Airworthiness Directives; Construcciones Aeronauticas, S.A. (CASA), Model CN-235, CN-235-100, and CN-235-200 Series Airplanes
This document proposes the adoption of a new airworthiness directive (AD) that is applicable to all CASA Model CN-235, CN-235-100, and CN-235-200 series airplanes. This proposal would require replacing the upper brackets in frames 33, 34, and 35, with improved brackets that are more fatigue resistant, and reinforcing frame 35. This action is necessary to prevent fatigue cracking in the zone of the fittings connecting the fuselage to stiffener rods located in frames 33, 34, and 35, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
Table of Contents
- Comments Invited
- Availability of NPRMs
- Explanation of Relevant Service Information
- FAA's Conclusions
- Explanation of Requirements of Proposed Rule
- Cost Impact
- Regulatory Impact
- The Proposed Amendment
- Bracket Replacement
- Alternative Methods of Compliance
- Special Flight Permits
Comments must be received by November 29, 2000.
Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2000-NM-264-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: firstname.lastname@example.org. Comments sent via fax or the Internet must contain “Docket No. 2000-NM-264-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 the proposed rule may be obtained from Construcciones Aeronauticas, S.A., Getafe, Madrid, Spain. This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,Washington.
For further information contact: ↑
Norman B. Martenson, Manager,International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149.
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 notice 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 notice must submit a self-addressed, stamped postcard on which the following statement is made: “Comments to Docket Number 2000-NM-264-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. 2000-NM-264-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.
The Dirección Général de l'Aviación Civil (DGAC), which is the airworthiness authority for Spain, notified the FAA that an unsafe condition may exist on all CASAModel CN-235, CN-235-100, and CN-235-200 series airplanes. The DGAC advises that, during fatigue testing of the Model CN-235 series airplane, cracks were found in the zone of the fittings connecting the fuselage to stiffener rods located in frame 35. Similar stiffener rods are attached to the fuselage at frames 33 and 34. Such fatigue cracking, if not detected and corrected, could result in reduced structural integrity of the airplane.
Explanation of Relevant Service Information ↑
CASA has issued Service Bulletin SB-235-53-48, dated December 11, 1997, which describes procedures for replacing the upper brackets in frames 33, 34, and 35, with improved brackets that are more fatigue resistant, and reinforcing frame 35. Accomplishment of the actions specified in the service bulletin is intended to adequately address the identified unsafe condition. The DGAC classified this service bulletin as mandatory and issued Spanish airworthiness directive 02/2000, dated January 31, 2000, in order to assure the continued airworthiness of these airplanes in Spain.
FAA's Conclusions ↑
This airplane model is manufactured in Spain and is type certificated for operation in the United States under the provisions of section 21.29 of the Federal AviationRegulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. The FAA has examined the findings of the DGAC, 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.
Cost Impact ↑
The FAA estimates that 1 airplane of U.S. registry would be affected by this proposed AD, that it would take approximately 80 work hours per airplane to accomplish the proposed actions, and that the average labor rate is $60 per work hour. Required parts would cost approximately $2,871 per airplane. Based on these figures, the cost impact of the proposed AD on the U.S. operator of the one affected airplane is estimated to be$7,671.
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 ↑
1. The authority citation for part 39 continues to read as follows:
49 U.S.C. 106(g), 40113, 44701.§ 39.13
2. Section 39.13 is amended by adding the following new airworthiness directive:
Construcciones Aeronauticas, S.A. (CASA): Docket 2000-NM-264-AD.
Applicability: All Model CN-235, CN-235-100, and CN-235-200 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 (b) 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 fatigue cracking in the zone of the fittings connecting the fuselage to stiffener rods located in frames 33, 34, and 35, which could result in reduced structural integrity of the airplane, accomplish the following:
Bracket Replacement ↑
(a) Prior to the accumulation of 25,000 total landings, replace the upper brackets in frames 33, 34, and 35, with improved brackets that are more fatigue resistant, and reinforce frame 35, in accordance with CASA Service Bulletin SB-235-53-48, dated December 11, 1997.
Alternative Methods of Compliance ↑
(b) 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, International Branch, ANM-116, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116.
Note 2: ↑
Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.
Special Flight Permits ↑
(c) 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.
Note 3: ↑
The subject of this AD is addressed in Spanish airworthiness directive 02/2000, dated January 31, 2000.Issued in Renton, Washington, on October 24, 2000. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.