Airworthiness Directives; Cessna Aircraft Company 180, 182, and 185 Series Airplanes

[Federal Register Volume 63, Number 53 (Thursday, March 19, 1998)] [Proposed Rules] [Pages 13374-13376] From the Federal Register Online via the Government Publishing Office [www.gpo.gov] [FR Doc No: 98-7089]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-CE-14-AD] RIN 2120-AA64

Airworthiness Directives; Cessna Aircraft Company 180, 182, and 185 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to adopt a new airworthiness directive (AD) that would apply to all Cessna Aircraft Company (Cessna) 180, 182, and 185 series airplanes equipped with wing extension supplemental type certificate (STC) SA00276NY. The proposed action would require inspecting between wing station (W.S.) 90 and W.S. 110 for an angle stiffener at the lower wing spar splice. If the angle stiffener is not installed, the proposed action would require installing a reinforcing strap. The proposed action is the result of failed test results revealing that the wings of these Cessna airplanes, without the stiffener, do not meet the applicable design requirements after being modified by the above STC. The actions specified by the proposed AD are intended to prevent wing failure during flight, which, if not corrected, could cause loss of control of the airplane.

DATES: Comments must be received on or before May 15, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 97-CE-14-AD, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. Comments may be inspected at this location between 8 a.m. and 4 p.m., Monday through Friday, holidays excepted. Service information that applies to the proposed AD may be obtained from Air Research Technology, Inc., 3440 McCarthy, Montreal, Quebec, Canada H4K 2P5; telephone (514) 337-7588; facsimile (514) 337-3293. This information also may be examined at the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Sol Maroof, Aerospace Engineer, New York Aircraft Certification Office, 10 Fifth Street, 3rd Floor, Valley Stream, New York, 11581-1200; telephone (516) 256-7522; facsimile (516) 568-2716.

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 should 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.

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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 that summarizes 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 No. 97-CE-14-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, Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 97-CE-14-AD, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.

Discussion

The FAA has been notified by the Canadian civil airworthiness authority, Transport Canada, that certain Cessna 180, 182, and 185 series airplanes, equipped with wing extensions by way of supplemental type certificate (STC) SA00276NY, may not have had a wing stiffener installed at factory. This condition has been discovered on several of these airplanes during routine inspections. Since this discovery, further investigation has shown that without the wing stiffener, the wing is susceptible to structural failure. Both the FAA and Transport Canada have been in contact with the manufacturer of this particular STC and have approved an alternative to the wing stiffener. Tests have shown that the wing would be stabilized by installing a wing reinforcement strap to add strength to this area of the wing, if it is without the wing stiffener.

Relevant Service Information

Air Research Technology, Inc. has issued Service Bulletin No. SB-1- 96, Issue 1, dated April 11, 1996, which specifies procedures for visually inspecting the underside of the wing, aft of the spar, closest to where the strut connects to the wing, for the installation of an angle stiffener along the lower spar cap between Wing Station (W.S.) 90 and W.S. 110. If an angle stiffener is not installed, then the service information provides procedures for installing a stainless steel reinforcement strap on the underside of the wing, along the spar, at W.S. 100.50.

The FAA's Determination

After examining the circumstances and reviewing all available information, including the relevant service information, related to the incidents described above, the FAA has determined that AD action should be taken to prevent wing failure during flight, which, if not corrected could cause loss of control of the airplane.

Explanation of the Provisions of the Proposed AD

Since an unsafe condition has been identified that is likely to exist or develop in other (Cessna) 180, 182, and 185 series airplanes equipped with wing extension STC SA00276NY, the proposed AD would require inspecting the inside of the underside of the wing, near Wing Station (W.S.) 100, for an angle stiffener. If an angle stiffener is not installed, the proposed AD would require installing a reinforcement strap along the lower wing spar.

Cost Impact

The FAA estimates that there are 55 airplanes in the U.S. registry that would be affected by the proposed AD, that it would take approximately 1 workhour for the initial inspection and 7 workhours for the installation of the reinforcement strap per airplane, and that the average labor rate is approximately $60 an hour. Parts are supplied by the wing extension kit manufacturer at no cost to the owner/operator. Based on these figures, the total cost impact of the proposed AD on U.S. operators is estimated to be $26,400 or $480 per airplane. The FAA has no way to determine the number of owners/operators who may have already accomplished the proposed action, and would presume that none of the owners/operators of the affected airplanes have accomplished the proposed action.

Regulatory Impact

The regulations proposed herein would not have substantial direct effects 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, in accordance with Executive Order 12612, it is determined that this proposal would not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. For the reasons discussed above, I certify that this action (1) is not a ``significant regulatory action'' under Executive Order 12866; (2) is not a ``significant rule'' under 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 has been placed 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:

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

Sec. 39.13 [Amended]

2. Section 39.13 is amended by adding a new airworthiness directive (AD) to read as follows:

Cessna Aircraft Company: Docket No. 97-CE-14-AD.

Applicability: The following airplane models (all serial numbers), certificated in any category, that are equipped with wing extension supplemental type certificate (STC) SA00276NY.

Models

180, 180A, 180B, 180C, 180D, 180E, 180F, 180G, 180H, 180J, 180K, 182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, 182R, 182S, R182, T182, TR182, 185, 185A, 185B, 185C, 185D, 185E, A185E, A185F

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.

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Compliance: Required within the next 50 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished. To prevent wing failure during flight, which, if not corrected, could cause loss of control of the airplane, accomplish the following: (a) Inspect inside both left and right wings, aft of the spar, closest to where the strut connects to the wing, for an angle stiffener along the lower spar cap between Wing Station (W.S.) 90 and W.S. 110 in accordance with Part A of the Accomplishment Instructions of Air Research Technology, Inc. (ART) Service Bulletin (SB) No. SB-1-96, Issue 1, dated April 11, 1996. (b) If an angle stiffener is not installed, prior to further flight, install a stainless steel reinforcement strap on the underside of each wing, along the spar at W.S. 100.50 in accordance with Part B of the Accomplishment Instructions of ART SB No. SB-1- 96, Issue 1, dated April 11, 1996. (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. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, New York Aircraft Certification Office, 10 Fifth Street, 3rd Floor, Valley Stream, New York, 11581-1200. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, New York Aircraft Certification Office.

Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York Aircraft Certification Office.

(e) All persons affected by this directive may obtain copies of the document referred to herein upon request to Air Research Technology, Inc., 3440 McCarthy, Montreal, Quebec, Canada H4K 2P5; or may examine this document at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.

Issued in Kansas City, Missouri, on March 11, 1998. Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-7089 Filed 3-18-98; 8:45 am] BILLING CODE 4910-13-U