[Federal Register Volume 66, Number 168 (Wednesday, August 29, 2001)]
[Proposed Rules]
[Pages 45648-45651]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-21754]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-01-AD]
RIN 2120-AA64


Airworthiness Directives; SOCATA--Groupe Aerospatiale Models TB 
9, TB 10, TB 20, TB 21, and TB 200 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 all SOCATA--Groupe Aerospatiale (SOCATA) 
Models TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes. The proposed AD 
would require you to repetitively inspect the lower rudder hinge 
fitting for cracks. The proposed AD would also require you to repair 
any crack found in accordance with a repair scheme obtained from the 
manufacturer through the Federal Aviation Administration (FAA). The 
proposed AD is the result of mandatory continuing airworthiness 
information (MCAI) issued by the airworthiness authority for France. 
The actions specified by the proposed AD are intended to detect and 
correct fatigue cracks in the lower rudder hinge fitting. This 
condition could cause the lower rudder to detach from the control 
linkage with consequent loss of control of the airplane.

DATES: The FAA must receive any comments on this proposed rule on or 
before September 28, 2001.

ADDRESSES: Submit comments in triplicate to FAA, Central Region, Office 
of the Regional Counsel, Attention: Rules Docket No. 2001-CE-01-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. Comments may be 
inspected at this location between 8 a.m. and 4 p.m., Monday through 
Friday, holidays excepted.
    Service information that applies to the proposed AD may be obtained 
from SOCATA Groupe AEROSPATIALE, Customer Support, Aerodrome Tarbes-
Ossun-Lourdes, BP 930--F65009 Tarbes Cedex, France; telephone: (33)

[[Page 45649]]

(0)5.62.41.73.00; facsimile: (33) (0)5.62.41.76.54; or the Product 
Support Manager, SOCATA--Groupe AEROSPATIALE, North Perry Airport, 7501 
Pembroke Road, Pembroke Pines, Florida 33023; telephone: (954) 894-
1160; facsimile: (954) 964-4191. This information also may be examined 
at the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer, 
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4146; facsimile: (816) 329-4090.

SUPPLEMENTARY INFORMATION:

Comments Invited

    How do I comment on the 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 in triplicate to the address specified under the 
caption ADDRESSES. The FAA will consider all comments received on or 
before the closing date. We may amend the proposed rule in light of 
comments received. Factual information that supports your ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
proposed AD action and determining whether we need to take additional 
rulemaking action.
    Are there any specific portions of the proposed AD I should pay 
attention to? The FAA specifically invites comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
rule that might suggest a need to modify the rule. You may examine 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 FAA contact with the public that concerns the 
substantive parts of the proposed AD.
    We are re-examining the writing style we currently use in 
regulatory documents, in response to the Presidential memorandum of 
June 1, 1998. That memorandum requires federal agencies to communicate 
more clearly with the public. We are interested in your comments on 
whether the style of this document is clear, and any other suggestions 
you might have to improve the clarity of FAA communications that affect 
you. You can get more information about the Presidential memorandum and 
the plain language initiative at http://www.plainlanguage.gov.
    How can I be sure FAA receives my comment? If you want us 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-01-AD.'' We will date stamp and mail the postcard 
back to you.

Discussion

    What events have caused this proposed AD? The Direction Generale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, recently notified FAA that an unsafe condition may exist on all 
SOCATA Models TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes. The DGAC 
reports an occurrence of the lower rudder separating from the control 
linkage on a Model TB 9 airplane. A break in the lower rudder hinge 
fitting caused this problem and was found during a scheduled inspection 
on the airplane with more than 6,000 hours time-in-service (TIS). The 
DGAC reports that material fatigue caused cracks in the lower rudder 
hinge fitting.
    What are the consequences if the condition is not corrected? If 
this condition is not detected and corrected, the lower rudder could 
detach from the control linkage with consequent loss of control of the 
airplane.
    Is there service information that applies to this subject? SOCATA 
has issued Service Bulletin SB 10-114 55, dated September 2000.
    What are the provisions of this service bulletin? The service 
bulletin includes procedures for inspecting the lower rudder hinge 
fitting for cracks. This document also includes information about where 
to obtain a repair scheme for a cracked lower rudder hinge fitting.
    What action did the DGAC take? The DGAC classified this service 
bulletin as mandatory and issued French AD Number 2001-002(A), dated 
January 10, 2001, in order to assure the continued airworthiness of 
these airplanes in France.
    Was this in accordance with the bilateral airworthiness agreement? 
These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept FAA informed of 
the situation described above.

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

    What has FAA decided? The FAA has examined the findings of the 
DGAC; reviewed all available information, including the service 
information referenced above; and determined that:
    --The unsafe condition referenced in this document exists or could 
develop on other SOCATA Models TB 9, TB 10, TB 20, TB 21, and TB 200 
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 the proposed AD require? This proposed AD would require 
you to repetitively inspect the lower rudder hinge fitting for cracks 
and repair any crack found in accordance with a repair scheme obtained 
from the manufacturer through the Federal Aviation Administration 
(FAA).
    Is there a modification I can incorporate instead of repetitively 
inspecting the lower rudder hinge fitting? The FAA has determined that 
long-term continued operational safety would be better assured by 
design changes that remove the source of the problem rather than by 
repetitive inspections or other special procedures. With this in mind, 
FAA will continue to work with SOCATA in collecting information and in 
performing fatigue analysis to determine whether a future design change 
may be necessary.

Cost Impact

    How many airplanes would the proposed AD impact? We estimate that 
the proposed AD affects 239 airplanes in the U.S. registry.
    What would be the cost impact of the proposed AD on owners/
operators of the affected airplanes? We estimate the following costs to 
accomplish the proposed inspection:

----------------------------------------------------------------------------------------------------------------
                                                                                                   Total cost on
                  Labor cost                               Parts cost             Total cost per       U.S.
                                                                                      airplane       operators
----------------------------------------------------------------------------------------------------------------
3 workhours  x  $60 per hour = $180...........  No parts required to perform the            $180         $43,020
                                                 inspection.
----------------------------------------------------------------------------------------------------------------


[[Page 45650]]

    The FAA has no method of determining the number of repetitive 
inspections each owner/operator would incur over the life of each of 
the affected airplanes so the cost impact is based on the initial 
inspection.
    We estimate the following costs to accomplish any necessary repairs 
that would be required based on the results of the proposed 
inspections. We have no way of determining the number of repairs each 
owner/operator would incur over the life of each of the affected 
airplanes based on the results of the proposed inspections.

------------------------------------------------------------------------
                                                          Total cost per
               Labor cost                   Parts cost        Airplane
------------------------------------------------------------------------
7 workhours  x  $60 = $420..............            $300            $720
------------------------------------------------------------------------

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:

SOCATA--Groupe Aerospatiale: Docket No. 2001-CE-01-AD

    (a) What airplanes are affected by this AD? This AD affects the 
following TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes, all 
serial numbers, that are certificated in any category.
    (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 correct fatigue cracks in the 
lower rudder hinge fitting. This condition could cause the lower 
rudder to detach from the control linkage with consequent 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) Visually inspect the      Upon accumulating     In accordance with
 lower rudder hinge fitting    2,000 hours time-in-  the ACCOMPLISHMENT
 for cracks.                   service (TIS) on      INSTRUCTIONS
                               the rudder hinge      section of SOCATA
                               fitting or within     Service Bulletin SB
                               the next 100 hours    10-114 55, dated
                               TIS after the         September 2000, and
                               effective date of     the applicable
                               this AD, whichever    aircraft
                               occurs later, and     maintenance manual.
                               thereafter at
                               intervals not to
                               exceed 12 calendar
                               months.
------------------------------------------------------------------------
(2) If any crack is found     Prior to further      In accordance with
 during any inspection         flight after the      the repair scheme
 required in paragraph         inspection required   obtained from
 (d)(1) of this AD,            in paragraph (d)(1)   SOCATA Groupe
 accomplish the following:     of this AD.           AEROSPATIALE,
   (i) Obtain a repair                               Customer Support,
 scheme from the                                     Aerodrome Tarbes-
 manufacturer through the                            Ossun-Lourdes, BP
 FAA at the address                                  930--F65009 Tarbes
 specified in paragraph (f)                          Cedex, France;
 of this AD; and                                     telephone: (33)
   (ii) Incorporate this                             05.62.41.76.68;
 repair scheme                                       facsimile: (33)
                                                     06.07.32.62.24; or
                                                     the Product Support
                                                     Manager, SOCATA--
                                                     Groupe
                                                     AEROSPATIALE, North
                                                     Perry Airport, 7501
                                                     Pembroke Road,
                                                     Pembroke Pines,
                                                     Florida 33023;
                                                     telephone: (954)
                                                     893-1450. Obtain
                                                     this repair scheme
                                                     through the FAA at
                                                     the address
                                                     specified in
                                                     paragraph (f) of
                                                     this AD.

[[Page 45651]]

 
(3) Report any cracks found   Upon completion of    Fill out the
 during the initial            the initial           compliance form in
 inspection required in        inspection required   SOCATA Service
 paragraph (d)(1) of this AD   in paragraph (d)(1)   Bulletin SB 10-114
 to the FAA with a copy to     of this AD.           55, dated September
 SOCATA. Information                                 2000. Send it to
 collection requirements                             the FAA at the
 contained in this                                   address specified
 regulation have been                                in paragraph (f) of
 approved by the Office of                           this AD. Send a
 Management and Budget (OMB)                         copy to SOCATA at
 under the provisions of the                         the address in
 Paperwork Reduction Act of                          paragraph (h) of
 1980 (44 U.S.C. 3501 et                             this AD.
 seq.) and have been
 assigned OMB Control Number
 2120-0056.
------------------------------------------------------------------------

    (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, Small Airplane Directorate, approves your 
alternative. Submit your request through an FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Small Airplane Directorate.

    Note 1: 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 Karl Schletzbaum, 
Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, 
Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; 
facsimile: (816) 329-4090.
    (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 obtain copies of the documents referenced in this AD from 
SOCATA Groupe AEROSPATIALE, Customer Support, Aerodrome Tarbes-
Ossun-Lourdes, BP 930--F65009 Tarbes Cedex, France; or the Product 
Support Manager, SOCATA--Groupe AEROSPATIALE, North Perry Airport, 
7501 Pembroke Road, Pembroke Pines, Florida 33023. You may examine 
these documents at FAA, Central Region, Office of the Regional 
Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.


    Note 2: The subject of this AD is addressed in French AD Number 
2001-002(A), dated January 10, 2001.


    Issued in Kansas City, Missouri, on August 22, 2001.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-21754 Filed 8-28-01; 8:45 am]
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