AD Amdt-39-10211

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 97-30603]



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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 inch<SUP>2</SUP> (500 
mm<SUP>2</SUP>); 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 <SUP>2</SUP> (500 
mm<SUP>2</SUP>) 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