5. General requirements – flight instruments. 6. Minimum ... Instrument 139 of 2018 Civil...S.I....

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Statutory Instrument 139 of 2018.[CAP. 13:16

Civil Aviation (Instruments and Equipment) Regulations, 2018

ARRANGEMENT OF SECTIONS

PART I Preliminary

1. Title. 2. Interpretation.

PART II

equiPment of aircraft

3. General equipment and instruments requirement. 4. Equipment for commercial air operations.

PART III

flight instruments

5. Generalrequirements–flightinstruments. 6.Minimumflightinstruments. 7. Instruments for operations requiring two pilots in day Visual

FlightRules. 8. InstrumentsrequiredforInstrumentFlightRulesoperations. 9. Standby attitude indicator. 10. Equipment and instruments for Category II operations. 11. Equipment and instruments for Category III operations. 12. Equipment of aeroplanes operated by a single pilot under

InstrumentFlightRulesoratnight.

PART IV

communication equiPment

13. Radio equipment.14. Flightcrewandcabincrewmemberinterphonesystemforaeroplanes.

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15.Publicaddresssystem—airoperatorcertificateholders.

PART V

navigation equiPment

16. Navigation equipment – general requirements. 17.Minimumnavigationperformancespecifications. 18. Reduced vertical separation minimum. 19. Electronic navigation data management. 20. Altitude reporting transponder.

PART VI

aircraft lights and instrument illumination

21.Requiredaircraftlightsandinstrumentsillumination. 22.Required aircraft lights and instruments illumination for

commercial air transport operations.

PART VII

engine instruments

23. Requirements for engine instruments.

PART VIII

Warning instruments and systems

24.Machnumberindicator. 25. Loss of pressurisation indicator. 26. Landing gear indicator position and aural warning device. 27. Altitude alerting system. 28. Ground proximity warning system. 29.Weatherradar. 30. Airborne collision avoidance system.

Section

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31.Forwardlookingwindshearwarningsystem–turbojetaeroplanes

PART IX

flight and cockPit voice recorders

32. Cockpit voice recorders. 33. Cockpit voice recorders performance requirements. 34.Flightdatarecorders. 35. Recording of data link communications.

PART X

emergency, rescue and survival equiPment

36. General emergency equipment requirements—all aircrafts. 37. Exit. 38.Emergencylighting. 39. Emergency exit access. 40.Mainaislewidth. 41. Visual signalling devices. 42. Survival kits. 43. Emergency locator transmitter. 44.Portablefireextinguishers. 45.Lavatoryfireextinguisher. 46. Lavatory smoke detector. 47.Crashaxe. 48. Marking of break-in points. 49. First-aid kit. 50. Emergency medical kit—aeroplanes. 51. Oxygen storage and dispensing apparatus.

Section

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52.Protectivebreathingequipment.53. First-aid oxygen dispensing units. 54.Megaphones. 55. Individualflotationdevices. 56. Life rafts. 57.Flotationdeviceforhelicopterditching.

PART XI miscellaneous systems and equiPment

58.Seats,safetybeltsandshoulderharnesses. 59. Passenger and pilot compartment doors—aeroplanes. 60. Passenger information signs. 61. Materials for cabin interiors, cargo and baggage compartments. 62. Power supply, distribution and indication system. 63. Protective circuit fuses. 64. Icing protection equipment. 65.Pitotheatandindicationsystems. 66. Static pressure system. 67.Windshieldwipers. 68.Chartholder. 69. Cosmic radiation detection equipment. 70.Electronicflightbags. 71. Offences and penalties. 72. Appeals. 73. Repeal. first schedule: Category II–instruments and equipment approval

and maintenance requirements. second schedule: Helicopter equipment requirements.

Section

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third schedule: Mainpassengeraislewidth. fourth schedule: minimumnumberofportablefireextinguishers. fifth schedule: Marking of break in points. sixth schedule:Flightdatarecorders. seventh schedule: Emergency locator transmitor. eighth schedule: Fees. IT is hereby notified that the Minister of Transport andInfrastructuralDevelopment,inconsultationwiththeBoard,has,intermsofsection79oftheCivilAviationAct[Chapter 13:16], made thefollowingRegulations:—

PART I Preliminary

Title 1.TheseregulationsmaybecitedastheCivilAviation(Equipmentand Instruments) Regulations, 2018.

Interpretation 2.Intheseregulations,unlessthecontextotherwiserequires— “aeroplane”meansapower-drivenheavier-than-airaircraft

deriving its lifting flight chiefly from aerodynamicreactionsonsurfaceswhichremainfixedundergivenconditionsofflight;

“airborne collision avoidance system (ACAS)” means an aircraftsystemwhich—

(a) conformstotherequirementsprescribedforthepurpose;

(b) is based on secondary surveillance radar transponder signals;and

(c) operates independently of ground based equipment. “AirOperatorCertificate(AOC)”meansacertificateissued

bytheAuthoritywhichauthorisesanoperatortocarryoutspecifiedcommercialairtransportoperations;

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“appropriate aeronautical radio station” means, in relation toanaircraft,anaeronauticalradiostationservingtheareainwhichtheaircraftis,forthetimebeing;

“areanavigation”meansamethodofnavigationthatpermitsaircraftoperationsonanydesiredflightpathwithinthecoverageofstation-referencednavigationaidsorwithinthelimitsofthecapabilityofself-containedaids,oracombinationofthese;

“automatic direction finding equipment” means radio navigation equipment which automatically indicatesthebearingofanyradiostationtransmittingthesignalsreceivedbysuchequipment;

“Category I operation (CAT I)” means a precision instrument approachandlandingwithadecisionheightnotlowerthan60metres(200ft)andwitheitheravisibilityofnotlessthan800metresorarunwayvisualrangenotlessthan550metres;

“Category II operation (CAT II)” means a precision instrument approachandlandingwithadecisionheightlowerthan60metres(200ft)butnotlowerthan30metres(100ft)andavisualrangenotless350metres;

“Category IIIA operation (CAT IIIA)” means a precision approachandlandingwith—

(a) adecisionheightlowerthan30metres(100ft)ornodecisionheight;and

(b) arunwayvisualrangenotlessthan200metres; “Category IIIB operation (CAT IIIB)”means a precision

approachandlandingwith— (a) adecisionheightlowerthan15metres(50ft)or

nodecisionheight;and (b) arunwayvisualrangelessthan200mbutnotless

than50metres; “Category IIIC operation (CAT IIIC)” means a precision

instrumentapproachandlandingwithnodecisionheightandnorunwayvisualrangelimitations;

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“controlledflightintoterrain(CFIT)”meanswhenanairworthyaircraftisflown,underthecontrolofaqualifiedpilot,intoterrain,waterorobstacles,withinadequateawarenessonthepartofthepilotoftheimpendingcollision;

“distance measuring equipment (DME)” means radio equipment capable of providing a continuous indication oftheaircraft’sdistancefromtheappropriateaeronauticalradiostations;

“emergency locator transmitter” means any equipment capable of broadcasting distinctive signals on designated frequencies and, depending on application, may be automatically activatedbyimpactorbemanuallyactivated;

“engine” means a unit used or intended to be used for aircraft propulsionandconsistsofat least thosecomponentsand equipment necessary for functioning and control, butexcludesthepropellerorrotors;

“enhanced ground proximity warning system (EGPWS)”meansaforwardlookingwarningsystemthatusestheterraindatabaseforterrainavoidance;

“flash resistant” means not susceptible to burning whenignited;

“flightrecorder”meansanytypeofrecorderinstalledintheaircraftforthepurposeofcomplementingaccidentorincident investigationand includes thecockpitvoicerecorderorflightdatarecorder;

“ground proximity warning system (GPWS)” means a warning systemthatusesradaraltimeterstoalertthepilotsofhazardousflightconditions;

“highspeedauralwarning”meansaspeedwarningthatisrequiredforturbine-enginedairplanesandairplaneswitha Velocity maximum operation (Vmo) or Maximum operationmachnumber(Mmo)greaterthan0.80Vdf/MdforVd/Md;

“Instrument Flight Rules (IFR)”means rules that governtheproceduresforconductingflightunderinstrumentmeteorologicalconditions;

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“long rangeoverwaterflights”means routes onwhich anaeroplanemaybeoverwaterandatmorethanadistancecorresponding to 120 minutes at cruising speed or 740 km(400NauticalMiles),whicheveristhelesser,awayfromlandsuitableformakinganemergencylanding;

“low altitude wind shear warning and guidance system”meansasystemthatissuesawarningoflowaltitudewindshearandmayprovide thepilotwithguidanceinformationoftheescapingmanoeuvre;

“mach number indicator” means an indicator that showsairspeedasafunctionoftheMachnumber;

“Minimum Equipment List means an equipment list approved bytheAuthoritywhichprovidesfortheoperationoftheaircraft,subjecttospecifiedconditions,withparticularequipment inoperative, prepared by an operator in conformitywith, ormore restrictive than, themasterminimumequipmentlistestablishedfortheaircrafttype;

“night”arethehoursbetweensunsetandsunriseorasmaybeprescribedbytheappropriateauthority;

“operator” means a person, organisation or enterprise engaged inorofferingtoengageinanaircraftoperation;

“reducedverticalseparationminimum”meansdefinedportionsofairspacewhere,basedonaRegionalAirNavigationAgreement, a reduced vertical separation minimum of 300m(1000ft)isappliedbetweenFlightLevel290andFlightLevel410inclusive;

“requirednavigationperformance”meansastatementofthenavigationperformancenecessaryforoperationswithadefinedairspace;

“runwayvisualrange”meanstherangeoverwhichthepilotofanaircraftonthecentrelineofarunwaycanseetherunwaysurfacemarkingsor the lightdelineating therunwayoridentifyingitscentreline;

“stateofoperator”meansthestateinwhichtheoperator’sprincipalplaceofbusinessislocated,orifthereisnosuchbusiness,theoperator’spermanentplaceofresidence;

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“state of registry”means the state on whose register theaircraftisentered;

“terrain awarenesswarning system”means a system thatprovides the flight crew with sufficient informationandalerting todetect apotentiallyhazardous terrainsituationandsothattheflightcrewmaytakeeffectiveactiontopreventacontrolledflightintoterrainevent;and

“typecertificatedaircraft”meansanaircraft thathasbeenissuedwithatypecertificate;

“VisualFlightRules”meansrulesthatgoverntheproceduresfor conducting flight under visual meteorologicalconditions;

“Velocity maximum operation” means maximum operating speed.

PART II equiPment of aircraft

General equipment and instruments requirement 3.(1)Inadditiontotheminimumequipmentnecessaryfortheissuance of a certificate of airworthiness under the regulations inforcerelatingtocivilaviationairworthiness,apersonshallnotflyanaircraftunlesstheaircraftisinstalledwithequipmentandinstrumentsspecifiedintheseregulationsasappropriate,inaccordancewiththecircumstancesunderwhichtheflightistobeconducted. (2)TheowneroroperatorofanyaircraftwhichisoperatedinZimbabwebutnotregisteredinZimbabwewhichusesanairworthinessinspectionprogrammeapprovedoracceptedbytheStateofRegistry,shallensurethatequipmentandinstrumentsinstalledintheaircraftareproperlyinstalledandinspectedinaccordancewiththeairworthinessrequirementsoftheStateofRegistry. (3)TheAuthoritymay specifyother additionalor specialequipmentasmayberequiredintheFirstSchedule. (4)Allrequiredequipmentandinstrumentsshallbeapprovedandinstalledinaccordancewithapplicableairworthinessrequirements.

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(5)Whereequipmentistobeusedbyoneflightcrewmemberathisorherstationduringflight,itshallbeinstalledsoastobereadilyoperablefromthatflightcrewmember’sstation. (6) Where a single item of equipment is required to beoperatedbymorethanoneflightcrewmember,itshallbeinstalledsothattheequipmentisreadilyoperablefromanystationatwhichtheequipmentisrequiredtobeoperated.

Equipment for commercial air operations 4.A person shall not commence a flight in commercial airtransportoperationsunlesstherequiredequipment— (a) meetstheminimumperformancestandard,alloperational

and airworthiness requirements and the relevantprovisions of International Civil Aviation Organisation Annex10,VolumeIV;

(b) isinstalledsuchthatthefailureofanysingleunitrequiredfor either communicationor navigationpurposes, orboth,willnotresultintheinabilitytocommunicateornavigatesafelyontheroutebeingflown;and

(c) iscapableofbeingoperatedforthekindofoperationbeingconducted,exceptasprovidedintheMinimumEquipment List.

PART III flight instruments

General requirements–flight instruments 5.(1)Anaircraftshallbeequippedwithflightinstrumentswhichenabletheflightcrewto— (a) controltheflightpathoftheaircraft; (b) carryoutanyrequiredproceduralmanoeuvres;and (c) observetheoperatinglimitationsoftheaircraftinthe

expected operating conditions. (2)Whereamethodisprovidedfortransferringaninstrumentfromitsprimaryoperatingsystemtoanalternativesystem,themethodshallincludeapositivepositioningcontrolandshallbemarkedsoastoindicateclearlywhichsystemisbeingused.

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(3)Theinstrumentsusedbyanyonepilotshallbesoarrangedas toallowthepilot toseetheindicationsreadilyfromhisorherstation,withtheminimumpracticabledeviationfromthepositionandlineofvisionwhichheorshenormallyassumeswhenlookingforwardalongtheflightpath.

Minimum flight instruments 6. A person may not operate any powered aircraft unless it is equippedwiththefollowingflightinstruments— (a) an airspeed indicating system calibrated in knots, miles

perhourorkilometresperhour; (b) asensitivepressurealtimetercalibratedinfeetwitha

sub-scalesettingcalibratedinhectopascalspermillibar,adjustableforanybarometricpressurelikelytobesetduringflight;

(c) an accurate time-piece indicating the time in hours,minutes,andseconds;

(d) amagneticcompass;and (e) anyotherequipmentasmaybespecifiedbytheAuthority.

Instruments for operations requiring two pilots in day Visual Flight Rules

7.Inanyflightwheretwopilotsarerequired,eachpilot’sstationshallhaveseparateflightinstrumentsasfollows— (a) anairspeedindicatorcalibratedinknots,milesperhour

orkilometresperhour; (b) asensitivepressurealtimetercalibratedinfeetwitha

sub-scalesettingcalibratedinhectopascalspermillibars,adjustableforanybarometricpressurelikelytobesetduringflight;

(c) averticalspeedindicator; (d) a turn and slip indicator, or a turn co-coordinator

incorporatingaslipindicator; (e) anattitudeindicator; (f) astabiliseddirectionindicator;and (g) anyotherequipmentasmaybespecifiedbytheAuthority.

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Instruments required for Instrument Flight Rules operations 8.(1)Inadditiontotherequirementsundersection5,allaircraftwhenoperatedinInstrumentFlightRules,orwhentheaircraftcannotbemaintainedinadesiredattitudewithoutreferencetooneormoreflightinstruments,shallbeequippedwith— (a) anairspeedindicatingsystemwithameansofpreventing

malfunctioningduetoeithercondensationoricing; (b) for commercial air transport operations, an additional

sensitive pressure altimeter calibrated in feetwith asub-scalesettingcalibratedinhectopascalspermillibars,adjustableforanybarometricpressurelikelytobesetduringflight;

(c) a turn and slip indicator for aeroplanes or a slip indicator forhelicopters;

(d) attitudeindicator(artificialhorizon)— (i) oneattitudeindicatorforaeroplanes; (ii) threeattitudeindicatorsforacommerciallyoperated

helicopter,oneofwhichmaybereplacedbyaturnindicator;or

(iii) two attitude indicators for a non-commercially operatedhelicopter,oneofwhichmaybereplacedbyaturnindicator;

(e) aheadingindicator(directionalgyroscope); (f) ameansofindicatingwhetherthesupplyofpowerto

thegyroscopicinstrumentsisadequate; (g) ameansofindicatingtheoutsideairtemperatureinthe

flightcrewcompartment; (h) arate-of-climbanddescentindicator; (i) for a commercial operated helicopter, a stabilisation

system operations, unless it has been demonstratedtothesatisfactionoftheAuthoritythatthehelicopterpossesses, by nature of its design, adequate stability withoutsuchasystem;and

(j) suchadditionalequipmentor instrumentsasmaybespecifiedbytheAuthority.

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(2)Therequirementsofsubsection(1)(c),(d)and(e)maybemetbycombinationsofinstrumentsorbyintegratedflightdirectorsystems: Providedthatthesafeguardsagainsttotalfailure,inherentintheseparateinstrumentsareretained. (3)ApersonshallnotoperateanaeroplanecommerciallyunderInstrumentFlightRules,orunderVisualFlightRulesoverroutesthatcannotbenavigatedbyreferencetovisuallandmarks,unlesstheaeroplaneisequippedwithnavigationequipmentinaccordancewiththerequirementsofairtrafficservicesintheareaorareasofoperation. (4)ApersonshallnotconductsinglepilotInstrumentFlightRulesoperationsforcommercialairoperationsunlesstheaeroplaneisequippedwithanautopilotwithatleastaltitudeholdandheadingmode. (5)ApersonshallnotoperateanaeroplaneunderInstrumentFlightRulesunlessitisequippedwithanaudioselectorpanelaccessibletoeachrequiredflightcrewmember. (6)ApersonshallnotconductsinglepilotInstrumentFlightRulesornightoperationsincommercialairtransportoperationsunlesstheaeroplaneisequippedwithaheadsetwithboommicrophoneoranequivalentandatransmitbuttononthecontrolwheel.

Standby attitude indicator 9.(1)Apersonshallnotoperateanaeroplanewithamaximumcertifiedtake-offmassexceeding5700kgoraperformanceClass1or2helicopterunlessitisequippedwithasinglestandbyattitudeindicator(artificialhorizon)that— (a) operatesindependentlyofanyotherattitudeindicating

system; (b) ispoweredcontinuouslyduringnormaloperation;and (c) afteratotalfailureofthenormalelectricalgenerating

system, is automatically powered for a minimum of 30minutesfromasourceindependentofthenormalelectrical generating system.

(2)Wherethestandbyattitudeindicatorisbeingoperatedbyemergencypower,itshallbeclearlyoperatingandilluminatedtotheflightcrew.

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(3)Wherethestandbyattitudeindicatorhasitsowndedicatedpowersupplythereshallbeanassociatedindication,eitherontheinstrumentorontheinstrumentpanelwhenthissupplyisinuse. (4)Wherethestandbyattitudeinstrumentsystemisinstalledandusablethroughflightattitudesof360degreesofpitchandroll,theturnandslipindicatorsmaybereplacedbyslipindicators.

Equipment and instruments for Category II operations 10.(1)Theinstrumentsandequipmentlistedintheseregulationsshallbeinstalled,approvedandmaintainedinaccordancewiththemanufacturer’sspecificationandasspecifiedundertheFirstScheduleforeachaircraftoperatedinaCategory II operation. (2) Group I of a CategoryIIoperationshallbeequippedwiththefollowingequipmentwhichshallbeinspectedbothwithinthreecalendarmonthsofthepreviousinspectionandshallalsohaveabenchinspectionwithin12monthsofthepreviousbenchinspectionusingprocedurescontainedintheapprovedmaintenanceprogramme— (a) twolocaliserandglideslopereceivingsystemsandeach

systemshallprovide— (i) abasicInstrumentLandingSystemsdisplay;and (ii) aninstrumentpanelcapableofshowingabasic

Instrument Landing Systems display: Provided that a single localiser antenna

and a single glide slope antenna may be used; (b) a communications system that does not affect the

operation of at least one of the Instrument LandingSystems;

(c) amarkerbeaconreceiverthatprovidesdistinctiveauralandvisualindicationsoftheouterandthemiddlemarkers;

(d) twogyroscopicpitchandbankindicatingsystems; (e) twogyroscopicdirectionindicatingsystems; (f) twoairspeedindicators; (g) two sensitive altimeters adjustable for barometric

pressure,havingmarkingsat20footintervalsandeachhavingaplacarddisplayingthecorrectionforaltimeterscaleerrorandforthewheelheightoftheaircraft;

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(h) oneself-monitoringradioaltimeterwithdualdisplay; (i) twoverticalspeedindicators;and (j) aflightcontrolguidancesystemthatconsistsofeitheran

automaticapproachcoupleroraflightdirectorsystem. (3)CategoryIIoperationswithdecisionheightsbelow150feetshallbeequippedwitharadioaltimeter. (4)GroupIIofaCategoryIIoperationshallbeequippedwiththefollowingequipmentwhich,withtheexceptionofthestaticsystem,doesnotrequirespecialmaintenanceproceduresotherthanthosenecessarytoretaintheoriginalapprovalcondition— (a) warningsystemsforimmediatedetectionbythepilot

of system faults in items under subsection (2) (a), (d), and(i);

(b) dualcontrols; (c) an externally vented static pressure system with an

alternatestaticpressuresource; (d) awindshieldwiperorequivalentmeansofproviding

adequate cockpit visibility for a safe visual transition byeitherpilottotouchdownandrollout;and

(e) aheatsourceforeachairspeedsystempitottubeinstalledor an equivalent means of preventing malfunctioning duetoicingofthepitotsystem.

(5)GroupIIofaCategoryIIoperationequipmentshallbeinspectedwithin12monthsofthepreviousinspectionusingprocedurescontainedintheapprovedmaintenanceprogramme.

Equipment and instruments for Category III operations 11.(1)Theequipmentandinstrumentslistedinthisregulationshall be installed, approved and maintained in accordance withinternationallyacceptablecriteriaandtheAircraftFlightManualineachaircraftoperatedinaCategoryIIIoperation. (2)AirbornesystemsforCategoryIIIAminimanotlessthanRunwayVisualRange200m (600 ft) shallbeequippedwith thefollowingequipment inaddition to the instrumentandnavigationequipmentrequiredby thisPart forInstrumentFlightRulesflightand Category II operations—

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(a) a redundant flight control or guidance systemdemonstrated in accordance with internationallyacceptablecriteriawhichincludes—

(i) a Fail Operational or Fail Passive automatic landing systematleasttotouchdown;

(ii) aFailOperationalorFailPassivemanualflightguidance system providing suitable head-up orhead-down command guidance, and suitablemonitoringcapabilityatleasttotouchdown;

(iii) ahybridsystem,usingautomaticlandingcapabilityas the primary means of landing at least totouchdown;or

(iv) othersystemsthatcanprovideanequivalentlevelofperformanceandsafety;

(b) anautomaticthrottleorautomaticthrustcontrolsystemthatmeetsapprovedcriteriaasspecifiedintheAircraftFlightManualexceptthatforoperationswitha15m(50ft)DecisionHeight,orotheroperationsthathavebeenspecificallyevaluatedsuchasforengineinoperativelanding capability, automatic throttles may not berequired if it has been demonstrated that operationscanbesafelyconducted,withanacceptableworkload,withouttheiruse;

(c) at least two independent navigation receivers or sensors providing lateral and vertical position or displacement information, typically with the first pilot’s stationreceiving the information from one and the secondpilot’sstationreceivingtheinformationfromtheother;

(d) atleasttwoapprovedradioaltimetersystemsthatmeettheperformancerequirementscriteriaasspecifiedintheAircraftFlightManual,typicallywiththefirstpilot’sstationreceivinginformationfromoneandthesecondpilot’sstationreceivinginformationfromtheother;

(e) failure detection, annunciation, and warning capability, asdeterminedtobeacceptablebycriteriaspecifiedintheAircraftFlightManual;

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(f) missedapproachguidanceprovidedbyoneormoreofthefollowingmeans—

(i) attitudedisplaysthatincludesuitablepitchattitudemarkings, or a pre-established computed pitchcommanddisplay;

(ii) anapprovedflightpathangledisplay;or (iii) an automatic or flight guidance go-around

capability; (g) suitableforwardandsideflightdeckvisibilityforeach

pilotasspecifiedintheAircraftFlightManual;and (h) suitablewindshieldrainremoval,iceprotection,ordefog

capabilityasspecifiedintheAircraftFlightManual. (3)The navigation receivers or sensors referred to undersubsection (2)(c)shallmeetthecriteriaspecifiedforcategoryIIIAoperations. (4)Airborne systems forCategory IIIBminima less thanRunwayVisualRange200m(600ft)butnotlessthanRunwayVisualRange125m(400ft)shallbeequippedwiththefollowingequipmentinadditiontotheinstrumentandnavigationequipmentrequiredbythisPartforInstrumentFlightRulesflight,CategoryIIandCategoryIIIA operations— (a) a redundant flight control or guidance system

demonstrated in accordance with internationallyacceptablecriteriawhichinclude—

(i) a Fail Operational landing system with a FailOperationalorFailPassiveautomaticrolloutsystem;

(ii) aFailPassivelandingsystem,limitedtotouchdownzoneRunwayVisualRangenotlessthanRunwayVisualRange200m(600ft),withFailPassiverollout provided automatically or by a flightguidancesystemprovidingsuitablehead-uporhead-downguidance,andsuitablemonitoringcapability;

(iii) a Fail Operational hybrid automatic landingand rollout system with comparable manualflightguidancesystem,usingautomaticlandingcapability as the primarymeans of landing; or

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(iv) othersystemthatcanprovideanequivalentlevelofperformanceandsafety;

(b) anautomatic throttleorautomatic thrustcontrol thatmeetstheappropriatecriteriaasspecifiedintheAircraftFlightManualexceptthatforoperationswitha15m(50 ft)DecisionHeight, automatic throttlesmaynotberequiredifithasbeendemonstratedthatoperationscansafelybeconducted,withanacceptableworkload,withouttheiruse;

(c) at least two independent navigation receivers or sensors providing lateral and vertical position or displacement information, typically with the first pilot’s stationreceivinginformationfromoneandthesecondpilot’sstationreceivinginformationfromtheother;

(d) atleasttwoapprovedradioaltimetersystemsthatmeettheperformancecriteriaspecifiedintheAircraftFlightManual,typicallywiththefirstpilot’sstationreceivinginformation from one and the second pilot’s stationreceivinginformationfromtheother;

(e) failure detection, annunciation and warning capability asspecifiedintheAircraftFlightManual;

(f) missedapproachguidanceprovidedbyoneormoreofthefollowingmeans—

(i) attitude displays that include calibrated pitchattitudemarkings,orapre-establishedcomputedpitchcommanddisplay;

(ii) anapprovedflightpathangledisplay;or (g) anautomaticorflightguidancego-aroundcapability; (h) suitableforwardandsideflightdeckvisibilityforeach

pilot,asspecifiedintheAircraftFlightManual;and (i) suitablewindshieldrainremoval,iceprotection,ordefog

capabilityasspecifiedintheAircraftFlightManual. (5)The navigation receivers or sensors referred to undersubsection(4)(c)shallmeetthecriteriaspecifiedintheAircraftFlightManual.

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(6)Airborne systems forCategory IIICminima less thanRunwayVisual Range 75m (250 ft) shall be equippedwith thefollowingequipment inaddition to the instrumentandnavigationequipmentrequiredby thisPart forInstrumentFlightRulesflightandCategoryII,CategoryIIIAandCategoryIIIBoperations— (a) aFailOperationalAutomaticFlightControlSystem,

ormanualflightguidancesystemdesignedtomeetfailoperationalsystemcriteria,orahybridsysteminwhichboththefail-passiveautomaticsystemandthemonitoredmanualflightguidancecomponentsprovideapproachandflareguidancetotouchdown,andincombinationprovidefullfailoperationalcapability;and

(b) aFailOperationalautomatic,manual,orhybridRolloutControl System.

Equipment of aeroplanes operated by a single pilot under Instrument Flight Rules or at night

12. An aeroplane operated by a single pilot under Instrument FlightRulesoratnightshallbeequippedwith— (a) aserviceableautopilotthathasatleastaltitudeholdand

headingselectmodes; (b) aheadsetwithaboommicrophoneorequivalent;and (c) means of displaying charts that enables them to be

readableinallambientlightconditions.

PART IV communication equiPment

Radio equipment 13.(1)Apersonshallnotoperateanaircraftunlessitisequippedwithradiocommunicationequipmentrequiredforthekindofoperationbeing conducted. (2)AnaircraftoperatedinVisualFlightRulesasacontrolledflight,inInstrumentFlightRules,atnight,asanextendedflightoverwater,oroverlanddesignatedbytheAuthorityasespeciallydifficultforsearchandrescue,shallbeequippedwithradiocommunicationequipment—

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(a) capable of conducting two-way communication at any timewithairtrafficservicesoraeronauticalstations;

(b) capable of conducting communications on thosefrequenciesprescribedbytheAuthority;

(c) capable of receiving meteorological information at any timeduringtheflight;

(d) capable of conducting communications on theaeronauticalemergencyfrequency121.5MHz;

(e) approved and installed in accordance with therequirementsapplicabletothem,includingtheminimumperformancerequirements;

(f) installedsuchthatthefailureofanysingleunitrequiredfor communication equipment,will not result in thefailure of another unit required for communicationpurposes;and

(g) meetinganyotherrequirementsasmaybespecifiedbytheAuthority.

(3)Apersonshallnotoperateanaircraftincommercialairtransportoperations,orasotherwisespecifiedbytheAuthority,unlesstheaircraftisequippedwithtwoindependentradiocommunicationssystems,appropriatetotherouteandairspaceused. (4)Wheremorethanonecommunicationsequipmentunitisrequired,eachshallbeindependentoftheotherorotherstotheextentthatafailureinanyonewillnotresultinfailureofanyother. (5)Apersonshallnotoperateanaircraftincommercialairtransportoperationsunlesstheaircraftisequippedwithaboomorthroatmicrophone available at each requiredflight crewmemberflightdutystation.

Flight crew and cabin crew member interphone system for aeroplanes

14.(1)Apersonshallnotoperateanaeroplaneincommercialairtransportoperationsonwhichaflightcrewofmorethanoneisrequiredunlesstheaeroplaneisequippedwithaflightcrewinterphonesystem,includingheadsetsandmicrophones,notofahandheldtype,forusebyallmembersoftheflightcrew.

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(2)Apersonshallnotoperateanaeroplaneincommercialairtransportoperationswithamaximumcertifiedtake-offmassexceeding15000kg,orhavinganapprovedpassengerseatingcapacityof19ormore,orhavingaflightcrewcompartmentdoor,unlesstheaeroplaneisequippedwithacrewmemberinterphonesystemthat— (a) operates independently of the public address system

except for handsets, headsets,microphones, selectorswitchesandsignallingdevices;

(b) provides a means of two-way communication between theflightcrewcompartmentandeach—

(i) passengercompartment; (ii) galleylocatedotherthanonapassengerdecklevel;

and (iii) remote crew compartment that is not on the

passenger deck and is not easily accessible from apassengercompartment;

(c) is readily accessible for use— (i) fromeachoftherequiredflightcrewstationsin

theflightcrewcompartment;and (ii) at required cabin crew member stations close to

eachseparateorpairoffloorlevelemergencyexits; (d) has an alerting system incorporating aural or visual

signalsforusebyflightcrewmemberstoalertthecabincrew,andforusebycabincrewmemberstoalerttheflightcrewintheeventofsuspiciousactivityorsecuritybreachesinthecabin;

(e) has ameans for the recipient of a call to determinewhetheritisanormalcalloranemergencycall;and

(f) provides on the ground a means of two-waycommunication between ground personnel and at least twoflightcrewmembers.

Public address system–air operator certificate holders 15. (1)An air operator certificate holder shall not operate apassengercarryingaeroplanewithamaximumapprovedpassenger

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seatingconfigurationofmorethan19unlessitisequippedwithapublicaddresssystemthat— (a) operatesindependentlyoftheinterphonesystemsexcept

forhandsets,headsets,microphones,selectorswitchesandsignallingdevices;

(b) isreadilyaccessibleforimmediateusefromeachrequiredflightcrewmemberstation;

(c) foreachrequiredfloorlevelpassengeremergencyexitwhichhasanadjacentcabincrewseat,isfurtherequippedwithamicrophonewhichisreadilyaccessibletotheseatedcabincrewmember,exceptthatonemicrophonemayservemorethanoneexit,providedtheproximityof the exits allowsunassistedverbal communicationbetweenseatedcabincrewmembers;

(d) iscapableofoperationwithin10secondsbyacabincrewmemberateachofthosestationsinthecompartmentfromwhichitsuseisaccessible;and

(e) is audible and intelligible at all passenger seats, toilets, and cabin crew seats and workstations.

(2)An air operator certificate holder shall not operate apassengercarryinghelicopterwithamaximumapprovedpassengerseatingconfigurationofmorethan19unlessitisequippedwithapublicaddresssystemthat— (a) operatesindependentlyoftheinterphonesystemsexcept

forhandsets,headsets,microphones,selectorswitchesandsignallingdevices;

(b) isreadilyaccessibleforimmediateusefromeachrequiredflightcrewmemberstation;

(c) foreachrequiredfloorlevelpassengeremergencyexitwhichhasanadjacentcabincrewseat,isfurtherequippedwithamicrophonewhichisreadilyaccessibletotheseatedcabincrewmember,exceptthatonemicrophonemayservemorethanoneexit,providedtheproximityof the exits allowsunassistedverbal communicationbetweenseatedcabincrewmembers;

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(d) iscapableofoperationwithin10secondsbyacabincrewmemberateachofthosestationsinthecompartmentfromwhichitsuseisaccessible;

(e) is audible and intelligible at all passenger seats, toilets, andcabincrewseatsandworkstations;and

(f) following a total failure of the normal electricalgenerating system, provide a reliable operation for a minimum period of 10 minutes.

(3)An air operator certificate holder shall not operate apassengercarryinghelicopterwithamaximumapprovedpassengerseating configurationofmore than9but less than19unless it isequippedwithapublicaddresssystem. (4)Subsection(3)shallnotapplywhere— (a) thehelicopterisdesignedwithoutabulkheadbetween

pilotandpassengers;and (b) theoperatorisabletodemonstrateinamanneracceptable

totheAuthoritythatwheninflight,thepilot’svoiceisaudible and intelligible at all passenger seats.

PART V navigation equiPment

Navigation equipment general requirements 16.(1)Apersonshallnotoperateanaircraftunlessitisequippedwithnavigationequipmentthatenablesittoproceedinaccordancewith— (a) itsoperationalflightplan;and (b) therequirementsofairtrafficservices. (2)Apersonshallnotoperateaflightindefinedportionsofairspace,includingMinimumNavigationPerformanceSpecifications,ReducedVerticalSeparationMinimum,oronrouteswhereaRequiredNavigationalPerformanceTypehasbeenprescribedunless— (a) thepersonhasreceivedauthorisationfromtheAuthority

in either operations specifications for air operatorcertificateholdersorletterofauthorisationfornon-airoperatorcertificateholders;

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(b) theaircraftisequippedwithnavigationequipmentwhichenablesittooperateinaccordancewiththeprescribedRequiredNavigationPerformanceType;and

(c) theaircraftisequippedwithnavigationequipmentthatcontinuouslyprovidesinformationtotheflightcrewofadherencetoordeparturefromtrackwithrespecttotherequireddegreeofaccuracyatanypointalongthattrack.

(3)Apersonshallnotoperateanaircraftunlessitisequippedwithsufficientnavigationequipmentthatwillenabletheaircrafttonavigateinaccordancewithsubsections(1)and(2),suchthat— (a) intheeventofthefailureofanypieceofnavigation

equipmentatanystageofflight,theremainingequipmentenablestheaircrafttocontinuetonavigate;and

(b) the failure of any single unit required for eithercommunicationsornavigationpurposes,orbothdoesnot result in the failure of another unit required forcommunications or navigation purposes.

(4)Theequipmentrequirementsspecifiedundersubsection(3)(a) shall not apply in instanceswhere theAuthority authorisesVisualFlightRulesbyvisualreferencetolandmarks. (5)ApersonshallnotoperateanaeroplaneunderInstrumentFlightRules,orunderVisualFlightRulesoverroutesthatcannotbenavigatedbyreferencetovisuallandmarks,unlesstheaeroplaneis equipped with navigation equipment in accordance with therequirementsofairtrafficservicesintheareaorareasofoperation. (6) An aircraft intended to land in Instrument Meteorological Conditions or at night shall be provided with radio navigationequipment capable of receiving signals providing guidance to— (a) apointfromwhichavisuallandingcanbeeffected; (b) each aerodrome at which it is intended to land in

InstrumentMeteorologicalConditions;and (c) any designated alternate aerodromes.

Minimum navigation performance specifications 17.(1)ApersonshallnotoperateanaeroplaneinMinimumNavigationPerformanceSpecificationairspaceunlessitisequippedwithnavigationequipmentthat—

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(a) continuouslyprovidesindicationstotheflightcrewofadherence toordeparture from track to the requireddegreeofaccuracyatanypointalongthattrack;and

(b) isauthorisedbytheAuthorityforMinimumNavigationPerformanceSpecificationoperationsconcernedthrougheitheroperationsspecificationsforairoperatorcertificateholdersorletterofauthorisationforgeneralaviation.

(2) The navigation equipment required for operations inMinimumNavigationPerformanceSpecificationairspaceshallbevisibleandusablebythepilotseatedathisorherdutystation. (3) For unrestricted operation in Minimum Navigation PerformanceSpecificationairspaceanaeroplaneshallbeequippedwithtwoindependentLong-RangeNavigationSystems. (4) For operation in Minimum Navigation Performance Specification airspace along notified special routes, an aeroplaneshallbeequippedwithoneLong-RangeNavigationSystem,unlessotherwisespecified.

Reduced vertical separation minimum 18.(1)Forflightsindefinedportionsofairspacewhere,basedona Regional Air Navigation Agreement, a Reduced Vertical Separation Minimumof 300 m (1 000 ft) is applied between FL 290 and FL 410 inclusive,anaeroplaneshallbe— (a) equippedsuchthattheequipmentiscapableof— (i) indicatingtotheflightcrewtheflightlevelbeing

flown; (ii) automaticallymaintainingaselectedflightlevel; (iii) providinganalerttotheflightcrewwhenadeviation

occursfromtheselectedflightlevel;and (iv) automaticallyreportingpressure-altitude;and (b) authorisedforoperationsintheairspaceconcernedby— (i) theStateofOperatorforairoperatorcertificate

holdersthroughoperationsspecifications;or (ii) theStateofRegistryfornon-airoperatorcertificate

holdersthroughaletterofauthorisation.

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(2) An application for Reduced Vertical Separation Minimum approvalorauthorisationshallbemadetotheAuthorityinanapprovedformandshallbeaccompaniedbyfeessetoutintheEighthSchedule. (3) Prior to granting a Reduced Vertical Separation Minimum approvalrequiredundersubsection(1),theAuthorityshallfirstsatisfyitselfthat— (a) the vertical navigation performance capability of

the aeroplane satisfies the requirements specified inInternationalCivilAviationOrganisationAnnex6;

(b) the operator has instituted appropriate proceduresin respect of continued airworthiness includingmaintenanceandrepairpracticesandprogrammes;and

(c) the operator has instituted appropriate flight crewprocedures for operations in Reduced Vertical Separation Minimum airspace.

(4)TheAuthority shall, in consultationwith the State ofRegistry,whereappropriate,ensurethatadequateprovisionsexist,inrespectofthoseaeroplanesreferredtoundersubsection(1),for— (a) receiving the reports of height-keeping performance

issued by the monitoring agencies establishedin accordance with International Civil AviationOrganisationAnnex11;and

(b) taking immediate corrective action for individual aircraft, or aircraft type groups, identified in such reports asnot complyingwith theheight-keeping requirementsfor operations in airspacewhere aReducedVerticalSeparation Minimum is applied.

(5)Anaeroplaneshallbesufficientlyequippedwithnavigationequipmenttoensurethat,intheeventofthefailureofoneitemofequipmentatanystageoftheflight,theremainingequipmentenablestheaeroplanetonavigateinareducedverticalseparationminimumspace. (6)Thethresholdforthealertreferredtoundersubsection(1)(a)(iii)shallnotexceed+or-90m(300ft).

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Electronic navigation data management 19.ApersonshallnotemployelectronicnavigationdataproductsthathavebeenprocessedforapplicationintheairandonthegroundunlesstheAuthorityhasapproved— (a) theoperator’sproceduresforensuringthattheprocess

applied and the products delivered have acceptablestandardsofintegrityandthattheproductsarecompatiblewiththeintendedfunctionoftheequipment;

(b) theoperator’sprogrammeforcontinualmonitoringofbothprocessandproducts;and

(c) theoperator’sprocedurestoensurethetimelydistributionand insertion of current and unaltered electronic navigationdatatoallaircraftthatrequireit.

Altitude reporting transponder 20.(1)Apersonshallnotoperateanaircraftinairspacethatrequiresapressurereportingtransponderunlessthepressurereportingtransponder is operative and functional. (2)ApersonshallnotoperateanaircraftataltitudesaboveFlight Level of 290 unless it is equipped with a system that isautomatically reporting pressure altitudes. (3)Apersonshallnotoperateanaircraftincommercialairtransport operationsunless it is equippedwith a pressure-altitudereportingtransponderthatoperatesinaccordancewiththerequirementsof Zimbabwe air traffic services and International CivilAviationOrganisation Annex 10, Volume 4. (4) An aeroplane for which the individual certificate ofairworthinesswasfirstissuedafter1January2009,shallbeequippedwithadatasourcethatprovidespressure-altitudeinformationwitharesolution of 7.62 m (25 ft), or better. (5)After1January2009,allaeroplanesflyinginZimbabweshallbeequippedwithadatasourcethatprovidespressure-altitudeinformationwitharesolutionof7.62m(25ft),orbetter. (6)WhereanaeroplaneisequippedwithaModeStranspondertheModeStranspondershallbeprovidedwithanairborneoron-the-groundstatusiftheaeroplaneisequippedsuchthatitiscapableofdetectingsuchstatusautomatically.

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PART VI aircraft lights and instruments illumination

Required aircraft lights and instruments illumination 21.(1)Anaircraftoperatedatnightshallbeequippedwith— (a) alandinglight; (b) navigationorpositionlights; (c) illuminationforallflightequipmentand instruments

thatareessentialforthesafeoperationoftheaircraft; (d) lightsinallpassengercompartments;and (e) aflashlightforeachcrewmemberstation. (2)Anaircrafttypecertificatedwithaviationredoraviationwhiteanti-collisionsystemshallbeequippedwithananti-collisionsystemoperativeinbothdayandnightandintheeventofthefailureofanylightoftheanti-collisionlightsystem,operationoftheaircraftshall continue toa locationwhere repairsor replacementscanbemade.

Required aircraft lights and instruments illumination for commercial air transport operations

22.A person shall not operate an aircraft in commercial airtransportoperationsunlessitisequippedwith— (a) twolandinglightsorasinglelighthavingtwoseparately

energisedfilaments; (b) ananti-collisionlightsystem; (c) illuminationforallflightequipmentand instruments

thatareessentialforthesafeoperationoftheaircraft; (d) lightsinallpassengercompartments; (e) aflashlightforeachcrewmemberstation; (f) navigationorpositionlights; (g) lights toconform to the international regulations for

preventingcollisionsatseaiftheaircraftisaseaplaneoranamphibianaircraft;and

(h) alandinglightthatistrainable,atleastintheverticalplaneforhelicopters.

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PART VII engine instruments

Requirements for engine instruments 23. (1) Unless the Authority allows or requires differentinstrumentation for turbine engine powered aeroplanes to provide equivalent safety, aperson shallnotoperateanypoweredaircraftunlessitisequippedwiththefollowingengineinstruments— (a) ameansforindicatingfuelquantityineachfueltank

tobeused; (b) anoilpressureindicatorforeachengine; (c) anoiltemperatureindicatorforeachengine; (d) amanifoldpressureindicatorforeachengine;and (e) atachometerforeachengine. (2) Unless the Authority allows or requires differentinstrumentation for turbine engine powered aeroplanes to provide equivalentsafety,inadditiontothelistedequipmentrequirementsundersubsection(1),apersonshallnotoperateanypoweredaircraftunlessitisequippedwiththefollowingengineinstruments— (a) acarburettorairtemperatureindicatorforeachpiston

engine; (b) acylinderheadtemperatureindicatorforeachair-cooled

pistonengine; (c) afuelpressureindicatorforeachengine; (d) afuelflowmeterorfuelmixtureindicatorforeachengine

notequippedwithanautomaticaltitudemixturecontrol; (e) anoilquantityindicatorforeachoil-tankwhenatransfer

orseparateoilreservesupplyisused; (f) anindependentfuelpressurewarningdeviceforeach

engineoramasterwarningdeviceforallengineswithameans for isolating the individualwarningcircuitsfromthemasterwarningdevice;

(g) device for each reversible propeller, to indicate tothepilotwhenthepropellerisinreversepitch,whichcomplieswiththefollowing—

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(i) the devicemaybe actuated at anypoint in thereversingcyclebetweenthenormallowpitchstoppositionandfullreversepitch,butitmaynotgiveanindicationatorabovethenormallowpitchstopposition;or

(ii) the source of indication shall be actuated by thepropeller blade angle or be directly responsive to it.

PART VIII Warning instruments and systems

Mach number indicator 24.An aircraftwith speed limitations expressed in terms ofMachnumbershallbeequippedwithaMachnumberindicator.

Loss of pressurisation indicator 25.Apressurisedaircraftintendedtobeoperatedatflightaltitudesabove25000feetshallbeequippedwithadevicetoprovidepositivewarningtotheflightcrewofanydangerouslossofpressurisation.

Landing gear indicator position and aural warning device 26.(1)Apoweredcivilaircraftwithretractablelandinggearshallbeequippedwithalandinggearpositionindicator. (2)Anaeroplanewithretractablelandinggearshallbeequippedwithanauralwarningdevicethatfunctionscontinuouslyunderthefollowing conditions— (a) foraeroplaneswithanestablishedapproachwing-flap

position,wheneverthewingflapsareextendedbeyondthemaximumcertifiedapproachclimbconfigurationpositionintheAeroplaneFlightManualandthelandinggearisnotfullyextendedandlocked;and

(b) foraeroplaneswithoutanestablishedapproachclimbwing-flapposition,wheneverthewingflapsareextendedbeyondthepositionatwhichlandinggearextensionisnormallyperformedandthelandinggearisnotfullyextendedandlocked;

(3)Thewarningsystemrequiredundersubsection(2)—

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(a) maynothaveamanualshutoff; (b) shallbeinadditiontothethrottle-actuateddeviceinstalled

underthetypecertificationairworthinessrequirements;and

(c) may utilise any part of the throttle-actuated systemincludingtheauralwarningdevice.

(4)Theflapposition-sensingunitreferredtoundersubsection(2)maybeinstalledatanysuitableplaceintheaeroplane.

Altitude alerting system 27.(1)ApersonshallnotoperateaturbinepoweredaeroplaneinZimbabwewithamaximumcertifiedtake-offmassinexcessof5700kgorhavingamaximumapprovedpassengerseatingconfigurationofmorethan9seats,oraturbojetpoweredaeroplane,unlessitisequippedwithanaltitudealertingsystemcapableof— (a) alertingtheflightcrewuponapproachingpreselected

altitudeineitherascentordescent;and (b) alertingtheflightcrewbyanauralsignal,whendeviating

above or below a preselected altitude. (2) For operations in defined portions of airspacewhere,based on Regional Air Navigation Agreement, a vertical separation minimumof300m(1000ft)isappliedaboveflightlevelof290,anaircraft shallbe equippedwithequipmentwhich is capableofprovidinganalerttotheflightcrewwhenadeviationoccursfromtheselectedflightlevel. (3)Thethresholdforthealertreferredtoundersubsection(2) may not exceed ±90 m (300 ft).

Ground proximity warning system 28. (1)Anoperator inZimbabweshallnotoperatea turbine-powered aeroplane, or piston-engined aeroplane of a maximum certificatedtake-offmassinexcessof5700kgorauthorisedtocarrymorethanninepassengers,unlessitisequippedwithaGroundProximityWarningSystemthathasaforwardlookingterrainavoidancefunction. (2) A Ground Proximity Warning System referred to under subsection(1)shallautomaticallyprovide,bymeansofauralsignals

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whichmaybesupplementedbyvisualsignals,timelyanddistinctivewarningtotheflightcrewofthefollowingcircumstances— (a) excessivedescentrate; (b) excessiveterrainclosurerate; (c) excessivealtitudelossaftertake-offorgo-around; (d) unsafeterrainclearancewhilenotinlandingconfiguration

suchas— (i) gearnotlockeddown;or (ii) flapsnotinalandingposition; and (e) excessivedescentbelowtheinstrumentglidepath.

Weather radar 29.Apersonshallnotoperate— (a) a pressurised aeroplane in commercial transport in an

areawherethunderstormsorotherpotentiallyhazardousweatherconditionsmaybeexpectedunlessitisequippedwithaweatherradar;

(b) ahelicopterincommercialairtransportwhencarryingpassengers in an areawhere thunderstorms or otherpotentially hazardous weather conditions may beexpectedunlessitisequippedwithaweatherradar.

Airborne collision avoidance system 30.(1)AnaircraftshallbeequippedwithsuchAirborneCollisionAvoidanceSystemasmaybeapprovedbytheAuthority. (2)ApersonoperatinganaircraftequippedwithanAirborneCollisionAvoidanceSystemshallhavethatsystemonandoperating. (3)Apersonshallnot— (a) operate a turbine engine aeroplane for which the

individual airworthiness certificate was first issuedafter24November2005,withamaximumcertificatedtake-offmassinexcessof15000kgorauthorisedtocarrymorethan30passengers;

(b) operate a turbine engine aeroplane of a maximum certificatedtake-offmassinexcessof5700kgbutnot

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exceeding15000kgorauthorisedtocarrymorethan19passengers,forwhichtheindividualairworthinesscertificatewasfirstissuedafter1stJanuary,2008;

(c) commerciallyoperateaturbinepoweredaeroplanewithamaximumcertificatedtake-offmassinexcessof5700kgorauthorisedtocarrymorethan19passengers;

unlessitisequippedwithanAirborneCollisionAvoidanceSystemII. (6) The Authority shall approve an Airborne CollisionAvoidance System that operates in accordance with the relevantprovisions of International Civil Aviation Organisation Annex 10, Volume IV.

Forward looking wind shear warning system–turbojet aeroplanes 31.(1)Aturbojetaeroplaneengagedincommercialairtransportoperationswithamaximumcertificatedtake-offmassinexcessof5700kgorauthorisedtocarrymorethan9passengersshallbeequippedwithaforward-lookingwindshearwarningsystem. (2)Theforward-lookingwindshearwarningsystemreferredtoundersubsection(1)shallbecapableof— (a) providingthepilotwithatimelyauralandvisualwarning

ofwindshearaheadoftheaircraftandtheinformationrequired topermit thepilot to safelycommenceandcontinueamissedapproachorgo-aroundortoexecuteanescapemanoeuvreifnecessary;and

(b) providing an indication to the pilot when the limitsspecified for the certification of automatic landingequipmentarebeingapproached,whensuchequipmentis in use.

PART IX flight and cockPit voice recorders

Cockpit voice recorders 32.(1)Apersonshallnotoperatethefollowingaircraftunlessitisequippedwithacockpitvoicerecordercapableofrecordingtheauralenvironmentoftheflightdeckduringflighttime—

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(a) allcommerciallyoperatedaeroplaneswithamaximumcertificatedtake-offmassofover5700kg;

(b) all aeroplanes with amaximum certificated take-offmassofmorethan27000kg;

(c) allcommerciallyoperatedhelicopterswithamaximumcertificatedtake-offmassofover3180kg;and

(d) allhelicopterswithacertificatedtake-offmassofover7 000 kg.

(2)Where a helicopter is not equippedwith a flight datarecorder,atleastamainrotorspeedshallberecordedononetrackofthecockpitvoicerecorder. (3) A cockpit voice recorder referred to in subsection (1) shallbecapableofretainingtheinformationrecordedduringatleastthelast30minutesofitsoperationortwohours,foraeroplanesofamaximumcertificatedtake-offmassofover5700kgorthatreceivedtheirindividualcertificateofairworthinessafter1January2003. (4)From1January2016,nopersonshalloperateanaircraftequippedwithacockpitvoicerecorderunlessitiscapableofretainingthe information recorded during at least the last two hours of itsoperation. (5)Allaeroplanesofamaximumcertificatedtake-offmassofover27000kgforwhichtheindividualcertificateofairworthinessisfirstissuedonorafter1January2021shallbeequippedwithacockpitvoicerecordercapableofretainingtheinformationrecordedduringatleastthelasttwenty-fivehoursofitsoperation.

Cockpit voice recorders performance requirements 33.(1)Acockpitvoicerecordershallbecapableofrecordingon at least four tracks simultaneously— (a) in an in-line format in one direction if a one directional

configurationisused;or (b) in both directions if a bi-directional configuration is

used. (2)Thetrackallocationforacockpitvoicerecordershallbeas follows— (a) Track1—co-pilotheadphonesandliveboommicrophone;

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(b) Track2—pilotheadphonesandliveboommicrophone; (c) Track3—areamicrophone;and (d) Track4—timereferenceplusthethirdandfourthcrew

members’headphoneandlivemicrophone,ifapplicable. (3)Topreservethecockpitvoicerecorderrecordings— (a) apersonshallnotturnoffacockpitvoicerecorderduring

flighttime; (b) the cockpit voice recorder shall be de-activated by

an authorisedpersonupon completionofflight timefollowinganaccidentorincident;and

(c) following an accident or incident, no person shallreactivatethecockpitvoicerecorderbeforeitsdispositionasdetermined inaccordancewith InternationalCivilAviation Organisation Annex 13.

(4) To facilitate location and identification in case of anaccident,theowneroroperatorshallensurethatthecockpitvoicerecordershall— (a) beeitherbrightorangeorbrightyellow; (b) havereflectivetapeaffixedtotheexternalsurfaceto

facilitateitslocationunderwater; (c) have an approved underwater locating device on or

adjacent to the recorder,which is secured in such amanner that it is not likely to be separatedduring acrashimpactandisautomaticallyactivated;and

(d) be constructed, located and installed so as to provide maximum practical protection for the recordings inorderthattherecordedinformationmaybepreserved,recovered and transcribed.

(5)The owner or operator of an aircraft equippedwith acockpitvoicerecordershallensurethat— (a) the aircraft has an alternate power source that

automatically engages and provides ten minutes, plus or minus one minute, of operation wheneveraeroplanepowertotherecorderceases,eitherbynormalshutdownorbyanyotherlossofpower;and

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(b) thealternatepowersourcereferredtoinparagraph(a)shallpowerthecockpitvoicerecorderanditsassociatedcockpitareamicrophonecomponents;

(c) thecockpitvoicerecordershallbelocatedascloseaspracticabletothealternatepowersource;

(d) allcockpitvoicerecordersshallbecapableofretainingthe information recordedduringat least the last twohoursoftheiroperation;

(e) theuseofmagnetictapeandwirecockpitvoicerecordersshallbediscontinued.

Flight data recorders 34.(1)Apersonshallnotoperatethefollowingaircraftunlessitisequippedwithaflightdatarecorder— (a) anaeroplaneincommercialairtransportoperationswith

amaximumcertificatedtake-offmassofover5700kguptoandincluding27000kgforwhichtheindividualcertificateofairworthinesswasfirstissuedonorafter01January1989unlessitisequippedwithaTypeIIFlightDataRecorder;

(b) an aeroplane with a maximum certificated take-offmassofmorethan27000kgforwhichtheindividualcertificateofairworthinesswasfirstissuedonorafter01January1989unless it isequippedwithaType IFlightDataRecorder;

(c) a turbine powered aeroplane in commercial air transport operationswithamaximumcertificatedtake-offmassofmorethan5,700kgforwhichtheindividualcertificateofairworthinesswasfirstissuedonorafter01January1987butbefore01January1989unlessitiswithaTypeIFlightDataRecorderwhichshallrecordtime,altitude,airspeed,normalaccelerationandheading;

(d) aturbinepoweredaeroplanewithamaximumcertificatedtake-offmassofmore than27000kgforwhich theindividualcertificateofairworthinesswasfirstissuedon or after 01 January 1987 but before 01 January1989andthatareoftypesofwhichtheprototypewas

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certificatedbytheappropriatenationalauthorityafter30September1969unlessitisequippedwithaTypeIIFlightDataRecorder;

(e) a turbine powered aeroplane with a maximumcertificated take-off mass of more than 5,700 kgforwhich the individualcertificateofairworthinesswasfirstissuedbefore1stJanuary,1987,unlessitisequippedwithaTypeIFlightDataRecorderwhichshallrecordtime,altitude,airspeed,normalaccelerationandheading;

(f) anaeroplanewithamaximumcertificatedtake-offmassofmorethan5700kgforwhichtheindividualcertificateofairworthinesswasfirstissuedafter01January2005unlessitisequippedwithaTypeIAFlightDataRecorder;

(g) anaeroplanewithamaximumcertificatedtake-offmassofmorethan5700kgforwhichtheindividualcertificateofairworthinesswasfirstissuedafter01January2016whichisequippedwithbothaflightdatarecorderandcockpitvoicerecorderunlessitisequippedwithtwocombinationrecorderswhichareflightdata recorderandcockpitvoicerecorder;

(h) a turbine powered aeroplane in commercial air transport operationswithamaximumcertificatedtake-offmassof5700kgorlessforwhichtheindividualcertificateofairworthinesswasfirstissuedonorafter01January1990unlessitisequippedwithaTypeIIAFlightDataRecorder;

(i) ahelicopterwithacertificatedtake-offmassofover7000kgunlessitisequippedwithaTypeIVFlightDataRecorder;and

(j) ahelicopterwithacertificatedtake-offmassofover3180kgunlessitisequippedwithaTypeIVAFlightData Recorder.

(2)Anyowneroroperatorofaircraftwhichisrequiredtobeequippedwithaflightdatarecorderandacockpitvoicerecordermayhaveacombinationrecorderfitted.

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(3) The owner or operator shall ensure that a flight datarecorderreferredtoinsubsection(1)shall— (a) be constructed, located and installed so as to provide

maximum practical protection for the recordings inorderthattherecordedinformationmaybepreserved,recoveredandtranscribed;

(b) becalibratedasrequiredbytheAuthority; (c) haveanapproveddevicetoassistinlocatingarecorder

that may be under water and can be automaticallyactivated;and

(d) becapableofretainingtheinformationrecordedduringthelast—

(i) 25hoursofoperation,inthecaseofTypesIandII;

(ii) 30minutesofoperation,inthecaseofaTypeIIA;and

(iii) 10hoursofoperation,inthecaseofTypesIVandV;and

(e) complywith the requirements specified in the SixthSchedule.

(4)The following flight data recordermedia shall not beacceptable for use in aircraft registered in Zimbabwe, or operated in commercial air transport operations in Zimbabwe— (a) engravingmetalfoil; (b) photographicfilm;or (c) analogue data using frequency modulation. (5)Apersonshallnot— (a) turnoffaflightdatarecorderduringflighttime; (b) deactivatetheflightdatarecorderuponcompletionof

flighttimefollowinganaccidentorincident;or (c) followinganaccidentorincident,reactivatetheflight

datarecorderbeforetheflightdispositionisdeterminedin accordance with International Civil AviationOrganisation Annex 13.

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Recording of data link communications 35.Anyowneroroperatorshallensurethat— (a) apoweredaircraftthatusesdatalinkcommunications

andisrequiredtocarryacockpitvoicerecordershallrecordonaflightrecorderalldatalinkcommunicationstoandfromtheaeroplane;

(b) theminimumrecordingdurationshallbeequaltotheduration of the cockpit voice recorder and shall becorrelatedtotherecordedcockpitaudio;

(c) the recording shall contain sufficient information toderive the content of the data link communicationsmessageand,wheneverpractical,thetimethemessagewas displayed to or generated by the crew shall berecorded.

PART X

emergency, rescue and survival equiPment

General emergency equipment requirements all aircraft 36.EachitemofemergencyandflotationequipmentreferredtounderthisPartshallbe— (a) readily accessible to the crew and, with regard to

equipment located in thepassenger compartment, topassengers without appreciable time for preparatoryprocedures;

(b) clearly identified and clearly marked to indicate itsmethodofoperation;

(c) markedastodateoflastinspection;and (d) markedastocontentswhencarriedinacompartment

or container.

Exits 37.(1)Apersonshallnotflyanaeroplaneunless,everyexitandeveryinternaldoor in theaeroplaneis inworkingorder,and,subjecttosubsections(2),(3)and(4),duringtake-offandlandingandduringanyemergency,everysuchexitanddoorshallbekeptfree

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ofobstructionandoperatinghandleshallnotbefastenedbylockingorotherwisesoastoprevent,hinderordelaydooroperationduringemergency. (2)Anexitmaybeobstructedbycargoifitisanexitwhich,inaccordancewitharrangementsapprovedbytheAuthority,eithergenerally or in relation to a class of aeroplane or a particular aeroplane, is not required for use by passengers. (3)Everyexitfromtheaeroplane,beinganexitintendedtobeusedbypassengersinnormalcircumstances,shallbeconspicuouslymarkedwiththeword“EXIT”incapitallettersandeveryexit,beinganexitintendedtobeusedbypassengersinanemergencyonly,shallbeconspicuouslymarkedwiththewords“EMERGENCYEXIT”incapitallettersorapprovedsymbolsdepictingthesame. (4) Every exit from the aeroplane shall be marked withinstructions andwith diagrams, to indicate the correctmethod ofopeningtheexitandthemarkingsshallbeplacedonorneartheinsidesurfaceofthedoororotherclosureoftheexitand,ifitcanbeopenedfromtheoutsideoftheaeroplane,andorneartheexteriorsurface. (5)Subject tocompliancewithsubsection (4), ifone,butnotmorethanone,exitfromanaeroplanebecomesinoperativeataplacewhereitisnotreasonablypracticableforittoberepairedorreplaced,nothinginthisregulationshallpreventthataeroplanefromcarryingpassengersuntilitnextlandsataplacewheretheexitcanbe repaired or replaced. (6)Onanyflightpursuanttosubsection(5)— (a) thenumberofpassengerscarriedandthepositionof

theseatswhichthepassengersoccupyshallbenolessthan thepercentageof thedoors thatareoperationalin accordance with arrangements approved by theAuthority;and

(b) inaccordancewitharrangementssoapproved,theexitshallbefastenedby lockingorotherwise, thewords‘‘EXIT’’and‘‘EMERGENCYEXIT’’shallbecovered,andtheexitshallbemarkedbyareddiscatleast23centimetres in diameter with a horizontal white baracrossitbearingthewords‘‘NOEXIT’’inredlettersorapprovedsymbolsdepictingthesame.

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(7)Inadditiontotherequirementsinthesubsectionsabove,arotorcraftshallhaveenoughopeningsontheside,top,bottomorendsofthefuselagetoallowevacuationwiththerotorcraftonitsside. (8)Apersonshallnotoperateahelicoptercertificatedwithamaximumtake-offmassofmorethan9072kgand10ormorepassengerseatsunlessitisequippedwithemergencyexitequipmentasspecifiedintheSecondSchedule.

Emergency lighting 38.(1)Apersonshallnotoperateapassengercarryingaeroplaneofamaximumapprovedpassengerseatingconfigurationofmorethannineunlesstheaeroplaneisprovidedwithanemergencylightingsystemhavinganindependentpowersupplytofacilitatetheevacuationoftheaeroplane. (2)Theemergencylightingsystemmustinclude— (a) for aeroplanes which have a maximum approved

passengerseatingconfigurationofmorethannineteen— (i) sourcesofgeneralcabinillumination; (ii) internallightinginfloorlevelemergencyexitareas; (iii) illuminated emergency exit marking and locating

signs; (iv) foraeroplanesforwhichtheapplicationforthe

type certificate or equivalent was filed in anappropriateauthorityandwhenflyingbynight,exterioremergencylightingatalloverwingexits,passenger emergency exits and at exits wheredescentassistmeansarerequired;and

(v) foraeroplanesforwhichthetypecertificatewasfirstissuedbyanappropriateauthorityonorafterthe1stJanuary,1958,floorproximityemergencyescape path marking system in the passengercompartment(s);

(b) for aeroplanes which have a maximum approvedpassengerseatingconfigurationof19orless—

(i) sourcesofgeneralcabinillumination;

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(ii) internallightinginemergencyexitareas;and (iii) illuminated emergency exit marking and locating

signs.

Emergency exit access 39. (1) A passageway between passenger compartments, and eachpassagewayleadingtoTypeIandTypeIIemergencyexitsinanaircraftshallbe— (a) unobstructed;and (b) atleast20incheswide. (2)Thereshallbeenoughspaceadjacenttoanemergencyexittoallowacrewmembertoassistintheevacuationofpassengerswithoutreducingtheunobstructedwidthofthepassagewaybelowthatrequiredforthatexit. (3)ThereshallbeaccessfromeachaisletoeachTypeIIIandTypeIVexit,sothat— (a) forrotorcraftthathaveapassengerseatingconfiguration

of 20 or more, excluding pilot seats, the projectedopeningoftheexitprovidedshallnotbeobstructedbyseats,berths,orotherprotrusions,includingseatbacksinanyposition,foradistancefromthatexitofnotlessthanthewidthofthenarrowestpassengerseatinstalledontherotorcraft;and

(b) forrotorcraftthathaveapassengerseatingconfigurationof19orless,excludingpilotseats,theremaybeminorobstructions in the region described in paragraph(a) if therearecompensating factors tomaintain theeffectivenessoftheexit.

Main aisle width 40.ThemainpassengeraislewidthbetweenseatsofanaircraftshallequalorexceedthevaluesasspecifiedintheThirdSchedule.

Visual signalling devices 41.ApersonshallnotoperateanaircraftoverwateroracrosslandareaswhichhavebeendesignatedbytheAuthorityasareasinwhichsearchandrescueisdifficultunlesstheaircraftisequipped

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withsuchsignallingdevicesasmaybeappropriatetotheareaoverflown,toinclude— (a) atleastonepyrotechnicsignallingdeviceforeachlife

raftrequiredforoverwateroperations;and (b) anyotherrequirementsspecifiedbytheAuthority.

Survival kits 42.ApersonshallnotoperateanaircraftacrosslandareaswhichhavebeendesignatedbytheAuthorityasareasinwhichsearchandrescueisdifficultunlesstheaircraftisequippedwithenoughsurvivalkitsforthenumberofoccupantsoftheaeroplaneappropriatefortheroutetobeflown.

Emergency locator transmitter 43.(1)Apersonshallnotoperateanaeroplaneforcommercialairtransportunlessitisequippedwithemergencylocatortransmitterequipment as follows— (a) anaeroplaneauthorisedtocarrymorethan19passengers

shallbeequippedwithatleastoneautomaticEmergencyLocator Transmitter or two Emergency Locator Transmittersofanytype;

(b) anaeroplaneauthorisedtocarrymorethan19passengersforwhichtheindividualcertificateofairworthinesswasfirstissuedafter1July2008shallbeequippedwithatleasttwoEmergencyLocatorTransmitters,oneofwhichshallbeautomatic;

(c) anaeroplaneauthorisedtocarry19passengersorlessforwhichtheindividualcertificateofairworthinessisfirstissuedafter1July2008shallbeequippedwithatleastoneautomaticEmergencyLocatorTransmitter;

(d) exceptasprovidedforunderparagraph(c),from1July2008,anaeroplaneauthorisedtocarry19passengersorlessshallbeequippedwithatleastoneEmergencyLocatorTransmitterofanytype;

(e) thedateforreplacementofthebatteryintheEmergencyLocator Transmitter shall be legibly marked on theoutsideofthetransmitter;and

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(f) at least one survival type Emergency Locator Transmitter shallbelocatedwitheachlife-raftcarried.

(2)Apersonshallnotoperateahelicopterunlessitisequippedwithemergencylocatortransmitterequipmentasfollows— (a) ahelicopteroperatinginperformanceClass1andClass2

shallbeequippedwithatleastoneautomaticEmergencyLocatorTransmitterand,whenoperatingonflightsoverwater,withatleastoneautomaticEmergencyLocatorTransmitter and one Emergency Locator Transmitter in araftorlifejacket;and

(b) a helicopter operating in performance Class 3 shallbe equippedwith at least one automatic EmergencyLocatorTransmitterand,whenoperatingonflightsoverwater,withatleastoneautomaticEmergencyLocatorTransmitter and one Emergency Locator Transmitter in araftorlifejacket.

(3)Apersonshallnotoperateanaeroplaneforgeneralaviationpurposesunless it isequippedwithemergency locator transmitterequipment as follows— (a) an aeroplane shall be equipped with at least one

EmergencyLocatorTransmitterofanytype;and (b) an aeroplane for which the individual certificate of

airworthinessisfirstissuedafter1July2008shallbeequippedwithatleastoneautomaticEmergencyLocatorTransmitter.

(4) Any Emergency Locator Transmitter equipment carried onanaeroplaneinaccordancewithsubsections(1)and(3)shallbecapableoftransmittingonthefrequencies121.5MHzand406MHzsimultaneously. (5)ThemannerinwhichtheEmergencyLocatorTransmittersshall be registered, carried, the specifications towhich they shalladhere,thefrequenciesonwhichtheyshallbeabletotransmitandthemannerinwhichtheyaretobemaintainedshallbeassetoutintheSeventhSchedule.

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Portable fire extinguishers 44.(1)Apersonshallnotoperateanaircraftunlessitisequippedwithportablefireextinguishersofatypewhich,whendischarged,doesnotcausedangerouscontaminationoftheairwithintheaircraft.

(2)Atleastoneportablefireextinguishershallbelocatedin— (a) thepilot’scompartment;and (b) eachpassengercompartmentthatisseparatefromthe

pilot’scompartmentandnotreadilyaccessibletotheflightcrew.

(3)Apersonshallnotoperateanaircraftunlessitisequippedwithportablefireextinguishersaccessibleforuseincrew,passenger,and cargo compartments as follows— (a) thetypeandquantityofextinguishingagentshallbe

suitable for the kinds of fires likely to occur in thecompartmentwheretheextinguisherisintendedtobeused;

(b) atleastoneportablefireextinguishershallbeprovidedandconvenientlylocatedforuseineachClassEcargocompartment which is accessible to crew membersduringflight,andatleastoneshallbelocatedineachupperandlowerlobegalley;

(c) atleastoneportablefireextinguishershallbeconvenientlylocatedontheflightdeckforusebytheflightcrew;

(d) atleastoneportablefireextinguishershallbeconvenientlylocatedinthepassengercompartmentifthepassengercompartmentisseparatefromtheflightdeckandnotreadilyaccessibletotheflightcrew;and

(e) foreachaeroplanehavingapassengerseatingcapacityofmorethan30,thenumberofportablefireextinguishersshallbeasspecifiedintheFourthScheduleandshallbe conveniently located and uniformly distributed throughoutthecompartment.

Lavatory fire extinguisher 45.(1)Apersonshallnotoperateapassenger-carryingtransportcategoryaeroplaneunlesseachlavatoryintheaeroplaneisequipped

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withabuilt-infireextinguisherforeachdisposalreceptaclefortowels,paper,orwastelocatedwithinthelavatory. (2)Abuilt-inlavatoryfireextinguisherreferredtoinsubsection(1)shallbedesignedtodischargeautomaticallyintoeachdisposalreceptacleuponoccurrenceofafireinthereceptacle. (3)Anyagentused inabuilt-infireextinguisher foreachlavatory disposal receptacle for towels, paper or waste in an aeroplane forwhich the individualcertificateofairworthiness isfirst issuedonorafter31December2011andanyextinguishingagentusedinaportablefireextinguisherinanaeroplaneforwhichtheindividualcertificateofairworthinesswasfirstissuedonorafter31December2016shall— (a) meettheapplicableminimumperformancerequirements

oftheStateofRegistry;and (b) notbeofatypelistedinthe1987MontrealProtocolon

SubstancesthatDepletetheOzoneLayerasitappearsintheEighthEditionoftheHandbookfortheMontrealProtocolonSubstancesthatDepletetheOzoneLayer,Annex A, Group II.

Lavatory smoke detector 46.Apersonshallnotoperateapassenger-carryingtransportcategoryaeroplaneunlesseachlavatoryintheaeroplaneisequippedwithasmokedetectorsystemorequivalentthatprovides— (a) awarninglightinthecockpit;or (b) awarninglightoraudiowarninginthepassengercabin

which is readily detected by a cabin crewmember,takingintoconsiderationthepositioningofcabincrewmembersthroughoutthepassengercompartmentduringvariousphasesofflight.

Crash axe 47.Apersonshallnotoperateanaeroplanecertificatedwithatake-offmassof500kgormoreunlessitisequippedwithacrashaxeappropriateforeffectiveuseinthattypeofaeroplane,storedinaplacenotvisibletopassengersontheaeroplane.

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Marking of break-in points 48.Whereareasofthefuselagesuitableforbreak-inbyrescuecrewsinanemergencyaremarkedonanaeroplane,suchareasshallbemarkedasintheFifthSchedule,andthecolourofthemarkingsshallberedoryellowand,ifnecessary,theyshallbeoutlinedinwhitecontrastwiththebackground.

First-aid kit 49.(1)Apersonshallnotoperateanaircraftunlessitisequippedwithanaccessible,approvedfirst-aidkitwithmedicalsuppliesadequatetothenumberofpassengerstheaircraftisauthorisedtocarry. (2)Thetype,number,locationandcontentsoffirst-aidkitstobecarriedinanaircraftreferredtoinsubsection(1)shallbeassetoutinAnnex6PartIAttachmentBtotheChicagoConvention.

Emergency medical kit–aircraft 50. (1)A person shall not operate a passenger flight in anaeroplanewith30seatsormoreunless theaeroplane isequippedwithanapprovedemergencymedicalkitfortreatmentofinjuriesormedicalemergenciesthatmightoccurduringflighttimeorinminoraccidents. (2)Thelocationandcontentsofemergencymedicalkitstobecarriedinanaircraftreferredtoinsubsection(1)shallbeassetoutinAnnex6PartIAttachmentBtotheChicagoConvention.

Oxygen storage and dispensing apparatus 51. (1) An aircraft intended to be operated at altitudes requiring the use of supplemental oxygen shall be equippedwith adequateoxygen storage and dispensing apparatus. (2)Theoxygenstorageanddispensingapparatus,theminimumrateofoxygenflow,andthesupplyofoxygenshallmeetapplicableairworthinessstandardsfortypecertificationinthetransportcategoryassetoutinAnnex6PartIChapter6fortheChicagoConvention. (3)Apersonshallnotoperateanaircraftataltitudesabove10,000feetunlessitisequippedwithoxygenmasks,locatedsoastobewithintheimmediatereachofflightcrewmemberswhileattheirassigned duty station.

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(4)A person shall not operate a pressurised aeroplane ataltitudes above 25,000 feet unless— (a) flightcrewmemberoxygenmasksareavailableatthe

flightdutystationandareofaquickdonningtype;and (b) sufficientspareoutletsandmasksorsufficientportable

oxygen units with masks are distributed evenlythroughoutthecabintoensureimmediateavailabilityofoxygentoeachrequiredcabincrewmemberregardlessofhisorherlocationatthetimeofcabinpressurisationfailure.

(5) An oxygen-dispensing unit connected to oxygen supply masksshallbeinstalledsoastobeimmediatelyavailabletoeachoccupant,whereverseated. (6)Thetotalnumberofoxygendispensingunitsandoxygensupplyterminalsshallexceedthenumberofseatsbyatleast10%andtheextraoxygenportableunitsaretobeevenlydistributedthroughoutthecabin. (7) The amount of supplemental oxygen for sustenancerequiredforaparticularoperationshallbedeterminedonthebasisofflightaltitudesandflightduration,consistentwiththeoperatingproceduresestablishedforeachoperationintheOperationsManualandwiththeroutestobeflown,andwiththeemergencyproceduresspecifiedintheOperationsManual.

Protective breathing equipment 52.(1)Anyairoperatorcertificateholdershallnotoperateanaeroplanewithamaximumcertifiedtake-offmassexceeding5700kgorhavingamaximumapprovedseatingconfigurationofmorethan19seatsunlessitisequippedwith— (a) protectivebreathingequipmenttoprotecttheeyes,nose

andmouthofeachflightcrewmemberwhileonflightdeck duty and to provide oxygen for a period of not less than15minutes;and

(b) sufficientportableprotectivebreathingequipment toprotecttheeyes,noseandmouthofallrequiredcabincrewmembersandtoprovidebreathinggasforaperiodofnotlessthan15minutes.

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(2)Theoxygensupplyforprotectivebreathingequipmentinanaircraftmaybeprovidedbytherequiredsupplementaloxygensystem. (3)Theprotectivebreathingequipmentintendedforflightcrewmember’suseshallbe— (a) convenientlylocatedontheflightdeck;and (b) easilyaccessibleforimmediateusebyeachrequired

flightcrewmemberattheirassigneddutystation. (4)Theprotectivebreathingequipmentintendedforcabincrewmember’suseshallbeinstalledadjacenttoeachrequiredcabincrew member duty station. (5) In any aeroplane, easily accessible portable protective breathing equipment shall be provided and located at or adjacentto the requiredhandfire extinguishers except that,where thefireextinguisher is locatedinsideacargocompartment, theprotectivebreathing equipment shall be stowed outside but adjacent to theentrancetothatcompartment. (6)Theprotectivebreathingequipmentinanaeroplaneshall,whileinuse,notpreventanyrequiredcommunication.

First-aid oxygen dispensing units 53. (1)Anairoperatorcertificateholder shallnotconductapassenger carrying operation in a pressurised aeroplane at altitudes above25,000feet,whenacabincrewmemberisrequiredtobecarried,unlesstheaeroplaneisequippedwith— (a) undiluted first-aid oxygen for passengers who, for

physiologicalreasons,mayrequireoxygenfollowingacabindepressurisation;and

(b) a sufficient number of oxygen dispensing units, butinnocaselessthantwo,withameansforcabincrewmemberstousethesupply.

(2)Theamountoffirst-aidoxygenrequiredforanoperationreferredtoinsubsection(1)(a)shallbedeterminedonthebasisof— (a) flight duration after cabin depressurisation at cabin

altitudesofmorethan8,000feet;

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(b) an averageflow rateof at least three litresStandardTemperaturePressureDryperminuteperperson;and

(c) atleast2%ofthepassengerscarried,butinnocaseforlessthanoneperson.

(3)Theamountoffirst-aidoxygenrequiredforanoperationreferredtoinsubsection(1)shallbedeterminedonthebasisofcabinpressurealtitudesandflightduration,consistentwiththeoperatingproceduresestablishedforeachoperationandroute. (4)Theoxygenequipmentreferredtoinsubsection(1)shallbecapableofgeneratingamassflowtoeachuserofatleastfourlitresper minute, Standard Temperature Pressure Dry and means may be providedtodecreasetheflowtonotlessthantwolitresperminutes,at a Standard Temperature Pressure Dry at any altitude.

Megaphones 54.(1)Anairoperatorcertificateholdershallequipanaeroplanewithaportablebattery-poweredmegaphoneormegaphonesreadilyaccessible to the crew members assigned to direct emergencyevacuation. (2)Thenumberandlocationofmegaphonesrequiredundersubsection(1)shallbedeterminedasfollows— (a) onaeroplaneswithaseatingcapacityofmorethan60

andlessthan100passengers,onemegaphoneshallbelocatedatthemostrearwardlocationinthepassengercabinwhereitwouldbereadilyaccessibletoanormalcabincrewmemberseat;

(b) onaeroplaneswithaseatingcapacityofmorethan99passengers,twomegaphonesinthepassengercabinoneachaeroplaneoneinstalledattheforwardendandtheotheratthemostrearwardlocationwhereitwouldbereadilyaccessibletoanormalcabincrewmemberseat;and

(c) foraeroplaneswithmorethanonepassengerdeck,inallcaseswhenthetotalpassengerseatingconfigurationofadeckismorethan60,atleastonemegaphoneisrequiredonthedeck.

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Individual flotation devices 55. (1) Land planes shall be equipped with one life-jacketor equivalent flotation device equipped with a means of electricilluminationforeachpersononboard,stowedinapositioneasilyaccessiblefromtheseatorberthofthepersonforwhoseuseit isprovided— (a) whenflyingen-routeoverwaterbeyondglidingdistance

fromtheshore; (b) whenflyingoverwateratadistanceofmorethan93

km(50NM)awayfromtheshoreforaircraftcapableofmaintainingsafealtitudeafterthefailureofoneenginefortwo-engineaircraftandthefailureoftwoenginesforthreeorfour-engineaircraft;or

(c) whentakingofforlandingatanaerodromewheretheStateof theOperatorhasdetermined the takeofforapproachpathissodisposedoverwaterthatintheeventofamishaptherewouldbealikelihoodofditching.

(2)Allseaplanesforallflightsshallbeequippedwith— (a) onelife-jacket,orequivalentindividualflotationdevice,

foreachpersononboard,stowedinapositioneasilyaccessiblefromtheseatorberthofthepersonforwhoseuseitisprovided;

(b) oneseaanchor(drogue); (c) equipmentformakingthesoundsignalsprescribedin

theInternationalRegulationsforPreventingCollisionsatSea,whereapplicable.

Life rafts 56.(1)Inadditiontotheequipmentspecifiedundersections55and57,thefollowingshallbeequippedwithlifesavingraftsinsufficientnumberstocarryallpersonsonboard— (a) aeroplanesoperatedonlongrangeover-waterflights; (b) allotheraeroplaneswhentheyareoperatedoverwater

away from land suitable for making an emergency landingatadistanceofmorethan185km(100NM)inthecaseofsingle-engineaeroplanes,andmorethan

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370km(200NM)inthecaseofmulti-engineaeroplanescapableofcontinuingflightwithoneengineinoperative;

(c) Class1and2helicopterswhentheyareoperatedoverwater at a distance from land corresponding to more than10minutesatnormalcruisespeed;and

(d) Class3helicopterswhentheyareoperatedoverwaterbeyond auto rotational or safe forced landing distance from land.

(2)Anaircraftshallbeequippedwithlifesavingraftswithasufficientcapacitytocarryallpersonsonboardintheeventofthelossofoneraftofthelargestcapacity. (3) All life saving rafts referred to under subsections (1) and (2)shallbestowedsoastofacilitatetheirreadyuseinanemergencyandshallbeequippedwiththefollowinglifesustainingequipment— (a) anelectricsurvivorlocatorlight; (b) asurvivalkit; (c) apyrotechnicsignallingdevice;and (d) an Emergency Locator Transmitter. (4)Inhelicopters,lifesavingraftswhicharenotdeployablebyremotecontrolandwhichhaveamassofmorethan40kgshallbeequippedwithameansofmechanicallyassisteddeployment.

Flotation device for helicopter ditching 57.A helicopter flying over water at a distance from landcorresponding tomore than10minutesatnormalcruisespeed inthecaseofperformanceClass1or2helicopter,orflyingoverwaterbeyond autorotational or safe forced landing distance from land in thecaseofperformanceClass3helicopter,shallbeequippedwithapermanentorrapidlydeployablemeansoffloatationsoastoensureasafeditchingofthehelicopter.

PART XImiscellaneous systems and equiPment

Seats, safety belts and shoulder harnesses 58.Anaircraftusedinpassengercarryingoperationsshallbeequippedwiththefollowingseats,safetybelts,andshoulderharnesses

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thatmeettheairworthinessrequirementsfortypecertificationofthataircraft— (a) aseatwithsafetybeltforeachpersononboardover

twoyearsofage;andarestrainingbeltforeachberthonboardtheaircraft;

(b) asafetyharnessforeachflightcrewmemberseat; (c) asafetyharnessforeachpilotseatwhich— (i) shallincorporateadevicewhichcanautomatically

restraintheoccupant’storsointheeventofrapiddeceleration;

(ii) includesshoulderstrapsandaseatbeltwithadeviceto prevent an incapacitated pilot from interfering withtheflightcontrols;

(d) aforwardorrearwardfacing(within15degreesofthelongitudinalaxisoftheaeroplane)seatequippedwithasafetyharnessforeachcabincrewmemberstationinthepassengercompartment;and

(e) thecabincrewmember’s seats shallbe locatednearfloor levelandotheremergencyexitsas requiredbytheAuthorityforemergencyevacuation.

Passenger and pilot compartment doors–aeroplanes 59.(1)Apersonshallnotoperateapassengercarryingaeroplaneofamaximumcertificatedtake-offmassinexcessof45000kgorwithapassengerseatingcapacitygreaterthan60unlessthataircraftisequippedwithanapprovedflightcrewcompartmentdoorthatisdesignedtoresistpenetrationbysmallarmsfireandgrenadeshrapnel,andtoresistforcibleintrusionsbyunauthorisedpersons. (2)Apersonshallnotoperateapassengercarryingaeroplanehavingacertificatedtakeoffmassoflessthan45000kgorwithapassengerseatingcapacityoflessthan60unlessthataircraftisequippedwithanapprovedflightcrewcompartmentdoor,wherepracticable,thatisdesignedtoresistpenetrationbysmallarmsfireandgrenadeshrapnel,andtoresistforcibleintrusionsbyunauthorisedpersons. (3)Apilotcompartmentdoorshallbecapableofbeinglockedandunlockedfromeitherpilot’sstation.

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(4)Anoperatorshallequipanaeroplanewithameansformonitoring from the pilot station the entire door area outside thepilot compartment to identify persons requesting entry and to detect suspiciousbehaviourorpotentialthreat. (5)Anoperatorshallequipanaeroplanewithapassengercompartmentdoordesignedtohave— (a) a means for a crew member, in an emergency, to unlock

eachdoorthatleadstoacompartmentthatisnormallyaccessible to passengers and that can be locked bypassengers;

(b) aplacardoneachdoorusedtoaccessarequiredpassengeremergencyexit,indicatingthatsuchdoorshallbeopenduringtake-offandlanding;and

(c) ameansreadilyavailableforeachcrewmembertounlockanydoorthatseparatesapassengercompartmentfromanothercompartmentthathasemergencyexitprovisions.

Passenger information signs 60.(1)Subjecttosubsection(2),apersonshallnotoperateapassengercarryingaeroplane,equippedwithsigns,withamaximumcertificatedtake-offweightof5700kgormoreunlessitisequippedwith— (a) at leastonepassenger informationsign (usingeither

lettersorsymbols)notifyingwhensmokingisprohibitedandonesign(usingeitherlettersorsymbols)notifyingwhensafetybeltsshouldbefastened,whichshall,whenilluminated, be legible to each person seated in thepassenger cabin under all probable conditions of cabin illumination;

(b) signswhichnotifywhensafetybeltsshouldbefastenedandwhensmokingisprohibitedshallbesoconstructedthatthecrewcanturnthemonandoff;and

(c) asignorplacardaffixedtoeachforwardbulkheadandeachpassengerseatbackthatreads“FastenSeatBeltWhileSeated”.

(2)Notwithstandingsubsection(1),apersonshallnotoperateanaircraftinwhichallpassengerseatsarenotvisiblefromtheflight

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deck,unlessitisequippedwithameansofindicatingtoallpassengersandcabincrewmemberswhenseatbeltsshallbefastenedandwhensmoking is not allowed.

Materials for cabin interiors, cargo and baggage compartments 61. (1) A person shall not operate an aircraft unless eachcompartmentusedbythecreworpassengersisequippedwiththefollowingrequirementsoftheStateofDesign— (a) materialsshallbeatleastflashresistant; (b) the wall and ceiling linings and the covering of

upholstering, floors and furnishings shall be flameresistant;

(c) each compartment where smoking is to be allowedshallbeequippedwithself-containedashtraysthatarecompletelyremovableandothercompartmentsshallbeplacardedagainstsmoking;and

(d) each receptacle for used towels, papers and wastesshallbeoffire-resistantmaterialandhaveacoverorothermeansofcontainingpossiblefiresstartedinthereceptacles.

(2)Acargocompartmentshallbeequippedwithceilingandsidewalllinerpanelswhichareconstructedofmaterialswhichmeetthetestrequirementsforflameresistanceofcargocompartmentlinersasspecifiedfortypecertification. (3)ForaircraftforwhichtheStateofDesignhasdevelopednewairworthinessrequirementsforcabininteriorssinceoriginaltypecertification,theowneroftheaircraftshallensurethatallmaterialsthatdonotmeetcurrentStateofDesignrequirementrefurbishingofthecabininteriorwithmaterialsthatcomplywithsubsections(1)and(2).

Power supply, distribution and indication system 62.(1)Anairoperatorcertificateholdershallnotoperateanaeroplaneunlessitisequippedwith— (a) a power supply and distribution system that meets

theairworthinessrequirementsforcertificationofan

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aeroplaneinthetransportcategory,asspecifiedbytheAuthority;

(b) a power supply and distribution system that is ableto produce and distribute the load for the requiredinstruments andequipment,withuseof an auxiliarypower supply if any one power source or component ofthepowerdistributionsystemfails;or

(c) ameansforindicatingtheadequacyofthepowerbeingsuppliedtorequiredflightinstruments.

(2)All engine-driven sourcesof energy,whenused, shallmake provision for back-up in emergencies.

Protective circuit fuses 63.Apersonshallnotoperateanaeroplaneinwhichprotectivefusesareinstalledunlesstherearesparefusesavailableofappropriateratingsforreplacementofthoseaccessibleinflight.

Icing protection equipment 64.(1)Apersonshallnotoperateanaircraftinexpectedoractualicingconditionsunlessitisequippedforthepreventionorremovaloficeonwindshields,wings,controlsurfaces,empennage,propellers,rotorblades,orotherpartsoftheaircraftwhereiceformationwilladverselyaffectthesafetyoftheaircraft. (2)A person shall not operate an aircraft in expected oractualicingconditionsatnightunlessitisequippedwithameanstoilluminateordetecttheformationofice. (3)Anyilluminationreferredtoundersubsection(2)shallbeofatypethatwillnotcauseglareorreflectionthatwouldhandicapcrewmembersintheperformanceoftheirduties.

Pitot heat and indication systems 65.(1)Apersonshallnotoperateanaircraftininstrumentflightconditionsunlessitisequippedwithapitotheatsystem. (2)An air operator certificate holder shall not operate anaeroplaneequippedwithaflightinstrumentpitotheatingsystemunlesstheaeroplaneisalsoequippedwithanoperablepitotheatindicationsystemthatcomplieswiththefollowingrequirements—

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(a) theindicationincorporatesanamberlightthatisinclearviewofaflightcrewmember;

(b) theindicationisdesignedtoalerttheflightcrewmembersif—

(i) thepitotheatingsystemisswitched“off”;and (ii) thepitotheatingsystemisswitched“on”andany

pitottubeheatingelementisinoperative;or (c) anintegratedflightcrewalertingsystemthatwillnotify

thecrewifthepitotsystemismalfunctioning.

Static pressure system 66.(1)Apersonshallnotoperateanaircraftunlessitisequippedwithastaticpressuresystemventedtotheoutsideatmosphericpressuresothattheywillbeleastaffectedbyairflowvariationormoistureorotherforeignmatter,andinstalledsoastobeairtightexceptforthevent. (2)ApersonshallnotoperateanaircraftinInstrumentFlightRulesorVisualFlightRulesatnightunlessitisequippedwithastaticpressuresystemventedtotheoutsideatmosphericpressuresothattheywillbeleastaffectedbyairflowvariationormoistureorotherforeignmatter,andinstalledsoastobeairtightexceptfortheventand a means of selecting an alternative source of static pressure. (3)Apersonshallnotoperateanaircraftunlessitisequippedwithtwoindependentstaticpressuresystems,ventedtotheoutsideatmosphericpressuresothattheywillbeleastaffectedbyairflowvariationormoistureorotherforeignmatter,andinstalledsoastobeairtightexceptforthevent.

Windshield wipers 67. An air operator certificate holder shall not operate anaeroplanewithamaximumcertifiedtake-offmassofmorethan5700kgunlessitisequippedateachpilotstationwithawindshieldwiperorequivalentmeans tomaintainaclearportionof thewindshieldduring precipitation.

Chart holder 68.ApersonshallnotoperateanaeroplaneincommercialairtransportoperationsundersinglepilotInstrumentFlightRulesorat

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nightunlesstheaeroplaneisequippedwithachartholderinstalledinaneasilyreadablepositionthatcanbeilluminatedfornightoperations.

Cosmic radiation detection equipment 69.(1)Apersonshallnotoperateanaeroplaneincommercialair transport operations in an aeroplane intended to be operated above 15000m(49000ft)unlessitisequippedwith— (a) aninstrumenttomeasureandindicatecontinuouslythe

dose rate of total cosmic radiation being received and thecumulativedoseoneachflight;or

(b) a system of on-board quarterly radiation sampling acceptabletotheAuthority.

Electronic flight bags 70.(1)Incaseswhereportableelectronicflightbagsareusedonboard,theoperatorshallensurethattheydonotaffecttheperformanceof the aeroplane systems, equipment or the ability to operate theaeroplane. (2)Incasesreferredtoinsubsection(1)above,theoperatorshall— (a) assess thesafetyriskassociatedwitheachelectronic

flightbagfunction; (b) establishanddocumenttheproceduresfortheuseof,

andtrainingrequirementsfor,thedevice; (c) ensure the electronic flight bag and its associated

installation hardware including interaction withaeroplanesystemsmeettheappropriateairworthinesscertificationrequirements;

(d) establishrequirementsforredundancyoftheinformation,containedinanddisplayedbytheelectronicflightbagfunction,whereapplicable;

(e) establishanddocumentproceduresforthemanagementof the electronic flight bag function including anydatabaseitmayuse;and

(f) establishanddocumenttheproceduresfortheuseof,andtrainingrequirementsfor,theelectronicflightbagandtheelectronicflightbagfunction.

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Offences and penalties 71.(1)Anypersonwhooperatesanaircraftwhichisnotfittedwiththeequipmentorinstrumentsrequiredundertheseregulationsshallbeguiltyofanoffenceandliabletoafinenotexceedinglevel14ortoimprisonmentforaperiodnotexceedingoneyearortobothsuchfineandsuchimprisonment. (2)Anypersonwho— (a) hindersorobstructsapersonauthorisedbytheAuthority

intheexerciseofhisorherpowersortheperformanceofhisorherduties;

(b) makesorcausestobemade,eitherorallyorinwriting— (i) any fraudulent, misleading or false statement for

the purpose of obtaining any rating, approval,authorisationorotherdocumentintermsoftheseregulations;

(ii) any fraudulent, misleading or false entry in any logbook,recordorreportwhichisrequiredtobekept,maintained,madeorusedtoshowcompliancewithanyprovisionoftheseregulations;

(c) falsifies, counterfeits, alters, defaces ormutilates, oraddsanythingto,anyrating,approval,authorisationorotherdocumentissuedintermsoftheseRegulations;or

(d) does or causes, or permits to be done or caused, any act contrarytotheseregulations;

(e) failstocomplywithanyprovisionoftheseregulations,oradirectiongivenoraprohibitionmadeoraconditionimposedintermsthereof;

shallbeguiltyofanoffenceandliabletoafinenotexceedinglevel8or to imprisonment for a period not exceeding one year. (3)Anycertificatedperson,aircraftoraviationorganisationwhich is foundguilty in termsof these regulationsmayhave thecertificatesuspended,revokedorcancelled.

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Appeals 72.Anypersonwhowishestoappealagainstanydecisionmadeintermsoftheseregulationsmayappealintermsofsection78oftheAct.

Repeal 73. (1) Part VIIoftheCivilAviation(AirNavigation)Regulations,2004,publishedinStatutoryInstrument151of2004,isrepealed. (2)Anycertificateissuedintermsoftheseregulationsshallcontinuetobevalid,subjecttotherepealedregulationsreferredtoinsubsection(1),asifthesamewasissuedintermsoftheseregulationsunlessotherwiserevokedorsuspended.

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first schedule (Sections 3(3), 10 (1))

CATEGORYII—INSTRUMENTSANDEQUIPMENTAPPROVALANDMAINTENANCEREQUIREMENTS

GENERAL Theinstrumentsandequipmentrequiredbysection10shallbeapprovedasprovidedinthisSchedulebeforebeingusedinCategoryIIoperations.Beforepresentinganaircraftforapprovaloftheinstrumentsandequipment,itmustbeshownthatsincethebeginningofthe12thcalendarmonthbeforethedateofsubmission— (a) theILSlocaliserandglideslopeequipmentwerebenchchecked

accordingtothemanufacturer’sinstructionsandfoundtomeetthosestandardsspecifiedinRTCAPaper23-63/DO-177datedMarch14,1963, “StandardsAdjustmentCriteria forAirborneLocaliser andGlideslopeReceivers.”;

(b) thealtimetersandthestaticpressuresystemsweretestedandinspected;and

(c) allotherinstrumentsanditemsofequipmentspecifiedinsection10thatarelistedintheproposedmaintenanceprogrammewerebenchcheckedandfoundtomeetthemanufacturer’sspecifications.

1. Flight control guidance system Allcomponentsoftheflightcontrolguidancesystemshallbeapprovedasinstalledbytheevaluationprogrammespecifiedinparagraph(e)iftheyhavenotbeen approved for Category III operations under applicable type or supplemental typecertificationprocedures.Inaddition,subsequentchangestomake,model,ordesignofthecomponentsmustbeapprovedunderthisparagraph.Relatedsystemsordevices, suchas theauto throttleandcomputedmissedapproachguidancesystem,shallbeapprovedinthesamemanneriftheyaretobeusedfor Category II operations.

2. Radio altimeter Aradioaltimetermustmeettheperformancecriteriaofthisparagraphfororiginalapprovalandaftereachsubsequentalteration— (a) itshalldisplaytotheflightcrewclearlyandpositivelythewheel

heightofthemainlandinggearabovetheterrain; (b) it shall displaywheel height above the terrain to an accuracy of

±5feetorfivepercent,whicheverisgreater,underthefollowingconditions—

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(i) pitchanglesofzeroto±50aboutthemeanapproachattitude; (ii) rollanglesofzeroto200ineitherdirection; (iii) forwardvelocities fromminimumapproachspeedup to200

knots;and (iv) sinkratesfromzeroto15feetpersecondataltitudesfrom100

to200feet; (c) over levelground, itmust track theactualaltitudeof theaircraft

withoutsignificantlagoroscillation; (d) withtheaircraftatanaltitudeof200feetorless,anyabruptchangein

terrainrepresentingnomorethan10percentoftheaircraft’saltitudemustnotcausethealtimetertounlock,andindicatorresponsetosuchchangesmustnotexceed0.1secondsand,inaddition,ifthesystemunlocksforgreaterchanges,itmustreacquirethesignalinlessthanonesecond;

(e) systemsthatcontainapushtotestfeaturemusttesttheentiresystem(withorwithoutanantenna)atasimulatedaltitudeoflessthan500feet;and

(f) thesystemmustprovidetotheflightcrewapositivefailurewarningdisplayanytimethereisalossofpoweroranabsenceofgroundreturnsignalswithinthedesignedrangeofoperatingaltitudes.

3. Other instruments and equipment Allotherinstrumentsanditemsofequipmentrequiredbysection10shallbecapable of performing as necessary for Category II operations. Approval is also requiredaftereachsubsequentalterationtotheseinstrumentsanditemsofequipment.4. Evaluation programme

(a) application: Approval by evaluation is requested as a part of theapplicationforapprovaloftheCategoryIImanual;

(b) demonstrations: UnlessotherwiseauthorisedbytheAuthority,the evaluation programme for each aircraft requires thedemonstrationsspecifiedinthisparagraph.Atleast50ILSapproachesshallbeflownwithatleastfiveapproachesoneachofthreedifferentILSfacilitiesandnomorethanonehalfofthetotalapproachesonanyoneILSfacility.Allapproachesshall be flown under simulated instrument conditions to a30m(100foot)decisionheightand90percentofthetotalapproachesmadeshallbesuccessful.Asuccessfulapproachisoneinwhich—

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(i) atthe30m(100foot)decisionheight,theindicatedairspeedandheadingaresatisfactoryforanormalflareandlanding(speedmust be ±5 knots of programmed airspeed, but may not be less thancomputedthresholdspeedifautothrottlesareused);

(ii) theaircraftatthe30m(100foot)decisionheight,ispositionedsothatthecockpitiswithin,andtrackingsoastoremainwithin,thelateralconfinesoftherunwayextended;

(iii) deviationfromglideslopeafterleavingtheoutermarkerdoesnotexceed50percentoffull-scaledeflectionasdisplayedontheILSindicator;

(iv) nounusualroughnessorexcessiveattitudechangesoccurafterleavingthemiddlemarker;and

(v) inthecaseofanaircraftequippedwithanapproachcoupler,theaircraftissufficientlyintrimwhentheapproachcouplerisdisconnectedatthedecisionheighttoallowforthecontinuationofanormalapproachandlanding;

(c) records: DuringtheevaluationprogrammethefollowinginformationshallbemaintainedbytheapplicantfortheaircraftwithrespecttoeachapproachandmadeavailabletotheAuthorityuponrequest—

(i) each deficiency in airborne instruments and equipment thatpreventedtheinitiationofanapproach;

(ii) thereasonsfordiscontinuinganapproach,includingthealtitudeabovetherunwayatwhichitwasdiscontinued;

(iii) speedcontrolatthe30m(100foot)DHifautothrottlesareused; (iv) trimconditionoftheaircraftupondisconnectingtheautocoupler

withrespecttocontinuationtoflareandlanding; (v) positionoftheaircraftatthemiddlemarkerandatthedecision

heightindicatedbothonadiagramofthebasicILSdisplayandadiagramoftherunwayextendedtothemiddlemarker.Estimatedtouchdownpointshallbeindicatedontherunwaydiagram;

(vi) compatibilityofflightdirectorwiththeautocoupler,ifapplicable;and

(vii) quality of overall system performance.

(d) evaluation: Afinalevaluationoftheflightcontrolguidancesystemismadeuponsuccessfulcompletionof thedemonstrations. Ifnohazardoustendencieshavebeendisplayedorareotherwiseknowntoexist,thesystemisapprovedasinstalled.

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Each maintenance programme for Category II instruments andequipmentshallcontainthefollowing—

(i) a list of each instrument and itemof equipment specified inregulation10thatisinstalledintheaircraftandapprovedforCategoryIIoperations,includingthemakeandmodelofthosespecifiedinsection10(2);

(ii) aschedulethatprovidesfortheperformanceofinspectionsundersubparagraph(5)ofthisparagraphwithin3calendarmonthsafterthedateofthepreviousinspection.

TheinspectionshallbeperformedbyapersonauthorisedundertheCivilAviation(Airworthiness)Regulations,exceptthateachalternateinspectionmaybereplacedbyafunctionalflightcheck.ThisfunctionalflightcheckshallbeperformedbyapilotholdingaCategoryIIpilotauthorisationforthetypeaircraftchecked;

(iii) aschedulethatprovidesfortheperformanceofbenchchecksforeachlistedinstrumentanditemofequipmentthatisspecifiedinsection10(2)within12calendarmonthsafterthedateofthepreviousbenchcheck;

(iv) aschedulethatprovidesfortheperformanceofatestandinspec-tionofeachstaticpressuresystemwithin12calendarmonthsafterthedateoftheprevioustestandinspection;

(v) theproceduresfortheperformanceoftheperiodicinspectionsand functionalflight checks todetermine the abilityof eachlistedinstrumentanditemofequipmentspecifiedinsection10(2) to perform as approved for Category II operations including aprocedureforrecordingfunctionalflightchecks;

(vi) aprocedureforassuringthatthepilotisinformedofalldefectsinlistedinstrumentsanditemsofequipment;

(vii) aprocedureforassuringthattheconditionofeachlistedinstrumentanditemofequipmentuponwhichmaintenanceisperformedis at least equal to its Category II approval condition before it isreturnedtoserviceforCategoryIIoperations;and

(viii) procedureforanentryinthemaintenancerecordsthatshowsthedate,airport,andreasonsforeachdiscontinuedCategoryII operation because of a malfunction of a listed instrument or item of equipment.

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(e) Bench check: (1)A bench check required by this section shall comply

with thisparagraph.Except as specified in (2)of thisparagraph,itshallbeperformedbyacertificatedrepairstationholdingoneofthe following ratings as appropriate to the equipment checked—

(i) aninstrumentrating;and (ii) an avionics rating. (2)Itshallbeperformedbyacertificatedairoperatoronaircraft

identifiedinitsapprovedOperationsSpecificationswiththeapprovedauthorisations to performmaintenance and approve for return toservice its own aircraft maintained under a continuous maintenance programmeunderanequivalentsystemidentifiedinCivilAviation(AirOperatorCertificationandAdministration)Regulations.

(3) It shallconsistof removalofan instrumentor itemofequipmentandperformanceofthefollowing—

(i) a visual inspection for cleanliness, impending failure, andtheneedforlubrication,repair,orreplacementofparts;

(ii) correctionofitemsfoundbythatvisualinspection;and (iii) calibrationtoatleastthemanufacturer’sspecifications

unlessotherwisespecifiedintheapprovedCategoryIImanualfortheaircraftinwhichtheinstrumentoritemof equipment is installed.

Extensions After the completion of one maintenance cycle of 12 calendarmonths,arequesttoextendtheperiodforchecks,tests,andinspectionsisapprovedifitisshownthattheperformanceofparticularequipmentjustifiestherequestedextension.

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second schedule (section 37(8)

HELICOPTEREQUIPMENTREQUIREMENTS Ahelicoptershallbeequippedwithemergencyexitequipmentasfollows: (a) TypeIexit—thistypeshallhavearectangularopeningofnotless

than24incheswideby48incheshigh,withcornerradiinotgreaterthanone-thirdthewidthoftheexit,inthepassengerareainthesideofthefuselageatfloorlevelandasfarawayaspracticablefromareasthatmightbecomepotentialfirehazardsinacrash;

(b) TypeIIexit—thistypeisthesameasTypeIexceptthattheopeningshallbeatleast20incheswideby44incheshigh;

(c) TypeIIIexit—thistypeisthesameasTypeIexceptthattheopeningshallbeatleast20incheswideby36incheshighandtheexitneednotbeatfloorlevel;and

(d) TypeIVexit—thistypeshallhavearectangularopeningofnotlessthan19incheswideby26incheshigh,withcornerradiinotgreaterthanone-thirdthewidthoftheexit,inthesideofthefuselagewithastep-upinsidetherotorcraftofnotmorethan29inches.

Emergencyexitsshallbeaccessibletoallpassengersandshallbeinaccordancewiththefollowingtable—

Passenger seating capacityEmergencyexitsforeachsideofthefuselage

Type I Type II Type III Type IV1through10 111through19 1 or 220through39 1 140through59 1 160through79 1 1 or 2

third schedule (Section 40)

MAIN PASSENGER AISLE WIDTH Themainpassengeraislewidthshallbeasfollows:

Passenger seating capacityMinimummainpassengeraislewidth

Lessthan25inchesfromfloor(inches)

25 inches andmorefromfloor(inches)

10 or less 12 1511through19 12 2020 or more 15 20

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fourth schedule (Section 44(3)(e)

MINIMUMNUMBEROFPORTABLEFIREEXTINGUISHERS Theminimumnumberofportablefireextinguishersinapassengercarryingaircraftshallbeasfollows:

MinimumNumberofHandHeldFireExtinguishersPassengerSeatingCapacity7through29 130through60 261through200 3201through300 4301through400 5401through500 6501through600 7601 or more 8

fifth schedule (Section 48)

MARKINGOFBREAKINPOINTS

Fifth Schedule (section 48)MarkingofBreakinPoints

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sixth schedule (Section 34(3)(e)

FLIGHT DATA RECORDERS(a) Types of flight data recorders:

1.TypesIandIAFDRsshallrecordtheparametersrequiredtodetermineaccurately: (i) Theaeroplaneflightpath. (ii) Speed. (iii) Altitude. (iv) Engine power. (v) Configurationandoperation. 2.TheparametersthatsatisfytherequirementsforaTypeIFDRarecontainedin Table A below. 3.TheparametersthatsatisfytherequirementsforaTypeIAFDRarelistedbelow.Theparameterswithoutanasterisk(*)aremandatoryparametersthatshallberecorded.Theparametersdesignatedbyanasterisk(*)shallalsoberecordedif an information data source for an asterisked parameter is used by aeroplane systemsortheflightcrewtooperatetheaeroplane. (i) Thefollowingparameterssatisfytherequirementsforflightpathand

speed: A. Pressure altitude. B. Indicatedorcalibratedairspeed. C. Air-groundstatusandeachlandinggearair-groundsensorwhen

practicable. D. Total or outside air temperature. E. Heading(primaryflightcrewreference). F. Normal acceleration. G. Lateral acceleration. H. Longitudinal acceleration (body axis). I. Time or relative time count. J. Navigationdata*:driftangle,windspeed,winddirection,latitude/

longitude. K. Groundspeed*. L. Radioaltitude*. (ii) Thefollowingparameterssatisfytherequirementsforaltitude:

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A. Pitchattitude. B. Rollattitude. C. Yaworsideslipangle*. D. Angleofattack*. (iii) Thefollowingparameterssatisfytherequirementsforenginepower: A. Enginethrustpower:propulsivethrust/poweroneachengine,

cockpitthrust/powerleverposition. B. Thrustreversestatus*. C. Enginethrustcommand*. D. Enginethrusttarget*. E. Enginebleedvalveposition*. F. Additionalengineparameters*:EPR,N1,indicatedvibration

level,N2,EGT,TLA,fuelflow,fuelcut-offleverposition,N3. (iv) Thefollowingparameterssatisfytherequirementsforconfiguration: A. Pitchtrimsurfaceposition. B. Flaps*:trailingedgeflapposition,cockpitcontrolselection. C. Slats*:leadingedgeflap(slat)position,cockpitcontrolselection. D. LandingGear*:landinggear,gearselectorposition. E. Yawtrimsurfaceposition*. F. Rolltrimsurfaceposition*. G. Cockpittrimcontrolinputpositionpitch*. H. Cockpittrimcontrolinputpositionroll*. I. Cockpittrimcontrolinputpositionyaw*. J. Groundspoilerandspeedbrake*:Groundspoilerposition,ground

spoiler selection, speed brake position, speed brake selection. K. De-icingand/oranti-icingsystemsselection*. L. Hydraulicpressure(eachsystem)*. M. Fuelquantity*. N. ACelectricalbusstatus*. O. DCelectricalbusstatus*. P. APUbleedvalveposition*. Q. Computedcentreofgravity*. (v) Thefollowingparameterssatisfytherequirementsforoperation:

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A. Warnings. B. Primaryflightcontrolsurfaceandprimaryflightcontrolpilot

input:pitchaxis,rollaxis,yawaxis. C. Marker beacon passage. D. Eachnavigationreceiverfrequencyselection. E. ManualradiotransmissionkeyingandCVR/FDRsynchronisation

reference. F. Autopilot/autothrottle/AFCSmodeandengagementstatus*. G. Selectedbarometricsetting*:pilotfirstofficer(co-pilot). H. Selectedaltitude(allpilotselectablemodesofoperation)*. I. Selectedspeed(allpilotselectablemodesofoperation)*. J. SelectedMACH(allpilotselectablemodesofoperation)*. K. Selectedverticalspeed(allpilotselectablemodesofoperation)*. L. Selectedheading(allpilotselectablemodesofoperation)*. M. Selectedflightpath(allpilotselectablemodesofoperation)*;

course/DSTRK,pathangle. N. Selecteddecisionheight*. O. EFISdisplayformat*:pilot,firstofficer(co-pilot). P. Multifunction/engine/alertsdisplayformat*. Q. GPWS/TAWS/GCASstatus*:selectionofterraindisplaymode

includingpop-updisplaystatus,terrainalerts,bothcautionsandwarning,andadvisories,on/offswitchposition.

R. Lowpressurewarning*:hydraulicpressure,pneumaticpressure. S. Computerfailure*. T. Lossofcabinpressure*. U. TCAS/ACAS (traffic alert and collision avoidance system/

airbornecollisionavoidancesystem)*. V. Icedetection*. W. Enginewarningeachenginevibration*. X. Enginewarningeachengineovertemperature*. Y. Enginewarningeachengineoilpressurelow*. Z. Enginewarningeachengineoverspeed*. AA.Windshearwarning*. BB. Operationalstallprotection,stickshakerandpusheractivation*.

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CC. Allcockpitflightcontrolforces*:controlwheel,controlcolumn,rudder pedal cockpit input forces.

DD. Vertical deviation*: ILS glide path, MLS elevation, GNSSapproachpath.

EE. Horizontaldeviation*:ILSlocaliser,MLSazimuth,GNSSap-proachpath.

FF. DME1and2distances*. GG. Primarynavigationsystemreference*:GNSS,INS,VOR/DME,

MLS, Loran C, ILS. HH. Brakes*:leftandrightbrakepressure,leftandrightbrakepedal

position. II. Date*. JJ. Eventmarker*. KK. Headupdisplayinuse*. LL. Paravisualdisplayon*. Note: Parameter requirements, including range, sampling, accuracy and resolution, as contained in the Minimum Operational Performance Specification (MOPS) document for Flight Recorder Systems of the European Organisation for Civil Aviation Equipment (EUROCAE) or equivalent documents.

Note:Thenumberofparameterstoberecordedwilldependonaeroplanecomplexity.arameterswithoutan(*)aretoberecordedregardlessofaeroplanecomplexity.Those parameters designated by an (*) are to be recorded if aninformation source for the parameter is used by aeroplane systems and/orflightcrewtooperatetheaeroplane. 4. TypesIIandIIAFDRsshallrecordtheparametersspecifiedinparagraph(a)(1)(i)through(iv)ofthissection,andthoseparametersrequiredtoaccuratelydeterminetheconfigurationofliftanddragdevices: 5.TheparametersthatsatisfytherequirementsforaTypeIIandTypeIIAFDR are contained in Table A below. Note: The differences between Type II and Type IIA parameters is the duration of the recording. Type II has a duration of 25 hours and Type IIA has a duration of 30 minutes.

6. TypeIVFDRsshallrecordtheparametersrequiredtodetermineaccurately: (i) Thehelicopterflightpath. (ii) Speed. (iii) Altitude.

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(iv) Engine power and operation. 7.The parameters that satisfy the requirements for aType IVFDR arecontainedinTableBbelow. 8.TypeIVAFDRsshallrecordtheparametersspecifiedinparagraph(a)(6)ofthissection,andtheparameterrequiredtoaccuratelydetermineconfiguration. 9. TheparametersthatsatisfytherequirementsforaTypeIVAFDRarelistedbelow.Theparameterswithoutanasterisk(*)aremandatoryparametersthatshallberecorded.Theparametersdesignatedbyanasterisk(*)shallalsobe recorded if an information data source for an asterisked parameter is used by aeroplanesystemsortheflightcrewtooperatethehelicopter. (i) Thefollowingparameterssatisfytherequirementsforflightpathand

speed: A. Pressure altitude. B. Indicatedairspeed. C. Total or outside air temperature. D. Heading(primaryflightcrewreference). E. Normal acceleration. F. Lateral acceleration. G. Longitudinal acceleration (body axis). H. Time or relative time count. I. Navigationdata*:driftangle,windspeed,winddirection,latitude/

longitude. J. Radioaltitude*. (ii) Thefollowingparameterssatisfytherequirementsforattitude: A. Pitchattitude. B. Rollattitude. C. Yawrate. (iii) Thefollowingparameterssatisfytherequirementsforenginepower: A. Poweroneachengine:freepowerturbinespeed(Nf), engine torque,

engine gas generator speed (Ng), cockpit power control position. B. Rotor:mainrotorspeed,rotorbrake. C. Maingearboxoilpressure*. D. Gearboxoiltemperature*,maingearboxoiltemperature,tailrotor

gearbox oil temperature. E. Engineexhaustgastemperature(T4)*. F. Turbineinlettemperature(TIT)*.

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(iv) Thefollowingparameterssatisfytherequirementsforconfiguration: A. Landinggearorgearselectorposition*. B. Fuelquality*. C. Icedetectorliquidwatercontent*. (v) Thefollowingparameterssatisfytherequirementsforoperation: A. Hydraulics low pressure. B. Warnings. C. Primaryflightcontrols—pilotinputand/orcontroloutputposition:

collectivepitch,longitudinalcyclicpitch,lateralcyclicpitch,tailrotorpetal,controllablestabilator,hydraulicselection.

D. Marker beacon passage. E. Eachnavigationreceiverfrequencyselection. F. AFCSmodeandengagementstatus*. G. Stabilityaugmentationsystemengagement*. H. Indicatedslingloadforce*. I. Verticaldeviation*:ILSglidepath,GNSSapproachpath. J. Horizontaldeviation*:ILSlocaliser,GNSSapproachpath. K. DME1and2distances*. L. Altituderate*. M. Icedetectorliquidwatercontent*. N. Helicopterhealthandusagemonitorsystem(HUMUS)*:engine

data,chipdetectors,tracktiming,exceedancediscretes,broadbandaverage engine vibration.

Note: Parameter requirements, including range, sampling, accuracy and resolution, as contained in the Minimum Operational Performance Specification (MOPS) document for Flight Recorder Systems of the European Organisation for Civil Aviation Equipment (EUROCAE) or equivalent documents.

Note: The number of parameters to be recorded will depend on helicopter complexity. Parameters without an (*) are to be recorded regardless of helicopter complexity. Those parameters designated by an (*) are to be recorded if an information source for the parameter is used by helicopter systems and/or flightcrew to operate the helicopter.

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10.TypeVFDRsshallrecordtheparametersspecifiedinparagraph(a)(6)(i)through(iii)ofthissection,andtheparameterrequiredtoaccuratelydetermineengine power. TheparametersthatsatisfytherequirementsforaTypeVFDRarecontainedinTableBbelow.

Table A—Aeroplanes ParametersforFlightDataRecorders

Serial number Parameter

Measurement range

Recording interval

(seconds)

Accuracy limits (sensor input compared to FDR

read-out)1 Time(UTCwhen

available,otherwiseelapsed time)

24hours 4 +/-0.125%perhour

2 Pressure-altitude– -300 m (-1 000 ft) to maximum certificatedaltitudeof aircraft 1 500 m (5000ft)

1 +/-30mto+/-200m(+/-100ftto+/-700ft)

3 Indicated airspeed 95 km/h (50 kt) tomax 1VSo(Note 1) VSo to 1.2 VD (Note 2)

1 +/-5%

+/-3%

4 Heading 360 degrees 1 +/-2%5 Normal acceleration– -3gto+6g 0.125 +/-1%ofmaximumrange

excluding datum error of +/-5%

6 Pitchattitude +/-75degrees 1 +/-2degrees7 Roll attitude +/-180degrees 1 +/-2degrees8 Radio transmission

keyingO n - o f f ( o n e discrete)

1

9 Poweroneachengine(Note 3)

Full range 1 (per engine)

+/-2%

10 Trailingedgeflapor cockpit control selection

Fullrangeoreachdiscrete position

2 +/-5%oraspilot’sindicator

11 Leadingedgeflapor cockpit control selection

Fullrangeoreachdiscrete position

2 +/-5%oraspilot’sindicator

12 Thrustreverserposition

Stowed, in transit, and Reverse

1 (per engine)

13 Groundspoiler/speedbrake selection

Full range or eachdiscrete position

1 +/-2%unlesshigheraccuracy uniquely

required14 Outside air

temperatureSensor range 2 +/-2degreesC

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Measurement range

Recording interval

(seconds)


read-out)15 Autopilot/auto

throttle/AFCSmodeand engagement status

A suitable combination of Discretes

1

Note—The preceding 15 parameters satisfy the requirements for a Type II FDR.16 Longitudinal

acceleration+/-1g 0.25 +/-1.5%maxrange


17 Lateral acceleration +/-1g 0.25 +/-1.5%maxrangeexcluding datum error of

+/-5%18 P i l o t i npu t and /

or control surface p o s i t i o n - p r i m a r y controls (pitch, roll,yaw) (Note 4)

Full range 1 +/-2degreesunlesshigheraccuracyuniquely

required

19 Pitchtrimposition Full range 1 +/-3%unlesshigheraccuracy uniquely

required 20 Radio altitude– -6 m to 750 m (–20

ft to 2 500 ft)1 +/-0.6m(+/-2ft)or+/-3%

whicheverisgreaterbelow150m(500ft)and+/-5%

above 150 m (500 ft) 21 Glidepathdeviation Signal range 1 +/-3%22 Localiser deviation Signal range 1 +/-3%23 Marker beacon

passageDiscrete 1

24 Master warning Discrete 125 NAV 1 and 2

frequency selection (Note 5)

Full range 4 As installed

26 DME 1 and 2 distance (Notes 5 and 6)

0–370 km 4 As installed

27 Landing gear squat switchstatus

Discrete 1

28 GPWS (ground proximity warning system)

Discrete 1

29 Angle of attack Full range 0.5 As installed30 Hydraulics,each

system (low pressure)

Discrete 2 As installed

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Measurement range

Recording interval

(seconds)


read-out)31 Navigation data

(latitude/longitude,ground speed and drift angle) (Note 7)

As installed 1 As installed

32 Landing gear or gear selector position


Note—The preceding 32 parameters satisfy the requirements for a Type I FDR.Notes—

1. VSostallingspeedorminimumsteadyflightspeedinthelandingconfiguration.2. VD design diving speed.3. Recordsufficientinputstodeterminepower.4. Foraeroplaneswithconventionalcontrolsystems‘‘or’’applies.Foraeroplaneswithnon-

mechanicalcontrolsystems‘‘and’’applies.Inaeroplaneswithsplitsurfaces,asuitablecombinationofinputsisacceptableinlieuofrecordingeachsurfaceseparately.

5. If signal available in digital form.6. RecordingoflatitudeandlongitudefromINSorothernavigationsystemisapreferred

alternative.7. If signals readily available.

Iffurtherrecordingcapacityisavailable,recordingofthefollowingadditionalinformationshouldbe considered:(a) operationalinformationfromelectronicdisplaysystems,suchaselectronicflightinstrument

systems (EFIS), electronic centralised aircraft monitor (ECAM) and engine indication and crew alertingsystem(EICAS).Usethefollowingorderofpriority:

(1) parametersselectedbytheflightcrewrelatingtothedesiredflightpath,e.g.barometricpressuresetting,selectedaltitude,selectedairspeed,decisionheight,andautoflightsystemengagementandmodeindicationsifnotrecordedfromanothersource;

(2) displaysystemselection/status,e.g.SECTOR,PLAN,ROSE,NAV,WXR,COMPOSITE,COPY,ETC.;

(3) warningsandalerts; (4) theidentityofdisplayedpagesforemergencyproceduresandchecklists;(b) retardation information includingbrake application for use in the investigation of landing

overrunsandrejectedtake-offs;and(c) additionalengineparameters(EPR,N1,EGT,fuelflow,etc.).

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Measurement range

Recording interval

(seconds)


read-out)1 Time(UTCwhen

available,otherwiseelapsed time)

24hours 4 +/-0.125%perhour

2 Pressure-altitude– -300 m (–1 000 ft) to maximum certificatedaltitudeofaircraft+1500m(+5000ft)

1 +/-30mto+/-200m(+/-100ftto+/-700ft)

3 Indicated airspeed As the instal ledmeasuring system

1 +/-3%

4 Heading 360 degrees 1 +/-2degrees

5 Normal acceleration– -3gto+6g 0.125 +/-1%

6 Pitchattitude +/-75degrees 0.5 +/-2degrees7 Roll attitude +/-180degrees 0.5 +/-2degrees8 Radio transmission

keyingOn-off (one discrete)

1

9 Poweroneachengine (Note 1)

Full range 1 (per engine)

+/-2%

10 Main rotor speed 50-130% 0.5 +/-2%11 Pilotinputand/

or control surface position-primary controls (Collective pitch,longitudinalcyclicpitch,lateralcyclicpitch,tailrotorpedal) (Note 2)

Full range 1 +/-2%unlesshigheraccuracy uniquely

required.

12 Hydraulics,eachsystem (low pressure)

Discrete 2

13 Outside air temperature

Sensor range 2 +/-2degreesC

14 Autopilot/autothrottle/AFCSmodeand engagement status

A suitable combination of Discretes

1

15 Stability augmentation system engagement

Discrete 1

. Note: The preceding 15 parameters satisfy the requirements for a Type V FDR16 Main gearbox oil

pressureAs installed 1 As installed

17 Main gearbox oil temperature


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Measurement range

Recording interval

(seconds)


read-out)18 Yawacceleration(or

yaw rate)+/-1g 0.25 +/-1.5%maxrange


19 Sling load force 0-200%ofcertifiedload

0.5 +/-3%ofmaxrange

20 Longitudinal acceleration

+/-1g 0.25 +/-1.5%maxrangeexcluding datum error of

+/-5%21 Lateral acceleration +/-1g 0.25 +/-1.5%maxrange


22 Radio altitude– -6 m to 750 m (–20 ft to 2 500 ft)

1 +/-0.6m(+/-2ft)or+/-3%whicheverisgreaterbelow

150 m (500ft)and+/-5%above

150 m (500 ft)23 Glidepathdeviation Signal range 1 +/-3%24 Localiser deviation Signal range 1 +/-3%25 Marker beacon

passageDiscrete 1

26 Master warning Discrete 127 NAV 1 and 2

frequency selection (Note 3)

Full range 4 As installed

28 DME 1 and 2 distance (Notes 3 and 4)

0-370 km 4 As installed

29 Navigation data (latitude/longitude,ground speed) (Note 5)


30 Landing gear or gear selector position


Note: The preceding 30 parameters satisfy the requirements for a Type IV FDR.Notes—

1. Recordsufficientinputstodeterminepower.2. Forhelicopterswith conventional control systems ‘‘or’’ applies. For helicopterswith

non-mechanicalcontrolsystems‘‘and’’applies.3. If signal available in digital form.4. RecordingoflatitudeandlongitudefromINSorothernavigationsystemisapreferred

alternative.

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Measurement range

Recording interval

(seconds)


read-out)5. If signals readily available.

Iffurtherrecordingcapacityisavailable,recordingofthefollowingadditionalinformationshouldbe considered:

(a) operationalinformationfromelectronicdisplaysystems,suchaselectronicflightinstrumentsystems (EFIS), electronic centralised aircraft monitor (ECAM) and engine indication and crew alertingsystem(EICAS).Usethefollowingorderofpriority:

(1) parametersselectedbytheflightcrewrelatingtothedesiredflightpath,e.g.barometricpressure setting, selected altitude, selected airspeed, decisionheight, and autoflightsystemengagementandmodeindicationsifnotrecordedfromanothersource;

(2) displaysystemselection/status,e.g.SECTOR,PLAN,ROSE,NAV,WXR,COMPOSITE,COPY,etc.;

(3) warningsandalertsdata;and (4) theidentityofdisplayedpagesforemergencyproceduresandchecklists;and(b) additionalengineparameters(EPR,N1,EGT,fuelflow,etc.).

seventh schedule (Section 43(5))

EMERGENCYLOCATORTRANSMITTER

(a) Types of emergency locator transmitters (1)ItisanICAOrecommendationthatallEmergencyLocatorTransmittersshouldbeautomatic. (2)TheEmergencyLocatorTransmitterequipmentrequiredshallmeettheminimumperformancestandarddefinedinFederalAviationAdministration’sTechnicalStandardOrderC91aorTechnicalStandardOrderC126providedthat— (a) anyEmergencyLocatorTransmitterinstalledpriorto1January1997

may meet the minimum performance standard defined in FederalAviationAdministration’sTechnicalStandardOrderC90until suchtimeasitbecomesunserviceableotherthanthroughtheneedforroutinemaintenance;and

(b) that the Emergency Locator Transmitter shall not be fitted with alithium-sulphurdioxidebatterythatdoesnotmeet therequirementsofFederalAviationAdministration’sTechnicalStandardOrderC97.

(3)ThefollowingaretypesofEmergencyLocatorTransmittersareinuse— (a) Automatic Fixed—Emergency Locator Transmitter (AF) (i) This typeofEmergencyLocatorTransmitter is intended to be

permanentlyattachedtotheaircraftbeforeandafteracrashandisdesignedtoaidsearchandrescueteamsinlocatingacrashsite.

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(ii) Automatic Portable—Emergency Locator Transmitter (AP). (iii) This typeofEmergencyLocatorTransmitter is intended to be

rigidlyattachedtotheaircraftbeforeacrash,butreadilyremovablefromtheaircraftafteracrash.ItfunctionsasanEmergencyLocatorTransmitterduringthecrashsequence.IftheEmergencyLocatorTransmitter does not employ an integral antenna, the aircraft-mounted antenna may be disconnected and an auxiliary antenna (storedontheEmergencyLocatorTransmittercase)attachedtotheEmergencyLocatorTransmitter.TheEmergencyLocatorTransmittercanbetetheredtoasurvivororaliferaft.ThistypeofEmergencyLocatorTransmitterisintendedtoaidsearchandrescueteamsinlocatingthecrashsiteorsurvivor/s.

(iv) Automatic Deployable—Emergency Locator Transmitter (AD). (v) This typeofEmergencyLocatorTransmitter is intended to be

rigidlyattachedtotheaircraftbeforethecrashandautomaticallyejectedanddeployedafterthecrashsensorhasdeterminedthatacrashhasoccurred.ThistypeofEmergencyLocatorTransmittershouldfloatinwaterandisintendedtoaidsearchandrescueteamsinlocatingthecrashsite.

(vi) Portable—Emergency Locator Transmitter (P). (vii) ThistypeofEmergencyLocatorTransmitterisnotintendedtobe

rigidlyattachedtotheaircraftbeforeacrash,butcarriedinsuchawaythatitisreadilyremovablefromtheaircraftafteracrash.TheEmergency Locator Transmitter employs an integral antenna, and canbetetheredtoasurvivororaliferaft.ThistypeofEmergencyLocatorTransmitterisintendedtoaidsearchandrescueteamsinlocatingthecrashsiteorsurvivor/s.

(viii) Emergency Locator Transmitter (S) or (W)—Emergency Locator Transmitter (survival) or Emergency Locator Transmitter (water-activated).

(ix) ThistypeofEmergencyLocatorTransmitterisnotaffixedtotheaircraftandtransmitsautomaticallywhenimmersedinwater.Itiswaterproof,floatsandoperatesonthesurfaceofthewater.Ithasnofixedmounting.Itshouldbetetheredtosurvivorsorliferafts.

(b) SpecificationInformation on technical characteristics and operational performance of121,5MHz.EmergencyLocatorTransmittersiscontainedinRadioTechnicalCommission on Aeronautics (RTCA) Document DO-183 and European Organisation for Civil Aviation Equipment (EUROCAE) ED.62.

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(1) Specification for the 121.5MHz component of Emergency LocatorTransmitterforsearchandrescue— (i) theEmergencyLocatorTransmittershalloperateon121,5MHz.The

frequencytoleranceshallnotexceedplusorminus0,005%; (ii) theemissionfromanEmergencyLocatorTransmitterundernormal

conditionsandattitudesoftheantennashallbeverticallypolarisedandessentiallyomni-directionalinthehorizontalplane;

(iii) overaperiodof48hoursofcontinuousoperation,atanoperatingtemperatureofminus200Celsius,thepeakeffectiveradiatedpower(PERP)shallatnotimebelessthan50mW;

(iv) thetypeofemissionshallbeA3X.Anyothertypeofmodulationthatmeetstherequirementsofsubparagraphs(e),(f)and(g)belowmaybeused,providedthatitwillnotprejudicepreciselocationofthebeaconbyhomingequipment;

Note—someEmergencyLocatorTransmittersareequippedwithanoptionalvoicecapability(A3E)inadditiontotheA3Xemission.

(v) thecarriershallbeamplitudemodulatedatamodulationfactorofatleast0,85;

(vi) themodulationappliedtothecarriershallhaveaminimumdutycycleof33%;

(vii) theemissionshallhavedistinctiveaudiocharacteristicsachievedbyamplitudemodulatingthecarrierwithanaudiofrequencysweepingdownwardoverarangeofnotlessthan700Hzwithintherange1600Hzto300Hzandwithasweeprepetitionrateofbetween2Hzand4Hz;and

(viii) theemissionshallincludeaclearlydefinedcarrierfrequencydistinctfromthemodulationsidebandcomponents.Inparticular,atleast30%of thepowershallbecontainedatall timeswithinplusorminus30Hzofthecarrierfrequencyon121,5MHz.

(2) Specification for the 406 MHz component of Emergency LocatorTransmitterforsearchandrescue— (i) transmissioncharacteristicsforEmergencyLocatorTransmitters

operating on 406 MHz are contained in ITU (InternationalTelecommunicationsUnion)M633/1;

(ii) informationontechnicalcharacteristicsandoperationalperformanceof406MHzEmergencyLocatorTransmittersiscontainedinRTCADocumentDO-204andEUROCAEDocumentED.62;

(iii) EmergencyLocatorTransmittersshalloperateonafrequencyof406,025MHzplusorminus2kHz.Thetransmittedfrequencyshall

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notvarymorethanplusorminus5kHzinfiveyearsincludingtheinitialfrequencyoffset.Itshallnotvarymorethan2partsin109milliseconds;

(iv) theperiodbetweentransmissionsshallbe50secondsplusorminus5%; (v) overaperiodof24hoursofcontinuousoperationatanoperating

temperatureofminus200Celsius, the transmitterpoweroutputshallbewithinthelimitsof5Wplusorminus2dB;and

(vi) the406MHzEmergencyLocatorTransmittershallbecapableoftransmitting a digital message.

(3)Transmitteridentificationcoding— (i) EmergencyLocatorTransmittersoperatingon406MHz shall be

assigned a unique coding for identification of the transmitter oraircraftonwhichitiscarried;and

(ii) theEmergencyLocatorTransmittershallbecoded inaccordancewiththeaviationuserprotocoloroneoftheserialiseduserprotocolsandshallberegisteredwiththeAuthority.

(c) Installation (1)EachEmergencyLocatorTransmitter,requiredtobecarriedintermsoftheseregulationsmustbeattachedtotheaircraftinsuchamannerthattheprobabilityofdamagetothetransmitterintheeventofcrashimpactisminimised.Fixed and deployable automatic Emergency Locator Transmitters must be attachedtoanaeroplaneasfaraftaspossible.TheinstallationofanEmergencyLocatorTransmitterconstitutesamodificationofanaircraftandmustthereforebecompletedinaccordancewithacceptabletechnicaldata.TheacceptablestandardsshouldproducereliableandeffectiveEmergencyLocatorTransmittersystems,and keep unwanted activations to a minimum. Acceptable standards are based onthosesetoutinthefollowingsources—

(i) Federal Aviation Administration Advisory Circular 91-44A (as amended);and

(ii) RTCA papers DO-182 and DO-183.

(2)Exceptwhereotherwisestated,thefollowinginstallationrequirementsshallapplytoEmergencyLocatorTransmitterinstallationsinanyaeroplane—

(i) wheninstalledinanaeroplane,theEmergencyLocatorTransmittershallbemountedwithitssensitiveaxispointinginthedirectionofflight;

(ii) theEmergencyLocatorTransmittershallbeinstalledtowithstandultimate inertia forces of 10g upward, 22.5g downward, 45g forward and7.5gsideward;

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(iii) thelocationchosenfortheEmergencyLocatorTransmittermustbesufficientlyfreefromvibrationtopreventinvoluntaryactivationofthetransmitter;

(iv) theEmergencyLocatorTransmittershallbelocatedandmountedsoastominimizetheprobabilityofdamagetothetransmitterandantennabyfireorcrushingasaresultofcrashimpact;and

(v) theEmergencyLocatorTransmittershallbeaccessibleformanualactivation and deactivation.

(3)Ifitisequippedwithanantennaforportableoperation,theEmergencyLocatorTransmittershallbeeasilydetachablefrominsidetheaeroplaneand— (i) theexternalsurfaceoftheaeroplaneshallbemarkedtoindicatethe

locationoftheEmergencyLocatorTransmitter;and (ii) the Emergency LocatorTransmitter shall not use the antenna of

anotheravionicssystem. (4)Theexternalantennalocationshallbechosenconsideringthefollowingfactors— (i) theEmergencyLocatorTransmitterantennashallbemountedasfar

awayaspossiblefromotherVeryHighFrequency(VHF)antennas; (ii) thedistancebetweenthetransmitterandantennashallbeinaccordance

withtheEmergencyLocatorTransmittermanufacturer’sinstallationinstructionsorotherapproveddata;

(iii) thepositionof the antenna shall be suchas to ensure essentiallyomni-directionalsignaltransmissionswhentheaeroplaneisinitsnormalgroundorwaterattitude;

(iv) theantennashallbemountedasfaraftaspossible; (v) the Emergency Locator Transmitter antenna shall not foul other

antennasinflight;and (vi) theEmergencyLocatorTransmittershallbesubjectedtoanoperational

testasspecifiedinEmergencyLocatorTransmittertestingstandards. (5)AnEmergencyLocatorTransmitterwithalithiumormagnesiumbatteryshallnotbepackedinsidealiferaftinanaeroplane. (6)WheretheEmergencyLocatorTransmittersystemincludesaremotecontrolsystemforactivatinganddeactivatingthetransmitter,provisionshallbemadetopreventinadvertentoperationoftheremotecontrolandaplacarddisplayingthefollowingwarningshallbeplacedneareachremotecontrol—

“FORAVIATIONEMERGENCYUSEONLY.UNAUTHORIZEDOPERATIONPROHIBITED.”

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(7)Whenanaeroplaneisupright,anantennalocatedexternallyontopoftherearfuselageprovidesbetteroverallefficiencythananinternalcockpitareaantenna. (8)Whenanaeroplaneisinverted— (i) aninternalantennaexhibitsthebestoverallefficiencyinahigh-wing

aeroplane;and (ii) neitherantennalocationhasasignificantadvantageinalow-wing

aeroplane. (9)Inhelicopterinstallations,careneedstobetakentositetheantennasoastominimisevibratoryresponsewhichcouldleadtoprematurefatiguefailure. (10)ThepresenceofanEmergencyLocatorTransmitterwhipantennainclose proximity to a second antenna can cause some detuning and distortion oftheradiationpatternofthesecondantennaandpossibleinterferencebyre-radiationofothersignals.e.g.therehavebeenreportsofanEmergencyLocatorTransmitterradiatingaweakharmonicsignal toVHFtransmissions,causinginterferencewithGPSequipment. (11)TheEmergencyLocatorTransmittermountmustprovidealoadpathfromaircraftprimarystructuralelementsdirectlytotheautomaticactivationsystem.Theattachmentshouldalsobefreeandclearofcablesandpulleys,etc.,andbedesigned to minimise vibration. Excessive vibration may prevent satisfactory crashimpactdetectionormaygeneratefalsecrashsignals.Attachmentstothinpartitionsortopanels,suchasthesidesofbaggagecompartments,shouldbeavoided.AttachmentssolelybymeansofVelcrostripsandotherflexiblematerial,suchastie-wrap,arenotacceptable. (12)As approximately onefifth of light aircraft accidents result infire,thecoaxialcablebetweentheEmergencyLocatorTransmitteranditsexternalantennashouldbesleevedwithfire-resistantmaterials. (13) Automatic fixed-type, inertially-activated Emergency Locator Transmittersareactivatedbyaninertialforceparalleltothelongitudinalaxisoftheaircraft.However,manyinadvertentactivationshavebeencausedbyinertialswitchesactuatinginotherdirections. ForportableEmergencyLocatorTransmitters,themanufacturer’sinstallationinstructions must be followed precisely since placement and orientation may be critical. (14)TheinteractionofcomponentsintheEmergencyLocatorTransmitteris often critical in arriving at acceptable overall performance. Component parts fromothersourcessuchasbatteries,coaxialcablesandantennae,shouldnotbesubstitutedfortheoriginalmanufacturer’sparts.

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(15) Tests after installation and tests and inspections of Emergency Locator Transmittersshallbeperformed. (16)OncompletionofthemodificationtoinstalltheEmergencyLocatorTransmitterthecertifyingpersonshall— (i) ensurethattheinstallationisrecordedintheaircraftíslogbook;and (ii) placetheEmergencyLocatorTransmittermanufacturer’soperating

instructions in the aircraft flight manual, unless the relevantinformationisalreadygiveninaflightmanualsupplement.

(17)Areleasetoservicestatementforthemodificationmustbeissued.(d) Batteries (1)BatterytypesinEmergencyLocatorTransmittersareasfollows— (i) mostcommonly:zinc-manganesedioxide(alkaline); (ii) magnesium-manganesedioxide(magnesium);and(iii)earlymodels:lithium-sulphurdioxide(lithium). (2)Lithium-sulphurdioxidebatteriesmaybeusedonlyif theymeettherequirements ofFederalAviationAdministration’sTechnical StandardOrderC97. (3)TheEmergencyLocatorTransmitterbatteryexpirationdatemustbevisiblewithouthavingtoremovetheEmergencyLocatorTransmitterfromitsmountintheaircraft. (4)WhereEmergencyLocatorTransmitterbatteriescanbechargedduringflight,provisionshallbemadeto— (i) indicatetotheflightcrewthatchargingistakingplace;and (ii) preventbatterydischargeresultingfromwiringshortcircuitsoccurring

duringnormalserviceorfromcrashdamage.

eighth schedule (Section 18(2)

FEES

ForapprovalofELT,RVSM,MNPSorotherspecialapproval

Aircraft TypeNon-Refundable Application Fee Issuance Fee

Aircraft below 5 700 kg MAUM $50 $100Aircraft between 5 700-22 500 kgs MAUM $200 $400Aircraft between 22 500-45 000 kgs MAUM $400 $600Aircraft above 45 000 kgs MAUM $500 $800

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Supplement to the Zimbabwean Government Gazette dated the 27th July, 2018. Printed by the Government Printer, Harare.

5. General requirements – flight instruments. 6. Minimum ... Instrument 139 of 2018 Civil...S.I....

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