Appendix 2
3. ADDITIONAL REQUIREMENTS.
3.1 This subject identifies those design requirements additional to the FAR certification basis which must be satisfied for a particular aircraft type to be eligible for Brunei certification.
3.2 Additional Requirements for Brunei certification are not specified for fixed wing aircraft:
(a) below a maximum authorized weight of 2730 kg (6000 1bs).
(b) below a maximum authorized weight of 5700 kg (12500 lbs) when certification will not be applied for in the Transport or Aerial Work Categories.
NOTE: Brunei air navigation legislation requires the carriage of equipment on scales related to the purpose for which the aircraft is being flown. The aircraft commander is responsible for determining that an aircraft is properly equipped for any proposed flight.
3.3 For all aircraft other than those defined in paragraph 3.2 the DCA may prescribe Additional Requirements. Details for any individual aircraft type will be supplied on written application; a limited type evaluation by the DCA may be required when no previous example has been certificated in Brunei Darussalam. Equipment required to be carried on flights for the purpose oi pubiic transport, to satisfy Brunei air navigation legislation, will also be specified.
4. SPECIAL REQUIREMENTS.
4.1 This subject identifies those special administrative requirements which must be satisfied for particular products to be eligible for Brunei registered aircraft.
Applicability Code:
+ Required only with first of type and model exported to Brunei Darussalam.
* Required only for aircraft with a maximum authorized weight greater than 5700 kg (12500 lbs).
4.2 All Aircraft.
* (a) Statement of build standard. This statement must include the aircraft specification, changes in design to satisfy Brunei Additional Requirements and a list of Service Bulletins incorporated during manufacture. The list of Service Bulletins incorporated must identiiy:
Appendix 2
(i) Production versions of the Service Bulletins.
(ii) Service Bulletins.
(iii) Alert Service Bulletins.
(b) Copy of the production flight test report or a statement that no flight test has been completed.
(c) Modification standard. This must include:
(i) Customer options and equipment incorporated including items of equipment not necessarily installed by the manufacturer of the aircraft.
(ii) Service Bulletins compliance.
(d) Export Certificate of Airworthiness (see paragraph 4.4 of this document).
+ (e) A copy of the aircraft Type Certificate Data Sheet.
(f) Details of any alterations which may have been embodied under the Supplemental Type Certificate (STC) procedure.
NOTE: Any STC which has been embodied but not previously investigated by the DCA will be subject to evaluation before a Brunei Certificate of Airworthiness is issued.
(g) A list of the defects, if any, at the time of issue of the Export Certificate of Airworthiness which will require rectification by the Brunei operator.
(h) The FAA Approved Flight Manual or Pilot's Operating Handbook for the individual aircraft concerned, for approval by the
(i) Airframe/engine/propeller/auxiliary power unit log books.
* (j) Seating configuration approval document, where relevant.
+ (k) Maintenance Review Board document, where relevant.
(1) A summary of FAA approved retirement life limitations.
+ (m) Electrical load analysis.
NOTE: For aircraft other than first of type, the DCA requires sufficient information to be available to determine the errect or customer options, etc., on the supp-y ol electrical energy to essential services.
Appendix 2 + (n) FAA approved Master Minimum Equipment List, where applicable.
(0) Weighing report and associated weight schedule.
+ (P) Manuals required by the DCA:
NO. REQUIRED
i) The FAA approved Flight Manual 2 (but see or Pilot's Operating Handbook. also 4.2 (h)) ii) Airframe Maintenance Manual. 1 iii) Operations Manual. 2 iv) Weight and Balance/Loading Procedures. 1 V) Engine Maintenance Manual. 1 vi) Structural significant items. 1 viil Maintenance planning guide including manufacturers recommended component overhaul lives. 1 viii) Set of Service Bulletins and Service Letters or equivalent documents. 1 NOTE: A condition of Brunei certification of the first of a type is the provision by the Brunei applicant for certification of a continuing amendment service for the required manuals.
(g) Record of compass system and magnetic compass swings.
(r) Record of rigging checks.
(s) A statement that suitable tests and measurements have been made and recorded to establish the satisfactory performance of the installed radio/radar apparatus and their associated antennae.
A list of antennae positions must be provided.
(t) Detailed list of equipment constituting the navigation and communications installation.
+ (u) Noise Type Certificate.
Appendix 2
4.3 Used Aircraft.
In addition to the requirements specified in paragraph 4.2 (but (b) need not necessarily be complied with) the following information is required for used aircraft:
* (a) Maintenance program to which these aircraft have previously been maintained including:
i) previous check cycle.
ii) future check cycle.
(D) Component overhaul life summary, including details oi service life remaining and modification standards.
(c) Component and structure retirement life summary where applicable, including details of service life remaining.
* (d) Component and structural inspection program. This must • gecher with peon include details of any structural sampling program in which these aircraft have been included, together with details of their position in this program.
NOTE: All used aircraft will be subject to a physical condition survey and review of the associated records, to the sproval met to feathe from the DA fOt the applicane e proposals for integration of the aircraft into a maintenance program approved by the DCA. Prospective purchasers of used aircraft are encouraged to discuss their proposals with the DCA before arranging import into Brunei Darussalam.
4„4 Requirement For Export Certificates Of Airworthiness (FAA Form 8130-4) to be issued.
An Export Certificate of Airworthiness (FAA Form 8130-4) is required for any Class I product or engine module exported from the United States to Brunei Darussalam.
agreed by the DCA.
(b) When Additional Requirements have been notified to the FAA or FAA designee in accordance with paragraph 3,4 [[paragraph 3.4 not enclosed in this advisory circular.]] of this document, the Certificate shall be so endorsed as to provide a detailed status of compliance. Items of non-compliance do not require a waiver from the DCA providing they are so endorsed on the Certificate, as Brunei 34
Appendix 2 Darussalam is principally concerned with establishing the status of compliance at the time of export from the United States.
(c) The Certificate shall be accompanied by a document furnished by the applicant (e.g., a log book) which contains entries identifying those applicable Airworthiness Directives (AD's) with which compliance has been achieved. This document shall also identify those AD's containing a repetitive compliance requirement and when compliance is next due to be satisfied. All AD's shall be complied with prior to the issue of the Certificate unless a waiver has been issued by the DCA.
4.5 Appliances - General.
. The DCA will accept that an appliance has those characteristics vouched for on an FAA Airworthiness Approval Tag which has a United Kingdom Civil Aviation Authority (CAA) registration number quoted. For the purpose of this procedure, an appliance means any instrument, equipment, mechanism, apparatus, or accessory used or intended to be used in operating an aircraft in flight, which is installed in, intended to be installed in, or attached to the aircraft, but is not part of an airframe, engine or propeller, and includes replacement and modification parts therefor.
(b) In the case of an appliance which has not been granted a CAA registration number and which meets either of the following alternatives then application for acceptance of the appliance shall be made to the DCA.
(i) The appliance has been accepted by the FAA as complying with the Minimum Performance Standards of the applicable Technicai Standard Order (TSO) as published in FAR, Subpart O and FAR 21.305 (b); OI, Edicable Papitanco In lieu of approval under a Technical Standard Order, the appliance has been accepted by the FAA as meeting the applicable FAR's and the terms of the applicant's specifications.
(iii) Individual appliances will be accepted by the DCA on the basis of an Airworthiness Approval Tag (FAA Form 8130-3) issued by the FAA. The FAA certification may be made on behalf of the FAA by authorized persons delegated by the FAA, and the FAA assumes full
(c) In the case of an appliance by which approval is implied by certification of the aircraft in which the appliance is installed, sufficient information shall be supplied to the user and be supplied with an FAA Airworthiness Approval Tag.
4.6 Radio Appliances. The DCA may require a declaration of design and performance in the format specified in the current issue of British Standard Specification G.100. Details for any individual type of radio appliance will be supplied on written request.
Appendix 2 NOTE: Where a radio appliance has been approved by the United Kingdom Civil Aviation Authority, the item will be accepted by the DCA without further investigation.
relevant CAA approval number must be quoted on the FAA Airworthiness Approval Tag.
4.7 Products other than aircraft or appliances.
(a) Engines (including APUs), engine modules, and propellers:
(i) Export Certificate of Airworthiness (refer to paragraph 4.4).
(ii) Service Bulletin compliance statement.
(b) Class II as defined in Subpart L of FAR Part 21:
(i) FAA Airworthiness Approval Tag.
(c) Class III as defined in Subpart L of FAR Part 21:
(i) FAA Airworthiness Approval Tag, or concerned was manufactured under a Production Certificate granted 020602 under Subpart F of FAR Part 21, a Parts Manufacturing Approval granted under Subpart K of FAR Part 21, or a Technical Standard Order authorization granted under Subpart O of FAR Part 21 as appropriate.
5. SPECIAL CONDITIONS.
Where an aircraft is of unusual or novel design, the DCA reserves the right to prescribe Special Conditions or refuse certification.
Applications for Brunei Darussalam certification are advised to give early notification to the DCA of any aircraft type in this 36
Appendix 2
CANADA - SPECIAL REQUIREMENTS (Revised June 25, 1990) SECTION 1. - INTRODUCTION.
The manner in which Canada accepts aeronautical products from the United States is governed by the Canada-U.S. Bilateral Airworthiness Agreement which was effected by an Exchange of Notes on August 31, 1984. The means of Bilateral Airworthiness Agreement is specified in a Schedule of Implementation Procedures signed by the Administrator of the FAA and the Administrator of the Canadian Air Transportation Administration in January 1985. (Note that the title Administrator, Canadian Air Transportation Administration has now changed, following you change, reorganization, to Assistant Deputy Minister, Aviation, in the Transport Canada Aviation Group (TCAG).)
SECTION 2. - PRODUCT TYPE DESIGN APPROVAL. Before an aeronautical product is accepted for operation in Canada, it is important to establish that the type design is approved by TCAG. The following section summarizes the TCAG position on Type Design Approval.
2.1 Aircraft.
(a) U.S. Designed and Manufactured. All U.S. aircraft types require either Canadian Aircraft Type Approvals or TCAG acceptance of the FAA Type Certificates. In the past, it has been customary for TCAG to issue Canadian Aircraft Type Approvals only for Transport Category, Commuter Category (SFAR 41C) and Restricted Category aircraft types. Aircraft in other categories have been accepted, based on the applicable FAA Type Certificate.
Effective June 1, 1989, all new U.S. aircraft types not previously accepted for use in Canada, will require a Canadian Aircraft Type Approval prior to the aircraft being eligible for Certificate of Airworthiness. U.S. applicants (Type Certificate holders) should make their request for Canadian Aircraft Type Approval through the applicable FAA Aircraft Certification Office (ACO) which processed the FAA Type Certificate.
The TCAG will advise the U.S. applicant, through the AA, of the TCAG Additional Technical Conditions. These Additional rechnical Conditions are the requirements, including Special conditions, Canadian Additional Airworthiness Requirements, environmental and operational requirements, that might be specified by TCAG in addition to the FAA basis of certification to assure compliance with the Canadian Type Approval basis.
Except for simple Normal Category aeroplanes, a prior condition for the determination of the Additional Technical Conditions will be a technical briefing to the TCAG by the applicant, followed by a familiarization inspection of the aircraft and its type 37
Appendix 2 design at the applicant's facility. This familiarization may involve a review of the type design data and the basis of type certification, as well as test flights of a representative aircraft.
All such familiarization visits are coordinated through the applicable FAA ACO. Since there is often a delay of several months, following receipt of the application, before such a familiarization can be made by TCAG, it is important that requests tor an Aircrait Type Approval are made in a timely manner. An additional condition for the acceptance of an application for a Canadian Type Approval is that there shall be a bona fide, committed, Canadian customer for the aircraft.
(b) Designed and Manufactured in a Third Country (other than Canada or the U.S.).
in a country other than Canada or the United States (third country) require Canadian Aircraft Type Approvals. The Type Approval is based on a validation/familiarization by TCAG of the type certification issued by the airworthiness authority in the third country. The procedure is similar to that specified in Section 2.1(a) above, except of course, that the TCAG will deal with the third country airworthiness authority, and not the FAA.
(c) Designed and Manufactured in the U.S. and a Third Country. Aircraft having a type design approval in one country and being manufactured in another country, one of which is the United States, are eligible for Canadian Certificates of Airworthiness providing there is a Canadian Type Approval and a written agreement on continuing airworthiness responsibilities between the FAA, ICAG and the third country airworthiness authority.
2.2 Engines and Propellers.
(a) U.S. Designed and Manufactured. Effective June 1, 1989, any U.S. designed and manufactured engine or propeller installed in an aircraft type which has been issued with a Canadian Aircraft Type Approval, will require a Canadian Type Approval. U.S.
applicants should make their request for the Canadian Type Approval through the applicable FAA Aircraft Certification Office (ACO) which processed the engine or propeller Type Certificate. This approval may require a TCAG familiarization inspection at the engine or propeller type design holder's facility.
(b) Designed and Manufactured in a Third Country (Other than Canada or the U.S.l. When an engine or propeller designed and manufactured in a third country, other than the U.s. or Canada, is intended for installation on an aircraft which has been issued with a Canadian Aircraft Type Approval, then a Canadian Type Approval is required. The application should be made to the TCAG through the third country airworthiness authority and may require a validation/familiarization inspection at the applicant's facility.
Appendix 2
2.3 Technical Standard Order (TSO) Products. No separate Canadian equipment approval is required for a TSO product where an FAA letter of design approval has been issued to an applicant located in the United States or Canada. The FAA letter of approval is acceptable to TCAG without any further validation being necessary.
2.4 Parts Manufacturing Approvals (PMA). A PMA issued to a U.S.
applicant for the design of a part installed on a product which was certificated by the FAA to FAR 21.21 (U.S. domestic type certification) is normally acceptable to TCAG without any additional design approval.
part installed on a product which was certificated to FAR 21.29 (foreign type certificate) will require TCAG approval before that part can be fitted to a Canadian registered aircraft, unless the PMA holder is a supplier to the foreign type certificate holder or has a licenced manufacturing agreement from the foreign type certificate holder.
2.5 Supplemental Type Certificates/Supplemental Type Approvals.
A product type design which has been approved in both the U.S. and Canada may be altered in the United States by an applicant who has obtained an FAA Supplemental Type Certificate (STC).
A number of these STC's are automatically recognized by TCAG without any additional approval procedure being required. However, any ST's relating to the following categories of aircraft will require review by TCAG and an approval, which will be issued as a Canadian Supplemental Type Approval:
(1) Canadian manufactured aircraft for which Transport Canada holds the type design responsibilities.
(2) Third country manufactured aircraft which were later granted either an FAA Type Certificate or a Canadian Type Approval. (3) Canadian or U.S. manufactured aircraft originally craft categoe! Whiche designed for Normal, Utility, Aerobatic or Transport Category which were later converted to Restricted Category, or when by virtue of the eitected change(s), these aircraft would normally have been subject to a separate Type Approval had these changes been proposed by the manufacturer (e.g., change in number of engines or engine types using different propulsion systems).
(4) U.S. manufactured aircraft type certificated in either Transport, Restricted or Commuter Category (SFAR 41C), which under the present regulations and policies would require a Canadian familiarization of their FAA Type Certificate. The above policy also applies to older aircraft which were accepted in Canada solely on the basis of their FAA certification, without the conduct of a formal DOT familiarization at the time of import, and thus were not issued with a corresponding Canadian Type Approval, e.g., Boeing 707, 727, McDonnell Douglas DC-8, etc.
Appendix 2
(5) U.S. manufactured aircraft modified to accommodate the installation of equipment for which no approved civil airworthiness standard exists for that particular change in type design (e.g., Steep Approach Approvals).
(6) Any aircraft whose related STC addresses the operational design requirements prescribed in either the Air Regulations, Air Navigation Orders, Engineering and Inspection Manual, or the Airworthiness Manual.
(7) Any aircraft whose related STC provides relief or alternate means of compliance with Canadian Airworthiness Directives.
(8) Any aircraft whose related STC authorizes the use of unusual methods of fabrication or unconventional design features
(e.g., canard flight controls).
A design approval granted under the FAA field approval procedures is not generally recognized by TCAG, although it may be reviewed on a case by case basis and, where compliance against applicable requirements can be shown by the applicant, a TCAC approval will be issued.
2.6 ICAG Contacts. All questions relating to Canadian type design approval of aeronautical products, as specified in Section 2 above, should be addressed to:
Chief, Programs (AARDE) Airworthiness Branch Transport Canada Aviation Group Centennial Towers 200 Kent Street Ottawa, Ontario, Canada K1A ON8 Facsimile: (613) 996-9178 Telephone: (613) 990-1267 SECTION 3 - TAG CONDITIONS FOR ACCEPTANCE OF AERONAUTICAL PRODUCTS.
3.1 Class I Aeronautical Products - Aircraft. Imported aircraft are eligible for use in Canada where it can be shown and TCAG is satisfied that the aircraft conforms to the Canadian approved type design and is in a condition for safe operation.
For an imported aircraft the preferred method of showing conformity is by means of an Export Certificate of Airworthiness.
When an aircraft is imported without an Export Airworthiness Certificate, or other acceptable document, the aircraft will be ineligible for use in Canada until it has been completely overhauled pursuant to Section 507.207(c) (c)(3) of the Airworthiness Manual or its 40
Appendix 2 conformity and condition has been completely verified by an inspection performed by an authorized person or organization in accordance with Section 507.207 (c) to (j).
In either case the requirement of Airworthiness Manual Chapter 507 D, Subchapter D must be complied with before the aircraft will be eligible for a Canadian Certificate of Airworthiness.
To be acceptable each export airworthiness certificate must be properly certified by an authorized representative of the FAA and shall include the following information:
a certification of conformity to the type design specified in the Canadian type approval;
(2) a list of any major modifications and major repairs approved by the country of export and embodied in the product; and
(3) a list of all applicable airworthiness directives or equivalent mandatory notices, issued by the country of export, indicating which have been complied with.
3.2 Class I Aeronautical Products - Aircraft Engines and Propellers. Imported aircraft engines or propellers are eligible to be installed on Canadian registered aircraft where it can be shown and TCAG is satisfied that the aircraft engine or propeller conforms to the Canadian approved type design and is in a condition for safe operation.
For an imported aircraft engine or propeller the preferred method of showing conformity is by means of an Export Certificate of Airworthiness.
Each imported aircraft engine or propeller must conform to the approved Canadian type design and be accompanied by an export airworthiness certificate. However, where an engine or propeller has been imported without the required certification but with complete and current maintenance records, that aircraft engine or propeller may be eligible for installation on a Canadian registered aircraft provided the aircraft engine or propeller has been inspected for conformity to approved type design in accordance with Airworthiness Manual Section 507,205(c) (4) by an authorized person or an approved organization.
When an aircrait engine or propeller is imported without an export airworthiness certificate, or other acceptabie document, the aircraft engine or propeller will be ineligible for use in Canada until its conformity and condition has been compietely verilled by an inspection performed by an authorized person or organization in accordance with Airworthiness Manual Section 507.205 (c) (4) of the Manual.
Appendix 2 When an aircraft engine or propeller does not pass the inspection and cannot be certified it will require a complete overhaul and re-certification before it will be eligible for installation in a Canadian registered aircraft.
To be acceptable to the Minister each export airworthiness certificate must be properly certified by an authorized representative of the FAA and shall include the following information:
a certification of conformity to the type design specified in the Canadian type approval;
(2) a list of any major modifications and major repairs approved by the country of export and embodied in the product; and
(3) a list of all applicable airworthiness directives or equivalent mandatory notices, issued by the country export, indicating which have been complied with.
3.3 Class Il Aeronautical Products - Parts and Appliances.
Imported parts and appliances will be eligible for installation on Canadian registered aircraft where:
(1) the product is new or newly overhauled and conforms to approved design data;
(2) the product is in a condition for safe operation;
(3) the product is identified pursuant to Air Regulations, Series II, No. 1.
For Class II aeronautical products imported directly from the United States, the TCAG will accept as proof of conformity:
(1) a signed certification on a company inspection release note, tag or other shipping document stating the name and address of the company, and FAA approval number of Production Certificate (PC), Parts Manufacturing Approval (PMA), Technical Standard Order (TSO) authorization, or Repair Station Certificate as applicable;
(2) a signed certification, showing the name and address of the supplier, referencing the original documentation issued by a company holding a PC, PMA, TSO authorization or Repair Station Certificate. An acceptable alternative would be for the supplier to attach a copy of the original documentation to his certificate; or
(3) an FAA Airworthiness Approval Tag, Form 8130-3 signed by an FAA airworthiness representative.