Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by Rolls-Royce plc) Turbofan Engines, 51600-51604 [2021-19982]
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Federal Register / Vol. 86, No. 177 / Thursday, September 16, 2021 / Rules and Regulations
21357 (85 FR 81790, December 17,
2020), and
■ b. Adding the following new AD:
existing AFM be removed before further
flight after the EEC software has been
updated.
2021–18–03 Yabora˜ Indu´stria Aerona´utica
S.A. (Type Certificate Previously Held
by Embraer S.A.) Airplanes:
Amendment 39–21704; Docket No.
FAA–2021–0701; Project Identifier
MCAI–2021–00365–T.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Large Aircraft
Section, 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 responsible Flight
Standards Office, as appropriate. If sending
information directly to the Large Aircraft
Section, International Validation Branch,
send it to the attention of the person
identified in paragraph (j) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, Large Aircraft Section,
International Validation Branch, FAA; or
ANAC; or ANAC’s authorized Designee. If
approved by the ANAC Designee, the
approval must include the Designee’s
authorized signature.
(a) Effective Date
This airworthiness directive (AD) becomes
effective October 1, 2021.
(b) Affected ADs
This AD replaces AD 2020–26–02,
Amendment 39–21357 (85 FR 81790,
December 17, 2020) (AD 2020–26–02).
(c) Applicability
This AD applies to Yabora˜ Indu´stria
Aerona´utica S.A. (type certificate previously
held by Embraer S.A.) Model ERJ 190–400
airplanes, certificated in any category, as
identified in Ageˆncia Nacional de Aviac
¸a˜o
Civil (ANAC) AD 2020–07–01R01, effective
March 26, 2021 (ANAC AD 2020–07–01R01).
(d) Subject
Air Transport Association (ATA) of
America Code 72, Turbine/turboprop engine.
(e) Reason
This AD was prompted by a report of an
in-flight shutdown (IFSD) due in part to
failure in the low-pressure compressor (LPC)
rotor 1 during operation in high altitude at
high thrust settings, and by the development
of updated electronic engine control (EEC)
software that will prevent the unsafe
condition. The FAA is issuing this AD to
address uncontained release of the LPC rotor
1 and damage to the engine and airplane
structure, which could result in loss of
control of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, ANAC AD 2020–07–01R01.
(h) Exceptions to ANAC AD 2020–07–01R01
(1) Where ANAC AD 2020–07–01R01 refers
to ‘‘the effective date of [ANAC] AD 2020–
07–01,’’ this AD requires using January 4,
2021 (the effective date of FAA AD 2020–26–
02).
(2) Where ANAC AD 2020–07–01R01 says
to ‘‘upgrade de EEC software,’’ this AD
requires to ‘‘upgrade the EEC software.’’
(3) Where ANAC AD 2020–07–01R01 refers
to its effective date, this AD requires using
the effective date of this AD.
(4) The ‘‘Alternative method of compliance
(AMOCs)’’ section of ANAC AD 2020–07–
01R01 does not apply to this AD.
(5) Where paragraph (c)(2) of ANAC AD
2020–07–01R01 requires removing the
airplane flight manual (AFM) amendments,
this AD requires that the amendments to the
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(j) Related Information
For more information about this AD,
contact Krista Greer, Aerospace Engineer,
Large Aircraft Section, International
Validation Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax 206–231–3221; email krista.greer@
faa.gov.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Ageˆncia Nacional de Aviac
¸a˜o Civil
(ANAC) AD 2020–07–01R01, effective March
26, 2021.
(ii) [Reserved]
(3) For ANAC AD 2020–07–01R01, contact
National Civil Aviation Agency (ANAC),
Aeronautical Products Certification Branch
(GGCP), Rua Dr. Orlando Feirabend Filho,
230—Centro Empresarial Aquarius—Torre
B—Andares 14 a 18, Parque Residencial
Aquarius, CEP 12.246–190—Sa˜o Jose´ dos
Campos—SP, BRAZIL, Tel: 55 (12) 3203–
6600; Email: pac@anac.gov.br; internet
www.anac.gov.br/en/. You may find this IBR
material on the ANAC website at https://
sistemas.anac.gov.br/certificacao/DA/
DAE.asp.
(4) You may view this material at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195. This material may be found
in the AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2021–0701.
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(5) You may view this material that is
incorporated by reference at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, email
fr.inspection@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on September 9, 2021.
Ross Landes,
Deputy Director for Regulatory Operations,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–19847 Filed 9–15–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0306; Project
Identifier MCAI–2020–01493–E; Amendment
39–21706; AD 2021–18–05]
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: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2020–15–
12 for certain Rolls-Royce Deutschland
Ltd & Co KG (RRD) Trent 1000 model
turbofan engines. AD 2020–15–12
required 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
required an inspection after asymmetric
power and cabin depressurization
events. This AD was prompted by IPC
rotor blade separations resulting in
engine failures. This AD requires initial
and repetitive ultrasonic or visual
inspections of certain IPC stage 1 rotor
blade root, IPC stage 2 rotor blade root,
and IPC shaft stage 2 dovetail posts until
replacement of the IPC stage 1 and stage
2 rotor blades with redesigned IPC stage
1 and stage 2 rotor blades in kitted sets.
The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective October 21,
2021.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 21, 2021.
SUMMARY:
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Federal Register / Vol. 86, No. 177 / Thursday, September 16, 2021 / Rules and Regulations
For service information
identified in this final rule, 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; website: https://www.rollsroyce.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. It is also available at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0306.
ADDRESSES:
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
final rule, any comments received, and
other information. The address for
Docket Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
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:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2020–15–12,
Amendment 39–21175 (85 FR 45081,
July 27, 2020), (AD 2020–15–12). AD
2020–15–12 applied to 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. The NPRM published
in the Federal Register on April 22,
2021 (86 FR 21233). The NPRM 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. In the NPRM,
the FAA proposed to continue to require
initial and repetitive ultrasonic or visual
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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 with the IPC stage 1 and
stage 2 rotor blades in kitted sets. The
FAA is issuing this AD to address the
unsafe condition on these products.
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, RollsRoyce 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 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 onwing 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
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51601
[EASA] 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, RollsRoyce 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.
Discussion of Final Airworthiness
Directive
Comments
The FAA received comments from 1
commenter. The commenter was The
Boeing Company (Boeing). Boeing
supported the NPRM without change.
Conclusion
The FAA reviewed the relevant data,
considered the comment received, and
determined that air safety requires
adopting the AD as proposed.
Accordingly, the FAA is issuing this AD
to address the unsafe condition on these
products. Except for minor editorial
changes, this AD is adopted as proposed
in the NPRM.
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51602
Federal Register / Vol. 86, No. 177 / Thursday, September 16, 2021 / Rules and Regulations
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.
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 specifies procedures for installing
the redesigned IPC stage 1 and stage 2
rotor blades.
Costs of Compliance
The FAA estimates that this AD
affects 7 engines installed on airplanes
of U.S. registry.
The FAA estimates the following
costs to comply with this AD:
ESTIMATED COSTS
Cost per
product
Labor cost
Inspect the IPC stage 1 rotor blade root
(Front Face).
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).
20 work-hours × $85 per hour = $1,700 ........
$0
$1,700
$11,900
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 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
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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 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
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Parts cost
$52,360
48,755
1,370,000
Cost per
product
$76,160
72,555
1,382,240
the States, or on the distribution of
power and responsibilities among the
various levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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Federal Register / Vol. 86, No. 177 / Thursday, September 16, 2021 / Rules and Regulations
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
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:
■
■
2021–18–05 Rolls-Royce Deutschland Ltd &
Co KG (Type Certificate previously held
by Rolls-Royce plc): Amendment 39–
21706; Docket No. FAA–2021–0306;
Project Identifier MCAI–2020–01493–E.
(a) Effective Date
This airworthiness directive (AD) is
effective October 21, 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.
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(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.
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
51603
(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
A special flight permit may be issued in
accordance with 14 CFR 21.197 and 21.199
to permit a one-time non-revenue ferry flight
to a location where the engine can be
removed from service for operators who are
E:\FR\FM\16SER1.SGM
16SER1
51604
Federal Register / Vol. 86, No. 177 / Thursday, September 16, 2021 / Rules and Regulations
prohibited from further flight due to a crack
finding as a result of paragraph (g) of this AD.
This ferry flight must be performed without
passengers, involve non-ETOPS operation,
and consume no more than three FCs.
Issued on August 23, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
(l) Alternative Methods of Compliance
(AMOCs)
[FR Doc. 2021–19982 Filed 9–15–21; 8:45 am]
BILLING CODE 4910–13–P
(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 Docket No. FAA–2021–0306.
(n) 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) Rolls-Royce Alert Non-Modification
Service Bulletin Trent 1000 72–AK313,
Revision 1, dated August 22, 2019.
(ii) Rolls-Royce Alert Service Bulletin
Trent 1000 72–AK430, Initial Issue, dated
August 17, 2020.
(3) For Rolls-Royce 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;
website: https://www.rolls-royce.com/
contact-us.aspx.
(4) 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email: fr.inspection@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
VerDate Sep<11>2014
16:05 Sep 15, 2021
Jkt 253001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0790; Project
Identifier MCAI–2021–01007–T; Amendment
39–21738; AD 2021–19–20]
RIN 2120–AA64
Airworthiness Directives; Dassault
Aviation Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
Dassault Aviation Model FALCON 7X
airplanes. This AD was prompted by a
report of defects on the piston hole
associated with the O2 saver feature that
may prevent efficient deactivation of the
O2 saver function. This AD requires
amending the existing airplane flight
manual (AFM) to incorporate a check
and an operating limitation regarding
the O2 saver function, as specified in a
European Union Aviation Safety Agency
(EASA) AD, which is incorporated by
reference. This AD also limits the
installation of affected parts under
certain conditions. The FAA is issuing
this AD to address the unsafe condition
on these products.
DATES: This AD becomes effective
September 16, 2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publications listed in this
AD as of September 16, 2021.
The FAA must receive comments on
this AD by November 1, 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
SUMMARY:
PO 00000
Frm 00016
Fmt 4700
Sfmt 4700
p.m., Monday through Friday, except
Federal holidays.
For material incorporated by reference
(IBR) in this AD, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne,
Germany; telephone +49 221 8999 000;
email ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find this
IBR material on the EASA website at
https://ad.easa.europa.eu. You may
view this material at the FAA,
Airworthiness Products Section,
Operational Safety Branch, 2200 South
216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available in the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0790.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0790; 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
AD, 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: Tom
Rodriguez, Aerospace Engineer, Large
Aircraft Section, FAA, International
Validation Branch, 2200 South 216th
St., Des Moines, WA 98198; telephone
and fax 206–231–3226; email
Tom.Rodriguez@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any
written data, views, or arguments about
this final rule. Send your comments to
an address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2021–0790;
Project Identifier MCAI–2021–01007–T’’
at the beginning of your comments. The
most helpful comments reference a
specific portion of the final rule, 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 final rule 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
E:\FR\FM\16SER1.SGM
16SER1
]]>Agencies
[Federal Register Volume 86, Number 177 (Thursday, September 16, 2021)]
[Rules and Regulations]
[Pages 51600-51604]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-19982]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0306; Project Identifier MCAI-2020-01493-E;
Amendment 39-21706; AD 2021-18-05]
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: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2020-15-12
for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent 1000 model
turbofan engines. AD 2020-15-12 required 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 required an inspection after asymmetric power and cabin
depressurization events. This AD was prompted by IPC rotor blade
separations resulting in engine failures. This AD requires initial and
repetitive ultrasonic or visual inspections of certain IPC stage 1
rotor blade root, IPC stage 2 rotor blade root, and IPC shaft stage 2
dovetail posts until replacement of the IPC stage 1 and stage 2 rotor
blades with redesigned IPC stage 1 and stage 2 rotor blades in kitted
sets. The FAA is issuing this AD to address the unsafe condition on
these products.
DATES: This AD is effective October 21, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 21,
2021.
[[Page 51601]]
ADDRESSES: For service information identified in this final rule,
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; 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. It is also available at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0306.
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 final rule, any
comments received, and other information. The address for Docket
Operations is U.S. Department of Transportation, Docket Operations, M-
30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue
SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: 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:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2020-15-12, Amendment 39-21175 (85 FR
45081, July 27, 2020), (AD 2020-15-12). AD 2020-15-12 applied to
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. The
NPRM published in the Federal Register on April 22, 2021 (86 FR 21233).
The NPRM 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. In the NPRM, the FAA
proposed to 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 with the IPC stage 1 and stage 2 rotor blades in kitted sets.
The FAA is issuing this AD to address the unsafe condition on these
products.
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 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 [EASA] 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.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from 1 commenter. The commenter was The
Boeing Company (Boeing). Boeing supported the NPRM without change.
Conclusion
The FAA reviewed the relevant data, considered the comment
received, and determined that air safety requires adopting the AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes, this
AD is adopted as proposed in the NPRM.
[[Page 51602]]
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 specifies procedures for installing the
redesigned IPC stage 1 and stage 2 rotor blades.
Costs of Compliance
The FAA estimates that this AD affects 7 engines installed on
airplanes of U.S. registry.
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
----------------------------------------------------------------------------------------------------------------
Inspect the IPC stage 1 rotor blade 20 work-hours x $85 per $0 $1,700 $11,900
root (Front Face). hour = $1,700.
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
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 AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
[[Page 51603]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
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:
2021-18-05 Rolls-Royce Deutschland Ltd & Co KG (Type Certificate
previously held by Rolls-Royce plc): Amendment 39-21706; Docket No.
FAA-2021-0306; Project Identifier MCAI-2020-01493-E.
(a) Effective Date
This airworthiness directive (AD) is effective October 21, 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.
(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
A special flight permit may be issued in accordance with 14 CFR
21.197 and 21.199 to permit a one-time non-revenue ferry flight to a
location where the engine can be removed from service for operators
who are
[[Page 51604]]
prohibited from further flight due to a crack finding as a result of
paragraph (g) of this AD. This ferry flight must be performed
without passengers, involve non-ETOPS operation, and consume no more
than three FCs.
(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 Docket No. FAA-2021-0306.
(n) 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) Rolls-Royce Alert Non-Modification Service Bulletin Trent
1000 72-AK313, Revision 1, dated August 22, 2019.
(ii) Rolls-Royce Alert Service Bulletin Trent 1000 72-AK430,
Initial Issue, dated August 17, 2020.
(3) For Rolls-Royce 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; website: https://www.rolls-royce.com/contact-us.aspx.
(4) 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on August 23, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021-19982 Filed 9-15-21; 8:45 am]
BILLING CODE 4910-13-P
