Appendix 2 - DHC-8 Series 400 Compliance Program, CAR 605 and 705

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INDEX

Section TITLE
9.1

DHC-8 Series 400 Compliance with CAR Part VI, Subpart 5 (605) and
CAR Part VII, Subpart 5 (705) – Introduction

9.2

DHC-8 Series 400 Compliance with CAR Part VI, Subpart 5 (605) and CAR Part VII, Subpart 5 (705)


CANADIAN AVIATION REGULATIONS
CAR PART VI, SUBPART 5 and CAR PART VII, SUBPART 5 COMPLIANCE
(TCCA ISSUE PAPER O-1)

INTRODUCTION

CAR Part VI, Subpart 5 (605), Division II specifies the equipment requirements for operation of all Canadian and foreign aircraft operating within Canadian airspace. CAR Part VII, Subpart 5 (705), Divisions V and VI specifies the additional equipment requirements for operation by a Canadian Air Operator in air transport service.

In order to assist DHC-8 Series 400 Operators in Canada, Bombardier Aerospace, as manufacturer of the DHC-8 Series 400, will provide information to Operators in order to assist them in demonstrating compliance with the above Canadian Aviation Regulations, specifically those related to equipment installations which are addressed at the time of Type Certification.

The following item is included in this report:

AEROC 84.1.AC.3 Sect. 9.2 DHC-8 Series 400 – Compliance with CAR Part VI, Subpart 5 (605) and
CAR Part VII, Subpart 5 (705) (TCCA Issue Paper O-1)

The following information outlines the basic structure and contents of the compliance records contained herein:

CAR ITEM This column contains the CAR 605 or 705 regulation number.
TITLE This column contains the subject of the regulation.
COMPLIANCE STATEMENT This column contains a brief synopsis of how compliance is demonstrated.
COMPLIANCE DOCUMENTS This column is a reference to a substantiating document retained by Bombardier.
COMP This column indicates whether the aircraft complies with the requirement.
REMARKS This column contains clarifications or notes.

The following is a list of those regulations for which Bombardier will provide compliance information:

CAR 605  
  DIVISION II
605.14 Day VFR Aircraft Equipment Requirements
605.15 VFR Over-The-Top Aircraft Equipment Requirements
605.16 Night VFR Aircraft Equipment Requirements                            
605.18 IFR Aircraft Equipment Requirements
605.22 Seat and Safety Belt Requirements
605.24 Shoulder Harness Requirements
605.28 Child Restraint System
605.29 Flight Control Locks
605.30 De-Icing or Anti-Icing Equipment
605.31 Oxygen Equipment and Supply
605.33 Flight Data Recorder and Cockpit Voice Recorder Requirements
605.35 Transponder and Automatic Pressure Altitude Reporting Equipment
605.36 Altitude Alerting System
605.37 Ground Proximity Warning System
605.38 Emergency Locator Transmitter
605.41 Standby Attitude Indicator
   
CAR 705  
  DIVISION V
705.67 General Requirements – Aircraft Equipment
705.68 Landing Lights
705.69 Operation of Aircraft in Icing Conditions
705.70 Weather Radar Equipment
705.71 Protective Breathing Equipment
705.72 First Aid Oxygen
705.73 Interphone System
705.74 Public Address System
705.75 Crewmember Shoulder Harnesses
705.76 Lavatory Fire Protection
705.77 Flammability Requirements for Aeroplane Seat Cushions
705.78 Floor Proximity Emergency Escape Path Markings
705.79 Flashlight Stowage
   
  DIVISION VI
705.89 Megaphones
705.90 First Aid Kits
705.91 Emergency Medical Kit
705.92 Crash Axe
705.93 Hand-Held Fire Extinguishers
705.94 Portable Oxygen
705.95 Survival Equipment
705.96 Emergency Equipment Inspection Requirements
705.97 Flashlights

NOTES:

Note 1: Compliance with these regulations needs to be evaluated by the TCCA Inspector at the Regional Office prior to the aircraft being used in revenue service.

Note 2: Reference to FAR Part 25 airworthiness standards in Section 8.2 relates to the amendment status specified in the type certification basis for the DHC-8 Series 400 (i.e. Amendments 25-1 through 25-86 and 25-92).

CAR ITEM TITLE COMPLIANCE STATEMENT COMPLIANCE DOCUMENTS COMP REMARKS
605.14 Day VFR – Aircraft Equipment Requirements The following instruments are displayed on each pilot’s Primary Flight Display (PFD), located directly in front of the pilot unless otherwise stated:-  
 
    (a) and (b) A display of barometric altitude. In addition there is a third (standby) display of altitude. The three altitude displays are adjustable for barometric pressure variations. 84.6.R.13 Y  
   
(c) Airspeed display via a dual airspeed indicating system with heated pitot-static tubes. A standby display of airspeed with a dedicated heated pitot-static probe is also fitted.
84.6.R.14 Y  
    (d) A magnetic compass is installed on the front windshield centre pillar. 84.6.R.14 Y  
    (e) A high pressure rotor speed and a low pressure rotor speed indicator for each engine is displayed on each pilot’s Engine Display Monitor. 84.5.PM.1; Sect. 2 Y  
    (f) and (h) An oil pressure/temperature indicator for each engine is displayed on each pilot’s Engine Display Monitor. Additionally, low oil pressure warning means for each engine is annunciated on the master caution warning panel. 84.5.PM.1; Sect. 2 Y  
    (j)(i) Fuel quantity indication for each fuel tank is displayed on each pilot’s Engine Display Monitor. 84.5.PF.1; Sect. 2 Y  
    (j)(ii) The DHC-8 Series 400 utilises a proximity switch system, compliant with FAR 25.729(e), to provide indication that the landing gear has attained both its fully extended and fully retracted position. 84.6.LG.2
84.6.LG.3
Y  
    (k),(l),(m) and (n) The DHC-8 Series 400 is equipped with:- A dual VHF communications system, each fitted with a dedicated rigid-type antenna; VHF1 antenna is mounted on top of the forward fuselage section; VHF2 antenna is mounted on the fuselage underside. A dual VHF Navigation system is connected to a single, rigidly mounted, VOR/LOC antenna, Marker Beacon antenna and Glideslope antenna. The systems are suitable for bi-directional communication with appropriate ground stations and ATC facilities, for obtaining weather information and for receiving radio navigation signals from all primary en-route and approach navigation facilities.


84.6.R.4 84.6.R.24 Y  
605.15 VFR Over-The-Top – Aircraft Equipment Requirements (1)(a) Refer to compliance statements against 605.14 (c) to (j) as applicable      
    (1)(b) Refer to compliance statements against 605.14 (a) and (b).      
    (1)(c) Refer to compliance statement against 605.14 (c).      
    (1)(d) A display of gyroscopically stabilised heading is presented on the lower portion of each pilot’s PFD, independently derived from the dual AHRS system. 84.6.R.14 Y  
    (1)(e) A gyroscopically stabilised display of attitude is displayed on the upper portion of each pilot’s PFD, independently derived from two independent AHRS systems. 84.6.R.14 Y  
    (1)(f) and (2) As a third, standby gyroscopically stabilised display of attitude is installed to the left of the Engine Display (ED), usable through 360 degrees of pitch and roll, slip-skid indication is displayed in the PFD attitude sphere, independently derived from dual AHRS systems. No rate-of-turn indications are presented. 84.6.R.14 Y  
    The standby gyroscopically stabilised display of attitude is capable of being used by either pilot.
(1)(h) and (i) Refer to compliance statements against 605.14 (k),(l), (m) and (n).

     
605.16 Night VFR – Aircraft Equipment Requirements (1)(a) Refer to compliance statements against 605.14 (c) to (n) as applicable.      
    (1)(b) Refer to compliance statements against 605.14 (a) and (b).      
    (1)(c) and (2) Refer to compliance statements against 605.15 (1)(f) and (2).      
    (1)(d) The electrical power generation and distribution system complies with the requirements of AWM 525.1309, 525.1351(a) and (b)(1) through (b)(4), 525.1353, 525.1355 and 525.1431(b). 84.6.E.1
84.6.E.2
84.9.E.1
Y  
    (1)(e) The DHC-8 Series 400 electrical system is routed through resettable circuit breakers. No fuses are required to be replaced. 84.6.E.1; Sect. 9    
    (1)(f) Refer to compliance statement against 605.15 (1)(d).      
    (1)(i) The aircraft is equipped with dimmable instrument lights which comply with AWM 525.1381. 84.6.E.1; Sect. 3 Y  
    (1)(j) The aircraft is equipped with two pairs of landing lights, installed on the wing leading edge, outboard of the nacelle, which are compliant with AWM 525.1383. 84.6.E.1; Sect. 4 Y  
    (1)(k) The aircraft is equipped with a position light system which is compliant with AWM 525.1385 through 25.1397. The aircraft is equipped with two anti-collision strobe lights (one on the horizontal stabiliser bullet fairing, the other on the underside of the fuselage), which are compliant with AWM 525.1401. 84.6.E.1; Sect. 4 Y  
    (3) The DHC-8 Series 400 is not equipped, as part of the type certificated design, with any light which may be mistaken for or downgrade the conspicuity of any installed position lights.   Y  
    (4)(a) Refer to compliance statement against 605.15 (1)(e).      
    (4)(b) An inertial vertical speed indication (IVSI) is displayed on each pilot’s PFD. 84.6.R.14 Y  
    (4)(c) Refer to compliance statement against 605.14 (c).      
    (4)(d) A display of static air temperature, calibrated in degrees Celsius, is displayed on the Engine Display. The temperature source is from a dual temperature sensor located at the left wingroot and may be derived from either ADC 1 or ADC 2. 84.6.R.15 Y  
605.18 IFR – Aircraft Equipment Requirements (a)and (b) Refer to compliance statements against 605.14 (c) to (n) and compliance statements against 605.16 (1)(b) to (k) as applicable.      
    (c) Refer to compliance statement against 605.15 (1)(e).      
    (d) Refer to compliance statement against 605.16 (4)(b).      
    (e) Refer to compliance statement against 605.16 (4)(d).      
    (f) Refer to compliance statement against 605.14 (c).      
    (g) Flags and/or visual alerts are displayed to indicate when power is not adequately supplied to the required flight instruments as required by AWM 525.1331. 84.6.R.13
84.6.R.14
84.6.R.15
Y  
    (h) Two independent static pressure systems are installed, each externally vented. An independent standby combined pitot-static probe is also installed. The three systems are independent and not pilot selectable.
Each static pressure system complies with AWM 525.1325.
(i) and (j) Refer to compliance statements against 605.14 (k),(l), (m) and (n).
The DHC-8 Series 400 is equipped with a dual VHF Navigation system each with the capability to receive navigation signals from VOR navaids. Additionally, the aircraft is equipped with two ADF receivers and two DME transceivers.
84.6.R.4
84.6.R.24
84.6.R.21
84.6.R.23
Y  
605.22 Seat and Safety Belt Requirements Each passenger seat has been approved to TSO C127a and is equipped with a lap type safety belt with metal-to-metal latching device approved to TSO C22g. The front row seats have a unique Y-type lap belt installed. 84.8.AC.10; Sect.4
84.4.FF.4
Y  
    Each flight crew seat has been approved to TSO C127 or C127a and is equipped with a five point full safety harness approved to TSO-C114.
The observer’s seat has been approved to TSO C127 and is fitted with a lap belt and diagonal shoulder strap approved to TSO C114.
     
    Each flight attendant seat is approved to TSO C127 and is equipped with a four point combined shoulder harness and lap belt approved to TSO C114.      
    Each seat installation has been shown to comply with the requirements of AWM 525.785 and meets the static and dynamic load criteria set forth in AWM 525.561 and 525.562 respectively to protect the occupant in the event of an emergency landing.      
605.24 Shoulder Harness Requirements (1) Each flight crew seat is equipped with a five point full safety harness approved to TSO-C114. The observer’s seat is fitted with a lap belt and diagonal shoulder strap approved to TSO C114.

(2) Each flight attendant seat is equipped with a four point combined shoulder harness and lap belt approved to TSO C114.

Each seat installation has been shown to comply with the requirements of AWM 525.785 and meets the static and dynamic load criteria set forth in AWM 525.561 and 525.562 respectively to protect the occupant in the event of an emergency landing.
84.8.AC.10; Sect.4 84.4.FF.4 Y  
605.28 Child Restraint System It has been demonstrated that the passenger seats, including the front row seats, are compatible for use with current automotive type approved child safety seats. 84.8.AC.10; Sect. 18 OPS  
605.29 Flight Control Locks (a) The gust lock design places the gust lock lever well away from the reach of either pilot when disengaged and requires a conscious effort to engage it.

The gust lock cannot be engaged without interfering with the power levers when they are in any normal flight position. The gust lock is spring biased to the disengaged position such that a double failure is required to create the potential for gust lock engagement.

Inadvertant engagement in flight can be alleviated using the roll disconnect.

(b) Lateral controls are immobilised until the gust locks are disengaged; therefore pre-flight checks cannot be accomplished. Additionally, the power levers cannot be set to take-off power settings with the gust lock in the engaged position.
84.6.CF.1; Sect. 2.2 Y  
605.30 De-Icing or Anti-Icing Equipment The DHC-8 Series 400 is certificated and equipped with the appropriate de-icing and anti-icing systems for operation in icing conditions in accordance with AWM 525.1419. Wing ice detection lights are mounted on the fuselage and on the nacelle on each side of the aircraft to detect the formation of ice on the wings. Testing has shown these will not cause glare or reflection that would handicap crewmembers in performing their duties. 84.6.DE.1 84.6.E.1; Sect. 4 Y  
605.31 Oxygen Equipment and Supply (2) The cabin pressure altitude is maintained at a max. of 8000 feet during all phases of flight. The DHC-8 Series 400 is equipped with supplemental oxygen which provides the quantity of oxygen required, considering altitude limitations of the aircraft, likely flight durations and the need to conduct an emergency descent in accordance with the AFM following cabin depressurisation.

The DHC-8 Series 400 is capable of descending from 25,000 ft to 13,000 ft in 4 minutes. The flight crew are provided with a fixed oxygen system incorporating a mask mounted diluter-demand type regulator qualified to TSO C89. Two, TSO C78 approved, quick donning oronasal type oxygen masks for the pilots are located in stowages on the bulkhead behind the pilots seats, within easy reach. The flight crew masks are continuously coupled to the supply outlets to ensure oxygen is readily available. Means to indicate the oxygen quantity and satisfactory flow is provided for the flight crew to assist them in determining serviceability.

Sufficient oxygen is provided for the flight crew to descend from its max operating altitude of 25,000 ft. to 13,000 ft. in 4 minutes and to continue at altitudes above 10,000 ft. for a further 116 minutes. The minimum mass flow rates meet AWM 525.1443(b) requirements.

An additional mask for the observer is also located in the flight compartment. Flight with an observer will consequently increase the minimum dispatch pressure in order to maintain this supply of oxygen.

A portable passenger oxygen system will supply sufficient oxygen for at least 30 minutes at cabin pressure altitudes above 10,000 ft, for 10% of the max passenger load and both required flight attendants.

Three oxygen cylinders are each fitted with constant flow type regulators and three TSO C64a qualified masks. Two are located in stowage compartments at the aft end of the cabin and one in the forward draft bulkhead stowage. Each location is prominently marked and within easy reach of the cabin crew at their stations.

The minimum despatch pressures are specified in the AOM.

The oxygen equipment including the cylinders, distribution and dispensing equipment comply with the applicable requirements of AWM 525.1441 through 525.1453.

84.6.SB.1 Y  
605.33 Flight Data Recorder and Cockpit Voice Recorder Requirements The DHC-8 Series 400 is not certificated for flight above FL250.

The DHC-8 Series 400 is currently equipped with a digital FDR capable of recording the parameters required by paragraphs (a)(1) through (a)(34) of FAR 121.344 (with the exception of parameters (a)(12) through (a)(14)) to the ranges, accuracies, recording intervals and resolutions required by FAR Part 121 Appendix M. Additional parameters are also recorded.
84.6.R.11
Y
 
   

An approved CVR qualified to TSO C123 is installed in the aircraft and complies with the installation requirements of AWM 525.1457.

A bulk erasure feature, with a discrete signal to the parking brake, is incorporated in the CVR which is designed to minimise the probability of inadvertant operation of this feature or accidental actuation during a crash impact.
84.6.R.7 Y  
605.35 Transponder and Automatic Pressure Altitude Reporting Equipment A dual Mode-S transponder and antenna system (SSR), approved to TSO C112, is installed in the DHC-8 Series 400 aircraft. 84.6.R.22 Y  
605.36 Altitude Alerting System The DHC-8 Series 400 is fitted with an altitude alerting system which provides both aural and visual alerts upon approaching a pre-selected altitude. The system alerts the pilot 1,000 feet prior to arrival, in either ascent or descent, at a pre-selected altitude by both a visual alert on each PFD and an aural tone. 84.6.R.10 Y  
605.37 Ground Proximity Warning System The DHC-8 Series 400 is equipped with a GPWS, approved to TSO C92b. Operating procedures for the GPWS system will be provided in an approved AFM Supplement. The GPWS provides a protection envelope covering Modes 1 through 6. 84.6.R.19 Y  
605.38 Emergency Locator Transmitter An ELT meeting TSO C91a specification is installed as standard on the DHC-8 Series 400 within the dorsal fin to fuselage fairing and in such a manner that probability of damage to the transmitter in the event of a crash impact is minimised. 84.6.R.8 Y  
605.41 Standby Attitude Indicator A standby gyroscopically stabilised display of attitude is installed to the left of the Engine Display (ED) and is capable of being used by either pilot.

It is powered continuously by both the left and right Essential DC buses (i.e. independent of the electrical generating system) thus there is no specific indication of operation by emergency power. The ADI does not have a dedicated power supply.

It continues reliable operation for a minimum of 30 minutes after total failure of the electrical generating system.

It operates independently of any other attitude indicating system.

It is operative, without selection, after total failure of the electrical generating system. It is appropriately lighted during all phases of operation. The standby ADI backlighting is from the left Main DC bus. Should the bus fail, the storm and/or the flight deck dome light will provide the required illumination.
84.6.R.14 Y  
705.67 General Requirements        
  Static Pressure Systems (a) Two independent static pressure systems are installed, each externally vented.
An independent standby combined pitot-static probe is also installed.
The three systems are independent and not pilot selectable.
Each static pressure system complies with AWM 525.1325.
84.6.R.13
84.6.R.15
Y  
  Windshield Wipers (b) The DHC-8 Series 400 has two windshield wipers, one on the pilot’s windshield and one on the co-pilot’s windshield. The wiper systems are independently driven so that in the event of failure of either unit, the remaining one will preserve unobstructed forward visibility for the pilot. 84.6.DE.1:
Sect. 2.5
Y  
  Internal Door Placards (d) The only internal doors are the flight compartment door, forward baggage compartment door and lavatory door. There are no internal doors that would obstruct access to a passenger emergency exit. 84.8.AC.10; Sect. 6 Y  
  Crew Access Means – Lockable Internal Doors Accessible to Passengers (e) The lavatory door latching mechanism has means to enable disengagement from the cabin side without use of special tools. 84.8.AC.10; Sect.3 Y  
705.68 Landing Lights The aircraft is equipped with two pairs of landing lights, installed on the wing leading edge, outboard of the nacelle, which are compliant with AWM 525.1383. 84.6.E.1; Sect. 4 Y  
705.69 Operation of Aircraft in Icing Conditions (1) The DHC-8 Series 400 is certificated and equipped with the appropriate de-icing and anti-icing systems for operation in icing conditions in accordance with AWM 525.1419. 84.6.DE.1 Y  
    (2) Wing ice detection lights are mounted on the fuselage and on the nacelle on each side of the aircraft to detect the formation of ice on the wings. Testing has shown these will not cause glare or reflection that would handicap crewmembers in performing their duties. 84.6.E.1; Sect. 4 Y  
705.70 Weather Radar Equipment The DHC-8 Series 400 is equipped with airborne weather radar equipment approved to TSO C63c. 84.6.R.17 Y  
705.71 Protective Breathing Equipment Fixed PBE is provided for the flight crewmembers. The flight crew PBE comprises eye goggles, which when used in conjunction with the supplemental oxygen dispensing equipment required for complying with CAR 605.31, meets the requirements of TSO C99 and is compliant with AWM 525.1439(b).
Additionally, a TSO C116 qualified portable PBE unit is installed in the flight compartment in a stowage container behind the co-pilot’s seat, near the fire extinguisher.  This unit is intended for crewmember use in combatting an in-flight fire.
It provides sufficient oxygen for 15 minutes at cabin pressure altitudes up to 8000 ft and fully complies with AWM 525.1439(b).
84.6.SB.1; Sect. 2 Y See Note 1.
    Three TSO C116 qualified portable PBE units, similar to the flight compartment unit, are installed in the passenger compartment adjacent to each required fire extinguisher. These are intended for flight attendant use in combatting an in-flight fire. Each location is prominently marked and within easy reach of the cabin crew at their stations.

Means to indicate the oxygen quantity and satisfactory flow is provided for the flight crew to assist them in determining serviceability. Each portable PBE unit has an indicator disc to allow determination of the serviceability of the unit.
84.6.SB.101;
Sect. 5
Y See Note 1.
705.72 First Aid Oxygen A customer option modification is available to equip the aircraft with first-aid oxygen.
Two oxygen cylinders are each fitted with constant flow type regulators and a TSO C64a qualified mask. They are located in stowage compartments at each end of the cabin. Each location is prominently marked.
Equipment performance complies with AWM 525.1443(d). At an average flow rate of 3LPM, the two cylinders provide sufficient oxygen for two people for one hour when charged to 1650 psig.
84.6.SB.101;
Sect. 1
Y See Note 1.
705.73 Interphone System The DHC-8 Series 400 aircraft is equipped with a PACIS system with the crew interphone function capable of being operated independently of the PA function. Handsets, headsets, microphones, selector switches and signalling devices are common to both functions as permitted.
The crew interphone function is readily accessible for use from the flight crew and flight attendant stations and provides for two-way communication between the pilot compartment and the two required flight attendant stations within the passenger compartment.
The system is provided with an alerting system comprising visual alerts for PA use and aural and visual alerts for interphone use. The alerts are visible via annunciator lights on each flight deck ARCDU and each flight attendant station control panel. The system annunciator lights are steadily illuminated for a normal call and flash for an emergency call.
84.6.R.3
84.6.R.6
Y  
705.74 Public Address System The aircraft is equipped with an approved PA system which complies with AWM 525.1423. The PA function of the PACIS system is capable of operation independent of the crew-member interphone function.
The cabin crew can access the PA system independently of the flight crew and while the flight crew are using the separate crew interphone system. The PA system is prioritised with the flight crew having priority over cabin crew.

 

84.6.R.6 Y  
705.75 Crewmember Shoulder Harnesses Each flight crew seat has been approved to TSO C127 or C127a and is equipped with a five point full safety harness approved to TSO-C114.
The observer’s seat has been approved to TSO C127 and is fitted with a lap belt and diagonal shoulder strap approved to TSO C114.
Each flight attendant seat is approved to TSO C127 and is equipped with a four point combined shoulder harness and lap belt approved to TSO C114.
84.8.AC.10;
Sect 4
Y  
705.76 Lavatory Fire Protection (a) A smoke detector with a built-in screamer is provided in the lavatory which flight testing has shown to provide the required warning to the crew as to comply with AWM 525.854(a).

 

84.6.CA.1;
Sect. 2.8
Y  
    (b) The lavatory waste container is equipped with a built-in fire extinguisher, containing Halon 1301, designed to automatically discharge upon detection of a preset actuation temperature. 84.8.AC.10;
Sect. 3
Y  
    (c) NO SMOKING IN LAVATORY placards are installed on each side of the lavatory door to comply with AWM 525.791 (d). 84.8.AC.10;
Sect. 9
Y  
    (d) A NO CIGARETTE DISPOSAL placard is installed near the waste receptacle in the lavatory to comply with AWM 525.791(c). 84.8.AC.10;
Sect. 9
Y  
    (e) Self-contained, removable ashtrays are provided in the armrest of each seat and on each side of the lavatory door to comply with AWM 525.853(f) and (g). 84.8.AC.10;
Sect. 3
Y  
705.77 Flammability Requirements for Seat Cushions All the materials used within compartments occupied by passengers or crew, including the passenger compartment seat cushions, meet the applicable flammability requirements of AWM 525.853 as tested in accordance with the applicable Parts of AWM 525 Appendix F. 84.8.AC.9 Y  
705.78 Floor Proximity Emergency Escape Path Markings The floor proximity emergency escape path marking system consists of photoluminescent strips along each side of the main aisle, running the entire length of the cabin and extending into the emergency exit access aisles at the forward exits, and electrically powered emergency exit identifiers installed adjacent to each exit at not more than 48 inches from the floor. It has been demonstrated by test to comply with AWM 525.812(e). 84.8.AC.10;
Sect. 11

84.6.E.1; Sect. 5.7
Y  
705.79 Flashlight Stowage Each flight attendant station is provided with a flashlight, stowed beneath the seats and protected by a quick release panel. 84.8.AC.10; Sect. 7 Y  
705.89 Megaphones The DHC-8 Series 400 has one megaphone which is readily accessible to the flight attendant at the forward flight attendant station. 84.8.AC.10; Sect. 7 Y See Note 1.
705.90 First Aid Kits The DHC-8 Series 400 aircraft is equipped with two first aid kits  located in the passenger compartment and meeting Transport Canada Commercial Air Service Standards.

These are uniformly distributed in the cabin, one at the forward end of the cabin and one at the aft end. Each location is prominently marked and within easy reach of the cabin crew at their stations.
84.8.AC.10; Sect. 7 Y See Note 1.
705.91 Emergency Medical Kits The DHC-8 Series 400 is configured with 78 passenger seats. Therefore an emergency medical kit is not required.      
705.92 Crash Axe A crash axe is installed in the flight compartment on the bulkhead behind the pilots seat. 84.8.AC.10; Sect. 7 Y  
705.93 Hand Held Fire Extinguishers There are a total of four approved 3.5lbs hand fire extinguishers (Halon 1211) on the DHC-8 Series 400 aircraft, designed for use on Class A, B and C fires. They have a toxicity rating of 5 per NFPA Std 12B.
One extinguisher is located in the flight compartment, behind the pilot’s seat.
Three are uniformly distributed in the cabin, one at the forward end of the cabin and two at the aft end and readily accessible for use in the galley area. Each location is prominently marked and within easy reach of the cabin crew at their stations
All galleys are located on the main passenger deck for the DHC-8 Series 400 aircraft. There are no isolated galleys.
The baggage compartments on the DHC-8 Series 400 aircraft are Class C and have their own built-in fire suppression systems.
84.8.AC.10; Sect. 7 Y See Note 1.
705.94 Portable Oxygen The DHC-8 Series 400 is not certificated for flight above FL250.

However, the DHC-8 Series 400 is capable of descending from 25,000 ft to 13,000 ft in 4 minutes and a portable passenger oxygen system is installed which will supply sufficient oxygen for at least 30 minutes at cabin pressure altitudes above 10,000 ft for 10% of the max passenger load and both required flight attendants.
84.6.SB.1; Sect. 2 Y  
705.95 Survival Equipment Although the DHC-8 Series 400 has the necessary structural provisions for ditching certification, certification for ditching is not included as part of the basic Type Certificate. Operator’s must ensure the required survival equipment is installed before conducting operations as specified in CAR 602.61 or 602.63.   OPS See Note 1.
705.96 Emergency Equipment Inspection Requirements It is the Operator’s responsibility to ensure that the emergency equipment required under this Division VI of CAR 705 is inspected in accordance with an approved schedule and is in a serviceable condition.   OPS See Note 1.
705.97 Flashlights Each flight attendant station is provided with a flashlight, stowed beneath the seats and protected by a quick release panel. 84.8.AC.10; Sect. 7 Y See Note 1.
Date modified: