Airworthiness Directives; Bell Helicopter Textron Canada Model 206A, B, L, L-1, L-3, and L-4 Helicopters, 60246-60250 [05-20681]
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60246
Federal Register / Vol. 70, No. 199 / Monday, October 17, 2005 / Proposed Rules
PART 39—AIRWORTHINESS
DIRECTIVES
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
1. The authority citation for part 39
continues to read as follows:
14 CFR Part 39
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
RIN 2120–AA64
2. Section 39.13 is amended by
adding a new airworthiness directive to
read as follows:
Eurocopter France: Docket No. FAA–2005–
22696; Directorate Identifier 2004–SW–
46–AD.
Applicability: Model EC 155B and B1
helicopters, certificated in any category.
Compliance: Required as indicated, unless
accomplished previously.
To prevent interference of the wiring with
the structure resulting in an electrical short
circuit, failure of the landing gear to extend,
and an emergency landing, accomplish the
following:
(a) Within 50 hours time-in-service (TIS),
(1) Inspect the wiring of panel 12 Alpha
(wiring) electrical cable bundle for wear. If
wear is present, replace the worn cable
bundle with an airworthy cable bundle by
following the Accomplishment Instructions,
paragraphs 2.A.1, 2.B.1, and 2.B.2 of
Eurocopter Alert Service Bulletin EC155,
Revision 1, dated May 14, 2004 (ASB).
Note 1: Aircraft Maintenance Manual
(AMM): Tasks 24.00.00.911 and 32–30–00–
721 and Standard Practices Manual (MTC)
Work Cards 20.02.01.415, 20.06.01.310,
20.06.01.406, and 20.02.06.409 pertain to the
subject of this AD.
(2) Modify the routing of the electrical
wiring (MOD 0739C28) and replace spreaders
and spacers by following the
Accomplishment Instructions, paragraph
2.B.3. through 2.B.9. of the ASB.
(b) 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 Safety Management Group,
FAA, for information about previously
approved alternative methods of compliance.
(c) Special flight permits will not be
issued.
Note 2: The subject of this AD is addressed
in Direction Generale de l’Aviation Civile
(France) AD F–2004–057 R1, dated July 21,
2004.
Issued in Fort Worth, Texas, on October 7,
2005.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 05–20679 Filed 10–14–05; 8:45 am]
BILLING CODE 4910–13–P
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[Docket No. FAA–2005–22696; Directorate
Identifier 2005–SW–22–AD]
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Airworthiness Directives; Bell
Helicopter Textron Canada Model
206A, B, L, L–1, L–3, and L–4
Helicopters
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: This document proposes
superseding an existing airworthiness
directive (AD) for the specified Bell
Helicopter Textron Canada (BHTC)
model helicopters. That AD currently
requires an initial inspection and at
specified intervals checks and
inspections of the tail rotor blade (blade)
for a deformation, a crack, and a bent or
deformed tail rotor weight (weight).
Also, that AD requires, before further
flight, replacing each blade with an
airworthy blade if a deformation, a
crack, or a bent or deformed weight is
found. This action would contain the
same actions as the existing AD and
would also propose adding certain
serial-numbered blades to the
applicability that were inadvertently
omitted from the current AD and would
require replacing each affected blade,
which would be terminating action.
This proposal is prompted by three
reports of skin cracks originating near
the blade trailing edge balance weight.
The actions specified by the proposed
AD are intended to prevent blade failure
and subsequent loss of control of the
helicopter.
Comments must be received on
or before December 16, 2005.
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,
DATES:
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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 Bell
Helicopter Textron Canada, 12,800 Rue
de l’Avenir, Mirabel, Quebec J7J1R4,
telephone (450) 437–2862 or (800) 363–
8023, fax (450) 433–0272
• 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:
Sharon Miles, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations
and Guidance Group, Fort Worth, Texas
76193–0111, telephone (817) 222–5122,
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–2005–22696, Directorate
Identifier 2005–SW–22–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. The postcard will be
date stamped and returned to the
commenter.
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
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Seventh Street, SW., Washington, DC.
Comments will be available in the AD
docket shortly after the DMS receives
them.
Discussion
On November 22, 2004, the FAA
issued AD 2004–24–08, Docket No.
2004–SW–12–AD, Amendment 39–
13884 (69 FR 69810, December 1, 2004).
That AD requires an initial inspection
and at intervals not to exceed 12 hours
time-in-service (TIS), a 10X inspection
or at intervals not to exceed 24 hours
TIS a 10X inspection and a 3-hour TIS
check between each 24 hour TIS
inspection of the blade for a
deformation, a crack, and a bent or
deformed weight. Also, that AD
requires, before further flight, replacing
each blade with an airworthy blade if a
deformation, a crack, or a bent or
deformed weight is found. That action
was prompted by three reports of skin
cracks originating near the blade trailing
edge balance weight. The requirements
of that AD are intended to prevent blade
failure and subsequent loss of control of
the helicopter.
Since issuing AD 2004–24–08, BHTC
has issued Alert Service Bulletin 206–
04–100 for Bell Model 206A and B
helicopters, and 206L–04–127 for Bell
Model 206L series helicopters, both
Revision C, both dated March 5, 2005
(ASB). These ASBs add two warnings in
the compliance section specifying
returning the blade for balancing to
Rotor Blades, Inc., and introduce new
skin damage limits that supersede the
previous damage limits. The ASB also
gives a new address for Rotor Blades
Inc.
When we issued AD 2004–24–08, we
intentionally did not include the longterm requirement (no later than April
27, 2007) for removing and sending the
affected blades to Rotor Blades, Inc. as
specified by the manufacturer. We are
including in this proposal a long-term
requirement that the affected blades be
replaced on or before April 27, 2007, as
terminating action. This will allow
public comments before any adoption of
the long-term proposal. Additionally, in
AD 2004–24–08, we inadvertently
omitted blade serial numbers 10102
through 10114 from the applicability.
We propose to correct that oversight
with this action.
Transport Canada, the airworthiness
authority for Canada, notified the FAA
that an unsafe condition may exist on
these helicopter models. Transport
Canada advises of three reports of skin
cracks originating near the blade trailing
edge balance weight. Two of the
occurrences caused a loss of the weight
and a strip of material along the trailing
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11:41 Oct 14, 2005
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edge leading to an imbalance, which
caused the fracture of three of the four
tail rotor gearbox attachments. One of
these occurrences resulted in the
gearbox shifting that caused failure of
the drive shaft and resulting loss of yaw
control. Transport Canada issued AD
No. CF–2004–05R1, dated June 28,
2004, to ensure the continued
airworthiness of these helicopters in
Canada.
These helicopter models are
manufactured in Canada 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, Transport Canada
has kept the FAA informed of the
situation described above. The FAA has
examined the findings of Transport
Canada, 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.
Interested persons were afforded an
opportunity to participate in the making
of AD 2004–24–08, Amendment 39–
13884, Docket No. 2004–SW–12–AD,
which we are proposing to supersede.
Due consideration has been given to the
one comment received.
The commenter expresses concern
about the 12-hour blade inspection by a
mechanic and states the inspection will
make this helicopter unsuitable for its
intended use. The commenter states the
alternate pilot check and mechanic
inspection would require them to shut
down 4–5 times each day increasing
engine cycles. The commenter further
states that since the only difference
between the pilot check and the
mechanic inspection is the 10X
magnifier, pilots need to be certified to
perform the 12-hour inspection.
While the FAA agrees the checks and
inspections could increase engine
cycles, the primary purpose of issuing
an AD is to correct an unsafe condition.
However, the terminating action
proposed in this AD would eliminate
the current mandated inspections. We
do not agree that pilots need to be
certified to perform inspections. Current
FAA policy allows pilots holding at
least a private pilot certificate to
perform checks that do not require the
use of tools, precision measuring
equipment, training, pilot logbook
endorsements, or reference to technical
data not contained in the body of the
AD. Pilots may only perform simple
maintenance tasks that do not require
special maintenance training. The
inspection in the AD requires the use of
a 10X or higher magnifying glass, which
is not considered a simple visual check.
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60247
In the interest of safety, the inspection
must occur at the specified intervals and
be performed by a qualified mechanic
until the terminating action is
accomplished.
The 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 2004–24–08 to
require:
• Before further flight, unless
accomplished previously, and before
installing any blade with an affected
part number and serial number (S/N),
cleaning the blade. Then, using a 10X or
higher magnifying glass, inspecting both
sides of each blade for a deformation, a
crack, and a bent or deformed weight.
• Thereafter, cleaning both sides of
each blade and using a 10X or higher
magnifying glass, inspecting for a
deformation, a crack, and a bent or
deformed weight as follows:
• At intervals not to exceed 12 hours
TIS, or
• At intervals not to exceed 24 hours
TIS and checking both sides of each
blade for a deformation, a crack, and a
bent or deformed weight at intervals not
to exceed 3 hours TIS between
inspections. An owner/operator (pilot)
holding at least a private pilot certificate
may perform the 3-hour TIS check for
deformed or cracked blades and for bent
or deformed weights. Pilots may
perform these checks because they
require no tools, can be done by
observation, and can be done equally
well by a pilot or a mechanic. However,
the pilot must enter compliance with
these requirements into the helicopter
maintenance records by following 14
CFR 43.11 and 91.417(a)(2)(v).
• Before further flight, replacing each
blade with an airworthy blade if you
find a deformation, a crack, or a bent or
deformed weight.
• On or before April 27, 2007,
replacing each affected blade with an
airworthy blade that is identified by a
‘‘V’’ at the end of the blade S/N or an
airworthy blade with a S/N other than
one listed in the applicability section of
this AD.
Replacing each blade with an
airworthy blade that is identified by a
‘‘V’’ at the end of the blade S/N or an
airworthy blade with a S/N other than
one listed in the applicability section of
this AD constitutes terminating action
for the requirements of this AD.
The FAA estimates that this proposed
AD would:
• Affect 2194 helicopters of U.S.
registry,
• Take about 1⁄4 work hour for a blade
check or inspection, and
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Federal Register / Vol. 70, No. 199 / Monday, October 17, 2005 / Proposed Rules
• Take 3 work hours to replace a
blade at an average labor rate of $65 per
work hour. Required parts would cost
about $5848 per helicopter. (In its ASB,
the manufacturer states it will give
warranty credit based on hour usage on
the blade with remaining life hours and
other restrictions.) Based on these
figures, we estimate the total cost
impact of the proposed AD on U.S.
operators to be $19,989,973. Costs
assume—200 pilot checks, 26 mechanic
inspections, and one blade replacement
for 90 percent of the fleet with a
nonconforming blade.
under the criteria of the Regulatory
Flexibility Act. A copy of the draft
regulatory evaluation prepared for this
action is contained in the Rules Docket.
A copy of it may be obtained by
contacting the Rules Docket at the
location provided under the caption
ADDRESSES.
Authority for This Rulemaking
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:
Regulatory Findings
The regulations proposed herein
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. Therefore,
it is determined that this proposal
would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I
certify that this 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); on a
substantial number of small entities
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.
Model 206A & B; Blade, P/N 206–016–201–
133, S/N with prefix ‘‘CS’’ and no ‘‘V’’ suffix
Model 206A, B, L, L–1, L–3, & L–4; Blade, P/N P/N 206–016–201–131, S/N with prefix ‘‘CS’’
and no ‘‘V’’ suffix
1381
1492
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7248
7272
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7821
7835
7841
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8119
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8178
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8298
8370
8378
8419
8421
8425
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8441
through 1442
through 1517
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through 1831
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1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
Sfmt 4702
[Amended]
2. Section 39.13 is amended by
removing Amendment 39–13884 (69 FR
69810, December 1, 2004), and by
adding a new airworthiness directive
(AD), to read as follows:
Bell Helicopter Textron Canada: Docket No.
FAA–2005, Directorate Identifier 2005–
SW–22–AD. Supersedes AD 2004–24–08,
Amendment 39–13884, Docket No.
2004–SW–12–AD.
Applicability: Model 206A, B, L, L–1, L–3,
and L–4 helicopters, with a tail rotor blade
(blade) with the following part number (P/N)
and serial number (S/N) installed,
certificated in any category.
10174
10220
10232
10235
10237
10244
10245
10248
10250
10266
10270
10276
10280
10284
10296
10300
10332
10333
10335
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10351
10363
10367
10373
10374
10377
10387
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10414
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through 8428
through 8438
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PART 39—AIRWORTHINESS
DIRECTIVES
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through 10427
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60249
Model 206A & B; Blade, P/N 206–016–201–
133, S/N with prefix ‘‘CS’’ and no ‘‘V’’ suffix
Model 206A, B, L, L–1, L–3, & L–4; Blade, P/N P/N 206–016–201–131, S/N with prefix ‘‘CS’’
and no ‘‘V’’ suffix
1909
1915
1916
1919
1924
1928
1933
1934
1943
1945
1947
1948
1952
1960
1962
8443
8445 through 8447
8449 through 8606
8608 through 8622
8624 through 8626
8628 through 8632
8635 through 8653
8655 through 8686
8690
8692 through 8700
8703 through 8715
8717 through 8722
8724 through 8742
8745 through 8828
8830 through 8835
8838 through 8840
8842 through 8881
8883 through 9032
9034 through 9139
9141 through 9198
9200
9202 through 9302
9304 through 9339
9341 through 9371
9373 through 9411
9413
9415 through 9417
9419 through 9496
9498 through 9585
9587 through 9594
9596 through 9618
9621 through 9629
9632 through 9642
9645 through 9651
9653 through 9673
9675 through 9707
9709 through 9724
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9741 through 9748
9751 through 9785
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9849 through 9928
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9955 through 9972
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9991 through 9995
9997 through 10004
10006 through 10009
10011
10013 through 10018
10021 through 10030
10034
10036 through 10057
10061 through 10082
10090 through 10092
10094 through 10100
10102 through 10114
10116
10119
10121
10123 through 10134
10136 through 10140
10142 through 10144
10146 through 10172
through 1912
through 1921
through 1931
through 1939
through 1957
through 1965
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Compliance: Required as indicated.
To prevent blade failure and subsequent
loss of control of the helicopter, do the
following:
(a) Before further flight, unless
accomplished previously, and before
installing any blade with a P/N and S/N
listed in the applicability section of this AD,
clean the blade. Using a 10X or higher
magnifying glass, inspect both sides of each
blade for a deformation, a crack, and a bent
or deformed weight in the area shown in
Figure 1 of this AD.
(b) After doing paragraph (a) of this AD, at
the following intervals, clean both sides of
each blade and do either paragraph (1) or (2)
as follows:
(1) At intervals not to exceed 12 hours
time-in-service (TIS), using a 10X or higher
magnifying glass, inspect both sides of each
blade for a deformation, a crack, and a bent
or deformed weight in the area shown in
Figure 1 of this AD, or
(2) Inspect and check both sides of each
blade for a deformation, a crack, and a bent
or deformed weight in the area shown in
Figure 1 of this AD as follows:
(i) Using a 10X or higher magnifying glass,
inspect at intervals not to exceed 24 hours
TIS, and
(ii) Check at intervals not to exceed 3 hours
TIS between the inspections required by
paragraph (b)(2)(i) of this AD. An owner/
operator (pilot), holding at least a private
pilot certificate, may perform this visual
check and must enter compliance with this
paragraph into the helicopter maintenance
records by following 14 CFR sections 43.11
and 91.417(a)(2)(v).
(c) Before further flight, replace any blade
that has a deformation, a crack, or a bent or
deformed weight with an airworthy blade.
Note 2: Bell Helicopter Textron Alert
Service Bulletin No. 206–04–100 for Model
206A and B and No. 206L–04–127 for Model
206L series, both Revision C, both dated
March 5, 2005, pertain to the subject of this
AD.
(d) On or before April 27, 2007, for any
affected part-numbered blade with a S/N
listed in the applicability section of this AD:
(1) Replace the blade with a blade that has
a S/N other than one listed in the
applicability section of this AD, or
(2) Replace the blade with a blade that has
a S/N listed in the applicability section of
this AD and also has a ‘‘V’’ suffix.
(e) Replacing each blade with an airworthy
blade as required by paragraph (d) of this AD
constitutes terminating action for the
requirements of this AD.
(f) 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 Safety Management Group,
Rotorcraft Directorate, FAA, for information
about previously approved alternative
methods of compliance.
Note 3: The subject of this AD is addressed
in Transport Canada (Canada) AD No. CF–
2004–05R1, dated June 28, 2004.
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Issued in Fort Worth, Texas, on October 7,
2005.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 05–20681 Filed 10–14–05; 8:45 am]
BILLING CODE 4910–13–P
E:\FR\FM\17OCP1.SGM
17OCP1
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VerDate Aug<31>2005
Note 1: Paint irregularities on the blade
may indicate a crack.
]]>Agencies
[Federal Register Volume 70, Number 199 (Monday, October 17, 2005)]
[Proposed Rules]
[Pages 60246-60250]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-20681]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22696; Directorate Identifier 2005-SW-22-AD]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada Model
206A, B, L, L-1, L-3, and L-4 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes superseding an existing airworthiness
directive (AD) for the specified Bell Helicopter Textron Canada (BHTC)
model helicopters. That AD currently requires an initial inspection and
at specified intervals checks and inspections of the tail rotor blade
(blade) for a deformation, a crack, and a bent or deformed tail rotor
weight (weight). Also, that AD requires, before further flight,
replacing each blade with an airworthy blade if a deformation, a crack,
or a bent or deformed weight is found. This action would contain the
same actions as the existing AD and would also propose adding certain
serial-numbered blades to the applicability that were inadvertently
omitted from the current AD and would require replacing each affected
blade, which would be terminating action. This proposal is prompted by
three reports of skin cracks originating near the blade trailing edge
balance weight. The actions specified by the proposed AD are intended
to prevent blade failure and subsequent loss of control of the
helicopter.
DATES: Comments must be received on or before December 16, 2005.
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 Bell Helicopter Textron Canada, 12,800 Rue de
l'Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437-2862 or (800)
363-8023, fax (450) 433-0272
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: Sharon Miles, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group,
Fort Worth, Texas 76193-0111, telephone (817) 222-5122, 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-2005-
22696, Directorate Identifier 2005-SW-22-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. The postcard will be
date stamped and returned to the commenter.
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
[[Page 60247]]
Seventh Street, SW., Washington, DC. Comments will be available in the
AD docket shortly after the DMS receives them.
Discussion
On November 22, 2004, the FAA issued AD 2004-24-08, Docket No.
2004-SW-12-AD, Amendment 39-13884 (69 FR 69810, December 1, 2004). That
AD requires an initial inspection and at intervals not to exceed 12
hours time-in-service (TIS), a 10X inspection or at intervals not to
exceed 24 hours TIS a 10X inspection and a 3-hour TIS check between
each 24 hour TIS inspection of the blade for a deformation, a crack,
and a bent or deformed weight. Also, that AD requires, before further
flight, replacing each blade with an airworthy blade if a deformation,
a crack, or a bent or deformed weight is found. That action was
prompted by three reports of skin cracks originating near the blade
trailing edge balance weight. The requirements of that AD are intended
to prevent blade failure and subsequent loss of control of the
helicopter.
Since issuing AD 2004-24-08, BHTC has issued Alert Service Bulletin
206-04-100 for Bell Model 206A and B helicopters, and 206L-04-127 for
Bell Model 206L series helicopters, both Revision C, both dated March
5, 2005 (ASB). These ASBs add two warnings in the compliance section
specifying returning the blade for balancing to Rotor Blades, Inc., and
introduce new skin damage limits that supersede the previous damage
limits. The ASB also gives a new address for Rotor Blades Inc.
When we issued AD 2004-24-08, we intentionally did not include the
long-term requirement (no later than April 27, 2007) for removing and
sending the affected blades to Rotor Blades, Inc. as specified by the
manufacturer. We are including in this proposal a long-term requirement
that the affected blades be replaced on or before April 27, 2007, as
terminating action. This will allow public comments before any adoption
of the long-term proposal. Additionally, in AD 2004-24-08, we
inadvertently omitted blade serial numbers 10102 through 10114 from the
applicability. We propose to correct that oversight with this action.
Transport Canada, the airworthiness authority for Canada, notified
the FAA that an unsafe condition may exist on these helicopter models.
Transport Canada advises of three reports of skin cracks originating
near the blade trailing edge balance weight. Two of the occurrences
caused a loss of the weight and a strip of material along the trailing
edge leading to an imbalance, which caused the fracture of three of the
four tail rotor gearbox attachments. One of these occurrences resulted
in the gearbox shifting that caused failure of the drive shaft and
resulting loss of yaw control. Transport Canada issued AD No. CF-2004-
05R1, dated June 28, 2004, to ensure the continued airworthiness of
these helicopters in Canada.
These helicopter models are manufactured in Canada 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, Transport Canada has kept the FAA
informed of the situation described above. The FAA has examined the
findings of Transport Canada, 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.
Interested persons were afforded an opportunity to participate in
the making of AD 2004-24-08, Amendment 39-13884, Docket No. 2004-SW-12-
AD, which we are proposing to supersede. Due consideration has been
given to the one comment received.
The commenter expresses concern about the 12-hour blade inspection
by a mechanic and states the inspection will make this helicopter
unsuitable for its intended use. The commenter states the alternate
pilot check and mechanic inspection would require them to shut down 4-5
times each day increasing engine cycles. The commenter further states
that since the only difference between the pilot check and the mechanic
inspection is the 10X magnifier, pilots need to be certified to perform
the 12-hour inspection.
While the FAA agrees the checks and inspections could increase
engine cycles, the primary purpose of issuing an AD is to correct an
unsafe condition. However, the terminating action proposed in this AD
would eliminate the current mandated inspections. We do not agree that
pilots need to be certified to perform inspections. Current FAA policy
allows pilots holding at least a private pilot certificate to perform
checks that do not require the use of tools, precision measuring
equipment, training, pilot logbook endorsements, or reference to
technical data not contained in the body of the AD. Pilots may only
perform simple maintenance tasks that do not require special
maintenance training. The inspection in the AD requires the use of a
10X or higher magnifying glass, which is not considered a simple visual
check. In the interest of safety, the inspection must occur at the
specified intervals and be performed by a qualified mechanic until the
terminating action is accomplished.
The 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 2004-24-08 to require:
Before further flight, unless accomplished previously, and
before installing any blade with an affected part number and serial
number (S/N), cleaning the blade. Then, using a 10X or higher
magnifying glass, inspecting both sides of each blade for a
deformation, a crack, and a bent or deformed weight.
Thereafter, cleaning both sides of each blade and using a
10X or higher magnifying glass, inspecting for a deformation, a crack,
and a bent or deformed weight as follows:
At intervals not to exceed 12 hours TIS, or
At intervals not to exceed 24 hours TIS and checking both
sides of each blade for a deformation, a crack, and a bent or deformed
weight at intervals not to exceed 3 hours TIS between inspections. An
owner/operator (pilot) holding at least a private pilot certificate may
perform the 3-hour TIS check for deformed or cracked blades and for
bent or deformed weights. Pilots may perform these checks because they
require no tools, can be done by observation, and can be done equally
well by a pilot or a mechanic. However, the pilot must enter compliance
with these requirements into the helicopter maintenance records by
following 14 CFR 43.11 and 91.417(a)(2)(v).
Before further flight, replacing each blade with an
airworthy blade if you find a deformation, a crack, or a bent or
deformed weight.
On or before April 27, 2007, replacing each affected blade
with an airworthy blade that is identified by a ``V'' at the end of the
blade S/N or an airworthy blade with a S/N other than one listed in the
applicability section of this AD.
Replacing each blade with an airworthy blade that is identified by
a ``V'' at the end of the blade S/N or an airworthy blade with a S/N
other than one listed in the applicability section of this AD
constitutes terminating action for the requirements of this AD.
The FAA estimates that this proposed AD would:
Affect 2194 helicopters of U.S. registry,
Take about \1/4\ work hour for a blade check or
inspection, and
[[Page 60248]]
Take 3 work hours to replace a blade at an average labor
rate of $65 per work hour. Required parts would cost about $5848 per
helicopter. (In its ASB, the manufacturer states it will give warranty
credit based on hour usage on the blade with remaining life hours and
other restrictions.) Based on these figures, we estimate the total cost
impact of the proposed AD on U.S. operators to be $19,989,973. Costs
assume--200 pilot checks, 26 mechanic inspections, and one blade
replacement for 90 percent of the fleet with a nonconforming blade.
Regulatory Findings
The regulations proposed herein 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. Therefore, it
is determined that this proposal would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I certify that this 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); on
a substantial number of small entities under the criteria of the
Regulatory Flexibility Act. A copy of the draft regulatory evaluation
prepared for this action is contained in the Rules Docket. A copy of it
may be obtained by contacting the Rules Docket at the location provided
under the caption ADDRESSES.
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 39-13884 (69 FR
69810, December 1, 2004), and by adding a new airworthiness directive
(AD), to read as follows:
Bell Helicopter Textron Canada: Docket No. FAA-2005, Directorate
Identifier 2005-SW-22-AD. Supersedes AD 2004-24-08, Amendment 39-
13884, Docket No. 2004-SW-12-AD.
Applicability: Model 206A, B, L, L-1, L-3, and L-4 helicopters,
with a tail rotor blade (blade) with the following part number (P/N)
and serial number (S/N) installed, certificated in any category.
------------------------------------------------------------------------
------------------------------------------------------------------------
Model 206A & B; Blade, Model 206A, B, L, L-1, L-3, & L-4; Blade, P/N P/
P/N 206-016-201-133, S/ N 206-016-201-131, S/N with prefix ``CS'' and
N with prefix ``CS'' no ``V'' suffix
and no ``V'' suffix
------------------------
1381 through 1442 7000 through 7018 10174 through 10218
1492 through 1517 7020 through 7043 10220
1520 through 1542 7045 through 7050 10232
1550 7052 through 7132 10235
1556 7134 through 7246 10237 through 10241
1560 7248 through 7270 10244
1562 7272 through 7277 10245
1564 through 1567 7279 through 7339 10248
1569 through 1606 7342 through 7368 10250 through 10264
1609 7784 10266 through 10268
1611 7786 10270 through 10274
1612 7788 10276 through 10278
1614 through 1631 7790 through 7796 10280 through 10282
1633 through 1675 7798 through 7819 10284 through 10292
1677 7821 through 7833 10296
1678 7835 through 7839 10300 through 10330
1680 through 1682 7841 through 8001 10332
1684 through 1787 8003 through 8026 10333
1789 through 1803 8029 through 8061 10335 through 10347
1810 through 1812 8064 through 8117 10349
1814 8119 10351 through 10359
1816 8121 through 8139 10363 through 10365
1820 8142 through 8176 10367
1823 through 1831 8178 through 8262 10373
1834 through 1836 8264 through 8294 10374
1838 8298 through 8368 10377 through 10385
1840 through 1844 8370 through 8375 10387 through 10408
1846 8378 through 8416 10410
1848 through 1882 8419 10414 through 10417
1884 through 1887 8421 10419 through 10427
1889 through 1893 8425 through 8428 10430
1896 through 1898 8430 through 8438 10432
1900 8440 10437
1904 8441 10438
[[Page 60249]]
Model 206A & B; Blade, Model 206A, B, L, L-1, L-3, & L-4; Blade, P/N P/
P/N 206-016-201-133, S/ N 206-016-201-131, S/N with prefix ``CS'' and
N with prefix ``CS'' no ``V'' suffix
and no ``V'' suffix
------------------------
1909 through 1912 8443 10442 through 10445
1915 8445 through 8447 10458 through 10466
1916 8449 through 8606 10469
1919 through 1921 8608 through 8622 10470
1924 8624 through 8626 10474
1928 through 1931 8628 through 8632 10476 through 10478
1933 8635 through 8653 10480 through 10487
1934 through 1939 8655 through 8686 10489 through 10491
1943 8690 10493 through 10495
1945 8692 through 8700 10497 through 10503
1947 8703 through 8715 10505 through 10588
1948 8717 through 8722 10591 through 10606
1952 through 1957 8724 through 8742 10608 through 10610
1960 8745 through 8828 10612 through 10620
1962 through 1965 8830 through 8835 10623
8838 through 8840 10624
8842 through 8881 10631 through 10655
8883 through 9032 10657 through 10669
9034 through 9139 10672
9141 through 9198 10673
9200 10676 through 10678
9202 through 9302 10680 through 10683
9304 through 9339 10685
9341 through 9371 10687
9373 through 9411 10689 through 10702
9413 10707
9415 through 9417 10712
9419 through 9496 10715
9498 through 9585 10730
9587 through 9594 10732 through 10734
9596 through 9618 10736
9621 through 9629 10738
9632 through 9642 10739
9645 through 9651 10746
9653 through 9673 10750
9675 through 9707 10756
9709 through 9724 10760
9727 through 9731 10761
9733 through 9735 10765
9737 through 9739 10770
9741 through 9748 10774 through 10776
9751 through 9785 10778
9787 10781
9788 10783 through 10785
9790 through 9792 10792
9795 through 9847 10794
9849 through 9928 10798
9930 through 9937 10799
9940 through 9942 10806 through 10808
9944 through 9952 10811
9955 through 9972 10814 through 10822
9974 through 9989 10824
9991 through 9995 10825
9997 through 10004 10829
10006 through 10009 10831
10011 10917
10013 through 10018 10923
10021 through 10030 10931
10034 10936
10036 through 10057 10937
10061 through 10082 10940
10090 through 10092 10943
10094 through 10100 10945
10102 through 10114 10947
10116 10948
10119 10964
10121 10965
10123 through 10134 10973
10136 through 10140 10982
10142 through 10144 10985
10146 through 10172 10986
------------------------------------------------------------------------
[[Page 60250]]
Compliance: Required as indicated.
To prevent blade failure and subsequent loss of control of the
helicopter, do the following:
(a) Before further flight, unless accomplished previously, and
before installing any blade with a P/N and S/N listed in the
applicability section of this AD, clean the blade. Using a 10X or
higher magnifying glass, inspect both sides of each blade for a
deformation, a crack, and a bent or deformed weight in the area
shown in Figure 1 of this AD.
Note 1: Paint irregularities on the blade may indicate a crack.
[GRAPHIC] [TIFF OMITTED] TP17OC05.002
(b) After doing paragraph (a) of this AD, at the following
intervals, clean both sides of each blade and do either paragraph
(1) or (2) as follows:
(1) At intervals not to exceed 12 hours time-in-service (TIS),
using a 10X or higher magnifying glass, inspect both sides of each
blade for a deformation, a crack, and a bent or deformed weight in
the area shown in Figure 1 of this AD, or
(2) Inspect and check both sides of each blade for a
deformation, a crack, and a bent or deformed weight in the area
shown in Figure 1 of this AD as follows:
(i) Using a 10X or higher magnifying glass, inspect at intervals
not to exceed 24 hours TIS, and
(ii) Check at intervals not to exceed 3 hours TIS between the
inspections required by paragraph (b)(2)(i) of this AD. An owner/
operator (pilot), holding at least a private pilot certificate, may
perform this visual check and must enter compliance with this
paragraph into the helicopter maintenance records by following 14
CFR sections 43.11 and 91.417(a)(2)(v).
(c) Before further flight, replace any blade that has a
deformation, a crack, or a bent or deformed weight with an airworthy
blade.
Note 2: Bell Helicopter Textron Alert Service Bulletin No. 206-
04-100 for Model 206A and B and No. 206L-04-127 for Model 206L
series, both Revision C, both dated March 5, 2005, pertain to the
subject of this AD.
(d) On or before April 27, 2007, for any affected part-numbered
blade with a S/N listed in the applicability section of this AD:
(1) Replace the blade with a blade that has a S/N other than one
listed in the applicability section of this AD, or
(2) Replace the blade with a blade that has a S/N listed in the
applicability section of this AD and also has a ``V'' suffix.
(e) Replacing each blade with an airworthy blade as required by
paragraph (d) of this AD constitutes terminating action for the
requirements of this AD.
(f) 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 Safety Management Group, Rotorcraft Directorate, FAA,
for information about previously approved alternative methods of
compliance.
Note 3: The subject of this AD is addressed in Transport Canada
(Canada) AD No. CF-2004-05R1, dated June 28, 2004.
Issued in Fort Worth, Texas, on October 7, 2005.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-20681 Filed 10-14-05; 8:45 am]
BILLING CODE 4910-13-P
