Rule2021-15694
Airworthiness Directives; General Electric Company Turbofan Engines
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
July 23, 2021
Effective
August 27, 2021
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF6-80A and CF6-80C2 model turbofan engines. This AD was prompted by an inspection by the manufacturer that revealed cracking of the high-pressure turbine (HPT) rotor stage 1 disk. This AD requires visual inspection and fluorescent penetrant inspection (FPI) of the HPT thermal shield and, if cracking is detected, removal from service of the HPT thermal shield, HPT rotor stage 1 disk and HPT rotor stage 2 disk. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 86 Issue 139 (Friday, July 23, 2021)</title>
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[Federal Register Volume 86, Number 139 (Friday, July 23, 2021)]
[Rules and Regulations]
[Pages 38912-38914]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2021-15694]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-1179; Project Identifier AD-2020-00818-E;
Amendment 39-21638; AD 2021-14-11]
RIN 2120-AA64
Airworthiness Directives; General Electric Company Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain General Electric Company (GE) CF6-80A and CF6-80C2 model
turbofan engines. This AD was prompted by an inspection by the
manufacturer that revealed cracking of the high-pressure turbine (HPT)
rotor stage 1 disk. This AD requires visual inspection and fluorescent
penetrant inspection (FPI) of the HPT thermal shield and, if cracking
is detected, removal from service of the HPT thermal shield, HPT rotor
stage 1 disk and HPT rotor stage 2 disk. The FAA is issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective August 27, 2021.
ADDRESSES: For service information identified in this final rule,
contact General Electric Company, 1 Neumann Way, Cincinnati, OH 45215;
phone: (513) 552-3272; email: <a href="/cdn-cgi/l/email-protection#f392859a92879a9c9ddd959f969687808683839c8187b39296dd9496dd909c9e"><span class="__cf_email__" data-cfemail="610017080015080e0f4f070d040415121411110e13152100044f06044f020e0c">[email protected]</span></a>; website:
<a href="http://www.ge.com">www.ge.com</a>. You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 1200
District Avenue, Burlington, MA 01803. For information on the
availability of this material at the FAA, call (781) 238-7759. It is
also available at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and
locating Docket No. FAA-2020-1179.
Examining the AD Docket
You may examine the AD docket at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by
searching for and locating Docket No. FAA-2020-1179; or in person at
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket contains this final rule, any
comments received, and other information. The address for Docket
Operations is U.S. Department of Transportation, Docket Operations, M-
30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue
SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Kevin M. Clark, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803;
phone: (781) 238-7088; fax: (781) 238-7199; email:
<a href="/cdn-cgi/l/email-protection#155e70637c7b3b583b567974677e557374743b727a63"><span class="__cf_email__" data-cfemail="eda6889b8483c3a0c3ae818c9f86ad8b8c8cc38a829b">[email protected]</span></a>.
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 General Electric
Company (GE) CF6-80A, CF6-80A1, CF6-80A2, CF6-80A3, CF6-80C2A1, CF6-
80C2A2, CF6-80C2A3, CF6-80C2A5, CF6-80C2A5F, CF6-80C2A8, CF6-80C2B1,
CF6-80C2B1F, CF6-80C2B1F1, CF6-80C2B1F2, CF6-80C2B2, CF6-80C2B2F, CF6-
80C2B3F, CF6-80C2B4, CF6-80C2B4F, CF6-80C2B5F, CF6-80C2B6, CF6-80C2B6F,
CF6-80C2B6FA, CF6-80C2B7F, CF6-80C2B8F, CF6-80C2D1F, CF6-80C2K1F, and
CF6-80C2L1F model turbofan engines. The NPRM published in the Federal
Register on February 22, 2021 (86 FR 10496). The NPRM was prompted by
an inspection by the manufacturer that revealed cracking of the HPT
rotor stage 1 disk caused by increased stress on the HPT rotor stage 1
disk as a result of flange-to-flange cracking on the HPT thermal
shield. In the NPRM, the FAA proposed to require visual inspection and
FPI of the HPT thermal shield and, if cracking is detected, removal
from service of the HPT thermal shield, HPT rotor stage 1 disk and HPT
rotor stage 2 disk. The FAA is issuing this AD to address the unsafe
condition on these products.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from five commenters. The commenters were
Atlas Air, Boeing Commercial Airplanes (Boeing), Delta Air Lines
(Delta), United Airlines (United) and the Air Line Pilots Association,
International (ALPA). The following presents the comments received on
the NPRM and the FAA's response to each comment.
Request To Update Shop Manual
Atlas Air requested that the FAA revise GE CF6-80C2, ESM 72-53-05,
High Pressure Turbine (HPT) Rotor Thermal Shield--Inspection to add the
proposed requirement to remove from service the HPT thermal shield, the
HPT rotor stage 1 disk, and the HPT rotor stage 2 disk from service if
a crack is found, since the thermal shield can be sent to different
vendors outside the engine shop. Delta also suggested that the
technical data within the Engine Shop Manual (ESM) should be updated to
ensure inspection requirements are equivalent across all tasks within
the ESM.
The FAA disagrees. Requiring updates to the ESM is unnecessary to
correct the unsafe condition identified in this AD. The visual and FPI
inspections in the required actions of this AD are the necessary
actions to correct the unsafe condition. Operators, at their
discretion, may work with the original equipment manufacturer to
suggest changes to the ESM to include the inspections required by this
AD.
[[Page 38913]]
Request To Revise References to Engine Manual
Boeing requested that the FAA update reference to the service
information in the Related Service Information section of the NPRM by
referencing Revision 90 of the GE CF6-80A Engine Manual and Revision 91
of the CF6-80C2 Engine Manual. These revisions of the respective
engines manuals include updated procedures regarding HPT rotor Stage 1
and Stage 2 disk serviceability for these model engines with respect to
HPT thermal shield inspection findings.
The FAA agrees and has updated the Related Service Information
section of this AD as suggested by the commenter.
Request To Clarify Inspection Instructions
Delta requested that the FAA clarify that the mandated visual and
FPI inspections should be accomplished in accordance with the engine
manual for the affected engine models.
The FAA disagrees. Operators may use any approved method to perform
the visual and FPI inspections required by this AD.
Request To Clarify Engine Applicability
United requested that the FAA remove CF6-80C2B8F model turbofan
engines from the applicability of this AD. United commented that two
HPT thermal shield configurations exist, part number (P/N) 2787M85P01
and P/N 9315M41P20. Neither of these configurations are applicable to
the R88DT HPT rotor installed on CF6-80C2B8F model turbofan engines.
United requested that if the FAA considers the CF6-80C2B8F turbofan
engine model affected by this AD, then the applicable engine manual
should be updated to reflect the inspections required by this AD.
The FAA agrees. This AD is not applicable to the R88DT HPT rotor
installed on CF6-80C2B8F model turbofan engines because that rotor
configuration does not have an affected thermal shield. The FAA added
the applicable part numbers for HPT thermal shields installed on CF6-
80A and CF6-80C2 model turbofan engines to the applicability paragraph
of this AD.
Support for the NPRM
ALPA supported the NPRM without change.
Conclusion
The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes and any
other changes described previously, this AD is adopted as proposed in
the NPRM. None of the changes will increase the economic burden on any
operator.
Related Service Information
The FAA reviewed ESM 72-53-00 High Pressure Turbine Rotor
Assembly--Disassembly (CF6-80A ESM 72-53-00), dated February 15, 2020
from the GE CF6-80A Engine Manual GEK72501--Rev 90, dated February 15,
2021. CF6-80A ESM 72-53-00 describes procedures for the removal of the
HPT thermal shield, the HPT rotor stage 1 disk, and the HPT rotor stage
2 disk installed on CF6-80A model turbofan engines.
The FAA also reviewed ESM 72-53-00 High Pressure Turbine Rotor
Assembly--Disassembly (CF6-80C2 ESM 72-53-00), dated December 1, 2019
from the GE CF6-80C2 Engine Manual GEK92451--Rev 91, dated December 1,
2020. CF6-80C2 ESM 72-53-00 describes procedures for the removal of the
HPT thermal shield, the HPT rotor stage 1 disk, and the HPT rotor stage
2 disk installed on CF6-80C2 model turbofan engines.
Costs of Compliance
The FAA estimates that this AD affects 1,084 engines installed on
airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Perform FPI and visual inspection of 2 work-hours x $85 per $0 $170 $184,280
HPT thermal shield. hour = $170.
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The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
inspection. The agency has no way of determining the number of aircraft
that might need these replacements.
On-Condition Costs
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Cost per
Action Labor cost Parts cost product
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Replace HPT thermal shield.................... 2 work-hours x $85 per hour = $209,600 $209,770
$170.
Replace HPT rotor stage 1 disk................ 2 work-hours x $85 per hour = 799,700 799,870
$170.
Replace HPT rotor stage 2 disk................ 2 work-hours x $85 per hour = 364,600 364,770
$170.
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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.
[[Page 38914]]
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
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:
2021-14-11 General Electric Company: Amendment 39-21638; Docket No.
FAA-2020-1179; Project Identifier AD-2020-00818-E.
(a) Effective Date
This airworthiness directive (AD) is effective August 27, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to General Electric Company (GE) CF6-80A, CF6-
80A1, CF6-80A2, CF6-80A3, CF6-80C2A1, CF6-80C2A2, CF6-80C2A3, CF6-
80C2A5, CF6-80C2A5F, CF6-80C2A8, CF6-80C2B1, CF6-80C2B1F, CF6-
80C2B1F1, CF6-80C2B1F2, CF6-80C2B2, CF6-80C2B2F, CF6-80C2B3F, CF6-
80C2B4, CF6-80C2B4F, CF6-80C2B5F, CF6-80C2B6, CF6-80C2B6F, CF6-
80C2B6FA, CF6-80C2B7F, CF6-80C2B8F, CF6-80C2D1F, CF6-80C2K1F, and
CF6-80C2L1F model turbofan engines with an installed thermal shield
having one of the following part numbers: 2787M85P01, 9315M41P09,
9315M41P13, 9315M41P14, 9315M41P15, 9315M41P16, 9315M41P20,
9348M13P01, 9367M63P01, 9367M63P02, 9367M63P03, 9367M63P04,
9367M63P05, 9367M63P06, 9367M63P07, or 9315M41P20.
(d) Subject
Joint Aircraft System Component (JASC) Code 7250, Turbine
Section.
(e) Unsafe Condition
This AD was prompted by an inspection by the manufacturer that
revealed cracking of the high-pressure turbine (HPT) rotor stage 1
disk, caused by initial flange-to-flange cracking on the HPT thermal
shield between the HPT rotor stage 1 disk and the HPT rotor stage 2
disk. The FAA is issuing this AD to prevent failure of the HPT rotor
stage 1 disk and the HPT rotor stage 2 disk. The unsafe condition,
if not addressed, could result in uncontained release of the HPT
rotor stage 1 and stage 2 disks, 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) After the effective date of this AD, at every piece-part
exposure of the HPT rotor stage 1 disk, HPT rotor stage 2 disk, or
the HPT thermal shield, perform a visual inspection and a
fluorescent penetrant inspection of the HPT thermal shield.
(2) During any inspection required by paragraph (g)(1) of this
AD, if a crack extending through either the forward or aft flange of
the HPT thermal shield is detected, remove the HPT thermal shield,
the HPT rotor stage 1 disk, and the HPT rotor stage 2 disk from
service.
(h) Installation Prohibition
Do not install onto any engine an HPT rotor stage 1 disk or HPT
rotor stage 2 disk that was removed from service due to the
requirements of paragraph (g)(2) of this AD.
(i) Definition
For the purpose of this AD, ``piece-part exposure'' is when the
HPT rotor stage 1 disk, HPT rotor stage 2 disk, or HPT thermal
shield is separated from their mating rotor parts within the HPT
rotor module.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, ECO Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
ECO Branch, send it to the attention of the person identified in
Related Information. You may email your request to: <a href="/cdn-cgi/l/email-protection#1958575c34585d345854565a597f7878377e766f"><span class="__cf_email__" data-cfemail="f7b6b9b2dab6b3dab6bab8b4b7919696d9909881">[email protected]</span></a>.
(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
For more information about this AD, contact Kevin M. Clark,
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: (781) 238-7088; fax: (781) 238-7199;
email: <a href="/cdn-cgi/l/email-protection#074c62716e69294a29446b66756c4761666629606871"><span class="__cf_email__" data-cfemail="6b200e1d020545264528070a19002b0d0a0a450c041d">[email protected]</span></a>.
(l) Material Incorporated by Reference
None.
Issued on June 25, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-15694 Filed 7-22-21; 8:45 am]
BILLING CODE 4910-13-P
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