Airworthiness Directives; Eurocopter France Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, AS350D1, and AS355E Helicopters, 37515-37517 [06-5880]
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Federal Register / Vol. 71, No. 126 / Friday, June 30, 2006 / Proposed Rules
Applicability
(c) This AD applies to all Airbus Model
A300 and A310 airplanes; and all Airbus
Model A300 B4–601, B4–603, B4–620, B4–
622, B4–605R, B4–622R, F4–605R, and F4–
622R airplanes, and A300 C4–605R Variant F
airplanes; certificated in any category.
Unsafe Condition
(d) This AD results from fuel system
reviews conducted by the manufacturer. We
are issuing this AD to prevent an ignition
source, which, in combination with
flammable fuel vapors, could result in a fuel
tank explosion and consequent loss of the
airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Service Bulletin Reference
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of the following service
bulletins, as applicable:
(1) For Model A300 airplanes: Airbus
Service Bulletin A300–24–0102, including
Appendix 01, dated December 15, 2005;
(2) For Model A310 airplanes: Airbus
Service Bulletin A310–24–2095, including
Appendix 01, dated December 15, 2005; and
(3) For Model A300 B4–601, B4–603, B4–
620, B4–622, B4–605R, B4–622R, F4–605R,
and F4–622R airplanes, and A300 C4–605R
Variant F airplanes: Airbus Service Bulletin
A300–24–6092, including Appendix 01,
dated December 15, 2005.
days after the effective date of the AD,
whichever is later: Submit a report of the
findings (both positive and negative) of the
inspections required by paragraph (g) of this
AD to Airbus Engineering, c/o SE–E54, 1
Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France. The report must include the
airplane serial number or registration
number, the number of flight cycles and
flight hours on the airplane, the date of the
inspection, the location of the defect, the
conditions found, and the type of repair.
Submitting Appendix 01 of the service
bulletin to Airbus is acceptable for
compliance with this requirement. Under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements contained in this AD and has
assigned OMB Control Number 2120–0056.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Related Information
(k) EASA’s airworthiness directive 2006–
0076, dated April 3, 2006, also addresses the
subject of this AD.
Issued in Renton, Washington, on June 22,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–5872 Filed 6–29–06; 8:45 am]
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
mstockstill on PROD1PC61 with PROPOSALS
Inspections and Corrective Actions
(g) Within 44 months after the effective
date of this AD, perform detailed inspections
for discrepancies of all electrical bundles
located in the leading and trailing edges of
the wings, and all applicable corrective
actions, by doing all of the actions in the
service bulletin, except as provided by
paragraph (h) of this AD. All corrective
actions must be done before further flight.
DEPARTMENT OF TRANSPORTATION
Exception to Corrective Action Instructions
(h) If inadequate clearance is found
between any electrical wire harness and
adjacent components or structure: Before
further flight, correct the inadequate
clearance using a method approved by either
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency (EASA)
(or its delegated agent).
Reporting
(i) Within 30 days after doing the
inspections required by this AD, or within 30
VerDate Aug<31>2005
14:43 Jun 29, 2006
Jkt 208001
BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25085; Directorate
Identifier 2006–SW–02–AD]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Model AS350B, AS350B1,
AS350B2, AS350B3, AS350BA,
AS350C, AS350D, AS350D1, and
AS355E Helicopters
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: This document proposes
adopting a new airworthiness directive
(AD) for the specified Eurocopter France
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
37515
(Eurocopter) model helicopters. This
proposal would require replacing a
certain hydraulic drive belt (drive belt).
Also proposed is reducing the
lubrication time interval for a certain
hydraulic pump drive shaft (drive
shaft). This proposal is prompted by inflight failures of the drive belt and the
drive shaft. The actions specified by this
proposed AD are intended to prevent inflight failure of the drive belt or drive
shaft, loss of hydraulic power to the
flight control system, and subsequent
loss of control of the helicopter.
DATES: Comments must be received on
or before August 29, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically;
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically;
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590;
• Fax: 202–493–2251; or
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
You may get the service information
identified in this proposed AD from
American Eurocopter Corporation, 2701
Forum Drive, Grand Prairie, Texas
75053–4005, telephone (972) 641–3460,
fax (972) 641–3527.
You may examine the comments to
this proposed AD in the AD docket on
the Internet at https://dms.dot.gov.
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:
Comments Invited
We invite you to submit any written
data, views, or arguments regarding this
proposed AD. Send your comments to
the address listed under the caption
ADDRESSES. Include the docket number
‘‘FAA–2006–25085, Directorate
Identifier 2006–SW–02–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
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37516
Federal Register / Vol. 71, No. 126 / Friday, June 30, 2006 / Proposed Rules
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed
rulemaking. Using the search function
of our docket Web site, you can find and
read the comments to any of our
dockets, including the name of the
individual who sent or signed the
comment. You may review the DOT’s
complete Privacy Act Statement in the
Federal Register published on April 11,
2000 (65 FR 19477–78), or you may visit
https://dms.dot.gov.
mstockstill on PROD1PC61 with PROPOSALS
Examining the Docket
You may examine the docket that
contains the proposed AD, any
comments, and other information in
person at the Docket Management
System (DMS) Docket Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Office (telephone 1–800–647–
5227) is located at the plaza level of the
Department of Transportation Nassif
Building in Room PL–401 at 400
Seventh Street, SW., Washington, DC.
Comments will be available in the AD
docket shortly after the DMS receives
them.
Discussion
On May 4, 2004, a Eurocopter Model
AS350BA helicopter lost hydraulic
system power, resulting in a non-fatal
accident. An investigation of the
accident showed that the drive belt, part
number (P/N) 704A33–690–004, failed
in-flight, approximately 160 hours short
of its 600-hour time-in-service (TIS) life
limit. Further investigations showed
that the drive belt had been installed
inside out and the exterior surface, as
installed, had numerous lateral cracks.
Historical records from both the FAA’s
Service Difficulty Report database and
the National Transportation Safety
Board’s Accidents and Incidents
database showed that 43 failures or
replacements of the affected P/Ned
drive belts occurred between February
1995 and January 2006. Twenty of the
affected drive belts were replaced
because they were found prematurely
stretched or worn past their service
limits and the remaining drive belts
failed in-flight after averaging 277 hours
TIS. These in-flight failures resulted in
loss of hydraulic system pressure that
required the pilots to make emergency
landings; three of those in-flight
failures, including the failure on May 4,
2004, resulted in accidents.
VerDate Aug<31>2005
14:43 Jun 29, 2006
Jkt 208001
Prior to that May 2004 accident, the
Transportation Safety Board of Canada
(TSB) investigated a fatal accident in
which a Eurocopter Model AS350B2
helicopter experienced hydraulic
system failure and crashed. Examination
of the installed drive belt showed that
it had failed at the manufacturing seam,
similar to the drive belt involved in the
May 2004 accident. The TSB’s further
examinations showed that similar inservice, intact drive belts had extensive
cracking in the same location, but that
the one improved ‘‘Poly-V’’ drive belt
examined had no cracks. On April 22,
2004, Transport Canada issued a
Canadian AD mandating the installation
of the ‘‘Poly-V’’ drive belt.
On January 9, 2006, the National
Transportation Safety Board (NTSB)
recommended that we:
• Require operators of Eurocopter
AS–350 series helicopters to comply
with the provisions of Eurocopter
Service Bulletin AS350, No. 63.00.08,
Revision 1, dated May 7, 2004, or
subsequent revision (NTSB Safety
Recommendation No. A–05–36).
• Identify an appropriate life limit or
inspection interval for the existing
Eurocopter AS–350 hydraulic pump flat
drive belt and require Eurocopter AS–
350 operators to comply with this limit/
interval until they accomplish
Eurocopter Service Bulletin AS350, No.
63.00.08, Revision 1, dated May 7, 2004
or subsequent revisions (NTSB Safety
Recommendation No. A–05–37).
Eurocopter has issued the following:
• Service Bulletin No. 63.00.08, dated
May 27, 2002, which specifies installing
a poly-v type drive belt on the driving
hydraulic pump; and
• Service Bulletin No. 29.00.04,
Revision 1, dated January 27, 2004,
which specifies reducing the lubrication
interval and installing an O-ring seal in
the groove of the hydraulic pump drive
shaft in order to prevent early wear of
the splines.
This previously described unsafe
condition is likely to exist or develop on
other helicopters of the same type
designs registered in the United States.
Therefore, the proposed AD would
require the following:
• At or before the next 500-hour TIS
inspection, replacing the drive belt with
an airworthy drive belt that is not
included in the applicability of this AD,
and
• Within 110 hours TIS or at the next
scheduled lubrication interval for the
drive shaft splines, and thereafter at
intervals not to exceed 110 hours TIS or
6 months, whichever occurs first,
lubricating the drive shaft splines.
We estimate that this proposed AD
would affect 700 helicopters of U.S.
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
registry. Replacing each drive belt
would take approximately 25 work
hours and lubricating the drive shaft
splines would take approximately 1
work hour. The average labor rate is $80
an hour. Each replacement drive belt
would cost about $3,500. Based on these
figures, we estimate the total cost
impact of the proposed AD on U.S.
operators to be $4,130,000, assuming no
helicopter has been modified with the
new drive shaft belt and the splines are
lubricated 5 times in the first year.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. Additionally, this proposed AD
would 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.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
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.
We prepared a draft economic
evaluation of the estimated costs to
comply with this proposed AD. See the
DMS to examine the draft economic
evaluation.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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Federal Register / Vol. 71, No. 126 / Friday, June 30, 2006 / Proposed Rules
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Issued in Fort Worth, Texas, on June 22,
2006.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 06–5880 Filed 6–29–06; 8:45 am]
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
Administration proposes to amend part
39 of the Federal Aviation Regulations
(14 CFR part 39) as follows:
BILLING CODE 4910–13–P
PART 39—AIRWORTHINESS
DIRECTIVES
15 CFR Parts 764 and 766
DEPARTMENT OF COMMERCE
Bureau of Industry and Security
[Docket No 060511128–6128–01]
1. The authority citation for part 39
continues to read as follows:
RIN 0694–AD36
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
mstockstill on PROD1PC61 with PROPOSALS
2. Section 39.13 is amended by
adding a new airworthiness directive to
read as follows:
Eurocopter France: Docket No. FAA–2006–
25085; Directorate Identifier 2006–SW–
02–AD.
Applicability: Model AS350B, AS350B1,
AS350B2, AS350B3, AS350BA, AS350C,
AS350D, and AS350D1 helicopters with a
hydraulic drive belt (drive belt), part number
(P/N) 704A33–690–004, or a hydraulic pump
drive shaft (drive shaft), P/N 704A34–310–
006, installed, certificated in any category.
Compliance: Required as indicated.
To prevent loss of hydraulic power to the
flight control system and subsequent loss of
control of the helicopter, accomplish the
following:
(a) At or before the next 500-hour time-inservice (TIS) inspection, unless
accomplished previously, replace the drive
belt with an airworthy drive belt that is not
included in the applicability of this AD.
(b) Within 110 hours TIS or at the next
scheduled lubrication interval for the drive
shaft splines, and thereafter at intervals not
to exceed 110 hours TIS or 6 months,
whichever occurs first, lubricate the drive
shaft splines.
(c) This action reduces the interval for
lubricating the drive shaft splines from 550
hours TIS or 2 years, whichever occurs first,
to 110 hours TIS or 6 months, whichever
occurs first.
Note: Eurocopter Service Bulletin No.
63.00.08, dated May 27, 2002, and No.
29.00.04, Revision 1, dated January 27, 2004,
pertain to the subject of this AD.
(d) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the Manager, Rotorcraft
Directorate, Regulations and Guidance
Group, FAA, ATTN: Gary Roach, Aviation
Safety Engineer, Fort Worth, Texas 76193–
0111, telephone (817) 222–5130, fax (817)
222–5961, for information about previously
approved alternative methods of compliance.
14:43 Jun 29, 2006
Bureau of Industry and
Security, Commerce.
ACTION: Proposed rule.
AGENCY:
[Amended]
VerDate Aug<31>2005
Antiboycott Penalty Guidelines
Jkt 208001
SUMMARY: This proposed rule would set
forth BIS policy concerning voluntary
self disclosures of violations of part 760
(Restrictive Trade Practices or Boycotts)
of the Export Administration
Regulations (EAR) and violations of part
762 (Recordkeeping) of the EAR that
relate to part 760. This proposed rule
also would set forth the factors that the
Bureau of Industry and Security (BIS)
considers when deciding whether to
pursue administrative charges or settle
allegations of such violations as well as
the factors that BIS considers when
deciding what level of penalty to seek
in administrative cases.
DATES: Comments must be received by
August 29, 2006.
ADDRESSES: Comments may be made via
the Federal e-Rulemaking portal at,
https://www.regulations.gov, by e-mail
directly to BIS at
publiccomments@bis.doc.gov, via fax at
(202) 482–3355 or to U.S. Department of
Commerce, Bureau of Industry and
Security, Regulatory Policy Division,
Room 2703, 14th Street and
Pennsylvania Avenue, NW.,
Washington, DC 20230. Please refer to
RIN 0694–AD36 in all comments.
FOR FURTHER INFORMATION CONTACT:
Edward O. Weant III, Acting Director,
Office of Antiboycott Compliance,
Bureau of Industry and Security, United
States Department of Commerce, at
(202) 482–2381.
SUPPLEMENTARY INFORMATION:
Background
Part 760 of the EAR—Restrictive
Trade Practices or Boycotts—prohibits
U.S. persons from taking or knowingly
agreeing to take certain actions with
intent to comply with, further, or
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
37517
support an unsanctioned foreign
boycott. Part 760 of the EAR also
requires U.S. persons who are recipients
of requests ‘‘* * * to take any action
which has the effect of furthering or
supporting a restrictive trade practice or
boycott fostered or imposed by a foreign
country against a country friendly to the
United States or against any United
States person * * *’’ to report receipt of
those requests and whether they took
the requested action. Part 762 of the
EAR—Recordkeeping—requires, inter
alia, retention of certain documents that
contain information related to the
prohibitions or reporting requirements
of part 760. Collectively these
provisions of the EAR are referred to in
this notice as the antiboycott provisions.
BIS administers and enforces the
antiboycott provisions through its Office
of Antiboycott Compliance (OAC). This
proposed rule would: Set forth specific
procedures for voluntary self
disclosures of violations to OAC,
provide guidance about how OAC
responds to violations of the antiboycott
provisions, and describe how OAC
makes penalty determinations in the
settlement of administrative
enforcement cases related to the
antiboycott provisions.
This rule would not address
disclosure provisions or penalty
determination factors in any other
matters such as criminal prosecutions
for violations of the antiboycott
provisions or tax penalties that the
Department of Treasury may impose for
antiboycott violations that arise
pursuant to the Ribicoff Amendment to
the Tax Reform Act of 1976, as
implemented by Section 999 of the
Internal Revenue Code. Voluntary selfdisclosure provisions and guidance on
charging and penalty determinations in
settlement of administrative
enforcement cases that are not related to
the antiboycott provisions are stated
elsewhere in the EAR.
Proposed Changes to the EAR in This
Rule
This rule would create a new § 764.8
setting forth the procedures for
voluntary self-disclosure of violations of
the antiboycott provisions. It would also
create a new supplement No. 2 to part
764 that would describe how BIS
responds to violations of the antiboycott
provisions and how BIS makes penalty
determinations in the settlement of
administrative enforcement cases. The
rule would also make technical and
conforming changes to part 766.
This rule would provide specific
criteria with respect to what constitutes
a voluntary self-disclosure and how
voluntary self-disclosures relate to other
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]]>Agencies
[Federal Register Volume 71, Number 126 (Friday, June 30, 2006)]
[Proposed Rules]
[Pages 37515-37517]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5880]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25085; Directorate Identifier 2006-SW-02-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS350B,
AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, AS350D1, and AS355E
Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes adopting a new airworthiness directive
(AD) for the specified Eurocopter France (Eurocopter) model
helicopters. This proposal would require replacing a certain hydraulic
drive belt (drive belt). Also proposed is reducing the lubrication time
interval for a certain hydraulic pump drive shaft (drive shaft). This
proposal is prompted by in-flight failures of the drive belt and the
drive shaft. The actions specified by this proposed AD are intended to
prevent in-flight failure of the drive belt or drive shaft, loss of
hydraulic power to the flight control system, and subsequent loss of
control of the helicopter.
DATES: Comments must be received on or before August 29, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically;
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically;
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590;
Fax: 202-493-2251; or
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
You may get the service information identified in this proposed AD
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie,
Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527.
You may examine the comments to this proposed AD in the AD docket
on the Internet at https://dms.dot.gov.
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:
Comments Invited
We invite you to submit any written data, views, or arguments
regarding this proposed AD. Send your comments to the address listed
under the caption ADDRESSES. Include the docket number ``FAA-2006-
25085, Directorate Identifier 2006-SW-02-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date
[[Page 37516]]
and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed rulemaking. Using the search
function of our docket Web site, you can find and read the comments to
any of our dockets, including the name of the individual who sent or
signed the comment. You may review the DOT's complete Privacy Act
Statement in the Federal Register published on April 11, 2000 (65 FR
19477-78), or you may visit https://dms.dot.gov.
Examining the Docket
You may examine the docket that contains the proposed AD, any
comments, and other information in person at the Docket Management
System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone 1-800-
647-5227) is located at the plaza level of the Department of
Transportation Nassif Building in Room PL-401 at 400 Seventh Street,
SW., Washington, DC. Comments will be available in the AD docket
shortly after the DMS receives them.
Discussion
On May 4, 2004, a Eurocopter Model AS350BA helicopter lost
hydraulic system power, resulting in a non-fatal accident. An
investigation of the accident showed that the drive belt, part number
(P/N) 704A33-690-004, failed in-flight, approximately 160 hours short
of its 600-hour time-in-service (TIS) life limit. Further
investigations showed that the drive belt had been installed inside out
and the exterior surface, as installed, had numerous lateral cracks.
Historical records from both the FAA's Service Difficulty Report
database and the National Transportation Safety Board's Accidents and
Incidents database showed that 43 failures or replacements of the
affected P/Ned drive belts occurred between February 1995 and January
2006. Twenty of the affected drive belts were replaced because they
were found prematurely stretched or worn past their service limits and
the remaining drive belts failed in-flight after averaging 277 hours
TIS. These in-flight failures resulted in loss of hydraulic system
pressure that required the pilots to make emergency landings; three of
those in-flight failures, including the failure on May 4, 2004,
resulted in accidents.
Prior to that May 2004 accident, the Transportation Safety Board of
Canada (TSB) investigated a fatal accident in which a Eurocopter Model
AS350B2 helicopter experienced hydraulic system failure and crashed.
Examination of the installed drive belt showed that it had failed at
the manufacturing seam, similar to the drive belt involved in the May
2004 accident. The TSB's further examinations showed that similar in-
service, intact drive belts had extensive cracking in the same
location, but that the one improved ``Poly-V'' drive belt examined had
no cracks. On April 22, 2004, Transport Canada issued a Canadian AD
mandating the installation of the ``Poly-V'' drive belt.
On January 9, 2006, the National Transportation Safety Board (NTSB)
recommended that we:
Require operators of Eurocopter AS-350 series helicopters
to comply with the provisions of Eurocopter Service Bulletin AS350, No.
63.00.08, Revision 1, dated May 7, 2004, or subsequent revision (NTSB
Safety Recommendation No. A-05-36).
Identify an appropriate life limit or inspection interval
for the existing Eurocopter AS-350 hydraulic pump flat drive belt and
require Eurocopter AS-350 operators to comply with this limit/interval
until they accomplish Eurocopter Service Bulletin AS350, No. 63.00.08,
Revision 1, dated May 7, 2004 or subsequent revisions (NTSB Safety
Recommendation No. A-05-37).
Eurocopter has issued the following:
Service Bulletin No. 63.00.08, dated May 27, 2002, which
specifies installing a poly-v type drive belt on the driving hydraulic
pump; and
Service Bulletin No. 29.00.04, Revision 1, dated January
27, 2004, which specifies reducing the lubrication interval and
installing an O-ring seal in the groove of the hydraulic pump drive
shaft in order to prevent early wear of the splines.
This previously described unsafe condition is likely to exist or
develop on other helicopters of the same type designs registered in the
United States. Therefore, the proposed AD would require the following:
At or before the next 500-hour TIS inspection, replacing
the drive belt with an airworthy drive belt that is not included in the
applicability of this AD, and
Within 110 hours TIS or at the next scheduled lubrication
interval for the drive shaft splines, and thereafter at intervals not
to exceed 110 hours TIS or 6 months, whichever occurs first,
lubricating the drive shaft splines.
We estimate that this proposed AD would affect 700 helicopters of
U.S. registry. Replacing each drive belt would take approximately 25
work hours and lubricating the drive shaft splines would take
approximately 1 work hour. The average labor rate is $80 an hour. Each
replacement drive belt would cost about $3,500. Based on these figures,
we estimate the total cost impact of the proposed AD on U.S. operators
to be $4,130,000, assuming no helicopter has been modified with the new
drive shaft belt and the splines are lubricated 5 times in the first
year.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. Additionally, this proposed
AD would 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.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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.
We prepared a draft economic evaluation of the estimated costs to
comply with this proposed AD. See the DMS to examine the draft economic
evaluation.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
[[Page 37517]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
Eurocopter France: Docket No. FAA-2006-25085; Directorate Identifier
2006-SW-02-AD.
Applicability: Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA,
AS350C, AS350D, and AS350D1 helicopters with a hydraulic drive belt
(drive belt), part number (P/N) 704A33-690-004, or a hydraulic pump
drive shaft (drive shaft), P/N 704A34-310-006, installed,
certificated in any category.
Compliance: Required as indicated.
To prevent loss of hydraulic power to the flight control system
and subsequent loss of control of the helicopter, accomplish the
following:
(a) At or before the next 500-hour time-in-service (TIS)
inspection, unless accomplished previously, replace the drive belt
with an airworthy drive belt that is not included in the
applicability of this AD.
(b) Within 110 hours TIS or at the next scheduled lubrication
interval for the drive shaft splines, and thereafter at intervals
not to exceed 110 hours TIS or 6 months, whichever occurs first,
lubricate the drive shaft splines.
(c) This action reduces the interval for lubricating the drive
shaft splines from 550 hours TIS or 2 years, whichever occurs first,
to 110 hours TIS or 6 months, whichever occurs first.
Note: Eurocopter Service Bulletin No. 63.00.08, dated May 27,
2002, and No. 29.00.04, Revision 1, dated January 27, 2004, pertain
to the subject of this AD.
(d) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Manager, Rotorcraft Directorate, Regulations and
Guidance Group, FAA, ATTN: Gary Roach, Aviation Safety Engineer,
Fort Worth, Texas 76193-0111, telephone (817) 222-5130, fax (817)
222-5961, for information about previously approved alternative
methods of compliance.
Issued in Fort Worth, Texas, on June 22, 2006.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 06-5880 Filed 6-29-06; 8:45 am]
BILLING CODE 4910-13-P
