Airworthiness Directives; Airbus Helicopters, 56109-56112 [2019-22567]
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Federal Register / Vol. 84, No. 203 / Monday, October 21, 2019 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0738; Product
Identifier 2019–SW–017–AD; Amendment
39–19749; AD 2019–19–13]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Helicopters Model EC225LP
helicopters. This AD requires
determining the total hours time-inservice (TIS) of the free wheel shafts of
certain main rotor gearboxes (MGBs),
replacing the MGB or right-hand side
(RH) free wheel shaft, installing
placard(s), and revising the Rotorcraft
Flight Manual (RFM) for your
helicopter. This AD was prompted by a
report of wear of the ramps of the RH
free wheel shaft. The actions of this AD
are intended to address an unsafe
condition on these products.
DATES: This AD becomes effective
November 5, 2019. The FAA must
receive comments on this AD by
December 20, 2019.
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:
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Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0738; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this AD, the
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European Aviation Safety Agency
(EASA) AD, the economic evaluation,
any comments received, and other
information. The street address for
Docket Operations is listed above.
Comments will be available in the AD
docket shortly after receipt.
For service information identified in
this final rule, contact Airbus
Helicopters, 2701 N Forum Drive, Grand
Prairie, TX 75052; telephone (972) 641–
0000 or (800) 232–0323; fax (972) 641–
3775; or at http:/
www.helicopters.airbus.com/website/
en/ref/Technical-Support_73.html. You
may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321,
Fort Worth, TX 76177.
FOR FURTHER INFORMATION CONTACT: Rao
Edupuganti, Aviation Safety Engineer,
Regulations and Policy Section,
Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110; email
rao.edupuganti@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
the FAA did not provide you with
notice and an opportunity to provide
your comments prior to it becoming
effective. However, the FAA invites you
to participate in this rulemaking by
submitting written comments, data, or
views. The FAA also invites 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. The FAA will file in the
docket all comments received, as well as
a report summarizing each substantive
public contact with FAA personnel
concerning this rulemaking during the
comment period. The FAA will consider
all the comments received and may
conduct additional rulemaking based on
those comments.
Discussion
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD No. 2019–
0152–E, dated June 28, 2019, to correct
an unsafe condition for Airbus
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56109
Helicopters (AH), formerly Eurocopter,
Eurocopter France, Model EC 225 LP
helicopters with MGB part number (P/
N) 332A325001.XX, P/N
332A325002.XX, or P/N
332A325003.XX equipped with main
reduction gear module P/N
332A325011.XX, P/N 332A325012.XX,
or P/N 332A325013.XX in post-mod 07–
53016 configuration installed, where XX
represents any dash number, and with
RH free wheel shaft P/N 332A322191.20
(16-roller free wheel) installed. EASA
advises of a report of wear of the ramps
and a broken roller cage of the RH free
wheel shaft that were discovered during
overhaul of an MGB. EASA states an
investigation to determine the root
cause of the occurrence is ongoing.
EASA advises that this condition, if not
corrected, could lead to reduced
capacity to transfer one engine
inoperative (OEI) power delivered by
the right side engine following an event
of in-flight shut down of the left side
engine, resulting in reduced control of
the helicopter.
Accordingly, the EASA AD requires
repetitive replacement of the affected
MGBs, installing placards that specify
an operational limitation for OEI
training flights, and introduces
conditions for installing a replacement
MGB. EASA states its AD is considered
an interim action and further AD action
may follow.
FAA’s Determination
These helicopters have been approved
by EASA and are approved for operation
in the United States. Pursuant to the
FAA’s bilateral agreement with the
European Union, EASA has notified the
FAA of the unsafe condition described
in the EASA AD. The FAA is issuing
this AD after evaluating all information
provided by EASA and determining the
unsafe condition exists and is likely to
exist or develop on other helicopters of
the same type design.
Related Service Information
Airbus Helicopters has issued
Emergency Alert Service Bulletin No.
04A016, Revision 1, dated June 28,
2019, which specifies procedures to
determine the total hours TIS of the free
wheel shafts, a life limit schedule and
instructions to replace the MGB or RH
free wheel shaft, and instructions to
install one or two labels (placards) in
view of both pilots about OEI training
procedures.
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56110
Federal Register / Vol. 84, No. 203 / Monday, October 21, 2019 / Rules and Regulations
AD Requirements
This AD requires determining the
total hours TIS of each free wheel shaft.
For the purpose of this AD, if the total
hours TIS of the RH and LH free wheel
shafts are different, the greater number
of total hours TIS will be considered as
the RH free wheel shaft total hours TIS.
If the RH free wheel shaft has
accumulated 1,000 or more total hours
TIS, or before the RH free wheel shaft
exceeds 1,000 total hours TIS, this AD
requires replacing the MGB with an
airworthy MGB or replacing the RH free
wheel shaft. This AD also requires
installing placard(s) in full view of both
pilots and revising the RFM for your
helicopter with OEI training procedures
pertaining to the ‘‘TRAINING IDLE’’
switches. As an option, this AD
specifies installing alternate MGB
configurations that would constitute
terminating action for the requirements
of this AD.
Differences Between This AD and the
EASA AD
The EASA AD requires repetitive
replacement of the MGB, whereas this
AD requires an initial replacement of
the MGB instead. The FAA plans to
publish a notice of proposed rulemaking
to give the public an opportunity to
comment on this longer-term
requirement. This AD requires revising
the RFM for your helicopter, whereas
the EASA AD does not.
Interim Action
The FAA considers this AD to be an
interim action. Repetitively replacing
the MGB at a longer interval is also
necessary. However, the planned
compliance time for the repetitive
replacement would allow enough time
to provide notice and opportunity for
prior public comment on the merits of
the replacement.
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Costs of Compliance
The FAA estimates that this AD
affects 23 helicopters of U.S. Registry.
The FAA estimates that operators may
incur the following costs in order to
comply with this AD. Labor costs are
estimated at $85 per work-hour.
Determining the hours TIS of each
free wheel shaft takes about 0.25 workhour, for an estimated cost of $21 per
helicopter and $483 for the U.S. fleet.
Installing placard(s) and revising the
RFM for your helicopter takes about 0.5
work-hour for an estimated cost of $43
per helicopter and $989 for the U.S.
fleet. Replacing an MGB takes about 40
work-hours and parts cost about
$850,000 (overhauled), for an estimated
cost of $853,400.
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Justification for Immediate Adoption
and Determination of the Effective Date
Section 553(b)(3)(B) of the
Administrative Procedure Act (APA) (5
U.S.C.) authorizes agencies to dispense
with notice and comment procedures
for rules when the agency, for ‘‘good
cause’’ finds that those procedures are
‘‘impracticable, unnecessary, or contrary
to the public interest.’’ Under this
section, an agency, upon finding good
cause, may issue a final rule without
seeking comment prior to the
rulemaking.
An unsafe condition exists that
requires the immediate adoption of this
AD without providing an opportunity
for public comments prior to adoption.
The FAA has found that the risk to the
flying public justifies foregoing notice
and comment prior to adoption of this
rule because the required corrective
actions must be completed within 10
hours TIS. Therefore, notice and
opportunity for prior public comment
are impracticable and contrary to public
interest pursuant to 5 U.S.C.
553(b)(3)(B). In addition, for the
reason(s) stated above, the FAA finds
that good cause exists pursuant to 5
U.S.C. 553(d) 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.
The FAA is 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
The FAA 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.
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For the reasons discussed, I certify
that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
and
(2) Will not affect intrastate aviation
in Alaska.
The FAA 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.
The Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2019–19–13 Airbus Helicopters:
Amendment 39–19749; Docket No.
FAA–2019–0738; Product Identifier
2019–SW–017–AD.
(a) Applicability
This AD applies to Airbus Helicopters
Model EC225LP helicopters, certificated in
any category, with a main rotor gearbox
(MGB) part number (P/N) 332A325001.XX, P/
N 332A325002.XX, or P/N 332A325003.XX,
with a main reduction gear module (main
module), with modification (MOD) 07–53016
(16-roller free wheel of free wheel shaft P/N
332A322191.20) installed, P/N
332A325011.XX, P/N 332A325012.XX, or P/
N 332A325013.XX, with ‘‘XX’’ denoting any
dash number.
(b) Unsafe Condition
This AD defines the unsafe condition as
wear of the ramps of the right-hand side (RH)
free wheel shaft. During an in-flight
shutdown of the left-hand side (LH) engine,
this condition could result in reduced ability
to transfer one engine inoperative (OEI)
power from the RH engine to the main rotor,
and subsequent reduced control of the
helicopter.
(c) Effective Date
This AD becomes effective November 5,
2019.
(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.
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(e) Required Actions
(1) Within 10 hours time-in-service (TIS),
determine the total hours TIS of the RH and
LH free wheel shafts since new or last RH
free wheel shaft replacement during
overhaul. For the purpose of this AD, if the
total hours TIS of the RH and LH free wheel
shafts are different, use the greater number of
total hours TIS as the RH free wheel shaft
total hours TIS.
(i) If the total hours TIS of the RH free
wheel shaft is 1,000 or more hours TIS,
before further flight, replace the MGB or
replace the RH free wheel shaft under the
supervision of an Airbus Helicopter
Specialist that is qualified for this
replacement.
(ii) If the total hours TIS of the RH free
wheel shaft is less than 1,000 hours TIS,
before exceeding 1,000 hours TIS, replace the
MGB or replace the RH free wheel shaft
under the supervision of an Airbus
Helicopter Specialist that is qualified for this
replacement.
(2) Within 10 hours TIS:
(i) Install one or two self-adhesive placards
on the instrument panel in full view of the
pilot and co-pilot with 6-millimeter red
letters on a white background that state the
information contained in Figure 1 to
paragraph (e)(2)(i) of this AD. Refer to Figure
1 of Airbus Helicopters Emergency Alert
Service Bulletin No. 04A016, Revision 1,
dated June 28, 2019, for an example of this
placard.
(ii) After installing the placard(s) required
by paragraph (e)(2)(i) of this AD, before
further flight, revise the limitations section of
the Rotorcraft Flight Manual (RFM) for your
helicopter by adding the information in
Figure 2 to paragraph (e)(2)(ii) of this AD, by
inserting a copy of this AD, or by making
pen-and-ink changes. This action may be
done by the owner/operator (pilot) holding at
least a private pilot certificate and must be
entered into the aircraft records showing
compliance with this AD by following 14
CFR 43.9 (a)(1) through (4) and 14 CFR
91.417(a)(2)(v). The record must be
maintained as required by 14 CFR 91.417,
121.380, or 135.439
(3) After the effective date of this AD, do
not install an MGB P/N 332A325001.XX, P/
N 332A325002.XX, or P/N 332A325003.XX,
with a main reduction gear module (main
module), with modification (MOD) 07–53016
(16-roller free wheel of free wheel shaft P/N
332A322191.20) installed, P/N
332A325011.XX, P/N 332A325012.XX, or P/
N 332A325013.XX, with ‘‘XX’’ denoting any
dash number unless the requirements of
paragraph (e)(2) of this AD have been
accomplished.
(4) As an optional terminating action for
the requirements of this AD, install MGB P/
N 332A325001.XX, P/N 332A325002.XX, or
P/N 332A325003.XX, with a main module
(12-roller free wheel), without MOD 07–
53016 installed, P/N 332A325011.XX, P/N
332A325012.XX, or P/N 332A325013.XX,
with ‘‘XX’’ denoting any dash number.
(f) Credit for Previous Actions
Actions accomplished before the effective
date of this AD by following the procedures
specified in Airbus Helicopters Emergency
Alert Service Bulletin No. 04A016, Revision
1, dated June 28, 2019, are considered
acceptable for compliance with the
corresponding requirements specified in
paragraphs (e)(1) through (e)(2)(i) of this AD.
(g) Special Flight Permits
A one-time special flight permit to a
maintenance facility may be permitted.
Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, the FAA suggests
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) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Section, Rotorcraft Standards Branch, FAA,
may approve AMOCs for this AD. Send your
proposal to Rao Edupuganti, Aviation Safety
Engineer, Regulations and Policy Section,
(i) Additional Information
(1) Airbus Helicopters Emergency Alert
Service Bulletin No. 04A016, Revision 1,
dated June 28, 2019, which is not
incorporated by reference, contains
additional information about the subject of
this AD. For service information identified in
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56111
ER21OC19.006</GPH>
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Federal Register / Vol. 84, No. 203 / Monday, October 21, 2019 / Rules and Regulations
56112
Federal Register / Vol. 84, No. 203 / Monday, October 21, 2019 / Rules and Regulations
this AD, contact Airbus Helicopters, 2701 N
Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–0323;
fax (972) 641–3775; or at https://
www.helicopters.airbus.com/website/en/ref/
Technical-Support_73.html. You may review
a copy of the service information at the FAA,
Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room 6N–
321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA)
No. 2019–0152–E, dated June 28, 2019. You
may view the EASA AD on the internet at
https://www.regulations.gov by searching for
and locating it in Docket No. FAA–2019–
0738.
(j) Subject
Joint Aircraft Service Component (JASC)
Code: 6320, Main Rotor Gearbox.
Issued in Fort Worth, Texas, on September
30, 2019.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2019–22567 Filed 10–18–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 97
[Docket No. 31276; Amdt. No. 3873]
Standard Instrument Approach
Procedures, and Takeoff Minimums
and Obstacle Departure Procedures;
Miscellaneous Amendments
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This rule establishes, amends,
suspends, or removes Standard
Instrument Approach Procedures
(SIAPs) and associated Takeoff
Minimums and Obstacle Departure
Procedures (ODPs) for operations at
certain airports. These regulatory
actions are needed because of the
adoption of new or revised criteria, or
because of changes occurring in the
National Airspace System, such as the
commissioning of new navigational
facilities, adding new obstacles, or
changing air traffic requirements. These
changes are designed to provide safe
and efficient use of the navigable
airspace and to promote safe flight
operations under instrument flight rules
at the affected airports.
DATES: This rule is effective October 21,
2019. The compliance date for each
SIAP, associated Takeoff Minimums,
and ODP is specified in the amendatory
provisions.
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SUMMARY:
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16:21 Oct 18, 2019
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The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of October 21,
2019.
ADDRESSES: Availability of matters
incorporated by reference in the
amendment is as follows:
For Examination
1. U.S. Department of Transportation,
Docket Ops—M30, 1200 New Jersey
Avenue SE, West Bldg., Ground Floor,
Washington, DC 20590–0001.
2. The FAA Air Traffic Organization
Service Area in which the affected
airport is located;
3. The office of Aeronautical
Navigation Products, 6500 South
MacArthur Blvd., Oklahoma City, OK
73169 or,
4. The National Archives and Records
Administration (NARA). For
information on the availability of this
material at NARA, email fedreg.legal@
nara.gov or go to: https://
www.archives.gov/federal-register/cfr/
ibr-locations.html .
Availability
All SIAPs and Takeoff Minimums and
ODPs are available online free of charge.
Visit the National Flight Data Center at
nfdc.faa.gov to register. Additionally,
individual SIAP and Takeoff Minimums
and ODP copies may be obtained from
the FAA Air Traffic Organization
Service Area in which the affected
airport is located.
FOR FURTHER INFORMATION CONTACT:
Thomas J. Nichols, Flight Procedures
and Airspace Group, Flight
Technologies and Procedures Division,
Flight Standards Service, Federal
Aviation Administration. Mailing
Address: FAA Mike Monroney
Aeronautical Center, Flight Procedures
and Airspace Group, 6500 South
MacArthur Blvd., Registry Bldg. 29,
Room 104, Oklahoma City, OK 73169.
Telephone: (405) 954–4164.
SUPPLEMENTARY INFORMATION: This rule
amends Title 14 of the Code of Federal
Regulations, Part 97 (14 CFR part 97), by
establishing, amending, suspending, or
removes SIAPS, Takeoff Minimums
and/or ODPS. The complete regulatory
description of each SIAP and its
associated Takeoff Minimums or ODP
for an identified airport is listed on FAA
form documents which are incorporated
by reference in this amendment under 5
U.S.C. 552(a), 1 CFR part 51, and 14
CFR part 97.20. The applicable FAA
forms are FAA Forms 8260–3, 8260–4,
8260–5, 8260–15A, and 8260–15B when
required by an entry on 8260–15A.
The large number of SIAPs, Takeoff
Minimums and ODPs, their complex
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nature, and the need for a special format
make publication in the Federal
Register expensive and impractical.
Further, airmen do not use the
regulatory text of the SIAPs, Takeoff
Minimums or ODPs, but instead refer to
their graphic depiction on charts
printed by publishers of aeronautical
materials. Thus, the advantages of
incorporation by reference are realized
and publication of the complete
description of each SIAP, Takeoff
Minimums and ODP listed on FAA form
documents is unnecessary. This
amendment provides the affected CFR
sections and specifies the types of
SIAPs, Takeoff Minimums and ODPs
with their applicable effective dates.
This amendment also identifies the
airport and its location, the procedure,
and the amendment number.
Availability and Summary of Material
Incorporated by Reference
The material incorporated by
reference is publicly available as listed
in the ADDRESSES section.
The material incorporated by
reference describes SIAPS, Takeoff
Minimums and/or ODPS as identified in
the amendatory language for part 97 of
this final rule.
The Rule
This amendment to 14 CFR part 97 is
effective upon publication of each
separate SIAP, Takeoff Minimums and
ODP as Amended in the transmittal.
Some SIAP and Takeoff Minimums and
textual ODP amendments may have
been issued previously by the FAA in a
Flight Data Center (FDC) Notice to
Airmen (NOTAM) as an emergency
action of immediate flight safety relating
directly to published aeronautical
charts.
The circumstances that created the
need for some SIAP and Takeoff
Minimums and ODP amendments may
require making them effective in less
than 30 days. For the remaining SIAPs
and Takeoff Minimums and ODPs, an
effective date at least 30 days after
publication is provided.
Further, the SIAPs and Takeoff
Minimums and ODPs contained in this
amendment are based on the criteria
contained in the U.S. Standard for
Terminal Instrument Procedures
(TERPS). In developing these SIAPs and
Takeoff Minimums and ODPs, the
TERPS criteria were applied to the
conditions existing or anticipated at the
affected airports. Because of the close
and immediate relationship between
these SIAPs, Takeoff Minimums and
ODPs, and safety in air commerce, I find
that notice and public procedure under
5 U.S.C. 553(b) are impracticable and
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]]>Agencies
[Federal Register Volume 84, Number 203 (Monday, October 21, 2019)]
[Rules and Regulations]
[Pages 56109-56112]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-22567]
[[Page 56109]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0738; Product Identifier 2019-SW-017-AD; Amendment
39-19749; AD 2019-19-13]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus Helicopters Model EC225LP helicopters. This AD requires
determining the total hours time-in-service (TIS) of the free wheel
shafts of certain main rotor gearboxes (MGBs), replacing the MGB or
right-hand side (RH) free wheel shaft, installing placard(s), and
revising the Rotorcraft Flight Manual (RFM) for your helicopter. This
AD was prompted by a report of wear of the ramps of the RH free wheel
shaft. The actions of this AD are intended to address an unsafe
condition on these products.
DATES: This AD becomes effective November 5, 2019. The FAA must receive
comments on this AD by December 20, 2019.
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 by searching for and locating Docket No. FAA-2019-
0738; or in person at Docket Operations 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 Docket Operations is listed above. Comments will be
available in the AD docket shortly after receipt.
For service information identified in this final rule, contact
Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at
http:/www.helicopters.airbus.com/website/en/ref/Technical-
Support_73.html. You may review the referenced service information at
the FAA, Office of the Regional Counsel, Southwest Region, 10101
Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.
FOR FURTHER INFORMATION CONTACT: Rao Edupuganti, Aviation Safety
Engineer, Regulations and Policy Section, Rotorcraft Standards Branch,
FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-
5110; email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and the FAA did not provide you with notice and an opportunity
to provide your comments prior to it becoming effective. However, the
FAA invites you to participate in this rulemaking by submitting written
comments, data, or views. The FAA also invites 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. The FAA will file in the docket all comments
received, as well as a report summarizing each substantive public
contact with FAA personnel concerning this rulemaking during the
comment period. The FAA will consider all the comments received and may
conduct additional rulemaking based on those comments.
Discussion
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD No. 2019-0152-E, dated June 28,
2019, to correct an unsafe condition for Airbus Helicopters (AH),
formerly Eurocopter, Eurocopter France, Model EC 225 LP helicopters
with MGB part number (P/N) 332A325001.XX, P/N 332A325002.XX, or P/N
332A325003.XX equipped with main reduction gear module P/N
332A325011.XX, P/N 332A325012.XX, or P/N 332A325013.XX in post-mod 07-
53016 configuration installed, where XX represents any dash number, and
with RH free wheel shaft P/N 332A322191.20 (16-roller free wheel)
installed. EASA advises of a report of wear of the ramps and a broken
roller cage of the RH free wheel shaft that were discovered during
overhaul of an MGB. EASA states an investigation to determine the root
cause of the occurrence is ongoing. EASA advises that this condition,
if not corrected, could lead to reduced capacity to transfer one engine
inoperative (OEI) power delivered by the right side engine following an
event of in-flight shut down of the left side engine, resulting in
reduced control of the helicopter.
Accordingly, the EASA AD requires repetitive replacement of the
affected MGBs, installing placards that specify an operational
limitation for OEI training flights, and introduces conditions for
installing a replacement MGB. EASA states its AD is considered an
interim action and further AD action may follow.
FAA's Determination
These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Union, EASA has notified the FAA of the
unsafe condition described in the EASA AD. The FAA is issuing this AD
after evaluating all information provided by EASA and determining the
unsafe condition exists and is likely to exist or develop on other
helicopters of the same type design.
Related Service Information
Airbus Helicopters has issued Emergency Alert Service Bulletin No.
04A016, Revision 1, dated June 28, 2019, which specifies procedures to
determine the total hours TIS of the free wheel shafts, a life limit
schedule and instructions to replace the MGB or RH free wheel shaft,
and instructions to install one or two labels (placards) in view of
both pilots about OEI training procedures.
[[Page 56110]]
AD Requirements
This AD requires determining the total hours TIS of each free wheel
shaft. For the purpose of this AD, if the total hours TIS of the RH and
LH free wheel shafts are different, the greater number of total hours
TIS will be considered as the RH free wheel shaft total hours TIS. If
the RH free wheel shaft has accumulated 1,000 or more total hours TIS,
or before the RH free wheel shaft exceeds 1,000 total hours TIS, this
AD requires replacing the MGB with an airworthy MGB or replacing the RH
free wheel shaft. This AD also requires installing placard(s) in full
view of both pilots and revising the RFM for your helicopter with OEI
training procedures pertaining to the ``TRAINING IDLE'' switches. As an
option, this AD specifies installing alternate MGB configurations that
would constitute terminating action for the requirements of this AD.
Differences Between This AD and the EASA AD
The EASA AD requires repetitive replacement of the MGB, whereas
this AD requires an initial replacement of the MGB instead. The FAA
plans to publish a notice of proposed rulemaking to give the public an
opportunity to comment on this longer-term requirement. This AD
requires revising the RFM for your helicopter, whereas the EASA AD does
not.
Interim Action
The FAA considers this AD to be an interim action. Repetitively
replacing the MGB at a longer interval is also necessary. However, the
planned compliance time for the repetitive replacement would allow
enough time to provide notice and opportunity for prior public comment
on the merits of the replacement.
Costs of Compliance
The FAA estimates that this AD affects 23 helicopters of U.S.
Registry. The FAA estimates that operators may incur the following
costs in order to comply with this AD. Labor costs are estimated at $85
per work-hour.
Determining the hours TIS of each free wheel shaft takes about 0.25
work-hour, for an estimated cost of $21 per helicopter and $483 for the
U.S. fleet. Installing placard(s) and revising the RFM for your
helicopter takes about 0.5 work-hour for an estimated cost of $43 per
helicopter and $989 for the U.S. fleet. Replacing an MGB takes about 40
work-hours and parts cost about $850,000 (overhauled), for an estimated
cost of $853,400.
Justification for Immediate Adoption and Determination of the Effective
Date
Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5
U.S.C.) authorizes agencies to dispense with notice and comment
procedures for rules when the agency, for ``good cause'' finds that
those procedures are ``impracticable, unnecessary, or contrary to the
public interest.'' Under this section, an agency, upon finding good
cause, may issue a final rule without seeking comment prior to the
rulemaking.
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies foregoing notice and comment prior to adoption of this rule
because the required corrective actions must be completed within 10
hours TIS. Therefore, notice and opportunity for prior public comment
are impracticable and contrary to public interest pursuant to 5 U.S.C.
553(b)(3)(B). In addition, for the reason(s) stated above, the FAA
finds that good cause exists pursuant to 5 U.S.C. 553(d) 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.
The FAA is 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
The FAA 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, and
(2) Will not affect intrastate aviation in Alaska.
The FAA 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.
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):
2019-19-13 Airbus Helicopters: Amendment 39-19749; Docket No. FAA-
2019-0738; Product Identifier 2019-SW-017-AD.
(a) Applicability
This AD applies to Airbus Helicopters Model EC225LP helicopters,
certificated in any category, with a main rotor gearbox (MGB) part
number (P/N) 332A325001.XX, P/N 332A325002.XX, or P/N 332A325003.XX,
with a main reduction gear module (main module), with modification
(MOD) 07-53016 (16-roller free wheel of free wheel shaft P/N
332A322191.20) installed, P/N 332A325011.XX, P/N 332A325012.XX, or
P/N 332A325013.XX, with ``XX'' denoting any dash number.
(b) Unsafe Condition
This AD defines the unsafe condition as wear of the ramps of the
right-hand side (RH) free wheel shaft. During an in-flight shutdown
of the left-hand side (LH) engine, this condition could result in
reduced ability to transfer one engine inoperative (OEI) power from
the RH engine to the main rotor, and subsequent reduced control of
the helicopter.
(c) Effective Date
This AD becomes effective November 5, 2019.
(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.
[[Page 56111]]
(e) Required Actions
(1) Within 10 hours time-in-service (TIS), determine the total
hours TIS of the RH and LH free wheel shafts since new or last RH
free wheel shaft replacement during overhaul. For the purpose of
this AD, if the total hours TIS of the RH and LH free wheel shafts
are different, use the greater number of total hours TIS as the RH
free wheel shaft total hours TIS.
(i) If the total hours TIS of the RH free wheel shaft is 1,000
or more hours TIS, before further flight, replace the MGB or replace
the RH free wheel shaft under the supervision of an Airbus
Helicopter Specialist that is qualified for this replacement.
(ii) If the total hours TIS of the RH free wheel shaft is less
than 1,000 hours TIS, before exceeding 1,000 hours TIS, replace the
MGB or replace the RH free wheel shaft under the supervision of an
Airbus Helicopter Specialist that is qualified for this replacement.
(2) Within 10 hours TIS:
(i) Install one or two self-adhesive placards on the instrument
panel in full view of the pilot and co-pilot with 6-millimeter red
letters on a white background that state the information contained
in Figure 1 to paragraph (e)(2)(i) of this AD. Refer to Figure 1 of
Airbus Helicopters Emergency Alert Service Bulletin No. 04A016,
Revision 1, dated June 28, 2019, for an example of this placard.
[GRAPHIC] [TIFF OMITTED] TR21OC19.006
(ii) After installing the placard(s) required by paragraph
(e)(2)(i) of this AD, before further flight, revise the limitations
section of the Rotorcraft Flight Manual (RFM) for your helicopter by
adding the information in Figure 2 to paragraph (e)(2)(ii) of this
AD, by inserting a copy of this AD, or by making pen-and-ink
changes. This action may be done by the owner/operator (pilot)
holding at least a private pilot certificate and must be entered
into the aircraft records showing compliance with this AD by
following 14 CFR 43.9 (a)(1) through (4) and 14 CFR 91.417(a)(2)(v).
The record must be maintained as required by 14 CFR 91.417, 121.380,
or 135.439
[GRAPHIC] [TIFF OMITTED] TR21OC19.007
(3) After the effective date of this AD, do not install an MGB
P/N 332A325001.XX, P/N 332A325002.XX, or P/N 332A325003.XX, with a
main reduction gear module (main module), with modification (MOD)
07-53016 (16-roller free wheel of free wheel shaft P/N
332A322191.20) installed, P/N 332A325011.XX, P/N 332A325012.XX, or
P/N 332A325013.XX, with ``XX'' denoting any dash number unless the
requirements of paragraph (e)(2) of this AD have been accomplished.
(4) As an optional terminating action for the requirements of
this AD, install MGB P/N 332A325001.XX, P/N 332A325002.XX, or P/N
332A325003.XX, with a main module (12-roller free wheel), without
MOD 07-53016 installed, P/N 332A325011.XX, P/N 332A325012.XX, or P/N
332A325013.XX, with ``XX'' denoting any dash number.
(f) Credit for Previous Actions
Actions accomplished before the effective date of this AD by
following the procedures specified in Airbus Helicopters Emergency
Alert Service Bulletin No. 04A016, Revision 1, dated June 28, 2019,
are considered acceptable for compliance with the corresponding
requirements specified in paragraphs (e)(1) through (e)(2)(i) of
this AD.
(g) Special Flight Permits
A one-time special flight permit to a maintenance facility may
be permitted.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Section, Rotorcraft Standards
Branch, FAA, may approve AMOCs for this AD. Send your proposal to
Rao Edupuganti, Aviation Safety Engineer, Regulations and Policy
Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; 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, the FAA suggests
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.
(i) Additional Information
(1) Airbus Helicopters Emergency Alert Service Bulletin No.
04A016, Revision 1, dated June 28, 2019, which is not incorporated
by reference, contains additional information about the subject of
this AD. For service information identified in
[[Page 56112]]
this AD, contact Airbus Helicopters, 2701 N Forum Drive, Grand
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax
(972) 641-3775; or at https://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You may review a copy of the service
information at the FAA, Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in European Aviation
Safety Agency (EASA) No. 2019-0152-E, dated June 28, 2019. You may
view the EASA AD on the internet at https://www.regulations.gov by
searching for and locating it in Docket No. FAA-2019-0738.
(j) Subject
Joint Aircraft Service Component (JASC) Code: 6320, Main Rotor
Gearbox.
Issued in Fort Worth, Texas, on September 30, 2019.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2019-22567 Filed 10-18-19; 8:45 am]
BILLING CODE 4910-13-P
