Airworthiness Directives; Erickson Air-Crane Incorporated Helicopters, 73265-73268 [2012-28434]
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Jkt 229001
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(b) Display. FHFA’s official logo and
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PO 00000
Chapter XVII—Office of Federal Housing
Enterprise Oversight, Department of
Housing and Urban Development
PART 1700—[REMOVED]
■
3. Remove part 1700.
Dated: December 3, 2012.
Edward J. DeMarco,
Acting Director, Federal Housing Finance
Agency.
[FR Doc. 2012–29695 Filed 12–7–12; 8:45 am]
BILLING CODE 8070–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1243; Directorate
Identifier 2007–SW–03–AD; Amendment 39–
17267; AD 2012–23–11]
RIN 2120–AA64
Airworthiness Directives; Erickson AirCrane Incorporated Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for
Erickson Air-Crane Incorporated
(Erickson) Model S–64F helicopters.
This AD requires inspecting for cracking
or working rivets in each left and right
splice fitting (transition fitting), the
pylon bulkhead assembly-canted
(bulkhead assembly), and the pylon
steel strap (strap). This AD was
prompted by several reports of cracking
in the transition fittings, the bulkhead
assembly, and the pylon. The actions
specified by this AD are intended to
detect cracking in the rotary rudder
boom or pylon due to fatigue, and to
prevent failure from static overload and
subsequent loss of control of the
helicopter.
SUMMARY:
DATES:
This AD is effective January 14,
2013.
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Federal Register / Vol. 77, No. 237 / Monday, December 10, 2012 / Rules and Regulations
73266
Federal Register / Vol. 77, No. 237 / Monday, December 10, 2012 / Rules and Regulations
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of January 14, 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 cerickson@ericksonaircrane.com.
You may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137.
10-power or higher magnifying glass. If
you could not determine that a crack
does not exist in the part after
inspecting it with a 10-power or higher
magnifying glass, the NPRM proposed to
require performing a fluorescent particle
inspection (FPI) of any part other than
a strap, and performing a magnetic
particle inspection (MPI) of any strap.
The NPRM also proposed to require
replacing any loose or working rivet.
The proposed requirements were
intended to detect cracking in the rotary
rudder boom or pylon due to fatigue,
and to prevent failure from static
overload and subsequent loss of control
of the helicopter.
Examining the AD Docket
Comments
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, Rotorcraft Certification Office,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5170; email
7-avs-asw-170@faa.gov.
SUPPLEMENTARY INFORMATION:
After our NPRM (73 FR 71952,
November 26, 2008) was published, we
received comments from one
commenter.
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Discussion
On November 26, 2008, at 73 FR
71952, 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 Erickson Model S–64F
helicopters with a transition fitting, part
number (P/N) 6420–66341–101, –102,
–103, or –104; bulkhead assembly, P/N
6420–66340–041, –043, or –044; or a
strap, P/N 6420–66301–119 or –127,
installed. That NPRM proposed to
require inspecting for cracking or
working rivets in each transition fitting,
the bulkhead assembly, the strap, and
the attaching rotary rudder boom and
pylon structure, and repairing or
replacing any cracked or damaged part
with an airworthy part. The NPRM also
proposed to require, for any part where
you could not visually determine that a
crack does not exist, inspecting using a
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Request
A commenter from Erickson AirCrane asked that we delete the bulkhead
assembly, P/N 6420–66340–041, from
the applicability and compliance
section of the NPRM (73 FR 71952,
November 26, 2008) since that P/N is
not used on Erickson Model S–64F
helicopters. We agree and have revised
this AD accordingly.
The commenter also asked that we
delete the words ‘‘other than a strap’’
from the requirement to perform an FPI
on a part other than a strap if you
cannot determine that a crack does not
exist, and delete the entire requirement
to perform an MPI of the strap if you
cannot determine that a crack does not
exist. The commenter states that an MPI
cannot be performed on the strap when
it is installed on a helicopter; instead an
FPI of the strap would need to be
performed with the other parts. We
partially agree. We agree that an MPI
cannot be performed on the strap while
it is installed on the helicopter because
the strap is attached to the aluminum
pylon section. An MPI for the strap was
initially proposed in the NPRM (73 FR
71952, November 26, 2008) because this
would be the type of inspection
normally used for a steel part. Instead of
changing the MPI on the strap to an FPI
as requested, after further review, we
determined that deleting this
inspection, as well as the magnifying
glass inspection and certain FPIs that
were proposed in the NPRM, will not
impact the overall level of safety. These
inspections were included in the event
a visual inspection was insufficient to
determine whether a crack exists. If any
additional inspections are necessary to
determine if a crack exists, a qualified
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individual performing the inspection
must make this determination.
FAA’s Determination
We have reviewed the relevant
information, considered the comments
received, and determined that an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design and that air safety and the
public interest require adopting the AD
requirements as proposed with the
changes described previously and minor
editorial changes. We have also revised
the estimated costs of complying with
this AD to reflect an average labor rate
of $85 per work-hour instead of $80 per
work-hour. These changes are consistent
with the intent of the proposals in the
NPRM (73 FR 71952, November 26,
2008) and will not increase the
economic burden on any operator nor
increase the scope of the AD.
Related Service Information
We have reviewed Erickson Service
Bulletin (SB) No. 64B20–6, Revision A,
dated December 12, 2007, which
describes procedures for inspecting the
transition fittings, the bulkhead
assembly, the strap, and the attaching
rotary rudder boom and pylon structure
for cracking or working rivets. We have
also reviewed Erickson SB No. 64F
General-3, Revision C, dated December
12, 2007, which summarizes a listing of
a portion of the Model S–64F helicopter
components, their part numbers, and
the corresponding SBs to use when
performing the structural inspections.
Costs of Compliance
We estimate that this AD will affect 7
helicopters of U.S. Registry. We estimate
that operators may incur the following
costs in order to comply with this AD.
It will take about 0.75 work-hour to
visually inspect the transition fittings,
skin panels, the bulkhead assembly,
strap, and pylon exterior in the strap
area; we estimate 30 of these visual
inspections per year. It will take about
0.50 work-hour to visually inspect the
pylon interior in the strap area; we
estimate 4 of these visual inspections
per year. It will take about 0.75 workhour to visually and fluorescent
penetrant inspect the skin panels at the
transition fitting; we estimate
performing these inspections 1 time per
year. It will take about 40 work-hours to
repair a pylon structural assembly. The
average labor rate is $85 per work-hour
and the cost for required parts to repair
a pylon structural assembly is
approximately $50,000. Based on these
figures, we estimate the annual cost of
the inspections will be $2,146 per
helicopter and $15,024 for the fleet on
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Federal Register / Vol. 77, No. 237 / Monday, December 10, 2012 / Rules and Regulations
U.S. operators. The estimated cost to
repair a pylon structural assembly,
including the cost for replacement parts
and labor, is $53,400.
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.
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
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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:
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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 adding
the following new airworthiness
directive (AD):
■
2012–23–11 Erickson Air-Crane
Incorporated: Amendment 39–17267;
Docket No. FAA–2008–1243; Directorate
Identifier 2007–SW–03–AD.
(a) Applicability
This AD applies to Erickson Air-Crane
Incorporated (Erickson) Model S–64F
helicopters with a left or right splice fitting
(transition fitting), part number (P/N) 6420–
66341–101, –102, –103, or –104; pylon
bulkhead assembly-canted (bulkhead
assembly), P/N 6420–66340–043 or –044; or
a pylon steel strap (strap), P/N 6420–66301–
119 or –127, installed, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as
cracking in the rotary rudder boom or pylon
due to fatigue, failure from static overload,
and subsequent loss of control of the
helicopter.
(c) Effective Date
This AD becomes effective January 14,
2013.
(d) 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.
(e) Required Actions
(1) Within 20 hours time-in-service (TIS),
and thereafter at intervals not to exceed 20
hours (TIS):
(i) Visually inspect each transition fitting,
P/N 6420–66341–101, –102, –103, or –104,
for a crack or working rivets on the inboard
face of the rotary rudder boom and pylon,
paying particular attention to the fastener
attachment holes, as depicted in Figure 1,
Detail A, of the Accomplishment Instructions
in Erickson Air-Crane Incorporated Service
Bulletin No. 64B20–6, Revision A, dated
December 12, 2007 (SB).
(ii) Visually inspect the outboard face of
each rotary rudder boom and pylon skin
panel (skin panel) that attaches to the
transition fittings for a crack or working
rivets in the transition fitting attachment
areas, paying particular attention to the
fastener attachment holes, as shown in Figure
1, Detail B, of the Accomplishment
Instructions in the SB.
(iii) Visually inspect the forward and aft
sides of each bulkhead assembly, P/N 6420–
66340–043 or –044, for a crack. Pay
particular attention to the circled areas
shown in Figure 2 of the Accomplishment
Instructions in the SB.
(iv) Visually inspect the upper 12 inches of
each strap, P/N 6420–66301–119 or –127, for
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73267
a crack or for working rivets as shown in
Figure 3 of the Accomplishment Instructions
in the SB.
(v) Visually inspect the pylon for a crack
or working rivets on each side of the upper
12 inches of the strap, and also 6 inches
above the end of the strap as shown in Figure
3 of the Accomplishment Instructions in the
SB.
(2) For any pylon with a strap installed,
within 155 hours TIS, and thereafter at
intervals not to exceed 155 hours TIS,
remove the inspection access covers, P/N
6420–66304–109 and P/N 6420–66303–125,
on the forward and aft sides of the pylon and
visually inspect the left-hand cap angle
(longeron), P/N 6420–66304–136, and the
interior area of the pylon adjacent to the
upper 12 inches of the strap, as well as 6
inches above the end of the strap, for a crack
or working rivets, as shown in Figure 3 of the
Accomplishment Instructions in the SB.
(3) At each transition fitting replacement,
which is required at intervals not to exceed
8,300 hours TIS:
(i) With each transition fitting removed,
visually inspect both sides of each skin panel
for a crack in the areas to which the
transition fitting attaches, paying particular
attention to the fastener attachment holes, as
depicted in Details A and B, Figure 1, of the
Accomplishment Instructions in the SB.
(ii) Perform a fluorescent penetrant
inspection of each skin panel for a crack in
the areas around the fastener holes where the
transition fittings attach to the rotary rudder
boom and pylon.
(4) If there is a crack, before further flight,
replace any cracked part with an airworthy
part, or repair the cracked part if the damage
is within the maximum repair damage limits.
Note to paragraph (e)(4) of this AD: The
maximum repair damage limitations are
stated in the applicable Component and
Repair Overhaul Manual.
(5) If any loose or working rivets are found,
before further flight, remove the rivets and
visually inspect the fastener holes and
surrounding area for a crack or any other
damage. Replace any part that is cracked
with an airworthy part; replace any damaged
part with damage exceeding the maximum
repair damage limits with an airworthy part;
or repair any damaged part that is within the
maximum repair damage limits. Also, replace
any loose or working rivets.
(f) Special Flight Permits
Special flight permits may be issued in
accordance with 14 CFR 21.197 and 21.199
to operate the helicopter to a location where
the inspection requirements of this AD can
be accomplished. No special flight permits
will be issued to accomplish replacements or
repairs, or if a crack is suspected.
(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, Rotorcraft
Certification Office, Rotorcraft Directorate,
FAA, 2601 Meacham Blvd., Fort Worth,
Texas 76137; telephone (817) 222–5170;
email 7-avs-asw-170@faa.gov.
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Federal Register / Vol. 77, No. 237 / Monday, December 10, 2012 / Rules and Regulations
(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.
DEPARTMENT OF TRANSPORTATION
(h) Additional Information
RIN 2120–AA64
Erickson Air-Crane Service Bulletin No.
64F General-3, Revision C, dated December
12, 2007, which is not incorporated by
reference, contains additional information
about the subject of this AD. For this service
information, 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 cerickson@ericksonaircrane.com.
You may also review this service information
at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137.
Airworthiness Directives; Rolls-Royce
plc Turbofan Engines
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 5302, Rotorcraft Tail Boom.
(j) Material Incorporated by Reference
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(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Erickson Air-Crane Incorporated Service
Bulletin No. 64B20–6, Revision A, dated
December 12, 2007.
(ii) Reserved.
(3) For Erickson Air-Crane Incorporated
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
cerickson@ericksonaircrane.com.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on November
13, 2012.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2012–28434 Filed 12–7–12; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1117; Directorate
Identifier 2012–NE–25–AD; Amendment 39–
17275; AD 2012–24–05]
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Rolls-Royce plc (RR) RB211-Trent 900
series turbofan engines. This AD
requires inspection of the low pressure
turbine (LPT) bearing housing end cover
assembly in certain engines and, if
necessary, its replacement. This AD was
prompted by a Trent 900 engine
experiencing a high intermediate
pressure vibration fault, along with
other fluctuating engine parameters,
while in flight. We are issuing this AD
to prevent fracture of the oil transfer
tube, which could result in uncontained
failure of the engine and damage to the
airplane.
DATES: This AD becomes effective
December 26, 2012.
We must receive comments on this
AD by January 24, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of December 26, 2012.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the instructions for sending your
comments electronically.
• Mail: U.S. Department of
Transportation, 1200 New Jersey
Avenue SE., West Building Ground
Floor, Room W12–140, Washington, DC
20590–0001.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: (202) 493–2251.
For service information identified in
this AD, contact Rolls-Royce plc,
Corporate Communications, P.O. Box
31, Derby, England, DE248BJ; phone:
011–44–1332–242424; fax: 011–44–
1332–245418 or email from https://
www.rolls-royce.com/contact/
civil_team.jsp, or download the
publication from https://
SUMMARY:
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www.aeromanager.com. You may view
this service information at the FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803. For information on the
availability of this material at the FAA,
call 781–238–7125.
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, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (phone:
(800) 647–5527) is the same as the Mail
address provided in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Alan Strom, Aerospace Engineer, Engine
Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: 781–238–7143; fax: 781–238–
7199; email: alan.strom@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive AD No. 2012–
0145, dated August 6, 2012 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
During a revenue service flight, a Trent 900
engine experienced a high Intermediate
Pressure (IP/N2) vibration fault along with
several other fluctuating engine parameters,
including Low Pressure (LP/N1) faults. The
flight crew decided to throttle back the
engine to idle and performed an air turn
back. The other engines continued to operate
normally and an uneventful landing was
made.
The results of an initial investigation
revealed that the LP system was seized.
Removal of the Low Pressure Turbine (LPT)
bearing housing end cover revealed that the
oil transfer tube assembly had fractured
because the spherical seat between the oil
transfer tube and the end cover was missing
(not installed).
This non-conformity caused the fracture of
the oil transfer tube, leading to reduced oil
flow and subsequent damage to the LP and
IP bearings. Rolls-Royce has identified that
other Trent 900 engines could potentially be
affected.
The in-service event engine was
assembled at the factory by RR. After the
in-service event, RR inspected all LPT
bearing housing end cover assemblies
E:\FR\FM\10DER1.SGM
10DER1
]]>Agencies
[Federal Register Volume 77, Number 237 (Monday, December 10, 2012)]
[Rules and Regulations]
[Pages 73265-73268]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-28434]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1243; Directorate Identifier 2007-SW-03-AD;
Amendment 39-17267; AD 2012-23-11]
RIN 2120-AA64
Airworthiness Directives; Erickson Air-Crane Incorporated
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for
Erickson Air-Crane Incorporated (Erickson) Model S-64F helicopters.
This AD requires inspecting for cracking or working rivets in each left
and right splice fitting (transition fitting), the pylon bulkhead
assembly-canted (bulkhead assembly), and the pylon steel strap (strap).
This AD was prompted by several reports of cracking in the transition
fittings, the bulkhead assembly, and the pylon. The actions specified
by this AD are intended to detect cracking in the rotary rudder boom or
pylon due to fatigue, and to prevent failure from static overload and
subsequent loss of control of the helicopter.
DATES: This AD is effective January 14, 2013.
[[Page 73266]]
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of January 14,
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
cerickson@ericksonaircrane.com. You may review 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, Rotorcraft Certification Office, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5170;
email 7-avs-asw-170@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On November 26, 2008, at 73 FR 71952, 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 Erickson
Model S-64F helicopters with a transition fitting, part number (P/N)
6420-66341-101, -102, -103, or -104; bulkhead assembly, P/N 6420-66340-
041, -043, or -044; or a strap, P/N 6420-66301-119 or -127, installed.
That NPRM proposed to require inspecting for cracking or working rivets
in each transition fitting, the bulkhead assembly, the strap, and the
attaching rotary rudder boom and pylon structure, and repairing or
replacing any cracked or damaged part with an airworthy part. The NPRM
also proposed to require, for any part where you could not visually
determine that a crack does not exist, inspecting using a 10-power or
higher magnifying glass. If you could not determine that a crack does
not exist in the part after inspecting it with a 10-power or higher
magnifying glass, the NPRM proposed to require performing a fluorescent
particle inspection (FPI) of any part other than a strap, and
performing a magnetic particle inspection (MPI) of any strap. The NPRM
also proposed to require replacing any loose or working rivet. The
proposed requirements were intended to detect cracking in the rotary
rudder boom or pylon due to fatigue, and to prevent failure from static
overload and subsequent loss of control of the helicopter.
Comments
After our NPRM (73 FR 71952, November 26, 2008) was published, we
received comments from one commenter.
Request
A commenter from Erickson Air-Crane asked that we delete the
bulkhead assembly, P/N 6420-66340-041, from the applicability and
compliance section of the NPRM (73 FR 71952, November 26, 2008) since
that P/N is not used on Erickson Model S-64F helicopters. We agree and
have revised this AD accordingly.
The commenter also asked that we delete the words ``other than a
strap'' from the requirement to perform an FPI on a part other than a
strap if you cannot determine that a crack does not exist, and delete
the entire requirement to perform an MPI of the strap if you cannot
determine that a crack does not exist. The commenter states that an MPI
cannot be performed on the strap when it is installed on a helicopter;
instead an FPI of the strap would need to be performed with the other
parts. We partially agree. We agree that an MPI cannot be performed on
the strap while it is installed on the helicopter because the strap is
attached to the aluminum pylon section. An MPI for the strap was
initially proposed in the NPRM (73 FR 71952, November 26, 2008) because
this would be the type of inspection normally used for a steel part.
Instead of changing the MPI on the strap to an FPI as requested, after
further review, we determined that deleting this inspection, as well as
the magnifying glass inspection and certain FPIs that were proposed in
the NPRM, will not impact the overall level of safety. These
inspections were included in the event a visual inspection was
insufficient to determine whether a crack exists. If any additional
inspections are necessary to determine if a crack exists, a qualified
individual performing the inspection must make this determination.
FAA's Determination
We have reviewed the relevant information, considered the comments
received, and determined that an unsafe condition exists and is likely
to exist or develop on other products of the same type design and that
air safety and the public interest require adopting the AD requirements
as proposed with the changes described previously and minor editorial
changes. We have also revised the estimated costs of complying with
this AD to reflect an average labor rate of $85 per work-hour instead
of $80 per work-hour. These changes are consistent with the intent of
the proposals in the NPRM (73 FR 71952, November 26, 2008) and will not
increase the economic burden on any operator nor increase the scope of
the AD.
Related Service Information
We have reviewed Erickson Service Bulletin (SB) No. 64B20-6,
Revision A, dated December 12, 2007, which describes procedures for
inspecting the transition fittings, the bulkhead assembly, the strap,
and the attaching rotary rudder boom and pylon structure for cracking
or working rivets. We have also reviewed Erickson SB No. 64F General-3,
Revision C, dated December 12, 2007, which summarizes a listing of a
portion of the Model S-64F helicopter components, their part numbers,
and the corresponding SBs to use when performing the structural
inspections.
Costs of Compliance
We estimate that this AD will affect 7 helicopters of U.S.
Registry. We estimate that operators may incur the following costs in
order to comply with this AD. It will take about 0.75 work-hour to
visually inspect the transition fittings, skin panels, the bulkhead
assembly, strap, and pylon exterior in the strap area; we estimate 30
of these visual inspections per year. It will take about 0.50 work-hour
to visually inspect the pylon interior in the strap area; we estimate 4
of these visual inspections per year. It will take about 0.75 work-hour
to visually and fluorescent penetrant inspect the skin panels at the
transition fitting; we estimate performing these inspections 1 time per
year. It will take about 40 work-hours to repair a pylon structural
assembly. The average labor rate is $85 per work-hour and the cost for
required parts to repair a pylon structural assembly is approximately
$50,000. Based on these figures, we estimate the annual cost of the
inspections will be $2,146 per helicopter and $15,024 for the fleet on
[[Page 73267]]
U.S. operators. The estimated cost to repair a pylon structural
assembly, including the cost for replacement parts and labor, is
$53,400.
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.
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 adding the following new airworthiness
directive (AD):
2012-23-11 Erickson Air-Crane Incorporated: Amendment 39-17267;
Docket No. FAA-2008-1243; Directorate Identifier 2007-SW-03-AD.
(a) Applicability
This AD applies to Erickson Air-Crane Incorporated (Erickson)
Model S-64F helicopters with a left or right splice fitting
(transition fitting), part number (P/N) 6420-66341-101, -102, -103,
or -104; pylon bulkhead assembly-canted (bulkhead assembly), P/N
6420-66340-043 or -044; or a pylon steel strap (strap), P/N 6420-
66301-119 or -127, installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as cracking in the rotary
rudder boom or pylon due to fatigue, failure from static overload,
and subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective January 14, 2013.
(d) 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.
(e) Required Actions
(1) Within 20 hours time-in-service (TIS), and thereafter at
intervals not to exceed 20 hours (TIS):
(i) Visually inspect each transition fitting, P/N 6420-66341-
101, -102, -103, or -104, for a crack or working rivets on the
inboard face of the rotary rudder boom and pylon, paying particular
attention to the fastener attachment holes, as depicted in Figure 1,
Detail A, of the Accomplishment Instructions in Erickson Air-Crane
Incorporated Service Bulletin No. 64B20-6, Revision A, dated
December 12, 2007 (SB).
(ii) Visually inspect the outboard face of each rotary rudder
boom and pylon skin panel (skin panel) that attaches to the
transition fittings for a crack or working rivets in the transition
fitting attachment areas, paying particular attention to the
fastener attachment holes, as shown in Figure 1, Detail B, of the
Accomplishment Instructions in the SB.
(iii) Visually inspect the forward and aft sides of each
bulkhead assembly, P/N 6420-66340-043 or -044, for a crack. Pay
particular attention to the circled areas shown in Figure 2 of the
Accomplishment Instructions in the SB.
(iv) Visually inspect the upper 12 inches of each strap, P/N
6420-66301-119 or -127, for a crack or for working rivets as shown
in Figure 3 of the Accomplishment Instructions in the SB.
(v) Visually inspect the pylon for a crack or working rivets on
each side of the upper 12 inches of the strap, and also 6 inches
above the end of the strap as shown in Figure 3 of the
Accomplishment Instructions in the SB.
(2) For any pylon with a strap installed, within 155 hours TIS,
and thereafter at intervals not to exceed 155 hours TIS, remove the
inspection access covers, P/N 6420-66304-109 and P/N 6420-66303-125,
on the forward and aft sides of the pylon and visually inspect the
left-hand cap angle (longeron), P/N 6420-66304-136, and the interior
area of the pylon adjacent to the upper 12 inches of the strap, as
well as 6 inches above the end of the strap, for a crack or working
rivets, as shown in Figure 3 of the Accomplishment Instructions in
the SB.
(3) At each transition fitting replacement, which is required at
intervals not to exceed 8,300 hours TIS:
(i) With each transition fitting removed, visually inspect both
sides of each skin panel for a crack in the areas to which the
transition fitting attaches, paying particular attention to the
fastener attachment holes, as depicted in Details A and B, Figure 1,
of the Accomplishment Instructions in the SB.
(ii) Perform a fluorescent penetrant inspection of each skin
panel for a crack in the areas around the fastener holes where the
transition fittings attach to the rotary rudder boom and pylon.
(4) If there is a crack, before further flight, replace any
cracked part with an airworthy part, or repair the cracked part if
the damage is within the maximum repair damage limits.
Note to paragraph (e)(4) of this AD: The maximum repair damage
limitations are stated in the applicable Component and Repair
Overhaul Manual.
(5) If any loose or working rivets are found, before further
flight, remove the rivets and visually inspect the fastener holes
and surrounding area for a crack or any other damage. Replace any
part that is cracked with an airworthy part; replace any damaged
part with damage exceeding the maximum repair damage limits with an
airworthy part; or repair any damaged part that is within the
maximum repair damage limits. Also, replace any loose or working
rivets.
(f) Special Flight Permits
Special flight permits may be issued in accordance with 14 CFR
21.197 and 21.199 to operate the helicopter to a location where the
inspection requirements of this AD can be accomplished. No special
flight permits will be issued to accomplish replacements or repairs,
or if a crack is suspected.
(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, Rotorcraft Certification Office,
Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222-5170; email 7-avs-asw-170@faa.gov.
[[Page 73268]]
(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 Air-Crane Service Bulletin No. 64F General-3, Revision
C, dated December 12, 2007, which is not incorporated by reference,
contains additional information about the subject of this AD. For
this service information, 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 cerickson@ericksonaircrane.com. You may
also review this service 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: 5302, Rotorcraft
Tail Boom.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Erickson Air-Crane Incorporated Service Bulletin No. 64B20-
6, Revision A, dated December 12, 2007.
(ii) Reserved.
(3) For Erickson Air-Crane Incorporated 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 cerickson@ericksonaircrane.com.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137. For information on the availability of this
material at the FAA, call (817) 222-5110.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call (202) 741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on November 13, 2012.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2012-28434 Filed 12-7-12; 8:45 am]
BILLING CODE 4910-13-P
