[Federal Register Volume 63, Number 39 (Friday, February 27, 1998)]
[Rules and Regulations]
[Pages 9926-9928]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-4243]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-CE-70-AD; Amendment 39-10358; AD 98-04-47]
RIN 2120-AA64
Airworthiness Directives; SOCATA--Groupe AEROSPATIALE Models TB9,
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 TB9,
TB10, and TB200 airplanes. This AD requires 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. 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 MLG failure caused by cracks in the support ribs, which could
result in loss of control of the airplane during landing operations.
DATES: Effective April 3, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 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--Groupe AEROSPATIALE, North Perry Airport, 7501 Pembroke Road,
Pembroke Pines, Florida 33023; telephone: (954) 964-
[[Page 9927]]
6877; facsimile: (954) 964-1668. 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-70-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, TB10, and TB200 airplanes was published in the Federal Register as
a notice of proposed rulemaking (NPRM) on December 24, 1997 (62 FR
67300). The NPRM proposed to 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 action as specified in the NPRM would be
in accordance with Socata Service Bulletin No. SB 10-085, Amdt. 2,
dated April 1996. Accomplishment of the kit modifications, as
applicable, would be in accordance with either the technical
instructions included with the kit or the maintenance manual.
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. No comments were received on the
proposed rule or the FAA's determination of the cost to the public.
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 146 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 1 workhour per
airplane to accomplish the required inspection, and that the average
labor rate is approximately $60 an hour. Based on these figures, the
total cost impact of this inspection on U.S. operators is estimated to
be $8,760, or $60 per airplane.
The required modification will take approximately 1 workhour to
incorporate the applicable kits on each wing (total of 2 workhours),
and the average labor rate is approximately $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
this modification on U.S. operators is estimated to be $192,720, or
$1,320 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:
98-04-47 Socata--Groupe Aerospatiale: Amendment 39-10358; 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 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) 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
[[Page 9928]]
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. OPT10 910800 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. OPT10 910800 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............. Apr. 1996.
3 through 27.......... Original Issue.......... Nov. 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 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.
(e) 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.
(f) The inspections required by this AD shall be done in
accordance with Socata Service Bulletin No. SB 10-085, Amdt. 2,
dated April 1996. The modification required by this AD should be
done 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............. Apr. 1996.
3 through 27.......... Original Issue.......... Nov. 1995.
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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--
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-
265(A)R4, dated June 19, 1996.
(g) This amendment (39-10358) becomes effective on April 3,
1998.
Issued in Kansas City, Missouri, on February 11, 1998.
Carolanne L. Cabrini,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-4243 Filed 2-26-98; 8:45 am]
BILLING CODE 4910-13-P