Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France), 38220-38223 [2021-15302]
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Federal Register / Vol. 86, No. 136 / Tuesday, July 20, 2021 / Rules and Regulations
(a) Effective Date
This airworthiness directive (AD) is
effective August 24, 2021.
(b) Affected ADs
This AD replaces AD 2011–18–52,
Amendment 39–17020 (77 FR 23109, April
18, 2012) (AD 2011–18–52).
(c) Applicability
This AD applies to Leonardo S.p.a. (type
certificate previously held by Agusta S.p.A.)
Model AB139 and AW139 helicopters,
certificated in any category, with tail rotor
(T/R) blade, part number (P/N)
3G6410A00131, 3G6410A00132,
3G6410A00133, 4G6410A00131,
4G6410A00132, or 4G6410A00133, installed.
(d) Subject
Joint Aircraft Service Component (JASC)
Code: 6410, Tail Rotor Blades.
(e) Unsafe Condition
This AD defines the unsafe condition as a
crack in a T/R blade. This condition could
result in failure of a T/R blade and
subsequent loss of control of 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 T/R blade P/Ns 3G6410A00131 and
4G6410A00131, within 5 hours time-inservice (TIS) after May 3, 2012 (the effective
date of AD 2011–18–52), establish a life limit
of 600 hours TIS or 1,500 takeoff and landing
cycles (cycles), whichever occurs first, on the
affected T/R blades and update the
helicopter’s historical records. If a T/R
blade’s total number of cycles is unknown,
determine the T/R blade cycles by
multiplying the T/R blade’s hours TIS by 4.
(2) For T/R blade P/Ns 3G6410A00131 and
4G6410A00131, thereafter following
paragraph (g)(1) of this AD, remove any T/R
blade from service before accumulating 600
total hours TIS or 1,500 total cycles,
whichever occurs first.
(3) For T/R blade P/Ns 3G6410A00132,
3G6410A00133, 4G6410A00132, and
4G6410A00133, within 5 hours TIS after the
effective date of this AD, determine the total
number of cycles. If a T/R blade’s total
number of cycles is unknown, determine the
T/R blade cycles by multiplying the blade’s
hours TIS by 4. Before further flight, remove
any T/R blade from service that has
accumulated or exceeded its life limit as
follows. Thereafter, remove any T/R blade
from service before accumulating its life limit
as follows:
(i) T/R blade P/Ns 3G6410A00132 and
4G6410A00132: 1,200 total hours TIS or
3,200 total cycles, whichever occurs first.
(ii) T/R blade P/N 3G6410A00133: 40,000
total cycles.
(iii) T/R blade P/N 4G6410A00133: 4,033
total hours TIS or 40,000 cycles, whichever
occurs first.
Note 1 to paragraph (g)(3): A combination
of T/R blades having different P/Ns can be
installed on the same helicopter. The eligible
combinations of T/R blades P/N are listed in
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AgustaWestland Mandatory Bollettino
Tecnico No. 139–265, Revision B, dated
February 18, 2014 (BT No. 139–265).
(4) For T/R blade P/Ns 3G6410A00131 and
P/N 4G6410A00131, within 25 hours TIS
after the effective date of this AD, and
thereafter at intervals not to exceed 25 hours
TIS, visually inspect the T/R blade for a crack
and damage that exceeds allowable limits.
Inspect in the area depicted in Figure 1 of BT
No. 139–265 using a mirror, a 5X or higher
power magnifying glass, and a flashlight, or
borescope. If there is a crack or damage that
exceeds allowable limits, before further
flight, remove the T/R blade from service.
(5) As of the effective date of this AD, do
not install on any helicopter any T/R blade
P/N 3G6410A00131 or P/N 4G6410A00131,
unless the actions required by paragraphs
(g)(1), (2), and (4) of this AD have been
accomplished.
(h) 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 (i)(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.
(i) Related Information
(1) For more information about this AD,
contact Matt Fuller, AD Program Manager,
General Aviation & Rotorcraft Unit,
Airworthiness Products Section, Operational
Safety Branch, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone (817) 222–
5110; email matthew.fuller@faa.gov.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (now
European Union Aviation Safety Agency)
(EASA) AD 2012–0076R2, dated February 20,
2014. You may view the EASA AD at https://
www.regulations.gov in Docket No. FAA–
2021–0348.
(j) 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) AgustaWestland Mandatory Bollettino
Tecnico No. 139–265, Revision B, dated
February 18, 2014.
(ii) [Reserved]
(3) For service information identified in
this AD, contact Leonardo S.p.A. Helicopters,
Emanuele Bufano, Head of Airworthiness,
Viale G.Agusta 520, 21017 C. Costa di
Samarate (Va) Italy; telephone +39–0331–
PO 00000
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225074; fax +39–0331–229046; or at https://
www.leonardocompany.com/en/home.
(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: fedreg.legal@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on July 2, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–15303 Filed 7–19–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0175; Project
Identifier 2001–SW–33–AD; Amendment 39–
21643; AD 2021–14–16]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters (Type Certificate
Previously Held by Eurocopter France)
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
Airbus Helicopters (type certificate
previously held by Eurocopter France)
Model SA–365N, SA–365N1, AS–
365N2, AS 365 N3, and SA–366G1
helicopters. This AD was prompted by
a quality control check that revealed
some stretcher attachment holes were
improperly located on the frame where
there was insufficient edge distance.
This AD requires measuring the 9degree frame flange (frame) for the
correct edge distance of the four
attachment holes for the stretcher
support and inspecting for cracks, and
repairing the frame, if necessary, and
installation of a reinforcement plate
(reinforcing angle), as specified in two
Direction Ge´ne´rale de l’Aviation Civile
(DGAC) ADs, which are incorporated by
reference. The FAA is issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective August 24,
2021.
SUMMARY:
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Federal Register / Vol. 86, No. 136 / Tuesday, July 20, 2021 / Rules and Regulations
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 24, 2021.
ADDRESSES: For DGAC material
incorporated by reference (IBR) in this
AD, contact the European Union
Aviation Safety Agency (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 the DGAC material on the EASA
website at https://ad.easa.europa.eu.
For American Eurocopter material,
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.airbus.com/helicopters/services/
technical-support.html. You may view
the DGAC and American Eurocopter
material at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321,
Fort Worth, TX 76177. Service
information that is incorporated by
reference is also available at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0175.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0175; 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, the DGAC ADs, any
comments received, and other
information. The street 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:
Blaine Williams, Aerospace Engineer,
Cabin Safety & Environmental Systems
Section, Los Angeles ACO Branch,
Compliance & Airworthiness Division,
3960 Paramount Blvd., Lakewood, CA
90712; telephone 562–627–5371; email
blaine.williams@faa.gov.
SUPPLEMENTARY INFORMATION:
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Background
The DGAC, which was the Technical
Agent for France, issued DGAC AD
2001–061–053(A), dated February 21,
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2001 (DGAC AD 2001–061–053(A)) for
certain Model SA–365N, SA–365N1,
AS–365N2, and AS 365 N3 helicopters;
and DGAC AD 2001–283–025(A), dated
July 11, 2001 (DGAC AD 2001–283–
025(A)) for all Model SA–366G1
helicopters (also referred to as the
Mandatory Continuing Airworthiness
Information, or the MCAI), to correct an
unsafe condition for those helicopters.
The FAA issued a second
supplemental notice of proposed
rulemaking (SNPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus Helicopters (type
certificate previously held by
Eurocopter France) Model SA–365N,
SA–365N1, AS–365N2, AS 365 N3, and
SA–366G1 helicopters. The second
SNPRM published in the Federal
Register on May 7, 2021 (86 FR 24556).
The second SNPRM proposed to require
inspecting the frame for the correct edge
distance of the four attachment holes of
the stretcher support and for a crack,
and repairing the frame, if necessary,
and installation of a reinforcement plate
(reinforcing angle) on the frame, as
specified in DGAC AD 2001–061–
053(A) and DGAC AD 2001–283–
025(A). The second SNPRM also
included references to an engineering
report that lists approved U.S.
alternative fasteners and materials that
may be used in any required repairs.
The second SNPRM was issued because
a significant amount of time elapsed
since the first SNPRM was published.
The FAA is issuing this AD to address
failure of the 9-degree frame due to a
crack at the stretcher support
attachment holes, which could result in
loss of a passenger door, damage to the
rotor system, and subsequent loss of
control of the helicopter. See the MCAI
for additional background information.
Discussion of Final Airworthiness
Directive
Comments
The FAA received no comments on
the second SNPRM or on the
determination of the costs.
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:
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• Are consistent with the intent that
was proposed in the second SNPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the second SNPRM.
Related Service Information Under 1
CFR Part 51
DGAC AD 2001–061–053(A) and
DGAC AD 2001–283–025(A) describe
procedures for measuring the edge
distance of the webs at the four
attachment holes of the stretcher
support on the left and right sides of the
9-degree frame, and additional actions
depending on the findings. The
additional actions include repetitively
inspecting the frame for cracking, repair
if necessary, and installation of a
reinforcement plate (reinforcing angle)
on the frame. These documents are
distinct since they refer to different
helicopter models.
American Eurocopter Engineering
Report No. AEC/03R–E–005,
‘‘Addendum ASB 53.00.42 and 53.00.43
AS365,’’ dated January 29, 2003,
specifies U.S. and European rivet
equivalent part numbers, U.S. rivet part
numbers with acceptable substitute
materials with greater strength
properties, and 5 rivet, 6 rivet, and pin
Hi-lok alternatives.
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
The FAA has determined that
acceptable U.S. alternatives to the
fasteners and materials needed to
perform repairs or modifications are
listed in American Eurocopter
Engineering Report No. AEC/03R–E–005
‘‘Addendum ASB 53.00.42 and
53.00.043 AS365’’, dated January 29,
2003.
Where DGAC AD 2001–061–053(A)
exempts helicopters that were delivered
after January 31, 2001, from the
applicability, this AD does not exempt
those helicopters.
Costs of Compliance
The FAA estimates that this AD
affects 31 helicopters of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
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Federal Register / Vol. 86, No. 136 / Tuesday, July 20, 2021 / Rules and Regulations
ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
3 work-hours × $85 per hour = $255 ..........................................................................................
$100
$355
$11,005
The FAA estimates the following
costs to do any necessary on-condition
actions that would 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 ACTION
Labor cost
Parts cost
Cost per
product
Up to 8 work-hours × $85 per hour = $680 ............................................................................................................
$250
Up to $930
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 helicopters identified in this
rulemaking action.
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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.
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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:
■
2021–14–16 Airbus Helicopters (Type
Certificate Previously Held by
Eurocopter France): Amendment 39–
21643; Docket No. FAA–2021–0175;
Project Identifier 2001–SW–33–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective August 24, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Helicopters
(type certificate previously held by
Eurocopter France) Model SA–365N, SA–
365N1, AS–365N2, AS 365 N3, and SA–
366G1 helicopters, certificated in any
category.
(d) Subject
Joint Aircraft Service Component (JASC)
Code 5311, Fuselage Main, Frame.
(e) Reason
This AD was prompted by a quality control
check that revealed some stretcher
attachment holes were improperly located on
the frame where there was insufficient edge
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distance. The FAA is issuing this AD to
address failure of the 9-degree frame flange
(frame) due to a crack at the stretcher support
attachment holes, which could result in loss
of a passenger door, damage to the rotor
system, and subsequent 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 the applicable Direction
Ge´ne´rale de l’Aviation Civile (DGAC) ADs
specified in paragraphs (g)(1) and (2) of this
AD.
(1) For Model SA–365N, SA–365N1, AS–
365N2, and AS 365 N3 helicopters: DGAC
AD 2001–061–053(A), dated February 21,
2001, (DGAC AD 2001–061–053(A)).
(2) For Model SA–366G1 helicopters:
DGAC AD 2001–283–025(A), dated July 11,
2001 (DGAC AD 2001–283–025(A)).
(h) Exceptions to DGAC AD 2001–061–
053(A) and DGAC AD 2001–283–025(A)
(1) Where paragraph 3.1 of DGAC AD
2001–061–053(A) and DGAC AD 2001–283–
025(A) specifies an initial compliance time to
do the measurement, for this AD, do the
measurement within 50 hours time-in-service
(TIS) after the effective date of this AD.
(2) Where paragraph 3.1. of DGAC AD
2001–061–053(A) and DGAC AD 2001–283–
025(A) specifies to do a measurement, for
this AD, do an inspection of the area around
the attachment holes for cracks concurrently
with the measurement.
(3) Where paragraph 3.2.1.a) of DGAC AD
2001–061–053(A) and DGAC AD 2001–283–
025(A) specifies ‘‘every 550 flight hours,
check that there is no crack in the flange,’’
for this AD, inspect (check) the area around
the attachment holes for cracks at intervals
not to exceed 550 hours TIS.
(4) Where paragraph 3.2.1.b) of DGAC AD
2001–061–053(A) and DGAC AD 2001–283–
025(A) requires installation of a
reinforcement plate (reinforcing angle) on the
flange for certain helicopters, do the
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installation within 550 hours TIS after
accomplishment of the measurement
specified in paragraph 3.1. of DGAC AD
2001–061–053(A) and DGAC AD 2001–283–
025(A).
(5) Where the service information referred
to in DGAC AD 2001–061–053(A) and DGAC
AD 2001–283–025(A) specifies to perform a
dye penetrant crack inspection ‘‘if in doubt,’’
this AD requires performing a dye penetrant
inspection.
(6) Where paragraph 3.2.2. of DGAC AD
2001–061–053(A) and DGAC AD 2001–283–
025(A) specifies to do various actions
specified in paragraphs 3.2.2.a), b), and c) of
those ADs, for this AD, if any frame is
cracked, before further flight, repair the
frame. Acceptable U.S. alternatives to the
fasteners and materials needed to perform
repairs or modifications are listed in
American Eurocopter Engineering Report No.
AEC/03R–E–005, ‘‘Addendum ASB 53.00.42
and 53.00.43 AS365’’, dated January 29,
2003.
(7) Where the Note in paragraph 3.2.2. of
DGAC AD 2001–061–053(A) and DGAC AD
2001–283–025(A) specifies the instructions
are no longer applicable after a customized
repair has been carried out, for this AD,
modifying or repairing the frame constitutes
terminating action for the requirements of
this AD.
(i) Special Flight Permit
Special flight permits, as described in 14
CFR 21.197 and 21.199, are prohibited.
(j) 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 (k) 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.
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(k) Related Information
For more information about this AD,
contact Blaine Williams, Aerospace Engineer,
Cabin Safety & Environmental Systems
Section, Los Angeles ACO Branch,
Compliance & Airworthiness Division, 3960
Paramount Blvd., Lakewood, CA 90712;
telephone 562–627–5371; email
blaine.williams@faa.gov.
(l) 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.
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Jkt 253001
(i) Direction Ge´ne´rale de l’Aviation Civile
(DGAC) AD 2001–061–053(A), dated
February 21, 2001.
(ii) DGAC AD 2001–283–025(A), dated July
11, 2001.
(iii) American Eurocopter Engineering
Report No. AEC/03R–E–005, ‘‘Addendum
ASB 53.00.42 and 53.00.43 AS365’’, dated
January 29, 2003.
(3) For DGAC AD 2001–061–053(A) and
DGAC AD 2001–283–025(A), contact the
European Union Aviation Safety Agency
(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 these
DGAC ADs on the EASA website at https://
ad.easa.europa.eu.
(4) For American Eurocopter material
identified in 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.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.
(6) 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: fedreg.legal@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on July 2, 2021.
Ross Landes,
Deputy Director for Regulatory Operations,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–15302 Filed 7–19–21; 8:45 am]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0031; Project
Identifier MCAI–2020–01420–T; Amendment
39–21625; AD 2021–13–20]
RIN 2120–AA64
Airworthiness Directives; Airbus
Canada Limited Partnership (Type
Certificate Previously Held by C Series
Aircraft Limited Partnership (CSALP);
Bombardier, Inc.) Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Canada Limited Partnership
SUMMARY:
Frm 00015
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Model BD–500–1A10 and BD–500–
1A11 airplanes. This AD was prompted
by reports of corrosion on the waste box,
waste access doubler, and waste service
door of the rear fuselage due to
contamination from waste valve leakage.
This AD requires an inspection for
corrosion of the waste box, waste access
doubler, and waste service door, and
corrective actions if necessary, as
specified in a Transport Canada Civil
Aviation (TCCA) AD, which is
incorporated by reference. The FAA is
issuing this AD to address the unsafe
condition on these products.
This AD is effective August 24,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 24, 2021.
DATES:
For material incorporated
by reference (IBR) in this AD, contact
TCCA, Transport Canada National
Aircraft Certification, 159 Cleopatra
Drive, Nepean, Ontario, K1A 0N5,
Canada; telephone 888–663–3639; email
AD-CN@tc.gc.ca; internet https://
tc.canada.ca/en/aviation. You may view
this IBR material at the FAA,
Airworthiness Products Section,
Operational Safety Branch, 2200 South
216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
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–
0031.
ADDRESSES:
Examining the AD Docket
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38223
Sfmt 4700
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0031; 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:
Siddeeq Bacchus, Aerospace Engineer,
Mechanical Systems and Administrative
Services Section, FAA, New York ACO
Branch, 1600 Stewart Avenue, Suite
410, Westbury, NY 11590; telephone
516–228–7362; fax 516–794–5531; email
9-avs-nyaco-cos@faa.gov.
SUPPLEMENTARY INFORMATION:
E:\FR\FM\20JYR1.SGM
20JYR1
]]>Agencies
[Federal Register Volume 86, Number 136 (Tuesday, July 20, 2021)]
[Rules and Regulations]
[Pages 38220-38223]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-15302]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0175; Project Identifier 2001-SW-33-AD; Amendment
39-21643; AD 2021-14-16]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters (Type Certificate
Previously Held by Eurocopter France)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Airbus Helicopters (type certificate previously held by Eurocopter
France) Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1
helicopters. This AD was prompted by a quality control check that
revealed some stretcher attachment holes were improperly located on the
frame where there was insufficient edge distance. This AD requires
measuring the 9-degree frame flange (frame) for the correct edge
distance of the four attachment holes for the stretcher support and
inspecting for cracks, and repairing the frame, if necessary, and
installation of a reinforcement plate (reinforcing angle), as specified
in two Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC)
ADs, which are incorporated by reference. The FAA is issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective August 24, 2021.
[[Page 38221]]
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 24,
2021.
ADDRESSES: For DGAC material incorporated by reference (IBR) in this
AD, contact the European Union Aviation Safety Agency (EASA), Konrad-
Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000;
email [email protected]; internet www.easa.europa.eu. You may find the
DGAC material on the EASA website at https://ad.easa.europa.eu. For
American Eurocopter material, 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.airbus.com/helicopters/services/technical-support.html. You may view the DGAC and American Eurocopter
material at the FAA, Office of the Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. Service
information that is incorporated by reference is also available at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2021-0175.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0175; 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, the
DGAC ADs, any comments received, and other information. The street
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: Blaine Williams, Aerospace Engineer,
Cabin Safety & Environmental Systems Section, Los Angeles ACO Branch,
Compliance & Airworthiness Division, 3960 Paramount Blvd., Lakewood, CA
90712; telephone 562-627-5371; email [email protected].
SUPPLEMENTARY INFORMATION:
Background
The DGAC, which was the Technical Agent for France, issued DGAC AD
2001-061-053(A), dated February 21, 2001 (DGAC AD 2001-061-053(A)) for
certain Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters;
and DGAC AD 2001-283-025(A), dated July 11, 2001 (DGAC AD 2001-283-
025(A)) for all Model SA-366G1 helicopters (also referred to as the
Mandatory Continuing Airworthiness Information, or the MCAI), to
correct an unsafe condition for those helicopters.
The FAA issued a second supplemental notice of proposed rulemaking
(SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to all
Airbus Helicopters (type certificate previously held by Eurocopter
France) Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1
helicopters. The second SNPRM published in the Federal Register on May
7, 2021 (86 FR 24556). The second SNPRM proposed to require inspecting
the frame for the correct edge distance of the four attachment holes of
the stretcher support and for a crack, and repairing the frame, if
necessary, and installation of a reinforcement plate (reinforcing
angle) on the frame, as specified in DGAC AD 2001-061-053(A) and DGAC
AD 2001-283-025(A). The second SNPRM also included references to an
engineering report that lists approved U.S. alternative fasteners and
materials that may be used in any required repairs. The second SNPRM
was issued because a significant amount of time elapsed since the first
SNPRM was published.
The FAA is issuing this AD to address failure of the 9-degree frame
due to a crack at the stretcher support attachment holes, which could
result in loss of a passenger door, damage to the rotor system, and
subsequent loss of control of the helicopter. See the MCAI for
additional background information.
Discussion of Final Airworthiness Directive
Comments
The FAA received no comments on the second SNPRM or on the
determination of the costs.
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
second SNPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the second SNPRM.
Related Service Information Under 1 CFR Part 51
DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A) describe
procedures for measuring the edge distance of the webs at the four
attachment holes of the stretcher support on the left and right sides
of the 9-degree frame, and additional actions depending on the
findings. The additional actions include repetitively inspecting the
frame for cracking, repair if necessary, and installation of a
reinforcement plate (reinforcing angle) on the frame. These documents
are distinct since they refer to different helicopter models.
American Eurocopter Engineering Report No. AEC/03R-E-005,
``Addendum ASB 53.00.42 and 53.00.43 AS365,'' dated January 29, 2003,
specifies U.S. and European rivet equivalent part numbers, U.S. rivet
part numbers with acceptable substitute materials with greater strength
properties, and 5 rivet, 6 rivet, and pin Hi-lok alternatives.
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
The FAA has determined that acceptable U.S. alternatives to the
fasteners and materials needed to perform repairs or modifications are
listed in American Eurocopter Engineering Report No. AEC/03R-E-005
``Addendum ASB 53.00.42 and 53.00.043 AS365'', dated January 29, 2003.
Where DGAC AD 2001-061-053(A) exempts helicopters that were
delivered after January 31, 2001, from the applicability, this AD does
not exempt those helicopters.
Costs of Compliance
The FAA estimates that this AD affects 31 helicopters of U.S.
registry. The FAA estimates the following costs to comply with this AD:
[[Page 38222]]
Estimated Costs For Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
3 work-hours x $85 per hour = $255........................... $100 $355 $11,005
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary on-
condition actions that would 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 Action
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
Up to 8 work-hours x $85 per hour = $250 Up to $930
$680.................................
------------------------------------------------------------------------
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 helicopters 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 adding the following new airworthiness
directive:
2021-14-16 Airbus Helicopters (Type Certificate Previously Held by
Eurocopter France): Amendment 39-21643; Docket No. FAA-2021-0175;
Project Identifier 2001-SW-33-AD.
(a) Effective Date
This airworthiness directive (AD) is effective August 24, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Helicopters (type certificate
previously held by Eurocopter France) Model SA-365N, SA-365N1, AS-
365N2, AS 365 N3, and SA-366G1 helicopters, certificated in any
category.
(d) Subject
Joint Aircraft Service Component (JASC) Code 5311, Fuselage
Main, Frame.
(e) Reason
This AD was prompted by a quality control check that revealed
some stretcher attachment holes were improperly located on the frame
where there was insufficient edge distance. The FAA is issuing this
AD to address failure of the 9-degree frame flange (frame) due to a
crack at the stretcher support attachment holes, which could result
in loss of a passenger door, damage to the rotor system, and
subsequent 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 the applicable Direction G[eacute]n[eacute]rale de
l'Aviation Civile (DGAC) ADs specified in paragraphs (g)(1) and (2)
of this AD.
(1) For Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3
helicopters: DGAC AD 2001-061-053(A), dated February 21, 2001, (DGAC
AD 2001-061-053(A)).
(2) For Model SA-366G1 helicopters: DGAC AD 2001-283-025(A),
dated July 11, 2001 (DGAC AD 2001-283-025(A)).
(h) Exceptions to DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A)
(1) Where paragraph 3.1 of DGAC AD 2001-061-053(A) and DGAC AD
2001-283-025(A) specifies an initial compliance time to do the
measurement, for this AD, do the measurement within 50 hours time-
in-service (TIS) after the effective date of this AD.
(2) Where paragraph 3.1. of DGAC AD 2001-061-053(A) and DGAC AD
2001-283-025(A) specifies to do a measurement, for this AD, do an
inspection of the area around the attachment holes for cracks
concurrently with the measurement.
(3) Where paragraph 3.2.1.a) of DGAC AD 2001-061-053(A) and DGAC
AD 2001-283-025(A) specifies ``every 550 flight hours, check that
there is no crack in the flange,'' for this AD, inspect (check) the
area around the attachment holes for cracks at intervals not to
exceed 550 hours TIS.
(4) Where paragraph 3.2.1.b) of DGAC AD 2001-061-053(A) and DGAC
AD 2001-283-025(A) requires installation of a reinforcement plate
(reinforcing angle) on the flange for certain helicopters, do the
[[Page 38223]]
installation within 550 hours TIS after accomplishment of the
measurement specified in paragraph 3.1. of DGAC AD 2001-061-053(A)
and DGAC AD 2001-283-025(A).
(5) Where the service information referred to in DGAC AD 2001-
061-053(A) and DGAC AD 2001-283-025(A) specifies to perform a dye
penetrant crack inspection ``if in doubt,'' this AD requires
performing a dye penetrant inspection.
(6) Where paragraph 3.2.2. of DGAC AD 2001-061-053(A) and DGAC
AD 2001-283-025(A) specifies to do various actions specified in
paragraphs 3.2.2.a), b), and c) of those ADs, for this AD, if any
frame is cracked, before further flight, repair the frame.
Acceptable U.S. alternatives to the fasteners and materials needed
to perform repairs or modifications are listed in American
Eurocopter Engineering Report No. AEC/03R-E-005, ``Addendum ASB
53.00.42 and 53.00.43 AS365'', dated January 29, 2003.
(7) Where the Note in paragraph 3.2.2. of DGAC AD 2001-061-
053(A) and DGAC AD 2001-283-025(A) specifies the instructions are no
longer applicable after a customized repair has been carried out,
for this AD, modifying or repairing the frame constitutes
terminating action for the requirements of this AD.
(i) Special Flight Permit
Special flight permits, as described in 14 CFR 21.197 and
21.199, are prohibited.
(j) 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 (k) 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.
(k) Related Information
For more information about this AD, contact Blaine Williams,
Aerospace Engineer, Cabin Safety & Environmental Systems Section,
Los Angeles ACO Branch, Compliance & Airworthiness Division, 3960
Paramount Blvd., Lakewood, CA 90712; telephone 562-627-5371; email
[email protected].
(l) 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) Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC)
AD 2001-061-053(A), dated February 21, 2001.
(ii) DGAC AD 2001-283-025(A), dated July 11, 2001.
(iii) American Eurocopter Engineering Report No. AEC/03R-E-005,
``Addendum ASB 53.00.42 and 53.00.43 AS365'', dated January 29,
2003.
(3) For DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A),
contact the European Union Aviation Safety Agency (EASA), Konrad-
Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000;
email [email protected]; internet www.easa.europa.eu. You may find
these DGAC ADs on the EASA website at https://ad.easa.europa.eu.
(4) For American Eurocopter material identified in 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.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.
(6) 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: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on July 2, 2021.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021-15302 Filed 7-19-21; 8:45 am]
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