[Federal Register Volume 80, Number 21 (Monday, February 2, 2015)]
[Rules and Regulations]
[Pages 5454-5457]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-01800]
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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.
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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 http://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 http://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
http://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
[email protected].
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 [email protected].
(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 http://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 http://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]
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