See also Subpart 500
Table of contents
- Preamble
- 500.01 - Applicability
- 500.02 - Interpretation
- 500.03 - Abbreviations and Symbols
- Airworthiness Manual Advisory (AMA) 500/00
Preamble
The Airworthiness Manual
The first reference to the Airworthiness Manual was contained in Part I of the Canada Gazette of January 1979, when the proposal to amend the Air Regulations relating to airworthiness were published. The Air Regulations were subsequently amended in August 1982. Section 211(1) stated that the Minister may cause to be published an Airworthiness Manual and an Engineering and Inspection Manual containing standards of airworthiness. The same revision to the Air Regulations also adopted by reference those U.S. Federal Aviation Regulations which contained the standards of airworthiness for a number of types of aeronautical products, such as aeroplanes, rotorcraft, aircraft engines and propellers. In addition, the U.S. airworthiness standards for appliances (TSOs), contained in FAA AC 20-110 were adopted, as well as the European JAR-22 for gliders and powered gliders, and ICAO Annex 16 Volume I addressing aircraft noise emissions.
Mr. Justice C. L. Dubin in Volume 2 of the report of his Commission of Inquiry on Aviation Safety recommended that an "Airworthiness Code" should be developed, containing the appropriate provisions of the Aeronautics Act and comprehensive regulations relating to airworthiness. The Aeronautics Act Task Force mandated to implement such recommendations reserved for airworthiness the Series V of the Canadian Code. For this reason, in publishing the Airworthiness Manual, the standards adopted by reference were numbered by adding a number "5" in front of the original number sections. What was envisaged as Canadian Aeronautics Code eventually developed in the present Canadian Aviation Regulations (CAR), which maintains the same structure. The airworthiness requirements are embodied in Part V of the CAR. The standards of airworthiness for the design of aeronautical products are and will continue to be published in the Manual, and this Manual forms part of the CAR.
Because of international obligations and harmonization, the numbering of CAR Part V and the related standards published in the Airworthiness Manual do not follow the conventional numbering system of the other Parts of the CAR, and the original structure of the standards of airworthiness adopted by reference is maintained intact.
Now that the entire Airworthiness Manual is published, the Engineering and Inspection Manual is superseded and serves the function of historic-reference document for past certifications. Aviation Notice A011 Edition 1 dated 31 December 1998 provides a concordance table.
Chapter 500 - General Provisions
First Edition
The definitions and the abbreviations and symbols used throughout the chapters of the Airworthiness Manual were initially published in Chapter 501 (1st Edition). After October 10, 1996, Chapter 501 was reissued to address the requirements for "Annual Airworthiness Information Report" (AAIR), leaving incertitude in the application of the airworthiness standards because these definitions were not covered in the Canadian Aviation Regulations.
As the old Chapter 501, this new chapter is based on the United States Code of Federal Regulations (CFR), Title 14, Chapter 1, Part 1, entitled "Definitions and Abbreviations". These definitions and abbreviations are updated to include FAR Amendment 1-48 dated 18 Feb. 1998 (FR). In addition, some of the definitions previously contained in Chapter 501 have been deleted, since they are now contained in the Canadian Aviation Regulations.
As a reminder to the user, the interpretation section includes the definitions of rated take-off augmented thrust, rated take-off power and take-off thrust which differ from the corresponding definitions of FAR Part 1. These Canadian definitions were published in Change 501-1 effective January 1, 1986 for use with the Canadian requirement of paragraph 525.1521(b)(6) as incorporated in Change 525-1 effective January 1, 1987.
Change 500-1
Published: 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 sections 500.1, 500.2 and 500.3 to reflect changes required because of the introduction of CAR 521.
As noted, the introduction of CAR 521 withdraws a number of Standards and Chapters of the AWM that are referenced in the table of section 500.01. In addition, a number of Chapters of the AWM have been renamed Standards. The table no longer reflects the same intent as when it was published and it is no longer possible to think of all of the Chapters as forming a single “Airworthiness Manual”. As such the table has been deleted.
Sections 500.02 and 500.03 have been amended to reflect this change.
This change incorporates the following amendment to the United States Code of Federal Regulations, Title 14, Chapter I, Part 33:
Table of Change Information | |
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Notice of Proposed Amendment | Amended Section(s) |
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This Amendment entitled “Airworthiness Standards: Aircraft Engine Standards Overtorque Limits” amends the airworthiness standards for aircraft engines to establish requirements for approval of maximum engine overtorque. Specifically, this action will add a new engine overtorque test, amend engine ratings and operating limits, and define maximum engine overtorque for certain turbopropeller and turboshaft engines. Notice of proposed amendment (NPA) 2009-120 proposes to amend section 500.02 of the Airworthiness Manual to introduce the new definition “maximum engine overtorque” relating to FAR amendment No. 33-30 as adopted into AWM 533.
This Change incorporates the following amendments to the United States Code of Federal Regulations, Title 14, Chapter I, Part 25 and Part 33:
Table of Change Information | |
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Notice of Proposed Amendment | Amended Section(s) |
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This amendment entitled Extended Operations (ETOPS) of Multi-Engine Aeroplanes amends the design standards of Chapters 525 and 533 of the Airworthiness Manual (AWM). As a result, Notice of proposed amendment (NPA) 2019-012 also proposes to amend sections 500.02 Interpretation and 500.03 Abbreviations and Symbols of AWM Chapter 500 to reflect changes required by the introduction of airworthiness standards for ETOPS.
Section 500.02 introduces the following definitions for “Configuration, Maintenance, and Procedures (CMP) document”, “Early ETOPS”, “Extended Operations (ETOPS) significant system”, “Extended Operations (ETOPS)” and “In-flight shutdown (IFSD)” relating to FAR amendments 25-120 and 33-21 as adopted into AWM Chapters 525 and 533.
Section 500.03 introduces the following abbreviations for “AFM”, “CMP”, “ETOPS” and “IFSD” relating to FAR amendments 25-120 and 33-21 as adopted into AWM 525 and 533.
Airworthiness Manual Chapter 500 - General
(2001/03/01)
500.01 Applicability
This Chapter contains definitions, abbreviations and symbols for use with the Standards and the Chapters of the Airworthiness Manual that make up Part V of the Canadian Aviation Regulations.
(amended 2009/12/01)
Information Note:
Background information on the Airworthiness Manual and its numbering system is presented in the preamble to this chapter.
(amended 2009/12/01)
500.02 Interpretation
The following definitions are used throughout the Standards and the Chapters of the Airworthiness Manual that make up Part V of the Canadian Aviation Regulations. They are in addition to those contained in the Aeronautics Act and the Canadian Aviation Regulations:
(amended 2009/12/01)
"aerodynamic coefficient" means nondimensional coefficient for aerodynamic forces and moments; (coefficient aérodynamique)
"aircraft engine" means an engine that is used or intended to be used for propelling aircraft. It includes turbosuperchargers, appurtenances and accessories necessary for its functioning but does not include propellers; (moteur d’aéronef)
"airframe" means the fuselage, booms, nacelles, cowlings, fairings, airfoil surfaces (including rotors but excluding propellers and rotating airfoils of engines), and landing gear of an aircraft and their accessories and controls; (cellule)
"altitude engine" means a reciprocating aircraft engine having a rated takeoff power that is producible from sea level to an established higher altitude; (moteur suralimenté)
"autorotation" means a rotorcraft flight condition in which the lifting rotor is driven entirely by action of the air when the rotorcraft is in motion; (autorotation)
"auxiliary rotor" means a rotor that serves either to counteract the effect of the main rotor torque on a rotorcraft or to maneuver the rotorcraft about one or more of its three principal axes; (rotor auxiliaire)
"brake horsepower" means the power delivered at the propeller shaft (main drive or main output) of an aircraft engine; (puissance au frein)
"calibrated airspeed" means indicated airspeed of an aircraft, corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level; (vitesse conventionnelle)
"canard" means the forward wing of a canard configuration and may be a fixed, movable, or variable geometry surface, with or without control surfaces; (canard)
"canard configuration" means a configuration in which the span of the forward wing is substantially less than that of the main wing; (configuration canard)
"category A" with respect to normal and transport category rotorcraft, means multiengine rotorcraft designed with engine and system isolation features specified in Chapter 527 or 529 and utilizing scheduled takeoff and landing operations under a critical engine failure concept which assures adequate designated surface area and adequate performance capability for continued safe flight in the event of engine failure; (catégorie A)
"category B" with respect to transport category rotorcraft, means single-engine or multiengine rotorcraft which do not fully meet all Category A standards. Category B rotorcraft have no guaranteed stay-up ability in the event of engine failure and unscheduled landing is assumed; (catégorie B)
“configuration, maintenance and procedures (CMP) document” means a document approved by the Minister that contains minimum configuration, operating, and maintenance requirements, hardware life-limits, and Master Minimum Equipment List (MMEL) constraints necessary for an aeroplane-engine combination to meet extended operations (ETOPS) type design approval requirements; (document de configuration, de maintenance et de procedures (CMP))
(effective 2019/08/25)
"critical altitude" means the maximum altitude at which, in standard atmosphere, it is possible to maintain, at a specified rotational speed, a specified power or a specified manifold pressure. Unless otherwise stated, the critical altitude is the maximum altitude at which it is possible to maintain, at the maximum continuous rotational speed, one of the following:
-
(1) The maximum continuous power, in the case of engines for which this power rating is the same at sea level and at the rated altitude;
-
(2) The maximum continuous rated manifold pressure, in the case of engines, the maximum continuous power of which is governed by a constant manifold pressure; (altitude critique)
“early ETOPS” means “early extended operations (ETOPS)” type design approval obtained without gaining non-ETOPS service experience on the candidate aeroplane-engine combination certified for extended operations (ETOPS); (ETOPS rapides)
(effective 2019/08/25)
"equivalent airspeed" means the calibrated airspeed of an aircraft corrected for adiabatic compressible flow for the particular altitude. Equivalent airspeed is equal to calibrated airspeed in standard atmosphere at sea level; (équivalent de vitesse-air)
“extended operations (ETOPS)” means an aeroplane flight operation, other than an all-cargo operation in an aeroplane with more than two engines, on a route containing a point that is farther from an adequate aerodrome than the distance that can be flown (at an approved one-engine-inoperative cruise speed under standard conditions in still air) of 60 minutes for a two-engine aeroplane or 180 minutes for an aeroplane with more than two engines; (opérations avec distance de vol prolongée (ETOPS))
(effective 2019/08/25)
“extended operations (ETOPS) significant system” means an aeroplane system, including the propulsion system, the failure or malfunctioning of which could adversely affect the safety of an extended operations (ETOPS) flight, or the continued safe flight and landing of an aeroplane during an extended operations (ETOPS) diversion. Each extended operations (ETOPS) significant system is either an extended operations (ETOPS) group 1 significant system or an extended operations (ETOPS) group 2 significant system;
- (1) An extended operations (ETOPS) group 1 significant system—
- (i) Has fail-safe characteristics directly linked to the degree of redundancy provided by the number of engines on the aeroplane.
- (ii) Is a system, the failure or malfunction of which could result in an IFSD, loss of thrust control, or other power loss.
- (iii) Contributes significantly to the safety of an extended operations (ETOPS) diversion by providing additional redundancy for any system power source lost as a result of an inoperative engine.
- (iv) Is essential for prolonged operation of an aeroplane at engine inoperative altitudes.
- (2) An extended operations (ETOPS) group 2 significant system is an extended operations (ETOPS) significant system that is not an extended operations (ETOPS) group 1 significant system. (système critique aux opérations avec distance de vol prolongée (ETOPS))
(effective 2019/08/25)
"extended over-water operations"
(Repealed 2015/08/01)
"external load" means a load that is carried, or extends outside of the aircraft fuselage; (charge externe)
"external-load attaching" means the structural components used to attach an external load to an aircraft, including external-load containers, the back-up structure at the attachment points, and any quick-release device used to jettison the external load; (moyens de fixation d’une charge extérieure)
"final take-off speed" means the speed of the aeroplane that exists at the end of the take-off path in the en route configuration with one engine inoperative (vitesse au décollage)
(amended 2003/11/10)
"fireproof" means
-
(1) with respect to materials and parts used to confine fire in a designated fire zone, the capacity to withstand at least as well as steel in dimensions appropriate for the purpose for which they are used, the heat produced when there is a severe fire of extended duration in that zone; and(2) with respect to other materials and parts, the capacity to withstand the heat associated with fire at least as well as steel in dimensions appropriate for the purpose for which they are used; (à l’épreuve du feu)
"fire resistant" means
-
(1) with respect to sheet or structural members, the capacity to withstand the heat associated with fire at least as well as aluminum alloy in dimensions appropriate for the purpose for which they are used; and
-
(2) with respect to fluid-carrying lines, fluid system parts, wiring, air ducts, fittings, and powerplant controls, the capacity to perform the intended functions under the heat and other conditions likely to occur when there is fire at the place concerned; (résistant au feu)
"flame resistant" means not susceptible to combustion to the point of propagating a flame, beyond safe limits, after the ignition source is removed; (résistant à la flamme)
"flammable"with respect to a fluid or gas, means susceptible to igniting readily or to exploding; (inflammable)
"flap extended speed" means the highest speed permissible with flaps in a prescribed extended position; (vitesse volets sortis)
"flash resistant" means not susceptible to burning violently when ignited; (non fusant)
"forward wing" means a forward lifting surface of a canard configuration or tandem-wing configuration aeroplane. The surface may be a fixed, movable, or variable geometry surface, with or without control surfaces; (aile avant)
"go-around power or thrust setting" means the maximum allowable in-flight power or thrust setting identified in the performance data (Régime de remise des gaz ou réglage de poussée)
"idle thrust" means the jet thrust obtained with the engine power control level set at the stop for the least thrust position at which it can be placed; (poussée au ralenti)
"indicated airspeed" means the speed of an aircraft as shown on its pilot static airspeed indicator calibrated to reflect standard atmosphere adiabatic compressible flow at sea level uncorrected for airspeed system errors; (vitesse indiquée)
“in-flight shutdown (IFSD)” means, for extended operations (ETOPS) only, when an engine ceases to function (when the aeroplane is airborne) and is shutdown, whether self-induced, flight crew initiated or caused by an external influence. The Minister considers IFSD for all causes: for example, flameout, internal failure, flight crew initiated shutdown, foreign object ingestion, icing, inability to obtain or control desired thrust or power, and cycling of the start control, however briefly, even if the engine operates normally for the remainder of the flight. This definition excludes the airborne cessation of the functioning of an engine when immediately followed by an automatic engine relight and when an engine does not achieve desired thrust or power but is not shutdown; (coupure de moteur en vol (ISFD))
(effective 2019/08/25)
"landing gear extended speed" means the maximum speed at which an aircraft can be safely flown with the landing gear extended; (vitesse train d’atterrissage sorti)
"landing gear operating speed" means the maximum speed at which the landing gear can be safely extended or retracted; (vitesse train d’atterrissage en manoeuvre)
"load factor" means the ratio of a specified load to the total weight of the aircraft. The specified load is expressed in terms of any of the following:
aerodynamic forces, inertia forces, or ground or water reactions; (facteur de charge)
"mach number" means the ratio of true airspeed to the speed of sound; (nombre de mach)
"main rotor" means the rotor that supplies the principal lift to a rotorcraft; (rotor principal)
"manifold pressure" means absolute pressure as measured at the appropriate point in the induction system and usually expressed in inches of mercury; (pression d’admission)
“maximum engine overtorque”, as it applies to turbopropeller and turboshaft engines incorporating free power turbines for all ratings except one engine inoperative (OEI) ratings of two minutes or less, means the maximum torque of the free power turbine rotor assembly, the inadvertent occurrence of which, for periods of up to 20 seconds, will not require rejection of the engine from service or any maintenance action other than to correct the cause. (surcouple maximal du moteur)
(amended 2010/05/27)
"maximum speed for stability characteristics (VFC/MFC)" means a speed that may not be less than a speed midway between maximum operating limit speed (VMO/MMO) and demonstrated flight diving speed (VDF/MDF), except that, for altitudes where the Mach number is the limiting factor, MFC need not exceed the Mach number at which effective speed warning occurs; (vitesse maximale pour la démonstration des caractéristiques de stabilité VFC/MFC)
"pitch setting" means the propeller blade setting as determined by the blade angle measured in a manner, and at a radius, specified by the instruction manual for the propeller; (calage de pas)
"rated continuous OEI power"means, with respect to rotorcraft turbine engines, the approved brake horsepower developed under static conditions at specified altitudes and temperatures within the operating limitations established for the engine under Chapter 533 of the Airworthiness Manual, and limited in use to the time required to complete the flight after the failure or shutdown of one engine of a multiengine rotorcraft; (puissance nominale continue avec un moteur en panne (OEI))
(amended 2010/01/29)
"rated maximum continuous augmented thrust" means, with respect to turbojet engine type certification, the approved jet thrust that is developed statically or in flight, in standard atmosphere at a specified altitude, with fluid injection or with the burning of fuel in a separate combustion chamber, within the engine operating limitations established under Chapter 533 of the Airworthiness Manual, and approved for unrestricted periods of use; (poussée nominale continue maximale augmentée)
"rated maximum continuous power" means, with respect to reciprocating, turbopropeller, and turboshaft engine, the approved brake horsepower that is developed statically or in flight, in standard atmosphere at a specified altitude, within the engine operating limitations established under Chapter 533 of the Airworthiness Manual, and approved for unrestricted periods of use; (puissance nominale maximale continue)
"rated maximum continuous thrust", with respect to turbojet engine type certification, means the approved jet thrust that is developed statically or in flight, in standard atmosphere at a specified altitude, without fluid injection and without the burning of fuel in a separate combustion chamber, within the engine operating limitations established under Chapter 533 of the Airworthiness Manual, and approved for unrestricted periods of use; (poussée nominale maximale continue)
"rated take-off augmented thrust" means, with respect to turbojet engine type certification, the approved jet thrust that is developed statically under standard sea level conditions, with fluid injection or with the burning of fuel in a separate combustion chamber, within the engine operating limitations established under Chapter 533 of the Airworthiness Manual, and limited in use to periods of not over 5 minutes for take-off operation or periods of not more than 10 minutes of one-engine-inoperative climb; (poussée nominale augmentée au décollage)
"rated take-off power" means, with respect to reciprocating, turbopropeller, and turboshaft engine type certification, the approved brake horsepower that is developed statically under standard sea level conditions, within the engine operating limitations established under Chapter 533 of the Airworthiness Manual, and limited in use to periods of not over 5 minutes for take-off operation or periods of not more than 10 minutes of one-engine-inoperative climb; (puissance nominale au décollage)
"rated take-off thrust" means, with respect to turbojet engine type certification, the approved jet thrust that is developed statically under standard sea level conditions, without fluid injection and without the burning of fuel in a separate combustion chamber, within the engine operating limitations established under Chapter 533 of the Airworthiness Manual, and limited in use to periods of not over 5 minutes for take-off operation or periods of not more than 10 minutes of one-engine-inoperative climb; (poussée nominale au décollage)
“rated 2-minute OEI power” means, with respect to rotorcraft turbine engines, the approved brake horsepower developed under static conditions at specified altitudes and temperatures within the operating limitations established for the engine under Chapter 533 of the Airworthiness Manual, for continuation of one-flight operation after the failure of one engine in multiengine rotorcraft, for up to three periods of use no longer than 2 minutes each in any one flight, and followed by mandatory inspection and prescribed maintenance action; (puissance nominale 2-minutes OEI)
(amended 2010/01/29)
“rated 2½-minute OEI power” means, with respect to rotorcraft turbine engines, the approved brake horsepower developed under static conditions at specified altitudes and temperatures within the operating limitations established for the engine under Chapter 533 of the Airworthiness Manual, for periods of use no longer than 2 ½ minutes after the failure or shutdown of one engine of a multiengine rotorcraft; (puissance nominale 2½ minutes OEI)
(amended 2010/01/29)
“rated 30-minutes OEI power” means, with respect to rotorcraft turbine engines, the approved brake horsepower developed under static conditions at specified altitudes and temperatures within the operating limitations established for the engine under Chapter 533 of the Airworthiness Manual, and limited to one period of use no longer than 30 minutes after the failure or shutdown of one engine of a multi-engine rotorcraft; (puissance nominale 30 minutes OEI)
(amended 2010/01/29)
“rated 30-second OEI power” means, with respect to rotorcraft turbine engines, the approved brake horsepower developed under static conditions at specified altitudes and temperatures within the operating limitations established for the engine under Chapter 533 of the Airworthiness Manual, for continuation of one-flight operation after the failure or shutdown of one engine in multiengine rotorcraft, for up to three periods of use no longer than 30 seconds each in any one flight, and followed by mandatory inspection and prescribed maintenance action; (puissance nominale 30 secondes OEI)
(amended 2010/01/29)
"reference landing speed" means the speed of the aeroplane, in a specified landing configuration, at the point where it descends through the 50 foot height in the determination of the landing distance (vitesse de référence à l'atterissage)
(amended 2003/11/10)
"rotorcraft" means a heavier-than-air aircraft that depends principally for its support in flight on the lift generated by one or more rotors; (giravion)
"rotorcraft-load combination"
Information Note:
Refer to CAR 101.01 definition of "Helicopter Class A, Class B, Class C, and Class D external loads"; (combinaison giravion-charge)
"sea level engine" means a reciprocating aircraft engine having a rated take-off power that is producible only at sea level; (moteur atmosphérique)
"standard atmosphere" means the atmosphere defined in U.S. Standard Atmosphere, 1962 (Geopotential altitude tables); (atmosphère type)
"take-off power" means
-
(1) with respect to reciprocating engines, means the brake horsepower that is developed under standard sea level conditions, and the maximum conditions of crankshaft rotational speed and engine manifold pressure approved for the normal take-off, and limited in continuous use to the period of time shown in the approved engine specification; and
-
(2) with respect to turbine engines, means the brake horsepower that is developed under static conditions at a specified altitude and atmospheric temperature, and under the maximum conditions of rotor shaft rotational speed and gas temperature to the period of time shown in the approved engine specification; (puissance au décollage)
"take-off thrust" with respect to turbine engines, means the jet thrust that is developed under static conditions at a specific altitude and atmospheric temperature under the maximum conditions of rotorshaft rotational speed and gas temperature approved for the normal take-off, and limited in continuous use to the period of time shown in the approved engine specification; (poussée au décollage)
"tandem wing configuration" means a configuration having two wings of similar span, mounted in tandem; (configuration à ailes en tandem)
"true airspeed" means the airspeed of an aircraft relative to undisturbed air. True airspeed is equal to equivalent airspeed multiplied by (ro/r)½; (vitesse vraie)
"winglet" or "tip fin" means an out-of-plane surface extending from a lifting surface. The surface may or may not have control surfaces. (ailette ou plan d’extrémité d’aile)
500.03 Abbreviations and Symbols
The following abbreviations and symbols are used throughout the Standards and the Chapters of the Airworthiness Manual that make up Part V of the Canadian Aviation Regulations. They are in addition to those contained in the Aeronautics Act and the Canadian Aviation Regulations:
(amended 2009/12/01)
“AFM” (effective 2019/08/25) |
means aeroplane flight manual; (AFM) |
"AIR" | means Airworthiness Inspection Representative; (RIN) |
"CAS" | means calibrated airspeed; (CAS) |
“CMP” (effective 2019/08/25) |
means configuration, maintenance, and procedures; (CMP) |
"DOT" | means Department of Transport; (MdT) |
"EAS" | means equivalent airspeed; (EAS) |
“ETOPS” (effective 2019/08/25) |
means extended operations; (ETOPS) |
"FAA" | means Federal Aviation Administration; (FAA) |
"FSR" | means Field Service Representative; (FSR) |
"GS" | means glide slope; (GS) |
"IAS" | means indicated airspeed; (IAS) |
"ICAO" | means International Civil Aviation Organization; (OACI) |
“IFSD” (effective 2019/08/25) |
means in-flight shutdown; (IFSD) |
"ILS" | means instrument landing system; (ILS) |
"LOC" | means ILS localizer; (LOC) |
"M" | means mach number; (M) |
"MSL" | means mean sea level; (MSL) |
"MRB" | means 1. Material Review Board; (MRB) 2. Maintenance Review Board; (MRB) |
"OEI" | means one engine inoperative; (OEI) |
"TAS" | means true airspeed; (TAS) |
"VA" | means design manoeuvring speed; (VA) |
"VB" | means design speed for maximum gust intensity; (VB) |
"VC" | means design cruising speed; (VC) |
"VD" | means design diving speed; (VD) |
"VDF/MDF" | means demonstrated flight diving speed; (VDF/MDF) |
"VEF" | means the speed at which the critical engine is assumed to fail during take-off (VEF) |
"VF" | means design flap speed; (VF) |
"VFC/MFC" | means maximum speed for stability characteristics; (VFC/MFC) |
"VFE" | means maximum flap extended speed; (VFE) |
"VFTO" | means final take-off speed; (VFTO) (amended 2003/11/10) |
"VH" | means maximum speed in level flight with maximum continuous power; (VH) |
"VLE" | means maximum landing gear extended speed; (VLE) |
"VLO" | means maximum landing gear operating speed; (VLO) |
"VLOF" | means lift-off speed; (VLOF) |
"VMC" | means minimum control speed with the critical engine inoperative; (VMC) |
"VMO/MMO" | means maximum operating limit speed; (VMO/MMO) |
"VMU" | means minimum unstick speed; (VMU) |
"VNE" | means never-exceed speed; (VNE) |
"VNO" | means maximum structural cruising speed; (VNO) |
"VR" | means rotation speed; (VR) |
"VREF" | means reference landing speed; (VREF) (amended 2003/11/10) |
"VS" | means the stalling speed or the minimum steady flight speed at which the aeroplane is controllable; (VS) |
"VSO" | means the stalling speed or the minimum steady flight speed in the landing configuration; (VSO) |
"VS1" | means the stalling speed or the minimum steady flight speed obtained in a specified configuration; (VS1) |
"VSR" | means reference stall speed; (VSR) (amended 2003/11/10) |
"VSR0" | means reference stall speed in the landing configuration; (VSR0) (amended 2003/11/10) |
"VSR1" | means reference stall speed in a specific configuration; (VSR1) (amended 2003/11/10) |
"VSW" | means speed at which onset of natural or artificial stall warning occurs; (VSW) (amended 2003/11/10) |
"VX" | means speed for best angle of climb; (VX) |
"VY" | means speed for best rate of climb; (VY) |
"V1" | means the maximum speed in the take-off at which the pilot must take the first action (e.g., apply brakes, reduce thrust, deploy speed brakes) to stop the aeroplane within the accelerate-stop distance. V1 also means the minimum speed in the take-off, following a failure of the critical engine at VEF at which the pilot can continue the take-off and achieve the required height above the take-off surface within the take-off distance.(V1) |
"V2" | means take-off safety speed; (V2) |
"V2 min" | means minimum take-off safety speed; (V2 min) |
"VRA" | means allowable rough-air speed; (VRA) |
"VT" | means maximum aero-tow speed (522 only); (VT) |
"VW" | means maximum winch-launch speed (522 only). (VW) |
Airworthiness Manual Advisory (AMA)
Content last revised: 2004/12/01
AMA: 500/00 M
Date: December 1, 2004
Airworthiness Manual Advisory Index
(This AMA supersedes AMA 500/00 L dated 2003-06-10.)
1. Purpose
This advisory provides information on advisory material related to the standards and procedures contained in the Airworthiness Manual (AWM). Updated lists of all current and cancelled AMAs are presented in Appendix A and B respectively. FAA Advisory Circulars excluded for use with the AWM are listed in Appendix C.
2. Advisory Material
Transport Canada issues advisory material to provide information, interpretations or acceptable means for demonstrating compliance with existing standards to the aviation community.
Information usually addresses issues or non regulatory material which may be of interest; in a few cases it is used to advise industry on the criteria or the requirements that the Department will apply in specific certification cases in the form of Special Conditions - Airworthiness.
Interpretations are used to advise industry on current policies, and in certain cases the Department reading of current requirements, pending the results of international harmonization.
Means of compliance are recommended means of complying with the requirements contained in the AWM, in particular with Canadian additional technical conditions (Canadian variants). In this case the content of the advisory is not binding on the public. The applicant may elect to follow an alternate method, provided that the proposed means is acceptable to the Department.
Advisory material may be presented in two forms: as a short and concise "Information Notes" imbedded in the text right after the affected standards, or as a separate document, i.e., "Airworthiness Manual Advisory" (AMA), when the information is too conspicuous to be published within the standards.
The current Airworthiness Manual Advisory (AMA) material for the series 500 AMAs, the Design Standards have been, as of December 1, 2004, renamed and reformatted as Advisory Circulars (AC). The conversion is strictly a format and number change while the contents remain unchanged. The conversion of advisory material from AMA to AC is undertaken to further harmonize the Canadian Aviation Regulatory system with the Federal Aviation Administration Regulations and the new European Aviation Safety Agency Certification Specifications. Not only will this conversion bring us closer to harmonization with the FAA and EASA but will also allow harmonization of the Aircraft Certification branch advisory material with the other branches of Transport Canada Civil Aviation that are currently using ACs.
Appendix B of this AMA provides a list of replacement AC numbers for the previously existing AMA numbers.
The AC Index to replace AMA 500/00 has been established and contains all of the current ACs with their new corresponding AC number that were previously published as AMAs. That Index is SI No. GEN-001. AMA 500/00 will continue to be published until the all the AMAs for Delegation and Certification Procedures, Recreational Aviation and Maintenance and Manufacturing are converted to ACs or for as long they continue to be relevant.
3. AMA Numbering System
AMA numbers are assigned to correspond to a subject area of the AWM according to the following system:
(a) Series 500 AMAs
AMAs containing miscellaneous or general information or addressing subjects applicable to more than one Chapter of the AWM will be issued in the 500 Series, e.g. AMA 500/n A;
where: n = sequential number (1, 2, 3 etc.)
A = sequential amendment status (A, B, C etc.)
Information Note:
Originally the 500 Series AMAs had a speciality ID letter (A to G), following the number 500. This system has been discontinued.
(b) Series 5XX AMAs
(i) AMAs providing information regarding a specific section of a chapter, e.g. AMA 525.101/n A;
(ii) providing information regarding more than one subchapter or section of the same chapter, e.g. AMA 525/n A;
where: n = sequential number, if more than one AMA (1, 2, 3 etc.)
A = sequential amendment status (A, B, C etc.)
(iii) AMAs providing information regarding an entire subchapter of a chapter were identified as AMA 505C/5 A;
where: A are the same as defined above, and
C = subchapter number
(c) Advisory Circular Numbering
Staff Instruction (SI) GEN-002 should be consulted for formatting and numbering of new Advisory Circulars (AC).
4. Foreign Advisory Material
Transport Canada also reviews advisory material published by the Federal Aviation Administration (FAA) of the USA and the Joint Aviation Authorities (JAA), and may accept this material for use with the design standards contained in the Airworthiness Manual, when they are not conflicting with Canadian regulations, standards, policies, interpretations and advisory material.
(a) FAA Advisory Material
Except when specifically excluded in Appendix C of this document, FAA ACs addressing the adopted design standards of FAR 23, 25, 27, 29, 31, 33 and 35, as well as some related ACs in the series 20, 43, 90, 91, 120 and 121, are considered acceptable for use with the Airworthiness Manual subject to the following:
(i) Only the airworthiness content is accepted.
(ii) Any reference to "FAA Administrator" and "Administration" will read the "Minister".
(iii) Any reference to FAR sections (Part 23 to 35) will read as sections of the corresponding AWM Chapter (523 to 535).
(iv) No advisory circular can modify or change a Canadian standard.
(v) Any reference to FAA regulations which have not been adopted in Canada may be allowed only if the foreign regulations are not in conflict with the Canadian Aviation Regulations (CARs).
(vi) FAA operational regulations do not apply in Canada and shall be replaced by reference to the applicable CARs.
(vii) Canadian equivalents will not be substituted where statements of fact are being made, e.g. "FAA does not require in FAR 91.125 etc."
FAA Advisory Circular exclusions will, as of December 1, 2004 be provided in SI No. GEN-001 published by the Aircraft Certification branch.
Information Note:
Federal Aviation Administration Advisory Circulars (ACs) are available (in English only) by mail order from:
Canada - Mail Orders
Renouf Publishing Co. Ltd.
1294 Algoma Road
Ottawa ON K1B 3W8
Telephone: (613) 741-4333
Fax: (613) 741-5439
Internet Address: http://www1.airweb.faa.gov/Regulatory_and_Guidance_Library/rgAdvisoryCircular.nsf/MainFrame?OpenFrameSet
(b) JAA Advisory Material
The JAA advisory material accepted for use with the design standards of Chapter 522, Gliders and Powered Gliders, and Chapter 523-VLA, Very Light Aeroplanes, are listed respectively in AMA 522/1 and AMA 523-VLA/1, as revised from time to time.
See Appendix B of this AMA for the replacement AC numbers of AMA 522/1 and AMA 523-VLA/1.
Appendix A
Airworthiness Manual Advisory (AMA)
1. Series 500 AMAs
Information Note:
All series 500 AMAs cancelled and replaced by ACs. See Appendix B for further detail.
2. Series 5xx AMAs
Delegation and Certification Procedures
505F/1 | Flight Permit Authorization (17 June 1992) |
Design Standards
Information Note:
All Design Standards AMAs have been cancelled and replaced by ACs. See Appendix B for further detail.
Recreational Aviation
549/1B | Amateur-Built Aircraft:General (01 April 1996) |
549.5 | Evaluation of Amateur-Built Aircraft Kits (03 January 1991) |
549.7A | Composite Primary Structures of Amateur Built Aircraft (31 October 1992) |
549.9 | Use of Automotive Gasoline in Aircraft Engines (15 April 1987) |
549.11 | Amateur-Built Aircraft - Noise Emission Control (26 September 1988) |
549.13/1A | Equipment and Instruments for Amateur-Built Aircraft (31 October 1992) |
549.13/2 | Prevention of Carburetor Icing in Amateur-Built Aircraft (15 April 1987) |
549.101A | Evaluation of Amateur-Built Aircraft as to Suitability for Performing Aerobatic Flights (01 April 1996) |
549.103/1 | High Performance Amateur Built Aeroplanes (30 October 1992) |
549.103/2 | Amateur-Built Aeroplanes Pilot License Requirements (12 November 1991) |
549.201 | Evaluation of Amateur-Built Helicopters (05 November 1990) |
Manufacturing & Maintenance
561/1 | Manufacturer Approval Requirements (01 January 1986) |
561/2 | Manufacturer Approval Procedures (01 January 1986) |
561/3A | Certification (15 May 1990) |
561/4 | Quality Program Manual Preparation (01 January 1986) |
563/1 | Distributor Standards and Procedures (01 January 1986) |
Distributor Standards and Procedures (01 January 1986) | |
563/2 | Distributor Standards and Procedures (01 January 1986) |
Product Control System Manual Preparation (01 January 1986) | |
571.101/1 | Reliability Monitoring Programs (01 April 1987) |
Appendix B
Cancellations
The following AMAs have been cancelled:
AMA No. |
Title / Date |
Cancellation Date |
Replaced By: |
500C/1 | Aircraft or Equipment Incorporating Digital Computer Technology (05/01/86) |
01/01/1996 |
FAA AC 20-115B |
500C/2 | Multipurpose Electronic Flight Deck Display Systems (01/05/86) |
02/02/1998 |
Superseded by several FAA ACs |
500C/3 | Fire Protection - Ignition Sources (01/05/86) |
01/12/2004 |
AC 500-005 Issue No. 1 |
500C/4 A | Portable Fire Extinguishers for Use in Aircraft (25/03/87) |
01/06/1998 |
FAA AC 20-42C |
500C/5B | Aircraft Operations After Ground Cold Soak (2/03/90) |
01/12/2004 |
AC 500-006 Issue No. 1 |
500C/6 | Lightning Protection of Aircraft Fuel Systems |
01/12/2004 |
AC 500-007 Issue No. 1 |
500/7A | Induction System Snow Protection 27/01/00) |
01/12/2004 |
AC 500-008 Issue No. 1 |
500/8B | Composite Aircraft Structure (8/11/99) |
01/12/2004 |
AC 500-009 Issue No. 1 |
500/9A | Standards for the Design and Installation of Aircraft Skis (29/10/99) |
01/12/2004 |
AC 500-010 Issue No. 1 |
500/10 | Restricted Category Certification for Small Aeroplane and Helicopters for Special Purpose Operations (23/08/01) |
01/12/2004 |
AC 500-011 Issue No. 1 |
500/11 | Airworthiness Standards for the Design of Aircraft Floats (2/02/98) |
01/12/2004 |
AC 500-012 Issue No. 1 |
500/12 | Carriage of Bulk Fluids in Aircraft (7/04/00) |
01/12/2004 |
AC 500-013 Issue No. 1 |
500/13 | Aircraft Flight Manuals (30/10/02) |
01/12/2004 |
AC 500-014 Issue No. 1 |
500/15A | Certification Plans (10/06/03) |
01/12/2004 |
AC 500-015 Issue No. 1 |
500/16 | Establishing The Certification Basis of Changed Aeronautical Products (10/06/03) |
01/12/2004 |
AC 500-016 Issue No. 1 |
500G/1 | Development and Implementation of Supplemental Structural Inspection Requirements for Aging Aircrafts (05/06/90) |
01/12/1998 |
STD 511.34 |
503.1 | Airworthiness Manual Amendment Process (01/12/94) |
02/02/1998 |
See CARAC Charter |
503.11 | Adoption of FAA or JAA or ICAO Amendments and Environmental Standards (01/12/94) |
02/02/1998 |
See CARAC Charter |
505C/1 | Design Approval Representative (30/11/93) |
01/12/2004 |
AC 505-001 Issue No. 1 |
505D/1B | Airworthiness Inspection Representative | 03/07/2013 | MSI 20, revision 03 |
507B/1A | Export Airworthiness Certificates (31/03/92) |
10/10/1996 |
CARs 509 and associated standards |
507B/2 | Authorized Release Certificate -Airworthiness Approval Tag - Class II and Class III Aeronautical Products (31/03/92) |
10/10/1996 |
STD 571, Appendix J |
507C/1 | Imported Aeronautical Products (29/08/88) |
10/10/1996 |
CARs 507 and associated standards |
507D/1A | Airworthiness Certification (30/03/92) |
10/10/1996 |
CARs 507 and associated standards |
507D/2 | Special Certificate of Airworthiness - Limited - Ex-military Aircraft for Private Use (15/06/90) |
10/10/1996 |
CARs 507 and associated standards |
507E/1A | Identification of Aircraft and Aeronautical Products (30/11/90) |
10/10/1996 |
CARs Part II and associated standards |
507F/1 | Annual Airworthiness Information Reporting (31/10/88) |
10/10/1996 |
AWM 501 |
511/1A | Type Certification Procedure for Canadian Aeronautical Products (2/02/98) |
01/12/2004 |
AC 511-002 Issue No. 1 |
511/2 | Type Certification of Foreign Type Design of Aeronautical Products including Related Airworthiness Activities (2/02/98) |
01/12/2004 |
AC 511-003 Issue No. 1 |
511E/1 | Type Approval Procedures for Aeronautical Appliances (09/06/89) |
01/12/1998 |
Combined in AMA 511/1 A |
511F/1 | Type Approval of Foreign Type Designs of Aircraft, Aircraft Engines and Propellers including related Airworthiness Activities (21/06/89) |
01/12/1998 |
AMA 511/2 |
511.107 | Time Period Required to Obtain an Aircraft Type Approval (18/05/89) |
01/12/1998 |
CARs 511.06 |
511.115/1 | Conditions for First Flight (24/05/89) |
01/12/1998 |
Section 511.08(3) and Chapter 511, Appendix B |
511.115/2 | Emergency Provisions - Flight Test Aircraft (18/05/89) |
01/12/1998 |
Section 511.08(1) |
511.201 | - Type Approval Certificates and Data Sheets - Aeronautical Products (23/05/89) |
01/12/1998 |
Appendix C of STD 511 |
511.315 | Criteria for the Issue of a New Aircraft Engine Type Approval (19/05/89) |
01/12/1998 |
Nil |
511.603 | Transfer of Type Approval (18/05/89) |
01/12/1998 |
STD 511.25 |
513/1 | Supplemental Type Approvals (19/04/90) |
01/12/1998 |
STD 513 - Information Notes |
513/2 | Familiarization of Supplemental Type Certificate Issued by the Federal Aviation Administration (FAA) (24/05/90) |
01/12/1998 |
STD 513 - Information Notes and AMA 513.20 |
513/3 | Repair Design Approvals: General Procedures (06/05/90) |
01/12/1998 |
STD 513 - Information Notes |
513/4 C | Payment of Fees and Reimbursement of Incremental Costs-Modification and Repair Design Approvals (10/06/03) |
01/12/2004 |
AC 513-005 Issue No. 1 |
513/5 | Privileges, Responsibilities and Obligations of Holders of Approvals (23/04/90) |
01/12/1998 |
STD 513 - Information Notes |
513.05/1 | Flight Test Considerations for the Approval of the Design of Aircraft Modifications (10/06/03) |
01/12/2004 |
AC 513-003 Issue No. 1 |
513.05/2 | Flight Manual Requirements Following Modification s (10/06/03) |
01/12/2004 |
AC 513-004 Issue No. 1 |
513.06/1A | Flight Test Considerations for the Approval of the Design of Aircraft Modifications (21/12/99) |
10/06/2003 |
AMA 513.05/1 |
513.06/2A | Flight Manual Requirements Following Modifications (21/12/99) |
10/06/2003 |
AMA 513.05/2 |
513.11 | Modifications and Repairs: Approval Basis Exceptions (28/05/90) |
01/12/1998 |
STD 513 - Information Notes |
513.17 | Flight Test Considerations for the Approval of the Design of Aircraft Modifications (22/03/90) |
01/12/1998 |
AMA 513.06/1 |
513.19 | Flight Manual Requirements following Modifications (11/04/90) |
01/12/1998 |
AMA 513.06/2 |
513.20A | Approval of Foreign Designed Changes to the Type Design of Aeronautical Products (10/06/03) |
01/12/2004 |
AC 513-006 Issue No. 1 |
522/1B | Advisory Circulars - Joint (ACJs) Gliders and Powered Gliders (30/06/93) |
01/12/2004 |
AC 522-001 Issue No. 1 |
523-VLA/1A | Advisory Circulars - Joint (ACJs) Very Light Aircraft (15/11/99) |
01/12/2004 |
AC 523-VLA-001 Issue No. 1 |
523-VLA/2 | Additional Technical Requirements For Night and IFR Operations (01/06/93) |
01/06/1993 |
Chapter 523-VLA - in the text and Information Notes |
523.1581B | Aeroplane Flight Manual (29/10/99) |
30/10/2002 |
AMA 500/13 |
523/1A | Stalls, Compliance (Commuter Category Aeroplanes) (08/11/99) |
01/12/2004 |
AC 523-002 Issue No. 1 |
523/2A | Flight in Icing Conditions - Performance (29/10/99) |
01/12/2004 |
AC 523-003 Issue No. 1 |
523/3A | Turbine Engine Propeller Reversing Systems (Commuter Category Aeroplanes) (28/08/01) |
01/12/2004 |
AC 523-004 Issue No. 1 |
523/4A | Flight in Icing Conditions - Flight Characteristics (29/10/99) |
01/12/2004 |
AC 523-005 Issue No. 1 |
523/5A | Performance Credit for Use of Power and Propeller Blade Pitch during Accelerate Stop and Landing Ground Roll (30/06/99) |
01/12/2004 |
AC 523-006 Issue No. 1 |
523/6 | Glider and Banner Towing (27/03/01) |
01/12/2004 |
AC 523-007 Issue No. 1 |
525.671A | Aeroplane Flight Control System Failure Analysis (14/07/00) |
01/12/2004 |
AC 525-015 Issue No. 1 |
525.697 | Lift and Drag Devices, Controls and Indicators (01/05/86) |
01/12/2004 |
AC 525-016 Issue No. 1 |
525.933 | Thrust Reversing Systems, Turbo-Jet Engines (01/05/86) |
01/01/1989 |
AMA 525/3 |
525.1091A | Engine Ingestion of Water/Slush Due to Runway Conditions (27/06/00) |
01/12/2004 |
AC 525-017 Issue No. 1 |
525.1191 | Firewalls - Criteria for Fireproofing (01/05/86) |
26/01/2000 |
FAA AC 20-135 |
525.1309 | Aeroplane Equipment, Systems, and Installation Probability Analysis (01/05/86) |
01/07/1991 |
FAA AC 25.1309-1A |
525.1521A | Conditional Use of Rated Take-off Power/Thrust (14/07/00) |
01/12/2004 |
AC 525-018 Issue No. 1 |
525.1581A | Aeroplane Flight Manual (12/11/99) |
30/10/2002 |
AMA 500/13 |
525.1581/2 A | Computerized Aeroplane Flight Manual Performance Systems (15/11/99) |
01/12/2004 |
AC 525-019 Issue No. 1 |
525/1A | Stalls, Compliance (12/11/99) |
01/12/2004 |
AC 525-020 Issue No. 1 |
525/2A | Flight in Icing Conditions - Performance (29/10/99) |
01/12/2004 |
AC 525-004 Issue No. 1 |
525/3 | Operation of Thrust Reversing Systems (24/08/88) |
01/12/2004 |
AC 525-005 Issue No. 1 |
525/4A | Operations from Unpaved Runways (02/09/99) |
01/12/2004 |
AC 525-006 Issue No. 1 |
525/5A | Flight in Icing Conditions - Flight Characteristics (20/10/99) |
01/12/2004 |
AC 525-007 Issue No. 1 |
525/6A | Downwind Take-Off and Landing (15/ 11/99) |
01/12/2004 |
AC 525-008 Issue No. 1 |
525/7A | Controllability During Approach and Landing (VMCL,) Considerations (30/06/99) |
01/12/2004 |
AC 525-009 Issue No. 1 |
525/8A | Performance Credit for Use of Propeller Blade Pitch During Accelerate Stop and Landing Roll (15/11/99) |
01/12/2004 |
AC 525-010 Issue No. 1 |
525/9A | Approval of Steep Approach and Short Landing Capability of Transport Category Aeroplanes (25/02/00) |
01/12/2004 |
AC 525-011 Issue No. 1 |
525/10A | Certification of Large Aeroplanes in the Restricted Category, Used for Special Purpose Operations (06/03/00) |
01/12/2004 |
AC 525-012 Issue No. 1 |
525/11A | Flight Characteristics with Lateral Center of Gravity (12/11/99) |
01/12/2004 |
AC 525-013 Issue No. 1 |
525/12 | Certification of Transport Category Aeroplanes on Narrow Runways (19/11/99) |
01/12/2004 |
AC 525-014 Issue No. 1 |
529/1 | Emergency Egress from a Transport Category Rotorcraft after Experiencing a Rollover (23/02/00) |
01/12/2004 |
AC 529-002 Issue No. 1 |
533.90 | Initial Maintenance Inspection (01/01/87) |
01/12/2004 |
AC 533-001 Issue No. 1 |
537/1 | Cross References used in Aviation Technical Standard Orders (15/05/87) |
01/12/1998 |
AWM Chapter 537, Section 3 (Change 537-4) |
551.100 | Flight Data Recorder Installation Calibration and Correlation Procedures (02/02/98) |
01/12/2004 |
AC 551-002 Issue No. 1 |
571.101/2 | Maintenance Development Programs (01/04/87) |
10/10/1996 |
- |
571.101/3 | Maintenance Review Boards (01/04/87) |
10/10/1996 |
FAA AC 121-22A |
571.101/4 | On-condition Maintenance of Piston Engines (05/10/87) |
10/10/1996 |
STD 625, Appendix D |
571.101/5 | Aircraft Wooden Components, Inspection for Deterioration (26/05/88) |
10/10/1996 |
STD 571, Appendix E |
571.103/1 | On-condition Maintenance of Piston Engines (30/11/86) |
10/10/1996 |
STD 625, Appendix C |
571.103/2 | Propeller Maintenance (27/02/87) |
10/10/1996 |
STD 625, Appendix C |
571.105 | Transfer of Aeronautical Products between Inspection Programs (31/01/87) |
10/10/1996 |
STD 625, Appendix F |
571.203A | Repairs and modifications (03/06/94) |
10/10/1996 |
AWM 571, sections 06 and 12 |
571.205 | Deferred Defects (05/10/87) |
10/10/1996 |
CARs 406, 604 and 706 |
571.207 | Inspection after Abnormal Occurrences (31/01/87) |
10/10/1996 |
N/A |
575.7 | Aircraft Maintenance Records (30/06/87) |
10/10/1996 |
CARs 571, 605 and associated standards |
575.103 | Certification of Maintenance (30/06/87) |
10/10/1996 |
N/A |
575.217 | Maintenance Release Tags (30/06/87) |
10/10/1996 |
CARs 571 and associated standards |
575.219 | Instructions for Completion of Form 24-0045, Repair or Modification Conformity Certificate (Airframe, Powerplant, Propeller, or Appliance) (30/06/87) |
15/10/1999 |
CARs 571 and associated standards |
591.103 | SDR Form 24-0038 Completion Instructions (30/10/87) |
10/10/1996 |
STD 591, Appendix A |
591.105 | Example Defects Requiring the Submission of a Report (30/10/87) |
10/10/1996 |
STD 591, Appendix C |
591/1 | Service Difficulty Reporting (30/10/87) |
10/10/1996 |
STD 591, Appendix B |
593/1 | Airworthiness Directives (30/09/87) |
10/10/1996 |
STD 593 |
Appendix C
FAA Advisory Circulars Exclusions
See SI No. GEN-001 published by the aircraft certification branch for information regarding exclusions to Transport Canada of FAA Advisory Circulars.