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CERTIFICATIONAN INTRODUCTION TO THE AERONAUTICAL

CERTIFICATION PROCESS IN EUROPE

An introduction to aircraft certification in Europe - DMD Solutions © 2016

TABLE OF CONTENTS

SLIDES 3-4 INTRODUCTION TO CERTIFICATION

SLIDES 5-10 TYPE CERTIFICATE

SLIDES 10-12 DESIGN ORGANISATION APPROVAL

SLIDES 14-15 CERTIFICATION OF PARTS

SLIDES 16 PRODUCTION APPROVAL

SLIDES 17-19 PRODUCTION ORGANISATION APPROVAL

SLIDE 20 PRODUCTION WITHOUT POA

SLIDES 21-29 ANNEXES


SLIDES 13 ALTERNATIVE PROCEDURES TO DOA

SLIDES 8-9 SUPPLEMENTAL TYPE CERTIFICATE

EU AVIATION AUTHORITIES & REGULATIONS

AUTHORITIES

REGULATIONS

1) Organization Approval

JOINT AVIATION AUTHORITIES

EUROPEAN AVIATION SAFETY AGENCY

JAR-21 JAR-145

2) Product Approval

Part 21 Part 145Procedures and

requirements to certify DOA, POA & MOA orgs

Technical requirements on aircraft parts and appliances

JAR-23 JAR-25 …

CS-23 CS-25 …

CS = Certification specifications

From 2004 onwards


AGENCIA ESTATAL DE SEGURIDAD AEREA

Certain member states manage the process locally, always complying with european EASA regulation

Competent authority in Spain

WHO NEEDS WHAT?

A new model of Aircraft, Engine or Propeller

An aircraft manufacturer company

A part manufacturer company

A maintenance services provider

TYPE CERTIFICATE

DESIGN ORGANIZATION APPROVAL

PRODUCTION ORGANIZATION APPROVAL

MAINTENANCE ORGANIZATION APPROVAL


TYPE CERTIFICATE

The type certificate is a document by which the authority states that an applicant has demonstrated the compliance of a type design to all applicable requirements

The applicant of a Type Certificate must* hold a

DOA

According to EASA Part 21.A.31, shall consist of: • Drawings and specs to define configuration • Information on materials and methods of manufacture • Airworthines limitation section of the instructions • Data necessary to determine airworthiness, noise, fuel

venting and exhaust emissions

Once issued, the applicant becomes a

Type Certificate Holder TCH

Stated on the Certification Specifications: • CS-23 Normal, Utility, Aerobatic and

Commuter Aeroplanes • CS-25 Large Aeroplanes • CS-27 Small Rotorcraft • CS-27 Large Rotorcraft • …

An introduction to aircraft certification in Europe - DMD Solutions © 2016*Except in case of ADOAP: Alternative Procedures to Design Organization Approval for aircrafts meeting requirements as specified in EASA Part 21.A.14

TYPE CERTIFICATE


Minor changes Major changes

A type-certificate shall be issued for an unlimited duration All deviations from a type design are ‘changes’

that must be approved by the authority

No appreciable effect on: Have an appreciable effect on:

mass, balance, structural strength reliability, operational characteristics (noise, fuel venting, exhaust emission) or other characteristics affecting airworthiness

In what cases will a new Type Certificate be needed?

Propeller If the proposed change is in the number of blades or principle of pitch change operation

Aircraft If the proposed change is: • In the number of

engines or rotors • To engines or rotors

using different principles of operation

Engine If the proposed change is in the principle of operation

TYPE CERTIFICATE


Change in type design

Classification of change in order to: ➡ Determine approval route ➡ Assess effect on airworthiness

Any of the following criteria met? ➡ Appreciable effect on weight ➡ Appreciable effect on balance ➡ Appreciable effect on structural strength ➡ Appreciable effect on reliability ➡ Appreciable effect on operational characteristics

Any of following criteria met? ➡ Adjustment of certification basis ➡ New interpretation of the requirements used for the TC basis ➡ Aspects of compliance demonstration not previously accepted ➡ Extent of new substantiation data and degree of reassessment

and re-evaluation considerable ➡ Alters the limitations directly approved by the agency ➡ Mandated by AD or terminating action of AD ➡ Introduces or affects function where failure condition is

catastrophic or hazardous EASA Part 21.A.91 EASA Part 21.A.91

3.3 Complementary guidance for classification of changes

MINOR CHANGE

MAJOR CHANGE

NO

NOYES

YES

Wherever there is a doubt as to the classification of a change, the authority should be consulted for clarification

SUPPLEMENTAL TYPE-CERTIFICATE


A major change to a type-certificate shall be approved to an appliccant diferent from the TC holder under the

Supplemental Type-Certificate procedureEASA Part 21 Subpart E

Supplemental TC procedure

Demonstration of capability Show compliance Issue of the

STCApplication for

STCAccceptance

from TC holder

DOA Holder

ADOAP Procedure

21.A.14 (b)Subpart J

21.A.112B 21.A.113

Shall include : a) Description of change, with parts and manuals affected and CS to comply b) New demonstrations necessary and means (calculation, test or analysis) to

show compliance c) Necessary changes to the operational suitability data d) A justification that the information is adequate either from the applicant's

own resources, or through arrangement with the TC holder

21.A.20

Arrangement with the Type-Certificate holder

Certification program21.A.20 (b)

21.A.115

• TC holder has no technical objection to the information submitted

• TC holder ensures discharge of all obligations for continued airworthiness of the changed product

SUPPLEMENTAL TYPE-CERTIFICATE


Certification program21.A.20 (b)

MUST INCLUDE:

✦ A plan containing the following information:

• Description of the project and operations envisaged

• Proposed certification specifications and requirements

• Description of proposed means of compliance

• A compliance checklist addressing each paragraph of the type-certification basis

• Identification of relevant personnel making decisions

✦ A project schedule including major milestones

TYPE CODE MEANS OF COMPLIANCE ASSOCIATED DOCUMENTS

Engineering evaluation

MC0

• Compliance statement • Reference to Type Design docs • Election of methods, factors, etc. • Definitions

• Type Design documents • Recorded statements

MC1 Design review • Descriptions • Drawings

MC2 Calculation/ Analysis Substantiation reports MC3 Safety assessment Safety analysis

Tests

MC4 Laboratory tests • Test programmes • Test reports • Test interpretations

MC5 Ground tests on related product MC6 Flight tests MC8 Simulation

Inspection MC7 Design inspection/ audit d) Inspection or audit reports

Equipment qualification

MC9 Equipment qualification Note : Equipment qualification is a process which may include all previous means of compliance

MEANS OF COMPLIANCE TYPES AND DOCUMENTATION


• To design • To demonstrate compliance with the applicable

requirements • To independently check the statements of

compliance • To provide items for continued airworthiness • To check the job performed by partners/

subcontractors • To independently monitor the above functions • To provide the authority with the compliance

documentation • To allow the authority to make any inspection and

any flight and ground tests necessary to check the validity of the statements of compliance

DUTIES AND RESPONSABILITIES PRIVILEGES [See EASA Part 21.A.263]


• The authority will accept, without further verification, compliance documents for: ✦ Permit to fly ✦ Type certificate ✦ Major change to a type certificate ✦ Supplemental type certificate ✦ ETSO authorization (part certification) ✦ Major repair design approval

• They may be entitled, depending on terms of approval: ✤ To classify changes to the type certificate ✤ To approve minor changes and repairs ✤ To issue information or instructions ✤ …among others



Why are certification privileges granted? There is a transfer for the authority

from the control of the product to the control of the organization

Design Organisation Approval means an “Engineering Quality Management System”

with:

• Organizational Structure • Procedures • Resources • Auditing

Head of Design Organization

Office of Airworthiness

Design Assurance System

DOA Handbook

Will provide the necessary resources for the proper functioning of the design organisation

Liaison between the DOA and the authority with respect to all aspects of the certification programme

Resources to control and supervise the design, and design changes to the products

Basic document of the organization, containing its description, the object of the certification, staff functions, aprocedures, tests, etc.



DAS

TYPE CERTIFICATION

Product specification

Design

Anaylsis and tests

Show compliance

Verification of compliance

Declaration of compliance

21.A.20 (b)

RequirementsD

esign Organization System

SYSTEM M

ON

ITORTy

pe in

vest

igat

ion

CS Environmental

Type investigation program

An organizational structure with the purpose to:

1. Control the design 2. Show compliance with the applicable

certification standard and environmental requirements

3. Show compliance with protection requirements

4. Independently check this compliance 5. Liaise with the Agency 6. Continuously evaluate the design

organization 7. Control subcontractors

CVEA staff of Certification Verification

Engineers is responsible for independent checking and signing all documents of

compliance with applicable requirements

ALTERNATIVE PROCEDURES TO DOA


Alternative procedures to DOA for applicants to demonstrate its capability apply to a limited set of products and cases

European Light Aircraft 1

Changes to TC of Group 2

• Airplanes or sailplanes with a MTOM of 1.200 kg or less • Balloons less than 3.400 m3 of hot air volume or less than

1.000 m3 gas • Airship for not more than 4 occupants • An engine or propeller installed in an ELA1 aircraft

European Light Aircraft 2

• Airplanes or sailplanes with a MTOM of 2.000 kg or less • Balloons, hot air ships or gas airships with 3% maximum

static heaviness, non-vectored thrust and simple design • A very light rotorcraft • A piston engine or a pitch propeller

Major repair designs

Major changes to type design to any product CS-23, CS-25, CS-27 o CS-29 classified as Group 2, including: • All changes related to cabin configuration • Fairings, gap seals, windshield type, floor panels, etc. • Accessories, inlet modifications, etc.

21.A.112B

Major repairs designs

21.A.432B

PRODUCT ALTERNATIVE PROCEDURE21.A.14 21.A.14 (b)

As an alternative to DOA, a Manual of Procedures must set out: • Specific design practices • Resources • Sequence of activities

Relevant to specific projects and taking account EASA Part 21 requirements.

In particular, the management of the process will be conducted as stated in:

• Certification program AMC for a TC • Certification program AMC for a

Supplemental TC • Procedures acceptable as described in paragraphs 3.2,

3.3 & 3.4 of for classification of changes to TC, repair design changes and production deviations from the approved design data

21.A.20 (b)

21.A.114

21.A.14 (b)

CERTIFICATION OF PARTS


All parts and appliances installed on certificated products (aircraft, engines, and propellers) must be approved

There are essentially three routes to certifying a part or appliance:

• Parts in accordance with standardization norms such as: ✓ Military standards ✓ Society of Automotive Engineers Inc. ✓ Electronic Industries Association

Standards Institute ✓ AIA-NAS ✓ Norms issued by the manufacturers

of parts or products and accepted by the authority

• These norms are technical specifications that become parts of the product type design or change of the same

• Applicable for any organisation that produces ETSO articles which they can install in every product

• The applicant must hold a POA or comply with EASA Part 21 Subpart F

Documents to obtain an ETSO authorisation:

✓ Technical Data ✓ Declaration of Design

and Performance (DDP) ✓Manual of procedures ✓ Exposition for the POA

or Manual for manufacturing

• The certification for a part can be obtained in conjuction with the Type Certificate procedures for the product where it will be installed

• In this case the applicant (DOA) is solely responsible for the airworthiness of the items

• Parts can only be installed in products of the same type

• For many non-critical parts the authority could accept simplified qualification procedures, based on previous experience, technical evaluations, etc

European Techincal Standard Order In the context of a TC or TC change Standard Part

EASA Part 21.A.605

[ 21.A.143 ]

[ 21.A.125A(b) ]

[ 21.A.602B(b) ]

[ 21.A.608 ]

CERTIFICATION OF PARTS


ETSO or non-ETSO?

• Only parts listed as standard in CS-ETSO

• The manufacturer must invest time and money on obtaining a POA or approval according to EASA Part 21 Subpart F

• The responsability for the airworthiness of the part falls on the manufacturer

• The manufacturer must associate with a single DOA holder in the context of a single type design for each certification

• Manufacturing processes will have to be certified by the DOA authorisation in any case

ETSO article

Non-ETSO part

• The article has an stand-alone certificate and can be sold to different customers and even to aircraft owners or maintenance organisations

• For larger organisations, it is preferable to obtain a POA in order to be able to make use of the privilege to classify and issue type change certificates

• The manufacturer organisation is not liable to obtain a POA certification, but only the quality approval of the associated DOA. Even though the requirements are equivalent, the process may be simplified.

• The certification is simplified for equipment not specifically required for airworthiness such as entertainment or domestic equipment, aerial work installations, experimental installations, instruments for additional information, etc

! ✓

PRODUCTION APPROVAL

Approval for production can be obtained by

two procedures:Production under POA

Production without POA

EASA Part 21 Subpart G

EASA Part 21 Subpart F

• Analogous to a DOA certification, there is transfer of privileges and responsabilities to the mafuacturer organisation

• The authority must therefore obtain a deep knowledge of the organisation and its procedures

• For the product they intend to manufacture, if they are not the TCH, they must be in agreement with the TCH and coordinate to obtain design details

• The authority will check and audit the coordination between design and production

• The authority may consider it inapropiate that the maufacturer applies for a POA if: ➡ Production is limitied to a certain number of units ➡ It is not intended to obtain a Direct Delivery

Authorisation for providing parts to the final user ➡ As a temporary approval for produtcion while in a

POA cettification process • The maufacturer will be exposed to closer

supervisition for the issue of the final certification • Design of the product must already be approved, so

the manufacturer must associate with a TCH[ 21.A.133 ]

[ 21.A.122 ]

[ 21.A.122 ]


PRODUCTION ORGANISATION APPROVAL

DUTIES AND RESPONSABILITIES PRIVILEGES [See EASA Part 21.A.163]

• To perform the production activities • To demonstrate compliance with the applicable

requirements in Part 21 Subpart G • To independently check the statements of

compliance • To provide items for continued airworthiness • To check the job performed by partners/

subcontractors • To independently monitor the above functions • To provide the authority with the compliance

documentation • To allow the authority to make any inspection and

any audit or tests necessary to check the validity of the statements of compliance

• Perform production activities under Part 21 • The authority will accept, without further

verification, compliance documents for: ✦ Airworthiness certificate

(presenting an EASA Form 52) ✦ Issue authorised release certificates

(EASA Form 1) ✦ Maintain an aircraft that it has produced and

issue release certificates (EASA Form 53)

• They may be entitled, depending on terms of approval: ✤ To classify changes to the type certificate ✤ To approve minor changes and repairs ✤ …among others



The characteristics and requirements for a POA focus mainly in three areas:

A detailed Product Organisation Exposition document with a

description of the organisation processes and staff

The organisation must set up an structure to ensure that the product achieves conformity to design data and conditions for safe operation.

It will include the following control procedures:

• Manufacturing processes • Verification of incoming materials • Vendor and subcontractor assessment, audit,

and control • Non-conforming item control • Personnel competence and qualification • Inspection and testing, including production

flight tests • Airworthiness co-ordination with the TCH • Internal quality audits and resulting corrective

action

The staff must include individuals with the following responsabilities:

• A manager accountable to the authority

• A quality manager for compliance supervision

• Staff with authority at each area to monitor airworthiness requirements

• Certifying staff authorized to sign final documents such as statements of conformity

QUALITY SYSTEMINDEPENDENT VERIFICATION

EXPOSITION

✓


PRODUCTION ORGANISATION APPROVAL The basic timeframe for the achievement of a POA is between 10 months and six years

Reception

Admin eligibility

check

Technical eligibility

check

Payment of fees

Investigation phase and implementation of corrective

actions

Closure of the findings

Prep of EASA

Form 56

Review of

Form 56

10 week days Around 1 month Max 3 months 3 months to 3 years 3 months to 3 years 1 month 2 weeks 2 weeks

Application recieved

Confirmation of reception

Application accepted and request for fees payment

Receipt of payment

POE and EASA F4 accepted

Corrective actions implemented

Findings closed

EASA F56 provided

POA


PRODUCTION WITHOUT POA

The characteristics and requirements for production without a POA focus mainly in three areas:

Which contains a description of the organisation processes and staff,

including the production inspection system

The organisation must set up an structure to ensure that the product achieves conformity to design data and conditions for safe operation.

It will include the following control procedures:

• Manufacturing processes and techniques • Verification of incoming materials and

subcontracted parts • Design changes (including material

substitutions)

In this case, the independent check for quality assurance is not a requirement, for

the manufacturer itself, since it will be performed by the associated DOA as part

of the quality system supervision of manufacturers and production processes

and additionally by means of a closer scrutiny of the authority.

PRODUCTION INSPECTION SYSTEMINDEPENDENT QUALITY ASSURANCE

ORGANISATION MANUAL

✓


QUESTIONS & ANSWERS

ANY QUESTIONS?

Q A&

THANKS FOR LISTENING


Annex I - Part 21 References

DESIGN ORGANISATION APPROVAL

GENERAL PROVISITIONS


Subpart A

Subpart J Subpart G

TYPE CERTIFICATE AND RESTRICTED TC

CHANGES TO TC AND RESTRICTED TC

Subpart B Subpart D

NOISE CERTIFICATION REPAIRSubpart I Subpart M

IDENTIFICATION OF PRODUCTS PARTS AND

APPLIANCES

AIRWORTHINESS CERTIFICATES

Subpart Q

Subpart D

SUPPLEMENTAL TYPE CERTIFICATES

Subpart E

EUROPEAN TECHINCAL STANDARD ORDER AUTHORISATION

Subpart O

PARTS AND APPLIANCES

Subpart K

PRODUCTION WITHOUT POA

Subpart F



GENERAL PROVISITIONS

Subpart A

REFERENCE CONTENT21A.1 Scope

21A.2 Undertakingbyanotherpersonthantheapplicantfor,orholderof,acertificate

21A.3 Failures,malfunctionsanddefects

21A.3B Airworthinessdirectives

21A.4 Coordinationbetweendesignandproduction


21A.233 Eligibility

21A.234 Application

21A.235 Issueofdesignorganisationapproval

21A.239 Designassurancesystem

21A.243 Data

21A.245 Approvalrequirements

21A.247 Changesindesignassurancesystem

21A.249 Transferability

21A.251 Termsofapproval

21A.253 Changestothetermsofapproval

21A.257 Investigations

21A.258 Findings

21A.259 Durationandcontinuedvalidity

21A.263 Privileges

21A.265 Obligationsoftheholder

DESIGN ORGANISATION APPROVAL

Subpart J




21A.13 Eligibility

21A.14 Demonstrationofcapability

21A.15 Application

21A.16A Airworthinesscodes

21A.16B Specialconditions

21A.17 Type-certificationbasis

21A.18 Designationofappl.environ.protec.requirements&certificationspecifications

21A.19 Changesrequiringanewtype-certificate

21A.20 CompliancewiththeTCbasisandenvironmentalprotectionrequirements

21A.21 Issueofatype-certificate

21A.23 Issueofarestrictedtype-certificate

21A.31 Typedesign

21A.33 Investigationsandtests

21A.35 Flighttests

21A.41 Type-certificate




21A.55 Recordkeeping

21A.57 Manuals

21A.61 Instructionsforcontinuedairworthiness

TYPE CERTIFICATE AND RESTRICTED TC

Subpart B




21A.91 Classificationofchangesintypedesign

21A.92 Eligibility

21A.93 Application

21A.95 Minorchanges

21A.97 Majorchanges

21A.101 Designationofappl.environ.protec.requirements&certificationspecifications

21A.103 Issueofapproval

21A.105 Recordkeeping

21A.107 Instructionsforcontinuedairworthiness


CHANGES TO TC AND RESTRICTED TC

Subpart D

NOISE CERTIFICATION

Subpart I


21A.203 Eligibility

21A.204 Application

21A.205 Issueofnoisecertificates

21A.207 Amendmentormodification

21A.209 Transferabilityandre-issuancewithinMemberStates

21A.210 Inspections




21A.133 Eligibility

21A.134 Application

21A.135 Issueofproductionorganisationapproval

21A.139 QualitySystem

21A.143 Exposition

21A.145 Approvalrequirements

21A.147 Changestotheapprovedproductionorganisation

21A.148 Changesoflocation


21A.151 Termsofapproval

21A.153 Changestothetermsofapproval

21A.157 Investigations

21A.158 Findings


21A.163 Privileges



PRODUCTION ORGANISATION

APPROVALSubpart G




21A.172 Eligibility

21A.173 Classification

21A.174 Application

21A.175 Language

21A.177 Amendmentormodification

21A.179 Inspections


21A.181 Transferabilityandre-issuancewithinMemberStates

21A.182 Aircraftidentification

21A.183 Issueofcertificatesofairworthiness

21A.184 Issueofrestrictedcertificatesofairworthiness

21A.185 Issueofpermitstofly

AIRWORTHINESS CERTIFICATES

Subpart D

IDENTIFICATION OF PRODUCTS PARTS AND

APPLIANCES

Subpart Q

REFERENCE CONTENT21A.801 Identificationofproducts

21A.803 Handlingofidentificationdata

21A.804 Identificationofpartsandappliances

21A.805 Identificationofcriticalparts

21A.807 IdentificationofETSOarticles

ETSO TITLE

C53A FuelandEngineOilSystemHoseAssemblies

C55A FuelandOilQuantityInstruments

C56B Engine-drivenDirectCurrentGenerators/Starter-generators

C62E AircraftTyres

C69C EmergencyEvacuationSlides,RampsandSlide/RaftCombinations

C71 AirborneStatic(‘DCtoDC’)ElectricalPowerConverter(forAirCarrierAircraft)

C72C IndividualFlotationDevices

C73 StaticElectricalPowerInverter

C79 FireDetectors(RadiationSensingType)

C80 FlexibleFuelandOilCellMaterial

C90C CargoPallets,NetsandContainers

C90D CargoPallets,NetsandContainers

C92C GroundProximityWarning,GlideSlopeDeviationAlertingEquipment

C95A MachMeters

C96A AnticollisionLightSystems

C100B ChildRestraintSystem(CRS)

C101 OverspeedWarningInstruments

C102 AirborneRadarApproachandBeaconSystemsforHelicopters

C103 ContinuousFlowOxygenMaskAssembly(forNon-transportCategoryAircraft)

ETSO TITLE

C2d AirspeedInstruments

C4c BankandPitchInstruments

C6e DirectionInstrument,Magnetic(GyroscopicallyStabilized)

C7d DirectionInstrument,MagneticNon-stabilizedType(MagneticCompass)

C8e VerticalVelocityInstrument(Rate-of-Climb)

C10b AircraftAltimeter,PressureActuated,SensitiveType

C13f Lifepreservers

C14B AircraftFabric,IntermediateGrade;ExternalCoveringMaterial

C15d AircraftFabric,GradeA;ExternalCoveringMaterial

C16a AirspeedTubes(ElectricallyHeated)

C22G SafetyBelts

C25A AircraftSeatsandBerths(TypeITransport6gForwardLoad)

C28 AircraftSkis

C30C AircraftPositionLights

C39C 9gTransportAirplaneSeatsCertifiedbyStaticTestingonly

C43C TemperatureInstruments

C44C FuelFlowmeters

C45B ManifoldPressureInstruments

C47A PressureInstruments–Fuel,OilandHydraulic

Annex II - List of most common ETSO Standards (1/3)


ETSO TITLE

C105 OptionalDisplayEquipmentforWeatherandGroundMappingRadarIndicators

C109 AirborneNavigationDataStorageSystem

C110A AirbornePassiveThunderstormDetectionSystems

C112D AirTrafficControlRadarBeaconSystem/ModeSelect(ATCRSB/ModeS)AirborneEquipment

C113 AirborneMultipurposeElectronicDisplays

C114 TorsoRestraintSystems

C115C FlightManagementSystems(FMS)usingMulti-SensorInputs

C117A AirborneWindshearWarningandEscapeGuidanceSystems(ReactiveType)forTransportAeroplanes

C118 TCASI

C119C TCASII

C121B UnderwaterLocatingDevice

C123B CockpitVoiceRecordersSystems

C124B FlightRecorder

C126A 406MHzEmergencyLocatorTransmitter

C127A Rotorcraft,TransportAeroplane,andNormalandUtilityAeroplaneSeatingSystems

C129A AirborneSupplementalNavigationEquipmentUsingGlobalPositioningSystem(GPS)

C132 GeosynchronousOrbitAeronauticalMobileSatelliteServicesAircraftEarthStationEquipment

ETSO TITLE

C135A TransportAeroplaneWheelsandWheel/BrakeAssemblies

C139 AircraftAudioSystemsandEquipment

C141 AircraftFluorescentLightingBallast/FixtureEquipment

C142A Non-rechargeableLithiumCellsandBatteries

C144A AirborneGlobalPositioningSystemAntenna

C145C AirborneNavigationSensorsUsingtheGlobalPositioningSystem(GPS)AugmentedbytheWideAreaAugmentationSystem(WAAS)

C146C Stand-AloneAirborneNavigationEquipmentUsingtheGlobalPositioningSystem(GPS)AugmentedbytheWideAreaAugmentationSystem(WAAS)

C147 TrafficAdvisorySystem(TAS)AirborneEquipment

C154C UniversalAccessTransceiver(UAT)AutomaticDependentSurveillance-Broadcast(ADS-B)EquipmentOperatingontheFrequencyof978MHz

C155A RecorderIndependentPowerSupply

C157A AircraftFlightInformationServices-Broadcast(FIS-B)DataLinkSystemsandEquipment

C158 AeronauticalMobileHighFrequencyDataLink(HFDL)Equipment

C159A AvionicsSupportingNextGenerationSatelliteSystems(NGSS)=IridiumPhone

C160A VDLMode2CommunicationsEquipment

C161A GroundBasedAugmentationSystemPositioningandNavigationEquipment

C162A GroundBasedAugmentationSystemVeryHighFrequencyDataBroadcastEquipment

C164 NightVisionGoggles(NVG)



ETSO TITLE

C165 ElectronicMapDisplayEquipmentforGraphicalDepictionofAircraftPosition

C166B ExtendedSquitterAutomaticDependentSurveillance-Broadcast(TIS-B)EquipmentOperatingontheRadioFrequencyof1090Megahertz(MHz)

C170 HighFrequency(HF)RadioCommunicationsTransceiverEquipmentOperatingWithintheRadioFrequency1.5to30Megahertz

C172 CargoRestraintStrapAssemblies

C173 Nickel-CadmiumandLead-AcidBatteries

C174 BatteryBasedEmergencyPowerUnit(BEPU)

C175 GalleyCart,ContainersandAssociatedComponents

C176 AircraftCockpitImageRecorderSystems

C177 DataLinkRecorderSystems

C178 SinglePhase115VAC,400HzArcFaultCircuitBreakers

C179A RechargeableLithiumCellsandLithiumBatteries

C184 GalleyEquipment

C190 ActiveAirborneGlobalNavigationSatelliteSystem(GNSS)Antenna

C194 HelicopterTerrainAwarenessandWarningSystem(HTAWS)

C195A AvionicsSupportingAutomaticDependentSurveillance-Broadcast(ADS-B)AircraftSurveillance

C196A AirborneSupplementalNavigationSensorsforGlobalPositioningSystemEquipmentUsingAircraft-BasedAugmentation

C198 AutomaticFlightGuidanceandControlSystem(AFGCS)Equipment

