text: Aircraft identification

text: Registration(s): Type: Serial No (s):

text: Basis for the Maintenance Programme

text: This Aircraft Maintenance Programme complies with (tick one option): M.A.302(b), (c), (d), (e) and (g) (Complete section 3 below), or M.A.302(h) (Only possible for ELA1 aircraft not used in commercial operations)

text: For Aircraft Maintenance Programmes complying with M.A.302(h) (see above) the following data is used (tick one option):

text: Design Approval Holder Maintenance Data (Complete section 3 below), or Minimum Inspection Programme as detailed in the latest revision of AMC M.A.302(i) , or Other Minimum Inspection Programme complying with M.A.302(i) (List the tasks in Appendix A to

text: this Aircraft Maintenance Programme)

text: Design Approval Holder Maintenance Data (not applicable if using Minimum Inspection Programmes)

text: Equipment manufacturer and type Applicable maintenance data reference (at latest

text: For aircraft other than balloons

text: 3a Aircraft

text: (other than balloons)

text: 3b Engine (if applicable) 3c Propeller (if applicable)

text: For balloons

text: 3d Envelope

text: (only for balloons)

text: 3e Basket(s)

text: (only for balloons)

text: 3f Burner(s)

text: (only for balloons)

text: 3g Fuel cylinders

text: (only for balloons)

text: Additional maintenance requirements not covered above (applicable to all Aircraft Maintenance Programmes,

text: regardless of whether they are based on Design Approval Holder Data or Minimum Inspection Programmes)

text: Indicate if any of the following additional maintenance requirements are applicable (when Yes No

text: replying ‘YES’, list the specific requirements in Appendix B to this Aircraft Maintenance Programme)

text: Maintenance related to specific equipment and modifications

text: Maintenance related to repairs implemented in the aircraft

text: Maintenance related to life-limited components

text: Maintenance related to Mandatory Continuing Airworthiness Information (ALIs, CMRs, specific requirements in the Type Certificate Data Sheet (TCDS), etc.)

text: Maintenance related to repetitive Airworthiness Directives

text: Maintenance related to specific operational/airspace directives/requirements (altimeter, compass, transponder, etc.)

text: Maintenance related to the type of operation or to operational approvals such as Reduced Vertical Separation Minima (RVSM), Minimum Navigation Performance Specification (MNPS), Basic Area Navigation (B-NAV).

text: Indicate if there are any specific maintenance recommendations made in Service Bulletins, Yes No

text: Service Letters, etc, that are applicable (when replying ‘YES’, list all the specific recommendations and any deviations in Appendix B to this Aircraft Maintenance Programme)

text: Pilot-owner maintenance (only for privately operated non-complex motor-powered aircraft of 2 730 kg MTOM and below, sailplanes, powered-sailplanes and balloons)

text: Does the Pilot-owner perform Pilot-owner maintenance (ref. Part-M, M.A.803)? Yes No 6 If yes, enter the name of the pilot-owner(s) or the alternative procedure described in AMC M.A.803 point 3: Pilot-owner name:_____________________ Licence Number:_________________ Signature: _______________________________________________ Date: ______________

text: If yes, list in Appendix B to this Aircraft Maintenance Programme the deviations to the list of Pilot-owner maintenance tasks contained in the AMC to Appendix VIII to Part-M (tasks which are not performed by the Pilot-owner and additional tasks performed)

text: Record of periodic reviews of the Aircraft Maintenance Programme (in accordance with M.A.302(g) or

text: M.A.302(h)5, as applicable)

text: Describe whether the review has resulted or not in changes to the Date and signature Aircraft Maintenance Programme (any changes introduced will be

text: described in field 8 below)

text: Revision control of the Aircraft Maintenance Programme

text: Rev. No Content of revision Date and signature

text: Approval/Declaration of the Maintenance Programme (select the appropriate option)

text: Declaration by owner: Approval by contracted CAMO (only Approval by Competent Authority: under ‘indirect approval procedure’ approved by the competent authority responsible for the Aircraft Maintenance Programme):

text: ‘I hereby declare that this is the Approval Reference No of the Competent Authority: maintenance programme CAMO:

text: applicable to the aircraft

text: referred to in field 1 and I am Signature/Name/Date: fully responsible for its content Signature/Name/Date:

text: and, in particular, for any deviations from the Design Approval Holder’s recommendations’

text: Certification statement

text: ‘I will ensure that the aircraft is maintained in accordance with this maintenance programme and that the

text: maintenance programme will be reviewed and updated as required’

text: Signed by the person/organisation responsible for the continuing airworthiness of the aircraft according to M.A.201: Owner - Lessee - CAMO

text: Name of owner/lessee or CAMO approval number: Address: Telephone/fax: E-mail:

text: Signature/Date: 11 Appendices attached: — Appendix A YES NO — Appendix B YES NO

text: Appendix A ‘Minimum Inspection Programme’ (only applicable if a Minimum Inspection Programme different from the one described in AMC M.A.302(i) is used) (see Section 2 above)

text: Detail the tasks and inspections contained in the Minimum Inspection Programme being used.

text: Appendix B ‘Additional Maintenance Requirements’ and ‘Pilot-owner maintenance’ (include only if applicable) (see Sections 4, 5 and 6 above)

text: Task Description References Interval

text: Maintenance related to Mandatory Continuing Airworthiness Instructions (ALIs, CMRs, specific requirements in the TCDS, etc.)

text: Maintenance related to the type of operation or operational approvals

text: Task Description Recommended Indicate: Alternative inspection/task (if Amended interval adopted with deviations) interval (if ‘Adopted’, or adopted with ‘Not adopted’, or deviations) ‘Adopted with deviations’

text: Maintenance recommendations contained in Service Bulletins, Service Letters, etc.

text: NOTE : List all the applicable maintenance recommendations, even those for which it has been decided not to accomplish the task or to accomplish it with deviations.

text: Task Description (Pilot-owner maintenance)

text: Pilot-owner maintenance tasks contained in AMC to Appendix VIII to Part-M which are not performed by the Pilotowner

text: Pilot-owner maintenance tasks performed by the Pilot-owner additional to those contained in AMC to Appendix VIII to Part-M

text: ELA1 aeroplanes not involved in commercial operations

text: System/component/area Task & Inspection detail

text: General Remove or open all necessary inspection plates, access doors, fairings, and cowlings. Clean the aircraft and aircraft engine as required.

text: Lubrication/servicing Lubricate and replenish fluids in accordance with the manufacturer’s requirements. Markings Check that side and under-wing registration markings are correct. If applicable, check that an exemption for alternate display is approved. Identification plate for National Aviation Authority registered aircraft is present. Other identification markings on fuselage are in accordance with local (national) rules.

text: Review weighing record to establish accuracy against installed equipment. Weighing Weigh the aircraft as required by the Part-NCO rules.

text: Fabric and skin Inspect for deterioration, distortion, other evidence of failure, and defective or insecure attachment of fittings. NOTE: When checking composite structures, check for signs of impact or pressure damage that may indicate underlying damage.

text: Fuselage structure Check frames, formers, tubular structure, braces, and attachments. Inspect for signs of corrosion. Systems and components Inspect for improper installation, apparent defects, and unsatisfactory operation. Pitot/static system Inspect for security, damage, cleanliness, and condition. Drain any water from condensation drains. General Inspect for lack of cleanliness and loose equipment that might foul the controls. Tow hooks Inspect for condition of moving parts and wear. Check service life. Carry out operational test.

text: CABIN AND COCKPIT

text: Seats, safety belts and Inspect for poor condition and apparent defects. harnesses Check for service life. Windows, canopies and Inspect for deterioration and damage, and for function of emergency jettison. windshields Instrument panel Inspect for poor condition, mounting, marking, and (where practicable) improper assemblies operation. Check markings of instruments in accordance with the Flight Manual. Flight and engine controls Inspect for improper installation and improper operation. Speed/weight/manoeuvre Check that the placard is correct and legible and accurately reflects the status of the placard aircraft. All systems Inspect for improper installation, poor general condition, apparent and obvious defects, and insecurity of attachment.

text: LANDING GEAR

text: Shock-absorbing devices Inspect for improper fluid level. Inspect for wear and deformation of rubber pads, bungees, and springs. All units Inspect for poor condition and insecurity of attachment.

text: Retracting and locking Inspect for improper operation. mechanism Linkages, trusses and Inspect for undue or excessive wear fatigue and distortion. members Hydraulic lines Inspect for leakage. Check service life. Electrical system Inspect for chafing and improper operation of switches. Wheels Inspect for cracks, defects, and condition of bearings. Tyres Inspect for wear and cuts. Brakes Inspect for improper adjustment and wear. Carry out operational test. Floats and skis Inspect for insecure attachment and apparent defects.

text: WING AND CENTRE SECTION

text: All components Inspect all components of the wing and centre section assembly for poor general condition, fabric or skin deterioration, distortion, evidence of failure, insecurity of attachment. Connections Inspect main connections (e.g. between wings, fuselage, wing tips) for proper fit, play within tolerances, wear or corrosion on bolts and bushings.

text: FLIGHT CONTROLS

text: Control circuit/stops Inspect control rods and cables. Check that the control stops are secure and make contact. Control surfaces Inspect aileron, flap, elevator, air brake and rudder assemblies, hinges, control connections, springs/bungees, tapes and seals. Check and record range of movement and cable tensions, if specified, and check free play. Trim systems Inspect trim surfaces, controls, and connections. Check full range of motion.

text: All components and Inspect all components and systems that make up the complete empennage systems assembly for poor general condition, fabric or skin deterioration, distortion, evidence of failure, insecure attachment, improper component installation, and improper component operation.

text: AVIONICS AND ELECTRICS

text: Batteries Inspect for improper installation, improper charge and spillage and corrosion. Radio and electronic Inspect for improper installation and insecure mounting. equipment Carry out ground function test. Wiring and conduits Inspect for improper routing, insecure mounting, and obvious defects. Bonding and shielding Inspect for improper installation, poor condition, and chafing and wear of insulation. Antennas Inspect for poor condition, insecure mounting, and improper operation.

text: Engine section Inspect for visual evidence of excessive oil, fuel or hydraulic leaks and sources of such leaks. Studs and nuts Inspect for looseness, signs of rotation and obvious defects. Internal engine Inspect for cylinder compression (record measures for each cylinder) and for metal particles or foreign matter in oil filter, screens and sump drain plugs. If there is weak cylinder compression, inspect for improper internal condition and improper internal tolerances. Engine mounts Inspect for cracks, looseness of mounting, and looseness of the engine to mount attachment. Flexible vibration Inspect for poor condition and deterioration. dampeners Engine controls Inspect for defects, improper travel, and improper safe tying. Lines, hoses and clamps Inspect for leaks, improper condition, and looseness.

text: Exhaust stacks Inspect for cracks, defects, and improper attachment. Turbocharger and Inspect for leaks, improper condition, and looseness of connections and fittings. intercooler Liquid cooling systems Inspect for leaks and proper fluid level. Electronic engine control Inspect for signs of chafing and proper electronics and sensor installation. Accessories Inspect for apparent defects in security of mounting. All systems Inspect for improper installation, poor general condition, defects and insecure attachment. Cowling Inspect for cracks and defects. Check cowling flaps. Cooling baffles and seals Inspect for defects, improper attachment, and wear. Fuel tanks Inspect for improper installation and connection.

text: CLUTCHES AND GEARBOXES

text: Filters, screens, and chip Inspect for metal particles and foreign matter. detectors Exterior Inspect for oil leaks. Output shaft Inspect for excessive bearing play and condition.

text: Propeller assembly Inspect for cracks, nicks, binds, and oil leakage. Propeller bolts Inspect for proper installation, looseness, signs of rotation, and lack of safe tying. Propeller control Inspect for improper operation, insecure mounting, and restricted travel. mechanism Anti-icing devices Inspect for improper operation and obvious defects.

text: Ballistic rescue system Inspect for proper installation, unbroken activation mechanism, proper securing while on ground, validity of inspection periods of pyrotechnic devices, and parachute packing intervals. Other miscellaneous items Inspect installed miscellaneous items that are not otherwise covered by this listing for improper installation and improper operation.

text: OPERATIONAL CHECKS

text: Power and revolutions per Check that power output, static and idle rpm are within published limits. minute (rpm) Magnetos Check for normal function. Fuel and oil pressure Check they are within normal values. Engine temperatures Check they are within normal values. Engine For engines equipped with automated engine control (e.g. FADEC), perform the published run-up procedure and check for discrepancies. Engine For dry-sump engines and engines with turbochargers and for liquid cooled engines, check for signs of disturbed fluid circulation. Pitot-static system Perform operational check. Transponder Perform operational check.

text: ELA1 sailplanes and ELA1 powered sailplanes not involved in commercial operations

text: General — all tasks The aircraft must be clean prior to inspection. Inspect for security, damage, wear, integrity, drain/vent holes clear, signs of overheating, leaks, chafing, cleanliness and condition as appropriate to the particular task. Whilst checking composite structures, check for signs of impact or pressure damage that may indicate underlying damage. Lubrication/servicing Lubricate and replenish fluids in accordance with the manufacturer’s requirements. Markings Check that side and under-wing registration markings are correct. If applicable, check that an exemption for alternate display is approved. Identification plate for National Aviation Authority registered aircraft is present. Other identification markings on fuselage in accordance with local (national) rules. Weighing: Review weighing record to establish accuracy against installed equipment. Weigh the aircraft as required by the Part-NCO rules.

text: Fuselage paint/gel coat, Inspect external surface and fairings, gel coat, fabric covering or metal skin, and including registration paintwork. Check that registration marks are correctly applied. markings Fuselage structure Check frames, formers, tubular structure, skin, and attachments. Inspect for signs of corrosion on tubular framework. Nose fairing Inspect for evidence of impact with ground or objects. Release hook(s) Inspect nose and Centre of Gravity (C of G) release hooks and controls. Check operational life. Carry out operational test. If more than one release hook or control is fitted, check operation of all release hooks from all positions. Pot pitot/ventilator Check alignment of probe, check operation of ventilator.

text: Pitot/static system Inspect pitot probes, static ports and all accessible tubing for security, damage, cleanliness, and condition. Drain any water from condensation drains.

text: Bonding/vents drains Check all bonding leads and straps. Check that all vents and drains are clear from debris.

text: CABIN AND COCKPIT

text: Cleanliness/loose articles Check under cockpit floor/seat pan and in rear fuselage for debris and foreign items.

text: Canopy, locks and jettison Inspect canopy, canopy frame and transparencies for cracks, unacceptable distortion, and discolouration. Check operation of all locks and catches. Carry out an operational test of the canopy jettison system from all positions.

text: Seat/cockpit floor Inspect seat(s). Check that all loose cushions are correctly installed and, as appropriate, energy absorbing foam cushions are fitted correctly. Ensure that all seat adjusters fit and lock correctly.

text: Harness(es) Inspect all harnesses for condition and wear of all fastenings, webbing, and fittings. Check operation of release and adjustments.

text: Rudder pedal assemblies Inspect rudder pedal assemblies and adjusters.

text: Flight control Inspect flight controls rods/cables. Check that control stops are secure and make circuits/stops contact. Pay particular attention to wear and security of liners and cables in ‘S’ tubes.

text: Inspect self-connecting control devices.

text: Instrument panel Inspect instrument panel and all instruments/equipment. Check instrument assemblies readings are consistent with ambient conditions. Check marking of all switches, circuit breakers, and fuses. Check operation of all installed equipment, as possible, in accordance with the manufacturer’s instructions.

text: Check markings of instruments in accordance with the Flight Manual.

text: Oxygen system Inspect oxygen system. Check bottle hydrostatic test date expiry in accordance with the manufacturer’s recommendations. Ensure that the bottle is not completely empty (13,8 bars/200 psi minimum) and refill with aviator’s oxygen only. Clean masks and regulators with suitable cleaning wipes.

text: Ensure that the oxygen installation is recorded on weight and C of G schedule. CAUTION: OBSERVE ALL SAFETY PRECAUTIONS.

text: Colour-coding of controls Ensure that controls are colour-coded and in good condition, as follows: Tow release: yellow Air Brakes: blue Trimmer: green Canopy normal operation: white Canopy jettison: red Other controls: clearly marked but not using any of the above colours. Equipment stowed in Check for security and condition. Check validity of any safety equipment. Check the centre section manufacturer’s and the NAA’s (if required) data plates. Speed/weight/ manoeuvre Check that the placard is correct and legible and accurately reflects the status of the placard aircraft.

text: LANDING GEAR

text: Front skid/nose wheel and Inspect for evidence of hard/heavy landings. Check skid wear. Inspect wheel, tyre, mounts and wheel box. Check tyre pressure. Main wheel and brake Check for integrity of hydraulic seals and leaks in pipe work. Check life of hydraulic assembly hoses and components if specified by the manufacturer. Remove brake drums, check brake lining wear. Check disk/drum wear. Refit drum. Check brake adjustment. CAUTION: BRAKE DUST MAY CONTAIN ASBESTOS. Check operation of brake. Check level of brake fluid and replenish if necessary. Check tyre pressure. CAUTION: CHECK TYPE OF BRAKE FLUID USED AND OBSERVE SAFETY PRECAUTIONS. Undercarriage suspension Check springs, bungees, shock absorbers, and attachments. Check for signs of damage. Service strut if applicable. Undercarriage retract Check retraction mechanism and controls, warning system if fitted, gas struts, doors system and doors and linkages/springs, over-centre/locking device. Perform retraction test. Tail skid/wheel Inspect for evidence of hard/heavy landings. Check skid wear. Inspect wheel, tyre, and wheel box. Check bond of bonded skids. Check tyre pressure. Wheel brake control Inspect wheel brake control rods/cables. If combined with air brake, ensure correct circuit rigging relationship. Check parking brake operation if fitted.

text: WING AND CENTRE SECTION

text: Centre section fairing Inspect for security, damage, and condition. Wing attachments Inspect the wing structural attachments. Check for damage, wear, and security. Check for rigging damage. Check condition of wing attachment pins. Aileron control Inspect aileron control rods/cables. Check that control stops are secure and make circuit/stops contact. Inspect self-connecting control devices. Air brake control circuit Inspect air brake control rods/cables. Check friction/locking device (if fitted). Inspect self-connecting control devices. Wing struts/wires Inspect wing struts for damage and internal corrosion. Re-inhibit wing struts internally every three years or in accordance with the manufacturer’s instructions. Wings including underside Check mainplane structure externally and internally as far as possible. Check gel registration markings coat, fabric covering, or metal skin. Check that registration marks are correctly applied. Ailerons and controls Inspect aileron and flaperon assemblies, hinges, control connections, springs/bungees, tapes, and seals. Ensure that seals do not impair full range of movement. Air brakes/spoilers Inspect air brake/spoiler panel(s) operating rods, closure springs, and friction devices as fitted. Flaps Check flap system and control. Inspect self-connecting control devices. Control deflections and Check and record range of movements and cable tensions, if specified, and check free play, and record on free play. worksheets

text: Tailplane and elevator With tailplane de-rigged, check tailplane and attachments, self-connecting and manual control connections. Check gel coat, fabric covering, or metal skin. Rudder Check rudder assembly, hinges, attachments, balance weights. Rudder control circuit/ Inspect rudder control rods/cables. Check that control stops are secure and make stops contact. Pay particular attention to wear and security of liners and cables in ‘S’ tubes.

text: Elevator control Inspect elevator control rods/cables. Check that control stops are secure and make circuit/stops contact. Inspect self-connecting control devices. Trimmer control circuit Inspect trimmer control rods/cables. Check friction/locking device. Control deflections and Check and record range of movements and cable tensions, if specified, and check free play, and record on free play. worksheets

text: AVIONICS AND ELECTRICS

text: Electrical installation/fuses Check all electrical wiring for condition. Check for signs of overheating and poor connections. Check fuses/trips for condition and correct rating. Battery security and Check battery mounting for security and operation of clamp. Check for evidence of corrosion electrolyte spillage and corrosion. Check that the battery has correct the main fuse fitted. It is recommended to carry out battery capacity test on gliders equipped with radio, used for cross-country, controlled airspace, or competition flying. Radio installations and Check radio installation, microphones, speakers and intercom, if fitted. Check that placards the call sign placard is installed. Carry out ground function test. Record radio type fitted. Altimeter datum Check barometric sub-scale. Maximum error 2 Mb. Pitot-static system Perform operational check. Transponder Perform operational check.

text: Removable ballast Check removable ballast mountings and securing devices (including fin ballast if applicable) for condition. Check that ballast weights are painted with conspicuous colour. Check that provision is made for the ballast on the loading placard. Drag chute and controls Inspect chute, packing and release mechanism. Check packing intervals. Water ballast system Check water ballast system, wing and tail tanks as fitted. Check filling points, level indicators, vents, dump and frost drains for operation and leakage. If loose bladders are used, check for leakage and expiry date as applicable.

text: POWERPLANT (when applicable)

text: Engine pylons and Inspect engine and pylon installation. Check engine compartment and fire sealing. mountings Gas strut Check gas strut. Pylon/engine stops Check limit stops on retractable pylons. Check restraint cables. Electric actuator Inspect electric actuator, motor, spindle drive, and mountings. Electrical wiring Inspect all electrical wiring. Pay special attention to wiring that is subject to bending during extension and retraction of engine/pylon. Limit switches Check operation of all limit switches and strike plates. Make sure that they are not damaged by impact. Fuel tank(s) Check fuel tank mountings and tank integrity. Check fuel quantity indication system if fitted. Fuel pipes and vents Check all fuel pipes especially those subject to bending during extension and retraction of engine/pylon. Check that vents are clear. Make sure that overboard drains do not drain into engine compartment. Check self-sealing. Fuel cock or shut off valve Check operation of fuel cock or shut-off valve and indications. Fuel pumps and filters Clean or replace filters as recommended by the manufacturer. Check operation of fuel pumps for engine supply or tank replenishment. Check fuel pump controls and indications. Decompression valve Inspect decompression valve and operating control. Spark plugs Carry out spark plug service. It is recommended to replace spark plugs at annual intervals. Harnesses and Magneto Inspect low-tension and high-tension wiring, connectors, spark plug caps. Check magneto to engine timing. Check impulse coupling operation. Propeller bolts, assembly, Inspect propeller, hub, folding mechanism, brake, pitch change mechanism, stow mounting, torquing & sensors. drive belt Doors Check engine compartment doors, operating cables, rods, and cams. Safety springs Check all safety and counterbalance springs.

text: Extension and retraction Check that extension and retraction operation times are within limits specified by manufacturer. Check light indications and interlocks for correct operation. Exhaust Inspect exhaust system, silencer, shock mounts, and links. Engine installation Inspect engine and all accessories. Carry out compression test and record results. Compression test results: No1 (left/front): No2 (right/rear): Lubrication Change engine oil and filter. Replenish oil and additive tanks. Engine instruments Inspect all engine instruments and controls. Check control unit, mounts, bonding and connections. Carry out internal self-test if fitted. Flexible vibration dampers Check for poor condition and deterioration. Engine battery If separate from airframe battery, inspect battery and mountings. If the main fuse is fitted, check rating and condition. Perform a functional test. Placards Check that all placards are in accordance with flight manual and legible. Oil and fuel leaks With the engine fully serviced, check the fuel and oil system for leaks.

text: Identification (type/serial Check for presence and verify type/serial number installed. number/registration plate) Crown ring and line In place; not corroded; crown line undamaged and has appropriate length. Vertical/horizontal load Check joints with the crown ring, top of the envelope and wires. All load tapes tapes undamaged along their entire length. Inspect base horizontal tape and edge of the envelope top. Inspect joint between base horizontal load tape and vertical load tapes. Envelope fabric Inspect the envelope fabric panels (including parachute and rotation vents if fitted) for damage, porosity overheating or weakness. Unrepaired damage is within tolerance given by the manufacturer. If substantial fabric porosity is suspected, then a flight test should be performed, but only after a grab test has demonstrated that the balloon is safe to fly. Perform grab test in accordance with the manufacturer’s instructions. Flying cables Inspect for damage (particularly heat damage). Kevlar cable — yellow core is not visible Karabiners Inspect for damage. Karabiner lock is working properly. Melting link and Check maximum temperature indication (flag/‘tell-tale’). Tempilabel Control system lines Inspect for damage wear, security of knots. Check proper length. Check lines attachments for damage, wear, security. Control lines and their Inspect for damage, wear, security of knots. Check proper length of the lines. attachments Envelope pulleys Inspect for damage, wear, free running, contamination, security of attachment.

text: Identification Check for presence and verify type/serial number installed. (type/serial number) Inspect welds for cracking. Inspect tubes for distortion/deformation/cuts/gouges. Burner frame Inspect frame for security of fasteners (heat shields, flexi-corners). Inspect frame lugs for wear, cracking. Inspect general condition (corrosion, heat shields). Gimballing Check stiffness, security of fitting manifolds. Leak check Perform leak check of the burner. Inspect all hoses for wear, damage, leak, and lifetime limitation. Hoses Inspect condition and correct function of the fuel. Pressure gauges Check Pressure gauge reads zero when no pressure applied, lens present. Pilot valves/flame Check Shut off, free movement, correct function, lubricate if necessary. Whisper valves/flame Check Shut off, free movement, correct function, lubricate if necessary. Main valves/flame Check Shut off, free movement, correct function, lubricate if necessary. Check for damage, distortion, security of fasteners. Inspect welds for cracking. Coils Check security of jets, tighten or replace as necessary. Fuel Check correct type, check dates (if applicable).

text: Identification Check for presence and verify type/serial number installed. (type/serial number) Basket body Check the general condition of the basket body. Inspect weave for damage, cracks/holes. No sharp objects inside the basket. Basket wires Inspect for damage, check eye rings. Karabiners Inspect for damage. Karabiner lock is working properly. Basket floor Inspect for damage and cracks. Runners Inspect for damage. Rawhide Inspect for damage, wear and attachments to the floor. Rope handles Inspect for damage, security of attachment. Cylinder straps Inspect for damage, deterioration. Padded basket edge trim Inspect for damage and wear. Burner rods Inspect for damage, wear and cracking. Padded burner rod Inspect for damage and wear. covers Basket equipment Check presence and functionality. pilot restraint Inspect for security and condition. Fire extinguisher Check expiration date and protection cover. First-aid kit Check for completeness and expiration date.

text: Identification (type/serial Check for presence. number) Check periodic inspections for each cylinder is valid (date) (e.g. 10 years’ Cylinder inspection). Cylinder body Inspect for damage, corrosion. Inspect for damage, corrosion, correct operation. Liquid valve Inspect 0-ring seals, lubricate/replace as required. Fixed liquid Inspect for damage, corrosion, correct operation. Level gauge Contents Gauge Inspect for damage, corrosion, freedom of movement. Inspect for damage, corrosion, correct operation (including regulator). Vapour valve Inspect Quick Release Coupling for correct operation, sealing. Padded cover Inspect for damage. Pressure relief valve Does not indicate over pressuring Inspect, leak-test all pressure holding joints using leak detector. Assembly Functional test

text: Instruments Functional check

text: Quick release Functional check and inspect the condition of the latch, bridle and ropes for wear and deterioration. Check that the karabiners are undamaged and operate correctly.

text: Communication/navigation Perform operational check. equipment (radio)

text: Transponder Perform operational check.

identifier: AMC to Part M — Amendment 13

beslut: ED Decision 2015/024/R

title: AMC to Part M — Amendment 13

text: Annex I to ED Decision 2015/024/R

text: Annex I (Acceptable Means of Compliance to Part-M), to Decision 2003/19/RM is amended as follows: The text of the amendment is arranged to show deleted text, new or amended text as shown below: (a) deleted text is marked with strikethrough; (b) new or amended text is highlighted in grey; (c) an ellipsis (…) indicates that the remaining text is unchanged in front of or following the reflected amendment.

text: AMC M.A.201(e) is amended as follows:

text: AMC M.A.201(e) Responsibilities

text: The limited contract for the development and, when applicable, processing of the approval of the aircraft maintenance programme should cover the responsibilities related to M.A.302(d), M.A.302(e) and M.A.302(g). This contract may also entitle the M.A. Subpart G organisation to use the indirect approval procedure described in M.A.302(c). In the case of ELA1 aircraft not involved in commercial operations, the limited contract between the owner and the CAMO/maintenance organisation should cover the following aspects: — Whether the maintenance programme will be based on the ‘Minimum Inspection Programme’ described in M.A.302(i); — The obligation for the CAMO/maintenance organisation to develop and propose to the owner a maintenance programme which:  identifies the owner and the specific aircraft, engine, and propeller (as applicable);  includes all mandatory maintenance information and any additional tasks derived from the evaluation of the recommendations issued by the Design Approval Holder;  does not go below the requirements of the Minimum Inspection Programme; and  is customised to the particular aircraft type, configuration and operation, in accordance with M.A.302(h)3. — Whether the maintenance programme is going to be approved by the competent authority or the owner is going to issue a declaration for the maintenance programme.  In the case of approval by the competent authority, whether indirect approval by the CAMO is permitted or not.  In the case of declaration by the owner, a statement in the contract making clear that the owner assumes full responsibility for any deviations introduced to the maintenance programme proposed by the CAMO/maintenance organisation.

text: AMC M.A.302 is amended as follows:

text: AMC M.A.302 Aircraft maintenance programme

text: NOTE: This AMC is not applicable to those ELA1 aircraft not involved in commercial operations for which the owner has elected to apply the provisions of M.A.302(h). For those cases, refer to AMC M.A.302(h). …

text: AMC M.A.302(d) is amended as follows:

text: AMC M.A.302(d) Aircraft maintenance programme compliance

text: A new AMC M.A.302(e) is introduced as follows:

text: AMC M.A.302(e) Aircraft maintenance programme

text: Except for complex motor-powered aircraft, the aircraft maintenance programme may take the format of the following standard template:

text: Aircraft Maintenance Programme (for aircraft other than ‘complex motor-powered aircraft’)

text: AMC M.A.302(f) is amended as follows:

text: AMC M.A.302(f) Aircraft maintenance programme – reliability programmes

text: A new AMC M.A.302(h) is introduced as follows:

text: AMC M.A.302(h) Aircraft maintenance programme

text: NOTE: This AMC is applicable to those ELA1 aircraft not involved in commercial operations for which the owner has elected to apply the provisions of M.A.302(h).

text: 1. The aircraft should only be maintained according to one maintenance programme at a given point in time. Where an owner wishes to change from one programme to another because of a change in the type of operation, a transfer check or inspection may need to be performed to implement the change.

text: 2. The maintenance programme may take the format of the standard template provided in AMC M.A.302(e).

text: 3. During the annual review of the maintenance programme, the following should be taken into consideration: — The results of the maintenance performed during that year, which may reveal that the current maintenance programme is not adequate. — The results of the airworthiness review performed on the aircraft, which may reveal that the current maintenance programme is not adequate. — Revisions introduced in the documents affecting the programme basis, such as the M.A.302(i) ‘Minimum Inspection Programme’ or the Design Approval Holder data. — Applicable mandatory requirements for compliance with Part-21, such as Airworthiness Directives, Airworthiness Limitations, Certification Maintenance Requirements and specific maintenance requirements contained in the TCDS. For the purpose of reviewing the results of the maintenance performed during that year, the airworthiness review staff should request the owner/CAMO to provide the records of all the maintenance performed during that year, including unscheduled maintenance. When reviewing the results of the maintenance performed during that year and the results of the airworthiness review, attention should be paid as to whether the defects found may have been prevented by introducing in the maintenance programme certain recommendations from the Design Approval Holder which were initially disregarded by the owner.

text: A new AMC M.A.302(i) is introduced as follows:

text: AMC M.A.302(i) Aircraft maintenance programme

text: This AMC contains an acceptable ‘Minimum Inspection Programme’ for the following categories of ELA1 aircraft not involved in commercial operations: — ELA1 aeroplanes; — ELA1 sailplanes and ELA1 powered sailplanes; and — ELA1 hot-air balloons. Although this AMC does not contain an acceptable ‘Minimum Inspection Programme’ for gas balloons, the use of a ‘Minimum Inspection Programme’ is still possible as long as it complies with the requirements established in M.A.302(i). The ‘Minimum Inspection Programmes’ defined in this AMC already comply with the requirements established in M.A.302(i) and may be used in order to define the basic information for the

text: maintenance programme as required by M.A.302(h)2. However, the maintenance programme must be customised as required by M.A.302(h)3, which may be done by using the standard template contained in AMC M.A.302(e).

text: It must be noted that using the ‘1-month’ tolerance permitted by M.A.302(i)1 for the annual inspection may result in an expired ARC.

text: Minimum Inspection Programme for ELA1 aeroplanes not involved in commercial operations

text: To be performed every annual/100 h interval, whichever comes first.

text: A tolerance of one month or 10 h may be applied. However, the next interval shall be calculated from the date/hours originally scheduled (without the tolerance).

text: Note 1: Use the manufacturer’s maintenance manual to accomplish each task/inspection.

text: Note 2: Proper operation of backup or secondary systems and components should be included for every instance where a check is performed for improper installation/operation.

text: Minimum Inspection Programme for ELA1 sailplanes and ELA1 powered sailplanes not involved in commercial operations

text: To be performed:

text: — every annual/100 h interval (for Touring Motor Gliders (TMG)), whichever comes first; or

text: — every annual interval (for other than TMGs).

text: A tolerance of one month or 10 h, as applicable, may be applied. However, the next interval shall be calculated from the date/hours originally scheduled (without the tolerance).

text: Note 2: In the case of TMGs, it is acceptable to control the hours of use of the aircraft, engine and propeller as separate entities. Any maintenance check to be done between two consecutive annual/100 h inspections may be performed separately on the aircraft, engine and propeller depending on when each element reaches the corresponding hours. However, at the time of the annual/100 h inspection, all the elements must be covered.

text: Note 3: Proper operation of backup or secondary systems and components should be included for every instance where a check is performed for improper installation/operation.

text: Minimum Inspection Programme for ELA1 hot-air balloons not involved in commercial operations

text: To be performed every annual interval.

text: A tolerance of one month may be applied. However, the next interval shall be calculated from the date originally scheduled (without the tolerance).

text: 1. Envelope

text: 2. Burner

text: 3. Basket

text: 4. Fuel tanks

text: 5. Additional equipment

text: AMC M.A.605(a) is amended as follows:

text: AMC M.A.605(a) Facilities

text: 1. Where a hangar is not owned by the M.A. Subpart F organisation, it may be necessary to establish proof of tenancy. In addition, sufficiency of hangar space to carry out planned maintenance should be demonstrated by the preparation of a projected aircraft hangar visit plan relative to the aircraft maintenance programme. The aircraft hangar visit plan should be updated on a regular basis. For balloons and airships a hangar may not be required where maintenance of the envelope and bottom end equipment can more appropriately be performed outside, providing all necessary maintenance can be accomplished in accordance with M.A.402. For complex repairs or component maintenance requiring an EASA Form 1, suitable approved workshops should be provided. The facilities and environmental conditions required for inspection and maintenance should be defined in the Maintenance Organisation Manual. Depending on the scope of work of the maintenance organisation, it may not be necessary to have a hangar available. For example, an organisation maintaining ELA2 aircraft (when not performing major repairs) may perform the work in alternative suitable facilities (and possibly at remote locations) as agreed by the competent authority. 2. … 3. ...

text: 4. Special case for ELA2 aircraft

text: For ELA2 aircraft, it is acceptable not to have access to a hangar or dedicated workshops. Depending on the scope of work, other facilities are acceptable as long as protection is ensured from inclement weather and contamination. This may include, for example, working in the field or in non-aviation premises (closed or not).

text: These facilities do not need to be individually approved by the competent authority as long as the maintenance organisation manual describes for each type of facility the scope of work, the tooling and equipment available, and the permitted environmental conditions (weather, contamination). The organisation should include, as part of the periodic internal organisational review, a sampling of the compliance with these conditions during certain maintenance events.

text: AMC M.A.607 is amended as follows:

text: AMC M.A.607 Certifying staff and airworthiness review staff

text: AMC M.A.607(c) is amended as follows:

text: AMC M.A.607(c) Certifying staff and airworthiness review staff

text: 1. … 2. The following minimum information, as applicable, should be kept on record in respect of each airworthiness review person: (a) name; (b) date of birth; (c) certifying staff authorisation; (d) experience as certifying staff on ELA1 aircraft; (e) qualifications relevant to the approval (knowledge of relevant parts of Part-M and knowledge of the relevant airworthiness review procedures); (f) scope of the airworthiness review authorisation and personal authorisation reference; (g) date of the first issue of the airworthiness review authorisation; and (h) if appropriate, expiry date of the airworthiness review authorisation. 2.3. Persons authorised to access the system should be maintained at a minimum to ensure that records cannot be altered in an unauthorised manner or that such confidential records become accessible to unauthorised persons. 3.4. The competent authority should be granted access to the records upon request.

text: AMC M.A.614(a) is amended as follows:

text: AMC M.A.614(a) Maintenance and airworthiness review records

text: AMC M.A.614(c) is amended as follows:

text: AMC M.A.614(c) Maintenance and airworthiness review records

text: AMC M.A.707(b) is amended as follows:

text: AMC M.A.707(b) Airworthiness review staff

text: The formal acceptance by the competent authority of the airworthiness review staff is granted through the corresponding EASA Form 4. An airworthiness review ‘under supervision’ means under the supervision of the competent authority. If the organisation has already properly authorised airworthiness review staff, the competent authority may accept that the supervision be performed by the existing airworthiness review staff in accordance with an approved procedure. In such case,If the airworthiness review is performed under the supervision of existing airworthiness review staff, evidence of the airworthiness review performed under supervision should be provided to the competent authority together with the EASA Form 4. If satisfied, the competent authority will issue the formal acceptance through the EASA Form 4. Once the airworthiness review staff has been accepted by the competent authority, the inclusion of their name in the exposition (refer to M.A.704(a)5) constitutes the formal authorisation by the organisation.

text: A new AMC M.A.710(ga) is introduced as follows:

text: AMC M.A.710(ga) Airworthiness review

text: This review of the maintenance programme is performed by the person who performed the airworthiness review, who could belong to the competent authority, an M.A. Subpart G organisation or a maintenance organisation or could also be independent certifying staff in accordance with M.A.901(g). During the annual review of the maintenance programme, the following should be taken into consideration: — The results of the maintenance performed during that year, which may reveal that the current maintenance programme is not adequate. — The results of the airworthiness review performed on the aircraft, which may reveal that the current maintenance programme is not adequate. — Revisions introduced in the documents affecting the programme basis, such as the M.A.302(i) ‘Minimum Inspection Programme’ or the Design Approval Holder data. — Applicable mandatory requirements for compliance with Part-21, such as Airworthiness Directives, Airworthiness Limitations, Certification Maintenance Requirements and specific maintenance requirements contained in the TCDS. For the purpose of reviewing the results of the maintenance performed during that year, the airworthiness review staff should request the owner/CAMO to provide the records of all the maintenance performed during that year, including unscheduled maintenance.

text: AMC M.A.803 is amended as follows:

text: AMC M.A.803 Pilot-owner authorisation

text: … 5. Not holding a valid medical examination does not invalidate the pilot licence (or equivalent) required under M.A.803(a)1 for the purpose of the Pilot-owner authorisation.

text: AMC M.A.901(a) is amended as follows:

text: AMC M.A.901(a) Aircraft airworthiness review

text: EASA Form 15a is issued by competent authorities while EASA Form 15b is issued by an M.A. Subpart G organisation and EASA Form 15c is issued by a Part-145 or an M.A. Subpart F maintenance organisation.

text: A new AMC M.A.901(l)1 is introduced as follows:

text: AMC M.A.901(l)1 Aircraft airworthiness review

text: Independence from the continuing airworthiness management process of the aircraft means being authorised to perform airworthiness reviews only on aircraft for which the person has not participated in their continuing airworthiness management. This may not be relevant for most maintenance organisations (Part-145 or Part-M Subpart F). Since these organisations cannot perform the continuing airworthiness management of aircraft (this is a privilege of CAMOs), it needs to be considered by those maintenance organisations (Part-145 or Part- M Subpart F) intending to nominate as airworthiness review staff certifying staff who are also employed/contracted by a CAMO and who have been involved in the continuing airworthiness management of the aircraft being reviewed. Nevertheless, such independence is not necessary if these airworthiness review staff (who are also employed/contracted by the CAMO) can show ‘overall authority on the continuing airworthiness management process of the complete aircraft’. This may be achieved, among other ways, if this person is: — the accountable manager or the nominated postholder of the CAMO. — responsible for the complete continuing airworthiness management process of the aircraft being reviewed. — the only person employed by an one-man CAMO.

text: AMC M.A.904(a)(2) is amended as follows:

text: AMC M.A.904(a)(2) Airworthiness review of aircraft imported into the EU

text: … 3. If there is no M.A. Subpart G organisation or maintenance organisation approved for the airworthiness review of the specific aircraft type available, the competent authority may carry out the airworthiness review in accordance with this paragraph and the provisions of M.A.901(h) and M.B.902. In this case, the airworthiness review should be requested to the competent authority with a 30-day notice.

text: AMC M.B.301(c) is amended as follows:

text: AMC M.B.301(c) Maintenance programme

text: … 3. When the competent authority requests it, the organisation should make provision for the attendance of a representative of the competent authority representative at meetings held to consider maintenance implications arising from reviews of the above provisions.

text: AMC M.B.603(a) is amended as follows:

text: AMC M.B.603(a) Issue of approval

text: 1. … 2. …

text: 3. Special case for ELA1 aircraft:

text: In order to promote standardisation, for this category of aircraft the following approach is recommended: — Possible ratings to be endorsed in EASA Form 3:  ELA1 sailplanes;  ELA1 powered sailplanes and ELA1 aeroplanes;  ELA1 balloons;  ELA1 airships. — Before endorsing any of those ratings (for example, ELA1 sailplanes) in EASA Form 3, the competent authority should audit that the organisation is capable of maintaining at least one aircraft type (for example, one type of sailplanes within the ELA1 category), including the availability of the necessary facilities, equipment, tooling, material, maintenance data, and certifying staff. — It is acceptable that the detailed scope of work in the Maintenance Organisation Manual (MOM) contains the same ratings endorsed in EASA Form 3 (for example, ELA1 sailplanes),

text: without a need to further limit them. However, the maintenance organisation will only be able to maintain a certain aircraft type when all the necessary facilities, equipment, tooling, material, maintenance data, and certifying staff are available.

text: AMC M.B.703 is amended as follows:

text: AMC M.B.703 Issue of approval

text: The table shown for the Approval Schedule in EASA Form 14 includes a field designated as ‘Aircraft type/series/group’ The intention is to give maximum flexibility to the competent authority to customise the approval to a particular organisation. Possible alternatives to be included in this field are the following: — A specific type designation that is part of a type certificate, such as Airbus 340-211 or Cessna 172R. — A type rating (or series) as listed in Part-66 Appendix I to AMC, which may be further subdivided, such as Boeing 737-600/700/800, Boeing 737-600, Cessna 172 Series. — An aircraft group such as, for example, ‘all sailplanes and powered sailplanes’ or ‘Cessna single piston engined aircraft’ or ‘Group 3 aircraft’ (as defined in 66.A.5) or ‘aircraft below 2 730 kg MTOM’. Reference to the engine type installed in the aircraft may or may not be included, as necessary. It is important to note that the scope of work defined in EASA Form 14 is further limited to the one defined in the Continuing Airworthiness Management Exposition (CAME). It is this scope of work in the CAME which ultimately defines the approval of the organisation. As a consequence, it is possible for a competent authority to endorse in EASA Form 14, for example, a scope of work for Group 3 aircraft while the detailed scope of work defined in the CAME does not include all Group 3 aircraft. Nevertheless, in all cases, the competent authority should be satisfied that the organisation has the capability to manage the requested types/groups/series endorsed in the EASA Form 14. Since the activities linked to continuing airworthiness management are mainly process-oriented rather than facility/tooling-oriented, changes to the detailed scope of work defined in the CAME (either directly or through a capability list), within the limits already included in EASA Form 14, may be considered as not affecting the approval and not subject to M.A.713. As a consequence, for these changes the competent authority may allow the use by the M.A. Subpart G organisation of the indirect approval procedure defined in M.A.704(c). In the example mentioned above, before endorsing the Group 3 in EASA Form 14 for the first time, the competent authority should make sure that the organisation is capable of managing this category of aircraft as a whole. In particular, the competent authority should ensure that Baseline/Generic Maintenance Programmes (see M.A.709) or individual maintenance programmes (for contracted customers) are available for all the aircraft which are intended to be initially included in the scope of work detailed in the CAME. Later on, if changes need to be introduced in the detailed scope of work detailed in the CAME to include new aircraft types (within Group 3), this may be done by the M.A. Subpart G organisation through the use of the indirect approval procedure.

text: Since, as mentioned above, the competent authority should make sure that the organisation is capable of managing the requested category as a whole, it is not reasonable to grant a full Group 3 approval based on an intended scope of work which is limited to, for example, a Cessna 172 aircraft. However, it may be reasonable to grant such full Group 3 approval, after showing appropriate capability, for an intended scope of work covering several aircraft types or series of different complexity and which are representative of the full Group 3.

text: Special case for ELA1 aircraft:

text: In order to promote standardisation, for this category of aircraft the following approach is recommended: — Possible ratings to be endorsed in EASA Form 14:  ELA1 sailplanes;  ELA1 powered sailplanes and ELA1 aeroplanes;  ELA1 balloons;  ELA1 airships. — Before endorsing any of those ratings (for example, ELA1 sailplanes) in EASA Form 14, the competent authority should audit that the organisation is capable of managing at least one aircraft type (for example, one type of sailplanes within the ELA1 category), including the availability of the necessary facilities, data, maintenance programmes, and staff. — It is acceptable that the detailed scope of work in the CAME contains the same ratings endorsed in EASA Form 14 (for example, ELA1 sailplanes), without a need to further limit them. However, the CAMO will only be able to manage a certain aircraft type when all the necessary facilities, data, maintenance programmes and staff are available.  Appendix IV to AMC M.A.604 is amended as follows:

text: Appendix IV to AMC M.A.604 Maintenance organisation manual

text: 1. Purpose

text: 2. Content

text: … Part A — General

text: — Table of contents

text: … Part B — Description

text: — Certifying staff and airworthiness review staff

text:  Minimum qualification and experience

text:  List of authorised certifying staff and airworthiness review staff, their scope of qualification and the personal authorisation reference … Part C — General Procedures … Part D — Working Procedures

text: — Records

text: — Airworthiness review procedures and records for ELA1 aircraft not involved in commercial operations

text: — Development and approval processing for maintenance programmes for ELA2 aircraft not involved in commercial operations

text: — Special procedures

text: Such as specialised tasks, disposal of unsalvageable components, re-certification of parts not having an EASA Form 1, etc. … Part E – Appendices …

text: 3. Approval

text: 4. Continuous compliance with Part-M

text: 5. Distribution

text: Appendix VI to AMC M.B.602(f) is amended as follows:

text: Appendix VI to AMC M.B.602(f) EASA Form 6F

text: M.A. SUBPART F APPROVAL RECOMMENDATION REPORT EASA FORM 6F

text: Part 1: General

text: Name of organisation: Approval reference: Requested approval rating/ EASA Form 3 dated*: Other approvals held (If app.) Address of facility audited:

text: Audit period: from to : Date(s) of audit(s): Audit reference(s): Persons interviewed: Competent authority surveyor: Signature(s): Competent authority office: Date of EASA Form 6F part 1 completion:

text: *delete where applicable

text: Part 2: M.A. Subpart F Compliance Audit Review

text: The five columns may be labelled and used as necessary to record the approval product line or facility, including subcontractor’s, reviewed. Against each column used of the following M.A. Subpart F subparagraphs please either tick () the box if satisfied with compliance or cross (X) the box if not satisfied with compliance and specify the reference of the Part 4 finding next to the box or enter N/A where an item is not applicable, or N/R when applicable but not reviewed. Para Subject M.A.603 Extent of approval M.A.604 Maintenance Organisation Manual (see Part 3) M.A.605 Facilities M.A.606 Personnel requirements M.A.607 Certifying staff and airworthiness review staff M.A.608 Components, Equipment and tools M.A.609 Maintenance data M.A.610 Maintenance work orders M.A.611 Maintenance standards

text: M.A.612 Aircraft certificate of release to service M.A.613 Component certificate of release to service M.A.614 Maintenance records M.A.615 Privileges of the organisation M.A.616 Organisational review M.A.617 Changes to the approved maintenance organisation M.A.619 Findings Competent authority surveyor(s): Signature(s): Competent authority office: Date of EASA Form 6F part 2 completion:

text: PART 3: Compliance with M.A. Subpart F maintenance organisation manual (MOM)

text: Please either tick () the box if satisfied with compliance; or cross (x) if not satisfied with compliance and specify the reference of the Part 4 finding; or enter N/A where an item is not applicable; or N/R when applicable but not reviewed. Part A General 1.1 Table of content 1.2 List of effective pages

text: 1.3 Record of amendments 1.4 Amendment procedure 1.5 Distribution 1.6 Accountable manager’s statement Part B Description 2.1 Organisation’s scope of work 2.2 General presentation of the organisation 2.3 Name and title of management personnel 2.4 Organisation chart 2.5 Certifying staff and airworthiness review staff 2.6 Personnel 2.7 General description of the facility 2.8 Tools, equipment and material 2.9 Maintenance data Part C General procedures 3.1 Organisational review 3.2 Training 3.3 Contracting Subcontracting of specialised services 3.4 One time authorisations

text: Part D Working Procedures 4.1 Work order acceptance 4.2 Preparation and issue of work package 4.3 Logistics 4.4 Execution 4.5 Release to service – Certifying staff

text: 4.6 Release to service – Supervision 4.7 Release to service – Certificate of release to service 4.8 Records Airworthiness review procedures and records for ELA1 aircraft not involved in 4.9 commercial operations

text: Procedures for the development and approval processing for maintenance 4.10 programmes for ELA2 aircraft not involved in commercial operations

text: 4.9 4.11 Special procedures 4.10 4.12 Occurrence reporting 4.11 4.13 Management of indirect approval of the manual Part E Appendices 5.1 Sample of all documents used 5.2 List of subcontractors. 5.3 List of maintenance locations 5.4 List of Part 145 or M.A. Subpart F organisations

text: MOM reference: MOM amendment: Competent authority audit staff: Signature(s): Competent authority office: Date of EASA Form 6F part 3 completion:

text: Part 4: Findings regarding M.A. Subpart F compliance status

text: Each level 1 and 2 finding should be recorded whether it has been rectified or not and should be identified by a simple cross reference to the Part 2 requirement. All non-rectified findings should be copied in writing to the organisation for the necessary corrective action. L Audit reference(s): e Corrective action Part v 2 or 3 Findings e Date Date ref. l Due Closed Reference

text: Part 5: M.A. Subpart F approval or continued approval or change recommendation

text: Name of organisation: Approval reference: Audit reference(s): The following M.A. Subpart F scope of approval is recommended for this organisation:

text: Or, it is recommended that the M.A. Subpart F scope of approval specified in EASA Form 3

text: Name of recommending competent authority surveyor: Signature of recommending competent authority surveyor: Competent authority office: Date of recommendation: EASA Form 6F review (quality check) : Date:

text: Appendix VIII to AMC M.A.616 is amended as follows:

text: Appendix VIII to AMC M.A.616

text: … Following is a typical example of a simplified organisational review checklist, to be adapted as

text: necessary to cover the MOM procedures:

text: 1 – Scope of work

text: Check that: — All aircraft and components under maintenance or under contract are covered in the EASA Form 3. — The scope of work in the MOM does not disagree with the EASA Form 3. — No work has been performed outside the scope of the Form 3 and the MOM.

text: 2 - Maintenance data

text: 3 – Equipment and Tools

text: 4 – Stores

text: 5 – Certification of maintenance, airworthiness review and development and approval processing of maintenance programmes

text: — Has maintenance on products and components been properly certified? — Have implementation of modifications/repairs been carried out with appropriate approval of such modifications/repairs (sample check)?. — Have airworthiness reviews been properly performed and the airworthiness review certificate properly been issued? — Have maintenance programmes for ELA2 aircraft not involved in commercial operations been properly developed?

text: 6 – Relations with the owners/operators

text: 7 – Personnel

text: 8 – Maintenance contracted

text: — Sample check of maintenance records:  Existence and adequacy of the work order,  Data received from the maintenance organisation:

text: o Valid CRS including any deferred maintenance, o List of removed and installed equipment and copy of the associated EASA Form 1 or equivalent. — Obtain a copy of the current approval certificate (EASA Form 3) of the maintenance organisations contracted.

text: 9 – Maintenance subcontracted

text: Check that subcontractors for specialised services are properly controlled by the organisation.

text: 10 – Technical records and record-keeping

text: — Have the maintenance actions been properly recorded? — Have the certificates (EASA Form 1 and Conformity certificates) been properly collected and recorded? — Perform a sample check of technical records to ensure completeness and storage during the appropriate periods. — Is storage of computerised data properly ensured?

text: 11 – Occurrence reporting procedures

text: — Check that reporting is properly performed. — Actions taken and recorded.

text: SCOPE OF APPROVAL AVAILABLE

text: CLASS RATING LIMITATION BASE LINE

text: AIRCRAFT A1 Aeroplanes above [Rating reserved to Maintenance [YES/ [YES/ 5 700 kg Organisations approved in NO]* NO]* accordance with Annex II (Part-145)] [State aeroplane manufacturer or group or series or type and/or the maintenance tasks]

text: Example: Airbus A320 Series

text: A2 Aeroplanes 5 700 [State aeroplane manufacturer or [YES/ [YES/ kg and below group or series or type and/or the NO]* NO]* maintenance tasks]

text: Example: DHC-6 Twin Otter Series

text: State whether the issue of airworthiness review certificates is requested or not (only possible for ELA1 aircraft not involved in commercial operations) A3 Helicopters [State helicopter manufacturer or [YES/ [YES/ group or series or type and/or the NO]* NO]* maintenance task(s)]

text: Example: Robinson R44

text: A4 Aircraft other than [State aircraft category (sailplane, [YES/ [YES/ A1, A2 and A3 balloon, airship, etc.), manufacturer NO]* NO]* or group or series or type and/or the maintenance task(s).] State whether the issue of airworthiness review certificates is requested or not (only possible for ELA1 aircraft not involved in commercial operations). ENGINES B1 Turbine [State engine series or type and/or the maintenance task(s)]

text: Example: PT6A Series

text: B2 Piston [State engine manufacturer or group or series or type and/or the maintenance task(s)]

text: B3 APU [State engine manufacturer or series or type and/or the maintenance task(s)]

text: C1 Air Cond & Press COMPONENTS C2 Auto Flight OTHER THAN C3 Comms and Nav [State aircraft type or aircraft manufacturer or component COMPLETE manufacturer or the particular component and/or cross refer C4 Doors - Hatches

text: CLASS RATING LIMITATION BASE LINE ENGINES OR to a capability list in the exposition and/or the maintenance C5 Electrical Power & APUs task(s).] Lights C6 Equipment C7 Engine - APU Example: PT6A Fuel Control C8 Flight Controls C9 Fuel C10 Helicopter - Rotors C11 Helicopter - Trans C12 Hydraulic Power C13 Indicating recording system C14 Landing Gear C15 Oxygen C16 Propellers C17 Pneumatic & Vacuum C18 Protection ice/rain/fire C19 Windows C20 Structural C21 Water ballast C22 Propulsion augmentation SPECIALISED D1 Non-Destructive [State particular NDT method(s)] Testing SERVICES * Delete as appropriate. EASA Form 2 Page 2 of 2


text: OJ L 240, 7.9.2002, p. 1. Regulation as last amended by

text: Regulation (EC) No 1701/2003

text: (OJ L 243, 27.9.2003, p. 5). OJ L 315, 28.11.2003, p. 1. Regulation as last amended by

text: Regulation (EC) No 707/2006

text: (OJ L 122, 9.5.2006, p. 17).

text: Decision of the Management Board concerning the procedure to be applied by the Agency for the issuing of opinions, certification specifications and guidance material (“rulemaking procedure”), EASA MB/7/03, 27.6.2003. See: NPA No 20-2005 See: CRD No 20-2005

identifier: AMC to Part-M — Amendment 2

amnesord: Part-M - Continuing airworthiness requirements

beslut: ED Decision 2006/014/R

publisher: Europeiska unionens byrå för luftfartssäkerhet

sprak: en

title: AMC to Part-M — Amendment 2

serie: amc

text: ED Decision 2006/14/R 20/12/2006

type: stycke

text: European Aviation Safety Agency

type: rubrik

text: DECISION No 2006/14/R

text: OF THE EXECUTIVE DIRECTOR OF THE EUROPEAN AVIATION SAFETY AGENCY

text: of 20 December 2006

text: amending Decision No 2003/19/RM of 28 November 2003 on acceptable means of compliance and guidance material to

text: Commission Regulation (EC) No 2042/2003

text: THE EXECUTIVE DIRECTOR OF THE EUROPEAN AVIATION SAFETY AGENCY,

text: Having regard to

text: Regulation (EC) No 1592/2002

text: of the European Parliament and of the Council of 15 July 2002 on common rules in the field of civil aviation and establishing a European Aviation Safety Agency (hereinafter referred to as the Basic Regulation), and in particular Articles

text: and

text: thereof.

text: Having regard to the

text: Commission Regulation (EC) No 2042/2003 of 20 November 2003

text: on the continuing airworthiness of aircraft and aeronautical products, parts and appliances, and on the approval of organisations and personnel involved in these tasks .

text: Whereas:

text: (1) Non-required equipment in sailplanes is certified on a non-hazard basis.

text: (2) The current explanation of the term “standard part” implies that all equipment in sailplanes must be produced under a Production Organisation Approval, which for non-required equipment is not commensurate with the design approval effort.

text: (3) An extension of the Standard Parts definition to include non-required equipment for sailplanes will restore consistency between the design an production requirements for these parts.

text: (4) The Agency shall issue certification specifications, including airworthiness codes and acceptable means of compliance, as well as any guidance material for the application of the Basic Regulation and its implementing rules.

text: ED Decision 2006/14/R 20/12/2006

text: (5) The Agency, pursuant to Article 43 of the Basic Regulation and Articles

text: and

text: 4 6 of the rulemaking procedure , has widely consulted interested parties on the matters which are the subject of this Decision and has provided thereafter a written response to the comments received .

text: HAS DECIDED:

text: Article 1

text: Decision N° 2003/19/RM is hereby amended as follows.

text: AMC M.A.501(c) is replaced by the following:

text: “AMC M.A.501(c) – Installation

text: 1. Standard parts are: a. Parts manufactured in complete compliance with an established industry, Agency, competent authority or other Government specification which includes design, manufacturing, test and acceptance criteria, and uniform identification requirements. The specification should include all information necessary to produce and verify conformity of the part. It should be published so that any party may manufacture the part. Examples of specifications are National Aerospace Standards (NAS), Army-Navy Aeronautical Standard (AN), Society of Automotive Engineers (SAE), SAE Sematec, Joint Electron Device Engineering Council, Joint Electron Tube Engineering Council, and American National Standards Institute (ANSI), EN Specifications etc… b. For sailplanes and powered sailplanes, non-required instruments and/or equipment certified under the provision of CS 22.1301(b), if those instruments or equipment, when installed, functioning, functioning improperly or not functioning at all, do not in itself, or by its effect upon the sailplane and its operation, constitute a safety hazard. “Required” in the term “non-required” as used above means required by the applicable airworthiness code (CS 22.1303, 22.1305 and 22.1307) or required by the relevant operating regulations and the applicable Rules of the Air or as required by Air Traffic Management (e.g. a transponder in certain controlled airspace). Examples of equipment which can be considered standard parts are electrical variometers, bank/slip indicators ball type, total energy probes, capacity bottles (for variometers), final glide calculators, navigation computers, data logger / barograph /turnpoint camera, bug-wipers and anti-collision systems. Equipment which must be approved in accordance to the airworthiness code shall comply with the applicable ETSO or equivalent and is not considered a standard part (e.g. oxygen equipment).

text: 2. To designate a part as a standard part the TC holder may issue a standard parts manual accepted by the competent authority of original TC holder or may make

text: ED Decision 2006/14/R 20/12/2006

text: reference in the parts catalogue to a national/international specification (such as a standard diode/capacitor etc) not being an aviation only specification for the particular part.

text: 3. Documentation accompanying standard parts should clearly relate to the particular parts and contain a conformity statement plus both the manufacturing and supplier source. Some material is subject to special conditions such as storage condition or life limitation etc. and this should be included on the documentation and / or material packaging.

text: 4. An EASA Form 1 or equivalent is not normally issued and therefore none should be expected.”

text: Article 2

text: This Decision shall enter into force on 27 December 2006.

text: Done at Cologne, 20 December 2006

text: P. GOUDOU

type: vagledning

utgivare: easa


text: ED Decision 2007/001/R 13/03/2007

text: DECISION No 2007/001/R

text: OF THE EXECUTIVE DIRECTOR OF THE AGENCY

text: of 13 March 2007

text: amending Annex I of Decision N° 2003/19/RM of the Executive Director of the Agency of 28 November 2003 on acceptable means of compliance and guidance material to

text: on the continuing airworthiness of aircraft and aeronautical products, parts and appliances, and on the approval of organisations and personnel involved in these tasks.

text: THE EXECUTIVE DIRECTOR OF THE EUROPEAN AVIATION SAFETY AGENCY,

text: Having regard to

text: Regulation (EC) No 1592/2002

text: of the European Parliament and of the Council of 15 July 2002 on common rules in the field of civil aviation and establishing a European Aviation Safety Agency (hereinafter referred to as the Basic Regulation), and in particular Articles

text: and

text: thereof,

text: Having regard to the

text: on the continuing airworthiness of aircraft and aeronautical products, parts and appliances, and on the approval of organisations and personnel involved in these tasks ,

text: (1) Annex I of Acceptable Means of Compliance to Part-M of Decision 2003/19/RM is required to be up to date to reflect the need of introducing the concept of Critical Design Control Configuration Limitations (CDCCL).

text: (2) To achieve this requirement the text of the Annex I of Acceptable Means of Compliance to Part-M of Decision 2003/19/RM should be amended accordingly.

text: (3) The Agency shall issue certification specifications, including airworthiness codes and acceptable means of compliance, as well as any guidance material for the application of the Basic Regulation and its implementing rules.

text: OJ L 240, 7.9.2002, p. 1. Regulation as last amended by

text: Regulation (EC) No 1701/2003

text: (OJ L 243, 27.9.2003, p. 5). OJ L 315, 28.11.2003, p. 1. Regulation as amended by

text: Regulation (EC) No 707/2006

text: (OJ L 122, 9.5.2006, p. 17).

text: (4) The Agency, pursuant to Article 43 of the Basic Regulation and Articles 5(3) and 6 of the rulemaking procedure , has widely consulted interested parties on the matters which are the subject of this Decision and has provided thereafter a written response to the comments received .

text: HAS DECIDED:

text: Article 1

text: The Annex I of Acceptable Means of Compliance to Part-M of Decision

text: on the continuing airworthiness of aircraft and aeronautical products, parts and appliances, and on the approval of organisations and personnel involved in these tasks, is hereby amended in accordance with the Annex 1 to this Decision.

text: Article 2

text: This Decision shall enter into force on 20 March 2007.

text: Done in Cologne, 13 March 2007

text: P. GOUDOU By delegation C. PROBST

text: Decision of the Management Board concerning the procedure to be applied by the Agency for the issuing of opinions, certification specifications and guidance material (“rulemaking procedure”), EASA MB/7/03, 27.6.2003. See: NPA No 22-2005 See: CRD No 22-2005

identifier: AMC to Part-M — Amendment 3

beslut: ED Decision 2007/001/R

title: AMC to Part-M — Amendment 3

text: European Aviation Safety Agency

text: Annex 1 to Decision 2007/001/R

text: The following paragraphs of Annex I to Decision 2003/19/RM AMC to Part-M are amended as follows:

text: AMC M.A.201 (h) Responsibilities

text: …. 4. An operator should therefore have adequate knowledge of the design status (type specification, customer options, airworthiness directives (AD), airworthiness limitations including Critical Design Configuration Control Limitations (CDCCL), modifications, major repairs, operational equipment) and required and performed maintenance. Status of aircraft design and maintenance should be adequately documented to support the performance of the quality system. ….

text: AMC M.A.301 -5- Continuing Airworthiness Tasks

text: …. Any other continued airworthiness requirement made mandatory by the Agency includes TC related requirements such as: certification maintenance requirements (CMR), certification life limited parts, airworthiness limitations including Airworthiness Limitation Items (ALI), Critical Design Configuration Control Limitations (CDCCL), etc.

text: AMC M.A.501(b) Installation

text: …. 3. The person referred to under M.A.801 or the M.A. Subpart F approved maintenance organisation should be satisfied that the component in question meets the approved data/standard, such as the required design and modification standards. This may be accomplished by reference to the TC holder or manufacturer's parts catalogue or other approved data (i.e. SBService Bulletin). Care should also be exercised in ensuring compliance with applicable ADs and the status of any service life limited parts fitted to the aircraft component as well as compliance with Critical Design Configuration Control Limitations.

text: AMC M.A.501(d) Installation

text: Insert a new paragraph 7:

text: 7. When using raw or consumable material on an aircraft or component near, or adjacent to, or that directly impacts an identified Critical Design Configuration Control Limitation item, it should be ensured that the CDCCL has not been compromised. AMC M.A.704 Continuing airworthiness management exposition …. Insert a new paragraph 11:

text: 10. Whenever the accountable manager is changed it is important to ensure that the new accountable manager signs the paragraph 9 statement at the earliest opportunity as part of the acceptance by the approving competent authority. Failure to carry out this action invalidates the M.A. Subpart G continuing airworthiness management approval or the air operator’s certificate. 11. The exposition should contain information as applicable, on how the continuing airworthiness management organisation complies with CDCCL instructions. Appendix V contains an example of an exposition lay-out. Add a new paragraph AMC M.A.706(f): AMC M.A.706(f) Personnel requirements Additional training in fuel tank safety as well as associated inspection standards and maintenance procedures should be required of continuing airworthiness management organisations’ technical personnel, especially those technical support staff involved with the management of CDCCL, Service Bulletin assessment, work planning and maintenance programme management. EASA guidance is provided for training to Continuing Airworthiness Management Organisations’ continuing airworthiness personnel in Appendix XII to AMC to M.A.706(f) and M.B.102(c). Add a new paragraph AMC M.A.708(b)3: AMC M.A.708(b)3. Continuing Airworthiness Management When managing the approval of modifications or repairs the organisation should ensure that Critical Design Configuration Control Limitations are taken into account. Modify paragraph 1.6 of AMC M.B.102(c): AMC M.B.102(c) Competent authority – Qualification and training 1.6 knowledge of a relevant sample of the type(s) of aircraft gained through a formalised training course, including Fuel Tank Safety (FTS) training as described in Appendix XII to AMC to M.A.706(f) and M.B.102(c). Appendix I to AMC M.A.302 and AMC M.B.301(b) Insert a new paragraph 1.1.14: 1.1.14. If applicable, details of Critical Design Configuration Control Limitations together with appropriate procedures. 1.1.1514 …. 1.1.1615 …. 1.1.1716 …. 1.1.1817 …. 1.1.1918 …. 1.1.2019 …. …. Insert a new paragraph 2.4: 2.4 Critical Design Configuration Control Limitations (CDCCL) If CDCCL have been identified for the aircraft type by the TC/STC holder, maintenance instructions should be developed. CDCCL’s are characterised by features in an aircraft installation or component that should be retained during modification, change, repair, or scheduled maintenance for the operational life of the aircraft or applicable component or part. Insert a new Appendix XII to AMC to Part-M: Appendix XII to AMC to M.A.706(f) and M.B.102(c) Fuel Tank Safety training This appendix includes general instructions for providing training on Fuel Tank Safety (FTS) issues.

text: 1. Levels of training Level 1 Familiarisation training Objectives: The attendant should, after the completion of the training: 1. be familiar with the basic elements of the fuel tank safety issues.

text: 2. be able to give a simple description of the historical background and the elements requiring a safety consideration, using common words and showing examples of non conformities.

text: 3. be able to use typical terms. The familiarisation training should include a presentation of bulletins/notices, short videos or CD material, poster campaigns, etc. Level 2 Detailed training Objectives: The attendant should, after the completion of the training: 1. know the history and the theoretical and practical elements of the subject, have an overview of Special Federal Aviation Regulations (SFARs) from 14 CFR SFAR 88 of the FAA and of JAA Temporary Guidance Leaflet TGL 47, be able to give a detailed description of the concept of Critical Design Configuration Control Limitations CDCCL, Airworthiness Limitations Items (ALI) and using theoretical fundamentals and specific examples, 2. have the capacity to combine and apply the separate elements of knowledge in a logical and comprehensive manner. 3. have detailed information on how the above items affect the aircraft in the scope of the activity of the organisation or in the fleet.

text: 4. understand and carry out activities with the use of manufacturer and regulatory authority data providing instructions on design and maintenance, such as Service Bulletins, Airworthiness Directives, Aircraft Maintenance Manual, Component Maintenance Manual etc.

text: 5. use easily the manufacturer’s documentation from various sources and apply corrective action where appropriate.

text: 6. identify the components or parts or the aircraft subject to FTS from the manufacturer’s documentation, plan the action or apply a Service Bulletin and an Airworthiness Directive. Continuing training The interval between continuing training shall be established by the Continuing Airworthiness management organisation, but should not exceed two years. The continuing training shall include knowledge on evolution of material, tools, documentation and manufacturer’s or competent authority’s directives.

text: 2. The personnel directly involved in Fuel Tank Safety (FTS) systems shall be qualified according to the following table: Organisation Personnel Level of Continuing knowledge training Continuing Any personnel required by 2 Yes Airworthiness M.A.706 except the Accountable Management Manager of the continuing Organisations airworthiness management organisation. The airworthiness review staff as required by M.A.707. Quality manager as required by 1 Not required M.A.712 NAA Management, inspectors and 1 Not required auditors.

text: 3. General requirements The training shall be carried out at the earliest for the personnel needing level 1 training. Nevertheless, the training for the personnel needing level 2 training has to be carried out before they perform any continuing airworthiness management activity. The training should be made in appropriate facilities containing examples of components, systems and parts affected by FTS issues and having access to aircraft or component where typical examples of FTS issues can be shown. The use of pictures, films and practical examples of the maintenance on fuel tank system is recommended. The training shall include a representative number of repair and inspections as required by the maintenance programme showing the necessity of using the manufacturer’s data.

text: 4. Characteristics of the training The following characteristics shall be taken into consideration when the level 1 or 2 training programmes are being established: a) understanding of the background and concepts of fuel tank safety as developed during the last 10 years, and b) how in maintenance instructions to maintenance organisations the mechanics can recognise, interpret and handle the improvements that have been made or are being made during fuel tank system maintenance, c) awareness of any hazards working on the fuel system, and especially with a Flammability Reduction System using nitrogen. a), b) and c) should be introduced in the training programme addressing the following issues: i) The theoretical background behind the fuel tank safety: the explosions of mixtures of fuel and air, the behaviour of those mixtures in an aviation environment, the effects of temperature and pressure, energy needed for ignition etc, the ‘fire triangle’, - Explain 2 concepts to prevent explosions: (1) ignition source prevention and (2) flammability reduction, ii) The major accidents and accident investigations and their conclusions, iii) SFARs from 14 CFR SFAR 88 of the FAA and JAA Internal Policy INT POL 25/12: reason of these documents, and what was the ultimate goal, margins of fuel system safety improvements (from 10-6 to 10-9, in fact improvement by a factor 100- 1000, to identify unsafe conditions and to correct them, to systematically improve fuel tank maintenance), iv) Explain the concepts that are being used: the results of SFAR 88 of the FAA and JAA INT/POL 25/12: modifications, airworthiness limitations and CDCCL, v) Where relevant information can be found by the mechanics and how to use and interpret this information (maintenance manuals, component maintenance manuals) vi) Fuel Tank Safety and Maintenance: fuel tank entry and exit procedures, clean working environment, what is meant by configuration control, wire separation, bonding of components etc, vii) Flammability reduction systems: reason for their presence, their effects, the hazards of an FRS using nitrogen for maintenance, safety precautions in maintenance/working with an FRS, viii) recording maintenance actions, recording measures and results of inspections.