Airworthiness Directives; Pratt & Whitney Division Engines, 80572-80575 [2023-25524]
Download as PDF
<![CDATA[
80572
Federal Register / Vol. 88, No. 222 / Monday, November 20, 2023 / Rules and Regulations
(4) This AD does not adopt the provisions
specified in paragraphs (4) and (5) of EASA
AD 2023–0060.
(5) This AD does not adopt the ‘‘Remarks’’
section of EASA AD 2023–0060.
(l) New Provisions for Alternative Actions
and Intervals
After the existing maintenance or
inspection program has been revised as
required by paragraph (j) of this AD, no
alternative actions (e.g., inspections) and
intervals are allowed unless they are
approved as specified in the provisions of the
‘‘Ref. Publications’’ section of EASA AD
2023–0060.
(m) Additional AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): 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
responsible Flight Standards Office, as
appropriate. If sending information directly
to the International Validation Branch, send
it to the attention of the person identified in
paragraph (n) of this AD. Information may be
emailed to: 9-AVS-AIR-730-AMOC@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the responsible Flight Standards Office.
(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, International Validation
Branch, FAA; or EASA; or Dassault
Aviation’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
ddrumheller on DSK120RN23PROD with RULES1
(o) 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.
(3) The following service information was
approved for IBR on December 26, 2023.
(i) European Union Aviation Safety Agency
(EASA) AD 2023–0060, dated March 16,
2023.
(ii) [Reserved]
(4) The following service information was
approved for IBR on December 23, 2020 (85
FR 73404, November 18, 2020).
(i) European Union Aviation Safety Agency
(EASA) AD 2019–0141, dated June 17, 2019.
(ii) [Reserved]
16:15 Nov 17, 2023
Jkt 262001
Issued on October 27, 2023.
Caitlin Locke, Director,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2023–25496 Filed 11–17–23; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–1638; Project
Identifier AD–2022–00466–E; Amendment
39–22586; AD 2023–22–02]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney Division Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2018–02–
10, which applied to certain Pratt &
Whitney Division (PW) Model PW4074,
PW4074D, PW4077, PW4077D,
PW4084D, PW4090, and PW4090–3
engines. AD 2018–02–10 required
performing repetitive fluorescent
penetrant inspections (FPIs) to detect
cracks in the outer diffuser case (ODC),
removal of any ODC that fails
inspection, and updating the mandatory
inspections in the Airworthiness
Limitations Section (ALS) of the
Instructions for Continued
Airworthiness (ICA). Since the FAA
issued AD 2018–02–10, PW developed a
modification to reduce the susceptibility
of ODC cracking. This AD retains the
ALS update requirement from AD 2018–
02–10, requires replacing certain ODC
part numbers with parts eligible for
installation, expands the applicability to
all ODC part numbers, and adjusts the
compliance threshold of the FPIs of the
ODC. The FAA is issuing this AD to
SUMMARY:
(n) Additional Information
For more information about this AD,
contact Tom Rodriguez, Aviation Safety
Engineer, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone: 206–231–
3226; email: tom.rodriguez@faa.gov.
VerDate Sep<11>2014
(5) For EASA ADs 2023–0060 and 2019–
0141, contact EASA, Konrad-Adenauer-Ufer
3, 50668 Cologne, Germany; telephone +49
221 8999 000; email ADs@easa.europa.eu;
website easa.europa.eu. You may find these
EASA ADs on the EASA website at
ad.easa.europa.eu.
(6) You may view this service information
at the FAA, Airworthiness Products Section,
Operational Safety Branch, 2200 South 216th
St., Des Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
(7) You may view this material at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
visit www.archives.gov/federal-register/cfr/
ibr-locations or email fr.inspection@nara.gov.
PO 00000
Frm 00020
Fmt 4700
Sfmt 4700
address the unsafe condition on these
products.
This AD is effective December
26, 2023.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 26, 2023.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2023–1638; 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.
Material Incorporated by Reference:
• For service information identified
in this final rule, contact Pratt &
Whitney Division, 400 Main Street, East
Hartford, CT 06118; phone: (800) 565–
0140; email: help24@prattwhitney.com;
website: 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 (817) 222–5110. It is also
available at regulations.gov under
Docket No. FAA–2023–1638.
FOR FURTHER INFORMATION CONTACT:
Carol Nguyen, Aviation Safety Engineer,
FAA, 2200 South 216th Street, Des
Moines, WA 98198; phone: (781) 238–
7655; email: carol.nguyen@faa.gov.
SUPPLEMENTARY INFORMATION:
DATES:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2018–02–10,
Amendment 39–19163 (FR 83 2896,
January 22, 2018), (‘‘AD 2018–02–10’’).
AD 2018–02–10 applied to PW Model
PW4074, PW4074D, PW4077,
PW4077D, PW4084D, PW4090, and
PW4090–3 engines with ODC part
number (P/N) 50J775 or P/N 50J930,
installed. The NPRM published in the
Federal Register on August 8, 2023 (88
FR 53406). The NPRM was prompted by
an updated analysis by the engine
manufacturer, which determined that
cracks on the ODC originated due to
high stress in the area between Tt3 boss
and thermocouple bracket boss. PW
developed a modification to improve
the surface area between Tt3 boss and
E:\FR\FM\20NOR1.SGM
20NOR1
80573
Federal Register / Vol. 88, No. 222 / Monday, November 20, 2023 / Rules and Regulations
thermocouple bracket boss to reduce the
ODC’s susceptibility to cracking.
Consequently, the FAA determined
that it is necessary to expand the
applicability to all ODC P/Ns, adjust the
initial FPI threshold for the ODC to
improve the inspection program, and to
require certain ODCs to be replaced
with an ODC that has been modified to
lower the stresses in the area between
Tt3 boss and thermocouple bracket boss.
In the NPRM, the FAA proposed to
continue to require retain certain
requirements of AD 2018–02–10. In the
NPRM, the FAA also proposed to
require revising the ALS of the existing
airplane maintenance manual or ICA
and your existing approved
maintenance program, as applicable, to
include piece-part inspections of the
ODC; expanding the applicability to
include all engines; initial and
repetitive FPIs, and depending on the
results of the FPI, require removal or reinspection of the ODC. Lastly the NPRM
proposed to require replacement of
certain ODCs with a part eligible for
installation at next piece-part exposure.
Discussion of Final Airworthiness
Directive
Comments
The FAA received comments from
three commenters. Commenters
included United Airlines, The Boeing
Company, and Air Lines Pilots
Association, International. All
commenters supported the NPRM
without change.
Conclusion
The FAA reviewed the relevant data,
considered the comments 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 which include updating the
manufacturer contact information, this
AD is adopted as proposed in the
NPRM.
Related Service Information Under 1
CFR Part 51
The FAA reviewed PW Alert Service
Bulletin (ASB) PW4G–112–A72–347,
Revision 4, dated September 1, 2022.
This ASB provides guidance on
performing FPIs on certain bosses of the
ODC. 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 PW Service
Bulletin (SB) PW4G–112–72–357, dated
February 25, 2019. This SB provides
procedures to modify and re-identify
ODC assemblies to lower the stresses in
the area between the Tt3 boss and the
thermocouple bracket boss.
Costs of Compliance
The FAA estimates that this AD,
affects 108 engines installed on
airplanes of U.S. registry. The FAA has
no way to determine the number of
operators that will replace the ODC with
a modified ODC or a zero-time ODC. As
a result, the total cost on U.S. operators
for these actions is not estimated.
The FAA estimates the following
costs to comply with this AD:
ddrumheller on DSK120RN23PROD with RULES1
ESTIMATED COSTS
Cost per
product
Parts cost
Cost on U.S.
operators
Action
Labor cost
Perform high sensitivity FPI of the ODC T3
thermocouple probe boss.
Revise the ALS ...............................................
Replace the ODC with modified ODC ............
Replace the ODC with zero-time ODC ...........
10 work-hours × $85 per hour = $850 ...........
$0
$850
$91,800
1 work-hour × $85 per hour = $85 .................
3 work-hours × $85 per hour = $255 .............
3 work-hours × $85 per hour = $255 .............
0
12,000
2,300,000
85
12,255
2,300,255
9,180
........................
........................
Authority for This Rulemaking
Regulatory Findings
The Amendment
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.
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.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR Part 39 as
follows:
VerDate Sep<11>2014
16:15 Nov 17, 2023
Jkt 262001
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
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
2018–02–10, Amendment 39–19163 (83
FR 2896, January 22, 2018); and
■ b. Adding the following new
airworthiness directive:
■
■
2023–22–02 Pratt & Whitney Division:
Amendment 39–22586; Docket No.
FAA–2023–1638; Project Identifier AD–
2022–00466–E.
E:\FR\FM\20NOR1.SGM
20NOR1
80574
Federal Register / Vol. 88, No. 222 / Monday, November 20, 2023 / Rules and Regulations
(a) Effective Date
This airworthiness directive (AD) is
effective December 26, 2023.
(b) Affected ADs
This AD replaces AD 2018–02–10,
Amendment 39–19163 (83 FR 2896, January
22, 2018).
(c) Applicability
This AD applies to Pratt & Whitney
Division (PW) Model PW4074, PW4074D,
PW4077, PW4077D, PW4084D, PW4090, and
PW4090–3 engines.
(d) Subject
Joint Aircraft System Component (JASC)
Code 7240, Turbine Engine Combustion
Section.
(e) Unsafe Condition
This AD was prompted by the discovery of
multiple cracked outer diffuser cases (ODCs).
We are issuing this AD to prevent failure of
the ODC. This condition, if not addressed,
could result in failure of the ODC, damage to
the engine, and damage to the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Within the compliance times specified
in paragraphs (g)(1)(i) though (iii) of this AD,
perform an initial high sensitivity fluorescent
penetrant inspection (FPI) of the ODC T3
thermocouple probe boss (Tt3 boss) for crack
indications in accordance with the
Accomplishment Instructions, paragraph 1.F.
of Part A or paragraph 1.B. of Part B, as
applicable, of PW Alert Service Bulletin
PW4G–112–A72–347, Revision 4, dated
September 1, 2022 (ASB PW4G–112–A72–
347, Rev 4).
(i) For an ODC that has accumulated less
than 12,000 cycles since new (CSN) with no
prior high sensitivity FPI of the ODC Tt3
boss, perform the high sensitivity FPI before
accumulating 9,200 CSN or within 1,000
flight cycles (FCs), after the effective date of
this AD, whichever occurs later.
(ii) For an ODC with unknown CSN or an
ODC that has accumulated 12,000 CSN or
more with no prior high sensitivity FPI of the
ODC Tt3 boss, perform the high sensitivity
FPI before accumulating 13,000 CSN or
within 1,000 FCs, after February 26, 2018
(the effective date of AD 2018–02–10),
whichever occurs later.
(iii) For an ODC that has undergone a high
sensitivity FPI of the ODC Tt3 boss prior to
the effective date of this AD that resulted in
no crack indication, perform the high
sensitivity FPI before accumulating 2,000 FCs
since performance of the last FPI or during
the next engine shop visit, whichever occurs
first.
(iv) For an ODC that has undergone a high
sensitivity FPI of the ODC Tt3 boss prior to
the effective date of this AD that resulted in
an indication of a crack, perform the actions
required by paragraphs (g)(3)(i) through (iii)
of this AD, as applicable.
(2) Thereafter, repeat the high sensitivity
FPI of the ODC Tt3 boss at each engine shop
visit or before exceeding 2,000 FCs from the
last high sensitivity FPI of the ODC Tt3 boss,
whichever occurs first, in accordance with
the Accomplishment Instructions, paragraphs
1.F. of Part A or paragraph 1.B. of Part B, as
applicable, of ASB PW4G–112–A72–347, Rev
4.
(3) If, during any inspection required by
paragraphs (g)(1) or (2) of this AD, there is
any crack indication, perform the actions
specified in paragraphs (g)(3)(i) through (iii)
of this AD.
(i) For engines installed on an aircraft,
repeat the high sensitivity FPI or remove the
ODC from service in accordance with the
actions and compliance times specified in
the Accomplishment Instructions, Part A,
paragraphs 1.G. and 1.H., of ASB PW4G–
112–A72–347, Rev 4.
(ii) For engines not installed on an aircraft,
repeat the high sensitivity FPI or remove the
ODC from service in accordance with the
actions and compliance times specified in
the Accomplishment Instructions, Part B,
paragraphs 1.C. and 1.D., of PW ASB PW4G–
112–A72–347, Rev 4.
(iii) For engines at an engine shop visit,
before further flight, remove the ODC from
service.
(4) Within 30 days after the effective date
of this AD, revise the Airworthiness
Limitations Section (ALS) of the existing
engine maintenance manual or Instructions
for Continued Airworthiness and the existing
approved maintenance program, as
applicable, to include the piece-part
inspections of the ODC as defined in Table
1 to paragraph (g)(4) of this AD.
TABLE 1 TO PARAGRAPH (g)(4)—ADDITION TO ALS
Description
Part No.
Case, Diffuser, Outer ...................................
All ...................
(5) For engines with ODC part number (P/
N) 50J775 or 50J930 installed, at the next
piece-part exposure after the effective date of
this AD, replace the ODC with a part eligible
for installation.
ddrumheller on DSK120RN23PROD with RULES1
(h) Definitions
(1) For the purpose of this AD, an ‘‘engine
shop visit’’ is any time the ‘‘M’’ flange is
separated.
(2) For the purpose of this AD, a ‘‘piecepart exposure’’ is when the ODC is removed
from the engine and fully disassembled.
(3) For the purpose of this AD, a ‘‘part
eligible for installation’’ is an ODC with P/
N 50J775–001, 50J775–002, 50J930–001, or
50J930–002.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, AIR–520 Continued
Operational Safety 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
VerDate Sep<11>2014
16:15 Nov 17, 2023
Jkt 262001
Cleaning,
inspection
and repair (CIR)
manual section
72–41–13
CIR manual inspection
Inspection/Check (I/C–02) ..........................
appropriate. If sending information directly
to the manager of the AIR–520 Continued
Operational Safety Branch, send it to the
attention of the person identified in
paragraph (j) of this AD and email to: ANEAD-AMOC@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(j) Related Information
For more information about this AD,
contact Carol Nguyen, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des
Moines, WA 98198; phone: (781) 238–7655;
email: carol.nguyen@faa.gov.
(k) 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.
PO 00000
Frm 00022
Fmt 4700
Sfmt 4700
CIR manual
P/N 51A750
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Pratt & Whitney Alert Service Bulletin
PW4G–112–A72–347, Revision 4, dated
September 1, 2022.
(ii) [Reserved]
(3) For service information identified in
this AD, contact Pratt & Whitney Division,
400 Main Street, East Hartford, CT 06118;
phone: (800) 565–0140; email: help24@
prattwhitney.com; website:
connect.prattwhitney.com.
(4) You may view this service information
at FAA, Airworthiness Products Section,
Operational Safety Branch, 1200 District
Avenue, Burlington, MA. For information on
the availability of this material at the FAA,
call (781) 238–7759.
(5) You may view this material at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
visit www.archives.gov/federal-register/cfr/
ibr-locations or email fr.inspection@nara.gov.
E:\FR\FM\20NOR1.SGM
20NOR1
Federal Register / Vol. 88, No. 222 / Monday, November 20, 2023 / Rules and Regulations
Issued on October 25, 2023.
Caitlin Locke,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2023–25524 Filed 11–17–23; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–1637; Project
Identifier MCAI–2023–00184–E; Amendment
39–22588; AD 2023–22–04]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Deutschland Ltd & Co KG Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
Rolls-Royce Deutschland Ltd & Co KG
(RRD) Model 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 engines. This AD was
prompted by reports of cracking and
separation of certain low-pressure
turbine (LPT) stage 1 blade assemblies.
This AD requires initial and repetitive
inspections of affected LPT stage 1 blade
assemblies for cracking or separation
and, depending on the results of the
inspections, reduction of the inspection
interval or replacement of the LPT stage
1 blade set and disk, as specified in a
European Union Aviation Safety Agency
(EASA) AD, which is incorporated by
reference. The FAA is issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective December
26, 2023.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 26, 2023.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2023–1637; or in person at
Docket Operations between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this final rule, the mandatory
ddrumheller on DSK120RN23PROD with RULES1
SUMMARY:
VerDate Sep<11>2014
16:15 Nov 17, 2023
Jkt 262001
continuing airworthiness information
(MCAI), 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.
Material Incorporated by Reference:
• For service information identified
in this final rule, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne,
Germany; phone: +49 221 8999 000;
email: ADs@easa.europa.eu; website:
easa.europa.eu. You may find this
material on the EASA website at
ad.easa.europa.eu.
• 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 (817) 222–5110. It is also
available at regulations.gov under
Docket No. FAA–2023–1637.
FOR FURTHER INFORMATION CONTACT:
Sungmo Cho, Aviation Safety Engineer,
FAA, 2200 South 216th Street, Des
Moines, WA 98198; phone: (781) 238–
7241; email: sungmo.d.cho@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all RRD Model 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 engines. The NPRM
published in the Federal Register on
July 31, 2023 (88 FR 49361). The NPRM
was prompted by EASA AD 2023–0027,
dated January 31, 2023 (EASA AD
2023–0027) (also referred to as the
MCAI) issued by EASA, which is the
Technical Agent for the Member States
of the European Union. The MCAI states
that manufacturer inspections detected
cracking and separation of blade pairs in
the weld region of certain LPT stage 1
blade assemblies. A blade assembly
consists of a pair of blades welded
together at the outer shroud. There are
85 LPT stage 1 blade assemblies in one
set. Such cracking and separation could
cause failure of affected parts and
damage to the LPT module.
PO 00000
Frm 00023
Fmt 4700
Sfmt 4700
80575
You may examine the MCAI in the
AD docket at regulations.gov under
Docket No. FAA–2023–1637.
In the NPRM, the FAA proposed to
require initial and repetitive inspections
of affected LPT stage 1 blade assemblies
for cracking or separation and,
depending on the results of the
inspections, reduction of the inspection
interval or replacement of the LPT stage
1 blade set and disk. The FAA is issuing
this AD to address the unsafe condition
on these products.
Discussion of Final Airworthiness
Directive
Comments
The FAA received one comment from
The Boeing Company (Boeing). Boeing
supported the NPRM without change.
Conclusion
These products have been approved
by the aviation authority of another
country and are approved for operation
in the United States. Pursuant to the
FAA’s bilateral agreement with this
State of Design Authority, it has notified
the FAA of the unsafe condition
described in the MCAI referenced
above. 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.
Related Service Information Under 1
CFR Part 51
The FAA reviewed EASA AD 2023–
0027, which specifies procedures for
inspection of affected LPT stage 1 blade
assemblies and replacement of the LPT
stage 1 blade set and disk. EASA AD
2023–0027 also specifies a reduction of
the repetitive inspection intervals if
cracking or separation is detected and
meets certain criteria.
This material is reasonably available
because the interested parties have
access to it through their normal course
of business or by the means identified
in ADDRESSES.
Costs of Compliance
The FAA estimates that this AD
affects 26 engines installed on airplanes
of U.S. registry.
The FAA estimates the following
costs to comply with this AD:
E:\FR\FM\20NOR1.SGM
20NOR1
]]>Agencies
[Federal Register Volume 88, Number 222 (Monday, November 20, 2023)]
[Rules and Regulations]
[Pages 80572-80575]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-25524]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-1638; Project Identifier AD-2022-00466-E;
Amendment 39-22586; AD 2023-22-02]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney Division Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2018-02-
10, which applied to certain Pratt & Whitney Division (PW) Model
PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3
engines. AD 2018-02-10 required performing repetitive fluorescent
penetrant inspections (FPIs) to detect cracks in the outer diffuser
case (ODC), removal of any ODC that fails inspection, and updating the
mandatory inspections in the Airworthiness Limitations Section (ALS) of
the Instructions for Continued Airworthiness (ICA). Since the FAA
issued AD 2018-02-10, PW developed a modification to reduce the
susceptibility of ODC cracking. This AD retains the ALS update
requirement from AD 2018-02-10, requires replacing certain ODC part
numbers with parts eligible for installation, expands the applicability
to all ODC part numbers, and adjusts the compliance threshold of the
FPIs of the ODC. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective December 26, 2023.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 26,
2023.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2023-1638; 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.
Material Incorporated by Reference:
For service information identified in this final rule,
contact Pratt & Whitney Division, 400 Main Street, East Hartford, CT
06118; phone: (800) 565-0140; email: [email protected]; website:
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 (817) 222-5110. It is
also available at regulations.gov under Docket No. FAA-2023-1638.
FOR FURTHER INFORMATION CONTACT: Carol Nguyen, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone:
(781) 238-7655; email: [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2018-02-10, Amendment 39-19163 (FR 83 2896,
January 22, 2018), (``AD 2018-02-10''). AD 2018-02-10 applied to PW
Model PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3
engines with ODC part number (P/N) 50J775 or P/N 50J930, installed. The
NPRM published in the Federal Register on August 8, 2023 (88 FR 53406).
The NPRM was prompted by an updated analysis by the engine
manufacturer, which determined that cracks on the ODC originated due to
high stress in the area between Tt3 boss and thermocouple bracket boss.
PW developed a modification to improve the surface area between Tt3
boss and
[[Page 80573]]
thermocouple bracket boss to reduce the ODC's susceptibility to
cracking.
Consequently, the FAA determined that it is necessary to expand the
applicability to all ODC P/Ns, adjust the initial FPI threshold for the
ODC to improve the inspection program, and to require certain ODCs to
be replaced with an ODC that has been modified to lower the stresses in
the area between Tt3 boss and thermocouple bracket boss.
In the NPRM, the FAA proposed to continue to require retain certain
requirements of AD 2018-02-10. In the NPRM, the FAA also proposed to
require revising the ALS of the existing airplane maintenance manual or
ICA and your existing approved maintenance program, as applicable, to
include piece-part inspections of the ODC; expanding the applicability
to include all engines; initial and repetitive FPIs, and depending on
the results of the FPI, require removal or re-inspection of the ODC.
Lastly the NPRM proposed to require replacement of certain ODCs with a
part eligible for installation at next piece-part exposure.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from three commenters. Commenters
included United Airlines, The Boeing Company, and Air Lines Pilots
Association, International. All commenters supported the NPRM without
change.
Conclusion
The FAA reviewed the relevant data, considered the comments
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 which
include updating the manufacturer contact information, this AD is
adopted as proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
The FAA reviewed PW Alert Service Bulletin (ASB) PW4G-112-A72-347,
Revision 4, dated September 1, 2022. This ASB provides guidance on
performing FPIs on certain bosses of the ODC. 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 PW Service Bulletin (SB) PW4G-112-72-357, dated
February 25, 2019. This SB provides procedures to modify and re-
identify ODC assemblies to lower the stresses in the area between the
Tt3 boss and the thermocouple bracket boss.
Costs of Compliance
The FAA estimates that this AD, affects 108 engines installed on
airplanes of U.S. registry. The FAA has no way to determine the number
of operators that will replace the ODC with a modified ODC or a zero-
time ODC. As a result, the total cost on U.S. operators for these
actions is not estimated.
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
----------------------------------------------------------------------------------------------------------------
Perform high sensitivity FPI of the 10 work-hours x $85 per $0 $850 $91,800
ODC T3 thermocouple probe boss. hour = $850.
Revise the ALS........................ 1 work-hour x $85 per 0 85 9,180
hour = $85.
Replace the ODC with modified ODC..... 3 work-hours x $85 per 12,000 12,255 ..............
hour = $255.
Replace the ODC with zero-time ODC.... 3 work-hours x $85 per 2,300,000 2,300,255 ..............
hour = $255.
----------------------------------------------------------------------------------------------------------------
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.
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 2018-02-10, Amendment 39-19163 (83
FR 2896, January 22, 2018); and
0
b. Adding the following new airworthiness directive:
2023-22-02 Pratt & Whitney Division: Amendment 39-22586; Docket No.
FAA-2023-1638; Project Identifier AD-2022-00466-E.
[[Page 80574]]
(a) Effective Date
This airworthiness directive (AD) is effective December 26,
2023.
(b) Affected ADs
This AD replaces AD 2018-02-10, Amendment 39-19163 (83 FR 2896,
January 22, 2018).
(c) Applicability
This AD applies to Pratt & Whitney Division (PW) Model PW4074,
PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 engines.
(d) Subject
Joint Aircraft System Component (JASC) Code 7240, Turbine Engine
Combustion Section.
(e) Unsafe Condition
This AD was prompted by the discovery of multiple cracked outer
diffuser cases (ODCs). We are issuing this AD to prevent failure of
the ODC. This condition, if not addressed, could result in failure
of the ODC, damage to the engine, and damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Within the compliance times specified in paragraphs
(g)(1)(i) though (iii) of this AD, perform an initial high
sensitivity fluorescent penetrant inspection (FPI) of the ODC T3
thermocouple probe boss (Tt3 boss) for crack indications in
accordance with the Accomplishment Instructions, paragraph 1.F. of
Part A or paragraph 1.B. of Part B, as applicable, of PW Alert
Service Bulletin PW4G-112-A72-347, Revision 4, dated September 1,
2022 (ASB PW4G-112-A72-347, Rev 4).
(i) For an ODC that has accumulated less than 12,000 cycles
since new (CSN) with no prior high sensitivity FPI of the ODC Tt3
boss, perform the high sensitivity FPI before accumulating 9,200 CSN
or within 1,000 flight cycles (FCs), after the effective date of
this AD, whichever occurs later.
(ii) For an ODC with unknown CSN or an ODC that has accumulated
12,000 CSN or more with no prior high sensitivity FPI of the ODC Tt3
boss, perform the high sensitivity FPI before accumulating 13,000
CSN or within 1,000 FCs, after February 26, 2018 (the effective date
of AD 2018-02-10), whichever occurs later.
(iii) For an ODC that has undergone a high sensitivity FPI of
the ODC Tt3 boss prior to the effective date of this AD that
resulted in no crack indication, perform the high sensitivity FPI
before accumulating 2,000 FCs since performance of the last FPI or
during the next engine shop visit, whichever occurs first.
(iv) For an ODC that has undergone a high sensitivity FPI of the
ODC Tt3 boss prior to the effective date of this AD that resulted in
an indication of a crack, perform the actions required by paragraphs
(g)(3)(i) through (iii) of this AD, as applicable.
(2) Thereafter, repeat the high sensitivity FPI of the ODC Tt3
boss at each engine shop visit or before exceeding 2,000 FCs from
the last high sensitivity FPI of the ODC Tt3 boss, whichever occurs
first, in accordance with the Accomplishment Instructions,
paragraphs 1.F. of Part A or paragraph 1.B. of Part B, as
applicable, of ASB PW4G-112-A72-347, Rev 4.
(3) If, during any inspection required by paragraphs (g)(1) or
(2) of this AD, there is any crack indication, perform the actions
specified in paragraphs (g)(3)(i) through (iii) of this AD.
(i) For engines installed on an aircraft, repeat the high
sensitivity FPI or remove the ODC from service in accordance with
the actions and compliance times specified in the Accomplishment
Instructions, Part A, paragraphs 1.G. and 1.H., of ASB PW4G-112-A72-
347, Rev 4.
(ii) For engines not installed on an aircraft, repeat the high
sensitivity FPI or remove the ODC from service in accordance with
the actions and compliance times specified in the Accomplishment
Instructions, Part B, paragraphs 1.C. and 1.D., of PW ASB PW4G-112-
A72-347, Rev 4.
(iii) For engines at an engine shop visit, before further
flight, remove the ODC from service.
(4) Within 30 days after the effective date of this AD, revise
the Airworthiness Limitations Section (ALS) of the existing engine
maintenance manual or Instructions for Continued Airworthiness and
the existing approved maintenance program, as applicable, to include
the piece-part inspections of the ODC as defined in Table 1 to
paragraph (g)(4) of this AD.
Table 1 to Paragraph (g)(4)--Addition to ALS
----------------------------------------------------------------------------------------------------------------
Cleaning,
inspection and CIR manual
Description Part No. repair (CIR) inspection CIR manual
manual section
----------------------------------------------------------------------------------------------------------------
Case, Diffuser, Outer........... All................... 72-41-13 Inspection/Check (I/ P/N 51A750
C-02).
----------------------------------------------------------------------------------------------------------------
(5) For engines with ODC part number (P/N) 50J775 or 50J930
installed, at the next piece-part exposure after the effective date
of this AD, replace the ODC with a part eligible for installation.
(h) Definitions
(1) For the purpose of this AD, an ``engine shop visit'' is any
time the ``M'' flange is separated.
(2) For the purpose of this AD, a ``piece-part exposure'' is
when the ODC is removed from the engine and fully disassembled.
(3) For the purpose of this AD, a ``part eligible for
installation'' is an ODC with P/N 50J775-001, 50J775-002, 50J930-
001, or 50J930-002.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, AIR-520 Continued Operational Safety 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 AIR-520 Continued
Operational Safety Branch, send it to the attention of the person
identified in paragraph (j) of this AD and email 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.
(j) Related Information
For more information about this AD, contact Carol Nguyen,
Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines,
WA 98198; phone: (781) 238-7655; email: [email protected].
(k) 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) Pratt & Whitney Alert Service Bulletin PW4G-112-A72-347,
Revision 4, dated September 1, 2022.
(ii) [Reserved]
(3) For service information identified in this AD, contact Pratt
& Whitney Division, 400 Main Street, East Hartford, CT 06118; phone:
(800) 565-0140; email: [email protected]; website:
connect.prattwhitney.com.
(4) You may view this service information at FAA, Airworthiness
Products Section, Operational Safety Branch, 1200 District Avenue,
Burlington, MA. For information on the availability of this material
at the FAA, call (781) 238-7759.
(5) You may view this material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].
[[Page 80575]]
Issued on October 25, 2023.
Caitlin Locke,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2023-25524 Filed 11-17-23; 8:45 am]
BILLING CODE 4910-13-P
