[Federal Register Volume 63, Number 99 (Friday, May 22, 1998)]
[Proposed Rules]
[Pages 28299-28301]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-13653]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-CE-72-AD]
RIN 2120-AA64
Airworthiness Directives; SOCATA--Groupe AEROSPATIALE Models TB9
and TB10 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 certain SOCATA--Groupe AEROSPATIALE (Socata)
Models TB9 and TB10 airplanes. The proposed AD would 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). 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 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: Comments must be received on or before June 25, 1998.
ADDRESSES: Submit comments in triplicate to 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. 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 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 information also may be examined at the Rules
Docket at the address above.
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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report that summarizes each FAA-public contact concerned
with the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 95-CE-72-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the 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.
[[Page 28300]]
Discussion
The Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, recently notified the FAA that an
unsafe condition may exist on all Socata Model TB9 airplanes and
certain Socata Model TB10 airplanes. The DGAC reports 15 cases of
cracks found on the wing front attachments of the referenced airplanes.
This condition, if not detected and corrected in a timely manner,
could result in structural failure of the wing attachment and the wing
separating from the airplane if the airplane is operated with cracked
wing front attachments over an extended period of time.
Relevant Service Information
Socata has issued Service Bulletin No. SB 10-081-57, Amendment 1,
dated August 1996, which specifies procedures for inspecting the wing
front attachments on the wing and fuselage sides for cracks. Also
included in this service bulletin is reference to certain wing front
attachment kits that should be incorporated on the Socata Models TB9
and TB10, depending on the inspection results. The procedures for
incorporating the modification kits are in the Technical Instructions
for Modification included with each kit.
The DGAC classified this service bulletin as mandatory and issued
DGAC AD 94-264(A), dated December 7, 1994, in order to assure the
continued airworthiness of these airplanes in France.
The FAA's Determination
This airplane model is manufactured in France and is 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 the FAA informed of the situation described above. The FAA has
examined the findings of the DGAC; reviewed all available information,
including the service information referenced above; and determined that
AD action is necessary for products of this type design that are
certificated for operation in the United States.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Socata Models TB9 and TB10 airplanes of the
same type design registered in the United States, the FAA is proposing
AD action. The proposed AD would 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 inspections 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.
Cost Impact
The FAA estimates that 113 airplanes in the U.S. registry would be
affected by the proposed AD.
The proposed inspection would 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 the proposed
inspection on U.S. operators is estimated to be $20,340, or $180 per
airplane.
The proposed modification would 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 proposed modifications on U.S. operators is
estimated to be $344,085, or $3,045 per airplane.
Regulatory Impact
The regulations proposed herein would 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
proposal would 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) 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, pursuant to 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. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
Socata--Groupe Aerospatiale: 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,
[[Page 28301]]
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
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0 and 1......................... Amendment......... January 31, 1992.
2 through 11.................... Original Issue.... October 1985.
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(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 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 9181-53, 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 9181-53, 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 aleady 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.
Note 5: The subject of this AD is addressed in French AD 94-
264(A), dated December 7, 1994.
Issued in Kansas City, Missouri, on May 14, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-13653 Filed 5-21-98; 8:45 am]
BILLING CODE 4910-13-P