[Federal Register Volume 62, Number 225 (Friday, November 21, 1997)]
[Rules and Regulations]
[Pages 62239-62241]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-30603]
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Rules and Regulations
Federal Register
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Federal Register / Vol. 62, No. 225 / Friday, November 21, 1997 /
Rules and Regulations
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-SW-22-AD; Amendment 39-10211; AD 97-24-04]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France (Eurocopter) Model SE
3130, SE 313B, SA 3180, SA 318B, and SA 318C 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 Model SE 3130, SE 313B, SA 3180, SA 318B,
and SA 318C helicopters. This action requires a visual inspection of
the main rotor blade reinforcement strips for debonding between the
reinforcement strips of the blade; and a visual inspection of the main
rotor blade (blade) skin for cracks or corrosion, and replacement of
the blade with an airworthy blade if certain debonding or a crack or
corrosion is found. This amendment is prompted by an accident in which
a blade separated in flight. The actions specified in this AD are
intended to detect debonding, cracks, or corrosion in the affected
blades and to prevent failure of a blade and subsequent loss of control
of the helicopter.
DATES: Effective December 8, 1997.
Comments for inclusion in the Rules Docket must be received on or
before January 20, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of Regional Counsel, Southwest Region,
Attention: Rules Docket No. 97-SW-22-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT: Mr. Richard Monschke, Aerospace
Engineer, Rotorcraft Standards Staff, 2601 Meacham Blvd., Fort Worth,
Texas 76137, telephone (817) 222-5116, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION: The Direction General De L'Aviation Civile
(DGAC), which is the airworthiness authority for France, recently
notified the FAA that an unsafe condition may exist on Eurocopter Model
SE 3130, SE 313B, SA 3180, SA 318B, and SA 318C helicopters with part
number (P/N) 3130-S-11-10000, 3130-S-11-20000, or 3130-S-11-30000 main
rotor blades installed. The DGAC advises that fatigue cracks, initiated
by skin debonding or skin corrosion in the area of the reinforcement
strip, may develop in the blade skin near the blade root, resulting in
failure of the blade in flight and subsequent loss of control of the
helicopter.
Eurocopter France has issued Eurocopter Telex Service 0033/00169/
97, dated June 18, 1997, which specifies visual inspections of the
blade root skin and reinforcement strip for bonding separation, and
replacement of the blade with an airworthy blade if bonding separation
is found; and a visual inspection of the blade root skin for cracks and
corrosion, and replacement of the blade with an airworthy blade if
cracks or corrosion are found. The DGAC classified this Telex Service
as mandatory and issued AD 97-135-055(B) 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
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 this 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 Model SE 3130, SE 313B, SA 3180,
SA 318B, and SA 318C helicopters of the same type design registered in
the United States, this AD is being issued to detect debonding, cracks,
or corrosion in the affected blades and to prevent failure of a blade
and subsequent loss of control of the helicopter. This AD requires a
visual inspection in the area extending 5 mm (0.200 inch) from the
strip reinforcing the inboard edge of the blade as shown in Figure 1
for debonding between the main rotor blade skin and reinforcement
strip, and replacement of the main rotor blade with an airworthy blade
if debonding is found; a visual inspection for debonding between the
blade and the reinforcement strip on the leading edge of the blade that
covers the blade spar, and replacement with an airworthy blade if
debonding is present for more than 0.750 inch2 (500
mm2); and a visual inspection of the main rotor blade skin
for cracks and corrosion, and replacement with an airworthy blade if
any crack or corrosion is found.
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,
[[Page 62240]]
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-22-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:
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:
97-24-04 Eurocopter France: Amendment 39-10211. Docket No. 97-SW-
22-AD.
Applicability: Model SE 3130, SE 313B, SA 3180, SA 318B, and SA
318C helicopters with part number (P/N) 3130-S-11-10000, 3130-S-11-
20000, or 3130-S-11-30000 main rotor blades, 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 as indicated, unless accomplished
previously.
To detect debonding, cracks, or corrosion in the affected blades
and to prevent failure of a main rotor blade (blade) and subsequent
loss of control of the helicopter, accomplish the following:
(a) Before further flight, and thereafter at intervals not to
exceed 25 hours time-in-service, for part number (P/N) 3130-S-11-
10000, 3130-S-11-20000, or 3130-S-11-30000, visually inspect:
(1) For debonding in the area extending 5 mm (0.200 inch) from
the strip reinforcing the inboard edge of the blade as shown in
Figure 1. If there is any debonding of the reinforcement strip,
replace the blade with an airworthy blade.
(2) For debonding between the blade and the reinforcement strip
on the leading edge of the blade that covers the blade spar. If
debonding is present for more than 0.750 inches 2 (500
mm2) at any point on the blade, replace the blade with an
airworthy blade.
(3) For cracks in the blade skin in the first 12 inches (300 mm)
of the blade measured from the root reinforcement strip using a 3 x
or higher magnifying glass. If any crack is found, replace the blade
with an airworthy blade.
(4) For corrosion in the blade skin in the first 12 inches (300
mm) of the blade measured from the root reinforcement strip. If any
corrosion 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, FAA, Rotorcraft Directorate,
Rotorcraft Standards Staff. 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 are prohibited.
(d) This amendment becomes effective on December 8, 1997.
Note 3: The subject of this AD is addressed in Direction General
De L'Aviation Civile (France) AD 97-135-055(B), dated June 20, 1997.
BILLING CODE 4910-13-U
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[GRAPHIC] [TIFF OMITTED] TR21NO97.013
BILLING CODE 4910-13-C
Issued in Fort Worth, Texas, on November 14, 1997.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 97-30603 Filed 11-20-97; 8:45 am]
BILLING CODE 4910-13-U
