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

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]

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