Pursuant to paragraph 5.9(2) of the Aeronautics Act, and after taking into account that the exemption is in the public interest and is not likely to affect aviation safety, I hereby exempt DECA Aviation Engineering Limited (hereinafter "DECA") 1804 Alstep Drive, Unit 21, Mississauga, Ontario from the requirements of the Canadian Aviation Regulation (CARs) 513.07(1)(a) only with respect to the requirements of paragraph 525.813(e) of the Airworthiness Manual
Paragraph 525.813(e) of the Airworthiness Manual requires that no door be installed in any partition between passenger compartments in transport category aeroplanes.
The details of the above provisions are provided in Appendix A.
PURPOSE
The purpose of this exemption is to allow DECA to install a door in a partition between passenger compartments on any BD700-1A10 aeroplane, for the purpose of private operator passenger transportation pursuant to CAR 604 or on-demand air transport service pursuant to CAR 704.
APPLICATION
This exemption applies to DECA only for the installation of a door in a partition between passenger compartments on any BD700-1A10 aeroplane (Type-Certificate No. A-177) with a maximum of 19 passengers for the purpose of private operator passenger transportation pursuant to CAR 604 or on-demand air transport service pursuant to CAR 704.
CONDITIONS
This exemption is subject to the following conditions:
- When operated under CAR 704, the "on-demand" client shall not sub-charter the aircraft to a third party or charge or accept remuneration from any third party for air transportation services.
- No more than one partition of the passenger seating area which incorporates a door shall be permitted.
- The door between passenger compartments shall translate laterally to open and close;
- The door between passenger compartments shall be frangible;
- The door between passenger compartments and, if applicable, any other door between a passenger compartment and emergency exits shall have dual means to retain it in the open position, each of which is capable of reacting the inertia loads specified in AWM 525.561;
- The door between passenger compartments and, if applicable, any other door between a passenger compartment and emergency exits shall have a means to signal to the flight crew in a timely manner when the cabin door(s) is (are) not latched open. This feature shall be integrated with the existing Engine Indicating and Crew Alerting System (EICAS). Appropriate procedures/limitations to ensure that take-off and landing is prohibited, when any such door is not in the proper take-off and landing configuration, shall be established;
- The door between passenger compartments and, if applicable, any other door between a passenger compartment and emergency exits shall be operable from either side and if a locking mechanism is installed, it shall be capable of being unlocked from either side without the aid of special tools;
- Where the door is to be installed in specified egress paths, a Supplement to the Aeroplane Flight Manual shall be developed containing:
- Instruction on the door operation, including its frangibility feature, and
- a limitation specifying that the aeroplane is limited to private operator passenger transportation pursuant to CAR 604 or on-demand air transport service pursuant to CAR 704 and shall comply with the applicable operational regulations, standards, policies and authorities, and
- instruction regarding the briefing of passengers in accordance with the applicable operational requirements CAR 604.18 or CAR 704.34. The briefing shall include the information from the AFM Supplement required at (h)(1) above.
- Due to the size and the layout of the aircraft a PA (Public Address) System shall be installed to allow effective communication between crew and passengers in an emergency situation. In lieu of compliance with AWM 525.1423, the applicant shall demonstrate to the Minister by means of functional tests at system integration/aircraft level that the PA system is:
- Powerable when the aircraft is in flight or stopped on the ground, after the shutdown or failure of all engines and auxiliary power units, or the disconnection or failure of all power sources dependent on their continued operation;
- Intelligible at all seats, lavatories, and work stations; and
- Accessible for immediate use from each crewmember station in the pilot compartment.
Note: It is not necessary for any of the components of the PA System to meet any particular TSO standard.
VALIDITY
This exemption is in effect until the earliest of the following:
- the date on which an amendment to the appropriate provisions of the Canadian Aviation Regulations comes into effect;
- the date on which any one of the conditions set out in this exemption is breached; or
- the date on which this exemption is cancelled in writing by the Minister where he is of the opinion that the exemption is no longer in the public interest or that it is likely to affect aviation safety.
Dated at Ottawa, Ontario this 31st day of October 2003, on behalf of the Minister of Transport.
Martin J. Eley
Director, Aircraft Certification
Civil Aviation
EXEMPTION FROM SECTION 513.07(1)(a) OF THE CANADIAN AVIATION REGULATIONS AND PARAGRAPH 525.813(e) OF THE AIRWORTHINESS MANUAL
APPENDIX A
Canadian Aviation Regulations 513
Approval of Modifications and Repair Designs
513.07(1)(a)
An applicant for a supplemental type certificate, a limited supplemental type certificate or a change to these certificates shall show that the changed aeronautical product meets the standards of airworthiness that are in force on the date of application for the proposed change.
Airworthiness Manual Section 525
525.813 Emergency Exit Access
Each required emergency exit must be accessible to the passengers and located where it will afford an effective means of evacuation. Emergency exit distribution must be as uniform as practical, taking passenger distribution into account; however, the size and location of exits on both sides of the cabin need not be symmetrical. If only one floor level exit per side is prescribed, and the aeroplane does not have a tail cone or ventral emergency exit, the floor level exit must be in the rearward part of the passenger compartment, unless another location affords a more effective means of passenger evacuation. Where more than one floor level exit per side is prescribed, at least one floor level exit per side must be located near each end of the cabin, except that this provision does not apply to combination cargo/passenger configurations. In addition:
e) No door may be installed in any partition between passenger compartments.
- Date de modification :