Airworthiness Directives; Honeywell International Inc. Engines, 32980-32983 [2023-10817]
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Federal Register / Vol. 88, No. 99 / Tuesday, May 23, 2023 / Proposed Rules
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
2018–21–11, Amendment 39–19469 (83
FR 54663, October 31, 2018); and
■ b. Adding the following new
airworthiness directive:
■
■
Pratt & Whitney Division: Docket No. FAA–
2023–0940; Project Identifier AD–2022–
01521–E.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) action by July 7,
2023.
(b) Affected ADs
This AD replaces AD 2018–21–11,
Amendment 39–19469 (83 FR 54663, October
31, 2018); (AD 2018–21–11).
(c) Applicability
This AD applies to all Pratt & Whitney
Division (PW) Model PW4074, PW4074D,
PW4077, PW4077D, PW4084D, PW4090, and
PW4090–3 engines.
(d) Subject
Joint Aircraft System Component (JASC)
Code 7230, Turbine Engine Compressor
Section.
(e) Unsafe Condition
This AD was prompted by an updated
analysis by the engine manufacturer, which
indicated certain low-pressure compressor
(LPC) fan hubs could crack before their
published life limit. We are issuing this AD
to prevent failure of the LPC fan hub. The
unsafe condition, if not addressed, could
result in uncontained hub release, damage to
the engine, and damage to the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Before accumulating 550 flight cycles
(FC) after the effective date of this AD, and
thereafter at intervals not to exceed 550 FC
since the last eddy current inspection (ECI),
perform an ECI of the LPC fan hub assembly,
in accordance with the Accomplishment
Instructions, For Engines Installed on
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Aircraft, paragraph 2., or For Engines Not
Installed on Aircraft, paragraph 3; of PW
Alert Service Bulletin PW4G–112–A72–362,
Revision 1 dated January 20, 2023 (ASB
PW4G–112–A72–362, Revision 1).
(2) If a rejectable or reportable indication
is found during the inspections required by
paragraph (g)(1) of this AD, before further
flight, replace the LPC fan hub assembly with
a part eligible for installation.
(h) Installation Prohibition
After the effective date of this AD, do not
install an LPC fan hub assembly on any
engine, unless it is a part eligible for
installation as defined in paragraph (j) of this
AD.
(i) No Reporting Requirement
This AD does not require reporting certain
information to the manufacturer as specified
in ASB PW4G–112–A72–362, Revision 1.
(j) Definitions
For the purposes of this AD, a ‘‘part
eligible for installation’’ is an affected LPC
fan hub assembly that has been inspected as
required by paragraph (g)(1) of this AD and
does not have a rejectable or reportable
indication or a LPC fan hub assembly with
zero cycles since new.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, 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 certification office,
send it to the attention of the person
identified in paragraph (l) of this AD.
(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.
(l) Related Information
For more information about this AD,
contact Carol Nguyen, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District
Avenue; phone: (781) 238–7655; email:
carol.nguyen@faa.gov.
(m) 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 Division Alert Service
Bulletin PW4G–112–A72–362, Revision 1,
dated January 20, 2023.
(ii) [Reserved]
(3) For service information identified in
this AD, contact Pratt & Whitney Division,
400 Main Street, East Hartford, CT 06118;
phone: (860) 565–0140; email: help24@
prattwhitney.com; website:
connect.prattwhitney.com.
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(4) You may view this service information
at 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email: fr.inspection@nara.gov, or go to:
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on May 4, 2023.
Michael Linegang,
Acting Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2023–10908 Filed 5–22–23; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–1050; Project
Identifier AD–2022–00602–E]
RIN 2120–AA64
Airworthiness Directives; Honeywell
International Inc. Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for all
Honeywell International Inc. Model
AS907–1–1A and AS907–2–1G engines.
This proposed AD was prompted by
reports of compressor surge, including a
dual engine compressor surge, during
takeoff climb out through a steep
temperature inversion, causing a loss of
engine thrust control. This proposed AD
would require either the replacement of
a certain electronic control unit (ECU)
software version installed on AS907–1–
1A engines with updated software or the
replacement of certain ECUs installed
on AS907–1–1A engines with ECUs
eligible for installation. This proposed
AD would also require the replacement
of certain ECUs installed on AS907–2–
1G engines with ECUs eligible for
installation. 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 July 7, 2023.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
SUMMARY:
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Federal Register / Vol. 88, No. 99 / Tuesday, May 23, 2023 / Proposed Rules
• Federal eRulemaking Portal: Go to
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.
AD Docket: You may examine the AD
docket at regulations.gov by searching
for and locating Docket No. FAA–2023–
1050; 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:
Joseph Costa, Aviation Safety Engineer,
West Certification Branch, FAA, 3960
Paramount Boulevard, Lakewood, CA
90712; phone: (562) 627–5246; email:
joseph.costa@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
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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–2023–1050; Project Identifier AD–
2022–00602–E’’ at the beginning of your
comments. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. The FAA will consider
all comments received by the closing
date and may amend this 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
regulations.gov, including any personal
information you provide. The agency
will also post a report summarizing each
substantive verbal contact received
about this NPRM.
32981
Confidential Business Information
CBI is commercial or financial
information that is both customarily and
actually treated as private by its owner.
Under the Freedom of Information Act
(FOIA) (5 U.S.C. 552), CBI is exempt
from public disclosure. If your
comments responsive to this NPRM
contain commercial or financial
information that is customarily treated
as private, that you actually treat as
private, and that is relevant or
responsive to this NPRM, it is important
that you clearly designate the submitted
comments as CBI. Please mark each
page of your submission containing CBI
as ‘‘PROPIN.’’ The FAA will treat such
marked submissions as confidential
under the FOIA, and they will not be
placed in the public docket of this
NPRM. Submissions containing CBI
should be sent to Joseph Costa, Aviation
Safety Engineer, West Certification
Branch, FAA, 3960 Paramount
Boulevard, Lakewood, CA 90712. Any
commentary that the FAA receives
which is not specifically designated as
CBI will be placed in the public docket
for this rulemaking.
the CGVs can lead to a compressor surge
event. The compressor surge margin is
decreased when scheduling is based on
a colder Tt2 temperature than what the
engine is actually running. Engine
deterioration impacts compressor surge
margin and can increase the likelihood
of a dual engine compressor surge as the
AS907–1–1A and AS907–2–1G engine
fleets age. Dual engine power loss due
to a temperature inversion occurring
within 75 feet AGL during takeoff climb
out may cause the loss of thrust control
of an airplane. This condition, if not
addressed, could result in reduced
controllability of the airplane, loss of
control of the airplane, reduced ability
of the flight crew to maintain the safe
flight and landing of the airplane, and
loss of the airplane.
Background
The FAA was notified of several
reports that Honeywell International
Inc. (Honeywell) Model AS907–1–1A
and AS907–2–1G engines experienced
compressor surge, including an AS907–
1–1A dual engine compressor surge,
during takeoff climb out through a steep
temperature inversion, which resulted
in loss of engine thrust control. The
FAA determined that the installed ECU
software version logic locked the engine
inlet total temperature (Tt2) at 60 knots
on a takeoff roll and that reference Tt2
remained locked until the aircraft
reached 400 feet above ground level
(AGL) or the pilot moved the throttle
before reaching 400 AGL. The locked
Tt2 is mathematically adjusted by the
ECU software for altitude and Mach
number changes as the takeoff
progresses. During the climb to 400 feet
AGL with a thermal inversion, the
actual engine Tt2 can increase above the
Tt2 that is being calculated by the ECU,
which causes the compressor guide
vanes’ (CGVs) position to be offschedule for the actual ambient
conditions. Significant off-scheduling of
This proposed AD would require
either the replacement of a certain ECU
software version installed on AS907–1–
1A engines with a software version
eligible for installation or the
replacement of certain ECUs installed
on AS907–1–1A engines with ECUs
eligible for installation. This proposed
AD would also require the replacement
of certain ECUs installed on AS907–2–
1G engines with ECUs eligible for
installation. ECUs with P/N 2119576–
3001 or P/N 2119576–3002 installed in
AS907–2–1G engines would be eligible
for reinstallation on the AS907–2–1G
engines until exceeding the compliance
time specified in Table 2 to paragraph
(g)(2) of this AD.
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.
Proposed AD Requirements in this
NPRM
Costs of Compliance
The FAA estimates that this AD, if
adopted as proposed, would affect 853
engines installed on airplanes of U.S.
registry. The FAA estimates that 175
engines installed on AS907–2–1G
engines will require replacing two
ECUs.
The FAA estimates the following
costs to comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Replace AS907–2–1G ECUs (2 per engine) ..
5 work-hours × $85 per hour = $425 .............
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16:36 May 22, 2023
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Parts cost
$109,044
E:\FR\FM\23MYP1.SGM
23MYP1
Cost per
product
$109,469
Cost on U.S.
operators
$19,157,075
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Federal Register / Vol. 88, No. 99 / Tuesday, May 23, 2023 / Proposed Rules
For either replacement of the AS907–
1–1A ECU software or replacement of
the AS907–1–1A ECUs, depending on
the option selected by the operator to
comply with this AD, the FAA estimates
the following costs:
Action
Labor cost
Replace AS907–1–1A ECU software (2 per engine) ...
Replace AS907–1–1A ECU (per ECU, per engine) ....
5 work-hours × $85 per hour = $425 ...........................
2 work-hours × $85 per hour = $170 ...........................
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
operators.
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 this 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:
$0
61,162
Cost per
product
$425
61,332
(c) Applicability
This AD applies to Honeywell
International Inc. (Honeywell) Model AS907–
1–1A and AS907–2–1G engines.
(d) Subject
Joint Aircraft System Component (JASC)
Code 7300, Engine Fuel and Control.
(e) Unsafe Condition
This AD was prompted by reports of
compressor surge, including a dual engine
compressor surge, during takeoff climb out
through a steep temperature inversion, which
caused a loss of engine thrust control. The
FAA is issuing this AD to prevent loss of
engine thrust control. The unsafe condition,
if not addressed, could result in reduced
controllability of the airplane, loss of control
of the airplane, reduced ability of the flight
crew to maintain the safe flight and landing
of the airplane, and loss of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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
Parts cost
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
Honeywell International Inc.: Docket No.
FAA–2023–1050; Project Identifier AD–
2022–00602–E.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by July 7, 2023.
(b) Affected ADs
None.
(g) Required Actions
(1) For AS907–1–1A engines with an ECU
having part number (P/N) 2119576–1011 and
software version AS907_1011 installed,
before exceeding the applicable compliance
time in Table 1 to paragraph (g)(1) of this AD,
either replace software version AS907_1001
with a software version eligible for
installation; or replace the ECU with an ECU
eligible for installation. Either the software or
ECU must be replaced for all four ECUs
installed in both airplane engines at the same
time.
Note 1 to paragraph (g)(1): Guidance for
removing and replacing the ECU software or
removing and replacing the ECU may be
found in Honeywell Service Bulletin (SB)
AS907–76–9031, Revision 2, dated May 15,
2022.
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TABLE 1 TO PARAGRAPH (g)(1)—MODEL AS907–1–1A ENGINES
Engine operating time since new
(TSN)
Compliance time
Greater than 5,000 hours TSN .......
Within 12 months or before exceeding 400 hours time-in-service (TIS), whichever occurs first after the effective date of this AD.
Within 18 months or before exceeding 600 hours TIS, whichever occurs first after the effective date of this
AD.
Within 24 months or before exceeding 800 hours TIS, whichever occurs first after the effective date of this
AD.
3,000 to 5,000 hours TSN ..............
Fewer than 3,000 hours TSN .........
(2) For AS907–2–1G engines with serial
numbers (S/N) P130101 through P130240
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that have not incorporated Honeywell SB
AS907–72–9063, and for AS907–2–1G
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engines with S/Ns P130241 through P130336,
and S/Ns P130101 through P130240 that
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Federal Register / Vol. 88, No. 99 / Tuesday, May 23, 2023 / Proposed Rules
have incorporated Honeywell SB AS907–72–
9063, before exceeding the applicable
compliance time in Table 2 to paragraph
(g)(2) of this AD, replace any installed ECU
having P/N 2119576–3001 or P/N 2119576–
3002 with an ECU eligible for installation.
All four ECUs installed in both airplane
engines must be replaced at the same time.
Note 2 to paragraph (g)(2): Guidance for
removing and replacing the ECU may be
found in Honeywell SB AS907–76–9014,
Revision 6, dated October 10, 2022.
32983
Note 3 to paragraph (g)(2): Guidance for
converting a standard flow compressor to a
high flow compressor for improving surge
margin may be found in Honeywell SB
AS907–72–9063, Revision 1, dated July 31,
2019.
TABLE 2 TO PARAGRAPH (g)(2)—MODEL AS907–2–1G ENGINES
Engine type
Compliance time
Standard Flow Compressor AS907–2–1G engines (engine S/Ns
P130101 through P130240 that have not incorporated Honeywell SB
AS907–72–9063).
High Flow Compressor AS907-2-1G engines (engine S/Ns P130241
through P130336 and engines that have incorporated Honeywell SB
AS907–72–9063).
Within 2 years or before exceeding 800 hours TIS, whichever occurs
first after the effective date of this AD.
(h) Installation Prohibition
(1) After the effective date of this AD, do
not install an ECU having P/N 2119576–1011
and software version AS907_1001 in any
AS907–1–1A engine.
(2) Do not install an ECU having P/N
2119576–3001 or P/N 2119576–3002 in any
AS907–2–1G engine if the ECU has exceeded
the compliance time specified in Table 2 to
paragraph (g)(2) of this AD.
(i) Definitions
(1) For the purpose of this AD, for the
AS907–1–1A engine, a ‘‘software version
eligible for installation’’ is a software version
that is not software version AS907_1001.
(2) For the purpose of this AD, for the
AS907–1–1A engine, an ‘‘ECU eligible for
installation’’ is an ECU that does not have P/
N 2119576–1011.
(3) For the purpose of this AD, for the
AS907–2–1G engine, an ‘‘ECU eligible for
installation’’ is an ECU that does not have P/
N 2119576–3001 or P/N 2119576–3002.
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(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, West Certification
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 branch,
send it to the attention of the person
identified in paragraph (k)(1) of this AD and
email to: 9-ANM-LAACO-AMOC-Requests@
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.
(k) Related Information
(1) For more information about this AD,
contact Joseph Costa, Aviation Safety
Engineer, West Certification Branch, FAA,
3960 Paramount Boulevard, Lakewood, CA
90712; phone: (562) 627–5246; email:
joseph.costa@faa.gov.
(2) For service information identified in
this AD that is not incorporated by reference,
contact Honeywell International Inc., 111
South 34th Street, Phoenix, AZ 85034;
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16:36 May 22, 2023
Jkt 259001
Within 7 years or before exceeding 2,800 hours TIS, whichever occurs
first after the effective date of this AD.
phone: (800) 601–3099; website:
myaerospace.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.
Issued on May 16, 2023.
Michael Linegang,
Acting Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
completing a flight instructor
certification practical test. Additionally,
the FAA proposes to amend the
qualification requirements for flight
instructors seeking to provide training
to initial flight instructor applicants by
adding two new methods under which
a flight instructor may become qualified
to provide this training. Lastly, the FAA
proposes to relocate and codify the
requirements of a Special Federal
Aviation Regulation into the
regulations.
[FR Doc. 2023–10817 Filed 5–22–23; 8:45 am]
DATES:
(l) Material Incorporated by Reference
None.
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Parts 61, 63, 65, and 141
[Docket No. FAA–2023–0825; Notice No. 23–
06]
RIN 2120–AL25
Removal of Expiration Date on a Flight
Instructor Certificate; Additional
Qualification Requirements To Train
Initial Flight Instructor Applicants; and
Other Provisions
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to amend
the flight instructor certificate renewal
requirements by changing the existing
renewal requirements to recent
experience requirements and adding a
new method for persons to establish
recent flight instructor experience. This
rulemaking would also allow a flight
instructor whose recent experience has
lapsed by no more than three calendar
months to reinstate flight instructor
privileges by taking an approved flight
instructor refresher course rather than
SUMMARY:
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Send comments on or before
June 22, 2023.
ADDRESSES: Send comments identified
by docket number FAA–2023–0825
using any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the online instructions for sending your
comments electronically.
• Mail: Send comments to Docket
Operations, M–30; U.S. Department of
Transportation (DOT), 1200 New Jersey
Avenue SE, Room W12–140, West
Building Ground Floor, Washington, DC
20590–0001.
• Hand Delivery or Courier: Take
comments to Docket Operations in
Room W12–140 of the West Building
Ground Floor at 1200 New Jersey
Avenue SE, Washington, DC, between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
• Fax: Fax comments to Docket
Operations at 202–493–2251.
Privacy: In accordance with 5 U.S.C.
553(c), DOT solicits comments from the
public to better inform its rulemaking
process. DOT posts these comments,
without edit, including any personal
information the commenter provides, to
www.regulations.gov, as described in
the system of records notice (DOT/ALL–
14 FDMS), which can be reviewed at
https://www.dot.gov/privacy.
Docket: Background documents or
comments received may be read at
https://www.regulations.gov at any time.
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]]>Agencies
[Federal Register Volume 88, Number 99 (Tuesday, May 23, 2023)]
[Proposed Rules]
[Pages 32980-32983]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-10817]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-1050; Project Identifier AD-2022-00602-E]
RIN 2120-AA64
Airworthiness Directives; Honeywell International Inc. Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Honeywell International Inc. Model AS907-1-1A and AS907-2-1G
engines. This proposed AD was prompted by reports of compressor surge,
including a dual engine compressor surge, during takeoff climb out
through a steep temperature inversion, causing a loss of engine thrust
control. This proposed AD would require either the replacement of a
certain electronic control unit (ECU) software version installed on
AS907-1-1A engines with updated software or the replacement of certain
ECUs installed on AS907-1-1A engines with ECUs eligible for
installation. This proposed AD would also require the replacement of
certain ECUs installed on AS907-2-1G engines with ECUs eligible for
installation. 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 July 7,
2023.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
[[Page 32981]]
Federal eRulemaking Portal: Go to 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.
AD Docket: You may examine the AD docket at regulations.gov by
searching for and locating Docket No. FAA-2023-1050; 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: Joseph Costa, Aviation Safety
Engineer, West Certification Branch, FAA, 3960 Paramount Boulevard,
Lakewood, CA 90712; phone: (562) 627-5246; 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-2023-1050; Project Identifier
AD-2022-00602-E'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this 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
regulations.gov, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to
Joseph Costa, Aviation Safety Engineer, West Certification Branch, FAA,
3960 Paramount Boulevard, Lakewood, CA 90712. 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 was notified of several reports that Honeywell
International Inc. (Honeywell) Model AS907-1-1A and AS907-2-1G engines
experienced compressor surge, including an AS907-1-1A dual engine
compressor surge, during takeoff climb out through a steep temperature
inversion, which resulted in loss of engine thrust control. The FAA
determined that the installed ECU software version logic locked the
engine inlet total temperature (Tt2) at 60 knots on a takeoff roll and
that reference Tt2 remained locked until the aircraft reached 400 feet
above ground level (AGL) or the pilot moved the throttle before
reaching 400 AGL. The locked Tt2 is mathematically adjusted by the ECU
software for altitude and Mach number changes as the takeoff
progresses. During the climb to 400 feet AGL with a thermal inversion,
the actual engine Tt2 can increase above the Tt2 that is being
calculated by the ECU, which causes the compressor guide vanes' (CGVs)
position to be off-schedule for the actual ambient conditions.
Significant off-scheduling of the CGVs can lead to a compressor surge
event. The compressor surge margin is decreased when scheduling is
based on a colder Tt2 temperature than what the engine is actually
running. Engine deterioration impacts compressor surge margin and can
increase the likelihood of a dual engine compressor surge as the AS907-
1-1A and AS907-2-1G engine fleets age. Dual engine power loss due to a
temperature inversion occurring within 75 feet AGL during takeoff climb
out may cause the loss of thrust control of an airplane. This
condition, if not addressed, could result in reduced controllability of
the airplane, loss of control of the airplane, reduced ability of the
flight crew to maintain the safe flight and landing of the airplane,
and loss of the airplane.
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.
Proposed AD Requirements in this NPRM
This proposed AD would require either the replacement of a certain
ECU software version installed on AS907-1-1A engines with a software
version eligible for installation or the replacement of certain ECUs
installed on AS907-1-1A engines with ECUs eligible for installation.
This proposed AD would also require the replacement of certain ECUs
installed on AS907-2-1G engines with ECUs eligible for installation.
ECUs with P/N 2119576-3001 or P/N 2119576-3002 installed in AS907-2-1G
engines would be eligible for reinstallation on the AS907-2-1G engines
until exceeding the compliance time specified in Table 2 to paragraph
(g)(2) of this AD.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 853 engines installed on airplanes of U.S. registry. The FAA
estimates that 175 engines installed on AS907-2-1G engines will require
replacing two ECUs.
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
----------------------------------------------------------------------------------------------------------------
Replace AS907-2-1G ECUs (2 per engine) 5 work-hours x $85 per $109,044 $109,469 $19,157,075
hour = $425.
----------------------------------------------------------------------------------------------------------------
[[Page 32982]]
For either replacement of the AS907-1-1A ECU software or
replacement of the AS907-1-1A ECUs, depending on the option selected by
the operator to comply with this AD, the FAA estimates the following
costs:
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replace AS907-1-1A ECU software (2 per engine) 5 work-hours x $85 per hour = $0 $425
$425.
Replace AS907-1-1A ECU (per ECU, per engine).. 2 work-hours x $85 per hour = 61,162 61,332
$170.
----------------------------------------------------------------------------------------------------------------
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 operators.
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 this 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 adding the following new airworthiness
directive:
Honeywell International Inc.: Docket No. FAA-2023-1050; Project
Identifier AD-2022-00602-E.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by July 7, 2023.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Honeywell International Inc. (Honeywell)
Model AS907-1-1A and AS907-2-1G engines.
(d) Subject
Joint Aircraft System Component (JASC) Code 7300, Engine Fuel
and Control.
(e) Unsafe Condition
This AD was prompted by reports of compressor surge, including a
dual engine compressor surge, during takeoff climb out through a
steep temperature inversion, which caused a loss of engine thrust
control. The FAA is issuing this AD to prevent loss of engine thrust
control. The unsafe condition, if not addressed, could result in
reduced controllability of the airplane, loss of control of the
airplane, reduced ability of the flight crew to maintain the safe
flight and landing of 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 AS907-1-1A engines with an ECU having part number (P/N)
2119576-1011 and software version AS907_1011 installed, before
exceeding the applicable compliance time in Table 1 to paragraph
(g)(1) of this AD, either replace software version AS907_1001 with a
software version eligible for installation; or replace the ECU with
an ECU eligible for installation. Either the software or ECU must be
replaced for all four ECUs installed in both airplane engines at the
same time.
Note 1 to paragraph (g)(1): Guidance for removing and replacing
the ECU software or removing and replacing the ECU may be found in
Honeywell Service Bulletin (SB) AS907-76-9031, Revision 2, dated May
15, 2022.
Table 1 to Paragraph (g)(1)--Model AS907-1-1A Engines
------------------------------------------------------------------------
Engine operating time since new
(TSN) Compliance time
------------------------------------------------------------------------
Greater than 5,000 hours TSN...... Within 12 months or before exceeding
400 hours time-in-service (TIS),
whichever occurs first after the
effective date of this AD.
3,000 to 5,000 hours TSN.......... Within 18 months or before exceeding
600 hours TIS, whichever occurs
first after the effective date of
this AD.
Fewer than 3,000 hours TSN........ Within 24 months or before exceeding
800 hours TIS, whichever occurs
first after the effective date of
this AD.
------------------------------------------------------------------------
(2) For AS907-2-1G engines with serial numbers (S/N) P130101
through P130240 that have not incorporated Honeywell SB AS907-72-
9063, and for AS907-2-1G engines with S/Ns P130241 through P130336,
and S/Ns P130101 through P130240 that
[[Page 32983]]
have incorporated Honeywell SB AS907-72-9063, before exceeding the
applicable compliance time in Table 2 to paragraph (g)(2) of this
AD, replace any installed ECU having P/N 2119576-3001 or P/N
2119576-3002 with an ECU eligible for installation. All four ECUs
installed in both airplane engines must be replaced at the same
time.
Note 2 to paragraph (g)(2): Guidance for removing and replacing
the ECU may be found in Honeywell SB AS907-76-9014, Revision 6,
dated October 10, 2022.
Note 3 to paragraph (g)(2): Guidance for converting a standard
flow compressor to a high flow compressor for improving surge margin
may be found in Honeywell SB AS907-72-9063, Revision 1, dated July
31, 2019.
Table 2 to Paragraph (g)(2)--Model AS907-2-1G Engines
------------------------------------------------------------------------
Engine type Compliance time
------------------------------------------------------------------------
Standard Flow Compressor AS907-2-1G Within 2 years or before
engines (engine S/Ns P130101 through exceeding 800 hours TIS,
P130240 that have not incorporated whichever occurs first after
Honeywell SB AS907-72-9063). the effective date of this AD.
High Flow Compressor Within 7 years or before
AS907[dash]2[dash]1G engines (engine S/ exceeding 2,800 hours TIS,
Ns P130241 through P130336 and engines whichever occurs first after
that have incorporated Honeywell SB the effective date of this AD.
AS907-72-9063).
------------------------------------------------------------------------
(h) Installation Prohibition
(1) After the effective date of this AD, do not install an ECU
having P/N 2119576-1011 and software version AS907_1001 in any
AS907-1-1A engine.
(2) Do not install an ECU having P/N 2119576-3001 or P/N
2119576-3002 in any AS907-2-1G engine if the ECU has exceeded the
compliance time specified in Table 2 to paragraph (g)(2) of this AD.
(i) Definitions
(1) For the purpose of this AD, for the AS907-1-1A engine, a
``software version eligible for installation'' is a software version
that is not software version AS907_1001.
(2) For the purpose of this AD, for the AS907-1-1A engine, an
``ECU eligible for installation'' is an ECU that does not have P/N
2119576-1011.
(3) For the purpose of this AD, for the AS907-2-1G engine, an
``ECU eligible for installation'' is an ECU that does not have P/N
2119576-3001 or P/N 2119576-3002.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, West Certification 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 branch, send it to the
attention of the person identified in paragraph (k)(1) 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.
(k) Related Information
(1) For more information about this AD, contact Joseph Costa,
Aviation Safety Engineer, West Certification Branch, FAA, 3960
Paramount Boulevard, Lakewood, CA 90712; phone: (562) 627-5246;
email: [email protected].
(2) For service information identified in this AD that is not
incorporated by reference, contact Honeywell International Inc., 111
South 34th Street, Phoenix, AZ 85034; phone: (800) 601-3099;
website: myaerospace.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.
(l) Material Incorporated by Reference
None.
Issued on May 16, 2023.
Michael Linegang,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2023-10817 Filed 5-22-23; 8:45 am]
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