[Federal Register Volume 67, Number 54 (Wednesday, March 20, 2002)]
[Rules and Regulations]
[Pages 12858-12859]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-6626]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-SW-20-AD; Amendment 39-12680; AD 2002-06-04]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS350B,
AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, AS350D1, AS355E,
AS355F, AS355F1, AS355F2, and AS355N Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) for
specified Eurocopter France (ECF) helicopters that requires replacing
the tail rotor hub pitch change plate ``SNR'' bearing (bearing). This
amendment is prompted by fatigue cracks found in the bearings. The
actions specified by this AD are intended to prevent seizure of the
bearing, loss of tail rotor effectiveness, and subsequent loss of
control of the helicopter.
DATES: Effective April 24, 2002.
FOR FURTHER INFORMATION CONTACT: Jim Grigg, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth,
Texas 76193-0110, telephone (817) 222-5490, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to
include an AD for ECF Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA,
AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, and AS355N
helicopters was published in the Federal Register on November 28, 2001
(66 FR 59375). That action proposed replacing each bearing with an
airworthy bearing at specified intervals. Also, that action noted that
transferring a bearing from one model to another is permissible by
complying with the transfer rules described in the Master Servicing
Recommendations Chapter 05.99.
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 514 helicopters of U.S. registry will be
affected by this AD, that it will take approximately 5 work hours per
helicopter to accomplish the required actions, and that the average
labor rate is $60 per work hour. Required parts will cost approximately
$90 per helicopter. Based on these figures, the total cost impact of
the AD on U.S. operators is estimated to be $200,460.
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 Rules Docket at 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
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends 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:
2002-06-04 Eurocopter France: Amendment 39-12680. Docket No. 2001-
SW-20-AD.
Applicability: Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA,
AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, and
AS355N helicopters, with tail rotor hub pitch change plate ``SNR''
bearing (bearing) part number (P/N) 6010F234M16 (Eurocopter France
P/N
[[Page 12859]]
704A33-651-190), 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 prevent seizure of the bearing, loss of tail rotor
effectiveness, and subsequent loss of control of the helicopter,
accomplish the following:
(a) For Model AS350B3 and AS355N helicopters, replace each
bearing with an airworthy bearing as follows:
(1) Within 30 hours time-in-service (TIS) for each bearing that
has 270 or more hours TIS as of the effective date of this AD.
(2) Before reaching 300 hours TIS for each bearing that has less
than 270 hours TIS as of the effective date of this AD.
(3) Thereafter, replace each bearing at intervals not to exceed
300 hours TIS.
(b) For all other Model AS350 or AS355 helicopters, replace each
bearing with an airworthy bearing as follows:
(1) Within 50 hours TIS for each bearing that has 1150 hours or
more TIS as of the effective date of this AD.
(2) Before reaching 1200 hours TIS for each bearing that has
less than 1150 hours TIS as of the effective date of this AD.
(3) Thereafter, replace each bearing at intervals not to exceed
1200 hours TIS.
Note 2: Eurocopter France Alert Telex Nos. 01.00.46 and
01.00.48, both dated February 22, 2001, pertain to the subject of
this AD.
(c) When transferring a bearing from one model helicopter to
another (refer to the equipment log card), adhere to the transfer
rules described in the applicable master servicing recommendations.
Remove each bearing from service at or before the service life
limits given in paragraphs (a)(3) and (b)(3) of this AD.
Note 3: The Master Servicing Recommendations for the affected
helicopters, Chapter 05.99, pertain to the subject 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, FAA. 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.
Note 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Regulations Group.
(e) 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.
Note 5: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD Nos. 2001-073-061(A) and
2001-074-081(A), both dated March 21, 2001.
(f) This amendment becomes effective on April 4, 2002.
Issued in Fort Worth, Texas, on March 11, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-6626 Filed 3-19-02; 8:45 am]
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