Supplemental Type Certificate Number: STC SVA582
Cessna 208 Caravan · Supplemental Type Certificate
Overview
This document is a Supplemental Type Certificate (STC) issued by the Australian Government's Civil Aviation Safety Authority for modifications made to the Cessna 208 and Cessna 208B aircraft. The STC certifies that the type design changes meet the applicable airworthiness requirements for Approved Single Engine Turbine Powered Aeroplanes (ASETPA). The primary modification involves replacing the original Pratt and Whitney PT6A-114(A) engine with a Pratt and Whitney PT6A-140 engine and a Hartzell propeller. The document outlines the limitations and conditions of the approval, as well as the certification basis and requirements for continued airworthiness. It is intended for use by aircraft owners, operators, and maintenance personnel involved in the modification and operation of these aircraft models.
- Modification involves replacing PT6A-114(A) engine with PT6A-140 engine.
- Compatible with Cessna 208 and 208B models only.
- Must comply with CAO 100.5 for ASETPA operations.
- Not compatible with specific serial numbers of Cessna 208 and 208B.
- Certification based on 14 CFR part 23 regulations.
Document
Source
Originally published by www.casa.gov.au. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Supplemental Type Certificate
- Year
- 2018
- Pages
- 2
- File size
- 485 KB
- Publisher
- www.casa.gov.au
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- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
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In this document
Description of Type Design Change
The STC details the replacement of the original Pratt and Whitney PT6A-114(A) engine with a PT6A-140 engine, along with a 3-blade Hartzell Propeller HC-B3TN-3AF(Y)/T10890CN(K)-2. The modifications must comply with FAA STC SA02546LA and are to be installed according to the FAA Approved Master Drawing List 201321-000, Rev IR, dated April 6, 2015, or later revisions.
Limitations and Conditions
The approval is not transferable to other aircraft models that have previously approved modifications unless the installer confirms no adverse effects on airworthiness. The aircraft must comply with CAO 100.5 for ASETPA operations, and the modification is not compatible with certain serial numbers of the Cessna 208 and 208B models.
Certification Basis
The certification is based on 14 CFR part 23 of the Federal Aviation Regulations, effective February 1, 1965, with various amendments. It includes special conditions for dynamic evaluation and engine installation.
Safety notes
- Approval not transferable to other aircraft with previous modifications unless confirmed safe.
- Modification not compatible with certain serial numbers.
Full document text
Australian Government Cml Aviation SafetyAuthority Supplemental Type Certificate Number: STC SVA582 This certificate issued to: Polar Aviation Suite 18 Hay Street Subiaco Western Australia, 6008 certifies that the type design for the following changed product with the limitations and conditions as specified herein meets the applicable ainvorthiness requirements for Approved Single Engine Turbine Powered Aeroplanes (ASETPA). Original Product: Type Acceptance Certificate Number: Referenced TC Number: Make/Model: A320 FAA A37CE Textron Aviation Inc. 208, 208B Description of Type Design Change: Option One: Replacement of the original Pratt and Whitney PT6A-114(A) engine and propeller with a Pratt and Whitney PT6A-140 and 3-blade Hartzell Propeller HC-B3TN-3AF(Y)/T10890CN(K)-2 and equipment in accordance with FAA STC SA02546LA, inclusive of Howell Instruments powerplant indicating system. Installations done in accordance with FAA Approved Master Drawing List 201321-000, Rev IR, dated Apr 6, 2015, or later FAA approved revisions. Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplements, AFMS 201321-208, Rev IR, dated Oct 09, 2015, or 201321-208B, Rev IR, dated October 09, 2015 or later FAA approved revisions. Instructions for continued airworthiness are contained in document ICA 201321-30, Rev IR, dated August 2015, or later. Date of application: 19/09/2018 Date of issuance: 01/11/2018 This certificate is issued pursuant to Part 21.113A of the Civil Aviation Regulations 1998. X^^i0^ ^^-—^/-£?> \%; RichaN?^ Delegate^iN eWefS. Supplemental Type Certificate- SVA582 (Continuation Sheet) Limitations and Conditions: This approval should not be extended to other aircraft of this model on which other previously approved modifications are incorporated unless it is determined by the installer that the interrelationship between this change and any of those previously approved modifications will produce no adverse effect upon the airworthiness of that aircraft. 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. This certificate and the supporting data which is the basis for approval shall remain in effect until suspended, cancelled or a termination date is otherwise established by the Civil Aviation Safety Authority. Conditions: The aircraft must meet the requirements of CAO 100.5 forASETPA operations. This modification is not compatible with Cessna Model 208, Serial Number 20800500 and greater or Cessna Model 208B Serial Number 208B1190, 208B1216, and 208B2000 and greater (Garmin 1000 installations) and aircraft equipped with TKS installation. Certification Basis: 14 CFR part 23 of the Federal Aviation Regulations effective February 1, 1965, as amended by Amendments 23-1 through 23-62 for 23.1, 23.25, 23.29, 23.33, 23.45, 23.53, 23.63, 23.65, 23.69, 23.75, 23.77, 23.143, 23.145, 23.161, 23.171, 23.173, 23.175, 23.177, 23.201, 23.203, 23.207, 23.251, 23.301, 23.303, 23.305, 23.307, 23.361, 23.363, 23.601, 23.603, 23.605, 23.607, 23.609, 23.611, 23.613, 23.619, 23.625, 23.627, 23.629, 23.863, 23.865, 23.901, 23.903, 23.905, 23.907, 23.925, 23.929, 23.933, 23.937, 23.939, 23,943, 23.993, 23.997, 23.1011, 23.1017, 23.1021, 23.1023, 23.1027, 23.1041, 23.1043, 23.1045, 23.1091, 23.1093, 23.1103, 23.1121, 23.1123, 23.1141, 23.1143, 23.1145, 23.1149, 23.1153, 23.1155, 23.1163, 23.1165, 23.1183, 23.1193, 23.1301, 23.1305, 23.1309, 23.1351, 23.1353, 23.1357, 23.1359, 23.1361, 23.1365, 23.1367, 23.1519, 23.1529, 23.1541, 23.1549, 23.1581, 23.1583, 23.1585, 23.1587, 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(a)(b)(c)(e)(1) and (2). 2. 14 CFR 34, effective January 1, 1994, as amended by Amendments 34-0. 3. 14 CFR 36, effective December 1, 1969, as amended through Amendment 36-30. This certificate may be transferred in accordance with CASR (1998) 21.47 Page 2 of 2 CAS402 Printed 05/2016 -T&