[Federal Register: August 28, 2003 (Volume 68, Number 167)]
[Rules and Regulations]
[Page 51681-51682]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr28au03-3]
[[Page 51681]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-SW-34-AD; Amendment 39-13276; AD 2003-15-51]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model SE3160, SA315B,
SA316B, SA316C, and SA319B 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) 2003-15-51, which was sent
previously to all known U.S. owners and operators of the specified
model Eurocopter France (Eurocopter) helicopters by individual letters.
This AD requires inspecting each main rotor blade (blade) root end bolt
(bolt) and bolt hole for a crack or corrosion or a crack on the blade
root end fitting (fitting) and for certain serial-numbered blades, a
one-time pull test on each fitting and blade root end doubler (doubler)
to detect disbonding. This amendment is prompted by a report from the
blade manufacturer of the discovery of a cracked blade; the cause of
the crack remains under investigation. The actions specified by this AD
are intended to prevent failure of a blade and subsequent loss of
control of the helicopter.
DATES: Effective September 12, 2003, to all persons except those
persons to whom it was made immediately effective by Emergency AD 2003-
15-51, issued on July 16, 2003, which contained the requirements of
this amendment.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 12, 2003.
Comments for inclusion in the Rules Docket must be received on or
before October 27, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 2003-SW-34-AD, 2601 Meacham Blvd., Room
663, Fort Worth, Texas 76137. You may also send comments electronically
to the Rules Docket at the following address: 9-asw-adcomments@faa.gov. The service information referenced in this AD may be obtained from
Rotor Trends, LLC, 1715 N. Pinal Avenue, Casa Grande, Arizona 85222,
telephone: (520) 421-7482, fax: (520) 421-7458, E-mail:
jmp@helisupport.com. 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: Jon Mowery, Aviation Safety Engineer,
FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960
Paramount Blvd., Lakewood, California 90712, telephone: (562) 627-5322,
fax: (562) 627-5210.
SUPPLEMENTARY INFORMATION: On July 16, 2003, the FAA issued Emergency
AD 2003-15-51 for the specified model helicopters, which requires
inspecting the blade bolts and bolt holes for a crack or corrosion or a
crack on the blade fittings using a 10x or higher magnifying glass, and
for certain serial-numbered blades, a one-time pull test on the blade
fittings and doublers to detect disbonding. That action was prompted by
a report from the blade manufacturer of a cracked blade, which was
discovered on May 27, 2003. The cause of the crack is unknown at this
time, however investigation indicates that the crack may be
attributable to a quality control system problem. This condition, if
not corrected, could result in failure of a blade and subsequent loss
of control of the helicopter.
The FAA has reviewed Rotor Trends, LLC Service Bulletin No. 01.03,
dated July 9, 2003, which describes procedures for initial and
repetitive inspections of the bolts and bolt holes for a crack or
corrosion using a 10x magnifying glass and light. A one-time pull test
on the blade fittings and doublers to detect disbonding is also
described. If a crack is found on a blade fitting or in a bolt hole, or
if any corrosion is found in a bolt hole or radiating from a bolt hole,
or if disbonding is detected in the blade fittings or doublers,
removing the blade and replacing it with an airworthy blade is
specified. If corrosion is detected only on bolts, replacing the
affected bolts with airworthy bolts is specified.
Since the unsafe condition described is likely to exist or develop
on other Eurocopter Model SE3160, SA315B, SA316B, SA316C, and SA319B
helicopters of the same type designs, the FAA issued Emergency AD 2003-
15-51 to prevent failure of a blade and subsequent loss of control of
the helicopter. The AD requires, for blades, part number (P/N) L3160-
100-01 (all serial numbers), within 10 hours time-in-service (TIS) or
30 days, whichever occurs first, inspecting the blade bolts and bolt
holes for a crack or corrosion using a 10x or higher magnifying glass.
If a crack is found on a blade fitting or in a bolt hole, or if any
corrosion is found in a bolt hole or radiating from a bolt hole,
removing the blade and replacing it with an airworthy blade is
required. If corrosion is detected only on bolts, replacing the
affected bolts with airworthy bolts, P/N NAS1105, is required. The AD
also requires, for blades, P/N L3160-100-01, serial numbers 600 through
671, within 50 hours TIS or 90 days, whichever occurs first, a one-time
pull test on the blade fittings and doublers to detect disbonding. The
actions must 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 controllability and structural integrity of the
helicopter. Therefore, inspections, pull test, and replacements, if
necessary, are required at short compliance times, and this AD must be
issued immediately.
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 16, 2003 to all known U.S. owners and operators of
Eurocopter Model SE3160, SA315B, SA316B, SA316C, and SA319B
helicopters. These conditions still exist, and the AD is hereby
published in the Federal Register as an amendment to 14 CFR 39.13 to
make it effective to all persons.
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's AD system. The
regulation now includes material that relates to altered products,
special flight permits, and alternative methods of compliance. Because
we have now included this material in part 39, we no longer need to
include it in each individual AD.
The FAA estimates that this AD will affect 30 helicopters of U.S.
registry, and the visual inspection and pull test will take
approximately 4 work hours each per helicopter to accomplish, and
replacing the blades (if necessary) will take approximately 3 hours to
accomplish at an average labor rate of $65 per work hour. Required
parts will cost approximately $100,000 per
[[Page 51682]]
helicopter, if replacement of the blades is necessary. Based on these
figures, we estimate the total cost impact of the AD on U.S. operators
to be $115,795 per helicopter, assuming one inspection per year and one
pull test for each helicopter in the entire fleet; and, replacing the
blades on one 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.
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 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 mailed
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. 2003-SW-34-AD.'' The postcard will be date
stamped and returned to the commenter.
The regulations adopted herein will not have a substantial direct
effect 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, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
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 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
0
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
0
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]
0
2. Section 39.13 is amended by adding a new airworthiness directive to
read as follows:
2003-15-51 Eurocopter France: Amendment 39-13276. Docket No. 2003-
SW-34-AD.
Applicability: Model SE3160, SA315B, SA316B, SA316C, and SA319B
helicopters, with main rotor blade (blade), part number (P/N) L3160-
100-01, produced under a Parts Manufacturer Approval approved by
Supplemental Type Certificate SH778GL, installed, certificated in
any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of a blade and subsequent loss of control of
the helicopter, accomplish the following:
(a) For helicopters that have a blade, part number (P/N) L3160-
100-01 (all serial numbers), installed, within 10 hours time-in-
service (TIS) or 30 days, whichever occurs first, using a 10x or
higher magnifying glass, visually inspect each blade root end bolt
(bolt) and bolt hole for corrosion in a bolt hole or radiating from
a bolt hole, or for a crack on a blade root end fitting (fitting) or
in a bolt hole, in accordance with Part A of Rotor Trends, LLC
Service Bulletin No. 01.03, dated July 9, 2003 (SB).
(b) If corrosion or a crack is found, replace the blade with an
airworthy blade before further flight. If corrosion is detected only
on a bolt, P/N NAS1105, replace the affected bolt with an airworthy
bolt before further flight.
(c) For helicopters that have a blade, P/N L3160-100-01, serial
numbers 600 through 671, installed, within 50 hours TIS or 90 days,
whichever occurs first, conduct a one-time pull test on each fitting
and blade root end doubler to detect disbonding in accordance with
Part B of the SB, except that you are not required to contact or
return a form to Rotor Trends, LLC.
(d) If disbonding is detected, replace the blade with an
airworthy blade before further flight.
(e) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Los Angeles Aircraft Certification Office, Transport
Airplane Directorate, FAA, for information about previously approved
alternative methods of compliance.
(f) Special flight permits will not be issued.
(g) The visual inspections and pull test shall be done in
accordance with Rotor Trends, LLC Service Bulletin No. 01.03, dated
July 9, 2003. 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 Rotor Trends, LLC,
1715 N. Pinal Avenue, Casa Grande, Arizona 85222, telephone: (520)
421-7482, fax: (520) 421-7458, Email: jmp@helisupport.com. Copies
may be inspected at the FAA, Office of the Regional Counsel,
Southwest Region, Attention: Rules Docket No. 2003-SW-34-AD, 2601
Meacham Blvd., Room 663, Fort Worth, Texas 76137; or at the Office
of the Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
(h) This amendment becomes effective on September 12, 2003, to
all persons except those persons to whom it was made immediately
effective by Emergency AD 2003-15-51, issued July 16, 2003, which
contained the requirements of this amendment.
Issued in Fort Worth, Texas, on August 8, 2003.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-21520 Filed 8-27-03; 8:45 am]
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