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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-29-AD; Amendment 39-11370; AD 99-21-25]

RIN 2120-AA64

Airworthiness Directives; Eurocopter France Model SE.3160,

SA.315B, SA.316B, SA.316C, and SA.319B 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)

applicable to Eurocopter France Model SE.3160, SA.315B, SA.316B,

SA.316C, and SA.319B helicopters with a main gearbox (MGB), all part

numbers, not modified in accordance with MOD 072241. This action

requires, prior to further flight and thereafter prior to the first

flight of each day, inspecting the MGB magnetic plug for metal

particles. This AD also requires inspecting the MGB oil filter for

metal particles. This amendment is prompted by the failure of a bevel

wheel gear attachment bolt (bolt) during testing of an SA.315B MGB. The

actions specified in this AD are intended to detect a condition that

could cause bolt failure and damage to the MGB, resulting in loss of

drive to the main rotor and subsequent loss of control of the

helicopter.

DATES: Effective October 29, 1999.

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

before December 13, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation

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

Attention: Rules Docket No. 99-SW-29-AD, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas 76137.

FOR FURTHER INFORMATION CONTACT: 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: The Direction Generale De L'Aviation Civile

(DGAC), the airworthiness authority for France, notified the FAA that

an unsafe condition may exist on Model SE.3160, SA.315B, SA.316B,

SA.316C, and SA.319B helicopters with a MGB, all part numbers, not

modified in accordance with MOD 072241. The DGAC advises that bolt

failure, which occurred when testing an SA.315B MGB, could lead to

damage of the MGB and loss of rotor drive.

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.

An unsafe condition has been identified that is likely to exist or

develop on other Model SE.3160, SA.315B, SA.316B, SA.316C, and SA.319B

helicopters with a MGB, all part numbers, not modified in accordance

with MOD 072241 of the same type design registered in the United

States. Therefore, this AD is being issued to detect a condition that

could cause bolt failure and damage to the MGB. This AD requires

inspecting the MGB magnetic plug for metal particles prior to further

flight and prior to the first flight of each day. This AD also requires

inspecting the MGB oil filter for metal particles at intervals not to

exceed 25 hours time-in-service. The actions are required to be

accomplished in accordance with the applicable maintenance manuals. The

short compliance time involved is required because the previously

described critical unsafe condition can adversely affect the

controllability of the helicopter. Therefore, inspecting the MGB

magnetic plug for metal particles is required prior to further flight

and this AD must be issued immediately.

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.

The FAA estimates that 93 helicopters will be affected by this AD,

that it will take approximately 0.25 work hour to inspect the magnetic

plug prior to the first flight of each day and 2 work hours to inspect

the oil filter every 25 hours TIS, and that the average labor rate is

$60 per work hour. Based on these figures, the total cost impact of the

AD on U.S. operators is estimated to be $318,060 annually, assuming any

metal particles found are not enough to require a cleaning or an

overhaul of the MGB and that each helicopter is flown 100 days per year

for 4 hours each day.

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

[[Page 55625]]

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. 99-SW-29-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:

AD 99-21-25 Eurocopter France: Amendment 39-11370. Docket No. 99-

SW-29-AD.

Applicability: Model SE.3160, SA.315B, SA.316B, SA.316C, and

SA.319B helicopters with a main gearbox, all part numbers, not

modified in accordance with MOD 072241, 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

otherwise 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 request approval for an

alternative method of compliance in accordance with paragraph (d) of

this AD. The request should include an assessment of the effect of

the modification, alteration, or repair on the unsafe condition

addressed by this AD; and, if the unsafe condition has not been

eliminated, the request should include specific proposed actions to

address it.

Compliance: Required as indicated, unless accomplished

previously.

To detect a condition that could cause failure of a bevel wheel

gear attachment bolt (bolt) and damage to the main gearbox (MGB),

resulting in loss of drive to the main rotor and subsequent loss of

control of the helicopter, accomplish the following:

(a) Prior to further flight and thereafter prior to the first

flight of each day, inspect the MGB magnetic plug for metal

particles. If metal particles are found, comply with the

instructions in the applicable maintenance manual.

(b) At intervals not to exceed 25 hours time-in-service, inspect

the MGB oil filter for metal particles. If metal particles are

found, comply with the instructions in the applicable maintenance

manual.

Note 2: Work Card 5.41.202 pertains to the subject of this AD.

(c) Modification of the MGB by MOD 072241 is terminating action

for the requirements of this AD.

(d) 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, Regulations Group, Rotorcraft

Directorate. Operators shall submit their requests through an FAA

Principal Maintenance Inspector, who may concur or comment and then

send it to the Manager, Regulations Group, Rotorcraft Directorate.

Note 3: Information concerning the existence of approved

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

obtained from the Regulations Group, Rotorcraft Directorate.

(e) Special flight permits are prohibited.

(f) This amendment becomes effective on October 29, 1999.

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

Generale De L'Aviation Civile (France) AD 98-304-058(A) for Model

SE.3160, SA.316B, SA.316C, and SA.319B helicopters, and AD 98-303-

041(A) for Model SA.315B helicopters, both dated July 29, 1998.

Issued in Fort Worth, Texas, on October 5, 1999.

Mark R. Schilling,

Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 99-26711 Filed 10-13-99; 8:45 am]

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