Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by Rolls-Royce plc) Turbofan Engines, 21233-21237 [2021-07660]
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Federal Register / Vol. 86, No. 76 / Thursday, April 22, 2021 / Proposed Rules
2. Will not affect intrastate aviation in
Alaska, and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The 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:
a. Removing Airworthiness Directive
(AD) 2014–11–02, Amendment 39–
17852 (79 FR 33050, June 10, 2014); and
■ b. Adding the following new AD:
■
■
Airbus Helicopters: Docket No. FAA–2021–
0195; Project Identifier MCAI–2020–
00262–R.
(a) Applicability
This airworthiness directive (AD) applies
to Airbus Helicopters Model SA–365N, SA–
365N1, AS–365N2, and AS–365–N3
helicopters, certificated in any category,
except helicopters with Eurocopter
modification (MOD) 53C17 or MOD 53D02,
or Airbus Helicopters MOD 07 53D21 or
MOD 07 53D22, installed.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in frame number (No.) 9, which if not
detected and corrected, could result in failure
of frame No. 9, loss of structural integrity,
and subsequent loss of control of the
helicopter.
(c) Affected ADs
This AD replaces AD 2014–11–02,
Amendment 39–17852 (79 FR 33050, June
10, 2014).
(d) Comments Due Date
The FAA must receive comments by June
7, 2021.
(e) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(f) Required Actions
(1) For helicopters that have any repair or
alteration to the frame No. 9, within 10 hours
time-in-service (TIS) after the effective date
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17:20 Apr 21, 2021
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of this AD and thereafter at intervals not to
exceed 110 hours TIS, using a 10X or higher
power magnifying glass, inspect the left-hand
(LH) and right-hand (RH) frame No. 9 for a
crack in the area of the latch support and
stretcher support, as depicted in Figure 1 of
Airbus Helicopters Emergency Alert Service
Bulletin No. 05.00.63, Revision 2, dated
December 20, 2018 (EASB 05.00.63).
(2) For all other helicopters, within 110
hours TIS after the effective date of this AD
and thereafter at intervals not to exceed 110
hours TIS, perform the inspection in
paragraph (f)(1) of this AD.
(3) If there is a crack, before further flight,
repair the frame No. 9. Repairing a frame is
not terminating action for the repetitive
inspections required by paragraphs (f)(1) and
(2) of this AD.
(4) As an optional terminating action for
the repetitive inspections required by
paragraphs (f)(1) and (2) of this AD, replace
the upper section of frame No. 9 with a
reinforced frame, Eurocopter MOD 53C17 or
MOD 53D02, or Airbus Helicopters MOD 07
53D21 or MOD 07 53D22.
technical-support.html. You may view this
referenced service information at the FAA,
Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room 6N–
321, Fort Worth, TX 76177. For information
on the availability of this material at the
FAA, call (817) 222–5110.
(3) The subject of this AD is addressed in
European Union Aviation Safety Agency
(EASA) AD 2012–0108R1, dated September
19, 2019. You may view the EASA AD on the
internet at https://www.regulations.gov in
Docket No. FAA–2021–0195.
(g) Special Flight Permits
Special flight permits to a repair facility
may be issued provided that the flight does
not exceed 10 hours TIS, any crack does not
exceed a maximum crack length of 80 mm,
and no passengers are onboard.
DEPARTMENT OF TRANSPORTATION
(h) Credit for Previous Actions
You may take credit for the actions
required by paragraphs (f)(1) and (2) of this
AD if you performed them before the
effective date of this AD using Eurocopter
Emergency Alert Service Bulletin No.
05.00.63, Revision 1, dated June 18, 2012.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, International Validation
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the International Validation
Branch office, send it to the attention of the
person identified in paragraph (j)(1) of this
AD. Information may be emailed to: 9-AVSAIR-730-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 Matthew Fuller, AD Program
Manager, General Aviation & Rotorcraft Unit,
Airworthiness Products Section, Operational
Safety Branch, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone (817) 222–
5110; email matthew.fuller@faa.gov.
(2) For service information identified in
this AD, contact Airbus Helicopters, 2701 N
Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–0323;
fax (972) 641–3775; or at https://
www.airbus.com/helicopters/services/
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(k) Subject
Joint Aircraft Service Component (JASC)
Code: 5300: Fuselage Structure.
Issued on March 19, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–08183 Filed 4–21–21; 8:45 am]
BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0306; Project
Identifier MCAI–2020–01493–E]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Deutschland Ltd & Co KG (Type
Certificate Previously Held by RollsRoyce plc) Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede Airworthiness Directive (AD)
2020–15–12, which applies to certain
Rolls-Royce Deutschland Ltd & Co KG
(RRD) Trent 1000 model turbofan
engines. AD 2020–15–12 requires initial
and repetitive ultrasonic or visual
inspections of the intermediate-pressure
compressor (IPC) stage 1 rotor blade root
(front face), IPC stage 2 rotor blade root
(front and rear face), and IPC shaft stage
2 dovetail post (front face), and removal
of any cracked parts from service. AD
2020–15–12 also requires an inspection
after asymmetric power and cabin
depressurization events. Since the FAA
issued AD 2020–15–12, the
manufacturer introduced IPC stage 1
and stage 2 rotor blades in kitted sets,
which terminate the need for initial and
repetitive ultrasonic or visual
inspections for certain IPC parts. This
proposed AD would continue to require
initial and repetitive ultrasonic or visual
inspections of certain IPC parts until
replacement of the IPC stage 1 and stage
SUMMARY:
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2 rotor blades with redesigned IPC stage
1 and stage 2 rotor blades in kitted sets.
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 June 7, 2021.
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: 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 Rolls-Royce plc,
Corporate Communications, P.O. Box
31, Derby, DE24 8BJ, United Kingdom;
phone: +44 (0)1332 242424; fax: +44
(0)1332 249936; email: https://
www.rolls-royce.com/contact-us/civilaerospace.aspx; website: https://
www.rolls-royce.com/contact-us.aspx.
You may view this 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 (781) 238–7759.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0306; 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 mandatory continuing
airworthiness information (MCAI), any
comments received, and other
information. The street address for
Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Kevin Clark, Aviation Safety Engineer,
ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone:
(781) 238–7088; fax: (781) 238–7199;
email: kevin.m.clark@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.
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17:20 Apr 21, 2021
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FAA–2021–0306; Project Identifier
MCAI–2020–01493–E’’ 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 NPRM
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 proposed
AD.
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 Kevin Clark, Aviation
Safety Engineer, ECO Branch, FAA,
1200 District Avenue, Burlington, MA
01803. Any commentary that the FAA
receives which is not specifically
designated as CBI will be placed in the
public docket for this rulemaking.
Background
The FAA issued AD 2020–15–12,
Amendment 39–21175 (85 FR 45081,
July 27, 2020), (AD 2020–15–12), for
certain RRD Trent 1000–A2, Trent
1000–AE2, Trent 1000–C2, Trent 1000–
CE2, Trent 1000–D2, Trent 1000–E2,
Trent 1000–G2, Trent 1000–H2, Trent
1000–J2, Trent 1000–K2, and Trent
1000–L2 model turbofan engines. AD
2020–15–12 was prompted by IPC rotor
blade separations resulting in engine
failures. Subsequently, the manufacturer
identified the need to add new
inspections and an optional terminating
action, amend the asymmetric power
condition for engine inspection, and to
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add an inspection after a cabin
depressurization event. AD 2020–15–12
requires initial and repetitive ultrasonic
or visual inspections of the IPC stage 1
rotor blade root (front face), IPC stage 2
rotor blade root (front and rear face),
and IPC shaft stage 2 dovetail posts
(front face), and removal of any cracked
parts from service. AD 2020–15–12 also
requires an inspection after asymmetric
power and cabin depressurization
events. The agency issued AD 2020–15–
12 to prevent failure of the IPC rotor
blades.
Actions Since AD 2020–15–12 Was
Issued
Since the FAA issued AD 2020–15–
12, the European Union Aviation Safety
Agency (EASA), which is the Technical
Agent for the Member States of the
European Community, has issued EASA
AD 2020–0240, dated November 5, 2020
(referred to after this as ‘‘the MCAI’’), to
address the unsafe condition on these
products. The MCAI states:
Occurrences were reported on RollsRoyce Trent 1000 ‘Pack C’ engines,
where some IPC Rotor 1 and Rotor 2
blades were found cracked.
This condition, if not detected and
corrected, could lead to in-flight blade
release, possibly resulting in reduced
control of the aeroplane.
To address this potential unsafe
condition, Rolls-Royce initially issued
Alert NMSB TRENT 1000 72–AJ814 and
72–AJ819 to provide inspection
instructions for IPC Rotor 1 blades, and
IPC Rotor 2 blades and IPC shaft Stage
2 dovetail posts, respectively. RollsRoyce also issued NMSB TRENT 1000
72–J871 to provide rework instructions
for the affected parts, and Alert NMSB
TRENT 1000 72–AJ869 to inspect those
post-rework parts.
Consequently, EASA issued AD 2017–
0248 to require repetitive inspections of
the affected IPC Rotor blades and IPC
shaft Stage 2 dovetail posts and,
depending on findings, removal from
service of the engine for corrective
action.
After that [EASA] AD was issued,
Rolls-Royce issued Alert NMSB TRENT
1000 72–AK058 to provide instructions
for a one-time on-wing inspection.
Consequently, EASA issued AD 2018–
0073, retaining the requirements of
EASA AD 2017–0248, which was
superseded, to require an additional
borescope inspection of certain engines
and, depending on findings, removal
from service of the engine for corrective
action.
After that [EASA] AD was issued, it
was determined that repetitive
borescope inspections are necessary on
all engines to ensure fleet-wide
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continued safe operation. Consequently,
Rolls-Royce revised Alert NMSB TRENT
1000 72–AJ869, Alert NMSB TRENT
1000 72–AJ814, Alert NMSB TRENT
1000 72–AJ819 and NMSB TRENT 1000
72–J871, and issued NMSB TRENT 1000
72–AK060 to consolidate all inspection
instructions. Consequently, EASA
issued AD 2018–0084 (later revised),
retaining the requirements of EASA AD
2018–0073, which was superseded, and
requiring repetitive on-wing borescope
inspections of the affected Rotor 1 parts
and affected Rotor 2 parts and,
depending on findings, removal from
service of the engine for corrective
action. That AD also introduced specific
requirements for engines installed on
aeroplanes involved in ETOPS, and
inspection following operation in
asymmetric power conditions.
Rolls-Royce then introduced NMSB
Trent 1000 72–AK092 to provide
inspections for the rear face of the Rotor
2 blades and NMSB TRENT 1000 72–
AK060 was revised (R1) accordingly.
Later, Rolls-Royce developed mod 72–
J941, installing improved IPC Stage 1
and Stage 2 rotor blades, and issued the
modification SB, providing the
necessary instructions for in-service
application. EASA issued AD 2018–
0084R2 to exclude post-mod 72–J941
engines from the Applicability and
introducing the modification SB as
terminating action for the repetitive
inspections as required by that [EASA]
AD.
After that [EASA] AD was issued,
Rolls-Royce issued NMSB TRENT 1000
72–AK313 and revised Alert NMSB
TRENT 1000 72–AJ814, 72–AJ819 and
72–AK092 to introduce new
inspections, new thresholds and new
intervals, depending on engine
configuration. These inspections are for
all operations, ETOPS and non-ETOPS.
The latest revision of the NMSB also
amended the asymmetric power
conditions for engine inspection and
introduced cabin depressurisation as an
event to trigger engine inspection(s).
Consequently, EASA issued AD 2019–
0250 to require introduction of the new
inspections, replacing those previously
imposed by EASA AD 2018–0084R2
(through NMSB TRENT 1000 72–
AK060), and to remove the references to
Engine Health Monitoring messages and
ETOPS-related requirements.
Since that [EASA] AD was issued, it
was discovered that the manufacturing
distribution of the individual blade
frequencies could differ from the
assumed values during certification of
the SB TRENT 1000 72–J941, which
means there may not be sufficient
margin to prevent the blades from
experiencing high vibration levels.
Prompted by these findings, Rolls-Royce
issued the modification SB to provide
blade kitting instructions.
You may obtain further information
by examining the MCAI in the AD
docket at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0306.
FAA’s Determination
This product has been approved by
EASA and is approved for operation in
the United States. Pursuant to our
bilateral agreement with the European
Community, EASA has notified the FAA
of the unsafe condition described in the
MCAI and service information. The
FAA is issuing this NPRM because the
agency evaluated all the relevant
information provided by EASA and
determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Rolls-Royce Alert
Non-Modification Service Bulletin
(NMSB) Trent 1000 72–AK313, Revision
1, dated August 22, 2019; and RollsRoyce Alert Service Bulletin (SB) Trent
1000 72–AK430, Initial Issue, dated
August 17, 2020. Rolls-Royce Alert
NMSB Trent 1000 72–AK313 defines
the initial inspection threshold and
repeat inspection intervals for Trent
1000 IPC stage 1 rotor blade, IPC stage
2 rotor blade, and IPC shaft stage 2
dovetail posts. Rolls-Royce Alert SB
Trent 1000 72–AK430 introduces the
IPC stage 1 and stage 2 rotor blades in
kitted sets and provides kitting
instructions. 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
ADDRESSES.
21235
Other Related Service Information
The FAA reviewed Rolls-Royce Alert
NMSB Trent 1000 72–AJ814, Revision 5,
dated May 3, 2019; Rolls-Royce Alert
NMSB Trent 1000 72–AJ819, Revision 4,
dated May 3, 2019; Rolls-Royce Alert
NMSB Trent 1000 72–AK092, Revision
4, dated May 3, 2019; Rolls-Royce SB
Trent 1000 72–J871, Revision 6, dated
December 12, 2019; and Rolls-Royce SB
Trent 1000 72–J941, Revision 1, dated
February 6, 2019.
Rolls-Royce Alert NMSB Trent 1000
72–AJ814 describes procedures for
performing an ultrasonic inspection
(USI) of the IPC stage 1 rotor blades.
Rolls-Royce Alert NMSB Trent 1000 72–
AJ819 describes procedures for
performing a visual borescope
inspection of the IPC stage 2 rotor
blades and IPC shaft stage 2 dovetail
posts. Rolls-Royce Alert NMSB Trent
1000 72–AK092 describes procedures
for performing a USI of the IPC stage 2
rotor blades. Rolls-Royce SB Trent 1000
72–J871 describes procedures for
reworking or replacing the affected
parts. Rolls-Royce SB Trent 1000 72–
J941 describes procedures for installing
the redesigned IPC stage 1 and stage 2
rotor blades.
Proposed AD Requirements in This
NPRM
This proposed AD would retain
certain requirements of AD 2020–15–12.
This proposed AD would continue to
require initial and repetitive ultrasonic
or visual inspection of the IPC stage 1
rotor blade root (front face), IPC stage 2
rotor blade root (front and rear face),
and IPC shaft stage 2 dovetail post (front
face), removal of any cracked parts from
service, and an inspection after
asymmetric power and cabin
depressurization events until the
installation of the IPC stage 1 and stage
2 rotor blades in kitted sets. As a
terminating action, this AD would
require replacement of IPC stage 1 and
stage 2 rotor blades with IPC stage 1 and
stage 2 rotor blades in kitted sets.
Costs of Compliance
The FAA estimates that this AD, if
adopted as proposed, would affect 7
engines installed on airplanes of U.S.
registry.
The FAA estimates the following
costs to comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Inspect the IPC stage 1 rotor blade root
(Front Face).
20 work-hours × $85 per hour = $1,700 ........
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Cost per
product
Parts cost
E:\FR\FM\22APP1.SGM
$0
22APP1
$1,700
Cost on U.S.
operators
$11,900
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Federal Register / Vol. 86, No. 76 / Thursday, April 22, 2021 / Proposed Rules
ESTIMATED COSTS—Continued
Cost per
product
Labor cost
Inspect the IPC stage 2 rotor blade root
(Front Face) and IPC shaft stage 2 dovetail
post (Front Face).
Inspect the IPC stage 2 rotor blade root
(Rear Face).
Replace all 34 IPC stage 1 rotor blades
(mandatory terminating action).
Replace all 49 IPC stage 2 rotor blades
(mandatory terminating action).
6 work-hours × $85 per hour = $510 .............
0
510
3,570
10 work-hours × $85 per hour = $850 ...........
0
850
5,950
280 work-hours × $85 per hour = $23,800 ....
52,360
76,160
533,120
280 work-hours × $85 per hour = $23,800 ....
48,755
72,555
507,885
The FAA estimates the following
costs to do any necessary replacements
that would be required based on the
Parts cost
Cost on U.S.
operators
Action
results of the proposed inspection. The
agency has no way of determining the
number of aircraft that might need these
replacements:
ON-CONDITION COSTS
Action
Labor cost
Replace all 34 IPC stage 1 rotor blades ......................
Replace all 49 IPC stage 2 rotor blades ......................
Replace the IPC drum assembly .................................
280 work-hours × $85 per hour = $23,800 ..................
280 work-hours × $85 per hour = $23,800 ..................
144 work-hours × $85 per hour = $12,240 ..................
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 has 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 that the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
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17:20 Apr 21, 2021
Jkt 253001
(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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
Parts cost
$52,360
48,755
1,370,000
Cost per
product
$76,160
72,555
1,382,240
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) action by June 7,
2021.
(b) Affected ADs
This AD replaces AD 2020–15–12,
Amendment 39–21175 (85 FR 45081, July 27,
2020).
(c) Applicability
This AD applies to Rolls-Royce
Deutschland Ltd & Co KG (Type Certificate
previously held by Rolls-Royce plc) Trent
1000–A2, Trent 1000–AE2, Trent 1000–C2,
Trent 1000–CE2, Trent 1000–D2, Trent 1000–
E2, Trent 1000–G2, Trent 1000–H2, Trent
1000–J2, Trent 1000–K2, and Trent 1000–L2
model turbofan engines, except those that
have the redesigned intermediate-pressure
compressor (IPC) stage 1 and stage 2 rotor
blades introduced by Rolls-Royce (RR)
Service Bulletin (SB) Trent 1000 72–J941,
Initial Issue, dated December 6, 2016, or
Revision 1, dated February 6, 2019.
(d) Subject
Joint Aircraft System Component (JASC)
Code 7230, Turbine Engine Compressor
Section.
(e) Unsafe Condition
■
2. The FAA amends § 39.13 by:
■ a. Removing Airworthiness Directive
AD 2020–15–12, Amendment 39–21175
(85 FR 45081, July 27, 2020); and
■ b. Adding the following new
airworthiness directive:
This AD was prompted by IPC rotor blade
separations resulting in engine failures. The
FAA is issuing this AD to prevent failure of
the IPC. The unsafe condition, if not
addressed, could result in failure of one or
more engines, loss of thrust control, and loss
of the airplane.
Rolls-Royce Deutschland Ltd & Co KG (Type
Certificate previously held by RollsRoyce plc): Docket No. FAA–2021–0306;
Project Identifier MCAI–2020–01493–E.
(f) Compliance
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Comply with this AD within the
compliance times specified, unless already
done.
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22APP1
Federal Register / Vol. 86, No. 76 / Thursday, April 22, 2021 / Proposed Rules
(g) Required Actions
(1) After the effective date of this AD,
before exceeding the initial inspection
thresholds and repeat inspection intervals
specified in Table 1 of RR Alert NonModification Service Bulletin (NMSB) Trent
1000 72–AK313, Revision 1, dated August
22, 2019 (RR NMSB Trent 1000 72–AK313
R1):
(i) Perform initial ultrasonic inspections
(USIs) of the IPC stage 1 rotor blade root
(front face).
(ii) Thereafter, perform repetitive USIs of
the IPC stage 1 rotor blade root (front face).
(iii) Use the Accomplishment Instructions,
paragraph 3.A.(1)(a) (on-wing) or 3.A.(2)(a)
and (b) (in-shop), of RR NMSB Trent 1000
72–AK313 R1 to perform the inspections.
(2) After the effective date of this AD,
before exceeding the initial inspection
thresholds and repeat inspection intervals
specified in Table 2 of RR NMSB Trent 1000
72–AK313 R1:
(i) Perform initial visual inspections of the
IPC stage 2 rotor blade root (front face) and
IPC shaft stage 2 dovetail post (front face).
(ii) Thereafter, perform repetitive visual
inspections of the IPC stage 2 rotor blade root
(front face) and IPC shaft stage 2 dovetail post
(front face).
(iii) Use the Accomplishment Instructions,
paragraph 3.B.(1)(a) (on-wing) or 3.B.(2)(b)
(in-shop), of RR NMSB Trent 1000 72–AK313
R1 to perform the inspections.
(3) After the effective date of this AD,
before exceeding the initial inspection
threshold and repeat inspection intervals
specified in Table 2 of RR NMSB Trent 1000
72–AK313 R1:
(i) Perform initial USIs of IPC stage 2 rotor
blade root (rear face).
(ii) Thereafter, perform repetitive USIs of
IPC stage 2 rotor blade root (rear face).
(iii) Use the Accomplishment Instructions,
paragraph 3.C.(1)(a) (on-wing) or 3.C.(2)(a)
(in-shop), of RR NMSB Trent 1000 72–AK313
R1 to perform the inspections.
(4) After the effective date of this AD,
within 5 engine flight cycles (FCs) after each
occurrence in which any engine operates in
asymmetric power conditions at an altitude
of less than 28,000 feet, perform the
following inspections on the engine not
affected by the power reduction or in-flight
shutdown (IFSD):
(i) Perform initial USIs and visual
inspections required by paragraphs (g)(1)
through (3) of this AD.
(ii) Thereafter, perform the repetitive USIs
and visual inspections required by
paragraphs (g)(1) through (3) of this AD.
(iii) Use the service information and
repetitive inspection thresholds required by
paragraphs (g)(1)(iii), (2)(iii), and (3)(iii) to
perform the inspections, as applicable.
(5) After the effective date of this AD,
within 5 engine FCs following a cabin
depressurization event, perform the
following inspections on both engines
installed on the airplane:
(i) Perform initial USIs and visual
inspections required by paragraphs (g)(1)
through (3) of this AD.
(ii) Thereafter, perform the repetitive USIs
and visual inspections required by
paragraphs (g)(1) through (3) of this AD.
VerDate Sep<11>2014
17:20 Apr 21, 2021
Jkt 253001
(iii) Use the service information and
repetitive inspection thresholds required by
paragraphs (g)(1)(iii), (2)(iii), and (3)(iii) to
perform the inspections, as applicable.
(6) If any IPC stage 1 rotor blade root (front
face), IPC stage 2 rotor blade root (front face),
or IPC stage 2 rotor blade root (rear face) is
found cracked during any inspection
required by this AD, replace the part with a
part eligible for installation before further
flight.
(7) If any IPC shaft stage 2 dovetail post
(front face) is found cracked during any
inspection required by this AD, replace the
IPC drum assembly.
(h) Mandatory Terminating Action
At the next engine shop visit after the
effective date of this AD, replace the IPC
stage 1 and stage 2 rotor blades with
redesigned IPC stage 1 and stage 2 rotor
blades introduced by RR SB Trent 1000 72–
J941, Revision 1, dated February 6, 2019.
Install the blades as kitted sets using the
Accomplishment Instructions, paragraph 3.C.
(In-Shop), of RR Alert SB Trent 1000 72–
AK430, Initial Issue, dated August 17, 2020.
This replacement of the IPC stage 1 and stage
2 rotor blades as kitted sets is a terminating
action for the initial and repetitive ultrasonic
or visual inspection requirements, as
applicable, required by paragraphs (g)(1)
through (5) of this AD.
(i) Definitions
(1) For the purpose of this AD, an
‘‘asymmetric power condition’’ is the
operation of the airplane at an altitude of less
than 28,000 feet, experiencing either single
engine take-off, engine fault (reduced power
on one engine), or single engine IFSD, which
includes execution of any non-normal
checklist procedure.
(2) For the purpose of this AD, an ‘‘engine
shop visit’’ is the induction of an engine into
the shop for maintenance involving the
separation of pairs of major mating engine
case flanges, except that the separation of
engine flanges solely for the purposes of
transportation without subsequent engine
maintenance does not constitute an engine
shop visit.
(j) Credit for Previous Actions
You may take credit for the initial
inspections required by paragraphs (g)(1)
through (5) of this AD if you performed these
inspections before the effective date of this
AD using any of the following.
(1) RR Alert NMSB Trent 1000 72–AJ819,
Revision 3, dated April 13, 2018, or earlier
revisions;
(2) RR Alert NMSB Trent 1000 72–AJ814,
Revision 4, dated September 28, 2018, or
earlier revisions;
(3) RR Alert NMSB Trent 1000 72–AK313,
Initial Issue, dated May 2, 2019; or
(4) RR Alert NMSB Trent 1000 72–AK092,
Revision 3, dated February 28, 2019, or
earlier revisions.
(k) Special Flight Permit
Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), are subject to the requirements
of paragraph (k)(1) of this AD.
PO 00000
Frm 00010
Fmt 4702
Sfmt 9990
21237
(1) Operators who are prohibited from
further flight due to a crack finding as a
result of paragraph (g) of this AD, may
perform a one-time non-revenue ferry flight
to a location where the engine can be
removed from service. This ferry flight must
be performed without passengers, involve
non-ETOPS operation, and consume no more
than three FCs.
(2) [Reserved]
(l) 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 Related Information. You may
email your request 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.
(m) Related Information
(1) For more information about this AD,
contact Kevin Clark, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: (781)
238–7088; fax: (781) 238–7199; email:
kevin.m.clark@faa.gov.
(2) Refer to European Union Aviation
Safety Agency (EASA) AD 2020–0240, dated
November 5, 2020, for more information. You
may examine the EASA AD in the AD docket
at https://www.regulations.gov by searching
for and locating it in Docket No. FAA–2021–
0306.
(3) For service information identified in
this AD, contact Rolls-Royce plc, Corporate
Communications, P.O. Box 31, Derby, DE24
8BJ, United Kingdom; phone: +44 (0)1332
242424; fax: +44 (0)1332 249936; email:
https://www.rolls-royce.com/contact-us/civilaerospace.aspx; website: https://www.rollsroyce.com/contact-us.aspx. 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 (781) 238–7759.
Issued on April 9, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–07660 Filed 4–21–21; 8:45 am]
BILLING CODE 4910–13–P
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22APP1
]]>Agencies
[Federal Register Volume 86, Number 76 (Thursday, April 22, 2021)]
[Proposed Rules]
[Pages 21233-21237]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-07660]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0306; Project Identifier MCAI-2020-01493-E]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG
(Type Certificate Previously Held by Rolls-Royce plc) Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2020-15-12, which applies to certain Rolls-Royce Deutschland Ltd & Co
KG (RRD) Trent 1000 model turbofan engines. AD 2020-15-12 requires
initial and repetitive ultrasonic or visual inspections of the
intermediate-pressure compressor (IPC) stage 1 rotor blade root (front
face), IPC stage 2 rotor blade root (front and rear face), and IPC
shaft stage 2 dovetail post (front face), and removal of any cracked
parts from service. AD 2020-15-12 also requires an inspection after
asymmetric power and cabin depressurization events. Since the FAA
issued AD 2020-15-12, the manufacturer introduced IPC stage 1 and stage
2 rotor blades in kitted sets, which terminate the need for initial and
repetitive ultrasonic or visual inspections for certain IPC parts. This
proposed AD would continue to require initial and repetitive ultrasonic
or visual inspections of certain IPC parts until replacement of the IPC
stage 1 and stage
[[Page 21234]]
2 rotor blades with redesigned IPC stage 1 and stage 2 rotor blades in
kitted sets. 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 June 7,
2021.
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: 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 Rolls-
Royce plc, Corporate Communications, P.O. Box 31, Derby, DE24 8BJ,
United Kingdom; phone: +44 (0)1332 242424; fax: +44 (0)1332 249936;
email: https://www.rolls-royce.com/contact-us/civil-aerospace.aspx;
website: https://www.rolls-royce.com/contact-us.aspx. You may view this
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
(781) 238-7759.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0306; 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
mandatory continuing airworthiness information (MCAI), any comments
received, and other information. The street address for Docket
Operations is listed above.
FOR FURTHER INFORMATION CONTACT: Kevin Clark, Aviation Safety Engineer,
ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone:
(781) 238-7088; fax: (781) 238-7199; 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-2021-0306; Project Identifier
MCAI-2020-01493-E'' 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 NPRM 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 proposed AD.
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 Kevin
Clark, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803. Any commentary that the FAA receives which is not
specifically designated as CBI will be placed in the public docket for
this rulemaking.
Background
The FAA issued AD 2020-15-12, Amendment 39-21175 (85 FR 45081, July
27, 2020), (AD 2020-15-12), for certain RRD Trent 1000-A2, Trent 1000-
AE2, Trent 1000-C2, Trent 1000-CE2, Trent 1000-D2, Trent 1000-E2, Trent
1000-G2, Trent 1000-H2, Trent 1000-J2, Trent 1000-K2, and Trent 1000-L2
model turbofan engines. AD 2020-15-12 was prompted by IPC rotor blade
separations resulting in engine failures. Subsequently, the
manufacturer identified the need to add new inspections and an optional
terminating action, amend the asymmetric power condition for engine
inspection, and to add an inspection after a cabin depressurization
event. AD 2020-15-12 requires initial and repetitive ultrasonic or
visual inspections of the IPC stage 1 rotor blade root (front face),
IPC stage 2 rotor blade root (front and rear face), and IPC shaft stage
2 dovetail posts (front face), and removal of any cracked parts from
service. AD 2020-15-12 also requires an inspection after asymmetric
power and cabin depressurization events. The agency issued AD 2020-15-
12 to prevent failure of the IPC rotor blades.
Actions Since AD 2020-15-12 Was Issued
Since the FAA issued AD 2020-15-12, the European Union Aviation
Safety Agency (EASA), which is the Technical Agent for the Member
States of the European Community, has issued EASA AD 2020-0240, dated
November 5, 2020 (referred to after this as ``the MCAI''), to address
the unsafe condition on these products. The MCAI states:
Occurrences were reported on Rolls-Royce Trent 1000 `Pack C'
engines, where some IPC Rotor 1 and Rotor 2 blades were found cracked.
This condition, if not detected and corrected, could lead to in-
flight blade release, possibly resulting in reduced control of the
aeroplane.
To address this potential unsafe condition, Rolls-Royce initially
issued Alert NMSB TRENT 1000 72-AJ814 and 72-AJ819 to provide
inspection instructions for IPC Rotor 1 blades, and IPC Rotor 2 blades
and IPC shaft Stage 2 dovetail posts, respectively. Rolls-Royce also
issued NMSB TRENT 1000 72-J871 to provide rework instructions for the
affected parts, and Alert NMSB TRENT 1000 72-AJ869 to inspect those
post-rework parts.
Consequently, EASA issued AD 2017-0248 to require repetitive
inspections of the affected IPC Rotor blades and IPC shaft Stage 2
dovetail posts and, depending on findings, removal from service of the
engine for corrective action.
After that [EASA] AD was issued, Rolls-Royce issued Alert NMSB
TRENT 1000 72-AK058 to provide instructions for a one-time on-wing
inspection. Consequently, EASA issued AD 2018-0073, retaining the
requirements of EASA AD 2017-0248, which was superseded, to require an
additional borescope inspection of certain engines and, depending on
findings, removal from service of the engine for corrective action.
After that [EASA] AD was issued, it was determined that repetitive
borescope inspections are necessary on all engines to ensure fleet-wide
[[Page 21235]]
continued safe operation. Consequently, Rolls-Royce revised Alert NMSB
TRENT 1000 72-AJ869, Alert NMSB TRENT 1000 72-AJ814, Alert NMSB TRENT
1000 72-AJ819 and NMSB TRENT 1000 72-J871, and issued NMSB TRENT 1000
72-AK060 to consolidate all inspection instructions. Consequently, EASA
issued AD 2018-0084 (later revised), retaining the requirements of EASA
AD 2018-0073, which was superseded, and requiring repetitive on-wing
borescope inspections of the affected Rotor 1 parts and affected Rotor
2 parts and, depending on findings, removal from service of the engine
for corrective action. That AD also introduced specific requirements
for engines installed on aeroplanes involved in ETOPS, and inspection
following operation in asymmetric power conditions.
Rolls-Royce then introduced NMSB Trent 1000 72-AK092 to provide
inspections for the rear face of the Rotor 2 blades and NMSB TRENT 1000
72-AK060 was revised (R1) accordingly. Later, Rolls-Royce developed mod
72-J941, installing improved IPC Stage 1 and Stage 2 rotor blades, and
issued the modification SB, providing the necessary instructions for
in-service application. EASA issued AD 2018-0084R2 to exclude post-mod
72-J941 engines from the Applicability and introducing the modification
SB as terminating action for the repetitive inspections as required by
that [EASA] AD.
After that [EASA] AD was issued, Rolls-Royce issued NMSB TRENT 1000
72-AK313 and revised Alert NMSB TRENT 1000 72-AJ814, 72-AJ819 and 72-
AK092 to introduce new inspections, new thresholds and new intervals,
depending on engine configuration. These inspections are for all
operations, ETOPS and non-ETOPS. The latest revision of the NMSB also
amended the asymmetric power conditions for engine inspection and
introduced cabin depressurisation as an event to trigger engine
inspection(s). Consequently, EASA issued AD 2019-0250 to require
introduction of the new inspections, replacing those previously imposed
by EASA AD 2018-0084R2 (through NMSB TRENT 1000 72-AK060), and to
remove the references to Engine Health Monitoring messages and ETOPS-
related requirements.
Since that [EASA] AD was issued, it was discovered that the
manufacturing distribution of the individual blade frequencies could
differ from the assumed values during certification of the SB TRENT
1000 72-J941, which means there may not be sufficient margin to prevent
the blades from experiencing high vibration levels. Prompted by these
findings, Rolls-Royce issued the modification SB to provide blade
kitting instructions.
You may obtain further information by examining the MCAI in the AD
docket at https://www.regulations.gov by searching for and locating
Docket No. FAA-2021-0306.
FAA's Determination
This product has been approved by EASA and is approved for
operation in the United States. Pursuant to our bilateral agreement
with the European Community, EASA has notified the FAA of the unsafe
condition described in the MCAI and service information. The FAA is
issuing this NPRM because the agency evaluated all the relevant
information provided by EASA and determined the unsafe condition
described previously is likely to exist or develop in other products of
the same type design.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Rolls-Royce Alert Non-Modification Service
Bulletin (NMSB) Trent 1000 72-AK313, Revision 1, dated August 22, 2019;
and Rolls-Royce Alert Service Bulletin (SB) Trent 1000 72-AK430,
Initial Issue, dated August 17, 2020. Rolls-Royce Alert NMSB Trent 1000
72-AK313 defines the initial inspection threshold and repeat inspection
intervals for Trent 1000 IPC stage 1 rotor blade, IPC stage 2 rotor
blade, and IPC shaft stage 2 dovetail posts. Rolls-Royce Alert SB Trent
1000 72-AK430 introduces the IPC stage 1 and stage 2 rotor blades in
kitted sets and provides kitting instructions. 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 ADDRESSES.
Other Related Service Information
The FAA reviewed Rolls-Royce Alert NMSB Trent 1000 72-AJ814,
Revision 5, dated May 3, 2019; Rolls-Royce Alert NMSB Trent 1000 72-
AJ819, Revision 4, dated May 3, 2019; Rolls-Royce Alert NMSB Trent 1000
72-AK092, Revision 4, dated May 3, 2019; Rolls-Royce SB Trent 1000 72-
J871, Revision 6, dated December 12, 2019; and Rolls-Royce SB Trent
1000 72-J941, Revision 1, dated February 6, 2019.
Rolls-Royce Alert NMSB Trent 1000 72-AJ814 describes procedures for
performing an ultrasonic inspection (USI) of the IPC stage 1 rotor
blades. Rolls-Royce Alert NMSB Trent 1000 72-AJ819 describes procedures
for performing a visual borescope inspection of the IPC stage 2 rotor
blades and IPC shaft stage 2 dovetail posts. Rolls-Royce Alert NMSB
Trent 1000 72-AK092 describes procedures for performing a USI of the
IPC stage 2 rotor blades. Rolls-Royce SB Trent 1000 72-J871 describes
procedures for reworking or replacing the affected parts. Rolls-Royce
SB Trent 1000 72-J941 describes procedures for installing the
redesigned IPC stage 1 and stage 2 rotor blades.
Proposed AD Requirements in This NPRM
This proposed AD would retain certain requirements of AD 2020-15-
12. This proposed AD would continue to require initial and repetitive
ultrasonic or visual inspection of the IPC stage 1 rotor blade root
(front face), IPC stage 2 rotor blade root (front and rear face), and
IPC shaft stage 2 dovetail post (front face), removal of any cracked
parts from service, and an inspection after asymmetric power and cabin
depressurization events until the installation of the IPC stage 1 and
stage 2 rotor blades in kitted sets. As a terminating action, this AD
would require replacement of IPC stage 1 and stage 2 rotor blades with
IPC stage 1 and stage 2 rotor blades in kitted sets.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 7 engines installed on airplanes of U.S. registry.
The FAA estimates the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspect the IPC stage 1 rotor blade 20 work-hours x $85 per $0 $1,700 $11,900
root (Front Face). hour = $1,700.
[[Page 21236]]
Inspect the IPC stage 2 rotor blade 6 work-hours x $85 per 0 510 3,570
root (Front Face) and IPC shaft stage hour = $510.
2 dovetail post (Front Face).
Inspect the IPC stage 2 rotor blade 10 work-hours x $85 per 0 850 5,950
root (Rear Face). hour = $850.
Replace all 34 IPC stage 1 rotor 280 work-hours x $85 per 52,360 76,160 533,120
blades (mandatory terminating action). hour = $23,800.
Replace all 49 IPC stage 2 rotor 280 work-hours x $85 per 48,755 72,555 507,885
blades (mandatory terminating action). hour = $23,800.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
proposed inspection. The agency has no way of determining the number of
aircraft that might need these replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replace all 34 IPC stage 1 rotor blades....... 280 work-hours x $85 per hour = $52,360 $76,160
$23,800.
Replace all 49 IPC stage 2 rotor blades....... 280 work-hours x $85 per hour = 48,755 72,555
$23,800.
Replace the IPC drum assembly................. 144 work-hours x $85 per hour = 1,370,000 1,382,240
$12,240.
----------------------------------------------------------------------------------------------------------------
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 has 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 that the 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:
0
a. Removing Airworthiness Directive AD 2020-15-12, Amendment 39-21175
(85 FR 45081, July 27, 2020); and
0
b. Adding the following new airworthiness directive:
Rolls-Royce Deutschland Ltd & Co KG (Type Certificate previously
held by Rolls-Royce plc): Docket No. FAA-2021-0306; Project
Identifier MCAI-2020-01493-E.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) action by June 7, 2021.
(b) Affected ADs
This AD replaces AD 2020-15-12, Amendment 39-21175 (85 FR 45081,
July 27, 2020).
(c) Applicability
This AD applies to Rolls-Royce Deutschland Ltd & Co KG (Type
Certificate previously held by Rolls-Royce plc) Trent 1000-A2, Trent
1000-AE2, Trent 1000-C2, Trent 1000-CE2, Trent 1000-D2, Trent 1000-
E2, Trent 1000-G2, Trent 1000-H2, Trent 1000-J2, Trent 1000-K2, and
Trent 1000-L2 model turbofan engines, except those that have the
redesigned intermediate-pressure compressor (IPC) stage 1 and stage
2 rotor blades introduced by Rolls-Royce (RR) Service Bulletin (SB)
Trent 1000 72-J941, Initial Issue, dated December 6, 2016, or
Revision 1, dated February 6, 2019.
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine Engine
Compressor Section.
(e) Unsafe Condition
This AD was prompted by IPC rotor blade separations resulting in
engine failures. The FAA is issuing this AD to prevent failure of
the IPC. The unsafe condition, if not addressed, could result in
failure of one or more engines, loss of thrust control, and loss of
the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
[[Page 21237]]
(g) Required Actions
(1) After the effective date of this AD, before exceeding the
initial inspection thresholds and repeat inspection intervals
specified in Table 1 of RR Alert Non-Modification Service Bulletin
(NMSB) Trent 1000 72-AK313, Revision 1, dated August 22, 2019 (RR
NMSB Trent 1000 72-AK313 R1):
(i) Perform initial ultrasonic inspections (USIs) of the IPC
stage 1 rotor blade root (front face).
(ii) Thereafter, perform repetitive USIs of the IPC stage 1
rotor blade root (front face).
(iii) Use the Accomplishment Instructions, paragraph 3.A.(1)(a)
(on-wing) or 3.A.(2)(a) and (b) (in-shop), of RR NMSB Trent 1000 72-
AK313 R1 to perform the inspections.
(2) After the effective date of this AD, before exceeding the
initial inspection thresholds and repeat inspection intervals
specified in Table 2 of RR NMSB Trent 1000 72-AK313 R1:
(i) Perform initial visual inspections of the IPC stage 2 rotor
blade root (front face) and IPC shaft stage 2 dovetail post (front
face).
(ii) Thereafter, perform repetitive visual inspections of the
IPC stage 2 rotor blade root (front face) and IPC shaft stage 2
dovetail post (front face).
(iii) Use the Accomplishment Instructions, paragraph 3.B.(1)(a)
(on-wing) or 3.B.(2)(b) (in-shop), of RR NMSB Trent 1000 72-AK313 R1
to perform the inspections.
(3) After the effective date of this AD, before exceeding the
initial inspection threshold and repeat inspection intervals
specified in Table 2 of RR NMSB Trent 1000 72-AK313 R1:
(i) Perform initial USIs of IPC stage 2 rotor blade root (rear
face).
(ii) Thereafter, perform repetitive USIs of IPC stage 2 rotor
blade root (rear face).
(iii) Use the Accomplishment Instructions, paragraph 3.C.(1)(a)
(on-wing) or 3.C.(2)(a) (in-shop), of RR NMSB Trent 1000 72-AK313 R1
to perform the inspections.
(4) After the effective date of this AD, within 5 engine flight
cycles (FCs) after each occurrence in which any engine operates in
asymmetric power conditions at an altitude of less than 28,000 feet,
perform the following inspections on the engine not affected by the
power reduction or in-flight shutdown (IFSD):
(i) Perform initial USIs and visual inspections required by
paragraphs (g)(1) through (3) of this AD.
(ii) Thereafter, perform the repetitive USIs and visual
inspections required by paragraphs (g)(1) through (3) of this AD.
(iii) Use the service information and repetitive inspection
thresholds required by paragraphs (g)(1)(iii), (2)(iii), and
(3)(iii) to perform the inspections, as applicable.
(5) After the effective date of this AD, within 5 engine FCs
following a cabin depressurization event, perform the following
inspections on both engines installed on the airplane:
(i) Perform initial USIs and visual inspections required by
paragraphs (g)(1) through (3) of this AD.
(ii) Thereafter, perform the repetitive USIs and visual
inspections required by paragraphs (g)(1) through (3) of this AD.
(iii) Use the service information and repetitive inspection
thresholds required by paragraphs (g)(1)(iii), (2)(iii), and
(3)(iii) to perform the inspections, as applicable.
(6) If any IPC stage 1 rotor blade root (front face), IPC stage
2 rotor blade root (front face), or IPC stage 2 rotor blade root
(rear face) is found cracked during any inspection required by this
AD, replace the part with a part eligible for installation before
further flight.
(7) If any IPC shaft stage 2 dovetail post (front face) is found
cracked during any inspection required by this AD, replace the IPC
drum assembly.
(h) Mandatory Terminating Action
At the next engine shop visit after the effective date of this
AD, replace the IPC stage 1 and stage 2 rotor blades with redesigned
IPC stage 1 and stage 2 rotor blades introduced by RR SB Trent 1000
72-J941, Revision 1, dated February 6, 2019. Install the blades as
kitted sets using the Accomplishment Instructions, paragraph 3.C.
(In-Shop), of RR Alert SB Trent 1000 72-AK430, Initial Issue, dated
August 17, 2020. This replacement of the IPC stage 1 and stage 2
rotor blades as kitted sets is a terminating action for the initial
and repetitive ultrasonic or visual inspection requirements, as
applicable, required by paragraphs (g)(1) through (5) of this AD.
(i) Definitions
(1) For the purpose of this AD, an ``asymmetric power
condition'' is the operation of the airplane at an altitude of less
than 28,000 feet, experiencing either single engine take-off, engine
fault (reduced power on one engine), or single engine IFSD, which
includes execution of any non-normal checklist procedure.
(2) For the purpose of this AD, an ``engine shop visit'' is the
induction of an engine into the shop for maintenance involving the
separation of pairs of major mating engine case flanges, except that
the separation of engine flanges solely for the purposes of
transportation without subsequent engine maintenance does not
constitute an engine shop visit.
(j) Credit for Previous Actions
You may take credit for the initial inspections required by
paragraphs (g)(1) through (5) of this AD if you performed these
inspections before the effective date of this AD using any of the
following.
(1) RR Alert NMSB Trent 1000 72-AJ819, Revision 3, dated April
13, 2018, or earlier revisions;
(2) RR Alert NMSB Trent 1000 72-AJ814, Revision 4, dated
September 28, 2018, or earlier revisions;
(3) RR Alert NMSB Trent 1000 72-AK313, Initial Issue, dated May
2, 2019; or
(4) RR Alert NMSB Trent 1000 72-AK092, Revision 3, dated
February 28, 2019, or earlier revisions.
(k) Special Flight Permit
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are subject to the requirements of paragraph (k)(1) of
this AD.
(1) Operators who are prohibited from further flight due to a
crack finding as a result of paragraph (g) of this AD, may perform a
one-time non-revenue ferry flight to a location where the engine can
be removed from service. This ferry flight must be performed without
passengers, involve non-ETOPS operation, and consume no more than
three FCs.
(2) [Reserved]
(l) 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 Related Information. 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.
(m) Related Information
(1) For more information about this AD, contact Kevin Clark,
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: (781) 238-7088; fax: (781) 238-7199;
email: [email protected].
(2) Refer to European Union Aviation Safety Agency (EASA) AD
2020-0240, dated November 5, 2020, for more information. You may
examine the EASA AD in the AD docket at https://www.regulations.gov
by searching for and locating it in Docket No. FAA-2021-0306.
(3) For service information identified in this AD, contact
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, DE24
8BJ, United Kingdom; phone: +44 (0)1332 242424; fax: +44 (0)1332
249936; email: https://www.rolls-royce.com/contact-us/civil-aerospace.aspx; website: https://www.rolls-royce.com/contact-us.aspx. 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 (781) 238-7759.
Issued on April 9, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-07660 Filed 4-21-21; 8:45 am]
BILLING CODE 4910-13-P
