Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters, 28476-28479 [2021-11080]
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28476
Federal Register / Vol. 86, No. 101 / Thursday, May 27, 2021 / Rules and Regulations
cycles per hour TIS, the IFWU assembly is
an REL IFWU assembly.
(ii) If any calculation specified in
paragraph (h)(2) of this AD results in 6 or less
lift cycles per hour TIS, the IFWU assembly
is a Non-REL IFWU assembly.
Note 1 to paragraph (h)(2): Sikorsky
Aircraft Corporation All Operators Letter
(AOL) CCS–61–AOL–04–0005, dated May 18,
2004, provides an example and additional
information about tracking cycles and the
moving average procedure.
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Note 2 to paragraph (h)(2): The following
is a sample calculation for subsequent 50
hour TIS intervals. Assume the total number
of lift cycles for the first 50 hour TIS interval
used in the previous moving average
calculation = 450 lift cycles and the total
number of lift cycles for the previous 300
hours TIS = 2,700 lift cycles. The subsequent
moving average of lift cycles per hour TIS =
(2,700¥450) divided by 250 = 9 lift cycles
per hour TIS.
(3) Once an IFWU assembly is determined
to be an REL IFWU assembly, it remains an
REL IFWU assembly for the rest of its service
life and is subject to the inspection for REL
IFWU assemblies required by paragraph (i) of
this AD.
(4) Once an IFWU assembly is determined
to be an REL IFWU assembly, you no longer
need to perform the 250-hour TIS moving
average calculation required by paragraph
(h)(2) of this AD, but you must continue to
count and record the lift cycles as required
by paragraph (g)(2) of this AD.
(i) Repetitive Inspections of REL IFWU
Assemblies and Replacement
For each REL IFWU assembly, as
determined by paragraph (h)(1) or (2) of this
AD:
(1) Within 500 hours TIS or 7,500 lift
cycles, whichever occurs first since the
assembly was determined to be a REL IFWU
assembly, and thereafter at intervals not to
exceed 500 hours TIS or 7,500 lift cycles,
whichever occurs first, inspect for wear,
surface distress, and endplay by following
paragraphs B.(1) through B.(6) of the
Accomplishment Instructions of Sikorsky
Aircraft Corporation Alert Service Bulletin
61B35–67B, Revision B, dated August 11,
2003. Record all the information specified in
Figures 1 through 3 of the Sikorsky Aircraft
Corporation Alert Service Bulletin 61B35–
67B, Revision B, dated August 11, 2003. You
may record this information on any suitable
maintenance record, or you may use the
Sikorsky evaluation forms provided in
Sikorsky Aircraft Corporation Alert Service
Bulletin 61B35–67B, Revision B, dated
August 11, 2003. This AD does not require
you to contact Sikorsky or provide
information to Sikorsky.
(2) If during any inspection required by
paragraph (i)(1) of this AD, any IFWU
assembly part is found whose average wear,
wear marks, surface distress, or endplay
exceeds the limits specified in paragraphs
B.(1) through B.(6) of the Accomplishment
Instructions of Sikorsky Aircraft Corporation
Alert Service Bulletin 61B35–67B, Revision
B, dated August 11, 2003, before further
flight, replace the affected part with an
airworthy IFWU assembly part.
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Note 3 to paragraph (i)(2): Sikorsky
Aircraft S–61L/N Overhaul Manual, SA4045–
83, Revision 20, dated August 15, 2003, as
revised by Temporary Revisions 65–193,
–194, –195, and –196, contains the overhaul
procedures for the IFWU assembly.
(j) Part Marking
For each REL IFWU assembly, as
determined by paragraph (h)(1) or (2) of this
AD: Before further flight after the assembly
was determined to be an REL IFWU
assembly, permanently mark IFWU
camshafts, P/N 61350–24052, 61350–24072,
S6135–20611, S6135–20614 and S6137–
23075, and IFWU gear housings, P/N 61350–
24051, 61350–24068, S6135–20695, and
S6137–23057, with the letters ‘‘REL’’. Mark
the camshafts by applying etching ink on the
surface of the part that is 0.5-inch square
with the depth of the letters not to exceed
0.001 inch. Before further flight and after
etching, neutralize the etched surface and oil
to prevent corrosion.
(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.
(l) Related Information
(1) For more information about this AD,
contact Isabel Saltzman, Aviation Safety
Engineer, Boston ACO Branch, FAA, 1200
District Avenue, Burlington, MA 01803;
telephone 781–238–7649; email
Isabel.L.Saltzman@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (m)(3) and (4) 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 the AD specifies otherwise.
(i) Sikorsky Aircraft Corporation Alert
Service Bulletin 61B35–67B, Revision B,
dated August 11, 2003.
(ii) [Reserved]
(3) For service information identified in
this AD, contact your local Sikorsky Field
Representative or Sikorsky’s Service
Engineering Group at Sikorsky Aircraft
Corporation, 124 Quarry Road, Trumbull, CT
PO 00000
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06611; telephone 1–800-Winged-S; email
wcs_cust_service_eng.gr-sik@lmco.com.
Operators may also log on to the Sikorsky
360 website at https://www.sikorsky360.com.
(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 May 4, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–11081 Filed 5–26–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–1171; Product
Identifier 2017–SW–124–AD; Amendment
39–21548; AD 2021–10–15]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters Deutschland GmbH
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
Airbus Helicopters Deutschland GmbH
Model MBB–BK 117 C–2 and Model
MBB–BK 117 D–2 helicopters. This AD
was prompted by a determination that a
life limit for the adapter forward (FWD)
of the outboard load system, repetitive
inspections of other components of that
system, and for certain helicopters, a
modification of the outboard load
system, are necessary to address the
unsafe condition. This AD requires a
modification of the outboard load
system for certain helicopters, repetitive
inspections of the outboard load system
and its components for any defect
(including cracking, damage, corrosion,
and incorrect installation) and
applicable corrective actions, and
implementation of a new life limit for
the FWD adapter, as specified in a
European Aviation Safety Agency (now
European Union Aviation Safety
Agency) (EASA) AD, which is
SUMMARY:
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Federal Register / Vol. 86, No. 101 / Thursday, May 27, 2021 / Rules and Regulations
incorporated by reference. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective July 1, 2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 1, 2021.
ADDRESSES: For material incorporated
by reference (IBR) in this AD, 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
material on the EASA website at https://
ad.easa.europa.eu. 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–2020–1171.
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–2020–
1171; 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:
Kathleen Arrigotti, Program Manager,
Large Aircraft Section, International
Validation Branch, Compliance &
Airworthiness Division, FAA, 2200
South 216th St., Des Moines, WA 98198;
telephone and fax 206–231–3218; email
kathleen.arrigotti@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
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The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2017–0177, dated September 14, 2017
(EASA AD 2017–0177) (also referred to
as the Mandatory Continuing
Airworthiness Information, or the
MCAI), to correct an unsafe condition
for all Airbus Helicopters Deutschland
GmbH Model MBB–BK 117 C–2
helicopters, except the Model C–2e
variant, and all Model MBB–BK 117
D–2 helicopters.
EASA’s Model MBB–BK 117 C–2e
variant helicopters are not a unique
model on the U.S. type certificate but
are considered a configuration of the
Model MBB–BK117 C–2. The U.S. type
certificate data sheet explains that the
FAA determined that the type design
changes involved did not rise to the
level that required an FAA amended
type certificate. However, the FAA does
recognize that helicopters with these
type design changes exist, therefore the
designation Model MBB–BK117 C–2(e)
is used, starting from Serial Number
9601. The Model MBB–BK117 C–2(e) is
a visual flight rules only configuration
of the Model MBB–BK117 C–2 utilizing
a Garmin 500H flight display system.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus Helicopters
Deutschland GmbH Model MBB–BK 117
C–2 and Model MBB–BK 117 D–2
helicopters, except the Model MBB–
BK117 C–2(e) configuration. The NPRM
published in the Federal Register on
March 11, 2021 (86 FR 13830). The
NPRM was prompted by a
determination that a life limit for the
adapter FWD of the outboard load
system, repetitive inspections of other
components of that system, and for
certain helicopters, a modification of the
outboard load system, are necessary to
address the unsafe condition. The
NPRM proposed to require a
modification of the outboard load
system for certain helicopters, repetitive
inspections of the outboard load system
and its components for any defect
(including cracking, damage, corrosion,
and incorrect installation) and
applicable corrective actions, and
implementation of a new life limit for
the FWD adapter, as specified in an
EASA AD.
The FAA is issuing this AD to address
detachment of an external load or
person from the helicopter hoist,
resulting in personal injury, or injury to
persons on the ground. See the MCAI
for additional background information.
28477
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.
Costs of Compliance Update
The NPRM had specified no definitive
data was available for the costs of the
modification and certain parts. The FAA
has received data on the costs of the
modification and parts and has updated
the costs of compliance accordingly.
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 and a change to
paragraph (i)(1) of this AD. 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 2017–0177 describes
procedures for modification of the
outboard load system for certain Model
MBB–BK 117 C–2 helicopters, repetitive
inspections of the outboard load system
and its components for any defect
(including cracking, damage, corrosion,
and incorrect installation) and
corrective actions, and implementation
of a new life limit for the FWD adapter
(i.e., repetitive replacements). The
corrective actions include replacement
of any defective component with a
serviceable part.
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.
Costs of Compliance
The FAA estimates that this AD
affects 175 helicopters of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
4 work-hours × $85 per hour = $340 ..........................................................................................
$2,276
$2,616
$457,800
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28478
Federal Register / Vol. 86, No. 101 / Thursday, May 27, 2021 / Rules and Regulations
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
2 work-hours × $85 per hour = $170 ......................................................................................................................
Up to $970 .....
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.
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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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:
■
2021–10–15 Airbus Helicopters
Deutschland GmbH: Amendment 39–
21548; Docket No. FAA–2020–1171;
Product Identifier 2017–SW–124–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective July 1, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Helicopters
Deutschland GmbH Model MBB–BK 117
C–2 and Model MBB–BK 117 D–2
helicopters, certificated in any category, all
manufacturer serial numbers, except the
Model MBB–BK117 C–2(e) configuration.
Note 1 to paragraph (c): Model MBB–
BK117 C–2 helicopters utilizing a Garmin
500H flight display system are designated by
EASA as Model MBB–BK117 C–2e variants
of the Model BK 117 C–2 helicopters, and by
the FAA as a Model MBB–BK117 C–2(e)
configuration.
(d) Subject
Joint Aircraft System Component (JASC)
Code 2500, Cabin Equipment/Furnishings.
(e) Reason
This AD was prompted by a determination
that a life limit for the adapter forward of the
outboard load system, repetitive inspections
of other components of that system, and for
certain helicopters, a modification of the
outboard load system, are necessary to
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Cost per
product
Up to $1,140.
address the unsafe condition. The FAA is
issuing this AD to address detachment of an
external load or person from the helicopter
hoist, which could result in personal injury,
or injury to persons on the ground.
(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 Aviation Safety
Agency (now European Union Aviation
Safety Agency) (EASA) AD 2017–0177, dated
September 14, 2017 (EASA AD 2017–0177).
(h) Exceptions to EASA AD 2017–0177
(1) Where EASA AD 2017–0177 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) The ‘‘Remarks’’ section of EASA AD
2017–0177 does not apply to this AD.
(3) Where the service information
referenced in EASA AD 2017–0177 specifies
contacting the applicable manufacturer of the
dedicated equipment for a definition of a
cycle and recalculation to hoist cycles, this
AD does not require contacting the
manufacturer for a definition of a cycle and
recalculation to hoist cycles.
(4) Where paragraph (3) of EASA AD 2017–
0177 specifies to do ‘‘applicable corrective
actions,’’ for this AD, if there are any
defective components, replace all defective
components with serviceable components in
accordance with FAA-approved procedures.
For the purposes of this AD, a defect may be
indicated by cracking, damage, corrosion, or
incorrect installation.
(5) Although the service information
referenced in EASA AD 2017–0177 specifies
to discard certain parts, this AD requires
removing those parts from service instead.
(6) Where the service information
referenced in EASA AD 2017–0177 refers to
flight hours (FH), this AD requires using
hours time-in-service.
(7) Paragraph (9) of EASA AD 2017–0177
does not apply to this AD.
(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
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Federal Register / Vol. 86, No. 101 / Thursday, May 27, 2021 / Rules and Regulations
to the manager of the International Validation
Branch, send it to the attention of the person
identified in paragraph (j) 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.
DEPARTMENT OF TRANSPORTATION
(j) Related Information
Airworthiness Directives; De Havilland
Aircraft of Canada Limited (Type
Certificate Previously Held by
Bombardier, Inc.) Airplanes
For more information about this AD,
contact Kathleen Arrigotti, Program Manager,
Large Aircraft Section, International
Validation Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; phone and fax:
206–231–3218; email: kathleen.arrigotti@
faa.gov.
(k) 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 Aviation Safety Agency
(EASA) AD 2017–0177, dated September 14,
2017.
(ii) [Reserved]
(3) For EASA AD 2017–0177, 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) 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–2020–1171.
(5) 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 fedreg.legal@
nara.gov, or go to https://www.archives.gov/
federal-register/cfr/ibr-locations.html.
Issued on May 3, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
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[FR Doc. 2021–11080 Filed 5–26–21; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0018; Project
Identifier MCAI–2020–01214–T; Amendment
39–21546; AD 2021–10–13]
RIN 2120–AA64
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
28479
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:
The FAA is superseding
Airworthiness Directive (AD) 2015–17–
08, which applied to certain
Bombardier, Inc. Model DHC–8–400
series airplanes. AD 2015–17–08
required installing new cable assemblies
with a pull-down resistor. This AD
requires modifications to the nose wheel
steering (NWS) system. This AD was
prompted by a report indicating that
several failure modes of the NWS
system may cause the loss of feedback
from both rotary variable differential
transformers to the steering control unit.
The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective July 1, 2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 1, 2021.
ADDRESSES: For service information
identified in this final rule, contact De
Havilland Aircraft of Canada Limited,
Q-Series Technical Help Desk, 123
Garratt Boulevard, Toronto, Ontario
M3K 1Y5, Canada; telephone 416–375–
4000; fax 416–375–4539; email thd@
dehavilland.com; internet https://
dehavilland.com. You may view this
referenced service information 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 on the internet at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0018.
Discussion
Examining the AD Docket
Comments
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0018; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
The FAA gave the public the
opportunity to participate in developing
this final rule. The FAA has considered
the comment received. The Air Line
Pilots Association, International (ALPA)
indicated its support for the NPRM.
SUMMARY:
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Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued TCCA AD CF–
2020–28, dated August 14, 2020 (also
referred to as the Mandatory Continuing
Airworthiness Information, or the
MCAI), to correct an unsafe condition
for certain De Havilland Aircraft of
Canada Limited Model DHC–8–401 and
–402 airplanes. You may examine the
MCAI in the AD docket on the internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0018.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2015–17–08,
Amendment 39–18241 (80 FR 51459,
August 25, 2015) (AD 2015–17–08). AD
2015–17–08 applied to certain
Bombardier, Inc. Model DHC–8–400
series airplanes. The NPRM published
in the Federal Register on February 24,
2021 (86 FR 11175). The NPRM was
prompted by a report indicating that
several failure modes of the NWS
system may cause the loss of feedback
from both rotary variable differential
transformers to the steering control unit.
The NPRM proposed to require
modifications to the NWS system. The
FAA is issuing this AD to address
failure modes of the NWS system,
which could lead to NWS runaway, loss
of directional control of the airplane,
and possible consequent runway
excursion. See the MCAI for additional
background information.
E:\FR\FM\27MYR1.SGM
27MYR1
]]>Agencies
[Federal Register Volume 86, Number 101 (Thursday, May 27, 2021)]
[Rules and Regulations]
[Pages 28476-28479]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-11080]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-1171; Product Identifier 2017-SW-124-AD; Amendment
39-21548; AD 2021-10-15]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters Deutschland GmbH
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Airbus Helicopters Deutschland GmbH Model MBB-BK 117 C-2 and Model MBB-
BK 117 D-2 helicopters. This AD was prompted by a determination that a
life limit for the adapter forward (FWD) of the outboard load system,
repetitive inspections of other components of that system, and for
certain helicopters, a modification of the outboard load system, are
necessary to address the unsafe condition. This AD requires a
modification of the outboard load system for certain helicopters,
repetitive inspections of the outboard load system and its components
for any defect (including cracking, damage, corrosion, and incorrect
installation) and applicable corrective actions, and implementation of
a new life limit for the FWD adapter, as specified in a European
Aviation Safety Agency (now European Union Aviation Safety Agency)
(EASA) AD, which is
[[Page 28477]]
incorporated by reference. The FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective July 1, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 1,
2021.
ADDRESSES: For 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. 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-2020-1171.
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-2020-
1171; 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: Kathleen Arrigotti, Program Manager,
Large Aircraft Section, International Validation Branch, Compliance &
Airworthiness Division, FAA, 2200 South 216th St., Des Moines, WA
98198; telephone and fax 206-231-3218; email
[email protected].
SUPPLEMENTARY INFORMATION:
Background
The EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2017-0177, dated September 14, 2017
(EASA AD 2017-0177) (also referred to as the Mandatory Continuing
Airworthiness Information, or the MCAI), to correct an unsafe condition
for all Airbus Helicopters Deutschland GmbH Model MBB-BK 117 C-2
helicopters, except the Model C-2e variant, and all Model MBB-BK 117 D-
2 helicopters.
EASA's Model MBB-BK 117 C-2e variant helicopters are not a unique
model on the U.S. type certificate but are considered a configuration
of the Model MBB-BK117 C-2. The U.S. type certificate data sheet
explains that the FAA determined that the type design changes involved
did not rise to the level that required an FAA amended type
certificate. However, the FAA does recognize that helicopters with
these type design changes exist, therefore the designation Model MBB-
BK117 C-2(e) is used, starting from Serial Number 9601. The Model MBB-
BK117 C-2(e) is a visual flight rules only configuration of the Model
MBB-BK117 C-2 utilizing a Garmin 500H flight display system.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to all Airbus Helicopters
Deutschland GmbH Model MBB-BK 117 C-2 and Model MBB-BK 117 D-2
helicopters, except the Model MBB-BK117 C-2(e) configuration. The NPRM
published in the Federal Register on March 11, 2021 (86 FR 13830). The
NPRM was prompted by a determination that a life limit for the adapter
FWD of the outboard load system, repetitive inspections of other
components of that system, and for certain helicopters, a modification
of the outboard load system, are necessary to address the unsafe
condition. The NPRM proposed to require a modification of the outboard
load system for certain helicopters, repetitive inspections of the
outboard load system and its components for any defect (including
cracking, damage, corrosion, and incorrect installation) and applicable
corrective actions, and implementation of a new life limit for the FWD
adapter, as specified in an EASA AD.
The FAA is issuing this AD to address detachment of an external
load or person from the helicopter hoist, resulting in personal injury,
or injury to persons on the ground. 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.
Costs of Compliance Update
The NPRM had specified no definitive data was available for the
costs of the modification and certain parts. The FAA has received data
on the costs of the modification and parts and has updated the costs of
compliance accordingly.
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 and a change to paragraph (i)(1) of
this AD. 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 2017-0177 describes procedures for modification of the
outboard load system for certain Model MBB-BK 117 C-2 helicopters,
repetitive inspections of the outboard load system and its components
for any defect (including cracking, damage, corrosion, and incorrect
installation) and corrective actions, and implementation of a new life
limit for the FWD adapter (i.e., repetitive replacements). The
corrective actions include replacement of any defective component with
a serviceable part.
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.
Costs of Compliance
The FAA estimates that this AD affects 175 helicopters of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
4 work-hours x $85 per hour = $340........................... $2,276 $2,616 $457,800
----------------------------------------------------------------------------------------------------------------
[[Page 28478]]
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
------------------------------------------------------------------------
2 work-hours x $85 per hour = Up to $970......... Up to $1,140.
$170.
------------------------------------------------------------------------
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.
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 adding the following new airworthiness
directive:
2021-10-15 Airbus Helicopters Deutschland GmbH: Amendment 39-21548;
Docket No. FAA-2020-1171; Product Identifier 2017-SW-124-AD.
(a) Effective Date
This airworthiness directive (AD) is effective July 1, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Helicopters Deutschland GmbH Model
MBB-BK 117 C-2 and Model MBB-BK 117 D-2 helicopters, certificated in
any category, all manufacturer serial numbers, except the Model MBB-
BK117 C-2(e) configuration.
Note 1 to paragraph (c): Model MBB-BK117 C-2 helicopters
utilizing a Garmin 500H flight display system are designated by EASA
as Model MBB-BK117 C-2e variants of the Model BK 117 C-2
helicopters, and by the FAA as a Model MBB-BK117 C-2(e)
configuration.
(d) Subject
Joint Aircraft System Component (JASC) Code 2500, Cabin
Equipment/Furnishings.
(e) Reason
This AD was prompted by a determination that a life limit for
the adapter forward of the outboard load system, repetitive
inspections of other components of that system, and for certain
helicopters, a modification of the outboard load system, are
necessary to address the unsafe condition. The FAA is issuing this
AD to address detachment of an external load or person from the
helicopter hoist, which could result in personal injury, or injury
to persons on the ground.
(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 Aviation Safety Agency (now European Union
Aviation Safety Agency) (EASA) AD 2017-0177, dated September 14,
2017 (EASA AD 2017-0177).
(h) Exceptions to EASA AD 2017-0177
(1) Where EASA AD 2017-0177 refers to its effective date, this
AD requires using the effective date of this AD.
(2) The ``Remarks'' section of EASA AD 2017-0177 does not apply
to this AD.
(3) Where the service information referenced in EASA AD 2017-
0177 specifies contacting the applicable manufacturer of the
dedicated equipment for a definition of a cycle and recalculation to
hoist cycles, this AD does not require contacting the manufacturer
for a definition of a cycle and recalculation to hoist cycles.
(4) Where paragraph (3) of EASA AD 2017-0177 specifies to do
``applicable corrective actions,'' for this AD, if there are any
defective components, replace all defective components with
serviceable components in accordance with FAA-approved procedures.
For the purposes of this AD, a defect may be indicated by cracking,
damage, corrosion, or incorrect installation.
(5) Although the service information referenced in EASA AD 2017-
0177 specifies to discard certain parts, this AD requires removing
those parts from service instead.
(6) Where the service information referenced in EASA AD 2017-
0177 refers to flight hours (FH), this AD requires using hours time-
in-service.
(7) Paragraph (9) of EASA AD 2017-0177 does not apply to this
AD.
(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
[[Page 28479]]
to the manager of the International Validation Branch, send it to
the attention of the person identified in paragraph (j) 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.
(j) Related Information
For more information about this AD, contact Kathleen Arrigotti,
Program Manager, Large Aircraft Section, International Validation
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; phone and
fax: 206-231-3218; email: [email protected].
(k) 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 Aviation Safety Agency (EASA) AD 2017-0177, dated
September 14, 2017.
(ii) [Reserved]
(3) For EASA AD 2017-0177, 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) 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-
2020-1171.
(5) 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 May 3, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-11080 Filed 5-26-21; 8:45 am]
BILLING CODE 4910-13-P
