[Federal Register Volume 62, Number 241 (Tuesday, December 16, 1997)]
[Proposed Rules]
[Pages 65768-65770]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-32727]


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Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

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Federal Register / Vol. 62, No. 241 / Tuesday, December 16, 1997 / 
Proposed Rules

[[Page 65768]]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-CE-71-AD]
RIN 2120-AA64


Airworthiness Directives; SOCATA-Groupe AEROSPATIALE Models 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 TB10 and TB200 airplanes. The proposed AD would require 
inspecting the wing rear attachment fittings for cracks, replacing any 
cracked fitting, and incorporating wing rear attachment fitting 
reinforcement kits. The proposed AD is the result of mandatory 
continued 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 rear attachment 
fittings caused by cracks in this area, which could result in a wing 
separating from the airplane with consequent loss of control of the 
airplane.

DATES: Comments must be received on or before January 11, 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-71-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 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-71-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-71-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 TB10 and TB200 
airplanes. The DGAC reports three incidents of cracks on the wing rear 
attachment fittings and one incident of rear wing attachment fitting 
deformation. These conditions, if not detected and corrected, could 
result in a wing separating from the airplane with consequent loss of 
control of the airplane.

Relevant Service Information

    Socata has issued Service Bulletin No. SB 10-082, Amdt. 1, dated 
April 1996, which specifies procedures for inspecting the wing rear 
attachment fittings for cracks. Also included in this service bulletin 
is reference to wing rear attachment fitting reinforcement kits that 
should be incorporated on the Socata Models TB10 and TB200 airplanes. 
The procedures for incorporating these reinforcement kits are in the 
technical instructions included with each kit.
    The DGAC classified this service bulletin as mandatory and issued 
French AD 94-249(A)R1, 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.

[[Page 65769]]

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 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 wing rear 
attachment fittings for cracks, replacing any cracked fitting, and 
incorporating wing rear attachment fitting reinforcement kits. 
Accomplishment of the proposed inspections would be in accordance with 
Socata Service Bulletin No. SB 10-082, Amdt. 1, dated April 1996. 
Accomplishment of the proposed reinforcement kits would be in 
accordance with the technical instructions included with each kit.

Differences Between the French AD, the Service Bulletin, and This 
Proposed AD

    French AD 94-249(A)R1, dated June 19, 1996, and Socata Service 
Bulletin No. SB 10-082, Amdt. 1, dated April 1996, both give the 
owners/operators of certain Models TB10 and TB200 airplanes the option 
of accomplishing one of the following if no cracks are found during the 
inspections:

--Incorporating the wing rear attachment fitting reinforcement kit No. 
OPT10 920300; or
--Reinspecting at certain intervals until cracks are found at which 
time the incorporation of a wing rear attachment fitting reinforcement 
kit would be mandatory.

    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 wing rear attachment fitting 
reinforcement kit No. OPT10 920300 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 incorporation 
of two of these kits on each wing.

Cost Impact

    The FAA estimates that 71 airplanes in the U.S. registry would be 
affected by the proposed AD.
    Accomplishing the actions of the proposed AD (both the inspection 
and incorporation of the reinforcement kits) would 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 the proposed AD cost approximately $200 per airplane ($50 
per kit  x  4 kits). Based on these figures, the total cost impact of 
the proposed initial inspection on U.S. operators is estimated to be 
$61,060 or $860 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 USC 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-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 rear wing attachment 
fittings caused by cracks in this area, which could result in a wing 
separating from the airplane with consequent loss of control of the 
airplane, 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) 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, mdt. 1, dated April 1996.
    (1) If any fitting is found cracked on the wing side, prior to 
further flight, 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, accomplish the following:
    (i) Incorporate wing rear attachment fitting reinforcement kit 
No. OPT10 920500 in accordance with the Technical Instruction of

[[Page 65770]]

Modification, OPT10 9205-57, Wing Rear Attachment Bracket, dated 
April 1996; and
    (ii) Incorporate wing rear attachment fitting reinforcement kit 
No. OPT10 920300 in accordance with the Technical Instruction of 
Modification, OPT109203-57, Wing Rear Attachment Bracket, dated 
April 1996.
    (3) If any fitting is not found cracked, prior to further 
flight, incorporate wing rear attachment fitting reinforcement kit 
No. OPT10 920300 in accordance with the Technical Instruction of 
Modification, OPT109203-57, Wing Rear Attachment Bracket, dated 
April 1996.
    (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 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.

    (d) All persons affected by this directive may obtain copies of 
the documents referred to herein upon request to Socata--Groupe 
Aerospatiale, Socata Product Support, Aeroport Tarbes-Ossun-Lourdes, 
B P 930, 65009 Tarbes Cedex, France; or Perry Airport, 7501 Pembroke 
Road, Pembroke Pines, Florida 33023. These documents may also be 
examined at the FAA, Central Region, Office of the Regional Counsel, 
Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.

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

    Issued in Kansas City, Missouri, on December 10, 1997.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 97-32727 Filed 12-15-97; 8:45 am]
BILLING CODE 4910-13-U