Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) Helicopters, 5454-5457 [2015-01800]
Download as PDF
5454
Federal Register / Vol. 80, No. 21 / Monday, February 2, 2015 / Rules and Regulations
required, triggered by hours since last
inspection (HSLI). We are issuing this AD to
prevent failure of 3rd-stage and 4th-stage
turbine wheel blades, which could cause
engine failure and damage to the aircraft.
DEPARTMENT OF TRANSPORTATION
(e) Compliance
[Docket No. FAA–2015–0049; Directorate
Identifier 2014–SW–037–AD; Amendment
39–18096; AD 2015–02–27]
Comply with this AD within the
compliance times specified, unless already
done. After the effective date of this AD:
(1) Within 1,750 HSLI, remove the affected
turbine wheels and perform a visual
inspection and a fluorescent-penetrant
inspection (FPI) on the removed turbine
wheels for cracks at the trailing edge of the
turbine blades near the fillet at the rim.
(2) Any time the power turbine is
disassembled, perform a visual inspection
and an FPI on the affected turbine wheels for
cracks at the trailing edge of the turbine
blades, near the fillet at the rim.
(3) Thereafter, re-inspect every 1,750 HSLI.
(4) Do not return to service any turbine
wheels that have cracks detected.
(f) Alternative Methods of Compliance
(AMOCs)
The Manager, Chicago Aircraft
Certification Office, may approve AMOCs for
this AD. Use the procedures found in 14 CFR
39.19 to make your request.
(g) Related Information
(1) For more information about this AD,
contact John Tallarovic, Aerospace Engineer,
Chicago Aircraft Certification Office, FAA,
2300 E. Devon Ave., Des Plaines, IL 60018;
phone: 847–294–8180; fax: 847–294–7834;
email: john.m.tallarovic@faa.gov.
(2) RRC Alert Commercial Engine Bulletin
(CEB) No. CEB–A–1407, Revision 3, dated
May 19, 2014, and Alert CEB No. CEB–A–72–
4098, Revision 3, dated May 19, 2014
(combined into one document), which are
not incorporated by reference in this AD, can
be obtained from RRC, using the contact
information in paragraph (g)(3) of this AD.
(3) For service information identified in
this AD, contact Rolls-Royce Corporation
Customer Support, 450 South Meridian
Street, Indianapolis, IN 46225–1103; phone:
888–255–4766 or 317–230–2720; email:
helicoptercustsupp@rolls-royce.com;
Internet: www.rolls-royce.com.
(4) 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.
(h) Material Incorporated by Reference
wreier-aviles on DSK5TPTVN1PROD with RULES
None.
Issued in Burlington, Massachusetts, on
January 20, 2015.
Colleen M. D’Alessandro,
Assistant Directorate Manager, Engine &
Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2015–01371 Filed 1–30–15; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
15:25 Jan 30, 2015
Jkt 235001
Federal Aviation Administration
14 CFR Part 39
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters (Previously Eurocopter
France) Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2013–19–
19 for certain Eurocopter France Model
AS332C, AS332L, AS332L1, AS332L2,
and EC225LP helicopters. AD 2013–19–
19 required replacing certain serialnumbered main gearbox (MGB) bevel
gear vertical shafts and inspecting and
replacing, if necessary, each MGB bevel
gear vertical shaft (shaft). This new AD
requires the same actions as AD 2013–
19–19 but corrects an error in the term
used to identify an inspection
qualification and updates the type
certificate holder’s name. This AD is
prompted by two incidents of
emergency ditching after warning
indications of loss of MGB oil pressure.
These actions are intended to detect a
cracked shaft, which could result in loss
of MGB oil pressure, loss of the MGB
lubrication system, and subsequent loss
of control of the helicopter.
DATES: This AD is effective February 17,
2015.
We must receive comments on this
AD by April 3, 2015.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
SUMMARY:
Docket Operations Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the European
Aviation Safety Agency (EASA) AD, the
economic evaluation, any comments
received, and other information. The
street address for the Docket Operations
Office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
For service information identified in
this AD, contact Airbus Helicopters,
Inc., 2701 N. Forum Drive, Grand
Prairie, TX 75052; telephone (972) 641–
0000 or (800) 232–0323; fax (972) 641–
3775; or at https://
www.airbushelicopters.com/techpub.
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.
FOR FURTHER INFORMATION CONTACT:
James Blyn, Aviation Safety Engineer,
Regulations and Policy Group,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
james.blyn@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments prior to it becoming effective.
However, we invite you to participate in
this rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that resulted from
adopting this AD. The most helpful
comments reference a specific portion of
the AD, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit them only one time. We will file
in the docket all comments that we
receive, as well as a report summarizing
each substantive public contact with
FAA personnel concerning this
rulemaking during the comment period.
We will consider all the comments we
receive and may conduct additional
rulemaking based on those comments.
Examining the AD Docket
Discussion
You may examine the AD docket on
the Internet at https://
www.regulations.gov or in person at the
On September 9, 2013, we issued AD
2013–19–19 (78 FR 60188, October 1,
2013), which required replacing certain
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
E:\FR\FM\02FER1.SGM
02FER1
wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 80, No. 21 / Monday, February 2, 2015 / Rules and Regulations
serial-numbered shafts because they are
no longer airworthy. Also, AD 2013–19–
19 required certain inspections at
specified intervals of each shaft for a
crack and, if there is a crack, replacing
the shaft with an airworthy part before
further flight. AD 2013–19–19 was
prompted by two incidents of
emergency ditching after warning
indication of loss of oil pressure. A full
circumferential crack of the lower shaft
occurred in the area where two sections
of the shaft are welded together. As a
result, the shaft stopped driving the
main and backup oil pumps, leading to
warning indications of the loss of the
MGB lubrication. The crew activated the
MGB emergency lubrication system, and
following a warning that indicated
failure of that system, performed a
controlled ditching into the sea. The
actions in AD 2013–19–19 were
intended to detect a cracked shaft,
which could result in loss of MGB oil
pressure, loss of the MGB lubrication
system, and subsequent loss of control
of the helicopter.
AD 2013–19–19 was prompted by AD
No. 2013–0138R1, dated July 15, 2013,
issued by EASA, which is the Technical
Agent for the Member States of the
European Union, to correct an unsafe
condition for the Eurocopter Model
AS332C, AS332C1, AS332L, AS332L1,
AS332L2, and EC225LP helicopters, all
serial numbers, with certain partnumbered shafts, installed. EASA
advises of two events of the Model
EC225LP helicopters where an
emergency ditching was performed after
warning indication of MGB loss of oil
pressure and subsequent additional red
alarm on the MGB emergency
lubrication system (EMLUB). EASA also
advises of a full circumferential crack of
the lower shaft in the area where the
two sections of the shaft are welded
together. As a result, the vertical shaft
ceased to drive the main and backup oil
pumps leading to warning indications of
the loss of the MGB main and standby
oil lubrication systems. The crew
activated the EMLUB system and,
following a subsequent warning
indicating failure of that system,
performed a controlled ditching into the
sea.
EASA advises that Eurocopter
determined after investigating the
incidents that the shaft failures resulted
from a combination of factors, including
stress hot-spots induced by the shaft
geometry, residual stresses in the shaft
weld material resulting from the
manufacturing process, and corrosion
pitting inside the shaft on areas where
gear spline wear particles accumulated.
The EASA AD allows continued
operations under certain conditions if
VerDate Sep<11>2014
15:25 Jan 30, 2015
Jkt 235001
equipped with a Vibration Health
Monitoring System (VHM).
Actions Since We Issued AD 2013–19–
19
After we issued AD 2013–19–19 (78
FR 60188, October 1, 2013), we
discovered an incorrect term used to
identify the inspection qualification for
one of the inspections in the AD.
Specifically, the AD included in the
Required Actions section, under
paragraph (e)(3)(ii), the following:
‘‘Before further flight and thereafter at
intervals not to exceed 11.5 hours TIS,
remove the main jet and emergency spraying
jet, and ultrasonic inspect the shaft in the
weld area for a crack, which must be done
by a Level II or Level III inspector certified
in the eddy current fault detection method in
the Aeronautics Sector according to the
EN4179 or NAS410 standard, or’’.
As published, the term ‘‘eddy
current’’ used to identify the inspection
qualification is incorrect. The correct
term is ‘‘ultrasonic.’’ Also, since the
issuance of AD 2013–19–19, the type
certificate holder’s name changed from
Eurocopter France to Airbus
Helicopters. This AD requires the same
actions as AD 2013–19–19 but corrects
the inspection qualification and updates
the type certificate holder’s name.
FAA’s Determination
These helicopters have been approved
by the aviation authority of France and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with France, EASA, its
technical representative, has notified us
of the unsafe condition described in the
EASA AD. We are issuing this AD
because we evaluated all information
provided by EASA and determined the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs.
Interim Action
We consider this AD interim action.
The design approval holder is currently
developing a newly-designed shaft that
will address the unsafe condition
identified in this AD. Once the newlydesigned shaft is developed, approved,
and available, we might consider
additional rulemaking.
Related Service Information
Eurocopter (now Airbus Helicopters)
issued the following service
information:
• Alert Service Bulletin (ASB) No.
AS332–01.00.82, Revision 3, dated July
8, 2013, for the Model AS332C, C1, L,
L1, L2 civil helicopters and Model
AS332B, B1, M, M1, and F1 military
model helicopters. The ASB defines
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
5455
inspection requirements to detect a
crack in the shaft, and
• ASB No. EC225–04A009, Revision
3, dated July 8, 2013 for Model EC225LP
helicopters. The ASB defines inspection
requirements to detect a crack in the
shaft.
AD Requirements
This AD requires:
• Removing certain part-numbered
and serial-numbered shafts that are no
longer considered airworthy from
service.
• For certain model helicopters,
before further flight and at specified
intervals, eddy current inspecting the
shaft for a crack in the area of the weld.
• For Model EC225LP helicopters,
before further flight, either installing a
placard in full view of the pilot with the
following statement in red, 6 millimeter
letters on a white background:
‘‘MAXIMUM CONTINUOUS TORQUE
LIMITED TO 70% DURING LEVEL
FLIGHTS AT IAS EQUAL TO OR MORE
THAN 60 KTS,’’ and before further
flight and thereafter at intervals not to
exceed 11.5 hours TIS, removing the
main jet and emergency spraying jet,
and ultrasonic inspecting the shaft in
the weld area for a crack; or
• Before further flight and thereafter
at intervals not to exceed 8 hours TIS,
removing the main jet and emergency
spraying jet, and ultrasonic inspecting
the shaft for a crack in the area of the
weld.
• Each eddy current or ultrasonic
inspection be done by a Level II or Level
III operator certified in the eddy current
or ultrasonic fault detection method in
the Aeronautics Sector according to the
EN4179 or NAS410 standard.
• If there is a crack, before further
flight, replacing the shaft with an
airworthy part.
Differences Between This AD and the
EASA AD
The EASA AD allows continued
operations under certain conditions if
equipped with a VHM. The VHM
system is validated by FAA for
information only, and therefore we have
not adopted that portion of the EASA
AD.
Costs of Compliance
We estimate that this AD affects 4
helicopters of U.S. Registry and that
operators may incur the following costs
to comply with this AD. At $85 per
work hour; minimal cost to install a
placard; and 3 work hours to inspect
each shaft for a crack, it will cost $255
per helicopter and $1,020 for the fleet
per inspection. It will take 44 work
hours to replace a shaft and $1,243,350
E:\FR\FM\02FER1.SGM
02FER1
5456
Federal Register / Vol. 80, No. 21 / Monday, February 2, 2015 / Rules and Regulations
for required parts for a total of
$1,247,090 per helicopter.
FAA’s Justification and Determination
of the Effective Date
Providing an opportunity for public
comments before adopting these AD
requirements would delay
implementing the safety actions needed
to correct this known unsafe condition.
Therefore, we find that the risk to the
flying public justifies waiving notice
and comment before adopting this rule
because the required corrective actions
must be done within 10 hours TIS and
at repeated intervals within short time
periods.
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we determined that notice and
opportunity for public comment before
issuing this AD are impracticable and
that good cause exists for making this
amendment effective in less than 30
days.
Authority for This Rulemaking
wreier-aviles on DSK5TPTVN1PROD with RULES
Regulatory Findings
We determined that 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, 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);
15:25 Jan 30, 2015
Jkt 235001
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:
■
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.
VerDate Sep<11>2014
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.
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2013–19–19, Amendment 39–17601 (78
FR 60188, October 1, 2013), and adding
the following new (AD):
■
2015–02–27 Airbus Helicopters
(Previously Eurocopter France):
Amendment 39–18096; Docket No.
FAA–2015–0049; Directorate Identifier
2014–SW–037–AD.
(a) Applicability
This AD applies to Airbus Helicopters
Model AS332C, AS332L, AS332L1, AS332L2,
and EC225LP helicopters with a main
gearbox (MGB) bevel gear vertical shaft
(shaft), part number (P/N) 332A32–5101–00,
332A32–5101–05, 332A32–5101–10, or
332A32–5101–15, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
cracked shaft resulting in loss of MGB oil
pressure. These actions are intended to
prevent loss of the MGB lubrication system
and subsequent loss of control of the
helicopter.
(c) Affected ADs
This AD supersedes AD 2013–19–19,
Amendment 39–17601 (78 FR 60188, October
1, 2013).
(d) Effective Date
This AD becomes effective February 17,
2015.
(e) Compliance
You are responsible for performing each
action required by this AD within the
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
specified compliance time unless it has
already been accomplished prior to that time.
(f) Required Actions
(1) Before further flight, remove shaft, P/N
332A32–5101–00, 332A32–5101–05,
332A32–5101–10, or 332A32–5101–15, with
S/N M330 through M340 (inclusive) and
S/N M370 through M5000 (inclusive) from
service, which are no longer considered
airworthy.
(2) For Model AS332C, AS332L, AS332L1,
and AS332L2 helicopters, before further
flight and thereafter at intervals not to exceed
10 hours time-in-service (TIS), eddy current
inspect the shaft for a crack in the area of the
weld, which must be done by a Level II or
Level III inspector certified in the eddy
current fault detection method in the
Aeronautics Sector according to the EN4179
or NAS410 standard.
(3) For Model EC225LP helicopters, either
do paragraphs (3)(i) and (3)(ii) or do
paragraph (3)(iii).
(i) Before further flight, install a placard in
full view of the pilot with the following
statement in red, 6 millimeter letters on a
white background: ‘‘MAXIMUM
CONTINUOUS TORQUE LIMITED TO 70%
DURING LEVEL FLIGHTS AT IAS EQUAL
TO OR MORE THAN 60 KTS,’’ and
(ii) Before further flight and thereafter at
intervals not to exceed 11.5 hours TIS,
remove the main jet and emergency spraying
jet, and ultrasonic inspect the shaft in the
weld area for a crack, which must be done
by a Level II or Level III inspector certified
in the ultrasonic fault detection method in
the Aeronautics Sector according to the
EN4179 or NAS410 standard, or
(iii) Before further flight, and thereafter at
intervals not to exceed 8 hours TIS, remove
the main jet and emergency spraying jet, and
ultrasonic inspect the shaft for a crack in the
area of the weld, which must be done by a
Level II or Level III operator certified in the
ultrasonic fault detection method in the
Aeronautics Sector according to the EN4179
or NAS410 standard.
(4) If there is a crack, before further flight,
replace the shaft with an airworthy part.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to James Blyn,
Aviation Safety Engineer, Regulations and
Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
james.blyn@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
(1) Eurocopter Alert Service Bulletin No.
AS332–01.00.82 and Alert Service Bulletin
No. EC225–04A009, both Revision 3 and both
dated July 8, 2013, which are not
E:\FR\FM\02FER1.SGM
02FER1
Federal Register / Vol. 80, No. 21 / Monday, February 2, 2015 / Rules and Regulations
incorporated by reference, contain additional
information about the subject of this AD. For
service information identified in this AD,
contact Airbus Helicopters, Inc., 2701 N.
Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–0323;
fax (972) 641–3775; or at https://
www.airbushelicopters.com/techpub. You
may review a copy of the service information
at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2013–0138R1, dated July 15, 2013. You
may view the EASA AD at https://
www.regulations.gov in the Docket No. FAA–
2015–0049.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6320 Main rotor gearbox.
Issued in Fort Worth, Texas, on January 16,
2015.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2015–01800 Filed 1–30–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HOMELAND
SECURITY
Coast Guard
33 CFR Part 117
[Docket No. USCG–2015–0003]
Drawbridge Operation Regulation;
Bonfouca Bayou, Slidell, LA
Coast Guard, DHS.
Notice of temporary deviation
from regulations.
AGENCY:
ACTION:
The Coast Guard has issued a
temporary deviation from the regulation
governing the operation of the State
Route 433 (SR433) Bridge across
Bonfouca Bayou, mile 7.0, at Slidell, St.
Tammany Parish, Louisiana. This
deviation provides for the bridge to
remain closed to navigation for five and
a half consecutive hours in the morning
and four and a half hours in the
afternoon with an opening in the middle
to pass vessels. There will be a two-hour
notice to pass vessels in the evenings
and a four-hour notice to pass vessels on
weekends. This deviation will last for
33 consecutive days. The purpose of the
closure is to conduct scheduled
maintenance and repairs to the
drawbridge.
wreier-aviles on DSK5TPTVN1PROD with RULES
SUMMARY:
This deviation is effective from
6:30 a.m. on February 2, 2015 through
5:30 p.m. on March 6, 2015.
ADDRESSES: The docket for this
deviation, [USCG–2015–0003] is
DATES:
VerDate Sep<11>2014
15:25 Jan 30, 2015
Jkt 235001
available at https://www.regulations.gov.
Type the docket number in the
‘‘SEARCH’’ box and click ‘‘SEARCH.’’
Click on Open Docket Folder on the line
associated with this rulemaking. You
may also visit the Docket Management
Facility in Room W12–140 on the
ground floor of the Department of
Transportation West Building, 1200
New Jersey Avenue SE., Washington,
DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays.
FOR FURTHER INFORMATION CONTACT: If
you have questions on this temporary
deviation, call or email Jim
Wetherington, Bridge Administration
Branch, Coast Guard, telephone
(504)671–2128, email
james.r.wetherington@uscg.mil. If you
have questions on viewing the docket,
call Cheryl F. Collins, Program Manager,
Docket Operations, telephone 202–366–
9826.
SUPPLEMENTARY INFORMATION: The
Louisiana Department of Transportation
and Development (LDOTD) requested a
temporary deviation from the normal
operation of the drawbridge at 33 CFR
117.433 in order to perform scheduled
maintenance and rehabilitation. This is
necessary for the continued operation of
the bridge. This deviation allows the
draw of the SR433 Bridge across
Bonfouca Bayou, mile 7.0, to remain
closed to navigation for five and a half
consecutive hours in the morning and
four and a half hours in the afternoon
with an opening in the middle to pass
vessels. This deviation is effective from
6:30 a.m. to noon and then again from
1 p.m. through 5:30 p.m. daily from
February 2 through March 6, 2015.
There will be two-hour notice required
in the evenings and a four-hour notice
all day on the weekends.
Broadcast Notice to Mariners will be
used to update mariners of any changes
in this deviation.
The bridge has a vertical clearance of
8 feet above high water in the closed-tonavigation position and unlimited
clearance above high water in the opento-navigation position. There is 125 feet
fender to fender horizontal clearance.
Navigation on the waterway consists of
tugs with tows, commercial fishing
vessels and mainly recreational craft.
There is no alternate route.
CEC (the contractor for the
maintenance and rehab) and the Coast
Guard have coordinated the closure
with waterway users, industry, and
other Coast Guard units. This date and
this schedule were chosen to minimize
the significant effects on vessel traffic.
In accordance with 33 CFR 117.35(e),
the drawbridge must return to its regular
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
5457
operating schedule immediately at the
end of the effective period of this
temporary deviation. This deviation
from the operating regulations is
authorized under 33 CFR 117.35.
Dated: January 27, 2015.
David M. Frank,
Bridge Administrator, Eighth District.
[FR Doc. 2015–01826 Filed 1–30–15; 8:45 am]
BILLING CODE 9110–04–P
ENVIRONMENTAL PROTECTION
AGENCY
40 CFR Parts 9 and 721
[EPA–HQ–OPPT–2014–0714; FRL–9919–68]
RIN 2070–AB27
Significant New Use Rules on Certain
Chemical Substances
Environmental Protection
Agency (EPA).
ACTION: Direct final rule.
AGENCY:
EPA is promulgating
significant new use rules (SNURs) under
the Toxic Substances Control Act
(TSCA) for 27 chemical substances
which were the subject of
premanufacture notices (PMNs). Two of
these chemical substances are subject to
TSCA section 5(e) consent orders issued
by EPA. This action requires persons
who intend to manufacture (including
import) or process any of these 27
chemical substances for an activity that
is designated as a significant new use by
this rule to notify EPA at least 90 days
before commencing that activity. The
required notification will provide EPA
with the opportunity to evaluate the
intended use and, if necessary, to
prohibit or limit that activity before it
occurs.
SUMMARY:
This rule is effective on April 3,
2015. For purposes of judicial review,
this rule shall be promulgated at 1 p.m.
(e.s.t.) on February 17, 2015.
Written adverse or critical comments,
or notice of intent to submit adverse or
critical comments, on one or more of
these SNURs must be received on or
before March 4, 2015 (see Unit VI. of the
SUPPLEMENTARY INFORMATION). If EPA
receives written adverse or critical
comments, or notice of intent to submit
adverse or critical comments, on one or
more of these SNURs before March 4,
2015, EPA will withdraw the relevant
sections of this direct final rule before
its effective date.
For additional information on related
reporting requirement dates, see Units
I.A., VI., and VII. of the SUPPLEMENTARY
INFORMATION.
DATES:
E:\FR\FM\02FER1.SGM
02FER1
Agencies
[Federal Register Volume 80, Number 21 (Monday, February 2, 2015)]
[Rules and Regulations]
[Pages 5454-5457]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-01800]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0049; Directorate Identifier 2014-SW-037-AD;
Amendment 39-18096; AD 2015-02-27]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters (Previously
Eurocopter France) Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2013-19-19 for
certain Eurocopter France Model AS332C, AS332L, AS332L1, AS332L2, and
EC225LP helicopters. AD 2013-19-19 required replacing certain serial-
numbered main gearbox (MGB) bevel gear vertical shafts and inspecting
and replacing, if necessary, each MGB bevel gear vertical shaft
(shaft). This new AD requires the same actions as AD 2013-19-19 but
corrects an error in the term used to identify an inspection
qualification and updates the type certificate holder's name. This AD
is prompted by two incidents of emergency ditching after warning
indications of loss of MGB oil pressure. These actions are intended to
detect a cracked shaft, which could result in loss of MGB oil pressure,
loss of the MGB lubrication system, and subsequent loss of control of
the helicopter.
DATES: This AD is effective February 17, 2015.
We must receive comments on this AD by April 3, 2015.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
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 European Aviation Safety
Agency (EASA) AD, the economic evaluation, any comments received, and
other information. The street address for the Docket Operations Office
(telephone 800-647-5527) is in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
For service information identified in this AD, contact Airbus
Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at
https://www.airbushelicopters.com/techpub. 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.
FOR FURTHER INFORMATION CONTACT: James Blyn, Aviation Safety Engineer,
Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham
Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email
james.blyn@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments prior to it becoming effective. However, we
invite you to participate in this rulemaking by submitting written
comments, data, or views. We also invite comments relating to the
economic, environmental, energy, or federalism impacts that resulted
from adopting this AD. The most helpful comments reference a specific
portion of the AD, explain the reason for any recommended change, and
include supporting data. To ensure the docket does not contain
duplicate comments, commenters should send only one copy of written
comments, or if comments are filed electronically, commenters should
submit them only one time. We will file in the docket all comments that
we receive, as well as a report summarizing each substantive public
contact with FAA personnel concerning this rulemaking during the
comment period. We will consider all the comments we receive and may
conduct additional rulemaking based on those comments.
Discussion
On September 9, 2013, we issued AD 2013-19-19 (78 FR 60188, October
1, 2013), which required replacing certain
[[Page 5455]]
serial-numbered shafts because they are no longer airworthy. Also, AD
2013-19-19 required certain inspections at specified intervals of each
shaft for a crack and, if there is a crack, replacing the shaft with an
airworthy part before further flight. AD 2013-19-19 was prompted by two
incidents of emergency ditching after warning indication of loss of oil
pressure. A full circumferential crack of the lower shaft occurred in
the area where two sections of the shaft are welded together. As a
result, the shaft stopped driving the main and backup oil pumps,
leading to warning indications of the loss of the MGB lubrication. The
crew activated the MGB emergency lubrication system, and following a
warning that indicated failure of that system, performed a controlled
ditching into the sea. The actions in AD 2013-19-19 were intended to
detect a cracked shaft, which could result in loss of MGB oil pressure,
loss of the MGB lubrication system, and subsequent loss of control of
the helicopter.
AD 2013-19-19 was prompted by AD No. 2013-0138R1, dated July 15,
2013, issued by EASA, which is the Technical Agent for the Member
States of the European Union, to correct an unsafe condition for the
Eurocopter Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP
helicopters, all serial numbers, with certain part-numbered shafts,
installed. EASA advises of two events of the Model EC225LP helicopters
where an emergency ditching was performed after warning indication of
MGB loss of oil pressure and subsequent additional red alarm on the MGB
emergency lubrication system (EMLUB). EASA also advises of a full
circumferential crack of the lower shaft in the area where the two
sections of the shaft are welded together. As a result, the vertical
shaft ceased to drive the main and backup oil pumps leading to warning
indications of the loss of the MGB main and standby oil lubrication
systems. The crew activated the EMLUB system and, following a
subsequent warning indicating failure of that system, performed a
controlled ditching into the sea.
EASA advises that Eurocopter determined after investigating the
incidents that the shaft failures resulted from a combination of
factors, including stress hot-spots induced by the shaft geometry,
residual stresses in the shaft weld material resulting from the
manufacturing process, and corrosion pitting inside the shaft on areas
where gear spline wear particles accumulated.
The EASA AD allows continued operations under certain conditions if
equipped with a Vibration Health Monitoring System (VHM).
Actions Since We Issued AD 2013-19-19
After we issued AD 2013-19-19 (78 FR 60188, October 1, 2013), we
discovered an incorrect term used to identify the inspection
qualification for one of the inspections in the AD. Specifically, the
AD included in the Required Actions section, under paragraph
(e)(3)(ii), the following:
``Before further flight and thereafter at intervals not to
exceed 11.5 hours TIS, remove the main jet and emergency spraying
jet, and ultrasonic inspect the shaft in the weld area for a crack,
which must be done by a Level II or Level III inspector certified in
the eddy current fault detection method in the Aeronautics Sector
according to the EN4179 or NAS410 standard, or''.
As published, the term ``eddy current'' used to identify the
inspection qualification is incorrect. The correct term is
``ultrasonic.'' Also, since the issuance of AD 2013-19-19, the type
certificate holder's name changed from Eurocopter France to Airbus
Helicopters. This AD requires the same actions as AD 2013-19-19 but
corrects the inspection qualification and updates the type certificate
holder's name.
FAA's Determination
These helicopters have been approved by the aviation authority of
France and are approved for operation in the United States. Pursuant to
our bilateral agreement with France, EASA, its technical
representative, has notified us of the unsafe condition described in
the EASA AD. We are issuing this AD because we evaluated all
information provided by EASA and determined the unsafe condition exists
and is likely to exist or develop on other helicopters of these same
type designs.
Interim Action
We consider this AD interim action. The design approval holder is
currently developing a newly-designed shaft that will address the
unsafe condition identified in this AD. Once the newly-designed shaft
is developed, approved, and available, we might consider additional
rulemaking.
Related Service Information
Eurocopter (now Airbus Helicopters) issued the following service
information:
Alert Service Bulletin (ASB) No. AS332-01.00.82, Revision
3, dated July 8, 2013, for the Model AS332C, C1, L, L1, L2 civil
helicopters and Model AS332B, B1, M, M1, and F1 military model
helicopters. The ASB defines inspection requirements to detect a crack
in the shaft, and
ASB No. EC225-04A009, Revision 3, dated July 8, 2013 for
Model EC225LP helicopters. The ASB defines inspection requirements to
detect a crack in the shaft.
AD Requirements
This AD requires:
Removing certain part-numbered and serial-numbered shafts
that are no longer considered airworthy from service.
For certain model helicopters, before further flight and
at specified intervals, eddy current inspecting the shaft for a crack
in the area of the weld.
For Model EC225LP helicopters, before further flight,
either installing a placard in full view of the pilot with the
following statement in red, 6 millimeter letters on a white background:
``MAXIMUM CONTINUOUS TORQUE LIMITED TO 70% DURING LEVEL FLIGHTS AT IAS
EQUAL TO OR MORE THAN 60 KTS,'' and before further flight and
thereafter at intervals not to exceed 11.5 hours TIS, removing the main
jet and emergency spraying jet, and ultrasonic inspecting the shaft in
the weld area for a crack; or
Before further flight and thereafter at intervals not to
exceed 8 hours TIS, removing the main jet and emergency spraying jet,
and ultrasonic inspecting the shaft for a crack in the area of the
weld.
Each eddy current or ultrasonic inspection be done by a
Level II or Level III operator certified in the eddy current or
ultrasonic fault detection method in the Aeronautics Sector according
to the EN4179 or NAS410 standard.
If there is a crack, before further flight, replacing the
shaft with an airworthy part.
Differences Between This AD and the EASA AD
The EASA AD allows continued operations under certain conditions if
equipped with a VHM. The VHM system is validated by FAA for information
only, and therefore we have not adopted that portion of the EASA AD.
Costs of Compliance
We estimate that this AD affects 4 helicopters of U.S. Registry and
that operators may incur the following costs to comply with this AD. At
$85 per work hour; minimal cost to install a placard; and 3 work hours
to inspect each shaft for a crack, it will cost $255 per helicopter and
$1,020 for the fleet per inspection. It will take 44 work hours to
replace a shaft and $1,243,350
[[Page 5456]]
for required parts for a total of $1,247,090 per helicopter.
FAA's Justification and Determination of the Effective Date
Providing an opportunity for public comments before adopting these
AD requirements would delay implementing the safety actions needed to
correct this known unsafe condition. Therefore, we find that the risk
to the flying public justifies waiving notice and comment before
adopting this rule because the required corrective actions must be done
within 10 hours TIS and at repeated intervals within short time
periods.
Since an unsafe condition exists that requires the immediate
adoption of this AD, we determined that notice and opportunity for
public comment before issuing this AD are impracticable and that good
cause exists for making this amendment effective in less than 30 days.
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
We determined that 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, 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 Airworthiness Directive (AD)
2013-19-19, Amendment 39-17601 (78 FR 60188, October 1, 2013), and
adding the following new (AD):
2015-02-27 Airbus Helicopters (Previously Eurocopter France):
Amendment 39-18096; Docket No. FAA-2015-0049; Directorate Identifier
2014-SW-037-AD.
(a) Applicability
This AD applies to Airbus Helicopters Model AS332C, AS332L,
AS332L1, AS332L2, and EC225LP helicopters with a main gearbox (MGB)
bevel gear vertical shaft (shaft), part number (P/N) 332A32-5101-00,
332A32-5101-05, 332A32-5101-10, or 332A32-5101-15, certificated in
any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a cracked shaft
resulting in loss of MGB oil pressure. These actions are intended to
prevent loss of the MGB lubrication system and subsequent loss of
control of the helicopter.
(c) Affected ADs
This AD supersedes AD 2013-19-19, Amendment 39-17601 (78 FR
60188, October 1, 2013).
(d) Effective Date
This AD becomes effective February 17, 2015.
(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, remove shaft, P/N 332A32-5101-00,
332A32-5101-05, 332A32-5101-10, or 332A32-5101-15, with S/N M330
through M340 (inclusive) and S/N M370 through M5000 (inclusive) from
service, which are no longer considered airworthy.
(2) For Model AS332C, AS332L, AS332L1, and AS332L2 helicopters,
before further flight and thereafter at intervals not to exceed 10
hours time-in-service (TIS), eddy current inspect the shaft for a
crack in the area of the weld, which must be done by a Level II or
Level III inspector certified in the eddy current fault detection
method in the Aeronautics Sector according to the EN4179 or NAS410
standard.
(3) For Model EC225LP helicopters, either do paragraphs (3)(i)
and (3)(ii) or do paragraph (3)(iii).
(i) Before further flight, install a placard in full view of the
pilot with the following statement in red, 6 millimeter letters on a
white background: ``MAXIMUM CONTINUOUS TORQUE LIMITED TO 70% DURING
LEVEL FLIGHTS AT IAS EQUAL TO OR MORE THAN 60 KTS,'' and
(ii) Before further flight and thereafter at intervals not to
exceed 11.5 hours TIS, remove the main jet and emergency spraying
jet, and ultrasonic inspect the shaft in the weld area for a crack,
which must be done by a Level II or Level III inspector certified in
the ultrasonic fault detection method in the Aeronautics Sector
according to the EN4179 or NAS410 standard, or
(iii) Before further flight, and thereafter at intervals not to
exceed 8 hours TIS, remove the main jet and emergency spraying jet,
and ultrasonic inspect the shaft for a crack in the area of the
weld, which must be done by a Level II or Level III operator
certified in the ultrasonic fault detection method in the
Aeronautics Sector according to the EN4179 or NAS410 standard.
(4) If there is a crack, before further flight, replace the
shaft with an airworthy part.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to James Blyn, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-
5110; email james.blyn@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
(1) Eurocopter Alert Service Bulletin No. AS332-01.00.82 and
Alert Service Bulletin No. EC225-04A009, both Revision 3 and both
dated July 8, 2013, which are not
[[Page 5457]]
incorporated by reference, contain additional information about the
subject of this AD. For service information identified in this AD,
contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax
(972) 641-3775; or at https://www.airbushelicopters.com/techpub. You
may review a copy of the service information at the FAA, Office of
the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room
663, Fort Worth, Texas 76137.
(2) The subject of this AD is addressed in European Aviation
Safety Agency (EASA) AD No. 2013-0138R1, dated July 15, 2013. You
may view the EASA AD at https://www.regulations.gov in the Docket No.
FAA-2015-0049.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 6320 Main rotor
gearbox.
Issued in Fort Worth, Texas, on January 16, 2015.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2015-01800 Filed 1-30-15; 8:45 am]
BILLING CODE 4910-13-P