Airworthiness Directives; Cessna Aircraft Company Models 208 and 208B Airplanes

[Federal Register Volume 69, Number 80 (Monday, April 26, 2004)]
[Rules and Regulations]
[Pages 22392-22393]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-9115]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2004-CE-09-AD; Amendment 39-13587; AD 2004-08-17]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company Models 208 and 
208B Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. 
This AD requires you to inspect any upper and lower wing strut attach 
fitting nut for existence of the corresponding cotter pin and do any 
necessary corrective action. This AD is the result of a report of one 
airplane having loose and improperly tied nuts on the wing struts upper 
attachment bolts. We are issuing this AD to detect and correct loose 
and improperly tied nuts on the wing struts, which could result in an 
attachment nut coming off the bolt. This could lead to the failure of 
the wing structure with consequent loss of control of the airplane.

DATES: This AD becomes effective on May 17, 2004.
    As of May 17, 2004, the Director of the Federal Register approved 
the incorporation by reference of certain publications listed in the 
regulation.
    We must receive any comments on this AD by June 22, 2004.

ADDRESSES: Use one of the following to submit comments on this AD:
    <bullet<ls-thn-eq> By mail: FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2004-CE-09-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106.
    <bullet<ls-thn-eq> By fax: (816) 329-3771.
    <bullet<ls-thn-eq> By e-mail: [email protected]. Comments sent 
electronically must contain ``Docket No. 2004-CE-09-AD'' in the subject 
line. If you send comments electronically as attached electronic files, 
the files must be formatted in Microsoft Word 97 for Windows or ASCII.
    You may get the service information identified in this AD from 
Cessna Aircraft Company, Product Support, PO Box 7706, Wichita, Kansas 
67277; telephone: (316) 517-5800; facsimile: (316) 942-9006.
    You may view the AD docket at FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2004-CE-09-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m. 
to 4 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Paul Nguyen, Aerospace Engineer, FAA, 
Wichita Aircraft Certification Office ACO, 1801 Airport Road, Room 100, 
Wichita, Kansas 67209; telephone: 316-946-4125; facsimile: 816-946-
4107.

SUPPLEMENTARY INFORMATION:
    What events have caused this AD? The FAA has received a report of a 
Cessna Model 208 airplane having loose and improperly tied nuts on the 
wing struts upper attachment bolts.
    A review of Cessna's manufacturing records shows that 15 Models 208 
and 208B airplanes could have this condition.
    What is the potential impact if FAA took no action? Loose and 
improperly tied nuts on the wing struts upper attachment bolts could 
lead to the failure of the wing structure with consequent loss of 
control of the airplane.
    Is there service information that applies to this subject? Cessna 
has issued Special Service Project No. SSP04-2, dated April 5, 2004.
    What are the provisions of this service information? This service 
information includes procedures for:
--Inspecting any upper wing strut attach fitting part number (P/N) 
MS17826-14 nut for the P/N MS24665-360 cotter pin and any lower wing 
strut attach fitting P/N MS17826-12 nut for the P/N MS24665-357 cotter 
pin;
--Tightening the nut and aligning the castellations of the 
corresponding P/N MS17826-14 or P/N MS17826-12 nut and the cotter pin 
hole in the bolt if any P/N MS24665-360 or P/N MS24665-357 cotter pin 
is not installed; and
--Installing the corresponding P/N MS24665-360 or P/N MS24665-357 
cotter pin.

FAA's Determination and Requirements of the AD

    What has FAA decided? We have evaluated all pertinent information 
and identified an unsafe condition that is likely to exist or develop 
on other products of this same type design.
    Since the unsafe condition described previously is likely to exist 
or develop on other Cessna Models 208 and 208B airplanes of the same 
type design, we are issuing this AD to detect and correct loose and 
improperly tied nuts on the wing struts, which could result in an 
attachment nut coming off the bolt. This could lead to the failure of 
the wing structure with consequent loss of control of the airplane.
    What does this AD require? This AD requires you to incorporate the 
actions in the previously-referenced service information.
    In preparing this rule, we contacted type clubs and aircraft 
operators to get technical information and information on operational 
and economic impacts. We did not receive any information through these 
contacts. If received, we would have included a discussion of any 
information that may have influenced this action in the rulemaking 
docket.
    How does the revision to 14 CFR part 39 affect this AD? On July 10, 
2002, we published a new version of 14 CFR part 39 (67 FR 47997, July 
22, 2002), which governs FAA's AD system. This regulation now includes 
material that relates to altered products, special flight permits, and 
alternative methods of compliance. This material previously was 
included in each individual AD. Since this material is included in 14 
CFR part 39, we will not include it in future AD actions.

Comments Invited

    Will I have the opportunity to comment before you issue the rule? 
This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 2004-CE-09-AD'' in the 
subject line of your comments. If you want us to

[[Page 22393]]

acknowledge receipt of your mailed comments, send us a self-addressed, 
stamped postcard with the docket number written on it; we will date-
stamp your postcard and mail it back to you. We specifically invite 
comments on the overall regulatory, economic, environmental, and energy 
aspects of the rule that might suggest a need to modify it. If a person 
contacts us through a nonwritten communication, and that contact 
relates to a substantive part of this AD, we will summarize the contact 
and place the summary in the docket. We will consider all comments 
received by the closing date and may amend the AD in light of those 
comments.

Regulatory Findings

    Will this AD impact various entities? We have determined that this 
AD will not have federalism implications under Executive Order 13132. 
This AD will 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.
    Will this AD involve a significant rule or regulatory action? For 
the reasons discussed above, I certify that this AD:
    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. 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.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 2004-CE-09-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under 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

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2004-08-17 Cessna Aircraft Company: Amendment 39-13587; Docket No. 
2004-CE-09-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on May 17, 2004.

Are Any Other ADs Affected By This Action?

    (b) None.

What Airplanes Are Affected by This AD?

    (c) This AD affects the following airplane models and serial 
numbers that are certificated in any category:

------------------------------------------------------------------------
                   Model                           Serial Numbers
------------------------------------------------------------------------
208.......................................   20800370 and 20800371.
208B......................................  208B1034 through 208B1043,
                                             208B1045, 208B1046, and
                                             208B1048.
------------------------------------------------------------------------

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of a report of one airplane having 
loose and improperly tied nuts on the wing struts upper attachment 
bolts. We are issuing this AD to detect and correct loose and 
improperly tied nuts on the wing struts, which could result in an 
attachment nut coming off the bolt. This could lead to the failure 
of the wing structure with consequent loss of control of the 
airplane.

What Must I do To Address This Problem?

    (e) To address this problem, you must do the following:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Inspect any upper wing    Within the next 10    Follow Cessna
 strut attach fitting part     hours time-in-        Special Service
 number (P/N) MS17826-14 nut   service (TIS) after   Project No. SSP04-
 for the P/N MS24665-360       May 14, 2004, the     2, dated April 5,
 cotter pin and any lower      effective date of     2004. The
 wing strut attach fitting P/  this AD, unless       applicable airplane
 N MS17826-12 nut for the P/   already done.         maintenance manual
 N MS24665-357 cotter pin.                           also addresses this
                                                     issue.
(2) If any P/N MS24665-360    Before further        Follow Cessna
 or P/N MS24665-357 cotter     flight after the      Special Service
 pin is not installed:.        inspection in         Project No. SSP04-
(i) tighten the                paragraph (e)(1) of   2, dated April 5,
 corresponding nut (P/N        this AD.              2004. The
 MS17826-14 or P/N MS17826-                          applicable airplane
 12) and align the                                   maintenance manual
 castellations of the nut                            also addresses this
 and the cotter pin hole in                          issue.
 the bolt; and.
(ii) install the
 corresponding P/N MS24665-
 360 or P/N MS24665-357
 cotter pin.
------------------------------------------------------------------------

May I Request an Alternative Method of Compliance?

    (f) You may request a different method of compliance or a 
different compliance time for this AD by following the procedures in 
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to 
your principal inspector. The principal inspector may add comments 
and will send your request to the Manager, Wichita Aircraft 
Certification Office (ACO), FAA. For information on any already 
approved alternative methods of compliance, contact Paul Nguyen, 
Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Room 100, 
Wichita, Kansas 67209; telephone: 316-946-4125; facsimile: 816-946-
4107.

Does This AD Incorporate Any Material by Reference?

    (g) You must do the actions required by this AD following the 
instructions in Cessna Special Service Project No. SSP04-2, dated 
April 5, 2004. The Director of the Federal Register approved the 
incorporation by reference of this service bulletin in accordance 
with 5 U.S.C. 552(a) and 1 CFR part 51. You may get a copy from 
Cessna Aircraft Company, Product Support, PO Box 7706, Wichita, 
Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-9006. 
You may review copies at FAA, Central Region, Office of the Regional 
Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at 
the Office of the Federal Register, 800 North Capitol Street, NW, 
suite 700, Washington, DC.

    Issued in Kansas City, Missouri, on April 16, 2004.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-9115 Filed 4-23-04; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T04:05:39.692957+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

cf1255e2ca68d0b1a809281affbf40b9f961431b7cd8107b98500c1b87027deb

Text SHA-256

554f64fc7cacaf176ccdb19e016bcd09981e1becfec249be3f0a842198e34b4f