[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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