[Federal Register Volume 64, Number 198 (Thursday, October 14, 1999)]
[Rules and Regulations]
[Pages 55621-55624]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-26712]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-75-AD; Amendment 39-11369; AD 99-21-24]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA-365C, C1, 
C2, N, and N1; AS-365N2; and SA-366G1 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-365C, C1, C2, N, and N1; AS-
365N2; and SA-366G1 helicopters, that requires inspecting the 
tightening torque of the main rotor hub blade attach beam spherical 
thrust bearing bolts (bolts). This AD also requires either applying the 
specified torque or, if necessary, conducting a dye penetrant 
inspection for cracks in the metal components. Replacing the spherical 
thrust bearing (bearing) with an airworthy bearing is also required if 
a crack is found. This amendment is prompted by reports of cracks in 
the metal components of the bearing attachment joint. The actions 
specified by this AD are intended to prevent loosening of bearing bolts 
in flight, which may cause cracks in the metal components, failure of 
the bearing, and subsequent loss of control of the helicopter.

EFFECTIVE DATE: November 18, 1999.

FOR FURTHER INFORMATION CONTACT: Shep Blackman, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Regulations Group, 2601 Meacham Blvd., 
Fort Worth, Texas 76137, telephone (817) 222-5296, 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-365C, 
C1, C2, N, and N1; AS-365N2; and SA-366G1 helicopters was published in 
the Federal Register on July 9, 1999 (64 FR 37046). That action 
proposed to require inspecting the tightening torque of the bolts and 
either applying a specified torque or, if

[[Page 55622]]

necessary, conducting a dye penetrant inspection for cracks in the 
metal components. Replacing the bearing with an airworthy bearing was 
also proposed if a crack was 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 as proposed.
    The FAA estimates that 100 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 0.5 work hour and 
approximately 3,000 inspections over the life of the fleet per 
helicopter to accomplish the required actions, and that the average 
labor rate is $60 per work hour. Required parts will cost approximately 
$3,000 per helicopter. Based on these figures, the total cost impact of 
the AD on U.S. operators is estimated to be $9,030,000 assuming 10 ship 
sets of bearings would need to be replaced on the fleet.
    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, 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 99-21-24  Eurocopter France: Amendment 39-11369. Docket No. 98-
SW-75-AD.

    Applicability: Model SA-365C, C1, C2, N, and N1; AS-365N2; and 
SA-366G1 helicopters, 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 (b) 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 within 550 hours time-in-service (TIS), 
unless accomplished previously, and thereafter at intervals not to 
exceed 550 hours TIS.
    To prevent loosening of the main rotor hub blade attach beam 
spherical thrust bearing bolts (bolts), cracks in the metal 
components, failure of a spherical thrust bearing (bearing), and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Inspect the tightening torque of the bolts as indicated by 
``A'' in Figure 1.
    (1) If tightening torque is equal to or less than 12 m.daN (88.4 
lb-ft), remove the bearing and conduct a dye penetrant inspection 
for cracks on the two contact surfaces identified as ``H'' in Figure 
1.
    (i) If a crack is detected, replace the bearing with an 
airworthy bearing.
    (ii) If no crack is detected, reinstall the bearing.

    Note 2: Eurocopter France Service Bulletins 05.22, 05.24, and 
05.00.39, all dated July 17, 1998, pertain to the subject of this 
AD.

    (2) If the tightening torque is greater than 12 m.daN (88.4 lb-
ft), then tighten to 19-22 m.daN (140-162.2 lb-ft).

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    (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 3: 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 November 18, 1999.

    Note 4: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD's 98-383-044(A) for the 
Model SA-365C, 98-382-024-(A) for the Model SA-366, and 98-384-
047(A) for the Model AS-365N helicopters. These AD's are all dated 
September 23, 1998.

    Issued in Fort Worth, Texas, on October 5, 1999.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-26712 Filed 10-13-99; 8:45 am]
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