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

RIN 2120-AA64

[Docket No. 97-SW-14-AD; Amendment 39-11062; AD 99-05-14]

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.

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SUMMARY: This amendment adopts a new airworthiness directive (AD),

applicable to Eurocopter France Model SA. 315B, SA. 316B, SA. 316C, SA.

319B, and SE. 3160 helicopters, that requires 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 amendment is prompted by a report of a

crack in a blade cuff attachment fitting/spar assembly that was

discovered during fatigue testing by the manufacturer. The actions

specified by this AD are intended to prevent failure of a blade cuff

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

subsequent loss of control of the helicopter.

EFFECTIVE DATE: April 7, 1999.

FOR FURTHER INFORMATION CONTACT: 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: A proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to include an airworthiness

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

SA. 316B, SA. 316C, SA. 319B, and SE. 3160 helicopters was published in

the Federal Register on November 3, 1998 (63 FR 59252). That action

proposed to require inspecting the blade cuff attachment fitting in the

area of the blade attachment bolt holes

[[Page 10217]]

for cracks, and removing and replacing any blade in which a crack is

found.

Interested persons have been afforded an opportunity to participate

in the making of this amendment. No comments were received on the

proposal or the FAA's determination of the cost to the public. The FAA

has determined that air safety and the public interest require the

adoption of the rule with only minor editorial changes that will

neither increase the economic burden on any operator nor increase the

scope of the AD.

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

affected by this AD, that it will take approximately 2 work hours per

helicopter for the 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 will cost approximately $40,000 per

blade, if needed. Based on these figures, the total cost impact of the

AD on U.S. operators is estimated to be $49,960 for one inspection and

one blade replacement for each helicopter per year.

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.

For the reasons discussed above, I certify that this action (1) is

not a ``significant regulatory action'' under Executive Order 12866;

(2) is not a ``significant rule'' under DOT Regulatory Policies and

Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action

and it is contained in the Rules Docket. A copy of it may be obtained

from the Rules Docket at 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.

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 99-05-14 Eurocopter France: Amendment 39-11062. 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)

3160S.11.10.000, 3160S.11.30.000, 3160S.11.35.000, 3160S.11.40.000,

3160S.11.45.000, 3160S.11.50.000, or 3160S.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 after the effective

date of this AD, 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.

[[Page 10218]]

[GRAPHIC] [TIFF OMITTED] TR03MR99.004

(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.

(e) This amendment becomes effective on April 7, 1999.

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 February 24, 1999.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 99-5178 Filed 3-2-99; 8:45 am]

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