Pursuant to subsection 5.9(2) of the Aeronautics Act and after taking into account that the exemption is both in the public interest and is not likely to affect adversely aviation safety, I hereby exempt Canadian air operators and their flight crew members from the requirements of paragraphs 723.22(1)(a) and (b) of the Commercial Air Service Standards (CASS) made pursuant to paragraph 703.22(2)(b) of the Canadian Aviation Regulations (CARs), subject to the conditions set out below.
Details of paragraph 703.22(2)(b) of the CARs and paragraphs 723.22(1)(a) and (b) of Standard 723 – Air Taxi – Aeroplanes are set out in Appendix A of this exemption.
PURPOSE
This exemption will allow Canadian air operators and their flight crew members to operate Cessna Caravan Model C208 aeroplanes retrofitted with PT6A-42A turboprop engine in accordance with the Supplemental Type Certificate STC SA02357LA issued by the FAA.
APPLICATION
This exemption applies to a Canadian air operator and its flight crew members for the purposes of operating a Cessna Caravan C208 aeroplane that has been retrofitted with PT6A-42A in accordance with STC SA02357LA (attached in Appendix B) and is being operated under subpart 3 of Part VII of the CARs.
The limitation and conditions of STC SA02357LA are as follows :
-
AeroAcoustics Aircraft Systems, Inc., “Aircraft Payload Extender STOL System,” STC SA01805SE is required as part of this alteration;
-
This modification is not compatible with Cessna Model 208B Serial Number 208B1190, 208B1216 and 208B2000 and greater (Garmin 1000 installations) and aircraft equipped with STC SA01478WI or Cessna SK208-174 (TKS installation).
CONDITIONS
This exemption is subject to the following conditions:
-
The air operator shall ensure that the retrofit of the Cessna Caravan C208 is completed in accordance with the Supplementary Type Certification STC SA02357LA which is fully compliant with the certification basis of the aircraft Type Certificate Data Sheet.
-
The air operator shall provide a transition ground school session to ensure that the pilot-in-command and the flight crew members are conversant with the operation of the C208 aeroplane in accordance with subsection 723.98(24) of the CASS.
VALIDITY
The exemption is in effect until the earliest of the following:
-
November 1st, 2014 at 23:59 EDT;
-
the date on which any 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 it is no longer in the public interest, or that it is likely to adversely affect aviation safety.
Dated at Ottawa, Ontario, Canada this____7th day of February 2013 , on behalf of the Minister of Transport.
[original signed by David Salisbury for]
Martin J. Eley
Director General,
Civil Aviation
Transport Canada
Appendix A
Pertinent provisions
703.22 Transport of Passengers in Single-engined Aircraft
- Subject to subsection (2), no air operator shall operate a single-engined aircraft with passengers on board in IFR flight or in night VFR flight.
- An air operator may operate a single-engined aircraft with passengers on board in IFR flight or in night VFR flight if the air operator
- is authorized to do so in its air operator certificate; and
- complies with the Commercial Air Service Standards.
- is authorized to do so in its air operator certificate; and
723.22 Transport of Passengers in Single-Engined Aeroplanes
The standard for transport of passengers in a single-engined aeroplane under IFR or VFR at night is:
- General
- only factory built, turbine-powered aeroplanes are permitted;
- the turbine-engine of the aeroplane type must have a proven Mean Time Between Failure (MTBF) of .01/1000 or less established over 100,000 hours in service; and
- pilot training in accordance with subsection 723.98(24).
- only factory built, turbine-powered aeroplanes are permitted;
Appendix B
United States Of America
Department of Transportation - Federal Aviation Administration
Supplemental Type Certificate
____________________________________________________________________________________________________________________________________
Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.
____________________________________________________________________________________________________________________________________
FAA Form 8110-2(10-68) Page 1 of 3 This certificate may be transferred in accordance with FAR 21.47.
Number SA02357LA
This Certificate issued to Blackhawk Modifications Inc.
7601 Karl May Drive
Waco, Texas 76708
certifies that the change in the type design for the following product with the limitations and conditions
therefor as specified hereon meets the airworthiness requirements of Part 23* of the Federal Aviation
Regulations. *Certification basis set forth on continuation sheet 2
Original Product Type Certificate Number :
Make :
Model :
A37CE
Cessna
208B
Description of Type Design Change: Replacement of the original Pratt and Whitney PT6A-114(A)engine and propeller with a Pratt and Whitney PT6A-42A and 4-blade Hartzell Propeller HCE4N-3P/D9900(K) propeller and associated equipment in accordance with FAA Approved Master Drawing List 200803-000, Revision A, dated March 29, 2012, or later FAA approved revisions and Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement, AFMS 200803, Rev IR, dated June 22, 2011 or later FAA approved revisions. Blackhawk Modifications Inc. Instructions for Continued Airworthiness document ICA 200803-
30, Revision A, dated May 2011, or later revisions.
Limitations and Conditions: The installation should not be incorporated in any aircraft unless it is determined that the interrelationship between this installation and any previously approved configuration will not introduce any adverse effect upon the airworthiness of that aircraft. The approval of this modification applies to the above-noted airplane models only. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission. (CONTINUED on page 3)
This certificate and the supporting data which is the basis for approval shall remain in effect until surrendered, suspended, revoked or a termination date is otherwise established by the Administrator of the Federal Aviation Administration.
Date of application : April 28, 2009
Date of issuance : June 23, 2011
Date reissued :
Date amended : April 16, 2012
By direction of the Administrator
____________________________________
(Signature)
Thomas A. Enyart
Manager, Propulsion Branch
Los Angeles Aircraft Certification Office
(Title)
United States Of America
Department of Transportation - Federal Aviation Administration
Supplemental Type Certificate
(Continuation Sheet)
____________________________________________________________________________________________________________________________________Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both.
____________________________________________________________________________________________________________________________________
FAA Form 8110-2(10-68) Page 3 of 2 This certificate may be transferred in accordance with FAR 21.47
Number SA02357LA
Limitations and Conditions(continued)
AeroAcoustics Aircraft Systems, Inc., “Aircraft Payload Extender STOL System,” STCSA01805SE is required as part of this alteration.
This modification is not compatible with Cessna Model 208B Serial Number 208B1190, 208B1216, and 208B2000 and greater (Garmin 1000 installations) and aircraft equipped with STC SA01478WI or Cessna SK208-174 (TKS installation).
Certification Basis
The certification basis for this modification is as follows:
14 CFR part 23 of the Federal Aviation Regulations effective February 1, 1965, as amended by Amendments 23-1 through 23-59 for 23.1, 23.21, 23.23, 23.25, 23.33, 23.45, 23.49, 23.51,23.53, 23.63, 23.65, 23.69, 23.73, 23.75, 23.77, 23.141, 23.143, 23.145, 23.147, 23.153, 23.155,23.157, 23.161, 23.171, 23.173, 23.175, 23.177, 23.179, 23.181, 23.201, 23.203, 23.221,23.231, 23.233, 23.251, 23.253, 23.301, 23.303, 23.305, 23.307, 23.321, 23.331, 23.333.
23.335, 23.337, 23.341, 23.361, 23.363, 23.371, 23.421, 23.471, 23.473, 23.479, 23.481,
23.483, 23.485, 23.493, 23.499, 23.507, 23.509, 23.561, 23.572, 23.601, 23.603, 23.605,
23.607, 23.609, 23.611, 23.613, 23.619, 23.623, 23.625, 23.627, 23.629, 23.735, 23.771,
23.831, 23.863, 23.865, 23.867, 23.901, 23.903, 23.905, 23.907, 23.925, 23.929, 23.933,
23.939, 23.955, 23.959, 23.961, 23.991, 23.993, 23.994, 23.999, 23.1011, 23.1017, 23.1019,23.1021, 23.1023, 23.1027, 23.1041, 23.1043, 23.1045, 23.1091, 23.1091, 23.1103, 23.1111,23.1121, 23.1123, 23.1141, 23.1163, 23.1165, 23.1181, 23.1183, 23.1193, 23.1203, 23.1301,23.1305, 23.1308, 23.1309, 23.1321, 23.1322, 23.1327, 23.1322, 23.1327, 23.1329, 23.1337,23.1351, 23.1357, 23.1359, 23.1365, 23.1381, 23.1416, 23.1431, 23.1501, 23.1507, 23.1519,23.1521, 23.1525, 23.1527, 23.1529, 23.1541, 23.1543, 23.1547, 23.1549, 23.1551, 23.1555,23.1557, 23.1581, 23.1583, 23.1585, 23.1587, 23.1589, except 23.1419 as amended by 23-1 through 23-14.
1. Special Condition 23-ACE-3, Dynamic Evaluation, Engine Installation. Factors from this special condition were incorporated into the whirl mode flutter analysis per 14 CFR
§ 23.629(e)(1) and (2) Amendment 23-54, Flutter.
2. 14 CFR 34, effective January 1, 1994, as amended by Amendments 34-1 thru 34-3.3.
3. 14 CFR 36, effective December 1, 1969, as amended by Amendments 36-1 thru 36-28.
-END
- Date de modification :