AD 2001-13-19

Applicability: Model DHC-8-102, -103, -106, -201, -202, -301, -311, -314, and -315 series airplanes, certificated in any category.

Note 1:

This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To ensure continued structural integrity of these airplanes, accomplish the following:

(a) Within 30 days after the effective date of this AD, accomplish the actions required by either paragraph (a)(1) or (a)(2) of this AD, as applicable.

(1) Revise the Bombardier maintenance program by incorporating the threshold and repetitive inspection intervals specified in the Temporary Revisions (TR's) to the DHC-8 Maintenance Program Manuals, Airworthiness Limitations List (AWL), Structural Inspection Program Task No. 5310/31A, into the Bombardier maintenance program. The TR's for specific airplane models are listed in Table 1, as follows:

Note 2:

When the TR documents listed in Table 1 in paragraph (a)(1) of this AD are incorporated into the general revisions of the DHC-8 Maintenance Program Manual, you may insert the general revisions into the Bombardier maintenance program, provided that the information contained in the general revisions is identical to that specified in the TR documents.

(2) For airplanes having closing angles that are identified as principal structural elements: Do the inspections specified by the applicable TR listed in Table 1 of paragraph (a) of this AD. Thereafter, repeat the inspection at intervals not to exceed 10,000 flight cycles at the time specified in paragraph (a)(2)(i), (a)(2)(ii), or (a)(2)(iii) of this AD, as applicable.

(i) For airplanes that have accumulated less than 8,000 flight cycles as of the effective date of this AD: Do the threshold inspection prior to the accomplishment of 10,000 flight cycles, or within 2,000 flight cycles after the effective date of this AD, whichever occurs later.

(ii) For airplanes that have accumulated 8,000 flight cycles or more as of the effective date of this AD: Do the threshold inspection within 2,000 flight cycles after the effective date of this AD.

(iii) For airplanes on which a 40,000 flight cycle inspection specified by the applicable TR listed in Table 1 of paragraph (a) of this AD has been done: Start the 10,000 flight cycle repetitive inspection at the time specified by paragraph (a)(2)(iii)(A) or (a)(2)(iii)(B) of this AD, as applicable.

(A) If no cracks were found, start the cycle from the date of the 40,000 flight cycle inspection.

(B) If cracks have been found and the closing angles have been replaced as provided in paragraph (b) of this AD, start the cycle from the date of the replacement.

(b) If any crack is detected during any structural inspection required by paragraph (a)(2) of this AD, before further flight, repair any such cracking or replace the closing angles per a method approved by the Manager, New York Aircraft Certification Office (ACO), FAA; or the Transport Canada Civil Aviation (or its delegated agent). For a repair or replacement method to be approved by the Manager, New York ACO, as required by this paragraph, the Manager's approval letter must specifically reference this AD.

(c) Except as provided by paragraph (d) of this AD: After the actions specified in paragraphs (a) and (b) of this AD have been accomplished, no alternative inspections or inspection intervals may be approved for the structural elements specified by the documents listed in Table 1 of paragraph (a)(1) of this AD.

(d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO.

Note 3:

Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO.

(e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.

(f) Except as provided in paragraph (b) of this AD, the actions shall be done in accordance with de Havilland Temporary Revision TR AWL-71, dated September 3, 1999; de Havilland Temporary Revision TR AWL 2-15, dated September 3, 1999; and de Havilland Temporary Revision TR AWL 3-78, dated November 19, 1999. This incorporation by reference was approved previously by the Director of the Federal Register as of August 10, 2001. Copies may be obtained from Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York ACO, 10 Fifth Street, Third Floor, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Note 4:

The subject of this AD is addressed in Canadian airworthiness directive CF-2000-07, dated March 3, 2000.

(g) The effective date of this amendment remains August 10, 2001.