[Federal Register Volume 63, Number 145 (Wednesday, July 29, 1998)]
[Rules and Regulations]
[Pages 40359-40361]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-20080]



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 Rules and Regulations
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  Federal Register / Vol. 63, No. 145 / Wednesday, July 29, 1998 / 
Rules and Regulations  

[[Page 40359]]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-CE-72-AD; Amendment 39-10677; AD 98-16-03]
RIN 2120-AA64


Airworthiness Directives; SOCATA--Groupe AEROSPATIALE Models TB9 
and TB10 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 TB9 and 
TB10 airplanes. This AD requires repetitively inspecting the wing front 
attachments on the wing and fuselage sides for cracks, and repetitively 
incorporating a certain modification kit (type of kit and time of 
incorporation depends on whether cracks are found during the 
inspection). This AD is the result of mandatory continuing 
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 front attachments caused by fatigue 
cracking, which could result in the wing separating from the airplane 
if the airplane is operated with cracked wing front attachments over an 
extended period of time.

DATES: Effective September 21, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 21, 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: 
33-5-62-41-76-52; facsimile: 33-5-62-41-76-54; or the Product Support 
Manager, SOCATA Aircraft, 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-72-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 
TB9 and TB10 airplanes was published in the Federal Register as a 
notice of proposed rulemaking (NPRM) on May 22, 1998 (63 FR 28299). The 
NPRM proposed to require repetitively inspecting the wing front 
attachments on the wing and fuselage sides for cracks, and repetitively 
incorporating a certain modification kit (type of kit and time of 
incorporation depends on whether cracks are found during the 
inspection). Accomplishment of the proposed action as specified in the 
NPRM would be in accordance with Socata Service Bulletin No. SB 10-081-
57, Amendment 1, dated August 1996. Accomplishment of the proposed 
modifications, as applicable, would be required in accordance with the 
Technical Instructions for Modification included with each kit.
    The NPRM was the result of mandatory continuing 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 one comment received.

Comment Disposition

    Socata states that reference to one of the service documents was 
incorrectly referenced in the NPRM. In particular, Socata Technical 
Instruction of Modification OPT 109081-53 was referenced as Socata 
Technical Instruction of Modification OPT 109181-53 in both paragraphs 
(e)(1) and (e)(2) of the AD.
    The FAA concurs that this service document was incorrectly 
referenced. This was inadvertent on the FAA's part. The final rule will 
include the correct reference to this document.

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 
minor editorial corrections. The FAA has determined that these 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 113 airplanes in the U.S. registry will be 
affected by this AD. The initial inspection will take approximately 3 
workhours per airplane to accomplish, at an average labor rate of 
approximately $60 an hour. Based on these figures, the total cost 
impact of this inspection on U.S. operators is estimated to be $20,340, 
or $180 per airplane.
    The initial modifications will take approximately 32 workhours to 
accomplish, at an average labor rate of $60 per hour. Parts cost 
approximately $1,125 per airplane. Based on these figures, the total 
cost impact of the initial modifications on U.S. operators is estimated 
to be $344,085, or $3,045 per airplane.
    These figures only take into account the costs of the initial 
inspection and initial modifications. The FAA has no way of determining 
the number of repetitive inspections and modifications each owner/
operator of the affected airplanes will incur.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects on the States, on the relationship between the

[[Page 40360]]

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:

    98-16-03  Socata--Groupe Aerospatiale: Amendment 39-10677; 
Docket No. 95-CE-72-AD.
    Applicability: The following airplane models and serial numbers, 
certificated in any category:
    Model TB9, serial numbers 1 through 9999; and
    Model TB10, serial numbers 1 through 803, 805, 806, 809 through 
815, 820, 821, and 822.

    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 (g) 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 front attachments 
caused by fatigue cracking, which could result in the wing 
separating from the airplane if the airplane is operated with 
cracked wing front attachments 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.

    (a) For all affected airplanes, upon accumulating 3,000 landings 
on the wing front attachments or within the next 100 landings after 
the effective date of this AD, whichever occurs later, and 
thereafter at intervals not to exceed 3,000 landings, inspect the 
wing front attachments (both the wing sides and fuselage sides) in 
accordance with Socata Service Bulletin No. SB 10-081-57, Amendment 
1, dated August 1996.
    (b) For all affected airplanes, accomplish the following on the 
wing front attachments on the wing sides:
    (1) If no cracks are found on the wing front attachments on the 
wing sides during any inspection required by paragraph (a) of this 
AD, upon accumulating 12,000 landings on these wing front 
attachments or within the next 100 landings after the effective date 
of this AD, whichever occurs later, and thereafter at intervals not 
to exceed 6,000 landings provided no cracks are found during any 
inspection required by paragraph (a) of this AD, incorporate 
Modification Kit OPT10 911000 in accordance with Socata Technical 
Instruction No. 9110, which incorporates the following pages:

----------------------------------------------------------------------------------------------------------------
                   Pages                           Revision level                          Date                 
----------------------------------------------------------------------------------------------------------------
0 and 1...................................  Amendment 1................  January 31, 1992.                      
2 through 11..............................  Original Issue.............  October 1985.                          
----------------------------------------------------------------------------------------------------------------

    (2) If a crack(s) is found on the wing front attachments on the 
wing sides during any inspection required by paragraph (a) of this 
AD, prior to further flight, incorporate Modification Kit OPT10 
911000 in accordance with Socata Technical Instruction No. 9110. 
Incorporate this kit at intervals not to exceed 6,000 landings 
thereafter provided no cracks are found during any inspection 
required by paragraph (a) of this AD.
    (c) For Models TB9 and TB10 airplanes, with a serial number in 
the range of 1 through 399, or with a serial number of 413; that do 
not have either Socata Service Letter (SL) 10-14 incorporated or 
Socata Modification Kit OPT10 908100 incorporated, accomplish the 
following on the wing front attachments on the fuselage sides:
    (1) If no cracks are found on the wing front attachments on the 
fuselage sides during any inspection required by paragraph (a) of 
this AD, upon accumulating 6,000 landings on these wing front 
attachments or within the next 100 landings after the effective date 
of this AD, whichever occurs later, and thereafter at intervals not 
to exceed 12,000 landings provided no cracks are found during any 
inspection required by paragraph (a) of this AD, incorporate 
Modification Kit OPT10 919800 in accordance with Socata Technical 
Instruction of Modification OPT10 9198-53, dated October 1994.
    (2) If a crack(s) is found on the wing front attachments on the 
fuselage sides during any inspection required by paragraph (a) of 
this AD, prior to further flight, incorporate Modification Kit OPT10 
919800 in accordance with Socata Technical Instruction of 
Modification OPT10 9198-53, dated October 1994. Incorporate this kit 
at intervals not to exceed 12,000 landings thereafter provided no 
cracks are found during any inspection required by paragraph (a) of 
this AD.
    (d) For Models TB9 and TB10 airplanes, with a serial number in 
the range of 1 through 399, or with a serial number of 413; that 
have either Socata Service Letter (SL) 10-14 incorporated or Socata 
Modification Kit OPT10 908100 incorporated, accomplish the following 
on the wing front attachments on the fuselage sides:
    (1) If no cracks are found on the wing front attachments on the 
fuselage sides during any inspection required by paragraph (a) of 
this AD, upon accumulating 12,000 landings on these wing front 
attachments or within the next 100 landings after the effective date 
of this AD, whichever occurs later, and thereafter at intervals not 
to exceed 12,000 landings provided no cracks are found during any 
inspection required by paragraph (a) of this AD, incorporate 
Modification Kit OPT10 919800 in accordance with Socata Technical 
Instruction of Modification OPT10 9198-53, dated October 1994.
    (2) If a crack(s) is found on the wing front attachments on the 
fuselage sides during any inspection required by paragraph (a) of 
this AD, prior to further flight, incorporate Modification Kit OPT10 
919800 in accordance with Socata Technical Instruction of 
Modification OPT10 9198-53, dated October 1994. Incorporate this kit 
at intervals not to exceed 12,000 landings thereafter provided no 
cracks are found during any

[[Page 40361]]

inspection required by paragraph (a) of this AD.
    (e) For Models TB9 and TB10 airplanes, with a serial number in 
the range of 400 through 412, or with a serial number in the range 
of 414 through 9999; accomplish the following on the wing front 
attachments on the fuselage sides:
    (1) If no cracks are found on the wing front attachments on the 
fuselage sides during any inspection required by paragraph (a) of 
this AD, upon accumulating 12,000 landings on these wing front 
attachments or within the next 100 landings after the effective date 
of this AD, whichever occurs later, and thereafter at intervals not 
to exceed 12,000 landings provided no cracks are found during any 
inspection required by paragraph (a) of this AD, incorporate 
Modification Kit OPT10 908100 in accordance with Socata Technical 
Instruction of Modification OPT10 9081-53, Amendment 2, dated 
October 1994.
    (2) If a crack(s) is found on the wing front attachments on the 
fuselage sides during any inspection required by paragraph (a) of 
this AD, prior to further flight, incorporate Modification Kit OPT10 
908100 in accordance with Socata Technical Instruction of 
Modification OPT10 9081-53, Amendment 2, dated October 1994. 
Incorporate this kit at intervals not to exceed 12,000 landings 
thereafter provided no cracks are found during any inspection 
required by paragraph (a) of this AD.

    Note 3: ``Unless already accomplished'' credit may be used if 
the kits that are required by paragraphs (c)(1), (d)(1), and (e)(1) 
of this AD are already incorporated on the applicable airplanes. As 
specified in the AD, repetitive incorporation of these kits would 
still be required at intervals not to exceed 12,000 landings 
provided no cracks are found.

    (f) 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.
    (g) An alternative method of compliance or adjustment of the 
initial or repetitive 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.

    (h) Questions or technical information related to the service 
information referenced in this AD should be directed to the SOCATA--
Groupe AEROSPATIALE, Socata Product Support, Aeroport Tarbes-Ossun-
Lourdes, B P 930, 65009 Tarbes Cedex, France; telephone: 33-5-62-41-
76-52; facsimile: 33-5-62-41-76-54; or the Product Support Manager, 
SOCATA Aircraft, North Perry Airport, 7501 Pembroke Road, Pembroke 
Pines, Florida 33023; telephone: (954) 893-1400; facsimile: (954) 
964-1402. 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.
    (i) The inspections required by this AD shall be done in 
accordance with Socata Service Bulletin No. SB 10-081-57, Amendment 
1, dated August 1996. The modifications required by this AD shall be 
done in accordance with Socata Technical Instruction of Modification 
OPT10 9198-53, dated October 1994; Socata Technical Instruction of 
Modification OPT10 9081-53, Amendment 2, dated October 1994; and 
Socata Technical Instruction No. 9110, which incorporates the 
following pages:

----------------------------------------------------------------------------------------------------------------
                   Pages                           Revision level                          Date                 
----------------------------------------------------------------------------------------------------------------
0 and 1...................................  Amendment 1................  January 31, 1992.                      
2 through 11..............................  Original Issue.............  October 1985.                          
----------------------------------------------------------------------------------------------------------------

    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 or the Product Support Manager, SOCATA 
Aircraft, 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-
264(A), dated December 7, 1994.

    (j) This amendment becomes effective on September 21, 1998.

    Issued in Kansas City, Missouri, on July 21, 1998.
Brian A. Hancock,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-20080 Filed 7-28-98; 8:45 am]
BILLING CODE 4910-13-U