Airworthiness Directives; Erickson Air-Crane Incorporated Model S-64E and S-64F Helicopters, 74210-74213 [E7-25411]
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Federal Register / Vol. 72, No. 249 / Monday, December 31, 2007 / Proposed Rules
mstockstill on PROD1PC66 with PROPOSALS
concurrently as a direct final rule in the
Rules and Regulations section of this
Federal Register. Adequate protection
of public health and safety continues to
be ensured. The direct final rule will
become effective on March 17, 2008.
However, if the NRC receives significant
adverse comments on the direct final
rule by January 30, 2008, then the NRC
will publish a document that withdraws
the direct final rule. If the direct final
rule is withdrawn, the NRC will address
the comments received in response to
the proposed revisions in a subsequent
final rule. Absent significant
modifications to the proposed revisions
requiring republication, the NRC will
not initiate a second comment period on
this action in the event the direct final
rule is withdrawn.
A significant adverse comment is a
comment where the commenter
explains why the rule would be
inappropriate, including challenges to
the rule’s underlying premise or
approach, or would be ineffective or
unacceptable without a change. A
comment is adverse and significant if:
(1) The comment opposes the rule and
provides a reason sufficient to require a
substantive response in a notice-andcomment process. For example, a
substantive response is required when:
(a) The comment causes the NRC staff
to reevaluate (or reconsider) its position
or conduct additional analysis;
(b) The comment raises an issue
serious enough to warrant a substantive
response to clarify or complete the
record; or
(c) The comment raises a relevant
issue that was not previously addressed
or considered by the NRC staff.
(2) The comment proposes a change
or an addition to the rule, and it is
apparent that the rule would be
ineffective or unacceptable without
incorporation of the change or addition.
(3) The comment causes the NRC staff
to make a change (other than editorial)
to the rule, CoC, or TS.
For additional procedural information
and the regulatory analysis, see the
direct final rule published in the Rules
and Regulations section of this Federal
Register.
List of Subjects In 10 CFR Part 72
Administrative practice and
procedure, Criminal penalties,
Manpower training programs, Nuclear
materials, Occupational safety and
health, Penalties, Radiation protection,
Reporting and recordkeeping
requirements, Security measures, Spent
fuel, Whistleblowing.
For the reasons set out in the
preamble and under the authority of the
Atomic Energy Act of 1954, as amended;
VerDate Aug<31>2005
17:27 Dec 28, 2007
Jkt 214001
the Energy Reorganization Act of 1974,
as amended; the Nuclear Waste Policy
Act of 1982, as amended; and 5 U.S.C.
553; the NRC is proposing to adopt the
following amendments to 10 CFR part
72.
PART 72—LICENSING
REQUIREMENTS FOR THE
INDEPENDENT STORAGE OF SPENT
NUCLEAR FUEL, HIGH-LEVEL
RADIOACTIVE WASTE, AND
REACTOR-RELATED GREATER THAN
CLASS C WASTE
1. The authority citation for part 72
continues to read as follows:
Authority: Secs. 51, 53, 57, 62, 63, 65, 69,
81, 161, 182, 183, 184, 186, 187, 189, 68 Stat.
929, 930, 932, 933, 934, 935, 948, 953, 954,
955, as amended; sec. 234, 83 Stat. 444, as
amended (42 U.S.C. 2071, 2073, 2077, 2092,
2093, 2095, 2099, 2111, 2201, 2232, 2233,
2234, 2236, 2237, 2238, 2282); sec. 274, Pub.
L. 86–373, 73 Stat. 688, as amended (42
U.S.C. 2021); sec. 201, as amended, 202, 206,
88 Stat. 1242; as amended, 1244, 1246 (42
U.S.C. 5841, 5842, 5846); Pub. L. 95–601, sec.
10, 92 Stat. 2951, as amended by Pub. L. 102–
486, sec. 7902, 106 Stat. 3123 (42 U.S.C.
5851); sec. 102, Pub. L. 91–190, 83 Stat. 853
(42 U.S.C. 4332); secs. 131, 132, 133, 135,
137, 141, Pub. L. 97–425, 96 Stat. 2229, 2230,
2232, 2241; sec. 148, Pub. L. 100–203, 101
Stat. 1330–235 (42 U.S.C. 10151, 10152,
10153, 10155, 10157, 10161, 10168); sec.
1704, 112 Stat. 2750 (44 U.S.C. 3504 note);
sec. 651(e), Pub. L. 109–58, 119 Stat. 806–10
(42 U.S.C. 2014, 2021, 2021b, 2111).
Section 72.44(g) also issued under secs.
142(b) and 148(c), (d), Pub. L. 100–203, 101
Stat. 1330–232, 1330–236 (42 U.S.C.
10162(b), 10168(c),(d)). Section 72.46 also
issued under sec. 189, 68 Stat. 955 (42 U.S.C.
2239); sec. 134, Pub. L. 97–425, 96 Stat. 2230
(42 U.S.C. 10154). Section 72.96(d) also
issued under sec. 145(g), Pub. L. 100–203,
101 Stat. 1330–235 (42 U.S.C. 10165(g)).
Subpart J also issued under secs. 2(2), 2(15),
2(19), 117(a), 141(h), Pub. L. 97–425, 96 Stat.
2202, 2203, 2204, 2222, 2244 (42 U.S.C.
10101, 10137(a), 10161(h)). Subparts K and L
are also issued under sec. 133, 98 Stat. 2230
(42 U.S.C. 10153) and sec. 218(a), 96 Stat.
2252 (42 U.S.C. 10198).
2. In § 72.214, Certificate of
Compliance 1014 is revised to read as
follows:
§ 72.214 List of approved spent fuel
storage casks.
*
*
*
*
*
Certificate Number: 1014.
Initial Certificate Effective Date: May 31,
2000.
Amendment Number 1 Effective Date:
July 15, 2002.
Amendment Number 2 Effective Date:
June 7, 2005.
Amendment Number 3 Effective Date:
May 29, 2007.
Amendment Number 4 Effective Date:
January 8, 2008.
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Amendment Number 5 Effective Date:
March 17, 2008.
SAR Submitted by: Holtec International.
SAR Title: Final Safety Analysis Report
for the HI–STORM 100 Cask System.
Docket Number: 72–1014.
Certificate Expiration Date: June 1, 2020.
Model Number: HI–STORM 100.
*
*
*
*
*
Dated at Rockville, Maryland, this 11th day
of December, 2007.
For the Nuclear Regulatory Commission.
Luis A. Reyes,
Executive Director for Operations.
[FR Doc. E7–25414 Filed 12–28–07; 8:45 am]
BILLING CODE 7590–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0373; Directorate
Identifier 2006–SW–14–AD]
RIN 2120–AA64
Airworthiness Directives; Erickson AirCrane Incorporated Model S–64E and
S–64F Helicopters
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: This document proposes
adopting a new airworthiness directive
(AD) for the specified Erickson AirCrane Incorporated (Erickson) model
helicopters. The AD would require
determining whether each specified tail
rotor blade assembly (blade assembly)
has an affected serial number or part
marking. If a blade assembly has a
certain serial number or part marking,
the AD would also require initially and
repetitively inspecting the tail rotor
blade for a crack in the strap and pocket
areas. If a crack is found, this AD would
also require, before further flight,
replacing the blade assembly with an
airworthy blade assembly that does not
have an affected serial number or part
marking. This proposal is prompted by
several reports of cracking in the strap
and pocket areas of the tail rotor blade.
The actions specified by the proposed
AD are intended to prevent failure of the
tail rotor blade and subsequent loss of
control of the helicopter.
DATES: Comments must be received on
or before February 29, 2008.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD:
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Federal Register / Vol. 72, No. 249 / Monday, December 31, 2007 / Proposed Rules
• 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
Erickson Air-Crane Incorporated, P. O.
Box 3247, Central Point, OR 97502,
telephone 541–664–5544, fax 541–664–
2312, or at https://
www.ericksonaircrane.com.
You may examine the comments to
this proposed AD in the AD docket on
the Internet at https://
www.regulations.gov.
FOR FURTHER INFORMATION CONTACT:
Michael Kohner, Aviation Safety
Engineer, FAA, Rotorcraft Directorate,
Rotorcraft Certification Office, Fort
Worth, Texas 76193–0170, telephone
(817) 222–5447, fax (817) 222–5783.
SUPPLEMENTARY INFORMATION:
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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–2007–0373, Directorate Identifier
2006–SW–14–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) or you may visit
https://dms.dot.gov.
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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.
Discussion
This document proposes adopting a
new AD for the specified Erickson
model helicopters. The AD would
require determining whether certain tail
rotor blade assemblies have an affected
serial number or part marking. If a blade
assembly has a certain serial number or
part marking, the AD would also require
initially and repetitively inspecting the
tail rotor blade for a crack in the strap
and pocket areas. If a crack is found,
this AD would also require, before
further flight, replacing the blade
assembly with an airworthy blade
assembly that does not have an affected
serial number or part marking. This
proposal is prompted by several reports
of cracking in the strap or pocket areas
of the tail rotor blade. This condition, if
not corrected, could result in failure of
the tail rotor blade and subsequent loss
of control of the helicopter.
We have reviewed Erickson Alert
Service Bulletin 64B15–9, Revision B,
dated October 6, 2006 (ASB), which
describes procedures for determining
and inspecting certain marked or serial
numbered tail rotor blades. The ASB
specifies repetitive inspections not to
exceed 6 flight hours for the S–64F
model and not to exceed 15 flight hours
for the S–64E model. Alternate
inspection schedules are also included
for ‘‘ferry flights’’ used for delivering the
helicopter from one area of operation to
another. The ‘‘ferry flight’’ time would
be the flight time beginning at the end
of the last operation in one area to the
beginning of the first operation in
another area. If a crack is found in the
strap or pocket, the ASB specifies
removing and replacing the blade.
We propose to depart from the
language of the ASB and propose to use
the terms hours time-in-service (TIS)
instead of maximum ground-air-ground
(GAG) cycles. We propose to define a
‘‘ferry flight’’ as a helicopter flight used
for delivering the helicopter from one
area of operation to another. During the
‘‘ferry flight’’ the helicopter would not
drop off an external load or pick up an
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external load. A GAG cycle as defined
in the ASB for the purposes of these
inspections is any maneuver that results
in a climb-out similar to one following
takeoff. The proposed inspection
intervals for the ferry flights were also
modified to accommodate a new range
of values based on specifications
supplied by Erickson. The proposed
inspection intervals were determined by
multiplying the maximum GAG cycles
in the ASB for the given takeoff weight
by the flight endurance of 2.5 hours TIS
for the Model S–64E and 2.2 hours TIS
for the Model S–64F helicopters and
rounding the result to a near whole
number as deemed appropriate.
This unsafe condition is likely to exist
or develop on other helicopters of these
same type designs. Therefore, the
proposed AD would require for each
blade assembly, part number (P/N)
65161–00001–042 or –043, the
following actions:
• Within 25 hours TIS, unless done
previously, determine if the blade
assembly has a serial number listed in
the ASB. Also, determine if the blade
assembly is marked with an ‘‘RS503’’
near the part number.
• If the blade assembly serial number
is not listed in the ASB and does not
have ‘‘RS503’’ marked near the part
number, no further action would be
required by this AD.
• If a blade assembly has either an
affected serial number or part marking,
before further flight, using a 10-power or
higher magnifying glass, inspect both
sides of the blade assembly for a crack
in the strap and pocket areas paying
particular attention to the circled area as
depicted in Figure 1 of the ASB.
• If no crack is found, inspect the
blade assembly at intervals not to
exceed those TIS intervals specified in
Table 1 of the AD.
• If a crack is found, before further
flight, replace the unairworthy blade
assembly with an airworthy FAA
approved blade assembly that does not
have a serial number listed in the ASB
and does not have ‘‘RS503’’ marked near
the part number.
The actions would be required to be
done by following the specified portions
of the ASB described previously.
We estimate that this proposed AD
would:
• Affect 20 helicopters of U.S.
registry; 13 Model S–64E and 7 Model
S–64F;
• Require about 1 work hour to
determine whether an affected blade is
installed;
• Require about 1 work hour to
inspect the blade assembly, assuming
about 40 inspections a year for each
Model S–64E (total 520) and about 100
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Federal Register / Vol. 72, No. 249 / Monday, December 31, 2007 / Proposed Rules
inspections a year for each Model S–64F
(total 700);
• Require about 4 work hours to
replace each tail rotor blade, assuming
10 tail rotor blade assemblies are
replaced;
• Cost about $80 per work hour; and
• Cost about $60,000 per blade
assembly.
Based on these figures, the estimated
total cost impact of the proposed AD on
U.S. operators would be $702,400, based
on the stated assumptions.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. Additionally, this proposed AD
would not have a substantial direct
effect on the States, on the relationship
between the national Government and
the States, or on the distribution of
power and responsibilities among the
various levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a draft economic
evaluation of the estimated costs to
comply with this proposed AD. See the
DMS to examine the draft economic
evaluation.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
Administration proposes to amend part
39 of the Federal Aviation Regulations
(14 CFR part 39) as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. Section 39.13 is amended by
adding a new airworthiness directive to
read as follows:
Erickson Air-Crane Incorporated: Docket
No. FAA–2007–0373; Directorate Identifier
2006–SW–14–AD.
Applicability
Model S–64E and S–64F helicopters, with
tail rotor blade assembly (blade assembly),
part number (P/N) 65161–00001–042 or –043,
installed, certificated in any category.
Compliance
Required as indicated.
To prevent failure of the tail rotor blade
and subsequent loss of control of the
helicopter, do the following:
(a) Within 25 hours time-in-service (TIS),
unless accomplished previously:
(1) Determine if the blade assembly has a
serial number listed in the Accomplishment
Instructions, paragraph 2.A., of Erickson AirCrane Incorporated Alert Service Bulletin No.
64B15–9, Revision B, dated October 6, 2006
(ASB). Also, determine if the blade assembly
has ‘‘RS503’’ marked near the P/N.
(2) If the blade assembly serial number is
not listed in the ASB and does not have
‘‘RS503’’ marked near the P/N, no further
action is required by this AD.
(3) If a blade assembly has either a serial
number listed in paragraph 2.A of the ASB
or has ‘‘RS503’’ marked near the part
number, before further flight, using a 10power or higher magnifying glass, inspect
both sides of the blade assembly for a crack
in the strap and pocket areas paying
particular attention to the circled area as
depicted in Figure 1 of the ASB.
(i) If no crack is found, inspect the blade
assembly as specified in paragraph (a)(3) of
this AD at intervals not to exceed those
shown in the following table:
TABLE 1
Maximum time
between
inspections
(hours TIS)
Gross takeoff weight
(lbs)
Mission type
Model S–64E Tail Rotor Blade Strap Inspection Intervals
Ferry Only .................................................
Ferry Only .................................................
Ferry Only .................................................
All Others ..................................................
Above 35,000 ...............................................................................................................
Above 30,000 and less than or equal to 35,000 .........................................................
Below or equal to 30,000 .............................................................................................
All .................................................................................................................................
30
35
40
15
Model S–64F Tail Rotor Blade Strap Inspection Intervals
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Ferry Only .................................................
Ferry Only .................................................
Ferry Only .................................................
All Others ..................................................
Above 35,000 ...............................................................................................................
Above 30,000 and less than or equal to 35,000 .........................................................
Below or equal to 30,000 .............................................................................................
All .................................................................................................................................
Note: For the purposes of this AD, a ferry
flight is defined as a helicopter flight used for
delivering the helicopter from one area of
operation to another. During the ferry flight,
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17:55 Dec 28, 2007
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the helicopter would not drop off an external
load or pick up an external load.
(ii) If a crack is found, before further flight,
replace the unairworthy blade assembly with
an airworthy FAA approved blade assembly
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8
15
17
6
that does not have a serial number listed in
paragraph 2.A of the ASB and does not have
‘‘RS503’’ marked near the P/N.
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Federal Register / Vol. 72, No. 249 / Monday, December 31, 2007 / Proposed Rules
(b) Installing an airworthy blade assembly
that does not have a serial number listed in
paragraph 2.A of the ASB and does not have
‘‘RS503’’ marked near the P/N is terminating
action for the requirements of this AD.
(c) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the Manager, Rotorcraft
Directorate, Rotorcraft Certification Office,
FAA, ATTN: Michael Kohner, Aviation
Safety Engineer, Fort Worth, Texas 76193–
0170, telephone (817) 222–5447, fax (817)
222–5783.
Issued in Fort Worth, Texas, on November
28, 2007.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E7–25411 Filed 12–28–07; 8:45 am]
BILLING CODE 4910–13–P
COMMODITY FUTURES TRADING
COMMISSION
17 CFR Part 150
RIN 3038–AC51
Revision of Federal Speculative
Position Limits
Commodity Futures Trading
Commission.
ACTION: Reopening of comment period.
mstockstill on PROD1PC66 with PROPOSALS
AGENCY:
SUMMARY: The Commodity Futures
Trading Commission is reopening the
period for public comment to provide
interested persons additional time to
comment on certain proposed
amendments pertaining to the Federal
speculative position limits for
agricultural commodities.
DATES: Comments must be received by
January 21, 2008.
ADDRESS: Comments should be
submitted to David A. Stawick,
Secretary, Commodity Futures Trading
Commission, Three Lafayette Centre,
1155 21st Street, NW., Washington, DC
20581. Comments may be sent by
facsimile to 202.418.5521, or by e-mail
to secretary@cftc.gov. Reference should
be made to the ‘‘Proposed Revision of
Federal Speculative Position Limits.’’
Comments may also be submitted
through the Federal eRulemaking Portal
at https://www.regulations.gov.
FOR FURTHER INFORMATION CONTACT: Don
Heitman, Attorney, Division of Market
Oversight, Commodity Futures Trading
Commission, Three Lafayette Centre,
1155 21st Street, NW., Washington, DC
20581, telephone (202) 418–5041,
facsimile number (202) 418–5507,
electronic mail dheitman@cftc.gov; or
Martin Murray, Economist, Division of
Market Oversight, telephone (202) 418–
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17:27 Dec 28, 2007
Jkt 214001
5276, facsimile number (202) 418–5507,
electronic mail mmurray@cftc.gov.
The
Commission is reopening the period for
public comment on proposed
amendments to regulation 150.2.1 The
amendments were proposed on
November 21, 2007 and the comment
period initially closed on December 21,
2007.2 The amendments, if adopted by
the Commission, would increase the
Federal speculative position limits
enumerated in regulation 150.2 for all
single-month and all-months-combined
positions in all commodities except
oats, pursuant to parameters specified in
Commission regulation 150.5(c). The
amendments would also aggregate
positions in all designated contract
market products that share substantially
identical terms with the contracts
enumerated in regulation 150.2 for the
purposes of ascertaining compliance
with the Federal speculative position
limits.
By letter dated December 7, 2007, the
National Grain and Feed Association, an
association representing companies that
utilize exchange traded agricultural
contracts to manage price and inventory
risks,3 and by letter dated December 14,
2007, the American Bakers Association,
an association representing the interests
of the wholesale baking industry,4
requested an extension of the comment
period to better develop a response to
Commission’s proposed amendments.
While the Commission has received
commentary on the proposed
amendments,5 it believes that it would
be appropriate to reopen the comment
period to ensure that an adequate
opportunity is provided for the
submission of additional meaningful
and substantive comments.
Accordingly, the Commission has
determined to reopen the comment
period for the proposed amendments to
regulation 150.2 to January 21, 2008.
The Commission notes that it will give
full consideration to any comment
received in the interval between the
closing and reopening of the comment
period for the proposed amendments.
SUPPLEMENTARY INFORMATION:
1 17
CFR 150.2.
FR 65783 (November 21, 2007).
3 Letter from Rod Clark, Chair, Risk Management
Committee, National Grain and Feed Association, to
David A. Stawick, Secretary of the Commission
(December 7, 2007) (on file with the Commission).
4 Letter from Lee Sanders, Senior Vice President,
Government Relations & Public Affairs, Corporate
Secretary, American Bakers Association, to David
A. Stawick, Secretary of the Commission (December
14, 2007) (on file with the Commission).
5 Comment File: 07–014, available at https://
www.cftc.gov/lawandregulation/federalregister/
federalregistercomments/2007/07–014.html.
2 72
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Issued in Washington, DC, on December
21, 2007 by the Commission.
David A. Stawick,
Secretary of the Commission.
[FR Doc. E7–25344 Filed 12–28–07; 8:45 am]
BILLING CODE 6351–01–P
DEPARTMENT OF THE TREASURY
Internal Revenue Service
26 CFR Part 1
[REG–147290–05]
RIN 1545–BF08
Nuclear Decommissioning Funds
Internal Revenue Service (IRS),
Treasury.
ACTION: Notice of proposed rulemaking
by cross reference to temporary
regulations.
AGENCY:
SUMMARY: In the Rules and Regulations
section of this issue of the Federal
Register, the IRS is issuing temporary
regulations under section 468A of the
Internal Revenue Code relating to
deductions for contributions to trusts
maintained for decommissioning
nuclear power plants. The temporary
regulations reflect changes to the law
made by the Energy Policy Act of 2005,
and affect most taxpayers that own an
interest in a nuclear power plant. The
text of the temporary regulations also
serves as the text of these proposed
regulations.
DATES: Written or electronic comments
and requests for a public hearing must
be received by March 31, 2008.
ADDRESSES: Send submissions to:
CC:PA:LPD:PR (REG–147290–05), room
5203, Internal Revenue Service, PO Box
7604, Ben Franklin Station, Washington,
DC 20044. Submissions may be hand
delivered Monday through Friday
between the hours of 8 a.m. and 4 p.m.
to: CC:PA:LPD:PR (REG–147290–05),
Courier’s Desk, Internal Revenue
Service, 1111 Constitution Avenue,
NW., Washington, DC, or sent
electronically, via the Federal
eRulemaking Portal at https://
www.regulations.gov/ (IRS REG–
147290–05).
FOR FURTHER INFORMATION CONTACT:
Concerning the regulations, Patrick S.
Kirwan, (202) 622–3110; concerning
submissions and to request a hearing,
Kelly Banks, (202) 622–7180 (not tollfree numbers).
SUPPLEMENTARY INFORMATION:
Paperwork Reduction Act
The collection of information
contained in this notice of proposed
E:\FR\FM\31DEP1.SGM
31DEP1
]]>Agencies
[Federal Register Volume 72, Number 249 (Monday, December 31, 2007)]
[Proposed Rules]
[Pages 74210-74213]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-25411]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0373; Directorate Identifier 2006-SW-14-AD]
RIN 2120-AA64
Airworthiness Directives; Erickson Air-Crane Incorporated Model
S-64E and S-64F Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes adopting a new airworthiness directive
(AD) for the specified Erickson Air-Crane Incorporated (Erickson) model
helicopters. The AD would require determining whether each specified
tail rotor blade assembly (blade assembly) has an affected serial
number or part marking. If a blade assembly has a certain serial number
or part marking, the AD would also require initially and repetitively
inspecting the tail rotor blade for a crack in the strap and pocket
areas. If a crack is found, this AD would also require, before further
flight, replacing the blade assembly with an airworthy blade assembly
that does not have an affected serial number or part marking. This
proposal is prompted by several reports of cracking in the strap and
pocket areas of the tail rotor blade. The actions specified by the
proposed AD are intended to prevent failure of the tail rotor blade and
subsequent loss of control of the helicopter.
DATES: Comments must be received on or before February 29, 2008.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
[[Page 74211]]
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 Erickson Air-Crane Incorporated, P. O. Box 3247, Central Point, OR
97502, telephone 541-664-5544, fax 541-664-2312, or at https://
www.ericksonaircrane.com.
You may examine the comments to this proposed AD in the AD docket
on the Internet at https://www.regulations.gov.
FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office,
Fort Worth, Texas 76193-0170, telephone (817) 222-5447, fax (817) 222-
5783.
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-2007-0373,
Directorate Identifier 2006-SW-14-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) or you may visit https://dms.dot.gov.
Examining the Docket
You may examine the docket that contains the proposed AD, any
comments, and other information in person at the Docket 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.
Discussion
This document proposes adopting a new AD for the specified Erickson
model helicopters. The AD would require determining whether certain
tail rotor blade assemblies have an affected serial number or part
marking. If a blade assembly has a certain serial number or part
marking, the AD would also require initially and repetitively
inspecting the tail rotor blade for a crack in the strap and pocket
areas. If a crack is found, this AD would also require, before further
flight, replacing the blade assembly with an airworthy blade assembly
that does not have an affected serial number or part marking. This
proposal is prompted by several reports of cracking in the strap or
pocket areas of the tail rotor blade. This condition, if not corrected,
could result in failure of the tail rotor blade and subsequent loss of
control of the helicopter.
We have reviewed Erickson Alert Service Bulletin 64B15-9, Revision
B, dated October 6, 2006 (ASB), which describes procedures for
determining and inspecting certain marked or serial numbered tail rotor
blades. The ASB specifies repetitive inspections not to exceed 6 flight
hours for the S-64F model and not to exceed 15 flight hours for the S-
64E model. Alternate inspection schedules are also included for ``ferry
flights'' used for delivering the helicopter from one area of operation
to another. The ``ferry flight'' time would be the flight time
beginning at the end of the last operation in one area to the beginning
of the first operation in another area. If a crack is found in the
strap or pocket, the ASB specifies removing and replacing the blade.
We propose to depart from the language of the ASB and propose to
use the terms hours time-in-service (TIS) instead of maximum ground-
air-ground (GAG) cycles. We propose to define a ``ferry flight'' as a
helicopter flight used for delivering the helicopter from one area of
operation to another. During the ``ferry flight'' the helicopter would
not drop off an external load or pick up an external load. A GAG cycle
as defined in the ASB for the purposes of these inspections is any
maneuver that results in a climb-out similar to one following takeoff.
The proposed inspection intervals for the ferry flights were also
modified to accommodate a new range of values based on specifications
supplied by Erickson. The proposed inspection intervals were determined
by multiplying the maximum GAG cycles in the ASB for the given takeoff
weight by the flight endurance of 2.5 hours TIS for the Model S-64E and
2.2 hours TIS for the Model S-64F helicopters and rounding the result
to a near whole number as deemed appropriate.
This unsafe condition is likely to exist or develop on other
helicopters of these same type designs. Therefore, the proposed AD
would require for each blade assembly, part number (P/N) 65161-00001-
042 or -043, the following actions:
Within 25 hours TIS, unless done previously, determine if
the blade assembly has a serial number listed in the ASB. Also,
determine if the blade assembly is marked with an ``RS503'' near the
part number.
If the blade assembly serial number is not listed in the
ASB and does not have ``RS503'' marked near the part number, no further
action would be required by this AD.
If a blade assembly has either an affected serial number
or part marking, before further flight, using a 10-power or higher
magnifying glass, inspect both sides of the blade assembly for a crack
in the strap and pocket areas paying particular attention to the
circled area as depicted in Figure 1 of the ASB.
If no crack is found, inspect the blade assembly at
intervals not to exceed those TIS intervals specified in Table 1 of the
AD.
If a crack is found, before further flight, replace the
unairworthy blade assembly with an airworthy FAA approved blade
assembly that does not have a serial number listed in the ASB and does
not have ``RS503'' marked near the part number.
The actions would be required to be done by following the specified
portions of the ASB described previously.
We estimate that this proposed AD would:
Affect 20 helicopters of U.S. registry; 13 Model S-64E and
7 Model S-64F;
Require about 1 work hour to determine whether an affected
blade is installed;
Require about 1 work hour to inspect the blade assembly,
assuming about 40 inspections a year for each Model S-64E (total 520)
and about 100
[[Page 74212]]
inspections a year for each Model S-64F (total 700);
Require about 4 work hours to replace each tail rotor
blade, assuming 10 tail rotor blade assemblies are replaced;
Cost about $80 per work hour; and
Cost about $60,000 per blade assembly.
Based on these figures, the estimated total cost impact of the
proposed AD on U.S. operators would be $702,400, based on the stated
assumptions.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. Additionally, this proposed
AD would not have a substantial direct effect on the States, on the
relationship between the national Government and the States, or on the
distribution of power and responsibilities among the various levels of
government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a draft economic evaluation of the estimated costs to
comply with this proposed AD. See the DMS to examine the draft economic
evaluation.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (14 CFR part 39) as
follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
to read as follows:
Erickson Air-Crane Incorporated: Docket No. FAA-2007-0373;
Directorate Identifier 2006-SW-14-AD.
Applicability
Model S-64E and S-64F helicopters, with tail rotor blade
assembly (blade assembly), part number (P/N) 65161-00001-042 or -
043, installed, certificated in any category.
Compliance
Required as indicated.
To prevent failure of the tail rotor blade and subsequent loss
of control of the helicopter, do the following:
(a) Within 25 hours time-in-service (TIS), unless accomplished
previously:
(1) Determine if the blade assembly has a serial number listed
in the Accomplishment Instructions, paragraph 2.A., of Erickson Air-
Crane Incorporated Alert Service Bulletin No. 64B15-9, Revision B,
dated October 6, 2006 (ASB). Also, determine if the blade assembly
has ``RS503'' marked near the P/N.
(2) If the blade assembly serial number is not listed in the ASB
and does not have ``RS503'' marked near the P/N, no further action
is required by this AD.
(3) If a blade assembly has either a serial number listed in
paragraph 2.A of the ASB or has ``RS503'' marked near the part
number, before further flight, using a 10-power or higher magnifying
glass, inspect both sides of the blade assembly for a crack in the
strap and pocket areas paying particular attention to the circled
area as depicted in Figure 1 of the ASB.
(i) If no crack is found, inspect the blade assembly as
specified in paragraph (a)(3) of this AD at intervals not to exceed
those shown in the following table:
Table 1
------------------------------------------------------------------------
Maximum time
Gross takeoff weight between
Mission type (lbs) inspections
(hours TIS)
------------------------------------------------------------------------
Model S-64E Tail Rotor Blade Strap Inspection Intervals
------------------------------------------------------------------------
Ferry Only..................... Above 35,000........... 30
Ferry Only..................... Above 30,000 and less 35
than or equal to
35,000.
Ferry Only..................... Below or equal to 40
30,000.
All Others..................... All.................... 15
------------------------------------------------------------------------
Model S-64F Tail Rotor Blade Strap Inspection Intervals
------------------------------------------------------------------------
Ferry Only..................... Above 35,000........... 8
Ferry Only..................... Above 30,000 and less 15
than or equal to
35,000.
Ferry Only..................... Below or equal to 17
30,000.
All Others..................... All.................... 6
------------------------------------------------------------------------
Note: For the purposes of this AD, a ferry flight is defined as
a helicopter flight used for delivering the helicopter from one area
of operation to another. During the ferry flight, the helicopter
would not drop off an external load or pick up an external load.
(ii) If a crack is found, before further flight, replace the
unairworthy blade assembly with an airworthy FAA approved blade
assembly that does not have a serial number listed in paragraph 2.A
of the ASB and does not have ``RS503'' marked near the P/N.
[[Page 74213]]
(b) Installing an airworthy blade assembly that does not have a
serial number listed in paragraph 2.A of the ASB and does not have
``RS503'' marked near the P/N is terminating action for the
requirements of this AD.
(c) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Manager, Rotorcraft Directorate, Rotorcraft
Certification Office, FAA, ATTN: Michael Kohner, Aviation Safety
Engineer, Fort Worth, Texas 76193-0170, telephone (817) 222-5447,
fax (817) 222-5783.
Issued in Fort Worth, Texas, on November 28, 2007.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-25411 Filed 12-28-07; 8:45 am]
BILLING CODE 4910-13-P
