[Federal Register Volume 70, Number 53 (Monday, March 21, 2005)]
[Rules and Regulations]
[Pages 13362-13365]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-5382]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20513; Directorate Identifier 2005-CE-07-AD; 
Amendment 39-14022; AD 2005-05-52]
RIN 2120-AA64


Airworthiness Directives; the Cessna Aircraft Company Models 402C 
and 414A Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) to 
supersede emergency AD 2005-05-51 and AD 2000-23-01 for The Cessna 
Aircraft Company (Cessna) Models 402C and 414A airplanes. This AD 
contains the same information as emergency AD 2005-05-52 and publishes 
the action in the Federal Register. It requires you to eddy current 
inspect the forward wing spars and visually inspect the aft and 
auxiliary spars. This AD is the result of extensive cracks found on 
three wing spars of the affected airplanes. We are issuing this AD to 
detect and correct cracking in the wing spars before the cracks grow to 
failure. Such a wing failure could result in the wing separating from 
the airplane with consequent loss of control of the airplane.

DATES: This AD becomes effective on March 21, 2005, to all affected 
persons who did not receive emergency AD 2005-05-52, issued March 2, 
2005. Emergency AD 2005-05-52 contained the requirements of this 
amendment and became effective immediately upon receipt. As of March 
21, 2005, the Director of the Federal Register approved the 
incorporation by reference of certain publications listed in the 
regulations.
    We must receive any comments on this AD by April 30, 2005.

ADDRESSES: Use one of the following to submit comments on this AD:

[[Page 13363]]

     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-001.
     Fax: 1-202-493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     To get the service information identified in this proposed 
AD, contact The Cessna Aircraft Company, Product Support P.O. Box 7706, 
Wichita, Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-
9006.
    To view the comments to this AD, go to http://dms.dot.gov. The 
docket number is FAA-2005-20513; Directorate Identifier 2005-CE-07-AD.

FOR FURTHER INFORMATION CONTACT: Paul Nguyen, Aerospace Engineer, FAA, 
Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent 
Airport, Wichita, Kansas 67209; telephone: (316) 946-4125; facsimile: 
(316) 946-4107; e-mail: [email protected].

SUPPLEMENTARY INFORMATION: What events caused previous FAA AD action? 
The FAA has received reports of (and is analyzing data from) cracks 
found in the wings of two Cessna Model 402C airplanes.
    On the first airplane, early information indicates the airplane had 
severe cracking on its left wing in the vicinity of the forward spar 
and outboard engine beam. The main lower spar cap had completely failed 
at about Wing Station (WS) 114. The airplane also had cracks in the 
lower wing skin and the web splice doubler. Also found were two popped 
rivets: one between the heat shield and the wing skin and another 
between the factory installed web splice doublers and web. The airplane 
had 20,355 total hours time-in-service (TIS).
    During the airplane's most recent flights before the cracking was 
found, the pilot noticed that roll trim was required. The flights 
required the pilot to use aileron trim for level flight to keep the 
wings level. The airplane landed safely and inspection revealed the 
cracks.
    On the second airplane, fatigue cracks were found at about WS 114 
in the main lower spar cap of another Model 402C airplane that had over 
20,000 total hours TIS. Fatigue analysis shows that similar fatigue 
cracks could also develop in the wings of the Model 414A airplanes.
    Airworthiness Directive (AD) 2000-23-01, Amendment 39-11971 (65 FR 
70645), required repetitive visual inspections of the forward, aft, and 
auxiliary wing spars for cracks on Cessna Model 402C airplanes. These 
inspections are at intervals not to exceed 110 hours TIS.
    Logbook records indicated that both airplanes with cracked spars 
were in compliance with AD 2000-23-01.
    The FAA's analysis of the incidents presented above showed that, in 
the interim, the inspections of AD 2000-23-01 should be done more 
frequently and particular attention paid to certain areas.
    Therefore, FAA issued Emergency AD 2005-05-51 to detect and correct 
cracking in the wing spars of the Cessna Models 402C and 414A airplanes 
before the cracks grow to failure. Such a wing failure could result in 
the wing separating from the airplane with consequent loss of control 
of the airplane.
    Emergency AD 2005-05-51 superseded AD 2000-23-01 and:
     Required the visual inspections of the forward, aft, and 
auxiliary wings spars for cracks more frequently on Model 402C 
airplanes including special emphasis areas;
     Added inspection requirements for the Model 414A 
airplanes; and
     Included provisions to position the airplane to a home 
base, hangar, maintenance facility, etc.
    Emergency AD 2005-05-51 did not affect those airplanes that 
incorporate a spar strap modification on each wing following the 
original release of (or a later FAA-approved revision to) Cessna 
Service Bulletin MEB02-5 and Cessna Service Kit SK402-47 (currently at 
MEB02-5 Revision 2 and SK402-47B).
    What has caused this particular AD action? Emergency AD 2005-05-51 
was considered an interim action to immediately require visual 
inspection of the forward, aft, and auxiliary wing spars for cracks. 
The intent was to detect immediate and existing cracking before it grew 
to wing failure.
    The FAA has also received a report of a third crack found at WS 112 
on a Model 402C airplane.
    Cessna has developed new inspection techniques (eddy current) for 
the forward spar that are more effective at detecting cracks before the 
structural integrity of the wing is compromised. These inspection 
techniques will allow for longer intervals between repetitive 
inspections than in emergency AD 2005-05-51.
    Recent fatigue analysis that Cessna did (and the FAA reviewed) 
reveals that eddy current inspections of the forward wing spars 
combined with visual inspections of the aft and auxiliary spars will 
address the unsafe condition of these airplanes until long-term 
continued operational safety is assured through the Cessna-developed 
and FAA-approved spar strap modifications. Specifically:
     The eddy current inspection will replace the visual 
inspection of the forward spar that emergency AD 2005-05-51 currently 
requires; and
     The visual inspections of the aft and auxiliary spars will 
be maintained from emergency AD 2005-05-51, but will only be required 
repetitively every 100 hours TIS instead of every 15 hours TIS.
    Cessna has issued the following service information to include 
procedures to eddy current inspect the Models 402C and 414A airplanes:
     Cessna Service Bulletin MEB99-3, Revision 2, dated 
February 28, 2005 (Model 402C); or
     Cessna Service Bulletin MEB00-7, Revision 2, dated 
February 28, 2005 (Model 414A).

The FAA's Determination

    After careful review of all available information related to the 
subject presented above, including the above-referenced service 
bulletins, FAA has determined that:
     The forward wings spars should be inspected using eddy 
current methods on Cessna Models 402C and 414A airplanes;
     The visual inspections of the aft and auxiliary spars 
should be maintained from emergency AD 2005-05-51 (but not inspected as 
often); and
     AD action should be taken to detect and correct cracking 
in the wing spars before the cracks grow to failure. Such a wing 
failure could result in the wing separating from the airplane with 
consequent loss of control of the airplane.
    Consequently, we issued emergency AD 2005-05-52 to supersede 
emergency AD 2005-05-51.
    Why is it important to publish this AD? The FAA found that 
immediate corrective action was required, that notice and opportunity 
for prior public comment were impracticable and contrary to the public 
interest, and that good cause existed to make the AD effective 
immediately by individual letters issued on March 2, 2005, to all known 
U.S. operators of Cessna Models 402C and 414A airplanes. These

[[Page 13364]]

conditions still exist, and the AD is published in the Federal Register 
as an amendment to section 39.13 of the Federal Aviation Regulations 
(14 CFR 39.13) to make it effective to all persons.

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 ``Docket No. FAA-2005-20513; 
Directorate Identifier 2005-CE-07-AD'' in the subject line of your 
comments. If you want us to 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.

Authority for This Rulemaking

    What authority does FAA have for issuing this rulemaking action? 
Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106 describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this AD.

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 
``Docket No. FAA-2005-20513; Directorate Identifier 2005-CE-07-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 removing Airworthiness Directive (AD) 
2000-23-01, Amendment 39-11971 (65 FR 70645), and adding the following 
new AD:

2005-05-52 The Cessna Aircraft Company: Amendment 39-14022; Docket 
No. FAA-2005-20513; Directorate Identifier 2005-CE-07-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on March 21, 2005, to all affected 
persons who did not receive emergency AD 2005-05-52, issued March 2, 
2005. Emergency AD 2005-05-52 contained the requirements of this 
amendment and became effective immediately upon receipt.

Are Any Other ADs Affected by This Action?

    (b) This AD supersedes the following:
    (1) Emergency AD 2005-05-51, issued February 20, 2005; and
    (2) AD 2000-23-01, Amendment 39-11971.

What Airplanes Are Affected by This AD?

    (c) This AD affects Model 402C and 414A airplanes, all serial 
numbers, that:
    (1) are certificated in any category; and
    (2) do not incorporate a spar strap modification on each wing 
spar following the original release of (or a later FAA-approved 
revision to) Cessna Service Bulletin MEB02-5 and Cessna Service Kit 
SK402-47 (currently at MEB02-5 Revision 2 and SK402-47B).

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of extensive cracks found on three 
wing spars of the affected airplanes. We are issuing this AD to 
detect and correct cracking in the wing spars before the cracks grow 
to failure. Such a wing failure could result in the wing separating 
from the airplane with consequent loss of control of the airplane.

What Must I Do to Address This Problem?

    (e) Visual Inspections for all Model 402C airplanes With Fewer 
than 15,000 Hours Total Time-in-service (TIS): Initially inspect 
upon accumulating 10,000 hours TIS on the airplane or at the next 
inspection that would have been required by AD 2000-23-01 or 
emergency AD 2005-05-51, whichever occurs later. Repetitively 
inspect thereafter at intervals not to exceed 110 hours TIS until 
accumulating 15,000 hours TIS:
    (1) Perform both a visual external and internal inspection of 
the forward, aft, and auxiliary wing spars for cracks.
    (2) Do these visual inspections following the Accomplishment 
Instructions section of Cessna Service Bulletin MEB99-3 (Model 
402C), Revision 2, dated February 28, 2005.
    (3) When doing the inspections, pay particular attention to the 
following areas:
    (i) Just Outboard of the Engine Beam
    (A) The main lower spar cap at Wing Station (WS) 114.
    (B) The three rivets on both the inboard and outboard sides of 
WS 114 (total of six rivets) in the main lower spar cap as viewed 
from the access hole.
    (C) The main spar web at WS 112.5.
    (ii) Just Inboard of the Inboard Engine Beam
    (A) The main lower spar cap between WS 80 and WS 89.
    (B) The two attach bolts on the main spar just inboard of the WS 
89.18 rib.
    (f) Eddy Current and Visual Inspections: Perform eddy current 
inspections of the forward wing spars combined with visual 
inspections of the aft and auxiliary spars. Do these inspections 
following the Accomplishment Instructions section of Cessna Service 
Bulletin MEB99-3 (Model 402C) or Cessna Service Bulletin MEB00-7 
(Model 414A), both at Revision 2 and both dated February 28, 2005.

[[Page 13365]]



------------------------------------------------------------------------
                                                       Repetitive Eddy
     Affected airplanes         Eddy current and     current and visual
                               visual inspections    inspection interval
------------------------------------------------------------------------
(1) For Model 414A            At whichever of the   Thereafter at
 airplanes, serial numbers     following occurs      intervals not to
 414A001 through 414A0047      later:                exceed 100 hours
 and 414A0049 through          Upon          TIS.
 414A0200.                     accumulating 8,500
                               hours TIS on the
                               airplanes;.
                               At the next
                               inspection that
                               would have been
                               required by
                               emergency AD 2005-
                               05-51 (required at
                               intervals not to
                               exceed 15 hours
                               TIS); or.
                               Within the
                               next 2 days after
                               the effective date
                               of this AD (2 days
                               after receipt for
                               those who received
                               emergency AD 200505-
                               52).
(2) For the following         At whichever of the   Thereafter at
 airplanes that have 15,000    following occurs      intervals not to
 hours or more TIS or upon     later:                exceed 100 hours
 accumulating 15,000 hours     Upon          TIS.
 TIS:                          accumulting 15,000
                               hours TIS on the
                               airplane;.
                               At the next
                               inspection that
                               would have been
                               required by
                               emergency AD 2005-
                               05-51 (required at
                               intervals not to
                               exceed 15 hours
                               TIS); or.
                               Within the
                               next 2 days after
                               effective date of
                               this AD (2 days
                               after receipt for
                               those who received
                               emergency AD 2005-
                               05-52).
    (i) All Model 402C
     airplanes.
    (ii) Model 414A
     airplanes, serial
     numbers 414A0201
     through 414A1212.
------------------------------------------------------------------------


    Note: The Cessna service bulletins allow for either a visual 
inspection or eddy current inspection of the forward spars on all 
airplanes affected by this AD. Visual inspections of the forward 
spars do not satisfy the requirements of this AD for the airplanes 
referenced in paragraphs (f)(1) and (f)(2) of this AD. These 
airplanes must have the forward spars inspected using the eddy 
current methods specified in the Cessna service bulletins.

    (g) Cracks Found: If you find any crack on any forward, aft, or 
auxiliary wing spar; or in surrounding structure such as spar webs 
or skins during any inspection required by this AD, before further 
flight do the following:
    (1) Obtain an FAA-approved repair scheme from the Cessna 
Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277; telephone: 
(316) 517-5800, facsimile: (316) 942-9006; and
    (2) Incorporate this repair scheme.
    (h) Reporting Requirement: As soon as possible, but no later 
than 24 hours after any inspection required by this AD and as 
defined below:
    (1) Submit a report of inspection findings to the Manager, 
Wichita Aircraft Certification Office (ACO), by fax: (316) 946-4107.
    (i) Include a report for ``cracks found'' or ``no cracks found'' 
on the initial inspection; and
    (ii) Include a report only for ``cracks found'' on the 
repetitive inspections.
    (2) The report must include your name and a contact phone 
number, the results of the findings, a description of any cracking 
found, the airplane serial number, and the total number of hours TIS 
on the airplane. The ``Lower Wing Spars and Skin Inspection Report'' 
included in Cessna Service Bulletin MEB99-3 and MEB00-7 may be 
utilized for this reporting requirement.

May I Request an Alternative Method of Compliance?

    (i) 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.
    (1) For information on any already approved alternative methods 
of compliance or for further information about this AD, contact Paul 
Nguyen, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, 
Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-
4125; facsimile: (316) 946-4107; e-mail: [email protected].
    (2) Alternative methods of compliance that were approved for AD 
2000-23-01 or emergency AD 2005-05-51 are not approved for this 
emergency AD.

Does This AD Incorporate Any Material by Reference?

    (j) You must do the actions required by this AD following the 
instructions in Cessna Service Bulletin MEB99-3 (Model 402C) or 
Cessna Service Bulletin MEB00-7 (Model 414A), both at Revision 2 and 
both dated February 28, 2005. 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. To get a copy of 
this service information, contact Cessna Aircraft Company, Product 
Support P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-
5800; facsimile: (316) 942-9006. To review copies of this service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To 
view the AD docket, go to the Docket Management Facility; U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif 
Building, Room PL-401, Washington, DC 20590-001 or on the Internet 
at http://dms.dot.gov. The docket number is FAA-2005-20513.

    Issued in Kansas City, Missouri, on March 11, 2005.
Nancy C. Lane,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-5382 Filed 3-18-05; 8:45 am]
BILLING CODE 4910-13-P