Airworthiness Directives; International Aero Engines AG Turbofan Engines, 59658-59662 [2021-23180]
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59658
Federal Register / Vol. 86, No. 206 / Thursday, October 28, 2021 / Proposed Rules
(4) Where paragraph (4) of EASA AD 2021–
0015 requires certain actions prior to the
installation of a tail boom on any helicopter,
including inspecting the tail boom, for this
AD, the requirements of paragraph (h)(2) of
this AD also apply to the inspection of the
tail boom.
(5) This AD does not mandate compliance
with the ‘‘Remarks’’ section of EASA AD
2021–0015.
(i) No Reporting Requirement
Although the service information
referenced in EASA AD 2021–0015 specifies
to submit certain information to the
manufacturer, this AD does not include that
requirement.
(j) Alternative Methods of Compliance
(AMOCs)
(k) Related Information
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(1) For EASA AD 2021–0015, contact
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; internet
www.easa.europa.eu. You may view this
material at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX 76177.
For information on the availability of this
material at the FAA, call (817) 222–5110.
This material may be found in the AD docket
at https://www.regulations.gov by searching
for and locating Docket No. FAA–2021–0887.
(2) For more information about this AD,
contact Gregory Koenig, Aerospace Engineer,
Airframe & Administrative Services Section,
Chicago ACO Branch, Compliance &
Airworthiness Division, FAA, 2300 E Devon
Ave., Des Plaines, IL 60018; telephone (847)
294–7127; email Gregory.L.Koenig@faa.gov.
[FR Doc. 2021–23233 Filed 10–27–21; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0835; Project
Identifier AD–2021–00971–E]
RIN 2120–AA64
Airworthiness Directives; International
Aero Engines AG Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede Airworthiness Directive (AD)
2021–11–15, which applies to certain
International Aero Engines AG (IAE)
V2500 model turbofan engines. AD
2021–11–15 requires performance of an
ultrasonic inspection (USI) of the highpressure turbine (HPT) 1st-stage disk
and HPT 2nd-stage disk and, depending
on the results of the inspections,
replacement of the HPT 1st-stage disk or
HPT 2nd-stage disk. Since the FAA
issued AD 2021–11–15, the FAA
determined the need to clarify the
compliance time for inspection of any
HPT 1st-stage disk or HPT 2nd-stage
disk that is installed on a low-thrust
model engine but had been previously
operated on a high-thrust model engine.
This proposed AD would require
performance of a USI of the HPT 1ststage disk and HPT 2nd-stage disk and,
depending on the results of the
inspections, replacement of the HPT 1ststage disk or HPT 2nd-stage disk. 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 December 13,
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 International Aero
Engines AG, 400 Main Street, East
Hartford, CT 06118; phone: (800) 565–
SUMMARY:
(1) The Manager, International Validation
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the International Validation
Branch, send it to the attention of the person
identified in paragraph (k)(2) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
Issued on October 19, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
DEPARTMENT OF TRANSPORTATION
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0140; email: help24@prattwhitney.com;
website: https://
connect.prattwhitney.com. 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–2021–0835; or in person at Docket
Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
NPRM, any comments received, and
other information. The street address for
Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Alberto Hernandez, Aviation Safety
Engineer, ECO Branch, FAA, 1200
District Avenue, Burlington, MA 01803;
phone: (781) 238–7329; fax: (781) 238–
7199; email: Alberto.J.Hernandez@
faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2021–0835; Project Identifier AD–
2021–00971–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 the proposal
because of those comments.
Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
agency will also post a report
summarizing each substantive verbal
contact we receive 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
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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 Alberto Hernandez,
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 2021–11–15,
Amendment 39–21577 (86 FR 30380,
June 8, 2021), (AD 2021–11–15), for all
IAE V2522–A5, V2524–A5, V2525–D5,
V2527–A5, V2527E–A5, V2527M–A5,
V2528–D5, V2530–A5, V2531–E5, and
V2533–A5 model turbofan engines with
a certain HPT 1st-stage disk or HPT 2ndstage disk installed. AD 2021–11–15
was prompted by an event involving an
uncontained failure of an HPT 1st-stage
disk that resulted in high-energy debris
penetrating the engine cowling. On
March 18, 2020, an Airbus Model A321–
231 airplane, powered by IAE V2533–
A5 model turbofan engines, experienced
an uncontained HPT 1st-stage disk
failure that resulted in an aborted
takeoff. The uncontained failure of the
HPT 1st-stage disk resulted in highenergy debris penetrating the engine
cowling. The FAA published Emergency
AD 2020–07–51 on March 21, 2020
(followed by publication in the Federal
Register on April 13, 2020, as a Final
Rule, Request for Comments (85 FR
20402)) and AD 2021–01–03 on January
6, 2021 (86 FR 458), to remove from
service HPT 1st-stage and HPT 2nd-
stage disks identified as having the
highest risk of failure. Based on the root
cause analysis performed since that
event, the manufacturer identified a
population of HPT 1st-stage disks and
HPT 2nd-stage disks that require
inspection and possible removal from
service. AD 2021–11–15 requires the
performance of an USI of the HPT 1ststage disk and HPT 2nd-stage disk and,
depending on the results of the
inspections, replacement of the HPT 1ststage disk or HPT 2nd-stage disk. The
agency issued AD 2021–11–15 to
prevent failure of the HPT 1st-stage disk
and HPT 2nd-stage disk.
Actions Since AD 2021–11–15 Was
Issued
Since the FAA issued AD 2021–11–
15, the FAA determined the need to
clarify the compliance time for
inspection of any HPT 1st-stage disk or
HPT 2nd-stage disk that is installed on
a V2500 low-thrust model engine but
that had been previously operated on a
V2500 high-thrust model engine. The
manufacturer categorizes V2527E–A5,
V2527M–A5, V2528–D5, V2530–A5,
and V2533–A5 model turbofan engines
as high-thrust model engines and
V2522–A5, V2524–A5, V2525–D5, and
V2527–A model turbofan engines as
low-thrust model engines. The FAA
determined that any HPT 1st-stage disk
and HPT 2nd-stage disk that was
operated on a high-thrust model engine
must follow shortened compliance
thresholds.
FAA’s Determination
The FAA is issuing this NPRM after
determining that the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design.
Related Service Information Under 1
CFR part 51
The FAA reviewed IAE NonModification Service Bulletin (NMSB)
59659
No. V2500–ENG–72–0713, Revision 1,
dated January 26, 2021. This NMSB
identifies the affected HPT 1st-stage
disks and HPT 2nd-stage disks on IAE
V2522–A5, V2524–A5, V2525–D5,
V2527–A5, V2527E–A5, V2527M–A5,
V2528–D5, V2530–A5, and V2533–A5
model turbofan engines and specifies
procedures for a USI of the HPT 1ststage disk and HPT 2nd-stage disk. The
Director of the Federal Register
approved IAE NMSB V2500–ENG–72–
0713, Revision 1, dated January 26, 2021
for incorporation by reference as of July
13, 2021 (86 FR 30380, June 8, 2021).
The FAA also reviewed IAE NMSB
No. V2500–E5–72–0015, Revision 1,
dated August 10, 2021. This NMSB
identifies the affected HPT 1st-stage
disks and HPT 2nd-stage disks on IAE
V2531–E5 model turbofan engines and
specifies procedures for a USI of the
HPT 1st-stage disk and HPT 2nd-stage
disk.
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.
Proposed AD Requirements in This
NPRM
This proposed AD would retain
certain requirements of AD 2021–11–15.
This proposed AD would require the
performance of an USI of the HPT 1ststage disk and HPT 2nd-stage disk and,
depending on the results of the
inspections, replacement of the HPT 1ststage disk or HPT 2nd-stage disk.
Costs of Compliance
The FAA estimates that this AD, if
adopted as proposed, would affect 1,100
engines installed on airplanes of U.S.
registry.
The FAA estimates the following
costs to comply with this proposed AD:
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ESTIMATED COSTS
Action
Labor cost
USI the HPT 1st-stage disk and HPT 2ndstage disk.
20 work-hours × $85 per hour = $1,700 ........
The FAA estimates the following
costs to do any necessary replacement
that would be required based on the
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results of the proposed inspection. The
agency has no way of determining the
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Cost per
product
Parts cost
$0
$1,700
Cost on U.S.
operators
$1,870,000
number of aircraft that might need this
replacement:
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Federal Register / Vol. 86, No. 206 / Thursday, October 28, 2021 / Proposed Rules
ON-CONDITION COSTS
Action
Labor cost
Replace the HPT 1st-stage disk or HPT 2nd-stage
disk.
0 work-hours × $85 per hour = $0 ...............................
The FAA has included all known
costs in its cost estimate. According to
the manufacturer, however, some of the
costs of this proposed AD may be
covered under warranty, thereby
reducing the cost impact on affected
individuals.
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.
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Regulatory Findings
The FAA determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Would not affect intrastate
aviation in Alaska, and
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(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.
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
AD 2021–11–15, Amendment 39–21577
(86 FR 30380, June 8, 2021); and
■ b. Adding the following new
airworthiness directive:
■
■
International Aero Engines AG: Docket No.
FAA–2021–0835; Project Identifier AD–
2021–00971–E.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) action by
December 13, 2021.
(b) Affected ADs
This AD replaces AD 2021–11–15,
Amendment 39–21577 (86 FR 30380, June 8,
2021) (AD 2021–11–15).
(c) Applicability
This AD applies to International Aero
Engines AG (IAE) V2522–A5, V2524–A5,
V2525–D5, V2527–A5, V2527E–A5,
V2527M–A5, V2528–D5, V2530–A5, V2531–
E5, and V2533–A5 model turbofan engines
with an installed:
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$300,000
Cost per
product
$300,000
(1) High-pressure turbine (HPT) 1st-stage
disk, part number (P/N) 2A5001, with a serial
number (S/N) listed in Appendix A, Table 1,
of IAE Non-Modification Service Bulletin
(NMSB) No. V2500–ENG–72–0713, Revision
1, dated January 26, 2021 (IAE NMSB V2500–
ENG–72–0713, Revision 1) or IAE NMSB No.
V2500–E5–72–0015, Revision 1, dated
August 10, 2021 (IAE NMSB V2500–E5–72–
0015, Revision 1); or
(2) HPT 2nd-stage disk, P/N 2A4802, with
an S/N listed in Appendix A, Table 2, of IAE
NMSB V2500–ENG–72–0713, Revision 1, or
IAE NMSB V2500–E5–72–0015, Revision 1.
(d) Subject
Joint Aircraft System Component (JASC)
Code 7250, Turbine Section.
(e) Unsafe Condition
■
§ 39.13
Parts cost
This AD was prompted by an analysis
performed by the manufacturer after an event
involving an uncontained failure of a HPT
1st-stage disk that resulted in high-energy
debris penetrating the engine cowling. The
FAA is issuing this AD to prevent failure of
the HPT 1st-stage disk and HPT 2nd-stage
disk. The unsafe condition, if not addressed,
could result in uncontained HPT disk failure,
damage to the engine, damage to the airplane,
and loss of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) For IAE V2527E–A5, V2527M–A5,
V2528–D5, V2530–A5, and V2533–A5 model
turbofan engines with an HPT 1st-stage disk,
P/N 2A5001, with an S/N listed in Appendix
A, Table 1, of IAE NMSB V2500–ENG–72–
0713, Revision 1, within the compliance time
specified in Figure 1 to paragraph (g)(1) of
this AD, or within 10 flight cycles (FCs) after
the effective date of this AD, whichever
occurs later, perform an ultrasonic inspection
(USI) of the HPT 1st-stage disk using the
Accomplishment Instructions, paragraph 6,
of IAE NMSB V2500–ENG–72–0713,
Revision 1.
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Note 1 to paragraph (g)(1): The USI
required by paragraphs (g)(1) through (6) of
this AD requires the HPT 1st-stage disk and
HPT 2nd-stage disks to be removed from the
engine allowing piece-part opportunity
inspections. Per the Airworthiness
Limitations Section of the manufacturer’s
Instructions for Continued Airworthiness, the
additional inspections are not required
unless the part has more than 100 FCs since
the last piece-part opportunity inspection, is
damaged, or is the cause for the removal of
the engine. Engine removal for the purposes
of complying with this AD is not ‘‘cause’’ for
removal as stated in the Airworthiness
Limitations Section.
(2) For IAE V2527E–A5, V2527M–A5,
V2528–D5, V2530–A5, and V2533–A5 model
turbofan engines with an HPT 2nd-stage disk,
P/N 2A4802, with an S/N listed in Appendix
A, Table 2, of IAE NMSB V2500–ENG–72–
0713, Revision 1, within the compliance time
specified in Figure 1 to paragraph (g)(1) of
this AD, or within 10 FCs after the effective
date of this AD, whichever occurs later,
perform a USI of the HPT 2nd-stage disk
using the Accomplishment Instructions,
paragraph 7, of IAE NMSB V2500–ENG–72–
0713, Revision 1.
(3) For IAE V2522–A5, V2524–A5, V2525–
D5, and V2527–A5 model turbofan engines
with an HPT 1st-stage disk, P/N 2A5001,
with an S/N listed in Appendix A, Table 1,
of IAE NMSB V2500–ENG–72–0713,
Revision 1, within the following compliance
times, perform a USI of the HPT 1st-stage
disk using the Accomplishment Instructions,
paragraph 6, of IAE NMSB V2500–ENG–72–
0713, Revision 1:
(i) If the affected HPT 1st-stage disk has not
operated at any time in an IAE V2527E–A5,
V2527M–A5, V2528–D5, V2530–A5, or
V2533–A5 model turbofan engine, perform
the inspection within the compliance time
specified in Figure 2 to paragraph (g)(3)(i) of
this AD, or within 10 FCs after the effective
date of this AD, whichever occurs later; or
(ii) If the affected HPT 1st-stage disk has
operated at any time in an IAE V2527E–A5,
V2527M–A5, V2528–D5, V2530–A5, or
V2533–A5 model turbofan engine, perform
the inspection within the compliance time
specified in Figure 1 to paragraph (g)(1) of
this AD, or within 10 FCs after the effective
date of this AD, whichever occurs later.
(4) For IAE V2522–A5, V2524–A5, V2525–
D5, and V2527–A5 model turbofan engines
with an HPT 2nd-stage disk, P/N 2A4802,
with an S/N listed in Appendix A, Table 2,
of IAE NMSB V2500–ENG–72–0713,
Revision 1, within the following compliance
times, perform a USI of the HPT 2nd-stage
disk using the Accomplishment Instructions,
paragraph 7, of IAE NMSB V2500–ENG–72–
0713, Revision 1:
(i) If the affected HPT 2nd-stage disk has
not operated at any time in an IAE V2527E–
A5, V2527M–A5, V2528–D5, V2530–A5, or
V2533–A5 model turbofan engine, perform
the inspection within the compliance time
specified in Figure 2 to paragraph (g)(3)(i) of
this AD, or within 10 FCs after the effective
date of this AD, whichever occurs later; or
(ii) If the affected HPT 2nd-stage disk has
operated at any time in an IAE V2527E–A5,
V2527M–A5, V2528–D5, V2530–A5, or
V2533–A5 model turbofan engine, perform
the inspection within the compliance time
specified in Figure 1 to paragraph (g)(1) of
this AD, or within 10 FCs after the effective
date of this AD, whichever occurs later.
(5) For IAE V2531–E5 model turbofan
engines with an HPT 1st-stage disk, P/N
2A5001, with an S/N listed in Appendix A,
Table 1, of IAE NMSB V2500–E5–72–0015,
Revision 1, within the compliance time
specified in Figure 1 to paragraph (g)(1) of
this AD, or within 10 FCs after the effective
date of this AD, whichever occurs later,
perform a USI of the HPT 1st-stage disk using
the Accomplishment Instructions, paragraph
6, of IAE NMSB V2500–E5–72–0015,
Revision 1.
(6) For IAE V2531–E5 model turbofan
engines with an HPT 2nd-stage disk, P/N
2A4802, with an S/N listed in Appendix A,
Table 2, of IAE NMSB V2500–E5–72–0015,
Revision 1, within the compliance time
specified in Figure 1 to paragraph (g)(1) of
this AD, or within 10 FCs after the effective
date of this AD, whichever occurs later,
perform a USI of the HPT 2nd-stage disk
using the Accomplishment Instructions,
paragraph 7, of IAE NMSB V2500–E5–72–
0015, Revision 1.
(7) If, during the USI required by
paragraphs (g)(1) through (6) of this AD, an
HPT 1st-stage disk or HPT 2nd-stage disk
does not pass the inspection as specified in
the Accomplishment Instructions, paragraph
8, of IAE NMSB V2500–ENG–72–0713,
Revision 1, or IAE NMSB V2500–E5–72–
0015, Revision 1, as applicable, before further
flight, remove the HPT 1st-stage disk or 2ndstage disk, as applicable, from service and
replace with a part eligible for installation.
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(h) Definitions
(1) 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
flanges, H–P, except for the following
situations, which do not constitute an engine
shop visit.
(i) Separation of engine flanges solely for
the purposes of transportation without
subsequent engine maintenance.
(ii) Engine removal for the purpose of
performing field maintenance activities at a
maintenance facility in lieu of performing
them on-wing.
(2) For the purpose for this AD, a ‘‘part
eligible for installation’’ is:
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(i) An HPT 1st-stage disk or HPT 2nd-stage
disk listed in Appendix A, Tables 1 and 2,
of IAE NMSB V2500–ENG–72–0713,
Revision 1, or Appendix A, Tables 1 and 2,
of IAE NMSB V2500–E5–72–0015, Revision
1, that passed the USI required by paragraphs
(g)(1) through (6) of this AD; or
(ii) An HPT 1st-stage disk or HPT 2nd-stage
disk that is not listed in Appendix A, Tables
1 and 2, of IAE NMSB V2500–ENG–72–0713,
Revision 1, or Appendix A, Tables 1 and 2,
of IAE NMSB V2500–E5–72–0015, Revision
1.
You may take credit for the USI of the HPT
1st-stage disk and HPT 2nd-stage disk
required by paragraphs (g)(5) and (6) of this
AD and the replacement of the HPT 1st-stage
disk and HPT 2nd-stage disk required by
paragraph (g)(7) of this AD, if you performed
these actions before the effective date of this
AD in accordance with IAE NMSB No.
V2500–E5–72–0015, original issue, dated
December 15, 2020.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, ECO Branch, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the certification office,
send it to the attention of the person
identified in paragraph (k)(1) of this AD. 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.
jspears on DSK121TN23PROD with PROPOSALS1
(k) Related Information
(1) For more information about this AD,
contact Alberto Hernandez, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: (781)
238–7329; fax: (781) 238–7199; email:
Alberto.J.Hernandez@faa.gov.
(2) For service information identified in
this AD, contact International Aero Engines
AG, 400 Main Street, East Hartford, CT
06118; phone: (800) 565–0140; email:
help24@prattwhitney.com; website: https://
connect.prattwhitney.com. You may view
this referenced service information at the
FAA, Airworthiness Products Section,
Operational Safety Branch, 1200 District
Avenue, Burlington, MA 01803. For
information on the availability of this
material at the FAA, call (781) 238–7759.
Issued on September 23, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–23180 Filed 10–27–21; 8:45 am]
BILLING CODE 4910–13–P
16:49 Oct 27, 2021
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0888; Project
Identifier MCAI–2021–00676–T]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
(i) Credit for Previous Actions
VerDate Sep<11>2014
DEPARTMENT OF TRANSPORTATION
Jkt 256001
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Airbus SAS Model A318 series;
A319–111, –112, –113, –114, –115,
–131, –132, –133, –151N, and –153N;
A320 series; and A321 series airplanes.
This proposed AD was prompted by a
determination that new or more
restrictive airworthiness limitations are
necessary. This proposed AD would
require revising the existing
maintenance or inspection program, as
applicable, to incorporate new or more
restrictive airworthiness limitations, as
specified in a European Union Aviation
Safety Agency (EASA) AD, which is
proposed for incorporation by reference.
The FAA is proposing this AD to
address the unsafe condition on these
products.
SUMMARY:
The FAA must receive comments
on this proposed AD by December 13,
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 material that will be incorporated
by reference (IBR) in this AD, contact
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221
8999 000; email ADs@easa.europa.eu;
internet www.easa.europa.eu. You may
find this IBR material on the EASA
website at https://ad.easa.europa.eu.
You may view this IBR material at the
FAA, Airworthiness Products Section,
Operational Safety Branch, 2200 South
DATES:
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
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 on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0888.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0888; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this NPRM, any
comments received, and other
information. The street address for
Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
Large Aircraft Section, FAA,
International Validation Branch, 2200
South 216th St., Des Moines, WA 98198;
telephone and fax 206–231–3223; email
sanjay.ralhan@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2021–0888; Project Identifier
MCAI–2021–00676–T’’ at the beginning
of your comments. The most helpful
comments reference a specific portion of
the proposal, explain the reason for any
recommended change, and include
supporting data. The FAA will consider
all comments received by the closing
date and may amend the proposal
because of those comments.
Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
agency will also post a report
summarizing each substantive verbal
contact received about this 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
E:\FR\FM\28OCP1.SGM
28OCP1
]]>Agencies
[Federal Register Volume 86, Number 206 (Thursday, October 28, 2021)]
[Proposed Rules]
[Pages 59658-59662]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-23180]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0835; Project Identifier AD-2021-00971-E]
RIN 2120-AA64
Airworthiness Directives; International Aero Engines AG Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2021-11-15, which applies to certain International Aero Engines AG
(IAE) V2500 model turbofan engines. AD 2021-11-15 requires performance
of an ultrasonic inspection (USI) of the high-pressure turbine (HPT)
1st-stage disk and HPT 2nd-stage disk and, depending on the results of
the inspections, replacement of the HPT 1st-stage disk or HPT 2nd-stage
disk. Since the FAA issued AD 2021-11-15, the FAA determined the need
to clarify the compliance time for inspection of any HPT 1st-stage disk
or HPT 2nd-stage disk that is installed on a low-thrust model engine
but had been previously operated on a high-thrust model engine. This
proposed AD would require performance of a USI of the HPT 1st-stage
disk and HPT 2nd-stage disk and, depending on the results of the
inspections, replacement of the HPT 1st-stage disk or HPT 2nd-stage
disk. 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 December
13, 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
International Aero Engines AG, 400 Main Street, East Hartford, CT
06118; phone: (800) 565-0140; email: [email protected]; website:
https://connect.prattwhitney.com. 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-2021-0835; or in person at
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket contains this NPRM, any comments
received, and other information. The street address for Docket
Operations is listed above.
FOR FURTHER INFORMATION CONTACT: Alberto Hernandez, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803;
phone: (781) 238-7329; 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-2021-0835; Project Identifier
AD-2021-00971-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
the proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact we receive 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
[[Page 59659]]
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 Alberto Hernandez, 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 2021-11-15, Amendment 39-21577 (86 FR 30380, June
8, 2021), (AD 2021-11-15), for all IAE V2522-A5, V2524-A5, V2525-D5,
V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, V2531-E5, and
V2533-A5 model turbofan engines with a certain HPT 1st-stage disk or
HPT 2nd-stage disk installed. AD 2021-11-15 was prompted by an event
involving an uncontained failure of an HPT 1st-stage disk that resulted
in high-energy debris penetrating the engine cowling. On March 18,
2020, an Airbus Model A321-231 airplane, powered by IAE V2533-A5 model
turbofan engines, experienced an uncontained HPT 1st-stage disk failure
that resulted in an aborted takeoff. The uncontained failure of the HPT
1st-stage disk resulted in high-energy debris penetrating the engine
cowling. The FAA published Emergency AD 2020-07-51 on March 21, 2020
(followed by publication in the Federal Register on April 13, 2020, as
a Final Rule, Request for Comments (85 FR 20402)) and AD 2021-01-03 on
January 6, 2021 (86 FR 458), to remove from service HPT 1st-stage and
HPT 2nd-stage disks identified as having the highest risk of failure.
Based on the root cause analysis performed since that event, the
manufacturer identified a population of HPT 1st-stage disks and HPT
2nd-stage disks that require inspection and possible removal from
service. AD 2021-11-15 requires the performance of an USI of the HPT
1st-stage disk and HPT 2nd-stage disk and, depending on the results of
the inspections, replacement of the HPT 1st-stage disk or HPT 2nd-stage
disk. The agency issued AD 2021-11-15 to prevent failure of the HPT
1st-stage disk and HPT 2nd-stage disk.
Actions Since AD 2021-11-15 Was Issued
Since the FAA issued AD 2021-11-15, the FAA determined the need to
clarify the compliance time for inspection of any HPT 1st-stage disk or
HPT 2nd-stage disk that is installed on a V2500 low-thrust model engine
but that had been previously operated on a V2500 high-thrust model
engine. The manufacturer categorizes V2527E-A5, V2527M-A5, V2528-D5,
V2530-A5, and V2533-A5 model turbofan engines as high-thrust model
engines and V2522-A5, V2524-A5, V2525-D5, and V2527-A model turbofan
engines as low-thrust model engines. The FAA determined that any HPT
1st-stage disk and HPT 2nd-stage disk that was operated on a high-
thrust model engine must follow shortened compliance thresholds.
FAA's Determination
The FAA is issuing this NPRM after determining that the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.
Related Service Information Under 1 CFR part 51
The FAA reviewed IAE Non-Modification Service Bulletin (NMSB) No.
V2500-ENG-72-0713, Revision 1, dated January 26, 2021. This NMSB
identifies the affected HPT 1st-stage disks and HPT 2nd-stage disks on
IAE V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5,
V2528-D5, V2530-A5, and V2533-A5 model turbofan engines and specifies
procedures for a USI of the HPT 1st-stage disk and HPT 2nd-stage disk.
The Director of the Federal Register approved IAE NMSB V2500-ENG-72-
0713, Revision 1, dated January 26, 2021 for incorporation by reference
as of July 13, 2021 (86 FR 30380, June 8, 2021).
The FAA also reviewed IAE NMSB No. V2500-E5-72-0015, Revision 1,
dated August 10, 2021. This NMSB identifies the affected HPT 1st-stage
disks and HPT 2nd-stage disks on IAE V2531-E5 model turbofan engines
and specifies procedures for a USI of the HPT 1st-stage disk and HPT
2nd-stage disk.
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.
Proposed AD Requirements in This NPRM
This proposed AD would retain certain requirements of AD 2021-11-
15. This proposed AD would require the performance of an USI of the HPT
1st-stage disk and HPT 2nd-stage disk and, depending on the results of
the inspections, replacement of the HPT 1st-stage disk or HPT 2nd-stage
disk.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 1,100 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
----------------------------------------------------------------------------------------------------------------
USI the HPT 1st-stage disk and HPT 2nd- 20 work-hours x $85 per $0 $1,700 $1,870,000
stage disk. hour = $1,700.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary
replacement 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 this replacement:
[[Page 59660]]
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replace the HPT 1st-stage disk or HPT 2nd- 0 work-hours x $85 per hour = $0 $300,000 $300,000
stage disk.
----------------------------------------------------------------------------------------------------------------
The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some of the costs of this
proposed AD may be covered under warranty, thereby reducing the cost
impact on affected individuals.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify 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 2021-11-15, Amendment 39-21577
(86 FR 30380, June 8, 2021); and
0
b. Adding the following new airworthiness directive:
International Aero Engines AG: Docket No. FAA-2021-0835; Project
Identifier AD-2021-00971-E.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) action by December 13, 2021.
(b) Affected ADs
This AD replaces AD 2021-11-15, Amendment 39-21577 (86 FR 30380,
June 8, 2021) (AD 2021-11-15).
(c) Applicability
This AD applies to International Aero Engines AG (IAE) V2522-A5,
V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-
A5, V2531-E5, and V2533-A5 model turbofan engines with an installed:
(1) High-pressure turbine (HPT) 1st-stage disk, part number (P/
N) 2A5001, with a serial number (S/N) listed in Appendix A, Table 1,
of IAE Non-Modification Service Bulletin (NMSB) No. V2500-ENG-72-
0713, Revision 1, dated January 26, 2021 (IAE NMSB V2500-ENG-72-
0713, Revision 1) or IAE NMSB No. V2500-E5-72-0015, Revision 1,
dated August 10, 2021 (IAE NMSB V2500-E5-72-0015, Revision 1); or
(2) HPT 2nd-stage disk, P/N 2A4802, with an S/N listed in
Appendix A, Table 2, of IAE NMSB V2500-ENG-72-0713, Revision 1, or
IAE NMSB V2500-E5-72-0015, Revision 1.
(d) Subject
Joint Aircraft System Component (JASC) Code 7250, Turbine
Section.
(e) Unsafe Condition
This AD was prompted by an analysis performed by the
manufacturer after an event involving an uncontained failure of a
HPT 1st-stage disk that resulted in high-energy debris penetrating
the engine cowling. The FAA is issuing this AD to prevent failure of
the HPT 1st-stage disk and HPT 2nd-stage disk. The unsafe condition,
if not addressed, could result in uncontained HPT disk failure,
damage to the engine, damage to the airplane, and loss of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) For IAE V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-
A5 model turbofan engines with an HPT 1st-stage disk, P/N 2A5001,
with an S/N listed in Appendix A, Table 1, of IAE NMSB V2500-ENG-72-
0713, Revision 1, within the compliance time specified in Figure 1
to paragraph (g)(1) of this AD, or within 10 flight cycles (FCs)
after the effective date of this AD, whichever occurs later, perform
an ultrasonic inspection (USI) of the HPT 1st-stage disk using the
Accomplishment Instructions, paragraph 6, of IAE NMSB V2500-ENG-72-
0713, Revision 1.
[[Page 59661]]
[GRAPHIC] [TIFF OMITTED] TP28OC21.000
Note 1 to paragraph (g)(1): The USI required by paragraphs
(g)(1) through (6) of this AD requires the HPT 1st-stage disk and
HPT 2nd-stage disks to be removed from the engine allowing piece-
part opportunity inspections. Per the Airworthiness Limitations
Section of the manufacturer's Instructions for Continued
Airworthiness, the additional inspections are not required unless
the part has more than 100 FCs since the last piece-part opportunity
inspection, is damaged, or is the cause for the removal of the
engine. Engine removal for the purposes of complying with this AD is
not ``cause'' for removal as stated in the Airworthiness Limitations
Section.
(2) For IAE V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-
A5 model turbofan engines with an HPT 2nd-stage disk, P/N 2A4802,
with an S/N listed in Appendix A, Table 2, of IAE NMSB V2500-ENG-72-
0713, Revision 1, within the compliance time specified in Figure 1
to paragraph (g)(1) of this AD, or within 10 FCs after the effective
date of this AD, whichever occurs later, perform a USI of the HPT
2nd-stage disk using the Accomplishment Instructions, paragraph 7,
of IAE NMSB V2500-ENG-72-0713, Revision 1.
(3) For IAE V2522-A5, V2524-A5, V2525-D5, and V2527-A5 model
turbofan engines with an HPT 1st-stage disk, P/N 2A5001, with an S/N
listed in Appendix A, Table 1, of IAE NMSB V2500-ENG-72-0713,
Revision 1, within the following compliance times, perform a USI of
the HPT 1st-stage disk using the Accomplishment Instructions,
paragraph 6, of IAE NMSB V2500-ENG-72-0713, Revision 1:
(i) If the affected HPT 1st-stage disk has not operated at any
time in an IAE V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, or V2533-A5
model turbofan engine, perform the inspection within the compliance
time specified in Figure 2 to paragraph (g)(3)(i) of this AD, or
within 10 FCs after the effective date of this AD, whichever occurs
later; or
[GRAPHIC] [TIFF OMITTED] TP28OC21.001
(ii) If the affected HPT 1st-stage disk has operated at any time
in an IAE V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, or V2533-A5
model turbofan engine, perform the inspection within the compliance
time specified in Figure 1 to paragraph (g)(1) of this AD, or within
10 FCs after the effective date of this AD, whichever occurs later.
(4) For IAE V2522-A5, V2524-A5, V2525-D5, and V2527-A5 model
turbofan engines with an HPT 2nd-stage disk, P/N 2A4802, with an S/N
listed in Appendix A, Table 2, of IAE NMSB V2500-ENG-72-0713,
Revision 1, within the following compliance times, perform a USI of
the HPT 2nd-stage disk using the Accomplishment Instructions,
paragraph 7, of IAE NMSB V2500-ENG-72-0713, Revision 1:
(i) If the affected HPT 2nd-stage disk has not operated at any
time in an IAE V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, or V2533-A5
model turbofan engine, perform the inspection within the compliance
time specified in Figure 2 to paragraph (g)(3)(i) of this AD, or
within 10 FCs after the effective date of this AD, whichever occurs
later; or
(ii) If the affected HPT 2nd-stage disk has operated at any time
in an IAE V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, or V2533-A5
model turbofan engine, perform the inspection within the compliance
time specified in Figure 1 to paragraph (g)(1) of this AD, or within
10 FCs after the effective date of this AD, whichever occurs later.
(5) For IAE V2531-E5 model turbofan engines with an HPT 1st-
stage disk, P/N 2A5001, with an S/N listed in Appendix A, Table 1,
of IAE NMSB V2500-E5-72-0015, Revision 1, within the compliance time
specified in Figure 1 to paragraph (g)(1) of this AD, or within 10
FCs after the effective date of this AD, whichever occurs later,
perform a USI of the HPT 1st-stage disk using the Accomplishment
Instructions, paragraph 6, of IAE NMSB V2500-E5-72-0015, Revision 1.
(6) For IAE V2531-E5 model turbofan engines with an HPT 2nd-
stage disk, P/N 2A4802, with an S/N listed in Appendix A, Table 2,
of IAE NMSB V2500-E5-72-0015, Revision 1, within the compliance time
specified in Figure 1 to paragraph (g)(1) of this AD, or within 10
FCs after the effective date of this AD, whichever occurs later,
perform a USI of the HPT 2nd-stage disk using the Accomplishment
Instructions, paragraph 7, of IAE NMSB V2500-E5-72-0015, Revision 1.
(7) If, during the USI required by paragraphs (g)(1) through (6)
of this AD, an HPT 1st-stage disk or HPT 2nd-stage disk does not
pass the inspection as specified in the Accomplishment Instructions,
paragraph 8, of IAE NMSB V2500-ENG-72-0713, Revision 1, or IAE NMSB
V2500-E5-72-0015, Revision 1, as applicable, before further flight,
remove the HPT 1st-stage disk or 2nd-stage disk, as applicable, from
service and replace with a part eligible for installation.
(h) Definitions
(1) 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 flanges, H-P, except for
the following situations, which do not constitute an engine shop
visit.
(i) Separation of engine flanges solely for the purposes of
transportation without subsequent engine maintenance.
(ii) Engine removal for the purpose of performing field
maintenance activities at a maintenance facility in lieu of
performing them on-wing.
(2) For the purpose for this AD, a ``part eligible for
installation'' is:
[[Page 59662]]
(i) An HPT 1st-stage disk or HPT 2nd-stage disk listed in
Appendix A, Tables 1 and 2, of IAE NMSB V2500-ENG-72-0713, Revision
1, or Appendix A, Tables 1 and 2, of IAE NMSB V2500-E5-72-0015,
Revision 1, that passed the USI required by paragraphs (g)(1)
through (6) of this AD; or
(ii) An HPT 1st-stage disk or HPT 2nd-stage disk that is not
listed in Appendix A, Tables 1 and 2, of IAE NMSB V2500-ENG-72-0713,
Revision 1, or Appendix A, Tables 1 and 2, of IAE NMSB V2500-E5-72-
0015, Revision 1.
(i) Credit for Previous Actions
You may take credit for the USI of the HPT 1st-stage disk and
HPT 2nd-stage disk required by paragraphs (g)(5) and (6) of this AD
and the replacement of the HPT 1st-stage disk and HPT 2nd-stage disk
required by paragraph (g)(7) of this AD, if you performed these
actions before the effective date of this AD in accordance with IAE
NMSB No. V2500-E5-72-0015, original issue, dated December 15, 2020.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, ECO Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
certification office, send it to the attention of the person
identified in paragraph (k)(1) of this AD. You may email your
request to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(k) Related Information
(1) For more information about this AD, contact Alberto
Hernandez, Aviation Safety Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: (781) 238-7329; fax: (781) 238-
7199; email: [email protected].
(2) For service information identified in this AD, contact
International Aero Engines AG, 400 Main Street, East Hartford, CT
06118; phone: (800) 565-0140; email: [email protected];
website: https://connect.prattwhitney.com. You may view this
referenced service information at the FAA, Airworthiness Products
Section, Operational Safety Branch, 1200 District Avenue,
Burlington, MA 01803. For information on the availability of this
material at the FAA, call (781) 238-7759.
Issued on September 23, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021-23180 Filed 10-27-21; 8:45 am]
BILLING CODE 4910-13-P
