2001-13-19
FR doc 01-16736 · 66 FR 35538AD 2001-13-19Published 2001-07-06Effective 2001-08-10
Requires revising the Bombardier maintenance program to incorporate repetitive inspections to detect fatigue cracking in certain structures; and corrective actions, if necessary.
1 correction to this AD FAA · 2001-08-27
Correction published 2001-08-27
- Issued by
- Federal Aviation Administration
- Published
- 2001-08-27
- Document
- Federal Register 01-21490 · Final rule; correction
This document corrects information in an existing airworthiness directive (AD) that applies to all Bombardier Model DHC- 8-102, -103, -106, -201, -202, -301, -311, -314, and -315 series airplanes. That AD currently requires revising the Bombardier maintenance program to incorporate repetitive inspections to detect fatigue cracking in certain structures; and corrective actions, if necessary. This document corrects certain airplane models specified in Table 1 of the final rule. This correction is necessary to ensure that operators are notified of the correct airplane models, as specified in Canadian airworthiness directive CF-2000-07, dated March 3, 2000, and de Havilland Temporary Revision TR AWL 2-15, dated September 3, 1999.
A correction restates part of an AD that was published incorrectly. It is not an additional requirement and it does not change the AD number or its effective date.
Source: Federal Register document 01-21490, retrieved 2026-08-17
Full official abstract
This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model DHC-8-102, -103, -106, -201, -202, - 301, -311, -314, and -315 series airplanes, that requires revising the Bombardier maintenance program to incorporate repetitive inspections to detect fatigue cracking in certain structures; and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information issued by a foreign airworthiness authority. The actions specified by this AD are intended to ensure that fatigue cracking of certain principal structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.