[Federal Register Volume 66, Number 242 (Monday, December 17, 2001)]
[Proposed Rules]
[Pages 64925-64928]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-30954]



[[Page 64925]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-42-AD]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company P206, TP206, 
TU206, U206, 207, T207, 210, P210, and T210 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to adopt a new airworthiness directive 
(AD) that would apply to certain Cessna Aircraft Company (Cessna) P206, 
TP206, TU206, U206, 207, T207, 210, P210, and T210 series airplanes. 
This proposed AD would require you to visually inspect certain 
horizontal stabilizer attachment reinforcement brackets for the 
existence of seam welds and replace any reinforcement bracket found 
without seam welds. This proposed AD authorizes the pilot to check the 
logbooks to determine whether one of the affected horizontal stabilizer 
attachment reinforcement brackets is installed. This proposed AD is the 
result of a report that certain parts were manufactured without seam 
welds. The actions specified by this proposed AD are intended to detect 
and replace structurally deficient horizontal stabilizer attachment 
brackets. Continued use of such brackets could result in structural 
failure of the horizontal stabilizer with reduced or loss of control of 
the airplane.

DATES: The Federal Aviation Administration (FAA) must receive any 
comments on this proposed rule on or before February 11, 2002.

ADDRESSES: Submit comments to FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2001-CE-42-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. You may view any 
comments at this location between 8 a.m. and 4 p.m., Monday through 
Friday, except Federal holidays.
    You may get service information that applies to this proposed AD 
from Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, 
Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-9006. You 
may also view this information at the Rules Docket at the address 
above.

FOR FURTHER INFORMATION CONTACT: Al Phillips, Aerospace Engineer, 
Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-
Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4116; 
facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Comments Invited

How Do I Comment on This Proposed AD?

    The FAA invites comments on this proposed rule. You may submit 
whatever written data, views, or arguments you choose. You need to 
include the rule's docket number and submit your comments to the 
address specified under the caption ADDRESSES. We will consider all 
comments received on or before the closing date. We may amend this 
proposed rule in light of comments received. Factual information that 
supports your ideas and suggestions is extremely helpful in evaluating 
the effectiveness of this proposed AD action and determining whether we 
need to take additional rulemaking action.

Are There Any Specific Portions of This Proposed AD I Should Pay 
Attention to?

    The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed rule that 
might suggest a need to modify the rule.
    You may view all comments we receive before and after the closing 
date of the rule in the Rules Docket. We will file a report in the 
Rules Docket that summarizes each contact we have with the public that 
concerns the substantive parts of this proposed AD.

How Can I Be Sure FAA Receives My Comment?

    If you want FAA to acknowledge the receipt of your comments, you 
must include a self-addressed, stamped postcard. On the postcard, write 
``Comments to Docket No. 2001-CE-42-AD.'' We will date stamp and mail 
the postcard back to you.

Discussion

What Events Have Caused This Proposed AD?

    Cessna notified FAA of a defect in the manufacturing of the 
horizontal stabilizer attachment reinforcement brackets. Cessna 
manufactured reinforcement brackets without seam welds on certain 
Cessna Model 206H and T206H airplanes. AD 2001-09-06, Amendment 39-
12211, (66 FR 21278, April 30. 2001), addresses these airplanes. The 
seam welds help provide the required structural integrity for the 
horizontal stabilizer attachment bracket.
    Since the issuance of AD 2001-09-06, Cessna determined that certain 
Model P206, TP206, TU206, U206, 207, T207, 210, P210, and T210 series 
airplanes may have had horizontal stabilizer attachment reinforcement 
brackets (part number 1232624-1) without seam welds installed as 
replacement parts. Cessna shipped these brackets from February 27, 
1998, through March 17, 2000.

What Are the Consequences if the Condition Is Not Corrected?

    This condition, if not corrected, could result in structural 
failure of the horizontal stabilizer with reduced or loss of control of 
the airplane.

Is There Service Information That Applies to This Subject?

    Cessna has issued Service Bulletin SEB00-10, dated November 6, 
2000.

What Are the Provisions of This Service Information?

    The service bulletin includes procedures for:

--Visually inspecting the right and left horizontal stabilizer 
attachment reinforcement brackets for the existence of seam welds along 
the lower inboard and outboard wall/flange; and
--Removing and replacing the horizontal stabilizer assemblies with new 
parts.

The FAA's Determination and an Explanation of the Provisions of 
This Proposed AD

What Has FAA Decided?

    After examining the circumstances and reviewing all available 
information related to the incidents described above, we have 
determined that:

--The unsafe condition referenced in this document exists or could 
develop on other Cessna P206, TP206, TU206, U206, 207, T207, 210, P210, 
and T210 series airplanes of the same type design;
--The actions specified in the previously-referenced service 
information should be accomplished on the affected airplanes; and
--AD action should be taken in order to correct this unsafe condition.

What Would This Proposed AD Require?

    This proposed AD would require you to incorporate the actions in 
the previously-referenced service bulletin.

What Are the Differences Between the Service Information and This 
Proposed AD?

    Cessna requires you to inspect and, if necessary, replace the 
horizontal stabilizer attachment reinforcement brackets, part number 
1232624-1, within 20 hours time-in-service (TIS),

[[Page 64926]]

not to exceed 30 days, of operation. We are proposing a requirement 
that you inspect and, if necessary, replace the horizontal stabilizer 
attachment reinforcement brackets, part number 1232624-1, within 50 
hours TIS of operation after the effective date of the proposed AD.
    We do not have justification to require this action within 20 hours 
TIS. Compliance times such as this are utilized when we have identified 
an urgent safety of flight situation. We believe that 50 hours TIS will 
give the owners/operators of the affected airplanes enough time to have 
the proposed actions accomplished without compromising the safety of 
the airplanes.

Cost Impact

How Many Airplanes Would This Proposed AD Impact?

    We estimate that this proposed AD affects 144 airplanes in the U.S. 
registry.

What Would Be the Cost Impact of This Proposed AD on Owners/Operators 
of the Affected Airplanes?

    We estimate the following costs to accomplish the proposed 
inspection:

----------------------------------------------------------------------------------------------------------------
                                                                         Total cost
                Labor cost                          Parts cost              per           Total cost on U.S.
                                                                          airplane            operators
----------------------------------------------------------------------------------------------------------------
2 workhours  x  $60 = $120...............  Not applicable.............         $120  $120  x  144 = $17,280.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to accomplish any necessary 
replacements that would be required based on the results of the 
proposed inspection. We have no way of determining the number of 
airplanes that may need such replacement:

------------------------------------------------------------------------
                                                        Total cost per
           Labor cost                 Parts cost           airplane
------------------------------------------------------------------------
24 workhours to replace both      $135 for both the   $1,440 + $135 =
 brackets  x  $60 = $1,440.        right and left      $1,575.
                                   bracket.
------------------------------------------------------------------------

Regulatory Impact

Would This Proposed AD Impact Various Entities?

    The regulations proposed herein would 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. Therefore, it 
is determined that this proposed rule would not have federalism 
implications under Executive Order 13132.

Would This Proposed AD Involve a Significant Rule or Regulatory Action?

    For the reasons discussed above, I certify that this proposed 
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) if 
promulgated, 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 draft regulatory 
evaluation prepared for this action has been placed 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, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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. FAA amends Sec. 39.13 by adding a new airworthiness directive 
(AD) to read as follows:

Cessna Aircraft Company: Docket No. 2001-CE-42-AD

    (a) What airplanes are affected by this AD? This AD affects the 
following airplane models and serial numbers that are certificated 
in any category:

------------------------------------------------------------------------
                 Model                             Serial Nos.
------------------------------------------------------------------------
P206C and TP206C.......................  P206-0420 through P206-0519.
P206D and TP206D.......................  P206-0520 through P206-0603.
P206E and TP206E.......................  P20600604 through P20600647,
                                          and P206-0001.
U206C and TU206C.......................  U206-0915 through U206-1234.
U206D and TU206D.......................  U206-1235 through U206-1444,
                                          U20601445 through U20601587.
U206E and TU206E.......................  U20601588 through U20601700.
U206F and TU206F.......................  U20601701 through U20602588,
                                          and U20602590 through
                                          U20603521.
U206G and TU206G.......................  676, U20602589, and U20603522
                                          through U20607020.
207 and T207...........................  20700001 through 20700362.
207A and T207A.........................  20700363 through 20700788.
210G...................................  21058819 through 21058936.
210H...................................  21058937 through 21059061.
210J...................................  21059062 through 21059199.
210K and T210K.........................  21059200 through 21059502.
210L and T210L.........................  21059503 through 21061041, and
                                          21061043 through 21061573.
210M and T210M.........................  21061042, and 21061574 through
                                          21062954.
210N and T210N.........................  21062955 through 21064897.
P210N..................................  P21000001 through P21000834.
T210G..................................  T210-0198 through T210-0307.

[[Page 64927]]

 
T210H..................................  T210-0308 through T210-0392.
T210J..................................  T210-0393 through T210-0454,
                                          and 21058140.
------------------------------------------------------------------------

    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the above airplanes must comply with this AD.
    (c) What problem does this AD address? The actions specified by 
this AD are intended to detect and replace structurally deficient 
horizontal stabilizer attachment brackets. Continued use of such 
brackets could result in structural failure of the horizontal 
stabilizer with reduced or loss of control of the airplane.
    (d) What actions must I accomplish to address this problem? To 
address this problem, you must accomplish the following:

------------------------------------------------------------------------
             Actions                  Compliance          Procedures
------------------------------------------------------------------------
(1) Maintenance Records Check:
    (i) Check the maintenance     Within the next 50  No special
     records to determine          hours time-in-      procedures
     whether a horizontal          service (TIS)       required to check
     stabilizer attachment         after the           the logbook.
     reinforcement bracket, part   effective date of
     number (P/N) 1232624-1        this AD, unless
     shipped by Cessna from        already
     February 27, 1998, through    accomplished.
     March 17, 2000, is
     installed. The owner/
     operator holding at least a
     private pilot certificate
     as authorized by section
     43.7 of the Federal
     Aviation Regulations (14
     CFR 43.7) may perform this
     check.
    (ii) If, by checking the
     maintenance records, the
     owner/operator can
     positively show that a
     horizontal stabilizer
     attachment reinforcement
     bracket, P/N 1232624-1
     shipped by Cessna from
     February 27, 1998, through
     March 17, 2000, is not
     installed, then the
     inspection requirement of
     paragraph (d)(2) and the
     replacement requirement of
     paragraph (d)(3) of this AD
     does not apply. You must
     make an entry into the
     aircraft records that shows
     compliance with this
     portion of the AD, in
     accordance with section
     43.9 of the Federal
     Aviation Regulations (14
     CFR 43.9).
------------------------------------------------------------------------
(2) Inspection:
    Visually inspect the right    Within the next 50  In accordance with
     and left horizontal           hours TIS after     the
     stabilizer attachment         the effective       Accomplishment
     reinforcement brackets,       date of this AD,    Instructions in
     part number (P/N) 1232624-    unless already      Cessna Service
     1, for the existence of       accomplished.       Bulletin SEB00-
     seam welds along both the                         10, dated
     lower inboard and outboard                        November 6, 2000,
     wall/flange.                                      and the
                                                       applicable
                                                       maintenance
                                                       manual.
------------------------------------------------------------------------
(3) Replacement:
    (i) If no seam weld is found  Accomplish any      In accordance with
     along both the lower          necessary           the
     inboard and outboard wall/    replacements        Accomplishment
     flange on the right and       prior to further    Instructions in
     left horizontal stabilizer    flight after the    Cessna Service
     attachment reinforcement      inspection          Bulletin SEB00-
     bracket during the            required by this    10, dated
     inspection required in        AD, unless          November 6, 2000,
     paragraph (d)(2) of this      already             and the
     AD, replace with a new or     accomplished.       applicable
     airworthy P/N 1232624-1                           maintenance
     horizontal stabilizer                             manual.
     attachment reinforcement
     bracket.
    (ii) If the right and left
     horizontal stabilizer
     attachment reinforcement
     bracket has seam welds
     along both the lower
     inboard and outboard wall/
     flange, no further action
     is required.
------------------------------------------------------------------------
(4) Installation Prohibition:
  Do not install any P/N 1232624- Not applicable....  Not applicable.
   1 horizontal stabilizer
   attachment reinforcement
   bracket (or FAA-approved
   equivalent part) unless the
   bracket:
    (i) is inspected as required
     in paragraph (d)(2) of this
     AD; and
    (ii) has seam welds along
     both the lower inboard and
     outboard wall/flange
------------------------------------------------------------------------


[[Page 64928]]

    (e) Can I comply with this AD in any other way? You may use an 
alternative method of compliance or adjust the compliance time if:
    (1) Your alternative method of compliance provides an equivalent 
level of safety; and
    (2) The Manager, Wichita Aircraft Certification Office (ACO), 
approves your alternative. Submit your request through an FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Wichita ACO.

    Note: This AD applies to each airplane identified in paragraph 
(a) of this AD, 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 you have not eliminated the unsafe condition, specific 
actions you propose to address it.

    (f) Where can I get information about any already-approved 
alternative methods of compliance? Contact Al Phillips, Aerospace 
Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport 
Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 
946-4116; facsimile: (316) 946-4407.
    (g) What if I need to fly the airplane to another location to 
comply with this AD? The FAA can issue a special flight permit under 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate your airplane to a location where 
you can accomplish the requirements of this AD.
    (h) How do I get copies of the documents referenced in this AD? 
You may get copies of the documents referenced in this AD from 
Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, 
Kansas 67277. You may view these documents at FAA, Central Region, 
Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, 
Missouri 64106.

    Issued in Kansas City, Missouri, on December 6, 2001.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 01-30954 Filed 12-14-01; 8:45 am]
BILLING CODE 4910-13-P