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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-0465; Project Identifier AD-2024-00139-E,R;
Amendment 39-22702; AD 2024-05-51]
RIN 2120-AA64
Airworthiness Directives; General Electric Company Engines, and
Various Restricted Category Rotorcraft
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD)
for
certain General Electric Company (GE) Model CT7-2E1, CT7-2F1, CT7-8A,
CT7-8E, CT7-8F5 engines, and various restricted category helicopters
with GE Model T700-GE-700,-701A, -701C, -701D/CC, -701D, -401, -401C,
CT7-2D or CT7-2D1 engines installed. This AD was prompted by at least
four reports of failures of the torque reference tube magnetic insert
braze joint of the power turbine drive shaft assembly within the last
several months. This AD requires a phase array ultrasonic inspection of
the torque reference tube magnetic insert braze joint of the power
turbine drive shaft assembly for inadequate braze coverage, and repair
or replacement of the power turbine drive shaft assembly if necessary.
The FAA previously sent an emergency AD to all known U.S. owners and
operators of these engines and helicopters and is now issuing this AD
to address the unsafe condition on these products.
DATES: This AD is effective April 1, 2024. Emergency AD 2024-05-51,
issued on February 28, 2024, which contained the requirements of this
amendment, was effective with actual notice.
The Director of the Federal Register approved the incorporation by
reference of certain publications identified in this AD as of April 1,
2024.
The FAA must receive comments on this AD by April 29, 2024.
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 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 under
Docket No. FAA-2024-0465; 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 street address for Docket Operations is listed above.
Material Incorporated by Reference:
For service information that is incorporated by reference,
contact General Electric Company, 1 Neumann Way, Cincinnati, OH 45215;
phone: (513) 552-3272; email: aviation.fleetsupport@ge.com; website:
ge.com.
You may view this service information that is incorporated
by reference 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-
2024-0465.
FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone:
(781) 238-7146; email: barbara.caufield@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written data, views, or arguments
about this final rule. Send your comments to an address listed under
ADDRESSES. Include ``Docket No. FAA-2024-0465; Project Identifier AD-
2024-00139-E,R'' at the beginning of your comments. The most helpful
comments reference a specific portion of the final rule, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this final rule because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
regulations.gov, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this final rule.
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 AD 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 AD, 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 AD. Submissions containing CBI should be sent to Barbara
Caufield, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des
Moines, WA 98198. Any commentary that the FAA receives which is not
specifically designated as CBI will be placed in the public docket for
this rulemaking.
Background
On February 28, 2024, the FAA issued Emergency AD 2024-05-51 (also
referred to as the emergency AD), which applies to certain GE Model
CT7-2E1, CT7-2F1, CT7-8A, CT7-8E, CT7-8F5 engines, and various
restricted category helicopters with GE Model T700-GE-700, -701A, -
701C, -701D/CC, -701D, -401, -401C, CT7-2D or CT7-2D1 engines
installed. The emergency AD requires a phase array ultrasonic
inspection of the torque reference tube magnetic insert braze joint of
the power turbine drive shaft assembly for inadequate braze coverage,
and repair or replacement of the power turbine drive shaft assembly if
necessary. The FAA sent the emergency AD to all known U.S. owners and
operators of these engines and helicopters. This action was prompted by
at least four reports of failures of the torque reference tube magnetic
insert braze joint of the power turbine drive shaft assembly within the
last several months. This condition, if not addressed, could result in
improper torque and engine speed indications, which in combination with
specific phases of flight, could create an unacceptably high flight
crew workload in maintaining control of the aircraft, and result in
consequent loss of control of the aircraft.
FAA's Determination
The FAA is issuing this AD because the agency evaluated all the
relevant information and determined the unsafe condition described
previously is likely to exist or develop in other products of the same
type design.
Related Service Information Under 1 CFR Part 51
The FAA reviewed GE Alert Service Bulletin (ASB) CT7-2E1 S/B 72-
A0034, dated February 26, 2024, and GE ASB CT7-8 S/B 72-A0118, Revision
01, dated February 26, 2024, which, among other actions, specify
procedures for a phase array ultrasonic inspection of the torque
reference tube magnetic insert braze joint of the power turbine drive
shaft assembly for inadequate braze coverage. This service information
also specifies repair or replacement of the power turbine drive shaft
assembly if necessary. These documents are distinct since they apply to
different engine models.
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 the ADDRESSES section.
Other Related Service Information
Since issuance of the emergency AD, Sikorsky Aircraft Corporation
issued ASB 70-04-17, dated February 28, 2024. For the engines installed
on restricted category helicopters, this ASB specifies procedures for
a
phase array ultrasonic inspection of the torque reference tube magnetic
insert braze joint of the power turbine drive shaft assembly for
inadequate braze coverage.
AD Requirements
This AD requires a phase array ultrasonic inspection of the torque
reference tube magnetic insert braze joint of the power turbine drive
shaft assembly for inadequate braze coverage, and repair or replacement
of the power turbine drive shaft assembly if necessary.
Interim Action
The FAA considers this AD to be an interim action. The manufacturer
is currently investigating the root cause of the unsafe condition
identified in this AD. If final action is later identified, the FAA
might consider further rulemaking.
Justification for Immediate Adoption and Determination of the Effective
Date
Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and
comment procedures for rules when the agency, for ``good cause,'' finds
that those procedures are ``impracticable, unnecessary, or contrary to
the public interest.'' Under this section, an agency, upon finding good
cause, may issue a final rule without providing notice and seeking
comment prior to issuance. Further, section 553(d) of the APA
authorizes agencies to make rules effective in less than thirty days,
upon a finding of good cause.
An unsafe condition exists that required the immediate adoption of
Emergency AD 2024-05-51, issued on February 28, 2024, to all known U.S.
owners and operators of these engines and helicopters. The FAA found
that the risk to the flying public justified waiving notice and comment
prior to adoption of this rule because failure of the torque reference
tube magnetic insert braze joint of the power turbine drive shaft
assembly could result in improper torque and engine speed indications,
which in combination with specific phases of flight, could create an
unacceptably high flight crew workload in maintaining control of the
aircraft, and result in consequent loss of control of the aircraft.
Since this condition happens rapidly and without warning, the
inspection and any necessary repair or replacement must be accomplished
before further flight. Thus, the FAA has determined that the affected
torque reference tube magnetic insert braze joint of the power turbine
drive shaft assembly must be inspected, and repaired or replaced if
necessary, before further flight. These conditions still exist,
therefore, notice and opportunity for prior public comment are
impracticable and contrary to the public interest pursuant to 5 U.S.C.
553(b)(3)(B).
In addition, the FAA finds that good cause exists pursuant to 5
U.S.C. 553(d) for making this amendment effective in less than 30 days,
for the same reasons the FAA found good cause to forego notice and comment.
Regulatory Flexibility Act
The requirements of the Regulatory Flexibility Act (RFA) do not
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt
a rule without prior notice and comment. Because FAA has determined
that it has good cause to adopt this rule without prior notice and
comment, RFA analysis is not required.
Costs of Compliance
The FAA estimates that this AD affects 100 engines installed on
aircraft of U.S. registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
|
Action
|
Labor cost
|
Parts cost
|
Cost per
product
|
Cost on
U.S. operators
|
| Phase array ultrasonic inspection |
1 work-hours x $85 per hour =
$85 |
$0
|
$85
|
$8,500
|
The FAA estimates the following costs
to do any necessary repairs
or replacements that would be required based on the results of the
inspection. The agency has no way of determining the number of engines
that might need these repairs or replacements:
On-Condition Costs
|
Action
|
Labor cost
|
Parts cost
|
Cost per
product
|
| Repair or replacement of the
power turbine drive
shaft assembly |
8 work-hours x $85 per hour =
$680 |
$50,000
|
$50,680
|
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
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
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]
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
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