kementerian perhubungan direktorat...

KEMENTERIAN PERHUBUNGAN

DIREKTORAT JENDERAL PERHUBUNGAN UDARA

PERATURAN DIREKTUR JENDERAL PERHUBUNGAN UDARA

NOMOR : KP 294 TAHUN 2017

TENTANG

PETUNJUK TEKNIS

PERATURAN KESELAMATAN PENERBANGAN SIPIL BAGIAN 8900-6.1

{STAFF INSTRUCTION PART 8900-6.1)

TENTANG PEMERIKSAAN PESAWAT UDARA [AIRCRAFT INSPECTION)

DENGAN RAHMAT TUHAN YANG MAHA ESA

Menimbang

Mengingat

DIREKTUR JENDERAL PERHUBUNGAN UDARA,

a. bahwa Peraturan Menteri Pehubungan Nomor

PM 98 Tahun 2015 Tentang Peraturan Keselamatan

Penerbangan Sipil Bagian 21 (Civil Aviation Safety

Regulation Part 21) Tentang Prosedur Sertifikasi Untuk

Produk dan Bagian-Bagiannya (Certification Procedures

for Product and Parts) mengatur tentang inspeksi

terhadap produk pesawat udara;

b. bahwa "dalam rangka memberikan panduan bagi

pelaksanaan pemeriksaan pesawat udara (aircraft

inspection) oleh Inspektur Penerbangan perlu disusun

suatu petunjuk teknis;

c. bahwa berdasarkan pertimbangan sebagaimana

dimaksud pada butir a dan b, perlu menetapkan

Peraturan Direktur ' Jenderal Perhubungah Udara

tentang Petunjuk Teknis Peraturan Keselamatan

Penerbangan Sipil Bagian 8900-6.1 (Staff Instruction Part

8900-6.1) tentang Pemeriksaan Pesawat Udara (Aircraft

Inspection);

1. Undang-Undang Republik Indonesia Nomor 1 Tahun

2009 tentang Penerbangan (Lembaran Negara Republik

Indonesia Tahun 2009 Nomor 1, Tambahan Lembaran

Negara Republik Indonesia Nomor 4956);

2. Peraturan Presiden Nomor 7 Tahun 2015 tentang

Organisasi Kementerian Negara (Lembaran Negara

Republik Indonesia Tahun 2015 Nomor 5);

3. Peraturan Presiden Nomor 40 Tahun 2015 tentang

Kementerian Perhubungan (Lembaran Negara Republik

Indonesia Tahun 2015 Nomor 75);

4. Peraturan Menteri Perhubungan Nomor PM 59 Tahun

2015 Tentang Kriteria, Tugas dan Wewenang Inspektur;


2015 tentang Organisasi dan Tata Keija Kementerian

Perhubungan;


2015 Tentang Peraturan Keselamatan Penerbangan

Sipil Bagian 21 {Civil Aviation Safety Regulation Part 21)

Tentang Prosedur Sertifikasi Untuk Produk dan Bagian-

Bagiannya {Certification Procedures for Product and

Parts);


2017 Tentang Perubahan Keempat Atas Peraturan

Menteri Perhubungan Nomor PM 28 Tahun 2013

Tentang Peraturan Keselamatan Penerbangan Sipil

Bagian 121 Tentang Persyaratan-Persyaratan Sertifikasi

dan Operasi Bagi Perusahaan Angkutan Udara yang

Melakukan Penerbangan Dalam Negeri, International

dan Angkutan Udara Niaga Tidak Berjadwal;

8. Peraturan Menteri Perhubungan Nomor 63 Tahun 2017

Tentang Perubahan Kesepuluh Atas Keputusan Menteri

Perhubungan Nomor KM 18 Tahun 2001 Tentang

Persyaratan-Persyaratan Sertifikasi dan Operasi Bagi

Perusahaan Angkutan Udara Niaga Untuk Penerbangan

Komuter dan Charter;

MEMUTUSKAN

Menetapkan : PERATURAN DIREKTUR JENDERAL PERHUBUNGAN

UDARA TENTANG PETUNJUK PELAKSANAAN PERATURAN

KESELAMATAN PENERBANGAN SIPIL BAGIAN 8900-6.1

(STAFF INSTRUCTION PART 8900-6.1) TENTANG

PEMERIKSAAN PESAWAT UDARA {AIRCRAFT INSPECTION)

Pasal 1

Memberlakukan Petunjuk Teknis Peraturan Keselamatan

Penerbangan Sipil Bagian 8900-6.1 (Staff Instruction Part

8900-6.2) Tentang Pemeriksaan Pesawat Udara (Aircraft

Inspection) sebagaimana tercantum dalam Lampiran yang

merupakan bagian tak terpisahkan dari Peraturan ini.

Pasal 2

Sejak berlakunya peraturan ini, maka Volume 2

Chapter 224 dan Chapter 225 Lampiran Peraturan Direktur

Jenderal Perhubungan Udara Nomor SKEP/44/III/2010

Tentang Staff Instruction 8300 (SI 8300) Airworthiness

Inspector's Handbook dicabut dan dinyatakan tidak

berlaku.

Pasal 3

Direktur Kelaikudaraan dan Pengoperasian Pesawat Udara

mengawasi Pelaksanaan Peraturan ini.

Pasal 4

Peraturan ini mulai berlaku sejak tanggal ditetapkan,

Ditetapkan : Jakarta

Pada tanggal : 11 OKTOBER 2017

DIREKTUR JENDERAL PERHUBUNGAN UDARA

ttd

Dr. Ir. AGUS SANTOSO, M.Sc

aslinya, Mla Mgian hukum

k/

UNAt

■ ^DAH Pt/p^AMA sflPT/ (IV/a)

NIP. 19680704 199503 2 001

LAMPIRAN PERATURAN DIREKTUR JENDERAL PERHUBUNGAN UDARANOMOR : KP 294 Tahun 2017TANGGAL : 11 Oktober2017

Staff Instruction

SI 8900 - 6.1

AIRCRAFT INSPECTION

Amendment : 0

Date : October 2017

REPUBLIC OF INDONESIA - MINISTRY OF TRANSPORTATION

DIRECTORATE GENERAL OF CIVIL AVIATION

JAKARTA - INDONESIA

J51 rUKlVl OyUU-D.l

OCTOBER 2017

AMENDMENT RECORD LIST

Amendment

No.Issue Date REFERENCE

Original Issue OCX 2017 -

SI FORM 8900-6.1

OCTOBER 2017

1. PURPOSE :

FOREWORD

This Staff Instruction on Aircraft Inspection isprepared for use and guidance of DGCA inspectorsand applicant dealing with DGCA for performingaircraft inspection to issuance Certificate ofAirworthiness (Original or Recurrent). It isdesigned to provide foundation for promotingsafety through proactive safety oversight system.The provision of this staff instruction shall applyto the aircraft inspection activities on both,original and recurrent of issuance airworthinesscertificate domestic and foreign aircraft operators.

All subject matters pertaining to aircraftinspection activities, procedures, functions andresponsibilities of DGCA are covered in this StaffInstruction.

2. REFERENCES :

3. CANCELLATION

4. AMENDMENT ;

This Staff Instruction should be used in

accordance with the applicable regulations.

SI 8300 Amdt. 4 Volume 2, Chapter 224, datedMarch 25*^, 2010 is canceled.

SI 8300 Amdt. 4 Volume 2, Chapter 225, datedMarch 25^, 2010 is canceled.

The amendment of this Staff Instruction shall be

approved by the Director General of Civil Aviation.

DIRECTOR GENERAL OF CIVIL AVIATION

signed

Dr. Ir. AGUS SANTOSO M. Sc

^suai aslinyavpaLab^gian hukum

LDAH PtlRNAMA SARI■^^Peiribfna / (IV/a)

NIP. 19680704 199503 2 001

IV

SI 8900-6.1

OCTOBER 2017

TABLE OF CONTENT

. AMENDMENT RECORD LIST i

FOREWORD ii

TABLE OF CONTENTS iii

CHAPTER I - INTRODUCTION 1

1. Aircraft Inspection 1

2. Purpose 1

CHAPTER II - AIRCRAFT INSPECTION POLICY 4

1. General 4

2. The Aircraft Inspection 4

3. The Physical Inspection Involves the Completion of DetailedChecklists and encompasses 4

4. Function of Directorate of Airworthiness and Aircraft Operations

(DAAO) for Aircraft Inspection in Issuing Airworthiness Certificate of

Aircraft (C of A) 19

5. Function of DGCA Regional Office 20

6. Function of Airworthiness Inspector Assigned for The Aircraft 20

Inspection

CHAPTER III - AIRCRAFT INSPECTION PROCEDURES 21

1. Aircraft Inspection And Related Processes - Overview 21

2. General instructions - Aircraft Inspection 21CHAPTER IV - AIRCRAFT INSPECTION FINDINGS 23

1. General 23

2. Findings - Categorization 23

CHAPTER V - FOLLOW UP ACTIONS 24

1. Aircraft Inspection - Follow-up Actions 24

2. Actions Resulting From An Inspection 243. Aircraft Grounded By DGCA Inspection Team 244. Generation And Distribution Of Aircraft Inspection Findings 24

5. Further Follow Up 24

CHAPTER VI - MONITORING OF AIRCRAFT INSPECTION DEFICIENCIES 25

1. Monitoring Deficiencies by DGCA (DAAO Office) 25

2. Review at DGCA (DAAO office) 253. Safety Related Issues 25

4. Records 25

APPENDIX 1 - QUALIFICATION AND TRAINING OF RAMP INSPECTOR 26

1. Competencies of the Inspector 26

2. Qualifications of the Inspector 263. Aircraft Certification Training 26

APPENDIX 2 - DGCA REFERENCES FOR AIRCRAFT INSPECTIONS

GUIDANCE 27

1. PART I General Data 27

2. PART II Aircraft Status 28

3. PART III Aircraft Inspection 32

SI 8900-6.1

OCTOBER 2017

4. PART IV Functional Check 45

5. PART V Ground Run and Test Flight 46

APPENDIX 3 - AIRCRAFT INSPECTION CHECKLIST 47

Instruction to complete Aircraft Inspection Checklist (DGCA Form 21.40) 47

Aircraft Inspection Checklist 49

SI 8900-6.1

OCTOBER 2017

CHAPTER I

INTRODUCTION

1. Aircraft inspection

Aircraft Inspections are planned inspections carried out to verify thecompliance of laid down standards and regulations prior issuing anairworthiness certificate ( Original or Recurrent ). This inspection iscarried out by a DGCA inspector as per standard checklist.

No aircraft may be operated unless a Certificate of Airworthiness hasbeen issued to that aircraft. DGCA is responsible to perform inspectionand test do determined its compliance with airworthiness standards.Standard Certificate of Airworthiness is issued to aeroplane certificatedin the transport, normal, utility, acrobatic, commuter categoiy and tohelicopter certificated in normsd and transport category, and to airshipand manned free balloon. Special Certificate of Airworthiness is issuedto aircraft operated in the limited, restricted, experimental and specialflight permit.

Refer to Staff Instruction SI 21-02, Original certification covers theinitial issuance of standeird or special airworthiness certificates.Recurrent certification applies to the issuance of standard or specialairworthiness certificates for aircraft that previously have been issuedan airworthiness certificate.

This Staff Instruction is prepared for use and guidance of DGCAinspectors for performing original and recurrent certification of aircraft.

2. Purpose

The purpose of the aircraft inspection is to determine its compliancewith airworthiness standard.

The aircraft inspection performed during original and recurrentcertification must be in accordance with the followings:

a. Original CertiHcationOriginal certification covers the initial issuance of standard orspecial airworthiness certificates and approvals, including export foraircraft and aeronautical products for aircraft holding a Republic ofIndonesia type design as follows:1) Aircraft or related products (new or used) that have not left the

original product manufacturer's quality control system.2) Aircraft or related products for which an DGCA airworthiness

certificate or approval has never been issued. Examples include:(a) All provisional Airworthiness Certificates and amendmentsthereto.

(b) All experimental certificates and amendments thereto,including amateur-built aircraft which are new or have beensubjected to a major change.

(c) Limited airworthiness certificates.(d) Aircraft manufactured to other than Republic of Indonesia,

requirements imported to the Republic of Indonesia.

SI 8900-6.1

OCTOBER 2017

3) Aircraft that previously have been issued an airworthinesscertificate and presented for certification in another category orclassification, for example; aircraft converted from standard torestricted for the first time or from a special airworthinesscertificate to standard for the first time.

4) Aircraft that have undergone changes to the type design andrequire flight testing, for example, under an experimentalcertificate for the purpose of showing compliance with regulationsincluding, as applicable, the issuance or reissuance of a standardairworthiness certificate.

5) Prototype or test articles to be used for design evsduation for TC orSTC purposes. This includes parts or installation approvals.

6) Aircraft with an DGCA-approved type design that have undergonea model change, as listed on the airworthiness certificate, andrequire a conformity inspection before issuance of an amendedairworthiness certificate.

7) Aircraft manufactured to a Indonesian ■ TC (TC Validation) andexported from a country with which the ROI has a bilateralagreement, when accompanied by an Export C of A from abilateral civil aviation authority (CAA). The CAA's Export C of Amust contain a statement from that CAA stating that the aircraftconforms to the type design approved under Indonesian TypeCertificate and is in a condition for safe operation.

8) Issuance of special flight permits for aircraft that previously havenot been issued an airworthiness certificate.

b. Recurrent Certification.

The term recurrent certificationll applies to the issuance of standardor special airworthiness certificates or approvals for the following:1) Aircraft that previously have been issued an airworthiness

certificate except those listed in paragraphs 2 a. 3) through 8) ofthis Staff Instruction.

2) Issuance of special flight permits for aircraft which have beenissued an airworthiness certificate.

3) Export certification or approval of aeronautical products orarticles that previously have been issued an airworthinesscertificate or approval.

4) Issuance of airworthiness certificates, except experimental andprovisional, for aircraft with certificates that have expired, beensurrendered, or been revoked.

5) Changes to operating limitations.6) Issuance of experimental certificates for research and developmentand exhibition which have expired.

7) ROI manufactured aircraft returning to the ROI. which werepreviously issued an airworthiness certificate or an Export C of Ain the R.I.

8) Aircraft manufactured to a Indonesian TC (TC Validation) andexported from a country with which the ROI has a bilateralagreement, when accompanied by an Export C of A from abilateral civil aviation authority (CAA). The CAA's Export C of Amust contain a statement from that CAA stating that the aircraftconforms to the type design approved under Indonesian TypeCertificate and is in a condition for safe operation.

SI 8900-6.1

OCTOBER 2017

Aircraft Inspection is concerned with the aircraft documents and theconditions of aircraft. The applicable requirements for these inspectionsare:

i. CASR Part 21, Part 91, Part 121, Part 135, Part 43, Part 39 andothers related CASR.

ii. Aircraft Manufacture Manual (Maintenance Manual, StructuralRepair Manual, Aircraft Weight 8b Balance Manual, Illustrated PartCatalog, Wiring Diagram Manual, etc).

iii. Aircraft delivery documentation, including build standards,components status, inspection and test;

iv. Operator Manual, including Maintenance Program, ReliabilityProgram, Continuous Airworthiness and Surveillance Program;

V. Aircraft document, including damage record, repair record,alteration record, Component Status, AD/SB status, etc.

Original and Recurrent certification of aircraft must be filed with IMSISdatabase.

Aircraft Inspection for issuance airworthiness certificate must beperformed at least 3 (three) working days for document and physicalcheck.

SI 8900-6.1OCTOBER 2017

CHAPTER II

AIRCRAFT INSPECTION POLICY

1. GENERAL

DGCA is responsible to cariy out the inspection for issuanceAirworthiness Certificate of aircraft (C of A).

2. THE AIRCRAFT INSPECTION

A. The DGCA Airworthiness Inspector will conduct inspection ofaircraft to check the aircrafts physic and aircraft document.Purpose of inspection is determining whether the aircraft conformsto the type design, any modification or repairs have been carriedout in accordance to approved data, and to ensure the aircraft isin a condition for safe operation (refer to CASR 21.183(c)).

B. The applicant must prepare an aircraft for inspection by the DGCAinspector on an agreed date.

3. THE PHYSICAL INSPECTION INVOLVES THE COMPLETION OF

DETAILED CHECKLISTS, AND ENCOMPASSES

The items to be checked by the DGCA inspector divided by 2 (two)categories, document check and physical check.

A. Document check

The document to be checked by the DGCA inspector duringaircraft inspection are summarized as:

a. Part I General Data

DGCA inspector must check

l.A. Aircraft Make Model:

Nationality Ss Registration Marks; Registration Number;Serial Number; A/C Category; Mfg. Year; Operator; TC/TCValidation Number ( Rev/Date); MTOW; No OF SEAT;TCDS; total time, current inspection, last inspection (tsn/csn ); aircraft utilization during one year ( year/hours/ cycles).

I.E. Engine Make & Model

(S/N, TSN, CSN, TBO, Remaining)

I.e. Propeller /Rotor Make & Model


l.D. APU Make & Model

SI 8900-6.1

OCTOBER 2017


I.E. Landing Gear :

Nose L/G, Left Main L/G, Right Main L/G (P/N, S/N, TBO,Remaining)

b. Part II Aircraft Status

DGCA inspector must check

II.A. Aircraft document and manual

II.A. 1. Certificate of Registration,II.A.2. Certificate of Airworthiness,II.A.3. Insurance,II.A.4. Maintenance manual,II.A.5. Weight and balance manual,II.A.6. Wiring diagram manual,II.A.7. Structure repair manual,II.A.8. Illustrated part catalog,II.A.9. Aircraft flight manual/ pilot operating handbook,II.A. 10. Flight crew operating handbook,II.A. 11. Quick reference handbook,II.A. 12. Master MEL and/or MEL,II.A. 13. Noise certificate,II.A. 14. Aircraft aeronautical station license.

II.B. Logbook and test reportII.B.l. Aircraft flight/ maintenance log,II.B.2. Deferred item list (ie, HIL, CDL, DMI, DDR),II.B.3. Airframe, engine, propeller,II.B.4. Compass wing and data report,II.B.5. Weight and balance report,II.B.6. Altimeter and static system test report,II.B.7. ATC transponder test report and mode Stransponder

encoding,II.B.8. VOR inspection for IFR andII.B.9. ELT test report.

II.C. Aircraft inspection and maintenance reportsII.C.l. Statement of build standard (new aircraft) from

manufacturer,II.C.2. Statement of accident/incident from the last

operator (if any),II.C.3. Approved maintenance program (Doc. No,

revision, date),II.C.4. Inspection work package for compliance,

annual/100 Hrs inspection, structuralinspection program, corrosion protection controlprogram, non routine inspection,

II.C.5. Component status (OC, CM, HT), life limitedpart (for bridging ref AC 121-1),

SI 8900-6.1

OCTOBER 2017

II.C.6. Airworthiness directives, alert service bulletingstatus,

II.C.7. Damage and repair status and work packagereport,

II.C.8. Alteration/modification status and workpackage and

II.C.9. Service difficulty report.

B. Physical check

The physical check performed by the DGCA inspector duringaircraft inspection are summarized as:

c. Part III Aircraft Inspection

DGCA inspector must check:

III.A. External Visual InspectionIII.A.l. Landing gear/ skid and wheel well areaIII.A. 1.1. Data plate, pacards and marking;III.A. 1.2. Sign of corrosion, wear, chafing lines or

wires;III.A.l.3. Structural integrity of gears and doors for

cracks, dents, other obvious damage,III.A. 1.4. Sign of leaks (struts, actuators valves, tube

and hose),III.A. 1.5. Wheel installation and safety locking device,III.A.l.6. Tire condition,III.A. 1.7. Brake installation for security, wear,

condition and leaks,III.A. 1.8. Skids and floats for security and condition,III.A. 1.9. Steering mechanism for security, wear, and

condition,III.A. 1.10. Brake pin indicator for minimum length,III.A. 1.11. Torque links for security and excessive play,III.A. 1.12. Fairing for security and missing fasteners,III.A. 1.13. Lighting for condition,III.A. 1.14. Main gear static discharge.

III.A.2. Fuselage and EmpenageIII.A.2.1. Identification Plate (CASR 45.11)

a. Aircraft

It must be secured to the aircraft fuselage

exterior so that it is legible to a person on the

ground, and must be either adjacent to and aftof the rearmost entrance door or on the

fuselage surface near the tail surfaces;

b. Manned Free Balloons

It must be secured to the balloon envelope and

must be located, if practicable, where it is

legible to the operator when the balloon is

inflated. In addition, the basket and heater

SI 8900-6.1

OCTOBER 2017

assembly must be permanently and legiblymarked with the manufacturer's name, part

number (or equivalent), aind serial number (orequivalent).

c. Power Parachute and Weight Shift Control

It must be secured to the aircraft fuselage

exterior so that it is legible to a person on theground.

d. Additional Identification Plate (Nationality &Registration Marks) CASR 45.30)It must be secured to the aircraft in a

prominent position near pilot's entrance;

III.A.2.2. Nationality 86 registration marks and national

flag for legibility, location and size, and othermarking requirements (casr 45.21, 45.22,

45.23, 45.24, 45.25. 45.27, 45.29),

III.A.2.3. Structure for cracks, corrosion, dents, rubbing

and other obvious damages,

III.A.2.4. Exterior exit markings and exterior emergency

lighting and escape route (casr 121.310,

135.349),

III.A.2.5. Drain holes for obstruction stain or other sign

of leaks,

III.A.2.6. Radome, pitot tubes, static ports, stall

warning, windshield, wiper, sensors, antennas,

for condition, security 86 corrosion,

III.A.2.7. Loose/missing improper fasteners,

III.A.2.8. Elevators, rudder and tabs for obvious damage,

cracks, corrosions, rubbing and excessive play,

III.A.2.9. Fire discharge dishes for indication,

III.A.2,10. Lavatory (evidence of fresh blue water streaks).

III.A.3. Auxiliaiy Power Unit

III.A.3.1. Identification plate,

IILA.3.2. Door for security and missing/loose fastener;

III.A.3.3. Any indication of wear, leak, chaffing line, wire;

III.A.3.4. Fire extinguisher and sensor.

III.A.4. Wings and Pylon

III.A.4.1. All lights for general condition and broken

lenses,

ni.A.4.2. Structure for cracks, corrosion, dents and

other damage;

III .A. 4.3. Fuel caps for security

III.A.4.4. Wing tip for general condition and damage

SI 8900-6.1

OCTOBER 2017

III .A. 4.5. Anti/de-icing devices for condition and damageIII.A.4.6. Leading edge for dents, abrasion, obvious

damage, and stall warning for functioncondition

III.A.4.7. Leading edge devices, rubber boots, wiring,hoses, for condition and leak

IILA.4.8. Evidence of fuel leaks;

IILA.4.9. Flaps, flaps track and flaps well for cracks,corrosion, leaks, abrasion, dents,

delamination, and condition of connectors,

wiring, lines and hoses

IILA.4.10. Aileron and tabs for obvious cracks, corrosion,

dents, delimination, excessive play

IILA.4.11. Static discharge for condition;

nLA.4,12. Access panels/hatch/inspection door for

security

11I.A.5. Power Plants

III.A. 5.1. Engine identificarion plate (casr 45.11);

IILA.5.2. Fan blade, turbine blade, and sensors for

damage,

111 .A. 5.3. Engine mount, cowling and pylons,

IIl.A.5.4. Cowling 86 doors for security and missing/loose

fasteners,

IILA.5.5. Inlet cowl for dents, corrosion aind abrasion,

IILA.5.6. Acoustic, access panel for security, dents,

corrosion, delimination and crack,

IILA.5.7. Reverse doors for stowage security and leaks,

III .A. 5.8. Exhaust for turbine/tail pipe damage and

leaks,

lll.A.5.9. Fire extinguisher bottle gauge for security and

correct pressure.

II1.A.6. Propeller/ Rotor

ni.A.6,1. Propeller/rotor identification plate;

III.A.6.2. Propeller blade and deicer boots, for dent,

crack, deterioration, delamination and general

condition;

III.A.6.3. Drive shaft, yoke, swash plate, rotor head for

wear, dent, crack, deterioration, delamination

and general condition;

III .A. 6.4. Spinner for cracks and dent;

III.A.6.5. Main rotor blades, for secured, wear, obvious

damage, and general condition (including colorcodes);

IIl.A.6.6. Tail rotor for secured, wear, obvious damage,

and general condition;

10

SI 8900-6.1

OCTOBER 2017

III.A.6.7. Tail rotor gearbox, drive shaft and oil level for

securily, cracks, damage, leaks and general

condition.

III.B Interior Inspection

III.B. 1. Lavatory fire protection;

III.B. 1.1. Each lavatory in the airplane must be equipped

with a smoke detector system or equivalentprovides a warning light in the cockpit or

provides a warning light or audio warning inthe passenger cabin readily detected by a flightattendant

III.B. 1.2. Each lavatory in the airplane must be equippedwith a built-in fire extinguisher and capable of

automatic discharge, for each disposalreceptacle for towels, paper, or waste located inthe lavatory

III.B.2. Emergency Equipment and Additional

Emergency Equipment (CASR 91.207, 91.533, CASR 121.309, CASR 121.310, CASR121 App. A, CASR 135.349)

note: Each item of emergency and flotationequipment:

(1) Must be inspected regularly, and soindicated date of last inspection;

(2) Must be readily accessible to the crew;

(3) Must be clearly identified and clearly markedto indicate its method of operation; and

When carried in a compartment or container,must be marked on the compartment orcontainer, the date of last inspection

III.B.2.1. Hand Fire Extinguisher

Note:

a. At least two of the required hand fire

extinguisher installed in passenger carryingairplanes must contain Halon 1211 (CASR121.309) or equivalent extinguisher agent.

b. At least one of the required hand fireextinguisher installed in passenger carryingairplanes must contain Halon 1211 (CASR135.349)

c. For individual Certificate of Airworthiness is

first issued on or after 31 December 2016

11

SI 8900-6.1

OCTOBER 2017

shall not be of a type listed in the 1987Montreal Protocol (Annex A, Group 11.)

1. Halon 1211

2. Halon 1301

3. Halon 2402

A. At least one hand fire extinguisher must beconveniently located for use:

i. in each galley compartment

ii. in each class E cargo compartment

iii. on the flight deck

B. In passenger compartment, at least oneHalon 1211 (CASR 121.309)

III.B.2.2.

7 - 30 at least one

o

1

CO

at least two

61-200 Minimum 3 ea

201-300 Minimum 4 ea



Firs§R}dTfiP,^ust

> 600 Minimum 8 ea

In passenger compartment

(CASR 135.349)

> 9 at least one

In passenger compartment

(CASR 91.533)

oOC

t

at least one

> 30 at least two

0-50 Minimum 1 ea

51-150 Minimum 2 ea


to the crew, stored seci

12

SI 8900-6.1

OCTOBER 2017

> 250 Minimum 4 ea

> 9 pax seat (CASR 135. 349)

First Aid Kit, must be readily acessible to thecrew, stored securely, free form dust, moisture

and temperature (CASR 91.533)

o o o muminiM1

ea

101 -200

muminiM2

ea

201 - 300

muminiM3

ea

301 - 400

muminiM4

ea

401 - 500

muminiM5

ea

>500

muminiM6

ea

III.B.2.3. Emergency Medical Kit (check contain in

accordance with appendix A)

At least one (CASR 121 Appendix A)

In airplanes for which a flight attendant is

required ( CASR 135.349)

III.B.2.4. Crash Axe

a. Each airplane accommodating more than 19

passengers (CASR 91.533)

b. Each airplane operated under CASR 135that has a lockable non frangible door

separating the flight deck from the

passenger cabin (CASR 135.349)

c. Each airplane operated under CASR 121

(CASR 121.309)

III.B.2.5. Megaphone (CASR 91.533, 121.309)

III.B.2.6.

61 -99 1 ea (rearward)

> 992 ea (forward 8b

rearward)

Emergency Exit (CASR 91.607, CASR 135.349,

CASR 121.310)

a. Interior Emergency Exit marking, placement

and legibility

b. Lighting for interior emergency exit marking

13

SI 8900-6.1

OCTOBER 2017

c. Emergency exit operating handles andinstruction

d. Emergency exit access, must beunobstructed

III.B.2.7. Portable lights, ensure available for each flightattendant seat and accesible from each fight

attendant seat (CASR 91.205, CASR 121.310,

CASR 135.357)

III.B.2.8 Protective Breathing Equipment (CASR

121.337)

a. One in flight deck

b. One PBE is required for each hand fireextinguisher located for use in a galley

c. One PBE is required for each hand fire

extinguisher in pax compartment (located

within 3 feet from hand firex)

d. One for use in each Class A, B, and E cargo

compartment

III.B.2.9 Portable Oxygen (CASR 121.333)

III.B.2.10 Emergency Locator Transmitter, type 406

(CASR 91.207).

Note: If the aircraft installed with fixed and

deployable automatic type transmitters, it

must be attached to the airplane as far aft as

practicable

a. Type of ELT

Automatic Fixed (AF)

Automatic Portable (AP)

Automatic Deployable (AD)

Survival (S)

b. < 20 passenger seat at least one (automatic)

Record ELT Battery due:

c. > 19 passengers for which the individual

certificate of airworthiness is first issued

after 1 July 2008 at least two (one of whichshall be automatic)


and

d. ELT annual inspection (after the lastinspection) for:

(i) Proper installation

(ii) Battery corrosion

(iii) Operation of the controls and crashsensor

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The presence of a sufficient signal radiatedfrom its antenna

e. ELT encoding

III.B.3. Emergency Equipment for Overwater Operation(CASR 91, 207, 91.223, CASR 121.309,121.339, CASR 135.349, 135.351, 135.355)

III.B.4. Miscellaneous Equipment (CASR 121.313,

135.321)

III.B.4.1. Spare of protective fuse or bulb (if installed)III.B.4.2. A windshield wiper or equivalent for each pilot

station

III.B.4.3. Two independent static pressure systems

III.B.4.4. A means to monitor from the flight deck side of

the door the area outside the flight deck door(except for cargo)

III.B.4.5. Door between the passenger and pilot or crewrest compartments, for transport category

and/or cargo operation with a mtow in excess

of 45.500 kg or with a passenger seatinggreater than 60

III.B.4.6. A placard on each door of access to a an

emergency exit, to indicate that it must be

open during takeoff and landing

III.B.5. Passenger Information (CASR 121.317)

III.B.5.1. Passenger information marking and placard in

Bahasa or Bilingual (Bahasa - English) (CASR21.29 a.3)

a. Fasten seat belt sign or placard is visible

from each passenger seat

b. No smoking sign or placard, in cabin and

lavatory

III.B.6. Public Address System

III.B.6.1. Public Address System (more than 19 pax)(CASR 121.318, CASR 135.331)

(note: Transport category manufactured afterDecember 1996)

III.B.7. Crewmember Interphone SystemIII.B.7.1. Crewmember Interphone System (more than 19

pax) (CASR 121.319, CASR 135.333)

III.B.8. Passenger Briefing Card

III.B.8.1. Passenger Briefing Card (CASR 91.537(b),

CASR 121.503(b), CASR 135.107(b)

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III.B.9. Seats, Safety Belts, Shoulder Harnesses, andChild Restraint Systems (CASH 121.311,CASK 135.119, CASK 91.521)

III.B.9.1. Passenger seats, seat belts,cushion/upholstery materials, armrest forcondition, reclining mechanism for properoperations

III.B.9.2. Exit seat, check table, reclining mechanism tomake sure not blocking emergency exit ( CASK121.585, 135.121)

III.B.9.3. Child Restraint System, check for securityIII.B.9.4. At each flight deck station equipped with a

combined safety belt and shoulder harness,

check for security

III.B.IO. Cargo and Bagggage Compartment (CASR121.221)

III.B.10.1. Fire precaution

a. Class "A" (All parts of the compartment areeasily accesible and fire therein would beready discernible to a crew member)

There must be a hand fire extinguisher

available for each Class A compartment.

b. Class "B" (Enough access for crew memberto reach all the compartment and no smoke,

flame or extingushing agent enter thecompartment occupied by crew or

passanger)

(1) It must have a separate approved smokeor fire detector system to give warning atthe pilot or flight engineer station

(2) There must be a hand fire extinguisheravailable for the compartment

(3) It must be lined with fire resistantmaterial

c. Class "C" (Not conform with requirementClass A, B, D or E)

1. It must have a separate smoke or firedetector system to give warning at thepilot or flight engineer station

2. It must have an approved built-in fireextinguishing system controlled from thepilot or flight engineer station

3. It must be designed to exclude hazardousquantities of smoke, flames, orextinguishing agents from entering into

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any compartment occupied by the crew orpassenger

4. It must have ventilation and draft

controlled so that the extinguishing agentprovided can control any fire that maystart in the compartment

5. It must be lined with fire resistant

material

d. Class "D" (Designed and constructed that afire occuring therein will be completelyconfined without endargingthe safety of theairplane or occupants)

1. It must have a means to exclude

hazardous quantities of smoke, flames,or noxious gases from entering anycompartment occupied by the crew orpassengers

2. Ventilation and drafts must be controlled

within each compartment

3. It must be completely lined with fireresistant material

e. Class "E" for Cargo only

1. It must be completely lined with fireresistant material

2. It must have a separate system of anapproved type smoke or fire detector togive warning at the pilot or flightengineer station

3. It must have a means to shut off the

ventilating air flow to or within thecompartment and the controls for thatmeans must be accessible to the flightcrew in the crew compartment

4. It must have a means to exclude

hazardous quantities of smoke, flames,or noxious gases from entering the flightcrew compartment

III.B.10.2. Check cargo door for leaks, damage andgeneral condition

III.B.10.3. Smoke detectors for damage

III.B. 10,4. Lighting is operable and protective cover isinstalled

III.B.10.5. Flooring and pallet system for generalcondition

III.B.10.6. Placard of weight limitation for availability andlegibility

III.B. 10.7. A 9G cargo net for condition (if applicable)

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III.C. COCKPIT INSPECTION

INSTRUMENT, EQUIPMENT MARKING, PLACARD ARE

CORRECTLY INSTALLED AND LEGIBLE.

III.C.l. Instrument for VFR (day) (CASR 91.205)

III.C. 1.1. Airspeed indicator

III. C. 1.2. Altimeter

III.C. 1.3 Magnetic Direction Indicator

III.C. 1.4. A tachometer for each engineIII.C. 1.5 A cylinder head temperature indicator for each

air cooled eng.

III.C. 1.6. Oil in temperature indicator for each engineIII.C. 1.7. A fuel quantity indicator for each fuel tank

III.C. 1.8. An oil pressure indicator for each engine

III.C, 1.9. A manifold pressure indicator for each engineIII.C. 1.10. Landing gear position indicator, if the aircraft

has a retractable landing gear

III.C.2. Instrument for IFR (CASR 91.205), specified

requirement VFR (day)III.C,2.1. Gyroscopic rate of turn indicator

III.C.2.2. Slip/Skid indicator

III.C.2.3. Sensitive altimeter adjustable for barometric

pressure

III.C.2.4. Clock

III.C.2.5. Gjrroscopic pitch and bank indicator (AH)

III.C.2.6. Gyroscopic direction indicator (directional gyroor equivalent)

1II.C.3. Flight and Navigation Instrument (CASR

121.305)

III.C.3.1. An airspeed indicating system with heated pitottube

III.C.3.2. Two sensitive pressure altimeter

III.C.3.3. Clock

III,C.3.4. A free air temperture indicator

III.C.3.5. Gyroscopic pitch and bank indicator (AH)III.C.3.6. Gjn-oscopic rate and turn indicator combined

with an integral skip/skid indicator (turn andbank indicator)

III.C.3.7. Gjrroscopic direction indicator (dyrectional gyroor equivedent)

III.C.3.8. A magnetic compass

III.C.3.9. A vertical speed indicator (rate of climb

indicator)

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III.C.3.10. Two Gyroscopic pitch and bank indicator (AH)or :

Third Gyroscopic pitch and bank indicator (AH)

for:

(i). turbojet ,or

(ii). turbo prop having pax seat >30 or payload> 7500 lbs

III.C.4. Engine Instrument (CASR 121.307)

III.0.4.1. Oil in temperature indicator for each engine

III.C.4.2. A fuel pressure indicator for each engine

III.C.4.3. A means for indicating fuel quantity for each

fuel tank

III.C.4.4. An oil pressure indicator for each engine

III.C.4.5. An oil quantity indicator for each oil tank

III.C.4.6. An independent fuel pressure warning devicefor each engine or a master warning device for

all engines

III.0.5. Flight and navigation Instrument (CASR

135.305)

III.0.5.1. Two independent airspeed indicating systemIII.0.5.2. Two independent sensitive altimeter systemin.0.5.3. Clock

II1.0.5.4. A free air temperature indicator

III.0.5.5. Gyroscopic direction indicator (directional gyro

or equivalent)

III. 0.5.6. A magnetic compass

III.0.5.7. Gyroscopic pitch and bank indicator (AH)III.0.5.8. Vertical speed indicator (rate of climb indicator)

IIl.C.5.9. Two Gyroscopic pitch and bank indicator (AH)for turbojet and turbo prop.

III.0.5.10. Third Gjnroscopic pitch and bank indicator (AH)

for turbojet

III.0.6. Engine Instrument (CASR 135.317)III.0.6.1. A tachometer for each engineIII.0.6.2. A carburetor air temperature indicator for each

engine

III.0.6.3. A cylinder head temperature indicator for each

air cooled eng.

III.0.6.4. Oil in temperature indicator for each engineIII.0.6.5. A fuel pressure indicator for each engine111.0.6.6. A fuel flowmeter or fuel mixture indicator for

each engine not equipped with an automaticaltitude mixture control

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III.C.6.7, A means for indicating fuel quantity for eachfuel tank

III.C.6,8. An oil pressure indicator for each engine

III.C.6.9. An oil quantity indicator for each oil tankIILC.6.10. An independent fuel pressure warning device

for each engine or a master warning device for

all engines

III.C.6.11. A device for each reversible propeller

III.C.6.12. A manifold pressure indicator for each engine

III.C.7. Navigation and Radio Communication

(CASR 91.205, CASR 91.175CASR, 91.215,

CASR 121.99, CASR 121.349, CASR

135.309, CASR 135.311, CASR 121.345,)III.C.7.1. HF

III.C.7.2. VHP

III.C.7.3. ATC Trainsponder

III.C.7.4. VOR

III.C.7.5. DME

III.C.7.6. ILS

III.C.8. EQUIPMENTS

III.C.8.1. Weather Radar (CASR 121.357, 135.315)

III.C.8.2. 1. TCAS (CASR 91.227)

Turbine, MTOW>33.000 lbs (15.000 Kg) for

which the individual Airworthiness

Certificate is first issued after 31 December

2015, shall be equipped with TCAS II

2. TCAS (CASR 121.356)

a. Turbine, MTOW>33.000 lbs (15.000 Kg),TSO 119a, version 6,04A Enhance or

equivalent installed before May 1, 2003

TSO 119b, version 7.1 or a later or

equivalent

b. Combi airplane PaxlO - 30 seat TCAS I

TSO 118

c. Piston, MTOW>33.000 lbs TCAS I TSO

118

III.C.8.3. TAWS (CASR 121.354, CASR 135.319)

TSO C-151Class A or equivalent for >9 pax

TSO C-151Class B or equivalent for 6-9 pax

CASR 91.229

MTOW > 5700 kg or Pax seat >9

TSO C-151 or equivalent

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III.C.8.4. GPS/INS/Doppler Radar/ONS/IRS or FMS(CASR 121.355, CASR 121.358)

III.C.8.5. Low altitude windshear system (CASR121.352)

Aeroplanes (except turboprop) manufactured

after 2 January 1991, must be equipped with

either an approved airborne windshear warning

&i flight guidance system, an approved airborne

detection & avoidance system, or combination

of these systems

III.C.8.6. Pitot Heat Indicating System (CASR 121.342,

CASR 135.325)

AH transport category aicraft (CASR 121.342)>20 pax (CASR 135.325)

III.C.8.7. Flight Data Recorder, check for applicability

and type of FDR CASR 91.233 and Appendix E(Airplane), F (Helicopter)

AIRPLANE

i All airplane first issue of C of A on or after

IJanuaiy 1989 with maximum certificated

take-off mass more than 27.000 kg (Type IFDR)

ii All airplane first issue C of A on or after 1

Jan. 1989 with maximum certificated take

off mass more than 5.700 kg, up to andincluding 27.000 kg (Type II FDR)

iii All airplane first issue of C of A after 1

January 2005 with maximum certificated

take-off mass more than 5.700 kg (Type LA)iv All turbine engine airplane first issue of C of

A on or after 1 January 2016 with a seating

configuration of more than 5 passenger seatand maximum certificated take-off mass of

5700 kg or less (Type II)HELICOPTER

i AH helicopters first issued of C of A on or

after 1 January 2016 with maximum

certificated take-off mass more than 3180

kg (Type IVA)ii AH helicopters first issued of C of A on or

after 1 January 1989 with maximum

certificated take-off mass more than 7000

kg or having a passanger seatingconfiguration of more than 19 (Type IV)

Record ULB Battery due:

Annual read out for required number of

parameter to be recorded and quality(measurement range, recording interval,accuracy, resolution)

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Calibration for 5 year or at least 2 year in

accordance with

manufacturer recommendation

III.C.8.8. CVR/CARS (CASR 91.235)

AIRPLANE

i All turbine-engine airplanes, for which the

individual certificate of airworthiness was

first issued on or after 1 January 2016, with

a seating configurations of more than five

passenger seats and a maximum certificated

take-off mass of 5 700 kg or less shall be

equipped with either a CVR or a CARS

ii All turbine-engine airplanes for a maximum

certificated take-off mass of over 5 700 kgfor which the individual certificate of

airworthiness was first issued on or after 1

January 2016 and required to be operated

by more than one pilot shall be equippedwith a CVR

iii All airplanes of a maximum certificated

take-off mass of over 27 000 kg for whichthe individual certificate of airworthiness is

first issued on or after 1 January 1987 shallbe equipped with a CVR

HELICOPTER

i All helicopters of a maximum certificated

take-off mass of over 7 000 kg for which the

individual certificate of airworthiness is first

issued on or after 1 January 1987 shall be

equipped with a CVR. For helicopters notequipped with an FDR, at least main rotor

speed shall be recorded on the CVR

ii All helicopters of a maximum certificated

take-off mass of over 7 000 kg for which the

individual certificate of airworthiness was

first issued before 1 January 1987 shall beequipped with a CVR. For helicopters notequipped with an FDR, at least main rotor

speed shall be recorded on the CVR

From 1 January 2016, a magnetic tape & wireshall be discontinued, and capable of two

hours recordingFrom 1 January 2016, all CVR shall be capableof retaining the information recorded during atleast the last two hours of their operation

Record ULB Battery, due:

Annual Examination

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IILC.9. Lighting (CASR 91.209, CASR 121.323,

CASR 135.307)

III.C.9.1. Instrument light

III.C.9.2. Anti Collision light

III.C.9.3. Position/Navigation light

III.C.9.4. Two Landing light

IILC.9.5. Taxi light

III.C.9.6. Logo light

III.C.9.7. Cabin light (ceiling, windows, service, entry,

exit, etc.)

d. Part IV Functional Check

DGCA Inspector must check :

IV.A Aircraft SystemIV. A. 1. Flight control system

rV.A.2. Recording system (FDR, CVR)IV.A.3. Fire precaution (engine, APU, cargo)IV.A.4. Smoke detector system (lavatory, cargo)IV.A.5. Public address system and interphone systemIV.A.6. Pitot heat indicating systemIV.A.7. Lighting (nav. Light anti-collision light,

instrument light, landing light, emergeny light,passenger information light)

IV.A. 8. ELTtest

IV.A.9. Other applicable systems.

IV. B. Communication

IV.B.l. HF, VHF, ATC transponder

IV.C. Navigation;

IV.C. 1. ADF, VOR, DME, ILS;

IV,C.2. Weather radar;

IV.C.3. TAWS TSO C151 class A and windshear;IV.C.4. TCAS;

IV.C.5. GPS/INS/IRS/FMS.

e. Part V Ground Run and Test Flight

DGCA Inspector must check :

V. 1. Ground run and test flight conducted

according to test plane;V.2. Ground run and test result;V.3. Test flight result.

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OCTOBER 2017

4. FUNCTION OF DIRECTORATE OF AIRWORTHINESS AND

AIRCRAFT OPERATIONS (DAAO) FOR AIRCRAFT INSPECTION IN

ISSUING AIRWORTHINESS CERTIFICATE OF AIRCRAFT (C OF

A)

The DGCA (DAAO Office) shall have following function to ensurecompliance of the Aircraft inspection programme:• To plan Aircraft Inspection Annualy for Indonesia aircraft

registered.

• To designate Airworthiness Inspector to conduct AircraftInspection.

• To maintain Inspector Training and Experience meet withrequirement as per Staff Instruction SI 8900-1.3 Inspector TrainingSystem.

• To maintain report of aircraft inspection in DGCA (DAAO Office)and notify the findings of aircraft inspection to the operators.

• To ensure follow up actions.

• To ensure that root cause analysis is carried out by the operators toprevent repeat findings.

• To organize regular meetings with all airworthiness inspectors tomaintain a high standard of quality relating to:

o any changes/updates to the aircraft inspection procedures,

o feedback on quality issues with regard to aircraft inspectionreports e.g. incorrect entry's, mistakes, omissions, etc.,

• To carry out analysis of findings operator wise and finding wise andinitiate action for improvement if required.

• To initiate investigation depending upon seriousness of findingsreported and initiate enforcement action as per enforcement policyand procedures on the basis of investigation report if required.

DAAO coordination for aircraft inspection is performed by Sub-Directorate Maintenance for coordination of the program. To facilitatethe implementation of aircraft inspection activities a coordinatedapproach is needed at DAAO. The monitoring of the aircraft inspectionshall be done similarly as other surveillance activities. The recordsshould be stored in the DAAO IMSIS data base system.

5. FUNCTION OF DGCA REGIONAL OFFICE

The DGCA Regional Office shall have following function to ensurecompliance of the aircraft inspection programme:

• Regional office received order from DAAO to perform aircraftinspection, according to DAAO annualy plan.

• To designate airworthiness inspector to conduct aircraft inspection.

• To maintain Inspector Training and Experience meet withrequirement as per Staff Instruction SI 8900-1.3 Inspector TrainingSystem.

• To report of aircraft inspection to DGCA (DAAO Office) and notify thefindings of aircraft inspection to the operators.

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SI 8900-6.1

OCTOBER 2017

• To ensure follow up actions.

• To maintain in the DAAO IMSIS database aircraft inspection recordperformed by their regional office.

6. FUNCTION OF AIRWORTHINESS INSPECTOR ASSIGNED FOR THEAIRCRAFT INSPECTION

Airworthiness inspectors assigned for the aircraft inspection mustensure that the aircraft inspections are carried out efficiently followingthis Staff Instruction as per applicable check list and report generatedand submitted to the respective Inspector office (DAAOOffice or DGCA Regional Office).

CHAPTER III

AIRCRAFT INSPECTION PROCEDURES

1. Aircraft Inspection and Related Processes - Overview

Aircraft Inspection

Finding(s)

Corrective action

Issue 0 of A

a. The inspection process consists of different elements like thepreparation of the inspection, the determination of which items needto be inspected and which standards to use. General guidance onthe DGCA regulation references are placed at Appendix 2.

b. There are three different categories of findings, depending on theimpact the finding has on the safety of the aircraft and/or itsoccupants. Chapter 4 of this Staff Instructions provides guidance onthe categorization of findings.

c. Based on the outcome of the inspection and subsequentcategorization, follow-up actions as detailed in Chapter 5 shall betaken.

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2. General Instructions - Aircraft Inspection

a. The main elements of the aircraft inspection are check generaldata, check aircraft status, perform physical aircraft inspection alsowitness of functional check, ground run and test flight (if necessary).

b.The inspection shall be as comprehensive as possible within thetime and resources available. The checklist to be used for carryingout the aircraft inspection (DGCA Form 21-40) is given at the StaffInstruction SI Form - 01.

c. The general principle shall be that the aircraft inspection,applicant must provide the available aircraft to inspect by DGCAinspector in sufficient time.

d. The applicant must prepare an aircraft for inspection by the DGCAinspector, the physical aircraft inspection time required by theDGCA inspector is at least 4 hours.

e. All findings during the physical aircraft inspection process must benotified to the accompan3dng operator's representative.

f. When conducting functional check, ground run and test flight, theoperator's representative must provide personnel who have training,licensed and experienced on the inspected aircraft.

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CHAPTER IV

AIRCRAFT INSPECTION FINDINGS

1. General

Aircraft inspection aims at assessing the compliance with theapplicable standards of an aircraft used in operations. A non-compliance found during an inspection is called a finding.

Findings found during original and recurrent inspection must becompleted prior issuance of particular certificate.

Processing findings:

1. Issued letter to the operator

2. Received corrective action from operator

3. Communicate with operator

2. Findings - Categorization

If during the inspection it is established that a certain situation is notin compliance with the relevant standards, this is then considered afinding. For each inspection item, 3 (three) categories of possibledeviations from the standards have been defined. The findings arecategorized as below according to the seriousness and perceivedinfluence on flight safely.

Minor : Category 1 finding is considered to have a minorinfluence on safety.

SigniHcant : Categoiy 2 finding may have a significant influence onsafety

Major : Category 3 finding may have a major influence onsafety.

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CHAPTER V

FOLLOW UP ACTIONS

1. Aircraft Inspection - Follow-up Actions

Follow up actions will be taken after the aircraft inspection. The follow-up actions may be distinguished in two stages. The first stage is thefollow-up action directly resulting from the findings, the second stage isthe monitoring and follow-up of any correspondence, sent out to theoperator.

2. Actions Resulting From An Inspection

Based on the results of the inspection and on how the findings havebeen categorized, following common follow-up actions may be used inorder of the seriousness of the findings.

1. Aircraft grounded by DGCA inspector

2. Corrective actions before issued the Airworthiness Certificate (C ofA)

3. No remarks

3. Aircraft Grounded By DGCA Inspection Team

If the category 3 (major) findings that have been established during theAircraft Inspection concern damage of a nature such that the aircraft isno longer airworthy, this has to be communicated immediately to theoperator. Although the first contact may be, as a matter of urgency,accomplished by telephone, it is advisable to use writtencommunication procedures.

An aircraft is grounded in a situation where the category 3 (three) majorfindings are not corrected by the operator before flight. Because thesafety of the aircraft and its occupants is at stake, the aircraft has to beprevented from resuming its flight and has to be ̂ grounded' until thesafety hazard is removedr

4. Generation And Distribution Of Aircraft Inspection Findings

The inspection report shall be generated after finalization of findings.The reports along with the findings shall be uploaded on IMSISdatabase. The Aircraft Inspection report along with findings shall bedistributed to operator.

The DGCA Regional Office should ensure the proper distribution ofAircraft Inspection Reports on Operators, with a copy to DGCA (DAAOOffice).

5. Further Follow Up

Any follow-up communication from the operators and the authoritiesshould be acknowledged and they should be informed about the closureof findings. Any request for clarification should equally be responded bythe DGCA (DAAO Office or Regional Office). The feedback or

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SI 8900-6.1

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clarifications from the DGCA (DAAO Office or Regional Office) should beperformed within 30 working days.

Findings should remain "open" as long as no satisfactory response ofthe operator. Findings could be closed if a re-inspection confirms thatthe appropriate corrective action was taken.

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CHAPTER VI

MONITORING OF AIRCRAFT INSPECTION DEFICIENCIES

1. Monitoring Deficiencies by DGCA (DAAO Office)

All deficiencies observed during aircraft inspection carried out by thevarious regional offices are required to be forwarded in a prescribedPerforma to the DGCA (DAAO Office) after the inspection.

2. Review at DGCA (DAAO office)

The review meeting for the compliance of aircraft inspection deficienciesis held at DGCA (DAAO Office), under the chairmanship of the Directorof Airworthiness and Aircraft Operations (DAAO).

The review of the aircraft maintenance program will be also carried outin the surveillance meeting. All major findings shall be discussed in themeeting to take a view on the action to be taken against the concernedorganization/operator/personnel.

3. Safety Related Issues

All , DGCA Airworthiness Inspector assigned for the Aircraft Inspectionshall report potential safety related issues reported during aircraftinspections and propose coordinated actions to the DAAO office whennecessary to address the problem.

Utilization of safety related information, necessaiy corrective actionsand appropriate effective preventive measures shall be initiated byDGCA to promote safety.

4. Records

All records related to Aircraft Inspection and follow up actions shall bemaintained at DGCA office and DGCA Regional Office. Soft copy of datashall be also maintained in IMSIS Database.

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APPENDIX 1

QUALIFICATION AND TRAINING OF INSPECTOR

1. Competencies of the Inspector

To cany out Aircraft Inspection in the most effective and efficientmanner, appropriate qualified and competent inspectors should bedeputed to cany out the task. This Chapter describes the trainingrequirements to reach the established level of competencies ofinspectors for this purpose. The DGCA (DAAO Office and RegionalOffice) should ensure that inspectors are competent to carry out thetasks assigned to them and that they are aware of the consequence oftheir actions for aviation safety.

2. Qualifications of the Inspector

The DGCA Inspector should meet the following qualification andexperience requirements:

a) Should have received initial and recurrent training as per StaffInstruction SI 8900-1.3 Inspector Training System and should befamiliar with CASR.

b) Should be familiar with the problems of operating or maintainingaircraft;

3. Aircraft CertiHcation Training

The training for aircraft inspection refer to SI 8900-1.3 InspectorTraining System

a. FCN 6003 Aircraft Certification.

b. FCN 6203 Major Repair and Alteration

c. FCN 61001 Airworthiness Directives

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APPENDIX 2

DGCA REFERENCES FOR AIRCRAFT INSPECTIONS GUIDANCE

Civil Aviation Safety Regulations Requirements

CASRPart91.

CASRPart 121.

CASR Part 135.

CASR Part 43.

CASR Part 45.

CASR Part 36

CASR Part 25.

PART I GENERAL DATA

I.A. AIRCRAFT MAKE MODEL

• Nationality 6b Registration Marks, Registration Number, Serial Number,Aircraft Category, Mfg. Year, Operator, TC/TCDS, Validation Number( Rev/Date), MTOW and Number OF SEATReference; TC, TCDS and Certificate of Registration

• TOTAL TIME, CURRENT INSPECTION, LAST INSPECTION (TSN/CSN),AIRCRAFT UTILIZATION DURING ONE YEAR (YEAR/ HOURS/CYCLES)

Reference: Aircraft Logbook

I.B. ENGINE MAKE & MODEL

• (S/N, TSN, CSN, TBO, Remaining)Reference: Engine Logbook

I.e. PROPELLER /ROTOR MAKE & MODEL

• (S/N, TSN, CSN, TBO, Remaining)

Reference: Propeller Logbook

I.D. APU MAKE & MODEL

• (S/N, TSN, CSN, TBO, Remaining)

Reference: APU Logbook

I.E. LANDING GEAR

• Nose L/G, Left Main L/G, Right Main L/G (P/N, S/N, TBO, Remaining)

Reference: Component Status

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PART II AIRCRAFT STATUS

II.A. Aircraft document and manual

• II.A.l. Certificate of Registration,Reference:

CASR 47

CASR 91.25

ILA.2. Certificate of Airworthiness

Reference:

CASR 21

CASR 91.25

II.A.3. Insurance

Reference:

CASR 47

CASR 91.25

II.A.4. Maintenance manual

Reference:

CASR 43

II.A.5. Weight and balance manualReference:

CASR 121.135(d)(7)CASR 121.153

CASR 121.165

CASR 135.135(d)(4)CASR 135.153

CASR 135.360

CASR 135.601

II.A.6. Wiring diagram manualReference:

CASR 43

II.A.7. Structure repair manualReference:

CASR 43

II.A.8. Illustrated part catalogReference:

CASR 43

II.A.9. Aircraft flight manual/ pilot operating handbookII.A. 10. Flight crew operating manualII.A. 11. Quick reference handbookReference:

CASR 91,25

CASR 91. 529(c)CASR 121.135(d)CASR 121.141

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CASR 121.143

CASR 121.173

CASR 135.135

CASR 135.143

CASR 135.173

CASR 135.175

CASR 135.183

CASR 135.303

CASR 135.307

II.A.12. Master MEL and/or MELReference:

CASR 91.509

CASR 121.135(c)(19)CASR 121 Appendix PCASR 135.303

CASR 135.321

CASR 135.443

CASR 135.445

CASR 135.611

CASR 135.637

II.A.13. Noise certificate

Reference:

CASR 21.183

CASR 36

CASR 91.25

CASR 91.525

CASR 91.529

II.A.14. Aircraft aeronautical station license

Reference:

CASR 91.25

Il.B. Logbook and test report

II.B.l. Aircraft flight/ maintenance logIl.B.2. Deferred item list (ie, HIL, CDL, DMI, DDR)Reference:

CASR 91.25

CASR 91.145

CASR 121.563

CASR 121.701

CASR 121.709

CASR 135.563

CASR 135.701

CASR 135.709

Il.B.3. Airframe, engine, propellerReference:

CASR 43.2

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II.B.4. Compass swing and data reportReference:

CASR 121.305

CASR 135.305

ILB,5. Weight and balance reportReference:

CASR 121.135

CASR 121.153

CASR 121.165

CASR 135.135

CASR 135.153

CASR 135.360

II.B.6. Altimeter and static system test reportReference:

CASR 43 Appendix ECASR 91.411

II.B.7. ATC transponder test report and mode S transponder encodingReference:

CASR 91.413

CASR 43 Appendix F

n.B.8. VOR inspection for IFRReference:

CASR 91.171

II.B.9. ELT test reportReference:

CASR 91.207

II.C. Aircraft inspection and maintenance reports

II.C. 1. Statement of build standard (new aircraft) from manufacturerReference:

CASR 21 Subpart H

II.C.2. Statement of accident/incident from the last operator (if any)Reference:

CASR 21.3

II.C.3. Approved maintenance program (Doc. No, revision, date)Reference:

CASR 91.409

CASR 135.367

CASR 121.367

II.C.4. Inspection work package for compliance, annual/100 Hrsinspection, structural inspection program, corrosionprotection control program, non routine inspection

Reference:

CASR 43 Appendix D

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CASR 121.367

CASR 135.367

CASR 135xGe

II.C.5. Component status (OC, CM, HT), life limited part (for bridging refAC 121-1)

Reference:

CASR 43.1

CASR 43.2

CASR 43.11

CASR 91.409

CASR 121.367

CASR 135.367

II.C.6. Airworthiness directives, alert service bulleting statusReference:

CASR 39

CASR 91.213

CASR 91.403

CASR 91.409

CASR 91.417

CASR 91.421

CASR 91.551

CASR 121.369

CASR 121.380

CASR 121.628

CASR 135.157

CASR 135.380

CASR 135.628

CASR 135.xGe

II.C.7. Damage and repair status and work package reportReference:

CASR 43.9

CASR 121.707

CASR 135.707

II.C.8. Alteration/modification status and work package andReference:

CASR 43 Appendix ACASR 121.707

CASR 135.707

II.C.9. Service difficulty reportReference:

CASR 121.703

CASR 135.703

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PART III AIRCRAFT INSPECTION

III.A. External Visual Inspection

III.A.l. Landing gear/ skid and wheel well areaIII.A. 1.1. Data plate, placards and markingReference:

CASR 45.11

CASR 45.13

III.A. 1.2. Sign of corrosion, wear, chafing lines or wiresReference: NIL

III.A. 1.3. Structural integrity of gears and doors for cracks, dents,other obvious damage

Reference: NIL

III.A. 1.4. Sign of leaks (struts, actuators valves, tube and hose)Reference: NIL

III.A. 1.5. Wheel installation and safety locking deviceReference:

CASR 43 Appendix D

III.A. 1.6. Tire condition

Reference:

CASR 43 Appendix D

III.A. 1.7. Brake installation for security, wear, condition and leaksReference:

CASR 43 Appendix D

III.A. 1.8. Skids and floats for security and conditionReference:

CASR 91.205

III.A. 1.9. Steering mechanism for security, wear, and conditionReference:

CASR91xA.2

III.A. 1.10. Brake pin indicator for minimum lengthReference: NIL

III.A. 1.11. Torque links for security and excessive playReference: NIL

III.A. 1.12. Fairing for security and missing fastenersReference: NIL

III.A. 1.13. Lighting for conditionReference: NIL

III.A. 1.14. Main gear static dischargeReference: NIL

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11I.A.2. Fuselage and EmpenageIII.A.2.1. Identification Plate

Reference:

CASR 45.11

CASR 45.30

a. Aircraft

It must be secured to the aircraft fuselage exterior so that it islegible to a person on the ground, and must be either

adjacent to and aft of the rearmost entrance door or on the

fuselage surface near the tail surfaces

Reference:

CASR 45.11


It must be secured to the balloon envelope and must be

located, if practicable, where it is legible to the operator whenthe balloon is inflated. In addition, the basket and heater

assembly must be permanently and legibly marked with the

manufacturer's name, part number (or equivalent), and serialnumber (or equivalent)

Reference:

CASR 45.11

c. Power Parachute and Weight Shift Control

It must be secured to the aircraft fuselage exterior so that it islegible to a person on the groundReference:

CASR 45.11

d. Additional Identification Plate (Nationality & RegistrationMarks)

It must be secured to the aircraft in a prominent positionnear pilot's entrance

Reference:

CASR 45.30

III.A.2.2. Nationality 85 registration marks and national flag forlegibility, location and size, and other marking requirements

Reference:

CASR 45.21

CASR 45.22

CASR 45.23

CASR 45.24

CASR 45.25

CASR 45.27

CASR 45.29

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III.A.2.3. Structure for cracks, corrosion, dents, rubbing and otherobvious damages

Reference: NIL

III.A.2.4. Exterior exit markings and exterior emergency lighting and

escape route

Reference:

CASR 121.310

CASR 135.349

III.A.2.5. Drain holes for obstruction stain or other sign of leaksReference: NIL

III.A.2.6. Radome, pitot tubes, static ports, stall warning, windshield,wiper, sensors, antennas, for condition, security 8e corrosion

Reference:

CASR91xA.2

CASR 25.1323

III.A.2.7. Loose/missing improper fasteners

III.A.2.8. Elevators, rudder and tabs for obvious damage, cracks,corrosions, rubbing and excessive play

Reference: NIL

III.A.2.9. Fire discharge dishes for indicationReference:

CASR 91.533

CASR 121.221

CASR 121.309

CASR 135.349

IILA.2,10. Lavatory (evidence of fresh blue water streaks)Reference:

CASR 121.308

CASR 135.347

CASR 25.820

CASR 25.854

IILA.3. Auxiliary Power Unit

IILA.3.1. Identification plate

Reference:

CASR 45.11

CASR 45.13

CASR 45.30

IILA.3.2. Door for security and missing/loose fastenerIII.A.3.3. Any indication of wear, leak, chaffing line, wire

Reference: NIL

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III.A.3.4. Fire extinguisher and sensor

Reference:

CASR 91.533

CASR 121.221

CASR 121.309

CASR 135.349

1II.A.4. Wings and Pylon

III.A.4.1. AH lights for general condition and broken lensesReference:

CASR 121.310

CASR 135.349

III.A.4.2. Structure for cracks, corrosion, dents and other damageIII.A.4.3. Fuel caps for security

IILA.4.4. Wing tip for general condition and damageIII.A.4.5. Anti/de-icing devices for condition and damageIII.A.4.6. Leading edge for dents, abrasion, obvious damage, and stall

warning for function condition

III.A,4.7. Leading edge devices, rubber boots, wiring, hoses, forcondition and leak

III.A.4.8. Evidence of fuel leaks;

III.A.4.9. Flaps, flaps track and flaps well for cracks, corrosion, leaks,abrasion, dents, delamination, and condition of connectors,


III.A.4.10. Aileron and tabs for obvious cracks, corrosion, dents,

delimination, excessive play

III.A.4.11. Static discharge for condition;

III.A.4.12. Access panels/hatch/inspection door for security

Reference: Aircraft Maintenance Manual

III.A.5. Power Plants

ni.A.5.1. Engine identification plate

Reference:

CASR 45.11

CASR 45.13

CASR 45.30

III.A.5.2. Fan blade, turbine blade, and sensors for damage

III.A.5.3. Engine mount, cowling and pylons

III.A.5.4. Cowling 86 doors for security and missing/loose fasteners

III.A.5.5. Inlet cowl for dents, corrosion and abrasion

III.A.5.6. Acoustic, access panel for security, dents, corrosion,delimination and crack

III.A.5.7. Reverse doors for stowage security and leaks,

III.A.5.8. Exhaust for turbine/tail pipe damage and leaks

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III.A.5.9, Fire extinguisher bottle gauge for security and correctpressure

Reference: Engine and Aircraft Maintenance Manual

1II.A.6. Propeller/ Rotor

III.A.6.1. Propeller/rotor identification plateReference:

CASR 45.11

CASR 45.13

CASR 45.30

ni.A.6.2. Propeller blade and deicer boots, for dent, crack,deterioration, delamination and general condition

III.A.6.3. Drive shaft, yoke, swash plate, rotor head for wear, dent,crack, deterioration, delamination and general condition

III.A.6.4. Spinner for cracks and dent

III.A.6.5. Main rotor blades, for secured, wear, obvious damage, and

general condition (including color codes)

III.A.6.6. Tail rotor for secured, wear, obvious damage, and general

condition;

III.A.6.7. Tail rotor gearbox, drive shaft and oil level for security,

cracks, damage, leaks and general condition

Reference: Propeller, Rotor and Aircraft Maintenance Manual

III.B Interior Inspection

III.B. 1. Lavatory fire protection;

III.B. 1.1. Each lavatory in the airplane must be equipped with a smoke

detector system or equivalent provides a warning light in the

cockpit or provides a warning light or audio warning in the

passenger cabin readily detected by a flight attendant

III.B. 1.2. Each lavatory in the airplane must be equipped with a built-

in fire extinguisher and capable of automatic discharge, for

each disposal receptacle for towels, paper, or waste located in

the lavatory

III.B.2. Emergency Equipment and Additional Emergency Equipment

note: Each item of emergency and flotation equipment:

(1) Must be inspected regularly, and so indicated date of lastinspection;

(2) Must he readily accessible to the crew;

(3) Must be clearly identified and clearly marked to indicate itsmethod of operation; and

When carried in a compartment or container, must be marked

on the compartment or container, the date of last inspection

III.B.2.1. Hand Fire Extinguisher

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Note:

a. At least two of the required hand fire extinguisher installedin passenger cariying airplanes must contain Halon 1211(CASR 121.309) or equivalent extinguisher agent.

b. At least one of the required hand fire extinguisher installedin passenger canying airplanes must contain Halon 1211(CASR 135.349)

c. For individual Certificate of Airworthiness is first issued on

or after 31 December 2016 shall not be of a type listed inthe 1987 Montreal Protocol (Annex A, Group II.)

1. Halon 1211

2. Halon 1301

3. Halon 2402

A. At least one hand fire extinguisher must be conveniently

located for use:


ii. in each class E cargo compartment


B. In passenger compartment, at least one Halon 1211

(CASR 121.309)

7 - 30 at least one

31 - 60 at least two

61-200 Minimum 3 ea





> 600 Minimum 8 ea

In passenger compartment (CASR

135.349)

> 9 at least one


91.533)

42

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OCTOBER 2017

—r^^-30

0-50

at least oneMinimum 1 ea

> oU

51 - 150 Minimum 2 ea


> 250 Minimum 4 ea

> 9 pax seat (CASR 135. 349)

III.B.2.2. First Aid Kit, must be readily acessible to the crew, storedsecurely, free form dust, moisture and temperature (CASR

121 App. A)

First Aid Kit, must be readily acessible to the crew, stored

securely, free form dust, moisture and temperature (CASR

91.533)



201 -300 Minimum 3 ea



>500 Minimum 6 ea

IILB.2.3. Emergency Medical Kit (check contain in accordance with

appendix A)


In airplanes for which a flight attendant is reqxiired ( CASR

135.349)

III.B.2.4. Crash Axe

a. Each airplane accommodating more than 19

passengers (CASR 91.533)

b. Each airplane operated under CASR 135 that

has a lockable non frangible door separating the flight deck

from the passenger cabin (CASR 135,349)

c. Each airplane operated under CASR 121 (CASR

121.309)

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III.B.2.5. Megaphone (CASR 91.533, 121.309)61 -99 1 ea (rearward)

> 99 2 ea (forward &rearward

)

III.B.2.6. Emergency Exit (CASR 91.607, CASR 135.349, CASR121.310)

a. Interior Emergency Exit marking, placement and legibility

b. Lighting for interior emergency exit marking

c. Emergency exit operating handles and instruction

d. Emergency exit access, must be unobstructed

III.B.2.7. Portable lights, ensure available for each flight attendant seat

and accesible from each fight attendant seat (CASR 91.205,CASR 121.310, CASR 135.357)

III.B.2.8 Protective Breathing Equipment (CASR 121.337)a. One in flight deck

b. One PBE is required for each hand fire extinguisher

located for use in a galley

c. One PBE is required for each hand fire extinguisher in pax

compartment (located within 3 feet from hand firex)d. One for use in each Class A, B, and E cargo compartment

III.B.2.9 Portable O^^gen (CASR 121.333)

III.B.2.10 Emergency Locator Transmitter, type 406 (CASR 91.207).

Note: If the aircraft installed with fixed and deployableautomatic type transmitters, it must be attached to the

airplane as far aift as practicable

a. Type of ELT




Survival (S)

b. < 20 passenger seat at least one (automatic)


c. > 19 passengers for which the individual certificate of

airworthiness is first issued after 1 July 2008 at least two(one of which shall be automatic)


and

d. ELT annual inspection (after the last inspection) for:

(iv) Proper installation

(v) Battery corrosion

(vi) Operation of the controls and crash sensor

44

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The presence of a sufficient signal radiated from its antenna

e. ELT encoding

III.B.3. Emergency Equipment for Overwater Operation (CASR 91,207, 91.223, CASR 121.309, 121.339, CASR 135.349,135.351, 135.355)

III.B.4. Miscellaneous Equipment (CASR 121.313, 135.321)

III.B.4.1. Spare of protective fuse or bulb (if installed)

HI.B.4.2. A windshield wiper or equivalent for each pilot stationIII.B.4.3. Two independent static pressure systems

III.B.4.4. A means to monitor from the flight deck side of the door the

area outside the flight deck door (except for cargo)

III.B.4.5. Door between the passenger and pilot or crew rest

compartments, for transport category and/or cargo operation

with a mtow in excess of 45.500 kg or with a passenger

seating greater than 60

III.B.4.6. A placard on each door of access to a an emergency exit, toindicate that it must be open during takeoff and landing

III.B.5. Passenger Information (CASR 121.317)III.B.5.1. Passenger information marking and placard in Bahasa or

Bilingual (Bahasa - English) (CASR 21.29 a.3)

a. Fasten seat belt sign or placard is visible from each

passenger seat

b. No smoking sign or placard, in cabin and lavatory

III.B.6. Public Address System

III,B.6,1. Public Address System (more than 19 pax) (CASR 121.318,CASR 135.331)

(note: Transport category manufactured after December 1996)III.B.7. Crewmember Interphone System

III.B.7.1. Crewmember Interphone System (more than 19 pax) (CASR

121.319, CASR 135.333)

III.B.8. Passenger Briefing Card

III.B.8.1. Passenger Briefing Card (CASR 91.537(b), CASR 121.503(b),

CASR 135.107(b)

III,B.9. Seats, Safety Belts, Shoulder Harnesses, and Child Restraint

Systems (CASR 121.311, CASR 135.119, CASR 91.521)III.B.9.1. Passenger seats, seat belts, cushion/upholstery materials,

armrest for condition, reclining mechanism for properoperations

III.B.9.2. Exit seat, check table, reclining mechanism to make sure notblocking emergency exit ( CASR 121.585, 135.121)

III.B.9.3. Child Restraint System, check for security

III.B.9.4. At each flight deck station equipped with a combined safety

belt and shoulder harness, check for security

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III.B.IO. Cargo and Bagggage Compartment (CASR 121.221)

III.B.lO.l. Fire precaution

a. Class "A" (All parts of the compartment are easily accesible

and fire therein would be ready discernible to a crewmember)

There must be a hand fire extinguisher available for each

Class A compartment.

b. Class "B" (Enough access for crew member to reach all

the compartment and no smoke, flame or extingushingagent enter the compartment occupied by crew or

passanger)

(1) It must have a separate approved smoke or fire detectorsystem to give warning at the pilot or flight engineerstation

(2) There must be a hand fire extinguisher available for thecompartment

(3) It must be lined with fire resistant material

c. Class "C" (Not conform with requirement Class A, B, D orE)

1. It must have a separate smoke or fire detector system togive warning at the pilot or flight engineer station

2. It must have an approved built-in fire extinguishingsystem controlled from the pilot or flight engineer station

3. It must be designed to exclude hazardous quantities ofsmoke, flames, or extinguishing agents from enteringinto any compartment occupied by the crew or passenger

4. It must have ventilation and draft controlled so that the

extinguishing agent provided can control any fire thatmay start in the compartment

5. It must be lined with fire resistant material

d. Class "D" (Designed and constructed that a fire occuringtherein will be completely confined without endargingthesafety of the airplane or occupants)

1. It must have a means to exclude hazardous quantities ofsmoke, flames, or noxious gases from entering anycompartment occupied by the crew or passengers

2. Ventilation and drafts must be controlled within each

compartment

3. It must be completely lined with fire resistant material

e. Class "E" for Cargo only

1. It must be completely lined with fire resistant material

2. It must have a separate system of an approved typesmoke or fire detector to give warning at the pilot or flightengineer station

46

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3. It must have a means to shut off the ventilating air flowto or within the compartment and the controls for thatmeans must be accessible to the flight crew in the crewcompartment

4. It must have a means to exclude hazardous quantities ofsmoke, flames, or noxious gases from entering the flightcrew compartment

III.B. 10.2. Check cargo door for leaks, damage and general condition

III.B.10.3. Smoke detectors for damage

III.B. 10.4. Lighting is operable and protective cover is installed

lll.B.10.5. Flooring and pallet system for general condition

III.B. 10.6. Placard of weight limitation for availability and legibility

lll.B.10.7. A 9G cargo net for condition (if applicable)

III.C. COCKPIT INSPECTION

INSTRUMENT, EQUIPMENT MARKING, PLACARD ARE CORRECTLYINSTALLED AND LEGIBLE.

III.C. 1. Instrument for VFR (day) (CASR 91.205)III. C. 1.1. Airspeed indicator

III. C. 1.2. Altimeter

III. C. 1.3 Magnetic Direction IndicatorIII.C. 1.4. A tachometer for each engine

III.C. 1.5 A cylinder head temperature indicator for each air cooled eng.III.C. 1.6. Oil in temperature indicator for each engineIII.C. 1.7. A fuel quantity indicator for each fuel tankIII.C. 1.8. An oil pressure indicator for each engineIII.C. 1.9. A manifold pressure indicator for each engineIII.C.1.10. Landing gear position indicator, if the aircraft has a

retractable landing gear

III.C.2. Instrument for IFR (CASR 91.205), specified requirement VFR(day)

III.C.2.1. GjTTOScopic rate of turn indicatorIII. C. 2.2. Slip / Skid indicator

III.C.2.3. Sensitive altimeter adjustable for barometric pressureIILC.2.4. Clock

IILC.2.5. Gyroscopic pitch and bank indicator (AH)III.C.2.6. Gyroscopic direction indicator (directional gyro or equivalent)

III.C.3. Flight and Navigation Instrument (CASR 121.305)III.C.3.1. An airspeed indicating system with heated pitot tubeIII.C.3.2. Two sensitive pressure altimeterIII.C.3.3. Clock

III.C.3.4. A free air temperture indicatorIII.C.3.5. Gyroscopic pitch and bank indicator (AH)

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III.C.3.6. Gjn-oscopic rate and turn indicator combined with an integralskip/skid indicator (turn and bank indicator)

III.C.3.7. Gjnroscopic direction indicator (dyrectional gyro or equivalent)III.C.3.8. A magnetic compass

III.C.3.9. A vertical speed indicator (rate of climb indicator)

III.C.3.10. Two Gyroscopic pitch and bank indicator (AH) or :

Third Gyroscopic pitch and bank indicator (AH) for :

(i). turbojet ,or

(ii). turbo prop having pax seat >30 or payload > 7500 lbs

III.C.4, Engine Instrument (CASR 121.307)

III.C.4.1. Oil in temperature indicator for each engine

III.C.4.2. A fuel pressure indicator for each engineIII.C.4.3, A means for indicating fuel quantity for each fuel tank

III.C.4.4. An oil pressure indicator for each engineIII.C.4.5. An oil quantity indicator for each oil tank

111,0.4.6. An independent fuel pressure warning device for each engineor a master warning device for all engines

III.0.5. Flight and navigation Instrument (OASR 135.305)III.0.5.1. Two independent airspeed indicating systemIII.0.5.2. Two independent sensitive altimeter system

III.0.5.3. Clock

III.0.5.4. A free air temperature indicator

III.0.5.5. GjToscopic direction indicator (directional gyro or equivalent)III.0.5.6. A magnetic compass

III.0.5.7. GjToscopic pitch and bank indicator (AH)III.0.5.8. Vertical speed indicator (rate of climb indicator)

III.0.5.9. Two Gyroscopic pitch and bank indicator (AH) for turbojetand turbo prop.

III.0.5.10. Third Gyroscopic pitch and bank indicator (AH) for turbojet

III.0.6. Engine Instrument (OASR 135.317)III.0.6.1. A tachometer for each engine

III.0.6.2. A carburetor air temperature indicator for each engineIII.0.6.3. A cylinder head temperature indicator for each air cooled eng.III.0.6.4. Oil in temperature indicator for each engine

III.0.6.5. A fuel pressure indicator for each engineIII.0.6.6. A fuel flowmeter or fuel mixture indicator for each engine not

equipped with an automatic altitude mixture control

III.0.6.7. A means for indicating fuel quantity for each fuel tank

III.0.6.8. An oil pressure indicator for each engineIII.0.6.9. An oil quantity indicator for each oil tank

III.0.6.10. An independent fuel pressure warning device for each engineor a master warning device for all engines

III.0.6.11. A device for each reversible propeller

48

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III.C.6.12. A manifold pressure indicator for each engine

IILC.7. Navigation and Radio Communication (CASR 91.205, CASR91.175CASR, 91.215, CASR 121.99, CASR 121.349, CASR

135.309, CASR 135.311, CASR 121,345,)

III.C.7.1. HF

III.C.7.2. VHF

III,C.7.3. ATC Transponder

III.C.7.4. VOR

III.C.7.5. DME

III.C.7.6. ILS

IILC.8. EQUIPMENTS

III.C.8.1. Weather Radar (CASR 121.357, 135.315)

III.C.8.2. 1. TCAS (CASR 91.227)

Turbine, MTOW>33.000 lbs (15.000 Kg) for whichthe individual Airworthiness Certificate is first issued after 31

December 2015, shall be equipped with TCAS II2. TCAS (CASR 121.356)

a. Turbine, MTOW>33.000 lbs (15.000 Kg), TSO 119a,

version 6,04A Enhance or equivalent installed before

May 1, 2003

TSO 119b, version 7.1 or a later or equivalent

b. Combi airplane PaxlO - 30 seat TCAS I TSO 118

c. Piston, MTOW>33.000 lbs TCAS I TSO 118

III.C.8.3. TAWS (CASR 121.354, CASR 135.319)

TSO C-151Class A or equivalent for >9 pax

TSO C-151Class B or equivalent for 6-9 pax

CASR 91.229

MTOW > 5700 kg or Pax seat >9

TSO C-151 or equivadent

III.C.8.4. GPS/INS/Doppler Radar/ONS/IRS or FMS

(CASR 121.355, CASR 121.358)

III.C.8.5. Low altitude windshear system (CASR121.352)

Aeroplanes (except turboprop) manufactured after 2 January1991, must be equipped with either an approved airborne

windshear warning & flight guidance system, an approvedairborne detection & avoidance system, or combination ofthese systems

ni.C.8.6. Pitot Heat Indicating System (CASR 121.342, CASR 135.325)

All transport category aicraft (CASR 121.342)>20 pax (CASR 135.325)

III.C.8.7. Flight Data Recorder, check for applicability and type of FDR

CASR 91.233 and Appendix E (Airplane), F (Helicopter)

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AIRPLANE

i Ail airplane first issue of C of A on or after IJanuaiy 1989with maximum certificated take-off mass more than

27.000 kg (Type I FDR)

ii All airplane first issue C of A on or after 1 Jan. 1989 with

maximum certificated take-off mass more than 5.700 kg,up to and including 27.000 kg Ciype II FDR)

iii All airplane first issue of C of A after 1 January 2005 withmaximum certificated take-off mass more than 5.700 kg(Type lA)

iv All turbine engine airplane first issue of C of A on or after1 January 2016 with a seating configuration of more than5 passenger seat and maximum certificated take-off mass

of 5700 kg or less (Type II)HELICOPTER

i All helicopters first issued of C of A on or after 1 January2016 with maximum certificated take-off mass more than

3180 kg (Type IVA)ii All helicopters first issued of C of A on or after 1 January

1989 with maximum certificated take-off mass more than

7000 kg or having a passanger seating configuration ofmore than 19 (Type IV)Record ULB Battery due:Annual read out for required number of parameter to berecorded and quality (measurement range, recordinginterval, accuracy, resolution)

Calibration for 5 year or at least 2 year in accordance with


III.C.8.8. CVR/CARS (CASR 91.235)AIRPLANE

1 All turbine-engine airplanes, for which the individualcertificate of airworthiness was first issued on or after 1

Januaiy 2016, with a seating configurations of more thanfive passenger seats and a maximum certificated take-off

mass of 5 700 kg or less shall be equipped with either aCVR or a CARS

ii All turbine-engine airplanes for a maximum certificatedtake-off mass of over 5 700 kg for which the individualcertificate of airworthiness was first issued on or after 1

January 2016 and required to be operated by more thanone pilot shall be equipped with a CVR

ill All airplanes of a maximum certificated take-off mass ofover 27 000 kg for which the individual certificate of

airworthiness is first issued on or after 1 Januaiy 1987shall be equipped with a CVR

50

SI 8900-6.1

OCTOBER 2017

HELICOPTER

i All helicopters of a maximum certificated take-off mass of

over 7 000 kg for which the individual certificate ofairworthiness is first issued on or after 1 January 1987

shall be equipped with a CVR. For helicopters not

equipped with an FDR, at least main rotor speed shall be

recorded on the CVR

ii All helicopters of a maximum certificated take-off mass of

over 7 000 kg for which the individual certificate of

airworthiness was first issued before 1 January 1987 shall

be equipped with a CVR. For helicopters not equipped with

an FDR, at least main rotor speed shall be recorded on the

CVR

From 1 January 2016, a magnetic tape 85 wire shall be

discontinued, and capable of two hours recording

From 1 Januaiy 2016, all CVR shall be capable of

retaining the information recorded during at least the last

two hours of their operation

Record ULB Battery, due:

Annual Examination

III.C.9. Lighting (CASR 91.209, CASR 121.323, CASR 135.307)

111. C. 9.1. Instrument light

III.C.9.2. Anti Collision lightIII. C.9.3. Position/Navigation light

III. C. 9.4. Two Landing light

III.C.9.5. Taxi light

III.C.9.6. Logo light

III.C.9.7. Cabin light (ceiling, windows, service, entry, exit, etc.)

PART IV FUNCTIONAL CHECK

IV.A Aircraft System

rV.A. 1. Flight control system

IV.A.2. Recording system (FDR, CVR)

IV.A.3. Fire precaution (engine, APU, cargo)

IV.A. 4. Smoke detector system (lavatory, cargo)

IV.A.5. Public address system and interphone system


IV.A. 6. Pitot heat indicating system

Reference:

CASR 121.342

CASR 135.325

IV.A.7. Lighting (nav. Light, anti-collision light, instrument light,

landing light, emergency light, passenger information light)

IV.A. 8. ELTtest


51

SI 8900-6.1

OCTOBER 2017

IV.A.9. Other applicable systems.


IV.B. Communication

IV.B.l. HF, VHF, ATC transponder


IV.C. Navigation

IV.C.l. ADF, VCR, DME, ILS

IV.C.2. Weather radar


IV.C.3. TAWS TSO 0151 class A and windshear

Reference:

CASR 121.352

IV.C,4. TCAS

IV.C.5. GPS/INS/IRS/FMSReference: Aircraft Maintenance Manual

PART V GROUND RUN AND TEST FLIGHT

V, 1. Ground run and test flight conducted according to test planeV.2. Ground run and test result

V.3. Test flight result


52

SI 8900-6.1

OCTOBER 2017

APPENDIX 3

AIRCRAFT INSPECTION CHECKLIST

Instruction to complete Aircraft Inspection Checklist (DGCA Form 21-40)

1) Inspection Place and Date (e.g. CGK, 2 October 2017, SUB, 2 October2017)

2) Aircraft Make Model (e.g. B737-800, ATR 72-600, BELL 429, A320-200)

3) Nationality and Registration Mark (E.G. PK-GIA, PK-DON, PK-LMA)

4) Registration Number : refer to Certificate of Registration (e.g. 1234, 3456,789)

5) Serial Number: Manufacture Serial Number (MSN) (e.g. 549, 2124, 3107)

6) Aircraft Category: refer to TO or TODS (e.g. Transport, Normal, Utility)

7) Manufacture Year: (e.g. 1990, 2000, 2017)

8) Operator : name of aircraft operator (e.g. Garuda, Lion, Sriwijaya)

9) TC/TC Validation Number: number of TO or TO Validation (e.g. A008HOOl, B002)

10) TC/TC Validation Revision: Revision index of TC or TC validation

11) TC/TC Validation Date : Date of TC or TC validation

12) MTOW: Maximum Take of Weight refer to TCDS

. 13) Total Time (TSN fis CSN): Time Since New (TSN) and Cycle Since New referto Aircraft Log Book

a. Total Time Current DGCA Inspection (TSN 86 CSN) : Time Since New (TSN)and Cycle Since New (CSN) when DGCA conduct aircraft Inspection referto Aircraft Log Book

b. Total Time Last DGCA Inspection (TSN 86 CSN): Time Since New (TSN) andCycle Since New (CSN) previous year DGCA conduct aircraft Inspectionrefer to Aircraft Log Book)

14) Aircraft Utilization During One Year (Per 31 December): Check to TSN andCSN per 31 December (e.g. TSN 31 December 2016 minus TSN 31December 2015)

15) Engine Make Model: (e.g. CFM 56-7, JT8D, RR250, PT6A, Trent 700 )16) Engine Serial Number: Manufacture Serial Number (MSN) (e.g. 549, 2124

3107)

17) Engine TSN: Time Since New (TSN) refer to Engine Log Book

18) Engine CSN: Cycle Since New (CSN) refer to Engine Log Book

19) Engine TBO: Time Between Overhaul (TBO) engine refer to CAMP, AMM orMPD

20) Engine Remaining; remaining TSN or CSN of engine compare with TBO '

21) Propeller/Rotor Make and Model: (e.g. Hartzel HC-B3TN-3DY)

22) Propeller/Rotor Serial Number Manufacture Serial Number (MSN) (e.g.549, 2124, 3107)

53

23) Propeller/Rotor TSN: Time Since New (TSN) refer to Propeller/Rotor LogBook

24) Propeller/Rotor CSN: Cycle Since New (CSN) refer to Propeller/Rotor LogBook

25) Propeller/Rotor TBO: Time Between Overhaul (TBO) propeller/rotor referto CAMP, AMM or MPD

26) Propeller/Rotor Remaining: remaining TSN or CSN of propeller/rotorcompare with TBO

27) APU Make and Model: (e.g. GTCP331-350)

28) APU Serial Number: Serial Number Manufacture Serial Number (MSN)(e.g. 549, 2124, 3107)

29) APU TSN: Time Since New (TSN) refer to APU Log Book

30) APU CSN: Cycle Since New (CSN) refer to APU Log Book

31) APU TBO: Time Between Overhaul (TBO) APU refer to CAMP, AMM orMPD

32) APU Remaining: remaining TSN or CSN of APU compare with TBO

33) Nose Landing Gear (part Number, Serial Number, TBO and Remaining)

34) Left Main Landing Gear (part Number, Serial Number, TBO andRemaining)

35) Right Main Landing Gear (part Number, Serial Number, TBO andRemaining)

36) Satisfactory Boxes: Tick for each inspection item performed "YES" or "NO"

37) Remark Boxes: Tick if fmding(s) are noted for each inspection item

38) Action Taken Select the action taken. Information to the representative ofoperator is defaulted action to be taken

a) [0) No remarks

b) (1) Corrective action before issued C ofA

c) (2) Aircraft grounded by DGCA Inspector

39) Item: Inspection item, e.g (ILA.12. Master MEL and/or MEL, II.B.3.Airframe, engine, propeller. III.A. 1.1. Data plate, pacards and marking)

40) Cat: Enter finding category based:G: General remarks or observations1: Category 1 finding is considered to have a minor influence on safety2: Categoiy 2 finding may have a significant influence3: Category 3 finding may have a major influence on safety

41) Remark and Finding : Indicate the detail(s) of the remark or observationor finding

42) Senior Inspector Signature: Inspector(s) name and signature

43) Assign inspector Signature: Inspector(s) name and signature

54

iifemA

MINISTRY OF TRANSPORTATION

DIRECTORATE GENERAL OF CIVIL AVIATION

Gedung Perkantoran Bandara Soekamo-Hatta

Jl. 03, Cengkareng - Tangerang

website: www.dephub.go.id; e-mail: [email protected]

INSPECTION RECORDS ISSUANCE OF ORIGINAL / RECURRENTCERTIFICATE OF AIRWORTHINESS

1). Inspection place and date

iPAimi^MERaLlD^T^M

2). A. AIRCRAFT MAKE MODEL:

3). Nationality &

Registration

Marks

4).

Registration

Number

5). Serial

Number

6). Aircraft

Category7). Mfg

Year

8). Operator

9). TO/TO VaUdation

Number.

10). TC/TC

Validation Revision

11 . TC/TC

Validation Date

12). MTOW

13). Total Time

a). Current DGCA Inspection b). Last DGCA Inspection

TSN (FH)

CSN (PC)

14). Aircra !t utilization duringone year (per 31 December)

Year: Hours Cycles:

15.) B. ENGINE MAKE £s MODEL:

No. 16). Serial Number 17). TSN 18). CSN 19). TBO 20). Remaining

21.) C. PROPELLER/ROTOR MAKE & MODEL:

No. 22). Serial

Number

23). TSN 24). CSN 25). TBO 26). Remaining

1

2

3

4

5

6

27.) D. APU MAKE & MODEL:

No. 28). Serial

Number

29). TSN 30). CSN 31). TBO 32). Remaining

1

E. LANDING GEAR

Nomenclature Part Number Serial Number TBO Remaining

33). Nose L/G

34). Left Main L/G

35). Right Main L/G

A. Aircraft Document & Manual (as applicable)

(check for currency and condition)

Item Description 36).

Satisfactory37). Remarks

Yes No

n.A.i Certificate of Registration

II.A.2 Certificate of Airworthiness

II.A.3 Insurance

II.A.4 Maintenance Manual

II.A.5 Weight & Balance Manual

II.A.6 Wiring Diagram Manual

II.A.7 Structure Repair Manual

II.A.8 Illustrated Part Catalog

II.A.9 Aircraft Flight Manual / Pilot

Operating Handbook

II.A.10 Flight Crew Operating Manual

II.A.11 Quick Reference Handbook

II.A.12 Master M.E.L and M.E.L

II.A.13 Noise Certificate

II.A.14 Aircraft Aeronautical Station License

B. Log Book and Test Report


Satisfactory

37). Remarks

Yes No

II.B.l Aircraft Flight/Maintenance Log

n.B.2Deferred item list (ie. HIL, CDL, DMI,

DDR)

II.B.3 Aiframe, Engine, Propeller

II.B.4 Compass Swing Data Report

II.B.5Weight 8b Balance Report

(CASR 121.153, CASR 135.153)

II.B.6Altimeter 8b Static System Test

Report

(CASR 91.411, CASR 43 App. E)

II.B.7ATC Transponder Test Report

(CASR 91.413, CASR 43 App. F)

Mode S Transponder encoding

II.B.8VOR inspection for IFR (CASR

91.171)

II,B.9ELT Test Report (CASR 91.207)

C. Aircraft Inspection and Maintenance Records


Satisfactory

37). Remarks

Yes No

II.C.l Statement of Build Standard (new

aircraft) from manufacturer

II.C.2 Statement of accident/incident fromthe last operator (if any)

^7

II.C.3 Approved Maintenance Program

(Doc. No, Revision, Date)

II.C.4 Inspection work package for

compIiance:(CASR91.409,135.367,121.367)

Latest inspection type:

date:

at:

/ TSN/CSN

Annual / 100 Hrs Inspection

Structural Inspection Program

Corrosion Protection Control

Program

Non routine inspection

II.C.5 Component status (OC, CM, HT) SsLife Limited Part

(for bridging refAC 121-1)

II.C.6 Airworthiness Directives 85 Allert

Service Bulletin Status

II.C.7 Damage and Repair status and work

package report

II.C.8 Alteration/Modification status andwork package

II.C.9 Service Difficulty Report

tg^|^l^^RC^EgUNSP£C7IONfl|||HA. External Visual Inspection

1. Landing gear / skid and wheel well area


Satisfactory

37). Remarks

Yes No

Data plate, placards and marking

III.A.1.2 Sign of corrosion, wear, chafing lines

or wires

iir.A.1.3 Structural integrity of gears and

-58

doors for cracks, dents, otherobvious damage

III.A.1.4 Sign of leaks (struts, actuatorsvalves, tube and hose)

III.A.1.5 Wheel installation and safety lockingdevice

III.A.1.6 Tire condition

III. A. 1.7 Brake installation for security, wear,condition and leaks

III.A.1.8 Skids and floats for security andcondition

III.A.1.9 Steering mechanism for security,wear, and condition

III.A.1.10 Brake pin indicator for minimum

length

iii.A.i.n Torque links for security andexcessive play

III.A.1.12 Fairing for security and missingfasteners

III.A.1.13 . Lighting for condition

III.A.1.14 Main Gear Static Discharge

2. Fuselage and Empenage



Yes No

III.A.2.1 Identification Plate (CASR 45.11)

a. Aircraft

It must be secured to the aircraft

fuselage exterior so that it is legibleto a person on the ground, and mustbe either adjacent to and aft of therearmost entrance door or on the

fuselage siorface near the tail

surfaces


It must be secured to the balloon

envelope and must be located, ifpracticable, where it is legible to the

operator when the balloon is

inflated. In addition, the basket and

heater assembly must be

permanently and legibly markedwith the manufacturer's name, part

number (or equivalent), and serial

number (or equivalent).

c. Power Parachute and Weight Shift

Control

It must be secured to the aircraft

fuselage exterior so that it is legibleto a person on the ground.

d. Additional Identification Plate

(Nationality & Registration Marks)

CASR 45.30).

It must be secured to the aircraft in

a prominent position near pilot's

entrance

III.A.2.2 Nationality & Registration Marks

and National Flag for legibility,location and size, and other marking

requirements (CASR 45.21, 45.22,

45.23, 45.24, 45.25. 45.27, 45.29)

III:a.2.3 Structure for cracks, corrosion,

dents, rubbing and other obvious

damages

III.A.2.4 Exterior Exit markings and exterior

emergency lighting and escape route(CASR 121.310, 135.349)

III.A.2.5 Drain holes for obstruction stain or

other sign of leaks

III.A.2.6 Radome, pitot tubes, static ports,stall warning, windshield, wiper,sensors, antennas, for condition,security 8b corrosion

Iir.A.2.7 Loose/missing improper fasteners

in.A.2.8 Elevators, rudder and tabs for

obvious damage, cracks, corrosions,

rubbing and excessive play

III.A.2.9 Fire discharge dishes for indication

m.A.2.10 Lavatory Servicing Areas (evidence of

fresh blue water streaks)

3. APU


Satisfactory

37). Remarks

Yes No

III.A.3.1 Identification Plate

m.A.3.2 Door for security and missing/loosefastener

III.A.3.3 Any indication of wear, leak, chaffingline, wire

III.A.3.4 Fire extinguisher and sensor

4. Wings and Pylon



Yes No

m.A.4.1 AH lights for general condition and

broken lenses

III.A.4.2 Structure for cracks, corrosion,

dents and other damage

III.A.4.3 Fuel caps for security

III.A.4.4 Wing tip for general condition and

damage

III.A.4.5 Anti/de-icing devices for conditionand damage

ni.A.4.6 Leading edge for dents, abrasion,

obvious damage, and stall warningfor function condition

III.A.4.7 Leading edge devices, rubber boots,

wiring, hoses, for condition and leak

III.A.4.8 Evidence of fuel leaks

III.A.4,9 Flaps and flaps track for cracks,

corrosion, leaks, abrasion, dents,delamination, and condition of


III.A.4.10 Aileron and tabs for obvious cracks,

corrosion, dents, delimination,

excessive play

m.A.4.11 Static discharge for condition

III.A.4.12 Access panels/hatch/inspection

door for security

5. Power plants


Satisfactory

37). Remarks

Yes No

III.A.5.1 Engine Identification Plate (CASR

45.11)

It must be affixed to the engine at an

accessible location

III.A.5.2 Fan blade, turbine blade, and

sensors for damage

in.A.5.3 Engine mount, cowling and pylons

III.A.5.4 Cowling & doors for security and

missing/loose fasteners

III.A.5.5 Inlet cowl for dents, corrosion and

abrasion

III.A.5.6 Acoustic, access panel for security,

dents, corrosion, delimination and

crack

III.A.5.7 Reverse doors for stowage security

and leaks

III.A.5.8 Exhaust for turbine/tail pipe

damage and leaks

IILA.5.9 Fire extinguisher bottle gauge for

security and correct pressure

6. Propeller / Rotor



Yes No

nLA.6.1 Propeller/rotor Identification Plate

(CASR 45.11)

It must be affixed to the propeller atan accessible location

III.A.6.2 Propeller blade and deicer boots, fordent, crack, deterioration, '

fn

delamination and general condition

IILA.6.3 Drive shaft, yoke, swash plate, rotor

head for wear, dent, crack,

deterioration, delamination and

general condition

in.A.6.4 Spinner for cracks and dent

ni.A.6.5 Main rotor blades, for secured, wear,

obvious damage, and general

condition (including color codes)

III.A.6.6 Tail rotor for secured, wear, obvious

damage, and general condition

m.A.6.7 Tail rotor gearbox, drive shaft and oil

level for security, cracks, damage,

leaks and general condition

B. Interior Inspection

1. Lavatory Fire Protection (CASR 121.308, CASR 135.347)


Satisfactory

37). Remarks

Yes No

Each lavatory in the airplane must

be equipped with a smoke detector

system or equivalent provides a

warning light in the cockpit or

provides a warning light or audio

warning in the passenger cabin

readily detected by a flight attendant

III.B.1.2 Each lavatory in the airplane must

be equipped with a built-in fire

extinguisher and capable ofautomatic discharge, for eachdisposal receptacle for towels, paper,

or waste located in the lavatory

2. Emergency Equipment and Additional Emergency Equipment (CASR 91.207, 91.533, CASR 121.309, CASR 121.310, CASR 121 App. A, CASR 135.349)

note: Each item of emergency and flotation equipment:

(4) Must be inspected regularly, and so indicated date of last inspection;

(5) Must be readily accessible to the crew;

(6) Must be clearly identified and clearly marked to indicate its method of operation;and

(7) When carried in a compartment or container, must be marked on the compartment

f.1

or container, the date of last inspection

Hand Fire Extinguisher

Note:

a. At least two of the required handfire extinguisher installed in

passenger carrying airplanes mustcontain Halon 1211 (CASR 121.309)or equivalent extinguisher agent.

b. At least one of the required handfire extinguisher installed in

passenger carrying airplanes must

contain Halon 1211 (CASR 135.349)

c. For individual Certificate of

Airworthiness is first issued on or

after 31 December 2016 shall not

be of a type listed in the 1987

Montreal Protocol (Annex A, GroupII.)

1. Halon 1211

2. Halon 1301

3. Halon 2402

A. At least one hand fire

extinguisher must be convenientlylocated for use:


ii. in each class E cargo

compartment


B. In passenger compartment, at

least one Halon 1211 (CASR121.309)

7-30

31 - 60

at least one

at least two

AA

61-200 Minimum 3 ea





> 600 Minimum 8 ea


135.349)

>9 at least one


91.533)

7-30 at least one

> 30 at least two

m.B.2.2 First Aid Kit, must be readily

acessible to the crew, stored

securely,

free form dust, moisture and

temperature (CASR 121 App. A)

0-50 Minimum 1 ea

51-150 Minimum 2 ea


>250 Minimum 4 ea

> '9 pax seat (CASR 135. 349)

First Aid Kit, must be readily

acessible to the crew, stored

securely, free form dust, moisture

and temperature (CASR 91.533)

0- 100 Minimum 1 ea





>500 Minimum 6 ea

III.B.2.3 Emergency Medical Kit (check

contain in accordance with appendixA)


In airplanes for which a flightattendant is required ( CASR135.349)

III.B.2.4Crash Axe

a. Each airplane accommodatingmore than 19 passengers (CASR91.533)

b. Each airplane operated underCASR 135 that has a lockable non

frangible door separating the flightdeck from the passenger cabin(CASR 135.349)

c. Each airplane operated underCASR 121 (CASR 121.309)

III.B.2.5 Megaphone (CASR 91.533, 121.309)

61 -991 ea (rearward)

>992 ea (forward &

rearward)

III.B.2.6Emergency Exit (CASR 91.607,CASR 135.349, CASR 121.310)

a. Interior Emergency Exit

marking, placement and legibility

b. Lighting for interior emergencyexit marking

c. Emergency exit operating

handles and instruction

d. Emergency exit access, must

be unobstructed

III.B.2.7 Portable lights, ensure available for

each flight attendant seat and

accesible from each fight attendantseat (CASR 91.205, CASR 121.310,

CASR 135.357)

III.B.2.8 Protective Breathing Equipment(CASR 121.337)

fxf.

a. One in flight deck

b. One PBE is required for eachhand fire extinguisher located foruse in a galley

c. One PBE is required for eachhand fire extinguisher in paxcompartment (located within 3 feetfrom hand firex)

d. One for use in each Class A,B, and E cargo compartment

III.B.2.9 Portable Ojgrgen (CASR 121.333)

m.B.2.10 Emergency Locator Transmitter, type406 (CASR 91.207).

Note: If the aircraft installed with

fixed and deployable automatic type

transmitters, it must be attached to

the airplane as far aft as practicable

a. Type of ELT




Survival (S)

b. < 20 passenger seat at least one

(automatic)


c. > 19 passengers for which theindividual certificate of airworthiness

is first issued after 1 July 2008 at

least two (one of which shall be

automatic)


and

d. ELT annual inspection (after

the last inspection) for:

(vii) Proper installation

(viii) Battery corrosion

(ix) Operation of the controls andcrash sensor

(x) The presence of a sufficientsignal radiated from its antenna

e. ELT encoding

3. Emergency Equipment for Overwater

Operation (CASR 91, 207, 91.223, CASR

121.309, 121.339, CASR 135.349, 135.351,135.355)

4. MisceUaneous Equipment (CASR 121.313, 135.321)

Spare of protective fuse or bulb (ifinstalled)

III.B.4.2 A windshield wiper or equivalent for

each pilot station

III.B.4.3 Two independent static pressuresystems

III.B.4.4 A means to monitor from the flightdeck side of the door the area

outside the flight deck door (exceptfor cargo)

III.B.4.5 Door between the passenger andpilot or crew rest compartments, fortransport category and/or cargooperation with a mtow in excess of

45.500 kg or with a passengerseating greater than 60.

III.B.4.6 A placard on each door of access to a

an emergency exit, to indicate that it

must be open during takeoff and

landing

5. Passenger Information (CASR 121.317)

III.B.5.1 Passenger information marking and placard in Bahasa or Bilingual (Bahasa -English) (CASR 21.29 a.3)

a. Fasten seat belt sign or placard is

visible from each passenger seat

b. No smoking sign or placard, incabin and lavatory

A9

6. Public Address System

Public Address System (more than

19 pax) (CASR 121.318, CASR

135.331)

(note: Transport category

manufactured after December 1996)

7. Crewmember Interphone System

Crewmember Interphone System(more than 19 pax) (CASR 121.319,

CASR 135.333)

8. Passenger Briefing Card

ni.B.8.1 Passenger Briefing Card (CASR

91.537(b), CASR 121.503(b), CASR

135.107(b).

9. Seats, Safety Belts, Shoulder Harnesses, and Child Restraint Systems (CASH

121.311, CASH 135.119, CASH 91.521)

UI.B.9.1 Passenger seats, seat belts,

cushion/upholstery materials,armrest for condition, recliningmechanism for proper operations

III.B.9.2 Exit seat, check table, reclining

mechanism to make sure not

blocking emergency exit ( CASR

121.585, 135.121)

III.B.9.3 Child Restraint System, check for

security

III.B.9.4 At each flight deck station equipped

with a combined safety belt and

shoulder harness, check for security.

10. Cargo and Bagggage Compartment (CASH 121.221)

III.B.lO.l Fire precaution

A. Class "A" (All parts of thecompartment are easily accesible

and fire therein would be ready

discernible to a crew member)

There must be a hand fire

extinguisher available for each Class

A compartment.

B. Class "B" (Enough access for

crew member to reach all the

compartment and no smoke, flame

or extingushing agent enter the

compartment occupied by crew or

passanger)

(4) It must have a separateapproved smoke or fire detectorsystem to give warning at the pilot orflight engineer station

(5) There must be a hand fireextinguisher available for thecompartment

(6) It must be lined with fireresistant material

C. Class "C" (Not conform with

requirement Class A, B, D or E)

(1) It must have a separate smokeor fire detector system to givewarning at the pilot or flightengineer station

(2) It must have an approvedbuilt-in fire extinguishing systemcontrolled from the pilot or flightengineer station

(3) It must be designed to excludehazardous quantities of smoke,flames, or extinguishing agents fromentering into any compartmentoccupied by the crew or passenger

(4) It must have ventilation anddraft controlled so that the

extinguishing agent provided cancontrol any fire that may start in thecompartment

(5) It must be lined with fireresistant material

D. Class "D" (Designed and

constructed that a fire occuringtherein will be completely confined

without endargingthe safety of the

airplane or occupants)

(1) It must have a means toexclude hazardous quantities ofsmoke, flames, or noxious gasesfrom entering any compartmentoccupied by the crew or passengers

(2) Ventilation and drafts must becontrolled within each compartment

(3) It must be completely linedwith fire resistant material

70

E. Class "E" for Cargo only

(1) It must be completely linedwith fire resistant material

(2) It must have a separatesystem of an approved type smoke orfire detector to give warning at thepilot or flight engineer station

(3) It must have a means to shutoff the ventilating air flow to orwithin the compartment and thecontrols for that means must beaccessible to the flight crew in thecrew compartment

(4) It must have a means toexclude hazardous quantities ofsmoke, flames, or noxious gasesfrom entering the flight crewcompartment

Iir.B.10.2 Check cargo door for leaks, damageand general condition

III.B.10.3 Smoke detectors for damage

III.B.10.4 Lighting is operable and protectivecover is installed

m.B.10.5 Flooring and pallet system forgeneral condition

III.B.10.6 Placard of weight limitation foravailability and legibility

III.B.10.7 A 9G cargo net for condition (ifapplicable)

C. COCKPIT INSPECTION

INSTRUMENT, EQUIPMENT MARKING, PLACARD ARE CORRECTLY INSTALLED ANDLEGIBLE.

1. Instrument for VFR (day) (CASR 91.205]



Yes No

71

nr.c.i.i Airspeed indicator

III.C.1.2 Altimeter

III.C.1.3 Magnetic Direction Indicator

m.c.1.4 A tachometer for each engine

III.C.1.5 A cylinder head temperature

indicator for each air cooled eng.

III.C.1.6 Oil in temperature indicator for eachengine

III.C.1.7 A fuel quantity indicator for each

fuel tank

III.C.1.8 An oil pressure indicator for each

engine

m.c.1.9 A manifold pressure indicator for

each engine

III.C.l.lO Landing gear position indicator, if

the aircraft has a retractable landinggear

2. Instrument for IFR (CASR 91.205), specified requirement VFR (day)



Yes No

III.C.2.1 Gyroscopic rate of turn indicator

III.C.2.2 Slip/Skid indicator

m.C.2.3 Sensitive altimeter adjustable forbarometric pressure

III.C.2.4 Clock

m.c.2.5 Gyroscopic pitch and bank indicator

(AH)

m.C.2.6 G3n-oscopic direction indicator

(directional gyro or equivalent)

3. Flight and Navigation Instrument (CASR 121.305)



Yes No

70

III.C.3.1 An airspeed indicating system with

heated pitot tube

III.C.3.2 Two sensitive pressure altimeter

III.C.3.3 Clock

III.C.3.4 A free air temperture indicator

III.C.3.5 Gjroscopic pitch and bank indicator

(AH)

III.C.3.6 Gyroscopic rate and turn indicator

combined with an integral skip/skid

indicator (turn and bank indicator)

III.C.3.7 Gyroscopic direction indicator(d5rrectional g3rro or equivalent)

IILC.3.8 A magnetic compass

III.C.3.9 A vertical speed indicator (rate of

climb indicator)

III.C.3.10 Two Gyroscopic pitch and bank

indicator (AH) or :

Third Gyroscopic pitch and bank

indicator (AH) for:

(i). turbojet ,or

(ii). turbo prop having pax seat >30

or payload > 7500 lbs

4. Engine Instrument (CASK 121.307)



Yes No

III.C.4.1 Oil in temperature indicator for each

engine

in:c.4.2 A fuel pressure indicator for each

engine

m.C.4.3 A means for indicating fuel quantityfor each fuel tank

m.C.4.4 An oil pressure indicator for each

engine

III.C.4.5 An oil quantity indicator for each oiltank

7-?

III.C.4.6 An independent fuel pressure

warning device for each engine or amaster warning device for all engines

5. Flight and navigation Instrument (CASR 135.305)



Yes No

III.C.5.1 Two independent airspeed indicatingsystem

III.C.5.2 Two independent sensitive altimeter

system

III.C.5.3 Clock

III.C.5.4 A free air temperature indicator

III.C.5.5 G3Toscopic direction indicator

(directional gyro or equivalent)

ni.C.5.6 A magnetic compass

III.C.5.7 Gyroscopic pitch and bank indicator(AH)

III.C.5.8 Vertical speed indicator (rate ofclimb indicator)

III.C.5.9 Two G5rroscopic pitch and bank

indicator (AH) for turbojet and turboprop.

III.C.5.10 Third G3Toscopic pitch and bank

indicator (AH) for turbojet

6. Engine Instrument (CASR 135.317)



Yes No

III.C.6.1 A tachometer for each engine

ni.C.6.2 A carburetor air temperature

indicator for each engine.

III.C.6.3 A cylinder head temperatureindicator for each air cooled eng.

IILC.6.4 Oil in temperature indicator for each

engine

74

III.C.6.5

IILC.6.6

III.C.6.7

A fuel pressure indicator for each

engine

A fuel flowmeter or fuel mixture

indicator for each engine notequipped with an automatic altitudemixture control

A means for indicating fuel quantityfor each fuel tank

III.C.6.8 An oil pressure indicator for each

engine

III.C.6.9 An oil quantity indicator for each oil

tank

III.C.6.10 An independent fuel pressurewarning device for each engine or amaster warning device for all engines

III.C.6.11 A device for each reversible propeller

III.C.6.12 A manifold pressure indicator for

each engine

7. Navigation and Radio Communication (CASH 91.205, CASR 91.175CASR, 91.215,CASK 121.99, CASR 121.349, CASR 135.309, CASR 135.311, CASR 121.345,)

Item

IILC.7.1

Description

HF .ea

36).

Satisfactory

Yes No

37). Remarks

III.C.7.2 VHF .ea

Ill.C.7.3 ATC Transponder .ea

III.C.7.4 VOR .ea

IIl.C.7.5 DME .ea

III.C.7.6 ILS .ea

8. EQUIPMENTS


Satisfactory

Yes No

37). Remarks

III.C.8.1 Weather Radar

(CASR 121.357,

135.315)a

7^

III.C.8.2 1. TCAS (CASR 91.227)

Turbine,

MTOW>33.000 lbs

(15.000 Kg) for

which the

individual

Airworthiness

Certificate is first

issued after 31

December 2015,

shall be equippedwith TCAS II

ea

2. TCAS (CASR 121.356)

(i) Turbine,

MTOW>33.000 lbs

(15.000 Kg),TSO

119a, version 6,04A

Enhance or

equivalent installed

before May 1, 2003

TSO 119b,

version 7.1 or a

later or equivalent

(ii) Combi

airplane PaxlO - 30

seat TCAS I

TSO 118

(iii) Piston,

MTOW>33.000 lbs

TCAS I TSO 118

.ea

.ea

.ea

m.C.8.3 TAWS (CASR

121.354, CASR

135.319)

TSO C-151Class A

or equivalent for >9

pax

TSO C-151ClassB

or equivalent for 6 -

9 pax

a

CASR 91.229

MTOW > 5700 kg orPax seat >9

TSO C-151 or

equivalent

a.

III.C.8.4 GPS/INS/Doppler

Radar/ONS/IRS or

FMS

(CASR 121.355,

CASR 121.358)

a

III.C.8.5 Low altitude windshear system

(CASR121.352)

Aeroplanes (except turboprop)manufactured after 2 January 1991,

must be equipped with either an

approved airborne windshear warningSs flight guidance system, an approved

airborne detection & avoidance

system, or combination of these

systems

III.C.8.6 Pitot Heat Indicating System (CASR

121.342, CASR 135.325)

(1) All transport category aicraft(CASR 121.342)

(11) >20 pax (CASR 135.325)

III.C.8.7 Flight Data Recorder, check for

applicability and type of FDR CASR

91.233 and Appendix E (Airplane), F

(Helicopter)

AIRPLANE

(i) All airplane first issue of C of Aon or after IJanuary 1989 withmaximum certificated take-off mass

more than 27.000 kg (Type I FDR)

(ii) All airplane first issue C of A onor after 1 Jan. 1989 with maximum

certificated take-off mass more than

5.700 kg, up to and including 27.000

ni

kg (Type II FDR)

(iii) All airplane first issue of C of Aafter 1 Januaiy 2005 with maximumcertificated take-off mass more than

5.700 kg [Type lA)

(iv) All turbine engine airplane firstissue of C of A on or after 1 Januaiy2016 with a seating configuration ofmore than 5 passenger seat andmaximum certificated take-off mass of

5700 kg or less (Type 11)

HELICOPTER

(i) All helicopters first issued of C

of A on or after 1 Januaiy 2016 with

maximum certificated take-off mass

more than 3180 kg (Type IVA)

(ii) All helicopters first issued of C

of A on or after 1 Januaiy 1989 with

maximum certificated take-off mass

more than 7000 kg or having a

passanger seating configuration of

more than 19 (Type IV)

Record ULB Batteiy due:

Annual read out for required number

of parameter to be recorded and

quality (measurement range,recording interval, accuracy,resolution)

Calibration for 5 year or at least 2

year in accordance with


III.C.8.8 CVR/CARS (CASR 91.235)

AIRPLANE

(i) All turbine-engine airplanes, forwhich the individual certificate of

airworthiness was first issued on or

after 1 January 2016, with a seatingconfigurations of more than fivepassenger seats and a maximumcertificated take-off mass of 5 700 kgor less shall be equipped with either aCVR or a CARS.

(ii) All turbine-engine airplanes fora maximum certificated take-off mass

78

of over 5 700 kg for which theindividual certificate of airworthiness

was first issued on or after 1 January2016 and required to be operated bymore than one pilot shall be equippedwith a CVR.

(iii) All airplanes of a maximumcertificated take-off mass of over 27

000 kg for which the individualcertificate of airworthiness is first

issued on or after 1 January 1987shall be equipped with a CVR.

HELICOPTER

(i) All helicopters of a maximum

certificated take-off mass of over 7

000 kg for which the individual

certificate of airworthiness is first

issued on or after 1 January 1987

shall be equipped with a CVR. For

helicopters not equipped with anFDR, at least main rotor speed shall

be recorded on the CVR.

(ii) All helicopters of a maximum

certificated take-off mass of over 7

000 kg for which the individual

certificate of airworthiness was first

issued before 1 January 1987 shall beequipped with a CVR. For helicopters

not equipped with an FDR, at leastmain rotor speed shall be recorded on

the CVR.

From 1 January 2016, a magnetic

tape & wire shall be discontinued,

and capable of two hours recording

From 1 January 2016, all CVR shall

be capable of retaining the

information recorded during at leastthe last two hours of their operation

Record ULB Batteiy, due:

Annual Examination

9. Lighting (CASR 91.209, CASR 121.323, CASR 135.307)


Satisfactory

37). Remarks

Yes No

70

III.C.9.1 Instrument light

III.C.9.2 Anti Collision light

III.C.9.3 Position/Navigation light

ni.C.9.4 Two Landing light

m.C.9.5 Taxi light

III.C.9.6 Logo light

III.C.9.7 Cabin light (ceiling, windows, service,entiy, exit, etc.)

A« Aircraft System


Satisfactory

37). Remarks

Yes No

IV.A. 1 Flight control system

IV.A.2 Recording system (FDR, CVR)

IV.A.3 Fire precaution (Engine, APU, Cargo)

IV.A.4 Smoke detector system (Lavatory,Cargo)

IV.A.5 Public address system 85 InterphoneSystem

IV.A.6 Pitot heat indicating system CASR121.342, CASR 135.325

IV.A.7 Lighting (nav. light, anti-collision

light, instrument light, landing light,emergency light, passenger

information light)

IV.A.8 ELT test

IV.A.9 Other Applicable System

B. Communication

Item Description

1

36).


Yes No

IV.B.l HF, VHF, ATC Transponder |1

sn

C. Navigation


Satisfactory

37). Remarks

Yes No

IV.C.l ADF, VOR, DME, ILS

IV.C.2 Weather Radar

IV.C.3 TAWS TSO C151 Class A 85

Windshear (CASR 121.352)

IV.C.4 TCAS

IV.C.5 GPS/INS/IRS/FMS

Nav. data base due period:


Satisfactory

37). Remarks

Yes No

V.l Ground run and test flight conductedaccording to test plan

V.2 Ground Run Test result

V.3 Test Flight result

Aircraft grounded by DGCA inspector

Corrective actions before issued the Airworthiness Certificate (C of A)

No remarks

lREKli\^RK(©R4BINiyuN,uifiuseaiset)arateisneeHas

61

SENIOR INSPECTOR

Name/ Signature / Date

ASSIGNED INSPECTOR

Name/ Signature / Date

Note:

This form can also be used to record airworthiness inspection for issuance of Export Certificate ofAirworthinessfor Aircraft. Special requirements of importing country must be considered to include in the inspection record.Finding must be clearly addressed prior to get an acceptance from importing country, when it intended to be putas an exemption to Export Certificate of Airworthiness.

DIRECTOR GENERAL OF CIVIL AVIATION

signed

Dr. Ir. AGUS SANTOSO,M.Sc

s6^uai aslinyaD4GIAN HUKUM

/O

lAltP&feNAMA SARI^cnilSina / (IV/a)

NIP. 19680704 199503 2 001

87

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