[Federal Register: November 26, 2008 (Volume 73, Number 229)]
[Proposed Rules]
[Page 71955-71957]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26no08-29]
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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
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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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 http://
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 http://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 http://
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]
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