MCAR 21 (2nd Edition)

Civil Aviation Requirements

MCAR-Part 21

Airworthiness _____________________ Second Edition 2010 Department of Civil Aviation Ministry of Transport, Myanmar

Myanmar Civil Aviation Requirements Part 21 Airworthiness ---------------------------------------------------------------------------------------------------------------------------------------------------------------------------

----------------------------------------------------------------------------------------------------------------------------------------------------------- Effective Date; 8th July 2010 1/21 Second Edition

PREFACE Myanmar is a Signatory to the Convention on International Civil Aviation (Chicago Convention, signed at Chicago on 7 December 1944). Under Article 12 of the Convention, Myanmar, as a Contracting State, is obligated to adopt measures to insure safety through conformity with international standards in its safety oversight obligations. The fundamental elements of national safety oversight legislation are establishing and empowering Department of civil aviation in Myanmar. MCAR Part-21 is part of the Myanmar Legislation and stipulates requirements in respect of Airworthiness of aircraft on Myanmar registered and aircraft operated under Myanmar AOCs. Most of the aircraft registered in Myanmar have the range to operate in both local and international Aviation. Simplicity in the legislation of civil aviation under such circumstances will support the consistent application of ICAO SARPs throughout the aviation community within Myanmar. This part sets forth requirements for the airworthiness of aircraft expected to operate in Myanmar using Myanmar aircraft rules, the SARPs in ICAO annex 6 and annex 8. Maintenance requirements in this part are also for persons who are neither employees of an Approved Maintenance Organization nor an Air Operator Certificates holder. All Myanmar Registered aircraft shall meets all the requirements related to airworthiness specified in Myanmar Aircraft Rules, Myanmar Civil Aviation Requirements and in addition to this requirement. This requirement has been issued under authority conferred by Section 5-A (c) of the Myanmar Aircraft Act (1934) by the Director General. Enquires on the contents of this requirement should be addressed to __ Director (Airworthiness) Airworthiness Division Department of Civil Aviation Yangon International Airport, Yangon 11021 Tel: 95 1 533 003 95 1 533 014 Fax: 95 1 533 016 _______________________ Director General Department of Civil Aviation Union of Myanmar



CONTENTS 21.1 GENERAL................................................................................................................................................ 3

21.1.1.1 Applicability.............................................................................................................................. 3 21.1.1.2 Definitions................................................................................................................................ 3 21.1.1.3 Acronyms................................................................................................................................. 7

21.2 AIRCRAFT AND COMPONENT ORIGINAL CERTIFICATION ................................................................ 7 21.2.1.1 Applicability.............................................................................................................................. 7

21.3 SUPPLEMENTAL TYPE CERTIFICATES ............................................................................................... 7 21.3.1.1 Applicability.............................................................................................................................. 7 21.3.1.2 Issuance of a Supplemental Type Certificate........................................................................... 6

21.4 AIRWORTHINESS CERTIFICATES ........................................................................................................ 6 21.4.1.1 Applicability.............................................................................................................................. 6 21.4.1.2 Eligibility................................................................................................................................... 8

21.4.1. 3 CLASSIFICATIONS OF AIRWORTHINESS CERTIFICATES..8 21.4.1.4 Amendment of Airworthiness Certificate.................................................................................. 8 21.4.1.5 Transfer or Surrender of Airworthiness Certificate................................................................... 8 21.4.1.6 Effective Dates of Airworthiness Certificate ............................................................................. 8 21.4.1.7 Aircraft Identification ................................................................................................................ 9 21.4.1.8 Issue, Validate and Renewal of Airworthiness Certificates ...................................................... 9 21.4.1.9 Commercial Air Transport ........................................................................................................ 9 21.4.1.10 Airworthiness Directives .......................................................................................................... 9 21.4.1.11 Issue of Special Airworthiness Certificates ............................................................................ 10

21.5 CONTINUED AIRWORTHINESS OF AIRCRAFT AND COMPONENTS ............................................... 11 21.5.1.1 Applicability............................................................................................................................ 11 21.5.1.2 Responsibility......................................................................................................................... 11 21.5.1.3 General .................................................................................................................................. 11 21.5.1.4 Requirements for Certificate of release to Service................................................................. 12 21.5.1.5 Requirements for Certificate of Maintenance Review ............................................................ 12 21.5.1.6 Aircraft, Engine and Propeller Log Books .............................................................................. 11 21.5.1.7 Technical Log ........................................................................................................................ 12 21.5.1.8 Equipment of Aircraft ............................................................................................................. 12 21.5.1.9 Qualification Requirements for NDT Personnel ..................................................................... 13 21.5.1.10 Reporting of Failures, Malfunctions, and Defects .................................................................. 14

21.6 AIRCRAFT MAINTENANCE AND INSPECTION................................................................................... 16 21.6.1.1 Applicability............................................................................................................................ 16 21.6.1.2 Persons Authorised to Perform Maintenance, Preventive Maintenance, and Modifications ..16 21.6.1.3 Persons Authorised to Perform Maintenance ........................................................................ 17 21.6.1.4 Authorised Personnel to Approve for Return to Service ........................................................ 17 21.6.1.5 Persons Authorised to Perform Inspections........................................................................... 18 21.6.1.6 Persons Authorised to Perform Duplicate Inspection of controls ........................................... 18 21.6.1.7 Performance Rules : Maintenance......................................................................................... 18 21.6.1.8 Performance Rules : Inspections ........................................................................................... 19 21.6.1.9 Performance Rules : Airworthiness Limitations...................................................................... 19

21.7 MAINTENANCE RECORDS AND ENTRIES ......................................................................................... 20 21.7.1.1 Content, Form, and Disposition of Maintenance, Preventive Maintenance, Rebuilding, and Modification Records ...................................................................................................... 20 21.7.1.2 Records of Overhaul and Rebuilding ..................................................................................... 20 21.7.1.3 Approval for Return to Service After Maintenance, Preventive maintenance, Rebuilding,or Modification............................................................................................................................ 20 21.7.1.4 Content, Form, and Disposition of Records for Inspections................................................... 20



21.1 GENERAL

21.1.1.1 APPLICABILITY

This part prescribes the requirements for

(1) Apply to aircraft registered in a contracting state and operated pursuant to an agreement for the lease, charter or interchange of the aircraft or any similar arrangement by an operator who has his principal place of business, or, if he has no such place of business, his permanent resident in Myanmar, provided that an agreement has been reached between the government of the State of registry of the Aircraft and the Government of Myanmar in regard to transfer of functions and duties pursuant to Article 83 bis of the Convention. The extent of application of this part to such aircraft shall be as per the agreement between the two Governments.

(2) Not apply to aircraft registered in Myanmar and operated pursuant to an agreement for the lease, charter or interchange of the aircraft or any similar arrangement by an operator who has his principal place of business, or, if he has no such place of business, his permanent resident in a contracting State, provided that an agreement has been reached between the Government of Myanmar and the Government of that contracting state in regard to transfer of functions and duties pursuant to Article 83 bis of the Convention. The extent of non-application of this part to such aircraft shall be as per the agreement between the two Governments.

(3) Certification of aircraft and aeronautical components; Issue, validate and renewal for Certificate of Airworthiness and other certifications of aeronautical products; Continued airworthiness of aircraft and aeronautical components; Rebuilding and modifications of aircraft and aeronautical components; Maintenance of aircraft and aeronautical components; Aircraft inspection requirements; and Air operator aircraft maintenance and inspection requirements.

21.1.1.2 DEFINITIONS

For the purpose of this Part, the following definitions shall apply

1. Aeroplane. A power-driven heavier-than-air aircraft, deriving its lift in flight chiefly from aerodynamic reactions on surfaces which remain fixed under given conditions of flight.

2. Aircraft. Any machine that can derive support in the atmosphere from the reactions of the air other than the reactions of the air against the earths surface.

3. Anticipated operating conditions. Those conditions which are known from experience or which can be reasonably envisaged to occur during the operational life of the aircraft taking into account the operations for which the aircraft is made eligible, the conditions so considered being relative to the meteorological state of the atmosphere, to the configuration of terrain, to the functioning of the aircraft, to the efficiency of personnel and to all the factors affecting safety in flight. Anticipated operating conditions do not include: a) those extremes which can be effectively avoided by means of operating procedures; and

b) those extremes which occur so infrequently that to require the Standards to be met in such extremes would give a higher level of airworthiness than experience has shown to be necessary and practical.

4. Appropriate airworthiness requirements. The comprehensive and detailed airworthiness codes established, adopted or accepted by a Contracting State for the class of aircraft, engine or propeller under consideration.

5. Approved. Accepted by a Contracting State as suitable for a particular purpose. 6. Category A Helicopters. With respect to helicopters, means a multi-engine helicopter designed with

engine and system isolation features specified in Part IVB of Annex 8 and capable of operations using take-off and landing data scheduled under a critical engine failure concept which assures adequate



designated surface area and adequate performance capability for continued safe flight or safe rejected take-off.

7. Category B Helicopters. With respect to helicopters, means a single-engine or multi-engine helicopter which does not meet Category A standards. Category B helicopters have no guaranteed capability to continue safe flight in the event of an engine failure, and a forced landing is assumed.

8. Configuration (as applied to the aeroplane). A particular combination of the positions of the moveable elements, such as wing flaps and landing gear, etc., that affects the aerodynamic characteristics of the aeroplane.

9. Critical power-unit(s). The power-unit(s) failure of which gives the most adverse effect on the aircraft characteristics relative to the case under consideration.

10. Design landing mass. The maximum mass of the aircraft at which, for structural design purposes, it is assumed that it will be planned to land.

11. Design take-off mass. The maximum mass at which the aircraft, for structural design purposes, is assumed to be planned to be at the start of the take-off run.

12. Design taxiing mass. The maximum mass of the aircraft at which structural provision is made for load liable to occur during use of the aircraft on the ground prior to the start of take-off.

13. Discrete source damage. Structural damage of the aeroplane that is likely to result from: impact with a bird, uncontained fan blade failure, uncontained engine failure, uncontained high-energy rotating machinery failure or similar causes.

14. Engine. A unit used or intended to be used for aircraft propulsion. It consists of at least those components and equipment necessary for functioning and control, but excludes the propeller (if applicable).

15. Factor of safety. A design factor used to provide for the possibility of loads greater than those assumed, and for uncertainties in design and fabrication.

16. Final approach and take-off area (FATO). A defined area over which the final phase of the approach manoeuvre to hover or landing is completed and from which the take-off manoeuvre is commenced. Where the FATO is to be used by performance Class 1 helicopters, the defined area includes the rejected take-off area available.

17. Fireproof. The capability to withstand the application of heat by a flame for a period of 15 minutes. 18. Fire resistant. The capability to withstand the application of heat by a flame for a period of 5 minutes. 19. Helicopter. A heavier-than-air aircraft supported in flight chiefly by the reactions of the air on one or

more power-driven rotors on substantially vertical axes. 20. Human Factors principles. Principles which apply to aeronautical design, certification, training,

operations and maintenance and which seek safe interface between the human and other system components by proper consideration to human performance.

21. Human performance. Human capabilities and limitations which have an impact on the safety and efficiency of aeronautical operations.

22. Landing surface. That part of the surface of an aerodrome which the aerodrome authority has declared available for the normal ground or water run of aircraft landing in a particular direction.

23. Limit loads. The maximum loads assumed to occur in the anticipated operating conditions. 24. Load factor. The ratio of a specified load to the weight of the aircraft, the former being expressed in

terms of aerodynamic forces, inertia forces, or ground reactions. 25. Maintenance. The performance of tasks required to ensure the continuing airworthiness of an aircraft,

including any one or combination of overhaul, inspection, replacement, defect rectification, and the embodiment of a modification or repair.

26. Performance Class 1 helicopter. A helicopter with performance such that, in case of engine failure, it is able to land on the rejected take-off area or safely continue the flight to an appropriate landing area.



27. Performance Class 2 Helicopter. A helicopter with performance such that, in case of engine failure, it is able to safely continue the flight, except when the failure occurs prior to a defined point after take-off or after a defined point before landing, in which cases a forced landing may be required.

28. Performance Class 3 Helicopter. A helicopter with performance such that, in case of engine failure at any point in the flight profile, a forced landing must be performed.

29. Power-unit. A system of one or more engines and ancillary parts which are together necessary to provide thrust, independently of the continued operation of any other power unit(s), but not including short period thrust-producing devices.

30. Pressure-altitude. An atmospheric pressure expressed in terms of altitude which corresponds to that pressure in the Standard Atmosphere.

31. Rendering (a Certificate of Airworthiness) valid. The action taken by a Contracting State, as an alternative to issuing its own Certificate of Airworthiness, in accepting a Certificate of Airworthiness issued by any other Contracting State as the equivalent of its own Certificate of Airworthiness.

32. Repair. The restoration of an aeronautical product to an airworthy condition as defined by the appropriate airworthiness requirements.

33. Safety management system. A systematic approach to managing safety, including the necessary organizational structures, accountabilities, policies and procedures.

34. Satisfactory evidence. A set of documents or activities that a Contracting State accepts as sufficient to show compliance with an airworthiness requirement.

35. Standard atmosphere. An atmosphere defined as follows: a) the air is a perfect dry gas; b) the physical constants are:

Sea level mean molar mass: M0 = 28.964420 103 kg mol1

Sea level atmospheric pressure: P0 = 1013.250 hPa

Sea level temperature: t0 = 15C; T0 = 288.15 K

Sea level atmospheric density: 0 = 1.2250 kg m3

Temperature of the ice point: Ti = 273.15 K

Universal gas constant: R* = 8.31432 JK1mol1

c) the temperature gradients are:

Geopotential altitude (km)

From

To

Temperature gradient (Kelvin per standard

geopotential kilometre)

5.0 11.0 6.5

11.0 20.0 0.0

20.0 32.0 +1.0

32.0 47.0 +2.8

47.0 51.0 0.0

51.0 71.0 2.8

71.0 80.0 2.0



36. State of Design. The State having jurisdiction over the organization responsible for the type design. 37. State of Manufacture. The State having jurisdiction over the organization responsible for the final

assembly of the aircraft. 38. State safety programme. An integrated set of regulations and activities aimed at improving safety. 39. Take-off surface. That part of the surface of an aerodrome which the aerodrome authority has

declared available for the normal ground or water run of aircraft taking off in a particular direction. 40. Ultimate load. The limit load multiplied by the appropriate factor of safety. Aeronautical product. Any

aircraft, aircraft engine, propeller, or subassembly, appliance, material, part or component to be installed thereon.

41. Airworthiness approval tag. A tag (Model CAA Form AAT) that may be attached to a part. The tag must include the part number, serial number, and current life status of the part. Each time the part is removed from a type certificated product, a new tag must be created or the existing tag must be updated with the current life status. The Model CAA Form AAT has two distinct purposes (1) is as a certification of release to service of a part, component or assembly after maintenance, preventive maintenance, overhaul or rebuilding, and (2) the other is as shipping of a newly manufactured part.

42. Airworthiness directive. Continuing airworthiness information that applies to the following products: aircraft, aircraft engines, propellers, and appliances. An airworthiness directive is mandatory if issued by the State of Design.

43. Life-limited part. Any part for which a mandatory replacement limit is specified in the type design, the Instructions for Continued Airworthiness, or the maintenance manual.

44. Major Modification. Major Modification means an alteration not listed in the aircraft, aircraft engine, or propeller specifications (1) that might appreciably affect weight, balance, structural strength, performance, power-plant, operations, flight characteristics, or other qualities affecting airworthiness; or (2) that cannot be done by elementary operations.

45. Major repair. Major repair means a repair: (1) that if improperly done might appreciably affect weight, balance, structural strength, performance, power-plant, operations, flight characteristics, or other qualities affecting airworthiness; or (2) that is not done according to accepted practices or cannot be done by elementary operations.

46. Overhaul. The restoration of an aircraft/aeronautical product using methods, techniques, and practices acceptable to the Authority, including disassembly, cleaning, and inspection as permitted, repair as necessary, and reassembly; and tested in accordance with approved standards and technical data, or in accordance with current standards and technical data acceptable to the Authority, which have been developed and documented by the State of Design, holder of the type certificate, supplemental type certificate, or a material, part, process, or appliance approval under a Technical Standard Order (TSO).

47. Preventive maintenance. Simple or minor preservation operations and the replacement of small standard parts not involving complex assembly operations.

48. Rebuild. The restoration of an aircraft/aeronautical product by using methods, techniques, and practices acceptable to the Authority, when it has been disassembled, cleaned, inspected as permitted, repaired as necessary, reassembled, and tested to the same tolerances and limits as a new item, using either new parts or used parts that conform to new part tolerances and limits.

49. Required inspection items. Maintenance items and/or alterations that must be inspected by a qualified and authorised person other than the one performing the work, and include at least those that could result in a failure, malfunction, or defect endangering the safe operation of the aircraft, if not properly performed or if improper parts or materials are used.

50. Type Certificate. A document issued by a Contracting State to define the design of an aircraft type and to certify that this design meets the appropriate airworthiness requirements of that State.



51. Validation of a Certificate of Airworthiness. The action taken by a Contracting State, as an alternative to issuing its own Certificate of Airworthiness, in accepting a Certificate of Airworthiness issued by any other Contracting State as the equivalent of its own Certificate of Airworthiness.

52. Control System. Means a system by which the flight path, attitude, main landing gear position, or propulsive force of an aircraft is changed, including the flight engine and propeller controls, the related system controls and the associated operating mechanisms.

53. Duplicate Inspection. The independent inspection and certification of any part of an aircraft control system or component control system by two authorised persons.

21.1.1.3 ACRONYMS

The following acronyms are used in this Part _

(1) AOC Air Operator Certificate

(2) AMO Approved Maintenance Organisation

(3) BCAR British Civil Aviation Requirements

(4) DCA Department of Civil Aviation (Myanmar)

(5) Director The Director who is responsible for the Airworthiness matters in Civil Aviation

(6) MCAR Myanmar Civil Aviation Requirements

(7) MEL Minimum Equipment List

(8) PIC Pilot in command

(9) TSO Technical Standard Order

21.2 AIRCRAFT AND COMPONENT ORIGINAL CERTIFICATION

Myanmar is not state of Design or State of Manufacturer, Myanmar does not issue Type Certificate.

Myanmar does not have Aircraft Engineering Division (AED) in Department of Civil Aviation; Myanmar will

not validate Type Certificate issued by other states. Myanmar will automatically accepte type certificate

issued by United State of America and EASA without investigation.

Apart from USA and EASA, State of Design has to consult with Myanmar DCA and must have a bilateral

agreement regarding acceptance of Type Certificate.


(a) This sub Part describes the procedures and requirements for original certification of aircraft and related aeronautical products.

(b) The DCA will hold this Part reserved until such time as he has received an application for Type Certificates, Production Certificates or other related approvals.

(c) Any applicant for a production certificate for any aircraft or aeronautical product thereof for manufacture in Myanmar shall comply with the type certificate as required by the State of Design for approval.

(d) At such time as the application for production is presented the DCA will make available suitable regulations or provisions for the issuance of an airworthiness certificate, or airworthiness document as appropriate for the product concerned.

21.3 SUPPLEMENTAL TYPE CERTIFICATES


This Sub-Part prescribes procedural requirements for the issue of supplemental type certificates (STC).



21.3.1.2 ISSUANCE OF A SUPPLEMENTAL TYPE CERTIFICATE

Any person who proposes to alter a product by introducing a major change in type design, not great enough to require a new application for a type certificate, shall apply for a Supplemental Type Certificate to the regulatory agency of the State of Design that approved the type certificate for that product, or to the State of Registry of the aircraft provided that the State of Registry has the technical expertise to evaluate the proposed change in accordance with the type design. The applicant shall apply in accordance with the procedures prescribed by that State. Upon receiving a request for a supplemental type certificate for an aircraft registered in any STATE shall forward the request to the State of Design.

21.4 AIRWORTHINESS CERTIFICATES


This Sub-Part prescribes procedures required for the Issue, Validate and Renewal of Airworthiness Certificates.

21.4.1.2 ELIGIBILITY

(a) Any aircraft shall not fly within Myanmar unless there is in force in respect thereof a certificate of airworthiness duly issued or rendered valid under this part and any conditions subject to which the certificate was issued or rendered valid are complied with.

(b) Any registered owner of a Myanmar registered aircraft, or agent of the owner, may apply for an airworthiness certificate for that aircraft.

(c) Each applicant for an airworthiness certificate shall apply in a form of CA 62 or CA 63 and manner acceptable to the DCA.

21.4.1.3 CLASSIFICATIONS OF AIRWORTHINESS CERTIFICATES

(a) Airworthiness Certificates will be issued for aircraft in the specific category and model designated by the State of Design in the type certificate.

(b) The DCA may issue a Special Airworthiness Certificate in the form of a restricted certificate or special flight permit.

21.4.1.4 AMENDMENT OF AIRWORTHINESS CERTIFICATE

The DCA may amend or modify an Airworthiness Certificate _

(1) Upon application from an operator.

(2) On its own initiative.

21.4.1.5 TRANSFER OR SURRENDER OF AIRWORTHINESS CERTIFICATE

(a) An owner shall transfer an Airworthiness Certificate _

(1) To the lessee upon lease of an aircraft within or outside Myanmar

(2) To the buyer upon sale of the aircraft within Myanmar.

(b) Myanmar owner of an aircraft shall surrender the Airworthiness Certificate for the aircraft to the issuing Authority upon sale of that aircraft outside Myanmar.

21.4.1.6 EFFECTIVE DATES OF AIRWORTHINESS CERTIFICATES

(a) Myanmar Airworthiness Certificates are effective for one year unless sooner surrendered, suspended or revoked, or a special termination date is otherwise established by the DCA.

(b) A special flight permit is valid for the period of time specified in the permit.



(c) When an aircraft imported for registration in Myanmar has a Certificate of Airworthiness issued by another Contracting State, Myanmar may, as an alternative to issuance of its own Certificate of Airworthiness, establish validity by suitable authorisation to be carried with the former Certificate of Airworthiness accepting it as the equivalent of a Certificate of Airworthiness issued by Myanmar. The validity of the authorisation shall not extend beyond the period of validity of the Certificate of Airworthiness or one year, whichever is less.

(d) The continuing airworthiness of the aircraft shall be determined by a periodical inspection at appropriate intervals having regard to lapse of time and type of service.

(e) Failure to maintain an aircraft in an airworthy condition as defined by the appropriate airworthiness requirements of the State of Registry shall render the aircraft ineligible for operations until the aircraft is restored to an airworthy condition.

21.4.1.7 AIRCRAFT IDENTIFICATION

Each applicant for an airworthiness certificate shall show that the aircraft is properly registered and marked, including identification plates.

21.4.1.8 ISSUE, VALIDATE AND RENEWAL OF AIRWORTHINESS CERTIFICATES

(a) The DCA may issue an Airworthiness certificate if

(1) The applicant presents evidence to the DCA to satisfy that the Aircraft manufactured/ imported meet the approved Airworthiness Standards in respect of design, method of construction, equipment and performance etc. in this regard the Design Standards specified in JAR 23 and JAR 25 of Airworthiness Authorities (JAA/EASA) of Europe and FAR 23 and FAR 25 of Federal Aviation Administration (FAA) of USA, is generally acceptable for Light and Transport Category aircraft. For Helicopters, Design Standards followed by FAA as specified FAR 27 & 29 are acceptable for Light and Transport Category helicopters, respectively.

(2) The aircraft has been inspected in accordance with the performance rules of this regulation for inspections and found airworthy by persons authorised by the DCA to make such determinations within the last 30 calendar days; and

(3) The DCA finds after an inspection that the aircraft conforms to type design and is in a condition for safe operation.

(b) The DCA may validate an airworthiness certificate issued by another Contracting State upon registration of the aircraft in Myanmar for the period specified in that certificate but in no case for a period longer than 12 months.

(c) The DCA may renew an airworthiness certificate if _

The applicant presents evidence to the DCA that the aircraft conforms to aircraft, or such of its equipment as is necessary for the airworthiness of the aircraft, is overhauled, repaired or modified, or if any part of the aircraft or of such equipment is removed or is replaced, either generally until the satisfactory completion of any inspection made for the purpose of ascertaining whether the aircraft remains airworthy or maintenance of the aircraft or of any equipment for the purpose of ensuring that the aircraft remains airworthy.

21.4.1.9 COMMERCIAL AIR TRANSPORT

The DCA will consider an airworthiness certificate valid for commercial air transport only when accompanied by an evaluation form issued by the state of design which identifies the specific types of commercial air transport authorised.



21.4.1.10 AIRWORTHINESS DIRECTIVES

(a) Upon registration of an aircraft in Myanmar, the DCA will notify the State of Design of the aircraft of the registration in Myanmar, and request that the DCA receives any and all airworthiness directives (ADs) addressing that aircraft, airframe, aircraft engine, propeller, appliance, or component part.

(b) Unless otherwise directed by DCA, owners or operators of aircraft registered in Myanmar must comply with all ADs or similar mandatory instructions issued by the Airworthiness Authority of the State of Design.

(c) The DCA may identify manufacturers service bulletins and other sources of data, or develop and prescribe inspections, procedures and limitations, for mandatory compliance pertaining to affected aircraft in Myanmar.

(d) No person may operate any Myanmar registered civil aircraft to which this subsection applies, except in accordance with the applicable directives.

21.4.1.11 ISSUE OF SPECIAL AIRWORTHINESS CERTIFICATES

(a) The DCA may issue a Special Airworthiness Certificate to the aircraft that does not qualify for a Certificate of Airworthiness.

(b) Aircraft holding Special Airworthiness Certificates shall be subject to operating limitations. The DCA shall issue specific operating limitations for each Special Airworthiness Certificate.

(c) The DCA may issue Special Flight Permits to an aircraft that is capable of safe flight, but unable to meet applicable airworthiness requirements, for the purpose of

(1) Flying to a base where repairs, modifications, maintenance, or inspections are to be performed, or to a point of storage;

(2) Testing after repairs, modifications, or maintenance have been performed;

(3) Delivering or exporting the aircraft;

(4) Evacuating aircraft from areas of impending danger; and

(5) Operating at weight in excess of the aircrafts maximum Certified Take-off Weight for flight beyond normal range over water or land areas where adequate landing facilities or appropriate fuel is not available. The excess weight is limited to additional fuel, fuel-carrying facilities, and navigation equipment necessary for the flight.

(d) The DCA may issue a special flight permit, with continuing authorisation that may be issued by the AOC holder to an aircraft that may not meet applicable airworthiness requirements, but is capable of safe flight, for the purpose of flying aircraft to a base where maintenance or alterations are to be performed. The permit issued under this paragraph is an authorisation, including conditions and limitations for flight, which is set forth in the AOC Holders manuals and specific operating provisions. This permit under this paragraph may be issued to an AOC Holder certificated under MCAR Part 1.

(e) In the case of Special Flight Permits, the DCA shall require a properly executed maintenance endorsement in the aircraft permanent record by a person or organisation, authorised in accordance with this Part, stating that the subject aircraft has been inspected and found to be safe for the intended flight.

(f) The operator shall obtain all required over flight authorisations from countries to be over flown on flights outside Myanmar.



21.5 CONTINUED AIRWORTHINESS OF AIRCRAFT AND COMPONENTS


This sub-part prescribes requirements governing the continued airworthiness of civil aircraft registered in Myanmar whether operating inside or outside of Myanmar. The owner of aircraft must follow the relevant requirements and procedures prescribed in the DCA Airworthiness Notices for his/her aircraft complied.

21.5.1.2 RESPONSIBILITY

The owner of an aircraft or, in the case of a leased aircraft, the lessee, shall be responsible for maintaining the aircraft in an airworthy condition by ensuring that

(1) All maintenance, overhaul, modifications and repairs which affect airworthiness are performed as prescribed by the State of Registry;

(2) Maintenance personnel make appropriate entries in the aircraft maintenance records certifying that the aircraft is airworthy;

(3) A Certificate of Release to Service is completed to the effect that the maintenance work performed has been completed satisfactorily and in accordance with the prescribed methods; and

(4) In the event there are open discrepancies, the maintenance release includes a list of the uncorrected maintenance items and these items are made a part of the aircraft permanent record.

21.5.1.3 GENERAL

(a) No person may perform maintenance or modifications on an aircraft other than as prescribed in this part.

(b) No person may operate an aircraft for which a manufacturers maintenance manual or instructions for continued airworthiness has been issued that contains an airworthiness limitation section unless the mandatory replacement times, inspection intervals, and related procedures specified in that section or alternative inspection intervals and related procedures set forth in the specific operating provisions approved under MCAR part 1, or in accordance with the inspection program approved have been complied with.

(c) No person may operate an aeronautical product to which an Airworthiness Directive applies, issued either by the State of Design or State of Manufacture and adopted for Myanmar Registered aircraft by the DCA, or by the State of Registry for aircraft operated within Myanmar, except in accordance with the requirements of that Airworthiness Directive.

(d) When the DCA determines that an airframe or aeronautical product has exhibited an unsafe condition and that condition is likely to exist or to develop in other products of the same type design, the DCA may issue a related Airworthiness inspections, conditions and limitations, if any, under which those products may continue to be operated.

21.5.1.4 REQUIREMENT FOR CERTIFICATE OF RELEASE TO SERVICE

(1) Any aircraft registered in Myanmar shall not fly unless there is in force a certificate of release to service issued under this part, if the aircraft or any part of the aircraft or such of its equipment as is necessary for the airworthiness of the aircraft has been overhauled, repaired, replaced, modified, maintained, or has been inspected.

(2) A certificate of release to service shall not be required to be in force in respect of an aircraft to which the maximum total weight authorized does not exceed 2730 kg, if it is an aircraft in respect of which a certificate of airworthiness in the special category is in force, unless the DCA gives a direction to the contrary in a particular case.



(3) A certificate of release to service issued under this part shall _ (a) Certify that the aircraft or any part thereof or its equipment has been overhauled, repaired,

replaced, modified or maintained, as the case may be, in a manner and with material of a type approved by FAA, EASA or the DCA either generally or in relation to a class of aircraft or the particular aircraft and shall identify the overhaul, repair, replacement, modification or maintenance to which the certificate relates and shall include particulars of the work done; or

(b) Certify in relation to any inspection required by the DCA that the aircraft or the part thereof or its equipment, has been inspected in accordance with the requirements of the DCA and that any consequential repair, replacement or modification has been carried out.

(4) A certificate of release to service issued under this part may be issued by _ (a) a person approved by the DCA as being competent to issue such certification, (b) a person whom the DCA has authorised to issue the certificate in a particular case, and in

accordance with that authority; (c) a person authorized in accordance with MCAR Part-145, and in accordance with that approval;

or (d) the holder of an aircraft maintenance licence granted by the DCA, in accordance with the

privileges endorsed on the licence. (5) Sample of certificate of release to service and certificate of release to service-schedule maintenance inspection (CRS-SMI) shall be prescribed in MCAR part-M.

21.5.1.5 REQUIREMENTS FOR CERTIFICATE OF MAINTENANCE REVIEW

(1) Any public transport or an aerial work aircraft registered in Myanmar shall not fly unless there is in force a certificate issued in respect of the aircraft in accordance with the provisions of this part and the certificate, certifies the date on which the maintenance review was carried out and the date when the next review is due.

(2) In approving a maintenance program or a maintenance schedule, the DCA may direct that certificates of maintenance review relating to that program or schedule, or to any part thereof specified in its direction, may be issued only by the holder of such a licence as is so specified.

(3) A certificate of maintenance review may be issued in accordance with BCAR Chapter A 6-2.

(4) Any person shall not issue a certificate of maintenance review unless_ (a) Maintenance has been carried out on the aircraft in accordance with the maintenance schedule

approved for that aircraft; (b) inspections and modifications required by the DCA as provided have been completed as

certified in the relevant certificate of release to service issued under this part or under MCAR Part-145;

(c) Defects entered in the technical log or approved record of the aircraft has been rectified or the rectification thereof has been deferred in accordance with procedures approved by the DCA;

(d) Certificates of release to service have been issued: (i) Under this part; or (ii) In respect of an aircraft required to be maintained in accordance with MCAR Part-145;

(5) A certificate of maintenance review shall be issued in duplicate, one copy of the most recently issued certificate of maintenance review shall be carried in the aircraft and the other shall be kept by the operator elsewhere than in the aircraft for a period of at least 2 years after it has been issued.

(6) Sample of certificate of maintenance review shall be prescribed in MCAR part-M.

21.5.1.6 AIRCRAFT, ENGINE AND PROPELLER LOG BOOKS

(1) The following log books shall be kept in respect of aircraft registered in Myanmar (a) an aircraft log book;



(b) a separate log book in respect of each engine fitted in the aircraft; and (c) a separate log book in respect of each variable pitch propeller fitted to the aircraft.

(2) Each entry in the log book: (a) such an entry shall be made as soon as practicable after the occurrence to which it relates, but in no event more than 7 days after the expiration of the certificate of maintenance review (if any) in force in respect of the aircraft at the time of the occurrence; (b) such an entry shall be made upon each occasion that any maintenance, overhaul, repair, replacement, modification or inspection is undertaken on the aircraft, engine or propeller.

(3) Every log book shall be preserved by the operator of the aircraft for a period of at least 2 years after the aircraft, the engine or the variable pitch propeller, as the case may be, has been destroyed or has been permanently withdrawn from use.

21.5.1.7 TECHNICAL LOG

(1) Any public transport and aerial work aircraft registered in Myanmar shall have_ (a) a technical log to be kept in respect of every aircraft to which this part applies. (b) an approved record to be kept instead of a technical log In the case of an aircraft of which the

maximum total weight authorised is 2730 kg or less and which is not operated by the holder of an air operators certificate granted by the DCA.

(2) At the end of every flight by an aircraft the commander shall enter in the technical log or the approved record as the case may be _ (a) The times when the aircraft took off and landed; (b) Particulars of any defect which is known to him and which affects the airworthiness or safe

operation of the aircraft, or if no such defect is known to him, an entry to that effect; and (c) such other particulars in respect of the airworthiness or operation of the aircraft as the DCA may

require; and he shall sign and date the entries. Note: In the case of two or more consecutive flights each of which begins and ends

(iii) within the same period of 24 hours; at the same aerodrome, (ii) except where each such flight is for the purpose of dropping or projecting any material for

agricultural, public health or similar purposes; and (iii) with the same person as commander of the aircraft, the commander may, except where he/she

becomes aware of a defect during an earlier flight, make the entries at the end of the last of such consecutive flights.

(3) Upon the rectification of any defect which has been entered in a technical log or approved record, a person issuing a certificate of release to service issued under this Part or under MCAR Part-145 in respect of that defect shall enter the certificate in the technical log or approved record in such a position as to be readily identifiable with the defect to which it relates.

(4) the technical log or approved record shall be carried in the aircraft and copies of the entries required by this article shall be kept on the ground.

(5) In the case of an aeroplane of which the maximum total weight authorized is 2730 kg or less, or a helicopter, if it is not reasonably practicable for the copy of the technical log or approved record to be kept on the ground it may be carried in the aeroplane or helicopter, as the case may be, in a container approved by the DCA for that purpose.

(6) a technical log or approved record required by this article shall be preserved by the operator of the aircraft to which it relates for a period of at least 2 years after the aircraft has been destroyed or has been permanently withdrawn from use, or for such shorter period as the DCA may permit in a particular case.



21.5.1.8 EQUIPMENT OF AIRCRAFT

(a) (1) the DCA may direct that an aircraft registered in Myanmar shall carry such additional or special equipment or supplies as it may specify for the purpose of facilitating the navigation of the aircraft, the carrying out of search and rescue operations, or the survival of the persons carried in the aircraft. (2) The equipment carried in compliance with this part shall be so installed or stowed and kept stowed, and so maintained and adjusted, as to be readily accessible and capable of being used by the person for whose use it is intended. (3) The position of equipment provided for emergency use shall be indicated by clear markings in or on the aircraft. (4) In every public transport aircraft registered in Myanmar shall be provided individually for each

passenger or, if the DCA so permits in writing, exhibited in a prominent position in every passenger compartment, a notice which complies with (a) is relevant to the aircraft in question; (b) contains pictorial instructions on the brace position to be adopted in the event of an emergency

landing; (c) contains pictorial instructions on the method of use of the safety belts and safety harnesses as

appropriate; (d) contains pictorial information as to where emergency exits are to be found and instructions as

to how they are to be used; and (e) contains pictorial information as to where the lifejackets, escape slides, life-rafts and oxygen

masks, if required to be provided by paragraph(2), are to be found and instructions as to how they are to be used.

(5) All equipment installed or carried in an aircraft, whether or not in compliance with this part shall be so installed or stowed and so maintained and adjusted as not to be a source of danger in itself or to impair the airworthiness of the aircraft or the proper functioning of any equipment or services necessary for the safety of the aircraft.

(b) Radio equipment of aircraft (1) An aircraft shall not fly unless it is so equipped with radio communication and radio navigation

equipment as to comply with the law of the country in which the aircraft is registered or the State of the operator and to enable communications to be made and the aircraft to be navigated, in accordance with the provisions of this part and any regulations made there under.

(2) In any particular case the DCA may direct that an aircraft registered in Myanmar shall carry such additional or special radio communication or radio navigation equipment as it may specify for the purpose of facilitating the navigation of the aircraft, the carrying out of search and rescue operations or the survival of the persons carried in the aircraft.

(3) Subject to such exceptions as may be prescribed the radio communication and radio navigation equipment provided in compliance with this part in an aircraft registered in Myanmar shall always be maintained in serviceable condition.

(c) Minimum equipment requirements The DCA may grant in respect of any aircraft or class of aircraft registered in Myanmar a permission permitting such aircraft to commence a flight in specified circumstances notwithstanding that any specified item of equipment required by or under this part to be carried in the circumstances of the intended flight is not carried or is not in a fit condition for use.

21.5.1.9 THE QUALIFICATION REQUIREMENTS FOR NON DESTRUCTIVE TESTING (NDT) PERSONNEL

(1) The qualification of Non-Destructive Testing (NDT) personnel shall be complied with the design or production under BCAR and/or EASA requirements, which shall be in accordance with the updated



European Standards EN473 1 or EN4179 2 or equivalent Standards and the Approved Organisations written practice/ procedures for the authorisation of NDT personnel.

(2) The term NDT is used throughout this part to include, but not be limited to, Liquid Penetrant, Magnetic Particle, Eddy Current, Ultrasonic, Radiographic and other recognized methods as identified in the above reference standard and shall be applicable to all NDT methods used by Approved Organization. Other methods and their associated procedures will be subject to acceptance by the DCA.

1 EN473 General Principle for Qualification and Certification of NDT Personnel, 2 EN4179 Qualification and Approval of personnel for non-destructive testing,

21.5.1.10 REPORTING OF FAILURES, MALFUNCTIONS, AND DEFECTS

(a) Owners or operators of aircraft shall report to the DCA any failures, malfunctions, or defects that result in at least the following

(1) Fires during flight and whether the related fire-warning system properly operated;

(2) Fires during flight not protected by a related fire-warning system;

(3) False fire warning during flight;

(4) An engine exhaust system that causes damage during flight to the engine, adjacent structure, equipment, or components;

(5) An aircraft component that causes accumulation or circulation of smoke, vapour, or toxic or noxious fumes in the crew compartment or passenger cabin during flight;

(6) Engine shutdown during flight because of flameout;

(7) Engine shutdown during flight when external damage to the engine or aircraft structure occurs;

(8) Engine shutdown during flight due to foreign object ingestion or icing;

(9) Shutdown during flight of more than one engine;

(10) A propeller feathering system or ability of the system to control over speed during flight;

(11) A fuel or fuel-dumping system that affects fuel flow or causes hazardous leakage during flight;

(12) An unintended landing gear extension or retraction, or opening or closing of landing gear doors during flight;

(13) Brake system components that result in loss of brake actuating force when the aircraft is in motion on the ground;

(14) Aircraft structure that requires major repair;

(15) Cracks, permanent deformation, or corrosion of aircraft structure, if more than the maximum acceptable to the manufacturer or the DCA;

(16) Aircraft components or systems malfunctions that result in taking emergency actions during flight (except action to shut down an engine);

(17) Each interruption to a flight, unscheduled change of aircraft en route, or unscheduled stop or diversion from a route, caused by known or suspected technical difficulties or malfunctions;

(18) Any abnormal vibration or buffeting caused by a structural or system malfunction, defect, or failure;

(19) A failure or malfunction of more than one attitude, airspeed, or altitude instrument during a given operation of the aircraft.

(20) The number of engines removed prematurely because of malfunction, failure or defect, listed by make and model and the aircraft type in which it was installed; or

(21) The number of propeller featherings in flight, listed by type of propeller and engine and aircraft on which it was installed.

(22) Defect of the aircraft or part(s) related to any bird-strike.



(b) Each report shall

(1) Be made within 3 days after determining that the failure, malfunction, or defect required to be reported has occurred; and

(2) Include as much of the following information as is available

a) Aircraft serial number, type, series and registration marks.

b) The name of operator of the aircraft.

c) the date of the reportable occurrence.

d) a description of the reportable occurrence, including its effects and any other relevant information.

e) in the case of a reportable occurrence which occurs during flight

(i) the Co-ordinated Universal Time of the occurrence; (ii) the last point of departure and the next point of intended landing of the aircraft at that

time; and (iii) the geographical position of the aircraft at that time;

f) When the failure, malfunction, or defect is associated with an article approved under a TSO authorisation, the article serial number and model designation.

g) When the failure, malfunction or defect is associated with an engine or propeller, the engine or propeller serial number.

h) Product model.

i) Identification of the part, component, or system involved, including the part number; and natures of the failure, malfunction, or defect.

j) the signature and name in block capitals of the person making the report in which he acts for that employer and the address or telephone number at which communications should be made to him.

(c) Myanmar if the State of Registry of the aircraft, will submit all such reports upon receipt to the State of Design.

(d) Myanmar, if not the State of Registry of the aircraft, will submit all such reports upon receipt to the State of Registry.

21.6 AIRCRAFT MAINTENANCE AND INSPECTION


This part prescribes rules governing the maintenance and inspection of any aircraft having a Myanmar Airworthiness Certificate or associated aeronautical products.

21.6.1.2 PERSONS AUTHORISED TO PERFORM MAINTENANCE, PREVENTIVE MAINTENANCE AND MODIFICATIONS

(a) The persons authorised to perform maintenance subject to this Subpart include

(1) A licensed pilot approved by the DCA to do specified maintenance;

(2) A person performing maintenance under the supervision of an aircraft maintenance engineer;

(3) A licensed aircraft maintenance engineer;

(4) A holder of a Inspection Authorisation;

(5) An aircraft repair specialist

(6) A holder of a certificate of maintenance approval;

(7) An AOC holder, approved to perform maintenance under an equivalent system; and

(8) An AMO.



(b) This Subpart outlines the privileges and limitations of these entities with respect to the extent and type of work they may perform regarding

(1) Maintenance,

(2) Modification,

(3) Inspection, and

(4) Approvals for return to service.

21.6.1.3 PERSONS AUTHORISED TO PERFORM MAINTENANCE

No person may perform any task defined as maintenance on an aircraft or aeronautical products, except as provided in the following

(1) A pilot licensed by the DCA may perform that maintenance as may be specifically approved by the DCA on any aircraft owned or operated by that pilot so long as the aircraft is not listed for use by an AOC holder.

(2) A person working under the supervision of a aircraft maintenance engineer, may perform the maintenance, and modifications that the supervisory aircraft maintenance engineer is authorised to perform If the supervisor personally observes the work being done to the extent necessary to ensure that it is being done properly, and If the supervisor is readily available, in person, for consultation.

(3) A person working under supervision of an aircraft maintenance engineer may not perform any inspection required or any inspection performed after a major repair or modification.

(4) A licensed aircraft maintenance engineer may perform or supervise the maintenance or modification of an aircraft or aeronautical product for which he or she is rated by the limitation.

(5) A holder of an Inspection Authorisation may perform or supervise the maintenance or modification of an aircraft or aeronautical product rated by the limitation.

(6) An aircraft repair specialist may perform or supervise the maintenance or modification of an aircraft or aeronautical product for which he or she is rated by the limitation.

(7) A holder of a certificate of maintenance approval may perform the maintenance or modification of an aircraft or aeronautical product as specified in its Authorization.

(8) An AMO may perform aircraft maintenance within the limits specified by the DCA.

(9) The AOC holder may perform aircraft maintenance as specified by the DCA.

(10) A manufacturer holding an AMO certificate may

(i) Rebuild or alter any aeronautical product manufactured by that manufacturer under a type or production certificate;

(ii) Rebuild or alter any aeronautical product manufactured by that manufacturer under a TSO Authorisation, a Parts Manufacturer Approval by the State of Design, or Product and Process Specification issued by the State of Design; and

(iii) Perform any inspection required on aircraft it manufacturers, while currently operating under a production certificate or under currently approved production inspection system for such aircraft.

21.6.1.4 AUTHORISED PERSONNEL TO APPROVE FOR RETURN TO SERVICE

No person or entity, other than the DCA, may approve an aircraft, airframe, aircraft engine, propeller, appliance, or component part for return to service after it has undergone maintenance, rebuilding, or modification, except as provided in the following:

(1) A pilot licensed by the DCA may return his or her aircraft to service after performing limited maintenance when specifically authorised by the DCA to do so.



(2) A licensed aircraft maintenance engineer may approve aircraft and aeronautical products for return to service after he or she has performed, supervised, or inspected its maintenance subject to the limitation.

(3) A holder of a Inspection Authorisation may approve any aircraft and aeronautical products for return to service subject to the limitation.

(4) A holder of a certificate of maintenance approval may approve any aircraft for return to service as specified in the certificate and subject to the limitation.

(5) An AMO may approve aircraft and aeronautical products for return to service as provided in the specifications approved by the DCA.

(6) An AOC holder may approve aircraft and aeronautical products for return to service as specified by the DCA.

21.6.1.5 PERSONS AUTHORISED TO PERFORM INSPECTIONS

No person, other than the Director, may perform the inspections required by and an aeronautical product prior to or after it has undergone maintenance, rebuilding, or modification, except as provided in the following:

(1) An aircraft maintenance engineer may conduct the required inspections of aircraft and aeronautical products for which he or she is rated and current.

(2) An AMO may perform the required inspections of aircraft and aeronautical products as provided in the specifications approved by the Director.

(3) An AOC holder may perform the required inspections of aircraft and aeronautical products in accordance with specifications issued by the Director.

21.6.1.6 PERSONS AUTHORISED TO PERFORM DUPLICATE INSPECTION OF CONTROLS

A person shall not certify an aircraft or component for release to service after the initial assembly, subsequent disturbance, or adjustment of any part of an aircraft control system or component control system unless a duplicate inspection of the control system has been performed that includes

(1) an inspection after maintenance by a person authorized to certify the release to service of the control system; and

(2) a second inspection by another person who has adequate training, knowledge and experience to carry out the second inspection; and is nominated by the person specified in subparagraph (1).

21.6.1.7 PERFORMANCE RULES: MAINTENANCE

(a) Each person performing maintenance, or modification on an aeronautical product shall use the methods, techniques, and practices prescribed in

(1) The current manufacturers maintenance manual or instructions for Continued Airworthiness prepared by its manufacturer; and

(2) Additional methods, techniques and practices required by the DCA; or methods, techniques and practices designated by the DCA where the manufacturers documents were not available.

(b) Each person shall use the tools, equipment, and test apparatus necessary to assure completion of the work in accordance with accepted industry practices. If the manufacturer involved recommends special equipment or test apparatus, the person performing maintenance shall use that equipment or apparatus or its equivalent acceptable to the DCA.

(c) Each person performing maintenance, or modification on an aeronautical product shall do that work in such a manner, and use materials of such a quality, that the condition of the aeronautical product



worked on will be at least equal to its original or properly altered condition with regard to aerodynamic function, structural strength, resistance to vibration and deterioration, and other qualities affecting airworthiness.

(d) The methods, techniques, and practices contained in an AOC holders maintenance control manual and continuous maintenance program, as approved by the DCA, will constitute an acceptable means of compliance with the requirements of this subsection.

21.6.1.8 PERFORMANCE RULES: INSPECTIONS

(a) General. Each person performing an inspection required by the DCA shall

(1) Perform the inspection so as to determine whether the aircraft, or portion(s) thereof under inspection, meets all applicable airworthiness requirements; and

(2) If there is an inspection program required or accepted for the specific aircraft being inspected perform the inspection in accordance with the instructions and procedures set forth in the inspection program.

(b) Rotorcraft. Each person performing an inspection required on a rotorcraft shall inspect the following systems in accordance with the maintenance manual or Instructions for Continued Airworthiness of the manufacturer concerned

(1) The drive shafts or similar systems,

(2) The main rotor transmission gear box for obvious defects,

(3) The main rotor and centre section (or the equivalent area), and

(4) The auxiliary rotor on helicopters.

(c) Annual inspections.

(1) Each person performing an annual inspection shall use a checklist while performing the inspection. The checklist may be of the persons own design, one provided by the manufacturer of the equipment being inspected, or one obtained from another source. This checklist shall include the scope and detail of the items prescribed by the DCA.

(2) Each person approving a reciprocating-engine-powered aircraft for return to service after an annual inspection shall, before that approval, run the aircraft engine or engines to determine satisfactory performance in accordance with the current manufacturers recommendations of

Power output (static and idle rpm);

Magnetos;

Fuel;

Oil pressure; Cylinder and Oil temperature;

(3) Each person approving a turbine-engine-powered aircraft for return to service after an annual or inspection shall, before that approval, run the aircraft engine or engines to determine satisfactory performance in accordance with the current manufacturers recommendations.

21.6.1.9 PERFORMANCE RULES: AIRWORTHINESS LIMITATIONS

Each person performing an inspection or other maintenance specified in an airworthiness limitations section of a current manufacturers maintenance manual, or Instructions for Continued Airworthiness, shall perform the inspection or other maintenance in accordance with that section, or in accordance with specifications approved by the DCA.



21.7 MAINTENANCE RECORDS AND ENTRIES

21.7.1.1 CONTENT, FORM, AND DISPOSITION OF MAINTENANCE, REBUILDING, AND MODIFICATION RECORDS

(a) Each person who maintains, performs rebuilds, or modifies an aircraft or aeronautical product shall, when the work is performed satisfactorily, make an entry in the maintenance record of that equipment as follows

(1) A description (or reference to data acceptable to the DCA) of work performed;

(2) Completion date of the work performed;

(3) Name, signature, certificate number, and kind of license held by the person approving the work.

(b) The person performing the work shall enter records of major repairs and major modifications, and dispose of that form in the manner prescribed by the DCA.

21.7.1.2 RECORDS OF OVERHAUL AND REBUILDING

(a) No person may describe in any required maintenance entry or form, an aeronautical product as being overhauled unless

(1) It has been disassembled, cleaned, inspected as permitted, repaired as necessary, and reassembled using methods, techniques, and practices acceptable to the DCA; and

(2) It has been tested in accordance with approved standards and technical data, or in accordance with current standards and technical data acceptable to the DCA, which have been developed and documented by the holder of the type certificate, supplemental type certificate, or a material, part, process, or appliance manufacturing approval.

(b) No person may describe in any required maintenance entry or form an aircraft or other aeronautical product as being rebuilt unless it has been disassembled, cleaned, inspected as permitted, repaired as necessary, reassembled, and tested to the same tolerances and limits as a new item, using either new parts or used parts that conform to new part tolerances and limits.

21.7.1.3 APPROVAL FOR RETURN TO SERVICE AFTER MAINTENANCE, REBUILDING, OR MODIFICATION

No person may approve for return to service any aeronautical product that has undergone maintenance, rebuilding, or modification unless

(1) The appropriate maintenance record entry has been made;

(2) The repair or modification form authorised by or furnished by the DCA has been executed in a manner prescribed by the DCA;

(3) If a repair or modification results in any change in the aircraft operating limitations or flight data contained in the approved aircraft flight manual, those operating limitations or flight data are appropriately revised and set forth as prescribed.

21.7.1.4 CONTENT, FORM, AND DISPOSITION OF RECORDS FOR INSPECTIONS

(a) Maintenance record entries. The person approving or disapproving the return to service of an aeronautical product after any inspection performed in accordance with the operation of aircraft shall make an entry in the maintenance record of that equipment containing the following information

(1) Type of inspection and a brief description of the extent of the inspection;

(2) Date of the inspection and aircraft total time in service;

(3) Signature, the license number, and kind of license held by the person approving or disapproving for return to service the aeronautical product;

(4) If the aircraft is found to be airworthy and approved for return to service, the following or a similarly worded statement I certify that this aircraft has been inspected in accordance with the Myanmar



Aircraft Rules and Myanmar Civil Aviation Requirements and (insert type) inspection schedule and was determined to be in an airworthy condition ;

(5) If the aircraft is not approved for return to service because of needed maintenance, non-compliance with the applicable specifications, airworthiness directives, or other approved data, the following or a similarly worded statement I certify that this aircraft has been inspected in accordance with the Myanmar Aircraft Rules and Myanmar Civil Aviation Requirements and (insert type) inspection schedule and a list of discrepancies and un-airworthy items (date) has been provided for the aircraft owner or operator ; and

(6) If an inspection is conducted under an inspection program, the person performing the inspection shall make an entry identifying the inspection program accomplished, and containing a statement that the inspection was performed in accordance with the inspections and procedures for that particular program.

(b) Listing of discrepancies. The person performing any inspection required, who finds that the aircraft is not airworthy or does not meet the applicable type certificate data sheet, airworthiness directives or other approved data upon which its airworthiness depends, shall give the owner/operator a signed and dated list of those discrepancies.

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MCAR 21 (2nd Edition)

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