Airworthiness Chapter 551 - Aircraft Equipment and Installation - Canadian Aviation Regulations (CARs)

Table of contents

• Interpretation Provision for Part V Standards
• Procurement of Reference Publication
• Preamble
• Subchapter A General
  • 551.01 - Application
  • 551.02 - Equipment Design Standards
  • 551.03 - Equipment Installation Standards
  • 551.04 to 551.09 - Reserved
• Subchapter B Mechanical Systems
  • 551.10 - Tow Hitch and Release Control System
  • 551.11 to 551.99 - Reserved
• Subchapter C Avionic Systems
  • 551.100 - Flight Data Recorder
  • 551.101 - Cockpit Voice Recorder
  • 551.102 - Terrain Awareness and Warning System (TAWS) and Ground Proximity Warning System (GPWS)(amended 2009/12/01)
  • 551.103 - Transponder and Automatic Pressure Altitude Reporting Equipment
  • 551.104 - Emergency Locator Transmitter
  • 551.105 - Altitude Alerting System
  • 551.106 - Thunderstorm Detection and Weather Radar Equipment
  • 551.107 - Radiocommunication Equipment
  • 551.108 - Radio Navigation Equipment
  • 551.109 to 551.199 - Reserved
• Subchapter D Electrical Systems
  • 551.200 - Electrical Power System
  • 551.201 - Battery
  • 551.202 to 551.299 - Reserved
• Subchapter E Powerplant Systems
  • 551.300 to 551.399 - Reserved
• Subchapter F Emergency Equipment
  • 551.400 - Hand-Held Fire Extinguisher
  • 551.401 - Life Saving Equipment Over Water - Life Preservers
  • 551.402 - Life Saving Equipment Over Water - Individual Flotation Devices (IFD) (amended 2009/12/01)
  • 551.403 - Life Saving Equipment Over Water - Personal Flotation Devices (PFD) (amended 2009/12/01)
  • 551.404 - Life Saving Equipment Over Water - Life Rafts
  • 551.405 - Protective Breathing Equipment (PBE) (amended 2009/12/01)
  • 551.406 - Seat Belt and Shoulder Harness
  • 551.407 - Aircraft Passenger Transportation Suit Systems
  • 551.408 - Crash Axe (amended 2009/12/01)
  • 551.409 to 551.499 - Reserved (amended 2009/12/01)
• Subchapter G Miscellaneous
  • 551.500 - Restraint of Carry-on Baggage
  • 551.501 - Child Restraint Systems (effective 2021/05/24)
  • 551.503 to 551.599 - Reserved (amended 2009/12/01)
• Standard not yet in force

Content last revised: 2009/12/01

Interpretation Provision for Part V Standards

In these Standards:

• (a) The passages giving the Minister power to determine, approve or authorise something without stating criteria for the use of such power are to be interpreted as requiring that the power be used in consideration of two factors only:

  the airworthiness of the aircraft that is the subject of the determination, approval or authorisation, or on which an aeronautical product that is the subject of the determination, approval or authorisation is to be installed, and the aircraft's level of safety;

• (b) The word "approved", when used without any indication of a method of approval, is to be interpreted as referring to an approval granted under the Aeronautics Act.

Procurement of Reference Publication

Copies of publications referenced in this Chapter of the Airworthiness Manual may be obtained from the following sources:

• (a) European Organisation for Civil Aviation Equipment (EUROCAE) Documents

  EUROCAE documents may be purchased from the European Organisation for Civil Aviation Equipment, 17 Rue Hamelin, 75783 Paris Cedex 16, France.

• (b) Radio Technical Commission for Aeronautics (RTCA) Documents

  RTCA documents may be purchased from the RTCA Inc., 1140 Connecticut, NW, Suite 1020, Washington, D.C. 20036, USA.

• (c) Industry Canada Documents

  Industry Canada documents may be obtained from Industry Canada, 300 Slater Street, Ottawa, Ontario K1A 0C8.

• (d) CAN/CGSB Documents

  CAN/CGSB documents may be obtained from Sales Centre, Canadian General Standards Board, Ottawa, Ontario K1A 1G6.

Preamble

First Edition
Effective: December 1, 1998

In the early nineties Transport Canada Civil Aviation identified the remaining additional operating requirements, contained in U.S. Code of Federal Regulations, Title 14, Part 91, 121, 127, 133 and 135, to be adapted and incorporated into a "Canadian code", as recommended by the Dubin Commission of Inquiry into Aviation in 1982.

A study was commissioned to SYPHER-MUELLER International Inc. to isolate those additional operating requirements for which there were no equivalent in Canada; and to analyse the potential impact of their incorporation in the Canadian Code. The results of this study were used in the development of Part VI or Part VI of the Canadian Aviation Regulations (CARs).

These CARs state that the required aircraft equipment must meet the applicable standards of airworthiness related to the design, manufacture and maintenance of aeronautical products. This chapter, published pursuant to Part V, Subpart 51 of the CARs, sets out standards of airworthiness for the design and installation of some of the aircraft equipment required by CAR Part VI or Part VI.

The standards contained in this chapter have been developed by a joint Transport Canada and aviation industry working group established by the Canadian Aviation Regulation Advisory Council (CARAC), Technical Committee V. The working group's first priority was to develop equipment standards to replace those remaining in the Engineering and Inspection Manual (E&I).

This chapter supersedes the following sections of the Engineering and Inspection Manual, which remains only as an historic document for past reference.

Engineering and Inspection Manual, Part II, Chapter III

Section	Title	Superseded by
3.1	Restraint of Carry-On Baggage	551.500
3.5	Portable Fire Extinguishers	551.400
3.9	Flight Data Recorders	551.100
3.10	Cockpit Voice Recorders	551.101
3.12	Emergency Locator Transmitter Systems	551.104
3.13	Ground Proximity Warning Systems	551.102
3.14	Air Traffic Control Transponder and Automatic Pressure Altitude Reporting Equipment	551.103
3.15	Safety Belts	551.406

While Chapter 537 "Appliances" of the Airworthiness Manual specifies the current standards for the issuance of a Type Certificate of new aviation appliances and is designer/manufacturer oriented, Chapter 551 lists acceptable design standards as well as installation standards for use by installers and users of these items of equipment.

Change 551-1
Effective: December 1, 2004

In an effort to harmonize our regulatory guidance documents with those of other international aviation authorities and other branches within Transport Canada Civil Aviation (TCCA), the Aircraft Certification Branch has decided to replace existing Airworthiness Manual Advisories (AMA) related to certification of aeronautical products with new Advisory Circulars (AC). While the content of the new ACs will remain technically the same as the corresponding AMAs, which they will replace, the format of the ACs will be standardized to conform to other guidance documents published within the branch.

This change in guidance documentation becomes effective 1 December 2004 at which time the AMAs will be cancelled and replaced by their corresponding Advisory Circular concurrent with the next publishing of the Canadian Aviation Regulations (CAR). After this time, the CARAC Secretariat will no longer publish these AMAs and, consequently, ACs will not be published with their corresponding AWM Chapter. As of the 1 December 2004 issue of the CARs, any affected AMA references and content will have been removed. However, the AMA Index found in AMA 500/00 will, for now, continue to exist to provide a cross-reference between the old AMAs and the new ACs.

Change 551-2
Effective: December 1, 2005

• 1. General

  Change 551-2 introduces a new amendment format. This new amendment format was originally introduced in Chapter 529 of the Airworthiness Manual in order to be more consistent with the administrative procedures followed to amend the Canadian Aviation Regulations (CARs).

  The following procedures are introduced in Change 551-2:

  • the preamble is, as of Change 551-2, the focal point regarding the sections affected by Change 551-2 and future Changes. For the current change only, an amendment tag identifying the coming into force date of the provision will follow the amended text. {example: (amended 2003/06/01)

  • On the paper version, new or revised text will be highlighted. In the electronic version, new or revised text will not be highlighted but followed by an electronic link to the previous version of the modified text. (example: amended 2003-06-01; previous version)

  • the preamble will include a table of change information. This table will include the Notices of Proposed Amendments (NPAs) with the corresponding amended sections.

• 2. CARAC Proposed Amendment Recommendations

  This change implements the amendments to the standard recommended by the CARAC Technical Committee Part V.

Table of Change Information

Notice of Proposed Amendment	Amended Section(s)
2000-333	551.10

This amendment provides standards of airworthiness for the approval of a tow hook/hitch and its release mechanism installed on aeroplanes for the purpose of towing gliders or banners.

Table of Change Information

Notice of Proposed Amendment	Amended Section(s)
2000-334	551.107

The Working Group noted in its final report that existing standards for radio communication equipment are adequate. However, the Working Group recommended that an information note be added to identify FAA Advisory Circular AC 23-8B (or later revision) as appropriate guidance material for evaluating installation of radio communication equipment required by CAR Part VI. This reference to acceptable advisory material will provide guidance on the evaluation of equipment installation to achieve acceptable installed performance.

Table of Change Information

Notice of Proposed Amendment	Amended Section(s)
2000-335	551.108

The Working Group noted in its final report that existing standards for radio navigation equipment are adequate. However, the Working Group recommended that an information note be added to identify FAA Advisory Circular AC 23-8B (or later revision) as appropriate guidance material for evaluating installation of radio navigation equipment required by CAR Part VI. This reference to acceptable advisory material will provide guidance on the evaluation of equipment installation to achieve acceptable installed performance.

Table of Change Information

Notice of Proposed Amendment	Amended Section(s)
2000-336	551.400

This amendment updates the information note in the hand-held fire extinguisher section to refer to the current accepted advisory material.

Table of Change Information

Notice of Proposed Amendment	Amended Section(s)
2001-019	551.407

This amendment is to add a section in the Airworthiness Manual (AWM) Chapter 551 to address the standards of airworthiness for aircraft passenger transportation suit systems.

Table of Change Information

Notice of Proposed Amendment	Amended Section(s)
2004-036	551.104

This amendment takes the specific requirements of the Emergency Locator Transmitters standard as specified in AWM Chapter 537 and incorporates them into AWM Chapter 551.

Change 551-3
Effective: December 1, 2009

On December 1, 2009, Part V Subpart 21 of the Canadian Aviation Regulations (CAR 521) came into force. CAR 521 replaces the following Regulations in Part V—Airworthiness:

Subpart 11 - Approval of the Type Design of an Aeronautical Product
Subpart 13 - Approval of Modification and Repair Designs
Subpart 16 - Aircraft Emissions
Subpart 22 - Gliders and Powered Gliders
Subpart 23 - Normal, Utility, Aerobatic and Commuter Category Aeroplanes
Subpart 25 - Transport Category Aeroplanes
Subpart 27 - Normal Category Rotorcraft
Subpart 29 - Transport Category Rotorcraft
Subpart 31 - Manned Free Balloons
Subpart 33 - Aircraft Engines
Subpart 35 - Aircraft Propellers
Subpart 37 - Aircraft Appliances and Other Aeronautical Products
Subpart 41 - Airships
Subpart 51 - Aircraft Equipment
Subpart 91 - Service Difficulty Reporting
Subpart 93 - Airworthiness Directives

In addition, with publication of CAR 521, the following Chapters of the Airworthiness Manual have been withdrawn:

Chapter 511 - Approval of the Type Design of an Aeronautical Product
Chapter 513 - Approval of Modification and Repair Designs
Standard 591 - Service Difficulty Reporting
Standard 593 - Airworthiness Directives

This change amends Chapter 551 of the AWM to reflect changes in legal drafting style, in terminology and in references required because of the introduction of CAR 521. This change also amends the French text to correct inconsistencies between the French and English text.

• (a) In addition to the above changes, this change:

• (b) introduces requirements for crash axes in section 551.408;

• (c) amends section 551.102 on Ground Proximity Warning Systems to introduce requirements for Terrain Awareness and Warning Systems;

• (d) introduces requirements for child restraint systems in section 551.501, which had previously been in Chapter 537 of the AWM; and

  amends the table of paragraph 551.403(c) to introduce the UL1180 Type II Standard with Canadian Addendum.

(amended 1998/12/01)

Change 551-4
Effective: May 29, 2019

This Change incorporates the following amendments to the standard:

Table of Change Information

Notice of Proposed Amendment	Amended Section(s)
2011-010	551.100
	551.101

This change amends the standards of airworthiness for the design and installation of Flight Data Recorder (FDR)  and Cockpit Voice Recorder (CVR)  equipment required by Part VI of the Canadian Aviation Regulations (CARs). It introduces new standards for FDRs, CVRs, Data Link Recorders (DLRs) and Underwater Locating Devices (ULDs). This amendment supports the regulatory amendments  introduced in Part VI of the CARs by NPA 2011-010. In particular, it  introduces a requirement for a two hour recording duration for CVRs and the requirement for a ten minute CVR independent power supply.

Change 551-5
Effective: November 25, 2020

This Change incorporates the following amendments to the standard:

Table of Change Information

Notice of Proposed Amendment	Amended Section(s)
2015-013	551.02
	551.104

This change amends the standards of airworthiness for the design and installation of Emergency Locator Transmitter (ELT) equipment required by Part VI of the Canadian Aviation Regulations (CARs). This amendment  supports the associated amendments to the CARs pertaining to ELTs published in Part II of the Canada Gazette on November 25, 2020.  The new standards for ELT equipment and installation support the requirement for  ELTs transmitting simultaneously on the frequencies of 406 MHz and 121.5 MHz. The objective is to facilitate search and rescue operations.

Change 551-6
Effective: May 24, 2021

This Change incorporates the following amendments to the standard:

Table of Change Information

Notice of Proposed Amendment	Amended Section(s)
2020-015	551.401
	551.402
	551.403

This amendment entitled “Life Preservers, Individual Flotation Devices and Personal Flotation Devices” amends the standards of airworthiness for the design and installation of aircraft equipment required by Part VI or Part VII of the Canadian Aviation Regulations (CARs) concerning life preservers, individual and personal flotation devices. Its objective is to update the list of eligible equipment standards to permit the use of life preservers and flotation devices meeting later standards than those currently specified in sections 551.401, 551.402 and 551.403 of the AWM. It also removes the eligibility for use of life preservers meeting TSO-C13c due to shortcomings with that standard. In addition, this amendment supports the entry into force on June 6, 2021 of new regulations amending the CARs (Parts I, VI and VII – Seaplane Operations).  In particular, a new section 703.83 of the CARs that will require passengers and pilots of commercial seaplanes with nine passengers or less conducting air taxi operations on or over water to wear a flotation device that is inflatable and not inherently buoyant.

Table of Change Information

Notice of Proposed Amendment	Amended Section(s)
2020-016	551.501

This amendment entitled “Child Restraint Systems” amends the standards of airworthiness for the design and installation of aircraft equipment required by Part VI of the Canadian Aviation Regulations (CARs) concerning child restraint systems. Its objective is to expand the range of approval standards recognized as appropriate for aviation use in Canada, increase harmonization with other major civil aviation authorities , clarify  that Transport Canada recognizes the approval of child restraint systems granted by specific organizations and clarify that child restraint systems are used on aircraft but not installed in aircraft.

Change 551-7
Effective: July 17, 2023

This Change incorporates the following amendments to the standard:

Table of Change Information

Notice of Proposed Amendment	Amended Section(s)
2023-001	551.103

Subsection 551.103 is amended to introduce equipment and installation standards for ADS-B Out installations based on a Mode S transponder.

Subchapter A
General

551.01 Application

Pursuant to subsection 521.31(2) of the Canadian Aviation Regulations (CARs), this Chapter specifies standards of airworthiness for the design and installation of aircraft equipment required by Part VI or Part VII of the CARs.
(amended 2009/12/01)

551.02 Equipment Design Standards

• (a) Subject to (b), equipment installed or intended for installation in aircraft must meet the applicable requirements of:
  (amended 2009/12/01)

  • (1) Part V, Subpart 21 of the CARs; or
    (amended 2009/12/01)

  • (2) this chapter, where the equipment was already approved for use on aircraft.

    Information note:

    Where a CAN-TSO is referenced as an acceptable standard of airworthiness, it is intended to mean that the design standards contained within the CAN-TSO are an acceptable minimum standard. However, the equipment does not necessarily need to have a Canadian Technical Standard Order (CAN-TSO) design approval, an FAA technical standard order authorization (TSOA) or letter of design approval (LODA), or equivalent design approval accepted by Transport Canada in accordance with an agreement or similar arrangement under subsection 521.455(3) of the CARs; the equipment may be approved in a manner set out in section 521.02 of the CARs.
    (effective 2020/11/25)

• (b) Where there are no specific design standards, the equipment must provide the same level of safety as that established by the certification basis of the aircraft.
  (amended 2009/12/01)

551.03 Equipment Installation Standards

In addition to meeting the requirements specified in this chapter, the installation of the equipment must meet the applicable standards of the certification basis of the aircraft.
(amended 2009/12/01)

551.04 to 551.09 Reserved

Subchapter B
Mechanical Systems

551.10 Tow Hitch and Release Control System
(amended 2005/12/01)

• (a) General
  (amended 2005/12/01)

  This section contains standards of airworthiness for the approval of a tow hitch and its release mechanism for towing gliders or banners as required by section 602.22 of the CARs.

  Information note:

  Section 602.22 of the CARs prohibits towing objects unless the aeroplanes are equipped with an approved tow hitch and release mechanism. The standards in this section apply only to glider and banner towing. The approval of tow hitches and release mechanisms for towing objects, other than gliders and banners will be evaluated on a case by case basis.

• (b) Equipment approval
  (amended 2005/12/01)

  Each tow hitch and its release mechanism not approved as part of the aircraft type design, must meet the minimum requirements contained in Chapter 8, section 126, paragraph (a) or (b) of FAA AC 43.13-2A, Change 2 dated October 30, 1989, respectively for glider or banner towing.
  (amended 2009/12/01)

• (c) Installation approval
  (amended 2005/12/01)

  In addition to complying with section 127, Structural testing, section 128, attachment points, section 129, Angles of tow, section 130, Placards and section132, Tow release mechanism, of Chapter 8 of FAA AC 43.13-2A, Change 2, the following is required for certification approval:

  • (1) Tow Release Mechanism

    The design of the release control must provide for a location which permits convenient operation by the pilot with seat belt and shoulder harness secured and which cannot be confused with other control handles. The release mechanism must be within pilot's reach with the flight controls in any possible position.
    (amended 2009/12/01)

  • (2) Weight and Balance

    A new Weight and Balance Report must be prepared according to the requirements of Appendix C of Standard 571 of the Canadian Aviation Regulations.
    (amended 2009/12/01)

  • (3) Markings and Placards

    The function and method of operation of the tow hitch release shall be on a placard mounted near the release control and in clear view of the pilot. The maximum load that can be applied to the tow hook must be on a placard in clear view of the pilot and specified as a limitation in any flight manual (or supplement) associated with towing.
    (amended 2009/12/01)

  • (4) Towing Approval and Flight Manual Supplement

    An aeroplane that is to be used to tow gliders, banners, or other objects must be approved for that purpose and be provided with an appropriate flight manual supplement.
    (amended 2009/12/01)

Information note:

551.11 to 551.99 Reserved
(amended 2005/12/01)

Subchapter C
Avionic Systems

551.100 Flight Data Recorder

• (a) Introduction

  This section contains standards of airworthiness for installation approval of Flight Data Recorder (FDR) required by CAR 605.33.

• (b) Definitions

  In this section,

  “Flight Data Recorder (FDR)” (deleted 2019/05/29)

  “Follow on series FDR installation” means an installation that is accomplished in conformity with approved data derived from the initial installation of the same type and model of FDR and aircraft; and

  “Initial installation” means the first installation of a particular type of FDR in an aircraft of a particular type and model.

• (c) Equipment

  These design standards in the following documents apply:

  Standard	Criteria for Acceptance for Installation
  As contained in Chapter 537: (effective 2019/05/29)
  CAN-TSO-C124 or later (effective 2019/05/29)	Acceptable for new and existing FDR installations (effective 2019/05/29)
  CAN-TSO-C121a or later (effective 2019/05/29)	Acceptable for a new or existing underwater locating device (effective 2019/05/29)
  Other: (effective 2019/05/29)
  CAN-TSO-C51a (amended 2009/12/01)	May remain in use for existing installations approved prior to 1 December 1998 (the date of issue of CAR 551), provided the equipment is capable of meeting the Aircraft Equipment and Maintenance Standards (Standard 625). (amended 2009/12/01)

• (d) Installation
  • (1) Installation

    FDR system installation must be in accordance with the European Organisation for Civil Aviation Equipment (EUROCAE) document ED 55, “Minimum Operational Specification for Flight Data Recorder Systems”, section 2.11, dated May 1990. In the event of any conflict between the ED 55 document and the certification basis of the aircraft, the certification basis applies.
    (effective 2019/05/29)

    Information note:

    For normal and transport category rotorcraft, the installation location requirements for non-ejectable record container of an FDR is set out in paragraphs 527.1459(b) and 529.1459(b) of Chapters 527 and 529 of the Airworthiness Manual.
    (effective 2019/05/29)

    Normally, for aeroplanes, an FDR installation location at the aft would satisfy the requirements. However, for rotorcraft, the forward locations are generally less susceptible to fire and it may be preferable to install the record containers in a forward location. In addition, a forward location may avoid a significant weight penalty in comparison to an aft location.

    It is therefore acceptable to install FDR non-ejectable record containers in forward locations of rotorcraft provided that the recorders are certified pursuant to CAN-TSO-C124 (or later) crash survivability standards.
    (effective 2019/05/29)

  • (2) Recorder Operation and Termination

    FDR system operation and termination must be in accordance with EUROCAE ED-55, sections 2.4.1 and 2.4.2
    (amended 2009/12/01)

  • (3) Data Sources

    Subject to the certification basis of the aircraft, each FDR system may obtain data on the parameters specified in Standard 625.33 whenever practical and permissible from the sources in the aircraft, or from transducers specifically installed and calibrated for correctly sensing the parameters.
    (amended 2009/12/01)

  • (4) Calibration and Correlation

    • (i) Initial Installation

      Each initial installation must be tested in the aircraft in which it is installed to demonstrate compliance with the system accuracy requirements of Standard 625.33 over the full range of each required parameter. The test must establish calibration and correlation data for each parameter.
      (amended 2009/12/01)

      In order to obtain approval for initial installations, the following information is required:

      • (A) A report providing:

        A description of the means utilised to convert the data sensed at the source into signals suitable for input to the Flight Data Acquisition Unit of the FDR,

        In respect of each parameter, conversion data and logic for translation of the recorded data stream into parameters expressed in engineering units;

      • (B) Reports of all tests of the full FDR system including calibration results and correlation data derived from the system accuracy tests;

      • (C) A maintenance plan; and

      • (D) Two copies of the operating, servicing, and maintenance instructions.

        Information note:

        If a Supplement to the Aircraft Flight Manual or equivalent publication is produced, it must be submitted to Transport Canada for approval.

    • (ii) Follow-on Series FDR Installations

      Each follow-on series FDR installation must be subjected to sufficient testing to confirm conformity with the calibration and correlation data applicable to the initial installation.
      (amended 2009/12/01)

551.101 Cockpit Voice Recorder

• (a) Introduction

  This section contains standards of airworthiness for installation approval of Cockpit Voice Recorder (CVR) required by CAR 605.34.
  (effective 2019/05/29)

• (b) Definition
  (effective 2019/05/29)

  In this section, “Initial installation” means the first installation of a particular type of CVR in an aircraft of a particular type and model, for which approval is sought.

  “Cockpit Voice Recorder (CVR)”
  (deleted 2019/05/29)

  “Follow on series CVR installation”
  (deleted 2019/05/29)

• (c) Equipment

  The design standards in the following documents apply:

  Standard	Criteria for Acceptance for Installation
  As contained in Chapter 537: (effective 2019/05/29)
  CAN-TSO-C123b or later (effective 2019/05/29)	Acceptable for new and existing CVR installations provided that: (effective 2019/05/29) (1) the CVR has a recording capacity of at least two hours; (effective 2019/05/29) (2) a recorder independent power supply that meets CAN-TSO-C155a, or later revision, is installed to support the CVR. (effective 2019/05/29)
  CAN-TSO-C177 or later (effective 2019/05/29)	Acceptable for a new or existing data-link recorder installation (effective 2019/05/29)
  CAN-TSO-C121a or later (effective 2019/05/29)	Acceptable for a new or existing underwater locating device (effective 2019/05/29)
  Other: (effective 2019/05/29)
  FAA TSO-C123a (effective 2019/05/29)	Acceptable for existing CVR installations provided that: (effective 2019/05/29) (1) the CVR has a recording capacity of at least two hours; (effective 2019/05/29) (2) a recorder independent power supply that meets CAN-TSO-C155, or later revision, is installed to support the CVR. (effective 2019/05/29)

• (d) Installation

  • (1) Installation and Installed Performance
    • (i) CVR installation and installed performance must be in accordance with the equipment’s minimum performance specification, which is the European Organisation for Civil Aviation Equipment (EUROCAE) document ED-112, “Minimum Operational Performance Specifications (MOPS) for Crash Protected Airborne Recorder Systems”, or later. In the event of any conflict between the ED-112 document and the certification basis of the aircraft, the basis of certification applies.
      (effective 2019/05/29)
    • (ii) Data-Link Recorder (DLR) installation and installed performance must be in accordance with the equipment’s minimum performance specification, CAN-TSO-C-177 or later, which references ED-112 or later, and where:
      (effective 2019/05/29)
      • (A) the minimum recording duration shall be equal to the recording duration of the CVR; and
        (effective 2019/05/29)
      • (B) data-link recording shall be able to be correlated to the recorded cockpit audio;
        (effective 2019/05/29)
    • (iii) Underwater Locating Device installation and installed performance must be in accordance with the equipment’s minimum performance specification, CAN-TSO-C121a or later.
      (effective 2019/05/29)

      Information note:

      For normal and transport category rotorcraft, the installation location requirements for record container of a CVR is set out in paragraphs 527.1457(e) and 529.1457(e) of Chapters 527 and 529 of the Airworthiness Manual.
      (effective 2019/05/29)

      Normally, for aeroplanes, a CVR installation location at the aft would satisfy the requirements. However, for rotorcraft, the forward locations are generally less susceptible to fire and it may be preferable to install the record containers in a forward location. In addition, a forward location may avoid a significant weight penalty in comparison to an aft location.

  • (2) Initial Installation

    Each initial installation must be tested in the aircraft in which it is installed to demonstrate compliance with the system recording requirements of Standard 625.34. The tests must be conducted in accordance with the procedures specified in the equipment’s minimum performance specification, which is EUROCAE ED-112 or later.
    (effective 2019/05/29)

    In order to obtain approval for initial installations, the following information is required:

    • (i) A test recording made under the noise conditions of flight operations, together with a report from a recognised CVR playback facility demonstrating that the quality and the intelligibility of the recorder information are satisfactory, including the data-link recording if data-link communications applications are installed and utilized;
      (effective 2019/05/29)

      Information note:

      It is acceptable to use a copy of the original recording for demonstrating compliance with this requirement.

    • (ii) Software documentation including conversion and logic data for retrieval of the recorded information, for the CVR as well as the DLR;
      (effective 2019/05/29)
    • (iii) A maintenance plan; and
    • (iv) Two copies of the operating, servicing, and maintenance instructions.

      Information note:

      If a Supplement to the Aircraft Flight Manual or equivalent publication is produced, it must be submitted to Transport Canada for approval.

  • (3) Follow on Series CVR Installation

    Each follow on series CVR installation must be subjected to testing to confirm conformity with the data applicable to the initial installation.
    (amended 2009/12/01)

551.102 Terrain Awareness and Warning System (TAWS) and Ground Proximity Warning System (GPWS)
(amended 2009/12/01)

• (a) Introduction

  This section contains standards of airworthiness for installation approval of Terrain Awareness and Warning Systems (TAWS) and Ground Proximity Warning System (GPWS) equipment.
  (amended 2009/12/01)

• (b) Equipment

  • (1) The design standards in the following documents apply:
    (amended 2009/12/01)

    Standard	Criteria for Acceptance for Installation
    Current - as contained in Chapter 537:
    CAN-TSO-C151b (amended 2009/12/01)	Acceptable, provided the conditions of (b)(3) are met. (amended 2009/12/01)
    Current - as contained in Chapter 537:
    CAN-TSO-C92c (amended 2009/12/01) CAN-TSO-C151a (amended 2009/12/01)	Acceptable Acceptable, provided the conditions of (b)(3) are met. (amended 2009/12/01)
    CAN-TSO-C92b (amended 2009/12/01)	Acceptable, provided the equipment has been approved for the installation in the subject aircraft prior to 26 April 1988 and the operator demonstrates that the equipment is compatible with the aircraft in which it is installed and the operating environment. (amended 2009/12/01)
    CAN-TSO-C92a (amended 2009/12/01)	Acceptable, provided the equipment has been approved for installation in the subject aircraft prior to 26 April, 1988 and the operator demonstrates that the equipment is compatible with the aircraft in which it is installed and the operating environment. (amended 2009/12/01)

  • (2) Ground Proximity Warning Systems (GPWS) must be installed to provide for the following warning envelopes as specified in section 2.1 of Radio Technical Commission for Aeronautics (RTCA) document DO-161A, Minimum Performance Standards - Airborne Ground Proximity Warning Equipment, revised 27 May 1976:
    (amended 2009/12/01)

    • (i) excessive rate of descent with respect to terrain (Mode 1);

    • (ii) excessive closure rate to terrain (Mode 2);

    • (iii) negative climb rate or altitude loss before acquiring 213 meters (700 feet) terrain clearance after take off or missed approach (Mode 3); and

    • (iv) flights above terrain with less than 152 meters (500 feet) terrain clearance while the aeroplane is not in landing configuration (Mode 4).

  • (3) Terrain Awareness Warning System (TAWS) Altitude Accuracy must meet the alerting criteria of CAN-TSO-C151a or later version:
    (amended 2009/12/01)

    • (i) without any pilot action or input;
      (amended 2009/12/01; no previous version)

    • (ii) independent of altimeter setting on the altimeter(s); and
      (amended 2009/12/01)

    • (iii) independent of temperature and pressure deviations from the International Standard Atmosphere (ISA).
      (amended 2009/12/01)

      Information note:

      The Altitude Accuracy requirements of (b)(3) will become a certification requirement for all installations, at the same time that they become an operational requirement under CAR Part VI or Part VII. It is recommended, but not required, that certifications before that date, meet these Altitude Accuracy requirements. Information regarding the Vertical Position Source provided in FAA Advisory circular AC 23-18 and AC 25-23 is superseded by the requirement in (b)(3).
      (amended 2009/12/01)

• (c) Optional Functions

  • (1) An installed Ground Proximity Warning System (GPWS) may also:

    • (i) provide a warning envelope for deviation from an instrument glide path (Mode 5, section 2.6 of DO-160A document);

    • (ii) include a guarded and witness wired switch inhibiting the operation of the entire system; and

    • (iii) include a guarded switch inhibiting only the Mode 4 warnings for flap positions other than normal landing flap.

  • (2) An installed Terrain Awareness and Warning System (TAWS) may also provide optional features as specified in CAN-TSO-C151a (or later version).
    (amended 2009/12/01)

551.103 Transponder and Automatic Pressure Altitude Reporting Equipment (effective 2023/07/17)

• (a) Introduction (effective 2023/07/17)

  This section contains standards of airworthiness for installation approval of Transponder and Automatic Pressure Altitude Reporting Equipment, including ADS-B Out capable equipment, as required by CAR 605.35.

  Information note: (effective 2023/07/17)

  Because the implementation of the ADS-B Out policy is made via a Mode S transponder-based equipment, the standards for the ADS-B Out capable equipment have been added to this section and support the operating rule policy direction.

• (b) Definitions (effective 2023/07/17)

  In this section,

  “Automatic Dependent Surveillance - Broadcast Out (ADS-B Out) equipment” means equipment that broadcasts aircraft information automatically without intervention from the flight crew or external interrogation ("automatic") to receiving equipment for the purpose of Air Traffic Services (ATS) surveillance or to other ADS-B receivers. The information transmitted is dependent on source systems on the aircraft ("dependent").

  “Initial installation” means the first installation of a particular type of ADS-B Out equipment and associated position source equipment (ADS-B Out System) in an aircraft of a particular type and model.

• (c) Equipment (effective 2023/07/17)

  The design standards in the following documents apply:

  • (1) Transponders (effective 2023/07/17)

    Standard	Criteria for Acceptance for Installation
    As contained in Chapter 537: CAN-TSO C74c	Acceptable
    Other: CAN-TSO C74b	Acceptable

  • (2) Automatic Pressure Altitude Reporting Equipment (effective 2023/07/17)

    Standard	Criteria for Acceptance for Installation
    As contained in Chapter 537: CAN-TSO C88a	Acceptable
    Other: CAN-TSO C88	Acceptable

  • (3) ADS-B Out Capable Equipment (effective 2023/07/17)

    Standard	Criteria for Acceptance for Installation
    As contained in Chapter 537: CAN-TSO-C166b or later	Acceptable for new or existing ADS-B Out equipment installations provided the equipment is a transmitter or transmitter/receiver: Class A1, A2, A3 or B1; or Class A1S or B1S subject to demonstration requirements per paragraph (d)(4)(ii) and the equipment is based on a Mode S transponder compliant with the requirements of CAN-TSO-C112 or later revision

    Information note: (effective 2023/07/17)

    In this section, Class A1S and B1S ADS-B Out equipment is understood as equipment that does not meet the transmitting diversity operation requirements of Class A1/A2/A3 and B1, including, but not limited to, installations containing a single antenna mounted at the bottom, a single antenna mounted at the top, a single antenna mounted elsewhere on the fuselage, or dual antennas mounted anywhere on the aircraft that do not transmit alternately.

    Information note: (effective 2023/07/17)

    Like all other equipment capable of transmitting or receiving radio or navigation signals, ADS-B equipment must also be approved by the Spectrum Management and Telecommunications Sector of Innovation, Science and Economic Development Canada (ISED), with respect to the “Radio-communication Act”. The details are contained in the Radio Standards Procedure, RSP-100 that can be obtained from ISED.

• (d) Installation (effective 2023/07/17)

  The following installation standards apply to ADS-B Out equipment as defined in paragraph (c) (3).

  Information note: (effective 2023/07/17)

  Although no installation standards are specified in this section for other transponder and automatic pressure altitude reporting equipment type, section 551.03 requires that the installation of equipment meet the applicable standards of the certification basis of the aircraft.

• (1) Parameters: (effective 2023/07/17)

  The ADS-B Out equipment shall broadcast the parameters providing the following essential information as a minimum:

  1. International Civil Aviation Organization (ICAO) 24-bit aircraft address;
  2. Surface horizontal position (latitude and longitude);
  3. Transponder IDENT when in use;
  4. Emergency/Priority status;
  5. Aircraft Identification (Flight identification or aircraft registration number/marking);
  6. Airborne horizontal position (latitude and longitude);
  7. Barometric pressure altitude;
  8. ADS-B emitter category;
  9. Geometric altitude (GNSS height);
  10. Horizontal velocity (airborne and on the ground)
  11. Length and width of aircraft;
  12. Mode A code;
  13. Navigation Integrity Category (NIC);
  14. Navigation Accuracy Category for Position (NAC_p);
  15. Navigation Accuracy Category for Velocity (NAC_v)
  16. Source Integrity Level (SIL);
  17. System Design Assurance (SDA);
  18. MOPS version number;
  19. TCAS installed and operational;
  20. TCAS traffic status (if installed);
  21. Selected altitude (if available in a suitable format); and
  22. Barometric pressure setting (if available in a suitable format).

  Information Note: (effective 2023/07/17)

  Refer to the terminology of document RTCA DO-260B for details of the descriptions in the above list.

• (2) Aircraft installation performance requirements for accuracy and integrity (effective 2023/07/17)

  In order to satisfy surveillance requirements, the position data transmitted by the ADS-B Out equipment shall meet the following minimum levels of accuracy and integrity, as applicable:

  • Navigation Accuracy Category for Position: NAC_p = 8
  • Navigation Accuracy Category for Velocity: NAC_v = 1
  • Navigation Integrity Category: NIC = 7
  • Source Integrity Level SIL = 3
  • System Design Assurance: SDA = 2

  The definitions of the accuracy and integrity parameters are those from document RTCA DO-260B.

  Any change in NAC_p, NAC_v, SDA, SIL or NIC shall be broadcast by the ADS-B Out equipment within 12 seconds.

  Information Note: (effective 2023/07/17)

  The accuracy, integrity, and the capacity to detect their changes will depend on the position source equipment interfacing with the ADS-B Out equipment. No requirement specific to the position source equipment is given herein. It will need to be selected so the entire system meets the above noted requirements.

• (3) Signal timing (effective 2023/07/17)

  The ADS-B Out equipment shall be installed and integrated with the position source equipment so that it meets the following timing requirements:

  Total latency: The ADS-B Out equipment shall transmit the aircraft’s geometric position and velocity no later than 2.0 seconds from the time of measurement by the position source equipment to the time of transmission by the antenna of the ADS-B Out system.

  Information note: (effective 2023/07/17)

  The aircraft can compensate for the latency of position data by extrapolating the measured geometric position to the time of transmission. The amount of latency that remains after compensation is uncompensated latency.

  The uncompensated latency of the aircraft's position transmitted by the ADS-B Out equipment shall not exceed 0.6 second.

  Overcompensation shall be limited to 200 ms maximum, i.e. the position extrapolation cannot result in a transmitted position that is ahead of the aircraft by more than 200 ms.

  The equipment shall transmit updated aircraft’s geometric position and velocity based on new source data at least once per second while airborne or moving on the ground.

  The equipment shall transmit updated aircraft’s geometric position and velocity based on new source data at least once every 5 seconds while stationary on the ground.

  Information note: (effective 2023/07/17)

  The latency will partially depend on the position source equipment interfacing with the ADS-B Out equipment. No requirement specific to the position source equipment is given herein. It will need to be selected so the entire system meets the above noted requirements.

• (4) Antenna installation (effective 2023/07/17)

  The antennas of the ADS-B equipment shall be installed so that:

  1. For Class A1, A2, A3 or B1 installed equipment, they comply with all antenna installation requirements specified in section 3.3 of RTCA DO-260B for a diverse installation and they transmit alternately towards the bottom and the top of the aircraft per the requirements specified in section 2.2.13.6 of RTCA DO-260B (“transmitting diversity”); or
  2. For Class A1S or B1S installed equipment, they comply with antenna installation requirements specified in section 3.3 of RTCA DO-260B for single antennas and it can be demonstrated that the equipment transmits satisfactorily to ground-based as well as space-based receiver in the normal aircraft operating envelope.

  Information note: (effective 2023/07/17)

  Compliance with these requirements may result in the necessity to have multiple antennas and antenna diversity, i.e. antennas mounted at both the bottom and top of the aircraft. Antenna diversity is not a requirement in itself but is expected to be an outcome of the requirement in most installation scenarios.

• (5) Testing (effective 2023/07/17)

  Each initial installation of an ADS-B Out equipment/system must be tested in the aircraft in which it is installed to demonstrate compliance with the requirements of paragraphs (d)(1) and, for Class A1S or B1S equipment, the requirements of paragraph (d)(4)(ii) of this section.

551.104 Emergency Locator Transmitter

• (a) Introduction

  This section contains standards of airworthiness for 406 MHz Emergency Locator Transmitter (ELT) equipment, as well as 406 MHz beacon coding protocols requirements, and for installation approval of Emergency Locator Transmitter (ELT) equipment required by section 605.38 of the CARs.
  (effective 2020/11/25)

• (b) Equipment Performance and Environmental Standards
  (effective 2020/11/25)

  (deleted 2020/11/25)

  • (1)
    (deleted 2020/11/25)

  • (2)
    (deleted 2020/11/25)

  • The design standards in the following documents apply with respect to ELTs and their batteries. The specified CAN-TSO standards are to be considered as interchangeable with their corresponding FAA TSO standards.
    (effective 2020/11/25)

    Standard	Criteria for Acceptance for Installation
    Current: (effective 2020/11/25)
    CAN-TSO-C126b, or later amendment (effective 2020/11/25)	Acceptable for new and existing installations, provided there is: (1) an integrated 121.5 MHz transmission as described in RTCA/DO-204A, or later revision; and (2) the ELT must have obtained a COSPAS-SARSAT type approval certificate. (effective 2020/11/25)
    Other: (effective 2020/11/25)
    CAN-TSO-C126a (effective 2020/11/25)	Acceptable for existing installations, provided there is: (1) an integrated 121.5 MHz transmission as described in RTCA/DO-204A; and (2) the ELT must have obtained a COSPAS-SARSAT type approval certificate. (effective 2020/11/25)
    CAN-TSO-C126 (effective 2020/11/25)	Acceptable for existing installations, provided there is: (1) a 121.5 MHz transmission, as stated in section (e)(2) of FAA TSO-C126 or an additional transmitter compliant with FAA TSO C91a; (2) if a lithium sulphur dioxide (LiSO2) battery is used, the battery must meet FAA TSO-C142, or later amendment; and (3) the ELT must have obtained a COSPAS-SARSAT type approval certificate. (effective 2020/11/25)

• (c) ELT Battery
  (amended 2005/12/01)

  • (1) An approved battery is any battery or battery pack designed for installation in a specific ELT that, with the specified battery or battery pack installed, complies with the requirements of paragraph (b).

  • (2) Each approved battery pack must be permanently and legibly marked with the type, model, and part number, and ELT type and model for which it has been approved.
    (amended 2009/12/01)

    (deleted 2020/11/25)

  • (3) Each ELT unit must be permanently and legibly marked with at least the type, model and part number of the battery or battery pack used to demonstrate initial compliance with the applicable performance and environmental standards, and may be marked with information concerning alternate approved batteries.
    (amended 2009/12/01)

  • (4) For each approved battery or battery pack, except for those essentially unaffected during probable storage intervals, the useful life and expiration date must be established as follows:
    (amended 2009/12/01)

    • (i) the useful life is the length of time after its date of manufacture or recharge that the battery or battery pack may be stored under normal environmental conditions without losing its ability to allow the ELT to meet the applicable performance standards of paragraph (b); and

    • (ii) the expiration date is the date of battery manufacture or recharge plus one half of its useful life.

  • (5) Either the expiration date or the date of manufacture or recharge and the useful life must be permanently and legibly marked on all ELT batteries.
    (amended 2009/12/01)

  • (6) The battery or battery pack expiration date must be permanently and legibly marked on the outside of the ELT case.
    (amended 2009/12/01)

  • (7) [Reserved]
    (deleted 2020/11/25)

• (d) [Reserved]
  (deleted 2020/11/25)

  • (1)

    • 1.

    • 2.

    • 3.

    • 4.

    • 5.

    • 6.
      (deleted 2020/11/25)

  • (2)

    • 1.

    • 2.
      (deleted 2020/11/25)

• (e) [Reserved]
  (amended 2005/12/01)

• (f) Requirements for New Installation/Design Approval
  (effective 2020/11/25)

  Information Note: The types of ELTs are defined in the minimum performance standards of the applicable TSO / CAN-TSO. The types are limited to Automatic Fixed (AF), Automatic Portable (AP), Automatic Deployable (AD), Survival (S) and Distress Tracking (DT).
  (effective 2020/11/25)

  In addition to the applicable certification basis for the aircraft upon which the ELT is to be installed, the following apply:
  (effective 2020/11/25)

  • (1) Where a small aircraft is to carry passengers on a flight for which an ELT is required, a readily visible placard or equivalent means must be installed in each passenger cabin to inform passengers of the location and operation of the ELT.
    (effective 2020/11/25)

  • (2) Each ELT must be installed in accordance with the manufacturer’s installation instructions.

    Information Note: ELT manufacturer’s installation instructions are intended to be generally applicable to any aircraft. It is acknowledged that installers integrating ELTs under an installation design approval may have installations that do not directly follow the ELT manufacturer’s instructions; such installations would have been assessed within the certification basis of the design approval at the aircraft level. Applicants for a design approval at the aircraft level for the installation of an ELT may develop installation instructions that are most appropriate for their aircraft configuration, having considered the ELT manufacturer’s installation instructions. Additional guidance on ELT installation can be found in FAA Advisory Circular (AC) 91-44, as amended.
    (effective 2020/11/25)

  • (3) Except where otherwise stated in the manufacturer’s installation instructions, the following requirements apply to type AF, AP or AD ELT installations in aeroplanes and helicopters:
    (effective 2020/11/25)

    • (i) Except for ELTs of type AD when installed in an aeroplane, if the ELT is equipped with a unidirectional crash activation sensor, the ELT must be mounted with its sensitive axis pointing in the direction of flight.
      (effective 2020/11/25)

    • (ii) Except for ELTs of type AD when installed in a helicopter, if the ELT is equipped with a unidirectional crash activation sensor, the ELT must be mounted with its sensitive axis pointing approximately 45 degrees downward from the normal forward direction of flight.
      (effective 2020/11/25)

    • (iii) [Reserved]
      (deleted 2020/11/25)

    • (iv) The location chosen for the ELT must be sufficiently free from vibration to prevent involuntary activation of the transmitter.
      (amended 2009/12/01)

    • (v) ELTs must be located and mounted so as to minimise the probability of damage to the transmitter and antenna in the event of a crash impact. For aeroplane installations, fixed and deployable automatic type transmitters must be attached to the aeroplane as far aft as practicable.
      (effective 2020/11/25)

    • (vi) The ELT must be accessible for manual activation and deactivation. If it is equipped with an antenna for portable operation, the ELT must be easily detachable from inside the aircraft.
      (amended 2009/12/01)

    • Information Note: In the case of ELTs installed away from the cockpit (i.e. have a remote control panel), the ELTs still need to be accessible for maintenance purposes (e.g. running built-in-tests).
      (effective 2020/11/25)

    • (vii) [Reserved]
      (deleted 2020/11/25)

    • (viii) The ELT must not use the antenna of another avionics system.
      (amended 2009/12/01)

    • (ix) The external antenna location must be chosen considering the following factors:
      (amended 2009/12/01)

      • (A) The ELT antenna must be mounted as far away as possible from other Very High Frequency (VHF) antennas. (amended 2009/12/01)
      • (B) The distance between the transmitter and antenna must be in accordance with the ELT manufacturer's installation instructions or other approved data.
      • (C) The position of the antenna must be such as to ensure essentially omni-directional radiation characteristics when the aircraft is in its normal ground or water attitude. (amended 2009/12/01)
      • (deleted 2020/11/25)
    • (x) The ELT antenna must not foul other antennas in flight. (amended 2009/12/01)
    • (xi) The ELT must be subjected to an operational test as specified in Appendix G, of Standard 571.
      (amended 2009/12/01)

  • (4) ELTs of Types S

    • (i) Where the table to subsection 605.38(2) of the CARs requires the carriage of one ELT of Type S, unless attached to a life raft, the ELT must be easily accessible in the event of a ditching without appreciable time for preparatory procedures. The equipment must be installed in a conspicuously marked location.
      (effective 2020/11/25)

    • (ii) Where the table to subsection 605.38(2) of the CARs requires the carriage of a second ELT of type S, that ELT must be either located near a life raft pack, or attached to a life raft in such a way that it will be available or retrievable when the life raft is inflated.
      (effective 2020/11/25)

    • (deleted 2020/11/25)

  • (5) Transmitter Remote Control

    Where the ELT system includes a remote control system for activating and deactivating the transmitter, provision must be made to prevent inadvertent operation of the remote control and a placard displaying the intent of the following warning must be placed near each remote control:
    (effective 2020/11/25)

    "For Aviation Emergency Use Only.
    Unauthorized Operation Prohibited."

  • (6) Battery Charging System

    Where ELT batteries can be charged during flight, provision must be made to:
    (amended 2009/12/01)

    • (i) indicate to the flight crew that charging is taking place; and

    • (ii) prevent battery discharge resulting from wiring short circuits occurring during normal service or from crash damage.

  • (7) Each ELT unit must be labelled with its 24-bit address.
    (effective 2020/11/25)

  • (8) Instructions for continued airworthiness must be established and furnished with each installation, and must include as a minimum: details of approved batteries and sources of supply; battery replacement or recharge instructions; battery capacity test procedures, if applicable; transmission or functional test procedures; procedures necessary to accomplish the performance tests specified in Appendix G of Standard 571; and instructions to verify the ELT has been programmed correctly per its type as required in paragraph (g) is this section.
    (effective 2020/11/25)

  • Information Note: Approval by other agencies. ELTs, as radio equipment, require certification to Innovation, Science and Economic Development Canada’s (ISED) (formerly Industry Canada) Spectrum Management and Telecommunications Radio standards and specifications. It is the responsibility of the ELT manufacturer to obtain certification of the radio equipment to ISED’s standards and specifications. Once ISED certification is granted, the ELT will be listed on their Radio Equipment List (REL). The applicant for ELT installation approval should consult the REL to ensure that certification of the radio equipment has been obtained.
    (effective 2020/11/25)

• (g) 406 MHz Beacon Coding Protocols and Registration
  (effective 2020/11/25)
  • (1) All 406 MHz ELTs must be coded using the following coding protocols:
    (effective 2020/11/25)
    • (i) An ELT that is able to determine its own location must be coded as follows:
      (effective 2020/11/25)

      • (A) in the case of an ELT of type AF, AP, AD or DT, using the Standard Location Protocol and the aircraft 24-bit address, assigned to the aircraft by Transport Canada when registering the aircraft, to uniquely identify the ELT;
        (effective 2020/11/25)

        Information Notes:

        • (a) The aircraft 24-bit address is currently being used in other airborne systems such as TCAS, and provides the advantage of uniquely identifying the airframe in addition to the ELT.
        • (b) If the ELT does not interface with a Global Positioning System (GPS) or any other navigation source equipment, the ELT should be reprogrammed as though it is an ELT that is not able to determine its own location, in accordance with (g)(1)(b) below. Otherwise, the search and rescue (SAR) response to the ELT distress signal could be delayed. (effective 2020/11/25)
      • (B) in the case of an ELT of type S, using the Standard Location Protocol and unique serial number assigned to the ELT by the ELT manufacturer and the COSPAS-SARSAT beacon type approval certificate number to uniquely identify the ELT; (effective 2020/11/25)
    • (ii) an ELT that is not able to determine its own location, must be coded as follows:
      • (A) in the case of an ELT of type AF, AP or AD, using the Serial User Protocol coded with the 24-bit binary aircraft identification assigned to the aircraft by Transport Canada when registering the aircraft to uniquely identify the ELT;
      • (B) in the case of an ELT of type S, using the Serial User Protocol with a unique Beacon Serial Number; (effective 2020/11/25)

        Information Note: This protocol allows the unique identification of each Type S ELT when more than one ELT of this type are to be carried on an aircraft.
        (effective 2020/11/25)

    • (iii) the country code must reflect the state in which the aircraft is registered. (effective 2020/11/25)
  • (2) Each 406 MHz ELT installed on a Canadian-registered aircraft must:
    • (i) be registered with the Canadian Beacon Registry; and
    • (ii) in the case of a change of aircraft ownership, aircraft registration, and/or emergency contact information, any required changes to the 406 MHz ELT coded information must be completed, and the Canadian Beacon Registry so advised. (effective 2020/11/25)

    • Information Note: The Canadian Beacon Registry for 406 MHz beacons is located in Trenton, Ontario at the Canadian Mission Control Centre and the contact information is as follows:

      • online at https://www.cbr-rcb.ca/cbr/presentation/other_autre/index.php?lang=en

      • by e-mail: cbr@sarnet.dnd.ca

      • by fax: 1-877-406-FAX8 (3298)

      • by telephone: 1-877-406-SOS1 (7671)

      • by mail:
        Canadian Beacon Registry
        CFB Trenton, P.O. Box 1000 Stn Forces
        Astra, Ontario K0K 3W0
        (effective 2020/11/25)

551.105 Altitude Alerting System

• (a) Introduction

  This section contains standards of airworthiness for installation approval of Altitude Alerting Systems or devices required by CAR 605.36.

• (b) Installation

  Each altitude alerting system or device must be able to:
  (amended 2009/12/01)

  • (1) alert the pilot upon approaching a preselected altitude in either ascent or descent, by a sequence of:

    • (i) both aural and visual signals in sufficient time to establish level flight at that preselected altitude; or

    • (ii) visual signals in sufficient time to establish level flight at that preselected altitude, and when deviating above and below that preselected altitude, by an aural signal;

  • (2) provide the required signals from sea level to the highest operating altitude approved for the aircraft in which it is installed;

  • (3) preselect altitudes in increments that are commensurate with the altitudes at which the aircraft is to be operated;

  • (4) be tested without special equipment to determine proper operation of alerting signals; and

  • (5) accept necessary barometric pressure settings if the system or device operates on barometric pressure.

Information note:

551.106 Thunderstorm Detection and Weather Radar Equipment

• (a) Introduction

  This section contains standards of airworthiness for installation approval of thunderstorm detection and weather radar equipment required by CAR 703.65, 704.64 and 705.70.

• (b) Equipment

  The design standards in the following documents apply:
  (amended 2009/12/01)

  Standard	Criteria for Acceptance for Installation
  Current - as contained in Chapter 537: CAN-TSO-C63c (amended 2009/12/01) CAN-TSO-C110a (amended 2009/12/01)	Acceptable Acceptable
  Other: Weather radar systems installed prior to the issue of CAN-TSO-C63c, 18 August, 1983 (amended 2009/12/01) Thunderstorm detection systems installed prior to the issue of CAN-TSO-C110a, 26 October, 1988 (amended 2009/12/01)	May remain in use May remain in use

• (c) Installation

  Information note:

  Although no installation standards are specified in this section, section 551.03 requires that the installation of equipment meet the applicable standards of the certification basis of the aircraft.
  (amended 2009/12/01)

551.107 Radiocommunication Equipment
(amended 2005/12/01)

Information notes:
(amended 2005/12/01)

551.108 Radio Navigation Equipment
(amended 2005/12/01)

Information notes:
(amended 2005/12/01)

551.109 to 551.199 Reserved
(amended 2005/12/01)

Subchapter D
Electrical Systems

551.200 Electrical Power System

• (a) Introduction

  This section contains standards of airworthiness for loading of the aircraft electrical power system.

• (b) Electrical Power System Loading

  • (1) The continuous load which may be placed on an electrical power source is dependent upon the configuration of the electrical system and must be determined as follows:
    (amended 2009/12/01)

    • (i) For aircraft without a loadmeter in the electrical power system feeders, the total continuous load under worst case conditions must be no greater than 80% of the rated electrical power source capacity.
      (amended 2009/12/01)

      Information note:

      The remaining 20% of the capacity is reserved for charging the aircraft battery system and for intermittent loads.

    • (ii) For aircraft with a loadmeter in the electrical power system feeders, total continuous load may be up to 100% of the rated generator capacity.

      Information note:

      With a loadmeter available, it is assumed that the flight crew is able to monitor the electrical load and adjust it to safe levels, if necessary.

  • (2) Electrical power sources must be able to furnish the required power at the proper voltage to each load circuit. Compliance must be shown, to account for the electrical loads applied to the electrical system in probable combinations and for probable durations, by:

    • (i) Electrical load analysis, if an analysis was a requirement for the initial certification of the aircraft type; or

    • (ii) Where an electrical load analysis was not a requirement for the initial certification of the aircraft type:

      • (A) By electrical load analysis; or

      • (B) By direct measurement of the electrical loads.

551.201 Battery

• (a) Introduction

  This section contains standards of airworthiness for battery capacity.

• (b) Battery Capacity

  Where a battery is required to provide emergency electrical power, the battery must have sufficient capacity to meet the emergency load demand in the event of a total generated power supply failure, for the period of time specified in the certification basis of the aircraft.
  (amended 2009/12/01)

Information note:

551.202 to 551.299 Reserved

Subchapter E
Powerplant Systems

551.300 to 551.399 Reserved

Subchapter F
Emergency Equipment

551.400 Hand-Held Fire Extinguisher

• (a) Introduction

  This section contains standards of airworthiness for Hand-Held Fire Extinguishers required by Parts VI and VII of the CARs.
  (amended 2009/12/01)

  Information note:

  As required by Parts VI and VII of the CARs, hand-held fire extinguishers must contain a type and quantity of extinguishing agent suitable for the kinds of fires likely to occur in the compartment where the extinguisher is intended to be used. For crew and passenger compartments, hand-held fire extinguishers must be designed to minimize the hazard of toxic gas concentrations.
  (amended 2009/12/01)

  Refer to FAA Advisory Circular AC 20-42C, dated 7 March 1984, as amended from time to time as an acceptable guidance regarding the different types of extinguishers, minimum capacities, and hazards of toxic gas concentration.
  (amended 2005/12/01)

• (b) Equipment

  The design standards in the following documents apply:
  (amended 2009/12/01)

  Standard	Criteria for Acceptance for Installation
  Current - as contained in Chapter 537: CAN-TSO-C19b (amended 2009/12/01)	Acceptable
  Other: Approved by Underwriters Laboratories of Canada, bearing ULC approval label Approved by the British Civil Aviation Authority (BCAA) for aircraft use Approved by the Federal Aviation Administration (FAA) for aircraft use. Includes extinguishers approved to CAN-TSO-C19b (amended 2009/12/01) Approved by Underwriters Laboratories Inc. (U.L.), Factory Mutual Research Corporation to specification U.L. 1093 (construction and operation), and to specification U.L. 711 (rating and testing) Approved by U.S. Coastguard under title 46 of the U.S. Code of Federal Regulations, for use in aircraft Approved for aircraft use by the airworthiness authority of any country, whose standards are accepted by the Minister	Acceptable Acceptable Acceptable Acceptable Acceptable Acceptable

• (c) Installation

  The installation of hand-held fire extinguishers must be such that when properly secured in its mounting:
  (amended 2009/12/01)

  • (1) the extinguisher will remain secure when subjected to the ultimate inertia loads established by the aircraft certification basis of the aircraft, but not less than the following ultimate load factors:
    (amended 2009/12/01)

    Load Factors	Aeroplanes	Rotorcrafts
    forward	9.0	4.0
    sideward	1.5	2.0
    upward	2.0	1.5
    downward	4.5	4.0

  • (2) the extinguisher will have a "quick release" function to enable easy removal from its mount.

• (d) Identification and Marking

  • (1) The hand-held fire extinguisher must be identified and marked with the applicable specifications as determined by the approving authority per paragraph (b).
    (amended 2009/12/01)

  • (2) A stowage compartment or stowage container that contains a hand held fire extinguisher must be clearly marked as to its contents.
    (amended 2009/12/01)

551.401 Life Saving Equipment Over Water - Life Preservers

• (a) Introduction

  This section contains standards of airworthiness for Life Preservers required by section 602.62 and referred to in section 703.83 of the CARs.
  (effective 2021/05/24)

• (b) Definition

  In this section, a "life preserver" is a flotation device, which when properly worn by a person, will provide adequate buoyant force to support the body in a safe and stable position in water and provide a self-righting force to maintain the face above the water; (gilet de sauvetage).

• (c) Equipment

  The design standards in the following documents apply:
  (amended 2009/12/01)

  Standard	Criteria for Acceptance for Installation
  Current - as contained in Chapter 537:
  CAN-TSO-C13g or later amendment (effective 2021/05/24)	Acceptable Information note: This standard includes several life preserver design categories, each one intended for a different weight range segment, which together fulfill the needs of persons of any weight. (effective 2021/05/24)
  Other:
  CAN-TSO-C13f (effective 2021/05/24)	Acceptable Information note: This standard includes several life preserver design categories, each one intended for a different weight range segment, which together fulfill the needs of persons of any weight. (effective 2021/05/24)
  CAN-TSO-C13e (amended 2009/12/01)	Acceptable Information note: This standard includes several life preserver design categories, each one intended for a different weight range segment, which together fulfill the needs of persons of any weight. (effective 2021/05/24)
  CAN-TSO-C13d (amended 2009/12/01)	Acceptable Information note: This standard includes several life preserver design categories, each one intended for a different weight range segment, which together fulfill the needs of persons of any weight. (effective 2021/05/24)

• (d) Installation

  Information note:

  Although no installation standards are specified in this section, section 551.03 requires that the installation of equipment meet the applicable standards of the certification basis of the aircraft.
  (amended 2009/12/01))

551.402 Life Saving Equipment Over Water - Individual Flotation Devices (IFD)
(amended 2009/12/01)

• (a) Introduction

  This section contains standards of airworthiness for Individual Flotation Devices (IFDs) required by section 602.62 and referred to in section 703.83 of the CARs.
  (effective 2021/05/24)

• (b) Definition

  In this section, an "Individual Flotation Devices" is a flotation device, which when used by a person, will provide an additional buoyant force to assist in supporting the body in water.

• (c) Equipment

  The design standards in the following documents apply:
  (amended 2009/12/01)

  Standard	Criteria for Acceptance for Installation
  Current - as contained in Chapter 537:
  CAN-TSO-C72c or later amendment (effective 2021/05/24)	Acceptable Information note: This standard is applicable to individual flotation devices adaptable for children as well as adults. (effective 2021/05/24)
  Other:
  CAN-TSO-C72b (amended 2009/12/01)	Acceptable Information note: This standard is applicable to individual flotation devices adaptable for children as well as adults. (effective 2021/05/24)
  CAN-TSO-C72a (amended 2009/12/01)	Acceptable Information note: This standard is applicable to individual flotation devices adaptable for children as well as adults. (effective 2021/05/24)
  CAN-TSO-C72 (amended 2009/12/01)	Acceptable Information note: This standard is applicable to individual flotation devices adaptable for children as well as adults. (effective 2021/05/24)

• (d) Installation

  Information note:

  Although no installation standards are specified in this section, section 551.03 requires that the installation of equipment meet the applicable standards of the certification basis of the aircraft.
  (amended 2009/12/01)

551.403 Life Saving Equipment Over Water - Personal Flotation Devices (PFD)
(effective 2021/06/04)

• (a) Introduction

  This section contains standards of airworthiness for Personal Flotation Devices (PFDs) required by section 602.62 and referred to in section 703.83 of the CARs.
  (effective 2021/06/04)

• (b) Definition

  In this section, a "Personal Flotation Devices" is a flotation device other than a life preserver or individual flotation device.

• (c) Equipment

  The design standards in the following documents apply:

  Standard	Criteria for Acceptance for Installation
  Current :
  ANSI/CAN/UL-12402-5:2015, Personal Flotation Devices – Part 5: Buoyancy Aids (Level 50) – Safety Requirements, First Edition, dated December 31, 2015, or later amendment. (effective 2021/05/24)	Acceptable, provided that the PFD has a performance level of Level 70, is not made of inherently buoyant material and is fitted with a manual only inflator. Information note: This standard is for PFDs for persons weighing 15 kg or more. (effective 2021/05/24)
  UL 1180, Fully Inflatable Recreational Personal Flotation Devices, Second Edition, dated February 13, 2009, or later amendment. (effective 2021/05/24)	Acceptable, provided that the PFD meets the level of performance of a Type III and is fitted with a manual only inflator and modified as per TP 14475, Edition 1, Chapter II, section 2.6.4. Information note: This standard is for PFDs for persons weighing 36 kg or more. (effective 2021/05/24)
  Other — If inflatable flotation devices are not required: (effective 2021/05/24)
  CAN/CGSB- 65.11-M88, Personal Flotation Devices, Amendment No. 4, dated January 1997. (effective 2021/05/24)	Acceptable. Information note: This standard is for PFDs for persons weighing 41 kg or more. (effective 2021/05/24)
  CAN/CGSB- 65.15-M88, Personal Flotation Devices for Children, Amendment No. 4, dated January 1997. (effective 2021/05/24)	Acceptable. Information note: This standard is for PFDs for persons weighing from 9 to 41 kg. (effective 2021/05/24)
  CAN/CGSB- 65.11-M88, Personal Flotation Devices, published February 1988 and Amendments Nos. 1 through 3. (effective 2021/06/04)	Acceptable. (effective 2021/06/04)
  CAN/CGSB- 65.15-M88, Personal Flotation Devices for Children, published April 1988 and Amendments Nos. 1 through 3. (effective 2021/06/04)	Acceptable. (effective 2021/06/04)
  CGSB- 65-GP-15M, Standard for: Personal Flotation Devices for Children dated August 1978. (effective 2021/06/04)	Acceptable. (effective 2021/06/04)
  CGSB 65-GP-11, Standard for: Personal Flotation Devices dated October 1972. (effective 2021/06/04)	Acceptable. (effective 2021/06/04)

• (d) Installation

  Information note:

  Although no installation standards are specified in this section, section 551.03 requires that the installation of equipment meet the applicable standards of the certification basis of the aircraft.
  (amended 2009/12/01)

551.404 Life Saving Equipment Over Water - Life Rafts

• (a) Introduction

  This section contains standards of airworthiness for Life Rafts required by CAR 602.63.

• (b) Definition

  In this section, "life raft" means a flotation device that meets the standards specified in Chapter 537 and 551 of the Airworthiness Manual.

• (c) Equipment

  The design standards in the following documents apply:
  (amended 2009/12/01)

  Standard	Criteria for Acceptance for Installation
  Current - as contained in Chapter 537: CAN-TSO-C70a (amended 2009/12/01)	Acceptable
  Other: CAN-TSO-C70 (amended 2009/12/01) CAN-TSO-C12c (amended 2009/12/01)	Acceptable Acceptable

• (d) Installation

  Information note:

  Although no installation standards are specified in this section, section 551.03 requires that the installation of equipment meet the applicable standards of the certification basis of the aircraft.
  (amended 2009/12/01)

551.405 Protective Breathing Equipment (PBE)
(amended 2009/12/01)

• (a) Introduction

  This section contains acceptable standards of airworthiness for Protective Breathing Equipment (PBE) required by Parts VI and VII of the CARs.
  (amended 2009/12/01)

  Information note:

  The operational requirements of CAR VI and VII require protective breathing equipment for two different roles:

  • (1) use of fixed or portable PBE by flight crewmembers (i.e. pilots, flight engineers, etc.) at their assigned duty stations on the flight deck - PBE is easily accessible for immediate use by the flight crew members at their duty stations (Note that per FAR 121.337, the FAA requires that these items of PBE meet TSO-C99 or TSO-C116); and
    (amended 2009/12/01)

  • (2) use of portable PBE by all crewmembers (i.e. not just flight crew but includes flight attendants) when investigating and combating fires throughout the aircraft (Note that per FAR 121.337, the FAA requires that these items of PBE meet TSO C116).

• (b) Definition (From CAR 101)

  "protective breathing equipment" - means equipment designed to cover the eyes, nose and mouth of the wearer, or the nose and mouth where accessory equipment is provided to protect the eyes, and to protect the wearer from the effects of smoke, carbon dioxide or other harmful gases. (inhalateur protecteur)

• (c) Equipment

  The design standards in the following documents apply:
  (amended 2009/12/01)

  Standard	Criteria for Acceptance for Installation
  Current - as contained in Chapter 537: CAN-TSO-C116 (amended 2009/12/01) CAN-TSO-C99 (amended 2009/12/01)	Acceptable Acceptable

• (d) Installation

  Information note:

  Although no installation standards are specified in this section, section 551.03 requires that the installation of equipment meet the applicable standards of the certification basis of the aircraft. In addition, CAR Part VI and VII also specify installation requirements for PBE.
  (amended 2009/12/01)

551.406 Seat Belt and Shoulder Harness

• (a) Introduction

• This section contains standards of airworthiness for Seat Belts and Shoulder Harnesses required by CAR 605.22, 605.24, 702.44, 703.69, 704.68 and 705.75.

  (b) Definition (From CAR 101)

  In this section,

  "safety belt" means a personal restraint system consisting of either a lap strap or a lap strap combined with a shoulder harness, (ceinture de sécurité);

  "shoulder harness" means any device that is used to restrain the upper torso of a person and that consists of a single diagonal upper torso strap or dual upper torso straps; (ceinture-baudrier).

• (c) Equipment

  The design standards in the following documents apply:

  • (1) Subject to (2), the design standards for seat belt and shoulder harness assemblies are as follows:
    (amended 2009/12/01)

    Standard	Criteria for Acceptance for Installation
    Current - as contained in Chapter 537: CAN-TSO-C22g (amended 2009/12/01) CAN-TSO-C114 (amended 2009/12/01)	Acceptable Acceptable
    Other: CAN-TSO-C22f (amended 2009/12/01) Safety belt or shoulder harness assemblies that are currently installed in the specific aircraft and that conform to the original aircraft type design Other Seat Belt or Shoulder Assembly design that is approved or accepted by Transport Canada (e.g. Supplemental Type Certificate, etc.) (amended 2009/12/01)	Acceptable, except for aircraft that have been type certified with a later CAN-TSO standard (e.g. CAN-TSO-C22g) (amended 2009/12/01) Acceptable Acceptable

  • (2) In addition to the design standard specified above, the following must be met:
    (amended 2009/12/01)

    • (i) Applicable CAR Part VI and VII operational requirements;

    • (ii) Each separate part of the safety belt assembly must be permanently and legibly marked as set out in Part II Subpart 1 of the CARs, and with the rated strength of the safety belt.
      (amended 2009/12/01)

    • (iii) Each safety belt must be designed to be used by not more than one occupant at a time;
      (amended 2009/12/01)

    • (iv) The correct method of wearing the safety belt, including the shoulder harness if fitted, must be obvious and convenient;
      (amended 2009/12/01)

    • (v) The design of the shoulder harness must be such that the unlatching of, or the failure of one or both shoulder straps, as applicable, must not affect the integrity of the lap strap portion of the safety belt;
      (amended 2009/12/01)

    • (vi) For safety belts including shoulder harnesses, the latching devices must be designed such that both the shoulder harness and the lap strap portions of the safety belt may be simultaneously released.
      (amended 2009/12/01)

• (d) Installation

  Seat belt and shoulder harness installations are classified as major modifications and must be accomplished in accordance with approved or specified data, as required by CAR Part V, Subpart 71 and Standard 571 of this manual.
  (amended 2009/12/01)

551.407 Aircraft Passenger Transportation Suit Systems
(amended 2005/12/01)

• (a) Introduction
  (amended 2005/12/01)

  This section contains standards of airworthiness for aircraft passenger transportation suit systems to satisfy the requirements of:

  • (1) paragraph 602.63(7)(a) of the CARs for a helicopter passenger transportation suit system; or

  • (2) subparagraph 602.39(b)(iii) of the CARs for hypothermia protection.

• (b) Definition
  (amended 2005/12/01)

  In this section, "Aircraft Passenger Transportation Suit System" means a personal immersion suit system that reduces thermal shock upon entry into cold water, delays onset of hypothermia during immersion in cold water and provides some flotation to minimize risk of drowning, while not impairing the wearer's ability to evacuate from a ditched aircraft.

• (c) Equipment
  (amended 2005/12/01)

  The design standards in the following documents apply to aircraft passenger transportation suit systems:
  (amended 2009/12/01)

  Standard	Criteria for Acceptance for Installation
  Current - (amended 2009/12/01) CAN/CGSB-65.17-99 "Helicopter Passenger Transportation Suit Systems", published December 1999	Acceptable
  Other: CAN/CGSB-65.17-M88 "Helicopter Passenger Transportation Suit Systems", published January 1988	Acceptable

  Information note:

  The above standards do not satisfy the requirements of section 602.62 of the CARs for approved life preservers. It is intended that either a life preserver meeting the life preserver standards of this Chapter be worn with the aircraft passenger transportation suit system, or alternately that the aircraft passenger transportation suit system be certified as complying with the life preserver standards of this Chapter in addition to the above standards.

• (d) Installation / Stowage
  (amended 2005/12/01)

  Information note:

  Although no installation / stowage standards are specified in this section, section 551.03 of the Airworthiness Manual requires that the installation of equipment meet the applicable standards of the certification basis of the aircraft.
  (amended 2009/12/01)

551.408 Crash Axe
(amended 2009/12/01)

• (a) Introduction
  (amended 2009/12/01)

  This section contains standards of airworthiness for a crash axe required by section 705.92 of the CARs.
  (amended 2009/12/01)

• (b) Definition
  (amended 2009/12/01)

  In this section,
  (amended 2009/12/01)

  "Crash axe" means a hand tool to aid aircraft crewmembers in emergencies. The hand tool is to assist crewmembers in penetrating aircraft materials and prying, twisting and cutting jammed items that are impeding the crews' response to an emergency. (Hache de secours)
  (amended 2009/12/01)

• (c) Equipment
  (amended 2009/12/01)

  The design standards in the following documents apply:
  (amended 2009/12/01)

  Standard	Criteria for Acceptance for Installation
  Current: SAE AS5402	Acceptable

• (d) Installation
  (amended 2009/12/01)

  Information note:

  Although no installation standards are specified in this section, section 551.03 of the Airworthiness Manual requires that the installation of equipment meet the applicable standards of the certification basis of the aircraft.
  (amended 2009/12/01)

551.409 to 551.499 Reserved
(amended 2009/12/01)

Subchapter G
Miscellaneous

551.500 Restraint of Carry-On Baggage

• (a) Introduction

  This section contains standards of airworthiness for installation approval of equipment for stowing and restraining of carry-on baggage required by CAR 602.86 and 705.42.

• (b) Equipment designed to stow or restrain carry-on baggage, equipment and cargo, including over-head bins, racks and underseat restraint areas, must meet the applicable standards of the certification basis of the aircraft. In addition, underseat restraint areas must be designed to meet not less than the following ultimate load factors:
  (amended 2009/12/01)

  Load Factors	Aeroplanes	Rotorcrafts
  forward	9.0	4.0
  sideward	1.5	2.0
  upward	2.0	1.5
  downward	4.5	4.0

  Information note:

  • (i) Placarding requirements:

    The maximum weight of the baggage that can be restrained in an area is determined by the design and approved as part of the original certification of the aircraft or as a modification. The certification basis of the aircraft requires that stowage and baggage areas be placarded for the maximum allowed weight. However, Airworthiness Manual Chapter 525, section 525.1557/ FAR Part 25.1557 (Transport Category aeroplanes) allows that underseat compartments designed for the storage of carry on articles weighing not more than 9.1 kg (20 lbs) need not have a loading limitation placard. This may be applied to other aircraft categories as well, as long as the underseat stowage area is designed for the storage of carry on articles weighing not more than 9.1 kg (20 lbs).
    (amended 2009/12/01)

551.501 Child Restraint Systems
(effective 2021/05/24)

• (a) Introduction

  This section contains standards of airworthiness for child restraint systems referred to in section 605.28 of the CARs.
  (effective 2021/05/24)

• (b) Equipment

  • (1) Subject to (2) and (3), the design standards in the following documents apply:
    (amended 2009/12/01)

    Standard	Criteria for Acceptance for Use (effective 2021/05/24)
    Current – as contained in Chapter 537: CAN-TSO-C100c, or later revision (effective 2021/05/24)	See applicable advisory material to CAR 605. (effective 2021/05/24)
    Other: CAN-TSO-C100b (effective 2021/05/24)	See applicable advisory material to CAR 605. (effective 2021/05/24)
    Motor Vehicle Restraint Systems and Booster Seats Safety Regulations, Part 2, CMVSS 213 –"Child Restraint Systems", effective May 12, 2010 or later amendment (effective 2021/05/24)	See applicable advisory material to CAR 605. (effective 2021/05/24)
    Motor Vehicle Restraint Systems and Booster Seats Safety Regulations, Part 3, CMVSS 213.1 - "Infant Restraint Systems" effective May 12, 2010 or later amendment	See applicable advisory material to CAR 605. (effective 2021/05/24)
    Title 49, United States Code of Federal Regulations (49 CFR) part 571, Federal Motor Vehicle Safety Standard, No. 213 "Child Restraint Systems", effective August 5, 2008 or later amendment (effective 2021/05/24)	See applicable advisory material to CAR 605. (effective 2021/05/24)
    United Nations Standard ECE R 44, “Uniform provisions concerning the approval of restraining devices for child occupants of power-driven vehicles (Child Restraint Systems)”, or later revision. (effective 2021/05/24)	When qualified by procedure TÜV/958-01/2001 –“Qualification Procedure for Child Restraint Systems (CRS) for Use in Aircraft”. See applicable advisory material to CAR 605. (effective 2021/05/24)
    United Nations Standard ECE R 129, “Uniform provisions concerning the approval of enhanced Child Restraint Systems used on board of motor vehicles (ECRS)”, or later revision. (effective 2021/05/24)	When qualified by procedure TÜV/958-01/2001 –“Qualification Procedure for Child Restraint Systems (CRS) for Use in Aircraft”. See applicable advisory material to CAR 605. (effective 2021/05/24)
    Australia/New Zealand Standard AS/NZS 1754:2013, “Child restraint systems for use in motor vehicles”, or later revision. (effective 2021/05/24)	See applicable advisory material to CAR 605. (effective 2021/05/24)
    Other foreign standard acceptable to Transport Canada Note: Information on how to proceed to request determination of a standard acceptability can be found in the applicable advisory material. (effective 2021/05/24)	See applicable advisory material to CAR 605. (effective 2021/05/24)

  • (2) Tether straps, as required in automobiles, and as defined in the Motor Vehicle Restraint Systems and Booster Seats Safety Regulations, are not authorized for use in aircraft.
    (effective 2021/05/24)

  • (3) Combination child restraint systems/booster cushions are acceptable only when the internal harness system is installed and all child restraint system labelling requirements are met.
    (effective 2021/05/24)

  • (4) Booster seats are not acceptable for use as child restraint systems.
    (effective 2021/05/24)

  • (5) Infant carriers that consist of a pouch, which holds the infant close to the wearer's body, are not acceptable for use as child restraint systems.
    (effective 2021/05/24)

  • (6) Infant "Belly" or "Loop" belts attached to a seat occupant's safety belt by feeding the occupant's belt segment through a loop on the infant's belt are not acceptable for use as child restraint systems.
    (effective 2021/05/24)

  • (7) A child restraint system installed in an aircraft passenger seat must rely only upon passenger seat lap belts (pelvic restraints) to secure the device to the seat. No passenger seat lap belt may contact the child-occupant of the child restraint system.
    (effective 2021/05/24)

    Information note:

    Additional information, in the form of advisory material, is available on the use and preferred location of child restraint systems, recommended evacuation procedures for occupants of child restraint systems and determination of other foreign standard acceptability.
    (effective 2021/05/24)

• (c) Installation

  Child restraint systems must be installed in a forward facing aircraft passenger seat as per the applicable installation instructions provided by the manufacturer of the child restraint system.
  (effective 2021/05/24)

551.503 to 551.599 Reserved
(amended 2009/12/01)

Standard not yet in force (effective 2023/07/17):