[Federal Register Volume 66, Number 169 (Thursday, August 30, 2001)]
[Rules and Regulations]
[Pages 45755-45756]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 01-21747]
[[Page 45755]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-SW-47-AD; Amendment 39-12424; AD 2001-17-32]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS350B, B1, B2,
B3, BA, D, D1 and AS355E, F, F1, F2, and N Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD) that applies to Eurocopter France (ECF) Model AS350B, B1, B2, B3,
BA, D, AS355E, F, F1, F2, and N helicopters. That AD requires
inspecting certain versions of the tail rotor pitch change spider
assembly (spider assembly) for the proper rotational torque, axial
play, and any brinelling of the bearing. This AD requires identifying
the spider assembly with index marks to detect bearing spacer rotation,
visually checking to ensure that the index marks are aligned before the
first flight of each day, and subsequently modifying the spider
assembly. This AD also adds the ECF Model AS350D1 helicopters to the
applicability. This AD is prompted by operator reports that the spider
assembly bearing spacers are rotating. The actions specified by this AD
are intended to detect rotation of the spider assembly bearing spacers,
prevent seizure of the bearing, loss of tail rotor control, and
subsequent loss of control of the helicopter.
DATES: Effective October 4, 2001.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 4, 2001.
ADDRESSES: The service information referenced in this AD may be
obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand
Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-
3527. This information may be examined at the FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort
Worth, Texas; or at the Office of the Federal Register, 800 North
Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Jim Grigg, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations Group, Fort Worth, Texas
76193-0111, telephone (817) 222-5490, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 by
superseding AD 99-24-18, Amendment 39-11443 (64 FR 66762, November 30,
1999), which applies to ECF Model AS350B, B1, B2, B3, BA, D, D1, and
AS355E, F, F1, F2, and N helicopters, was published in the Federal
Register on May 22, 2001 (66 FR 28133). That action proposed the
following:
Within 10 hours time-in-service (TIS), install index marks
on the spider assembly to detect any bearing spacer rotation;
Before the first flight of each day, visually check to
ensure that the index marks are aligned; and
Within 25 hours TIS if bearing spacer rotation is detected
or at the next 500 hours inspection if no bearing spacer rotation is
detected, modify the spider assembly.
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, except for non-substantive editorial
changes.
The FAA estimates that this AD will affect 514 helicopters of U.S.
registry. It will take approximately 0.25 work hour per helicopter to
identify each spider assembly with index marks and 6 work hours to
modify the spider assembly. The average labor rate is $60 per work
hour. Required parts will cost approximately $200 per helicopter. Based
on these figures, the total cost impact of this AD on U.S. operators is
estimated to be $295,550, assuming that the index marks are installed
on all helicopters and that the spider assembly is modified on all the
helicopters.
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 location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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 removing Amendment 39-11443 (64 FR
66762, November 30, 1999), and by adding a new airworthiness directive
(AD), Amendment 39-12424, to read as follows:
2001-17-32 Eurocopter France: Amendment 39-12424. Docket No. 2000-
SW-47-AD. Supersedes AD 99-24-18, Amendment 39-11443, Docket No. 99-
SW-41-AD.
Applicability: AS350B, B1, B2, B3, BA, D, D1 and AS355E, F, F1,
F2, and N helicopters, with tail rotor pitch change spider assembly
(spider assembly), part number (P/N) 350A33-2004-00, -01, -02, -03,
-05, or 350A33-2009-00 or -01, installed, and which do not
incorporate MOD 076554, 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 (e) 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 detect rotation of the spider assembly bearing spacers,
prevent seizure of the bearing, loss of tail rotor control, and
[[Page 45756]]
subsequent loss of control of the helicopter, accomplish the
following:
(a) Within 10 hours time-in-service (TIS), install identifying
index marks on the spider assembly in accordance with (IAW) the
Accomplishment Instructions, paragraph 2.B.1, of Eurocopter France
Service Bulletin (SB) No. 05.00.33 for Model AS 350 series
helicopters or 05.00.33 for Model AS 355 series helicopters. Both
SB's are dated May 15, 2000.
(b) Before the first flight of each day, visually check that the
index marks on the rotating plate and on the spacer are aligned. The
visual check required by the AD may be performed by an owner/
operator (pilot) but must be entered into the aircraft records
showing compliance with paragraph (b) of this AD in accordance with
14 CFR 43.11 and 91.417(a)(2)(v).
Note 2: This AD allows a pilot to perform this check because it
involves only a visual check of the index marks on the spider
assembly and can be performed equally well by a pilot or a mechanic.
(c) At the following intervals, modify the spider assembly:
(1) If bearing spacer rotation is detected, within 25 hours TIS,
IAW paragraph 2.B.4 of the applicable SB.
(2) If no bearing spacer rotation is detected, at the next 500-
hour (``T'') inspection, IAW paragraph 2.B.3 of the applicable SB.
(d) Modifying the bearing assembly with MOD 076554 constitutes
terminating action for the requirements of this AD.
(e) 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Regulations Group.
(f) 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.
(g) The modifications shall be done in accordance with the
Accomplishment Instructions, paragraphs 2.B.1, 2.B.3, and 2.B.4 of
Eurocopter France Service Bulletin No. 05.00.33 for Model AS 350
series helicopters or 05.00.33 for Model AS 355 series helicopters.
Both service bulletins are dated May 15, 2000. This incorporation by
reference was approved by the Director of the Federal Register in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be
obtained from American Eurocopter Corporation, 2701 Forum Drive,
Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972)
641-3527. Copies may be inspected at the FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.
(h) This amendment becomes effective on October 4, 2001.
Note 4: The subject of this proposal is addressed in Direction
Generale de L'Aviation Civile (France) AD No.'s T2000-222-079(A) and
T2000-223-059(A), both dated June 2, 2000.
Issued in Fort Worth, Texas, on August 17, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-21747 Filed 8-29-01; 8:45 am]
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