AIR NAVIGATION ORDER … · D2.5.2 A seat belt for each seat, ... The color of the markings shall be red or yellow, and if necessary they shall be out-lined in white to contrast with

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AIRCRAFT INSTRUMENTS, EQUIPMENT AND DOCUMENTS FOR FLIGHT

AIR NAVIGATION ORDER

VERSION : 3.0 DATE OF IMPLEMENTATION : 04-04-2011 OFFICE OF PRIME INTEREST : Airworthiness Directorate

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A. AUTHORITY: A1. This Air Navigation Order is issued by Director General Civil Aviation Authority in pursuance of Rules 4, 5, 180, 248, 252, 253, 334 (3), 360 and all other enabling provision of Civil Aviation Rules 1994 (CARs 94).

B. PURPOSE: B1. In addition to the minimum equipment necessary for the issuance of a Certificate of Airworthiness, the instruments, equipment and documents prescribed in this Air Navigation Order shall be installed or carried, as appropriate, in aeroplane/helicopter according to the aeroplane/ helicopter used and to the circumstances under which the flight is to be conducted.

C. SCOPE: C1. This ANO is applicable to all air operators involved in operation of aeroplanes / helicopters in Pakistan.

D. DESCRIPTION: D1. DEFINITIONS:

D1.1 The following terms when used in this ANO, have the meanings assigned to them respectively.

Any term used in this ANO but not defined, shall have the same meaning as given in the Civil Aviation Ordinance, 1960, Pakistan Civil Aviation Authority Ordinance 1982, CARs, 1994 and relevant ICAO Annexes.

D1.2 Type I and IAFDR: shall record the parameters required to determine accurately the

aeroplane flight path, speed, attitude, engine power, configuration and operation. D1.3 Type II and IIA FDR:, shall record the parameters required to determine accurately the

aeroplane flight path, speed, attitude, engine power, configuration of lift and drag devices.

D1.4 Type IV FDR: shall record the parameters required to determine accurately the

helicopter flight path, speed, attitude, engine power and operation. D1.5 Type IVA FDR: shall record the parameters required to determine accurately the

helicopter flight path, speed, attitude, engine power, operation and configuration. D1.6 Type V FDR: shall record the parameters required to determine accurately the

helicopter flight path, speed, attitude and engine power. D2. APPLICABILITY: D2.1. ALL AEROPLANES / HELICOPTERS ON ALL FLIGHTS:

An Aeroplane / helicopter shall be equipped with instruments which will enable the flight crew to control the flight path of the aeroplane / helicopter, carry out any required procedural maneuvers and observe the operating limitations of the aeroplane / helicopter in the expected operating conditions.


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D2.2. FIRST AID / MEDICAL KITS: D2.2.1. Accessible and adequate first aid kit appropriate to the number of passengers an aeroplane / helicopter is authorized to carry. D2.2.2. Medical kit for the use of medical doctors or other qualified persons in treating in-flight medical emergencies for aeroplane authorized to carry more than 100 passengers, on the sector length of more than two hours.

D2.2.3. Universal precaution kit shall be carried on an aeroplane/helicopter that is required to operate with at least one cabin crew member. Note: Requirements for first aid kit, medical kits and universal precaution kit are prescribed in latest

version of Airworthiness Notice No.AWNOT-019-AWXX.

D2.3. Number of first-aid kits required for an aeroplane / helicopter are detailed below:-

No. of passenger seats installed

No. of First Aid Kits required

0 to 100 1 101 to 200 2 201 to 300 301 to 400

3 4

401 to 500 5 More than 500 6

D2.4. FIRE EXTINGUISHER: D2.4.1 Portable fire extinguisher of a type which, when discharged, will not cause dangerous contamination to the air within the aeroplane / helicopter. At least one will be located:

D2.4.1.1 in the pilot’s compartment; and

D2.4.1.2 each passenger compartment that is separate from the pilot’s compartment and that is not readily accessible to the flight crew.

D2.4.2 The numbers of fire extinguishers required and that must be conveniently located in the passenger compartment(s) are detailed below:

Max. approved passenger seating

configuration Number of Extinguishers.

1 to 30 1 31 to 60 2 61 to 200 3

201 to 300 4 01 to 400 5

401 to 500 6

Note: Any portable fire extinguisher so fitted in accordance with the certificate of airworthiness of the aeroplane may count as one prescribed.


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D2.5. SEATS, SEAT SAFETY BELTS, HARNESSES AND INFANT RESTRAINT DEVICES:

D2.5.1 A seat or berth for each person who is aged two years or more.

D2.5.2 A seat belt for each seat, restraining belts for each berth and a supplement loop belt or other restraint device for each infant.

D2.5.3 A safety harness for each flight crew seat. The safety harness for each pilot seat shall incorporate a device which will automatically retrain the occupant's torso in the event of rapid deceleration.

D2.5.4 The safety harness for each pilot seat should incorporate a device to prevent a suddenly incapacitated pilot from interfering with the flight controls.

Note: Safety harness includes shoulder straps and seat belt, which may be used independently.

D2.6. MEANS OF ENSURING INFORMATION AND INSTRUCTIONS TO PASSENGERS: D2.6.1 Means of ensuring that the following information and instructions are conveyed to passengers through announcement and/or demonstration:

D2.6.1.1 When seat belts are to be fastened

D2.6.1.2 When and how oxygen equipment is to be used if the carriage of oxygen is required;

D2.6.1.3 Restriction on smoking;

D2.6.1.4 Location and usage of life jackets and/or equivalent individual flotation devices where their carriage is required; and

D2.6.1.5 Location and method of opening emergency exits.

D2.6.1.6 Other emergency equipment provided for individual use, including passenger emergency cards.

D2.7. ELECTRICAL FUSES: D2.7.1 Spare electrical fuses of appropriate ratings for replacement of those accessible in flight.

D2.8. MARKINGS OF BREAK-IN POINTS:

D2.8.1 If areas of the fuselage suitable for break-in by rescue crews in emergency are marked on an aeroplane such areas shall be marked as shown below. The color of the markings shall be red or yellow, and if necessary they shall be out-lined in white to contrast with the background. If the corner marking are more than 2m apart, intermediate lines 9 cm x 3 cm shall be inserted so that there is no more than 2m between adjacent markings.

09 cm 09 cm

03 cm

Not over 2 m

09 cm

03 cm

MARKING OF BREAK-IN POINTS


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D2.9. LEAST RISK BOMB LOCATION:

D2.9.1 The operator is required to coordinate with the manufacturer in order to identify a least risk location on the aeroplane where bomb or other explosive device may be placed to minimize the effects on aeroplane in case of detonation. The information regarding least risk location shall be incorporated in the Aeroplane Flight Manual / Flight Crew Operating Manual and additionally, this information shall be included in cabin crew Training Manual.

D3. INTERNATIONAL COMMERCIAL AIR TRANSPORT – AEROPLANES FDR (FLIGHT DATA RECORDER) D3.1 All multi-engined turbine-poweredengined aeroplanes of a maximum certificated take-off mass of 5 700 kg or less for which the individual certificate of airworthiness is first issued on or after 1 January 1990 should be equipped with a Type IIA FDR. D3.2 All turbine-engined aeroplanes of a maximum certificated take-off mass of 5 700 kg or less for which the individual certificate of airworthiness is first issued on or after 1 January 2016 should be equipped with: D3.2.1 a Type II FDR; or D3.2.2 a Class C AIR (Aircraft Image Recorder) capable of recording flight path and speed

parameters displayed to the pilot(s); or D3.2.3 an ADRS (Aircraft Data Recoding System) capable of recording the essential

parameters given below: D3.2.3.1 Heading (Magnetic or True). D3.2.3.2 Pitch attitude. D3.2.3.3 Roll attitude. D3.2.3.4 Yaw rate. D3.2.3.5 Pitch rate. D3.2.3.6 Roll rate. D3.2.3.7 Positioning system; latitude/longitude. D3.2.3.8 Positioning system estimated error. D3.2.3.9 Positioning system; altitude. D3.2.3.10 Positioning system; time*. D3.2.3.11 Positioning system; ground speed. D3.2.3.12 Positioning system; channel. D3.2.3.13 Normal acceleration. D3.2.3.14 Longitudinal acceleration. D3.2.3.15 Lateral acceleration. D3.3 All aeroplanes of a maximum certificated take-off mass of over 27 000 kg for which the individual certificate of airworthiness is first issued on or after 1 January 1989 shall be equipped with a Type I FDR. D3.4 All aeroplanes of a maximum certificated take-off mass of over 5 700 kg, up to and including 27 000 kg, for which the individual certificate of airworthiness is first issued on or after 1 January 1989, shall be equipped with a Type II FDR.


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D3.5 All turbine-engined aeroplanes, for which the individual certificate of airworthiness was first issued on or after 1 January 1987 but before 1 January 1989, with a maximum certificated take-off mass of over 5 700 kg, shall be equipped with an FDR which shall record time, attitude, airspeed, normal acceleration and heading. D3.6 All turbine engine aeroplane of a maximum certificated take-off weight of over 27000 Kg shall be equipped with a flight data recorder which shall record time, attitude, airspeed, normal acceleration and heading. D3.7 All turbine-engined aeroplanes, for which the individual certificate of airworthiness was first issued before 1 January 1987, with a maximum certificated take-off mass of over 27 000 kg that are of types of which the prototype was certificated by the appropriate national authority after 30 September 1969 should be equipped with an FDR which should record, in addition to time, attitude, airspeed, normal acceleration and heading, such additional parameters as are necessary to meet the objectives of determining: D3.7.1 the attitude of the aeroplane in achieving its flight path; and D3.7.2 the basic forces acting upon the aeroplane resulting in the achieved flight path and the

origin of such basic forces. D3.8 All aeroplanes which are required to record normal acceleration, lateral acceleration and longitudinal acceleration for which a type certificate is first issued on or after 1st January 2016 and which are required to be fitted with an FDR shall record those parameters at a maximum sampling and recording interval of 0.0625 seconds. D3.9 All aeroplanes which are required to record pilot input and/or control surface position primary controls (pitch, roll, yaw) for which a type certificate is first issued on or after 1st January 2016 and which are required to be fitted with an FDR shall record those parameters at a maximum sampling and recording interval of 0.125 seconds. D3.10 DISCONTINUITY D3.10.1 Metal foil type FDR shall be discontinued. D3.10.2 FDR, using frequency modulation (FM) shall be discontinued. D3.10.3 Use of analog FDRs using frequency modulation FM shall be discontinued by 1st

January 2012. D3.10.4 Use of photographic film FDR shall be discontinued. D3.10.5 The use of magnetic tape FDRs shall be discontinued by 1 January 2016. D3.11 DURATION D3.11.1 All FDRs shall be capable of retaining the information recorded during at least the last 25 hours of their operation, except for the Type IIA FDR which shall be capable of retaining the information recorded during at least the last 30 minutes of its operation.


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D4. CVRS (COCKPIT VOICE RECORDERS) CARS (COCKPIT AUDIO RECORDING SYSTEM) D4.1 All turbine-engined aeroplanes for which the individual certificate of airworthiness is first issued on or after 1 January 2016 and required to be operated by more than one pilot should be equipped with either a CVR or a CARS.

D4.2 All aeroplanes of a maximum certificated take off mass of over 5700 kg for which the indivisual Certificate of Airworthiness is first issued and or after 1st January 2003 shall be equipped with CVR capable of repairing the information recorded during at least the last two hours of its operation. D4.3 All aeroplanes of maximum certificated take off mass of over 5700 kg for which the individual Certificate of Airworthiness is first issued on or after 1st January 1987 shall be equipped with CVR. D4.4 All turbine-engined aeroplanes of, for which the individual certificate of airworthiness was first issued before 1 January 1987, with a maximum certificated take-off mass of over 5700 kg up to and including 27000 kg that are of types of which the prototype was certificated by the appropriate national authority after 30 September 1969 should be equipped with a CVR. D4.5 All turbine engined aeroplanes for which individual Certificate of Airworthiness was first issued before 1st January 1987 with maximum certificated take off mass of over 27000 kg that are of types of which prototype was certificated by appropriate national authority after 30th September 1969 shall be equipped with CVR. D4.6 DISCONTINUITY D4.6.1 The use of magnetic tape and wire CVRs shall be discontinued by 1 January 2016.

D4.7 DURATION D4.7.1 All CVRs shall be capable of retaining the information recorded during at least the last 30 minutes of operation. D4.7.2 From 1 January 2016, all CVRs shall be capable of retaining the information recorded during at least the last two hours of their operation. D4.8 RECORDERS INDEPENDENT POWER D4.8.1 The independent power source shall automatically engage and provide ten minutes of operation whenever aircraft power to the recorder ceases, either by normal shutdown or by any other loss of power to the reorder. D4.8.2 For all aeroplanes for which the individual certificate of airworthiness is first issued on or after 1 January 2016 and which are required to be fitted with a CVR, the independent power source should power exclusively the CVR and the cockpit area microphone components.


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D4.8.3 From 1 January 2016, for all aeroplanes required to be equipped with a CVR, the CVR should be provided with an independent power source. In installations where two CVRs are fitted in aeroplanes the forward CVR should be provided with an independent power source. D4.9 DATA LINK RECORDERS D4.9.1 All aeroplanes for which the individual certificate of airworthiness is first issued on or after 1 January 2016, or modified after 1st January, 2016, which utilize any of the data link communications applications listed below and are required to carry a CVR, shall record on a flight recorder the data link communications messages. D4.9.1.1 Data link initiation capability. D4.9.1.2 Controller – pilot data link communications. D4.9.1.3 Data link – flight information services. D4.9.1.4 Automatic dependent surveillance – contract. D4.9.1.5 Automatic dependent surveillance – broadcast*. D4.9.1.6 Aeronautical operational control*. Note: Application with * mark shall be recorded only as far as practicable given the architecture of the system. D4.10 DURATION D4.10.1 The minimum recording duration shall be equal to the duration of the CVR. D4.11 FLIGHT & RECORDER ELECTRONIC DOCUMENTATION D4.11.1 The documentation requirement concerning FDR parameters provided by operators to accident investigation authorities should be in electronic format and take account of industry specifications. D4.12 COMBINATION RECORDERS D4.12.1 All aeroplanes of a maximum certificated take-off mass of over 15 000 kg for which the type certificate is first issued on or after 1 January 2016 and which are required to be equipped with both a CVR and an FDR, shall be equipped with two combination recorders (FDR/CVR). One recorder should be located as close to the cockpit as practicable and the other recorder located as far aft as practicable. D4.13 INTERNATIONAL GENERAL AVIATION – AEROPLANES FDR (Flight Data Recorder) D4.13.1 All turbine-engined aeroplanes of a maximum certificated take-off mass of 5 700 kg or less for which the individual certificate of airworthiness is first issued on or after 1 January 2016 should be equipped with: D4.13.1.1 a Type II FDR; or D4.13.1.2 a Class C AIR capable of recording flight path and speed parameters displayed to

the pilot(s); or D4.13.1.3 an ADRS capable of recording the following 14 essential parameters:


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1. Pitch attitude………………………………… If not available record rate. 2. Roll attitude.……………………………… If not available record rate. 3. Yaw rate.……………………………… essential if no heading available. 4. Pitch rate.……………………………… essential if no pitch available. 5. Roll rate.……………………………… essential if no roll attitude available. 6. Positioning system latitude/longitude. 7. Positioning system estimated error.………if available. 8. Positioning system altitude. 9. Positioning system time.…………………UTC time preferred where available. 10. Positioning system ground speed. 11. Positioning system channel. 12. Normal acceleration. 13. Longitude acceleration. 14. Lateral acceleration.

D4.13.2 All aeroplanes of a maximum certificated take-off mass of over 5 700 kg for which the individual certificate of airworthiness is first issued on or after 1 January 2005 shall be equipped with a Type IA flight data recorder FDR. D4.13.3 All aeroplanes of a maximum certificated take-off mass of over 27 000 kg for which the individual certificate of airworthiness is first issued on or after 1 January 1989 shall be equipped with a Type I flight data recorder FDR. D4.13.4 All aeroplanes of a maximum certificated take-off mass of over 5 700 kg, up to and including 27 000 kg, for which the individual certificate of airworthiness is first issued on or after 1 January 1989, should be equipped with a Type II flight data recorder FDR. D4.13.5 All aeroplanes for which a type certificate is first issued on or after 1 January 2016 and which are required to be fitted with an FDR, shall record the following parameters at a maximum recording interval of 0.125 seconds: D4.13.6 Pilot input and/or control surface position – primary controls (pitch, roll, yaw). Note-1: For aeroplanes with conventional control systems “or” applies. For aeroplanes with non-mechanical control systems “and” applies. In aeroplanes with independent moveable surfaces, each surface needs to be recorded separately. In aeroplanes with independent pilot input on primary controls,each pilot input on primary controls needs to be recorded separately. Note-2: Type certificate first issued refers to the date of issuance of the original “Type Certificate” for the aeroplane type, not the date of certification of particular aeroplane variation or derivative models. D4.14 DISCONTINUITY D4.14.1 Engraving metal foil FDRs shall be discontinued. D4.14.2 Use of analogue FDRs using frequency modulation shall be discontinued by 1st

January 2012.


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D4.14.3 The use of magnetic tape FDRs should be discontinued by 1 January 2016. D4.15 DURATION D4.15.1 All FDRs shall be capable of retaining the information recorded during last 25 hours of their operation. D4.16 COCKPIT VOICE RECORDER & COCKPIT AUDIO RECORDING SYSTEM D4.16.1 All turbine-engined aeroplanes for which a Type Certificate of first issued on or after 1st January 2016 are required to be operated by more than one pilot shall be equipped with either CVR or CARS. D4.16.2 All aeroplanes of a maximum certificated take-off mass of over 27 000 kg for which the individual certificate of airworthiness is first issued on or after 1 January 1987 shall be equipped with a cockpit voice recorder CVR. D4.17 DISCONTINUITY D4.17.1 Use of magnetic type and wire CVRs shall be discontinued by 1st January 2016. D4.18 DURATION D4.18.1 All CVRs shall be capable of retaining the information during at least the last 30 minutes of operation. D4.18.2 From 1st January 2016 all CVRs shall be capable of retaining information recorded during at least last two hours of their operation. D4.19 RECORDER INDEPENDENT POWER D4.19.1 The independent power source shall authentically engage and provide ten minutes of operation whenever aircraft power to the recorder cases either by normal shutdown or by any other loss of power to the recorder. D4.20 DATA LINK RECORDERS D4.20.1 All aeroplanes which are modified on or after 1 January 2016 to install and utilize any of the data link communications applications listed below and are required to carry a CVR, shall record on a flight recorder the data link communications messages. D4.20.1.1 Data link initiation capability. D4.20.1.2 Controller – pilot data link communications. D4.20.1.3 Data link – flight information services. D4.20.1.4 Automatic dependent surveillance – contract. D4.20.1.5 Automatic dependent surveillance – broadcast*. D4.20.1.6 Aeronautical operational control*. Note: Applications with * mark to be recorded only as far as is practicable given the architecture of the system.


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D4.21 DURATION D4.21.1 The minimum recording duration be equal to duration of CVR. D4.22 FLIGHT RECORDER ELECTRONIC DOCUMENTATION D4.22.1 The documentation requirement concerning FDR parameters provided by operators to accident investigation authorities should be in electronic format and take account of industry specifications. Note: Industry specification for documentation concerning FDR parameters may be found in the ARINC 647A, Flight Recorder Electronic Documentation, or equivalent document. D5. INTERNATIONAL FLIGHT DATA RECORDER COMMERCIAL OPERATIONS – HELICOPTERS D5.1. FDR (Flight Data Recorder) D5.1.1 All helicopters of maximum certificated take-off mass of over 3180 kg for which the individual certificate of airworthiness is first issued on or after 1st January 2016 shall be equipped within a Type-IVA FDR. D5.1.2 All helicopters of a maximum certificated take-off mass of over 7 000 kg, or having a passenger seating configuration of more than nineteen, for which the individual certificate of airworthiness is first issued on or after 1 January 1989 shall be equipped with a Type IV FDR. D5.2. DISCONTINUITY D5.2.1 The use of engraving metal foil FDRs shall be discontinued. D5.2.2 The use of photographic film FDRs shall be discontinued. D5.2.3 The use of analogue FDRs using frequency modulation (FM) should be discontinued. D5.2.4 The use of analogue FDRs using frequency modulation (FM) shall be discontinued by 1 January 2012. D5.2.5 The use of magnetic tape FDRs shall be discontinued by 1 January 2016. D5.3. DURATION D5.3.1 Types IV, IVA FDRs shall be capable of retaining the information recorded during at least the last ten hours of their operation. D5.4. COCKPIT VOICE RECORDER D5.4.1 All helicopter of maximum certificated type of mass of over 7000 kg for which the individual certificate of airworthiness is first issued before and after 1st January 1987 shall be


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equipped with CVR for helicopters not equipped with FDR al least main rotor speed shall be recorded on the CVR. D5.5. DISCONTINUITY D5.5.1 The use of magnetic tape and wire CVRs shall be discontinued by 1st January, 2010. D5.6. DURATION D5.6.1 A CVR shall be capable of retaining the information recorded during at least the last 30 minutes of its operation. D5.6.2 From 1 January 2016, all helicopters required to be equipped with a CVR shall be equipped with a CVR capable of retaining the information recorded during the last two hours of its operation. D5.7. RECORDER INDEPENDENT POWER D5.7.1 The independent power source shall automatically engage and provide 10 minutes of operation whenever aircraft power to the recorder cases, wither by normal shutdown or by any other loss of power to the recorders. D5.7.2 For all helicopters for which the type certificate is first issued on or after 1 January 2016 and required to be fitted with a CVR, the CVR shall be provided with an independent power source that should power exclusively the CVR and the cockpit area microphone components. Note: For all helicopters for which the individual is first issued on or after 1st January 2016 and which are required to be fitted with CVR, the CVR shall be provided with an independent power source that shall power exclusively the CVR and the cockpit area microphone components. D5.8. DATA LINK RECORDER D5.8.1 All helicopters for which the individual certificate of airworthiness is first issued on or after 1st January, 2016 and all helicopters which are modified on or after 1st January 2016 to install and utilize any of the data link communication applications listed below and are required to carry a CVR shall record on a flight recorder the data link communications messages:- D5.8.1.1 Data link initiation capability. D5.8.1.2 Controller Pilot data link communications. D5.8.1.3 Data link flight information services. D5.8.1.4 Automatic dependent surveillance contract. D5.8.1.5 Automatic dependent surveillance – broadcast *. D5.8.1.6 Aeronautical operational control *. Note: Application with * mark are to be recorded only as far as is practicable given the architecture of system. D5.9. DURATION D5.9.1 The minimum recording duration shall be equal to the recorded cockpit audio.


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D5.10. GENERAL AVIATION HELICOPTER, INSTRUMENT EQUIPMENT & FLIGHT DOCUMENTS D5.10.1 All helicopter of maximum certificated take off mass of over 7000 kg or having passenger seating capacity of more than 19 for which individual certificate of airworthiness is first issued on or after 1st January 1989 shall be equipped with type IV FDR. D5.11. DISCONTINUITY D5.11.1 The use of engraving metal foil FDR, shall be discontinued. D5.11.2 The use of photographic film FDRs shall be discontinued. D5.11.3 The use of analogue FDRs using frequency modulation (FM) shall be discontinued by 1st January 2012. D5.11.4 The use of magnetic tape FDRs shall be discontinued by 1st January 2016. D5.12. DURATION D5.12.1 Type IV and IVA shall be capable of retaining the information recoded during at least the last ten (10) hours of their operation. D5.13. CVR D5.13.1 All helicopters of a maximum certificated take-off mass of over 7 000 kg for which the individual certificate of airworthiness was first issued before and after 1 January 1987 shall be equipped with a CVR. For helicopters not equipped with an FDR, at least main rotor speed shall be recorded on the CVR. D5.14. DISCONTINUITY D5.14.1 The use of magnetic tape and wire CVRs shall be discontinued by 1 January 2016. D5.15. DURATION D5.15.1 A CVR shall be capable of retaining the information recoded during at least the last 30 minutes of its operation. D5.15.2 From 1 January 2016, all helicopters required to be equipped with a CVR shall be equipped with a CVR capable of retaining the information recorded during the last two hours of its operation. D5.16. RECORDER INDEPENDENT POWER D5.16.1 The independent power source shall automatically engage and provide ten (10) minutes of operation whenever aircraft powered to the recorder ceases, either by normal shutdown or by any other loss of power to the recorder.


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D5.17. DATA LINK RECORDERS D5.17.1 All helicopter for which individual Certificate of Airworthiness is first issued on or after 1st January 2016 or modified on or after 1ST January 2016 to install and utilize any of the data link communication application listed below and are required to carry a CVR shall record on a flight recorder the data link communication. D5.17.1.1 Data link initiation capability. D5.17.1.2 Controller – pilot data link communications. D5.17.1.3 Data link – flight information services. D5.17.1.4 Automatic dependent surveillance – contract. D5.17.1.5 Automatic dependant surveillance – broadcast *. D5.17.1.6 Aeronautical operational control *. Note: Application with * are to be recorded as well as is practicable given the architecture of the system. D5.18. DURATION D5.18.1 The minimum recording duration shall be equal to the duration of the CVR. D6. ALL AEROPLANE/HELICOPTER OPERATED IN ACCORDANCE WITH VISUAL FLIGHT RULE D6.1 All aeroplanes/helicopters when operated as VFR flights shal be equipped with: D6.1.1 a magnetic compass; D6.1.2 an accurate timepiece indicating the time in hours, minutes and seconds; D6.1.3 a sensitive pressure altimeter; D6.1.4 an airspeed indicator; and D6.1.5 such additional instruments or equipment as may be prescribed by the Civil Aviation Authority. D7. ALL AEROPLANES ON FLIGHTS OVER WATER

D7.1 all seaplanes for all flights shall be equipped with:

D7.1.1 one life jacket, or equivalent individual floatation device, for each person on board, stowed in a position easily accessible from the seat or berth of the person for whose use it is provided; D7.1.2 equipment for making the sound signals prescribed in the International Regulations for Preventing Collisions at Sea, where applicable; and D7.1.3 one sea anchor (drogue). Note: Seaplanes" includes amphibians operated as seaplanes"

D7.2 Landplanes shall carry the equipment prescribed in D7.3.

D7.2.1 when flying over water and at a distance of more than 93 km (50 NM) away from the shore, in the case of landplanes operated in accordance with their performance operating limitations.


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D7.2.2 when flying en route over water beyond gliding distance from the shore, in the case of all other land-planes; and D7.2.3 when taking off or landing at an aerodrome where, in the opinion of the PCAA, the take-off or approach path is so disposed over water that in the event of a mishap there would be a likelihood of a ditching. D7.3 The equipment referred to in D7.1.4 shall comprise one life jacket or equivalent individual floatation device for each person on board, stowed in a position easily accessible from the seat or berth of the person for whose use it is provided.

Note: “Landplanes” includes amphibians operated as landplanes.

D7.4 All aeroplanes on long range over-water flights - In addition to the equipment prescribed in D7.1.1 or D7.2 whichever is applicable, the following equipment shall be installed in all aeroplanes when used over routes on which the aeroplane may be over water and at more than a distance corresponding to 120 minutes at cruising speed of 740 km (400 NM), whichever is the lesser, away from land suitable for making an emergency landing in the case of aeroplane operated in accordance with its performance operating limitations and 30 minutes or 185 km (100 NM), whichever is the lesser, for all other aeroplane:

D7.4.1 Life-saving rafts in sufficient numbers to carry all persons on board, stowed so as to facilitate their ready use in emergency, provided with such life-saving equipment including means of sustaining life as is appropriate to the flight to be undertaken; and D7.4.2 Equipment for making the pyrotechnical distress signals described in ICAO Annex 2. D7.5 Each life jacket and equivalent individual floatation device, when certified in accordance with D7.1.1, D7.2 and D7.3, shall be equipped with a means of electric illumination for the purpose of facilitating the location of persons, except where the requirement of D7.2.3 is met by the provision of individual floatation devices other than life jackets. D8. ALL HELICOPTERS ON FLIGHT OVER WATER D8.1 Means of floatation - All helicopters intended to be flown over water shall be fitted with a permanent or rapidly deployable means of floatation so as to ensure a safe ditching of the helicopter when: D8.1.1 flying over water at a distance from land corresponding to more than 10 minutes at normal cruise speed in the case of performance Class 1 or 2 helicopters; or D8.1.2 flying over water beyond auto-rotational or safe forced landing distance from land in the case of performance Class 3 helicopters. D8.2 Emergency equipment - Performance Class 1 and 2 helicopters, operating in accordance with the provisions of D8.1, shall be equipped with:

D8.2.1 One life jacket, or equivalent individual flotation device, for each person on board, stowed in a position easily accessible from the seat or berth of the person for whose use it is provided; D8.2.2 Life-saving rafts in sufficient numbers to carry all persons on board, stowed so as to facilitate their ready use in emergency, provided with such life-saving equipment including means of sustaining life as is appropriate to the flight to be undertaken; and


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D8.2.3 Equipment for making the pyrotechnical distress signals described in ICAO Annex 2. D8.3 Performance Class 3 helicopters when operating beyond auto-rotational distance from land but within a distance from land specified by the CAA shall be equipped with one life jacket, or equivalent individual floatation device, for each person on board, stowed in a position easily accessible form the seat or berth of the person for whose use it is provided.

Note: When determining the distance from land referred to in D8.2 consideration should be given to environmental conditions and the availability of SAR facilities.

D8.4 Performance Class 3 helicopters when operating outside the provisions of D8.2 shall be equipped as in D8.3.

D8.5 In the case of performance Class 2 and Class 3 helicopters, when taking off or landing at a heliport where in the opinion of the CAA, the take-off or approach path is so disposed over water that in the event of a mishap there would be likelihood of a ditching, at least the equipment required in D8.2.1 shall be carried.

D8.6 Each life jacket and equivalent individual floatation device, when carried in accordance with D8, shall be equipped with means of electric illumination for the purpose of facilitating the location of persons.

D8.7 On any helicopter for which the individual certificate of airworthiness is first issued on or after 1 January 1991, at least 50 per cent of the life rafts carried in accordance with the provisions of D8.2. should be deployable by remote control.

D8.8 Rafts which are not deployable by remote control and which have a weight of more than 40 Kg should be equipped with some means of mechanically assisted deployment.

D8.9 On any helicopter for which the individual certificate of Airworthiness was first issued before 1 January 1991, the provisions of D8.7 and D8.8 should be complied with no later than 31 December 1992. D9. ALL AEROPLANES / HELICOPTERS ON FLIGHT OVER DESIGNATED LAND AREA

D9.1 All aeroplanes / helicopters, when operated across land areas which have been designated by the CAA as areas in which search and rescue would be especially difficult, shall be equipped with:

D9.1.1 Signaling devices; and D9.1.2 Life saving equipment (including means of sustaining life) as may be appropriate to the area over

flown.

D9.2 All aeroplanes / helicopters on high altitude flights

Note: Approximate altitude in the Standard Atmosphere corresponding to the value of absolute pressure used in this text is as follows:

Absolute Pressure

Meters Feet

700 hPa 3000 10000 620 hPa 4000 13000 376 hPa 7600 25000


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D9.2.1 An aeroplane/helicopter intended to be operated at flight altitudes at which the atmospheric pressure is less then 700 hPa in personnel compartments shall be equipped with oxygen storage and dispensing apparatus capable of storing and dispensing the oxygen supplies required in CAR 94 Rule 249(1). D9.2.2 An aeroplane/ helicopter intended to be operated at flight altitudes at which the atmospheric pressure is less than 700 hPa but which is provided with means of maintaining pressures greater than 700 hPa in personnel compartments shall be provided with oxygen storage and dispensing apparatus capable of storing and dispensing the oxygen supplies as required in Rule 249(2) of Civil Aviation Rules 1994. D9.2.3 Pressurized aeroplane newly introduced into service on or after 1st July 1962 and intended to be operated at flight altitudes at which the atmospheric pressure is less than 376 hPa shall be equipped with a device to give positive warning to the pilot of any dangerous loss of pressurization. D9.2.4 A flight to be operated with a pressurized aeroplane shall not be commenced unless a sufficient quantity of stored breathing oxygen is carried to supply all the crew members and passengers, as is appropriate to the circumstances of the flight being undertaken, in the event of loss of pressurization, for any period that the atmospheric pressure in any compartment occupied by them would be less than 700hPa. In addition, when an aeroplane is operated at flight altitudes at which the atmospheric pressure is less than 376 hPa, or which, if operated at flight altitudes at which the atmospheric pressure is more than 376 hPa and cannot descend safely within four minutes to a flight altitude at which the atmospheric pressure is equal to 620 hPa, there shall be not less than a 10-minute supply for the occupants of the passenger compartment.

D9.2.5 An aeroplane intended to be operated at flight altitudes at which the atmospheric pressures is less than 376 hPa, cannot descend safety within four minutes to a flight attitude at which the atmospheric pressure is equal to 620 hPa and for which the individual certificate of airworthiness is issued on or after 9th November 1998 shall be provided with automatically deployable oxygen equipment to satisfy the requirements of D2.10.41.4 the total number of oxygen dispensing units shall exceed the number of passenger and cabin attendant seats by at least 10 per cent.

D9.2.6 An aeroplane intended to be operated at flight attitudes at which the atmospheric pressure is less than 376 hPa or which if operated at flight attitudes at which the atmospheric pressure is more than 376 hPa cannot descend safely within four minutes to a flight attitude at which the atmospheric pressure is equal to 620 hPa, and for which the individual certificate of airworthiness was issued before 9th November 1998, should be provided with automatically deployable oxygen equipment to satisfy the requirements of D2.10.41.4 the total number of oxygen dispensing units should exceed the number of passenger and cabin attendant seats by at least 10 per cent.

D9.2.7 A flight to be operated with a pressurized helicopter shall not be commenced unless a sufficient quantity of stored breathing oxygen is carried to supply all the crew members and passengers, as is appropriate to the circumstances of the flight being undertaken, in the event of loss of pressurization, for any period that the atmospheric in any compartment occupied by them would be less than 700 hPa. In addition, when the helicopter is operated at flight altitudes at which the atmospheric pressure is more than 376 hPa and cannot descend safely to a flight altitude at which the atmospheric pressure is equal to 620 hPa within four minutes, there shall be no less than 10- minute supply for the occupants of the passenger compartment.

D9.2.8 A helicopter intended to be operated at flight altitudes at which the atmospheric pressure is more than 376 hPa which cannot descend safely within four minutes to a flight altitude at which the atmospheric pressure is equal to 620 hPa, and for which the individual certificate of airworthiness was issued on or after 9th November 1998, shall be provided with automatically deployable oxygen equipment to satisfy the requirements of D2.10.41.8 the total number of oxygen dispensing units shall exceed the number of passenger and cabin attendant seats by at least 10 per cent.


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D9.2.9 Un-pressurized helicopter intended to be operated at high altitudes shall carry equipment for storing and dispensing the oxygen supplies.

D10. ALL AEROPLANES / HELICOPTERS IN ICING CONDITIONS

D10.1 All aeroplanes / helicopters shall be equipped with suitable anti-icing and / or de-icing devices when operated in circumstances in which icing conditions are reported to exist or are expected to be encountered.

D11. ALL AEROPLANES / HELICOPTERS OPERATED IN ACCORDANCE WITH INSTRUMENT FLIGHT RULES

D11.1 All aeroplanes / helicopters when operated in accordance with the instrument flight rules or when the aeroplane cannot be maintained in a desired attitude without reference to one or more flight instruments shall be equipped with:

D11.1.1 A magnetic compass; D11.1.2 An accurate timepiece indicating the time in hours, minutes and seconds; D11.1.3 Two sensitive pressure altimeters with counter drum-pointer or equivalent presentation; Note: - Neither three-pointer nor drum-pointer altimeters satisfy the requirement in D11.1.3 above. D6.5.1.4. An airspeed indicating system with means of preventing malfunctioning due to either condensation or icing.

D6.4.1 A turn and slip indicator., D6.4.2 An attitude indicator (artificial horizon); D6.4.3 A heading indicator (directional gyroscope);

Note: The requirements of D6.4.1, D6.4.2 and D6.4.3 above may be met by combinations of instruments or by integrated flight director systems provided that the safeguards against total failure, inherent in the three separate instruments, are retained.

D6.4.4 A means of indicating whether the power supply to the gyroscopic instrument is adequate; D6.4.5 A means of indicating in the flight crew compartment the outside air temperature; D6.4.6 A rate-of-climb and descent indicator; D6.4.7 For helicopter a stabilization, unless it has been demonstrated to the satisfaction of the certification authority that the helicopter possesses by nature of its design, adequate stability with such a system; and D6.4.8 Such additional instruments or equipment as may be prescribed by the PCAA. D11.2 All aeroplanes over 5700 kg Emergency power supply for electrically operated attitude indicating Instruments.

D11.2.1 All aeroplanes of a maximum certificated take-off weight of over 5 700 kg newly introduced into service after 1 January 1975 and all performance Class I and Class II helicopters when operated in accordance with IFR shall be fitted with an emergency power supply, independent of the main electrical generating system, for the purpose of operating and illuminating, for a minimum period of 30 minutes, an attitude indicating instrument (artificial horizon), clearly visible to the pilot-in-command. The emergency power supply shall be automatically operative after the total failure of the main electrical


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generating system and clear indication shall be given on the instrument panel that the attitude indicators is being operated by emergency power. D11.2.2 Those instruments that are used by any one pilot, shall be so arranged as to permit the pilot to see their indications readily from his or her station, with the minimum practicable deviation from the position and line of vision normally assumed when looking forward along the flight path. D11.3 All performance Class 1 and Class 2 helicopters when operated in accordance with the instrument flight rules shall be fitted with an emergency power supply, independent of the main electrical generating system, for the purpose of operating and illuminating, for a minimum period of 30 minutes, an attitude indicating instrument (artificial horizon), clearly visible to the pilot-in-command. The emergency power supply shall be automatically operative after the total failure of the main electrical generating system and clear indication shall be given on the instrument panel that the attitude indicator(s) is being operated by emergency power.

D12. ALL AEROPLANES / HELICOPTERS WHEN OPERATED AT NIGHT D12.1 All aeroplanes / helicopters when operated at night shall be equipped with: D12.1.1 Flight instruments as mentioned in D2.10.42; D12.1.2 The lights required by ICAO Annex 2 for the aeroplane in flight or operating on the

movement area of an aerodrome/ heliport.

Note: Specifications for lights meeting the requirements of ICAO Annex 2 for navigation lights are contained in Appendix 1 of chapter 6 ICAO Annex 6 Part I. The general characteristics of lights are specified in Annex 8. Detailed specifications for lights meeting the requirements of ICAO Annex 2 for aeroplane in flight or operating on the movement area of an aerodrome are contained in ICAO Airworthiness Manual (Doc 9760).

D12.1.3 Two landing lights for Regular Public Transport category and helicopter.

Note: Aeroplane not certificated in accordance with ICAO Annex 8 which are equipped with a single landing light having two separately energized filaments will be considered to have complied with D2.10.44.1.3.

D12.1.4 One landing light for General Aviation category

D12.1.5 Illumination for all instrument and equipment that are essential for the safe operation of the aeroplane that are used by the flight crew,

D12.1.6 Lights in all passenger compartments; and

D12.1.7 An electric torch for each crewmember station.

D12.2 One of the landing lights in helicopters should be trainable, at least in the vertical plane.

D13. WEATHER RADAR

D13.1 Pressurized aeroplane and helicopters when carrying passengers should be equipped with operative weather radar whenever such aeroplane / helicopters are being operated in areas where thunderstorms or other potentially hazardous weather conditions regarded as detectable with airborne


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weather radar may be expected to exist along the route either at night or under instrument meteorological conditions.

D14. ALL AEROPLANES OPERATED ABOVE 15 000 M (49 000 FT) - RADIATION INDICATOR

D14.1 All aeroplanes intended to be operated above 15 000 m (49 000 ft) shall carry equipment to measure and indicate continuously the dose rate of total cosmic radiation being received (i.e. the total of ionizing and neutron radiation of galactic and solar origin) and the cumulative dose on each flight. The display unit of the equipment shall be readily visible to a flight crewmember.

Note.- The equipment is calibrated on the basis of assumptions acceptable to the state of Design / manufacture.

D15. MACH NUMBER INDICATOR

D15.1 All aeroplanes with speed limitations expressed in terms of Mach number shall be equipped with a Mach number indicator. Note: This does not preclude the use of the airspeed indicator to derive Mach number for ATS

purposes.

D16. GROUND PROXIMITY WARNING SYSTEM (GPWS) D16.1 All turbine-engined aeroplanes of a maximum certificated take-off mass in excess of 5700 kg or authorized to carry more than nine passengers shall be equiped with a ground proximity warning system. D16.2 All turbine-engined aeroplanes of a maximum certificated take-off mass in excess of 15000 kg or authorized to carry more than 30 passengers shall be equipped with a ground proximity warning system which has a forward looking terrain avoidance function. D16.3 All turbine engine aeroplane of a maximum certificated take-off weight in excess of 5700 Kg or authorized to carry more than nine passengers, for which the individual certificate of airworthiness is first issued on or after 1st January 2004, shall be equipped with a ground proximity warning system which has a forward looking terrain avoidance function. D16.4 From 1st January, 2008 all turbine-engined aeroplanes of maximum certificated take-off mass in excess of 5700 kg or authorized to carry more than nine passengers, shall be equipped with a ground proximity warning system which has a forward looking terrain avoidance function. D16.5 From 1st January 2007 all piston-engined aeroplanes of a maximum certificated take-off mass in excess of 5700 kg or authorized to carry more than nine passengers shall be equipped with a ground proximity warning system which provides the warning in 3.xx a) and c), warning of unsafe terrain clearance and forward looking terrain avoidance function.

D16.6 A ground proximity warning system shall provide automatically a timely and distinctive warning to the flight crew when the aeroplane is in potentially hazardous proximity to the earth’s surface. The GPWS shall also provide, as a minimum, warning of the following circumstances:

D16.6.1 excessive descent rate; D16.6.2 excessive terrain closure rate;


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D16.6.3 excessive altitude loss after take-off or go-around; D16.6.4 unsafe terrain clearance while not in landing configuration; D16.6.5 gear not locked down; D16.6.6 flaps not in a landing position; and

D16.7 excessive decent below the instrument glide path.

Note: Enhance Ground Proximity System (EGPWS) AND Terrain Awareness Warning System (TAWS) are also required.

D17. AEROPLANE / HELICOPTER CARRYING PASSENGERS-CABIN CREW SEATS

D17.1 All aeroplanes / helicopters shall be equipped with a forward or rearward facing (within 15 degrees of the longitudinal axis of the aeroplane) seat, fitted with a safety harness for the use of each cabin crew member required to effect a safe and expeditious evacuation of the aeroplane and the necessary functions to be performed in an emergency or a situation requiring emergency evacuation. The operator shall assign there functions for each type of aeroplane. Note: - Safety harness includes shoulder straps and a seat belt which may be used independently.

D17.2 Cabin crew seats provided in accordance with D16.2 shall be located near floor level and other emergency exits as may be prescribed by the CAA for emergency evacuation.

D18. EMERGENCY LOCATOR TRANSMITTER (ELT)

D18.1 Except as provided for in D18.2, until 1 January 2005 all aeroplanes operated on long-range over-water flights as described in D8 shall be equipped with at least two ELT(S). D18.2 All aeroplanes for which the individual certificate of airworthiness is first issued after 1 January 2002, operated on long-range over-water flights as described in D8, shall be equipped with at least two ELTs, one of which shall be automatic. D18.3 From 1 January 2005, all aeroplanes operated on long-range over-water flights as described in D2.10.31 shall be equipped with at least two ELTs, one of which shall be automatic. D18.4 Except as provided for in D18.5, until 1 January 2005 aeroplanes on flights over designated land areas as described in D9 shall be equipped with at least one ELT(S). D18.5 All aeroplanes for which the individual certificate of airworthiness is first issued after i January 2002, on flights over designated land areas as described in D9, shall be equipped with at least one automatic ELT. D18.6 From 1 January 2005, aeroplanes on flights over designated land areas as described in D9 shall be equipped with at least one automatic ELT. D18.7 ELT equipment carried to satisfy the requirements of D18 shall operate in accordance with the relevant provisions of Annex 10, Volume III. Note 1: ELT operatble on 406 MHZ & 121.5 MHZ frequencies, in case of General Aviation Operator

shall be complianed from 01.January 2009.


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Note 2: ITU Radio Regulations (S5.256 and Appendix S13) provide for the use of 243 MHz in

addition to the above frequencies.

D19. AEROPLANE SHALL BE EQUIPPED WITH AIRBORNE COLLISION AVOIDANCE SYSTEM (ACAS II)

D19.1 From 1 January 2003, all turbine-engined aeroplane of a maximum certificated take-off weight in excess of 15 000 kg or authorized to carry more than 30 passengers shall be equipped with an airborne collision avoidance system (ACAS 11). D19.2 From 1 January 2005, all turbine-engined aeroplane of a maximum certificated take-off weight in excess of 5700 Kg or authorized to carry more than 19 passengers shall be equipped with an airborne collision avoidance system (ACAS II). D19.3 An airborne collision avoidance system shall operate in accordance with the relevant provisions of Annex 10, Volume IV. D19.4 Aeroplane / helicopter required to be equipped with a pressure-altitude reporting transponder. D19.5 All aeroplanes / helicopters shall be equipped with a pressure-altitude reporting transponder which operates in accordance with the relevant provisions of ICAO Annex 10, Volume IV.

Note: This provision is intended to improve the effectiveness of air traffic services as well as airborne

collision avoidance systems.

D20. MICROPHONES

D20.1 All flight crew members required to be on flight deck duty shall communicate through boom or throat microphones below the transition level/ altitude.

D21. CREW PROTECTIVE BREATHING EQUIPMENT

D21.1 All aeroplanes / helicopters having a maximum certificated take-off weight of 5700 Kg and above or with seating capacity of 19 or more passengers shall be equipped with Protective Breathing Equipment (PBE) or an equipment to protect the eyes, nose and mouth of each flight crew and cabin crew members. The equipment shall be located at or adjacent to the hand fire extinguisher from where it is easily accessible for immediate use. It shall provide oxygen for a period of not less than 15 minutes. PBE for cabin crew shall be portable type and while it is in use, must not prevent communication where required.

D22. EMERGENCY LIGHTING SYSTEM

D22.1 An aeroplane which has a maximum approved passenger seating configuration of more than 19 shall have an emergency lighting system having its own independent power supply. The system shall include: D23. SOURCES OF GENERAL CABIN ILLUMINATION D23.1 Internal lighting in floor level emergency exit areas or Passengers Emergency Evacuation Path Lighting System (PEEPLS).


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D23.2 Illuminated emergency exit marking and location signs; and D23.3 when flying by night, exterior emergency lighting at all overwing exits / emergency exits, where descent assist means are required. D23.4 A helicopter which has a maximum approved passenger seating configuration of more than 19 shall have an emergency lighting system having its own independent power supply to provide a source of general cabin illumination to facilitate the evacuation of the passengers ; and illuminate emergency exit marking and locating signs. D24. LAVATORY FIRE PROTECTION

D24.1 Aeroplane each lavatory compartment shall be equipped with an approved smoke detection system which shall provide a warning light and/or aural warning in the passenger compartment, so located as to be readily seen or heard by a flight attendant and/or a warning light in the flight compartment or appropriate equivalent arrangement. D24.2 Built-in fire extinguisher shall be installed for each disposable receptacle for towels, paper and waste or appropriate equivalent arrangements in the aeroplane lavatory compartment. D25. CRASH AXE AND / OR CROWBAR D25.1 All aeroplanes / helicopters with a maximum certificated take-off weight of exceeding 5700 kg or a maximum approved passenger seating configuration of more than 09 seats shall be equipped with one crash axe or crowbar located in the flight deck. If the maximum approved passenger seating configuration of more than 200 an addition crash axe or crowbar must be carried and located in or near the most rearwards galley area.

D26. COMMUNICATION EQUIPMENT

D26.1 All aeroplanes / helicopters shall be provided with radio communication equipment capable of : D26.1.1 Conducting two-way communication for aerodrome control purposes; D26.1.2 receiving meteorological information at any time during flight; and D26.1.3 conducting two-ways communication at any time during flight with at least one

aeronautical station and with such other aeronautical stations and on such frequencies as may be prescribed by the Civil Aviation Authority.

D26.1.4 When compliance with D2.10.60.1.3 requires that more than one communication equipment unit be provided, 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. D26.1.5 A helicopter to be operated in accordance with the visual flight rules, but as a controlled flight, shall unless exempted by the CAA, be provided with radio communication equipment capable of conducting two-way communication at any time during the flight with such aeronautical stations and on such frequencies as may be prescribed by CAA. D26.1.6 A helicopter to be operated on a flight to which the provisions of D2.10.32 or D2.10.40 apply shall, unless exempted by the CAA, be provided with radio communication equipment capable of conducting two-way communication at any time during flight with such aeronautical stations and on such frequencies as may be prescribed by CAA.


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Note: The requirenents of D2.10.60.1 are considered fulfilled if the ability to conduct the

communications specified therein is established during radio propagation conditions which are normal for the route.

D26.1.7 The radio communication equipment required in accordance with D2.10.60.1 shall provide for communications on the aeronautical emergency frequency 121.5 MHz. D27. NAVIGATION EQUIPMENT

D27.1 An aeroplane / helicopter shall be provided with navigation equipment which will enable it to proceed: D27.1.1 in accordance with its operational flight plan; D27.1.2 in accordance with prescribed PBN types; and D27.1.3 in accordance with the requirements of air traffic services; except when, if not so precluded

by the Civil Aviation authority, navigation for flights under the visual flight rules is accomplished by visual reference to landmarks.

Note: Information on PBN and associated procedures is contained in ICAO Manual on Required

Navigation Performance (RNP) (Doc 9613), and PCAA Airworthiness Notice No. AWNOT-070-AWXX-2.0.

D27.2 For flights in defined portions of airspace where, based in Regional Air Navigation Agreement, minimum navigation performance specifications (MNPS) are prescribed, an aeroplane shall be provided with navigation equipment which:

D27.3 continuously provides indications to the flight crew of adherence to or departure from track to the required degree of accuracy at any point along that treack; and D6.19.1 has been authorized by the Civil Aviation Authority for MNPS operations concerned. Note: The prescribed minimum navigation performance specifications and the procedures governing

their application are published in ICAO Regional Supplemenrary Procedures (Doc 7030)

D27.4 For flights in defined portions of airspace where, based on Regional Air Navigation Agreement, a vertical separation minimum (VSM) of 300 m(1000 ft) is applied above FL 290, an aeroplane shall be provided with equipment which is capable of:

D27.4.1 indicating to the flight crew the flight level being flown; D27.4.2 automatically maintaining a selected flight level; D27.4.3 providing an alert to the flight crew when a deviation occurs from the selected flight level.

The threshold for the alert shall not exceed + 90 m (300 ft); D27.4.4 automatically reporting pressure-altitude; and D27.4.5 shall be authorized by the CAA for operation in the airspace concerned. D27.4.6 The aeroplane shall be suficiently provided with navigation equipment to ensure that, in the event of the failure of one item of equipment at any stage of the flight, the remaining equipment will enable the aeroplane to navigate in accordance with D2.10.65.1 and where applocable D2.10.65.2 and D2.10.65.3.


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Note: Guidance material relating to aeroplane equipment necessary for flight in airspace where a 300 m (1000 ft) VSM is applied above FL 290 is contained in ICAO Manual on Implementation of a 300 m (1000 ft) Vertical Separation Minimum Between FL 290 and FL 410 Inclusive (Doc 9574).

D27.4.7 On flights in which it is intended to land in instrument meteorological conditions an aeroplane shall be provided with radio equipment capable of receiving signals providing guidance to a point from which a visual landing can be effected.This equipment shall be capable of providing such guidance at each aerodrome at which it is intended to land in instrument meteorological condition and at any designated alternate aerodromes. D28. INSTALLATION D28.1 The equipment installation shall be such that the failure of any single unit required for either communucations or navigation purposes or both will not result in the failure of another unit required for communucations or navigation purposes.

D29. PUBLIC ADDRESS SYSTEM

D29.1 Public Address System which shall be audible at all passenger seats, lavatories and flight attendant seats and work stations for aeroplane / helicopter with a seating capacity of more than 19 passengers and shall be capable of operation from pilots and cabin attendant station(s).

D30. MEGAPHONES D30.1 Portable battery powered megaphones shall be readily accessible for use by crew members during emergency evacuation of passengers. One megaphone shall be installed at the rearward location in the passenger cabin for the normal crew seat for aeroplane with seating capacity of more than 30 and less than 100 passengers. Two megaphones, one is installed at the forward location and other is installed at the most rearward location of passenger cabin for normal crew seats for aeroplane with seating capacity of more than 100 passengers. D30.2 Helicopter with a maximum approved passenger-seating configuration of more than 19 shall be equipped with a portable battery powered megaphone readily accessible for use by crew members during emergency evacuation. D31. DOCUMENTS FOR FLIGHT D31.1 An aeroplane / helicopter shall be provided with manuals, placards or other documents specified below:

D31.2 Flight manual, placards or other documents stating the approved limitations with which the aeroplane is considered airworthy as defined by the appropriate Airworthiness requirements, and additional instructions and information necessary for the safety of the aeroplane.

D31.2.1 Certificate of Registration D31.2.2 Certificate of Airworthiness D31.2.3 Certificate of Maintenance Review D31.2.4 Certificate of Release to Service D31.2.5 Certificate for Radio Installation D31.2.6 PTA License for Radio Set Operators D31.2.7 Approved weight and balance schedule


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D31.2.8 Noise Certificate issued in accordance with the latest issue of Airworthiness Notice No. AWNOT-062-AWXX.

D32. AMENDMENTS AND MODIFICATIONS:

D32.1 Any subsequent amendments or modifications to this ANO may be processed and incorporated through Airworthiness Directorate, HQ CAA, in consultation with Chief Legal Services, HQ CAA as and when required or deemed expedient or appropriate. E. EVIDENCES (ACRONYMS / RECORDS / REFERENCES):

E1. ACRONYMS:

ANO AIR NAVIGATION ORDER CAA CIVIL AVIATION AUTHORITY CARs CIVIL AVIATION RULES 1994 CVR COCKPIT VOICE RECORDER FDR FLIGHT DATA RECORDER FM FREQUENCY MODULATION CARS COCKPIT AUDIO RECORDING SYSTEM PTA PAKISTAN TELECOMMUNICATION AUTHORITY

E2. RECORDS: Nil E3. REFERENCES

Nil


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INDEX

Sr. No. Contents Page No.

1 Authority 01 2 Purpose 01 3 Scope 01 4 Description 01 5 Definition 01 6 Applicability 01

7 International Commercial Air Transport – Aeroplanes FDR (Flight Data Recorder). 04

8 CVRS (Cockpit Voice Recorders) CARS (Cockpit Audio Recording System) 06

9 International flight data recorder commercial operations – helicopters 10

10 Document for flight. 24

11 Amendments and modifications: 25

12 Evidences (Acronyms / Records / References) 25

13 Implementation 25

Documents

AIR NAVIGATION ORDER … · D2.5.2 A seat belt for each seat, ... The color of the markings shall be red or yellow, and if necessary they shall be out-lined in white to contrast with