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

[Federal Register Volume 63, Number 145 (Wednesday, July 29, 1998)]
[Rules and Regulations]
[Pages 40361-40363]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-20225]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-CE-14-AD; Amendment 39-10679; AD 98-16-04]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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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.

DATES: Effective September 21, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 21, 1998.

ADDRESSES: Service information that applies to this 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 may also be examined at 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; or at the Office of the Federal Register, 
800 North Capitol Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr. Sol Maroof, Aerospace Engineer, 
FAA, New York Aircraft Certification Office, 10 Fifth Street, 3rd 
Floor, Valley Stream,

[[Page 40362]]

New York, 11581-1200; telephone: (516) 256-7522; facsimile: (516) 568-
2716.

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.


Sec. 39.13  [Amended]

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

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.


[[Page 40363]]


    (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. Copies may be inspected at the FAA, 
Central Region, ffice 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.

    Issued in Kansas City, Missouri, on July 23, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-20225 Filed 7-28-98; 8:45 am]
BILLING CODE 4910-13-U

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