[Federal Register Volume 63, Number 54 (Friday, March 20, 1998)]
[Rules and Regulations]
[Pages 13512-13514]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-7247]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-SW-51-AD; Amendment 39-10415; AD 98-06-36]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA341G and 
SA342J Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Eurocopter France Model SA341G and SA342J helicopters. 
This action requires inspecting the tail gearbox support tripod 
(support tripod) for cracks. This amendment is prompted by reports of 
cracks that were discovered during routine maintenance inspections. The 
actions specified in this AD are intended to detect cracks at the welds 
of the tail gearbox support tripod, which could cause failure of one or 
more of the tripod arms, subsequent separation of the tail gearbox, and 
loss of control of the helicopter.

DATES: Effective April 6, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 6, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before May 19, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 97-SW-51-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.
    The service information referenced in this AD may be obtained from 
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 
75053-4005, telephone (972) 641-3460, fax (972) 641-3527. This 
information may be examined at the FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or 
at the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr. Shep Blackman, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5296, fax (817) 
222-5961.

SUPPLEMENTARY INFORMATION: 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 Eurocopter 
France Model SA341G and SA342J helicopters. The DGAC advises that 
cracks have been found in the welds of the support tripod, part number 
341A23-1136-00 -01, or -02, and is mandating a visual inspection, and 
if the results of the visual inspection are inconclusive, a dye-
penetrant inspection for cracks.
    Eurocopter France has issued Eurocopter SA 341/342 Service Bulletin 
No. 05.32, dated July 17, 1997, which specifies visual inspections, and 
if there is any doubt about the results of the visual inspection, a 
dye-penetrant inspection, for cracks on the support tripod and 
replacement with an airworthy support tripod if a crack is found. The 
DGAC classified this service bulletin as mandatory and issued AD 97-
144-038(B), dated July 2, 1997, in order to assure the continued 
airworthiness of these helicopters in France.
    This helicopter 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, and determined that AD 
action is necessary for products of this

[[Page 13513]]

type design that are certificated for operation in the United States.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Eurocopter France Model SA341G and SA342J 
helicopters of the same type design registered in the United States, 
this AD is being issued to detect cracks at the welds of the tail 
gearbox support tripod, which could cause failure of one or more of the 
tripod arms, separation of the tail gearbox and subsequent loss of 
control of the helicopter. This AD requires, before further flight, and 
thereafter, prior to the first flight of each day, or at intervals not 
to exceed 10 hours time-in-service, whichever occurs first, visual 
inspections of the support tripod for cracks. If the visual inspections 
indicate potential cracks, a dye-penetrant inspection is required. If a 
crack is found, replacing the support tripod with an airworthy support 
tripod is required. The actions are required to be accomplished in 
accordance with the service bulletin described previously.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability of the helicopter. Therefore, the inspections for 
cracks are required prior to further flight, and this AD must be issued 
immediately.
    The FAA estimates that 24 helicopters of U.S. registry would be 
affected by this AD, that it would take approximately one-half work 
hour to conduct the visual inspection and 9 work hours to replace the 
support tripod, and that the average labor rate is $60 per work hour. 
Required parts would cost approximately $203,304. Based on these 
figures, the total cost impact of this AD on U.S. operators is 
estimated to be $4,892,976, if the support tripod is replaced in all of 
the U.S. fleet.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 97-SW-51-AD.'' The postcard will be date stamped and 
returned to the commenter.
    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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, may be obtained from 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 
to read as follows:

AD 98-06-36  Eurocopter France: Amendment 39-10415. Docket No. 97-
SW-51-AD.

    Applicability: Eurocopter France Model SA341G and SA342J 
helicopters, with tail gearbox support tripods, part number (P/N) 
341A23-1136-00, -01 or -02, installed, certificated in any category.

    Note 1: This AD applies to each helicopter 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 helicopters that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must use the authority 
provided in paragraph (d) to request approval from the FAA. This 
approval may address either no action, if the current configuration 
eliminates the unsafe condition, or different actions necessary to 
address the unsafe condition described in this AD. Such a request 
should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any helicopter from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To detect cracks at the welds of the tail gearbox support 
tripod, which could cause failure of one or more of the tripod arms, 
separation of the tail gearbox, and subsequent loss of control of 
the helicopter, accomplish the following:
    (a) Before further flight, visually inspect the tail gearbox 
support tripod (support tripod), P/N 341A23-1136-00, -01 or -02, for 
cracks in accordance with the Accomplishment Instructions, paragraph 
2(B)(1), of Eurocopter SA 341/342 Service Bulletin No. 05.32, dated 
July 17, 1997; thereafter, conduct this visual inspection prior to 
the first flight of each day, or at intervals not to exceed 10 hours 
time-in-service (TIS), whichever occurs first.

[[Page 13514]]

    (1) If there is any doubt as to whether there is a crack 
present, perform a dye-penetrant inspection in accordance with 
paragraph (2)(B)(1) of the service bulletin.
    (2) If a crack is found, replace the support tripod with an 
airworthy support tripod.

    Note 2: The FAA has requested the DGAC to contact the type 
certificate holder and solicit terminating action that would 
eliminate the recurring inspection requirement of this AD.

    (b) Remove from service any support tripod, P/N 341A23-1136-00, 
-01, or -02, which has accumulated 9,000 or more hours TIS, and 
replace it with an airworthy support tripod.
    (c) This AD revises the Limitation section of the maintenance 
manual by establishing a new retirement life for the support tripod, 
P/N 341A23-1136-00, -01, and -02, of 9,000 hours TIS.
    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Rotorcraft Standards Staff, 
Rotorcraft Directorate, FAA. Operators shall submit their requests 
through an FAA Principal Maintenance Inspector, who may concur or 
comment and then send it to the Manager, Rotorcraft Standards Staff.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Standards Staff.

    (e) 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 helicopter to a location where 
the requirements of this AD can be accomplished.
    (f) The inspections and replacement, if necessary, shall be done 
in accordance with Eurocopter SA 341/342 Service Bulletin No. 05.32, 
dated July 17, 1997. 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 American 
Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 
75053-4005, telephone (972) 641-3460, fax (972) 641-3527. Copies may 
be inspected at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.
    (g) This amendment becomes effective on April 6, 1998.

    Note 4: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 97-144-038(B), dated July 
2, 1997.

    Issued in Fort Worth, Texas, on March 12, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-7247 Filed 3-19-98; 8:45 am]
BILLING CODE 4910-13-P