Airworthiness Directives; Airbus Helicopters, 50226-50230 [2021-19247]
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§ 39.13
Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2021–16–16 Airbus Helicopters:
Amendment 39–21679; Docket No.
FAA–2021–0449; Project Identifier
2018–SW–001–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective October 13, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Helicopters
Model AS350B, AS350BA, AS350B1,
AS350B2, AS350B3, and AS350D
helicopters; and Model AS355E, AS355F,
AS355F1, AS355F2, AS355N, and AS355NP
helicopters, certificated in any category, with
litter kits installed having any part number
specified in paragraphs (c)(1) through (3) of
this AD:
(1) Part number (P/N) 350–200034 (lefthand litter kit).
(2) P/N 350–200194 (left-hand litter kit).
(3) P/N 350–200144 (right-hand litter kit).
(d) Subject
Joint Aircraft Service Component (JASC)
Code: 6700, Rotorcraft Flight Control.
(e) Unsafe Condition
This AD was prompted by reports that the
lanyards (bead chain tethers), which hold the
quick release pins to the forward bracket
assembly of certain litter kits, can loop
around the directional control pedal stubs,
limiting the movement of the pedals, which
affect the control of the flight. The FAA is
issuing this AD to address interference
between the litter kit lanyards and the flight
controls. The unsafe condition, if not
addressed, could result in limited flight
control movement and difficulty controlling
the helicopter.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) For litter kits having any part specified
in paragraphs (c)(1) through (3) of this AD:
Prior to each flight until the modification
required by paragraph (g)(2) of this AD is
accomplished, do a pre-flight check to
determine if there is interference (e.g. limited
movement of the pedals due to the lanyards
that hold the quick release pins to the
forward bracket assembly being looped
around the directional control pedal stubs)
between the lanyards that hold the quick
release pins to the forward bracket assembly
and the pedals. If interference is found,
before further flight, do the modification
required by paragraph (g)(2) of this AD for
the affected litter kit. The pre-flight check
may be performed by the owner/operator
(pilot) holding at least a private pilot
certificate and must be entered into the
aircraft records showing compliance with
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this AD in accordance with § 43.9(a)(1)
through (4) and § 91.417(a)(2)(v). The record
must be maintained as required by § 91.417,
§ 121.380, or § 135.439.
(2) Within 25 hours time-in-service (TIS)
after the effective date of this AD, modify the
attachment location of the lanyard for litter
kits having any part specified in paragraphs
(c)(1) through (3) of this AD. Do the
modification in accordance with paragraph
3.B.2., ‘‘Procedure,’’ of the Accomplishment
Instructions of Airbus Helicopters Service
Bulletin SB–AHCA–128, Revision 0, dated
March 24, 2017.
Note 1 to paragraph (g): Litter kits, P/N
350–200034 and P/N 350–200194, may have
been installed under supplemental type
certificate (STC) SR00406NY (for Model
AS355E, AS355F, AS355F1, AS355F2,
AS355N, and AS355NP helicopters) or STC
SR00407NY (for Model AS350B, AS350BA,
AS350B1, AS350B2, AS350B3, and AS350D
helicopters). Litter kit P/N 350–200144 may
have been installed under STC SR00458NY
(for Model AS350BA, AS350B2, and
AS350B3 helicopters).
(h) Parts Installation Limitation
As of the effective date of this AD, no
person may install a litter kit having a part
number identified in paragraphs (c)(1)
through (3) of this AD, on any helicopter,
unless the installation is modified as
required by paragraph (g)(2) of this AD.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Airbus Helicopters Service Bulletin SB–
AHCA–128, Revision 0, dated March 24,
2017.
(ii) [Reserved]
(3) For service information identified in
this AD, contact Airbus Helicopters, 2701
North Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–0323;
fax (972) 641–3775; or at https://
www.airbus.com/helicopters/services/
technical-support.html.
(4) You may view this service information
at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email: fr.inspection@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, International Validation
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the International Validation
Branch, send it to the attention of the person
identified in paragraph (j)(1) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
Issued on July 30, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
(j) Related Information
(1) For more information about this AD,
contact Andrea Jimenez, Aerospace Engineer,
COS Program Management Section,
Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 1600 Stewart
Ave., Mail Stop: Room 410, Westbury, NY
11590; telephone (516) 228–7330; email
andrea.jimenez@faa.gov.
(2) For information about AMOCs, contact
the Manager, International Validation
Branch, FAA, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; telephone (817) 222–5110;
email 9-AVS-AIR-730-AMOC@faa.gov.
(3) The subject of this AD is addressed in
Transport Canada AD CF–2017–37 dated
December 19, 2017. You may view the
Transport Canada AD at https://
www.regulations.gov in Docket No. FAA–
2021–0449.
Airworthiness Directives; Airbus
Helicopters
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[FR Doc. 2021–19252 Filed 9–7–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0379; Project
Identifier MCAI–2021–00068–R; Amendment
39–21667; AD 2021–16–05]
RIN 2120–AA64
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2016–12–
51, which applied to all Airbus
Helicopters Model AS332L2 and Model
EC225LP helicopters. AD 2016–12–51
prohibited all further flight of Model
AS332L2 and Model EC225LP
helicopters. This AD requires replacing
certain second stage planet gear
assemblies, removing certain epicyclic
modules, installing a full flow magnetic
plug (FFMP), revising the existing
SUMMARY:
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rotorcraft flight manual (RFM) for your
helicopter, repetitively inspecting the
main gearbox (MGB) particle detectors,
repetitively inspecting the MGB oil filter
and oil cooler, and corrective action if
necessary, as specified in a European
Union Aviation Safety Agency (EASA)
AD, which is incorporated by reference.
The actions specified in this AD
terminate the flight prohibition. The
FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective October 13,
2021.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 13, 2021.
ADDRESSES: For EASA material
incorporated by reference (IBR) in this
AD, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne,
Germany; telephone +49 221 8999 000;
email ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find this
material on the EASA website at https://
ad.easa.europa.eu. For Airbus
Helicopters service information, contact
Airbus Helicopters, 2701 North Forum
Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–
0323; fax (972) 641–3775; or at https://
www.airbus.com/helicopters/services/
technical-support.html. You may view
this material at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321,
Fort Worth, TX 76177. For information
on the availability of this material at the
FAA, call 817–222–5110. It is also
available in the AD docket on the
internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0379.
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–2021–
0379; 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 final rule,
any comments received, and other
information. The address for Docket
Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Mahmood Shah, Aviation Safety
Engineer, Fort Worth ACO Branch,
FAA, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; telephone 817–222–
5538; email mahmood.g.shah@faa.gov.
SUPPLEMENTARY INFORMATION:
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Background
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–
0134R2, dated April 16, 2020 (EASA AD
2017–0134R2) (also referred to as the
Mandatory Continuing Airworthiness
Information, or the MCAI), to correct an
unsafe condition for all Airbus
Helicopters Model AS332L2 and
EC225LP helicopters.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2016–12–51,
Amendment 39–18578 (81 FR 43479,
July 5, 2016) (AD 2016–12–51). AD
2016–12–51 applied to all Airbus
Helicopters Model AS332L2 and
EC225LP helicopters. The NPRM
published in the Federal Register on
June 1, 2021 (86 FR 29212). The NPRM
was prompted by an accident involving
an Airbus Helicopters Model EC225LP
helicopter in which the main rotor hub
detached from the MGB. The Airbus
Helicopters Model AS332L2 helicopter
has a similar design to the affected
Model EC225LP helicopter, therefore,
this model may be subject to the unsafe
condition revealed on the Model
EC225LP helicopter. The NPRM
proposed to require replacing certain
second stage planet gear assemblies,
removing certain epicyclic modules,
installing an FFMP, revising the existing
RFM for your helicopter, repetitively
inspecting the MGB particle detectors,
repetitively inspecting the MGB oil filter
and oil cooler, and corrective action if
necessary, as specified in EASA AD
2017–0134R2. The NPRM also proposed
to provide terminating action for certain
repetitive inspections.
The FAA is issuing this AD to address
failure of the main rotor system, which
would result in loss of control of the
helicopter. See the MCAI for additional
background information.
Discussion of Final Airworthiness
Directive
Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The FAA received no
comments on the NPRM or on the
determination of the cost to the public.
Conclusion
The FAA reviewed the relevant data
and determined that air safety and the
public interest require adopting this
final rule as proposed, except for minor
editorial changes. The FAA has
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
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50227
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
EASA AD 2017–0134R2 references
procedures for replacing certain second
stage planet gear assemblies with
serviceable parts; removing certain
epicyclic modules from service;
modifying the helicopter by installing
an FFMP; revising the RFM to prohibit
MGB particle burning in-flight;
repetitively inspecting the FFMP and
MGB particle detectors for metal
particles, analyzing any metal particles
that are found, and corrective action;
and repetitively inspecting the MGB oil
filter and oil cooler for particles and
corrective action. The corrective actions
include replacing an affected MGB with
a serviceable MGB. EASA AD 2017–
0134R2 also provides terminating action
for certain repetitive inspections.
Airbus Helicopters has issued
Emergency Alert Service Bulletin
05A049, Revision 6, dated July 25, 2017,
for Model EC225 helicopters; and
Emergency Alert Service Bulletin
05.01.07, Revision 6, dated July 27,
2017, for Model AS332 helicopters. The
service information specifies procedures
for, among other things, replacing the
MGB.
This material is reasonably available
because the interested parties have
access to it through their normal course
of business or by the means identified
in the ADDRESSES section.
Differences Between This AD and the
MCAI
Although the service information
referenced in EASA AD 2017–0134R2
specifies to return affected planetary
gear assemblies to the manufacturer for
module overhaul, this AD does not
include that requirement.
Although the service information
referenced in EASA AD 2017–0134R2
specifies that retrofit of the planet gear
of the MGB can only be done by Airbus
Helicopters or Airbus Helicopters
approved repair centers, this AD does
not include that requirement.
EASA AD 2017–0134R2 requires
operators to ‘‘inform all flight crews’’ of
revisions to the RFM, and thereafter to
‘‘operate the helicopter accordingly.’’
However, this AD does not specifically
require those actions. FAA regulations
mandate compliance with only the
operating limitations section of the
flight manual. The flight manual
changes required by this AD apply to
the emergency procedures section of the
existing RFM for your helicopter.
Furthermore, compliance with such
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Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations
requirements in an AD is impracticable
to demonstrate or track on an ongoing
basis; therefore, a requirement to
operate the aircraft in such a manner is
unenforceable. Nonetheless, the FAA
recommends that flight crews of the
helicopters listed in the applicability
operate in accordance with the revised
emergency procedures mandated by this
AD.
Interim Action
The FAA considers this AD interim
action. If final action is later identified,
the FAA might consider further
rulemaking then.
Costs of Compliance
The FAA estimates that this AD
affects 28 helicopters of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS *
Parts
cost
Action
Labor cost
New actions ............................................
Up to 6 work-hours × $85 per hour =
$510.
Cost per
product
$0
Up to $510 .............
Cost on U.S.
operators
Up to $14,280.
* Table does not include estimated costs for reporting.
The FAA estimates that it will take
about 1 work-hour per product to
comply with the reporting requirement
in this AD. The average labor rate is $85
per hour. Based on these figures, the
FAA estimates the cost of reporting the
inspection results on U.S. operators to
be $2,380, or $85 per product.
The FAA estimates the following
costs to do any necessary on-condition
actions that will be required based on
the results of any required actions. The
FAA has no way of determining the
number of helicopters that might need
these on-condition actions:
ESTIMATED COSTS OF ON-CONDITION ACTIONS
Labor cost
Parts cost
Cost per
product
40 work-hours × $85 per hour = $3,400 .................................................................................................................
$295,000
$298,400
According to the manufacturer, some
or all of the costs of this AD may be
covered under warranty, thereby
reducing the cost impact on affected
operators. The FAA does not control
warranty coverage for affected operators.
As a result, the FAA has included all
known costs in the cost estimate.
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Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is mandatory. Comments
concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to Information
Collection Clearance Officer, Federal
Aviation Administration, 10101
Hillwood Pkwy., Fort Worth, TX 76177–
1524.
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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.
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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:
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.
Frm 00016
List of Subjects in 14 CFR Part 39
■
Regulatory Findings
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For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) 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.
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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
2016–12–51, Amendment 39–18578 (81
FR 43479, July 5, 2016); and
■ b. Adding the following new
airworthiness directive:
■
■
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Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations
2021–16–05 Airbus Helicopters:
Amendment 39–21667; Docket No.
FAA–2021–0379; Project Identifier
MCAI–2021–00068–R.
(a) Effective Date
This airworthiness directive (AD) is
effective October 13, 2021.
(b) Affected ADs
This AD replaces AD 2016–12–51,
Amendment 39–18578 (81 FR 43479, July 5,
2016) (AD 2016–12–51).
(c) Applicability
This AD applies to all Airbus Helicopters
Model AS332L2 and EC225LP helicopters,
certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)
Code 6320, Main Rotor Gearbox.
(e) Reason
This AD was prompted by an accident
involving a Model EC225LP helicopter in
which the main rotor hub detached from the
main gearbox. The FAA is issuing this AD to
address failure of the main rotor system,
which would result in loss of control of the
helicopter.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, European Union Aviation
Safety Agency (EASA) AD 2017–0134R2,
dated April 16, 2020 (EASA AD 2017–
0134R2).
(h) Exceptions to EASA AD 2017–0134R2
(1) Where EASA AD 2017–0134R2 refers to
the effective dates specified in paragraphs
(h)(1)(i) through (v) of this AD, this AD
requires using the effective date of this AD.
(i) The effective date of EASA AD 2017–
0134R2.
(ii) October 13, 2016 (the effective date of
EASA AD 2016–0199, dated October 7,
2016).
(iii) March 20, 2017 (the effective date of
EASA AD 2017–0050–E, dated March 17,
2017).
(iv) June 30, 2017 (the effective date of
EASA AD 2017–0111, dated June 23, 2017).
(v) August 1, 2017 (the effective date of
EASA AD 2017–0134, dated July 27, 2017).
(2) The ‘‘Remarks’’ section of EASA AD
2017–0134R2 does not apply to this AD.
(3) Where any service information referred
to in EASA AD 2017–0134R2 specifies to
discard certain parts after they have been
removed from the helicopter, this AD
requires removing those parts from service.
(4) Where paragraph (2) of EASA AD 2017–
0134R2 specifies to replace a part before
exceeding the applicable ‘‘new service life
limit,’’ this AD requires removing that part
from service.
(5) Where any service information referred
to in EASA AD 2017–0134R2 specifies to
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return certain parts to the manufacturer,
including for overhaul, after they have been
removed from the helicopter, this AD does
not include that requirement.
(6) Where EASA AD 2017–0134R2 refers to
flight hours (FH), this AD requires using
hours time-in-service.
(7) Where any service information referred
to in EASA AD 2017–0134R2 specifies to
perform a metallurgical analysis and contact
the manufacturer if unsure about the
characterization of the particles collected,
this AD does require characterization of the
particles collected, however this AD does not
require contacting the manufacturer to
determine the characterization of the
particles collected.
(8) Where EASA AD 2017–0134R2 requires
actions during each ‘‘after last flight’’ of the
day (ALF) inspection, this AD requires those
actions before the first flight of each day.
(9) Where any service information referred
to in EASA AD 2017–0134R2 specifies to do
the actions identified in paragraphs (h)(9)(i)
through (iv) of this AD, this AD does not
include those requirements.
(i) Watch a video for removing the grease
from the full flow magnetic plug (FFMP),
using a cleaning agent, and collecting
particles.
(ii) Return affected planetary gear assembly
to the manufacturer for module overhaul.
(iii) Contact the approved repair station/
Airbus Helicopters if the reason for a repair
to an epicyclic module is unknown and
inform/contact Airbus Helicopters.
(iv) Contact the approved repair station/
Airbus Helicopters depending on who
performed the last overhaul (RG) to
determine if a repair has been done on the
second stage planet gears since new.
(10) Where any service information
referred to in EASA AD 2017–0134R2
specifies that retrofit of the planet gear of the
main gearbox (MGB) can only be done by
Airbus Helicopters or Airbus Helicopters
approved repair centers, this AD does not
require that the retrofit of the planet gear be
done only by Airbus Helicopters or Airbus
Helicopters approved repair centers. For this
AD the retrofit can also be done by an FAAapproved repair station.
(11) Where paragraph (5) of EASA AD
2017–0134R2 specifies accomplishing the
FFMP additional work within 3 months after
August 1, 2017, this AD requires
accomplishing the FFMP additional work
within 4 months after the effective date of
this AD.
(12) Where paragraph (6) of EASA AD
2017–0134R2 specifies to ‘‘inform all flight
crews and, thereafter, operate the helicopter
accordingly,’’ this AD does not require those
actions.
(13) Where any service information
referred to in EASA AD 2017–0134R2
specifies that if any 16NCD13 particles are
found you are to take a 1-liter sample of oil
and send it to the manufacturer, this AD does
not require those actions.
(14) Where any service information
referred to in EASA AD 2017–0134R2
specifies ‘‘Do not resume flights until
corrective action(s) are agreed by Airbus
Helicopters,’’ or to contact Airbus
Helicopters before resuming flights ‘‘if
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further particles are collected during the
close monitoring period’’ for this AD, you
must repair before further flight using a
method specified in paragraph (h)(14)(i) or
(ii) of this AD.
(i) In accordance with FAA approved
procedures.
(ii) The procedures specified in Appendix
4.A., Particle Analysis, of Airbus Helicopters
Emergency Alert Service Bulletin 05A049,
Revision 6, dated July 25, 2017; or
Emergency Alert Service Bulletin 05.01.07,
Revision 6, dated July 27, 2017, as
applicable, except as required by paragraphs
(h)(5), (7), and (13) of this AD.
(15) Where the service information
identified in EASA AD 2017–0134R2
specifies to report inspection results to
Airbus Helicopters, for this AD, report the
inspection results at the applicable time
specified in paragraph (h)(15)(i) or (ii) of this
AD.
(i) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the date of the
inspection.
(ii) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
(i) Credit for Previous Actions
(1) This paragraph provides credit for the
actions specified in paragraph (4) of EASA
AD 2017–0134R2, if those actions were
performed before the effective date of this AD
using Airbus Helicopters Emergency Alert
Service Bulletin 63.00.83 or 63A030, both
Revision 1, both dated October 7, 2016.
(2) Corrective action(s) for the inspections
required by paragraphs (8) and (10) of EASA
AD 2017–0134R2 accomplished on a
helicopter before the effective date of this
AD, in accordance with Paragraph 3.B. and
Appendix 4.A. of the Accomplishment
Instructions of the applicable Airbus
Helicopters service information specified in
paragraphs (i)(2)(i) through (viii) of this AD,
as applicable, are acceptable to comply with
the requirements of paragraph (11) of EASA
AD 2017–0134R2 for that helicopter, but only
for the corrective actions for the inspections
required by paragraphs (8) and (10) of EASA
AD 2017–0134R2.
(i) Emergency Alert Service Bulletin
05.01.07, Revision 2, dated October 7, 2016.
(ii) Emergency Alert Service Bulletin
05.01.07, Revision 3, dated February 25,
2017.
(iii) Emergency Alert Service Bulletin
05.01.07, Revision 4, dated March 17, 2017.
(iv) Emergency Alert Service Bulletin
05.01.07, Revision 5, dated June 23, 2017.
(v) Emergency Alert Service Bulletin
05A049, Revision 2, dated October 7, 2016.
(vi) Emergency Alert Service Bulletin
05A049, Revision 3, dated February 25, 2017.
(vii) Emergency Alert Service Bulletin
05A049, Revision 4, dated March 17, 2017.
(viii) Emergency Alert Service Bulletin
05A049, Revision 5, dated June 23, 2017.
(j) Special Flight Permit
Special flight permits, as described in 14
CFR 21.197 and 21.199, are prohibited.
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(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, International Validation
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the International Validation
Branch, send it to the attention of the person
identified in paragraph (l)(1) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, email
fr.inspection@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
(l) Related Information
(1) For more information about this AD,
contact Mahmood Shah, Aviation Safety
Engineer, Fort Worth ACO Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone 817–222–5538; email
mahmood.g.shah@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (m)(4) and (5) of this AD.
14 CFR Part 39
16:25 Sep 07, 2021
Jkt 253001
[FR Doc. 2021–19247 Filed 9–7–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. FAA–2021–0198; Project
Identifier MCAI–2020–00950–E; Amendment
39–21695; AD 2021–17–12]
RIN 2120–AA64
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency
(EASA) AD 2017–0134R2, dated April 16,
2020.
(ii) Airbus Helicopters Emergency Alert
Service Bulletin 05A049, Revision 6, dated
July 25, 2017.
(iii) Airbus Helicopters Emergency Alert
Service Bulletin 05.01.07, Revision 6, dated
July 27, 2017.
(3) For EASA AD 2017–0134R2, contact the
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; Internet
www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://
ad.easa.europa.eu.
(4) For Airbus Helicopters service
information, contact Airbus Helicopters,
2701 North Forum Drive, Grand Prairie, TX
75052; telephone (972) 641–0000 or (800)
232–0323; fax (972) 641–3775; or at https://
www.airbus.com/helicopters/services/
technical-support.html.
(5) You may view this service information
at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call 817–222–5110. This
material may be found in the AD docket on
the internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0379.
(6) You may view this material that is
incorporated by reference at the National
VerDate Sep<11>2014
Issued on July 22, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
Airworthiness Directives; Rolls-Royce
Deutschland Ltd & Co KG (Type
Certificate Previously Held by RollsRoyce plc) Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2020–13–
07 for all Rolls-Royce Deutschland Ltd
& Co KG (RRD) Trent 1000–D2, Trent
1000–J2, and Trent 1000–K2 model
turbofan engines with a certain partnumbered fuel pump installed. AD
2020–13–07 required removal and
replacement of the fuel pump with a
part eligible for installation. This AD
was prompted by the manufacturer’s
investigation into an unexpected
reduction in fuel pump performance in
certain high life fuel pumps and
subsequent determination that an
additional part-numbered fuel pump is
subject to the same unsafe condition.
This AD requires new and reduced life
limits for certain part-numbered fuel
pumps, depending on the engine model
the fuel pump is installed on. The FAA
is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective October 13,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of October 13, 2021.
ADDRESSES: For service information
identified in this final rule, contact
Rolls-Royce plc, P.O. Box 31, Derby,
DE24 8BJ, United Kingdom; phone: +44
(0)1332 242424; website: https://
SUMMARY:
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
www.rolls-royce.com/contact-us.aspx.
You may view this service information
at the FAA, Airworthiness Products
Section, Operational Safety Branch,
1200 District Avenue, Burlington, MA
01803. For information on the
availability of this material at the FAA,
call (781) 238–7759. It is also available
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0198.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0198; 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 mandatory continuing
airworthiness information (MCAI), any
comments received, and other
information. The address for Docket
Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Kevin M. Clark, Aviation Safety
Engineer, ECO Branch, FAA, 1200
District Avenue, Burlington, MA 01803;
phone: (781) 238–7088; fax: (781) 238–
7199; email: kevin.m.clark@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2020–13–07,
Amendment 39–21152 (85 FR 38312,
June 26, 2020), (AD 2020–13–07). AD
2020–13–07 applied to all RRD Trent
1000–D2, Trent 1000–J2, and Trent
1000–K2 model turbofan engines with
fuel pump, part number G5030FPU01,
installed. The NPRM published in the
Federal Register on March 30, 2021 (86
FR 16548). The NPRM was prompted by
the manufacturer’s investigation into an
unexpected reduction in fuel pump
performance in certain high life fuel
pumps and life-related wear-out of the
internal components and subsequent
determination that an additional partnumbered fuel pump is subject to this
same unsafe condition. In the NPRM,
the FAA proposed to retain all the
requirements of AD 2020–13–07. In the
NPRM, the FAA also proposed to add an
additional part-numbered fuel pump
and additional Trent 1000 model
turbofan engines on which this fuel
pump is installed to the applicability. In
the NPRM, the FAA also proposed to
require new and reduced life limits for
certain part-numbered fuel pumps,
E:\FR\FM\08SER1.SGM
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]]>Agencies
[Federal Register Volume 86, Number 171 (Wednesday, September 8, 2021)]
[Rules and Regulations]
[Pages 50226-50230]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-19247]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0379; Project Identifier MCAI-2021-00068-R;
Amendment 39-21667; AD 2021-16-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2016-12-
51, which applied to all Airbus Helicopters Model AS332L2 and Model
EC225LP helicopters. AD 2016-12-51 prohibited all further flight of
Model AS332L2 and Model EC225LP helicopters. This AD requires replacing
certain second stage planet gear assemblies, removing certain epicyclic
modules, installing a full flow magnetic plug (FFMP), revising the
existing
[[Page 50227]]
rotorcraft flight manual (RFM) for your helicopter, repetitively
inspecting the main gearbox (MGB) particle detectors, repetitively
inspecting the MGB oil filter and oil cooler, and corrective action if
necessary, as specified in a European Union Aviation Safety Agency
(EASA) AD, which is incorporated by reference. The actions specified in
this AD terminate the flight prohibition. The FAA is issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective October 13, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 13,
2021.
ADDRESSES: For EASA material incorporated by reference (IBR) in this
AD, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany;
telephone +49 221 8999 000; email [email protected]; internet
www.easa.europa.eu. You may find this material on the EASA website at
https://ad.easa.europa.eu. For Airbus Helicopters service information,
contact Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775;
or at https://www.airbus.com/helicopters/services/technical-support.html. You may view this material at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321,
Fort Worth, TX 76177. For information on the availability of this
material at the FAA, call 817-222-5110. It is also available in the AD
docket on the internet at https://www.regulations.gov by searching for
and locating Docket No. FAA-2021-0379.
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-2021-
0379; 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 final rule, any comments received, and other information. The
address for Docket Operations is U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Mahmood Shah, Aviation Safety
Engineer, Fort Worth ACO Branch, FAA, 10101 Hillwood Pkwy., Fort Worth,
TX 76177; telephone 817-222-5538; email [email protected].
SUPPLEMENTARY INFORMATION:
Background
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2017-0134R2, dated April 16, 2020
(EASA AD 2017-0134R2) (also referred to as the Mandatory Continuing
Airworthiness Information, or the MCAI), to correct an unsafe condition
for all Airbus Helicopters Model AS332L2 and EC225LP helicopters.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2016-12-51, Amendment 39-18578 (81 FR
43479, July 5, 2016) (AD 2016-12-51). AD 2016-12-51 applied to all
Airbus Helicopters Model AS332L2 and EC225LP helicopters. The NPRM
published in the Federal Register on June 1, 2021 (86 FR 29212). The
NPRM was prompted by an accident involving an Airbus Helicopters Model
EC225LP helicopter in which the main rotor hub detached from the MGB.
The Airbus Helicopters Model AS332L2 helicopter has a similar design to
the affected Model EC225LP helicopter, therefore, this model may be
subject to the unsafe condition revealed on the Model EC225LP
helicopter. The NPRM proposed to require replacing certain second stage
planet gear assemblies, removing certain epicyclic modules, installing
an FFMP, revising the existing RFM for your helicopter, repetitively
inspecting the MGB particle detectors, repetitively inspecting the MGB
oil filter and oil cooler, and corrective action if necessary, as
specified in EASA AD 2017-0134R2. The NPRM also proposed to provide
terminating action for certain repetitive inspections.
The FAA is issuing this AD to address failure of the main rotor
system, which would result in loss of control of the helicopter. See
the MCAI for additional background information.
Discussion of Final Airworthiness Directive
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The FAA received no comments on the NPRM or
on the determination of the cost to the public.
Conclusion
The FAA reviewed the relevant data and determined that air safety
and the public interest require adopting this final rule as proposed,
except for minor editorial changes. The FAA has determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
EASA AD 2017-0134R2 references procedures for replacing certain
second stage planet gear assemblies with serviceable parts; removing
certain epicyclic modules from service; modifying the helicopter by
installing an FFMP; revising the RFM to prohibit MGB particle burning
in-flight; repetitively inspecting the FFMP and MGB particle detectors
for metal particles, analyzing any metal particles that are found, and
corrective action; and repetitively inspecting the MGB oil filter and
oil cooler for particles and corrective action. The corrective actions
include replacing an affected MGB with a serviceable MGB. EASA AD 2017-
0134R2 also provides terminating action for certain repetitive
inspections.
Airbus Helicopters has issued Emergency Alert Service Bulletin
05A049, Revision 6, dated July 25, 2017, for Model EC225 helicopters;
and Emergency Alert Service Bulletin 05.01.07, Revision 6, dated July
27, 2017, for Model AS332 helicopters. The service information
specifies procedures for, among other things, replacing the MGB.
This material is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.
Differences Between This AD and the MCAI
Although the service information referenced in EASA AD 2017-0134R2
specifies to return affected planetary gear assemblies to the
manufacturer for module overhaul, this AD does not include that
requirement.
Although the service information referenced in EASA AD 2017-0134R2
specifies that retrofit of the planet gear of the MGB can only be done
by Airbus Helicopters or Airbus Helicopters approved repair centers,
this AD does not include that requirement.
EASA AD 2017-0134R2 requires operators to ``inform all flight
crews'' of revisions to the RFM, and thereafter to ``operate the
helicopter accordingly.'' However, this AD does not specifically
require those actions. FAA regulations mandate compliance with only the
operating limitations section of the flight manual. The flight manual
changes required by this AD apply to the emergency procedures section
of the existing RFM for your helicopter. Furthermore, compliance with
such
[[Page 50228]]
requirements in an AD is impracticable to demonstrate or track on an
ongoing basis; therefore, a requirement to operate the aircraft in such
a manner is unenforceable. Nonetheless, the FAA recommends that flight
crews of the helicopters listed in the applicability operate in
accordance with the revised emergency procedures mandated by this AD.
Interim Action
The FAA considers this AD interim action. If final action is later
identified, the FAA might consider further rulemaking then.
Costs of Compliance
The FAA estimates that this AD affects 28 helicopters of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
New actions.................... Up to 6 work-hours x $0 Up to $510........ Up to $14,280.
$85 per hour = $510.
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.
The FAA estimates that it will take about 1 work-hour per product
to comply with the reporting requirement in this AD. The average labor
rate is $85 per hour. Based on these figures, the FAA estimates the
cost of reporting the inspection results on U.S. operators to be
$2,380, or $85 per product.
The FAA estimates the following costs to do any necessary on-
condition actions that will be required based on the results of any
required actions. The FAA has no way of determining the number of
helicopters that might need these on-condition actions:
Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
40 work-hours x $85 per hour = $3,400. $295,000 $298,400
------------------------------------------------------------------------
According to the manufacturer, some or all of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected operators. The FAA does not control warranty coverage for
affected operators. As a result, the FAA has included all known costs
in the cost estimate.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to
Information Collection Clearance Officer, Federal Aviation
Administration, 10101 Hillwood Pkwy., Fort Worth, TX 76177-1524.
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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) 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.
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:
0
a. Removing Airworthiness Directive 2016-12-51, Amendment 39-18578 (81
FR 43479, July 5, 2016); and
0
b. Adding the following new airworthiness directive:
[[Page 50229]]
2021-16-05 Airbus Helicopters: Amendment 39-21667; Docket No. FAA-
2021-0379; Project Identifier MCAI-2021-00068-R.
(a) Effective Date
This airworthiness directive (AD) is effective October 13, 2021.
(b) Affected ADs
This AD replaces AD 2016-12-51, Amendment 39-18578 (81 FR 43479,
July 5, 2016) (AD 2016-12-51).
(c) Applicability
This AD applies to all Airbus Helicopters Model AS332L2 and
EC225LP helicopters, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC) Code 6320, Main Rotor
Gearbox.
(e) Reason
This AD was prompted by an accident involving a Model EC225LP
helicopter in which the main rotor hub detached from the main
gearbox. The FAA is issuing this AD to address failure of the main
rotor system, which would result in loss of control of the
helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, European Union Aviation Safety Agency (EASA) AD
2017-0134R2, dated April 16, 2020 (EASA AD 2017-0134R2).
(h) Exceptions to EASA AD 2017-0134R2
(1) Where EASA AD 2017-0134R2 refers to the effective dates
specified in paragraphs (h)(1)(i) through (v) of this AD, this AD
requires using the effective date of this AD.
(i) The effective date of EASA AD 2017-0134R2.
(ii) October 13, 2016 (the effective date of EASA AD 2016-0199,
dated October 7, 2016).
(iii) March 20, 2017 (the effective date of EASA AD 2017-0050-E,
dated March 17, 2017).
(iv) June 30, 2017 (the effective date of EASA AD 2017-0111,
dated June 23, 2017).
(v) August 1, 2017 (the effective date of EASA AD 2017-0134,
dated July 27, 2017).
(2) The ``Remarks'' section of EASA AD 2017-0134R2 does not
apply to this AD.
(3) Where any service information referred to in EASA AD 2017-
0134R2 specifies to discard certain parts after they have been
removed from the helicopter, this AD requires removing those parts
from service.
(4) Where paragraph (2) of EASA AD 2017-0134R2 specifies to
replace a part before exceeding the applicable ``new service life
limit,'' this AD requires removing that part from service.
(5) Where any service information referred to in EASA AD 2017-
0134R2 specifies to return certain parts to the manufacturer,
including for overhaul, after they have been removed from the
helicopter, this AD does not include that requirement.
(6) Where EASA AD 2017-0134R2 refers to flight hours (FH), this
AD requires using hours time-in-service.
(7) Where any service information referred to in EASA AD 2017-
0134R2 specifies to perform a metallurgical analysis and contact the
manufacturer if unsure about the characterization of the particles
collected, this AD does require characterization of the particles
collected, however this AD does not require contacting the
manufacturer to determine the characterization of the particles
collected.
(8) Where EASA AD 2017-0134R2 requires actions during each
``after last flight'' of the day (ALF) inspection, this AD requires
those actions before the first flight of each day.
(9) Where any service information referred to in EASA AD 2017-
0134R2 specifies to do the actions identified in paragraphs
(h)(9)(i) through (iv) of this AD, this AD does not include those
requirements.
(i) Watch a video for removing the grease from the full flow
magnetic plug (FFMP), using a cleaning agent, and collecting
particles.
(ii) Return affected planetary gear assembly to the manufacturer
for module overhaul.
(iii) Contact the approved repair station/Airbus Helicopters if
the reason for a repair to an epicyclic module is unknown and
inform/contact Airbus Helicopters.
(iv) Contact the approved repair station/Airbus Helicopters
depending on who performed the last overhaul (RG) to determine if a
repair has been done on the second stage planet gears since new.
(10) Where any service information referred to in EASA AD 2017-
0134R2 specifies that retrofit of the planet gear of the main
gearbox (MGB) can only be done by Airbus Helicopters or Airbus
Helicopters approved repair centers, this AD does not require that
the retrofit of the planet gear be done only by Airbus Helicopters
or Airbus Helicopters approved repair centers. For this AD the
retrofit can also be done by an FAA-approved repair station.
(11) Where paragraph (5) of EASA AD 2017-0134R2 specifies
accomplishing the FFMP additional work within 3 months after August
1, 2017, this AD requires accomplishing the FFMP additional work
within 4 months after the effective date of this AD.
(12) Where paragraph (6) of EASA AD 2017-0134R2 specifies to
``inform all flight crews and, thereafter, operate the helicopter
accordingly,'' this AD does not require those actions.
(13) Where any service information referred to in EASA AD 2017-
0134R2 specifies that if any 16NCD13 particles are found you are to
take a 1-liter sample of oil and send it to the manufacturer, this
AD does not require those actions.
(14) Where any service information referred to in EASA AD 2017-
0134R2 specifies ``Do not resume flights until corrective action(s)
are agreed by Airbus Helicopters,'' or to contact Airbus Helicopters
before resuming flights ``if further particles are collected during
the close monitoring period'' for this AD, you must repair before
further flight using a method specified in paragraph (h)(14)(i) or
(ii) of this AD.
(i) In accordance with FAA approved procedures.
(ii) The procedures specified in Appendix 4.A., Particle
Analysis, of Airbus Helicopters Emergency Alert Service Bulletin
05A049, Revision 6, dated July 25, 2017; or Emergency Alert Service
Bulletin 05.01.07, Revision 6, dated July 27, 2017, as applicable,
except as required by paragraphs (h)(5), (7), and (13) of this AD.
(15) Where the service information identified in EASA AD 2017-
0134R2 specifies to report inspection results to Airbus Helicopters,
for this AD, report the inspection results at the applicable time
specified in paragraph (h)(15)(i) or (ii) of this AD.
(i) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the date of the
inspection.
(ii) If the inspection was done before the effective date of
this AD: Submit the report within 30 days after the effective date
of this AD.
(i) Credit for Previous Actions
(1) This paragraph provides credit for the actions specified in
paragraph (4) of EASA AD 2017-0134R2, if those actions were
performed before the effective date of this AD using Airbus
Helicopters Emergency Alert Service Bulletin 63.00.83 or 63A030,
both Revision 1, both dated October 7, 2016.
(2) Corrective action(s) for the inspections required by
paragraphs (8) and (10) of EASA AD 2017-0134R2 accomplished on a
helicopter before the effective date of this AD, in accordance with
Paragraph 3.B. and Appendix 4.A. of the Accomplishment Instructions
of the applicable Airbus Helicopters service information specified
in paragraphs (i)(2)(i) through (viii) of this AD, as applicable,
are acceptable to comply with the requirements of paragraph (11) of
EASA AD 2017-0134R2 for that helicopter, but only for the corrective
actions for the inspections required by paragraphs (8) and (10) of
EASA AD 2017-0134R2.
(i) Emergency Alert Service Bulletin 05.01.07, Revision 2, dated
October 7, 2016.
(ii) Emergency Alert Service Bulletin 05.01.07, Revision 3,
dated February 25, 2017.
(iii) Emergency Alert Service Bulletin 05.01.07, Revision 4,
dated March 17, 2017.
(iv) Emergency Alert Service Bulletin 05.01.07, Revision 5,
dated June 23, 2017.
(v) Emergency Alert Service Bulletin 05A049, Revision 2, dated
October 7, 2016.
(vi) Emergency Alert Service Bulletin 05A049, Revision 3, dated
February 25, 2017.
(vii) Emergency Alert Service Bulletin 05A049, Revision 4, dated
March 17, 2017.
(viii) Emergency Alert Service Bulletin 05A049, Revision 5,
dated June 23, 2017.
(j) Special Flight Permit
Special flight permits, as described in 14 CFR 21.197 and
21.199, are prohibited.
[[Page 50230]]
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, International Validation Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the International Validation Branch, send
it to the attention of the person identified in paragraph (l)(1) of
this AD. Information may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(l) Related Information
(1) For more information about this AD, contact Mahmood Shah,
Aviation Safety Engineer, Fort Worth ACO Branch, FAA, 10101 Hillwood
Pkwy., Fort Worth, TX 76177; telephone 817-222-5538; email
[email protected].
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (m)(4) and (5) of this AD.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency (EASA) AD 2017-0134R2,
dated April 16, 2020.
(ii) Airbus Helicopters Emergency Alert Service Bulletin 05A049,
Revision 6, dated July 25, 2017.
(iii) Airbus Helicopters Emergency Alert Service Bulletin
05.01.07, Revision 6, dated July 27, 2017.
(3) For EASA AD 2017-0134R2, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email
[email protected]; Internet www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://ad.easa.europa.eu.
(4) For Airbus Helicopters service information, contact Airbus
Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or
at https://www.airbus.com/helicopters/services/technical-support.html.
(5) You may view this service information at the FAA, Office of
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room
6N-321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call 817-222-5110. This material may be
found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2021-0379.
(6) You may view this material that is incorporated by reference
at the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, email
[email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on July 22, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021-19247 Filed 9-7-21; 8:45 am]
BILLING CODE 4910-13-P
