Airworthiness Directives; Eurocopter France Model SA341G, SA342J, and SA-360C Helicopters, 27215-27216 [E6-7096]
Download as PDF
Federal Register / Vol. 71, No. 90 / Wednesday, May 10, 2006 / Proposed Rules
Issued in Fort Worth, Texas, on May 1,
2006.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E6–7092 Filed 5–9–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24733; Directorate
Identifier 2005–SW–08–AD]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Model SA341G, SA342J, and
SA–360C Helicopters
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This amendment proposes
superseding an existing airworthiness
directive (AD) for the specified
Eurocopter France (ECF) model
helicopters that currently requires
replacing each affected main rotor head
torsion tie bar (tie bar) with an
airworthy tie bar and revising the
limitations section of the maintenance
manual by adding life limits for certain
tie bars. This action would retain the
current requirements and reduce life
limits of another part-numbered tie bar.
This proposal is prompted by the FAA
determination, after reviewing the
manufacturer’s data, that another partnumbered tie bar should be included in
the applicability of the AD. The actions
specified by the proposed AD are
intended to prevent failure of a tie bar,
loss of a main rotor blade, and
subsequent loss of control of the
helicopter.
SUMMARY:
Comments must be received on
or before July 10, 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
rmajette on PROD1PC67 with PROPOSALS
DATES:
VerDate Aug<31>2005
14:25 May 09, 2006
Jkt 208001
• 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.
Examining the Docket
You may examine the docket that
contains this AD, any comments, and
other information on the Internet at
https://dms.dot.gov, or at the Docket
Management System (DMS), U.S.
Department of Transportation, 400
Seventh Street SW., Room PL–401, on
the plaza level of the Nassif Building,
Washington, DC.
Gary
Roach, Aviation Safety Engineer, FAA,
Rotorcraft Directorate, Rotorcraft
Standards Staff, Fort Worth, Texas
76193–0111, telephone (817) 222–5130,
fax (817) 222–5961.
FOR FURTHER INFORMATION CONTACT:
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–2006–24733, Directorate
Identifier 2005–SW–08–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
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.
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
27215
Discussion
On April 11, 2002, we issued AD
2002–08–16 (67 FR 19640, April 23,
2002), Amendment 39–12725, to
supersede AD 2001–19–51 (66 FR
58663, November 23, 2001),
Amendment 39–12508. AD 2001–19–51
was published after we issued
Emergency AD 2001–19–51 on
September 21, 2001. AD 2001–19–51
requires removal of certain partnumbered tie bars and adds a life limit
for other part-numbered tie bars. AD
2002–08–16 retained requirements
removing certain part-numbered tie bars
and further reduced the life of the tie
bars. Those actions were prompted by
an accident involving an ECF Model
SA341G helicopter due to the failure of
a tie bar. The ECF Model SA342J and
SA–360C helicopters have tie bars
identical to the one that failed on the
ECF Model SA341G helicopter. The
requirements of the current AD are
intended to prevent failure of a tie bar,
loss of a main rotor blade, and
subsequent loss of control of the
helicopter.
Since issuing that AD, the Direction
Generale De L’Aviation Civile (DGAC),
the airworthiness authority for France,
notified the FAA of another affected tiebar, part number (P/N) 704A33–633–
270, and additional flight restrictions for
the new-affected tie bar.
Also, since issuing that AD, ECF has
issued Alert Service Bulletin No. 01.29,
dated December 4, 2002 (ASB), for the
Models SA341G and SA342J
helicopters. The ASB cancels Alert
Telex (AT) No. 01.28, dated August 7,
2001, and supersedes AT 01.29 R1,
dated December 11, 2001. The ASB
specifies additional flight restrictions
for the affected tie bars and adds tie bar,
P/N 704A33–633–270, to the ASB
effectivity. The DGAC classified this
ASB as mandatory and issued AD 2001–
587–041(A) R2, dated January 8, 2003,
for the Model SA341/342 helicopters to
ensure the continued airworthiness of
these helicopters in France.
These helicopter models are
manufactured in France and are type
certificated for operation in the United
States under the provisions of 14 CFR
21.29 and the applicable bilateral
agreement. Pursuant to the applicable
bilateral agreement, the DGAC has kept
the FAA informed of the situation
described above. The FAA has
examined the findings of the DGAC,
reviewed all available information, and
determined that AD action is necessary
for products of these type designs that
are certificated for operation in the
United States.
E:\FR\FM\10MYP1.SGM
10MYP1
27216
Federal Register / Vol. 71, No. 90 / Wednesday, May 10, 2006 / Proposed Rules
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.
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.
rmajette on PROD1PC67 with PROPOSALS
This previously described unsafe
condition is likely to exist or develop on
other helicopters of these same type
designs. Therefore, the proposed AD
would supersede AD 2002–08–16 to
retain the same requirements and would
add tie bar, P/N 704A33–633–270, to the
applicability, remove it from service
within 600 hours TIS or 2 years,
whichever occurs first, and revise the
limitations section of the maintenance
manual accordingly.
We estimate that this proposed AD
would affect 33 helicopters of U.S.
registry. The proposed actions would
take about 8 work hours per helicopter
to replace the tie bars at an average labor
rate of $65 per work hour. Required
parts would cost about $13,335 per
helicopter, assuming all 3 tie bars are
replaced. Based on these figures, we
estimate the total cost impact of the
proposed AD on U.S. operators to be
$457,215 ($13,855 per helicopter).
1. The authority citation for part 39
continues to read as follows:
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
VerDate Aug<31>2005
14:25 May 09, 2006
Jkt 208001
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
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. Section 39.13 is amended by
removing Amendment 39–12725 (67 FR
19640, April 23, 2002), and by adding
a new airworthiness directive (AD), to
read as follows:
Eurocopter France: Docket No. FAA–2006–
24733; Directorate Identifier 2005–SW–
08–AD. Supersedes AD 2002–08–16,
Amendment 39–12725, Docket No.
2001–SW–72–AD.
Applicability: Model SA341G, SA342J, and
SA–360C helicopters with a main rotor head
torsion tie bar (tie bar), part number (P/N)
341A31–4904–00, –01, –02, –03; 341A31–
4933–00, –01; 360A31–1097–02, –03; or
704A33–633–270, installed, certificated in
any category.
Compliance: Required as indicated, unless
accomplished previously.
To prevent failure of a tie bar, loss of a
main rotor blade, and subsequent loss of
control of the aircraft, do the following:
(a) Before further flight, remove each tie
bar, P/N 341A31–4904–00, –01, –02, or –03;
and 360A31–1097–02 or –03; from service.
(b) For each tie bar, P/N 341A31–4933–00
or –01:
(1) Before further flight, determine the date
of initial installation on any helicopter using
the date of manufacture if the date of
installation cannot be determined.
(2) For each tie bar with 7 or more years
time-in-service (TIS) since initial installation
on any helicopter, remove within 5 hours
TIS.
(3) For each tie bar manufactured before
1995 with less than 7 years TIS since initial
installation on any helicopter, remove before
accumulating 7 years TIS, within 300 hours
TIS, or within 1 year, whichever occurs first.
(4) For each tie bar manufactured in 1995
or subsequent years with less than 7 years
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
TIS since initial installation on any
helicopter, remove before accumulating 7
years TIS since initial installation, within
600 hours TIS, or within 2 years, whichever
occurs first.
Note 1: Eurocopter France (ECF) Alert
Telex AT 01.39 R1, dated December 11, 2001,
pertains to the subject of this AD for the
Model SA–360C helicopters.
(c) Remove each tie bar, P/N 704A33–633–
270, within 600 hours TIS, or within 2 years,
whichever occurs first.
Note 2: ECF Alert Service Bulletin 01.29,
dated December 4, 2002, pertains to the
subject of this AD for the Models SA341G
and SA342J helicopters.
(d) This AD revises the Limitations section
of the maintenance manual by adding to the
current life limit of 5000 hours TIS for tie
bars, P/N 341A31–4933–00 and –01 the
following additional alternative life limits:
(1) Seven years TIS from initial installation
on any helicopter, or
(2) For tie bars manufactured before 1995,
a life limit of 300 hours TIS or 1 year, or
(3) For P/N 341A31–4933–00 and –01, for
tie bars manufactured in 1995 or subsequent
years, a life limit of 600 hours TIS or 2 years,
whichever occurs first.
(e) This AD revises the Limitations section
of the maintenance manual by reducing the
current life limit of 1000 hours TIS for tie
bar, P/N 704A33–633–270, to a life limit of
600 hours TIS or 2 years, whichever occurs
first.
(f) Special flight permits will not be issued.
Note 3: The subject of this AD is addressed
in Direction Generale De L’Aviation Civile
(France) ADs 2001–588–047(A) R1, dated
December 26, 2001, and 2001–587–041(A)
R2, dated January 8, 2003.
Issued in Fort Worth, Texas, on April 28,
2006.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E6–7096 Filed 5–9–06; 8:45 am]
BILLING CODE 4910–13–P
ENVIRONMENTAL PROTECTION
AGENCY
40 CFR Part 271
[EPA–R03–RCRA–2006–0381; FRL–8165–6]
Virginia: Final Authorization of State
Hazardous Waste Management
Program Revisions
Environmental Protection
Agency (EPA).
ACTION: Proposed rule.
AGENCY:
SUMMARY: Virginia has applied to EPA
for final authorization of revisions to its
hazardous waste program under the
Resource Conservation and Recovery
Act (RCRA). EPA proposes to grant final
authorization to Virginia. In the ‘‘Rules
E:\FR\FM\10MYP1.SGM
10MYP1
Agencies
[Federal Register Volume 71, Number 90 (Wednesday, May 10, 2006)]
[Proposed Rules]
[Pages 27215-27216]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-7096]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24733; Directorate Identifier 2005-SW-08-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model SA341G, SA342J,
and SA-360C Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This amendment proposes superseding an existing airworthiness
directive (AD) for the specified Eurocopter France (ECF) model
helicopters that currently requires replacing each affected main rotor
head torsion tie bar (tie bar) with an airworthy tie bar and revising
the limitations section of the maintenance manual by adding life limits
for certain tie bars. This action would retain the current requirements
and reduce life limits of another part-numbered tie bar. This proposal
is prompted by the FAA determination, after reviewing the
manufacturer's data, that another part-numbered tie bar should be
included in the applicability of the AD. The actions specified by the
proposed AD are intended to prevent failure of a tie bar, loss of a
main rotor blade, and subsequent loss of control of the helicopter.
DATES: Comments must be received on or before July 10, 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.
Examining the Docket
You may examine the docket that contains this AD, any comments, and
other information on the Internet at https://dms.dot.gov, or at the
Docket Management System (DMS), U.S. Department of Transportation, 400
Seventh Street SW., Room PL-401, on the plaza level of the Nassif
Building, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 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-
24733, Directorate Identifier 2005-SW-08-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 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.
Discussion
On April 11, 2002, we issued AD 2002-08-16 (67 FR 19640, April 23,
2002), Amendment 39-12725, to supersede AD 2001-19-51 (66 FR 58663,
November 23, 2001), Amendment 39-12508. AD 2001-19-51 was published
after we issued Emergency AD 2001-19-51 on September 21, 2001. AD 2001-
19-51 requires removal of certain part-numbered tie bars and adds a
life limit for other part-numbered tie bars. AD 2002-08-16 retained
requirements removing certain part-numbered tie bars and further
reduced the life of the tie bars. Those actions were prompted by an
accident involving an ECF Model SA341G helicopter due to the failure of
a tie bar. The ECF Model SA342J and SA-360C helicopters have tie bars
identical to the one that failed on the ECF Model SA341G helicopter.
The requirements of the current AD are intended to prevent failure of a
tie bar, loss of a main rotor blade, and subsequent loss of control of
the helicopter.
Since issuing that AD, the Direction Generale De L'Aviation Civile
(DGAC), the airworthiness authority for France, notified the FAA of
another affected tie-bar, part number (P/N) 704A33-633-270, and
additional flight restrictions for the new-affected tie bar.
Also, since issuing that AD, ECF has issued Alert Service Bulletin
No. 01.29, dated December 4, 2002 (ASB), for the Models SA341G and
SA342J helicopters. The ASB cancels Alert Telex (AT) No. 01.28, dated
August 7, 2001, and supersedes AT 01.29 R1, dated December 11, 2001.
The ASB specifies additional flight restrictions for the affected tie
bars and adds tie bar, P/N 704A33-633-270, to the ASB effectivity. The
DGAC classified this ASB as mandatory and issued AD 2001-587-041(A) R2,
dated January 8, 2003, for the Model SA341/342 helicopters to ensure
the continued airworthiness of these helicopters in France.
These helicopter models are manufactured in France and are type
certificated for operation in the United States under the provisions of
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the
applicable bilateral agreement, the DGAC has kept the FAA informed of
the situation described above. The FAA has examined the findings of the
DGAC, reviewed all available information, and determined that AD action
is necessary for products of these type designs that are certificated
for operation in the United States.
[[Page 27216]]
This previously described unsafe condition is likely to exist or
develop on other helicopters of these same type designs. Therefore, the
proposed AD would supersede AD 2002-08-16 to retain the same
requirements and would add tie bar, P/N 704A33-633-270, to the
applicability, remove it from service within 600 hours TIS or 2 years,
whichever occurs first, and revise the limitations section of the
maintenance manual accordingly.
We estimate that this proposed AD would affect 33 helicopters of
U.S. registry. The proposed actions would take about 8 work hours per
helicopter to replace the tie bars at an average labor rate of $65 per
work hour. Required parts would cost about $13,335 per helicopter,
assuming all 3 tie bars are replaced. Based on these figures, we
estimate the total cost impact of the proposed AD on U.S. operators to
be $457,215 ($13,855 per helicopter).
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.
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 removing Amendment 39-12725 (67 FR
19640, April 23, 2002), and by adding a new airworthiness directive
(AD), to read as follows:
Eurocopter France: Docket No. FAA-2006-24733; Directorate Identifier
2005-SW-08-AD. Supersedes AD 2002-08-16, Amendment 39-12725, Docket
No. 2001-SW-72-AD.
Applicability: Model SA341G, SA342J, and SA-360C helicopters
with a main rotor head torsion tie bar (tie bar), part number (P/N)
341A31-4904-00, -01, -02, -03; 341A31-4933-00, -01; 360A31-1097-02,
-03; or 704A33-633-270, installed, certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of a tie bar, loss of a main rotor blade, and
subsequent loss of control of the aircraft, do the following:
(a) Before further flight, remove each tie bar, P/N 341A31-4904-
00, -01, -02, or -03; and 360A31-1097-02 or -03; from service.
(b) For each tie bar, P/N 341A31-4933-00 or -01:
(1) Before further flight, determine the date of initial
installation on any helicopter using the date of manufacture if the
date of installation cannot be determined.
(2) For each tie bar with 7 or more years time-in-service (TIS)
since initial installation on any helicopter, remove within 5 hours
TIS.
(3) For each tie bar manufactured before 1995 with less than 7
years TIS since initial installation on any helicopter, remove
before accumulating 7 years TIS, within 300 hours TIS, or within 1
year, whichever occurs first.
(4) For each tie bar manufactured in 1995 or subsequent years
with less than 7 years TIS since initial installation on any
helicopter, remove before accumulating 7 years TIS since initial
installation, within 600 hours TIS, or within 2 years, whichever
occurs first.
Note 1: Eurocopter France (ECF) Alert Telex AT 01.39 R1, dated
December 11, 2001, pertains to the subject of this AD for the Model
SA-360C helicopters.
(c) Remove each tie bar, P/N 704A33-633-270, within 600 hours
TIS, or within 2 years, whichever occurs first.
Note 2: ECF Alert Service Bulletin 01.29, dated December 4,
2002, pertains to the subject of this AD for the Models SA341G and
SA342J helicopters.
(d) This AD revises the Limitations section of the maintenance
manual by adding to the current life limit of 5000 hours TIS for tie
bars, P/N 341A31-4933-00 and -01 the following additional
alternative life limits:
(1) Seven years TIS from initial installation on any helicopter,
or
(2) For tie bars manufactured before 1995, a life limit of 300
hours TIS or 1 year, or
(3) For P/N 341A31-4933-00 and -01, for tie bars manufactured in
1995 or subsequent years, a life limit of 600 hours TIS or 2 years,
whichever occurs first.
(e) This AD revises the Limitations section of the maintenance
manual by reducing the current life limit of 1000 hours TIS for tie
bar, P/N 704A33-633-270, to a life limit of 600 hours TIS or 2
years, whichever occurs first.
(f) Special flight permits will not be issued.
Note 3: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) ADs 2001-588-047(A) R1, dated
December 26, 2001, and 2001-587-041(A) R2, dated January 8, 2003.
Issued in Fort Worth, Texas, on April 28, 2006.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E6-7096 Filed 5-9-06; 8:45 am]
BILLING CODE 4910-13-P