| AD Number | 86-10-05 | Status | Active |
| Effective Date | June 05, 1986 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-5266 |
| Product Type | ["Engine"] | Product Subtype | Not specified |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Pratt & Whitney Canada Corp. |
| Model(s) | PT6A-42 |
86-10-05 PRATT & WHITNEY CANADA: Amendment 39-5266. Applies to Pratt & Whitney Canada (PWC) PT6A-42 turboprop engines.
Compliance is required as indicated unless already accomplished.
To prevent first stage compressor hub failure, and possible engine failure, accomplish the following:
Remove from service Part Number (P/N) 3030356 first stage compressor hub on PWC Engine Model PT6A-42 with engine Serial Numbers 93001 thru 93804 inclusive at or before 5,000 total cycles in accordance with PWC Service Bulletin (SB) 3002, Revision 12, dated November 9, 1983, or FAA approved equivalent.
NOTE: The 15,000 hour life limit remains unaffected by this airworthiness directive (AD).
Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished.
PWC SB 3002, Revision 12, dated November 9, 1983, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Pratt & Whitney Canada, Longueuil, Quebec, Canada, J4K-4X9. This document also may be examined at the Office of the Regional Counsel, Rules Docket 85-ANE-29, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803.
This amendment becomes effective on June 5, 1986.