Airworthiness Directives; Engine Alliance Turbofan Engines, 49944-49947 [2019-20599]
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Federal Register / Vol. 84, No. 185 / Tuesday, September 24, 2019 / Rules and Regulations
and importers voting in a referendum
conducted in September and October
2018. The Act requires that, upon such
a determination by referendum, the
Department shall terminate the Order.
The assets of the Council have been
liquidated, and a final audit of the
Council’s books has been conducted.
It is therefore ordered, that pursuant
to section 522 of the Act, the Order is
hereby terminated.
It is also found and determined upon
good cause that it is impracticable,
unnecessary, and contrary to the public
interest to give preliminary notice or to
engage in further public procedure prior
to putting this action into effect, and
that good cause exists for not
postponing the effective date of this
action until 30 days after publication in
the Federal Register because (1) this
action relieves restrictions on handlers
and importers by terminating the
requirements of the Order; (2)
termination of the Order was favored by
a majority of qualified producers and
importers voting in a referendum in
September–October 2018; and (3) the
assets of the Council have been
liquidated and a final audit of the
Council’s books has been conducted.
List of Subjects in 7 CFR Part 1208
Administrative practice and
procedure, Advertising, Consumer
information, Marketing agreements,
Raspberry promotion, Reporting and
recordkeeping requirements.
PART 1208—[REMOVED]
For the reasons set forth in the
preamble, and under the authority of 7
U.S.C. 6802 et seq., 7 CFR part 1208 is
removed.
■
Dated: September 16, 2019.
Bruce Summers,
Administrator.
[FR Doc. 2019–20343 Filed 9–23–19; 8:45 am]
BILLING CODE 3410–02–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
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14 CFR Part 39
[Docket No. FAA–2019–0692; Product
Identifier 2018–NE–19–AD; Amendment 39–
19735; AD 2019–18–08]
RIN 2120–AA64
Airworthiness Directives; Engine
Alliance Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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15:47 Sep 23, 2019
Jkt 247001
Final rule; request for
comments.
ACTION:
The FAA is superseding
Airworthiness Directive (AD) 2019–16–
04 for all Engine Alliance (EA) GP7270
and GP7277 model turbofan engines.
AD 2019–16–04 required a visual
inspection of the 1st-stage low-pressure
compressor (LPC) rotor assembly,
referred to after this as the ‘‘engine fan
hub assembly,’’ for damage, a one-time
eddy current inspection (ECI) of the
engine fan hub blade slot bottom and
blade slot front edge for cracks; and
removal of parts if damage or defects are
found. AD 2019–16–04 also required
replacement of the engine fan hub blade
lock assembly for certain GP7270 and
GP7277 model turbofan engines. This
AD, for certain GP7270 and GP7277
model turbofan engines, reduces the
compliance time for the initial ECI and
requires repetitive ECIs of the engine fan
hub blade slot bottom and blade slot
front edge for cracks. This AD also
retains the visual inspection
requirements of the engine fan hub
assembly for all GP7270 and GP7277
model turbofan engines. This AD was
prompted by an uncontained failure of
the engine fan hub. The FAA is issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective October 9,
2019.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of October 9, 2019.
The FAA must receive any comments
on this AD by November 8, 2019.
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.
• 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: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this final rule, contact Engine Alliance,
411 Silver Lane, East Hartford, CT
06118; phone: 800–565–0140; email:
help24@pw.utc.com; website:
www.engineallianceportal.com. You
may view this service information at the
SUMMARY:
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FAA, Engine and Propeller Standards
Branch, 1200 District Avenue,
Burlington, MA 01803. For information
on the availability of this material at the
FAA, call 781–238–7759. It is also
available on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0692.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0692; 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 regulatory evaluation, any
comments received, and other
information. The street address for
Docket Operations is listed above.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Matthew Smith, Aerospace Engineer,
ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone:
781–238–7735; fax: 781–238–7199;
email: matthew.c.smith@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued AD 2019–16–04,
Amendment 39–19707 (84 FR 41617,
August 15, 2019), (‘‘AD 2019–16–04’’),
for all EA GP7270 and GP7277 model
turbofan engines. AD 2019–16–04
required a visual inspection of the
engine fan hub assembly for damage, a
one-time ECI of the engine fan hub
blade slot bottom and blade slot front
edge for cracks, and removal of parts if
damage or defects are found that are
outside serviceable limits. AD 2019–16–
04 required an independent inspection
of the engine fan hub assembly prior to
reassembly of the engine fan hub blade
lock assembly. AD 2019–16–04 also
required replacement of the engine fan
hub blade lock assembly for certain
serial-numbered GP7270 and GP7277
model turbofan engines. AD 2019–16–
04 resulted from the manufacturer’s
determination that an independent
inspection of the fan hub assembly for
damage was necessary prior to the
reassembly of the engine fan hub blade
lock assembly for all EA GP7270 and
GP7277 model turbofan engines. The
FAA issued AD 2019–16–04 to detect
defects, damage, and cracks that could
result in an uncontained failure of the
engine fan hub assembly.
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Federal Register / Vol. 84, No. 185 / Tuesday, September 24, 2019 / Rules and Regulations
Actions Since AD 2019–16–04 Was
Issued
Since the FAA issued AD 2019–16–
04, the manufacturer identified a fatigue
crack originating inboard of a blade slot
after the manufacturer performed a
metallurgical examination of the engine
fan hub that was recovered, related to
the September 30, 2017 event. After
performing a risk assessment, the
manufacturer determined the need to
reduce the compliance time for the
initial ECI and add a repetitive ECI. The
FAA is issuing this AD to address the
unsafe condition on these products.
Related Service Information Under 1
CFR Part 51
The FAA reviewed EA Alert Service
Bulletin (ASB) EAGP7–A72–389,
Revision No. 5, dated August 23, 2019.
The ASB describes procedures for ECI of
the EA GP7270 and GP7277 model
turbofan engines fan hub assembly. 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.
Other Related Service Information
The FAA reviewed EA ASB EAGP7–
A72–418, Revision No. 1, dated January
11, 2019. The ASB provides guidance
on replacement or modification of the
engine fan hub blade lock assembly.
The FAA also reviewed the following
service information:
Subtask 72–31–42–210–001–A, of
Task 72–31–42–000–802–A, from the
A380 Aircraft Maintenance Manual
(AMM). This subtask describes an onwing visual inspection that is to be
performed after removal of the engine
fan hub blade lock assembly.
Figure 405 of Task 72–00–31–420–004
of the EA GP7000 Series Engine Manual
(EM). This figure and task describe a
visual inspection that is to be performed
after removal of the engine fan hub
blade lock assembly when the engine is
in the shop.
Subtask 72–00–00–210–012–A, of
Task 72–00–00–210–806–A, from the
A380 Aircraft Maintenance Manual
(AMM). This subtask describes an onwing visual inspection that is to be
performed after reassembly of the
engine fan hub blade lock assembly.
Task 72–00–31–420–004, Paragraph
1.E.(13), of the GP7000 Series EM
describes a visual inspection that is to
be performed after reassembly of the
engine fan hub blade lock assembly
when the engine is in the shop.
Table 601 in Subtask 72–00–00–210–
012–A, Task 72–00–00–210–806, from
the A380 AMM or Task 72–00–31–220–
010 of the EA GP7000 Series EM. Table
601 and Task 72–00–31–220–010
provide guidance on acceptable damage
service limits.
FAA’s Determination
The FAA is issuing this AD because
all the relevant information was
evaluated and the FAA determined the
unsafe condition described previously is
likely to exist or develop in other
products of the same type design.
AD Requirements
This AD requires, for certain GP7270
and GP7277 model turbofan engines, an
initial and repetitive ECI of the engine
fan hub blade slot bottom and blade slot
front edge for cracks. For all GP7270
and GP7277 model turbofan engines,
this AD also requires an independent
inspection of the engine fan hub
assembly prior to the reassembly of the
engine fan hub blade lock assembly and
a visual inspection of the engine fan hub
assembly for damage. For certain serialnumbered GP7270 and GP7277 model
turbofan engines, this AD requires
replacement of the engine fan hub blade
lock assembly with a part eligible for
installation.
FAA’s Justification and Determination
of the Effective Date
No domestic operators use this
product. Therefore, the FAA finds good
cause that notice and opportunity for
prior public comment are unnecessary.
In addition, for the reason stated above,
the FAA finds that good cause exists for
making this amendment effective in less
than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
the FAA did not provide you with
notice and an opportunity to provide
your comments before it becomes
effective. However, the FAA invites you
to send any written data, views, or
arguments about this final rule. Send
your comments to an address listed
under the ADDRESSES section. Include
the docket number FAA–2019–0692 and
product identifier 2018–NE–19–AD at
the beginning of your comments. The
FAA specifically invites comments on
the overall regulatory, economic,
environmental, and energy aspects of
this final rule. The FAA will consider
all comments received by the closing
date and may amend this final rule
because of those comments.
The FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
FAA will also post a report
summarizing each substantive verbal
contact received about this final rule.
Regulatory Flexibility Act
The requirements of the Regulatory
Flexibility Act (RFA) do not apply when
an agency finds good cause pursuant to
5 U.S.C. 553 to adopt a rule without
prior notice and comment. Because FAA
has determined that it has good cause to
adopt this rule without notice and
comment, RFA analysis is not required.
Costs of Compliance
The FAA estimates that this AD
affects zero engines installed on
airplanes of U.S. registry. We have
revised the estimate of work hours to
complete the ECI based on updated
service information.
The FAA estimates the following
costs to comply with this AD:
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ESTIMATED COSTS
Action
Labor cost
ECI ..................................................................
Visual inspection .............................................
Replace fan hub blade lock assembly ............
20 work-hours × $85 per hour = $1,700 ........
1 work-hour × $85 per hour = $85 .................
25 work-hours × $85 per hour = $2,125 ........
The FAA estimates the following
costs to do any necessary replacements
that would be required based on the
results of the inspection. The FAA has
no way of determining the number of
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Parts cost
$0
0
28,000
Cost per
product
Cost on U.S.
operators
$1,700
85
30,125
engines that might need these
replacements:
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$0
0
0
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Federal Register / Vol. 84, No. 185 / Tuesday, September 24, 2019 / Rules and Regulations
ON-CONDITION COSTS
Action
Labor cost
Replace engine fan hub assembly ...............................
50 work-hours × $85 per hour = $4,250 ......................
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701, ‘‘General requirements.’’ Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to engines, propellers, and
associated appliances to the Manager,
Engine and Propeller Standards Branch,
Policy and Innovation Division.
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,
and
(2) Will not affect intrastate aviation
in Alaska.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
VerDate Sep<11>2014
15:47 Sep 23, 2019
Jkt 247001
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends part 39 of the Federal
Aviation Regulations (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
removing Airworthiness Directive (AD)
AD 2019–16–04, Amendment 39–19707
(84 FR 41617, August 15, 2019), and
adding the following new AD:
■
2019–18–08 Engine Alliance: Amendment
39–19735; Docket No. FAA–2019–0692;
Product Identifier 2018–NE–19–AD.
(a) Effective Date
This AD is effective October 9, 2019.
(b) Affected ADs
This AD replaces AD 2019–16–04,
Amendment 39–19707 (84 FR 41617, August
15, 2019) (‘‘AD 2019–16–04’’).
(c) Applicability
This AD applies to all Engine Alliance (EA)
GP7270 and GP7277 model turbofan engines.
(d) Subject
Joint Aircraft System Component (JASC)
Code 7230, Turbine Engine Compressor
Section.
(e) Unsafe Condition
This AD was prompted by an uncontained
failure of the engine fan hub. The FAA is
issuing this AD to detect defects, damage,
and cracks that could result in an
uncontained failure of the engine fan hub
assembly. The unsafe condition, if not
addressed, could result in uncontained
failure of the engine fan hub assembly,
damage to the engine, and damage to the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) For EA GP7270 and GP7277 model
turbofan engines with engine fan hub
assembly part numbers (P/Ns) 5760221 or
5760321, within 1,700 cycles since new, or
within 150 flight cycles (FCs) after the
effective date of this AD, or within 330 FCs
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Parts cost
$790,500
Cost per
product
$794,750
since an eddy current inspection (ECI) was
performed in accordance with the
Accomplishment Instructions, For Fan Hubs
at LPC Module Assembly Level, paragraphs
2.A and 2.B, of EA ASB EAGP7–A72–389,
Revision No. 4, dated June 14, 2019, or
earlier versions of that ASB; or within 330
FCs since overhaul, whichever occurs later:
(i) For engine fan hub assemblies at the
low-pressure compressor (LPC) module
assembly level, perform an ECI of the engine
fan hub blade slot bottoms and front edges
in accordance with the Accomplishment
Instructions, For Fan Hubs at LPC Module
Assembly Level, paragraphs 1.B. and 1.C., of
EA ASB EAGP7–A72–389, Revision No. 5,
dated August 23, 2019.
(ii) For engine fan hub assemblies at the
piece part level, perform an ECI of the engine
fan hub blade slot bottoms and front edges,
in accordance with the Accomplishment
Instructions, For Fan Hubs at Piece Part
Level, paragraphs 1.A. and 1.B., of EA ASB
EAGP7–A72–389, Revision No. 5, dated
August 23, 2019.
(iii) For engine fan hub assemblies
installed in an engine (on-wing or off-wing),
perform an ECI of the engine fan hub blade
slot bottoms and front edges, in accordance
with the Accomplishment Instructions, For
Fan Hubs Installed in an Engine, paragraphs
3.B. and 3.C., of EA ASB EAGP7–A72–389,
Revision No. 5, dated August 23, 2019.
(iv) Thereafter, repeat the ECI of the engine
fan hub blade slot bottoms and front edges
at intervals not exceeding 330 FCs since the
previous ECI required by paragraphs (g)(1)(i)
through (iii) of this AD, as applicable.
(v) If any ECI of the engine fan hub
assembly results in a rejectable indication per
the Appendix, Added Data, of EA ASB
EAGP7–A72–389, Revision No. 5, dated
August 23, 2019, remove the engine fan hub
assembly from service and, before further
flight, replace with a part that is eligible for
installation.
(2) For all GP7270 and GP7277 model
turbofan engines, after the effective date of
this AD:
(i) At the next disassembly of the engine
fan hub blade lock assembly, visually inspect
the following areas for damage:
(A) The fan hub blade lock retention hooks
(also known as lock ring contact area); and
(B) The fan hub rim face.
(ii) At the next reassembly of the fan hub
blade lock assembly, visually inspect the
following areas of the engine fan hub for
damage:
(A) The fan hub scallop areas;
(B) The fan hub bore area behind the
balance flange;
(C) The fan hub fan blade lock retention
hooks;
(D) The fan hub rim face; and
(E) The clinch nut holes.
(iii) After any reassembly per paragraph
(g)(2)(ii), before further flight, perform an
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Federal Register / Vol. 84, No. 185 / Tuesday, September 24, 2019 / Rules and Regulations
independent inspection of all areas of the
engine fan hub referenced in paragraph
(g)(2)(ii) of this AD for damage.
(iv) Thereafter, repeat the inspections
required by paragraphs (g)(2)(i) through (iii)
of this AD at each disassembly and
reassembly of the engine fan hub blade lock
assembly.
(v) As an optional terminating action to the
inspection requirements and independent
inspection requirements of paragraph (g)(2)(i)
through (iii) of this AD, insert the
requirements for the visual inspections and
independent inspections required by these
paragraphs as Required Inspection Items in
the approved continuous airworthiness
maintenance program for the airplane.
(vi) If damage is found outside serviceable
limits during the inspections required by
(g)(2)(i) through (iii) of this AD, before further
flight, remove the engine fan hub assembly
from service and replace it with a part
eligible for installation.
(3) For GP7270 and GP7277 model
turbofan engines with engine serial numbers
P550101 through P550706, remove the
engine fan hub blade lock assembly, P/N
5700451, by September 1, 2020, and replace
with a part eligible for installation. Refer to
EA ASB EAGP7–A72–418, Revision No. 1,
dated January 11, 2019, for guidance on
replacement of the engine fan hub blade lock
assembly.
(h) Credit for Previous Actions
You may take credit for the inspections
required by paragraph (g)(1)(i) through (iii) of
this AD if you performed the inspections
before the effective date of this AD using EA
ASB EAGP7–A72–389, Revision No. 4, dated
June 14, 2019, or an earlier version.
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(i) Definitions
(1) For the purpose of this AD, a part
eligible for installation for replacement of the
engine fan hub blade lock assembly is:
(i) A part that is not P/N 5700451, or
(ii) An engine fan hub blade lock assembly
that has been modified in accordance with
EA ASB EAGP7–A72–418, Revision No. 1,
dated January 11, 2019, or EA ASB EAGP7–
A72–418, Revision No. 0, dated December 7,
2018.
(2) For the purpose of this AD, an
independent inspection is a second visual
inspection performed by an individual
qualified to perform inspections who was not
involved in the original inspection of the
engine fan hub assembly following
disassembly and reassembly of the engine fan
hub blade lock assembly.
(j) 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 (k) of this AD. You
may email your request to: ANE-ADAMOC@faa.gov.
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Jkt 247001
(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.
(3) AMOCs approved for AD 2019–16–04,
AD 2018–11–16 (83 FR 27891, June 15,
2018), and AD 2019–03–04 (84 FR 4694,
February 19, 2019) are approved as AMOCs
for the corresponding provisions of this AD.
(k) Related Information
For more information about this AD,
contact Matthew Smith, Aerospace Engineer,
ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: 781–238–
7735; fax: 781–238–7199; email:
matthew.c.smith@faa.gov.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Engine Alliance (EA) Alert Service
Bulletin EAGP7–A72–389, Revision No. 5,
dated August 23, 2019.
(ii) [Reserved]
(3) For EA service information identified in
this AD, contact Engine Alliance, 411 Silver
Lane, East Hartford, CT 06118; phone: 800–
565–0140; email: help24@pw.utc.com;
website: www.engineallianceportal.com.
(4) You may view this service information
at the FAA, Engine & Propeller Standards
Branch, 1200 District Avenue, Burlington,
MA 01803. For information on the
availability of this material at the FAA, call
781–238–7759.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email: fedreg.legal@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Burlington, Massachusetts, on
September 18, 2019.
Karen M. Grant,
Acting Manager, Engine & Propeller
Standards Branch, Aircraft Certification
Service.
[FR Doc. 2019–20599 Filed 9–23–19; 8:45 am]
BILLING CODE 4910–13–P
CONSUMER PRODUCT SAFETY
COMMISSION
16 CFR Part 1130
[Docket No. CPSC–2018–0018]
Amendment to Requirements for
Consumer Registration of Durable
Infant or Toddler Products
Consumer Product Safety
Commission.
ACTION: Final rule.
AGENCY:
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49947
In 2009, the Consumer
Product Safety Commission (CPSC)
fulfilled a statutory requirement in the
Consumer Product Safety Improvement
Act of 2008 (CPSIA) to issue a rule
requiring manufacturers of durable
infant or toddler products to establish a
consumer registration program. The
Commission is now finalizing an
amendment to the definition of ‘‘durable
infant or toddler product’’ in the rule to
include the full statutory definition;
clarify that the scope of each listed
product category is further defined in
the applicable mandatory standard;
clarify listed product categories using
the product name in the applicable
mandatory standard; and clarify the
scope of the infant carriers and bassinets
and cradles product categories.
DATES:
Effective Date: The rule will become
effective on October 24, 2019.
Compliance Date for Contoured
Changing Pads: Contoured changing
pads, a subcategory of baby changing
products in § 1130.2(a)(14), must
comply with this rule starting on
September 24, 2020.
FOR FURTHER INFORMATION CONTACT:
Keysha L. Walker, Compliance Officer,
Office of Compliance & Field
Operations, Regulatory Enforcement
Division, Consumer Product Safety
Commission, 4330 East-West Highway,
Bethesda, MD 20814; 301–504–6820,
Email: kwalker@cpsc.gov.
SUPPLEMENTARY INFORMATION:
SUMMARY:
I. Background and Statutory Authority
Section 104 of the CPSIA is the Danny
Keysar Child Product Safety
Notification Act. Section 104 of the
CPSIA requires that for ‘‘durable infant
or toddler products,’’ the CPSC must (1)
issue a mandatory rule for each product
based on the applicable voluntary
standard, and (2) issue a rule requiring
consumer registration for such products.
15 U.S.C. 2056a(b) and (d).1 In 2009, the
Commission issued a regulation to
implement the second requirement, i.e.,
that manufacturers provide a means for
consumers to register ‘‘durable infant or
toddler products’’ so that consumers can
receive direct notification in the event
of a product recall. The rule is codified
at 16 CFR part 1130, Requirements for
Consumer Registration of Durable Infant
or Toddler Products (part 1130, or the
consumer registration rule).
1 Since 2009, the Commission has issued final
rules for 23 durable infant or toddler products.
Mandatory standards for durable infant or toddler
products are codified in 16 CFR parts 1215 through
1235, and parts 1237 and 1238. Currently, part 1236
is reserved for Inclined Infant Sleep Products, a
proposed rule that has not been finalized.
E:\FR\FM\24SER1.SGM
24SER1
]]>Agencies
[Federal Register Volume 84, Number 185 (Tuesday, September 24, 2019)]
[Rules and Regulations]
[Pages 49944-49947]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-20599]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0692; Product Identifier 2018-NE-19-AD; Amendment
39-19735; AD 2019-18-08]
RIN 2120-AA64
Airworthiness Directives; Engine Alliance Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2019-16-04
for all Engine Alliance (EA) GP7270 and GP7277 model turbofan engines.
AD 2019-16-04 required a visual inspection of the 1st-stage low-
pressure compressor (LPC) rotor assembly, referred to after this as the
``engine fan hub assembly,'' for damage, a one-time eddy current
inspection (ECI) of the engine fan hub blade slot bottom and blade slot
front edge for cracks; and removal of parts if damage or defects are
found. AD 2019-16-04 also required replacement of the engine fan hub
blade lock assembly for certain GP7270 and GP7277 model turbofan
engines. This AD, for certain GP7270 and GP7277 model turbofan engines,
reduces the compliance time for the initial ECI and requires repetitive
ECIs of the engine fan hub blade slot bottom and blade slot front edge
for cracks. This AD also retains the visual inspection requirements of
the engine fan hub assembly for all GP7270 and GP7277 model turbofan
engines. This AD was prompted by an uncontained failure of the engine
fan hub. The FAA is issuing this AD to address the unsafe condition on
these products.
DATES: This AD is effective October 9, 2019.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 9,
2019.
The FAA must receive any comments on this AD by November 8, 2019.
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.
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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this final rule, contact
Engine Alliance, 411 Silver Lane, East Hartford, CT 06118; phone: 800-
565-0140; email: [email protected]; website:
www.engineallianceportal.com. You may view this service information at
the FAA, Engine and Propeller Standards Branch, 1200 District Avenue,
Burlington, MA 01803. For information on the availability of this
material at the FAA, call 781-238-7759. It is also available on the
internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2019-0692.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0692; 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 regulatory evaluation, any comments received, and
other information. The street address for Docket Operations is listed
above. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Matthew Smith, Aerospace Engineer, ECO
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7735; fax: 781-238-7199; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued AD 2019-16-04, Amendment 39-19707 (84 FR 41617,
August 15, 2019), (``AD 2019-16-04''), for all EA GP7270 and GP7277
model turbofan engines. AD 2019-16-04 required a visual inspection of
the engine fan hub assembly for damage, a one-time ECI of the engine
fan hub blade slot bottom and blade slot front edge for cracks, and
removal of parts if damage or defects are found that are outside
serviceable limits. AD 2019-16-04 required an independent inspection of
the engine fan hub assembly prior to reassembly of the engine fan hub
blade lock assembly. AD 2019-16-04 also required replacement of the
engine fan hub blade lock assembly for certain serial-numbered GP7270
and GP7277 model turbofan engines. AD 2019-16-04 resulted from the
manufacturer's determination that an independent inspection of the fan
hub assembly for damage was necessary prior to the reassembly of the
engine fan hub blade lock assembly for all EA GP7270 and GP7277 model
turbofan engines. The FAA issued AD 2019-16-04 to detect defects,
damage, and cracks that could result in an uncontained failure of the
engine fan hub assembly.
[[Page 49945]]
Actions Since AD 2019-16-04 Was Issued
Since the FAA issued AD 2019-16-04, the manufacturer identified a
fatigue crack originating inboard of a blade slot after the
manufacturer performed a metallurgical examination of the engine fan
hub that was recovered, related to the September 30, 2017 event. After
performing a risk assessment, the manufacturer determined the need to
reduce the compliance time for the initial ECI and add a repetitive
ECI. The FAA is issuing this AD to address the unsafe condition on
these products.
Related Service Information Under 1 CFR Part 51
The FAA reviewed EA Alert Service Bulletin (ASB) EAGP7-A72-389,
Revision No. 5, dated August 23, 2019. The ASB describes procedures for
ECI of the EA GP7270 and GP7277 model turbofan engines fan hub
assembly. 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.
Other Related Service Information
The FAA reviewed EA ASB EAGP7-A72-418, Revision No. 1, dated
January 11, 2019. The ASB provides guidance on replacement or
modification of the engine fan hub blade lock assembly.
The FAA also reviewed the following service information:
Subtask 72-31-42-210-001-A, of Task 72-31-42-000-802-A, from the
A380 Aircraft Maintenance Manual (AMM). This subtask describes an on-
wing visual inspection that is to be performed after removal of the
engine fan hub blade lock assembly.
Figure 405 of Task 72-00-31-420-004 of the EA GP7000 Series Engine
Manual (EM). This figure and task describe a visual inspection that is
to be performed after removal of the engine fan hub blade lock assembly
when the engine is in the shop.
Subtask 72-00-00-210-012-A, of Task 72-00-00-210-806-A, from the
A380 Aircraft Maintenance Manual (AMM). This subtask describes an on-
wing visual inspection that is to be performed after reassembly of the
engine fan hub blade lock assembly.
Task 72-00-31-420-004, Paragraph 1.E.(13), of the GP7000 Series EM
describes a visual inspection that is to be performed after reassembly
of the engine fan hub blade lock assembly when the engine is in the
shop.
Table 601 in Subtask 72-00-00-210-012-A, Task 72-00-00-210-806,
from the A380 AMM or Task 72-00-31-220-010 of the EA GP7000 Series EM.
Table 601 and Task 72-00-31-220-010 provide guidance on acceptable
damage service limits.
FAA's Determination
The FAA is issuing this AD because all the relevant information was
evaluated and the FAA determined the unsafe condition described
previously is likely to exist or develop in other products of the same
type design.
AD Requirements
This AD requires, for certain GP7270 and GP7277 model turbofan
engines, an initial and repetitive ECI of the engine fan hub blade slot
bottom and blade slot front edge for cracks. For all GP7270 and GP7277
model turbofan engines, this AD also requires an independent inspection
of the engine fan hub assembly prior to the reassembly of the engine
fan hub blade lock assembly and a visual inspection of the engine fan
hub assembly for damage. For certain serial-numbered GP7270 and GP7277
model turbofan engines, this AD requires replacement of the engine fan
hub blade lock assembly with a part eligible for installation.
FAA's Justification and Determination of the Effective Date
No domestic operators use this product. Therefore, the FAA finds
good cause that notice and opportunity for prior public comment are
unnecessary. In addition, for the reason stated above, the FAA finds
that good cause exists for making this amendment effective in less than
30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and the FAA did not provide you with notice and an opportunity
to provide your comments before it becomes effective. However, the FAA
invites you to send any written data, views, or arguments about this
final rule. Send your comments to an address listed under the ADDRESSES
section. Include the docket number FAA-2019-0692 and product identifier
2018-NE-19-AD at the beginning of your comments. The FAA specifically
invites comments on the overall regulatory, economic, environmental,
and energy aspects of this final rule. The FAA will consider all
comments received by the closing date and may amend this final rule
because of those comments.
The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact received about this final rule.
Regulatory Flexibility Act
The requirements of the Regulatory Flexibility Act (RFA) do not
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt
a rule without prior notice and comment. Because FAA has determined
that it has good cause to adopt this rule without notice and comment,
RFA analysis is not required.
Costs of Compliance
The FAA estimates that this AD affects zero engines installed on
airplanes of U.S. registry. We have revised the estimate of work hours
to complete the ECI based on updated service information.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
ECI................................... 20 work-hours x $85 per $0 $1,700 $0
hour = $1,700.
Visual inspection..................... 1 work-hour x $85 per 0 85 0
hour = $85.
Replace fan hub blade lock assembly... 25 work-hours x $85 per 28,000 30,125 0
hour = $2,125.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
inspection. The FAA has no way of determining the number of engines
that might need these replacements:
[[Page 49946]]
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replace engine fan hub assembly............... 50 work-hours x $85 per hour = $790,500 $794,750
$4,250.
----------------------------------------------------------------------------------------------------------------
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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to engines, propellers, and
associated appliances to the Manager, Engine and Propeller Standards
Branch, Policy and Innovation Division.
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, and
(2) Will not affect intrastate aviation in Alaska.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends part 39 of the Federal Aviation
Regulations (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 removing Airworthiness Directive (AD)
AD 2019-16-04, Amendment 39-19707 (84 FR 41617, August 15, 2019), and
adding the following new AD:
2019-18-08 Engine Alliance: Amendment 39-19735; Docket No. FAA-2019-
0692; Product Identifier 2018-NE-19-AD.
(a) Effective Date
This AD is effective October 9, 2019.
(b) Affected ADs
This AD replaces AD 2019-16-04, Amendment 39-19707 (84 FR 41617,
August 15, 2019) (``AD 2019-16-04'').
(c) Applicability
This AD applies to all Engine Alliance (EA) GP7270 and GP7277
model turbofan engines.
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine Engine
Compressor Section.
(e) Unsafe Condition
This AD was prompted by an uncontained failure of the engine fan
hub. The FAA is issuing this AD to detect defects, damage, and
cracks that could result in an uncontained failure of the engine fan
hub assembly. The unsafe condition, if not addressed, could result
in uncontained failure of the engine fan hub assembly, damage to the
engine, and damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) For EA GP7270 and GP7277 model turbofan engines with engine
fan hub assembly part numbers (P/Ns) 5760221 or 5760321, within
1,700 cycles since new, or within 150 flight cycles (FCs) after the
effective date of this AD, or within 330 FCs since an eddy current
inspection (ECI) was performed in accordance with the Accomplishment
Instructions, For Fan Hubs at LPC Module Assembly Level, paragraphs
2.A and 2.B, of EA ASB EAGP7-A72-389, Revision No. 4, dated June 14,
2019, or earlier versions of that ASB; or within 330 FCs since
overhaul, whichever occurs later:
(i) For engine fan hub assemblies at the low-pressure compressor
(LPC) module assembly level, perform an ECI of the engine fan hub
blade slot bottoms and front edges in accordance with the
Accomplishment Instructions, For Fan Hubs at LPC Module Assembly
Level, paragraphs 1.B. and 1.C., of EA ASB EAGP7-A72-389, Revision
No. 5, dated August 23, 2019.
(ii) For engine fan hub assemblies at the piece part level,
perform an ECI of the engine fan hub blade slot bottoms and front
edges, in accordance with the Accomplishment Instructions, For Fan
Hubs at Piece Part Level, paragraphs 1.A. and 1.B., of EA ASB EAGP7-
A72-389, Revision No. 5, dated August 23, 2019.
(iii) For engine fan hub assemblies installed in an engine (on-
wing or off-wing), perform an ECI of the engine fan hub blade slot
bottoms and front edges, in accordance with the Accomplishment
Instructions, For Fan Hubs Installed in an Engine, paragraphs 3.B.
and 3.C., of EA ASB EAGP7-A72-389, Revision No. 5, dated August 23,
2019.
(iv) Thereafter, repeat the ECI of the engine fan hub blade slot
bottoms and front edges at intervals not exceeding 330 FCs since the
previous ECI required by paragraphs (g)(1)(i) through (iii) of this
AD, as applicable.
(v) If any ECI of the engine fan hub assembly results in a
rejectable indication per the Appendix, Added Data, of EA ASB EAGP7-
A72-389, Revision No. 5, dated August 23, 2019, remove the engine
fan hub assembly from service and, before further flight, replace
with a part that is eligible for installation.
(2) For all GP7270 and GP7277 model turbofan engines, after the
effective date of this AD:
(i) At the next disassembly of the engine fan hub blade lock
assembly, visually inspect the following areas for damage:
(A) The fan hub blade lock retention hooks (also known as lock
ring contact area); and
(B) The fan hub rim face.
(ii) At the next reassembly of the fan hub blade lock assembly,
visually inspect the following areas of the engine fan hub for
damage:
(A) The fan hub scallop areas;
(B) The fan hub bore area behind the balance flange;
(C) The fan hub fan blade lock retention hooks;
(D) The fan hub rim face; and
(E) The clinch nut holes.
(iii) After any reassembly per paragraph (g)(2)(ii), before
further flight, perform an
[[Page 49947]]
independent inspection of all areas of the engine fan hub referenced
in paragraph (g)(2)(ii) of this AD for damage.
(iv) Thereafter, repeat the inspections required by paragraphs
(g)(2)(i) through (iii) of this AD at each disassembly and
reassembly of the engine fan hub blade lock assembly.
(v) As an optional terminating action to the inspection
requirements and independent inspection requirements of paragraph
(g)(2)(i) through (iii) of this AD, insert the requirements for the
visual inspections and independent inspections required by these
paragraphs as Required Inspection Items in the approved continuous
airworthiness maintenance program for the airplane.
(vi) If damage is found outside serviceable limits during the
inspections required by (g)(2)(i) through (iii) of this AD, before
further flight, remove the engine fan hub assembly from service and
replace it with a part eligible for installation.
(3) For GP7270 and GP7277 model turbofan engines with engine
serial numbers P550101 through P550706, remove the engine fan hub
blade lock assembly, P/N 5700451, by September 1, 2020, and replace
with a part eligible for installation. Refer to EA ASB EAGP7-A72-
418, Revision No. 1, dated January 11, 2019, for guidance on
replacement of the engine fan hub blade lock assembly.
(h) Credit for Previous Actions
You may take credit for the inspections required by paragraph
(g)(1)(i) through (iii) of this AD if you performed the inspections
before the effective date of this AD using EA ASB EAGP7-A72-389,
Revision No. 4, dated June 14, 2019, or an earlier version.
(i) Definitions
(1) For the purpose of this AD, a part eligible for installation
for replacement of the engine fan hub blade lock assembly is:
(i) A part that is not P/N 5700451, or
(ii) An engine fan hub blade lock assembly that has been
modified in accordance with EA ASB EAGP7-A72-418, Revision No. 1,
dated January 11, 2019, or EA ASB EAGP7-A72-418, Revision No. 0,
dated December 7, 2018.
(2) For the purpose of this AD, an independent inspection is a
second visual inspection performed by an individual qualified to
perform inspections who was not involved in the original inspection
of the engine fan hub assembly following disassembly and reassembly
of the engine fan hub blade lock assembly.
(j) 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 (k) of this AD. You may email your request
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.
(3) AMOCs approved for AD 2019-16-04, AD 2018-11-16 (83 FR
27891, June 15, 2018), and AD 2019-03-04 (84 FR 4694, February 19,
2019) are approved as AMOCs for the corresponding provisions of this
AD.
(k) Related Information
For more information about this AD, contact Matthew Smith,
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: 781-238-7735; fax: 781-238-7199; email:
[email protected].
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Engine Alliance (EA) Alert Service Bulletin EAGP7-A72-389,
Revision No. 5, dated August 23, 2019.
(ii) [Reserved]
(3) For EA service information identified in this AD, contact
Engine Alliance, 411 Silver Lane, East Hartford, CT 06118; phone:
800-565-0140; email: [email protected]; website:
www.engineallianceportal.com.
(4) You may view this service information at the FAA, Engine &
Propeller Standards Branch, 1200 District Avenue, Burlington, MA
01803. For information on the availability of this material at the
FAA, call 781-238-7759.
(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 in Burlington, Massachusetts, on September 18, 2019.
Karen M. Grant,
Acting Manager, Engine & Propeller Standards Branch, Aircraft
Certification Service.
[FR Doc. 2019-20599 Filed 9-23-19; 8:45 am]
BILLING CODE 4910-13-P
