civil aviation (equipment and instruments) … · 24. mach number indicator 25. loss of...

C.1Supplement C — Botswana Government Gazette dated 4th January, 2013

Statutory Instrument No. 1 of 2013

CIVIL AVIATION ACT(Cap. 71:01)

CIVIL AVIATION (EQUIPMENT AND INSTRUMENTS) REGULATIONS, 2013(Published on 4th January, 2013)

ARRANGEMENT OF REGULATIONS

REGULATION

PART I — Preliminary

1. Citation 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. InstrumentsforoperationsrequiringtwopilotsindayVFR 8. Instruments required for IFR operations 9. Standby attitude indicator10. EquipmentandinstrumentsforcategoryIIoperations11. EquipmentandinstrumentsforcategoryIIIoperations12. EquipmentofaeroplanesoperatedbyasinglepilotunderIFRoratnight

PART IV — Communication Equipment

13. Radio equipment14. Flightcrewandcabincrewmemberinterphonesystemforaeroplanes15. Publicaddresssystem–airoperatorcertificateholders

PART V — Navigation Equipment

16. Navigationequipment–general17. MinimumNavigationPerformanceSpecifications 18. Reduced Vertical Separation Minimum19. Electronicnavigationdatamanagement20. Altitudereportingtransponder

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PART VI — Aircraft Lights and Instrument Illumination

21. Requiredaircraftlightsandinstrumentsillumination22. Requiredaircraftlightsandinstrumentsilluminationforcommercialairtransportoperations

PART VII — Engine Instruments

23. Engineinstruments

PART VIII — Warning Instruments and Systems

24. Mach number indicator25. Loss of pressurisation indicator26. Landinggearindicatorpositionandauralwarningdevice27. Altitudealertingsystem28. Groundproximitywarningsystem29. Weather radar30. Airborne collision avoidance system31. Forwardlookingwindshearwarningsystem–turbojetaeroplanes

PART IX — Flight and Cockpit Voice Recorders

32. Cockpit voice recorders33. Cockpit voice recorders performance requirements34. Flightdatarecorders35. Recordingofdatalinkcommunications

PART X — Emergency, Rescue and Survival Equipment

36. Emergencyequipment–allaircrafts37. Emergencyexitequipment–passengers38. Ditchingemergencyexitsforpassengers39. Ramp exits40. Emergencyexitarrangement41. Emergencyexitmarking42. Emergencylighting43. Emergencyexitaccess44. Main aisle width45. Visualsignallingdevices46. Survival kits47. Emergencylocatortransmitter48. Portablefireextinguishers49. Lavatoryfireextinguisher50. Lavatory smoke detector51. Crash axe52. Markingofbreak-inpoints53. First-aidkit

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54. Emergencymedicalkit–aeroplanes55. Oxygenstorageanddispensingapparatus56. Protectivebreathingequipment57. First-aidoxygendispensingunits58. Megaphones59. Individualflotationdevices60. Life rafts61. Flotationdeviceforhelicopterditching

PART XI — Miscellaneous Systems and Equipment

62. Seats, safety belts and shoulder harnesses63. Passengerandpilotcompartmentdoors–aeroplanes64. Passengerinformationsigns65. Materialsforcabininteriors,cargoandbaggagecompartments66. Power supply, distribution and indication system67. Protective circuit fuses68. Icingprotectionequipment69. Pitot heat and indication systems70. Static pressure system71. Windshield wipers72. Chart holder73. Cosmic radiation detection equipment74. Offences and penalties75. Administrative penalties SCHEDULES

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IN EXERCISE of the powers conferred on the Minister of Transport and Communications by section 89 of the Civil Aviation Act and on the recommendation of the Civil Aviation Authority,thefollowingRegulationsareherebymade—

PART I — Preliminary

1. TheseRegulationsmaybecitedas theCivilAviation (EquipmentandInstruments)Regulations,2013. 2. IntheseRegulations,unlessthecontextotherwiserequires—“aeroplane”means a power-driven heavier-than-air aircraft deriving its lift

inflightchieflyfromaerodynamicreactionsonsurfaceswhichremainfixedundergivenconditionsofflight;

“air operator certificate (AOC)”means a certificate issuedby theAuthoritywhichauthorisesanoperatortocarryoutspecifiedcommercialairtransportoperations;

“airborne collision avoidance system (ACAS)” means an aircraft system which — (a) conformstotherequirementsprescribedforthepurpose; (b) isbasedonsecondarysurveillanceradartranspondersignals;and (c) operatesindependentlyofgroundbasedequipment, designedtoprovideadviceandappropriateavoidancemanoeuvrestothepilot in relation to other aircrafts which are equipped with secondary surveillance radarandareinundueproximity;“appropriate aeronautical radio station” means, in relation to an aircraft, an

aeronauticalradiostationservingtheareainwhichtheaircraftis,forthetimebeing;

“automatic directionfinding equipment”means radio navigation equipmentwhichautomaticallyindicatesthebearingofanyradiostationtransmittingthesignalsreceivedbysuchequipment;

“areanavigation”meansamethodofnavigationthatpermitsaircraftoperationsonanydesiredflightpathwithinthecoverageofstation-referencednavigationaidsorwithinthelimitsofthecapabilityofself-containedaids,oracombinationofthese;

“categoryIoperation(CATI)”meansaprecision instrumentapproachandlandingwithadecisionheightnotlowerthan60metres(200ft)andwitheitheravisibilityofnotlessthan800metresorarunwayvisualrangenotlessthan550metres;

“categoryIIoperation(CATII)”meansaprecisioninstrumentapproachandlandingwith a decision height lower than 60metres (200 ft) but notlowerthan30metres(100ft)andavisualrangenotless350metres;

“categoryIIIAoperation(CATIIIA)”meansaprecisionapproachandlandingwith —

(a) adecisionheightlowerthan30metres(100ft)ornodecisionheight;and (b) arunwayvisualrangenotlessthan200metres;“categoryIIIBoperation(CATIIIB)”meansaprecisionapproachandlanding

with — (a) adecisionheightlowerthan15metres(50ft)ornodecisionheight;and (b) arunwayvisualrangelessthan200mbutnotlessthan50metres;

Citation

Interpretation

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“categoryIIICoperation(CATIIIC)”meansaprecisioninstrumentapproachandlandingwithnodecisionheightandnorunwayvisualrangelimitations;

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

“distancemeasuring equipment (DME)”means radio equipment capable ofproviding a continuous indication of the aircraft’s distance from theappropriateaeronauticalradiostations;

“emergency locator transmitter (ELT)” means any equipment capable ofbroadcastingdistinctivesignalsondesignatedfrequenciesand,dependingon application, may be automatically activated by impact or be manually activated;

“enhanced ground proximitywarning system (EGPWS)” means a forwardlooking warning system that uses the terrain data base for terrainavoidance;

“flashresistant”meansnotsusceptibletoburningwhenignited;“flightrecorder”meansanytypeofrecorderinstalledintheaircraftforthe

purpose of complementing accident or incident investigation andincludesthecockpitvoicerecorderorflightdatarecorder;

“ground proximitywarning system (GPWS)”means awarning system thatusesradaraltimeterstoalertthepilotsofhazardousflightconditions;

“highspeed auralwarning”means a speedwarning that is required forturbine-engined airplanes and airplanes with a Vmo/Mmo greater than0.80 Vdf/Mdf or Vd/Md;

“IFR”meansInstrumentFlightRules;“longrangeoverwaterflights”meansroutesonwhichanaeroplanemaybe

overwaterandatmorethanadistancecorrespondingto120minutesatcruisingspeedor740km(400NM),whicheveristhelesser,awayfromlandsuitableformakinganemergencylanding;

“lowaltitudewindshearwarningandguidancesystem”meansasystemthatissuesawarningoflowaltitudewindshearandmayprovidethepilotwithguidanceinformationoftheescapermanoeuvre;

“Mach number indicator” means an indicator that shows airspeed as a function oftheMachnumber;

“Minimum Equipment List (MEL)” means a list approved by the Authority which provides for theoperationof the aircraft, subject to specifiedconditions,with particular equipment inoperative, prepared by an operator in conformity with, or more restrictive than, the master minimum equipment list established fortheaircrafttype;

“operator”meansaperson,organisationorenterpriseengagedinorofferingtoengageinanaircraftoperation;

“PBE”meansprotectivebreathingequipment;“required navigation performance” means a statement of the navigation

performancenecessaryforoperationswithadefinedairspace;“reducedverticalseparationminimum(RVSM)”meansdefinedportionsofairspace

where,basedonaRegionalAirNavigationAgreement,areducedverticalseparation minimum of 300 m (1000 ft) is applied between FL 290 and FL410inclusive;

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“runwayvisualrange(RVR)”meanstherangeoverwhichthepilotofanaircraftonthecentrelineofarunwaycanseetherunwaysurfacemarkingsorthelightdelineatingtherunwayoridentifyingitscentreline;

“StateofOperator”meansthestateinwhichtheoperator’sprincipalplaceofbusiness is located,or if there isno suchbusiness, theoperator’spermanentplaceofresidence;

“StateofRegistry”meansthestateonwhoseregistertheaircraftisentered;“terrainawarenesswarningsystem”meansasystemthatprovidestheflightcrew

withsufficientinformationandalertingtodetectapotentiallyhazardousterrainsituationandsotheflightcrewmaytakeeffectiveactiontopreventacontrolledflightintoterrainevent;and

“VFR”meansVisualFlightRules.

PART II — Equipment of Aircraft

3. (1) In addition to the minimum equipment necessary for the issuance of a certificate of airworthiness under theCivilAviation, (Airworthiness)Regulations,apersonshallnotflyanaircraftunlesstheaircraftisinstalledwithequipmentandinstrumentsspecifiedintheseRegulations. (2) The owner or operator of any aircraft which is operated in Botswana but not registered inBotswanawhichusesanairworthiness inspectionprogramapprovedoracceptedbytheStateofRegistry,shallensurethatequipmentandinstruments installed in the aircraft are properly installed and inspected in accordancewiththerequirementsoftheStateofRegistry. (3) The Authority may specify other additional or special equipment as mayberequiredintheSchedulestotheseRegulations. (4) All required equipment and instruments shall be approved and installed inaccordancewithapplicableairworthinessrequirementsspecifiedundertheCivilAviation(Airworthiness)Regulations. 4. Apersonshallnotcommenceaflightincommercialairtransportoperationsunless the required equipment — (a) meets the minimum performance standard, all operational and airworthiness requirementsandtherelevantprovisionsofICAOAnnex10,VolumeIV; (b) isinstalledsuchthatthefailureofanysingleunitrequiredforeither communicationornavigationpurposes,orboth,willnotresultinthe inabilitytocommunicateornavigate,orcommunicateandnavigate safelyontheroutebeingflown;and (c) iscapableofbeingoperatedforthekindofoperationbeingconducted, except as provided in the Minimum Equipment List.

PART III — Flight Instruments

5. (1) Anaircraftshallbeequippedwithflightinstrumentswhichenabletheflightcrewto— (a) controltheflightpathoftheaircraft; (b) carryoutanyrequiredproceduralmanoeuvres;and (c) observetheoperatinglimitationsoftheaircraftintheexpectedoperating conditions.

General equipment and instruments requirement

Equipment for commercial air operations

General requirement – flightinstruments

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(2) Where amethod is provided for transferring an instrument from itsprimaryoperatingsystemtoanalternativesystem,themethodshallincludeapositivepositioningcontrolandshallbemarkedsoastoindicateclearlywhichsystemisbeingused. (3) Theinstrumentsusedbyanyonepilotshallbesoarrangedastoallowthe pilot to see the indications readily from his or her station, with the minimum practicable deviation from the position and line of vision which he or she nor-mallyassumeswhenlookingforwardalongtheflightpath. 6. A person may not operate any powered aircraft unless it is equipped with thefollowingflightinstruments— (a) anairspeedindicatingsystemcalibratedinknots,milesperhouror kilometresperhour; (b) asensitivepressurealtimetercalibratedinfeetwithasub-scalesetting calibratedinhectopascalspermillibars,adjustableforanybarometric pressurelikelytobesetduringflight; (c) anaccuratetime-pieceindicatingthetimeinhours,minutes,andseconds; (d) amagneticcompass;and (e) anyotherequipmentasmaybespecifiedbytheAuthority. 7. Inanyflightwheretwopilotsarerequired,eachpilot’sstationshallhaveseparateflightinstrumentsasfollows— (a) an airspeed indicator calibrated in knots, miles per hour or kilometres perhour; (b) asensitivepressurealtimetercalibratedinfeetwithasub-scalesetting calibratedinhectopascalspermillibars,adjustableforanybarometric pressurelikelytobesetduringflight; (c) averticalspeedindicator; (d) aturnandslipindicator,oraturnco-coordinatorincorporatingaslip indicator; (e) anattitudeindicator; (f) astabiliseddirectionindicator;and (g) anyotherequipmentasmaybespecifiedbytheAuthority. 8. (1) Inadditiontotherequirementsunderregulation5,allaircraftwhenoperated in IFR, or when the aircraft cannot be maintained in a desired attitude withoutreferencetooneormoreflightinstruments,shallbeequippedwith— (a) anairspeedindicatingsystemwithameansofpreventingmalfunctioning duetoeithercondensationoricing; (b) for commercial air transport operations, an additional sensitive pressure altimetercalibratedinfeetwithasub-scalesettingcalibratedin hectopascalspermillibars,adjustableforanybarometricpressurelikely tobesetduringflight; (c) aturnandslipindicatorforaeroplanesoraslipindicatorforhelicopters; (d) attitudeindicator(artificialhorizon)— (i) one attitude indicator for aeroplanes, (ii) three attitude indicators for a commercially operated helicopter, one of which may be replaced by a turn indicator, or (iii) twoattitudeindicatorsforanon-commerciallyoperatedhelicopter, oneofwhichmaybereplacedbyaturnindicator;

Minimum flightinstruments

Instruments for operations requiringtwopilots in day VFR

Instruments required for IFR operations

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(e) aheadingindicator(directionalgyroscope); (f) ameansofindicatingwhetherthesupplyofpowertothegyroscopic instrumentsisadequate; (g) ameansofindicatingtheoutsideairtemperatureintheflightcrew compartment; (h) arate-of-climbanddescentindicator; (i) for a commercial operated helicopter, a stabilisation system operations, unless it has been demonstrated to the satisfaction of the Authority that thehelicopterpossesses,bynatureofitsdesign,adequatestability withoutsuchasystem;and (j) suchadditionalequipmentorinstrumentsasmaybespecifiedbythe Authority. (2) Therequirementsofsubregulation(1)(c), (d) and (e) may be met by combinationsofinstrumentsorbyintegratedflightdirectorsystemsprovidedthat thesafeguardsagainst total failure, inherent in theseparate instrumentsare retained. (3) A person shall not operate an aeroplane commercially under IFR, or under VFRoverroutesthatcannotbenavigatedbyreferencetovisuallandmarks,unlesstheaeroplaneisequippedwithnavigationequipmentinaccordancewiththerequirementsofairtrafficservicesintheareaorareasofoperation. (4) ApersonshallnotconductsinglepilotIFRoperationsforcommercialair operations unless the aeroplane is equipped with an autopilot with at least altitudeholdandheadingmode. (5) A person shall not operate an aeroplane under IFR unless it is equipped withanaudioselectorpanelaccessibletoeachrequiredflightcrewmember. (6) A person shall not conduct single pilot IFR or night operations incommercial air transport operations unless the aeroplane is equipped with a headset with boom microphone or an equivalent and a transmit button on the control wheel. 9. (1) Apersonshallnotoperateanaeroplanewithamaximumcertifiedtake-off massexceeding5,700kgoraperformanceClass1or2helicopterunlessitisequippedwithasinglestandbyattitudeindicator(artificialhorizon)that — (a) operatesindependentlyofanyotherattitudeindicatingsystem; (b) ispoweredcontinuouslyduringnormaloperation;and (c) afteratotalfailureofthenormalelectricalgeneratingsystem,is automatically powered for a minimum of 30 minutes from a source independentofthenormalelectricalgeneratingsystem. (2) Where the standbyattitude indicator isbeingoperatedbyemergencypower,itshallbeclearlyoperatingandilluminatedtotheflightcrew. (3) Where the standby attitude indicator has its own dedicated power supply there shall be an associated indication, either on the instrument or on the instrument panel when this supply is in use. (4) Where the standby attitude instrument system is installed and usable throughflightattitudesof3600 of pitch and roll, the turn and slip indicators may be replaced by slip indicators.

Standby attitude indicator

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10. (1) The instruments and equipment listed in this regulation shall beinstalled, approved and maintained in accordance with the manufacturer’sspecificationandasspecifiedunderSchedule1foreachaircraftoperatedinacategoryIIoperation. (2) GroupIofacategoryIIoperationshallbeequippedwiththefollowingequipment which shall be inspected both within three calendar months of the previous inspection and shall also have a bench inspection within 12 months ofthepreviousbenchinspectionusingprocedurescontainedintheapprovedmaintenanceprogram— (a) twolocalizerandglideslopereceivingsystemsandeachsystemshall provide — (i) abasicInstrumentLandingSystemsdisplay,and (ii) aninstrumentpanelcapableofshowingabasicInstrumentLanding Systems display: Providedasinglelocaliserantennaandasingleglideslopeantenna maybeused; (b) a communications system that does not affect the operation of at least oneoftheInstrumentLandingSystems; (c) a marker beacon receiver that provides distinctive aural and visual indicationsoftheouterandthemiddlemarkers; (d) twogyroscopicpitchandbankindicatingsystems; (e) twogyroscopicdirectionindicatingsystems; (f) twoairspeedindicators; (g) twosensitivealtimetersadjustableforbarometricpressure,having markingsat20footintervalsandeachhavingaplacarddisplayingthe correctionforaltimeterscaleerrorandforthewheelheightoftheaircraft; (h) oneself-monitoringradioaltimeterwithdualdisplay; (i) twoverticalspeedindicators;and (j) aflightcontrolguidancesystemthatconsistsofeitheranautomatic approachcoupleroraflightdirectorsystem. (3) Category II operationswithdecisionheights below150 feet shall beequipped with a radio altimeter. (4) GroupIIofacategoryIIoperationshallbeequippedwiththefollowingequipment which, with the exception of the static system, does not require special maintenance procedures other than those necessary to retain the originalapproval condition — (a) warningsystemsforimmediatedetectionbythepilotofsystemfaults initemsundersubregulation(2)(a), (d), and (i); (b) dualcontrols; (c) an externally vented static pressure system with an alternate static pressure source; (d) awindshieldwiperorequivalentmeansofprovidingadequatecockpit visibility for a safe visual transition by either pilot to touchdown and rollout;and (e) a heat source for each airspeed system pitot tube installed or an equivalent meansofpreventingmalfunctioningduetoicingofthepitotsystem.

Equipment and instruments forcategoryIIoperations

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(5) GroupIIofacategoryIIoperationequipmentshallbeinspectedwithin12monthsofthepreviousinspectionusingprocedurescontainedintheapprovedmaintenanceprogram. 11. (1) Theequipmentandinstrumentslistedinthisregulationshallbeinstalled,approved and maintained in accordance with internationally acceptable criteria and theAircraftFlightManualineachaircraftoperatedinacategoryIIIoperation. (2) AirbornesystemsforcategoryIIIAminimanotlessthanRVR200m(600 ft) shall be equippedwith the following equipment in addition to theinstrumentandnavigationequipmentrequiredbythisPartforIFRflightandcategoryIIoperations— (a) aredundantflightcontrolorguidancesystemdemonstratedinaccordance with internationally acceptable criteria which include — (i) aFailOperationalorFailPassiveautomaticlandingsystemat least to touchdown, (ii) aFailOperationalorFailPassivemanualflightguidancesystem providingsuitablehead-uporhead-downcommandguidance, andsuitablemonitoringcapabilityatleasttotouchdown, (iii) ahybridsystem,usingautomaticlandingcapabilityastheprimary meansoflandingatleasttotouchdown,or (iv) other systems that can provide an equivalent level of performance andsafety; (b) an automatic throttle or automatic thrust control system that meets approvedcriteriaasspecifiedintheAircraftFlightManualexceptthat foroperationswitha15m(50ft)DecisionHeight,orotheroperations thathavebeenspecificallyevaluatedsuchasforengineinoperative landingcapability,automaticthrottlesmaynotberequiredifithasbeen demonstrated that operations can be safely conducted, with an acceptable workload,withouttheiruse; (c) atleasttwoindependentnavigationreceiversorsensorsprovidinglateral andverticalpositionordisplacementinformation,typicallywiththefirst pilot’sstationreceivingtheinformationfromoneandthesecondpilot’s stationreceivingtheinformationfromtheother; (d) at least two approved radio altimeter systems that meet the performance requirementscriteriaasspecifiedintheAircraftFlightManual,typically withthefirstpilot’sstationreceivinginformationfromoneandthe secondpilot’sstationreceivinginformationfromtheother; (e) failuredetection,annunciation,andwarningcapability,asdetermined tobeacceptablebycriteriaspecifiedintheAircraftFlightManual; (f) missedapproachguidanceprovidedbyoneormoreofthefollowing means — (i) attitudedisplaysthatincludesuitablepitchattitudemarkings,or apre-establishedcomputedpitchcommanddisplay, (ii) anapprovedflightpathangledisplay,or (iii) anautomaticorflightguidancego-aroundcapability; (g) suitableforwardandsideflightdeckvisibilityforeachpilotasspecified intheAircraftFlightManual;and (h) suitablewindshieldrainremoval,iceprotection,ordefogcapabilityas specifiedintheAircraftFlightManual.

Equipment and instru-ments for categoryIIIoperations

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(3) Thenavigationreceiversorsensorsreferredtoundersubregulation(2)(c) shallmeetthecriteriaspecifiedforcategoryIIIAoperations. (4) AirbornesystemsforcategoryIIIBminimalessthanRVR200m(600ft)butnotlessthanRVR125m(400ft)shallbeequippedwiththefollowingequipmentinadditiontotheinstrumentandnavigationequipmentrequiredbythisPartforIFRflight,categoryIIandcategoryIIIAoperations— (a) aredundantflightcontrolorguidancesystemdemonstratedinaccordance with internationally acceptable criteria which include — (i) aFailOperationallandingsystemwithaFailOperationalorFail Passive automatic rollout system, (ii) aFailPassivelandingsystem,limitedtotouchdownzoneRVR not less than RVR 200 m (600 ft), with Fail Passive rollout provided automaticallyorbyaflightguidancesystemprovidingsuitable head-uporhead-downguidance,andsuitablemonitoringcapability, (iii) aFailOperationalhybridautomaticlandingandrolloutsystem withcomparablemanualflightguidancesystem,usingautomatic landingcapabilityastheprimarymeansoflanding,or (iv) other system that can provide an equivalent level of performance andsafety; (b) an automatic throttle or automatic thrust control that meets the appropriate criteriaasspecifiedintheAircraftFlightManualexceptthatforoperations witha15m(50ft)DecisionHeight,automaticthrottlesmaynotbe required if it has been demonstrated that operations can safely be conducted, withanacceptableworkload,withouttheiruse; (c) atleasttwoindependentnavigationreceiversorsensorsprovidinglateral and vertical position or displacement information, typically with the firstpilot’sstationreceivinginformationfromoneandthesecondpilot’s stationreceivinginformationfromtheother; (d) at least two approved radio altimeter systems that meet the performance criteriaspecifiedintheAircraftFlightManual,typicallywiththefirst pilot’sstationreceivinginformationfromoneandthesecondpilot’s stationreceivinginformationfromtheother; (e) failuredetection,annunciationandwarningcapabilityasspecifiedin theAircraftFlightManual; (f) missedapproachguidanceprovidedbyoneormoreofthefollowing means — (i) attitudedisplaysthatincludecalibratedpitchattitudemarkings, orapre-establishedcomputedpitchcommanddisplay, (ii) anapprovedflightpathangledisplay,or (iii) anautomaticorflightguidancego-aroundcapability; (g) suitableforwardandsideflightdeckvisibilityforeachpilot,asspecified intheAircraftFlightManual;and (h) suitablewindshieldrainremoval,iceprotection,ordefogcapabilityas specifiedintheAircraftFlightManual. (5) Thenavigationreceiversorsensorsreferredtoundersubregulation(4)(c)shallmeetthecriteriaspecifiedintheAircraftFlightManual.

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(6) AirbornesystemsforcategoryIIICminimalessthanRVR75m(250ft)shallbeequippedwiththefollowingequipmentinadditiontotheinstrumentandnavigationequipmentrequiredbythisPartforIFRflightandcategoryII,categoryIIIAandcategoryIIIBoperations— (a) aFailOperationalAutomaticFlightControlSystem,ormanualflight guidancesystemdesignedtomeetfailoperationalsystemcriteria,ora hybridsysteminwhichboththefail-passiveautomaticsystemand themonitoredmanualflightguidancecomponentsprovideapproach andflareguidancetotouchdown,andincombinationprovidefullfail operational capability, and (b) a Fail Operational automatic, manual, or hybrid Rollout Control System. 12. AnaeroplaneoperatedbyasinglepilotunderIFRoratnightshallbeequipped with — (a) aserviceableautopilotthathasatleastaltitudeholdandheadingselect modes; (b) aheadsetwithaboommicrophoneorequivalent;and (c) meansofdisplayingchartsthatenablesthemtobereadableinallambient lightconditions.

PART IV — Communication Equipment

13. (1) A person shall not operate an aircraft unless it is equipped with radio communication equipment required for the kind of operation beingconducted. (2) AnaircraftoperatedinVFRasacontrolledflight,inIFR,atnight,asan extended flightoverwater, or over landdesignatedby theAuthority asespeciallydifficultforsearchandrescue,shallbeequippedwithradiocommunication equipment — (a) capableofconductingtwo-waycommunicationatanytimewithairtraffic servicesoraeronauticalstations; (b) capableofconductingcommunicationsonthosefrequenciesprescribed bytheAuthority; (c) capableofreceivingmeteorologicalinformationatanytimeduringthe flight; (d) capableofconductingcommunicationsontheaeronauticalemergency frequency121.5MHz; (e) approved and installed in accordance with the requirements applicable tothem,includingtheminimumperformancerequirements; (f) installedsuchthatthefailureofanysingleunitrequiredforcommunication equipment, will not result in the failure of another unit required for communicationpurposes;and (g) meetinganyotherrequirementsasmaybespecifiedbytheAuthority. (3) A person shall not operate an aircraft in commercial air transport operations, or as otherwise specifiedby theAuthority, unless the aircraft isequipped with two independent radio communications systems, appropriate to the route and airspace used. (4) Where more than one communications equipment unit is required, each shall be independent of the other or others to the extent that a failure in any one will not result in failure of any other.

Equipment of aeroplanes operated by asinglepilotunder IFR or atnight

Radioequipment

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(5) A person shall not operate an aircraft in commercial air transport operations unless the aircraft is equipped with a boom or throat microphone available at eachrequiredflightcrewmemberflightdutystation. 14. (1) A person shall not operate an aeroplane in commercial air transport operationsonwhichaflightcrewofmorethanoneisrequiredunlesstheaeroplaneisequippedwithaflightcrewinterphonesystem,includingheadsetsandmicrophones,notofahandheldtype,forusebyallmembersoftheflightcrew. (2) A person shall not operate an aeroplane in commercial air transport operationswithamaximumcertifiedtake-offmassexceeding15,000kg,orhavinganapprovedpassengerseatingcapacityof19ormore,orhavingaflightcrew compartment door, unless the aeroplane is equipped with a crew member interphone system that — (a) operates independently of the public address system except for handsets, headsets,microphones,selectorswitchesandsignallingdevices; (b) providesameansoftwo-waycommunicationbetweentheflightcrew compartment and each — (i) passengercompartment, (ii) galleylocatedotherthanonapassengerdecklevel,and (iii) remotecrewcompartmentthatisnotonthepassengerdeckand isnoteasilyaccessiblefromapassengercompartment; (c) is readily accessible for use — (i) fromeachoftherequiredflightcrewstationsintheflightcrew compartment, and (ii) at required cabin crew member stations close to each separate or pairoffloorlevelemergencyexits; (d) hasanalertingsystemincorporatingauralorvisualsignalsforuseby flightcrewmemberstoalertthecabincrew,andforusebycabincrew memberstoalerttheflightcrewintheeventofsuspiciousactivityor securitybreachesinthecabin; (e) has a means for the recipient of a call to determine whether it is a normal calloranemergencycall;and (f) providesonthegroundameansoftwo-waycommunicationbetween groundpersonnelandatleasttwoflightcrewmembers. 15. (1) Anairoperator certificateholder shall notoperate apassengercarryingaeroplanewithamaximumapprovedpassengerseatingconfigurationof more than 19 unless it is equipped with a public address system that — (a) operates independently of the interphone systems except for handsets, headsets,microphones,selectorswitchesandsignallingdevices; (b) isreadilyaccessibleforimmediateusefromeachrequiredflightcrew memberstation; (c) foreachrequiredfloorlevelpassengeremergencyexitwhichhasan adjacentcabincrewseat,isfurtherequippedwithamicrophonewhich is readily accessible to the seated cabin crew member, except that one microphone may serve more than one exit, provided the proximity of the exits allows unassisted verbal communication between seated cabin crewmembers;

Flightcrewand cabin crew member interphone system for aeroplanes

Public address system – air operator certificateholders

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(d) is capable of operation within 10 seconds by a cabin crew member at eachofthosestationsinthecompartmentfromwhichitsuseisaccessible; and (e) isaudibleandintelligibleatallpassengerseats,toilets,andcabincrew seats and workstations. (2) Anairoperatorcertificateholdershallnotoperateapassengercarryinghelicopterwithamaximumapprovedpassengerseatingconfigurationofmorethan 19 unless it is equipped with a public address system that — (a) operates independently of the interphone systems except for handsets, headsets,microphones,selectorswitchesandsignallingdevices; (b) isreadilyaccessibleforimmediateusefromeachrequiredflightcrew memberstation; (c) foreachrequiredfloorlevelpassengeremergencyexitwhichhasan adjacentcabincrewseat,isfurtherequippedwithamicrophonewhich is readily accessible to the seated cabin crew member, except that one microphone may serve more than one exit, provided the proximity of the exits allows unassisted verbal communication between seated cabin crewmembers; (d) is capable of operation within 10 seconds by a cabin crew member at eachofthosestationsinthecompartmentfromwhichitsuseisaccessible; (e) isaudibleandintelligibleatallpassengerseats,toilets,andcabincrew seatsandworkstations;and (f) followingatotalfailureofthenormalelectricalgeneratingsystem, provide a reliable operation for a minimum of 10 minutes. (3) Anairoperatorcertificateholdershallnotoperateapassengercarryinghelicopterwithamaximumapprovedpassengerseatingconfigurationofmorethan 9 but less than 19 unless it is equipped with a public address system. (4) Subregulation(3)shallnotapplywhere— (a) thehelicopterisdesignedwithoutabulkheadbetweenpilotandpassengers; and (b) the operator is able to demonstrate in a manner acceptable to the Authority thatwheninflight,thepilot’svoiceisaudibleandintelligibleatallpassenger seats.

PART V — Navigation Equipment

16. (1) A person shall not operate an aircraft unless it is equipped with navigationequipmentthatenablesittoproceedinaccordancewith— (a) itsoperationalflightplan;and (b) therequirementsofairtrafficservices. (2) A person shall not operate a flight in defined portions of airspace,including Minimum Navigation Performance Specifications, ReducedVertical SeparationMinimum, or on routeswhere aRequiredNavigationalPerformance Type has been prescribed unless — (a) the person has received authorisation from the Authority in either operationsspecificationsforairoperatorcertificateholdersorletterof authorisationfornon-airoperatorcertificateholders; (b) theaircraftisequippedwithnavigationequipmentwhichenablesitto operateinaccordancewiththeprescribedRequiredNavigation PerformanceType;and

Navigationequipment – general

C.15

(c) theaircraftisequippedwithnavigationequipmentthatcontinuously providesinformationtotheflightcrewofadherencetoordeparture fromtrackwithrespecttotherequireddegreeofaccuracyatanypoint alongthattrack. (3) Apersonshallnotoperateanaircraftunlessitisequippedwithsufficientnavigationequipment thatwillenable theaircraft tonavigate inaccordancewithsubregulations(1)and(2),suchthat— (a) intheeventofthefailureofanypieceofnavigationequipmentatany stageofflight,theremainingequipmentenablestheaircrafttocontinue tonavigate;and (b) thefailureofanysingleunitrequiredforeithercommunicationsor navigationpurposes,orbothdoesnotresultinthefailureofanother unitrequiredforcommunicationsornavigationpurposes. (4) Theequipmentrequirementsspecifiedundersubregulation(3)(a) shall not apply in instances where the Authority authorises VFR by visual reference to landmarks. (5) A person shall not operate an aeroplane under IFR, or under VFR over routesthatcannotbenavigatedbyreferencetovisual landmarks,unlesstheaeroplane is equippedwithnavigationequipment inaccordancewith therequirementsofairtrafficservicesintheareaorareasofoperation. (6) AnaircraftintendedtolandinInstrumentMeteorologicalConditionsoratnightshallbeprovidedwithradionavigationequipmentcapableofreceivingsignalsprovidingguidanceto— (a) apointfromwhichavisuallandingcanbeeffected;or (b) each aerodrome at which it is intended to land in Instrument MeteorologicalConditions;and (c) anydesignatedalternateaerodromes. 17. (1) Aperson shall notoperate an aeroplane inMinimumNavigationPerformance Specification airspace unless it is equipped with navigationequipment that — (a) continuouslyprovidesindicationstotheflightcrewofadherencetoor departurefromtracktotherequireddegreeofaccuracyatanypoint alongthattrack;and (b) isauthorisedbytheAuthorityforMinimumNavigationPerformance Specificationoperationsconcernedthrougheitheroperationsspecifications forairoperatorcertificateholdersorletterofauthorisationforgeneral aviation. (2) ThenavigationequipmentrequiredforoperationsinMinimumNavigationPerformanceSpecificationairspaceshallbevisibleandusablebythepilotseatedat his or her duty station. (3) ForunrestrictedoperationinMinimumNavigationPerformanceSpecificationairspaceanaeroplaneshallbeequippedwithtwoindependentLong-RangeNavigationSystems. (4) ForoperationinMinimumNavigationPerformanceSpecificationairspacealongnotifiedspecialroutes,anaeroplaneshallbeequippedwithoneLong-RangeNavigationSystem,unlessotherwisespecified.

Minimum NavigationPerformance Specifications

C.16

18. (1) For flights in defined portions of airspace where, based on aRegionalAirNavigationAgreement,aReducedVerticalSeparationMinimum(RVSM) of 300 m (1 000 ft) is applied between FL 290 and FL 410 inclusive, an aeroplane shall be — (a) equipped such that the equipment is capable of — (i) indicatingtotheflightcrewtheflightlevelbeingflown, (ii) automaticallymaintainingaselectedflightlevel, (iii) providinganalerttotheflightcrewwhenadeviationoccursfrom theselectedflightlevel,and (iv) automaticallyreportingpressure-altitude;and (b) authorised for operations in the airspace concerned by — (i) theStateofOperatorforairoperatorcertificateholdersthrough operationsspecifications,or (ii) theStateofRegistryfornon-airoperatorcertificateholdersthrough a letter of authorisation. (2) An application for Reduced Vertical Separation Minimum approval or authorisation shall be made to the Authority in the form set out in Part I of Schedule 2 and shall be accompanied by a fee of P2 000. (3) Prior to granting aReducedVertical SeparationMinimum approvalrequiredundersubregulation(1),theAuthorityshallfirstsatisfyitselfthat— (a) theverticalnavigationperformancecapabilityoftheaeroplanesatisfies therequirementsspecifiedinPartIIofSchedule2; (b) the operator has instituted appropriate procedures in respect of continued airworthinessincludingmaintenanceandrepairpracticesandprogrammes; and (c) theoperatorhasinstitutedappropriateflightcrewproceduresforoperations in Reduced Vertical Separation Minimum airspace. (4) TheAuthorityshall,inconsultationwiththeStateofRegistry,whereappropriate, ensure that adequate provisions exist, in respect of those aeroplanes referredtoundersubregulation(1),for— (a) receivingthereportsofheight-keepingperformanceissuedbythe monitoringagenciesestablishedinaccordancewithICAOAnnex11;and (b) takingimmediatecorrectiveactionforindividualaircraft,oraircraft typegroups,identifiedinsuchreportsasnotcomplyingwiththe height-keepingrequirementsforoperationsinairspacewherea Reduced Vertical Separation Minimum is applied. (5) Anaeroplaneshallbesufficientlyequippedwithnavigationequipmenttoensurethat,intheeventofthefailureofoneitemofequipmentatanystageoftheflight,theremainingequipmentenablestheaeroplanetonavigateinareduced vertical separation minimum space. (6) Thethresholdforthealertreferredtoundersubregulation(1)(a) (iii) shallnotexceed+or-90m(300ft).

Reduced Vertical Separation Minimum

C.17

19. ApersonshallnotemployelectronicnavigationdataproductsthathavebeenprocessedforapplicationintheairandonthegroundunlesstheAuthorityhas approved — (a) theoperator’sproceduresforensuringthattheprocessappliedandthe productsdeliveredhaveacceptablestandardsofintegrityandthatthe productsarecompatiblewiththeintendedfunctionoftheequipment; (b) theoperator’sprogramforcontinualmonitoringofbothprocessand products;and (c) theoperator’sprocedurestoensurethetimelydistributionandinsertion ofcurrentandunalteredelectronicnavigationdatatoallaircraft. 20. (1) A person shall not operate an aircraft in airspace that requires a pressure reporting transponderunless thepressure reporting transponder isoperative and functional. (2) A person shall not operate an aircraft at altitudes above FL 290 unless it isequippedwithasystemthatautomaticallyreportingpressurealtitudes. (3) A person shall not operate an aircraft in commercial air transport operations unlessitisequippedwithapressure-altitudereportingtransponderthatoperatesinaccordancewiththerequirementsofBotswanaairtrafficservicesandICAOAnnex 10, Volume 4. (4) Anaeroplaneforwhichtheindividualcertificateofairworthinesswasfirst issued after 1 January 2009 shall be equippedwith a data source thatprovidespressure-altitudeinformationwitharesolutionof7.62m(25ft),orbetter. (5) After1January2012,allaeroplanesflyinginBotswanashallbeequippedwithadatasourcethatprovidespressure-altitudeinformationwitharesolutionof 7.62 m (25 ft), or better. (6) Where an aeroplane is equipped with a Mode S transponder the Mode S transponder shall be providedwith an airborne or on-the-ground status ifthe aeroplane is equipped such that it is capable of detecting such statusautomatically.

PART VI — Aircraft Lights and Instruments Illumination

21. (1) Anaircraftoperatedatnightshallbeequippedwith— (a) alandinglight; (b) navigationorpositionlights; (c) illuminationforallflightequipmentandinstrumentsthatareessential forthesafeoperationoftheaircraft; (d) lightsinallpassengercompartments;and (e) aflashlightforeachcrewmemberstation. (2) An aircraft type certificated with aviation red or aviation white anti-collisionsystemshallbeequippedwithananti-collisionsystemoperativein both day and night and in the event of the failure of any light of theanti-collisionlightsystem,operationoftheaircraftshallcontinuetoalocationwhere repairs or replacements can be made.

Electronic navigationdatamanage-ment

Altitude reportingtransponder

Required aircraftlightsand instruments illumination

C.18

22. A person shall not operate an aircraft in commercial air transport operations unless it is equipped with — (a) twolandinglightsorasinglelighthavingtwoseparatelyenergisedfilaments; (b) ananti-collisionlightsystem; (c) illuminationforallflightequipmentandinstrumentsthatareessential forthesafeoperationoftheaircraft; (d) lightsinallpassengercompartments; (e) aflashlightforeachcrewmemberstation; (f) navigationorpositionlights; (g) lightstoconformtotheinternationalregulationsforpreventing collisionsatseaiftheaircraftisaseaplaneoranamphibianaircraft;and (h) alandinglightthatistrainable,atleastintheverticalplaneforhelicopters.

PART VII — Engine Instruments

23. (1) Unless the Authority allows or requires different instrumentation forturbineenginepoweredaeroplanestoprovideequivalentsafety,apersonshallnotoperateanypoweredaircraftunlessitisequippedwiththefollowingengineinstruments— (a) ameansforindicatingfuelquantityineachfueltanktobeused; (b) anoilpressureindicatorforeachengine; (c) anoiltemperatureindicatorforeachengine; (d) amanifoldpressureindicatorforeachengine;and (e) atachometerforeachengine. (2) Unless the Authority allows or requires different instrumentation for turbineenginepoweredaeroplanestoprovideequivalentsafety,inadditiontothelistedequipmentrequirementsundersubregulation(1),apersonshallnotoperateanypoweredaircraftunlessitisequippedwiththefollowingengineinstruments — (a) acarburettorairtemperatureindicatorforeachpistonengine; (b) acylinderheadtemperatureindicatorforeachair-cooledpistonengine; (c) afuelpressureindicatorforeachengine; (d) afuelflowmeterorfuelmixtureindicatorforeachenginenotequipped withanautomaticaltitudemixturecontrol; (e) anoilquantityindicatorforeachoil-tankwhenatransferorseparateoil reservesupplyisused; (f) anindependentfuelpressurewarningdeviceforeachengineoramaster warningdeviceforallengineswithameansforisolatingtheindividual warningcircuitsfromthemasterwarningdevice; (g) a device for each reversible propeller, to indicate to the pilot when the propellerisinreversepitch,whichcomplieswiththefollowing— (i) thedevicemaybeactuatedatanypointinthereversingcycle between the normal low pitch stop position and full reverse pitch, butitmaynotgiveanindicationatorabovethenormallow pitchstopposition;or (ii) the source of indication shall be actuated by the propeller blade angleorbedirectlyresponsivetoit.

Required air-craftlightsandinstrumentsillumination for commercial air transport operations

Engineinstruments

C.19

PART VIII — Warning Instruments and Systems

24. An aircraft with speed limitations expressed in terms of Mach number shall be equipped with a Mach number indicator.

25. Apressurisedaircraftintendedtobeoperatedatflightaltitudesabove25,000feetshallbeequippedwithadevicetoprovidepositivewarningtotheflightcrewofanydangerouslossofpressurisation.

26. (1) A powered civil aircraft with retractable landing gear shall beequippedwithalandinggearpositionindicator. (2) Anaeroplanewith retractable landinggear shall be equippedwithan auralwarningdevice that functions continuouslyunder the followingconditions — (a) foraeroplaneswithanestablishedapproachwing-flapposition,whenever thewingflapsareextendedbeyondthemaximumcertifiedapproachclimb configurationpositionintheAeroplaneFlightManualandthelandinggear isnotfullyextendedandlocked;and (b) foraeroplaneswithoutanestablishedapproachclimbwing-flapposition, wheneverthewingflapsareextendedbeyondthepositionatwhichlanding gearextensionisnormallyperformedandthelandinggearisnotfully extended and locked. (3) Thewarningsystemrequiredundersubregulation(2)— (a) maynothaveamanualshutoff; (b) shallbeinadditiontothethrottle-actuateddeviceinstalledunderthe typecertificationairworthinessrequirements;and (c) mayutiliseanypartofthethrottle-actuatedsystemincludingtheaural warningdevice. (4) Theflapposition-sensingunitreferredtoundersubregulation(2)maybe installed at any suitable place in the aeroplane. 27. (1) A person shall not operate a turbine powered aeroplane in Botswana with amaximum certified take-offmass in excess of 5,700 kg or having amaximumapprovedpassengerseatingconfigurationofmorethan9seats,ora turbojetpoweredaeroplane,unless it isequippedwithanaltitudealertingsystem capable of — (a) alertingtheflightcrewuponapproachingpreselectedaltitudeineither ascentordescent;and (b) alertingtheflightcrewbyanauralsignal,whendeviatingaboveor below a preselected altitude. (2) Foroperationsindefinedportionsofairspacewhere,basedonRegionalAirNavigationAgreement,averticalseparationminimumof300m(1000ft)is applied above FL 290, an aircraft shall be equipped with equipment which is capableofprovidinganalerttotheflightcrewwhenadeviationoccursfromtheselectedflightlevel. (3) Thethresholdforthealertreferredtoundersubregulation(2)maynotexceed ±90 m (300 ft).

Mach number indicator

Loss ofpressurisation indicator

Landinggear indicator posi-tion and aural warningdevice

Altitude alert-ingsystem

C.20

28. (1) An operator in Botswana shall not operate a turbine-poweredaeroplane, or piston-engined aeroplane of a maximum certificated take-offmassinexcessof5,700kgorauthorisedtocarrymorethan9passengers,unless it is equippedwith aGroundProximityWarningSystem thathasaforwardlookingterrainavoidancefunction. (2) AGroundProximityWarningSystemreferredtoundersubregulation(1)shall automatically provide, by means of aural signals which maybesupplementedbyvisualsignals,timelyanddistinctivewarningtotheflightcrewofthefollowingcircumstances— (a) excessivedescentrate; (b) excessiveterrainclosurerate; (c) excessivealtitudelossaftertake-offorgo-around; (d) unsafeterrainclearancewhilenotinlandingconfigurationsuchas— (i) gearnotlockeddown,or (ii) flapsnotinalandingposition;and (e) excessivedescentbelowtheinstrumentglidepath. 29. (1) A person shall not operate an aeroplane in commercial transport in an area where thunderstorms or other potentially hazardous weather conditions may be expected unless it is equipped with a weather radar. (2) A person shall not operate a helicopter in commercial air transport whencarryingpassengersinanareawherethunderstormsorotherpotentiallyhazardous weather conditions may be expected unless it is equipped with a weather radar. 30. (1) An aircraft shall be equipped with such Airborne Collision Avoidance System as may be approved by the Authority. (2) A person operating an aircraft equipped with anAirborne CollisionAvoidanceSystemshallhavethatsystemonandoperating. (3) Apersonshallnotoperateaturbineengineaeroplaneforwhichtheindividualairworthinesscertificatewasfirst issuedafter24November2005withamaximumcertificatedtake-offmassinexcessof15000kgorauthorisedtocarrymore than30passengers, unless it is equippedwith anAirborneCollision Avoidance System II. (4) Apersonshallnotoperateaturbineengineaeroplaneofamaximumcertificatedtake-offmassinexcessof5700kgbutnotexceeding15000kgorauthorisedtocarrymorethan19passengers,forwhichtheindividualairworthinesscertificatewasfirstissued after 1 January 2008 unless it is equipped with an Airborne Collision Avoidance System II. (5) A person shall not commercially operate a turbine powered aeroplane withamaximumcertificatedtake-offmassinexcessof5700kgorauthorisedtocarrymorethan19passengers,unlessitisequippedwithanAirborneCollisionAvoidance System II. (6) The Authority shall approve an Airborne Collision Avoidance System that operates in accordance with the relevant provisions of ICAO Annex 10, Volume IV.

Ground proximitywarningsystem

Weather radar

Airborne collision avoidance system

C.21

31. (1) Aturbojetaeroplaneengagedincommercialairtransportoperationswithamaximumcertificatedtake-offmassinexcessof5700kgorauthorisedtocarrymorethan9passengersshallbeequippedwithaforward-lookingwindshearwarningsystem. (2) The forward-looking wind shear warning system referred to undersubregulation(1)shallbecapableof— (a) providingthepilotwithatimelyauralandvisualwarningofwindshear ahead of the aircraft and the information required to permit the pilot to safelycommenceandcontinueamissedapproachorgo-aroundorto executeanescapemanoeuvreifnecessary;and (b) providinganindicationtothepilotwhenthelimitsspecifiedforthe certificationofautomaticlandingequipmentarebeingapproached, when such equipment is in use.

PART IX — Flight and Cockpit Voice Recorders

32. (1) Apersonshallnotoperatethefollowingaircraftunlessitisequippedwithacockpitvoicerecordercapableofrecordingtheauralenvironmentoftheflightdeckduringflighttime— (a) allcommerciallyoperatedaeroplaneswithamaximumcertificated take-offmassofover5700kg; (b) allaeroplaneswithamaximumcertificatedtake-offmassofmorethan 27000kg; (c) allcommerciallyoperatedhelicopterswithamaximumcertificated take-offmassofover3180kg;and (d) allhelicopterswithacertificatedtake-offmassofover7000kg. (2) Whereahelicopterisnotequippedwithaflightdatarecorder,atleastamain rotor speed shall be recorded on one track of the cockpit voice recorder. (3) Acockpitvoicerecorderreferredtoinsubregulation(1)shallbecapableofretainingtheinformationrecordedduringatleastthelast30minutesofitsoperationor2hours,foraeroplanesofamaximumcertificatedtake-offmassofover5700kgorthatreceivedtheirindividualcertificateofairworthinessafter 1 January 2003. 33. (1) Acockpitvoicerecordershallbecapableofrecordingonatleastfour tracks simultaneously — (a) inanin-lineformatinonedirectionifaonedirectionalconfigurationis used;or (b) inbothdirectionsifabi-directionalconfigurationisused. (2) The track allocation for a cockpit voice recorder shall be as follows — (a) Track1—co-pilotheadphonesandliveboommicrophone; (b) Track2—pilotheadphonesandliveboommicrophone; (c) Track3—areamicrophone;and (d) Track4—timereferenceplusthethirdandfourthcrewmembers’ headphone and live microphone, if applicable. (3) Topreservethecockpitvoicerecorderrecordings— (a) apersonshallnotturnoffacockpitvoicerecorderduringflighttime; (b) thecockpitvoicerecordershallbede-activateduponcompletionof flighttimefollowinganaccidentorincident;and

Forward lookingwind shear warningsystem – turbojetaeroplanes

Cockpit voice recorders

Cockpit voice recorders performance requirements

C.22

(c) followinganaccidentorincident,thecockpitvoicerecordershallnot bere-activatedbeforetheirdispositionasdeterminedinaccordance with ICAO Annex 13. (4) Tofacilitatelocationandidentificationincaseofanaccident,thecockpitvoice recorder shall — (a) beeitherbrightorangeorbrightyellow; (b) havereflectivetapeaffixedtotheexternalsurfacetofacilitateitslocation underwater; (c) haveanapprovedunderwaterlocatingdeviceonoradjacenttothe recorder, which is secured in such a manner that it is not likely to be separatedduringacrashimpactandisautomaticallyactivated;and (d) be constructed, located and installed so as to provide maximum practical protectionfortherecordingsinorderthattherecordedinformation may be preserved, recovered and transcribed. 34. (1) Apersonshallnotoperatethefollowingaircraftunlessitisequippedwithaflightdatarecorder— (a) an aeroplane in commercial air transport operations with a maximum certificatedtake-offmassofover5700kguptoandincluding27000kg forwhichtheindividualcertificateofairworthinesswasfirstissued onorafter01January1989shallbeequippedwithaTypeIIFlight DataRecorder; (b) anaeroplanewithamaximumcertificatedtake-offmassofmorethan 27000kgforwhichtheindividualcertificateofairworthinesswasfirst issued on or after 01 January 1989 shall be equipped with a Type I FlightDataRecorder; (c) a turbine powered aeroplane in commercial air transport operations withamaximumcertificatedtake-offmassofmorethan5,700kgfor whichtheindividualcertificateofairworthinesswasfirstissuedonor after 01 January 1987 but before 01 January 1989 shall be equipped withaTypeIFlightDataRecorderwhichshallrecordtime,altitude, airspeed,normalaccelerationandheading; (d) aturbinepoweredaeroplanewithamaximumcertificatedtake-off massofmorethan27000kgforwhichtheindividualcertificateof airworthinesswasfirstissuedonorafter01January1987butbefore 01 January 1989 and that are of types of which the prototype was certificatedbytheappropriatenationalauthorityafter30September 1969shallbeequippedwithaTypeIIFlightDataRecorder; (e) aturbinepoweredaeroplanewithamaximumcertificatedtake-offmass ofmorethan5,700kgforwhichtheindividualcertificateofairworthiness wasfirstissuedbefore01January1987shallbeequippedwithaTypeI FlightDataRecorderwhichshallrecordtime,altitude,airspeed,normal accelerationandheading; (f) anaeroplanewithamaximumcertificatedtake-offmassofmorethan 5,700kgforwhichtheindividualcertificateofairworthinesswasfirst issuedafter01January2005shallbeequippedwithaTypeIAFlight DataRecorder;

Flightdatarecorders

C.23

(g) a turbine powered aeroplane in commercial air transport operations withamaximumcertificatedtake-offmassof5,700kgorlessfor whichtheindividualcertificateofairworthinesswasfirstissuedonor after01January1990shallbeequippedwithaTypeIIAFlightData Recorder; (h) ahelicopterwithacertificatedtake-offmassofover7000kgshallbe equippedwithaTypeIVFlightDataRecorder;and (i) ahelicopterwithacertificatedtake-offmassofover3180kgshall beequippedwithaTypeIVAFlightDataRecorder. (2) Aflightdatarecorderreferredtoinsubregulation(1)shall— (a) be constructed, located and installed so as to provide maximum practical protectionfortherecordingsinorderthattherecordedinformationmaybe preserved,recoveredandtranscribed; (b) becalibratedasrequiredbytheAuthority; (c) haveanapproveddevicetoassistinlocatingarecorderthatmaybe underwaterandcanbeautomaticallyactivated;and (d) becapableofretainingtheinformationrecordedduringthelast— (i) 25 hours of operation, in the case of a Type I and II, (ii) 30 minutes of operation, in the case of a Type IIA, and (iii) 10hoursofoperation,inthecaseofaTypeIVandV;and (e) complywiththerequirementsspecifiedinSchedule3. (3) The followingflightdata recordermedia shall notbe acceptable foruseinaircraftregisteredinBotswana,oroperatedincommercialairtransportoperations in Botswana — (a) engravingmetalfoil; (b) photographicfilm;or (c) analoguedatausingfrequencymodulation. (4) A person shall not — (a) turnoffaflightdatarecorderduringflighttime; (b) deactivatetheflightdatarecorderuponcompletionofflighttime followinganaccidentorincident;or (c) followinganaccidentorincident,reactivatetheflightdatarecorder beforetheflightdispositionisdeterminedinaccordancewithICAO Annex 13. 35. (1) A powered aircraft that uses data link communications and is required tocarryacockpitvoicerecordershallrecordonaflightrecorderalldatalinkcommunications to and from the aeroplane. (2) Theminimumrecordingdurationshallbeequaltothedurationofthecockpit voice recorder and shall be correlated to the recorded cockpit audio. (3) Therecordingshallcontainsufficientinformationtoderivethecontentofthedatalinkcommunicationsmessageand,wheneverpractical,thetimethemessagewasdisplayedtoorgeneratedbythecrewshallberecorded.

Recordingofdata linkcommunications

C.24

PART X — Emergency, Rescue and Survival Equipment

36. EachitemofemergencyandflotationequipmentreferredtounderthisPart shall be — (a) readilyaccessibletothecrewand,withregardtoequipmentlocatedin thepassengercompartment,topassengerswithoutappreciabletimefor preparatoryprocedures; (b) clearlyidentifiedandclearlymarkedtoindicateitsmethodofoperation; (c) markedastodateoflastinspection;and (d) marked as to contents when carried in a compartment or container. 37. (1) A person shall not operate an aeroplane in Botswana unless it is equippedwiththefollowingemergencyexitequipment— (a) eachpassenger-carryinglandplaneemergencyexit(otherthanover-the- wing)thatismorethan6feetfromthegroundwiththeaeroplaneonthe groundandthelandinggearextended,shallhaveanapprovedmeansto assisttheoccupantsindescendingtotheground; (b) eachpassengeremergencyexit,itsmeansofaccess,anditsmeans ofopeningshallbeconspicuouslymarkedbyasignvisibletooccupants approachingalongthemainpassengeraisle; (c) eachpassenger-carryingaeroplaneshallhaveanemergencylighting system,independentofthemainlightingsystemthat— (i) illuminateseachpassengerexitmarkingandlocatingsign, (ii) providesenoughgenerallightinginthepassengercabin,and (iii) includesfloorproximityemergencyescapepathmarking; (d) eachpassengeremergencyexitandthemeansofopeningthatexitfrom theoutsideshallbemarkedontheoutsideoftheaeroplane; (e) eachpassenger-carryingaeroplaneshallbeequippedwithaslip-resistant escape route that meets the requirements under which that aeroplane wastypecertified;and (f) eachpassengercarryingaeroplaneshallmeetthedetailedrequirements foremergencyexitsforpassengersassetoutinSchedule4. (2) A person shall not operate a helicopter certificatedwith amaximumtake-offmassof3180kgorlessandnineorlesspassengerseatsunlessitisequippedwiththefollowingemergencyexitequipment— (a) atleastoneemergencyexitoneachsideofthecabinreadilyaccessible toeachpassengerandoneoftheseexitsshallbeusableinanyprobable attitudethatmayresultfromacrash; (b) doorsintendedfornormalusemayalsoserveasemergencyexits, providedthattheymeettherequirementsofthisregulation;and (c) ifemergencyflotationdevicesareinstalled,thereshallbeanemergency exitaccessibletoeachpassengeroneachsideofthecabinthatisshown by test, demonstration, or analysis to — (i) be above the waterline, and (ii) beopenwithoutinterferencefromflotationdevices,whether stowed or deployed.

Emergencyequipment – all aircraft

Emergencyexit equipment –passengers

C.25

(3) Eachemergencyexitspecifiedundersubsection(1)shall— (a) consist of a movable window or panel, or additional external door, providinganunobstructedopeningthatcanadmita19-by26-inch ellipse; (b) havesimpleandobviousmethodsofopening,fromtheinsideandfrom theoutside,whichdonotrequireexceptionaleffort; (c) bearrangedandmarkedsoastobereadilylocatedandopenedevenin darkness;and (d) bereasonablyprotectedfromjammingbyfuselagedeformation. (4) A person shall not operate a helicopter certificatedwith amaximumtake-offmassofmorethan9072kgand10ormorepassengerseatsunlessitisequippedwiththefollowingemergencyexitequipment— (a) TypeIexit:thistypeshallhavearectangularopeningofnotlessthan 24incheswideby48incheshigh,withcornerradiinotgreaterthan one-thirdthewidthoftheexit,inthepassengerareainthesideofthe fuselageatfloorlevelandasfarawayaspracticablefromareasthat mightbecomepotentialfirehazardsinacrash; (b) TypeIIexit:thistypeisthesameasTypeIexceptthattheopeningshall beatleast20incheswideby44incheshigh; (c) TypeIIIexit:thistypeisthesameasTypeIexceptthattheopening shallbeatleast20incheswideby36incheshighandtheexitneednot beatfloorlevel;and (d) TypeIVexit:thistypeshallhavearectangularopeningofnotlessthan 19incheswideby26incheshigh,withcornerradiinotgreaterthanone- thirdthewidthoftheexit,inthesideofthefuselagewithastep-up inside the rotorcraft of not more than 29 inches. (5) Emergency exits shall be accessible to all passengers and except asprovidedinregulation38(2),shallbeprovidedforassetoutinSchedule5. (6) Inadditiontotherequirementssetoutinsubregulation(5),thereshallbeenoughopeningsinthetop,bottomorendsofthefuselagetoallowevacuationwith the rotorcraft on its side. 38. (1) Wherecertificationwithditchingprovisionsisrequested,themarkingsrequiredunderregulation37shallbedesignedtoremainvisibleiftherotorcraftiscapsizedandthecabinissubmerged. (2) Whereahelicopterwascertificatedwithditchingprovisions,ditchingemergencyexitsshallbeprovidedinaccordancewiththefollowing— (a) forrotorcraftthathaveapassengerseatingconfiguration,excluding pilots seats, of 9 seats or less, one exit above the waterline in each side oftherotorcraft,meetingatleastthedimensionsofaTypeIVexit; (b) forrotorcraftthathaveapassengerseatingconfiguration,excluding pilots seats, of 10 seats or more, one exit above the waterline in a side oftherotorcraftmeetingatleastthedimensionsofaTypeIIIexit, foreachunit(orpartofaunit)of35passengerseats,butnolessthan twosuchexitsinthepassengercabin,withoneoneachsideofthe rotorcraft;and (c) flotationdevices,whetherstowedordeployed,maynotinterferewith or obstruct the exits.

Ditchingemergencyexits for passengers

C.26

39. One Type I exit only, or one Type II exit only, that is required in the side ofthefuselagereferredtounderregulation37maybeinstalledinsteadintherampoffloorramprotorcraftif— (a) itsinstallationinthesideofthefuselageisimpractical;and (b) itsinstallationintherampmeetsemergencyexitaccessrequirements specifiedinregulation43. 40. (1) Anemergencyexitofanaircraftshallconsistofamovabledoororhatchintheexternalwallsofthefuselageandshallprovideanunobstructedopeningtotheoutside. (2) Anemergencyexitshallbecapableofbeingopenedfromtheinsideandfrom the outside. (3) Themeansofopeningeachemergencyexitshallbesimple,obviousandnot require exceptional effort. (4) Thereshallbemeansforlockingeachemergencyexitandforpreventingopeninginflightinadvertentlyorasaresultofmechanicalfailure. (5) Thereshallbemeanstominimisetheprobabilityofthejammingofanyemergencyexitinaminorcrashlandingasaresultoffuselagedeformation. (6) Except as provided in these Regulations, each land-based rotorcraftemergencyexitshallhaveanapprovedslideoritsequivalent,toassistoccupantsindescendingtothegroundfromeachfloorlevelexitandanapprovedrope,orits equivalent, for all other exits, if the exit threshold is more that 6 feet above theground— (a) withtherotorcraftonthegroundandwiththelandinggearextended; (b) withoneormorelegsorpartofthelandinggearcollapsed,broken,or notextended;and (c) withtherotorcraftrestingonitsside,providedthiswasaccomplished duringtheemergencyevacuationtestduringtypecertificationofthe helicopter. (7) Theslideforeachpassengeremergencyexitshallbeaself-supportingslideorequivalent,andshallbedesignedtomeetthefollowingrequirements— (a) aslideshallbeautomaticallydeployedandthedeploymentshallbegin duringtheintervalbetweenthetimetheexitopeningmeansisactuated from inside the rotorcraft and the time the exit is fully opened and where apassengeremergencyexitisalsoapassengerentrancedoororservice door, it shall be provided with means to prevent deployment of the slide whentheexitisopenedfromeithertheinsideortheoutsideundernon- emergencyconditionsfornormaluse; (b) a slide shall be automatically erected within 10 seconds after deployment isbegun; (c) aslideshallbeofsuchlengthafterfulldeploymentsuchthatthelower endisselfsupportingonthegroundandprovidessafeevacuationof occupantstothegroundaftercollapseofoneormorelegsorpartofthe landinggear;and (d) a slide shall have the capacity, in 25 knot winds directed from the most criticalangle,todeployand,withtheassistanceofonlyoneperson to remain usable after full deployment to evacuate occupants safely to theground.

Ramp exits

Emergencyexit arrangement

C.27

(8) Ahelicopterwhichhas30orfewerpassengerseatsandhasanexitthresholdmorethan6feetabovetheground,mayhavearopeorotherassistmeansusedinplaceof the slide referred tounder subregulation (7),provided thiswasaccomplishedduringtheemergencyevacuationtestduringtypecertificationofthe helicopter. (9) Wherearope,withitsattachment,isusedforcompliancewithsubregulations(6) and (8) it shall be able to — (a) withstanda400poundstaticload;and (b) attachtothefuselagestructureatorabovethetopoftheemergencyexit opening,oratanotherapprovedlocationifthestowedropewouldreduce thepilot’sviewinflight. 41. (1) Apassengeremergencyexitofanaircraft,itsmeansofaccess,anditsmeansofopeningshallbeconspicuouslymarkedfortheguidanceofoccupantsusingtheexitsindaylightorinthedark. (2) Themarkingsof anemergencyexitof anaircraft shallbedesigned toremainvisible for rotorcraftequippedforoverwaterflights if the rotorcraft iscapsizedandthecabinissubmerged. (3) Theidentityandlocationofeachpassengeremergencyexitshallberecognisablefromadistanceequaltothewidthofthecabin. (4) Thelocationofeachpassengeremergencyexitshallbeindicatedbyasign visible to occupants approaching along themain passenger aisle and alocatingsign— (a) nexttoorabovetheaisleneareachflooremergencyexit,exceptthatone signmayservetwoexitsifbothexistscanbeseenreadilyfromthatsign;and (b) oneachbulkheadordividerthatpreventsforeandaftvisionalongthe passengercabin,toindicateemergencyexitsbeyondandobscuredby it,exceptthatifthisisnotpossiblethesignmaybeplacedatanother appropriate location. (5) Theemergencyexitmarkings specifiedunder subregulations (1) to (4)shall apply in addition to those requirements set out in Part II of Schedule 4. 42. (1) Asourceoflightwithitspowersupplyindependentofthemainlightingsystem shall be installed in an aircraft to — (a) illuminateeachpassengeremergencyexitmarkingandlocatingsign;and (b) provideenoughgenerallightinginthepassengercabinsothatthe averageillumination,whenmeasuredat40-inchintervalsatseatarmrest heightonthecenterlineofthemainpassengeraisle,isatleast0.05foot-candle. (2) Exterior emergency lighting of an aircraft shall be provided at eachemergencyexitandtheexterioremergencylightingmaybeprovidedbyeitherinterior or exterior sourceswith light intensitymeasurementsmadewith theemergencyexitsopen. (3) Eachlightrequiredundersubregulation(1)or(2)shallbeoperablemanuallyfromthecockpitstationandfromapointinthepassengercompartmentthatisreadilyaccessible. (4) The cockpit control device shall have an “on”, “off” and “armed” position sothatwhenturnedonatthecockpitorpassengercompartmentstationorwhenarmedatthecockpitstation,theemergencylightswilleitherilluminateorremainilluminateduponinterruptionoftherotorcraft’snormalelectricpower. (5) Anymeansrequiredtoassisttheoccupantsindescendingtothegroundshall be illuminated so that the erected assist means is visible from the rotorcraft.

Emergencyexitmarking

Emergencylighting

C.28

43. (1) Apassagewaybetweenpassengercompartments,andeachpassagewayleadingtoTypeIandTypeIIemergencyexitsinanaircraftshallbe— (a) unobstructed;and (b) at least 20 inches wide. (2) Thereshallbeenoughspaceadjacenttoanemergencyexittoallowacrewmembertoassist in theevacuationofpassengerswithoutreducingtheunobstructedwidthofthepassagewaybelowthatrequiredforthatexit. (3) There shall be access from each aisle to each Type III and Type IV exit, so that — (a) forrotorcraftthathaveapassengerseatingconfigurationof20ormore, excludingpilotseats,theprojectedopeningoftheexitprovidedshall notbeobstructedbyseats,berths,orotherprotrusions,includingseatbacks in any position, for a distance from that exit of not less than the width of thenarrowestpassengerseatinstalledontherotorcraft;and (b) forrotorcraftthathaveapassengerseatingconfigurationof19orless, excludingpilotseats,theremaybeminorobstructionsintheregion describedinparagraph(a)iftherearecompensatingfactorstomaintain the effectiveness of the exit. 44. Themainpassengeraislewidthbetweenseatsofanaircraftshallbeasset out in Schedule 6.

45. A person shall not operate an aircraft over water or across land areas whichhavebeendesignatedby theAuthority as areas inwhich search andrescueisdifficultunlesstheaircraftisequippedwithsuchsignallingdevicesasmaybeappropriatetotheareaoverflown,toinclude— (a) atleastonepyrotechnicsignallingdeviceforeachliferaftrequiredfor overwateroperations;and (b) anyotherrequirementsspecifiedbytheAuthority. 46. A person shall not operate an aircraft across land areas which have been designatedby theAuthorityasareas inwhich searchand rescue isdifficultunless theaircraft isequippedwithenoughsurvivalkits for thenumberofoccupantsoftheaeroplaneappropriatefortheroutetobeflown. 47. (1) A person shall not operate an aeroplane for commercial air transport unlessitisequippedwithemergencylocatortransmitterequipmentasfollows— (a) anaeroplaneauthorisedtocarrymorethan19passengersshallbe equippedwithatleastoneautomaticELTortwoELTsofanytype; (b) anaeroplaneauthorisedtocarrymorethan19passengersforwhichthe individualcertificateofairworthinesswasfirstissuedafter1July2008 shallbeequippedwithatleasttwoELTs,oneofwhichshallbeautomatic; (c) anaeroplaneauthorisedtocarry19passengersorlessforwhichthe individualcertificateofairworthinessisfirstissuedafter1July2008 shallbeequippedwithatleastoneautomaticELT; (d) exceptasprovidedforunderparagraph(c), from 1 July 2008, an aeroplane authorisedtocarry19passengersorlessshallbeequippedwithatleastone ELTofanytype;and (e) atleastonesurvivaltypeELTshallbelocatedwitheachlife-raftcarried.

Emergencyexit access

Main aisle width

Visual signallingdevices

Survival kits

Emergencylocator trans-mitter

C.29

(2) A person shall not operate a helicopter unless it is equipped with emergencylocatortransmitterequipmentasfollows— (a) ahelicopteroperatinginperformanceClass1and2shallbeequipped withatleastoneautomaticELTand,whenoperatingonflightsoverwater, withatleastoneautomaticELTandoneELTinaraftorlifejacket;and (b) ahelicopteroperatinginperformanceClass3shallbeequippedwithat leastoneautomaticELTand,whenoperatingonflightsoverwater,with atleastoneautomaticELTandoneELTinaraftorlifejacket. (3) Apersonshallnotoperateanaeroplaneforgeneralaviationpurposesunlessitisequippedwithemergencylocatortransmitterequipmentasfollows— (a) anaeroplaneshallbeequippedwithatleastoneELTofanytype;and (b) anaeroplaneforwhichtheindividualcertificateofairworthinessisfirst issued after 1 July 2008 shall be equipped with at least one automatic ELT. (4) AnyELTequipmentcarriedonanaeroplaneinaccordancewithsubregulation(1)and(3)shallbecapableoftransmittingonthefrequencies121.5MHzand406MHz simultaneously. (5) ThemannerinwhichtheELTsshallberegistered,carried,thespecificationsto which they shall adhere, the frequencies on which they shall be able to transmit and the manner in which they are to be maintained shall be as set out in Schedule 7. 48. (1) A person shall not operate an aircraft unless it is equipped with portablefire extinguishers of a typewhich,whendischarged, doesnot causedangerouscontaminationoftheairwithintheaircraft. (2) Atleastoneportablefireextinguishershallbelocatedin— (a) thepilot’scompartment;and (b) eachpassengercompartmentthatisseparatefromthepilot’scompartment andnotreadilyaccessibletotheflightcrew. (3) A person shall not operate an aircraft unless it is equipped with portable fireextinguishersaccessibleforuseincrew,passenger,andcargocompartmentsas follows — (a) thetypeandquantityofextinguishingagentshallbesuitableforthekinds offireslikelytooccurinthecompartmentwheretheextinguisheris intendedtobeused; (b) atleastoneportablefireextinguishershallbeprovidedandconveniently locatedforuseineachClassEcargocompartmentwhichisaccessibleto crewmembersduringflight,andatleastoneshallbelocatedineach upperandlowerlobegalley; (c) atleastoneportablefireextinguishershallbeconvenientlylocatedonthe flightdeckforusebytheflightcrew; (d) atleastoneportablefireextinguishershallbeconvenientlylocatedinthe passengercompartmentifthepassengercompartmentisseparatefrom theflightdeckandnotreadilyaccessibletotheflightcrew;and (e) foreachaeroplanehavingapassengerseatingcapacityofmorethan30, thereshallbeatleastanumberofportablefireextinguishersassetout in Schedule 8 which shall be conveniently located and uniformly distributed throughoutthecompartment.

Portablefireextinguishers

C.30

49. (1) Aperson shall not operate a passenger-carrying transport categoryaeroplaneunlesseachlavatoryintheaeroplaneisequippedwithabuilt-infireextinguisher for each disposal receptacle for towels, paper, or waste locatedwithin the lavatory. (2) Abuilt-inlavatoryfireextinguisherreferredtoinsubregulation(1)shallbedesignedtodischargeautomaticallyintoeachdisposalreceptacleuponoccurrenceofafireinthereceptacle. 50. Apersonshallnotoperateapassenger-carryingtransportcategoryaeroplaneunless each lavatory in the aeroplane is equipped with a smoke detector system or equivalent that provides — (a) awarninglightinthecockpit;or (b) awarninglightoraudiowarninginthepassengercabinwhichisreadily detectedbyacabincrewmember,takingintoconsiderationthepositioningof cabincrewmembersthroughoutthepassengercompartmentduringvarious phasesofflight. 51. Apersonshallnotoperateanaeroplanecertificatedwithatake-offmassof5700kgormoreunlessitisequippedwithacrashaxeappropriateforeffectiveuse in that typeofaeroplane,storedinaplacenotvisible topassengersontheaeroplane. 52. Whereareasofthefuselagesuitableforbreak-inbyrescuecrewsinanemergencyaremarkedonanaeroplane,suchareasshallbemarkedassetoutinSchedule 9. 53. (1) A person shall not operate an aircraft unless it is equipped with an accessible,approvedfirst-aidkitwithmedicalsuppliesadequatetothenumberofpassengerstheaircraftisauthorisedtocarry. (2) Thetype,number,locationandcontentsoffirst-aidkitstobecarriedinanaircraftreferredtoinsubregulation(1)shallbeassetoutinSchedule10. 54. (1) Aperson shall not operate a passengerflight in an aeroplanewith30seatsormoreunlesstheaeroplaneisequippedwithanapprovedemergencymedicalkit for treatmentof injuriesormedicalemergencies thatmightoccurduringflighttimeorinminoraccidents. (2) Thelocationandcontentsofemergencymedicalkitstobecarriedinanaircraftreferredtoinsubregulation(1)shallbeassetoutinSchedule11. 55. (1) Anaircraftintendedtobeoperatedataltitudesrequiringtheuseofsupplemental oxygen shall be equippedwith adequate oxygen storage anddispensingapparatus. (2) Theoxygenstorageanddispensingapparatus,theminimumrateofoxygenflow,andthesupplyofoxygenshallmeetapplicableairworthinessstandardsfortypecertificationinthetransportcategoryassetoutinSchedule12. (3) A person shall not operate an aircraft at altitudes above 10,000 feet unless itisequippedwithoxygenmasks,locatedsoastobewithintheimmediatereachofflightcrewmemberswhileattheirassigneddutystation. (4) A person shall not operate a pressurised aeroplane at altitudes above 25,000 feet unless — (a) flightcrewmemberoxygenmasksareavailableattheflightdutystation andareofaquickdonningtype;and (b) sufficientspareoutletsandmasksorsufficientportableoxygenunitswith masksaredistributedevenlythroughoutthecabintoensureimmediate availabilityofoxygentoeachrequiredcabincrewmemberregardlessof his or her location at the time of cabin pressurisation failure.

Lavatoryfireextinguisher

Lavatory smoke detector

Crash axe

Markingofbreak-inpoints

First-aidkit

Emergencymedical kit — aeroplanes

Oxygenstorageanddispensingapparatus

C.31

(5) Anoxygen-dispensingunitconnected tooxygensupplymasksshallbeinstalled so as to be immediately available to each occupant, wherever seated. (6) Thetotalnumberofoxygendispensingunitsandoxygensupplyterminalsshallexceedthenumberofseatsbyatleast10%andtheextraoxygenportableunitsaretobeevenlydistributedthroughoutthecabin. (7) Theamountofsupplementaloxygenforsustenancerequiredforaparticularoperationshallbedeterminedonthebasisofflightaltitudesandflightduration,consistentwith the operating procedures established for eachoperation in theOperationsManualandwith theroutes to beflown, andwith the emergencyproceduresspecifiedintheOperationsManual. 56. (1) Anyairoperatorcertificateholdershallnotoperateanaeroplanewithamaximumcertifiedtake-offmassexceeding5700kgorhavingamaximumapprovedseatingconfigurationofmorethan19seatsunlessitisequippedwith— (a) protectivebreathingequipment(PBE)toprotecttheeyes,noseandmouth ofeachflightcrewmemberwhileonflightdeckdutyandtoprovideoxygen foraperiodofnotlessthan15minutes;and (b) sufficientportableprotectivebreathingequipment(PBE)toprotectthe eyes, nose and mouth of all required cabin crew members and to provide breathinggasforaperiodofnotlessthan15minutes. (2) Theoxygensupplyforprotectivebreathingequipment(PBE)inanaircraftmaybeprovidedbytherequiredsupplementaloxygensystem. (3) Theprotectivebreathingequipment(PBE)intendedforflightcrewmember’suse shall — (a) beconvenientlylocatedontheflightdeck;and (b) beeasilyaccessibleforimmediateusebyeachrequiredflightcrewmember attheirassigneddutystation. (4) The protective breathing equipment (PBE) intended for cabin crewmember’suseshallbeinstalledadjacenttoeachrequiredcabincrewmemberdutystation. (5) Inanyaeroplane,easilyaccessibleportableprotectivebreathingequipment(PBE) shall be provided and located at or adjacent to the requiredhandfireextinguishersexcept that,where thefireextinguisher is located insideacargocompartment,theprotectivebreathingequipment(PBE)shallbestowedoutsidebutadjacenttotheentrancetothatcompartment. (6) Theprotectivebreathingequipment(PBE)inanaeroplaneshall,whileinuse, not prevent any required communication. 57. (1) Anairoperatorcertificateholdershallnotconductapassengercarryingoperation in a pressurised aeroplane at altitudes above 25,000 feet, when a cabin crew member is required to be carried, unless the aeroplane is equipped with — (a) undilutedfirst-aidoxygenforpassengerswho,forphysiologicalreasons, mayrequireoxygenfollowingacabindepressurisation;and (b) asufficientnumberofoxygendispensingunits,butinnocaselessthan two, with a means for cabin crew members to use the supply. (2) Theamountoffirst-aidoxygenrequiredforanoperationreferred to insubregulation(1)(a) shall be determined on the basis of — (a) flightdurationaftercabindepressurisationatcabinaltitudesofmorethan 8,000feet; (b) anaverageflowrateofatleast3litresStandardTemperaturePressureDry perminuteperperson;and (c) atleast2%ofthepassengerscarried,butinnocaseforlessthanoneperson.

Protective breathingequipment

First-aidoxygendispensingunits

C.32

(3) Theamountoffirst-aidoxygenrequiredforanoperationreferredtoinsubregulation(1)shallbedeterminedonthebasisofcabinpressurealtitudesandflightduration, consistentwith theoperatingproceduresestablished foreach operation and route. (4) Theoxygenequipmentreferredtoinsubregulation(1)shallbecapableofgeneratingamassflowtoeachuserofatleast4litresperminute,StandardTemperaturePressureDryandmeansmaybeprovidedtodecreasetheflowtonot less than 2 litres per minutes, at a Standard Temperature Pressure Dry at any altitude. 58. (1) Anairoperatorcertificateholdershallequipanaeroplanewithaportablebattery-poweredmegaphoneormegaphonesreadilyaccessibletothecrewmembersassignedtodirectemergencyevacuation. (2) Thenumberandlocationofmegaphonesrequiredundersubregulation(1) shall be determined as follows — (a) onaeroplaneswithaseatingcapacityofmorethan60andlessthan 100passengers,onemegaphoneshallbelocatedatthemostrearward locationinthepassengercabinwhereitwouldbereadilyaccessibleto anormalcabincrewmemberseat; (b) onaeroplaneswithaseatingcapacityofmorethan99passengers,two megaphonesinthepassengercabinoneachaeroplaneoneinstalledat the forward end and the other at the most rearward location where it wouldbereadilyaccessibletoanormalcabincrewmemberseat;and (c) foraeroplaneswithmorethanonepassengerdeck,inallcaseswhen thetotalpassengerseatingconfigurationofadeckismorethan60,at leastonemegaphoneisrequiredonthedeck. 59. (1) Landplanes shallbeequippedwithone life-jacketor equivalentflotationdeviceequippedwithameansofelectricilluminationforeachpersonon board, stowed in a position easily accessible from the seat or berth of the person for whose use it is provided — (a) whenflyingen-routeoverwaterbeyondglidingdistancefromtheshore; (b) whenflyingoverwateratadistanceofmorethan93km(50NM)away fromtheshoreforaircraftcapableofmaintainingsafealtitudeafterthe failureofoneenginefortwo-engineaircraftandthefailureoftwoengines forthreeorfour-engineaircraft;or (c) whentakingofforlandingatanaerodromewheretheStateofthe Operator has determined the take off or approach path is so disposed over water that in the event of a mishap there would be a likelihood of ditching. (2) Allseaplanesforallflightsshallbeequippedwith— (a) onelife-jacket,orequivalentindividualflotationDevice,foreachperson on board, stowed in a position easily accessible from the seat or berth of the personforwhoseuseitisprovided; (b) equipmentformakingthesoundsignalsprescribedintheInternational RegulationsforpreventingCollisionsatSea,whereapplicable;and (c) oneseaanchor(drogue).

Megaphones

Individual flotationdevices

C.33

60. (1) Inadditiontotheequipmentspecifiedunderregulations59and61,thefollowingshallbeequippedwithlifesavingraftsinsufficientnumberstocarryall persons on board — (a) aeroplanesoperatedonlongrangeover-waterflights; (b) all other aeroplanes when they are operated over water away from land suitableformakinganemergencylandingatadistanceofmorethan 185km(100NM)inthecaseofsingle-engineaeroplanes,andmorethan 370km(200NM)inthecaseofmulti-engineaeroplanescapableof continuingflightwithoneengineinoperative; (c) class 1 and 2 helicopters when they are operated over water at a distance fromlandcorrespondingtomorethan10minutesatnormalcruisespeed;and (d) class 3 helicopters when they are operated over water beyond autorotational orsafeforcedlandingdistancefromland. (2) Anaircraft shallbeequipped with lifesavingraftswithasufficientcapacity to carry all persons on board in the event of the loss of one raft of the largestcapacity. (3) All life saving rafts referred to under subregulation (1) and (2) shall bestowedsoastofacilitatetheirreadyuseinanemergencyandshallbeequippedwiththefollowinglifesustainingequipment— (a) anelectricsurvivorlocatorlight; (b) asurvivalkit; (c) apyrotechnicsignallingdevice;and (d) an ELT. (4) Inhelicopters,lifesavingraftswhicharenotdeployablebyremotecontrolandwhichhaveamassofmorethan40kgshallbeequippedwithameansofmechanically assisted deployment. 61. Ahelicopterflyingoverwater at a distance from land corresponding tomore than 10 minutes at normal cruise speed in the case of performance Class 1or2 helicopters, orflyingoverwater beyond autorotationalor safe forcedlandingdistancefromlandinthecaseofperformanceClass3helicopters,shallbeequippedwithapermanentorrapidlydeployablemeansoffloatationsoastoensureasafeditchingofthehelicopter.

PART XI — Miscellaneous Systems and Equipment

62. Anaircraftusedinpassengercarryingoperationsshallbeequippedwiththefollowingseats,safetybelts,andshoulderharnessesthatmeettheairworthinessrequirementsfortypecertificationofthataircraft— (a) aseatwithsafetybeltforeachpersononboardover2yearsofage;anda restrainingbeltforeachberthonboardtheaircraft; (b) asafetyharnessforeachflightcrewmemberseat; (c) a safety harness for each pilot seat which — (i) shall incorporate a device which can automatically restrain the occupant’storsointheeventofrapiddeceleration, (ii) includes shoulder straps and a seat belt with a device to prevent an incapacitatedpilotfrominterferingwiththeflightcontrols; (d) aforwardorrearwardfacing(within15degreesofthelongitudinalaxis of the aeroplane) seat equipped with a safety harness for each cabin crew memberstationinthepassengercompartment;and (e) thecabincrewmember’sseatsshallbelocatednearfloorlevelandother emergencyexitsasrequiredbytheAuthorityforemergencyevacuation.

Seats, safety belts and shoulder har-nesses

Flotation device forchelicopter ditching

Life rafts

C.34

63. (1) Apersonshallnotoperateapassengercarryingaeroplaneofamaximumcertificatedtake-offmassinexcessof45000kgorwithapassengerseatingcapacitygreaterthan60unlessthataircraftisequippedwithanapprovedflightcrewcompartmentdoorthatisdesignedtoresistpenetrationbysmallarmsfireandgrenadeshrapnel,andtoresistforcibleintrusionsbyunauthorisedpersons. (2) Apersonshallnotoperateapassengercarryingaeroplanehavingacertificatedtakeoffmassoflessthan45000kgorwithapassengerseatingcapacityoflessthan60unlessthataircraftisequippedwithanapprovedflightcrewcompartmentdoor,wherepracticable,thatisdesignedtoresistpenetrationbysmallarmsfireandgrenadeshrapnel,andtoresistforcibleintrusionsbyunauthorisedpersons. (3) Apilotcompartmentdoorshallbecapableofbeinglockedandunlockedfromeitherpilot’sstation. (4) Anoperatorshallequipanaeroplanewithameansformonitoringfromthepilot station the entire door area outside the pilot compartment to identify persons requestingentryandtodetectsuspiciousbehaviourorpotentialthreat. (5) Anoperatorshallequipanaeroplanewithapassengercompartmentdoordesignedtohave— (a) ameansforacrewmember,inanemergency,tounlockeachdoorthat leadstoacompartmentthatisnormallyaccessibletopassengersandthat canbelockedbypassengers; (b) aplacardoneachdoorusedtoaccessarequiredpassengeremergencyexit, indicatingthatsuchdoorshallbeopenduringtake-offandlanding;and (c) a means readily available for each crew member to unlock any door that separatesapassengercompartmentfromanothercompartmentthathas emergencyexitprovisions. 64. (1) Subjecttosubregulation(2),apersonshallnotoperateasignspassengercarryingaeroplanewithamaximumcertificatedtake-offweightof5,700kgormore unless it is equipped with — (a) atleastonepassengerinformationsign(usingeitherlettersorsymbols) notifyingwhensmokingisprohibitedandonesign(usingeitherlettersor symbols)notifyingwhensafetybeltsshouldbefastened,whichshall, whenilluminated,belegibletoeachpersonseatedinthepassengercabin underallprobableconditionsofcabinillumination; (b) signswhichnotifywhensafetybeltsshouldbefastenedandwhensmoking isprohibitedshallbesoconstructedthatthecrewcanturnthemonandoff;and (c) asignorplacardaffixedtoeachforwardbulkheadandeachpassengerseat back that reads “Fasten Seat Belt While Seated”. (2) Notwithstandingsubregulation(1),apersonshallnotoperateanaircraftinwhichallpassengerseatsarenotvisiblefromtheflightdeck,unless it isequippedwithameansofindicatingtoallpassengersandcabincrewmemberswhenseatbeltsshallbefastenedandwhensmokingisnotallowed. 65. (1) A person shall not operate an aircraft unless each compartment used bythecreworpassengersisequippedwiththefollowingrequirementsoftheStateofDesign— (a) materialsshallbeatleastflashresistant; (b) thewallandceilingliningsandthecoveringofupholstering,floorsand furnishingsshallbeflameresistant;

Pilot and passengercompartment doors –aeroplanes

Passengerinformation signs

Materials for cabin interiors, cargoandbaggagecompartments

C.35

(c) eachcompartmentwheresmokingistobeallowedshallbeequippedwith self-containedashtraysthatarecompletelyremovableandothercompartments shallbeplacardedagainstsmoking;and (d) eachreceptacleforusedtowels,papersandwastesshallbeoffire-resistant materialandhaveacoverorothermeansofcontainingpossiblefiresstarted in the receptacles. (2) Acargocompartmentshallbeequippedwithceilingandsidewalllinerpanelswhichareconstructedofmaterialswhichmeet thetestrequirementsforflameresistanceofcargocompartmentlinersasspecifiedfortypecertification. (3) ForaircraftforwhichtheStateofDesignhasdevelopednewairworthinessrequirementsforcabininteriorssinceoriginaltypecertification,theowneroftheaircraft shall ensure that allmaterials thatdonotmeet currentStateofDesignrequirement refurbishingof the cabin interiorwithmaterials thatcomplywithsubregulation(1)and(2). 66. (1) Anairoperatorcertificateholdershallnotoperateanaeroplaneunlessit is equipped with — (a) a power supply and distribution system that meets the airworthiness requirementsforcertificationofanaeroplaneinthetransportcategory,as specifiedbytheAuthority; (b) a power supply and distribution system that is able to produce and distribute the load for the required instruments and equipment, with use of an auxiliary power supply if any one power source or component of the power distribution systemfails;or (c) ameansforindicatingtheadequacyofthepowerbeingsuppliedtorequired flightinstruments. (2) Allengine-drivensourcesofenergy,whenused,shallmakeprovisionforback-upinemergencies. 67. A person shall not operate an aeroplane in which protective fuses are installedunlesstherearesparefusesavailableofappropriateratingsforreplacementofthoseaccessibleinflight. 68. (1) Apersonshallnotoperateanaircraftinexpectedoractualicingconditionsunlessitisequippedforthepreventionorremovaloficeonwindshields,wings,controlsurfaces,empennage,propellers,rotorblades,orotherpartsoftheaircraftwhereiceformation will adversely affect the safety of the aircraft. (2) Apersonshallnotoperateanaircraftinexpectedoractualicingconditionsatnightunlessitisequippedwithameanstoilluminateordetecttheformationof ice. (3) Anyilluminationreferredtoundersubregulation(2)shallbeofatypethatwillnotcauseglareorreflectionthatwouldhandicapcrewmembersintheperformanceof their duties. 69. (1) Apersonshallnotoperateanaircraftininstrumentflightconditionsunless it is equipped with a pitot heat system. (2) Anairoperatorcertificateholdershallnotoperateanaeroplaneequippedwithaflightinstrumentpitotheatingsystemunlesstheaeroplaneisalsoequippedwithanoperablepitotheat indicationsystemthatcomplieswiththefollowingrequirements — (a) theindicationincorporatesanamberlightthatisinclearviewofaflight crewmember;

Power supply, distribution and indication system

Protective circuit fuses

Icingprotection equipment

Pitot heat and indication systems

C.36

(b) theindicationisdesignedtoalerttheflightcrewmembersif— (i) thepitotheatingsystemisswitched“off”,and (ii) thepitotheatingsystemisswitched“on”andanypitottubeheating elementisinoperative;or (c) anintegratedflightcrewalertingsystemthatwillnotifythecrewifthe pitotsystemismalfunctioning. 70. (1) A person shall not operate an aircraft unless it is equipped with a static pressure system vented to the outside atmospheric pressure so that they will be leastaffectedbyairflowvariationormoistureorotherforeignmatter,andinstalledsoastobeairtightexceptforthevent. (2) ApersonshallnotoperateanaircraftinIFRorVFRatnightunlessitisequipped with a static pressure system vented to the outside atmospheric pressure sothattheywillbeleastaffectedbyairflowvariationormoistureorotherforeignmatter,andinstalledsoastobeairtightexceptfortheventandameansofselectingan alternative source of static pressure. (3) A person shall not operate an aircraft unless it is equipped with two independent static pressure systems, vented to the outside atmospheric pressure sothattheywillbeleastaffectedbyairflowvariationormoistureorotherforeignmatter,andinstalledsoastobeairtightexceptforthevent. 71. Anairoperatorcertificateholdershallnotoperateanaeroplanewithamaximumcertifiedtake-offmassofmorethan5700kgunlessitisequippedateachpilotstationwith a windshield wiper or equivalent means to maintain a clear portion of the windshield duringprecipitation. 72. A person shall not operate an aeroplane in commercial air transport operationsundersinglepilotIFRoratnightunlesstheaeroplaneisequippedwitha chart holder installed in an easily readable position that can be illuminated for nightoperations. 73. (1) A person shall not operate an aeroplane in commercial air transport operations in an aeroplane intended to be operated above 15000 m unless it is equipped with — (a) an instrument to measure and indicate continuously the dose rate of total cosmicradiationbeingreceivedandthecumulativedoseoneachflight;or (b) asystemofon-boardquarterlyradiationsamplingacceptabletotheAuthority. 74. (1) Anypersonwhooperatesanaircraftwhichisnotfittedwiththeequipmentorinstrumentsrequiredundertheseregulationscommitsanoffenceandisliable,forafirstoffencetoafinenotexceedingP15000,ortoimprisonmenttoatermnotexceeding3years,forasecondoffencetoafinenotexceedingP20000,ortoimprisonmenttoatermnotexceeding4yearsandforasubsequentoffencetoafinenotexceedingP30000,ortoimprisonmentforatermnotexceeding6years. (2) Whereanoffenceundersubregulation(1)iscommittedbyabodycorporatethefineshallnotexceedP50000forafirstoffence,P100000forasecondoffenceand P150 000 for any subsequent offence. (3) Any person who — (a) hinders or obstructs a person authorised by the Authority in the exercise of hisorherpowersortheperformanceofhisorherduties;

Static pressure system

Windshield wipers

Chart holder

Cosmic radiation detection equipment

Offences and penalties

C.37

(b) makesorcausestobemade,eitherorallyorinwriting— (i) anyfraudulent,misleadingorfalsestatementforthepurposeof obtaininganyrating,approval,authorisationorotherdocumentin termsoftheseRegulations, (ii) anyfraudulent,misleadingorfalseentryinanylogbook,recordor report which is required to be kept, maintained, made or used to showcompliancewithanyprovisionoftheseRegulations; (c) falsifies,counterfeits,alters,defacesormutilates,oraddsanythingto,any rating,approval,authorisationorotherdocumentissuedintermsofthese Regulations;or (d) does or causes, or permits to be done or caused, any act contrary to, or whofailstocomplywithanyprovisionoftheseRegulations,oradirection givenoraprohibitionmadeoraconditionimposedintermsthereof,commitsanoffenceandisliabletoafinenotexceedingP5000000,ortoimprisonmenttoatermnotexceeding10years. (4) AnypersonwhocontravenesanyoftheprovisionsoftheseRegulationsforwhichapenaltyisnotprescribedisliabletoafinenotexceedingP5000000,ortoimprisonmenttoatermnotexceeding10years. 75. Any person authorised by the Authority may impose an administrative penalty ofanamountnotexceedingthatspecifiedinregulation74whereapersoncontravenesanyoftheprovisionsoftheseRegulations.

Administrative penalties

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SCHEDULE 1(regulation 10 (1))

CATEGORYII-INSTRUMENTSANDEQUIPMENTAPPROVALANDMAINTENANCEREQUIREMENTS

GENERALTheinstrumentsandequipmentrequiredbyregulation10shallbeapprovedasprovidedinthisSchedulebeforebeingusedinCategoryIIoperations.Beforepresentinganaircraftforapprovaloftheinstrumentsandequipment,itmustbeshownthatsincethebeginningofthe12th calendar month before the date of submission —

(a) the ILS localizer and glide slope equipmentwere bench checked according tothemanufacturer’sinstructionsandfoundtomeetthosestandardsspecifiedinRTCAPaper 23-63/DO-177 datedMarch 14, 1963, “StandardsAdjustmentCriteria forAirborneLocalizerandGlideslopeReceivers.”;

(b) thealtimetersandthestaticpressuresystemsweretestedandinspected;and

(c) allotherinstrumentsanditemsofequipmentspecifiedinregulation10thatarelistedintheproposedmaintenanceprogramwerebenchcheckedandfoundtomeetthemanufacturer’sspecifications.

1. Flight control guidance systemAllcomponentsoftheflightcontrolguidancesystemshallbeapprovedasinstalledbytheevaluationprogramspecifiedinparagraph(e)iftheyhavenotbeenapprovedforCategoryIIIoperationsunderapplicabletypeorsupplementaltypecertificationprocedures.Inaddition,subsequentchangestomake,model,ordesignofthecomponentsmustbeapprovedunderthisparagraph.Relatedsystemsordevices,suchas theauto throttleandcomputedmissedapproachguidancesystem,shallbeapprovedinthesamemanneriftheyaretobeusedforCategoryIIoperations.

2. Radio altimeterAradioaltimetermustmeettheperformancecriteriaofthisparagraphfororiginalapprovaland after each subsequent alteration —

(a) itshalldisplaytotheflightcrewclearlyandpositivelythewheelheightofthemainlanding gearabovetheterrain;

(b) itshalldisplaywheelheightabovetheterraintoanaccuracyof±5feetor5percent,which everisgreater,underthefollowingconditions— (i) Pitchanglesofzeroto±50 about the mean approach attitude, (ii) Rollanglesofzeroto200 in either direction, (iii) Forward velocities from minimum approach speed up to 200 knots, and (iv) Sink rates from zero to 15 feet per second at altitudes from 100 to 200 feet.

(c) overlevelground,itmusttracktheactualaltitudeoftheaircraftwithoutsignificantlag oroscillation;

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(d) withtheaircraftatanaltitudeof200feetorless,anyabruptchangeinterrainrepresenting nomorethan10percentoftheaircraft’saltitudemustnotcausethealtimetertounlock,and indicatorresponsetosuchchangesmustnotexceed0.1secondsand,inaddition,ifthe systemunlocksforgreaterchanges,itmustreacquirethesignalinlessthan1second;

(e) systems that contain a push to test feature must test the entire system (with or without an antenna)atasimulatedaltitudeoflessthan500feet;and

(f) thesystemmustprovidetotheflightcrewapositivefailurewarningdisplayanytimethere isalossofpoweroranabsenceofgroundreturnsignalswithinthedesignedrangeof operatingaltitudes.

3. Other instruments and equipment. Allother instrumentsand itemsofequipmentrequiredbyregulation10shallbecapableofperformingasnecessaryforCategoryIIoperations.Approvalisalsorequiredaftereachsubsequent alteration to these instruments and items of equipment.

4. Evaluation program. (a) Application Approval by evaluation is requested as a part of the application for approval of the CategoryIImanual.

(b) DemonstrationsUnlessotherwiseauthorisedbytheAuthority,theevaluationprogramforeachaircraftrequiresthedemonstrationsspecifiedinthisparagraph.Atleast50ILSapproachesshallbeflownwithatleastfiveapproachesoneachofthreedifferentILSfacilitiesandnomorethanonehalfofthetotalapproachesonanyoneILSfacility.Allapproachesshallbeflownundersimulatedinstrumentconditionstoa30m(100foot)decisionheightand90percentofthetotalapproachesmadeshallbe successful. A successful approach is one in which —

(i) atthe30m(100foot)decisionheight,theindicatedairspeedandheadingare satisfactoryforanormalflareandlanding(speedmustbe±5knotsofprogrammed airspeed, but may not be less than computed threshold speed if auto throttles are used), (ii) theaircraftatthe30m(100foot)decisionheight,ispositionedsothatthecockpitis within,andtrackingsoastoremainwithin,thelateralconfinesoftherunway extended, (iii) deviationfromglideslopeafterleavingtheoutermarkerdoesnotexceed50percent offull-scaledeflectionasdisplayedontheILSindicator, (iv) nounusualroughnessorexcessiveattitudechangesoccurafterleavingthemiddle Marker, and (v) inthecaseofanaircraftequippedwithanapproachcoupler,theaircraftissufficiently intrimwhentheapproachcouplerisdisconnectedatthedecisionheighttoallowfor thecontinuationofanormalapproachandlanding.

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(c) Records Duringtheevaluationprogramthefollowinginformationshallbemaintainedbythe applicant for the aircraft with respect to each approach and made available to the Authority upon request — (i) eachdeficiencyinairborneinstrumentsandequipmentthatpreventedtheinitiation of an approach, (ii) thereasonsfordiscontinuinganapproach,includingthealtitudeabovetherunway at which it was discontinued, (iii) speed control at the 30 m (100 foot) DH if auto throttles are used, (iv) trimconditionoftheaircraftupondisconnectingtheautocouplerwithrespectto continuationtoflareandlanding, (v) positionoftheaircraftatthemiddlemarkerandatthedecisionheightindicatedboth onadiagramofthebasicILSdisplayandadiagramoftherunwayextendedtothe middlemarker.Estimatedtouchdownpointshallbeindicatedontherunwaydiagram, (vi) compatibilityofflightdirectorwiththeautocoupler,ifapplicable,and (vii) quality of overall system performance.

(d) Evaluation Afinalevaluationoftheflightcontrolguidancesystemismadeuponsuccessfulcompletion of the demonstrations. If no hazardous tendencies have been displayed or are otherwise known to exist, the system is approved as installed.

EachmaintenanceprogramforCategoryIIinstrumentsandequipmentshallcontain thefollowing—

(i) alistofeachinstrumentanditemofequipmentspecifiedinregulation10thatis installedintheaircraftandapprovedforCategoryIIoperations,includingthemake andmodelofthosespecifiedinregulation10(2), (ii) aschedulethatprovidesfortheperformanceofinspectionsundersubparagraph(5) ofthisparagraphwithin3calendarmonthsafterthedateofthepreviousinspection. The inspection shall be performed by a person authorised under the Civil Aviation (Airworthiness)Regulations,exceptthateachalternateinspectionmaybereplaced byafunctionalflightcheck.Thisfunctionalflightcheckshallbeperformedbya pilotholdingaCategoryIIpilotauthorisationforthetypeaircraftchecked, (iii) a schedule that provides for the performance of bench checks for each listed instrumentanditemofequipmentthatisspecifiedinregulation10(2)within12 calendar months after the date of the previous bench check, (iv) a schedule that provides for the performance of a test and inspection of each static pressure system within 12 calendar months after the date of the previous test and inspection, (v) theproceduresfortheperformanceoftheperiodicinspectionsandfunctionalflight checkstodeterminetheabilityofeachlistedinstrumentanditemofequipmentspecified inregulation10(2)toperformasapprovedforCategoryIIoperationsincludinga procedureforrecordingfunctionalflightchecks, (vi) aprocedureforassuringthatthepilotisinformedofalldefectsinlistedinstruments and items of equipment,

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(vii) aprocedureforassuringthattheconditionofeachlistedinstrumentanditemof equipmentuponwhichmaintenanceisperformedisatleastequaltoitsCategoryII approvalconditionbeforeitisreturnedtoserviceforCategoryIIoperations,and (viii) a procedure for an entry in the maintenance records that shows the date, airport, andreasonsforeachdiscontinuedCategoryIIoperationbecauseofamalfunction of a listed instrument or item of equipment.

(e) Bench check (1) Abenchcheckrequiredbythissectionshallcomplywiththisparagraph.Except asspecifiedin(2)ofthisparagraph,itshallbeperformedbyacertificatedrepairstation holdingoneofthefollowingratingsasappropriatetotheequipmentchecked—

(i) aninstrumentrating,and (ii) anavionicsrating.

(2) Itshallbeperformedbyacertificatedairoperatoronaircraftidentifiedinitsapproved OperationsSpecificationswiththeapprovedauthorisationstoperformmaintenanceand approve for return to service its own aircraft maintained under a continuous maintenance programunderanequivalentsystemidentifiedinCivilAviation(AirOperatorCertification andAdministration)Regulations.

(3) It shall consist of removal of an instrument or item of equipment and performance ofthefollowing—

(i) avisualinspectionforcleanliness,impendingfailure,andtheneedforlubrication, repair,orreplacementofparts; (ii) correctionofitemsfoundbythatvisualinspection;and (iii) calibrationtoatleastthemanufacturer’sspecificationsunlessotherwisespecified intheapprovedCategoryIImanualfortheaircraftinwhichtheinstrumentor item of equipment is installed.

(f) Extensions After the completion of one maintenance cycle of 12 calendar months, a request to extend the period for checks, tests, and inspections is approved if it is shown that the performanceofparticularequipmentjustifiestherequestedextension.

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SCHEDULE 2

PART 1 — Application for Reduced Vertical Separation Minimum(regulation 18 (2))

Applications forRVSMshallbemadeusingCAABFormFSD133.Submit formsandapplicationpackagereferencedinparagraph4ofRVSMapplicationformto:

DIRECTOR, FLIGHT SAFETY CIVIL AVIATION AUTHORITY OF BOTSWANA P. O. BOX 250 GABORONE, BOTSWANA

GENERAL

General InformationApplicant’sNameand Address

AeroplaneRegistration SerialNumber

Aeroplane Manufacturer

AeroplaneTypeDesignation/Model

Aeroplane Address (Hexadecimal)

Scope of Application YES NO

Application for AFI RVSM operations?

Other?

Initial request for RVSM approval for aeroplane type referenced in 1.5?

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AIRWORTHINESS

TypeDesignApprovalforreferencedAeroplaneTypeDesignation

TheRVSMtypedesignapprovalisreflectedin:

AFM AFM TypeCertificationData Supplemental Type Other

AeroplaneFlightManual(AFM)orAFMSupplementreferstothefollowingairworthinessapproval basis for RVSM system installation:

TemporaryGuidanceLeaflet(TGL)No.6 FAADocument91-RVSM

Other: YES NO

Group aeroplane?

Non-groupaeroplane?

BasicRVSMflightenvelope?

Full RVSM envelope?

Airworthiness performance requirements in the form of a Minimum Aeroplane Systems PerformanceSpecification(MASPS):

MASPS compliance demonstrated by:

Manufacturer:

Designorganisation:

MASPScompliancedatapackage:

Reference number:

NavigationSystemEligibilityforreferencedAeroplaneSerialNumber

Equipment for RVSM operations:

Altitude measurement systems: Make: Model:

SSR Transponder: Make: Model:

AltitudeAlertingSystem: Make: Model:

Automatic altitude control system: Make: Model:

The approval of the RVSM systems installation is based on:

TypeDesign FAA STC EASA STC Service Bulletin

Major Other:

MaintenanceProgram(*) YES NO

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Note:TheapplicantshouldhaveanestablishedMaintenanceProgrammethatcontainsallRVSMrequirementsprescribedbymanufacturerordesignorganisation.

MinimumEquipmentList(*)

Note: The applicant should have revised parts of the Minimum Equipment Listtoreflectsystemrequirements(e.g.redundancylevels)appropriateto the intended RVSM operations.

MaintenancePracticesandProcedures(*)

Note: The applicant must institute procedures To be completed by applicantinrespectofcontinuingairworthinesspracticesfor RVSM. These procedures should cover the RVSM Maintenance Practices andfollowingsubjects. Proceduresaredescribedin(Add manual reference, chapter and sub-chapter) Maintenance of RVSM equipment (adherencetomanufacturer’smaintenanceinstructions,modificationprocedures,systemcalibrationpolicy, leak check policy, skin waviness checks, autopilot/automatic altitude controlmaintenancepractices,handlingon-boardsystems, etc.)

Actionfornon-compliantaeroplane(down-gradingreportingtoCAAB,responsetoinquiries from AFI RMA, corrective actions, upgrading,etc.)

MaintenanceTraining(trainingofapplicant’smaintenancemanagementstaff,trainingofcontractor’smaintenancepersonnel,initialtraining,recurrenttraining,trainingsyllabi, etc.)

TestEquipment(useoftestequipment,handling, calibration, etc.)

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OPERATION

OperatingPracticesandProcedures(*) To be completed by applicant

Note: The applicant must institute RVSM OperatingPracticesandProcedures.These RVSMOperatingPracticesandpractices and procedures should cover the Procedures are described in (Addfollowingsubjects: manualreference,chapterand sub-chapter)

FlightplanningproceduresforoperationsinRVSM airspace (RVSM approval of aeroplane, reported and forecast weather, use of minimum equipmentlist(MEL),airframeoroperatingrestrictions, etc.)

Pre-flightproceduresforeachflightinRVSMairspace(reviewoftechnicallog,externalinspection), functional check of altitude measurement & control systems, etc.).

RVSMin-flightprocedures(priortoRVSMin-flightentry,serviceabilityofrequiredequipment,altimetersettings,adherencetoATCinstructions,phraseology,changingflightlevels,useofaltitudecontrolandalertingsystems,altimetercross-checks,ACASprocedures,specificregionaloperatingprocedures(MNPS,AFIRVSM,etc.),reporting of wake turbulence encounters in AFI RVSM airspace, etc.)

Procedureswithrespecttoflightcrewresponsetoabnormalsituations(reportingofaltitudedeviations and altimetry system errors, contingencyproceduresafterenteringRVSMairspace, etc.).

Post-flightprocedures(technicallogentries,defectsdescription,reportingofaltitudedeviations and altimetry system errors, etc.).

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FlightCrewTrainingandQualification(*)

To be completed by applicantNote: The applicant is required to establish thefollowing(coveringsubjectsunder3.1to3.5): Descriptionin(Addmanualreference, chapterandsub-chapter)

Flightcrewqualificationrequirements.

Descriptionofinitialandrecurrenttraining,checking-andtrainingsyllabi.

APPLICATION PACKAGE

Documentation to be submitted to the CAAB Submitted?

YES NO

Compliance statement which shows how the criteria of JAA TemporaryGuidanceLeafletNo.6havebeensatisfied(*).

Sections of the AFM or AFM supplements that document RVSMairworthiness approval

Sections of the AFM or AFM supplements that document RVSM airworthiness approval

MASPScompliancedatapackage(*)

FlightcrewRVSMtrainingprogrammesandsyllabiforinitialandrecurrenttraining(*)

OperationmanualsandcheckliststhatincludeRVSMoperatingpracticesandprocedures(OM-A,OMB,OM-D,AOM,FCOM,RouteManuals,stand-aloneRVSMmanual,etc.)(*)

Minimum Equipment List (MEL) that include items pertinent to RVSMoperations(*)

MaintenanceprogramorrevisionthereofthatincludeitemspertinenttoRVSMequipment(*).

RVSM maintenance practices & procedures (MME, maintenance program,stand-alonedocument)(*)

ServiceBulletin,STCorMajorModificationApprovaldocumentation,if approval is based on documents as detailed in 2.9 above (except ifbasedonapprovedtypedesign)

PlanforparticipationintheRVSMmonitoringprogram(*)

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APPLICANT’SSTATEMENT

Theundersignedcertifiestheaboveinformationtobecorrectandtrueandthataeroplanesysteminstallation,continuingairworthinessofsystems,minimumequipmentfordispatch,operatingproceduresandflightcrewtrainingcomplywiththerequirementsoftheBotswanaCivilAviationRegulations,JAATemporaryGuidanceLeafletNo.6andFAADocument91-RVSM.

NameofPostHolder Signature: Date:Maintenance:

NameofPostHolderOperations: Signature: Date:

NameofPostHolderTraining: Signature: Date:

PART II — REDUCED VERTICAL SEPARATION MINIMUM ALTIMETRY SYSTEM PERFORMANCEREQUIREMENTSFOROPERATIONSINRVSMAIRSPACE

(regulation 18 (3))

(a) Inrespectofgroupsofaeroplanesthatarenominallyofidenticaldesignandbuild withrespecttoalldetailsthatcouldinfluencetheaccuracyofheight-keepingperformance, theheight-keepingperformancecapabilityshallbesuchthatthetotalverticalerror(TVE) forthegroupofaeroplanesshallhaveameannogreaterthan25m(80ft)inmagnitudeand shallhaveastandarddeviationnogreaterthan28–0.013z2for0≤z≤25whenzisthe magnitudeofthemeanTVEinmetres,or92–0.004z2for0≤z≤80wherezisinfeet.In addition,thecomponentsofTVEshallhavethefollowingcharacteristics—

(1) themeanaltimetrysystemerror(ASE)ofthegroupshallnotexceed25m(80ft) inmagnitude;

(2) the sum of the absolute value of the mean ASE and of three standard deviations ofASEshallnotexceed75m(245ft);and

(3) thedifferencesbetweenclearedflightlevelandtheindicatedpressurealtitude actuallyflownshallbesymmetricaboutameanof0m,withastandarddeviation nogreaterthan13.3m(43.7ft),andinaddition,thedecreaseinthefrequencyof differenceswithincreasingdifferencemagnitudeshallbeatleastexponential.

(b) In respect of aeroplanes for which the characteristics of the airframe and altimetry systemfitareuniqueandsocannotbeclassifiedasbelongingtoagroupofaeroplanes encompassedbyparagraph(1),theheight-keepingperformancecapabilityshallbe suchthatthecomponentsoftheTVEoftheaeroplanehavethefollowingcharacteristics—

(1) theASEoftheaeroplaneshallnotexceed60m(200ft)inmagnitudeunderall flightconditions;and

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(2) thedifferencesbetweentheclearedflightlevelandtheindicatedpressurealtitude actuallyflownshallbesymmetricaboutameanof0m,withastandarddeviation nogreaterthan13.3m(43.7ft),andinaddition,thedecreaseinthefrequencyof differenceswithincreasingdifferencemagnitudeshallbeatleastexponential.


FLIGHT DATA RECORDERS

(a) Nopersonmayoperatethefollowingaircraftunlessitisequippedwithaflightdata recordercapableofrecordingtheauralenvironmentoftheflightdeckduringflighttime.

(1) [AOC]Allaeroplaneswithamaximumcertificatedtakeoffmassofover5700kgup toandincluding27000kgshallbeequippedwithaTypeIIFDR.

(2) [AOC]Allaeroplaneswithamaximumcertificatedtakeoffmassofmorethan 27000kgshallbeequippedwithaTypeIFDR.

(3) [AOC]Allturbinepoweredaeroplaneswithamaximumcertificatedtakeoffmassof lessthan5,700kgshallbeequippedwithaTypeIIAFDR.

(4) [AAC]Allaeroplaneswithamaximumcertificatedtakeoffmassofmorethan 27000kgshallbeequippedwithaTypeIFDR.

(5) [AAC]Allaeroplaneswithamaximumcertificatedtakeoffmassofmorethan 5700kgshallbeequippedwithaTypeIAFDR.

(6) [AOC]Allhelicopterswithacertificatedtakeoffmassofover7000kgshallhavea Type IV FDR.

(7) [AOC]Allhelicopterswithacertificatedtakeoffmassofover3180kgshallhavea Type IVA FDR.

(8) [AAC]Allhelicopterswithacertificatedtakeoffmassofover-7000kgshallhavea Type IV FDR.

(9) [AAC]Allhelicopterswithacertificatedtakeoffmassofover3180kgshallhavea Type IVA FDR.

(b) [AOC]Flightdatarecordersshall—

(1) be constructed, located and installed so as to provide maximum practical protection fortherecordingsinorderthattherecordedinformationmaybepreserved,recovered andtranscribed;

(2) becalibratedasrequiredbytheAuthority;and

(3) haveanapproveddevicetoassistinlocatingarecorderthatmaybeunderwater and can be automatically activated.

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(c) Flightdatarecordersshallbecapableofretainingtheinformationrecordedduringthelast— (1) Type I and II — 25 hours of operation. (2) Type IIA — 30 minutes of operation. (3) Type IV and V — 10 hours of operation.

(d) FlightdatarecordermedianotacceptableforuseinaircraftregisteredinBotswana,or operated in commercial air transport operations in Botswana, are —

(1) Engravingmetalfoil; (2) Photographicfilm;or (3) Analoguedatausingfrequencymodulation.

PARTII—FlightDataRecorders:SpecificRequirements

(a) [AOC]Typesofflightdatarecorders.

(1) Types I and IA FDRs shall record the parameters required to determine accurately —

(i) Theaeroplaneflightpath. (ii) Speed. (iii) Altitude. (iv) Enginepower. (v) Configurationandoperation.

(2) The parameters that satisfy the requirements for a Type I FDR are contained in Table A below.

(3) The parameters that satisfy the requirements for a Type IA FDR are listed below. Theparameterswithoutanasterisk(*)aremandatoryparametersthatshallbe recorded.Theparametersdesignatedbyanasterisk(*)shallalsoberecorded if an information data source for an asterisked parameter is used by aeroplane systemsortheflightcrewtooperatetheaeroplane.

(i) Thefollowingparameterssatisfytherequirementsforflightpathand speed —

(a) Pressure altitude. (b) Indicated or calibrated airspeed. (c) Air-groundstatusandeachlandinggearair-groundsensorwhen practicable. (d) Total or outside air temperature. (e) Heading(primaryflightcrewreference). (f) Normal acceleration. (g) Lateral acceleration. (h) Longitudinalacceleration(bodyaxis). (i) Time or relative time count.

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(j) Navigationdata*:driftangle,windspeed,winddirection,latitude/ longitude. (k) Groundspeed*. (l) Radioaltitude*.

(ii) Thefollowingparameterssatisfytherequirementsforaltitude—

(a) Pitch attitude. (b) Roll attitude. (c) Yaworsideslipangle*. (d) Angleofattack*.

(iii) Thefollowingparameterssatisfytherequirementsforenginepower—

(a) Enginethrustpower:propulsivethrust/poweroneachengine, cockpit thrust/power lever position. (b) Thrustreversestatus*. (c) Enginethrustcommand*. (d) Enginethrusttarget*. (e) Enginebleedvalveposition*. (f) Additionalengineparameters*:EPR,N1,indicatedvibrationlevel, N2,EGT,TLA,fuelflow,fuelcut-offleverposition,N3.

(iv) Thefollowingparameterssatisfytherequirementsforconfiguration— (a) Pitch trim surface position. (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*.

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(v) Thefollowingparameterssatisfytherequirementsforoperation— (a) Warnings. (b) Primaryflightcontrolsurfaceandprimaryflightcontrolpilot input: pitch axis, roll axis, yaw axis. (c) Markerbeaconpassage. (d) Eachnavigationreceiverfrequencyselection. (e) ManualradiotransmissionkeyingandCVR/FDRsynchronization 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,bothcautionsand warning,andadvisories,on/offswitchposition. (r) Lowpressurewarning*:hydraulicpressure,pneumaticpressure. (s) Computerfailure*. (t) Lossofcabinpressure*. (u) TCAS/ACAS(trafficalertandcollisionavoidancesystem/airborne collisionavoidancesystem)*. (v) Icedetection*. (w) Enginewarningeachenginevibration*. (x) Enginewarningeachengineovertemperature*. (y) Enginewarningeachengineoilpressurelow*. (z) Enginewarningeachengineoverspeed*.

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(aa) Windshearwarning*. (bb) Operationalstallprotection,stickshakerandpusheractivation*. (cc) Allcockpitflightcontrolforces*:controlwheel,controlcolumn, rudder pedal cockpit input forces. (dd) Verticaldeviation*:ILSglidepath,MLSelevation,GNSS approach path. (ee) Horizontaldeviation*:ILSlocalizer,MLSazimuth,GNSS approach path. (ff) DME1and2distances* (gg) Primarynavigationsystemreference*:GNSS,INS,VOR/DME, MLS, Loran C, ILS. (hh) Brakes*:leftandrightbrakepressure,leftandrightbrake pedal 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 Organization for Civil Aviation Equipment (EUROCAE) or equivalent documents.

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

ICAO Annex 6, Part I: 6.3.1.1; 6.3.1.8; 6.3.1.8.1; 6.3.1.8.2; 6.3.1.8.3; 6.3.1.8.4; 6.3.1.8.5ICAO Annex 6, Part II: 6.10.1.1; 6.10.1.7; 6.10.1.7.1; 6.10.1.7.2; 6.10.1.7.3; 6.10.1.7.4; 6.10.1.7.5

(4) TypesIIandIIAFDRsshallrecordtheparametersspecifiedinparagraph(a) (1)(i)through(iv)ofthissection,andthoseparametersrequiredtoaccurately determinetheconfigurationofliftanddragdevices:

ICAO Annex 6, Part I: 6.3.1.2 ICAO Annex 6, Part II: 6.10.1.2

(5) The parameters that satisfy the requirements for a Type II and Type IIA FDR 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.

ICAO Annex 6, Part I: Attachment D, Introduction and Paragraph 1.2

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(6) Type IV FDRs shall record the parameters required to determine accurately —

(i) Thehelicopterflightpath. (ii) Speed. (iii) Altitude. (iv) Enginepowerandoperation.

ICAO Annex 6, Part III, Section II: 4.3.1.1 ICAO Annex 6, Part III, Section III: 4.9.1.1

(7) The parameters that satisfy the requirements for a Type IV FDR are contained in Table B below.

(8) TypeIVAFDRsshallrecordtheparametersspecifiedinparagraph(a)(6)ofthis section,andtheparameterrequiredtoaccuratelydetermineconfiguration.


(9) The parameters that satisfy the requirements for a Type IVA FDR are listed below. Theparameterswithoutanasterisk(*)aremandatoryparametersthatshallbe recorded.Theparametersdesignatedbyanasterisk(*)shallalsoberecordedifan information data source for an asterisked parameter is used by aeroplane systems ortheflightcrewtooperatethehelicopter.

(i) Thefollowingparameterssatisfytherequirementsforflightpathand speed — (a) Pressure altitude. (b) Indicated airspeed. (c) Total or outside air temperature. (d) Heading(primaryflightcrewreference). (e) Normal acceleration. (f) Lateral acceleration. (g) Longitudinalacceleration(bodyaxis). (h) Time or relative time count. (i) Navigationdata*:driftangle,windspeed,winddirection,latitude/ longitude. (j) Radioaltitude*.

(ii) Thefollowingparameterssatisfytherequirementsforattitude—

(a) Pitch attitude. (b) Roll attitude. (c) Yaw rate.

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(iii) Thefollowingparameterssatisfytherequirementsforenginepower—

(a) Poweroneachengine:freepowerturbinespeed(Nf),engine torque,enginegasgeneratorspeed(Ng),cockpitpowercontrol position. (b) Rotor: main rotor speed, rotor brake. (c) Maingearboxoilpressure*. (d) Gearboxoiltemperature*,maingearboxoiltemperature,tail rotorgearboxoiltemperature. (e) Engineexhaustgastemperature(T4)*. (f) Turbineinlettemperature(TIT)*.

(10) Thefollowingparameterssatisfytherequirementsforconfiguration— (i) Landinggearorgearselectorposition*. (a) Fuelquality*. (b) Icedetectorliquidwatercontent*.

(ii) Thefollowingparameterssatisfytherequirementsforoperation—

(a) Hydraulics low pressure. (b) Warnings. (c) Primaryflightcontrols-pilotinputand/orcontroloutputposition: collectivepitch,longitudinalcyclicpitch,lateralcyclicpitch,tail rotor petal, controllable stabilator, hydraulic selection. (d) Markerbeaconpassage. (e) Eachnavigationreceiverfrequencyselection. (f) AFCSmodeandengagementstatus*. (g) Stabilityaugmentationsystemengagement*. (h) Indicatedslingloadforce*. (i) Verticaldeviation*:ILSglidepath,GNSSapproachpath. (j) Horizontaldeviation*:ILSlocalizer,GNSSapproachpath. (k) DME1and2distances*. (l) Altituderate*. (m) Icedetectorliquidwatercontent*. (n) Helicopterhealthandusagemonitorsystem(HUMUS)*: enginedata,chipdetectors,tracktiming,exceedancediscretes,broadband averageenginevibration.

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 Organization 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.

ICAO Annex 6, Part III, Section II: 4.3.1.7; 4.3.1. 7.1; 4.3.1.7.2; 4.3.1.7.3; 4.3.1.7.4; 4.3.1.7.5ICAO Annex 6, Part III, Section II: 4.9.1.7; 4.9.1.7.1; 4.9.1.7.2; 4.9.1.7.3; 4.9.1.7.4; 4.9.1.7.5

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(11) TypeVFDRsshallrecordtheparametersspecifiedinparagraph(a) (6) (i) through(iii)ofthissection,andtheparameterrequiredtoaccuratelydetermine enginepower.


(12) The parameters that satisfy the requirements for a Type V FDR are contained in Table B below.

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Table A — AeroplanesParameters for Flight Data Recorders

Serial Parameter Measurementrange Recording Accuracylimits number interval (sensor input compared (seconds) toFDRread-out)

1 Time(UTCwhen 24hours 4 +/-0.125%perhour available, otherwise elapsed time)

2 Pressure-altitude— -300m(-1000ft)to 1 +/-30mto+/-200m maximumcertificated (+/-100ftto+/-700ft) altitude of aircraft 1 500 m ( 5 000 ft)

3 Indicatedairspeed 95km/h(50kt)to1max +/-5% VSo(Note1) +/-3% VSo to 1.2 VD (Note 2)

4 Heading 360degrees 1 +/-2%

5 Normalacceleration— -3gto+6g 0.125 +/-1%ofmaximumrange excludingdatumerrorof+/-5%

6 Pitchattitude +/-75degrees 1 +/-2degrees

7 Rollattitude +/-180degrees 1 +/-2degrees

8 Radiotransmission On-off(onediscrete) 1 keying

9 Poweroneachengine Fullrange 1(per +/-2% (Note3) engine)

10 Trailingedgeflapor Fullrangeoreach 2 +/-5%oraspilot’sindicator cockpit discrete position control selection

11 Leadingedgeflapor Fullrangeoreach 2 +/-5%oraspilot’sindicator cockpit discrete position control selection 12 Thrust reverser position Stowed, in transit, and 1 (per reverse engine)

13 Groundspoiler/speed Fullrangeoreachdiscrete 1 +/-2%unlesshigher brake selection position accuracy uniquely required

14 Outsideairtemperature Sensorrange 2 +/-2degreesC

15 Autopilot/auto A suitable combination 1 throttle/AFCS of discretes modeandengagement status

Note— Thepreceding15parameterssatisfytherequirementsforaTypeIIFDR.

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16 Longitudinal +/-1g 0.25 +/-1.5%maxrange acceleration excludingdatumerror of+/-5%

17 Lateralacceleration +/-1g 0.25 +/-1.5%maxrangeexcluding datumerrorof+/-5%

18 Pilotinputand/orcontrol Fullrange 1 +/-2degreesunlesshigher surfaceposition-primary accuracyuniquelyrequired controls (pitch, roll, yaw) (Note 4)

19 Pitchtrimposition Fullrange 1 +/-3%unlesshigheraccuracy uniquely required

20 Radioaltitude— -6mto750m 1 +/-0.6m(+/-2ft)or+/-3% (—20ftto2500ft) whicheverisgreaterbelow 150m(500ft)and+/-5% above 150 m (500 ft)

21 Glidepathdeviation Signalrange 1 +/-3%

22 Localizerdeviation Signalrange 1 +/-3%

23 Markerbeaconpassage Discrete 1

24 Masterwarning Discrete 1

25 NAV1and2frequency Fullrange 4 Asinstalled selection (Note 5)

26 DME 1 and 2 distance 0 — 370 km 4 As installed (Notes 5 and 6)

27 Landinggearsquat Discrete 1 switch status

28 GPWS(ground Discrete 1 proximity warningsystem)

29 Angleofattack Fullrange 05 Asinstalled

30 Hydraulics, each system Discrete 2 (low pressure)

31 Navigationdata Asinstalled 1 Asinstalled (latitude/longitude, ground speedanddriftangle) (Note 7)

32 Landinggearorgear Discrete 4 Asinstalled selector position

Note—Thepreceding32parameterssatisfytherequirementsforaTypeIFDR.

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Notes —

1. VSostallingspeedorminimumsteadyflightspeedinthelandingconfiguration. 2. VDdesigndivingspeed. 3. Recordsufficientinputstodeterminepower. 4. Foraeroplaneswithconventionalcontrolsystems“or”applies.Foraeroplaneswithnon-mechanicalcontrol systems “and” applies. In aeroplanes with split surfaces, a suitable combination of inputs is acceptable in lieu ofrecordingeachsurfaceseparately. 5. Ifsignalavailableindigitalform. 6. RecordingoflatitudeandlongitudefromINSorothernavigationsystemisapreferredalternative. 7. Ifsignalsreadilyavailable.

Iffurtherrecordingcapacityisavailable,recordingofthefollowingadditionalinformationshouldbeconsidered:

(a) operationalinformationfromelectronicdisplaysystems,suchaselectronicflightinstrumentsystems (EFIS),electroniccentralizedaircraftmonitor(ECAM)andengineindicationandcrewalertingsystem (EICAS).Usethefollowingorderofpriority:

(1) parametersselectedbytheflightcrewrelatingtothedesiredflightpath,e.g.barometricpressure setting,selectedaltitude,selectedairspeed,decisionheight,andautoflightsystemengagementand modeindicationsifnotrecordedfromanothersource; (2) displaysystemselection/status,e.g.SECTOR,PLAN,ROSE,NAV,WXR,COMPOSITE,COPY,ETC.; (3) warningsandalerts; (4) theidentityofdisplayedpagesforemergencyproceduresandchecklists;

(b) retardationinformationincludingbrakeapplicationforuseintheinvestigationoflandingoverrunsand rejectedtake-offs;and

(c) additionalengineparameters(EPR,N1,EGT,fuelflow,etc.).

ICAO Annex I, Part I, Attachment D, Table D-1ICAO Annex I, Part II, Attachment A, Table A-1

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Table B — HelicoptersParameters for Flight Data Recorders

Serial Parameter Measurementrange Recording Accuracylimits number interval (sensor input compared (seconds) toFDRread-out)

1 Time(UTCwhen 24hours 4 +/-0.125%perhour available, otherwise elapsed time)

2 Pressure-altitude— -300m(—1000ft)to 1 +/-30mto+/-200m maximumcertificated (+/-100ftto+/-700ft) altitude of aircraft +1 500 m (+5 000 ft)

3 Indicatedairspeed Astheinstalled 1 +/-3% measuringsystem

4 Heading 360degrees 1 +/-2degrees

5 Normalacceleration— -3gto+6g 0.125 +/-1%

6 Pitchattitude +/-75degrees 0.5 +/-2degrees

7 Rollattitude +/-180degrees 0.5 +/-2degrees

8 Radiotransmission On-off(onediscrete) 1 keying

9 Poweroneachengine Fullrange 1(per +/-2% (Note1) engine)

10 Mainrotorspeed 50-130% 0.5 +/-2%

11 Pilotinputand/orcontrol Fullrange 1 +/-2%unlesshigheraccuracy surfaceposition-primary uniquelyrequired. controls (Collective pitch, longitudinalcyclicpitch, lateral cyclic pitch, tail rotor pedal) (Note 2)

12 Hydraulics, each system Discrete 2 (low pressure)

13 Outsideairtemperature Sensorrange 2 +/-2degreesC

14 Autopilot/auto A suitable combination of 1 throttle/AFCS discretes modeandengagement status

15 Stabilityaugmentation Discrete 1 systemengagement

Note:Thepreceding15parameterssatisfytherequirementsforaTypeVFDR.

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16 Maingearboxoilpressure Asinstalled 1 Asinstalled

17 Maingearboxoil Asinstalled 2 Asinstalled temperature

18 Yawacceleration +/-1g 0.25 +/-1.5%maxrangeexcluding (oryawrate) datumerrorof+/-5%

19 Slingloadforce 0-200% 0.5 +/-3%ofmaxrange ofcertifiedload

20 Longitudinalacceleration +/-1g 0.25 +/-1.5%maxrangeexcluding datumerrorof+/-5%

21 Lateralacceleration +/-1g 0.25 +/-1.5%maxrangeexcluding datumerrorof+/-5%

22 Radioaltitude— -6mto750m 1 +/-0.6m(+/-2ft)or+/-3% (—20ftto2500ft) whicheverisgreaterbelow 150m(500ft)and+/-5% above 150 m (500 ft)

23 Glidepathdeviation Signalrange 1 +/-3%

24 Localizerdeviation Signalrange 1 +/-3%

25 Markerbeaconpassage Discrete 1

26 Masterwarning Discrete 1

27 NAV1and2frequency Fullrange 4 Asinstalled selection (Note 3)

28 DME1and2distance 0-370km 4 Asinstalled (Notes 3 and 4)

29 Navigationdata Asinstalled 2 Asinstalled (latitude/longitude, groundspeed)(Note5)

30 Landinggearorgear Discrete 4 Asinstalled selector position

Note:Thepreceding30parameterssatisfytherequirementsforaTypeIVFDR.

Notes —

1. Recordsufficientinputstodeterminepower. 2. Forhelicopterswithconventionalcontrolsystems“or”applies.Forhelicopterswithnon-mechanical control systems “and” applies. 3. Ifsignalavailableindigitalform. 4. RecordingoflatitudeandlongitudefromINSorothernavigationsystemisapreferredalternative. 5. Ifsignalsreadilyavailable.

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Iffurtherrecordingcapacityisavailable,recordingofthefollowingadditionalinformation should be considered:

(a) operationalinformationfromelectronicdisplaysystems,suchaselectronicflightinstrment systems(EFIS),electroniccentralizedaircraftmonitor(ECAM)andengineindication andcrewalertingsystem(EICAS).Usethefollowingorderofpriority:

(1) parametersselectedbytheflightcrewrelatingtothedesiredflightpath,e.g.barometric pressuresetting,selectedaltitude,selectedairspeed,decisionheight,andautoflight systemengagementandmodeindicationsifnotrecordedfromanothersource;

(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.).

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SCHEDULE 4(regulations 37 (1) (f), 41 (5))

EMERGENCYEXITEQUIPMENT-PASSENGERS

PARTI—TheemergencyexitequipmentrequiredunderRegulation37(1)shallmeetthefollowingrequirements —

(a) Theassistingmeansforafloorlevelemergencyexitshallmeettherequirementsunder whichtheaeroplanewastypecertified. (b) Thelocationofeachpassengeremergencyexitshallbe—

(1) recognisablefromadistanceequaltothewidthofthecabin;and (2) indicatedbyasignvisibletooccupantsapproachingalongthemainpassengeraisle.

(c) Thereshallbeanemergencyexitlocatingsign—

(1) abovetheaisleneareachover-the-wingpassengeremergencyexit,oratanother ceilinglocationifitismorepracticalbecauseoflowheadroom;

(2) nexttoeachfloorlevelpassengeremergencyexit,exceptthatonesignmayserve twosuchexitsiftheybothcanbeseenreadilyfromthatsign;and

(3) oneachbulkheadordividerthatpreventsforeandaftvisionalongthepassenger cabin,toindicateemergencyexitsbeyondandobscuredbyit,exceptthatifthisis notpossible,thesignmaybeplacedatanotherappropriatelocation.

(d) Eachpassengeremergencyexitmarkingandeachlocatingsignshallbemanufactured tomeettheinterioremergencyexitmarkingrequirementsunderwhichtheaeroplane wastypecertified,unlesstheAuthoritycitesdifferentrequirementsforcompliancewith thisparagraph.

Note: No sign may continue to be used if its luminescence (brightness) decreases to below 250 micro lamberts.

(e) Sourcesofgeneralcabinilluminationmaybecommontoboththeemergencyandthe mainlightingsystemsifthepowersupplytotheemergencylightsystemisindependent ofthepowersupplytothemainlightingsystem. (f) Theemergencylightingsystemshallprovideenoughgenerallightinginthepassenger cabinsothattheaverageillumination,whenmeasuredat40-inchintervalsatseatarmrest height,onthecenter-lineofthemainpassengeraisle,isatleast0.05foot-candles. (g) Eachemergencylightshall—

(1) beoperablemanuallybothfromtheflightcrewstationandfromapointinthe passengercompartmentthatisreadilyaccessibletoanormalcabincrew memberseat;

(2) haveameanstopreventinadvertentoperationofthemanualcontrols;

(3) whenarmedorturnedonateitherstation,remainlightedorbecomelighted uponinterruptionoftheaeroplane’snormalelectricpower:

Provide the required level of illumination for at least 10 minutes at the critical ambientconditionsafteremergencylanding;and

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(4) have a cockpit control device that has an “on”, “off”, and “armed” position.

(h) Thelocationofeachpassengeremergencyexitoperatinghandleandinstructionsfor openingtheexitshallbeshowninaccordancewiththerequirementsunderwhichthe aeroplanewastypecertified,unlesstheAuthoritycitesdifferentrequirementsforcompliance withthisparagraph. (i) Nooperatinghandleoroperatinghandlecovermaycontinuetobeusedifitsluminescence (brightness)decreasestobelow100microlamberts. (j) Accesstoemergencyexitsshallbeprovidedasfollowsforeachpassengercarrying aeroplane: (k) Eachpassagewaybetweenindividualpassengerareas,orleadingtoaTypeIorTypeII emergencyexit,shallbeunobstructedandatleast20incheswide. (l) ThereshallbeenoughspacenexttoeachTypeIorTypeIIemergencyexittoallow acrewmembertoassistintheevacuationofpassengerswithoutreducingthe unobstructedwidthofthepassagewaybelowthatrequiredinparagraph(j) 1. of this section. (m) There shall be access from the main aisle to each Type III and Type IV exit. The access from the aisle to these exits shall not be obstructed by seats, berths, or other protrusions in a manner that would reduce the effectiveness of the exit. In addition, the access shall meettheemergencyexitaccessrequirementsunderwhichtheaeroplanewastypecertificated, unlesstheAuthoritycitesdifferentrequirementsforcompliancewiththisparagraph. (n) Ifitisnecessarytopassthroughapassagewaybetweenpassengercompartmentsto reachanyrequiredemergencyexitfromanyseatinthepassengercabin,thepassageway shallnotbeobstructed.However,curtainsmaybeusediftheyallowfreeentrythrough thepassageway. (o) Nodoormaybeinstalledinanypartitionbetweenpassengercompartments. (p) Ifitisnecessarytopassthroughadoorwayseparatingthepassengercabinfromother areastoreachanyrequiredemergencyexitfromanypassengerseat,thedoorshall haveameanstolatchitinopenposition,andthedoorshallbelatchedopenduring eachtake-offandlanding.Thelatchingmeansshallbeabletowithstandtheloads imposeduponitwhenthedoorissubjectedtotheultimateinertiaforces,relativeto thesurroundingstructure,prescribedintheairworthinessstandardsfortypecertification inthetransportcategoryascitedbytheAuthority. (q) Eachpassengeremergencyexitandthemeansofopeningthatexitfromtheoutside shallbemarkedontheoutsideoftheaeroplanewitha2-inchcolouredbandoutlining theexitonthesideofthefuselage. (r) Eachpassengeremergencyexitmarking,includingtheband,shallbereadilydistinguishable fromthesurroundingfuselageareabycontrastincolourandshallcomplywiththefollowing— (1) Ifthereflectanceofthedarkercolouris15percentorless,thereflectanceofthe lightercolourshallbeatleast45percent;and

(2) Ifthereflectanceofthedarkercolourisgreaterthan15percent,atleasta 30percentdifferencebetweenitsreflectanceandthereflectanceofthelighter colour shall be provided.

Note: “Reflectance” is the ratio of the luminous flux reflected by a body to the luminous flux it receives.

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(s) Exitsthatarenotinthesideofthefuselageshallhaveexternalmeansofopeningandapplicableinstructionsmarkedconspicuouslyinredor,ifredisinconspicuousagainstthebackgroundcolour,inbrightchromeyellowand,whentheopeningmeansforsuchanexitislocatedononlyonesideofthefuselage,aconspicuousmarkingtothateffectshall be provided on the other side.

(t) Eachpassenger-carryingaeroplaneshallbeequippedwithexteriorlightingthatmeetstherequirementsunderwhichthataeroplanewastypecertificated,unlesstheAuthoritycitesdifferentrequirementsforcompliancewiththisparagraph.

(u) Eachpassenger-carryingaeroplaneshallbeequippedwithaslip-resistantescaperoutethatmeetstherequirementsunderwhichthataeroplanewastypecertificated,unlesstheAuthoritycitesdifferentrequirementsforcompliancewiththisparagraph.

(v) Eachfloorleveldoororexitinthesideofthefuselage(otherthanthoseleadingintoacargoorbaggagecompartmentthatisnotaccessiblefromthepassengercabin)thatis44ormoreincheshighand20ormoreincheswide,butnotwiderthan46inches,eachpassengerventralexitandeachtailconeexit,shallmeettherequirementsofthissectionforfloorlevelemergencyexits.

Note: The Authority may grant a deviation from this paragraph if he finds that circumstances make full compliance impractical and that an acceptable level of safety has been achieved.

(w) Approved emergency exits in thepassenger compartments that are in excessoftheminimumnumberofrequiredemergencyexitsshallmeetalloftheapplicableprovisions of this subsection section and shall be readily accessible.

(x) Eachlargepassenger-carryingaeroplanewithaventralexitandtailconeexitshallbe—

(1) designedandconstructedsothatitcannotbeopenedduringflight;and

(2) marked with a placard readable from a distance of 30 inches and installed at a conspicuouslocationnearthemeansofopeningtheexit,statingthattheexithas beendesignedandconstructedsothatitcannotbeopenedduringflight.

(y) Portablelights-Nopersonmayoperateapassengercarryingaeroplaneunless it isequippedwith flight stowage provisions accessible from each cabin crewmemberseat.

PARTII—TheemergencyexitmarkinginRegulation41shallmeetthefollowingrequirements—

(a) Eachpassengeremergencyexitmarkingandeachlocatingsignshallhavewhiteletters1 inchhighon a redbackground2 incheshigh, be self or electrically illuminated,andhaveaminimumluminescence(brightness)ofatleast160microlamberts.Thecoloursmaybereversed if thiswill increase theemergencyilluminationofthepassengercompartment.

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(b) Thelocationofeachpassengeremergencyexitoperatinghandleandinstructionsforopeningshallbeshown—

(1) foreachemergencyexit,byamarkingonorneartheexitthatisreadablefroma distanceof30inches;and

(2) foreachTypeIorTypeIIemergencyexitwithalockingmechanismreleasedby rotary motion of the handle, by —

(i) aredarrow,withashaftatleastthree-fourthsinchwideandaheadtwicethe widthoftheshaft,extendingalongatleast70degreesofarcataradius approximatelyequaltothree-fourthsofthehandlelength,and (ii) theword“open”inredletters1inchhigh,placedhorizontallynearthe head of the arrow.

(c) Eachemergencyexit,anditsmeansofopening,shallbemarkedontheoutsideofthe rotorcraft.Inaddition,thefollowingapply—

(1) thereshallbea2-inchcolouredbandoutliningeachpassengeremergencyexit, exceptsmallrotorcraftwithamaximumweightof12,500poundsorlessmayhave a2-inchcolouredbandoutliningeachexitreleaseleverordeviceofpassenger emergencyexitswhicharenormallyuseddoors;and

(2) eachoutsidemarking,includingtheband,shallhavecolourcontrasttobereadily distinguishablefromthesurroundingfuselagesurface.Thecontrastshallbesuch that,ifthereflectanceofthedarkercolouris15percentorless,thereflectanceof thelightercolourmustbeatleast45percent.“Reflectance”istheratioofthe luminousfluxreflectedbyabodytotheluminousfluxitreceives.Whenthe reflectanceofthedarkercolourisgreaterthan15percent,atleasta30percent differencebetweenitsreflectanceandthereflectanceofthelightercolourmustbe provided.

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PASSENGEREMERGENCYEXITS:SIDE—OF-FUSELAGE

Emergencyexitsforeachsideofthefuselage

Passenger Seating Emergency exits for each side of thefuselage

Capacity Type I Type II Type III Type IV

1through10 1

11through19 1or 2

20through39 1

40through59 1 1

59through79 1 1or 2

SCHEDULE 6(regulation 44)

MAIN AISLE WIDTH

Main aisle width.

Themainpassengeraislewidthbetweenseatsmustequalorexceedthevaluesinthefollowingtable:

Minimummainpassenger aisle width

Passengerseating Lessthan25 25Inchescapacity inchesfromfloor andmore (inches) fromfloor (inches)

10 or less 12 15

11through19 12 20

20 or more 15 20

A narrower width of not less than 9 inches may be approved when substantiated by tests found necessary by the State of Manufacturer.

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EMERGENCY LOCATOR TRANSMITTER (ELT)

(a) Typesofemergencylocatortransmitters

(1) It is an ICAO recommendation that all ELTs should be automatic.

(2) The ELT equipment required shall meet the minimum performance standard definedinFAA’sTSOC91aorTSOC126:

Provided that any ELT installed prior to 1 January 1997 may meet the minimumperformancestandarddefinedinFAA’sTSOC90untilsuchtimeas itbecomesunserviceableotherthanthroughtheneedforroutinemaintenance, andfurthermoreprovidedthattheELTshallnotbefittedwithalithium-sulphur dioxidebatterythatdoesnotmeettherequirementsofFAA’sTSOC97.

(3) ThefollowingaretypesofELTsinuse—

(i) Automatic Fixed — ELT/AF This type of ELT is intended to be permanently attached to the aircraft beforeandafteracrashandisdesignedtoaidsearchandrescueteamsin locatingacrashsite.

(ii) Automatic Portable — ELT/AP ThistypeofELTisintendedtoberigidlyattachedtotheaircraftbeforea crash, but readily removable from the aircraft after a crash. It functions as anELTduringthecrashsequence.IftheELTdoesnotemployanintegral antenna,theaircraft-mountedantennamaybedisconnectedandanauxiliary antenna (stored on the ELT case) attached to the ELT. The ELT can be tethered to a survivor or a life raft. This type of ELT is intended to aid search and rescue teamsinlocatingthecrashsiteorsurvivor/s.

(iii) Automatic Deployable — ELT/AD ThistypeofELTisintendedtoberigidlyattachedtotheaircraftbeforethe crashandautomaticallyejectedanddeployedafterthecrashsensorhas determinedthatacrashhasoccurred.ThistypeofELTshouldfloatinwater andisintendedtoaidsearchandrescueteamsinlocatingthecrashsite.

(iv) Portable — ELT/P ThistypeofELTisnotintendedtoberigidlyattachedtotheaircraft before a crash, but carried in such a way that it is readily removable from the aircraftafteracrash.TheELTemploysanintegralantenna,andcanbe tethered to a survivor or a life raft. This type of ELT is intended to aid searchandrescueteamsinlocatingthecrashsiteorsurvivor/s.

(v) ELT(S)or(W)—ELT(survival)orELT(water-activated) ThistypeofELTisnotaffixedtotheaircraftandtransmitsautomatically whenimmersedinwater.Itiswaterproof,floatsandoperatesonthe surfaceofthewater.Ithasnofixedmounting.Itshouldbetetheredto survivors or life rafts.

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(b) Specification

Information on technical characteristics and operational performance of 121,5 MHz ELTsiscontainedinRTCADocumentDO-183andEUROCAEDocumentED.62.

(1) Specificationforthe121.5MHzcomponentofELTforsearchandrescue—

(i) the ELT shall operate on 121,5 MHz. The frequency tolerance shall not exceedplusorminus0,005%; (ii) the emission from an ELT under normal conditions and attitudes of the antennashallbeverticallypolarisedandessentiallyomni-directional inthehorizontalplane; (iii)overaperiodof48hoursofcontinuousoperation,atanoperating temperature of minus 200 Celsius, the peak effective radiated power (PERP)shallatnotimebelessthan50mW; (iv) the type of emission shall be A3X. Any other type of modulation that meetstherequirementsofsubparagraphs(e), (f) and (g) below may be used,providedthatitwillnotprejudicepreciselocationofthebeaconby homingequipment;

Note — some ELTs are equipped with an optional voice capability (A3E) in addition to the A3X emission.

(v) the carrier shall be amplitude modulated at a modulation factor of at least 0,85; (vi) the modulation applied to the carrier shall have a minimum duty cycle of33%; (vii) the emission shall have distinctive audio characteristics achieved by amplitudemodulatingthecarrierwithanaudiofrequencysweeping downwardoverarangeofnotlessthan700Hzwithintherange1600Hz to300Hzandwithasweeprepetitionrateofbetween2Hzand4Hz;and (viii) theemissionshallincludeaclearlydefinedcarrierfrequencydistinct from the modulation sideband components. In particular, at least 30% of the power shall be contained at all times within plus or minus 30Hz of the carrier frequency on 121,5 MHz.

(2) Specificationforthe406MHzcomponentofELTforsearchandrescue—

(i) transmissioncharacteristicsforELTsoperatingon406MHzarecontained inITUM633/1; (ii) information on technical characteristics and operational performance of 406MHzELTsiscontainedinRTCADocumentDO-204andEUROCAE DocumentED.62; (iii) ELTs shall operate on a frequency of 406,025 MHz plus or minus 2 kHz. The transmitted frequency shall not vary more than plus or minus 5 kHz in fiveyearsincludingtheinitialfrequencyoffset.Itshallnotvarymore than2partsin109milliseconds; (iv) theperiodbetweentransmissionsshallbe50secondsplusorminus5%; (v) overaperiodof24hoursofcontinuousoperationatanoperatingtemperture of minus 200 Celsius, the transmitter power output shall be within thelimitsof5Wplusorminus2dB;and (vi) the406MHzELTshallbecapableoftransmittingadigitalmessage.

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(3) Transmitteridentificationcoding— (i) ELTs operatingon406MHzshallbeassignedauniquecodingfor identificationofthetransmitteroraircraftonwhichitiscarried;and (ii) the ELT shall be coded in accordance with the aviation user protocol or oneoftheserialiseduserprotocolsandshallberegisteredwiththe Authority.

(c) Installation

(1) Each ELT, required to be carried in terms of SGR 7.9.1.5, must be attached to the aircraftinsuchamannerthattheprobabilityofdamagetothetransmitterin the event of crash impact is minimised. Fixed and deployable automatic ELTs must be attached to an aeroplane as far aft as possible. The installation of an ELT constitutesamodificationofanaircraftandmustthereforebecompletedin accordance with acceptable technical data. The acceptable standards should produce reliable and effective ELT systems, and keep unwanted activations to a minimum.Acceptablestandardsarebasedonthosesetoutinthefollowing sources —

(i) FAAAC91-44A(asamended);and (ii) RTCApapersDO-182andDO-183.

(2) Exceptwhereotherwisestated,thefollowinginstallationrequirementsshallapply to ELT installations in any aeroplane —

(i) when installed in an aeroplane, the ELT shall be mounted with its sensitive axispointinginthedirectionofflight; (ii) theELTshallbeinstalledtowithstandultimateinertiaforcesof10g upward,22.5gdownward,45gforwardand7.5gsideward; (iii)thelocationchosenfortheELTmustbesufficientlyfreefromvibration topreventinvoluntaryactivationofthetransmitter; (iv) the ELT shall be located and mounted so as to minimize the probability ofdamagetothetransmitterandantennabyfireorcrushingasaresult ofcrashimpact;and (v) the ELT shall be accessible for manual activation and deactivation.

(3) If it is equipped with an antenna for portable operation, the ELT shall be easily detachable from inside the aeroplane and —

(i) the external surface of the aeroplane shall be marked to indicate the locationoftheELT;and (ii) the ELT shall not use the antenna of another avionics system.

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(4) Theexternalantennalocationshallbechosenconsideringthefollowingfactors (i) the ELT antenna shall be mounted as far away as possible from other Very HighFrequency(VHF)antennas; (ii) the distance between the transmitter and antenna shall be in accordance withtheELTmanufacturer’sinstallationinstructionsorotherapproved data; (iii)thepositionoftheantennashallbesuchastoensureessentiallyomni- directionalsignaltransmissionswhentheaeroplaneisinitsnormalground orwaterattitude; (iv) theantennashallbemountedasfaraftaspossible; (v) theELTantennashallnotfoulotherantennasinflight;and (vi) theELTshallbesubjectedtoanoperationaltestasspecifiedinELT testingstandards.

(5) AnELTwithalithiumormagnesiumbatteryshallnotbepackedinsidealiferaft in an aeroplane.

(6) WheretheELTsystemincludesaremotecontrolsystemforactivatingand deactivatingthetransmitter,provisionshallbemadetopreventinadvertent operationoftheremotecontrolandaplacarddisplayingthefollowingwarning shall be placed near each remote control —

“FOR AVIATION EMERGENCY USE ONLY. UNAUTHORIZED OPERATION PROHIBITED.”

(7) Whenanaeroplaneisupright,anantennalocatedexternallyontopoftherear fuselageprovidesbetteroverallefficiencythananinternalcockpitareaantenna.

(8) When an aeroplane is inverted —

(i) aninternalantennaexhibitsthebestoverallefficiencyinahigh-wing aeroplane;and (ii) neitherantennalocationhasasignificantadvantageinalow-wing aeroplane.

(9) In helicopter installations, care needs to be taken to site the antenna so as to minimisevibratoryresponsewhichcouldleadtoprematurefatiguefailure. (10) The presence of an ELT whip antenna in close proximity to a second antenna can causesomedetuninganddistortionoftheradiationpatternofthesecondantenna andpossibleinterferencebyre-radiationofothersignals.e.g.therehavebeen reportsofanELTradiatingaweakharmonicsignaltoVHFtransmissions, causinginterferencewithGPSequipment.

(11) The ELT mount must provide a load path from aircraft primary structural elements directly to the automatic activation system. The attachment should also be free and clearofcablesandpulleys,etc.,andbedesignedtominimisevibration.Excessive vibrationmaypreventsatisfactorycrashimpactdetectionormaygeneratefalse crashsignals.Attachmentstothinpartitionsortopanels,suchasthesidesof baggagecompartments,shouldbeavoided.Attachmentssolelybymeansofvelcro stripsandotherflexiblematerial,suchastie-wrap,arenotacceptable.

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(12) Asapproximatelyonefifthoflightaircraftaccidentsresultinfire,thecoaxial cablebetweentheELTanditsexternalantennashouldbesleevedwithfire- resistant materials.

(13) Automaticfixed-type,inertially-activatedELTsareactivatedbyaninertialforce paralleltothelongitudinalaxisoftheaircraft.However,manyinadvertent activationshavebeencausedbyinertialswitchesactuatinginotherdirections. ForportableELTs,themanufacturer’sinstallationinstructionsmustbefollowed precisely since placement and orientation may be critical.

(14) TheinteractionofcomponentsintheELTisoftencriticalinarrivingatacceptable overall performance. Component parts from other sources such as batteries, coaxialcablesandantennae,shouldnotbesubstitutedfortheoriginal manufacturer’sparts.

(15) Tests after installation and tests and inspections of ELTs shall be performed.

(16) OncompletionofthemodificationtoinstalltheELTthecertifyingpersonshall— (i) ensurethattheinstallationisrecordedintheaircraftíslogbook;and (ii) placetheELTmanufacturer’soperatinginstructionsintheaircraftflight manual,unlesstherelevantinformationisalreadygiveninaflight manual supplement.

(17) Areleasetoservicestatementforthemodificationmustbeissued.

(d) Batteries

(1) Battery types in ELTs are as follows —

(i) mostcommonly:zinc-manganesedioxide(alkaline); (ii) magnesium-manganesedioxide(magnesium);and (iii) earlymodels:lithium-sulphurdioxide(lithium).

(2) Lithium-sulphurdioxidebatteriesmaybeusedonlyiftheymeettherequirements ofFAA’sTSOC97.

(3) TheELTbatteryexpirationdatemustbevisiblewithouthavingtoremovethe ELT from its mount in the aircraft.

(4) WhereELTbatteriescanbechargedduringflight,provisionshallbemadeto—

(i) indicatetotheflightcrewthatchargingistakingplace;and (ii) preventbatterydischargeresultingfromwiringshortcircuitsoccurring duringnormalserviceorfromcrashdamage.

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PORTABLE FIRE EXTINGUISHER

MinimumNumberofHandFireExtinguishers PassengerSeatingCapacity

7through29 1 30through60 2

61through200 3

201through300 4

301through400 5

401through500 6

501through600 7 601 or more 8

SCHEDULE 9(regulation 52)

MARKINGOFBREAK-INPOINTS

[AllAircraft(AAC)]Ifareasofthefuselagesuitableforbreak-inbyrescuecrewsinanemer-gencyaremarkedonanaeroplane,suchareasshallbemarkedasshownbelow,andthecolourof themarkingsshallberedoryellowand, ifnecessary, theyshallbeoutlinedinwhitetocontrastwiththebackground.

Ifthecornermarkingsaremorethan2mapart,intermediatelines9cmx3cmshallbeinsertedsothatthereisnomorethan2mbetweenadjacentmarkings.

10 cm

2.5 cm

not over 2 m

10 c

m

2.5 cm

2.5 cm

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FIRST-AIDKIT

(a) First-AidKits[AllAircraft]Types.Onetypeoffirst-aidkitshallbeprovidedforcarriagein all aircraft.

(1) [AIRCRAFT IN COMMERCIAL OPERATIONS] Therequiredfirst-aidkitsshallincludeatleastthefollowingequipment—

Contents

Antiseptic swabs (10/pack) Bandage:adhesivestrips Bandage:gauze7.5cmx4.5m Bandage:triangular;safetypins Dressing:burn10cmx10cm Dressing:compress,sterile7.5cmx12cm Dressing:gauze,sterile10.4cmx10.4cm Tape: adhesive 2.5 cm (roll) Steri-strips(orequivalentadhesivestrip) Handcleanserorcleansingtowelettes Pad with shield, or tape, for eye Scissors:10cm(ifallowedbynationalregulations) Tape:Adhesive,surgical1.2cmx4.6m Tweezers: splinter Disposablegloves(multiplepairs) Thermometers(non-mercury) Mouth-to-mouthresuscitationmaskwithone-wayvalve First-aidmanual,currentedition Incident record form

(2) [AIRCRAFT IN COMMERCIAL OPERATIONS]

Contents.

Therequiredfirst-aidkitsmayincludethefollowingmedicationswherepermitted bynationalregulations—

Mildtomoderateanalgesic; Antiemetic; Nasaldecongestant; Antacid; Antihistamine.

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(3) [AIRCRAFT IN COMMERCIAL OPERATIONS] Numberoffirst-aidkits.

Eachaircraftshallcarryfirst-aidkitsinaccordancewiththefollowingtable—

NumberofPassengerSeats NumberofFirst-AidKits

0 — 100 1 101 — 200 2 201 — 300 3 301 — 400 4 401 — 500 5 More than 500 6

(4) [AIRCRAFT IN COMMERCIAL OPERATIONS]

Location.

Therequiredfirst-aidkitsbedistributedevenlythroughouttheaircraft,andshall be readily accessible to cabin crew members, if cabin crew members are required fortheflight;and Thefirst-aidkitsshallbelocatedneartheaircraftexitsshouldtheiruseberequired outsidetheaircraftinanemergencysituation.


EMERGENCY MEDICAL KIT – AEROPLANES

(a) [AirOperatorCertificate(AOC)] Therequiredemergencymedicalkitshallincludethefollowingequipment—

Airways,oropharyngeal(threesizes) Antiseptic wipes. Bag-valvemask. Basic life support cards. Disposable scalpel handle and blade. Disposablesyringesandneedles; Emergencytrachealcatheter(orlargegaugeintravenouscannula). Flashlightandbatteries. Haemostaticbandagesortourniquet. Haemostatic forceps. Intravenouscatheters(appropriaterangeofsizes). Needle disposal box. Onepairofsterilesurgicalgloves.

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Sphygmomanometer. Spongegauze. Sterileequipmentforsuturingwounds. Sterile scissors. Stethoscope. Surgicalmask. Systemfordeliveringintravenousfluids. Tape — adhesive. Thermometers(non-mercury). Umbilical cord clamp. Urinary catheter.

(b) [AOC] Therequiredemergencymedicalkitshallincludethefollowingmedications—

Acetyl salicylic acid (aspirin) for oral use Adrenocorticalsteroid—injectable Antiemetic—injectable Antihistamine—injectableanti-allergic Atropine—injectable Bronchial dilator — inhaler Dextrose50%(orequivalent)—injectable:50mlSedatives. Diuretic—injectable Epinephrine1:1000Analgesics. Sedativeanticonvulsant—injectable Majoranalgesic Medicationforpostpartumbleeding Nitro-glycerinetablets,orspray Oral beta blocker Sodium chloride 0.9% (minimum 250 ml)

(c) [AOC] Therequireduniversalprecautionkitshallincludethefollowingequipment—

Bio-hazarddisposalwastebag Drypowderthatcanconvertsmallliquidspillintoasterilegranulatedgel Face/eye mask (separate or combined) Germicidaldisinfectantforsurfacecleaning Gloves (disposable) Instructions: Largeabsorbenttowel Pick-upscoopwithscraper Protective apron Skin wipes

(d) [AOC] The medical kit shall be stored in a secure location.

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OXYGEN STORAGE AND DISPENSING APPARATUS

(a) Thesupplementaloxygensupplyrequirementsfornon-pressurisedaeroplanesareas follows —

(1) Anoperatorshallnotoperateanon-pressurisedaeroplaneatpressurealtitudes above10000ftunlesssupplementaloxygenequipment,capableofstoringand dispensingtheoxygensuppliesrequired,isprovided.

(2) Theamountofsupplementaloxygenforsustenancerequiredforaparticular operationshallbedeterminedonthebasisofflightaltitudesandflightduration, consistentwiththeoperatingprocedures,establishedforeachoperationinthe OperationsManualandwiththeroutestobeflown,andwiththeemergency proceduresspecifiedintheOperationsManual.

(3) An aeroplane intended to be operated above 10 000 ft pressure altitude shall be providedwithequipmentcapableofstoringanddispensingtheoxygensupplies required.

(4) Oxygensupplyrequirements.

(i) Flightcrewmembers-Eachmemberoftheflightcrewonflightdeckduty shallbesuppliedwithsupplementaloxygeninaccordancewithTable1. Ifalloccupantsofflightdeckseatsaresuppliedfromtheflightcrew sourceofoxygensupplythentheyshallbeconsideredasflightcrew membersonflightdeckdutyforthepurposeofoxygensupply.

(ii) Cabincrewmembers,additionalcrewmembersandpassengers–Cabin crewmembersandpassengersshallbesuppliedwithoxygenin accordance with Table 1. Cabin crew members carried in addition to the minimum number of cabin crew members required, and additional crew members,shallbeconsideredaspassengersforthepurposeofoxygen supply.

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Table1-SupplementalOxygenforNon-PressurisedAeroplanes

(a) (b)

SUPPLY FOR: DURATION AND PRESSURE ALTITUDE

1. Alloccupantsofflightdeckseats Entireflighttimeatpressurealtitudesabove onflightdeckduty 10,000feet

2.Allrequiredcabincrewmembers Entireflighttimeatpressurealtitudesabove 13,000ftandforanyperiodexceeding30minutes atpressurealtitudesabove10,000ftbutnotexceeding 13,000 ft

3.100%ofpassengers(seenote) Entireflighttimeatpressurealtitudesabove13,000ft

4.10%ofpassengers(seenote) Entireflighttimeafter30minutesatpressure altitudesgreaterthan10,000ftbutnotexceeding 13,000 ft

Note: For the purpose of this table “passengers” means passengers actually carried and includes infants.

(b) Thesupplementaloxygensupplyrequirementsforpressurisedaeroplanesareas follows —

(1) An operator shall not operate a pressurised aeroplane at pressure altitudes above 10000ftunlesssupplementaloxygenequipment,capableofstoringanddispensing theoxygensuppliesrequiredbythisparagraph,isprovided.

(2) Theamountofsupplementaloxygenrequiredshallbedeterminedonthebasisof cabinpressurealtitude,flightdurationandtheassumptionthatacabinpressurisation failurewilloccuratthealtitudeorpointofflightthatismostcriticalfromthestandpoint ofoxygenneed,andthat,afterthefailure,theaeroplanewilldescendinaccordance withemergencyproceduresspecifiedintheAeroplaneFlightManualtoasafealtitude fortheroutetobeflownthatwillallowcontinuedsafeflightandlanding.

(3) Followingacabinpressurisationfailure,thecabinpressurealtitudeshallbeconsidered the same as the aeroplane pressure altitude, unless it is demonstrated to the Authority that no probable failure of the cabin or pressurisation system will result in a cabin pressure altitude equal to the aeroplane pressure altitude. Under these circumstances, the demonstrated maximum cabin pressure altitude may be used as a basis for determinationofoxygensupply.

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(4) Oxygenequipmentandsupplyrequirements.

(i) Flightcrewmembers.

(a) Eachmemberoftheflightcrewonflightdeckdutyshallbesupplied withsupplementaloxygen inaccordancewithTable2. Ifall

occupants of flight deck seats are supplied from the flight crewsourceofoxygensupplythentheyshallbeconsideredasflightcrewmembersonflightdeckdutyforthepurposeofoxygensupply.

(b) Flightdeckseatoccupants,notsuppliedbytheflightcrewsource,aretobeconsideredaspassengersforthepurposeofoxygensupply.

(c) Oxygenmasks shallbe locatedsoas tobewithin the immediatereachofflightcrewmemberswhilstattheirassigneddutystation.

(d) Oxygenmasks for use by flight crewmembers in pressurisedaeroplanesoperatingatpressurealtitudesabove25000ft,shallbeaquickdonningtypemask.

(ii) Cabincrewmembers,additionalcrewmembers,andpassengers.

(a) Cabin crew members and passengers shall be supplied withsupplementaloxygen inaccordancewithTable2. Cabincrewmembers carried in addition to the minimum number of cabin crew members required, and additional crew members, shall be consideredaspassengersforthepurposeofoxygensupply.

(b) Aeroplanes intended to be operated at pressure altitudes above 25000ftshallbeprovidedsufficientspareoutletsandmasksand/orsufficientportableoxygenunitswithmasksforusebyall required cabin crew members. The spare outlets and/or portableoxygenunitsaretobedistributedevenlythroughoutthe cabin to ensure immediate availability of oxygen to eachrequiredcabincrewmemberregardlessofhislocationat thetime of cabin pressurisation failure.

(c) Aeroplanes intended to be operated at pressure altitudes above 25000ftshallbeprovidedanoxygendispensingunitconnectedtooxygensupplyterminalsimmediatelyavailabletoeachoccupant,wheneverseated.Thetotalnumberofdispensingunitsandoutletsshall exceed the number of seats by at least 10 percent. The extra unitsshallbeevenlydistributedthroughoutthecabin.

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(d) Aeroplanes intended to be operated at pressure altitudes above 25 000 ft or which, if operated at or below 25 000 ft, cannot descend safely within four minutes to 13 000 ft, and for which the individual certificate of airworthinesswas first issued onor after 9 November 1998, shall be provided with automatically deployable oxygen equipment immediately available to eachoccupant,whereverseated.Thetotalnumberdispensingunitsand outlets shall exceed the number of seats by at least 10 percent. Theextraunitsshallbeevenlydistributedthroughoutthecabin.

(e) The oxygen supply requirements, as specified in Table 2, foraeroplanesnotcertificatedtoflyataltitudesabove25,000ft,maybereducedtotheentireflighttimebetween10,000ftand13,000ftcabin pressure altitudes for all required cabin crew members and

foratleast10%ofthepassengersif,atallpointsalongtherouteto beflown,theaeroplaneisabletodescendsafelywithin4minutes to a cabin pressure altitude of 13,000 ft.

Table2—RequirementsforSupplementalOxygen-PressurisedAeroplaneDuringandFollowingEmergencyDescent(Note)

SUPPLY FOR: DURATION AND CABIN PRESSURE ALTITUDE

1. Alloccupantsofflightdeckseats Entireflighttimewhenthecabinpressure onflightdeckdutyflight altitudeexceeds13,000andentiretimewhen the cabin pressure altitude exceeds 10,000 ft but does not exceed 13,000 ft after the first 30 minutes at those altitudes, but in no case less than:

(i) 30minutesforaeroplanescertificatedto flyataltitudesnotexceeding25,000ft (Note 2) (ii) 2hoursforaeroplanescertificatedtofly at altitudes more than 25,000 ft (Note 3).

2.Allrequiredcabincrewmembers Entireflighttimewhencabinpressurealtitude exceeds 13,000 ft but not less than 30 minutes (Note2),andentireflighttimewhencabin pressurealtitudeisgreaterthan10,000ft butdoesnotexceed13,000ftafterthefirst 30 minutes at these altitudes.

3.100%ofpassengers 10minutesortheentireflighttimewhenthe cabin pressure altitude exceeds 13,000 ft whicheveristhegreater(Note4)

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4.10%ofpassengers Entireflighttimewhenthecabinpressure altitude exceeds 10,000 ft but does not exceed13,000ftafterthefirst30minutes at these altitudes.

Note 1: The supply provided shall take account of the cabin pressure altitude and descent profile for the routes concerned.

Note 2: The required minimum supply is that quantity of oxygen necessary for a constant rate of descent from the aeroplane’s maximum certificated operating altitude to 10,000 ft in 10 minutes and followed by 20 minutes at 10,000 ft.

Note 3: The required minimum supply is that quantity of oxygen necessary for a constant rate of descent from the aeroplane’s maximum certificated operating altitude to 10,000 ft in 10 minutes and followed by 110 minutes at 10,000 ft. The oxygen required to meet the Crew Protective Breathing Equipment provisions of this Part may be included in determining the supply required.

Note 4: The required minimum supply is that quantity of oxygen necessary for a constant rate of descent from the aeroplane’s maximum certificated operating altitude to 15,000 ft.

Note 5: For the purpose of this table “passengers” means passengers actually carried and includes infants.

(c) Thesupplementaloxygensupplyrequirementsfornon-pressurisedhelicoptersareas follows —

(1) Anoperatorshallnotoperateanon-pressurisedhelicopteratpressurealtitudesabove10000ftunlesssupplementaloxygenequipment,capableofstoringanddispensingtheoxygensuppliesrequired,isprovided.

(2) The amount of supplemental oxygen for sustenance required for a particularoperationshallbedeterminedonthebasisofflightaltitudesandflightduration,consistentwiththeoperatingprocedures,establishedforeachoperationintheOperationsManual andwith the routes tobeflown, andwith theemergencyproceduresspecifiedintheOperationsManual.

(3) A helicopter intended to be operated above 10 000 ft pressure altitude shall be providedwithequipmentcapableofstoringanddispensingtheoxygensuppliesrequired.

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(4) Oxygensupplyrequirements—

(i) Flightcrewmembers.Eachmemberoftheflightcrewonflightdeckduty shallbesuppliedwithsupplementaloxygeninaccordancewithTable3.If alloccupantsofflightdeckseatsaresuppliedfromtheflightcrewsource ofoxygensupplythentheyshallbeconsideredasflightcrewmemberson flightdeckdutyforthepurposeofoxygensupply.

(ii) Cabincrewmembers,additionalcrewmembersandpassengers.Cabincrew membersandpassengersshallbesuppliedwithoxygeninaccordance with Table 3. Cabin crew members carried in addition to the minimum number of cabin crew members required, and additional crew members, shall be consideredaspassengersforthepurposeofoxygensupply.

Table3—SupplementalOxygenforNon-PressurisedHelicopters

(a) (b)

SUPPLY FOR: DURATION AND PRESSURE ALTITUDE

1. Alloccupantsofflightdeckseats Entireflighttimeatpressurealtitudesabove onflightdeckduty 10,000feet

2.Allrequiredcabincrewmembers Entireflighttimeatpressurealtitudesabove 13,000ftandforanyperiodexceeding 30 minutes at pressure altitudes above 10,000 ft butnotexceeding13,000ft

3.100%ofpassengers(seenote) Entireflighttimeatpressurealtitudesabove 13,000 ft

4..10%ofpassengers(seenote) Entireflighttimeafter30minutesatpressure altitudesgreaterthan10,000ftbutnot exceeding13,000ft

Note: For the purpose of this table “passengers” means passengers actually carried and includes infants.

MADE this 18th day of December, 2012.

HON. NONOFO MOLEFHI,Minister for Transport and Communications.

civil aviation (equipment and instruments) … · 24. mach number indicator 25. loss of...

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