[Federal Register Volume 74, Number 31 (Wednesday, February 18, 2009)]
[Rules and Regulations]
[Pages 7552-7554]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-3016]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0118; Directorate Identifier 2008-CE-073-AD;
Amendment 39-15810; AD 2009-04-04]
RIN 2120-AA64
Airworthiness Directives; Cessna Aircraft Company Models 401,
401A, 401B, 402, 402A, and 402B 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) for
certain Cessna Aircraft Company (Cessna) Models 401, 401A, 401B, 402,
402A, and 402B airplanes. This AD requires an inspection of the
auxiliary wing spar near the location where the main landing gear
trunnion is mounted for cracks; immediate replacement if cracks of 0.5
inch or more are found; repetitive inspections with replacement at a
later time as long as cracks of less than 0.5 inch are found; and a
report to the FAA and Cessna if any cracks are found. This AD results
from several reports of fatigue cracking on the affected airplanes in
the auxiliary wing spar. We are issuing this AD to detect and correct
such cracks, which, if not corrected, could result in failure of the
wing auxiliary spar web and cause landing gear collapse during normal
landing. This could lead to loss of control and passenger injury.
DATES: This AD becomes effective on March 2, 2009.
On March 2, 2009, the Director of the Federal Register approved the
incorporation by reference of certain publications listed in this AD.
We must receive any comments on this AD by April 20, 2009.
ADDRESSES: Use one of the following addresses to comment on this AD.
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
To get the service information identified in this AD, contact
Cessna Aircraft Company, P.O. Box 7704, Wichita, Kansas 67277;
telephone: (800) 423-7762 or (316) 517-6056; Internet: http://www.cessna.com.
To view the comments to this AD, go to http://www.regulations.gov.
The docket number is FAA-2009-0118; Directorate Identifier 2008-CE-073-
AD.
FOR FURTHER INFORMATION CONTACT: Adam Neubauer, Aerospace Engineer,
1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316)
946-4156; fax: (316) 946-4107.
SUPPLEMENTARY INFORMATION:
Discussion
We have received several reports of fatigue cracking on Cessna
Models 402A and 402B airplanes in the area of the auxiliary wing spar
where the main landing gear trunnion is mounted. Other models with
similar design that share
[[Page 7553]]
the same risk of auxiliary wing spar cracking include Cessna Models
401, 401A, 401B, and 402.
This condition, if not corrected, could result in failure of the
wing auxiliary spar web and cause landing gear collapse during normal
landing. This could lead to loss of control and passenger injury.
Cessna has shown the FAA that parts with cracks in this area that
are 0.5 inch or more need immediate replacement as they pose an
immediate safety of flight issue. Cessna's analysis also shows that
residual strength in the wing, up to ultimate design loads, will remain
with cracks less than 0.5 inch, and the growth of these cracks is slow.
Because analysis shows that a repetitive inspection program can
provide an interim acceptable level of safety, the FAA will allow
repetitive inspections when a crack less than 0.5 inch is found in the
wing auxiliary spar during the initial inspection required by this
action. Cracks need to be monitored (inspected every 50 hours time-in-
service (TIS)) to show they do not reach 0.5 inch.
If any crack reaches 0.5 inch or more, then the cracked
part must be replaced before further flight.
If no crack reaches 0.5 inch or more, then the cracked
part must be replaced within 200 hours TIS or 12 months, whichever
occurs first, regardless of crack growth.
Relevant Service Information
We reviewed Cessna Service Bulletin MEB08-8, dated December 23,
2008. The service information describes procedures for inspecting the
wing auxiliary spar webs for cracks and replacing the left web/right
web with a new left web/right web.
FAA's Determination and Requirements of This AD
We are issuing this AD because we evaluated all the information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design. This AD requires:
An inspection of the auxiliary wing spar near the location
where the main landing gear trunnion is mounted for cracks;
Immediate replacement if cracks are 0.5 inch or more;
Repetitive inspections (50 hours TIS) with replacement at
200 hours TIS or 12 months, whichever occurs first, if cracks are found
that are less than 0.5 inch; and
A report to the FAA and Cessna if any cracks are found.
The FAA considers this interim action. We will work with Cessna and
evaluate the crack reports and all other information. Based on this
information, we may initiate additional rulemaking action.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
cracks in the wing auxiliary spar web could lead to failure in this
area and could cause landing gear collapse during normal landing. This
could lead to loss of control and passenger injury. Some of the
affected airplanes are operated 100 hours TIS or more monthly.
Therefore, the repetitive inspections on these airplanes would occur in
short intervals, and the replacement would be required within 2 months.
Therefore, we determined that notice and opportunity for public comment
before issuing this AD are impracticable and that good cause exists for
making this amendment effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and an opportunity for
public comment. We invite you to send any written relevant data, views,
or arguments regarding this AD. Send your comments to an address listed
under the ADDRESSES section. Include the docket number ``FAA-2009-0118;
Directorate Identifier 2008-CE-073-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD. We will consider
all comments received by the closing date and may amend the AD in light
of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive concerning this AD.
Authority for This Rulemaking
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
rulemaking action.
Regulatory Findings
We 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.
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 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 regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that contains the AD, the regulatory
evaluation, any comments received, and other information on the
Internet at http://www.regulations.gov; or in person at the Docket
Management Facility between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Office (telephone (800) 647-5527)
is located at the street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
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 FAA amends 14 CFR part 39 as follows:
[[Page 7554]]
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):
2009-04-04 Cessna Aircraft Company: Amendment 39-15810; Docket No.
FAA-2009-0118; Directorate Identifier 2008-CE-073-AD.
Effective Date
(a) This AD becomes effective on March 2, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following airplane models and serial
numbers that are certificated in any category:
------------------------------------------------------------------------
Models Serial Nos.
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401............................................. 655 and 401-0001
through 401-0322.
401A............................................ 655 and 401A0001
through 401A0132.
401B............................................ 401B0001 through
401B0221.
402............................................. 402-0001 through 402-
0322.
402A............................................ 402A0001 through
402A0129.
402B............................................ 402B0001 through
402B0122, 402B0201
through 402B0249,
402B0301 through
402B0455, 402B0501
through 402B0640,
402B0801 through
402B0935, 402B1001
through 402B1100,
402B1201 through
402B1250, and
402B1301 through
402B1384.
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Unsafe Condition
(d) This AD is the result of several reports of fatigue cracking
on the affected airplanes in the auxiliary wing spar. We are issuing
this AD to detect and correct such cracks, which, if not corrected,
could result in failure of the wing auxiliary spar web and cause
landing gear collapse during normal landing. This could lead to loss
of control and passenger injury.
Compliance
(e) To address this problem, you must do the actions below using
Cessna Service Bulletin MEB08-8, dated December 23, 2008, at the
following compliance time, unless already done:
Note 1: Cessna Service Bulletin MEB08-8, dated December 23,
2008, provides detailed instructions on measuring, inspecting, and
replacing cracked parts, including how to handle two or more cracks
in the same hole.
(1) Within the next 10 hours time-in-service (TIS) after March
2, 2009 (the effective date of this AD) and, in addition, before
further flight anytime the airplane experiences a ``hard landing,''
visually inspect the auxiliary wing spar near the location where the
main landing gear trunnion is mounted for cracks.
(2) If any crack is found during any inspection required by this
AD that is 0.5 inch or more, before further flight after any such
crack is found, replace the cracked parts.
(3) If cracks are found during any inspection required by this
AD that are less than 0.5 inch, do the following:
(i) Repetitively thereafter inspect the cracks for length at
intervals not to exceed 50 hours TIS and, before further flight,
replace any part that has a crack length of 0.5 inch or more; and
(ii) Replace the cracked part within 200 hours TIS after the
original crack was found or within 12 months after the original
crack was found, whichever occurs first.
(4) If you find any cracks as a result of any inspection
required by this AD, report the results to Cessna using the form in
the service bulletin. Send a copy of this report to the FAA at the
address specified in paragraph (f) of this AD. For the reporting
requirement in this AD, under the provisions of the Paperwork
Reduction Act, the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056. Do the reporting requirement at
whichever of the following that occurs later:
(i) Within 10 days after the inspection; or
(ii) Within the next 10 days after March 2, 2009 (the effective
date of this AD).
Note 2: The FAA considers this interim action. We will work with
Cessna and evaluate the crack reports and all other information.
Based on this information, we may initiate additional rulemaking
action.
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Wichita Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. Send information to
ATTN: Adam Neubauer, Wichita ACO, Aerospace Engineer, 1801 Airport
Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4156;
fax: (316) 946-4107. Before using any approved AMOC on any airplane
to which the AMOC applies, notify your appropriate principal
inspector (PI) in the FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
Material Incorporated by Reference
(g) You must use Cessna Service Bulletin MEB08-8, dated December
23, 2008, to do the actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Cessna Aircraft Company, P.O. Box 7704, Wichita, Kansas 67277;
telephone: (800) 423-7762 or (316) 517-6056; Internet: http://www.cessna.com.
(3) You may review copies of the service information
incorporated by reference for this AD at the FAA, Central Region,
Office of the Regional Counsel, 901 Locust, Kansas City, Missouri
64106. For information on the availability of this material at the
Central Region, call (816) 329-3768.
(4) You may also review copies of the service information
incorporated by reference for this AD at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Kansas City, Missouri, on February 6, 2009.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E9-3016 Filed 2-17-09; 8:45 am]
BILLING CODE 4910-13-P