[Federal Register: September 18, 2003 (Volume 68, Number 181)]
[Rules and Regulations]
[Page 54653-54654]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18se03-3]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-SW-61-AD; Amendment 39-13303; AD 2003-19-01]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS 365 N3 and
EC 155B 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 (Eurocopter) Model AS 365 N3 and EC
155B helicopters, that requires replacing each Fenestron pitch change
control rod (control rod) with an improved reinforced steel airworthy
control rod. This amendment is prompted by a failure of a control rod
on a prototype helicopter and by the manufacturer making available a
newly-designed reinforced steel control rod. The actions specified by
this AD are intended to prevent failure of the control rod, loss of
control of the tail rotor, and subsequent loss of control of the
helicopter.
DATES: Effective October 23, 2003.
FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort
Worth, Texas 76193-0111, telephone (817) 222-5130, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an AD that is
applicable to Eurocopter Model AS 365 N3 and EC 155B helicopters was
published in the Federal Register on October 2, 2002 (67 FR 61843).
That action proposed to require replacing the affected control rod
every 300 hours time-in-service (TIS). However, before the final rule
was published, the manufacturer made available a redesigned control rod
to replace the affected control rod and issued new service information.
Therefore, since we decided to require replacing the affected control
rod with the redesigned control rod, we reopened the comment period by
publishing a supplemental notice of proposed rulemaking on April 1,
2003 (68 FR 15687). That action proposed to require removing the
control rod, P/N 365A33-6161-21, and replacing it with a reinforced
steel control rod, P/N 365A33-6214-20.
The Direction Generale De L'Aviation Civile (DGAC), the
airworthiness authority for France, notified the FAA that an unsafe
condition may exist on Eurocopter Model AS 365 N and Model EC 155B
helicopters. The DGAC advises that a control rod failure occurred on a
prototype aircraft and mandates removing control rod, P/N 365A33-6161-
21, at certain times depending on the number of helicopter flight
hours, and replacing it with a reinforced steel control rod, P/N
365A33-6214-20.
Eurocopter has issued Alert Telex No. 04A005 for Model EC 155B
helicopters, and Alert Telex No. 01.00.55 for Model AS 365 N3
helicopters, both dated July 4, 2002. The alert telexes specify
removing the control rod, P/N 365A33-6161-21, and replacing it with a
reinforced steel control rod, P/N 365A33-6214-20. The DGAC classified
these alert telexes as mandatory and issued AD No. 2002-472-057(A) for
Model AS 365 N3 helicopters, and AD No. 2002-473-006(A) for Model EC
155B helicopters to ensure the continued airworthiness of these
helicopters in France. Both AD's are dated September 18, 2002.
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.
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's AD system. The
regulation now includes material that relates to altered products,
special flight permits, and alternative methods of compliance. However,
for clarity and consistency in this final rule, we have retained the
language of the NPRM regarding that material.
The FAA estimates that 3 helicopters of U.S. registry will be
affected by this AD, that it will take approximately 2 work hours per
helicopter to remove and replace the control rod, and that the average
labor rate is $60 per work hour. Required parts will cost approximately
$2,677. Based on these figures, the total cost impact of the AD on U.S.
operators is estimated to be $8,391.
[[Page 54654]]
The regulations adopted herein will not have a substantial direct
effect 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, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
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 Office of the Regional Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
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
0
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]
0
2. Section 39.13 is amended by adding a new airworthiness directive to
read as follows:
2003-19-01 Eurocopter France: Amendment 39-13303. Docket 2001-SW-61-
AD.
Applicability: Model AS 365 N3 helicopters with MOD 0764B39
(Quiet Fenestron) and Model EC 155B helicopters with tail rotor
pitch change control rod (control rod), part number (P/N) 365A33-
6161-21, 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 (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 as indicated, unless accomplished
previously.
To prevent failure of the control rod, loss of control of the
tail rotor, and subsequent loss of control of the helicopter,
accomplish the following:
(a) Remove the control rod, P/N 365A33-6161-21, and replace it
with a reinforced steel control rod, P/N 365A33-6214-20, in
accordance with the following table:
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Remove the control rod: For control rods with:
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Before further flight.................. 700 or more hours TIS.
Within 20 hours TIS.................... 500 or more hours TIS but less
than 700 hours TIS.
Within 30 hours TIS.................... More than 270 hours TIS and
less than 500 hours TIS.
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Note 2: Eurocopter Alert Telex No. 04A005, for Model EC 155B
helicopters, and Alert Telex No. 01.00.55, for Model AS 365 N3
helicopters, both dated July 4, 2002, pertain to the subject of this
AD.
(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, Safety Management Group, 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, Safety Management Group.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Safety Management Group.
(c) Special flight permits may be issued in accordance with 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 October 23, 2003.
Note 4: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD No. 2002-472-057(A) for
Model AS 365 N3 helicopters, and AD No. 2002-473-006(A) for Model EC
155B helicopters. Both AD's are dated September 18, 2002.
Issued in Fort Worth, Texas, on September 9, 2003.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-23830 Filed 9-17-03; 8:45 am]
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