[Federal Register Volume 63, Number 74 (Friday, April 17, 1998)]
[Rules and Regulations]
[Pages 19178-19180]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-10057]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-CE-71-AD; Amendment 39-10470; AD 98-08-21]
RIN 2120-AA64


Airworthiness Directives; SOCATA-Groupe AEROSPATIALE Models TB10 
and TB200 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 SOCATA-Groupe AEROSPATIALE (Socata) Models TB10 and 
TB200 airplanes. This AD requires inspecting the wing rear attachment 
fittings for cracks, replacing any cracked fitting, and incorporating 
wing rear attachment fitting reinforcement kits. This AD is the result 
of mandatory continued airworthiness information (MCAI) issued by the 
airworthiness authority for France. The actions specified by this AD 
are intended to prevent structural failure of the wing rear attachment 
fittings caused by cracks in this area, which could result in the wing 
separating from the airplane if the airplane is operated with cracked 
wing rear attachment fittings over an extended period of time.

DATES: Effective June 3, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 3, 1998.

ADDRESSES: Service information that applies to this AD may be obtained 
from the SOCATA-Groupe AEROSPATIALE, Socata Product Support, Aeroport 
Tarbes-Ossun-Lourdes, B P 930, 65009 Tarbes Cedex, France; telephone: 
62.41.74.26; facsimile: 62.41.74.32; or the Product Support Manager, 
SOCATA Aircraft-Groupe AEROSPATIALE, North Perry Airport, 7501 Pembroke 
Road, Pembroke Pines, Florida 33023; telephone: (954) 893-1160; 
facsimile: (954) 964-4141. This information may also be examined at the 
Federal Aviation Administration (FAA), Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 95-CE-71-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. Karl Schletzbaum, Aerospace 
Engineer, FAA, Small Airplane Directorate, 1201 Walnut Street, suite 
900, Kansas City, Missouri 64106; telephone: (816) 426-6934; facsimile: 
(816) 426-2169.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This AD

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to certain Socata Models 
TB10 and TB200 airplanes was published in the Federal Register as a 
notice of proposed rulemaking (NPRM) on December 16, 1997 (62 FR 
65768). The NPRM proposed to require inspecting the wing rear 
attachment fittings for cracks, replacing any cracked fitting, and 
incorporating wing rear attachment fitting reinforcement kits. 
Accomplishment of the proposed action as specified in the NPRM would be 
in accordance with Socata Service Bulletin No. SB 10-082-57, Amdt. 1, 
dated April 1996. Accomplishment of the proposed reinforcement kits 
would be in accordance with the technical instructions included with 
each kit.
    The NPRM was the result of mandatory continued airworthiness 
information (MCAI) issued by the airworthiness authority for France.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the four comments received from one commenter.

Comment No. 1: Allow for Repetitive Inspections Instead of 
Mandatory Replacement

    The commenter suggests that the proposal incorporate Socata Service 
Bulletin SB 10-082-57, Amendment 1, as written. This service bulletin 
allows for repetitive inspections of the wing rear attachment fitting 
rather than replacement.
    The FAA does not concur. The FAA's policy is to provide corrective 
action, when available, that will eliminate the need for repetitive 
inspections. The FAA has determined that long-term operational safety 
will be better assured by design changes that remove the source of the 
problem, rather than by repetitive inspections or other special 
procedures. Therefore, since a design change exists for the wing rear 
attachment fittings that eliminates the need for repetitive 
inspections, no changes to the final rule are necessary as a result of 
this comment.

Comment No. 2: The FAA Has Exaggerated the Severity of the Unsafe 
Condition

    The commenter believes the FAA has exaggerated the severity of the 
unsafe condition with the statement ``* * * which could result in a 
wing separating from the airplane with consequent loss of control of 
the airplane.'' The commenter states that the Models TB10 and TB200 
airplanes, even without the wing rear attachment fittings, resist the 
ultimate flight loads throughout the flight envelope, and that the wing 
rear attachment fittings on these airplanes resist the ultimate landing 
loads up to a weight of 1,092 kilograms.
    The FAA partially concurs. The FAA infers that the commenter does 
not believe that the wing rear attachment fittings are considered 
primary structure since the commenter states that the design of the 
airplane is such that this area resists ultimate flight and landing 
loads. In this area, the FAA does not concur, and has determined that 
the wing rear attachment fittings are ultimate flight and landing load 
bearing areas and considers the wing rear attachment fittings primary 
structure.
    The FAA does concur that the statement of the wing separating from 
the airplane with consequent loss of control of the airplane could be 
considered extreme. Wing separation would only occur after continued 
operation over a long period of time. The FAA will change the above 
statement that the commenter believes is exaggerated to read: ``* * * 
which could result in the wing separating from the airplane if the 
airplane is operated with cracked wing rear attachment fittings over an 
extended period of time.''

Comment No. 3: Incorrect Formula for Converting Hours Time-in-
Service Into Landings

    The commenter states that the AD contains the wrong formula for 
converting hours time-in-service (TIS) into landings for the conditions 
of the proposed AD. The commenter states that hours TIS should be 
multiplied by 1.5 to obtain the number of landings, instead of divided 
by 1.5 (multiplied by .67).

[[Page 19179]]

    The FAA concurs and has changed the final rule accordingly.

Comment No. 4: No Justification To Require Kit Incorporation Prior 
to Further Flight on Wing Rear Attachment Fittings Not Found 
Cracked

    The commenter believes that there is no justification for requiring 
the incorporation of Socata Kit OPT 10 920300 prior to further flight, 
as is presented in the AD.
    The FAA concurs that mandating the incorporation of this kit prior 
to further flight after the effective date of the AD would be 
unjustified. However, the FAA's intent is to require the incorporation 
of this kit prior to further flight after the inspection required by 
the AD. This inspection compliance time is stated as ``upon 
accumulating 3,000 landings on each wing rear attachment fitting (total 
of four; two per wing) or within the next 75 landings after the 
effective date of this AD, whichever occurs later.'' The FAA will 
change the kit incorporation compliance time to read ``prior to further 
flight after the inspection required by paragraph (a) of this AD'' to 
eliminate any confusion.

The FAA's Determination

    After careful review of all available information related to the 
subject presented above, the FAA has determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
the changes described above and minor editorial corrections. The FAA 
has determined that these changes and minor corrections will not change 
the meaning of the AD and will not add any additional burden upon the 
public than was already proposed.

Cost Impact

    The FAA estimates that 71 airplanes in the U.S. registry will be 
affected by this AD. Accomplishing the actions of this AD (both the 
inspection and incorporation of the reinforcement kits) will take 
approximately 11 workhours per airplane (3 workhours for the inspection 
of all four wing rear attachment fitting areas, and 2 workhours to 
incorporate the reinforcement kit at each of the four wing rear 
attachment fitting areas), at an average labor rate of approximately 
$60 an hour. Parts to accomplish this AD cost approximately $200 per 
airplane ($50 per kit X 4 kits). Based on these figures, the total cost 
impact of this AD on U.S. operators is estimated to be $61,060, or $860 
per airplane.

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.
    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, 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:

98-08-21  Socata--Groupe Aerospatiale: Amendment 39-10470; Docket 
No. 95-CE-71-AD.

    Applicability: Models TB10 and TB200 airplanes, serial numbers 
804; 807; 808; 816 through 819; 823 through 1701; 1707 through 1733; 
and 1737 through 1761, 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 (c) 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.
    To prevent structural failure of the wing rear attachment 
fittings caused by cracks in this area, which could result in the 
wing separating from the airplane if the airplane is operated with 
cracked wing rear attachment fittings over an extended period of 
time, accomplish the following:

    Note 2: The compliance times of this AD are presented in 
landings instead of hours time-in-service (TIS). If the number of 
landings is unknown, hours TIS may be used by multiplying the number 
of hours TIS by 1.5.
    Note 3: The paragraph structure of this AD is as follows:

Level 1: (a), (b), (c), etc.
Level 2: (1), (2), (3), etc.
Level 3: (i), (ii), (iii), etc.

Level 2 and Level 3 structures are designations of the Level 1 
paragraph they immediately follow.

    (a) Upon accumulating 3,000 landings on each wing rear 
attachment fitting (total of four; two per wing) or within the next 
75 landings after the effective date of this AD, whichever occurs 
later, inspect the wing rear attachment fittings for cracks in 
accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Socata 
Service Bulletin (SB) No. SB 10-082-57, Amdt. 1, dated April 1996.
    (1) If any fitting is found cracked on the wing side, prior to 
further flight after the inspection required by paragraph (a) of 
this AD, replace the cracked fitting and incorporate wing rear 
attachment fitting reinforcement kit No. OPT10 920300 in accordance 
with the Technical Instruction of Modification, OPT10 9203-57, Wing 
Rear Attachment Bracket, dated April 1996.
    (2) If any fitting is found cracked on the fuselage side, prior 
to further flight after the inspection required by paragraph (a) of 
this AD, accomplish the following:
    (i) Incorporate wing rear attachment fitting reinforcement kit 
No. OPT10 920500 in accordance with the Technical Instruction of 
Modification, OPT10 9205-57, Wing Rear Attachment Rod, dated April 
1996; and
    (ii) Incorporate wing rear attachment fitting reinforcement kit 
No. OPT10 920300 in accordance with the Technical Instruction of 
Modification, OPT10 9203-57, Wing Rear Attachment Bracket, dated 
April 1996.
    (3) If any fitting is not found cracked, prior to further flight 
after the inspection required by paragraph (a) of this AD, 
incorporate wing rear attachment fitting reinforcement kit No. OPT10 
920300 in accordance with the Technical Instruction of Modification, 
OPT10 9203-57, Wing Rear Attachment Bracket, dated April 1996.

[[Page 19180]]

    (b) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.
    (c) An alternative method of compliance or adjustment of the 
compliance times that provides an equivalent level of safety may be 
approved by the Manager, Small Airplane Directorate, FAA, 1201 
Walnut, suite 900, Kansas City, Missouri 64106. The request shall be 
forwarded through an appropriate FAA Maintenance Inspector, who may 
add comments and then send it to the Manager, Small Airplane 
Directorate.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Small Airplane Directorate.

    (d) Questions or technical information related to the service 
information referenced in this AD should be directed to SOCATA--
Groupe AEROSPATIALE, Socata Product Support, Aeroport Tarbes-Ossun-
Lourdes, B P 930, 65009 Tarbes Cedex, France; telephone: 
62.41.74.26; facsimile: 62.41.74.32; or the Product Support Manager, 
SOCATA--Groupe AEROSPATIALE, North Perry Airport, 7501 Pembroke 
Road, Pembroke Pines, Florida 33023; telephone: (954) 964-6877; 
facsimile: (954) 964-1668. This service information may be examined 
at the FAA, Central Region, Office of the Regional Counsel, Room 
1558, 601 E. 12th Street, Kansas City, Missouri.
    (e) The inspection required by this AD shall be done in 
accordance with Socata Service Bulletin No. SB 10-082-57, Amdt. 1, 
dated April 1996. The replacements and modifications required by 
this AD shall be done in accordance with the Technical Instruction 
of Modification, OPT10 9203-57, Wing Rear Attachment Bracket, dated 
April 1996; and the Technical Instruction of Modification, OPT10 
9205-57, Wing Rear Attachment Rod, dated April 1996. 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 SOCATA--Groupe AEROSPATIALE, Socata 
Product Support, Aeroport Tarbes-Ossun-Lourdes, B P 930, 65009 
Tarbes Cedex, France; Product Support Manager, SOCATA Aircraft--
Groupe AEROSPATIALE, North Perry Airport, 7501 Pembroke Road, 
Pembroke Pines, Florida 33023. 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.

    Note 5: The subject of this AD is addressed in French AD 94-
249(A)R1, dated June 19, 1996.

    (f) This amendment becomes effective on June 3, 1998.

    Issued in Kansas City, Missouri, on April 8, 1998.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-10057 Filed 4-16-98; 8:45 am]
BILLING CODE 4910-13-U