Airworthiness directives: Bombardier,
[Federal Register: May 5, 2004 (Volume 69, Number 87)]
[Proposed Rules]
[Page 25041-25043]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05my04-31]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. 2002-NM-339-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-102, -103, and - 106 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
SUMMARY: This document proposes the adoption of a new airworthiness directive (AD) that is applicable to certain Bombardier Model DHC-8- 102, -103, and -106 airplanes. This proposal would require repetitive detailed inspections of the left and right aileron tab actuator arm channels for cracking, and corrective actions if necessary. This proposal also provides an optional terminating action for the repetitive inspections. This action is necessary to prevent increased roll forces due to cracking of the left and right aileron tab actuator arms, which could be interpreted by the pilot as a flight control problem and might lead to loss of control of the airplane. This action is intended to address the identified unsafe condition.
DATES: Comments must be received by June 4, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2002-NM-339-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Comments may be inspected at this location between 9 a.m. and 3 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-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2002-NM-339-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 or 2000 or ASCII text.
The service information referenced in the proposed rule 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.
FOR FURTHER INFORMATION CONTACT: Richard Beckwith, Aerospace Engineer, Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Ave., Westbury, NY 11590; telephone (516) 228-7306; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the proposed 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 above. All communications received on or before the closing date for comments, specified above, will be considered before taking action on the proposed rule. The proposals contained in this action may be changed in light of the comments received.
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 proposed 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 proposed 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 summarizing each FAA-public contact concerned with the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this action must submit a self-addressed, stamped postcard on which the following statement is made: ``Comments to Docket Number 2002-NM-339-AD.'' The postcard will be date stamped and returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2002-NM-339-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.
Discussion
Transport Canada Civil Aviation (TCCA), which is the airworthiness authority for Canada, notified the FAA that an unsafe condition may exist on certain Bombardier Model DHC-8-102, -103, and -106 airplanes. TCCA advises that it has received reports of cracking of the left and right aileron tab actuator arm channels, possibly due to oscillation of the tab against its stops while the airplane was parked tail into wind. This condition, if not corrected, could result in consequent increased roll forces, which could be interpreted by the pilot as a flight control problem and might lead to loss of control of the airplane.
Explanation of Relevant Service Information
Bombardier has issued Service Bulletin 8-57-07, Revision `F,' dated March 27, 2002, which describes procedures for repetitive detailed inspections (referred to in the service bulletin as special inspections) of
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certain left and right aileron tab actuator arm channels for cracking; and for replacement and/or reinforcement of such aileron tab actuator arm channels, which eliminates the need for the repetitive inspections. Accomplishment of the actions specified in the service bulletin is intended to adequately address the identified unsafe condition. TCCA classified this service bulletin as mandatory and issued Canadian airworthiness directive CF-2002-29, dated May 22, 2002, to ensure the continued airworthiness of these airplanes in Canada. The service bulletin also describes procedures for replacement of the aileron tab with a new, improved tab, which eliminates the need for the repetitive inspections of the replaced tab. TCCA's AD provides for this action as optional.
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, TCCA has kept the FAA informed of the situation described above. The FAA has examined the findings of TCCA, 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 Proposed 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, the proposed AD would require accomplishment of the actions specified in the service bulletin described previously.
Difference Between Proposed AD and Canadian Airworthiness Directive
Although the Canadian Airworthiness Directive specifies that inspections, repairs, or modifications accomplished per previous issues of the service bulletin are acceptable, this proposed AD requires actions to be accomplished per revision `F' of the service bulletin. Revision `F' of the service bulletin includes additional rework not specified in previous issues.
Cost Impact
The FAA estimates that 30 airplanes of U.S. registry would be affected by this proposed AD, that it would take approximately 1 work hour per airplane to accomplish each proposed repetitive inspection, and that the average labor rate is $65 per work hour. Based on these figures, the cost impact of the proposed AD on U.S. operators is estimated to be $1,950, or $65 per airplane, per inspection.
The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the proposed requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions.
Regulatory Impact
The regulations proposed herein would 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 proposal would not have federalism implications under Executive Order 13132.
For the reasons discussed above, I certify that this proposed regulation (1) is not a ``significant regulatory action'' under Executive Order 12866; (2) is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated, will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A copy of the draft regulatory evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
-
The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
-
Section 39.13 is amended by adding the following new airworthiness directive:
Bombardier, Inc. (Formerly de Havilland, Inc.): Docket 2002-NM-339- AD.
Applicability: Model DHC-8-102, -103, and -106 airplanes; serial numbers 3 through 119 inclusive; without Bombardier Modification 8/ 0864 incorporated; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent increased roll forces due to cracking of the left and right aileron tab actuator arm channels, which could be interpreted by the pilot as a flight control problem and might lead to loss of control of the airplane, accomplish the following:
Inspection and Corrective Actions
(a) Within 500 flight hours after the effective date of this AD, perform a detailed inspection of the left and right aileron tab actuator arm channels for cracking, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8-57-07, Revision ``F,'' dated March 27, 2002.
Note 1: For the purposes of this AD, a detailed inspection is defined as: ``An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.''
(1) If no cracked actuator arm channel is found, repeat the inspection at intervals not to exceed 500 flight hours, until paragraph (a)(2) or (b) of this AD has been accomplished.
(2) If any cracked actuator arm channel is found, prior to further flight, accomplish paragraph (a)(2)(i) or (a)(2)(ii) of this AD. Accomplishment of paragraph (a)(2)(i) or (a)(2)(ii) terminates the repetitive inspections required by paragraph (a)(1) of this AD for the repaired or replaced aileron tab only.
(i) Replace the actuator arm channel with a new actuator arm channel; install a reinforcing angle on the new actuator arm channel; and replace the balance weight arm with a new balance weight arm; in accordance with Part A of the Accomplishment Instructions of the service bulletin.
(ii) Replace the aileron tab with a new, improved aileron tab in accordance with Part C of the Accomplishment Instructions of the service bulletin.
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Optional Terminating Action
(b) Reinforcement of both actuator arm channels with reinforcing angles and installation of new balance weight arms in accordance with Part B of the Accomplishment Instructions of Bombardier Service Bulletin 8-57-07, Revision ``F,'' dated March 27, 2002; or replacement of the aileron tabs with new, improved tabs in accordance with Part C of the Accomplishment Instructions of that service bulletin; constitutes terminating action for the repetitive inspections required by paragraph (a)(1) of this AD.
Part Installation
(c) As of the effective date of this AD, no person may install any actuator arm channel or any aileron tab on any airplane except in accordance with paragraph (a)(2) or (b) of this AD.
Alternative Methods of Compliance
(d) In accordance with 14 CFR 39.19, the Manager, New York Aircraft Certification Office (ACO), FAA, is authorized to approve alternative methods of compliance for this AD.
Note 2: The subject of this AD is addressed in Canadian airworthiness directive CF-2002-29, dated May 22, 2002.
Issued in Renton, Washington, on April 26, 2004. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 04-10253 Filed 5-4-04; 8:45 am]
BILLING CODE 4910-13-P
