Part V - Airworthiness Manual Chapter 551 - Aircraft Equipment and Installation

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 orPart 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 Superseded by
Section Title
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

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

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

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

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

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

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.

AIRWORTHINESS MANUAL
CHAPTER 551 - AIRCRAFT EQUIPMENT
AND INSTALLATION

(amended 1998/12/01; no previous version)

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; previous version)

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; previous version)

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

(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; the equipment may be approved in a manner set out in section 521.02 of the CARs.
(amended 2009/12/01; previous version)

(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; previous version)

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; previous version)

551.04 to  551.09 Reserved

SUBCHAPTER B
MECHANICAL SYSTEMS

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

(a) General
(amended 2005/12/01; previous version)

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; previous version)

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; previous version)

(c) Installation approval
(amended 2005/12/01; previous version)

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; previous version)

(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; previous version)

(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; previous version)

(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; previous version)

Information Note:

Refer to AC 523-007 for additional advisory material on glider and banner towing.
(amended 2005/12/01; previous version)

551.11 to 551.99   Reserved
(amended 2005/12/01; previous version)

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,

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

“Flight Data Recorder (FDR)” means a system of flight data recording equipment; and

“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.

(c) Equipment

These design standards in the following documents apply:

Standard Criteria for Acceptance for Installation
Current - as contained in Chapter 537:

CAN-TSO C124a
(amended 2009/12/01; previous version)


Acceptable
Other:

CAN-TSO C124
(amended 2009/12/01; previous version)

CAN-TSO C51a
(amended 2009/12/01; previous version)


Acceptable


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; previous version)

(d) Installation

(1) Installation

FDR system installation must be in accordance with 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.
(amended 2009/12/01; previous version)

Information Note:

For normal and transport category rotorcraft, the installation location requirements for non-ejectable record container of an FDR is set out in section 527.1459(b) and 529.1459(b) of Chapter 527 and 529 of the Airworthiness Manual.

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 to CAN-TSO-C124a or CAN-TSO-C124 crash survivability standards.
(amended 2009/12/01; previous version)

(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; previous version)

(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; previous version)

(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; previous version)

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; previous version)

551.101 Cockpit Voice Recorder

(a) Introduction

This section contains standards of airworthiness for installation approval of Cockpit Voice Recorder (CVR) required by CAR 605.33.

(b) Definitions

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)” means a system of flight data recording equipment; and

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

(c) Equipment

The design standards in the following documents apply:

Standard Criteria for Acceptance for Installation
Current - as contained in Chapter 537:

CAN-TSO C123a
(amended 2009/12/01; previous version)



Acceptable
Other:

CAN-TSO C123
(amended 2009/12/01; previous version)

CAN-TSO C 84
(amended 2009/12/01; previous version)


Acceptable


May remain in use for existing installations, approved prior to 1 December 1998 (the date of issue of CAR 551)
(amended 2009/12/01; previous version)

(d) Installation

(1) Installation and Installed Performance

CVR system installation and installed performance must be in accordance with European Organisation for Civil Aviation Equipment (EUROCAE) document ED-56A, “Minimum Operational Requirements for Cockpit Voice Recorder System”, Chapter 6, dated October, 1993. In the event of any conflict between the ED 56A document and the certification basis of the aircraft, the basis of certification applies.
(amended 2009/12/01; previous version)

Information Note:

For normal and transport category rotorcraft, the installation location requirements for record container of a CVR is set out in section 527.1457(e) and 529.1457(e) of Chapter 527 and 529 of the Airworthiness Manual.

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.

It is therefore acceptable to install CVR record containers in forward locations of rotorcraft provided that the recorders are certified to CAN-TSO-C123a or CAN-TSO-C123 crash survivability standards.
(amended 2009/12/01; previous version)

(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 625.33. The tests must be conducted in accordance with the procedures specified in EUROCAE ED-56A.
(amended 2009/12/01; previous version)

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;

Information Note:

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

(ii) For CVRs that utilise solid-state recording media, software documentation including conversion and logic data for retrieval of the recorded information;

(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; previous version)

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

(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; previous version)

(b) Equipment

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

Standard Criteria for Acceptance for Installation
Current - as contained in Chapter 537:

CAN-TSO-C151b
(amended 2009/12/01; previous version)


Acceptable, provided the conditions of (b)(3) are met.
(amended 2009/12/01; previous version)
Current - as contained in Chapter 537:

CAN-TSO C92c
(amended 2009/12/01; previous version)

CAN-TSO C151a
(amended 2009/12/01; previous version)


Acceptable


Acceptable, provided the conditions of (b)(3) are met.
(amended 2009/12/01; previous version)
CAN-TSO C92b
(amended 2009/12/01; previous version)
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; previous version)
CAN-TSO C92a
(amended 2009/12/01; previous version)
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; previous version)

(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; previous version)

(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; no previous version)

(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; no previous version)

(iii) independent of temperature and pressure deviations from the International Standard Atmosphere (ISA).
(amended 2009/12/01; no previous version)

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; no previous version)

(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; no previous version)

551.103 Transponder and Automatic Pressure Altitude Reporting Equipment

(a) Introduction

This section contains standards of airworthiness for installation approval of Transponder and Automatic Pressure Altitude Reporting Equipment as required by CAR 605.35.

(b) Equipment

The design standards in the following documents apply:

(1) Transponders
(amended 2009/12/01; previous version)

Standard Criteria for Acceptance for Installation
Current - as contained in Chapter 537:

CAN-TSO C74c
(amended 2009/12/01; previous version)


Acceptable
Other:

CAN-TSO C74b
(amended 2009/12/01; previous version)


Acceptable

(2) Automatic Pressure Altitude Reporting Equipment

Standards Criteria for Acceptance for Installation
Current - as contained in Chapter 537:

CAN-TSO C88a
(amended 2009/12/01; previous version)


Acceptable
Other:

CAN-TSO C88
(amended 2009/12/01; previous version)


Acceptable

(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; previous version)

551.104 Emergency Locator Transmitter

(a) Introduction

This section contains standards of airworthiness for Emergency Locator Transmitter (ELT) equipment and for installation approval of Emergency Locator Transmitter (ELT) equipment required by section 605.38 of the CARs.
(amended 2005/12/01; previous version)

(b) Performance and Environmental Standards
(amended 2005/12/01; previous version)

The ELT must meet the performance and environmental standards of either:
(amended 2009/12/01; previous version)

(1) CAN-TSO-C91 or CAN-TSO-C91a; or
(amended 2009/12/01; previous version)

(2) CAN-TSO-C126.
(amended 2009/12/01; previous version)

(c) ELT Battery
(amended 2005/12/01; previous version)

(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; previous version)

Information Note:

Refer to Airworthiness Notice B014 for a list of approved batteries and battery packs for ELTs.

(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; previous version)

(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; previous version)

(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; previous version)

(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; previous version)

(7) For a rechargeable battery, the ELT or battery pack manufacturer must establish a battery recharge procedure, a battery capacity test procedure and occurrence frequency, and capacity test acceptance criteria.
(amended 2009/12/01; previous version)

(d) Data Requirements
(amended 2005/12/01; previous version)

(1) To obtain airworthiness approval, the following information is required:

(i) manufacturer’s operating instructions and equipment limitations, containing a statement identifying the type designation as prescribed in the applicable performance and environmental standard;

(ii) recommended installation instructions including preferred installation locations and orientation; applicable schematic diagrams; wiring diagrams; typical transmitter, antenna, and remote switch installation details; and applicable procedures and specifications. The specifications must set forth all limitations, restrictions or other conditions pertinent to the installation;
(amended 2009/12/01; previous version)

(iii) list of components by part number, including any alternate or optional components, that make up the equipment system complying with the applicable performance and environmental standards;

(iv) manufacturer’s test reports substantiating compliance with the applicable performance and environmental standards;

(v) equipment data sheets specifying, within the prescribed range of operating conditions, the actual performance of equipment of the type with respect to each performance factor prescribed in the applicable standard;

(vi) instructions for continued airworthiness, which 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 Standard 571 Appendix G; and for 406 Mhz ELTs, instructions to verify the aircraft 24 bit address or serialized protocol as applicable; and
(amended 2009/12/01; previous version)

(vii) for ELTs approved to the performance and environmental standards of CAN-TSO-C126, a sample COSPAS-SARSAT Registration Form.
(amended 2009/12/01; previous version)

(2) The ELT manufacturer must supply with each unit:
(amended 2009/12/01; previous version)

(i) a copy of the operating instructions and equipment limitations prescribed in (d)(1)(i), the installation instructions prescribed in (d)(1)(ii), equipment data sheets prescribed in (d)(1)(v), and the instructions for continued airworthiness prescribed in (d)(1)(vi), above; and

(ii) for ELTs approved to the performance and environmental standards of CAN-TSO-C126, a COSPAS-SARSAT Registration Form.
(amended 2009/12/01; previous version)

(e) Equipment
(amended 2005/12/01; previous version)

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

Standard Criteria for Acceptance for Installation
Current – As contained in Chapter 537:
(amended 2009/12/01; previous version)

CAN-TSO C91a
(amended 2009/12/01; previous version)



Acceptable, provided the transmission frequency is either 121.5 MHz, or 121.5 MHz and 243.0 MHz.
(amended 2009/12/01; previous version)
CAN-TSO C126
(amended 2009/12/01; previous version)
Acceptable, provided there is a 121.5MHz transmission that meets the requirements of CAN-TSO-C91a, as stated in section (e)(2) of CAN-TSO-C126.
(amended 2009/12/01; previous version)
Other:

CAN-TSO-C91
(amended 2009/12/01; previous version)
 
Radio Standards Specification, RSS-147, Emergency Locator Transmitters Operating at 121.5 MHz or 121.5 MHz and 243.0MHz (Issued by Industry Canada): Acceptable, provided the transmission frequency is either 121.5 MHz, or 121.5 MHz and 243.0 MHz.
(amended 2009/12/01; previous version)
(a) RSS-147, Issue 2 Type F and W units manufactured before April 1, 1982.
(b) RSS-147, Issue 3 Type W units manufactured before April 1, 1982.
(c) RSS-147, Issue 3, as amended by Canada Gazette Part I Public Notice DGTR-015-77 of 17 December 1977.
(amended 2009/12/01; previous version)
Type A, F and W units manufactured after September 30, 1977, but before April 1, 1982.
(d) RSS-147, Issue 3, with modified endurance requirement of 50 hours at -20 degrees C. Type A and F units manufactured before October 1, 1977.

(f) Installation
(amended 2005/12/01; previous version)

(1) Where an aircraft of 5700 kg (12,566 pounds) maximum take-off weight or less 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.
(amended 2009/12/01; previous version)

(2) Types F, AF, AP

Except where otherwise stated, the following requirements apply to type F, AF, AP ELT installations in aeroplanes and helicopters:

(i) When installed in an aeroplane the ELT must be mounted with its sensitive axis pointing in the direction of flight.
(amended 2009/12/01; previous version)

(ii) When installed in a helicopter the ELT must be mounted with its sensitive axis pointing approximately 45 degrees downward from the normal forward direction of flight.
(amended 2009/12/01; previous version)

(iii) The ELT must be installed to withstand ultimate inertia forces of 10g upward, 22.5g downward, 45g forward and 7.5g sideward.
(amended 2009/12/01; previous version)

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

(v) ELTs must be located and mounted so as to minimise the probability of damage to the transmitter and antenna by fire or crushing as a result of crash impact.
(amended 2009/12/01; previous version)

(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; previous version)

(vii) The external surface of the aircraft must be marked to indicate the location of the ELT.
(amended 2009/12/01; previous version)

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

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

(A) The ELT antenna must be mounted as far away as possible from other Very High Frequency (VHF) antennas.
(amended 2009/12/01; previous version)

(B) The distance between the transmitter and antenna must be in accordance with the ELT manufacturer’s installation instructions or other approved data.
(amended 2009/12/01; previous version)

(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; previous version)

(D) The antenna must be mounted as far aft as possible.
(amended 2009/12/01; previous version)

(x) The ELT antenna must not foul other antennas in flight.
(amended 2009/12/01; previous version)

(xi) The ELT must be subjected to an operational test as specified in Appendix G, Chapter 571 of this manual.
(amended 2009/12/01; previous version)

(3) Types W and S

(i) ELTs of type W and S must be installed as specified in (f)(2)(iii) above with a means of quick release, and located as near to an exit as practicable without being an obstruction or hazard to aircraft occupants.
(amended 2009/12/01; previous version)

(ii) Where the table of CAR 605.38 requires the carriage of one ELT of type W or S, that ELT must be readily accessible to passengers and crew; where the carriage of a second type W or S ELT is required, 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 raft is inflated.
(amended 2009/12/01; previous version)

(iii) No ELT with a lithium or magnesium battery must be packed inside a life raft in an aircraft.
(amended 2009/12/01; previous version)

(4) 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 following warning must be placed near each remote control:
(amended 2009/12/01; previous version)

“FOR AVIATION EMERGENCY USE ONLY.
UNAUTHORIZED OPERATION PROHIBITED.”

(5) Battery Charging System

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

(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.

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; previous version)

(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:

For operation below 3,000 feet AGL, the altitude alerting system or device need only provide one signal, either visual or aural. A radio altimeter may be included to provide the signal if the operator has an approved procedure for its use to determine decision height or minimum decent altitude, as appropriate.

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; previous version)

Standard Criteria for Acceptance for Installation
Current - as contained in Chapter 537:

CAN-TSO-C63c
(amended 2009/12/01; previous version)

CAN-TSO-C110a
(amended 2009/12/01; previous version)


Acceptable


Acceptable
Other:

Weather radar systems installed prior to the issue of CAN-TSO C63c, 18 August, 1983
(amended 2009/12/01; previous version)

Thunderstorm detection systems installed prior to the issue of CAN-TSO-C110a, 26 October, 1988
(amended 2009/12/01; previous version)


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; previous version)

551.107 Radiocommunication Equipment
(amended 2005/12/01; previous version)

Information Notes:
(amended 2005/12/01; previous version)

(a) Installation of Radiocommunication equipment required by sections 602.117, 605.14, 605.15, 605.16, 605.18, 605.19, 605.20 and 605.21 of the CARs should be carried out according to manufacturers’ instructions and tested and evaluated using Chapter 5 of FAA Advisory Circular AC 23-8B, as amended from time to time, as guidance.
(amended 2005/12/01; previous version)

(b) In addition, according to section 551.03 of the Airworthiness Manual, the installation of equipment must meet the applicable standards of the certification basis of the aircraft.
(amended 2009/12/01; previous version)

551.108 Radio Navigation Equipment
(amended 2005/12/01; previous version)

Information Notes:
(amended 2005/12/01; previous version)

(a) Installation of Radio navigation equipment required by sections 605.14, 605.15, 605.16 and 605.18 of the CARs should be carried out according to manufacturers’ instructions and tested and evaluated using Chapter 5 of FAA Advisory Circular AC 23-8B, as amended from time to time, as guidance.
(amended 2005/12/01; previous version)

(b) In addition, according to section 551.03 of the Airworthiness Manual, the installation of equipment must meet the applicable standards of the certification basis of the aircraft.
(amended 2009/12/01; previous version)

551.109 to  551.199 Reserved
(amended 2005/12/01; previous version)

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; previous version)

(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; previous version)

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; previous version)

Information Note:

Where no time is specified in the certification basis of the aircraft, it is recommended that 30 minutes flying time would be appropriate depending upon the intended operation of the aircraft.
(amended 2009/12/01; previous version)

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; previous version)

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; previous version)

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; previous version)

(b) Equipment

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

Standard Criteria for Acceptance for installation
Current - as contained in Chapter 537:

CAN-TSO-C19b
(amended 2009/12/01; previous version)


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; previous version)

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; previous version)

(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; previous version)

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; previous version)

(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; previous version)

551.401 Life Saving Equipment Over Water - Life Preservers

(a) Introduction

This section contains standards of airworthiness for Life Preservers required by CAR 602.62.

(b) Definitions

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; previous version)

Standard Criteria for Acceptance for Installation
Current - as contained in Chapter 537:

CAN- TSO-C13f
(amended 2009/12/01; previous version)


Acceptable
Other: CAN-TSO-C13e
(amended 2009/12/01; previous version)

CAN-TSO-C13d
(amended 2009/12/01; previous version)

CAN-TSO-C13c
(amended 2009/12/01; previous version)



Acceptable


Acceptable

To be acceptable, must be demonstrated to meet:

(i) the total buoyancy requirement for an adult life jacket of not less than 15.9 kg;

(ii) gas inflation system must provide a buoyancy of not less than 14.5 kg;

(iii) additional requirement for a survivor locator light.

(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; previous version)

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

(a) Introduction

This section contains standards of airworthiness for Individual Flotation Devices (IFDs) required by CAR 602.62.

(b) Definitions

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; previous version)

Standard Criteria for Acceptance for Installation
Current - as contained in Chapter 537:

CAN-TSO-C72c
(amended 2009/12/01; previous version)


Acceptable
Other:

CAN-TSO-C72b
(amended 2009/12/01; previous version)

CAN-TSO-C72a
(amended 2009/12/01; previous version)

CAN-TSO-C72
(amended 2009/12/01; previous version)


Acceptable


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; previous version)

551.403 Life Saving Equipment Over Water - Personal Flotation Devices (PFD)
(amended 2009/12/01; previous version)

(a) Introduction

This section contains standards of airworthiness for Personal Flotation Devices (PFDs) required by CAR 602.62.

(b) Definitions

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:
(amended 2009/12/01; previous version)

Standard Criteria for Acceptance for Installation
Current -

CAN/CGSB-65.11-M88, Personal Flotation Devices, Amendment No. 4 dated January 1997

CAN/CGSB-65.15-M88 , Personal Flotation Devices for Children, Amendment No. 4 dated January 1997

UL1180 Type II Standard with Canadian Addendum
(amended 2009/12/01; previous version)


Acceptable


Acceptable


Acceptable only when fitted with a manual only inflator per the Canadian Addendum to UL1180 Standard
(amended 2009/12/01; previous version)
Other:

CAN/CGSB-65.11-M88 , Personal Flotation Devices, published February 1988 and Amendments Nos. 1 through 3

CAN/CGSB-65.15-M88 , Personal Flotation Devices for Children, published April 1988 and Amendments Nos. 1 through 3

CGSB-65-GP-15M, Standard for: Personal Flotation Devices for Children dated August 1978

CGSB 65-GP-11, Standard for: Personal Flotation Devices dated October 1972


Acceptable



Acceptable



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; previous version)

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) Definitions

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; previous version)

Standard Criteria for Acceptance for Installation
Current - as contained in Chapter 537:

CAN-TSO C70a
(amended 2009/12/01; previous version)


Acceptable
Other:

CAN-TSO C70
(amended 2009/12/01; previous version)

CAN-TSO C12c
(amended 2009/12/01; previous version)


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; previous version)

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

(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; previous version)

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; previous version)

(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) Definitions (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; previous version)

Standard Criteria for Acceptance for Installation
Current - as contained in Chapter 537:

CAN-TSO-C116
(amended 2009/12/01; previous version)

CAN-TSO-C99
(amended 2009/12/01; previous version)


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; previous version)

551.406 Seat Belt and Shoulder Harness

(a) Introduction

This section contains standards of airworthiness for Seat Belts and Shoulder Harnesses required by CAR 605.22605.24, 702.44, 703.69, 704.68 and 705.75.

(b) Definitions (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; previous version)

Standard Criteria for Acceptance for Installation
Current - as contained in Chapter 537:

CAN-TSO-C22g
(amended 2009/12/01; previous version)

CAN-TSO-C114
(amended 2009/12/01; previous version)


Acceptable


Acceptable
Other:

CAN-TSO C22f
(amended 2009/12/01; previous version)



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; previous version)

 

Acceptable, except for aircraft that have been type certified with a later CAN-TSO standard (e.g. CAN-TSO-C22g)
(amended 2009/12/01; previous version)

Acceptable



Acceptable

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

(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; previous version)

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

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

(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; previous version)

(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; previous version)

(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; previous version)

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

(a) Introduction
(amended 2005/12/01; previous version)

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) Definitions
(amended 2005/12/01; previous version)

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; previous version)

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

Standard Criteria for Acceptance for Installation
Current -
(amended 2009/12/01; previous version)

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; previous version)

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; previous version)

551.408 Crash Axe
(amended 2009/12/01; no previous version)

(a) Introduction
(amended 2009/12/01; no previous version)

This section contains standards of airworthiness for a crash axe required by section 705.92 of the CARs.
(amended 2009/12/01; no previous version)

(b) Definitions
(amended 2009/12/01; no previous version)

In this section,
(amended 2009/12/01; no previous version)

“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; no previous version)

(c) Equipment
(amended 2009/12/01; no previous version)

The design standards in the following documents apply:
(amended 2009/12/01; no previous version)

Standard Criteria for Acceptance for Installation
Current:

SAE AS5402


Acceptable

(d) Installation
(amended 2009/12/01; no previous version)

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; no previous version)

551.409 to  551.499 Reserved
(amended 2009/12/01; previous version)

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; previous version)

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; previous version)

551.501 Child Restraint Systems
(amended 2009/12/01; no previous version)

(a) Introduction
(amended 2009/12/01; no previous version)

This section contains standards of airworthiness for the approval of child restraint systems as set out in section 605.28 of the CARs.
(amended 2009/12/01; no previous version)

(b) Equipment
(amended 2009/12/01; no previous version)

(1) Subject to (2) and (3), the design standards in the following documents apply:
(amended 2009/12/01; no previous version)

Standard Criteria for Acceptance for Installation
Current – as contained in Chapter 537:

CAN-TSO-C100b


Acceptable for use in transport category aeroplanes
Other:

Canada Motor Vehicle Safety Standards (CMVSS) No. 213 titled “Child Restraint Systems”, effective April 5, 1990


Acceptable for restraint systems manufactured between April 5, 1990 and March 14, 1998
Motor Vehicle Restraint Systems and Booster Cushions Safety Regulations (RSSR) Section 6, titled “Child Restraint Systems” effective March 15, 1998 and subsequent amendments Acceptable for restraint systems manufactured on or after this effective date
Canada Motor Vehicle Safety Standards (CMVSS) No. 213.1 titled “Infant Restraint Systems”, effective April 5, 1990 Acceptable for restraint systems manufactured between April 5, 1990 and March 14, 1998
Motor Vehicle Restraint Systems and Booster Cushions Safety Regulations (RSSR) Section 7, titled “Infant Restraint Systems” effective March 15, 1998 and subsequent amendments Acceptable for restraint systems manufactured on or after this effective date
Federal Motor Vehicle Safety Standard, (FMVSS) No. 213 (FMVSS 213), titled “Child Restraint Systems”, published by the Government of the United States:

(a) effective prior to amendment dated February 26, 1985




(b) amended effective February 26, 1985 and subsequent amendments
 




Acceptable for child restraint systems, except for Vest and harness-type, manufactured between January 1, 1981 and February 25, 1985, carrying the label “This child restraint system conforms to all applicable Federal Motor Vehicle Safety Standards”

i) Acceptable for child restraint systems manufactured on or after this effective date and approved for use in aircraft, carrying two labels which read: This child restraint system conforms to all applicable Federal Motor Vehicle Safety Standards”; and

ii) “This restraint is certified for use in motor vehicles and aircraft” printed in red lettering
 

(2) Tether straps, as required in automobiles, and as defined in the Motor Vehicle Restraint Systems and Booster Cushions Safety Regulations (RSSR) Section 6 and 7, are not authorized for use in aircraft.
(amended 2009/12/01; no previous version)

(3) Combination Child Restraint Systems/Booster Cushions certified to both CMVSS 213 and CMVSS 213.2 standards are acceptable only when the internal harness system is installed and all child restraint system labelling requirements are met.
(amended 2009/12/01; no previous version)

(4) Booster cushions and booster seats not meeting the above standards are not acceptable for use as Child Restraint Systems.
(amended 2009/12/01; no previous version)

(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.
(amended 2009/12/01; no previous version)

(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.
(amended 2009/12/01; no previous version)

(7) A Child Restraint System installed in an aeroplane 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.
(amended 2009/12/01; no previous version)

Information Note:

Additional information, in the form of advisory material, is available on the use and preferred location of child restraint systems and recommended evacuation procedures for occupants of child restraint systems.
(amended 2009/12/01; no previous version)

(c) Installation
(amended 2009/12/01; no previous version)

Child restraint systems must be installed in a forward facing aeroplane passenger seat as per the applicable installation instructions provided by the manufacturer of the child restraint system.
(amended 2009/12/01; no previous version)

551.503 to  551.599 Reserved
(amended 2009/12/01; previous version)