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Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, -314, and -315 Series Airplanes

Document Details

Information about this document as published in the Federal Register.

Published Document

This document has been published in the Federal Register. Use the PDF linked in the document sidebar for the official electronic format.

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AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Final rule; correction.

SUMMARY:

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.

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DATES:

Effective August 10, 2001.

The incorporation by reference of certain publications listed in the regulations was approved previously by the Director of the Federal Register as of August 10, 2001 (66 FR 35538, July 6, 2001).

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FOR FURTHER INFORMATION CONTACT:

Serge Napoleon, Aerospace Engineer, ANE-171, FAA, New York Aircraft Certification Office, 10 Fifth Street, Third Floor, Valley Stream, New York 11581; telephone (516) 256-7512; fax (516) 568-2716.

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SUPPLEMENTARY INFORMATION:

On June 26, 2001, the Federal Aviation Administration (FAA) issued AD 2001-13-19, amendment 39-12301 (66 FR 35538, July 6, 2001), which applies to all Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, -314, and -315 series airplanes. That AD requires revising the Bombardier maintenance program to incorporate repetitive inspections to detect fatigue cracking in certain structures; and corrective actions, if necessary. That AD was prompted by issuance of mandatory continuing airworthiness information issued by a foreign airworthiness authority. The actions required by that 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.

Need for the Correction

The FAA notes that paragraph (a)(1), Table 1, of AD 2001-13-19, contains an error in referencing certain airplane models for the effectivity of de Havilland Temporary Revision TR AWL 2-15, dated September 3, 1999. Our intent was to specify the airplane models referenced in TR AWL 2-15 as only Models DHC-8-201 and -202 series airplanes. We also note that Canadian airworthiness directive CF-2000-07, dated March 3, 2000, as referenced in AD 2001-13-19, specifies only Model DHC-8-201 and -202 series airplanes for the effectivity of TR AWL 2-15. We have revised Table 1 of this AD accordingly.

The FAA has determined that the correction to Table 1 in paragraph (a)(1) of this AD is necessary. The correction will ensure that operators are notified of the correct airplane models that must be inspected, as required by this AD.

Correction of Publication

This document corrects the error and correctly adds the AD as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13).

The AD is reprinted in its entirety for the convenience of affected operators. The effective date of the AD remains August 10, 2001.

Since this action only corrects the airplane models as specified by Canadian airworthiness directive CF-2000-07 and TR AWL 2-15, it has no adverse economic impact and imposes no additional burden on any person. Therefore, the FAA has determined that notice and public procedures are unnecessary.

List of Subject in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Correction

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Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (

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PART 39—AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

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Authority: 49 U.S.C. 106(g), 40113, 44701.

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[Corrected]
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2. Section 39.13 is amended by correctly adding the following airworthiness directive (AD):

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2001-13-19 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 39-12301. Docket 2000-NM-45-AD.

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.

Maintenance Program Revisions

(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:

Table 1.—List of Temporary Revisions

Bombardier modelsTR NumberDate
DHC-8-102, -103, and -106 series airplanesTR AWL-71September 3, 1999.
DHC-8-201 and -202 series airplanesTR AWL 2-15September 3, 1999.
DHC-8-301, -311, -314, and -315 series airplanesTR AWL 3-78November 19, 1999.

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.

Structural Inspections

(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 Start Printed Page 44960prior 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.

Corrective Actions

(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.

Alternative Methods of Compliance

(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.

Special Flight Permits

(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.

Incorporation by Reference

(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.

Effective Date

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

Start Signature

Issued in Renton, Washington, on August 20, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

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[FR Doc. 01-21490 Filed 8-24-01; 8:45 am]

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