Airworthiness Directives; Leonardo S.p.a. Helicopters, 15899-15902 [2022-05588]
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Federal Register / Vol. 87, No. 54 / Monday, March 21, 2022 / Proposed Rules
blades. The unsafe condition, if not
addressed, could result in failure of the
engine, in-flight shutdown, loss of thrust
control, and loss of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Group 1 Engines: Borescope Inspection
(BSI) of HPT Rotor Stage 1 Blades and HPT
Stator Stage 1 Nozzle Set
For Group 1 engines with an affected HPT
rotor stage 1 blade installed:
(i) Within 100 flight cycles (FCs) after
accumulating 800 MENA takeoffs on the HPT
rotor stage 1 blade, before the HPT rotor stage
1 blade accumulates 1,750 cycles since new
(CSN), or within 100 FCs after the effective
date of this AD, whichever occurs later,
perform an initial BSI of the HPT rotor stage
1 blades and HPT stator stage 1 nozzle set in
accordance with the Accomplishment
Instructions, paragraphs 5.E.(1)(c) and
5.E.(1)(d), of CFM Service Bulletin LEAP–
1A–72–00–0461–01A–930A–D, Issue 002–00,
dated December 21, 2021 (the SB).
(ii) Thereafter, at intervals not to exceed
150 FCs since the last BSI, perform a
repetitive BSI of the HPT rotor stage 1 blades
and HPT stator stage 1 nozzle set in
accordance with the Accomplishment
Instructions, paragraphs 5.E.(1)(c) and
5.E.(1)(d), of the SB.
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(2) Group 2 Engines: BSI of HPT Rotor Stage
1 Blades and HPT Stator Stage 1 Nozzle Set
For Group 2 engines with an affected HPT
rotor stage 1 blade installed:
(i) Within 100 FCs after accumulating 800
MENA takeoffs on the HPT rotor stage 1
blade, before the HPT rotor stage 1 blade
accumulates 2,600 CSN, or within 100 FCs
after the effective date of this AD, whichever
occurs later, perform an initial BSI of the
HPT rotor stage 1 blades and HPT stator stage
1 nozzle set in accordance with the
Accomplishment Instructions, paragraphs
5.E.(1)(c) and 5.E.(1)(d), of the SB.
(ii) Thereafter, at intervals not to exceed
300 FCs since the last BSI, perform a
repetitive BSI of the HPT rotor stage 1 blades
and HPT stator stage 1 nozzle set in
accordance with the Accomplishment
Instructions, paragraphs 5.E.(1)(c) and
5.E.(1)(d), of the SB.
(3) BSI Results Disposition
Based on the results of the BSI required by
paragraph (g)(1) or (2) of this AD, as
applicable, either re-inspect or replace the
HPT rotor stage 1 blades or HPT stator stage
1 nozzle set using the criteria, compliance
times, and procedures referenced in the
Accomplishment Instructions, paragraph
5.E.(1)(f), of the SB.
(4) Conditional Inspection of the Sister
Engine on the Same Airplane
(i) Based on the BSI results disposition
required by paragraph (g)(3) of this AD, if reinspection or replacement of the HPT rotor
stage 1 blades or HPT stator stage 1 nozzle
set is required within 50 FCs based on the
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criteria, compliance times, and procedures
referenced in the Accomplishment
Instructions, paragraph 5.E.(1)(f), of the SB,
then perform the actions required in
paragraph (g)(4)(ii) of this AD.
(ii) Within 5 FCs after performing the
inspection required by paragraph (g)(1) or (2)
of this AD, as applicable, either inspect or
replace the HPT rotor stage 1 blades or HPT
stator stage 1 nozzle set on the sister engine
using the procedures and compliance times
in the Accomplishment Instructions,
paragraph, 5.E.(1)(g), of the SB. Where the SB
specifies to remove the engine, this AD
requires replacement of the HPT rotor stage
1 blades or HPT stator stage 1 nozzle set, as
applicable.
(5) Reporting Requirements
If, during any inspection required by
paragraph (g)(1), (2), (3), or (4) of this AD, as
applicable, any HPT unserviceable finding is
found on an engine as identified in the
Accomplishment Instructions, paragraph
5.E.(1)(f) of the SB, within 30 days of
performing the inspection, report the HPT
unserviceable finding to CFM in accordance
with the Accomplishment Instructions,
paragraph 5.E.(1)(f)1, of the SB.
Note 1 to paragraph (g): The
Accomplishment Instructions in paragraph
5.E.(1)(f) of the SB reference applicable
aircraft maintenance manual tasks for
procedures and compliance times for the
actions required by paragraphs (g)(3) through
(5) of this AD.
(h) Definitions
(1) Group 1 engines are CFM LEAP–1A29,
LEAP–1A29CJ, LEAP–1A30, LEAP–1A32,
LEAP–1A33, LEAP–1A33B2, and LEAP–
1A35A model turbofan engines.
(2) Group 2 engines are CFM LEAP–1A23,
LEAP–1A24, LEAP–1A24E1, LEAP–1A26,
LEAP–1A26CJ, and LEAP–1A26E1 model
turbofan engines.
(3) For the purpose of this AD, a ‘‘MENA
takeoff’’ is any takeoff accomplished in the
MENA region, as defined in the Planning
Information, paragraph 3.D., of the SB.
(4) For the purpose of this AD, ‘‘sister
engine’’ refers to the other engine installed
on the same airplane.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, ECO 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 certification office,
send it to the attention of the person
identified in paragraph (j)(1) of this AD and
email to: ANE-AD-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.
(j) Related Information
(1) For more information about this AD,
contact Mehdi Lamnyi, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District
PO 00000
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15899
Avenue, Burlington, MA 01803; phone: (781)
238–7743; email: Mehdi.Lamnyi@faa.gov.
(2) For service information identified in
this AD, contact CFM International, S.A.,
Aviation Operations Center, 1 Neumann
Way, M/D Room 285, Cincinnati, OH 45125;
phone: (877) 432–3272; email:
aviation.fleetsupport@ge.com. You may view
this referenced service information at the
FAA, Airworthiness Products Section,
Operational Safety Branch, 1200 District
Avenue, Burlington, MA 01803. For
information on the availability of this
material at the FAA, call (817) 222–5110.
Issued on March 10, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022–05524 Filed 3–18–22; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2022–0283; Project
Identifier MCAI–2021–01285–R]
RIN 2120–AA64
Airworthiness Directives; Leonardo
S.p.a. Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Leonardo S.p.a. Model AB139
and AW139 helicopters. This proposed
AD was prompted by a large crack
detected on the tail gearbox (TGB)
fitting during a scheduled inspection
and the determination that certain TGB
fittings are required to be inspected by
the use of a borescope. This proposed
AD would require a one-time borescope
inspection of certain part-numbered
TGB fittings, and depending on the
inspection results, removing the affected
part from service and replacing with an
airworthy part, as specified in a
European Union Aviation Safety Agency
(EASA) AD, which is proposed for
incorporation by reference (IBR). The
FAA is proposing this AD to address the
unsafe condition on these products.
DATES: The FAA must receive comments
on this proposed AD by May 5, 2022.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
SUMMARY:
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Federal Register / Vol. 87, No. 54 / Monday, March 21, 2022 / Proposed Rules
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For EASA material that is proposed
for IBR in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221
8999 000; email ADs@easa.europa.eu;
internet www.easa.europa.eu. You may
find the EASA 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. This material is
also available at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2022–
0283.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2022–0283; 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
NPRM, the EASA AD, any comments
received, and other information. The
street address for Docket Operations is
listed above.
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:
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Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2022–0283; Project Identifier
MCAI–2021–01285–R’’ at the beginning
of your comments. The most helpful
comments reference a specific portion of
the proposal, explain the reason for any
recommended change, and include
supporting data. The FAA will consider
all comments received by the closing
date and may amend this proposal
because of those comments.
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Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
agency will also post a report
summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial
information that is both customarily and
actually treated as private by its owner.
Under the Freedom of Information Act
(FOIA) (5 U.S.C. 552), CBI is exempt
from public disclosure. If your
comments responsive to this NPRM
contain commercial or financial
information that is customarily treated
as private, that you actually treat as
private, and that is relevant or
responsive to this NPRM, it is important
that you clearly designate the submitted
comments as CBI. Please mark each
page of your submission containing CBI
as ‘‘PROPIN.’’ The FAA will treat such
marked submissions as confidential
under the FOIA, and they will not be
placed in the public docket of this
NPRM. Submissions containing CBI
should be sent to 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. Any
commentary that the FAA receives that
is not specifically designated as CBI will
be placed in the public docket for this
rulemaking.
Background
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2021–0259,
dated November 17, 2021 and corrected
November 22, 2021 (EASA AD 2021–
0259), to correct an unsafe condition for
Leonardo S.p.A. Helicopters, formerly
Finmeccanica S.p.A, AgustaWestland
S.p.A., Agusta S.p.A.; and
AgustaWestland Philadelphia
Corporation, formerly Agusta Aerospace
Corporation, Model AB139 and AW139
helicopters, all serial numbers.
EASA advises that during a scheduled
inspection of a Model AW139
helicopter, a large crack was detected on
the inner forward-right side of TGB
fitting part number 3G5351A01151.
EASA further advises that investigation
results determined previous inspections
on the inner-right side of the TGB fitting
were accomplished without the use of a
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borescope. The FAA is proposing this
AD to detect cracks on the TGB fitting.
The unsafe condition, if not addressed,
could result in crack propagation up to
a critical length, reduced load capability
of the TGB and tail rotor, and
subsequent reduced control of the
helicopter. See EASA AD 2021–0259 for
additional background information.
Related Service Information Under 1
CFR Part 51
EASA AD 2021–0259 specifies
procedures, within the applicable
compliance times, for a one-time
borescope inspection of certain TGB
fittings for a crack or any discrepancy,
and replacement of an affected part with
a new part as specified in the
manufacturer’s service information.
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.
Other Related Service Information
The FAA also reviewed Leonardo
Helicopters Alert Service Bulletin
No.139–686, dated November 8, 2021
(ASB 139–686). This service
information specifies procedures for
borescope inspecting the right-hand and
forward parts of certain TGB fittings for
any cracks or damage and replacing the
TGB fitting with a new one, if any
cracks or damage are detected. ASB
139–686 also specifies procedures for
reporting inspection results if a crack or
discrepancy is detected.
FAA’s Determination
These helicopters have been approved
by EASA and are approved for operation
in the United States. Pursuant to the
FAA’s bilateral agreement with the
European Union, EASA has notified the
FAA about the unsafe condition
described in its AD. The FAA is
proposing this AD after evaluating all
known relevant information and
determining that the unsafe condition
described previously is likely to exist or
develop on other helicopters of the same
type designs.
Proposed AD Requirements in This
NPRM
This proposed AD would require
accomplishing the actions specified in
EASA AD 2021–0259, described
previously, as incorporated by
reference, except for any differences
identified as exceptions in the
regulatory text of this proposed AD and
except as discussed under ‘‘Differences
Between this Proposed AD and EASA
AD 2021–0259.’’
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Federal Register / Vol. 87, No. 54 / Monday, March 21, 2022 / Proposed Rules
Explanation of Required Compliance
Information
In the FAA’s ongoing efforts to
improve the efficiency of the AD
process, the FAA developed a process to
use some civil aviation authority (CAA)
ADs as the primary source of
information for compliance with
requirements for corresponding FAA
ADs. The FAA has been coordinating
this process with manufacturers and
CAAs. As a result, the FAA proposes to
incorporate EASA AD 2021–0259 by
reference in the FAA final rule. This
proposed AD would, therefore, require
compliance with EASA AD 2021–0259
in its entirety through that
incorporation, except for any differences
identified as exceptions in the
regulatory text of this proposed AD.
Using common terms that are the same
as the heading of a particular section in
EASA AD 2021–0259 does not mean
that operators need comply only with
that section. For example, where the AD
requirement refers to ‘‘all required
actions and compliance times,’’
compliance with this AD requirement is
not limited to the section titled
‘‘Required Action(s) and Compliance
Time(s)’’ in EASA AD 2021–0259.
Service information referenced in EASA
AD 2021–0259 for compliance will be
available at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2022–0283 after the FAA final
rule is published.
Differences Between This Proposed AD
and EASA AD 2021–0259
EASA AD 2021–0259 applies to
Model AB139 and AW139 helicopters,
all serial numbers, whereas this
proposed AD would only apply to
Model AB139 and AW139 helicopters
with certain part-numbered TGB fittings
installed. This proposed AD would not
require compliance with paragraph (3)
of EASA AD 2021–0259.
Service information referenced in
EASA AD 2021–0259 specifies that if
any crack or damage is found, replace
the damaged TGB fitting with a new
one, whereas this proposed AD would
require before further flight, removing
the affected TGB fitting from service and
replacing with an airworthy part.
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Costs of Compliance
The FAA estimates that this AD, if
adopted as proposed, would affect 129
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 proposed AD.
Borescope inspecting the TGB fitting
for a crack and any discrepancy (i.e.,
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damage) would take about 4 work-hours
for an estimated cost of $340 per
helicopter and $43,860 for the U.S. fleet.
Replacing the TGB fitting with an
airworthy TGB fitting would take about
36 work-hours and parts would cost
about $6,650 for an estimated cost of
$9,710 per replacement.
The FAA has included all known
costs in its cost estimate. According to
the manufacturer, however, some of the
costs of this proposed 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 products identified in this
rulemaking action.
Regulatory Findings
The FAA determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would 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 this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Would not affect intrastate
aviation in Alaska, and
(3) Would 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.
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15901
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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:
■
Leonardo S.p.a.: Docket No. FAA–2022–
0283; Project Identifier MCAI–2021–
01285–R.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by May 5, 2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Leonardo S.p.a. Model
AB139 and AW139 helicopters, certificated
in any category, with an affected part as
identified in European Union Aviation Safety
Agency (EASA) AD 2021–0259, dated
November 17, 2021, and corrected November
22, 2021 (EASA AD 2021–0259).
(d) Subject
Joint Aircraft Service Component (JASC)
Code: 5300, Fuselage Structure.
(e) Unsafe Condition
This AD was prompted by a large crack
detected on the tail gearbox (TGB) fitting
during a scheduled inspection and the
determination that certain TGB fittings are
required to be inspected by the use of a
borescope. The FAA is issuing this AD to
detect cracks on the TGB fitting. The unsafe
condition, if not addressed, could result in
crack propagation up to a critical length,
reduced load capability of the TGB and tail
rotor, and subsequent reduced control of the
helicopter.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, EASA AD 2021–0259.
(h) Exceptions to EASA AD 2021–0259
(1) Where EASA AD 2021–0259 requires
compliance in terms of flight hours (FH), this
AD requires using hours time-in-service.
(2) Where EASA AD 2021–0259 refers to its
effective date, this AD requires using the
effective date of this AD.
(3) Where paragraph (1) of EASA AD 2021–
0259 specifies ‘‘inspect, using a borescope,
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Federal Register / Vol. 87, No. 54 / Monday, March 21, 2022 / Proposed Rules
the affected part in accordance with the
instructions of Section 3 Part I of the ASB,’’
for this AD replace ‘‘in accordance with the
instructions of Section 3 Part I of the ASB’’
with ‘‘in accordance with the
Accomplishment Instructions, Section 3 Part
I, paragraphs 5. through 5.5 of the ASB.’’
(4) Where paragraph (2) of EASA AD 2021–
0259 specifies ‘‘if, during the inspection as
required by paragraph (1) this AD, a crack or
any discrepancy is detected, replace the
affected part in accordance with the
instructions of Section 3 Part II of the ASB,’’
this AD requires before further flight,
removing the TGB fitting from service and
replacing with an airworthy part, if any crack
or discrepancy is detected. For this AD,
discrepancies include damage, which
includes scratches and dents on the outer
surfaces of the forward and right-hand sides
of the TGB fitting above the horizontal row
of fastener holes. The instructions specified
in paragraph (2) of EASA AD 2021–0259 are
for reference only and are not required for the
replacement required by this paragraph.
(5) Where paragraph (4) of EASA AD 2021–
0259 allows (re)installing an affected part
provided it is inspected as required by
paragraph (1) of EASA AD 2021–0259, for
this AD, the inspected part cannot be
(re)installed if any crack or discrepancy is
detected.
(6) This AD does not mandate compliance
with paragraph (3) of EASA AD 2021–0259.
(7) This AD does not mandate compliance
with the ‘‘Remarks’’ section of EASA AD
2021–0259.
(i) Special Flight Permit
Special flight permits may be issued in
accordance with 14 CFR 21.197 and 21.199,
provided no passengers are onboard.
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(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, International Validation
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the International Validation
Branch, send it to the attention of the person
identified in paragraph (k)(2) 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.
(k) Related Information
(1) For EASA AD 2021–0259, contact
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 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.
This material may be found in the AD docket
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Jkt 256001
at https://www.regulations.gov by searching
for and locating Docket No. FAA–2022–0283.
(2) 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
andrea.jimenez@faa.gov.
Issued on March 10, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022–05588 Filed 3–18–22; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2022–0103; Project
Identifier AD–2021–00977–T]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain The Boeing Company Model 777
airplanes. This proposed AD was
prompted by reports of discrepancies
between the center wing tank (CWT)
fuel quantity, as indicated by the fuel
quantity indicating system (FQIS), and
the refueling truck uploaded fuel
amount, followed by certain engineindicating and crew-alerting system
(EICAS) messages. This proposed AD
would require installing new software
in the fuel quantity processor unit
(FQPU), or replacing the FQPU with one
that includes new software, depending
on airplane configuration; and doing a
software version check and FQPU
operational check. This proposed AD
would also prohibit the installation of
certain FQPUs on certain airplanes. The
FAA is proposing this AD to address the
unsafe condition on these products.
DATES: The FAA must receive comments
on this proposed AD by May 5, 2022.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
SUMMARY:
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone 562–797–1717;
internet https://
www.myboeingfleet.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 at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2022–
0103.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2022–0103; 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
NPRM, any comments received, and
other information. The street address for
Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Kevin Nguyen, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–
231–3555; email: kevin.nguyen@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2022–0103; Project Identifier AD–
2021–00977–T’’ at the beginning of your
comments. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. The FAA will consider
all comments received by the closing
date and may amend this proposal
because of those comments.
Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
E:\FR\FM\21MRP1.SGM
21MRP1
]]>Agencies
[Federal Register Volume 87, Number 54 (Monday, March 21, 2022)]
[Proposed Rules]
[Pages 15899-15902]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-05588]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0283; Project Identifier MCAI-2021-01285-R]
RIN 2120-AA64
Airworthiness Directives; Leonardo S.p.a. Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Leonardo S.p.a. Model AB139 and AW139 helicopters. This
proposed AD was prompted by a large crack detected on the tail gearbox
(TGB) fitting during a scheduled inspection and the determination that
certain TGB fittings are required to be inspected by the use of a
borescope. This proposed AD would require a one-time borescope
inspection of certain part-numbered TGB fittings, and depending on the
inspection results, removing the affected part from service and
replacing with an airworthy part, as specified in a European Union
Aviation Safety Agency (EASA) AD, which is proposed for incorporation
by reference (IBR). The FAA is proposing this AD to address the unsafe
condition on these products.
DATES: The FAA must receive comments on this proposed AD by May 5,
2022.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
[[Page 15900]]
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For EASA material that is proposed for IBR in this AD, contact
EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221
8999 000; email [email protected]; internet www.easa.europa.eu. You
may find the EASA 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. This material is also
available at https://www.regulations.gov by searching for and locating
Docket No. FAA-2022-0283.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2022-0283; 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 NPRM, the EASA AD,
any comments received, and other information. The street address for
Docket Operations is listed above.
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:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2022-0283; Project Identifier
MCAI-2021-01285-R'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to
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]. Any commentary that the FAA
receives that is not specifically designated as CBI will be placed in
the public docket for this rulemaking.
Background
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2021-0259, dated November 17, 2021
and corrected November 22, 2021 (EASA AD 2021-0259), to correct an
unsafe condition for Leonardo S.p.A. Helicopters, formerly Finmeccanica
S.p.A, AgustaWestland S.p.A., Agusta S.p.A.; and AgustaWestland
Philadelphia Corporation, formerly Agusta Aerospace Corporation, Model
AB139 and AW139 helicopters, all serial numbers.
EASA advises that during a scheduled inspection of a Model AW139
helicopter, a large crack was detected on the inner forward-right side
of TGB fitting part number 3G5351A01151. EASA further advises that
investigation results determined previous inspections on the inner-
right side of the TGB fitting were accomplished without the use of a
borescope. The FAA is proposing this AD to detect cracks on the TGB
fitting. The unsafe condition, if not addressed, could result in crack
propagation up to a critical length, reduced load capability of the TGB
and tail rotor, and subsequent reduced control of the helicopter. See
EASA AD 2021-0259 for additional background information.
Related Service Information Under 1 CFR Part 51
EASA AD 2021-0259 specifies procedures, within the applicable
compliance times, for a one-time borescope inspection of certain TGB
fittings for a crack or any discrepancy, and replacement of an affected
part with a new part as specified in the manufacturer's service
information.
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.
Other Related Service Information
The FAA also reviewed Leonardo Helicopters Alert Service Bulletin
No.139-686, dated November 8, 2021 (ASB 139-686). This service
information specifies procedures for borescope inspecting the right-
hand and forward parts of certain TGB fittings for any cracks or damage
and replacing the TGB fitting with a new one, if any cracks or damage
are detected. ASB 139-686 also specifies procedures for reporting
inspection results if a crack or discrepancy is detected.
FAA's Determination
These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Union, EASA has notified the FAA about the
unsafe condition described in its AD. The FAA is proposing this AD
after evaluating all known relevant information and determining that
the unsafe condition described previously is likely to exist or develop
on other helicopters of the same type designs.
Proposed AD Requirements in This NPRM
This proposed AD would require accomplishing the actions specified
in EASA AD 2021-0259, described previously, as incorporated by
reference, except for any differences identified as exceptions in the
regulatory text of this proposed AD and except as discussed under
``Differences Between this Proposed AD and EASA AD 2021-0259.''
[[Page 15901]]
Explanation of Required Compliance Information
In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA developed a process to use some civil aviation
authority (CAA) ADs as the primary source of information for compliance
with requirements for corresponding FAA ADs. The FAA has been
coordinating this process with manufacturers and CAAs. As a result, the
FAA proposes to incorporate EASA AD 2021-0259 by reference in the FAA
final rule. This proposed AD would, therefore, require compliance with
EASA AD 2021-0259 in its entirety through that incorporation, except
for any differences identified as exceptions in the regulatory text of
this proposed AD. Using common terms that are the same as the heading
of a particular section in EASA AD 2021-0259 does not mean that
operators need comply only with that section. For example, where the AD
requirement refers to ``all required actions and compliance times,''
compliance with this AD requirement is not limited to the section
titled ``Required Action(s) and Compliance Time(s)'' in EASA AD 2021-
0259. Service information referenced in EASA AD 2021-0259 for
compliance will be available at https://www.regulations.gov by
searching for and locating Docket No. FAA-2022-0283 after the FAA final
rule is published.
Differences Between This Proposed AD and EASA AD 2021-0259
EASA AD 2021-0259 applies to Model AB139 and AW139 helicopters, all
serial numbers, whereas this proposed AD would only apply to Model
AB139 and AW139 helicopters with certain part-numbered TGB fittings
installed. This proposed AD would not require compliance with paragraph
(3) of EASA AD 2021-0259.
Service information referenced in EASA AD 2021-0259 specifies that
if any crack or damage is found, replace the damaged TGB fitting with a
new one, whereas this proposed AD would require before further flight,
removing the affected TGB fitting from service and replacing with an
airworthy part.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 129 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 proposed AD.
Borescope inspecting the TGB fitting for a crack and any
discrepancy (i.e., damage) would take about 4 work-hours for an
estimated cost of $340 per helicopter and $43,860 for the U.S. fleet.
Replacing the TGB fitting with an airworthy TGB fitting would take
about 36 work-hours and parts would cost about $6,650 for an estimated
cost of $9,710 per replacement.
The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some of the costs of this
proposed 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 products identified in this rulemaking action.
Regulatory Findings
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would 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 Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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:
Leonardo S.p.a.: Docket No. FAA-2022-0283; Project Identifier MCAI-
2021-01285-R.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by May 5, 2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Leonardo S.p.a. Model AB139 and AW139
helicopters, certificated in any category, with an affected part as
identified in European Union Aviation Safety Agency (EASA) AD 2021-
0259, dated November 17, 2021, and corrected November 22, 2021 (EASA
AD 2021-0259).
(d) Subject
Joint Aircraft Service Component (JASC) Code: 5300, Fuselage
Structure.
(e) Unsafe Condition
This AD was prompted by a large crack detected on the tail
gearbox (TGB) fitting during a scheduled inspection and the
determination that certain TGB fittings are required to be inspected
by the use of a borescope. The FAA is issuing this AD to detect
cracks on the TGB fitting. The unsafe condition, if not addressed,
could result in crack propagation up to a critical length, reduced
load capability of the TGB and tail rotor, and subsequent reduced
control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2021-0259.
(h) Exceptions to EASA AD 2021-0259
(1) Where EASA AD 2021-0259 requires compliance in terms of
flight hours (FH), this AD requires using hours time-in-service.
(2) Where EASA AD 2021-0259 refers to its effective date, this
AD requires using the effective date of this AD.
(3) Where paragraph (1) of EASA AD 2021-0259 specifies
``inspect, using a borescope,
[[Page 15902]]
the affected part in accordance with the instructions of Section 3
Part I of the ASB,'' for this AD replace ``in accordance with the
instructions of Section 3 Part I of the ASB'' with ``in accordance
with the Accomplishment Instructions, Section 3 Part I, paragraphs
5. through 5.5 of the ASB.''
(4) Where paragraph (2) of EASA AD 2021-0259 specifies ``if,
during the inspection as required by paragraph (1) this AD, a crack
or any discrepancy is detected, replace the affected part in
accordance with the instructions of Section 3 Part II of the ASB,''
this AD requires before further flight, removing the TGB fitting
from service and replacing with an airworthy part, if any crack or
discrepancy is detected. For this AD, discrepancies include damage,
which includes scratches and dents on the outer surfaces of the
forward and right-hand sides of the TGB fitting above the horizontal
row of fastener holes. The instructions specified in paragraph (2)
of EASA AD 2021-0259 are for reference only and are not required for
the replacement required by this paragraph.
(5) Where paragraph (4) of EASA AD 2021-0259 allows
(re)installing an affected part provided it is inspected as required
by paragraph (1) of EASA AD 2021-0259, for this AD, the inspected
part cannot be (re)installed if any crack or discrepancy is
detected.
(6) This AD does not mandate compliance with paragraph (3) of
EASA AD 2021-0259.
(7) This AD does not mandate compliance with the ``Remarks''
section of EASA AD 2021-0259.
(i) Special Flight Permit
Special flight permits may be issued in accordance with 14 CFR
21.197 and 21.199, provided no passengers are onboard.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, International Validation Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the International Validation Branch, send
it to the attention of the person identified in paragraph (k)(2) of
this AD. Information may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(k) Related Information
(1) For EASA AD 2021-0259, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
[email protected]; internet www.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. This material may be found in the AD docket at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2022-0283.
(2) 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].
Issued on March 10, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2022-05588 Filed 3-18-22; 8:45 am]
BILLING CODE 4910-13-P
