CIVIL AVIATION REQUIREMENT
SECTION 3 AIR TRANSPORT
SERIES ‘C’ PART VI
17th MAY, 2000 EFFECTIVE : FORTHWITH
Subject: Airworthiness and operational requirements for Charter operations using single-engined aeroplane.
1. INTRODUCTION
ICAO Annex 6, Part-I stipulates that single-engined aeroplanes shall only be operated in conditions of weather and light, and over such areas and diversions therefrom, that permit a safe forced landing to be executed in the event of engine failure. CAR Section 2, Series ‘O’, Part-II and CAR Section 3, Series ‘C’, Part-III, however, lay down that only twin-engined aeroplanes shall be used for non-scheduled air transport operations. Considering the improvements in engine reliability and increasing use of single-engined aeroplanes in the world for air transportation, Government has decided to permit the use of single-engined aeroplanes for charter operations in accordance with the requirements and guidelines stipulated by DGCA. Detailed requirements for grant of Non-Scheduled Operators Permit to undertake charter operations are contained in CAR Section-3, Series ‘C’, Part-V. This CAR lays down the guidelines and requirements for charter operations with single-engined aeroplanes. This CAR is issued under the provisions of Rule 133A of the Aircraft Rules,1937.
2. GENERAL REQUIREMENTS
2.1 The maximum certified passenger seating capacity excluding pilot seats shall not be more than nine in case of turbine engine aeroplane and four in case of piston engine aeroplane.
2.2 The piston engine aeroplanes shall be operated for charter operations during day-time and VFR weather conditions. The turbine engine aeroplanes may be operated during day/night and VFR/IFR weather conditions as specifically approved.
2.3 The operator shall lay down their own requirements, which shall not be lower than the requirements contained in this CAR, keeping in view the nature and area of their operations. The company requirements for such operations shall be specified in the company Operations Manual.
2.4 Deactivation of duplicate control shall be ensured if the Co-Pilot seat is occupied by passengers.
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CIVIL AVIATION REQUIREMENTS SECTION 3 - AIR TRANSPORT
SERIES ‘C’ PART V 17TH MAY, 2000
2.5 The operator shall comply with all the security requirements laid down by Bureau of Civil Aviation Security.
2.6 The operator shall not sell tickets for individual seats like an airline operator, only the entire aeroplane can be charted.
2.7 The operator shall be responsible for paying all taxes and charges including PSF, IATT, FTT as applicable to the concerned authorities.
3. PILOT QUALIFICATION & EXPERIENCE REQUIREMENTS
3.1 The pilot operating single-engined aeroplane under the provisions of this CAR shall meet the following minimum requirements:
3.1.1 For Piston Engine Aeroplanes
The pilot shall have a minimum of :
a) Total flying experience - 500 hours
b) Total PIC flying experience - 200 hours
c) Total flying experience on type - 50 hours.
d) Total PIC flying experience on type - 25 hours
e) PIC flying experience in the
last six months on type - 10 hours.
3.1.2 For Turbine Engined Aeroplane
The pilot shall have current instrument rating and a minimum of :
a) Total flying experience - 700 hours
b) Total PIC flying experience - 300 hours
c) Total instrument flying
experience as PIC - 100 hours
d) Total PIC flying experience on type - 50 hours
e) PIC flying experience in the
Last six months on type - 10 hours
f) Total flying experience in
night operations * - 10 hours
*For night operations only.
3.2 The pilot shall have valid endorsement on his/her licence of the type of aeroplane to be flown.
3.3 Initial and Recurrent Pilot Training
Details of checks and training requirements for such operations about pilot competency, specifically in respect of, "engine inoperative or malfunctioning" during take-off, climb, cruise, descent, approach, landing and significant mal-functioning of other system, shall be specified in the company Operations Manual. An appropriate entry in the pilot logbook shall be made to confirm the compliance of this requirement.
4. OPERATIONAL REQUIREMENTS
4.1 The operator shall strictly adhere to FDTL specified by the DGCA.
4.2 The aeroplane shall be flown over hilly terrain, sea and thick forest provided safe forced landing can be executed in the event of engine failure. The operator shall identify suitable sites for forced landings for each route to cater for any possibility of engine failure during flight.
4.3 All flights shall be operated in accordance with the company Operations Manual.
4.4 The operations shall be to/from airports having air traffic control services and during the watch hours. The operators should adhere strictly to the approved flight plan. Any deviation there from shall be with the prior approval of the concerned ATC unit.
4.5 The minimum operating altitude shall not be less than 1000 feet above the highest obstacle located within a horizontal distance of 2000 feet from a point vertically below the aeroplane.
4.6 The operator shall ensure that minimum fuel carried on board the aeroplane shall be in accordance with the requirements specified in CAR Section 2, Series ‘O’, Part II.
4.7 Take-off Limitations
The company Operations Manual must specify procedures to cater for departure emergencies for each runway to be used in these operations.
4.8 Route Limitations
The routes must be such that the aeroplane remains within a distance equivalent to 15 minutes of cruise flight plus the gliding distance from cruise altitude, both in still air, of a suitable landing area.
5. AIRWORTHINESS AND MAINTENANCE REQUIREMENTS
The requirements given hereunder in respect of instruments and equipment are in addition to those given in various Civil Aviation Requirements of Section 2 ( Airworthiness).
5.1 The aeroplane should have been type certified to meet the design requirements of FAR 23 or JAR 23 or any other equivalent requirements acceptable to DGCA.
5.2 The aeroplane should be fitted with all instruments and equipment declared mandatory by DGCA as specified in CARs of Section 2 Airworthiness. The aeroplane shall also be equipped with suitable anti-icing or de-icing devices when operated in circumstances in which icing conditions are reported to exist or expected to be encountered.
5.3 For all operations in the event of engine failure, the aircraft shall have sufficient battery capacity to maintain the operation of all essential flight instruments and navigation systems during a descent from cruising altitude whilst maintaining a glide range configuration capable of meeting suitable landing area route limitations.
5.4 Maintenance of airplane and the engine shall be carried out by DGCA approved organisation(s). The maintenance programme shall be strictly in accordance with that given by the manufacturer and approved by the DGCA. The approved
organisation carrying out the maintenance of the aeroplane shall reflect the maintenance program in the Quality Control manual .
5.5 Additional Requirements for Turbine Engined Aeroplane :
5.5.1 The aeroplane shall be maintained in accordance with an approved system of maintenance by an approved organisation. Each operator shall have a program to continually monitor and analyse the airframe system and engine reliability. The engine reliability program shall incorporate a reporting procedure to the DGCA and manufacturer for significant events detrimental to the operations, such as an engine over-temperature, in addition to any other major defect.
5.5.2 Engine Monitoring
For monitoring the health of the engine, critical parameters of engine shall be electronically recorded by means of an onboard automatic data recording system. This requires an automatic activated, electronic engine trend monitoring recording system to be installed for these operations. Operations with the Engine Trend Monitoring (ETM) equipment unserviceable shall not exceed 2 consecutive days.
5.5.3 Monitoring Based Preventive Maintenance
Engine trend monitoring data is to be accessed and interpreted in accordance with the engine manufacturer's published data at intervals not to exceed 4 days.
5.5.4 Redundant Engine Control
A manual throttle, which bypasses the governing section of the engine fuel control unit (FCU), shall be available to the pilot for these operations. Reference to the appropriate section of the flight manual or pilot operating notes will suffice.
5.5.5 Ignition system
For these operations, the engine must be fitted with either :
a) An automatic ignition system which activates in the event of a loss of engine RPM and/or torque, or
b) An ignition system, which can be selected "ON" for take-off, landing or operations where visible moisture is present.
If an auto ignition system is not fitted, the company Operations Manual shall provide procedures specifying the use of ignition and the ignition system shall have a duty cycle greater than one hour.
5.5.6 Chip Detector
An electronic magnetic particle detection system which provides the pilot with an in-flight, visual, caution/warning indication of a possible contamination of the engine and/or gear box oil system shall be fitted and serviceable for all these operations. The company Operations Manual must specify procedures to be followed by a pilot in the event of chip detector warnings and rectification and recording procedures for all chip detector warnings.
5.5.7 Engine Fire Warning System
An approved fire detection and warning system shall be fitted and serviceable for all operations. The company Operations Manual shall amplify the Aeroplane Flight Manual requirements for actions in the event of fire warnings.
5.5.8 Duplicate Electrical Power Generating System
A second source of electrical power shall be available to the pilot for these operations. The second source may be a secondary battery or a generator, which may be engine or non-engine driven. The secondary electrical power source shall be capable of supplying power to all essential flight instruments, navigation systems and aeroplane systems required for flight under the IFR or at night for at least one hour.
5.5.9 Battery Storage Capacity
In addition to requirements as specified in para 5.3, the battery(s) shall have sufficient capacity to conduct two engine start attempts and to lower the flaps and undercarriage as required. The requirements for two engine starts may be reduced to one engine start provided :
a) The aircraft fuel distribution system is automatic, and
b) The engine compressor air intake incorporates continuous anti-icing, and
c) The aircraft system of maintenance includes a requirement to service the aircraft battery(s), including capacity testing, at intervals not to exceed 110 hours time in service or as per manufacturers requirement, whichever is lower.
5.5.10 Flight Instruments and Power Supply
For all operations, the aircraft shall be equipped with duplicate flight and navigation instruments both of which are to be visible to Pilot-in-Command.
5.5.11 Autopilot
An approved autopilot shall be fitted and serviceable for all operations, or the aircraft shall be operated with two pilots.
5.5.12 Supplementary Oxygen Requirements for Pressurised Aeroplanes
For pressurised aeroplane, sufficient supplemental oxygen shall be carried on all flights to permit, following engine failure, a descent from cruise altitude to 10,000 feet AMSL whilst maintaining an approved descent configuration capable of meeting route operating limitations.
5.5.13 Weather Radar
An approved weather radar system shall be fitted and serviceable.
5.5.14 Radio Altimeter
An approved radio altimeter shall be fitted and serviceable.
5.5.15 Passenger Shoulder Harness
Approved shoulder harnesses shall be fitted to all passenger seats.
5.5.16 Passenger Seats and Mountings
Passenger seats, identified by part number and/or model number, meeting the requirements of amendment 36 of FAR 23, parts 23.562 and 23.785 of USA shall be fitted.
6. PERMIT FOR CHARTER OPERATIONS
The DGCA, on satisfactory compliance by the operator with these requirements, will grant specific operation permission to the operator for carrying out passenger charter operations with specific airplanes. If at any time during the approval of such operations it comes to the notice of the DGCA that there exist unsafe conditions or these operations are carried out jeopardizing the safety, the DGCA may alter, suspend, revoke or cancel the permission for specific operation.
( SATENDRA SINGH )
Joint Director General of Civil Aviation
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