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. 98-SW-23-AD; Amendment 39-10725; AD 98-10-09]

RIN 2120-AA64

Airworthiness Directives; Eurocopter France Model 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

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adopting Airworthiness Directive (AD) 98-10-09 which was sent

previously to all known U.S. owners and operators of Eurocopter France

Model SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 helicopters by

individual letters. This AD requires an initial and recurring

inspections of the blade spar for cracks. This amendment is prompted by

an accident in which a Model SA.315B helicopter lost a main rotor

blade. The cause of the blade failure was fatigue cracking. This

condition, if not corrected, could result in separation of a blade and

subsequent loss of control of the helicopter.

DATES: Effective September 15, 1998, to all persons except those

persons to whom it was made immediately effective by priority letter AD

98-10-09, issued on May 6, 1998, which contained the requirements of

this amendment.

The incorporation by reference of certain publications listed in

the regulations is approved by the Director of the Federal Register as

of September 15, 1998.

Comments for inclusion in the Rules Docket must be received on or

before October 30, 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-23-AD, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas 76137.

The applicable service information may be obtained from American

Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-

4005, telephone (972) 641-3460, fax (972) 641-3527. This information

may be examined at the FAA, Office of the Regional Counsel, Southwest

Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the

Office of the Federal Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

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 February 12, 1998, the FAA issued

priority letter AD 98-04-40 (FAA Docket 98-SW-09-AD), applicable to

Eurocopter France Model SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160

helicopters. That AD was published in the Federal Register on April 17,

1998 (63 FR 19183). That AD requires, for blades with 400 or more hours

time-in-service (TIS), within 25 hours TIS, inspecting each blade spar

for cracks using a dye-penetrant method, and visually inspecting each

blade cuff for cracks using a 10-power or higher magnifying glass. If a

crack is discovered in either a blade spar or cuff, removal and

replacement of the blade with an airworthy blade is required prior to

further flight. That action was prompted by an accident in which a

Model SA.315B helicopter lost a main rotor blade (blade) just prior to

take-off. Although the main gearbox and the remainder of the main rotor

assembly separated from the helicopter and passed through the cockpit,

there were no fatalities. The cause of the blade failure was determined

to be fatigue cracks that originated from the outboard blade-to-cuff

attachment bolt hole and progressed through the blade spar and cuff.

That condition, if not corrected, could result in separation of a blade

and subsequent loss of control of the helicopter. Priority Letter AD

98-10-09 issued May 6, 1998, superseded AD 98-04-40. AD 98-10-09

requires the same one-time inspections as required by AD 98-04-40, but

also requires, at intervals not to exceed 25 hours TIS, a recurring

visual inspection of the blade spar at the outboard blade-to-cuff

attachment bolt hole for cracks using a 10-power or higher magnifying

glass.

The FAA has reviewed Eurocopter France Service Telex No. 00055/

0034/98, dated February 3, 1998 (Eurocopter Service Telex: 316/319 No.

01.64 and 315 No. 01.29), which describes procedures for inspecting

each blade spar for cracks using a dye-penetrant method, and visually

inspecting each blade cuff for cracks using a 10-power or higher

magnifying glass; and Eurocopter France Service Telex No. 00060/00099/

98, dated April 9, 1998 (Eurocopter Service Telex: 316/319 No. 01.65

and 315 No. 01.30), which describes procedures for repetitively

inspecting each blade spar for cracks using a 10-power or higher

magnifying glass. Additionally, the Direction Generale De L'Aviation

Civile, which is the airworthiness authority for France, has issued AD

98-088-055(A) and 98-089-038(A), both dated February 25, 1998; and AD

98-170-056(A)R1 and 98-171-039(A)R1, both dated May 6, 1998, to mandate

these actions.

Since the unsafe condition described 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, the FAA issued

priority letter AD 98-10-09 to prevent separation of a blade and

subsequent loss of control of the helicopter. This AD requires, for

blades with 400 or more hours time-in-service (TIS), within 25 hours

TIS, inspecting each blade spar for cracks using a dye-penetrant

method, and visually inspecting each blade cuff for cracks using a 10-

power or higher magnifying glass; and thereafter, visually inspecting

each blade spar with a 10-power or higher magnifying glass at intervals

not to exceed 25 hours TIS. If a crack is discovered in either a blade

spar or cuff, removal and replacement of the blade with an airworthy

blade is required prior to further flight. The actions are required to

be accomplished in accordance with the service telexes described

previously.

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 May 6, 1998 to all known U.S. owners and operators of

Eurocopter France Model 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 has made two non-substantive changes to the

Priority Letter AD which will neither increase the economic burden on

an operator nor increase the scope of the AD. The 400 or more hours TIS

threshold provision has been moved from the compliance paragraph to the

applicability paragraph. Additionally, Figure 1 has been enhanced to

provide a clearer picture of the affected blade area.

Previous completion of the inspections required by AD 98-04-40

constitutes compliance with the initial blade inspections required by

this AD. The recurring visual inspections specified in this AD shall

begin on or before 25 hours TIS after the initial inspections required

by either this AD or AD 98-04-40, whichever occurred first. If more

than 25 hours TIS has elapsed since the inspections required by AD 98-

04-40, then the recurring visual inspection specified in this AD must

be accomplished prior to further flight.

The FAA estimates that 106 helicopters of U.S. registry will be

affected by this AD, that it will take approximately 4 work hours per

helicopter to inspect a blade and 4 work hours to replace a main rotor

blade, if necessary, and that the average labor rate is $60 per work

hour. Required parts will cost approximately $49,700 per blade. Based

on these figures, the total cost impact of the AD on U.S. operators is

estimated to be $5,319,080

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for the first year, assuming one blade replacement per helicopter and

$25,440 each subsequent year, assuming five inspections per year and no

blade replacements.

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, 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-23-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, Incorporation by

reference, 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 removing Amendment 39-10479 (63 FR

19183, April 17, 1998) and by adding a new airworthiness directive

Amendment 39-10725 to read as follows:

AD 98-10-09 Eurocopter France: Amendment 39-10725. Docket No. 98-

SW-23-AD. Supersedes AD 98-04-40, Amendment 39-10479, Docket 98-SW-

09-AD.

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

SE.3160 helicopters, with main rotor blades, part numbers 3160S11-

10000 all dash numbers, 3160S11-30000 all dash numbers, 3160S11-

35000 all dash numbers, 3160S11-40000 all dash numbers, 3160S11-

45000 all dash numbers, 3160S11-50000 all dash numbers, or 3160S11-

55000 all dash numbers, with 400 or more hours time-in-service

(TIS), 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 (f) 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 prevent separation of a blade and subsequent loss of control

of the helicopter, accomplish the following:

(a) Within 25 hours TIS, inspect each blade spar for cracks

using a dye-penetrant method in accordance with paragraphs CC.1

through CC.4 of the Operational Procedures in Eurocopter France

Service Telex No. 00055/0034/98, dated February 3, 1998 (Eurocopter

Service Telex: 316/319 No. 01.64 and 315 No. 01.29).

(b) Within 25 hours TIS, visually inspect the upper and lower

surfaces of each blade cuff for cracks, especially around the

attachment bolts, using a 10-power or higher magnifying glass.

(c) Within 25 hours TIS from the last required inspection of

each blade spar for cracks in the area indicated in Figure 1, and

thereafter at intervals not to exceed 25 hours TIS:

(1) Without removing the blade from the helicopter, clean each

blade root area using ``Teepol'' or an equivalent product.

(2) Support the blade tip to eliminate blade droop while

inspecting the lower blade surface.

(3) Visually inspect each blade spar with a 10-power or higher

magnifying glass along the hatched area indicated in Figure 1,

beginning on the blade lower surface, then on the flat section of

the trailing edge (B), on the blade upper surface, and then on the

flat section of the leading edge (A).

(4) Before returning the blades to service, confirm that there

is a sealing bead (1) around the edge of the blade cuff.

Note 2: Eurocopter France Service Telex No. 00060/00099/98,

dated April 9, 1998 (Eurocopter Service Telex: 316/319 No. 01.65 and

315 No. 01.30) pertains to the subject of this AD.

(d) If more than 25 hours TIS have elapsed since the last

required inspection of each blade spar for cracks in the area

indicated in Figure 1, before further flight, conduct the

inspections required by paragraph (c) of this AD.

(e) If a crack is found in a blade spar or cuff, remove the

blade and replace it with an airworthy blade prior to further

flight.

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(f) 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 3: Information concerning the existence of approved

alternative methods of compliance with this AD, if any, may be

obtained from the Rotorcraft Standards Staff.

(g) Special flight permits will not be issued.

(h) The inspection shall be done in accordance with paragraphs

CC.1 through CC.4 of the Operational Procedures in Eurocopter France

Service Telex No. 00055/0034/98, dated February 3, 1998. This

incorporation by reference was approved by the Director of the

Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part

51. Copies may be obtained from American Eurocopter Corporation,

2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972)

641-3460, fax (972) 641-3527. Copies may be inspected at the FAA,

Office of the Regional Counsel, Southwest Region, 2601 Meacham

Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(i) This amendment becomes effective on September 15, 1998, to

all persons except those persons to whom it was made immediately

effective by Priority Letter AD 98-10-09, issued May 6, 1998, which

contained the requirements of this amendment.

Note 4: The subject of this AD is addressed in Direction

Generale De L'Aviation Civile (France) AD 98-088-055(A) and 98-089-

038(A), both dated February 25, 1998; and Direction Generale De

L'Aviation Civile (France) AD 98-170-056(A)R1 and 98-171-039(A)R1,

both dated May 6, 1998.

Issued in Fort Worth, Texas, on August 21, 1998.

Larry M. Kelly,

Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 98-23095 Filed 8-28-98; 8:45 am]

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