AD 98-16-04

This amendment adopts a new airworthiness directive (AD) that applies to all Cessna Aircraft Company (Cessna) 180, 182, and 185 series airplanes that have wing extension supplemental type certificate (STC) SA00276NY or supplemental type approval (STA) SA93-136 incorporated. This AD requires 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, this AD requires installing a reinforcing strap. This AD 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 this AD are intended to prevent wing failure during flight caused by the absence of an angle stiffener, which could cause loss of control of the airplane.

Final rule

98-16-04 CESSNA AIRCRAFT COMPANY: Amendment 39-10679; Docket No. 97-CE-14-AD.
Applicability: The following airplane models, all serial numbers, certificated in any category, that have wing extension supplemental type certificate (STC) SA00276NY or supplemental type approval (STA) SA93-136 incorporated.

NOTE 1: The STA is the Canadian version of the U.S. STC.

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 2: 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 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 caused by the absence of an angle stiffener, which could cause loss of control of the airplane, accomplish the following:

(a) Inspect inside the 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 3: 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) The inspection and installation required by this AD shall be done in accordance with Air Research Technology Service Bulletin No. SB-1-96, Issue 1, dated April 11, 1996. 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 Air Research Technology, Inc., 3440 McCarthy, Montreal, Quebec, Canada H4K 2P5. Copies may be inspected at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC.

(f) This amendment becomes effective on September 21, 1998.

Events Leading to the Issuance of This AD
A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to all Cessna 180, 182, and 185 series airplanes equipped with wing extension STC SA00276NY or STA SA93-136 was published in the Federal Register as a notice of proposed rulemaking (NPRM) on March 19, 1998 (63 FR 13374). The NPRM proposed to 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. Accomplishment of the proposed action as specified in the NPRM would be in accordance with Air Research Technology Service Bulletin No. SB-1-96, Issue 1, dated April 11, 1996.

The NPRM was 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 or STA.

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposed rule or the FAA's determination of the cost to the public.

The FAA's Determination
After careful review of all available information related to the subject presented above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed except for minor editorial corrections. The FAA has determined that these minor corrections will not change the meaning of the AD and will not add any additional burden upon the public than was already proposed.

Cost Impact
The FAA estimates that there are 55 airplanes in the U.S. registry that will be affected by this AD, that it will 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 this 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 this action, and will presume that none of the owners/operators of the affected airplanes have accomplished this action.

Regulatory Impact
The regulations adopted herein will 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 final rule does 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) 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 final 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, Incorporation by reference, Safety.

Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends 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.

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