Airworthiness Directives; Bell Helicopter Textron Canada Model 206L, 206L-1, and 206L-3 Helicopters, 71955-71957 [E8-28113]
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Federal Register / Vol. 73, No. 229 / Wednesday, November 26, 2008 / Proposed Rules
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depicted in Details A and B, Figure 1, of the
Accomplishment Instructions in the SB.
(2) Perform a fluorescent penetrant
inspection of each skin panel for a crack in
the areas around the fastener holes where the
transition fittings attach to the rotary rudder
boom and pylon.
(d) Before further flight, accomplish the
following:
(1) If you cannot visually determine that a
crack does not exist in a part, inspect the part
and the surrounding area using a 10-power
or higher magnifying glass.
(2) If you cannot determine that a crack
does not exist in a part other than a strap
after inspecting it with a 10-power or higher
magnifying glass, perform a fluorescent
penetrant inspection of the part.
(3) If you cannot determine that a crack
does not exist in a strap after inspecting it
with a 10-power or higher magnifying glass,
perform a magnetic particle inspection of the
strap.
(e) If a crack is found, before further flight,
replace any cracked part with an airworthy
part, or repair the cracked part if the damage
is within the maximum repair damage limits.
Note: The maximum repair damage
limitations are stated in the applicable
Component and Repair Overhaul Manual.
(f) If any loose or working rivets are found,
before further flight, remove the rivets and
visually inspect the fastener holes and
surrounding area for a crack or any other
damage. Replace any part that is cracked
with an airworthy part; replace any damaged
part with damage exceeding the maximum
repair damage limits with an airworthy part
or repair any damaged part that is within the
maximum repair damage limits. Also, replace
any loose or working rivets.
(g) 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
Certification Office, FAA, ATTN: Michael
Kohner, Aviation Safety Engineer, FAA,
Rotorcraft Directorate, Rotorcraft Certification
Office, Fort Worth, Texas 76193–0170,
telephone (817) 222–5170, fax (817) 222–
5783, for information about previously
approved alternative methods of compliance.
(h) Special flight permits may be issued in
accordance with 14 CFR 21.197 and 21.199
to operate the helicopter to a location where
the inspection requirements of this AD can
be accomplished. No special flight permits
will be issued to accomplish replacements or
repairs, or if a crack is suspected.
Issued in Fort Worth, Texas, on November
14, 2008.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E8–28109 Filed 11–25–08; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1242; Directorate
Identifier 96–SW–13–AD]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada Model
206L, 206L–1, and 206L–3 Helicopters
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: This document proposes to
revise an existing airworthiness
directive (AD) for Bell Helicopter
Textron Canada (BHTC) Model 206L,
206L–1, and 206L–3 helicopters with
certain part-numbered tailbooms. That
AD currently requires a visual
inspection of the tailboom skin in the
areas around the nutplates and in the
areas of the tailboom drive shaft cover
retention clips for cracks and corrosion
using a 10-power or higher magnifying
glass until the tailboom is replaced with
an airworthy tailboom. This action
would require the same actions as the
existing AD but would allow a longer
interval for the repetitive inspections if
the tailboom is modified. Replacement
with an airworthy tailboom other than
a part-numbered tailboom affected by
this proposal would constitute
terminating action for the requirements
of this AD. The existing AD was
prompted by an accident and several
reports of fatigue cracks in the tailboom
skin in the areas around the nutplates
for the tail rotor fairing and in the areas
of the tail rotor drive shaft cover
retention clips. These proposed actions
are intended to prevent failure of the
tailboom and subsequent loss of control
of the helicopter.
DATES: Comments must be received by
January 26, 2009.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
PO 00000
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71955
Washington, DC 20590, 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, or at https://
www.bellcustomer.com/files/.
Examining the Docket: You may
examine the docket that contains the
proposed AD, any comments, and other
information in person at the Docket
Operations office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Operations office (telephone (800) 647–
5527) is located in Room W12–140 on
the ground floor of the West Building at
the street address stated in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
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–2008–1242, Directorate Identifier
96–SW–13–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://
www.regulations.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).
Discussion
On August 22, 1996, we issued AD
96–18–05, Amendment 39–9729 (61 FR
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45876, August 30, 1996), to require,
before further flight, and thereafter at
intervals not to exceed 50 hours time-inservice (TIS), a visual inspection of the
tailboom skin in the areas around the
nutplates and in the areas of the
tailboom drive shaft cover retention
clips for cracks and corrosion using a
10-power or higher magnifying glass.
That AD requires the 50-hour TIS
inspection regardless of whether the
tailboom has been modified in
accordance with Bell Helicopter Textron
Alert Service Bulletin No. 206L–87–47,
Revision C, dated October 23, 1989
(ASB). That AD also requires repeating
those inspections until the tailboom is
replaced with a tailboom, part number
(P/N) 206–033–004–143 or –177. That
action was prompted by an accident and
several reports of fatigue cracks in the
tailboom skin in the areas around the
nutplates for the tail rotor fairing and in
the areas of the tail rotor drive shaft
cover retention clips. That condition, if
not corrected, could result in failure of
the tailboom and subsequent loss of
control of the helicopter.
Since issuing that AD, we have reevaluated our AD determination that
modified tailbooms should be inspected
at intervals not to exceed 50 hours TIS.
Therefore, we have issued several
alternate method of compliances
(AMOCs) to allow owners and operators
to conduct 100 hours TIS repetitive
inspections, as described in the ASB,
instead of the 50 hours TIS repetitive
inspections required by the existing AD
for those tailbooms modified in
accordance with Part I of the ASB. We
have determined that increasing the
inspection interval for modified
tailbooms does not compromise the
safety of this helicopter. To provide this
relief to all operators, we have decided
to propose to revise the AD.
This helicopter model is
manufactured in Canada and is type
certificated for operation in the United
States under the provisions of 14 CFR
21.29 and the applicable bilateral
agreement. When AD 96–18–05 was
issued, the type certificate for these
affected model helicopters was in the
U.S. and the FAA had oversight
responsibility for these model
helicopters. Transport Canada issued an
AD following the FAA AD, except that
Transport Canada required modifying
the tailboom in accordance with the
ASB and increasing the inspection
interval to 100 hours TIS. Subsequently,
these type certificates were transferred
to Canada.
Therefore, the proposed AD would
revise AD 96–18–05 to allow an
increased inspection interval to 100
hours TIS for a tailboom modified in
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accordance with the ASB. The
inspection interval for an unmodified
tailboom would remain at 50 hours TIS.
The visual inspection of the tailboom
skin in the areas around the nutplates
and in the areas of the tailboom drive
shaft cover retention clips for cracks and
corrosion using a 10-power or higher
magnifying glass would still be
required. The proposed AD would also
require repeating the 50-hour TIS
inspections until the tailboom is
modified per the requirements of the
AD. Once modified, repeating the 100
hour TIS inspection until the tailboom
is replaced with a tailboom, part
number (P/N) 206–033–004–143 or
–177, or a tailboom not affected by this
AD, would be required.
We estimate that this proposed AD
would affect 551 helicopters of U.S.
registry, and the proposed actions
would take approximately 0.8 work
hour per helicopter to inspect and 8
work hours per helicopter to modify, at
an average labor rate of $80 per work
hour. If a helicopter is modified to
increase the inspection intervals,
required parts would cost
approximately $385. Based on these
figures, we estimate the total cost
impact of the proposed AD on U.S.
operators to be $423,168 per year,
assuming all the helicopters are
unmodified and 12 50-hour TIS
inspections per helicopter. If we assume
that all helicopters are modified at the
beginning of the year, the cost impact of
the proposed AD on U.S. operators
would be $776,359 for the first year,
assuming there are 6 100-hour TIS
inspections the first year, and $211,584
for each year thereafter.
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
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comply with this proposed AD. See the
AD docket 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, Incorporation by reference,
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.
§ 39.13
[Amended]
2. Section 39.13 is amended by
removing Amendment 39–9729 (61 FR
45876, August 30, 1996), and by adding
a new airworthiness directive (AD), to
read as follows:
Bell Helicopter Textron Canada: Docket No.
FAA–2008–1242; Directorate Identifier
96–SW–13–AD. Revises AD 96–18–05,
Amendment 39–9729.
Applicability: Model 206L, 206L–1, and
206L–3 helicopters, with tailboom, part
number (P/N) 206–033–004–003, –011, –045,
or –103, installed, certificated in any
category.
Compliance: Required as indicated.
To prevent failure of the tailboom and
subsequent loss of control of the helicopter,
accomplish the following:
(a) Before further flight, unless
accomplished previously, using a 10-power
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Federal Register / Vol. 73, No. 229 / Wednesday, November 26, 2008 / Proposed Rules
or higher magnifying glass, inspect the
tailboom for cracks or corrosion in
accordance with the Accomplishment
Instructions, Part II, steps (1) through (7), of
Bell Helicopter Textron Alert Service
Bulletin No. 206L–87–47, Revision C, dated
October 23, 1989 (ASB).
(b) For a tailboom that has not been
modified in accordance with the
Accomplishment Instructions, Part I of the
ASB, using a 10-power or higher magnifying
glass, inspect the tailboom for a crack at
intervals not to exceed 50 hours time-inservice (TIS) in accordance with the
Accomplishment Instructions, Part II, steps
(1) through (7), of the ASB.
(c) For a tailboom that has been modified
in accordance with the Accomplishment
Instructions, Part I, of the ASB, using a 10power or higher magnifying glass, inspect the
tailboom for a crack or corrosion at intervals
not to exceed 100 hours TIS in accordance
with the Accomplishment Instructions, Part
II and Part III of the ASB, except you are not
required to contact the manufacturer.
(d) If a crack or corrosion is detected that
is beyond the repairable limits stated in the
applicable maintenance manual, remove the
tailboom and replace it with an airworthy
tailboom.
(e) Replacing the tailboom with a tailboom,
P/N 206–033–004–143 or –177, or an
airworthy part-numbered tailboom that is not
listed in the Applicability section of this AD,
constitutes a 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 Manager, Safety
Management Group, FAA, ATTN: 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, for information about previously
approved alternative methods of compliance.
(g) Special flight permits will not be
issued.
Issued in Fort Worth, Texas, on November
18, 2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E8–28113 Filed 11–25–08; 8:45 am]
jlentini on PROD1PC65 with PROPOSALS
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0186; Directorate
Identifier 2007–NM–226–AD]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model DC–10–10, DC–10–10F,
DC–10–15, DC–10–30, DC–10–30F (KC–
10A and KDC–10), DC–10–40, DC–10–
40F, MD–10–10F, and MD–10–30F
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
AGENCY:
SUMMARY: The FAA is revising an earlier
NPRM for an airworthiness directive
(AD) that applies to certain McDonnell
Douglas Model DC–10–10, DC–10–10F,
DC–10–15, DC–10–30, DC–10–30F (KC–
10A and KDC–10), DC–10–40, and DC–
10–40F airplanes. The original NPRM
would have revised an existing AD that
currently requires installing or replacing
with improved parts, as applicable, the
bonding straps between the metallic
frame of the fillet and the wing leading
edge ribs, on both the left and right
sides of the airplane. The original
NPRM proposed to revise the
applicability to clarify the identity of
the affected airplanes. The original
NPRM resulted from fuel system
reviews conducted by the manufacturer.
This new action proposes to revise the
applicability to add and remove certain
airplanes, and to add a requirement to
reposition or replace two bonding straps
for certain airplanes. This new action
also proposes to supersede, rather than
revise, the existing AD. We are
proposing this supplemental NPRM to
reduce the potential of ignition sources
inside fuel tanks in the event of a severe
lightning strike, which, in combination
with flammable fuel vapors, could result
in fuel tank explosions and consequent
loss of the airplane.
DATES: We must receive comments on
this supplemental NPRM by December
22, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
PO 00000
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71957
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach,
California 90846, Attention: Data and
Service Management, Dept. C1–L5A
(D800–0024); telephone (206) 544–9990;
fax (206) 766–5682; e-mail
DDCS@boeing.com; Internet https://
www.myboeingfleet.com.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Samuel Lee, Aerospace Engineer,
Propulsion Branch, ANM–140L, FAA,
Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard,
Lakewood, California 90712–4137;
telephone (562) 627–5262; fax (562)
627–5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–0186; Directorate Identifier
2007–NM–226–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
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]]>Agencies
[Federal Register Volume 73, Number 229 (Wednesday, November 26, 2008)]
[Proposed Rules]
[Pages 71955-71957]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-28113]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1242; Directorate Identifier 96-SW-13-AD]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada Model
206L, 206L-1, and 206L-3 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes to revise an existing airworthiness
directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 206L,
206L-1, and 206L-3 helicopters with certain part-numbered tailbooms.
That AD currently requires a visual inspection of the tailboom skin in
the areas around the nutplates and in the areas of the tailboom drive
shaft cover retention clips for cracks and corrosion using a 10-power
or higher magnifying glass until the tailboom is replaced with an
airworthy tailboom. This action would require the same actions as the
existing AD but would allow a longer interval for the repetitive
inspections if the tailboom is modified. Replacement with an airworthy
tailboom other than a part-numbered tailboom affected by this proposal
would constitute terminating action for the requirements of this AD.
The existing AD was prompted by an accident and several reports of
fatigue cracks in the tailboom skin in the areas around the nutplates
for the tail rotor fairing and in the areas of the tail rotor drive
shaft cover retention clips. These proposed actions are intended to
prevent failure of the tailboom and subsequent loss of control of the
helicopter.
DATES: Comments must be received by January 26, 2009.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, 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, or at https://www.bellcustomer.com/files/.
Examining the Docket: You may examine the docket that contains the
proposed AD, any comments, and other information in person at the
Docket Operations office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Operations office
(telephone (800) 647-5527) is located in Room W12-140 on the ground
floor of the West Building at the street address stated in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
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-2008-1242,
Directorate Identifier 96-SW-13-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://
www.regulations.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).
Discussion
On August 22, 1996, we issued AD 96-18-05, Amendment 39-9729 (61 FR
[[Page 71956]]
45876, August 30, 1996), to require, before further flight, and
thereafter at intervals not to exceed 50 hours time-in-service (TIS), a
visual inspection of the tailboom skin in the areas around the
nutplates and in the areas of the tailboom drive shaft cover retention
clips for cracks and corrosion using a 10-power or higher magnifying
glass. That AD requires the 50-hour TIS inspection regardless of
whether the tailboom has been modified in accordance with Bell
Helicopter Textron Alert Service Bulletin No. 206L-87-47, Revision C,
dated October 23, 1989 (ASB). That AD also requires repeating those
inspections until the tailboom is replaced with a tailboom, part number
(P/N) 206-033-004-143 or -177. That action was prompted by an accident
and several reports of fatigue cracks in the tailboom skin in the areas
around the nutplates for the tail rotor fairing and in the areas of the
tail rotor drive shaft cover retention clips. That condition, if not
corrected, could result in failure of the tailboom and subsequent loss
of control of the helicopter.
Since issuing that AD, we have re-evaluated our AD determination
that modified tailbooms should be inspected at intervals not to exceed
50 hours TIS. Therefore, we have issued several alternate method of
compliances (AMOCs) to allow owners and operators to conduct 100 hours
TIS repetitive inspections, as described in the ASB, instead of the 50
hours TIS repetitive inspections required by the existing AD for those
tailbooms modified in accordance with Part I of the ASB. We have
determined that increasing the inspection interval for modified
tailbooms does not compromise the safety of this helicopter. To provide
this relief to all operators, we have decided to propose to revise the
AD.
This helicopter model is manufactured in Canada and is type
certificated for operation in the United States under the provisions of
14 CFR 21.29 and the applicable bilateral agreement. When AD 96-18-05
was issued, the type certificate for these affected model helicopters
was in the U.S. and the FAA had oversight responsibility for these
model helicopters. Transport Canada issued an AD following the FAA AD,
except that Transport Canada required modifying the tailboom in
accordance with the ASB and increasing the inspection interval to 100
hours TIS. Subsequently, these type certificates were transferred to
Canada.
Therefore, the proposed AD would revise AD 96-18-05 to allow an
increased inspection interval to 100 hours TIS for a tailboom modified
in accordance with the ASB. The inspection interval for an unmodified
tailboom would remain at 50 hours TIS. The visual inspection of the
tailboom skin in the areas around the nutplates and in the areas of the
tailboom drive shaft cover retention clips for cracks and corrosion
using a 10-power or higher magnifying glass would still be required.
The proposed AD would also require repeating the 50-hour TIS
inspections until the tailboom is modified per the requirements of the
AD. Once modified, repeating the 100 hour TIS inspection until the
tailboom is replaced with a tailboom, part number (P/N) 206-033-004-143
or -177, or a tailboom not affected by this AD, would be required.
We estimate that this proposed AD would affect 551 helicopters of
U.S. registry, and the proposed actions would take approximately 0.8
work hour per helicopter to inspect and 8 work hours per helicopter to
modify, at an average labor rate of $80 per work hour. If a helicopter
is modified to increase the inspection intervals, required parts would
cost approximately $385. Based on these figures, we estimate the total
cost impact of the proposed AD on U.S. operators to be $423,168 per
year, assuming all the helicopters are unmodified and 12 50-hour TIS
inspections per helicopter. If we assume that all helicopters are
modified at the beginning of the year, the cost impact of the proposed
AD on U.S. operators would be $776,359 for the first year, assuming
there are 6 100-hour TIS inspections the first year, and $211,584 for
each year thereafter.
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 AD docket 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, Incorporation by
reference, 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 39-9729 (61 FR
45876, August 30, 1996), and by adding a new airworthiness directive
(AD), to read as follows:
Bell Helicopter Textron Canada: Docket No. FAA-2008-1242;
Directorate Identifier 96-SW-13-AD. Revises AD 96-18-05, Amendment
39-9729.
Applicability: Model 206L, 206L-1, and 206L-3 helicopters, with
tailboom, part number (P/N) 206-033-004-003, -011, -045, or -103,
installed, certificated in any category.
Compliance: Required as indicated.
To prevent failure of the tailboom and subsequent loss of
control of the helicopter, accomplish the following:
(a) Before further flight, unless accomplished previously, using
a 10-power
[[Page 71957]]
or higher magnifying glass, inspect the tailboom for cracks or
corrosion in accordance with the Accomplishment Instructions, Part
II, steps (1) through (7), of Bell Helicopter Textron Alert Service
Bulletin No. 206L-87-47, Revision C, dated October 23, 1989 (ASB).
(b) For a tailboom that has not been modified in accordance with
the Accomplishment Instructions, Part I of the ASB, using a 10-power
or higher magnifying glass, inspect the tailboom for a crack at
intervals not to exceed 50 hours time-in-service (TIS) in accordance
with the Accomplishment Instructions, Part II, steps (1) through
(7), of the ASB.
(c) For a tailboom that has been modified in accordance with the
Accomplishment Instructions, Part I, of the ASB, using a 10-power or
higher magnifying glass, inspect the tailboom for a crack or
corrosion at intervals not to exceed 100 hours TIS in accordance
with the Accomplishment Instructions, Part II and Part III of the
ASB, except you are not required to contact the manufacturer.
(d) If a crack or corrosion is detected that is beyond the
repairable limits stated in the applicable maintenance manual,
remove the tailboom and replace it with an airworthy tailboom.
(e) Replacing the tailboom with a tailboom, P/N 206-033-004-143
or -177, or an airworthy part-numbered tailboom that is not listed
in the Applicability section of this AD, constitutes a 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 Manager, Safety Management Group, FAA, ATTN: 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, for information about
previously approved alternative methods of compliance.
(g) Special flight permits will not be issued.
Issued in Fort Worth, Texas, on November 18, 2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-28113 Filed 11-25-08; 8:45 am]
BILLING CODE 4910-13-P
