[Federal Register Volume 64, Number 229 (Tuesday, November 30, 1999)]
[Rules and Regulations]
[Pages 66762-66763]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-30797]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-SW-41-AD; Amendment 39-11443; AD 99-24-18]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS-350B, B1,
B2, B3, BA, and D, and AS-355E, F, F1, F2, and N Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to Eurocopter France Model AS-350B, B1, B2, B3, BA,
and D, and AS-355E, F, F1, F2, and N helicopters, that requires
inspecting certain versions of the tail rotor spider plate bearing
(bearing) for the proper rotational torque, axial play, and any
brinelling of the bearing. This amendment has the same inspection
requirements as the current AD. Also, this AD expands the applicability
to include additional part numbers (P/N's) and reduces the initial and
recurring inspection compliance times. This amendment is prompted by
additional reports of deterioration of the bearing. The actions
specified by this AD are intended to prevent seizure of the bearing,
loss of tail rotor control, and subsequent loss of control of the
helicopter.
DATES: Effective December 15, 1999. The incorporation by reference of
certain publications listed in the regulations is approved by the
Director of the Federal Register as of December 15, 1999.
Comments for inclusion in the Rules Docket must be received on or
before January 31, 2000.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 99-SW-41-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
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
76137; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Shep Blackman, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5296, fax (817)
222-5961.
SUPPLEMENTARY INFORMATION: On April 14, 1999, the FAA issued AD 99-09-
06, Amendment 39-11139 (64 FR 19881, April 23, 1999), to require
inspecting the bearing for the proper rotational torque, axial play,
and any brinelling of the bearing. That action was prompted by service
difficulty reports citing the need to prematurely replace bearings due
to wear and by two in-flight incidents of increased tail rotor
vibration levels due to bearing wear. That condition, if not corrected,
could result in seizure of the bearing, loss of tail rotor control, and
subsequent loss of control of the helicopter.
Since the issuance of that AD, the FAA has received additional
reports of deterioration of the bearing affected by AD 99-09-06 and
other bearings not covered by AD 99-09-06. Therefore, this AD expands
the applicability to include additional bearing P/N's and to reduce the
initial and recurring inspection compliance times.
Eurocopter France has issued Service Bulletin (SB) 05.00.29,
Revision 2, applicable to Model AS-350 series helicopters, and SB
05.00.30, Revision 2, applicable to Model AS-355 series helicopters,
both dated September 29, 1999. These SB's specify a check of the
bearing for rotational torque. The Direction Generale De L'Aviation
Civile (DGAC), the airworthiness authority for France, classified these
SB's as mandatory and issued AD's 1999-085-076(A)R2 and 1999-084-
057(A)R2, both dated October 20, 1999, to ensure the continued
airworthiness of these helicopters in France.
Since an unsafe condition has been identified that is likely to
exist or develop on other Eurocopter France Model AS-350B, B1, B2, B3,
BA, and D, and AS-355E, F, F1, F2, and N helicopters of the same type
design, this AD supersedes AD 99-09-06 (64 FR 19881, April 23, 1999).
This AD has the same requirements as the current AD. This AD also
expands the applicability to include additional P/N's 350A33-2004-00, -
01 and -02, and 350A33-2009-00 and -01, installed, and excludes a
bearing which has MOD 076551 incorporated. This AD also revises the
initial and recurring inspection compliance times. The actions are
required to be accomplished in accordance with the SB's described
previously. The short compliance time involved is required because the
previously described critical unsafe condition can adversely affect the
controllability of the helicopter. Therefore, including additional P/
N's in the applicability, requiring an initial inspection within 10
hours time-in-service (TIS) to measure the bearing rotational torque,
and inspecting the bearing for axial play or brinelling at intervals
not to exceed 50 hours TIS or 6 months, whichever occurs first, are
required and this AD must be issued immediately.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
The FAA estimates that 507 helicopters will be affected by this AD,
that it will take approximately 1 work hour to accomplish the
inspection, and 4 work hours to replace a bearing, if required, and
that the average labor rate is $60 per work hour. Required parts will
cost approximately $60 per helicopter. Based on these figures, the
total cost impact of the AD on U.S. operators is estimated to be
$182,520 to inspect all affected helicopters and to replace one bearing
in each helicopter in the fleet.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications should identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
[[Page 66763]]
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 99-SW-41-AD.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will not impose substantial direct
compliance costs on states or local governments or 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 13132, the FAA has not consulted with
States or local authorities prior to the publication of this rule.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, 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 39-11139 (64 FR
19881, April 23, 1999), and by adding a new airworthiness directive
(AD), Amendment 39-11443, to read as follows:
AD 99-24-18 Eurocopter France: Amendment 39-11443. Docket No. 99-
SW-41-AD. Supersedes AD 99-09-06, Amendment 39-11139, Docket No. 98-
SW-44-AD.
Applicability: AS-350B, B1, B2, B3, BA, and D, and AS-355E, F,
F1, F2, and N helicopters, with tail rotor 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 076551,
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 tail rotor spider plate bearing
(bearing), loss of tail rotor control, and subsequent loss of
control of the helicopter, accomplish the following in accordance
with the specified paragraphs of Eurocopter Service Bulletin (SB)
05.00.29, Revision 2, applicable to Model AS-350 helicopters, or SB
05.00.30, Revision 2, applicable to Model AS 355 helicopters, both
dated September 29, 1999, as applicable.
(a) Within 10 hours time-in-service (TIS), measure the
rotational torque of the bearing using the operational procedure in
paragraph 2.B.1) of the Accomplishment Instructions in the
applicable SB. If the rotational load is equal to or greater than
300 grams, replace the pitch change spider plate assembly with an
airworthy pitch change spider plate assembly before further flight.
(b) At intervals not to exceed 50 hours TIS or at intervals not
to exceed 6 months, whichever occurs first, measure the axial play
and inspect for rotational binding or brinelling of the bearing
using the operational procedure in paragraph 2.B.2) of the
Accomplishment Instructions in the applicable SB.
(c) If the bearing fails to meet the airworthiness criteria
stated in paragraph 2.B.3)b) of the Accomplishment Instructions in
the applicable SB, replace the pitch change spider plate assembly
with an airworthy pitch change spider plate assembly before further
flight.
(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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Regulations Group, Rotorcraft Directorate.
(e) 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.
(f) The inspections and replacements, if necessary, shall be
done in accordance with paragraph 2.B of Eurocopter SB 05.00.29,
Revision 2, applicable to Model AS-350 helicopters, or Eurocopter SB
05.00.30, Revision 2, applicable to Model AS 355 helicopters, both
dated September 29, 1999, as applicable. 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, Rules Docket No. 99-SW-41-AD, 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.
(g) This amendment becomes effective on December 15, 1999.
Note 3: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD 1999-084-057(A)R2 and AD
1999-085-076(A)R2, both dated October 20, 1999.
Issued in Fort Worth, Texas, on November 19, 1999.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-30797 Filed 11-29-99; 8:45 am]
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