functionally Check Aileron Hydraulic Actuation 551/651 I: 8000 FH ALL
or
96 MO
± 60 Days
27-12-01-212-001-A00 SYS 7 Inspect (General Visual) Aileron PCA Hoses 551/651 I: 4000 FH ALL
or
48 MO
± 30 Days
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CHAPTER 27 - FLIGHT CONTROLS (CONTINUED)

27-12-01-720-002-A01 SYS 9 Functionally Check Aileron Actuator Force Fight (for aircraft 551/661 I: 4000 FH ALL
under ANAC/FAA certifications) or
24 MO
± 30 Days
27-13-00-710-001-A00 SYS 8 Operationally Check Aileron Solenoid Manifold Shutoff Function 223/224 I: 4000 FH ALL
225/226 or
48 MO
± 30 Days
27-14-00-720-001-A00 SYS 9 Functionally Check Roll Trim 223/224 I: 4000 FH ALL
225/226 or
48 MO
± 30 Days
27-15-00-710-001-A00 SYS 8 Operationally Check Aileron Disconnect System 221 I: 4000 FH ALL
or
24 MO
± 30 Days
27-15-02-640-001-A00 SYS 8 Lubricate Aileron Disconnect System 123 I: 8000 FH ALL
NOTE: The plate mechanism is bench lubricated 221 or
96 MO
± 60 Days
27-21-01-220-001-A00 SYS 9 Inspect (Detailed Inspection) Rudder Primary Mechanical 123/124 I: 4000 FH ALL
Control Checking Cables, Pulleys and Quadrants 131/132 or
141/142 48 MO
151/152 ± 30 Days
153/154
155/156
161/162
171/172
192/193
221/231
241/242
251/252
261/271
272/273
312/321
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27-21-01-720-001-A00 SYS 9 Functionally Check Tension of Rudder Control Cables 123 I: 4000 FH ALL
NOTE: For new cables, check tension at first 6 MO and 12 MO 251/261 or
before escalating to 4000 FH or 48 MO 312 48 MO
± 30 Days
27-21-02-220-001-A00 SYS 8 Inspect (Detailed Inspection) Rudder Main Control Feedback 325/326 I: 4000 FH ALL
Path, PCU Linkage and Mounting Points, Rudder Actuator 327 or
Attachments, Hinges, and Connecting Rods. 48 MO
NOTE: Requires Removal of Concentric and Eccentric Pins ± 30 Days
27-22-00-720-001-A00 SYS 9 Functionally Check Rudder Backlash 123 I: 4000 FH ALL
325 or
48 MO
± 30 Days
27-22-01-720-001-A00 SYS 9 Functionally Check Rudder Power Control Unit/ Actuators 223/224 I: 4000 FH ALL
Differential Pressure 325 or
48 MO
± 30 Days
27-22-02-212-001-A00 SYS 6 Inspect (General Visual) Rudder Actuators 325/326 I: 4000 FH ALL
or
48 MO
± 30 Days
27-31-00-720-001-A00 SYS 6 Functionally Check Elevator Primary Mechanical Control 123 I: 4000 FH ALL
Backlash or
48 MO
± 30 Days
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27-31-01-220-001-A00 SYS 6 Inspect (Detailed Inspection) Elevator Control Cables 123 I: 4000 FH ALL
155/156 or
192 48 MO
221/231 ± 30 Days
241/242
251/252
261/271
272/312
324/325
27-31-01-720-001-A00 SYS 6 Functionally Check Tension of Elevator Control Cables 123 I: 4000 FH ALL
NOTE: For new cables, check tension at first 6 MO and 12 MO 251 or
before escalating to 4000 FH or 48 MO 48 MO
± 30 Days
27-31-04-710-001-A00 SYS 9 Operationally Check Spring/Servo Tab 223/224 I: 1000 FH ALL
225/226 or
335/336 12 MO
± 15 Days
27-31-05-220-002-A00 SYS 8 Inspect (Detailed Inspection) Spring Tab Attachment Link 335/336 I: 4000 FH ALL
or
48 MO
± 30 Days
27-35-00-640-001-A00 SYS 8 Lubricate Elevator Disconnect System 123 I: 8000 FH ALL
NOTE: The plate mechanism is bench lubricated 221 or
96 MO
± 60 Days
27-35-00-710-001-A00 SYS 8 Operationally Check Elevator Disconnect System 123 I: 4000 FH ALL
221 or
24 MO
± 30 Days
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27-36-00-710-001-A00 SYS 8 Operationally Check Stall Protection System 223/224 I: 500 FH ALL
or
12 MO
± 15 Days
27-36-00-720-001-A00 SYS 9 Functionally Check ICE/SPS Speeds Interface Circuit 223 I: 1000 FH ALL
225 or
12 MO
± 15 Days
27-40-00-710-002-A00 SYS 9 Operationally Check Backup/Main Cut-out Switch and Quick 223/224 I: 4000 FH ALL
Disconnect Switch or
48 MO
± 30 Days
27-40-00-710-003-A00 SYS 9 Operationally Check Lockout Logic of Horizontal Stabilizer 223/224 I: 500 FH ALL
Control Unit Post-Mod SB 145LEG-27-0016 or with an No Tolerance
equivalent modification factory-incorporated
27-40-00-720-001-A00 SYS 8 Functionally Check Horizontal Stabilizer Backlash 324 I: 5000 FH ALL
or
48 MO
± 30 Days
27-40-02-220-001-A00 SYS 8 Inspect (Detailed Inspection) Horizontal Stabilizer Actuator 324 I: 4000 FH ALL
Integrity and Attachments or
48 MO
± 30 Days
27-40-02-610-001-A00 SYS 6 Service (Replenish) Horizontal Stabilizer Actuator and Check 324 I: 2000 FH ALL
for Leakage No Tolerance
27-51-00-212-001-A00 SYS 7 Inspect (General Visual) Flap Mechanical Line 193 I: 4000 FH ALL
541 or
5711/ 48 MO
5721 ± 30 Days
641
6711
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SECTION : 2
MAINTENANCE PROGRAM
PAGE : 55
ISSUE : 1
DATE : 05/07/2019

27-51-00-220-001-A00 SYS 6 Inspect (Detailed Inspection) Flap Flexible Shafts 193 I: 4000 FH ALL
5711 or
5721 48 MO
6711 ± 30 Days
6721
27-51-00-610-001-A00 SYS 6 Service (Lubricate) Flap Screwjack Actuators Gearbox Pre-Mod 541/641 I: 4000 FH L600
SB 145LEG-27-0026 or
48 MO
± 30 Days
27-51-00-610-001-A01 SYS 6 Service (Lubricate) Flap Screwjack Actuators Gearbox Post- 541/641 I: 8000 FH ALL
Mod SB 145LEG-27-0026 or with an equivalent modification or
factory incorporated 72 MO
± 30 Days
27-51-00-640-001-A00 SYS 6 Service (Lubricate) Flap Screw-Jack Actuators (FSAs) 571/572 I: 12 MO ALL
671/672 ± 15 Days
27-51-01-720-001-A00 SYS 8 Functionally Check Flap Transmission Brake Holding Capability 5721/6721 I: 2500 FH ALL
or
24 MO
± 30 Days
27-51-15-220-001-A00 SYS 8 Inspect (Detailed Inspection) Flap Rollers for Structural Integrity 5711/5721 I: 8000 FH ALL
6711/6721 or
96 MO
± 60 Days
27-51-17-720-001-A00 SYS 8 Functionally Check MTB (Flap Drive Motor Unit) Holding 155/156 I: 4000 FH ALL
Capability 157 or
48 MO
± 30 Days
27-53-00-710-001-A00 SYS 9 Operationally Check FLAP FAIL Message 223/225 I: 500 FH ALL
or
24 MO
± 30 Days
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SECTION : 2
MAINTENANCE PROGRAM
PAGE : 56
ISSUE : 1
DATE : 05/07/2019
MAINTENANCE SOURCE CAT/ REQUIREMENT TYPE/TITLE ZONES THR/INT/ EFFETC

27-53-00-710-002-A00 SYS 8 Operationally Check of Take-off Flap Aural Warning and No 223/224 I: 500 FH ALL
Take-off Configuration Visual Warning or
24 MO
± 30 Days
27-63-01-710-001-A00 SYS 9 Operationally Check Spoiler System 223 I: 4000 FH ALL
or
48 MO
± 30 Days
27-71-00-220-001-A00 SYS 6 Inspect (Detailed Inspection) Electromechanical Gust Lock 321 I: 4000 FH ALL
Mechanism or
48 MO
± 30 Days
27-71-00-710-004-A00 SYS 9 Operationally Check Electromechanical Gust Lock Solenoid 223 I: 500 FH ALL
Function 224 or
12 MO
± 15 Days
CHAPTER 28 - FUEL

28-11-04-710-001-A00 SYS 9 Operationally Check (Manual Check for Free Movement and 192 I: 8000 FH ALL
Sealing Condition) Flap Valves (Ribs 1 and 7) 155/156 or
NOTE: Check during Internal Tank Inspection 531/631 96 MO
± 60 Days
28-12-01-710-001-A00 SYS 9 Operationally Check (Manual Check) Vent Float Valves 531/541 I: 8000 FH ALL
NOTE: Check during Internal Tank Inspection 631/641 or
96 MO
± 60 Days
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SECTION : 2
MAINTENANCE PROGRAM
PAGE : 57
ISSUE : 1
DATE : 05/07/2019
CHAPTER 28 - FUEL (CONTINUED)

28-12-04-710-001-A00 SYS 9 Operationally Check Flap Valve (Manual Check for Free 541/641 I: 8000 FH ALL
Movement and Sealing Condition) or
NOTE: Check during Internal Tank Inspection 96 MO
± 60 Days
28-12-05-211-001-A00 SYS 8 Visually Check Flame Arrestor for Honey Comb Clogging, and 551/651 I: 4000 FH ALL
Attaching Parts for Security or
48 MO
± 30 Days
28-12-05-710-001-A00 SYS 8 Operationally Check Flame Arrestor in/out Flow Valves for 551/651 I: 4000 FH ALL
Freedom Movement or
48 MO
± 30 Days
28-13-00-220-001-A00 SYS 6 Inspect (Detailed Inspection) of Aft Fuel Tanks 271/272 T: 96 MO I: ALL
NOTE: Check together with Task 28-13-01-720-001-A00 24 MO
± 30 Days
28-13-01-720-001-A00 SYS 8 Functionally Check Aft Fuel Tanks 271/272 T: 96 MO I: ALL
NOTE: Check together with Task 28-13-00-220-001-A00 24 MO
± 30 Days
28-13-02-960-001-A00 DELETED
28-14-00-710-001-A00 SYS 9 Operationally Check Aft Fuel Tank Positive Relief System 171/172 I: 1000 FH ALL
191 or
223/225 12 MO
272 ± 15 Days
28-14-01-710-001-A00 SYS 9 Operationally Check Aft Fuel Tank Float Vent Valves PRE-MOD 272 I: 8000 FH L600
SB 145LEG-28-0019. or
96 MO
± 60 Days
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SECTION : 2
MAINTENANCE PROGRAM
PAGE : 58
ISSUE : 1
DATE : 05/07/2019

28-14-04-720-001-A00 SYS 9 Functionally Check Aft Fuel Tanks Positive Relief Valve 272 I: 2000 FH ALL
or
24 MO
± 30 Days
28-14-05-720-001-A00 SYS 9 Functionally Check Aft Fuel Tanks Negative Relief Valve 272 I: 2000 FH ALL
or
24 MO
± 30 Days
28-14-06-960-001-A00 SYS 8 Discard Aft Fuel Tank Air Filter 272 I: 1200 FH ALL
or
12 MO
± 15 Days
28-14-07-220-001-A00 SYS 6 Inspect (Detailed Inspection) Aft Fuel Tanks Flame Arrestors 272 I: 4000 FH ALL
NOTE: Flame Arrestors installed in the Skin of the Fuselage and or
Flame Arrestors installed close to container box, if installed. 48 MO
± 30 Days
28-15-03-710-001-A00 SYS 9 Operationally Check Forward Fuel Tanks Flap Valves 197 I: 8000 FH ALL
or
96 MO
± 60 Days
28-16-00-710-001-A00 SYS 8 Operationally Check "Fuel Tanks Vent Open" Caution System 191 I: 500 FH No ALL
223 Tolerance
28-16-01-710-001-A00 SYS 9 Operationally Check Forward Fuel Tanks Float Valves 197 I: 8000 FH ALL
(Manually Checked) or
96 MO
± 60 Days
28-16-04-710-001-A00 SYS 9 Operationally Check Forward Fuel Tanks Automatic Float Drain 197 I: 8000 FH ALL
Valves or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 59
ISSUE : 1
DATE : 05/07/2019

28-16-05-220-001-A00 SYS 6 Inspect (Detailed Inspection) Forward Fuel Tank Flame 191 I: 4000 FH ALL
Arrestors or
NOTE: Flame Arrestors installed on NACA Air Duct and Flame 48 MO
Arrestors installed on Refuel/Overfill Ventilation Line, if ± 30 Days
installed.
28-21-03-720-001-A00 SYS 9 Functionally Check Relief Valve 155/156 I: 8000 FH ALL
NOTE: Bench Test 192 or
96 MO
± 60 Days

28-21-04-710-001-A00 SYS 9 Operationally Check Crossfeed Valve 155 I: 4000 FH ALL

or
48 MO
± 30 Days
28-21-10-710-001-A00 SYS 8 Operationally Check Fuel Feed Line Shroud 155/156 I: 10000 FH ALL
414/424 or
72 MO
± 30 Days
28-22-03-710-001-A00 SYS 8 Operationally check APU Fuel Feed Line Shroud 155/156 I: 8000 FH ALL
312 or
72 MO
± 30 Days
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SECTION : 2
MAINTENANCE PROGRAM
PAGE : 60
ISSUE : 1
DATE : 05/07/2019
28-26-00-710-001-A00 SYS 8 Operationally Check of FWD Pump and Circuitry 223 I: 2000 FH ALL
or
24 MO
± 30 Days
28-26-00-720-001-A00 SYS 9 Functionally Check Aft/Forward Fuel Tanks Transfer 197 I: 8000 FH ALL
Check/Relief Valves 271/272 or
273/274 96 MO
± 60 Days
28-26-16-710-001-A00 SYS 8 Operationally Check Fuel Transfer Line Shroud 155/156 I: 8000 FH ALL
251/252 or
261/262 72 MO
271/272 ± 30 Days
28-26-18-710-001-A00 SYS 8 Operationally Check Aft Tank Electrical Isolating Shut-Off Valve 220 I: 1000 FH ALL
and Circuitry or
12 MO
± 15 Days
28-26-21-710-001-A00 SYS 9 Operationally Check Forward Tanks Low Level Switch 171 I: 2000 FH L600
197 or
223 24 MO
± 30 Days

28-26-22-710-001-A00 SYS 9 Operationally Check Aft Tanks Low Level Switch 171 I: 2000 FH L600
223 or
272 24 MO
± 30 Days
28-26-24-710-001-A00 SYS 9 Operationally Check Aft Tanks Transfer Check Valve 155/156 I: 8000 FH ALL
192 or
96 MO
± 60 Days
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SECTION : 2
MAINTENANCE PROGRAM
PAGE : 61
ISSUE : 1
DATE : 05/07/2019
28-41-00-710-001-A00 SYS 9 Operationally Check Electrical Fuel Quantity Indicating System 223 I: 4000 FH L600
(Fuel Low Level Logic) or
48 MO
± 30 Days
28-43-00-720-001-A00 SYS 9 Functionally Check Fuel Temperature Indication System 155 I: 8000 FH ALL
or
96 MO
± 60 Days
28-44-00-720-001-A00 SYS 9 Functionally Check Low Level Warning System 220 I: 8000 FH ALL
NOTE: Check during Internal Tank Inspection or
96 MO
± 60 Days
28-45-00-710-001-A00 SYS 8 Operationally Check Low Pressure Warning System 220 I: 1000 FH No ALL
Tolerance

28-46-00-710-001-A00 SYS 8 Operationally Check "FUSELAGE FUEL IMB" Warning System 223 I: 1200 FH L600
or
12 MO
± 15 Days
28-46-00-720-001-A00 SYS 9 Functionally Check "CHECK ACFT LOAD" or “FUEL XFER 220 I: 2000 FH L600
CRITICAL” Caution System or
24 MO
± 30 Days
28-46-00-720-002-A00 SYS 8 Functionally Check of Auxiliary Tanks Probes and FCU 191 I: 2000 FH ALL
232 or
24 MO
± 30 Days
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MAINTENANCE PROGRAM
PAGE : 62
ISSUE : 1
DATE : 05/07/2019
28-50-01-220-001-A00 SYS 8 Inspect (Detailed Inspection) Fuel Pump Electrical Harness 155/156 I: 10000 FH No L600
NOTE: This task complies with Fuel Tank Ignition Sources 192 Tolerance
Prevention (SFAR-88)
28-50-02-220-001-A00 SYS 8 Inspect (Detailed Inspection) Wing Fuel Tank Unit 155/156 I: 10000 FH No L600
NOTE: This task complies with Fuel Tank Ignition Sources 191/192 Tolerance
Prevention (SFAR-88) 531/541
631/641
28-50-03-220-002-A00 SYS 8 Inspect (Detailed Inspection) Fwd Fuel Tank Unit 197 I: 10000 FH No L600
NOTE: This task complies with Fuel Tank Ignition Sources Tolerance
28-50-04-212-001-A00 SYS 8 Inspect (General Visual) Wing Stub Harness 192 I: 10000 FH No L600
NOTE: This task complies with Fuel Tank Ignition Sources Tolerance

28-50-05-212-001-A00 SYS 8 Inspect (General Visual) Trailing Edge Harness 5711/5721 I: 10000 FH No L600
NOTE: This task complies with Fuel Tank Ignition Sources 5731/5732 Tolerance
6731/6732
28-50-06-212-001-A00 SYS 8 Inspect (General Visual) Leading Edge Harness 511/512 I: 10000 FH No L600
NOTE: This task complies with Fuel Tank Ignition Sources 513 Tolerance
613
28-50-07-220-001-A00 SYS 8 Inspect (Detailed Inspection) Aft Fuel Tank Units 272 I: 10000 FH L600
NOTE: This task complies with Fuel Tank Ignition Sources No Tolerance
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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MAINTENANCE PROGRAM
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ISSUE : 1
DATE : 05/07/2019
CHAPTER 29 - HYDRAULIC

29-10-00-710-001-A00 SYS 9 Operationally Check Electric Motor Driven Pumps Input Signals 193 I: 4000 FH ALL
226 or
48 MO
± 30 Days
29-10-00-790-001-A00 SYS 9 Functionally Check of Hydraulic Power System for Internal 226 I: 8000 FH ALL
Leakage or
96 MO
± 60 Days
29-10-01-710-001-A00 SYS 8 Operationally Check Shutoff Valve by Means of the Hydraulic 193 I: 4000 FH ALL
Panel Switch or
48 MO
± 30 Days
29-10-04-900-001-A00 SYS 7 Discard EMDP Brushes 193 I: 6000 FH No ALL
Tolerance
CHAPTER 29 - HYDRAULIC (CONTINUED)

29-10-08-211-001-A00 SYS 9 Visually Check Differential Pressure Indicators for Red Pins 193 I: 500 FH ALL
Popped out or
12 MO
± 15 Days
29-10-10-720-001-A00 SYS 8 Functionally Check Return Filter By-Pass Valve. 193 I: 4000 FH ALL
NOTE: 8000 FH or 72 MO if fluid contamination is checked at or
4000 FH or 48 MO interval 48 MO
± 30 Days
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MAINTENANCE PROGRAM
PAGE : 64
ISSUE : 1
DATE : 05/07/2019
29-10-13-720-001-A00 SYS 9 Functionally Check Priority Valve 223/224 I: 4000 FH ALL

225/226 or
48 MO
± 30 Days
29-30-03-720-001-A00 SYS 9 Functionally Check Hydraulic Filters Differential Pressure 193 I: 4000 FH ALL
Indicators or
NOTE: 8000 FH or 72 MO if fluid contamination is checked at 48 MO
4000 FH or 48 MO interval ± 30 Days
29-30-05-710-001-A00 SYS 9 Operationally Check HYD SYS OVHT Message 193 I: 8000 FH ALL
or
96 MO
± 60 Days
CHAPTER 30 - ICE AND RAIN PROTECTION

30-00-00-710-001-A00 SYS 8 Operationally Check Anti-icing System Messages 223 I: 100 FH ALL
224 or
225 6 MO
226 ± 15 Days
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SECTION : 2
MAINTENANCE PROGRAM
PAGE : 65
ISSUE : 1
DATE : 05/07/2019
CHAPTER 30 - ICE AND RAIN PROTECTION (CONTINUED)

30-11-05-710-001-A00 SYS 9 Operationally Check Wing Leak Thermostat 191 E I: 8000 FH ALL
223 or
72 MO
± 30 Days
30-12-00-710-001-A00 SYS 8 Operationally Check Electrical Hardware of the Horizontal 321 I: 4000 FH ALL
Stabilizer Thermal Anti-Icing System 324 or
48 MO
± 30 Days
30-12-05-710-001-A00 SYS 9 Operationally Check Horizontal Stabilizer Leak Thermostat 223 I: 8000 FH ALL
323/325 or
333/334 96 MO
± 60 Days
30-20-00-220-001-A00 SYS 9 Inspect (Detailed Inspection) Thermal Anti-Ice (TAI) Exhaust 413 I: 4000 FH ALL
Duct for Condition and Security of Installation 423 or
48 MO
± 30 Days
30-20-01-720-001-A00 SYS 9 Functionally Check Thermal Anti-Ice (TAI) Interbulkhead 411 I: 4000 FH ALL
Assembly for Leakage 421 or
48 MO
± 30 Days
30-31-00-710-001-A00 SYS 9 Operationally Check Pitot Anemometric Static Port Heating 123/124 I: 4000 FH ALL
224
30-31-00-710-002-A00 SYS 9 Operationally Check Pressurization Static Port Heating 171/172 I: 4000 FH ALL
No Tolerance
30-31-08-710-001-A00 SYS 9 Operationally Check Pitot Lines Heater 213 I: 10000 FH ALL
or
96 MO
± 60 Days
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SECTION : 2
MAINTENANCE PROGRAM
PAGE : 66
ISSUE : 1
DATE : 05/07/2019
CHAPTER 30 - ICE AND RAIN PROTECTION (CONTINUED)

30-32-00-710-001-A00 SYS 9 Operationally Check AOA Sensor Heating 223/224 I: 4000 FH No ALL
Tolerance
30-33-00-710-001-A00 SYS 9 Operationally Check TAT Sensor Heating 123 I: 4000 FH No ALL
213/223 Tolerance
30-41-00-710-001-A00 CAT II - Operationally Check Windshield Wiper 223/224 I: 4000 FH ALL
NOTE: Only for CAT II operation or
48 MO
± 30 Days
30-42-00-710-001-A00 SYS 9 Operationally Check Windshield Heating 223 I: 4000 FH ALL
or
48 MO
± 30 Days
30-43-01-211-001-A00 SYS 9 Visually Check Rain Repellent Coating (RRC) 223/224 I: 1500 FH ALL
or
24 MO
± 30 Days
CHAPTER 31 - INDICATING/RECORDING SYSTEMS

31-21-00-710-001-A00 SYS 9 Operationally Check Digital Clock 223/224 I: 4000 FH ALL
NOTE: Or in accordance with Local Regulatory Authority or
Requirements. Check Together With Task 31-31-00-720-001- 48 MO
A00 ± 30 Days
31-31-00-720-001-A00 SYS 6 Functionally Check Flight Data Recorder System 223 I: 4000 FH ALL
NOTE: Or in accordance with Local Regulatory Authority 272 or
Requirements 48 MO
± 30 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 67
ISSUE : 1
DATE : 05/07/2019
CHAPTER 31 - INDICATING/RECORDING SYSTEMS (CONTINUED)

31-31-00-970-001-A00 SYS 9 FDR DATA - Personal Computer Downloading 223 I: 12 MO ALL

272 ± 15 Days
31-31-02-710-001-A00 SYS 9 Operationally Check FDR 272 I: 24 MO ALL
Underwater Locator Beacon ± 30 Days
31-31-02-960-001-A00 SYS 9 Discard FDR Underwater Locator Beacon Battery 272 I: 72 MO ALL
NOTE: ULB battery change in accordance with manufacturer’s No Tolerance
Dataplate Expiration date
31-41-00-710-001-A00 SYS 9 Operationally Check DAU Channel Reversion Function 223/224 I: 4000 FH ALL
or
48 MO
± 30 Days
CHAPTER 32 - LANDING GEAR

32-Z711-213-001-A00 ZNL - General Visual Inspection (External) 113/114 E I: 24 MO L600
115/116 ± 30 Days
711/713
714
32-Z721-213-001-A00 ZNL - General Visual Inspection (External) 721/731 I: 24 MO L600
722/732 ± 30 Days
532/632
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SECTION : 2
MAINTENANCE PROGRAM
PAGE : 68
ISSUE : 1
DATE : 05/07/2019
CHAPTER 32 - LANDING GEAR (CONTINUED)

E
32-10-00-210-C01-L00 CPCP ED General Visual Inspection (External) of MAIN LANDING GEAR 721/731 I: 48 MO ALL
components: ± 30 Days
• Leg structure, equipped (left) - MLG (SSI 32-10-01)
• Leg structure, equipped (right) - MLG (SSI 32-10-02)
• Upper secondary brace strut assy - MLG (SSI 32-10-09)
• Lower secondary brace strut assy - MLG (SSI 32-10-10)
32-10-00-210-C02-L00 CPCP ED General Visual Inspection (External) of MAIN LANDING GEAR 721/731 I: 48 MO ALL
• Shock absorber piston tube assy - MLG (SSI 32-10-05)
• Shock absorber cylinder assy - MLG (SSI 32-10-06)
32-10-00-210-801-L00 STR AD General Visual Inspection (External) of MAIN LANDING GEAR 721/731 I: 2000 FC ALL
components: or
• Trailing arm - MLG (SSI 32-10-03) 96 MO
± 60 Days
32-10-00-220-801-L00 STR AD Detailed Inspection (External) of MAIN LANDING GEAR 721/731 I: 1000 FC ALL
components: or
• Wheel axle - MLG (SSI 32-10-04) 48 MO
± 30 Days
32-10-01-900-001-A00 SYS 8 Restore (Overhaul) Main Landing Gear (MLG) Leg Strut Assy 721/731 I: 144 MO ALL
± 60 Days
32-10-01-900-002-A00 SYS 8 Restore (Overhaul) MLG Trailing Arm Assy 721/731 I: 144 MO ALL
± 60 Days
32-10-02-610-001-A00 SYS 9 Service (Replenish) MLG Shock Absorber 721/731 I: 2500 FH ALL
or
15 MO
± 15 Days
32-10-02-900-001-A00 SYS 8 Restore (Overhaul) MLG Shock Absorber Assy 721/731 I: 144 MO ALL
± 60 Days
32-10-03-900-001-A00 SYS 8 Restore (Overhaul) MLG Upper Main Side Strut Assy 721/731 I: 144 MO ALL
± 60 Days
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SECTION : 2
MAINTENANCE PROGRAM
PAGE : 69
ISSUE : 1
DATE : 05/07/2019

32-10-03-900-002-A00 SYS 8 Restore (Overhaul) MLG Lower Main Side Strut Assy 721/731 I: 144 MO ALL
± 60 Days
32-10-04-900-001-A00 SYS 8 Restore (Overhaul) MLG Upper Secondary Side Strut Assy 721/731 I: 144 MO ALL
± 60 Days
32-10-04-900-002-A00 SYS 8 Restore (Overhaul) MLG Lower Secondary Side Strut Assy 721/731 I: 144 MO ALL
± 60 Days
32-10-05-900-002-A00 SYS 8 Restore (Overhaul) MLG Spring Cartridges Assy 721/731 I: 144 MO ALL
± 60 Days
32-20-00-210-C01-L00 CPCP ED General Visual Inspection (External) of NOSE LANDING GEAR 711 I: 48 MO ALL
• Lower drag stay - NLG (SSI 32-20-14)
32-20-00-210-801-L00 STR AD General Visual Inspection (External) of NOSE LANDING GEAR 711 I: 2000 FC ALL
components: or
• Strut (main fitting) - NLG (SSI 32-20-12) 48 MO
• Lower locking strut (SSI 32-20-16) ± 30 Days
• Upper drag stay - NLG (SSI 32-20-13)
• Upper locking stay - NLG (SSI 32-20-15)
• Torque links - NLG (SSI 32-20-17)
32-20-00-210-802-L00 STR AD General Visual Inspection (External) of NOSE LANDING GEAR 711 I: 1000 FC ALL
components: or
• Sliding tube - NLG (SSI 32-20-18) 96 MO
± 60 Days
32-20-00-220-801-L00 STR AD Detailed Inspection (External) of NOSE LANDING GEAR 711 I: 1000 FC ALL
components: or
• Wheel axle (SSI 32-20-19) 48 MO
± 30 Days
32-20-01-610-001-A00 SYS 9 Service (Replenish) NLG Shock Absorber 711 I: 2500 FH ALL
or
15 MO
± 15 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 70
ISSUE : 1
DATE : 05/07/2019

32-20-01-720-001-A00 SYS 8 Functionally Check NLG Leg for Centering Cam Play 711 I: 144 MO ALL
NOTE: Perform at the time of NLG Sliding Tube Assy ± 60 Days
Restoration
32-20-01-900-001-A00 SYS 8 Restore (Overhaul) Nose Landing Gear (NLG) Main Fitting Assy 711 I: 144 MO ALL
± 60 Days
32-20-01-900-002-A00 SYS 8 Restore (Overhaul) NLG Sliding Tube Assy 711 I: 144 MO ALL
± 60 Days
32-20-01-900-003-A00 SYS 8 Restore (Overhaul) NLG Steering Cuff Assy 711 I: 144 MO ALL
± 60 Days
32-20-01-900-004-A00 SYS 8 Restore (Overhaul) NLG Torque Link Assy 711 I: 144 MO ALL
± 60 Days
32-20-02-900-001-A00 SYS 8 Restore (Overhaul) NLG Main Drag Strut Top Stay Assy 711 I: 144 MO ALL
± 60 Days
32-20-02-900-002-A00 SYS 8 Restore (Overhaul) NLG Main Drag Strut Bottom Stay Assy 711 I: 144 MO ALL
± 60 Days
32-20-03-900-001-A00 SYS 8 Restore (Overhaul) NLG Upper Auxiliary Drag Strut Assy 711 I: 144 MO ALL
± 60 Days
32-20-03-900-002-A00 SYS 8 Restore (Overhaul) NLG Lower Auxiliary Drag Strut Assy 711 I: 144 MO ALL
± 60 Days
32-20-04-900-002-A00 SYS 8 Restore (Overhaul) NLG Downlock Spring Assy 711 I: 144 MO ALL
± 60 Days
32-32-00-710-001-A00 SYS 9 Operationally Check Landing Gear Extension and Retraction 220 I: 4000 FH ALL
(Electrical) Indication and Downlock Relays by Channels A and or
B 48 MO
± 30 Days
32-32-02-710-001-A00 SYS 8 Operationally Check Solenoid and Downlock Release Button of 220 I: 8000 FH ALL
the Landing Gear Control Lever or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 71
ISSUE : 1
DATE : 05/07/2019

32-34-00-640-001-A00 SYS 8 Lubricate Landing Gear (MLG & NLG) and Steering System 711/721 I: 500 FH ALL
731 or
500/600 12 MO
± 15 Days
32-34-00-710-001-A00 SYS 9 Operationally Check Landing Gear Emergency Extension 220 I: 4000 FH ALL
(Override Switch) 114 or
48 MO
± 30 Days
32-34-00-720-001-A01 SYS 8 Functionally Check Landing Gear Emergency Extension 220 I: 4000 FH ALL
114 or
48 MO
± 30 Days
32-34-03-720-001-A00 SYS 8 Functionally Check Condition and Tension of Free-Fall Control 155 I: 8000 FH ALL
Cables or
72 MO
± 30 Days
32-41-00-720-001-A00 SYS 6 Functionally Check Main Brake System 124 I: 4000 FH ALL
223 or
48 MO
± 30 Days
32-41-01-710-001-A00 SYS 8 Operationally Check Brake Pedal Transducer 123 I: 8000 FH ALL
or
96 MO
± 60 Days
32-41-07-720-001-A00 SYS 9 Functionally Check Brake Hydraulic Fuse 532/632 I: 4000 FH ALL
or
48 MO
± 30 Days
32-41-09-710-001-A00 SYS 8 Operationally Check Return Line Check Valve of Main Brake 192 I: 4000 FH ALL
System or
48 MO
± 30 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 72
ISSUE : 1
DATE : 05/07/2019

32-44-00-720-001-A00 SYS 8 Functionally Check Emergency Parking Brake System 220 I: 8000 FH ALL
or
96 MO
± 60 Days
32-44-02-720-001-A00 SYS 8 Functionally Check Hydraulic Accumulator for Nitrogen 193 I: 1000 FH ALL
Pre-Charge or
12 MO
± 15 Days
32-44-06-720-001-A00 SYS 8 Functionally Check Thermal Relief Valve of the Emer- 193 I: 8000 FH ALL
gency/Parking Brake System or
96 MO
± 60 Days
32-44-08-710-001-A00 SYS 8 Operationally Check Return Line Check Valve of 192 I: 4000 FH ALL
Emergency/Parking Brake System 193 or
48 MO
± 30 Days
32-44-10-640-001-A00 SYS 8 Lubricate Mechanical Hardware (Handle) and Roller of 220 I: 4000 FH ALL
Emergency Parking Brake Valve 114 or
48 MO
± 30 Days
32-49-02-220-001-A00 SYS 7 Inspect (Detailed Inspection) of Wheels Speed Transducer Clip 721/731 (*) ALL
in the Hub Cap Drive Clip No Tolerance
(*) NOTE: At Each Tire Change
32-49-03-220-001-A00 SYS 6 Inspect (Detailed Inspection) of Brake Wear Indicator 721/731 (*) ALL
(*) NOTE: At Each Tire Change No Tolerance
32-49-07-710-001-A00 SYS 8 Operationally Check Brake Shuttle Valve 220 (*) ALL
(*) NOTE: At Each Brake Replacement 721/731 No Tolerance
32-50-00-710-001-A00 SYS 8 Operationally Check Nosewheel Steering System Disengage 220 I: 500 FH ALL
711 or
6 MO
± 15 Days
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DATE : 05/07/2019

32-50-06-720-001-A00 SYS 8 Functionally Check 7-Degree Proximity Switch 220 I: 4000 FH ALL
711 or
48 MO
± 30 Days
32-62-00-710-001-A00 SYS 8 Operationally Check Landing Gear Warning System 220 I: 500 FH ALL
or
6 MO
± 15 Days
CHAPTER 33 - LIGHTS

33-47-03-720-001-A00 SYS 8 Functionally Check White Strobe Lighting System 321 I: 1500 FH No ALL
NOTE: This task is applicable only to aircraft under ANAC/FAA 561/661 Tolerance
Certifications
33-50-00-710-001-A00 SYS 8 Operationally Check Emergency Lighting System 220/230 I: 500 FH No ALL
240/250 Tolerance
260
33-50-04-720-001-A00 SYS 8 Functionally Check DLE Emergency Lighting System Battery 232 I: 6 MO ALL
Power Supply 241/251 ± 15 Days
33-50-04-720-001-A01 SYS 8 Functionally Check RADIANT or BRUCE Emergency Lighting 232 I: 18 MO No ALL
System Battery Power Supply 241/251 Tolerance
33-51-01-720-001-A00 SYS 8 Functionally Check of Flashlight Rechargeable Battery 223 I: 12 MO ALL

224/231 ± 15 Days
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DATE : 05/07/2019
CHAPTER 33 - LIGHTS (CONTINUED)

33-51-01-720-001-A01 SYS 8 Functionally Check of Flashlight Non Rechargeable Battery 223 I: 12 MO ALL
224/231 ± 15 Days
33-51-03-960-001-A00 SYS 8 Discard Non Rechargeable Flashlight Battery Pack 231 I: 24 MO ALL
± 30 Days
CHAPTER 34 - NAVIGATION

34-01-00-720-001-A00 SYS 8 Functionally Check Integrated Standby Instrument System - 223/224 I: 5000 FH No ALL
ISIS 225/226 Tolerance
Requirements
34-13-00-610-001-A00 SYS 6 Service (Cleaning) Pitot-Static System 113/114 I: 8000 FH ALL
NOTE: Or in accordance with Local Regulatory Authority 213/214 or
Requirements 220 72 MO
± 30 Days
34-13-00-680-001-A00 SYS 6 Service (Drain) Pitot Lines 113/114 I: 500 FH ALL
213/214 or
6 MO
± 15 Days
34-13-00-790-001-A00 SYS 6 Functionally Check Pitot-Static System for Leakage 123/124 I: 5000 FH No ALL
NOTE: Or in accordance with Local Regulatory Authority 213/214 Tolerance
Requirements
34-13-04-280-001-A00 SYS 6 Inspect (Special Inspection) RVSM Critical Region (Skin) for 231/232 I: 5000 FH ALL
Waviness or
NOTE: Only for RVSM operation 48MO
± 30 Days
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DATE : 05/07/2019
CHAPTER 34 - NAVIGATION (CONTINUED)

34-13-04-280-002-A00 SYS 6 Inspect (Special Inspection) Static Port Surrounding Plate for 231/232 I: 5000 FH ALL
Flushness and Integrity or
NOTE: Only for RVSM operation 48MO
± 30 Days
34-13-04-280-003-A00 SYS 6 Inspect (Special Inspection) Oxygen Service Panel for Flush- 123/124 I: 5000 FH ALL
ness and Integrity (Passenger Gaseous Oxygen System Only) or
NOTE: If installed 48MO
NOTE: Only for RVSM operation ± 30 Days
34-15-00-720-001-A00 SYS 8 Functionally Check ADC system 223 I: 5000 FH ALL
NOTE: Or in accordance with Local Regulatory Authority No Tolerance
Requirements
34-21-03-140-001-A00 SYS 6 Restore (Cleaning) AHRS Fan Filter 113 I: 1000 FH ALL
No Tolerance
34-22-00-710-001-A00 SYS 9 Operationally Check Electronic Flight Instrument System 223 I: 4000 FH ALL
Reversion Function or
48 MO
± 30 Days
34-25-00-720-001-A00 SYS 6 Functionally Check Standby Compass for proper compensation 220 I: 24 MO ALL
NOTE: Or in accordance with Local Regulatory Authority 721/731 ± 30 Days
Requirements
34-27-03-140-001-A00 SYS 6 Restore (Cleaning) Dual IRS Mounting Tray Fan Filter 113 I: 500 FH ALL
No Tolerance
34-41-00-710-003-A00 SYS 9 Operationally Check EGPWS/ Windshear 223 I: 4000 FH ALL
or
48 MO
± 30 Days
34-52-00-720-001-A00 SYS 9 Functionally Check Transponder System 220 I: 24 MO ALL
NOTE: Or in accordance with Local Regulatory Authority No Tolerance
Requirements
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DATE : 05/07/2019
CHAPTER 34 - NAVIGATION (CONTINUED)

34-63-01-720-001-A00 SYS 6 Functionally Check Electronic Flight Bag Display Unit (EDU), 223/224 I: 12 MO ALL
Battery Capacity. ± 15 Days
NOTE: Only for aircraft equipped with EFB.
CHAPTER 35 - OXYGEN

35-10-00-710-001-A00 SYS 8 Operationally Check Crew/Pax Oxygen Masks 220 I: 4000 FH ALL
or
48 MO
± 30 Days
35-10-07-720-001-A00 SYS 8 Functionally Check Crew Oxygen Cylinder Pressure Regulator 224 I: 60 MO No ALL
Tolerance
35-10-07-720-002-A01 SYS 9 Functionally Check (Hydrostatic Test) Crew Oxygen Cylinder. 224 I: 60 MO No ALL
NOTE: Or in accordance with Local Regulatory Authority Tolerance
Requirements
35-11-02-212-001-A00 SYS 8 Visually Check Pressure Transducer Indication on MFD Versus 124 I: 2500 FH ALL
External Gauge Indication or
24 MO
± 30 Days
35-20-00-710-001-A00 SYS 8 Operationally Check Passenger Gaseous Oxygen System in 220/230 I: 2000 FH ALL
Manual Mode 240/250 or
260 12 MO
± 15 Days
35-20-00-710-002-A00 SYS 8 Operationally Check Gaseous Oxygen Low Pressure Indicating 232 I: 36 MO ALL
Circuit ± 30 Days
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DATE : 05/07/2019
CHAPTER 35 - OXYGEN (CONTINUED)

35-20-00-720-001-A00 SYS 8 Functionally Check Passenger Gaseous Oxygen System in 220/230 I: 4000 FH ALL
Auto Mode 240/250 or
260 48 MO
± 30 Days
35-20-02-211-001-A00 SYS 8 Visually Check Passenger Gaseous Oxygen Mask 233/243 I: 4000 FH ALL
244 or
251/252 48 MO
262 ± 30 Days
35-20-04-720-001-A00 SYS 9 Functionally Check (hydrostatic Test) Passenger Gaseous 232 I: 60 MO ALL
Oxygen Cylinder No Tolerance
35-20-04-960-001-A00 SYS 9 Discard Passenger Gaseous Oxygen Cylinder 230/240 I: 180 MO ALL
35-20-06-900-001-A00 SYS 8 Restore (Overhaul) Gaseous Oxygen Electric Pulse/Latching 232 I: 2000 FH ALL
On-Off Valve or
60 MO
± 30 Days
35-20-07-900-001-A00 SYS 8 Restore (Overhaul) Gaseous Oxygen Sequence Regulator 232 I: 2000 FH ALL
or
60 MO
± 30 Days
35-20-08-211-001-A00 SYS 9 Visually Check Pressure Transducer Indicator on MFD Versus 124 I: 2000 FH ALL
Gaseous Oxygen Cylinder Gauge Indication or
24 MO
± 30 Days
35-20-12-211-001-A00 SYS 9 Visually Check Passenger Gaseous Oxygen Pressure Indicator 124 I: 2000 FH ALL
Gauge or
24 MO
± 30 Days
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DATE : 05/07/2019
CHAPTER 35 - OXYGEN (CONTINUED)

35-20-15-790-001-A00 SYS 8 Functionally Check (Leak) Passenger Gaseous Oxygen 124/224 I: 4000 FH ALL
Distribution (HP) Lines 232 or
48 MO
± 30 Days
35-20-16-790-001-A00 SYS 8 Functionally Check (Leak) Passenger Gaseous Oxygen 232/233 I: 4000 FH ALL
Distribution (LP) Lines 263 or
48 MO
± 30 Days
35-30-01-211-001-A00 SYS 9 Visually Check Portable Oxygen Cylinder Gauge Pressure 231 I: 500 FH ALL
Indication or
NOTE: Or in accordance with Local Regulatory Authority 12 MO
Requirements ± 15 Days
35-30-01-720-001-A00 SYS 9 Functionally Check Portable Oxygen Cylinder Pressure 220 I: 60 MO No ALL
Regulator 231 Tolerance
35-30-01-720-002-A00 SYS 9 Functionally Check (Hydrostatic Test) Portable Oxygen 220 I: 60 MO No ALL
Cylinder 231 Tolerance
Requirements
35-30-02-211-001-A00 SYS 9 Visually Check Continuous Flow Mask 220/231 I: 2500 FH ALL
or
24 MO
± 30 Days
35-30-03-960-001-A00 SYS 9 Discard Protective Breathing Equipment 220 I: 120 MO No ALL
231/232 Tolerance
261/262
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CHAPTER 36 - PNEUMATIC

36-10-01-130-001-A00 SYS 6 Restore (Cleaning) Crossbleed Valve Filter by Ultrasonic 272 I: 4000 FH ALL
Method No Tolerance
36-11-01-220-001-A00 SYS 6 Inspect (Detailed Inspection) Engine Low Pressure Bleed Air 415/425 I: 4000 FH ALL
Check Valve P/N 816603-3 or
48 MO
± 30 Days
36-11-02-130-001-A00 SYS 9 Restore (Cleaning) High-Stage Valve Filter by Ultrasonic 412/422 I: 4000 FH ALL
Method No Tolerance
36-11-03-130-001-A00 SYS 6 Restore (Cleaning) Fan Air Valve Filter by Ultrasonic Method 414/424 I: 4000 FH ALL
No Tolerance
36-11-04-110-001-A00 SYS 6 Restore (Cleaning) Pre-Cooler by Chemical Method 414/424 I: 6000 FH ALL
or
60 MO
± 30 Days
36-11-05-130-001-A00 SYS 6 Restore (Cleaning) Engine Bleed Valve Filter by Ultrasonic 414/424 I: 4000 FH ALL
Method No Tolerance
36-11-11-710-001-A00 SYS 8 Operationally Check Thermostat Shutoff Valve 272 I: 2000 FH ALL
813 or
24 MO
± 30 Days
36-20-00-710-001-A00 SYS 8 Operationally Check Bleed Valve Indicating Function 412/422 I: 8000 FH or ALL
96 MO
± 60 Days
36-20-00-720-001-A00 SYS 8 Functionally Check the Overtemperature Warning Circuit 270 I: 8000 FH ALL
or
96 MO
± 60 Days
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DATE : 05/07/2019
CHAPTER 36 - PNEUMATIC (CONTINUED)

36-20-02-710-003-A00 SYS 8 Operationally Check Thermal Switch 193/194/195 I: 4000 FH ALL
261/262 or
271/272/320 48 MO
414/424/813 ± 30 Days
36-20-05-710-002-A00 SYS 8 Operationally Check Bleed Automatic Shut-off and 272 I: 1600 FH ALL
Circuitry 312/412 or
422/414 18 MO
424 ± 15 Days
CHAPTER 38 - WASTE AND WATER

38-10-00-610-001-A00 SYS 9 Restore (Cleaning) Sterilize Potable Water System. 193 I: 500 FH ALL
NOTE: Or in accordance with Local Regulatory Authority or
Requirements 6 MO
± 15 Days
38-10-00-710-001-A00 SYS 9 Operationally Check Potable Water Heater System 232 I: 48 MO L600
NOTE: Applicable to Aircraft Equipped with One (01) Potable ± 30 Days
Water Service Panel
38-10-03-960-001-A00 SYS 9 Discard Water Filter cartridge 262 I: 1200 FH No ALL

Tolerance
38-10-05-720-001-A00 SYS 9 Functionally Check of Mechanical Relief Valve GOODRICH 262 I: 2000 FH L600
PN 4E3263-1. or
24 MO
± 30 Days
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DATE : 05/07/2019
CHAPTER 38 - WASTE AND WATER (CONTINUED)

38-10-05-720-001-A01 SYS 7 Functionally Check of Mechanical Relief Valve HYDRAFLOW 232 I: 4000 FH ALL
PN VA046-series. or
48 MO
± 30 Days
38-32-04-960-001-A00 SYS 7 Discard Waste Drain Valve O’ring 1932 I: 18 MO ALL
196 ± 15 Days
38-32-10-960-001-A00 SYS 7 Discard Waste Drain Valve Cap Seal 1932 I: 60 MO ALL
196 ± 30 Days
38-33-00-710-001-A00 SYS 9 Operationally Check of Waste Water Heater System 231 I: 48 MO ALL
± 30 Days
CHAPTER 49 - AIRBONE POWER UNIT

49-17-00-160-001-A00 SYS 9 Restore (Cleaning) APU Drains Post-Mod SB 145LEG-49-0006 313 I: 4000 FH or ALL
or with an equivalent modification factory-incorporated 48 MO
± 30 Days
49-20-05-960-001-A00 SYS 6 Discard of turbine wheel. 313 I: 15000 AH ALL
NOTE: Applicable only for APU Model APS500R (T 62T -40C14). No Tolerance
49-31-00-710-001-A01 SYS 9 Operationally Check of the FADEC BITE Display for Fault 272 I: 400 AH ALL
Messages for APU MODEL T-62T-40C14 (APS500R) No Tolerance
49-31-04-960-001-A01 SYS 9 Discard APS 500R Inlet Fuel Filter for APU MODEL 313 I: 1200 AH ALL
T-62T-40C14 No Tolerance
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DATE : 05/07/2019
CHAPTER 49 - AIRBONE POWER UNIT (CONTINUED)

49-41-03-220-001-A00 SYS 6 Inspect (Detailed Inspection) Igniter Plug 313 I: 1200 AH No ALL
Tolerance
49-62-00-710-001-A00 SYS 8 Operationally Check Emergency Shutdown by Using APU Fuel 156 I: 8000 FH ALL
Shutoff Switch and Fire Test Switch or
72 MO
± 30 Days
49-91-00-610-001-A00 SYS 6 Service (Replenish) Check Oil Level and Service Oil System as 313 I: 400 AH No ALL
required Tolerance
49-91-00-680-001-A00 SYS 9 Service (Drain) and Replace Oil Supply 313 I: 2000 AH ALL
or
12 MO
No Tolerance
49-91-01-960-001-A00 SYS 9 Discard Oil Filter Element 313 I: 2000 AH or ALL
24 MO
No Tolerance
CHAPTER 52 - DOORS

52-Z811-213-001-A00 ZNL - General Visual Inspection (External) 811 I: 48 MO ALL
± 30 Days
52-Z811-214-001-A00 ZNL - General Visual Inspection (Internal) 811 I: 24 MO ALL
± 30 Days
52-Z812-213-001-A00 ZNL - General Visual Inspection (External) 812/822 I: 96 MO ALL
± 60 Days
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DATE : 05/07/2019
CHAPTER 52 - DOORS (CONTINUED)

52-Z812-214-001-A00 ZNL - General Visual Inspection (Internal) 812/822 I: 96 MO ALL
± 60 Days
± 30 Days
± 30 Days
52-00-00-211-001-A00 SYS 7 Visually Check Locking Red Marks 811 I: 4000 FH ALL
NOTE: Repaint if necessary 231 or
48 MO
± 30 Days
52-10-00-220-C01-L00 CPCP ED Detailed Inspection (External) of MAIN DOOR components: 811 I: 48 MO L600
• Structure (SSI 52-10-01) ± 30 Days
52-10-00-220-C02-L00 CPCP ED Detailed Inspection (Internal) of MAIN DOOR components: 811 I: 48 MO L600
• Structure (SSI 52-10-01) ± 30 Days
52-10-00-220-801-L00 STR AD Detailed Inspection (Internal) of MAIN DOOR components: 811 I: 4000 FC ALL
• Main door Stop & back up structures (SSI 52-10-03) or
• Main door folding flap stops (SSI 52-10-04) 48 MO
NOTE: During this inspection, the CPCP basic task shall also be ± 30 Days
performed for SSI 52-10-04
52-10-00-220-802-L00 STR AD Detailed Inspection (Internal) of MAIN DOOR components: 811 I: 8000 FC ALL
• Main door folding flap structure (SSI 52-10-02) or
• Main door-to-fuselage attachment fittings & interface parts 96 MO
(SSI 52-10-05) ± 60 Days
52-10-00-220-803-L00 STR AD Detailed Inspection (External) of MAIN DOOR components: 811 I: 4000 FC ALL
• Main door-to-fuselage attachment fittings & interface parts or
(SSI 52-10-05) 96 MO
• Main door folding flap structure (SSI 52-10-02) ± 60 Days
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DATE : 05/07/2019

52-10-00-220-804-L00 STR AD Detailed Inspection (External) of MAIN DOOR components: 811 E I: 2000 FC ALL
• Stop & back up structures (SSI 52-10-03) or
96 MO
± 60 Days
52-11-00-640-001-A00 SYS 6 Lubricate Standard Main Door Actuating and Locking Mecha- 811 I: 4000 FH ALL
nism or
48 MO
± 30 Days
52-11-00-720-005-A00 SYS 8 Functionally Check Standard Main Door Actuating, Latching 811 I: 4000 FH ALL
and Locking Mechanism or
48 MO
± 30 Days
52-12-00-710-001-A00 SYS 9 Operationally Check Alternate Opening System 222 I: 4000 FH ALL
231 or
48 MO
± 30 Days
52-12-00-720-001-A00 SYS 7 Functionally Check Main Door Hydraulic Accumulator Nitrogen 114 I: 2500 FH ALL
Charge or
24 MO
± 30 Days
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DATE : 05/07/2019

52-14-00-220-001-A00 SYS 9 Inspect (Detailed inspection) Main Door Draining System for 811 I: 4000 FH ALL
Obstruction or Damage or
48 MO
± 30 Days
52-21-00-220-801-L00 STR AD Detailed Inspection (External) of PASSENGER CABIN 812/822 I: 4000 FC ALL
ESCAPE HATCH components: or
• Escape hatch structure (SSI 52-21-06) 96 MO
• Escape hatch window frame (SSI 52-21-07) ± 60 Days
52-21-00-220-802-L00 STR AD Detailed Inspection (Internal) of PASSENGER CABIN ESCAPE 812/822 I: 4000 FC ALL
HATCH components: or
• Escape hatch structure (SSI 52-21-06) 96 MO
• Escape hatch window frame (SSI 52-21-07) ± 60 Days
52-21-00-640-001-A00 SYS 8 Lubricate Passenger Cabin Escape Hatch Support Pins 812/822 I: 4000 FH ALL
or
48 MO
± 30 Days
52-21-00-710-001-A00 SYS 8 Operationally Check Passenger Cabin Escape Hatch Mecha- 822 I: 4000 FH ALL
nism or
48 MO
± 30 Days
52-22-00-710-001-A00 SYS 9 Operationally Check Cockpit Emergency Exit 223/224 I: 4000 FH ALL
or
48 MO
± 30 Days
52-22-01-640-001-A00 SYS 9 Lubricate Cockpit Emergency Exit Locking Mechanism 223/224 I: 4000 FH ALL
or
48 MO
± 30 Days
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ISSUE : 1
DATE : 05/07/2019

52-30-00-210-C01-L00 CPCP ED General Visual Inspection (External) of BAGGAGE DOOR 813 I: 48 MO L600
• Baggage door structure (SSI 52-30-08)
52-30-00-210-801-L00 STR AD General Visual Inspection (Internal) of BAGGAGE DOOR 813 I: 4000 FC ALL
components: or
• Baggage door structure (SSI 52-30-08) 96 MO
± 60 Days
52-30-00-220-801-L00 STR AD Detailed Inspection (Internal) of BAGGAGE DOOR 813 I: 3200 FC L600
components: or
• Baggage door stops and fittings (SSI 52-30-09) 96 MO
NOTE: Applicable to aircraft Pre-Mod. SB 145LEG-00-0007 ± 60 Days
52-30-00-220-801-L01 STR AD Detailed Inspection (Internal) of BAGGAGE DOOR 813 I: 2000 FC ALL
components: or
• Baggage door stops and fittings (SSI 52-30-09) 96 MO
NOTE: Applicable to aircraft Post-Mod. SB 145LEG-00-0007 or ± 60 Days
with an equivalent modification factory-incorporated
52-31-00-640-001-A00 SYS 6 Lubricate Baggage Door Gear Box 813 I: 4000 FH ALL
or
48 MO
± 30 Days
52-32-00-220-001-A00 SYS 7 Inspect (Detailed Inspection) Baggage Door Lifting and 813 I: 4000 FH ALL
Lowering Mechanism for General Condition and Torsion Bar for or
Torsion 48 MO
± 30 Days
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DATE : 05/07/2019

52-42-01-220-001-A00 SYS 9 Inspect (Detailed Inspection) Cockpit Underfloor Access Hatch 123 I: 4000 FH ALL
Mechanism or
48 MO
± 30 Days
52-44-00-220-801-L00 STR AD Detailed Inspection (External) of REAR ELECTRONIC 272 I: 2000 FC ALL
COMPARTMENT DOOR components: or
• Rear Electronic Compartment Door Structure (SSI 52-44-01) 48 MO
± 30 Days
52-44-00-220-802-L00 STR AD Detailed Inspection (Internal) of REAR ELECTRONIC 272 I: 2000 FC ALL
COMPARTMENT DOOR components: or
• Rear Electronic Compartment Door Structure (SSI 52-44-01) 48 MO
± 30 Days
52-44-01-220-001-A00 SYS 9 Inspect (Detailed Inspection) Rear Electronic Compartment 272 I: 4000 FH ALL
Door Mechanism or
48 MO
± 30 Days
52-71-00-710-001-A00 SYS 8 Operationally Check Forward Electronic Compartment Door 113/114 I: 4000 FH ALL
Warning Message or
48 MO
± 30 Days
52-72-00-710-001-A00 SYS 9 Operationally Check Rigging Door Warning Message 123/124 I: 4000 FH ALL
or
48 MO
± 30 Days
52-73-00-710-001-A00 SYS 9 Operationally Check Main Door Warning Message 811 I: 4000 FH ALL
or
48 MO
± 30 Days
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DATE : 05/07/2019

52-73-01-720-001-A00 SYS 9 Functionally Check Main Door Warning Microswitches 811 I: 4000 FH or ALL
48 MO
± 30 Days
52-75-00-710-001-A00 SYS 8 Operationally Check Emergency Exit Warning Message 822 I: 4000 FH or ALL
48 MO
± 30 Days
52-76-00-710-001-A00 SYS 8 Operationally Check Baggage Door Warning Message 813 I: 4000 FH or ALL
48 MO
± 30 Days
52-77-00-710-001-A00 SYS 8 Operationally Check Rear Electronic Compartment Door 272 I: 4000 FH or ALL
Warning Message 48 MO
± 30 Days
CHAPTER 53 - FUSELAGE

± 30 Days
± 30 Days
± 30 Days
± 30 Days
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DATE : 05/07/2019
CHAPTER 53 - FUSELAGE (CONTINUED)

53-Z114-214-001-A00 ZNL - General Visual Inspection (Internal) 114 I: 48 MO L600
± 30 Days
± 30 Days
53-Z213-214-001-A00 ZNL - General Visual Inspection (Internal) 113/114 I: 48 MO L600
213/214 ± 30 Days
215/216
± 30 Days
123/124 ± 30 Days
± 30 Days
223/224 ± 30 Days
± 60 Days
± 60 Days
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± 30 Days
± 30 Days
NOTE: Applicable to Aircraft Pre-Mod. SB 145LEG-53-0031. ± 15 Days
NOTE: Applicable to Aircraft Post-Mod. SB 145LEG-53-0031 or ± 30 Days
with an equivalent modification factory-incorporated.
± 30 Days
± 30 Days
± 60 Days
± 60 Days
± 30 Days
± 60 Days
± 30 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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± 60 Days
± 60 Days
153/154 ± 30 Days
155/156
157
157 ± 30 Days
± 60 Days
± 60 Days
± 60 Days
± 60 Days
± 30 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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DATE : 05/07/2019

± 60 Days
± 30 Days
± 60 Days
± 60 Days
± 30 Days
± 30 Days
± 30 Days
± 30 Days
± 60 Days
± 30 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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± 30 Days
53-Z191-213-001-A00 ZNL - General Visual Inspection (External) 191/192 I: 48 MO L600
NOTE: Do not remove the fuel tank 193/194 ± 30 Days
195/196
197/198
199
1921/1922
1923/1971
1981/1982
1991/1992

193/194 ± 30 Days
195/196
198/199
1921/1922
1923/1971
1981/1982
1991/1992

± 30 Days
± 30 Days
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± 30 Days
± 30 Days
± 30 Days

317/318 ± 60 Days
53-00-01-220-001-A00 SYS 9 Inspect (Detailed Inspection) Fuselage Drains for Obstruction or 120/130 I: 4000 FH ALL
Damage 140/150 or
160/170 48 MO
± 30 Days
53-11-00-210-C01-L00 CPCP ED General Visual Inspection (Internal) of FUSELAGE 113/114 I: 96 MO ALL
• Bulkhead 1 structure (SSI 53-10-23)
• Battery compartment cutout structure (SSI 53-10-44)
• Hydraulic compartment cutout structure (SSI 53-10-45)
• Longerons (SSI 53-10-46)
53-11-00-210-C02-L00 CPCP ED General Visual Inspection (External) of FUSELAGE compo- 113/114 T: 96 MO I: ALL
nents: 213/214 48 MO
• Fuselage skin panel at stringers, frames/bulkheads, and ± 30 Days
splices (SSI 53-10-07)
• Fuselage skin panel at pressure bulkhead (SSI 53-10-15)
53-11-00-220-C01-L00 CPCP ED Detailed Inspection (Internal) of FUSELAGE components: 113/114 I: 48 MO ALL
• Nose landing gear fitting, including bearing cap and trunnion ± 30 Days
fitting (SSI 53-10-25)
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DATE : 05/07/2019

• Fuselage skin circumferential splice (SSI 53-10-14) 213/214 ± 60 Days
• Frames (SSI 53-10-43)
• Fuselage skin longitudinal splice (SSI 53-10-08) ± 60 Days

53-11-00-220-C05-L00 CPCP ED Detailed Inspection (External) of FUSELAGE components: 113/114 T: 96 MO I: ALL
• Nose landing gear bay structure (SSI 53-10-24) 48 MO
± 30 Days
53-11-00-220-C06-L00 CPCP ED Detailed Inspection (Internal) of FUSELAGE components: 113/114 T: 96 MO I: ALL
• Nose landing gear bay structure (SSI 53-10-24) 48 MO
± 30 Days
53-11-00-220-801-L00 STR AD Detailed Inspection (Internal) of FUSELAGE components: 213/214 I: 8000 FC ALL
• Fuselage skin panel at stringers, frames/ bulkheads, and or
splices (SSI 53-10-07) 96 MO
± 60 Days
53-11-00-250-801-L00 STR AD Special Detailed Inspection (Internal) of FUSELAGE 113/114 I: 10000 FC No ALL
components by using Eddy Current Inspection Method: Tolerance
• Nose landing gear fitting, including Bearing Cap and Trunnion
Fitting (SSI 53-10-25)
53-12-00-210-C01-L00 CPCP ED General Visual Inspection (External) of FUSELAGE 123/124 T: 96 MO I: ALL
components: 223/224 48 MO
• Fuselage skin panel at stringers, frames/bulkheads, and 225/226 ± 30 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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PAGE : 96
ISSUE : 1
DATE : 05/07/2019

components: 223/224 48 MO
• Fuselage skin panel at pressure bulkhead (SSI 53-10-15) ± 30 Days
53-12-00-210-C04-L00 CPCP ED General Visual Inspection (External) of FUSELAGE 223/224 I: 48 MO L600
• Windshield panel (SSI 53-10-21)
components: 48 MO
• Maintenance door cutout structure (SSI 53-10-49) ± 30 Days

53-12-00-210-801-L00 STR AD General Visual Inspection (Internal) of FUSELAGE 223/224 I: 4000 FC ALL
components: or
• Windshield panel (SSI 53-10-21) 96 MO
± 60 Days
• Fuselage skin circumferential splice (SSI 53-10-14) 223/224 ± 60 Days
• Frames (SSI 53-10-43) 225/226
• Cockpit floor beams and columns (SSI 53-10-27) ± 60 Days
• Maintenance door cutout structure (SSI 53-10-49)
• Fuselage skin panel at pressure bulkhead ± 60 Days
(SSI 53-10-15)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 97
ISSUE : 1
DATE : 05/07/2019
• Windshield cutout structure (SSI 53-10-17) 225/226 or
• Cockpit window cutout structure (SSI 53-10-18) 96 MO
± 60 Days
53-12-00-220-802-L00 STR AD Detailed Inspection (Internal) of FUSELAGE components: 221/222 I: 4000 FC No ALL
• Windshield center post and its attachment (SSI 53-10-19) 223/224 Tolerance
• Windshield lateral post and its attachment (SSI 53-10-20) Tolerance
• Cockpit window rear post and its attachment (SSI 53-10-22)

• Forward pressure bulkhead (SSI 53-10-26) 215/216 or
121/122 96 MO
221/222 ± 60 Days
53-12-00-220-806-L00 STR AD Detailed Inspection (External) of FUSELAGE components: 223/224 I: 2000 FC ALL
• Cockpit window cutout structure (SSI 53-10-18) 225/226 or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 98
ISSUE : 1
DATE : 05/07/2019
• Cockpit window rear post and its attachment (SSI 53-10-22) or
96 MO
± 60 Days
• Cockpit floor beams and columns (SSI 53-10-27) or
NOTE: Applicable to aircraft Post-Mod. S.B. 145LEG-00-0007 96 MO
or with an equivalent modification factory-incorporated ± 60 Days

53-12-00-250-804-L00 STR AD Special Detailed Inspection (Internal) of FUSELAGE 223/224 T: 7380 FC I: L600
components by using Eddy Current Inspection Method: 1840 FC
• Windshield center post, including its attachments and lower No Tolerance
NOTE: Applicable to aircraft Pre-Mod. S.B. 145LEG-00-0007
and Pre-Mod. S.B. 145LEG-53-0021
53-12-00-250-804-L01 STR AD Special Detailed Inspection (Internal) of FUSELAGE 223/224 I: 8000 FC No L600
components by using Eddy Current Inspection Method: Tolerance
• Windshield center post, including its attachments and lower
and Post-Mod. S.B. 145LEG-53-0021 or with an
equivalent modification factory-incorporated
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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MAINTENANCE PROGRAM
PAGE : 99
ISSUE : 1
DATE : 05/07/2019
53-12-00-250-804-L02 STR AD Special Detailed Inspection (Internal) of FUSELAGE 223/224 T: 5000 FC I: L600
NOTE: Applicable to aircraft Post-Mod. S.B. 145LEG-00-0007
or with an equivalent modification factory-incorporated and
Pre-Mod. S.B. 145LEG-53-0021
53-12-00-250-804-L03 STR AD Special Detailed Inspection (Internal) of FUSELAGE 223/224 T:5000 FC I: ALL
and Post-Mod. S.B. 145LEG-53-0021 or with an equivalent
modification factory-incorporated

53-12-00-250-805-L00 STR AD Special Detailed Inspection (External) of FUSELAGE 223/224 T:7000 FC I: L600
component by using Eddy Current Inspection Method: 10000 FC No
• Windshield lateral post and its attachment (SSI 53-10-20). Tolerance
NOTE: Applicable to aircraft Pre-Mod. S.B.145LEG-00-0007
and Pre-Mod. S.B. 145LEG-53-0030.
53-12-00-250-806-L00 STR AD Special Detailed Inspection (External) of FUSELAGE 223/224 T:6000 FC I: ALL
component by using Eddy Current Inspection Method: 6212 FC
• Windshield lateral post and its attachment (SSI 53-10-20). No Tolerance
NOTE: Applicable to aircraft Post-Mod. S.B.145LEG-00-0007 or
with an equivalent modification factory-incorporated and
Pre-Mod. S.B.145LEG-53-0030.
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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PAGE : 100
ISSUE : 1
DATE : 05/07/2019
53-12-00-250-807-L00 STR AD Special Detailed Inspection (Internal) of FUSELAGE 223/224 T:7000 FC I: L600
and Pre-Mod. S.B.145LEG-53-0030.
53-12-00-250-808-L00 STR AD Special Detailed Inspection (Internal) of FUSELAGE 223/224 T:6000 FC I: ALL
Pre-Mod. S.B.145LEG-53-0030.
53-12-00-250-809-L00 STR AD Special Detailed Inspection (External) of FUSELAGE 223/224 T:6915 FC I: L600
and Post-Mod. S.B.145LEG-53-0030 or with an
equivalent modification factory-incorporated.

53-12-00-250-810-L00 STR AD Special Detailed Inspection (External) of FUSELAGE 223/224 T:4170 FC I: ALL
Post-Mod. S.B.145LEG-53-0030 or with an equivalent
modification factory-incorporated.
53-21-00-210-C01-L00 CPCP ED General Visual Inspection (External) of FUSELAGE 231 I: 48 MO ALL
• Main door attachments fittings and interface parts
(SSI 53-20-04)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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MAINTENANCE PROGRAM
PAGE : 101
ISSUE : 1
DATE : 05/07/2019
53-21-00-210-C02-L00 CPCP ED General Visual Inspection (Internal) of FUSELAGE 231 I: 96 MO ALL

• Main door attachments fittings and interface parts
(SSI 53-20-04)
• Passenger cabin floor beams and columns (SSI 53-20-11)
• Passenger door cutout reinforcing structures (SSI 53-20-09) 233 or
96 MO
± 60 Days
53-21-00-220-802-L00 STR AD Detailed Inspection (External) of FUSELAGE components: 231 I: 2000 FC ALL
• Stops and backup structures for main door (SSI 53-20-01) or
48 MO
± 30 Days
53-21-00-220-803-L00 STR AD Detailed Inspection (Internal) of FUSELAGE components: 231 I: 4000 FC ALL
• Stops and backup structures for main door (SSI 53-20-01) or
NOTE: During this inspection, the CPCP basic task shall also be 48 MO
performed for this SSI ± 30 Days

• Fuselage skin panel at stringers, frames/ bulkheads, and 233/234 or
± 60 Days
• Frame 15 & 18 LHS splices at stringers 3L & 16L or
(SSI 53-20-12) 96 MO
performed for this SSI
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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MAINTENANCE PROGRAM
PAGE : 102
ISSUE : 1
DATE : 05/07/2019
53-21-00-220-806-L00 STR AD Detailed Inspection (Internal) of FUSELAGE components: 231/232 I: 8000 FC L600
• Passenger cabin window frame (SSI 53-20-06) or
NOTE: If installed in the Zone.
• Frame 15 & 18 LHS splices at stringers 3L & 16L or
(SSI 53-20-12) 96 MO
± 60 Days
53-21-00-220-808-L00 STR AD Detailed Inspection (External) of FUSELAGE components: 231/232 I: 2000 FC L600
NOTE: If installed in the Zone. 96 MO
± 60 Days
• Passenger door cutout reinforcing structures (SSI 53-20-09) 233 or
• Fuselage skin longitudinal splices at main door cutout or
(SSI 53-20-41) 96 MO

------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 103
ISSUE : 1
DATE : 05/07/2019
• Machined Shear Clip at frames 23, 33 and 35 (SSI 53-20-79) 231/232 or
96 MO
± 60 Days
53-21-00-220-814-L00 STR AD Detailed Inspection (Internal) of FUSELAGE components: 131/132 T: 10000 FC L600
• Fuselage skin longitudinal splice (SSI 53-20-08) 231/232 or
NOTE: During this inspection, the CPCP basic task shall also be 233/234 96 MO
performed for (SSI 53-20-08) I: 1500 FC
or
96 MO
± 60 Days
• Forward Auxiliary Fuel Tank Fitting, Doubler and Pin at frames or
23, 33 and 35 (SSI 53-20-82) 96 MO
± 60 Days
splices (SSI 53-20-07) 233/234 96 MO
NOTE: Do not remove the fuel tank ± 60 Days

53-21-02-640-001-A00 SYS 7 Lubricate Main Door Frame Rollers 231 I: 1000 FH ALL
or
12 MO
± 15 Days
53-22-00-210-801-L00 STR AD General Visual Inspection (External) of FUSELAGE 141/142 I: 4000 FC ALL
components: or
• Fuselage skin panel at stringers, frames/ bulkheads, and 96 MO
splices (SSI 53-20-07) ± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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MAINTENANCE PROGRAM
PAGE : 104
ISSUE : 1
DATE : 05/07/2019
components: or
components: 241/242 or
• Machined Shear Clip at frames 23, 33 and 35 (SSI 53-20-79) 96 MO
• Machined Shear Clip at frames 25 and 31 (SSI 53-20-80) ± 60 Days
components: or
53-22-00-210-805-L00 STR AD General Visual Inspection (Internal) of FUSELAGE 197 I: 4000 FC ALL
components: or
• Forward Auxiliary Fuel Tank (SSI 53-20-81) 96 MO
± 60 Days
53-22-00-210-806-L00 STR AD General Visual Inspection (External) of FUSELAGE 197 I: 4000 FC ALL
components: or
• Forward Auxiliary Fuel Tank (SSI 53-20-81) 96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 105
ISSUE : 1
DATE : 05/07/2019

• Passenger cabin floor beams and columns ± 60 Days
(SSI 53-20-11)
splices (SSI 53-20-07) 243/244 96 MO
• Fuselage skin circumferential splice (SSI 53-20-14) ± 60 Days
• Frames (SSI 53-20-43)
96 MO
± 60 Days
• Forward Auxiliary Fuel Tank Fitting, Doubler and Pin at frames or
23, 33 and 35 (SSI 53-20-82) 96 MO
• Forward Auxiliary Fuel Tank Fitting, Doubler and Pin at frames ± 60 Days
25 and 31 (SSI 53-20-83)
96 MO
± 60 Days
• Machined Shear Clip at frames 23, 33 and 35 (SSI 53-20-79) or
96 MO
± 60 Days
• Passenger cabin window frame (SSI 53-20-06)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 106
ISSUE : 1
DATE : 05/07/2019

components: or
• Overwing fuselage skin panel (SSI 53-20-16) 96 MO
components: or
• Overwing fuselage skin panel (SSI 53-20-16) 96 MO
± 60 Days
• Fuselage skin panel at stringers, frames/bulkheads, and 153/154 ± 30 Days
53-23-00-220-C04-L00 CPCP ED Detailed Inspection (External) of FUSELAGE components: 151/152 I: 48 MO L600
• Fuselage skin panel at stringers, frames/bulk heads, and 153/154 ± 30 Days
• Fuselage machined bulkhead (SSI 53-20-30) 153/154 Tolerance
NOTE: During this inspection, the CPCP basic task shall also be 253/254
performed for zones 151/152 and 153/154
± 60 Days
• Skin and reinforcement around escape hatch cutout or
(SSI 53-20-51) 96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 107
ISSUE : 1
DATE : 05/07/2019

• Frames (SSI 53-20-43) or
96 MO
± 60 Days
53-23-00-220-805-L00 STR AD Detailed Inspection (Internal) of FUSELAGE components: 151/152 I: 4000 FC or ALL
• Frames (SSI 53-20-43) 153/154 96 MO
± 60 Days
• Fuselage machined bulkhead (SSI 53-20-30) or
• Frames (SSI 53-20-43) 96 MO
• Skin and reinforcement around escape hatch cutout ± 60 Days
(SSI 53-20-51)
• Fuselage skin panel at stringers, frames/ bulkheads, and
NOTE: During this inspection, the CPCP basic task shall also be
performed for (SSI 53-20-30)
NOTE: Applicable to aircraft Pre-Mod. S.B. 145LEG-00-0007 ± 60 Days
NOTE: Applicable to aircraft Post-Mod. S.B. 145LEG-00-0007 ± 60 Days
or with an equivalent modification factory-incorporated.
NOTE: Applicable to aircraft Pre-Mod. S.B. 145LEG-00-0007 ± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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MAINTENANCE PROGRAM
PAGE : 108
ISSUE : 1
DATE : 05/07/2019

• Passenger cabin floor beams and columns (SSI 53-20-11) 153/154 or
NOTE: Applicable to aircraft Pre-Mod. S.B. 145LEG-00-0007. 96 MO
± 60 Days
• Passenger cabin floor beams and columns (SSI 53-20-11) 153/154 or
NOTE: Applicable to aircraft Post-Mod. S.B. 145LEG-00-0007 96 MO
or with an equivalent modification factory-incorporated. ± 60 Days
53-23-00-250-801-L00 STR AD Special Detailed Inspection (External) of FUSELAGE compo- 251/252 T: 10000 FC I: L600
nent by using Eddy Current High Frequency Inspection Method: 3999 FC
• Passenger cabin window frame (SSI 53-20-06) No Tolerance
• Passenger cabin window frame (SSI 53-20-06)
• Passenger cabin floor beams and columns (SSI 53-20-11) ± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 109
ISSUE : 1
DATE : 05/07/2019

splices (SSI 53-20-07).
or with an equivalent modification factory-incorporated
± 60 Days
263/264 96 MO
± 60 Days
53-24-00-220-803-L00 STR AD Detailed Inspection (Internal) of FUSELAGE components: 161/162 T: 8000 FC L600
• Fuselage skin circumferential splice (SSI 53-20-14) 261/262 or
• Frames (SSI 53-20-43) 263/264 96 MO
I: 3370 FC
or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 110
ISSUE : 1
DATE : 05/07/2019

53-24-00-220-805-L00 STR AD Detailed Inspection (External) of FUSELAGE components: 161/162 T: 8000 FC L600
splices (SSI 53-20-07) 263/264 48 MO
I: 2000 FC
or
48 MO
± 30 Days
components: 271/272 or
• Rear auxiliary fuel tank fitting at attachments (SSI 53-30-56) 273/274 96 MO
± 60 Days

53-31-00-210-802-L00 STR AD General Visual Inspection (Internal) of FUSELAGE 271 I: 4000 FC No ALL
components: Tolerance
• Baggage door lateral L-shape (SSI 53-30-03)
components: or
• Baggage door cutout structure (SSI 53-30-48) 96 MO
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 111
ISSUE : 1
DATE : 05/07/2019
53-31-00-210-804-L00 STR AD General Visual Inspection (Internal) of FUSELAGE 272 I: 8000 FC L600
components: or
• Rear electronic compartment door cutout structure 96 MO
(SSI 53-30-49) ± 60 Days
performed for this SSI.
53-31-00-210-804-L01 STR AD General Visual Inspection (Internal) of FUSELAGE compo- 272 T: 8000 FC L600
nents: or
• Rear electronic compartment door cutout structure 96 MO
(SSI 53-30-49) I: 4000 FC
NOTE: During this inspection, the CPCP basic task shall also be or
performed for this SSI. 96 MO
NOTE: Applicable to aircraft Post-Mod. S.B. 145LEG-00-0007 ± 60 Days
or with an equivalent modification factory-incorporated
53-31-00-210-807-L00 DELETED

53-31-00-210-811-L00 STR FD General Visual Inspection (Internal) of FUSELAGE compo- 171/172 T: 10000 FC ALL
nents: 271/272 or
• Fuselage skin panel at stringers, frames/bulkheads, and 273/274 96 MO
splices (SSI 53-30-07). I: 4000 FC
• Fuselage skin panel at pressure bulkhead (53-30- 15). or
• Fuselage machined bulkhead (53-30-30). 96 MO
• Frames (53-30-43). ± 60 Days
• Toilet waste drain valve support (SSI 53-30-29) ± 30 Days
• Frames (SSI 53-30-43)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 112
ISSUE : 1
DATE : 05/07/2019

• Fuselage skin panel at stringers, frames/bulk heads, and ± 30 Days
53-31-00-220-C03-L00 CPCP ED Detailed Inspection (External) of FUSELAGE components: 171/172 I: 48 MO ALL
• Fuselage skin panel at pressure bulkhead ± 30 Days
(SSI 53-30-15)
53-31-00-220-C04-L00 CPCP ED Detailed Inspection (External) of FUSELAGE components: 171/172 I: 48 MO ALL
• Toilet waste drain valve support (SSI 53-30-29) ± 30 Days
• Frames (SSI 53-30-43) 273/274 ± 60 Days
• Baggage compartment floor beams and columns or
(SSI 53-30-28) 96 MO
± 60 Days
• Frame Reinforcement - Machined Shear Clip (SSI 53-30-55) or
96 MO
± 60 Days

53-31-00-220-804-L00 DELETED
• Frame Reinforcement - Machined Shear Clip (SSI 53-30-55) or
96 MO
± 60 Days
• Fuselage skin panel at pressure bulkhead (SSI 53-30-15) or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 113
ISSUE : 1
DATE : 05/07/2019
53-31-00-220-807-L00 STR ad Detailed Inspection (Internal) of FUSELAGE components: 171/172 I: 4000 FC ALL
• Fuselage skin circumferential splice (SSI 53-30-14) 273/274 96 MO
± 60 Days
• Baggage door cutout structure (SSI 53-30-48) or
96 MO
± 60 Days
53-31-00-220-809-L00 STR AD Detailed Inspection (External) of FUSELAGE components: 272 T: 4000 FC L600
• Rear electronic compartment door cutout structure or
(SSI 53-30-49) 96 MO
I: 2000 FC
or
96 MO
± 60 Days
53-31-00-220-810-L00 STR FD Detailed Inspection (Internal) of FUSELAGE components: 271/272 T: 10000 FC L600
• Bulkhead-to-engine pylon attachment (SSI 53-30-35) or
performed for SSI 53-30-35 I: 4000 FC
or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 114
ISSUE : 1
DATE : 05/07/2019

53-31-00-220-811-L00 STR AD Detailed Inspection (External) of FUSELAGE components: 171/172 I: 4000 FC No ALL
• Fuselage machined bulkhead (SSI 53-30-30) 271/272 Tolerance
273/274
• Fuselage skin panel at pressure bulkhead (SSI 53-30-15) ± 60 Days
• Fuselage to vertical stabilizer spar attachment fitting
(SSI 53-30-38)
53-31-00-220-814-L00 DELETED
53-31-00-220-815-L00 DELETED
53-31-00-220-816-L00 DELETED
53-31-00-220-817-L00 DELETED
53-31-00-220-820-L00 STR FD Detailed Inspection (Internal) of FUSELAGE components: 275/276 T:10000 FC ALL
• Fuselage skin panel at stringers, frames/bulkheads and or
splices (SSI 53-30-36). 96 MO
I: 4000 FC
or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 115
ISSUE : 1
DATE : 05/07/2019

• Fuselage skin panel at stringers, frames/bulkheads, and 271/272 or
splices (SSI 53-30-07). 273/274 96 MO
• Fuselage skin panel at pressure bulkhead (SSI 53-30-15). ± 60 Days
• Fuselage machined bulkhead (SSI 53-30-30).
NOTE: Remove bumper plates, if installed
53-31-00-250-801-L00 STR AD Special Detailed Inspection (Internal) of FUSELAGE compo- 171/172 I: 10000 FC No ALL
nent by using Eddy Current High Frequency Inspection Method: Tolerance
• Toilet waste drain valve support (SSI 53-30-29)
or with an equivalent modification factory-incorporated.
53-31-00-250-802-L00 STR AD Special Detailed Inspection (External) of FUSELAGE compo- 271 T: 10000 FC I: ALL
nent by using Eddy Current Low Frequency Inspection Method: 2450 FC
• Baggage door cutout structure (SSI 53-30-48) No Tolerance
53-31-00-250-803-L00 STR AD Special Detailed Inspection (External) of FUSELAGE compo- 271 T: 10000 FC I: ALL
nent by using Eddy Current High Frequency Inspection Method: 2450 FC
• Baggage door cutout structure (SSI 53-30-48) No Tolerance
53-31-00-250-804-L00 STR FD Special Detailed Inspection (External) of FUSELAGE skin at 273/274 I: 2907 FC No ALL
frames 61, 62, and 63, by using the high frequency eddy current Tolerance
method:
• Fuselage skin panel at stringers, frames/bulkheads,and
splices: (SSI 53-30-07)
53-31-00-250-805-L00 STR FD Special Detailed Inspection (Internal) aft side of the rear 275/276 T:10000 FC I: ALL
pressure bulkhead, by using the high frequency eddy current 3105 FC No
method. tolerance
• Rear Pressure Bulkhead. (SSI 53-30-36)
53-31-00-250-806-L00 STR FD Special Detailed Inspection (External) of FUSELAGE 273/274 T: 10000 FC I: ALL
component by using high frequency eddy current method.: 2907 FC
• SSI 53-30-15 (fuselage skin panel at pressure bulkhead) No Tolerance
• SSI 53-30-30 (fuselage machined bulkhead)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 116
ISSUE : 1
DATE : 05/07/2019

53-31-00-270-801-L00 DELETED
53-31-00-270-803-L00 DELETED
53-31-00-270-804-L00 DELETED
53-31-00-270-806-L00 DELETED
53-31-00-270-807-L00 DELETED
53-31-00-270-809-L00 DELETED
53-31-00-270-810-L00 DELETED
53-31-00-270-811-L00 DELETED
53-31-00-270-812-L00 DELETED
53-31-00-270-813-L00 DELETED
53-31-00-270-814-L00 DELETED
53-31-00-270-815-L00 DELETED

components: 48 MO
53-32-00-210-C02-L00 CPCP ED General Visual Inspection (Internal) of FUSELAGE 311/312 T: 96 MO I: ALL
components: 48 MO
• Fuselage skin longitudinal splice (SSI 53-30-08)
• Fuselage skin circumferential splice (SSI 53-30-14)
• Tail cone frame at APU mounting attachment (SSI 53-30-39)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 117
ISSUE : 1
DATE : 05/07/2019

components: or
• APU mounting (SSI 53-30-40) 96 MO
± 60 Days
53-32-00-210-802-L00 STR AD General Visual Inspection (External) of FUSELAGE 312 I: 4000 FC ALL
components: or
• Tail cone access door cutout structure (SSI 53-30-50) 96 MO
± 60 Days
• Rear pressure bulkhead (SSI 53-30-36) ± 30 Days
53-32-00-220-C02-L00 CPCP ED Detailed Inspection (Internal) of FUSELAGE components: 311/312 T: 96 MO I: ALL
• Frames (SSI 53-30-43) 48 MO
± 30 Days
• Fuselage to vertical stabilizer spar attachment fitting Tolerance
(SSI 53-30-38)
• Fuselage machined bulkhead (SSI 53-30-30) Tolerance
• L Profile Strake Attachment (SSI 53-30-53) 317/318 or
96 MO
± 60 Days
• Tail cone access door cutout structure (SSI 53-30-50) or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 118
ISSUE : 1
DATE : 05/07/2019
CHAPTER 54 - NACELE/PYLONS


± 30 Days
± 30 Days
54-50-00-210-801-L00 STR AD General Visual Inspection (External) of PYLON components: 414/424 I: 2000 FC ALL
• Pylon Skin (SSI 54-50-04) or
48 MO
± 30 Days
54-50-00-220-C01-L00 CPCP ED Detailed Inspection (Internal) of PYLON components: 414/424 I: 48 MO ALL
• Pylon yokes III and IV (SSI 54-50-02) ± 30 Days
• Pylon yokes I and II (SSI 54-50-05) ± 30 Days
• Pylon yokes I and II upper flange (SSI 54-50-06). ± 30 Days
54-50-00-220-802-L00 STR AD Detailed Inspection (Internal) of PYLON component: 414/424 I: 1000 FC L600
• FWD engine mounts (including bolts) (SSI 54-50-03) or
48 MO
± 30 Days
54-50-00-220-803-L00 STR AD Detailed Inspection (Internal) of PYLON components: 414/424 I: 2000 FC L600
• Pylon spars I, II, III and IV (SSI 54-50-01) or
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 119
ISSUE : 1
DATE : 05/07/2019
CHAPTER 54 - NACELE/PYLONS (CONTINUED)

54-50-00-220-806-L00 STR AD Detailed Inspection (Internal) of PYLON component: 414/424 I: 1000 FC or L600
• AFT engine mounts (including bolts) (SSI 54-50-07) 48 MO
± 30 Days
54-50-00-220-808-L00 STR AD Detailed Inspection (Internal) of PYLON component: 414/424 I: 4713 FC ALL
• Pylon yokes I and II (SSI 54-50-05) primary element. No Tolerance
54-50-00-220-809-L00 STR AD Detailed Inspection (Internal) of PYLON component: 414/424 T: 10000 FC ALL
• Pylon yokes I and II (SSI 54-50-05) secondary element. I: 1130 FC
No Tolerance
54-50-00-250-801-L00 STR AD Special Detailed Inspection (Internal) of PYLON components by 414/424 I: 10000 FC ALL
the Eddy Current method: No Tolerance
• Pylon yokes I and II (SSI 54-50-05)
CHAPTER 54 - NACELE/PYLONS (CONTINUED)

54-50-00-250-802-L00 STR AD Special Detailed Inspection (Internal) of PYLON components by 414/424 I: 3660 FC ALL
• Pylon yokes I and II upper flange (SSI 54-50-06)
NOTE: Applicable to aircraft Pre-Mod SB 145LEG-54-0001
54-50-00-250-802-L01 STR FD Special Detailed Inspection (Internal) of PYLON components by 414/424 I: 5360 FC ALL
• Pylon yokes I and II upper flange (SSI 54-50-06)
NOTE: Applicable to aircraft Post-Mod SB 145LEG-54-0001 or
with an equivalent modification factory-incorporated.
54-50-00-290-801-L00 STR AD Special Detailed Inspection (Internal) of PYLON component 414/424 I: 2000 FC ALL
using boroscope: or
• Pylon Skin (SSI 54-50-04) 48 MO
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ISSUE : 1
DATE : 05/07/2019
CHAPTER 55 - STABILIZERS

55-Z321-213-001-A00 ZNL - General Visual Inspection (External) 321/322/ I: 48 MO ALL

323 ± 30 Days
323/337 ± 30 Days
± 30 Days
± 30 Days
CHAPTER 55 - STABILIZERS (CONTINUED)


± 30 Days
± 30 Days
333/334 ± 30 Days
333/334 ± 30 Days
± 30 Days
± 30 Days
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DATE : 05/07/2019
55-10-00-210-C01-L00 CPCP ED General Visual Inspection (External) of HORIZONTAL 337 I: 48 MO ALL

STABILIZER components: ± 30 Days
• U shape, L shape and box structure - elevator command
(SSI 55-10-22)
55-10-00-210-C02-L00 CPCP ED General Visual Inspection (External) of HORIZONTAL 337 T: 96 MO ALL
STABILIZER components: I: 48 MO
• Support quadrant assy, stabilizer (SSI 55-10-23) ± 30 Days
55-10-00-210-802-L00 STR AD General Visual Inspection (External) of HORIZONTAL 333/334 I: 4000 FC ALL
STABILIZER components: or
• Skin, from rib sta. YH=350 to rib sta. YH=990 - upper surface 96 MO
(SSI 55-10-07) ± 60 Days
55-10-00-210-805-L00 STR AD General Visual Inspection (External) of HORIZONTAL 337 I: 4000 FC ALL
STABILIZER components: No Tolerance
• Support pulley central stabilizer (SSI 55-10-14)

55-10-00-220-C01-L00 CPCP ED Detailed Inspection (Internal) of HORIZONTAL STABILIZER 333/334 I: 48 MO ALL

• Front spar web and cap, from fin to rib sta. YH=350, including
center fitting/ spar attachment (SSI 55-10-09)
• 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)
55-10-00-220-C02-L00 CPCP ED Detailed Inspection (External) of HORIZONTAL STABILIZER 333/334 I: 48 MO ALL
• Skin, from rib sta. YH=990 to rib sta. YH=2965- lower surface
(SSI 55-10-08)
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DATE : 05/07/2019
55-10-00-220-C03-L00 CPCP ED Detailed Inspection (Internal) of HORIZONTAL STABILIZER 337 I: 48 MO ALL

• Pin, internal and external hinge, stabilizer (SSI 55-10-24)
55-10-00-220-801-L00 STR AD Detailed Inspection (External) of HORIZONTAL STABILIZER 333/334 I: 4000 FC ALL
components: or
• Elevator support fittings (SSI 55-10-15) 48 MO
± 30 Days
55-10-00-220-802-L00 STR AD Detailed Inspection (External) of HORIZONTAL STABILIZER 337 I: 4000 FC ALL
components: or
• Fitting hinge support stabilizer (SSI 55-10-21) 96 MO
± 60 Days
55-10-00-220-803-L00 STR AD Detailed Inspection (Internal) of HORIZONTAL STABILIZER 333/334 I: 4000 FC ALL
component: or
• Rear spar web and cap, from fin to rib sta. YH=350, including 96 MO
center fitting/spar attachment (SSI 55-10-12) ± 60 Days
55-10-00-220-804-L00 STR AD Detailed Inspection (Internal) of HORIZONTAL STABILIZER 337 T: 8000 FC ALL
components: or
• Root rib (SSI 55-10-17) 96 MO
I: 3650 FC
or
96 MO
± 60 Days

55-10-00-220-805-L00 STR AD Detailed Inspection (External) of HORIZONTAL STABILIZER 333/334 T: 4000 FC L600
components: or
• Skin, from fin to sta. YH=350 - lower surface (SSI 55-10-06) 96 MO
• Skin, from fin to sta. YH=350 - upper surface (SSI 55-10-01) I: 2000 FC
or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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DATE : 05/07/2019
55-10-00-220-806-L00 STR AD Detailed Inspection (Internal) of HORIZONTAL STABILIZER 337 T: 4000 FC I: L600
components: 2000 FC
• Skin splice at upper and lower surface (SSI 55-10-16) No Tolerance
• Front/ Rear auxiliary spar center fitting (SSI 55-10-19)
• Rear spar center fitting (SSI 55-10-18)
• Front spar center fittings (SSI 55-10-20)
55-10-00-220-808-L00 STR AD Detailed Inspection (External) of HORIZONTAL STABILIZER 333/334 T: 4000 FC L600
components: or
• Skin, from rib sta YH=350 to rib YH=990 - upper surface 96 MO
(SSI 55-10-02) I: 2000 FC
or
96 MO
± 60 Days
55-10-00-220-809-L00 STR AD Detailed Inspection (Internal) of HORIZONTAL STABILIZER 333/334 T: 3900 FC I: L600
components: 2000 FC
• Front and rear auxiliary spar webs and caps, including center No Tolerance
fitting/spar attachment (SSI 55-10-11)
55-10-00-220-810-L00 STR AD Detailed Inspection (External) of HORIZONTAL STABILIZER 333/334 I: 2000 FC ALL
components: or
• Skin, from rib sta. YH=990 to rib sta. YH=2965- upper surface 96 MO
(SSI 55-10-03) ± 60 Days

55-10-00-220-811-L00 STR AD Detailed Inspection (Internal) of HORIZONTAL STABILIZER 333/334 T: 8000 FC ALL
components: or
• Ribs, from rib sta. YH=30 to rib sta. YH=990 (SSI 55-10-04) 96 MO
• Ribs, from rib sta. YH=990 to rib sta. YH=2965 (SSI 55-10-05) I: 2000 FC
or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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DATE : 05/07/2019
55-10-00-220-812-L00 STR AD Detailed Inspection (Internal) of HORIZONTAL STABILIZER 333/334 T: 2600 FC L600
components: or
• Front spar web and cap, from rib sta. YH=350 to rib sta. 96 MO
YH=2965 (SSI 55-10-10) I: 1370 FC
or
96 MO
± 60 Days
55-10-00-220-813-L00 STR AD Detailed Inspection (Internal) of HORIZONTAL STABILIZER 333/334 T: 4000 FC or L600
components: 48 MO
• Front spar web and cap, from fin to rib sta. YH=350, including I: 1000 FC
center fitting/spar attachment (SSI 55-10-09) or
48 MO
± 30 Days

55-10-00-240-801-L00 STR AD Special Detailed Inspection (External) of HORIZONTAL 337 I: 10000 FC No ALL
STABILIZER components by the magnetic particle inspection Tolerance
method:
• Pin, internal and external hinge, STABILIZER (SSI 55-10-24)
55-10-00-250-805-L00 STR AD Special Detailed Inspection (External) of HORIZONTAL 333/334 T: 4680 FC I: L600
STABILIZER components by the eddy current inspection 3130 FC
method: No Tolerance
• Skin, from fin to sta. YH=350 - upper surface (SSI 55-10-01)
55-10-00-250-806-L00 STR AD Special Detailed Inspection (External) of HORIZONTAL 333/334 I: 4000 FC No L600
STABILIZER components by the eddy current inspection Tolerance
method:
• Skin, from rib to sta. YH=350 to rib YH=990 - upper surface
(SSI 55-10-02)
STABILIZER components by the eddy current inspection 3130 FC
method: No Tolerance
• Skin, from fin to sta. YH=350 - lower surface (SSI 55-10-06)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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ISSUE : 1
DATE : 05/07/2019

55-10-00-250-808-L00 STR AD Special Detailed Inspection (External) of HORIZONTAL 333/334 T: 4900FC I: L600
STABILIZER components by using Eddy Current Low 1130 FC
Frequency Inspection Method: No Tolerance
• Front spar web and cap, from fin to rib sta. YH=350, including
center fitting/spar attachment (SSI 55-10-09)
STABILIZER components by using Eddy Current Low 1130 FC
• Front and rear auxiliary spar webs and caps, including center
fitting/spar attachment (SSI 55-10-11)
STABILIZER components by using Eddy Current Low 1130FC
• Rear spar web and cap, from fin to rib sta. YH=350, including
center fitting/spar attachment (SSI 55-10-12)
55-20-00-210-C01-L00 CPCP ED General Visual Inspection (External) of ELEVATOR 335/336 T: 96 MO I: ALL

components: 48 MO
• Skin, between root and sta. YH=160 (SSI 55-20-26) ± 30 Days
• Skin, between sta. YH=160 and sta. YH=3320 (SSI 55-20-28)
55-20-00-210-C02-L00 CPCP ED General Visual Inspection (Internal) of ELEVATOR 335/336 I: 96 MO ALL
• Spars between root and sta. YH=160 (SSI 55-20-25)
• Spars, between sta. YH=160 and sta. YH=3320
(SSI 55-20-27)
55-20-00-210-C03-L00 CPCP ED General Visual Inspection (External) of ELEVATOR 335/336 I: 48 MO ALL
• Tab (SSI 55-20-37)
55-20-00-210-801-L00 STR AD General Visual Inspection (Internal) of ELEVATOR 335/336 I: 1000 FC ALL
components: or
• Elevator horn mass balance weights and attachments 48 MO
(SSI 55-20-90) ± 30 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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MAINTENANCE PROGRAM
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ISSUE : 1
DATE : 05/07/2019

55-20-00-220-C01-L00 CPCP ED Detailed Inspection (Internal) of ELEVATOR components: 335/336 I: 96 MO ALL

• Ribs, between root and sta. YH=160 (SSI 55-20-29) ± 60 Days
• Ribs, between sta. YH=160 and sta. YH=983.4 (SSI 55-20-30)
• Ribs, between sta. YH=3001 and sta. YH=3320
(SSI 55-20-33)
55-20-00-220-801-L00 STR AD Detailed Inspection (Internal) of ELEVATOR components: 335/336 I: 4000 FC ALL
• Torque tube fittings (SSI 55-20-34) or
• Tab wheel drive support fittings (SSI 55-20-35) 96 MO
±60 Days
55-20-00-220-802-L00 STR AD Detailed Inspection (External) of ELEVATOR components: 335/336 I: 4000 FC ALL
• Tab Hinge Fittings (SSI 55-20-36) or
96 MO
±60 Days
55-20-00-290-C01-L00 CPCP ED Detailed Inspection (Internal) of ELEVATOR components using 335/336 I: 48 MO ALL
a boroscope: ± 30 Days
• Ribs, between sta. YH=983,4 and sta. YH=1898
(SSI 55-20-31)
• Ribs, between sta. YH=1898 and sta. YH=3001
(SSI 55-20-32)
55-30-00-210-C01-L00 CPCP ED General Visual Inspection (External) of VERTICAL 324 T: 96 MO I: ALL

STABILIZER components: 48 MO
• Skin at windows from fuselage to sta. ZV=1169 (SSI 55-30-44) ± 30 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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MAINTENANCE PROGRAM
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ISSUE : 1
DATE : 05/07/2019

55-30-00-210-C02-L00 CPCP ED General Visual Inspection (External) of VERTICAL 325 I: 48 MO ALL

STABILIZER components: ± 30 Days
• Skin at spar 3, auxiliary spar 52%, and stringers 46.5% &
57.65%, between fuselage & rib sta. ZV=1169 (SSI 55-30-39)
57.65%, between ribs sta. ZV=1169 & sta. ZV=2799
(SSI 55-30-41)
57.65%, between rib sta. ZV=2799 & horizontal stabilizer
(SSI 55-30-43)
• Skin at windows between sta. ZV=1169 & sta. ZV=2799
(SSI 55-30-45)
• Skin at ribs, between sta. ZV=1169 and sta. ZV=2799
(SSI 55-30-48)
• Skin at ribs, between sta. ZV=2799 and horizontal stabilizer
(SSI 55-30-49)

• Skin at ribs from fuselage to sta. ZV=1169 (SSI 55-30-47) ± 30 Days
55-30-00-210-C04-L00 CPCP ED General Visual Inspection (Internal) of VERTICAL STABILIZER 325 T: 96 MO I: ALL
components: 48 MO
• Ribs (sta. ZV=3461, ZV=2538, ZV=1677, ZV=1550.5, ± 30 Days
ZV=1430.5, ZV=1423, ZV=1302, ZV=1169 and ZV=915)
(SSI 55-30-73)
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DATE : 05/07/2019


• Skin at spars 1, 2, auxiliary spar 41% and stringers 20% & ± 30 Days
35.5% between fuselage & rib sta. ZV=1169 (SSI 55-30-38)
• Skin at spars 1, 2, auxiliary spar 41% and stringers 20% &
35.5% between ribs sta. ZV=1169 & sta. ZV=2799
(SSI 55-30-40)
• Skin at spars 1, 2, auxiliary spar 41% and stringers 20% &
35.5% between rib sta. ZV=2799 & horizontal stabilizer
(SSI 55-30-42)
• Skin at windows between sta. ZV=2799 and horizontal
stabilizer (SSI 55-30-46)
55-30-00-210-802-L00 STR AD General Visual Inspection (Internal) of VERTICAL STABILIZER 324 I: 4000 FC L600
components: or
• Spar 2 (web and cap), from fuselage contour line to tip rib sta. 96 MO
ZV=3015 (SSI 55-30-67) ±60 Days
• Spar 1 (web and cap), from fuselage contour line to tip rib
(SSI 55-30-68)
55-30-00-210-804-L00 DELETED
55-30-00-220-C01-L00 CPCP ED Detailed Inspection (Internal) of VERTICAL STABILIZER 325 T: 96 MO I: ALL
components: 48 MO
• Root rib, including bolts (SSI 55-30-70) ± 30 Days
• Ribs of actuator area (sta. ZV=1932 and ZV=2277)
(SSI 55-30-72)
55-30-00-220-C02-L00 CPCP ED Detailed Inspection (Internal) of VERTICAL STABILIZER 325 I: 96 MO ALL
• Ribs of horizontal stabilizer actuators (sta. ZV=3145, ZV=3015
and ZV=2799) (SSI 55-30-71)
• Rear spar actuator support fitting (elevator) (SSI 55-30-77)
• Spar 1 - tip rib attachment (SSI 55-30-53)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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ISSUE : 1
DATE : 05/07/2019

55-30-00-220-C04-L00 CPCP ED Detailed Inspection (External) of VERTICAL STABILIZER 325 I: 48 MO ALL

• Rudder hinge fittings (SSI 55-30-78)
• Fin-to-horizontal stabilizer attachment fitting to spar 3
(SSI 55-30-50)
• Fin-to-horizontal stabilizer
attachment fitting to auxiliary spar 52% (SSI 55-30-51)
• Fin-to-horizontal stabilizer
attachment fitting to auxiliary spar 41% (SSI 55-30-52)
55-30-00-220-801-L00 STR AD Detailed Inspection (Internal) of VERTICAL STABILIZER 325 I: 4000 FC ALL
components: or
• Tip rib (SSI 55-30-69) 96 MO
±60 Days
55-30-00-220-802-L00 STR AD Detailed Inspection (Internal) of VERTICAL STABILIZER 324 I: 8000 FC L600
components: or
• Fin-to-fuselage attachment fitting to spar 1 (SSI 55-30-58) 96 MO
• Fin-to-fuselage attachment fitting to bulkhead 77 ±60 Days
(SSI 55-30-59)
55-30-00-220-804-L00 STR AD Detailed Inspection (Internal) of VERTICAL STABILIZER 324/325 I: 4000 FC L600
components: or
• Fitting hinge support (SSI 55-30-76) 96 MO
±60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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MAINTENANCE PROGRAM
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ISSUE : 1
DATE : 05/07/2019

components: or
• Fin-to-fuselage attachment fitting to spar 3 (SSI 55-30-54) 96 MO
• Fin-to-fuselage attachment fitting to bulkhead 78 ±60 Days
(SSI 55-30-60)
• Fin-to-fuselage attachment fitting to bulkhead 79
(SSI 55-30-61)
• Fin-to-fuselage attachment fitting to bulkhead 80
(SSI 55-30-62)
• Spar 41% (web and cap), from sta. ZV=1550.5, including
attachment bolts (SSI 55-30-66)
components: No Tolerance
• Fin-to-fuselage attachment fitting to auxiliary spar 52%
(SSI 55-30-55)
• Fin-to-fuselage attachment fitting to auxiliary spar 41%
(SSI 55-30-56)
• Spar 3 (web and cap), from
fuselage contour line to tip rib, including attachment bolts
(SSI 55-30-63)
• Spar 52% (web and cap), from fuselage contour line to tip rib,
including attachment bolts (SSI 55-30-64)
• Spar 41% (web and cap), from sta. ZV=2538 to tip rib,
including
attachment bolts (SSI 55-30-65)
• Fin-to-horizontal stabilizer support actuators, including bolt
(SSI 55-30-75)
• Actuator support fittings (rudder) (SSI 55-30-79)
• PCU support fittings (SSI 55-30-80)
components: No Tolerance
• Fin-to-fuselage attachment fitting to spar 2 (SSI 55-30-57)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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PAGE : 131
ISSUE : 1
DATE : 05/07/2019

55-30-00-250-801-L00 STR AD Special Detailed Inspection 325 I: 9000 FC ALL

(External) of VERTICAL STABILIZER components by the eddy No Tolerance
current inspection method:
• Fitting hinge support (SSI 55-30-76)
55-30-00-290-801-L00 STR AD Special Detailed Inspection (External) of VERTICAL 325 I: 4000 FC or ALL
STABILIZER components using boroscope 96 MO
• Trailing edge ribs (SSI 55-30-74). ±60 Days
55-40-00-210-C01-L00 CPCP ED General Visual Inspection (External) of RUDDER components: 326 I: 48 MO ALL
• Front spar - skin attachment (rudder I) (SSI 55-40-81) ± 30 Days
• Rear spar - skin attachment (rudder I) (SSI 55-40-82)
• LT & RT skin - spar cap attachment (rudder I) (SSI 55-40-83)
• Ribs - skin attachment (rudder I) (SSI 55-40-84)
• Hinges - rudder I (SSI 55-40-85)

55-40-00-210-C02-L00 CPCP ED General Visual Inspection (External) of RUDDER components: 327 I: 48 MO ALL
• Spar - skin attachment (rudder II) (SSI 55- 40- 86) ± 30 Days
• LT & RT skin - spar cap attachment (rudder II) (SSI 55-40-87)
• Ribs - skin attachment (rudder II) (SSI 55-40-88)
• Hinges - rudder II (SSI 55-40-89)
55-40-00-220-C01-L00 CPCP ED Detailed Inspection (Internal) of RUDDER components: 326 I: 48 MO ALL
• Front spar - skin attachment (rudder I) (SSI 55-40-81) ± 30 Days
• Rear spar - skin attachment (rudder I) (SSI 55-40-82)
• LT & RT skin - spar cap attachment (rudder I) (SSI 55-40-83)
• Ribs - skin attachment (rudder I) (SSI 55-40-84)
• Hinges - rudder I (SSI 55-40-85)
55-40-00-220-C02-L00 CPCP ED Detailed Inspection (Internal) of RUDDER components: 327 I: 48 MO ALL
• Spar - skin attachment (rudder II) (SSI 55-40-86) ± 30 Days
• LT & RT skin - spar cap attachment (rudder II) (SSI 55-40-87)
• Ribs - skin attachment (rudder II) (SSI 55-40-88)
• Hinges - rudder II (SSI 55-40-89)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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ISSUE : 1
DATE : 05/07/2019
CHAPTER 57 - WINGS


512/612 ± 30 Days
513/613
512/612 ± 30 Days
513/613
CHAPTER 57 - WINGS (CONTINUED)


± 30 Days
± 30 Days
± 30 Days
± 30 Days
± 30 Days
± 30 Days
651/661 ± 30 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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ISSUE : 1
DATE : 05/07/2019

651/661 ± 30 Days
5711/6711 ± 30 Days
5712/6712
5713/6713


5711/6711 ± 30 Days
5712/6712
5713/6713
5721/6721 ± 30 Days
5722/6722
5721/6721 ± 30 Days
5722/6722
5731/6731 ± 30 Days
5732/6732
5731/6731 ± 30 Days
5732/6732
57-01-00-220-C01-L00 CPCP ED Detailed Inspection (Internal) of WING STUB components: 155/156/ I: 96 MO ALL
• Wing stub - lower skin - rib 2A attachment (SSI 57-01-15) 157 ± 60 Days
• Wing stub - Spar 2 - brackets ribs 2A attachments
(SSI 57-01-17)
• Wing stub - spar 1 - brackets ribs 2A attachments
(SSI 57-01-16)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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MAINTENANCE PROGRAM
PAGE : 134
ISSUE : 1
DATE : 05/07/2019

• Wing stub - rib 2A skin supports and their attachments to web, 157 ± 30 Days
lower flange, and FWD & AFT web supports (SSI 57-01-18)
• Wing stub - upper skin - rib 2A attachments (SSI 57-01-19)
57-01-00-220-C03-L00 CPCP ED Detailed Inspection (External) of WING STUB components: 155/156/ I: 96 MO ALL
• Wing stub - lower skin - rib 2A attachment (SSI 57-01-15) 157 ± 60 Days
• Wing stub - upper skin - rib 2A attachments (SSI 57-01-19) 157 ± 30 Days
57-10-00-210-C01-L00 CPCP ED General Visual Inspection (External) of WING STUB 155/156/ I: 96 MO ALL
components: 157 ± 60 Days
• Upper skin - tire compartment composite panel (SSI 57-10-14)
57-10-00-210-801-L00 STR AD General Visual Inspection (External) of WING STUB 155/156/ I: 8000 FC ALL
components: 157 or
• Spar 2 - brackets and rib 2A web attachments (SSI 57-10-27) 96 MO
± 60 Days
• Spar 1 - brackets, ribs 1 and 3 attachments (SSI 57-10-04) 157 ± 30 Days
• Spar 2 - center brackets & rib 2 attachments and ribs 1 & 3 web
attachments (SSI 57-10-07)
57-10-00-220-C02-L00 CPCP ED Detailed Inspection (External) of WING STUB components: 155/ I: 48 MO ALL
• Upper skin - rib 1 attachments and spanwise splice of integral 156 ± 30 Days
panel (SSI 57-10-13) 157
57-10-00-220-C03-L00 CPCP ED Detailed Inspection (External) of WING STUB components: 155/ I: 48 MO ALL
• Rib 4 - lower flange and web (SSI 57-10-11) 156 ± 30 Days
157
• Spar 3 - lower skin attachments (SSI 57-10-09) 157 ± 30 Days
• Spar 3 - lower skin attachments (SSI 57-10-09) 157 ± 30 Days
• Upper skin - tire compartment composite panel (SSI 57-10-14)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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ISSUE : 1
DATE : 05/07/2019

• Upper skin - rib 1 attachments and spanwise splice of integral 157 ± 30 Days
panel (SSI 57-10-13)
• Rib 4 - lower flange and web (SSI 57-10-11) 157 ± 30 Days
• Rib 2 - Longitudinal stringer-to- web attachments
(SSI 57-10-12)
• Spar 3 - center bracket and rib 2 attachments (SSI 57-10-10) 157 ± 60 Days
57-10-00-220-801-L00 STR AD Detailed Inspection (External) of WING STUB components: 155/156/ I: 2000 FC ALL
• Spar 1 - auxiliary cap attachments & auxiliary cap splice at 157 or
wing attachments (SSI 57-10-05) 48 MO
• Lower skin - ribs 1, 2 & 3 ± 30 Days
attachments and tire compartment wall attachments
(SSI 57-10-02)
• Spar 1 - lower skin attachments (SSI 57-10-03)
performed for these SSIs
57-10-00-220-802-L00 STR AD Detailed Inspection (Internal) of WING STUB components: 155/156/ T: 3970 FC or L600
• Spar 2 - brackets and rib 2A web attachments (SSI 57-10-27) 157 48 MO
• Spar 1 - lower skin attachments (SSI 57-10-03) I: 2000 FC or
• Spar 1 - auxiliary cap attachments & auxiliary cap splice at 48 MO
wing attachments (SSI 57-10-05) ± 30 Days
57-10-00-220-803-L00 STR AD Detailed Inspection (Internal) of WING STUB components: 155/156/ I: 2000 FC ALL
• Lower skin - ribs 1, 2 & 3 attachments and tire compartment 157 or
wall attachments (SSI 57-10-02) 48 MO
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
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PAGE : 136
ISSUE : 1
DATE : 05/07/2019

57-10-00-220-804-L00 STR FD Detailed Inspection (External) of WING STUB components: 155/156/ T: 10000 FC L600
• Lower skin - Spanwise splice at spar 2, access holes, 157 or
stringers, integral milled panels & spanwise splice of integral 96 MO
panel (SSI 57-10-01) I: 2381 FC
• Spar 2 - Lower skin attachments (SSI 57-10-06) or
performed for this SSI’s ± 60 Days
57-10-00-220-805-L00 STR FD Detailed Inspection (Internal) of WING STUB components: 155/156/ T: 10000 FC L600
• Lower skin - Spanwise splice at spar 2, access holes, 157 or
stringers, integral milled panels & spanwise splice of integral 96 MO
panel (SSI 57-10-01) I: 2381 FC
• Spar 2 - Lower skin attachments (SSI 57-10-06) or
• Spar 2 - auxiliary cap attachments and auxiliary cap splice at 96 MO
wing attachments (SSI 57-10-08) ± 60 Days
performed for this SSI’s 57-10-06 and 57-10-08

57-10-00-250-803-L00 STR FD Special Detailed Inspection (Internal) of WING STUB 155/156/ T: 10000 FC I: L600
components by the Ultrasonic inspection method: 157 4000 FC
• Lower skin - spanwise splice at spar 2, access holes, stringers, No Tolerance
integral milled panels & spanwise splice of integral panel
(SSI 57-10-01)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 137
ISSUE : 1
DATE : 05/07/2019
57-11-00-220-801-L00 STR AD Detailed Inspection (External) of WING STUB components: 155/156/ I: 4000 FC ALL
• Lower skin - rear fitting-to-skin attachments and spars 1 & 2 - 157 or
stub-to-wing attachments (SSI 57-11-17) 96 MO
• Fuselage bulkhead at frame 50 and its attachments to frame ± 60 Days
50 (SSI 57-11-25)
performed for these SSIs
57-11-00-220-802-L00 STR AD Detailed Inspection (Internal) of WING STUB components: 155/156/ I: 8000 FC ALL
• Lower skin - rear fitting-to-skin attachments and spars 1 & 2 - 157 or
stub-to-wing attachments (SSI 57-11-17) 96 MO
• Fuselage bulkhead at frame 50 and its attachments to frame ± 60 Days
50 (SSI 57-11-25)

57-11-00-220-803-L00 STR AD Detailed Inspection (External) of WING STUB components: 155/156/ I: 4000 FC L600
• Spar 1 - lower front fitting attachments and spar 2 - lower rear 157 or
fitting attachments (SSI 57-11-18) 96 MO
• Spar 2 - Titanium fitting attachments and fuselage bulkhead at ± 60 Days
frame 46 (SSI 57-11-20)
• Spar 3 - Fuselage bulkhead attachments at frame 50, L- shape
fuselage frame 50 attachments & fuselage stringers
• Spar 1 - Titanium fitting
attachments, fuselage bulkhead attachments at frame 40,
L-shape fuselage frame 40 attachments & fuselage stringers
(SSI 57-11-19)
performed for SSIs 57-11-18 and 57-11-20
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 138
ISSUE : 1
DATE : 05/07/2019
57-11-00-220-805-L00 STR AD Detailed Inspection (Internal) of WING STUB components: 155/156/ I: 4000 FC No ALL
• Spar 1 - Titanium fitting attachments, fuselage bulkhead 157 Tolerance
attachments at frame 40, L shape fuselage frame 40
attachments & fuselage stringers attachments (SSI 57-11-19)
• Spar 3 - Fuselage bulkhead attachments at frame 50, shall
L- shape fuselage frame 50 attachments & fuselage stringers
57-11-00-220-806-L00 STR AD Detailed Inspection (Internal) of WING STUB components: 155/156 I: 4000 FC L600
• Spar 1 - lower front fitting attachments and spar 2 - lower rear 157 or
fitting attachments (SSI 57-11-18) 96 MO
• Spar 2 - Titanium fitting attachments and fuselage bulkhead at ± 60 Days
frame 46 (SSI 57-11-20)

57-11-00-220-807-L00 STR AD Detailed Inspection (External) of WING STUB components: 155/156/ T: 8000 FC L600
• Spar 3 and rib 4 - rod-end link (SSI 57-11-22) 157 or
• Fuselage bulkhead at frame 40 and its attachments to frame 96 MO
(SSI 57-11-23) I: 4000 FC
• Fuselage bulkhead attachment to frame 46 (SSI 57-11-24) or
performed for these SSIs ± 60 Days
57-11-00-220-808-L00 STR AD Detailed Inspection (Internal) of WING STUB components: 155/156/ T: 8000 FC I: L600
• Fuselage bulkhead at frame 40 and its attachments to frame 157 4000 FC
40 (SSI 57-11-23) No Tolerance
• Fuselage bulkhead attachment to frame 46 (SSI 57-11-24)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 139
ISSUE : 1
DATE : 05/07/2019

57-11-00-250-801-L00 STR AD Special Detailed Inspection (Internal) of WING STUB 155/156 I: 10000 FC No ALL
components by the Eddy Current Inspection method: 157 Tolerance
• Lower skin - rear fitting-to-skin attachments and spars 1 & 2 -
stub-to-wing attachments (SSI 57-11-17)
57-21-00-210-C01-L00 CPCP ED General Visual Inspection (External) of WING components: 541/641 T: 96 MO I: ALL
• Lower vent hole (SSI 57-21-33) 48 MO
• Gravity fuel hole (SSI 57-21-35) ± 30 Days
• Upper skin/ spar attachment (SSI 57-21-37) 551/651 48 MO
± 30 Days
57-21-00-210-C04-L00 CPCP ED General Visual Inspection (Internal) of WING components: 532/632 I: 48 MO ALL
• Upper skin panel spanwise joint (SSI 57-21-31) ± 30 Days
• Upper skin/ spar stub attachment (SSI 57-21-39) ± 30 Days
• Skin panels (SSI 57-21-26) 541/641 ± 60 Days
• Upper skin panel spanwise joint (SSI 57-21-31) 551/651
• Upper skin/ spar attachment (SSI 57-21-37)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 140
ISSUE : 1
DATE : 05/07/2019

• Lower skin access holes (SSI 57-21-32) 48 MO
± 30 Days
57-21-00-210-C10-L00 CPCP ED General Visual Inspection (External) of WING components: 531/631 I: 48 MO ALL
• Lower skin/ wing stub attachment (SSI 57-21-38) ± 30 Days
• Gravity fuel hole (SSI 57-21-35) ± 60 Days
• Upper skin/ wing stub attachment (SSI 57-21-39) ± 30 Days
57-21-00-210-C14-L00 CPCP ED General Visual Inspection (External) of WING components: 531/631 I: 48 MO L600
• Skin panels (SSI 57-21-26) 541/641 ± 30 Days
• Upper skin panel spanwise joint (SSI 57-21-31) 551/651
• Upper skin/ spar attachment (SSI 57-21-37) ± 30 Days
• Lower skin panel spanwise joint (SSI 57-21-30) 551/651 ± 60 Days
• Lower skin/wing stub attachment (SSI 57-21-38) ± 60 Days
• Lower skin panel spanwise joint (SSI 57-21-30) 551/651 ± 30 Days
57-21-00-210-801-L00 STR AD General Visual Inspection (External) of WING components: 531/631 I: 1000 FC ALL
• Lower skin/spar attachments (SSI 57-21-36) 532/632 or
541/641 96 MO
± 60 Days
57-21-00-210-806-L00 STR AD General Visual Inspection (Internal) of WING components: 532/632 I: 1000 FC L600
• Upper skin/spar attachment (SSI 57-21-37) or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 141
ISSUE : 1
DATE : 05/07/2019

57-21-00-210-809-L00 STR AD General Visual Inspection (Internal) of WING components: 532/632 I: 4000 FC or ALL
• Lower skin access holes (SSI 57-21-32) 96 MO
± 60 Days
57-21-00-210-812-L00 STR AD General Visual Inspection (External) of WING components: 532/632 I: 1000 FC or ALL
• Lower skin panel spanwise joint (SSI 57-21-30) 96 MO
• Upper skin panel spanwise joint (SSI 57-21-31) ± 60 Days
• Upper skin/spar attachment (SSI 57-21-37)
• Lower skin panel chordwise joint (SSI 57-21-29) 96 MO
• Lower skin panel spanwise joint (SSI 57-21-30) ± 60 Days
• Lower skin access holes (SSI 57-21-32) 541/641 96 MO
± 60 Days
• Lower skin panel spanwise joint (SSI 57-21-30) 96 MO
• Lower Skin panel chordwise joint (SSI 57-21-29) 96 MO
• Lower skin/ spar attachments (SSI 57-21-36) 96 MO
± 60 Days
57-21-00-210-822-L00 STR AD General Visual Inspection (Internal) of WING components: 532/632 I: 4000 FC ALL
• Lower skin panel spanwise joint (SSI 57-21-30) or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 142
ISSUE : 1
DATE : 05/07/2019

• Skin panels (SSI 57-21-26) or
96 MO
± 60 Days
• Upper skin panel at spanwise joint (SSI 57-21-31) or
96 MO
± 60 Days
57-21-00-210-826-L00 STR AD General Visual Inspection (External) of WING components: 532/632 I: 2000 FC ALL
• Lower skin access holes (SSI 57-21-32) or
96 MO
± 60 Days
57-21-00-220-C01-L00 CPCP ED Detailed Inspection (Internal) of WING components: 541/641 I: 96 MO ALL
• Lower vent hole (SSI 57-21-33) ± 60 Days
57-21-00-220-801-L00 CPCP ED Detailed Inspection (External) of WING components: 532/632 I: 2000 FC ALL
• Skin panels (SSI 57-21-26) or
96 MO
± 60 Days
57-21-00-220-802-L00 STR AD Detailed Inspection (External) of WING components: 531/631 I: 2000 FC ALL
• Lower skin access holes (SSI 57-21-32) 551/651 or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 143
ISSUE : 1
DATE : 05/07/2019

57-21-00-220-803-L00 STR AD Detailed Inspection (Internal) of WING components: 532/632 I: 2000 FC ALL
• Lower skin/spar attachments (SSI 57-21-36) 541/641 or
551/651 96 MO
± 60 Days
• Actuator access holes (SSI 57-21-34) or
• Lower skin/spar attachments (SSI 57-21-36) 96 MO
± 60 Days
• Actuator access holes (SSI 57-21-34) or
96 MO
± 60 Days
• Lower skin access holes (SSI 57-21-32) or
96 MO
± 60 Days
• Upper skin / spar attachment (SSI 57-21-37) or
• Skin panels (SSI 57-21-26) 96 MO
± 60 Days
57-21-00-250-802-L00 STR AD Special Detailed Inspection (External) of WING components by 531/631 I: 5120 FC No L600
using Eddy Current Low Frequency Inspection Method: Tolerance
• Lower skin panel chordwise joint (SSI 57-21-29)
• Spar 1/ leading edge attachments (SSI 57-22-43) ± 30 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 144
ISSUE : 1
DATE : 05/07/2019

• Spar 1/ wing stub attachment (SSI 57-22-44) or
96 MO
± 60 Days
• Spar 1 cap (SSI 57-22-41) 541/641 or
96 MO
± 60 Days
57-22-00-210-803-L00 STR AD General Visual Inspection (External) of WING components: 531/631 I: 2000 FC No L600
• Spar 1/ leading edge attachments (SSI 57-22-43) Tolerance
57-22-00-210-804-L00 STR AD General Visual Inspection (Internal) of WING components: 531/631 I: 4000 FC No ALL
• Spar 1/ leading edge attachments (SSI 57-22-43) 541/641 Tolerance
• Spar 1 cap (SSI 57-22-41) or
96 MO
± 60 Days
• Spar 1/ leading edge attachments (SSI 57-22-43) or
96 MO
± 60 Days
57-22-00-220-801-L00 STR AD Detailed Inspection (External) of WING components: 531/631 I: 4000 FC No ALL
• Spar 1/ web and stiffeners (SSI 57-22-40) 541/641 Tolerance
57-22-00-220-802-L00 STR AD Detailed Inspection (External) of WING components: 551/651 I: 4000 FC No ALL
• Spar 1/ web and stiffeners (SSI 57-22-40) Tolerance
• Spar 1, web cutouts (SSI 57-22-42)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 145
ISSUE : 1
DATE : 05/07/2019

• Spar 1, web cutouts (SSI 57-22-42) or
96 MO
± 60 Days
57-22-00-220-804-L00 STR AD Detailed Inspection (Internal) of WINGLET components: 561/661 I: 8000 FC ALL
• Front Spar - Winglet (SSI 57-22-45) or
96 MO
± 60 Days
• Spar 1, web and stiffeners (SSI 57-22-40) 541/641 or
• Spar 1, web and stiffeners (SSI 57-22-40) or
57-23-00-220-C01-L00 CPCP ED Detailed Inspection (External) of WING components: 531/631 I: 48 MO ALL
• Spar 2, web and stiffeners (SSI 57-23-45) 541/641 ± 30 Days
• Spar 2, web cutouts (SSI 57-23-47) 551/651
• Spar 2 cap (SSI 57-23-46) 541/641 or
551/651 96 MO
± 60 Days
57-23-00-210-802-L00 STR AD General Visual Inspection (External) of WING components: 531/631 I: 2000 FC L600
• Spar 2/ Wing Stub Attachments (SSI 57-23-48) or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 146
ISSUE : 1
DATE : 05/07/2019

• Spar 2/ Wing Stub Attachments (SSI 57-23-48) or
96 MO
± 60 Days
• Spar 2, web and stiffeners (SSI 57-23-45) 541/641 or
551/651 96 MO
± 60 Days
• Spar 2, web cutouts (SSI 57-23-47) 541/641 or
96 MO
± 60 Days
• Spar 2, web cutouts (SSI 57-23-47) or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 147
ISSUE : 1
DATE : 05/07/2019

57-23-00-290-801-L00 STR AD Special Detailed Inspection (Internal) of WING components 561/661 I: 8000 FC L600
using boroscope: or
• Rear Spar - Winglet (SSI 57-23-49) 96 MO
± 60 Days
• Spar 3, web and stiffeners (SSI 57-24-49) ± 30 Days
• Spar 3, web and stiffeners (SSI 57-24-49) ± 30 Days
• Spar 3, cap (SSI 57-24-50) or
96 MO
± 60 Days
• Spar 3, wing stub attachment (SSI 57-24-52) or
96 MO
± 60 Days
• Ribs, main box (SSI 57-25-53) 541/641 ± 60 Days
• Lower skin/ rib attachment (SSI 57-25-54) 551/651
• Upper skin/ rib attachment (SSI 57-25-55)
• Lower skin/ rib attachment (SSI 57-25-54) 541/641 ± 30 Days
• Upper skin/ rib attachment (SSI 57-25-55) 551/651
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 148
ISSUE : 1
DATE : 05/07/2019

57-25-00-290-801-L00 STR AD Special Detailed Inspection 561/661 I: 8000 FC ALL

(Internal) of WINGLET components using boroscope: or
• Rib 25 - Winglet (SSI 57-25-56) 96 MO
± 60 Days
• FWD & aft side brace fittings MLG (SSI 57-26-56) ± 30 Days
• Bearing Cap (SSI 57-26-94)
• Trunnion fitting (SSI 57-26-95)
• FWD & AFT side brace fittings, MLG (SSI 57-26-56) or
48 MO
± 30 Days
57-26-00-250-801-L00 DELETED
57-26-00-250-802-L00 STR AD Special Detailed Inspection (Internal) of WING components by 532/632 I: 10000 FC No L600
the Eddy Current Inspection Method: Tolerance
• Bearing cap - MLG (SSI 57-26-94)
57-26-00-250-803-L00 STR AD Special Detailed Inspection (Internal) of WING components by 532/632 I: 10000 FC No ALL
• FWD & AFT side brace fittings, MLG (SSI 57-26-56)
57-26-00-250-804-L00 STR AD Special Detailed Inspection (External) of WING components by 532/632 I: 10000 FC No ALL
• Trunnion fittings (SSI 57-26-95)
• Lower skin, torque box (SSI 57-28-58) 541/641 ± 30 Days
551/651
• Spar attachment, torque box (SSI 57-28-57) ± 30 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 149
ISSUE : 1
DATE : 05/07/2019

• Upper skin, torque box (SSI 57-28-61) 541/641 48 MO
551/651 ± 30 Days
• Flap actuator attachment fittings (SSI 57-28-67) 541/641 48 MO
± 30 Days
• Lower skin, torque box (SSI 57-28-58) 541/641 ± 30 Days
551/651
57-28-00-210-C09-L00 CPCP ED General Visual Inspection (Internal) of WING components: 532/632 T: 96 MO I: ALL
• Upper skin, torque box (SSI 57-28-61) 48 MO
± 30 Days
• Spar attachment, torque box (SSI 57-28-57) 48 MO
± 30 Days
• Spar attachment, torque box (SSI 57-28-57) or
96 MO
± 60 Days
• Spar 3 attachment, torque box (SSI 57-28-63) or
• Outboard flap center track attachment (SSI 57-28-68) 96 MO
± 60 Days
• Spar 3 attachment, torque box 2 (SSI 57-28-63) or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 150
ISSUE : 1
DATE : 05/07/2019

57-28-00-210-807-L00 STR AD General Visual Inspection (External) of WING components: 551/651 T: 10000 FC or L600
• Attachment lugs aileron (SSI 57-28-66) 96 MO
NOTE: During this inspection, the CPCP basic task shall also be I: 2000 FC
performed for this SSI or
96 MO
± 60 Days
• Upper skin, torque box (SSI 57-28-61) 551/651 or
57-28-00-220-C02-L00 CPCP ED Detailed Inspection (External) of WING components: 532/632 T: 96 MO I: ALL
• Flap track, torque box (SSI 57-28-59) 541/641 48 MO
551/651 ± 30 Days
57-28-00-220-C03-L00 CPCP ED Detailed Inspection (External) of WING components: 551/651 I: 48 MO L600
• Ribs, torque box 3 (SSI 57-28-64) ± 30 Days
• Tracks/ rib attachment, torque box 3 (SSI 57-28-65)
• Attachment actuator lugs, inboard/ outboard spoilers ± 30 Days
(SSI 57-28-70)
• Tracks/ ribs attachment, torque box (SSI 57-28-62) 541/641 ± 60 Days
• Ribs, torque box 3 (SSI 57-28-64) ± 60 Days
• Tracks/ rib attachment, torque box 3 (SSI 57-28-65)
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 151
ISSUE : 1
DATE : 05/07/2019

57-28-00-220-C07-L00 CPCP ED Detailed Inspection (Internal) of WING components: 532/632 T: 96 MO I: ALL

• Ribs, torque box 3 (SSI 57-28-60) 48 MO
± 30 Days
57-28-00-220-C08-L00 CPCP ED Detailed Inspection (External) of WING components: 532/632 T: 96 MO I: ALL
• Ribs, torque box (SSI 57-28-60) 48 MO
± 30 Days
• Ribs, torque box (SSI 57-28-60) ± 30 Days
57-28-00-220-C10-L00 CPCP ED Detailed Inspection (External) of WING components: 541/641 I: 48 MO L600
• Ribs, torque box (SSI 57-28-60) ± 30 Days
• Spar attachment, torque box (SSI 57-28-57) or
96 MO
± 60 Days
• Center track and rib 15 trailing edge (SSI 57-28-69) or
96 MO
± 60 Days
• Tracks/ ribs attachment, torque box (SSI 57-28-62) 541/641 or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 152
ISSUE : 1
DATE : 05/07/2019

• Spar attachment, torque box (SSI 57-28-57)
• Ribs, torque box (SSI 57-28-60)
• Spar attachment, torque box (SSI 57-28-57)
• Ribs, torque box (SSI 57-28-60)
the Eddy Current Inspection Method: 541/641 Tolerance
• Flap track, torque box (SSI 57-28-59) 551/651
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 153
ISSUE : 1
DATE : 05/07/2019

• Skin/ rib attachment, MLGB (SSI 57-29-72) or
96 MO
± 60 Days
• Ribs, main landing gear bay (SSI 57-29-71) or
• Skin/ rib attachment, MLGB (SSI 57-29-72) 96 MO
± 60 Days
57-41-00-210-C01-L00 CPCP ED General Visual Inspection (External) of WING LEADING EDGE 511/611 I: 48 MO L600
• Wing leading edge 1 skin (SSI 57-41-94)
57-41-00-220-801-L00 STR AD Detailed Inspection (Internal) of WING LEADING EDGE 511/611 I: 4000 FC ALL
components: or
• Machined rib flange (SSI 57-41-98) 96 MO
± 60 Days
57-42-00-210-C01-L00 CPCP ED General Visual Inspection (External) of WING LEADING EDGE 512/612 I: 48 MO L600
components: or
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 154
ISSUE : 1
DATE : 05/07/2019

57-42-00-220-802-L00 STR AD Detailed Inspection (External) of WING LEADING EDGE 512/612 I: 2000 FC ALL
components: or
• Wing leading edge 2 bottom skin at connections to lower rear 48 MO
girder & wing lower spar cap (SSI 57-42-97) ± 30 Days
57-43-00-210-C01-L00 CPCP ED General Visual Inspection (External) of LEADING EDGE 513/613 I: 48 MO L600
components: or
± 60 Days
57-50-00-220-C01-L00 CPCP ED Detailed Inspection (External) of FLAP components: 571/671 T: 96 MO I: ALL
• Tracks/ rib attachment, flaps (SSI 57-50-77) 572/672 48 MO
± 30 Days
57-50-00-220-801-L00 DELETED
57-50-00-220-802-L00 DELETED
57-50-00-220-803-L00 STR AD Detailed Inspection (External) of FLAP components: 571/671 I: 4000 FC ALL
• Roller attachment, flaps (SSI 57-50-76) 572/672 or
96 MO
± 60 Days
• Tracks, flaps (SSI 57-50-80) 572/672 or
48 MO
± 30 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 155
ISSUE : 1
DATE : 05/07/2019

57-50-00-220-805-L00 STR FD Detailed Inspection (External) of FLAP components: 571/671 I: 4000 FC ALL
• Flap root-spar fitting (SSI 57-50-74). 572/672 or
• Inboard flap fitting tip spar (SSI 57-52-73). 96 MO
• Outboard flap tip spar fitting (SSI 57-53-83). ± 60 Days
• Inboard flap ribs/skin attachment (SSI 57-52-79). 572/672 or
• Inboard flap vane inboard/outboard fittings (SSI 57-52-81). 96 MO
• Outboard flap ribs/skin attachment (SSI 57-53-86). ± 60 Days
• Outboard flap vane inboard/outboard fittings (SSI 57-53-88).
57-50-00-250-801-L00 STR AD Special Detailed Inspection (External) of FLAP components by 571/671 I: 10000 FC No ALL
• Roller attachment, flaps (SSI 57-50-76)
57-50-00-250-802-L00 STR AD Special Detailed Inspection (External) of FLAP components by 571/671 I: 9000 FC No L600
• Tracks, flaps (SSI 57-50-80)
57-50-00-290-801-L00 STR FD Special Detailed Inspection (Internal) of FLAP components by 571/671 I: 4000 FC ALL
borescope Inspection Method: 572/672 or
• Structural Significant Item: SSI 57-50-74 - Flap rootspar fitting. 96 MO
• Structural Significant Item: SSI 57-52-73 - Inboard flap tip spar ± 60 Days
fitting.
• Structural Significant Item: SSI 57-53-83 - Outboard flap tip
spar fitting.
57-52-00-210-801-L00 DELETED
57-52-00-210-802-L00 DELETED
57-52-00-210-803-L00 STR AD General Visual Inspection (External) of FLAP components: 571/671 I: 1450 FC L600
• Vane center fitting, inboard flap (SSI 57-52-78) or
96 MO
± 60 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 156
ISSUE : 1
DATE : 05/07/2019

57-52-00-210-804-L00 STR AD General Visual Inspection (External) of FLAP components: 571/671 T: 4600 FC L600
• Pin and actuator lugs, inboard flap (SSI 57-52-75) or
96 MO
I: 1140 FC
or
96 MO
± 60 Days
57-52-00-220-801-L00 DELETED
57-52-00-220-802-L00 DELETED
57-52-00-250-801-L00 DELETED
57-53-00-210-C01-L00 CPCP ED General Visual Inspection (External) of FLAP components: 572/672 T: 96 MO I: L600
• Center ribs attachment, outboard flap (SSI 57-53-87) 48 MO
± 30 Days
57-53-00-210-801-L00 STR AD General Visual Inspection (External) of FLAP components: 572/672 I: 1450 FC L600
• Vane center fitting, outboard flap (SSI 57-53-85) or
96 MO
± 60 Days
57-53-00-210-802-L00 DELETED
57-53-00-210-803-L00 STR AD General Visual Inspection (Internal) of FLAP components: 572/672 I: 8000 FC No ALL
• Center ribs attachment, outboard flap (SSI 57-53-87) Tolerance
57-53-00-210-804-L00 DELETED
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 157
ISSUE : 1
DATE : 05/07/2019

57-53-00-210-805-L00 DELETED
57-53-00-210-806-L00 STR AD General Visual Inspection (External) of FLAP components: 572/672 T: 4000 FC L600
• Pin and actuator lugs, outboard flap (SSI 57-53-84) or
96 MO
I: 1140 FC
or
96 MO
± 60 Days
57-53-00-220-801-L00 DELETED
57-53-00-220-802-L00 DELETED
57-61-00-210-C01-L00 CPCP ED General Visual Inspection (External) of AILERON components: 573/673 T: 96 MO I: ALL
• Spar cap, aileron (SSI 57-61-91) 48 MO
± 30 Days
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 2
MAINTENANCE PROGRAM
PAGE : 158
ISSUE : 1
DATE : 05/07/2019

57-61-00-210-801-L00 STR AD General Visual Inspection (External) of WING components: 573/673 T: 10000 FC L600
• Hinges attachment, aileron (SSI 57-61-89) or
performed for this SSI I: 4000 FC
or
96 MO
± 60 Days
57-61-00-220-801-L00 STR AD Detailed Inspection (External) of AILERON components: 573/673 I: 2000 FC ALL
• Actuator attachment, aileron (SSI 57-61-90) or
96 MO
± 60 Days
57-61-00-220-802-L00 STR AD Detailed Inspection (Internal) of AILERON components: 573/673 I: 4000 FC No ALL
• Actuator attachment, aileron (SSI 57-61-90) Tolerance
57-70-00-210-C01-L00 CPCP ED General Visual Inspection (External) of SPOILER components: 5712/6712 I: 48 MO ALL
• Hinges attachment, spoilers (SSI 57-70-92) 5713/6713 ± 30 Days
• Actuator attachment, spoilers (SSI 57-70-93)
CHAPTER 71 - POWERPLANT


413 ± 30 Days
421/422
423
CHAPTER 71 - POWERPLANT (CONTINUED)

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413/415 ± 30 Days
421/422
423/425
71-10-00-211-001-A00 SYS 9 Visually Check Cowling Seals 410/420 I: 4000 FH ALL
or
48 MO
± 30 Days
71-10-00-220-001-A00 SYS 9 Inspect (Detailed Inspection) Cowling Inboard/ Outboard 410/420 I: 4000 FH ALL
Attachment and Surrounding Structure or
48 MO
± 30 Days
71-20-00-220-001-A00 SYS 8 Inspect (Detailed Inspection) Engine Mounting Assy 412/422 I: 4000 FH ALL
413/423 or
48 MO
± 30 Days
71-60-01-211-001-A00 SYS 9 Visually Check Air Intake Attachment 412/422 I: 4000 FH ALL
413/423 or
48 MO
± 30 Days
71-60-01-211-002-A00 SYS 9 Visually Check Air Intake Rear Bulkhead and Fire Shield 412/422 I: 4000 FH ALL
413/423 or
48 MO
± 30 Days
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CHAPTER 72 - ENGINE

72-00-00-970-001-A00 SYS 9 Engine Trend Download / Analysis 223 I: 100 FH ALL

or
70 FC
No Tolerance
72-20-00-212-001-A00 SYS 9 Inspect (General Visual) Engine Air Intake 415/425 I: 500 FH No ALL
Tolerance
72-21-01-220-001-A00 SYS 9 Inspect (Detailed Inspection) Fan Blades 415/425 I: 4000 FH No ALL
Tolerance
72-21-20-220-002-A00 SYS 8 Inspect (Detailed Inspection) Fan Spinner P/N 23054034, 413 I: 500 FH No ALL
23064250 or 23065046 only 423 Tolerance
72-63-01-710-001-A00 SYS 9 Operationally Check Starter Drain Adapter Pre-Mod SB 415 I: 800 FH No L600
AE3007A-72-330. 425 Tolerance
CHAPTER 73 - ENGINE FUEL AND CONTROL

73-11-00-960-001-A00 SYS 6 Discard of Engine Fuel Filter 413/423 I: 2000 FH No ALL

Element. Tolerance
73-11-10-130-001-A00 SYS 6 Restore (Cleaning) Fuel Nozzles except P/N 23075904, P/N 413/423 I: 2000 FH No ALL
23077006, P/N 23087207 and P/N 23090046. 412/422 Tolerance
NOTE: If installed
73-11-10-130-001-A01 SYS 6 Restore (Cleaning) Fuel Nozzles P/N 23075904, P/N 413/423 I: 10000 FH No ALL
23077006, P/N 23087207 And P/N 23090046. 412/422 Tolerance
NOTE: If installed
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CHAPTER 73 - ENGINE FUEL AND CONTROL (CONTINUED)

73-21-00-211-001-A00 SYS 9 Visually Check Fuel Pump and Metering Unit for Fuel Leakage 413/423 I: 1000 FH No ALL
Tolerance
73-21-06-720-001-A00 SYS 9 Functionally Check Fuel Filter Impending Bypass Indicating 413/423 I: 3000 FH No ALL
System Tolerance
73-22-01-720-003-A00 SYS 9 Functionally Check Multi-Function Display for ENG( ) LT FAULT 223 I: 500 FH ALL
and ENG( ) SCHED MAINT REPAIR Maintenance Messages or
6 MO
No Tolerance
73-30-04-220-001-A00 SYS 9 Inspect (Detailed Inspection) FADEC Anti-Vibration Mounts 272 I: 4000 FH No ALL
Tolerance
CHAPTER 74 - IGNITION

74-21-01-960-001-A00 SYS 6 Discard Igniters 413/423 I: 4000 FH ALL
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CHAPTER 76 - ENGINE CONTROLS

76-12-00-710-001-A00 SYS 8 Operationally Check WOW input signal to FADEC 223 I: 8000 FH ALL
or
96 MO
± 60 Days
76-13-03-710-001-A00 SYS 8 Operationally Check Idle Lockout 220 I: 500 FH ALL
NOTE: Only aircraft with Thrust Reversers. or
12 MO
± 15 Days
CHAPTER 76 - ENGINE CONTROLS (CONTINUED)

76-20-00-710-001-A00 SYS 8 Operationally Check Emergency Shutdown System 155/156 I: 2500 FH ALL
193 or
414/424 24 MO
412/422 ± 30 Days
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CHAPTER 78 - EXHAUST


426 ± 30 Days
426 ± 30 Days
NOTE: For aircraft without thrust reversers only. ± 30 Days
NOTE: For aircraft without thrust reversers only. ± 30 Days
78-10-01-212-002-A00 SYS 8 Inspect (General Visual) Plain Exhaust Assy for Damage, 412/422 I: 8000 FH ALL
Failure or Irregularities 413/423 or
NOTE: Not applicable to aircraft with thrust reversers installed 72 MO
± 30 Days
78-31-00-220-001-A00 SYS 8 Inspect (Detailed Inspection) Thrust Reverser Structure 416/426 I: 8000 FH ALL
or
72 MO
± 30 Days
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CHAPTER 78 - EXHAUST (CONTINUED)

78-32-00-211-001-A00 SYS 8 Visually Check Thrust Reverser 1RY and 3RY Locks 416/426 I: 500 FH ALL
or
12 MO
± 15 Days
78-32-00-710-001-A00 SYS 8 Operationally Check Thrust Reverser 2RY and 3RY Locks 416/426 I: 1000 FH ALL
or
12 MO
± 15 Days
78-33-00-720-001-A00 SYS 9 Functionally Check Thrust Reverser Control Lever 223 I: 8000 FH ALL
Microswitches or
96 MO
± 60 Days
78-34-01-720-001-A00 SYS 8 Functionally Check Stow/Transit Thrust Reverser Micro- 416 I: 1200 FH L600
switches for Insulation Pre-Mod. S.B. 145LEG-78-0006 426 or
12 MO
No Tolerance
CHAPTER 79 - OIL

79-25-02-211-001-A00 DELETED
79-27-00-211-001-A00 SYS 9 Visually Check Oil Plumbing 413/423 I: 10000 FH ALL
No Tolerance
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79-34-00-212-001-A00 SYS 6 Inspect (General Visual) of Multi-Function Display for ENG 1(2) 223/224 I: 50 FH or L600
OIL DEBRIS Engine AE3007A1P Maintenance Message 225/226 30 Calendar
NOTE: If installed Days
(Whichever
occurs first)
No Tolerance
CHAPTER 79 - OIL (CONTINUED)

79-34-00-212-001-A01 SYS 6 Inspect (General Visual) of Multi-Function Display for ENG 1(2) 223/224 I: 70 FH or ALL
OIL DEBRIS Engine AE3007A1E or Engine AE3007A2 225/226 30 Calendar
Maintenance Message Days
NOTE: If installed (Whichever
occurs first) No
Tolerance
79-34-01-720-001-A00 SYS 9 Functionally Check Indicating Magnetic Plug Assembly 413/423 I: 8000 FH ALL
No Tolerance
79-37-00-720-001-A00 SYS 9 Functionally Check Oil Filter Impending Bypass Indicating 413/423 I: 8000 FH ALL
System No Tolerance
CHAPTER 80 - STARTING

80-10-01-720-001-A00 SYS 6 Functionally Check Air Turbine Starter (ATS) including Oil 413/423 I: 500 FH or ALL
Servicing 6 MO
± 15 Days
80-10-02-160-001-A00 SYS 6 Service (Cleaning) Start Control Valve Filter 413 I: 4000 FH or ALL
423 48 MO
± 30 Days
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Section 3 National Requirements REVISION : 0
DATE : 05/07/2019
SECTION 3 - NATIONAL REQUIREMENTS
3.1 GENERAL
A. Special Rules Pertaining to United States of America FAA Certification.
An operator may take credit for tasks described in this section when accomplished by the flightcrew as part of a Federal Aviation Administration (FAA) approved
cockpit normal checklist. Those tasks must be reviewed and approved by the principal maintenance inspector (PMI) to assure accountability.
B. Special Rules Pertaining to EASA Certification

• The individual check intervals listed in this Report may be escalated following the completion of the required series or sequence of checks and the satisfactory
review of check results and approval by the responsible NAA, or in accordance with the operator's NAA approved reliability program.
• Individual task intervals may be escalated based on satisfactory substantiation by the operator, and review and approval by his responsible NAA, or in accordance
with the operator's NAA-approved reliability program.
• Task interval parameters expressed in the Legacy BJ – MPG Report may be converted to an individual operator's desired. Units, provided this conversion does not
result in the operator exceeding the initial requirements of the Legacy BJ – MPG Report.
• The use of Non-Destructive Inspection (NDI) methods, such as "X-ray", "ultrasonic", "eddy current", "radio isotope", etc, which are approved by the TC Holder, can
provide an alternative to the methods prescribed in this Report. The operator should notify their responsible NAA of the use of an acceptable alternate method.
• Within this Report the terms "check" and "inspection" are not intended to imply a level of skill required to accomplish a task.
• Life-limited parts must be retired in accordance with the limits established in the engine and aircraft Type Certificate Data Sheets or the
Airworthiness Limitations Section of the engine or aircraft manufacturer's instructions for Continued Airworthiness.
• After the accumulation of industry service experience, the Manufacturer and Certification Authority may request changes to the requirements of this Legacy BJ –
MPG Report
• Whenever a task has dual frequencies, it must be accomplished at WHICHEVER PERIOD OCCURS FIRST.
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B.1 List of Scheduled EASA System Maintenance Requirements Presentation These following tasks are specific for EASA Inspection Requiriments.
EASA INSPECTION REQUIREMENTS

27-21-00-710-001-A00 SYS 7 Operationally Check Rudder 311/312 I: 4000 FH ALL
Movable Primary Stop Mechanism or
48 MO
± 30 Days
27-22-00-720-002-A00 SYS 9 Functionally Check Rudder Hydraulic Damping 325/326/ I: 1200 FH ALL
NOTE: Or in accordance with Local Regulatory Authority 327 or
Requirements. 12 MO
± 15 Days
27-23-00-710-002-A00 SYS 9 Operationally Check Alert ing Light of the Rudder Movable 312 I: 2000 FH ALL
Primary Stop or
24 MO
± 30 Days
33-12-00-710-002-A00 SYS 9 Operationally Check Pushbutto Lighting 223/224 I: 1000 FH ALL
76-11-04-720-001-A00 SYS 9 Functionally Check Friction lock Assembly for Pre-Load Value 223 I: 2000 FH ALL
or
24 MO
± 30 Days
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B.2. List of Scheduled EASA Structural Maintenance Requirements Presentation.
These following tasks are specific for EASA Inspection Requirements.
EASA STRUCTURAL MAINTENANCE REQUIREMENTS

57-61-00-220-804-L00 STR - Detailed Inspection (Internal) of AILERON components: 573/673 I: 4000 FC ALL
• Aileron Actuator fittings (SSI 57-61-12) No Tolerance
C Special Rules Pertaining to CAAC Certification

C.1 List of Scheduled CAAC System Maintenance Requirements Presentation.

25-63-00-710-001-A00 SYS 8 Operationaly Check Portable 573/673 I: 12 MO ALL
Emergency Locator Transmiter System No Tolerance
Requirements
NOTE: If Installed
25-63-02-960-001-A00 SYS 8 Discard Portable ELT Battery ELTA PN 05N62123 262 I: 60 MO ALL
NOTE: Portable ELT battery change in accordance with No Tolerance
manufacturer's data plate expiration date or in accordance with
Local Regulatory Authority Requirements
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Table Difinitions

a b c d e f g
a- MAINTENANCE REQUIREMENT - Numbering as defined in Section 1 - Item 13.

b- SOURCE - The source column defines to which maintenance requirement program belongs as defined in Section 1 - Item 13.
c- CAT/CSD - Task Category and Critical Source of Damage are defined in Section 1 - Item 13.
d- REQUIREMENT TYPE/TITLE - Description of the task to be performed.
e- ZONES - Zones of the aircraft where each task is accomplished as defined in Section 1 - Item 13.
f- THR/INT/TOLERANCE - Definitions as described in Section 1 - Item 13.
g- EFFECT - Task effectivity as defined in Section 1 - Item 13.
>>>>>>>>>> END<<<<<<<<<<
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DATE : 05/07/2019
SECTION-4 APPENDIXES
APPENDIX A - AIRWORTHINESS LIMITATIONS (CMR’s and ALI’s)

A1.1 GENERAL
This appendix contains the Certification Maintenance Requirements (CMR's) resulting from the procedures of AC 25-19 and established by the CMR
Meeting (representatives of EMBRAER, Aircraft Certification Office (ACO) Specialists, and the EMB-145 MRB Chairperson). These CMR's are
inspections established through the safety analysis process developed in accordance with RBHA/FAR/JAR 25.1309, aimed at detecting safety
significant latent failures which would, in combination with one or other more specific failures or events, result in a hazardous or catastrophic failure
condition.
The CMR's are referenced in the Type Certificate Data Sheet and all CMR's candidates are listed in Certification Report 145-MS-015 and 135- MS-
715 including certain fightcrew checks that cannot be deleted from the AFM, unless an equivalent task is established for maintenance personnel.
The CMR's and related intervals listed herein are mandatory and cannot be changed, escalated, or deleted without the concurrence of manufacturer
and approval of the Regulatory Authority. Whenever a task has dual frequencies, it must be accomplished at WHICHEVER PERIOD OCCURS
FIRST. Any post-certification changes to CMR's should be reviewed by the CMR Meeting and must be approved by the Regulatory Authority that
approved the type design.
The Certification Maintenance Requirements (CMR’s) are a result of the Engineering Certification analysis and have been approved by CAAT.
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A1.2 LIST OF CMR’S APPLICABLE TO AIRCRAFT UNDER CAAT CERTIFICATIONS

27-25-00-710-001-A00 SYS - Operationally Check Rudder Pedals Auto Shutoff and Rudder 223 I: 2500 FH ALL
Manual Shutoff Functions 224 or
225 24 MO
226 ± 30 Days
27-31-05-220-001-A00 SYS - Inspect (Detailed Inspection) Servo Tab Failsafe Actuation Link 335 I: 4000 FH ALL
336 or
48 MO
± 30 Days
27-62-00-720-001-A00 SYS - Functionally Check G. Spoiler/Speed Brake Valves, Control 192 I: 8000 FH ALL
Cir- cuit and Associated Messages or
96 MO
± 60 Days
CHAPTER 28 - FUEL
MAINTENANCE CAT/ REQUIREMENT THR/INT/

SOURCE ZONES EFFETC
REQUIREMENT CSD TYPE/TITLE TOLERANCE
28-14-08-710-001-A00 SYS - Operationally Check 3/4 Zero Leakage Check Valves 272 I: 1000 FH ALL
No Tolerance
28-14-09-710-001-A00 SYS - Operationally Check 3/8 Zero Leakage Check Valves 272 I: 1000 FH ALL
or
12 MO
± 15 Days
28-14-10-710-001-A00 SYS - Operationally Check AFT Fuel Tanks Pressurization Vent Plumb- 171 I: 2000 FH ALL
ing Shroud 172 or
191 24 MO
223 ± 30 Days
225
272
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CHAPTER 30 - ICE AND RAIN PROTECTION

30-11-00-720-001-A00 SYS - Functionally Check Pressure Sensors of the Wing Thermal 191/192 I: 4000 FH ALL
Anti-Icing System (Bench Test) or
48 MO
± 30 Days
30-12-00-720-001-A00 SYS - Functionally Check Pressure Sensors of the Horizontal Stabilizer 321/324 I: 4000 FH ALL
Thermal Anti-Icing System (Bench Test) or
48 MO
± 30 Days
30-21-00-720-001-A00 SYS - Functionally Check Pressure Sensors of the Engine Thermal 412/422 I: 4000 FH ALL
Anti-Icing System (Bench Test) or
48 MO
± 30 Days
CHAPTER 32 - LANDING GEAR

32-63-00-710-001-A00 SYS - Operationally Check Air/Ground System 220 I: 500 FH ALL
711 or
721 6 MO
731 ± 15 Days
CHAPTER 78 - EXHAUST
78-33-00-710-001-A00 SYS - Operationally Check Air/Ground Input Signal to Thrust Reverser 312 I: 1000 FH ALL
System 416 or
426 12 MO
± 15 Days
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CHAPTER 78 - EXHAUST (CONTINUED)

78-33-00-710-002-A00 SYS - Operationally Check Wheel Speed Input Signal to Thrust 312 I: 1000 FH ALL
Reverser System 416 or
426 12 MO
± 15 Days
78-33-01-710-001-A00 SYS - Operationally Check Isolation Control Unit 272 I: 1000 FH ALL
312 or
12 MO
± 15 Days
78-34-00-710-001-A00 SYS - Operationally Check Thrust Reverser Indicating System 272 I: 10000 FH ALL
312 or
72 MO
± 30 Days
A1.3 LIST OF ADDITIONAL CMR’S APPLICABLE TO AIRCRAFT UNDER CAAT CERTIFICATION

27-12-00-720-003-A02 SYS - Functionally Check External Leakage of Aileron Hydraulic 551 I: 1000 FH ALL
Actuator 651 or
24 MO
± 30 Days
27-12-01-212-002-A02 SYS - Inspect (General Visual) Aileron PCA Rod Ends/Fitting Lugs for 551 I: 1000 FH ALL
Integrity and General Condition 651 or
24 MO
± 30 Days
27-12-01-720-001-A02 SYS - Functionally Check Aileron Actuator Damping Components and 551 I: 1000 FH ALL
Monitoring Devices 651 or
12 MO
± 15 Days
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A1.3 LIST OF ADDITIONAL CMR’S APPLICABLE TO AIRCRAFT UNDER CAAT CERTIFICATION (CONTINUED)

27-12-01-720-002-A00 SYS - Functionally Check Aileron Actuator Force Fight 551 I: 1000 FH ALL
651 or
24 MO
± 30 Days
A1.4 LIST OF ADDITIONAL CMR’S APPLICABLE TO AIRCRAFT UNDER CAAT CERTIFICATIONS

SOURCE REQUIREMENTTYPE/TITLE ZONES EFFETC
27-12-00-720-003-A01 SYS - Functionally Check External Leakage of Aileron Hydraulic 551 I: 2000 FH ALL
Actuator 651 or
24 MO
± 30 Days
27-12-01-212-002-A01 SYS - Inspect (General Visual) Aileron PCA Rod Ends/Fitting Lugs for 551 I: 1000 FH ALL
24 MO
± 30 Days
27-12-01-720-001-A01 SYS - Functionally Check Aileron Actuator Damping Components and 551 I: 2500 FH ALL
Monitoring Devices 651 or
12 MO
± 15 Days
27-12-03-212-001-A00 SYS - Visually Check Aileron Damper Rod Ends/ Fitting Lugs for 551 I: 1000 FH ALL
18 MO
± 15 Days
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27-12-03-720-001-A00 SYS - Functionally Check Aileron Damper Damping Force 551 I: 2500 FH ALL
651 or
5731 24 MO
6731 ± 30 Days
27-12-03-720-002-A00 SYS - Functionally Check External Leakage of Aileron Damper 5731 I: 2500 FH ALL
6731 or
24 MO
± 30 Days
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AIRWORTHINESS LIMITATION REQUIREMENTS
A2.1 GENERAL
These Airworthiness Limitations are mandatory actions derived from the certification activities, namely, the Damage Tolerance
Analysis and the Fatigue Tests.
This appendix presents the maintenance actions established in order to fully comply with the requirements of RBHA/FAR/JAR
25.571 and, therefore, are required to be accomplished in strict compliance with the life limits, maximum intervals limits, inspection
methods and SSI location established herein.
The Airworthiness Limitations shall be revised by TCH with the approval of the CAAT.
A2.2 LIFE LIMITED COMPONENTS
These Airworthiness Limitations are mandatory actions derived from certification Fatigue Tests. The Airworthiness Limitations for
all model Rolls-Royce AE3007A engines are listed in Chapter 5 of Rolls-Royce Maintenance Manual (CSP34022).
CHAPTER 32 - EMB-145 LANDING GEAR - LIFE LIMITED COMPONENTS
DESCRIPTION NOTE PART NUMBER SUPPLIER LIFE LIMIT (FC) EFFECTIVITY

MLG LEG STRUT
Leg Strut Left (LH) N/P 2309-1302-501 Embraer 60000 (Note 2) ALL
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CHAPTER 32 - EMB-145 LANDING GEAR - LIFE LIMITED COMPONENTS (CONTINUED)

MLG LEG STRUT (CONTINUED)
Leg Strut Right (RH) N/P 2309-1302-502 Embraer 60000 (Note 2) ALL
Trunnion Axle P 2309-2025-001 Embraer 60000 (Note 2) ALL
Trunnion Axle P 2309-3025-001 Embraer 60000 (Note 2) ALL
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Shock Absorber Attachment Axle P 2309-1329-001 Embraer 60000 (Note 2) ALL
Shock Absorber Attachment Axle P 2309-2029-001 Embraer 60000 (Note 2) ALL
Main Side Strut Attachment Axle (Pivot Pin) P 2309-2032-001 Embraer 60000 (Note 2) ALL
Trailing Arm Axle Left (LH) P 2309-1305-001 Embraer 60000 (Note 2) ALL
Trailing Arm Axle Right (RH) P 2309-1305-002 Embraer 60000 (Note 2) ALL
Trailing Arm N/P 2309-1310-501 Embraer 21454 (Note 1) ALL
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Wheel Axle P 2309-2040-001 Embraer 60000 (Note 2) ALL
Wheel Axle P 2309-3040-001 Embraer 60000 (Note 2) ALL
Pivot P 2309-2050-001 Embraer 60000 (Note 2) ALL
Cardan Joint P 2309-2048-001 Embraer 15760 (Note 2) ALL
MLG SHOCK ABSORBER
Piston Tube N/P 2309-2058-001 Embraer 60000 (Note 2) ALL
Cylinder N/P 2309-2056-001 Embraer 60000 (Note 2) ALL
Bearing Cap P 2309-2066-001 Embraer 60000 (Note 2) ALL
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CHAPTER 32 - EMB-145 LANDING GEAR - LIFE LIMITED COMPONENTS (Continued)

MLG SHOCK ABSORBER (CONTINUED)
Bearing Cap P 2309-2082-001 Embraer 60000 (Note 2) ALL
MLG SECONDARY SIDE STRUT
Upper Secondary Side Strut - 2309-2609-001 Embraer 60000 (Note 2) ALL
Upper Secondary Side Strut N/P 2309-2611-001 Embraer 60000 (Note 2) ALL
Upper Secondary Side Strut N/P 2309-2611-003 Embraer 60000 (Note 2) ALL
Lower Secondary Side Strut - 2309-2603-001 Embraer 60000 (Note 2) ALL
Lower Secondary Side Strut N/P 2309-2624-001 Embraer 60000 (Note 2) ALL
Cardan N/P 2309-2618-001 Embraer 60000 (Note 2) ALL
Shaft P 2309-2621-001 Embraer 60000 (Note 2) ALL
Bolt P 2309-2626-001 Embraer 60000 (Note 2) ALL
Pivot Pin P 2309-2613-001 Embraer 60000 (Note 2) ALL
Spring P 2309-2651-001 Embraer 20000 (Note 2) ALL
MLG MAIN SIDE STRUT
Upper Main Side Strut - 2309-2503-001 Embraer 60000 (Note 2) ALL
Upper Main Side Strut N/P 2309-2524-001 Embraer 60000 (Note 2) ALL
Lower Main Side Strut - 2309-2511-001 Embraer 60000 (Note 2) ALL
Lower Main Side Strut N/P 2309-2532-001 Embraer 60000 (Note 2) ALL
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CHAPTER 32 - EMB-145 LANDING GEAR - LIFE LIMITED COMPONENTS (Continued)

MLG MAIN SIDE STRUT (CONTINUED)
NLG LEG STRUT
Sliding Tube N/P 1170-1401 Liebherr 60000 (Note 2) ALL
Sliding Tube P 2233-0201 Liebherr 60000 (Note 2) ALL
Sliding Tube P 2233-0401 Liebherr 20000 (Note 2) ALL
Wheel Axle N/P 1170-1402 Liebherr 60000 (Note 2) ALL
Wheel Axle P 1170-1403 Liebherr 60000 (Note 2) ALL
Steering Cuff N/P 1170A2300-01 Liebherr 60000 (Note 2) ALL
Torque Link N/P 1170-0301 Liebherr 60000 (Note 2) ALL
Torque Link Pin P 1170-0001 Liebherr 60000 (Note 2) ALL
Torque Link Central Bolt P 1170-0002 Liebherr 60000 (Note 2) ALL
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NLG LEG STRUT (CONTINUED)
Main Fitting N/P 1170-1301 Liebherr 20000 (Note 2) ALL
Main Drag Strut Attachment Pin P 1170-0070 Liebherr 60000 (Note 2) ALL
Pintle Pin P 1170-0032 Liebherr 60000 (Note 2) ALL
NLG MAIN DRAG STRUT
Main Drag Strut Top Stay N/P 1172-0501 Liebherr 6000 (Note 2) ALL
Main Drag Strut Bottom Stay N/P 1172-0201 Liebherr 60000 (Note 2) ALL
Main Drag Strut Bottom Stay N/P 1172-0701 Liebherr 30000 (Note 2) ALL
Pintle Pin N/P 1172-0007 Liebherr 6000 (Note 2) ALL
Pintle Pin P 1172-0037 Liebherr 60000 (Note 2) ALL
Hinge Point Bolt P 1172-0001 Liebherr 60000 (Note 2) ALL
NLG AUXILIARY DRAG STRUT
Upper Auxiliary Drag Strut N/P 1173-0201 Liebherr 60000 (Note 2) ALL
Lower Auxiliary Drag Strut N/P 1173-0101 Liebherr 60000 (Note 2) ALL
Hinge Point Bolt P 1173-0001 Liebherr 60000 (Note 2) ALL
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NLG AUXILIARY DRAG STRUT (CONTINUED)
Cardan Joint P KSL 113608V Liebherr 60000 (Note 2) ALL
Cardan Joint P 2000A0830K01 Liebherr 60000 (Note 2) ALL
Downlock Spring - 1173A0300-01 Liebherr 20000 (Note 2) ALL
Downlock Spring N/P 1173A0600-01 Liebherr 20000 (Note 1) ALL
Downlock Spring P 1173A0700-01 Liebherr 20000 (Note 1) ALL
Auxiliary Drag Strut Assy N/P 1173B0000-02 Liebherr 6000 (Note 3) ALL
NOTE: The column "NOTE" indicates if the P/N is Procurable (P) or Non-procurable (N/P).
NOTE 1: The definitive life limits will be based on fatigue tests being concluded. The current status of these fatigue tests assure a minimum of the
above flight cycles of safe operation.
NOTE 2: Permanent life limit.
NOTE 3: The life limit is applicable "only" for Parts Numbers 1173B0000-02, Auxiliary Drag Strut Assy, which are engraved with serial numbers
SP010-96, SP011-96, SP012-96 and SP013-96.
NOTE 4: 20000 for rod end installed in actuator 2309-3700-501/503.60000 for rod end installed in actuator 2309-2700-501/503/505.
CHAPTER 35 – OXYGEN
LIFE
DESCRIPTION PART NUMBER SUPPLIER EFFECTIVITY
LIMIT
Oxygen Cylinder 176250-50 B/E AEROSPACE 180 MO ALL
4441009-050 180 MO
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CHAPTER 36 – PNEUMATIC
LIFE
LIMIT
Low Pressure Bleed-Air Check Valve 816603-1 Hamilton 1600 FH ALL
816603-2 Standard 1600 FH ALL
CHAPTER 72 – ENGINE
The airworthiness Limitations for all model Rolls-Royce AE3007A engines are listed in Chapter 5 of Rolls-Royce Maintenance Manual
(CSP34022).
CHAPTER 78 - THRUST REVERSER
LIFE LIMIT
(Note 5)
Primary Door Lock Actuator TY2038-01A LUCAS 60,250 TRC ALL
Primary Door Lock Actuator TY2038-02A LUCAS 60,250 TRC ALL
Pivot Door Actuator TY2039-03A LUCAS 1,800 TRC ALL
Pivot Door Actuator TY2039-03B LUCAS 1,800 TRC ALL
Pivot Door Actuator TY2039-03C LUCAS 1,800 TRC ALL
Pivot Door Actuator TY2039-05B LUCAS 15,000 TRC ALL
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LIFE LIMIT
(Note 5)
Pivot Door Actuator TY2039-05B-629 LUCAS 15,000 TRC ALL
Pivot Door Actuator TY2039-05B-629-7 LUCAS 60,250 TRC ALL
Pivot Door Actuator TY2039-05B-7 LUCAS 60,250 TRC ALL
Directional Control Unit TY2040-01A LUCAS 60,250TRC ALL
Lock Sequencer TY2047-02A LUCAS 60,250 TRC ALL
Lock Sequencer TY2047-03A LUCAS 60,250 TRC ALL
Lock Sequencer TY2047-03B LUCAS 60,250 TRC ALL
Tertiary Lock TY2037-02A LUCAS 1,500 TRC ALL
Tertiary Lock TY2138-01B LUCAS 13,100 TRC ALL
Isolation Control Unit TY2041-03A LUCAS 60,250 TRC ALL
Isolation Control Unit TY2041-02B LUCAS 1,932 TRC ALL
NOTE 5: Every time the Thrust Reverser is operated must be considered one Thrust Reverser Cycle (TRC), either in Normal operation or
Power Back operation in the authorized aircraft.
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A2.3 STRUCTURAL MAXIMUM INSPECTION INTERVAL LIMITS

A2.3.1 FATIGUE THRESHOLD LIMIT
The Fatigue Threshold Limits have been established in the basis of the Full Scale Fatigue Test results factored by an appropriate scatter
factor approved by the Regulatory Authorities and establish the initial inspection, in flight cycles, for those SSI’s where inspection is governed
by fatigue concerns.
The threshold are subject to further change as additional fatigue testing results are obtained.
A2.3.2 IMPLEMENTATION OF REVISED AIRWORTHINESS LIMITATIONS
This Section will be used to include the Implementation Plan when an ALI is included or reduced and when one or more aircraft of the fleet have
already reached the ALI value:
A2.3.2.1 NEW AIRWORTHINESS LIMITATION INCLUDED FOR PYLON LINKAGE FITTING
Due to the Damage Tolerance Analysis reassessment, some new ALIs were included. So, in order to allow the aircraft operation with this
new limitation, the following implementation plan (see Table below) should be used to bridge these new limitations into operators’
maintenance plan.
The instructions herein mentioned, should be used for all operators to bridge a new Airworthiness Limitation Requirement addressed to SSI
54-50-05, located in zones 414/424, into their Maintenance Plan approved by Local Regulatory Authorities.
- SSI 54-50-05 - Zone 414 / 424
- MPG Task Number: 54-50-00-220-808-L00
Accumulated Flight Cycles

1st Inspection 2nd Inspection Next Inspections
(FCacc) (Note A)
Until 4713 FC 4713 FC (Note B) 9426 FC Repeat interval (Note C)
4713 FC to 6284 FC Next 400 FC 9426 FC Repeat interval (Note C)
6285 FC to 6634 FC 6684 FC 9426 FC Repeat interval (Note C)
NOTE A: Accumulated flight cycles since the beginning of the aircraft operation.
NOTE B: If 1st Inspection - FCacc < 400 FC, so 1st Inspection is FCacc + 400 FC.
NOTE C: Inspection Interval from task 54-50-00-220-808-L00.
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A2.3.3 INSPECTION INTERVAL LIMIT
The inspection interval limits are considered Airworthiness Limitations and were defined per Damage Tolerance Analysis and establish the maximum
escalation limits due to fatigue considerations, allowed for the inspection intervals presented in the baseline program.
These Airworthiness Limitations are defined according to the Damage Tolerance Analysis and establish the maximum escalation limits allowed for the
inspection intervals presented in the baseline program.
The Legacy BJ – MPG Report Section 2 outlines the initial minimum scheduled maintenance requirements for the aircraft structure, including all the
SSI’s. This baseline program provides accidental, environmental and fatigue damage detection opportunity for the entire airframe and, therefore,
these maintenance actions are to be used as the current interval limits.
The additional information presented herein is to be considered in conjunction with the baseline program, in order to determine the ultimate inspection
interval limits necessary to guarantee an adequate fatigue damage detection. Therefore, any escalation to the baseline program can be done
according to the rules from Section 1 - Item 4. General Rules, but without exceeding the limits defined herein.
Pre-Mod SB Pos-Mod SB
145LEG-00-0007 145LEG-00-0007
SSI ZONE TYPE SIDE TASK EFFECT Fatigue

Inspection Threshold Inspection
Threshold
Interval Limit Interval Limit Interval Limit
Limit
(Flight Cycles) (Flight Cycles) (Flight Cycles)
(Flight Cycles)
53-10-19 a 223/224 SDE INT 53-12-00-250-804-L00 L600 7,380 1,843 - -
PRE-MOD SB
145LEG-53-0021 b c d e f g h i j k
53-10-19 a 223/224 SDE INT 53-12-00-250-804-L02 L600 - - 5,560 1,160
PRE-MOD SB
145LEG-53-0021 b c d e f g h i j k
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a - SSI Nº - SSI numbering as defined in 4.6 - List of Structural Significant Items (SSIs);
b - SSI Nº - Additional space for information regarding the SSIs configuration. It is represented by the use of the configuration control number L00,
L01, L02;
c - Zone - Aircraft zone where the SSI is located;
d - Type - Inspection method defined by the Damage Tolerance Analysis. The inspection interval is based on the inspection method analysis and
definition;
e - Side - The side where the limitation is obtained by crack propagation analysis (Damage Tolerance Analysis);
f - Task - Requirement covering each SSI stated in this Appendix. They are found in Section 02 (Scheduled Maintenance Requirements - List of
Requirements);
g - Effectivity - Corresponds to the aircraft version covered by MPG-1483;
h - Fatigue Threshold Limit (Pre-Mod SB 145LEG-00-0007) - As defined in A2.3.1, established in Flight Cycles. The symbol "-" indicates that such
fatigue limitation or threshold is not applicable for that specific line;
I - Inspection Interval Limit (Pre-Mod SB 145LEG-00-0007) - As defined in A2.3.2, established in Flight Cycles. The symbol "-" indicates that such
fatigue limitation or threshold is not applicable for that specific line;
J - Fatigue Threshold Limit (Pos-Mod SB 145LEG-00-0007 or with an equivalent modification factory-incorporated) - As defined in A2.3.1,
established in Flight Cycles. The symbol "-" indicates that such fatigue limitation or threshold is not applicable for that specific line;
k - Inspection Interval Limit (Pos-Mod SB 145LEG-00-0007 or with an equivalent modification factory-incorporated) - As defined in A2.3.2,
established in Flight Cycles. The symbol "-" indicates that such fatigue limitation or threshold is not applicable for that specific line.
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145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
52-10-01 811 DET EXT 52-10-00-220-C01-L00 L600 - 10000 - 8066
52-10-01 811 DET INT 52-10-00-220-C02-L00 L600 - 10000 - 8066
52-10-02 811 DET EXT 52-10-00-220-803-L00 L600 - 10000 - 10000
52-10-02 811 DET INT 52-10-00-220-802-L00 L600 - 10000 - 10000
52-10-03 811 DET EXT 52-10-00-220-804-L00 L600 - 2502 - -
52-10-03 811 DET INT 52-10-00-220-801-L00 L600 - 10000 - 4592
52-10-04 811 DET INT 52-10-00-220-801-L00 L600 - 10000 - 10000
52-10-05 811 DET EXT 52-10-00-220-803-L00 L600 - 10000 - 10000
52-10-05 811 DET INT 52-10-00-220-802-L00 L600 - 10000 - 10000
52-21-06 812/822 DET EXT 52-21-00-220-801-L00 L600 - 5060 - 5060
52-21-06 812/822 DET INT 52-21-00-220-802-L00 L600 - 10000 - 10000
52-21-07 812/822 DET EXT 52-21-00-220-801-L00 L600 - 6060 - 6060
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145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
52-21-07 812/822 DET INT 52-21-00-220-802-L00 L600 - 10000 - 10000
52-30-08 813 GVI EXT 52-30-00-210-C01-L00 L600 - 8026 - 4392
52-30-08 813 GVI INT 52-30-00-210-801-L00 L600 - - - 4392
52-30-09 813 DET INT 52-30-00-220-801-L00 L600 - 3200 - -
52-30-09 813 DET INT 52-30-00-220-801-L01 L600 - - - 2188
53-10-07 113/114 DET INT 53-11-00-220-C02-L00 L600 - 10000 - 10000
53-10-07 123/124 DET INT 53-12-00-220-805-L00 L600 - 10000 - 8200
53-10-07 213/214 DET INT 53-11-00-220-801-L00 L600 - 10000 - 10000
53-10-07 223/224 DET INT 53-12-00-220-807-L00 L600 - 10000 - 8200
53-10-07 225/226 DET INT 53-12-00-220-C01-L00 L600 - 10000 - 8200
53-10-08 123/124 DET INT 53-12-00-220-805-L00 L600 - 10000 - 10000
53-10-08 213/214 DET INT 53-11-00-220-C04-L00 L600 - 10000 - 10000
53-10-08 223/224 DET INT 53-12-00-220-807-L00 L600 - 10000 - 10000
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Threshold
Limit
(Flight Cycles)
53-10-14 113/114 DET INT 53-11-00-220-C03-L00 L600 - 10000 - 10000
53-10-14 123/124 DET INT 53-12-00-220-C02-L00 L600 - 10000 - 10000
53-10-14 213/214 DET INT 53-11-00-220-C03-L00 L600 - 10000 - 10000
53-10-14 223/224 DET INT 53-12-00-220-C02-L00 L600 - 10000 - 10000
53-10-14 225/226 DET INT 53-12-00-220-C02-L00 L600 - 10000 - 10000
53-10-15 113/114 GVI EXT 53-11-00-210-C02-L00 L600 - 10000 - 10000
53-10-15 113/114 DET INT 53-11-00-220-C03-L00 L600 - 10000 - 10000
53-10-15 123/124 GVI EXT 53-12-00-210-C02-L00 L600 - 10000 - 10000
53-10-15 123/124 DET INT 53-12-00-220-805-L00 L600 - 10000 - 10000
53-10-15 213/214 GVI EXT 53-11-00-210-C02-L00 L600 - 10000 - 10000
53-10-15 213/214 DET INT 53-11-00-220-C03-L00 L600 - 10000 - 10000
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Threshold
Limit
(Flight Cycles)
53-10-15 223/224 GVI EXT 53-12-00-210-C02-L00 L600 - 10000 - 10000
53-10-15 223/224 DET INT 53-12-00-220-C04-L00 L600 - 10000 - 10000
53-10-17 223/224 DET INT 53-12-00-220-801-L00 L600 - 4400 - 4400
53-10-17 225/226 DET INT 53-12-00-220-801-L00 L600 - 4400 - 4400
53-10-18 223/224 DET INT 53-12-00-220-801-L00 L600 10000 10000 10000 10000
53-10-18 225/226 GVI INT 53-12-00-220-801-L00 L600 - 10000 - 10000
53-10-19 221/222 DET INT 53-12-00-220-802-L00 L600 - - - 10000
53-10-19 221/222 GVI INT 53-12-00-220-802-L00 L600 - 10000 - -
53-10-19 223/224 SDE INT 53-12-00-250-804-L00 L600 7382 1843 - -
PRE-MOD SB
145LEG-53-0021
53-10-19 223/224 SDE INT 53-12-00-250-804-L01 L600 - 8019 - -
POS-MOD SB
145LEG-53-0021
53-10-19 223/224 SDE INT 53-12-00-250-804-L02 L600 - - 5661 1165
PRE-MOD SB
145LEG-53-0021
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Threshold
Limit
(Flight Cycles)
53-10-19 223/224 SDE INT 53-12-00-250-804-L03 L600 - - 5660 4931
POS-MOD SB
145LEG-53-0021
53-10-20 223/224 DET INT 53-12-00-220-803-L00 L600 10000 10000 10000 10000
53-10-20 223/224 SDE EXT 53-12-00-250-805-L00 L600 7000 10000 - -
PRE-MOD SB
145LEG-53-0030
53-10-20 223/224 SDE EXT 53-12-00-250-806-L00 L600 - - 6000 6212
PRE-MOD SB
145LEG-53-0030
53-10-20 223/224 SDE INT 53-12-00-250-807-L00 L600 7000 3151 - -
PRE-MOD SB
145LEG-53-0030
53-10-20 223/224 SDE INT 53-12-00-250-808-L00 L600 - - 6000 1969
PRE-MOD SB
145LEG-53-0030
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145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
53-10-20 223/224 SDE EXT 53-12-00-250-809-L00 L600 6915 3247 - -
POST-MOD SB
145LEG-53-0030
53-10-20 223/224 SDE EXT 53-12-00-250-810-L00 L600 - - 4170 2011
POST-MOD SB
145LEG-53-0030
53-10-21 223/224 GVI EXT 53-12-00-210-C04-L00 L600 - 10000 - 7234
53-10-21 223/224 GVI INT 53-12-00-210-801-L00 L600 - 10000 - 7234
53-10-22 223/224 GVI INT 53-12-00-220-803-L00 L600 - 10000 - 10000
53-10-23 113/114 GVI INT 53-11-00-210-C01-L00 L600 - 10000 - 10000
53-10-24 113/114 DET EXT 53-11-00-220-C05-L00 L600 - 10000 - 10000
53-10-24 113/114 DET INT 53-11-00-220-C06-L00 L600 - 10000 - 10000
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Threshold
Limit
(Flight Cycles)
53-10-25 113/114 SDE INT 53-11-00-250-801-L00 L600 - 10000 - 10000
53-10-26 115/116 DET INT 53-12-00-220-804-L00 L600 - 10000 - 10000
53-10-26 121/122 DET INT 53-12-00-220-804-L00 L600 - 10000 - 10000
53-10-26 215/216 DET INT 53-12-00-220-804-L00 L600 - 10000 - 10000
53-10-26 221/222 DET INT 53-12-00-220-804-L00 L600 10000 8234 10000 7130
53-10-27 123/124 DET INT 53-12-00-220-C03-L00 L600 - 10000 - -
53-10-27 123/124 DET INT 53-12-00-220-809-L00 L600 - - - 6506
53-10-43 113/114 DET INT 53-11-00-220-C03-L00 L600 - 10000 - 10000
53-10-43 123/124 DET INT 53-12-00-220-C02-L00 L600 - 10000 - 10000
53-10-43 213/214 DET INT 53-11-00-220-C03-L00 L600 - 10000 - 10000
53-10-43 223/224 DET INT 53-12-00-220-C02-L00 L600 - 10000 - 9958
53-10-43 225/226 DET INT 53-12-00-220-C02-L00 L600 - 10000 - 10000
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Threshold
Limit
(Flight Cycles)
53-10-44 113/114 GVI INT 53-11-00-210-C01-L00 L600 - 10000 - 10000
53-10-45 113/114 GVI INT 53-11-00-210-C01-L00 L600 - 10000 - 10000
53-10-46 113/114 GVI INT 53-11-00-210-C01-L00 L600 - 10000 - 10000
53-10-49 123/124 DET INT 53-12-00-220-C03-L00 L600 - 10000 - 10000
53-20-01 231 DET EXT 53-21-00-220-802-L00 L600 - 9330 - 5000
53-20-01 231 DET INT 53-21-00-220-803-L00 L600 - 9215 - 4000
53-20-04 231/232 GVI INT 53-21-00-210-C02-L00 L600 - 10000 - 10000
53-20-06 231/232 DET EXT 53-21-00-220-808-L00 L600 - 3066 - 2300
53-20-06 241/242 GVI INT 53-22-00-220-807-L00 L600 - 4231 - 6012
53-20-06 251/252 SDE EXT 53-23-00-250-801-L00 L600 10000 3999 - -
53-20-06 251/252 GVI INT 53-23-00-210-C02-L00 L600 - 10000 - 10000
53-20-07 131/132 DET EXT 53-21-00-220-818-L00 L600 - 1930 - 2210
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Threshold
Limit
(Flight Cycles)
53-20-07 131/132 DET INT 53-21-00-220-812-L00 L600 - 5000 - 5000
53-20-07 141/142 GVI INT 53-22-00-220-802-L00 L600 - 7670 - 6549
53-20-07 151/152 DET EXT 53-23-00-220-809-L00 L600 - 2391 - -
53-20-07 151/152 GVI EXT 53-23-00-220-C04-L00 L600 - - - 6026
53-20-07 151/152 DET INT 53-23-00-220-C01-L00 L600 - 8786 - 8777
53-20-07 153/154 DET EXT 53-23-00-220-809-L00 L600 - 2391 - -
53-20-07 153/154 GVI EXT 53-23-00-220-C04-L00 L600 - - - 6026
53-20-07 153/154 DET INT 53-23-00-220-C01-L00 L600 - 8786 - 8777
53-20-07 161/162 DET EXT 53-24-00-220-805-L00 L600 10000 2758 10000 2004
53-20-07 231/232 DET EXT 53-21-00-220-818-L00 L600 - 1930 - 2210
53-20-07 231/232 DET INT 53-21-00-220-804-L00 L600 - 5000 - 5000
53-20-07 233/234 DET EXT 53-21-00-220-818-L00 L600 - 1930 - 2210
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Threshold
Limit
(Flight Cycles)
53-20-07 233/234 DET INT 53-21-00-220-804-L00 L600 - 5000 - 5000
53-20-07 241/242 GVI INT 53-22-00-220-802-L00 L600 - 7670 - 6549
53-20-07 243/244 GVI INT 53-22-00-220-802-L00 L600 - 7670 - 6549
53-20-07 251/252 DET EXT 53-23-00-220-808-L00 L600 - 2391 - -
53-20-07 251/252 GVI EXT 53-23-00-220-808-L01 L600 - - - 6026
53-20-07 251/252 DET INT 53-23-00-220-806-L00 L600 - 8786 - 8777
53-20-07 253/254 DET EXT 53-23-00-220-808-L00 L600 - 2391 - -
53-20-07 253/254 GVI EXT 53-23-00-220-808-L01 L600 - - - 6026
53-20-07 253/254 DET INT 53-23-00-220-802-L00 L600 - 8786 - 8777
53-20-07 261/262 DET EXT 53-24-00-220-805-L00 L600 10000 2758 10000 2004
53-20-07 263/264 DET EXT 53-24-00-220-805-L00 L600 10000 2758 10000 2004
53-20-08 131/132 DET INT 53-21-00-220-814-L00 L600 10000 1500 10000 1500
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Threshold
Limit
(Flight Cycles)
53-20-08 141/142 GVI INT 53-22-00-220-804-L00 L600 - 9332 - 5305
53-20-08 161/162 GVI INT 53-24-00-220-802-L00 L600 - 8517 - 8517
53-20-08 231/232 DET INT 53-21-00-220-814-L00 L600 10000 1500 10000 1500
53-20-08 233/234 DET INT 53-21-00-220-814-L00 L600 10000 1500 10000 1500
53-20-08 241/242 GVI INT 53-22-00-220-804-L00 L600 - 9332 - 5305
53-20-08 251/252 GVI INT 53-23-00-220-C03-L00 L600 - 9653 - 9653
53-20-08 261/262 GVI INT 53-24-00-220-802-L00 L600 - 8517 - 8517
53-20-08 263/264 GVI INT 53-24-00-220-802-L00 L600 - 8517 - 8517
53-20-09 231 DET EXT 53-21-00-220-801-L00 L600 - 8986 - 5000
53-20-09 231 DET INT 53-21-00-220-810-L00 L600 - 6457 - 5000
53-20-11 131/132 DET INT 53-21-00-220-C01-L00 L600 - 10000 10000 9900
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Threshold
Limit
(Flight Cycles)
53-20-11 141/142 DET INT 53-22-00-220-C01-L00 L600 - 10000 - 10000
53-20-11 151/152 DET INT 53-23-00-220-811-L00 L600 - 8601 - -
53-20-11 151/152 DET INT 53-23-00-220-811-L01 L600 - - - 5425
53-20-11 153/154 DET INT 53-23-00-220-811-L00 L600 - 8601 - -
53-20-11 153/154 DET INT 53-23-00-220-811-L01 L600 - - - 5425
53-20-11 161/162 DET INT 53-24-00-220-C02-L00 L600 - 10000 - 10000
53-20-12 231 DET EXT 53-21-00-220-807-L00 L600 - 3423 - 5000
53-20-12 231 DET INT 53-21-00-220-805-L00 L600 - 6600 - 5000
53-20-14 141/142 GVI INT 53-22-00-220-802-L00 L600 - 4501 - 10000
53-20-14 161/162 DET INT 53-24-00-220-803-L00 L600 10000 4561 10000 3373
53-20-14 241/242 GVI INT 53-22-00-220-802-L00 L600 - 4501 - 10000
53-20-14 243/244 GVI INT 53-22-00-220-802-L00 L600 - 4501 - 10000
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Threshold
Limit
(Flight Cycles)
53-20-14 261/262 DET INT 53-24-00-220-803-L00 L600 10000 4561 10000 3373
53-20-14 263/264 DET INT 53-24-00-220-803-L00 L600 10000 4561 10000 3373
53-20-16 251/252 GVI EXT 53-23-00-210-804-L00 L600 - 4682 - 10000
53-20-16 251/252 GVI INT 53-23-00-210-801-L00 L600 - 10000 - 10000
53-20-30 151/152 GVI INT 53-23-00-220-801-L00 L600 - - - 8785
53-20-30 153/154 GVI INT 53-23-00-220-801-L00 L600 - - - 8785
53-20-30 251/252 GVI INT 53-23-00-220-806-L00 L600 - - - 8785
53-20-30 253/254 GVI INT 53-23-00-220-801-L00 L600 - - - 8785
53-20-41 231 DET INT 53-21-00-220-811-L00 L600 - 6667 - 5000
53-20-43 141/142 GVI INT 53-22-00-220-802-L00 L600 - 7670 - 6549
53-20-43 151/152 GVI INT 53-23-00-220-805-L00 L600 - 9653 - 10000
53-20-43 153/154 GVI INT 53-23-00-220-805-L00 L600 - 9653 - 10000
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 205
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
53-20-43 241/242 GVI INT 53-22-00-220-802-L00 L600 - 7670 - 6549
53-20-43 243/244 GVI INT 53-22-00-220-802-L00 L600 - 7670 - 6549
53-20-43 251/252 GVI INT 53-23-00-220-806-L00 L600 - 9653 - 10000
53-20-43 253/254 GVI INT 53-23-00-220-804-L00 L600 - 9653 - 10000
53-20-51 251/252 DET EXT 53-23-00-220-803-L00 L600 - 3849 - -
53-20-51 251/252 GVI EXT 53-23-00-220-803-L00 L600 - - - 10000
53-20-51 251/252 GVI INT 53-23-00-220-806-L00 L600 - 8361 - 8793
53-20-79 141/142 GVI INT 53-22-00-210-803-L00 L600 - 4739 - 10000
53-20-79 231/232 DET EXT 53-22-00-220-808-L00 L600 - 6600 - 5000
53-20-79 231/232 DET INT 53-21-00-220-813-L00 L600 - 6375 - 5100
53-20-79 241/242 GVI INT 53-22-00-210-803-L00 L600 - 4739 - 10000
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 206
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
53-20-80 141/142 GVI INT 53-22-00-210-803-L00 L600 - 4739 - 10000
53-20-80 241/242 GVI INT 53-22-00-210-803-L00 L600 - 4739 - 10000
53-20-81 197 GVI EXT 53-22-00-210-806-L00 L600 - 10000 - 10000
53-20-81 197 GVI INT 53-22-00-210-805-L00 L600 - 10000 - 10000
53-20-82 231/232 GVI EXT 53-21-00-220-816-L00 L600 - 10000 - 10000
53-20-82 241/242 GVI EXT 53-22-00-220-806-L00 L600 - 10000 - 10000
53-20-83 241/242 GVI EXT 53-22-00-220-806-L00 L600 - 10000 - 10000
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 207
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
53-30-03 271 GVI INT 53-31-00-210-802-L00 L600 - 6841 - 5321
53-30-07 171/172 GVI EXT 53-31-00-210-807-L00 L600 DELETED
53-30-07 171/172 DET EXT 53-31-00-220-821-L00 L600 10000 10000 10000 10000
53-30-07 171/172 DET INT 53-31-00-220-C02-L00 L600 10000 10000 10000 10000
53-30-07 271/272 GVI INT 53-31-00-210-811-L00 L600 10000 10000 10000 10000
53-30-07 271/272 GVI INT 53-31-00-220-810-L00 L600 DELETED
53-30-07 271/272 DET EXT 53-31-00-220-821-L00 L600 10000 10000 10000 10000
53-30-07 273/274 DET EXT 53-31-00-220-821-L00 L600 10000 10000 10000 10000
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 208
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
53-30-07 273/274 SDE EXT 53-31-00-250-804-L00 L600 10000 2907 10000 2907
53-30-07 273/274 SDE EXT 53-31-00-270-801-L00 L600 DELETED
53-30-07 311/312 GVI EXT 53-32-00-210-C01-L00 L600 - 10000 - 10000
53-30-07 311/312 GVI INT 53-32-00-210-C02-L00 L600 - 10000 - 10000
53-30-08 171/172 DET INT 53-31-00-220-807-L00 L600 10000 6842 10000 5131
53-30-08 271/272 DET INT 53-31-00-220-807-L00 L600 10000 6842 10000 5131
53-30-08 273/274 DET INT 53-31-00-220-807-L00 L600 10000 6842 10000 5131
53-30-08 311/312 GVI INT 53-32-00-210-C02-L00 L600 - 10000 - 10000
53-30-14 171/172 DET INT 53-31-00-220-807-L00 L600 - 7663 - 5747
53-30-14 271/272 DET INT 53-31-00-220-807-L00 L600 - 7663 - 5747
53-30-14 273/274 DET INT 53-31-00-220-807-L00 L600 - 7663 - 5747
53-30-14 311/312 GVI INT 53-32-00-210-C02-L00 L600 - 10000 - 10000
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 209
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
53-30-15 171/172 GVI INT 53-31-00-210-811-L00 L600 10000 10000 10000 10000
53-30-15 171/172 DET EXT 53-31-00-220-821-L00 L600 10000 10000 10000 10000
53-30-15 271/272 GVI INT 53-31-00-210-811-L00 L600 10000 10000 10000 10000
53-30-15 271/272 DET EXT 53-31-00-220-821-L00 L600 10000 10000 10000 10000
53-30-15 273/274 GVI INT 53-31-00-210-811-L00 L600 10000 10000 10000 10000
53-30-15 273/274 SDE EXT 53-31-00-250-806-L00 L600 10000 2907 10000 2907
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 210
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
53-30-28 171/172 DET INT 53-31-00-220-801-L00 L600 - 9900 - 9900
53-30-29 171/172 DET EXT 53-31-00-220-C04-L00 L600 10000 6140 - -
53-30-29 171/172 SDE INT 53-31-00-250-801-L00 L600 - - - 10000
53-30-30 171/172 GVI INT 53-31-00-210-811-L00 L600 10000 10000 10000 10000
53-30-30 171/172 DET EXT 53-31-00-220-821-L00 L600 10000 10000 10000 10000
53-30-30 271/272 GVI INT 53-31-00-210-811-L00 L600 10000 10000 10000 10000
53-30-30 271/272 DET EXT 53-31-00-220-821-L00 L600 10000 10000 10000 10000
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 211
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
53-30-30 273/274 GVI INT 53-31-00-210-811-L00 L600 10000 10000 10000 10000
53-30-30 273/274 SDE EXT 53-31-00-250-806-L00 L600 10000 2907 10000 2907
53-30-30 273/274 SDE EXT 53-31-00-270-807-L00 L600 Pre-Mod SB DELETED Pos-Mod SB
53-30-30 311/312 DET INT 53-32-00-220-802-L00 L600 145LEG-00-0007
- 10000 -145LEG-00-0007
10000
53-30-35
SSI 271/272
ZONE DET
TYPE INT 53-31-00-220-810-L00
SIDE TASK L600
EFFECT Fatigue
10000 10000 10000 10000
Threshold
53-30-36 171/172 DET INT 53-31-00-220-804-L00 L600 Interval Limit Interval
DELETED Limit Interval Limit
Limit
53-30-36 171/172 SDE INT 53-31-00-270-803-L00 L600 (Flight Cycles) DELETED
53-30-36 271/272
275/276 DET INT 53-31-00-220-810-L00
53-31-00-220-820-L00 L600 10000 10000 DELETED10000 10000
53-30-36 271/272
275/276 SDE INT 53-31-00-270-803-L00
53-31-00-250-805-L00 L600 10000 3105 DELETED10000 3105
53-30-36 273/274 DET INT 53-31-00-220-814-L00 L600 DELETED
53-30-36 273/274
311/312 SDE
DET INT 53-31-00-270-803-L00
53-32-00-220-C01-L00 L600 - 8779 DELETED - 8779
53-30-38 311/312 DET INT 53-32-00-220-801-L00 L600 - 10000 - 10000
53-30-39 311/312 GVI INT 53-32-00-210-C02-L00 L600 - 10000 - 10000
53-30-40 313 GVI INT 53-32-00-210-801-L00 L600 - 10000 - 10000

------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
This document 53-30-43 is property of171/172 AC Aviation Co., DETLtd. DoINT not Copied or distributed without company
53-31-00-220-C01-L00 allowed. Doc. 10000
L600 Ref: ACA-ENG-MP-DID
10000 10000 10000
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 212
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
53-30-43 273/274 SDE INT 53-31-00-270-804-L00 L600 DELETED
53-30-43 311/312 GVI INT 53-32-00-220-C02-L00 L600 - 10000 - 10000
53-30-48 271 GVI INT 53-31-00-210-803-L00 L600 - 7229 - 7229
53-30-48 271 SDE EXT 53-31-00-250-802-L00 L600 10000 2465 10000 2465
53-31-00-250-803-L00
53-30-49 272 GVI INT 53-31-00-210-804-L00 L600 10000 10000 - -
53-30-49 272 GVI INT 53-31-00-210-804-L01 L600 - - 10000 7229
53-30-49 272 DET EXT 53-31-00-220-809-L00 L600 10000 3143 7229 3118
53-30-50 311/312 GVI EXT 53-32-00-210-802-L00 L600 - 10000 - 10000
53-30-50 311/312 DET INT 53-32-00-220-804-L00 L600 - 8193 - 8193
53-30-53 315/316 DET EXT 53-32-00-220-803-L00 L600 - 10000 - 10000
53-30-53 317/318 DET EXT 53-32-00-220-803-L00 L600 - 10000 - 10000
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 213
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
53-30-55 171/172 GVI EXT 53-31-00-220-802-L00 L600 - 10000 - 10000
53-30-55 171/172 GVI INT 53-31-00-220-805-L00 L600 10000 10000 10000 10000
53-30-56 171/172 GVI INT 53-31-00-210-801-L00 L600 - 6555 - 6555
53-30-56 271/272 GVI INT 53-31-00-210-801-L00 L600 - 6555 - 6555
53-30-56 273/274 GVI INT 53-31-00-210-801-L00 L600 - 6555 - 6555
54-50-01 414/424 DET INT 54-50-00-220-803-L00 L600 - 2375 - 2375
54-50-02 414/424 DET INT 54-50-00-220-C01-L00 L600 - 10000 - 10000
54-50-03 414/424 DET INT 54-50-00-220-802-L00 L600 - 1000 - 1000
54-50-04 414/424 GVI EXT 54-50-00-210-801-L00 L600 - 10000 - 10000
54-50-05 414/424 DET INT 54-50-00-220-808-L00 L600 - 4713 - 4713
54-50-05 414/424 DET INT 54-50-00-220-809-L00 L600 10000 1130 10000 1130
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 214
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
54-50-05 414/424 DET INT 54-50-00-220-C02-L00 L600 - 10000 - 10000
54-50-06 414/424 SDE INT 54-50-00-250-802-L00 L600 - 3661 - 3661
PRE MOD SB
145LEG-54-0001
54-50-06 414/424 SDE INT 54-50-00-250-802-L01 L600 - 5360 - 5360
POST MOD SB
145LEG-54-0001
54-50-07 414/424 DET INT 54-50-00-220-806-L00 L600 - 1000 - 1000
55-10-01 333/334 SDE EXT 55-10-00-250-805-L00 L600 4680 3130 4680 3130
55-10-02 333/334 SDE EXT 55-10-00-250-806-L00 L600 - 4275 - 4275
55-10-03 333/334 DET EXT 55-10-00-220-810-L00 L600 - 3244 - 3244
55-10-04 333/334 DET INT 55-10-00-220-811-L00 L600 8462 3657 8462 3657
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 215
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
55-10-05 333/334 DET INT 55-10-00-220-811-L00 L600 8462 3657 8462 3657
55-10-06 333/334 SDE EXT 55-10-00-250-807-L00 L600 4680 3130 4680 3130
55-10-07 333/334 GVI EXT 55-10-00-210-802-L00 L600 - 10000 - 10000
55-10-08 333/334 GVI EXT 55-10-00-220-C02-L00 L600 - 10000 - 10000
55-10-09 333/334 SDE EXT 55-10-00-250-808-L00 L600 4904 1134 4904 1134
55-10-10 333/334 DET INT 55-10-00-220-812-L00 L600 2600 1370 2600 1370
55-10-11 333/334 SDE EXT 55-10-00-250-809-L00 L600 4904 1134 4904 1134
55-10-11 333/334 DET INT 55-10-00-220-809-L00 L600 3972 3252 3972 3252
55-10-12 333/334 SDE EXT 55-10-00-250-810-L00 L600 4904 1134 4904 1134
55-10-13 333/334 DET INT 55-10-00-220-C01-L00 L600 - 9171 - 9171
55-10-14 337 GVI EXT 55-10-00-210-805-L00 L600 - 10000 - 10000
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 216
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
55-10-15 333/334 DET EXT 55-10-00-220-801-L00 L600 - 10000 - 9171
55-10-16 337 DET INT 55-10-00-220-806-L00 L600 4275 3360 4275 3360
55-10-17 337 DET INT 55-10-00-220-804-L00 L600 8462 3657 8462 3657
55-10-18 337 DET INT 55-10-00-220-806-L00 L600 4000 2607 4000 2607
55-10-19 337 DET INT 55-10-00-220-806-L00 L600 4000 2607 4000 2607
55-10-20 337 DET INT 55-10-00-220-806-L00 L600 4000 2607 4000 2607
55-10-21 337 DET EXT 55-10-00-220-802-L00 L600 - 10000 - 10000
55-10-22 337 GVI EXT 55-10-00-210-C01-L00 L600 - 10000 - 10000
55-10-23 337 GVI EXT 55-10-00-210-C02-L00 L600 - 10000 - 10000
55-10-24 337 SDE EXT 55-10-00-240-801-L00 L600 - 10000 - 10000
55-20-25 335/336 GVI INT 55-20-00-210-C02-L00 L600 - 10000 - 10000
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 217
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
55-20-26 335/336 GVI EXT 55-20-00-210-C01-L00 L600 - 10000 - 10000
55-20-27 335/336 GVI INT 55-20-00-210-C02-L00 L600 - 10000 - 10000
55-20-28 335/336 GVI EXT 55-20-00-210-C01-L00 L600 - 10000 - 10000
55-20-29 335/336 DET INT 55-20-00-220-C01-L00 L600 - 10000 - 10000
55-20-30 335/336 DET INT 55-20-00-220-C01-L00 L600 - 10000 - 10000
55-20-31 335/336 DET INT 55-20-00-290-C01-L00 L600 - 10000 - 10000
55-20-32 335/336 DET INT 55-20-00-290-C01-L00 L600 - 10000 - 10000
55-20-33 335/336 DET INT 55-20-00-220-C01-L00 L600 - 10000 - 10000
55-20-34 335/336 DET INT 55-20-00-220-801-L00 L600 - 5000 - 5000
55-20-35 335/336 DET INT 55-20-00-220-801-L00 L600 - 5000 - 5000
55-20-36 335/336 DET EXT 55-20-00-220-802-L00 L600 - 4000 - 4000
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 218
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
55-20-37 335/336 GVI EXT 55-20-00-210-C03-L00 L600 - 10000 - 10000
55-20-90 335/336 GVI INT 55-20-00-210-801-L00 L600 - 1000 - 1000
55-30-38 324 GVI EXT 55-30-00-210-C05-L00 L600 - 10000 - 10000
55-30-39 325 GVI EXT 55-30-00-210-C02-L00 L600 - 10000 - 10000
55-30-40 324 GVI EXT 55-30-00-210-C05-L00 L600 - 10000 - 10000
55-30-41 325 GVI EXT 55-30-00-210-C02-L00 L600 - 10000 - 10000
55-30-42 324 GVI EXT 55-30-00-210-C05-L00 L600 - 10000 - 10000
55-30-43 325 GVI EXT 55-30-00-210-C02-L00 L600 - 10000 - 10000
55-30-44 324 GVI EXT 55-30-00-210-C01-L00 L600 - 10000 - 10000
55-30-45 325 GVI EXT 55-30-00-210-C02-L00 L600 - 10000 - 10000
55-30-46 324 GVI EXT 55-30-00-210-C05-L00 L600 - 10000 - 10000
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 219
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
55-30-47 325 GVI EXT 55-30-00-210-C03-L00 L600 - 10000 - 10000
55-30-48 325 GVI EXT 55-30-00-210-C02-L00 L600 - 10000 - 10000
55-30-49 325 GVI EXT 55-30-00-210-C02-L00 L600 - 10000 - 10000
55-30-50 325 GVI INT 55-30-00-220-C05-L00 L600 - 10000 - 10000
55-30-51 325 GVI INT 55-30-00-220-C05-L00 L600 - 10000 - 10000
55-30-52 325 GVI INT 55-30-00-220-C05-L00 L600 - 10000 - 10000
55-30-53 324 GVI INT 55-30-00-220-C03-L00 L600 - 10000 - 10000
55-30-54 325 DET INT 55-30-00-220-805-L00 L600 - 10000 - 10000
55-30-55 325 DET INT 55-30-00-220-806-L00 L600 - 10000 - 10000
55-30-56 325 DET INT 55-30-00-220-806-L00 L600 - 10000 - 10000
55-30-57 324 DET INT 55-30-00-220-807-L00 L600 - 10000 - 10000
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 220
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
55-30-58 324 DET INT 55-30-00-220-802-L00 L600 - 10000 - 10000
55-30-59 324 DET INT 55-30-00-220-802-L00 L600 - 10000 - 10000
55-30-60 325 DET INT 55-30-00-220-805-L00 L600 - 10000 - 10000
55-30-61 325 DET INT 55-30-00-220-805-L00 L600 - 10000 - 10000
55-30-62 325 DET INT 55-30-00-220-805-L00 L600 - 10000 - 10000
55-30-63 325 GVI INT 55-30-00-220-806-L00 L600 - 10000 - 10000
55-30-64 325 GVI INT 55-30-00-220-806-L00 L600 - 10000 - 10000
55-30-65 325 GVI INT 55-30-00-220-806-L00 L600 - 10000 - 10000
55-30-66 325 GVI INT 55-30-00-220-805-L00 L600 - 10000 - 10000
55-30-67 324 GVI INT 55-30-00-210-802-L00 L600 - 10000 - 10000
55-30-68 324 GVI INT 55-30-00-210-802-L00 L600 - 10000 - 10000
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 221
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
55-30-79 325 DET INT 55-30-00-220-806-L00 L600 - 10000 - 10000
55-30-80 325 DET INT 55-30-00-220-806-L00 L600 - 10000 - 10000
55-40-81 326 GVI EXT 55-40-00-210-C01-L00 L600 - 10000 - 10000
55-40-81 326 DET INT 55-40-00-220-C01-L00 L600 - 10000 - 10000
55-40-82 326 GVI EXT 55-40-00-210-C01-L00 L600 - 10000 - 10000
55-40-82 326 DET INT 55-40-00-220-C01-L00 L600 - 10000 - 10000
55-40-83 326 GVI EXT 55-40-00-210-C01-L00 L600 - 10000 - 10000
55-40-83 326 DET INT 55-40-00-220-C01-L00 L600 - 10000 - 10000
55-40-84 326 GVI EXT 55-40-00-210-C01-L00 L600 - 10000 - 10000
55-40-84 326 DET INT 55-40-00-220-C01-L00 L600 - 10000 - 10000
55-40-85 326 GVI EXT 55-40-00-210-C01-L00 L600 - 5000 - 5000
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 222
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
55-40-85 326 DET INT 55-40-00-220-C01-L00 L600 - 5000 - 5000
55-40-86 327 GVI EXT 55-40-00-210-C02-L00 L600 - 10000 - 10000
55-40-86 327 DET INT 55-40-00-220-C02-L00 L600 - 10000 - 10000
55-40-87 327 GVI EXT 55-40-00-210-C02-L00 L600 - 10000 - 10000
55-40-87 327 DET INT 55-40-00-220-C02-L00 L600 - 10000 - 10000
55-40-88 327 GVI EXT 55-40-00-210-C02-L00 L600 - 10000 - 10000
55-40-88 327 DET INT 55-40-00-220-C02-L00 L600 - 10000 - 10000
55-40-89 327 GVI EXT 55-40-00-210-C02-L00 L600 - 5000 - 5000
55-40-89 327 DET INT 55-40-00-220-C02-L00 L600 - 5000 - 5000
57-10-01 155/156/ DET EXT 57-10-00-220-804-L00 L600 10000 6061 10000 6061
former 157
57-11-15
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 223
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-10-01 155/156/ DET INT 57-10-00-220-805-L00 L600 10000 2381 10000 2381
former 157
57-11-15
57-10-01 155/156/ SDE INT 57-10-00-250-803-L00 L600 10000 4162 10000 4162
157
57-10-02 155/156/ DET EXT 57-10-00-220-801-L00 L600 - 6740 - 4798
157
57-10-02 155/156/ DET INT 57-10-00-220-803-L00 L600 - 6740 - 4798
157
57-10-03 155/156/ DET INT 57-10-00-220-802-L00 L600 3979 2381 3979 2381
157
57-10-04 155/156/ DET INT 57-10-00-220-C01-L00 L600 - 10000 - 10000
157
57-10-05 155/156/ DET INT 57-10-00-220-802-L00 L600 3979 2381 3979 2381
157
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 224
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-10-06 155/156/ DET EXT 57-10-00-220-804-L00 L600 10000 3963 10000 3963
157
57-10-06 155/156/ DET INT 57-10-00-220-805-L00 L600 10000 3963 10000 3963
157
57-10-07 155/156/ DET INT 57-10-00-220-C01-L00 L600 - 10000 - 10000
157
57-10-08 155/156/ DET INT 57-10-00-220-805-L00 L600 10000 3963 10000 3963
157
57-10-09 155/156/ DET EXT 57-10-00-220-C04-L00 L600 - 10000 - 10000
157
57-10-09 155/156/ DET INT 57-10-00-220-C05-L00 L600 - 10000 - 10000
157
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
SECTION : 4
MAINTENANCE PROGRAM
PAGE : 225
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-10-10 155/156/ DET INT 57-10-00-220-C08-L00 L600 - 10000 - 10000
157
57-10-11 155/156/ DET EXT 57-10-00-220-C03-L00 L600 - 10000 - 8332
157
57-10-11 155/156/ DET INT 57-10-00-220-C07-L00 L600 - 10000 - 8332
157
57-10-12 155/156/ DET INT 57-10-00-220-C07-L00 L600 - 10000 - 10000
157
57-10-13 155/156/ DET EXT 57-10-00-220-C02-L00 L600 - 10000 - 10000
157
57-10-13 155/156/ DET INT 57-10-00-220-C06-L00 L600 - 10000 - 10000
157
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145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-10-14 155/156/ GVI EXT 57-10-00-210-C01-L00 L600 - 10000 - 10000
157
57-10-14 155/156/ GVI INT 57-10-00-220-C05-L00 L600 - 10000 - 10000
157
57-10-27 155/156/ GVI EXT 57-10-00-210-801-L00 L600 - 10000 - 10000
157
57-10-27 155/156/ DET INT 57-10-00-220-802-L00 L600 - 10000 - 10000
157
57-11-17 155/156/ DET EXT 57-11-00-220-801-L00 L600 - 10000 - 10000
157
57-11-17 155/156/ SDE INT 57-11-00-250-801-L00 L600 - 10000 - 10000
157
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ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-11-18 155/156/ DET EXT 57-11-00-220-803-L00 L600 10000 6061 10000 6061
157
57-11-18 155/156/ DET INT 57-11-00-220-806-L00 L600 10000 6061 10000 6061
157
57-11-19 155/156/ DET EXT 57-11-00-220-803-L00 L600 - 10000 - 10000
157
57-11-19 155/156/ DET INT 57-11-00-220-805-L00 L600 - 10000 - 10000
157
57-11-20 155/156/ DET EXT 57-11-00-220-803-L00 L600 - 10000 - 10000
157
57-11-20 155/156/1 DET INT 57-11-00-220-806-L00 L600 - 10000 - 10000
57
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145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-11-21 155/156/ DET EXT 57-11-00-220-803-L00 L600 - 10000 - 10000
157
57-11-21 155/156/ DET INT 57-11-00-220-805-L00 L600 - 10000 - 10000
157
57-11-22 155/156/ DET EXT 57-11-00-220-807-L00 L600 10000 10000 10000 7670
157
57-11-23 155/156/ DET EXT 57-11-00-220-807-L00 L600 10000 10000 10000 8084
157
57-11-23 155/156/ DET INT 57-11-00-220-808-L00 L600 10000 10000 10000 8084
157
57-11-24 155/156/ DET EXT 57-11-00-220-807-L00 L600 10000 10000 10000 10000
157
57-11-24 155/156/ DET INT 57-11-00-220-808-L00 L600 - 10000 - 10000
157
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ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-11-25 155/156/ DET EXT 57-11-00-220-801-L00 L600 - 10000 - 10000
157
57-11-25 155/156/ DET INT 57-11-00-220-802-L00 L600 - 10000 - 10000
157
57-21-26 532/632 DET EXT 57-21-00-220-801-L00 L600 - 10000 - 10000
57-21-26 532/632 DET INT 57-21-00-220-807-L00 L600 - 10000 - 10000
57-21-26 551/651 GVI EXT 57-21-00-210-C14-L00 L600 - 7374 - 7374
57-21-26 551/651 GVI INT 57-21-00-210-823-L00 L600 - 7374 - 7374
57-21-29 531/631 SDE EXT 57-21-00-250-802-L00 L600 - 5129 - 5129
57-21-30 532/632 GVI EXT 57-21-00-210-812-L00 L600 - 10000 - 10000
57-21-30 532/632 GVI INT 57-21-00-210-822-L00 L600 - 10000 - 10000
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ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-21-30 551/651 GVI EXT 57-21-00-210-C18-L00 L600 - 10000 - 10000
57-21-30 551/651 GVI INT 57-21-00-210-C16-L00 L600 - 10000 - 10000
57-21-31 531/631 GVI EXT 57-21-00-210-C14-L00 L600 - 6369 - 6369
57-21-31 531/631 GVI INT 57-21-00-210-824-L00 L600 - 6369 - 6369
57-21-31 532/632 GVI EXT 57-21-00-210-812-L00 L600 - 6369 - 6369
57-21-31 532/632 GVI INT 57-21-00-210-C04-L00 L600 - 6369 - 6369
57-21-32 532/632 GVI EXT 57-21-00-210-826-L00 L600 - 10000 - 10000
57-21-32 532/632 GVI INT 57-21-00-210-809-L00 L600 - 10000 - 10000
57-21-32 551/651 DET EXT 57-21-00-220-802-L00 L600 - 10000 - 10000
57-21-32 551/651 DET INT 57-21-00-220-806-L00 L600 - 10000 - 10000
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ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-21-34 551/651 DET EXT 57-21-00-220-804-L00 L600 - 10000 - 10000
57-21-34 551/651 DET INT 57-21-00-220-805-L00 L600 - 10000 - 10000
57-21-36 532/632 GVI EXT 57-21-00-210-801-L00 L600 - 10000 - 10000
57-21-36 532/632 GVI INT 57-21-00-220-803-L00 L600 - 10000 - 10000
57-21-36 551/651 DET EXT 57-21-00-220-804-L00 L600 - 10000 - 10000
57-21-36 551/651 DET INT 57-21-00-220-803-L00 L600 - 10000 - 10000
57-21-37 532/632 GVI EXT 57-21-00-210-812-L00 L600 - 1151 - 1151
57-21-37 532/632 GVI INT 57-21-00-210-806-L00 L600 - 1151 - 1151
57-21-37 532/632 GVI EXT 57-21-00-210-812-L00 L650 - - - 10000
57-22-40 531/631 GVI EXT 57-22-00-220-801-L00 L600 - 10000 - 10000
57-22-40 531/631 GVI INT 57-22-00-220-805-L00 L600 - 10000 - 10000
57-22-40 541/641 GVI EXT 57-22-00-220-801-L00 L600 - 10000 - 10000
57-22-40 541/641 GVI INT 57-22-00-220-805-L00 L600 - 10000 - 10000
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ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-22-40 551/651 GVI EXT 57-22-00-220-802-L00 L600 - 10000 - 10000
57-22-40 551/651 GVI INT 57-22-00-220-806-L00 L600 - 10000 - 10000
57-22-41 531/631 GVI INT 57-22-00-210-802-L00 L600 - 10000 - 10000
57-22-41 541/641 GVI INT 57-22-00-210-802-L00 L600 - 10000 - 10000
57-22-41 551/651 GVI INT 57-22-00-210-805-L00 L600 - 10000 - 10000
57-22-42 551/651 GVI EXT 57-22-00-220-802-L00 L600 - 10000 - 10000
57-22-42 551/651 GVI INT 57-22-00-220-803-L00 L600 - 10000 - 10000
57-22-43 531/631 GVI EXT 57-22-00-210-803-L00 L600 - 10000 - 10000
57-22-43 531/631 GVI INT 57-22-00-210-804-L00 L600 - 10000 - 10000
57-22-43 541/641 GVI INT 57-22-00-210-804-L00 L600 - 10000 - 10000
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ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-22-43 551/651 GVI EXT 57-22-00-210-C01-L00 L600 - 10000 - 10000
57-22-43 551/651 GVI INT 57-22-00-210-806-L00 L600 - 10000 - 10000
57-22-44 531/631 GVI INT 57-22-00-210-801-L00 L600 - 10000 - 10000
57-23-45 531/631 GVI EXT 57-23-00-220-C01-L00 L600 - 7313 - 9284
57-23-45 531/631 GVI INT 57-23-00-220-801-L00 L600 - 7313 - 9284
57-23-45 541/641 GVI EXT 57-23-00-220-C01-L00 L600 - 7313 - 9284
57-23-45 541/641 GVI INT 57-23-00-220-801-L00 L600 - 7313 - 9284
57-23-45 551/651 GVI EXT 57-23-00-220-C01-L00 L600 - 10000 - 10000
57-23-45 551/651 GVI INT 57-23-00-220-801-L00 L600 - 10000 - 10000
57-23-46 531/631 GVI INT 57-23-00-210-801-L00 L600 - 7313 - 9284
57-23-46 541/641 GVI INT 57-23-00-210-801-L00 L600 - 7313 - 9284
57-23-46 551/651 GVI INT 57-23-00-210-801-L00 L600 - 10000 - 10000
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ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-23-47 531/631 GVI EXT 57-23-00-220-C01-L00 L600 - 10000 - 10000
57-23-47 531/631 GVI INT 57-23-00-220-804-L00 L600 - 10000 - 10000
57-23-47 541/641 GVI EXT 57-23-00-220-C01-L00 L600 - 10000 - 10000
57-23-47 541/641 GVI INT 57-23-00-220-804-L00 L600 - 10000 - 10000
57-23-47 551/651 GVI EXT 57-23-00-220-C01-L00 L600 - 10000 - 10000
57-23-47 551/651 GVI INT 57-23-00-220-805-L00 L600 - 10000 - 10000
57-23-48 531/631 GVI EXT 57-23-00-210-802-L00 L600 - 3284 - 3284
57-23-48 531/631 GVI INT 57-23-00-210-803-L00 L600 - 3284 - 3284
57-24-49 532/632 GVI EXT 57-24-00-210-C01-L00 L600 - 8973 - 8973
57-24-49 532/632 GVI INT 57-24-00-210-C02-L00 L600 - 8973 - 8973
57-24-50 532/632 GVI INT 57-24-00-210-801-L00 L600 - 8973 - 8973
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DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-24-51 532/632 GVI EXT 57-24-00-210-C01-L00 L600 - 8973 - 8973
57-24-51 532/632 GVI INT 57-24-00-210-C02-L00 L600 - 8973 - 8973
57-24-52 532/632 GVI EXT 57-24-00-210-802-L00 L600 - 10000 - 10000
57-25-53 551/651 GVI INT 57-25-00-210-C01-L00 L600 - 7374 - 7374
57-25-54 551/651 GVI EXT 57-25-00-210-C02-L00 L600 - 7374 - 7374
57-25-54 551/651 GVI INT 57-25-00-210-C01-L00 L600 - 7374 - 7374
57-26-56 532/632 SDE INT 57-26-00-250-803-L00 L600 - 10000 - 10000
57-26-94 532/632 SDE INT 57-26-00-250-802-L00 L600 - 10000 - 10000
57-26-95 532/632 SDE EXT 57-26-00-250-804-L00 L600 - 10000 - 10000
57-28-57 532/632 SDE EXT 57-28-00-250-803-L00 L600 - 10000 - 10000
57-28-57 532/632 SDE INT 57-28-00-250-801-L00 L600 - 10000 - 10000
57-28-57 541/641 GVI EXT 57-28-00-210-C02-L00 L600 - 10000 - 10000
57-28-57 541/641 GVI INT 57-28-00-210-801-L00 L600 - 10000 - 10000
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ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-28-57 551/651 GVI EXT 57-28-00-220-C01-L00 L600 - 10000 - 10000
57-28-57 551/651 GVI INT 57-28-00-220-801-L00 L600 - 10000 - 10000
57-28-58 532/632 GVI EXT 57-28-00-210-C01-L00 L600 - 10000 - 10000
57-28-58 532/632 GVI INT 57-28-00-210-C07-L00 L600 - 10000 - 10000
57-28-58 541/641 GVI EXT 57-28-00-210-C01-L00 L600 - 10000 - 10000
57-28-58 541/641 GVI INT 57-28-00-210-C07-L00 L600 - 10000 - 10000
57-28-58 551/651 GVI EXT 57-28-00-210-C01-L00 L600 - 10000 - 10000
57-28-58 551/651 GVI INT 57-28-00-210-C07-L00 L600 - 10000 - 10000
57-28-59 532/632 SDE EXT 57-28-00-250-805-L00 L600 - 10000 - 10000
57-28-59 541/641 SDE EXT 57-28-00-250-805-L00 L600 - 10000 - 10000
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PAGE : 237
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-28-59 551/651 SDE EXT 57-28-00-250-805-L00 L600 - 10000 - 10000
57-28-60 532/632 SDE EXT 57-28-00-250-804-L00 L600 - 10000 - 10000
57-28-60 532/632 SDE INT 57-28-00-250-802-L00 L600 - 10000 - 10000
57-28-60 541/641 GVI EXT 57-28-00-220-C10-L00 L600 - 10000 - 10000
57-28-60 541/641 GVI INT 57-28-00-220-C09-L00 L600 - 10000 - 10000
57-28-61 532/632 GVI EXT 57-28-00-210-C03-L00 L600 - 10000 - 10000
57-28-61 532/632 GVI INT 57-28-00-210-C09-L00 L600 - 10000 - 10000
57-28-61 541/641 GVI EXT 57-28-00-210-C03-L00 L600 - 10000 - 10000
57-28-61 541/641 GVI INT 57-28-00-210-808-L00 L600 - 10000 - 10000
57-28-62 532/632 DET EXT 57-28-00-220-805-L00 L600 - 10000 - 10000
57-28-62 532/632 DET INT 57-28-00-220-C05-L00 L600 - 10000 - 10000
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PAGE : 238
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-28-62 541/641 DET EXT 57-28-00-220-805-L00 L600 - 10000 - 10000
57-28-62 541/641 DET INT 57-28-00-220-C05-L00 L600 - 10000 - 10000
57-28-63 541/641 GVI EXT 57-28-00-210-804-L00 L600 - 10000 - 10000
57-28-63 541/641 GVI INT 57-28-00-210-806-L00 L600 - 10000 - 10000
57-28-64 551/651 GVI EXT 57-28-00-220-C03-L00 L600 - 10000 - 10000
57-28-64 551/651 GVI INT 57-28-00-220-C06-L00 L600 - 10000 - 10000
57-28-65 551/651 DET EXT 57-28-00-220-C03-L00 L600 - 10000 - 10000
57-28-65 551/651 DET INT 57-28-00-220-C06-L00 L600 - 10000 - 10000
57-28-66 551/651 GVI EXT 57-28-00-210-807-L00 L600 10000 2412 10000 2412
57-28-68 541/641 GVI EXT 57-28-00-210-804-L00 L600 - 4774 - 4774
57-28-69 541/641 DET EXT 57-28-00-220-804-L00 L600 - 3950 - 3950
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PAGE : 239
ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-28-70 532/632 DET EXT 57-28-00-220-C04-L00 L600 - 10000 - 10000
57-29-71 532/632 GVI INT 57-29-00-220-802-L00 L600 - 10000 - 10000
57-29-72 532/632 DET EXT 57-29-00-220-801-L00 L600 10000 4312 10000 4312
57-29-72 532/632 DET INT 57-29-00-220-802-L00 L600 10000 4312 10000 4312
57-41-94 511/611 GVI EXT 57-41-00-210-C01-L00 L600 - 6267 - 6267
57-41-98 511/611 DET INT 57-41-00-220-801-L00 L600 - 5300 - 5300
57-42-95 512/612 GVI EXT 57-42-00-210-C01-L00 L600 - 6267 - 6267
57-42-97 512/612 DET EXT 57-42-00-220-802-L00 L600 - 3180 - 3180
57-42-98 512/612 DET INT 57-42-00-220-801-L00 L600 - 5300 - 5300
57-43-96 513/613 GVI EXT 57-43-00-210-C01-L00 L600 - 6267 - 6267
57-43-98 513/613 DET INT 57-43-00-220-801-L00 L600 - 5300 - 5300
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DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-50-74 571/671 DET EXT 57-50-00-220-801-L00 L600 DELETED
57-50-74 571/671 DET EXT 57-50-00-220-805-L00 L600 - 7360 - 7360
57-50-74 572/672 DET EXT 57-50-00-220-805-L00 L600 - 7360 - 7360
57-50-74 571/671 DET INT 57-50-00-290-801-L00 L600 - 7360 - 7360
57-50-74 572/672 DET INT 57-50-00-290-801-L00 L600 - 7360 - 7360
57-50-76 571/671 SDE EXT 57-50-00-250-801-L00 L600 - 10000 - 10000
57-50-76 572/672 SDE EXT 57-50-00-250-801-L00 L600 - 10000 - 10000
57-50-77 571/671 DET EXT 57-50-00-220-C01-L00 L600 - 10000 - 10000
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DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-50-77 572/672 DET EXT 57-50-00-220-C01-L00 L600 - 10000 - 10000
57-50-80 571/671 DET EXT 57-50-00-220-804-L00 L600 - 3241 - 3241
57-50-80 571/671 SDE EXT 57-50-00-250-802-L00 L600 - 9150 - 9150
57-50-80 572/672 DET EXT 57-50-00-220-804-L00 L600 - 3241 - 3241
57-50-80 572/672 SDE EXT 57-50-00-250-802-L00 L600 - 9150 - 9150
57-52-73 571/671 DET EXT 57-50-00-220-805-L00 L600 - 7360 - 7360
57-52-73 571/671 DET INT 57-50-00-290-801-L00 L600 - 7360 - 7360
57-52-75 571/671 GVI EXT 57-52-00-210-804-L00 L600 4600 1143 4600 1143
57-52-78 571/671 GVI EXT 57-52-00-210-803-L00 L600 - 1454 - 1454
57-52-79 571/671 DET EXT 57-50-00-220-806-L00 L600 - 8375 - 8375
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DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-52-81 571/671 DET EXT 57-50-00-220-806-L00 L600 - 8375 - 8375
57-53-83 572/672 DET EXT 57-50-00-220-805-L00 L600 - 7359 - 7359
57-53-83 572/672 DET INT 57-50-00-290-801-L00 L600 - 7359 - 7359
57-53-84 572/672 GVI EXT 57-53-00-210-806-L00 L600 4600 1143 4600 1143
57-53-85 572/672 GVI EXT 57-53-00-210-801-L00 L600 - 1450 - 1450
57-53-86 572/672 DET EXT 57-50-00-220-806-L00 L600 - 8375 - 8375
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ISSUE : 1
DATE : 05/07/2019
145LEG-00-0007 145LEG-00-0007
Threshold
Limit
(Flight Cycles)
57-53-87 572/672 GVI EXT 57-53-00-210-C01-L00 L600 - 10000 - 10000
57-53-87 572/672 GVI INT 57-53-00-210-803-L00 L600 - 10000 - 10000
57-53-88 572/672 DET EXT 57-50-00-220-806-L00 L600 - 8375 - 8375
57-61-89 573/673 GVI EXT 57-61-00-210-801-L00 L600 10000 4229 10000 4229
57-61-90 573/673 DET EXT 57-61-00-220-801-L00 L600 10000 10000 10000 10000
57-70-92 5712/6712 GVI EXT 57-70-00-210-C01-L00 L600 - 5124 - 5124
57-70-92 5713/6713 GVI EXT 57-70-00-210-C01-L00 L600 - 5124 - 5124
57-70-93 5712/6712 GVI EXT 57-70-00-210-C01-L00 L600 - 5124 - 5124
57-70-93 5713/6713 GVI EXT 57-70-00-210-C01-L00 L600 - 5124 - 5124
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A2.4 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION (CDCCL).
CDCCL 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 Fuel System Safety Review evaluation required by the SFAR 88 rule (for the EMB-135BJ Not Equipped with Ventral Fuel Tank and
AE3007A2 Engines) or the CFR 25.981/Amdt 102 rule (for the EMB-135BJ Equipped with Ventral Fuel Tank and AE3007A2 Engines), the following
features were identified as CDCCLs:
1) Wing tanks FQIS / HLEIS harness between wing FCU / LCU and wing fuel tank wall 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 stub spar 1, divides in two and reaches an hermetic tank wall connector on each wing.
This harness is 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.
NOTE: Applicable to aircraft Not Equipped with Ventral Fuel Tank and AE3007A2 Engines, commercially called Legacy 600 and identified in the
MPG as L600.
2) FQIS / HLEIS / LLS harnesses between FCU / LCU and aft 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 Fuel Quantity Indicating System, High Level Exceeding Indication System and Low Level
Switch harnesses outside the aft fuel tank, and must be accomplished each time any kind of maintenance is performed to, or in the nearby areas
that could affect the harnesses installation.
NOTE: Applicable to aircraft Not Equipped with Ventral Fuel Tank and AE3007A2 Engines, commercially called Legacy 600 and identified in the
MPG as L600.
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 tanks
wall. This connector is highlighted as CDCCL in the appropriate AMM procedures, to check faying surface bonding whenever pump is changed
and to assure adequate bonding to any fuel tank in the aircraft.
NOTE: Applicable to aircraft with fuel pumps equipped with hermetic electrical connectors.
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4) Intrinsically safe harnesses (FQGMS) between FCUs and hermetic tank wall connectors of the Wing, Forward and Ventral
tanks
Wires from each wing, forward and ventral tank wall connectors (two per tank), carrying intrinsically safe power levels, run along the wing-to- fuselage fairing
(W1640 and W1641) converging to two interface connectors, aft of the forward tanks, into the pressurized cabin then (W1642) running to the FCU#1 under
the cockpit floor to the FCU#2 at the central IV left fuselage, along the fuselage floor over the W101 and W102 susceptible bundles.
These harnesses (W1640, W1641 and W1642) design and installation are highlighted as being a CDCCL at the applicable maintenance
procedures in the AMM, providing awareness that the proper and correct installation have to be preserved and checked to avoid alterations that may violate
the design configuration of the FQGMS (Fuel Quantity Gauging and Management System) harnesses outside those fuel tanks, what includes the routing and
sleeving (Nomex® where running over the ’s’ bundles in the pressurized area). The verification must be accomplished each time any kind of maintenance is
performed to, or in the nearby areas that could affect these harnesses installation.
NOTE: Applicable to aircraft Equipped with Ventral Fuel Tank and AE3007A2 Engines, commercially called Legacy 650 and identified in the MPG as L650.
5) Intrinsically safe harness (FQGMS) between FCUs and hermetic tank wall connectors of the Aft tanks
Wires (W1642) from each aft tank wall connectors (two per tank), carrying intrinsically safe power levels, run thru the components box attached to each aft
tank passing thru interface connectors (two per tank) and running along the fuselage floor over the W101 and W102 susceptible bundles to the FCU#2 at the
central IV left fuselage and to the FCU#1 under the cockpit floor.
This harness installation is highlighted as being a CDCCL at the applicable maintenance procedures in the AMM, providing awareness that the
proper and correct installation have to be preserved and checked to avoid alterations that may violate the design configuration of the FQGMS (Fuel Quantity
Gauging and Management System) harness outside the aft fuel tanks, what includes the routing and sleeving (Nomex® where running over the ’s’ bundles).
The verification must be accomplished each time any kind of maintenance is performed to, or in the nearby areas that could affect this harness installation.
6) Fuel Tanks Structural Lightning Protection Features
These protection features are present in the structural elements from all integral fuel tanks, which comprise the wing fuel tanks, the forward underbelly fuel
tanks and the ventral fuel tank. Any structural repair in these areas must be carried out considering to always installing rivets before the drilled panel painting
process, which guarantees the continued structural lightning strike protection in the repaired areas. The Structural Lightning Protection Features are
highlighted as CDCCL in the appropriate AMM procedures to inspect the structural elements (for loose or missing structural items, nicks, cracks, dents,
erosion, corrosion, deformation, deteriorated protective treatment, foreign object, and integrity of the sealant). This check must be carried out whenever an
integral fuel tank access panel is open, in the associated internal area from the integral fuel tank access panel removed. Furthermore, before the fuel tank
access panel installation, a check must be accomplished to make sure that the countersunk holes in the clamp ring are not painted, which ascertain the
structural lightning strike protection in the access panel installation is preserved.
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7) Fuel Pumps Harness installation inside the tanks
The proper design precautions were taken to guarantee the pumps’ harness in the tanks does not chafe with structures or other component inside the tank.
The designs precautions comprise redundant clamps, type of clamps and the proper harness routing thru the clamps avoiding slack variations. The pump
design and installation is a CDCCL item and must be retained if any maintenance task that require the tank to be opened is performed, not only the
replacement of the pump. These maintenance tasks provide warnings about the critical configuration of the pumps harness installation. The pumps
drawing and CMM properly warns the assembler to retain the configuration of the pump harness when assembling or manufacturing a pump. This is
applicable for all fuel pumps of all tanks of the aircraft, including the pumps equipped with the CHA.
8) Wires inside the pumps
The type, length and supporting of wires used inside the fuel pumps are such that provide enough clearance from any internal surface of the pump, what
prevents from chafing and arcing. This configuration is a CDCCL item and must be retained if any maintenance task that requires the pump to be
disassembled is performed. The pumps CMM provide warnings about the critical configuration of the wires in the pumps. This is applicable for all fuel pumps
of all tanks of the aircraft, including the pumps equipped with the CHA.
9) Fuel Pump’s Radio Noise Filter (RNF) cover
The non-conductive anodizing finishing of fuel pump’s RNF (radio noise filter) cover shall observe the thickness defined in the part’s drawing and shall not be
altered, as it is a critical design feature that enable the fuel pump and hence the aircraft where installed, to meet the required safety levels and number of
protection layers to prevent from tank ignition.
10) Fuel Pump PTFE Interface fitting at the Tank Wall
Fuel pumps of main wing tanks and auxiliary tanks having PTFE interface fitting, which are installed on the tanks wall. This fitting is highlighted as CDCCL in
the appropriate AMM procedures, to check proper installation, leakproofness, during periodic inspections or whenever pump is changed.
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This list contain the following limitations:
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 a specific repair or overhaul instruction approved by a Certification
Authority.
c. Any alteration on those CDCCL features in this list is classified as major and requires a Certification Authority approval.
A2.5 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 88,
SFAR 88 and FAA memorandum ANM112-05-011, Policy Statement on Process for Developing SFAR No. 88 – related Instructions for Maintenance and
Inspection of Fuel Tank and EASA policy statement on the process for developing instructions for maintenance 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 operational life of the airplane.
A2.5.1 – IMPLEMENTATION OF FUEL SYSTEM LIMITATIONS
The first mandatory inspections must be accomplished at each inspections interval, stated in the A2.5.2 – Fuel System Limitations
Items.
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A2.5.2 – FUEL SYSTEM LIMITATION ITEMS
CHAPTER 28 - FUEL SYSTEM LIMITATION ITEMS

28-11-00-720-001-A00 SYS - Functionally Check critical bonding integrity of selected conduits 531/631 EI: 30000 FH L600
inside the wing tank, Fuel Pump and FQIS connectors at tank wall 541/641 No Tolerance
by conductivity measurements.
28-11-00-720-002-A01 SYS - Functionally Check critical bonding integrity of selected conduits 531/631 I: 30000 FH L650
inside the wing tank, fuel pump connectors at tank wall by 541/641 or
conductivity measurements 144 MO
NOTE: Applicable to fuel pumps with tank wall hermetic connector. No Tolerance

28-11-00-720-003-A01 SYS - Functionally Check critical bonding integrity of selected conduits 171/172
EI: 30000 FH L650
inside the wing tank, FQIS connectors at tank wall by conductiv- 271/272 or
ity measurements 144 MO
No Tolerance
28-13-01-720-002-A00 SYS - Functionally Check Aft Fuel tank critical bonding integrity of Fuel 171/172 I: 30000 FH L600
Pump, FQGS and low Level SW connectors at tank wall by 271/272 No Tolerance
conductivity measurements
28-13-01-720-003-A01 SYS - Functionally Check Aft Fuel tank critical bonding integrity of Fuel 171/172 I: 30000 FH L650
Pump connectors at tank wall by conductivity measurements 271/272 or
NOTE: Applicable to fuel pumps with tank wall hermetic connector 144 MO
No Tolerance
28-13-01-720-004-A01 SYS - Functionally Check Aft Fuel tank critical bonding integrity of FQGS 171/172 I: 30000 FH L650
connectors at tank wall by conductivity measurements 271/272 or
144 MO
No Tolerance
28-15-04-720-001-A00 SYS - Functionally Check Fwd Fuel tank critical bonding integrity of Fuel 197 I: 30000 FH L600
Pump, FQGS and low Level SW connectors at tank wall by conduc- No Tolerance
tivity measurements
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28-15-04-720-002-A01 SYS - Functionally Check Fwd Fuel tank critical bonding integrity of Fuel 197 I: 30000 FH L650
Pump connectors at tank wall by conductivity measurements or
NOTE: Applicable to fuel pumps with tank wall hermetic connector 144 MO
No Tolerance
28-15-04-720-003-A01 SYS - Functionally Check Fwd Fuel tank critical bonding integrity of 197 I: 30000 FH L650
FQGS connectors at tank wall by conductivity measurements or
144 MO
No Tolerance
28-17-01-720-002-A01 SYS - Functionally Check Ventral tank critical bonding integrity of Fuel 193 I: 30000 FH L650
Pump connectors at tank wall by conductivity measurements 1924 or
NOTE: Applicable to fuel pumps with tank wall hermetic connector 1972 144 MO
No Tolerance

E
28-17-01-720-003-A01 SYS - Functionally Check Ventral tank critical bonding integrity of FQGS 193 I: 30000 FH L650
connectors at tank wall by conductivity measurements 1924 or
1972 144 MO
No Tolerance
28-21-01-220-001-A00 SYS - Inspect (Detailed Inspection) Wing Electric Fuel Pump Connector 531/631 I: 10000 FH L600
No Tolerance
28-23-03-220-001-A00 SYS - Inspect (Detailed Inspection) Pilot Valve harness inside the conduit 531/631 I: 20000 FH L600
28-23-04-220-001-A00 SYS - Inspect (Detailed Inspection) Vent Valve harness inside the conduit 531/631 I: 20000 FH L600
28-23-04-220-001-A01 SYS - Inspect (Detailed Inspection) Vent Valve harness inside the conduit 531/631 I: 20000 FH L650
541/641 or
96 MO
No Tolerance
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28-41-00-220-001-A01 SYS - Inspect (Detailed Inspection) W1642 intrinsically safe harnesses 221/222 I: 10000 FH L650
for sleeve integrity 231/232 or
241/242 48 MO
261/271
28-41-01-720-001-A01 SYS - Functionally Check of the Safe life Features of the Fuel 132 I: 10000 FH L600
Conditioning Unit (FCU) - Initial Functional Check No Tolerance
- 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 SYS - Inspect (Detailed Inspection) FQIS harness for clamp and wire 531/631 I: 20000 FH L600
jacket integrity. 541/641 No Tolerance

28-41-03-220-001-A01 SYS - Inspect (Detailed Inspection) FQIS harness for clamp and wire 531/631 EI: 20000 FH L650
jacket integrity. 541/641 or
96 MO
No Tolerance
28-41-07-220-001-A01 SYS - Inspect (Detailed Inspection) Ventral Tank internal Inspection: 193/1924/1 I: 20000 FH L650
FQGS harness for clamp and wire jacket integrity 972 or
96 MO
No Tolerance
28-46-02-220-001-A00 SYS - Inspect (Detailed Inspection) Aft Fuel Tank Internal Inspection: 171/172 I: 20000 FH L600
FQGS harness and Low Level SW harness for clamp and wire 271/272 No Tolerance
jacket integrity
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28-46-02-220-001-A01 SYS - Inspect (Detailed Inspection) Aft Fuel Tank Internal Inspection: 171/172 I: 20000 FH L650
FQGS harness for clamp and wire jacket integrity 271/272 or
96 MO
No Tolerance
28-46-04-220-001-A00 SYS - Inspect (Detailed Inspection) Fwd Fuel Tank Internal Inspection: 197 I: 20000 FH L600
FQGS harness and Low Level SW harness for clamp and wire No Tolerance
jacket integrity
28-46-04-220-001-A01 SYS - Inspect (Detailed Inspection) Fwd Fuel Tank Internal Inspection: 197 I: 20000 FH L650
FQGS harness for clamp and wire jacket integrity or
96 MO
No Tolerance
28-46-05-720-001-A01 SYS - Functionally Check of the Safe life Features of the Auxiliary Fuel 132 I: 10000 FH L600
Conditioning Unit (AFCU) No Tolerance
- 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.

E
28-50-01-220-001-A01 SYS - Inspect (Detailed Inspection) Fuel Pump Electrical Harness and 155 I: 10000 FH L650
connectors 156 or
NOTE: Applicable to fuel pumps with tank wall hermetic connector 192 48 MO
No Tolerance
28-50-01-220-001-A02 SYS - Inspect (Detailed Inspection) Fuel Pump Electrical Harness CHA 155/156 I: 10000 FH L650
(Cable Harness Assembly) end fitting. 157/197 or
NOTE: Applicable to aircraft with fuel pump harness with 271/272 48 MO
corrugated conduit. 1972 No Tolerance
28-50-01-720-001-A00 SYS - Functionally Check Fuel Pump Electrical Harness for Leakage. 155/156 I: 20000 FH L650
NOTE: Applicable to aircraft with fuel pump harness with 157/197 or
corrugated conduit. 271/272 96 MO
1972 No Tolerance
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28-50-02-220-001-A01 SYS - Inspect (Detailed Inspection) Wing Fuel Tank Units 155/156 I: 10000 FH L650
192/531 or
631/641 48 MO
No Tolerance
28-50-03-220-002-A01 SYS - Inspect (Detailed Inspection) Fwd Fuel Tank Units 197 I: 10000 FH L650
or
48 MO
No Tolerance
28-50-04-212-001-A01 SYS - Inspect (General Visual) Wing Stub Harness 192 I: 10000 FH L650
or
48 MO
No Tolerance
28-50-05-212-001-A01 SYS - Inspect (General Visual) Trailing Edge Harness 5711/5721 I: 10000 FH L650
5731/5732 or
6711/6721 48 MO
28-50-06-212-001-A01 SYS - Inspect (General Visual) Leading Edge Harness 511/512 I: 10000 FH L650
513/611 or
612/613 48 MO
No Tolerance

28-50-07-220-001-A01 SYS - Inspect (Detailed Inspection) Aft Fuel Tank Units 272 EI: 10000 FH L650
or
48 MO
No Tolerance
28-50-08-212-001-A00 SYS - Inspect (General Visual) Ventral Fuel Tank External Harness 1972 I: 10000 FH L650
or
48 MO
No Tolerance
28-50-08-220-001-A00 SYS - Inspect (Detailed Inspection) Ventral Fuel Tank Units 193 I: 10000 FH L650
1972 or
48 MO
No Tolerance
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28-50-09-212-001-A00 SYS - Inspect (General Visual) FWD Fuel Tank External Harness 191 I: 10000 FH L650
197 or
48 MO
No Tolerance
28-50-10-212-001-A00 SYS - Inspect (General Visual) Aft Fuel Tank External Harness 271/272 I: 10000 FH L650
or
48 MO
No Tolerance
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Section 4 Appendixs REVISION : 0
DATE : 05/07/2019
Appendix-B Aircraft Zoning – Component Location
1. General
A. The aircraft is divided into zones to give the references necessary for the identification of the service areas
or components. This makes the maintenance easier and is an important aid when task guides are prepared.
B. The system for identification of the aircraft zoning includes three levels and uses a three-digit number as
follows:
(1) Major zones: the number increases by the hundreds, from 100 thru 800.
(2) Major sub-zones: after the first digit of the major zones, the number increases by the tens, from 10
thru 90.
(3) Zone: after the first digit of the major zones and the second digit of the major sub-zones, the number
increases by the units (more digits can be used to permit you to go down to lower levels). It identifies a
component and its location: an even number shows the right side and an odd number shows the left side.
C. The sequence of the numbers which identify the zones is as follows:
(1) Wing - From the inboard side to the outboard side and from the front to the rear.
(2) Fuselage - From the nose to the tail cone.
(3) Vertical Stabilizer - From the root to the tip of the vertical stabilizer. D. Figure 101 shows the major
zones and Figure 102 shows the zones.
2. Major Zones
Table 101
MAJOR ZONE AREA

100 Lower fuselage (below the floor line)
200 Upper fuselage (above the floor line)
300 Tail cone and empennage group
400 Powerplant and nacelles
500 Left half-wing
600 Right half-wing
700 Landing gear wheelwell doors
800 Doors (main, service, cargo, emergency)
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Figure-101
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3. Major Zone 100 - Lower Fuselage
A. Major sub-zone 110 - STA X = 0 thru STA X = 600.0 and fuselage forward section I. The major sub-
zone 110 is zoned as follows:
Table 102 - MAJOR SUB-ZONE 110
ZONE DESCRIPTION
111 Radome
113 Forward fuselage I - LH (STGR 13L thru Y = 0.0)
114 Forward fuselage I - RH (STGR 13R thru Y = 0.0)
115 Pressure bulkhead - Fwd fuselage I - LH lower side
116 Pressure bulkhead - Fwd fuselage I - RH lower side
B. Major sub-zone 120 - Fuselage Forward Section II (X = 2364.0 thru X = 4154.5). The major sub- zone
120 is zoned as follows:
ZONE DESCRIPTION
121 Pressure bulkhead - cockpit LH lower side
122 Pressure bulkhead - cockpit RH lower side
123 Area below cockpit floor - LH (STGR 13L thru Y = 0.0)
124 Area below cockpit floor - RH (STGR 13R thru Y = 0.0)
C. Major sub-zone 130 - Fuselage Center Section I (X = 4154.5 thru X = 7131.0) and (STGR 16L
thru STGR 16R). The major sub-zone 130 is zoned as follows:
ZONE DESCRIPTION
131 Area below passenger cabin floor - LH (STGR 16L thru Y = 0.0)
132 Area below passenger cabin floor - RH (STGR 16R thru Y = 0.0)
D. Major sub-zone 140 - Fuselage Center Section II (X = 7131.0 thru X = 9984.0) and (STGR 16L
ZONE DESCRIPTION
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E. Major sub-zone 150 - Fuselage Center Section III (X = 9984.0 thru X = 15721.0) and (STGR 16L
ZONE DESCRIPTION
151 Fwd area below passenger cabin floor - LH (STGR 16L thru Y = 0.0)
152 Fwd area below passenger cabin floor - RH (STGR 16R thru Y = 0.0)
153 Aft area below passenger cabin floor - LH (STGR 16L thru Y = 0.0)
155 Wing stub - LH (Y= -960.0 thru Y = -230.0)
156 Wing stub - RH (Y = 230.0 thru Y = 960.0)
157 Wing Stub (Y = -230.0 thru Y = 230.0)
F. Major sub-zone 160 - Fuselage Center Section IV (X = 15721.0 thru X = 17253.0) and (STGR 16L
ZONE DESCRIPTION
G. Major sub-zone 170 - Fuselage Rear Section I (X = 17253.0 thru X = 22041.0) and (STGR 16L
ZONE DESCRIPTION
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H. Major sub-zone 190 - Wing-to-fuselage Attachment Fairing. The major sub-zone 190 is zoned as follows:
ZONE DESCRIPTION
191 FWD wing-to-fuselage fairing
192 Center wing-to-fuselage fairing
1921 Front ski fairing
1923 Main drain
193 Rear wing-to-fuselage fairing
1931 Rear ski fairing
194 RH lateral wing-to-fuselage fairing
195 LH lateral wing-to-fuselage fairing
196 FWD fuel tank fairing
197 FWD fuel tank
1971 Drain Duct
198 LH forward fuel tank lateral fairing I
1981 LH forward fuel tank lateral fairing II
1982 LH forward fuel tank lateral fairing III
199 RH forward fuel tank lateral fairing I
1991 RH forward fuel tank lateral fairing II
1992 RH forward fuel tank lateral fairing III
4. Major Zone 200 - Upper Fuselage
A. Major sub-zone 210 - Fuselage Forward Section I (X = 600.0 thru X = 2364.0). The major sub- zone
ZONE DESCRIPTION
213 Electronic compartment - LH upper side (STGR 13L thru Y = 0.0)
214 Electronic compartment - RH upper side (STGR 13R thru Y = 0.0)
215 Pressure bulkhead - electronic comp - LH upper side
216 Pressure bulkhead - electronic comp - RH upper side
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B. Major sub-zone 220 - Fuselage Forward Section II (X = 2364.0 thru X = 4154.5). The major sub- zone
ZONE DESCRIPTION
221 Pressure bulkhead - cockpit LH upper side
222 Pressure bulkhead - cockpit RH upper side
223 Cockpit - LH (STGR 13L thru STGR 7L)
224 Cockpit - RH (STGR 13R thru STGR 7R)
225 Cockpit ceiling - LH (STGR 7L thru Y = 0.0)
226 Cockpit ceiling - RH (STGR 7R thru Y = 0.0)
C. Major sub-zone 230 - Fuselage Center Section I (X = 4154.5 thru X = 7131.0) and (STGR 16L
ZONE DESCRIPTION
231 Passenger cabin - LH (STGR 16L thru STGR 5L)
232 Passenger cabin - RH (STGR 16R thru STGR 5R)
233 Passenger cabin ceiling - LH (STGR 5L thru Y = 0.0)
234 Passenger cabin ceiling - RH (STGR 5R thru Y = 0.0)
D. Major sub-zone 240 - Fuselage Center Section II (X = 7131.0 thru X = 9984.0) and (STGR 16L
thru 16R). The major sub-zone 240 is zoned as follows:
ZONE DESCRIPTION
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E. Major sub-zone 250 - Fuselage Center Section III (X = 9984.0 thru X = 15721.0) and (STGR 16L
ZONE DESCRIPTION
F. Major sub-zone 260 - Fuselage Center Section IV (X = 15721.0 thru X = 17253.0) and (STGR 16L
ZONE DESCRIPTION
G. Major sub-zone 270 - Fuselage Rear Section I (X = 17253.0 thru X = 22041.0) and (STGR 16L
ZONE DESCRIPTION
271 Baggage compartment and rear electronic compartment - LH (STGR
272 16L
Baggage compartment and rear electronic compartment - RH (STGR
273 16R
Baggage
thru STGRcompartment
5L) ceiling - LH (STGR 5L thru Y = 0.0)
274 Baggage
thru STGRcompartment
5R) ceiling - RH (STGR 5R thru Y = 0.0)
275 Pressure bulkhead - baggage compartment LH side
276 Pressure bulkhead - baggage compartment RH side
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Figure-102
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5. Major Zone 300 - Tail Cone and Empennage Group
A. Major sub-zone 310 - Fuselage Rear Section II (X = 22041.0 thru X = 24388.5). The major sub- zone
ZONE DESCRIPTION
311 Structural area aft of rear pressure bulkhead - LH
312 Structural area aft of rear pressure bulkhead - RH
313 Tail cone fairing
315 LH strake
316 RH strake
317 LH strake tip fairing
318 RH strake tip fairing
B. Major sub-zone 320 - Vertical Stabilizer and Rudders. The major sub-zone 320 is zoned as follows:
ZONE DESCRIPTION
321 Upper front and rear front fairings of vertical stabilizer
322 Dorsal fin
323 Leading edge
324 Area between spar I and spar II
325 Area between spar II and spar III
326 Rudder I
327 Rudder II
C. Major sub-zone 330 - Horizontal Stabilizer and Elevators. The major sub-zone 330 is zoned as follows:
ZONE DESCRIPTION
331 Leading edge - LH
332 Leading edge - RH
333 Horizontal stabilizer - LH
334 Horizontal stabilizer - RH
335 Elevator - LH
336 Elevator - RH
337 Center section for attachment of stabilizer to the tail fin
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6. Major Zone 400 - Powerplant and Nacelles
A. Major sub-zone 410 - LH Powerplant. The major sub-zone 410 is zoned as follows:
ZONE DESCRIPTION
411 Forward cowling
412 Upper cowling
413 Cowling door
414 Pylon
415 Engine
416 Thrust reverser module
B. Major sub-zone 420 - RH Powerplant. The major sub-zone 420 is zoned as follows:
ZONE DESCRIPTION
421 Forward cowling
422 Upper cowling
423 Cowling door
424 Pylon
425 Engine
426 Thrust reverser module
7. Major Zone 500/600 - Left Wing/Right Wing
A. Major sub-zones 510/610 - Wing Leading Edge. The major sub-zones 510/610 are zoned as follows:
Table 122 - MAJOR SUB-ZONES 510/610
ZONE DESCRIPTION
511/611 Leading edge I
512/612 Leading edge II
513/613 Leading edge III
514/614 Leading edge I Fairing
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B. Major sub-zones 530/630 Area between Y = 960.0 and Y = 3815.0. The major sub-zones 510/610 are
zoned as follows:
ZONE DESCRIPTION
531/631 Area between spar I and spar II
532/632 Area between spar II and spar III
533/633 Torque Box Fairing
C. Major sub-zones 540/640 - Area between Y = 3815.0 and YA = 7792.08. The major sub-zones
540/640 are zoned as follows:
ZONE DESCRIPTION
D. Major sub-zones 550/650 - Area between YA = 7792.08 and YA = 9785.0. The major sub-zones
550/650 are zoned as follows:
ZONE DESCRIPTION
E. Major sub-zones 560/660 - Winglet. The major sub-zones 560/660 are zoned as follows:
ZONE DESCRIPTION
561/661 Wing tip fairing
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F. Major sub-zones 570/670 - Wing Trailing Edge. The major sub-zones 570/670 are zoned as follows:
ZONE DESCRIPTION
571/671 Inboard flap
572/672 Outboard flap
573/673 Aileron
5711/6711 Inboard flap lower shroud
5712/6712 Ground spoiler
5713/6713 Ground spoiler/speed breaker
5721/6721 Outboard flap lower shroud
5722/6722 Outboard flap upper shroud
5731/6731 Aileron lower shroud
5732/6732 Aileron upper shroud
8. Major Zone 700 - Landing Gears and Gear Compartment Doors
A. Major sub-zone 710 - Nose Landing Gear and Gear Compartment Doors. The major sub-zone
ZONE DESCRIPTION
711 Landing gear
713 Gear compartment LH forward door
714 Gear compartment RH forward door
B. Major sub-zone 720 - RH Main Landing Gear and Gear Compartment Doors. The major sub-zone
ZONE DESCRIPTION
721 Landing gear
722 Gear compartment door
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C. Major sub-zone 730 - LH Main Landing Gear and Wheelwell Doors. The major sub-zone 730 is zoned
as follows:
ZONE DESCRIPTION
731 Landing gear
732 Gear compartment door
9. Major Zone 800 - Doors
A. Major sub-zone 810 - Fuselage LH side. The major sub-zone 810 is zoned as follows:
ZONE DESCRIPTION
811 Main door
812 Escape hatch (not used)
813 Baggage door
B. Major sub-zone 820 - Fuselage RH side. The major sub-zone 820 is zoned as follows:
ZONE DESCRIPTION
822 Escape hatch
>>>>>>>>>>> END >>>>>>>>>
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Appendix-C Prefilght and PostFlight checklist

Appendix-C1 : Preflight checklist
Refer to ACA-ENG-MP-DID-F01
Pre-Flight Inspection
Completion of Inspection
Aircraft registration: Aircraft Serial No:
LH Engine total hours:

Aircraft total A/F hours:
RH Engine total hours:
Date of completion (dd-mm-yy): Time (hh-mm) :
Checked by:
License #:
LAE Signature:
Preamble
A. General J. Aft Fuselage — Left Side

B. Left Nose and Fuselage K. Left Engine and Nacelle
C. Nose Landing Gear and Bay L. Left Main Landing Gear
D. Right Nose and Fuselage M. Left Wing
E. Right Wing N. Cockpit
F. Right Main Landing Gear O. Passenger Cabin and Toilet
G. Right Engine and Nacelle P. Final Items
H. Aft Fuselage — Right Side
I. Empennage (Tail Section)
List of Illustrations
Walk Around Sequence - Figure 1 - Recommended Walk-Around Sequence Airplanes
Safety warning
Always Wear the Standard Personal Protection Equipment.
If found any abnormal must report to related person immediately
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Figure 1
Walk-Around Sequence
Instruction:
1) Follow Walk around direction strictly.
2) Normal conditions mark " ✓ " , if found abnormal conditions Mark " X " with record ATA –Name – defective in
the block. See sample below.
Note-1: If found abnormal condition, must report to related persons (HOE/LAE/PIC/OPS/Safety/QA)

Note-2: All defective must be corrected before flight by follow approved AMM and/or approved MEL.
3) After check accomplished, must be final verified by LAE with his signature on the page-1
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A. General
No. Marked when Complete
Make sure that any defects reported in the technical log or Pilot’s Report have been cleared
1 or cleared for flight in accordance with the CAAT approved Minimum Equipment List.
Assure that Post Flight Checks have been accomplished.
2 NOTE: Do not remove gear pins.
3 Remove external covers, plugs, guards, internal control locks (if installed) and stow correctly
No. B. Left Nose and Fuselage Marked when Complete

Check static plate and static ports for condition free from dents corrosion contaminants and
1 obstructions
2 Check TAT probe for condition no obstruction
3 Check Ice detector for condition no obstruction
4 Check AOA sensor for condition no obstruction free movement
5 Check Pitot tube for condition no obstruction
6 Check Battery compartment secured and condition
7 Check GPU receptacle secured and condition
8 Check Air inlets no obstruction
9 Check Radome secured and condition
10 Check Red Beacon and Antennas
No. C. Nose Landing Gear and Bay Marked when Complete

Check Nose Gear Wheels position indicator mark is with in the nose wheel position indication
1
scale limits
Check Nose Tires condition and should not be worn past the bottom of the tire grooves (Cold
2
tire pressure should be with gray range 84 +/- 2PSI)
3
Check Struts/Wheel/Door condition no leaks
Check Absorber extension
4
5 Check Static Discharger condition
Check Gear Uplock Hook unlocked if the uplock hook is in the LOCKED position ,cycle the
6
freefall lever to reposition the uplock to the UNLOCKED position condition
7 Check Landing and Taxi Lights condition
Check Nose Gear Wheels position indicator mark is with in the nose wheel position indication
8
scale limits
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All Areas. Access: As visible.

Access Area Mechanic Inspector
A. General
B. Left Nose and Fuselage
C. Nose Landing Gear and Bay
Note :
No. D. Right Nose and Fuselage Marked when Complete
1
Check Radome secured and condition
2
Check Air inlets no obstruction
3
Hydraulic compartment secured and condition no leaks and Maintenance Safety Pin Remove
4
Check TAT probe for condition no obstruction
5
Check Pitot tube for condition no obstruction
6
Check AOA sensor for condition no obstruction free movement
7
Check Ice detector for condition no obstruction
8
Check Pitot/Static tube for condition no obstruction
Check static plate and static ports for condition free from dents corrosion contaminants and
9
obstructions
10
Check Oxygen Pressure Green Dish in Place
No. E. Right Wing and Winglet Marked when Complete
1
Check Fluid Drain Holes no leak
2
Check Ram Air inlets and Outlets no obstruction
3
Check Antennas condition
4
Check Fueling Compartment Door secured
5
Check Inspection Lights condition
6
Check Emergency Lights condition
7
Check Access Doors and Panels secured
8
Check Landing Lights condition
Check the condition of the external structure of the wing to make sure it clean and
9
undamaged upper and lower surface (no fuel leak)
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10
Leading edge condition
11
Check Clear Ice Sensor condition
12
Check Direct Measuring Sticks Pushed In
13
Check Ram Air inlets and Outlets and Vents no obstruction
14
Check Vortilons and Vortex Generators number and condition
15
Check Navigation and Strobe Lights condition
16
Check Static Discharger number and condition
Check Flight Control Surfaces and Fairings condition (Flaps must be retracted and spoilers
17
closed)
18
Check Main Gear Struts/Wheel well condition no leak
No. F. Right Main Landing Gear Marked when Complete

Check Main Tires condition and should not be worn past the bottom of the tire grooves
1
(Cold tire pressure should be with gray range 160 +/- 4PSI)
2
Check Absorber extension 48 mm minimum extension
3
Check Ground Locking Pins Removed
4
Check Brakes Wear Indicators should be no less than flush with housing

D. Right Nose and Fuselage
E. Right Wing and Winglet
F. Right Main Landing Gear
Note:
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No. G. Right Engine and Nacelle Marked when Complete

Check right engine, remove engine cover and make sure there are no visible oil leaks
1 in the engine intake and cowling and free from foreign objects.
WARNING, DO NOT TO ATTEMPT TO STOP THE FAN BY HOLDING THE BLADES IF
THE FAN IS WINDMILLING
2
Check no damage fan blade
3
Check general condition of cowing and latches are secured vent and drain holes clear
4
Check Pylons condition
5
Check Thrust Reverser Door flush with nacelle
6
Check no damage turbine blade when viewed through the exhaust
No. H. Aft Fuselage — Right Side Marked when Complete

Check Emergency / Parking Brake Hydraulic accumulator discharge/check the pressure
1
from The condition Emergency / Parking Brake Hydraulic accumulator
2 Check Access Doors and Panels secured
3 Check Toilet Service panel secured
4 Check Water Service panel secured
No. I. Empennage (Tail Section) Marked when Complete
1 Check no damage and condition Horizontal Stabilizer and Elevator Control Surfaces
2 Check no damage and condition Vertical Stabilizer and Rudder Control Surfaces
3 Check Logo Lights condition
4 Check Static Dischargers number and condition
5 Check APU condition
6 Check Pressurization Static Ports no obstruction
7 Check Fluid Drain Holes no leak

G. Right Engine and Nacelle
Note :
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This document is property of AC Aviation Co., Ltd. Do not Copied or distributed without company allowed. Doc. Ref: ACA-ENG-
MP-DID
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No. J. Aft Fuselage — Left Side Marked when Complete
1 Check Baggage Door latched/lock panel closed
No. K. Left Engine and Nacelle Marked when Complete

Check left engine, remove engine cover and make sure there are no visible oil leaks
1 in the engine intake and cowling and free from foreign objects.
WARNING, DO NOT TO ATTEMPT TO STOP THE FAN BY HOLDING THE BLADES IF
THE FAN IS WINDMILLING
2 Check no damage turbine blade when viewed through the exhaust
3 Check no damage fan blade
4 Check Thrust Reverser Door flush with nacelle
5 Check Pylons condition
6 Check general condition of cowing and latches are secured vent and drain holes clear
No. L. Left Main Landing Gear Marked when Complete

Check Gear Uplock Hook unlocked if the uplock hook is in the LOCKED position, cycle
1
the freefall lever to reposition the uplock to the UNLOCKED position condition
2 Check Brakes Wear Indicators should be no less than flush with housing
3 Check Ground Locking Pins Removed
4 Check Absorber extension 48 mm minimum extension
Check Main Tires condition and should not be worn past the bottom of the tire grooves
5
(Cold tire pressure should be with gray range 160 +/- 4PSI)
6 Check Main Gear Struts/Wheel well condition no leak
No. M. Left Wing and Winglet Marked when Complete
1 Check Main Gear Struts/Wheel well condition no leak
Check Flight Control Surfaces and Fairings condition (Flaps must be retracted and
2
spoilers closed)
3 Check Static Discharger number and condition
4 Check Navigation and Strobe Lights condition
5 Check Vortilons and Vortex Generators number and condition
6 Check Ram Air inlets and Outlets and Vents no obstruction
7 Check Direct Measuring Sticks Pushed In
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8 Check Clear Ice Sensor condition
Check the condition of the external structure of the wing to make sure it clean and
9
undamaged upper and lower surface (no fuel leak)
10 Leading edge condition
11 Check Inspection Lights condition
12 Check Landing Lights condition
13 Check Ram Air inlets and Outlets no obstruction
14 Check Fluid Drain Holes no leak

J. Aft Fuselage — Left Side

K. Left Engine and Nacelle
L. Left Main Landing Gear
M. Left Wing and Winglet
Note:
No. N. Cockpit + RVSM Marked when Complete
1 Make sure all flashlights function correctly
Make sure there is full and free movement of the aileron, elevator and rudder primary
2
controls
3 Make sure the oxygen system contents are adequate and the valves are ON
With the landing gear ground locks installed, make sure that the emergency dump valve
is properly exercised by operating the auxiliary hydraulic system selector handle several
4 times. Investigate any undue stiffness in operation. On completion of the check, make
sure the selector handle is reset to the fully-in position
5 Check protective breathing equipment and portable breathing equipment
Check the fuel tanks for required fuel quantities.

NOTE: If the airplane will be operated in an area where microbiological
6 contamination of
fuel is likely to exist, it is strongly recommended that regular use is made of fuel
treated with an approved biocidal additive.
7 Check TCAS system check (RVSM)
8 Altimeter system check (RVSM)
9 Check EGPWS system check (RVSM)
10 FMS system check (RVSM)
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No. O. Passenger Cabin and Toilet Marked when Complete
1 Make sure all emergency equipment is on board and properly stowed
2 Make sure the emergency exit door is secure
3 Remove the emergency exit internal locking pin (if installed) and stow securely
4 Make sure Tow bar & Safety Pin on board and secured.
No. P. Final Items Marked when Complete
1 Make sure that all access doors and servicing panels are secure
2 Remove the gear pins and stow

Mechanic Inspector
Access Area
N. Cockpit
O. Passenger Cabin and Toilet
P. Final Items
Note :
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Tire Pressure check

Access Area : Mechanic Inspector
Ref. Specification
Tire pressure check Nose gear 84 ± 2 PSI
Remark: Use calibrated tools only. Main gear 160 ± 4 PSI
Nose Gear Main Gear

RH (1) LH (2) Out-RH(3) In-RH(4) Out-LH(5) In-LH(6)
Before
After
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Appendix-C2: Postflight Checklist

Refer to ACA-ENG-MP-DID-F02
Post-Flight Inspection
Completion of Inspection
Aircraft registration: Aircraft Serial No:
LH Engine total hours:

Aircraft total A/F hours:
RH Engine total hours:
Date of completion (dd-mm-yy): Time (hh-mm) :
Checked by:
License #:
LAE Signature:
Preamble
A. General J. Aft Fuselage — Left Side

B. Left Nose and Fuselage K. Left Engine and Nacelle
C. Nose Landing Gear and Bay L. Left Main Landing Gear
D. Right Nose and Fuselage M. Left Wing
E. Right Wing N. Cockpit
F. Right Main Landing Gear O. Passenger Cabin and Toilet
G. Right Engine and Nacelle P. Final Items
List of Illustrations
Walk Around Sequence - Figure 1 - Recommended Walk-Around Sequence Airplanes
Safety warning
Always Wear the Standard Personal Protection Equipment.
If found any abnormal must report to related person immediately
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DATE : 05/07/2019
Figure 1
Walk-Around Sequence
Instruction:
1) Follow Walk around direction strictly.
2) Normal conditions mark " ✓ " , if found abnormal conditions Mark " X " with record ATA –Name
– defective in the block. See sample below.
Note-1: If found abnormal condition, must report to related persons (HOE/LAE/PIC/OPS/Safety/QA)

Note-2: All defective must be corrected before flight by follow approved AMM and/or approved MEL.
3) After check accomplished, must be final verified by LAE with his signature on the page-1
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A. General
No. Marked when Complete
1 Install the landing gear ground locking pins
No. B. Left Nose and Fuselage Marked when Complete
1 Check external fuselage and Cockpit Windshield for damage
2 Check nose skin, free from dents, paint bubbles and sealant bulges.
3 Check RADOME for condition and security
No. C. Nose Landing Gear and Bay Marked when Complete
1 Make sure the landing gear ground locking pin is installed and secure
2 Make sure there is no visible damage to the doors, nose gear assembly, wheels or tires
3 Check the nose gear and inside the nose gear bay to make sure there is no fluid leakage

A. General
B. Left Nose and Fuselage
C. Nose Landing Gear and Bay
Note :
No. D. Right Nose and Fuselage Marked when Complete
1 Check RADOME for condition and security.
2 Check nose skin, free from dents, paint bubbles and sealant bulges.
3 Check external fuselage and Cockpit Windshield for damage
No. E. Right Wing Marked when Complete

Check the condition of the external structure of the wing to make sure it is clean and
1 undamaged; upper and lower surface (no fuel leaks), leading edge, stall strip, landing and
taxi lights (condition of lens and bulbs) and vortilon.
2 Make sure Vortilons and Vortex Genetors,Outlets and Vents clear
3 Check condition of wing tip.
4 Check condition of aileron .
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Make sure there is no damage to the top or bottom surfaces of the flap, and with the flap
lowered, that there is no slush, snow or ice trapped between the flap and wing structure
5
NOTE: Step E. (6) is only applicable following a landing on a runway covered with deep
water puddles, slush, snow or ice
6 Check for missing or damaged static wicks.
No. F. Right Main Landing Gear Marked when Complete
1 Make sure the main landing gear ground locking pin is installed and secure
2 Make sure the main wheel tires are not damaged or excessively worn
3 Make sure there is no visible damage to the fairing and main landing gear doors
4 Check the main gear and inside the main gear bay to make sure there is no fluid leakage
5 Check the main wheel tie bolt nuts for evidence of loosening
6 Make sure the extension of the brake wear indicators has been checked

D. Right Nose and Fuselage
E. Right Wing
F. Right Main Landing Gear
Note:
No. G. Right Engine and Nacelle Marked when Complete

Make sure there are no visible oil leaks in the engine intake and engine cowling.
1 WARNING: DO NOT ATTEMPT TO STOP THE FAN BY HOLDING THE BLADES IF THE FAN IS
WINDMILLING. THE BLADES ARE SHARP. STOP THE FAN BY PUSHING ON THE SPINNER
2 Make sure there is no damage to the fan blades when viewed through the engine intake
3 Check general condition of cowling and latches for damage
4 Make sure there are no signs of hydraulic fluid leakage from the engine drain
5 Make sure there is no damage to the turbine blades when viewed through the exhaust
6 Make sure there are no visible oil leaks in the engine cowling and engine exhaust areas
No. H. Aft Fuselage — Right Side Marked when Complete
1 Check external fuselage for damage
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No. I. Empennage (Tail Section) Marked when Complete
1 Check the APU (if installed) exhaust is unobstructed/undamaged.
2 Check condition of Tailcone and Tail Navigation Lights
3 Make sure there is no visible damage to the vertical stabilizer and rudder.
3 Make sure there is no visible damage to the horizontal stabilizer and elevator.
5 Check condition of static wicks, present and undamaged.

G. Right Engine and Nacelle
Note :
No. J. Aft Fuselage — Left Side Marked when Complete
1 Check external fuselage for damage
No. K. Left Engine and Nacelle Marked when Complete
1 Make sure there is no damage to the turbine blades when viewed through the exhaust
2 Make sure there are no visible oil leaks in the engine cowling and engine exhaust areas
3 Check general condition of cowling and latches for damage
4 Make sure there are no signs of hydraulic fluid leakage from the engine drain
Make sure there are no visible oil leaks in the engine intake and engine cowling.
5 WARNING: DO NOT ATTEMPT TO STOP THE FAN BY HOLDING THE BLADES IF THE FAN IS
WINDMILLING. THE BLADES ARE SHARP. STOP THE FAN BY PUSHING ON THE SPINNER
6 Make sure there is no damage to the fan blades when viewed through the engine intake
No. L. Left Main Landing Gear Marked when Complete
1 Make sure the main landing gear ground locking pin is installed and secure
2 Make sure the main wheel tires are not damaged or excessively worn.
3 Make sure there is no visible damage to the fairing and main landing gear doors
4 Check the main gear and inside the main gear bay to make sure there is no fluid leakage
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5 Check the main wheel tie bolt nuts for evidence of loosening
6 Make sure the extension of the brake wear indicators have been checked
7 Check all antennas attached to keel are secure and undamaged
No. M. Left Wing and Winglet Marked when Complete

Make sure there is no damage to the top or bottom surfaces of the flap, and with the flap
lowered, that there is no slush, snow or ice trapped between the flap and wing structure.
1
NOTE: Step N. (1) is only applicable following a landing on a runway covered with deep water
puddles, slush, snow or ice.
2 Check for missing or damaged static wicks
3 Check condition of aileron
4 Check condition of wing tip.
5 Make sure Vortilons and Vortex Genetors,Outlets and Vents clear
Check the condition of the external structure of the wing to make sure it is clean and
6 undamaged; upper and lower surface (no fuel leaks), leading edge, stall strip, landing and
taxi lights (condition of lens and bulbs) and vortilon
7 Check condition of main entry door seal/frame, fuselage and passenger windows

J. Aft Fuselage — Left Side

K. Left Engine and Nacelle
L. Left Main Landing Gear
M. Left Wing and Winglet
Note:
No. N. Cockpit Marked when Complete

Check condition of lens and bulbs of all external lights.
1
NOTE: APU or external power required
No. O. Vestibule, Passenger Cabin and Toilet Compartment Marked when Complete
CAUTION: DRAIN ALL OF THE WATER FROM THE WATER SYSTEMS WHEN THE
AIRPLANE IS TO REMAIN ON THE GROUND AND THE AMBIENT TEMPERATURE IS,
1 OR WILL BE, LESS THAN 0 DEGREES C.
Make sure all passenger seat safety belts operate correctly and are secure. Check latch,
security and wear
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P. Final Items Marked when

No.
Complete
1 Make sure the external covers, plugs and guards are installed
2 Make sure the emergency exit internal locking pin
3 Make sure all internal gust locks are installed

Mechanic Inspector
Access Area
N. Cockpit
O. Passenger Cabin and Toilet
P. Final Items
Note :
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Appendix-D AO-Maintenance Programe Amendment Approval Submission
Note : Ref. CAAT-ENG-01 Aircraft Maintenance Schedules and Programes
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MAINTENANCE PROGRAM (MP)

This Maintenance Program is establishing for the Aircraft Model

Approved by Civil Aviation Authority of Thailand

Type text here

Authority Position Signature Date (dd/mm/yy)

Prepared by Head of Engineer 05/07/2019

Reviewed by Head of Quality 05/07/2019

TABLE OF CONTENTS (TOC)

1.2 Annual Utilization and Maintenance Review ........................................................................................... 2

1.3 Aircraft Application ................................................................................................................................... 2

1.3.1 MP Owner and Maintenance Oragnization Address .............................................................................. 3

1.4 DOCUMENT REFERENCE ............................................................................................................................ 3

1.5 Flying Times ............................................................................................................................................... 3

1.6 Certification Maintenance Requirements (CMR’s) .................................................................................... 3

1.7 Task Escalation .......................................................................................................................................... 3

1.9 Fatigue Lives and Airworthiness Limitation Items .................................................................................... 4

2.0 Maintenance Practices and Procedures ................................................................................................... 4

2.8 Ageing Aircraft System .............................................................................................................................. 7

3.0 Aircraft Electrical Wiring Interconnect System (EWIS) .............................................................................. 8

3.1 Limit Of Validity (LOV) ................................................................................................................................ 8

3.2 MP Amendments and Review ................................................................................................................... 8

3.5 CVR/FDR Download Procedures ............................................................................................................... 9

3.6 Calibration of the FDR system................................................................................................................... 9

CHAPTER 25 - EQUIPMENT/FURNISHINGS ................................................................................................... 44

CONTROL DISTRIBUTION LIST (CDL)

Copy No. Name Position/Location

001 Master copy for Company Document Control Center/QA office

002 Master copy for CAAT AIR,CAAT

003 Stephen Christopher Levesque Accountable Manager / General Manger

004 Palang Khamlek Head of Flight Operation

005 Teerapong Prajittanon Head of Engineer

006 Smith Pongstaporn Head of SMS and AVSEC

007 Phrompratan Sorassa Head of Training

008 Songsit Lertcharoon Head of Quality

SECTION-0 GENERAL REQUIREMENTS

1.1 Company Statements

Name: Teerapong Prajittanon Position: Head of Engineering

1.2 Annual Utilization and Maintenance Review

1.3 Aircraft Application

A Aircraft model EMB-135BJ

B Manufacture date October 2008

C Serial No. 14501069

D Registration No. HS-DID

E Engine Manufacture and Model Rolls-Royce model AE3007A1E

F APU Manufacture and Model Hamilton Sundstrand model T-62T-40C14

1.3.1 MP Owner and Maintenance Oragnization Address

Owner’s address Maintenance

Website www.bangkokjets.com www.hawkerpacific.com

1.4 DOCUMENT REFERENCE

Document Name Sourcing Remark

1.5 Flying Times

1.6 Certification Maintenance Requirements (CMR’s)

1.7 Task Escalation

1.8 ADs/SBs Assessment

1.9 Fatigue Lives and Airworthiness Limitation Items

2.0 Maintenance Practices and Procedures

2.1 Area or Zonal Inspection

2.2 Inspection Standards

2.3 Condition Monitored Maintenance/Reliability Programe