[Federal Register Volume 68, Number 167 (Thursday, August 28, 2003)]
[Rules and Regulations]
[Pages 51681-51682]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-21520]



[[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: [email protected].
    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: 
[email protected]. 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: [email protected]. 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]
BILLING CODE 4910-13-P