Airworthiness Directives; Sikorsky Aircraft-Manufactured Model S-64F Helicopters, 15599-15602 [2013-05503]
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Federal Register / Vol. 78, No. 48 / Tuesday, March 12, 2013 / Rules and Regulations
which, although recognizable, appears
cumbersome. Honeywell suggested that,
‘‘Rated limited use 21⁄2-minute OEI’’
could be a better definition that would
still distinguish it from the existing
unlimited use of the 30-second, 2minute, and 21⁄2-minute OEI ratings.
We do not agree. The applicant
requested the new rating be named in
closer relation with the 30-second and
2-minute OEI ratings for consistency
across existing engine models and to
align the new rating with the 30-second
and 2-minute-OEI ratings at the
rotorcraft level. We agree with the
applicant’s proposed name. We also do
not agree with the commenter that the
30-second and 2-minute OEI ratings are
‘‘unlimited use.’’ These ratings are
limited to a maximum use of 3 times per
flight and require post-flight inspection,
per 14 CFR 1.1, Definitions.
documents, the following definition
applies: ‘‘Rated Flat 30-second and 2minute One Engine Inoperative (OEI)
Power,’’ with respect to rotorcraft
turbine engines, means: (1) A rating for
which the shaft horsepower and
associated operating limitations of the
30-second OEI and 2-minute OEI ratings
are equal, and (2) the shaft horsepower
is that developed under static
conditions at the altitude and
temperature for the hot day, and within
the operating limitations established
under part 33. The rating is for
continuation of one flight operation
after the failure or shutdown of one
engine in multiengine rotorcraft. The
rating is for up to three periods of use
no longer than 2.5 minutes each in any
one flight, and followed by mandatory
inspection and prescribed maintenance
action.
Applicability
These special conditions are
applicable to the GE CT7–2E1 turboshaft
engine model. If GE applies later for a
change to the type certificate, to include
another closely related model
incorporating the same novel or unusual
design feature, these special conditions
would apply to that model, as well. This
is true, provided the certification basis
is the same or contains later
amendments that satisfy the
certification basis discussed in the
section titled, ‘‘Type Certification
Basis.’’
2. Part 33 Requirements
(a) In addition to the airworthiness
standards in the type certification basis
applicable to the engine and the 30second and 2-minute OEI ratings, the
special conditions in this section apply.
(b) Section 33.7 Engine ratings and
operating limitations. Flat 30-second
and 2-minute OEI rating and operating
limitations are established by power,
torque, rotational speed, gas
temperature, and time duration.
(c) Section 33.27 Turbine,
compressor, fan, and turbosupercharger
rotor overspeed. In addition to the
requirements of § 33.27(b):
(1) The turbine and compressor rotors
must have sufficient strength to
withstand the test conditions specified
in paragraph (2) below.
(2) The applicant must determine, by
analysis or other acceptable means, the
most critically stressed rotor component
of each turbine and compressor,
including integral drum rotors and
centrifugal compressors. These
components must be tested for the
conditions in paragraphs (i) or (ii)
below. The test selection from the
following paragraphs (i) or (ii) below is
determined by the speed defined in
paragraph (i)(B) or (ii)(B), whichever is
higher.
(i) Test for a period of 5 minutes:
(A) At its maximum operating
temperature, except as provided in
§ 33.27(c)(2)(iv); and
(B) At the highest speed determined,
in accordance with § 33.27(c)(2)(i)
through (iv).
(C) This test may be performed using
a separate test vehicle as desired.
(ii) Test for a period of 5 minutes:
(A) At its maximum operating
temperature, except as provided in
paragraph (ii)(C) below; and
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting these
special conditions. This action affects
certain novel or unusual design features
on the CT7–2E1 turboshaft engine
model. It is not a rule of general
applicability and applies only to GE,
whom requested FAA approval for this
engine feature.
List of Subjects in 14 CFR Part 33
Air transportation, Aircraft, Aviation
safety, Safety.
The authority citation for these
special conditions is as follows:
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Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Special Conditions
Accordingly, the FAA issues the
following special conditions as part of
the type certification basis for the GE
CT7–2E1 turboshaft engine model.
1. Part 1 Definitions
Unless otherwise approved by the
Administrator and documented in the
appropriate manuals and certification
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15599
(B) At 100 percent of the highest
speed that would result from failure of
the most critical component of each
turbine and compressor, or system, in a
representative installation of the engine
when operating at the flat 30-second
and 2-minute OEI rating conditions; and
(C) The test speed must take into
account minimum material properties,
maximum operating temperature, if not
tested at that temperature, and the most
adverse dimensional tolerances.
(D) This test may be performed using
a separate test vehicle as desired.
Following the test, rotor growth and
distress beyond dimensional limits for
an overspeed condition are permitted
provided the structural integrity of the
rotor is maintained, as shown by a
procedure acceptable to the FAA.
(d) Section 33.67(d) Fuel system.
Engines must incorporate a means, or a
provision for a means, for automatic
availability and automatic control of the
flat 30-second and 2-minute OEI power
for the duration of 2.5 minutes and
within the declared operating
limitations.
(e) Section 33.87 Endurance test. The
requirements applicable to 30-second
and 2-minute OEI ratings, except for:
(1) The test of § 33.87(a)(7) as
applicable to the 21⁄2-minute OEI rating.
(2) The tests in § 33.87(f)(2) and (3)
must be run continuously for the
duration of 2.5 minutes, and
(3) The tests in § 33.87(f)(6) and (7)
must be run continuously for the
duration of 2.5 minutes.
(f) Section 33.88 Engine
overtemperature test. The requirements
of § 33.88(c), except that the test time is
5 minutes instead of 4 minutes.
Issued in Burlington, Massachusetts on
March 4, 2013.
Robert J. Ganley,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2013–05676 Filed 3–11–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0689; Directorate
Identifier 2009–SW–065–AD; Amendment
39–17301; AD 2012–26–06]
RIN 2120–AA64
Airworthiness Directives; Sikorsky
Aircraft-Manufactured Model S–64F
Helicopters
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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ACTION:
Federal Register / Vol. 78, No. 48 / Tuesday, March 12, 2013 / Rules and Regulations
Final rule.
We are adopting a new
airworthiness directive (AD) for
Sikorsky Aircraft Corporationmanufactured Model S–64F helicopters,
now under the Erickson Air-Crane
Incorporated (Erickson) Model S–64F
type certificate. This AD supersedes an
existing AD which requires inspections,
rework, and replacement, if necessary,
of the main gearbox (MGB) second stage
lower planetary plate (plate). Since we
issued that AD, the manufacturer has
conducted a configuration review and
analysis, and a review of the service
history of certain components. The
actions of this AD are intended to
establish life limits for certain
components, remove various parts from
service, and require consistency in the
part numbers of certain four bladed tail
rotor (T/R) assemblies to prevent fatigue
cracking, failure from static overload,
and subsequent loss of control of the
helicopter.
DATES: This AD is effective April 16,
2013.
ADDRESSES: For service information
identified in this AD, contact Erickson
Air-Crane Incorporated, ATTN: Chris
Erickson/Compliance Officer, 3100
Willow Springs Rd., P.O. Box 3247,
Central Point, OR 97502, telephone
(541) 664–5544, fax (541) 664–2312,
email address
cerickson@ericksonaircrane.com. You
may review a copy of the referenced
service information at the FAA, Office
of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room
663, Fort Worth, Texas 76137.
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SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov or in person at the
Docket Operations Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, any
incorporated-by-reference service
information, the economic evaluation,
any comments received, and other
information. The street address for the
Docket Operations Office (phone: 800–
647–5527) is U.S. Department of
Transportation, Docket Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Michael Kohner, Aviation Safety
Engineer, FAA, Rotorcraft Directorate,
Rotorcraft Certification Office, Fort
Worth, Texas 76137, telephone (817)
222–5170, email 7-avs-asw-170@faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
On June 29, 2012, at 77 FR 38744, the
Federal Register published our notice of
proposed rulemaking (NPRM), which
proposed to amend 14 CFR part 39 to
include an AD that would apply to
Sikorsky Aircraft Corporationmanufactured Model S–64F helicopters,
now under the Erickson Air-Crane
Incorporated Model S–64F type
certificate. That NPRM proposed to
supersede existing AD 97–10–15 (62 FR
28321, May 23, 1997), to require
reducing or establishing the life limits
for certain flight-critical components,
removing other parts with service
difficulties from service, and require
that T/R blade assembly, P/N 65160–
00001–048, be installed only as a set of
four and not be installed with another
part-numbered blade. The proposed
requirements were intended to prevent
a fatigue crack in a flight critical
component, which could result in
component failure from static overload
and subsequent loss of control of the
helicopter.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we did not receive any comments on the
NPRM (77 FR 38744, June 29, 2012).
hours, for a cost per helicopter of $170
and a fleet cost of $1,190.
• Replacing the rotary rudder spindle
assembly will require 10 work-hours
and a parts cost of $2,787, for a cost per
helicopter of $3,637 and a fleet cost of
$25,459.
• Replacing the plate will require 40
work-hours and a parts cost of $43,750,
for a cost per helicopter of $47,150 and
a fleet cost of $330,050.
• Replacing the main servo bracket
assembly will require 2 work-hours and
a parts cost of $5,223, for a cost per
helicopter of $5,393 and a fleet cost of
$37,751.
• Replacing the primary servo link
assembly of the M/R tandem servo will
require 10 work-hours and a parts cost
of $14,533, for a cost per helicopter of
$15,383 and a fleet cost of $107,681.
• Replacing the T/R shoulder bolt
will require 10 work-hours and a parts
cost of $571, for a cost per helicopter of
$1,421 and a fleet cost of $9,947.
• Replacing the T/R Blade Assembly
will require 8 work-hours and a parts
cost of $125,765 for a cost per helicopter
of $126,445 and a fleet cost of $885,115.
• The total cost to replace the parts
that are required to be removed from
service is estimated to be $199,599 per
helicopter and a fleet cost of $1,397,193.
Related Service Information
Erickson Service Bulletin No. 64F
General-1, Rev. 17, contains the
Airworthiness Limitations Schedule for
the Model S–64F helicopter and lists the
parts and assemblies with their
specified retirement lives.
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.
Costs of Compliance
We estimate that this AD will affect 7
helicopters of U.S. Registry and
estimate, at an average labor rate of $85
per hour, the following costs for
removing from service the parts listed in
Table 2 of this AD:
• Reviewing helicopter records to
determine if an affected part is installed
will require approximately 2 work-
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will 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.
FAA’s Determination
We have reviewed the relevant
information and determined that an
unsafe condition exists and is likely to
exist or develop on other helicopters of
the same type design and that air safety
and the public interest require adopting
the AD requirements as proposed except
for minor editorial changes to meet
current publication requirements. These
minor editorial changes are consistent
with the intent of the proposals in the
NPRM (77 FR 38744, June 29, 2012) and
will not increase the economic burden
on any operator nor increase the scope
of the AD.
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Federal Register / Vol. 78, No. 48 / Tuesday, March 12, 2013 / Rules and Regulations
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation
in Alaska to the extent that it justifies
making a regulatory distinction; and
(4) 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 an economic evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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. The FAA amends § 39.13 by
removing Amendment 39–10028 (62 FR
28321, May 23, 1997) and adding the
following new airworthiness directive
(AD):
■
2012–26–06 ERICKSON AIR-CRANE
INCORPORATED: Amendment 39–
17301; Docket No. FAA–2012–0689;
Directorate Identifier 2009–SW–065–AD.
(a) Applicability
This AD applies to Sikorsky Aircraft
Corporation-manufactured Model S–64F
helicopters, now under the Erickson AirCrane Incorporated Model S–64F type
certificate, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
fatigue crack in a flight critical component.
This condition could result in component
failure from static overload and subsequent
loss of control of the helicopter.
(c) Other Affected ADs
This AD supersedes AD 97–10–15,
Amendment 39–10028 (62 FR 28321, May 23,
1997).
(d) Effective Date
This AD becomes effective April 16, 2013.
(e) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(f) Required Actions
(1) Before further flight:
(i) Remove from service any part with a
number of hours time-in-service (TIS) equal
to or greater than the part’s retirement life as
stated in Table 1 to Paragraph (f) of this AD.
TABLE 1 TO PARAGRAPH (f)—PARTS WITH NEW OR REVISED LIFE LIMITS
Part name
Part No. (P/N)
Main Rotor (M/R) Blade Assembly ......................................................................................................
Main Transmission Support Beam Assembly, LH ...............................................................................
Main Transmission Support Beam Assembly, RH ...............................................................................
Left Splice Fitting (Transition Fitting), Rotary, Rudder Boom ..............................................................
Right Splice Fitting (Transition Fitting), Rotary, Rudder Boom ...........................................................
M/R Drive Shaft ....................................................................................................................................
Pressure Plate Assembly, Rotary Wing Head .....................................................................................
Horn and Liner Assembly .....................................................................................................................
Lower Hub Plate Assembly ..................................................................................................................
Horizontal Hinge Pin, Rotary Wing Head ............................................................................................
Damper Bracket Assembly, Rotary Wing Head ...................................................................................
Hub Subassembly, Rotary Wing ..........................................................................................................
Shaft Assembly, Pitch Control Tail Gearbox .......................................................................................
Rod End Assembly, Primary Servo Assembly .....................................................................................
Note 1 to Table 1 to Paragraph (f) of this
AD: The list of parts in Table 1 to Paragraph
(f) of this AD contains only a portion of the
life-limited parts for this model helicopter
and is not an all-inclusive list.
(ii) Revise the retirement life of each part
as shown in Table 1 to Paragraph (f) of this
AD by making pen and ink changes or by
inserting a copy of this AD into the
Airworthiness Limitations section of the
maintenance manual.
(iii) Record on the component history card
or equivalent record the retirement life for
each part as shown in Table 1 to Paragraph
(f) of this AD.
6415–20601–045
6420–62363–045
6420–62363–046
6420–66341–101
6420–66341–102
6435–20536–101
65101–11016–042
65102–11047–041
65103–11009–041
65103–11020–103
65103–11032–043
65103–11310–043
65358–07035–043
65652–11212–041
Retirement life
13,280 hours TIS.
9,300 hours TIS.
9,300 hours TIS.
8,300 hours TIS.
8,300 hours TIS.
2,200 hours TIS.
8,800 hours TIS.
1,140 hours TIS.
15,500 hours TIS.
5,100 hours TIS.
20,000 hours TIS.
21,600 hours TIS.
9,400 hours TIS.
20,800 hours TIS.
(2) Before further flight, remove from
service any part with a P/N listed in Table
2 to Paragraph (f) of this AD, regardless of the
part’s TIS. The P/Ns listed in Table 2 to
Paragraph (f) of this AD are not eligible for
installation on any helicopter.
TABLE 2 TO PARAGRAPH (f)—PARTS TO BE REMOVED FROM SERVICE
Part name
P/N
Spindle Assembly, Rotary Rudder ..................................................................................................................
Main Gearbox Second Stage Lower Planetary Plate .....................................................................................
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Bracket Assembly, Main Servo .......................................................................................................................
Primary Servo Link, Tandem Servo, M/R .......................................................................................................
Shoulder Bolt, Tail Rotor (T/R) .......................................................................................................................
T/R Blade Assembly .......................................................................................................................................
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6410–30302–041.
6435–20516–101 or
102.
6435–20527–041 or
042.
6465–62161–042.
65111–07001–102.
65161–00001–041.
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6435–20527–
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Federal Register / Vol. 78, No. 48 / Tuesday, March 12, 2013 / Rules and Regulations
(3) Before further flight, if a T/R blade
assembly, P/N 65160–00001–048, is
installed, remove any of the other three T/R
blade assemblies that have a different P/N
and replace it with a T/R blade assembly, P/
N 65160–00001–048. The T/R blade
assembly,
P/N 65160–00001–048, must be installed in
sets of four only.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Rotorcraft Certification
Office, FAA, may approve AMOCs for this
AD. Send your proposal to: Michael Kohner,
Aviation Safety Engineer, FAA, Rotorcraft
Directorate, Rotorcraft Certification Office,
Fort Worth, Texas 76137, telephone (817)
222–5170, email 7-avs-asw-170@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
(h) Additional Information
Erickson Service Bulletin No. 64F General1, Revision 17, dated August 17, 2010, which
is not incorporated by reference, contains
additional information about the subject of
this AD. For service information identified in
this AD, contact Erickson Air-Crane
Incorporated, ATTN: Chris Erickson/
Compliance Officer, 3100 Willow Springs Rd,
P.O. Box 3247, Central Point, OR 97502,
telephone (541) 664–5544, fax (541) 664–
2312, email address
cerickson@ericksonaircrane.com. You may
review a copy of this information at the FAA,
Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6300: Main Rotor Drive System and
6400: Tail Rotor System.
Issued in Fort Worth, Texas, on March 1,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–05503 Filed 3–11–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF ENERGY
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1. The authority citation for Part 11
continues to read as follows:
■
In accordance with the
Commission’s regulations, the
Commission, by its designee, the
Executive Director, issues this annual
update to the fee schedule which lists
per-acre rental fees by county (or other
geographic area) for use of government
lands by hydropower licensees.
DATES: This rule is effective March 12,
2013.
FOR FURTHER INFORMATION CONTACT:
Norman Richardson, Financial
Management Division, Office of the
Executive Director, Federal Energy
Regulatory Commission, 888 First Street
NE., Washington, DC 20426, (202) 502–
6219, Norman.Richardson@ferc.gov.
SUPPLEMENTARY INFORMATION:
SUMMARY:
Authority: 16 U.S.C. 792–828c; 42 U.S.C.
7101–7352.
2. Appendix A to Part 11 is added to
read as follows:
■
APPENDIX A TO PART 11—FEE
SCHEDULE FOR FY 2013
State
County
Alabama .............
Autauga ..............
Baldwin ...............
Barbour ...............
Bibb ....................
Blount .................
Bullock ................
Butler ..................
Calhoun ..............
Chambers ...........
Cherokee ............
Chilton ................
Choctaw .............
Clarke .................
Clay ....................
Cleburne .............
Coffee .................
Colbert ................
Conecuh .............
Coosa .................
Covington ...........
Crenshaw ...........
Cullman ..............
Dale ....................
Dallas .................
DeKalb ................
Elmore ................
Escambia ............
Etowah ...............
Fayette ...............
Franklin ...............
Geneva ...............
Greene ...............
Hale ....................
Henry ..................
Houston ..............
Jackson ..............
Jefferson .............
Lamar .................
Lauderdale .........
Lawrence ............
Lee .....................
Limestone ...........
Lowndes .............
Macon .................
Madison ..............
Marengo .............
Marion ................
Marshall ..............
Mobile .................
Monroe ...............
Montgomery .......
Morgan ...............
Perry ...................
Pickens ...............
Pike ....................
Randolph ............
Russell ................
St. Clair ..............
Shelby ................
Sumter ................
Talladega ............
Tallapoosa ..........
Tuscaloosa .........
Walker ................
Washington ........
Wilcox .................
Winston ..............
Aleutian Islands
Chain.
142 FERC ¶ 62,166
Issued February 27, 2013.
Section 11.2 of the Commission’s
regulations provides a method for
computing reasonable annual charges
for recompensing the United States for
the use, occupancy, and enjoyment of
its lands by hydropower licensees.1
Annual charges for the use of
government lands are payable in
advance, and are based on an annual
schedule of per-acre rental fees
published in Appendix A to Part 11 of
the Commission’s regulations.2 This
document updates the fee schedule in
Appendix A to Part 11 for fiscal year
2013 (October 1, 2012, through
September 30, 2013).
Effective Date
This Final Rule is effective March 12,
2013. The provisions of 5 U.S.C. 804,
regarding Congressional review of final
rules, do not apply to this Final Rule
because the rule concerns agency
procedure and practice and will not
substantially affect the rights or
obligations of non-agency parties. This
Final Rule merely updates the fee
schedule published in the Code of
Federal Regulations to reflect scheduled
adjustments, as provided for in section
11.2 of the Commission’s regulations.
By the Director.
Anton C. Porter,
Director, Office of the Executive Director.
18 CFR Part 11
[Docket No. RM11–6–000]
Annual Update to Fee Schedule for the
Use of Government Lands by
Hydropower Licensees
Federal Energy Regulatory
Commission, DOE.
AGENCY:
14:38 Mar 11, 2013
PART 11—[AMENDED]
List of Subjects in 18 CFR Part 11
Public lands.
Federal Energy Regulatory
Commission
VerDate Mar<15>2010
Final rule; annual update to fee
schedule.
ACTION:
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In consideration of the foregoing, the
Commission amends Chapter I, Title 18,
Code of Federal Regulations, as follows.
1 Annual Charges for the Use of Government
Lands, Order No. 774, 78 FR 5256 (January 25,
2013), FERC Stats. & Regs. ¶ 31,341 (2013).
2 18 CFR Part 11 (2012).
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Fee/acre/Yr
$53.06
89.12
48.00
61.16
87.24
55.08
58.11
86.56
49.30
59.31
75.66
46.85
44.72
63.88
83.84
59.17
58.82
49.98
56.88
61.08
58.08
101.36
57.51
44.94
94.36
71.03
57.43
82.01
46.33
57.56
56.31
42.14
49.85
49.49
57.92
57.45
93.62
38.84
63.48
70.94
82.09
72.47
44.45
51.29
72.96
45.68
54.86
101.03
87.13
48.84
53.09
77.98
43.58
51.13
59.09
66.04
59.58
96.10
101.11
39.30
63.37
67.48
67.32
68.49
57.62
37.67
70.53
1.52
]]>Agencies
[Federal Register Volume 78, Number 48 (Tuesday, March 12, 2013)]
[Rules and Regulations]
[Pages 15599-15602]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-05503]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0689; Directorate Identifier 2009-SW-065-AD;
Amendment 39-17301; AD 2012-26-06]
RIN 2120-AA64
Airworthiness Directives; Sikorsky Aircraft-Manufactured Model S-
64F Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
[[Page 15600]]
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for
Sikorsky Aircraft Corporation-manufactured Model S-64F helicopters, now
under the Erickson Air-Crane Incorporated (Erickson) Model S-64F type
certificate. This AD supersedes an existing AD which requires
inspections, rework, and replacement, if necessary, of the main gearbox
(MGB) second stage lower planetary plate (plate). Since we issued that
AD, the manufacturer has conducted a configuration review and analysis,
and a review of the service history of certain components. The actions
of this AD are intended to establish life limits for certain
components, remove various parts from service, and require consistency
in the part numbers of certain four bladed tail rotor (T/R) assemblies
to prevent fatigue cracking, failure from static overload, and
subsequent loss of control of the helicopter.
DATES: This AD is effective April 16, 2013.
ADDRESSES: For service information identified in this AD, contact
Erickson Air-Crane Incorporated, ATTN: Chris Erickson/Compliance
Officer, 3100 Willow Springs Rd., P.O. Box 3247, Central Point, OR
97502, telephone (541) 664-5544, fax (541) 664-2312, email address
cerickson@ericksonaircrane.com. You may review a copy of the referenced
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, any incorporated-by-reference
service information, the economic evaluation, any comments received,
and other information. The street address for the Docket Operations
Office (phone: 800-647-5527) is U.S. Department of Transportation,
Docket Operations Office, M-30, West Building Ground Floor, Room W12-
140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office,
Fort Worth, Texas 76137, telephone (817) 222-5170, email 7-avs-asw-170@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On June 29, 2012, at 77 FR 38744, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 to include an AD that would apply to Sikorsky Aircraft
Corporation-manufactured Model S-64F helicopters, now under the
Erickson Air-Crane Incorporated Model S-64F type certificate. That NPRM
proposed to supersede existing AD 97-10-15 (62 FR 28321, May 23, 1997),
to require reducing or establishing the life limits for certain flight-
critical components, removing other parts with service difficulties
from service, and require that T/R blade assembly, P/N 65160-00001-048,
be installed only as a set of four and not be installed with another
part-numbered blade. The proposed requirements were intended to prevent
a fatigue crack in a flight critical component, which could result in
component failure from static overload and subsequent loss of control
of the helicopter.
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (77 FR 38744,
June 29, 2012).
FAA's Determination
We have reviewed the relevant information and determined that an
unsafe condition exists and is likely to exist or develop on other
helicopters of the same type design and that air safety and the public
interest require adopting the AD requirements as proposed except for
minor editorial changes to meet current publication requirements. These
minor editorial changes are consistent with the intent of the proposals
in the NPRM (77 FR 38744, June 29, 2012) and will not increase the
economic burden on any operator nor increase the scope of the AD.
Related Service Information
Erickson Service Bulletin No. 64F General-1, Rev. 17, contains the
Airworthiness Limitations Schedule for the Model S-64F helicopter and
lists the parts and assemblies with their specified retirement lives.
Costs of Compliance
We estimate that this AD will affect 7 helicopters of U.S. Registry
and estimate, at an average labor rate of $85 per hour, the following
costs for removing from service the parts listed in Table 2 of this AD:
Reviewing helicopter records to determine if an affected
part is installed will require approximately 2 work-hours, for a cost
per helicopter of $170 and a fleet cost of $1,190.
Replacing the rotary rudder spindle assembly will require
10 work-hours and a parts cost of $2,787, for a cost per helicopter of
$3,637 and a fleet cost of $25,459.
Replacing the plate will require 40 work-hours and a parts
cost of $43,750, for a cost per helicopter of $47,150 and a fleet cost
of $330,050.
Replacing the main servo bracket assembly will require 2
work-hours and a parts cost of $5,223, for a cost per helicopter of
$5,393 and a fleet cost of $37,751.
Replacing the primary servo link assembly of the M/R
tandem servo will require 10 work-hours and a parts cost of $14,533,
for a cost per helicopter of $15,383 and a fleet cost of $107,681.
Replacing the T/R shoulder bolt will require 10 work-hours
and a parts cost of $571, for a cost per helicopter of $1,421 and a
fleet cost of $9,947.
Replacing the T/R Blade Assembly will require 8 work-hours
and a parts cost of $125,765 for a cost per helicopter of $126,445 and
a fleet cost of $885,115.
The total cost to replace the parts that are required to
be removed from service is estimated to be $199,599 per helicopter and
a fleet cost of $1,397,193.
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.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will 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.
[[Page 15601]]
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction; and
(4) 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 an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-10028 (62 FR
28321, May 23, 1997) and adding the following new airworthiness
directive (AD):
2012-26-06 ERICKSON AIR-CRANE INCORPORATED: Amendment 39-17301;
Docket No. FAA-2012-0689; Directorate Identifier 2009-SW-065-AD.
(a) Applicability
This AD applies to Sikorsky Aircraft Corporation-manufactured
Model S-64F helicopters, now under the Erickson Air-Crane
Incorporated Model S-64F type certificate, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as a fatigue crack in a
flight critical component. This condition could result in component
failure from static overload and subsequent loss of control of the
helicopter.
(c) Other Affected ADs
This AD supersedes AD 97-10-15, Amendment 39-10028 (62 FR 28321,
May 23, 1997).
(d) Effective Date
This AD becomes effective April 16, 2013.
(e) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(f) Required Actions
(1) Before further flight:
(i) Remove from service any part with a number of hours time-in-
service (TIS) equal to or greater than the part's retirement life as
stated in Table 1 to Paragraph (f) of this AD.
Table 1 to Paragraph (f)--Parts With New or Revised Life Limits
----------------------------------------------------------------------------------------------------------------
Part name Part No. (P/N) Retirement life
----------------------------------------------------------------------------------------------------------------
Main Rotor (M/R) Blade Assembly................. 6415-20601-045 13,280 hours TIS.
Main Transmission Support Beam Assembly, LH..... 6420-62363-045 9,300 hours TIS.
Main Transmission Support Beam Assembly, RH..... 6420-62363-046 9,300 hours TIS.
Left Splice Fitting (Transition Fitting), 6420-66341-101 8,300 hours TIS.
Rotary, Rudder Boom.
Right Splice Fitting (Transition Fitting), 6420-66341-102 8,300 hours TIS.
Rotary, Rudder Boom.
M/R Drive Shaft................................. 6435-20536-101 2,200 hours TIS.
Pressure Plate Assembly, Rotary Wing Head....... 65101-11016-042 8,800 hours TIS.
Horn and Liner Assembly......................... 65102-11047-041 1,140 hours TIS.
Lower Hub Plate Assembly........................ 65103-11009-041 15,500 hours TIS.
Horizontal Hinge Pin, Rotary Wing Head.......... 65103-11020-103 5,100 hours TIS.
Damper Bracket Assembly, Rotary Wing Head....... 65103-11032-043 20,000 hours TIS.
Hub Subassembly, Rotary Wing.................... 65103-11310-043 21,600 hours TIS.
Shaft Assembly, Pitch Control Tail Gearbox...... 65358-07035-043 9,400 hours TIS.
Rod End Assembly, Primary Servo Assembly........ 65652-11212-041 20,800 hours TIS.
----------------------------------------------------------------------------------------------------------------
Note 1 to Table 1 to Paragraph (f) of this AD: The list of
parts in Table 1 to Paragraph (f) of this AD contains only a portion
of the life-limited parts for this model helicopter and is not an
all-inclusive list.
(ii) Revise the retirement life of each part as shown in Table 1
to Paragraph (f) of this AD by making pen and ink changes or by
inserting a copy of this AD into the Airworthiness Limitations
section of the maintenance manual.
(iii) Record on the component history card or equivalent record
the retirement life for each part as shown in Table 1 to Paragraph
(f) of this AD.
(2) Before further flight, remove from service any part with a
P/N listed in Table 2 to Paragraph (f) of this AD, regardless of the
part's TIS. The P/Ns listed in Table 2 to Paragraph (f) of this AD
are not eligible for installation on any helicopter.
Table 2 to Paragraph (f)--Parts To Be Removed From Service
----------------------------------------------------------------------------------------------------------------
Part name P/N
----------------------------------------------------------------------------------------------------------------
Spindle Assembly, Rotary Rudder................. 6410-30302-041.
Main Gearbox Second Stage Lower Planetary Plate. 6435-20516-101 or 6435-20516-102.
Bracket Assembly, Main Servo.................... 6435-20527-041 or 6435-20527-042.
Primary Servo Link, Tandem Servo, M/R........... 6465-62161-042.
Shoulder Bolt, Tail Rotor (T/R)................. 65111-07001-102.
T/R Blade Assembly.............................. 65161-00001-041.
----------------------------------------------------------------------------------------------------------------
[[Page 15602]]
(3) Before further flight, if a T/R blade assembly, P/N 65160-
00001-048, is installed, remove any of the other three T/R blade
assemblies that have a different P/N and replace it with a T/R blade
assembly, P/N 65160-00001-048. The T/R blade assembly, P/N 65160-
00001-048, must be installed in sets of four only.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Rotorcraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Michael Kohner,
Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft
Certification Office, Fort Worth, Texas 76137, telephone (817) 222-
5170, email 7-avs-asw-170@faa.gov.
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office before operating any aircraft
complying with this AD through an AMOC.
(h) Additional Information
Erickson Service Bulletin No. 64F General-1, Revision 17, dated
August 17, 2010, which is not incorporated by reference, contains
additional information about the subject of this AD. For service
information identified in this AD, contact Erickson Air-Crane
Incorporated, ATTN: Chris Erickson/Compliance Officer, 3100 Willow
Springs Rd, P.O. Box 3247, Central Point, OR 97502, telephone (541)
664-5544, fax (541) 664-2312, email address
cerickson@ericksonaircrane.com. You may review a copy of this
information at the FAA, Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 6300: Main Rotor
Drive System and 6400: Tail Rotor System.
Issued in Fort Worth, Texas, on March 1, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-05503 Filed 3-11-13; 8:45 am]
BILLING CODE 4910-13-P
