AD 2002-07-01

[Federal Register Volume 67, Number 64 (Wednesday, April 3, 2002)]
[Rules and Regulations]
[Pages 15714-15717]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-7645]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-42-AD; Amendment 39-12695; AD 2002-07-01]
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: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain Cessna Aircraft Company (Cessna) P206, TP206, TU206, 
U206, 207, T207, 210, P210, and T210 series airplanes. This AD requires 
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 AD authorizes the 
pilot to check the logbooks to determine whether one of the affected 
horizontal stabilizer attachment reinforcement brackets is installed. 
This AD is the result of a report that certain parts were manufactured 
without seam welds. 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.

DATES: This AD becomes effective on May 13, 2002.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of May 
13, 2002.

ADDRESSES: You may get the service information referenced in this AD 
from Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, 
Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-9006. You 
may view this information at the Federal Aviation Administration (FAA), 
Central Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 2001-CE-42-AD, 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.

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:

Discussion

What events have caused this 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 is the potential impact if FAA took no action?

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

Has FAA taken any action to this point?

    We issued a proposal to amend part 39 of the Federal Aviation 
Regulations (14 CFR part 39) to include an AD that would apply to 
certain Cessna P206, TP206, TU206, U206, 207, T207, 210, P210, and T210 
series airplanes. This proposal was published in the Federal Register 
as a notice of proposed rulemaking (NPRM) on December 17, 2001 (66 FR 
64925). The NPRM proposed to require you to visually inspect the right 
and left horizontal stabilizer attachment reinforcement brackets for 
the existence of seam welds along the lower inboard and outboard wall/
flange. The NPRM also proposed to require you to remove and replace any 
horizontal stabilizer bracket found without seam welds.

Was the public invited to comment?

    The FAA encouraged interested persons to participate in the making 
of this amendment. We did not receive any comments on the proposed rule 
or on our determination of the cost to the public.

FAA's Determination

What is FAA's final determination on this issue?

    After careful review of all available information related to the 
subject presented above, we have determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. We have determined that these minor 
corrections:
--Provide the intent that was proposed in the NPRM for correcting the 
unsafe condition; and
--Do not add any additional burden upon the public than was already 
proposed in the NPRM.

[[Page 15715]]

What are the differences between the service information and this 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), not to exceed 30 
days, of operation. We are requiring 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 this 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 actions accomplished without compromising the safety of the 
airplanes.

Cost Impact

How many airplanes does this AD impact?

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

What is the cost impact of this AD on owners/operators of the affected 
airplanes?

    We estimate the following costs to accomplish the inspection:

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                                                                                          Total cost on U.S.
               Labor cost                   Parts cost      Total cost per airplane            operators
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2 workhours  x  $60 = $120..............             Not   $120.....................  $120  x  144 = $17,280.
                                             applicable.
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    We estimate the following costs to accomplish any necessary 
replacements that will be required based on the results of the 
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

Does this AD impact various entities?

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

Does this AD involve a significant rule or regulatory action?

    For the reasons discussed above, I certify that this 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) 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 final evaluation prepared for this 
action is contained 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

    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

    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 AD to read as follows:

2002-07-01 Cessna Aircraft Company: Amendment 39-12695; 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 numbers
------------------------------------------------------------------------
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 20601700
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
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 airplanes identified in paragraph (a) of this AD 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

[[Page 15716]]

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:

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                      Actions                                 Compliance                     Procedures
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(1) Maintenance Records Check:                      Within the next 50 hours time- No special procedures
                                                     in-service (TIS) after May     required to check the
                                                     13, 2002 (the effective date   logbook.
                                                     of this AD), unless already
                                                     accomplished.
    (i) Check the maintenance records to determine
     whether a horizontal stabilizer attachment
     reinforcement bracket, part number (P/N)
     1232624-1, shipped by Cessna from February
     27, 1998, through 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 do 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 and      Within the next 50 hours TIS   In accordance with the
 left horizontal stabilizer attachment               after May 13, 2002 (the        Accomplishment Instructions
 reinforcement brackets, part number (P/N) 1232624-  effective date of this AD),    in Cessna Service Bulletin
 1, for the existence of seam welds along both the   unless already accomplished.   SEB00-10, dated November 6,
 lower inboard and outboard wall/flange.                                            2000, and the applicable
                                                                                    maintenance manual.
(3) Replacement:                                    Accomplish any necessary       In accordance with the
                                                     replacements prior to          Accomplishment Instructions
                                                     further flight after the       in Cessna Service Bulletin
                                                     inspection required by         SEB00-10, dated November 6,
                                                     paragraph (d)(2) of this AD,   2000, and the applicable
                                                     unless already accomplished.   maintenance manual.
    (i) If no seam weld is found along both the
     lower inboard and outboard wall/flange on the
     right and left horizontal stabilizer
     attachment reinforcement bracket during the
     inspection required in paragraph (d)(2) of
     this AD, replace with a new or airworthy P/N
     1232624-1 horizontal stabilizer 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    As of May 13, 2002 (the        Not applicable.
     any P/N 1232624-1 horizontal stabilizer         effective date of this AD).
     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.
    (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) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with Cessna Service Bulletin SEB00-10, dated November 6, 2000. The 
Director of the Federal Register approved this incorporation by 
reference under 5 U.S.C. 552(a) and 1 CFR part 51. You can get 
copies from Cessna Aircraft Company, Product Support, P.O. Box 7706, 
Wichita, Kansas 67277. You can look at copies at the FAA, Central 
Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas 
City, Missouri, or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.
    (i) When does this amendment become effective? This amendment 
becomes effective on May 13, 2002.


[[Page 15717]]


    Issued in Kansas City, Missouri, on March 22, 2002.
Dorenda D. Baker,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-7645 Filed 4-2-02; 8:45 am]
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