[Federal Register Volume 64, Number 106 (Thursday, June 3, 1999)]
[Rules and Regulations]
[Pages 29781-29783]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-13875]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-CE-21-AD; Amendment 39-11184; AD 99-11-13]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company Model 402C 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain Cessna Aircraft Company (Cessna) Model 402C 
airplanes. This AD requires inspecting the forward, aft, and auxiliary 
wing spars for cracks; repairing any cracks found; and reporting the 
results of the inspection to the Federal Aviation Administration (FAA). 
This AD is the result of an accident of one of the affected airplanes 
where the right-hand wing failed just inboard of the nacelle at Wing 
Station (WS) 87. Investigation of this accident revealed fatigue 
cracking of the forward main spar that initiated at the edge of the 
front spar forward lower spar cap. The actions specified by this AD are 
intended to detect and correct any cracks in the forward, aft, and 
auxiliary wing spars, which could result in reduced or loss of control 
of the airplane.

DATES: Effective June 21, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 21, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before July 23, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 99-CE-21-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.
    Service information that applies to this AD may be obtained from 
the Cessna Aircraft Company, P. O. Box 7706, Wichita, Kansas 67277; 
telephone: (316) 941-7550, facsimile: (316) 942-9008. This information 
may also be examined at the Federal Aviation Administration (FAA), 
Central Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 99-CE-21-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. Eual Conditt, Aerospace Engineer, 
FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 
100, Mid-Continent Airport, Wichita, Kansas 67209, telephone: (316) 
946-4128; facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA has received a report of an accident on a Cessna Model 402C 
airplane where the right-hand wing failed just inboard of the nacelle 
at Wing Station (WS) 87 during a normal descent. Investigation of this 
accident revealed fatigue cracking of the forward main spar that 
initiated at the edge of the front spar forward lower spar cap.
    The airplane involved in the above-referenced accident had 
accumulated over 20,000 hours time-in-service (TIS). Analysis shows 
that the fatigue cracks could propagate after 10,000 hours TIS. 
Information available to the FAA shows that a large percentage of the 
Cessna Model 402C airplane fleet has already accumulated 10,000 hours 
TIS.

Relevant Service Information

    Cessna has issued Service Bulletin MEB99-3, dated May 6, 1999, 
which includes procedures for conducting an internal and external 
inspection of the forward, aft, and auxiliary wing spars for cracks.

The FAA's Determination

    After examining the circumstances and reviewing all available 
information related to the incidents described above, including the 
relevant service information, the FAA has determined that:

--In order to detect cracking on Cessna Model 402C airplanes, an 
external and internal inspection of the forward, aft, and auxiliary 
wing spars for cracks should be accomplished upon accumulating 10,000 
hours total TIS on the airplane or within the next 25 hours TIS for 
those airplanes having already accumulated 10,000 hours TIS; and
--AD action should be taken to assure that these inspections are 
accomplished.

Explanation of the Provisions of the AD

    Since an unsafe condition has been identified that is likely to 
exist or develop in other Cessna Model 402C airplanes of the same type 
design, this AD requires inspecting the forward, aft, and auxiliary 
wing spars for cracks; repairing any cracks found; and reporting the 
results of the inspection to the FAA.
    Accomplishment of the inspections as specified in this AD is 
required in accordance with Cessna Service Bulletin MEB99-3, dated May 
6, 1999. The repair, if necessary, is required in accordance with an 
FAA-approved repair scheme.

Possible Follow-Up AD Action

    The FAA is requiring a reporting requirement of the inspection 
results in order to analyze the situation and determine whether 
repetitive inspections of the wing spars are necessary. The FAA will 
review all information received and will then determine whether 
additional AD action is necessary.

[[Page 29782]]

Determination of the Effective Date of the AD

    Since a situation (possible loss of control of the airplane caused 
by a cracked wing spar) exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for public 
prior comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting immediate flight safety and, thus, was not 
preceded by notice and opportunity to comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
in triplicate to the address specified above. All communications 
received on or before the closing date for comments will be considered, 
and this rule may be amended in light of the comments received. Factual 
information that supports the commenter's ideas and suggestions is 
extremely helpful in evaluating the effectiveness of the AD action and 
determining whether additional rulemaking action would be needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 99-CE-21-AD.'' The postcard will be date stamped and 
returned to the commenter.

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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and is not a significant regulatory action under 
Executive Order 12866. It has been determined further that this action 
involves an emergency regulation under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979). If it is determined that 
this emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the Rules Docket (otherwise, an evaluation is 
not required). A copy of it, if filed, may be obtained from the Rules 
Docket.

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:

99-11-13  Cessna Aircraft Company: Amendment 39-11184; Docket No. 
99-CE-21-AD.
    Applicability: Model 402C airplanes, serial numbers 689; 
402C0001 through 402C0125; 402C0201 through 402C0355; 402C0401 
through 402C0528; 402C0601 through 402C0653; and 402C0801 through 
402C1020, certificated in any category.

    Note 1: 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 (e) 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 as indicated in the body of this AD, unless 
already accomplished.

    Note 2: The compliance times specified in Cessna Service 
Bulletin MEB99-3, dated May 6, 1999, are different than those 
required by this AD. The compliance times of this AD take precedence 
over those specified in the service bulletin.

    To detect and correct any cracks in the forward, aft, and 
auxiliary wing spars, which could result in reduced or loss of 
control of the airplane, accomplish the following:
    (a) Upon accumulating 10,000 hours total time-in-service (TIS) 
on the airplane or within the next 25 hours TIS after the effective 
date of this AD, whichever occurs later, accomplish the external and 
internal inspection of the forward, aft, and auxiliary wing spars 
for cracks, in accordance with the ACCOMPLISHMENT INSTRUCTIONS 
section of Cessna Service Bulletin MEB99-3, dated May 6, 1999.
    (b) If any crack(s) is/are found on any forward, aft, or 
auxiliary wing spar during the inspections required by paragraph (a) 
of this AD, prior to further flight, accomplish the following:
    (1) Obtain an FAA-approved repair scheme from the Cessna 
Aircraft Company, P. O. Box 7706, Wichita, Kansas 67277; telephone: 
(316) 941-7550, facsimile: (316) 942-9008; and
    (2) Incorporate this repair scheme.
    (c) If any crack(s) is/are found during the inspections required 
by paragraph (a) of this AD, submit a report of inspection findings 
to the Manager, Wichita Aircraft Certification Office (ACO), 1801 
Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 
67209; facsimile: (316) 946-4407; at the applicable time specified 
in paragraph (c)(1) or (c)(2) of this AD. The report must include 
the results of the findings, a description of any cracking found, a 
description of any previous wing repairs or modifications, the 
airplane serial number, and the total number of hours TIS on the 
airplane. The ``Lower Wing Spars and Skin Inspection Report'' 
included as page 6 of Cessna Service Bulletin MEB99-3, dated May 6, 
1999, may be utilized for this reporting requirement. Information 
collection requirements contained in this regulation have been 
approved by the Office of Management and Budget (OMB) under the 
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et 
seq.) and have been assigned OMB Control Number 2120-0056.
    (1) For airplanes on which the inspections are accomplished 
after the effective date of this AD: Submit the report within 10 
days after performing the inspection required by paragraph (a) of 
this AD.
    (2) For airplanes on which the inspections have already been 
accomplished prior to the effective date of this AD: Submit the 
report within 10 days after the effective date of this AD, unless 
already accomplished.
    (d) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the airplane to a

[[Page 29783]]

location where the requirements of this AD can be accomplished.
    (e) An alternative method of compliance or adjustment of the 
compliance times that provides an equivalent level of safety may be 
approved by the Manager, Wichita Aircraft Certification Office 
(ACO), 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, 
Kansas 67209. The request shall be forwarded through an appropriate 
FAA Maintenance Inspector, who may add comments and then send it to 
the Manager, Wichita ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita ACO.

    (f) The inspections required by this AD shall be done in 
accordance with Cessna Service Bulletin MEB99-3, dated May 6, 1999. 
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 the Cessna Aircraft Company, P. O. 
Box 7706, Wichita, Kansas 67277. 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.
    (g) This amendment becomes effective on June 21, 1999.

    Issued in Kansas City, Missouri, on May 21, 1999.
Michael K. Dahl,
Acting Manager, Small Airplane Directorate.
[FR Doc. 99-13875 Filed 6-2-99; 8:45 am]
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