Airworthiness Directives; Eurocopter France Model SA. 315B, SA. 316B, SA. 316C, SA. 319B, and SE. 3160 Helicopters

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-SW-14-AD]

Airworthiness Directives; Eurocopter France Model SA. 315B, SA.

316B, SA. 316C, SA. 319B, and SE. 3160 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness

directive (AD) that is applicable to Eurocopter France Model SA. 315B,

SA. 316B, SA. 316C, SA. 319B, and SE. 3160 helicopters. This proposal

would require inspecting the main rotor blade cuff attachment fitting

in the area of the main rotor blade (blade) attachment bolts for

cracks, and removing and replacing the blade if a crack is found. This

proposal is prompted by a report of a crack in a main rotor blade cuff

attachment fitting/spar assembly that was discovered during fatigue

testing by the manufacturer. The actions specified by the proposed AD

are intended to prevent failure of a main rotor blade cuff attachment

fitting at a bolt hole location, loss of a main rotor blade, and

subsequent loss of control of the helicopter.

DATES: Comments must be received on or before January 4, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation

Administration (FAA), Office of the Regional Counsel, Southwest Region,

Attention: Rules Docket No. 97-SW-14-AD, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas 76137. Comments may be inspected at this location

between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal

holidays.

FOR FURTHER INFORMATION CONTACT: Mr. Richard Monschke, Aerospace

Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601

Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5116, fax

(817) 222-5961.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to participate in the making of the

proposed 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 above. All

communications received on or before the closing date for comments,

specified above, will be considered before taking action on the

proposed rule. The proposals contained in this notice may be changed in

light of the comments received.

Comments are specifically invited on the overall regulatory,

economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with

the substance of this proposal will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments

submitted in response to this notice must submit a self-addressed,

stamped postcard on which the following statement is made: ``Comments

to Docket No. 97-SW-14-AD.'' The postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this NPRM by submitting a request

to the FAA, Office of the Regional Counsel, Southwest Region,

Attention: Rules Docket No. 97-SW-14-AD, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas 76137.

Discussion

The Direction Generale De L'Aviation Civile (DGAC), which is the

airworthiness authority for France, recently notified the FAA that an

unsafe condition may exist on Eurocopter France Model SA. 315B, SA.

316B, SA. 316C, SA. 319B, and SE. 3160 helicopters. The DGAC advises

that, within 400 operating hours, and thereafter at every 400 operating

hours, a crack detection inspection of the main rotor blade cuff

attachment fitting in the area of the main rotor blade attachment bolt

holes must be performed. The DGAC issued AD 96-081-036(B)R1, applicable

to Eurocopter France Model SA. 315B helicopters, and AD 96-082-54(B)R1

applicable to Eurocopter France Model SA. 316B, SA. 316C, SA. 319B, and

SE. 3160 helicopters, both dated April 24, 1996, in order to assure the

continued airworthiness of these helicopters in France.

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 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 France Model SA. 315B, SA. 316B,

SA. 316C, SA. 319B, and SE. 3160 helicopters of the same type design

registered in the United States, the proposed AD would require

inspecting the attachment fitting in the area of the blade attachment

bolt holes for cracks, and removing and replacing any blade in which a

crack is found.

The FAA estimates that 83 helicopters of U.S. registry would be

affected by this proposed AD, that it would take approximately 2 work

hours per helicopter to accomplish the proposed initial inspection and

2 work hours per helicopter for each repetitive inspection, and that

the average labor rate is $60 per work hour. Required parts would cost

$40,000 per blade, if needed. Based on these figures, the total cost

impact of the proposed AD on U.S. operators is

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estimated to be $49,960 for one inspection and one blade replacement

for each helicopter per year.

The regulations proposed herein would 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

proposal would not have sufficient federalism implications to warrant

the preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this proposed

regulation (1) is not a ``significant regulatory action'' under

Executive Order 12866; (2) is not a ``significant rule'' under the DOT

Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);

and (3) if promulgated, will not have a significant economic impact,

positive or negative, on a substantial number of small entities under

the criteria of the Regulatory Flexibility Act. A copy of the draft

regulatory evaluation prepared for this action is contained in the

Rules Docket. A copy of it may be obtained by contacting 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.

The Proposed Amendment

Accordingly, pursuant to the authority delegated to me by the

Administrator, the Federal Aviation Administration proposes to amend

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:

Eurocopter France: Docket No. 97-SW-14-AD.

Applicability: Model SA. 315B, SA. 316B, SA. 316C, SA. 319B, and

SE. 3160 helicopters, with a main rotor blade, part number (P/N)

316OS.11.10.000, 316OS.11.30.000, 316OS.11.35.000, 316OS.11.40.000,

316OS.11.45.000, 316OS.11.50.000, or 316OS.11.55.000, 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 (c) 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: (1) For blades with less than 400 hours time-in-

service (TIS), required prior to the accumulation of 400 hours TIS,

unless accomplished previously, and thereafter at intervals not to

exceed 400 hours TIS; or (2) for blades with 400 hours or more TIS,

required within 50 hours TIS or 30 calendar days, whichever occurs

first, unless accomplished previously, and thereafter at intervals

not to exceed 400 hours TIS:

To prevent failure of a main rotor blade (blade) cuff attachment

fitting at a bolt hole location, loss of a blade, and subsequent

loss of control of the helicopter, accomplish the following:

(a) Inspect both upper and lower blade surfaces of each blade

cuff for cracks (see Figure 1) as follows:

(1) Use a mild liquid detergent or equivalent to remove all dirt

from the blade cuff.

(2) Inspect the blade cuff for cracks, paying particular

attention to the area around the attaching bolts, using a 10-power

or higher magnifying glass.

(3) If a crack is suspected, remove any paint and clean the area

under inspection using a Naptha-type solvent or equivalent, and

conduct a dye penetrant inspection. Completely isolate the area

under inspection with self-adhesive aluminum tape to prevent solvent

or penetrating dye seepage into the other areas of the blade.

(b) If a crack is detected, remove the blade and replace it with

an airworthy blade.

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(c) 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.

(d) 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.

Note 3: The subject of this AD is addressed in Direction

Generale De L'Aviation Civile (France) AD 96-081-036(B)R1 and AD 96-

082-054(B)R1, both dated April 24, 1996.

Issued in Fort Worth, Texas, on October 27, 1998.

Eric Bries,

Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 98-29378 Filed 11-2-98; 8:45 am]

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