[Federal Register Volume 62, Number 247 (Wednesday, December 24, 1997)]
[Proposed Rules]
[Pages 67300-67302]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-33511]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-CE-70-AD]
RIN 2120-AA64
Airworthiness Directives; Socata--Groupe Aerospatiale Models TB9,
TB10, and TB200 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, TB10, and TB200 airplanes. The proposed AD would require
inspecting the main landing gear (MLG) support ribs for cracks,
replacing MLG support ribs that have cracks beyond a certain level, and
incorporating a certain MLG support rib reinforcement kit. 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 MLG failure caused
by cracks in the support ribs, which could result in loss of control of
the airplane during landing operations.
DATES: Comments must be received on or before January 26, 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-70-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:
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 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
[[Page 67301]]
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-70-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-70-AD, Room 1558, 601 E. 12th Street, Kansas
City, Missouri 64106.
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 certain Socata Models TB9, TB10, and
TB200 airplanes. The DGAC reports several incidents of the main landing
gear (MLG) support ribs cracking on the above-referenced airplanes.
These conditions, if not detected and corrected, could result in MLG
failure with consequent loss of control of the airplane during landing
operations.
Relevant Service Information
Socata has issued Service Bulletin No. SB 10-085, Amdt. 2, dated
April 1996, which specifies procedures for inspecting the MLG support
ribs for cracks. Also included in this service bulletin is reference to
certain MLG support rib reinforcement kits that should be incorporated
on the Socata Models TB9, TB10, and TB200 airplanes, depending on the
inspection results. The procedures for incorporating the modification
kits are either in the technical instructions included with the kit or
the maintenance manual.
The DGAC classified this service bulletin as mandatory and issued
DGAC AD 94-265(A)R4, dated June 19, 1996, 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
section 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, TB10, and TB200 airplanes
of the same type design registered in the United States, the FAA is
proposing AD action. The proposed AD would require inspecting the MLG
support ribs for cracks, replacing any MLG support ribs that have
cracks beyond a certain level, and incorporating a certain MLG support
rib reinforcement kit if cracks beyond a certain level are not found.
Accomplishment of the proposed inspections would be in accordance with
Socata Service Bulletin No. SB 10-085, Amdt. 2, dated April 1996.
Accomplishment of the proposed kit modifications, as applicable, would
be in accordance with either the technical instructions included with
the kit or the maintenance manual.
Differences Between the French AD, the Service Bulletin, and This
Proposed AD
French AD 94-265(A)R4, dated June 19, 1996, and Socata Service
Bulletin No. SB 10-085, Amdt. 2, dated April 1996, both give the
owners/operators of certain Models TB10 and TB200 airplanes the option
of incorporating a MLG support rib reinforcement kit or repetitively
inspecting if no cracks are found in the MLG support ribs during the
initial inspection.
The FAA's policy is to provide corrective action 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.
Because the incorporation of the applicable MLG support rib
reinforcement kit on the affected airplanes eliminates the need for
repetitive inspections, the proposed AD differs from the service
bulletin and French AD in that it would mandate eventual incorporation
of the applicable MLG support rib reinforcement kit.
Cost Impact
The FAA estimates that 146 airplanes in the U.S. registry would be
affected by the proposed AD.
Accomplishing the proposed inspection would take approximately 1
workhour per airplane, 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 $8,760, or $60 per
airplane.
The proposed modification would take approximately 1 workhour to
incorporate the applicable kits on each wing (total of 2 workhours), at
an average labor rate of $60 per hour. Parts cost approximately $1,200
per airplane ($300 per kit; 2 kits per wing x 2 wings per airplane).
Based on these figures, the total cost impact of the proposed
modification on U.S. operators is estimated to be $192,720 or $1,320
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.
[[Page 67302]]
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-70-AD.
Applicability: Models TB9, TB10, and TB200 airplanes, serial
numbers 1 through 9999, 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 (d) 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 main landing gear (MLG) failure caused by cracks in
the support ribs, which could result in loss of control of the
airplane during landing operations, 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 0.67.
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) For TB9, serial numbers (S/N) 1 through 1442 and 1444
through 1574; and TB10,
S/N 1 through 803; 805; 806; 809 through 815; 820; 821; and 822,
airplanes that are not equipped with either wing rib reinforcement
kit No. OPT10910800 (TB9 and TB10 airplanes) or do not have
reinforced ribs (TB10 airplanes), part number (P/N) TB10 11008001
and P/N TB10 11008002, accomplish the following:
(1) Upon accumulating 1,500 landings on the MLG support ribs or
within the next 75 landings after the effective date of this AD,
whichever occurs later, inspect the MLG support ribs for cracks at
all four locations (two per wing) in accordance with the
ACCOMPLISHMENT INSTRUCTIONS section of Socata Service Bulletin No.
SB 10-085, Amdt. 2, dated April 1996.
(2) If any cracks are found that are out of the tolerances
specified in the maintenance manual, prior to further flight,
replace the ribs with reinforced ribs, P/N TB10 11008001 and P/N
TB10 11008002. Accomplish the replacement in accordance with the
maintenance manual.
(3) If any cracks are found that are within the tolerances
specified in the maintenance manual, prior to further flight,
incorporate wing rib reinforcement kit No. OPT10910800 in accordance
with the maintenance manual.
(4) If no cracks are found, upon accumulating 3,000 landings on
the MLG support ribs or within the next 100 landings after the
effective date of this AD, whichever occurs later, incorporate wing
rib reinforcement kit No. OPT10910800 in accordance with the
maintenance manual.
(b) For Models TB10 and TB200 airplanes, S/N 804; 807; 808; 816
through 819; 823 through 1701; 1707 through 1733; and 1737 to 1761,
accomplish the following:
(1) Upon accumulating 6,000 landings on the MLG support ribs or
within the next 75 landings after the effective date of this AD,
whichever occurs later, inspect the MLG support ribs for cracks at
all four locations (two per wing) in accordance with the
ACCOMPLISHMENT INSTRUCTIONS section of Socata Service Bulletin No.
SB 10-085, Amdt. 2, dated April 1996.
(2) At the applicable compliance time presented below,
incorporate wing rib reinforcement kit No. OPT10 920100 in
accordance with the Technical Instruction of Modification, OPT10
9201-57, Reinforcement of the Main Landing Gear Support Ribs, which
incorporates the following pages:
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Pages Revision level Date
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1 and 2.......................... Amendment 1........ April 1996.
3 through 27..................... Original Issue..... November 1995.
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(i) Prior to further flight if any cracks are found.
(ii) Upon accumulating 7,500 landings on the MLG support ribs or
within the next 100 landings after the effective date of this AD,
whichever occurs later, if no cracks are found.
(c) 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.
(d) An alternative method of compliance or adjustment of the
compliance time 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.
(e) 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:
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.
Note 5: The subject of this AD is addressed in French AD 94-
265(A)R4, dated June 19, 1996.
Issued in Kansas City, Missouri, on December 16, 1997.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 97-33511 Filed 12-23-97; 8:45 am]
BILLING CODE 4910-13-U