# AD 98-16-04: Inspect Angle Stiffener Along Lower Spar Cap - Type: Airworthiness directive - Status: Current - Products: Cessna 180, 180A, 180B, 180C, 180D, 180E, 180F, 180G, 180H, 180J, 180K, 182 and 28 more - Effective: September 21, 1998 - Published: July 29, 1998, 63 FR 40361–40363 - Issued as: Final rule - Superseded by: Nothing supersedes this AD - Product type: Aircraft, Small airplane - Amendment: 39-10679 - Docket: 97-CE-14-AD - Registered aircraft: 15,946 may be affected, by airframe or engine model (OpenAirDocs) - Official PDF: https://openairdocs.org/files/sha256/78/9b/789badf91928484b767e9f2632f02a04308f3c1522f7f9c78f922ecb085a442b (from https://www.govinfo.gov/content/pkg/FR-1998-07-29/pdf/98-20225.pdf) - Federal Register: https://www.federalregister.gov/documents/1998/07/29/98-20225/airworthiness-directives-cessna-aircraft-company-180-182-and-185-series-airplanes - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/C7343B79CBF9BF1586256A4F0044E41E.0001 - DRS record last changed: May 30, 2024 - Page: https://openairdocs.org/ad/98-16-04 ## Summary 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. ## The airworthiness directive 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. ## Rule preamble ### Supplementary information 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: ## Affected data sheets (3) (OpenAirDocs) The type certificate data sheets whose models the AD names. - [TCDS 3A13](https://openairdocs.org/tcds/3A13): Textron Aviation Inc.; names 21 of 23 models: 182D, 182A, 182J, 182P, 182B, TR182, 182L, 182G… - [TCDS 5A6](https://openairdocs.org/tcds/5A6): Textron Aviation Inc.; names 11 of 11 models: 180E, 180J, 180F, 180H, 180A, 180, 180B, 180D… - [TCDS 3A24](https://openairdocs.org/tcds/3A24): Textron Aviation Inc.; names 8 of 8 models: 185B, A185F, 185E, 185C, A185E, 185A, 185D, 185 ## Registered aircraft it may apply to (OpenAirDocs) Matched by airframe and engine model; the AD's applicability may narrow it by serial number, part number or equipment. - Aircraft: 15,946 (15,946 by airframe model, 0 by engine model) - Makers: Cessna 15,943, Cessna Wren 3 Models with the most aircraft: - [Cessna 182P](https://openairdocs.org/model/cessna-182p): 2,099 aircraft (airframe model) - [Cessna 182Q](https://openairdocs.org/model/cessna-182q): 1,565 aircraft (airframe model) - [Cessna 180](https://openairdocs.org/model/cessna-180): 1,177 aircraft (airframe model) - [Cessna A185F](https://openairdocs.org/model/cessna-a185f): 1,120 aircraft (airframe model) - [Cessna 182A](https://openairdocs.org/model/cessna-182a): 784 aircraft (airframe model) - [Cessna R182](https://openairdocs.org/model/cessna-r182): 706 aircraft (airframe model) - [Cessna 182S](https://openairdocs.org/model/cessna-182s): 606 aircraft (airframe model) - [Cessna 182J](https://openairdocs.org/model/cessna-182j): 487 aircraft (airframe model) - [Cessna 182R](https://openairdocs.org/model/cessna-182r): 487 aircraft (airframe model) - [Cessna TR182](https://openairdocs.org/model/cessna-tr182): 465 aircraft (airframe model) - [Cessna 182](https://openairdocs.org/model/cessna-182): 446 aircraft (airframe model) - [Cessna 182M](https://openairdocs.org/model/cessna-182m): 432 aircraft (airframe model) - [Cessna 182H](https://openairdocs.org/model/cessna-182h): 423 aircraft (airframe model) - [Cessna 182K](https://openairdocs.org/model/cessna-182k): 413 aircraft (airframe model) - [Cessna 182L](https://openairdocs.org/model/cessna-182l): 411 aircraft (airframe model) - [Cessna 182B](https://openairdocs.org/model/cessna-182b): 406 aircraft (airframe model) - [Cessna 182G](https://openairdocs.org/model/cessna-182g): 391 aircraft (airframe model) - [Cessna 182E](https://openairdocs.org/model/cessna-182e): 380 aircraft (airframe model) - [Cessna 180H](https://openairdocs.org/model/cessna-180h): 366 aircraft (airframe model) - [Cessna 182N](https://openairdocs.org/model/cessna-182n): 336 aircraft (airframe model) All 44 models: https://openairdocs.org/ad/98-16-04/models.md Every aircraft: https://openairdocs.org/ad/98-16-04/aircraft.md ## Related documents - [Proposed rule 97-CE-14-AD](https://openairdocs.org/proposed/97-CE-14-AD): Notice of proposed rulemaking (NPRM), published Mar 19, 1998 - [STC SA00276NY](https://openairdocs.org/stc/SA00276NY): Reinforcement of wing assemblies and installation of Air Research Technology wing tip extension.. Air Research Technology, Inc, Named in the applicability --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.