[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