[Federal Register Volume 63, Number 161 (Thursday, August 20, 1998)]
[Rules and Regulations]
[Pages 44552-44553]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-22365]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-36-AD; Amendment 39-10716; AD 98-16-02]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model SA 3180, SA
318B, SA 318C, SE 3130, SE 313B, SA.315B, SA.316B, SA.316C, SA.319B,
and SE.3160 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This document publishes in the Federal Register an amendment
adopting Airworthiness Directive (AD) 98-16-02 which was sent
previously to all known U.S. owners and operators of Eurocopter France
Model SA 3180, SA 318B, SA 318C, SE 3130, SE 313B, SA.315B, SA.316B,
SA.316C, SA.319B, and SE.3160 helicopters by individual letters. This
AD requires an initial and recurring visual inspections of the upper
and lower surfaces of the tail rotor blade (blade) skin for cracks. If
a crack is found, replacing the blade with an airworthy blade is
required. This amendment is prompted by a report of a crack on the
blade skin near an attachment bolt on the blade cuff stem. This
condition, if not corrected, could result in fatigue failure of a blade
and subsequent loss of control of the helicopter.
DATES: Effective September 4, 1998, to all persons except those persons
to whom it was made immediately effective by priority letter AD 98-16-
02, issued on July 22, 1998, which contained the requirements of this
amendment.
Comments for inclusion in the Rules Docket must be received on or
before October 19, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 98-SW-36-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
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: On July 22, 1998, the FAA issued priority
letter AD 98-16-02, applicable to Eurocopter France Model SA 3180, SA
318B, SA 318C, SE 3130, SE 313B, SA.315B, SA.316B, SA.316C, SA.319B,
and SE.3160 helicopters, which requires, within 10 hours time-in-
service (TIS), and thereafter, at intervals not to exceed 10 hours TIS,
visually inspecting the blade skin near the attachment bolts on the
blade cuff stem for cracks on the upper and lower surfaces using an 8-
power or higher magnifying glass. If a crack is found, replacing the
blade with an airworthy blade is necessary. That action was prompted by
a report of a crack on the lower surface of the blade skin near an
attachment bolt on the blade cuff stem. This condition, if not
corrected, could result in fatigue failure of a blade and subsequent
loss of control of the helicopter.
The FAA has reviewed Eurocopter France Service Telexes No. 05.36,
No. 05.94, and No. 05.95, as transmitted by Information Telex 00068,
dated July 10, 1998, which describes procedures for visually checking
the blade skin for cracks using an 8-power magnifying glass.
These helicopter models are manufactured in France and are 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, and determined that AD
action is necessary for products of these type designs that are
certificated for operation in the United States.
Since the unsafe condition described is likely to exist or develop
on other Eurocopter France Model SA 3180, SA 318B, SA 318C, SE 3130, SE
313B, SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 helicopters of
the same type design, the FAA issued priority letter AD 98-16-02 to
prevent fatigue failure of a blade and subsequent loss of control of
the helicopter. The AD requires, within 10 hours time-in-service (TIS),
and thereafter, at intervals not to exceed 10 hours TIS, visually
inspecting the blade skin near the attachment bolts on the blade cuff
stem for cracks on the upper and lower surfaces using an 8-power or
higher magnifying glass. If a crack is found, replacing the blade with
an airworthy blade is necessary.
Since it was found that immediate corrective action was required,
notice and opportunity for prior public comment thereon were
impracticable and contrary to the public interest, and good cause
existed to make the AD effective immediately by individual letters
issued on July 22, 1998 to all known U.S. owners and operators of
Eurocopter France Model SA 3180, SA 318B, SA 318C, SE 3130, SE 313B,
SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 helicopters. These
conditions still exist, and the AD is hereby published in the Federal
Register as an amendment to section 39.13 of the Federal Aviation
Regulations (14 CFR 39.13) to make it effective to all persons.
The FAA estimates that 106 helicopters of U.S. registry will be
affected by this AD, that it will take approximately 1 work hour per
helicopter to inspect each blade and 3 work hours to replace it, if
necessary, and that the average labor rate is $60 per work hour.
Required parts will cost approximately $8780 per blade. Based on these
figures, the total cost impact of the AD on U.S. operators is estimated
to be $956,120, assuming one blade replacement for each helicopter.
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.
[[Page 44553]]
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. 98-SW-36-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, 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:
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:
98-16-02 Eurocopter France: Amendment 39-10716. Docket No. 98-SW-
36-AD.
Applicability: Model SA 3180, SA 318B, SA 318C, SE 3130, SE
313B, SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 helicopters,
with tail rotor blades, part number (P/N) 3160S-34-10000-all dash
numbers, or P/N 3160S-34-11000-all dash numbers, 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 (b) 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 within 10 hours time-in-service (TIS), and
thereafter at intervals not to exceed 10 hours TIS, unless
accomplished previously.
To prevent fatigue failure of a tail rotor blade (blade), and
subsequent loss of control of the helicopter, accomplish the
following:
(a) With the blade installed on the helicopter:
(1) Clean the blade root skin area using Teepol or an equivalent
product.
(2) Using an 8-power or higher magnifying glass, visually
inspect the blade skin near the attachment bolts on the blade cuff
stem for cracks on the upper and lower surfaces.
(3) If a crack is found, replace the blade with an airworthy
blade.
(b) 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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Standards Staff.
(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 helicopter to a location where
the requirements of this AD can be accomplished.
(d) This amendment becomes effective on September 4, 1998, to
all persons except those persons to whom it was made immediately
effective by Priority Letter AD 98-16-02, issued July 22, 1998,
which contained the requirements of this amendment.
Issued in Fort Worth, Texas, on August 12, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-22365 Filed 8-19-98; 8:45 am]
BILLING CODE 4910-13-U