Airworthiness Directives; Hélicoptères Guimbal Helicopters, 70000-70003 [2021-26543]
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Federal Register / Vol. 86, No. 234 / Thursday, December 9, 2021 / Rules and Regulations
into the aircraft records showing compliance
with this AD in accordance with 14 CFR
43.9(a)(1) through (4) and 14 CFR
91.417(a)(2)(v). The record must be
maintained as required by 14 CFR 91.417,
121.380, or 135.439.
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:
■
2021–24–04 Bell Textron Canada Limited
(Type Certificate Previously Held by Bell
Helicopter Textron Canada Limited):
Amendment 39–21825; Docket No.
FAA–2021–0783; Project Identifier
2019–SW–009–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective January 13, 2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bell Helicopter Textron
Canada Limited (type certificate previously
held by Bell Helicopter Textron Canada
Limited) Model 505 helicopters having serial
number 65011 and subsequent, certificated in
any category.
(d) Subject
Joint Aircraft Service Component (JASC)
Code: 7300, Engine fuel and control.
(e) Unsafe Condition
This AD was prompted by the
determination that reducing the pressure
altitude limitations for certain fuel types is
necessary. The FAA is issuing this AD to
address unsatisfactory flight performance of
the engine above pressure altitude limitations
for Jet B and JP–4 fuels. The unsafe
condition, if not addressed, could result in
low fuel pressure, engine flame-out, or
engine power interruption.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
Within 30 calendar days after the effective
date of this AD, revise the Limitations
Section of the existing Rotorcraft Flight
Manual (RFM) for your helicopter by
replacing Figure 1–6. with Figure 1–6. Fuel
Operating Envelope (Sheet 1 of 1) of Bell 505
Rotorcraft Flight Manual BHT–505–FM–1,
Revision 3, dated July 25, 2018 (BHT–505–
FM–1 Revision 3). Using a different
document with information identical to that
in Figure 1–6. Fuel Operating Envelope
(Sheet 1 of 1) of BHT–505–FM–1 Revision 3
is acceptable for compliance with the
requirements of this AD. The action required
by this paragraph may be performed by the
owner/operator (pilot) holding at least a
private pilot certificate and must be entered
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(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 Rao Edupuganti, Aerospace Engineer,
Dynamic Systems Section, Technical
Innovation Policy Branch, Policy &
Innovation Division, FAA, 10101 Hillwood
Pkwy., Fort Worth, TX 76177; telephone
(817) 222–5110; email rao.edupuganti@
faa.gov.
(2) The subject of this AD is addressed in
Transport Canada AD CF–2019–08, dated
March 5, 2019. You may view the Transport
Canada AD at https://www.regulations.gov in
Docket No. FAA–2021–0783.
(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) Figure 1–6. Fuel Operating Envelope
(Sheet 1 of 1) of Bell 505 Rotorcraft Flight
Manual BHT–505–FM–1, Revision 3, dated
July 25, 2018.
(ii) [Reserved]
(3) For service information identified in
this AD, contact Bell Textron Canada
Limited, 12,800 Rue de l’Avenir, Mirabel,
Quebec J7J 1R4, Canada; telephone 1–450–
437–2862 or 1–800–363–8023; fax 1–450–
433–0272; email productsupport@
bellflight.com; or at https://
www.bellflight.com/support/contact-support.
(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:
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https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on November 12, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–26605 Filed 12–8–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0688; Project
Identifier 2019–SW–025–AD; Amendment
39–21781; AD 2021–22–08]
RIN 2120–AA64
Airworthiness Directives; He´licopte`res
Guimbal Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for
He´licopte`res Guimbal (HG) Model Cabri
G2 helicopters. This AD was prompted
by the determination that certain parts
need life limits and certification
maintenance requirement (CMR) tasks.
This AD requires establishing life limits
and CMR tasks for various parts and
removing any parts from service that
have reached or exceeded their life
limits. Depending on the results of the
CMR tasks, this AD requires corrective
action. The FAA is issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective January 13,
2022.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of January 13, 2022.
ADDRESSES: For service information
identified in this final rule, contact
He´licopte`res Guimbal, 1070, rue du
Lieutenant Parayre, Ae´rodrome d’Aixen-Provence, 13290 Les Milles, France;
telephone 33–04–42–39–10–88; email
support@guimbal.com; or at https://
www.guimbal.com. You may view the
referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177. For information on the
availability of this material at the FAA,
call (817) 222–5110. It is also available
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0688.
SUMMARY:
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Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0688; 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 European Aviation Safety
Agency (now European Union Aviation
Safety Agency) (EASA) AD, 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:
Andrea Jimenez, Aerospace Engineer,
COS Program Management Section,
Operational Safety Branch, Compliance
& Airworthiness Division, FAA, 1600
Stewart Ave., Suite 410, Westbury, NY
11590; telephone (516) 228–7330; email
andrea.jimenez@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to He´licopte`res Guimbal (HG)
Model Cabri G2 helicopters. The NPRM
published in the Federal Register on
August 23, 2021 (86 FR 47038). In the
NPRM, the FAA proposed to require
before further flight, removing from
service certain part-numbered cooling
fan front flanges and engine pulley ball
bearings that have accumulated or
exceeded their life limit. The NPRM
also proposed to require establishing
recurring CMR tasks for certain partnumbered cooling fan front flanges.
Depending on the results of the CMR
tasks, the NPRM proposed to require
corrective action. Additionally, the
NPRM proposed to require painting
certain part-numbered tail booms with
glossy white paint.
The NPRM was prompted by a series
of EASA ADs beginning with EASA AD
2016–0032, dated February 24, 2016
(EASA AD 2016–0032), issued by
EASA, which is the Technical Agent for
the Member States of the European
Union, to correct an unsafe condition
for HG Model Cabri G2 helicopters.
EASA AD 2016–0032 states HG has
revised the airworthiness limitations
and maintenance tasks specified in the
existing maintenance manual. EASA
further advised the revisions include
new and more restrictive applicable life
limits and compliance times for
applicable tasks. Accordingly, EASA
2016–0032 required replacing each
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affected part before exceeding its life
limit, accomplishing all applicable
maintenance tasks within the defined
intervals as described in revised
maintenance manual and if
discrepancies were found
accomplishing the corrective actions in
accordance with the applicable
maintenance instructions or contacting
HG. EASA AD 2016–0032 also required
revising the existing Aircraft
Maintenance Program (AMP) for your
helicopter by incorporating the actions
specified in the revised maintenance.
After EASA issued EASA AD 2016–
0032, HG again revised the
airworthiness limitations and
maintenance tasks.
Accordingly, EASA superseded EASA
AD 2016–0032 with EASA AD 2019–
0025, dated February 4, 2019 (EASA AD
2019–0025). EASA advises new and
more restrictive life limits have been
established for cooling fan part number
(P/N) G52–00–001, and P/N G52–00–
002, which have been identified as
mandatory for continued airworthiness
in He´licopte`res Guimbal Cabri G2
Maintenance Manual (MM) No. J70–002
Issue 06, dated December 6, 2018,
Section C, Airworthiness Limitations
(the ALS). In addition to the new life
limits, EASA advises of new and more
restrictive inspection intervals
identified in the ALS for cooling fan P/
N G52–00–001 with a certain mounted
cooling fan front flange P/N G52–02–
200, or P/N G52–02–201. EASA further
advises that the ALS revised the tail
structure paint to include certain partnumbered tail booms and an additional
figure. This condition, if not addressed,
could result in parts remaining in
service beyond their fatigue life and
failure of a part, which could result in
loss of control of the helicopter.
Accordingly, EASA AD 2019–0025
retains the requirements of EASA AD
2016–0032 and requires replacing each
affected part before exceeding its life
limit, accomplishing all applicable
maintenance tasks within the defined
intervals as described in the ALS, and
if discrepancies are found
accomplishing the corrective actions in
accordance with the applicable
maintenance instructions or contacting
HG. EASA AD 2019–0025 also requires
revising the tail structure paint scheme
to include certain part-numbered tail
booms and an additional figure. EASA
AD 2019–0025 requires revising the
existing AMP for your helicopter by
incorporating the actions specified in
the ALS.
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Comments
The FAA received no comments on
the NPRM or on the determination of
the costs.
Conclusion
These helicopters have been approved
by EASA and are approved for operation
in the United States. Pursuant to the
FAA’s bilateral agreement with the
European Union, EASA has notified the
FAA about the unsafe condition
described in its AD. The FAA reviewed
the relevant data and determined that
air safety requires adopting this AD as
proposed. Accordingly, the FAA is
issuing this AD to address the unsafe
condition on these helicopters. Except
for minor editorial changes, this AD is
adopted as proposed in the NPRM.
Changes include clarifying the name of
and the specific portions of Guimbal
France He´licopte`res Guimbal Cabri G2
Maintenance Manual and Instructions
for Continued Airworthiness, J70–002—
Issue 06, dated December 6, 2018 (MM
J70–002 Issue 06) that are required to
accomplish this final rule. MM J70–002
Issue 06 also refers to a flashlight as a
torchlight; accordingly, changes have
been made in this final rule to clarify
that where MM J70–002 Issue 06
specifies to use a torchlight, to use a
flashlight instead. This final rule also
removes the requirements of
accomplishing sub section 52–A–10
Cooling Fan Inspection, paragraph d), of
MM J70–002 Issue 06 because it is
unnecessary, this final rule already
provides requirements pertaining to
what to do if there is a crack.
Related Service Information Under 1
CFR Part 51
The FAA reviewed page C–6 of
Section C, Airworthiness Limitations,
and page E–5–53 of Section E,
Maintenance Instructions, of MM J70–
002 Issue 06. This service information
specifies airworthiness life limits,
inspection intervals, and CMR
requirements for parts installed on Cabri
G2 helicopters. MM J70–002 Issue 06
also establishes life limits for certain
part-numbered cooling fan front flanges,
and engine pulley ball bearings and
CMR requirements for certain cooling
fan front flanges.
This service information 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 EASA
2019–0025
EASA AD 2019–0025 requires
contacting He´licopte`res Guimbal for
corrective actions when a discrepancy is
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found, whereas this AD requires
removing the part from service. EASA
AD 2019–0025 requires accomplishing
the actions specified in the ALS,
whereas this AD requires establishing a
life limit for certain part-numbered
cooling fan front flanges and certain
part-numbered engine pulley ball
bearings and removing any part from
service accordingly instead. EASA AD
2019–0025 requires revising the AMP
with the actions specified in the ALS,
whereas this AD does not.
Costs of Compliance
The FAA estimates that this AD
affects 32 helicopters of U.S. Registry.
Labor rates are estimated at $85 per
work-hour. Based on these numbers, the
FAA estimates the following costs to
comply with this AD.
Replacing a cooling fan front flange
takes about 16 work-hours and parts
cost about $4,500 for an estimated cost
of $5,860 per helicopter and $187,520
for the U.S. fleet, per replacement cycle.
Replacing an engine pulley ball
bearing takes about 12 work-hours and
parts cost about $250 for an estimated
cost of $1,270 per helicopter and
$40,640 for the U.S. fleet, per
replacement cycle.
The FAA has no way of determining
the estimated costs to do allowable
repairs based on the results of the CMR
tasks. If required, replacing a cracked
cooling fan front flange takes about 16
work-hours and parts cost about $4,500
for an estimated cost of $5,860.
The FAA has included all known
costs in its cost estimate. According to
the manufacturer, however, some of the
costs of this AD may be covered under
warranty, thereby reducing the cost
impact on affected operators.
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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
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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
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:
■
2021–22–08 He´licopte`res Guimbal:
Amendment 39–21781; Docket No.
FAA–2021–0688; Project Identifier
2019–SW–025–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective January 13, 2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to He´licopte`res Guimbal
(HG) Model Cabri G2 helicopters, certificated
in any category.
(d) Subject
Joint Aircraft Service Component (JASC)
Code: 7100, Powerplant System.
(e) Unsafe Condition
This AD was prompted by a notification of
certain parts remaining in service beyond
their fatigue life or beyond maintenance
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intervals required by the certification
maintenance requirements (CMRs) of the
Instructions for Continued Airworthiness.
The FAA is issuing this AD to prevent failure
of a part, which could result in loss of control
of the helicopter.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Before further flight after the effective
date of this AD, remove from service any part
that has reached or exceeded its life limit, as
specified in paragraphs (g)(1)(i) through (iii)
of this AD, and thereafter remove from
service any part on or before each part
reaches its life limit:
(i) The life limit for cooling fan front flange
part number (P/N) G52–02–200 mounted on
pulley (12 screws) P/N G52–10–100 or G52–
10–101; and cooling fan front flange P/N
G52–02–201 mounted or having been
mounted on pulley (12 screws) P/N G52–10–
100 or G52–10–101, installed on cooling fan
P/N G52–00–001 or G52–00–002; is 2,200
total hours time-in-service (TIS).
(ii) The life limit for cooling fan front
flange P/N G52–02–201 mounted on pulley
(24 screws) P/N G52–10–102 and having
never been mounted on pulley (12 screws)
P/N G52–10–100 or G52–10–101, installed on
cooling fan P/N G52–00–001 or G52–00–002,
is 4,400 total hours TIS.
(iii) The life limit for engine pulley ball
bearing P/N HG61–0790 and HG61–1944,
installed on engine pulley assembly P/N
G51–14–1XX, is 2,200 total hours TIS.
(2) Perform the following CMR tasks as
follows:
(i) Cooling fan front flange P/N G52–02–
200 mounted on pulley (12 screws) P/N G52–
10–100 or G52–10–101; and cooling fan front
flange P/N G52–02–201 mounted or having
been mounted on pulley (12 screws) P/N
G52–10–100 or G52–10–101, installed on
cooling fan P/N G52–00–001, and with 500
or more total hours TIS since new as of the
effective date of this AD: Within 5 hours TIS
after the effective date of this AD and
thereafter at intervals not to exceed 50 hours
TIS, or 70 engine start-stop cycles, whichever
occurs first, inspect the cooling fan front
flange for a crack in accordance with Section
E, Maintenance Instructions, sub section 52–
A–10 Cooling Fan Inspection, paragraph c),
on page E–5–53, of Guimbal France
He´licopte`res Guimbal Cabri G2 Maintenance
Manual (MM) and Instructions for Continued
Airworthiness, J70–002—Issue 06, dated
December 6, 2018 (MM J70–002 Issue 06),
except where MM J70–002 Issue 06 specifies
to use a torchlight, use a flashlight. If any
crack is found, before further flight, remove
the cooling fan front flange from service.
(ii) Cooling fan front flange P/N G52–02–
200 mounted on pulley (12 screws) P/N G52–
10–100 or G52–10–101; and cooling fan front
flange P/N G52–02–201 mounted or having
been mounted on pulley (12 screws) P/N
G52–10–100 or G52–10–101, installed on
cooling fan P/N G52–00–001, and with less
than 500 total hours TIS since new as of the
effective date of this AD: Before
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accumulating 500 total hours TIS since new
and thereafter at intervals not to exceed 50
hours TIS, or 70 engine start-stop cycles,
whichever occurs first, inspect the cooling
fan front flange for a crack in accordance
with Section E, Maintenance Instructions,
sub section 52–A–10 Cooling Fan Inspection,
paragraph c), on page E–5–53, of MM J70–
002 Issue 06, except where MM J70–002
Issue 06 specifies to use a torchlight, use a
flashlight. If any crack is found, before
further flight, remove the cooling fan front
flange from service.
(iii) Cooling fan front flange P/N G52–02–
201 mounted on pulley (24 screws) P/N G52–
10–102 and having never been mounted on
pulley (12 screws) P/N G52–10–100 or G52–
10–101, installed on cooling fan P/N G52–
00–002: Before accumulating 500 total hours
TIS since new and thereafter at intervals not
to exceed 100 hours TIS, inspect the cooling
fan front flange for a crack in accordance
with Section E, Maintenance Instructions,
sub section 52–A–10 Cooling Fan Inspection,
paragraph c), on page E–5–53, of MM J70–
002 Issue 06, except where MM J70–002
Issue 06 specifies to use a torchlight, use a
flashlight. If any crack is found, before
further flight, remove the cooling fan front
flange from service.
(iv) For helicopters with tail boom P/N
G65–00–101, G65–00–102 or G65–00–103
and subsequent installed: Before further
flight after the effective date of this AD, paint
or verify the tail boom upper surface in
accordance with Section C, Airworthiness
Limitations, sub section C–23 Tail Structure
Paint, on page C–6, of MM J70–002 Issue 06,
as applicable to your helicopter.
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(h) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraphs (g)(2)(i)
through (iii) of this AD, if those actions were
performed before the effective date of this AD
using Section E, Maintenance Instructions,
sub section 52–A–10 Cooling Fan Inspection,
paragraphs (c) and (d), of Guimbal France
He´licopte`res Guimbal Cabri G2 MM and
Instructions for Continued Airworthiness,
J70–002 Issue—05.1, dated October 30, 2015.
(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.
COS Program Management Section,
Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 1600 Stewart
Ave., Suite 410, Westbury, NY 11590;
telephone (516) 228–7330; email
andrea.jimenez@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the contact information specified
in paragraphs (k)(3) and (4) of this AD.
(3) The subject of this AD is addressed in
European Aviation Safety Agency (now
European Union Aviation Safety Agency
(EASA) AD 2019–0025, dated February 4,
2019. You may view the EASA AD on the
internet at https://www.regulations.gov in
Docket No. FAA–2021–0688.
(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) Page C–6 of Section C, Airworthiness
Limitations, of Guimbal France He´licopte`res
Guimbal Cabri G2 Maintenance Manual and
Instructions for Continued Airworthiness,
J70–002—Issue 06, dated December 6, 2018.
(ii) Page E–5–53 of Section E, Maintenance
Instructions, of Guimbal France He´licopte`res
Guimbal Cabri G2 Maintenance Manual and
Instructions for Continued Airworthiness,
J70–002—Issue 06, dated December 6, 2018.
(3) For service information identified in
this AD, contact He´licopte`res Guimbal, 1070,
rue du Lieutenant Parayre, Ae´rodrome d’Aixen-Provence, 13290 Les Milles, France;
telephone 33–04–42–39–10–88; email
support@guimbal.com; or at https://
www.guimbal.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: fr.inspection@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on October 14, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–26543 Filed 12–8–21; 8:45 am]
BILLING CODE 4910–13–P
(j) Related Information
(1) For more information about this AD,
contact Andrea Jimenez, Aerospace Engineer,
VerDate Sep<11>2014
16:33 Dec 08, 2021
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70003
DEPARTMENT OF COMMERCE
Bureau of Industry and Security
15 CFR Part 705
[Docket No. 211115–0229]
RIN 0694–AH55
Removal of Certain General Approved
Exclusions (GAEs) Under the Section
232 Steel and Aluminum Tariff
Exclusions Process
Bureau of Industry and
Security, U.S. Department of Commerce.
AGENCY:
ACTION:
Interim final rule.
On December 14, 2020, the
Department of Commerce published an
interim final rule (the ‘‘December 14
rule’’) that revised aspects of the process
for requesting exclusions from the
duties and quantitative limitations on
imports of aluminum and steel
discussed in three previous Department
of Commerce (‘‘Commerce’’) interim
final rules implementing the exclusion
process authorized by the President
under Section 232 of the Trade
Expansion Act of 1962, as amended, as
well as a May 26, 2020 notice of inquiry.
The December 14 rule included adding
123 General Approved Exclusions
(GAEs) to the regulations. Subsequently,
based on Commerce’s review of the
public comments received in response
to the December 14 rule and additional
analysis conducted by Commerce on the
Section 232 exclusion request
submissions, Commerce determined
that a subset of the GAEs added in the
December 14 rule no longer meets the
criteria for inclusion as a GAE and
should therefore be removed. Commerce
is removing these GAEs in this interim
final rule to ensure only those GAEs that
meet the stated criteria from the
December 14 rule will continue to be
included as eligible GAEs. This interim
final rule removes thirty of the GAEs
that were added to the regulations in the
December 14 rule, consisting of twentysix GAEs for steel and four GAEs for
aluminum. As a conforming change to a
recent U.S. International Trade
Commission (ITC) decision, this rule
also removes one additional steel GAE.
Lastly, this interim final rule adds a
note to both GAE supplements to
address future changes to the
Harmonized Tariff Schedule of the
United States (HTSUS).
SUMMARY:
E:\FR\FM\09DER1.SGM
09DER1
]]>Agencies
[Federal Register Volume 86, Number 234 (Thursday, December 9, 2021)]
[Rules and Regulations]
[Pages 70000-70003]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-26543]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0688; Project Identifier 2019-SW-025-AD; Amendment
39-21781; AD 2021-22-08]
RIN 2120-AA64
Airworthiness Directives; H[eacute]licopt[egrave]res Guimbal
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
H[eacute]licopt[egrave]res Guimbal (HG) Model Cabri G2 helicopters.
This AD was prompted by the determination that certain parts need life
limits and certification maintenance requirement (CMR) tasks. This AD
requires establishing life limits and CMR tasks for various parts and
removing any parts from service that have reached or exceeded their
life limits. Depending on the results of the CMR tasks, this AD
requires corrective action. The FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective January 13, 2022.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of January 13,
2022.
ADDRESSES: For service information identified in this final rule,
contact H[eacute]licopt[egrave]res Guimbal, 1070, rue du Lieutenant
Parayre, A[eacute]rodrome d'Aix-en-Provence, 13290 Les Milles, France;
telephone 33-04-42-39-10-88; email [email protected]; or at https://www.guimbal.com. You may view the referenced service information at the
FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood
Pkwy., Room 6N-321, Fort Worth, TX 76177. For information on the
availability of this material at the FAA, call (817) 222-5110. It is
also available at https://www.regulations.gov by searching for and
locating Docket No. FAA-2021-0688.
[[Page 70001]]
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0688; 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
European Aviation Safety Agency (now European Union Aviation Safety
Agency) (EASA) AD, 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: Andrea Jimenez, Aerospace Engineer,
COS Program Management Section, Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY
11590; telephone (516) 228-7330; email [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to
H[eacute]licopt[egrave]res Guimbal (HG) Model Cabri G2 helicopters. The
NPRM published in the Federal Register on August 23, 2021 (86 FR
47038). In the NPRM, the FAA proposed to require before further flight,
removing from service certain part-numbered cooling fan front flanges
and engine pulley ball bearings that have accumulated or exceeded their
life limit. The NPRM also proposed to require establishing recurring
CMR tasks for certain part-numbered cooling fan front flanges.
Depending on the results of the CMR tasks, the NPRM proposed to require
corrective action. Additionally, the NPRM proposed to require painting
certain part-numbered tail booms with glossy white paint.
The NPRM was prompted by a series of EASA ADs beginning with EASA
AD 2016-0032, dated February 24, 2016 (EASA AD 2016-0032), issued by
EASA, which is the Technical Agent for the Member States of the
European Union, to correct an unsafe condition for HG Model Cabri G2
helicopters. EASA AD 2016-0032 states HG has revised the airworthiness
limitations and maintenance tasks specified in the existing maintenance
manual. EASA further advised the revisions include new and more
restrictive applicable life limits and compliance times for applicable
tasks. Accordingly, EASA 2016-0032 required replacing each affected
part before exceeding its life limit, accomplishing all applicable
maintenance tasks within the defined intervals as described in revised
maintenance manual and if discrepancies were found accomplishing the
corrective actions in accordance with the applicable maintenance
instructions or contacting HG. EASA AD 2016-0032 also required revising
the existing Aircraft Maintenance Program (AMP) for your helicopter by
incorporating the actions specified in the revised maintenance. After
EASA issued EASA AD 2016-0032, HG again revised the airworthiness
limitations and maintenance tasks.
Accordingly, EASA superseded EASA AD 2016-0032 with EASA AD 2019-
0025, dated February 4, 2019 (EASA AD 2019-0025). EASA advises new and
more restrictive life limits have been established for cooling fan part
number (P/N) G52-00-001, and P/N G52-00-002, which have been identified
as mandatory for continued airworthiness in H[eacute]licopt[egrave]res
Guimbal Cabri G2 Maintenance Manual (MM) No. J70-002 Issue 06, dated
December 6, 2018, Section C, Airworthiness Limitations (the ALS). In
addition to the new life limits, EASA advises of new and more
restrictive inspection intervals identified in the ALS for cooling fan
P/N G52-00-001 with a certain mounted cooling fan front flange P/N G52-
02-200, or P/N G52-02-201. EASA further advises that the ALS revised
the tail structure paint to include certain part-numbered tail booms
and an additional figure. This condition, if not addressed, could
result in parts remaining in service beyond their fatigue life and
failure of a part, which could result in loss of control of the
helicopter.
Accordingly, EASA AD 2019-0025 retains the requirements of EASA AD
2016-0032 and requires replacing each affected part before exceeding
its life limit, accomplishing all applicable maintenance tasks within
the defined intervals as described in the ALS, and if discrepancies are
found accomplishing the corrective actions in accordance with the
applicable maintenance instructions or contacting HG. EASA AD 2019-0025
also requires revising the tail structure paint scheme to include
certain part-numbered tail booms and an additional figure. EASA AD
2019-0025 requires revising the existing AMP for your helicopter by
incorporating the actions specified in the ALS.
Comments
The FAA received no comments on the NPRM or on the determination of
the costs.
Conclusion
These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Union, EASA has notified the FAA about the
unsafe condition described in its AD. The FAA reviewed the relevant
data and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these helicopters. Except for minor editorial changes,
this AD is adopted as proposed in the NPRM. Changes include clarifying
the name of and the specific portions of Guimbal France
H[eacute]licopt[egrave]res Guimbal Cabri G2 Maintenance Manual and
Instructions for Continued Airworthiness, J70-002--Issue 06, dated
December 6, 2018 (MM J70-002 Issue 06) that are required to accomplish
this final rule. MM J70-002 Issue 06 also refers to a flashlight as a
torchlight; accordingly, changes have been made in this final rule to
clarify that where MM J70-002 Issue 06 specifies to use a torchlight,
to use a flashlight instead. This final rule also removes the
requirements of accomplishing sub section 52-A-10 Cooling Fan
Inspection, paragraph d), of MM J70-002 Issue 06 because it is
unnecessary, this final rule already provides requirements pertaining
to what to do if there is a crack.
Related Service Information Under 1 CFR Part 51
The FAA reviewed page C-6 of Section C, Airworthiness Limitations,
and page E-5-53 of Section E, Maintenance Instructions, of MM J70-002
Issue 06. This service information specifies airworthiness life limits,
inspection intervals, and CMR requirements for parts installed on Cabri
G2 helicopters. MM J70-002 Issue 06 also establishes life limits for
certain part-numbered cooling fan front flanges, and engine pulley ball
bearings and CMR requirements for certain cooling fan front flanges.
This service information 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 EASA 2019-0025
EASA AD 2019-0025 requires contacting H[eacute]licopt[egrave]res
Guimbal for corrective actions when a discrepancy is
[[Page 70002]]
found, whereas this AD requires removing the part from service. EASA AD
2019-0025 requires accomplishing the actions specified in the ALS,
whereas this AD requires establishing a life limit for certain part-
numbered cooling fan front flanges and certain part-numbered engine
pulley ball bearings and removing any part from service accordingly
instead. EASA AD 2019-0025 requires revising the AMP with the actions
specified in the ALS, whereas this AD does not.
Costs of Compliance
The FAA estimates that this AD affects 32 helicopters of U.S.
Registry. Labor rates are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates the following costs to comply with
this AD.
Replacing a cooling fan front flange takes about 16 work-hours and
parts cost about $4,500 for an estimated cost of $5,860 per helicopter
and $187,520 for the U.S. fleet, per replacement cycle.
Replacing an engine pulley ball bearing takes about 12 work-hours
and parts cost about $250 for an estimated cost of $1,270 per
helicopter and $40,640 for the U.S. fleet, per replacement cycle.
The FAA has no way of determining the estimated costs to do
allowable repairs based on the results of the CMR tasks. If required,
replacing a cracked cooling fan front flange takes about 16 work-hours
and parts cost about $4,500 for an estimated cost of $5,860.
The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected operators.
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:
2021-22-08 H[eacute]licopt[egrave]res Guimbal: Amendment 39-21781;
Docket No. FAA-2021-0688; Project Identifier 2019-SW-025-AD.
(a) Effective Date
This airworthiness directive (AD) is effective January 13, 2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to H[eacute]licopt[egrave]res Guimbal (HG) Model
Cabri G2 helicopters, certificated in any category.
(d) Subject
Joint Aircraft Service Component (JASC) Code: 7100, Powerplant
System.
(e) Unsafe Condition
This AD was prompted by a notification of certain parts
remaining in service beyond their fatigue life or beyond maintenance
intervals required by the certification maintenance requirements
(CMRs) of the Instructions for Continued Airworthiness. The FAA is
issuing this AD to prevent failure of a part, which could result in
loss of control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Before further flight after the effective date of this AD,
remove from service any part that has reached or exceeded its life
limit, as specified in paragraphs (g)(1)(i) through (iii) of this
AD, and thereafter remove from service any part on or before each
part reaches its life limit:
(i) The life limit for cooling fan front flange part number (P/
N) G52-02-200 mounted on pulley (12 screws) P/N G52-10-100 or G52-
10-101; and cooling fan front flange P/N G52-02-201 mounted or
having been mounted on pulley (12 screws) P/N G52-10-100 or G52-10-
101, installed on cooling fan P/N G52-00-001 or G52-00-002; is 2,200
total hours time-in-service (TIS).
(ii) The life limit for cooling fan front flange P/N G52-02-201
mounted on pulley (24 screws) P/N G52-10-102 and having never been
mounted on pulley (12 screws) P/N G52-10-100 or G52-10-101,
installed on cooling fan P/N G52-00-001 or G52-00-002, is 4,400
total hours TIS.
(iii) The life limit for engine pulley ball bearing P/N HG61-
0790 and HG61-1944, installed on engine pulley assembly P/N G51-14-
1XX, is 2,200 total hours TIS.
(2) Perform the following CMR tasks as follows:
(i) Cooling fan front flange P/N G52-02-200 mounted on pulley
(12 screws) P/N G52-10-100 or G52-10-101; and cooling fan front
flange P/N G52-02-201 mounted or having been mounted on pulley (12
screws) P/N G52-10-100 or G52-10-101, installed on cooling fan P/N
G52-00-001, and with 500 or more total hours TIS since new as of the
effective date of this AD: Within 5 hours TIS after the effective
date of this AD and thereafter at intervals not to exceed 50 hours
TIS, or 70 engine start-stop cycles, whichever occurs first, inspect
the cooling fan front flange for a crack in accordance with Section
E, Maintenance Instructions, sub section 52-A-10 Cooling Fan
Inspection, paragraph c), on page E-5-53, of Guimbal France
H[eacute]licopt[egrave]res Guimbal Cabri G2 Maintenance Manual (MM)
and Instructions for Continued Airworthiness, J70-002--Issue 06,
dated December 6, 2018 (MM J70-002 Issue 06), except where MM J70-
002 Issue 06 specifies to use a torchlight, use a flashlight. If any
crack is found, before further flight, remove the cooling fan front
flange from service.
(ii) Cooling fan front flange P/N G52-02-200 mounted on pulley
(12 screws) P/N G52-10-100 or G52-10-101; and cooling fan front
flange P/N G52-02-201 mounted or having been mounted on pulley (12
screws) P/N G52-10-100 or G52-10-101, installed on cooling fan P/N
G52-00-001, and with less than 500 total hours TIS since new as of
the effective date of this AD: Before
[[Page 70003]]
accumulating 500 total hours TIS since new and thereafter at
intervals not to exceed 50 hours TIS, or 70 engine start-stop
cycles, whichever occurs first, inspect the cooling fan front flange
for a crack in accordance with Section E, Maintenance Instructions,
sub section 52-A-10 Cooling Fan Inspection, paragraph c), on page E-
5-53, of MM J70-002 Issue 06, except where MM J70-002 Issue 06
specifies to use a torchlight, use a flashlight. If any crack is
found, before further flight, remove the cooling fan front flange
from service.
(iii) Cooling fan front flange P/N G52-02-201 mounted on pulley
(24 screws) P/N G52-10-102 and having never been mounted on pulley
(12 screws) P/N G52-10-100 or G52-10-101, installed on cooling fan
P/N G52-00-002: Before accumulating 500 total hours TIS since new
and thereafter at intervals not to exceed 100 hours TIS, inspect the
cooling fan front flange for a crack in accordance with Section E,
Maintenance Instructions, sub section 52-A-10 Cooling Fan
Inspection, paragraph c), on page E-5-53, of MM J70-002 Issue 06,
except where MM J70-002 Issue 06 specifies to use a torchlight, use
a flashlight. If any crack is found, before further flight, remove
the cooling fan front flange from service.
(iv) For helicopters with tail boom P/N G65-00-101, G65-00-102
or G65-00-103 and subsequent installed: Before further flight after
the effective date of this AD, paint or verify the tail boom upper
surface in accordance with Section C, Airworthiness Limitations, sub
section C-23 Tail Structure Paint, on page C-6, of MM J70-002 Issue
06, as applicable to your helicopter.
(h) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraphs (g)(2)(i) through (iii) of this AD, if those actions were
performed before the effective date of this AD using Section E,
Maintenance Instructions, sub section 52-A-10 Cooling Fan
Inspection, paragraphs (c) and (d), of Guimbal France
H[eacute]licopt[egrave]res Guimbal Cabri G2 MM and Instructions for
Continued Airworthiness, J70-002 Issue--05.1, dated October 30,
2015.
(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: [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
(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., Suite 410, Westbury, NY 11590; telephone (516) 228-
7330; email [email protected].
(2) Service information identified in this AD that is not
incorporated by reference is available at the contact information
specified in paragraphs (k)(3) and (4) of this AD.
(3) The subject of this AD is addressed in European Aviation
Safety Agency (now European Union Aviation Safety Agency (EASA) AD
2019-0025, dated February 4, 2019. You may view the EASA AD on the
internet at https://www.regulations.gov in Docket No. FAA-2021-0688.
(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) Page C-6 of Section C, Airworthiness Limitations, of Guimbal
France H[eacute]licopt[egrave]res Guimbal Cabri G2 Maintenance
Manual and Instructions for Continued Airworthiness, J70-002--Issue
06, dated December 6, 2018.
(ii) Page E-5-53 of Section E, Maintenance Instructions, of
Guimbal France H[eacute]licopt[egrave]res Guimbal Cabri G2
Maintenance Manual and Instructions for Continued Airworthiness,
J70-002--Issue 06, dated December 6, 2018.
(3) For service information identified in this AD, contact
H[eacute]licopt[egrave]res Guimbal, 1070, rue du Lieutenant Parayre,
A[eacute]rodrome d'Aix-en-Provence, 13290 Les Milles, France;
telephone 33-04-42-39-10-88; email [email protected]; or at
https://www.guimbal.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: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on October 14, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-26543 Filed 12-8-21; 8:45 am]
BILLING CODE 4910-13-P
