[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]
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