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Rule

Airworthiness Directives; Bombardier Model DHC-8-200, and -300 Series Airplanes

Document Details

Information about this document as published in the Federal Register.

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Start Preamble

AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Final rule; request for comments.

SUMMARY:

This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model DHC-8-200, and -300 series airplanes. This action requires repetitive inspections to detect chafing or arcing damage to the cable/wire and fuel tube assemblies on the right hand side of each engine, and replacement with new components, if necessary. This action also provides an optional terminating action for the repetitive inspections required by this AD. This action is necessary to prevent chafing of the cable/wire bundles against the fuel line, which could result in arcing and a consequent fire or explosion. This action is intended to address the identified unsafe condition.

DATES:

Effective February 6, 2001.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of February 6, 2001.

Comments for inclusion in the Rules Docket must be received on or before February 21, 2001.

ADDRESSES:

Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2001-NM-03-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Comments may be inspected at this location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal holidays. Comments may be submitted via fax to (425) 227-1232. Comments may also be sent via the Internet using the following address: 9-anm-iarcomment@faa.gov. Comments sent via fax or the Internet must contain “Docket No. 2001-NM-03-AD” in the subject line and need not be submitted in triplicate. Comments sent via the Internet as attached electronic files must be formatted in Microsoft Word 97 for Windows or ASCII text.

The service information referenced in this AD may be obtained from Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York Aircraft Certification Office, 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.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

James Delisio, Aerospace Engineer, Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft Certification Office, 10 Fifth Street, Third Floor, Valley Stream, New York 11581; telephone (516) 256-7521; fax (516) 568-2716.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

Transport Canada Civil Aviation (TCCA), which is the airworthiness authority for Canada, recently notified the FAA that an unsafe condition may exist on certain Bombardier Model DHC-8-200 and -300 series airplanes. TCAA advises that a pinhole in the high pressure fuel line was detected. Investigation revealed that the cause of the pinhole was due to arcing from an adjoining wire. The arcing occurred approximately four inches from the fuel-cooled oil cooler. Although the fuel line and wire are separated by two cushion clamps, the cushion clamps can rotate and thereby allow the wire bundle to chafe against the fuel line. Such chafing of the wire bundles could result in arcing and a consequent fire or explosion.

Explanation of Relevant Service Information

Bombardier has issued Alert Service Bulletin A8-73-23, dated November 3, 2000, which describes procedures for repetitive general visual inspections to detect chafing or arcing damage to the cable and the fuel tube assemblies on the right hand side of each engine, and replacement with new components, if necessary. The alert service bulletin also describes procedures for an optional modification that entails, among other things, rerouting the existing wire harness to the opposite side of the oil cooler, and shortening and securing the wire harness, if necessary. That modification eliminates the need for the repetitive inspections. TCAA classified this alert service bulletin as mandatory and issued Canadian airworthiness directive CF-2000-33, dated November 14, 2000, in order to assure the continued airworthiness of these airplanes in Canada. Start Printed Page 6455

FAA's Conclusions

These airplane models are manufactured in Canada and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, TCAA has kept the FAA informed of the situation described above. The FAA has examined the findings of TCAA, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States.

Explanation of Requirements of Rule

Since an unsafe condition has been identified that is likely to exist or develop on other airplanes of the same type design registered in the United States, this AD is being issued to prevent chafing of the cable/wire bundles against the fuel line, which could result in arcing and a consequent fire or explosion. This AD requires accomplishment of the repetitive general visual inspections, and replacement, if necessary, in accordance with the inspection and repair procedures specified in the alert service bulletin described previously. This AD also provides an optional terminating action for the repetitive inspections required by this AD.

Interim Action

This is considered to be interim action. The FAA is currently considering superseding this AD to require modification of the cable assembly, which would constitute terminating action for the repetitive inspections required by this AD. However, the planned compliance time for the installation of the modification is sufficiently long so that notice and opportunity for prior public comment will be practicable.

Determination of Rule's Effective Date

Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days.

Comments Invited

Although this action is in the form of a final rule that involves requirements affecting flight safety and, thus, was not preceded by notice and an opportunity for public comment, comments are invited on this rule. Interested persons are invited to comment on this rule by submitting such written data, views, or arguments as they may desire. Communications shall identify the Rules Docket number and be submitted in triplicate to the address specified under the caption ADDRESSES. All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed.

Submit comments using the following format:

  • Organize comments issue-by-issue. For example, discuss a request to change the compliance time and a request to change the service bulletin reference as two separate issues.
  • For each issue, state what specific change to the AD is being requested.
  • Include justification (e.g., reasons or data) for each request.

Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report that summarizes each FAA-public contact concerned with the substance of this AD will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this rule must submit a self-addressed, stamped postcard on which the following statement is made: “Comments to Docket Number 2001-NM-03-AD.” The postcard will be date stamped and returned to the commenter.

Regulatory Impact

The regulations adopted herein will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132.

The FAA has determined that this regulation is an emergency regulation that must be issued immediately to correct an unsafe condition in aircraft, and that it is not a “significant regulatory action” under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket. A copy of it, if filed, may be obtained from the Rules Docket at the location provided under the caption ADDRESSES.

Start List of Subjects

List of Subjects in 14 CFR Part 39

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Adoption of the Amendment

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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

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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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[Amended]
Start Amendment Part

2. Section 39.13 is amended by adding the following new airworthiness directive:

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2001-02-02 Bombardier, Inc. (Formerly deHavilland, Inc.): Amendment 39-12086. Docket 2001-NM-03-AD.

Applicability: Model DHC-8-201, -202, -301, -311, and -315 airplanes having serial numbers 100 through 552 inclusive, 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 prevent possible arcing between the electrical wiring and the fuel tube, which could result in a fire or explosion, accomplish the following:

Inspection

(a) Within 50 flight hours or 10 days after the effective date of this AD, whichever Start Printed Page 6456occurs first: Do a general visual inspection to detect chafing or arcing damage to the cable and the fuel tube assemblies on the right hand side of each engine, per Bombardier Alert Service Bulletin A8-73-23, dated November 3, 2000. Repeat the inspection every 500 flight hours or 3 months, whichever occurs first.

Note 2:

For the purposes of this AD, a general visual inspection is defined as: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or drop-light, and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.”

Repair

(b) If any damage to the fuel tube or cable assembly is detected, before further flight, replace the damaged component per Bombardier Alert Service Bulletin A8-73-23, dated November 3, 2000. Thereafter, repeat the inspection required by paragraph (a) of this AD every 500 flight hours or 3 months, whichever occurs first.

Optional Terminating Action

(c) Accomplishment of the modification instructions described in Bombardier Alert Service Bulletin A8-73-23, dated November 3, 2000, that specifies, among other actions, rerouting the existing wire harness to the opposite side of the oil cooler, constitutes terminating action for the repetitive inspection requirements 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 Aircraft Certification Office (ACO), FAA. 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 §§ 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) The actions shall be done in accordance with Bombardier Alert Service Bulletin A8-73-23, dated November 3, 2000. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 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; at the FAA, New York Aircraft Certification Office, 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-2000-33, dated November 14, 2000.

Effective Date

(g) This amendment becomes effective on February 6, 2001.

Start Signature

Issued in Renton, Washington, on January 12, 2001.

Donald L. Riggin,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. 01-1659 Filed 1-19-01; 8:45 am]

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