AD 2001-23-04

[Federal Register Volume 66, Number 223 (Monday, November 19, 2001)]
[Rules and Regulations]
[Pages 57857-57859]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-28333]



[[Page 57857]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-01-AD; Amendment 39-12501; AD 2001-23-04]
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: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to all SOCATA--Groupe Aerospatiale (SOCATA) Models TB 9, TB 10, 
TB 20, TB 21, and TB 200 airplanes. This AD requires you to 
repetitively inspect the lower rudder hinge fitting for cracks. This AD 
also requires you to repair any crack found in accordance with a repair 
scheme obtained from the manufacturer through the Federal Aviation 
Administration (FAA). This AD is the result mandatory continuing 
airworthiness information (MCAI) issued by the airworthiness authority 
for France. 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.

DATES: This AD becomes effective on January 4, 2002.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of 
January 4, 2002.

ADDRESSES: You may get the service information referenced in this AD 
from SOCATA Groupe Aerospatiale, Customer Support, Aerodrome Tarbes-
Ossun-Lourdes, BP 930--F65009 Tarbes Cedex, France; telephone: (33) 
(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. You may view this information at the 
Federal Aviation Administration (FAA), Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2001-CE-01-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: 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:

Discussion

    What events have caused this 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 Model 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 is the potential impact if FAA took no action? 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.
    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 all SOCATA Models TB 9, TB 10, TB 20, 
TB 21, and TB 200 airplanes. This proposal was published in the Federal 
Register as a notice of proposed rulemaking (NPRM) on August 29, 2001 
(66 FR 45648). The NPRM proposed to 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 FAA.
    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.

Cost Impact

    How many airplanes does this AD impact? We estimate that this AD 
affects 239 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:

----------------------------------------------------------------------------------------------------------------
                                                                             Total cost per   Total cost on U.S.
               Labor cost                            Parts cost                 airplane          operators
----------------------------------------------------------------------------------------------------------------
3 workhours  x  $60 per hour = $180.....  No parts required to perform the            $180        $180  x  239 =
                                           inspection.                                                  $43,020.
----------------------------------------------------------------------------------------------------------------

    We have no method of determining the number of repetitive 
inspections each owner/operator will 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 will be required based on the results of the inspections. We have 
no way of determining the number of repairs each owner/operator will 
incur over the life of each of the affected airplanes based on the 
results of the inspections.

[[Page 57858]]



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

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:

2001-23-04  Socata--Groupe Aerospatiale: Amendment 39-12501; Docket 
No. 2001-CE-01-AD.

    (a) What airplanes are affected by this AD? This AD affects the 
following Model 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-  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 January     September 2000, and
                               4, 2002 (the          the applicable
                               effective date of     aircraft
                               this AD), whichever   maintenance manual.
                               occurs later, and
                               thereafter at
                               intervals not to
                               exceed 12 calendar
                               months.
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(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 the
 (d)(1) of this AD,            in paragraph (d)(1)   SOCATA Groupe
 accomplish the following:     of this AD.           AEROSPATIALE,
 (i) Obtain a repair scheme                          Customer Support,
 from the manufacturer                               Aerodrome Tarbes-
 through the FAA at the                              Ossun-Lourdes, BP
 address specified in                                930-F65009 Tarbes
 paragraph (f) of this AD;                           Cedex, France;
 and (ii) Incorporate this                           telephone: (33)
 repair scheme.                                      05.62.41.76.68;
                                                     facsimile: (33)
                                                     06.07.32.62.24; or
                                                     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.
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(3) Report any cracks found   Within 10 days after  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-
 to the FAA with a copy to     of this AD or         11455, dated
 SOCATA. Information           within 10 days        September 2000.
 collection requirements       after the effective   Send it to the FAA
 contained in this             date of this AD,      at the address
 regulation have been          whichever occurs      specified in
 approved by the Office of     later.                paragraph (f) of
 Management and Budget (OMB)                         this AD. Send a
 under the provisions of the                         copy to SOCATA at
 Paperwork Reduction Act of                          the address in
 1980 (44 U.S.C. 3501 et.                            paragraph (h) of
 seq.) and have been                                 this AD.
 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,

[[Page 57859]]

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) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with SOCATA Service Bulletin SB 10-114-55, dated September 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 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 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 January 4, 2002.

    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 November 5, 2001.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 01-28333 Filed 11-16-01; 8:45 am]
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